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BK117 D-2 (HELIONIX STEP 2)
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APPROVED ROTORCRAFT FLIGHT MANUAL
BK117 D-2 (HELIONIX STEP 2)
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Valid for model:
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Registration mark:
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Serial No.:
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Year of manufacture:
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IT IS THE OPERATOR’S RESPONSIBILITY TO MAINTAIN THIS MANUAL IN A CURRENT STATUS IN ACCORDANCE WITH THE LIST OF EFFECTIVE PAGES. This manual includes the material to be furnished to the pilot as required by CS/FAR-29.
THIS MANUAL MUST BE CARRIED IN THE HELICOPTER AT ALL TIMES. Original Issue - DEC 11, 2015 Approved by EASA:
Published by:
EASA approval no. 10055971
AIRBUS HELICOPTERS DEUTSCHLAND GmbH
Rev. 0
TITLE
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK117 D-2 (HELIONIX STEP 2)
APPROVING AUTHORITIES
APPROVING AUTHORITIES
EUROPEAN AVIATION SAFETY AGENCY (EASA) Revisions to this flight manual beginning with Revision No. 0 are approved by EASA based on Regulation (EC) No. No. 216/2008 of the European Parliament and of the Council of 15 July 2002. FEDERAL AVIATION ADMINISTRATION (FAA)
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for U.S. registered BK 117 D–2 helicopters in accordance with the provisions of 14 CFR Section § 21.29 on March 20, 2017. The Manual is required by FAA Type Certificate Data Sheet No. H13EU.
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ADMINISTRACIÓN NACIONAL DE AVIACIÓN CIVIL (ANAC):
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This Rotorcraft Flight Manual applicable for BK117 D–2 helicopters is approved by the ”Administración Nacional de Aviación Civil (ANAC)”, for Argentinean registered helicopters, in accordance with Section 21.29 of RAAC 21.
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This ANAC approved RFM supplemented by Appendix 11–16 is required by ANAC Type Certificate Data Sheet N_ HE–9504 last revision.
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Later revisions and supplements of this Flight Manual that have been approved by EASA, are considered as ANAC approved.
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AGÊNCIA NACIONAL DE AVIAÇÃO CIVIL (ANAC):
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This Rotorcraft Flight Manual is approved by EASA on behalf of the ”Agência Nacional de Aviação Civil” for Brazilian registered rotorcraft, in accordance with the ”Regulamentos Brasileiros da Aviação Civil (RBAC) 21, Section 21.29.
APPROVING AUTHORITIES
Rev. 16.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK117 D-2 (HELIONIX STEP 2) MANUAL CONTENTS
LIMITATIONS
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EMERGENCY PROCEDURES
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MANUAL CONTENTS
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DESCRIPTION OF SYSTEMS
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MBR
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MASS AND BALANCE (EQUIPMENTLIST/MASSANDBALANCERECORD)
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PERFORMANCE DATA (APPROVED PART / NON-APPROVED PART)
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HANDLING, SERVICING, MAINTENANCE
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OPERATIONAL TIPS
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APPENDIX
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FLIGHT MANUAL SUPPLEMENTS (SPECIAL OPERATIONS / OPTIONAL EQUIPMENT)
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MANUAL CONTENTS - 1/( - 2 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK117 D-2 (HELIONIX STEP 2) LOG OF REVISIONS
LOG OF REVISIONS FIRST ISSUE DEC 11, 2015 REVISION 6.2
MAY 08, 2017
REVISION 6.3
JUN 01, 2017
REVISION 1 EASA approval no.: 10057320
MAR 21, 2016 REVISION 6.4
JUL 28, 2017
REVISION 2 EASA approval no.: 10057989
MAY 11, 2016 REVISION 6.5
REVISION 2.1
MAY 19, 2016
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ORIGINAL EASA approval no.: 10055971
REVISION 6.7
JUL 04, 2016
REVISION 4 EASA approval no.: 10059564
SEP 28, 2016
REVISION 4.1
OCT 06, 2016 REVISION 7.1
REVISION 4.2
OCT 13, 2016
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SEP 21, 2017 OCT 19, 2017 OCT 27, 2017
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REVISION 6.8
JUL 31, 2017
NOV 10, 2017
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REVISION 7 EASA approval no.: 10063687
DEC 14, 2017
REVISION 9 DEC 14, 2016 EASA approval no.: 10064108
DEC 28, 2017
DEC 22, 2016 REVISION 9.1
JAN 26, 2018
FEB23, 2017 REVISION 9.2
MAR 05, 2018
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NOV 09, 2016
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NOV 27, 2017
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REVISION 6 MAR 20, 2017 REVISION 10 EASA approval no.: 10061343 and 10061344 EASA approval no.: 10065411
MAY 02, 2018
REVISION 6.1
MAY 07, 2018
APR 26, 2017 REVISION 11 EASA approval no.: 10065454
CONTINUED
APPROVED Rev. 11.1
LOR - 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK117 D-2 (HELIONIX STEP 2) LOG OF REVISIONS
LOG OF REVISIONS (CONTINUED) REVISION 11.1
MAY 28, 2018 REVISION 17 EASA approval no.: 10071105
REVISION 11.2
JUN 01, 2018
SEP 30, 2019
OCT 01, 2019
REVISION 11.3
JUN 08, 2018 OCT 02, 2019
REVISION 11.4
REVISION 18 SEP 10, 2018 EASA approval no.: 10071124
REVISION 11.5
OCT 05, 2018 REVISION 18.1
OCT 23, 2019
REVISION 12 EASA approval no.: 10067611
NOV 22, 2018 REVISION 19 EASA approval no.: 10071268
REVISION 12.1
NOV 14, 2019 DEC 04, 2018 REVISION 20 EASA approval no.: 10071610 Rev. 1
REVISION 13 EASA approval no.: 10067883
DEC 07, 2018
REVISION 14 EASA approval no.: 10067884
DEC 07, 2018
REVISION 15 EASA approval no.: 10067961
DEC 12, 2018 REVISION 21.2
FEB 13, 2020
REVISION 21.3
APR 02, 2020
REVISION 22 APR 09, 2019 EASA approval no.: 10073067
APR 21, 2020
OCT 17, 2019
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DEC 13, 2018
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REVISION 17.1
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MAY 06, 2019 REVISION 22.1
(see entry below)
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REVISION 16 EASA approval no.: 10069781 REVISION 16.1
MAY 20, 2019
REVISION 16.2
SEP 20, 2019
REVISION 22.1 Date: JUN 02, 2020 Approved under authority of the DOA ref. EASA.21J.700.
LOR - 2
APPROVED Rev. 22.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK117 D-2 (HELIONIX STEP 2) RECORD OF REVISIONS
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Rev. No.
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BK117 D-2 (HELIONIX STEP 2) LIST OF EFFECTIVE PAGES
LIST OF EFFECTIVE PAGES − APPROVED (PART 1) N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA ref. EASA.21J.700, “DOA”.
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LIST OF EFFECTIVE PAGES − MANUFACTURER‘S DATA (PART 2)
N, R, or D indicate pages which are new, revised or deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the record of revisions as necessary.
LEP 8
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APPROVED MANUFACTURER’S DATA Rev. 22.1
O N
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Form EL-1 Form EL-2 Form EL-3 Form EL-4 Form MBR-1-long. Form MBR-2-long. Form MBR-3-long. Form MBR-4-long. Form MBR-1-lat. Form MBR-2-lat. Form MBR-3-lat. Form MBR-4-lat.
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17 17 17 18.1
7-2−12 7-3−1 7-3−2
22 0 0
7-3−3 7-3−4 7-3−5
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11.2 15.2 15.2 15.2
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9 9 9 9
APPROVED MANUFACTURER’S DATA Rev. 22.1
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9 9 9
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9 9 9
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9 9 9 9
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9 9 9 9
7-13−34 7-13−35 7-13−36 7-13−37
9 9 9 9
7-13−73 7-13−74 7-13−75 7-13−76
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MANUFACTURER’S DATA APPROVED Rev. 22.1
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7-15−6
0 11.1 Before MR1/SB
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7-17−3
0
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9 9 9 9
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7-18−1
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APPROVED MANUFACTURER’S DATA Rev. 22.1
9 9 9
7-18−11 7-18−12 7-18−13 7-18−14
9 9 9 9
7-18−15 7-18−16 7-18−17 7-18−18
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Before MR1
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9 9 9 9
Before MR1 Before MR1 Before MR1 Before MR1
7-19−6 7-19−1 7-19−2 7-19−3
9 9 9 9
Before MR1 After MR1 After MR1 After MR1
7-19−4 7-19−5 7-19−6
9 9 9.2
After MR1 After MR1 After MR1
7-19−7 7-19−8 7-19−9 7-19−10
9.2 9.2 9.2 9.2
After MR1 After MR1 After MR1 After MR1
7-19−11 7-19−12 7-20−1
9.2 9.2 6.6
After MR1 After MR1
N
7-18−19 7-18−20 7-19−1
PY O C
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0
O N
7-17−2
O N
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7-17−1
7-18−8 7-18−9 7-18−10
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12.1
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− Appendices − STC’s
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Inserted
Date Approved
Removed
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Initials
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Inserted
Date Approved
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Record of installed software versions and of performed SBs and ASBs
SOFTWARE – RECORD OF INSTALLED VERSIONS This Flight Manual applies to all the BK117 D-2 helicopter model variants listed on the title page. Certain portions of the manual, however, may apply to only specific software versions of the installed equipment. Therefore, the record given below should be used to indicate the applicable versions of this Software to the pilot. Updates of this Software-record are the responsibility of the H/C operator.
ED
This Record shall be inserted in the Flight Manual BK117 D-2 of the helicopter with the below listed serial number:
N TR
O
LL
S/N ____________/ Registration____________ Installed Software version
Engines installed
TURBOMECA ARRIEL 2E
Date
Signature
N
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EQUIPMENT
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ROIV
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BK 117 D-2 (HELIONIX STEP 2)
Record of installed software versions and of performed SBs and ASBs
Equipment
Date
Signature
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Installed Software version
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL
BK 117 D-2 (HELIONIX STEP 2)
Record of installed software versions and of performed SBs and ASBs
RECORD OF SERVICE– UND ALERT SERVICE BULLETINS The record given below should be used to indicate the performed SB’s and ASB’s. Date
Signature
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Number and Titel of the SB/ASB
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BK 117 D-2 (HELIONIX STEP 2)
Record of installed software versions and of performed SBs and ASBs
Date
Signature
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Number and Titel of the SB/ASB
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BK117 D-2 (HELIONIX STEP 2) RECORD OF OIL TYPES
OIL – RECORD OF OIL TYPES This Flight Manual applies to all the BK117 D-2 helicopter model variants listed on the title page. To avoid mixing different oil types the record given below should be used to indicate the applicable oil types to the pilot. Updates of this oil types-record are the responsibility of the H/C operator. This Record shall be inserted in the Flight Manual BK117 D-2 of the helicopter with the below listed serial number:
Viscosity
Date
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Oil type
Signature
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S/N ____________/ Registration____________
ROOT - 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL
BK117 D-2 (HELIONIX STEP 2)
RECORD OF OIL TYPES
Oil type
Viscosity
Date
Signature
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Component
ROOT - 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
SECTION 1 GENERAL TABLE OF CONTENTS
Page INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1.2
ORGANIZATION OF THE MANUAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1.2.1
Approved and non-approved data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–1
1.2.2
Description of the sections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–1
1.2.3
Page numbering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–3
1.2.4
Flight manual supplements (FMS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–3
1.2.5
Flight manual appendices (FMA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–3
1.3
EFFECTIVITY STATEMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–4
1.3.1
Definition of effectivity indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–4
1.3.2
Method of indicating effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–4
1.3.3
Incorporating pages having entire page effectivity statements . . . . . . . . . .
1–5
1.4
REVISION SERVICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–5
1.4.1
Revisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–5
1.4.2
Temporary revisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–5
1.4.3
Revisions of supplements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–5
1.4.4
Procedure for minor changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–5
1.4.5
Identifying revised material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–6
1.4.6
Page approval status . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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CONVERSION CHARTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1–1 1–1
1–6 1–7
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1.1
WIND COMPONENT CHART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 – 14 NOISE LEVELS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 – 15
1.8
TERMINOLOGY AND DEFINITIONS OF TERMS . . . . . . . . . . . . . . . . . . . . . 1 – 16
1.8.1
Warnings, Cautions and Notes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 – 16
1.8.2
Use of procedural terms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 – 16
1.9
ABBREVIATIONS AND SYMBOLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 – 17
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1.7
APPROVED Rev. 9
1–i
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
LIST OF FIGURES Page Conversion chart: Celsius (°C) – Fahrenheit (°F) . . . . . . . . . . . . . . . . . . . . .
1–7
Fig. 1-2
Conversion chart: kilometers/hour (km/h) – knots (kt) . . . . . . . . . . . . . . . . .
1–8
Fig. 1-3
Conversion chart: meters/second (m/s) – feet/minute (ft/min) . . . . . . . . . .
1–9
Fig. 1-4
Conversion chart: kilograms (kg) – pounds (lb) . . . . . . . . . . . . . . . . . . . . . . 1 – 10
Fig. 1-5
Conversion chart: liters (l) – US gallons (US gal) – imp. gallons (imp. gal) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 – 11
Fig. 1-6
Conversion chart: hectopascals (hPa) – inches of mercury (in. Hg) . . . . . 1 – 12
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Fig. 1-7 Wind component chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 – 14
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Tab. 1-1 Standard atmosphere . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 – 13
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Tab. 1-2 Noise levels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 – 15
1 – ii
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
SECTION 1 GENERAL
1.1
INTRODUCTION
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This flight manual contains the information necessary for safe and efficient operation of the BK117 D-2 and subsequent helicopter. To achieve the required degree of safety, this manual must be used in conjunction with the relevant regulations covering aircraft operation, such as aerial navigation laws, in the operators country. It is essential for the crew to become familiar with the contents of this manual, special certification requirements and any information specific to customized configurations, and to check all revisions and related requirements.
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ORGANIZATION OF THE MANUAL
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Approved and non-approved data
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The approved part of this manual meets all certificating authority requirements for approved data.
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Description of the sections
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Approved part: SECTION 1
GENERAL – approved data – presents information of general interest to the pilot, a description of the manual and conversion tables. In addition, it provides definitions and explanation of symbols, abbreviations, and terminology used in the manual.
SECTION 2
LIMITATIONS – approved data – contains those limitations required by regulation or necessary for safe operation of the helicopter and approved by the regulatory authority.
SECTION 3
EMERGENCY AND MALFUNCTION PROCEDURES – approved data – contains the recommended procedures for dealing with various types of emergencies, malfunctions or critical situations.
APPROVED Rev. 6.1
1–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
NORMAL PROCEDURES – approved data – contains the recommended procedures for normal ground and air operation of the helicopter.
SECTION 5
PERFORMANCE DATA – approved and non approved data – contains airworthiness and performance information necessary for preflight and inflight mission planning. Subsection 5.1 contains approved data. Subsection 5.2 contains non-approved data supplied by the aircraft manufacturer.
SECTION 6
MASS AND BALANCE – non approved data – contains the definitions for various mass and balance locations and the procedure for the determination of the center of gravity. Appended to this section are the mass and balance record form for maintaining a continuous record of changes in structure and equipment affecting the mass and balance, and the equipment list form for the listing of optional equipment with data necessary for mass and balance computations.
SECTION 7
SYSTEMS DESCRIPTION – non approved data – contains a brief description of the helicopter, its systems and the various standard equipment with information considered most important to the flight crew.
SECTION 8
HANDLING, SERVICE, MAINTENANCE – non approved data – contains servicing data, cleaning and care procedures as well as information for ground handling.
SECTION 9
FLIGHT MANUAL SUPPLEMENTS – approved and non approved data – Subsection 9.0 contains an equipment compatibility matrix and additional performance data. Subsection 9.1 contains Flight Manual Supplements (FMS) with instructions for special operations (e.g. Category A, etc.). Subsection 9.2 contains Flight Manual Supplements (FMS) providing operating instructions of approved optional equipment.
1–2
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SECTION 4
SECTION 10
OPERATIONAL TIPS – non approved data – contains general information and indications for an efficient operation of the helicopter bearing in mind environmental aspects (e.g. “minimum noise” procedures, etc.).
SECTION 11
APPENDIX – approved and non approved data – contains Flight Manual Appendices (FMA) for optional equipment and special operations.
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
1.2.3
Page numbering The numbering of pages within each section consists of the section number or designation, a dash and the consecutive number of the page beginning with “1”; e.g. for section 3: 3-1, 3-2, etc. Figures are likewise numbered consecutively by section, such as Fig. 3-1, Fig. 3-2, etc. Exceptions: – The numbering of the table of contents pages preceding each section in this manual consists of the section number, a dash and the consecutive roman numeral (lower case) of the page, beginning with ”i”; e.g. for section 3: 3-i, 3-ii, etc.
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Flight manual supplements (FMS)
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The manufacturer retains the right to convert optional equipment to standard equipment at any time as a product improvement program. FLM coverage of the converted optional equipment, however, will remain as an FMS in Section 9 and also as an optional equipment item entry in the equipment list. An entry in the STD EQPT EFFECTIVITY column of the log of supplements is used to indicate the converted optional equipment by providing an effectivity statement of the affected helicopters. FMS’s of non-installed optional equipment and FMS’s of non-unintended special operations, need not to be carried in the helicopter. These FMS’s can be filed in the binder “EXTRANEOUS FLIGHT MANUAL SUPPLEMENTS”.
1.2.5
Flight manual appendices (FMA) Each FMA is self-contained and corresponds in its general arrangement to the basic flight manual, but only additional information or different data will be the subject of a FMA.
APPROVED Rev. 0
1–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
Each FMA, although complete in nature, shall therefore be used in conjunction with the approved flight manual. When two or more appendices are issued, a log of appendices will be provided as an index listing the current appendices. 1.3
EFFECTIVITY STATEMENTS
1.3.1
Definition of effectivity indications
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The contents of this manual applies to all the BK 117 D-2 helicopter model variants listed on the title page and defined in this section. However, certain portions of the manual may apply to only specific models, variants and/or serial numbers. Therefore, an effectivity identification system is used to indicate where differences brought about by helicopter modifications, configurations, service bulletins, customer options, variations of the basic model helicopter, etc. occur within the manual.
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This system comprises effectivity statements, identified by the word EFFECTIVITY followed by the definition of applicability. The applicability may be defined using:
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– a service bulletin (SB) modification number, and/or
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– a clear text definition.
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The ten-digit numeric indicator begins with the five digits of the lowest assigned manufacturer ’s serial number, to indicate first effectivity, and ends with the five digits of the highest assigned manufacturer’s serial number, to indicate last effectivity, of an unbroken sequence of assigned serial numbered helicopters. A hyphen is shown between the two numbers. Open ended effectivity is indicated by “99999” in the last effectivity, e.g. 20415-99999 indicates helicopter serial number S-20415 and subsequent.
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Method of indicating effectivity
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The amount of manual coverage required by the differences brought about by model, variants or modification differences (effectivity) varies from small or minor (portions of text) to extensive (entire pages). Therefore, the effectivity statements may apply to portions of a page or an entire page. Effectivity statements applying to portions of a page immediately preceed and are located in the extreme left hand margin directly above the text to which they relate. When the defined applicability ends, an effectivity statement defined as “ALL” is used to mean that the information following applies again to all models, variants, etc. as listed on the FLM title page or, when applicable, as defined by the page effectivity statement. Effectivity statements applying to the entire page content will be located at the bottom of the page adjacent to the page number. Therefore, pages that are applicable to the basic series helicopter will not have an effectivity statement at the bottom of the page.
1–4
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
1.3.3
Incorporating pages having entire page effectivity statements Compare the effectivity statements of those pages having identical page numbers and determine which page(s) applies to your helicopter (front and back page, if necessary). Insert that page(s) in the FLM binder. Discard the page(s) which does not apply. Do not discard pages having a page effectivity statement “After SB......” that at present may not apply to the helicopter unless however, it is absolutely certain that the stated service bulletin will never be incorporated.
NOTE
1.4
REVISION SERVICE This manual is kept up-to-date by revisions and temporary revisions. Revisions
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1.4.1
Temporary revisions
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1.4.2
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Temporary revisions provid information between revisions. They are printed on yellow paper and are accompanied by a “change instructions” sheet and an updated “list of effective temporary revisions” page.
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Revisions of supplements
–
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Procedure for minor changes in the Flight Manual
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In the event of minor changes according to DOA No. EASA.21J.700 and changes on “manufacturer‘s data” pages, AIRBUS HELICOPTERS is authorized by EASA to release a revision which needs not to be certified by the authorities. In this case the procedures for a normal revision apply, except of the revision number mentioned on the LEP and on the bottom of each page which follows the rules stated below: Example: Basic Flight Manual, last revision was Rev. 4, afterwards on page 4 a typing error was found and has been corrected. The revision for the minor change is numbered with the next subsequent revision number (here 4.1), which has to be included on the respective page and on the LEP. The next “normal” revision, approved by EASA (with a corresponding approval number), will be Rev. 5. Page
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APPROVED Rev. 9
Approved by
Rev. No.
2-1
EASA
4
2-2
EASA
2-3 2-4
Remarks
Page
Approved by
Rev. No.
2-33
EASA
0
4
2-34
EASA
0
EASA
3
2-35
EASA
4
DOA
4.1
2-36
EASA
4
Remarks
1–5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
1.4.5
Identifying revised material Changes (except as noted below) to the text and tables (including new material on added pages) are indicated by a vertical line in the outer margin. Change symbols will not be shown for: – introductory material. – blank space resulting from the deletion of text, or an illustration or a part of an illustration, or table.
ED
– correction of minor inaccuracies, such as spelling, punctuation, relocation of material, etc., unless such correction changes the meaning of instructive information and procedures.
Page approval status
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ÓÓÓÓ ÓÓÓÓ ÓÓÓÓ
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Changes to illustrations (except diagrams and schematics) may be indicated by a miniature pointing hand. A vertical line next to changed text and callouts on illustrations may be used in lieu of a pointing hand. Shading and screening are used for diagrams and schematics to highlight the area containing the changed information. Extensively changed presentations may be indicated by a screen border around the affected area.
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1–6
APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
1.5
CONVERSION CHARTS For conversion of most important units within the FLM use the charts Fig.1-1 thru Fig.1-6 and the standard atmosphere table (Table 1-1) on the following pages.
CELSIUS – FAHRENHEIT
ǒǓ
°F + 9 5
ǒǓ
°C + 5 9
°C ) 32 + 1.8(°C)17.8) 845 _C = 1553 _F
225 _F = 107 _C
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Examples:
(°F*32)
DEGREES CELSIUS ( _C )
Fig. 1-1 APPROVED Rev. 0
Conversion chart: Celsius (_C) – Fahrenheit (_F)
1–7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
KILOMETERS PER HOUR – KNOTS
1kmh + 0.54kts
266 KM/H = 143.6 KTS
42 KTS = 78 KM/H
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EXAMPLES:
1kt + 1.853kmh
KILOMETER PER HOUR (km/h)
Fig. 1-2
1–8
Conversion chart: kilometers/hour (km/h) – knots (kts) APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
METERS / SECOND – FEET / MINUTE
1ms + 196.85ftmin 4.7 M/S = 925.2 FT/MIN
3447 FT/MIN = 17.5 M/S
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EXAMPLES:
100ftmin + 0.508ms
FEET PER MINUTE (ft/min)
Fig. 1-3
APPROVED Rev. 0
Conversion chart: meters/second (m/s) – feet/minute (ft/min)
1–9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
KILOGRAMS – POUNDS
1kg + 2.205lb 540 KG = 1190.7 LB
5821 LB = 2643 KG
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EXAMPLES:
1lb + 0.454kg
POUNDS (lb)
Fig. 1-4
1 – 10
Conversion chart: kilograms (kg) – pounds (lb)
APPROVED Rev. 0
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LITERS – U.S. GALLONS – IMP. GALLONS
1U.S.gal + 3.786l 1l + 0.264U.S.gal EXAMPLES:
1imp.gal + 4.544l 1l + 0.220imp.gal
320 L = 84.5 U.S. GAL
OR:
320 L = 70.4 IMP. GAL
BRITISH IMPERIAL GALLONS (Imp. gal)
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IN
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–
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U.S. GALLONS (U.S. gal)
PY
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ED
70.4 IMP. GAL = 84.5 U.S. GAL
LITERS (l)
Fig. 1-5
APPROVED Rev. 0
Conversion chart: liters (l) – US gallons (US gal) – imp. gallons (imp. gal)
1 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
HECTOPASCALS – INCHES OF MERCURY
1hPa(mbar) + 0.02953in.Hg
1007.5 HPA = 29.75 IN. HG
30.96 IN. HG = 1048.4 HPA (MBAR)
O N PY O C – LY O N O N TI C U R ST IN FO
R
HECTOPASCALS - MILLIBARS (hPa - mbar)
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EXAMPLES:
1in.Hg + 33.865hPa(mbar)
INCHES OF MERCURY (in. Hg)
Fig. 1-6
1 – 12
Conversion chart: Hectopascals (hPa) – Inches of Mercury (in. Hg)
APPROVED Rev. 0
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STANDARD ATMOSPHERE TABLE Standard sea level conditions: Temperature: 15 _C (59 _F) Pressure:
1013.25 hPa / mbar (29.921 inches Hg.)
Density:
1.225 kg/m3 (0.0023769 slugs/cu.ft.) DENSITY RATIO
Ǹs
TEMPERATURE (_C) (_F)
PRESSURE
PRESSURE
PRESSURE
(hPa/mbar)
ED
1/
RATIO
29.921
1.0000
N TR
ALTITUDE
977.18
28.856
0.9644
942.14
27.821
0.9298
908.14
26.817
0.8962
44.735
875.12
25.842
0.8637
41.169
843.08
24.896
0.8320
37.603
811.99
23.978
0.8014
1.132
34.037
781.86
23.088
0.7716
1.1279
-0.850
30.471
752.63
22.225
0.7428
0.7620
1.1456
-2.831
26.905
724.29
21.388
0.7148
10000
0.7385
1.1637
-4.812
23.338
696.82
20.577
0.6877
11000
0.7155
1.1822
-6.793
19.772
670.21
19.791
0.6614
12000
0.6932
1.2011
-8.774
16.206
644.40
19.029
0.6360
13000
0.6713
1.2205
-10.756
12.640
619.44
18.292
0.6113
14000
0.6500
1.2403
-12.737
9.074
595.23
17.577
0.5875
15000
0.6292
1.2606
-14.718
5.508
571.83
16.886
0.5643
16000
0.6090
1.2815
-16.699
1.941
549.14
16.216
0.5420
0.5892
1.3028
-18.680
-1.625
527.23
15.569
0.5203
18000
0.5699
1.3246
-20.662
-5.191
505.99
14.942
0.4994
19000
0.5511
1.3470
-22.643
-8.757
485.48
14.336
0.4791
20000
0.5328
1.3700
-24.624
-12.323
465.63
13.750
0.4595
s 1.0000
1.0000
15.000
59.000
1013.25
1000
0.9711
1.0148
13.019
55.434
2000
0.9428
1.0299
11.038
51.868
3000
0.9151
1.0454
9.056
48.302
4000
0.8881
1.0611
7.076
5000
0.8617
1.0773
5.094
6000
0.8359
1.0938
3.113
7000
0.8106
1.1107
8000
0.7860
9000
Table 1-1
APPROVED Rev. 0
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O
N
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–
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O N
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ST
IN
FO
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17000
O
0
(Hg)
LL
(ft)
Standard atmosphere
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1.6
WIND COMPONENT CHART Charts and calculating examples represented in this Flight Manual do not take into account wind speed factors. Apply any necessary factors as required by operational rules.
NOTE
HEADWIND COMPONENT – kt 10
15
20
25
30
35
40
45
ED
20
LL O N TR
10
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15
PY
N
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5
0
O 10
15
20
25
C
5
–
0
CROSSWIND COMPONENT – kt
5
90º
0
30
35
40
45
O N
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REPORTED WINDSPEED – kt Wind Component Chart
TI
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Fig. 1-7
U
C
EXAMPLE:
Takeoff heading
270°
ST
R
Known:
FO
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IN
Reported wind direction 240° Reported wind speed
30 kt
Determine:
a) b)
Crosswind component Headwind component
Solution:
a) Crosswind component = 15 kt b) Headwind component = 26 kt 1. Wind direction relative to takeoff heading is 270° – 240° = 30° 2. Enter chart at reported wind speed (30 kt). 3. Move upward, following the shape of the curved lines to wind direction relative to takeoff heading (30°). 4. Move vertically upward (read 26 kt headwind component) and horizontally right (read 15 kt crosswind component).
1 – 14
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1.7
NOISE LEVELS The noise levels determined for a gross mass of 3700 kg under conditions prescribed in Chapter 8 and Appendix 2 of Annex 16 of ICAO, volume 1 and prescribed in 14 CFR 36 Appendix H, are as follows:
ICAO / FAR limit
[EPNdB]
[EPNdB]
84.7
Takeoff
86.5
Approach
90.3
94.7
95.7
96.7
Noise levels
LY
No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be acceptable or unacceptable for operation at, into, or out of, any airport.
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NOTE
–
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Table 1-2
PY
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Flyover
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Noise Level
LL
Reference measurement configurations
APPROVED Rev. 0
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1.8
TERMINOLOGY AND DEFINITIONS OF TERMS
1.8.1
Warnings, Cautions and Notes Throughout this manual WARNINGs, CAUTIONs and NOTEs are used to emphasize important and critical instructions. AN OPERATING PROCEDURE, TECHNIQUE, ETC. WHICH, IF NOT STRICTLY OBSERVED, COULD RESULT IN PERSONAL INJURY OR LOSS OF LIFE.
CAUTION
AN OPERATING PROCEDURE, TECHNIQUE, ETC. WHICH, IF NOT STRICTLY OBSERVED, COULD RESULT IN DAMAGE TO OR DESTRUCTION OF EQUIPMENT.
An operating procedure, technique, condition, etc. which is essential to emphasize.
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NOTE
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WARNING
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WARNINGs and CAUTIONs always precede and are located directly above the text to which they relate.
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Use of Procedural Terms
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1.8.2
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NOTEs are located directly below the text to which they apply.
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–
The procedural term usage and meaning are as follows: have been used to express a mandatory requirement.
“Should”
has been used to express non-mandatory provisions.
“May”
has been used to express permissiveness.
“Will”
has been used only to indicate futurity, never to express a mandatory requirement.
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IN
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O N
O N
“Shall” and “Must”
1 – 16
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ABBREVIATIONS AND SYMBOLS
ED
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O
ALT.A AMC AMM AMPS AP APCH APCP APP APR API AR ARIS ASB ASL ASTM ATC ATT
Ampere(s) or aft Aircraft Alternating current Airborne Collision Avoidance System Audio Control unit Anti-collision Air data computer Automatic direction finder Automatic Dependent Surveillance-Broadcast Air data unit All engines operating Automatic Flight Control System Above ground level Ampere-hour(s) Attitude Heading Reference System Altitude or Altitude hold (also AFCS mode of the same name) Altitude acquire (also AFCS mode of the same name) Aircraft Management Computer Aircraft Maintenance Manual Amperes Autopilot Approach Auto pilot control panel Approach (also AFCS mode of the same name) Approach Application Program Interface Autorotation Anti-resonance Rotor Isolation System Alert service bulletin Above sea level American Society for Testing Material Air traffic control Attitude or Long term attitude hold (also AFCS mode of the same name)
N TR
-
BAT B.L. BOT BRT BSK, bsk Cat. CAU cb, C/B APPROVED Rev. 4
N
PY
O
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O N TI C U R
ST
IN
R FO
B B.A.
C CAS
O
T
a/c, acft AC,ac ACAS ACU ACOL ADC ADF ADS-B ADU AEO AFCS AGL Ah AHRS ALT
O
A A
C
1.9
-
Bleed air Battery Buttock line Bottle Brightness Bottom select key
-
Calibrated airspeed Category Caution Circuit breaker
1 – 17
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ED
LL
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PY
O
C
– – -
Cable Cockpit Control Panel Course Deviation Indication Compact Flash Code of Federal Regulations Center of gravity Chip Commonwealth of Independent States Cockpit Closed Collision or collective Communication (radio) Configuration Cockpit Reference Guide Cruise height (also AFCS mode of the same name) Cursor Centistokes Certification specification Control stability augmentation system Continuity test or Clearance test Centro Técnico Aeroespacial (Brazil) Cubic feet Cockpit Voice and Flight Data Recorder
LY
–
CBL CCP CDI CF CFR C.G., CG CHP CIS CKPT CL, CLSD Coll. COMM, COM CONF CRG CRHT, CR.HT CRS cSt CS CSAS CT CTA cu ft, cu.ft. CVFDR
D DA
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IN
ST
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U
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TI
O N
O N
- Density altitude or Descision altitude DC - Direct current DCPL - Decoupled DDM - Difference in the Depth of Modulation DEG, DEGR - Degraded DG - Directional gyro DGAC - Direction Génerale de‘l Aviation Civile (France) DH – Decision height DISCH - Discharge DISCON, DISCONN - Disconnected DMAP - Digital Map Display System DMAU - Dynamic Monitoring Acquisition Unit DME - Distance measuring equipment DNA - Dirección Nacional De Aeronavegabilidad (Argentina) DOA - Design Organisation Approval DPIFR - Dual pilot IFR DPRT - Departure DR - Dead Reckoning DSAS - Digital SAS (also AFCS mode of the same name) DST – Distance DTD - Data Transfer Device DTK - Desired Track
1 – 18
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– -
European Aviation Safety Agency Equipment deviation list Electronic Engine Control Unit For example Electronic Flight Bag European Geostationary Navigation Overlay System Exhaust gas temperature Electrohydraulic servo actuator Equipment list Emergency Locator Transmitter Emergency Engine Enroute Engine power check External power unit Extended Squitter Essential External or extinguisher
F F
-
Fuel or France or forward Federal Aviation Administration (United States) Full Authority Digital Engine Control Final Approach Fix Federal Aviation Regulation Flight direction Flight Data Cockpit Recorder Flight Data Recorder System Flight Display System Figure Filter First limit indicator Forward Looking Infra-Red Flight manual Forward Looking Terrain Avoidance Flight essential bus Flight manual appendix Flight manual supplement or Flight management system Flight Navigation Display Fiber optic gyro Flight Path Angle (also AFCS mode of the same name) Feet per minute Fuselage station Fasten seat belt Foot (feet) Force Trim Release
FO
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IN
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FAA FADEC FAF FAR FD FDCR FDRS FDS Fig.,fig. FILT, FLT FLI FLIR FLM FLTA FLT ESS BUS FMA FMS
N
O
T
C
O
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O
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ED
E EASA EDL EECU e.g. EFB EGNOS EGT EHS EL ELT EMER, Emer ENG ENR EPC EPU ES ESS EXT
FND FOG FPA
-
fpm F.S. F.S.B. ft FTR
-
APPROVED Rev. 9
1 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
- Follow up - Foreward
ED
LL
-
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GTC GTC.H same name) GTN
N TR
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GEN GLS GM GPIP GPWS GPS GPU GS,gs
C
–
N
O
GAL,gal GARP
Go around (also AFCS mode of the same name) Gallon(s) GNSS Azimuth Reference Point (the virtual localizer antenna location) Generator GPS Landing System Gross mass Glidepath Interception Point Ground Proximity Warning System Global positioning system Ground power unit Ground speed or Glide slope (also AFCS mode of the same name) Ground trajectory control (also AFCS mode of the same name) Ground trajectory control with hover mode (also AFCS mode of the
T
G GA
O N
LY
–
C
O
Hours of time Height Above Terrain Heading (also AFCS mode of the same name) Helicopter emergency egress light Mercury (hydrargyrum) Hover in ground effect Hover out of ground effect Horizon Hectopascal Helicopter Terrain Awareness and Warning System Heater switch Health and Usage Monitoring System Height-velocity Hydraulic
FO
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IN
ST
R
U
C
HAT HDG HEEL Hg HIGE HOGE HOR hPa HTAWS HTR sw HUMS HV, H-V HY, HYD, HYDR -
O N
H h, hr
PY
- GARMIN GTN 750
TI
FU FWD, fwd
I i
1 – 20
IAC-AR IAF IAS
-
IBF IC ICAO ICS i.e. IESI IF
–
indicates a numeric value (e.g. GLSi = GLS1 or GLS2) Interstate Aviation Commitee-Aviation Register (CIS) Initial Approach Fix Indicated airspeed (also AFCS mode of the same name) Inlet Barrier Filter Intercommunication International civil aviation organisation Intercommunication system Id est = that is (to say) Integrated Electronic Stand-by Instrument/Indicator Intermediate Fix APPROVED Rev. 9
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LL O
Instrument flight rules In ground effect Instrument landing system Integrated Modular Avionics Instrument meteorological conditions Imperial Inertial Measurement Unit Inch Indicator Input Instrument Integrity Inverter Instrument panel International Standard Atmosphere Imminent Terrain Impact
N TR
– -
O
IFR IGE ILS IMA IMC Imp. IMU in. IND INP INSTR INTG INV IP ISA ITI
ED
GENERAL
- Joint Airworthiness Requirements
K KCAS
-
Knots calibrated airspeed Kilogram(s) Knots indicated airspeed Kilometer(s) Knot(s) Knots true airspeed Kilowatt
-
Liter(s) Pound(s) Luftfahrt-Bundesamt (Federal Republic of Germany) Landing Landing decision point List of effective pages Left hand Lateral Navigation approach (non-precision) Non–precision LNAV approach with advisory vertical guidance Lateral Navigation and Vertical Navigation approach Localizer (also AFCS mode of the same name) Localizer Back Course Loss Of Integrity Level of Service Low altitude Localizer Performance without vertical guidance or leveling point Localizer Performance with advisory vertical guidance Localizer Performance with vertical guidance Lateral Navigation and Vertical Navigation approach Line select key
FO
R
IN
ST
R
LOC-BC LOI LOS LOW ALT LP LP+V LPV L/VNAV LSK APPROVED Rev. 9
N
PY
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lb LBA LDG LDP LEP LH LNAV LNAV+V LNAV/VNAV LOC
O N
L L, l, LTR, ltr
O N
kg KIAS km kt, kts KTAS kW
O
T
C
J JAR
-
1 – 21
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1 – 22
LL O N TR O C
TI
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N
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Meter(s) Manual mode of operation Missed Approach Point Maximum Maximum continuous Maximum continuous power Minimum equipment list Multifunction display Main gearbox Maintenance Ground station Measured gas temperature Mechanohydraulic servo actuator Military standard or specification Minimum Minute(s) of time Minor Miscellaneous Master list Microwave Landing System Mast moment Millimeter(s) Master Minimum Equipment List Modification Maintenance Release 1 Main Rotor Tuning Minimum radar vectoring altitude Minimum safe altitude Message Main select key Mean sea level Master Maximum Takeoff weight
U R
N1, n1, Ng, ng N2, n2, Np, np NAV
-
NAVD No., no. NORM NM, nm NOTAM NR, NRo, NRO NVG NXT
S -
IN
R
FO
N N
-
ST
MAN MAP max, MAX MC, mc MCP MEL MFD MGB MGS MGT MHS MIL min., MIN min MINR MISC ML MLS MM mm MMEL MOD MR1 MROT MRVA MSA MSG MSK MSL MSTR MTOW
C
Mm
ED
GENERAL
Newton Gas generator speed Power turbine speed Navigation (radio) or En-route navigation (also AFCS mode of the same name) Navigation display Number Normal mode of operation Nautical mile(s) Notice to airmen Rotor speed Night vision goggles Next
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FO
R
IN
RA RADALT RAI RAIM RCNF R/C, ROC R/D RD REL, Rel. RES, RST resp. RF Rev. RH RNAV
APPROVED Rev. 15
LL O N TR
C
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PY
N
O
T
C
O
Pitch (axis) Performance Bsaed Navigation Ambient pressure Pressure Pascal Pressure altitude Paragraph Passenger Push button Position error correction Primary Flight Display Point in Space Pilot induced/assisted oscillation Part number Position Previous Pitch and Roll Power
TI C
U
ST
R R
R
Q QTY
-
O N
PBN P0 P, PRESS Pa PA Para. PAX pb PEC PFD PinS PIO/PAO P/N POS PREV P&R PWR
Oil Outside air temperature Omni Bearing Selector One engine inoperative Oil filter Out of ground effect Open Optional equipment Oil temperature Overheat
–
P P
-
LY
OAT OBS OEI OF OGE OPN OPT OT OVHT
O N
O O
ED
GENERAL
- Quantity
S -
Roll (axis) Radar alitude Radio altimeter Registro Aeronautico Italiano Receiver autonomous integrity monitoring Reconfiguration Rate of climb Rate of descent Reference datum Release Reset Respectively Radius to fix Revision Right hand Area Navigation
1 – 23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL
-
FO
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IN
ED LL O
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Temperature Engine air inlet temperature True airspeed Terrain Awareness System Traffic Collision Alert Device Traffic Collision Avoidance System Transport Canada Airworthiness Group Takeoff decision point Temperature Temporary revision Terminal Terminal Instrument Procedures Tail gearbox Takeoff Takeoff power Turbine outlet temperature Torque Tail rotor gear box
U R
ST
T1 TAS TAWS TCAD TCAS TCAG TDP TEMP Temp. Rev. TERM TERPS TGB TO, T/O TOP TOT TRQ, TQ TRGB
1 – 24
Seconds of time Stability augmentation system Service bulletin Satellite Based Augumentation System Simplified directional facility Section Selector Smart electro-mechanic actuator select Single Shaft horse power Standard Instrument Departure Soft key Sea level Serial number Shutoff valve Single pilot IFR Square Seat reference point Station Standby Standard Suspended Synthetic Vision System Switch or Software System
C
T T
-
O N
SAS SB SBAS SDF Sect. SEL SEMA sel. SGL SHP SID sk SL S/N SOV SPIFR sq SRP STA. STBY, stby STD, std SUSP SVS SW, sw SYS, SYST
O N
S s, sec
- Required navigation performance - Revolutions per minute
TI
RNP RPM, rpm
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- Track (also AFCS mode of the same name) - Tail Rotor Tuning - Time To Go
-
-
Visual flight rules Maximum horizontal speed Very high frequency VOR and LOCalizer (pre-selection on GTN unit) Visual meteorological conditions Vehicle Monitoring Display Maximum operating speed Vehicle Management System Vertical Navigation (non-precision) Vectors to Final Never-exceed speed (velocity never exceed) Maximum speed in autorotation / power off conditions VHF omnidirectional radio ranging (also AFCS mode of the same name) Vertical speed (also AFCS mode of the same name) Takeoff safety speed Best rate-of-climb speed Vector Mast Moment System
-
Wide Area Augmentation System Weight/Altitude/Temperature Waterline Waypoint Warning unit Weather radar
-
Fuel transfer pump Fuel transfer pump - Aft Fuel transfer pump - Forward Fuel transfer pump - Forward and Aft Transmission Transponder Fuselage station
LL
O
N TR
O
C
T
O
N
PY
O N
-
ED
United States of America Usage monitoring system Unsuspended Volt(s) or Speed Virtual Control Panel Vertical approach (also AFCS mode of the same name) Vehicle Ventilation
O
VFR VH VHF VLOC VMC VMD VMO, VMO VMS VNAV VtF VNE, VNE VNE power off VOR
-
C
UMS UNSUSP V V VCP V.APP VEH VENT
–
U U.S., US, USA
LY
TROT TTG
O N
TRK
-
U R
ST
VTOSS VY VMMS
C
TI
VS, V/S
IN
W WAAS
FO
R
WAT W.L. WPT WU WXR
X XFER XFER-A XFER-F XFER-(F+A) XMSN XPDR X-STA
APPROVED Rev. 15
1 – 25
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Y Y Y-BL
- Yaw (axis) - Buttock line
Z Zp
- Pressure altitude
SYMBOLS:
ED
LL
O
N TR
N
1Ǹs
O
°C °F σ DPA
C
FO
R
IN
ST
R
U
C
TI
O N
O N
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–
C
O
PY
ratio, at the density altitude)
1 – 26
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
SECTION 2 LIMITATIONS TABLE OF CONTENTS
Page GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 1
2.2
KINDS OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 1
2.3
BASIS OF CERTIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 1
2.4
MINIMUM FLIGHT CREW / MAXIMUM NUMBER OF OCCUPANTS . . . . 2 - 1
2.5 2.5.1 2.5.2 2.5.3 2.5.4 2.5.5 2.5.5.1 2.5.5.2 2.5.5.3 2.5.6 2.5.6.1 2.5.6.2 2.5.7 2.5.7.1 2.5.7.2 2.5.7.3 2.5.8
OPERATIONAL LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Prohibited flight maneuvers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rotor starting and stopping in high wind . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Hover with wind . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Slope landing limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Autopilot limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operating limitations of the autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operations without A.TRIM function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operating limitations without autopilot and/or SAS . . . . . . . . . . . . . . . . . . . . IFR Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Minimum airspeed limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Descent and approach limitations and recommendations . . . . . . . . . . . . . . Avionics limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Garmin GTN750, FMS, and COM/NAV equipment . . . . . . . . . . . . . . . . . . . . Synthetic Vision System (SVS, optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Helicopter terrain awareness system (HTAWS, optional) . . . . . . . . . . . . . . . Copilot’s seat armrest with mission equipment (optional) . . . . . . . . . . . . . . .
2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2
2.6 2.6.1 2.6.2 2.6.3 2.6.4 2.6.5
MASS AND LOAD LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Maximum gross mass . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Minimum gross mass . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Loading limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tie-down ring limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Multi purpose bracket limits (cabin) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2- 9 2- 9 2- 9 2- 9 2- 9 2 -9
2.7 2.7.1 2.7.1.1 2.7.2
CENTER OF GRAVITY LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Longitudinal center of gravity limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Additional Limitations for Operation within extended CG Envelope . . . . . . 2 Lateral center of gravity limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 -
2.8 2.8.1
AIRSPEED LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 12 Maximum airspeed (VFR and IFR) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 12
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APPROVED Rev. 22
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2 2 2 2 2 3 3 4 4 4 4 4 5 5 7 8 8
10 10 10 11
2- i
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Page ALTITUDE AND ENVIRONMENTAL OPERATING LIMITATIONS . . . . . . . 2 Max operating altitudes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Ambient air temperature limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Altitude-temperature diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Power-up and engine starting envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Minimum cockpit temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2
2.10 2.10.1
NR AND N2 LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 20 Rotor speed indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 21
2.11 2.11.1 2.11.2 2.11.3 2.11.4
ENGINE AND FLI, TQ, TOT AND N1 LIMITATIONS . . . . . . . . . . . . . . . . . . 2 FLI Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Torque limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 TOT limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 N1 limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2
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2.9 2.9.1 2.9.2 2.9.3 2.9.4 2.9.5
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2.12 OTHER ENGINE AND TRANSMISSION LIMITATIONS . . . . . . . . . . . . . . . 2 2.12.1 Engine oil temperature and pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.12.2 FADEC operating modes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.12.3 Engine starter/generator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.12.4 Generator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.12.4.1 Generator abnormal or failure indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.12.5 Main transmission oil pressure and temperature . . . . . . . . . . . . . . . . . . . . . . 2 2.12.6 Main rotor mast moment limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.12.6.1 Main rotor mast moment limits indications . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.12.7 Engine operating time . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2
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2.13 FUEL LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.13.1 Fuel Specification and Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.13.1.1 Normal Unrestricted Fuel Specification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.13.1.2 Normal Unrestricted Fuel Temperature Limitation . . . . . . . . . . . . . . . . . . . . . 2 2.13.1.3 Replacement Fuel Specification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.13.1.4 Replacement Fuel Temperature Limitation . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.13.2 Fuel additives . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2.13.3 Fuel quantities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2
2 - ii
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17 17 17 18 18 19
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22 22 24 26 27
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28 28 28 29 29 29 30 31 31 32
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32 32 32 33 34 35 36 36
2.14 2.14.1 2.14.2
OIL LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 37 Oil specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 37 Oil quantities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 37
2.15 2.15.1 2.15.2 2.15.3
HYDRAULIC SYSTEM LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Hydraulic pressures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Hydraulic system quantities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Hydraulic fluid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2
2.16
PLACARDS AND DECALS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 39
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38 38 38 38
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
LIST OF FIGURES Page Fig. 2-1
Multi- purpose brackets - typical installation . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 9
Fig. 2-2
Allowable CG envelope (longitudinal) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 10
Fig. 2-3
Allowable CG envelope (lateral) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 11
ED
Before Helionix Maintenance Release 1 VNE power off and VNE exceedance indication . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 12
Fig. 2-4
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After Helionix Maintenance Release 1
VNE power off and VNE exceedance indication . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 13
Fig. 2-5
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Minimum temperatures for proper defogging/defrosting and heating capabilities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 17
Fig. 2-7
Altitude-temperature diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 18
Fig. 2-8
Rotor speed indication (color coding on FND and VMD) . . . . . . . . . . . . . . 2 - 20
Fig. 2-9
Rotor speed indication in FND format (AEO) . . . . . . . . . . . . . . . . . . . . . . . . 2 - 21
Fig. 2-10
Rotor speed indication in VMD format (engine 1 in IDLE) . . . . . . . . . . . . 2 - 21
Fig. 2-11
AEO torque limitations as a function of airspeed . . . . . . . . . . . . . . . . . . . . 2 - 24
Fig. 2-12
AEO torque limitations as a function of airspeed - IAS > VY+20 kt . . . 2 - 25
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Fig. 2-6
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Fig. 2-13
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Engine oil temperature and pressure indications . . . . . . . . . . . . . . . . . . . . 2 - 28 Main transmission oil pressure and temperature indications . . . . . . . . . . 2 - 30
Fig. 2-15
Mast moment indicator on the FLI page - linear scale . . . . . . . . . . . . . . . 2 - 31
Fig. 2-16
Mast moment indicator and cyclic stick position on the FLI page circular scale . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 31
Fig. 2-17
Altitude and temperature limits for approved primary fuels . . . . . . . . . . . 2 - 33
Fig. 2-18
Altitude and temperature limits for replacement fuels . . . . . . . . . . . . . . . . 2 - 35
Fig. 2-19
Hydraulic pressure indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 - 38
APPROVED Rev. 22
2 - iii
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
LIST OF TABLES Page 2 - 14
Table 2-2 Never-exceed speed for any helicopter gross mass > 3000 kg (VNE - KIAS)
2 - 14
Table 2-3 Never-exceed speed OEI for any helicopter gross mass ≤ 3000 kg (VNE - KIAS)
2 - 15
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Table 2-4 Never-exceed speed OEI for any helicopter gross mass > 3000 kg (VNE - KIAS)
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Table 2-1 Never-exceed speed for any helicopter gross mass ≤ 3000 kg (VNE - KIAS)
2 - 16
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Table 2-5 Never exceed speed in autorotation (power off condition) for any helicopter gross mass ≤ 3000 kg (VNE - KIAS)
2 - 15
2 - 16
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Table 2-6 Never exceed speed in autorotation (power off condition) for any helicopter gross mass > 3000 kg (VNE - KIAS)
2 - iv
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
SECTION 2 LIMITATIONS IF ANY LIMITATION HAS BEEN EXCEEDED, MAINTENANCE ACTION MAY BE REQUIRED AND NECESSARY BEFORE NEXT FLIGHT. ENTER DURATION AND AMOUNT OF THE EXCEEDANCE IN LOGBOOK AND APPROPRIATE SYSTEM LOGBOOK (FOR EXAMPLE ENGINE LOGBOOK).
GENERAL
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This helicopter shall be operated in compliance with the limitations of this section.
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KINDS OF OPERATION
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For definitions of terms, abbreviations and symbols used in this section refer to section 1.
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This helicopter in its basic configuration is approved for day and night operation under Visual and Instrument Flight Rules (VFR and IFR) provided that the equipment required by operational regulations is installed and serviceable.
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With special equipment installed and operative and under observance of the respective procedures and limitations, the helicopter is also approved for:
O N
– Over water operation in accordance with FMS 9.2-9
BASIS OF CERTIFICATION
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– Flight with night vision goggles in accordance with FMS 9.2-11
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MINIMUM FLIGHT CREW / MAXIMUM NUMBER OF OCCUPANTS
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This helicopter is certified under CS/FAR 29 requirements.
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The minimum flight crew consists of one pilot operating the helicopter from the right crew seat.
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For special missions under VFR only, the aircraft may be flown by a single pilot occupying the left crew seat, provided no passengers are seated in the right crew seat and the rotor brake is not required for the mission. When a short collective is installed no single pilot operations from left hand side are allowed, furthermore, CAT A procedures (if required) must be flown from the right hand seat in this configuration. The maximum number of occupants is 10 persons (including the flight crew). If the optional vertical rack is installed the cabin may only be occupied when at least one fire extinguisher is installed in the cabin.
APPROVED Rev. 17
2–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.5
OPERATIONAL LIMITATIONS
2.5.1
Prohibited flight maneuvers The following are prohibited: – aerobatic maneuvers – intentional full autorotation landings for training – flight into icing conditions. In the case that icing conditions are encountered unexpectedly, the icing conditions shall be left immediately.
2.5.2
Rotor starting and stopping in high wind
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Hover with wind
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2.5.3
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Starting and stopping the rotor is authorized with wind from any horizontal direction up to 50 kt.
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Maximum relative wind speed from any direction, except headwind ($30_) . . . . . . . 30 kt
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NOTE D Above 16000 ft density altitude, additional performance constraints may apply (see section 5).
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Slope landing limitation
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D When flying with relative winds of more than 25 kt from the left, increased control activity and / or large pedal inputs may be required to maintain aircraft heading.
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Slope operations (takeoff/landing) are limited by the maximum mast moment (normal range) and the slope of the terrain as follows:
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– Ground sloping nose down (if tail clearance allows) . . . . . . . . . . . . . . . . . . . . . . max 10°
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– Ground sloping up to the right . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . max 12°
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– Ground sloping up to the left . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . max 8°
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– Ground sloping nose up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . max 8°
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The maximum achievable slope angle may be further limited by character and friction of the landing surface.
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NOTE D When the attitude indicator is used to determine the slope, the normal attitude on ground of 3.5° nose up shall be considered. For example: – 8° nose up slope = 11.5° nose up on attitude indicator – 8° nose down slope = 4.5° nose down on attitude indicator D During slope operations, it is recommended to switch the autopilot A.TRIM to OFF. D Roll oscillations might occur during nose up slope operations with high mast moment. When encountered, temporarily reducing the mast moment using aft cyclic will stop the oscillation immediately. D In case of mast moment indication failure, maximum slope limit is 3°, refer to the procedure detailed in section 3.3.5.4.
2–2
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.5.5
Autopilot limitations
2.5.5.1 Operating limitations of the autopilot WHEN OPERATING NEAR THE GROUND, IN THE VICINITY OF OBSTACLES, BELOW THE MINIMUM OR ABOVE THE MAXIMUM RECOMMENDED AIRSPEED OR HEIGHT: - WITH THE AUTOPILOT BASIC OPERATION MODE, OR - WITH THE AUTOPILOT UPPER MODES ENGAGED THE PILOT SHALL REMAIN ATTENTIVE TO THE FLIGHT PATH WITH HANDS AND FEET ON THE CONTROLS, SINCE CERTAIN MALFUNCTIONS OF THE AUTOPILOT COULD RESULT IN LOSS OF ATTITUDE, ALTITUDE OR DEVIATION FROM THE FLIGHT PATH.
CAUTION
WHEN OPERATING ABOVE 90 KIAS IN GUSTY CONDITIONS IN 4- AXIS MODE CLOSE TO THE MCP LIMIT, PILOTS SHOULD BE ATTENTIVE ON THE COLLECTIVE TO INTERVENE MANUALLY IF MCP LIMITS ARE INFRINGED.
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Minimum airspeed - Minimum airspeed with IAS mode engaged . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 KIAS
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- Minimum recommended airspeed with VS, FPA, TRK mode engaged . . . . . . 30 KIAS
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Before Helionix Maintenance Release 1 or before ASB MBB BK117 D-2- 42A- 004 (HELIONIX STEP 2.0.1)
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- Minimum recommended airspeed for GA engagement . . . . . . . . . . . . . . . . . . . 30 KIAS
EFFECTIVITY
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- Minimum airspeed with CRHT mode engaged . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 KIAS All
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Minimum height above the ground or obstacles for hands-off and/or feet-off operation
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CRHT mode
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- During takeoff and approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 ft - During all other flight phases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 500 ft
IN
Use of the CRHT mode is limited to:
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- Operations above water or flat surface - Minimum recommended height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 ft
ILS approach mode Use of the ILS approach mode is limited to: - Minimum LOC interception distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 nm - Maximum LOC interception angle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90 GTC/GTC.H mode - The GTC/GTC.H mode is intended for use in VFR only. The pilot must remain attentive to the flight path at all times, especially when operating near the ground, near obstacles, during precision operations (e.g. hoisting), and in high wind conditions. APPROVED Rev. 22
2- 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.5.5.2 Operations without A.TRIM function Sustained piloting in DSAS mode (A.TRIM OFF) is not recommended for IFR operations in IMC except for IFR training or in case of a malfunction of the A.TRIM. In DSAS mode, the pilot shall be on the controls all the time, since long term stabilization is not provided. 2.5.5.3 Operations without AP1 and AP2, or without AP1, AP2 and backup SAS (IESI)
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Flying with backup SAS only (AP1 and AP2 off) or without any stabilization (AP1, AP2 and backup SAS off) is permitted for training purposes only or in accordance with the MMEL. The following limitations apply:
LL
- Visual Meteorological Conditions only.
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- Maximum airspeed 110 KIAS or VNE (whichever is less). - Maximum bank angle 45_.
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- Slope landings (>3_) using backup SAS only are prohibited.
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- The pilot shall be on the controls all the time.
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WHEN OPERATING BEYOND THE RECOMMENDED LIMITS, THE PILOT SHALL REMAIN ATTENTIVE WITH HANDS AND FEET ON THE CONTROLS.
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2.5.6.1 Minimum airspeed limitations
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IFR limitations
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2.5.6
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- Both AMCs and at least two MFDs shall be operational.
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The minimum airspeed under IFR is:
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- 4-axis AFCS on and upper modes engaged (VMINI) . . . . . . . . . . . . . . . . . . . . . . 30 KIAS
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- Collective AFCS axis inoperative (VMINI) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60 KIAS
IN
2.5.6.2 Descent and approach limitations and recommendations
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Maximum glideslope angle:
FO
- during ILS approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7_ - during LPV and LNAV/VNAV approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10,0_ Maximum sustained rate of descent: - During ILS, LOC, NDB, VOR, LPV or LNAV/VNAV approach
. . . . . . . . . . . 1000 ft/min
- During enroute (recommended) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1500 ft/min Maximum tailwind during steep approaches (>6_) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 kt Maximum recommended airspeed (rate of descent > 500 ft/min) . . . . . . . . . . . . . 120 KIAS Minimum IFR height during approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 ft During LP+V or LNAV+V approaches, vertical guidance is provided for information only. The pilot shall perform the approach using the altitude profile shown on the approach chart.
2- 4
APPROVED Rev. 22
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.5.7
Avionics limitation
2.5.7.1 Garmin GTN750, FMS, and COM/NAV equipment CAUTION D BEFORE OPERATING THE GTN750 IN VFR/IFR, THE PILOT MUST BE FAMILIAR WITH THE EQUIPMENT. PROPER TRAINING AND/OR STUDY OF THE GARMIN PILOT’S GUIDE IS STRONGLY RECOMMENDED.
LL
ED
D THE GTN 750 COCKPIT REFERENCE GUIDE (GARMIN P/N 190- 01007- 04) IN ITS LATEST REVISION SHOULD BE AVAILABLE TO THE FLIGHT CREW.
N TR
O
The following equipment and functions are approved for IFR navigation: VOR:
O
En- route, terminal, and non- precision approach navigation.
C
-
PY
LOC:
O
Non- precision approach navigation.
C
-
O
Precision approach navigation.
N
-
T
ILS:
–
GPS, SBAS not required:
Basic- RNAV (RNAV5) and RNP2 for en-route navigation.
-
RNP4 navigation for oceanic and remote.
-
Precision-RNAV (RNAV1) and RNP1 navigation for en-route, terminal, SIDs, STARs, initial (IAF) and missed (MAP) approach.
-
RNP0.3 all phases of flight.
-
RNP APCH for initial (IAF), intermediate (IF), final approach (FAF) and missed approach (MAP) for:
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
-
EFFECTIVITY
D LNAV navigation down to LNAV minima including PinS helicopter approach for LNAV. Main SW 6.62 only D LNAV+V navigation with advisory vertical guidance only down to LNAV minima.
EFFECTIVITY -
All Radius-to-fix (RF) leg capability for terminal, arrival, initial and intermediate approach, and departure. continued
APPROVED Rev. 22
2- 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
GPS required, SBAS required: - RNP APCH for initial (IAF), intermediate (IF), final (FAF) and missed (MAP) approach, for: EFFECTIVITY
Main SW 6.00 and 6.21 only D LNAV+V navigation with advisory vertical guidance only down to LNAV minima.
EFFECTIVITY
All D LP+V navigation with advisory vertical guidance only down to LP minima.
ED
D LNAV/VNAV navigation with vertical guidance down to LNAV/VNAV minima.
LL
D LP/LPV navigation down to LP/LPV minima.
O
D PinS helicopter approach for LPV.
PY
N
O
T
C
O
N TR
The following equipment and functions are not approved for IFR navigation: - Unapproved GPS overlay approach. The final segment of an ILS, LOC, LOC-BC, LDA, SDF, MLS and any other type of approach not specifically approved as a GPS approach, shall not be flown using GPS navigation. - Dead reckoning (DR). Dead reckoning is only a position estimate and should not be used as the sole means of navigation. Approved software version and GTN750 configuration:
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
- MAIN SW version 6.00 or 6.21 or 6.62 must be installed. This is indicated on the start-up page immediately after start-up. Use of subsequent software versions requires prior EASA approval. - The GTN750 ACAS and GTN750 HTAWS functions must be disabled. - Both GTN750 units must be configured to automatic crossfill (unless exceptional operational circumstances dictate otherwise). - Display brightness must be adjusted to the factory settings (refer to the Airbus Helicopters maintenance documentation). - Use of USER MAGNETIC VARIATION is prohibited. Because Helionix does not support a user (manual) magnetic variation, erroneous indications and erratic autopilot behavior could result when user magnetic variation is selected.
R
Aeronautical database and data card:
FO
- Use of RNAV as a primary navigation source is permitted only when a current and approved aeronautical database is installed. The database must be installed either with an SD card or with the Flight Stream 510 (using Data Concierge). - The SD card or Flight Stream 510 must be present in the unit at all times. It is prohibited to insert or remove it while the unit is powered up. - The use of the Flight Stream 510 in combination with Transmitting Personal Electronic Devices (T-PED) on the BK117 D- 2 helicopters and using Wi-Fi and Bluetooth technology is approved. The following restrictions, however, apply: -
2- 6
Any powered- on T- PED may produce spurious out of band emissions, which can interfere with the on- board COM/NAV equipment reception. If disturbances occur, the T- PED shall be first set to ”airplane mode” and if necessary switched OFF. APPROVED Rev. 21.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
-
Use of a transmitting PED during low visibility approaches is permitted only when the PED was specifically approved for use during this phase of flight. This approval must be obtained by the operator from the national authority in accordance with the applicable requirements.
Use of gloves and sunglasses: - Sun glasses with polarized lenses shall not be used, because this could jeopardize the readability of the GTN display.
LL
ED
- Flight crew is allowed to wear gloves, provided the Glove Qualification Procedure described in the Garmin Pilot’s Guide/Cockpit Reference Guide - has been successfully completed. The Glove Qualification Procedure is specific to a pilot / glove / GTN combination.
N TR
Before Helionix Maintenance Release 1
O
EFFECTIVITY
O
2.5.7.2 Synthetic Vision System (SVS, optional)
THE SVS DOES NOT DISPLAY ANY OBSTACLES.
N
After Helionix Maintenance Release 1
PY
EFFECTIVITY
O
T
C
CAUTION
–
C
O
WARNING D THE SVS ONLY DISPLAYS OBSTACLES WHICH ARE INCLUDED IN THE HTAWS DATABASE.
O N
O N
LY
D A GROUP OF OBSTACLES IS SOMETIMES PRESENTED ONLY BY A SINGLE ”GROUP” OBSTACLE IN THE HTAWS DATABASE. IN THIS CASE, THE INDIVIDUAL OBSTACLES WILL NOT APPEAR AT THE CORRECT LOCATION ON THE SVS. THE SVS DOES NOT DISPLAY ANY LINE OBSTACLES (CABLES, WIRES, LINES).
All
ST
EFFECTIVITY
R
U
C
TI
CAUTION
FO
R
IN
The Synthetic Vision System (SVS) is intended to increase the pilot’s situation awareness in VFR and IFR. Use of the SVS does not change the rules and minima for VFR and IFR (i.e. no operational credit shall be claimed). Navigation and terrain avoidance shall not be based upon SVS information. In VFR, the pilot shall use external references; in IFR, the pilot shall use the published procedures. Simultaneous display of SVS on all MFDs is prohibited.
EFFECTIVITY
FAA registered helicopters and before Helionix Maintenance Release 1
The SVS is not approved and is not selectable. EFFECTIVITY
APPROVED Rev. 21.1
All
2- 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.5.7.3 Helicopter terrain awareness system (HTAWS, optional) WARNING D NOT ALL OBSTACLES AND WIRES ARE INCLUDED IN THE HTAWS DATA BASE. WHEN AN OBSTACLE, WIRES, OR TERRAIN IS NOT IN THE DATABASE, AN ALERT WILL NOT BE PRODUCED. IT IS THE PILOT’S RESPONSIBILITY TO MAINTAIN A PROPER LOOKOUT.
O
When operating near the border of the loaded data base area, the OBS MISSING indication may be inoperative.
N TR
NOTE
LL
ED
D A GROUP OF OBSTACLES IS SOMETIMES PRESENTED ONLY BY A SINGLE ”GROUP” OBSTACLE IN THE HTAWS DATABASE. IN SUCH CASES, THE HTAWS WILL NOT WARN FOR THE INDIVIDUAL OBSTACLES AND ONLY A SYMBOLIC OBSTACLE GROUP WILL BE DISPLAYED.
C
O
Navigation and terrain avoidance shall not be based upon HTAWS information.
PY
N
O
T
The HTAWS provides advisory information only, and shall be considered as a backup to recognize and avoid terrain and obstacle collisions. If an HTAWS caution or warning is received:
C
O
- in VMC, the pilot should not initiate a maneuver based on the HTAWS indication alone, but should first visually acquire the environment and threat.
LY
–
- in IMC (especially below the MSA), immediate activation of the go-around mode should be considered.
O N
When HTAWS is used, the pilot shall be familiar with the system operation.
ST
Copilot’s seat armrest with mission equipment (optional)
IN
2.5.8
R
U
C
TI
O N
When LOW ALTITUDE mode is selected and if all screens are operational, the HTAWS layer shall be selected on at least one screen with a display range of 2 NM unless a procedure requiring the display of the weather radar as the primary sensor for obstacle clearance is planned or in progress (oil rig approach or special procedure at sea).
FO
R
WARNING
AS EMERGENCY EGRESS MIGHT BE HAMPERED WITH COPILOT SEAT ARMREST IN HORIZONTAL POSITION, WHEN ABLE, STOW ARMREST IF AN EMERGENCY SITUATION ARISES.
The armrest must be in upward and locked position for takeoff and landing. When aircraft is flown from the copilot seat, armrest must be moved to upward and locked position. The armrest installation is not compatible with the standard collective lever. The short collective lever must be installed instead. NOTE
2- 8
A standard collective lever should be installed whenever mission equipment, which requires the use of a short collective, is removed and planned missions do no longer require this specific configuration. APPROVED Rev. 22
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.6
MASS AND LOAD LIMITS
2.6.1
Maximum gross mass The maximum permissible takeoff and landing gross mass, as a function of the given atmospheric conditions (Pa, OAT), is to be derived from the relevant HOVER CEILING IN GROUND EFFECT (TAKEOFF POWER) performance chart in section 5 of this manual. Maximum approved gross mass for flight is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3700 kg
2.6.2
Minimum gross mass Minimum approved gross mass for flight is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2000 kg Loading limits
ED
2.6.3
O
LL
Maximum allowable floor loading is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 600 kg/m2 CARGO, BAGGAGE AND LOOSE ITEMS MUST BE PROPERLY STOWED AND TIED DOWN IN ORDER TO MAKE IN-FLIGHT SHIFTING IMPOSSIBLE (SEE ALSO REMARKS IN SECTION 6).
T
Tie-down ring limits
O
2.6.4
C
O
N TR
CAUTION
O
Multi purpose bracket limits (cabin)
U
C
TI
O N
O N
LY
–
C
BKD2_FLH_0572_R
2.6.5
PY
N
Maximum allowable load per tie-down ring is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70 kg
ST
R
Fig. 2-1
Flight direction Multi- purpose brackets - typical installation
FO
R
IN
The forward and middle brackets are able to sustain a maximum load of 8000N, therefore it is permitted to secure the following loads: - Securing of persons (direct attachment of hoist operator or other persons with lanyard or connecting rope): . . . . . . . . . . . . . . . . . . . . . . . . . max 200kg per bracket
WARNING
ALL PERSONS MUST BE SEATED IN CRASHWORTHY SEATS WITH THE SEAT BELTS FASTENED DURING TAKEOFF AND LANDING. PERSONS SECURED ONLY BY LANYARD OR CONNECTING ROPE TO THE ATTACHMENT POINTS ARE NOT SUFFICIENTLY PROTECTED IN CASE OF A CRASH OR HARD LANDING.
- Securing of equipment (mass attached in flight and during takeoff and landing) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . max 40kg per bracket The aft brackets are able to sustain a maximum load of 2000N, therefore it is permitted to secure equipment up to a maximum load of 10 kg. APPROVED Rev. 22
2- 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.7
CENTER OF GRAVITY LIMITATIONS
2.7.1
Longitudinal center of gravity limits Station zero (datum) is an imaginary vertical plane, perpendicular to the aircraft centerline and located 3950 mm forward of the leveling point (see section 6). A
B
A B C D
3600 3400
3700 3000
O
3000
4250 4250
N TR
D’
C
O
2800
2400
O
T
2600
D
PY
N
Gross Mass (kg)
A’ D’
Extended Envelope
3200
X- STA (mm) GM (kg) 4380 3700 4535 3700 4700 2000 4347 2400
ED
A’
LL
3800
O
2200
C
2000 1800 4300
4350
Fig. 2-2
4400
4450
O N
4250
4500
4550
4600
4650
4700
4750
X- STA (mm)
Allowable CG envelope (longitudinal)
O N
4200
LY
–
C
C
TI
2.7.1.1 Additional Limitations for Operation within extended CG Envelope (shaded area Fig. 2-2)
FO
R
IN
ST
R
U
The extended CG envelope is intended for specific operations during which the CG moves forward during the flight, because passengers or crew temporarily change their position in the cabin (e.g. during fast roping). Whenever the aircraft is operated within the extended CG envelope, it must be possible to return the CG within the normal envelope without undue delay. Takeoff and landing Takeoff and landing while the CG is within the extended envelope is prohibited. Altitude limitation Maximum operating altitude is . . . . . . . . . . . . . . . . . . . 12 000 ft PA or DA, whichever is less Wind limitation CAUTION
2 - 10
WHEN HOVERING IN WIND CONDITIONS, THE MAST MOMENT CAN REACH THE YELLOW CAUTION AREA. THIS IS MOST LIKELY WITH WIND FROM THE RIGHT. DURING THESE OPERATIONS, THE PILOT SHALL CLOSELY MONITOR THE MAST MOMENT AND AVOID OPERATION WITH THE MAST MOMENT IN THE CAUTION AREA. APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Max. wind speed up to 10000 ft density altitude: – from the rear-left . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 kts – from other directions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 kts Max. wind speed above 10000 ft density altitude: – from the rear-left . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 kts – from the right . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 kts – from other directions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 kts Airspeed limitation
ED
VNE extcg . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 110 KIAS or basic VNE, whichever is less
N TR
O
LL
AFCS limitations and requirements: – AFCS shall be fully functional (i.e. no AFCS related degradation). – In case of AFCS degradation in flight, the CG must be relocated within the normal CG envelope.
O
T
The extended CG envelope is not compatible with:
C
O
Compatibility with optional equipment
2.7.2
PY
N
– External Hoist (an enlarged hoist CG envelope is defined in FMS 9.2–4) – Cargo Hook(s)
C
O
Lateral center of gravity limits
LY
–
Buttock line (datum) is an imaginary vertical plane through the centerline of the aircraft.
O N
Lateral center of gravity limits left and right of the fuselage centerline are: 3800
C
TI
3600
R
U
3400
ST
3200
E
E’
F’
F
R
IN
3000
Y–BL (mm) GM (kg) –80 3700 80 3700 80 3000 100 3000 100 2000 –100 2000 –100 3000 –80 3000
2800
FO
Gross Mass (kg)
B
O N
A
A B F’ F C D E E’
2600 2400
BKD2_FLH_0294_R
2200
C
D
2000 1800 –150
–100
Fig. 2-3 APPROVED Rev. 21
–50
0 Y–BL (mm)
50
100
150
Allowable CG envelope (lateral)
2 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.8
AIRSPEED LIMITATIONS NOTE
2.8.1
All airspeed values given in this manual are indicated airspeed (IAS).
Maximum airspeed (VFR and IFR) The maximum airspeed (VNE) is automatically calculated as a function of the aircraft weight, altitude, temperature, AEO/OEI/autorotation and AFCS status (off or backup SAS, AP1/AP2 on). The VNE is shown as follows on the airspeed indicator: – Solid red line: VNE = Maximum speed in AEO or OEI. power off
= Maximum speed in autorotation / power off
ED
– Dashed red/yellow line: VNE conditions
O C T
When the VNE power off is exceeded, a red strip extending to the top of the scale is not shown.
PY
N
NOTE
Before Helionix Maintenance Release 1
O
EFFECTIVITY
N TR
O
LL
When VNE is exceeded, this is shown by a red strip in the airspeed indicator, extending from VNE to the top of the scale (Fig 2-4, right). In addition, the voice message ”maximum speed” is triggered when VNE or VNE power off is exceeded.
O N
LY
VNE
120
–
C
O
160
120
U
VNE power off
ST
R
80
100
FO
R
IN
BKD2_FLH_0400_R
C
TI
O N
100
140
VNE exceedance indication
2 – 12
Fig. 2-4
VNE power off and VNE exceedance indication
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
After Helionix Maintenance Release 1
EFFECTIVITY
When the VNE power off is exceeded, a dashed red/yellow strip extending to the top of the scale is shown.
NOTE
120 VNE
120
100
LL
O N TR O
N
O
VNE power off and VNE exceedance indication
All
O
EFFECTIVITY
60
PY
Fig. 2-5
80
T
80
VNE exceedance indication
C
BKD2_FLH_0400_R
VNE power off
BKD2_FLH_0520_R
ED
100
LY
–
C
In the case that the VNE indication on the FND is not available, the following airspeed limitations shall be used:
O N
– All engines operating (AEO): Below 3000 kg, Table 2-1 shall be used. Above 3000 kg, Table 2-2 shall be used.
TI
O N
– One engine inoperative (OEI) or AFCS off or backup SAS only: Below 3000 kg, Table 2-3 shall be used. Above 3000 kg, Table 2-4 shall be used.
FO
R
IN
ST
R
U
C
– Steady autorotation: Below 3000 kg Table 2-5 shall be used. Above 3000 kg Table 2-6 shall be used
APPROVED Rev. 21
2 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
VNE
OAT - °C
Zp
–35
–30
–20
–10
0
10
20
30
40
50
0
150
150
150
150
150
150
150
150
150
150
150
2000 4000 6000 8000 10000 12000 14000 16000 18000 20000
150 148 142 137 128 115 104 97 93 89
150 150 148 144 131 118 107 103 99 95
150 150 148 145 132 120 111 106 102 98
150 150 149 146 136 124 118 113 106 94
150 150 149 146 139 129 124 113 101 88
150 150 149 146 142 132 119 107 95 82
150 150 148 146 138 126 114 102 90 77
150 150 148 143 133 121 109 97 84 71
150 150 146 140 128 116 104
150 150 144 135 123
150 147
C
O
N TR
O
LL
ED
–45
- ft -
–
C
O
PY
N
O
T
Table 2-1 Never-exceed speed for any helicopter gross mass v 3000 kg (VNE – KIAS)
OAT - °C
–35
–30
–20
–10
0
10
20
30
40
50
0
144
145
145
145
145
144
144
143
142
141
138
2000 4000 6000 8000 10000 12000 14000 16000 18000 20000
141 138 135 131 125 115 104 97 85 82
142 139 136 132 126 118 107 100 86 79
142 140 137 132 126 118 110 100 85 76
143 140 137 132 126 119 110 96 83 69
143 140 136 132 126 117 104 87 76 62
142 139 134 129 122 111 98 83 70 56
141 137 132 126 118 105 91 77 64
140 135 129 123 112 99 86 71 58
137 132 127 119 107 93 80
135 130 124 114 101
133 127
FO
R
C
U
R
ST
IN
- ft -
TI
–45
O N
Zp
O N
LY
VNE
Table 2-2 Never-exceed speed for any helicopter gross mass > 3000 kg (VNE – KIAS)
2 – 14
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
OEI VNE table VNE
OAT - °C
Zp
–35
–30
–20
–10
0
10
20
30
40
50
0
110
110
110
110
110
110
110
110
110
110
110
2000 4000 6000 8000 10000 12000 14000 16000 18000 20000
110 110 110 110 110 99 90 86 83 79
110 110 110 110 110 104 97 94 90 86
110 110 110 110 110 106 101 97 93 89
110 110 110 110 110 110 108 104 100 94
110 110 110 110 110 110 110 110 101 88
110 110 110 110 110 110 110 107 95 82
110 110 110 110 110 110 110 102 90 77
110 110 110 110 110 110 109 97 84 71
110 110 110 110 110 110 104
110 110 110 110 110
110 110
LL
O
N TR
O
T
C
ED
–45
- ft -
C
O
PY
N
O
Table 2-3 Never-exceed speed OEI for any helicopter gross mass v 3000 kg (VNE – KIAS)
LY
–
OEI VNE table OAT - °C
O N
VNE Zp
–35
–30
–20
–10
0
10
20
30
40
50
110
110
110
110
110
110
110
110
110
110
110
2000 4000 6000 8000 10000 12000 14000 16000 18000 20000
110 110 110 110 110 99 90 86 83 79
110 110 110 110 110 104 97 94 86 79
110 110 110 110 110 106 101 97 85 76
110 110 110 110 110 110 108 96 83 69
110 110 110 110 110 110 104 87 76 62
110 110 110 110 110 110 98 83 70 56
110 110 110 110 110 105 91 77 64
110 110 110 110 110 99 86 71 58
110 110 110 110 107 93 80
110 110 110 110 101
110 110
FO
R
IN
ST
R
U
C
0
TI
O N
–45
- ft -
Table 2-4 Never-exceed speed OEI for any helicopter gross mass > 3000 kg (VNE – KIAS)
APPROVED Rev. 21
2 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Autorotation / poweroff VNE table VNE
OAT - °C
Zp
–35
–30
–20
–10
0
10
20
30
40
50
0
90
90
90
90
90
90
90
90
90
90
90
2000 4000 6000 8000 10000 12000 14000 16000 18000 20000
90 90 90 90 90 90 89 86 83 79
90 90 90 90 90 90 90 90 90 86
90 90 90 90 90 90 90 90 90 89
90 90 90 90 90 90 90 90 90 90
90 90 90 90 90 90 90 90 90 88
90 90 90 90 90 90 90 90 90 82
90 90 90 90 90 90 90 90 90 77
90 90 90 90 90 90 90 90 84 71
90 90 90 90 90 90 90
90 90 90 90 90
90 90
T
C
O
N TR
O
LL
ED
–45
- ft -
C
O
PY
N
O
Table 2-5 Never exceed speed in autorotation (power off condition) for any helicopter gross mass v 3000 kg (VNE – KIAS)
LY
–
Autorotation / poweroff VNE table
–35
0
90
90
2000 4000 6000 8000 10000 12000 14000 16000 18000 20000
90 90 90 90 90 90 89 86 83 79
FO
R
IN
OAT - °C
–30
–20
–10
0
10
20
30
40
50
90
90
90
90
90
90
90
90
90
90 90 90 90 90 90 90 90 85 76
90 90 90 90 90 90 90 90 83 96
90 90 90 90 90 90 90 87 76 62
90 90 90 90 90 90 90 83 70 56
90 90 90 90 90 90 90 77 64
90 90 90 90 90 90 86 71 58
90 90 90 90 90 90 80
90 90 90 90 90
90 90
TI
U
90 90 90 90 90 90 90 90 86 79
R
ST
- ft -
O N
–45
C
Zp
O N
VNE
Table 2-6 Never exceed speed in autorotation (power off condition) for any helicopter gross mass > 3000 kg (VNE – KIAS)
2 – 16
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.9
ALTITUDE AND ENVIRONMENTAL OPERATING LIMITATIONS
2.9.1
Max operating altitudes Maximum operating altitude is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 000 ft PA Maximum operating altitude for hover in ground effect / takeoff and landing is . . . . . . . . . . . 20000 ft PA or DA, whichever is less
2.9.2
Ambient air temperature limitations Basic aircraft configuration:
ED
– Maximum air temperature is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ISA +35_C (max +50_C)
LL
– Minimum air temperature is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . –30 _C
N TR
O
With oil cooler blocking plates installed (part of cold weather kit):
– Maximum air temperature is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . +35_C
C
O
– Minimum air temperature is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . –45 _C
N
O
T
If OAT w +35_C, lower the cockpit temperature by setting maximum ventilation (refer to section 4 para 4.16.3).
O
PY
If OAT w +40_C, the maximum operating time on ground is limited to 20 minutes.
U
See also fuel temperature limits in this section.
FO
R
IN
ST
R
NOTE
C
TI
O N
O N
LY
–
C
To ensure proper defogging/defrosting and heating capabilities, the minimum temperatures of Fig. 2-6 shall be observed (in case of a heating system failure, flight at lower temperatures is permitted in accordance with the MMEL/MEL). At very low temperatures, cabin heating outlets shall be blocked by installing a metallic plate (part of cold weather kit). To ensure constant defogging, the heating shall be switched on permanently with maximum defogging settings when operating at temperatures close to the minima (see Fig. 2-6).
OAT_C
No heater
Bleed air heater
Prohibited
Cabin outlets blocked
Bleed air + electric heater
20
10 0 –10
BKD2_FLH_0022_R
–20
Fig. 2-6 APPROVED Rev. 21
–30 –40 –45
Heating shall be ON Cabin outlets blocked
Prohibited
Heating shall be ON
Minimum temperatures for proper defogging/defrosting and heating capabilities
2 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.9.3
Altitude-temperature diagram
20000
In–flight
18000
16000
LL
ED
Takeoff and landing
14000
O N TR C
O
10000
T
8000
O
Pressure Altitude (ft)
12000
PY
N
6000
–
C
O
4000
O N
LY
2000
O N –30
–10
0
10
20
30
40
50
R IN
Fig. 2-7
Altitude-temperature diagram
R
Power-up and engine start envelope
FO
2.9.4
–20
C
–40
U
–50
TI
–2000
ST
BKD2_FLH_0514_R
0
Minimum cabin temperature for power-up and engine starting . . . . . . . . . . . . . . . . . . –40 _C Minimum battery temperature (if battery is used for engine starting) . . . . . . . . . . . . . –20 _C NOTE
2 – 18
For starting with cabin temperatures below –40_C, contact Airbus Helicopters for special procedure.
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.9.5
Minimum cockpit temperature for IFR For proper operation of the GTN750 communication / navigation equipment: Minimum cockpit temperature (max 30 minutes) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . –40 _C
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Minimum cockpit temperature (continuous operation) . . . . . . . . . . . . . . . . . . . . . . . . . –20 _C
APPROVED Rev. 21
2 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.10
NR AND N2 LIMITATIONS 107.5 to 109% 108.3% 94%
ED
LL
0 to 50
–
Minimum transient
85
N
O
Power off min. continuous GM >2200kg GM 109% : fast beep (mutable)
113
>113% : fast beep (not mutable)
–
C
ST
R
U
Power off transient (max 12 s)
IN
R
ROTOR RPM
–
–
O N
O N
C
TI
High NR transient (max 12 s)
–
85 80
LY
Low NR transient (max 20 sec) NRmin is 3% below the nominal rotor speed or 94%, whichever is higher.
Power off max transient
O
–
Audio signal
N TR
PWR OFF [%]
O
PWR ON [%]
C
Rotor brake permitted
FO
101
T
NR Limit
2 – 20
113%
Rotor speed indication (color coding on FND and VMS)
O
Fig. 2-8
109 to 113%
BKD2_FLH_0401_R
85 to NRmin 85% GM>2200kg
– –
on the WU will be triggered, when NR: – 109%
N2 Limit
–
–
–
Minimum continuous
94
–
–
Maximum continuous
108.3
–
–
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.10.1
Rotor speed indication On FND
O N TR
101
C
O
Rotor speed indication in FND format (AEO)
O
T
Fig. 2-9
LL
BKD2_FLH_0401_R
ED
The rotor speed indication in FND–format displays the segment between 80% – 120% rotor speed (digital value with 1% resolution). This indication shows the engine parameter N2 (outer pointer) and the rotor speed (inner pointer)
LY
–
C
O
PY
N
The dedicated arc segment is filled if the rotor speed is within the associated range. Numerical value colour is displayed accordingly. When NR < 50% the numerical NR indication is shown with a white rectangle, to indicate that the rotor brake can be operated. Color indications and audio tones are suppressed during engine start, acceleration from IDLE to FLIGHT, and shutdown.
O N
On VMS
FO
R
IN
ST
R
U
C
TI
O N
The rotor speed indication in VMS-format (digital values with 0.1% resolution) displays the entire NR range and the digital N2 value below the rotor speed indication. This indication is the default after electrical power up and must be used for engine start.
(1)
86. Fig. 2-10
9
% N2 101. 0 %
BKD2_FLH_0010_R
100. 8
Rotor speed indication in VMS format (engine 1 in IDLE)
The white arc (1) indicates the operating range of the rotor brake (NR < 50%). APPROVED Rev. 21
2 – 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.11
ENGINE AND FLI, TQ, TOT AND N1 LIMITATIONS Turbomeca ARRIEL 2E
Engine:
2.11.1
FLI Limitations
O
LL
ED
The FLI shows the remaining power margin from any of the limiting parameters (torque, TOT or N1) with respect to the current collective lever position. The indications differ between AEO and OEI.
N TR
AEO indications: – Red teardrop:
O
D Transient limit: Unintended power applications up to the transient limit are permitted for a maximum duration of 12 seconds. Each exceedance of the transient limit requires maintenance action and must be recorded in the aircraft logbook.
PY
N
O
T
C
6
C
4
O
– Red line:
O N
– Amber rectangle: D Takeoff power rating: Use limited to maximum 30 minutes
C
TI
O N
2
FO
R
IN
ST
R
U
BKD2_FLH_0402_R
LY
–
D Maximum power limit: Exceeding the maximum power limit by more than 2% torque will sound a dedicated audio tone
NOTE: D 90 seconds before the 30 minute rating expires, a white counter will be displayed D When the aircraft is torque limited, the amber rectangle gradually disappears between VY+5kt and VY+20kt. – Below amber rectangle: D Continuous operation. – Blue line: D OEI power limit: Shows the maximum power that will be available at the OEI 30 second limit in case of a sudden engine failure. – White dashed line: D Desynchronization line (if the collective is lowered below this line, NR may increase).
2 – 22
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
OEI indications (red OEI flag indicated): NOTE
10
Except in emergency, the use of OEI 2 min / 30 sec power range is prohibited.
– Upper red line: D Topping signal: NOTE: A red triangle next to the limit indicates the active topping limit.
8
D OEI 30 sec power limit: Exceedance of this limit is automatically inhibited by the FADEC.
LL
BKD2_FLH_0403_R
ED
OEI
O
6
O
N TR
– Red hatched rectangle (not shown, only appears if power is above 2 min power limit):
C
O
PY
N
O
T
C
D OEI 30 sec power rating: Use of the 30 sec power rating is limited to 30 seconds. A red timer indicates use of this rating. The timer flashes 5 seconds before reaching the 30 seconds. Use and duration of the OEI 30 sec rating must be recorded in the aircraft logbook.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
– Lower red line: D OEI 2 min power limit: Exceedance of this limit is automatically inhibited by the FADEC, but only if the topping is set to the 2 min power limit.
– Amber hatched rectangle (only appers if the power is above the OEI continuous limit): D OEI 2 min power rating: Use of the OEI rating is limited to a total of 2.5 minutes (this includes the time used in the 30 sec range). An amber timer indicates use of this rating. The timer flashes 5 seconds before the end of the 2.5 minute period. Use and duration of the OEI 2 min rating must be recorded in the aircraft logbook. – Amber line: D
APPROVED Rev. 21
OEI continuous limit
2 – 23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Torque limitations 1
2
3 1 2 (2)
Torque (1)
Max continuous
2 x 74 %
Takeoff power (v30 min )
2 x 95 % below VY+5kt Above VY+5kt, see Fig. 2-11
TRQ
BKD2_FLH_0059_R _R
AEO Limitations
3
2 x 104.5 % below VY+5kt Above VY+5kt, see Fig. 2-11
N TR
O
LL
68. 0 %
Transient limit (unintended use)
ED
2.11.2
C
O
1) In AEO, the torque of one engine is allowed to exceed the given MCP resp. TOP limit value by up to 3% as long as the average torque of both engines is below 74% resp. 95%.
104.5
C
O
PY
N
O
T
2) In accordance with Fig. 2-11, the amber range will gradually disappear above VY+5kt. The red line and red teardrop will move accordingly. Above VY+20kt, the torque indication will be as shown in Fig. 2-12.
LY
–
Transient
95
Transient
C
TI
O N
O N
79 74
MCP
ST IN R FO
BKD2_FLH_0396_R
R
U
Torque – %
TOP
VY
Fig. 2-11
2 – 24
VY+10 VY+20 IAS – kt
VY+30
AEO torque limitations as a function of airspeed
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
BKD2_FLH_0059_R
TRQ
Fig. 2-12
59. 5 %
AEO torque limitations as a function of airspeed – IAS > VY+20 kt
LL
OEI Limitations
Torque
Max continuous
2
2 min power
3
30 sec power
O
1
N TR
O
2
1 x 100 %
T O
1 x 130 %
C
O
PY
128.0 %
N
TRQ
1 x 150 %
–
B BKD2_FLH_0060_ 0_R
C
1
ED
TU206 NOT installed
EFFECTIVITY
O N
LY
3
OEI Limitations
Torque
1
Max continuous
1 x 100 %
2
2 min power
1 x 143 %
3
30 sec power
1 x 150 %
TI
2
IN
R
TRQ
128.0 %
FO
B BKD2_FLH_0060_ 0_R
ST
R
U
C
1
O N
TU206 installed or after Helionix Maintenance Release 1
EFFECTIVITY
3 EFFECTIVITY
APPROVED Rev. 21
All
2 – 25
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.11.3
TOT limitations TOT
1
Continuous starting
760 _C
TOT
2
Starting transient (max. 10 sec)
840 _C (3)
O
LL
740 _c
ED
Starting Limitations (START label indicated)
2
N TR
BKD2_FLH_0061_R
1
N
PY
AEO Limitations
3 1
Max continuous
2
Takeoff power (v30 min)
O
2
TOT 901 _C
585_c
–
LY
Transient limit (unintended use)
945 _C (5)
C
TI
O N
3
O N
TOT
918 _C
U
BKD2_FLH_0062_ 2_R
C
1
O
T
C
O
3) When TOT reaches 840_C an automatic stop function interrupts the starting procedure. In the case of automatic stop, inspect the engine in accordance with the engine maintenance manual.
BKD2_FLH_00 0063_R
FO
1
R
IN
ST
R
4) An AEO transient limit of 945 _C is available for unintended use for a maximum duration of 20 sec. 2
OEI Limitations
TOT
1
Max continuous
945 _C
2
2 min power
987 _C
3
30 sec power
1006 _C
3
TOT
940_c
NOTE D The FADEC automatically records any limit exceedance. Transient TOT values slightly above the limits are allowed and will not be recorded.
2 – 26
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
D Record the duration of each use of the OEI 2 min and/or 30 sec rating in the aircraft logbook. After a maximum total of 10 minutes in the 2 min rating or 30 seconds in the 30 second rating, maintenance action is required. N1 limitations AEO Limitations
N1 (5)
1
Max continuous
98.5 %
2
Takeoff power (v30 min)
100.6 %
3
Transient limit (unintended use)
3
ED
2
(6)
O
101.7 %
C
89. 0 %
N TR
O
N1
T
BKD2_FLH_0064 64_R
1
LL
2.11.4
O
PY
N
O
5) The displayed N1 speed limits are functions of altitude and OAT, the table shows the upper limits only. The limits are calculated and presented in the FLI indication by the needle position and in the color of the N1 digital value.
2
OEI Limitations
3
O N
1
LY
–
C
6) An AEO transient limit of 101.7% (or the value calculated as a function of altitude and OAT) is available for unintended use for a maximum duration of 20 sec.
Max continuous
101.7 %
2
2 min power
104.3 %
3
30 sec power
105.7 %
U R ST
N1
R
IN
103. 0 %
FO
BKD2_FLH_00 0065_R
C
TI
O N
1
N1 (6)
NOTE D The FADEC automatically records any limit exceedance. Transient N1 values slightly above the limits are allowed and will not be recorded. D Record the duration of each use of the OEI 2 min and/or 30 sec rating in the aircraft logbook. After a maximum total of 10 minutes in the 2 min rating or 30 seconds in the 30 second rating, maintenance action is required.
APPROVED Rev. 21
2 – 27
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.12
OTHER ENGINE AND TRANSMISSION LIMITATIONS
2.12.1
Engine oil temperature and pressure Minimum oil pressure (low red limit) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.5 – 3.3 bar
(1)
Low amber limit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.25 – 4.2 bar
(1)
Maximum oil pressure (high red limit) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 – 12 bar
(1)
Minimum oil temperature at power application with 3 cSt oil . . . . . . . . . . . . . . . . . . . . –10°C Minimum oil temperature at power application with 5 cSt oil . . . . . . . . . . . . . . . . . . . . . . 0°C
ED
Low amber limit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0°C
LL
Maximum oil temperature (high red limit) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 117°C
O
Minimum for starting:
N TR
Oil viscosity 3 cSt . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . -45°C
C
O
Oil viscosity 5 cSt . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . -30°C
C
–
LY 72
TI
Engine oil temperature and pressure indications
R
FADEC operating modes
ST
2.12.2
U
C
Fig. 2-13
3.7
O N
O N
BKD2_FLH_0006_R
O
PY
ENG OIL B °C A R
N
O
T
(1) The limits are automatically calculated by the FADEC and displayed.
R
IN
Usage of FADEC EMER mode on both engines simultaneously is not permitted.
FO
Usage of FADEC EMER mode is not permitted during engine start (except in accordance with specific MMEL or maintenance procedures), in training mode, or in OEI.
2 – 28
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.12.3
Engine starter/generator Minimum battery capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 Ah Max ground power unit (24 V - 29 V) current . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 800 A To avoid starter overheat damage, the following must be observed: Between starting/ventilation attempts, a 60 second waiting time shall be observed.
–
Maximum ventilation time: 20 seconds (with battery) or 15 seconds (with EPU).
–
After 3 starting/ventilation attempts, a waiting period of 30 minutes shall be observed.
–
When the caution STARTER ON appears on the master list, abort the start immediately.
O
Generator
N
2.12.4
T
C
Ventilating both engines simultaneously is prohibited.
O
N TR
O
LL
ED
–
PY
Maximum continuous load per generator below 15000 ft . . . . . . . . . . . . . . . . . . . . . . 200 A
C
O
Maximum continuous load per generator above 15000 ft . . . . . . . . . . . . . . . . . . . . . . 180 A
LY
–
Total maximum continuous load (from both generators operative) . . . . . . . . . . . . . . . 360 A
O N
2.12.4.1 Generator abnormal or failure indications
TI
O N
Ampere indication on VMS page: above Zp 15000 ft
> 300 A for more than 5 sec or > 200 A for more than 2 min
> 270 A for more than 5 sec or > 180 A for more than 2 min
> 200 A
> 180 A
R
FO
Amber
IN
ST
R
U
Red
below Zp 15000 ft
C
Value indication
Volt indication on VMS page:
Value indication red
Value > 31 V
amber
> 29.5 V
amber
< 24 V
red
APPROVED Rev. 21
< 21 V; < 12 V during engine start or during ventilation
2 – 29
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.12.5
Main transmission oil pressure and temperature Minimum oil pressure (lower red limit) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.7 bar - 1.0 bar
(1)
Caution oil pressure range (lower amber limit) . . . . . . . . . . . . . . . . . . . . . 1.0 bar - 1.3 bar
(1)
Continuous operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.3 bar - 5.0 bar Maximum operating pressure (upper red limit) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.0 bar Minimum oil temperature at power application (lower amber limit) . . . . . . . . . . . . . . . –10 °C Continuous operation temperature range . . . . . . . . . . . . . . . . . . . . . . . . . . . . –10 °C - 105 °C
ED
Maximum operating temperature (upper red limit) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105 °C (1)
O
PY
N
O
T
C
B A R
O
1.8 1.8 1.8 3030 1.8
LY
During sideward flight or sideways slope landing, the oil pressure in one system may fall below the normal range. This is acceptable for up to 7 minutes consecutively, provided the oil pressure of the other system is normal. The pilot will be alerted to this condition after 5 minutes by the MGB TREND alert and after 7 minutes by the MGB OVERLIMIT caution.
FO
R
IN
ST
R
U
C
TI
O N
NOTE
Main transmission oil pressure and temperature indications
O N
Fig. 2-14
–
C
BKD2_FLH_0008_R
°C
MGB OIL B A R
N TR
O
LL
The minimum and caution oil pressure limits are automatically calculated (depending on rotor speed)
2 – 30
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.12.6
Main rotor mast moment limits
2.12.6.1 Main rotor mast moment limits indications NOTE D The mast moment (MM) indication can be configured on the VMS CONF page (LINEAR or CIRCULAR ). D A numeric value of the mast moment (in %) is available on the VMS page in the STATUS area.
PY
Mast moment indicator on the FLI page – linear scale
O
Fig. 2-15
N
O
T
C
O
N TR
BKD2_FLH_0066_R
O
LL
ED
LINEAR: The mast moment magnitude is indicated using a nonlinear scale indication (e.g. amber area is expanded up).
O N
LY
–
C
CIRCULAR: Circular mast moment is indicated using a circular format that displays both direction and the mast moment magnitude including amber and red limits.
TI
O N
NOTE D If the mast moment direction signal is not available (e.g. when NR 66% – WHITE (end of scale): . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% A voice message “MAST MOMENT” is triggered when red limit is exceeded. APPROVED Rev. 21
2 – 31
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
The mast-moment indicator is displayed only when IAS < 50 kt and remains displayed until 55 kt is exceeded. If the mast moment exceeds a red limit or amber caution when IAS is above 50 kt, the mast moment indicator will appear momentarily. 2.12.7
Engine operating time Maximum consecutive operating time of the engines (FLIGHT or IDLE) is 12 hours.
2.13
FUEL LIMITATIONS
O
LL
Fuel Specification and Limitations
NATO CODE
USA
UK
FRANCE
Kerosene-50 (AVTUR/FS II) JP-8
F-34
MIL-DTL83133H Amendt 2
DEF STAN 91–87 Issue 6
DCSEA 134/C
JP-8+100
F-37
MIL-DTL83133H Amendt 2
–
Kerosene-50 (AVTUR) JET A1
F-35
ASTM D1655
Kerosene Jet-A
–
ASTM D1655
Jet-A + military additives of JP-8
F-24
F-24 + 100 (with additive NATO S-1749)
C
T
O
N
PY
With
DCSEA 134/C
Without
O
–
C –
O N
LY
DEF STAN 91–91
O N
With
–
–
With
C
TI
NATO standard: STANAG 3747 Issue 10
Without
U F-27
ST
IN
ORIGINAL ANTI-ICE ADDITIVES
NATO standard: STANAG 3747 Issue 10
With
XF-43
–
–
DCSEA 144/C
Without
High flash point Kerosene JP-5 (AVCAT FS II)
F-44
MIL-DTL5624V
DEF STAN 91–86 Issue 6
DCSEA 144/C
With
FO
R
High flash point Kerosene
P.R. Chinese Jet Fuel n_3 Russian TS-1 (TC-1), RT (PT) Ukrainian TS-1 (TC-1), RT (PT)
2 – 32
O
TYPE OF FUEL
R
2.13.1.1 Normal Unrestricted Fuel Specification
N TR
2.13.1
ED
Maximum fuel viscosity (all temperatures) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 cSt
–
China GB 6537-2006
Without
–
Russian Interstate standard GOST 10227-86 Ed 2008
Without
–
Industrial Standard of Ukraine TS-1(TC-1) GSTU 320.00149943.011-99 RT (PT) GSTU 320.00149943.007-97
Without
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
NOTE D Specifications ASTM D1655 and DEF STAN 91–91 apply at latest index, latest amendment inforce. For all other specifications the version of the specification to be used is explicitly mentioned in the table. Further evolutions of these specifications are only usable after AH agreement. D When using TS-1 or RT weight units (kg or pounds) shall be selected for fuel indication in HELIONIX. In case of volumetric units, the fuel indication will show less fuel than actually present.
LL
ED
Normally JP–5/JP–8/JP–8+100/F–24/F–27 fuels are preblended with anti-icing additives. It is the operator‘s responsibility to ensure that the fuel used contains an anti-icing addtive when necessary. Additional anti–icing additives shall not be added to pre-blended fuels.
N TR
–35_C
O
–40_C
54_C
T O
All normal fuels except RT and TS–1
N PY O C –
O N
LY
JET A, Jet A–1, XF–43, No.3 Jet Fuel, RT, TS–1
Anti–icing additives required for:
All normal fuels
0
–40
–20 0 Fuel temperature _C
20
40
60
FO
R
IN
–60
ST
R
U
C
TI
5000
All normal fuels
10000
O N
15000
No.3 Jet Fuel, Jet A–1, RT and TS–1 with ani–icing additive and JP–8, JP–8+100
Pressure Altitude (ft)
20000
BKD2_FLH_0053_R
50_C
C
–47_C
O
2.13.1.2 Normal Unrestricted Fuel Temperature Limitation
Fig. 2-17
Altitude and temperature limits for approved primary fuels
NOTE D For Jet A–1, Jet A, XF–43, No.3 Jet Fuel, RT and TS-1 the use of anti-icing additive is mandatory at fuel temperature below –20_C. JP–5, JP–8, JP–8+100, F–24 and F–27 are already mixed with anti-icing additive. D When no anti–icing additive was added to the fuel, the fuel temperature in the engine must be above 2.3_C before power is applied. This is automatically monitored by the FADEC and indicated through the ENG1 FUEL LOW TEMP ENG2
APPROVED Rev. 21
advisory (see section 3 para 3.8.3).
2 – 33
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
D To determine if the fuel temperature is within the permitted range, the pilot shall consider the following: –
The current OAT;
–
The ambient temperature of the aircraft during the last 12 hours (e.g. hangar temperature, overnight temperature);
–
The temperature of the fuel that was recently refuelled.
Be aware that fuel may take up to 12 hours to adopt the ambient temperature. In flight, the fuel temperature will follow the OAT very slowly.
N TR
O
LL
ED
If it cannot be determined with certainty that fuel temperature is within the required range, the actual fuel temperature shall be determined from a fuel sample taken immediately before the flight.
C
TU193 NOT installed
T
EFFECTIVITY
O
2.13.1.3 Replacement Fuel Specification
TU193 installed
O
EFFECTIVITY
PY
N
O
The use of replacement fuels, e.g. JP-4 and JET B, is prohibited.
Kerosene (Wide cut) JP-4
F-40
MIL-DTL5624V
Kerosene (Wide cut) JET B
–
FRANCE
ORIGINAL ANTI-ICE ADDITIVES
DEF STAN 91-88 Issue 4
–
With
–
–
Without
C
USA
UK
–
NATO CODE
O N
O N
LY
TYPE OF FUEL
R
U
C
TI
ASTM D6615
FO
R
IN
ST
NOTE D Specification ASTM D6615 applies at latest index, latest amendment inforce. For all other specifications the version of the specification to be used is explicitly mentioned in the table. Further evolutions of these specifications are only usable after AH agreement. D When using JP–4 or Jet B weight units (kg or pounds) shall be selected for fuel indication in HELIONIX. In case of volumetric units, the fuel indication will show less fuel than actually present.
2 – 34
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.13.1.4 Replacement Fuel Temperature Limitation –47_C
LL
ED
–40
–20
0
O
O
–60
T
C
0
All replacement fuels
N TR
5000
O
10000
Jet B
Anti-icing additive required for :
15000
All replacement fuels
Pressure Altitude (ft)
20000
20
40
60
N
Fuel temperature _C
PY
Altitude and temperature limits for replacement fuels
O
Fig. 2-18
LY
–
C
NOTE D For Jet B the use of anti-icing additive is mandatory at fuel temperature below –20_C . JP–4 is already mixed with anti-icing additive.
O N
O N
D To determine if the fuel temperature is within the permitted range, the pilot shall consider the following: The current OAT;
–
The ambient temperature of the aircraft during the last 12 hours (e.g. hangar temperature, overnight temperature);
U
C
TI
–
The temperature of the fuel that was recently refuelled.
FO
R
IN
ST
R
–
EFFECTIVITY
APPROVED Rev. 21
Be aware that fuel may take up to 12 hours to adopt the ambient temperature. In flight, the fuel temperature will follow the OAT very slowly. If it cannot be determined with certainty that fuel temperature is within the required range, the actual fuel temperature shall be determined from a fuel sample taken immediately before the flight.
All
2 – 35
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.13.2
Fuel additives Anti-icing fuel additives Fuel System Anti-Icing Additives/ Icing Inhibitors (FSII) Specifications
NATO symbol
USA
UK
FRANCE
DIEGME
S–1745
MIL-DTL-85470
DEF STAN 68-252 (AL–41)
DCSEA 745
FLUID “I”
–
ED
Type of additive
LL
Russian standard GOST 8313-88
N TR
O
When using fuels with an anti-icing additive (pre-blended or added), ensure that the following requirements are fulfilled:
C
O
Concentration by volume: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . max 0.15%, min 0.10%
N
O
T
NOTE D All other fuel additives require Airbus Helicopters Deutschland approval.
O
PY
D The chinese additives T1502, T1601 and T1602 are not approved for the use on the BK117 D–2.
O N
Fuel quantities
USABLE FUEL
O N
2.13.3
LY
–
C
Except for the Russia/CIS additives, all authorized additives can be intermixed.
kg*
777,8
FO
R
TOTAL FUEL
kg*
liters
kg*
622,2
5,0
4,0
782,8
626,2
59,0
47,2
3,75
3,0
62,75
67,0
53,6
3,25
2,6
903,8
723,0
12,0
9,6
U R
IN
Supply RH
ST
Supply LH
UNUSABLE FUEL liters
C
Main
Total
liters
TI
TANK
70,25 915,8
50,2 56,2 732,6
* Fuel mass in kg calculated with a fuel density of 0,8kg/liter ((8.018 lb/gal (imp.); 6.676 lb/gal (U.S.)). The usable fuel quantity is depleted when zero is indicated on the relevant fuel quantity gauge.
2 – 36
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.14
OIL LIMITATIONS
2.14.1
Oil specifications Equipment
Oil type
Engine
OAT limit*
MIL-PRF-23699 (5 cSt)
–30 °C to +50 °C –45 °C to +30 °C
MIL-PRF-7808 (3 cSt) ZFN L 3001
–45 °C
Tail rotor gearbox
ZFN L 3001
–45 °C
Main rotor hub
MIL-PRF-23699
LL C
–45 °C
T
All
O
EFFECTIVITY
ZFN L 3001
N TR
Main rotor hub
–45 °C
O
After SB MBB–BK117 D–2–62–011
O
EFFECTIVITY
ED
Main transmission
Do not mix different oil specifications when refilling.
–
Oil quantities
Liters
Kilograms 3.43 5.00 0.39
5.50
5.39
Main transmission
12.50
12.25
Tail rotor gearbox
0.75
0.64
1.90
1.86
IN
ST
R
U
C
TI
O N
3.50 5.10 0.40
R
Engines (each tank) Usable (min.) Usable (max) Unusable
O N
Equipment
LY
2.14.2
C
O
NOTE
PY
N
* Minimum temperature of the oil in case of cold start.
FO
Main rotor hub
Total
Oil mass values are based on an oil density of 0.98 kg/liter (20°C)
APPROVED Rev. 21
2 – 37
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.15
HYDRAULIC SYSTEM LIMITATIONS HYD TEST sw must not be operated during flight.
2.15.1
Hydraulic pressures bar bar bar bar bar
O
LL
ED
Minimum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69 Caution range . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69 bar to 90 Continuous operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90 bar to 120 Caution range (high pressure relief valve starts to open) . . . . . . . . . . . . . . . . . . . . . . . . . 120 bar to 122 Maximum (high pressure relief valve open with max fluid flow) . . . . . . . . . . . . . . . . 150
N TR O C T
O
N
105
PY
104
C
Hydraulic pressure indication
O N
Liters
Kilograms
1.2 1.2
1.02 1.02
U
C
Hydraulic system 1 Hydraulic system 2
O N
Hydraulic system quantities
TI
2.15.2
LY
–
Fig. 2-19
B A R
B A R
O
BKD2_FLH_0007_R
HYD
Hydraulic fluid
IN
2.15.3
ST
R
Oil mass values are based on an oil density of 0.85kg/liter (20_C).
FO
R
Hydraulic fluid type MIL-H-5606 is authorized for use at all ambient temperatures.
2 – 38
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
2.16
PLACARDS AND DECALS All placards shown below are usually presented in English. However, depending on national regulations, markings and placards intended for emergency passenger information and instruction, and instruction for operation of passenger doors may be provided in the local language.
ED
The following illustrations of placards and decals are typical presentations. Slight formal differences from the installed placards and decals do not affect the information presented therein.
O
LL
Placard:
PY
RH side of center spar
O
Location:
N
O
T
C
O
N TR
THIS HELICOPTER IS APPROVED FOR VFR DAY AND NIGHT OPERATION, AND FOR IFR OPERATION IN ACCORDANCE WITH THE APPROVED FLIGHT MANUAL
LY
–
C
Placard:
U
Center spar
ST
R
Location:
C
TI
O N
O N
THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED ROTORCRAFT FLIGHT MANUAL
FO
R
IN
Placard:
Location:
MAX. PERMISS. GROSS MASS 3700kg Below forward RH cabin door
Placard:
Location:
APPROVED Rev. 21
Cabin roof, sliding doors and windows at the rear part of the cabin (inside, LH and RH)
2 – 39
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Placard: FOR FUNCTIONAL TESTS DURING GROUND OPERATION APPLY ONLY SMALL CYCLIC STICK DISPLACEMENTS Location: Center spar
LL
ED
Placard:
O
N TR
O
OR
O
T
C
Location: Rotor brake lever
N
Placard:
C
O
PY
ATE DOT4 TYP SL Below rotor brake hydraulic fluid reservoir
O N
LY
–
Location:
O N
Placard: (optional)
U
C
TI
SAFETY CABLE – USE TO SECURE CREW MEMBERS (200 KG MAX.) Inside, near safety harness fitting
IN
ST
R
Location:
FO
R
Placard: (optional)
Location:
2 – 40
USE ONLY TO SECURE PERSONS (200 KG MAX.) Inside, near safety harness fitting
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
O
Cabin panelling, RH
C
Location:
N TR
O
LL
ED
Placard:
O
T
Placard:
–
Clamshell door inside
LY
Location:
C
O
PY
N
NO CARGO LOAD MUST PRESS AGAINST REAR DOORS
INTERCOM
R
Beside external power connection
ST
Location:
U
C
TI
O N
O N
Placard:
FO
R
IN
Placard:
SERVICING STARTING 28 VDC Location:
APPROVED Rev. 21
Beside external power connection
2 – 41
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Placard: OPEN
SLIDING DOOR OPEN
CLOSED Sliding doors, inside (LH) and outside (RH)
Location:
N TR
O
OPEN
SLIDING DOOR
LL
ED
Placard:
C
O
OPEN
PY
N
O
T
CLOSED
Sliding doors, inside (RH) and outside (LH)
C
O
Location:
LY
–
Placard:
TI
O N
O N
DO NOT OPERATE DOOR HANDLE DURING FLIGHT
Sliding door, inside, LH and RH and cockpit door LH
IN
FO
R
Placard:
ST
R
U
C
Location:
CLOSED POSITION Location:
2 – 42
Sliding doors, inside, and cockpit doors, inside
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Placard:
CLOSED
Location:
Cockpit doors (inside and outside)
ED
Placard:
Cockpit doors (inside and outside)
C
O
Location:
N TR
O
LL
OPEN
N
O
T
Placard:
PY
EMERGENCY EXIT
Outside, upper part LH and RH sliding door
FO
R
IN
U
ST
R
Placard:
C
TI
Location:
O N
O N
LY
–
C
O
REMOVE CAP PULL HANDLE PUSH WINDOW AT ONE MARKING ( ) INSIDE
Location:
APPROVED Rev. 21
EMERGENCY EXIT REMOVE CAP PULL HANDLE PUSH WINDOW AT ONE MARKING ( ) OUTSIDE
Inside, upper part LH and RH sliding door
2 – 43
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Placard:
Inside, upper part LH corner and RH corner of the sliding door window
Location:
and Outside, lower part LH corner and RH corner of the sliding door window
LL
ED
Location:
C
O
PY
N
O
T
C
O
N TR
O
Placard:
LY
–
Near fuel tank filler neck
Location:
FO
R
IN
ST
R
U
C
TI
O N
O N
Placard:
Location:
2 – 44
Near fuel tank filler neck
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Placard: DO NOT STOW ANYTHING UNDER THE SEATS Location:
L/H and R/H sliding door upper frames (cabin). Lower part of the seats (pilot and co-pilot seats
Placard:
LL O
On RH and LH pitot tubes support
N TR
Location:
ED
CAUTION HOT
–
C
O
PY
N
O
T
C
O
Placard:
O N
O N
Location: Grounding socket
LY
GROUND (EARTH) HERE
NO STEP
U
C
TI
Placard:
IN
ST
R
Location: Horizontal stabilizer, upper side, LH and RH
FO
R
Placard:
NO HANDLING
Location: Antenna cover on lower side of tailboom and horizontal stabilizer lower side
Placard:
HANDLE HERE Location: Tail skid
Placard:
NO PUSH Location: Vertical fin, lower center position
APPROVED Rev. 21
2 – 45
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Placard:
OIL ZFN L 3001 Location: Main gearbox filler neck, Tail gearbox
EFFECTIVITY
After SB MBB–BK117 D–2–62–011
ED
Placard:
O
LL
OIL IN USE:
C
O
N TR
ZFN–L–3001
O N
All
PY
EFFECTIVITY
T
Location: Main rotor head
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
Placard: (colour: RAL 2005 or 9005)
FO
Location: LH cockpit door, RH and LH sliding cabin door, outer door handle
2 – 46
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Placard: PRESSURE-TEMPERATURE CORRECTION TABLE –45
–29
–18
–7
+4
°F TEMP
–49
–20
0
+20
+40
122
148
174
207
249
149
180
212
251
299
°C TEMP
+16
+21
+27
+38
+49
°F TEMP
+60
+70
+80
+100
304
334
367
442
532
354
385
417
492
582
T
C
O
LL O
N TR
+120
N
IND PRESS
O
IND PRESS
ED
°C TEMP
C
O
PY
Location: RH Fairing near fire extinguisher bottles
ATTENTION HOT AIR KEEP NOZZLE FREE
R
IN
ST
R
U
C
TI
O N
O N
LY
–
Placard:
FO
Location: Air outlet beside RH/LH sliding door
Placard: (optional)
28V DC 15A Location: Beside power sockets, rear cabin
APPROVED Rev. 21
2 – 47
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Placard: (optional)
28V DC 20A Location: Beside power sockets, rear cabin
Placard: (optional)
N TR
O
LL
ED
MAX 250V MAX 16A
O
T
C
O
Location: Beside power sockets, Clam shell doors inside and outside
PY
N
Placard: (optional)
LY
–
C
O
DO NOT COVER
FO
R
IN
ST
R
U
C
TI
O N
O N
Location: Beside cargo compartment smoke detector
2 – 48
APPROVED Rev. 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
EFFECTIVITY
Before SB MBB- BK117 D- 2- 11- 007
Placard: (optional)
MAX.LOAD 8000N RH and LH cabin wall near forward and middle attachment points (refer to para 2.6.5)
Location:
LL
ED
Placard: (optional)
O
N TR
O
MAX.LOAD 2000N
RH and LH cabin wall near aft attachment points (refer to para 2.6.5)
After SB MBB- BK117 D- 2- 11- 007
PY
EFFECTIVITY
N
O
T
C
Location:
O
Placard: (optional)
O N
O N
LY
–
C
MAX. LOAD ACC. TO FLM SECTION 2
C U
All
ST
R
EFFECTIVITY
TI
RH and LH cabin wall near aft attachment points (refer to para 2.6.5)
Location:
IN
Placard: (optional)
FO
R
MAX.LOAD 5 kg
Location:
APPROVED Rev. 21
Beside cabin ceiling rails
2 - 49
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) LIMITATIONS
Placard: (optional)
MAX.LOAD 5 kg Beside cabin ceiling rails
Location:
EFFECTIVITY
If reinforced ceiling rails are installed
LL
ED
Placard: (optional)
O
T
Beside cabin ceiling rails
Location:
N
All
PY
EFFECTIVITY
C
O
N TR
O
MAX.LOAD 10 kg
–
C
O
Placard: (optional)
O N
O N
LY
MAX.LOAD 4 kg
Beside outer brackets on forward cabin frame
U
C
TI
Location:
FO
R
IN
ST
R
Placard: (optional)
Location:
MAX.LOAD 20 kg
Beside inner brackets on forward cabin frame
Placard: TILT ARMREST IN UPRIGHT POSITION FOR TAKE-OFF AND LANDING Location: Left side of co-pilot seat frame if armrest is installed
2 - 50
APPROVED Rev. 22
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
SECTION 3 EMERGENCY AND MALFUNCTION PROCEDURES TABLE OF CONTENTS Page
O
T
C
O
N TR
O
LL
ED
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Basic rules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Alerting system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Memory items . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operating condition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Urgency of landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Resetting tripped circuit breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Definition of terms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MMEL / MEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3 3 3 3 3 3 3 3 3
-
1 1 2 2 2 2 3 4 4
N
3.1 3.1.1 3.1.2 3.1.3 3.1.4 3.1.5 3.1.6 3.1.7 3.1.8
AFCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 5 Warning indications AFCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 5 AUTOPILOT (ML) and AP (WARNING UNIT) . . . . . . . . . . . . . . . . . . . . 3 - 5 3.2.2 Caution indications AFCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 8 AP ACTUATOR (one series actuator) . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 8 AP ACTUATOR (both series actuators of one axis) . . . . . . . . . . . . . . . . 3 - 9 AP CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 9 AP REDUNDANCY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 10 AP TRIM OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 11 BACKUP SAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 13 3.2.3 Emergency/malfunction conditions AFCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 14 3.2.3.1 Trim actuator runaway or stuck beep trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 14 3.2.3.2 Cyclic force trim release failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 14 3.2.3.3 Collective force trim release failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 14 3.2.3.4 Autopilot fly-up (from CRHT mode) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 15 FLYUP (AFCS STRIP) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 15 3.2.3.5 Autopilot decouple . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 15 3.2.3.5 Autopilot disarmed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 16 3.2.3.6 Collective lever position sensor failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 16 3.2.3.8 Degraded reliability of displayed AFCS data . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 17 3.2.3.9 Excessive deviation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 17 3.2.3.10 Yaw series actuator saturation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 18 3.2.3.11 Pitch series actuator saturation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 19 3.2.3.12 Roll series actuator saturation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 19 3.2.3.13 Collective series actuator saturation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 20 3.2.3.14 Upper mode override . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 20
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3.2 3.2.1
APPROVED Rev. 22
3- i
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
Page 3.3 3.3.1
AVIONICS AND DISPLAYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 21 FND warning indications AVIONICS AND DISPLAYS . . . . . . . . . . . . . . . . . . 3 - 21
3.3.1.1 HTAWS warning (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL UP alternating with TERRAIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL UP alternating with OBSTACLE . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.2 Caution indications AVIONICS AND DISPLAYS . . . . . . . . . . . . . . . . . . . . . . AIR1 or 2 DATA FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AIR1 and 2 DATA FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Before Helionix Maintenance Release 1
3 - 22 3 - 22 3 - 22
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AMC1 or 2 CHAN A FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 23 AMC1 or 2 CHAN A FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 24
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AMC1 or 2 CHAN B FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 26
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28 29 29 30
3 - 31 3 - 31 3 - 31 3 - 32 3 - 32
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ATT1 or 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ATT1 and 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUDIO ALERT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MM EXCEEDED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.3 FND caution indications AVIONICS AND DISPLAYS . . . . . . . . . . . . . . . . . . 3.3.3.1 HTAWS caution (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TERRAIN OR OBSTACLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.3.2 Air data discrepancy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3.3.3.3 Heading discrepancy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 33 HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 33 3.3.3.4 SVS failure (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 33 SVS FAIL or SVS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 33 3.3.3.5 Radar altimeter failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.3.6 VNE indication failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK VNE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.4 White advisories AVIONICS AND DISPLAYS . . . . . . . . . . . . . . . . . . . . . . . . . DATA CARD FULL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DATA CARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DATABASE EXPIRED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWNLOAD FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3 - ii
3 3 3 3 3 3 3 3
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34 35 35 36 36 36 37 37
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
Page FDRS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLT REPORT OVLIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FMS1 or FMS2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HDG1 or 2 MAG HDG FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HDG1 and 2 MAG HDG FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IESI AIR DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IESI ATT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IESI FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MFD XTALK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
38 38 39 40 40 41 41 41 42
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TAWS DEGRADED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 43
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HTAWS DEGRADED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 43
After Helionix Maintenance Release 1
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TAWS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 44
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HTAWS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 44
After Helionix Maintenance Release 1
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TAWS TERR INHIB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 45
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HTAWS TERR INHIB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 45
Emergency/malfunction conditions AVIONICS AND DISPLAYS . . . . . . . . . 3 – 47
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3.3.5.1 Loss of MFD1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 47
IN
3.3.5.2 Loss of MFD2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 49
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3.3.5.3 Loss of MFD4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 51 3.3.5.4 Mast moment indication failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 52 3.3.5.5 Static system failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 53 3.3.5.6 Magnetic heading degraded . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 55
3.3.5.7 Color failure on MFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 56 3.3.5.8 Black or abnormal SVS colors (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 56 3.4
CLIMATE CONTROL AND ICING PROTECTION . . . . . . . . . . . . . . . . . . . . . 3 – 57
3.4.1
Caution indications CLIMATE CONTROL AND ICING PROTECTION . . . AVIONICS OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HEATING FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HEATING OVERTEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MFD OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
APPROVED Rev. 9
3 3 3 3 3
– – – – –
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3 – iii
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
Page PITOT1/2 HEATER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 59 PITOT1/2 HEATER OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 59 PITOT1/2 STAT HTR FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 60 3.4.2 Malfunction conditions climate control and icing protection . . . . . . . . . . . . . 3 – 60 3.4.2.1 Electrical heater failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 60 61 61 61 61
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COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 62 Intercom and audio system (DVCS6100) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 62
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3.4.2.2 GTN overtemp or cooling failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MSG (FND/NAVD) and MSG (GTN) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.2.3 VHF COM radio overheating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MSG (FND/NAVD) and MSG (GTN) . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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3.5.2.1 Transponder failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 63 3.5.2.2 Loss of ADS–B out function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 64 3.5.3 VHF COM radio (GTN750) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 65
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3.5.3.1 VHF COM failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 65 3.5.3.2 GTN touchscreen failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 66
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3.5.4 VOR/ILS navigation (GTN750) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.4.1 VOR/LOC/ILS failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.4.2 Glideslope and/or localizer discrepancy during final approach . . . . . . . . . . GPS or ILS and/or GPS or LOC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.5 GPS navigation and flight management system (GTN750) . . . . . . . . . . . . .
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3.5.5.1 Loss of GPS integrity on both GTN units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MSG (FND/NAVD) and LOI (GTNs) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.5.2 Approach downgraded from LPV and LNAV/VNAV to LNAV . . . . . . . . . . . . MSG (FND/NAVD) and MSG (GTN) . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3– 3– 3– 3– 3–
68 68 69 69 70
3– 3– 3– 3–
70 70 72 72
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3.5.5.3 GTN crossfill function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 –73 MSG (FND/NAVD) and MSG (GTN) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 73
3 – iv
3.6 3.6.1
DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Caution indications DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EPU DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOOR OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3 3 3 3
– 74 – 74 – 74 – 74
3.7 3.7.1
ELECTRICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 75 Warning indications ELECTRICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 75 BAT OVERHEAT (ML) and BAT OVHT (WARNING UNIT) . . . . . . . . 3 – 75
3.7.2
Caution indications ELECTRICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 77 BAT DISCHARGING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 77 BAT DISCONN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 78 APPROVED Rev. 16.2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
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ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 87 Warning indications ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 87 ENG1 and 2 FAIL (ML) and ENG1 and 2 FAIL (WARNING UNIT) . . 3 – 87 ENG1 or 2 FAIL (ML) and ENG1 or 2 FAIL (WARNING UNIT) . . . . . 3 – 88 Single engine failure – HIGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 89 Single engine failure – HOGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 90 Single engine failure – takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 91 Single engine failure – flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 91 Caution indications ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 92 ENG1 or 2 CHIP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 92 ENG1 or 2 FADEC EMER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 93 ENG1/2 FUEL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 94 ENG1/2 FUEL VALVE CLSD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 94 ENG1/2 FUEL VALVE POS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 95 ENG1/2 IDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 95 ENG1/2 OIL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 96 ENG1/2 OIL HIGH PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 96 ENG1/2 OIL HIGH TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 97 ENG1/2 OIL LOW PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 98 ENG1/2 OIL OVERLIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 99 ENG1/2 OVERSPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 100 ENG1/2 STARTER ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 101 ENG1/2 USAGE EXPIRED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 102 FADEC1/2 DEGRADED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 103 FADEC 1/2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 104 FADEC 1/2 N2 DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 105 TRAINING ABORTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 106 White advisories ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 107 ENG1/2 CHIP SENSOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 107 ENG1/2 FUEL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 107 ENG1/2 FUEL LOW TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 108 ENG1/2 OIL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 108 ENG1/2 OVSPD PROT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 109 ENG1/2 SERVICE NEEDED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 109
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ELEC OVERLIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER SHED BUS ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EPU CONNECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GEN1 or 2 DISCONNECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GEN1 and 2 DISCONNECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GEN1 or 2 OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INVERTER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY BAT DISCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY BAT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SYS1 and/or 2 BUS TIE OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . White advisories ELECTRICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REAR PANEL C/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3.8.3
APPROVED Rev. 13
3–v
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
Page ENG TREND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 110 FADEC1/2 REDUNDANCY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 110 FADEC1/2 SIGNAL FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 111 3.8.4
Emergency/malfunction conditions ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 112
3.8.4.1 Double engine emergency shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 112 3.8.4.2 Autorotation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 112 3.8.4.3 Single engine emergency shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 113 3.8.4.4 Inflight restart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 115
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3.8.4.5 Single engine landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 115
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3.8.4.6 FLI degraded . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 116
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3.8.4.8 Abnormal engine governing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 117 FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 118
3.9.1
Warning indications FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 118 CARGO SMOKE (ML and WARNING UNIT) . . . . . . . . . . . . . . . . . . . . 3– 118 ENG1 or 2 FIRE (ML) and FIRE (WARNING UNIT) . . . . . . . . . . . . . . 3– 119
3.9.2
Caution indications FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 121 FIRE BOT 1 or 2 or 1+2 USED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 121
3.9.3
Emergency conditions FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 122
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3.10.1
Warning indications FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 125 FUEL1/2 LOW (ML) and LOW FUEL1/2 (WARNING UNIT) . . . . . . . 3– 125
3.10.2
Caution indications FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– AFT FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– AFT+FWD FUEL PMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– FUEL QTY DEG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– FUEL QTY FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3–
EFFECTIVITY
127 127 128 129 130
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FUEL RESERVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 131
After Helionix Maintenance Release 1 FUEL RESERVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 133
EFFECTIVITY
All FUEL1/2 PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– FUEL1/2 PRIME PUMP ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– FWD FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– JET FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3–
EFFECTIVITY
134 134 135 135
After Helionix Maintenance Release 1 WEIGHT EXCEEDED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 136
3 – vi
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EFFECTIVITY
Before Helionix Maintenance Release 1 MAIN FUEL FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 137
EFFECTIVITY
After Helionix Maintenance Release 1 MAIN FUEL FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 137
EFFECTIVITY
All
3.11
GEARBOX AND DRIVE SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 138
3.11.1
Failure conditions TAIL ROTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 138
3.11.1.1 Tail rotor drive failure – hover . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 138 Warning indications GEARBOX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 140 MGB LOW PRESS (ML) and MGB OIL P (WARNING UNIT) . . . . . . 3– 140
3.11.3
Caution indications GEARBOX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– MGB CHIP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– MGB HIGH TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– MGB OVERLIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– ROTOR BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– TGB CHIP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3–
141 141 141 142 142 143
3.11.4
White advisories GEARBOX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– MGB CHIP SENSOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– MGB TREND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– TGB CHIP SENSOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3–
144 144 144 145
3.12
HYDRAULICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 146
3.12.1
Caution indications HYDRAULICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– HYD1 or 2 LOW PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– HYD OVERLIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– HYD1 TR SHUT OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3–
3.12.2
White advisories HYDRAULICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 148 HYD TREND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 148
146 146 146 147
LIGHT AND MEDIUM HELICOPTER ACTIVE VIBRATION CONTROL SYSTEM (LAVCS) . . . . . . . . . . . . . . . . . 3– 149 LAVCS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 149
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APPROVED Rev. 9
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SECTION 3 EMERGENCY AND MALFUNCTION PROCEDURES INDEX OF INDICATIONS Page
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WARNING LIGHTS ON WARNING UNIT AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 4 BAT OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 75 CARGO SMOKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 117 ENG1 and 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 87 ENG1 or 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 88 FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 119 LOW FUEL1/2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 125 MGB OIL P . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 140 ROTOR RPM (in conjunction with ENG1 and 2 FAIL) . . . . . . . . . . . . . 3 - 80
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Before Helionix Maintenance Release 1 AMC1 or 2 CHAN A FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 22
EFFECTIVITY
After Helionix Maintenance Release 1
EFFECTIVITY
AMC1 or 2 CHAN A FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 23 Before Helionix Maintenance Release 1
EFFECTIVITY
AMC1 or 2 CHAN B FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 24 After Helionix Maintenance Release 1 AMC1 or 2 CHAN B FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 25
EFFECTIVITY
Before Helionix Maintenance Release 1 AMC1 or 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 26
EFFECTIVITY APPROVED Rev. 22
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AP ACTUATOR (one series actuator) . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 7 AP ACTUATOR (both series actuators of one axis) . . . . . . . . . . . . . . . 3 - 8 AP CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 9 AP REDUNDANCY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 10 AP TRIM OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 11 ATT1 or 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 27 ATT1 and 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 28 AUDIO ALERT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 28 AVIONICS OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 57 BACKUP SAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 13 BAT DISCHARGING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 77 BAT DISCONN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 78 DOOR OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 74 ELEC OVERLIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 78 EMER SHED BUS ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 79 ENG1 or 2 CHIP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 92 ENG1 or 2 FADEC EMER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 93 ENG1/2 FUEL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 94 ENG1/2 FUEL VALVE CLSD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 94 ENG1/2 FUEL VALVE POS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 95 ENG1/2 IDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 95 ENG1/2 OIL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 96 ENG1 or 2 OIL HIGH PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 96 ENG1 or 2 OIL HIGH TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 97 ENG1 or 2 OIL LOW PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 98 ENG1/2 OIL OVERLIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 99 ENG1/2 OVERSPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 100 ENG1/2 STARTER ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 101 ENG1/2 USAGE EXPIRED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 102 EPU CONNECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 80 EPU DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 74 FADEC 1/2 DEGRADED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 103 FADEC 1/2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 104 FADEC 1/2 N2 DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 105 FIRE BOT 1 or 2 or 1+2 USED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 121 FUEL QTY DEG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 129 FUEL QTY FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 130
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Before Helionix Maintenance Release 1 FUEL RESERVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 131
EFFECTIVITY
After Helionix Maintenance Release 1 FUEL RESERVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 133
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All FUEL1/2 PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 134 FUEL1/2 PRIME PUMP ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 134 FWD FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 135
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Page CAUTION INDICATIONS (ML) (CONTINUED)
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GEN1 and 2 DISCONNECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 81 GEN1 or 2 DISCONNECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 80 GEN1/2 OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 83 HEATING FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 57 HEATING OVERTEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 58 HYD OVERLIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 146 HYD1 TR SHUT OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 147 HYD1 or 2 LOW PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 146 INVERTER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 75 JET FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 135 MFD OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 58 MGB CHIP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 141 MGB HIGH TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 141 MGB OVERLIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 142 MM EXCEEDED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 29 PITOT1/2 HEATER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 59 PITOT1/2 HEATER OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 59 PITOT1/2 STAT HTR FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 60 ROTOR BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 142 STBY BAT DISCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 84 STBY BAT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 84 SYS1/2 BUS TIE OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 85 TGB CHIP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 143 TRAINING ABORTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 106 After Helionix Maintenance Release 1
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CAUTION INDICATIONS (FND) AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK VNE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBSTACLE (if HTAWS is installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . SVS FAIL or SVS (if SVS is installed) . . . . . . . . . . . . . . . . . . . . . . . . . . TERRAIN (if HTWAS is installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3 – 35 3 – 28 3 – 32 3 - 30 3 – 33 3 - 30
WHITE ADVISORIES (ML) DATA CARD FULL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 36 DATA CARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 36 DATABASE EXPIRED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 37 DOWNLOAD FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 37 ENG1/2 CHIP SENSOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 107 ENG1/2 FUEL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 107 ENG1/2 FUEL LOW TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 108 ENG1/2 OIL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 108 APPROVED Rev. 9
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After Helionix Maintenance Release 1
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ENG1/2 OVSPD PROT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 109 ENG1/2 SERVICE NEEDED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 109 ENG TREND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 110 FADEC1/2 REDUNDANCY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 110 FADEC1/2 SIGNAL FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 111 FDRS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 38 FLT REPORT OVLIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 38 FMS1 or FMS2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 39 HDG1 and 2 MAG HDG FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 40 HDG1 or 2 MAG HDG FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 40
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HYD TREND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 148 IESI AIR DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 41 IESI ATT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 41 IESI FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 41 LAVCS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3– 149
After Helionix Maintenance Release 1
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MFD XTALK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 42 MGB CHIP SENSOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 144 MGB TREND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 144 REAR PANEL C/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 – 78
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TAWS DEGRADED (if HTAWS is installed) . . . . . . . . . . . . . . . . . . . . . . 3 - 43 TAWS FAIL (if HTAWS is installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 44 TAWS TERR INHIB (if HTAWS is installed) . . . . . . . . . . . . . . . . . . . . . . 3 - 44
All TGB CHIP SENSOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 145 VMS SENSOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 - 46
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SECTION 3 EMERGENCY AND MALFUNCTION PROCEDURES
3.1
GENERAL
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This section contains the recommended procedures for managing various types of emergencies, malfunctions and critical situations. Alerts related to the (semi-)automatic system tests are detailed in Sect. 4. AFTER AN ACTUAL EMERGENCY OR MALFUNCTION MAKE AN ENTRY IN THE HELICOPTER LOGBOOK AND, WHEN NECESSARY, THE AFFECTED SYSTEM LOGBOOK (E.G. ENGINE LOGBOOK). MAINTENANCE ACTION MAY BE REQUIRED AND NECESSARY BEFORE NEXT FLIGHT.
CAUTION
TO EXPEDITE EMERGENCY EGRESS, IF TIME PERMITS, THE COPILOT’S ARMREST WITH MISSION EQUIPMENT (IF INSTALLED) SHOULD BE STOWED AS SOON AS AN EMERGENCY SITUATION REQUIRING A LANDING ARISES.
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WARNING
Basic rules
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These procedures deal with common emergencies. The pilot may deviate from these procedures if judged necessary under the given circumstances (specific failure condition, outside factors, and type of terrain overflown).
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APPROVED Rev. 22
It is impossible to establish a predetermined set of instructions which would provide a ready-made decision applicable to all situations.
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3.1.2
Alerting system Alerts in the master list are categorized as Warning, Caution or Advisory Alert. All Warnings are duplicated on the warning unit. Warning (red): indicates a condition which requires immediate crew awareness and immediate crew response. Caution (amber): indicates a condition which requires immediate crew awareness and possibly subsequent (but not immediate) crew response.
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Advisory alert (white): indicates a condition which requires crew awareness and may require monitoring by the crew. A crew response is not required. In some cases, maintenance may be necessary before further flights are possible.
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Takeoff with a warning, caution, or advisory alert is generally not permitted, except when this is stated explicitly in the flight manual and/or MMEL/MEL.
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Emergency procedure steps which shall be performed immediately without reference to either this manual or the pilot’s checklist are written in boldface letters on a gray background (as shown here) and shall be committed to memory.
Operating condition
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Therefore, those emergency procedures appearing without boldface letters on a gray background may be accomplished referring to this manual and when time and situation permit.
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The following terms are used in emergency procedures to describe the operating condition of a system, subsystem, assembly or component:
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Operates in the normal or usual manner
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Urgency of landing The type of emergency and the emergency conditions combined with the pilot’s analysis of the condition of the helicopter and his proficiency are of prime importance in determining the urgency of a landing.
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Fails to operate in the normal or usual manner
The following terms are used to reflect the degree of urgency of an emergency landing: LAND IMMEDIATELY The urgency of landing is paramount. Primary consideration is to assure survival of the occupants. Landing in water, trees or other unsafe areas should be considered only as a last resort. In IMC, an ATC assisted emergency descent even below MSA should be established - providing terrain and traffic situation permits - to attain VMC conditions, in order to perform an immediate landing.
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LAND AS SOON AS POSSIBLE (LAND ASAP) Land without delay at the nearest adequate site (i.e. open field) at which a safe approach and landing can be made. In IMC, establish a radar assisted emergency descent to MSA / MRVA to attain VMC and land at the nearest adequate landing site. If VMC cannot be achieved: proceed to the nearest airfield, which provides an instrument approach, where weather conditions allow a safe landing. LAND AS SOON AS PRACTICABLE
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The landing site and duration of flight are at the discretion of the pilot. Extended flight beyond the nearest approved landing area where appropriate assistance can be expected is not recommended.
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Resetting tripped circuit breakers
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In case of IFR, continue to the original destination or - if possible - proceed to a closer alternate where an IFR approach is available.
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There is a latent danger in resetting a circuit breaker (cb) tripped by an unknown cause because the tripped condition is a signal that something may be wrong in the related circuit. Until the root cause of the tripped cb was determined, crew members have no way of knowing the consequences of resetting a tripped cb.
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A cb tripped by an unknown cause may only be reset on the ground after maintenance has determined the root cause of the trip and has determined that the cb may be safely reset. A cb may be cycled (tripped, pulled or reset) where it is required to be performed within approved maintenance inspection criteria, or as part of an approved trouble-shooting procedure, unless doing so is specifically prohibited. Resetting a cb tripped by an unknown cause, should normally be a maintenance function conducted on the ground.
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In-Flight:
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A tripped cb shall not be reset in flight unless doing so is consistent with explicit procedures specified in the approved Flight/Maintenance Manual, its supplements and checklists used by the crew members or unless, in the judgment of the pilot-in-command, resetting the cb is necessary for the safe completion of the flight. Crew members should limit resetting of cb‘s to one in-flight reset where this action is required. No attempt should be made to reset a cb if it trips a second time. Logbook entry: A detailed logbook write-up is a proven safety practice.
APPROVED Rev. 22
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3.1.7
Definition of terms The term “OEI flight condition ....- Establish” is used as a leading step in some engine emergency procedures to express the following: - Maintain the normal engine within OEI limits.
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- Continue with the remaining steps of the relevant procedure.
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- Attempt to obtain a safe single engine flight condition. If a climb is necessary to reach a safe flight altitude, attempt to obtain Vy (best rate of climb) or 45 kts (best climb gradient speed).
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C
O
The MMEL / MEL specifies if a flight may be commenced in case of inoperative, malfunctioning, or missing equipment. Specific procedures, maintenance actions, or conditions as defined in the MMEL / MEL may be required for flights with inoperative equipment. The MMEL / MEL should be carried in the helicopter to ensure that subsequent flights can be safely conducted in case of equipment malfunction or failure.
3- 4
APPROVED Rev. 22
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.2
AFCS A detailed autopilot status can be seen on the VMS SYSTEM page. The following colors are used to indicate the state of the various sub-systems:
NOTE
D Green: The affected system is fully operational. D Cyan: The affected system is operative in standby. D Red: A failure of the affected system was detected and the system was automatically shut down.
ED
D Amber: The affected system has partially failed.
3.2.1
N TR
O
LL
D Grey: The affected system is inoperative. Re-activation may be possible. Warning indications AFCS
AP
C
O
on Warning Unit for 10 sec
O
T
and
AUTOPILOT
PY
N
on ML
C
O
and audio tone and voice message “HANDS ON”
YR
P
then:
O N
AFCS DISENGAGED
SAS
SAS
AFCS DISENGAGED amber frames flashing for 10 sec, then off
C
TI
flashing for 10 sec
C
BKD2_FLH_0104_R
LY O N
C
–
Conditions/Indications - FND AFCS strip:
ST
TRIMS ACTUATORS
IN
AFCS
R
U
- VMS SYSTEM page: COLL
FO
R
PITCH
BACKUP AP1
AP2
ROLL YAW
BKD2_FLH_0105_R
CTRL PANEL
AP1
AP2
OFF
OFF
BKD2_FLH_0106_R
- APCP:
- Both autopilot systems are lost
APPROVED Rev. 22
AFCS
3- 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
Procedure 1. Flying controls
Before Helionix Maintenance Release 1 or before ASB MBB BK117 D-2- 42A- 004 (HELIONIX STEP 2.0.1)
After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2- 42A- 004 (HELIONIX STEP 2.0.1)
EFFECTIVITY
-
Re-engage (cyclic grip )
N TR
2. AP2 + AP1
LL
EFFECTIVITY
- Re-engage (cyclic grip AP/BKUP ON sw right then left (AP2 before AP1))
ED
2. AP2 + AP1
O
EFFECTIVITY
- Hands-on
All
C
O
If unsuccessful:
- Reduce to VNE AP OFF (110kt)
O
T
3. Airspeed
N
4. LAND AS SOON AS PRACTICABLE
C
O
PY
NOTE D The operating limitations for flight with BACKUP SAS (see Sect. 2, para 2.5.5.3) shall be observed, if possible.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
D Takeoff with the autopilot inoperative is permitted in VFR in accordance with the MMEL/MEL and within the limitations for flight without autopilot (see Sect. 2, para 2.5.5.3).
AFCS
3- 6
APPROVED Rev. 22
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.2.2
Caution indications AFCS
AP ACTUATOR and audio tone Conditions/Indications
XXX XXX
affected axis flashing in amber for 10 sec
XXX XXX
XXX
XXX
XXX
O
XXX
N TR
after 10 sec:
C
R without upper mode
N
O
T
with upper mode
PY
- VMS SYSTEM page: AFCS
affected axis displayed in amber
O
TRIMS ACTUATORS
C
COLL
CTRL PANEL
affected actuator displayed in red
ROLL YAW
O N
O N
AP2
BKD2_FLH_0110_R
LY
–
PITCH
BACKUP AP1
BKD2_FLH_0109_R
O
XXX
LL
XXX
ED
- FND AFCS strip:
C
TI
- Failure of one series actuator
IN
ST
R
U
Procedure 1. System performance
FO
R
EFFECTIVITY
Before Helionix Maintenance Release 1 or before ASB MBB BK117 D-2- 42A- 004 (HELIONIX STEP 2.0.1)
2. Affected axis
EFFECTIVITY
- Re-engage (cyclic grip AP/BKUP ON sw right then left (AP2 before AP1))
After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2- 42A- 004 (HELIONIX STEP 2.0.1)
2. Affected axis EFFECTIVITY
- Monitor (stabilization degraded on affected axis), especially in turbulence
-
Re-engage (cyclic grip )
All
If unsuccessful: 3. Continue flight (hands-on) if required APPROVED Rev. 22
AFCS
3- 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
AP ACTUATOR and audio tone and voice message “HANDS ON” Conditions/Indications - FND AFCS strip (example if upper modes engaged): XXX XXX
P
affected axis flashing in red for 10 sec
after 10 sec:
O
P
affected axis displayed in amber
ED
XXX
LL
AFCS
N TR
- VMS SYSTEM page: TRIMS ACTUATORS
O
COLL
C
CTRL PANEL
both affected actuator displayed in red
T
PITCH AP2
O
ROLL
N
BACKUP AP1
BKD2_FLH_0108_R
XXX
BKD2_FLH_0107_R
XXX XXX
PY
YAW
C
O
- Failure of both (series) actuators of one axis
LY
–
Procedure
Before Helionix Maintenance Release 1 or before ASB MBB BK117 D-2- 42A- 004 (HELIONIX STEP 2.0.1)
TI
O N
EFFECTIVITY
- Hands-on
O N
1. Flying controls
- Re-engage (cyclic grip AP/BKUP ON sw right then left (AP2 before AP1))
IN
After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2- 42A- 004 (HELIONIX STEP 2.0.1)
FO
R
EFFECTIVITY
ST
R
U
C
2. AP2 + AP1
2. AP2 + AP1 EFFECTIVITY
- Re-engage (cyclic grip)
All
If successful: 3. Continue flight If unsuccessful: 3. VMS / SYSTEM page
- Select
If both pitch actuators are affected: 4. Airspeed
- Reduce to 110 kt or below
5. LAND AS SOON AS PRACTICABLE AFCS
3- 8
APPROVED Rev. 22
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
AP CONTROL and audio tone Conditions/Indications - FND AFCS strip (only if engaged mode affected by failure): XXX
XXX XXX
XXX
affected axis flashing in amber for 10 sec
XXX XXX
XXX
XXX
O
R without upper mode
N TR
with upper mode
COLL
CTRL PANEL
PY
ROLL
or
AP2
PITCH
N
PITCH
O
CTRL PANEL
BACKUP AP1
TRIMS ACTUATORS
T
COLL
C
AFCS
TRIMS ACTUATORS
O
- VMS SYSTEM PAGE: AFCS
affected axis displayed in amber
ED
XXX
LL
XXX
BKD2_FLH_0109_R
after 10 sec:
BACKUP AP1
AP2
YAW
C
O
YAW
ROLL
LY
–
or AFCS
TI
AP2
COLL PITCH
affected AP control unit displayed in amber
ROLL YAW
R
U
C
BACKUP AP1
O N
CTRL PANEL
BKD2_FLH_0111_R
O N
TRIMS ACTUATORS
IN
ST
- Failure or partial failure of the autopilot control panel or of the autopilot function switches on the cyclic or collective grips
FO
R
Procedure EFFECTIVITY
Before Helionix Maintenance Release 1 or before ASB MBB BK117 D-2- 42A- 004 (HELIONIX STEP 2.0.1)
1. AP2 + AP1
EFFECTIVITY
- Re-engage (cyclic grip AP/BKUP ON sw right then left (AP2 before AP1))
After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2- 42A- 004 (HELIONIX STEP 2.0.1)
1. AP2 + AP1 EFFECTIVITY
-
Re-engage (cyclic grip )
All continued:
APPROVED Rev. 22
AFCS
3- 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
2. Continue flight NOTE D Autopilot hands-on attitude stabilization is not affected D Depending on affected autopilot control function, re-engagement of upper modes - once disengaged - may not be possible.
LL
ED
D The AP CONTROL caution may be triggered if conflicting trim inputs are given (e.g. opposing beep trim inputs on pilot and copilot side or force trim release and beep trim input simultaneously).
N TR
O
AP REDUNDANCY
C
O
and audio tone
O
T
Conditions/Indications
PY AFCS
C
COLL CTRL PANEL
ROLL
AP2
COLL CTRL PANEL PITCH
or BACKUP AP1
AP2
YAW
ROLL YAW
TI
O N
O N
BACKUP AP1
LY
–
PITCH
TRIMS ACTUATORS
O
TRIMS ACTUATORS
BKD2_FLH_0112_R
AFCS
N
- VMS SYSTEM page:
U
BKD2_FLH_0113_R
C
- APCP:
AP2
ST
or
R
AP1
OFF
R
IN
OFF
FO
- One AP lost due to internal failure detection - System will reconfigure automatically - Autopilot stabilization not affected Procedure 1. Autopilot performance
- Monitor
2. Continue flight
AFCS
3 - 10
APPROVED Rev. 22
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
AP TRIM OFF and audio tone Conditions/Indications – FND AFCS strip XXX XXX
affected axis flashing in amber for 10 sec
XXX
– VMS SYSTEM page AFCS
ROLL
T
PY
AP2
affected trim actuator displayed in red if failed, displayed in red then gray if switched off by AP
O
PITCH
N
COLL CTRL PANEL
C
O
TRIMS ACTUATORS
BACKUP AP1
LL
affected axis displayed in amber
O
DSAS
N TR
XXX
ED
after 10 sec:
C
O
YAW
A.TRIM
O N
only if A.TRIM function disengaged by crew on APCP
O N
OFF
BKD2_FLH_0116_R
LY
–
– APCP
BKD2_FLH_0114_R
DSAS
BKD2_FLH_0115_R
XXX XXX
ST
R
Procedure
U
C
TI
– Autopilot trim actuator failed – Loss of autotrim and upper mode on affected axis – Hands-on
IN
1. Flying controls
FO
R
EFFECTIVITY
Before Helionix Maintenance Release 1 or before ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
2. AP2 + AP1
EFFECTIVITY
– Re-engage (cyclic grip AP/BKUP ON sw right then left (AP2 before AP1))
After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
2. AP2 + AP1 EFFECTIVITY
–
Re-engage (cyclic grip )
All continued:
APPROVED Rev. 10
AFCS 3 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
If unsuccessful: 3. AP2
– Disengage (via APCP in order to reconfigure to AP1)
LL
In case saturation arrow appears on affected axis, manual correction will be necessary to recenter SEMA.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
NOTE
ED
If successful: 4. Continue flight If unsuccessful: If VFR or DPIFR (IMC) flight: 5. Continue flight If SPIFR (IMC) flight: 5. LAND AS SOON AS PRACTICABLE
AFCS 3 – 12
APPROVED Rev. 10
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
BACKUP SAS and audio tone Conditions/Indications – VMS SYSTEM page AFCS
TRIMS ACTUATORS
TRIMS ACTUATORS
COLL
COLL
BACKUP AP1
ROLL
AP2
or BACKUP AP1
N TR
YAW
AP2
LL
PITCH
ED
CTRL PANEL
O
CTRL PANEL
ROLL YAW
O
T
BKUP
BKD2_FLH_0118_R
C
O
– APCP
PITCH
BKD2_FLH_0117_R
AFCS
O
PY
N
OFF
–
C
– Back-up SAS failed
LY
Procedure
O N
1. Back-up SAS
O N
2. Continue flight
– Try to re-engage (cyclic grip)
TI
NOTE D Autopilot stabilization is not affected.
FO
R
IN
ST
R
U
C
D In case of additional loss of both APs, no stabilization will be available.
APPROVED Rev. 9
AFCS 3 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.2.3
Emergency/malfunction conditions AFCS
3.2.3.1 Trim actuator runaway or stuck beep trim Conditions/Indications – Possibly significant deviation from intended flight path – Unintended change of upper mode references Procedure – Hands-on, feet-on. Use TRIM REL pb if required.
2. Safe flight conditions
– Establish
3. Affected axis
– Try to identify, if possible beep in opposite direction for more than 2 sec
LL
O
N TR
O
AFTER LANDING, FLYING CONTROLS HANDS-ON AND FEET-ON UNTIL MAIN ROTOR HAS STOPPED.
O
High control forces on affected axis may persist throughout the rest of the flight.
PY
N
NOTE
T
C
CAUTION
ED
1. Flying controls
O N
Conditions/Indications
LY
3.2.3.2 Cyclic force trim release failure
–
C
O
4. LAND AS SOON AS PRACTICABLE
TI
O N
– Cyclic force trim release function inoperative (either partially, i.e. in one axis, or completely)
U
C
Procedure
ST
R
1. BEEP TRIM sw (cyclic stick)
– Operate to adjust cyclic stick position
FO
R
IN
2. LAND AS SOON AS PRACTICABLE
3.2.3.3 Collective force trim release failure Conditions/Indications – Collective force trim release function inoperative Procedure 1. BEEP TRIM sw (collective)
– Operate position
to
adjust
collective
or 1. Operate collective against friction trim 2. LAND AS SOON AS PRACTICABLE AFCS 3 – 14
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
FLYUP
XXX
XXX
XXX
XXX
XXX
BKD2_FLH_0557_R
3.2.3.4 Autopilot fly-up (from CRHT mode)
FLYUP flashing in the AFCS strip and voice message ”autopilot flyup”
Conditions/Indications
ED
– FLY-UP is triggered when the autopilot is in CH.RT mode and the aircraft descends below (whichever is lower): 200 ft, or
–
30 ft below the CH.RT reference.
N TR
O
LL
–
O
– FND AFCS strip: CHRT label is replaced by >FLY–UP
10 MINUTES) OPERATION WITH ONE AHRS IN MAG AND THE OTHER IN DG MODE SHOULD BE AVOIDED, SINCE IT COULD LEAD TO AUTOMATIC DE–SELECTION OF THE HEADING IN MAG MODE.
C U
Procedure
TI
O N
D 3. TO AVOID ERRATIC HEADING BEHAVIOR, THE AFCS UPPER MODES HDG AND NAV SHALL BE DESELECTED WHILE MANUALLY SLEWING HDG1 OR HDG2.
ST
R
1. DG 1 and 2 pb’s
THE TIME BETWEEN SETTING OF HDG1 AND HDG2 MUST NOT EXCEED ONE MINUTE.
FO
R
IN
CAUTION
– Push and hold to select free, DG appears on FND
2. HDG 1 and 2
– Set to correct heading within one minute
When magnetic perturbations no longer persist, return to slaved mode as follows: 3. DG 1 and 2 pb’s
– Push and hold, DG extinguishes on FND
4. Continue flight
APPROVED Rev. 15
AVIONICS AND DISPLAYS 3 – 55
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.3.5.7 Color failure on MFD Conditions/Indications – Unusual colors displayed on MFD (red, green or blue missing). Procedure 1. Affected MFD
– Switch off
ED
2. Apply malfunction procedure for loss of the affected MFD
O
LL
3.3.5.8 Black or abnormal SVS colors (if installed)
N TR
Conditions/Indications
O
T
Procedure
C
– The SVS does not automatically revert to FDS format.
O
– The SVS background is black or the SVS colors are abnormal.
– Push to select FDS
N
1. FDS bsk (on FND)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
2. Continue flight
AVIONICS AND DISPLAYS 3 – 56
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.4
CLIMATE CONTROL AND ICING PROTECTION
3.4.1
Caution indications CLIMATE CONTROL AND ICING PROTECTION
AVIONICS OVHT
ED
and audio tone Conditions/Indications
O
N TR
O
LL
– Upper and/or lower avionics compartment overheat (lower avionics compartment is only monitored if avionics are installed). – Temperature of avionics compartment exceeds 55_C (or 65_C, depending on installed equipment)
T
C
Procedure
N
O
1. PUSH FOR AIR lever
PY
2. Maximum ventilation/cooling
– Set
O
If caution extinguishes:
– Push
C
3. Continue flight
LY
–
If caution remains:
HEATING FAIL and audio tone
IN
ST
R
U
C
TI
O N
O N
3. LAND AS SOON AS PRACTICABLE
R
Conditions/Indications
FO
– Heating is permanently on and cannot be switched off. – Bleed air mixing valve open (
indicated ) with heating switched off
Procedure 1. Heating
– On, then off
If caution extinguishes: 2. Continue flight If caution remains on: 2
Continue flight
NOTE
APPROVED Rev. 15
Engine performance may be degraded during takeoff or landing > DA12000ft. Use performance charts for heating on, if available. CLIMATE CONTROL AND ICING PROTECTION 3 – 57
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
HEATING OVERTEMP and audio tone
Conditions/Indications – Mixing valve inlet temperature > 82_C, or mixing valve outlet temperature > 105_C.
LL
ED
– Caution will extinguish if inlet temperature is < 71_C.
– Off
N TR
1. Heating
O
Procedure If caution disappears:
– On, if required
C
O
2. Heating
O
T
If caution remains on or comes on again:
– Off
N
3. Heating
O
C
COCKPIT DEMISTING IS NOT AVAILABLE WITH HEATING OFF.
MFD OVERHEAT and audio tone
IN
ST
R
U
C
TI
O N
O N
LY
–
CAUTION
PY
4. Continue flight
FO
R
Conditions/Indications – Normal operating temperature (65_C) of MFD exceeded. Procedure 1. INST COOL cb
– Check in
2. PUSH FOR AIR lever
– Push
3. Maximum ventilation/cooling
– Set
If caution extinguishes: 4. Continue flight If caution indication remains on: 4. LAND AS SOON AS PRACTICABLE CLIMATE CONTROL AND ICING PROTECTION 3 – 58
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
PITOT1
HEATER FAIL and/or
HEATER FAIL
PITOT2
and audio tone
ED
Conditions/Indications
LL
– Pitot tube heater failed.
N TR
O
– Corresponding airspeed indicators may give false indications in sub-freezing conditions (v5_C, visible moisture).
O
Procedure
– Monitor, system
T
Airspeed indication
N
O
2.
– Check
C
1. PT/ST cb
with
other
O N
HEATER OFF and/or
HEATER OFF
PITOT2
and audio tone
ST
R
U
C
TI
O N
PITOT1
LY
–
C
O
PY
3. Continue flight
compare
IN
Conditions/Indications
FO
R
– Pitot tube and/or static port heater are not switched on. – Corresponding airspeed, altitude and vertical speed indicators may give false indications in sub-freezing conditions (v5_C, visible moisture). Procedure 1. PT/STATIC HTG sw
– Check ON
2. Continue flight
APPROVED Rev. 15
CLIMATE CONTROL AND ICING PROTECTION 3 – 59
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
PITOT1
STAT HTR FAIL and/or
STAT HTR FAIL
PITOT2
and audio tone
ED
Conditions/Indications – Static port heating system has failed
N TR
O
LL
– Corresponding barometric indicators may give false indications in sub-freezing conditions (v5_C, visible moisture).
C
O
Procedure
– Monitor, system
compare
with
other
N
O
T
1. Altimeter and airspeed
PY
If signals are unaffected, i.e. no discrepancies indicated:
O
2. Continue flight
C
If discrepancies indicated:
LY
–
2. Apply static system failure procedure (refer to Para. 3.3.5.5)
Malfunction conditions climate control and icing protection
R
IN
ST
R
U
C
TI
3.4.2.1 Electrical heater failure
O N
3.4.2
O N
3. LAND AS SOON AS PRACTICABLE
FO
(symbol on FLI)
Conditions/Indications – Electrical heater not available due to overheating. Procedure 1. Maximum ventilation
– Set
2. Continue flight CAUTION NOTE
COCKPIT DEMISTING CAPABILITY MAY BE REDUCED.
Observe temperature limitations for defogging/defrosting and heating (see Section 2.9)
CLIMATE CONTROL AND ICING PROTECTION 3 – 60
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.4.2.2 GTN overtemp or cooling failure
MSG
and
(on FND/NAVD unit)
(on GTN)
Conditions/Indications
N TR
O
LL
COOLING GTN overtemp. Reducing backlight brightness.
ED
– On the GTN, one of the following messages is indicated:
C
O
COOLING FAN The cooling fan has failed.
O
T
Procedure
N
1. Maximum ventilation/cooling
– Set
O N
C and
O N
MSG
LY
–
3.4.2.3 VHF COM radio overheating
O
PY
2. Continue flight – be prepared for failure of the affected GTN unit
(on GTN)
U
C
TI
(on FND/NAVD unit)
ST
R
Conditions/Indications
IN
– On the GTN, the following message is indicated:
FO
R
COM RADIO Com overtemp or undervoltage. Reducing transmitter power.
– Output power is decreased. Radio range will be reduced. Procedure 1. Maximum ventilation/cooling
– Set
2. Communication
– Reduce as much as possible or use other radio.
3. Continue flight
APPROVED Rev. 9
CLIMATE CONTROL AND ICING PROTECTION 3 – 61
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.5
COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR)
3.5.1
Intercom and audio system (DVCS6100)
3.5.1.1 Intercom failure Conditions/Indications – Intercommunication and/or radio communication is not possible, or – One or both Audio Control Unit (ACU) are inoperative, or
ED
– The pilot’s or copilot’s intercom circuit is defective.
O
Some intercom failures may cause the BACK UP mode to activate automatically.
N TR
NOTE
LL
Procedure
C
O
1. Check if pilot and copilot system is affected
O
T
If both systems are affected:
– Select BACKUP
N
2. Emer sw on any ACUs
– Pilot can receive/transmit on VHF2 – Copilot can receive/transmit on VHF1
LY
–
C
O
PY
3. Radio communication
O N
If one system (pilot or copilot) is affected:
– Select SLAVED
3. Com/Nav selection
– Use operative ACU (same settings apply for pilot and copilot)
U
C
TI
O N
2. Emer sw on defective ACU
FO
R
IN
ST
R
4. Continue flight
COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 62
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.5.2
Transponder (GTX) (if installed)
3.5.2.1 Transponder failure
MSG
and (on GTN)
ED
(on FND/NAVD unit)
LL
Conditions/Indications
O
T
C
O
N TR
O
– Transponder is inoperative.
N
(GTN display)
O
PY
– On the GTN, one of the following messages is indicated:
LY
–
C
TRANSPONDER 2 Transponder 2 is inoperative or connection to GTN is lost.
O N
TRANSPONDER 2 Transponder 2 needs service.
ST
R
Procedure
U
C
TI
O N
DATA SOURCE Pressure altitude source inoperative or connection to GTN lost.
– Advise about possible loss or degradation of transponder
R
IN
1. Air Traffic Control (ATC)
FO
2. Continue flight
APPROVED Rev. 16.2
COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 63
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.5.2.2 Loss of ADS–B out function
MSG
and
(on FND/NAVD unit)
(on GTN)
Conditions/Indications
ED
– Transponder ADS–B out function is lost (e.g. because GPS signal is invalid)
O
LL
– On the GTN, the following message is indicated:
C
O
N TR
TRANSPONDER 2 ADS–B is not transmitting position.
O
T
Procedure
N
If ADS–B is used and/or mandatory:
– Advise about loss of ADS–B function
C
O
PY
1. Air Traffic Control (ATC)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
2. Continue flight
COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 64
APPROVED Rev. 9
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3.5.3
VHF COM radio (GTN750)
3.5.3.1 VHF COM failure
MSG
and (on GTN)
ED
(on FND/NAVD unit)
LL
Conditions/Indications
O
T
C
O
N TR
O
– VHF COM is inoperative
N
(GTN display)
C –
LY
COM RADIO Com radio needs service.
O
PY
– On GTN, one of the following messages is indicated:
O N
O N
COM RADIO Com radio may be inoperative.
C
TI
Procedure
IN
ST
R
U
1. Affected FMS pb
– Press to switch off GTN – Wait 10 seconds – Press to switch on GTN
R
If failure remains:
FO
2. COM of other GTN unit
– Use
3. Continue flight
APPROVED Rev. 9
COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 65
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.5.3.2 GTN touchscreen failure Conditions/Indications – GTN touchscreen does not respond to inputs. Procedure 1. Affected FMS pb
– Press to switch off GTN – Wait 10 seconds – Press to switch on GTN
If function is restored:
ED
2. Continue flight
LL
If function is not restored:
N TR
O
3. Use backup rotary knobs and other GTN 4. Continue flight
T O N
–
C
O
PY
Conditions/Indications – Display has failed and/or – COM/NAV frequencies cannot be tuned – Communication on active frequency is possible
C
O
3.5.3.3 GTN double display failure
O N
1. Radio communications
LY
Procedure
– Communicate frequency
on
last
active
– Press briefly to toggle between FMS2 active and standby frequencies, or – Press more than 2 seconds to switch to VFR guard frequency (121.50 MHz)
FO
R
IN
ST
R
U
C
TI
2. VHF2 XFER pb
O N
If no radio contact on active frequency is possible:
NOTE
Once the guard frequency was selected by pressing the VHF2 XFER pb, the VHF2 XFER pb must be pressed for more than 2 seconds to return to normal frequency selection.
3. FMS1 pb
– Press to switch off GTN – Wait 10 sec – Press to switch on GTN
If FMS1 was recovered and/or communication and frequency changes are possible: 4. FMS2 pb
– Press to switch off GTN – Wait 10 sec – Press to reactivate GTN
COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 66
APPROVED Rev. 15
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3.5.3.4 VHF COM transmit key stuck
MSG
and
(on FND/NAVD unit)
(on GTN)
Conditions/Indications
ED
– On GTN, the following message is indicated:
N TR
O
LL
REMOTE KEY STUCK Com push-to-talk key is stuck.
T
C
O
– Transmission automatically stops after 30 seconds
N
O
Procedure
O
If transmission key remains stuck:
C
2. COM of other GTN unit
– Use
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
3. Continue flight
– Release
PY
1. Transmit pb
APPROVED Rev. 9
COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 67
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3.5.4
VOR/ILS navigation (GTN750)
3.5.4.1 VOR/LOC/ILS failure
MSG
and (on GTN)
ED
(on FND/NAVD unit)
LL
Conditions/Indications
N TR
O
– On GTN, one of the following messages is indicated:
O
GLIDESLOPE Glideslope receiver needs service
O
T
C
GLIDESLOPE Glideslope receiver has failed.
Procedure
O N
1. NAV source (VOR/ILS)
O N
PY
LY
–
C
O
VLOC RECEIVER Navigation receiver has failed.
N
VLOC RECEIVER Navigation receiver needs service.
FO
R
IN
ST
R
U
C
TI
2. Continue flight
– Select other source
COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 68
APPROVED Rev. 9
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3.5.4.2 Glideslope and/or localizer discrepancy during final approach Conditions/Indications
or
N TR
O
LL
ED
– On FND
or
C
O
PY
N
O
T
C
O
and/or
LY
–
– Discrepancy of glideslope and/or localizer signal during ILS, LPV, or L/VNAV approach
O N
O N
Procedure
– Push
2. Missed approach
– Perform
R
U
C
TI
1. GA pb (on collective)
IN
ST
If erroneous source can be determined:
FO
R
3. Erroneous source 4. Approach
– Deselect – Repeat using single source (indications will be shown in amber instead of magenta).
If erroneous source can not be determined: 3. Use alternate approach procedure (not requiring erroneous source) to complete the flight.
APPROVED Rev. 15
COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 69
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.5.5
GPS navigation and flight management system (GTN750)
3.5.5.1 Loss of GPS integrity on both GTN units
MSG
LOI
and
(on both GTN units)
(on FND/NAVD unit)
O
PY
N
O
T
C
O
N TR
O
LL
ED
and during an approach (e.g. LPV)
–
C
Conditions/Indications
LY
– Loss of GPS integrity on both GTN units
O N
– On GTN, one of the following messages is indicated:
TI
O N
GPS NAVIGATION LOST Insufficient satellites. Use other navigation source.
R
U
C
GPS NAVIGATION LOST Erroneous position. Use other navigation source.
IN
ST
GPS RECEIVER GPS receiver has failed. Check GPS coax for electrical short.
FO
R
GPS RECEIVER GPS receiver needs service. LOSS OF INTEGRITY (LOI) Verify GPS position with other navigation equipment.
– On GTN, one of the following messages is indicated during an approach: ABORT APPROACH GPS approach no longer available. APPROACH NOT ACTIVE Do not continue GPS approach. – Course guidance and flight plan will be removed from the FND/NAVD. CDI and VDI will be shown in amber. COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 70
APPROVED Rev. 9
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– If the autopilot was coupled to a GPS mode, the modes will flash amber and then disappear. The voice message “autopilot decouple“ will be triggered. During an LPV approach, the autopilot V.APP mode will be replaced by the FPA mode with reference set to level flight. – The digital map functions (on MFD and GTN) will be unavailable. – HTAWS (if installed) will be degraded: Terrain and obstacle warnings, as well as glideslope (mode 5) warnings are not available. Procedure
LL
ED
During the final approach of a GPS based approach in IMC: – Push
2. Missed approach
– Perform, use alternate navigation source (VOR, ADF, radar guidance)
O
T
C
O
N TR
O
1. GA pb (on collective)
PY
N
During GPS based en-route navigation:
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
1. Use alternate navigation source (VOR, ILS, ADF, radar guidance) to complete the flight.
APPROVED Rev. 15
COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 71
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.5.5.2 Approach downgraded from LPV and LNAV/VNAV to LNAV
MSG
LOI
and
(on FND/NAVD unit)
(on GTN)
PY
N
O
T
C
O
N TR
O
LL
ED
and during an LPV approach
C
O
Conditions/Indications
LY
–
– Approach has been downgraded from LPV or LNAV/VNAV, to an LNAV approach. Vertical guidance is no longer available. Different approach minima apply.
O N
– On GTN, the following message is indicated:
C
TI
O N
APPROACH DOWNGRADE Approach downgraded. Use LNAV minima.
IN
Procedure
ST
R
U
– After the FAF, the AFCS (if coupled), will automatically revert from V.APP to V/S or FPA mode with zero rate of climb/descent.
FO
R
Before FAF:
1. DA and DH
– Adjust to LNAV minima
2. LNAV approach
– Perform (refer to Section 4)
During final approach (runway not yet visible): 1. GA pb (on collective)
– Push
2. Missed approach
– Perform – Repeat approach with LNAV minima or use alternate navigation source.
3. Use alternative approach procedure to complete the flight COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 72
APPROVED Rev. 15
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3.5.5.3 GTN crossfill function
MSG
LOI
and
(on FND/NAVD unit)
(on GTN)
T
C
O
N TR
O
LL
ED
and if FMS was selected as NAV source
N
O
Conditions/Indications
–
C
O
PY
– Automatic crossfill between the GTN units is lost or disabled. User waypoints, flight plans, and various settings will not be exchanged between the units. The units may have a different flight plan and procedure loaded.
LY
– On GTN, one of the following messages is indicated:
O N
O N
CROSSFILL ERROR Crossfill is inoperative. See CRG for crossfilled items.
C
TI
CROSSFILL ERROR GTN software mismatch. See CRG for crossfilled items.
ST
R
U
CROSSFILL ERROR GTN Navigation DB mismatch. See CRG for crossfilled items.
FO
R
IN
CROSSFILL STATUS Crossfill is turned off.
Procedure 1. GTN HOME pb
– Push
2. GTN SYSTEMS icon
– Touch
3. GTN SETUP icon
– Touch
4. GTN CROSSFILL indication
– Check CROSSFILL is selected.
If crossfill remains off: 5. Flight plan / procedure (FMS1 or FMS2)
– Check correct flight procedure is loaded
6. NAV source
– Select FMS1 or FMS2
plan
/
7. Continue flight APPROVED Rev. 15
COMMUNICATION, NAVIGATION, AND SURVEILLANCE (COM/NAV/XPDR) 3 – 73
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3.6
DOORS
3.6.1
Caution indications DOORS
EPU DOOR
LL
ED
and audio tone
N TR
O
Conditions/Indications
O
– External power receptacle access door is open and EPU is not connected
C
Procedure
O
T
F ON GROUND
– Close
PY
N
1. EPU access door
DOOR OPEN and audio tone
IN
ST
R
U
C
TI
O N
O N
LY
–
1. LAND AS SOON AS PRACTICABLE
C
O
F IN FLIGHT
R
Conditions/Indications
FO
Any of the following doors is not properly latched: – Cockpit doors – Cabin sliding doors – Cabin clamshell doors Procedure 1. Doors
– Close, check latched
If visual inspection of the doors can ensure that all doors are properly latched: 2. Continue flight. If the caution remains on and door status is uncertain: 2. LAND AS SOON AS PRACTICABLE DOORS 3 – 74
APPROVED Rev. 9
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3.7
ELECTRICS
3.7.1
Warning indications ELECTRICS
BAT OVHT
on Warning Unit
ED
and audio tone and
LL
BAT OVERHEAT
on ML
O
N TR
O
and voice message “BATTERY OVERHEAT”
T
C
Conditions/Indications
N
O
Battery overtemperature (above 70 _C)
PY
Procedure
C
O
F ON GROUND
–
1. BAT MSTR sw
LY
– BAT DISCONN will appear – Shut down
O N
2. Engines
– OFF
BATTERY MUST BE INSPECTED OR REPLACED PRIOR TO NEXT FLIGHT.
C
TI
O N
CAUTION
R
U
F IN FLIGHT (dual crew)
– OFF
ST
1. BAT MSTR sw
IN
– BAT DISCONN will appear
R
2. LAND AS SOON AS POSSIBLE
FO
After landing: 3. Pilot remaining on seat
– “Hands-on”
4. Engines
– Leave running in IDLE
5. Visual inspection of battery
– Perform
If visual inspection reveals no indication of battery overheating, a flight to the nearest service station is permitted in VMC with BAT OVHT warning light ON. 6. LAND AS SOON AS PRACTICABLE CAUTION
BATTERY MUST BE INSPECTED OR REPLACED PRIOR TO NEXT FLIGHT. continued:
APPROVED Rev. 9
ELECTRICS 3 – 75
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F IN FLIGHT (single crew)
1. BAT MSTR sw
– OFF – BAT DISCONN will appear
2. LAND AS SOON AS POSSIBLE After landing: 3. Engine shutdown
– Perform
4. Visual inspection of battery
– Perform
ED
If visual inspection reveals no indication of battery overheating, a flight to the nearest service station is permitted in VMC with BAT OVHT warning light ON. – Perform
6. BAT MSTR sw
– OFF, BAT DISCONN will appear
O
N TR
7. LAND AS SOON AS PRACTICABLE
O
BATTERY MUST BE INSPECTED OR REPLACED PRIOR TO NEXT FLIGHT.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
CAUTION
LL
5. Start-up procedure
ELECTRICS 3 – 76
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3.7.2
Caution indications ELECTRICS
BAT DISCHARGING and audio tone Conditions/Indications
ED
– Battery is the only electrical power source
N TR
In the following conditions, BAT DISCHARGING may appear on ground before engine start or after engine shutdown when BAT MSTR sw is ON and no EPU is connected: – Prolonged battery operation (> 3 min) and current is low (BAT AMPS < 40A) – Battery current is high (BAT AMPS > 40A) – Battery voltage is low (Bus 1/2 voltage < 24.5V) – Engine ventilation > 15 seconds
PY
N
O
T
C
O
NOTE
O
LL
– Short circuit on battery bus or battery feeder line (discharge > 5A)
LY
1. VMS page
–
F ON GROUND, engines OFF
C
O
Procedure
– Select
O N
O N
2. Electrical parameters (BAT AMPS and GEN – Check, verify electrical drain on AMPS) battery
C
or
U
Engine start
ST
R
3
– Connect
TI
3. EPU
– Perform before voltage is below 23.5 V.
IN
F IN FLIGHT, or on ground engines ON
FO
R
NOTE
If BAT DISCHARGING caution appears when GEN1 DISCONNECTED GEN2 is present, proceed in accordance with GEN1 DISCONNECTED GEN2.
1. VMS page
– Select
2. Electrical parameters (BAT AMPS and GEN – Check, verify electrical drain on AMPS) battery 3. BAT MSTR sw
– OFF, BAT DISCONN indicated
4. LAND AS SOON AS PRACTICABLE
APPROVED Rev. 9
ELECTRICS 3 – 77
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BAT DISCONN and audio tone Conditions/Indications – Battery is off-line – BAT MSTR sw in OFF position
– OFF, then ON
LL
1. BAT MSTR sw
O
If caution indication extinguishes:
N TR
2. Continue flight. If caution indication remains on:
C
O
3. LAND AS SOON AS PRACTICABLE
O
T
BAT DISCONN is suppressed on ground when EPU is connected.
PY
N
NOTE
ED
Procedure
C
O
ELEC OVERLIMIT
–
and audio tone
O N
LY
Conditions/Indications
– DC parameters are outside normal operating range
TI
O N
– May occur on ground if battery voltage < 24 V. Engine starting is allowed even if battery voltage is only 23.5 V (refer to Sect. 4).
R
IN
ST
R
U
C
Procedure 1. VMS page – Select 2. Electrical parameters – Check EFFECTIVITY H/C before Maintenance Release 1 or before ASB MBB–BK117 D–2–42A–005 (HELIONIX Step 2.0.3)
FO
ON GROUND If EPU is connected and no indication exceeds the limit (no amber or red) 3. Master list – Check EPU CONNECTED indicated
F
4. Electrical load
– Check battery current indication >125A
5. Continue operation on ground EFFECTIVITY All F IN FLIGHT If indication of GEN AMPS exceeds limits (amber or red): 3. Electrical load – Reduce as much as possible, or until GEN AMPS normal ELECTRICS 3 – 78
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4. GEN AMPS – Check If indication of GEN AMPS is normal: 5. Continue flight with reduced load If indication of GEN AMPS is still amber or red: 5. Affected GEN sw – OFF, GENi DISCONNECTED indicated 6. LAND AS SOON AS PRACTICABLE If indication of GEN VOLTS exceeds limits (amber or red): 3. Affected BUS TIE sw – OFF, SYSi BUS TIE OPEN indicated – OFF, GENi indicated
DISCONNECTED
LL
ED
4. Affected GEN sw
C
O
N TR
O
5. LAND AS SOON AS PRACTICABLE
N
O
T
EMER SHED BUS ON
C
O
PY
and audio tone
–
Conditions/Indications
O N
LY
– EMER SHD BUS switch is switched to ON.
O N
Procedure
1. EMER SHD BUS sw
FO
R
IN
ST
R
U
C
TI
2. Continue flight
– NORM and guard
APPROVED Rev. 15
ELECTRICS 3 – 79
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EPU CONNECTED and audio tone
Conditions/Indications – External power is applied to the electrical distribution system. Procedure
ED
After EPU start:
– Disconnect, verify cable physically disconnected
2. EPU access door
– Close
is
N TR
O
LL
1. EPU cable
PY
N
O
T
C
O
– Check EPU DOOR indication off
DISCONNECTED
–
C
or
O
GEN1
LY
DISCONNECTED
GEN2
TI
Conditions/Indications
O N
O N
and audio tone
C
– Respective generator has failed or is disconnected from the power distribution system.
IN
Procedure
ST
R
U
– Both non-essential buses are disconnected.
R
1. Affected GEN sw
FO
2. Affected GEN sw
– OFF – RESET, then ON
If reset was successful: 3. Continue flight If reset was unsuccessful: 3. Affected GEN sw 4. Electrical consumers
– OFF – Reduce as much as possible
5. LAND AS SOON AS PRACTICABLE NOTE D One generator alone will provide sufficient power for normal services. D Although more than one attempt could be made to reset a tripped generator, good airmanship dictates performing the reset procedure only once. ELECTRICS 3 – 80
APPROVED Rev. 13
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GEN1
DISCONNECTED
GEN2
and audio tone
Conditions/Indications – Both generators have failed or are disconnected from the power distribution system. – Only ESS BUS 1 + 2 are available.
ED
Procedure
– OFF, BUS TIE OPEN SYS2 indicated
2. VMS page
– Select
3. GEN 1 and GEN 2 sw’s
– RESET, then NORM
4. DC VOLTS and GEN AMPS
– Check if normal
T
C
O
N TR
O
LL
1. BUS TIE 2 sw
N
O
If reset was successful (Caution GEN1 DISCONNECTED GEN2 extinguished and DC VOLTS and GEN AMPS are normal and BUS TIE OPEN SYS2 indicated):
PY
5. Continue flight
LY
6. BUS TIE 2 sw
– OFF – NORM
O N
5. Affected GEN sw
–
C
O
If only reset of GEN1 or GEN2 was successful (Caution GEN1 DISCONNECTED or DISCONNECTED GEN2 appears and DC VOLTS and GEN AMPS are normal):
– Reduce
O N
7. Electrical consumers
TI
8. LAND AS SOON AS PRACTICABLE
C
If reset was not successful (Caution GEN1 DISCONNECTED GEN2 remains): – OFF
R
U
5. GEN 1 and GEN 2 sw’s
FO
R
IN
ST
NOTE D In case of double generator failure, the battery will supply the ESS BUS 1 and 2. BAT DISCHARGING caution may appear. Mission functions (including HTAWS) and external video are no longer available on the MFDs. D Radar altimeter indication will disappear. Switching EMER SHED to ON will recover radar altimeter indication.
6. Electrical consumers
– Reduce as much as possible
7. BUS TIE 2 sw
– NORM
continued:
APPROVED Rev. 15
ELECTRICS 3 – 81
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WARNING
IF EMER SHD BUS SW IS ON, FLIGHT TIME REDUCED TO LESS THAN 30 MINUTES.
CAUTION
SINCE AFT FUEL TRANSFER PUMP IS POWERED BY THE SHED BUS, THE AMOUNT OF UNUSABLE FUEL INCREASES ABOVE THAT STATED IN SECTION 2 WHEN THE EMER SHD BUS SW IS NOT SWITCHED ON.
8. EMER SHD BUS sw
– ON if required (Caution EMER SHED BUS ON appears)
9. Land within 30 minutes
IN CASE OF TOTAL ELECTRICAL FAILURE:
LL
WARNING
ED
Flight beyond 30 min may lead to a total electrical failure.
O
N TR
O
D FUEL AVAILABLE WILL BE LIMITED TO QUANTITY CONTAINED IN SUPPLY TANKS AT TIME OF FAILURE AND THUS WILL LIMIT THE RESIDUAL FLIGHT TIME.
PY
N
D ALL COM/NAV WILL BE LOST.
O
T
C
D IESI WILL PROVIDE AIRSPEED, ALTITUDE AND ATTITUDE DATA FOR APPROXIMATELY 30 MIN.
O
D ALL MFD INDICATIONS WILL BE LOST.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
D ALL AIRCRAFT STABILIZATION WILL BE LOST.
ELECTRICS 3 – 82
APPROVED Rev. 15
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GEN1
OVERHEAT or
OVERHEAT
GEN2
and audio tone Conditions/Indications
ED
– Temperature of generator high
O
LL
Procedure
– OFF, GENi indicated
2. Electrical load
– Reduce
DISCONNECTED
O
N TR
1. Affected GEN sw
T
C
If caution disappears within one minute:
N
O
3. Continue flight
PY
If caution remains on for more than 1 minute:
O
2. OEI flight condition
C
3. Affected engine
–
Identify
–
Perform
LAND AS SOON AS PRACTICABLE
INVERTER FAIL and audio tone
IN
ST
R
U
C
TI
O N
O N
5
Establish
LY
–
4. Single engine emergency shutdown
–
FO
R
Conditions/Indications – Inverter failure. – The stabilization function of the weather radar, if installed, is inoperative. Procedure 1. Continue flight
APPROVED Rev. 9
ELECTRICS 3 – 83
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
STBY BAT DISCH and audio tone
Conditions/Indications – Standby battery (emergency power supply unit) is discharging. – Power supply from essential bus to the standby battery is interrupted.
ED
Procedure
O
LL
1. Continue flight
N TR
NOTE D IESI will continue to operate for 30 min.
PY
N
O
T
C
O
D Emergency lighting system can be operated for 40 minutes.
O
STBY BAT FAIL
LY
–
C
and audio tone
O N
Conditions/Indications
TI
O N
– A failure of the standby battery (emergency power supply unit) was detected during activation of the STBY BAT sw.
U
C
Procedure
ST
R
If VFR day:
IN
1. Continue flight. If VFR night or IFR:
FO
R
1. Engine shut down perform
ELECTRICS 3 – 84
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
SYS1
BUS TIE OPEN and / or
BUS TIE OPEN
SYS2
and audio tone Conditions/Indications
ED
– Electrical systems are separated (load sharing impossible).
LL
– If both BUS TIE OPEN caution indications come on, the battery will not be charged.
N TR
O
– Caution is normal when BUS TIE sw is set to OFF deliberately.
C
If SYS1 BUS TIE OPEN SYS2 caution appears on ground after PWR-UP Test, set the BAT MSTR switch to ENGAGE once.
O
T
NOTE
O
Procedure
PY
N
F ON GROUND
O
1. VMS page
C
2. DC VOLTS, GEN AMPS and BAT AMPS
– Select – Monitor
LY
–
If voltmeter / ammeter indication is abnormal:
O N
3. Respective GEN sw or BAT MSTR sw
– OFF, GENi DISCONNECTED or BAT DISCONN indicated – Perform
5. EPU, if connected
– Disconnect
R
U
1. VMS page
C
F IN FLIGHT
TI
O N
4. Double engine shutdown
– Select
ST
If GEN AMPS > 200 A:
IN
2. Electrical consumers
– Reduce as much as possible
FO
R
3. LAND AS SOON AS PRACTICABLE
If GEN AMPS normal (0 – 200 A): 1. LAND AS SOON AS PRACTICABLE CAUTION
APPROVED Rev. 9
IF BUS TIE OPEN APPEARS AS A RESULT OF AN ELECTRICAL FAILURE, RESETTING THE BUS TIE COULD LEAD TO ADDITIONAL DAMAGE AND ELECTRICAL FIRE. THEREFORE, A BUS TIE RESET IN FLIGHT SHOULD ONLY BE PERFORMED IF THE BUS TIE WAS DELIBERATELY SWITCHED OFF.
ELECTRICS 3 – 85
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.7.3
White advisories ELECTRICS
REAR PANEL C/B
ED
Conditions/Indications
LL
– Circuit breaker located in the rear panel 1 or 2 open
N TR
O
Procedure
N
O
Emergency conditions ELECTRICS
PY
3.7.4
T
C
O
1. Continue flight
C
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
See procedures for FIRE, para 3.9.3.2 .
O
3.7.4.1 Electrical fire/short circuit
ELECTRICS 3 – 86
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.8
ENGINE
3.8.1
Warning indications ENGINE
ENG1 FAIL
ENG2 FAIL
and
on Warning Unit
ENG2
on ML
LL
FAIL
O
N TR
O
ENG1
ED
and
C
Conditions/Indications
O
T
– Warning Unit:
N
ROTOR RPM
PY
and warning tone (NR low)
C
O
– Master List:
DISCONNECTED
O N
– Yawing motion nose left
GEN2
LY
–
GEN1
– NR and both N2 decrease
O N
– VMS engine instruments (both engines) indicate power loss
C U
F HIGE
TI
Procedure
IN
ST
R
1. Right pedal
– Apply as necessary to stop yaw – Establish
3. Collective lever
– Raise to cushion landing
FO
R
2. Landing attitude F IN FLIGHT
1. Autorotation
APPROVED Rev. 9
– Perform
ENGINE 3 – 87
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1 FAIL
ENG2 FAIL
or
on Warning Unit
and
ENG1
FAIL
on ML
or
FAIL
ENG2
on ML
and PWR SPLIT audio tone
ED
Conditions/Indications
O
and warning tone (NR low)
N TR
ROTOR RPM
LL
– Possibly (depending on power setting): Warning unit
C
DISCONNECTED
T
GEN1
O
– Master List (affected engine):
–
C
O
– FLI:
GEN2
PY
DISCONNECTED
N
O
or
TI
O N
O N
LY
7
C
6
U
Red OEI flag
R
5
FO
BKD2_FLH_0411_R
IN
ST
R
OEI
– Jerk in the yaw axis, nose left. Severance of left jerk depending on power setting. – Possible change in noise level – VMS instruments indicate power loss of affected engine Procedure 1. Perform respective single engine failure procedure: Single engine failure – HIGE Single engine failure – HOGE ENGINE 3 – 88
– Para. 3.8.1.1 – Para. 3.8.1.2 APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
Single engine failure – takeoff Single engine failure – flight EFFECTIVITY
– Para. 3.8.1.3 – Para. 3.8.1.4
H/C before Maintenance Release 1 installed: Before HELIONIX Step 2.0.3 or before ASB MBB–BK117 D–2–42A–005 (HELIONIX Step 2.0.3)
OR H/C after Maintenance Release 1 installed: Before HELIONIX Step 3.0.2 or before ASB MBB–BK117 D–2–42A–005(HELIONIX
LL
IF THE AIRCRAFT DESCENDS MORE THAN 3000 FT FOLLOWING A SINGLE ENGINE FAILURE OR SHUT DOWN, AN ERRONEOUS LOW NR ALERT MAY BE TRIGGERED. IN THIS CASE, PROCEED AS FOLLOWS:
N TR
O
WARNING
ED
Step 3.0.2)
– Maintain above 98%
C
O
1. Digital NR
O N PY
3. Amber chevrons in FLI
C
O
4. Amber NR indication on NR gauge
– Disregard, monitor digital NR value
–
All
– Disregard
LY
EFFECTIVITY
– Disregard, use ACK pb (cyclic grip) to reduce volume
T
2. NR low warning tone
Before Helionix Maintenance Release 1
ST
EFFECTIVITY
R
U
C
TI
O N
O N
NOTE D Bleed air heating will be switched off automatically when the power exceeds OEI MCP and the ambient conditions lead to the engine being N1 or TOT limited. After lowering the collective below OEI MCP the heating will come on again. D If the last position of the “blue line” is known, this information shall be used for the initial collective adjustment.
R
IN
D Endurance calculation, if installed, is incorrect.
FO
EFFECTIVITY
All
3.8.1.1 Single engine failure - HIGE Procedure 1. Landing attitude
– Establish
2. Collective lever
– Raise to cushion landing
After landing: 3. Double engine emergency shutdown
APPROVED Rev. 16
– Perform
ENGINE 3 – 89
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.8.1.2 Single engine failure - HOGE Procedure F EMERGENCY LANDING
If hover height above ground w 100 ft: 1. Attitude
– Adjust to –15_ to –25_ nose down
2. Collective lever
– Adjust to maintain normal range
NR
in
ED
– Set to OEI 30s limit or as required – Establish
4. Collective lever
– Raise to cushion landing
N TR
O
LL
3. Landing attitude
O
If hover height above ground t 100 ft:
– Adjust to –5_ nose down
2. Collective lever
– Adjust to maintain normal range
NR
in
N
O
T
C
1. Attitude
O
PY
– Set to OEI 30s limit or as required
–
C
3. Landing attitude
– Raise to cushion landing – Perform
O N
O N
LY
4. Collective lever After landing: 5. Double engine emergency shutdown
– Establish
TI
F TRANSITION TO OEI FLIGHT
R
U
C
1. Attitude
FO
R
IN
ST
2. Collective lever
3. Airspeed
– Adjust to –15_ to –25_ nose down – Adjust to maintain normal range
NR
in
– Set to OEI 30s limit or as required – Accelerate to VY – Reduce power to OEI 2 min limit, latest when red OEI counter flashes.
ENGINE 3 – 90
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
After reaching safe altitude: 4. Collective lever
– Reduce to OEI MCP or below, latest when amber OEI counter flashes.
5. Affected engine
– Identify
6. Single engine emergency shutdown
– Perform
7. LAND AS SOON AS PRACTICABLE
ED
3.8.1.3 Single engine failure - takeoff
LL
Procedure
– Adjust to maintain normal range
NR
in
N TR
O
1. Collective lever F REJECTED TAKEOFF
– Establish
C
O
2. Landing attitude
– Raise to cushion landing
T
3. Collective lever
N
O
After landing:
LY
–
C
2. Collective lever
O
F TRANSITION TO OEI - FLIGHT
PY
4. Double engine emergency shutdown
TI
O N
O N
3. Airspeed
– Perform – Adjust to OEI 30 sec limit or below – Gain, VY – Reduce power to OEI 2 min limit, latest when red OEI counter flashes.
U
C
After reaching safe altitude:
FO
R
IN
ST
R
4. Collective lever
– Reduce to OEI MCP or below, latest when amber OEI counter flashes.
5. Affected engine
– Identify
6. Single engine emergency shutdown
– Perform
7. LAND AS SOON AS PRACTICABLE
3.8.1.4 Single engine failure - flight Procedure 1. OEI flight condition
– Establish
2. Affected engine
– Identify
3. Single engine emergency shutdown
– Perform
4. LAND AS SOON AS PRACTICABLE APPROVED Rev. 9
ENGINE 3 – 91
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.8.2
Caution indications ENGINE
ENG1
CHIP or
CHIP
ENG2
LL
ED
and audio tone
O
Conditions/Indications
N TR
– Metal particles detected in engine oil
O
Procedure
T
C
F ON GROUND
– Identify
– Perform
PY
2. Single / double engine emergency shutdown
N
O
1. Affected engine
O
F IN FLIGHT
C
1. OEI flight condition
– Identify
LY
–
2. Affected engine
– Establish
O N
1. Alternative:
– Perform
O N
3. Single engine emergency shutdown
TI
2. Alternative:
– IDLE, check indications
ST
THE SECOND ALTERNATIVE ENABLES THE CREW TO USE THE AFFECTED ENGINE FOR LANDING IF NECESSARY. BE PREPARED FOR ENGINE FAILURE. MONITOR N1, TOT, TORQUE, OIL PRESSURE AND TEMPERATURE OF AFFECTED ENGINE CLOSELY. IF THE PARAMETERS FLUCTUATE OR THEIR LIMITS ARE EXCEEDED PERFORM SINGLE ENGINE EMERGENCY SHUTDOWN IMMEDIATELY.
FO
R
IN
CAUTION
R
U
C
3. ENG MAIN sw
4
ENGINE 3 – 92
LAND AS SOON AS PRACTICABLE
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
FADEC EMER or
FADEC EMER
ENG2
and audio tone
LL
O
O
TU206 NOT installed
C
EFFECTIVITY
SELECTION OF FADEC EMERGENCY MODE ON BOTH ENGINES (BOTH FADEC EMER SW’S ON) IS PROHIBITED.
N TR
WARNING
ED
Conditions/Indications
DURING ENGAGEMENT OF FADEC EMERGENCY, AN OEI CONDITION MAY OCCUR RANDOMLY. THIS OEI CONDITION NORMALLY DISAPPEARS WITHIN 10 SECONDS. THEREFORE, FOR TRAINING PURPOSES, FADEC EMER SHALL NOT BE USED IN CRITICAL FLIGHT PHASES, AT HIGH ALTITUDE, OR WHEN HIGH POWER SETTINGS (ABOVE 2X50% TORQUE) ARE USED.
All
O N
EFFECTIVITY
LY
–
C
O
PY
N
O
T
CAUTION
TI
O N
– FADEC EMERGENCY mode is selected (FADEC EMER sw ON) following FADEC FAIL caution indication or for training
U
C
– TOT of the engine in ULT BACKUP mode is matched to the TOT of the other engine.
ST
R
– Engine acceleration and deceleration may be degraded.
FO
R
IN
CAUTION
AVOID USING MAXIMUM POWER AND PERFORM POWER VARIATION SLOWLY. LARGE OR MODERATELY FAST POWER VARIATIONS MAY CAUSE AN OEI CONDITION INDICATION. THIS OEI CONDITION NORMALLY DISAPPEARS AFTER A FEW SECONDS AT A STEADY POWER SETTING.
Procedure 1. Collective lever
– Make slow adjustments
2. LAND AS SOON AS PRACTICABLE After landing: 3. Engine shutdown NOTE
APPROVED Rev. 15
– Perform
If the ULT BACKUP mode is used for training purposes, the engine TOT should be matched before switching back to normal mode. Otherwise, an OEI caution may appear transiently. ENGINE 3 – 93
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
FUEL FILTER and/or
FUEL FILTER
ENG2
and audio tone Conditions/Indications
LL
ED
– Engine fuel filter(s) contaminated
O
Procedure
N TR
One caution indication:
C
BE PREPARED FOR SINGLE ENGINE FAILURE.
O
T
CAUTION
O
1. LAND AS SOON AS PRACTICABLE
N
Both caution indications:
O
C
BE PREPARED FOR DOUBLE ENGINE FAILURE.
O N
O N
LY
–
CAUTION
PY
1. LAND AS SOON AS POSSIBLE
FUEL VALVE CLSD
TI
ENG1
FUEL VALVE CLSD
ENG2
and audio tone
R
IN
ST
R
U
C
or
FO
Conditions/Indications – Fuel valve is in closed position. – The respective ACTIVE light (EMER OFF SW panel) will come on. NOTE
The FUEL VALVE CLSD caution indication will come on after pressing and releasing the respective EMER OFF switch labelled “FIRE”.
Procedure 1. OEI conditions
– Establish
2. LAND AS SOON AS PRACTICABLE CAUTION ENGINE 3 – 94
BE PREPARED FOR SINGLE ENGINE FAILURE. APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
FUEL VALVE POS or
FUEL VALVE POS
ENG2
and audio tone Conditions/Indications
LL
A FUEL VALVE POS caution indication coming on for a short time while valve is in transition from open to closed position, or vice versa, indicates normal operation following activation of the EMER OFF sw.
O
N TR
O
NOTE
ED
– Fuel valve is in a position other than commanded.
C
Procedure
– Establish
N
PY
2. LAND AS SOON AS PRACTICABLE
O
T
1. OEI conditions
BE PREPARED FOR SINGLE ENGINE FAILURE.
IDLE and/or
IDLE
ENG2
and audio tone
IN
ST
R
U
C
TI
O N
ENG1
O N
LY
–
C
O
CAUTION
R
Conditions/Indications
FO
– Engine idle Procedure 1. Respective ENG MAIN sw
APPROVED Rev. 9
– FLIGHT
ENGINE 3 – 95
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
OIL FILTER and / or
OIL FILTER
ENG2
and audio tone Conditions/Indications
– Select
2. Engine oil pressure and engine oil temperature
– Monitor
O
N TR
1. VMS page
O
Procedure
LL
ED
– Engine oil filter contaminated
O
PY
N
O
T
C
3. LAND AS SOON AS PRACTICABLE
OIL HIGH PRESS
–
C
ENG1
LY
or
O N
OIL HIGH PRESS
ENG2
TI
O N
and audio tone
U
C
Conditions/Indications
IN
Procedure
ST
R
– High pressure in engine oil system
– Select
2. Affected engine
– Check oil temperature and pressure, compare with normal engine
FO
R
1. VMS page
If overlimit is not confirmed: 3. Continue flight. Monitor engine oil pressure. If overlimit is confirmed: 3. OEI flight condition
– Establish
4. Affected ENG MAIN sw
– IDLE, ENGi IDLE indicated
5. LAND AS SOON AS PRACTICABLE NOTE
ENGINE 3 – 96
Prior landing the affected engine may be switched to FLIGHT in order to perform a normal landing. APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
OIL HIGH TEMP or
OIL HIGH TEMP
ENG2
and audio tone Conditions/Indications
Procedure
LL
ED
– High temperature in engine oil system
– Select
2. Affected engine
– Check oil temperature and pressure, compare with normal engine
C
O
N TR
O
1. VMS page
T
If overlimit is not confirmed:
N
O
3. Continue flight. Monitor engine oil temperature.
PY
If overlimit is confirmed:
O
3. Airspeed
–
OEI flight condition
– Establish
5. Affected engine
– Identify
6. ENG MAIN sw (affected engine)
– IDLE, ENGi IDLE indicated
7. Oil temperature indicator (affected engine)
– Monitor
ST
R
U
C
TI
O N
4
LY
If caution remains:
O N
4. Continue flight
C
If caution disappears:
– Increase if possible
FO
R
IN
If engine oil temperature decreases below limit: NOTE
Prior landing the affected engine may be switched to FLIGHT in order to perform a normal landing.
8. LAND AS SOON AS PRACTICABLE If engine oil temperature remains above limit: 8. Single engine emergency shutdown
– Perform
9. LAND AS SOON AS PRACTICABLE
APPROVED Rev. 9
ENGINE 3 – 97
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
OIL LOW PRESS or
OIL LOW PRESS
ENG2
and audio tone Conditions/Indications
ED
– Affected engine oil pressure below minimum
F ON GROUND
– Perform
N TR
1. Single engine shutdown
O
LL
Procedure
O
F IN FLIGHT
– Establish
2. VMS page
– Select
O
T
C
1. OEI flight condition
– Check
N
3. Engine oil pressure indicator
– Identify
O
– Perform
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
6. LAND AS SOON AS PRACTICABLE
C
5. Single engine emergency shutdown
PY
4. Affected engine
ENGINE 3 – 98
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
OIL OVERLIMIT and / or
OIL OVERLIMIT
ENG2
and audio tone Conditions/Indications
ED
– Engine oil pressure or temperature near limit, or engine oil temperature < 0_C
O
LL
Procedure
N TR
F ON GROUND
– Select
2. Engine parameters
– Check
C
O
1. VMS page
C
O
3. Affected engine
F IN FLIGHT
O N
1. VMS page
– IDLE until engine temperature > 0_C
oil
LY
O N
4. Continue flight
– Perform
–
If caution disappears:
O
PY
If engine oil temperature < 0_C:
N
3. Single / double engine shutdown
T
If engine oil pressure low:
TI
2. Engine parameters
– Select – Check and monitor regulary
R
U
C
3. Be prepared for OIL HIGH TEMP, OIL LOW PRESS or OIL HIGH PRESS caution indication for affected engine.
FO
R
IN
ST
4. LAND AS SOON AS PRACTICABLE
APPROVED Rev. 15
ENGINE 3 – 99
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
OVERSPEED or
OVERSPEED
ENG2
and audio tone Conditions/Indications
ED
– Engine overspeed detected
LL
– Affected engine N2 > 120%
N TR
O
– Affected engine was shut down automatically Procedure
C
O
F ON GROUND
– Perform
T
1. Double engine shutdown
N
PY
WHEN AN ENGINE HAS BEEN SHUT DOWN BY ITS OVERSPEED PROTECTION SYSTEM, THE OTHER ENGINE’S OVERSPEED PROTECTION SYSTEM IS INTERLOCKED TO AN INACTIVE STATUS. THUS, THE NORMAL ENGINE IS NO LONGER PROTECTED AGAINST POWER TURBINE OVERSPEED.
LY
–
C
O
CAUTION
O
F IN FLIGHT
O N
1. OEI flight condition
O N
2. Affected engine
– Identify – Perform
TI
3. Single engine emergency shutdown
– Establish
R
ENG i FAIL (red) will be triggered on affected engine. White advisory ENG OVSPD PROT FAIL will be displayed for the normal engine.
FO
R
IN
ST
NOTE
U
C
4. LAND AS SOON AS PRACTICABLE
ENGINE 3 – 100
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
STARTER ON or
STARTER ON
ENG2
and audio tone Conditions/Indications
ED
– Starter is active
LL
– Starter energize time limit exceeded
N TR
O
– If ENGi STARTER ON caution indication remains on after reaching IDLE, a relay or stuck electromagnetic switch is evident.
O
Procedure
T
C
F ON GROUND
PY
N
O
1. Affected GEN sw 2. Double engine shutdown
DISCONNECTED
– Perform
C
O
F IN FLIGHT
– OFF, GENi indicated
LY
–
1. Affected GEN sw
O N
2. Electrical load
TI
If caution remains:
O N
3. Affected ENG STARTER ON caution
C
4. Affected ST/IGN cb
DISCONNECTED
– Check, reduce if required – Check off – Pull
ENGINE STOP ELECTRO VALVE IS DISABLED. ENGINE SHUTDOWN WILL TAKE LONGER THAN NORMAL.
ST
R
U
CAUTION
– OFF, GENi indicated
FO
R
IN
5. LAND AS SOON AS PRACTICABLE
APPROVED Rev. 9
ENGINE 3 – 101
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
USAGE EXPIRED and/or
USAGE EXPIRED
ENG2
Conditions/Indications
LL
– Engine 1 and/or 2 limitations were exceeded. Exceedances may be:
ED
and audio tone
Total time in engine OEI range exceeded (duration 30 sec or 2 min)
–
Engine time in OEI exceeded
–
TOT or N1 limits exceeded
N TR O C
Further flights are prohibited.
N
O
T
NOTE
O
–
PY
Procedure
C
O
1. LAND AS SOON AS PRACTICABLE
– Check, record parameters
exceeded
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
2. Flight report page
ENGINE 3 – 102
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
FADEC1
DEGRADED and/or
DEGRADED
FADEC2
and audio tone Conditions/Indications
ED
– FADEC DEGRADED indicates a change of governing functions (level 2 failure).
AND
PERFORM
POWER
C
O
N TR
CAUTION D AVOID USING MAXIMUM POWER VARIATION SLOWLY. D DO NOT START THE ENGINE.
O
LL
– Engine/NR governing may be slower than normal.
T
Procedure
N
O
F ON GROUND
PY
1. Double engine shutdown
O
F IN FLIGHT
– Avoid
–
Caution FADEC N2 DISAGREE may appear
LY
NOTE
C
1. Rapid power changes
– Perform
O N
2. LAND AS SOON AS PRACTICABLE After landing:
– Perform
FO
R
IN
ST
R
U
C
TI
O N
3. Normal engine shutdown procedure
APPROVED Rev. 9
ENGINE 3 – 103
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
FADEC1
FAIL or
FAIL
FADEC2
and audio tone
ED
Conditions/Indications
O
LL
– FND
O C
5
BKD2_FLH_0407_R
O
T
amber FADEC FAIL flag on FLI
N
F AF DAI E CL
N TR
6
–
C
O
PY
4
O N
LY
– VMS page
82.0 % TOT
U
TOT
750 _C
R N1
93.0 %
affected engine: no limits displayed
N1
95.0 %
normal engine: AEO limits displayed
R
IN
ST
740 _C
amber FADEC FAIL message
TRQ
C
TI
72.0 %
Example: engine 1 affected
BKD2_FLH_0128_R
TRQ
O N
FADEC FAIL
FO
– Automatic engine control has failed, fuel metering valve is frozen (level 3 failure) – Affected engine does not respond to power/collective variations Procedure F ON GROUND
1. Double engine emergency shutdown
– Perform
F IN FLIGHT
1. Collective lever CAUTION
– Make slow adjustments
LOWERING COLLECTIVE BELOW “DESYNCHRONISATION (WHITE DASHED LINE ON FLI) WILL LEAD TO NR INCREASE.
LINE”
continued: ENGINE 3 – 104
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
NOTE
On FLI and VMS page, the power limits are always displayed in AEO format. Depending on the constant power delivered by the affected engine, the limits may be driven by AEO or OEI operating limitations. The FLI limits and the associated OEI counters must be respected.
2. Affected engine FADEC EMER sw
– ON
If FADEC FAIL disappears: 3. FADEC DEGRADED and FADEC EMER will appear. Proceed i.a.w. FADEC DEGRADED procedure
ED
If FADEC FAIL remains: – OFF
4. VMS page
– Select
5. Affected engine
– Verify by making small collective inputs (power of affected engine will remain unchanged)
O
N TR
O
LL
3. Affected engine FADEC EMER sw
T
C
6. LAND AS SOON AS PRACTICABLE
O
Landing area should permit OEI landing
NOTE
PY
N
Prior landing:
O
7. OEI flight condition
C
8. Affected engine
– Verify – Perform
O N
O N
LY
–
9. Single engine emergency shutdown
– Establish
N2 DISAGREE and/or
N2 DISAGREE
FADEC2
and audio tone
FO
R
IN
ST
R
U
C
TI
FADEC1
Conditions/Indications – FADEC 1 and/or FADEC 2 N2 differs from the standard N2 datum. In some cases, NR may revert to backup value (104%). In high altitude operation performance and yaw controllability may be reduced. Procedure F IN FLIGHT
1. Airspeed
– Reduce to VNE –20 kts
2. Maneuvering
– Avoid aggressive maneuvers, avoid using max. power
3. Continue flight. APPROVED Rev. 15
ENGINE 3 – 105
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
TRAINING ABORTED and audio tone
Conditions/Indications – Training mode will abort in the following conditions: NR < 91%
–
NR < nominal NR –11%
–
FADEC malfunction or engine failure occured
N TR
O
LL
ED
–
Procedure
– Push, to switch TRAIN MODE OFF
C
O
1. TRAINING pb
O
T
2. Continue flight
PY
N
If continuation of engine training is desired:
– ON
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
2. TRAINING pb
ENGINE 3 – 106
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.8.3
White advisories ENGINE
ENG1
CHIP SENSOR and / or
ENG2
ED
CHIP SENSOR
O
LL
Conditions/Indications
N TR
– Chip detector continuity test failure
ENG CHIP CAUTION IS NOT AVAILABLE.
C
O
CAUTION
T
Procedure
N
O
F ON GROUND
PY
1. Flights to complete the mission may be performed in accordance with MMEL/MEL.
O
F IN FLIGHT
–
LY
After each flight, chip sensors must be checked to be free of metal particles before further flights are conducted.
C
TI
O N
O N
NOTE
C
1. Continue flight
FUEL FILTER and / or
FUEL FILTER
ENG2
FO
R
IN
ST
R
U
ENG1
Conditions/Indications – Fuel filter clogging on engine 1 and/or engine 2 Procedure F ON GROUND
1. Do not start engines F IN FLIGHT
1. Continue flight NOTE APPROVED Rev. 9
Be prepared for ENGi FUEL FILTER caution ENGINE 3 – 107
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
FUEL LOW TEMP
ENG2
Conditions/Indications
LL
ED
– The fuel in the engine is too cold (below 2.3_C) for use without anti-icing additives. If no anti icing additives are added, use of power above FLI 2 is not allowed.
N TR
O
Procedure
O
If no anti-icing additives are added to the fuel:
– Maintain below 2 on FLI, until the advisory disappears
O
T
C
1. Collective
N
If anti-icing additives are added to the fuel:
LY
–
C
O
PY
1. Continue flight
OIL FILTER and / or
OIL FILTER
ENG2
ST
R
U
C
TI
O N
O N
ENG1
IN
Conditions/Indications
FO
R
– Filter pre-clogging in engine oil system Procedure 1. Continue flight NOTE
ENGINE 3 – 108
After 15 operating hours, the caution ENGi OIL FILTER will be automatically triggered.
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG1
OVSPD PROT FAIL and / or
OVSPD PROT FAIL
ENG2
ED
Conditions/Indications
O
LL
– Overspeed protection system failure
N TR
Procedure F ON GROUND
C
O
1. Do not start engines
T
F IN FLIGHT
N
O
1. Continue flight
THE AFFECTED ENGINE IS NO LONGER PROTECTED AGAINST POWER TURBINE OVERSPEED BY THE OVERSPEED PROTECTION SYSTEM.
O N
LY
–
C
O
PY
CAUTION
SERVICE NEEDED and / or
SERVICE NEEDED
ENG2
FO
R
IN
ST
R
U
C
TI
O N
ENG1
Conditions/Indications – A minor problem, which requires engine maintenance before the next flight, was detected by the FADEC. Procedure F ON GROUND
1. Do not start engines F IN FLIGHT
1. Continue flight NOTE APPROVED Rev. 9
Consult the FLT REPORT page after flight for problem description. ENGINE 3 – 109
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
ENG TREND
Conditions/Indications – Engine parameter abnormal trend
– Monitor
LL
2. Engine parameters
O
– Select
N TR
1. VMS page
ED
Procedure
N
O
T
C
O
3. Continue flight
REDUNDANCY
O
PY
FADEC1
C
and / or
FADEC2
C
TI
Conditions/Indications
O N
O N
LY
–
REDUNDANCY
U
– FADEC 1/2 redundancy lost
ST
R
– Engine governing unaffected
FO
R
IN
Procedure F ON GROUND 1. BAT MSTR sw
– OFF, wait 30 seconds – ON and engage
2. BAT MSTR sw If caution reappears: 3. Do not start engines (except in accordance with MMEL/MEL). F IN FLIGHT
1. Continue flight NOTE D Training mode and EPC shall not be used. D FADEC EMER shall not be used for training purposes. ENGINE 3 – 110
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
FADEC1
SIGNAL FAIL and / or
SIGNAL FAIL
FADEC2
Conditions/Indications
ED
– Some engine monitoring data are not received from the affected FADEC.
LL
– Engine governing unaffected.
T
C
O
N TR
O
Procedure F ON GROUND 1. Do not start engines F IN FLIGHT
O
1. VMS page
PY
N
2. Engine parameters
– Monitor, cross check with other engine
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
3. Continue flight
– Select
APPROVED Rev. 9
ENGINE 3 – 111
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.8.4
Emergency/malfunction conditions ENGINE
3.8.4.1 Double engine emergency shutdown Procedure F ON GROUND
1. Both ENG MAIN sw’s
– OFF
2. Both FUEL PRIME PUMP sw’s
– OFF – Press
4. BAT MSTR sw
– OFF
F IN FLIGHT
– Set to Vy
2. Autorotation glide
– Establish
3. Both ENG MAIN sw’s
– OFF
T
C
O
N TR
1. IAS
O
LL
3. Both EMER OFF sw’s
ED
If there is an indication that the engines are still running:
N
O
If there is an indication that the engines are still running:
– Press
PY
4. Both EMER OFF sw’s
C
O
3.8.4.2 Autorotation
LY
–
Procedure
O N
1. Collective lever
– Reduce to maintain NR within limits
4
4 Amber chevrons if amber NR limit exceeded
FO
2
R
IN
ST
4
2
Chevrons on FLI indicate direction of corrective movement for collective lever.
Red chevrons if red NR limit exceeded 2
2. Airspeed NOTE
BKD2_FLH_0408_R
R
U
C
TI
O N
Additional indications in case of low or high NR: FLI:
– VY
Maximum range airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90 KIAS Minimum rate-of-descent airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60 KIAS
If situation permits: 3. EMER SHD BUS sw
– Lift guard, ON
4. Double engine emergency shutdown
– Perform
ENGINE 3 – 112
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
AT APPROXIMATELY 100 FT AGL: 5. Flare attitude
– Establish (approx. 15_ to 20_) to reduce forward speed and rate of descent; control NR
AT APPROXIMATELY 8 – 12 FT AGL: 6. Flare attitude
– Reduce to approx 10_
7. Heading
– Maintain
8. Collective lever
– Raise to stop cushion landing
and
After landing:
O
The appropriate values must be adjusted according to prevailing conditions of gross mass, wind and terrain.
O
T
C
NOTE
– OFF
N TR
9. BAT MSTR sw
O
LL
ED
descent
PY
N
3.8.4.3 Single engine emergency shutdown
PRIOR TO PERFORMING THE ENGINE EMERGENCY SHUTDOWN IN FLIGHT, THE PILOT SHALL DOUBLE–CHECK THAT THE AFFECTED ENGINE WILL BE SHUT DOWN. THE MASTER LIST WILL INDICATE WHICH ENGINE IS AFFECTED. ADDITIONAL INDICATIONS IN CASE OF ENGINE FAILURE ARE TO BE FOUND ON THE VMS PAGE (E.G. N1 BELOW 60%, N2 BELOW NR AND BELOW THE OTHER ENGINE’S N2, ZERO OIL PRESSURE). IN CASE OF DOUBT, DO NOT PERFORM A SINGLE ENGINE EMERGENCY SHUT DOWN UNTIL AFTER LANDING.
TI
O N
O N
LY
–
C
O
WARNING
ST
R
U
C
NOTE D Before performing an inflight single engine emergency shutdown, determine if the situation will allow for OEI flight (level flight at Vy).
FO
R
IN
D Make certain that: –
the collective lever is adjusted to maintain the normal engine within the OEI limits
Procedure 1. Affected engine ENG MAIN sw
– IDLE, check NR, ENGi IDLE indicated
2. Affected engine ENG MAIN sw
– OFF, ENGi FAIL indicated
If there is an indication that the engine is still running: 3. Affected engine EMER OFF sw (labeled – Lift guard FIRE) – Press and release – Check FUEL comes on
VALVE
CLSD
continued APPROVED Rev. 9
ENGINE 3 – 113
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EFFECTIVITY
H/C before Maintenance Release 1 installed: Before HELIONIX Step 2.0.3 or before ASB MBB–BK117 D–2–42A–005 (HELIONIX Step 2.0.3)
OR H/C after Maintenance Release 1 installed: Before HELIONIX Step 3.0.2 or before ASB MBB–BK117 D–2–42A–005(HELIONIX Step 3.0.2)
IF THE AIRCRAFT DESCENDS MORE THAN 3000 FT FOLLOWING A SINGLE ENGINE FAILURE OR SHUT DOWN, AN ERRONEOUS LOW NR ALERT MAY BE TRIGGERED. IN THIS CASE, PROCEED AS FOLLOWS:
LL
ED
WARNING
– Maintain above 98%
2. NR low warning tone
– Disregard, use ACK pb (cyclic grip) to reduce volume
3. Amber chevrons in FLI
– Disregard
4. Amber NR indication on NR gauge
– Disregard, monitor digital NR value
PY
All
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
EFFECTIVITY
N
O
T
C
O
N TR
O
1. Digital NR
ENGINE 3 – 114
APPROVED Rev. 16
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.8.4.4 Inflight restart NOTE
An inflight restart may be attempted after a flameout or shutdown subject to the pilot‘s evaluation of the cause of flameout. DO NOT ATTEMPT INFLIGHT RESTART IF CAUSE OF ENGINE FAILURE IS OBVIOUSLY MECHANICAL.
CAUTION Procedure
– Adjust to OEI MCP or below
2. Electrical consumption
– Reduce
3. ENG MAIN sw (affected engine)
– OFF
4. Caution indication
– Check no FADEC FADEC DEGRADED
5. FUEL PRIME PUMP sw (affected engine)
– ON, FUELi indicated
6. ENG MAIN sw (affected engine)
– FLIGHT
FAIL
or
PRIME
PUMP
C
O
N TR
O
LL
ED
1. Collective lever
– As required
N
8. FUEL PRIME PUMP sw (affected engine)
O
T
7. Electrical consumers
PY
If restart is not successful:
– OFF
C
O
9. LAND AS SOON AS PRACTICABLE
LY O N
Conditions/Indications
–
3.8.4.5 Single engine landing
O N
One engine inoperative (OEI)
FO
R
IN
ST
R
U
C
TI
Procedure LANDING APPROACH: 1. Rotor speed 2. Airspeed 3. Shallow approach ON FINAL, AT 50 FT AGL: 4. Airspeed 5. Rate of descent TOUCHDOWN: 6. Airspeed 7. Landing attitude 8. Collective lever
– Check – VY – Establish – 30 KIAS – Max. 500 ft/min – Reduce to minimum depending on power available – Establish – Raise as necessary to stop descent and cushion landing
AFTER LANDING:
APPROVED Rev. 9
9. Collective lever
– Lower slowly
10. Cyclic stick
– Maintain neutral position ENGINE 3 – 115
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.8.4.6 FLI degraded Conditions/Indications – FLI display degraded, some limits may not be correctly indicated – FND:
4
LL
Amber DEG flag on FLI
C
O
N TR
O
2
BKD2_FLH_0409_R
ED
D E G
O
T
Procedure 2. Select VMS page, whenever practicable.
LY
–
C
O
3. Continue flight
PY
N
1. Avoid using maximum power.
C
U
– FLI display failed
TI
Conditions/Indications
O N
O N
3.8.4.7 FLI failed
R
IN
ST
R
– FND:
FLI framed in red or
FL I
2
or FLI framed in amber, scale replaced by amber FLI flag
BKD2_FLH_0410_R
FO
4
Procedure 1. Select VMS page. 2. Observe indicated limits. 3. Continue flight ENGINE 3 – 116
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.8.4.8 Abnormal engine governing Conditions/Indications – Unusual N2/NR or engine parameter (N1, TOT, torque) oscillations without any FADEC alert or caution indications – Unusual mismatch between the engine parameters NOTE
A 5% torque mismatch between the engines is normal when one bleed valve is open and the other bleed valve is closed.
F ON GROUND
– Perform
N TR
O
1. Double engine shutdown
LL
ED
Procedure
F IN FLIGHT
– Select
2. Affected engine
– Identify. If it is not possible to positively identify the affected engine, continue the procedure with the engine suspected to be affected.
O
PY
N
O
T
C
O
1. VMS page
O N
LY
–
C
3. Affected engine FADEC EMER sw
– ON, ENGi FADEC EMER and ENGi FADEC DEGRADED indicated – Monitor engine parameters
O N
If the unusual behavior stops and NR governing is normal:
TI
4. LAND AS SOON AS PRACTICABLE – OFF
5. Other engine FADEC EMER sw
– ON – Monitor engine parameters
ST
R
U
4. Affected engine FADEC EMER sw
IN
C
If the unusual behavior continues:
FO
R
If the unusual behavior stops: 6. LAND AS SOON AS PRACTICABLE If the unusual behavior continues: 6. LAND AS SOON AS POSSIBLE
APPROVED Rev. 9
ENGINE 3 – 117
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.9
FIRE
3.9.1
Warning indications FIRE If cargo compartment separation wall is installed
CARGO SMOKE
on Warning Unit
ED
EFFECTIVITY
O
LL
and audio tone and
N TR
CARGO SMOKE
on ML
N
O
T
C
O
and voice message “SMOKE, CARGO SMOKE”
PY
Conditions/Indications
C
O
– Smoke has been detected in cargo compartment
–
Procedure
LY
F ON GROUND
– Perform
2. Passengers
– Alert/Evacuate
O N
O N
1. Double engine emergency shutdown
– Extinguish if possible
R
ST
F IN FLIGHT
U
C
TI
3. Fire
– Alert
2. Heating/Air conditioning (if installed)
– OFF
3. Fire
– Extinguish if possible
4. Fumes, smoke, fire extinguishing fumes/gas
– Eliminate, open doors, windows and vents (fresh air)
FO
R
IN
1. Passengers
CAUTION NOTE
AVOID INHALATION OF FUMES, SMOKE, FIRE EXTINGUISHING FUMES/GAS.
The cargo compartment is accessible from the cabin by means of a small access door (separation wall) or a zip-fastener (quilted mats) which enable any person in the cabin to fight the fire using the hand fire extinguisher.
5. LAND AS SOON AS POSSIBLE EFFECTIVITY FIRE 3 – 118
All APPROVED Rev. 12
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
on Warning Unit and audio tone and
ENG1
FIRE
on ML
and voice message “FIRE, ENGINE ONE FIRE” or
ENG2
LL
and voice message “FIRE, ENGINE TWO FIRE”
on ML
ED
FIRE
N TR
O
Conditions/Indications
O
Overtemperature in engine compartment
T
C
Procedure
N
O
F ON GROUND
PY
1. FIRE sw (affected engine)
– Raise guard, press
Affected engine will shut down automatically, ACTIVE indicator light and BOT 1 label (EMER OFF SW panel), and FUEL VALVE CLSD caution indication come on. FIRE warning remains on as long as overheat condition exists.
LY
–
C
O
NOTE
– Check OFF
3. BOT 1/BOT 2 pb
– Press; bottle 1 activated;
O N
O N
2. Both FUEL PRIME PUMP sw’s
C
TI
– EXT indicator light comes on (EMER OFF SW panel)
Extinguisher bottle will begin discharging when N1t 45%. After discharge of bottle contents, BOT 1 label and EXT indicator light go off; BOT 2 label comes on.
4. Clock stop watch
– Start, after BOT1 and EXT light extinguish
5. Both ENG MAIN sw’s
– OFF
6. Passengers
– Alert/Evacuate
FO
R
IN
ST
R
U
NOTE
If situation permits and FIRE warning is still on after 1 minute: 7.
BOT 1/BOT 2 pb
– Press; bottle 2 activated; – EXT indicator light comes on (EMER OFF SW panel)
8.
BAT MSTR sw
– OFF continued:
APPROVED Rev. 9
FIRE 3 – 119
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F IN FLIGHT
1. OEI flight condition
– Establish
2. FIRE sw (affected engine)
– Raise guard, press
Affected engine will shut down automatically, ACTIVE indicator light, BOT 1 label (both EMER OFF SW panel), and FUEL VALVE CLSD caution indication come on. FIRE warning remains on as long as overheat condition exists.
NOTE
3. BOT 1/BOT 2 pb
– Press; bottle 1 activated;
ED
– EXT indicator light comes on (EMER OFF SW panel) Extinguisher bottle will begin discharging when N1t 45%. After discharge of bottle contents, BOT 1 label and EXT indicatior light go off; BOT 2 label comes on. – Start, after BOT1 and EXT light extinguish
5. VMS page
– Select
6. Affected engine
T
C
O
4. Clock stop watch
O
N TR
O
LL
NOTE
N
– Identify
– Perform
PY
7. Single engine emergency shutdown
– Alert
C
O
8. Passengers
LY
–
If FIRE warning disappears:
O N
9. LAND AS SOON AS POSSIBLE
O N
If FIRE warning is still on after 1 minute: BOT 1/BOT 2 pb
– Press; bottle 2 activated; – EXT indicator light comes on (EMER OFF SW panel)
R
U
C
TI
9.
ST
If FIRE warning remains on:
FO
R
IN
10. LAND IMMEDIATELY
FIRE 3 – 120
APPROVED Rev. 9
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3.9.2
Caution indications FIRE
FIRE BOT 1 USED or
FIRE BOT 2 USED or
LL
ED
FIRE BOT 1+2 USED
N TR
O
and audio tone
O
Conditions/Indications
C
– Respective fire extinguisher(s) not available or discharged
N
O
T
– Normal during FIRE TEST procedure (refer to Sect. 4.)
PY
Procedure
O
F ON GROUND
C
1. FIRE TEST sw
O N
F IN FLIGHT
NOTE
– Do not start
LY
–
2. Engines
– Check OFF
Indication normal following engine fire procedure and pressing BOT1/2 pb’s
O N
1. VMS page
TI
2. Engine indications
– Select – Monitor
U
C
If indications are normal:
ST
R
3. Continue flight 3. OEI flight condition
– Establish
4. Affected engine
– Identify
5. Single engine emergency shutdown
– Perform
FO
R
IN
If engine indications show abnormal behavior or oscillate:
6. LAND AS SOON AS PRACTICABLE
APPROVED Rev. 9
FIRE 3 – 121
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3.9.3
Emergency conditions FIRE
3.9.3.1 Cabin fire Conditions/Indications – Smoke, burning odor, flames Procedure F ON GROUND
– Perform
2. Passengers
– Alert/Evacuate
3. Fire
– Extinguish if possible
O
LL
ED
1. Double engine emergency shutdown
N TR
F IN FLIGHT
– VY recommended
2. Passengers
– Alert
3. Heating/air conditioning (if installed)
– OFF
N
O
T
C
O
1. Airspeed
– Extinguish if possible
O
– Eliminate, open doors, windows and vents (fresh air)
–
AVOID INHALATION OF FUMES, SMOKE, FIRE EXTINGUISHING FUMES/GAS.
O N
LY
CAUTION
C
5. Fumes, smoke, fire extinguishing fumes/gas
PY
4. Fire
6. LAND AS SOON AS POSSIBLE
O N
After landing:
– Perform
R
U
C
TI
7. Double engine emergency shutdown
IN
ST
3.9.3.2 Electrical fire/short circuit
FO
R
Conditions/Indications – Odor of burning insulation and/or acrid smoke Procedure F ON GROUND
1. Double engine emergency shutdown
– Perform
2. Passengers
– Alert/evacuate
3. EPU, if connected
– Disconnect
4. Fire
– Extinguish if possible
In flight procedure see next page FIRE 3 – 122
APPROVED Rev. 12
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ELECTRICAL FIRE / SHORT CIRCUIT continued F IN FLIGHT
WARNING
BE PREPARED FOR LOSS OF ALL ELECTRICAL SYSTEMS AND INDICATIONS, EXCEPT IESI.
If the source of smoke or fire can be positively identified: 1. Electrical power
– Remove from source (equipment OFF or C/B pull)
ED
If the source can not be identified: – OFF (SYS1 BUS TIE OPEN SYS2 caution present)
3. GEN 1 and GEN 2 sw’s
– OFF (GEN1 DISCONNECTED GEN2 caution and BAT DISCHARGING caution present)
O
T
C
O
N TR
O
LL
2. Both BUS TIE sw’s
N
4. Electrical consumers
– Alert
O
PY
5. Passengers
– Reduce as much as possible
–
C
NOTE D If conditions require open window(s) or sliding door(s) and vents for fresh air.
O N
LY
D If landing without electrical systems is possible (observe warning), switch off all electrical power sources.
U
C
TI
O N
D A generator reset should only be attempted when flight safety is at risk or the source of smoke or fire is positively identified and isolated from the electrical system.
R
6. Follow flow chart procedure (see next page) IN CASE OF TOTAL ELECTRICAL FAILURE:
FO
R
IN
ST
WARNING
D FUEL AVAILABLE WILL BE LIMITED TO QUANTITY CONTAINED IN SUPPLY TANKS AT TIME OF FAILURE AND THUS WILL LIMIT THE RESIDUAL FLIGHT TIME. D IESI WILL PROVIDE AIRSPEED, ALTITUDE AND ATTITUDE DATA FOR APPROXIMATELY 30 MIN. D ALL COM/NAV WILL BE LOST. D ALL MFD INDICATIONS WILL BE LOST. D ALL AIRCRAFT STABILIZATION WILL BE LOST.
NOTE D When operating on battery, flight endurance depends on battery type, loading and temperature. D When operating on battery, further see GEN1 DISCONNECTED GEN2 procedure. APPROVED Rev. 9
FIRE 3 – 123
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
Fire / Smoke continues?
Landing without electrical systems possible?
Yes
No
BAT MSTR sw – OFF
Yes
LAND ASAP
No GEN 2 sw – RESET, NORM
Fire / Smoke continues?
LL
ED
BAT MSTR sw – OFF
GEN 1 sw – RESET, NORM
N TR
O
Yes
GEN 2 sw – OFF
C
O
No
O
T
LAND AS SOON AS
PY
Fire / Smoke continues?
O
LAND AS SOON AS PRACTICABLE
–
C
Yes
Landing within 30 minutes possible?
N
PRACTICABLE
LY
within 30 minutes
O N
No
LAND AS SOON AS PRACTICABLE
Yes
LAND ASAP
ST
R
U
C
TI
O N
WARNING: By switching ”ON” the generators, the electr. fire can restart. This may lead to severe additional damage to the aircraft.
No
FO
R
IN
GEN 2 sw – RESET, NORM
Fire / Smoke restarts?
Yes
GEN 1 sw – RESET, NORM GEN 2 sw – OFF LAND AS SOON AS PRACTICABLE
No LAND AS SOON AS PRACTICABLE
FIRE 3 – 124
The steps in this Flow–Chart are not memory items.
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.10
FUEL AND WEIGHT
3.10.1
Warning indications FUEL
LOW FUEL1
LOW FUEL2
and/or
on Warning Unit
LOW
on ML
N TR
O
and voice message “FUEL ONE, LOW” and/or
LL
FUEL1
ED
and audio tone and
FUEL2
on ML
C
O
LOW
N
O
T
and voice message “FUEL TWO, LOW”
PY
Conditions/Indications
C
O
– Respective supply tank fuel quantity below 26 kg
LY
–
Procedure
– Start stopwatch
O N
1. Clock
O N
If one LOW FUEL warning light is on: 2. Expect single engine failure (after approx. 10 minutes)
C
TI
If both LOW FUEL warning lights are on:
ST
R
U
2. LAND WITHIN 8 MINUTES
FO
R
IN
WARNING
AFTER 8 MINUTES, A FLAME OUT OF BOTH ENGINES MUST BE EXPECTED. IF NO ADEQUATE LANDING SITE IS FOUND WITHIN 8 MINUTES, CONSIDER PERFORMING A POWER ON IMMEDIATE LANDING.
3. Fuel quantity indication WARNING
– Check
IRRESPECTIVE OF FUEL QTY INDICATIONS, LOW FUEL WARNING PROCEDURE SHALL BE OBEYED.
If positive fuel indication in the main tank: 4. FUEL XFER PUMP A and F sw’s
– Check ON
5. FUEL XPMP–A and –F cb’s
– Check in continued:
APPROVED Rev. 9
FUEL AND WEIGHT 3 – 125
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
NOTE
Due to sloshing fuel, the LOW FUEL indication on the warning unit may come on/off a few times. The indication on the master list is automatically latched for 60 seconds.
If both LOW FUEL warning lights remain on: 6. LAND WITHIN 8 MINUTES AFTER 8 MINUTES, A FLAME OUT OF BOTH ENGINES MUST BE EXPECTED. IF NO ADEQUATE LANDING SITE IS FOUND WITHIN 8 MINUTES, CONSIDER PERFORMING A POWER ON IMMEDIATE LANDING.
LL
ED
WARNING
N TR
O
If one LOW FUEL warning light remains on:
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
6. Expect single engine failure (after approximately 10 minutes)
FUEL AND WEIGHT 3 – 126
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.10.2
Caution indications FUEL
AFT FUEL PUMP and audio tone Conditions/Indications
Procedure
LL
ED
– Aft fuel transfer pump failed or switched off
– Check
2. FUEL XFER PUMP A sw
– Check ON
3. FUEL XPMP–A cb
– Check in
C
O
N TR
O
1. Fuel level in the main tank
N
O
T
4. Continue flight, consider unusable fuel
O
PY
NOTE D Each fuel transfer pump is capable of feeding more fuel than both engines will consume.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
D In the event of aft fuel transfer pump failure the main tank unusable fuel increases to 33 liter / 26 kg.
APPROVED Rev. 15
FUEL AND WEIGHT 3 – 127
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
AFT+FWD FUEL PMP and audio tone
Conditions/Indications – AFT and FWD fuel pumps failed or switched off
– Check ON
3. FUEL XPMP–A and F cb
– Check in
LL
2. FUEL XFER PUMP A and F sw
O
– Check
N TR
1. Fuel level in the main tank
ED
Procedure
O
When FUEL RESERVE appears:
T
C
4. LAND WITHIN 20 MIN
N
O
NOTE D Be prepared for FUEL RESERVE caution indication.
PY
D Be prepared for LOW FUEL 1/2 warning indications.
O
D The FND shows the correct usable fuel quantity.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
D The aircraft weight calculation and VNE indication is unaffected.
FUEL AND WEIGHT 3 – 128
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
FUEL QTY DEG and audio tone
Conditions/Indications – Failure of one main tank sensor
LL
ED
NOTE D The degraded fuel quantity indication represents the minimum fuel level within pitch attitude ranges of –3° to +6°.
N TR
O
D Aircraft weight calculation will no longer be updated. The last valid fuel quantity is used for computation of the weight and VNE.
O
T
C
O
D To check the remaining flight time, the most accurate fuel reading will be obtained at zero degree pitch attitude (~100 kt).
N
Procedure
PY
1. Level flight
O
2. Fuel quantity
– Read – Verify destination can reached with remaining fuel
be
– Select if required
FO
R
IN
ST
R
U
C
TI
O N
O N
4. Alternate destination
LY
–
C
3. Remaining flight time
– Establish, 100 kt if feasable
APPROVED Rev. 9
FUEL AND WEIGHT 3 – 129
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
FUEL QTY FAIL and audio tone
Conditions/Indications – Failure of the fuel quantity indication system (both main sensors or one supply sensor is inoperative).
N TR
O
LL
ED
CAUTION D PART OF THE FUEL QUANTITY INDICATION SYSTEM HAS FAILED. THE INDICATED FUEL QUANTITY MAY BE LOWER THAN THE ACTUAL FUEL QUANTITY.
C
O
D THE LOW FUEL WARNING AND ”FUEL LOW” VOICE MESSAGE REMAIN FULLY OPERATIONAL. THE LOW FUEL WARNING IS INDEPENDENT OF THE FUEL QUANTITY INDICATION.
PY
N
O
T
D AIRCRAFT WEIGHT CALCULATION WILL NO LONGER BE UPDATED. THE LAST VALID FUEL QUANTITY IS USED FOR COMPUTATION OF THE WEIGHT AND VNE.
C
O
Procedure
–
If indicated fuel quantity is sufficient to reach the destination:
LY
1. Fuel quantity
– Monitor
O N
2. Continue to destination or proceed to a suitable closer alternate landing site
O N
If indicated fuel quantity is not sufficient to reach the destination: – Monitor
TI
1. Fuel quantity
FO
R
IN
ST
R
U
C
2. Select suitable alternate landing site which can be reached with the indicated fuel quantity.
FUEL AND WEIGHT 3 – 130
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
Before Helionix Maintenance Release 1
EFFECTIVITY
FUEL RESERVE and audio tone Conditions/Indications
ED
– Both fuel pumps are running “dry“, or fuel in the left supply tank is less than 42 kg (52 liters, 92 lbs, 14 US gallons), or fuel in the right supply tank is less than 48 kg (60 liters, 105 lbs, 16 US gallons).
N TR
O
LL
– FND fuel indicationVMS fuel indication
54
41
0
51
46
0
47
O
45
N
47
T
C
O
LOW
O N
LY
–
C
O
PY
146 Kg
C U
FO
R
IN
BKD2_FLH_0412_R
ST
R
92 Kg
TI
O N
LOW
LOW
93 Kg
NOTE D Up to approximately 45 kg (56 liters, 100 lbs, 15 US gallons) of fuel may still be indicated in the main tank even if both pumps are running “dry”. The supply tanks will be shown in amber. continued: APPROVED Rev. 9
FUEL AND WEIGHT 3 – 131
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
D If attitude changes are made, fuel may run back from the supply tank to the main tank. This may cause the FUEL RESERVE caution to disappeartemporarily. At the latest, the FUEL RESERVE caution will remain when the fuel quantity in the supply tanks is below 42 kg (left tank) or 48 kg (right tank). Procedure – Check
2. Remaining flight time
– Verify destination can be reached with the remaining fuel quantity
3. AFT+FWD FUEL PMP procedure
– Perform
O
If the caution AFT+FWD FUEL PMP is present:
LL
ED
1. Fuel quantity
O
The FUEL LOW warning is independent from the FUEL RESERVE caution.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
NOTE
N TR
– Land within 20 minutes
FUEL AND WEIGHT 3 – 132
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
After Helionix Maintenance Release 1
EFFECTIVITY
FUEL RESERVE and audio tone Conditions/Indications – Fuel in the left supply tank is less than 42 kg (52 liters, 92 lbs, 14 US gallons), or fuel in the right supply tank is less than 48 kg (60 liters, 105 lbs, 16 US gallons).
LL
ED
– FND fuel indicationVMS fuel indication
N TR
0
51
C
O
41
BKD2_FLH_0412_R
O
LOW
T
92 Kg
N
O
146
PY
Procedure
O
1. Fuel quantity
LY
–
C
2. Remaining flight time
– Check – Verify destination can be reached with the remaining fuel quantity
O N
If the caution AFT+FWD FUEL PMP is present:
R
U
C
The FUEL LOW warning is independent from the FUEL RESERVE caution. All
FO
R
IN
EFFECTIVITY
– Land within 20 minutes
ST
NOTE
– Perform
TI
O N
3. AFT+FWD FUEL PMP procedure
APPROVED Rev. 9
FUEL AND WEIGHT 3 – 133
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
FUEL1
PRESSURE and / or
PRESSURE
FUEL2
and audio tone Conditions/Indications
Procedure
O
LL
1. Be prepared for single/double engine failure (affected engine).
ED
– Engine fuel pump inlet pressure low
– ON; FUEL PRIME PUMP ON caution indication will come on.
N TR
2. FUEL PRIME PUMP sw (affected engine)
C
O
If FUEL PRESSURE caution indication goes off:
O
N
If FUEL PRESSURE caution indication remains on:
T
3. LAND AS SOON AS PRACTICABLE
– OFF
PY
3. FUEL PRIME PUMP sw
O
If one engine is affected:
C
4. LAND AS SOON AS PRACTICABLE
LY
–
If both engines are affected:
PRIME PUMP ON and / or
PRIME PUMP ON
FO
R
IN
ST
R
U
C
FUEL1
TI
O N
O N
4. LAND AS SOON AS POSSIBLE
FUEL2
and audio tone
Conditions/Indications – Prime pump(s) switched ON Procedure 1. FUEL PRIME PUMP sw
– OFF (unless there is a specific need to keep the prime pumps on, e.g. low fuel pressure)
NOTE D Prime pumps must be OFF during normal flight operations. D Normal during engine start (refer to Sect. 4) FUEL AND WEIGHT 3 – 134
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
FWD FUEL PUMP and audio tone Conditions/Indications – Forward fuel transfer pump failed or switched off
– Check
2. FUEL XFER PUMP F sw
– Check ON
3. FUEL XPMP–F cb
– Check in
O
LL
1. Fuel level in the main tank
ED
Procedure
O
N TR
4. Continue flight, consider unusable fuel
O
T
C
NOTE D Each fuel transfer pump is capable of feeding more fuel than both engines will consume.
LY
–
C
O
PY
N
D In the event of forward fuel transfer pump failure the main tank unusable fuel increases to 16 liter / 13 kg.
and audio tone
TI
O N
O N
JET FUEL PUMP
C
Conditions/Indications
Caution indication may come on when main tank is nearly empty.
IN
NOTE
ST
R
U
– Aft main tank jet pump is not capable of delivering fuel to forward main tank.
R
Procedure
FO
1. FUEL XFER PUMP F + A sw
– Check ON
2. Continue flight, consider unusable fuel
NOTE D If JET FUEL PUMP caution indication remains on, the main tank unusable fuel increases to 72 liter / 58 kg. The aft main fuel tank volume is no longer used in the indication of the remaining fuel quantity. D The JET FUEL PUMP caution may come on when the fuel temperature is below –40_C and fuel density is high. D The aircraft weight calculation and VNE indication is unaffected.
APPROVED Rev. 15
FUEL AND WEIGHT 3 – 135
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EFFECTIVITY
After Helionix Maintenance Release 1
WEIGHT EXCEEDED and audio tone Conditions/Indications – The indicated aircraft weight exceeds the maximum takeoff weight. Procedure entered
N TR
O
If the indicated weight is correct: 2. Reduce weight as required.
C
O
All
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
EFFECTIVITY
is
ED
– Check weight correctly
LL
1. Weight page
FUEL AND WEIGHT 3 – 136
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
EFFECTIVITY
Before Helionix Maintenance Release 1
MAIN FUEL LOW Conditions/Indications – One main tank fuel pump is running “dry“.(fuel quantity in the main tank is below approximately 50 kg, 62 liters, 110 lbs, 16 US gallons).
– Check
O
If the fuel level in the main tank is above 50 kg:
LL
1. Fuel quantity
ED
Procedure
– Check ON
3. Remaining flight time
– Land within 20 minutes. The fuel quantity indication must be considered unreliable
T
C
O
N TR
2. FUEL XFER PUMP A and F sw
N
O
NOTE D Be prepared for FUEL RESERVE caution indication
–
After Helionix Maintenance Release 1
O N
LY
EFFECTIVITY
C
O
PY
D If attitude changes are made, the MAIN FUEL LOW indication may temporarily disappear.
TI
O N
MAIN FUEL LOW
U
C
Conditions/Indications
ST
R
– One main tank fuel pump is running “dry” (fuel quantity in the main tank is below approximately 50 kg, 62 liters, 110 lbs, 16 US gallons). or
R
IN
– main fuel quantity is below 32 kg (40 liters, 70 lbs, 10 US gallons).
FO
Procedure 1. Fuel quantity
– Check
If the fuel level in the main tank is above 50 kg: 2. FUEL XFER PUMP A and F sw
– Check ON
3. Remaining flight time
– Land within 20 minutes. The fuel quantity indication must be considered unreliable
NOTE D Be prepared for FUEL RESERVE caution indication D If attitude changes are made, the MAIN FUEL LOW indication may temporarily disappear. EFFECTIVITY APPROVED Rev. 9
All FUEL AND WEIGHT 3 – 137
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3.11
GEARBOX AND DRIVE SYSTEM
3.11.1
Failure conditions TAIL ROTOR
3.11.1.1 Tail rotor drive failure - hover Conditions/Indications Complete loss of tail rotor thrust – Tail rotor failure in power-on flight is indicated by a severe yawing motion nose right.
ED
Procedure
N TR
O
LL
F HOVER IN GROUND EFFECT
– Establish
2. Collective lever
– Lower immediately
O
1. Landing attitude
T
C
After landing:
– Perform
N
O
3. Double engine emergency shutdown
O
PY
F HOVER OUT OF GROUND EFFECT
C
1. Collective lever 2. Airspeed
– Increase – Raise to stop descent
O N
3. Collective lever
O N
LY
–
If height permits:
– Lower immediately
TI
After landing:
– Perform
FO
R
IN
ST
R
U
C
4. Double engine emergency shutdown
GEARBOX AND DRIVE SYSTEM 3 – 138
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.11.1.2 Tail Rotor Drive Failure/Fixed-pitch Tail Rotor Control Failure - Forward Flight Conditions/Indications – No directional response after pedal inputs and/or – Complete loss of tail rotor thrust and/or – Blocked pedals NOTE
The procedure will vary depending on flight conditions, power setting and mass of the helicopter.
ED
Procedure – Adjust to obtain sideslip angle
minimum
2. Airspeed
– Maintain 70 KIAS or higher
3. Suitable landing area
– Select
O
N TR
O
LL
1. Collective lever
T
C
NOTE D Landing surface should be hard (e.g. concrete, asphalt) and flat.
PY
N
O
D Landing area should permit running landing – a runway is preferable
– Perform
–
C
4. Shallow approach with nose left
O
D Left crosswind is advantageous
U
C
TI
5. Airspeed
O N
O N
LY
If the airspeed can be reduced below appropriate low speed with the nose still pointing to the left:
– Perform
ST
R
6. Landing
– Reduce close to the ground until nose is aligned with the flight direction
FO
R
IN
If the nose direction changes from left to right at airspeeds higher than low speed: 5. Airspeed
– Increase
6. Approach
– Abort, climb to sufficient height for autorotation
NOTE
Headwind is advantageous
7. Autorotation glide
– Establish
8. Double engine emergency shutdown
– Perform
9. Autorotation landing
– Perform
NOTE D In final phase of flare the helicopter can yaw to the left due to friction effects. D Before touchdown, the ground speed should be reduced to a minimum APPROVED Rev. 9
GEARBOX AND DRIVE SYSTEM 3 – 139
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.11.2
Warning indications GEARBOX
MGB OIL P
on Warning Unit
and audio tone and
MGB LOW PRESS
N TR
O
LL
and voice message “MAIN GEARBOX, LOW PRESSURE”
ED
on ML
O
Conditions/Indications
C
– Main gearbox oil pressure is below minimum
O
T
– Transmission oil pressure indication 1 bar or less (SYS 1 and 2)
PY
N
Procedure
– Perform
–
When landing, shutting down or starting up on a slope, the MGB LOW PRESS warning may appear.
LY
NOTE
C
1. Single / double engine shutdown
O
F ON GROUND
O N
F IN FLIGHT
O N
1. Power
TI
2. Airspeed
– Reduce – Set to VY
R
U
C
3. LAND IMMEDIATELY (maximum 15 min)
IN
ST
NOTE D Descend with minimum power.
FO
R
D Main gearbox loss of oil capability has been demonstrated on a bench test (at power setting for VY) for 30 minutes.
GEARBOX AND DRIVE SYSTEM 3 – 140
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.11.3
Caution indications GEARBOX
MGB CHIP
ED
and audio tone
LL
Conditions/Indications
N TR
O
– Metal particles detected in the main gearbox.
C
O
Procedure
O
N
Reduce power as much as possible.
LY
–
C
O
PY
NOTE
T
1. LAND AS SOON AS PRACTICABLE
O N
MGB HIGH TEMP
U
C
TI
O N
and audio tone
ST
R
Conditions/Indications
FO
R
IN
– Gearbox oil temperature above maximum.
Procedure 1. VMS page
– Select
2. MGB oil temperature and oil pressure indication
– Check
If indications are out limits: 3. Power
– Reduce, as much as possible
If oil temperature indication remains out of limits: 4. LAND AS SOON AS POSSIBLE If indications are within limits: 4. LAND AS SOON AS PRACTICABLE APPROVED Rev. 9
GEARBOX AND DRIVE SYSTEM 3 – 141
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MGB OVERLIMIT and audio tone Conditions/Indications – Main gearbox temperature or pressure outside of the normal operating range
– Select
2. MGB parameters
– Check
Be prepared for MGB HIGH TEMP caution indication or MGB LOW PRESS warning indication.
N TR
NOTE
O
LL
1. VMS page
ED
Procedure
C
O
3. LAND AS SOON AS PRACTICABLE
N
O
T
NOTE D If MGB oil pressure is low on one system only (e.g. sideward flight, lateral slope landing), MGB OVERLIMIT will appear after 7 min.
O N
LY
–
C
O
PY
D During lateral slope landing, MGB OVERLIMIT may appear as soon as the collective is lowered.
O N
ROTOR BRAKE
C
TI
and audio tone
R
U
Conditions/Indications
R
IN
ST
– Rotor brake engaged
FO
Procedure
1. Rotor brake lever
– Check fully down
If the ROTOR BRAKE caution remains on: 2. LAND AS SOON AS POSSIBLE NOTE
Engines will not start with rotor brake engaged
GEARBOX AND DRIVE SYSTEM 3 – 142
APPROVED Rev. 9
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TGB CHIP and audio tone
Conditions/Indications – Metal particles detected in the tail rotor gearbox
ED
Procedure
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
1. LAND AS SOON AS PRACTICABLE
APPROVED Rev. 9
GEARBOX AND DRIVE SYSTEM 3 – 143
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3.11.4
White advisories GEARBOX
MGB CHIP SENSOR
ED
Conditions/Indications
O
MGB CHIP CAUTION IS NOT AVAILABLE.
N TR
CAUTION
LL
– MGB chip detector continuity test failure
O
Procedure
C
F ON GROUND
O
T
1. A flight to complete the mission may be performed in accordance with MMEL/MEL.
N
F IN FLIGHT
O
C
After each flight, chip sensors must be checked to be free of metal particles before further flights are conducted.
MGB TREND
ST
R
U
C
TI
O N
O N
LY
–
NOTE
PY
1. Continue flight
IN
Conditions/Indications
FO
R
– MGB oil temperature or pressure unusually high or low but still in normal range. Procedure 1. VMS page
– Select
2. MGB parameters
– Monitor
3. Continue flight NOTE D Be prepared for MGB OVERLIMIT or MGB HIGH TEMP caution indications, or LOW PRESS warning D If MGB oil pressure is low on one system only (e.g. sideward flight, lateral slope landing) MGB TREND will appear after 5 min. D During lateral slope landing, MGB TREND may appear as soon as the collective is lowered. GEARBOX AND DRIVE SYSTEM 3 – 144
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
TGB CHIP SENSOR
Conditions/Indications – TGB chip detector continuity test failure
ED
TGB CHIP CAUTION IS NOT AVAILABLE.
CAUTION
LL
Procedure
O
F ON GROUND
N TR
1. A flight to complete the mission may be performed in accordance with MMEL/MEL.
O
F IN FLIGHT
T
O
After each flight, chip sensor must be checked to be free of metal particles before further flights are conducted.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
NOTE
C
1. Continue flight
APPROVED Rev. 9
GEARBOX AND DRIVE SYSTEM 3 – 145
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.12
HYDRAULICS
3.12.1
Caution indications HYDRAULICS
HYD1
LOW PRESS or
ED
HYD2
LL
LOW PRESS
N TR
O
and audio tone
O
Conditions/Indications
O
DO NOT OPERATE TEST HYD SWITCH IN FLIGHT.
N
WARNING
T
C
– Pressure loss in the affected system, the normal system retains power.
PY
Procedure
O N
LY
–
C
O
1. LAND AS SOON AS PRACTICABLE
O N
HYD OVERLIMIT
ST
R
U
C
TI
and audio tone
IN
Conditions/Indications
FO
R
– Hydraulic pressure out of normal range
Procedure 1. VMS page
– Select
2. HYD parameters
– Check
3. Affected system
– Identify
4. LAND AS SOON AS PRACTICABLE NOTE
HYDRAULICS 3 – 146
Be prepared for HYDi LOW PRESS caution
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
HYD1
TR SHUT OFF and audio tone
Conditions/Indications – Tail rotor hydraulic shut–off valve (SYS 1) has activated IN COMBINATION WITH A FAILURE OF HYDRAULIC SYSTEM 2, FENESTRON ACTUATION WILL BE LOST.
N TR
O
LL
ED
CAUTION
O
Procedure
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
1. LAND AS SOON AS PRACTICABLE
APPROVED Rev. 15
HYDRAULICS 3 – 147
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.12.2
White advisories HYDRAULICS
HYD TREND
ED
Conditions/Indications
LL
– Hydraulic pressure unusually high or low but still within normal operating range
N TR
O
Procedure F ON GROUND AFTER ENGINE START
– Perform
O
1. Single / double engine shutdown
T
C
F IN FLIGHT
– Select
O
1. VMS page
– Monitor (affected parameters indicated inverse video)
PY
N
2. HYD parameters
C
–
BE PREPARED FOR HYD OVERLIMIT OR HYD1/2 LOW PRESS CAUTION INDICATIONS
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
CAUTION
O
3. Continue flight
HYDRAULICS 3 – 148
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY AND MALFUNCTION PROCEDURES
3.13
LIGHT AND MEDIUM H/C ACTIVE VIBRATION CONTROL SYSTEM
LAVCS FAIL
ED
Conditions/Indications
LL
– No power on non-essential bus
O
– LAVCS switch in OFF position
N TR
– LAVCS failure after built in test on ground
O
– LAVCS failure or system automatically shut down due to excessive vibrations (> 0.5 g)
T O
If LAVCS is installed
N
EFFECTIVITY
C
Procedure
– Check PIL or PAX
– Check ON
O N
1. LAVCS sw All
O N
EFFECTIVITY
–
If LAVCS+ is installed
LY
EFFECTIVITY
C
O
PY
1. LAVCS sw
– Check in
TI
2. LAVCS cb
FO
R
IN
ST
R
U
C
3. Continue flight
APPROVED Rev. 15
LIGHT AND MEDIUM H/C ACTIVE VIBRATION CONTROL SYSTEM 3 – 149/(3 – 150 blank)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS Page 4–1 4–1 4–1 4–1 4–1 4–1
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PREPARATION FOR FLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flight restrictions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flight planning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Mission database . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Mass and balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4.3 4.3.1 4.3.2 4.3.2.1 4.3.2.2 4.3.2.3 4.3.2.4 4.3.2.5
PREFLIGHT CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 2 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 2 Exterior check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 2 Before exterior check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 3 Fuselage – right side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 4 Tail boom . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 7 Fuselage – left side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 8 Cabin – nose area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 11
4.3.3
Interior check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 11
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
4.1 4.2 4.2.1 4.2.2 4.2.3 4.2.4
STARTING ENGINES AND SYSTEM CHECKS NORMAL PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.4.1 Standard start-up procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.4.1.1 Pre-start check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.4.1.2 Starting Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.4.1.3 After engine start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4 4 4 4 4
– – – – –
13 13 13 16 20
ST
R
U
C
TI
O N
O N
4.4
STARTING ENGINES AND SYSTEM CHECKS QUICK START-UP PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 25 4.5.1 Additional pre-flight checks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 25 4.5.1.1 Starting phase . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 29
FO
R
IN
4.5
4.6
PRE-TAKEOFF CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 32
4.7
TAKEOFF CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 33
4.8
TAKEOFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 33
4.9
PRE-LANDING CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 34
4.10
LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 34
4.11
ENGINE SHUTDOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 35
4.12 4.12.1 4.12.2
FLIGHT CHARACTERISTICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 36 Flight controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 36 Recommended maximum rate-of-descent during hover or low speed flight . 4 – 36
APPROVED Rev. 15.1
4–i
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Page 4.13
IFR AND AFCS PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 37
4.13.1
Pre–flight check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 37
4.13.2
IFR Standard Instrument Departure (SID) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 37
4.13.3
IFR en-route navigation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 38
4.13.3.1 OBS navigation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 38 4.13.3.2 Parallel track . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 39 IFR approach navigation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 40
4.13.4
4.13.4.1 Holding pattern . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 40
ED
4.13.4.2 ILS approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 41
LL
4.13.4.3 LNAV or LP approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 42
N TR
O
4.13.4.4 LPV or LNAV/VNAV approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 43
O
4.13.4.5 Missed approach (GPS approaches only) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 44 4.13.4.6 Vectors-to-final . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 45 HTAWS (OPTIONAL) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 46
4.14.1
HTAWS operation and indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 46
4.14.2 4.14.3
Audio inhibition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 46 HTAWS standby . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 47
4.15
AHRS PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 48
4.15.1
Use of AHRS free steering mode (DG) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 48
4.16
HEATING AND VENTILATION SYSTEM PROCEDURES . . . . . . . . . . . . . . 4 – 49
4.16.1
Maximum defrosting / defogging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 49
4.16.2
Maximum heating in cockpit / cabin . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 49
4.16.3 4.16.4
Maximum ventilation / cooling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 50 Heating system on / off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 50
4.16.5
Selecting recirculated air . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 50
4.16.6
Use of electrical heater with EPU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 50
4.17 4.17.1
COLD WEATHER PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 51 MGB temperature below –30°C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 51
T
O
N
PY
O
C
–
LY
O N
O N
TI
C
U
R
ST
IN
R
Oil temperatures below –35°C during pre-flight test . . . . . . . . . . . . . . . . . . . 4 – 51
FO
4.17.3
C
4.14
4.18
SYSTEM (SEMI-)AUTOMATIC TESTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 52
4.18.1 4.18.2
Power-up test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 53 Lamp test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 59
4.18.3
Start-up test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 60
4.18.4
Pre-flight test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 – 61
LIST OF FIGURES Fig. 4-1
4 – ii
Exterior check sequence . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4–3
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
SECTION 4 NORMAL PROCEDURES 4.1
GENERAL This section contains instructions and recommended procedures which are peculiar to the operation of this helicopter.
O
A standard collective lever should be installed whenever mission equipment, which requires the use of a short collective, is removed and planned missions do no longer require this specific configuration.
C
O
NOTE
LL
PREPARATION FOR FLIGHT
N TR
4.2
ED
For definition of terms, abbreviations and symbols used in this section refer to section 1.
T
Flight restrictions
O
4.2.1
O
PY
N
The minimum, normal, maximum and cautionary operation ranges for the helicopter and its subsystems are indicated by instrument markings, placards and decals.
Flight planning
LY
4.2.2
–
C
For helicopter and subsystem restrictions refer to section 2, Limitations.
TI
Before flight it is necessary to check that the fuel grade is selected properly relative to fuel temperature/altitude limitations given in section 2.
ST
Mission databases
IN
4.2.3
R
U
C
NOTE
O N
O N
Refer to sections 5 and 9 to determine required fuel, airspeeds and power settings for takeoff, climb, cruise, hovering and landing data necessary to accomplish the mission.
Helionix Maintenance Release 1
R
EFFECTIVITY
FO
CAUTION
EFFECTIVITY
LOADING OR SWAPPING THE MISSION DATABASE IN FLIGHT COULD LEAD TO LOSS OF THE SVS IMAGE. NEVER LOAD OR SWAP THE MISSION DATABASE IN FLIGHT.
All
If the use of mission databases (HTAWS, DMAP, SVS) is planned, check that the databases are not expired. Database expiry date can be checked on the VMS/SYST page using the DATAB pb. 4.2.4
Mass and balance The takeoff and anticipated landing gross mass and balance should be obtained before takeoff and checked against mass and load limits and center of gravity restrictions (see section 2).
APPROVED Rev. 17
4–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
For pre-flight checks and flight preparations on ground with engines running, fuel up to 20 kg in excess of the maximum gross mass can be taken on board (fuel burn rate with both engines at idle is approximately 1.7 kg/min). The pilot is responsible to ensure that the aircraft mass at takeoff does not exceed the maximum gross mass (see section 2). 4.3
PREFLIGHT CHECK
4.3.1
General The preflight check shall be accomplished in accordance with the flight manual, the maintenance manual or the pilot’s checklist.
LL
ED
The preflight check is not a detailed mechanical inspection, but essentially a visual check of the helicopter for correct condition.
O
N TR
O
This check shall be completed before each flight. However, items not marked with an asterisk (L) need only be checked before the first flight of the day or for aircraft on alert / on call status these items should be performed within a 24 hours cycle.
O
T
C
When unusual local conditions dictate, the extent and/or frequency of this check shall be increased as necessary to promote safe operation.
PY
N
NOTE D The following list contains only check items for the standard configuration.
–
C
O
D In addition to these items, check antennas and all installed optional equipment.
O N
LY
D Make certain that all relevant intermediate and special inspections in accordance with the maintenance manual have been complied with.
TI
O N
D For optional equipment check items, refer to the respective flight manual supplement or to the relevant chapter of the maintenance manual.
Exterior check
IN
4.3.2
ST
R
U
C
D When checking the “condition” of an item, the item shall be checked for external damage and proper seating. When checking if an item is “secured”, check if lockwire or other means of securing are properly installed.
FO
R
The exterior check is laid out as a walk-around check, starting forward right at the pilot’s door, proceeding clockwise to the tail boom, to the left hand side (including the upper and lower areas of the helicopter) and is completed at the helicopter nose area. NOTE D If possible, the helicopter should be headed into the wind before starting the engines. D The area around the helicopter should be clear of all foreign objects. D To avoid excessive drain on the helicopter battery, particularly during cold weather, all ground operations should be conducted using an external power unit (EPU) whenever possible. D When the battery is used, the operation of electrical equipment should be kept to a minimum.
4–2
APPROVED Rev. 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.3.2.1 Before exterior check Helicopter and mission documents
– Check, complete
L
Weight, CG
– Check
Fuel tanks / drain valves (5)
– Drained (see sec.8, para 8.3)
L
Fuselage underside / drain ports
– Condition, no fuel / oil leaks
L
Covers and tie-downs
– Removed
L
Ice and snow (if any)
– Removed
L
Ground handling wheels
– Removed
L
Equipment and cargo
– Secured
N TR
O
LL
ED
L
PY
2
3
–
C
O
BKD2_FLH_0004_R
5
N
O
T
C
O
1
–
Right side
2. Cabin
–
Roof
–
Aft area
4. Fuselage
–
Left side
5. Cabin
–
Front
C
TI
1. Fuselage
R
O N
O N
LY
4
Fig. 4-1
Exterior check sequence
FO
R
IN
ST
U
3. Tail boom
APPROVED Rev. 0
4–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.3.2.2 Fuselage – right side – Clear
OAT sensor
– Condition
Cockpit door
– Condition, function
Cockpit door sliding window (if installed)
– Open and close, check no dirt / ice in sliding rail
BAT MSTR sw
– Check, OFF
Fabric glare shield (before night flights)
– Check installed
Pilot seat and safety belt
– Condition, function
LL
O
N TR
EFFECTIVITY ELT RH side pilot seat
– Main switch to ARM
Sliding door
– Condition, function
Landing gear and step
– Condition
Landing gear dampers and fairing
– Condition, no leakage
Fuselage right side
– Condition
C
O
PY
N
O
T
C
O
ELT unit
Drain ports
O N
Static pressure drain port
O N
LY
–
Strobe light (if installed)
– Condition – Clear – Clear – Condition, secured
TI
Antennas on underside (if any)
U
C
Cabin top
ST
R
Cockpit windshield, upper part
– Condition, clean – Condition
Antennas (if any)
– Condition, secured
R
IN
Cabin air intake (if installed)
FO 4–4
ED
NACA cockpit air intake
Hydraulic access door
– Open
Hydraulic system
– Condition, no leakage, no foreign objects
Hydraulic actuators
– Condition, no leakage, free play
Hydraulic reservoirs (2)
– Condition, no leakage
Fluid level indicator 1, 2
– Check levels
Sight glasses 1, 2
– Check oil visible, air fills less than half of sight glass
Control rods
– Condition APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
SEMA actuators
– Condition, free play – Closed, secured
Hydraulic pump
– Condition, no leakage
Oil cooler fan inlet screen
– Clear
Oil cooler fan
– Condition, no leakage
L
Main transmission oil level
– Check (below –35°C, refer to Para. 4.17.2)
L
Transmission compartment
– No foreign objects
Sliding door
– Closed
Transmission compartment access door
– Open
LL O
Rotor brake fluid reservoir
– Fluid level, no leakage
Scavenge oil filter clogging indicator pin (if installed)
– Check in
Oil cooler
C
T
O
N
PY
O C –
O N
LY
Oil cooler block plate
– Check, clear – Installed, if OAT below –30°C 1) – Removed, if OAT above +35°C – Clear, condition – Condition, secured
LEngine oil level
– Check
Engine oil tank
– Condition, no leakage, security of attachment, filler cap closed and secured, drain plug closed and secured
ST
R
U
C
TI
O N
Oil cooler insulation
IN R
N TR
– Condition, no leakage
O
Transmission compartment
Oil cooler air inlet duct
FO
ED
Hydraulic access door
L
Generator air intake
– Clear
Engine air intake (incl. screen)
– Clear
Mixing lever assembly
– Condition
Main transmission
– Condition
Main transmission struts
– Condition, secured
Main transmission oil filter clogging indicator pins (2)
– Check in
1) Check for limitation in section 2.
APPROVED Rev. 15
4–5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Main transmission oil filter cap
L
Transmission compartment access door
– Closed, secured
Air opening in access door
– Clear
Swash plate and boot
– Condition, boot properly fixed
Rotating control rods
– Condition, free movement, secured
Rotating bearings
rod
spherical
– Check for smooth operation by moving control rods by hand
Main rotor head
– Condition, oil level, nuts secured (below –35°C, refer to Para. 4.17.2)
Blade attachment bolts, driving link assembly
– Condition, secured
Rotor hub cap
– Condition, secured
Vibration absorbers
– Condition, free movement, no leakage, secured
Rotor blades and trim tabs
– Condition, rotate rotor by hand in direction of rotation and check for free movement
–
LY
Erosion protection (PU film or anti-erosion paint, if fitted)
C
O
PY
N
O
T
C
O
N TR
O
LL
L
control
ED
L
– Secured, locked, marks matched
O N
O N
Static dischargers and bonding jumper
– Condition – Clear
C
TI
Engine compartment door air opening
– Condition, no seperation
– No leakage, no foreign objects – Check free wheeling
ST
Engine compartment
R
Drive shaft Engine
– Condition
Air/fuel separator pipe
– Check (no cracks)
Engine oil ducts
– No leakage
Bleed air hose
– Condition, secured
Engine wiring, connectors and pipes
– Condition, no leakage, no chafing
Engine wash system (if installed)
– Cap secured
FO 4–6
– Open
IN
R
U
Engine compartment access door
APPROVED Rev. 6.5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Fuel drain collector and drain pipes
– Condition
Engine exhaust pipe (fwd part)
– Condition, secured
Rear bearing oil ducts
– No leakage
Engine mounts and bushings
– Condition, secured
Engine compartment access door
– Closed, secured
L
Maintenance steps (5)
– Closed
Bleed air heater screen
– Clear
Circuit breaker for EPU
– Check in
EPU access door
– Closed, secured (if BAT start)
LL
O
L
ED
L
N TR
– Opened, EPU connected (if EPU start) Fuselage – right side
– Condition
L
Static ports (2)
– Clear
Battery
– Connected, condition, no electrolyte spillage, security of mounting, drain connected
PY
N
O
T
C
O
L
C
O
Battery door
L
–
Aft engine cowling
O N
LY
Engine exhaust pipe (rear part) Fire ext sys discharge indicator
O N
L
– Check red disk is present and undamaged – Check according to the pressure–temperature table
R
U
Engine must be cold for pressure–temperature table to be valid. – Condition, function – On board
ST
Clam shell doors
FO
R
First aid kit
L
– Condition
IN
NOTE
– Secured
C
TI
Fire ext bottle pressure indicators (2)
– Closed, secured
Avionic rack
– Condition, secured
Clam shell doors
– Closed, secured
4.3.2.3 Tail boom L
L
APPROVED Rev. 9
Tail boom – right side
– Condition
Antenna(s) (if installed)
– Condition, secured
External multipurpose lights (if installed)
– Condition
RH horizontal stabilizer, position light, bonding jumpers, IR flasher and formation light (if installed)
– Condition
4–7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
L
Position light, anti-collision light, tail flood light, IR flasher and formation light (if installed)
– Condition
Tail bumper
– Condition
Rear camera (if installed)
– Condition
Fenestron blades
– Condition
Fenestron rotor
– Check centered with fenestron structure (constant blade tip clearance), visual check, blade free play
Fenestron structure and fin, LH
– Condition
Stators
– Condition
Tail rotor gearbox
– No leakage
O
LL
ED
– Condition
N TR
L
Fenestron structure and fin, RH
C
O
– Check oil level in sight glass Tail rotor gearbox cover
– Condition, no foreign objects, secured
L
Tail rotor actuator
– Condition, no leakage
L
LH horizontal stabilizer, position light, bonding jumpers, IR flasher and formation light (if installed)
– Condition
L
Tail boom – left side
LY
–
C
O
PY
N
O
T
L
O N
Clam shell door windows (if installed)
O N
Antennas (if any)
– Condition, secured – Condition, clear – Condition
C
TI
Rear-view camera (if installed)
– Condition
– Clear
Bleed air heater screen
– Clear
Static ports (2)
R
IN
L
ST
R
U
4.3.2.4 Fuselage – left side
– Secured
Engine exhaust pipe (rear part)
– Condition
Formation light (if installed)
– Condition
Engine compartment access door
– Open
FO
Aft engine cowling
4–8
Engine compartment
– No leakage, no foreign objects
Fuel drain tank and drain pipes
– Condition
Engine mounts and bushings
– Condition, secured
Rear bearing oil ducts
– No leakage
Engine exhaust pipe (forward part)
– Condition, secured
APPROVED Rev. 11.3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Engine wiring, connectors and pipes
– Condition, no leakage, no chafing
Engine oil ducts
– No leakage
Bleed air hose
– Condition, secured
Engine
– Condition
Drive shaft
– Condition, secured
Air/fuel separator pipe
– Check (no cracks) – Closed, secured
Transmission compartment access door
– Open
Scavenge oil filter clogging indicator pin (if installed)
– Check in
O
LY
–
C
Mixing lever assembly Main transmission
C
T
O
PY
– Clear
Engine air intake
– Clear – Condition, secured – Condition – Condition, secured
LEngine oil level
– Check
Engine oil tank
– Condition, no leakage, security of attachment, filler cap closed and secured, drain plug closed and secured
ST
R
U
C
TI
O N
O N
Main transmission struts
Oil cooler
– Clear, condition
Oil cooler insulation
– Condition, secured
Oil cooler block plate
– Installed, if OAT below –30°C 2)
IN R
N TR
– Condition, no leakage
O
Transmission compartment
Generator air intake
FO
O
LL
Engine compartment access door
ED
– Cap secured
N
L
Engine wash system (if installed)
– Removed if OAT above +35°C Oil cooler air inlet duct
– Check clear
L
Transmission compartment access door
– Closed, secured
L
Transmission compartment
– No foreign objects
Air opening in access door
– Clear
2) Check for limitation in section 2. APPROVED Rev. 15
4–9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
– Closed
Oil cooler fan inlet screen
– Clear
Oil cooler fan
– Condition, no leakage
Hydraulic pump
– Condition, no leakage
Hydraulic compartment door
– Closed, secured
Cockpit windshields, upper part
– Condition, clean
Landing gear and step
– Condition
Landing gear dampers and fairing
– Condition, no leakage
L
Fuel filler cap
– Secured, locked
L
Fuel filler access door
– Closed
Antennas (if any)
– Condition, secured
Fuselage – left side
– Condition
Strobe light (if installed)
– Condition
Drain ports
– Clear
O N
LY
–
Cabin passenger seats and safety belts
O N
Cabin interior
TI
Sliding door
U
C
Cockpit door
– Loose items secured – Condition, function – Condition, function
Copilot seat and safety belt
– Condition, function
For single pilot flights: Copilot’s safety belts
– Fastened, secured
OAT sensor
– Condition
NACA Cockpit air intake
– Clear
Antenna on underside (if any)
– Condition, secured
ST
R
– Open and close, check no dirt / ice in sliding rail
R
IN
4 – 10
– Condition, function
Cockpit door sliding window (if installed)
FO
L
O
– Clear
C
Static pressure drain port
L
N TR
O
C
T
O
N
PY
L
O
L
LL
Maintenance steps (5)
L
ED
NORMAL PROCEDURES
APPROVED Rev. 4.2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.3.2.5 Cabin – Nose area
– Clear, condition
Windshield wipers
– Condition, stowed in center of windshield
Pedal areas
– No foreign objects
Landing lights
– Condition
Search light
– Condition, retracted if necessary
Fuselage bottom
– Condition
N TR
O
L
Pitot tubes (2)
ED
L
– Condition, clean
LL
L
Windshields, front and lower part
O
4.3.3L Interior check
– Stowed, secured
Hand fire extinguisher
– On board, check pressure
N
O
T
C
Baggage, cargo, loose items
– On board, check function
PY
Hand lamp
C
O
Passengers
– Adjust
O N
Adjust the seat fore-aft and (if available) up-down to find a comfortable seating position in which the imaginary plane extending from the top of the instrument panel meets the eye. Check that the warning unit is fully visible. Then adjust the pedals.
C
TI
O N
NOTE
LY
–
Seat and pedals
– Briefed
– Fasten, adjust
ST
R
U
Safety belts
FO
R
IN
NOTE D First pull the lap belts tight, then attach the shoulder harness. D All shoulder harnesses are equipped with an inertia reel, which will automatically lock the harness during strong deceleration. Some seats are equipped with a lever to lock the inertia reel manually. When a hard landing or ditching is likely and time permits, locking the inertial reel may provide additional safety. However, before the flight each pilot should ensure that all necessary switches (e.g. FIRE pushbuttons) can be reached.
Pilot/copilot door
NOTE
– Check all latches properly engaged (green indication visible)
For cold weather operations, close cabin heating outlets if required (refer to Para. 4.16.1). continued
APPROVED Rev. 17
4 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Overhead panel Switch guards
– Closed
All circuit breakers
– In
All switches
– OFF or NORM, priority NORM
– Guarded
ENG1 and 2 MAIN sw’s
– OFF
FADEC EMER 1 and 2 sw’s
– OFF and guarded
TRAINING pb
– Off
LL
EMER OFF 1 and 2 sw’s
ED
Instrument panel
N TR
O
ELT remote control unit (alternative on center console) ELT sw
T
– ARMED
C
O
EFFECTIVITY ELT RH side pilot seat
N
O
EFFECTIVITY ELT beside center console ELT sw LED/buzzer
C
O
PY
– RES/TST for at least 1 sec – One long signal/beep followed in 5 sec by a short signal/beep, test succesful – ARMED
–
ELT sw
O N
Static pressure switch
LY
Center console
TI
O N
Intercom sw (BACK-UP/NORM/SLAVED)
U
C
REARCAM sw (if installed)
ST
R
CCP MFD COPILOT sw
– NORM – OFF – NORM – As required
IN
PUSH FOR AIR/DEFOG lever
– Secured
R
Collective pitch levers – Set as required
Pilot collective
– Down & latched
Copilot collective
– Check type of collective installed and familiarize with location of grip and switches
Rotor brake
– Released
FO
S/L LT/MIR/HISL sw
4 – 12
APPROVED Rev. 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.4
STARTING ENGINES AND SYSTEM CHECKS – NORMAL PROCEDURE
4.4.1
Standard start-up procedure
4.4.1.1 Pre-start check NOTE
After switching BAT MSTR sw to OFF, wait at least 30 sec before switching BAT MSTR sw back to ON. – DAY, NIGHT or NVG, as required
BAT MSTR sw
– ON and ENGAGE, allow approx. 20 sec for system to boot
FND ML
– Acknowledge ML (Cyclic or MFD)
O
LL
ED
INSTR mode selector sw
O
If PWR–UP TST OK does not appear, refer to Para. 4.18.1.
C
NOTE
N TR
– Check PWR–UP TST OK
– Check FDRS extinguished
N
O
T
FDRS (if installed)
O
The fire protection check must be performed at least once a day.
C
NOTE
PY
FIRE Protection Test, System 1
FO
R
IN
ST
R
U
C
TI
O N
TEST FIRE 1 sw
O N
LY
–
TEST FIRE 1 sw
TEST FIRE 1 sw
– EXT –
FIRE BOT1+2 USED and audio tone
– EXT WRN – ENG1 FIRE – FIRE BOT1+2 TEST – Audio tone + “FIRE – ENGINE 1 FIRE” – FIRE
(WU)
– BOT1
/ BOT2
– EXT
(WU)
(WU)
– OFF – No ACTIVE light illuminated in EMER OFF sw area
FIRE Protection Test, System 2 Repeat TEST FIRE 2 sw
APPROVED Rev. 15
– Same indications, except: – FIRE ENG2 – Audio tone + ”FIRE – ENGINE 2 FIRE”
4 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Lamp test – LAMP and hold, check
TEST sw
–
LOW ENG 1 FUEL 1 FAIL BAT OVHT
ROTOR ENG 2 LOW RPM FAIL FUEL 2 MGB CARGO AP OIL P SMOKE
– Voice message “AUDIO TEST” –
(Engine CP)
TRAIN
ED
– APCP all lights on
O
LL
– EXIT lights illuminate
N TR
NOTE D If master list alerts appear during the lamp test, refer to Para. 4.18.2.
T
C
O
D During Lamp test, the WU might display indications of systems that are not actually installed. In this case these indications can be ignored. – Release
VMS page
– Press NUM
Center MFD
– Check Volt w 23.5 V
LY
–
C
O
PY
N
O
TEST sw
O N
O N
Weight computation
– Adjust weight as required – Press VAL – Press PREV
+35_C and IFR flight is planned:
C
TI
If OAT/cabin temperature u
– Check fuel quantity
– Check on (can be heard)
ST
R
U
Instrument panel fan
IN
Avionics and Flight Control Check
FO
R
FND ML
– ENG 1 –
FAIL
ENG2
EPU CONNECTED (if connected)
–
AFT+FWD FUEL PMP
– PITOT1 HEATER OFF PITOT2 – PWR-UP TST OK – NOTE
ROTOR BRAKE extinguished
The engine will not start if the rotor brake is engaged.
continued
4 – 14
APPROVED Rev. 20
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Flight instruments
– Aligned, set baro press if required
IESI
– Set baro press if required
NOTE
In case of MGB temperature < –30°C, refer to Para. 4.17.1 before checking free movement of flight controls.
Flight controls
– Press TRIM REL sw
LL
Low NR audio tone will sound when raising collective lever.
O
NOTE
ED
– Check free movement throughout full travel including non-interference with optional equipment
– Center cyclic using stick position indicator
N TR
Flight controls
C
O
– Release TRIM REL sw
O
T
– Latch collective lever – Set as required
N
EXT LIGHTS ACOL sw
– Set as required
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
IR FLASH sw (if installed)
APPROVED Rev. 17.1
4 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.4.1.2 Starting Engines Before starting engines Fire guard (if available)
– Posted
Rotor area
– Clear
Abort Starting Procedure (if required) IMMEDIATELY ABORT START AND PERFORM MAINTENANCE BEFORE RESTART FOR ANY OF THE FOLLOWIING CONDITIONS:
LL
ED
CAUTION
C
O
N TR
O
D WHEN TOT REACHES 840_C AN AUTOMATIC STOP FUNCTION INTERRUPTS THE STARTING SEQUENCE. IN CASE OF AUTOMATIC STOP, INSPECT THE ENGINE IN ACCORDANCE WITH THE ENGINE MAINTENANCE MANUAL.
N
O
T
D NO POSITIVE ENGINE OR TRANSMISSION OIL PRESSURE INDICATIONS UPON REACHING GROUND IDLE CONDITION.
–
C
O
PY
D N2 AND NR NEEDLES ARE NOT MATCHED AFTER REACHING STABILIZED GROUND IDLE CONDITION.
LY
CAUTION D DO NOT EXCEED STARTER DUTY CYCLE (REFER TO SECT. 2).
O N
D MONITOR CLOSELY TOT. For TCCA registered helicopters only
TI
O N
EFFECTIVITY
– OFF, wait 60 s
Engine ventilation (affected engine)
– Perform
IN
ST
R
U
C
ENG MAIN sw (affected engine)
FO
R
Engine Ventilation (if required) N1
– Check t 10%
Fuel SOV
– Check opened (FUEL VALVE CLOSED extinguished)
ENG MAIN sw
– OFF
ENG VENT pb
– Push and hold 20 s (BAT power) 15 s (EPU)
NOTE D Observe Engine starter/generator limitations (refer to Sect. 2). D Ventilating both engines simultaneously is prohibited.
4 – 16
APPROVED Rev. 15.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Not for TCCA registered helicopters
EFFECTIVITY
ENG MAIN sw (affected engine)
– OFF, wait 60 s
Engine ventilation (affected engine)
– Perform
Engine Ventilation (if required) – Check t 10%
Fuel SOV
– Check opened (FUEL VALVE CLOSED extinguished)
ENG MAIN sw
– OFF
ENG VENT pb
– Push and hold 20 s (BAT power) 15 s (EPU)
O
N TR
O
LL
ED
N1
T
C
NOTE D Observe Engine starter/generator limitations (refer to Sect. 2).
N
O
D Ventilating both engines simultaneously is prohibited.
O
PY
All
EFFECTIVITY
–
C
Starting first engine
LY
NOTE D Engines may be started in any order.
O N
D BAT DISCHARGING may appear momentarily on ML.
TI
O N
D If, for any reason a starting attempt is discontinued, the entire starting sequence must be repeated from the beginning (see Para. 4.4.1.2).
IN
ST
R
U
C
D If the engine does not ignite, the EECU will automatically interrupt the starting sequence and may attempt a second start. If ignition does not occur within 30 sec (no TOT rise), abort the start.
FO
R
START PROCEDURE FUEL PRIME PUMP 1 and 2 sw’s
– ON – FUEL1 PRIME PUMP ON FUEL2
FND ML
– Acknowledge ML (Cyclic or MFD) – No ELEC OVERLIMIT
NOTE
If ELEC OVERLIMIT appears, check voltage y 23.5 V on VMS page.
ENG 1 or 2 MAIN sw
– IDLE, start clock
N1
– Check increase continued
APPROVED Rev. 15.1
4 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
TOT
– Monitor, check increase
N2/NR
– Monitor increase
Engine and MGB oil pressure, hydraulic pressure
– Check positive indication
FND ML
– Check
At approx. 60% N1
–
STARTER ON (FND ML) extinguishes
–
START (VMS page) extinguishes
START–UP TST
– Approx. 78% in IDLE mode, check matched
Caution indications
– No system related cautions
EPU (if used)
– Disconnect now or after 2nd engine start, as required
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
N2/NR
4 – 18
APPROVED Rev. 15.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Hydraulic check CAUTION D TEST HYD SW MUST NOT BE OPERATED DURING FLIGHT. D OBSERVE MAST MOMENT LIMITS DURING HYDRAULIC CHECK. The hydraulic check must be performed at least once a day. – SYS1 and hold, check:
TEST HYD sw FND ML
–
VMS page
– HYD2 P values in amber
HYD2
ED
Cyclic TRIM REL sw
LOW PRESS
– Press
LL
NOTE
N TR
O
Perform small movements:
– Check longitudinal/lateral motion
Collective lever
– FLI 0 – 1, Check normal forces
Pedals
– Check normal forces
N
O
T
C
O
Cyclic stick
– SYS2 and hold, check:
PY
TEST HYD sw
–
C
O
FND ML
LY
VMS page
–
HYD1 HYD1
LOW PRESS TR SHUT OFF
– HYD1 P values in amber
O N
Cyclic stick
O N
Perform small movements:
C
TI
Collective lever
R
U
Pedals
ST
Cyclic TRIM REL sw
– FLI 0 – 1, Check normal forces – Check normal forces – Release – Release
FO
R
IN
TEST HYD sw
– Check longitudinal/lateral motion
Starting Second Engine (sequential procedure) Start second engine following Starting First Engine procedure above. FND ML NOTE
APPROVED Rev. 15.1
START–UP TST OK
If START–UP TST OK does not appear, refer to Para. 4.18.3.
EPU (if still conntected) NOTE
– Check
– Disconnect
Disconnecting the EPU later on in the pre-flight procedure can cause systems and the AFCS to disengage. In this case, systems/AFCS must be re-engaged before takeoff.
4 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.4.1.3 After engine start PT/STATIC HTG COPILOT and PILOT sw’s
– ON
STBY BAT and AVIO MSTR 1 and 2 sw’s
– ON
Up to S/N 20189 and before SB MBB–BK117 D–2–18–002
LAVCS sw
S/N 20190 and subsequent or after SB MBB–BK117 D–2–18–002
LAVCS sw
– ON
O
All
N TR
EFFECTIVITY
ED
EFFECTIVITY
– PIL or PAX, as required
LL
EFFECTIVITY
– OFF FUEL1 PRIME PUMP ON FUEL2 extinguished
FUEL XFER PUMP A and F sw’s
– ON, AFT+FWD FUEL PMP extinguished
EXT LIGHTS POS sw’s
– As required
C
O
PY
N
O
T
C
O
FUEL PRIME PUMP 1 and 2 sw’s
– As required
INT LIGHTS EM/EX sw
– ARM
O N
LY
–
EXT LIGHTS STROBE, IR FLASH and FORM sw’s (if installed)
U
C
Ventilation
R
Maximum ventilation required if OATw +35_C.
ST
NOTE
– Check on
TI
O N
Avionics and COMM/NAV equipment
FO
R
IN
Ventilation
– Set as required – Refer to Para. 4.16.3 for maximum ventilation
Heating system check NOTE D Only applicable if electical heater is installed. If no electrical heater is installed, check only that heating can be switched ON (
appears).
D Only required if flight is intended in ambient conditions OAT < 10_C or heating is intended to be used. D The heating system check must be performed once a day.
4 – 20
DEFOG / DEMIST
– Deselect
VMS page
– Press NUM APPROVED Rev. 15.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Cockpit ventilation
– OFF
Heating
– MAX – check
on
– Check and remember GEN AMPS – Select
GEN AMPS
– Verify increase by approx. 30 A (only if electrical heater is installed)
CKPT fan
– Verify operation (feel airflow by hand at demisting or instrument panel outlet)
Heating
– Off
O
LL
ED
DEFOG / DEMIST
O
N TR
– Verify GEN AMPS decreases (only if electrical heater is installed) – Verify stop of operation (feel airflow by hand)
N
O
T
C
CKPT fan
PY
Avionics checks
C
TI
O N
O N
LY
–
C
O
GTN
– Press CONTINUE (both units) – Press CONTINUE (both units) – Set frequencies/transponder as required – Check heading indication consistent with MFD (TRUE or MAG) – Check and set
FO
R
IN
ST
R
U
All other instruments and equipment
– Check data bases valid
APPROVED Rev. 15.1
4 – 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
AFCS/Avionics Pre-flight Test NOTE D The AFCS/Avionics pre-flight test must be performed before each IFR flight. Before VFR flights, the test must be performed at least once a day. D Do not start the AFCS/Avionics pre-flight test until the main gearbox oil temperature is above –10°C.
Collective lever
LL
– Unlatch, full down
O
Do not unlatch the collective by physically pushing down on the collective.
N TR
NOTE
ED
D Remain attentive, but allow all controls to move slightly. Do not interfere with controls during the test.
– LAMP and hold, check
C
O
TEST sw
DME1
DME2
HI
HOLD
HOLD
FMS1
FMS2
OFF
OFF
LY
–
C
O
PY
N
O
T
MKR
– P-FLT (hold briefly) –
P–FLT TEST test runs
– Wait and check until P–FLT TEST OK appears when test is complete
IN
Before Helionix Maintenance Release 1 or before ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
FO
EFFECTIVITY
If P–FLT TST OK does not appear, refer to Para. 4.18.4.
R
NOTE
ST
R
U
C
TI
O N
O N
TEST sw
– Release
CAUTION
AP2 MUST ALWAYS BE ACTIVATED BEFORE AP1. OTHERWISE, AP1 COULD MALFUNCTION WHEN AP2 FAILS OR IS SWITCHED OFF.
AP2
– Engage (Cyclic or APCP)
AP1
– Engage (Cyclic or APCP) – FND AFCS Strip green rectangles 3x
EFFECTIVITY
After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
AP1 + AP2
– Engage (Cyclic or APCP) – FND AFCS Strip green rectangles 3x
4 – 22
APPROVED Rev. 15.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
EFFECTIVITY
All
Cyclic AP/BKUP CUT sw
– Press – AP1+AP2 –
Cyclic AP/BKUP CUT sw
(APCP)
OFF
SAS SAS AFCS DISENGAGED
(FND)
– Press again – BKUP+AP1+AP2 –
(APCP)
OFF
SAS SAS AFCS DISENGAGED
(FND)
– Check in all four directions
Cyclic/pedals
– Centered/parallel
N TR
O
LL
ED
Cyclic BEEP TRIM
Autopilot engagement
O
Before Helionix Maintenance Release 1 or before ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
C
EFFECTIVITY
AP2 and BKUP AP1
N
O
T
– Engage (Cyclic or APCP) – Engage (Cyclic or APCP)
C
After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1) – FND AFCS Strip green rectangles 3x
– Latch if required
R
U
Collective
TI
All
C
EFFECTIVITY
– Engage (Cyclic or APCP)
O N
O N
AP1 + AP2 + BKUP
LY
–
EFFECTIVITY
O
PY
– FND AFCS Strip green rectangles 3x
ST
Preparation for night flight
R
IN
MFDs
FO
EFFECTIVITY
Before Helionix Maintenance Release 1
If use of the SVS (if installed) is planned:
EFFECTIVITY
APPROVED Rev. 15.1
– Adjust luminance
SVS
– Select
Brightness (BRT sw)
– Adjust as required
All
Cockpit illumination
– Adjust
Fixed and S/L landing lights
– Check function, set as required
Fabric glare shield
– Installed
4 – 23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Optional equipment checks Optional equipment
– Check as required (refer to Sect. 7 and Sect. 9)
Power check Perform ground power check as required (refer to Sect. 5).
– FLIGHT, guards closed
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ENG 1/2 MAIN sw’s
ED
Preparation for Pre-takeoff check
4 – 24
APPROVED Rev. 15.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.5
STARTING ENGINES AND SYSTEM CHECKS – QUICK START-UP PROCEDURE D Quick start-up procedure is recommended only if special circumstances require.
NOTE
D Do not use quick start-up procedure if main gearbox oil temperature is below –30°C. In this case perform a normal engine start according to Para. 4.4.1.1 and Para. 4.4.1.2 in order to warm up the helicopter for possible quick start-up. Additional pre-flight checks
ED
4.5.1
D Standard pre-flight checks (according to para. 4.3) and the additional pre-flight checks must be performed to prepare the helicopter for a subsequent quick start-up (according to para. 4.5.1.1).
N TR
O
LL
NOTE
O
T
C
O
D After switching BAT MSTR sw to OFF, wait at least 30 sec before switching BAT MSTR sw back to ON. INSTR mode selector sw
PY
N
– DAY, NIGHT or NVG, as required
C
O
BAT MSTR sw
– Check PWR–UP TST OK
If PWR-UP TST OK does not appear, refer to Para. 4.18.1.
FO
R
IN
ST
R
U
C
TI
O N
NOTE
– Acknowledge ML (Cyclic or MFD)
O N
LY
–
FND ML
– ON and ENGAGE, allow approx. 20 sec for system to boot
APPROVED Rev. 15.1
4 – 25
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
FIRE Protection Test, System 1 NOTE
The fire protection check must be performed at least once a day.
TEST FIRE 1 sw
– EXT –
TEST FIRE 1 sw
FIRE BOT1+2 USED and audio tone
– EXT WRN – ENG1 FIRE – FIRE BOT1+2 TEST
/ BOT2
– EXT
(WU)
(WU)
O
– OFF
C
TEST FIRE 1 sw
LL
– BOT1
O
(WU)
N TR
– FIRE
ED
– Audio tone + “FIRE – ENGINE 1 FIRE”
N
O
T
– No ACTIVE light illuminated in EMER OFF sw area
PY
FIRE Protection Test, System 2
– Same indications, except: – FIRE ENG2 – Audio tone + ”FIRE – ENGINE 2 FIRE”
LY
–
C
O
Repeat TEST FIRE 2 sw
O N
Lamp test
– LAMP and hold, check –
LOW ENG 1 FUEL 1 FAIL BAT OVHT
ROTOR ENG 2 LOW RPM FAIL FUEL 2 MGB CARGO AP OIL P SMOKE
– Voice message “AUDIO TEST” –
TRAIN
(Engine CP)
FO
R
IN
ST
R
U
C
TI
O N
TEST sw
– APCP all lights on – EXIT lights illuminate
D If master list alerts appear during the lamp test, refer to Para. 4.18.2. D During Lamp test, the WU might display indications of systems that are not actually installed. In this case these indications can be ignored. TEST sw
– Release
VMS page
– Press NUM Continued:
4 – 26
APPROVED Rev. 20
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Center MFD
– Check Volt w 23.5 V – Check fuel quantity
Weight computation
– Adjust weight as required – Press VAL – Press PREV
Avionics and Flight Control Check FND ML
– ENG 1
ENG2
ED
FAIL
–
LL
EPU CONNECTED (if connected)
–
N TR
O
AFT+FWD FUEL PMP
– PITOT1 HEATER OFF PITOT2
O
– PWR-UP TST OK ROTOR BRAKE extinguished
O
T
C
–
– Aligned, set baro press if required
PY
N
Flight instruments
O
IESI
R
IN
ST
R
U
C
Flight controls
FO
– Check free movement throughout full travel including non-interference with optional equipment
Low NR audio tone will sound when raising collective lever.
TI
NOTE
– Press TRIM REL sw
O N
O N
LY
–
C
Flight controls
– Set baro press if required
– Center cyclic using stick position indicator – Release TRIM REL sw – Latch collective lever
EXT LIGHTS ACOL sw
– Set as required
IR FLASH sw (if installed)
– Set as required
Preparation for night flight EMER SHD BUS sw
– ON –
APPROVED Rev. 17.1
EMER SHED BUS ON
Fixed and S/L landing lights
– Check function, set as required
EMER SHD BUS sw
– NORM and guard
Fabric glare shield
– Installed
4 – 27
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Avionic checks – ON
LAVCS sw (if installed)
– PIL or PAX, as required
COMM/NAV equipment
– ON and check
NAV equipment
– Check heading indication consistent with MFD (TRUE or MAG)
All other instruments and equipment
– Check and set
ED
AVIO MSTR 1 and 2 sw’s
LL
Heating system check
N TR
O
NOTE D Only applicable if electical heater is installed. If no electrical heater is installed, check only that heating can be switched ON (
O
appears).
N
O
T
C
D Only required if flight is intended in ambient conditions OAT < 10_C or heating is intended to be used.
PY
D The heating system check must be performed once a day. DEFOG / DEMIST
C
O
– Deselect
–
VMS page
O N
LY
Cockpit ventilation
TI
O N
Heating
R
ST
BAT AMPS
U
C
DEFOG / DEMIST
FO
R
IN
CKPT fan
Heating
– Press NUM – OFF
– MAX – check
on
– Check and remember GEN AMPS – Select – Verify increase by approx. 30 A (only if electrical heater is installed) – Verify operation (feel airflow by hand at demisting or instrument panel outlet) – Off – Verify GEN AMPS decreases (only if electrical heater is installed)
CKPT fan
– Verify stop of operation (feel airflow by hand) continued
4 – 28
APPROVED Rev. 15.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Preparation for power OFF Optional equipment
– Check as far as possible
AVIO MSTR 1 and 2 sw’s
– OFF
Power OFF – OFF
Helicopter
– Ensure that settings or conditions are not interfered with until quick start-up is necessary.
ED
BAT MSTR sw
LL
4.5.1.1 Starting phase
DO NOT USE THE QUICK START-UP PROCEDURE IF, AFTER COMPLETION OF THE STANDARD AND ADDITIONAL PRE-FLIGHT CHECKS, ANY OF THE FOLLOWING APPLIES: – THE HELICOPTER WAS LEFT UNATTENDED. – THE HELICOPTER’S SETTINGS OR CONFIGURATION WERE CHANGED OR INTERFERED WITH. – SINCE COMPLETION OF THE STANDARD AND ADDITIONAL PRE-FLIGHT CHECKS, MORE THAN 12 HOURS HAVE PASSED.
NOTE
In case of operation under low OAT, observe oil limits, fuel limits and warm up procedure as detailed in FLM.
After switching BAT MSTR sw to OFF, wait at least 30 sec before switching BAT MSTR sw back to ON.
O N
NOTE
O N
Interior & Pre-start checks
LY
–
C
O
PY
N
O
T
C
O
N TR
O
CAUTION
– DAY, NIGHT or NVG, as required
BAT MSTR sw
– ON and ENGAGE, allow approx. 20 sec for system to boot – Fastened – Check all latches properly engaged (green indication visible)
ST
Safety belt
IN
R
U
C
TI
INSTR mode selector sw
FO
R
Pilot / copilot door FND ML
– Acknowledge ML (Cyclic or MFD) – Check PWR–UP TST OK – Check no ELEC OVERLIMIT
If OAT/cabin temperature u
+35_C and IFR flight is planned:
Instrument panel fan
– Check on (can be heard)
NOTE D If PWR–UP TST OK does not appear, refer to Para. 4.18.1. D If ELEC OVERLIMIT appears, check battery voltage y 23.5 V on VMS page. FUEL PRIME PUMP 1 and 2 sw’s
– ON – FUEL1 PRIME PUMP ON FUEL2
APPROVED Rev. 15.1
4 – 29
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Starting engines Fire guard (if available)
– Posted
Rotor area
– Clear
NOTE D For engine start abort and engine ventilation, refer to Para. 4.4.1.2. D For quick start-up, the second engine may be started as soon as the starter of the first engine has engaged. The second start sequence will begin as soon as the START label of the 1st engine has disappeared. ENG 1 and 2 MAIN sw’s
ED
LL
O
The second engine is automatically blocked until the first starter phase is completed (START label has disappeared).
N TR
NOTE
– IDLE (wait approx. 1sec) – FLIGHT
– Monitor increase
Engine and MGB oil pressure, hydraulic pressure
– Check positive indication
FND ML
– Check
O
PY
N
O
T
C
O
Both engines’ parameters (N1, TOT, N2), NR
–
STARTER ON (FND ML) extinguishes
–
START (VMS page) extinguishes
LY
–
C
At approx. 60% N1
O N
N2/NR
– NOMINAL in FLIGHT mode, check matched – ON
PT/STATIC HTG COPILOT and PILOT sw’s
– ON
C
TI
O N
STBY BAT and AVIO MSTR 1 and 2 sw’s
ST
R
U
START–UP TST
FO
R
IN
FUEL PRIME PUMP 1 and 2 sw’s
– OFF FUEL1 PRIME PUMP ON FUEL2 extinguished
FUEL XFER PUMP A and F sw’s
– ON, AFT+FWD FUEL PMP extinguished
EXT LIGHTS POS sw’s
– As required
EXT LIGHTS STROBE, IR FLASH and FORM sw’s (if installed)
– As required
INT LIGHTS EM/EX sw
– ARM
Hydraulic check (to be performed at least once a day) Hydraulic check
4 – 30
– Perform (refer to Para. 4.4.1.2) APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Ventilation NOTE
Maximum ventilation required if OAT≥ +35_C.
Ventilation
FND ML
Set as required
-
Refer to Para. 4.16.3 for maximum ventilation
-
Check START- UP TST OK
If START- UP TST OK does not appear, refer to Para. 4.18.3.
ED
NOTE
-
LL
Avionic checks -
Check on and set
GTN
-
Check data bases valid
-
Press CONTINUE (both units)
-
Press CONTINUE (both units)
-
Set frequencies/transponder as required
PY
N
O
T
C
O
N TR
O
Avionics
-
Check and set
C
O
All other instruments and equipment
LY
–
AFCS/Avionics Pre-Flight Test (to be performed at least once a day and before each IFR flight) -
Perform (refer to Para. 4.4.1.3)
O N
O N
AFCS/Avionics Pre-Flight Test
U
C
Before Helionix Maintenance Release 1 or before ASB MBB BK117 D-2- 42A- 004 (HELIONIX STEP 2.0.1)
ST
R
EFFECTIVITY
TI
Autopilot engagement
FO
R
IN
CAUTION
AP2 MUST ALWAYS BE ACTIVATED BEFORE AP1. OTHERWISE, AP1 COULD MALFUNCTION WHEN AP2 FAILS OR IS SWITCHED OFF.
AP2 and BKUP
-
Engage (Cyclic or APCP)
AP1
-
Engage (Cyclic or APCP)
-
FND AFCS Strip green rectangles 3x
EFFECTIVITY
After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2- 42A- 004 (HELIONIX STEP 2.0.1)
AP1 + AP2 + BKUP
EFFECTIVITY APPROVED Rev. 15
-
Engage (Cyclic or APCP)
-
FND AFCS Strip green rectangles 3x
All
4 - 31
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Preparation for night flight -
MFDs EFFECTIVITY
Adjust luminance
Before Helionix Maintenance Release 1
If use of the SVS (if installed) is planned: SVS
-
Select
Brightness (BRT sw)
-
Adjust as required
-
Check as required (refer to Sect. 9)
ENG1/2 MAIN sw’s
-
Check FLIGHT, guards closed
Rotor speed
-
NOMINAL in FLIGHT mode
Pressure and temperature indications
-
Check
All
ED
EFFECTIVITY
N TR
O
Optional equipment
O
LL
System checks
C
O
PY
N
O
T
C
4.6 L PRE-TAKEOFF CHECK
LY
–
If OAT < 0C and no fuel anti-icing additive is used: -
Extinguished
Cautions, warnings, alerts
-
Check
Fuel quantity
-
Check
-
Select required page
-
Check aligned, IAS and ALT valid
AP/BCKUP SAS
-
Check on
Optional equipment controls
-
As required
TI C U
R
MFD 4 and 1
O N
O N
ENG1 FUEL LOW TEMP ENG2 alert
FO
R
IN
ST
IESI
CAUTION
4 - 32
ESPECIALLY WHEN OPERATING MISSION EQUIPMENT WITH OPTIONAL COPILOT’S ARMREST LOWERED, CARE SHOULD BE TAKEN THAT LEGS AND FEET ARE PLACED IN SUCH A WAY TO ALLOW UNRESTRICTED MOVEMENT OF CYCLIC AND PEDALS BY THE PILOT.
Copilot’s armrest (if installed)
-
Check tilted upright and locked
Cockpit dome light (if installed)
-
Off
APPROVED Rev. 22
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
For night flight Before SB MBB- BK117 D- 2- 33- 07
EFFECTIVITY
-
Check ON and adjusted
Fixed landing light
-
ON
S/L landing light
-
ON and adjusted
Hover flight
-
Perform
N2/NR
-
Check ≥101%
FLI
-
Check AEO indication
Hover power
-
Check at 4’ skid height
Fixed and/or S/L landing lights After SB MBB- BK117 D- 2- 33- 07
EFFECTIVITY
ED
All
EFFECTIVITY
O
N TR
O
C
T
O
Note position of blue line on FLI
PY
N
-
LL
4.7 L TAKEOFF CHECK
-
Check off
–
TAKEOFF
O N
4.8
If SVS (optional) is used. Select appropriate information level (SVS1 or SVS2) for takeoff.
LY
NOTE
C
O
All warnings and cautions, ML
Hover
Perform with 4 ft skid height
-
Start nose down pitch rotation and simultaneously increase power smoothly (use hover power plus 0.5 1.0 FLI, without exceeding TOP) for acceleration. Adjust pitch attitude at about 20 KIAS to achieve 30 KIAS at 15 ft height. Observe height-velocity-diagram as described in Sect. 5.
When reaching 50 KIAS
-
Maintain airspeed until reaching 50ft AGL, then accelerate to VY and climb through 100ft AGL
N2/NR
-
Check nominal decrease above 60 KIAS
-
Press
-
Check A.TRIM
-
DSAS
O N
-
FO
R
IN
ST
R
U
C
TI
Acceleration and climb
Recommended slope takeoff procedure: A.TRIM sw (APCP)
APPROVED Rev. 22
OFF
DSAS DSAS
(APCP) (FND)
4 - 33
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.9
Collective
-
Increase gently to ±30% TQ
Mast moment
-
Increase in direction of slope (use no more than normal MM range)
Collective
-
Increase to lift from slope, maintain MM within limits
A.TRIM sw
-
Press to engage
-
Check ON and adjusted
Fixed landing light
-
ON
S/L landing light
-
ON and adjusted
PRE-LANDING CHECK
O
C T
-
Check
-
Check
-
Check increase ≥101% below 50 KIAS
-
As required
-
Check tilted upright and locked
C –
O N
Decision height (DH)
LY
N2/NR
O N
All warnings, cautions, ML
C
TI
Copilot’s armrest (if installed)
ST
R
U
LANDING
Prior landing in sandy conditions, close NACA inlets by selecting recirculated air.
IN
NOTE
O
All
All instruments
4.10
O
PY
EFFECTIVITY
After SB MBB- BK117 D- 2- 33- 07
O
EFFECTIVITY
N TR
Fixed and/or S/L landing lights
LL
Before SB MBB- BK117 D- 2- 33- 07
N
EFFECTIVITY
ED
For night flight
FO
R
Recommended landing procedure: Approach
-
Initiate to arrive at 100 ft with a speed of 40 KIAS and a rate of descent of not more than 500 ft/min
After reaching 100 ft
-
Adjust collective pitch to maintain desired rate of descent, gradually slow down aiming for 30 KIAS at 50 ft, then continue to proceed into ground cushion for landing
-
Neutral position
-
Press TRIM REL sw
After landing: Cyclic stick
4 - 34
APPROVED Rev. 22
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Recommended slope landing procedure: NOTE
Observe slope landing limitations (refer to Sect. 2).
Prior to touchdown: A.TRIM sw (APCP)
– Press – Check A.TRIM –
DSAS
(APCP)
OFF
(FND)
DSAS DSAS
ED
Upon initial ground contact:
– Increase towards slope as required (use no more than normal MM range)
Collective
– Lower gently for full touchdown (monitor mast moment, reduce necessary to maintain within limits).
Cyclic
– Center after collective fully lowered, as required
if
N
O
T
C
O
N TR
O
LL
Mast moment
PY
ENGINE SHUTDOWN
O
4.11
–
C
Cyclic stick
– Latch – IDLE
O N
Wait 30 sec for engines to cool down.
TI
NOTE
O N
ENG1/2 MAIN sw’s
LY
Collective lever
– Neutral position
U
C
MFD 4
– OFF, except EXT LIGHTS ACOL sw
IN
ST
R
All consumers
– Select VMS page
– OFF ENG1
TOT and N1
– Monitor decrease
Rotor brake (if required)
– Apply below 50% NR
FO
R
ENG1/2 MAIN sw’s
FAIL
ENG2
When rotor has stopped:
APPROVED Rev. 15
EXT LIGHTS ACOL sw
– OFF
MFD VMS
– Check FLIGHT REPORT page
Rotor brake (if used)
– Release
4 – 35
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
NOTE
EFFECTIVITY
Before Helionix Maintenance Release 1 Allow the data download to complete before switching BAT MASTR off: – When HMS is installed, the download time is approximately 1 minute per flight hour. – Without HMS, data download is approximately 10 seconds. Data download starts automatically when NR is below 10%. After Helionix Maintenance Release 1
FND ML
– Check DOWNLOAD IN PROGRESS disappeared
ED
EFFECTIVITY
– Check
LL
O
All
N TR
EFFECTIVITY
DOWNLOAD COMPLETE
– OFF
4.12.1
Flight controls
N
FLIGHT CHARACTERISTICS
–
AVOID EXTREME CYCLIC STICK GROUND WITH ROTOR TURNING.
DISPLACEMENTS
WHEN
ON
LY
CAUTION
C
O
PY
4.12
O
T
C
O
BAT MSTR sw
C
Recommended maximum rate-of-descent during HOGE or low speed flight
U
4.12.2
TI
O N
O N
During ground operations with rotor turning, the cyclic stick must remain in the neutral position and the collective pitch lever in the full down position; however, for functional test purposes, minimum control movements (less than 3 cm from neutral) are allowed.
FO
R
IN
ST
R
Any descent during hover or low speed flight (up to 20 KIAS) should be performed with a descent rate of less than 500 ft/min.
4 – 36
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.13
IFR PROCEDURES WHEN USING ALTITUDE CONSTRAINED LEGS, THE BARO SETTING MUST BE IDENTICAL ON MFD1 AND MFD2. THE CREW MUST REMEMBER TO SYNCHRONIZE THE BARO SETTING WHENEVER IT WAS CHANGED.
CAUTION
Pre–flight check
LL
4.13.1
The IFR procedures do not detail all required inputs and keystrokes on the GTN. The pilot shall be familiar with the operation of the GTN in accordance with the limitations.
ED
NOTE
O
If a GPS based approach is planned:
O
N TR
– In areas served by SBAS (EGNOS, WAAS, or MSAS): Check NOTAMs to verify SBAS availability throughout the flight and during the approach.
C
O
Before takeoff:
LY
–
Departure procedure
O N
Baro settings
O N
NAV source
– Select and load – Set VOR/ADF frequencies, if required – Select according to SID – Check (FND/IESI) – Set (FND) – Check ON
ST
R
U
C
TI
Decision height (DH) AP2+AP1
N
IFR Standard Instrument Departure (SID)
PY
4.13.2
O
T
C
– In areas not served by SBAS: RAIM availability must be checked on the UTILITY/RAIM Prediction sub-page.
IN
Departure:
FO
R
Normal or Cat A takeoff After passing VTOSS: AFCS upper modes
APPROVED Rev. 15
– Perform
– As required acc. to procedure/flight plan
4 – 37
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.13.3
IFR en-route navigation
4.13.3.1 OBS navigation WHEN OBS IS SELECTED, THE FLIGHT PLAN INDICATION ON FND/NAVD WILL DISAPPEAR. REFER TO THE GTN MAP DISPLAY TO VISUALIZE THE FLIGHT PLAN.
CAUTION
LL
ED
The Omni Bearing Selector (OBS) function allows the pilot to select a desired course TO or FROM a waypoint and prevents the FMS from sequencing to the next waypoint (automatic leg sequencing is suspended). Pressing the OBS sk again will return to normal operation with automatic sequencing of waypoints.
N TR
O
To select an OBS TO or FROM the active waypoint, proceed as follows: – Touch to select OBS page
Course pop-up
– Select the desired course to the OBS waypoint
ENTER sk
– Touch to activate the OBS function
N
O
T
C
O
OBS sk (on GTN)
SUSP appears on FND/NAVD
PY
–
C
O
– Check OBS and course on FND – CPL, as required
O N
LY
–
Autopilot NAV mode
O N
To cancel an OBS TO or FROM the active waypoint, proceed as follows:
TI
OBS sk (on GTN)
– Touch to de-activate the OBS function
R
U
C
ENTER sk
– Touch to select OBS page
FO
R
IN
ST
NOTE D When OBS is cancelled on the TO side of the OBS waypoint, the GTN will automatically continue with a DIRECT–TO navigation to the active waypoint, with automatic leg sequencing unsuspended. D When OBS is cancelled on the FROM side of the OBS waypoint, the GTN will substitute OBS with DIRECT–TO navigation to the active waypoint with automatic leg sequencing suspended ( SUSP illuminates). Touching the UNSUSP sk will enable automatic leg sequencing again and the GTN will sequence to the next waypoint of the flight plan.
4 – 38
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.13.3.2 Parallel track CAUTION
WHEN PARALLEL TRACK IS USED, OFFSET WAYPOINTS ON THE INTERNAL DMAP MAY BE SHOWN AT THE WRONG LOCATION. IT IS RECOMMENDED TO USE THE NAVD INDICATION WHEN NAVIGATING WITH PARALLEL TRACK.
To select a parallel track, proceed as follows: – Select
MENU sk on GTN
– Touch
Parallel Track sk on GTN
– Touch
Parallel Track pop-up
– Enter direction (L/R) and offset
Activate sk
– Touch
O
N TR
O
LL
ED
FLIGHT PLAN page on GTN
–
appears on FND/NAVD
T
C
OFST
– CPL, as required
PY
N
O
Autopilot NAV mode
C
O
NOTE D Offset waypoints are shown with the suffix “p“ on FND and NAVD
O N
LY
–
D Certain leg types (such as approach) or leg geometries (changes in desired track greater than 120 degrees), combined with large offset values do not support parallel track. Refer to the Garmin Pilots Guide for details.
TI
O N
To cancel a parallel track, proceed as follows:
U
C
FLIGHT PLAN page on GTN
ST
R
MENU sk on GTN
– Touch – Touch
Parallel Track pop-up
– Enter direction (L/R) and offset
Deactivate sk
– Touch
IN
Parallel Track sk on GTN
R FO APPROVED Rev. 15
– Select
4 – 39
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.13.4
IFR approach navigation CAUTION D IN CASE DIFFERENT DH SETTINGS ARE SET ON MFD2, 4, OR 1, ONLY THE HIGHEST ONE WILL TRIGGER THE “DECISION HEIGHT“ VOICE MESSAGE. D IN CASE THE APPROACH PROCEDURE IS CHANGED AFTER THE INITIAL APPROACH FIX, THE AUTOPILOT MUST BE DE-COUPLED AND RE-COUPLED AFTER THE NEW APPROACH IS ACTIVATED.
ED
4.13.4.1 Holding pattern
O
LL
Activating a holding pattern (not required if holding is part of the procedure): – Select
Holding waypoint
– Touch to select sub-menu
Hold At Waypoint sk
– Touch
T
C
O
N TR
Flight plan on GTN
N
O
– Set holding parameters
O
PY
– Activate holding
–
C
Before reaching the holding fix:
O N
LY
Autopilot NAV mode
– Check
SUSP indicated (FND/NAVD)
– Check aircraft follows holding
TI
O N
When passing the holding fix
– CPL, if required
R
U
C
To exit the holding pattern:
FO
R
IN
ST
UNSUSP sk on GTN
4 – 40
– Touch – Check
SUSP disappears (FND/NAVD)
– Check aircraft exits holding
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.13.4.2 ILS approach CAUTION
BEFORE ENGAGING THE AUTOPILOT VIA CPL BUTTON ON THE MFD, THE COURSE POINTER (CRS) MUST BE SET TO THE PUBLISHED APPROACH COURSE. AN INCORRECTLY SET COURSE POINTER MAY LEAD TO SIGNIFICANT TRACK DEVIATIONS.
Before intercepting the final approach course: – Set ILS frequency
NAV sk on MFD1
– Select ILS1
NAV sk on MFD2
– Select ILS2
LL
ED
Both GTN units
The ILS will be shown in magenta, when ILS is tuned to the same frequency on both GTN and when ILS1 is selected on MFD1 and ILS2 is selected on MFD2.
O
N TR
O
NOTE
– Select HSI presentation
CRS knob on MFD
– Set to final approach course
N
O
T
C
FND (or NAVD)
– Check (FND/IESI)
PY
Baro settings
C
O
DA and DH
– As required – ARM or CPL (on FND or NAVD)
O N
Autopilot NAV mode
LY
–
Landing light
– Set as required
TI
O N
NOTE D Avoid arming or coupling the ILS too soon (before the aircraft has turned to intercept the ILS), because the autopilot may couple on an ILS side lobe signal.
FO
R
IN
ST
R
U
C
D Minimum LOC interception distance: 4 nm D Capturing of LOC and GS will occur automatically when the aircraft is within: $ 2 dots (LOC) $ 0.5 dots (GS)
ILS LOC indicated less than 2 dots
– Check
APP
appears in AFCS strip
ILS GS indicates less than 0.5 dots
– Check
GS
appears in AFCS strip
At the decision altitude / height : If safe landing using visual references is assured: Normal or Cat A landing
– Perform
If safe landing using visual references is not assured: Missed approach APPROVED Rev. 15
– Perform
4 – 41
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4.13.4.3 LNAV or LP approach Before the Initial Approach Fix (IAF): Approach procedure
– Select and activate. If vectors-to-final are expected, refer to para 4.13.4.6
Navigation mode (on FND or NAVD)
– Check GPS or SBAS
ED
NOTE D If GPS is indicated, expect an LNAV approach.
O
LL
D If SBAS is indicated, expect the selected approach (LNAV, LNAV+V, LP, or LP+V). – Check (FND/IESI)
DA and DH
– Set to LNAV or LP minima
Autopilot NAV mode
– CPL
N
O
T
C
O
N TR
Baro settings
O
PY
Less than 60 seconds before the Final Approach Fix (FAF): – Check
TI
O N
O N
LY
–
C
FND or NAVD page
LNAV LNAV
or +V
LP
or
LP
+V
or
is indicated
FO
R
IN
ST
R
U
C
NOTE D If LNAV or LNAV+V or LP or LP+V do not appear (e.g. due to degradation of GPS), perform a missed approach. D If LP or LP+V do not appear but LNAV is indicated (e.g. due to loss of SBAS), perform an approach using LNAV minima (adjust DA/ DH).
D If LNAV+V or LP+V appears, vertical guidance (VDI) will be shown for advisory information only. The autopilot cannot be coupled to the vertical guidance. D During the approach, the HSI scale will automatically reduce from 1 NM FSD (Full Scale Deflection) to 0.3 NM or less at the FAF.
4 – 42
Airspeed
– Adjust to approach airspeed
Autopilot ALT.A, FPA or V/S mode
– Pre-select as required
Landing light
– As required APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
At the Final Approach Fix (FAF): Autopilot mode indication (FND or NAVD)
– Check
Autopilot ALT.A, FPA or V/S mode
– Activate, as required
APP
indicated
At the decision altitude / height : If safe landing using visual references is assured: – Perform
ED
Normal or Cat A landing
If safe landing using visual references is not assured (aerodrome not visual): – Perform (see para 4.13.4.5)
N TR
O
LL
Missed approach
O
4.13.4.4 LPV or LNAV/VNAV approach
T
C
Before the Initial Approach Fix (IAF):
– Select and activate. If vectors-to-final are expected, refer to para 4.13.4.6
PY
N
O
Approach procedure
– Check GPS or SBAS
O
Navigation mode (on FND or NAVD)
–
C
NOTE D If GPS is indicated, expect an LNAV approach.
LY
D If SBAS is indicated, expect the selected approach (LPV, L/VNAV).
O N
DA and DH
O N
Baro settings
– Set to LPV or LNAV/VNAV minima – CPL
C
TI
Autopilot NAV mode
– Check (FND/IESI)
ST
R
U
Less than 60 seconds before the Final Approach Fix (FAF): – Check
IN
FND or NAVD page
FO
R
LPV
or
L/VNAV NOTE D If LPV or L/VNAV or LNAV do not appear (e.g. due to degradation of GPS), perform a missed approach. D If LPV or L/VNAV do not appear, but LNAV is indicated (e.g. due to loss of SBAS), perform an approach using LNAV minima (adjust DA/DH). Vertical coupling will not be provided (refer to para 4.13.4.3). D During the approach, the HSI scale will automatically reduce from 1 NM FSD (Full Scale Deflection) to 0.3 NM or less at the FAF. continued
APPROVED Rev. 15
4 – 43
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
Airspeed
– Adjust to approach airspeed If the autopilot IAS mode is engaged, the autopilot will automatically adjust the IAS to achieve a maximum rate of descent of 1000 ft/min. The pilot can further reduce the IAS, if required, but cannot increase the IAS reference above the limit set by the autopilot.
NOTE
Autopilot FPA–TRK/HDG–VS knob
– Select FPA/TRK
Approach angle (
– Check (shall match approach chart)
)
– As required
ED
Landing light
N TR
O
LL
At the Final Approach Fix (FAF): Autopilot mode indication (FND or NAVD)
and
APP
indicated
C
O
– Check V.APP
N
O
T
At the decision altitude / height :
PY
If safe landing using visual references is assured:
– Perform
C
O
Normal or Cat A landing
LY
–
If safe landing using visual references is not assured (aerodrome not visual): – Perform (see para 4.13.4.5)
O N
Missed approach
TI
O N
4.13.4.5 Missed approach (GPS approaches only)
R
U
C
Before the Missed Approach Point (MAP) but after the FAF: – Select
MENU sk
– Touch
R
IN
ST
Flight plan page (GTN unit)
FO
ACTIVATE GPS APPROACH sk NOTE
4 – 44
MISSED
– Touch
When an immediate climb is desired, the GA pb on the collective can also be used to initiate the missed approach. The autopilot will remain coupled on the NAV mode and automatic waypoint sequencing is provided.
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
At or after the Missed Approach Point (MAP): At the MAP
– Check SUSP appears
GA pb on collective
– Push
NOTE D When using the GA pb on the collective, the autopilot NAV mode remains coupled and automatic waypoint sequencing is provided.
LL
ED
D When use of the autopilot GA mode is not desired, the missed approach can also be sequenced using the ACTIVATE GPS MISSED APPROACH sk on the GTN unit.
O
4.13.4.6 Vectors-to-Final
T
C
O
N TR
Vectors-to-final are typically used when flying under radar guidance. In this case, selecting a Vectors-to-Final (VTF) approach will ensure a smooth transition between the radar guided segment (typically flown with autopilot HDG or TRK mode) and the final approach segment.
N
O
Before intercepting the final approach course:
– Select and activate. Select Vectors as transition.
C
O
PY
Approach procedure
LY
–
On the FROM side of the approach
SUSP is indicated
– Check GPS or SBAS
O N
Navigation mode (on FND or NAVD)
–
O N
NOTE D If GPS is indicated, expect an LNAV approach.
C
TI
D If SBAS is indicated, expect the selected approach (LPV, L/VNAV, LNAV, LNAV+V, LP, or LP+V). – Check (FND/IESI)
DA and DH
– Set to approach minima
IN
ST
R
U
Baro settings
FO
R
When cleared to intercept final course: Autopilot NAV mode
Final course intercepted
– CPL –
SUSP disappeared
Less than 60 seconds before the Final Approach Fix (FAF): Continue with the appropriate procedure (see para 4.13.4.3 or para 4.13.4.4).
APPROVED Rev. 15
4 – 45
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.14
HTAWS (OPTIONAL)
EFFECTIVITY NOTE EFFECTIVITY 4.14.1
Before Helionix Maintenance Release 1 Any TAWS alert indications in the master list refer to HTAWS. All
HTAWS operation and indication
ED
Pre–flight test:
N TR
O
LL
After power on, HTAWS performs a self–test for about 2 minutes. This is indicated by the following label on the FND:
O
T
C
O
HTAWS TEST
THE HAT INDICATION IS NOT COMPATIBLE WITH THE INTERNAL DMAP TOPOGRAPHIC CHARTS. WHEN SELECTING DMAP, TERRAIN AND OBSTACLE CONFLICTS WILL NOT BE INDICATED. HTAWS ALERTS WILL, HOWEVER, BE GENERATED.
O N
LY
–
C
O
CAUTION
PY
N
Activation of Height Above Terrain (HAT) indication:
O N
To activate the HAT layer on the NAVD or internal DMAP (if installed): – Push – Check
on NAVD/DMAP
R
Audio inhibition
FO
4.14.2
IN
ST
R
U
C
TI
HTAWS sk on NAVD/DMAP
The HTAWS audio may be inhibited once terrain and obstacles were visually acquired and a safe operation is assured. To inhibit the audio warnings of the HTAWS, proceed as follows: EFFECTIVITY
Before Helionix Maintenance Release 1
TAWS switch in overhead console or MUTE pb on cyclic (if installed)
– MUTE and hold for 2 seconds
After 5 minutes
– Audio is automatically re-activated,
– Check
TAWS MUTE
TAWS MUTE
4 – 46
on ML
disappears APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
EFFECTIVITY
After Helionix Maintenance Release 1
TAWS switch in overhead console or MUTE pb on cyclic (if installed)
– MUTE and hold for 2 seconds
After 5 minutes
– Audio is automatically re-activated,
– Check
HTAWS MUTE on ML
HTAWS MUTE EFFECTIVITY
disappears
All
NOTE D When HTAWS audio is inhibited, HTAWS internal DMAP.
LL
ED
is displayed on the NAVD and
T
HTAWS standby
O
4.14.3
C
O
N TR
O
D HTAWS audio can be re-activated at any time by activating the HTAWS/MUTE switch in the overhead console
–
C
O
PY
N
For operations where terrain and obstacle clearance can be assured visually and HTAWS alerts would create unnecessary disturbances (e.g. utility operations at low height), the standby mode may be used to inhibit all HTAWS functions (audio alarms, visual alarms, and terrain display).
– Check
HTAWS STBY
indicated on FND
C
When the TAWS switch is set to NORM, full HTAWS functionality is restored immediately.
FO
R
IN
ST
R
U
NOTE
– STBY
TI
O N
O N
LY
TAWS switch in overhead console
APPROVED Rev. 15
4 – 47
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.15
AHRS PROCEDURES
4.15.1
Use of the AHRS free steering mode (DG) The AHRS free steering mode shall be used when operating to and from an area with an abnormal or perturbed magnetic field (e.g. large metallic platforms or structures). CAUTION D TO AVOID DISCREPANCY INDICATIONS AND AUTOMATIC DESELECTION OF HEADING SOURCES, HDG1 AND HDG2 MUST BE SET TO THE SAME VALUE ($7_) WITHIN ONE MINUTE.
N TR
O
LL
ED
D PROLONGED (>10 MINUTES) OPERATION WITH ONE AHRS IN MAG AND THE OTHER IN DG MODE SHOULD BE AVOIDED, SINCE IT COULD LEAD TO AUTOMATIC DE-SELECTION OF THE HEADING IN MAG MODE.
O
T
C
O
D TO AVOID ERRATIC HEADING BEHAVIOR, THE AFCS UPPER MODES HDG AND NAV SHALL BE DESELECTED WHILE MANUALLY SLEWING HDG1 OR HDG2.
PY
N
Arrival:
C
– Push DG appears on all MFDs (FND or NAVD mode)
O N
LY
–
DG1 and DG2 pb’s (on CCP)
O
Before entering an area with an abnormal / perturbed magnetic field:
Takeoff / departure:
TI
O N
Before taking off from an area with an abnormal / perturbed magnetic field, determine aircraft heading using other means. After engine start-up:
ST
R
U
C
DG1 and DG2 pb’s (on CCP)
While correcting (slewing) the aircraft heading, an ALIGN indication will appear and a HDGi MAG HDG FAIL alert may appear temporarily.
FO
NOTE
– Adjust correct aircraft heading
R
IN
HDG1 and HDG2 sw’s
– Push DG appears on all MFDs (FND or NAVD mode)
After leaving the area with an abnormal / perturbed magnetic field: DG1 and DG2 pb’s (on CCP)
4 – 48
– Push DG disappears on all MFDs (FND or NAVD mode)
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.16
HEATING AND VENTILATION SYSTEM PROCEDURES If the optional Environmental Control System / Air Conditioning System is installed, refer to FMS 9.2–12.
4.16.1
Maximum defrosting / defogging PUSH FOR DEFOG lever
– Push
PUSH FOR AIR lever
– Pull for defrosting, or – Push for defogging – Set to MAX
VENTILATION CKPT rheostat
– Initially set to approx. 40%
Cockpit ventilation outlets
– Close
Cabin heating outlets
– Close if possible
N
O
T
C
O
N TR
O
LL
ED
BLD HTG rheostat
– OFF
PY
VENTILATION PAX sw
– Close all (9) if possible
C
O
Pax vent nozzles
O N
LY
–
NOTE D Once the central part of the windshield has cleared, the VENTILATION CKPT rheostat can be gradually increased to clear the rest of the windshield.
Maximum heating in cockpit / cabin
TI
4.16.2
O N
D The bleed air heating system is most effective at high power settings.
U
C
PUSH FOR DEFOG lever
– Pull – Pull
BLD HTG rheostat
– Set to MAX
VENTILATION CKPT rheostat
– Initially set to 40%
Cabin heating outlets
– Open
VENTILATION PAX sw
– OFF
Pax vent nozzles
– Close all (9) if possible
FO
R
IN
ST
R
PUSH FOR AIR lever
NOTE
APPROVED Rev. 15
Once the cabin/cockpit has warmed up, the VENTILATION CKPT rheostat can be set as required.
4 – 49
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
PUSH FOR AIR lever
– Push
BLD HTG rheostat
– OFF
VENTILATION CKPT rheostat
– Set to HI
VENTILATION PAX sw
– ON
Pax vent nozzles
– Open all (9)
Airspeed
– Increase (if possible)
ED
– Pull
LL
PUSH FOR DEFOG lever
Heating system on / off
O
4.16.4
Maximum ventilation / cooling
N TR
4.16.3
O
To switch the Heating on:
– ON, adjust as required on
O
T
– Check
C
BLD HTG rheostat
PY
N
To switch the Heating off:
– OFF
O
BLD HTG rheostat
off
Selecting recirculated air
O N
4.16.5
LY
–
C
– Check
O N
To prevent outside air from entering the ventilation system (e.g. during landings in sand/dust, during very cold conditions), select recirculated air as follows: – PULL
The electrical heater, if installed, can be used on the ground to slightly pre-heat the windshields, if an EPU is connected. The heating capacity of the electrical heater, however, is insufficient to fully heat the aircraft in cold conditions.
FO
R
NOTE
ST
R
Use of electrical heater with EPU
IN
4.16.6
U
C
TI
PUSH FOR AIR lever
EPU
– Connected
BAT MSTR
– ON, wait 20 seconds – Check
4 – 50
on VMS page
PUSH FOR DEFOG lever
– Push
PUSH FOR AIR lever
– PULL
BLD HTG rheostat
– Set to MAX
Cockpit ventilation
– Check on (ventilator can be heard or airflow can be felt) APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.17
COLD WEATHER PROCEDURES
4.17.1
MGB temperature below –305C Engine start
NOTE
– Perform (see Para. 4.4.1.1 and Para. 4.4.1.2)
Starting only one engine is sufficient to warm up the MGB and hydraulic system. – Monitor
MGB oil temperature
– Shut down
LL
Engine
ED
When MGB oil temperature > –10°C:
O
After rotor has stopped:
– Press TRIM REL sw
N TR
Flight controls
C
O
– Check free movement throughout full travel
O
Oil temperatures below –355C during pre-flight test
C
4.17.2
PY
N
O
T
– Release TRIM REL sw
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
When oil temperature is below –35°C, the MGB and main rotor head oil level is allowed below the MIN level, as long as oil is visible in the sight gauge. If oil level drops below the sight gauge, fill up MGB / main rotor head oil to MIN level, to ensure that enough oil is provided to the system. Further filling is not recommended in order to prevent overflow when the oil warms up.
APPROVED Rev. 15
4 – 51
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.18
SYSTEM (SEMI-)AUTOMATIC TESTS The pre-flight test process is composed of four test phases performed before the flight: – Power-up test: automatically launched when both AMCs are powered up. – Lamp test: initiated by the crew before engine start. – Start-up test: automatically launched when one engine is started and completed when the second engine is in IDLE. – Pre-flight test: initiated by the crew when both engines have started and the avionic master switches are on and both GTN units are operational (CONTINUE pushed).
ED
For each test phase, status messages are displayed in the master list. Failures will be indicated by system related failure messages.
O
N TR
O
LL
When the next test phase is initiated, any messages from the previous test phase will be deleted from the master list, but can be viewed anytime on the CT page (see section 7). To remind the crew that a test phase ended with failure messages, an encircled (T) will be displayed above the master list area.
O
T
C
In addition to the pre-flight test process, the chip sensors are automatically tested at a 10 minute interval throughout the flight (continuity test).
PY
N
Definition of actions:
–
C
O
The actions below are provided for the case where an MMEL/MEL is not readily available and a single flight is required to complete an important mission. If an MMEL/MEL is readily available, the crew shall refer to the MMEL/MEL.
U
C
TI
O N
O N
LY
COMPLETE MISSION: A single flight (until engine shutdown) to complete the mission and reposition the helicopter to an appropriate location where assistance is available is permitted if only a single failure is present. Additional flight rule restrictions may be shown in brackets (e.g. VFR). Before further flights are performed or if multiple failures are present, the MMEL/MEL must be consulted to determine if and under which conditions further flights are possible.
Power-up test
R
4.18.1
IN
ST
R
ABORT MISSION: Do not start the engines. Maintenance is normally required before the next flight. Consultation of the MMEL/MEL is recommended in any case.
FO
The power-up test is launched automatically when the helicopter electrical system is powered up (BAT MSTR sw ON). During the test, the message PWR–UP TST will be displayed. Successful completion of the test is indicated by the message PWR–UP TST OK.
4 – 52
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
ML message / description AIR1
Consequence / Action Complete mission (VFR)
DATA REDUNDANCY or DATA REDUNDANCY
AIR2
Air data monitoring degraded Before Helionix Maintenance Release 1 Complete mission (VFR)
AMC MINOR REDUND
NOTE
This alert may be caused by a failed or switched off MFD. In this case, this alert is not considered a multiple failure.
N TR
O
LL
AMC degraded (loss of signal monitoring)
ED
EFFECTIVITY
All Complete mission
T
CHAN A REDUND
N
AMC2
C
O
CHAN B REDUND
–
or CHAN B REDUND
AMC2
LY
AMC1
O
or CHAN A REDUND
PY
AMC1
C
O
EFFECTIVITY
REDUNDANCY
O N
ATT1
O N
Respective AMC channel degraded
ATT2
U
C
TI
or REDUNDANCY
Complete mission
ST
R
Attitude monitoring degraded (AHRS degradation) Procedure:
IN
ATT REDUNDANCY
R
AHRS 3 CBs (2x) in overhead panel
FO
AHRS 3 has failed. ENG1
Complete Mission Complete mission (see also Sect. 3)
CHIP SENSOR or CHIP SENSOR
– Pull
ENG2
Engine chip sensor failed FADEC1
Abort mission
SIGNAL FAIL or SIGNAL FAIL
FADEC2
No information is being received from the FADECs APPROVED Rev. 15
4 – 53
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ML message / description GEN1
Consequence / Action Complete mission
DISC SENSOR or DISC SENSOR
GEN2
The sensor, which monitors GEN DISCONNECT, failed Check if collective was latched during test
GND/FLT SENSOR
If collective was not latched: – Latch
BAT MSTR sw
– OFF, wait 30 sec, ON and engage
O
LL
ED
Collective lever
O
T
C
O
N TR
– Check GND/FLT SENSOR not displayed
N
Ground/Flight detection degraded
– Check PWR-UP TST OK di l displayed d
O
PY
If message remains: Abort mission
LY
–
C
EFFECTIVITY
This failure can be caused by an MFD failure (refer to MMEL/MEL for start-up procedure).
EFFECTIVITY
All
FO
R
IN
ST
R
U
C
TI
O N
O N
NOTE
Before SB MBB–BK117 D–2–42–003 (Helionix Maintenance Release 1)
4 – 54
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
ML message / description HYD1
Consequence / Action
PRESS SENSOR
Procedure:
or PRESS SENSOR
VMS page HYD2
– Select
If VMS SENSOR is indicated in FND: Hydraulic pressure
– Check affected system indicates (***)
Engine start
– Perform
Hydraulic check
– Perform
LL
ED
– Check control forces are normal (hydraulically boosted)
C
O
N TR
O
– HYD1 LOW PRESS resp. LOW PRESS HYD2 appear on FND
O
T
Complete mission
N
If VMS SENSOR is not indicated in FND: – Check valid indication
Engine start
– Perform
Hydraulic pressure
– Check normal indication
Hydraulic check
– Perform
PY
Hydraulic pressure
– Check control forces are normal (hydraulically boosted)
TI
O N
O N
LY
–
C
O
Low pressure sensor for hydraulic system 1/2 failed
ST
R
U
C
– Affected system HYD1 LOW PRESS resp.
FO
R
IN
LOW PRESS HYD2 does not appear on FND Complete mission Otherwise: abort mission
HYD1 TR PRESS SENSOR
Abort mission
The pressure sensor, which monitors the tail rotor shut-off valve, failed.
APPROVED Rev. 15
4 – 55
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
ML message / description IBF1
INCORRECT CONFIG
Consequence / Action IBF2
Procedure:
IBF incorrect configuration
CONFIG page
– Select
IBF config
– Select and validate
BAT MSTR sw
– OFF, wait 30 sec
BAT MSTR sw
– ON and engage
Master list
– PWR-UP TST OK
If unsuccesful: Abort mission
ED
Complete mission
MAG HDG REDUND
or CPU1 MINOR DEG
O
MFD1
N TR
MFD1
or CPU2 MAJOR DEG
Procedure: MFD1
– Switch off
MFD1-CP CBs
– Pull (in OVHP)
O
CPU1 MAJOR DEG
C
MFD1
LL
One magnetic sensor (MAS) failed
T
Complete mission (VFR):
N
O
NOTE
–
C
O
PY
– Pilot flying must be in the right hand seat, – Weather radar must be controlled through MFD2
TI
or
MFD2
O N
MFD2
MFD2
– Switch off
MFD-P CBs
– Pull (in OVHP)
MFD copilot sw (CCP)
FO
R
IN
ST
R
U
C
CPU1 MINOR DEG
Procedure:
LY
or CPU2 MAJOR DEG
MFD2
O N
CPU1 MAJOR DEG
Complete mission (VFR) CAUTION
NOTE
4 – 56
– Check normal operation (or qualified crew member on copilot’s seat to operate MFD1)
THE WAETHER RADAR SHALL BE SWITCHED OFF MANUALLY BELOW 50 FT
If weather radar is required, a qualified crew memeber in the left hand seat is required to operate WXR through MFD1.
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
ML message / description
Consequence / Action Procedure:
CPU1 MAJOR DEG
MFD4
or CPU2 MAJOR DEG
MFD4
– Switch off
MFD4
MFD-CTR CBs
– Pull (in OVHP)
MFD4
MFD copilot sw (CCP)
– Check normal operation (or qualified crew member on copilot’s seat to operate MFD1)
LL
Complete mission (VFR)
ED
or CPU1 MINOR DEG
O
NOTE
T
C
O
N TR
– ACAS shall be considered inoperative. – If the weight cannot be set before takeoff, a conservative VNE will be calculated based on the MTOW. Complete mission (see also Sect. 3)
N
O
MGB CHIP SENSOR
PY
MGB chip sensor failed
Complete mission if:
C
O
MGB TEMP SENSOR
LY O N
Mast moment sensor failed
O N
MM SENSOR
– MGB oil temperature and pressures properly indicated on the VMS page.
–
MGB high temperature switch failed
C
TI
OAT SENSOR DEG
ST
R
U
OAT sensor degraded.
R
IN
PWR-UP TST ABORT
FO
The automatic power-up test could not be completed
are
Refer to Sect. 3 (Mast moment indication failure)
Complete mission (VFR), if: – Valid OAT is indicated on FND Otherwise: Abort mission Procedure: BAT MSTR sw
– OFF, wait 30 sec
FADEC cb’s b’
– Check Ch k iin
BAT MSTR sw
– ON
If alert remains: Abort mission PWR-UP TST PENDG The automatic power-up test could not be launched
APPROVED Rev. 15
Procedure: BAT MSTR sw
– OFF, wait 30 sec
BAT MSTR sw
– ON and engage
If alert remains: Abort mission
4 – 57
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ML message / description MGB PRESS SENSOR
Procedure:
or MGB PRESS SENSOR SYS2
VMS page
– Select
MGB oil temperature
– Check valid indication
If VMS SENSOR is i indicated i di t d in i FND: FND
Before Helionix Maintenance Release 1
EFFECTIVITY
After Helionix Maintenance Release 1
Warning unit
– Check MGB OIL P
Complete mission If VMS SENSOR is not indicated in FND:
MGB LOW PRESSURE warning is triggered based on the pressure sensor.
MGB oil pressure
– Check valid indication
After Engine start
– Check oil presssure rises
O
Complete mission
All
C
Otherwise: abort mission
T
EFFECTIVITY
– Check affected system indicates (***)
ED
MGB LOW PRESSURE warning is not available
MGB oil pressure
LL
EFFECTIVITY
O
MGB pressure switch sensor failed
N TR
SYS1
Consequence / Action
Complete mission (see also Sect. 3)
N
O
TGB CHIP SENSOR
PY
TGB chip sensor failed
Consult MMEL or abort mission.
C
O
VMS/UMS SIGNAL
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
Some ML messages and/or VMS parameters may be missing
4 – 58
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.18.2
Lamp test The lamp test is initiated by the crew before engine start. During the lamp test, additional automatic tests are conducted. If a failure is detected, any of the messages listed below may appear. (T) will not appear. ML message / description
Consequence / Action Procedure:
BAT OVHT SENSOR
Battery
Battery temperature sensor failed
– Check full charged
GEN 1 and GEN 2
ED
After engine start: – Check operative
LL
(green symbol)
– OFF
N TR
O
BAT MSTR sw
C Complete l t mission i i (VFR)
IN CASE OF A DOUBLE GENERATOR FAILURE, ALL ELECTRICAL POWER WILL BE TEMPORARILY LOST. SET BAT MSTR SWITCH TO ON TO REGAIN BATTERY POWER FOR UP TO 30 MINUTES.
Abort mission
O N
Fuel low sensor failed
LY
or LOW SENSOR
–
LOW SENSOR
C
TI
SMOKE SENSOR
U
FUEL2
O N
FUEL1
C
O
PY
N
O
T
C
O
CAUTION
Complete mission, if a cabin/cargo compartment separation (wall or quilted mats) is not installed.
FO
R
IN
ST
R
The cargo smoke detector failed.
APPROVED Rev. 15
4 – 59
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.18.3
Start-up test The start-up test is launched automatically when one engine is started. The start–up test completes when the second engine is in IDLE. During the test, the message START–UP TST will be displayed. Successful completion of the test is indicated by the message START–UP TST OK. If failures were detected during the test, any of the messages listed below may appear. ML message / description
Abort mission
and/or WU CONFIG FAIL
ED
WU CONFIG FAIL ENG2
LL
ENG1
Consequence / Action
N TR O O
T
or SIGNAL FAIL
C
Abort mission
SIGNAL FAIL FADEC2
N
FADEC1
O
Not applicable for normal operation. Alert may appear only after change of engine or warning unit.
O
PY
No information is being received from the FADECs
Complete mission, if:
–
C
HEATING FAIL
LY O N
EECU bleed air inhibition signal failed
– Missions requiring Cat A certification are not performed,
O N
– Performance charts for Heating ON are used. Procedure: If VMS SENSOR is indicated in FND: NR gauge on FND
ST
FO
R
IN
NR sensor values inconsistent or unavailable
4 – 60
– Check valid indication – NR and N2 are matched t h d (t1%)
R
U
C
TI
NR SENSOR
Complete mission NOTE
Aggressive maneuvers which could lead to an NR/N2 desynchronisation should be avoided
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
4.18.4
Pre-flight test The pre-flight test is initiated by the crew when both engines are running. Avionic master switches must be ON before starting the test. Make sure CONTINUE is pressed on both GTN units. During the test, the message P–FLT TST will be displayed. Successful completion of the test is indicated by the message P–FLT TST OK. If failures were detected during the test, any of the messages listed below may appear. If required, the pre-flight test can be aborted by pushing the AP/BKUP CUT switch twice (APi TST ABORTED will appear).
Complete mission AMC2
AMC2
– O N
LY
TST ABORTED
AP2
FO
R
IN
ST
R
U
C
TI
O N
or TST ABORTED
C
Respective AMC channel degraded AP1
AFCS selftest aborted before completion
APPROVED Rev. 15
PY
or CHAN B REDUND
N
CHAN B REDUND
O
AMC1
O
T
or CHAN A REDUND
O
CHAN A REDUND
C
AMC1
Consequence / Action
O
ML message / description
LL
ED
The rad-alt function is checked automatically during the pre-flight test.
N TR
NOTE
Procedure: AFCS status on VMS page Affected systems AP/BKUP CUT pb AFCS test prerequisites AFCS test NOTE
– Check – – – –
Verify Press Set Repeat
If the pre-flight test aborts or fails more than 3 times, consider the test as unsuccessful.
If the AFCS test was unsuccessful: VMS/SYSTpage – Select – Check SEMA set 1 (pitch, roll, yaw) are operative (green or cyan) – Check BKUP SAS is indicated AP1 and AP2 pb – Switch OFF AFCS strip – SAS SAS Return to the nearest repair station (VFR) – Observe the respective AFCS limitation for flight with BKUP SAS (refer to Sect. 2)
4 – 61
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
ML message / description AP1
Consequence / Action
TST FAIL or TST FAIL
AP2
Procedure: AFCS status on VMS page on VMS SYST page Affected systems AP/BKUP CUT pb AFCS test prerequisites
LL
If the pre-flight test aborts or fails more than 3 times, consider the test as unsuccessful.
N TR
O
NOTE
– Verify – Press – Set, ensure collective is unlatched. – Repeat
ED
AFCS test
– Check
C
O
If the AFCS test was unsuccessful: VMS/SYST page – Select / p g – Check SEMA set 1 (pitch, roll, yaw) are operative (green or cyan) – Check BKUP SAS (IESI) is operative (green or cyan) AP1 and AP2 pb – Switch OFF AFCS strip (FND) – SAS SAS is indicated Return to the nearest repair station (VFR) – Observe the respective AFCS limitation for flight with BKUP SAS (refer to Sect. 2) Complete mission
R
REDUNDANCY
ST
ATT1
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
AFCS selftest failed
ATT2
R
IN
or REDUNDANCY
FO
Attitude monitoring degraded (AHRS degradation)
4 – 62
APPROVED Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
ML message / description
Consequence / Action Procedure:
AVIONIC TST FAIL
VMS SYST page
– Check affected systems
Verify affected systems – On If system(s) off Pre-flight test
– Switch ON – Repeat
If not successful and affected system is:
ED
– FMS1, FMS2, GPS1 or GPS2: Complete mission (VFR). De–activate the affected FMS using the FMS OFF switch. switch
LL
One or more avionic system(s) off or failed
C
O
N TR
O
– Direction finder (DF) or weather radar (WXR) or ACAS: Complete mission, if the affected system is not required for the mission. De-activate the affected system.
PY
N
O
T
– VOR1, VOR2, ADF, and/or DME: Complete mission (VFR) if navigation by visual landmarks is possible.
C
O
– Radar altimeter (RA): See RA FAIL / RA TST FAIL message description Complete mission (VFR)
LY
–
IESI SIGNAL FAIL
FO
R
IN
ST
R
U
C
TI
O N
O N
Loss or degradation of IESI altitude, air data and backup monitoring
APPROVED Rev. 15
4 – 63
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) NORMAL PROCEDURES
ML message / description EFFECTIVITY
Consequence / Action Complete mission (VFR):
Before Helionix Maintenance Release 1
– Cat A procedures that require the use of rad-alt are prohibited; – VFR night using NVGs is prohibited; – ILS approach using GS is prohibited; – Flight lower than 500 ft over water is prohibited, except for takeoff and landing; – Over water, descending below 500 ft during an approach is permitted only when the landing site is clearly visible to the pilot; – if flight without rad-alt is permitted by the operational rules.
RA FAIL EFFECTIVITY
After Helionix Maintenance Release 1
LL
All
N TR
O
EFFECTIVITY
ED
RA TST FAIL
O
T
C
O
CAUTION D THE AUTOPILOT WILL NOT PERFORM AUTOMATIC LEVEL OFF.
C
O
PY
N
D THE AUTOMATIC SHUT DOWN FUNCTION OF WEATHER RADAR OR LASER POINTER WILL BE INOPERATIVE. REMEMBER TO MANUALLY SHUT OFF ANY AFFECTED EQUIPMENT. D DECISION HEIGHT WILL BE INOPERATIVE, USE DECISION ALTITUDE WHEN POSSIBLE.
NOTE D HTAWS will be degraded. D GTC.H and GTC may be degraded. D The autopilot mode CR.HT cannot be selected.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
The rad-alt test has failed. Rad-alt indication is not reliable.
4 – 64
APPROVED Rev. 15
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ML message / description
Consequence / Action Procedure:
VMS SENSOR
VMS page
– Select
If MGB temperature indication is invalid (*** indicated): Start-up test
–MGB TEMP SENSOR did not appear during start-uup test. – Valid indication
OAT
– Above –10_C
LL
N TR
O
Complete mission
ED
MGB oil pressure
In case of vehicle sensor loss (hydraulic pressure, MGB temperature, MGB pressure, electrical sensor)
O
If MGB oil pressure indication is invalid (*** indicated):
C
Refer to the procedure for
N
O
T
SYS1/2 MGB PRESS SENSOR
Refer to the procedure for HYD1/2 PRESS SENSOR
If any other indications have failed (***): Abort mission.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
If HYD oil pressure indication is invalid (*** indicated):
APPROVED Rev. 15
4 – 65/(4 – 66 blank)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
SECTION 5 PERFORMANCE DATA TABLE OF CONTENTS
Page APPROVED PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 1
5.1.1
Standard performance conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 1
5.1.2
Variable factors affecting performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 2
5.1.3
Reading of the charts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 2
5.1.4
Performance indication on the VMS page . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 2
5.1.5
Power check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 3
C
O
N TR
O
LL
ED
5.1
O
T
5.1.5.1 Power check procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 3
N
5.1.5.2 Power check intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 3
PY
5.1.5.3 Automatic ground power check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 4
C
O
5.1.5.4 Automatic in-flight power check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 6
LY
–
5.1.5.5 Manual ground power check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 8
O N
5.1.5.6 Power trend monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 17 Density altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 18
5.1.7
Airspeed system calibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 20
5.1.8
Static system correction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 23
C
TI
O N
5.1.6
U
5.1.8.1 Normal static system altitude correction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 23 Height–velocity envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 25
IN
5.1.9
ST
R
5.1.8.2 Alternate static system altitude and airspeed correction . . . . . . . . . . . . . . . . 5 – 23
FO
R
5.1.10 5.1.11
Hover ceiling - AEO performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 28 Hover ceiling in gound effect - OEI performance . . . . . . . . . . . . . . . . . . . 5 –37
5.1.11.1 Bleed air consumers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 37 5.1.11.2 Performance data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 37 5.1.12
Hover ceiling out of gound effect - OEI performance . . . . . . . . . . . . . . . 5 –40
5.1.12.1 Bleed air consumers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 40 5.1.12.2 Performance data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 40 5.1.13
Takeoff distance from hover to 50 feet height . . . . . . . . . . . . . . . . . . . . . . 5 – 45
5.1.14
Rate of climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 48
5.1.15
Landing distance from 50 feet height to a complete stop on the ground (1 x TURBOMECA ARRIEL 2E) . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 76
APPROVED Rev. 6
5–i
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Page ADDITIONAL NON-APPROVED PERFORMANCE DATA . . . . . . . . . . . . . 5 –79
5.2.1
Standard performance conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 79
5.2.2
Variable factors affecting performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 –79
5.2.3
Reading of the charts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 79
5.2.4
Maximum cruising speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 80
5.2.5
Specific fuel consumption . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 85
5.2.6
Maximum range . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 89
5.2.7
Endurance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 102
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
5.2
5 – ii
APPROVED Rev. 6
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LIST OF FIGURES Page WEIGHT & PERFORMANCE area on VMS page
Fig. 5-2
Automatic ground power check RESULTS page for engine 2 – example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 5 Automatic in-flight power check RESULTS page for engine 1 – example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 7 Manual ground power check (TOT) for engine No. 1 and 70% torque . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 11 Manual ground power check (TOT) for engine No. 2 and 70% torque . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 12 Manual ground power check (N1) for engine No. 1 and 70% torque, bleed valve open . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 13 Manual ground power check (N1) for engine No. 2 and 70% torque, bleed valve open . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 14 Manual ground power check (N1) for engine No. 1 and 70% torque, bleed valve closed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 – 15
Fig. 5-8
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Manual ground power check (N1) for engine No. 2 and 70% torque, bleed valve closed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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Fig. 5-9
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Fig. 5-7
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Fig. 5-6
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Fig. 5-5
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Fig. 5-4
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Fig. 5-3
.................... 5 – 2
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Fig. 5-1
5 – 16 5 – 17 5 – 19 5 – 21
Fig. 5-13 Fig. 5-14
Airspeed system calibration (copilot) . . . . . . . . . . . . . . . . . . . . . . . . . . . Height-velocity diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 22 5 – 27
Fig. 5-15 Fig. 5-16
Hover ceiling in ground effect (AEO, TOP, heating off ) . . . . . . . . . . Hover ceiling in ground effect (AEO, TOP, heating on ) . . . . . . . . . .
5 – 29 5 – 30
Fig. 5-17 Fig. 5-18 Fig. 5-19
Hover ceiling in ground effect (AEO, MCP, heating off ) . . . . . . . . . . Hover ceiling in ground effect (AEO, MCP, heating on ) . . . . . . . . . . Hover ceiling out of ground effect (AEO, TOP, heating off ) . . . . . . .
5 – 31 5 – 32 5 – 33
Fig. 5-20 Fig. 5-21
Hover ceiling out of ground effect (AEO, TOP, heating on ) . . . . . . . Hover ceiling out of ground effect (AEO, MCP, heating off ) . . . . . . .
5 – 34 5 – 35
Fig. 5-22 Hover ceiling out of ground effect (AEO, MCP, heating on ) . . . . . . . EFFECTIVITY TU206 NOT installed Fig. 5-23 Hover ceiling in ground effect (OEI, 2 min power, without TU206, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 36
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Fig. 5-10 Plotting example for power trend monitoring . . . . . . . . . . . . . . . . . . . . Fig. 5-11 Density altitude chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fig. 5-12 Airspeed system calibration (pilot) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EFFECTIVITY TU206 installed Fig. 5-24 Hover ceiling in ground effect (OEI, 2 min power, with TU206, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EFFECTIVITY TU206 NOT installed Fig. 5-25 Hover ceiling out off ground effect (OEI, 2 min power, without TU206, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EFFECTIVITY TU206 installed Fig. 5-26 Hover ceiling out off ground effect (OEI, 2 min power, with TU206, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EFFECTIVITY All APPROVED Rev. 6
5 – 38
5 – 39
5 – 42
5 – 43
5 – iii
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
Page 5-27 5-28 5-29 5-30 5-31
Hover ceiling out off ground effect (OEI, 30 sec power, heating off) Takeoff profile (category B) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Takeoff distance from hover to 50 ft height (AEO) . . . . . . . . . . . . . . . . Vy – Diagramm . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rate of climb (AEO, TOP, 2000 kg to 2600 kg, heating off) . . . . . . .
5 5 5 5 5
– – – – –
44 45 47 48 50
Fig. 5-32 Rate of climb (AEO, TOP, 2000 kg to 2600 kg, heating off) . . . . . . . Fig. 5-33 Rate of climb (AEO, TOP, 2600 kg to 3200 kg, heating off) . . . . . . . Fig. 5-34 Rate of climb (AEO, TOP, 2600 kg to 3200 kg, heating on) . . . . . . . Fig. 5-35 Rate of climb (AEO, TOP, 3200 kg to 3700 kg, heating off) . . . . . . . Fig. 5-36 Rate of climb (AEO, TOP, 3200 kg to 3700 kg, heating on) . . . . . . . Fig. 5-37 Rate of climb (AEO, MCP, 2000 kg to 2600 kg, heating off) . . . . . . . Fig. 5-38 Rate of climb (AEO, MCP, 2000 kg to 2600 kg, heating on) . . . . . . . Fig. 5-39 Rate of climb (AEO, MCP, 2600 kg to 3200 kg, heating off) . . . . . . . Fig. 5-40 Rate of climb (AEO, MCP, 2600 kg to 3200 kg, heating on) . . . . . . . Fig. 5-41 Rate of climb (AEO, MCP, 3200 kg to 3700 kg, heating off) . . . . . . . Fig. 5-42 Rate of climb (AEO, MCP, 3200 kg to 3700 kg, heating on) . . . . . . . Fig. 5-43 Rate of climb (OEI, MCP, 2000 kg to 2600 kg, heating off) . . . . . . . Fig. 5-44 Rate of climb (OEI, MCP, 2000 kg to 2600 kg, heating on) . . . . . . . Fig. 5-45 Rate of climb (OEI, MCP, 2600 kg to 3200 kg, heating off) . . . . . . . Fig. 5-46 Rate of climb (OEI, MCP, 2600 kg to 3200 kg, heating on) . . . . . . . Fig. 5-47 Rate of climb (OEI, MCP, 3200 kg to 3700 kg, heating off) . . . . . . . Fig. 5-48 Rate of climb (OEI, MCP, 3200 kg to 3700 kg, heating on) . . . . . . . EFFECTIVITY TU206 NOT installed Fig. 5-49 Rate of climb (OEI, 2 min. power, VY, without TU206, 3200 kg to 3700 kg, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EFFECTIVITY TU206 installed Fig. 5-50 Rate of climb (OEI, 2 min. power, VY, with TU206, 3200 kg to 3700 kg, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EFFECTIVITY TU206 NOT installed Fig. 5-51 Rate of climb (OEI, 2 min. power, VTOSS, without TU206, 2000 kg to 2600 kg, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fig. 5-52 Rate of climb (OEI, 2 min. power, VTOSS, without TU206, 2600 kg to 3200 kg, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fig. 5-53 Rate of climb (OEI, 2 min. power, VTOSS, without TU206, 3200 kg to 3700 kg, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EFFECTIVITY TU206 installed Fig. 5-54 Rate of climb (OEI, 2 min. power, VTOSS, with TU206, 2000 kg to 2600 kg, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fig. 5-55 Rate of climb (OEI, 2 min. power, VTOSS, with TU206, 2600 kg to 3200 kg, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fig. 5-56 Rate of climb (OEI, 2 min. power, VTOSS, with TU206, 3200 kg to 3700 kg, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EFFECTIVITY All
5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5
– – – – – – – – – – – – – – – – –
51 52 55 54 55 56 57 58 59 60 61 62 63 64 65 66 67
5 – 68
5 – 69
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Fig. Fig. Fig. Fig. Fig.
5 – iv
5 – 70 5 – 71 5 – 72
5 – 73 5 – 74 5 – 75
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
Landing profile (category B) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 76
Fig. 5-58
Landing distance from 50 feet height to a complete stop on the ground (OEI) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 78
Fig. 5-59
Maximum cruising speed (AEO, ISA) . . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 81
Fig. 5-60
Maximum cruising speed (AEO, ISA –20_C) . . . . . . . . . . . . . . . . . . . .
5 – 82
Fig. 5-61
Maximum cruising speed (AEO, ISA +20_C) . . . . . . . . . . . . . . . . . . . .
5 – 83
Fig. 5-62
Maximum cruising speed (AEO, ISA +35_C) . . . . . . . . . . . . . . . . . . . .
5 – 84
Fig. 5-63
Specific fuel consumption (AEO, level speed 0 – 55 KCAS) . . . . . . .
5 – 86
Fig. 5-64
Specific fuel consumption (AEO, level speed 55 – 138 KCAS) . . . .
5 – 87
Fig. 5-65
Specific fuel consumption vs torque and temperature (AEO) . . . . . .
5 – 88
Fig. 5-66
Maximum range (2800 kg, ISA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 90
Fig. 5-67
Maximum range (2800 kg, ISA–20_C) . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 91
Fig. 5-68
Maximum range (2800 kg, ISA+20_C) . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 92
Fig. 5-69
Maximum range (2800 kg, ISA+35_C) . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 93
Fig. 5-70
Maximum range (3200 kg, ISA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fig. 5-71
Maximum range (3200 kg, ISA–20_C) . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 95
Fig. 5-72
Maximum range (3200 kg, ISA+20_C) . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 96
Fig. 5-73
Maximum range (3200 kg, ISA+35_C) . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 97
Fig. 5-74
Maximum range (3700 kg, ISA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 98
Fig. 5-75
Maximum range (3700 kg, ISA–20_C) . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 99
Fig. 5-76
Maximum range (3700 kg, ISA+20_C) . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 100
Fig. 5-77
Maximum range (3700 kg, ISA+35_C) . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 101
Fig. 5-78
Maximum Endurance (2800 kg, ISA) . . . . . . . . . . . . . . . . . . . . . . . . . . .
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5 – 103
Fig. 5-79
Maximum Endurance (2800 kg, ISA–20_C) . . . . . . . . . . . . . . . . . . . . .
5 – 104
Fig. 5-80
Maximum Endurance (2800 kg, ISA+20_C) . . . . . . . . . . . . . . . . . . . . .
5 – 105
Fig. 5-81
Maximum Endurance (2800 kg, ISA+35_C) . . . . . . . . . . . . . . . . . . . . .
5 – 106
Fig. 5-82
Maximum Endurance (3200 kg, ISA) . . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 107
Fig. 5-83
Maximum Endurance (3200 kg, ISA–20_C) . . . . . . . . . . . . . . . . . . . . .
5 – 108
Fig. 5-84
Maximum Endurance (3200 kg, ISA+20_C) . . . . . . . . . . . . . . . . . . . . .
5 – 109
Fig. 5-85
Maximum Endurance (3200 kg, ISA+35_C) . . . . . . . . . . . . . . . . . . . . .
5 – 110
Fig. 5-86
Maximum Endurance (3700 kg, ISA) . . . . . . . . . . . . . . . . . . . . . . . . . . .
5 – 111
Fig. 5-87
Maximum Endurance (3700 kg, ISA–20_C) . . . . . . . . . . . . . . . . . . . . .
5 – 112
Fig. 5-88
Maximum Endurance (3700 kg, ISA+20_C) . . . . . . . . . . . . . . . . . . . . .
5 – 113
Fig. 5-89
Maximum Endurance (3700 kg, ISA+35_C) . . . . . . . . . . . . . . . . . . . . .
5 – 114
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Fig. 5-57
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PERFORMANCE DATA
APPROVED Rev. 6
5 – 94
5 – v/(5 – vi blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
SECTION 5 PERFORMANCE DATA This section contains the performance data charts necessary for pre-flight and in-flight mission planning.
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APPROVED PERFORMANCE DATA
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For a definition of the terms, abbreviations and symbols used in this section (refer to section 1).
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Standard performance conditions
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5.1.1
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This subsection contains approved performance data charts necessary for preflight and inflight mission planning.
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All performance in this section is based on the following conditions: Helicopter limits will be respected (refer to section 2)
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Installation and accessory losses are included in each performance chart.
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The engine bleed valve, which switches automatically between open and closed, is taken into account.
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APPROVED Rev. 0
5–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.2
Variable factors affecting performance Details of the variable factors affecting performance are given in the appropriate diagrams. NOTE D None of the curves presented should be extrapolated, but interpolation between given data is permissible.
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D Unless otherwise authorized by operating regulations, the pilot is not authorized to credit more than the performance increase resulting from 50% of the reported headwind component.
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D For negative pressure altitudes, if not shown in the respective chart, the line for 0 ft shall be used.
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Reading of the charts
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5.1.3
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D Performance data contained in this flight manual are not assured in the event of sand or hailstone ingestion into the engine(s).
EFFECTIVITY
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Performance indication on the VMS page
Before Helionix Maintenance Release 1 THE PERFORMANCE DATA ON THE VMS PAGE SHOULD NOT BE USED FOR THE FOLLOWING CASES: – ABOVE 13000 FT DENSITY ALTITUDE, AND – WHEN TU206 IS INSTALLED: FOR OEI 2MIN HOGE DATA. FOR THOSE CASES REFER TO THE FLIGHT MANUAL.
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CAUTION
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lt is of the utmost importance that the charts be read accurately, especially the multi-variable graphs. In this type of presentation, errors in reading can be cumulative, resulting in large final errors. Close attention should be paid to subdivisions of the grid.
CAUTION
THE CAT A VTOL WEIGHT DOES NOT CONSIDER WEIGHT REDUCTIONS RESULTING FROM OPTIONAL EQUIPMENT. ALWAYS COMPARE THE INDICATED CAT A VTOL WEIGHT WITH THE CAT A CLEAR HELIPORT WEIGHT OBTAINED FROM THE PERFORMANCE CHARTS (PROCEED ACCORDING TO SECTION 9.1–1.C)
The data field of the VMS page (Fig. 5-1) shows the maximum gross weight for AEO HIGE, AEO HOGE, Cat A VTOL (see section 9.1–1.C), OEI 30s HOGE, and OEI 2min HOGE. This maximum gross weight is calculated based on the current altitude, OAT, heating condition (on or off). All maximum gross weights are based on conditions with zero wind. Any hover performance penalty entered on the weight and performance page (see Para 7.13.5.1) will be applied to the weights shown the VMS page.
5–2
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
Power check
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5.1.5
WEIGHT & PERFORMANCE area on the VMS page
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Fig. 5-1
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(TURBOMECA ARRIEL 2E) 5.1.5.1 Power check procedures
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The power check procedure allows the crew to verify that the engine power available is within the limits established for legal use of the flight manual performance charts.
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Three different engine power check procedures are provided:
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a) Automatic ground power check
C –
c) Manual ground power check
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b) Automatic in-flight power check
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The ground power check shall be used when operational rules require a power check before flight.
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If a sandfilter system is installed, observe the procedures in accordance with FMS 9.2-5 “IBF-System”.
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5.1.5.2 Power check intervals
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Either ground or inflight power check shall be accomplished
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– at intervals not exceeding 25 flight hours for Category B operation.
– whenever abnormal engine function is suspected. National operating rules may require a different power check interval.
APPROVED Rev. 9
5–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.5.3 Automatic ground power check To obtain correct check results, the following preconditions must be established: – Adequate distance from buildings, trees, etc. to reduce possibility of wind vortices. – Helicopter heading into wind. Maximum wind speed 10 kt. – Bleed air heating OFF. The automatic ground power check procedure (Fig. 5-2) shall be carried out: – On the ground, and
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– Under single engine operating condition (other engine at IDLE)
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CAUTION D ENGINE/TRANSMISSION CONTINUOUS POWER LIMITATIONS IN SECTION 2 ARE NOT TO BE EXCEEDED.
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It is recommended to switch off the AFCS during the power check. Mast moment limits could be infringed as the AFCS tries to maintain the helicopter attitude when increasing the collective and the helicopter gets light on skids.
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D DURING THE POWER CHECK, THE PILOT SHALL REMAIN VIGILANT AS THE AIRCRAFT MAY BECOME LIGHT ON SKIDS DURING THE CHECK. FOR THIS REASON, GROUND POWER CHECKS WITH A VERY LIGHT AIRCRAFT SHALL BE AVOIDED.
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To perform the power check, the standard start-up procedure (refer to section 4) shall be used. Both engines are in IDLE at the start of the procedure. The power check should be performed on each engine, in sequence, using the same procedure.
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1. Master List
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2. VMS page
– Check no FADEC related alerts – Select – FLIGHT
4. Affected engine GEN switch
– OFF
5. Collective lever
– Slowly increase to 70% torque
While increasing the collective, the power split audio tone will sound above 2 FLI.
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NOTE
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3. Affected ENG MAIN switch
6. Clock
– Start – Maintain 70% torque steady for 2 minutes
7. VMS page / EPC area
– Press RUN key – COMPUTING DATA appears – EPC appears in the FLI – Do not move collective until progress bar is filled – The power check result appears
5–4
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
8. Collective lever
– Slowly decrease to flat pitch
9. Affected ENG MAIN switch
– IDLE
10. Affected engine GEN switch
– RESET, then NORM
11. BARO setting
– Set as required
Repeat for other engine, if desired. Interpreting the results of the automatic ground power check: 1) RESULTS page is shown
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The results shown on the VMS page /EPC area are shown as in the example of Fig. 5-2. The mean parameter values recorded during the check are shown on the left. The power check results (margins) are shown on the right. The margins are given in torque at ISO-TOT and in torque at ISO-N1. If both margins (TOT and N1) are zero or positive (green), the engine power is assured and the performances in the flight manual are achievable. A performance surplus cannot be calculated from the margins.
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If one or both torque margins are negative (amber), the test is failed and maintenance is required.
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387 ON–GROUND POWER CHECK RESULTS ENGINE2 MEAN VALUES: MARGINS: N1 : 90.9 % TRQ ISO–TOT : 8.3 % N2 : 101.4 % TRQ ISO–N1 : 5.0 % TRQ : 69.6 % TOT : 716 P0 : 967.5 hPa T1 : 21.2
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Automatic ground power check RESULTS page for engine 2 – example
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Fig. 5-2
When T1 is shown in _F, temperatures > 99.9_F will not be indicated.
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FLIGHT
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The results from the last 8 power checks can be viewed by pressing EXIT and then HIST. 2) NO EPC RESULTS AVAILABLE is shown –
APPROVED Rev. 6
Repeat the power check (wait at least 3 seconds, then press RUN), maintaining the collective steady. If the power check fails again, perform a manual ground power check (see 5.1.5.5).
5–5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.5.4 Automatic in-flight power check To obtain correct check results, the following preconditions must be established: – Level flight in steady conditions. A power check in strong turbulence shall be avoided. – Bleed air heating OFF. – Generator loads reduced (no high power consumers switched on).
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– The bleed valves should have the same position (both closed or both open). If the bleed valves are mismatched, change altitude to match the bleed valves.
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The automatic in-flight power check procedure (Fig. 5-3) shall be carried out:
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– In level flight > Vy, and
POWER
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ENGINE/TRANSMISSION CONTINUOUS SECTION 2 ARE NOT TO BE EXCEEDED.
LIMITATIONS
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CAUTION
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– Under AEO engine operating conditions.
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To perform the power check, the aircraft shall be in level forward flight. As the procedure takes two minutes to complete, a flight segment, preferabely in calm air, with no heading /altitude changes for two minutes shall be selected. The power check is performed on both engines simultaneously. During the power check, both engines are fully operative.
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3. Master List
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2. Steady level flight
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4. VMS page
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5. Collective lever
6. VMS page / EPC area
5–6
– Establish (> 500 ft ground) – Establish (> Vy) – Check no FADEC related alerts – Select, press EPC – Set power to 2x70% torque – If AEO MCP is reached at less than 70% torque, set collective at MCP – AFCS ALT mode can be used to maintain a steady altitude, if desired – Check all conditions are correct and correctly established (no amber labels)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
7. Clock
– Start – Maintain 70% torque for 2 minutes
8. VMS page / EPC area
– Press RUN key – COMPUTING DATA appears – EPC appears in the FLI – Do not move collective until progress bar is filled
ED
– The power check result appears If the autopilot was in 4-axis mode before the power check, the AFCS will automatically revert to 3-axis mode when the power check is started (RUN is pressed).
N TR
O
LL
NOTE
O
Interpreting the results of the automatic in-flight power check:
T
C
1) RESULTS page is shown
C
O
PY
N
O
The results shown on the VMS page /EPC area are shown as in the example of Fig 5-3. The mean parameter values recorded during the check are shown on the left. The power check results (margins) are shown on the right. The margins are given in torque at ISO-TOT and in torque at ISO-N1. If both margins (TOT and N1) are zero or positive (green), the engine power is assured and the performances in the flight manual are achievable. A performance surplus cannot be calculated from the margins.
–
If one or both torque margins are negative (amber), the test is failed and maintenance is required.
TI
O N
O N
LY
–
–
U
C
To access the results of engine 1, press NXT.
390 IN–FLIGHT POWER CHECK RESULTS ENGINE1 MEAN VALUES: MARGINS: N1 : 90.5 % TRQ ISO–TOT : 6.8 % N2 : 98.9 % TRQ ISO–N1 : 7.7 % TRQ : 69.6 % TOT : 731 _C P0 : 852.9 hPa T1 : 11.3 _C
BKD2_FLH_0074_R
FO
R
IN
ST
R
FLIGHT
N X T
Fig. 5-3 NOTE
PREV
STATUS
E X I T
WEIGHT
Automatic in-flight power check RESULTS page for engine 1 – example When T1 is shown in _F, temperatures > 99.9_F will not be indicated.
To access the results of engine 2, press NXT. The results from the last 8 power checks can be viewed by pressing EXIT and then HIST. APPROVED Rev. 6
5–7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
2) NO EPC RESULTS AVAILABLE is shown –
Repeat the power check (wait at least 3 seconds, then press RUN), maintaining the collective steady. If the power check fails again, perform an automatic ground power check (see 5.1.4.3).
5.1.5.5 Manual ground power check The manual ground power check is to be used only in case an automatic power check is not possible.
ED
To obtain correct check results, the following preconditions must be established:
LL
– Adequate distance from buildings, trees, etc. to reduce possibility of wind vortices.
N TR
– Bleed air heating OFF.
O
– Helicopter heading into wind. Maximum wind speed 10 kt.
O
The manual ground power check procedure shall be carried out:
T
C
– On the ground, and
N
O
– Under single engine operating condition (second engine at IDLE)
O
PY
CAUTION D ENGINE/TRANSMISSION CONTINUOUS POWER LIMITATIONS IN SECTION 2 ARE NOT TO BE EXCEEDED.
O N
LY
–
C
D DURING THE POWER CHECK, THE PILOT SHALL REMAIN VIGILANT AS THE AIRCRAFT MAY BECOME LIGHT ON SKIDS DURING THE CHECK. FOR THIS REASON, POWER CHECKS WITH A VERY LIGHT AIRCRAFT SHALL BE AVOIDED.
O N
It is recommended to switch off the AFCS during the power check. Mast moment limits could be infringed as the AFCS tries to maintain the helicopter attitude when increasing the collective and the helicopter gets light on skids.
U
C
TI
NOTE
R
IN
ST
R
To perform the power check, the standard start-up procedure (refer to section 4) shall be used. Both engines are in IDLE at the start of the procedure. The power check should be performed on each engine, in sequence, using the same procedure.
1. 2. 3. 4. 5. 6. 7. 8.
FO
Proceed as follows: Collective lever BARO setting Pressure altitude Master List
– – – –
Full down Select STD Record Check no FADEC related alerts
VMS page Affected ENG MAIN switch Affected engine GEN switch Collective lever
– – – –
Select FLIGHT OFF Slowly increase to 70% torque
NOTE
5–8
While increasing the collective, the power split audio tone will sound above 2 FLI. APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
9. Clock
– Start – Maintain 70% torque steady for 2 minutes
After 2 minutes: – Maintain 70% torque steady – Record OAT – Record N1 – Record TOT
O
LL
Slowly decrease to flat pitch IDLE RESET, then NORM Set as required
N TR
– – – –
T
C
O
10. Collective lever 11. Affected ENG MAIN switch 12. Affected engine GEN switch 13. BARO setting Repeat for other engine, if desired.
ED
– Record bleed valve condition (open = /// symbol present)
N
O
To determine the result of the power check, proceed as follows:
C
–
O N
–
If the TOT recorded during the power check is equal or less than the TOT obtained from the chart, the engine power is assured. If the TOT recorded during the power check is higher than the TOT obtained from the chart, the engine power check has failed and maintenance is required.
LY
–
O
PY
Select the TOT power check chart (fig 5-4 or 5-5) based on the engine (1 or 2). Using the chart, read the maximum TOT corresponding to the recorded ambient conditions
C
If the N1 recorded during the power check is equal or less than the N1 obtained from the chart, the engine power is assured. If the N1 recorded during the power check is higer than the N1 obtained from the chart, the engine power check has failed and maintenance is required.
ST
IN
–
R
U
–
TI
O N
Select the N1 power check chart (fig 5-6, 5-7, 5-8 or 5-9) based on the engine (1 or 2) and the bleed valve position (open or closed). Using the chart, read the maximum N1 corresponding to the recorded ambient conditions.
FO
R
NOTE
APPROVED Rev. 6
Power margins obtained from the automatic power check and the manual ground power check are given in different metrics. Therefore, the results cannot be compared to each other.
5–9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
EXAMPLE:
(see Fig. 5-4)
Determine:
TOT margin
Known:
Pressure altitude
1600 ft
OAT
4 °C
Indicated TOT
670 °C
TOT margin from average trend line: 40 °C (see power trend monitoring)
ED
TOT margin = 365C
Solution:
LL
1. Enter chart at known OAT (4 °C)
O
2. Move vertically upwards to known pressure altitude (1600 ft)
N TR
3. Move horizontally left and read chart limit TOT = 706°C
C
O
4. The TOT margin = chart limit TOT (706°C ) – indicated TOT (670 °C) = 36 °C
PY
N
O
T
In the example above, the TOT margin is 36 °C. Since the TOT margin from the average power trend line is 40 °C, TOT margin drop down (4 °C) is permissible. The conditions for an acceptable power check are satisfied.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
A continuous power trend monitoring procedure is given in paragraph 5.1.4.6.
5 – 10
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MANUAL GROUND POWER CHECK (TOT) ENG1 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF
910 890
ED
870
LL
850
N TR
O
830
C
O
810
O
T
790
N PY C
O
750
–
730
LY
TOT – _C
770
O N
O N
710
TI
690
U R ST
IN
650
C
670
FO
R
630 610
ARR2E_GPC_LH_T4
590 570 550 –40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 5-4 APPROVED Rev. 6
Manual ground power check (TOT) for engine No.1 and 70% torque
5 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MANUAL GROUND POWER CHECK (TOT) ENG2 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF
910 890
ED
870
LL
850
N TR
O
830
C
O
810
O
T
790
N PY C
O
750
–
730
LY
TOT – _C
770
O N
O N
710
TI
690
R
U
C
670
IN R
FO
630
ST
650
610
ARR2E_GPC_RH_T4
590 570 550 –40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 5-5
5 – 12
Manual ground power check (TOT) for engine No.2and 70% torque APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MANUAL GROUND POWER CHECK (N1) ENG1 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF
BLEED VALVE OPEN 100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
T
C
O
95.0
N
O
94.0
O
PY
93.0
C – LY
91.0
O N
N1 – %
92.0
O N
90.0
U
C
TI
89.0
ST
R
IN
87.0
R
88.0
FO
86.0
ARR2E_GPC_LH_N1_BVO
85.0 84.0 83.0 82.0 –40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 5-6
APPROVED Rev. 6
Manual ground power check (N1) for engine No.1and 70% torque, bleed valve open
5 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MANUAL GROUND POWER CHECK (N1) ENG2 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF
BLEED VALVE OPEN
100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
C
O
95.0
N
O
T
94.0
O
PY
93.0
C – LY
91.0
O N
N1 – %
92.0
O N
90.0
C
TI
89.0
IN
87.0
ST
R
U
88.0
FO
R
86.0
ARR2E_GPC_RH_N1_BVO
85.0 84.0 83.0 82.0
–40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 5-7
5 – 14
Manual ground power check (N1) for engine No.2 and 70% torque, bleed valve open APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MANUAL GROUND POWER CHECK (N1) ENG1 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF
BLEED VALVE CLOSED
100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
C
O
95.0
N
O
T
94.0
O
PY
93.0
C – LY
91.0
O N
N1 – %
92.0
O N
90.0
C
TI
89.0
IN
87.0
ST
R
U
88.0
FO
R
86.0
ARR2E_GPC_LH_N1_BVC
85.0 84.0 83.0 82.0 –40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 5-8
APPROVED Rev. 6
Manual ground power check (N1) for engine No.1 and 70% torque, bleed valve closed
5 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MANUAL GROUND POWER CHECK (N1) ENG2 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF
BLEED VALVE CLOSED
100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
C
O
95.0
N
O
T
94.0
O
PY
93.0
C – LY
91.0
O N
N1 – %
92.0
O N
90.0
C
TI
89.0
ST
R
U
88.0
IN
87.0
FO
R
86.0
ARR2E_GPC_RH_N1_BVC
85.0 84.0 83.0 82.0
–40
Fig. 5-9
5 – 16
–30
–20
–10
0
OAT – °C
10
20
30
40
50
Manual ground power check (N1) for engine No.2 and 70% torque, bleed valve closed APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.5.6 Power trend monitoring Power trend monitoring should be established to observe the deterioration of the engines with time in service as well as potential engine malfunctions or sudden degradations. Although the results from both the ground or inflight power checks can be used for establishing a power trend chart, it is recommended to perform either always ground or always inflight power checks. NOTE
The power check preconditions and the power check procedure have to be followed very accurately, otherwise the trend monitoring will not be reliable.
O
N TR
O
LL
ED
Two power trend charts must be established, one for TOT and one for N1. If the automatic power check is used, the TRQ margins shown on the EPC RESULTS page shall be recorded versus time in service. If the manual power check is used, the TOT and N1 margins (defined as chart TOT minus measured TOT, respectively chart N1 minus measured N1) shall be recorded versus time in service.
– LY O N O N
Drop Down > 5%
Time
Plotting example for power trend monitoring
TI
Fig. 5-10
–5%
0% TRQ Margin ISO–N1 (%) Power check unacceptable
C
BKD2_FLH_0150_R
O
PY
N
O
T
C
Average trend
TRQ Margin ISO–N1 (%)
FO
R
IN
ST
R
U
C
For each engine, establish average trend lines for TOT and N1 margins based on the most recent consecutive 5 data points. If the automatic power check is used, the maximum permissible margin drop down between a single power check result and the average trend line is 5% TRQ for both ISO–TOT and ISO–N1. If the manual power check is used, the maximum permissible margin drop down between a single power check result and the average trend line is 15°C for TOT and 1% for N1. If any margin drop is greater, abnormal function of the engine or engine instrumentation should be assumed and maintenance action in accordance with the maintenance manual is highly recommended.
APPROVED Rev. 6
5 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.6
Density altitude The density altitude chart (Fig. 5-11) expresses density altitude in terms of pressure altitude and temperature. The less dense the air the higher the density altitude. For standard conditions of temperature and pressure, density altitude is identical to pressure altitude. A high density altitude affects the performance of both the main rotor and the engine. When density altitude is high, less lift is developed by the rotor blades for any given power setting than at standard conditions and the power output of the engine is reduced below the output for standard conditions.
ED
Each takeoff and landing must be separately evaluated as density altitude may change considerably in a short period of time. 1
PY
N
O
T
C
O
N TR
O
LL
The value √σ is a conversion factor used to obtain true airspeed from calibrated airspeed by correcting for density altitude.
(see Fig. 5-11)
Determine:
Density altitude (DA), true airspeed factor, and true airspeed (TAS)
Known:
OAT
O N
LY
–
C
O
EXAMPLE:
– 14°C 5000 ft
CAS
100 kts
C
TI
O N
Pressure altitude
R
U
Solution:
ST
1. Enter chart at known OAT (– 14°C)
IN
2. Move vertically upwards to known pressure altitude (5000 ft)
FO
R
3. Move horizontally left and read density altitude = 2700 ft 4. Move horizontally right and read true airspeed factor = 1.04 5. Multiply the known calibrated airspeed (100 kts) by true airspeed factor (
1 √σ
= 1.04) to obtain true airspeed.
6. TAS = CAS x
5 – 18
1 √σ
= 100 x 1.04 =104 knots
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
BK2B-5DACHART,0
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
DENSITY ALTITUDE – ft
N
O
T
C
TRUE AIRSPEED FACTOR – 1/pσ
O
N TR
O
LL
ED
DENSITY ALTITUDE CHART
OUTSIDE AIR TEMPERATURE – °C
Fig. 5-11 APPROVED Rev. 6
Density altitude chart
5 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.7
Airspeed system calibration The pilot’s and copilot’s airspeed system calibration charts (Fig. 5-12 and 5-13) provide information for determining CAS from IAS or vice versa. The charts are provided to show the necessary position error correction for level flight, climb flight and autorotation flight. The correction is applicable at all practical altitudes and helicopter masses. The correction applies only when the helicopter is flown with no appreciable side slip.
PY
N
O
T
C
O
N TR
O
LL
ED
NOTE
(see Fig. 5-12)
Determine:
Calibrated airspeed (CAS)
Known:
Level flight
O N
LY
–
C
O
EXAMPLE:
O N
Indicated airspeed (IAS) (pilot’s system) = 80 KIAS
TI
Solution:
U
C
1. Enter chart at known indicated airspeed (80 KIAS)
R
2. Move vertically upwards to level flight line
FO
R
IN
ST
3. Move horizontally left and read calibrated airspeed = 79 KCAS
5 – 20
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
AIRSPEED SYSTEM CALIBRATION PILOT’S SYSTEM TURBOMECA ARRIEL 2E
CLEAN CONFIGURATION INDICATED AIRSPEED ASSUMES ZERO INSTRUMENT ERROR
ED
NOTE
LL
160
O N TR C
O
120
O
T
100
PY
N
80
C
O
60
LY
–
40
Climb
O N
O N
20
Level Flight
0 20
40
TI
0
60 80 100 INDICATED AIRSPEED – KNOTS (KIAS)
Autorotation 120
140
160
FO
R
IN
ST
R
U
C
BKD2_FLH_0515_R
CALIBRATED AIRSPEED – KNOTS (KIAS)
140
Fig. 5-12
APPROVED Rev. 6
Airspeed system calibration (pilot)
5 – 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
AIRSPEED SYSTEM CALIBRATION COPILOT’S SYSTEM TURBOMECA ARRIEL 2E
CLEAN CONFIGURATION INDICATED AIRSPEED ASSUMES ZERO INSTRUMENT ERROR
ED
NOTE
N TR
O
LL
160
T
C
O
120
N
O
100
O
PY
80
–
C
60
LY
40
O N
Level Flight Climb Autorotation
O N
20
20
40
C
0
TI
0
60 80 100 INDICATED AIRSPEED – KNOTS (KIAS)
120
140
160
FO
R
IN
ST
R
U
BKD2_FLH_0516_R
CALIBRATED AIRSPEED – KNOTS (KIAS)
140
Fig. 5-13
5 – 22
Airspeed system calibration (copilot)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.8
Static system correction
5.1.8.1 Normal static system altitude correction With the altimeter connected to the normal static, the altimeter pressure error does not exceed 25 ft for any airspeed in level flight, climb or descent. 5.1.8.2 Alternate static system altitude and airspeed correction
LL
Add DPA to indicated altitude to obtain calibrated altitude.
Continued
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
NOTE
ED
When the altimeter is connected to the cabin static and the pilot’s window is closed, significant errors are introduced. The corrections which apply to indicated altitude and airspeed in order to obtain true altitude and calibrated airspeed are shown on the following table (Table 5-1) for level flight.
APPROVED Rev. 6
5 – 23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
(see Table 5-1)
Determine:
Calibrated airspeed and true altitude
Known:
Indicated pressure altitude
1000 ft
Indicated airspeed
70 kts
Bleed air heating
ON 100 %
Ventilation
ON 50 %
Pilot’s window
CLOSED
NACA
OPEN
N TR
O
LL
EXAMPLE:
ED
PERFORMANCE DATA
CAS = 87 kts
Solution:
N
O
T
C
O
True altitute is 1000 ft + 100 ft = 1100 ft
IAS (kts)
O
NACA
50
70
90
110
130
140
150
CAS (kts)
54
77
98
116
131
138
144
D PA (ft)
10
50
65
55
20
–10
–40
CAS (kts)
68
87
105
122
139
146
154
D PA (ft)
65
100
120
120
100
85
65
CAS (kts)
64
84
103
120
137
144
152
D PA (ft)
40
75
95
105
110
100
100
CAS (kts)
49
67
85
103
120
130
138
D PA (ft)
–25
–40
–65
–95
–135 –160 –180
C
VENTILATION
–
BLEED AIR HTG
ON 50%
CLOSED
O N
ON 100%
OPEN
ST
R
U
ON 50%
OPEN
OFF
FO
CLOSED
R
IN
CLOSED
ON 100%
C
TI
CLOSED
O N
LY
PILOT’S WINDOW
PY
ALTERNATE STATIC SYSTEM CORRECTION
OFF
ON 100%
ON 100%
OPEN
OPEN
– ADD DPA TO INDICATED PRESSURE ALTITUDE TO OBTAIN CALIBRATED PRESSURE ALTITUDE. – COPILOT’S WINDOW CLOSED.
Table 5-1
5 – 24
Alternate static system correction APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.9
Height–velocity envelope The height-velocity envelope shown in the height-velocity diagram (Fig. 5-14) is the combination of indicated airspeed and height above ground as a function of gross mass, pressure altitude and outside air temperature. The diagram shows the area which is critical for helicopter operation in the event of a single engine failure during takeoff, landing or other operations near the ground.
ED
The curves are applicable for landing sites with smooth firm surfaces and define the conditions in which a safe landing can be made after an engine suddenly becomes inoperative.
N TR
O
LL
NOTE D The height–velocity diagram is applicable only if the aircraft weight is achievable in hover out of ground effect for the given altitude and temperature (see section 5.1.10).
N
O
T
C
O
D The lowest reference point P (”high hover” point) achievable in the chart is 100 ft (shaded area in Fig. 5-14). Safe landing from any point within the shaded area is guaranteed only if the calculation shows no H–V area for the given weight–altitude–temperature combination.
C
O
PY
D The data presented in the height-velocity diagram (Fig. 5-14) for density altitudes above 13000 ft have been established by theoretical analysis only.
O N
LY
–
D To determine the airspeed to be used in the height-velocity diagram, the indicated airspeed shall be used above 25 KIAS. Below 25 KIAS, a combination of forward groundspeed and factored headwind (= 50% of the reported wind) may be used.
O N
EXAMPLE 1 (see Fig. 5-14):
R
U
C
TI
The critical height-velocity area which should be avoided, can be defined by first determining point P, a point on the requested boundary curve. Critical height-velocity curve
IN
ST
Determine:
FO
R
Known:
OAT
14 °C
Pressure altitude
6000 ft
Gross mass
3600 kg
Solution: 1. Enter chart at known OAT (14 °C) 2. Move vertically upwards to known pressure altitude (6000 ft) 3. Move horizontally right to known gross mass (3600kg) 4. Move vertically downwards to intersect the reference line 5. From intersection with reference line move horizontally left and read height above ground for point P = 160 ft 6. Draw the boundary curve through point P by interpolating between the existing curves on the chart APPROVED Rev. 6
5 – 25
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
EXAMPLE 2 (see Fig. 5-14): Determine:
Critical height-velocity curve
Known:
OAT
14 °C
Pressure altitude
6000 ft
Gross mass
3250 kg
Solution: 1. Enter chart at known OAT (14 °C)
LL
O
3. Move horizontally right to known gross mass (3250kg)
ED
2. Move vertically upwards to known pressure altitude (6000 ft)
N TR
4. Move vertically downwards to intersect the reference line
O
5. From intersection with reference line move horizontally left and read height above ground for point P = 100 ft
PY
N
O
T
C
6. Use the boundary curve through point P = 100 ft
C
O
EXAMPLE 3 (see Fig. 5-14):
Critical height-velocity curve
Known:
OAT
LY
–
Determine:
O N
14 °C
O N
Pressure altitude
3200 kg
TI
Gross mass
6000 ft
U
C
Solution:
ST
R
1. Enter chart at known OAT (14 °C)
IN
2. Move vertically upwards to known pressure altitude (6000 ft)
FO
R
3. Move horizontally right to known gross mass (3200kg)
5 – 26
4. No interception possible, no H–V area exists for the given gross mass
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
HEIGHT-VELOCITY DIAGRAM MAX. DENSITY ALTITUDE 20000 ft
10 20 30 40 50
N TR O C
PY
–50 –40 –30 –20 –10 0
C
O
320
–
300
LY
280
O N
260
O N
240
TI U
C
200
IN
P
ST
R
180
R
140 120
FO
SKID HEIGHT – ft AGL
220
160
N
O
T
NO H–V AREA
O
LL
ED
16000 ft
100
80
BK117D2038_1_r2
60 40 20 0 0
10
20
30
40
AIRSPEED – kt
Fig. 5-14 APPROVED Rev. 6
Height-velocity diagram
5 – 27
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.10
Hover ceiling - AEO Performance The hover ceiling charts for hover in ground effect (HIGE) (Fig.5-15 to 5-18) are provided for AEO conditions, with takeoff power (TOP) and maximum continuous power (MCP) and various combinations of pressure altitude, outside air temperature and gross mass. At the maximum aircraft weight shown in the HIGE performance charts, controllability for hover in ground effect was demonstrated with the following wind speeds: – Up to 16000 ft density altitude . . . . . . . . . . . . . . . . . . . . . . up to 30 kts from all directions – Above 16000 ft density altitude . . . . . . . . . . . up to 17 kts from the right, 30 kts from all other directions
LL
ED
Controllability during standard type takeoff and landing has been demonstrated for flight conditions with crosswind components up to 17 kts.
C
O
N TR
O
The hover ceiling charts for hover out of ground effect (HOGE) (Fig.5-19 to 5-22) are provided for AEO conditions, with takeoff power (TOP) and maximum continuous power (MCP), and various combinations of pressure altitude, outside air temperature and gross mass.
N
O
T
At the maximum aircraft weight shown in the HOGE performance charts, controllability for hover out of ground effect was demonstrated with the following wind speeds:
PY
– Up to 16000 ft density altitude . . . . . . . . . . . . . . . . . . . . . . up to 30 kts from all directions
–
C
O
– Above 16000 ft density altitude . . . . . . . . . . . up to 17 kts from the right, 30 kts from all other directions The term “heating” is used for bleed air heating and electrical heater.
O N
LY
NOTE
(based on Fig. 5-15)
Determine:
Maximum gross mass for hover in ground effect
Known:
OAT
ST
R
U
C
TI
O N
EXAMPLE:
FO
R
Solution:
13000 ft
IN
Pressure altitude
4°C
1. Enter chart at known OAT (4°C)
2. Move upwards to known pressure altitude (13000 ft) 3. Move horizontally left and read maximum takeoff and landing gross mass = 3450 kg
5 – 28
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
HOVER CEILING IN GROUND EFFECT 2 X TURBOMECA ARRIEL 2E TAKEOFF POWER
ZERO WIND OR HEADWIND OR CROSSWIND HEATING OFF
2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
LL
ED
2400
N TR
O
2500
N
O
T
2700
C
MAX. DENSITY ALTITUDE 20000 FT
O
2600
MAX. OAT
LY
–
C
MIN. OAT
2900
O N
3000
O N
3100
TI
GROSS MASS – kg
O
PY
2800
ST
IN
3300
R
U
C
3200
FO
R
3400
3500
BK117D2001_1_r2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 5-15 APPROVED Rev. 6
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (AEO, TOP, heating off)
5 – 29
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
HOVER CEILING IN GROUND EFFECT 2 X TURBOMECA ARRIEL 2E TAKEOFF POWER
ZERO WIND OR HEADWIND OR CROSSWIND HEATING ON
2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
ED
2400
N TR
O
LL
2500
2600
C
O
MAX. DENSITY ALTITUDE 20000 FT
N
O
T
2700
MAX. OAT
–
C
O
MIN. OAT
O N
LY
3000
O N
3100
TI
GROSS MASS – kg
2900
PY
2800
R
U
C
3200
IN
FO
R
3400
ST
3300
3500
BK117D2001_11_r2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
–40
Fig. 5-16
5 – 30
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (AEO, TOP, heating on) APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
HOVER CEILING IN GROUND EFFECT 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
ZERO WIND OR HEADWIND OR CROSSWIND HEATING OFF
2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
2400
2500
N TR
O
16000
LL
ED
MAX. DENSITY ALTITUDE 20000 FT
O
2600
O
T
C
2700
MAX. OAT
PY –
C
O
MIN. OAT
O N
LY
3000
3100
O N
GROSS MASS – kg
2900
N
2800
U
C
TI
3200
IN
ST
R
3300
FO
R
3400
3500
BK117D2002_1_r2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
–40
Fig. 5-17 APPROVED Rev. 6
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (AEO, MCP, heating off)
5 – 31
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
HOVER CEILING IN GROUND EFFECT 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
ZERO WIND OR HEADWIND OR CROSSWIND HEATING ON
2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
2400
ED
MAX. DENSITY ALTITUDE 20000 FT
2600
N TR
O
LL
2500
O
16000
O
T
C
2700
MAX. OAT
PY –
C
O
MIN. OAT
O N
LY
3000
O N
3100
TI
GROSS MASS – kg
2900
N
2800
R
U
C
3200
IN
ST
3300
3600
2000
BK117D2002_11_r2
3500
FO
R
3400
1000 3700 GROSS MASS LIMIT 3700 KG 3800 –50
–40
Fig. 5-18
5 – 32
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (AEO, MCP, heating on) APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E TAKEOFF POWER
ZERO WIND OR HEADWIND OR CROSSWIND HEATING OFF
2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
O
MAX. DENSITY ALTITUDE 20000 FT
N TR
2500
LL
ED
2400
C
O
2600
N
O
T
2700
MAX. OAT
–
C
O
MIN. OAT
2900
O N
LY
3000
O N
3100
TI
GROSS MASS – kg
PY
2800
R
U
C
3200
IN
ST
3300
FO
R
3400
3500
BK117D2005_1_r2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 5-19 APPROVED Rev. 6
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, TOP, heating off)
5 – 33
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E TAKEOFF POWER
ZERO WIND OR HEADWIND OR CROSSWIND HEATING ON
2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
2400
ED
MAX. DENSITY ALTITUDE 20000 FT
N TR
O
LL
2500
O
2600
O
T
C
2700
MAX. OAT
PY –
C
O
MIN. OAT
O N
LY
3000
3100
O N
GROSS MASS – kg
2900
N
2800
U
C
TI
3200
FO
R
3400
IN
ST
R
3300
3500
BK117D2005_11_r2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
–40
Fig. 5-20
5 – 34
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, TOP, heating on) APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
ZERO WIND, HEADWIND AND CROSSWIND HEATING OFF
2200 MAX. DENSITY ALTITUDE 20000 FT
2300
16000
LL
ED
2400
N TR
O
2500
C
O
2600
N
O
T
2700
MAX. OAT
–
C
O
MIN. OAT
O N
LY
3000
O N
3100
TI
GROSS MASS – kg
2900
PY
2800
IN
ST
3300
R
U
C
3200
FO
R
3400
3500
For altitude/oat combinations not shown,
3600
BK117D2006_1_r2
the GROSS MASS LIMIT line is applicable 3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 5-21 APPROVED Rev. 6
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, MCP, heating off)
5 – 35
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
ZERO WIND OR HEADWIND OR CROSSWIND HEATING ON
2200 MAX. DENSITY ALTITUDE 20000 FT
2300
2400
LL
ED
16000
N TR
O
2500
C
O
2600
N
O
T
2700
MAX. OAT
O LY
–
C
MIN. OAT
O N
3000
O N
3100
TI
GROSS MASS – kg
2900
PY
2800
R
U
C
3200
IN R
FO
3400
ST
3300
3500
For altitude/oat combinations not shown,
3600
BK117D2006_11_r2
the GROSS MASS LIMIT line is applicable 3700 GROSS MASS LIMIT 3700 KG 3800 –50
–40
Fig. 5-22
5 – 36
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, MCP, heating on) APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.11
Hover ceiling in ground effect - OEI Performance For specific operations OEI – HIGE capability may be required and shall be performed in accordance with national operational rules.
5.1.11.1 Bleed air consumers Bleed air heating and other bleed air consumption is not permitted during operation which requires OEI–hover. 5.1.11.2 Performance data
ED
Maximum gross mass to ensure OEI-HIGE capability:
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
The maximum gross mass is limited by the OEI–hover chart (see Fig. 5-23, Fig. 5-24).
APPROVED Rev. 6
5 – 37
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
TU206 NOT installed
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
HOVER CEILING IN GROUND EFFECT 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN. POWER
ZERO WIND OR HEADWIND HEATING OFF
2000
LL
ED
2100
N TR
O
2200
O
2300
T
C
2400
N
O
2500
O
PY
2600
O N O N
2900
MAX. OAT
LY
2800
MIN. OAT
TI
3000
C
GROSS MASS – kg
–
C
2700
ST
R
U
3100
IN
3200
FO
3400
R
3300
3500
3700 3800
Fig. 5-23
5 – 38
BK117D2009_1_r1
3600
GROSS MASS LIMIT 3700 KG
–50
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (OEI, 2 min power, without TU206, heating off) APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
TU206 installed
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
HOVER CEILING IN GROUND EFFECT 1 X TURBOMECA ARRIEL 2E (WITH TU206) 2 MIN. POWER
ZERO WIND OR HEADWIND HEATING OFF
ED
2000
LL
2100
N TR
O
2200
O
2300
T
C
2400
N
O
2500
O
PY
2600
C LY O N O N
2900
TI
3000
ST
R
U
C
3100 3200
MAX. OAT
–
2800
MIN. OAT
GROSS MASS – kg
2700
FO
R
IN
3300 3400 3500
3700 3800
Fig. 5-24 EFFECTIVITY APPROVED Rev. 6
BK117D2009_1_r2
3600
GROSS MASS LIMIT 3700 KG –50
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (OEI, 2 min power, with TU206, heating off) All
5 – 39
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.12
Hover ceiling out of ground effect - OEI Performance For specific operations OEI–HOGE capability may be required and shall be performed in accordance with national operational rules.
5.1.12.1 Bleed air consumers Bleed air heating and other bleed air consumption is not permitted during operation which requires OEI-hover. 5.1.12.2 Performance data
ED
Maximum gross mass to ensure OEI-HOGE capability:
LL
The maximum gross mass is limited by the OEI–hover chart (see Fig. 5-25 to Fig. 5-27).
T
O
OEI-HOGE performance with vertical R/C reserve:
C
O
N TR
O
In order to achieve and remain at the maximum rated torque value a slight rotor speed droop is required at the OEI 30sec / 2min power limitations. The HOGE OEI 30sec chart has been established for nominal rotor speed minus 3% and the HOGE OEI 2min chart for nominal rotor speed minus 1%. Higher rotor speed droop will result in a slight rate of descent.
– LY
C
TI
150
O N
50 100
n Gross Mass
O N
Vertical climb reserve [ft / min]
C
O
PY
N
Specific operations may require an additional vertical R/C reserve to the OEI–HOGE. The following gross mass values have to be subtracted from the derived gross mass of Fig. 5-25 to Fig. 5-27, :
– 25 – 45 – 70 – 90
R
U
200
[kg]
ST
Wind credit chart
FO
R
IN
The wind credit chart is valid for headwind components. Operations with tailwind components should be avoided. Wind accountability in Fig.5-25 to Fig.5-27 is UNFACTORED. NOTE
5 – 40
Unless otherwise authorized by operating regulations, the pilot is not authorized to credit more than the performance increase resulting from 50% of the actual headwind component.
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
EXAMPLE:
(see Figure 5-25)
Determine:
Maximum gross mass for OEI-HOGE (2 min power)
Known:
OAT
+15 °C
Pressure altitude
0 ft (SL)
Windspeed
16 kt
Bleed air consumers
OFF
For calculation: 50% headwind
ED LL O
Maximum gross mass = 3115 kg
N TR
Solution:
8 kt
O
1. Enter chart at known OAT (+15°C).
C
2. Move upwards to known pressure altitude (0 ft)
N
O
T
3. From point of intersection move horizontally right to the reference line of the wind credit chart.
PY
4. From this point follow the direction of the wind credit guide lines.
C
O
5. Enter chart at known windspeed (8 kt)
LY
–
6. Move vertically upwards to intersect tracing from above.
O N
7. From point of intersection move horizontally right and read max. gross mass = 3115 kg
FO
R
IN
ST
R
U
C
TI
O N
(Using the example on the assumption of no wind, the solution is 3065kg)
APPROVED Rev. 6
5 – 41
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
EFFECTIVITY
OEI
OEI
TU206 NOT installed
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
HOVER CEILING OUT OF GROUND EFFECT 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN. POWER
ZERO WIND OR HEADWIND HEATING OFF 2000
2200
N TR
O
LL
ED
2100
O
2300
T
C
2400
N
O
2500
O
PY
2600
2900
TI
3000
GROSS MASS – kg
MAX. OAT
2800
O N
O N
LY
–
MIN. OAT
C
2700
R
U
C
3100
ST
3200
R
IN
3300
FO
3400
REFERENCE LINE
3500
–50
–40
–30
–20
–10
0
10
20
30
40
50
60 0
3700
10
20
3800 30 [kt]
BK117D2008_1_r1
GROSS MASS LIMIT 3700 KG
3600
0 10 20 30 40 50 60 [km/h] HEADWIND
Fig. 5-25
5 – 42
Hover ceiling out off ground effect (OEI, 2 min power, without TU206, heating off) APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
EFFECTIVITY
OEI
OEI
TU206 installed
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
HOVER CEILING OUT OF GROUND EFFECT 1 X TURBOMECA ARRIEL 2E (WITH TU206) 2 MIN. POWER
ZERO WIND OR HEADWIND HEATING OFF 2000
O
LL
ED
2100 2200
N TR
2300
C
O
2400
O
T
2500
2800 2900
O N
3000
GROSS MASS – kg
MAX. OAT
2700
O N
LY
–
C
MIN. OAT
O
PY
N
2600
C
TI
3100
ST
R
U
3200
IN
3300
FO
R
3400
GROSS MASS LIMIT 3700 KG –50
–40
–30
–20
–10
0
10
20
30
40
50
60 0
3600 3700
10
20
3800 30 [kt]
BK117D2008_1_r2_TQ
REFERENCE LINE
3500
0 10 20 30 40 50 60 [km/h] HEADWIND
Fig. 5-26 EFFECTIVITY APPROVED Rev. 6
Hover ceiling out off ground effect (OEI, 2 min power, with TU206, heating off) All
5 – 43
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
HOVER CEILING OUT OF GROUND EFFECT 1 X TURBOMECA ARRIEL 2E 30 SEC POWER
ZERO WIND OR HEADWIND HEATING OFF 2000
20000
ED
2100
N TR
O
LL
2200 2300
O
2400
T
C
2500
2800 2900
O N
3000
GROSS MASS – kg
MAX. OAT
2700
O N
LY
–
C
MIN. OAT
O
PY
N
O
2600
C
TI
3100
R
U
3200
IN
ST
3300
FO
R
3400
REFERENCE LINE
3500
–50
–40
–30
–20
–10
0
10
20
30
40
50
60 0
3700
10
20
3800 30 [kt]
BK117D2007_1_r2
GROSS MASS LIMIT 3700 KG
3600
0 10 20 30 40 50 60 [km/h] HEADWIND
Fig. 5-27
5 – 44
Hover ceiling out off ground effect (OEI, 30 sec power, heating off) APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.13
Takeoff distance from hover to 50 feet height The takeoff distance chart (Fig. 5-29) provides takeoff performance data utilizing a takeoff profile as shown in Fig. 5-28. The chart is provided for preflight planning to compute the takeoff distance to a height of 50 feet at various combinations of gross mass, pressure altitude, outside air temperature and headwind. The takeoff distance to a height of 50 feet is presented in Fig. 5-29.
O
LL
ED
If an engine failure occurs during takeoff, continued takeoff and climbout capability is NOT assured (FAR 29, category B provisions). The category B takeoff profile (Fig. 5-28) assures the capability to land safely (on a smooth level surface) from any point in the takeoff profile should an engine failure occur.
ACCELERATE TO AND CLIMB WITH VY
T
C
O
N TR
TAKEOFF POWER AS REQUIRED
PY AIM TO ACHIEVE 50 KIAS AT 50 ft
ST
O N
R
U
C
TI
HIGE AT 4 ft SKID HEIGHT
IN
BKD2_FLH_0158_R
O N
INCREASE POWER SMOOTHLY (0.5 – 1.0 FLI)
LY
–
C
O
30 KIAS 15 ft HEIGHT
N
O
ACCELERATE TO VY
TAKEOFF DISTANCE
Fig. 5-28
Takeoff profile (category B)
FO
R
To achieve values given in the chart, proceed as follows: 1. Hover flight with 4ft skid height
– Perform
2. Acceleration and climb
– Start nose down pitch rotation and simultaneously increase power smoothly (use hover power plus 0.5 – 1.0 FLI, without exceeding TOP) for acceleration. Adjust pitch attitude at about 20 KIAS to achieve 30 KIAS at 15 ft height.
3. When reaching 50 KIAS
– Maintain airspeed until reaching 50 ft AGL, then accelerate to VY and climb through 100 ft AGL.
APPROVED Rev. 6
5 – 45
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
EXAMPLE:
(see Fig. 5-29)
Determine:
Takeoff distance required to clear a 50 ft obstacle For headwind calculation refer to the wind component chart section 1 of the FLM page 1-14. Pressure altitude
3000 ft
OAT
25°C
Headwind component
50 kt
For calculation 50% of the headwind component.
25 kt
O
LL
Takeoff distance required = 125 m
Solution:
ED
Known:
N TR
1. Enter chart at known OAT (25_C).
2. Move vertically upwards to to known pressure altitude (3000 ft).
T
C
O
3. From point of intersection move horizontally right to the reference line of the right chart.
N
O
4. Move vertically downwards to the reference line of the wind credit chart.
PY
5. From this point follow the direction of the wind credit guide lines.
O
6. Enter chart at calculated headwind (25 kt)
–
C
7. Move horizontally to intersect tracing from above.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
8. From point of intersection move downwards and read takeoff distance = 125 m (The result under the assumption of no wind is 251 m)
5 – 46
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
TAKEOFF DISTANCE FROM HOVER TO 50 FEET HEIGHT 2 X TURBOMECA ARRIEL 2E TAKEOFF POWER
INITIATED FROM 4 FT SKID HEIGHT IN A STABILIZED HOVER HEATING ON OR OFF
R
IN
ST
BK117D2031_1_r2
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
20000 ft DA
–40
–30
–20
–10
0
10
20
30
40
50 0
Headwind – kts Unfactored
FO
–50
10 20 30 0
Fig. 5-29 APPROVED Rev. 6
100 200 300 400 Cat. B Takoff Distance – m
Takeoff distance from hover to 50 ft height (AEO)
5 – 47
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.14
Rate of climb The following rate of climb charts (Fig. 5-31 to 5-56) show the rate of climb for all engines operating condition at VY and for one-engine inoperative conditions at VY and VTOSS with various combinations of power settings, bleed air heating, pressure altitude, outside air temperature and gross mass. Fig. 5-30 shows VY as a function of altitude. VY is automatically calculated and displayed on the IAS indicator. VTOSS is constant at 45 kt.
VY – DIAGRAM
ED
21000
LL
Max. Operating Altitude 20000 ft PA
N TR
O
20000
O
T
C
O
19000
PY
N
18000
LY O N
O N
16000
C
TI
15000
U
14000
ST
R
Pressure Altitude [ft]
–
C
O
17000
FO
R
IN
13000
12000
BK117 D–2 Vy
11000
10000 0 0
55
60
65 Vy [kts]
Fig. 5-30
5 – 48
70
75
VY – Diagramm APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
EXAMPLE:
(see Fig. 5-31)
Determine:
Rate of climb
Known:
Takeoff power 20°C
Pressure altitude
9800 ft
Gross mass
2400 kg
N TR
2. Move horizontally right to known OAT(20°C).
O
1. Enter chart at known pressure altitude (9800 ft).
ED
Rate of climb = 2880 ft/min
LL
Solution:
OAT
3. Move vertically downwards to reference line.
T
C
O
4. Move further downwards following the direction of the gross mass guide lines.
N
O
5. Enter chart at known gross mass (2400 kg).
PY
6. Move horizontally right to intersect tracing from above.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
7. From the point of intersection move vertically downwards and read rate of climb ( 28.8 x100 ft/min = 2880 ft/min).
APPROVED Rev. 6
5 – 49
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
TAKEOFF POWER
VY HEATING OFF
20000 2000kg – 2600kg
19000 18000 17000
N TR
–10 to 50
12000
C
O
11000
T
10000
O
9000
N
8000
PY
7000 6000
O
PRESSURE ALTITUDE –ft
13000
C
5000
–
4000
LY
3000
O N
2000 1000
TI
2500
R
U
2300
BK117D2M011_1
C
2400
ST
2200 2000 10
12
FO
8
IN
2100
R
GROSS MASS – kg
REFERENCE LINE
O N
0 2600
Fig. 5-31
5 – 50
LL
–30 to –20
14000
O
15000
ED
–45 to –40
16000
14
16
18
20
22
24
26
28
30
32
34
36
38
40
RATE OF CLIMB – 100 ft/min
Rate of climb (AEO, TOP, 2000 kg to 2600 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
TAKEOFF POWER
VY HEATING ON
20000 2000kg – 2600kg
19000 17000
–45 to –40
16000
–30 to –20
LL
15000
O
13000
N TR
–10 to 20
12000
O
11000
C
10000
T
9000
O
8000
N
7000 6000
PY
PRESSURE ALTITUDE –ft
14000
O
5000
C
4000
–
3000
LY
2000
O N
1000 0
REFERENCE LINE
O N
2600 2500
C
2300
BK117D2M011_11
TI
2400
R
U
2200
ST
2100 2000
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
RATE OF CLIMB – 100 ft/min
FO
R
8
IN
GROSS MASS – kg
ED
18000
Fig. 5-32
APPROVED Rev. 6
Rate of climb (AEO, TOP, 2000 kg to 2600 kg, heating on)
5 – 51
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
TAKEOFF POWER
VY HEATING OFF
20000 2600kg – 3200kg
19000 18000 17000
ED
–45 to –40
16000
LL
–30 to –20
15000
O N TR
13000 12000
–10 to 50
O
11000
C
10000
T
9000
N
O
8000 7000
PY
PRESSURE ALTITUDE –ft
14000
6000
O
5000
C
4000
–
3000
LY
2000
O N
1000 0
REFERENCE LINE
O N
3100
U
C
2900
BK117D2M011_2
TI
3000
R
2800
ST
2700 2600 2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
0
IN
GROSS MASS – kg
3200
Fig. 5-33
5 – 52
Rate of climb (AEO, TOP, 2600 kg to 3200 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
TAKEOFF POWER
VY HEATING ON
20000 2600kg – 3200kg
19000 18000
–30 to –20
15000
O N TR
13000
–10 to 20
12000
O
11000
C
10000
T
9000
O
8000
N
7000 6000
PY
PRESSURE ALTITUDE –ft
14000
O
5000
C
4000
–
3000
LY
2000
O N
1000 0
REFERENCE LINE
3100
TI
3000
BK117D2M011_21
O N
3200
C
2900
U
2800
ST
R
2700 2600
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
0
IN
GROSS MASS – kg
LL
16000
ED
–45 to –40
17000
Fig. 5-34
APPROVED Rev. 6
Rate of climb (AEO, TOP, 2600 kg to 3200 kg, heating on)
5 – 53
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
TAKEOFF POWER
VY HEATING OFF
20000 3200kg – 3700kg
19000 18000
–45 to –40
ED
17000 15000
–30 to –20
O N TR
13000 12000
–10 to 50
O
11000
C
10000
T
9000
N
O
8000 7000
PY
PRESSURE ALTITUDE –ft
14000
6000
O
5000
C
4000
–
3000
LY
2000
O N
1000 0
REFERENCE LINE
2
4
6
ST
0
R
U
C
TI
BK117D2M011_3
O N
3200 3300 3400 3500 3600 3700
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
IN
GROSS MASS – kg
LL
16000
Fig. 5-35
5 – 54
Rate of climb (AEO, TOP, 3200 kg to 3700 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
TAKEOFF POWER
VY HEATING ON
20000 3200kg – 3700kg
19000 18000
–30 to –20
O
15000
N TR
13000
–10 to 20
O
12000
C
11000
T
10000
O
9000
N
8000
PY
7000 6000
O
PRESSURE ALTITUDE –ft
14000
C
5000
–
4000
LY
3000
O N
2000 1000
REFERENCE LINE
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
IN
0
ST
R
U
C
TI
3200 3300 3400 3500 3600 3700
BK117D2M011_31
O N
0 GROSS MASS – kg
LL
16000
ED
–45 to –40
17000
Fig. 5-36
APPROVED Rev. 6
Rate of climb (AEO, TOP, 3200 kg to 3700 kg, heating on)
5 – 55
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING OFF
20000
–45 to –40
19000
2000kg – 2600kg
–30
18000
ED
17000 15000
–30 to 0
O N TR
13000 12000
O
11000
10 to 20
C
10000
T
9000
O
8000
N
7000 6000
30 to 50
PY
PRESSURE ALTITUDE –ft
14000
O
5000
C
4000
–
3000
LY
2000
O N
1000 0
REFERENCE LINE
O N
2600 2500
C
2300
BK117D2M012_1
TI
2400
U
2200
R
2100 2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
0
ST
2000
IN
GROSS MASS – kg
LL
16000
Fig. 5-37
5 – 56
Rate of climb (AEO, MCP, 2000 kg to 2600 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING ON
20000
–45 to –40
19000
2000kg – 2600kg
–30
18000
–30 to 0
O
15000
N TR
13000 12000
C
O
11000 10000
O
T
9000
10 to 20
N
8000 7000
PY
PRESSURE ALTITUDE –ft
14000
6000
C
O
5000 4000
LY
–
3000 2000
O N
1000 0
REFERENCE LINE
O N
2600
C
2400
BK117D2M012_11
TI
2500
U
2300
R
2200
ST
2100 2000
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
0
IN
GROSS MASS – kg
LL
16000
ED
17000
Fig. 5-38
APPROVED Rev. 6
Rate of climb (AEO, MCP, 2000 kg to 2600 kg, heating on)
5 – 57
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING OFF
20000
–45 to –40 –30
19000 18000
2600kg – 3200kg
ED
17000
LL
16000
O
12000
C
11000
T
10000
O
9000
N
8000
PY
7000 6000
C
5000
–
4000
LY
3000 2000
O N
1000 0
REFERENCE LINE
O N
3200
TI
3100
U
2900
BK117D2M012_2
C
3000
R
2800
ST
2700 2600 2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
0
IN
GROSS MASS – kg
N TR
–30 to 50
13000
O
PRESSURE ALTITUDE –ft
14000
O
15000
Fig. 5-39
5 – 58
Rate of climb (AEO, MCP, 2600 kg to 3200 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING ON
20000
–45 to –40
19000
2600kg – 3200kg
–30
18000
ED
17000
LL
16000
12000
C
O
11000
T
10000
O
9000
N
8000 7000 6000
C
O
5000
–
4000
LY
3000 2000
O N
1000 0
REFERENCE LINE
O N
3200
C
3000
BK117D2M012_21
TI
3100
U
2900
R
2800
ST
2700 2600
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
0
IN
GROSS MASS – kg
N TR
–30 to 20
13000
PY
PRESSURE ALTITUDE –ft
14000
O
15000
Fig. 5-40
APPROVED Rev. 6
Rate of climb (AEO, MCP, 2600 kg to 3200 kg, heating on)
5 – 59
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING OFF
20000
–45 to –40
19000
3200kg – 3700kg
–30
ED
18000 17000 15000
N TR
13000
O
12000
C
11000
T
10000
O
9000
N
8000
PY
7000 6000
O
PRESSURE ALTITUDE –ft
O
–30 to 50
14000
C
5000
–
4000
LY
3000
O N
2000 1000
REFERENCE LINE
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
IN
0
ST
R
U
C
TI
3200 3300 3400 3500 3600 3700
BK117D2M012_3
O N
0 GROSS MASS – kg
LL
16000
Fig. 5-41
5 – 60
Rate of climb (AEO, MCP, 3200 kg to 3700 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING ON
20000
–45 to –40
19000
3200kg – 3700kg
–30
18000 16000
ED
17000
O
LL
–30 to 20
15000
N TR
13000 12000
C
O
11000
T
10000
O
9000
N
8000 7000
PY
PRESSURE ALTITUDE –ft
14000
6000
C
O
5000 4000
LY
–
3000 2000
O N
1000
U
C
TI
BK117D2M012_31
O N
REFERENCE LINE
R ST
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
IN
GROSS MASS – kg
0 3200 3300 3400 3500 3600 3700
Fig. 5-42
APPROVED Rev. 6
Rate of climb (AEO, MCP, 3200 kg to 3700 kg, heating on)
5 – 61
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING OFF
20000 19000
2000kg – 2600kg
18000
ED
–45 to –40
15000
–30 to –10
O
13000
C
12000
T
11000
O
10000
N
9000
PY
8000
O
7000 6000
LY
4000
–45 to –40
–30 to –10
O N
3000 2000
O N
1000 0
REFERENCE LINE
TI
2600
C
2500
ST
R
2300
BK117D2M013_1
U
2400 2200
IN
2100 2000 –8
–6
FO
–10
R
GROSS MASS – kg
0 to 50
–
5000
Fig. 5-43
5 – 62
40
C
PRESSURE ALTITUDE –ft
14000
O
–30 –20
N TR
16000
LL
17000
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
Rate of climb (OEI, MCP, 2000 kg to 2600 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING ON
20000 2000kg – 2600kg
18000 16000
13000
N TR
–20
14000
O
–30
15000
O
–30 to –10
C
12000
T
11000
O
10000
N
9000
PY
8000
0 to 20
O
7000 6000
C
PRESSURE ALTITUDE –ft
LL
–45 to –40
17000
–
5000
LY
4000 3000
–45 to –40
–30 to –10
O N
2000 1000
O N
0
REFERENCE LINE
TI
2600
C
2500
R
2300
BK117D2M013_11
U
2400
ST
2200 2100
IN
GROSS MASS – kg
ED
19000
2000
–8
–6
FO
R
–10
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
Fig. 5-44
APPROVED Rev. 6
–4
Rate of climb (OEI, MCP, 2000 kg to 2600 kg, heating on)
5 – 63
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING OFF
20000 2600kg – 3200kg
18000
ED
19000 –45 to –40
12000
O
–30 to –10
13000
C
0 to 50
T
11000
O
10000 8000 40
5000
O
6000
C
7000
PY
N
9000
–
PRESSURE ALTITUDE –ft
14000
N TR
15000
O
–30 –20
16000
LY
4000 3000
O N
1000
O N
0
REFERENCE LINE
TI
3200
C
3100
ST
R
2900
BK117D2M013_2
U
3000 2800
IN
2700 –8
FO
–10
R
2600
–6
Fig. 5-45
5 – 64
0 to 50
–30 to –10
–45 to –40
2000
GROSS MASS – kg
LL
17000
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
Rate of climb (OEI, MCP, 2600 kg to 3200 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING ON
20000 2600kg – 3200kg
18000
ED
19000
16000
LL
–45 to –40
17000
N TR
O
–30 –20
15000 13000
C 0 to 20
N
O
10000 9000
PY
8000
O
7000 6000
–
5000
0 to 20
LY
4000 3000
–30 to –10
O N
–45 to –40
2000
O N
1000 0
REFERENCE LINE
TI
3200
U
C
3100
ST
2900
BK117D2M013_21
R
3000
IN
2800
R
2700
FO
GROSS MASS – kg
T
11000
2600
O
–30 to –10
12000
C
PRESSURE ALTITUDE –ft
14000
–10
–8
–6
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
Fig. 5-46
APPROVED Rev. 6
–4
Rate of climb (OEI, MCP, 2600 kg to 3200 kg, heating on)
5 – 65
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING OFF
20000 3200kg – 3700kg
18000
ED
19000 –45 to –40
14000
N TR
–20
15000
–30 to –10
12000
C
O
13000
0 to 50
T
11000
N
O
10000
PY
9000 8000
O
7000 6000
C
PRESSURE ALTITUDE –ft
O
–30
16000
–
5000
O N
3000
–45 to –40
2000
–30 to –10
O N
1000
TI
0
REFERENCE LINE
C
3200
R
3400
BK117D2M013_3
U
3300
ST
3500
IN
3600 3700
–6
R
–8
FO
–10
Fig. 5-47
5 – 66
0 to 50
LY
4000
GROSS MASS – kg
LL
17000
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
Rate of climb (OEI, MCP, 3200 kg to 3700 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E
MAXIMUM CONTINUOUS POWER
VY HEATING ON
ED
20000
3200kg – 3700kg
18000
–45 to –40
16000
–30
15000 13000
O
–20
14000
11000
N
0 to 20
O
T
C
–30 to –10
12000 10000
PY
9000
O
8000
C
7000 6000
0 to 20
–
PRESSURE ALTITUDE –ft
N TR
O
17000
LY
5000
O N
4000
–30 to –10
–45 to –40
3000
O N
2000 1000
TI
0
REFERENCE LINE
R
IN
ST
R
BK117D2M013_31
U
C
3200 3300 3400 3500 3600 3700 –10
–8
–6
FO
GROSS MASS – kg
LL
19000
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
Fig. 5-48
APPROVED Rev. 6
–4
Rate of climb (OEI, MCP, 3200 kg to 3700 kg, heating on)
5 – 67
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
TU206 NOT installed
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN. POWER
VY HEATING OFF
ED
20000
3200kg – 3700kg
LL
19000 18000
N TR
O
17000 16000 15000
T O N
11000
–30 to –10
PY
10000 9000
O
8000
C
7000 6000
0 to 40
LY
5000
O N
4000 3000 1000
TI
0
–30 to –10
–45 to –40
O N
2000
REFERENCE LINE
R
3300
BK117D2M513_3
U
C
3200
ST
3400
IN
3500 3700 –10
Fig. 5-49
R
3600 –8
FO
GROSS MASS – kg
C
–45 to –40
12000
–
PRESSURE ALTITUDE –ft
–40
13000
5 – 68
O
–45
14000
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
Rate of climb (OEI, 2 min. power, VY, wtihout TU206, 3200 kg to 3700 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
TU206 installed or after Helionix Maintenance Release 1
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITH TU206) 2 MIN. POWER
VY
ED
HEATING OFF
20000
LL
19000
O
18000
N TR
17000 15000
–45
C –40
T
13000
O
12000
N
11000
PY
10000
C
8000
–
7000 6000
O N
5000 4000
O N
3000 2000
TI
1000
C
0
REFERENCE LINE
ST
3300
BK117D2513_3_r2
R
U
3200 3400
R
IN
3500
FO
GROSS MASS – kg
–45 to 40
O
9000
LY
PRESSURE ALTITUDE –ft
14000
3700
O
16000
3600
3200kg – 3700kg
–10
–8
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
Fig. 5-50
Rate of climb (OEI, 2 min. power, VY, with TU206, 3200 kg to 3700 kg, heating off)
EFFECTIVITY APPROVED Rev. 9
All
5 – 69
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
TU206 NOT installed
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN. POWER
VTOSS = 45 KIAS HEATING OFF
20000 2000kg – 2600kg
ED
19000 18000
LL
17000 15000
–40
13000
O
–45 to –40
C
12000
O
10000
N
9000
PY
8000
–10 to 10
O
7000 6000
20 to 40
–
5000
LY
4000
O N
3000 2000
O N
1000 0
REFERENCE LINE
TI
2600
C
2500
R
BK117D2M512_1
U
2400
ST
2300 2200
–4
–2
FO
2000
R
IN
2100
0
Fig. 5-51
5 – 70
–30 to –20
T
11000
C
PRESSURE ALTITUDE –ft
N TR
–45
14000
GROSS MASS – kg
O
16000
2
4
6
8
10
12
14
16
18
20
22
24
26
28
RATE OF CLIMB – 100 ft/min
Rate of climb (OEI, 2 min. power, VTOSS, without TU206, 2000 kg to 2600 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
TU206 NOT installed
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN. POWER
VTOSS = 45 KIAS HEATING OFF
20000 2600kg – 3200kg
ED
19000 18000 16000
LL
17000
N TR
O
–45 –40
15000 13000
C
10000
N
O
–30 to 40
9000
PY
8000
O
7000 6000
– LY
4000
–45 to 40
O N
3000 2000
O N
1000 0
REFERENCE LINE
TI
3200
C
3100
ST
R
2900
BK117D2M512_2
U
3000 2800
R
IN
2700 2600
T
11000
5000
GROSS MASS – kg
O
–45 to –40
12000
C
PRESSURE ALTITUDE –ft
14000
FO
–4
–2
0
4
6
8
10
12
14
16
18
20
22
24
26
28
RATE OF CLIMB – 100 ft/min
Fig. 5-52
APPROVED Rev. 6
2
Rate of climb (OEI, 2 min. power, VTOSS, without TU206, 2600 kg to 3200 kg, heating off)
5 – 71
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
TU206 NOT installed
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN. POWER
VTOSS = 45 KIAS HEATING OFF
ED
20000
3200kg – 3700kg
19000
LL
18000 16000
N TR
O
17000 –45 –40
15000
O –45 to –40
T
12000 10000
O
8000
PY
–30 to 40
9000
C
7000 6000
LY
4000
O N
–45 to 40
3000
O N
2000 1000
TI
0
REFERENCE LINE
C
3200
R
BK117D2M512_3_r1
U
3300
ST
3400 3500 3700 –2
FO
–4
R
IN
3600
0
Fig. 5-53
5 – 72
N
O
11000
5000
GROSS MASS – kg
C
13000
–
PRESSURE ALTITUDE –ft
14000
2
4
6
8
10
12
14
16
18
20
22
24
26
28
RATE OF CLIMB – 100 ft/min
Rate of climb (OEI, 2 min. power, VTOSS, without TU260, 3200 kg to 3700 kg, heating off)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
TU206 installed or after Helionix Maintenance Release 1
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITH TU206) 2 MIN. POWER
VTOSS = 45 KIAS HEATING OFF
20000 2000kg – 2600kg
ED
19000 18000
LL
17000 15000
–45 –40
O
13000
C
12000
T
11000
N
9000
–30 to –20
PY
8000
O
7000 6000
–10 to 10
–
5000
LY
4000
20 to 40
O N
3000 2000
O N
1000 0
REFERENCE LINE
TI
2600
C
2500
R
BK117D2512_1_r2
U
2400
ST
2300 2200
IN
2100
R
GROSS MASS – kg
–45 to –40
O
10000
C
PRESSURE ALTITUDE –ft
14000
2000
N TR
O
16000
FO
–4
–2
0
4
6
8
10
12
14
16
18
20
22
24
26
28
RATE OF CLIMB – 100 ft/min
Fig. 5-54
APPROVED Rev. 9
2
Rate of climb (OEI, 2 min. power, VTOSS, with TU206, 2000 kg to 2600 kg, heating off)
5 – 73
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
EFFECTIVITY
OEI
TU206 installed or after Helionix Maintenance Release 1
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITH TU206) 2 MIN. POWER
VTOSS = 45 KIAS HEATING OFF
20000 2600kg – 3200kg
19000
ED
18000 17000 16000
N TR
O
–40
14000 13000
O
12000
C
11000 10000
T
–45 to 30
O
9000
N
8000
PY
7000 6000
O
PRESSURE ALTITUDE –ft
LL
–45
15000
C
5000
–
4000
LY
3000 2000
O N
1000
O N
REFERENCE LINE
C
3000
BK117D2512_2_r2
TI
3100
U
2900
R
2800
ST
2700 2600 –6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
24
RATE OF CLIMB – 100 ft/min
FO
R
–8
IN
GROSS MASS – kg
0 3200
Fig. 5-55
5 – 74
Rate of climb (OEI, 2 min. power, VTOSS, with TU206, 2600 kg to 3200 kg, heating off)
APPROVED Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
TU206 installed or after Helionix Maintenance Release 1
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITH TU206) 2 MIN. POWER
VTOSS = 45 KIAS HEATING OFF
20000
ED
3200kg – 3700kg
19000
LL
18000 16000
O
17000
N TR
–45 –40
15000
O C
13000
T
12000
O
11000
N
10000
PY
9000
O
8000
C
7000 6000
LY
5000
O N
4000 3000
O N
2000 1000
TI C
REFERENCE LINE
R
BK117D2512_3_r2
U
3300
ST
3400
IN
3500 3600
R
GROSS MASS – kg
0 3200
3700
–45 to 30
–
PRESSURE ALTITUDE –ft
14000
FO
–8
–6
–4
–2
APPROVED Rev. 9
2
4
6
8
10
12
14
16
18
20
22
24
RATE OF CLIMB – 100 ft/min
Fig. 5-56
EFFECTIVITY
0
Rate of climb (OEI, 2 min. power, VTOSS, with TU206, 3200 kg to 3700 kg, heating off)
All
5 – 75
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.1.15
Landing distance from 50 feet height to a complete stop on the ground (1 x TURBOMECA ARRIEL 2E) The landing distance chart (Fig. 5-58) provides single engine landing performance data. The category B landing profile (Fig. 5-57) assures the capability to land safely (on a smooth level surface) should an engine failure occur any time prior to or during an approach. Under this certification basis (FAR 29, category B), go-around capability is NOT assured during one-engine-inoperative operation.
ED
The chart (Fig. 5-58) shows the landing distance required until the helicopter comes to a complete stop on a smooth, hard and dry level surface.
O
N TR
O
LL
POWER AS REQUIRED
C
O
REDUCE RATE OF DESCENT
LY
–
AIM TO ACHIVE 30 KIAS AT 50 FT
PY
N
O
T
C
40 KIAS 100 ft AGL R/D < 500 ft/min
TERMINATE APPROACH
LANDING DISTANCE
Fig. 5-57
Landing profile (category B)
IN
ST
R
U
C
TI
O N
BKD2_FLH_0159_R
O N
100 ft
FO
R
To achieve values given in the chart, proceed as follows: 1. Approach
2. After reaching 100 ft
5 – 76
– Initiate to arrive at 100 ft with a speed 40 KIAS and a rate of descent of not more than 500 ft/min. – Adjust collective pitch to maintain desired rate of descent, gradually slow down aiming for 30 KIAS at 50 ft, then terminate the approach.
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
EXAMPLE:
(see Fig. 5-58)
Determine:
Landing distance required to clear a 50 ft obstacle For headwind calculation refer to the wind component chart section 1 of the FLM page 1-14.
OAT
25°C
Headwind component
50 kt
For calculation 50% of the headwind component.
25 kt
Landing distance = 256 m
ED
5000 ft
LL
Solution:
Pressure altitude
O
Known:
N TR
1. Enter chart at known OAT (25°C)
2. Move upwards to known pressure altitude (5000 ft)
T
C
O
3. From point of intersection move horizontally right to the reference line of the right chart.
N
O
4. Move vertically downwards to the reference line of the wind credit chart.
PY
5. From this point follow the direction of the wind credit guide lines.
O
6. Enter chart at calculated headwind (25 kt)
–
C
7. Move horizontally to intersect tracing from above.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
8. From point of intersection move downwards and read OEI landing distance = 256 m (The result under the assumption of no wind is 440 m)
APPROVED Rev. 6
5 – 77
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
LANDING DISTANCE FROM 50 FEET TO A COMPLETE STOP ON THE GROUND 1 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ROD 500 FT/MIN, 40 KIAS AT 50 FT HEATING OFF
–40
–30
–20
–10
0
10
20
30
40
50 0
Headwind – kts Unfactored
FO
–50
R
IN
ST
R
BK117D2035_1_r2
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
20000 ft DA
10 20 30 100
Fig. 5-58
5 – 78
200 300 400 500 Cat. B Takoff Distance – m
600
Landing distance from 50 ft height to a complete stop on the ground (OEI)
APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.2
ADDITIONAL NON-APPROVED PERFORMANCE DATA This subsection contains additional, non-approved performance data which are supplied by the aircraft manufacturer, useful for preflight and inflight mission planning.
5.2.1
Standard performance conditions All information in this section is based on the following conditions: 1. Engine power does not exceed helicopter limits (see Section 2).
Variable factors affecting performance
LL
5.2.2
ED
2. Helicopter is regarded in its clean configuration.
N TR
O
Details of the variable factors affecting performance are given in the respective diagrams.
C
O
NOTE D None of the curves presented should be extrapolated, but interpolation between given data is permissible.
Reading of the charts
O
5.2.3
PY
N
O
T
D Performance data contained in this section are not assured in the event of sand or hailstone ingestion into the engine(s).
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
It is of outmost importance that the charts be read accurately, especially the multi-variable graphs. In this type of presentation, errors in reading can be cumulative, resulting in large final errors. Close attention should be paid to subdivisions of the grid.
MANUFACTURER’S DATA APPROVED Rev. 6
5 – 79
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.2.4
Maximum cruising speed The diagrams (Fig. 5-59 to Fig. 5-62) provide maximum cruising speed data in terms of true airspeed as a function of helicopter gross mass and pressure altitude for the atmospheric conditions ISA, ISA –20_C, ISA +20_C and ISA +35_C under AEO conditions. For information concerning the influence of optional equipment on max. cruising speed refer to subsection 9.0.
(see figure 5-59)
Determine:
Maximum cruising speed
Known:
Atmospheric condition
ISA
Pressure altitude
9400 ft
Gross mass
2800 kg
N
O
T
C
O
N TR
O
LL
ED
EXAMPLE:
Maximum cruising speed = 147 KTAS
PY
Solution:
O
1. Enter chart (ISA) at known pressure altitude (9400 ft).
C
2. Move horizontally right to known gross mass (2800 kg).
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
3. From this point move vertically downwards and read maximum cruising speed = 147 KTAS.
5 – 80
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM CRUISING SPEED 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
ED
BLEED AIR HEATING OFF
LL
20000
N TR
O
18000
C
O
16000
N
PRESSURE ALTITUDE – FT
O
T
14000
3000 kg
PY
12000
O
2800 kg 2600 kg
C
10000
3700 kg
–
2400 kg
LY
8000
O N
3600 kg 3200 kg
O N
6000
2200 kg
3400 kg
U
ISA
ST
R
2000
80
90
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
R
IN
0
FO
BKD2_FLH_0332_R
C
TI
4000
Fig. 5-59
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum cruising speed (AEO, ISA)
5 – 81
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM CRUISING SPEED 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER BLEED AIR HEATING OFF
ED
20000
O
LL
18000
N TR
16000
T O
12000
N
3000 kg
2400 kg
LY
3400 kg
2200 kg
–
3600 kg
6000
3200 kg
TI
O N
4000
U
C
2000
R
0
90
IN
ST
80
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
FO
R
BKD2_FLH_0336_R
2600 kg
C
3700 kg
8000
2800 kg
O
PY
10000
O N
PRESSURE ALTITUDE – FT
C
O
14000
Fig. 5-60
5 – 82
Maximum cruising speed (AEO, ISA –20_C)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM CRUISING SPEED 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER BLEED AIR HEATING OFF
ED
20000
LL
18000
N TR
O
16000
C
PRESSURE ALTITUDE – FT
O
14000
O
T
12000
3000 kg
N
2800 kg 2600 kg
PY
10000 3700 kg
2400 kg
O
8000
2200 kg
C
3600 kg
–
3400 kg
O N
4000
2000
U
0
C
TI
BKD2_FLH_0335_R
3200 kg
O N
LY
6000
90
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
FO
R
IN
ST
R
80
Fig. 5-61
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum cruising speed (AEO, ISA +20_C)
5 – 83
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM CRUISING SPEED 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER BLEED AIR HEATING OFF
ED
20000
O
LL
18000
O
N TR
16000
T PY
N
O
12000
2200 kg
LY
3400 kg
6000
3200 kg
TI
O N
4000
U
C
2000
ST
R
0
90
IN
80
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
FO
R
BKD2_FLH_0364_R
C
3600 kg
2400 kg
–
3700 kg
8000
2800 kg 2600 kg
O
10000
3000 kg
O N
PRESSURE ALTITUDE – FT
C
14000
Fig. 5-62
5 – 84
Maximum cruising speed (AEO, ISA +35_C)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.2.5
Specific fuel consumption The diagrams (fig. 5-63 to 5-65) are based on the following conditions: – Fuel density is 0.8 kg/l – The used fuel meets one of the approved fuel types as specified in section 2. – Bleed air heating off With bleed air heating on, under AEO conditions (fig. 5-63 to 5-65) the fuel consumption is increased by 2%.
LL
ED
For information concerning the influence of optional equipment on the specific fuel consumption refer to subsection 9.0.
(see figure 5-64 and figure 5-65)
Determine:
Specific fuel consumption
Known:
OAT Pressure altitude
20 °C 5000 ft
Gross mass
3000 kg
N
O
T
C
O
N TR
O
EXAMPLE:
115 KCAS
PY
CAS
Off
C
O
Bleed air
FO
R
IN
–
LY
O N
O N
TI
ST
R
5. 6. 7. 8. 9. 10. 11.
C
1. 2. 3. 4.
Specific fuel consumption = 223 kg/h Enter chart fig.5-64 at known CAS (115 KCAS). Move horizontally right to known gross mass (3000 kg). Move vertically downwards to temperature reference line 0°C. From this point move upwards, following the direction of the temperature guide lines. Enter chart at known OAT(20°C). Move horizontally right to intersect tracing. From this point move vertically downwards to altitude reference line (0 ft). Move further downwards, following the altitude guide lines. Enter chart at known pressure altitude (5000 ft). Move horizontally right to intersect tracing from above. From point of intersection move vertically downwards and read reference torque ca. 59%. Now enter chart fig. 5-65 at known torque 59%, move horizontally right to known pressure altitude (5000 ft). Move vertically downwards to temperature reference line 0°C From this point move upwards, following the direction of the temperature guide lines. Enter chart at known OAT(20°C). Move horizontally right to intersect tracing. From this point of intersection move vertically downwards and read specific fuel consumption = 223kg/h.
U
Solution:
12. 13. 14. 15. 16. 17.
MANUFACTURER’S DATA APPROVED Rev. 6
5 – 85
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
SPECIFIC FUEL CONSUMPTION 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED BLEED AIR HEATING OFF 90
3700
3600
3400
3200
3000
2800
2600
70
2400
2200
60
ED
50
LL
40
O
30
N TR
LEVEL SPEED – KCAS
0–55 KCAS
GROSS MASS – KG
80
20
O
10
C
0
O
T
60
PY
N
40 20
C
O
REF. LINE
0
–
–20
LY
–40
0
O N
–60
O N
REF. LINE
BKD2_FLH_0316_R
TI C
4000
R
U
6000
R
12000
IN
10000
ST
8000
14000
FO
PRESSURE ALTITUDE – FT
2000
16000 18000 20000
10
Fig. 5-63
5 – 86
20
30
40 50 60 REFERENCE TORQUE – %
70
80
90
100
Specific fuel consumption (AEO, level speed 0 – 55 KCAS)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
SPECIFIC FUEL CONSUMPTION 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED BLEED AIR HEATING OFF 140
55–138 KCAS
130 LEVEL SPEED – KCAS
120
LL
3700
100 2800
2400
60
2200
3200
O
70
N TR
3400
2600
3000
C
80
O
3600
90
O
T
50
N
60
PY
40
O
20
–
C
REF. LINE
0
LY
–20
O N
–40
0
REF. LINE
C
TI
2000
O N
–60
U
4000
ST
R
6000
IN
8000
10000
R
PRESSURE ALTITUDE – FT
ED
110
BKD2_FLH_0318_R
FO
12000 14000 16000 18000 20000 10
Fig. 5-64
20
30
40 50 60 REFERENCE TORQUE – %
70
80
90
100
Specific fuel consumption (AEO, level speed 55 – 138 KCAS)
MANUFACTURER’S DATA APPROVED Rev. 6
5 – 87
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
SPECIFIC FUEL CONSUMPTION 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED BLEED AIR HEATING OFF
110 100
LL
ED
90 80
N TR
70
C
60
O
BLEED VALVE CLOSED
SL
N
O
T
20000
50
2000
40
PY
16000
4000
O
TORQUE – %
O
BLEED VALVE OPEN
30
C
12000
–
8000
LY
20
O N
10
O N
60
C
TI
40
ST
R
U
20
FO
BKD2_FLH_0314_R
R
–20
REF. LINE
IN
0
–40 –60
80
Fig. 5-65
5 – 88
100
120
140
160
180 200 220 240 260 FUEL CONSUMPTION – KG/H
280
300
320
340
Specific fuel consumption vs torque and temperature (AEO)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.2.6
Maximum range The diagrams (fig. 5-66 to 5-77) provide data for maximum range (without reserve) as a function of level speed and pressure altitude (at ISA, ISA –20_C, ISA +20_C and ISA +35_C) for 2800kg, 3200kg and 3700kg takeoff gross mass. The diagrams are based on the following conditions: – Usable fuel is 723 kg – Level flight – Bleed air heating off
LL
ED
With bleed air heating on, under AEO conditions (fig. 5-66 to 5-77) the maximum range is –2.5% less.
(see figure 5-66)
Determine:
Maximum range
Known:
Atmospheric condition
ISA
Pressure altitude
10.000 ft
T/O Gross mass
2800 kg
CAS
105 KCAS
Bleed air
Off
ST
R
U
TI
O N
O N
LY
–
C
O
EXAMPLE:
C
PY
N
O
T
C
O
N TR
O
For information concerning the influence of optional equipment on the maximum range refer to subsection 9.0.
FO
R
IN
Solution:
Maximum range = 470 NM
1. Enter chart (ISA, 2800 kg) at known CAS (105 KCAS). 2. Move vertically up to known pressure altitude(1000 ft). 3. From this point move horizontally to the left and read maximum range = 470 NM.
MANUFACTURER’S DATA APPROVED Rev. 6
5 – 89
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ISA
2800 kg
N TR
O
LL
600
ED
BLEED AIR HEATING OFF
10000 FT
C
O
500
T
5000 FT
O N PY
SEA LEVEL
C
O
300
LY
–
RANGE – NM
400
O N
O N
200
TI C U ST
20
IN
0
R
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0319_R
100
Fig. 5-66
5 – 90
Maximum range (2800 kg, ISA)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
2800 kg
N TR
O
LL
600
10000 FT
C
O
500
O N PY O
300
C
SEA LEVEL
LY
–
RANGE – NM
T
5000 FT
400
O N
O N
200
TI C U
ST
R
0
20
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0324_R
100
Fig. 5-67
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum range (2800 kg, ISA–20_C)
5 – 91
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
2800 kg
N TR
O
LL
600
10000 FT
C
O
500
T
5000 FT
O N PY O
SEA LEVEL
C
300
LY
–
RANGE – NM
400
O N
O N
200
TI C U R ST
0
20
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0323_R
100
Fig. 5-68
5 – 92
Maximum range (2800 kg, ISA+20_C)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
2800 kg
N TR
O
LL
600
10000 FT
PY
N
O
T
5000 FT
400
SEA LEVEL
C
O
300
LY
–
RANGE – NM
C
O
500
O N
O N
200
R
0
U
C
BKD2_FLH_0356_R
TI
100
20
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
IN
ST
0
Fig. 5-69
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum range (2800 kg, ISA+35_C)
5 – 93
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
3200 kg
500
N TR
O
LL
ISA
600
O
PY
N
5000 FT
SEA LEVEL
C
300
LY
–
RANGE – NM
400
O
T
C
O
10000 FT
O N
O N
200
TI C U R ST
0
20
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0320_R
100
Fig. 5-70
5 – 94
Maximum range (3200 kg, ISA)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
3200 kg
500
N TR
O
LL
600
PY
N
5000 FT
O
300
C
SEA LEVEL
LY
–
RANGE – NM
400
O
T
C
O
10000 FT
O N
O N
200
TI C U ST
R
0
20
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0326_R
100
Fig. 5-71
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum range (3200 kg, ISA–20_C)
5 – 95
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
3200 kg
500
N TR
O
LL
600
ED
BLEED AIR HEATING OFF
C
O
10000 FT
O N PY
SEA LEVEL
C
O
300
LY
–
RANGE – NM
T
5000 FT
400
O N
O N
200
TI C U 20
ST
0
R
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
IN
BKD2_FLH_0325_R
100
Fig. 5-72
5 – 96
Maximum range (3200 kg, ISA+20_C)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
3200 kg
500
N TR
O
LL
600
PY
N
O
5000 FT
SEA LEVEL
C
O
300
–
RANGE – NM
400
T
C
O
10000 FT
O N
O N
LY
200
0
20
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
IN
ST
0
R
U
C
BKD2_FLH_0357_R
TI
100
Fig. 5-73
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum range (3200 kg, ISA+35_C)
5 – 97
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
3700 kg
N TR
O
LL
ISA
600
ED
BLEED AIR HEATING OFF
C
O
500
T
10000 FT
O N O
PY
5000 FT
C
300
SEA LEVEL
LY
–
RANGE – NM
400
O N
O N
200
TI C U R 20
40
IN
0
ST
0
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0322_R
100
Fig. 5-74
5 – 98
Maximum range (3700 kg, ISA)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED BLEED AIR HEATING OFF
ED
3700 kg
N TR
O
LL
600
O
500
C
10000 FT
O
T
400
N PY
RANGE – NM
5000 FT
O
300
–
C
SEA LEVEL
O N
O N
LY
200
0
20
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
IN
ST
0
R
U
C
BKD2_FLH_0330_R
TI
100
Fig. 5-75
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum range (3700 kg, ISA–20_C)
5 – 99
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
O N TR C
O
500
O
T
10000 FT
N O
PY
5000 FT
C
300
–
SEA LEVEL
LY
RANGE – NM
400
O N
O N
200
ST
R
U
C
TI
100
0
IN
0
20
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0329_R
LL
3700 kg
600
ED
BLEED AIR HEATING OFF
Fig. 5-76
5 – 100
Maximum range (3700 kg, ISA+20_C)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM RANGE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
3700 kg
N TR
O
LL
600
C
O
500
T
10000 FT
N
O
400
PY
RANGE – NM
5000 FT
O
300
LY
–
C
SEA LEVEL
O N
O N
200
TI C U
ST
R
0
20
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0359_R
100
Fig. 5-77
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum range (3700 kg, ISA+35_C)
5 – 101
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
5.2.7
Endurance The diagrams (fig. 5-78 to 5-89) provide endurance data (without reserve) as a function of level speed and pressure altitude (at ISA, ISA –20_C, ISA +20_C and ISA +35_C) for 2800kg, 3200kg and 3700kg takeoff gross mass. The diagrams are based on the following conditions: – Usable fuel is 723 kg – Level flight – Bleed air heating off
LL
ED
With bleed air heating on, under AEO conditions (fig. 5-78 to 5-89) the maximum endurance is –2.5% less.
PY
N
O
T
C
O
N TR
O
For information concerning the influence of optional equipment on the endurance refer to subsection 9.0.
(see figure 5-78)
Determine:
Maximum endurance
Known:
Atmospheric condition
ISA
Pressure altitude
5000 ft
T/O Gross mass
2800 kg
CAS
105 KCAS
LY
O N
O N
TI
C
U
ST
R
Bleed air
Off
Maximum range = 3.78h = 03h 47min
IN
Solution:
–
C
O
EXAMPLE:
FO
R
1. Enter chart (ISA, 2800 kg) at known CAS (105 KCAS). 2. Move vertically up to known pressure altitude (5000 ft). 3. From this point move horizontally to the left and read maximum endurance = 3.78h.
5 – 102
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
LL
ED
BLEED AIR HEATING OFF
2800 kg
N TR
O
ISA
5.0
O
10000 FT
5000 FT
N
SEA LEVEL
C
O
PY
4.0
LY
–
3.5
O N
ENDURANCE – HOURS
O
T
C
4.5
TI
O N
3.0
C U R
ST 0
20
R
IN
2.0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
BKD2_FLH_0302_R
2.5
Fig. 5-78
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum Endurance (2800 kg, ISA)
5 – 103
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
LL
ED
BLEED AIR HEATING OFF
2800 kg
N TR
O
5.0
O
10000 FT 4.5
N
SEA LEVEL
C
O
PY
4.0
LY
–
3.5
O N
ENDURANCE – HOURS
O
T
C
5000 FT
TI
O N
3.0
C U R ST
2.0
20
R
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
BKD2_FLH_0307_R
2.5
Fig. 5-79
5 – 104
Maximum Endurance (2800 kg, ISA–20_C)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
2800 kg
N TR
O
LL
5.0
10000 FT
O
4.0
SEA LEVEL
PY
N
ENDURANCE – HOURS
5000 FT
T
C
O
4.5
LY
–
C
O
3.5
O N
O N
3.0
TI C U
ST
R
2.0
20
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0306_R
2.5
Fig. 5-80
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum Endurance (2800 kg, ISA+20_C)
5 – 105
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
2800 kg
N TR
O
LL
5.0
ED
BLEED AIR HEATING OFF
10000 FT
T N PY
SEA LEVEL
–
C
O
3.5
O N
O N
3.0
R
U
C
TI
2.5
ST
2.0
20
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0352_R
5000 FT
O
4.0
LY
ENDURANCE – HOURS
C
O
4.5
Fig. 5-81
5 – 106
Maximum Endurance (2800 kg, ISA+35_C)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
3200 kg
N TR
O
LL
ISA
5.0
4.5
O N
4.0
O
PY
SEA LEVEL
–
C
3.5
O N
O N
3.0
ST
2.0
R
U
C
TI
2.5
IN
0
20
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0303_R
5000 FT
LY
ENDURANCE – HOURS
T
C
O
10000 FT
Fig. 5-82
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum Endurance (3200 kg, ISA)
5 – 107
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
3200 kg
N TR
O
LL
5.0
ED
BLEED AIR HEATING OFF
10000 FT
O
4.5
T SEA LEVEL
PY
N
O
4.0
–
C
O
3.5
LY
ENDURANCE – HOURS
C
5000 FT
O N
O N
3.0
TI C U ST
R
2.0
20
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0309_R
2.5
Fig. 5-83
5 – 108
Maximum Endurance (3200 kg, ISA–20_C)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
3200 kg
N TR
O
LL
5.0
O
4.5
O
T
C
10000 FT
O
PY
SEA LEVEL
LY
–
C
3.5
O N
O N
3.0
R
U
C
TI
2.5
ST
2.0
20
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0308_R
5000 FT
N
ENDURANCE – HOURS
4.0
Fig. 5-84
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum Endurance (3200 kg, ISA+20_C)
5 – 109
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
LL
3200 kg
ED
BLEED AIR HEATING OFF
N TR
O
5.0
O
4.5
O PY
N
4.0
O
SEA LEVEL
–
C
3.5
O N
O N
3.0
R
U
C
TI
2.5
ST
2.0
IN
0
20
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0353_R
5000 FT
LY
ENDURANCE – HOURS
T
C
10000 FT
Fig. 5-85
5 – 110
Maximum Endurance (3200 kg, ISA+35_C)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
ISA
3700 kg
N TR
O
LL
5.0
C
O
4.5
T
10000 FT
O
5000 FT
N
ENDURANCE – HOURS
4.0
PY
SEA LEVEL
LY
–
C
O
3.5
O N
O N
3.0
TI C U 20
IN
ST
0
R
2.0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0305_R
2.5
Fig. 5-86
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum Endurance (3700 kg, ISA)
5 – 111
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
LL
ED
BLEED AIR HEATING OFF
3700 kg
O
N TR
O
5.0
C
4.5
N PY
4.0
5000 FT
C
O
SEA LEVEL
LY
–
3.5
O N
ENDURANCE – HOURS
O
T
10000 FT
TI
O N
3.0
U R ST
2.0
20
R
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
BKD2_FLH_0313_R
C
2.5
Fig. 5-87
5 – 112
Maximum Endurance (3700 kg, ISA–20_C)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
ED
BLEED AIR HEATING OFF
LL
3700 kg
N TR
O
5.0
O PY
5000 FT
O
SEA LEVEL
–
C
3.5
O N
O N
3.0
2.0
ST
R
U
C
TI
2.5
IN
0
20
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0312_R
10000 FT
N
4.0
LY
ENDURANCE – HOURS
T
C
O
4.5
Fig. 5-88
MANUFACTURER’S DATA APPROVED Rev. 6
Maximum Endurance (3700 kg, ISA+20_C)
5 – 113
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PERFORMANCE DATA
MAXIMUM ENDURANCE 2 X TURBOMECA ARRIEL 2E POWER AS REQUIRED
LL
3700 kg
ED
BLEED AIR HEATING OFF
N TR
O
5.0
O
10000 FT
N
4.0
PY O
SEA LEVEL
–
C
3.5
O N
O N
3.0
R
U
C
TI
2.5
ST
2.0
20
IN
0
40
60 80 LEVEL SPEED – KCAS
100
120
140
FO
R
BKD2_FLH_0355_R
5000 FT
LY
ENDURANCE – HOURS
T
C
O
4.5
Fig. 5-89
5 – 114
Maximum Endurance (3700 kg, ISA+35_C)
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MASS AND BALANCE
SECTION 6 MASS AND BALANCE TABLE OF CONTENTS
Page GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 1
6.1.1
Mass definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 1
6.1.2
Balance definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 1
6.2
BASIC EMPTY MASS CENTER OF GRAVITY . . . . . . . . . . . . . . . . . . . . . . . 6 – 4
6.2.1
Mass and balance record . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 4
6.2.2
Equipment list . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 4
6.3
LOADING EXAMPLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 6
6.3.1
Loading example for longitudinal CG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 6
6.3.2
Loading example for lateral CG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 8
6.4
LOADING CHARTS AND TABLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 10
6.4.1
C.G. of the pilot / copilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 11
6.4.2
C.G. of the passengers for “Comfort Seat Installation” refer to FMS 9.2–1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 11
6.4.3
CG of the passengers for “Seat Arrangement” refer to FMS 9.2–40 . . . . . 6 – 11
6.4.6
C.G. of the passengers for “Special Seat Arrangement” Forward seat configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 12
6.4.7
C.G. of the passengers for “Special Seat Arrangement” AFT seat configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 12
6.4.8
Operator seat installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 13
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
6.1
Page
R FO
LIST OF FIGURES
Fig. 6-1
Station diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 3
Fig. 6-2
Longitudinal CG envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 7
Fig. 6-3
Lateral CG envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 9
Fig. 6-4
Baggage centroids . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 10
Fig. 6-5
Operator seat on adapter plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 13
MANUFACTURER’S DATA Rev. 17
6–i
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MASS AND BALANCE
LIST OF TABLES Page Crew C.G. table . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 11
Table 6-2
Passengers C.G. table – “Special Seat Arrangement” Forward seat configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 12
Table 6-3
Passengers C.G. table – “Special Seat Arrangement” AFT seat configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 12
Table 6-4
C.G. of empty seat and of seat occupant (operator seat on adapter plate) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 13
Table 6-5
Cabin loading table . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 14
Table 6-6
Fuel loading table – longitudinal– MASS (KG) . . . . . . . . . . . . . . . . . . . . 6 – 15
Table 6-7
Fuel loading table – lateral– MASS (KG) . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 16
Table 6-8
Fuel loading table (with Self-Sealing Supply Tank) longitudinal– MASS (KG) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 17
Table 6-9
Fuel loading table (with Self-Sealing Supply Tank) lateral – MASS (KG) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 – 18
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Table 6-1
6 – ii
MANUFACTURER’S DATA Rev. 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MASS AND BALANCE
SECTION 6 MASS AND BALANCE 6.1
GENERAL This section provides information required for helicopter loading and computing mass and balance.
ED
It shall be the pilot’s responsibility to make certain that:
O
LL
– the helicopter is properly loaded so that the entire flight is conducted within the center of gravity limits.
N TR
– all cargo is stowed and tied down properly so that in-flight shifting is impossible
O
Mass definitions
N
6.1.1
T
C
O
– proper tie-down equipment (i.e. ropes, belts, etc.) of sufficient strength has to be used. As many tie-down fittings as possible have to be used per single cargo item in order to reduce the individual load per fitting and to avoid inadvertent in-flight shifting.
PY
Basic empty mass
LY
–
C
O
The basic empty mass consists of the basic helicopter with required standard equipment, optional equipment, unusable fuel, and full operating fluids including transmission, gearbox and engine oils, hydraulic fluid, rotor brake oil.
O N
Gross mass
U
C
Balance definitions
R
6.1.2
TI
O N
The gross mass is the sum of the basic empty mass and the pilot/crew, the passengers, the baggage/cargo and the fuel. This value will vary with mission.
FO
R
IN
ST
Locations on and within the helicopter can be determined in relation to fuselage stations, buttock lines and waterlines, measured in millimeters (mm) from known reference points (Fig. 6-1). Fuselage stations, buttock lines, and waterlines are planes perpendicular to each other. Reference plane is the plane at the longitudinal centerline of the helicopter perpendicular to the cabin floor. Fuselage stations (F.S. or STA.) Fuselage stations are vertical planes perpendicular to, and measured along, the longitudinal axis of the helicopter. Station 0 is an imaginary vertical plane forward of the nose of the helicopter, from which all horizontal distances are measured for balance purposes (see also ”reference datum”). Buttock lines (B.L.) Buttock lines are vertical planes perpendicular to, and measured to the left and right along the lateral axis of the helicopter. Buttock line (0) is the plane at the longitudinal centerline of the helicopter.
MANUFACTURER’S DATA Rev. 0
6–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MASS AND BALANCE
Waterline (W.L.) Waterlines are horizontal planes perpendicular to, and measured along, the vertical axis of the helicopter. Waterline (0) is a plane below the lowest point on the fuselage of the helicopter. Reference datum (RD) The reference datum (RD) is station 0. It is located 3950 mm (155.5 in) in front of the leveling point (LP) (see Fig. 6-1). Arm
O
LL
ED
The arm, for longitudinal balance purposes, is the horizontal distance from the reference datum to the center of gravity of a given item. For other purposes, fuselage stations (F.S. or STA) may be used. For the BK 117 D-2 arm and fuselage station are the same.
N TR
Moment (Mass moment)
arm (mm)
= mass (kg)
O
T
Center of gravity (C.G.)
C
moment (kgmm)
O
The moment is the mass of an item muliplied by its arm.
–
sum of all moments (kgmm) sum of all masses (kg)
LY
arm (mm) =
C
O
PY
N
Center of gravity is the point about which the helicopter would balance if suspended. Distance from the RD is found by dividing the total moment by the gross mass of the helicopter.
O N
C.G. limits
FO
R
IN
ST
R
U
C
TI
O N
C.G. limits are the extremes of movements to which the helicopter C.G. can travel. The C.G. of the loaded helicopter must remain within these limits at takeoff, throughout flight, and at landing.
6–2
MANUFACTURER’S DATA Rev. 0
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BUTTOCKLINE – mm
BL 2000 BL 1000 BL 0 BL 1000 BL 2000 STA 4000
STA 6000
STA 8000
STA 10000
STA 12000
ED
STA 2000
N TR
O
LL
STA 0
N
O
T
WL 4000
O
PY
WL 3000
–
C
WL 2000
LY
WL 1000
O N
levelingpoint sta 3950
O N
WL 0 STA 2000
C
TI
STA 0
STA 4000
STA 6000
STA 8000
STA 10000
STA 12000
FUSELAGE STATION – mm
Fig. 6-1
Station diagram
FO
R
IN
ST
R
U
BKD2_FLH_0005_R
WATERLINE – mm
C
O
WL 5000
MANUFACTURER’S DATA Rev. 0
6–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MASS AND BALANCE
6.2
BASIC EMPTY MASS CENTER OF GRAVITY The procedure for establishing mass and moment (relative to the reference datum) of the empty helicopter is described in the aircraft maintenance manual (AMM). The MASS AND BALANCE RECORD (Form MBR-1) appended to this section is used to maintain a continuous history of changes to the basic ’’as delivered” helicopter mass and balance data.
6.2.1
Mass and balance record
LL
ED
The basic empty mass (BEM) and center of gravity (C.G.) location are determined through actual weighing carried out by the helicopter manufacturer. This data is then entered on the first line of the MASS AND BALANCE RECORD, Form MBR-1 which then becomes a permanent part of the flight manual.
N TR
O
It is the responsibility of the pilot in command to operate the aircraft within the certified C.G. envelope.
T
C
O
The following procedure is a recommendation, however alternative methods for recording the helicopter’s mass and balance and computing the basic empty mass and balance status of the helicopter may be used on the operator’s own responsibility.
PY
N
O
The MASS AND BALANCE RECORD shall normally be updated (by transcribing the applicable information from the EQUIPMENT LIST) when necessary, as follows:
LY
–
C
O
– When additional equipment is installed on the helicopter necessitating a change in the basic empty mass (as per definition), add the new entry or entries to the previous totals of basic empty mass and moment then compute the new basic empty mass, moment and C.G. Iocation (arm).
O N
O N
– Likewise, when equipment is removed from the helicopter, subtract the new entry or entries from the previous totals of basic empty mass and moment then compute the new basic empty mass, moment and C.G. location (arm).
R
Equipment list
ST
6.2.2
U
C
TI
The MASS AND BALANCE RECORD shall normally be kept up to date and is considered the current basic empty mass and balance status of the helicopter.
FO
R
IN
An EQUIPMENT LIST, Form EL-1 is appended to this section and contains optional equipment of the particular helicopter when delivered. Each item on the list is provided with a number and description for identification, together with its mass, arm and moment. Those items of equipment that were installed when the particular helicopter was initially weighed are indicated by a check (4) mark in the ,,initial weighing” column. Therefore the mass, arm and moment of these items are included in the basic empty mass (BEM) data found on the MASS AND BALANCE RECORD, Form MBR.
6–4
MANUFACTURER’S DATA Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
C
O
N TR
O
LL
ED
MASS AND BALANCE
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
Intentionally left blank
MANUFACTURER’S DATA Rev. 0
6–5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MASS AND BALANCE
6.3
LOADING EXAMPLE The following examples show the method of calculation of the longitudinal and lateral center of gravity. The mass empty C.G. and mass moment is to be taken from the “empty mass and balance report” in this section.
NOTE
6.3.1
Loading example for longitudinal C.G.
[kg]
[mm]
[kgmm]
4819
+ 5 Pax Club Seats installation
60,1
3610
216961
+ Pilot (SRP=2513)
80,0
2312
184960
+ Copilot (SRP=2513)
80,0
2312
184960
240,0
3265
783600
160,0
4193
670880
76,0
5500
418000
729,0
4368
3184272
–
C
+ Baggage
O N
LY
+ Fuel
O N
O
9247661
C T
O
+ 2 mid passengers in FD
3344,1
–
14891294
–
4453*
–
IN
ST
R
U
C
TI
Result
O
PY
+ 3 fwd passengers against FD
Total
N TR
1919,0
N
Baseline Aircraft Definition
Mass moment
LL
Arm
O
Weight
ED
X–STA
X–STA: C.G. =
14891294, 0 3344, 1
kgmm kg
= 4453 mm
FO
R
*)
The longitudinal C.G. is 4456 mm aft of the reference datum. From Fig. 6-2 it can be seen, that the C.G. lies within the allowable C.G. limit.
6–6
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MASS AND BALANCE
A
STA (mm) 4380 4535 4700 4347
B A B C D
3500
Weight (kg) 3700 3700 2000 2400
ED
3000
2500 D
LL
Baggage Mid Passenger fd.
O
Fwd Passenger ag. fd.
N TR
Weight (kg)
Fuel
O
Pilot
C
2000
5 Pax Club Seat
C
4500
4700
4800
4900
Longitudinal C.G. envelope
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
Fig. 6-2
4600 STA (mm)
N
4400
PY
4300
O
T
Empty mass
O
BKD2_FLH_0296_R
Copilot
MANUFACTURER’S DATA Rev. 0
6–7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MASS AND BALANCE
6.3.2
Loading example for lateral C.G. Y–BL Weight
Arm
Mass moment
[kg]
[mm]
[kgmm] 13
24947
+ 5 Pax Club Seats installation
60,1
0
0
+ Pilot (SRP=2513)
80,0
390
31200
+ Copilot (SRP=2513)
80,0
–390
–31200
+ 3 fwd passengers against FD
240,0
0
+ 2 mid passengers in FD
160,0
0
76,0 729,0
Total
3344
LL O
0
0
0
0
O
N PY
–
–
24947 7*
–
LY
–
C
O
Result
T
C
+ Fuel
0 0
O
+ Baggage
ED
1919,0
N TR
Baseline Aircraft Definition
Y–BL: C.G. = 24947.0 3344.1
kgmm kg
= 7 mm
O N
O N
*)
C
TI
The lateral C.G. is 7 mm right of the centerline.
FO
R
IN
ST
R
U
From Fig. 6-3 it can be seen, that the C.G. lies within the allowable C.G. limit.
6–8
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MASS AND BALANCE
A
B
3500
E’
F’
Baggage
Mid Passenger fd.
2500
F
ED
E
3000
A B F’ F C D E E’
Weight (kg) 3700 3700 3000 3000 2000 2000 3000 3000
LL
Weight (kg)
Fuel
BL (mm) –80 80 80 100 100 –100 –100 –80
N TR
Copilot
O
Pilot
D
5 Pax Club Seat
C
2000
C
–100
–50
0 BL (mm)
N
–150
O
T
Empty mass 50
100
150
C
Lateral C.G. envelope
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
Fig. 6-3
O
PY
BKD2_FLH_0297_R
O
Fwd Passenger ag. fd.
MANUFACTURER’S DATA Rev. 0
6–9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MASS AND BALANCE
LOADING CHARTS AND TABLES
O
T
C
O
N TR
O
LL
ED
6.4
N
2820 mm
PY
1820 mm 820 mm
U
C
TI
BKD2_FLH_0197_R
O N
O N
LY
–
C
O
Inner Seat Rails
STA 4500
STA 5500
STA 6320
FO
R
IN
ST
R
STA 3500
Fig. 6-4
Baggage centroids
CAUTION D FOR LOADING LIMITATIONS REFER ALSO TO SECTION PARA 2.6.3. D THE CARGO CENTROID IS TO BE MEASURED FROM THE REAR END OF THE INNER SEAT RAILS. D CARGO SHOULD BE CENTERED IN THE CABIN. D ENSURE THAT CARGO IS PROPERLY SECURED BY RESTRAINING IT FROM SHIFTING WITH TIEDOWNS. D THE OPERATOR IS RESPONSIBLE FOR THE PROPER PLACEMENT AND SECURING OF CARGO IN ACCORDANCE WITH STANDARD OPERATING PROCEDURES AND PRACTICES.
6 – 10
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
C
Y–BL
PY
N
O
O
X–STA
T
C.G. of pilot and copilot
N TR
O
LL
ED
LY
–
C
O
NOTE D S
O N
O N
D
C
TI
D
FO
R
IN
ST
R
U
6 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
X–STA
N TR
CG of passengers
O
LL
ED
O
N
PY
O
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
T
C
Y–BL
CG of passengers
X–STA
Y–BL
6 – 12
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
LL
ED
NOTE D
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
D
O N
U
C
TI
R ST
FO
R
IN
NOTE
6 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
CABIN LOADING TABLE
6 – 14
LL O
N TR
O
C
T O N PY O
–
LY
O N O N TI
U
R
ST IN
ED
C
R FO
C
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FUEL LOADING TABLE – MASS (KG) – longitudinal CAUTION
R
FO
–
LL
N TR
O
C
T
O
N
O
PY
C
O
LY
O N
TI
C
O N
U
R
ST
IN
ED
6 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FUEL LOADING TABLE – MASS (KG) – lateral
O N
O N TR
O
C
N
PY
T
LL
O C –
LY
O
O N
TI
U
6 – 16
C
R
ST
IN
FO
ED
R
CAUTION
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
EFFECTIVITY
If Self-Sealing Supply Tank (FMS 9.2-39) is installed
FUEL LOADING TABLE (with Self-Sealing Supply Tank) – MASS (KG) – longitudinal CAUTION
R
FO
O N
O
LL
N TR
O
T
C
N
O
PY
C
O
LY
O N
TI
C
–
U
R
ST
IN
ED
6 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FUEL LOADING TABLE (with Self-Sealing Supply Tank) – MASS (KG) – lateral
6 – 18
TI
O N
ED
LL
C
O
N TR
T
PY
N
O
O C –
LY
O
O N
C
U
EFFECTIVITY
R
ST
IN
FO
R
CAUTION
All
IN
OUT
Form MBR -1 longitudinal
D Date
Equipment List Item No.
MODEL/VARIANT:
Modification
IN R
AS DELIVERED
S Description of Article or T
R
FO
O N
TI
Mass (kg)
C
U O N LY – N T
O
Page No.:
of
Mass (kg)
Massmoment (kgmm)
CG long (mm)
Signature
RUNNING BASIC EMPTY MASS (BEM)
ED
LL
O
N TR
O
C
Massmoment (kgmm)
Removed (–) Mass (kg)
PY
O
C
Massmoment (kgmm)
Added (+)
MASS CHANGE
SERIAL NO.:
(Continuous History of Changes in Structure or Equipment Affecting Mass and Balance)
BK117 D-2 M A S S A N D B A L A N C E R E C O R D – L O N G I T U D I N A L
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
IN
OUT
Form MBR -2 longitudinal
D t Date
Equipment List Item No.
MODEL/VARIANT:
MASS AND BALANCE
RECORD – LONGITUDINAL
R
F Article or Description of O R Modification IN ST O N
TI
C
U
Mass (kg)
O N LY – N T
O
Page No.:
of
Mass (kg)
Massmoment (kgmm)
CG long (mm)
Signature
RUNNING BASIC EMPTY MASS (BEM)
ED
LL
O
N TR
O
C
Massmoment (kgmm)
Removed (–) Mass (kg)
PY
O
C
Massmoment (kgmm)
Added (+)
MASS CHANGE
SERIAL NO.:
(Continuous History of Changes in Structure or Equipment Affecting Mass and Balance)
BK117 D-2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
IN
OUT
Form MBR -3 longitudinal
D Date
Equipment List Item No.
MODEL/VARIANT:
MASS AND BALANCE RECORD – LONGITUDINAL
Modification
IN R
S Description of Article or T
R
FO
O N
TI
Mass (kg)
C
U O N LY – N T
O
Page No.:
of
Mass (kg)
Massmoment (kgmm)
CG long (mm)
Signature
RUNNING BASIC EMPTY MASS (BEM)
ED
LL
O
N TR
O
C
Massmoment (kgmm)
Removed (–) Mass (kg)
PY
O
C
Massmoment (kgmm)
Added (+)
MASS CHANGE
SERIAL NO.:
(Continuous History of Changes in Structure or Equipment Affecting Mass and Balance)
BK117D-2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
IN
OUT
Form MBR -4 longitudinal
D Date
Equipment List Item No.
MODEL/VARIANT:
MASS AND BALANCE
RECORD – LONGITUDINAL
R
F Article or Description of O R Modification IN ST O N
TI
C
U
Mass (kg)
O N LY – N T
O
Page No.:
of
Mass (kg)
Massmoment (kgmm)
CG long (mm)
Signature
RUNNING BASIC EMPTY MASS (BEM)
ED
LL
O
N TR
O
C
Massmoment (kgmm)
Removed (–) Mass (kg)
PY
O
C
Massmoment (kgmm)
Added (+)
MASS CHANGE
SERIAL NO.:
(Continuous History of Changes in Structure or Equipment Affecting Mass and Balance)
BK117 D-2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
IN
OUT
Form MBR -1 lateral
D Date
Equipment List Item No.
MODEL/VARIANT:
Modification
IN R
AS DELIVERED
S Description of Article or T
R
FO
O N
TI
Mass (kg)
C
U O N LY – N T
O
of
Mass (kg)
Massmoment (kgmm)
CG lat (mm)
Signature
RUNNING BASIC EMPTY MASS (BEM)
ED
LL
O
N TR
O
C
Massmoment (kgmm)
Removed (–) Mass (kg)
PY
O
C
Massmoment (kgmm)
Added (+)
MASS CHANGE
SERIAL NO.: Page No.:
AND BALANCE RECORD – LATERAL
(Continuous History of Changes in Structure or Equipment Affecting Mass and Balance)
BK 117 D-2 (HELIONIX STEP2) M A S S
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
IN
OUT
Form MBR -2 lateral
D t Date
Equipment List Item No.
MODEL/VARIANT:
MASS AND BALANCE
R
F Article or Description of O R Modification IN ST O N
TI
C
U
Mass (kg)
O N LY – N T
O
of
Mass (kg)
Massmoment (kgmm)
CG lat (mm)
Signature
RUNNING BASIC EMPTY MASS (BEM)
ED
LL
O
N TR
O
C
Massmoment (kgmm)
Removed (–) Mass (kg)
PY
O
C
Massmoment (kgmm)
Added (+)
MASS CHANGE
SERIAL NO.: Page No.:
RECORD – LATERAL
(Continuous History of Changes in Structure or Equipment Affecting Mass and Balance)
BK 117 D-2 (HELIONIX STEP2)
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
IN
OUT
Form MBR -3 lateral
D Date
Equipment List Item No.
MODEL/VARIANT:
MASS AND BALANCE
Modification
IN R
S Description of Article or T
R
FO
O N
TI
Mass (kg)
C
U O N LY – N T
O
of
Mass (kg)
Massmoment (kgmm)
CG lat (mm)
Signature
RUNNING BASIC EMPTY MASS (BEM)
ED
LL
O
N TR
O
C
Massmoment (kgmm)
Removed (–) Mass (kg)
PY
O
C
Massmoment (kgmm)
Added (+)
MASS CHANGE
SERIAL NO.: Page No.:
RECORD – LATERAL
(Continuous History of Changes in Structure or Equipment Affecting Mass and Balance)
BK 117 D-2 (HELIONIX STEP2)
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
IN
OUT
Form MBR -4 lateral
D t Date
Equipment List Item No.
MODEL/VARIANT:
MASS AND BALANCE
R
F Article or Description of O R Modification IN ST O N
TI
C
U
Mass (kg)
O N LY – N T
O
of
Mass (kg)
Massmoment (kgmm)
CG lat (mm)
Signature
RUNNING BASIC EMPTY MASS (BEM)
ED
LL
O
N TR
O
C
Massmoment (kgmm)
Removed (–) Mass (kg)
PY
O
C
Massmoment (kgmm)
Added (+)
MASS CHANGE
SERIAL NO.: Page No.:
RECORD – LATERAL
(Continuous History of Changes in Structure or Equipment Affecting Mass and Balance)
BK 117 D-2 (HELIONIX STEP2)
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Item No.
R
FO
FLM / FMS
1)
O N
TI
C
U
Mass (kg)
O N – PY
O
C N T
O
(kgmm)
long.
Massmoment
ED
(kgmm)
lat.
Massmoment
LL
O
N TR
(mm)
Arm lat.
(EL)
O
C
LIST
n = installed; 0 = not installed.
LY
(mm)
Arm long.
EQUIPMENT
Required markings:
R
ST
IN
Description of article Modification/ Part No. No /
Page No.: 1 of 4
MODELE/VARIANT : BK 117 D-2 SERIAL NO.: :
BK 117 D-2
Marked as required 1)
Date/Sign.
Initial
Marked as required 1)
Date/Sign.
Second
WEIGHINGS
Marked as required 1)
Date/Sign.
Third
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Item No.
R
FO
FLM / FMS
1)
O N
TI
C
U
Mass (kg)
O N – PY
O
C N T
O
(kgmm)
long.
Massmoment
ED
(kgmm)
lat.
Massmoment
LL
O
N TR
(mm)
Arm lat.
(EL)
O
C
LIST
n = installed; 0 = not installed.
LY
(mm)
Arm long.
EQUIPMENT
Required markings:
R
ST
IN
Description of article Modification/ Part No./ No /
Page No.: 2 of 4
MODELE/VARIANT : BK 117 D-2 SERIAL NO.: :
BK 117 D-2
Marked as required 1)
Date/Sign.
Initial
Marked as required 1)
Date/Sign.
Second
WEIGHINGS
Marked as required 1)
Date/Sign.
Third
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Item No.
R
FO
FLM / FMS
1)
O N
TI
C
U
Mass (kg)
O N – PY
O
C N T
O
(kgmm)
long.
Massmoment
ED
(kgmm)
lat.
Massmoment
LL
O
N TR
(mm)
Arm lat.
(EL)
O
C
LIST
n = installed; 0 = not installed.
LY
(mm)
Arm long.
EQUIPMENT
Required markings:
R
ST
IN
Description of article Modification/ Part No./ No /
Page No.: 3 of 4
MODELE/VARIANT : BK 117 D-2 SERIAL NO.: :
BK 117 D-2
Marked as required 1)
Date/Sign.
Initial
Marked as required 1)
Date/Sign.
Second
WEIGHINGS
Marked as required 1)
Date/Sign.
Third
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Item No.
R
FO
FLM / FMS
1)
O N
TI
C
U
Mass (kg)
O N – PY
O
C N T
O
(kgmm)
long.
Massmoment
ED
(kgmm)
lat.
Massmoment
LL
O
N TR
(mm)
Arm lat.
(EL)
O
C
LIST
n = installed; 0 = not installed.
LY
(mm)
Arm long.
EQUIPMENT
Required markings:
R
ST
IN
Description of article Modification/ Part No./ No /
Page No.: 4 of 4
MODELE/VARIANT : BK 117 D-2 SERIAL NO.: :
BK 117 D-2
Marked as required 1)
Date/Sign.
Initial
Marked as required 1)
Date/Sign.
Second
WEIGHINGS
Marked as required 1)
Date/Sign.
Third
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
SECTION 7 DESCRIPTION OF SYSTEMS TABLE OF CONTENTS
Page GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUSELAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAIL BOOM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LANDING GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HELICOPTER DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−1−1 7−1−1 7−1−1 7−1−1 7−1−1
7.2 7.2.1 7.2.1.1 7.2.1.2 7.2.1.3 7.2.2 7.2.3 7.2.3.1 7.2.4 7.2.5 7.2.6 7.2.7
COCKPIT ARRANGEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Overhead panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Overhead panel (system 1 circuit breaker panel) . . . . . . . . . . . . . . . Overhead panel (system 2 circuit breaker panel) . . . . . . . . . . . . . . . Overhead switch panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Instrument panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Center console . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cockpit control panel (CCP) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Vertical rack (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Chart holder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Holder for tablet PC (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Copilot’s armrest (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−2−1 7−2−2 7−2−3 7−2−4 7−2−5 7−2−6 7−2−7 7−2−8 7−2−9 7 − 2 − 10 7 − 2 − 11 7 − 2 − 12
7.3 7.3.1 7.3.2 7.3.3 7.3.4 7.3.5 7.3.6 7.3.6.1 7.3.6.2 7.3.6.3 7.3.6.4 7.3.6.5 7.3.6.6 7.3.6.7 7.3.6.8 7.3.6.9 7.3.6.10
FLIGHT CONTROL SYSTEM AND AFCS . . . . . . . . . . . . . . . . . . . . . Main rotor controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tail rotor control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dual/Single control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cyclic stick . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Collective lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AFCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Autopilot control panel (APCP) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Collective lever switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cyclic stick switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SEMAs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Trim actuators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . General AFCS functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AFCS indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AFCS strip . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AFCS status area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
7.1 7.1.1 7.1.2 7.1.3 7.1.4
MANUFACTURER’S DATA Rev. 22
7−3−1 7−3−2 7−3−2 7−3−2 7−3−3 7−3−4 7−3−5 7−3−5 7−3−7 7−3−8 7−3−8 7 − 3 − 10 7 − 3 − 11 7 − 3 − 11 7 − 3 − 12 7 − 3 − 12 7 − 3 − 13
7−i
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
AFCS architecture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 3 − 14
7.3.6.12
AFCS coupling to navigation sources . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 3 − 15
7.3.6.13
AFCS modes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 3 − 16
7.4
DUAL HYDRAULIC BOOST SYSTEM . . . . . . . . . . . . . . . . . . . . . . . .
7−4−1
7.4.1
Hydraulic power system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−4−1
7.4.1.1
Degraded operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−4−1
7.4.2
Hydraulic indication and testing system . . . . . . . . . . . . . . . . . . . . . . .
7−4−3
7.4.2.1
Hydraulic indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−4−3
7.4.2.2
Hydraulic system test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−4−3
7.5
POWER PLANT AND RELATED SYSTEMS . . . . . . . . . . . . . . . . . .
7−5−1
7.5.1
Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−1
7.5.2
Engine operation and control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−3
7.5.2.1
General architecture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−3
7.5.2.2
Engine control panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−4
7.5.2.3
Engine starting / stopping . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−4
7.5.2.4
N2 control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−4
7.5.2.5
Rotor speed governing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Load sharing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−5 7−5−5
Engine overspeed protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−5
O
PY
N
O
T
C
O
N TR
O
ED
7.3.6.11
LL
Page
LY
–
C
7.5.2.6 7.5.2.7
Ultimate backup mode (FADEC EMER) . . . . . . . . . . . . . . . . . . . . . . .
7−5−6
7.5.2.9
Engine ventilation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−6
7.5.3
Engine oil system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−6
7.5.4
Engine fuel system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−7
7.5.5
Engine indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 10
7.5.5.1
First limit indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 10
7.5.5.2
NR / N2 indicator on FND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 14
7.5.5.3
Vehicle management page indications . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 16
Engine fire detection and extinguishing system . . . . . . . . . . . . . . . .
7 − 5 − 17
Fire detection system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 17
7.5.6.2
Fire extinguishing system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 17
7.5.6.3
Fire indication and operation of the extinguishers . . . . . . . . . . . . . .
7 − 5 − 18
7.6
FUEL SYSTEM (SEE FIG.7-6-1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−6−1
7.6.1
Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−6−1
7.6.2
Supply . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Monitoring system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−6−1 7−6−2
Refueling and grounding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−6−3
7.6.5
Fuel indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−6−5
7.6.5.1
Detailed fuel quantitiy indication (VMS) . . . . . . . . . . . . . . . . . . . . . . .
7−6−6
7.6.5.2
FND fuel quantity indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−6−7
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7.5.2.8
7.6.3 7.6.4
7 − ii
MANUFACTURER’S DATA Rev. 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page GEARBOX AND DRIVE SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−7−1
7.7.1
Main transmission . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−7−1
7.7.2
Main transmission oil system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−7−3
7.7.3
Tail rotor drive shaft and tail gearbox . . . . . . . . . . . . . . . . . . . . . . . . . .
7−7−4
7.7.4
Gearbox and drive system indications . . . . . . . . . . . . . . . . . . . . . . . .
7−7−5
7.8
ROTOR SYSTEMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−8−1
7.8.1
Main rotor system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−8−1
7.8.1.1
Main rotor head . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−8−1
7.8.1.2
Main rotor blades . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−8−2
7.8.2
Tail rotor system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−8−3
7.8.3
Rotor systems indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−8−4
7.9
ELECTRICAL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−9−1
7.9.1
DC power system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−9−1
7.9.2
DC power system control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−9−3
7.9.2.1
Generator switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−9−3
7.9.2.2
Battery master switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−9−3
7.9.2.3
Standby battery switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−9−3
7.9.2.4
BUS TIE control switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−9−3
7.9.2.5
Emergency SHED BUS switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7.9.3
Electrical system indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−9−5
7.9.4
Ground power switch (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−9−5
7.10
HEATING/VENTILATION SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 10 − 1
7.10.1
Bleed air heating system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 10 − 1
7.10.2
Electrical heater . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 10 − 1
Ventilation system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 10 − 2
7.10.3.1
Cockpit ventilation system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 10 − 2
7.10.3.2
Avionics cooling system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 10 − 2
7.10.3.3
PAX ventilation system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 10 − 2
7.11
LIGHTING EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 1
7.11.1
Standard internal lights − non NVG Helicopter configuration . . . . .
7 − 11 − 1
7.11.1.1
Emergency lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 1
7.11.1.2
Cargo dome light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 1
7.11.2
NVG compatible internal lights (if installed) . . . . . . . . . . . . . . . . . . . .
7 − 11 − 1
7.11.2.1
Emergency lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 1
7.11.2.2
Cargo dome light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 2
7.11.3
Supplementary Internal Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 3
7.11.3.1
Cockpit Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 3
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7.7
MANUFACTURER’S DATA Rev. 17
7 − iii
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page LED Cockpit Light (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 4
7.11.3.3
Cockpit dome light (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 5
7.11.3.4
No Smoking and Fasten Seat Belt Indication (optional) . . . . . . . . .
7 − 11 − 6
7.11.3.5
Ambient and Functional Lighting (optional) . . . . . . . . . . . . . . . . . . . .
7 − 11 − 6
7.11.4
External Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 7
7.11.4.1
Fixed landing light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 7
7.11.4.2
Search and landing light (S/L light) . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 8
7.11.4.3
Operation of the landing and S/L lights . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 9
7.11.4.4
2nd − S/L light 450W (white light) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 11
7.11.4.5
Fabric glare shield . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 14
7.11.4.6
Position lights (Standard) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 15
7.11.4.7
Anti-collision light (Standard) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 15
7.11.4.8
LED multimode position lights with anti-collision light function (optional) . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 16
7.11.4.9
LED dual color anti-collision light (optional) . . . . . . . . . . . . . . . . . . . . 7 − 11 − 17
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7.11.4.10 Strobe lights (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 19
O
7.11.4.11 Tail flood light (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 19
C
7.11.4.12 IR flasher on horizontal stabilizer (optional) . . . . . . . . . . . . . . . . . . . . 7 − 11 − 20
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7.11.4.13 Formation lights (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 20 AIR DATA SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 12 − 1
7.12.1
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 12 − 1
7.12.1.1
Static ports . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 12 − 1
7.12.1.2
Pitot tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 12 − 1
7.12.1.3
Pitot/Static heating system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 12 − 1
7.12.1.4
Alternate static source selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 12 − 1
7.12.2
7 − 12 − 3
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Air data indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HELIONIX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 13 − 1
7.13.1
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 13 − 1
7.13.1.1
Aircraft Management Computers (AMC) . . . . . . . . . . . . . . . . . . . . . . .
7 − 13 − 1
7.13.1.2
Multifunction Displays (MFD) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 13 − 1
7.13.1.3
Helionix system architecture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 13 − 4
7.13.2
MFD formats . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 13 − 5
7.13.2.1
Flight and Navigation Display (FND) format . . . . . . . . . . . . . . . . . . . .
7 − 13 − 6
7.13.2.2
Vehicle management system (VMS) format . . . . . . . . . . . . . . . . . . . . 7 − 13 − 15
7.13.2.3
Navigation display (NAVD) format . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 23
7.13.2.4
Digital map display (DMAP) format . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 25
7.13.2.5
Miscellaneous display (MISC) format . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 25
FO
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7.11.4.14 External multipurpose light (optional) . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 21
7 − iv
MANUFACTURER’S DATA Rev. 17.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page 7.13.2.6
Electronic flight bag (EFB) format . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 26
7.13.2.7
EFB books viewer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 28
7.13.2.8
Chart viewer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 30
7.13.2.9
Electronic Check List (ECL) viewer . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 33
7.13.2.10 Shortcut function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 35 7.13.2.11 Search function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 36 7.13.2.12 MFD configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 37 Alerting system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 39
7.13.3.1
Warnings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 39
7.13.3.2
Cautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 40
7.13.3.3
White advisories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 41
7.13.3.4
Information messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 41
7.13.3.5
Warning unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 42
7.13.3.6
Master List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 42
7.13.4
Flight data monitoring and automatic sensor reconfiguration . . . . . 7 − 13 − 44
7.13.4.1
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 44
7.13.4.2
Data monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 44
7.13.4.3
Data source display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 46
7.13.4.4
Sensor status display and manual re-configuration . . . . . . . . . . . . . 7 − 13 − 47
7.13.5
Vehicle management . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 49
7.13.5.1
VMS textual pages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 50
7.13.6
Master list messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 57
7.13.6.1
List of warning messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 57
7.13.6.2
List of caution messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 58
7.13.6.3
List of white advisory messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 65
7.13.6.4
List of information messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 72
7.13.7
List of audio tones and voice messages . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 75
7.14
GARMIN GTN 750, FMS, AND COM/NAV EQUIPMENT . . . . . . . .
7 − 14 − 1
7.14.1
VHF 2 Transfer Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 4
7.14.2
DMS Hold Selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 4
7.14.3
Marker (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 5
7.14.4
GTX 33 transponder and ADS−B Out . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 7
7.14.4.1
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 7
7.14.4.2
Transponder operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 7
7.14.4.3
Normal Operating Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 9
7.14.4.4
ADS−B Out failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 9
7.14.4.5
Surveillance capabilities (ICAO 2012 flight plan form) . . . . . . . . . . . 7 − 14 − 10
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7.13.3
MANUFACTURER’S DATA Rev. 17
7−v
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page Flight Management System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 10
7.14.5.1
GPS navigation and SBAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 11
7.14.5.2
Equipment and capabilities (ICAO 2012 Flight Paln Form) . . . . . . . 7 − 14 − 12
7.14.5.3
Conformity with guidance material . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 13
7.14.5.4
Status and phase of flight indications . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 14
7.14.5.5
Flight plan indication on FND and NAVD . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 15
7.14.6
Fuel planning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 16
7.14.6.1
Without (optional) fuel flow sensors . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 16
7.14.6.2
With fuel flow sensors installed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 16
7.14.7
Alerts and failure indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 17
7.14.8
Chart-view (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 17
7.14.8.1
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 17
7.14.9
Flight Stream 510 (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 19
7.15
COMMUNICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 15 − 1
7.15.1
Emergency locator transmitter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 15 − 1
7.15.2
Intercom . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 15 − 3
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Before Helionix Maintenance Release 1 or before ASB MBB BK117 D−2-42A-004 (HELIONIX STEP 2.0.1)
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HEALTH MONITORING SYSTEM (HMS) . . . . . . . . . . . . . . . . . . . . .
7.16.1
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 1
7.16.2
Component description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 2
7.16.2.1
DMAU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 2
7.16.2.2
Data Transfer Device (DTD) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 3
7.16.2.3
MFD Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 3
7.16.3
Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 4
7.16.4
Display/menus . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 4
Main rotor (M ROT) menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 4
7.16.4.2
Tail rotor (T ROT) menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 5
7.16.4.3
Shaft vibration check menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 5
7.16.4.4
Sensor test menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 6
7.16.4.5
Configuration menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 7
7.16.5
Power supply . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 7
7.16.6
Maintenance mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 7
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7 − vi
7 − 16 − 1
MANUFACTURER’S DATA Rev. 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page After Helionix Maintenance Release 1 or after ASB MBB BK117 D−2-42A-004 (HELIONIX STEP 2.0.1)
EFFECTIVITY
HEALTH MONITORING SYSTEM (HMS) . . . . . . . . . . . . . . . . . . . . . GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Component description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DMAU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Data Transfer Device (DTD) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MFD Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Display/menus . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 1 7 − 16 − 1 7 − 16 − 2 7 − 16 − 2 7 − 16 − 3 7 − 16 − 3 7 − 16 − 4 7 − 16 − 5
7.16.4.1 7.16.4.2 7.16.4.3 7.16.4.4 7.16.4.5 7.16.4.6 7.16.4.7 7.16.5 7.16.6
Main rotor (M ROT) menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tail rotor (T ROT) menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Shaft vibration check menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Sensor test menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Configuration menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HMS download menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HMS Version page / Troubleshotting mode . . . . . . . . . . . . . . . . . . . . Power supply . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Maintenance mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 5 7 − 16 − 5 7 − 16 − 6 7 − 16 − 6 7 − 16 − 7 7 − 16 − 7 7 − 16 − 8 7 − 16 − 8 7 − 16 − 8
7.17 7.17.1 7.17.1.1 7.17.1.2 7.17.1.3
USAGE MONITORING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UMS functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UMS on-board data storage and reliability . . . . . . . . . . . . . . . . . . . . . UMS monitoring function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7.17.1.4 7.17.1.5 7.17.1.6 7.17.1.7
FLIGHT REPORT pages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 17 − 3 FLIGHT REPORT history pages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 17 − 13 Engine power check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 17 − 14 Data downloading and ground tool . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 17 − 14
7 − 17 − 1 7 − 17 − 1 7 − 17 − 1 7 − 17 − 2 7 − 17 − 2
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7.16 7.16.1 7.16.2 7.16.2.1 7.16.2.2 7.16.2.3 7.16.3 7.16.4
7.18
7.18.1 7.18.2
HELICOPTER TERRAIN AWARENESS SYSTEM HTAWS (OPTIONAL) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAWS switch on overhead panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7.18.3 7.18.4 7.18.4.1 7.18.4.2 7.18.4.3 7.18.5 7.18.5.1
Virtual contol panel (VCP) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 3 FLTA (FORWARD LOOKING TERRAIN AVOIDANCE) function . . 7 − 18 − 4 HTAWS Altitude/Color Correlation and terrain/obstacle alerts . . . . 7 − 18 − 5 Protection envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 7 Terrain and Obstacles conflict symbols . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 9 GPWS (Ground Proximity Warning System) function . . . . . . . . . . . . 7 − 18 − 10 Excessive Descent Rate (mode 1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 10
MANUFACTURER’S DATA Rev. 17
7 − 18 − 1 7 − 18 − 1 7 − 18 − 1
7 − vii
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page 7.18.5.2
Descent After Takeoff mode (mode 3) . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 11
7.18.5.3
Excessive Downward Deviation from an ILS\GLS Glide slope (mode 5) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 12
7.18.6
HTAWS on NAVD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 15
7.18.7
Direct access HTAWS format . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 16
7.18.8
HTAWS on FND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 18
7.18.8
HTAWS Voice messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 19
SYNTHETIC VISION SYSTEM (SVS) (OPTIONAL) . . . . . . . . . . . .
7 − 19 − 1
7.19.1
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 1
7.19.2
SVS Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 1
7.19.3
SVS controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 4
7.19.4
SVS messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7.19.5
Indication of excessive/unusual attitudes on the SVS . . . . . . . . . . .
7.19.6
Databases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 5 7 − 19 − 6 7 − 19 − 6
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Before Helionix Maintenance Release 1
EFFECTIVITY
After Helionix Maintenance Release 1
SYNTHETIC VISION SYSTEM (SVS) (OPTIONAL) . . . . . . . . . . . .
7.19.1
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7.19.2
SVS Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 1
7.19.3
SVS controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 8
7.19.4
SVS messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 9
7.19.5
Indication of excessive/unusual attitudes on the SVS . . . . . . . . . . . 7 − 19 − 10
7.19.6
Databases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 19 − 10
7.20
ADDITIONAL EQUIPMENT (IF INSTALLED) . . . . . . . . . . . . . . . . . .
7.20.1
7 − 19 − 1
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7 − 20 − 1 7 − 20 − 1
7.20.2
Crew/operator seat resonator (damper) . . . . . . . . . . . . . . . . . . . . . . .
7 − 20 − 3
7.20.3
Cargo compartment smoke detector . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 20 − 4
7.20.4
Rear camera (adjustable) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 20 − 5
7.20.5
Digital multi-purpose camera system . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 20 − 6
7.20.5.1
Forward looking camera . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 20 − 6
7.20.5.2
Rear-view camera . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 20 − 6
7.20.5.3
Video Management System (VMS) . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 20 − 7
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Light and medium helicopter Active Vibration Control System (LAVCS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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7 − 19 − 1
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MANUFACTURER’S DATA Rev. 22.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
LIST OF FIGURES Page Principal dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−1−2
Fig. 7-1-2
Cabin dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−1−3
Fig. 7-2-1
Cockpit arrangement − typical installation . . . . . . . . . . . . . . . . . . . .
7−2−1
Fig. 7-2-2
Overhead panel − typical installation . . . . . . . . . . . . . . . . . . . . . . . .
7−2−2
Fig. 7-2-3
System 1 circuit breaker panel − typical installation . . . . . . . . . . . .
7−2−3
Fig. 7-2-4
System 2 circuit breaker panel − typical installation . . . . . . . . . . . .
7−2−4
Fig. 7-2-5
Overhead switch panel − typical installation . . . . . . . . . . . . . . . . . .
7−2−5
Fig. 7-2-6
Instrument panel arrangement − typical installation . . . . . . . . . . . .
7−2−6
Fig. 7-2-7
Center console − typical installation . . . . . . . . . . . . . . . . . . . . . . . . .
7−2−7
Fig. 7-2-8
Cockpit control panel (CCP) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−2−8
Fig. 7-2-9
Vertical rack − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−2−9
Fig. 7-2-10
Chart holder − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . .
Fig. 7-2-11
Holder for tablet PC − typical installation . . . . . . . . . . . . . . . . . . . .
7 − 2 − 11
Fig. 7-2-12
Copilot’s armrest − typical installation . . . . . . . . . . . . . . . . . . . . . .
7 − 2 − 12
Fig. 7-3-1
Flight control system and AFCS . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−3−1
Fig. 7-3-2
Cyclic stick controls− typical installation . . . . . . . . . . . . . . . . . . . . . .
7−3−3
Fig. 7-3-3
Collective lever controls− typical installation . . . . . . . . . . . . . . . . . .
7−3−4
Fig. 7-3-4
AFCS − equipment locations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−3−6
Fig. 7-3-5
Autopilot control panel (APCP) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−3−7
Fig. 7-3-6
AFCS indication on VMD and FND − typical display . . . . . . . . . . .
7 − 3 − 12
Fig. 7-3-7
AFCS strip − typical display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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7 − 3 − 13
AFCS status area − typical display . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 3 − 13
AFCS − simplified schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 3 − 14
Fig. 7-3-10
AFCS coupling to navigation sources . . . . . . . . . . . . . . . . . . . . . .
7 − 3 − 15
Fig. 7-3-11
ATT mode − Engagement / disengagement . . . . . . . . . . . . . . . . .
7 − 3 − 18
Fig. 7-3-12
DSAS mode − Engagement / disengagement and indications .
7 − 3 − 20
Fig. 7-3-13
ALT mode − Engagement / disengagement and indications . . .
7 − 3 − 22
Fig. 7-3-14
HDG mode − Engagement / disengagement and indications . .
7 − 3 − 25
Fig. 7-3-15
IAS mode − Engagement / disengagement and indications . . .
7 − 3 − 27
Fig. 7-3-16
VS mode − Engagement / disengagement and indications . . . .
7 − 3 − 30
Fig. 7-3-17
ALT.A mode − Engagement / disengagement and indications .
7 − 3 − 33
Fig. 7-3-18
GA mode − Engagement / disengagement and indications . . . .
7 − 3 − 36
Fig. 7-3-19
CRHT mode − Engagement / disengagement and indications .
7 − 3 − 39
IN
Fig. 7-3-8
7 − 2 − 10
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MANUFACTURER’S DATA Rev. 22
7 − ix
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page LOC mode − Engagement / disengagement and indications . . .
7 − 3 − 42
Fig. 7-3-21
GS mode − Engagement / disengagement and indications . . . .
7 − 3 − 45
Fig. 7-3-22
APP mode − Engagement / disengagement and indications . . .
7 − 3 − 47
Fig. 7-3-23
V.APP mode − Engagement / disengagement and indications .
7 − 3 − 50
Fig. 7-3-24
VOR mode − Engagement / disengagement and indications . .
7 − 3 − 53
Fig. 7-3-25
NAV mode − Engagement / disengagement and indications . . .
7 − 3 − 55
Fig. 7-3-26
FPA mode − Engagement / disengagement and indications . . .
7 − 3 − 58
Fig. 7-3-27
TRK mode − Engagement / disengagement and indications . . .
7 − 3 − 61
Fig. 7-3-28
GTC mode − Engagement / disengagement and indications . .
7 − 3 − 64
Fig. 7-3-29
GTC.H mode − Engagement / disengagement and indications
7 − 3 − 67
Fig. 7-4-1
Hydraulic pressure supply systems and actuators . . . . . . . . . . . . .
Fig. 7-4-2
Hydraulic indication on VMD and FND − typical display . . . . . . . .
Fig. 7-4-3
Hydraulic system test switch − typical installation . . . . . . . . . . . . .
Fig. 7-4-4
Hydraulic system − schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fig. 7-5-1
Engine modules and compartments overview . . . . . . . . . . . . . . . .
Fig. 7-5-2
Engine components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−2
Fig. 7-5-3
Simplified avionic − engine system architecture . . . . . . . . . . . . . . .
7−5−3
Fig. 7-5-4
Engine control panel − typical installation . . . . . . . . . . . . . . . . . . . .
7−5−4
Fig. 7-5-5
Rotor RPM (NR) vs Density Altitude . . . . . . . . . . . . . . . . . . . . . . . . .
Fig. 7-5-6
Engine oil system schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−7
Fig. 7-5-7
Engine fuel system schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−5−8
7−4−2 7−4−3 7−4−3 7−4−4
7−x
7−5−1
7−5−5
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Fig. 7-5-8
Engine indication on VMD and FND − typical display . . . . . . . . . .
7 − 5 − 10
Fig. 7-5-9
FLI indication − typical display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 11
Fig. 7-5-10
FLI indication − typical display . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 12
Fig. 7-5-11
NR / N2 indicator on FND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 14
Fig. 7-5-12
Vehicle management page indications . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 16
Fig. 7-5-13
Engine oil temperature and pressure indications . . . . . . . . . . . . .
7 − 5 − 17
Fig. 7-5-14
Additional NR/N2 indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 17
Fig. 7-5-15
Fire extinguishing system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 18
Fig. 7-5-16
Warning unit indication − fire ENG 1, FIRE sw pushed, BOT1 active and discharching . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 5 − 19
MANUFACTURER’S DATA Rev. 11.5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Fuel system − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−6−4
Fig. 7-6-2
Fuel system − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−6−4
Fig. 7-6-3
Fuel indication on VMD and FND − typical display . . . . . . . . . . . .
7−6−5
Fig. 7-6-4
Detailed fuel quantitiy indication (VMS) − typical display . . . . . . .
7−6−6
Fig. 7-6-5
FND fuel quantity indication − typical display . . . . . . . . . . . . . . . . .
7−6−7
Fig. 7-7-1
Main transmission . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−7−1
Fig. 7-7-2
Main transmission oil system − schematic . . . . . . . . . . . . . . . . . . . .
7−7−3
Fig. 7-7-3
Tail gearbox . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−7−4
Fig. 7-7-4
Gearbox and drive system indication on VMD and FND − typical display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−7−5
Fig. 7-8-1
Main rotor head . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−8−1
Fig. 7-8-2
Main rotor blade . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−8−2
Fig. 7-8-3
Tail rotor components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−8−3
Fig. 7-8-4
Main rotor system indication on VMD and FND − typical display
7−8−4
Fig. 7-9-1
DC power distribution − schematic . . . . . . . . . . . . . . . . . . . . . . . . . .
Fig. 7-9-2
DC power system control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−9−4
Fig. 7-9-3
Electrical system indication on VMD and FND − typical display .
7−9−5
Fig. 7-9-4
Electrical system area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7−9−6
7−9−2
Typical heating/ ventilation system − schematic . . . . . . . . . . . . . .
ST
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Fig. 7-10-1
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Fig. 7-6-1
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Page
Typical lighting equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 2
Fig. 7-11-2
Cockpit light − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 3
Fig. 7-11-3
LED Cockpit light − typical installation . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 4
Fig. 7-11-4
Cockpit dome light − typical installation . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 5
Fig. 7-11-5
No Smoking and Fasten Seat Belt Indication . . . . . . . . . . . . . . . .
7 − 11 − 6
Fig. 7-11-6
BLT/SMK switch in the overhead panel − typical installation . . .
7 − 11 − 6
Fig. 7-11-7
Location of the nose mounted landing light. . . . . . . . . . . . . . . . . .
7 − 11 − 7
Fig. 7-11-8
S/L light 400/200W (IR) or 450W . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 11 − 8
Fig. 7-11-9
S/L light 400/200W (IR) or 450W controls − typical installation .
7 − 11 − 9
FO
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IN
Fig. 7-11-1
7 − 10 − 3
Fig. 7-11-10
2nd S/L light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 11
Fig. 7-11-11
2nd−S/L light controls − typical installation . . . . . . . . . . . . . . . . . 7 − 11 − 12
MANUFACTURER’S DATA Rev. 11.5
7 − xi
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page Fabric glareshield − typical installation on right hand side. . . . 7 − 11 − 14
Fig. 7-11-13
Position lights switch − typical installation . . . . . . . . . . . . . . . . . . 7 − 11 − 15
Fig. 7-11-14
Anti-collision light switch − typical installation . . . . . . . . . . . . . . . 7 − 11 − 15
Fig. 7-11-15
Multimode position lights switch − typical installation . . . . . . . . 7 − 11 − 16
Fig. 7-11-16
Dual color anti-collision light switch − typical installation . . . . . 7 − 11 − 17
Fig. 7-11-17
Dual color anti-collision light switch − typical installation . . . . . 7 − 11 − 17
Fig. 7-11-18
IR FLASH switch − typical installation . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 18
Fig. 7-11-19
Strobe lights switch − typical installation . . . . . . . . . . . . . . . . . . . 7 − 11 − 19
Fig. 7-11-20
Tail flood light switch − typical installation . . . . . . . . . . . . . . . . . . 7 − 11 − 19
Fig. 7-11-21
IR flasher switch − typical installation . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 20
Fig. 7-11-22
Formation lights switch − typical installation . . . . . . . . . . . . . . . . 7 − 11 − 20
Fig. 7-11-23
External multipurpose light - typical installation . . . . . . . . . . . . . 7 − 11 − 21
Fig. 7-11-24
External multipurpose light switch on center console typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 22
Fig. 7-11-25
Hoist Light switch on panel installed in the cabin (LH and RH) typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 11 − 22 Air data system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fig. 7-12-2
Air data system indications on IESI and FND − typical display .
Fig. 7-13-1
MFDs − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 13 − 2
Fig. 7-13-2
MFD controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 13 − 3
Fig. 7-13-3
Helionix system architecture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 13 − 4
Fig. 7-13-4
MFD modes − typical display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 13 − 5
Fig. 7-13-5
7 − 13 − 6
R
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Fig. 7-12-1
ST
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Fig. 7-11-12
7 − 12 − 3
IN
FND format, MFD1 and MFD4− typical display . . . . . . . . . . . . . .
7 − 12 − 2
R
Fig. 7-13-6
Fig. 7-13-7
VMS SYST sub-format − typical display . . . . . . . . . . . . . . . . . . . . 7 − 13 − 18
Fig. 7-13-8
CT sub-page − typical display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 19
Fig. 7-13-9
Mission database information window . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 20
Fig. 7-13-10
VMS RCNF sub-format − typical display . . . . . . . . . . . . . . . . . . . 7 − 13 − 21
Fig. 7-13-11
NAVD format − typical display . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 23
Fig. 7-13-12
MISC format − typical display . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 25
Fig. 7-13-13
EFB format (BOOK function) − typical display . . . . . . . . . . . . . . 7 − 13 − 26
Fig. 7-13-14
Books main menu − typical presentation . . . . . . . . . . . . . . . . . . . 7 − 13 − 28
Fig. 7-13-15
Book TOC menu − typical presentation . . . . . . . . . . . . . . . . . . . . 7 − 13 − 29
Fig. 7-13-16
Chart main menu − typical presentation . . . . . . . . . . . . . . . . . . . 7 − 13 −30
FO
7 − xii
VMS main format − typical display . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 15
MANUFACTURER’S DATA Rev. 17.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page Chart stage menu − typical presentation . . . . . . . . . . . . . . . . . . . 7 − 13 − 31
Fig. 7-13-18
Display of a chart − typical presentation . . . . . . . . . . . . . . . . . . . 7 − 13 − 32
Fig. 7-13-19
ECL main menu − typical presentation . . . . . . . . . . . . . . . . . . . . 7 − 13 − 33
Fig. 7-13-20
Checklist display − typical presentation . . . . . . . . . . . . . . . . . . . . 7 − 13 − 34
Fig. 7-13-21
Shortcut menu − typical presentation . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 35
Fig. 7-13-22
Search function − typical presentation . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 36
Fig. 7-13-23
MFD format reconfiguration − single MFD failure . . . . . . . . . . . . 7 − 13 − 37
Fig. 7-13-24
MFD format reconfiguration − dual MFD failure . . . . . . . . . . . . . 7 − 13 − 38
Fig. 7-13-25
Examples of red warning indications on the FND . . . . . . . . . . . 7 − 13 − 40
Fig. 7-13-26
Examples of amber caution indications on the FND . . . . . . . . . 7 − 13 − 41
Fig. 7-13-27
Warning unit − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 42
Fig. 7-13-28
Indication of messages in the master list (left: unacknowledged right: acknowledged) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 43
Fig. 7-13-29
Discrepancy indication (airspeed indication) . . . . . . . . . . . . . . . . 7 − 13 − 45
Fig. 7-13-30
Indication of a total loss of all air data sensors . . . . . . . . . . . . . . 7 − 13 − 45
Fig. 7-13-31
Sensor sources used on each MFD indicated on the RCNF page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 46
Fig. 7-13-32
Sensor sources used following an attitude sensor (IESI replaces ATT1 and ATT2) and a radar altimeter failure (RA shown as failed). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 46
Fig. 7-13-33
Sensor status indication on the RCNF page. . . . . . . . . . . . . . . . 7 − 13 − 47
Table 7-13-1
Sensor status indications on the RCNF page . . . . . . . . . . . . . . 7 − 13 − 47
Fig. 7-13-34
Manual sensor de-selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 48
Fig. 7-13-35
Navigation in VMS textual pages . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 50
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Fig. 7-13-17
System status page − typical display . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 51
Fig. 7-13-37
Configuration system page − typical display . . . . . . . . . . . . . . . . 7 − 13 − 52
Fig. 7-13-38
Configuration units page − typical display . . . . . . . . . . . . . . . . . . 7 − 13 − 53
Fig. 7-13-39
Weight page − typical display . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 54
Fig. 7-13-40
Weight page − fuel system invalid − typical display . . . . . . . . . . 7 − 13 − 55
Fig. 7-13-41
Weight page − total weight exceeds max. certified weight − typical display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 55
Fig. 7-13-42
Performance computation page . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 13 − 55
FO
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Fig. 7-13-36
Fig. 7-14-1
FMS ON/OFF pb − typical installation . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 1
Fig. 7-14-2
Garmin GTN − Control and Display Unit . . . . . . . . . . . . . . . . . . . .
7 − 14 − 2
Fig. 7-14-3
Antenna layout − typical installation . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 3
Fig. 7-14-4
VHF2 XFER switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 4
MANUFACTURER’S DATA Rev. 17.1
7 − xiii
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page DME 1/2 annunciators − typical installation . . . . . . . . . . . . . . . . . .
7 − 14 − 5
Fig. 7-14-6
VOR indication with DME hold in the lower left hand corner of the FND. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 5
Fig. 7-14-7
Marker indication on the FND. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 6
Fig. 7-14-8
Marker annunciator pushbutton (shown in HI mode) − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 7
Fig. 7-14-9
Transponder information shown at the top of the GTN750 display. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 14 − 8
Fig. 7-14-10
XPDR controls on the FMS−transponder page . . . . . . . . . . . . .
Fig. 7-14-11
NAV area within the FND (top) and NAVD (bottom), indicating that SBAS is available. . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 11
Fig. 7-14-12
NAVD with indicated flight plan (next waypoint LFMH, final waypoint LFML). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 15
Fig. 7-14-13
MSG annunciation on the FND and NAVD page. . . . . . . . . . . . 7 − 14 − 17
Fig. 7-14-14
ChartView . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 14 − 18
ED
Fig. 7-14-5
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7 − 15 − 1
Fig. 7-15-2
ELT remote control unit − typical installation . . . . . . . . . . . . . . . . .
7 − 15 − 1
Fig. 7-15-3
C
N
ELT − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Intercom − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 15 − 3
–
O
PY
Fig. 7-15-1
LY
Before Helionix Maintenance Release 1 or before ASB MBB BK117 D−2-42A-004 (HELIONIX STEP 2.0.1)
O N
EFFECTIVITY
System architecture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 1
Fig. 7-16-2
DMAU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 2
Fig. 7-16-3
DTD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fig. 7-16-4
DMAU MROT default page on MFD: . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 4
Fig. 7-16-5
7 − 16 − 3
ST
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Fig. 7-16-1
7 − 16 − 5
T ROT acquisition menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 5
Fig. 7-16-7
Shaft vibration check menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 6
Fig. 7-16-8
Sensor test menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 6
Fig. 7-16-9
Configuration menu (CONF) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 7
M ROT acquisition menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IN
FO
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Fig. 7-16-6
EFFECTIVITY
7 − xiv
7 − 14 − 9
After Helionix Maintenance Release 1 or after ASB MBB BK117 D−2-42A-004 (HELIONIX STEP 2.0.1)
Fig. 7-16-1
System architecture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 1
Fig. 7-16-2
DMAU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 2
Fig. 7-16-3
DTD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 3
Fig. 7-16-4
HMS M ROT default page on MFD: . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 4
Fig. 7-16-5
HMS M ROT acquisition menu . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 5
MANUFACTURER’S DATA Rev. 17.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page HMS T ROT acquisition menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 5
Fig. 7-16-7
HMS shaft vibration check menu . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 6
Fig. 7-16-8
HMS sensor test menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 6
Fig. 7-16-9
HMS configuration menu (CONF) . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 7
Fig. 7-16-10
HMS data loading menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 7
Fig. 7-16-11
HMS Version page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 16 − 8
Fig. 7-17-1
Data Transfer Device (DTD) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LL 7 − 17 − 4
T
C
Flight report page 1 − typical display . . . . . . . . . . . . . . . . . . . . . . .
7 − 17 − 4
All
Flight report page 2 − OEI usage − typical display . . . . . . . . . . .
7 − 17 − 6
Fig. 7-17-5
Flight report page 3 − Creep life damage indication − typical display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 17 − 7
Fig. 7-17-6
Flight report page 4 − Landing and hoist cycles . . . . . . . . . . . . . .
7 − 17 − 7
Fig. 7-17-7
Flight report page TOT OVLIM − typical display . . . . . . . . . . . . . .
Fig. 7-17-8
Flight report page N1 OVLIM − typical display . . . . . . . . . . . . . . .
7 − 17 − 8
Fig. 7-17-9
Flight report page N2 OVLIM − typical display . . . . . . . . . . . . . . .
7 − 17 − 9
Fig. 7-17-10
Flight report page ENG TRQ OVLIM − typical display . . . . . . .
7 − 17 − 9
Fig. 7-17-11
Flight report page NR OVLIM − typical display . . . . . . . . . . . . . .
7 − 17 − 9
7 − 17 − 8
R
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Fig. 7-17-4
C
EFFECTIVITY
O
After Helionix Maintenance Release 1
Fig. 7-17-3
7 − 17 − 1
O
EFFECTIVITY
Flight report page 1 − typical display . . . . . . . . . . . . . . . . . . . . . . .
N TR
Fig. 7-17-2
O
Before Helionix Maintenance Release 1
N
EFFECTIVITY
ED
Fig. 7-16-6
Flight report page MGB TRQ OVLIM (AEO) − typical display . 7 − 17 − 10
Fig. 7-17-13
Flight report page MGB TRQ OVLIM (OEI) − typical display . . 7 − 17 − 11
Fig. 7-17-14
Flight report page MM OVLIM − typical display . . . . . . . . . . . . . 7 − 17 − 11
FO
R
IN
ST
Fig. 7-17-12
Fig. 7-17-15
Flight report page CHIP DETECTION − typical display . . . . . . 7 − 17 − 12
Fig. 7-17-16
Flight report page ENG SVC NEEDED − typical display . . . . . 7 − 17 − 12
Fig. 7-17-17
FLIGHT REPORT history pages − typical display . . . . . . . . . . . 7 − 17 − 13
Fig. 7-18-1
TAWS sw on OVHP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 18 − 1
Fig. 7-18-2
VCP window . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 18 − 3
Fig. 7-18-3
Altitude/Color Correlation and terrain/obstacle alerts . . . . . . . . .
7 − 18 − 5
Fig. 7-18-4
Typical HTAWS presentation on NAVD (HTAWS and ACAS activated) . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 18 − 6
Fig. 7-18-5
Protection envelope for level flight and climb . . . . . . . . . . . . . . . .
7 − 18 − 7
MANUFACTURER’S DATA Rev. 17.1
7 − xv
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page Fig. 7-18-6
Protection envelope for during descent . . . . . . . . . . . . . . . . . . . . .
7 − 18 − 8
Fig. 7-18-7
Terrain and Obstacles conflict symbols . . . . . . . . . . . . . . . . . . . . .
7 − 18 − 9
Fig. 7-18-8
Excessive descent rate mode envelope . . . . . . . . . . . . . . . . . . . . 7 − 18 − 10
Fig. 7-18-9
Descent After Takeoff mode − normal sensitivity . . . . . . . . . . . . 7 − 18 − 11
EFFECTIVITY
Before Helionix Maintenance Release 1 GPWS Mode 5 alerting principle . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 12
Fig. 7-18-11
GPWS Mode 5 alerting envelope . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 12
After Helionix Maintenance Release 1
LL
EFFECTIVITY
ED
Fig. 7-18-10
GPWS Mode 5 alerting principle . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 13
Fig. 7-18-13
GPWS Mode 5 alerting envelope . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 14
N TR
C
After Helionix Maintenance Release 1
T
EFFECTIVITY
Typical HTAWS status indication on NAVD . . . . . . . . . . . . . . . . . 7 − 18 − 15
O
Fig. 7-18-14
O
All
N
EFFECTIVITY
O
Fig. 7-18-12
Direct access HTAWS key . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 16
Fig. 7-18-16
Direct access HTAWS page showing a decluttered 2 NM range display of the terrain/obstacle situation . . . . . . . . . . . . . . . . . . . . 7 − 18 − 17
EFFECTIVITY
O
C
LY
Typical HTAWS message on FND . . . . . . . . . . . . . . . . . . . . . . . . 7 − 18 − 18
O N
Fig. 7-18-17
–
All
Before Helionix Maintenance Release 1
O N
EFFECTIVITY
PY
Fig. 7-18-15
Typical SVS display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 2
Fig. 7-19-2
Vertical field of view$23.5° . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 3
Fig. 7-19-3
SVS horizontal field of view as depicted with black/white lines on the Helionix DMAP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 4
SVS and FDS controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 5
SVS indication during excessive nose up (left) or nose−down (right) attitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 6
C
U
R
ST
IN
Fig. 7-19-4
TI
Fig. 7-19-1
FO
R
Fig. 7-19-5
EFFECTIVITY
Fig. 7-19-1
Typical SVS display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 2
Fig. 7-19-2
Vertical field of view$23.5° . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 3
Fig. 7-19-3
SVS horizontal field of view as depicted with black/white lines on the Helionix DMAP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 4
Fig. 7-19-4
SVS and FDS controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 19 − 8
Fig. 7-19-5
SVS indication during excessive nose up (left) or nose−down (right) attitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 − 19 − 10
EFFECTIVITY
7 − xvi
After Helionix Maintenance Release 1
All MANUFACTURER’S DATA Rev. 17.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Page LAVCS principle functionality . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 20 − 2
Fig. 7-20-2
Crew/Operator seat resonator − typical installation . . . . . . . . . . .
7 − 20 − 3
Fig. 7-20-3
Rear Camera − typical installation . . . . . . . . . . . . . . . . . . . . . . . . .
7 − 20 − 5
Fig. 7-20-4
Rear Camera control switches − typical installation . . . . . . . . . . .
7 − 20 − 5
Fig. 7-20-5
Digital multi-purpose camera system − typical installation . . . . .
7 − 20 − 6
Fig. 7-20-6
Compound camera image on MFD4 (typical) . . . . . . . . . . . . . . . .
7 − 20 − 8
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Fig. 7-20-1
MANUFACTURER’S DATA Rev. 22.1
7 − xvii/(7 − xviii blank)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
SECTION 7 DESCRIPTION OF SYSTEMS 7.1
GENERAL
ED
The BK 117 D-2 is a multi-purpose helicopter, utilizing a four-bladed hingeless main rotor system with fibre-reinforced composite blades and a FENESTRON antitorque design. The pilot’s seat is on the RH side.
FUSELAGE
N TR
7.1.1
O
LL
This section contains information that applies specifically to BK 117 D-2 helicopters with HELIONIX Avionic System.
C
O
The primary structure consists mainly of sheet metal and composite material.
PY
N
O
T
The BK 117 D-2 helicopter is accessible through six doors: two hinged doors for the crew/front occupant, two sliding doors for the rear passengers, and two aft clam shell doors for the rear compartment.
C
O
The sliding door windows can be quickly removed to serve as emergency exit. Jettisonable cockpit doors and sliding doors can be installed (optional).
–
TAIL BOOM
LY
7.1.2
LANDING GEAR
TI
7.1.3
O N
O N
The tail boom can be separated from the fuselage, and consists of the horizontal stabilizer, vertical fin, including FENESTRON structure, housing and gearbox.
7.1.4
FO
R
IN
ST
R
U
C
The non-retractable type landing gear of the BK117 D–2 consists of two cross tubes, two skids and two boarding/maintenance steps (standard step or multifunction step). Two landing gear dampers are installed between the forward cross tube and the fuselage on the LH and RH side of the helicopter. The dampers can be covered by a fairing (optional, see Fig. 7-1-1). HELICOPTER DIMENSIONS Fig.7-1-1 shows a three-view drawing of the helicopter with its principal dimensions. For cabin dimensions see Fig.7-1-2. Locations on and within the helicopter can be determined in relation to fuselage stations (F.S. or STA.), waterlines (W.L.), and buttock lines (B.L.), measured in millimeters from known reference points (see Sect. 6 ’’Mass and balance”).
MANUFACTURER’S DATA Rev. 0
7–1–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
3.95 m / 12.95 ft
ED
0.98 m 3.22 ft
0.75 m 2.46 ft
0.45 m 1.46 ft
0.93 m 3.05 ft
1.00 m 3.28 ft
Approx. 3.10 m 10.17 ft
3.46 m 11.35 ft
13.64 m 44.76 ft
O
LL
11.69 m 38.36 ft
1.73 m 5.68 ft 2.40 m 7.87 ft
Fig. 7-1-1
7–1–2
2.72 m / 8.95 ft
2.54 m / 8.33 ft
BKD2_FLH_0198_R
BKD2_FLH_0185_R
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
6.17 m 20.24 ft
Principal dimensions MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
0.15 m 0.48 ft
1.22 m 4 ft
1.3 m 4.26 ft
1.27 m 4.16 ft
0.95 m 3.12 ft
*
1.22 m 4 ft
DESCRIPTION OF SYSTEMS
ED
* or 0.93m S/N20081 and subsequent
1.4 m 4.26 ft
O
T
C
1.55 m 5.047 ft
PY
N
O
1.4 m 4.59 ft
0.62 m 2.03 ft
N TR
O
LL
1.14 m 3.75 ft
O
LY
–
3.42 m 11.23 ft
C
2.26 m 7.41 ft
O N
4.65 m 15.25 ft
0.77 m 2.53 ft
1.7 m 5.57 ft
1.66 m 5.45 ft
1.46 m 4.79 ft
R ST IN R FO
BKD2_FLH_0019_R
1.72 m 5.65 ft
U
C
TI
O N
Floor Level
Shoulder Level
Fig. 7-1-2 MANUFACTURER’S DATA Rev. 0
Cabin dimensions
7–1–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
O
T
C
O
N TR
O
LL
ED
DESCRIPTION OF SYSTEMS
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
Intentionally left blank
7–1–4
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.2
COCKPIT ARRANGEMENT
ED
1
2
3
4
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
6
FO
R
IN
ST
R
U
C
5
Fig. 7-2-1 1 2 3 4 5 6
Cockpit arrangement – typical installation
Overhead panel (see Fig. 7-2-2) Cyclic stick (refer to Para. 7.3.4) Pedals (refer to Para. 7.3.2) Collective lever (refer to Para. 7.3.5) Center console (see Fig. 7-2-7) Instrument panel (see Fig. 7-2-6)
MANUFACTURER’S DATA Rev. 0
7–2–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.2.1
Overhead panel
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
The overhead panel is divided into three sections to provide easy access to the respective circuit breakers or switches.
LY
2
C
TI
O N
O N
1
FO
R
IN
ST
R
U
3
Fig. 7-2-2
Overhead panel – typical installation
1
System 1 circuit breaker panel (see Fig. 7-2-3)
2
System 2 circuit breaker panel (see Fig. 7-2-4)
3
Overhead switch panel (see Fig. 7-2-5)
7–2–2
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.2.1.1 Overhead panel (system 1 circuit breaker panel)
C
O
N TR
O
LL
ED
1
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
2
FO
R
IN
ST
R
3
Fig. 7-2-3
System 1 circuit breaker panel – typical installation
1
Bus control switches (refer to Para. 7.9.2)
2
Shedding buses
3
Essential buses
MANUFACTURER’S DATA Rev. 0
7–2–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.2.1.2 Overhead panel (system 2 circuit breaker panel)
C
O
N TR
O
LL
ED
1
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
2
FO
R
IN
ST
R
3
Fig. 7-2-4
System 2 circuit breaker panel – typical installation
1
Bus control switches (refer to Para. 7.9.2)
2
Shedding buses
3
Essential buses
7–2–4
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
7.2.1.3 Overhead switch panel
Fig. 7-2-5
MANUFACTURER’S DATA Rev. 0
Overhead switch panel – typical installation
7–2–5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.2.2
Instrument panel
NAVD
VMS ALT
DMAP
MISC
NAV
CLOCK
FND
IAS
NAVD
DMAP
MISC
CLOCK
EFB ALT
160
10
DA
hPa
10
TRQ 54.0
%
TOT
N1
HYD B A R
N
N1 %
ENG OIL B A R
N U M
94.0
%
ENG OIL B A R
MGB OIL B A R
B A R
B A R
DH FUEL
Kg
6
FSD
FMS GPS LFMH
0
A C K
O
S
S E L 100.
DH OAT STATUS
REPORT
EPC
CONF
100.
TUNE
0 %
PY
SVS
N2
20
20
10
10
D A
10
10
20
20
33
DTK
B A R O
DA
hPa
DH
3
30
6 E
24
12 21
N A V
N
D H
S
1
15
FSD
A C K
FMS GPS LFMH
0
DH DCPL
SCT
SVS
OAT
3
TI
Instrument panel arrangement – typical installation
U
C
Fig. 7-2-6
O N
O N
LY
–
C
O
SCT
0 %
8
W
T
D A T A
1
15
N
12 21
FF Kg/h
C
FF Kg/h
E 24
DCPL
%
710
94.0
07
100
IAS
1
700
R C N F
NAV
101
TOT
010
3
W
DTK
012
08 10
30
N A V
10
120
B A R O
20
N
33
10
09
10
20
29 . 69 in
011 140 D H
TRQ 55.0
O
10
S Y S T
N TR
20
10
D A
O
20
8
LL
101 1
ED
2
1
IESI
2
Warning Unit (refer to Para. 7.13.3.1)
3
Engine control panel (refer to Para. 7.5.2.2)
FO
R
IN
ST
R
1
7–2–6
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
N TR
O
LL
ED
O N
O N
LY
–
C
O
PY
N
O
T
C
O
R
IN
ST
R
U
C
TI
FO
7–2–7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
ED
O
LL
N TR
O
O
T
C
PY
N
O
–
C
FO
R
IN
ST
R
U
C
TI
O N
LY
O N
7–2–8
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Vertical rack (optional)
LL
ED
PY
N
O
T
C
O
N TR
O
O N
LY
–
C
O
IN
ST
R
U
C
TI
O N
FO
R
7–2–9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Chart holder NOTE
LL
ED
O
N TR
O
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
7 – 2 – 10
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Holder for tablet PC (optional)
NOTE D D
N TR
O
LL
ED
O
O
T
C
O
PY
N
–
C
R
U
C
TI
O N
O N
LY
IN
ST
FO
R
7 − 2 − 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Copilot’s armrest (optional)
LL
N TR
O
ED
O
O N
O N
LY
–
C
O
PY
N
O
T
C
U
C
TI
Description
ST
R
Pos.
FO
R
IN
7 − 2 − 12
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.3
FLIGHT CONTROL SYSTEM AND AFCS
ED
Main rotor head
O
LL
Tail rotor actuator
N TR
Main rotor actuators
Mixing lever gear unit
Control rods
O
T
C
O
SEMA type actuators, cyclic and collective control
–
C
O
PY
N
Ball bearing control cables (flexball), cyclic and collective control
O N
LY
SEMA type actuators, tail rotor control
O N
Ball bearing control cable (flexball), tail rotor control
R
U
C
TI
Cyclic stick
Collective lever
IN
ST
Pedals
PVC protection tube
FO
R
Steel outer races (2) Teflon ball cage
BKD2_FLH_0044_R
Flexible steel tube Movable steel center blade Trim actuators
Fig. 7-3-1 MANUFACTURER’S DATA Rev. 0
Steel ball of linear ball arrangement (teflon ball cage not shown) Flight control system and AFCS
7–3–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.3.1
Main rotor controls
ED
The pilot’s control inputs are applied through the cyclic stick and the collective lever and are transmitted through three ball bearing control cables (flexballs) (see Fig. 7-3-1). These flexballs are leading through the nose section and then up to the main rotor actuators on the roof. The flexballs transmit the control inputs via their center blade to the input control levers of the main rotor actuators. The control inputs are boosted by the main rotor actuator (refer to Para. 7.4). The boosted inputs leave the main rotor actuators at the output boost pistons and are transmitted via control rods to the mixing lever assembly. There, they are combined to an input that tilts the swash plate in the desired direction (cyclic stick input), or moves the sliding sleeve up or down, which creates the desired simultaneous variation of the angle of incidence on all four rotor blades (collective lever input).
Tail rotor control
O
7.3.2
N TR
O
LL
The AFCS provides additional control inputs to the main rotor controls via trim actuators and SEMA type actuators. Refer to Para. 7.3.6.5 and 7.3.6.6 for AFCS control inputs.
N
O
T
C
The pilot’s control inputs are applied through the pedals and transmitted to the tail rotor actuator via a flexball (see Fig. 7-3-1). The tail rotor actuator boosts the control inputs and transmits them to the tail rotor blades via the control linkage inside the tail rotor gear box.
Dual/Single control
–
7.3.3
C
O
PY
The AFCS provides additional control inputs to the tail rotor control via trim actuators and SEMA type actuators. Refer to Para. 7.3.6.5 and 7.3.6.6 for AFCS control inputs.
O N
LY
The cyclic stick, collective lever and pedals on the copilot’s side are removable via quick-release connections for single pilot operation.
TI
O N
Dual control covers protect the control system from unintentional control inputs by a person occupying the copilot’s seat.
FO
R
IN
ST
R
U
C
The cover kit comprises a metal pedal cover, a metal blade which covers the stump of the cyclic stick, and a cover to protect the stump of the collective pitch lever on the copilot’s side.
7–3–2
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Cyclic stick
ED
O
LL
N TR
O
O
T
C
O N
O N
LY
–
C
O
PY
N
U
R
SWITCH
C
TI
IN
R
FO
ST
7–3–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Collective lever
ED
C
O
PY
N
O
T
C
O
N TR
O
LL
–
TI
U
C
LY
O N
O N
FO
R
IN
ST
R
7–3–4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
SWITCH
LL O N TR O C T O N
AFCS
PY
ED
C
O
O N
LY
–
O N
C
TI
R
U
FO
R
IN
ST
7–3–5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
O
LL
ED
PY
N
O
T
C
O
N TR
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
FO
R
7–3–6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.3.6.2 Autopilot control panel (APCP) The APCP (see Fig. 7-3-5) is used to control the current configuration of the AFCS and engage/disengage various modes, as well as adjust their references. 1
2
3
A.TRIM
BKUP
AP1
AP2
OFF
OFF
OFF
OFF
CRHT
IAS
ALTA
LL
ED
11
4
O
6
ALT
N TR
BKD2_FLH_0048_R
TRK
5
ON
8
7
LY
Autopilot control panel (APCP)
1
A.TRIM (push button)
2
BKUP (push button)
3
AP1 (push button)
4
AP2 (push button)
Engages / disengages AP2. OFF illuminated when disengaged.
5
FO
O N
Fig. 7-3-5
HDG
–
C
O
VS
9
PY
10
N
O
T
C
O
FPA
ALTA (rotary switch with push function)
Adjusts altitude reference. Engages / disengages ALT.A mode. Green light illuminated when engaged.
6
IAS (rotary switch with push function)
Adjusts airspeed reference. Engages / disengages IAS mode. Green light illuminated when engaged.
7
ALT (push button)
Engages / disengages ALT mode. ON illuminated when engaged.
8
HDG/TRK (rotary switch with push function)
Adjusts heading or track angle reference. Engages / disengages HDG mode or TRK mode. Green light illuminated when engaged.
O N
Engages / disengages auto-trim functions for pitch, roll and yaw. OFF illuminated when disengaged.
R
IN
ST
R
U
C
TI
Engages / disengages back-up SAS. OFF illuminated when disengaged.
MANUFACTURER’S DATA Rev. 0
Engages / disengages AP1. OFF illuminated when disengaged.
7–3–7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
9
HDG–VS/ TRK–FPA (butterfly rotary switch)
Selects between mode combinations HDG+VS (traditional) or TRK+FPA (GPS based).
10 VS/FPA (rotary switch with push function)
Adjusts vertical speed or flight path angle reference. Engages / disengages VS mode or FPA mode. Green light illuminated when engaged.
11 CRHT (rotary switch with push function)
Adjusts radio height reference. Engages / disengages CRHT mode. Green light illuminated when engaged.
LL
ED
7.3.6.3 Collective lever switches
Up/down: Changes upper mode references according to currently active vertical modes (ALT, CRHT, FPA, VS). Left / right: Changes the references of the active upper modes HDG or TRK.
PY
N
O
T
C
O
BEEP TRIM
N TR
O
The collective lever switches for AFCS are identical for pilot and copilot. Refer to Fig. 7-3-3 for arrangement of the switches.
–
C
O
Provides manual trim of collective and pedals in basic attitude hold mode if no upper modes engaged. Opens clutch in collective trim unit, reduces friction felt by the pilot.
GA
Activates GA mode.
O N
O N
7.3.6.4 Cyclic stick switches
LY
TRIM REL
FO
R
IN
ST
R
U
C
TI
The cyclic stick switches for AFCS are identical for pilot and copilot. Refer to Fig. 7-3-2 for arrangement of the switches.
7–3–8
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
AP/BKUP ON
Engages / resets AFCS as follows: – Left press simultaneously engages AP1 and sets back-up SAS in stand-by. It also tries to recover a fully functional state of AP1 by resetting transient failures. – Right press simultaneously engages AP2 and sets back-up SAS in stand-by. It also tries to recover a fully functional state of AP2 by resetting transient failures. – Single forward press also provides an AFCS recovery function, aiming to recover a fully functional state by engaging/resetting both APs according to the following logic:
LL
ED
– If AP1 and AP2 are OFF, they are reengaged and transient failures are reset.
O
N TR
O
– If one AP was deactivated by the system, it is considered to have a failure and it is not automatically reengaged. The active AP is reset in particular transient failures.
C
– If both APs are ON, they are both reset.
O
T
If back-up SAS is OFF, forward press sets back-up SAS in stand-by.
C
Disengages AFCS in 2 steps: – Press once for AP1 and AP2 disconnection.
LY
–
AP/BKUP CUT
O
PY
N
– Double forward press is used in flight for a quick engagement of traditional upper modes (ALT, IAS, HDG/TRK). It establishes a safe flight attitude, e.g. in case of disorientation.
O N
Adjusts longitudinal and lateral mode references both in hover and forward flight. – In backup SAS mode and DSAS (A.TRIM off), it performs a manual beep trim.
TI
BEEP TRIM (cyclic)
O N
– Re-press after 0.3 sec for disconnection of back-up SAS.
U
C
– In ATT mode, it adjusts the attitude reference (pitch and roll axis).
ST
R
– Forward / aft adjusts the reference of the upper modes IAS, GTC, or GTC.H.
FO
R
IN
– Left / right adjusts the reference of the upper modes HDG, TRK, GTC, or GTC.H.
BEEP TRIM (collective)
Adjusts collective pitch and directional mode references both in hover and forward with upper modes engaged. – In DSAS (A.TRIM off) and ATT mode, the collective trim performs a manual beep trim. – In ATT mode in hover, the directional trim slews the reference for HDG. – In 3 and 4-axis mode, it slews references for ALT, CR.HT, VS/FPA, HDG/ TRK.
TRIM REL
Opens the clutch in cyclic trim units and thus de-activates the force feel system of cyclic trim units.
MANUFACTURER’S DATA Rev. 10
7–3–9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
AP UM OFF
Disarms and disengages all upper modes. When pressed for more than 1 sec on ground with autopilot engaged, it will approximately center cyclic stick and pedals. When pressed for more than 1 sec in flight, it will erase pre-selected references of upper modes (i.e. ALT.A).
GTC
Single press: – Engage GTC mode Double press: – Engage GTC.H mode
LL
ED
7.3.6.5 SEMAs
C
O
N TR
O
The pitch, roll and collective SEMAs (see Fig. 7-3-4) are integrated in the mechanical control rods above the cabin roof. Two SEMAs each are installed in the pitch and roll axis, one SEMA is installed in the collective axis. In the yaw axis, two SEMAs are installed between the end of the flexball and the tail rotor actuator. One yaw SEMA is installed inside and one outside the vertical fin structure.
LY
–
C
O
PY
N
O
T
The SEMAs operate in series with the pilot’s controls. They transmit AFCS control inputs to the main rotor actuators and tail rotor actuator without movement of the cyclic stick, collective lever or pedals. The SEMAs have a limited control authority, their control inputs do not use the total control travel of the flight control system. The control authorities are limited to the following portions of total control travel: – roll axis (both actuators): ±19%
O N
– pitch axis (both actuators): ±11%
– collective axis (one actuator): ±7%
O N
– yaw axis (both actuators): ±21.5%
FO
R
IN
ST
R
U
C
TI
For safety reasons, the back-up SAS function uses only one SEMA actuator (SEMA set No. 1) in pitch, roll, and yaw axis.
7 – 3 – 10
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.3.6.6 Trim actuators
ED
The trim actuators (see Fig. 7-3-4) are installed under the cabin floor. Each trim actuator is connected to one axis of the flight control system. All trim actuators transmit control inputs from the AFCS for automatic trim control (pitch, roll, and yaw axis) and automatic power setting (collective axis). In addition, the trim actuators create an artificial control force to give the pilot a feedback about his control inputs on the cyclic stick, collective lever and pedals. With the respective TRIM REL push button, the pilot can change the zero force position of the cyclic stick and the collective lever. If the AFCS is disengaged, the zero force position of the cyclic stick can also be changed by using the BEEP TRIM switch.
O
LL
7.3.6.7 General AFCS functions
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
AFCS engagement / disengagement: The autopilots AP1 and AP2 are engaged via AP1 and AP2 pb on the APCP (refer to Para. 7.3.6.2), or via AP/BKUP ON sw on the cyclic (refer to Para. 7.3.6.4). By default, the ATT mode will be engaged. Ground / flight state detection logic: The condition ”aircraft on ground” is detected by use of collective pitch, MGB pressure, N1, vertical speed and angular rates. When ground is detected, the upper modes are forbidden and ATT mode is inhibited. Flight envelope protections for operation in upper modes: – Air speed limitation: an airspeed protection limits the air speed between 30 kts and VNE when vertical modes are engaged on the pitch axis (3 axis mode). When the airspeed reduces below 60 kt, the 4 upper axis mode is automatically engaged. – Attitude limitation: the commanded pitch attitude is limited between –12_ and + 14_, commanded roll attitude is limited to ±30_. – Altitude limitation (automatic level-off upon ground proximity): if IAS, VS, FPA, GS, V.APP or ALT.A mode is engaged, the mode is changed automatically to ALT mode when approaching ground. The ALT mode uses radio height information to level-off the aircraft at 150ft (65 ft when GS or V.APP mode are active) to avoid controlled flight into terrain.
FO
R
Recovery function: The recovery function tries to recover a fully functional state by engaging/resetting the APs. It is performed by double pressing the AP/BKUP ON sw on cyclic forward (refer to Para. 7.3.6.4). It engages IAS, HDG/TRK and ALT (4 axis mode) simultaneously from any AFCS state (OFF, backup SAS only, DSAS or ATT mode). From unusual attitude, it obtains wings level and captures and maintains airspeed, altitude, and heading/track angle at the time of engagement. CAUTION
WHEN THE MODE IS ENGAGED FROM HOVER, THE AIRCRAFT WILL AUTOMATICALLY ACCELERATE TO 30 KT.
Back-up SAS: The back-up SAS mode provides stability augmentation on pitch, roll and yaw axes in case of loss of both autopilots. It is implemented in the stand-by instrument (IESI). MANUFACTURER’S DATA Rev. 9
7 – 3 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.3.6.8 AFCS indications The following AFCS information can be displayed on the FND (see Fig. 7-3-6): – Upper mode references on dedicated flight data scales such as: altitude, airspeed, vertical speed, ground speed. – Upper mode status information on the AFCS strip, such as: engaged/armed modes, mode change or loss indication, excessive deviation from mode reference, hands-on/feet-on detection, trim centering, axis degradation. Refer to Para. 7.3.6.9 for a detailed description of the AFCS strip.
ED
– Master list messages for the AFCS. Refer to Para. 7.13.6 for complete list of master list messages.
DMAP
FMS1 FMS2
+ C T R S –
EFB
ALT
RA
HDG
101
DME ADF
6
20 10
VOR1 VOR2
4
100
2
80
10
10
20
20
R N G
–
TRIMS ACTUATORS
ROLL
AP2
O N
AP1
+ L U M –
PREV
DATAB
LOAD
O N
YAW
MAINT
+ B R G –
+ L U M –
N
33
600 DA
17
17
16
16
1 500
15
14
14
13
13
30
D H B A R O
1013 200 hPa DH
6 E
24
12 21
S
15
DTK
DCPL
D A
3
W
N 000 A FMS V INS/GPS 6.0NM 4 min
2
A C K
AP CONTROL
415 Kg SCT
SVS
OAT 20
+ B R G –
3
TI
1
BKD2_FLH_0413_R
PITCH
LY
COLL CTRL PANEL
3
VY
C
AFCS
18
10
PY
GPS1 GPS2 IESI
+ C T R S –
CLOCK
IAS
20
N
120
O
R C N F
C
VMS
T
NAVD
O
FND
MFD – FND
O
MFD – VMD
N TR
O
LL
Additional status information regarding AFCS components can be displayed on the AFCS status area on the VMD (see Fig. 7-3-6). Refer to Para. 7.3.6.10 for a detailed description of the AFCS status area.
AFCS indication on VMD and FND – typical display
ST
R
U
C
Fig. 7-3-6
AFCS status area
2
AFCS strip
3
Master list area
FO
R
IN
1
For indications on APCP, refer to Para. 7.3.6.2. For indications on warning panel, refer to Para. 7.13.3.1. 7.3.6.9 AFCS strip The AFCS strip (see Fig. 7-3-7) is divided into two rows and three colums. The upper row indicates the engaged mode(s), the lower row indicates the armed mode(s). The colums – when AFCS is operated in 4-axis mode – correspond to the aircraft axes: – left column: collective axis – center column: yaw and roll axis – right column: pitch axis
7 – 3 – 12
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
HDG LOC
IAS
AFCS strip – typical display
ED
Fig. 7-3-7
BKD2_FLH_0199_R
ALT GS
5
Lower row (indication of armed mode(s))
2
Upper row (indication of engaged mode(s))
3
Left column (collective axis)
4
Center column (yaw / roll axis)
3
Right column (pitch axis)
O
T
C
O
N TR
1
LL
1
4
O
2
3
PY
N
7.3.6.10 AFCS status area
–
C
O
The AFCS status area (see Fig. 7-3-8) shows the status of all AFCS components. The status of each component is represented by its color: Status
Green
active / nominal
Cyan
active, but stand-by
Amber
degraded
Grey
inactive:
C
TI
O N
O N
LY
Color
R
– system deliberately deactivated by the pilot. failed
FO
Red
IN
ST
R
U
– failed but AFCS failure can be recovered via AP/BKUP ON sw on cyclic, or
AFCS
TRIMS ACTUATORS COLL
CTRL PANEL
AP2
ROLL YAW
Fig. 7-3-8 MANUFACTURER’S DATA Rev. 2
BKD2_FLH_0217_R
BACKUP AP1
PITCH
AFCS status area – typical display
7 – 3 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.3.6.11 AFCS architecture
ED
APCP
LL
SEMA1 Pitch
O
Backup (IESI)
N TR
SEMA1 Roll
FOG
N
O
T
AMC1
Pitot/Static
AMC2
LY
–
GPS / FMS
C
OAT
O
PY
ADU
O N
O N
RADALT
U
C
TI
Warning Panel
MFD1 MFD2
SEMA2 Roll SEMA2 Yaw SEMA2 Coll.
Trim Act. Pitch Trim Act. Roll Trim Act. Yaw Trim Act. Coll.
FMS / Radio Nav. / RADALT
R
IN
ST
R
MFD4
SEMA2 Pitch
FO
BKD2_FLH_0049_R
SEMA1 Yaw
C
O
IESI
Fig. 7-3-9
7 – 3 – 14
AFCS – simplified schematic
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.3.6.12 AFCS coupling to navigation sources The autopilot can be coupled or armed to available navigation sources on any MFD. The navigation source and autopilot coupling/arming information is displayed on the MFD in FND format (see Fig. 7-3-10) or NAVD format. The navigation source coupled/armed to the autopilot is displayed in cyan inverse video while coupling/arming, green inverse video when coupled. Press NAV key on the MFD until the desired navigation source is displayed.
Coupling / decoupling
Depending on the present coupling status, the label of the coupling key is CPL, DCPL, or DISARM, or it disappears.
ED
Selection of navigation source
O
LL
CPL: couples the autopilot to the selected navigation source.
N TR
DCPL: decouples the autopilot from the coupled navigation source.
O
DISARM: disarms the autopilot.
N
RNP
PY
000 3.00 FMS
INS/GPS
6.0 NM 12 min
O C
–
+ L U M –
DTK
CPL
O N
LY
BKD2_FLH_0254_R
N A V
O
T
C
No label: coupling inactive.
AFCS coupling to navigation sources
TI
O N
Fig. 7-3-10 Coupling on MFD 1:
FO
R
IN
ST
R
U
C
If the autopilot is coupled on the copilot’s MFD (MFD 1), this MFD is designated as master MFD and coupling to another MFD is not possible. To stay coupled, the navigation source must remain displayed on the MFD. If the navigation source on MFD 1 is changed, or if a format without navigation source display (e.g. VMS) is selected on MFD 1, the AP mode on the AFCS strip will flash in inverse video and will deactivate, after 10 sec in, if the navigation source is not returned to MFD 1.
Coupling on MFD 2 or MFD 4: If the autopilot is coupled on the pilot’s MFD (MFD 2) or center MFD (MFD 4), these MFDs are both designated as master MFDs. In this case, coupling on MFD 1 is not possible (the CPL label is not displayed). If the two master MFDs are set to the same navigation source, the NAV source will be indicated on both MFDs in inverse video. One of the MFDs can be switched to display a page without navigation source or to another navigation source without impact on the autopilot coupling. As long as one of the MFDs on the master side displays the coupled source, the autopilot coupling remains unaffected. If the coupled navigation source is no longer displayed on any of the master side MFDs, the AP mode on the AFCS strip will flash in inverse video and will deactivate, after 10 sec, if the navigation source is not returned to one of the displays.
MANUFACTURER’S DATA Rev. 2
7 – 3 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.3.6.13 AFCS modes The AFCS provides the following modes for automatic flight: Basic stabilisation: – ATT mode (Long Term Attitude Hold): The ATT mode is engaged by default when the AFCS is engaged, and when an upper mode is disengaged. – DSAS mode (Digital SAS) Basic upper modes: – ALT mode (Altitude Hold) – HDG mode (Heading)
ED
– IAS mode (Indicated Air Speed)
LL
– VS mode (Vertical Speed)
N TR
O
– ALT.A mode (Altitude Acquire) – GA mode (Go Around)
C
O
– CRHT mode (Cruise Height)
O
T
Navigation and approach upper modes: – LOC mode (Localizer)
PY
N
– GS mode (Glide Slope)
–
– APP mode (Approach)
C
– NAV mode (En-Route Navigation)
O
– VOR mode (VHF Omnidirectional Radio Range)
O N
LY
– V.APP mode (Vertical Approach)
O N
GPS based operation: – FPA mode (Flight Path Angle)
TI
– TRK mode (Track Angle)
C
– GTC mode (Ground Trajectory Control)
FO
R
IN
ST
R
U
– GTC.H mode (Ground Trajectory Control with Hover hold)
7 – 3 – 16
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ATT MODE Description
Provides long term attitude stabilization on pitch and roll axes for hands-off operation. Stabilizes and holds heading at hover and low airspeed. Stabilizes and provides turn coordination in forward cruise and turning flight. Cross couplings between helicopter axes are automatically compensated. Press AP1 pb (1, Fig. 7-3-11) and AP2 pb (2) on APCP .
ED
Engagement by pilot action
LL
or:
O
LH and RH press AP/BKUP ON sw (3) on cyclic.
N TR
or:
C
O
Single fwd press AP/BKUP ON sw (3) on cyclic, (when engines are on). Engaged by default following AFCS engagement.
O
T
Automatic engagement
N
Engaged following disengagement of upper modes. ATT mode is a prerequisite for selecting an upper mode.
Display
No mode related displays on APCP or on MFDs.
Fly-through mode: Hover follow-up
When in hover (i.e. below 30 knots with a hysteresis to 40 knots), the AFCS follows the cyclic stick movement of the pilot with the cyclic trim motors. During maneuvers with rates above 1_/sec, the follow-up is momentarily stopped. In the hover domain, the ATT mode holds the heading on which the aircraft has stabilized.
TI C U
ST
R
Fly-through mode: Beep trim
O N
O N
LY
–
C
O
PY
Compatibility with other modes
Change attitude references in pitch and roll axis using BEEP TRIM sw (4) on cyclic. Change heading reference in yaw axis using BEEP TRIM sw (6) on collective. When the pilot overrides the spring forces, the trim acutator command is automatically disabled and the AFCS automatically switches to the CSAS mode (hands-on mode) on the relevant axis. After fly-through action, the helicopter returns to the original attitude.
Fly-through mode: Trim release
When pressing the TRIM REL pb (5) on cyclic, the cyclic trim actuators are declutched and the AFCS switches to the CSAS mode. After fly-through action, the AFCS holds the new pitch and roll attitude references.
FO
R
IN
Fly-through mode: Override against spring loads
MANUFACTURER’S DATA Rev. 2
7 – 3 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Fly-through mode: Beep trim with forces against spring loads
When the pilot presses the BEEP TRIM sw (4) on cyclic and simultaneously overrides the spring loads, the attitude reference slowly synchronises to the current attitude. The trim follows the stick position.
Trim re-centering function
The AFCS moves the trim acutators to align the control positions with the AFCS commands. This function enables re-centering of the SEMAs to avoid a long lasting saturation of the SEMAs.
LL
ED
In case of long lasting saturation, a respective out-of-trim indication (see 3.2.3.8) is displayed on the FND AFCS strip, indicating the required corrective action to counteract the saturation.
AP2
OFF
OFF ALTA
4
O N
LY
–
IAS
PY
AP1
OFF
O
BKUP
OFF
C
A.TRIM
3
N
2
1
CRHT
O
T
C
O
N TR
O
The trim-recentering function is inactive during fly-through actions, except in hover follow-up and beep trim with forces against spring loads.
TRK
ALT ON
FO
R
IN
ST
R
U
C
TI
O N
FPA
5
BKD2_FLH_0200_R
6
Fig. 7-3-11
7 – 3 – 18
ATT mode – Engagement / disengagement MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
DSAS MODE Degraded mode, provides stability augmentation on max. three axes. Auto-trim function is inhibited on affected axes.
Engagement by pilot action
Press A.TRIM pb (1, Fig. 7-3-12) on APCP.
Automatic engagement
Engaged on affected axis only in case of a trim (actuator) failure or if the hands-on detection (override detection) has failed.
Display
APCP: amber OFF caption on A.TRIM pb if disengaged by pressing A.TRIM pb.
ED
Description
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
FND AFCS strip (4): DSAS label on affected axis. (2 and 3, Fig. 7-3-12)
MANUFACTURER’S DATA Rev. 9
7 – 3 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
1
A.TRIM
BKUP
AP1
AP2
OFF
OFF
OFF
OFF
CRHT
IAS
ALTA
TRK
ALT
LL
ED
ON
FPA
17
17
10
10
16
16
1 500
15
10
10
14
14
20
20
13
13
100
VY
C
T DSAS
DTK
A C K 415 Kg SVS
+ B R G –
OAT 20
DSAS
one axis affected only
3
DSAS mode – Engagement / disengagement and indications
FO
R
IN
ST
Fig. 7-3-12
DSAS
U
C
TI
SCT
max. three axes affected
R
BKD2_FLH_0415_R
S
15
N 000 A V FMS INS/GPS 6.0NM 4 min DCPL
O
E 12 21
DSAS
–
6
W
DSAS or
3
30 24
+ L U M –
B A R O
600 1013 200 DA hPa DH
N
33
R N G
DSAS
D H
LY
80
3
D A
N
20
O N
2
20
O N
4
18
120
PY
101 6
2
+ C T R S –
CLOCK
DSAS
O
DSAS
C
DSAS
O
N TR
O
4
7 – 3 – 20
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ALT MODE Maintains the current barometric altitude upon engagement. Minimum altitude (ground height): 30 ft
Engagement by pilot action
Maximum vertical speed to acquire the new reference following a beep trim input: 500 ft/min above 40 kt, going down to 200 ft/min at 25 kt and below. The mode is controlled through the pitch (3-axis mode) or the collective axis (4-axis mode). Below 60 kt the mode controls the collective axis. It shifts to the pitch axis if the airspeed exceeds 65 kt for at least 5 sec. Press ALT pb (1, Fig. 7-3-13) on APCP.
ED
Description Conditions & Limitations
LL
or:
N TR
O
Double fwd press AP/BKUP ON sw (2) on cyclic (simultaneously engages IAS, HDG/TRK and ALT). Reversion from ALT.A mode to ALT mode when final reference becomes visible on the altitude scale. Reversion from any vertical upper mode (except CRHT) to ALT mode when ground proximity is detected in descent (refer to Para. 7.3.6.7) APCP: green ON caption on ALT pb (1).
N
O
T
C
O
Automatic engagement
PY
Display
–
C
O
FND altitude scale (7): reference indicated by green triangle shaped bug. Bug displayed as follows:
LY
– green if mode engaged,
O N
– flashing white-green while changing reference.
O N TI
IN
ST
R
U
C
Reference management
FND AFCS strip (8): ALT label in pitch or collective axis column (5, 6) The altitude reference is set to the current barometric altitude upon mode engagement. When the baro setting is changed, the original reference altitude will be maintained. With ALT mode engaged, change altitude reference using BEEP TRIM sw (4) on collective (75 ft/sec). Press ALT pb (1) on APCP.
FO
R
Disengagement
or: Press AP UM OFF pb (3) on cyclic. or:
Compatibility with other modes
Engage incompatible mode. ALT mode incompatible with VS, ALT.A, GA, CHRT, FPA, V.APP or GS mode. Engagement of these modes will disengage ALT mode. ALT mode shifted from pitch axis to collective axis when IAS mode engaged (IAS mode engages automatically below 60 kt).
Override
MANUFACTURER’S DATA Rev. 9
Altitude reference not changed by override of spring forces or force trim release.
7 – 3 – 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
A.TRIM
BKUP
AP1
AP2
OFF
OFF
OFF
OFF
CRHT
IAS
ALTA
1 TRK
ALT ON
FPA
O
LL
ED
2
O
N TR
3
LY
–
C
O
PY
N
O
T
C
4
O N DSAS
101 20
20
10
10
100 10 80
20
VY
10
FO
33
R N G
17
3
20
R
2
N
600 DA
30
17
16
16
1 500
15
14
14
13
13
BKD2_FLH_0416_R
ALT mode engaged in pitch axis (3–axis use)
TI
DSAS
B A R O
1013 200 hPa DH
6 16
15
DTK
N 000 A V FMS INS/GPS 6.0NM 4 min
A C K 415 Kg SVS
OAT 20
1 500 + B R G –
7
14 13
Fig. 7-3-13
7 – 3 – 22
DSAS
D H
12
SCT
ALT
or
E
24
DCPL
ALT mode engaged in collective axis
D A
6
S
DSAS
3
W
21
DSAS
R
120
ST
4
18
IN
6
+ C T R S –
CLOCK
C
DSAS
ALT
U
ALT
+ L U M –
5
O N
8
ALT mode – Engagement / disengagement and indications
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
HDG MODE Description
Maintains current heading upon engagement, or acquires and holds a pre-selected heading.
Conditions & Limitations
Maximum turn rate to acquire reference: 3 deg/sec in forward flight, 10 deg/sec in hover
Engagement by pilot action
ED
The mode controls the heading on the roll axis or on the yaw axis, depending on the heading error and the flight condition. Press HDG/TRK rotary sw (2, Fig. 7-3-14) on APCP (butterfly rotary sw in HDG–VS mode combination).
LL
or:
N TR
O
Double fwd press AP/BKUP ON sw (3) on cyclic simultaneously engages IAS, HDG and ALT (butterfly rotary sw on APCP in HDG–VS mode combination). Reversion from engaged TRK mode if butterfly rotary sw on APCP is set from TRK–FPA mode combination to HDG–VS mode combination. APCP: green light (1) next to HDG/TRK rotary sw (2).
O
T
C
O
Automatic engagement
N
Display
O
PY
FND heading scale (8): reference indicated by triangle as follows:
–
C
– cyan if mode not engaged,
LY
– green if mode engaged,
O N
– flashing white-green while changing reference.
FO
R
IN
ST
R
U
C
TI
O N
Reference management
FND AFCS strip (9): HDG label in yaw/roll axis column (7). To pre-select heading reference, turn HDG/TRK rotary sw (2) on APCP (1 deg/tick) before mode engagement. Pre-selection is kept in case of recovery action on cyclic. If no heading reference pre-selected, reference is set to current heading upon mode engagement. With HDG mode engaged, change heading reference using: – BEEP TRIM sw (4) on cyclic (5 deg/sec) in forward flight (except when GTC/GTC.H is engaged), or – BEEP TRIM sw (6) on collective at all speeds, or – HDG/TRK rotary sw (2) on APCP – In hover, a pedal input will slew the HDG reference. When the pedal input is stopped, the HDG will be maintained.
MANUFACTURER’S DATA Rev. 2
7 – 3 – 23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Disengagement
Press HDG/TRK rotary sw (2) on APCP. or: Set butterfly rotary sw on APCP to TRK–FPA mode combination to revert to TRK mode. or: Press AP UM OFF pb (5) on cyclic. or: Engage incompatible mode. HDG mode incompatible with GTC, GTC.H, LOC, NAV, APP or VOR mode. Engagement of these modes will disengage HDG mode.
LL
ED
Compatibility with other modes
Heading reference not changed by override of spring forces or force trim release.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
Override
7 – 3 – 24
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
A.TRIM
BKUP
AP1
AP2
OFF
OFF
OFF
OFF
CRHT
IAS
ALTA
VS
ALT ON
HDG
2
1
N TR
O
LL
ED
3
O
4
C
6
C
O
PY
N
O
T
5
LY
–
9
O N
7
HDG
14
14
13
13
3
20
IN 33
N
600 DA
R FO
BKD2_FLH_0417_R
8 33
24
12 15
415 Kg
Fig. 7-3-14
SVS
OAT 20
3 6
W
A C K
SCT
N
30
E
N 000 A FMS V INS/GPS 6.0NM 4 min DCPL
B A R O
1013 200 hPa DH
DTK
+ L U M –
DSAS
D H
6
S
HDG
D A
3
30
W
21
ALT
TI 15
10
ST
20
VY
R N G
16
1 500
10
100 80
17
16
20
10
10 2
17
20
C
120
U
4
18
R
6
CLOCK
DSAS
101
+ C T R S –
O N
ALT
+ B R G –
E
24
12 21
S
15
HDG mode – Engagement / disengagement and indications
MANUFACTURER’S DATA Rev. 0
7 – 3 – 25
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
IAS MODE
Description
Maintains current indicated airspeed upon engagement, or acquires and holds a pre-selected indicated airspeed.
Conditions & Limitations
Minimum airspeed: 30 kt Maximum acceleration to acquire reference: 1.3 kt/sec The mode controls the pitch axis. Press IAS rotary sw (1, Fig. 7-3-15) on APCP.
LL
Engagement by pilot action
ED
Maximum deceleration to acquire reference: 1.5 kt/sec
O
or:
N TR
Double fwd press AP/BKUP ON sw (3) on simultaneously engages IAS, HDG/TRK and ALT.
cyclic
If airspeed drops below protection speed (60 kt) while vertical mode (ALT, ALT.A, VS, FPA, V.APP or GS) is engaged on the pitch axis, and if collective axis is available, vertical mode will be transferred to collective axis and IAS mode engaged in pitch axis.
Display
APCP: green light (2) next to IAS rotary sw (1).
C
O
PY
N
O
T
C
O
Automatic engagement
LY
–
FND airspeed scale (7): reference indicated by triangle displayed as follows:
O N
– cyan if mode not engaged, – green if mode engaged,
O N
– flashing white-green while changing reference.
C U
FO
R
IN
ST
R
Reference management
TI
FND AFCS strip (8): IAS label in pitch axis column (6). To pre-select airspeed reference, turn IAS rotary sw (1) on APCP (1 kt/tick) before mode engagement. If no airspeed reference pre-selected, reference is set to current airspeed upon mode engagement. With IAS mode engaged, change airspeed reference between 30 kt and VNE using BEEP TRIM sw (4) on cyclic (8 kt/sec) or IAS rotary sw on APCP. NOTE – The reference cannot be beeped above VNE, except for the power-off VNE. – In V.APP mode, the reference cannot be beeped above the maximum airspeed for a 1000 ft/min rate of descent.
Disengagement by pilot action
Press IAS rotary sw (1) on APCP. or: Press AP UM OFF pb (5) on cyclic.
7 – 3 – 26
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Compatibility with other modes
IAS mode incompatible with GTC and GTC.H mode. Engaging these modes will automatically disengage IAS mode.
Override
Airspeed reference not changed by override of spring forces or force trim release. 1
3
A.TRIM
BKUP
AP1
AP2
OFF
OFF
OFF
OFF ALTA
TRK
4
LL
IAS
5
ALT
O
CRHT
O
T
C
O
N TR
ON
FPA
ED
2
6
2
20
10
10
100 80
10
10
20
20
VY
13
15 14
D H
13
B A R O
120
3
C U
R
S
7
E
12
100
15 A C K
ST
IN DCPL
14
SCT
SVS
415 Kg OAT 20
+ B R G –
80 VY
R
+ L U M –
FO
BKD2_FLH_0418_R
21
DTK
16
1 500
IAS
6
W
N 000 A V FMS INS/GPS 6.0NM 4 min
16
D A
TI
30 24
17
600 1013 200 DA hPa DH
N
33
R N G
3
17
HDG
O N
20
O N
4
18
120
ALT
–
IAS
101 6
+ C T R S –
CLOCK
HDG
LY
ALT
C
O
PY
N
8
Fig. 7-3-15
IAS mode – Engagement / disengagement and indications
MANUFACTURER’S DATA Rev. 2
7 – 3 – 27
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
VS MODE
Description
Maintains current vertical speed upon engagement, or acquires and holds a pre-selected vertical speed.
Conditions & Limitations
The upper reference is limited to +2500 ft/min. The lower reference is reduced from –2500 ft/min at 55 kt to –300 ft/min at 25 kt and below.
ED
The mode controls the pitch or the collective axis, depending on airspeed and availability of pitch and collective axis.
O
LL
Below 60 kt the mode controls the collective axis. It shifts to the pitch axis if the airspeed exceeds 65 kt for at least 5 sec. Press VS/FPA rotary sw (1, Fig. 7-3-16) on APCP (butterfly rotary sw in HDG–VS mode combination).
Automatic engagement
Reversion from engaged FPA mode if butterfly rotary sw on APCP is set from TRK–FPA mode combination to HDG–VS mode combination.
O
T
C
O
N TR
Engagement by pilot action
PY
N
Engaged during ALT.A mode acquisition phase, or after pressing GA pb (5) on collective. APCP: green light (2) next to VS/FPA rotary sw.
C
O
Display
LY
–
FND vertical speed scale (8): reference indicated by triangle displayed as follows:
O N
– cyan if mode not engaged, – green if mode engaged,
O N
– flashing white-green while changing reference.
FO
R
IN
R
ST
Reference management
U
C
TI
FND AFCS strip (9): VS label in pitch or collective axis column (6, 7).
Disengagement
To pre-select vertical speed reference, turn VS/FPA rotary sw (1) on APCP (50 fpm/tick) before mode engagement. If no vertical speed reference pre-selected, reference is set to current vertical speed upon mode engagement. With VS mode engaged, change vertical speed reference using BEEP TRIM sw (4) on collective (600 fpm/sec) or VS/FPA rotary sw on APCP. Press VS/FPA rotary sw (1) on APCP. or: Set butterfly rotary sw on APCP to TRK–FPA mode combination to revert to FPA mode. or: Press AP UM OFF pb (3) on cyclic. or: Engage incompatible mode.
7 – 3 – 28
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Automatic level off
When approaching the ground, the VS mode is automatically changed to ALT mode, to achieve a level off at 150 ft.
Compatibility with other modes
VS mode incompatible with ALT, ALT.A, GA, CRHT, FPA, V.APP or GS mode. Engagement of these modes will disengage VS mode. VS mode shifted from pitch axis to collective axis when IAS mode engaged (IAS mode engages automatically below 60 kt). Vertical speed reference not changed by override of spring forces or force trim release.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Override
MANUFACTURER’S DATA Rev. 9
7 – 3 – 29
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
A.TRIM
BKUP
AP1
AP2
OFF
OFF
OFF
OFF
CRHT
IAS
ALTA
VS
ALT ON
HDG
2
LL
ED
1
O
N TR
O
3
5
–
C
O
PY
N
O
T
C
4
HDG
DSAS
10
16
10
10
20
20
100 80 VY
R N G
30
FO
W
N
1 500
15
14
14
13
13
DSAS
B A R O
DSAS
VS mode engaged in pitch axis
V/S
E
S
8
15
7
A C K 415 Kg SCT
SVS
OAT 20
+ B R G –
BKD2_FLH_0419_R
3
Fig. 7-3-16
7 – 3 – 30
D H
12
N 000 A V FMS INS/GPS 6.0NM 4 min DCPL
or
6
DTK
+ L U M –
D A
600 1013 200 DA hPa DH
24
21
16
3
R
33
3
17
VS mode engaged in collective axis
DSAS
U
17
10
ST
2
20
DSAS
IN
4
20
R
120
V/S
C
18
6
6
TI
V/S 101
+ C T R S –
CLOCK
O N
O N
LY
9
VS mode – Engagement / disengagement and indications MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ALT.A MODE Description
Acquires a pre-selected altitude by using VS or FPA control, depending on position of butterfly rotary sw on APCP.
Conditions & Limitations
Maximum acceleration to acquire reference: ±185 fpm/sec The mode controls the pitch or the collective axis, depending on airspeed and availability of pitch and collective axis. Below 60 kt the mode controls the collective axis. It shifts to the pitch axis if the airspeed exceeds 65 kt for at least 5 sec.
EFFECTIVITY
ED
Press ALT.A rotary sw (2, Fig. 7-3-17) on APCP. Before Helionix Maintenance Release 1
LL
Engagement by pilot action
C
O
N TR
O
When ALT.A was preselected, activating the GA mode will also activate ALT.A. The ALT.A reference will then be either the pre–selected one, or 1000 ft above the current altitude upon GA engagement, whichever is higher.
T
After Helionix Maintenance Release 1
O
EFFECTIVITY
O
PY
N
When ALT–A was preselected at least 40ft above current altitude, activating GA will also activate ALT.A.
C
EFFECTIVITY
APCP: green light (1) next to ALT.A rotary sw (2).
–
Display
All
R
U
C
TI
O N
O N
LY
FND altitude scale (7): reference indicated by cyan triangle and by cyan alphanumeric value above altitude scale. Vertical speed indicated by a green triangle (VS control) or a green diamond (FPA control).
FO
R
IN
ST
Reference management
FND AFCS strip (8): VS label or FPA label in pitch or collective axis column. ALT.A label below that in same axis column (5, 6). To select reference altitude, turn ALT.A rotary sw (2) on APCP. Default vertical speed reference is 1000 ft/min in climb and 500 ft/min in descent upon mode engagement. If a vertical speed reference was preselected before engaging ALT.A mode, AFCS uses the preselected reference if it is smaller than the default reference, or uses the default reference if the preselected reference is greater than the default reference. With ALT.A mode engaged, adjust vertical speed in accordance with VS mode description, or adjust flight path angle in accordance with FPA mode description, using VS/FPA rotary sw (2) on APCP or BEEP TRIM sw (4) on collective. A preselected – but not engaged – reference can be deleted by pressing AP UM OFF pb (3) on cyclic u 1 sec.
MANUFACTURER’S DATA Rev. 9
7 – 3 – 31
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Disengagement
Press ALT.A rotary sw (2) on APCP. or: Press AP UM OFF pb (3) on cyclic. or: Engage incompatible mode. When approaching the ground, the VS mode is automatically changed to ALT mode, to achieve a level off at 150 ft.
Compatibility with other modes
ALT.A mode incompatible with ALT, VS, CRHT, FPA, V.APP or GS mode. Engagement of these modes will disengage ALT.A mode.
ED
Automatic level off
O
LL
ALT.A mode shifted from pitch axis to collective axis when IAS mode engaged. Vertical speed reference not changed by override of spring forces or force trim release.
C
O
N TR
Override
N
O
T
ALT.A crossing voice message
O
PY
If an ALT.A reference is preselected but the ALT.A is not engaged, a voice message “ALT.A crossing“ will sound when the aircraft is about to cross the reference.
–
C
If ”ALT.A crossing” voice message is sounded, proceed as follows: – Check
O N
LY
1. FND, baro altitude
– Engage
TI
2. ALT.A or ALT mode
O N
If level off is desired:
ST
R
U
C
NOTE D The ALT.A crossing voice message will sound only on the first crossing of the reference. On subsequent crossings, it will not sound.
FO
R
IN
D To remove a preselected ALT.A reference, without engaging ALT.A press AP UM OFF pb (3) on the cyclic > 1 second.
7 – 3 – 32
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
A.TRIM
BKUP
AP1
AP2
OFF
OFF
OFF
OFF
CRHT
IAS
1
ALTA
2 TRK
ALT ON
O
LL
ED
FPA
LY
O
–
C
O
PY
N
O
T
C
4
N TR
3
5
18
IN 20
R
FO
R N G
80 VY
10
ST
100
10
2
20
R
20
120
10
4
CLOCK
DSAS
C
101 6
DSAS
U
V/S ALT.A
TI
O N
O N
8
33
10
3
20
N
17
17
16
16
1 500
15
14
14
13
13
ALT.A mode engaged in collective axis
DSAS
ALT.A
D A
or
D H
DSAS
B A R O
DSAS
ALT.A mode engaged in pitch axis (if used in 3–axis mode)
V/S ALT.A
600 1013 200 DA hPa DH
30
6
W
ALT.A 6700
E
24
12 21
S
15
N 000 A V FMS INS/GPS 6.0NM 4 min
69
A C K 415 Kg SCT
SVS
OAT 20
BKD2_FLH_0420_R
DCPL
DSAS
3
DTK
+ L U M –
V/S
+ C T R S –
7
6
68 + B R G –
67 3
66
Example shown: ALT.A mode in combination with VS mode
6 500
Fig. 7-3-17
ALT.A mode – Engagement / disengagement and indications
MANUFACTURER’S DATA Rev. 0
7 – 3 – 33
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
GA MODE Description
Provides a means to quickly climb out to a safe altitude following an aborted approach.
Conditions & Limitations
GA mode is active for a few seconds (typically 15 sec in cruise and 25 sec from hover) and then transfers control to the VS/FPA mode and IAS mode.
LL
ED
The mode controls vertical speed or flight path angle via collective axis and airspeed via pitch axis, with a priority on the climb rate versus airspeed. At high speed, the aircraft will decelerate if maximum power is reached.
N TR
O
Climb rate: +1000 ft/min or, if higher, the current vertical speed upon mode engagement.
O
T
C
O
Airspeed: VY or, if higher, the current airspeed upon mode engagement. In case of engine failure below VY, at least VTOSS is acquired or the current airspeed between VTOSS and VY is maintained.
PY
N
If GA is engaged without any lateral mode coupled, the aircraft will adopt a wings level attitude.
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
NOTE D Although the GA mode can be engaged at low speed, use of the mode is recommended only above 40 kt. If used below 40 kt, the flight path and trajectory must be actively controlled by the pilot.
Display
FO
R
Engagement by pilot action
D In OEI, the GA mode can be used above 40 kt. The aircraft will initially maintain VTOSS and 1000 ft/min rate of climb. Once a safe height is reached, the IAS reference can be increased to VY. The pilot must actively control the NR by acting on the collective.
Press GA pb (3, Fig. 7-3-18) on collective. APCP: green light (1) next to VS/FPA rotary sw. FND AFCS strip (5): GA label in pitch and collective axis column (4) FND: references displayed in accordance with VS, FPA and IAS mode description (see Fig. 7-3-15, 7-3-16, 7-3-26).
7 – 3 – 34
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Reference management
Adjust vertical speed reference in accordance with VS mode description. Adjust flight path angle reference in accordance with FPA mode description. Adjust airspeed reference in accordance with IAS mode description. EFFECTIVITY
Before Helionix Maintenance Release 1
After Helionix Maintenance Release 1
O
EFFECTIVITY
N TR
O
LL
ED
If an ALT.A reference was pre-selected prior to GA engagement, its acquisition is activated together with the GA mode (ALT.A displayed on FND AFCS strip (4, Fig. 7-3-18) in upper row). ALT.A reference is either the pre-selected one, or 1000 ft above the current altitude upon GA engagement, whichever is higher.
PY
N
O
T
C
When ALT–A was preselected at least 40ft above current altitude, activating GA will also activate ALT.A mode and the helicopter will use the preselected altitude target. All
O
EFFECTIVITY or:
C
Press GA pb (3) on collective.
–
Disengagement
LY
Press AP UM OFF pb (2) on cyclic.
O N
or:
O N
Engage incompatible mode. GA mode incompatible with ALT, ALT.A, or CRHT mode. Engagement of these modes will disengage GA mode in the corresponding axis and leaves the mode engaged on the other axis. Engaging IAS or VS/FPA mode during GA deactivates the corresponding mode only, but leaves the other one active.
FO
R
IN
ST
R
U
C
TI
Compatibility with other modes
MANUFACTURER’S DATA Rev. 9
7 – 3 – 35
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
A.TRIM
BKUP
AP1
AP2
OFF
OFF
OFF
OFF
CRHT
IAS
ALTA
TRK
ALT ON
FPA
N TR
O
LL
ED
1
3
O N
LY
–
C
O
PY
N
O
T
C
O
2
TI
O N
5
U
C
4
101
10
10
R
100
20
IN
20
120
FO
10
2
R
CLOCK
18
6
4
GA
DSAS
ST
GA
80
20
10
3
20
VY
33
R N G
N
17
17
16
16
1 500
15
14
14
13
13
30
D H B A R O
E 12 21
S
15
DTK
BKD2_FLH_0421_R
GA
6
N 000 A FMS V INS/GPS 6.0NM 4 min
A C K 415 Kg SCT
SVS
Fig. 7-3-18
7 – 3 – 36
DSAS
600 1013 200 DA hPa DH
W
DCPL
GA
D A
3
24
+ L U M –
+ C T R S –
OAT 20
+ B R G –
GA mode – Engagement / disengagement and indications MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
CRHT MODE Description
Acquires and holds a pre-selected radio height in hover and flight. Designed to be used over water.
Conditions & Limitations
Requires a valid radar altimeter signal. Minimum radar altimeter reference: decision height, min. 3 ft. Maximum radar altimeter reference: 2200 ft (AGL).
O
When operating near the ground, a sensor error could cause the aircraft to descend suddenly. The pilot shall therefore be attentive to the collective in accordance with the limitations (see section 2.5.5.1).
O
N TR
NOTE
LL
The mode controls the collective axis.
ED
Descent rate is limited close to the ground and during low speed descent to avoid inadvertent settling with power.
Press CRHT rotary sw (1, Fig. 7-3-19) on APCP.
Display
APCP: green light (2) next to CRHT rotary sw (1).
O
T
C
Engagement by pilot action
O
PY
N
FND radar altimeter scale (6): reference indicated by triangle shaped bug, and by cyan alphanumeric value above altitude scale. Bug displayed as follows:
–
C
– cyan if mode not engaged,
LY
– green if mode engaged,
O N
– flashing white-cyan reference.
or
white-green
while
changing
TI
FO
R
IN
ST
R
U
C
Reference management
O N
FND AFCS strip (7): CRHT label in collective axis column (5).
Disengagement
To pre-select radio height reference, turn CRHT rotary sw (1) on APCP (10 ft/tick) before mode engagement. If no radio height reference pre-selected, reference is set to current radio height upon mode engagement. With CRHT mode engaged, change radio height reference using: – CRHT rotary sw (1) on APCP (10 ft/tick), or – BEEP TRIM sw (4) on collective (25 ft/sec). Press CRHT rotary sw (1) on APCP. or: Press AP UM OFF pb (3) on cyclic. or: Engage incompatible mode.
MANUFACTURER’S DATA Rev. 10
7 – 3 – 37
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Compatibility with other modes
CRHT mode incompatible with ALT, VS, ALT.A, GA, FPA, V.APP or GS mode. Engagement of these modes will disengage CRHT mode.
Override
Radio height reference not changed by override of spring forces or force trim release.
CRHT mode with FLY UP Commands maximum climb rate when a significant deviation (>30ft) from the selected CRHT height is detected.
Engagement
The FLY–UP protection mode is automatically engaged when
LL
ED
Description
N TR
O
the aircraft descends below (whichever is lower): – 200 ft, or Display / Voice message
O
– 30 ft below the CRHT reference.
flashes.
T
C
FND AFCS strip (7): FLYUP
N
O
Voice message “AUTOPILOT FLYUP“ sounds if the FLY–UP protection mode activates. Disengage CRHT mode.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
Disengagement
7 – 3 – 38
MANUFACTURER’S DATA Rev. 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
2
1 A.TRIM
BKUP
AP1
AP2
OFF
OFF
OFF
OFF
CRHT
IAS
ALTA
TRK
ALT ON
O
LL
ED
FPA
O N
LY
–
C
O
PY
N
O
T
4
C
O
N TR
3
O N
7
R
U
C
TI
5
101
120
IN
6
ST
CR.HT
FO
2
18
20
20
17
17
10
10
16
16
1 500
15
14
80
14
13
13
10
10
20
20
3
VY
R N G
33
E
DTK
BKD2_FLH_0422_R
1 51
15
S
N 000 A V FMS INS/GPS 6.0NM 4 min
Fig. 7-3-19
SVS
415 Kg OAT 20
1
5 000 215
A C K
SCT
DSAS
6
52
12 21
DSAS
CRHT 2280
B A R O
6
W
DCPL
D H
3
30
CR.HT
D A
600 1013 200 DA hPa DH
N
24
+ L U M –
+ C T R S –
CLOCK
DSAS
100
R
4
DSAS
+ B R G –
49
214
48
23
CRHT mode – Engagement / disengagement and indications
MANUFACTURER’S DATA Rev. 0
7 – 3 – 39
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
LOC MODE Description
Captures and tracks the inbound front course localizer beam for an ILS runway approach.
Conditions & Limitations
Requires a VOR/LOC receiver tuned to an ILS frequency and this navigation source to be used/engaged. The mode controls the roll attitude. Capture conditions:
ED
– At intecept angle ≤ 25 deg the mode captures when localizer deviation is below 2.1 dot. The aircraft is then aligned to the runway heading.
N TR
O
LL
– At intercept angle > 25 deg the mode captures when localizer deviation is below 2.1 dot. The aircraft is then pre-aligned at approx. 25 deg intercept angle. Final alignment to runway heading is initiated at 1 dot.
N
FOR THE AUTOPILOT TO FUNCTION PROPERLY, THE FINAL COURSE MUST BE SET CORRECTLY. IF THE COURSE IS SET INCORRECTLY, ERRATIC COURSE CHANGES OR ROLL OSCILLATIONS MAY OCCUR.
LY
–
C
O
PY
CAUTION
O
T
C
O
The mode follows the localizer track when localizer deviation is below 1 dot.
O N
Armament / Engagement by pilot Select desired NAV source and press CPL key (5, Fig. action 7-3-20) on MFD FND or MFD NAVD:
– LOC mode engaged if capture conditions met.
FO
R
IN
ST
R
U
C
TI
O N
– LOC mode armed if valid localizer deviation signal available but capture conditions not met. Any engaged lateral/directional mode remains active until LOC mode captures.
7 – 3 – 40
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Display / Voice messages
FND AFCS strip (1): LOC label in yaw/roll axis column. Label displayed as follows: – cyan in bottom row if mode armed, – green in upper row if mode engaged (3). FND HSI display: course deviation indicator (CDI) (4) displayed as follows: – magenta if mode armed, – green if mode engaged.
LL
ED
When the LOC mode is armed and the signal is lost (or the frequency is changed), the voice message “AP DISARM” sounds after 10 sec (refer to Sect. 3).
N TR
O
When the LOC mode is engaged and the signal is lost (or the frequency is changed), the voice message “AP DECOUPLE” sounds after 10 sec (refer to Sect. 3). Set desired course via CRS key (6) on MFD. Cyclic and collective BEEP TRIM sw have no effect.
Disarmament / Disengagement
Press AP UM OFF pb (2) on cyclic.
O
T
C
O
Reference management
PY
N
or:
–
or:
C
O
Change navigation source or NAV receiver frequency for more than 10 sec.
O N
LY
Press DCPL key (5) on MFD FND or MFD NAVD (short press < 1 sec).
ST
R
U
C
TI
O N
or:
or: Engage incompatible mode. LOC mode incompatible with HDG, TRK, VOR, NAV, APP, GTC, GTC.H or GA mode. Engagement of these modes will disengage LOC mode.
FO
R
IN
Compatibility with other modes
ILS source no longer visible on any master side display for more than 10 sec.
MANUFACTURER’S DATA Rev. 9
7 – 3 – 41
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ED
2
16
1 500
15
14
14
80
13
13
10
10
20
20
3
VY
33
N
B A R O
600 1013 200 DA hPa DH
3 6
C
E 12 S
15
–
21 DTK
N 000 A FMS V INS/GPS 6.0NM 4 min
A C K 415 Kg
DCPL
SCT
SVS
O
O
O
30 W 24
+ L U M –
D H
OAT 20
+ B R G –
4
O N
BKD2_FLH_0423_R
17
16
100
R N G
6
17
10
LY
2
20
10
DSAS
O N
4
20
LOC
C
120
DSAS
D A
T
18
O
101 6
+ C T R S –
CLOCK
DSAS
N
LOC
PY
DSAS
N TR
3
LL
1
U
C
LOC mode – Engagement / disengagement and indications
FO
R
IN
ST
R
Fig. 7-3-20
TI
5
7 – 3 – 42
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
GS MODE Description
Captures and tracks the glide slope beam for an ILS runway approach.
Conditions & Limitations
Requires a VOR/LOC receiver tuned to an ILS frequency and this navigation source to be used/engaged. The mode controls the pitch or the collective axis, depending on airspeed and availability of pitch and collective axis.
ED
Below 60 kt the mode controls the collective axis. It shifts to the pitch axis if the airspeed exceeds 65 kt for at least 5 sec.
LL
Capture conditions:
C
O
N TR
O
– The mode captures if the deviation is valid and lower than 2.2 dots for at least 1 sec (glide slope bug at the bottom of the scale) and higher than –0.7 dots for at least 3 sec (glide bug above the center).
N
O
T
– The capture takes place if the LOC mode is engaged and if the deviation is lower than 2.05 dots and higher than –0.3 dots (threshold depending on the flight conditions).
PY
When captured, the mode follows the glide slope beam.
–
C
O
Armament / Engagement by pilot Select desired NAV source and press CPL key (6, Fig. action 7-3-21) on MFD FND or MFD NAVD:
LY
– GS mode armed if:
– LOC mode armed or engaged (upon same pressing of CPL key) Any engaged pitch mode remains active until GS mode captures.
– GS mode engaged if capture conditions met.
FO
R
IN
ST
R
U
C
TI
O N
O N
– valid localizer course deviation signal available but capture conditions not met, and
MANUFACTURER’S DATA Rev. 0
7 – 3 – 43
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Display / Voice messages
FND AFCS strip (1): GS label in pitch or collective axis column (3, 4). Label displayed as follows: – cyan in bottom row if mode armed, – green in upper row if mode engaged. FND HSI display: triangle of vertical deviation indicator (VDI) (5) displayed as follows: – magenta if mode armed, – green if mode engaged.
N TR
O
LL
ED
When the GS mode is armed and the signal is lost (or the frequency is changed), the voice message “AP DISARM” sounds after 10 sec. If the GS signal is available again, the GS mode will automatically re-arm, as long as the LOC mode is not disarmed/decoupled.
C
O
When the GS mode is engaged and the signal is lost (or the frequency is changed), the voice message “AP DECOUPLE” sounds after 10 sec. No reference adjustment required. Cyclic and collective BEEP TRIM sw have no effect.
Disarmament / Disengagement
Press AP UM OFF pb (2) on cyclic.
PY
N
O
T
Reference management
C
O
or:
O N
or:
LY
–
Change navigation source or NAV receiver frequency for more than 10 sec. Press DCPL key (6) on MFD FND or MFD NAVD:
O N
– short press < 1 sec deactivates both LOC and GS mode,
FO
R
IN
ST
R
U
C
TI
– long press >1 sec deactivates only GS mode or:
ILS source no longer visible on any master side display for more than 10 sec. or: Engage incompatible mode.
Automatic level off
When approaching the ground, the G/S mode is automatically changed to ALT mode, to achieve a level off at 65 ft.
Compatibility with other modes
GS mode incompatible with ALT, VS, ALT.A, GA, CRHT, V.APP, GTC, or GTC.H or FPA mode. Engagement of these modes will disengage LOC mode. GS mode shifted from pitch axis to collective axis when IAS mode engaged (IAS mode engages automatically below 60 kt).
7 – 3 – 44
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
2
LL
ED
1
100 10
10
20
20
VY
33
16
1 500
15
14
14
13
13
N
E 12 21
15
S
DTK
N 000 A V FMS INS/GPS 6.0NM 4 min
A C K
SCT
SVS
415 Kg OAT 20
+ B R G –
O N
DCPL
N TR
O
DSAS
GS mode engaged in pitch axis
4
5
U
C
TI
6
R
BKD2_FLH_0424_R
DSAS
6
24
+ L U M –
B A R O
3
W
G/S
or
D H
600 1013 200 DA hPa DH
30
GS mode engaged in collective axis
O
R N G
16
C
80
3
17
DSAS
C
10
DSAS
–
2
20
10
O N
4
20
G/S
D A
LY
120
17
T
18
O
101 6
+ C T R S –
CLOCK
DSAS
N
LOC
PY
G/S
O
3
GS mode – Engagement / disengagement and indications
FO
R
IN
ST
Fig. 7-3-21
MANUFACTURER’S DATA Rev. 0
7 – 3 – 45
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
APP MODE
Description
The lateral RNP approach mode (APP) aligns the aircraft along the horizontal flight path for an LPV or point in space approach. The APP mode commands the roll attitude to maintain the horizontal flight path. Requires an active flight plan with an RNP approach (LNAV, LNAV/VNAV, LP or LPV) and the required Level of Service (GPS or SBAS, depending on the approach selected).
Automatic engagement
APP mode is armed and engaged automatically when:
O
LL
ED
Conditions & Limitations
N TR
– The NAV mode is coupled.
C
O
– The flight plan data is active and data are received from the FMS
PY
N
O
T
– The required Level of Service (LNAV, LNAV/VNAV, LP, or LPV) is available.
O
The APP mode is first armed and then engaged:
–
C
– APP is armed when the required Level of Service is available, which is normally at the Intermediate Fix (IF).
O N
O N
LY
– APP is captured as soon as the cross track error with respect to the final axis is less than 0.1 NM (earliest 10 sec after armament of the APP mode). FND AFCS strip (1): APP label in yaw/roll axis column. Label displayed as follows: – cyan in bottom row if mode armed, – green in upper row if mode engaged (3).
FO
R
IN
ST
R
U
C
TI
Display / Voice messages
FND HSI display: course deviation indicator (CDI) (4) displayed as follows: – cyan if mode armed, – green if mode engaged. When the APP mode is armed and the Level of Service is lost, the voice message “AUTOPILOT DISARM“ sounds after 10 sec (refer to Sect. 3). When the APP mode is engaged and the Level of Service is lost, the voice message “AUTOPILOT DECOUPLE” sounds after 10 sec (refer to Sect. 3).
Reference management
7 – 3 – 46
Reference management is automatic through the selected flight plan. MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Disarmament / Disengagement
Press AP UM OFF pb (2) on cyclic. or: Change navigation source. or: Press DCPL key (5) on MFD FND or MFD NAVD (short press < 1 sec). or: Engage incompatible mode. APP mode incompatible with HDG, TRK, VOR, NAV, LOC, GTC, GTC.H or GA mode. Engagement of these modes will disengage APP mode.
O
N TR
O
LL
ED
Compatibility with other modes
LY
–
C
O
PY
N
O
T
C
2
O N
O N
1
TI
DSAS
C
R
IN
2
20
20
17
17
10
10
16
16
1 500
15
14
14
13
13
100 80
10
10
20
20
3
VY
33
R N G
FO
18
N
DSAS
D H B A R O
600 1013 200 DA hPa DH
30
6
W
E
4
12 21
S
15
DTK
+ L U M –
APP
3
24
6
DSAS
D A
N 000 A V FMS INS/GPS 6.0NM 4 min
A C K 415 Kg
DCPL
SCT
SVS
OAT 20
+ B R G –
BKD2 FLH 0480 R
U 120
R ST
4
+ C T R S –
CLOCK
DSAS
APP
101 6
3
5 Fig. 7-3-22
APP mode – Engagement / disengagement and indications
MANUFACTURER’S DATA Rev. 2
7 – 3 – 47
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
V.APP MODE
Description
The vertical RNP approach mode (V.APP) aligns the aircraft along the descent flight path for an approach with vertical guidance (LNAV/VNAV or LPV). The V.APP mode commands the pitch attitude or collective to maintain the vertical flight path. Requires an active flight plan with an RNP approach (LNAV/VNAV or LPV) and the required Level of Service (GPS or SBAS, depending on the approach selected).
Automatic engagement
V.APP mode is armed and engaged automatically when:
O
LL
ED
Conditions & Limitations
O C
– The NAV mode is coupled.
N TR
– The required Level of Service (LNAV/VNAV or LPV) is available.
PY
N
O
T
– The flight plan data is active and data are received from the FMS.
O
The V.APP mode is first armed and then engaged:
O N
LY
–
C
– V.APP is armed when the required Level of Service is available, which is normally at the Intermediate Fix (IF). While V.APP is armed, the previously engaged upper modes remain active.
TI
O N
– V.APP is captured as soon as APP is captured and the vertical deviation is valid and lower than a specific threshold.
FO
R
IN
ST
R
U
C
Display / Voice messages
FND AFCS strip (1): V.APP label in collective or pitch axis column. Label displayed as follows: – cyan in bottom row if mode armed, – green in upper row if mode engaged (3). FND HSI display: Vertical deviation indication (4) – cyan if mode armed, – green if mode engaged. When the V.APP mode is armed and the Level of Service is lost, the voice message “AUTOPILOT DISARM“ sounds after 10 sec (refer to Sect. 3). After automatic disengagement of V.APP mode, the mode automatically reverts to VS or FPA mode with the reference set to 0 ft/min vertical rate or 0 % flight path.
7 – 3 – 48
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Reference management
Reference management is automatic through the selected flight plan.
Disarmament / Disengagement
Press AP UM OFF pb (2) on cyclic. or: Change navigation source. or: Press DCPL key (5) on MFD FND or MFD NAVD (short press < 1 sec). or:
ED
Engage incompatible mode.
O
LL
V.APP is automatically disengaged when the Level of Service is lost or if the APP mode is disengaged. When approach the ground, the V.APP mode automatically reverts to ALT mode to level the aircraft off at:
O
N TR
Automatic level off
T
C
– 65 ft above the ground when LPV Level of Service is used.
PY
N
O
– 150 ft above the ground if LNAV/VNAV Level of Service is used. Prior to the FAF, the IAS reference is automatically set so that the rate of descent during the approach does not exceed 1000 ft/min.
Compatibility with other modes
V.APP mode incompatible with ALT, ALT.A, V/S, FPA, CRHT, LOC, GTC, GTC.H or GA mode. Engagement of these modes will disengage V.APP mode.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
Airspeed management
MANUFACTURER’S DATA Rev. 9
7 – 3 – 49
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
1
20
20
VY
15
14
14
13
13
6
O
30 W
E 12 21
15
S
DTK
N 000 A V FMS INS/GPS 6.0NM 4 min
A C K
SVS
OAT 20
O N
SCT
4
+ B R G –
O N
415 Kg
DCPL
BKD2_FLH_0479_R
B A R O
3
24
+ L U M –
D H
600 1013 200 DA hPa DH
N
33
R N G
16
1 500
C
80
10
16
–
2
10
3
O
10
D A
C
10 100
17
LY
4
17
IAS
T
20
18
120
APP
O
20
101 6
V.APP
+ C T R S –
CLOCK
IAS
N
APP
PY
V.APP
N TR
O
LL
3
ED
2
V.APP mode – Engagement / disengagement and indications
FO
R
IN
ST
Fig. 7-3-23
R
U
C
TI
5
7 – 3 – 50
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
VOR MODE Description
Captures and tracks a radial inbound or outbound a VOR station.
Conditions & Limitations
Requires a VOR receiver tuned to a VOR frequency and this navigation source to be used/engaged. The mode controls the roll axis. Capture conditions:
C
O
N TR
O
> 45 deg the mode captures when between 1 and 2 dot. The aircraft is approx. 45 deg intercept angle. Final radial is initiated between 0.4 and
T
– At intercept angle course deviation is then pre-aligned at alignment to VOR 1.5 dot.
LL
ED
– At intercept angle v 45 deg the mode captures and aligns the aircraft to VOR radial when course deviation is between 0.4 and 1.5 dot.
N
O
The mode follows the VOR radial inbound or outbound a station for any course deviation below 0.4 dot.
LY
–
C
O
PY
While crossing the cone of silence over the VOR station, the bearing signal will show fast and large amplitude variations and then becomes invalid for some time. The mode maintains the current heading. When exiting the cone of silence, tracking is resumed.
– VOR mode armed if valid course deviation signal available but capture conditions not met. Any engaged lateral/directional mode remains active until VOR mode captures. – VOR mode engaged if capture conditions met.
FO
R
IN
ST
R
U
C
TI
O N
O N
Armament / Engagement by pilot Select desired NAV source and press CPL key (5, Fig. action 7-3-24) on MFD FND or MFD NAVD:
MANUFACTURER’S DATA Rev. 2
7 – 3 – 51
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Display / Voice messages
FND AFCS strip (1): VOR label in yaw/roll axis column. Label displayed as follows: – cyan in bottom row if mode armed, – green in upper row if mode engaged (3). FND HSI display: course deviation indicator (CDI) (4) displayed as follows: – cyan if mode armed, – green if mode engaged.
LL
ED
When the VOR mode is armed and the signal is lost (or the frequency is changed), the voice message “AP DISARM” sounds after 30 sec.
N TR
O
When the VOR mode is engaged and the signal is lost (or the frequency is changed), the voice message “AP DECOUPLE” sounds after 30 sec. Set desired VOR course via CRS key (6) on MFD.
C
O
Reference management
T
Cyclic and collective BEEP TRIM sw have no effect. Press AP UM OFF pb (2) on cyclic.
N
O
Disarmament / Disengagement
PY
or:
O
Change navigation source or NAV receiver frequency.
C
or:
LY
–
Press DCPL key (5) on MFD FND or MFD NAVD.
O N
or:
O N
VOR source no longer visible on any master side display for more than 10 sec.
C
TI
or:
VOR mode incompatible with HDG, GTC, GTC-H, TRK, LOC, APP or NAV mode. Engagement of these modes will disengage VOR mode.
FO
R
IN
ST
R
U
Compatibility with other modes
Engage incompatible mode.
7 – 3 – 52
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ED
2
16
1 500
15
14
14
13
13
10
20
20
VY
33
3
30
6
W
E 21
15
S
DTK
A C K
SVS
O
+ B R G –
O N
415 Kg SCT
4
OAT 20
O N
BKD2_FLH_0425_R
12
N 000 A V FMS INS/GPS 6.0NM 4 min DCPL
B A R O
600 1013 200 DA hPa DH
N
24
+ L U M –
D H
O
80
10
3
DSAS
C
17
16
VOR
T
17
10
100
R N G
6
20
10
C
2
20
–
4
120
DSAS
D A
LY
6
18
O
101
+ C T R S –
CLOCK
DSAS
N
VOR
PY
DSAS
N TR
O
3
LL
1
C
VOR mode – Engagement / disengagement and indications
FO
R
IN
ST
R
U
Fig. 7-3-24
TI
5
MANUFACTURER’S DATA Rev. 2
7 – 3 – 53
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
NAV MODE Description
Enables coupling to a flight navigation computer and tracking of a programmed horizontal flight path. Using the OBS function within the NMS allows intercepts to a desired waypoint leg.
Conditions & Limitations
Requires a flight plan (at least one waypoint to be selected) to be active on the FMS, and the navigation source to be the FMS.
ED
The mode controls the roll axis.
O
LL
Track changes will be conducted with standard rate turns (max. 21_ bank).
O
N TR
Roll reference is automatically set to “wings level” (zero bank angle) when NAV mode is disengaged and ATT mode engaged. Press CPL key (4, Fig. 7-3-25) on MFD FND or MFD NAVD.
Display
FND AFCS strip (1): NAV label in yaw/roll axis column (3)
Reference management
No reference adjustment required. Cyclic and collective BEEP TRIM sw have no effect.
Disengagement
Press AP UM OFF pb (2) on cyclic.
C
O
PY
N
O
T
C
Engagement by pilot action
–
or:
O N
or:
LY
Change navigation source.
O N
Press DCPL key (4) on MFD FND or MFD NAVD.
C
TI
or:
NAV mode incompatible with HDG, TRK, GTC, GTC.H, VOR, or LOC mode. Engagement of these modes will disengage NAV mode.
FO
R
IN
ST
R
U
Compatibility with other modes
Engage incompatible mode.
7 – 3 – 54
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ED
2
17
17
10
16
16
1 500
15
14
14
13
13
10
20
20
VY 600 DA
N
33
R N G
30
E 12 21
S
15
DTK
N 000 A V FMS INS/GPS 6.0NM 4 min
A C K
SVS
415 Kg OAT 20
O C
+ B R G –
O N
SCT
TI
BKD2_FLH_0426_R
1013 200 hPa DH
6
W
DCPL
B A R O
3
24
+ L U M –
D H
C
80
10
3
O
100
T
20
10
DSAS
–
2
20
NAV
LY
4
120
DSAS
D A
O N
6
18
O
101
+ C T R S –
CLOCK
DSAS
N
NAV
PY
DSAS
N TR
3
O
LL
1
C
4
NAV mode – Engagement / disengagement and indications
FO
R
IN
ST
R
U
Fig. 7-3-25
MANUFACTURER’S DATA Rev. 2
7 – 3 – 55
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
FPA MODE Description
Maintains the current flight path angle (ground slope) upon engagement or acquires and holds a pre-selected flight path angle.
Conditions & Limitations
The flight path angle reference is limited to $30.5%. Maximum acceleration/deceleration to acquire reference is limited depending on airspeed.
LL
ED
The maximum climb rate is limited to +2500 ft/min. The maximum descent rate is –2500 ft/min above 55 kt. Below 55 kt, it gradually reduces to reach a maximum of –300 ft/min below 25 kt.
N TR
O
The mode controls the pitch or the collective axis, depending on airspeed and availability of pitch and collective axis.
C
O
Below 60 kt the mode controls the collective axis. It shifts to the pitch axis if the airspeed exceeds 65 kt for at least 5 sec.
PY
N
O
T
Flight path angle can not be pre-selected below 20 kt. FPA mode can be engaged but will be realized by VS mode until sufficient ground speed is reached. Press VS/FPA rotary sw (3, Fig. 7-3-26) on APCP (butterfly rotary sw in TRK–FPA mode combination).
Automatic engagement
Reversion from engaged VS mode if butterfly rotary sw on APCP is set from HDG–VS mode combination to TRK–FPA mode combination.
Display
APCP: green light (4) next to VS/FPA rotary sw.
O N
LY
–
C
O
Engagement by pilot action
FO
R
IN
ST
R
U
C
TI
O N
FND (8): reference indicated by a diamond on the vertical speed scale and in the attitude indicator, and by alphanumeric value (%) above vertical speed scale. While adjusting the reference, an alphanumeric value in degrees is shown in the attitude scale, displayed as follows: – cyan if mode not engaged, – green if mode engaged, – flashing white-green while changing reference. Alphanumeric value and references in the ADI not displayed below 20 kt ground speed. FND AFCS strip (1): FPA label in pitch or collective axis column (6, 7).
7 – 3 – 56
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Reference management
To pre-select flight path angle reference, turn VS/FPA rotary sw (3) on APCP before mode engagement. If no flight path angle reference pre-selected, reference is set to current flight path angle upon mode engagement. With FPA mode engaged, change FPA reference using: – VS/FPA rotary sw (3) on APCP or – BEEP TRIM sw (5) on collective.
Disengagement
Press VS/FPA rotary sw (3) on APCP. or:
LL
ED
Set butterfly rotary sw on APCP to HDG–VS mode combination to revert to VS mode.
O
or:
N TR
Press AP UM OFF pb (2) on cyclic.
O
or:
C
Engage incompatible mode.
When approaching the ground, the FPA mode is automatically changed to ALT mode, to achieve a level off at 150 ft.
Compatibility with other modes
FPA mode incompatible with ALT, ALT.A, GA, CRHT, GTC, GTC.H, V.APP, or GS mode. Engagement of these modes will disengage FPA mode.
–
C
O
PY
N
O
T
Automatic level off
O N
LY
FPA mode shifted from pitch axis to collective axis when IAS mode engaged. Flight path angle reference not changed by override of spring forces or force trim release.
FO
R
IN
ST
R
U
C
TI
O N
Override
MANUFACTURER’S DATA Rev. 2
7 – 3 – 57
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
A.TRIM
BKUP
AP1
AP2
OFF
OFF
OFF
OFF
CRHT
IAS
ALTA
TRK
ALT ON
FPA
4
N TR
O
LL
ED
3
O
2
–
C
O
PY
N
O
T
C
5
101
17
120 100 80
33
N
600 DA
FO 21
+ L U M –
16
1 500
15
14
14
13
13
DSAS
FPA mode engaged in collective axis
FPA
FPA mode engaged in pitch axis
or
D H
DSAS
B A R O
DSAS
DSAS
1013 200 hPa DH
7
E 12
S
15
41 %
N 000 A V FMS INS/GPS 6.0NM 4 min DCPL
FPA
6
24
DTK
D A
3
R
30 W
IN
VY
R N G
17
16
ST
3
2
18
U
4
41%
R
6
+ C T R S –
CLOCK
DSAS
TI
LOC
6
C
FPA
O N
O N
LY
1
A C K
SCT
SVS
415 Kg OAT 20
+ B R G –
BKD2_FLH_0427_R
8
Fig. 7-3-26
7 – 3 – 58
FPA mode – Engagement / disengagement and indications MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
TRK MODE Description
Maintains the current track angle upon engagement, or acquires and holds a pre-selected track angle, compensating for drift due to wind.
Conditions & Limitations
Maximum turn rate to acquire reference: 3 deg/sec (standard turn rate).
ED
The mode controls the track on the roll axis or on the yaw axis, depending on the track deviation and the flight condition.
N TR
O
LL
At low airspeed, the track cannot be computed. Consequently, the TRK mode behaves like the HDG mode below 30 kt. Press HDG/TRK rotary sw (6, Fig. 7-3-27) on APCP (butterfly rotary sw in TRK–FPA mode combination).
O
Engagement by pilot action
C
or:
N
O
T
Double fwd press AP/BKUP ON sw (4) on cyclic (butterfly rotary sw on APCP in TRK–FPA mode combination). Reversion from engaged HDG mode if butterfly rotary sw on APCP is set from HDG–VS mode combination to TRK–FPA mode combination.
Display
APCP: green light (5) next to HDG/TRK rotary sw (6).
LY
–
C
O
PY
Automatic engagement
ST
R
U
C
TI
O N
O N
FND heading scale (9): reference indicated by a diamond (and by alphanumeric value if the HSI is in sector indication). Diamond and alphanumeric value displayed as follows:
FO
R
IN
Reference management
– cyan if mode not engaged, – green if mode engaged, – bug flashing white-green while changing reference. FND AFCS strip (1): TRK label in yaw/roll axis column (8). To pre-select track reference, turn HDG/TRK rotary sw (6) on APCP before mode engagement. Pre-selection is kept in case of recovery action on cyclic. If no track reference pre-selected, reference is set to current track upon mode engagement. With TRK mode engaged, change track reference using: – HDG/TRK rotary sw (6) on APCP, or – BEEP TRIM sw (3) on cyclic in forward flight, or – BEEP TRIM sw (7) on collective.
MANUFACTURER’S DATA Rev. 2
7 – 3 – 59
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Disengagement
Press HDG/TRK rotary sw (6) on APCP. or: Set butterfly rotary sw on APCP to HDG–VS mode combination to revert to HDG mode. or: Press AP UM OFF pb (2) on cyclic. or: Engage incompatible mode. TRK mode incompatible with LOC, NAV, APP, GTC, or GTC.H or VOR mode. Engagement of these modes will disengage TRK mode.
Override
Track reference not changed by override of spring forces or force trim release.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Compatibility with other modes
7 – 3 – 60
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
A.TRIM
BKUP
AP1
AP2
OFF
OFF
OFF
OFF
CRHT
IAS
ALTA
TRK
ALT ON
FPA
5
6
N TR
O
LL
ED
4
–
C
O
PY
N
O
T
C
7
2
O
3
LY
1
TRK
101 20 10
10
20
20
ST
10
80
3
IN
VY
FO BKD2_FLH_0428_R
10
R
100
R
R N G
20
U
120
C
18
6
2
CLOCK
DSAS
TI
DSAS
4
O N
O N
8
33
17
17
16
16
1 500
15
14
14
13
13
33
12
24
A C K
SCT
Fig. 7-3-27
SVS
415 Kg OAT 20
N
3 6
W
15
S
DSAS
30
E
24
N 000 A V FMS INS/GPS 6.0NM 4 min DCPL
B A R O
6
W
TRK
D H
3
30
21
DSAS
D A
600 1013 200 DA hPa DH
N
DTK
+ L U M –
+ C T R S –
+ B R G –
E 21
S
15
9
12
TRK mode – Engagement / disengagement and indications
MANUFACTURER’S DATA Rev. 2
7 – 3 – 61
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
GTC MODE THE GTC MODE RELIES ON GPS AND MAGNETIC HEADING:
CAUTION
D IN CASE OF POOR GPS RECEPTION (E.G. WHEN OPERATING IN A CANYON OR WHEN AN ASSOCIATED GTN MESSAGE IS INDICATED), THE GTC MODE SHALL NOT BE USED.
O
LL
ED
D IN CASE OF MAGNETIC HEADING PERTURBATIONS (E.G. WHEN OPERATING NEAR LARGE METALLIC STRUCTURES OR MAG DEGR INDICATED), THE DG MODE (WITH CORRECT HEADING) SHALL BE USED. The Ground Trajectory Command (GTC) mode is an upper mode that changes its references through pilot actions or with beep trim inputs. As soon as the cyclic is released, the autopilot maintains the new ground speed. The GTC mode is most useful for low airspeed operations, including Cat A takeoff and approach/landing. The GTC mode should be flown “hands–on, feet– on“, even if the trajectory is maintained when the controls are released.
–
C
O
NOTE
PY
N
O
T
C
O
N TR
Description
Groundspeed (forward) < 7 kt:
LY
Conditions & Limitations
O N
– The GTC mode maintains the longitudinal and lateral ground speed.
FO
R
IN
ST
R
U
C
TI
O N
– The GTC mode maintains the heading (a green triangle is shown on the compass). Groundspeed (forward) > 7 kt: – The GTC mode maintains the longitudinal speed. Ground speed is maintained at low speed; airspeed is maintained at high speed. – The GTC mode maintains the track. – The GTC mode provides turn coordination (no heading bug is shown on the compass).
Armament / Engagement by pilot Single press on the GTC sw (3). action Automatic engagement
7 – 3 – 62
GTC is automatically engaged from GTC.H mode when accelerating forward above 20 kt groundspeed.
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Display / Voice messages
FND AFCS strip (1): GTC label in pitch and yaw/roll column (4). Groundspeed (forward) < 7 kt: – Groundspeed reference is shown as a green circle in the hover indication. – Heading reference is shown as a green triangle on the compass indication Groundspeed (forward) > 7 kt: References are not indicated.
Reference management
Groundspeed (forward) < 7 kt:
O
LL
ED
– Longitudinal / lateral ground speed reference can be changed by overriding the cyclic stick or by longitudinal / lateral beep inputs.
T
C
O
N TR
– Heading reference can be changed by pedal input (heading reference is slewed) or by left/right collective beep inputs.
O
Groundspeed (forward) > 7 kt:
PY
N
– Longitudinal ground speed reference can be changed by overriding the cyclic stick or by longitudinal beep inputs.
Press AP UM OFF pb (2) on cyclic.
LY
Disarmament / Disengagement
–
C
O
– Track reference can be changed by lateral control inputs or by left/right cyclic or collective beep inputs.
O N
or:
O N
Engage incompatible mode. The GTC mode is incompatible with GTC.H, IAS, HDG, TRK, NAV, LOC, APP, V.APP, GS, or VOR. Engagement of these modes will disengage the GTC mode.
FO
R
IN
ST
R
U
C
TI
Compatibility with other modes
MANUFACTURER’S DATA Rev. 9
7 – 3 – 63
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
3
ED
2
O
LL
1
17
17
10
16
16
1 500
15
14
14
13
13
100
20
20
3
VY
R N G
3
30
6
W
E 12 21
15
S
415 Kg SCT
SVS
OAT 20
O C
33
6
2690
30
E
30
24
10 10
W
21
30
S
12 15
RANGE 1 NM
GTC mode – Engagement / disengagement and indications
FO
R
IN
ST
R
U
Fig. 7-3-28
+ B R G –
3
N
TI
O N
DCPL
A C K
O N
N 000 A V FMS INS/GPS 6.0NM 4 min
5
C
BKD2_FLH_0482_R
24 DTK
+ L U M –
B A R O
600 1013 200 DA hPa DH
N
33
D H
O
10
C
80
10
GTC
T
20
10
GTC
O
20
–
2
120
ALT
D A
LY
4
18
N
101 6
+ C T R S –
GTC
PY
GTC
ALT
N TR
3 4
7 – 3 – 64
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
GTC.H MODE CAUTION
THE GTC.H MODE RELIES ON GPS AND MAGNETIC HEADING. D IN CASE OF POOR GPS RECEPTION (E.G. WHEN OPERATING IN A CANYON OR WHEN AN ASSOCIATED GTN MESSAGE IS INDICATED), THE GTC.H MODE SHALL NOT BE USED.
LL
ED
D IN CASE OF MAGNETIC HEADING PERTURBATIONS (E.G. WHEN OPERATING NEAR LARGE METALLIC STRUCTURES OR MAG DEGR INDICATED), THE DG MODE (WITH CORRECT HEADING) SHALL BE USED. Description
N TR
O
The Ground Trajectory Command in Hover (GTC.H) mode is an upper mode which assists the pilot in acquiring and maintaining hover.
C
O
– When engaged from forward flight, the mode will acquire zero ground speed.
C
O
Principally, the GTC.H mode shall be flown “hands– on, feet–on“. Even when the controls are “released“, the pilot should cautiously keep hand and feet at the controls.
O N
LY
–
NOTE
PY
N
O
T
– In hover, the GTC.H mode maintains zero ground speed and constant heading when the cyclic stick and pedals are released.
The GTC.H mode can be engaged from any flight condition. When accelerating from hover, the GTC.H mode will automatically revert to GTC mode when forward groundspeed > 20 kt.
IN
ST
R
U
C
TI
O N
Conditions & Limitations
When using the beep function, the maximum lateral speed is 5 kt, the maximum rearward speed is 10 kt. Higher speeds can be obtained by overriding the cyclic.
FO
R
Armament / Engagement by pilot Double press on the GTC sw (3). action Automatic engagement
GTC is automatically engaged from GTC.H mode when accelerating forward above 20 kt groundspeed.
Display / Voice messages
FND AFCS strip (1): GTC.H label in pitch and yaw/roll column (4). – Groundspeed reference is shown as a green circle in the hover indication (5). – Heading reference is shown as a green triangle on the compass indication (low speed only) (5). – A semi–circle in the NAVD page and on the hover indication showsthe approximate aircraft stopping position during deceleration to hover with GTC.H mode (5).
MANUFACTURER’S DATA Rev. 9
7 – 3 – 65
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Reference management
GTC.H engaged in forward flight: – Forward/aft cyclic beep inputs: Changes the rate of deceleration and consequently the stopping position (semi–circle indication on the NAVD changes). GTC.H engage in hover: – Short cyclic beep inputs: Each beep input modifies the position reference by approximately 1 meter.
ED
– Long cyclic beep inputs: Increases the groundspeed up to 5 kt laterally and up to 10 kt rearward.
N TR
O
LL
– Cyclic stick input: Changes the aircraft position. When the controls are released, the aircraft returns to a new hover position (zero ground speed). – Left/right collective beep: Changes the heading reference.
T
C
O
– Pedal input: Slews the heading reference. When the pedals are released, heading will be maintained again. Press AP UM OFF pb (2) on cyclic.
O
Disarmament / Disengagement
PY
N
or:
Engage incompatible mode. GTC.H is automatically disengaged to GTC accelerating above 20 kt (forward) groundspeed.
Compatibility with other modes
The GTC.H mode is incompatible with GTC, IAS, HDG, TRK, NAV, LOC, APP, V.APP, GS, or VOR.
when
O N
LY
–
C
O
Automatic disengagement
FO
R
IN
ST
R
U
C
TI
O N
Engagement of these modes will disengage the GTC.H mode.
7 – 3 – 66
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
3
ED
2
17
16
16
1 500
15
14
14
13
13
100 80
10
10
20
20
3
VY
33
R N G
N
6
W
E 12 21
S
15
O N
N 000 A V FMS INS/GPS 6.0NM 4 min
415 Kg
SVS
O
C 33 30
E
30
24 + B R G –
6
2690
10 10
W
21
30
S
12 15
RANGE 1 NM
GTC.H mode – Engagement / disengagement and indications
FO
R
IN
ST
R
U
Fig. 7-3-29
OAT 20
A C K
3
N
TI
O N
SCT
5
C
BKD2_FLH_0481_R
24
DCPL
B A R O
600 1013 200 DA hPa DH
DTK
+ L U M –
D H
3
30
GTC.H
T
17
10
GTC.H
O
20
10
C
2
20
–
4
120
ALT
D A
LY
6
18
3 4
N
101
+ C T R S –
CLOCK
GTC.H
PY
GTC.H
O
ALT
N TR
O
LL
1
MANUFACTURER’S DATA Rev. 2
7 – 3 – 67
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
O
T
C
O
N TR
O
LL
ED
DESCRIPTION OF SYSTEMS
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
Intentionally left blank
7 – 3 – 68
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.4
DUAL HYDRAULIC BOOST SYSTEM
7.4.1
Hydraulic power system The hydraulic power system generates and supplies pressure to boost the pilot inputs and transmit them to the actuators of the flight control system. For redundancy reasons, the hydraulic system consists of two similar but independent pressure supply systems (see Fig. 7-4-1 and 7-4-4). Both pressure supply systems and the main rotor actuators are installed on a module plate assembly, which is located on the roof in front of the main transmission. The tail rotor actuator is installed on the tail rotor gear box.
LL
ED
The pumps of both systems are driven by accessory drives of the main transmission. They supply the main rotor actuators and the tail rotor actuator with operating pressure.
N TR
O
7.4.1.1 Degraded operation
O
T
C
O
If one of the pressure supply systems fails, the normal system continues to supply the main and tail rotor actuators. The generated output forces of the hydraulic actuators will be maintained at 50% of the normal operation value. This booster force is sufficient to provide flight control actuation during all normal maneuvers.
C
O
PY
N
In case of fluid loss in system 1, the supply of the tail rotor actuator is automatically shut off by the mechanically actuated emergency shut-off valve (ESOV) which is integrated into the valve block/reservoir. In that case, the tail rotor controls are boosted by system 2 only.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
In case that fluid is lost from both hydraulic systems, the tail rotor controls will no longer be boosted, but system 1 will continue to boost the main rotor controls.
MANUFACTURER’S DATA Rev. 0
7–4–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
1
LL
ED
4
3
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
2
IN
BKD2_FLH_0043_R
ST
R
U
C
TI
O N
6
FO
R
5
Fig. 7-4-1
Hydraulic pressure supply systems and actuators
1
Tail rotor actuator
2
Hydraulic pump system 1
3
Hydraulic pump system 2
4
Main rotor actuators
5
Valve block / reservoir system 1
6
Valve block / reservoir system 2
7–4–2
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.4.2
Hydraulic indication and testing system
7.4.2.1 Hydraulic indication The hydraulic pressure of both pressure supply systems is indicated on the VMD (see Fig. 7-4-2). Refer to Sect. 2 for limit markings. The VMD hydraulic pressure is continuously monitored by the avionics system. Any exceedance of the caution range or an unusually high or low pressure is presented on the master list (HYD OVERLIMIT or HYD TREND). Master list messages for the hydraulic system are indicated on the FND above 40% NR (see Fig. 7-4-2). Refer to Sect. 7.13.6 for complete list of master list messages.
B A R
72 9.0 FUELKg
47
D A T A
314
MGB OIL B B A A R R
72 9.0
30
10 2
R N G C R S
TIME ZONE 101. 0
CONF
WEIGHT
PY O
STATUS
+ B R G –
C
EPC
+ L U M –
FSD
N 354 1.0 A V FMS GPS INS/GPS LFMH 20.0NM 12min DCPL
ND
LL
O 3
10 20
17
16
16
1 500
15
14
14
13
13
600 DA
3
20
DTK
101. 0 % N2 101. 0 % EPCPL REPORT
20
VY
17
D A
D H B A R O
1013 200 hPa DH
20
10
2
10
HYD1
A C K
LOW PRESS
415 Kg SCT
WXR
SVS
OAT 25
+ B R G –
LY
–
+ L U M –
80
10
N
G2
FF Kg/h 137
54
100
3.0 3.0
G1
100
4
N
2 h 30 min
30 %
ENG OIL B A R
10
N U M
IBF
IAS
20
C
ENG OIL B A R
85 103
FF Kg/h 137
N1
94.0 %
20
120
710 N1
94.0 %
HDG
18
CHK VNE
T
700 10 %
ALT
101 6 TOT
IBF
+ C T R S –
CLOCK
55.0 %
TOT
HYD
+ C T R S –
EFB
N TR
MISC
TRQ
55.0 %
B A R
BKD2_FLH_0429_R
DMAP
TRQ
R C N F
1
VMS
O
S Y S T
NAVD
O
FND
MFD – FND
ED
MFD – VMD
Hydraulic indication on VMD and FND – typical display
O N
Fig. 7-4-2
Hydraulic pressure indication
2
Master list area
C
TI
O N
1
R
U
7.4.2.2 Hydraulic system test
FO
R
IN
ST
The hydraulic system can be tested on ground, if NR ≥ 50%, by means of the TEST HYD switch located on the overhead panel (see Fig.7-4-3). Refer to Sect. 4 for hydraulic system test. Selecting spring loaded test switch position SYS1 disengages the hydraulic supply system 2 and the respective caution message is indicated on the FND. Selecting spring loaded position SYS2 disengages the hydraulic supply system 1, including the tail rotor shut-off valve, and the respective caution messages are indicated on the FND. Cyclic and pedal control forces will remain unchanged during the hydraulic system test, irrespective which system is tested. BKD2_FLH_0042_R
SYS1
SYS2
HYD
Fig. 7-4-3 MANUFACTURER’S DATA Rev. 0
OFF O F F
P–FLT O F F
EXT
1
EXT/ WARN
FIRE TEST
2
LAMP
Hydraulic system test switch – typical installation
7–4–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
System 1
Tail Rotor Actuator
System 2
O
LL
ED
System 1
C
O
N TR
Main Rotor Actuators
N
O
T
System 2
Valve Block
Reservoir
O N
O N
LY
–
C
O
PY
Shut– off Valve Valve Reservoir Block
Pump
ST
R
U
C
TI
Pump
IN
Pressure Supply System 1
Relay
Pressure Supply System 2
FO
R
Relay
Pressure line
Switch TEST HYD
BKD2_FLH_0040_R
Suction line Return line
FND
Fig. 7-4-4
7–4–4
Indicating and Testing System
VMD
Hydraulic system – schematic MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.5
POWER PLANT AND RELATED SYSTEMS
7.5.1
Engines The helicopter is powered by two Turbomeca ARRIEL 2E turboshaft engines. The ARRIEL 2E engine consists of 5 modules (see Fig. 7-5-1). The engines are located in a separate fireproof compartment aft of the main trainsmission and above the passenger/cargo compartment.
ED
Each engine transmits its power to the main transmission via an independent drive shaft.
LL
4
N TR
O
3
TI
BKD2_FLH_0018_R
O N
O N
LY
–
C
O
PY
N
O
T
C
O
2
U
C
5
Fig. 7-5-1
Engine modules and compartments overview
FO
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IN
ST
R
1
1
Module 01: Transmission shaft
2
Module 02: Axial compressor including accessory drive gearbox
3
Module 03: Centrifugal compressor with combustion chamber and single stage compressor
4
Module 04: Single stage free power turbine
5
Module 05: Reduction gearbox
MANUFACTURER’S DATA Rev. 0
7–5–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
3
2
5
4
6
7
TI
O N
13
O N
LY
BKD2_FLH_0068_R
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
1
11
10
9
8
Engine components
ST
R
U
C
Fig. 7-5-2
12
Fuel metering unit
2
Air inlet
3
Fuel filter
4
FO
R
IN
1
5
Bleed valve
6
Fuel valve assembly (start/stop electro valve)
7
Oil filter
8
Electrical magnetic plug
9
Oil temperature transmitter
10
Oil pump
11
Oil pressure transmitter
12
Chip detector (front bearing)
13
Mounting struts
7–5–2
Fuel flow meter (optional)
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.5.2
Engine operation and control The engines are controlled and monitored by EECUs (Electronic engine control unit) (see Fig. 7-5-3). The EECUs provide all FADEC (Full Authority Digital Engine Control) functions which are necessary for economical, comfortable and safe engine operation.
7.5.2.1 General architecture
ED
Each engine is controlled by a two-channel EECU (Electronic engine control unit). The two channels of each EECU communicate with each other and with the helicopter’s avionic system. In addition, the two EECUs communicate with each other.
N TR
O
LL
The EECU constantly calculates the engine fuel demand and actuates the metering valve. The metering valve is equipped with two independent stepper motors, one being connected to each EECU channel, but only the channel in control actuates the metering valve.
T
C
O
The main engine control parameters N1, N2, and T45 are acquired separately for each channel by redundant sensors. The sensors for further parameters are common to both channels (e.g TQ, EOP, EOT etc.).
O
PY
N
O
Some analogue and discrete signals are transmitted directly from the engine to the helicopter (fire detector, chip detector, backup N1 speed signal, fuel flow from optional flowmeter).
LY
–
C
Each engine comprises an engine data recorder (EDR) for maintenance, troubleshooting and data storage purposes.
O N
Chip detection Eng1
EDR 1
R FO AMC2
Warning Unit
OEI30”/OEI2’
Discrete outputs EECU2
A
Ch. B Ch. A EECU Engine 2
BKD2_FLH_0069_R
Fire detector(s)
B
LVDT ENG2 MAIN SW: OFF/IDLE/FLIGHT
Fig. 7-5-3 MANUFACTURER’S DATA Rev. 0
Engine 1 Analog N1_1
U R
Ch. A Ch. B
IN
B
Discrete outputs EECU1
Sensors (N1, N2, T4 etc)
Sensors (N1, N2, T4 etc)
Analog N1_2
C AMC1
ST
A
EECU Engine 1
Fire detector(s)
LVDT
TI
O N
ENG1 MAIN SW: OFF/IDLE/FLIGHT
Engine 2
EDR 2 Chip detection Eng2
Simplified avionic – engine system architecture
7–5–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.5.2.2 Engine control panel The engine control panel (see Fig. 7-5-4) is installed in the instrument panel. FADEC TRAINING FADEC EMER EMER VENT
ON
OFF
ED
5
Engine control panel – typical installation
N TR
Fig. 7-5-4
OFF
OFF
4
3
I D L E
ON
OFF
2
FLIGHT
LL
I D L E
BKD2_FLH_0017_R
1
ENG II
VENT
O
ENG I FLIGHT
ENG MAIN switch
2
Switch guard
3
VENT switch
4
FADEC EMER switch
5
TRAINING selector switch (for a description of the OEI training mode, refer to FMS 9.1–3 “OEI Training”)
C
O
PY
N
O
T
C
O
1
LY
–
7.5.2.3 Engine starting / stopping
FO
R
IN
ST
R
U
C
TI
O N
O N
The starting sequence is fully automatic. It is initiated by setting the ENG MAIN switch for an engine from OFF to IDLE or FLIGHT. During starting phase, T45 and N1 are monitored by the EECU, and the engine is protected against over-temperature. If an over-temperature is detected, the engine starting sequence is aborted automatically. If the first attempt of engine ignition fails (ignition after raise of N1), the engine is automatically decelerated and a second start attempt is launched. If the second start attempt also fails, it has to be manually interrupted by setting the ENG MAIN switch back to OFF. Starting of both engines at the same time is not possible. Even when both ENG MAIN switches are set to FLIGHT at the same time, the engines are started one after the other. Starting of the first engine is not possible when the rotor brake is engaged. When the ENG MAIN switch is put to OFF position, the engine’s stop electrovalve is closed, shutting off the fuel flow to the combustion chamber. Below a certain N1 threshold, the metering valve is additionally closed. If, after the OFF command, the engine is not decelerated (e.g. due to stop electrovalve failure), the metering needle is closed, setting the fuel flow to zero to stop the engine. 7.5.2.4 N2 control In IDLE mode, the engine is normally governed to a fix N2_datum of 78%. When one engine is in FLIGHT and another engine is in IDLE, the N2 of the idling engine may be higher in order to maintain a minimum N1 of 62%. The N2 control in FLIGHT is fully automatic. Each channel of the EECU receives an N2_datum from the avionic system. The N2_datum values are checked for discrepancies
7–5–4
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
between the two channels and between the two EECUs. In case of discrepancy, an N2_datum backup value of 104% is used. 7.5.2.5 Rotor speed governing In normal operation the (N2_datum) is automatically calculated by the avionic system as a function of density altitude. See Fig. 7-5-5 for rotor RPM (NR) vs density altitude under AEO conditions. Under OEI conditions (including OEI training mode), the NR law for IAS < 55 kt is used at all airspeeds. 108 107
ED
106
LL N TR
O
104 103
O
102
T
C
101 100
O
Rotor rpm [%]
105
N
99
IAS 55–70 kt
C
O
97
IAS > 120 kt
–
96
0
1000
2000
3000
4000
5000
6000
7000
8000
9000
10000
11000
12000
Density altitude [ft]
Rotor RPM (NR) vs Density Altitude
U
C
TI
O N
Fig. 7-5-5 7.5.2.6 Load sharing
LY
95
O N
BKD2_FLH_0051_R
IAS < 55 kt
PY
98
FO
R
IN
ST
R
To maximize the total power delivered by the two engines, during normal operation around AEO MCP and AEO TOP rating, the engines are matched automatically not only on torque but on the minimum margin on their first limit to N1, T4 or TQ. This so called FLI matching principle can lead to a certain TQ split of the engines when the engines are operated around AEO MCP or AEO TOP (e.g. when one old and one new engine are installed on the helicopter).
7.5.2.7 Engine overspeed protection Each engine is monitored by an independent and separate overspeed circuit inside the EECU box. The engine overspeed protection system uses different and independent sensors for N2 survey than the regular N2 speed indication. In case of an overspeed detection (N2 > 120%) the respective engine is shut off automatically by activating the overspeed fuel shut off valve. In this case, or in case of a failure detection of the overspeed system on the engine, the engine overspeed protection of the other engine will be disabled to prevent untimely shutdown of the remaining engine. MANUFACTURER’S DATA Rev. 0
7–5–5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.5.2.8 Ultimate backup mode (FADEC EMER) In case of FADEC FAIL condition, the fuel metering valve of the affected engine is blocked and the engine does not respond to power/collective variations. In some FADEC FAIL cases, control of the affected engine, can be regained by activating the ultimate backup mode. When ultimate backup mode is selected, the TOT of the affected engine is matched to the TOT of the normal engine. The ultimate backup mode is activated by setting the FADEC EMER switch of the affected engine to ON. The ultimate backup mode (FADEC EMER) may also be used if a governing problem (e.g. oscillating torque values) is encountered. Refer to Section 3.
ED
7.5.2.9 Engine ventilation
7.5.3
N TR
O
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Engine ventilation can be performed using the VENT switch on the engine control panel. Refer to Section 2 and Section 4 for engine ventilation procedure. Engine oil system
C
O
Each engine has its own independent and separated oil system (see Fig. 7-5-6).
N
O
T
The engine oil pressure (EOP) and engine oil temperature (EOT) are acquired by the EECU and are sent to the avionic system.
C
O
PY
There is no mechanical oil filter blockage indicator. The oil filter blockage is surveyed by an oil pressure sensor up- and downstream of the filter. The Δp calculation is done inside the EECU. An oil filter (pre-)blockage is indicated by an alert in the Master list.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
There is one electrical magetic plug downstream of the oil pressure scavenge pump and one mechanical chip detector on the front and rear bearing.
7–5–6
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Oil Tank
T
ED
Oil Cooler
T
C
O
N TR
O
LL
P
T
M
N
O
P
M
Oil Filter Mech. Driven Pump
C
O
M
PY
T
Drain Valve
LY O N
FND
O N
VMD
TI
BKD2_FLH_0071_R
–
EECU
Press Relief Valve M
Chip Detector
P
Press Transmitter
T
Temp. Transmitter
Engine oil system schematic
Engine fuel system
ST
7.5.4
R
U
C
Fig. 7-5-6
Thermo Bypass Valve Supply line Return line Vent line Drain hose
FO
R
IN
The engine fuel system (see Fig. 7-5-7) is monitored by the fuel pressure transducer (6) upstream of the fuel filter inlet and the combined fuel pressure / temperature transducer (3) downstream of the fuel filter (5). The fuel flow meter (16) is an optional equipment.
MANUFACTURER’S DATA Rev. 0
7–5–7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
11
10
12
13
9 P3
8
15
LL
To drain collector
ED
14
O
N TR
O
13
16
N
O
T
C
7
18
–
C
O
PY
6
17
O N
LY
5
13
ST
R
20 To drain collector
21
2
BKD2_FLH_0072_R
FO
R
IN
3
U
C
TI
O N
4
19
22 1
23 Return to fuel tank
Fig. 7-5-7
Engine fuel system schematic
1
Air purge valve
2
Oil / fuel heat exchanger
3
Fuel pressure / temperature transducer (downstream)
7–5–8
Fuel inlet
MANUFACTURER’S DATA Rev. 0
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Bypass valve
5
Main fuel filter
6
Fuel pressure transducer (upstream)
7
Pressurizing valve
8
Injection manifold purge valve
9
Stop electrovalve
10
Pressurizing valve
11
Fuel injection
12
Start injectors
13
Screen filter
14
Start injection purge valve
15
Start electrovalve
16
Fuel flow meter (optional)
17
Metering needle
18
Actuator
19
Constant delta p valve
20
Relief valve
21
High pressure pump
22
Low pressure pump
23
Ejector
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
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LL
ED
4
MANUFACTURER’S DATA Rev. 0
7–5–9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.5.5
Engine indications Engine parameters are indicated on the VMD and FND (FLI) (see Fig. 7-5-8). 2
3
700
710
ENG OIL B A R
B A R
103 103
72 9.0 FUELKg
2 h 30 min
FF Kg/h 137
47
D A T A
314
54
IBF
N1
94.0 %
30 %
ENG OIL B A R
N U M
4
MGB OIL B B A A R R
72 9.0
30
2
R N G
FF Kg/h 137
101. 0 % N2 STATUS
CONF
10
10
16
16
1 500
15
14
80
14
13
13
10
10
20
20
3
20
101. 0 %
WEIGHT
+ B R G –
+ L U M –
20
10 DTK
B A R O
4
A C K
ENG TREND
ND
D H
10
RNP FSD
N 354 000 3.00 1.0 A FMS V GPS INS/GPS LFMH 20.0NM 6.0NM 12min DCPL
600 1013 200 DA hPa DH
3
D A
HDV
WXR
SVS
415 Kg OAT 32
+ B R G –
PY
N
O
EPC
17
VY
C R S
TIME ZONE
EPCPL REPORT
17
N
G2
101. 0
+ L U M –
20
100
+ C T R S –
CLOCK
20
3.0 3.0
G1
100
MISC IAS
O
N1
94.0 %
10 %
DMAP HDG
18
6 TOT
IBF
VMS ALT
101 120
55.0 %
TOT
B A R
NAVD
TRQ
55.0 %
HYD
+ C T R S –
EFB
ED
MISC
LL
DMAP
TRQ
R C N F
BKD2_FLH_0430_R
VMS
C
S Y S T
NAVD
N TR
FND
T
1
MFD – FND
O
MFD – VMD
Engine indication on VMD and FND – typical display
2
FLI
3
NR/N2 indication
4
Master list area
–
Engine parameters indication
O N
O N
LY
1
C
O
Fig. 7-5-8
TI
7.5.5.1 First limit indicator
U
C
The First Limit Indicator is a dedicated powerplant information display located on each FND.
FO
R
IN
ST
R
The FLI displays the position of the collective pitch on a moveable scale ranging from 0 (full down) to 10 (full up). Upon this scale, the collective position at which the power limits are expected to be reached is shown. An additional ”blue line” indicates the maximum available OEI power at the 30sec rating. A white dashed line predicts the collective position below which NR and N2 will desynchronize. The power margins – with respect to the various torque, N1, and TOT limits – are automatically calculated by the FADEC. For each limit (MCP, TOP, etc), the FLI calculates the associated collective pitch position and selects the smallest margin (i.e. the limit that will be reached first when the collective is increased). The FLI is a highly complex instrument, which needs to anticipate the engine response for a given collective input. As a result, during a very rapid collective input, the FLI may indicate the exceedance of a limit before the engine has actually surpassed it. This is easily recognizable because the color enhancement of the various limits (i.e. filling of the amber rectangle, the red line appearing) is based on the actual engine power. Therefore, the exceedance of a limit on the FLI will only be recorded when the associated color enhancement was indicated.
7 – 5 – 10
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
The FLI indications in AEO are as follows (see Section 2 for details concerning the associated limitations):
6
1 2
3
4
6
7
BKD2_FLH_0402_R
O
T
C
O
2
FLI indication – typical display
C
O
Fig. 7-5-9
PY
N
8
N TR
O
LL
5
ED
4
AEO transient limit When this limit is exceeded, a red band, which extends up to the top of the scale, will appear.
2
AEO maximum limit When this limit is exceeded, a red band extending from the AEO takeoff power limit to the AEO transient limit will appear.
C
At airspeeds above VY+20 kt, this limit is the same as the AEO maximum continuous limit.
R
U
NOTE
TI
O N
O N
LY
–
1
AEO 30 minute Take-Off Power range. When Take-Off Power (TOP) is used, the amber rectangle will be filled amber.
4
OEI safe collective pitch position (”blue line”) The ”blue line” shows the power margin at the OEI 30sec limit. – If the ”blue line” is above the reference, the collective pitch position is ”safe”, i.e. it does not need to be immediately lowered in case of a single engine failure, but can be maintained for at least 30 seconds.
FO
R
IN
ST
3
– If the ”blue line” is below the reference, the pilot will need to lower the collective to the approximate position of the ”blue line” to maintain NR in the case of a sudden single engine failure. In forward flight, the ”blue line” position accounts for the NR increase in OEI. NOTE 5
The ”blue line” is based on the actual power margin of the engines. It automatically selects the most limiting engine.
Collective pitch scale reference
MANUFACTURER’S DATA Rev. 0
7 – 5 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Collective pitch scale (showing 40% collective position in this example)
7
Desynchronization line The desynchronization line shows the collective pitch position where (almost) zero torque is reached. When the collective is lowered below the ”desynchronization line”, the pilot shall include NR into his scan, because the aircraft could enter autorotation.
8
AEO counter The AEO counter appears when less than 90 seconds remain in the AEO takeoff power range. The counter starts flashing when less than 15 seconds remain. When the counter is full, the AEO takeoff power time limit of 30 minutes was exceeded. The counter will disappear when power is set below MCP.
O
LL
ED
6
N TR
BKD2_FLH_0440_R
PY
– N1 difference between the engines > 6%N1.
N
O
– Torque difference between the engines > 53 %, or
T
C
O
On the BK117 D–2, OEI detection is automatically performed by the FADEC if a power split condition is met, in the nominal case when:
–
C
O
When this condition is detected, the specific power split audio and the OEI indication will be triggered.
10
2
1
6
Fig. 7-5-10
7 – 5 – 12
OEI
5
BKD2_FLH_0441_R
FO
R
IN
ST
R
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C
TI
O N
O N
LY
The FLI indications in OEI are as follows (see Section 2 for details concerning the associated limitations):
8
6
3
4
FLI indication – typical display
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
OEI topping triangle The triangle shows the current FADEC limit. When the topping switch is pushed above OEI MCP, this triangle will jump between the OEI 30sec and OEI 2min limit. Unless a major FADEC failure occurs, it is impossible to exceed the FADEC limit.
2
OEI 30sec power limit The line shows the maximum OEI 30sec power available. When the OEI 30sec rating is used (i.e. power above the OEI 2min limit), a red dashed rectangle appears.
3
OEI 2min power limit The line shows the maximum OEI 2min power available. When the OEI 2min rating is used (i.e. power above the OEI continuous limit, but not above the OEI 2min limit), an amber dashed rectangle appears.
4
OEI continuous power limit
5
OEI flag
6
OEI counter The OEI counter indicates the power being used (red = OEI 30sec; amber = OEI 2min). The counter appears as soon as the associated power rating is being used. It starts flashing when less than 5 seconds remain. When the counter is full, the associated power time limit was exceeded. As soon as the power is lowered below OEI continuous, the counters disappear.
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
1
C
TI
O N
BKD2_FLH_0442_R
IN
OEI mode detected OEI was detected and OEI indications are shown
R
OEI
ST
R
U
Further symbols which may appear in the FLI are:
Training mode indication Training mode is active. The power margins will be indicated as in OEI.
FO
T
FF AA DI E CL
FADEC FAIL A FADEC fail condition was detected. The FLI indication indicates power margins for AEO and OEI in an AEO format. See section 3.8.2 for details. Heating on Bleed air heating is on. The electrical heater will automatically switch on when demisting is selected. Heating partially failed Bleed air heating is on. The electrical heater is off due to an overheating condition.
MANUFACTURER’S DATA Rev. 2
7 – 5 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
EPC
Engine power check in progress High or low NR indication (see section 7.5.5.2)
or or
7.5.5.2 NR / N2 indicator on FND
N TR
O
LL
ED
The NR/N2 indicator on the FND covers the NR/N2 range between 80% and 120% NR. For engine start, the NR/N2 indicator on the VMS page shows the range between 0% and 120% NR. The inner scale of the instrument shows the rotor speed, NR, and its limit; the outer scale shows the engine power turbine speed, N2, and its limits. For details concerning the limitations, refer to Section 2.10.
C
O
1
O
6
T
7
4
LY
–
101
Fig. 7-5-11
3
NR / N2 indicator on FND
C
TI
10
O N
O N
2
R
U
N2 indication – Engine 1:
IN
ST
1
9
C
O
5
BKD2_FLH_0401_R
PY
N
8
FO
R
– Engine 2:
2
The matched N2 needles merge to a ”trident” image, which allows immediate identification of a normal AEO condition. When an N2 is below 80%, the needle is shown outside of the scale. NR indication (needle and grey area)
3
Digital rotor speed (NR) indication The indication is shown in amber or red inverse video when the NR limits are exceeded in flight. The indication is shown with a white frame, when the rotor brake can be applied (NR < 50%).
4
Minimum power minimum power off NR (>2200 kg) and minimum power on transient NR. When this limit is exceeded, a red band from 80% to the transient limit will appear.
7 – 5 – 14
MANUFACTURER’S DATA Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Low NR transient range The amber segment ranges from the minimum power off NR, NRmin, (which is variable) and the minimum transient NR. When NR is below NRmin, the segment is automatically highlighted.
6
Minimum continuous N2
7
Maximum continuous N2
8
High NR transient range (power on) When NR is within this range, the segment is automatically highlighted in amber.
9
High NR transient range (power off) When NR is within this range, the segment is automatically highlighted in red.
10
Maximum power off transient NR When this limit is exceeded, a red segment extending to 120% is shown.
N TR
O
LL
ED
5
Audio
Condition
N
O
FLI
T
NR/N2 indicator
C
O
For alerting purposes, high and low NR is indicated on the FND as follows:
PY
NR too high
C
O
BKD2_FLH_0443_R
Fast beep
C
TI
Lower collective (in direction of the arrows on the FLI)
IN R FO
BKD2_FLH_0445_R
ST
R
90
NR too low
Slow beep
U
BKD2_FLH_0444_R
O N
O N
LY
–
113
Increase collective (in direction of the arrows on the FLI
82
MANUFACTURER’S DATA Rev. 2
NR too low Slow beep Lower collective (in direction of the arrows on the FLI)
7 – 5 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.5.5.3 Vehicle management page indications Detailed engine parameters can be found on in the upper area of the VMS page. All indications related to engine 1 are located on the left hand side of the area; engine 2 related items are shown on the right. 2
3
4
5
6
3
IDLE
1
IDLE TRQ
84.0 %
T
TOT
LL
85.0 %
ED
TRQ
TOT
700
710
IBF
N1
94.0 %
O
30 %
C
Vehicle management page indications
O
T
Fig. 7-5-12
IBF
N1
94.0 %
10 %
O
BKD2_FLH_0446_R
2
N TR
1
1
Engine bleed valve indication (open when
2
Engine status flag The following flags can be displayed: – START indicates that the engine is in starting mode.
C
O
PY
N
is shown).
IDLE indicates that the engine is in IDLE.
–
FAIL indicates that the engine has failed (only indicated in flight).
–
FADEC FAIL indicates that the engine has a level 3 FADEC failure.
O N
LY
–
–
O N
– When the engine is FLIGHT (normal operation), no flag is shown. Engine torque, TOT and N1 indication For limitations, refer to section 2.11.
4
Engine training symbol
5
Heating symbol White for heating on, amber for heating degraded (for details, see FND symbols).
6
Engine counter White in AEO, amber or red in OEI (for details, see FND symbols).
FO
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3
Engine oil temperature and pressure indications can also be found on the VMS page. Engine 1 is shown on the left and engine 2 on the right. The digital values can be selected with the NUM key on the VMS. The digital values will be shown in white, amber or red inverse video, if the values are in a pre-cautionary ( ENG TREND alert), a cautionary, or warning range.
7 – 5 – 16
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
BKD2_FLH_0448_R
ENG OIL B A R
100
Fig. 7-5-13
ENG OIL B A R
8.0
100
8.0
Engine oil temperature and pressure indications
O C
100. 0 % N2 100. 0 %
2
O N
LY
–
2
Additional NR/N2 indicator
O N
Fig. 7-5-14
BKD2_FLH_0449_R
O
1
PY
N
100. 0
3
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An additional NR/N2 indicator is shown on the VMS page. This indicator extends from 0% to 120% NR. The indications are identical to the indications on the FND page, with the following variations:
Digital NR indication (0.1% accuracy).
2
Digital N2 indication (0.1% accuracy). Engine 1 (left) and engine 2 (right).
3
Rotor brake range Appears in white, when rotor speed is below 50%.
R
Engine fire detection and extinguishing system
FO
7.5.6
IN
ST
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1
7.5.6.1 Fire detection system Each engine system is equipped with three temperature sensing fire detectors, one installed to the engine, the other two installed to the aft firewall. The electrical power for the fire detectors is provided by the ESS BUS 1/2. 7.5.6.2 Fire extinguishing system The fire extinguishing system is a semi–automatic system with an extinguishing logic, integrated into the warning unit. Two extinguishing bottles are installed to the right hand side of the aft deck. The bottles have two outlet ports each, guarded by explosive cartridges. From these outlets ports tubes are routed to the respective engine compartment. The extinguishing agent used is HALON 1301 with nitrogen as a propellant. MANUFACTURER’S DATA Rev. 0
7 – 5 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
O N
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–
C
O
BKD2_FLH_0193_R
PY
N
O
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Pressure gauges, which can be read through openings in the cowling, indicate the bottle pressure and are checked during preflight. A mechanical discharge indicator is connected to the pressure outlet. If a bottle discharges, a red disc will indicate the discharge.
Fire extinguishing system
O N
Fig. 7-5-15
TI
7.5.6.3 Fire indication and operation of the extinguishers
ST
R
U
C
If a fire (excessive temperature) is detected in one of the engine compartments, a voice message and the ENG FIRE 1/2 will appear in the master list. On the warning unit, the FIRE caption on the EMER OFF SW 1/2 button will illuminate.
R
IN
To activate the fire extinguishers, the illuminated FIRE switch needs to be pushed. This causes:
FO
– The fuel shut–off valve to close (indicated by a FUEL VALVE CLSD caution on the master list) – The green ACTIVE light on the warning unit to come on – The amber BOT 1 label on the warning unit to come on To activate the first extinguisher bottle, push the bottle select switch. This causes: – The green EXT light above the bottle select switch to illuminate – The selected bottle to discharge, as soon as N1 is below 45%. Successful activation of the bottle will be indicated by the FIRE BOT1 USED caution in the master list. If the fire is not extinguished with the first bottle, the second bottle is automatically available after 15 seconds. This is indicated by the BOT2 label on the selector switch. If the fire is not
7 – 5 – 18
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
extinguished by the first bottle after one minute, the second bottle should be discharged. Pushing the bottle select switch will immediately discharge the second bottle (since N1 is already below 45%). EXT BOT 1
FIRE
BOT 2
EMER OFF SW 1 ACTIVE
LOW FUEL 1 BAT OVHT
ENG 1 FAIL
ROTOR ENG 2 LOW RPM FAIL FUEL 2 MGB CARGO AP OIL P SMOKE
EMER OFF SW 2 ACTIVE
EXT
FIRE
BOT 1 BOT 2
BKD2_FLH_0192_R
Warning unit indication – fire ENG 1, FIRE sw pushed, BOT1 active and discharching
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Fig. 7-5-16
MANUFACTURER’S DATA Rev. 0
7 – 5 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
O
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DESCRIPTION OF SYSTEMS
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Intentionally left blank
7 – 5 – 20
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.6
FUEL SYSTEM (see Fig.7-6-2)
7.6.1
Storage
Supply
LL
7.6.2
ED
Fuel is stored in underfloor compartments, using bladder type, crash resistant fuel cells, comprising a main tank (forward and aft part) and a supply tank, divided in a left and a right chamber. They are interconnected by means of a flexible fuel supply and hose system (overflow channels and transfer channels). Each tank is equipped with equipment plates as attaching platforms for the operating and monitoring components. The system is equipped with 5 drain valves. The left supply tank provides fuel for the left engine, and the right supply tank for the right engine. An internal ventilation system ensures ventilation of the fuel tanks during flight and fueling. The fuel system has a usable fuel capacity of 903.8 l.
O
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The fuel supply system consists of two independent systems, one for each engine. Fuel is transferred from the main tanks to each supply tank by two electrically driven fully redundant centrifugal transfer pumps, installed in the forward main tank. A jet pump, driven by both fuel transfer pumps, is installed in the aft main tank to transfer the fuel from the aft main tank to the fwd main tank. Surplus fuel in the supply tanks returns to the main tank via two overflow channels.
For helicopters with S/N 20231 and subsequent or after SB BK117D–2–28–001
–
EFFECTIVITY
C
O
PY
N
After starting the engines, the fuel pumps are activated by the FUEL XFER PUMP F/A switches, located on the overhead switch panel (see Fig.7-2-5) and supplied via the XPMP–F/A circuit breakers.
All
ST
EFFECTIVITY
Double action FUEL XFER PUMP F/A switches – typical installation
R
Fig. 7-6-1
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Double action FUEL XFER PUMP F/A switches are installed instead of single action switches.
FO
R
IN
To ensure that all fuel is transferred from the main tank to the supply tanks, both pumps shall remain ON for the duration of the flight. Because the fuel pumps were demonstrated to be capable of ”running dry” for up to 30 min without damage, the pumps can safely continue to run, even when the main tank is empty. The prime pumps, one in each supply tank, serve to purge air from the fuel feed system and supply the engines with fuel during start. The prime pumps are activated by the FUEL PRIME PUMP 1/2 switches, located on the overhead switch panel (see Fig.7-2-5). During prime pump operation the FUEL 1/2 PRIME PUMP ON caution indication comes on. The prime pumps must be shut off during normal flight. The engine driven fuel pumps, mounted in the fuel control unit, draw fuel from each supply tank to the respective engine. Two electrically and individually operated fuel shut-off valves, one on each side of the fuselage underneath the engine deck are installed to immediately interrupt fuel supply to the related engine in case of emergency. The fuel shut–off valves are activated on the warning unit.
MANUFACTURER’S DATA Rev. 11.5
7–6–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.6.3
Monitoring system CAUTION
ENDURANCE IS CALCULATED BASED ON THE ENTIRE FUEL QUANTITY (MAIN + SUPPLY TANKS). THE ENDURANCE DOES NOT INCLUDE A FUEL RESERVE.
Five fuel quantity sensors are installed in the fuel system; two in the fwd main tank, one in the aft main tank and one in each supply tank. All sensors are electrically connected to the AMCs and the fuel quantity is indicated on the VMD and FND. The display system indicates the fuel quantity in the main tank and in the two supply tank chambers.
Before Helionix Maintenance Release 1
N
EFFECTIVITY
O
T
C
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The indicated fuel quantity of the two supply tank chambers represents the quantity measured up to the lower edge of the overflow channels. The fuel quantity measured by the supply tank sensors above the overflow channels is added to the fuel quantity indicated for the main tank. In a level attitude, the fuel will be indicated where it is actually located. At other flight attitudes, some of the fuel contained in the supply tanks may be indicated in the main tank or fuel may remain in the main tank even though the supply tanks do not indicate as full. The volume of the right hand supply tank is slightly larger. In case of total fuel starvation, the left engine will normally fail before the right engine does.
–
C
O
PY
When one fuel transfer pump (forward or aft) is running dry, the advisory alert MAIN FUEL LOW will be triggered. This alert will appear when the main tank fuel capacity is less than 50 kg.
O N
LY
When both fuel transfer pumps (forward and aft) are running dry, or when the fuel drops below 42 kg in the left supply tank or below 47 kg in the right supply tank, the caution FUEL RESERVE will appear.
IN
ST
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– In forward and/or descending flight (nose down attitude), fuel will tend to gather in the supply tanks. Because with a nose down attitude, the supply tanks hold more than the maximum indicated value of 47/54 kg, some of the supply tank fuel quantity will be indicated as part of the main tank. As soon as the main tank is empty (and both fuel transfer pumps are confirmed to ”run dry”), the FUEL RESERVE caution is triggered. In forward and/or descending flight, this may happen with up to 146 kg of total fuel remaining.
FO
R
– In hovering flight (nose up attitude), fuel will flow back from the supply tanks to the main tank. As a result, the main tank may not be fully empty yet, when the supply tanks start to empty. Therefore, with a nose up attitude, the FUEL RESERVE caution will normally be triggered with 100 kg or less of fuel remaining. An additional and independent fuel low level sensor is installed in each supply tank. If a fuel low level sensor detects a fuel quantity below 26 kg in a supply tank, the respective LOW FUEL 1/2 warning and associated voice message appears, irrespective of the fuel quantity indicated on the MFD. The remaining flight time is approx. 10 minutes. When a low fuel pressure at the inlet of the engine fuel pump is detected, the respective caution indication comes on.
7–6–2
MANUFACTURER’S DATA Rev. 11.5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
If the optional fuel flow sensors are installed, the remaining flight time (endurance) is calculated from the main and supply tank quantities and the actual fuel flow. The endurance is indicated on the VMD. Since endurance uses the actual fuel flow, the endurance obtained during climb or descent will not be representative. If the fuel transfer pumps are off or failed, the endurance will be based only on the fuel contained in the supply tanks. NOTE EFFECTIVITY
In case of OEI, the endurance is not reliable as it does not consider that the fuel from the supply tank supplying the failed engine is unusable. After Helionix Maintenance Release 1
LL
ED
When one fuel transfer pump (forward or aft) is running dry, the advisory alert MAIN FUEL LOW will be triggered (typically when the main tank fuel capacity is less than 50 kg). The MAIN FUEL LOW will also be triggered if the indicated main fuel quantity is below 40 kg.
N TR
O
When the fuel drops below 42 kg in the left supply tank or below 47 kg in the right supply tank, the caution FUEL RESERVE will appear.
O
PY
N
O
T
C
O
An additional and independent fuel low level sensor is installed in each supply tank. If a fuel low level sensor detects a fuel quantity below 26 kg in a supply tank, the respective LOW FUEL 1/2 warning and associated voice message appears, irrespective of the fuel quantity indicated on the MFD. The remaining flight time is approx. 10 minutes. When a low fuel pressure at the inlet of the engine fuel pump is detected, the respective caution indication comes on.
U
When LOW FUEL is indicated, the endurance calculation is shown as invalid (***). All
IN
EFFECTIVITY
ST
R
NOTE
C
TI
O N
O N
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–
C
If the optional fuel flow sensors are installed, the remaining flight time (endurance) is calculated from the main and supply tank quantities and the actual fuel flow. The endurance is indicated on the VMD. Since endurance uses the actual fuel flow, the endurance obtained during climb or descent will not be representative. If the fuel transfer pumps are off or failed, the endurance will be based only on the fuel contained in the supply tanks. In case of OEI, the endurance is based on the available fuel only (fuel of supply tank of the failed engine is not considered).
R
Refueling and grounding
FO
7.6.4
The refueling system comprises a filler neck, accessible through a lockable access cover, and a grounding connection. The filler neck, located on the left side of the fuselage, is equipped with a filler cap and is designed for gravity refueling. The grounding connection, located underneath the access to the filler neck, provides a means for static discharge after landing and during fueling of the helicopter. The time required to fill the tanks to max. capacity is approx. 11 minutes.
MANUFACTURER’S DATA Rev. 11.5
7–6–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ED
1
C
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16
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3
C
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15
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4 5
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14
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R FO BKD2_FLH_0021_R
7
8 9
10 13 11 12
Fig. 7-6-2
7–6–4
Fuel system – typical installation MANUFACTURER’S DATA Rev. 11.5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Engine 2
2
Engine 1
3
Engine driven fuel pump system 1
4
Aft main tank
5
Fuel sensor aft tank
6
Jet pump
7
Fuel shut-off valve system 1
8
Expansion tank
9
Fuel filler neck
10
Equipment plates (main fuel tank sensors and forward/aft pumps)
11
Supply tank system 1, LH section of split supply tank
12
Equipment plates
13
Supply tank system 2, RH section of split supply tank
14
Fwd main tank
15
Fuel shut-off valve system 2
16
Vent lines
17
Engine driven fuel pump system 2
LL O
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Fuel indications
LY
–
7.6.5
ED
1
O N
Fuel quantities are indicated in detail on the VMD and in simplified form on the FND (see Fig. 7-6-3).
U
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Master list messages for the fuel system are indicated on the FND (see Fig. 7-6-3). Refer to Para. 7.13.6 for complete list of master list messages.
ST
R
MFD – VMD
IN
FND
FO
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S Y S T
DMAP
MISC
700
B A R
103 103
FF Kg/h 137
ENG OIL B A R
ENG OIL B A R
72 9.0
72 9.0
FUELKg
2 h 30 min
47
314
54
IBF
N1
94.0 %
30 %
4
MGB OIL B B A A R R 30
2
R N G
FF Kg/h 137
101. 0 % N2
Fig. 7-6-3 MANUFACTURER’S DATA Rev. 11.5
EPC
STATUS
CONF
10
80
10
10
20
20
3
VY
DTK
101. 0 %
WEIGHT
+ B R G –
+ L U M –
FSD
DCPL
ND
17
16
16
1 500
15
14
14
13
13
D A
D H B A R O
20
10
N 354 1.0 A FMS V GPS INS/GPS LFMH 20.0NM 12min
17
600 1013 200 DA hPa DH
3
20
C R S
TIME ZONE
EPCPL REPORT
10 100
N
G2
101. 0
+ L U M –
20
3.0 3.0
G1
100
N U M
20
+ C T R S –
CLOCK
IAS 18
120
710 N1
94.0 %
10 %
HDG
101 6 TOT
IBF
D A T A
ALT
55.0 %
TOT
HYD
+ C T R S –
EFB
TRQ
55.0 %
B A R
BKD2_FLH_0414_R
VMS
TRQ
R C N F
1
NAVD
MFD – FND
2
10
RA
A C K
JET FUEL PUMP
415 Kg SCT
WXR
SVS
OAT 25
+ B R G –
3
Fuel indication on VMD and FND – typical display
7–6–5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
1
Detailed fuel quantity indication
2
Master list area
3
Simplified fuel quantity indication
7.6.5.1 Detailed fuel quantitiy indication (VMS) Fig. 7-6-4 shows detailed fuel quantitiy indication on the VMS page with (optional) fuel flow sensors installed. 2
47
181
7
6
5
53
N TR O
137
O
137
T
C
FF Kg/h
O C
4
3
–
Detailed fuel quantitiy indication (VMS) – typical display
O N
LY
Fig. 7-6-4
PY
N
BKD2_FLH_0462_R
O
FUEL Kg
2 h 30 min
FF Kg/h
LL
ED
1
Remaining endurance
2
Unit used for fuel indication
3
Fuel flow engine 2
4
Fuel quantity supply tank 2
5
Fuel quantity main tank
6
Fuel quantity supply tank 1
7
Fuel flow engine 1
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The following units can be selected on the VMS/CONF page to indicate the fuel quantity: – Liters (L) – US gallons (GUS) – Imperial gallons (Gimp) – Weight (Kg or Lb)
7–6–6
MANUFACTURER’S DATA Rev. 11.5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.6.5.2 FND fuel quantity indication Fig. 7-6-5 shows detailed fuel quantitiy indication on the VMS page with (optional) fuel flow sensors installed.
BKD2_FLH_0463_R
2 2 3
492 Kg
LL
FND fuel quantity indication – typical display
N TR
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Fig. 7-6-5
ED
4
Fue quantity main tank
2
Fuel transfer status (red line = interrupted fuel fransfer)
3
Fuel quantity supply tank
4
Total useable fuel
FO
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1
MANUFACTURER’S DATA Rev. 11.5
7–6–7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
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DESCRIPTION OF SYSTEMS
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Intentionally left blank
7–6–8
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.7
GEARBOX AND DRIVE SYSTEM
7.7.1
Main transmission The main transmission (see Fig. 7-7-1) is a two-stage flat design gearbox. The first stage, also called the input bevel gear stage, consists of engine drive shafts, free-wheel clutches, bevel gear shafts and bevel gears to deflect the power flow. The second stage, also called collector gear stage, consists of a collector gear, bevel gear shafts and bevel gears which form the interface to the input bevel gear stage.
O
N TR
O
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ED
The main transmission provides output power for the main rotor, the tail rotor, the hydraulic system pumps and the oil cooling fans. A freewheeling unit, located at each main transmission input, permits either one or both engines to be disengaged from the main transmission. The freewheeling units will disengage both engines during autorotation, one engine for single engine operation, or any time engine drive shaft RPM is below the RPM of the driven shaft in the main transmission.
PY
N
O
T
C
A mast moment monitoring system is installed on the main rotor mast to monitor the bending moment acting on the main rotor mast.
C
O
5
LY
–
6 4
O N
1
2
12
14
13
7
11 8 9 Fig. 7-7-1
MANUFACTURER’S DATA Rev. 0
10
9
BK117_FLH_0114_R
FO
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3
Main transmission
7–7–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Oil filter clogging indicator pin
2
Oil pressure switch
3
Oil pressure transmitter
4
Oil filler cap
5
Rotor brake disk
6
Tail rotor drive shaft
7
Main rotor mast
8
Engine drive shaft
9
Vertical load strut
10
Engine oil reservoir
11
Oil cooler
12
Oil cooling fan inlet
13
Oil level sight gauge
14
Hydraulic pump
FO
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IN
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1
7–7–2
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.7.2
Main transmission oil system The main transmission oil system (see Fig.7-7-2) lubricates and cools transmission components. A lubrication pump and a chip detector are installed on each right and left hand side of the oil sump which is integrated in the lower part of the transmission housing. Two oil pumps, mounted on the bottom of the transmission, suck oil from the sump through a filter screen and feed it to a fine mesh filter mounted above the oil level sight gauge. The filter incorporates a bypass to ensure oil circulation in the event of filter clogging. The oil quantity can be checked through an oil level sight gauge.
N TR
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ED
Oil temperature and oil pressure are monitored permanently and indicated on the VMD (refer to Para. 7.7.4). Warnings and cautions for oil temperature, oil pressure, chip detection and oil filter contamination are triggered by respective sensors.
FND
T
C
O
VMD
FAN
PY
N
O
FAN
OIL COOLER
–
C
O
OIL COOLER
O N
LY
Supply line Return line Oil Filter
O N
Mech. Driven Pump
TI
Press Relief Valve Chip Detector
P
Press Transmitter
P
Press Switch
U
P
P
P
ST
R
P
Temp. Bulb
IN
T
C
M
Temp. Switch
FO
R
T
BKD2_FLH_0165_R
T
M
VMD
Fig. 7-7-2
MANUFACTURER’S DATA Rev. 0
M
T
FND
Main transmission oil system – schematic
7–7–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.7.3
Tail rotor drive shaft and tail gearbox The tail rotor drive shaft transmits power from the main transmission along the top center of the tail boom to the tail gearbox (see Fig.7-7-3). The tail gearbox is installed on the stator hub in the ducted opening of the Fenestron structure. The tail gearbox is a single-stage design gearbox. The power flow from the main transmission is changed by an angle of 90_ through a bevel gear stage. In addition, the input speed is increased by a gear ratio of 1.30. The lubrication system of the tail gearbox is a wet sump lubrication system. During operation, all parts of the gearbox are lubricated by the splashed oil.
2
3
O
T
C
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1
N TR
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The tail gearbox housing contains an oil filler neck, an oil level sight glass and a chip detector. In case of chip detection, a respective caution is triggered.
A
A
R
IN
ST
R
U
BKD2_FLH_0169_R
C
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–
C
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4
FO
5
6
Fig. 7-7-3 1
Stator hub
2
Tail gearbox
3
Oil filler neck
4
Oil level sight glass
5
Chip detector
6
Tail rotor drive shaft
7–7–4
Tail gearbox
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.7.4
Gearbox and drive system indications The main transmission oil temperature and oil pressure are indicated on the VMD (see Fig. 7-7-4). Refer to Sect. 2 for limit markings. The VMD MGB oil pressure and temperature are continuously monitored by the avionics system. Any exceedance of the caution or warning range or an unusual pressure or temperature trend is presented on the master list (MGB OVERLIMIT or MGB TREND). The main rotor mast moment is indicated on the FND. Refer to Sect. 2 for indication formats and limit markings.
1
120
710 N1
N1
94.0 %
94.0 %
103 103
72 9.0 FUELKg
2 h 30 min
47
D A T A
314
54
MGB OIL B B A A R R
72 9.0
30
3.0 3.0
G1
100
2
G2
R N G
FF Kg/h 137
TIME ZONE
EPC
O N
101. 0 % N2 101. 0 %
EPCPL REPORT
STATUS
CONF
WEIGHT
80
+ L U M –
N TR
10
10
20
20
3
N
DCPL
ND
16
16
1 500
15
14
14
13
13
D A
D H B A R O
20
10 FSD
N 354 1.0 A FMS V GPS INS/GPS LFMH 20.0NM 12min
17
600 1013 200 DA hPa DH
3
20
DTK
+ B R G –
10
17
2
10
RA
A C K
TGB CHIP
415 Kg SCT
WXR
SVS
OAT 25
+ B R G –
3
C
TI
O N
+ L U M –
10
+ C T R S –
CLOCK
18
20
VY
C R S
LY
101. 0
IAS
100
N
ENG OIL B A R
4
PY
B A R
30 %
O
ENG OIL B A R
N U M
IBF
C
10 %
20
O
700
HDG
C
101 6 TOT
IBF
FF Kg/h 137
ALT
55.0 %
TOT
HYD
+ C T R S –
EFB
O
MISC
TRQ
55.0 %
B A R
U
Gearbox and drive system indication on VMD and FND – typical display
ST
R
Fig. 7-7-4
DMAP
TRQ
R C N F
BKD2_FLH_0414_R
VMS
–
S Y S T
NAVD
T
FND
MFD – FND
O
MFD – VMD
LL
ED
Master list messages for the main transmission and for the tail gearbox are indicated on the FND. Refer to Para. 7.13.6 for complete list of master list messages.
Main transmission oil temperature and pressure indication
2
Master list area
R
Main rotor mast moment indication (indicated below 55 KIAS) (refer to Section 2, Para NO TAG)
FO
3
IN
1
MANUFACTURER’S DATA Rev. 0
7–7–5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
O
T
C
O
N TR
O
LL
ED
DESCRIPTION OF SYSTEMS
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
Intentionally left blank
7–7–6
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.8
ROTOR SYSTEMS
7.8.1
Main rotor system The helicopter is equipped with a four-bladed hingeless main rotor. The main rotor blades are attached to the main rotor head by two bolts each. The main rotor head is bolted directly to the rotor mast of the main transmission.
7.8.1.1 Main rotor head
LL
ED
The titanium main rotor head (see Fig.7-8-1) consists of a one-piece cross-shaped drop forging. Four titanium inner sleeve assemblies are retained within the head by flexible tension-torsion straps. They are attached to two quadruple retaining nuts each, located in the head center to take up the centrifugal forces.
T
C
O
N TR
O
Main rotor control inputs are transmitted to the main rotor head via the swash plate and the rotating control rods (refer to Para. 7.3.1). Moving the rotating control rods up or down changes the pitch angle of the inner sleeves and of the attached main rotor blades. Lead-lag and flap of the rotor blades is accomplished without mechanical hinges because of the flexible properties of the main rotor blades (refer to Para. 7.8.1.2).
N
O
For aerodynamic reasons a hub cap is mounted on the top of the main rotor head.
O
PY
1
–
C
2
LY
8
O N
3 4
R
5 4
R
IN
ST
6
FO
BKD2_FLH_0166_R
U
C
TI
O N
7
1
Hub cap
2
Inner sleeve
3
Control lever
4
Oil reservoir
5
Rotating control rod
6
Swash plate
7
Main blade bolt
8
Secondary blade bolt
MANUFACTURER’S DATA Rev. 0
Fig. 7-8-1
Main rotor head
7–8–1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.8.1.2 Main rotor blades The main rotor blades (see Fig.7-8-2) are composed of composite fiber materials. The flexible design allows the blades to flex vertically and horizontally. Each main rotor blade is attached to a blade mounting fork of the main rotor head by a blade fitting assembly. The blade is retained in the mounting fork by a main blade bolt and a secondary blade bolt.
2
5
3
LL
1
ED
The main blade bolt is hollow to allow the addition of dynamic balance weights. An oil lubricated pendulum vibration absorber is fitted to the blade root to reduce vibration transmitted to the fuselage. A balancing chamber system provides the capability to tune and adapt the main rotor blades to each other, in order to reduce the main rotor vibration level.
N TR
O
4
6 7
N
O
T
C
O
Cross section
O
PY
12
8
O N
EC145_FLH_0032_R
O N
LY
–
C
11
TI
9
Fig. 7-8-2
Main rotor blade
ST
R
U
C
10
Blade core (hard foam)
2
Blade spar (prepreg glass rovings)
3
FO
R
IN
1
4
Anti-erosion strip (nickel)
5
Balance weight
6
Static discharger
7
Blade skin (fiberglass prepreg/carbon fiber)
8
Trim tab
9
Blade root
10
Blade fitting assembly
11
Electrical bonding lead
12
Pendulum vibration absorber
7–8–2
Lead rod
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.8.2
Tail rotor system The tail rotor is a fenestron-type shrouded rotor. The direction of rotation is counter-clockwise as seen from the right side of the helicopter. The tail rotor head is installed on the output gear shaft of the tail gearbox. The tail rotor blades are mounted to the tail rotor head by integrated tension-torsion straps to compensate the centrifugal forces.
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
The tail rotor counteracts the main rotor torque and provides control around the helicopter’s yaw axis. This is achieved by adjusting the pitch angle of the ten tail rotor blades collectively. Control inputs are initiated by the pilot or AFCS, and are boosted by the tail rotor actuator (refer to Para. 7.3.2).
TI
O N
O N
1
FO
R
IN
BKD2_FLH_0167_R
ST
R
U
C
2
Fig. 7-8-3 1
Tail rotor head
2
Tail rotor blade
MANUFACTURER’S DATA Rev. 0
Tail rotor components
7–8–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.8.3
Rotor systems indications The NR (main rotor RPM) is picked up by a sensor in the main transmission and by a backup-sensor in the tail rotor transmissionis and displayed on the FND and VMD (see Fig.7-8-4). Refer to section 7.5 for a description of the N2/NR gauge and to Sect. 2 for limit markings. 1
B A R
103 103
72 9.0 FUELKg
2 h 30 min
FF Kg/h 137 D A T A
47
314
54
30 %
4
MGB OIL B B A A R R
72 9.0
30
2
R N G
FF Kg/h 137
WEIGHT
+ B R G –
10 FSD
N 354 1.0 A V FMS GPS INS/GPS LFMH 20.0NM 12min
+ L U M –
1 500
15
ED
D A
14
14
D H
13
13
B A R O
600 1013 200 DA hPa DH
3
20
PY
CONF
20
16
16
DCPL
ND
10
RA
A C K
SCT
WXR
SVS
415 Kg OAT 25
+ B R G –
–
C
O
STATUS
20
20
DTK
101. 0 % N2 101. 0 % EPC
10
3
VY
C R S
TIME ZONE
EPCPL REPORT
80
10
N
G2
101. 0
+ L U M –
10
100
3.0 3.0
G1
100
10
N U M
IBF
N1
94.0 % ENG OIL B A R
17
O
ENG OIL B A R
17
N TR
710 N1
94.0 %
10 %
20
T
700
20
120
+ C T R S –
CLOCK
IAS 18
6 TOT
IBF
HDG
101
55.0 %
TOT
B A R
ALT
TRQ
55.0 %
HYD
+ C T R S –
EFB
LL
MISC
C
DMAP
TRQ
R C N F
BKD2_FLH_0414_R
VMS
O
S Y S T
NAVD
N
FND
MFD – FND
O
MFD – VMD
O N
Main rotor system indication on VMD and FND – typical display
O N
Fig. 7-8-4
LY
2
NR indication on FND
2
NR indication on VMD
FO
R
IN
ST
R
U
C
TI
1
7–8–4
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.9
ELECTRICAL SYSTEM
7.9.1
DC power system The DC Power System (see Fig.7-9-1) supplies electrical power for operation and control of helicopter electrical systems. It provides the DC power generation and control and the DC power distribution.
ED
The system is supplied by two generators and a main battery. A standby battery provides emergency power to the standby air data and attitude indicator (IESI) and to the emergency exit lights, e.g. if both generators and the main battery are lost. An external power unit (EPU) can be connected for maintenance and ground operation.
N TR
O
LL
When operated by the generators, the system supplies about 28V DC to the airborne electrical system and about 24V DC when operated by the battery. The standby battery supplies about 24V DC to the emergency equipment.
O
The following consumer busbars are available:
T
C
O
DC power is distributed via electrical boxes and panels. Several busbars are installed in the electrical boxes and panels, to which all electrical consumers of the helicopter are connected by means of circuit breakers.
LY
–
C
O
PY
N
– ESS BUSes 1 and 2: Connects all flight essential consumers. Each ESS BUS is supplied via diode boxes by its MAIN BUS with alternative supply paths from the battery and the opposite MAIN BUS. A soon as battery power, at least one generator or external power is connected to the electrical system, the ESS BUSes are energized.
O N
O N
– SHED BUSes 1 and 2: Connects the consumers of secondary importance that are shed in case of a double generator failure. Each SHED BUS is supplied by its MAIN BUS.
U
C
TI
– NON ESS BUSes 1 and 2: Connects all non-essential high load consumers which are supplied only when both generators are in operation or an EPU is connected. Each NON ESS BUS is supplied by its MAIN BUS.
R
IN
ST
R
– EMER BUS: Connects the standby air data and attitude indicator (IESI) and the emergency exit lights. The EMER BUS is supplied by the ESS BUS 2 with an alternate power supply from the standby battery.
FO
The electrical distribution network includes a BUS TIE control system which connects MAIN BUS 1 to MAIN BUS 2 and to the BAT BUS. In case of an abnormal electrical condition, the respective BUS TIE will open and separate the MAIN BUS from the opposite MAIN BUS and the BAT BUS.
MANUFACTURER’S DATA Rev. 9
7–9–1
Fig. 7-9-1
7–9–2
AFT J BOX LH
GEN BUS 1
SR1
NEBR1
SHED BUS 1
DIODE BOX 1
SBR1
R O N
Aft junction box LH side Aft junction box RH side Battery relay Bus tie relay Distribution box External power relay External power receptacle
O N
BTR1
TI
C
U
ESS BUS 1
ST
IN
MAIN BUS 1
R
DISTR. BOX 1
FO
NON ESS BUS 1
AFT J BOX LH AFT J BOX RH BR BTR DISTR. BOX EPR EXT PWR RECEP
GR1
STR/ GEN 1
–
BATTERY
EPR
N T
O
EXT PWR RECEP
ESS BUS 2
NEBR2
NON ESS BUS 2
SHED BUS 2
DIODE BOX 2
SBR2
MAIN BUS 2
relay N Generator essential bus relay TNon R bus relay Shed O relay Starter LL Starter–Generator ED
O
C
BATTERY BOX
GR NEBR SBR SR STR/GEN
PY
O
C
BAT HOT BUS
BR
LY BAT BUS
BTR2
DISTR. BOX 2
SR2
AFT J BOX RH
GEN BUS 2
STR/ GEN 2
GR2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
DC power distribution – schematic
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.9.2
DC power system control The switches for DC power system control are installed in the overhead panel (see Fig. 7-9-2).
7.9.2.1 Generator switches
LL
ED
The generator switches GEN 1 and GEN 2 are used to connect or disconnect the generators to/from the electrical system. NORM is the position for normal operation. The respective generator is automatically connected to the electrical system when the engines are running. In the OFF position, the generator is disconnected from the electrical system. In order to reset and reconnect the generator, the GEN switch is momentarily set to the spring-loaded RES position and then released to return to NORM position.
N TR
O
7.9.2.2 Battery master switch
C
O
PY
N
O
T
C
O
The battery master switch BAT MSTR controls the battery system, the EPU system and the BUS TIE system. In the OFF position, the battery or EPU is disconnected from the electrical system. In the ON position, the battery is connected to the BAT BUS. Additionally, power will be delivered to the warning unit and the BUS TIE system. If an EPU is connected, the EPU will deliver power to the BAT BUS. In order to activate the BUS TIE control system, the BAT MSTR switch is momentarily set to the spring-loaded ENGAGE position and then released to return to ON position.
LY
–
7.9.2.3 Standby battery switch
TI
O N
O N
The standby battery switch controls the emergency power supply. In the OFF position, the standby battery is charged as soon as ESS BUS 2 is powered. In the ON position, if ESS BUS 2 is not energized, the standby battery provides power to the EMER BUS.
U
C
7.9.2.4 BUS TIE control switches
FO
R
IN
ST
R
The BUS TIE switches provide manual control to the BUS TIE system. During normal operation, the switches are guarded in the NORM position. In the NORM position, the MAIN BUS 1 and 2 are connected to each other and to the BAT BUS. In the OFF position, the respective MAIN BUS is disconnected from the opposite MAIN BUS and from the BAT BUS. In order to reconnect a disconnected MAIN BUS, the respective BUS TIE switch is momentarily set to the spring-loaded RES position and then released to return to NORM position.
7.9.2.5 Emergency SHED BUS switch The EMER SHD BUS switch allows to supply the SHED BUS 1 and 2 with battery power, e.g. in case of double generator failure. During normal operation, the switch is guarded in the NORM position. In the NORM position, SHED BUS 1 and 2 are normally controlled by the generator relays. If both generators fail, SHED BUS 1 and 2 are de-energized. In order to re-energize SHED BUS 1 and 2, the EMER SHED BUS switch is set to ON position. MANUFACTURER’S DATA Rev. 0
7–9–3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
2
3
O F F
O F F
O F F
N O R M
N O R M
N O R M
N O R M
R E S
R E S
R E S
R E S
GEN
GEN
AMC2
AMC BUS
CKPT
INSTR
CC–COL BOOM
FLOATS
HOIST
3
1
7.5
1
AVIO
AV ESS
B/T
GCU BU
GEN
5
5
1
3
1
APCP
FTR
5
2
FIRE–E
5
SEMA2
SEMA1 GRIP AP
1
WIPER SMOKE–D FIRE–D
BASIC
7.5
7.5
7.5
5
E S S
B U S
B U S
ENGAGE
HYD OFF
7
W/U
HYD
2
1
ARM
C
U
ST ON
PILOT
R
PT/STATIC HTG MUTE
TEST
STBY
TAWS
BKD2_FLH_0013_R
AUDIO OFF
NORM
3 ACOL
N2
ROTOR RPM
LIGHTING
HISL
7.5
FIRE–D
MM
PT/ST
7.5
7.5
BASIC
FUEL
7.5 ENG
OFF
2
OFF
IBF
OFF
ON
ON
GND PWR
LO/ OFF
ON
HI
ON
CKPT PAX VENTILATION
STBY BAT
MIN/ OFF
ON
1 2 AVIO MSTR
ON
OFF
6
OFF
1 2 PRIME PUMP
EMERG
AUX TK
MAX
BLD HTG
OFF
OFF
OFF
ON
INV OFF
AIR COND
RECALL
HISL
TAIL FLD OFF
Fig. 7-9-2
GEN 1/2 switch
3
EM/EX
ON
FUEL
OFF
OFF
A F XFER PUMP OFF
O N
ON
2/3
1
OFF
WIPER
OFF
BLT/SMK CARGO PAX
BUS TIE 1/2 switch
1
OFF
S L O W
RECALL
2 IBF
P A X
1/4
FIRE–E
N O R M
OFF
ON
OFF
OFF
N O R M
ACAS
SEMA2 FLOATS CC–PED HOIST
5
OFF
O P E N
MUTE N O R M
5
ON
FAST
LAVCS
CLOSE
1
IN
COPILOT
SAS/AFCS
DC RECEPT
P I L PAX
FUZZ BURN
R
OFF
FO
O –
ON
TEST
EMER FLOATS
GRIP AP SEMA1
2
1
OFF
A R M
CARGO HOOK
5
INSTR
FUEL–L FUEL–V PRIM–P AUX TK FADEC2 FADEC1 ST/IGN
LAMP
TI
CC TEST
HOIST/ CBL CUT
5
W/U
2
OFF
OFF
1
ELEC
IESIBAT
O F F
FIRE TEST
O N
1
AVIO
HYD
O N
OFF
20 AV ESS
2
P–FLT
EXT/ WARN
1
IMA
B/T
2
EXT
SYS2
BAT MSTR
MFD–P MFD–CTR MFD–CP CVFDR
GCU BU
2
OFF N O R M
7.5
GEN
3
2
7.5
1
APCP
1
7.5
SL CTL STROBE
LIGHTING
7.5
2
FUEL
SYS1 O N
7–9–4
E S S
SL PWR
1
C
ENG
OFF
5
AMC BUS AMC1
ST/IGN FADEC2 FADEC1 XPMP–F PRIM–P FUEL–V FUEL–L
IBF
7.5
TRIM
SAS/AFCS
15
CKPT BLW HTG–C
ELEC
15
PAX BLW
O
POS
20
10 INST COOL
N
LDG
1
3
XPMP–A HTG–V
ED
15
5
INV
LL
7.5
FLIR
O
7.5
2
AV SHED
N TR
7.5
1
3 IESI
O
7.5
LOAD HOOK
B U S
3 EM/EX
EMER BUS
EMER SHD BUS
PY
1
7.5
CARGO PAX LT
B U S
BUS TIE
N O R M
20
LY
BKD2_FLH_0012_R
1
PT/ST
IMA
3
CONT
FUZZ BURN
CVFDR MFD–CP MFD–CTR MFD–P
10
LIGHTING
5
PWR
S H E D
O N
TAIL FLD
7.5 MIR
S H E D
O N
T
BUS TIE
AV SHED
N2
5
O F F
20
BAMBI BUCKET
4
C
1
ON
ON
ON
STROBE
ON
POS
ON
ON
ACOL
EXT LIGHTS
OFF A R M
EM/EX
ON
IR FLASH
DAY A R D M I M
HEEL
B R T
INSTR
NVG
N I G H T
INT LIGHTS
DC power system control
EMER SHD BUS switch MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
6
STBY BAT switch
7
BAT MSTR switch
7.9.3
Electrical system indications Electrical system parameters are indicated in the electrical system area on the VMD (see Fig. 7-9-3). Master list messages for the electrical system are indicated on the FND (see Fig. 7-9-3). Refer to Para. 7.13.6 for complete list of master list messages.
MISC
N1
72 9.0 FUELKg
47
D A T A
314
54
30 %
72 9.0
30
G2
R N G
FF Kg/h 137
ED
O 16
16
1 500
15
10
10
14
14
20
20
13
13
3
N
600 DA
3
20
D A
D H B A R O
1013 200 hPa DH
20
CONF
PY O
WEIGHT
+ B R G –
+ L U M –
10 DTK
DCPL
ND
2
10
RA
FSD
N 354 1.0 A V FMS GPS INS/GPS LFMH 20.0NM 12min
A C K 415 Kg SCT
WXR
SVS
OAT 25
+ B R G –
Electrical system indication on VMD and FND – typical display
O N
Fig. 7-9-3
O N
LY
–
STATUS
C
101. 0 % N2 101. 0 % EPC
VY
C R S
TIME ZONE
EPCPL REPORT
80
2
101. 0
+ L U M –
17
10
100
3.0 3.0
G1
100
4
MGB OIL B B A A R R
17
10
O
103 103 2 h 30 min
FF Kg/h 137
94.0 % ENG OIL B A R
20
+ C T R S –
N
B A R
N U M
IBF
N1
94.0 % ENG OIL B A R
20
N TR
710
CLOCK
IAS
18
120
O
700 10 %
HDG
101 6 TOT
IBF
ALT
55.0 %
TOT
HYD
+ C T R S –
EFB
TRQ
55.0 %
B A R
BKD2_FLH_0414_R
DMAP
TRQ
R C N F
1
VMS
C
S Y S T
NAVD
T
FND
MFD – FND
LL
MFD – VMD
Electrical system area
2
Master list area
R
U
C
TI
1
FO
R
IN
ST
The electrical system area (see Fig. 7-9-4) displays the following information:
MANUFACTURER’S DATA Rev. 0
7–9–5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
BUS1 / GEN1
BAT / EPU
BUS2 / GEN2
1
2
G1
0 A
250 A N TR
O
350 A
LL
5
50. 0 V ED
30. 0 V
3
C
O
4
BKD2_FLH_0216_R
6
G2
Electrical system area
PY
N
O
T
Fig. 7-9-4
Generator state symbol
2
EPU state symbol
3
Battery current digital indication
4
Battery state symbol
5
Generator current digital indication
6
Bus voltage digital indication
TI
O N
O N
LY
–
C
O
1
R
U
C
The colors of the generator, battery state, and EPU symbols represent the respective system conditions.
ST
Generator state symbol color logic:
IN
– Green: generator is connected
FO
R
– Amber: generator is disconnected or degraded while its respective engine is running – Light gray: generator is disconnected and its respective engine is off Battery state symbol color logic: – Green: battery is connected – Amber: battery is disconnected or degraded – Red: battery overheat – Light gray: battery is off, power is provided by EPU EPU state symbol color logic: – Green: EPU is connected – No symbol: EPU is not connected
7–9–6
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
The digital values of generator current, bus voltage and battery current are not indicated during normal electrical system operation. The digital indication can be activated at any time by pressing the NUM key. The digital indication is also activated automatically if a parameter overlimit is detected. The parameter exceeding the limit is marked with an amber or red frame. During engine start (engine START label indicated), amber or red marked parameters are normal and acceptable. If an electrical parameter is out of sensor signal range, it is set to invalid and the numerical value is displayed as amber stars.
LL
GND PWR switch (optional)
O
7.9.4
ED
If the battery is discharged in flight, the battery current value is marked with an amber frame. Battery charging is indicated as negative current, discharging as positive current.
C
O
N TR
The ground power (GND PWR) switch enables radio communication and the use of specific mission equipment (e.g. tactical radios) when the helicopter is on ground using battery power without battery- and avionics switches set to on.
O
Activation of the ground power switch will discharge the battery. Therefore, use of the ground power switch should be kept to a minimum.
–
C
NOTE
PY
N
O
T
When activated, ON (green) is diplayed on the indicator. Ground power activation is automatically limited to 10 minutes. After time has elapsed, power is shut off automatically. If required, the GND PWR switch has to be activated again.
O N
LY
As soon as the BAT MSTR and Avionic Master switches are switched on, ground power will be deactivated and the systems will be supplied normally.
GND PWR
ST
R
U
C
TI
O N
The ground power can be de-activated by pushing the GND PWR switch to off.
GND
IN
ON OFF
OFF
R FO
Fig. 7-9-5
ON
GND PWR switch and status indicator – typical installation
MANUFACTURER’S DATA Rev. 15
7–9–7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
O
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LL
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DESCRIPTION OF SYSTEMS
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O N
O N
LY
–
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O
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N
Intentionally left blank
7–9–8
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.10
HEATING/VENTILATION SYSTEM (SEE FIG. 7-10-1 ) If an air condition system is installed, refer to FMS 9.2–12.
7.10.1
Bleed air heating system The heating system ducted to the cabin aera is connected to the ventilation ducting system. It consists of: – Ventury-type mixing valve assy to mix bleed air from the engines with cabin air – Temperature control computer
ED
– Temperature sensors located in the cabin ceiling and in the heater supply duct
LL
– Overtemperature switches located in the heater supply duct
O
– BLD HTG rheostat
N TR
– Cabin air outlets
N
O
T
C
O
The valve position is constantly adjusted by the computer as a function of cabin air temperature, as sensed by the cabin temperature thermistor and the BLD HTG rheostat setting.The fully opened and closed position are monitored by micro switches. will be shown in the first limit
O
PY
When the heating is switched on, the heating symbol indicator.
C
The heating fail caution indication will appear in the master list in case of:
LY
–
– the shut off valves remain open after shutting off the bleed air heating system.
O N
– the shut off valves remain closed after switching on the bleed air heating system.
TI
O N
If a mixing valve malfunction causes an air temperature increase above a specific threshold value an overtemperature switch will cause the shut off valves to close and the HEATING OVERTEMP caution indication to appear in the master list.
Electrical heater
FO
7.10.2
R
IN
ST
R
U
C
The bleed air heating system is automatically switched off by the FADEC as soon as the engine power exceeds the OEI maximum continuous (i.e. as soon as the OEI 2min or OEI 30sec ratings are used). When power reduces below OEI continuous, the heating will automatically return to its normal function (i.e. switch on depending on the rheostat setting).
An (optional) electrical heater is installed to accelerate defogging/defrosting. The electrical heater is active only when the following conditions are met: – The bleed air heating system is on (heating symbol indicated) – Demisting is selected (PUSH FOR DEFOG) lever fully pushed When the electrical heater is switched on, the ventilation system is automatically switched on to a minimum level as well. It is recommended to allow the ventilation to run for at least 30 seconds after the heater was switched off. The correct operation of the electrical heater can be checked by monitoring the electric current while switching the heater on/off. A total current difference of about 40A (20A per generator) should be noticeable.
MANUFACTURER’S DATA Rev. 9
7 – 10 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.10.3
Ventilation system The ventilation system consists of: – Cockpit ventilation system – Avionics cooling system – PAX ventilation system
7.10.3.1 Cockpit ventilation system The cockpit ventilation system consists of:
ED
– Air nozzles in the instrument panel directing air onto the windshield.
LL
– PUSH FOR AIR lever (aft part of the center console). When pushed, outside air from the NACA inlet is used for ventilation. When pulled, air from the cockpit is recirculated.
C
– VENTILATION CKPT rheostat (blower speed variation)
O
N TR
O
– PUSH FOR DEFOG lever (aft part of the center console). When pushed, the air is guided through the windshield outlets; when pulled air is guided to the pilot/copilot air outlets.
O
T
– Pilot/Copilot air outlets (adjustable in direction and aperture)
C
O
PY
N
Cockpit heating/windshield defogging/deicing is achieved by mixing hot air from the bleed air heating system with air from the ventilation system. Therefore, the ventilation rheostat setting will affect the heating performance.
LY
–
7.10.3.2 Avionics cooling system
TI
7.10.3.3 PAX ventilation system
O N
O N
A thermoswitch activates the avionics cooling blower automatically depending on the temperature inside the instrument panel.
C
The PAX ventilation system consists of:
R
U
– Nine pax nozzles (adjustable in direction and aperture)
FO
R
IN
ST
– PAX BLW sw (overhead panel)
7 – 10 – 2
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
FO
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IN
ST
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O N
O N
LY
–
C
O
PY
N
O
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ED
DESCRIPTION OF SYSTEMS
Fig. 7-10-1 MANUFACTURER’S DATA Rev. 9
Typical heating/ ventilation system – schematic
7 – 10 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
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DESCRIPTION OF SYSTEMS
FO
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O N
O N
LY
–
C
O
PY
N
Intentionally left blank
7 – 10 – 4
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11
LIGHTING EQUIPMENT
7.11.1
Standard internal lights – non NVG Helicopter configuration
7.11.1.1 Emergency lighting Three exit signs, two boarding step lights and two EMER EXIT/ PAX LT lights are supplied with power via ESS BUS 2 and the LIGHTING EM/EX cb on the overhead panel. They are controlled by means of the INT LIGHTS EM/EX sw on the overhead panel. Position OFF
all lights off
Position ARM
lighting will be switched on in case of:
ED
– activation of the impact switch
LL
– opened door(s)
O
– activation of the EM/EXIT LT sw in the cabin
C
O
N TR
– activation of the EMER PAX LT sw (beside the EMER EXIT/PAX LT). Each EMER EXIT/PAX LT can be switched ON individually by the EMER PAX LT sw beside the EMER EXIT PAX LT
N
O
T
– ESS BUS 2 power supply break down (emergency power supply)
O
–
Press the LIGHTING EM/EX cb and the EMER BUS EM/EX cb simultaneously.
LY
NOTE
all lights on
C
Position ON
PY
– INT LIGHTS CARGO PAX sw ON –> EMER EXIT/PAX LT lights and the CARGO DOME LIGHT on
O N
7.11.1.2 Cargo dome light
C
U
Position OFF
TI
O N
The cargo dome light receives power via SHED BUS 1 and the CARGO PAX LT cb on the overhead panel. It is controlled by means of the INT LIGHTS CARGO PAX sw on the overhead panel and the CARGO DOME LT sw, located beside the light.
– activation of the CARGO DOME LT sw (beside dome light)
Position ON
– Cargo dome light on
R
– opened cargo door(s)
FO 7.11.2
light will be switched on in case of:
IN
ST
R
Position PAX
cargo dome light off
– EMER EXIT PAX lights on
NVG compatible internal lights (if installed) For NVG mode the INT LIGHTS INSTR sw on the overhead panel has to be in NVG position.
7.11.2.1 Emergency lighting The two NVG compatible EMER EXIT/PAX LT lights are supplied with power via ESS BUS 2 and the LIGHTING EM/EX cb on the overhead panel. They are controlled by means of the INT LIGHTS EM/EX sw on the overhead panel. Position OFF
all lights off
Position ARM
lighting will be switched on in case of:
MANUFACTURER’S DATA Rev. 0
7 – 11 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
– activation of the impact switch – activation of the EM/EXIT LT sw in the cabin – activation of the EMER PAX LT sw (beside the EMER EXIT/PAX LT) – ESS BUS II power supply break down Position ON NOTE
all lights on
Press the LIGHTING EM/EX cb and the EMER BUS EM/EX cb simultaneously.
7.11.2.2 Cargo dome light
Position PAX
light will be switched on in case of:
O
cargo dome light off
C
Position OFF
N TR
O
LL
ED
The cargo dome light receives power via SHED BUS I and the CARGO DOME LIGHT cb on the overhead panel. It is controlled by means of the INT LIGHTS CARGO PAX sw on the overhead panel and the CARGO DOME LT sw, located beside the light.
N
4
13
14
6
– 7
8
17
9
5
1
3
11
12
FO
R
IN
ST
R
U
C
TI
O N
15
O N
16
LY
10
C
O
2
O
Cargo dome light on
PY
Position ON
T
– CARGO DOME LT sw is switched on (beside dome light)
1/2
Stairway light
3/4/5
EXIT sign light
6/7
Fig. 7-11-1
EMER EXIT/ PAX LT light
8
Cargo dome light
9 to 14
PAX LT
15
INT LIGHTS EM/EX sw
16
INT LIGHTS CARGO PAX sw
17
EM/EXIT LT sw
7.11.3
Typical lighting equipment
Standard internal lights – non NVG Helicopter configuration
7 – 11 – 2
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.3.1 Cockpit Light
LL
ED
The cockpit light (see Fig. 7-11-2) is a spotlight, installed on the cockpit ceiling aft of the overhead panel. It provides a rectangular illumination and is controlled by the spotlight switch on/off and dim ring. The size of the rectangular illumination can be controlled by the spotlight focusing ring. The cockpit light is supplied with power via ESS BUS I and the LIGHTING CKPT cb on the overhead panel. A spare bulb for exchange is located behind the cockpit light housing cover.
2
4 Fig. 7-11-2
3
Cockpit light – typical installation
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
1
1
Mounting bracket
2
Spotlight focus ring
3
Spotlight switch on/off and dim ring
4
Housing cover
MANUFACTURER’S DATA Rev. 0
7 – 11 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.3.2 LED Cockpit Light (optional)
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
The NVG compatible LED cockpit light is mounted in the cockpit roof behind the circuit breaker panel (see Fig. 7-11-3) and electrically connected through a spiral cable. The beams brightness is dimmable and the beam can be focussed via a rotating ring on the front of the light. The light is detachable and for more convenient operation, removal from its stowed position is possible. Electrical supply of the LED cockpit light is provided via ESS BUS I and the LIGHTING CKPT cb in the overhead panel.
LED Cockpit light – typical installation
FO
R
IN
ST
Fig. 7-11-3
7 – 11 – 4
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.3.3 Cockpit dome light (optional) The cockpit dome light (see Fig. 7-11-4) is a white LED light installed in the overhead panel. It is controlled by means of a push button beside the cockpit dome light. NOTE EFFECTIVITY
The cockpit dome light must be switched off during flight. Up to S/N 20055
LL
S/N 20056 and subsequent
O
EFFECTIVITY
ED
The GND power switch, allows to switch on the cockpit dome light on ground without powering up the complete electrical system via EPU or battery. In this case, the cockpit dome light is automatically switched off after 10 min if not switched off earlier by the crew. A re-activation of the light is possible. While BAT MSTR is switched ON and engines are running the light is supplied by GND SHED BUS I (no automatic switch-off).
T
C
O
N TR
While BAT MSTR SW is OFF and engines are not running, the Cockpit Dome Light is supplied by main battery directly. When the push button is activated, the light will be illuminated for 10 min and then be switched off automatically if not switched off earlier by the crew. A re-activation of the light is possible.
–
All
IN
ST
R
U
C
TI
O N
O N
LY
EFFECTIVITY
C
O
PY
N
O
While BAT MSTR SW is ON, the Cockpit Dome Light is supplied from ESS Bus (independent from engine status). In this case the Cockpit Dome Light can be switched on by the crew with the push button and remains on until the push button is pressed again (no automatic switch-off) or the BAT MSTR SW is switched off.
BKD2_FLH_0164_R
FO
R
2
1 Fig. 7-11-4 1
Push button
2
Cockpit dome light
MANUFACTURER’S DATA Rev. 0
Cockpit dome light – typical installation
7 – 11 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.3.4 No Smoking and Fasten Seat Belt Indication (optional)
Fig. 7-11-5
No Smoking and Fasten Seat Belt Indication
LL
ED
The optional “No Smoking and Fasten Seat Belt” – indication allows the flight crew to indicate passengers to stop smoking and to fasten their seat belts. The system is supplied from SHED Bus 1 and via the same circuit breaker as the Pax Lighting System.
N TR
O
The “No Smoking and Fasten Seat Belt” – indication consists of two No Smoking/Fasten Seat Belt Signs, installed in the forward ceiling area, and following control elements:
O ON
N A RD M I M
HEEL
B R T
INSTR
NVG
N I G H T
INT LIGHTS
BLT/SMK switch in the overhead panel – typical installation
O N
Fig. 7-11-6
ON
EM/EX
C
ON
BLT/SMK CARGO PAX
DAY
LY
ON
A R M
–
P A X
OFF
O N
BKD2_FLH_0262_R
OFF
PY
OFF
OFF
O
T
C
O
– BLT/SMK switch (2 positions) in the group INT LIGHTS in the overhead panel as shown in Fig. 7-11-6
C
TI
– If BLT/SMK switch is in position OFF the “No Smoking and Fasten Seat Belt Indication“ is inactive.
ST
R
U
– If BLT/SMK switch is in position ON “No Smoking and Fasten Seat Belt Indication“ is active.
R
IN
The ”No Smoking” and ”Fasten Seatbelt” indications cannot be activated separately.
FO
7.11.3.5 Ambient and Functional Lighting (optional) The ambient and functional lighting is supplied with electrical power from the shedding bus no.1 via the circuit breaker AMB FUNC LT in the group LIGHTING. The system is controlled by the AMB/FUNC LT switch located in the overhead panel. If the AMB/FUNC LT switch is in: – OFF position: All ambient and functional lights are OFF. No individual switching by the passenger possible. – DAY position: All ambient and functional lights are ON and illuminate with maximum brightness in warm white. – NIGHT position: All ambient and functional lights are ON and illuminate with minimum brightness in blue.
7 – 11 – 6
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.4
External Lighting
7.11.4.1 Fixed landing light The fixed landing light is normally installed in the aircraft nose with a fixed angle, so that the landing area is properly illuminated (Fig. 7-11-7).
O
PY
N
O
T
BKD2_FLH_0288_R
C
O
N TR
O
LL
ED
This installation is incompatible with the optional weather radar installation. Therefore a fixed landing light can optionally be installed on the landing gear cross tube (refer to FMS 9.2–23).
O N
Location of the nose mounted landing light.
O N
Fig. 7-11-7
LY
–
C
Landing light
FO
R
IN
ST
R
U
C
TI
The fixed landing light receives power from No. 1 DC essential bus via LDG circuit breaker, located on the overhead panel.
MANUFACTURER’S DATA Rev. 11.2
7 – 11 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
N TR
O
LL
ED
7.11.4.2 Search and landing light (S/L light)
Fig. 7-11-8
S/L light 400/200W (IR) or 450W or LED
O
T
C
O
The S/L light (see Fig.7-11-8) is installed on RH side of the forward fuselage access cover. – 400W/200W (IR)
O
– 400W/200W (IR) with dimmable white light
PY
N
There are different possible configurations of the S/L light:
–
C
– 450W white light
LY
– LED white light / optional IR
O N
O N
The system receives power from the No. 2 DC shedding bus via the SL PWR and the SL CTL circuit breakers, located on the overhead panel.
R
U
C
TI
The S/L lights are operated by switches on the collective lever grips on pilot side (see Fig. 7-11-9). Unless a 2nd S/L light is installed, the S/L light is equally controllable from the co-pilot’s collective grip.
IN
ST
S/L light 400W/200W (IR) / LED (with IR): Depending on the light configuration, the following logic applies when switching S/L on:
FO
R
Configuration 400W/200W
400W/200W IR LED (with IR)
INSTR sw position
Result
DAY or NIGHT or NVG
WHT
DAY or NIGHT
WHT Basic version WHT
NVG
After SB MBB BK117 D–2–33–007 IR
S/L light 400W/200W (IR) can be extended up to an angle of 73_. When extended more than 40_, the lamp can be rotated 90_ to the right and 60_ to the left. An activation of the S/L light is possible from 0_. As an option, the 400W visible light is dimmable (2 x 200W light bulbs).
7 – 11 – 8
MANUFACTURER’S DATA Rev. 15.2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
The S/L light LED can be extended up to an angle of max. 90_. The lamp can be rotated max. 90_ to the right and max. 90_ to the left (depending on installation). An activation of the S/L light is possible from 0_. When the light is activated from the stowed position, it automatically extends 40_ (optimum angle for Cat A rearward procedure). The S/L light 450W without IR can be extended up to 90_. When extended more than 27_ the lamp can be rotated 90_ to the right and 60_ to the left. An activation of the S/L light is possible from 27_.
CUT
L D G L T
LL O
3
S/L LT ON
N TR
DIM/FOC
S/L LT M I R HISL
O
CABLE
2
OFF
4
C
1
ED
7.11.4.3 Operation of the Landing and S/L lights
T
STOW
O
BAMBI
DUMP
O N
LY
–
C
O
PY
BEEP TRIMORIENT CTL
BKD2_FLH_0014_R
N
IR/ VIS
S/L light controls – typical installation
O N
Fig. 7-11-9
C U R
IN
ST
1 S/L LT–MIR– HISL (3-way sw)
ML
TI
Collective lever control panel pilot/copilot Selects the function of the ORIENT CTL and DIM/FOC switch between S/L light, external mirror or high intensity search light. For S/L light operation, the switch must be in the S/L LT position. Switches the S/L light off automatically and retracts the S/L light to its stowed position NOTE Only operational if S/L LT–MIR–HISL sw is in S/L LT position.
S/L LIGHT RETR
2 400/200W (IR) STOW (2-way button with push function)
Retracts the S/L light to its stowed position NOTE The light is not switched off automatically. Only operational if S/L LT–MIR–HISL sw is in S/L LT position.
S/L LIGHT RETR
FO
R
2 450W STOW (2-way button with push function)
2 400/200W (IR) dimmable
fwd – aft
MANUFACTURER’S DATA Rev. 15.2
Indication only visible as long as the S/L light is retracting
Indication only visible as long as the S/L light is retracting
Dims the S/L light (if switch (1) is selected to S/L LT).
7 – 11 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Collective lever control panel pilot/copilot
ML
3 S/L LT and ON Switches the S/L light on. LDG LT (4-way (forward) LED: Light on and extends to 40_ toggle switch, (depending on installation) momentary) OFF Switches the S/L light off. (back) Switches the fixed landing light on.
OFF (left)
Switches the fixed landing light off.
FXD LIGHT
ED
ON (right)
S/L LIGHT
When both the LDG and the S/L light are on, a combined label is shown in the ML.
N TR
O
LL
FXD + S/L LIGHT
swivels the S/L light in all directions NOTE Directional control is only operational if S/L LT–MIR–HISL sw is in S/L LT position
Push
switches between VIS and IR mode (If IR mode is installed)
O
PY
N
O
T
C
fwd– aft – left– right–
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
4 ORIENT CTL (4-way toggle switch with push function)
O
When both the LDG and the S/L light (in IR mode) are FXD+S/L LIGHT IR on, a combined label is shown in the ML.
7 – 11 – 10
MANUFACTURER’S DATA Rev. 15.2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
O
LL
BKD2_FLH_0288_R
ED
7.11.4.4 2nd – S/L Light
O
C
2nd S/L Light
N
O
T
Fig. 7-11-10
N TR
2nd S/L Light
C
O
PY
The 2nd S/L light (see Fig.7-11-10) is installed on LH side of the forward fuselage access cover.
LY
–
There are different possible configurations of the 2nd S/L light:
O N
– 450W white light
O N
– LED white light / optional IR
R
U
C
TI
The system receives power from the No. 2 DC SHED bus via the SL PWR and the SL CTL circuit breakers, located on the overhead panel.
FO
R
IN
ST
The 450W SL can be extended up to 90_. When extended more than 27_ the lamp can be rotated 90_ to the right and 60_ to the left. An activation of the S/L light is possible from 27_. The LED SL light can be extended up to 90_ and rotated 90_ left and right. An activation of the S/L light is possible at any position.
The 2nd S/L light is normally controlled by the crew member on the co-pilot’s seat using controls on the co-pilot’s collective grip or by either cockpit crew member using the control panel in the center console (Fig. 7-11-11). For single pilot operation, the pilot is able to quickly switch the 2nd S/L light off using a push button on the pilot’s collective grip. When a 2nd S/L light is installed, the standard S/L light can no longer be controlled from the co-pilot’s collective grip. In addition the fixed landing light can be switched on and off via the control panel. MANUFACTURER’S DATA Rev. 21.2
7 – 11 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
2
1
3 CABLE OFF
L D G L T
S/L LT
ON
OFF
STOW BAMBI
I NA CT I V E
CP S/L I NA CT I V E
ON
5
O
N TR
Pilot
EXTERNAL LIGHTS FWD
R
O
PY
L
C
BKD2_FLH_0289_R
S T O W
N
O
ON
BEEP TRIM ORIENT CTL BKD2_FLH_0291_R
BKD2_FLH_0290_R
Copilot
OFF
ED
DUMP
BEEP TRIM ORIENT CTL
LL
BAMBI
DUMP
CUT
4
STOW
DIM/FOC
S/L LT M I R HISL
ON
O
L D G L T
S/L LT
C
CUT
DIM/FOC
T
CABLE
S/L LT M I R HISL
OFF
–
OFF
AFT
CP S/L
7
6
Control panel – center console
IN
ST
R
U
C
TI
8
O N
O N
LY
LDG
2nd–S/L light controls – typical installation
FO
R
Fig. 7-11-11
Collective lever control panel copilot 1
S/L LT–MIR– HISL (3-way sw)
2
STOW (2-way button with push function)
7 – 11 – 12
ML
Selects the function of the ORIENT CTL switch between S/L light, external mirror or high intensity search light. For S/L light operation, the switch must be in the S/L LT position. Push
Switches 2nd S/L light off automatically CP S/L LIGHT RETR and retracts the light to its stowed position. NOTE Only operational if S/L LT– MIR–HISL sw is in S/L LT position MANUFACTURER’S DATA Rev. 21.2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Collective lever control panel copilot Switches the 2nd S/L light on.
ORIENT CTL (4-way toggle switch with push function)
fwd– aft – left– right–
Swivels in all directions. NOTE Directional control is only operational if S/L LT–MIR–HISL sw is in S/L LT position.
Push
Switches between VIS and IR mode NOTE Push function inactive (no IR mode) for the 2nd S/L light.
CP S/L LIGHT
ED
Switches 2nd S/L light off.
O
4
S/L LT and ON LDG LT (4-way (forward) toggle switch, s itch OFF momentary) (back)
LL
3
ML
Push
Switches the 2nd S/L light off.
O
CP S/L–OFF (push button)
C
5
N TR
Pilot’s control concerning the 2nd S/L light on the collective lever control panel
O
T
Control panel center console CP S/L – 4-way toggle switch
fwd– aft– left– right–
Swivels in all directions. NOTE Directional control is only operational if S/L LT–MIR–HISL sw (see Collective lever control panel copilot) is in S/L LT position.
7
ON–STOW– OFF
ON (forward) OFF (back)
Switches the 2nd S/L light on and off.
CP S/L LIGHT
TI
O N
O N
LY
–
C
O
PY
N
6
Switches 2nd S/L light off automatically CP S/L LIGHT RETR and retracts the light to its stowed position.
ST
R
U
C
STOW (push)
ON–OFF
Switches fixed landing light on and off. FXD LIGHT
FO
R
8
IN
Fixed LDG light sw
MANUFACTURER’S DATA Rev. 21.2
7 – 11 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.4.5 Fabric Glare Shield For night flights, a fabric glare shields (Fig.7-11-12) shall be installed in the lower part of the cockpit on the left and right hand side, to reduce glare from the landing lights. When the pilot/copilot are correctly seated, the glare shield does not affect the field of view.
Fabric glare shield – typical installation on right hand side.
FO
R
IN
ST
Fig. 7-11-12
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
If necessary, the fabric glare shield can remain installed for day operations.
7 – 11 – 14
MANUFACTURER’S DATA Rev. 11.2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.4.6 Position lights (Standard) The position lights are installed: – on the aft end of the fin tip fairing (white) – on the LH end of the horizontal stabilizer (red) – on the RH end of the horizontal stabliizer (green). The system is supplied with electrical power from the essential bus 1 via the circuit breaker POS in the group LIGHTING and the switch POS in the group EXT LIGHTS on the overhead panel (see para 7.6 of the basic FLM).
ED
If the POS switch is in:
LL
– ON position: position lights are on.
OFF
OFF
OFF
N TR
O
– OFF position: position lights are off. OFF
OFF
O
O
OFF
ON
ON
ON
STROBE
T
IR FLASH
ON
ON
ACOL
POS
EXT LIGHTS
N
O
TAIL FLD
HISL
C
N
Position lights switch – standard installation
O
PY
Fig. 7-11-13
–
C
7.11.4.7 Anti-collision light (Standard)
LY
The anti-collision light is installed on top of the vertical fin.
O N
O N
The system is supplied with electrical power from the essential bus 2 via the circuit breaker ACOL in the group LIGHTING and the switch ACOL in the group EXT LIGHTS on the overhead panel (see para 7.6 of the basic FLM).
TI
If the ACOL switch is in:
U
C
– ON position: anti-collision light is on.
IN
ST
R
– OFF position: anti-collision light is off. OFF
OFF
OFF
OFF
O
R FO
OFF
OFF
N ON
HISL
Fig. 7-11-14
MANUFACTURER’S DATA Rev. 11.2
TAIL FLD
ON
IR FLASH
ON
STROBE
ON
POS
ON
ACOL
EXT LIGHTS
Anti-collision light switch – standard installation
7 – 11 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.4.8 LED multimode position lights with anti-collision light function (optional) CAUTION
THE RED ANTI–COLLISION LIGHT MAY NOT BE VISIBLE TO PILOTS FLYING WITH NIGHT VISION GOGGLES (NVG). IT IS RECOMMENDED TO SWITCH ON AN ADDITIONAL WHITE STROBE LIGHT IF CONFLICTING INTRUDER TRAFFIC USING NVG CAN BE EXPECTED.
The LED multimode position lights combine two position lights, emitting red (LH) or green (RH) light in forward direction and white light in backward direction, with a red anti-collision light function in the same housing.
ED
The multimode position lights are installed as replacement of the standard position lights:
LL
– on the LH end of the horizontal stabilizer (red/white)
O
– on the RH end of the horizontal stabliizer (green/white).
O
N TR
The white position light on the aft end of the fin tip fairing from standard installation remains installed additionally.
N
O
T
C
The system is supplied with electrical power from the essential bus 1 via the circuit breaker POS in the group LIGHTING and the switch POS in the group EXT LIGHTS on the overhead panel (see para 7.6 of the basic FLM).
PY
If the POS switch is in:
O
– ON position: position lights are on.
OFF
O N
OFF
LY
– OFF position: position lights are off.
O N
O N
ON
TAIL FLD
OFF
OFF
OFF + A B C O / U L
ON
IR FLASH
OFF
ON
STROBE
ON
POS
ON
ACOL
EXT LIGHTS
U
C
TI
HISL
–
C
– +ACOL B/U position: position lights and backup anti-collision lights are on.
Multimode position lights switch – typical installation
FO
R
IN
ST
R
Fig. 7-11-15
7 – 11 – 16
MANUFACTURER’S DATA Rev. 17.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.4.9 LED dual color anti-collision light (optional) If ACOL sw labeled ”BOTH–RED–OFF” is installed
EFFECTIVITY
CAUTION
THE RED ANTI–COLLISION LIGHT MAY NOT BE VISIBLE TO PILOTS FLYING WITH NIGHT VISION GOGGLES (NVG). IT IS RECOMMENDED TO SWITCH ON BOTH LIGHTS IF CONFLICTING INTRUDER TRAFFIC USING NVG CAN BE EXPECTED.
ED
The LED dual color anti-collision light combines a red anti-collision light and a white flashing light in one housing which is installed on top of the vertical fin instead of the standard anti-collision light.
OFF
OFF
OFF
OFF
OFF
C
OFF
O
N TR
O
– BOTH: red anti-collision light and white flashing light are on. – RED: red anti-collision light is on. – OFF: red anti-collision light and white flashing light are off.
LL
If the ACOL switch is in:
O ON
STROBE
ON
POS
BOTH
ACOL
EXT LIGHTS
O
Dual color anti-collision light switch – typical installation
C
Fig. 7-11-16
ON
IR FLASH
PY
ON
TAIL FLD
N
N
HISL
R E D
T
O
O N
LY
–
The system is supplied with electrical power from the essential bus 2 via the circuit breaker ACOL in the group LIGHTING and the switch ACOL in the group EXT LIGHTS on the overhead panel (see para 7.9 of the basic FLM). If ACOL sw labeled ”R+WHT–RED–OFF” is installed
O N
EFFECTIVITY
ST
R
U
C
TI
The LED dual color anti-collision light combines a red anti-collision light (which includes an IR part) and a white flashing light in one housing which is installed on top of the vertical fin instead of the standard anti-collision light. The IR part ensures that the anti-collision light is visible when viewed with night vision goggles.
IN
If the ACOL switch is in:
FO
R
– R+WHT: red anti-collision light and white flashing light are on – RED: red+IR anti-collision light is on. – OFF: red+IR anti-collision light and white flashing light are off. OFF
OFF
OFF
OFF
OFF
OFF R E D
O N ON
HISL
Fig. 7-11-17
TAIL FLD
ON
IR FLASH
ON
STROBE
ON
POS
R+WHT
ACOL
EXT LIGHTS
Dual color anti-collision light switch – typical installation
The system is supplied with electrical power from the essential bus 2 via the circuit breaker ACOL in the group LIGHTING and the switch ACOL in the group EXT LIGHTS on the overhead panel (see para 7.9 of the basic FLM). MANUFACTURER’S DATA Rev. 17.1
7 – 11 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
EFFECTIVITY
If IR FLASH sw labeled ”HIGH–LOW–NORM” is installed
The IR flasher is an additional function to the LED dual color anti-collision light (labeled ”R+WHT–RED–OFF”). The three way IR FLASH switch is located on the overhead panel and provides the following functions according the logic in the table below: Switch position RED
WHITE
IR
NORM
OFF
OFF
OFF
LOW
OFF
OFF
LOW
HIGH
OFF
OFF
HIGH
NORM
ON
OFF
LOW
ON
OFF
HIGH
ON
OFF
NORM
ON
ON
OFF
LOW
ON
OFF***
LOW
HIGH
ON
OFF***
HIGH
LL O
N TR
LOW
LOW**
O
R+WHT
O
RED
LOW*
C
OFF
ED
IR FLASH sw
T
ACOL sw
Equipment state
PY
N
* In order to make the helicopter visible to NVIS operators when only the red anti–collision light is ON, the IR flasher is automatically switched in LOW mode when the ACOL switch is on RED.
–
C
O
** When the ACOL switch is placed on RED, the IR flasher will flash in LOW mode even if the IR FLASH switch is placed on HIGH (linked to equipment internal design)
O N
O N
LY
*** The IR modes LOW and HIGH have priority on the White mode (linked to equipment internal design), therefore the White mode is automatically deactivated when IR is switched on.
ST
R
U
C
N
TAIL FLD
OFF
OFF R
ON
IR FLASH
HIGH
E D ON
STROBE
R+WHT
ON
ACOL
POS
EXT LIGHTS
IR FLASH switch – typical installation
R
IN
Fig. 7-11-18
OFF
L O W
TI
O
HISL
NORM
OFF
OFF
FO
The system is supplied with electrical power from the essential bus 2 via the circuit breaker ACOL in the group LIGHTING. The IR FLASH switch is part of the MULTI MODE LED IR-FLASHER system. The ACOL switch is part of the DUAL COLOR MODE LED ANTICOLLION LIGHT system. The MULTI MODE LED IR–FLASHER system is only operable when the DUAL COLOR MODE LED ANTICOLLION LIGHT system is installed. Both the switch ACOL and the switch IR FLASH are in the group EXT LIGHTS on the overhead panel (see para 7.9 of the basic FLM). EFFECTIVITY
7 – 11 – 18
All
MANUFACTURER’S DATA Rev. 17.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.4.10
Strobe lights (optional)
The strobe light system is supplied with electrical power from the shedding bus 2 via the circuit breaker STROBE in the group LIGHTING and the switch STROBE in the group EXT LIGHTS on the overhead panel (see para 7.6 of the basic FLM). If the STROBE switch is in: – ON position: LED strobe lights flash. – OFF position: LED strobe lights are off. OFF
OFF
OFF
OFF
OFF
OFF
ED
O
ON
ON
POS
STROBE
ON
ACOL
N TR
EXT LIGHTS
Strobe lights switch – typical installation
O
Fig. 7-11-19
C
Tail flood light (optional)
T
7.11.4.11
ON
IR FLASH
O
ON
TAIL FLD
HISL
LL
N
–
If the tail flood light switch is in:
C
O
PY
N
O
The tail flood light illuminates the rear doors area to allow easy loading/unloading at night. The system is supplied with electrical power from the essential bus 1 via the circuit breaker TAIL FLD in the group LIGHTING and the switch TAIL FLD in the group EXT LIGHTS on the overhead panel (see para 7.2 of the basic FLM).
LY
– ON position: Tail flood light is on.
O N
O N
– OFF position: Tail flood light is off. OFF
OFF
OFF
OFF
OFF
OFF
TI
O
U
C
N
Fig. 7-11-20
ON
TAIL FLD
ON
IR FLASH
ON
STROBE
ON
POS
ON
ACOL
EXT LIGHTS
Tail flood light switch – typical installation
FO
R
IN
ST
R
HISL
MANUFACTURER’S DATA Rev. 17.1
7 – 11 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.4.12
IR flasher on horizontal stabilzer (optional)
Two IR flasher can be installed, one on each end cap of the horizontal stabilizer, to improve helicopter recognizability. The IR flasher are supplied with electrical power from the shedding bus 1 via the circuit breaker IR FLASH on the overhead panel. The IR flasher can be switched ON and OFF via the IR FLASH sw located in the group EXT LIGHTS on the overhead panel (see para 7.6 of the basic FLM). If the IR flasher switch is in: – ON position: IR flasher flash in IR mode with a rate of 1,5 - 2 Hz.
OFF
OFF
OFF
OFF
OFF
LL
OFF
ED
– OFF position: IR flasher are off.
O
ON
ON
ON
STROBE
POS
EXT LIGHTS
ON
ACOL
C
IR flasher switch – typical installation
Formation lights (optional)
N
7.11.4.13
O
T
Fig. 7-11-21
ON
IR FLASH
O
TAIL FLD
HISL
N TR
O
N
–
C
O
PY
Four formation lights can be installed on the helicopter: one in the center of the engine cowling, one on the upper side of each horizontal stabilizer and one at the rear end of the tailboom structure.
O N
LY
The formation lights are supplied with electrical power from the shedding bus 1 via the circuit breaker FORM LT on the overhead panel. The formation lights can be switched ON and OFF via the FORM sw located in the group EXT LIGHTS on the overhead panel.
O N
If the formation lights switch is in:
TI
– ON position: Formation lights are on.
R
U
C
– OFF position: Formation lights are off. OFF
FO
R
IN
ST
OFF
OFF
OFF
OFF
O N ON
HISL
Fig. 7-11-22
7 – 11 – 20
OFF
FORM
ON
IR FLASH
ON
STROBE
ON
POS
ON
ACOL
EXT LIGHTS
Formation lights switch – typical installation
MANUFACTURER’S DATA Rev. 17.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.11.4.14
External multipurpose light (optional)
External multipurpose light – typical installation
O N
Fig. 7-11-23
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
The system consists of two fixed LED Lights (see Fig. 7-11-23) installed on the lower side of the tail boom. The light is useable for hoist operations, external cargo operations and any other operations requiring an external light beam.Depending on the required operation (hoist left or right, hoist height, cargo hook, etc), the field of illumination must be defined and adjusted accordingly prior to flight. Refer to the maintenance documentation for adjustment of the external multipurpose light.
ST
R
U
C
TI
The external multipurpose light is switched on and off by an optional switch (labelled HOIST LIGHT) on the EXTERNAL LIGHTS control panel (center console) or by switches (labelled HOIST LIGHT) installed on panels in the cabin LH and RH side sliding door upper frame.
IN
The switches and the function of the multipurpose light are fully independent from the functions of the external hoist system (if installed).
FO
R
To switch the light on: – Press HOIST LIGHT switch, either on the center console or in the cabin LH or RH – ON will be indicated on each switch To switch the light off: – Press HOIST LIGHT switch, either on the center console or in the cabin LH or RH – ON extinguishes on each switch
MANUFACTURER’S DATA Rev. 17.1
7 – 11 – 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ON
ON
EXTERNAL LIGHTS FWD
BKD2_FLH_0289_R
S T O W OFF
HOIST LIGHT
R
ON
OFF
LDG
AFT
CP S/L
External multipurpose light switch on center console – typical installation
Hoist Light switch on panel installed in the cabin (LH and RH) – typical installation
FO
R
IN
ST
R
U
C
TI
O N
Fig. 7-11-25
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Fig. 7-11-24
L
7 – 11 – 22
MANUFACTURER’S DATA Rev. 17.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.12
AIR DATA SYSTEM
7.12.1
General The air data system (see Fig. 7-12-1) provides pitot and static pressure to the air data computers (ADC) and the standby instrument IESI. The architecture is based on two similar, but independent barometrical systems. System 1 is installed on the LH side of the helicopter (co-pilot system), system 2 on the RH side (pilot system). Each system contains one heated pitot tube and two heated static ports.
ED
7.12.1.1 Static ports
T
C
O
N TR
O
LL
Each system contains two external static ports to sense the ambient pressure. One static port is installed on the LH side, the other on the RH side, and they are interconnected. The static ports are flush mounted at the ring frame above the clam shell doors. To prevent entry of moisture and dirt in the pipe system, the connector of the static port is installed with an upward orientation.
N
O
7.12.1.2 Pitot tube
LY
O N
7.12.1.3 Pitot/Static heating system
–
C
O
PY
The pitot tubes are the air intakes for ram-air pressure. They are installed at the front of the helicopter at the pitot tube support.
ST
R
U
C
TI
O N
The static ports and pitot tubes are electrically heated to prevent the formation of ice. The heating system is controlled separately for system 1 and system 2 by means of the PT/STATIC HTG PILOT sw and PT/STATIC HTG COPILOT sw on the overhead panel. System 1 is supplied with electrical power via the SHED BUS I and the PT/ST cb. System 2 is supplied via the ESS BUS II and the PT/ST cb.
IN
7.12.1.4 Alternate static source selector
FO
R
WARNING
USE OF THE ALTERNATE STATIC SOURCE SHALL BE PERFORMED STRICTLY IN ACCORDANCE WITH THE ASSOCIATED EMERGENCY PROCEDURE (REFER TO SECT. 3).
The alternate static source selector, installed in system 2 at the RH side of the instrument panel, supplies the ambient pressure in the cockpit as an alternate source of static pressure if the external static ports become blocked. The alternate static source selector is a pure mechanical device, whose design allows that when one source is selected, the other source is blocked. It is not possible to block the two sources simultaneously. The position of the switch is labelled with a marking plate showing “static tube static pressure” or “selector valve alternate source“. When selecting the alternate source of pressure (cabin pressure), Helionix must be properly configured to use the correct source (see section 3). Once the alternate pressure source is properly selected, the indicated altitude and airspeed have to be corrected in accordance with the correction table given in Sect. 5. MANUFACTURER’S DATA Rev. 0
7 – 12 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
4
3
5
ED
6
N TR
O
LL
2
T
C
O
1
C
O
PY
N
O
A
8 7
Fig. 7-12-1
Pitot tube, RH
2
Air data computer 2 (ADC2)
R
FO
5/6
IN
1 3/4
Static ports, RH Static ports, LH
7
Alternate static source selector
8
Air data computer 1 (ADC1)
9
Pitot tube, LH
7 – 12 – 2
Air data system
ST
R
U
C
TI
O N
9
O N
BKD2_FLH_0160_R
LY
–
A
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.12.2
Air data indications Two ACDs process the pitot and static pressure values and provide the resulting altitude and airspeed values to the FND. Altitude and airspeed are indicated on the FND in scale format (see Fig. 7-12-2). In addition, the pitot and static pressure of system 1 are provided to the IESI to indicate altitude and airspeed.
ED
Master list messages for the air data system are indicated on the FND if the heating systems are off or if a failure is detected. The air data indications are permanently monitored and (if the failure can be localized) automatically reconfigured by the Helionix flight monitoring function (refer to Para 7.13.4).
O
1
LL
Refer to Para. 7.13.6 for complete list of master list messages.
24
10
10
10
20
20
33
N
140 D H B A R O
3
DA
hPa
120 100
S Y S T
29.69in 012 011 10 10 010 09 08 10 10 07
21
S
12
15
OAT
ENG OIL B A R
CLOCK ALT
18
N U M
N1 94.0 % ENG OIL B A R
MGB OIL B A R
B A R
FUELKg
D A T A
1
A C K
30
FF Kg/h
W 24
S E L
DH
STATUS REPORT
N A V 100. 0 % N2 EPC
CONF
100. 0 % TUNE
IAS
NAV
101 20
20
10
10
10
10
20
20
33
21
N
S
D A
D H
3
DA
15
hPa
DH
6 E 12
1
DTK FSD FMS GPS LFMH
DCPL
0
SCT
3
B A R O
SVS
OAT
A C K
4
DH
O N
LY
–
SVS
B A R
EFB
TOT 710
FF Kg/h
0
SCT
HYD
MISC
TRQ 54.0 %
N1 94.0 %
DH
E
FMS GPS LFMH
DMAP
TOT 700
B A R
N
NAVD
TRQ 55.0 %
R C N F
6
DTK FSD
DCPL
160
T
10
FND
D A
O
30 W
N A V
CLOCK
O
MISC IAS 18
20
N
DMAP NAV
20
PY
VMS ALT
C
NAVD
101
C
O
N TR
2
Air data system indications on IESI and FND – typical display
O N
Fig. 7-12-2
Integrated electronic standby instrument (IESI)
2
FND airspeed scale
3
FND altitude scale
4
Master list area
FO
R
IN
ST
R
U
C
TI
1
MANUFACTURER’S DATA Rev. 0
7 – 12 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
O
T
C
O
N TR
O
LL
ED
DESCRIPTION OF SYSTEMS
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
Intentionally left blank
7 – 12 – 4
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13
HELIONIX
7.13.1
General The helicopter is equipped with the integrated modular avionics system Helionix. The main system components are: – two duplex Aircraft Management Computers (AMC) – three Multifunction Displays (MFD) In addition, the system interacts with the following units: – Data Transfer Device (DTD)
ED
– Cockpit Control Panel (CCP)
LL
– Integrated Electronic Stand-by Instrument (IESI)
N TR
O
– Attitude and Heading Reference Systems (AHRS) – Air Data Computers (ADC)
O
– Magnetometers
T
C
– Memory module
N
O
The system provides the following main capabilities:
PY
– Flight and navigation instruments
O
– Vehicle management
C
– Alerting system – Usage monitoring (UMS)
O N
– Automatic flight control
LY
–
– Flight monitoring
O N
– Air data / Attitude / Heading reference computation
TI
– Flight data recording (FDR)
C
– Enhanced situation awareness (HTAWS, SVS, DMAP)
ST
R
U
– Electronic flight bag
IN
7.13.1.1 Aircraft Management Computers (AMC)
FO
R
The AMCs are installed in the lower avionics compartment and comprise mainly two physically separated acquisition and processing modules, and aural alert generator. Various analog and digital inputs are processed, transferred to the MFDs and recording systems. Built-in tests monitor the system itself and external equipment and wiring. The system architecture is based on software partitions for different applications, e.g. vehicle and engine management (VMS partition) or automatic flight control system (AFCS partition). Each AMC contains two separate hardware channels, which perform complementary functions and provide internal integrity monitoring.
7.13.1.2 Multifunction Displays (MFD) Three MFDs (see Fig.7-13-1) are installed in the instrument panel. MFD1 is installed in front of the copilot’s seat, MFD2 is installed in front of the pilot’s seat, and MFD4 is installed between MFD1 and MFD2. MANUFACTURER’S DATA Rev. 0
7 – 13 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
The MFDs are LCD displays with integrated processing modules. They are optionally NVG compatible and interchangeable. The MFDs receive signals from the navigation systems installed in the helicopter to process and indicate them. Via the AMCs, vehicle monitoring information is routed toward the MFDs and displayed in order to inform the crew about the status of the helicopter’s main systems. Additionally, the MFDs can be connected to different mission equipment, e.g. EOS, and video information. The MFD controls (see Fig.7-13-2 and 7-13-5) are located around the display bezel. 2
LL
ED
1
24 N A V
10
10
20
20
33
N
DA
S Y S T
D H
R C N F
hPa
S
15
12
N1 94.0 % ENG OIL B A R
MGB OIL B A R
B A R
30
FF Kg/h
W 24
D A T A A C K
S E L
N A V 100. 0 % N2
DH STATUS
REPORT
EPC
CONF
100. 0 % TUNE
20
20
10
10
10
10
20
20
33
21
D A
D H
B A R O
N
3
DA
hPa
S
15
DH
6
E 12
1
DTK FSD FMS GPS LFMH
DCPL
SCT
0
SVS
OAT
A C K
DH
C
MFDs – typical installation
MFD4
3
MFD2
O N
2
O N
MFD1
FO
R
IN
ST
R
U
C
TI
1
LY
–
Fig. 7-13-1
O
PY
N
OAT
ENG OIL B A R
B A R
NAV
18
N U M
FUELKg
1
0
SVS
HYD
IAS
101
TOT 710
FF Kg/h
DTK FSD
SCT
CLOCK
EFB
TRQ 54.0 %
N1 94.0 %
DH
E 21
TRQ 55.0 % TOT 700
B A R
6
FMS GPS LFMH
DCPL
D A
B A R O
3
MISC
N TR
10
DMAP
7 – 13 – 2
MANUFACTURER’S DATA Rev. 0
BKD2_FLH_0404_R
30 W
20
10
NAVD
ALT
18 20
FND
C
101
CLOCK
O
MISC IAS
T
DMAP NAV
O
VMS ALT
O
3
NAVD
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
1
2 + C T R S –
3
N TR
O
LL
ED
4
C
O
PY
N
O
T
C
O
9
– LY
+ L U M –
6
MFD controls
R
IN
ST
R
ON/OFF key Main select keys (MSK) (bezel keys), 6x CTRS key (rocker switch) – can be used to control the overlay contrast RH Line select keys (LSK) (bezel keys), 6x BRT key (rocker switch) – can be used to adjust the brightness of the video overlays (including DMAP and SVS) Double rotary knob and push button Bottom select keys (BSK) (bezel keys), 6x LUM key (rocker switch) – can be used to adjust the overall display luminance LH Line select keys (LSK) (bezel keys), 6x
FO
1 2 3 4 5
Fig. 7-13-2
5
U
C
TI
O N
7
+ B R T –
O N
BKD2_FLH_0219_R
8
6 7 8 9
The bezel keys (MSK, LSK and BSK) are associated to specific functions shown on the display next to the key. The CTRS key, BRT key and LUM key can be used to adjust display contrast, brightness and luminosity. The double rotary knob and push button can be used to navigate on the MFD screens and to modify parameters. MANUFACTURER’S DATA Rev. 0
7 – 13 – 3
7 – 13 – 4
Fig. 7-13-3
Air Data Probes, (pilots, OAT, static)
AFCS actuators
Vehicle and engine sensors
CVFDR
Control panels, Indicators
Ground station and test tools
External computers (DMAU, Mission PU, ...)
External FMS
Radionav/ radiocom sensors
Mission sensors (FLIR, WXR, ...)
Video
A429
R
FO R
ST
A429
LY
ADU(s)
PY
O
C
Ethernet network
–
MFD(s)
A429, discretes, analog
A429, analog
A717
O N
Discretes
DTD
O N
TI
C
U
Video, A429, A708, RS422
IN
N
CWP
A429
ED
AHRS without MAS Memory Module
IESI
HELIONIX system
AHRS including MAS
MFD
LL
O
N TR
O
C
AMC(s)
T
O
System network
Xcheck
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.1.3 Helionix system architecture
Helionix system architecture
MANUFACTURER’S DATA Rev. 0
BKD2_FLH_0295_R
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2
MFD formats The following formats are available for display on the MFDs: – Flight and navigation display (FND) – Vehicle management system (VMS) – Navigation display (NAVD) – Digital map display (DMAP) – Miscellaneous display (MISC)
MISC
EFB
MFD modes – typical display
PY
N
Fig. 7-13-4
DMAP
C
VMS
T
NAVD
+ C T R
O
FND
O
N TR
BKD2_FLH_0220_R
O
LL
The MFD format labels are displayed below the main select keys.
ED
– Electronic flight bag (EFB)
C
O
On MFD1, the available MFD formats depend on the setting of the MFD COPILOT rotary knob on the Cockpit Control Panel (CCP) (refer to Para 7.2.3.1):
LY
–
– NORM: the MFD1 formats can be freely selected. NORM should be selected when a crew member occupies the co-pilot’s seat.
O N
– VMD: MFD1 is set to the VMS format
O N
– FND: MFD1 is set to the FND format
TI
– OFF
R
U
C
For dual pilot IFR operation, the pilot flying must select NORM and set the FND in the primary field of view.
R
IN
ST
On MFD4, all formats are selectable. After helicopter power on, the VMD format is selected by the system. To allow monitoring of the engine parameters, the VMS page must be selected during engine start and shutdown.
FO
On MFD2, the FND format is displayed permanently. No labels for selection of other formats are displayed.
MANUFACTURER’S DATA Rev. 0
7 – 13 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2.1 Flight and Navigation Display (FND) format The FND format (see Fig.7-13-5) presents all primary flight information. 2
VMS
DMAP
ALT
NAV
20
17
10
10
16
16
1 500
15
14
14
13
C
80
10
10
20
20
3
VY
N
3
O C
W
–
24
GPS
15
O N
S
C
U
DCPL
8
12
A C K
415 Kg
TI
20.0 NM 12 min
7
SCT
SVS
OAT
25
_C
9 + B R G –
10
IN
ST
R
+ L U M –
FO
R
BKD2_FLH_0397_R
LFMH
1013 200 hPa DH
E
O N
12
FSD
354 1.0 FMS
LY
21 DTK
13
6
6
30
N A V
B A R O
PY
33
13*
600 DA
D H
N TR
100
5
LL
20
T
2
120
D A
17
O
4
18
4
N
14
7 – 13 – 6
IAS
101 6
+ C T R S –
CLOCK
O
15
MISC
ED
NAVD
3
O
1
Fig. 7-13-5
11 FND format, MFD1 and MFD4– typical display
MANUFACTURER’S DATA Rev. 0
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1
NR/N2 indicator (refer to Section 2, para 2.10)
2
Attitude indicator
2 3
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
1
–
1. Sideslip indicator
O N
O N
LY
2. Flight path angle (brown diamond): Indicates the flight path (climb/descent) angle in degrees. When the autopilot is coupled in FPA mode, the glidepath angle is displayed in green.
TI
3. Autopilot flight path angle (cyan or green): Flight path angle selected for FPA mode or flight path angle of the LPV final approach segment.
IN
AFCS strip (refer to Para 7.3.6.9)
FO
R
3
ST
R
U
C
For improved situational awareness, the attitude indicator covers the entire upper area of the FND. The attitude indicator can be replaced by the (optional) SVS. Refer to 7.19 for details on the SVS.
MANUFACTURER’S DATA Rev. 0
7 – 13 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Vertical speed indicator The digital value indicates the rate of climb/descent in hundreds of feet.
5
Altitude indicator
N TR
O
LL
ED
4
2
3
4
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
1
FO
1. DA + 500 ft indication: Indicates 500 ft above the selected Decision Altitude. 2. Autopilot Altitude Reference 3. Decision Altitude (DA) 4. Radar height: Indicates 0 ft above ground (based on radar altimeter).
7 – 13 – 8
MANUFACTURER’S DATA Rev. 0
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6
Radar altimeter indication
C
O
N TR
O
LL
ED
1
1. Decision Height (DH)
O
2. Ground: Below 0 ft radar height.
PY
N
O
T
2
LY
7
–
C
Maximum height indicated by the radar altimeter is 2200 ft. Wind vector THE WIND INDICATION IS PROVIDED AS AN ESTIMATE ONLY. THIS ESTIMATE IS OFTEN UNRELIABLE, PARTICULARLY IN TURNS, WHILE SIDESLIPPING, OR AT LOW SPEED. THEREFORE, THE WIND ESTIMATE SHOULD NOT BE USED AS THE SOLE MEANS TO DETERMINE THE WIND DIRECTION AND SPEED – ESPECIALLY NOT FOR TAKEOFF AND LANDING.
R
U
C
TI
O N
O N
CAUTION
FO
R
IN
ST
An estimate of the current wind direction and speed is calculated by the GTN750 based on true airspeed, aircraft heading, and ground speed. This estimate is calculated and constantly updated when IAS > 40 kt. Below 40 kt, the last valid wind estimate is indicated. Wind vector symbols are used, as follows: Wind calm Wind 25 kt (each long line 10 kt, short line 5 kt) Wind 50 kt (triangle 50 kt) Wind 75 kt
MANUFACTURER’S DATA Rev. 0
7 – 13 – 9
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8
Heading indicator. Three formats are available: HSI, SCT, and HOV. Horizontal situation indicator (HSI): 1 2 3 4
LL O
6
ED
5
T
C
O
N TR
1. Track angle (diamond symbol): Indicates the current track. The difference between the reference and the track is the current drift angle. A brown diamond indicates the current track angle. A cyan or green diamond indicates the autopilot track angle (in TRK mode).
N
O
2. Double pointer: Shows the bearing to the selected source (VOR, ADF, FMS)
PY
3. Course deviation indicator
C
O
4. Deviation scale (up to 2 dots each direction). When an FMS navigation source is used, the full scale deflection (FSD) in NM is indicated above the NAV window.
–
5. 45_ mark
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
6. Single pointer: Shows the bearing to the selected source (VOR, ADF, FMS)
7 – 13 – 10
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Sector indicator (SCT): 6 1 2
4
3
ED
5
LL
1. Course indicator.
N TR
O
2. Range indication: The full scale range (5 NM in the figure) is shown near the 45_ mark.
C
O
3. Waypoint: The active waypoint is shown in cyan or green; subsequent waypoints are shown in white.
PY
N
O
T
4. Deviation indication (during LPV or ILS approach only). When an FMS navigation source is used, the full scale deflection (FSD) in NM is indicated above the NAV window.
C
O
5. Altitude prediction: Point at which the target altitude (in the figure 4000 ft) will be reached.
FO
R
IN
ST
R
U
C
TI
O N
O N
Hover indicator (HOV):
LY
–
6. Track angle (diamond symbol)
1. Track angle (diamond symbol)
1 2 3 4 5 6
2. Altitude prediction: Predicted altitude at the hover position when the current vertical rate is maintained. 3. Hover target (semi–circle): Predicted hover position of the GTC.H mode (symbol shown in cyan when GTC is active and in green when GTC.H is active) 4. Groundspeed lines: The groundspeed can be obtained from the relative position of the aircraft symbol and the groundspeed symbols. In the figure shown, the groundspeed is approximately 22 kt with a 6kt right sideways component. 5. Autopilot groundspeed target: The center of the green oval shows the hover target speed (0 kt in the figure). 6. Range: The full scale range (relevant for the hover target)
MANUFACTURER’S DATA Rev. 2
7 – 13 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
9
Fuel quantity indication (refer to Para 7.6.5)
10
OAT indication
11
Master list (refer to Para 7.13.3)
12
Navigation information (refer to Para 7.14)
13*
Mast moment indication (indicated below 55 KIAS) (refer to Section 2, Para 2.12.6)
14
Airspeed indicator 1
ED
2
O
LL
3
O
N TR
4
T O
PY
N
6
C
5
C
O
7
LY
–
1. VNE: Indicates the maximum speed.
O N
2. Autopilot IAS target.
3. VNE power off: Indicates the maximum speed in power off conditions.
O N
4. Airspeed trend: Indicates the speed expected in 5 seconds.
TI
5. VY: Indicates the best rate of climb speed.
ST
R
U
C
6. Groundspeed: Indicates the ground speed in the longitudinal direction. If the ground speed cannot be shown on the scale, a digital value will be shown at the top or bottom of the airspeed scale.
7 – 13 – 12
First limit indicator (FLI) (Refer to Section 2, Para 2.11.1)
FO
15
R
IN
7. VTOSS: Indicates the VTOSS. If the airspeed is less than VTOSS, a digital indication of VTOSS will be shown.
MANUFACTURER’S DATA Rev. 0
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Select key
Description
NAVD (not available on MFD 2)
Displays NAVD format (refer to Para. 7.13.2.3)
VMS (not available on MFD 2)
Displays VMS main format (refer to Para. 7.13.2.2)
DMAP (not available on MFD 2)
Displays DMAP format (refer to Para. 7.13.2.4)
MISC (not available on MFD 2)
Displays MISC format (refer to Para. 7.13.2.5)
CLOCK / CHR / LCL
First press selects stop watch (CHR).
ED
Second press selects display of time of the zone selected.
LL
Third press deselects clock functions. – First short press starts stop watch;
N TR
O
Operate stop watch with rotary knob/push button as follows: indicated indicated
C
O
– Second short press stops stop watch;
N
O
T
– Long press while stop watch is running resets and restarts stop watch; indicated
O
PY
– Long press when stop watch is not running resets stop watch; indicated Selects / deselects Descision Altitude (DA) for manual input.
–
C
DA
LY
Change DA with rotary knob/push button as follows:
O N
– Large rotary knob: 100 ft/tick – Small rotary knob: 10 ft/tick
TI
O N
A long press of DA key – after DA is selected for manual input – will indicate DA OFF. After 5 sec the DA window will disappear. Selects / deselects Descision Height (DH) for manual input.
U
C
DH
FO
BARO
R
IN
ST
R
Change DH with rotary knob/push button as follows: – Large rotary knob: 10 ft/tick – Small rotary knob: 1 ft/tick Selects / deselects barometric pressure for manual input. Change BARO with rotary knob/push button as follows: – Large rotary knob: 10 hPa/tick – Small rotary knob: 1/2 hPa/tick Selects the single bearing source to be referenced (VOR1, ADF (if installed), FMS).
MANUFACTURER’S DATA Rev. 0
7 – 13 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Select key
Description Selects the double bearing source to be referenced (VOR2, ADF (if installed), FMS).
ACK
Short press acknowledges new master list messages.
ED
Push and hold recalls messages on the master list which were not acknowledged. This allows recalling messages that popped up and disappeared again. The master list returns to the current display when the key is released. Refer to FMS 9.2-8 or 9.2–30 for Weather Radar System operation and indication.
SCT / HOV / HSI
Selects heading indicator display mode (SECTOR / HOVER / HSI)
CPL / DCPL / DISARM
CPL: Couples the AP to the navigation source.
N TR
O
LL
WXR (if installed)
C
O
DCPL: Decouples the AP from the navigation source.
T
DISARM: Disarms the autopilot.
Selects navigation source for AP coupling (VOR/ILS1, VOR/ILS2, FMS)
RNG (only present if heading indicator in HOV or SCT display mode)
Selects heading indicator display range for manual input.
PY
N
O
NAV
C
– HSI mode: 0.5 – 240 NM
O
Change RNG with rotary knob/push button as follows:
LY
–
– HOVER mode: 1 or 2 NM
Selects the display format between standard FDS and SVS. For details on SVS, refer to 7.19.
FO
R
IN
ST
R
U
C
TI
O N
O N
SVS / FDS
7 – 13 – 14
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2.2 Vehicle management system (VMS) format The VMS format displays information related to the vehicle and sensor status. The VMS main format (see Fig.7-13-6) displays vehicle information to the crew, providing detailed information on engines, rotor, main gearbox, fuel, hydraulics, and electrical system. Refer to Sect. 2 for indication formats and limit markings. 2
3
ED
1
DMAP
MISC
EFB
O
C LY
47
N 72
9.0
314
54
100
R
R FO
BKD2_FLH_0469_R
IN
ST
7
+ L U M –
3 4 5 6
30
3.0
G1
B A R
5
3.0 G2
137
6 101. 0
S E L
101. 0 % N2 101. 0 % CPL
4
TIME ZONE
REPORT
Fig. 7-13-6 1 2
_C
FF Kg/h
U
C
TI
O N
137
9.0
FUEL Kg
O N
FF Kg/h
C
72
–
103
2 h 30 min
8
30 %
MGB OIL B A R
O
B A R
94.0 %
_CENG OIL B A R
PY
_C ENG OIL B A R
N U M
IBF
N1
94.0 %
10 %
TOT _C 710
O
N1
HYD
103
T
IBF
B A R
D A T A
55.0 %
TOT _C 700
R C N F
9
TRQ
55.0 %
N TR
TRQ
S Y S T
+ C T R S –
LL
NAVD
O
FND
EPC
STATUS
CONF
WEIGHT
+ B R T –
VMS main format – typical display
Engine 1 indicators TRQ, TOT, N1 (refer to Para 7.5.5) Engine 1 and engine 2 oil temperature and oil pressure indicators (refer to Para 7.5.5) Engine 2 indicators TRQ, TOT, N1 (refer to Para 7.5.5) Main transmission oil temperature and oil pressure indicators (refer to Para 7.7.4) Electrical system indication (refer to Para 7.9.3) N2/NR indicator (refer to Para 7.5.5)
MANUFACTURER’S DATA Rev. 9
7 – 13 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7
Data area The data area can present up to 4 different pages: – Weight & performance page – Time zone page – Hoist page (if configured) – Cargo hook page (if configured)
LL
ED
Weight page: The weight page displays: – Total aircraft weight. If the total weight exceeds the maximum all up gross mass, the weight is shown in amber.
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
– Performance data (as per the flight manual) for AEO HIGE, AEO HOGE, Cat A VTOL, OEI 30s HOGE and OEI 2min HOGE. The performance data is calculated based on the current altitude, temperature, heating condition (on or off) and IBF configuration (installed or not). Wind is not taken into account (i.e. the calculation is based on a zero wind condition). It also takes into account any hover performance degradations entered on the weight and performance page (see Para 7.13.5.1). If the total weight exceeds the calculated performance weight, the weight is shown in amber.
FO
R
IN
ST
R
U
Time zone: The time zone page displays the current time (depending on the selected zone) and allows entering different time zones, which are used to indicate the time on the FND. The time zone can be changed in 15 minute steps by pressing SEL and the rotary buttons on the MFD.
Hoist page: See FMS 9.2–4 Dual external cargo hook page: See FMS 9.2–6 Sling type cargo hook page: See FMS 9.2–7
7 – 13 – 16
MANUFACTURER’S DATA Rev. 0
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8
Fuel indication (refer to Para 7.6.5)
9
Hydraulic indication (refer to Para 7.4.2) Description
FND
Displays FND format (refer to Para. 7.13.2.1)
NAVD
Displays NAVD format (refer to Para. 7.13.2.3)
DMAP
Displays DMAP format (refer to Para. 7.13.2.4)
MISC
Displays MISC format (refer to Para. 7.13.2.5)
EFB
Displays EFB format (refer to Para. 7.13.2.6)
NUM
Selects / deselects permanent display of digital values on the VMD main format.
WEIGHT
Displays weight page (refer to Para. 7.13.5.1)
CONF
Displays configuration system page (refer to Para. 7.13.5.1)
STATUS
Displays system status page (refer to Para. 7.13.5.1)
EPC
Selects engine power check (refer to Sect. 5)
REPORT
Displays flight report page (refer to Para. 7.17.1)
DATA
Scrolls through display of total weight, time zone, cargo hook load weight (if installed), or hoist cable length (if installed) on data page area.
PY
N
O
T
C
O
N TR
O
LL
ED
Select key
–
C
First press: time zone
O
Total weight is displayed on system start-up.
LY
Second press: cargo hook load weight (if installed)
O N
Third press: hoist cable length (if installed) Fourth press: return to display of total weight Displays RCNF sub-format (see Fig. 7-13-10)
SYST
Displays SYST sub-format (see Fig. 7-13-7)
FO
R
IN
ST
R
U
C
TI
O N
RCNF
MANUFACTURER’S DATA Rev. 0
7 – 13 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
The VMS SYST sub-format (see Fig.7-13-7) displays an overview of the navigation and mission equipment status, and AFCS status.
FND
1
FMS1 FMS2
DMAP
GPS2 TACAN IESI
DME DF HOMG ADF
MISC
EFB
+ C T R S –
ACAS RA WXR
ED
R C N F
VMS
VOR1
LL
C T
NAVD
O
VOR2
N TR
GPS1
T
C
O
2 AFCS
N
O
TRIMS ACTUATORS
O
COLL PITCH ROLL
C
AP2
YAW
O N
LY
–
BACKUP AP1
PY
CTRL PANEL
DATAB
O N
PREV
LOAD
+ B R T –
MAINT
U
C
TI
BKD2_FLH_0223_Rx
+ L U M –
VMS SYST sub-format – typical display
IN
ST
R
Fig. 7-13-7
Status area for external avionics equipment.
R
1 2
FO
A system failing the pre-flight test will be indicated red. AFCS status area (refer to Para. 7.3.6.10)
Select key
Description
FND
Displays FND format (refer to Para. 7.13.2.1)
NAVD
Displays NAVD format (refer to Para. 7.13.2.3)
VMS
Displays VMS main format (refer to Para. 7.13.2.2)
DMAP
Displays DMAP format (refer to Para. 7.13.2.4)
MISC
Displays MISC format (refer to Para. 7.13.2.5)
EFB
Displays EFB format (refer to Para. 7.13.2.6)
MAINT
Selects maintenance page (refer to AMM).
7 – 13 – 18
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Select key
Description
LOAD
Allows to download the UMS/HMS data manually, in case DOWNLOAD FAIL is indicated on the ML (refer to Section 8).
DATAB
Provides information concerning of the Helionix databases (DMAP, HTAWS, EFB) (see Fig. 7-13-9)
PREV
Displays previous page (VMS main format or VMS RCNF sub-format)
RCNF
Displays RCNF sub-format (see Fig. 7-13-10)
CT
Displays the results of the pre-flight tests
O
LL
ED
The CT (Clearance Test) sub-page provides a list of all failures found during the clearance tests (i.e. the power-up, start-up, and pre-flight test). This page can be accessed throughout the flight (until power down).
T
C
O
N TR
Immediately after completion of each clearance test, the test results (i.e. all detected failures) are shown in the master list. When the next clearance test is started, when the autopilot is engaged, or when the aircraft takes off, the results of the previous clearance test are erased from the master list. To remind the pilot that clearance test failures occurred, the
–
If a pre-flight test is re-performed, the results of the new pre-flight test will replace the previous results on the CT page.
NAV
VMS
DMAP
MISK
EFB
+ C T R S –
IN
ST
R
FND
U
C
TI
O N
O N
LY
NOTE
C
O
PY
N
O
T symbol is displayed on the FND above the master list. At the same time, all recorded failures are copied onto the CT page (Fig 7-13-8). In addition, the CT page also indicates if a test was not performed (P–FLT TST NOT DONE) or aborted (e.g. AP1 TST ABORTED).
FO
R
S Y S T
PW–UP: GND/FLT SENSOR P–FLT : AP1 TST FAIL P–FLT : TST FAIL AP2
R C N F
Fig. 7-13-8 MANUFACTURER’S DATA Rev. 6.1
CT sub-page – typical display
7 – 13 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
The database information window is accessible through the DATAB key on the VMS/SYST page. All databases used by the Mission functions (DMAP, HTAWS, SVS and EFB) are loaded individually on each of the MFDs in the helicopter. Each database includes cyclic data (obstacles, aeronautical) which carry expiry dates and therefore need to be refreshed periodically, and non-cyclic data (terrain, ground vector, raster) that do not have expiry dates. The mission database window provides the operator a view on the stored DB EXPIRED databases. If any cyclic data expires, then an amber label in the Mission Database page.
ED
After Helionix Maintenance Release 1
LL
EFFECTIVITY
is raised
All
O
EFFECTIVITY
N TR
O
At the same time, an alert DATABASE EXPIRED is also displayed in the Master List (on ground only).
C
O
Before Helionix Maintenance Release 1
–
All
MISSION DATABASE
PAGE
1 / 10
PREV.PAGE AERONAUTICAL EUROPE
05SEP10
R
U
C
TI
O N
EFFECTIVITY
DO NOT SWITCH THE AERONAUTICAL DATABASE IN FLIGHT.
LY
CAUTION
O N
EFFECTIVITY
PY
N
O
T
C
Up to two sets of aeronautical databases can be loaded in the MFD memory as part of the mission database. It is possible to switch between aeronautical databases when helicopter is on ground. The switch command is however disabled in flight mode. When the aero DB switch is performed, DMAP, HTAWS, SVS use the new aeronautical database.
10OCT10
–
ST
OBSTACLES AAAAAAAAAA AAAAAAAAAA AAAAAAAAAA AAAAAAAAAA
IN
TERRAIN – S WRLDWIDE
–
–
2.2
R
TERRAIN – HR
FO
WRLDWIDE
–
–
3.1
–
3.1
VECTOR – S EUROPE
–
VECTOR – HR WRLDWIDE
–
–
3.1
NEXT PAGE
BKD2_FLH_0536_R
DB EXPIRE
Fig. 7-13-9
7 – 13 – 20
AERONAUTICAL WRLDWIDE
10OCT10
10OCT10
C N F R M C A N C L
Mission database information window
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
The VMS RCNF sub-format (see Fig.7-13-10) displays an overview of the status and reconfiguration of the primary sensors.
R C N F
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Refer to Para. 7.13.4.4 for description of the automatic and manual redonfiguration.
Fig. 7-13-10
VMS RCNF sub-format – typical display
Select key
Description
FND
Displays FND format (refer to Para. 7.13.2.1)
NAVD
Displays NAVD format (refer to Para. 7.13.2.3)
VMS
Displays VMS main format (refer to Para. 7.13.2.2)
DMAP
Displays DMAP format (refer to Para. 7.13.2.4)
MISC
Displays MISC format (refer to Para. 7.13.2.5)
EFB
Displays EFB format (refer to Para. 7.13.2.6)
RCNF / DESEL / SEL
Deselect / select primary sensors (refer to Para 7.13.4.4 for details).
MANUFACTURER’S DATA Rev. 9
7 – 13 – 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Select key
Description
AIR
Resets AIR data after manual switching to cabin static pressure
FMS
Selects FMS1 or FMS2
HDG
Selects heading configuration TRUE or MAG NOTE
After changing between TRUE and MAG, a delay of 2 seconds should be observed before selecting another MFD page. Failure to do so could result in blocking the TRUE/MAG selection.
Displays previous page (VMS main format or VMS SYST sub-format)
SYST
Displays SYST sub-format (see Fig. 7-13-7)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
PREV
7 – 13 – 22
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2.3 Navigation display (NAVD) format
N TR
O
LL
ED
The NAVD format displays detailed navigation information (see Fig.7-13-11). The navigation information is shown on the compass rose or segment, and in the top line of the NAVD display. Additional information can be displayed in the lower third of the display after pressing the DATA key. In addition, HTAWS, ACAS (if installed) can be displayed. A weather radar image (if installed) can be displayed as overlay.
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
_
ST
R
_ _ _
_
FO
R
IN
_
Fig. 7-13-11
NAVD format – typical display
Select key
Description
FND
Displays FND format (refer to Para. 7.13.2.1).
VMS
Displays VMS main format (refer to Para. 7.13.2.2).
DMAP
Displays DMAP format (refer to Para. 7.13.2.4).
MISC
Displays MISC format (refer to Para. 7.13.2.5).
MANUFACTURER’S DATA Rev. 9
7 – 13 – 23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Select key
Description
EFB
Displays EFB format (refer to Para. 7.13.2.6). Selects the single bearing source to be referenced (VOR1, ADF (if installed), FMS).
ED
Selects the double bearing source to be referenced (VOR2, ADF (if installed), FMS).
Displays data of all selected navigation sources.
HTAWS
– Short press: (De)-Activates the HTAWS indications and the Height Above Terrain coloring.
N TR
O
LL
DATA
– Long press: Displays the HTAWS virtual control panel. – Short press: (De)-Activates the ACAS indications.
T
ACAS (if installed)
C
O
Refer to Section 7.18 for details on HTAWS operation and indications.
N
O
– Long press: Displays the ACAS virtual control panel.
O
PY
Refer to FMS 9.2-3 or FMS 9.2-43 for or details on ACAS operation and indications. Refer to FMS 9.2-8 or FMS 9.2-30 for Weather Radar System operation and indication.
SCT/ROS/PLN
Selects navigation area display mode (SECTOR / ROSE / PLAN).
LY
–
C
WXR (if installed)
O N
1. ROSE: Heading up. Own aircraft symbol is centered on the map. PLAN mode should be used for pre-flight planning only. In flight, a north–up orientation does not allow obstacles and terrain to be properly recognized.
R
U
C
TI
NOTE
O N
2. PLAN: North up. Own aircraft symbol is centered on the map.
R
CPL: Couples the AP to the navigation source.
FO
CPL / DCPL / DISARM
IN
ST
3. SCT: Heading up. Shows a $45_ sector with the own aircraft symbol in the lower part of the display. DCPL: Decouples the AP from the navigation source. DISARM: Disarms the autopilot.
OFRT
Selects / deselects display of waypoints (e.g. airports) that are not part of an active flight plan. Off route waypoints are indicated on the NAVD in brown.
RNG
Change display range by turning rotary knob/push button. Permanently selected in NAVD format.
NAV
Selects navigation source.
7 – 13 – 24
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2.4 Digital map display (DMAP) format Refer to FMS 9.2-2 and 9.2-32. 7.13.2.5 Miscellaneous display (MISC) format
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
The MISC format displays up to four different external video inputs (see Fig.7-13-12). External video can be from an EOS sensor or from cameras installed on the aircraft.
Fig. 7-13-12
MISC format – typical display
Select key
Description
FND
Displays FND format (refer to Para. 7.13.2.1)
NAVD
Displays NAVD format (refer to Para. 7.13.2.3)
VMS
Displays VMS main format (refer to Para. 7.13.2.2).
DMAP
Displays DMAP format (refer to Para. 7.13.2.4)
EFB
Displays EFB format (refer to Para. 7.13.2.6)
MANUFACTURER’S DATA Rev. 9
7 – 13 – 25
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2.6 Electronic flight bag (EFB) format The EFB is provided only for information and is not intended to replace documents requested by the airworthiness and operational regulations (flight manual, charts, ...).
NOTE
LL
ED
The EFB format (see Fig. 7-13-14) can be used to display various information (books, charts, checklists, and electronic documents). The EFB data base has to be prepared in a dedicated ground tool (Mission Ground Station, MGS) and transferred on board through the Data Transfer Device (DTD). A built-in zoom function facilitates reading of small characters or viewing of details.
VMS
DMAP
MISC
EFB PAGE 1 /44
O
PY
N
O
T
C
O
SECTION 4
+ C T R S –
O
NAVD
N TR
FND
C H A R T
O N
LY
–
C
E C L
S R C T
FO
BKD2_FLH_0227_R
R
IN
ST
R
U
C
TI
O N
N I G H T
+ L U M –
SEARCH
Fig. 7-13-13
LIBRRY
TOC
ROT
VIEW
+ B R T –
PG 1
EFB format (BOOK function) – typical display
Select key
Description
FND
Displays FND format (refer to Para. 7.13.2.1)
NAVD
Displays NAVD format (refer to Para. 7.13.2.3)
VMS
Displays VMS main format (refer to Para. 7.13.2.2).
DMAP
Displays DMAP format (refer to Para. 7.13.2.4)
7 – 13 – 26
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Select key
Description
MISC
Displays MISC format (refer to Para. 7.13.2.5)
BOOK
Selects the books viewer format
CHART
Selects the chart viewer format
ECL
Selects the electronic check list viewer format
SRCT
Selects shortcut function
PG
Display of page number, not selectable
VIEW
Zooms in/out
LL
ED
When the page is zoomed, arrows ( ) will appear to indicate that parts of the page are not visible. The rotary knob can be used to move the page. Rotates the displayed page
NIGHT / DAY
Toggles between night and day mode
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
ROT
MANUFACTURER’S DATA Rev. 9
7 – 13 – 27
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2.7 EFB books viewer The books viewer function allows books (mission books, user manualy, flight manuals) to be displayed on the MFD. The books viewer function uses 2 types of menus: – LIB (library) menu, containing the list of all books available in the data base, divided to 3 subsections (MISSION BOOKS, USER BOOKS, MANUALS). – TOC (Table Of Content) menu, presenting the chapter and sub–chapters for each book available in the data base.
ED
The rotary knob is used for navigation, selection of menu items, and visual manipulations.
1
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
Main menu selection
IN
ST
R
3
FO
R
2
Fig. 7-13-14
Books main menu – typical presentation
Item
Label
Description
1
BOOK
Book format sk
2 3
7 – 13 – 28
Knob for selection and navigation SEARCH LIBRARY TOC
Submenus
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
After selection of a book in the LIB menu, the TOC key opens the table of content of a specific book and allows the selection of chapter within the book. Once chapter is selected, the displayed pages can be rotated (ROT) and zoomed (VIEW).
Book TOC menu – typical presentation
FO
R
IN
ST
R
U
C
TI
O N
Fig. 7-13-15
MANUFACTURER’S DATA Rev. 9
7 – 13 – 29
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2.8 Chart viewer The chart viewer format uses 3 types of menus: – ARPT (airport) menu, containing the list of up to 5 airports available in the data base. The user can select each airport and proceed to the airports stage menu. – Stage menu contains a list of stages, relevant for the selected airport (INFO, STAR, SID, GND, APP, VFR). – Chart menu contains a list of all the charts belong to the selected stage.
ED
The knob is used for navigation, selection of menu items and visual manipulations.
N
O
T
C
O
N TR
O
LL
Main menu selection
U
C
TI
O N
O N
LY
–
C
O
PY
1
IN
ST
R
3
FO
R
2
Fig. 7-13-16
Chart main menu – typical presentation
Item
Label
Description
1
CHART
Chart format sk
2
EDIT
EDIT mode allows searching an airport using ICAO code
3
ARPT STAGE CHART
Submenus
7 – 13 – 30
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Stage selection
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
The stage selection menu provides access to the different charts and the selected airport.
Chart stage menu – typical presentation
FO
R
IN
ST
R
U
C
TI
Fig. 7-13-17
MANUFACTURER’S DATA Rev. 9
7 – 13 – 31
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Chart selection
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Chart selection activates the display of the selected chart. Different tools are then available to rotate (ROT) and zoom (VIEW) the chart.
Display of a chart – typical presentation
FO
R
IN
ST
R
U
C
Fig. 7-13-18
7 – 13 – 32
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2.9 Electronic Check List (ECL) viewer The ECL viewer format allows the user to display Check List (CL) available in the data base. One menu shows a list of all available ECLs. The rotary knob is used to select a CL.
1
2
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Main menu selection
2
R
1
Label
ECL main menu – typical presentation Description
ECL
Check list format sk
PROC
Qiuck access to main menu
FO
Item
IN
ST
R
Fig. 7-13-19
MANUFACTURER’S DATA Rev. 9
7 – 13 – 33
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Electronic CheckList display
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Upon check list selection several check list items are available as well as several pages.
Checklist display – typical presentation
U
CHECKLIST COMPLETED appears in the last page of selected CL
FO
R
IN
ST
R
NOTE
C
TI
Fig. 7-13-20
7 – 13 – 34
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2.10
Shortcut function
The EFB allows the user to quickly select a target page by using shortcuts in a dedicated menu. The shortcut window presents 4 categories of available shortcuts (Books, Charts, ECL and EC), each with up to 7 shortcuts.
1
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
The shortcuts can be created at the MGS or during flight. Shortcuts can be deleted during flight. A history category is available, showing the last 7 pages/charts/CL that were opened. The shortcut menu is available from any format, and is opened by a long press on the SRCT key.
Fig. 7-13-21
Shortcut menu – typical presentation
Item
Label
Description
1
SRCT
Long press: short cut to open menu
MANUFACTURER’S DATA Rev. 9
7 – 13 – 35
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2.11
Search function
The search function gives the capability to search for a word/phrase within the BOOK/AIRPORT format.
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Search capability
O N
LY
1
R
U
C
TI
O N
2
Search function – typical presentation
Label
1
OK
To select the characters
2
SEARCH
To search a word/phrase
7 – 13 – 36
R
Item
FO
IN
ST
Fig. 7-13-22
Description
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.2.12
MFD configuration
After power up, the system automatically displays the default configuration: – MFD1: FND – MFD2: FND – MFD4: VMD
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
In case of failure of one or two MFD(s), the remaining MFD(s) are automatically reconfigured (see Fig.7-13-23 and Fig.7-13-24). The FND format has the highest priority. It is always visible on the remaining screen (except in case of a double failure on MFD 4 and 2 - in this case, the pilot must manually select the FND using the upper select keys or the CCP).
Fig. 7-13-23 MANUFACTURER’S DATA Rev. 9
MFD format reconfiguration – single MFD failure
7 – 13 – 37
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
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LL
ED
DESCRIPTION OF SYSTEMS
MFD format reconfiguration – dual MFD failure
FO
R
IN
Fig. 7-13-24
7 – 13 – 38
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.3
Alerting system The alerting system informs the crew about: – failure or abnormal configuration of aircraft systems – exceedance of operational limitations – exposure to external hazards or threats Alerts are indicated by one or more of the following means: – Warning indications on the warning unit (refer to Para 7.13.3.5) – Master List on the FND (refer to Para 7.13.3.6)
O
– Audio tones and voice messages in the intercom system
LL
ED
– Alert indications on FND and NAVD (see Fig. 7.13.6). Red and amber labels and markings on FND and NAVD are used to indicate failure conditions.
O
N TR
Alerts are categorized as Warning, Caution, and Advisory alerts. In addition, normal events and normal system configurations may be displayed as Information Message.
T
C
7.13.3.1 Warnings
PY
N
O
A Warning (red) indicates a condition which requires immediate crew awareness and immediate crew response.
O
Warnings due to an aircraft system failure or abnormal configuration are indicated by:
C
– Red Warning indication on the warning unit
LY
–
– Red message on the master list (refer to Para. 7.13.6.1. for a complete list of master list warnings)
O N
– Audio tone and voice message
TI
O N
Warnings for exceedance of operational limitations or dangerous operational conditions are indicated by:
C
– Red ROTOR RPM indication on the warning unit
R
U
– Red warning indication on the FND (see Fig. 7-13-25)
FO
R
IN
ST
– Specific audio tones or voice messages (refer to Para 7.13.8 for a complete list of audio tones and voice messages).
MANUFACTURER’S DATA Rev. 9
7 – 13 – 39
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
NAVD
VMS
DMAP
ALT
SAS
SAS
10
10
16
16
1500
15
14
14
13
13
100 80
10
10
20
20
3
VY 600 DA
OBSTACLE
N
33
3
6
30
E
T
C
W
FSD
O
354 1.0 FMS
LY
_
–
C
GPS
LFMH 20.0 NM 12 _min
SCT
_ _ _ SVS
OAT
A C K
47 Kg 25
+ B R G –
O N
O N
DCPL
LOW
Examples of red warning indications on the FND
IN
R
7.13.3.2 Cautions
ST
R
U
C
Fig. 7-13-25
TI
BKD2_FLH_0476_R
+ L U M –
S
PY
DTK
15
N
21
O
12
24
N A V
1013 200 hPa DH
B A R O
O
6
D H
ED
17
LL
20
D A
N TR
7
20
17
O
18
120
OEI
+ C T R S –
CLOCK
AFCS DISENGAGED
101 8 _
MISC
FO
A Caution (amber) indicates a condition which requires immediate crew awareness and not immediate but subsequent crew response. Cautions due to an aircraft system failure or abnormal configuration are indicated by: – Amber message on the master list (refer to Para 7.13.6.2 for a complete list of all cautions) – Generic audio tone Cautions for use of cautionary ranges, malfunctions, or hazardous operational conditions are indicated by: – Amber alert indications on the FND. – Specific audio tones and voice messages (refer to Para 7.13.7 for a complete list of audio tones and voice messages).
7 – 13 – 40
MANUFACTURER’S DATA Rev. 9
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_
NAVD
VMS
DMAP
ALT
SAS
10
10
16
16
1 500
15
14
14
13
13
10
20
20
3
VY
1600 1013 200 DA hPa DH
3
6
W
_
_
FSD
O
354 1.0 FMS
– LY
SVS
25
+ B R G –
O N
O N
SCT
415 Kg OAT
A C K
TI
BKD2_FLH_0475_R
20.0 NM 12 min
DCPL
LOW
C
GPS
LFMH + L U M –
15
N
S
PY
DTK
21
O
12
24
N A V
E
T
_
_ _
C
30
GPS
N TR
HTAWS TERRAIN FAIL N MAG DEGR 33
B A R O
O
2
10
D H
ED
20
D A
LL
20
100 80
17
17
O
18
120
4
SAS
+ C T R S –
CLOCK
AFCS DISENGAGED
101 6
MISC
Examples of amber caution indications on the FND
R
U
C
Fig. 7-13-26
IN
ST
7.13.3.3 White advisories
FO
R
An advisory alert (white) indicates a condition which requires crew awareness and may require monitoring by the crew. A crew response is not required. In some cases, maintenance may be necessary before further flights are possible. White advisories are indicated by: – White message on the master list (refer to Para 7.13.6.3 for a complete list of all advisory alerts)
7.13.3.4 Information messages An information message indicates normal operation (e.g. an ongoing or successful test), or a particular but normal system configuration. Information messages are indicated by: – Green message on the master list (refer to Para 7.13.6.4 for a complete list of all information messages) MANUFACTURER’S DATA Rev. 9
7 – 13 – 41
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.3.5 Warning unit The warning unit, centrally located on the instrument panel, displays most all warning indications (see Fig. 7-13-27), as well as The warning unit is mostly independent of Helionix and remains operational in case of a complete Helionix failure. The engine shut off valves and fire extinguishing system are also operated through the warning unit. For details concerning the fire indication and extinguishing system, refer to Para 7.5.6.3). 2
3
4
5
6
5
4
3
2
1
11
9
8
7
Warning unit – typical installation
PY
N
Fig. 7-13-27
10
C
12
T
8
O
7
O
N TR
O
LL
ED
1
EXT indicates activation of fire extinguisher bottle discharge (system 1/2)
2
FIRE warning light / EMER OFF sw (system 1/2)
3
EMER OFF sw indication (system 1/2)
4
LOW FUEL warning (supply tank 1/2)
5
ENG 1/2 FAIL warning (respective N1 below threshold value)
6
ROTOR RPM warning (NR too low or too high)
7
BOT1/2 pb indicates availability of fire extinguisher bottle / activates resp. bottle
8
ACTIVE indicates EMER OFF sw position
9
CARGO SMOKE warning (optional)
10
AP warning (autopilot)
11
MGB OIL P warning (main gearbox oil pressure below minimum)
12
BAT OVHT warning (battery overtemperature)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
1
7.13.3.6 Master List The messages on the master list are displayed sorted from top to bottom according to their category, with Warnings on top, followed by Cautions, Advisories alerts, and Information messages at the bottom. Within each category, the messages are sorted according to their priority. The Master List displays a maximum of 7 messages at the same time. If more messages are present, a scroll bar appears at the right side of the master list. The crew can scroll down the list of messages by turning the rotary knob of the MFD. If required, the last messages can be recalled on the master list by pushing and holding the ACK key on the FND. When the key is released, the master list returns to the current display. This function allows the crew to check a message that disappeared before it could be read.
7 – 13 – 42
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
New Warning, Caution and Advisory alert messages are accompanied by visual indications, audio tones and/or voice messages to attract the crew’s attention: – Unacknowledged Warning, Caution and Advisory alert messages in the master list are highlighted (FIg. 7-13-28). – The master list area is marked by a blinking frame in the same color as the new message. If several unacknowledged messages are present, the blinking frame has the same color as the highest ranking message. – The associated audio tone and/or voice message is played via intercom.
ED
The crew acknowledges new messages either by pushing the RESET button on the cyclic stick grip or the ACK key on the FND.
O
LL
An acknowledged message in the master list is displayed on black background in red, amber or white letters (Fig. 7-13-28).
LY
Indication of messages in the master list (left: unacknowledged right: acknowledged)
O N
Fig. 7-13-28
–
C
O
PY
N
O
T
C
O
N TR
Information messages do not require acknowledgement and are always displayed on black background in green letters (exception: TRAINING).
O N
Alerts and messages in the master list may be concatenated or suppressed in some cases:
FO
R
IN
ST
R
U
C
TI
– Concatenation: A typical concatenation is to combine the same alert for two systems into one. Other concatenations are the indication of fixed and S/L light into a single message.
– Suppression: Alerts or messages may be suppressed when they are considered irrelevant (e.g. some alerts on ground) or when they are superseded by a more important causal alert (e.g. suppression of low engine oil pressure when ENG1 FAIL is present).
MANUFACTURER’S DATA Rev. 9
7 – 13 – 43
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.4
Flight data monitoring and automatic sensor reconfiguration
7.13.4.1 General Flight data monitoring generally describes the process of acquiring, monitoring, and providing of flight data. Data are obtained from two ADCs, three AHRS, two magnetometers, one IESI, various radio navigation equipment, and two flight management systems. Flight data are acquired, processed, and monitored in the AMCs and displayed on the MFDs. All critical flight data are subject to continuous monitoring and are automatically reconfigurated if failures are identified.
LL
ED
7.13.4.2 Data monitoring
T
C
– IESI (ATT and AIR data)
O
– AHRS1, AHRS2, and AHRS3 (ATT data and HDG data)
N TR
O
To ensure that the pilot and AFCS are continuously provided with the best possible data, various flight data are acquired by redundant or complementary sensors and then provided to the AMCs:
O
– ADU1 and ADU2 (AIR data)
PY
N
– Radio altimeter (RA data)
O
– GPS/FMS (FMS data)
O N
LY
–
C
Each AMC channel monitors sensor data from all available sources to detect discrepancies and locate erroneous flight data. Each parameter is labeled with a respective monitoring result:
O N
– Normal operation:
R
U
– Localized failure
C
TI
The parameter is considered reliable. It is available to be displayed to the crew and will be used by the AFCS. If desired, the pilot can manually de-select the source.
FO
R
IN
ST
The parameter is recognized as having failed or being erroneous and is therefore considered invalid. The detection of erroneous signals is done by comparing redundant parameters (e.g. AHRS and IESI data) or by monitoring the rate of deviation of complementary parameters (e.g. pressure altitude and GPS height). If a parameter is invalid, it is automatically de–selected and cannot be manually re-selected. On the MFDs, the indication will be automatically replaced by a redundant source (if available). Any failure of an indicated source will also generate a master list alert (e.g. ATT1 FAIL, AIR1 DATA FAIL, IESI AIR DATA). Failure of a non-indicated source will only be shown during the start-up phase (e.g. ATT REDUNDANCY in case of AHRS3 failure). Parameters which were recognized as failed or erroneous will continue to be monitored. Should the parameter become reliable again, it will automatically be re-used and the master list alert will disappear.
7 – 13 – 44
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
– Non–localized failure: In some cases, Helionix may detect a difference between parameters without being able to determine which parameter is erroneous. This is particularly the case when only two sources are available (e.g. airspeed) , but can also happen when a source is read by two different AMCs. . In this case, the pilot will be informed that a discrepancy exists by a discrepancy indication (´) near the instrument (Fig. 7-13-29).
ED
In case of a discrepancy between sensors, the pilot must determine which source is correct (e.g. by using additional sources like the standby compass or track/groundspeed) and manually de-select the erroneous source. Once a sensor source is de-selected, Helionix considers it invalid and treats it like a localized failure.
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
Any manually de-selected source can be re-selected by the pilot.
Discrepancy indication (airspeed indication)
C
TI
Fig. 7-13-29
FO
R
IN
ST
R
U
In case of total failure of all sensors, the parameters will be displayed in amber on the FND (Fig. 7-13-30).
Fig. 7-13-30 MANUFACTURER’S DATA Rev. 9
Indication of a total loss of all air data sensors
7 – 13 – 45
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.4.3 Data source display The MFDs use the monitoring result to determine which information is to be displayed. If all sensors provide valid data, MFD1 (copilot s side) will display data from the ATT1/AIR1/HDG1 sensors and MFD2 and MFD4 (pilot’s side) will display data from ATT2/AIR2/HDG2 sensors. Normally, flight management and GPS data from FMS2 are displayed on all MFDs. Since only one radar altimeter is installed, it is indicated on all displays.
Sensor sources used on each MFD indicated on the RCNF page
C
O
Fig. 7-13-31
PY
N
O
T
C
O
N TR
O
LL
ED
The top part of the RCNF subpage (accessible through the RCNF key on the VMS page) visualizes which sensor sources are indicated on each MFD (Fig. 7-13-31).
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
In case a non-standard sensor is indicated on an MFD (following automatic reconfiguration or manual de-selection), the indicated sensor will be shown and the failed sensor will be shown in amber (Fig. 7-13-32). When a sensor has failed completely and re-configuration is not possible, the sensor is shown in amber (Fig. 7-13-32).
Fig. 7-13-32
7 – 13 – 46
Sensor sources used following an attitude sensor (IESI replaces ATT1 and ATT2) and a radar altimeter failure (RA shown as failed).
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.4.4 Sensor status display and manual re-configuration
N
Sensor status indication on the RCNF page.
PY
Fig. 7-13-33
O
T
C
O
N TR
O
LL
ED
The lower part of the RCNF page indicates the status of all sensors sources (except AHRS3 and FMS). In addition to the sensor status, the page also shows key parameters to provide the pilot with a direct means of comparison (Fig. 7-13-33). The possible sensor status indications are shown in Table 7-13-1.
Functional status
–
Normal operation.
C
O
Indication
O N
LY
Sensor is fully operational. The sensor can be manually de-selected by the pilot.
O N
Non-localized failure.
U
C
TI
The sensor is operational, but an unresolved discrepancy with another sensor is detected. The crew should manually de-select the erroneous sensor.
FO
R
IN
ST
R
Localized failure. The sensor has failed. The sensor cannot be selected. Deselected. The sensor is operational, but currently deselected. The de-selection may be the result of an automatic or manual de-selection. Heading degraded. The magnetic heading was recognized as degraded. Refer to Section 3 for the emergency procedure. Heading in DG mode. The magnetic heading is in DG mode. Refer to Section 4 for the DG/MG selection procedure.
Table 7-13-1 MANUFACTURER’S DATA Rev. 9
Sensor status indications on the RCNF page
7 – 13 – 47
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Sensors can be manually (de)-selected using the sensor status area of the RCNF page. To manually de-select a sensor source, proceed as follows: 1. VMS/RCNF page
– Select
2. RCNF key
– Push – DESEL/SEL LSK label appears and blue brackets around ATT1 are shown (Fig. 7-13-34). – Rotate to select sensor
4. DESEL key
– Push to deselect sensor
ED
3. Rotary knob
as
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
– Sensor is indicated deselected (grey)
Manual sensor de-selection
U
C
TI
Fig. 7-13-34
ST
R
To reselect a de-selected sensor, proceed in a similar manner: – Select
2. RCNF key
– Push
FO
R
IN
1. VMS/RCNF page
– DESEL/SEL LSK label appears and blue brackets around ATT1 are shown (Fig. 7-13-34).
3. Rotary knob
– Rotate to select sensor
4. SEL key
– Push to select sensor – Sensor is indicated as valid (white)
NOTE
7 – 13 – 48
Do not use manual (de)-selection when the alternate static pressure source is selected or de-selected. In this case, use the emergency procedure detailed in Section 3.3.5.5. MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.5
Vehicle management The vehicle management function acquires and processes all information allowing engine and vehicle parameters indication, monitoring, and control. Each AMC acquires data from vehicle and engine sensors in the VMS partitions and sends data to the MFDs for display of vehicle and engine information. Checks are performed at different stages to detect errors in data acquisition and processing. Most vehicle and engine information is displayed on the VMS format. Some vehicle parameters (e.g. FLI and NR/N2 indicator, fuel quantity) are shown on the FND display. The VMS function also triggers the vehicle related master list alerts.
LL
ED
The vehicle management function processes the following parameters:
O
Vehicle parameters:
N TR
– Helicopter total weight – VNE computation
T
C
O
– Electrical power parameters (DC bus voltage, generator current, battery current) and status
N
O
– Fire detection system status, fire protection system and test status
PY
– Fuel system parameters (tank quantities, fuel flow, remaining flight time) and status, auxiliary fuel transfer control
C
O
– Hydraulic system parameters (hydraulic pressure) and status
–
– Flight/ground state
O N
LY
– Main and tail rotor parameters (rotor speed, mast moment, cyclic stick/collective lever position, rotor brake)
TI
C
– Doors status
O N
– Main gearbox parameters (oil pressure, oil temperature) and status, tail gearbox status
U
– Pitot and static heater status
ST
R
– External lighting status (landing light, search and landing light, search light)
IN
– Environmental control system status
R
– Hoist parameters (reeled cable length) and status
FO
– Cargo hook weight and status – Emergency floatation system status – LAVCS status Engine parameters: The vehicle management function communicates with the FADEC and processes and controls the following parameters: – Engine main parameters incl. limits (torque, gas generator temperature, gas generator speed, power turbine speed) and status – First limit indicator (FLI) computation – Engine oil system parameters (oil pressure, oil temperature) and status – Engine air inlet filter (IBF) parameters and status
MANUFACTURER’S DATA Rev. 9
7 – 13 – 49
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
– Engine control system parameters and status – Overspeed protection system status – Engine / FADEC control (computation of NR target speed, control of training mode, ultimate backup control, engine start inhibition, IBF bypass door control) 7.13.5.1 VMS textual pages The following VMS textual pages are available to the crew: – System status page – Configuration page
ED
– Weight and performance computation page
LL
– Flight report pages (refer to Para. 7.17.1)
O
– Engine power check (refer to Sect. 5)
O
N TR
These pages are displayed after pressing the respective BSK on the VMS main format (see Fig. 7-13-35).
PY
N
O
T
C
P R E V
V A L
LY O N
REPORT
EPC
STATUS
CONF
WEIGHT
+ B R T –
R
U
C
TI
MAIN
O N
+ L U M –
ST
BKD2_FLH_0232_R
–
C
O
N X T
A B R T
Navigation in VMS textual pages
NXT
FO
Select key
R
IN
Fig. 7-13-35
Description Scrolls to next page
PREV
Scrolls to previous page
ABRT
Stops and resets current process
VAL
Validates change
Rotary knob / push button
Rotation changes data
WEIGHT
Displays weight page
CONF
Displays configuration page
STATUS
Displays system status page
EPC
Displays engine power check page
7 – 13 – 50
Push moves to next line if select active
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Select key
Description
REPORT
Displays flight report page
MAIN
Displays VMS main page System status page:
C
1 – 2 1 0 1 0 1
A 1 . . . . . .
D E C 2 3 h P a 0 C 0 % 0 % 0 % 0 C 5 %
ED
0 1 L P 2 D A T U M L T E M P M
F 0 2 0 1 1 5 0
LL
S T A T U S
System status page – typical display
O
Fig. 7-13-36
C
O
5 . 0
S Y S T E M P T C N N 2 F U E M
O
1 h P a C % %
N TR
F A D E C 1 0 1 3 – 2 2 . 0 0 . 0 1 0 1 . 0
T
BKD2_FLH_0233_R
The system status page (see Fig. 7-13-36) is displayed by pressing STATUS. It is normally used for maintenance tasks only.
PY
N
The system status page presents the following data in digital format:
C
O
– P0 and T1: Engine entry pressure and temperature measured by the respective engine FADECs.
LY
–
– CLP (collective pitch position): Collective pitch position used by the respective engine FADECs.
O N
– N2: Engine power turbine speed measured by the respective engine FADECs.
TI
O N
– N2 DATUM: Target power turbine speed target set by Helionix
R
IN
ST
R
U
C
– Fuel temperature: The fuel temperature is normally obtained obtained from the optional fuel flow sensor (if installed). Otherwise the fuel temperature is obtained from the FADECs. The FADEC measured fuel temperature is not representative of the fuel tank temperature, but is the temperarture of the fuel after it has passed through the engine fuel heater.
FO
– Mast moment: Digital value of the current mast moment. Used for maintenance purposes.
MANUFACTURER’S DATA Rev. 9
7 – 13 – 51
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Configuration system page: The configuration system page (see Fig. 7-13-37) is displayed by pressing CONF. The page allows configuring installed equipment. It is only available on ground.
X E G I R S
I L I S G T
L I F N E T O M O
A R Y F U E L T A N K L OW S E N S O R I N L E T F I L T E R H O O K M E N T
I N S T A I N S T A I . I N S T A W I T H WE C I R C
D O U B L E S Y S T E M
L L B L I U
L L . L G L
E E F E H A
D D . D T R
ED
U U N O A A
S Y S T E M
Fig. 7-13-37
O
LL
A F E H C M
–
Configuration system page – typical display
N TR
BKD2_FLH_0234_R
C O N F I G U R A T I O N
Configurations
Impacted parameter
AUXILIARY FUEL TANK
INSTALLED NOT INSTALLED
Indication of auxiliary fuel tank.
FUEL FLOW SENSOR
INSTALLED NOT INSTALLED
ENGINE INLET FILTER
NOT INSTALLED I.B.F.
HOIST
INSTALLED NOT INSTALLED
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
Option
U R ST IN R FO
MAST MOMENT SYSTEM
Indication of IBF clogging and IBF alerts, as well as automatic opening of the IBF in emergencies. Hoist cable length indication and hoist UMS functions.
NOT INSTALLED HOOK W/O WEIGHT SINGLE W/O WEIGHT SINGLE WITH WEIGHT DOUBLE W/O WEIGHT DOUBLE WITH WEIGHT
Indication of cargo hook information and associated master list alerts.
LINEAR CIRCULAR
Indication of the mast moment on the FND.
C
CARGO HOOK
Indication of fuel flow and endurance, as well as the fuel temperature on the STATUS page.
Pressing the rotary knob activates the selection mode. To change the selected line, the rotary knob has to be pressed again until the desired line is selected. To modify the selected item, the rotary knob has to be turned until the desired configuration is displayed. To save a modified configuration, VAL has to be pressed before leaving the configuration system page. Pressing ABORT or leaving the page without pressing VAL will cancel the modification. If the configuration system page has never been accessed and modified, all the items are set to NOT INSTALLED.
7 – 13 – 52
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Configuration units page: The configuration system page (see Fig. 7-13-38) is displayed by pressing NXT on the system configuration page.
T I E M B
/ G L P L
L O N G H T
D e g
E R A T U R E E L E N G T H
mm . mmm ” K g L i t e r C M e t e r
ED
A E U E A
U N I T S
O
LL
L W F T C
–
Configuration units page – typical display
N TR
Fig. 7-13-38
O
BKD2_FLH_0235_R
C O N F I G U R A T I O N
Unit choice for display
LAT/LONG
Deg_mm.mmm’
WEIGHT
Kg Lb
FUEL
Liter US Gallon IMP Gallon Weight (Kg / Lb)
Fuel indication Fuel flow
_C _F
OAT Fuel temperature
m ft
Hoist cable length (only available if hoist is configured)
O N
O N
LY
–
C
O
PY
N
O
T
C
Unit
R
Latitude / longitude on NAVD page Hook load Fuel (if option “WEIGHT UNIT selected) Total weight
R
IN
ST
CABLE LENGTH
U
C
TI
TEMPERATURE
Impacted parameter
FO
NOTE D The barometric pressure unit (hPa or inHg) cannot be configured by the crew. To configure the pressure unit, a new Helionix configuration file must be generated and installed. D T1 will always be indicated in _C. Pressing the rotary knob activates the selection mode. To change the selected line, the rotary knob has to be pressed again until the desired line is selected. To modify the selected item, the rotary knob has to be turned until the desired configuration is displayed. To save a modified configuration, VAL has to be pressed before leaving the configuration unit page. Pressing ABORT or leaving the page without pressing VAL will cancel the modification.
MANUFACTURER’S DATA Rev. 9
7 – 13 – 53
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Weight page:
Y E P R
T O T A L
2 1 1 6 7
F U E L
5 6 0 0
0 0 0 0
7 0 0
K K K K
G G G G
K G
ED
A R M A
W E I G H T C OM P U T A T I O N L O A D W T Y E Q U I P P E D G O H O O K
T O T A L
3 4 1 0
Weight page – typical display
K G
N TR
Fig. 7-13-39
LL
1/2 P C E C
O
BKD2_FLH_0236_R
The weight page (see Fig. 7-13-39) is automatically displayed at power-up, or by pressing WEIGHT.
PY
N
O
T
C
O
Pressing the rotary knob activates the selection mode. To change the selected line, the rotary knob has to be pressed again until the desired line is selected. To modify the selected item, the rotary knob has to be turned until the desired configuration is displayed. Rotating the external rotator modifies the weight in steps of 100 kg / 200 lbs, the internal rotator in steps of 5 kg / 10 lbs.
LY
–
C
O
When a weight on the page was manually modified, the VAL key will appear. To save a modified weight, VAL has to be pressed before leaving the weight page. Leaving the page without pressing VAL will cancel the modification.
O N
TOTAL FUEL value is provided by the fuel gauging system.
O N
PAYLOAD, CREW and EMPTY EQUIPPED should be entered manually. Values must be within the following ranges:
R
U
C
TI
– PAYLOAD: 0–2100 kg / 0–4700 lbs
IN
ST
– CREW: 50–1100 kg / 100–2400 lbs
FO
R
– EMPTY EQUIPPED: 1500–3200 kg / 3300–7000 lbs On power-up, the default value for PAYLOAD is calculated as: PAYLOAD = MTOW – (EMPTY EQUIPPED) – (CREW) – (TOTAL FUEL) – (CARGO HOOK) For EMPTY EQUIPPED, CREW and CARGO HOOK, the values displayed at power-up are the stored values from the previous flight. If an optional cargo hook is configured in the configuration system page the CARGO HOOK load can be entered manually. The value must be within the range of 0–1500 kg / 0–3300 lbs. If no cargo hook is configured, the load is automatically set to 0. If the fuel gauging system is invalid, the last valid value is used for calculation. This value is displayed in amber reverse video as TOTAL FUEL value, and the TOTAL weight calculated is displayed in amber inverse video (see Fig. 7-13-40).
7 – 13 – 54
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
BKD2_FLH_0237_R
W E I G H T C OM P U T A T I O N 1/2 P A Y L O A D C R E W E M P T Y E Q U I P P E D
T O T A L
2 5 0 1 6 0 1 6 0 0
F U E L
T O T A L
G G G G
7 0 0
K G
2 7 1 0
K G
Weight page – fuel system invalid – typical display
ED
Fig. 7-13-40
K K K K
O
C
T
Y E P R
O
A R M A
2 1 1 6 1 1
5 6 0 0
0 0 0 0
K K K K
G G G G
N
P C E C
W E I G H T C OM P U T A T I O N L O A D W T Y E Q U I P P E D G O H O O K
PY
F U E L
O
T O T A L
K G
3 8 1 0
K G
Weight page – total weight exceeds max. certified weight – typical display
LY
Fig. 7-13-41
C
T O T A L
7 0 0
–
BKD2_FLH_0238_R
1/2
N TR
O
LL
If the TOTAL weight calculated is above the maximum certified weight or below the minimum certified weight, then the WEIGHT value is displayed in amber inverse video (see Fig. 7-13-41).
O N
Performance computation page:
FO
R
IN
ST
R
U
C
TI
O N
From the WEIGHT sub–page, the performance computation page (Fig. 7-13-42) can be accessed by pressing NXT.
Fig. 7-13-42
Performance computation page
The computation performance page provides direct access to the performance charts within Helionix. It also allows defining a weight penalty for the performance charts. Access to the input values is through the rotary button (similar as for the weight page). Pressing the rotary button scrolls through the input fields; rotating the button allows the values to be modified. When heating, altitude, or OAT data are changed, the destination performance is automatically updated. A weight penalty, however, must be validated using the VAL key. MANUFACTURER’S DATA Rev. 9
7 – 13 – 55
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
– PENALTY: Allows a fixed weight penalty (between 0 and 400 kg) to be defined for the performance calculations. This weight penalty is to be used when external equipment is installed which reduces the performance in hover or Cat A VTOL. Any weight penalty also applies to the charts displayed in the VMS data field. The penalty must be validated using the VAL key. – HEATING: Set the heating status (ON or OFF) for calculation of the destination performance. – ALT: Set the destination altitude (currently limited to 0–16000 ft).
O
LL
ED
– OAT: Set the destination OAT (limited to –45_C / +50_C).
N TR
NOTE D IBF performance data are automatically used when an IBF is configured.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
D If data cannot be calculated (e.g. because the entered parameters are outside of the certified envelope), NO DATA will be indicated.
7 – 13 – 56
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.6
Master list messages
7.13.6.1 List of warning messages AFCS ML message AUTOPILOT
Description
Refer to
Disengagement or failure of both autopilot modules.
Section 3
Excessive battery temperature detected.
N TR
BAT OVERHEAT
Refer to Section 3
T
C
O
ENGINE Description
N
O
ML message
Respective N1 below threshold value (45%).
and/or FAIL
–
ENG2
Section 3
O
PY
FAIL
Refer to
C
ENG1
LL
Description
O
ML message
ED
ELECTRICS
O N
ML message
O N
LY
FIRE
C
TI
CARGO SMOKE FIRE
R
U
ENG1
IN
ST
or FIRE
Description
Refer to
Smoke detected in cargo compartment (optional).
Section 3
Very high temperature in engine compartment detected.
Section 3
Description
Refer to
ENG2
FO
R
FUEL
FUEL1
ML message LOW and/or LOW
FUEL2
Respective supply tank fuel quantity Section 3 below threshold value (approx 26 kg).
GEARBOX AND DRIVE SYSTEM ML message MGB LOW PRESS
MANUFACTURER’S DATA Rev. 9
Description
Refer to
Main gearbox oil pressure below minimum (1 bar).
Section 3
7 – 13 – 57
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.6.2 List of caution messages AFCS Description
Refer to
AP ACTUATOR
Failure of one or autopilot series actuator(s).
Section 3
AP CONTROL
Failure or partial failure of the autopilot control panel or of the autopilot function switches on the cyclic or collective grips.
Section 3
Section 3
N TR
O
LL
Loss of one AP due to internal failure detection.
AP REDUNDANCY
ED
ML message
Failure of an autopilot trim actuator.
Section 3
BACKUP SAS
Failure of back-up SAS.
Section 3
T
C
O
AP TRIM OFF
Air data failure detected on ADC1 and/or ADC2.
R
ST FAIL or FAIL
–
Section 3
Complete loss of respective AMC (channel A and B).
Section 3
Failure of AHRS1 and/or AHRS2.
Section 3
Failure of the audio alerting function.
Section 3
Some ML messages and/or VMS parameters may be missing.
Section 4 Power-up test
AMC2
FAIL and/or FAIL AUDIO ALERT VMS/UMS SIGNAL
7 – 13 – 58
Failure of corresponding AMC channel.
AMC2
IN R FO
ATT1
Section 3
O N O N TI
C
CHAN B FAIL
or CHAN B FAIL AMC1
Failure of corresponding AMC channel.
AMC2
U
AMC1
AIR2
CHAN A FAIL or CHAN A FAIL
Section 3
C
O
DATA FAIL and/or DATA FAIL
AMC1
Refer to
LY
AIR1
Description
PY
ML message
N
O
AVIONICS AND DISPLAYS
ATT2
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
CLIMATE CONTROL AND ICING PROTECTION ML message
Description
Refer to
AVIONICS OVHT
High avionics deck temperature detected.
Section 3
HEATING FAIL
Bleed air mixing valve open with HEATING OFF
Section 3
Mixing valve inlet or outlet temperature exceeds limit.
Section 3
ED
HEATING OVERTEMP
Normal operating temperature of MFD exceeded.
Section 3
PItot tube heater failed.
and/or HEATER FAIL
N TR
HEATER FAIL PITOT2
C
PItot tube and/or static port heater are not switched on.
and/or HEATER OFF
PITOT2
O
Static port heating system failed.
STAT HTR FAIL
C
PITOT1
Section 3
–
and/or STAT HTR FAIL
Section 3
N
O
T
HEATER OFF
PY
PITOT1
Section 3
O
PITOT1
O
LL
MFD OVERHEAT
O N
LY
PITOT2
O N
DOORS
C
TI
ML message
IN
ST
R
U
DOOR OPEN
FO
R
EPU DOOR
Description
Refer to
Cockpit door, cabin sliding door or cabin clamshell door not properly locked.
Section 3
External power receptacle access door is open and EPU is not connected to the power distribution system.
Section 3
Description
Refer to
Battery is the only electrical power source and is discharging.
Section 3
Battery is off-line.
Section 3
DC parameters are outside normal operating range.
Section 3
ELECTRICS ML message BAT DISCHARGING BAT DISCONN ELEC OVERLIMIT
MANUFACTURER’S DATA Rev. 9
7 – 13 – 59
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
EPU CONNECTED DISCONNECTED and/or DISCONNECTED GEN1
GEN2
OVERHEAT and/or OVERHEAT
EMER SHD BUS switch is switched to ON.
Section 3
External power is applied to the electrical distribution system.
Section 3
Respective generator failed or disconnected from the power distribution system.
Section 3
Temperature of generator excessively high.
Section 3
GEN2
N TR
O
GEN1
Refer to
ED
EMER SHED BUS ON
Description
LL
ML message
Standby battery (emergency power supply unit) is discharging.
Section 3
C
O
STBY BAT DISCH
Failure of the standby battery (emergency power supply unit) detected during activation of the STBY BAT sw.
BUS TIE OPEN
Electrical systems are separated (load sharing impossible).
Section 3
C
–
and/or BUS TIE OPEN
Section 3
O N
SYS2
LY
SYS1
O
PY
N
O
T
STBY BAT FAIL
C
TI
O N
ENGINE
R
U
ML message CHIP
ST
ENG1
ENG1
FADEC EMER or FADEC EMER
ENG1
ENG1
7 – 13 – 60
Section 3
FADEC EMER (ultimate backup) mode selected.
Section 3
Engine fuel filter contaminated.
Section 3
Fuel valve in closed position.
Section 3
ENG2
FUEL VALVE CLSD and/or FUEL VALVE CLSD
Metal particles detected in the engine oil.
ENG2
FUEL FILTER and/or FUEL FILTER
Refer to
ENG2
FO
R
IN
or CHIP
Description
ENG2
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ML message ENG1
FUEL VALVE POS and/or FUEL VALVE POS
ENG1
and/or IDLE
Section 3
Engine oil filter contaminated.
Section 3
LL O
High pressure in engine oil system.
N TR
T
C
ENG2
High temperature in engine oil system.
O
OIL HIGH TEMP
Engine oil pressure or temperature outside the normal range, or engine oil temperature t0_C.
Section 3
Engine overspeed detected.
Section 3
Starter active, starter energize time limit exceeded.
Section 3
Engine 1 and 2 limitations were exceeded. Engine maintenance is required.
Section 3
FADEC DEGRADED indicates a change of governing functions.
Section 3
C
Section 3
LY
O N
O N
ENG2
ENG2
U
C
TI
Affected engine oil pressure below minimum.
–
or OIL LOW PRESS
and/or OIL OVERLIMIT
PY O
ENG2
OIL LOW PRESS
OIL OVERLIMIT
Section 3
N
or OIL HIGH TEMP
Section 3
O
or OIL HIGH PRESS
ENG1
Engine in IDLE.
ENG2
OIL HIGH PRESS
ENG1
Section 3
ED
and/or OIL FILTER
ENG1
Fuel valve in a position other than commanded.
ENG2
OIL FILTER
ENG1
Refer to
ENG2
IDLE
ENG1
Description
OVERSPEED
R
ENG1
FO
ENG1
R
IN
ST
or OVERSPEED
ENG1
STARTER ON and/or STARTER ON
ENG2
USAGE EXPIRED and/or USAGE EXPIRED
FADEC1
ENG2
ENG2
DEGRADED and/or DEGRADED
MANUFACTURER’S DATA Rev. 9
FADEC2
7 – 13 – 61
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ML message
Automatic engine control failed, fuel Section 3 metering valve is blocked.
FAIL and/or FAIL
FADEC1
Refer to
FADEC2
N2 DISAGREE and/or N2 DISAGREE
Respective FADEC N2 differs from the N2 commanded by Helionix.
Section 3
Training mode aborted automatically.
Section 3 FMS 9.1-3
FADEC2
LL
TRAINING ABORTED
ED
FADEC1
Description
ML message
N TR
O
FIRE Description
O
Respective fire extinguisher bottle(s) not available or discharged.
C
FIRE BOT 1 USED
Section 3 Section 4 Fire Protection Test
C
O
PY
N
O
T
or FIRE BOT 2 USED or FIRE BOT 1+2 USED
Refer to
LY
–
FUEL AND WEIGHT
Description Aft fuel transfer pump failed or switched off.
Section 3
Aft and forward fuel pumps failed or switched off.
Section 3
FUEL QTY DEG
Failure of one main tank sensor.
Section 3
FUEL QTY FAIL
Failure of fuel quantity indication system (both main sensors or one supply sensor).
Section 3
Fuel level in supply tank(s) below threshold or both transfer pumps running dry (main tank empty).
Section 3
Engine fuel pump inlet pressure low.
Section 3
Prime pump(s) switched on.
Section 3
O N
AFT FUEL PUMP
FO
R
IN
ST
R
U
C
TI
AFT+FWD FUEL PMP
FUEL RESERVE
FUEL1
PRESSURE and/or PRESSURE
FUEL1
FUEL2
PRIME PUMP ON and/or PRIME PUMP ON
7 – 13 – 62
Refer to
O N
ML message
FUEL2
MANUFACTURER’S DATA Rev. 10
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ML message
Description
Refer to
FWD FUEL PUMP
Forward fuel transfer pump failed or switched off.
Section 3
JET FUEL PUMP
Aft main tank jet pump not capable of transfering fuel to forward main tank.
Section 3
After Helionix Maintenance Release 1
EFFECTIVITY
The indicated aircraft weight exceeds the maximum takeoff weight.
Section 3
O
LL
ED
WEIGHT EXCEEDED
N TR
All
EFFECTIVITY
Description
T
ML message
C
O
GEARBOX AND DRIVE SYSTEM
O
Metal particles detected in the main gearbox oil.
Section 3
PY
N
MGB CHIP
Refer to
Main gearbox oil temperature above Section 3 maximum.
–
C
O
MGB HIGH TEMP
O N
LY
MGB OVERLIMIT
TI
O N
MM EXCEEDED
U
C
ROTOR BRAKE
Section 3
Mast moment exceeded 79%.
Section 3
Rotor brake engaged.
Section 3
Metal particles detected in the tail rotor gearbox oil.
Section 3
Description
Refer to
Pressure loss in the affected system, the normal system retains power.
Section 3
Hydraulic pressure out of normal range.
Section 3
Tail rotor hydraulic shut-off valve (SYS 1) has activated. Hydraulic system 1 no longer pressurizes the tail rotor (Fenestron) actuator.
Section 3
IN
ST
R
TGB CHIP
Main gearbox temperature or pressure outside of the normal operating range.
FO
R
HYDRAULICS
HYD1
ML message LOW PRESS or LOW PRESS HYD OVERLIMIT
HYD1
TR SHUT OFF
MANUFACTURER’S DATA Rev. 9
HYD2
7 – 13 – 63
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
OPTIONALS Description
Refer to
AUX FUEL XFR
Aux fuel transfer inoperative.
FMS 9.2–33
CARGO HOOK OFF
A load is attached to the cargo hook, but the electrical hook release is not armed.
FMS 9.2–6
EOS LASER ARMED
The EOS laser is armed.
FMS 9.2–29
The HISL laser is on.
FMS 9.2–14
HISL LASER ON
O
O
Respective IBF bypass door is not in fully opened or fully closed position.
O
BYPASS FAIL
N
Respective IBF maximum allowed clogging level is exceeded
C
CLOGGED
IBF1
INCORRECT CONFIG
IBF2
IBF1
PRESS SENSOR
LY
O N
Section 4 Power-up test FMS 9.2-5
Respective IBF pressure sensor failed.
FMS 9.2-5
The electrical inverter has failed.
FMS 9.2–30
TI
O N
Incorrect IBF configuration.
C U
R
ST
IN
and/or PRESS SENSOR
R
FMS 9.2-5
–
IBF2
INVERTER FAIL
FO
FMS 9.2-5
PY
O
IBF2
and/or CLOGGED
7 – 13 – 64
FMS 9.2-5
C T
IBF2
and/or BYPASS FAIL IBF1
Respective IBF bypass door closed via the IBF sw. Automatic opening in case of OEI is inhibited.
N TR
BYPASS CLOSED and/or BYPASS CLOSED
IBF1
FMS 9.2–14
LL
The HISL is in IR mode.
HISL IR ON IBF1
ED
ML message
IBF2
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.6.3 List of white advisory messages AFCS
AP1
ML message
Description
Refer to
TST ABORTED
AFCS selftest aborted before completion.
Section 4 Pre-flight test
AFCS selftest failed.
Section 4 Pre-flight test
or TST ABORTED
or TST FAIL
ED
TST FAIL AP2
LL
AP1
AP2
Air data monitoring degraded.
CHAN B REDUND
T O N C
AMC2
O N
AMC1
Respective AMC channel degraded. Section 4 Power-up test Pre-flight test
O
CHAN A REDUND or CHAN A REDUND
AMC2
TI
O N
or CHAN B REDUND
AMC degraded (loss of VMS input signal monitoring).
Section 4 Power-up test
Attitude monitoring degraded (AHRS degradation).
Section 4 Power-up test Pre-flight test
One or more avionic system(s) off or failed.
Section 4 Pre-flight test
ST
R
U
C
AMC MINOR REDUND
IN
REDUNDANCY
or REDUNDANCY or ATT REDUNDANCY
FO
R
ATT1
Section 4 Power-up test
–
AMC1
AIR2
Refer to
PY
or DATA REDUNDANCY
C
DATA REDUNDANCY
LY
AIR1
Description
O
ML message
N TR
O
AVIONICS AND DISPLAYS
AVIONIC TST FAIL
DATA CARD DATA CARD FULL
MANUFACTURER’S DATA Rev. 9
ATT2
DTD cover is not closed or data card is missing.
Section 3
Remaining space on the data card is not sufficient to record FDCR data for the next flight.
Section 3
7 – 13 – 65
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ML message
Description
Refer to
Flight data download failed (e.g. data card corrupt or full or data transmission interrupted).
DOWNLOAD FAIL
Before Helionix Maintenance Release 1
EFFECTIVITY
Section 7 UMS
A brief 3 second appearance is normal.
LL
Wrong warning unit is installed. Section 4 Should not appear during operation Start-up test (only after exchange of warning unit or software.
O
WU CONFIG FAIL or WU CONFIG FAIL
O
ENG2
N TR
ENG1
ED
All
EFFECTIVITY
Failure of one component of the FDRS system.
Section 3
N
O
T
C
FDRS
UMS detected an exceedance of an engine parameter or vehicle Section 3 parameter during the preceeding flight.
–
C
O
PY
FLT REPORT OVLIM
Ground/flight detection degraded.
HDG1
MAG HDG FAIL
Section 4 Power-up test
Failure of respective magnetometer. Section 3
IESI air data failure.
Section 3
IESI ATT FAIL
IESI attitude failure.
Section 3
IESI failure.
Section 3
FO
R
IN
ST
IESI AIR DATA
IESI FAIL
IESI SIGNAL FAIL
MAG HDG REDUND
MFD XTALK
7 – 13 – 66
HDG2
R
U
C
TI
and/or MAG HDG FAIL
O N
O N
LY
GND/FLT SENSOR
Loss or degradation of IESI altitude, Section 4 air data and backup monitoring. Pre-flight test One magnetic sensor (MAS) failed.
Crosstalk failure between the MFDs.
Section 4 Power-up test Section 3
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ML message MFD1
CPU1 MAJOR DEG or CPU1 MAJOR DEG or CPU1 MAJOR DEG
Refer to
Major degradation of affected MFD.
Section 4 Power-up test
MFD2 MFD4
CPU2 MAJOR DEG
ED LL
MFD4
Minor degradation of affected MFD.
C T O
MFD4
C
–
MFD2 MFD4
O N
or CPU2 MINOR DEG or CPU2 MINOR DEG
O
CPU2 MINOR DEG
LY
MFD1
MFD2
Section 4 Power-up test
N
or CPU1 MINOR DEG or CPU1 MINOR DEG
O
CPU1 MINOR DEG
PY
MFD1
MFD2
O
or CPU2 MAJOR DEG or CPU2 MAJOR DEG
N TR
MFD1
Description
OAT sensor degraded.
Section 4 Power-up test
The automatic power-up test could not be completed.
Section 4 Power-up test
The automatic power-up test could not be launched.
Section 4 Power-up test
U
C
TI
O N
OAT SENSOR DEG
IN
ST
R
PWR–UP TST ABORT
FO
R
PWR–UP TST PENDG
EFFECTIVITY
Before Helionix Maintenance Release 1 RA FAIL
MANUFACTURER’S DATA Rev. 9
The radar altimeter has failed.
Section 4 Pre-flight test
7 – 13 – 67
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ML message EFFECTIVITY
Description
After Helionix Maintenance Release 1 The radar altimeter has failed.
RA TST FAIL
EFFECTIVITY
Refer to Section 4 Pre-flight test
All A VMS sensor indication has failed or degraded.
VMS SENSOR
ED
CLIMATE CONTROL AND ICING PROTECTION
Section 3
Description
Refer to
HEATING FAIL
EECU bleed air inhibition signal failed.
Section 4 Start-up test
FMS1 and/or FMS2 have failed or signals are no longer received.
and/or FAIL
O
FMS2
C
Before Helionix Maintenance Release 1
–
EFFECTIVITY
HTAWS degradation.
O N
TI
C
U
R
ST
IN
HTAWS failure.
Section 3
R
FO
7 – 13 – 68
Section 3
HTAWS FLTA function switched off by the crew.
Section 3
After Helionix Maintenance Release 1
HTAWS TERR INHIB EFFECTIVITY
HTAWS failure.
Before Helionix Maintenance Release 1
TAWS TERR INHIB
EFFECTIVITY
Section 3
After Helionix Maintenance Release 1 HTAWS FAIL
EFFECTIVITY
HTAWS degradation.
Before Helionix Maintenance Release 1 TAWS FAIL
EFFECTIVITY
O N
After Helionix Maintenance Release 1
HTAWS DEGRADED EFFECTIVITY
Section 3
LY
TAWS DEGRADED EFFECTIVITY
Section 3
N
O
FAIL
PY
FMS1
T
C
O
COMMUNICATIONS, NAVÍGATION, AND SURVEILLANCE
N TR
O
LL
ML message
HTAWS FLTA function switched off by the crew.
Section 3
All
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ML message
Description
Refer to
Description
Refer to
BAT OVHT SENSOR
Failure of battery overtemperature sensor.
Section 4 LAMP TEST
DISC SENSOR
The sensor that is used to trigger the GEN DISCONNECT caution has failed.
Section 4 POWER UP TEST
ELECTRICS ML message
and/or DISC SENSOR
ED
GEN2
LL
GEN1
Circuit breaker located in rear panel 1 or 2 is open.
N TR
C
O
ENGINE Description
CHIP SENSOR
Engine chip sensor failed.
and/or CHIP SENSOR
PY
N
O
T
ML message
ENG2
FUEL FILTER
O N
ENG1
O N
LY
–
C
O
ENG1
U
ENG2
R
FO
ENG1
IN
ST
R
FUEL LOW TEMP
ENG1
OIL FILTER
and/or OIL FILTER
ENG1
ENG TREND
MANUFACTURER’S DATA Rev. 9
Fuel filter clogging on engine 1 and/or engine 2.
Section 3
Engine fuel temperature is too cold for takeoff without fuel anti-icing additives.
Section 3
Filter pre-clogging in engine oil system.
Section 3
Overspeed protection system failure.
Section 3
ENG2
SERVICE NEEDED and/or SERVICE NEEDED
ON GROUND: Section 4 Power-up test IN FLIGHT: Section 3
ENG2
OVSPD PROT FAIL and/or OVSPD PROT FAIL
Refer to
ENG2
C
TI
and/or FUEL FILTER ENG1
Section 3
O
REAR PANEL C/B
ENG2
A minor problem which requires Section 3 engine maintenance before the next flight was detected by the FADEC. Engine parameter abnormal trend.
Section 3
7 – 13 – 69
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FADEC1
ML message
Description
REDUNDANCY
FADEC 1/2 redundancy lost. Engine Section 3 control is not affected.
and/or REDUNDANCY FADEC1
Refer to
FADEC2
SIGNAL FAIL and/or SIGNAL FAIL
Section 3 Section 4 Power-up test Start-up test
ED
FADEC2
Some engine monitoring data are not received from the affected FADEC.
Description
LOW SENSOR
Fuel low sensor failed.
and/or LOW SENSOR
T
C
O
ML message
PY
Main fuel tank level is low, one transfer pump is running dry.
Section 3
LY
O N
GEARBOX AND DRIVE SYSTEM
–
C
O
MAIN FUEL LOW
Section 4 LAMP TEST
O
FUEL2
Refer to
N
FUEL1
N TR
O
LL
FUEL AND WEIGHT
Description
Refer to
MGB chip sensor failed.
ON GROUND: Section 4 Power-up test IN FLIGHT: Section 3
MGB TEMP SENSOR
MGB temperature sensor failed.
Section 4 Power-up test
MGB TREND
MGB oil temperature or pressure unusally high or low but still in normal range.
MM SENSOR
Mast moment sensor failed.
Section 4 Power-up test
NR SENSOR
NR sensor values inconsistent or unavailable.
Section 4 Start-up test
O N
ML message
FO
R
IN
ST
R
U
C
TI
MGB CHIP SENSOR
7 – 13 – 70
Section 3
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ML message SYS1
MGB PRESS SENSOR
Description
Refer to
MGB pressure sensor failed.
Section 4 Power-up test Start-up test
TGB chip sensor failed.
ON GROUND: Section 4 Power-up test IN FLIGHT: Section 3
and/or MGB PRESS SENSOR SYS2
LL
ED
TGB CHIP SENSOR
Low pressure sensor for hydraulic system 1/2 failed.
C
PRESS SENSOR
O
T
and/or PRESS SENSOR
HYD2
Refer to Section 4 Power-up test
PY
N
HYD1
Description
O
ML message
N TR
O
HYDRAULICS
Hydraulic pressure unusually high or low but still within normal operating range.
Section 3
O N
TR PRESS SENSOR
LY
–
C
O
HYD TREND
O N
OPTIONALS
C
TI
ML message
Section 3
Description
Refer to
No cargo attached to the hook.
FMS 9.2-6
IBF clogging trend.
FMS 9.2-5
Failure of LAVCS or LAVCS sw is OFF.
Section 7 Additional equipment
ST
R
U
HOOK UNLOADED
The pressure sensor monitoring the TR shut-off valve is inoperative.
LAVCS FAIL
FO
R
IN
IBF CLOG TREND
MANUFACTURER’S DATA Rev. 9
7 – 13 – 71
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.6.4 List of information messages AVIONICS AND DISPLAYS Refer to
Pre-flight test running.
Section 4 Pre-flight test
P–FLT TST OK
Pre-flight test completed without failure.
Section 4 Pre-flight test
PWR–UP TST
Power-up test running.
N TR
O
P–FLT TST
ED
Description
Power-up test completed without failure.
Section 4 Power-up test
O
T
C
O
PWR–UP TST OK
Section 4 Power-up test
LL
ML message
Start-up test running.
Section 4 Start-up test
PY
N
START–UP TST
Start-up test completed without failure.
Section 4 Start-up test
–
C
O
START–UP TST OK
EFFECTIVITY
O N
LY
COMMUNICATIONS, NAVÍGATION, AND SURVEILLANCE Before Helionix Maintenance Release 1
TI
C
R
FO 7 – 13 – 72
Section 4
HTAWS and ACAS aural alerts inhibited by the crew.
Section 4
After Helionix Maintenance Release 1
HTAWS+ACAS MUTE EFFECTIVITY
HTAWS aural alerts inhibited by the crew.
Before Helionix Maintenance Release 1
TAWS+ACAS MUTE
EFFECTIVITY
Section 4
IN
ST
R
HTAWS MUTE EFFECTIVITY
HTAWS aural alerts inhibited by the crew.
After Helionix Maintenance Release 1
U
EFFECTIVITY
O N
TAWS MUTE
HTAWS and ACAS aural alerts inhibited by the crew.
Section 4
All
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
ENGINE ML message ENG1
STARTER ON and/or STARTER ON
Refer to
Respective engine starter is active.
Section 4 Engine starting
ENG2 Engine training mode is active.
TRAINING or TRAINING
ENG2
FMS 9.1-3
LL
ED
ENG1
Description
O
Description
C
ML message
N TR
O
EXTERNAL LIGHTS
Fixed landing light is on.
PY
N
O
T
LDG LIGHT
Fixed landing light is on, and steerable search and landing light is on.
–
C
O
LDG+S/L LIGHT
Refer to Section 7 Lighting equipment Section 7 Lighting equipment Section 7 Lighting equipment
Steerable search and landing light is on.
Section 7 Lighting equipment
Steerable search and landing light is on in IR mode.
Section 7 Lighting equipment
S/L LIGHT RETR
Steerable search and landing light is retracting.
Section 7 Lighting equipment
CP
S/L LIGHT
Steerable search and landing light copilot’s (LH) side is on.
Section 7 Lighting equipment
CP
S/L LIGHT IR
Steerable search and landing light copilot’s (LH) side is on in IR mode.
Section 7 Lighting equipment
CP
S/L LIGHT RETR
Steerable search and landing light copilot’s (LH) side is retracting.
Section 7 Lighting equipment
O N
O N
LY
Fixed landing light is on, and steerable search and landing light is on in IR mode.
LDG+S/L LIGHT IR
U
C
TI
S/L LIGHT
FO
R
IN
ST
R
S/L LIGHT IR
MANUFACTURER’S DATA Rev. 15.2
7 – 13 – 73
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
FIRE ML message FIRE BOT 1 TEST
Description
Refer to
Fire extinguisher test successful.
Section 4 Fire protection test
or FIRE BOT 2 TEST or FIRE BOT 1+2 TEST
Description
Refer to
LL
ML message
ED
OPTIONALS
ACAS aural alerts inhibited by the crew.
N TR
O
ACAS MUTE
Hoist cable cutter test ok.
C
O
CABLE CUT TST OK
Cargo hook release armed.
O
T
CARGO HOOK
Emergency floats armed.
FMS 9.2-14
–
LY C
TI
HISL EXTENDED
O N
HISL STOWED
HISL lamp on in IR mode.
FMS 9.2-14
HISL stowed.
FMS 9.2-14
HISL extended and operatioal.
FMS 9.2-14
HISL laser and lamp on.
FMS 9.2-14
HISL laser and IR on in IR mode.
FMS 9.2-14
Hoist on.
FMS 9.2-4
Respective IBF bypass door in open position.
FMS 9.2-5
O N
HISL IR
ST
R
U
HISL ON+LASER
FMS 9.2-9 FMS 9.2-14
HISL laser on.
HISL LASER
FMS 9.2-6
HISL on.
O
HISL
FMS 9.2-4
C
PY
N
FLOATS ARMED
FMS 9.2-43
IN
HISL IR+LASER
IBF1
FO
R
HOIST
BYPASS OPEN
and/or BYPASS OPEN
7 – 13 – 74
IBF2
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.13.7
List of audio tones and voice messages
The following audio tones are generated by the Helionix audio system:
Sound
Triggering condition
NR min
Slow beep (decreasing 600 to 460 Hz tone)
NR below minimum NR (94% or 3 % below nominal NR) Inhibited on ground.
O
When ACK is pressed, the volume of the tone is reduced.
NR above 109%.
C
Fast beep (1400 Hz tone)
T
NR max
O
N TR
NOTE
LL
ED
Name
O
PY
N
O
NOTE
3 repetitions of 2 marimba percussions
Warning/caution tone
String arpeggio
U
C
TI
O N
O N
LY
–
C
Power split tone
IN
Appearance of a caution in the master list. Tone also used as pre-amble for warning audios. Continuous or takeoff power limits are exceeded.
3 vibraphone tones
Tone used as pre-amble for TAWS alerts.
FO
R
Alert pre-amble
Difference between the engines is >6% N1 or >52% torque, or training mode is active. Inhibited on ground, when collective lever MAINT –> HMS. Description of the HMS menu on the MFD pages is shown below:
GND
C
DMAU MROT default page on MFD:
O
T
Fig. 7-16-4
O
N TR
O
LL
ED
80KTS 120KTS
LABEL
FUNCTION
1
RUN or
To run an acquisition.
ABRT
To abort an acquisition
C
O
PY
N
ITEM
–
NOTE: ABRT key appears when RUN is selected
To validate the choice of parameters in CONF menu.
3
Knob (no label)
4
CONF
5
SHAFT
6
T ROT
7
M ROT
O N TI C
U
ST
R 7.16.4
IN R
9
To select sensor, harmonic or unit on sub–menu. Level and phase unit change.
SYST
FO
8
LY
VAL
O N
2
SEL
Shaft acquisition. Tail Rotor Tuning page display. Main Rotor Tuning page display. NOTE: MROT is the Default page on MFD when the HMS function is called up for the first time.
Exit the MFD DMAU display and go back to the MFD SYSTEM page. To change cursor position on page.
Display/Menus
7.16.4.1 Main rotor (M ROT) menu The Main rotor acquisition menu is used to select different flight stages by crew before engaging acquisition for rotor tuning. Four flight stages have to be selected for complete main rotor tuning analysis. Level and phase are processed and displayed at the end of each acquisition. For each flight stage, accelerometer sensor and harmonic lines are selected by the crew with the Rocher’s internal rob.
7 – 16 – 4
MANUFACTURER’S DATA Before Helionix Maintenance Release 1 or Rev. 11.1 before ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
80KTS
DMAU Software upload
120KTS
DMAU configuration H/C parameters
LL
M ROT acquisition menu
N TR
O
Fig. 7-16-5
ED
MFD Key pressed
O
7.16.4.2 Tail rotor (T ROT) menu
Fig. 7-16-6
T ROT acquisition menu
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
The Tail rotor acquisition menu is used to select ground stage by crew before engaging acquisition for tail rotor tuning. Level and phase are processed and displayed at the end of acquisition.
FO
If an error occurs on MR or TR tuning MFD pages, FAILED is displayed instead of values for level and phase.
7.16.4.3 Shaft vibration check menu The shaft acquisition menu SHAFT assesses the vibration level manually on following components onboard during any flight stage: – Main Rotor – Tail Rotor – Tail Drive Shaft The values can be displayed onboard. Raw data and results are also stored on the compact flash card and can be accessed on ground. MANUFACTURER’S DATA Rev. 11.1 Before Helionix Maintenance Release 1 or before ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
7 – 16 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
Shaft vibration check menu
C
O
7.16.4.4 Sensor test menu
N TR
Fig. 7-16-7
O
LL
ED
DESCRIPTION OF SYSTEMS
N
O
T
The sensor test menu is used for the maintenance of the system. It checks the system, including sensors, wires, connectors and acquisition unit.
–
C
O
PY
The sensor test function is launched by simultaneously pressing the top lateral left key (1) and bottom lateral right key (2) for more than 2 seconds when no manual acquisition is running.
O N
LY
The result of the acquisition is stored on the CF and not displayed on MFD. The ”SEL” key on the sensor tests MFD page shall be used to select the sensor tests acquisition type in the following order:
O N
– CAL048
TI
– CAL239
R
FO
R
IN
ST
– GENERIC
U
C
– CAL957
Fig. 7-16-8
7 – 16 – 6
Sensor test menu
MANUFACTURER’S DATA Before Helionix Maintenance Release 1 or Rev. 11.1 before ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
The sensor tests function detects the following failures: For accelerometers: – Short and open circuit (Yes/No) – % of Saturation on the acquisition – Level of offset For phase sensors: – Measured frequency – % of variation in the acquisition duration
LL
ED
7.16.4.5 Configuration menu
O
The CONF menu allows the selection of the following parameters:
N TR
– Harmonics Level units display (G, mG or IPS)
O
– Phase units display (degree, HH:MM)
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
The selector is used to change the level. The ”VAL” key is used to validate the choice.
Configuration menu (CONF)
Power supply
IN
7.16.5
ST
R
U
C
Fig. 7-16-9
FO
R
The HMS is supplied with electrical power from the AMC Bus 1 via the circuit breaker ”HMS“ located on the LH service connecter panel in the passenger compartment.
7.16.6
Maintenance mode The DMAU maintenance mode is only accessible on ground when maintenance switch is activated. The maintenance switch is located the on the LH service connector panel in the passenger compartment. A ground station connected to the DTD via Ethernet, provides the following functions: – Uploading the DMAU application software into the DMAU PFM. – Uploading the configuration file into the DMAU PFM. – Downloading application software, configuration and hardware versions. – Downloading data files from the Compact flash
MANUFACTURER’S DATA Rev. 11.1 Before Helionix Maintenance Release 1 or before ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
7 – 16 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
O
T
C
O
N TR
O
LL
ED
DESCRIPTION OF SYSTEMS
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
Intentionally left blank
7 – 16 – 8
MANUFACTURER’S DATA Before Helionix Maintenance Release 1 or Rev. 11.1 before ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
EFFECTIVITY 7.16
HEALTH MONITORING SYSTEM (HMS)
7.16.1
General The purpose of the Health Monitoring System (HMS) is: – To monitor all rotating mechanical components of the drivetrain – To monitor the vibrations of the engines
ED
– To provide assistance for tuning of main and tail rotors
LL
The acquired data are recorded in flight and processed, displayed and analyzed on ground
O
The HMS is composed of:
N TR
– A Dynamic Monitoring Acquisition Unit (DMAU)
O
– A set of accelerometers and rotor synchronization sensors
C
– A ground station (PC) (refer to description in the maintenance manual)
N
O
T
The HMS is connected to the avionics and comprises the AMC computer, the MFD display for crew interface management and the Data Transfer Device (DTD).
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
Two removable memory modules are integrated in the DMAU equipment for aircraft configuration and data storage.
Fig. 7-16-1
System architecture
MANUFACTURER’S DATA Rev. 11.1 After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
7 – 16 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.16.2
Component description
7.16.2.1 DMAU The DMAU is located in the overhead panel on the left hand side of the cabin. It performs the acquisition and processing of signals delivered by the sensors. During flight, data is automatically stored in removable memory modules (compact flash card). Recorded data will be automatically transferred to the DTD via Ethernet connection after each HMS session.
ED
The DMAU performs the following functions:
O
– Accessory gears, shafts, and bearings vibration monitoring
LL
– Main rotor gearbox shafts, gears and bearings vibration monitoring
N TR
– Intermediate and tail gearbox gears, shafts, and bearings vibration monitoring – Tail rotor drive shaft and support bearings vibration monitoring
C
O
– Main and tail rotor tachometer monitoring
T
– Main and tail rotor tuning
N
O
– Engine vibration Monitoring
O N
LY
–
C
O
PY
– HMS failure recording
C
TI
O N
CONF CARD (Compact Flash)
FO
R
IN
ST
R
U
RES CARD (Compact Flash)
Fig. 7-16-2
7 – 16 – 2
DMAU
MANUFACTURER’S DATA After Helionix Maintenance Release 1 or Rev. 11.1 after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.16.2.2 Data Transfer Device (DTD) HMS data transfer between the aircraft and the ground station is carried out by the Data Transfer Device (DTD). Two different downloading means are provided: – via removable memory device (compact flash card) performed automatically at the end of the flight – via Ethernet to a connected computer (launched manually in maintenance mode only) The download procedures are described in section 8. The DTD comprises:
ED
– An Ethernet socket (1)
LL
– A USB socket (2)
O
– A Compact Flash (CF) memory card (3)
N TR
– A LED which is lighted when the DTD is accessing to the Compact Flash Card.
DTD
C
U
7.16.2.3 MFD Display
Fig. 7-16-3
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
– A door to close the CF receptacle.
ST
R
The MFD is used to display and control the following HMS functions:
IN
– Trigger manual acquisitions for rotor tuning and sensor tests.
R
– Display sensor vibration level and phase.
FO
– Display and change basic settings of the DMAU. The ground station must be disconnected before starting procedures.
MANUFACTURER’S DATA Rev. 11.1 After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
7 – 16 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.16.3
Controls The HMS menu is accessed on the MFD via buttons SYST –> MAINT –> HMS. Description of the HMS menu on the MFD pages is shown below: 1
3
6
4
5
T
7
PY
HMS M ROT default page on MFD:
O
Fig. 7-16-4
N
O
8
C
O
N TR
O
LL
ED
2
LABEL
FUNCTION
1
RUN or
To run an acquisition.
LY
–
C
ITEM
To abort an acquisition
O N
ABRT
NOTE: ABRT key appears when RUN is selected
VAL
3
Knob (no label)
4
CONF
5
SHAFT
Shaft acquisition.
6
T ROT
Tail Rotor Tuning page display.
M ROT
Main Rotor Tuning page display.
8
7 – 16 – 4
TI
C
U
R
ST
IN R FO
7
O N
2
SYST
To validate the choice of parameters in CONF menu. To select flight state, sensor, harmonic or unit on sub-menu. Level and phase unit change.
NOTE: MROT page is the default page on MFD when the HMS function is called up for the first time. In this case no label M ROT is displayed in bottom line.
Exit the MFD DMAU display and go back to the MFD SYSTEM page.
MANUFACTURER’S DATA After Helionix Maintenance Release 1 or Rev. 11.1 after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.16.4
Display/Menus
7.16.4.1 Main rotor (M ROT) menu The Main rotor acquisition menu is used to select different flight stages for main rotor measurements in order to perform main rotor tuning on the ground PC.
1
2
–
HMS M ROT acquisition menu
LY
Fig. 7-16-5
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
The flight condion is selected by the rotary knob (2) and executed by RUN (1). Harmonic vibration level and phase are processed and displayed at the end of each acquisition. The crew is able to switch between the result of each HMS sensor (PILX, PILY, PILZ, COPX, COPY, COPZ, CABX, CABY and CABZ) and harmonic (1/rev, 2/rev, 3/rev, 4/rev) by selecting the SENSOR or HARMONIC via button (2).
O N
7.16.4.2 Tail rotor (T ROT) menu
O N
The Tail rotor acquisition menu T ROT is used to start tail rotor measurement on-ground in order to perform tail rotor tuning.
FO
R
IN
ST
R
U
C
TI
The measurement is executed by RUN (1). Harmonic vibration level and phase are processed and displayed at the end of each acquisition. The crew is able to switch between the result of each harmonic (1/rev, 2/rev) by selecting HARMONIC via SEL and switching via button (2). Only sensor TGB is active during measurement.
1
2
Fig. 7-16-6
HMS T ROT acquisition menu
If an error occurs during main or tail rotor tuning MFD pages, FAILED is displayed instead of values for level and phase. MANUFACTURER’S DATA Rev. 11.1 After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
7 – 16 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.16.4.3 Shaft vibration check menu The tail drive shaft acquisition menu SHAFT allows direct measuring of the vibration level of Tail Rotor Drive Shaft Bearings 1 to 4 (TDSB1 to 4) on board (numbering from FWD to AFT) and checking the imbalance vibration levels automatically with respect to a max. admissible imbalance.
1
2
O N
HMS SHAFT VIBRATION acquisition menu
O N
Fig. 7-16-7
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Each component is selected via the rotary knob (2) and the measurement is executed by RUN (1). The vibration signals are processed and the imbalance is displayed at the end of each acquisition. Vibration level and convergence rate are displayed as results for each acquisition along with a GO / NOGO message. The harmonic vibration levels of the tail rotor drive shaft imbalance are processed and if the levels are detected within limits, the HMS displays the message ”GO”. In case of limit exceedance, the message ”NOGO” will be shown. The crew is able to switch between the result of each harmonic (1/rev, 2/rev) by selecting HARMONIC using the rotary knob (2).
TI
7.16.4.4 Sensor test menu
ST
R
U
C
The sensor test menu is used for the maintenance and troubleshooting of the system.
IN
1
FO
R
2
Fig. 7-16-8
HMS SENSOR TEST menu
The sensor test menu is entered by simultaneously pressing the top lateral left key (1) and the bottom lateral right key (2) for more than 2 seconds when no manual acquisition is running. The rotary knob is used to select the item in order to perform a test or enter the subpage of: Calibration test / Continuity test / Location test / Generic acquisition.
7 – 16 – 6
MANUFACTURER’S DATA After Helionix Maintenance Release 1 or Rev. 11.1 after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.16.4.5 Configuration menu The CONF menu allows the selection the display settings of vibration measurements. The level unit allows displaying vibration levels following units: G, mG or IPS. Phase units can be displayed in degree or HH:MM. Selection of level or phase unit is done via SEL (1). The unit may be switched via (3) and validated by key (3).
2
O
LL
ED
1
T
HMS configuration menu (CONF)
N
O
Fig. 7-16-9
C
O
N TR
3
O
Refer to section 8 for the HMS manual data downloading procedures.
C
NOTE
PY
7.16.4.6 HMS download menu
O N
O N
LY
–
After each flight, the status information about the download process is available once the rotor has fully stopped. A progress bar indicates the download in progress and after completion “DOWNLOAD COMPLETE“ is shown. In case of malfunction, a failure message will be displayed.
R
U
C
TI
The crew is also able to initiate manual download of the current flight (current flight ID) and previous flight (with the previous flight ID). Older flights cannot be accessed for download via MFD, but need to be downloaded directly from DMAU compact flash cards.
FO
R
IN
ST
The SEL key (1) is used to change cursor position on page. The download can be started with the RUN key (2) The ABRT key is used to abort the download. ABRT key is shown when RUN has been selected.
2 1
Fig. 7-16-10
HMS Data Loading menu
MANUFACTURER’S DATA Rev. 11.1 After Helionix Maintenance Release 1 or after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
7 – 16 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.16.4.7 HMS Version page / Troubleshooting mode The HMS page for version display of DMAU software and hardware is not directly accessible via the bottom keys. The crew can access the page by pressing simultaneously top lateral left key (1) and bottom lateral left key (2) on any HMS menu. Part numbers of application software (APSW), configuration file (C/F) and DMAU hardware are listed.
LL
ED
The TROUBLESHOOTING Mode can be enabled or disabled (default setting) via button (3) on MFD. The Troubleshooting mode increases the amount of raw data stored per flight hour for health acquisitions of the main gearbox, cabin, tail drive shaft and tail gearbox.
O
N TR
O
1
3
Power supply
–
O N
7.16.5
HMS Version page
LY
Fig. 7-16-11
C
O
PY
N
O
T
C
2
U
Maintenance mode
R
7.16.6
C
TI
O N
The HMS is supplied with electrical power from the AMC Bus 1 via the circuit breaker ”HMS“ located on the LH service connecter panel in the passenger compartment.
FO
R
IN
ST
The DMAU maintenance mode is only accessible on ground when maintenance switch is activated. The maintenance switch is located the on the LH service connector panel in the passenger compartment. A ground station connected to the DTD via Ethernet, provides the following functions: – Uploading the DMAU application software into the DMAU PFM. – Uploading the configuration file into the DMAU PFM. – Downloading application software, configuration and hardware versions. – Downloading data files from the Compact flash
7 – 16 – 8
MANUFACTURER’S DATA After Helionix Maintenance Release 1 or Rev. 11.1 after ASB MBB BK117 D-2–42A–004 (HELIONIX STEP 2.0.1)
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.17
USAGE MONITORING
7.17.1
General The objective of the Usage Monitoring System (UMS) is to facilitate flight follow-up, by monitoring several vehicle and engine parameters in order to assist the operator with definition of maintenance measures. The UMS function was designed to: – Ensure information accuracy and reliability, so that UMS data can be used as input for helicopter maintenance. – Ensure information accuracy and reliability so that the pilot is not obliged to validate each UMS data item at the end of the flight.
LL
ED
– Comply with required information accuracy and reliability regardless of whether the On Board reporting or On Ground reporting is used.
N TR
O
7.17.1.1 UMS functions The UMS (Usage Monitoring System) function performs:
C
O
– Acquisition of parameters from engine and vehicle systems
O
T
– Processing of UMS data – Recording of UMS data
PY
N
– Display of UMS data on the FLIGHT REPORT page or on a ground station.
O
The UMS function is achieved by two parts:
–
C
– An on-board segment (airborne system) which monitors and records UMS data throughout each flight.
O N
LY
– An on-ground segment (ground station) which is used to display recorded UMS data on a ground station.
U
C
TI
O N
Acquisition, processing, and recording of UMS data is centralized within both Aircraft Management Computers (AMC). Displaying the recorded parameters is possible through the FLIGHT REPORT, which displays part of the parameters on MFD4 at the end of the flight, and on ground through a PC–based ground station.
FO
R
IN
ST
R
Transfer of UMS data between the aircraft and the ground station is performed via the Data Transfer Device (DTD). The Data Transfer Device comprises an Ethernet socket, a USB socket, and a Compact Flash (CF) memory card (Fig. 7-17-1). Data transfer is normally performed through the removable CF card, which is automatically written at the end of each flight. In the absence of a CF card, however, the data can also be manually downloaded through the Ethernet connection.
Fig. 7-17-1 MANUFACTURER’S DATA Rev. 0
Data Transfer Device (DTD)
7 – 17 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.17.1.2 UMS on-board data storage and reliability The UMS monitoring function operates from the beginning to the end of the flight and guarantees full time monitoring by self-verifying and validating the running time of the VMS partition. UMS data monitoring starts when either the first engine is started or the main rotor speed exceeds 10%. It remains active as long as at least one engine is not stopped and the main rotor speed is above 10%.
N TR
O
LL
ED
The UMS guarantees full time monitoring by self-verifying and validating the running time of the VMS partition. This check is done by comparing the VMS partition running time to the block time by using separate time references. If consistent, all the UMS data are considered reliable and are automatically validated. In case of discrepancy, the pilot is invited to validate or invalidate the block time displayed on the flight report. When data are validated, the UMS data are considered reliable; if the data are invalidated, the computed UMS data must be considered unreliable and the maintenance operator must conservatively replace the computed UMS data on the ground station.
C
O
PY
N
O
T
C
O
The UMS on-board segment is capable of storing in a non-volatile memory, the UMS data from the last to 320 flights. Normally, the UMS data are automatically downloaded at end of the flight (on ground with rotor stopped) but can also be downloaded at the pilot’s request when the helicopter is on ground with rotor turning. In that case, the UMS data are partial and are just an indication of what occurred since the beginning of the flight. Partial UMS data are not validated and the data are automatically erased by the complete UMS data at the completion of the flight.
O N
LY
–
The white advisory DOWNLOAD FAIL on the FND ML indicates that the downloading means are not operational (e.g. data card is corrupt or full).
O N
The white advisory DATA CARD FULL on the FND ML indicates that FDCR data (if the option is installed) cannot be recorded on the data card anymore.
U
C
TI
The white advisory DATA CARD on the FND ML indicates that the DTD cover is not closed or the data card is missing.
IN
ST
R
If a limit exceedance occurred, the white advisory FLT REPORT OVLIM is displayed on the FND ML until the next flight.
FO
R
7.17.1.3 UMS monitoring function The usage monitoring system (UMS) acquires, processes, stores, and displays vehicle and engine parameters. For Flight identification and helicopter assignment, the UMS monitors: – Flight number (this flight number will also increase when the helicopter is only run on ground without taking off) – H/C serial number – H/C type – Calendar time – Flight duration according to the ICAO definition (also known as the “block time“, i.e. the time from start of the first engine to stopping of the rotor)
7 – 17 – 2
MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
For vehicle maintenance purposes, the UMS monitors: – Vehicle limit exceedances (NR, main gearbox TRQ, mast moment) – Vehicle chip detection (MGB and TGB) – Maintenance flight time (airborne time, time used to calculate the aircraft flight hours) – Vehicle cycles (landing cycles, NR cycles, MGB TRQ cycles) – OAT at first takeoff – IBF clogging level exceedance (if installed) – Hoist cycle counting (if installed)
ED
Although hoist operating time and cargo hook cycles are also monitored and stored, these are not validated and therefore shall not be used for maintenance purposes.
O
LL
NOTE
N TR
For engine maintenance purposes, the UMS monitors for each engine:
O
– Engine cycles (N1, N2)
C
– Blade creep damage counter
O
T
– Engine power check (EPC)
N
– Engine limit exceedances (N1, N2, TOT, TRQ)
PY
– Engine chip detection
C
O
– Engine OEI counters
LY
– Engine OEI detected
O N
– Engine OEI exceedances
–
– Engine operating time
O N
– Engine service needed message from the FADEC
TI
7.17.1.4 FLIGHT REPORT pages
IN
ST
R
U
C
The UMS parameters are displayed to the crew at the end of the flight through the flight report (FR) as soon as NR is below 10%. When the helicopter is on ground, electrical power is on and no engine has been started, the last FR (REPORT key) and the last EPC results (EPC key, then HIST) on both engines are available for display on crew request.
FO
R
The flight report consists of a minimum of 4 and a maximum of 14 pages, depending on the recorded events. (see Fig. 7-17-3 to Fig. 7-17-16). The LSK PREV and NXT allow scrolling through the pages. If any limit exceedance, chip detection or OEI event occurred, the message will be displayed on the first page of the FR. Detailed information is provided on the dedicated FR pages.
MANUFACTURER’S DATA Rev. 0
7 – 17 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
EFFECTIVITY
The term INCIDENT is used only to indicate that additional flight report pages are available. It does not imply that an incident in accordance with the ICAO (Annex 13) definition has occurred.
O
Flight report page 1 – typical display
LY
After Helionix Maintenance Release 1
O N
O N
EFFECTIVITY
–
C
Fig. 7-17-2
PY
N
O
T
C
O
N TR
O
LL
ED
NOTE
Before Helionix Maintenance Release 1
FO
R
IN
ST
R
U
C
TI
H I S T
EVENT
Fig. 7-17-3 EFFECTIVITY
7 – 17 – 4
Flight report page 1 – typical display
All
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
1
2 3
Flight time according to the ICAO definition (”BLOCK TIME”) from engine start, to rotor stopping. Flight time according to the maintenance definition (”FLIGHT TIME”), counting only the time when the aircraft is airborne. Flight report current page / total page number Flight number The flight number will be increased for each flights and ground runs where power was applied. Flight time validation status VAL (LSK on MFD) Engine cycles for the last flight (FLT) and total number of cycles (CUM) EFFECTIVITY Before Helionix Maintenance Release 1
LL
4 5 6 7
ED
NOTE
N TR
O
INCIDENT message
After Helionix Maintenance Release 1
EFFECTIVITY
C
O
EVENT message
N
PY
8 9
O
T
EFFECTIVITY All NXT (LSK on MFD) EFFECTIVITY After Helionix Maintenance Release 1
C
O
HIST (LSK on MFD)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
All
EFFECTIVITY
MANUFACTURER’S DATA Rev. 9
7 – 17 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Display of the flight time validation status depends on the status:
VALIDATED
Both time references consistent, parameters automatically validated.
VALIDATE
Time references not consistent, UTC flight time valid. Crew can validate ICAO time by pressing VAL LSK, or change to INVALIDATE. Time references not consistent, UTC time valid. Crew can invalidate parameters by pressing VAL LSK, or change to VALIDATE.
INVALIDATED
Parameters invalidated automatically (UTC time invalid) or by the crew (ICAO time invalidated)
O
LL
ED
INVALIDATE
N
O
T
C
O
N TR
As long as the flight report is not validated, the text description, units and values appear in dark gray. When the flight report has been invalidated, the text description and units appear in white and the values appear in dark gray. When the flight report has been validated, the text description appears in white, the units in dark gray and the values appear in cyan when valid.
Flight report page 2 – OEI usage – typical display
ST
R
U
Fig. 7-17-4
C
TI
O N
O N
LY
–
C
O
PY
Numerical values are replaced by a failure symbol (one or several asterisks (*)) if parameters are unreliable.
FO
R
IN
This page shows the number and duration of OEI events for the current flight and for all flights cumulated so far. n / x mn y s, means that n events have been recorded and that the total duration of these events was x minutes and y seconds. Data for engine 1 are shown on the left; engine 2 on the right. ENG OEI DETECTED appears when an OEI rating was used (maintenance is required to reset this label). ENG OEI EXCEEDED appears when the maximum time allowed in OEI or the maximum engine limits were exceeded and immediate maintenance is required.
7 – 17 – 6
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Fig. 7-17-5
Flight report page 3 – Creep life damage indication – typical display
Flight report page 4 – Landing and hoist cycles
O
Fig. 7-17-6
PY
N
O
T
C
O
N TR
O
LL
ED
This page shows the creep life damage incurred during the current flight and accumulated for all flights performed so far. Once the cumulated creep damage reaches 100%, the affected engine must be overhauled in accordance with the engine maintenance instructions.
TI
C
If the hoist cable length was not available in flight (due to a failure), the hoist cycles will not be properly counted (*** indicated). In this case, the hoist operator should manually count the hoist cycles.
IN
ST
R
NOTE
Before Helionix Maintenance Release 1
U
EFFECTIVITY
O N
O N
LY
–
C
HOIST CYCLES (if hoist is configured): The number of hoist cycles that were performed since the previous flight. A hoist cycle is counted each time the cable is extended beyond 5m. The hoist cycle count also includes all hoist cycles performed on ground (e.g. as part of a daily inspection or maintenance action) since the last flight.
FO
R
EFFECTIVITY
NOTE
EFFECTIVITY
AfterHelionix Maintenance Release 1
Helionix Maintenance Release 1 installed. NOTE If the hoist cable length was temporarily unavailable in flight, the hoist cycles will be indicated in amber. In this case, the hoist operator should verify the counted hoist cycles. All
MANUFACTURER’S DATA Rev. 9
7 – 17 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
LANDING CYCLES: The number of landings that was performed during the flight.
Flight report page TOT OVLIM – typical display
O
Fig. 7-17-7
LL
ED
The flight report pages 5 to 14 (see Fig. 7-17-7 to Fig. 7-17-16) are only displayed if one or several respective limit exceedances occurred during the current flight.
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
The page shows the number of exceedances, the maximum value and the duration of the exceedance. The page distinguishes exceedances during AEO/OEI operation and during the START phase.
Flight report page N1 OVLIM – typical display
O N
Fig. 7-17-8
FO
R
IN
ST
R
U
C
TI
The page shows the number of exceedances, the maximum N1 reached, and the duration of the N1 exceedance.
7 – 17 – 8
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Fig. 7-17-9
Flight report page N2 OVLIM – typical display
N
O
T
C
O
N TR
O
LL
ED
The page shows the number of exceedances, the maximum N2 reached, and the duration of the N2 exceedance.
Flight report page ENG TRQ OVLIM – typical display
PY
Fig. 7-17-10
ST
R
U
C
TI
O N
O N
LY
–
C
O
The page shows the number of exceedances, the maximum torque reached, and the duration of the engine torque exceedance.
Flight report page NR OVLIM – typical display
IN
Fig. 7-17-11
FO
R
The exceedance time shown on the page NR OVLIM (see Fig. 7-17-11) shows the total time spent in the respective NR range. Events will only be considered if the allowed transient is exceeded. In the example shown above, the total time above 109% NR in the power off condition was 13.2 seconds, which is 1.2 seconds longer than the permitted transient of 12 seconds.
MANUFACTURER’S DATA Rev. 9
7 – 17 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Fig. 7-17-12
Flight report page MGB TRQ OVLIM (AEO) – typical display
LL
ED
The page MGB TRQ OVLIM (AEO) (see Fig. 7-17-12) shows torque exceedances during AEO operation. The time shown is the total time spent in the respective range (including the allowed transient). Events are shown only when the allowed transients were exceeded.
N TR
O
NOTE D The LO SPEED range covers exceedances below VY+5kt; the HI SPEED range covers any exceedance above VY+5kt.
N
O
T
C
O
D The maximum torque shown (MAX AEO), represents the maximum torque during the exceedance. If more than one exceedance is recorded, the torque from the exceedance with the highest torque is shown.
O
PY
The time and amplitude spent in each segment shall be recorded immediately in the aircraft maintenance logbook and allows the specific maintenance actions to be defined.
A single flight to complete the mission and reach a base where maintenance is possible, under the following conditions:
O N
–
LY
–
C
The following guidelines may be used to decide if flights are allowed until full maintenance is performed:
•
The time in the > TOP TRANS category is less than 30.0 seconds.
C
TI
O N
The maximum torque (MAX AEO) does not exceed 110%.
R
U
Flight operations can be continued for a maximum of 50 flight hours without maintenance action (except for recording of the event), under the following conditions:
FO
R
•
IN
ST
–
•
•
7 – 17 – 10
The time in the > MCP > HI SPEED category does not exceed 600 sec and MAX AEO torque is less than 95% and the exceedance did not occur during turns with more than 30_ bank angle or IAS above VNE–10 kt.
The time in the > TOP (HI SPEED or LO SPEED category does not exceed 30 seconds.
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Fig. 7-17-13
Flight report page MGB TRQ OVLIM (OEI) – typical display
ED
The page MGB TRQ OVLIM (OEI) (see Fig. 7-17-13) shows torque exceedances during OEI operation. The time shown is the total time spent in the respective range (including the allowed transient). Events are shown only when the allowed transients were exceeded.
N TR
O
LL
NOTE D The maximum torque shown (MAX OEI), represents the maximum torque during the exceedance. If more than one exceedance is recorded, the torque from the exceedance with the highest torque is shown.
O
T
C
O
D The OEI TRANSIENT limits can normally not be exceeded, except in case of a FADEC malfunction
–
Provided both engines are fully serviceable, a single flight to complete the mission and reach a base where maintenance is available can be conducted, provided:
O N
LY
–
C
O
PY
N
The time spent in each segment and the maximum amplitude shall be recorded immediately in the aircraft maintenance logbook and allows specific maintenance actions to be defined. The following guideline may be used to decide which immediate actions are allowed until full maintenance is performed:
The time in the >OEI TRANSIENT category is 0.0 seconds.
FO
R
IN
ST
R
U
C
TI
O N
•
Fig. 7-17-14
Flight report page MM OVLIM – typical display
The page MM OVLIM (see Fig. 7-17-14) shows the maximum mast moment during the last flight and the time spent in each exceedance segment. It also shows the cumulated time (CUM) spent in the respective segment as well as the number of mast moment exceedance events. The time spent in each segment allows the specific maintenance actions to be defined. Flight operations can be continued without immediate maintenance (except for recording of the event), under the following conditions: – The cumulated time in the 66%–79% segment is less than 25.0 seconds. – The cumulated time in the 79%–90% segment is less than 7.0 seconds.
MANUFACTURER’S DATA Rev. 9
7 – 17 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Fig. 7-17-15
Flight report page CHIP DETECTION – typical display
O
Flight report page ENG SVC NEEDED – typical display
C
Fig. 7-17-16
PY
N
O
T
C
O
N TR
O
LL
ED
The page CHIP DETECTION (see Fig. 7-17-15) shows the number of chip detections during the last flight for the respective systems. This includes chip detections which were subsequently removed by the fuzz burner.
LY
–
The page ENG SVC NEEDED (see Fig. 7-17-16) shows IBF clogging theshold exceedances (if installed) as well as engine maintenance messages generated by the FADEC.
O N
Refer to FMS 9.2–5 for details on the IBF indication.
TI
O N
The following engine related messages can be indicated. The engine maintenance manual shall be consulted to determine the maintenance required:
R
U
C
– RUN DOWN: The N2 run down time following engine shut down is too short.
IN
ST
– FUEL TEMP: The maximum fuel temperature was exceeded.
FO
R
– PUMP PRESS: The LP fuel pump pressure was below the minimum. – FUEL FILT PRE–CLOGGING: Fuel filter pre-clogging status was recorded. – OIL FLOW: An engine oil flow interruption occurred. – OIL PRESS: The maximum oil pressure was exceeded. – OIL TEMP: The maximum oil temperature was exceeded.
7 – 17 – 12
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.17.1.5 FLIGHT REPORT history pages EFFECTIVITY
After Helionix Maintenance Release 1
C
FLIGHT REPORT history pages – typical display
O
T
Fig. 7-17-17
O
N TR
O
LL
ED
When the HIST LSK on the flight report page is pressed, the flight history page opens. This page provides immediate access to the last 49 flight reports.
PY
N
The flight history displays the available flight reports in the following format: “500 27/4/17 – 14h11mn”, where:
O
– “500” is the flight number
C
– 27/ 4/17 is the data in day/month/year format
LY
–
– “14h11mn” is the time of the first takeoff in hours:minutes format
O N
In some cases, the label DATA NOT AVAILABLE may be appear. In this case, the flight report data shall be obtained from the download UMS/VMS data. Maintenance may be required to restore the flight history page.
R
All
FO
R
IN
ST
EFFECTIVITY
U
C
TI
NOTE
O N
A flight report can be selected from the flight history by using the MFD’s rotary button.
MANUFACTURER’S DATA Rev. 9
7 – 17 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.17.1.6 Engine power check Refer to Section 5. 7.17.1.7 Data downloading and ground tool Data downloading is normally performed automatically after each flight onto the CF memory card. Manual downloading to the card or to a pc connected via the DTD Ethernet socket can also be performed (refer to Section 8.7 for the downloading procedure).
N TR
O
LL
ED
Downloaded data can be accessed with the ground tool (i.e. a special software installed on a pc or laptop). The ground tool displays all UMS data from the transferred flight and can generate a printable flight report. The ground tool also calculates and visualizes UMS data cumulated over a number of flights (data relative to successive flights) and can trend EPC data. If unscheduled maintenance is diagnosed, the ground tool provides a links or information between the recorded UMS data and the corresponding maintenance manual chapter to be applied.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
The ground tool is used to manage UMS information as a database (per helicopter type, per helicopter S/N.....) and to store it in a convenient, easy to check format. If FDCR data are available, the ground tool can also be used to display context flight data from FDCR parallel with the UMS data to assist the analysis of incidents or maintenance events.
7 – 17 – 14
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.18
HELICOPTER TERRAIN AWARENESS SYSTEM - HTAWS (OPTIONAL)
7.18.1
General The HTAWS provides the flight crew with alerts of pending collision of the helicopter with the terrain or obstacles included in the database. The system provides the following two functions: – The Forward Looking Terrain Avoidance (FLTA) function with alerts of pending collision with terrain or an obstacle.
O
TAWS switch on overhead panel
N TR
7.18.2
LL
ED
– The Ground Proximity Warning System (GPWS) function with alerts of pending vertical collision with terrain.
O
A three position switch HTAWS switch is located on the overhead control panel.
O
TAWS sw on OVHP - typical installation
O N
Fig. 7-18-1
LY
–
C
STBY TAWS
O
PY
N
N O R M
T
C
MUTE
C
TI
O N
The switch allows the crew to select TAWS mute mode (MUTE), TAWS normal mode (NORM) and standby mode (STBY). The NORM position is the standard position during H/C operation.
R
U
Switch position
ST
EFFECTIVITY
Before Helionix Maintenance Release 1
MUTE
R
IN
This unstable switch position inhibits the audio for 5 minutes. Audio alarns are inhibited, TAWS MUTE is displayed on ML and is diplayed on NAVD (or DMAP) HTAWS Inhibition is immediately stopped by operating the switch a second time
FO EFFECTIVITY
Type
After Helionix Maintenance Release 1
MUTE
MANUFACTURER’S DATA Rev. 9
This unstable switch position inhibits the audio for 5 minutes. Audio alarns are inhibited, HTAWS MUTE is displayed on ML and is diplayed on NAVD (or DMAP) HTAWS Inhibition is immediately stopped by operating the switch a second time
7 – 18 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
EFFECTIVITY
All
NORM
Normal position for the HTAWS. The system is operational.
STBY
Total inhibition of the HTAWS functions (audio alarms, visual alarms and terrain display. Depending on the aircraft configuration, the HTAWS MUTE function may also be accessible on the cyclic grip.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
NOTE
7 – 18 – 2
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.18.3
Virtual control panel (VCP) When NAVD or internal DMAP (see FMS 9.2–32) format is displayed, a long press on the HTAWS bsk opens or closes the HTAWS VCP window. The related lsk on the HTAWS VCP displays a toggle button providing the following options: NOTE
Only one VCP can be used at a time. Therefore, the VCP must always be closed before leaving the NAVD or DMAP page formats.
SYSTEM CONTROL PANEL
LL
ED
HTAWS
TERR FLTA FAIL OBST FLTA FAIL GPWS MODE 1 FAIL GPWS MODE 3 FAIL GPWS MODE 5 FAIL
N TR
O
NORMAL TERRAIN INHIBIT
O
NORMAL GS OVERRIDE
N
VCP window
PY
Fig. 7-18-2
O
T
C
BKD2_FLH_0145_R
NORMAL LOW ALTITUDE
O
LOW ALTITUDE MODE
–
C
The LOW ALTITUDE mode is intended for VFR operations below 500 ft AGL.
O N
LY
This mode shall be used only if visual contact with all terrain and obstacles can be maintained at all times except as required for specific instrument approaches, for specific procedures, or for approaches with significant obstacles in the visual segment.
U
Despite the reduction of the FLTA warning boundaries around airports/ heliports, obstacle nuisance alerts may still occur in the course of departure or approach procedures with significant obstacles in the visual segment. It is therefore recommended to select the LOW ALTITUDE mode prior to procedures where an obstacle alert is susceptible to be triggered in the visual segment. This recommendation applies only to procedures and obstacle environments already familiar to the pilot.
FO
R
IN
ST
R
NOTE
C
TI
O N
The LOW ALTITUDE mode significantly reduces the warning boundaries of mode 3 and mode 5 of the GPWS function (refer to para 7.18.4), and reduces the FLT.A sensitivity.
TERRAIN INHIBIT MODE
For operations in day VMC where terrain and obstacle clearance may be assured visually and terrain and obstacles alerts will hamper aircrew performance, the Terrain Inhibit function may be used to inhibit all terrain and obstacles alerts. When Terrain Inhibit is activated, TAWS TERR INHIB is displayed on ML. Terrain Inhibit suppresses all terrain and obstacle awarness alerts (FLTA alerts), however the terrain display remains operational. Terrain Inhibit remains active until the Terrain Inhibit control is reset. MANUFACTURER’S DATA Rev. 9
7 – 18 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
GS OVERRIDE MODE For deliberate operations below the ILS glideslope, mode 5 (glideslope mode) can be inhibited. FAILURE MESSAGES In case of (partial) HTAWS malfunction or inhibition, the VCP provides detailed failure messages. 7.18.4
FLTA (FORWARD LOOKING TERRAIN AVOIDANCE) FUNCTION
N TR
O
LL
ED
The FLTA function uses a combination of database information, GPS localization and helicopter data to estimate the helicopter position relative to the surrounding terrain and obstacles included in the database. Should the projected flight path of the helicopter conflict with terrain or obstacles included in the database, the FTLA function will provide the crew with alerts (visual and voice, see details in para 7.18.9).
N
O
T
C
O
The HTAWS will issue terrain alerts not only when the aircraft altitude is below the terrain elevation but also when the aircraft is projected to come within minimum clearance values of the terrain. This alerting is also provided for obstacles. Any potential impact points will be depicted on the display.
PY
The FLTA function uses:
Position and ground speed information provided by the GPS 2 receiver,
–
Data from the helicopter sensors (radio height, baro–altitude and vertical speed, IAS, OAT, heading).
–
Terrain, obstacle and navigational information from three databases
O N
LY
–
C
O
–
Terrain elevation data base,
–
Obstacles data base (including points and lines),
–
Aeronautical data base of airports, airfields, heliports. The aeronautical data base is used to desensitize the FLTA function during takeoff from, approach and landing to airports, airfields and heliports in order to avoid nuisance alerts.
FO
R
IN
ST
R
U
C
TI
O N
–
The data bases are loaded on the ground into the HTAWS function non-volatile memory using the Data Transfer Device (DTD).The status and expiry date of the data base can be verified on the VMS/SYST page by pushing the DATAB key. An integrity check of this database is launched if the content has changed since the last loading process.
7 – 18 – 4
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.18.4.1 HTAWS Altitude/Color Correlation and terrain/obstacle alerts The Height Above Terrain (HAT) overlay is composed of several colored translucent layers that depict the terrain above or below the ownship altitude. The HTAWS provides display of proximate terrain. Terrain and obstacles are color coded to provide visual information of the relative vertical distance between the aircraft and the terrain/obstacles. EFFECTIVITY
To avoid excessive cluttering, the NAVD displays only obstacles which are at a distance of 4 NM or less.
O
A ”group” obstacle is a symbolic presentation of multiple (more or less) co-located obstacles. Information on the location of the individual obstacles in the group is missing. Depending on the database quality, a group obstacle may represent anything from a tight cluster of towers to a vast area of windmills. Therefore, particular caution shall be used when navigating in the vicinity of a group obstacle. All
–
EFFECTIVITY
C
O
PY
N
O
T
C
O
NOTE
After Helionix Maintenance Release 1
N TR
EFFECTIVITY
LL
ED
NOTE
Before Helionix Maintenance Release 1
0
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
The colors are as shown below:
–250
–500
–1500
Group
Lighted Obstacles < 1000’ AGL > 1000’ AGL
Group
BKD2_FLH_0097_R
Unlighted Obstacles < 1000’ AGL > 1000’ AGL
Fig. 7-18-3
Altitude/Color correlation and terrain/obstacle alerts (height in ft)
MANUFACTURER’S DATA Rev. 9
7 – 18 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
Typical HTAWS presentation on NAVD (HTAWS and ACAS activated)
O
Fig. 7-18-4
N TR
O
LL
ED
DESCRIPTION OF SYSTEMS
PY
TYPE
O
DISPLAY
N
O
T
C
The status lines at the bottom of the NAVD and DMAP page show if HAT coloring is available and/or indicated as follows:
O N
LY
–
C
HAT display available
HAT layer displayed
HAT layer not displayed
FO
R
IN
ST
R
U
C
TI
O N
HAT display not available
7 – 18 – 6
MANUFACTURER’S DATA Rev. 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
7.18.4.2 Protection envelope FLTA uses a protection envelope calculated around the H/C from its flight parameters. The envelope includes 3 alert regions: Warning Alerts: alerts which require immediate flight crew attention and decision. This is the envelope region which is closest to the helicopter (see red area in Figure 7-18-5).
–
Caution Alerts: alerts which require flight crew awareness. Subsequent corrective action will normally be necessary. This alert region continues after the warning region (farther from the helicopter, see amber area in Figure 7-18-5).
–
ITI (Imminent Terrain Impact) Alerts: ITI alerts are calculated even farther from the helicopter than caution alerts (see grey area in Figure 7-18-5). When terrain with an elevation significantly above the current helicopter altitude is present along the projected flight path, the ITI provides an anticipated terrain alert so that a standard vertical avoidance manoeuver can safely clear the terrain far ahead.
PY
N
O
T
C
O
N TR
O
LL
ED
–
TI
ITI Additional Look Ahead Distance
ITI
Protection envelope for level flight and climb
R
U
C
Fig. 7-18-5
Caution
Terrain Clearance Buffer
O N
O N
Warning
LY
BKD2_FLH_0098_R
–
Warning Look Ahead Distance
C
O
Caution Look Ahead Distance
R
IN
ST
In NORMAL mode, the caution alert shall normally be triggered at least 22 seconds and a warning alert at least 12 seconds of flight time before the projected impact.
FO
In LOW ALTITUDE mode, the caution alert shall normally be triggered at least 15 seconds and a warning alert at least 8 seconds of flight time before the projected impact. During a descent, the warning/caution time will decrease to a value that allows the pilot to pull-up to level flight above the required clearance threshold.
MANUFACTURER’S DATA Rev. 9
7 – 18 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DESCRIPTION OF SYSTEMS
Look Ahead Caution Distance Look Ahead Warning Distance Look Ahead Caution Time X Vertical Speed
LL N TR
O
BKD2_FLH_0099_R
Caution
ED
Vertical Buffer
Warning
Protection envelope for during descent
C
O
Fig. 7-18-6
O
T
The FLT.A alert is automatically inhibited if:
PY
N
– Groundspeed is < 10 kt
C
O
– Aircraft is in OEI (real or training) and IAS is below VTOSS
LY
–
– Rad–Alt is < 10 ft
O N
– In the immediate vicinity (< 0.25 NM) of an airport or heliport.
FO
R
IN
ST
R
U
C
TI
O N
The warning boundaries of the FLTA are progressively reduced when the aircraft is operated at low speed (below 40 kt), at low altitude (below 500 ft), and near airports or heliports ( 35 ft
Fig. C7
OEI Continued Takeoff Profile (surface level or elevated heliport) APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
C.3.3.
SURFACE LEVEL OR ELEVATED HELIPORT – BALKED LANDING WITH ONE ENGINE INOPERATIVE PRIOR TO LDP The following procedures are to be used if the decision is to balk the landing: Procedure 1. Collective lever
– Adjust to 30sec Power
2. Airspeed
– Accelerate to VTOSS (45 KIAS)
3. Climb – Initiate with VTOSS After positive climb is established, latest when the OEI 30sec counter flashes: – Select
5. Upon reaching 200 ft AHE
– Accelerate to VY
6. Collective lever
– Adjust to OEI MCP (latest when OEI 2min counter flashes)
7. Climbout
– Continue with VY to 1000 ft AHE or desired flight altitude
O N
– Perform
PY
8. Single engine emergency shutdown 9. LAND AS SOON AS PRACTICABLE
T
C
O
N TR
O
LL
ED
4. 2min power (pb on collective)
C
O
NOTE D Correct application of the procedure ensures a minimum ground clearance of 35 ft.
O N
LY
–
D When balking the landing, turns with up to 10_ of bank are permitted. The maximum heading change during balked landing procedure should not exceed 45_.
U
ONE ENGINE INOPERATIVE PRIOR TO LDP
FO BKD2_FLH_0034_R
ACCELERATE TO VTOSS (45 kt)
POWER RATING
CLIMB WITH VTOSS
VTOSS > 35 ft
Fig. C8
APPROVED Rev. 4
2 min.
LDP 20 KIAS 130 ft AHE R/D 300 ft/min
R
IN
ST
R
30 KIAS 200 ft AHE
C
TI
O N
30 sec POWER RATING
OEI Balked Landing Profile (surface level or elevated heliport)
9.1-1 – C9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
C.3.4.
SURFACE LEVEL OR ELEVATED HELIPORT – SINGLE ENGINE FAILURE DURING LANDING AFTER LDP The following procedure can be applied if an engine failure occurs prior to LDP and a helipad landing is ensured. Procedure
– Adjust to 30 sec power or below
ED
1. Collective lever
O
LL
Before touchdown: – Establish
3. Collective lever
– Raise to cushion landing
O
N TR
2. Landing attitude
T
C
After touchdown:
– Lower to full down
N
O
4. Collective lever
– Neutral position; observe mast moment limits
O
PY
5. Cyclic stick
– Perform
LY
–
C
6. Engines shutdown
TI
O N
O N
30 sec POWER RATING AS REQUIRED
FO
R
IN
ST
R
U
C
LDP 20 KIAS 130 ft AHE R/D 300 ft/min
SINGLE ENGINE FAILURE AFTER LDP
BKD2_FLH_0035_R
INCREASE COLLECTIVE PITCH
Fig. C9
9.1-1 – C10
OEI Continued Landing Profile (surface level or elevated heliport)
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
C.4.
NORMAL PROCEDURES
C.4.1.
SURFACE LEVEL OR ELEVATED HELIPORT – TAKEOFF – Headed into the wind as far as possible (observe obstacles)
Pre–takeoff check
– Perform
Altimeter/Radar altimeter
– Set
LL
ED
Takeoff flight path
N TR
O
For VTOL operation to or from elevated heliport or in the case of a radar altimeter failure, the barometric altimeter is to be used as source for LDP/TDP identification as follows:
C
O
If VTOL operation from elevated heliport:
N
O
T
Set the barometric altimeter for TDP identification by using the following procedure:
O
Reading the altimeter with high power setting on ground or during hover in ground effect will lead to erroneous results.
LY
–
C
NOTE
PY
1. Aircraft on MTLS with collective fully down.
O N
2. Set altimeter to QNH or QFE and read the helipad altitude.
O N
3. Determine the indicated TDP height on baro altimeter by adding 50ft to the common TDP height of 130ft (130ft + 50ft = 180ft).
Continued
FO
R
IN
ST
R
U
C
TI
4. The TDP altitude can be set as Decision Altitude limit, if desired.
APPROVED Rev. 0
9.1-1 – C11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
Hover
– 4-ft skid height above heliport center
VMS page
– Select – Check aircraft weight is below maximum VTOL weight.
Takeoff check
– Perform
Rearward hover
– Hover aft approx. 10 ft; “H” - sign of heliport in sight
Rearward climb
– Initiate
O
LL
ED
– max. 300 fpm rate of climb and maintain takeoff area in sight (see Fig. C11 and Fig. C12)
N TR
– Note position of “blue line” – Adjust to Takeoff Power simultaneously
Pitch attitude
T
C
Collective lever
O
O
When TDP is reached:
N
– Nosedown accelerate to VY
PY
At VY:
C
O
Collective lever
– Continue to desired altitude
O N
LY
–
Climbout
– Reduce to AEO MCP
ST
R
U
C
TI
O N
TAKEOFF POWER
FO
R
IN
ACCELERATE TO VY
TDP 130 ft AHE
BKD2_FLH_0036_R
CLIMB WITH HOVER POWER plus 0.5 – 1.0 FLI (~ 300 ft/min)
MAINTAIN TAKEOFF AREA IN SIGHT
HIGE 4 ft HOVER 10 ft REARWARD
9.1-1 – C12
Fig. C10
Vertical Takeoff Profile (surface or elivated heliport) APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
Heliport Sight Picture at 130 ft AHE (TDP) surface level heliport
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
Fig. C11
Fig. C12 APPROVED Rev. 0
Heliport Sight Picture at 130 ft AHE (TDP) elevated heliport
9.1-1 – C13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
C.4.2.
SURFACE LEVEL OR ELEVATED HELIPORT – LANDING Prelanding check
– Perform
Landing approach
– Initiate 40 KIAS at 300 ft AHE, and plan to arrive at LDP (see fig. C13 to fig. C15).
Approach airspeeds can be increased by half of the wind speed.
NOTE
After passing LDP: – Decrease slowly to arrive at a 4-ft hover above landing point
Slow vertical descent
– Initiate to touchdown
LL
ED
Speed
N TR
O
After landing: Cycli stick
– Neutral position
N
O
T
C
O
– Press TRIM REL sw
C –
If VTOL operation to elevated heliport:
O
PY
For VTOL operation to or from elevated heliport or in the case of a radar altimeter failure, the barometric altimeter shall be used as source for LDP identification, as follows:
O N
LY
Set the barometric altimeter for LDP identification by using the following procedure:
O N
1. In level flight, set altimeter to QNH or QFE of the helipad.
U
C
TI
2. When QNH is used, add 200 ft to the known helipad elevation to obtain the LDP altitude. If QFE is used, the LDP altitude is 200 ft.
IN
As approach guide points, 40 kt and 170 ft above LDP and 30 kt and 70 ft above LDP can be used.
FO
R
NOTE
ST
R
3. The LDP altitude can be set as a Decision Altitude, if desired.
9.1-1 – C14
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
POWER AS REQUIRED
APPROACH GUIDE POINTS
30 KIAS 200 ft AHE R/D 300 ft/min
LDP 20 KIAS 130 ft AHE R/D 300 ft/min
C
O
BKD2_FLH_0037_R
N TR
O
LL
ED
40 KIAS 300 ft AHE
O
T
Vertical Landing Profile (surface or elevated heliport)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
Fig. C13
APPROVED Rev. 0
9.1-1 – C15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
O
PY
N
O
T
C
O
N TR
O
LL
ED
VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
Heliport Sight Picture at 130 ft AHE (LDP) - surface level heliport
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
Fig. C14
Fig. C15
9.1-1 – C16
Heliport Sight Picture at 130 ft AHE (LDP) - elevated heliport APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
C.5.
PERFORMANCE DATA
C.5.1.
TAKEOFF PERFORMANCE
C.5.1.1. Obstacle clearance For Cat A VTOL takeoff the standard TDP height is 130 ft AHE. For heliports with obstacles in the clearway or in the takeoff flight path, an extended TDP between 130 ft and 210 ft can be selected.
LL
ED
For a given TDP height, the minimum safe obstacle clearance can be determined as follows (using Table C1 for key data) : Unrestricted rearward obstacles: Obstacles with unrestricted height are permitted at a distance of 17 m behind the rearward takeoff distance point. This includes a 35 ft / 10 m horizontal clearance between aircraft and obstacle.
–
Rearward obstacles: Obstacles may be present below an imaginary line drawn from a point at 0 ft and 14 m behind the center of the MTLS through a point at 30 ft and 50 m behind the center of the MTLS. Obstacles more than 50 m behind the center of the MTLSshall be located below an imaginary line drawn between a point 50 m and 30 ft and a point 82 m and 100 ft behind the center of the MTLS.
–
Forward obstacles: In takeoff direction, a clearway shall be available between the MTLS and the end of the continued takeoff distance. Within this clearway, obstacles with a maximum height equal to the “minimum height“ in the Table below minus the obstacle clearance height (normally 35 ft) are permitted. The continued takeoff distance is measured from the center of the MTLS.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
–
APPROVED Rev. 0
9.1-1 – C17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
C.5.1.2. Takeoff Flight Path TDP
HEIGHT ACHIEVED VTOSS
35 ft
C T
N C
O
PY
50 m
17 m SAFETY AREA
CLEARWAY
O
MTLS
14 m
SEGMENT I
Continued Takeoff Flight Path
FO
R
IN
ST
R
U
C
TI
O N
Fig. C16
CONTINUED TAKEOFF DISTANCE
O N
LY
REARWARD TAKEOFF DISTANCE
–
BKD2_FLH_0181_R
O
N TR
O
MINIMUM HEIGHT
30 ft
ED
35 ft
LL
OBSTACLE CLEARANCE
9.1-1 – C18
APPROVED Rev. 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
C.5.1.2.1.
Modified takeoff flight path Up to 12000 ft DA or 12000 ft PA, whichever is less
[ft]
Height achieved VTOSS *) [ft]
Continued takeoff distance [m]
[ft]
[m]
130
50
35
40
190
140
54
45
50
186
150
58
55
60
160
62
65
70
170
66
75
80
174
180
70
85
90
170
190
74
95
100
166
200
78
105
110
162
210
82
115
120
158
ED
Minimum height
LL
Rearward takeoff distance
N
O
T
C
O
N TR
O
TDP height
182 178
O
PY
*) Height at which VTOSS and a positive rate of climb is achieved. Distances and Heights with Variable TDP (heliport - surface level / elevated)
LY
–
C
Table C1
If the barometric altimeter is used as source for TDP identification add 50ft to the TDP height given in Table C1 in accordance with the procedure described in subparagraph C.4.1.
C
TDP height for vertical takeoff
ST
R
Determine:
(see Fig. C16 and Table C1)
U
EXAMPLE:
TI
O N
O N
NOTE
Obstacle height . . . . . . . 50 ft Obstacle distance . . . . . . 50 m (in direction of departure)
FO
R
IN
Known:
Solution: 1. Add minimum clearance as defined by operational rules (e.g. 35 ft) to known obstacle height (50 ft) to obtain minimum height for takeoff (85 ft). 2. Using table C1, select for the derived minimum height (85 ft) the corresponding TDP height = 180 ft.
APPROVED Rev. 3
9.1-1 – C19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
Above 12000 ft DA or 12000 ft PA and up to 16000 ft DA or 15000 ft PA, whichever is less Continued takeoff distance [m]
[ft]
[m]
140
54
35
40
220
150
58
45
50
216
160
62
55
60
212
170
66
65
70
208
180
70
75
80
190
74
85
90
200
78
95
100
210
82
105
ED
[ft]
Height achieved VTOSS *) [ft]
204
LL
Minimum height
O
Rearward takeoff distance
N TR
TDP height
110
200 196 192
O
N
PY
If the barometric altimeter is used as source for TDP identification add 50ft to the TDP height given in Table C1 or Table C2 in accordance with the procedure described in subparagraph C.4.1.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
NOTE
Distances and Heights with Variable TDP (heliport - surface level / elevated)
O
Table C2
T
C
O
*) Height at which VTOSS and a positive rate of climb is achieved.
9.1-1 – C20
APPROVED Rev. 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
C.5.1.3. OEI Climbout Flight Path The OEI climbout flight path (Fig. C17) begins when VToss is reached and a positive rate of climb has been established. The OEI climbout path is divided in: –
Segment I OEI climb from the ”Height achieved VTOSS” (see Table C1) to 200 ft with VTOSS and 2-min Power. Segment I climb performance data are presented in Subsection A, Fig.A2 to Fig. A7. Acceleration from Segment I to Segment II
ED
–
–
N TR
O
LL
Acceleration in level flight with 2 min Power. The distance required for horizontal acceleration from VTOSS to VY is presented in Fig. C18 Segment II
T
C
O
OEI climb from 200 ft to 1000 ft with VY and Max Continuous Power. Segment II climb performance data are presented in Subsection A, Fig. A8 to Fig. A13.
C
O
PY
N
O
For obstacle clearance, turns are permitted in accordance with section A.5.4.1.
LY
100 ft/min
–
OEI 2 min. POWER RATING
OEI MCP RATING
MINIMUM RATE OF CLIMB 150 ft/min
O N U
C
TI
O N
ACCELERATION TO VY IN LEVEL FLIGHT 965 ft
200 ft
R
CLIMB WITH VTOSS
200 ft
IN
ST
HEIGHT ACHIEVED VTOSS
1000 ft
CLIMB WITH VY
165 ft
BKD2_FLH_0176_R
FO
R
165 ft
CONTINUED TAKEOFF DISTANCE
SEGMENT I
Fig. C17
APPROVED Rev. 3
ACCELERATION TO VY
SEGMENT II
OEI climbout flight path (VTOL)
9.1-1 – C21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
EXAMPLE:
(see Fig. C18)
Determine:
Acceleration distance
Known:
OAT
25°C
Pressure altitude
5000 ft
Headwind component
40 kt
For calculation 50% of the headwind component.
20 kt
ED
Acceleration distance required = 375 m
Solution:
1. Enter chart at known OAT (25_C).
O
LL
2. Move vertically upwards to to known pressure altitude (5000 ft).
N TR
3. From point of intersection move horizontally right to the wind reference line of the right chart.
PY
N
O
T
C
O
4. From point of intersection move downwards and read acceleration distance = 375 m
U
C
TI
O N
O N
LY
–
C
O
16000 ft DA
BK117D2534_1_r2
FO
R
IN
ST
R
Headwind (unfactored) – kts
–50
–40
–30
–20
–10
0
10
20
30
40
50
200
400 600 800 1000 Acceleration Distance – m
NOTE: This chart is also valid if Inlet Barrier Filter (IBF), FMS 9.2–5 is installed
Fig. C18
9.1-1 – C22
Acceleration distance VTOSS to VY (VTOL) APPROVED Rev. 3
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To determine the optimal TDP for a takeoff with obstacles beyond the continued takeoff distance, proceed as follows: 1. Determine the available obstacle clearance using the standard TDP of 130 ft. If high obstacles are present, this clearance may not be sufficient. 2. Determine the height increase that would be required to safely clear the obstacle. A safe clearance height (e.g. 35 ft) shall be included in the consideration.
ED
3. Add this required height increase to 40 ft and find the required height at VTOSS from Table C1. At this height, read the TDP height.
Since the continued takeoff distance reduces when the TDP height is increased (see Table C1), the calculation should be repeated with the modified continued take–off distance, until the optimal TDP height is obtained.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
NOTE
LL
Using the new TDP height, verify the rearward takeoff distance is available.
O
4.
APPROVED Rev. 3
9.1-1 – C23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
C.5.2.
LANDING PERFORMANCE
C.5.2.1. Obstacle clearance For Cat A VTOL landing, the minimum obstacle clearance heights and distances are shown in Fig. C19. For landing at a helipad where obstacles are located in the takeoff or climb–out flight path for a balked landing, the LDP can be increased to:
ED
LDP mod . . . . . . 170 ft / 25 KIAS
O
N TR
Approach airspeeds can be increased by half of the wind speed. Minimum height and obstacle clearance data for the takeoff and climb-out flight path can be calculated using the data from table C1 for a TDP of 170 ft and 210 ft respectively.
N
O
T
C
O
NOTE
LL
LDP mod . . . . . 210 ft / 30 KIAS
O C O N
LY
–
35 ft
PY
LDP* 20 KIAS 130 ft
35 ft
82 m
R
15 ft
R
IN
ST
30 ft
FO
BKD2_FLH_0179_R
U
C
TI
O N
100 ft
50 m
27.5 m
14 m
MTLS MTLA
Fig. C19
Landing flight path obstacle clearance
C.5.2.2. OEI Landing distance from 25 ft AHE to a complete stop Elevated heliports . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 m
9.1-1 – C24
APPROVED Rev. 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
C.6.
MASS AND BALANCE No change in the basic Flight Manual data.
C.7.
SYSTEM DESCRIPTION No change in the basic Flight Manual data.
HANDLING, SERVICING AND MAINTENANCE
ED
C.8.
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No change in the basic Flight Manual data.
MANUFACTURER’S DATA APPROVED Rev. 3
9.1-1 – C25
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
T
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VTOL (1) – SURFACE LEVEL OR ELEVATED HELIPORTS
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O N
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N
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Intentionally left blank
9.1-1 – C26
APPROVED MANUFACTURER’S DATA Rev. 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
FMS
9.1–2
SUPPLEMENT FOR
C
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OPERATION WITH OPENED/REMOVED DOORS
Approved by EASA:
EASA approval no.: 10055971
FO
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ST
R
Date: DEC 11, 2015
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This supplement shall be attached to the BK 117 D-2 Flight Manual (Section 9.1) when operating with OPENED AND/OR REMOVED DOORS.
APPROVED Rev. 0
9.1-2 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”. LEP – approved (part 1): App.
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LOG OF REVISION
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FIRST ISSUE
IN R
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(see entry below)
FO
REVISION
(SEE PAGE 9.2–1)
ST
ORIGINAL
REVISION 1
Date: FEB 01, 2017
9.1-2 – 2
Approved by EASA
EASA approval no.: 10060869 APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
1.
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
1.1.
INTRODUCTION For special missions the helicopter is approved to be operated with Opened or removed cockpit door(s) (in the following named hinged doors),
–
Opened or removed sliding door(s) (also applicable for the doors mentioned in the FMS 9.2-19 “Sliding door jettisoning”)
–
Removed rear clamshell doors.
N TR
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LIMITATIONS
2.1.
CONFIGURATION REQUIREMENTS
N
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2.
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For operation with opened sliding doors, the sliding door locking device must be installed and the cockpit curtain must be removed.
LY
–
For operation with opened hinged doors, the hinged door locking device must be installed and the cockpit curtain must be removed.
O N
O N
Use of EXTENSION position is only allowed when the special hinged door locking device P/N B520M4023051 and/or B520M4022051 and/or B520M4041052 and/or B520M4042052 and/or B520M4007052 is installed.
ST
KINDS OF OPERATION
IN
2.2.
R
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Flying without clamshell doors is only allowed when hinged and sliding doors are removed as well.
FO
R
Category A takeoff/landing is generally prohibited when flying with opened/removed door(s). If required for operational reasons, doors may be opened during Cat A VTOL: –
Before reaching the TDP during takeoff (door must be closed latest after reaching the TDP).
–
After reaching the LDP during landing.
Flights in IMC are prohibited when flying with opened/removed door(s). For operation with opened or removed doors, exposure to precipitation shall be avoided or minimized.
APPROVED Rev. 0
9.1-2 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
2.3.
AIRSPEED LIMITATIONS
Sliding door(s) Opening/Closing
VNE
50
50
80 or VNE*
50
50
Spoiler pos.: Open 1) Extension pos.:
120 or VNE* rwd flt 15 kts
80 or VNE* rwd flt 15 kts
120 or VNE* rwd flt 15 kts
Opening/
30
30
30 rwd flt 30 kts VNE
30 rwd flt 30 kts 50
Closed
Both open
1)
Closed
Spoiler pos.:
N TR
O
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Closing
C
T
30
30 rwd flt 30 kts 50
N
Extension pos.: Open 1) Both removed
O
Closing
O
Hinged d door(s (s)
Opening/
PY
Sliding door(s) One removed
50
LY
O N
50 rwd flt 15 kts
C
50
VNE
50
50
50 rwd flt 15 kts
120 rwd flt 15 kts
30
30
U R ST
Opening/ Closing
TI
Spoiler pos.: Open 1) Extension pos.:
Both removed
30
IN
Hinged d door(s (s)
Closing
O N
Spoiler pos.: Opening/
the other closed
–
50
Closed
1)
C
the other closed
O
One open
FO
R
Extension pos.: 30 30 30 Open 1) rwd flt 30 kts rwd flt 30 kts rwd flt 30 kts Both removed 50 50 VNE 2) All values are in KIAS. VNE*: The given limitation or the basic aircraft VNE as shown on the airspeed indicator, whichever is less. 1) open sliding door(s) and hinged door(s) have to be secured. The limitations are valid for fully open and half-open sliding doors. 2) also valid with clamshell doors removed (flying w/o clamshell doors is only allowed when hinged doors and sliding doors are also removed)
9.1-2 – 4
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
NOTE
For flight with removed doors, the following airspeed and altitude corrections must be applied: IAS 100 kt
no correction
IAS > 100 kt
reduce IAS by 3 kt, and reduce indicated altitude by 1%
Autorotation ( > 80 kt) 2.3.1.
reduce indicated altitude by 1%
Airspeed limitation with drip tray (water capturing cabin floor) installed
SIDESLIP LIMITS
O
2.4.
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In addition to the limits of chapter 2.3, the maximum forward airspeed (VNE) with open doors and drip tray installed is 50 kts.
N TR
Sideslip is limited to $1 bar for flights with open, half open or removed door(s).
O
OCCUPANTS
N
2.5.
T
C
O
Sideslip is limited to $1/2 bar for flights with hinged door in spoiler position above 100KIAS.
PLACARDS
LY
2.6.
–
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All occupants, including the flight crew, must be seated with their seat belts fastened, or properly secured with an approved harness to an approved cabin attachment point (see Section 7) during flight with open, half open or removed door(s).
O N
Placard:
SCHIEBETÜRVERRIEGELUNG SLIDING DOOR LOCKING DEVICE
R
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O N
SCHIEBETÜRVERRIEGELUNG SLIDING DOOR LOCKING DEVICE
ST
INTERMEDIATE+OPEN POSITION
OF FLIGHT FLUGRICHTUNG
OPEN POSITION
OPEN POSITION
SCHIEBETÜR OFFEN
SCHIEBETÜR OFFEN
DIRECTION OF FLIGHT FLUGRICHTUNG
INTERMEDIATE+OPEN POSITION SCHIEBETÜR HALBOFFEN+OFFEN
R
IN
SCHIEBETÜR HALBOFFEN+OFFEN
DIRECTION
FO
Location: RH and LH Sliding Door, near door locking lever Placard:
ACHTUNG: FLUG MIT OFFENEN TUEREN NUR GEMAESS FLH WARNING: FLIGHT WITH OPEN DOORS ONLY ACC. TO FLM Location: H/C doors APPROVED Rev. 1
9.1-2 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
EMERGENCY AND MALFUNCTION PROCEDURES DOOR OPEN message will be present if doors are open or removed and should be ignored.
NORMAL PROCEDURES
4.1.
PREFLIGHT CHECK Loose objects, such as navigation equipment etc.
manuals,
maps, – Fixed and secured
N TR
Loose objects, which are not essential for the – Removed flight
ED
4.
LL
NOTE
O
3.
Seat belts
– Fastened
C
O
If takeoff with open door(s) is intended:
– Check secured (by means of an certified locking device)
N
O
T
Opened door(s)
O
THE OPERATOR SHALL NOT RELEASE THE SLIDING DOOR WHILE OPENING OR CLOSING, UNTIL THE DOOR IS SECURED BY MEANS OF THE FIXATION DEVICE OR COMPLETELY CLOSED AND LOCKED.
O N
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CAUTION
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OPERATION
C
4.2.
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NOTE D During hover and low speed, where the spoiler or extension position are not required for the operation, it is recommended to keep the hinged doors closed to preclude excessive wear.
ST
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D In accordance with pilot’s instructions, one or both sliding door(s) may be opened by a crew member in the cabin.
FO
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D For single pilot operations it is advised not to operate the hinged doors close to the ground at low airspeed.
The door(s) may be opened/closed on ground or inflight. If opening or closing inflight is intended, proceed as follows: All crew and passengers
– Seat belts fastened/secured to approved attachement point
Objects in cockpit/cabin
– No loose items
"
Opening hinged door(s):
Hinged door locking device
– Turn safety knob 90_
Hinged door
– Open until safety knob is latched
9.1-2 – 6
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
"
Closing hinged door(s):
Hinged door locking device
– Pull safety knob and turn it 90_
Hinged door
– Close and lock
"
Opening sliding door(s) – Pull and turn locking knob 90_
Sliding door
– Open door and slide aft until knob locks in intermediate or full open position.
Closing sliding door(s)
LL
"
ED
Sliding door locking device
– Hold door at door handle
Sliding door locking device
– Pull and turn locking knob 90_
Sliding door
– Slide door forward until closed, lock with door handle.
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Sliding door
APPROVED Rev. 1
9.1-2 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
5.
PERFORMANCE DATA
5.1.
AEO AND OEI MAXIMUM RATE OF CLIMB
5.1.1.
Rate of climb reduction for climb with VY All results obtained from the appropriate R/C diagrams, contained in section 5 of the basic Flight Manual, must be reduced as follows:
EFFECTIVITY
Hinged doors in spoiler position and sliding doors open:
LL
ED
Helicopter gross mass below 2600 kg . . . . . . . . . . . . . . . . . . . . . . . . . . . . Subtract 90 ft/min
O
Helicopter gross mass above 2600 kg and below 3200 kg . . . . . . . . . . Subtract 70 ft/min
O
Hinged doors, sliding doors and clamshell doors removed:
C
EFFECTIVITY
N TR
Helicopter gross mass 3200 kg and above . . . . . . . . . . . . . . . . . . . . . . . . Subtract 55 ft/min
O
T
Helicopter gross mass below 2600 kg . . . . . . . . . . . . . . . . . . . . . . . . . . . . Subtract 45 ft/min
PY
N
Helicopter gross mass above 2600 kg and below 3200 kg . . . . . . . . . . Subtract 35 ft/min
–
The rate of climb reduction values are independent of power rating.
Rate of climb reduction for climb with V= 50 kts
O N
5.1.2.
LY
NOTE
All
O N
EFFECTIVITY
C
O
Helicopter gross mass 3200 kg and above . . . . . . . . . . . . . . . . . . . . . . . . Subtract 30 ft/min
C
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For flight with certain door configurations, an airspeed limit of 50 KIAS applies.
IN
AEO–MCP and AEO–TOP
R
EFFECTIVITY
ST
R
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Compared to the climb performance at VY, the following maximum rate of climb reductions apply:
FO
Helicopter gross mass below 2600 kg . . . . . . . . . . . . . . . . . . . . . . . . . . . Subtract 150 ft/min Helicopter gross mass above 2600 kg and below 3200 kg . . . . . . . . . Subtract 175 ft/min Helicopter gross mass 3200 kg and above . . . . . . . . . . . . . . . . . . . . . . . Subtract 250 ft/min EFFECTIVITY
OEI–MCP
Helicopter gross mass below 2600 kg . . . . . . . . . . . . . . . . . . . . . . . . . . . Subtract 100 ft/min Helicopter gross mass above 2600 kg and below 3200 kg . . . . . . . . . Subtract 250 ft/min Helicopter gross mass 3200 kg and above . . . . . . . . . . . . . . . . . . . . . . . Subtract 375 ft/min EFFECTIVITY
9.1-2 – 8
All APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
6.
MASS AND BALANCE
6.1.
FLIGHT WITH REMOVED DOORS Refer to equipment list entries in section 6 of the basic flight manual.
6.2.
FLIGHT WITH OPEN SLIDING DOORS
7.1.
OPEN CABIN DOORS
LL
SYSTEM DESCRIPTION
N TR
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7.
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The C.G. shift due to opening of the sliding doors does not need to be considered.
OPEN
SECURED
FO
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The sliding cabin doors are designed to be opened and closed in flight when the sliding door locking device (see Figure 1) is installed. The doors can be opened and secured in an intermediate (half–open) or fully open position.
Fig. 1
Sliding door locking device
To be able to operate the helicopter at higher speeds with open doors, the hinged cockpit door(s) can be set to the spoiler position (Figure 2) if the hinged door locking device is installed. In this case, the hinged door(s) must be set to the spoiler position before the sliding door(s) are opened. When closing the door(s), the sliding door(s) shall be closed before the hinged door(s).
APPROVED MANUFACTURER’S DATA Rev. 0
9.1-2 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
Hinged door in spoiler position and associated locking device position
R
COCKPIT DOORS EXTENSION POSITION
ST
7.2.
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O N
Fig. 2
O N
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The speed limitations while opening/closing the sliding door(s) and for flight with the sliding door(s) in a secured half or fully open position shall be observed. Exceeding this maximum speed may result in excessive forces or harmful vibrations.
FO
R
IN
To allow the pilot to look down through the opened doors at low speed (e.g. during external load operations), the cockpit doors can be set to the extension position (Figure 3) if the locking device P/N B520M4023051 and/or B520M4022051 and/or B520M4041052 and/or B520M4042052 and/or B520M4007052 is installed. The hinged door locking device features a mount which enables the operator to safely secure the door in the extension position. This mount is designed to automatically catch the door as soon as the locking device bolt runs over the locking point.
9.1-2 – 10
APPROVED MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
Cockpit door set to the extension position and hinged door locking device allowing the door to be set to spoiler and extension position
REMOVED DOORS
ST
7.3.
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Fig. 3
O N
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The hinged cockpit doors can be operated single–handedly by the pilot or copilot. The locking device for the spoiler and extension position is attached to the gas–pressure spring of the door. The design does not affect emergency egress of the cockpit, as the doors attachment in general is not altered.
FO
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IN
If operations require the doors to be open without any additional airspeed restrictions, it is possible to remove the door(s) as follows: – Both cockpit door(s) removed – All cockpit and sliding cabin doors removed – All cockpit, cabin, and clamshell doors removed Other combinations of removed and open doors are possible with the restrictions given in the limitations section of this supplement. For removal and installation of the doors, refer to the maintenance manual.
APPROVED MANUFACTURER’S DATA Rev. 0
9.1-2 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
7.4.
CLAMSHELL DOORS (OPTIONAL)
Clamshell doors with mount and demount hinges
SECURING ECURING POINTS IN THE CABIN (OPTIONAL)
PY
7.5.
N
O
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Fig. 4
C
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The clamshell doors are optionally fitted with the so called “toolless mount and demount hinges“ and a removable damper.
FAILURE TO PROPERLY ATTACH LIFELINES OR PCDS TO THE ATTACHMENT POINTS CAN RESULT IN FATAL ACCIDENTS, WHEN FALLING OUT OF THE HELICOPTER. THE INSTRUCTIONS FOR USE OF THE CABIN ATTACHMENT POINTS SHALL BE STRICTLY FOLLOWED.
O N
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WARNING
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CAUTION D THE CABIN ATTACHMENT POINTS ARE NOT INTENDED AS A MEANS TO SUSTAIN SHOCKLOADS, IN CASE OF PERSONAL FALLING OUT OF THE HELICOPTER. THEREFORE, THE ROPE OR LANYARD USED TO CONNECT TO THE ATTACHMENT POINT OR LIFELINE SHALL ALWAYS BE ADJUSTED TO MINIMUM NECESSARY LENGTH TO PREVENT OPERATING CREW FALLING OUT OF THE HELICOPTER WHEN OPERATING WITH OPEN DOORS. ALTERNATIVELY, A PCDS WITH INTEGRATED ENERGY ABSORBER SHALL BE USED. D THE CABIN ATTACHMENT POINTS CAN NOT EFFECTIVELY PROTECT THE SECURED OCCUPANTS DURING A CRASH LANDING. THEREFORE, ALL PERSONS SHALL BE SEATED WITH THEIR SEAT BELTS FASTENED WHENEVER POSSIBLE, ESPECIALLY DURING TAKEOFF AND LANDING. IN ADDITION, IT IS HIGHLY RECOMMENDED FOR THE PERSONS SECURED TO THE CABIN ATTACHMENT POINTS TO WEAR A PROTECTIVE HELMET. Optionally, several cabin attachment points are available to secure persons or to attach lifelines (safety cables).
9.1-2 – 12
APPROVED MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
Forward cabin attachment point Maximum load: 200 kg
Forward cabin attachment point
N TR
Fig. 5
O
LL
ED
Normal use: Direct attachment of hoist operator or other persons with lanyard or connecting rope.
Maximum load: 200 kg
Normal use: Securing persons entering/leaving the cabin during hoist operations.
Fig. 6
R
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O N
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N
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Door frame lifeline (safety cable):
Door frame attachment points
FO
Cabin (frame 4000/5000) attachment points: (1): Attachment point frame 4000 Maximum load: 200 kg (2): Attachment point frame 5000 Maximum load: 100 kg Normal use: Direct attachment of person(s) with lanyard or connecting rope. Fig. 7
APPROVED MANUFACTURER’S DATA Rev. 0
Cabin frame attachment points
9.1-2 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATION WITH OPENED/REMOVED DOORS
Mid cabin lifeline: Maximum load: 100 kg Typical use: Secure person with rope lanyard to the installed lifeline.
O
Life line attachment points
FO
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Fig. 8
LL
ED
CAUTION: TO AVOID EXCESSIVE LOADS, A LIFELINE WITH A TOTAL LENGTH OF AT LEAST 1055 MM SHALL BE USED.
9.1-2 – 14
APPROVED MANUFACTURER’S DATA Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OEI TRAINING
FMS
9.1–3
SUPPLEMENT FOR
C
O
N TR
O
LL
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OEI TRAINING
–
Due to the nature of its content, this supplement is divided into four separate, related subsections that first present General Data applicable to all training flights and then specific Category A and Category B Operations with data applicable to approved types of operation.
FO
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NOTE
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N
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This supplement shall be attached to the BK 117 D-2 Flight Manual (Section 9.1) when OEI Training is intended.
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971 APPROVED Rev. 0
9.1-3 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OEI TRAINING
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
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LEP – approved (part 1):
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FIRST ISSUE
(see page 9.1-3-1)
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ORIGINAL
REVISION 1 MAR 14, 2016 EASA approval no.: 10057217 REVISION
REVISION 2
Date: DEC 18, 2017
9.1-3 – 2
2
(see entry below)
Approved by EASA
EASA approval no.: 10064108 APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OEI TRAINING
TABLE OF CONTENTS Page GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 4
A.2.
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 4
A.2.1.
Torque limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 4
A.3.
EMERGENCY AND MALFUNCTION PROCEDURES . . . . . . . . . . . . . . 9.1-3 – 5
A.4.1.
OEI Training mode activation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 5
A.4.2.
Reset to normal AEO mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 6
A.5.
PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 6
A.6.
MASS AND BALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 7
A.7.
SYSTEMS DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 7
B.1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 11
B.2.
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 11
B.3.
EMERGENCY AND MALFUNCTION PROCEDURES . . . . . . . . . . . . . 9.1-3 – 11
B.4.
NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 11
C.1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 12
C.2.
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 12
C.2.1.
Altitude limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 12
C.2.2.
Mass limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 12
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A.1.
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C.2.2.1. Mass Limitations with optional equipment installed . . . . . . . . . . . . . . . . 9.1-3 – 12 EMERGENCY AND MALFUNCTION PROCEDURES . . . . . . . . . . . . . 9.1-3 – 13
C.4.
NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 13
C.5.
PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 13
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EMERGENCY AND MALFUNCTION PROCEDURES . . . . . . . . . . . . . 9.1-3 – 18
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D.2.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 15
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D.1.
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C.3.
D.3.
NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 18
D.4.
PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 18
LIST OF FIGURES Fig. A1
Engine control panel – typical installation . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 8
Fig. A2
OEI training mode – indications on VMS . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 8
Fig. A3
OEI training mode – indications on FND . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 9
Maximum Takeoff and Landing Gross Mass for Category A (Clear Heliport) Training . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 16 Fig. D1 Maximum Takeoff and Landing Gross Mass for Category A (VTOL) Training . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1-3 – 19 Fig. C1
APPROVED Rev. 2
9.1-3 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL DATA
A. GENERAL DATA
A.1.
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
For OEI simulation a minimum flight crew of one pilot and one copilot is recommended.
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LIMITATIONS
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A.2.
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NOTE
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The training and demonstration of OEI emergency situations are simulated with the real OEI limitations, the power being shared equally between the two engines (twin engine training).
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D OEI training is prohibited if FADEC REDUNDANCY white advisory or FADEC DEGRADED caution is present on ML.
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D Use of OEI training mode is only allowed with avionics fully operational.
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TORQUE LIMITATIONS
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A.2.1.
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D During OEI Training the air conditioning system (FMS 9.2–12) must be switched OFF.
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The torque limitations of the basic aircraft (2x74% above VY+22 kt) also apply to the OEI training mode. Therefore, use of the OEI 30s limit (150% torque, which corresponds to 2x75% torque in training mode) is limited as follows:
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OEI 30s limit above VY+10 kt. . . . . . . . . . . . . . . . . . . . . . . . max. 12 sec NOTE
9.1-3 – 4
An exceedance will be recorded each time more 2x74% torque are used above VY+10 kt for longer than 12 seconds. A limit exceedance may require maintenance actions.
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL DATA
A.3.
EMERGENCY AND MALFUNCTION PROCEDURES
TRAINING ABORTED and audio tone
NORMAL PROCEDURES
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A.4.
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Refer to Sect. 3 of the basic Flight Manual.
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Training mode alternates automatically between engine 1 and engine 2.
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OEI TRAINING MODE ACTIVATION
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A.4.1.
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NOTE
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(EXAMPLE SHOWN FOR ENG 2 IN TRAINING MODE, SEE FIG. A2 AND A3)
– Push
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Left yaw motion occurs during change of NR governing from AEO to OEI.
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NOTE
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TRAINING pb
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Audio tones
– PWR SPLIT audio tone upon training mode activation – Possibly LOW NR audio depending on power setting
tone,
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Indications on FND:
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TRAINING
ENG2
– OEI presentation – – Topping triangle 30 sec (default)
Indications on VMS: Training engine (ENG2)
– Pointers (TQ, TOT, N1) zero
“OEI” engine (ENG1)
– OEI presentation including OEI limits
Digital values (both engines)
– Real values
Engine instruments
APPROVED Rev. 1
9.1-3 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL DATA
Additional indications: NR/N2
– Real NR values
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NOTE D Due to engines being limited to 2x75% TQ or equivalent N1/TOT limits for 30 sec topping at higher altitudes, NR droop may be encountered upon training mode activation if actual power setting exceeds these values. In this case the collective should be adjusted to maintain NR. Whilst operating in AEO at low density altitude (OEI 30 sec power limited by torque), the AEO 30 sec power line (”blue line”) provides an ideal indication to determine available OEI power. If – prior to TRAINING MODE activation – the collective is above the “blue line”, an NR droop will be encountered. If – prior to TRAINING MODE activation – the collective position is at, or below the “blue line”, no collective action will be required to achieve and maintain nominal OEI NR.
RESET TO NORMAL AEO MODE
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D At high density altitude, where the OEI 30 sec power is limited by N1/TOT, the collective position for the ”blue line” (which is based on the available performance of the actual engines) and the collective position at the OEI 30 sec TRAINING limit (which is calculated for a minimum rated engine with IBF) may differ noticeably. Therefore, when failing an engine at the ”blue line” at high altitude, the pilot may have to lower the collective to maintain NR.
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TRAINING pb
– Normal AEO indication
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All MFDs
– Push
Slight yaw motion may occur upon automatic or manual OEI TRAINING MODE abort.
NOTE
An automatic training mode abort occurs under following circumstances:
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NOTE
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D FADEC malfunctions i.e. FADEC DEGRADED or FADEC FAIL D Real engine failure D NR droop t91% or 12% below nominal NR
A.5.
PERFORMANCE DATA Refer to section C and D of this supplement.
9.1-3 – 6
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL DATA
A.6.
MASS AND BALANCE No change in the basic Flight Manual data.
A.7.
SYSTEMS DESCRIPTION The OEI training mode is implemented to perform realistic OEI training. This engine training mode is based on a twin engine training concept.
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1. FADEC governing change from AEO to OEI governing law
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The training mode is accessed through a push button on the engine control panel (see Fig. A1). Activation – indicated by a green light – starts an OEI simulation of the engine failure behavior, whereby both engines remain in AEO mode. The simulation consists of:
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2. FADEC engine topping at desired topping value (default 30 sec topping) 3. OEI indication on VMS and FND (FLI)
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4. Power split and – if NR droops below threshold values – low NR audio warnings
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5. NR law for OEI
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The training mode alternates between engine 1 and engine 2 during subsequent activations.
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The combined power of both engines in training mode will simulate the maximum assured power available in the 30 sec / 2 min rating for an engine with zero power margin (minimum specified engine power) and an IBF installed. Topping functions automatically limit the 30 sec and 2 min power. The training mode is designed in a way that engine acceleration/deceleration and NR governing reflects a real OEI situation. The power will be equally distributed between both engines.
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If the engine is operated within the normal NR range necessary for training, the torque topping is set at a constant value of approx. 2x 75% (30 sec), respectively 2x 65% (2 min). At higher altitudes, the topping is set to the values (N1/TOT) equivalent to represent OEI 30 sec / 2 min power according to given altitude/temperature for the worst possible configuration, i.e. Inlet Barrier Filter.
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If, during OEI training mode operation, the RPM decreases down to 91% NR, or to 12% below nominal NR, the training mode is automatically deactivated. The rotorspeed is increased to its nominal (reference) value in a controlled manner while the torque of the engines is limited to an acceptable level (approximately 2x 95%), in order to avoid excessive torque and rotorspeed overshoots. The caution TRAINING ABORTED is indicated on the ML. In case of real engine or FADEC failure or FADEC malfunctions during OEI training mode operation, the training mode is automatically aborted and the remaining engine automatically returns to normal AEO or OEI operation. At any time, the OEI training mode can be immediately aborted manually, by pushing on the lit (activated) TRAINING push button on the engine control panel. While the FLI simulates OEI, the real engine parameters are available as digital values on the VMS page (see Fig. A2).
APPROVED MANUFACTURER’S DATA Rev. 2
9.1-3 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL DATA
ENG I I D L E
BKD2_FLH_0017_R
ENG II
FADEC TRAINING FADEC EMER EMER VENT
VENT
FLIGHT
ON
OFF
I D L E
ON
OFF
OFF
OFF
Engine control panel – typical installation
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Fig. A1
FLIGHT
TRQ
S Y S T
75.0 %
O 88.4 %
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516
54
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80
FUEL Kg
47
MGB OIL B A R
100
G1
G2
FF Kg/h
137
C
WEIGHT & PERFORMANCE TOTAL
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4.5
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137
D A T A
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80
FF Kg/h
ENG OIL B A R
C
ENG OIL B A R
B A R
TOT
670
88.6 %
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HYD
2 h 30 min
BKD2_FLH_0477_R
N1
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N1
B A R
+ C T R S –
T
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685
R C N F
EFB
TRQ
75.0 %
TOT
+ L U M –
3527 kg
AEO HIGE AEO HOGE
3650 kg 3650 kg
CAT A VTOL
3650 kg
OEI 30s HIGE OEI 2min HOGE
3384 kg 3034 kg EPC
Fig. A2
9.1-3 – 8
MISC
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DMAP
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FND
STATUS
96. 7
96. 9 % N2
96. 9 %
WEIGHT
+ B R G –
OEI training mode – indications on VMS
APPROVED MANUFACTURER’S DATA Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) GENERAL DATA
ON
NAVD
VMS
DMAP
ALT
OFF
MISC
NAV
+ C T R S –
CLOCK
IAS
97
T
20
20
10
10
10
10
1 500
5
20
D H
14
40 20
2
13
3
1
12
20
6
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12
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FSD
GPS
–
TRAINING
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ENG2
470 Kg SVS
OAT
+ B R G –
25
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SCT
Fig. A3
OEI training mode – indications on FND
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BKD2_FLH_0460_R
20.0 NM 12 min
DCPL
A C K
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354 1.0 FMS
LFMH + L U M –
15
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21 DTK
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24
N A V
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3
30
1013 200 hPa DH
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33
R N G
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11 600 DA
B A R O
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60
6
D A
16
LL
VY
7
APPROVED MANUFACTURER’S DATA Rev. 1
9.1-3 – 9/(9.1-3 – 10 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) CATEGORY B OEI TRAINING - TAKEOFF AND LANDING
B. CATEGORY B OEI TRAINING - TAKEOFF AND LANDING
B.1.
GENERAL
ED
This subsection provides information necessary for engine failure simulation during Category B takeoff and landing.
LIMITATIONS
B.2.1.
MASS LIMITATION
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B.2.
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EMERGENCY AND MALFUNCTION PROCEDURES
C
B.3.
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For determining the training takeoff and landing gross mass in order to simulate OEI conditions, refer to the diagram of subsection C (Fig. C1).
NORMAL PROCEDURES
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Refer to para A.3. of this supplement.
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Refer to para A.4. Takeoff and landing training procedures must be performed according to the basic Flight Manual, para 4.7 and 4.9.
APPROVED Rev. 1
9.1-3 – 11/(9.1-3 – 12 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) CATEGORY A TRAINING – CLEAR HELIPORT
C. CATEGORY A TRAINING – CLEAR HELIPORT
C.1.
GENERAL This subsection provides information necessary for Category A training operations at CLEAR HELIPORTS.
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When simulating OEI operation, follow the emergency procedures of Category A operations (supplement 9.1–1, subsection B) and use the GENERAL CAT A Limitations (supplement 9.1–1, subsection A) and the gross mass value from the TRAINING WAT curve of this subsection (Fig. C1).
LIMITATIONS
C.2.1.
ALTITUDE LIMITATIONS
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C.2.
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MASS LIMITATIONS
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C.2.2.
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Maximum operating altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8000 ft PA
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For determining the training takeoff and landing gross mass in order to simulate OEI conditions during Category A (clear heliport), refer to the diagram of this subsection (Fig. C1).
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C.2.2.1. Mass Limitations with optional equipment installed
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If external mounted optional equipment is installed, proceed as follows:
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All results obtained from maximum takeoff and landing gross mass chart (Fig. C1) are to be corrected using the relevant correction values listed in FMS 9.1–1 subsection B 2.2.
APPROVED Rev. 2
9.1-3 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) CATEGORY A TRAINING – CLEAR HELIPORT
EXAMPLE:
For helicopter with external optional equipment installed (Fig. C1)
Determine:
Maximum takeoff and landing gross mass (Cat A training – clear heliport)
Known:
OAT . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 _C Pressure altitude . . . . . . . . . . . . . . . . 2000 ft
Gross mass = 3700 kg
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Solution:
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External Optional Equipment . . . . . . External Loudspeaker
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1. Enter chart (Fig. C1) at known OAT (11_C)
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2. Move vertically upwards to to known pressure altitude (2000 ft)
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3. Move horizontally left and read max. gross mass (3770 kg)
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4. Determine correction value for external optional equipment (see FMS 9.1–1 B.2.2): –55 kg.
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5. Apply correction values for external optional equipment as follows: 3770 kg – 55 kg = 3715 kg
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6. Since the max. gross mass limit = 3700 kg is lower than the calculated max. gross mass (3715 kg), the result for clear heliport is 3700 kg.
9.1-3 – 14
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) CATEGORY A TRAINING – CLEAR HELIPORT
C.3.
EMERGENCY AND MALFUNCTION PROCEDURES Refer to para A.3. of this supplement.
C.4.
NORMAL PROCEDURES Refer to para A.4 of this supplement and FMS 9.1-1, subsection B.
PERFORMANCE DATA
ED
C.5.
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In supplement 9.1–1, subsection B, the figures B10 (Rejected Takeoff Distance Required), B11 (continued takeoff distance required) and B14 (landing distance from 50 ft height to a complete stop on the ground) are not valid for CAT A – Clear Heliport Training.
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However these diagrams/values should be used as a guideline to determine the minimum size required to conduct the training. In order to compensate for possible variations in profiles, naturally encountered during training, an appropriate safety margin should be added.
APPROVED Rev. 2
9.1-3 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) CATEGORY A TRAINING – CLEAR HELIPORT
CATEGORY A (CLEAR HELIPORT) TRAINING MAXIMUM TAKEOFF AND LANDING GROSS MASS TURBOMECA ARRIEL 2E OEI – TRAINING RATINGS 2400 Note: Altitude Lines refer to Takeoff/Landing Pressure Altitudes 2500
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2600
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2700
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2800
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2900
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MAX. OAT
PY C
3100
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MIN. OAT
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3200
3300
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GROSS MASS – kg
3000
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3400
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3500
GROSS MASS LIMIT
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3700
R
IN
3600
BK117D2M621_1
3800
3900
4000 –50
–40
–30
–20
–10
0
10
20
30
40
50
60
Fig. C1 Maximum Takeoff and Landing Gross Mass for
Category A (Clear Heliport) Training
9.1-3 – 16
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) CATEGORY A TRAINING – VTOL
D. CATEGORY A TRAINING – VTOL
D.1.
GENERAL This subsection provides information necessary for Category A training operations – VTOL 1 “Surface or Elivated Heliports”.
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To simulate OEI operation with one engine at IDLE, follow the emergency procedures of Category A operations supplement 9.1–1 subsection C, however, use the GENERAL DATA, Engine Limitations (see subsection A) and the gross mass value from the TRAINING WAT curves this subsection.
LIMITATIONS
D.2.1.
ALTITUDE LIMITATIONS
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D.2.
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MASS LIMITATIONS
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D.2.2.
–
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Maximum operating altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8000 ft PA
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D.2.2.1. Mass Limitations with optional equipment installed
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Generally the VTOL training weight is lower than the Clear Heliport training weight. However, in case multiple optional equipment is installed the climbout gradients for Segment I or Segment II may become the limiting factor. For that reason calculate the VTOL weight (Fig. D1) and compare that with the Clear Heliport weight (Fig C1). For the calculation of the Clear Heliport weight the deductions for optional equipment shall be taken into account. The lower of the two weights (VTOL and Clear Heliport) shall be used for training.
APPROVED Rev. 2
9.1-3 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) CATEGORY A TRAINING – VTOL
EXAMPLE: For helicopter with external optional equipment installed (Fig. C1 and D1)
Determine:
Maximum takeoff and landing gross mass (Cat A training – VTOL)
Known:
OAT . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 _C
ED
Pressure altitude . . . . . . . . . . . . . . . . 2000 ft
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1. Enter chart (Fig. D1) at known OAT (11_C)
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Gross mass = 3620 kg
C
Solution:
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External Optional Equipment . . . . . . External Loudspeaker
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2. Move vertically upwards to to known pressure altitude (2000 ft)
PY
3. Move horizontally left and read max. gross mass (3620 kg)
LY
–
C
O
4. To guarantee the minimum climb performance in the OEI climbout flight path, the maximum takeoff gross mass limit for clear heliport with external loudspeaker must be verified. (see example in §C.2.2): 3700 kg.
FO
R
IN
ST
R
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C
TI
O N
O N
5. Since the gross mass limit for VTOL = 3620 kg is lower than the calculated max. gross mass for clear heliport (3700 kg), the max. training take-off and landing gross mass is 3620 kg.
9.1-3 – 18
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) CATEGORY A TRAINING – VTOL
CATEGORY A (VTOL – SURFACE LEVEL OR ELEVATED HELIPORT)TRAINING MAXIMUM TAKEOFF AND LANDING GROSS MASS TURBOMECA ARRIEL 2E OEI – TRAINING RATINGS 2200 Note: Altitude Lines refer to Takeoff/Landing Pressure Altitudes 2300
LL
ED
2400
N TR
O
2500
C
O
2600
N
O
T
2700
MAX. OAT
PY C –
2900
O
MIN. OAT
O N
LY
3000
3100
O N
GROSS MASS – kg
2800
U
C
TI
3200
ST IN
R
3400
R
3300
FO
3500
3700
BK117D2M631_1
3600
GROSS MASS LIMIT
3800 –50
–40
–30
–20
–10
0
10
20
30
40
50
60
Fig. D1 Maximum Takeoff and Landing Gross Mass for
Category A (VTOL) Training APPROVED Rev. 2
9.1-3 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) CATEGORY A TRAINING – VTOL
D.3.
EMERGENCY AND MALFUNCTION PROCEDURES Refer to para A.3. of this supplement.
D.4.
NORMAL PROCEDURES Refer to para A.4 of this supplement and FMS 9.1-1, subsection C.
PERFORMANCE DATA
ED
D.5.
FO
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IN
ST
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C
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O N
O N
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–
C
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PY
N
O
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C
O
N TR
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No changes to the FMS 9.1-1, subsection C.
9.1-3 – 20
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPTIONAL EQUIPMENT
SUBSECTION 9.2 OPTIONAL EQUIPMENT
LOG OF SUPPLEMENTS
FMS NUMBER
ED
FIRST APPROVAL
VALID REVISION
Airborne collision avoidance system (ACAS) (Avidyne TAS 620A)
9.2 -43
Auxiliary fuel tank
9.2 -33
EASA; DEC 11, 2015 FAA; MAR 20, 2017
N TR
9.2 -3
Revision 1
O
T
C
O
Airborne collision avoidance system (ACAS) (Rayn 9900BX/Avidyne TAS 620)
O
LL
NAME OF EQUIPMENT
Revision 2
EASA; DEC 11, 2015
Revision 0
9.2 -37
EASA; FEB 14, 2017
Revision 0
9.2 -16
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 3
9.2−22
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 0
Dual External Cargo Hook / External Mirror
9.2−6
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 3.1
ECS/ACS
9.2−12
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 2
Emergency floatation system
9.2−9
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 1
EOS Wescam MX15D (centerline)
9.2−28
EASA; OCT 20, 2016
Revision 3
EOS Wescam MX15S (Step mounted RH)
9.2−35
EASA; FEB 04, 2020
Revision 0
LY
–
C
O
PY
N
EASA; MAR 21, 2016
C
TI
Comfort seat installation
O N
O N
Ballistic protection kit
FO
R
IN
ST
R
U
Dual controls pedal cover
LOG OF SUPPLEMENTS Rev. 22.1
9.2 − i
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPTIONAL EQUIPMENT
FMS NUMBER
NAME OF EQUIPMENT
VALID REVISION
FIRST APPROVAL
9.2−29
EASA; FEB 05, 2016
Revision 1.2
EOS Ultraforce 350HD
9.2−38
EASA; SEP 30, 2016
Revision 1.2
Equipment for offshore operation
9.2−27
EASA; DEC 11, 2015
Revision 0.1
Enhanced Reality System (ERS)
9.2−50
EASA; OCT 18, 2019
Revision 0
EuroNav 7
9.2−2
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 2
External Hoist System
9.2−4
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 6
External loudspeakers
9.2−20
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Fixed landing light 250W (cross tube)
9.2 -23
Revision 0
O
PY
N
O
T
C
O
N TR
O
LL
ED
EOS Star SAFIRE 380−HD/HDc
Revision 0.1
9.2 -32
EASA; DEC 11, 2015
Revision 4
Helionix Digital Map System (DMAP) After Helionix Maintenance Release 1
9.2 -49
EASA; DEC 18, 2017
Revision 1
HF 9000 communication system
9.2 -44
EASA; DEC 11, 2015
Revision 1
High Intensity Searchlight (HISL) (Trakka A800)
9.2 -14
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 4.1
Inlet Barrier Filter System
9.2 -5
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 3
Main rotor blade folding kit
9.2-34
EASA; DEC 11, 2015
Revision 0
– LY O N
O N
FO
R
IN
ST
R
U
C
TI
Helionix Digital Map System (DMAP) Before Helionix Maintenance Release 1
C
EASA; DEC 11, 2015
9.2 − ii
LOG OF SUPPLEMENTS Rev. 22.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPTIONAL EQUIPMENT
FMS NUMBER
NAME OF EQUIPMENT
EASA; DEC 11, 2015
Revision 1.6
Night Vision Imaging Systems (NVIS) / NVG
9.2-11
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 1
Pilot/copilot door jettisoning
9.2-24
EASA; DEC 11, 2015
Revision 0.1
Polycon Radio
9.2-45
EASA; DEC 11, 2015
Revision 0.1
9.2-31
EASA; DEC 11, 2015
Revision 0
9.2 -40
EASA; DEC 11, 2015
Revision 5
9.2 -39
EASA; DEC 11, 2015
Revision 0
9.2 -10
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 0
Sliding door jettisonning
9.2-19
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 0
Sling type cargo hook
9.2-7
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 2.1
Snow Skids
9.2 -13
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 0
Special cabin equipment
9.2 -42
EASA; DEC 11, 2015
Revision 0
ED
9.2-48
–
Miscellaneous COM and NAV Equipment: RT5000 MR6000R Direction Finder DF935 Transponder − SAAB R4A MkII
VALID REVISION
FIRST APPROVAL
Polycon Radio NG
LL
CARLS tactical radio system
N TR
O
BGH-12 FM radio control unit
MTM5X00 tactical radio
C
TI
Seat Arrangement
ST
R
U
Self sealing supply tank
FO
R
IN
Settling Protectors
LOG OF SUPPLEMENTS Rev. 22.1
O N
PY
O
C
LY O N
O N
Pulsed chip detector system
T
C
O
NPX138N VHF−FM radio
9.2 − iii
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPTIONAL EQUIPMENT
FMS NUMBER
NAME OF EQUIPMENT
VALID REVISION
FIRST APPROVAL
9.2 -41
EASA; DEC 11, 2015
Revision 2
TACAN system
9.2 -47
EASA; APR 15, 2016
Revision 0
Vision 1000 Cockpit Camera
9.2 -21
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Revision 0
Weather radar system RDR 1600
9.2 -30
EASA; JUN 08, 2016
Weather radar system RDR 2000
9.2 -8
EASA; DEC 11, 2015 FAA; MAR 20, 2017
Wire strike protection system (WSPS)
9.2 -15
EASA; DEC 11, 2015 FAA; MAR 20, 2017
ED
Special seat arrangemant
Revision 2
Revision 1
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
Revision 0.1
9.2 − iv
LOG OF SUPPLEMENTS Rev. 22.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
FMS
9.2-2
SUPPLEMENT FOR
N TR
O
LL
ED
DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
N
O
T
C
O
This supplement shall be attached to the BK117 D-2 Flight Manual (subsection 9.2) when the EuroNav 7 is installed.
Effectivity All
For approving authorities and respective dates of approval refer to the log of supplements.
FO
R
IN
ST
R
U
C
TI
O N
NOTE
O N
LY
–
C
O
EuroNav 7 (RN7 OR RN7CM)
PY
System/Equipment Designation
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-2 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA ref. EASA.21J.700, “DOA”.
9.2-2-1
0
EASA
R
9.2-2-2
2
EASA
R
9.2-2-3
2
EASA
R
Rev.No
App.
Page
9.2-2-4
1
EASA
9.2-2-5
1.1
DOA
9.2-2-6
2
EASA
Rev.No
Rem
Page 9.2-2 -12
9.2-2-7
R
Rev.No
App.
2
EASA
Rev.No
Rem
LL
Page
O
App.
N TR
Rev.No
N
Page
ED
LEP – approved (part 1):
9.2-2-8
2
R
9.2-2-9
2
Page R
9.2-2 -10
2
9.2-2 -11
1.1
1.1
C
O
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Rem
O
Rev.No
PY
Page
T
C
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LEP – manufacturer‘s data (part 2):
LY
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LOG OF REVISION
O N
O N
FIRST ISSUE
(see 9.2-2-1)
TI
ORIGINAL
ST
R
U
C
REVISION 1 MAY 04, 2016 EASA approval no.: 10057989 REV.1
R FO
REVISION
1.1
IN
REVISION
REVISION 2
Date: NOV 08, 2019
9.2-2 – 2
2
SEP 08, 2016 (see entry below)
Approved by EASA
EASA approval no.: 10071609
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
1
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual.
2
LIMITATIONS NOT ALL OBSTACLES AND WIRES ARE INCLUDED IN THE DATABASE. WHEN AN OBSTACLE, WIRES, OR TERRAIN IS NOT IN THE DATA BASE, AN ALERT WILL NOT BE PRODUCED. IT IS THE PILOT’S RESPONSIBILITY TO MAINTAIN A PROPER LOOKOUT.
LL
ED
WARNING
O
The EuroNav 7 is approved for VFR operation only.
N TR
The EuroNav 7 shall not be used as a primary means of navigation.
C
O
The crew must be familiar with system operation.
O
T
The operator is responsible for using the current map-software version.
C
O
PY
N
The EuroNav 7 digital map system is intended to increase the pilot’s situational awareness in VFR. Navigation and terrain/obstacle avoidance shall not be based on the EuroNav 7 information. If a caution or warning is received, the pilot should not initiate a maneuver based on the display alone, without first visually acquiring the environment.
O N
LY
–
During T/O and Landing the operator has to turn aside and stow the keyboard and second monitor (if installed).
C
CONFIGURATION REQUIREMENT
U
2.1
TI
O N
The FLARM and 1090 MHz receiver data (e.g. “ADS–B In”) on Euronav7 are for information only.
IN
TEMPERATURE LIMITATIONS
R
2.2
ST
R
The EuroNav 7 bearing line function must be deconfigured via DMAP CONFIG setting.
FO
Minimum cabin temperature for operation . . . . . . . . . . – 40_C
Minimum temperature for storage of the optional keyboard . . . . . . . . . . . . . . . . . . . . . . . . . . – 25_C
APPROVED Rev. 2
9.2-2 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
2.3
PLACARDS
EURONAV SYSTEM APPROVED FOR VFR ONLY
Location: On the EuroNav 7 (RN7CM) or in pilot’s view (RN7)
ED
If EuroNav 7 keyboard is installed (optional):
N TR
O
LL
EFFECTIVITY
PY
N
O
T
C
O
STOW MONITOR + KEYBOARD FOR TAKE–OFF AND LANDING
O N
All
O N
EFFECTIVITY
LY
–
C
O
Location: On the EuroNav 7 keyboard
EMERGENCY AND MALFUNCTION PROCEDURES
3.1
FAILURE OF MFD4
ST
R
U
C
TI
3
ACAS information is lost
FO
R
–
IN
Conditions/Indications
Procedure 1. Continue flight
9.2-2 – 4
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
4
NORMAL PROCEDURES VERIFY NAV UNIT SELECTION IS COHERENT WITH HELIONIX SETTING (TRUE/MAG).
CAUTION NOTE
As a backup, the crew must have a paper version of the relevant and valid maps available during flight.
For additional information, refer to the EuroNav 7 Operators Manual. 4.1
PREFLIGHT CHECK/ SYSTEM CHECK
O
OPERATION WITH THE EURONAV 7 KEYBOARD (OPTIONAL)
N TR
4.2
LL
ED
The self-test starts automatically, after the AVIO MSTR switches are switched ON.
THE EURONAV 7 KEYBOARD PROVIDES FULL ACCESS TO THE EURONAV SYSTEM.
C
O
CAUTION
PY
EURONAV 7 CONTROL VIA MFD LINE–SELECTABLE KEYS AND MMI “NEW GENERATION” – (OPTIONAL)
C
O
4.3
N
O
T
Minimum recommended temperature for operation of the optional keyboard: 0_C.
TRANSFERRING WAYPOINTS TO THE FLIGHT MANAGEMENT SYSTEM (FMS)
O N
4.4
O N
LY
–
The ”CONTROL via MFD” provides remote access to the major functions of the EuroNav 7 system via bezel keys and rotary knobs on the MFD (see Para 7.3).
ST
R
U
C
TI
NOTE D It is only possible to transfer one waypoint at a time from the EuroNav 7 to the GTN 750. If the transfer of a complete flightplan from the EuroNav 7 to the GTN 750 is performed, only the last waypoint of the flightplan is used by the GTN 750.
R
IN
To transfer a waypoint from EuroNav 7 to the FMS, proceed as follows:
FO
1. Waypoint
– Select – SEND TO FMS label appears
2. SEND TO FMS
– Push (LSK or control knob)
On the GTN750, a Create User Waypoint window will appear. 3. Waypoint coordinates / name
– Check
4. Create
– Touch
The transferred waypoint is now created as a user waypoint and can be used as required. APPROVED Rev. 1.1
9.2-2 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
Use of OBS function on GTN750:
1. Direct-to pb (GTN)
– Press
2. Remove icon (GTN)
– Touch
3. Direct-to pb (GTN)
– Press
ED
When the GTN750 OBS function is used, the EuroNav 7 will not display the selected LEG, DISTANCE, and DTK. When the OBS function is deselected on the GTN750, the DTK on the EuroNav 7 will be shown with an offset. To recover the proper indication on EuroNav 7, proceed as follows:
OPERATION WITH WEATHER RADAR 2000 (OPTIONAL)
O
O
4.5
– Touch
N TR
4. Activate icon (GTN)
LL
– Reselect waypoint
O
OPERATION WITH ACAS TAS620 OR TAS620A (OPTIONAL)
C
4.6
PY
N
O
T
C
The range setting of the WX overlay is only possible via MFD2 FND page or MFD4 NAVD page. The DMAP range setting is unaffected by the WX range setting. To obtain full WX overlay display, the DMAP range setting has to be adjusted via the EuroNav control panel accordingly.
LY
–
It is not possible to adjust the vertical filtering on DMAP. The selected vertical filtering in NAVD mode is also applied in DMAP mode.
C
EURONAV7 FLARM FUNCTION (OPTIONAL)
U
4.7
TI
O N
O N
For detailed information refer to FMS 9.2–3 “AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS) – (AVIDYNE TAS 620)” or FMS 9.2–43 “AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS) – (AVIDYNE TAS 620A)”.
R
IN
ST
R
The EuroNav7 system is capable of displaying FLARM traffic on the DMAP, including relative height. The FLARM overlay can be activated/deactivated by pressing the TFC pb located on the EuroNav7 control panel (see fig. 1).
FO
CAUTION D FLARM AUDIO IS NOT AVAILABLE.
NOTE
D FLARM INDICATIONS ARE NOT AVAILABLE WHEN FLYING SLOWER THAN 30 KTS. GROUNDSPEED.
With transponder modes S and/or SQ ON, the own aircraft is indicated as a FLARM threat.
For display and symbols description refer to the EuroNav7 Pilot’s guide. 4.8
EURONAV7 SATCOM FUNCTION (OPTIONAL) The EuroNav7 system is equipped with a SatCom module or connected to an external SatCom system, allowing to receive and transmit telephone calls via the IRIDIUM SatCom system
9.2-2 – 6
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
4.9
EURONAV 7 1090 MHZ RECEIVER (OPTIONAL) The EuroNav 7 system is capable of displaying traffic information from a 1090 MHz receiver. The 1090 MHz receiver overlay can be activated/deactivated by pressing the TFC pb on the Euronav7 control panel (see fig. 1). For display and symbols description refer to the EuroNav7 Pilot’s guide.
PERFORMANCE DATA
ED
5
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
No change to the basic flight manual data.
APPROVED Rev. 2
9.2-2 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
6
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
7
SYSTEM DESCRIPTION For detailed operational information refer the EURONAV 7 – Operator’s Manual. The EuroNav 7 is a digital moving map system using real time presentation of coloured topographical maps and mission related overlays to increase the crew’s situational awareness and support mission management.
O
LL
ED
The EuroNav 7 system provides the following functions (depending on the installed options):
N TR
– Digital map display (terrain, vector maps, aeronautical maps, street maps, etc.)
O
– Database access (airspace, user, address, and points of interest databases)
T
C
– HTAWS functions
N
O
– Mission flight plan creation and specific mission functions
PY
– Flight path and event recording
LY
–
– Interface with EOS systems (optional)
C
O
– ACAS, FLARM and 1090 MHz receiver indications (optional)
O N
– Interface with HISL systems (optional)
O N
– Data and SATCOM voice communication (including exchange of waypoints)
C
TI
– Weather radar indication (optional)
R
IN
ST
R
U
The EuroNav 7 is displayed on the MFDs and (optionally) on an operator console in the cabin. The system is controlled through a control panel installed in the center console or (optionally) through a control panel or optional keyboard installed on an operator console.
FO
Weather Radar System indications
WX NO WXR
Alerts when the Weather Radar is switched off
STBY
Indicates when the Weather Radar is in the STBY mode
GMAP
Indicates when the Weather Radar is in the MAP mode (ground scan)
WXR
9.2-2 – 8
Indicates normal operation of Weather Radar System
Alerts about any abnormal/ failure condition of the Weather Radar System. MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
Indicates when the Weather Radar is in the TEST mode
TEST
Alerts when the stabilization of the Weather Radar is not active
STAB OFF 7.1
CLR
FNC
COM
TFC
WXR
TWS
ED
ESC
O
LL
MAP
T
EuroNav 7 control panel
N
O
Fig. 1
C
O
N TR
BKD2_FLH_0052_R
EURONAV 7 CONTROL PANEL
O
PY
Functionalities of control panel buttons and keyboard function keys may depend on Euronav 7 configuration. In the table below, a typical configuration is described.
LY
–
C
Keyboard function keys
Control panel
F4
The MAP button has no specific function
ESC
ESC
The ESC button is used to quit a menu, cancel an input field entry and to exit panning mode
COM
F3
TFC
F2
CLR
F6
O N
O N
MAP
The TFC button is used to activate/deactivate the overlay of traffic avoidance systems (FLARM, ACAS). The CLR button provides access to camera steering/slaving functions, lists and databases
F1
The FNC button provides access to main functions such as flight planning, maintenance, system and user settings
WXR
F7
The WXR button activates the WXR overlay if a Weather Radar is connected to the EuroNav
TWS
F5
The TWS button is used to activate/deactivate the overlay of terrain avoidance systems (TAWS).
IN
ST
R
U
C
TI
The COM button provides access to communication functions
FO
R
FNC
Control knob
MANUFACTURER’S DATA APPROVED Rev. 2
Push function: To select an option and to confirm a data entry Rotate function (CW/CCW): Zoom in and zoom out function; move through menus, dialogs and operational MMI (OMMI) pages Joystick function: Pan map; move through menus and dialogs
9.2-2 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
7.2
MAIN MODES – Pre-flight planning: provides distance and bearing to the destination or of any leg of the flight plan or the total distance of a complicated flight plan involving many stops. – Flight planning: flights can be planned and previewed on the screen. It is possible to create specific waypoints. Single waypoints can be transferred to the NMS. The system displays additional flight information. A flightplan can be created and activated via the NMS which is automatically displayed by the EuroNav 7 unit.
ED
– Direct to: provides information from present position to the selected destination; not for navigation purposes.
N TR
O
LL
– Search process: for direct map query a single button click offers complete information about selected objects in the area.
T
C
O
– Air databases: the database can hold vector and digital raster maps of the entire area. It uses Jeppesen databases showing airspace structures, topographical airport information like runways, available VOR’s, NDB’s, restricted airspaces etc...
O
PY
N
O
– Maps: provides coloured and zoomable maps. All map material can be displayed in North-up or Track-up modes. Map labels move with the map but remain upright to enable easy reading even in Track-up mode.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
– Emergency mode: in case of emergency, the emergency mode shows the pilot a list of the nearest suitable landing fields together with the associated navigational information about the displayed location.
9.2-2 – 10
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
7.3
EURONAV 7 CONTROL VIA MFD LINE–SELECTABLE KEYS AND MMI “NEW GENERATION” – (OPTIONAL)
7.3.1
EuroNav 7 control via MFD Line Selectable Keys The EuroNav 7 is optionally controllable via the LSK (Line Select Keys) of the MFD 1 and 4 of the HELIONIX system
EN7 menu label and LSK
MFD rotary knob
FO
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IN
ST
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O N
O N
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–
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O
PY
N
O
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LSKs which affect the control of the EuroNav 7 are the left, right and bottom LSK as well as the inner and outer rotary knobs. The configuration of the LSKs is customer dependent.
Fig. 2
EURONAV 7 control via HELIONIX MFD
Pushing once on the rotary knob in the center console activates the menu function, displays the labels and activates the corresponding line select keys. The menu function (e.g. ZOOM– or ZOOM+) can be executed via the line select key or alternatively via the rotary knob on the center control panel. In this case the rotary knob has to be turned to highlight and activate the desired menu function and then to be pushed to execute it. The map zoom level can be changed by turning the grey rotary knobs at the lower right corner of the corresponding MFD. MANUFACTURER’S DATA APPROVED Rev. 1.1
9.2-2 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DIGITAL MOVING MAP SYSTEM EURONAV 7 (RN7 OR RN7CM)
7.3.2
New Man Machine Interface (MMI) – ”Next Generation”: The MMI introduces a new menu interface coupled with the MFD 1 and 4 LSKs.
O N
Example for the new MMI presentation
FO
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IN
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O N
Fig. 3
LY
–
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O
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N
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The customer related maps have to be loaded on the Euronav solid state Disk FDRN with the customized media by a software upload via USB–Stick.
9.2-2 – 12
MANUFACTURER’S DATA APPROVED Rev. 1.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
FMS
9.2-3
SUPPLEMENT FOR AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
C
O
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O
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ED
(AVIDYNE TAS 620)
C
System/Equipment Designation
O
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N
O
T
This supplement shall be attached to the BK117 D-2 Flight Manual (subsection 9.2) when the Airborne Collision Avoidance System (ACAS) is installed.
All
C
For approving authorities and respective dates of approval refer to the log of supplements.
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NOTE
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O N
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–
Airborne Collision Avoidance System (Avidyne TAS 620)
Effectivity
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971
APPROVED date – see Rev. 0 entry above
9.2-3 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. LEP – approved (part 1):
9.2-3 -1
–
EASA
R
9.2-3 -2
1
EASA
R
9.2-3 -3
1
EASA
9.2-3 -4
0
EASA
9.2-3 -5
0
EASA
Rev.No
App.
Rev.No
Rem
Page
Rev.No
App.
ED
Page
LL
App.
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Rev.No
N TR
Page
0
9.2-3 -9
0
9.2-3 -7
0
9.2-3 -10
0
9.2-3 -8
0
9.2-3 -11
0
Page 9.2-3 -12
Rev.No
Rem
0
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O
9.2-3 -6
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Page
O
Rem
N
Rev.No
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Page
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O
LEP – manufacturer‘s data (part 2):
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LOG OF REVISION
O N
O N
FIRST ISSUE
(see page 9.2-3-1)
C
(see entry below)
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1
IN
ST
R
REVISION
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ORIGINAL
Approved by EASA:
FO
R
Date: MAY 04, 2016
EASA approval no.: 10057989
9.2-3 – 2
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
1
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual.
– Airborne Collision Avoidance System
ATC
– Air Traffic Control
CPA
– Closest Point of Approach
EOS
- Electro–optical sight
OT
– Other traffic
OVHP
– Overhead panel
PT
– Proximate traffic
sk
– soft key
TA(S)
– Traffic Advisory (System)
PY
N
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N TR
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ED
ACAS
LIMITATIONS
O
2
ABBREVATIONS
C
1.1
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–
CAUTION D ACAS INFORMATION IS ADVISORY ONLY.
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O N
O N
D IF A TA OCCURS, DO NOT INITIATE A MANEUVER BASED ON THE ACAS DISPLAY: – VFR: WITHOUT FIRST VISUALLY ACQUIRING THE THREAT. – IFR: BEFORE RECONFIRMATION BY ATC TO AVOID THE INTRUDER AIRCRAFT.
NOTE
2.1
D THE ACAS IS NOT ABLE TO TRACK AND NON–TRANSPONDER EQUIPPED / OPERATED AIRCRAFT.
DISPLAY
Target duplication (a target splitting into two targets at same altitude and close to the same range) may be encountered for a few seconds. Target duplication is generally caused by reflections on the ground, on water or nearby buildings.
COMPATIBILITY WITH OTHER OPTIONAL EQUIPMENT External optional systems like EOS, High Intensity Search Light (HISL), cargo hook, loudspeakers may temporarily shadow one of the ACAS antennas and/or cause signal reflections.
CAUTION
APPROVED Rev. 1
WHEN EXTERNAL OPTIONAL SYSTEMS ARE INSTALLED, UNRELIABLE ACAS INDICATION MAY BE ENCOUNTERED.
POSSIBLE
9.2-3 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
3
EMERGENCY AND MALFUNCTION PROCEDURES
3.1
ACAS FAILURE
FAILURE INDICATIONS
FAIL
ACAS FAIL
and
ACAS sk FAIL indication on NAVD
ED
ACAS failure indication on FND
LL
ACAS
N TR
O
Conditions/Indications – ACAS failure detected (e.g. TAS processor failed). – ACAS test failed.
O
If MFD 4 fails ACAS is no longer avaiable.
N
NOTE
T
C
O
– ACAS is not longer usable.
PY
Procedure
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O N
O N
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C
O
Continue flight
9.2-3 – 4
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
4
NORMAL PROCEDURES NOTE D The ACAS self test will be launched automatically after AVIONIC MASTER switch ON or by pilots decision using the TEST switch. No dedicated TEST indication is provided. Failed TEST will be indicated by means of the ACAS FAIL annunciation on the FND.
SYSTEM CHECKS
LL
4.1
ED
D If the indication is not reliable an additional test can be performed. During the test (20sec) no ACAS information will be provided. The test was successfully performed if no traffic indications appers. If the test failed refer to section 3.
N TR
O
The ACAS self test will be launched after AVIONIC MASTER switch ON. After completion of the self test the ACAS traffic advisories will be indicated on the FND.
PERFORMANCE DATA
PY
5
N
O
T
C
O
To increase situational awarness it is recommended to activate the ACAS overlay display on the NAVD.
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O N
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C
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No change to the basic flight manual data.
APPROVED Rev. 0
9.2-3 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
6
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
7
SYSTEM DESCRIPTION
7.1
GENERAL Additional information about the system has to be obtained from the pilot’s guide.
ED
NOTE
N TR
O
LL
The ACAS offers a safer flight enviroment by alerting pilots of potential mid-air collisions threats. ACAS is providing situational awareness of surrounding aircraft to assist pilots in avoiding other nearby aircraft.
PY
N
O
T
C
O
The system in the BK117 D-2 is an actively interrogating onbord air traffic detection system and has a development assurance level consistent with TSO-C147 Class A, that indicates the presence and relative location of intruder aircraft and an aural and visual alert informing the crew of a traffic advisory (TA). It provides a maximum 30 second alert while tracking up to 50 transponder equipped aircraft.
O
The system consists of one processor unit, a transponder coupler and two antennas.
LY
–
C
The system includes built-in tests which displays any unit malfunction, failure logging on data card for maintenance support and setup functionality.
O N
This ACAS is advisory only, and is a backup to the see and avoid concept, and the ATC radar enviroment.
TI
O N
Under IFR the system should not be used solely but only after reconfirmation by ATC to avoid intruder aircraft.
U
C
The system provides alerts which enable the pilot to:
IN
– locate it
ST
R
– visually search for the intruding aircraft
FO
R
– determine if an avoiding maneuver is necessary – accomplish the avoiding maneuver, if necesary Power supply: Via avionic shed bus 2 (3A circuit breaker / 28V DC, both on the OVHP). The ACAS system displays the surrounding traffic situation to the flight crew upon activation of the corresponding display mode on the navigation main mode. Further it provides mode independent visual alerting of critical traffic advisories to the flight crew on the MFD. In addition to the visual alert an aural alert (”TRAFFIC TRAFFIC”) is created for each detected traffic advisory. No Bearing and distance will be announced. The ACAS traffic display on the NAVD main mode is controlled using a soft key on the MFD. When a MFD is switched to NAVD main mode the ACAS symbol is indicated above a soft key on the bottom of the screen if an ACAS system is installed (see Fig 4). This button can be used to activate the ACAS traffic display, if pushed once, or to activate a
9.2-3 – 6
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
decluttered ACAS traffic display, if pushed twice. The selection is made locally per FND display and it is indicated above the soft key. The ACAS indications on the FND main mode cannot be suppressed or cancelled by the flight crew. The ACAS traffic information is also provided to the external, optional Euronav 7 DMAP, if installed, to allow the display of the traffic information as an overlay on the external DMAP.
NAV
IAS
101
2
10
69 1 –1
10
20
20
VY
C 3
C
–
600 DA
3
LY
O N TI
C
DTK
TRFC
24 14
13
23 13
B A R O
FND compass
1013 200 hPa DH
20
LVL
10
FSD
A C K
354 1.0 FMS
U R ST
10
14
D H
GPS
LFMH
20.0 NM 12 min
DCPL
415 Kg SCT
SVS
OAT
25
+ B R G –
FO
R
IN
BKD2_FLH_0436_R
+ L U M –
15 500 000 25 1 –2
Master list
O N
20
D A
16
T
80
10
N
N A V
17
O
10
O
2
20
O
4
20 100
20
78 1 –1
N
4
87 1 –1
40 120
PY
6
+ C T R S –
CLOCK
LL
ALT
MISC
ED
DMAP
O
VMS
N TR
NAVD
Fig. 1
MANUFACTURER’S DATA APPROVED Rev. 0
FND display main mode - typical indication
9.2-3 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
FND
NAVD
VMS
N A V
DMAP
EFB
GS TAS
110.30
N 33
R N G2
MISC
VOR1
61 min MLK 3 010? / 29.0NM
20 10
Selection softkey for sector / rose format and active overlay indication
M A P
3
+1
6 D H
30
10
CRS
ACAS soft key
12
LL
W
ED
E
–4
+10
WXR softkey
24
C R S
O
20
000
N TR
OFF
MAP soft key in NAVD
+ C T R S –
15 21
S
C
O
ON
N
O
T
C R S
HTAWS soft key
PY O
CPL
PLS
SCT
WXR
ACAS
–
VOR1
C
NORMAL
HTAWS
Range knob + B R G –
O N
LY
+ L U M –
D A T A
O N
BKD2_FLH_0080_R
N A V
NAVD display main mode - typical indication
FO
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IN
ST
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TI
Fig. 2
9.2-3 – 8
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
7.1.1
Examples of traffic information display on NAVD The traffic without bearing, range or altitude are indicated as shown in Fig. 3: –
No altitude: Traffic is indicated with correct bearing and range but without altitude information.
–
No bearing: Traffic Advisory is indicated with correct range and altitude. Proximate and other traffic is not indicated if no bearing information is available. The missing bearing is indicated by a circle around the H/C in the same color as the traffic symbol.
O
T
C
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O
LL
ED
Traffic advisory out of display range indication, half dot Proximate traffic indication
Traffic advisory without range information indication
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O N
O N
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N
Other traffic indication
Fig. 3
MANUFACTURER’S DATA APPROVED Rev. 0
NAVD display main mode - typical indication
9.2-3 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
7.2
ACAS MODES AND SYMBOLOGY The ACAS modes listed below can be selected with a long push of ACAS sk and then with side soft keys. Activation begins with a long push of ACAS sk. ACAS modes
Description Proximate and other traffic are indicated if in a relative altitude band of –2700ft to +2700 ft
ABOVE
Proximate and other traffic are indicated if in a relative altitude band of –2700ft to +9900 ft
BELOW
Proximate and other traffic are indicated if in a relative altitude band of –9900ft to +2700 ft
UNRESTRICTED
Proximate and other traffic are indicated if in a relative altitude band of –9900ft to +9900 ft
N TR
O
LL
ED
NORMAL
C
O
The following figure shows a set of examples of ACAS indication above the soft key:
ACAS traffic display off
–
ACAS failure mode
–
ACAS normal altitude band in TA mode
N
–
TI
NORMAL
O N
O N
ACAS
LY
FAIL
–
C
O
PY
ACAS
O
T
NORMAL
IN –
ACAS above altitude band in TA mode
UNRST
–
ACAS unrestricted altitude band in TA mode, display decluttered
ACAS
–
When ACAS overlay is allready selected and pressing the SK again (short push), the ACAS display can be decluttered.
FO
ACAS
R
ABOVE
ST
R
U
C
ACAS
Fig. 4
9.2-3 – 10
Examples of ACAS indication - typical indications
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
The following symbology is used to indicate the different types of detected traffic:
Other Traffic
BKD2_FLH_0087_R
Proximate Advisory
LL
ED
Traffic Advisory
T
C
O
N TR
O
The following symbols are used to indicate traffic information in the horizontal situation indication area of the FND display (see Fig. 1) :
ABV
–
Traffic advisory, above, approaching from the front right–hand side
TRFC
LVL
–
Traffic advisory, level, approaching from the front left–hand side
TRFC
BLW
–
O N
O N
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–
C
O
PY
N
O
TRFC
R
ABV
–
FO
TRFC
IN
ST
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C
TI
Traffic advisory, below, approaching from the back
Traffic advisory, no altitude information, approaching from the back left–hand side
ABV is indicated if the intruder has a relative altitude of >300ft LVL is indicated if the intruder has a relative altitude of –300ft v relative altitude v300ft BLW is indicated if the intruder has a relative altitude of 25 kt) and from the front right (> 15 kt) may cause some unsteadiness. If operationally feasible, it is recommended to avoid winds from these azimuths.
O
up to 10000ft DA
PY
N
O
T
C
O
–
LL
External Hoist System (RH) installed.
N TR
EFFECTIVITY
ED
Hoist operations have been demonstrated under the following conditions:
C
above 10000ft DA
up to 25 kt
BKD2_FLH_0256_R
FO
R
IN
ST
R
U
–
up to 30 kt
TI
O N
O N
LY
BKD2_FLH_0255_R
–
C
O
up to 70 kt
9.2-4 – 28
up to 70 kt
up to 30 kt
APPROVED Rev. 2.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
EFFECTIVITY
External Hoist System (LH) installed. –
up to 10000ft DA
up to 25 kt
O C
above 10000ft DA
up to 25 kt
O N
O N
LY
–
–
PY
N
O
T
C
O
up to 30 kt
N TR
O
BKD2_FLH_0257_R
LL
ED
up to 70 kt
ST IN
R
BKD2_FLH_0258_R
R
U
C
TI
up to 70 kt
FO
up to 30 kt
EFFECTIVITY
All Fig. 1
APPROVED Rev. 2.1
Demonstrated wind conditions
9.2-4 – 29
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
5.4
HEC HOIST OPERATIONS REQUIRING OEI PERFORMANCE Wind accountability is UNFACTORED. NOTE D Unless otherwise authorized by operationg regulations, the pilot is not authorized to credit more than the performance increase resulting from 50% of actual headwind component. Clear area hoist operation: Hoist operation where the takeoff flight path of the hoist load is free of obstacles (see Fig 4). Clear area hoist operations can typically be found over open water or open areas.
LL
ED
Clearway: An area free of significant obstacles over which the helicopter can accelerate and achieve a safe height.
C
O
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O
Acceleration distance: The horizontal distance along the takeoff flight path from the hover hoisting position to the point at which the HEC is at least 35 feet above the obstacles and the helicopter attains and maintains a speed of at least VTOSS, and establishes a positive rate of climb.
PY
N
O
T
Confined area hoist operation: Hoist operation where the takeoff flight path of the hoist load is not free of obstacles (see Fig 9). Confined area hoist operations can typically be found over forests, canyons, or built-up areas.
–
C
O
Takeoff Safety Speed (VTOSS): The reference airspeed obtained after takeoff at which the required OEI climb performance can be achieved. VTOSS = 45 KIAS.
R
U
5.4.1.1 Hover performance
TI
Clear area hoist operations
C
5.4.1
O N
O N
LY
Obstacle clearance height: Height between the obstacle and the helicopter or helicopter load during the emergency procedure. A default obstacle clearance height of 35 ft / 10 m was used.
FO
R
IN
ST
The hover performance chart for clear area operations is based on the hover out of ground effect performance achievable with the OEI 30 sec rating with consideration given to the maximum aircraft height loss of 4 ft after an engine failure. The hover performance chart is valid only if used in conjunction with the following emergency procedures: –
HEC operations single engine failure – cargo close to the ground
–
HEC operations single engine failure – clear area operations
9.2-4 – 30
APPROVED Rev. 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
EXAMPLE:
(see Fig. 2)
Determine:
Maximum gross mass for hoist operations requiring OEI performance in clear area
Known:
OAT . . . . . . . . . . . . . . . . . . . . . . . +15 _C Pressure altitude . . . . . . . . . . . . . 8000 ft Windspeed . . . . . . . . . . . . . . . . . . 25 kt
N TR
Enter chart (Fig. 2) at known OAT (+15_C)
LL
Gross mass = 2690 kg
O
Solution:
ED
For calculation: 50% headwind . . . . . . . . . . . . . . . 12,5 kt
Move vertically upwards to known pressure altitude (8000 ft)
C
O
From point of intersection move horizontally right to the reference line of the wind credit chart.
O
T
From this point follow the direction of the wind credit guide lines.
PY
N
Enter chart at known windspeed (12,5 kt).
O
Move vertically upwards to intersect tracing from above.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
From point of intersection move horizontally right and read max. gross mass = 2690 kg. (Using the example on the assumption of no wind, the solution is 2625 kg).
APPROVED Rev. 2.1
9.2-4 – 31
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
HEC HOIST OPERATIONS REQUIRING OEI PERFORMANCE CLEAR AREA (OEI 30 SEC)
1900
ED
2000
LL
2100
N TR
O
2200
C
O
MAX. DENSITY ALTITUDE 12000 FT
O
T
2500
2800 2900
O N O N
3100
C
TI
3200
R
U
3300
–10
0
10
20
30
40
50
60 0
3600 3700
10
20
3800 30 [kt]
BK117D2707_1_r1
–20
3500
REFERENCE LINE
IN
ST
3400
R –30
GROSS MASS – kg
MAX. OAT
LY
–
C
MIN. OAT
O
PY
N
2600
3000
FO –40
2400
2700
GROSS MASS LIMIT 3700 KG –50
2300
0 10 20 30 40 50 60 [km/h] HEADWIND
Fig. 2
9.2-4 – 32
HEC hoist operations requiring OEI performance – clear area (OEI 30 sec) APPROVED Rev. 2.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
HEC HOIST OPERATIONS REQUIRING OEI PERFORMANCE CLEAR AREA (OEI 30 SEC) IBF INSTALLED
1900 2000 2100
O
LL
ED
MAX. DENSITY ALTITUDE 12000 FT
N TR
2400
O
2500
2700 MAX. OAT
2800 2900
LY
–
3000
GROSS MASS – kg
T
C
2600
O N
2300
C
O
PY
MIN. OAT
2200
O N
3100
O N
3200
C
TI
3300
–40
–30
–20
–10
0
10
20
30
OAT – _C
Fig. 3
APPROVED Rev. 2.1
40
50
60 0
3600 3700
10
20
3800 30 [kt]
BK117D2707_1_IBF_3_r1
ST IN R FO
GROSS MASS LIMIT 3700 KG –50
3500
REFERENCE LINE
R
U
3400
0 10 20 30 40 50 60 [km/h] HEADWIND
HEC hoist operations requiring OEI performance – clear area (OEI 30 sec) IBF installed
9.2-4 – 33
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
5.4.1.2 Obstacle clearance CAUTION
SAFE OBSTACLE CLEARANCE IS ONLY GUARANTEED IF THE HEC IS HOISTED UP AT MAXIMUM SPEED DURING FLY AWAY.
Safe obstacle clearance can be determined in accordance with Fig 4 as follows:
Acceleration distance:
ED
No obstacles above 5 ft shall be present in the area required for acceleration from hover to VTOSS. Up to 2000 ft DA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 m / 660 ft
–
Above 2000 ft DA and up to 7000 ft DA: . . . . . . . . . . . . . . . . . . . . . . . . . . 300 m / 980 ft
–
Above 7000 ft DA: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 400 m / 1310 ft
C
O
N TR
O
LL
–
N
The climb rate and distance covered during the Segment I climb from the hover height during hoisting to (at least) 300 ft AGL can be determined using the Segment I climb rates given in the Cat A flight manual supplement (FMS 9.1–1). If the Segment 1 climb is extended above 300 ft AGL, the maximum Segment 1 distance shall not exceed 7500 ft / 2300 m.
LY
–
C
O
PY
–
O
T
Segment I distance:
(see Fig. 4)
Determine:
Maximum Cat A HEC clear area gross mass
Known:
OAT . . . . . . . . . . . . . . . . . . . . . . . . 15 _C
U
C
TI
O N
O N
EXAMPLE:
ST
R
Pressure altitude . . . . . . . . . . . . . 4000 ft
FO
R
Solution:
IN
All up mass (incl. hoist load) . . . 3100 kg Acceleration distance = 300 m or 980 ft Height gain = 19 ft /100 ft (from Figure A.3 of FLM 9.1–1)
To climb from 45 ft to 300 ft, a segment 1 distance of 1340 ft / 410 m is needed.
9.2-4 – 34
APPROVED Rev. 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
300 ft
N TR
BKD2_FLH_0252_R
O
LL
ED
45 ft
O
CLEARWAY
SEGMENT I DISTANCE
C
Clear area hoist operation
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
Fig. 4
O
PY
N
O
T
C
ACCELERATION DISTANCE
APPROVED Rev. 2.1
9.2-4 – 35
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
5.4.2
Confined area hoist operations
5.4.2.1 Hover performance The hover performance chart for confined area operations is based on the hover out of ground effect performance achievable with the OEI 2 min rating with consideration given to the maximum aircraft height loss of 4 ft after an engine failure. The hover performance chart is valid only if used in conjunction with the following emergency procedures: Single engine failure – confined area operations
ED
–
(see Fig. 5)
Determine:
Maximum gross mass for hoist operations requiring OEI performance in confined area
Known:
OAT . . . . . . . . . . . . . . . . . . . . . . . +15 _C
C
O
N TR
O
LL
EXAMPLE:
O
T
Pressure altitude . . . . . . . . . . . . . 8000 ft
PY
N
Windspeed . . . . . . . . . . . . . . . . . . 25 kt
Gross mass = 2690 kg
LY
Solution:
–
C
O
For calculation: 50% headwind . . . . . . . . . . . . . . . 12,5 kt
O N
Enter chart (Fig. 5) at known OAT (+15_C) Move vertically upwards to known pressure altitude (8000 ft)
TI
O N
From point of intersection move horizontally right to the reference line of the wind credit chart.
U
C
From this point follow the direction of the wind credit guide lines.
ST
R
Enter chart at known windspeed (12,5 kt).
FO
R
IN
Move vertically upwards to intersect tracing from above.
9.2-4 – 36
From point of intersection move horizontally right and read max. gross mass = 2690 kg. (Using the example on the assumption of no wind, the solution is 2625 kg).
APPROVED Rev. 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
TU206 NOT installed
EFFECTIVITY
HEC HOIST OPERATIONS REQUIRING OEI PERFORMANCE CONFINED AREA (OEI 2 MIN) TURBOMECA ARRIEL 2E (WITHOUT TU206) 1900 2000
LL
ED
2100
N TR
O O
2400
T
C
2500
MAX. OAT
2800 2900
LY
–
C
O
MIN. OAT
PY
N
O
2600 2700
O N
3000
O N
3100
TI
3200
U
C
3300
–30
–20
–10
0
10
20
30
40
50
60 0
3600 BK117D2708_1_r1
IN R FO –40
3500
REFERENCE LINE
ST
R
3400
GROSS MASS LIMIT 3700 KG –50
2300
GROSS MASS – kg
MAX. DENSITY ALTITUDE 12000 FT
2200
3700
10
20
3800 30 [kt]
0 10 20 30 40 50 60 [km/h] HEADWIND
Fig. 5
APPROVED Rev. 3
HEC hoist operations requiring OEI performance – confined area (OEI 2 min)
9.2-4 – 37
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
EFFECTIVITY
TU206 NOT installed
HEC HOIST OPERATIONS REQUIRING OEI PERFORMANCE CONFINED AREA (OEI 2MIN) IBF INSTALLED TURBOMECA ARRIEL 2E (WITHOUT TU206)
ED
1900
N TR
O
LL
2000
O
MAX. DENSITY ALTITUDE 12000 FT
T
C
2300
N
O
2400
PY
2500
MAX. OAT
2900
TI
3000
U
C
3100
ST
R
3200
IN
3300 3400
R –20
–10
0
10
20
30
REFERENCE LINE
3500
40
50
60 0
3600 3700
10
20
3800 30 [kt]
BK117D2708_1_IBF_3_r1
–30
GROSS MASS – kg
O C
2800
O N
O N
LY
MIN. OAT
–
2700
FO –40
2200
2600
GROSS MASS LIMIT 3700 KG –50
2100
0 10 20 30 40 50 60 [km/h] HEADWIND
Fig. 6
9.2-4 – 38
HEC hoist operations requiring OEI performance – confined area (OEI 2min) IBF installed
APPROVED Rev. 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
TU206 installed or after Helionix Maintenance Release 1
EFFECTIVITY
HEC HOIST OPERATIONS REQUIRING OEI PERFORMANCE CONFINED AREA (OEI 2 MIN) TURBOMECA ARRIEL 2E (WITH TU206) 2000 2100
ED
2200 MAX. DENSITY ALTITUDE 12000 FT
O
N TR
O
LL
2300
2800 2900
– LY O N
3100
O N
3200
TI
3300
–10
0
10
20
30
40
50
60 0
3600 3700
10
20
3800 30 [kt]
BK117D2708_1_r2
ST –20
3500
REFERENCE LINE
R
U
C
3400
GROSS MASS LIMIT 3700 KG –30
GROSS MASS – kg
C T MAX. OAT
N
O
2700
3000
IN –40
2500 2600
C
O
PY
MIN. OAT
R FO –50
2400
0 10 20 30 40 50 60 [km/h] HEADWIND
Fig. 7
APPROVED Rev. 4
HEC hoist operations requiring OEI performance – confined area (OEI 2 min)
9.2-4 – 39
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
TU206 installed or after Helionix Maintenance Release 1
EFFECTIVITY
HEC HOIST OPERATIONS REQUIRING OEI PERFORMANCE CONFINED AREA (OEI 2MIN) IBF INSTALLED TURBOMECA ARRIEL 2E (WITH TU206) 2000
ED
2100
MAX. DENSITY ALTITUDE 12000 FT
O
N TR
O
LL
2200
C T MAX. OAT
PY
2700 2800 2900
O N O N
3100
TI
3200
U
C
3300
–10
0
10
20
30
40
50
60 0
3600 3700
10
20
3800 30 [kt]
BK117D2708_1_IBF_3_r2
IN –20
3500
REFERENCE LINE
ST
R
3400
GROSS MASS LIMIT 3700 KG –30
GROSS MASS – kg
N
O
2600
3000
R –40
2400 2500
LY
–
C
O
MIN. OAT
FO –50
2300
0 10 20 30 40 50 60 [km/h] HEADWIND
Fig. 8
EFFECTIVITY
9.2-4 – 40
HEC hoist operations requiring OEI performance – confined area (OEI 2min) IBF installed
All APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
5.4.2.2 Obstacle clearance SAFE OBSTACLE CLEARANCE IS ONLY GUARANTEED IF THE HELICOPTER IS HOVERING CLEAR OF OBSTACLES DURING THE HOIST OPERATION.
CAUTION
Safe obstacle clearance can be determined in accordance with Fig. 9 as follows: Acceleration distance:
LL
ED
The aircraft height during the hoist operation shall be such that all obstacles in the area required for acceleration from hover to VTOSS are at least 35 ft below the initial aircraft hover height. Up to 2000 ft DA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 m / 660 ft
–
Above 2000 ft DA and up to 7000 ft DA: . . . . . . . . . . . . . . . . . . . . . . . . . . 300 m / 980 ft
–
Above 7000 ft DA: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 400 m / 1310 ft
C
O
N TR
O
–
O
T
Segment I distance:
The climb rate and distance covered during the Segment I climb from the hover height during hoisting to (at least) 300 ft AGL can be determined using the Segment I climb rates given in the Cat A flight manual supplement (FMS 9.1–1). If the Segment 1 climb is extended above 300 ft AGL, the maximum Segment 1 distance shall not exceed: 8000 ft – 30 x (hover height in ft) or 2400 m – 30 x (hover height in m)
LY
–
C
O
PY
N
–
(see Fig. 9)
Determine:
Obstacle clearance
Known:
OAT . . . . . . . . . . . . . . . . . . . . . . . . 15 _C
U
C
TI
O N
O N
EXAMPLE:
ST
R
Pressure altitude . . . . . . . . . . . . . 4000 ft
R
IN
All up mass (incl. hoist load) . . . 2900 kg Desired height at end of segment 1 climb 500 ft instead of 300 ft
FO EFFECTIVITY
Hover height . . . . . . . . . . . . . . . . . 140 ft IBF not installed
TU206 NOT installed
Solution:
Acceleration distance = 300 m or 980 ft Height gain = 24 ft /100 ft (from Fig A3 of FMS 9.1–1) To climb from 140 ft to 500 ft, a segment 1 distance of 1500 ft / 460 m is needed. The maximum allowed distance of the Segment 1 climb is 8000 – 30x140= 5200 ft. Since 5200 ft / 1560 m is less than the distance required to climb to 500 ft (1500 ft / 460 m), the climb to 500 ft is possible.
APPROVED Rev. 5
9.2-4 – 41
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
EFFECTIVITY
TU206 installed or after Helionix Maintenance Release 1
Solution:
Acceleration distance = 300 m or 980 ft Height gain = 32 ft /100 ft (from Fig A9 of FMS 9.1–1) To climb from 140 ft to 500 ft, a segment 1 distance of 1125 ft / 340 m is needed.
All
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
EFFECTIVITY
ED
The maximum allowed distance of the Segment 1 climb is 8000 – 30x140= 5200 ft. Since 5200 ft/ 1560 m is less than the distance required to climb to 500 ft (1125 ft / 340 m), the climb to 500 ft is possible.
9.2-4 – 42
APPROVED Rev. 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
Example
N
O
T
BKD2_FLH_0253_R
C
O
N TR
O
LL
ED
300 ft
SEGMENT I DISTANCE
–
C
O
PY
ACCELERATION DISTANCE
OEI TRAINING
LY
O N
5.5
Confined area hoist operation
O N
Fig. 9
U
C
TI
Training of the following single engine emergency procedures may be conducted using the procedures detailed in FLM supplement 9.1–3:
ST
R
– HEC hoist operations requiring OEI performance – single engine failure – clear area operations
R
IN
– HEC hoist operations requiring OEI performance – single engine failure – confined area operations
FO
The maximum weight of the rotorcraft-load combination to be used for OEI training shall be obtained from the respective charts with IBF INSTALLED (Fig. 3 for clear area hoist operations and Fig. 6 for confined area hoist operations). NOTE
APPROVED Rev. 4
It is good practice to perform all OEI training with an NHEC load only.
9.2-4 – 43
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
6
MASS AND BALANCE
6.1
MASS AND BALANCE CORRECTION Refer to Equipment List entries in Section 6 of the basic Flight Manual. For calculation of the C.G., the operating position of the hoist operator shall be considered. CG of the hoist operater:
N
O
T
C
O
N TR
O
LL
ED
1
C
O
PY
2
LY
1070 –1070
O N
3500
Y–BL
CG CALCULATION PROCEDURE
TI
6.2
3500
O N
1 RH 2 LH
–
X–STA
FO
R
IN
ST
R
U
C
To determine the longitudinal and lateral C.G. position during hoist operation, a “pre-hoist” mass and C.G. of the helicopter without considering the hoist load shall be calculated. This “pre-hoist” mass and C.G. includes the mass/C.G. of the aircraft and hoist installation, the flight crew, and the hoist operator standing on the skid. It does not include the hoist load attached to the hook. In other words, the “pre-hoist” mass/C.G. is the aircraft mass/C.G. before picking up the load from the ground or after dropping off a load on the ground. 6.2.1
Determining the longitudinal CG for hoist operations The overall mass and longitudinal C.G. must stay within the mass and C.G. diagram of the basic helicopter under all circumstances during hoist operation. To determine the overall mass and longitudinal C.G. during hoist operations, enter the “pre-hoist” mass and C.G. in the mass/C.G. envelope chart of Fig. 10. From the auxiliary lines, read the maximum permissable hoist load. If necessary, interpolation between the auxiliary lines is permitted. This mass and C.G. calculation takes into account all hoist boom positions between retracted and fully extended.
9.2-4 – 44
MANUFACTURER’S DATA APPROVED Rev. 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
EXAMPLE:
Fig. 10
Determine:
Maximum hoist load for given helicopter mass and C.G. without hoist load
Known:
Helicopter in-flight gross mass without expected hoist load 2800 kg In-flight C.G.
4450 mm
Expected load weight
ED
Helicopter C.G. remains within permissible range when hoist load is picked up and hoist boom is retracted. Enter chart at known C.G. (4450 mm)
N TR
O
Move vertically upwards to gross mass (2800 kg)
LL
Solution:
160 kg
O
Interpolate between the dashed lines to obtain the maximum permissible hoist load = 250 kg
O
T
C
Basic C.G. envelope for hoist operation
BKD2_FLH_0367_R
C –
B
A B C D
O N
O N
LY
A
X–STA – mm 4380 4535 4700 4347
GM – kg 3700 3700 2000 2400
U
C
TI
Auxiliary lines
180 kg
272 kg
R ST IN R
3900 3800 3700 3600 3500 3400 3300 3200 3100 3000 2900 2800 2700 2600 2500 2400 2300 2200 2100 2000 1900
FO
Gross Mass – [kg]
O
PY
N
The dashed lines indicate the maximum load which can be picked up safely to stay within longitudinal C.G limit when hoist boom will be retracted during hoist operation (most forward C.G. condition).
D
C 4300
4350
4400
4450
4500
4550
4600
4650
4700
4750
X–STA – [mm]
Fig. 10
Basic C.G. envelope with additional information to determine the C.G. envelope with hoist load.
MANUFACTURER’S DATA APPROVED Rev. 4
9.2-4 – 45
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
Special hoist C.G. envelope Max. allowable hoist load is indicated by the smallest envelope, which encloses the intersection point of in-flight gross mass and in-flight C.G. 3800
A’
A
B
3600
3000
GM – kg 3700 3700 2000 2400
A’ D’
4300 4300
3700 3000
LL
D’
N TR
O
2800
O
2600 2400
C
D
N
O
T
2200
C
PY
2000
4300
4350
4400
4450
4500
C
4250
O
1800
4550
4600
4650
4700
4750
–
X–STA – mm
LY
BKD2_FLH_0478_R
X–STA – mm 4380 4535 4700 4347
ED
50 kg 100 kg 150 kg 200 kg
Gross Mass – kg
3200
272 kg
3400
A B C D
Special hoist C.G. envelope with additional information to determine the CG envelope with hoist load.
Determining the lateral CG for hoist operations
TI
6.2.2
O N
O N
Fig. 11
IN
The actual lateral C.G. of the aircraft during the hoist operation (i.e. the aircraft C.G. including the hoist load) is allowed to exceed the basic lateral C.G. envelope.
FO
R
NOTE
ST
R
U
C
The lateral “pre-hoist” mass and C.G. shall be within the basic helicopter’s lateral C.G. envelope during hoist operations.
9.2-4 – 46
MANUFACTURER’S DATA APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
7
SYSTEM DESCRIPTION The external hoist system is attached with quick-release pins to the LH side or RH side of the main gear box deck. It provides lifting capability via a boom mounted, motor driven hoist. The external hoist system consists of the winch unit, an electric driven boom, a cable cutter assembly and a control pendant. As an option a light could be attached to the external hoist system.
WINCH UNIT
ED
7.1
LL
The winch unit comprises of:
A main drive motor supplied with 28V DC providing continous operation with a power consumption of up to 125 A.
–
An automatic load-sensitive brake assembly which controls the reel-out of the cable and holds the load in a selected position when hoist operation is interrupted.
–
A level wind and storage drum assembly which ensures correct and even winding of the cable on the drum.
–
A traction sheave assembly provides a constant minimum tension on the cable at all times to prevent miswrap during no-load operation.
–
An overload clutch.
–
A steel cable with 91 m (295 ft) or 50 m (169 ft) usable length. The first and the last 6.1 m (20 ft) of the cable are colored bright orange.
–
A hook-damper unit. The hook-damper can be optionally equipped with a floatation element and with a weight-kit that allows the installation of up to three weights of 1kg each to improve the aerodynamic stability of the damper. If installed, these weights reduce the maximum hoist payload accordingly.
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
–
FO
R
IN
The average cable speed with a hoist load of 270 kg is 0.76 m/s (150 ft/min) or 1.02 m/s (200 ft/min) with 130 kg. The maximum cable speed is 1.27 m/s (250 ft/min). During hoist cable reel-out within approx. the first and the last 3 m (10 ft) of the cable the speed is automatically limited to 0.51 m/s (100 ft/min). During hoist cable reel-in within approx. the first and the last 3 m (10 ft) of the cable the speed is automatically limited to 0.25 m/s (50 ft/min). Additionally the speed is further reduced to 0.08 m/s (15 ft/min) when there is approx. 0.25 m (0.8 ft) cable left between cable guide and hook striker disk. For further information refer to the “Hoist manufacturers - Component Maintenance Manual”.
MANUFACTURER’S DATA APPROVED Rev. 6
9.2-4 – 47
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
Overhead panel OFF
SYS1
ENGAGE
EXT
SYS2
BATT MSTR
HYD
OFF
1
OFF
OFF
ARM
TEST
HOIST CBL CUT
1
EXT/ WARN
2
FIRE TEST OFF A R M
O N CC TEST
2
OFF N O R M
O N
CARGO HOOK
ON
EMER FLOATS
FUZZ BURN
OFF
ON
COPILOT PILOT PT/STATIC HTG
LAVCS
Sliding door upper frame 2
O
T
C
O
N TR
O
LL
ED
1
CLOSE O P E N NORM
PY
N
Cable Cutter
RAISE FOR CABLE CUT
10 9
REEL OVERHEAT
BOOM
TI
3
CABLE METER OUT
IN
8
IN
6
7
R
U
C
5
CAUTION
OUT
O N
O N
LY
–
C
O
4
R
CUT
DIM/FOC
ST
IN
CABLE
S/L LT M I R HISL
L D G L T
S/L LT
ON
OFF
STOW
FO
BAMBI
BKD2_FLH_0190_R
DUMP
IR/ VIS BEEP TRIM ORIENT CTL
Collective lever hoist control Control pendant Fig. 12
9.2-4 – 48
External hoist system – typical installation MANUFACTURER’S DATA APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
HOIST CBL CUT (3-way switch)
OFF
No power supply to the external hoist system.
ON
Initiates power supply to the external hoist system.
CC TEST
(momentary)
Starts cable cutter electrical test. A successful cable cutter test is indicated in the master list by the CABLE CUT TEST OK message.
HOIST
Hoist motor is operational.
HOIST STBY
Hoist motor is stopped. Reeling the cable in and out is no longer possible.
O
HOIST/HOIST STBY (push button) Refer to the NOTE belowthis table
ED
FUNCTION
N TR
2
POSITION
LL
1
SWITCH/ DISPLAY
CUT CABLE (push button, guarded)
Causes the pyrotechnic cable cutter to cut cable when pressed.
4
CABLE METER (digital display)
Allows a continuous monitoring of cable length in meters during hoist operation.
5
CAUTION (yellow light)
Illuminates when the cable length is within 10 ft before fully reeled in or reeled out position. The light flashes for two seconds to check for operation when the hoist is initially powered-up.
6
OVERHEAT (red light)
7
REEL (thumb wheel, y, momentary, center-off) ff)
O N
O N
LY
–
C
O
PY
N
O
T
C
O
3
Slight rotation forward initiates hoist cable reel-out movement. Cable speed is proportional to the rotation of the thumb wheel.
IN
Slight rotation backwards initiates hoist cable reelin movement. Cable speed is proportional to the rotation of the thumb wheel.
IN
ST
R
U
C
TI
OUT
Intercom (trigger)
9
BOOM (2-way (2 way switch, momentary, center-off)
Allows communication with pilot or other connected personnel when pressed.
FO
R
8
OUT
Extends hoist boom.
IN
Retracts hoist boom.
10 RAISE FOR CABLE CUT (push button, guarded)
Causes the pyrotechnic cable cutter to cut cable when pressed.
Fig. 13 MANUFACTURER’S DATA APPROVED Rev. 4
Illuminates if the hoist gearbox lube oil or hoist motor temperature limitations are exceeded. The light flashes for two seconds to check for operation when the hoist is initially powered-up.
Controls and display functions
9.2-4 – 49
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
EFFECTIVITY NOTE
EFFECTIVITY
S/N 20103 and subsequent or after SB MBB–BK117 D–2–33–005 If the HOIST / HOIST STBY pb is switched to ”HOIST” and a cabin door is opened, all emergency lights will remain off. In this case the cabin lights can be switched on by pushing the button next to the light. If the HOIST / HOIST STBY pb is switched to ”HOIST STBY” or if the HOIST CBL CUT switch is set to OFF, the emergency lighting system will be activated again. All
HOIST CONT (ESS BUS 1): Supplies the hoist motor and control unit.
–
HOIST CC–COL (ESS BUS 1): Supplies the pilot/copilot cable cut system
–
HOIST BOOM (ESS BUS 1): Supplies the hoist boom motor.
–
HOIST CC–PED (ESS BUS 2): Supplies the hoist operator cable cut system.
N TR
O
C O
T
MFD INDICATIONS –
O
LL
–
Cable Length:
N
7.2
ED
In addition to the switches detailed in Fig. 13, the following circuit breakers are located in the overhead console:
LY
The hoist unit (meters or feet) selection on the VMS/CONF page only affects the cable length indication on the VMS page. It does not affect the indication on the hoist pendant, which is always in meters. CABLE CUT TEST OK
TI
–
O N
O N
NOTE
–
C
O
PY
A digital display on the VMS page (DATA area) allows a continuous monitoring of cable length reeled-out in meters or feet (as configured on the CONF page) during hoist operation.
(ML information message):
ST
R
U
C
Hoist system electrical test of the cable cutter wiring (HOIST/CBLCUT switch, CC TEST) has been succesfully performed. –
(ML information message):
IN
HOIST
–
FO
R
Indicates that the external hoist system is activated (HOIST/CBLCU switch ON) and electrical cable cutter is armed.
Flight report page: Page 4 of the flight report page shows the number of hoist cycles that were performed during the flight. A hoist cycle is counted each time the hoist cable is extended beyond 5 m.
NOTE D Hoist cycles performed on the ground with engines stopped (e.g. for maintenance) will be automatically added to the hoist cycle count of the next flight. D Due to a problem with data acquisition, the hoist cycle counting sometimes does not work (** cycles indicated). In this case, record the number of cycles counted by the operator.
9.2-4 – 50
MANUFACTURER’S DATA APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
7.3
CABLE CUTTER
7.3.1
Pyrotechnic cable cutting device (primary) An electrically activated pyrotechnic cable cutting device (primary) is installed at the exit of cable from winch unit for emergency use to cut off the extended portion of the cable.
O
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1
O N
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Manually operated cable cutter (secondary)
U
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7.3.2
Pyrotechnic cable cutting device (primary) – typical installation
O N
Fig. 14
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–
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O
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N
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1 Cable cutter cartridge
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R
IN
ST
R
A manually operated pair of cable cutting shears is located inside the cabin. It operates as a back-up system in case the pyrotechnic cable cutter fails to operate for any reason.
MANUFACTURER’S DATA APPROVED Rev. 4
9.2-4 – 51
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7.4
HOIST HOOKS
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Two different types of hooks can be installed on the hoist hook/damper unit:
D-lock hook
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Hoist hooks – typical installation
D-lock hook
O
7.4.1
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Fig. 15
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Standard hook
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The D-lock hook consists of one large hook and a small ring. The large hook shall be used to attach the main load. The small ring can be used to attach very light loads only (e.g. an anti-static line).
TI
Standard hook
R
THE STANDARD HOOK HAS NO LOCKABLE KEEPER. THEREFORE, IMPROPER LOAD ATTACHMENTS CAN ROLL OUT OF THE HOOK UNDER DYNAMIC CONDITIONS.
R
IN
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WARNING
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7.4.2
O N
The large hook is automatically protected against inadvertent opening (e.g. due to dynamic roll out).
FO
CAUTION
LOADS ATTACHED TO THE SMALL HOOK COULD CAUSE THIS HOOK TO BE SIGNIFICANTLY DAMAGED. LOADS SHALL ONLY BE HOOKED INTO THE LARGE HOOK.
The standard hook consists of a large load-bearing hook, a small non-load-bearing hook and a small ring. The large hook shall be used to attach the main load. The small hook and ring shall be used to attach very light loads or an anti-static line only. The risk of dynamic roll-out from the main hook can be eliminated by using a means of attachment (e.g. ring, special attachment plate) with an inner diameter of 40 mm or less.
9.2-4 – 52
MANUFACTURER’S DATA APPROVED Rev. 4
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7.5
CABLE OSCILLATIONS The cable with or without load is susceptible to start oscillating under certain conditions (e.g. abrupt maneuvers, wind gusts, non-vertical load pickup, flight with poor visual references). If not taken care of immediately, an oscillating load may rapidly become unmanageable. This can lead to: Load swinging into objects (rock faces, ship structures), causing injuries to persons on the hoist.
–
Cable chafing on the skids, resulting in damage to the cable.
–
Damage to the hoist unit.
–
Load getting caught or wrapped around the end of the skids or other parts of the helicopter, resulting in dangerous C.G. changes and possibly critical cable damage.
–
Load swinging into the main rotor or fenestron, causing loss of control to the helicopter.
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Hoist (schematic)
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The physics of the pendulum (Fig. 16), dictates that the pendulum energy is constant. As a result, the angle and frequency of the oscillation will become larger as the cable is reeled in, whilst the amplitude remains more or less constant. Conversely, the angle and frequency of oscillation will reduce when the cable is reeled out, resulting in a less violent swinging of the load.
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Short Cable
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h1
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h1 = h2
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BKD2_FLH_0577_R
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Long Cable
h2
Fig. 16
Pendulum schematic
Therefore, the hoist should never be reeled in further if oscillations are present. Small oscillations can often be damped by acting on the cable (grabbing it with hand or feet and pushing it against the direction of swing). Care should be taken to avoid injuries while doing this. Large oscillations or divergent oscillations should be reduced by reeling-out the cable whenever possible. In this case, care should be taken to prevent the load from contacting the ground or obstacles. MANUFACTURER’S DATA APPROVED Rev. 6
9.2-4 – 53
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
Most often, a small forward speed of about 30 kt (up to 45 kt) will also have a stabilizing effect on oscillations. 7.6
CABIN AUDIO CONTROL PANEL
7.6.1
Single winch operator configuration P–VOL
CALL
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W–VOX
WINCH OPER.
C
BKD2_FLH_0189_R
O
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O
W–VOL
PAX PAX HEADSET
C
O
Cabin audio control panel – typical single configuration
–
Fig. 17
PY
N
O
T
WINCH PAX HEADSET
O N
O N
LY
The hoist operator should connect to the WINCH connector on the cabin audio control panel (Fig. 17). This connects the hoist operator to Intercom 1 (copilot). Adjustments can be made through ACU1 or directly through the cabin audio control panel, as follows: VOX level increase: Press the W-VOX switch for a short time (0.3 s to ~3 s), to increase the VOX level (i.e. decrease the sensitivity of the “hot mike“ function). By pressing the W-VOX switch for more than 3 seconds, the VOX level will be reset to the level set on the copilot’s ACU.
–
Volume level increase: Press the W-VOL switch for a short time (0.3 s to ~3 s), to increase the volume of intercom and radio. By pressing the W-VOL switch for more than 3 seconds, the volume will be reset to the level set on the copilot’s ACU.
FO
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–
9.2-4 – 54
MANUFACTURER’S DATA APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
Dual winch operator configuration W–VOX
CALL
WINCH OPER.
WINCH CREW I
PAX
WINCH CREW II
O
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WINCH BKUP
ED
BKD2_FLH_0189_R
W–VOL
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7.6.2
Cabin audio control panel – typical dual configuration
T
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Fig. 18
C
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N
O
The hoist operator / instructor should connect to the respective WINCH CREW connectors on the cabin audio control panel (Fig. 18). Adjustments to the intercom settings can be made on the respective CREW intercom control panel (ACU) as described in para 7.6.1.
LY
–
The WINCH CREW connectors should be used as follows:
O N
– WINCH CREW I for the hoist instructor (trainer), using the smaller hoist control pendant, which does not have all functionalities (only cable cut and hoist boom in/out).
TI
O N
– WINCH CREW II for the hoist student (trainee), using the hoist control pendant, which has all functionalities.
IN
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R
U
C
The intercom system has a built in backup-circuit. The switch over to backup is iniated by cockpit crew action – the selector switch on pilot or co–pilot ACU has to be switched to BKUP – or if the intercom system detects an internal failure. In case the intercom system is in backup-mode only the following routings and functionalities are active:
R
– Intercom 1 (copilot) – TX1 (VHF–AM 1) and FIX1 (AMC)
FO
– Intercom 2 (pilot) – TX2 (VHF–AM 2) and FIX 2 (AMC) – Intercom volume level is fixed to 50% – No actions on the ACUs are supported In backup mode the hoist operators are disconnected from the intercom system. This can be recognised by loosing the hot mike function, tels audio and sidetone in the cabin crew headsets. In this case the hoist operator in charge has to disconnect his/her headset from the WINCH CREW socket and connect to the WINCH BKUP socket to restore communication to the pilot via intercom 1.
MANUFACTURER’S DATA APPROVED Rev. 4
9.2-4 – 55
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
7.7
EXTERNAL HOIST LIGHT (OPTIONAL)
Fig. 19
External hoist light
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The external hoist light can be attached to the external hoist to provide sufficient lighting during hoist operation. The light is similar to the fixed landing light and clamped to the external hoist boom. It can be switched on/off by the hoist operator via a switch installed at the upper sliding door frame.
9.2-4 – 56
MANUFACTURER’S DATA APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL HOIST SYSTEM
8
HANDLING, SERVICE, MAINTENANCE
8.1
DAILY POST FLIGHT INSPECTION WARNING D LUBRICATING OIL, MIL–L–23699, IS TOXIC TO SKIN, EYES AND RESPIRATORY TRACT. AVOID SKIN AND EYE CONTACT. GOOD GENERAL VENTILATION IS NORMALLY ADEQUATE.
LL
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D TO AVOID INJURIES FROM E.G. BROKEN STRANDS, ALL PERSONS HANDLING THE HOIST CABLE MUST WEAR ADEQUATE PROTECTIVE GLOVES.
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CAUTION D WHEN HANDLING THE HOIST CABLE WITH A CLOTH, DO NOT ALLOW THE CLOTH TO GET CAUGHT UP INTO THE DRUM ASSEMBLY.
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D WHILE REELING THE CABLE OUT, USE CARE NOT TO PULL CABLE TAUT AGAINST THE CABLE GUIDE ROLLERS, AS KINKING OF THE CABLE CAN RESULT. THIS CAN BE AVOIDED BY USING A SETUP AS SHOWN IN FIG. 20.
O N
O N
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–
C
D REELING THE CABLE IN AND OUT WITHOUT A HOOK LOAD MAY RESULT IN LOOSENING OF THE OUTER CABLE LAYERS. TO AVOID POSSIBLE DAMAGE TO THE CABLE, MINIMIZE NO LOAD CABLE CYCLES. ONE METHOD TO AVOID THIS IS TO KEEP TENSION ON THE CABLE WHEN REELING IN AND OUT AS SHOWN IN FIG. 20.
ST
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D CABLE CONTACT WITH THE GROUND OR OTHER ABRASIVE SURFACE SHALL BE AVOIDED AS DIRT OR ABRASIONS MAY DAMAGE THE CABLE.
FO
R
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NOTE D The post-flight cable inspection must be performed by a person properly trained to identify and evaluate the various possible cable defects and damages. This includes broken wires, kinks, bird cages, flattened areas, abrasion, necking, gouges, and shock load damage (refer to the Hoist Manufacturer ’s Component Maintenance Manual). D Details of the materials, fluids and lubricants to be used shall be obtained from the Hoist Manufacturer’s Component Maintenance Manual. D When reeling the cable in and out, it is recommended not to lay the cable on the ground to prevent damage and entanglement to the cable. The following proven methods can be used: – Use a large rotatable container to lay down the cable. This is the method of choice if cable cleaning is required. – Use the set–up as shown in Fig. 20. If this method is used to inspect a long
MANUFACTURER’S DATA APPROVED Rev. 5
9.2-4 – 57
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cable length, additional persons may be required to support the cable and prevent it from dragging on the ground. – Use a protective pad and lay down the cable in large figure of eight pattern.
ED
D When the cable is reeled in, a tension of at least 9 kg (20 lbs) should be maintained. This can be most conveniently accomplished by applying the pre–tensioning technique shown in Fig. 20. The person pulling the cable should apply a tension of at least 9 kg. If not enough persons are available to apply this method without dragging the cable on the ground or through dirt, cable tension can be applied by maintaining a positive pull to the cable while reeling in with a gloved hand (and low lint cloth).
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The daily post flight inspection of the hoist cable must be performed at end of each day when the hoist was in use. For helicopters on operation 24 h/day, the daily post flight inspection must be performed at least once every 24 hours if the hoist was in use.
– Connect
2. BAT MSTR sw
T
1. External power unit
O
C
O
Procedure
PY
N
– ON and ENGAGE, allow approx. 20 sec for system to boot
C
O
3. HOIST / CBL CTR switch
If the cable was in contact with salt water during the day
O N
EFFECTIVITY
– Check HOIST illuminated
LY
–
4. HOIST/HOIST STBY push button in cabin
– ON
O N
5. Using the hoist pendant, reel out the hoist cable to the full extend. Reel the cable into a large container filled with a mild soap and water solution.
U
C
TI
6. Drain the soap solution from the wash container and rinse the cable with fresh water.
IN
ST
R
7. Slowly reel-in the cable assembly using a low lint cloth to dry the cable while maintaining tension on the cable.
R
8. Using the hoist pendant, reel out the hoist cable to the full extend.
FO
9. Saturate a low lint cloth with WD–40 or VPCI340CLP lubricant. Wrap saturated cloth around the cable. 10. Slowly reel in cable assembly while holding cloth wrapped around cable. Maintain tension to the cable while reeling in. 11. Remove cloth and fully extend cable assembly. 12. Saturate a low lint cloth with MIL–L–23699 or MIL–L–7808 oil. Wrap saturated cloth around cable assembly. 13. While holding cloth wrapped around cable, slowly reel in cable assembly. Maintain tension to the cable while reeling in. 14. Remove cloth from cable.
EFFECTIVITY
9.2-4 – 58
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15. Slowly rotate the control pendant REEL IN/OUT thumbwheel in the REEL OUT. direction and reel-out the cable at a controlled speed to the maximum length used during the day + 3 meters (10 ft). Cleaning the cable with a low-lint cloth will aid in the inspection requirement to locate broken wires. Broken wires will snag the cloth being used to clean the cable.
NOTE
16. Slowly rotate the control pendant REEL IN/OUT thumbwheel in the REEL IN direction and slowly reel-in the cable at a controlled speed.
N TR
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17. As the cable is reeling in, remove dirt from cable and visually inspect cable for broken wires, kinks, bird caging, flattened areas, abrasion, necking or other visible damage. Also check for correct alignment and lay of the cable on the cable drum. Make sure the cable lays evenly on the cable drum. Make sure there is a tension applied to the cable, that the crowder roller rotates freely, and that there is no interference to the reeling in of the cable.
T
C
O
18. Slowly reel-in the cable until the limit switches stop the hoist operation automatically and the final reel-in movement applies a tension to the hoist cable.
C
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N
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19. Control pendant REEL IN/OUT thumbwheel
LY
–
20. HOIST/HOIST STBY push button in cabin
– Release – Check thumbwheel returns to the center position automatically. – Push, check extinguishes – OFF
22. BAT MSTR sw
– OFF
O N
O N
21. HOIST / CBL CTR switch
– Disconnect
FO
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IN
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23. External power unit
HOIST
Fig. 20 Typical set-up for performing a ground cable inspection. The diameter of the pulley (1) shall be at least 75 mm. If necessary, additional persons may be required to support the cable and prevent it from dragging on the ground. MANUFACTURER’S DATA APPROVED Rev. 4
9.2-4 – 59/(9.2-4 – 60 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
FMS
9.2-5
SUPPLEMENT FOR
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INLET BARRIER FILTER SYSTEM
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This Supplement shall be attached to the BK117 D-2 Flight Manual (Section 9.2) when the Inlet Barrier Filter System is installed.
Effectivity
Inlet Barrier Filter System
All
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System/Equipment Designation
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-5 – 1
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LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
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APPROVED Rev. 3
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LEP – manufacturer‘s data (part 2): Page
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Date: DEC 12, 2018
Approved by EASA:
EASA approval no.: 10067961
APPROVED Rev. 3
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TABLE OF CONTENTS Page GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 9
1.1
DEFINITION OF TERMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 9
2
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 9
2.1
OPERATIONAL LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 9
2.1.1 2.1.2
OAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 9 Maximum pressure altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 9
3
EMERGENCY AND MALFUNCTION PROCEDURES . . . . . . . . . . . . . 9.2-5 – 10
3.1 3.2
CAUTION INDICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 10 WHITE ADVISORIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 14
3.3
SINGLE ENGINE FAILURE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 14
4
NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 15
4.1 4.1.1
PREFLIGHT CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 15 Exterior check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 15
4.1.2 4.2
Interior check (to be performed before engine start, before first flight of the day) . . 9.2-5 – 16 ENGINE SHUTDOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 16
5
PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 17
5.1
Performance indication on the VMS page . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 17
5.2 5.2.1
POWER CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 17 Automatic ground power check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 17
5.2.2 5.2.3
Automatic in-flight power check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 19 Manual ground power check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 21
5.2.4 5.3
Power trend monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 36 HEIGHT-VELOCITY ENVELOPE (H–V DIAGRAM) . . . . . . . . . . . . . . . 9.2-5 – 36
5.4 5.5
HOVER CEILING – AEO performance . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 40 HOVER CEILING – OEI Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 51
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5.5.1 Hover ceiling in ground effect - OEI Performance . . . . . . . . . . . . . . . . . 9.2-5 – 51 5.5.1.1 Bleed air consumers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 51 5.5.1.2 Performance data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 51 5.5.2 Hover ceiling out of ground effect - OEI Performance . . . . . . . . . . . . . 9.2-5 – 54 5.5.2.1 Bleed air consumers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 54 5.5.2.2 Performance data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 54 5.6 5.7
RATE OF CLIMB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 59 Landing distance from 50 feet height to a complete stop on the ground . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 80
5.8 5.8.1
ADDITIONAL NON-APPROVED PERFORMANCE DATA . . . . . . . . . . 9.2-5 – 82 Standard performance conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 82
9.2-5 – 4
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
Page Variable factors affecting performance . . . . . . . . . . . . . . . . . . . . . . . . . . Reading of the charts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Maximum cruising speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Specific fuel consumption . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Maximum range . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Endurance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6
MASS AND BALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 92
7
SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 92
7.1 7.2 7.3 7.3.1 7.4
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IBF system Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IBF indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IBF Master List messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flight report page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9.2-5 9.2-5 9.2-5 9.2-5 9.2-5 9.2-5
9.2-5 9.2-5 9.2-5 9.2-5 9.2-5
– 82 – 82 – 82 – 91 – 91 – 91
– 92 – 94 – 95 – 96 – 97
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5.8.2 5.8.3 5.8.4 5.8.5 5.8.6 5.8.7
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LIST OF FIGURES Automatic ground power check RESULTS page for engine 2 – example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Automatic ground power check RESULTS page for engine 2 – example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Automatic in-flight power check RESULTS page for engine 1 – example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Manual ground power check (TOT) for engine No.1 and 70% torque, clean bypass closed . . . . . . . . . . . . . . . . . . . . . . . . . . . . Manual ground power check (TOT) for engine No.2 and 70% torque, clean bypass closed . . . . . . . . . . . . . . . . . . . . . . . . . . . . Manual ground power check (N1) for engine No.1 and 70% torque, bleed valve open, clean bypass closed . . . . . . . . . . . . Manual ground power check (N1) for engine No.2 and 70% torque, bleed valve open, clean bypass closed . . . . . . . . . . . . Manual ground power check (N1) for engine No.1 and 70% torque, bleed valve closed, clean bypass closed . . . . . . . . . . Manual ground power check (N1) for engine No.2 and 70% torque, bleed valve closed, clean bypass closed . . . . . . . . . . Manual ground power check (TOT) for engine No.1 and 70% torque, bypass open . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Manual ground power check (TOT) for engine No.2 and 70% torque, bypass open . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Manual ground power check (N1) for engine No.1 and 70% torque, bleed valve open, bypass open . . . . . . . . . . . . . . . . . . Manual ground power check (N1) for engine No.2 and 70% torque, bleed valve open, bypass open . . . . . . . . . . . . . . . . . . Manual ground power check (N1) for engine No.1 and 70% torque, bleed valve closed, bypass open . . . . . . . . . . . . . . . . .
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Fig. 2
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Fig. 3
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Fig. 4
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9.2-5 – 19 9.2-5 – 21 9.2-5 – 24 9.2-5 – 25 9.2-5 – 26 9.2-5 – 27
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Fig. 7
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Fig. 6
9.2-5 – 17
FO
Fig. 8 Fig. 9
Fig. 10 Fig. 11 Fig. 12 Fig. 13 Fig. 14
APPROVED Rev. 1
9.2-5 – 28 9.2-5 – 29 9.2-5 – 30 9.2-5 – 31 9.2-5 – 32 9.2-5 – 33 9.2-5 – 34
9.2-5 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
Page
Fig. 18 Fig. 19 Fig. 20
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9.2-5 – 45 9.2-5 – 46 9.2-5 – 47
9.2-5 – 49 9.2-5 – 50
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TU206 NOT installed
9.2-5 – 48
Hover ceiling in ground effect (OEI, 2 min power, without TU206, heating off) . . . . . . . . . . . . . . . . 9.2-5 – 52 TU206 installed or after Hlelionix Maintenance Release 1 Hover ceiling in ground effect (OEI, 2 min power, with TU206, heating off) . . . . . . . . . . . . . . . . . . . 9.2-5 – 53
ST
TU206 installed or after Hlelionix Maintenance Release 1
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EFFECTIVITY
Hover ceiling out off ground effect (OEI, 2 min power, without TU206, heating off) . . . . . . . . . . . . . . . . 9.2-5 – 56
IN
Fig. 29
TU206 NOT installed
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EFFECTIVITY
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Fig. 28
9.2-5 – 44
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EFFECTIVITY
9.2-5 – 43
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Fig. 27
9.2-5 – 42
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EFFECTIVITY
9.2-5 – 41
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Fig. 25
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Fig. 24
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Fig. 23
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Fig. 22
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Fig. 21
9.2-5 – 35 9.2-5 – 39
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Fig. 16 Fig. 17
Manual ground power check (N1) for engine No.2 and 70% torque, bleed valve closed, bypass open . . . . . . . . . . . . . . . . . Height-velocity diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Hover ceiling in ground effect (AEO, TOP, clean bypass closed, heating off) . . . . . . . . . . . . . . . . . Hover ceiling in ground effect (AEO, TOP, clog trend bypass closed, heating off) . . . . . . . . . . . . . Hover ceiling in ground effect (AEO, TOP, bypass open, heating off) . . . . . . . . . . . . . . . . . . . . . . . . Hover ceiling in ground effect (AEO, TOP, bypass closed or open, heating on) . . . . . . . . . . . . . . . Hover ceiling out of ground effect (AEO, TOP, clean bypass closed, heating off) . . . . . . . . . . . . . . . . . Hover ceiling out of ground effect (AEO, TOP, clog trend bypass closed, heating off) . . . . . . . . . . . . . Hover ceiling out of ground effect (AEO, TOP, bypass open, heating off) . . . . . . . . . . . . . . . . . . . . . . . . Hover ceiling out of ground effect (AEO, TOP, bypass closed or open, heating on) . . . . . . . . . . . . . . . Hover ceiling out of ground effect (AEO, MCP, bypass closed or open, heating off) . . . . . . . . . . . . . . . Hover ceiling out of ground effect (AEO, MCP, bypass closed or open, heating on) . . . . . . . . . . . . . . .
LL
Fig. 15
Fig. 30 EFFECTIVITY Fig. 31 Fig. 32 Fig. 33 Fig. 34
9.2-5 – 6
Hover ceiling out off ground effect (OEI, 2 min power, with TU206, heating off) . . . . . . . . . . . . . . . . . . . 9.2-5 – 57 All Hover ceiling out off ground effect (OEI, 30 sec power, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rate of climb (AEO, MCP, 2000 kg to 2600 kg, clean bypass closed, clog trend bypass closed, bypass open, heating off) . . . . . . . . . . . . Rate of climb (AEO, MCP, 2600 kg to 3200 kg, clean bypass closed, clog trend bypass closed, bypass open, heating off) . . . . . . . . . . . . Rate of climb (AEO, MCP, 3200 kg to 3700 kg, clean bypass closed, clog trend bypass closed, bypass closed, heating off) . . . . . . . . . .
9.2-5 – 58 9.2-5 – 60 9.2-5 – 61 9.2-5 – 62 APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
Page Rate of climb (AEO, MCP, 2000 kg to 2600 kg, clean bypass closed, clog trend bypass closed, bypass open, heating on) . . . . . . . . . . . . 9.2-5 – 63
Fig. 36
Rate of climb (AEO, MCP, 2600 kg to 3200 kg, clean bypass closed, clog trend bypass closed, bypass open, heating on) . . . . . . . . . . . . 9.2-5 – 64
Fig. 37
Rate of climb (AEO, MCP, 3200 kg to 3700 kg, clean bypass closed, clog trend bypass closed, bypass closed, heating on) . . . . . . . . . . 9.2-5 – 65
Fig. 38
Rate of climb (OEI, MCP, 2000 kg to 2600 kg, bypass open, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 66
Fig. 39
Rate of climb (OEI, MCP, 2600 kg to 3200 kg, bypass open, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 67
Fig. 40
Rate of climb (OEI, MCP, 3200 kg to 3700 kg, bypass open, heating off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 68 Rate of climb (OEI, MCP, 2000 kg to 2600 kg, bypass open, heating on) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 69
LL
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Fig. 35
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Fig. 41
Rate of climb (OEI, MCP, 2600 kg to 3200 kg, bypass open, heating on) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 70 Rate of climb (OEI, MCP, 3200 kg to 3700 kg, bypass open, heating on) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 71
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EFFECTIVITY
Rate of climb (OEI, 2 min. power, without TU206, 2000 kg to 2600 kg, bypass open, heating off) . . . . . . . . . . . . . . . . . 9.2-5 – 72 Rate of climb (OEI, 2 min. power without TU206, 2600 kg to 3200 kg, bypass open, heating off) . . . . . . . . . . . . . . . . . 9.2-5 – 73
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Fig. 45
Rate of climb – VTOSS (OEI, 2 min. power, without TU206, 3200 kg to 3700 kg, bypass open, heating off) . . . . . . . . . . . . . . . . . 9.2-5 – 74
O N
Fig. 46
TU206 installed or after Helionix Maitenance Release 1
O N
EFFECTIVITY
Rate of climb (OEI, 2 min. power, with TU206, 2000 kg to 2600 kg, bypass open, heating off) . . . . . . . . . . . . . . . . . 9.2-5 – 75
Fig. 48
Rate of climb (OEI, 2 min. power, with TU206, 2600 kg to 3200 kg, bypass open, heating off) . . . . . . . . . . . . . . . . . 9.2-5 – 76
Fig. 49
Rate of climb – VTOSS (OEI, 2 min. power, with TU206, 3200 kg to 3700 kg, bypass open, heating off) . . . . . . . . . . . . . . . . . 9.2-5 – 77
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EFFECTIVITY Fig. 50
EFFECTIVITY Fig. 51 EFFECTIVITY Fig. 52
TU206 NOT installed
Rate of climb – VY (OEI, 2 min. power, without TU206, 3200 kg to 3700 kg, bypass open, heating off) . . . . . . . . . . . . . . . . . 9.2-5 – 78 TU206 installed or after Helionix Maitenance Release 1 Rate of climb – VY (OEI, 2 min. power, 3200 kg to 3700 kg, bypass open, heating off) . . . . . . . . . . . . . . . . . 9.2-5 – 79 All
Fig. 53
Landing distance from 50 ft height to a complete stop on the ground (OEI) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 81 Maximum cruising speed (AEO, bypass closed, ISA) . . . . . . . . . . . . . 9.2-5 – 83
Fig. 54
Maximum cruising speed (AEO, bypass closed, ISA –20_C) . . . . . . . 9.2-5 – 84
APPROVED Rev. 2
9.2-5 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
Page Maximum cruising speed (AEO, bypass closed, ISA +20_C) . . . . . . . 9.2-5 – 85
Fig. 56
Maximum cruising speed (AEO, bypass closed, ISA +35_C) . . . . . . . 9.2-5 – 86
Fig. 57
Maximum cruising speed (AEO, bypass open, ISA) . . . . . . . . . . . . . . 9.2-5 – 87
Fig. 58
Maximum cruising speed (AEO, bypass open, ISA –20_C) . . . . . . . . 9.2-5 – 88
Fig. 59
Maximum cruising speed (AEO, bypass open, ISA +20_C) . . . . . . . . 9.2-5 – 89
Fig. 60
Maximum cruising speed (AEO, bypass open, ISA +35_C) . . . . . . . . 9.2-5 – 90
Fig. 61
IBF, typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 93
Fig. 62
IBF switches, typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 94
Fig. 63
IBF indication on VMD and FND – typical display . . . . . . . . . . . . . . . . 9.2-5 – 95
Fig. 64
Example of a flight report page with clogging level between 65% and 80% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-5 – 97
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Fig. 55
9.2-5 – 8
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
1
GENERAL The information contained herein supplements the information in the basic Flight Manual. For limitations, procedures, and performance data not contained in this Supplement, refer to the basic Flight Manual.
1.1
DEFINITION OF TERMS CLEAN BYPASS CLOSED: – Both bypass doors closed and both clogging indications below 40%
ED
CLOG TREND BYPASS CLOSED:
N TR
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– One or both bypass doors closed and one or both clogging indicators equal or above 40% (white advisory IBF CLOG TREND indicated on FND ML) BYPASS OPEN:
C
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– Both bypass doors open
LIMITATIONS
2.1
OPERATIONAL LIMITATIONS
2.1.1
OAT
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Maximum air temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ISA + 35_C (max. + 50_C) Minimum air temperature (one or both bypass door(s) closed) . . . . . . . . . . . . . . . . . – 25_C
C
Maximum pressure altitude
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Minimum air temperature (both bypass doors open, cold weather kit installed) . . – 45_C
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Maximum operating altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 000 ft PA
APPROVED Rev. 1
9.2-5 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
3
EMERGENCY AND MALFUNCTION PROCEDURES
3.1
CAUTION INDICATIONS
IBF1
BYPASS CLOSED and/or
ED
IBF2
LL
BYPASS CLOSED
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and audio tone
O
Conditions/Indications
T
C
– Respective IBF bypass door closed via the IBF sw.
PY
N
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– The IBF will not open automatically in the case of excessive clogging or in the case of a single engine failure.
O
Procedure
– NORM or OPEN
LY
–
C
1. IBF1 and/or 2 sw
IF THE IBF REMAINS CLOSED BEYOND 100% CLOGGING AND ADDITIONAL CLOGGING IS ACCUMULATED, AN ENGINE FAILURE AND/OR ENGINE DAMAGE MAY OCCUR.
CAUTION
IF THE IBF REMAINS CLOSED BEYOND 100% CLOGGING OR IN THE CASE OF A SINGLE ENGINE FAILURE, THE AIRCRAFT PERFORMANCE MAY BE SIGNIFICANTLY DEGRADED.
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WARNING
9.2-5 – 10
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
IBF1
BYPASS FAIL and/or
BYPASS FAIL
IBF2
and audio tone
ED
Conditions/Indications
LL
– Respective bypass door is not in fully opened or fully closed position.
N TR
FLYING IN SANDY CONDITIONS WITH OPEN BYPASS DOOR(S) WILL CAUSE EXCESSIVE ENGINE WEAR.
C
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CAUTION
O
Procedure
– OPEN
PY
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1. IBF 1 and/or 2 sw’s
C –
2. Sandy conditions
– Wait 10 sec
O
If caution indication(s) remain(s):
– Wait 10 sec, then NORM
– Avoid, if operation permits
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3. LAND AS SOON AS PRACTICABLE
APPROVED Rev. 1
9.2-5 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
IBF1
CLOGGED and/or
CLOGGED
IBF2
and audio tone
ED
Conditions/Indications
LL
– The caution indication(s) comes on whenever a specific low pressure value within the housing is reached (clogging of the IBF).
N TR
O
– IBF CLOG TREND white advisory is on.
O
– The IBF clogging indication on the VMS page shows 100% clogging.
C
Procedure
– Avoid, if operation permits
N
O
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1. Sandy conditions
– OPEN
C
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3. IBF1/2 CLOGGED caution indication(s)
PY
2. IBF 1 and/or 2 sw’s
–
4. IBF1/2 BYPASS OPEN information message
– Check on
LY
FLYING IN SANDY CONDITIONS WITH OPEN BYPASS DOOR(S) WILL CAUSE EXCESSIVE ENGINE WEAR.
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CAUTION
– Check off
9.2-5 – 12
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
IBF1
INCORRECT CONFIG IBF2
Conditions/Indications – Caution indication appears only during power-up test.
Procedure – Select
N TR
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1. VMS/CONF
LL
ED
– IBF is not selected as configuration for ENGINE INLET FILTER on VMS/CONF page. IBF parameters will not be indicated during flight.
– Correctly configure installed IBF
C
O
– Press VAL – OFF, wait 30 seconds, then ON
O
PY
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2. BAT MSTR sw
PRESS SENSOR
LY
–
C
IBF1
and/or
IBF2
and audio tone
C
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O N
O N
PRESS SENSOR
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Conditions/Indications
IN
ST
– Respective IBF pressure sensor failed
R
Procedure – Avoid, if operation permits
2. Affected IBF sw
– OPEN
FO
1. Sandy conditions
CAUTION
FLYING IN SANDY CONDITIONS WITH OPEN BYPASS DOOR(S) WILL CAUSE EXCESSIVE ENGINE WEAR.
3. Continue flight
APPROVED Rev. 1
9.2-5 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
3.2
WHITE ADVISORIES
IBF CLOG TREND
ED
Conditions/Indications
LL
– The white advisory (one for both IBFs) comes on whenever a specific low pressure value within the housing is reached.
N TR
O
– The IBF CLOG TREND advisory will appear when 40% clogging on the VMS have been indicated.
C
O
Procedure
C
SINGLE ENGINE FAILURE IN FLIGHT
–
3.3
O
PY
N
O
T
1. Performance charts for a degraded filter (”CLOG TREND BYPASS CLOSED”) shall be used.
O N
LY
Conditions/Indications
O N
Bypass doors will open automatically.
C
TI
Procedure
ST
R
U
1. Perform standard single engine failure emergency procedure (see basic Flight Manual Sect. 3) – OPEN
FO
R
IN
2. IBF1 and 2 sw’s
9.2-5 – 14
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
4
NORMAL PROCEDURES NOTE D Flying in sandy conditions with open bypass door(s) will cause excessive engine wear. D The following configurations are considered normal operations: – both IBF sw’s NORM – both IBF sw’s OPEN
PREFLIGHT CHECK
4.1.1
Exterior check
C O
T
It is recommended to keep the gearbox deck clean at all times, because any dust/sand accumulated on the gearbox deck could be ingested by the engines when the IBF bypass doors are opened.
O
PY
N
NOTE
O
4.1
N TR
O
LL
ED
D Should a mixed configuration (one IBF in NORM and the other in OPEN position) be used, the performance charts for IBF CLEAN BYPASS CLOSED or IBF CLOG TREND BYPASS CLOSED shall be used (according to the respective clogging indication) (refer to Sect. 5 of this supplement).
–
C
Fuselage right side:
L IBF filter element
O N
Bypass door and screen
O N
LY
Drain port fwd
– Check condition, unobstructed – Check condition, unobstructed – Check condition
C
TI
Drain port aft
– Check condition
R
U
Fuselage left side:
– Check condition
Bypass door and screen
– Check condition, unobstructed
R
IN
ST
Drain port aft
FO
L IBF filter element Drain port fwd
– Check condition, unobstructed – Check condition
L To be checked before each flight
APPROVED Rev. 3
9.2-5 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
4.1.2
Interior check (to be performed before engine start, before first flight of the day) – OPEN
IBF1 and 2 sw’s
– Wait 10 sec, check IBF1 BYPASS OPEN IBF1 and 2 sw’s
IBF2
– NORM – Wait 10 sec, check no indication
LL
ENGINE SHUTDOWN
O
4.2
During a normal engine start, the bypass doors will remain closed if both IBF are set to NORM.
ED
NOTE
N TR
Prior to engine shutdown:
C
T
During a normal engine shutdown, the bypass doors will remain closed if both IBF are set to NORM.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
NOTE
– Check NORM
O
IBF1 and 2 sw’s
9.2-5 – 16
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
5
PERFORMANCE DATA
5.1
PERFORMANCE INDICATION ON THE VMS PAGE Before Helionix Maintenance Release 1
All
THE CAT A VTOL WEIGHT DOES NOT CONSIDER WEIGHT REDUCTIONS RESULTING FROM OPTIONAL EQUIPMENT. ALWAYS COMPARE THE INDICATED CAT A VTOL WEIGHT WITH THE CAT A CLEAR HELIPORT WEIGHT OBTAINED FROM THE PERFORMANCE CHARTS (PROCEED ACCORDING TO SECTION 9.1–1.C)
O
T
C
O
N TR
CAUTION
O
EFFECTIVITY
ED
THE PERFORMANCE DATA ON THE VMS PAGE SHOULD NOT BE USED FOR THE FOLLOWING CASES: – ABOVE 13000 FT DENSITY ALTITUDE, AND – WHEN TU206 IS INSTALLED: FOR OEI 2MIN HOGE DATA. FOR THOSE CASES REFER TO THE FLIGHT MANUAL.
CAUTION
LL
EFFECTIVITY
5.2
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
The data field of the VMS page (Fig. 21) shows the maximum gross weight for AEO HIGE, AEO HOGE, Cat A VTOL (see section 9.1–1.C), OEI 30s HOGE, and OEI 2min HOGE. This maximum gross weight is calculated based on the current altitude, OAT, heating condition (on or off). All maximum gross weights are based on conditions with zero wind. Any hover performance penalty entered on the weight and performance page (see Para 7.13.5.1) will be applied to the weights shown the VMS page.
WEIGHT & PERFORMANCE area on the VMS page
POWER CHECK NOTE
5.2.1
Fig. 21
Power checks shall not be performed with degraded filter and bypass door closed. If the white advisory IBF CLOG TREND is indicated on the FND ML, the bypass door must be opened prior to power checks.
Automatic ground power check To obtain correct check results, the following preconditions must be established: – Adequate distance from buildings, trees, etc. to reduce possibility of wind vortices. – Helicopter heading into wind.
APPROVED Rev. 2
9.2-5 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
– Bleed air heating OFF. The automatic ground power check procedure (Fig. 22) shall be carried out: – On the ground, and – with the IBF switch in OPEN or NORM position, and – under single engine operating condition (second engine at IDLE).
ED
CAUTION D ENGINE/TRANSMISSION CONTINUOUS POWER LIMITATIONS IN SECTION 2 ARE NOT TO BE EXCEEDED.
C
O
It is recommended to switch off the AFCS during the power check. Mast moment limits could be infringed as the AFCS tries to maintain the helicopter attitude when increasing the collective and the helicopter gets light on skids.
N
O
T
NOTE
N TR
O
LL
D DURING THE POWER CHECK, THE PILOT SHALL REMAIN VIGILANT AS THE AIRCRAFT MAY BECOME LIGHT ON SKIDS DURING THE CHECK. FOR THIS REASON, POWER CHECKS WITH A VERY LIGHT AIRCRAFT SHALL BE AVOIDED.
C
O
PY
To perform the power check, the standard start-up procedure (refer to section 4) shall be used. Both engines are in IDLE at the start of the procedure. The power check should be performed on each engine, in sequence, using the same procedure.
LY
–
Proceed as follows:
O N
1. Master List 2. VMS page
– Check no FADEC related alerts – Select – FLIGHT
4. Affected engine GEN switch
– OFF
C
TI
O N
3. Affected ENG MAIN switch
R
U
5. Affected engine IBF switch
– Slowly increase to 70% torque
IN
While increasing the collective, the power split audio tone will sound above 2 FLI.
FO
R
NOTE
ST
6. Collective lever
– OPEN or NORM, as required
7. Clock
– Start – Maintain 70% torque steady for 2 minutes
8. VMS page / EPC area
– Press RUN key – COMPUTING DATA appears – EPC appears in the FLI – Do not move collective until progress bar is filled – The power check result appears
9. Collective lever
9.2-5 – 18
– Slowly decrease to flat pitch APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
10. Affected ENG MAIN switch
– IDLE
11. Affected engine GEN switch
– RESET, then NORM
12. BARO setting
– Set as required
Repeat for other engine, if desired. Interpreting the results of the automatic ground power check: 1) RESULTS page is shown
LL
ED
The results shown on the VMS page /EPC area are shown as in the example of Fig. 22. The mean parameter values recorded during the check are shown on the left. The power check results (margins) are shown on the right. The margins are given in torque at ISO-TOT and in torque at ISO-N1. If both margins (TOT and N1) are zero or positive (green), the engine power is assured and the performances in the flight manual are achievable. A performance surplus cannot be calculated from the margins.
–
If one or both torque margins are negative (amber), the test is failed and maintenance is required.
O
T
C
O
N TR
O
–
387 ON–GROUND POWER CHECK RESULTS ENGINE2 MEAN VALUES: MARGINS: N1 : 90.9 % TRQ ISO–TOT : 8.3 % N2 : 101.4 % TRQ ISO–N1 : 5.0 % TRQ : 69.6 % TOT : 716 P0 : 967.5 hPa T1 : 21.2
E X I T
LY
O N
O N
PREV
STATUS
WEIGHT
TI
BKD2_FLH_0073_R
–
C
O
PY
N
FLIGHT
Automatic ground power check RESULTS page for engine 2 – example
NOTE
When T1 is shown in _F, temperatures > 99.9_F will not be indicated.
ST
R
U
C
Fig. 22
IN
The results from the last 8 power checks can be viewed by pressing EXIT and then HIST.
FO
R
2) NO EPC RESULTS AVAILABLE –
5.2.2
Repeat the power check (press RUN), maintaining the collective steady. If the power check fails again, perform a manual ground power check (see Para. 5.2.3).
Automatic in-flight power check To obtain correct check results, the following preconditions must be established: – Level flight in steady conditions. A power check in strong turbulence shall be avoided. – Bleed air heating OFF. – Generator loads reduced (no high power consumers switched on). – The bleed valves should have the same position (both closed or both open). If the bleed valves are mismatched, change altitude to match the bleed valves.
APPROVED Rev. 1
9.2-5 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
The automatic in-flight power check procedure (Fig. 23) shall be carried out: – In level flight > Vy, and – with both IBF switches in OPEN or NORM position, and – under AEO engine operating conditions. CAUTION
ENGINE/TRANSMISSION CONTINUOUS SECTION 2 ARE NOT TO BE EXCEEDED.
POWER
LIMITATIONS
IN
N TR
O
LL
ED
To perform the power check, the aircraft shall be in level forward flight. As the procedure takes two minutes to complete, a flight segment with no heading /altitude changes for two minutes shall be selected. The power check is performed on both engines simultaneously. During the power check, both engines are fully operative. Proceed as follows:
– Establish (> 500 ft ground)
2. Steady level flight
– Establish (> Vy)
3. Master List
– Check no FADEC related alerts
N
O
T
C
O
1. Safe altitude
– Select, press EPC
PY
4. VMS page
O
5. Both IBF switches
C
TI
O N
O N
LY
–
C
6. Collective lever
FO
R
8. Clock
IN
ST
R
U
7. VMS page / EPC area
9. VMS page / EPC area
– OPEN or NORM, as required
– Set power to 2x70% torque – If AEO MCP is reached at less than 70% torque, set collective at MCP – AFCS ALT mode can be used to maintain a steady altitude, if desired – Check all conditions are correct and correctly established (no amber labels) – Start – Maintain 2 minutes
70%
torque
for
– Press RUN key – COMPUTING DATA appears – EPC appears in the FLI – Do not move collective until progress bar is filled – The power check result appears
NOTE
9.2-5 – 20
If the autopilot was in 4-axis mode before the power check, the AFCS will automatically revert to 3-axis mode when the power check is started (RUN is pressed). APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
Interpreting the results of the automatic in-flight power check: 1) RESULTS page is shown The results shown on the VMS page /EPC area are shown as in the example of Fig 23. The mean parameter values recorded during the check are shown on the left. The power check results (margins) are shown on the right. The margins are given in torque at ISO-TOT and in torque at ISO-N1. If both margins (TOT and N1) are zero or positive (green), the engine power is assured and the performances in the flight manual are achievable. A performance surplus cannot be calculated from the margins.
–
If one or both torque margins are negative (amber), the test is failed and maintenance is required.
O
LL
ED
–
N TR
To access the results of engine 1, press NXT.
390 IN–FLIGHT POWER CHECK RESULTS ENGINE1 MEAN VALUES: MARGINS: N1 : 90.5 % TRQ ISO–TOT : 6.8 % N2 : 98.9 % TRQ ISO–N1 : 7.7 % TRQ : 69.6 % TOT : 731 _C P0 : 852.9 hPa T1 : 11.3 _C
E X I T
O
–
C
O
PY
N
N X T
PREV
LY
BKD2_FLH_0074_R
T
C
O
FLIGHT
STATUS
WEIGHT
Automatic in-flight power check RESULTS page for engine 1 – example
NOTE
When T1 is shown in _F, temperatures > 99.9_F will not be indicated.
O N
O N
Fig. 23
TI
To access the results of engine 2, press NXT.
U
C
The results from the last 8 power checks can be viewed by pressing EXIT and then HIST. Repeat the power check (press RUN), maintaining the collective steady. If the power check fails again, perform an automatic ground power check (see Para. 5.2.1) or, if not feasible, perform a manual ground power check (see Para. 5.2.3).
5.2.3
FO
R
IN
–
ST
R
2) NO EPC RESULTS AVAILABLE
Manual ground power check The manual ground power check can be performed with the IBF switched OPEN, CLOSE or NORM. The bypass door position should be recorded. The manual ground power check is to be used only in case an automatic power check is not possible. To obtain correct check results, the following preconditions must be established: – Adequate distance from buildings, trees, etc. to reduce possibility of wind vortices. – Helicopter heading into wind. – Bleed air heating OFF.
APPROVED Rev. 1
9.2-5 – 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
The manual ground power check procedure shall be carried out: – On the ground, and – Under single engine operating condition (second engine at IDLE) CAUTION D ENGINE/TRANSMISSION CONTINUOUS POWER LIMITATIONS IN SECTION 2 ARE NOT TO BE EXCEEDED.
LL
It is recommended to switch off the AFCS during the power check. Mast moment limits could be infringed as the AFCS tries to maintain the helicopter attitude when increasing the collective and the helicopter gets light on skids.
N TR
O
NOTE
ED
D DURING THE POWER CHECK, THE PILOT SHALL REMAIN VIGILANT AS THE AIRCRAFT MAY BECOME LIGHT ON SKIDS DURING THE CHECK. FOR THIS REASON, POWER CHECKS WITH A VERY LIGHT AIRCRAFT SHALL BE AVOIDED.
O
T
C
O
To perform the power check, the standard start-up procedure (refer to section 4, basic FLM) shall be used. Both engines are in IDLE at the start of the procedure. The power check should be performed on each engine, in sequence, using the same procedure.
LY
–
C
O
PY
– – – – – – – –
Full down Select STD Record Check no FADEC related alerts Select FLIGHT OFF Slowly increase to 70% torque
C
While increasing the collective, the power split audio tone will sound above 2 FLI.
IN
FO
R
9. Clock
ST
R
NOTE
TI
O N
O N
Collective lever BARO setting Pressure altitude Master List VMS page Affected ENG MAIN switch Affected engine GEN switch Collective lever
U
1. 2. 3. 4. 5. 6. 7. 8.
N
Proceed as follows:
– Start – Maintain 70% torque steady for 2 minutes
After 2 minutes: – Maintain 70% torque steady – Record OAT – Record N1 – Record TOT – Record bleed valve condition (closed = /// symbol present) – Record IBF bypass door position 10. Collective lever 11. Affected ENG MAIN switch
9.2-5 – 22
– Slowly decrease to flat pitch – IDLE APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
12. Affected engine GEN switch 13. BARO setting 14. IBF switch Repeat for other engine, if desired.
– RESET, then NORM – Set as required – Set as required
To determine the result of the power check, proceed as follows: Select the TOT power check chart (Fig. 24, 25, 30, or 31) based on the engine (1 or 2) and the bypass door position (open or closed). Using the chart, read the maximum TOT corresponding to the recorded ambient conditions If the TOT recorded during the power check is equal or less than the TOT obtained from the chart, the engine power is assured.
–
If the TOT recorded during the power check is higher than the TOT obtained from the chart, the engine power check has failed and maintenance is required.
N TR
O
LL
ED
–
C
O
Select the N1 power check chart (Fig. 26–29 or 32–35) based on the engine (1 or 2), the bypass door position (open or closed), and the bleed valve position (open or closed). Using the chart, read the maximum N1 corresponding to the recorded ambient conditions. If the N1 recorded during the power check is equal or less than the N1 obtained from the chart, the engine power is assured.
–
If the N1 recorded during the power check is higer than the N1 obtained from the chart, the engine power check has failed and maintenance is required.
O
PY
N
O
T
–
Power margins obtained from the automatic power check and the manual ground power check are given in different metrics. Therefore, the results cannot be compared to each other.
O N
LY
–
C
NOTE
(see Fig. 24)
Determine:
TOT margin
Known:
Pressure altitude
1600 ft
OAT
4_C
Indicated TOT
670_C
FO
R
IN
ST
R
U
C
TI
O N
EXAMPLE:
Solution:
TOT margin from average trend line: 40_C (see power trend monitoring) TOT margin = 38_C
Enter chart at known OAT (4_C) Move vertically upwards to known pressure altitude (1600 ft) Move horizontally left and read chart limit TOT = 708_C The TOT margin = chart limit TOT (708_C) – indicated TOT (670_C) = 38_C In the example above, the TOT margin is 38_C. Since the TOT margin from the average power trend line is 40_C, TOT margin drop down (2_C) is permissible. The conditions for an acceptable power check are satisfied. A continuous power trend monitoring procedure is given in section 5 of the basic FLM. APPROVED Rev. 2
9.2-5 – 23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (TOT) ENG1 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF CLEAN BYPASS CLOSED
910 890
ED
870
O
LL
850
N TR
830
C
O
810
N
O
T
790
O
PY
770
C – O N
LY
730 710
O N
TOT – _C
750
C
TI
690
ST
R
U
670
IN
650
FO
R
630
ARR2E_GPC_LH_T4_IBF_BPC
610 590 570 550
–40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 24
9.2-5 – 24
Manual ground power check (TOT) for engine No.1 and 70% torque, clean bypass closed APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (TOT) ENG2 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF CLEAN BYPASS CLOSED
910 890
ED
870
LL
850
N TR
O
830
C
O
810
N
O
T
790
PY
770
–
C
O
750
LY O N
TOT – _C
730
O N
710
U
ST
R
670
C
TI
690
IN
650
FO
R
630
ARR2E_GPC_RH_T4_IBF_BPC
610 590 570 550 –40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 25
Manual ground power check (TOT) for engine No.2 and 70% torque, clean bypass closed
APPROVED Rev. 1
9.2-5 – 25
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (N1) ENG1 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF CLEAN BYPASS CLOSED
BLEED VALVE OPEN
100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
C
O
95.0
N
O
T
94.0
O
PY
93.0
C – LY
91.0
O N
N1 – %
92.0
O N
90.0
C
TI
89.0
IN
87.0
ST
R
U
88.0
ARR2E_GPC_LH_N1_BVO_IBF_BPC
FO
R
86.0 85.0 84.0 83.0 82.0
–40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 26
9.2-5 – 26
Manual ground power check (N1) for engine No.1 and 70% torque, bleed valve open, clean bypass closed APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (N1) ENG2 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF CLEAN BYPASS CLOSED
BLEED VALVE OPEN
100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
C
O
95.0
N
O
T
94.0
O
PY
93.0
C –
N1 – %
92.0
O N
LY
91.0
O N
90.0
C U
ST
R
88.0
TI
89.0
IN
87.0
ARR2E_GPC_RH_N1_BVO_IBF_BPC
FO
R
86.0 85.0 84.0 83.0 82.0 –40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 27
APPROVED Rev. 1
Manual ground power check (N1) for engine No.2 and 70% torque, bleed valve open, clean bypass closed
9.2-5 – 27
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (N1) ENG1 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF CLEAN BYPASS CLOSED
BLEED VALVE CLOSED
100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
C
O
95.0
N
O
T
94.0
O
PY
93.0
C – LY
91.0
O N
N1 – %
92.0
O N
90.0
C
TI
89.0
IN
87.0
ST
R
U
88.0
ARR2E_GPC_LH_N1_BVC_IBF_BPC
FO
R
86.0 85.0 84.0 83.0 82.0
–40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 28
9.2-5 – 28
Manual ground power check (N1) for engine No.1 and 70% torque, bleed valve closed, clean bypass closed APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (N1) ENG2 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF CLEAN BYPASS CLOSED
BLEED VALVE CLOSED
100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
C
O
95.0
N
O
T
94.0
O
PY
93.0
N1 – %
–
C
92.0
O N
LY
91.0
O N
90.0
C U
ST
R
88.0
TI
89.0
IN
87.0
ARR2E_GPC_RH_N1_BVC_IBF_BPC
FO
R
86.0 85.0 84.0 83.0 82.0 –40
Fig. 29
APPROVED Rev. 1
–30
–20
–10
0
10
OAT – °C
20
30
40
50
Manual ground power check (N1) for engine No.2 and 70% torque, bleed valve closed, clean bypass closed
9.2-5 – 29
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (TOT) ENG1 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF BYPASS OPEN
910 890
ED
870
O
LL
850
N TR
830
C
O
810
N
O
T
790
O
PY
770
C – O N
LY
730 710
O N
TOT – _C
750
C
TI
690
IN
650
ST
R
U
670
FO
R
630
ARR2E_GPC_LH_T4_IBF_BPO
610 590 570 550
–40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 30
9.2-5 – 30
Manual ground power check (TOT) for engine No.1 and 70% torque, bypass open APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (TOT) ENG2 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF BYPASS OPEN
910 890
ED
870
O
LL
850
N TR
830
C
O
810
N
O
T
790
O
PY
770
C – LY
730
O N
TOT – _C
750
O N
710
C U R
ST
670
TI
690
R
IN
650
FO
630 ARR2E_GPC_RH_T4_IBF_BPO
610 590 570 550 –40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 31 APPROVED Rev. 1
Manual ground power check (TOT) for engine No.2 and 70% torque, bypass open
9.2-5 – 31
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (N1) ENG1 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF BYPASS OPEN
BLEED VALVE OPEN
100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
C
O
95.0
N
O
T
94.0
O
PY
93.0
C – LY
91.0
O N
N1 – %
92.0
O N
90.0
C
TI
89.0
R ST IN
R
87.0
U
88.0
ARR2E_GPC_LH_N1_BVO_IBF_BPO
FO
86.0 85.0 84.0 83.0 82.0
–40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 32
9.2-5 – 32
Manual ground power check (N1) for engine No.1 and 70% torque, bleed valve open, bypass open APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (N1) ENG2 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF BYPASS OPEN
BLEED VALVE OPEN
100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
T
C
O
95.0
N
O
94.0
O
PY
93.0
N1 – %
–
C
92.0
O N
LY
91.0
O N
90.0
R
ST
88.0
U
C
TI
89.0
R
IN
87.0
ARR2E_GPC_RH_N1_BVO_IBF_BPO
FO
86.0 85.0 84.0 83.0 82.0 –40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 33
APPROVED Rev. 1
Manual ground power check (N1) for engine No.2 and 70% torque, bleed valve open, bypass open
9.2-5 – 33
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (N1) ENG1 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF BYPASS OPEN
BLEED VALVE CLOSED
100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
C
O
95.0
N
O
T
94.0
O
PY
93.0
C – LY
91.0
O N
N1 – %
92.0
O N
90.0
C
TI
89.0
IN
R
87.0
ST
R
U
88.0
ARR2E_GPC_LH_N1_BVC_IBF_BPO
FO
86.0 85.0 84.0 83.0 82.0
–40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 34
9.2-5 – 34
Manual ground power check (N1) for engine No.1 and 70% torque, bleed valve closed, bypass open APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MANUAL GROUND POWER CHECK (N1) ENG2 1 X TURBOMECA ARRIEL 2E 70% TORQUE
BLEED AIR HEATING OFF GENERATOR OFF BYPASS OPEN
BLEED VALVE CLOSED
100.0 99.0
ED
98.0
O
LL
97.0
N TR
96.0
T
C
O
95.0
N
O
94.0
O
PY
93.0
N1 – %
–
C
92.0
O N
LY
91.0
O N
90.0
C U R
ST
88.0
TI
89.0
R
IN
87.0
ARR2E_GPC_RH_N1_BVC_IBF_BPO
FO
86.0 85.0 84.0 83.0 82.0 –40
–30
–20
–10
0
10
20
30
40
50
OAT – °C
Fig. 35
APPROVED Rev. 1
Manual ground power check (N1) for engine No.2 and 70% torque, bleed valve closed, bypass open
9.2-5 – 35
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
5.2.4
Power trend monitoring Power trend monitoring based on the automatic power checks can be performed either always IBF CLOSE or always IBF OPEN. Power trend monitoring based on the manual power checks can be performed either always IBF NORM or always IBF CLOSE or always IBF OPEN.
5.3
HEIGHT-VELOCITY ENVELOPE (H–V DIAGRAM)
ED
The helicopter configuration shall comply with the mass-altitude-temperature limits shown in section 5 of this supplement.
N TR
O
LL
The height-velocity envelope shown in the height-velocity diagram (Fig. 36) is the combination of indicated airspeed and height above ground as a function of gross mass, pressure altitude and outside air temperature.
C
O
The diagram shows the area which is critical for helicopter operation in the event of a single engine failure during takeoff, landing or other operations near the ground.
O
PY
N
O
T
The curves are applicable for landing sites with smooth firm surfaces and define the conditions in which a safe landing can be made after an engine suddenly becomes inoperative.
O N
LY
–
C
NOTE D The height–velocity diagram is applicable only if the aircraft weight is achievable in hover out of ground effect for the given altitude and temperature (see section 5.4 of this supplement).
U
C
TI
O N
D The lowest reference point P (”high hover” point) achievable in the chart is 100 ft (shaded area in Fig. 36). Safe landing from any point within the shaded area is guaranteed only if the calculation shows no H–V area for the given weight–altitude–temperature combination.
IN
ST
R
D The data presented in the height-velocity diagram (Fig. 36) for density altitudes above 13000 ft have been established by theoretical analysis only.
FO
R
D To determine the airspeed to be used in the height-velocity diagram, the indicated airspeed shall be used above 25 KIAS. Below 25 KIAS, a combination of forward groundspeed and factored headwind (= 50% of the reported wind) may be used.
9.2-5 – 36
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
EXAMPLE 1 (see Fig. 36): The critical height-velocity area which should be avoided, can be defined by first determining point P, a point on the requested boundary curve. Determine:
Critical height-velocity curve
Known:
OAT
14_C
Pressure altitude
6000 ft
Gross mass
3600 kg
ED
Solution:
LL
Enter chart at known OAT (14_C)
N TR
O
Move vertically upwards to known pressure altitude (6000 ft) Move horizontally right to known gross mass (3600 kg)
C
O
Move vertically downwards to intersect the reference line
O
T
From intersection with reference line move horizontally left and read height above ground for point P = 197 ft
PY
N
Draw the boundary curve through point P by interpolating between the existing curves on the chart
C
O
EXAMPLE 2 (see Fig. 36):
Critical height-velocity curve
Known:
OAT
LY
–
Determine:
O N
6000 ft
Gross mass
3150 kg
U
C
TI
O N
Pressure altitude
R
Solution:
14_C
FO
R
IN
ST
Enter chart at known OAT (14_C)
Move vertically upwards to known pressure altitude (6000 ft) Move horizontally right to known gross mass (3150 kg) Move vertically downwards to intersect the reference line From intersection with reference line move horizontally left and read height above ground for point P = 100 ft
Use the boundary curve through point P = 100 ft
APPROVED Rev. 1
9.2-5 – 37
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
EXAMPLE 3 (see Fig. 36): Determine:
Critical height-velocity curve
Known:
OAT
14_C
Pressure altitude
6000 ft
Gross mass
3100 kg
Solution: Enter chart at known OAT (14_C)
LL
O
Move horizontally right to known gross mass (3100 kg)
ED
Move vertically upwards to known pressure altitude (6000 ft)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
No interception possible, no H–V area exists for the given gross mass
9.2-5 – 38
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MAX. DENSITY ALTITUDE 20000 ft
O N TR O C
10 20 30 40 50
O
T
–50 –40 –30 –20 –10 0
LL
NO H–V AREA
ED
16000 ft
N
320
PY
300
C
O
280
–
260
LY
240
O N O N
200 P
TI
180
U
C
160
R
140 120
ST R
FO
80
IN
100
BK117D2038_1_IBF_3_r2
SKID HEIGHT – ft AGL
220
60 40 20 0
0
10
20
30
40
AIRSPEED – kt
Fig. 36 APPROVED Rev. 1
Height-velocity diagram
9.2-5 – 39
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
5.4
HOVER CEILING – AEO PERFORMANCE The hover ceiling charts for hover in ground effect (HIGE) (Fig.37 to 40) are provided for AEO conditions, with takeoff power (TOP) and maximum continuous power (MCP) and various combinations of pressure altitude, outside air temperature and gross mass. At the maximum aircraft weight shown in the HIGE performance charts, controllability for hover in ground effect was demonstrated with the following wind speeds: – Up to 16000 ft density altitude . . . . . . . . . . . . . . . . . . . . . . up to 30 kts from all directions – Above 16000 ft density altitude . . . . . . . . . . . up to 17 kts from the right, 30 kts from all other directions
LL
ED
Controllability during standard type takeoff and landing has been demonstrated for flight conditions with crosswind components up to 17 kts.
O
N TR
O
The hover ceiling charts for hover out of ground effect (HOGE) (Fig.41 to 46) are provided for AEO conditions, with takeoff power (TOP) and maximum continuous power (MCP), and various combinations of pressure altitude, outside air temperature and gross mass.
O
T
C
At the maximum aircraft weight shown in the HOGE performance charts, controllability for hover out of ground effect was demonstrated with the following wind speeds:
N
– Up to 16000 ft density altitude . . . . . . . . . . . . . . . . . . . . . . up to 30 kts from all directions
–
The term “heating” is used for bleed air heating and electrical heater.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
NOTE
C
O
PY
– Above 16000 ft density altitude . . . . . . . . . . . up to 17 kts from the right, 30 kts from all other directions
9.2-5 – 40
APPROVED Rev. 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
HOVER CEILING IN GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
CLEAN BYPASS CLOSED HEATING OFF 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
LL
ED
2400
C
O
MAX. DENSITY ALTITUDE 20000 FT
2600
N TR
O
2500
N
MAX. OAT
PY O
O N
3000
C
GROSS MASS – kg
2900
–
2800
LY
MIN. OAT BYPASS CLOSED
O
T
2700
TI
O N
3100
IN
ST
3300
R
U
C
3200
FO
R
3400
3500
BK117D2001_1_IBF_1_r2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 37 APPROVED Rev. 1
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (AEO, TOP, clean bypass closed, heating off)
9.2-5 – 41
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
HOVER CEILING IN GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
CLOG TREND BYPASS CLOSED HEATING OFF 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
LL
ED
2400
O
2500
N TR
MAX. DENSITY ALTITUDE 20000 FT
C
O
2600
MAX. OAT
C – LY O N
O N
3000
3100
C
TI
GROSS MASS – kg
2900
O
MIN. OAT BYPASS CLOSED
2800
PY
N
O
T
2700
ST
R
U
3200
FO
3400
R
IN
3300
3500
BK117D2001_1_IBF_2_r2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 38
9.2-5 – 42
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (AEO, TOP, clog trend bypass closed, heating off) APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
HOVER CEILING IN GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
BYPASS OPEN HEATING OFF 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
LL
ED
2400
O
2500
C
O
2600
N TR
MAX. DENSITY ALTITUDE 20000 FT
N
O
T
2700
MAX. OAT
O LY
–
C
MIN. OAT
O N
3000
O N
3100
TI
GROSS MASS – kg
2900
PY
2800
ST
R
U
C
3200
IN
3300
FO
R
3400
3600
BK117D2001_1_IBF_3_r2
3500
5000
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 39 APPROVED Rev. 1
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (AEO, TOP, bypass open, heating off)
9.2-5 – 43
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
HOVER CEILING IN GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
BYPASS CLOSED OR OPEN HEATING ON 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
ED
2300
2400
O N TR
2500
LL
MAX. DENSITY ALTITUDE 20000 FT
T
C
O
2600
O
MAX. OAT
C – LY
O N
3000
O N
MIN. OAT
2900 GROSS MASS – kg
MIN. OAT BYPASS CLOSED
2800
PY
N
O
2700
C
TI
3100
IN
R
3300
ST
R
U
3200
FO
3400
3600
BK117D2001_11_IBF_3_r2
3500
8000
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 40
9.2-5 – 44
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (AEO, TOP, bypass closed or open, heating on) APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
CLEAN BYPASS CLOSED HEATING OFF 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
O
LL
ED
MAX. DENSITY ALTITUDE 20000 FT
2400
N TR
2500
T
C
O
2600
PY O
MAX. OAT
C –
O N
3000
TI
3100
C
GROSS MASS – kg
2900
LY
2800
O N
MIN. OAT BYPASS CLOSED
N
O
2700
IN
R
3300
ST
R
U
3200
FO
3400
3500
BK117D2005_1_IBF_1_r2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 41 APPROVED Rev. 1
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, TOP, clean bypass closed, heating off)
9.2-5 – 45
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
CLOG TREND BYPASS CLOSED HEATING OFF 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
LL
ED
MAX. DENSITY ALTITUDE 20000 FT
2400
N TR
O
2500
C
O
2600
O
MAX. OAT
C – LY
O N
3000
3100
C
TI
GROSS MASS – kg
2900
O N
2800
PY
MIN. OAT BYPASS CLOSED
N
O
T
2700
ST
R
U
3200
FO
3400
R
IN
3300
3500
BK117D2005_1_IBF_2_r2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 42
9.2-5 – 46
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, TOP, clog trend bypass closed, heating off) APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
BYPASS OPEN HEATING OFF 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
LL
ED
MAX. DENSITY ALTITUDE 20000 FT
2400
N TR
O
2500
C
O
2600
N
O
T
2700
MAX. OAT
LY
–
MIN. OAT
2900
O N
O N
3000
3100
C
TI
GROSS MASS – kg
C
O
PY
2800
ST
R
U
3200
R
IN
3300
FO
3400
3500 3000 BK117D2005_1_IBF_3_r2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 43 APPROVED Rev. 1
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, TOP, bypass open, heating off)
9.2-5 – 47
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
BYPASS CLOSED OR OPEN HEATING ON 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300 MAX. DENSITY ALTITUDE 20000 FT
LL
ED
2400
N TR
O
2500
T
C
O
2600
MAX. OAT
O C – LY
O N
3000
TI
3100
C
GROSS MASS – kg
2900
O N
MIN. OAT
2800
PY
MIN. OAT BYPASS CLOSED
N
O
2700
ST
R
U
3200
FO
3400
R
IN
3300
BK117D2005_11_IBF_3_r2
3500
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 44
9.2-5 – 48
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, TOP, bypass closed or open, heating on) APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
MAXIMUM CONTINUOUS POWER
BYPASS CLOSED OR OPEN HEATING OFF 2200 16000
MAX. DENSITY ALTITUDE 20000 FT
2300
LL
ED
2400
N TR
O
2500
C
O
2600
N
O
T
2700
PY
MAX. OAT
O C –
O N
LY
15000
3000
O N
3100
TI
GROSS MASS – kg
2900
MIN. OAT BYPASS CLOSED
MIN. OAT
2800
ST
IN
3300
R
U
C
3200
FO
R
3400
3500
BK117D2006_1_IBF_2
For altitude/oat combinations not shown,
3600
the GROSS MASS LIMIT line is applicable 3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 45 APPROVED Rev. 1
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, MCP, bypass closed or open, heating off)
9.2-5 – 49
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
HOVER CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER
2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND BYPASS CLOSED OR OPEN HEATING ON
2200
MAX. DENSITY ALTITUDE 20000 FT
2300
ED
2400
LL
16000
N TR
O
2500
C
O
2600
N
O
T
2700
PY
MAX. OAT
O C – LY
C
TI
3100
O N
3000
O N
MIN. OAT
GROSS MASS – kg
2900
MIN. OAT BYPASS CLOSED
2800
ST
R
U
3200
FO
3400
R
IN
3300
3500
BK117D2006_11_IBF_2
For altitude/oat combinations not shown,
3600
the GROSS MASS LIMIT line is applicable 3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 46
9.2-5 – 50
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, MCP, bypass closed or open, heating on) APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
5.5
HOVER CEILING – OEI PERFORMANCE
5.5.1
Hover ceiling in ground effect - OEI Performance For specific operations OEI – HIGE capability may be required and shall be performed in accordance with national operational rules.
5.5.1.1 Bleed air consumers Bleed air heating and other bleed air consumption is not permitted during operation which requires OEI-hover.
O
Maximum gross mass to ensure OEI-HIGE capability:
LL
ED
5.5.1.2 Performance data
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
The maximum gross mass is limited by the OEI–hover chart (see Fig. 47, Fig. 48).
APPROVED Rev. 1
9.2-5 – 51
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
TU206 NOT installed
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
HOVER CEILING IN GROUND EFFECT 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN POWER
ZERO WIND OR HEADWIND HEATING OFF
ED
2000
O
LL
2100
N TR
2200
C
O
2300
N
O
T
2400
PY
2500
C
O
2600
MAX. OAT
– LY
2800
O N
MIN. OAT
TI
O N
2900
C
3000
U
GROSS MASS – kg
2700
ST IN
R
3200
R
3100
FO
3300 3400
BK117D2009_1_IBF_3_r1
3500 3600 3700 3800
Fig. 47
9.2-5 – 52
GROSS MASS LIMIT 3700 KG –50
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (OEI, 2 min power, without TU206, heating off) APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
TU206 installed or after Helionix Maintenance Release 1
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
HOVER CEILING IN GROUND EFFECT 1 X TURBOMECA ARRIEL 2E (WITH TU206) 2 MIN POWER
ZERO WIND OR HEADWIND HEATING OFF 2000
ED
2100
O
LL
2200
N TR
2300
C
O
2400
N
O
T
2500
PY
2600
MAX. OAT
O – LY
2800
C
MIN. OAT
GROSS MASS – kg
2700
O N
2900
O N
3000
ST
R
3200
U
C
TI
3100
3400 3500 BK117D2009_1_IBF_3_r2
FO
R
IN
3300
3600 3700 3800
Fig. 48 EFFECTIVITY APPROVED Rev. 2
GROSS MASS LIMIT 3700 KG –50
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (OEI, 2 min power, with TU206 or after Helionix Maintenance Release 1, heating off) All
9.2-5 – 53
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
5.5.2
Hover ceiling out of ground effect - OEI Performance For specific operations OEI–HOGE capability may be required and shall be performed in accordance with national operational rules.
5.5.2.1 Bleed air consumers Bleed air heating and other bleed air consumption is not permitted during operation which requires OEI-hover. 5.5.2.2 Performance data
ED
Maximum gross mass to ensure OEI-HOGE capability:
LL
The maximum gross mass is limited by the OEI-hover chart (see Fig. 49 to Fig. 51).
T
O
OEI-HOGE performance with vertical R/C reserve:
C
O
N TR
O
In order to achieve and remain at the maximum rated torque value a slight rotor speed droop is required at the OEI 30sec / 2min power limitations. The HOGE OEI 30sec chart has been established for nominal rotor speed minus 3% and the HOGE OEI 2min chart for nominal rotor speed minus 1%. Higher rotor speed droop will result in a slight rate of descent.
–
C
TI
150
O N
50 100
LY
O N
Vertical climb reserve [ft / min]
C
O
PY
N
Specific operations may require an additional vertical R/C reserve to the OEI–HOGE. The following gross mass values have to be subtracted from the derived gross mass of Fig. 49 to Fig. 51:
[kg] – 25 – 45 – 70 – 90
R
U
200
n Gross Mass
ST
Wind credit chart
FO
R
IN
The wind credit chart is valid for headwind components. Operations with tailwind components should be avoided. Wind accountability in Fig.49 to Fig.51 is UNFACTORED. NOTE
9.2-5 – 54
Unless otherwise authorized by operating regulations, the pilot is not authorized to credit more than the performance increase resulting from 50% of the actual headwind component.
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
EXAMPLE:
(see Figure 49)
Determine:
Maximum gross mass for OEI-HOGE (2 min power)
Known:
OAT
+15 °C
Pressure altitude
0 ft (SL)
Windspeed
16 kt
Bleed air consumers
OFF
For calculation: 50% headwind
ED LL O
Maximum gross mass = 3115 kg
N TR
Solution:
8 kt
O
Enter chart at known OAT (+15°C).
C
Move upwards to known pressure altitude (0 ft)
N
O
T
From point of intersection move horizontally right to the reference line of the wind credit chart.
PY
From this point follow the direction of the wind credit guide lines.
C
O
Enter chart at known windspeed (8 kt)
LY
–
Move vertically upwards to intersect tracing from above.
O N
From point of intersection move horizontally right and read max. gross mass = 3115 kg
FO
R
IN
ST
R
U
C
TI
O N
(Using the example on the assumption of no wind, the solution is 3065kg)
APPROVED Rev. 1
9.2-5 – 55
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
TU206 NOT installed
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
HOVER CEILING OUT OF GROUND EFFECT 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN. POWER
ZERO WIND OR HEADWIND HEATING OFF 2000
N TR
O
LL
ED
2100
2300
C
O
2400
O
T
2500
PY
N
2600
MAX. OAT
2800 2900
O N
3000
GROSS MASS – kg
2700
O C O N
LY
–
MIN. OAT
2200
C
TI
3100
ST
R
U
3200
IN
3300
FO
R
3400
GROSS MASS LIMIT 3700 KG –50
–40
–30
–20
–10
0
10
20
30
40
50
60 0
3600 3700
10
20
3800 30 [kt]
BK117D2008_1_IBF_3_r1
REFERENCE LINE
3500
0 10 20 30 40 50 60 [km/h] HEADWIND
Fig. 49
9.2-5 – 56
Hover ceiling out off ground effect (OEI, 2 min power, without TU206, heating off) APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
TU206 installed or after Helionix Maintenance Release 1
EFFECTIVITY
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
HOVER CEILING OUT OF GROUND EFFECT 1 X TURBOMECA ARRIEL 2E (WITH TU206) 2 MIN. POWER
ZERO WIND OR HEADWIND HEATING OFF 2000
O
LL
ED
2100 2200
N TR
2300
C
O
2400
O
T
2500
2800 2900
O N
3000
GROSS MASS – kg
MAX. OAT
2700
O N
LY
–
C
MIN. OAT
O
PY
N
2600
TI
3100
R
U
C
3200
ST
3300
R
IN
3400
GROSS MASS LIMIT 3700 KG –50
–40
–30
–20
–10
0
10
20
30
40
50
60 0
3600 3700
10
20
3800 30 [kt]
BK117D2008_1_IBF_3_r2
REFERENCE LINE
FO
3500
0 10 20 30 40 50 60 [km/h] HEADWIND
Fig. 50
Hover ceiling out off ground effect (OEI, 2 min power, with TU206 or after Helionix Maintenance Release 1, heating off)
EFFECTIVITY APPROVED Rev. 2
All
9.2-5 – 57
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
HOVER CEILING OUT OF GROUND EFFECT 1 X TURBOMECA ARRIEL 2E 30 SEC POWER
ZERO WIND OR HEADWIND HEATING OFF 2000 2100
ED
2200
O
LL
2300
N TR
2400
C
O
2500
O
T
2600
2900
O N
3000
GROSS MASS – kg
MAX. OAT
2800
LY
–
C
O
MIN. OAT
PY
N
2700
O N
3100
C
TI
3200
ST
R
U
3300
IN
3400
GROSS MASS LIMIT 3700 KG –50
–40
–30
–20
–10
0
10
20
30
40
50
60 0
3600 3700
10
20
3800 30 [kt]
BK117D2007 1 IBF 3 r2
FO
REFERENCE LINE
R
3500
0 10 20 30 40 50 60 [km/h] HEADWIND
Fig. 51
9.2-5 – 58
Hover ceiling out off ground effect (OEI, 30 sec power, heating off)
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
5.6
RATE OF CLIMB
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
The following rate of climb charts (Fig. 52 to Fig. 71) show the rate of climb for all engines operating condition at VY and for one-engine inoperative conditions at VY and VTOSS with various combinations of power settings, bleed air heating, pressure altitude, outside air temperature and gross mass.
APPROVED Rev. 1
9.2-5 – 59
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY CLEAN BYPASS CLOSED CLOG TREND BYPASS CLOSED BYPASS OPEN
20000 19000 18000
–45 to –40
LL
O N
O
T
C
O
N TR
–30 to 0
14000 13000 12000 11000
10 to 20
O
PY
10000 9000 8000
30 to 50
–
C
7000 6000 5000 4000
–45 to 20
O N
O N
3000 2000 1000
REFERENCE LINE
R
U
C
BK117D2M012_1_IBF_2
TI
0 2600 2500 2400
IN
ST
2300 2200 2100 2000
2
FO
0
R
GROSS MASS – kg
2000kg – 2600kg
LY
PRESSURE ALTITUDE –ft
17000 16000 15000
Fig. 52
ED
HEATING OFF
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
Rate of climb (AEO, MCP, 2000 kg to 2600 kg, clean bypass closed, clog trend bypass closed, bypass open, heating off)
9.2-5 – 60
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY CLEAN BYPASS CLOSED CLOG TREND BYPASS CLOSED BYPASS OPEN HEATING OFF
20000 19000 18000
LL O
N TR
–30 to 40
O
T
C
O
14000 13000 12000 11000
PY
N
10000 9000 8000
–
C
O
7000 6000 5000 4000
LY O N O N
–45 to 50 REFERENCE LINE
TI
0 3200 3100 3000
U
C
BK117D2M012_2_IBF_2
PRESSURE ALTITUDE –ft
–45 to –40
3000 2000 1000
ST
R
2900 2800 2700 2600
IN
GROSS MASS – kg
2600kg – 3200kg
–30
17000 16000 15000
FO
R
–10
Fig. 53
ED
–45 to –40
–8
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
Rate of climb (AEO, MCP, 2600 kg to 3200 kg, clean bypass closed, clog trend bypass closed, bypass open, heating off)
APPROVED Rev. 1
9.2-5 – 61
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY CLEAN BYPASS CLOSED CLOG TREND BYPASS CLOSED BYPASS OPEN
20000 19000 18000
–45 to –40
3200kg – 3700kg
N TR
–45 to –40 –30 to 40
O
T
C
O
14000 13000 12000 11000
PY
N
10000 9000 8000
LY
–
C
O
7000 6000 5000 4000
O N O N
–45 to 50 REFERENCE LINE
4
IN
2
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
0
ST
R
U
C
TI
0 3200 3300 3400 3500 3600 3700
BK117D2M012_3_IBF_2
3000 2000 1000 GROSS MASS – kg
O
LL
–30
17000 16000 15000 PRESSURE ALTITUDE –ft
ED
HEATING OFF
Fig. 54
Rate of climb (AEO, MCP, 3200 kg to 3700 kg, clean bypass closed, clog trend bypass closed, bypass closed, heating off)
9.2-5 – 62
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY CLEAN BYPASS CLOSED CLOG TREND BYPASS CLOSED BYPASS OPEN
20000 19000 18000
N TR
O
2000kg – 2600kg
O
–30 to 0
N
O
T
C
14000 13000 12000 11000
10 to 20
C
O
PY
10000 9000 8000
LY
–
7000 6000 5000 4000
O N O N
3000 2000 1000
TI
0
REFERENCE LINE
U
C
2600 2500 2400
ST
R
BK117D2012_11_IBF_2
PRESSURE ALTITUDE –ft
LL
–45 to –40
17000 16000 15000
R
IN
2300 2200 2100 2000
FO
GROSS MASS – kg
ED
HEATING ON
0
Fig. 55
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
Rate of climb (AEO, MCP, 2000 kg to 2600 kg, clean bypass closed, clog trend bypass closed, bypass open, heating on)
APPROVED Rev. 1
9.2-5 – 63
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY CLEAN BYPASS CLOSED CLOG TREND BYPASS CLOSED BYPASS OPEN
–45 to –40
N TR O C
–30 to 20
N
O
T
12000 11000 10000
O
PY
9000 8000 7000 6000
– LY O N O N
2000 1000 0
REFERENCE LINE
ST
R
U
C
BK117D2012_21_IBF_2
TI
3200 3100 3000 2900
IN
2800 2700 2600
–8
FO
–10
R
GROSS MASS – kg
LL O
–45 to –40
16000 15000 14000 13000
5000 4000 3000
Fig. 56
2600kg – 3200kg
–30 –20
C
PRESSURE ALTITUDE –ft
20000 19000 18000 17000
ED
HEATING ON
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
Rate of climb (AEO, MCP, 2600 kg to 3200 kg, clean bypass closed, clog trend bypass closed, bypass open, heating on)
9.2-5 – 64
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
RATE OF CLIMB 2 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY CLEAN BYPASS CLOSED CLOG TREND BYPASS CLOSED BYPASS OPEN HEATING ON
3200kg – 3700kg
LL
17000 16000 15000 14000
N TR
O
–45 to –40
O
T
C
O
–30 to 20
13000 12000 11000
O
PY
N
10000 9000 8000 7000
LY
–
C
6000 5000 4000 3000
REFERENCE LINE
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
RATE OF CLIMB – 100 ft/min
FO
R
0
IN
ST
R
U
C
TI
3200 3300 3400 3500 3600 3700
BK117D2012_31_IBF_2
O N
2000 1000 0 GROSS MASS – kg
ED
–45 to –40 –30 –20
O N
PRESSURE ALTITUDE –ft
20000 19000 18000
Fig. 57
Rate of climb (AEO, MCP, 3200 kg to 3700 kg, clean bypass closed, clog trend bypass closed, bypass closed, heating on)
APPROVED Rev. 1
9.2-5 – 65
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY BYPASS OPEN HEATING OFF
20000 19000 18000
–45 to –40
LL O T
C
O
–30 to –10
N TR
–30 –20
14000 13000 12000 11000
PY
N
O
10000 9000 8000
O
7000 6000 5000 4000
C
40
–
–45 to –40
0 to 50
LY
3000 2000 1000
O N
–30 to –10 REFERENCE LINE
O N
0
C
TI
2600 2500 2400
BK117D2M013_1_IBF_3
PRESSURE ALTITUDE –ft
17000 16000 15000
ST
R
U
2300 2200 2100 2000 –8
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
FO
R
–10
IN
GROSS MASS – kg
ED
2000kg – 2600kg
Fig. 58
9.2-5 – 66
Rate of climb (OEI, MCP, 2000 kg to 2600 kg, bypass open, heating off)
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY BYPASS OPEN HEATING OFF
20000 19000 18000
N TR
O
–30 –20 –45 to –40
14000 13000 12000 11000
C
O
–30 to –10
T
0 to 50
PY
N
O
10000 9000 8000
C
O
7000 6000 5000 4000
40
–
0 to 50
LY
3000 2000 1000
–45 to –40
O N
–30 to –10
O N
0 3200 3100 3000
REFERENCE LINE
C
TI
BK117D2M013_2_IBF_3
PRESSURE ALTITUDE –ft
LL
–45 to –40
17000 16000 15000
ST
R
U
2900 2800 2700 2600
IN
GROSS MASS – kg
ED
2600kg – 3200kg
–8
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
FO
R
–10
Fig. 59
APPROVED Rev. 1
Rate of climb (OEI, MCP, 2600 kg to 3200 kg, bypass open, heating off)
9.2-5 – 67
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY BYPASS OPEN
ED
HEATING OFF
20000 19000 18000 –45 to –40
T N
O
–30 to –10
PY
O
0 to 50
LY
–
C
7000 6000 5000 4000
0 to 50
–45 to –40
O N
–30 to –10
REFERENCE LINE
–8
FO
R
–10
IN
ST
R
U
C
TI
0 3200 3300 3400 3500 3600 3700
Fig. 60
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
BK117D2M013_3_IBF_3
3000 2000 1000 GROSS MASS – kg
C
–20
10000 9000 8000
9.2-5 – 68
O
–30
14000 13000 12000 11000
O N
PRESSURE ALTITUDE –ft
17000 16000 15000
N TR
O
LL
3200kg – 3700kg
22
RATE OF CLIMB – 100 ft/min
Rate of climb (OEI, MCP, 3200 kg to 3700 kg, bypass open, heating off)
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY BYPASS OPEN HEATING ON
O
–30
N TR
16000 15000 14000 13000
LL
–45 to –40
O
–20 –30 to –10
O
T
C
12000 11000 10000
PY
N
9000 8000 7000 6000
–45 to –40
0 to 20
LY
–
C
5000 4000 3000
–30 to –10
O N
2000 1000 0 2600
BK117D2013_11_IBF_3
O N
REFERENCE LINE
U
C
TI
2500 2400 2300
ST
R
2200 2100 2000
IN
GROSS MASS – kg
ED
2000kg – 2600kg
O
PRESSURE ALTITUDE –ft
20000 19000 18000 17000
–8
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
FO
R
–10
Fig. 61
APPROVED Rev. 1
Rate of climb (OEI, MCP, 2000 kg to 2600 kg, bypass open, heating on)
9.2-5 – 69
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY BYPASS OPEN HEATING ON
ED
20000 19000 18000
N TR O
T
–30 to –10
PY
N
10000 9000 8000
–
C
O
7000 6000 5000 4000
–45 to –40
O N
0 to 20
O N
–30 to –10 REFERENCE LINE
U
C
BK117D2013_21_IBF_3
TI
0 3200 3100 3000
–8
FO
–10
R
2600
IN
ST
R
2900 2800 2700
Fig. 62
9.2-5 – 70
C
O
–30 –20 –10
14000 13000 12000 11000
3000 2000 1000
GROSS MASS – kg
O
–45 to –40
LY
PRESSURE ALTITUDE –ft
17000 16000 15000
LL
2600kg – 3200kg
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
Rate of climb (OEI, MCP, 2600 kg to 3200 kg, bypass open, heating on)
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E MAXIMUM CONTINUOUS POWER
VY BYPASS OPEN HEATING ON
20000 19000
15000 14000 13000 12000
C
O
–30 –20 –10 –30 to –10
N
O
T
11000 10000 9000
O
PY
8000 7000 6000 5000
–
–45 to –40
LY
0 to 20
O N
–30 to –10
O N
1000 0 3200 3300 3400 3500
U
C
TI
REFERENCE LINE
IN
–8
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
RATE OF CLIMB – 100 ft/min
FO
R
–10
ST
R
3600 3700
BK117D2013_31_IBF_3
4000 3000 2000
GROSS MASS – kg
N TR
O
–45 to –40
C
PRESSURE ALTITUDE –ft
18000 17000 16000
LL
ED
3200kg – 3700kg
Fig. 63
APPROVED Rev. 1
Rate of climb (OEI, MCP, 3200 kg to 3700 kg, bypass open, heating on)
9.2-5 – 71
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
EFFECTIVITY
OEI
OEI
TU206 NOT installed
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN. POWER
VTOSS = 45 KIAS BYPASS OPEN
LL
ED
HEATING OFF
O
20000 19000 18000
N TR
2000kg – 2600kg
O C T PY
N
O
14000 13000 12000 11000
– O N TI
3000 2000 1000
20 to 40
C
–45 to –20
U
0 2600 2500 2400
R
IN
ST
BK117D2M512_1_IBF_3
R
REFERENCE LINE
FO
GROSS MASS – kg
–10 to 10
LY
7000 6000 5000 4000
2300 2200 2100 2000
–30 to –20
C
O
10000 9000 8000
–45 to –40
O N
PRESSURE ALTITUDE –ft
17000 16000 15000
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
RATE OF CLIMB – 100 ft/min
Fig. 64
9.2-5 – 72
Rate of climb (OEI, 2 min. power, without TU206, 2000 kg to 2600 kg, bypass open, heating off) APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
EFFECTIVITY
OEI
OEI
TU206 NOT installed
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN. POWER
VTOSS = 45 KIAS BYPASS OPEN
LL
ED
HEATING OFF
O
20000 19000 18000
N TR O T O
14000 13000 12000 11000
C
–45 –40
PY
N
–45 to –40 –30 to 40
–
C
O
10000 9000 8000
LY
7000 6000 5000 4000
O N
–45 to 40
C
TI
O N
3000 2000 1000
REFERENCE LINE
R
U
0 3200 3100 3000
IN
ST
BK117D2M512_2_IBF_3
PRESSURE ALTITUDE –ft
17000 16000 15000
R
2900 2800 2700 2600
FO
GROSS MASS – kg
2600kg – 3200kg
–8
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
24
RATE OF CLIMB – 100 ft/min
Fig. 65
Rate of climb (OEI, 2 min. power without TU206, 2600 kg to 3200 kg, bypass open, heating off)
APPROVED Rev. 1
9.2-5 – 73
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
EFFECTIVITY
OEI
OEI
TU206 NOT installed
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN. POWER
VTOSS = 45 KIAS BYPASS OPEN
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
HEATING OFF
Fig. 66
9.2-5 – 74
Rate of climb – VTOSS (OEI, 2 min. power without TU206, 3200 kg to 3700 kg, bypass open, heating off) APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
EFFECTIVITY
OEI
OEI
TU206 installed or after Helionix Maintenance Release 1
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITH TU206) VTOSS = 45 KIAS
2 MIN. POWER
HEATING OFF
O
LL
ED
BYPASS OPEN
N TR
20000 19000
O C O
–45
PY
N
–40
O
11000 10000 9000
–
C
–45 to –40 –30 to –20
O N
LY
8000 7000 6000 5000
–10 to 10
20 to 30
C
TI
4000 3000 2000
R
U
1000 0 2600 2500
IN
BK117D2512_1_IBF_3_r2
ST
REFERENCE LINE
R
2400 2300 2200
FO
GROSS MASS – kg
T
15000 14000 13000 12000
O N
PRESSURE ALTITUDE –ft
18000 17000 16000
2000kg – 2600kg
2100 2000
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
RATE OF CLIMB – 100 ft/min
Fig. 67
Rate of climb (OEI, 2 min. power, with TU206 or after Helionix Maintenance Release 1, 2000 kg to 2600 kg, bypass open, heating off)
APPROVED Rev. 2
9.2-5 – 75
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
EFFECTIVITY
OEI
OEI
TU206 installed or after Helionix Maintenance Release 1
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITH TU206) 2 MIN. POWER
VTOSS = 45 KIAS BYPASS OPEN
N TR
O
LL
ED
HEATING OFF
20000 19000
2600kg – 3200kg
O C T
LY
–
–45 to 30
O N
8000 7000 6000 5000
U
C
TI
4000 3000 2000
ST
R
1000 0 3200 3100
R
IN
BK117D2512_2_IBF_3_r2
REFERENCE LINE
FO
GROSS MASS – kg
N PY O C
11000 10000 9000
3000 2900 2800
O
–45 –40
15000 14000 13000 12000
O N
PRESSURE ALTITUDE –ft
18000 17000 16000
2700 2600 –8
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
24
RATE OF CLIMB – 100 ft/min
Fig. 68
Rate of climb (OEI, 2 min. power, with TU206 or after Helionix Maintenance Release 1, 2600 kg to 3200 kg, bypass open, heating off)
9.2-5 – 76
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
EFFECTIVITY
OEI
TU206 installed or after Helionix Maintenance Release 1
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITH TU206) 2 MIN. POWER
VTOSS = 45 KIAS
PY
N
O
T
C
–45 –40
15000 14000 13000 12000
O
11000 10000 9000
C
–45 to 30
LY
–
8000 7000 6000 5000
O N TI
O N
4000 3000 2000
U
C
1000 0 3200 3300 3400 3500 3600 3700
FO
R
IN
ST
R
REFERENCE LINE
–8
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
22
BK117D2512_3_IBF_3_r2
PRESSURE ALTITUDE –ft
18000 17000 16000
3200kg – 3700kg
O
N TR
O
20000 19000
GROSS MASS – kg
HEATING OFF
LL
ED
BYPASS OPEN
24
RATE OF CLIMB – 100 ft/min
Fig. 69
Rate of climb – VTOSS (OEI, 2 min. power, with TU206 or after Helionix Maintenance Release 1, 3200 kg to 3700 kg, bypass open, heating off)
EFFECTIVITY APPROVED Rev. 2
All
9.2-5 – 77
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
EFFECTIVITY
OEI
OEI
TU206 NOT installed
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITHOUT TU206) 2 MIN. POWER
VY BYPASS OPEN
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
HEATING OFF
Fig. 70
9.2-5 – 78
Rate of climb – VY (OEI, 2 min. power, without TU206, 3200 kg to 3700 kg, bypass open, heating off) APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
EFFECTIVITY
OEI
TU206 installed or after Helionix Maintenance Release 1
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
RATE OF CLIMB 1 X TURBOMECA ARRIEL 2E (WITH TU206) 2 MIN. POWER
VY HEATING OFF
O
LL
ED
BYPASS OPEN
N TR
20000 19000
O C T O
15000 14000 13000 12000
N
–45
PY
–40
C
O
11000 10000 9000
– O N
LY
8000 7000 6000 5000
C
TI
4000 3000 2000
R
IN
ST
REFERENCE LINE
3600 3700
–10
–8
–6
–4
–2
0
2
4
6
8
10
12
14
16
18
20
BK117D2513_3_IBF_3_r2
R
U
1000 0 3200 3300 3400 3500
FO
GROSS MASS – kg
–45 to 40
O N
PRESSURE ALTITUDE –ft
18000 17000 16000
3200kg – 3700kg
22
RATE OF CLIMB – 100 ft/min
Fig. 71
Rate of climb – VY (OEI, 2 min. power, with TU206 or after Helionix Maintenance Release 1, 3200 kg to 3700 kg, bypass open, heating off)
EFFECTIVITY APPROVED Rev. 2
All
9.2-5 – 79
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
5.7
Landing distance from 50 feet height to a complete stop on the ground (1 x TURBOMECA ARRIEL 2E) The landing distance chart (Fig. 72) provides single engine landing performance data. Under this certification basis (FAR 29, category B), go-around capability is NOT assured during one-engine-inoperative operation.
Determine:
Landing distance required to clear a 50 ft obstacle
LL
(see Fig. 72)
O
EXAMPLE:
ED
The chart (Fig. 72) shows the landing distance required until the helicopter comes to a complete stop on a smooth, hard and dry level surface.
N TR
For headwind calculation refer to the wind component chart section 1 of the FLM page 1-14.
C
O
Pressure altitude
Known:
O
T
OAT
N
Headwind component
Landing distance = 290 m
50 kt 25 kt
C
Solution:
25_C
O
PY
For calculation 50% of the headwind component.
5000 ft
LY
–
Enter chart at known OAT (25_C)
O N
Move upwards to known pressure altitude (5000 ft)
O N
From point of intersection move horizontally right to the reference line of the right chart.
TI
Move vertically downwards to the reference line of the wind credit chart.
U
C
From this point follow the direction of the wind credit guide lines.
ST
R
Enter chart at calculated headwind (25 kt)
FO
R
IN
Move horizontally to intersect tracing from above.
9.2-5 – 80
From point of intersection move downwards and read OEI landing distance = 290 m (The result under the assumption of no wind is 495 m)
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
OEI
LANDING DISTANCE FROM 50 FEET TO A COMPLETE STOP ON THE GROUND 1 X TURBOMECA ARRIEL 2E ROD 500 FT/MIN, 40 KIAS AT 50 FT
POWER AS REQUIRED
HEATING OFF
IN
ST
R
U
C
BK117D2035_1_IBF_3_r2
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
20000 ft DA
–40
–30
–20
–10
0
10
20
30
40
FO
R
–50
50
Headwind – kts Unfactored
0 10 20 30 100
Fig. 72
APPROVED Rev. 1
200 300 400 500 Cat. B Takoff Distance – m
600
Landing distance from 50 ft height to a complete stop on the ground (OEI)
9.2-5 – 81
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
5.8
ADDITIONAL NON-APPROVED PERFORMANCE DATA This subsection contains additional, non-approved performance data which are supplied by the aircraft manufacturer, useful for preflight and inflight mission planning.
5.8.1
Standard performance conditions All information in this section is based on the following conditions: 1. Engine power does not exceed helicopter limits (see section 2 of basic the FLM).
Variable factors affecting performance
LL
5.8.2
Helicopter is regarded in its clean configuration with IBF installed.
ED
2.
N TR
O
Details of the variable factors affecting performance are given in the respective diagrams.
C
O
NOTE D None of the curves presented should be extrapolated, but interpolation between given data is permissible.
Reading of the charts
O
5.8.3
PY
N
O
T
D Performance data contained in this section are not assured in the event of sand or hailstone ingestion into the engine(s).
Maximum cruising speed
O N
5.8.4
O N
LY
–
C
It is of outmost importance that the charts be read accurately. In this type of presentation, errors in reading can be cumulative, resulting in large final errors. Close attention should be paid to subdivisions of the grid.
U
C
TI
The diagrams (Fig.73 to Fig.80) provide maximum cruising speed data in terms of true airspeed as a function of helicopter gross mass and pressure altitude for the atmospheric conditions ISA, ISA –20_C, ISA +20_C and ISA +35_C under AEO conditions.
R
IN
ST
R
For information concerning the influence of optional equipment on max. cruising speed refer to subsection 9.0. (see figure 73)
Determine:
Maximum cruising speed
Known:
Atmospheric condition
ISA
Pressure altitude
9200 ft
Gross mass
2600 kg
FO
EXAMPLE:
Solution:
Maximum cruising speed = 148 KTAS Enter chart (ISA) at known pressure altitude (9200 ft). Move horizontally right to known gross mass (2600 kg). From this point move vertically downwards and read maximum cruising speed = 148 KTAS.
9.2-5 – 82
MANUFACTURER’S DATA APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MAXIMUM CRUISING SPEED MAXIMUM CONTINUOUS POWER
BYPASS CLOSED BLEED AIR HEATING OFF
ED
20000
N TR
O
LL
18000
O
16000
T N
O
12000
PY
2400 kg 2200 kg
–
3600 kg
LY
3400 kg
6000
3200 kg
TI
O N
4000
2000
U
C
ISA
ST
R
0
90
IN
80
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
FO
R
BKD2_FLH_0344_R
2600 kg
C
3700 kg
8000
3000 kg 2800 kg
O
10000
O N
PRESSURE ALTITUDE – FT
C
14000
Fig. 73
MANUFACTURER’S DATA APPROVED Rev. 1
Maximum cruising speed (AEO, bypass closed, ISA)
9.2-5 – 83
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MAXIMUM CRUISING SPEED MAXIMUM CONTINUOUS POWER
BYPASS CLOSED BLEED AIR HEATING OFF
ED
20000
N TR
O
LL
18000
O
16000
C T O
12000
PY
N
3000 kg
2400 kg 2200 kg
–
3600 kg
LY
3400 kg
6000
3200 kg
TI
O N
4000
0
ST
R
U
C
2000
90
IN
80
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
FO
R
BKD2_FLH_0348_R
2600 kg
C
3700 kg
8000
2800 kg
O
10000
O N
PRESSURE ALTITUDE – FT
14000
Fig. 74
9.2-5 – 84
Maximum cruising speed (AEO, bypass closed, ISA –20_C)
MANUFACTURER’S DATA APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MAXIMUM CRUISING SPEED MAXIMUM CONTINUOUS POWER
BYPASS CLOSED BLEED AIR HEATING OFF
ED
20000
O
LL
18000
N TR
16000
O C N
O
T
12000
2600 kg 2400 kg
O
3700 kg
2800 kg
PY
10000
3000 kg
C
8000
2200 kg
LY
–
3600 kg
6000
3200 kg
O N
4000
0
R
U
C
TI
2000
BKD2_FLH_0347_R
3400 kg
O N
PRESSURE ALTITUDE – FT
14000
90
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
FO
R
IN
ST
80
Fig. 75
Maximum cruising speed (AEO, bypass closed, ISA +20_C)
MANUFACTURER’S DATA APPROVED Rev. 1
9.2-5 – 85
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MAXIMUM CRUISING SPEED MAXIMUM CONTINUOUS POWER
BYPASS CLOSED BLEED AIR HEATING OFF
ED
20000
O
LL
18000
O
N TR
16000
T O
12000
N
3000 kg
PY
2600 kg
2200 kg
–
3600 kg
2400 kg
C
3700 kg
8000
LY
3400 kg
6000
3200 kg
TI
O N
4000
U
C
2000
ST
R
0
90
IN
80
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
FO
R
BKD2_FLH_0362_R
2800 kg
O
10000
O N
PRESSURE ALTITUDE – FT
C
14000
Fig. 76
9.2-5 – 86
Maximum cruising speed (AEO, bypass closed, ISA +35_C)
MANUFACTURER’S DATA APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MAXIMUM CRUISING SPEED MAXIMUM CONTINUOUS POWER
BYPASS OPEN BLEED AIR HEATING OFF
ED
20000
O
LL
18000
N TR
16000
PRESSURE ALTITUDE – FT
C
O
14000
O
T
12000
N
2800 kg
2400 kg
C
O
3700 kg
8000
2600 kg
PY
10000
3000 kg
2200 kg
–
3600 kg
3400 kg
LY
6000
O N
3200 kg
O N
4000
TI
ISA
R
0
U
C
BKD2_FLH_0338_R
2000
90
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
FO
R
IN
ST
80
Fig. 77
MANUFACTURER’S DATA APPROVED Rev. 1
Maximum cruising speed (AEO, bypass open, ISA)
9.2-5 – 87
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MAXIMUM CRUISING SPEED MAXIMUM CONTINUOUS POWER
BYPASS OPEN BLEED AIR HEATING OFF
LL
ED
20000
N TR
O
18000
C
O
16000
O N
12000
PY
3000 kg
2400 kg 2200 kg
LY
3600 kg
3400 kg
O N
6000
3200 kg
TI
4000
0
IN
80
ST
R
U
C
2000
90
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
FO
R
BKD2_FLH_0342_R
2600 kg
–
3700 kg
8000
2800 kg
C
O
10000
O N
PRESSURE ALTITUDE – FT
T
14000
Fig. 78
9.2-5 – 88
Maximum cruising speed (AEO, bypass open, ISA –20_C)
MANUFACTURER’S DATA APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MAXIMUM CRUISING SPEED MAXIMUM CONTINUOUS POWER
BYPASS OPEN BLEED AIR HEATING OFF
LL
ED
20000
N TR
O
18000
O
16000
O
PRESSURE ALTITUDE – FT
T
C
14000
N
12000
PY
2800 kg 2600 kg
O
10000 3700 kg
C
2400 kg
–
8000
2200 kg
LY
3600 kg
O N
6000
3400 kg 3200 kg
TI
O N
4000
ST
0
R
U
C
2000
90
IN
80
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
FO
R
BKD2_FLH_0341_R
3000 kg
Fig. 79
Maximum cruising speed (AEO, bypass open, ISA +20_C)
MANUFACTURER’S DATA APPROVED Rev. 1
9.2-5 – 89
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
MAXIMUM CRUISING SPEED MAXIMUM CONTINUOUS POWER
BYPASS OPEN BLEED AIR HEATING OFF
20000
LL
ED
18000
N TR
O
16000
O C
12000
O
T
3000 kg 2600 kg
2200 kg
C
3600 kg
2800 kg
2400 kg
O
3700 kg
8000
3400 kg
–
6000
3200 kg
O N
O N
4000
C
TI
2000
U
0
90
ST
R
80
100
110
120
130
140
150
160
170
180
MAXIMUM CRUISING SPEED – KTAS
FO
R
IN
BKD2_FLH_0360_R
PY
N
10000
LY
PRESSURE ALTITUDE – FT
14000
Fig. 80
9.2-5 – 90
Maximum cruising speed (AEO, bypass open, ISA +35_C)
MANUFACTURER’S DATA APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
5.8.5
Specific fuel consumption For information concerning the influence of the IBF system on the specific fuel consumption refer to subsection 9.0.
5.8.6
Maximum range For information concerning the influence of the IBF system on the maximum range refer to subsection 9.0. Endurance
ED
5.8.7
FO
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IN
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–
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N
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For information concerning the influence of the IBF system on the endurance refer to subsection 9.0.
MANUFACTURER’S DATA APPROVED Rev. 1
9.2-5 – 91
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
6
MASS AND BALANCE Refer to Equipment List entries in Section 6 of the basic Flight Manual.
7
SYSTEM DESCRIPTION
7.1
GENERAL
LL
ED
The Inlet Barrier Filter (IBF) system is installed to remove foreign objects such as sand, dust or other particles from the engine inlet air stream in order to prevent premature erosion of compressor blades and other engine components.
C
O
N TR
O
The IBF system (see Fig. 81) consists of two completely separated filter frames (1), which are installed so that each engine intake in front of the firewall is completely covered. The filter frame creates two passageways for the air to enter the engine: Through the filter element (2) and via a bypass door (9).
PY
N
O
T
The filter element allows air to pass through the filter while effectively retaining most foreign matter. The filter element is made of cotton gauze soaked with oil and can be easily replaced and cleaned through a maintenance action. Water entering through the filter can escape through two drain ports (4, 7) at the bottom of each frame.
LY
–
C
O
The bypass doors (9) are installed to prevent excessive performance detriments and engine flame out when the filter element is clogged. The bypass doors are controlled by an electric actuator (5), which is connected to the essential bus.
FO
R
IN
ST
R
U
C
TI
O N
O N
Filter element clogging is measured through a static pressure port (6) located in the filter frame. The pressure difference between the filter frame and aircraft static ports is an indication of the degree of filter contamination (clogging). The pressure measurement is presented as a clogging level in percent on the VMS page. This percentage level is calculated from the pressure loss taking into account altitude, airspeed and power setting. Despite these corrections, slight clogging indication variations can still occur.
9.2-5 – 92
MANUFACTURER’S DATA APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
2 3
N
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ED
1
O
PY
A
C
4
O N
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–
5 7
6
C
TI
O N
8
9 Fig. 81 1
Filter frame
2
Filter element
MANUFACTURER’S DATA APPROVED Rev. 1
D2_FLH_0134_R
FO
R
IN
ST
R
U
A
IBF, typical installation
9.2-5 – 93
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
3
Electrical line
4
Drain port aft
5
Bypass door actuator
6
Pressure port
7
Pressure line
8
Drain port fwd
9
Bypass door and screen IBF SYSTEM OPERATION
ED
7.2
N TR
O
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The switches for operation of the IBF system are located in the overhead panel (see Fig. 82). The IBF system is operated through two separate IBF switches with three switch positions: NORM, OPEN and CLOSE.
OFF
CLOSE
PY O C
2 IBF
RECALL
RECALL
O N
IBF switches, typical installation
O N
Fig. 82
The IBF system is active, the bypass door is closed. The engine is protected from foreign matter. When an OEI condition is detected in flight (power split condition), both bypass doors will open automatically. When dangerously excessive clogging is detected (equivalent to about 140% clogging), the bypass doors will open automatically to protect the engines from being damaged or surging.
CLOSE
9.2-5 – 94
IBF system is inactive, the bypass door is open. The engine is not protected from foreign matter.
FO
OPEN
R
IN
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NORM
NORM
LY
1
–
BKD2_FLH_0135_R
O P E N
N
O
T
C
O
The IBF RECALL switch allows the maximum clogging level that was encountered since the last reset to be displayed by momentarily placing the switch in the RECALL position. Each time a new or cleaned filter is installed, the RECALL value shall be reset to zero (by holding the switch in the RECALL position for more than 15 seconds).
The bypass doors are closed and will not open automatically in case of OEI condition or dangerously excessive clogging. This mode can be used to override an automatic opening of the bypass doors in case of OEI, to protect the remaining engine.
MANUFACTURER’S DATA APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
7.3
IBF INDICATIONS The IBF status is indicated on the VMD and FND (see Fig. 83). The IBF indicators (1, 2) on the VMD show the IBF clogging level and the IBF operation configuration. The clogging is indicated in percent (0 to 100%). Clogging beyond 100% is not indicated (indication remains at 100%). Master list messages for the IBF system are indicated on the FND in the master list area (3). Refer to Para. 7.3.1 for a complete list of master list messages.
700 N1
94.0 %
72 _C 9.0 FUELKg
D A T A
314
54
2
30 _C 3.0 3.0
G1
G2
R N G
FF Kg/h 137
O
TIME ZONE
STATUS
CONF
C
WEIGHT
10
80
20
20
N
O
600 DA
3
20
+ B R G –
+ L U M –
DTK
FSD
DCPL
IBF1
ND
16
16
1 500
15
14
14
13
13
D A
D H B A R O
1013 200 hPa DH
3
20
10
N 354 1.0 A FMS V GPS INS/GPS LFMH 20.0NM 12min
17
10
RA
BYPASS FAIL
A C K
IBF2
415 Kg SCT
WXR
SVS
+ B R G –
OAT 25
_F
IBF indication on VMD and FND – typical display
O N
Fig. 83
10
3
17
+ C T R S –
O N
LY
EPC
101. 0 %
–
101. 0 % N2 EPCPL REPORT
10
VY
C R S
101. 0
+ L U M –
100
N
47
MGB OIL _C B B A A R R
72 _C 9.0 100
4
PY
103 103
ENG OIL B A R
10
N U M
IBF
30 %
20
T
_C ENG OIL B B A A R R
2 h 30 min
FF Kg/h 137
N1
94.0 %
20
120
710
10 %
CLOCK
IAS
18
6 TOT
IBF
HDG
101
55.0 %
TOT
B A R
ALT
TRQ
55.0 %
HYD
+ C T R S –
EFB
N TR
MISC
O
DMAP
TRQ
R C N F
BKD2_FLH_0414_R
VMS
O
S Y S T
1
NAVD
C
FND
MFD – FND
LL
MFD – VMD
ED
2
IBF indicator, engine 1
2
IBF indicator, engine 2
3
Master list area
IN
ST
R
U
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TI
1
IBF
10 % IBF OPEN
IBF 65 %
BKD2_FLH_0139_R BKD2_FLH_0138_R BKD2_FLH_0137_R
FO
R
The presentation of the IBF indicator depends on the current clogging level and operation configuration. Normal operation, bypass door closed
Bypass door open
Bypass door closed Limit of clean filter performance exceeded (more than 40% clogging exceeded)
MANUFACTURER’S DATA APPROVED Rev. 1
9.2-5 – 95
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
IBF 100 % IBF
Bypass door closed IBF clogged (100% or more) IBF pressure sensor failed
IBF Master List messages
O O
IBF2
Respective IBF bypass door is not in fully opened or fully closed position
C
BYPASS FAIL
O
T
and/or BYPASS FAIL
PY
N
IBF2
Respective IBF is clogged (w 100% clogging)
CLOGGED
O
IBF1
N TR
and/or BYPASS CLOSED IBF1
ED
Respective IBF bypass door closed via the IBF sw
BYPASS CLOSED
and/or CLOGGED
EFFECTIVITY
LY
IBF2
C
IBF1
Description
LL
ML cautions
–
7.3.1
BKD2_FLH_0141_R BKD2_FLH_0140_R
INLET BARRIER FILTER SYSTEM
The IBF CLOGGING caution will be latched until the clogging level has been reset (by holding the IBF RECALL switch in the RECALL position for more than 15 seconds).
Incorrect IBF configuration (discrepancy between hardware installation and VMS/CONF page)
PRESS SENSOR
Respective IBF pressure sensor failed
IN
INCORRECT CONFIG
and/or PRESS SENSOR
9.2-5 – 96
All
R IBF1
EFFECTIVITY IBF2
FO
IBF1
ST
R
U
C
TI
O N
O N
NOTE
After Helionix Maintenance Release 1
IBF2
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
ML white advisories
Description IBF clogging trend (40% clogging)
IBF CLOG TREND
After Helionix Maintenance Release 1
EFFECTIVITY
The IBF CLOG TREND alert will be latched until the clogging level has been reset (by holding the IBF RECALL switch in the RECALL position for more than 15 seconds). All
ML information messages
Description
Respective IBF bypass door in open position
and/or BYPASS OPEN
T
C
O
BYPASS OPEN
O
IBF2
FO
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O N
O N
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–
C
O
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N
IBF1
N TR
O
EFFECTIVITY
LL
ED
NOTE
MANUFACTURER’S DATA APPROVED Rev. 2
9.2-5 – 97
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) INLET BARRIER FILTER SYSTEM
7.4
FLIGHT REPORT PAGE During flight, the maximum clogging level is monitored by the UMS. If the clogging level exceeded 65%, this will be indicated on the flight report page (see Fig. 84). Maintenance is recommended based on the exceeded clogging level as follows: – Clogging level > 65%: Maintenance is recommended before the next flight if operations are planned in sandy or dusty conditions (all operations/landings in sand or dust).
O
LL
– Clogging level >100%: Maintenance is required before the next flight.
ED
– Clogging level > 80%: Maintenance is recommended before the next flight if operations are planned in normal conditions (occasional operations in light sand or dust).
O
T
C
O
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If maintenance as recommended above cannot be performed, clogging level during the next flight is likely to exceed 100%, which requires opening the by-pass doors and will lead to excessive engine wear when flying in sandy/dusty conditions.
ENG SVC NEEDED FLT 478 CLOGGING 65% EXCEEDED CLOGGING 65% EXCEEDED
BKD2_FLH_0191_R
–
C
O
PY
N
4/4 IBF1 IBF2
_C
_C
_C
U
Example of a flight report page with clogging level between 65% and 80%
FO
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Fig. 84
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TI
O N
_C
O N
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_C
9.2-5 – 98
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
FMS
9.2-6
SUPPLEMENT FOR
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DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
Effectivity All All
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–
Dual External Cargo Hook External Mirror
O
C
System/Equipment Designation
PY
N
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This supplement shall be attached to the BK117 D-2 Flight Manual (Section 9.2) when the Dual External Cargo Hook and / or External Mirror are installed.
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971
APPROVED Rev. 0
9.2-6 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which a0re New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
Page
9.2-6 -11
3
EASA
9.2-6 -21
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3.1
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9.2-6 -22
9.2-6 -3
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9.2-6 -13
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3
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Rev.No
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N
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ED
App.
LL
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Page
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LOG OF REVISION
FIRST ISSUE ORIGINAL
(see page 9.2-6-1)
REVISION 1 EASA approval no.: 10059945
NOV 04, 2016
REVISION 2 DEC 18; 2017 EASA approval no.: 10064108 REVISION 3 DEC 12, 2018 EASA approval no.: 10067961 REVISION
3.1
(see entry below)
Revision 3.1 Date: MAR 07, 2019 Revision 3.1 is approved under authority of DOA ref. EASA.21J.700.
9.2-6 – 2
APPROVED Rev. 3.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
TABLE OF CONTENTS
Page GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 6
1.1 1.2
Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 6 Operational rules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 6
2
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 7
2.1
Type of operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 7
2.2 2.3 2.4
Occupants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 7 Mass and load limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 8 Center of gravity limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 8
2.5 2.6 2.7
Airspeed limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 9 Bank angle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 9 External load operational limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 9
2.8 2.9 2.10
Night operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 10 Compatibility with other optional equipment . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 10 Load attaching means . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 10
2.11 2.12
Communication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 11 Placards and decals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 11
3
EMERGENCY AND MALFUNCTION PROCEDURES . . . . . . . . . . . . . 9.2-6 – 15
3.1 3.2
External load jettisoning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 15 Engine failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 16
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
1
NHEC or HEC cargo hook operations not requiring OEI performance
C
TI
EFFECTIVITY
Single engine failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 16
R
U
3.2.1
HEC hook operations requiring OEI performance
IN
Single engine failure – cargo close to the ground . . . . . . . . . . . . . . . . 9.2-6 – 16 Single engine failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 17
FO
R
3.2.2 3.2.3
ST
EFFECTIVITY
3.2.4
EFFECTIVITY
Single engine landing with load attached . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 18 All
3.3
Master list indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 19
4
NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 20
4.1
Preflight check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 20
4.1.1 4.1.2 4.2
Cargo hook . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 20 External mirror (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 21 Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 22
4.2.1 4.2.2
Load attachment and lifting the load . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 22 Setting down the load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 23
APPROVED Rev. 3
9.2-6 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
Page Recording external cargo hook operations . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 24
5
PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 25
5.1
Cargo hook operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 25
5.2
Wind information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 25
5.3
AEO and OEI maximum rate of climb . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 25
5.4
Cargo hook operation requiring oei performance . . . . . . . . . . . . . . . . . 9.2-6 – 26
5.4.1
Hover OEI performance for HEC operations . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 26
5.4.2
Obstacle clearance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 28
5.5
OEI training . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 29
6
MASS AND BALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 30
6.1
Cargo hook loading charts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 30
7
SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 33
7.1
External cargo hook assy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 33
7.2
Cargo hook helionix indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 36
7.3
Power supply . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 38
7.4
Weighing system (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 38
7.5
Cargo hook mirror (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 40
8
HANDLING, SERVICING, AND MAINTENANCE . . . . . . . . . . . . . . . . . 9.2-6 – 42
8.1
Attachment of the external cargo hook assy . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 42
8.2
Cargo hook loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 43
8.2.1
Y–Rope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 44
8.2.2
Sling load rope swivel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 44
8.2.3
Additional rigging information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 44
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4.3
9.2-6 – 4
APPROVED Rev. 3
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LIST OF FIGURES Page HEC cargo hook operation OEI 30 sec . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 26
Fig. 2
HEC cargo hook operation OEI 30 sec – IBF installed . . . . . . . . . . 9.2-6 – 27
Fig. 3
Obstacle clearance during HEC cargo hook operation with OEI performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 28
Fig. 4
Basic C.G. envelope for single cargo hook operation (MTOW=3650kg, load path only to hook 1 (aft)) . . . . . . . . . . . . . . . 9.2-6 – 31
Fig. 5
Basic C.G. envelope for dual cargo hook operation (MTOW=3650kg, symmetric Y-rope: load path to hook 1+2) . . . . . 9.2-6 – 31
Fig. 6
Basic C.G. envelope for dual cargo hook operation (MTOW=3650kg, asymmetric Y-rope: load path to hook 1 and long leg to hook 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 32
Fig. 7
Cargo hook – Manual release side . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 33
Fig. 8
Cargo hook – Electrical release side . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 34
Fig. 9
Cargo hook lock indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 34
Fig. 10
Mechanical release on collective lever . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 35
Fig. 11
Safety guard . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 35
Fig. 12
Electrical release on cyclic stick . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 36
Fig. 13
Cargo hook load indication on VMS . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 36
Fig. 14
Cargo hook indication in the data area of VMD-format . . . . . . . . . . 9.2-6 – 37
Fig. 15
Weighing system – typical installation . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 39
Fig. 16
Cargo hook mirror assy – typical installation . . . . . . . . . . . . . . . . . . . 9.2-6 – 40
Fig. 17
Mirror controls on collective lever – typical installation . . . . . . . . . . 9.2-6 – 41
Fig. 18
External cargo hook beam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 42
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Cargo hook rigging – recommended . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 43
Cargo hook rigging dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 43
Fig. 21
Recommended cargo hook rigging – example . . . . . . . . . . . . . . . . . 9.2-6 – 45
Fig. 22
Jamming . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-6 – 45
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Fig. 20
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Fig. 19
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Fig. 1
APPROVED Rev. 0
9.2-6 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
1
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual. This FMS also applies for the installation of an external mirror only. In this particular case only the sections 2.2, 2.8, 2.10, 4.1.2, 5.3 and 7.5 are to be considered.
1.1
DEFINITIONS
LL
Non-Human External Cargo. Any cargo hook operation that does not at any time involve a person(s) being carried on the hook.
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NHEC:
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Human External Cargo. Any cargo hook operation where a person(s) is carried on the hook.
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HEC:
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HEC hook operations requiring the use of Cat A rotorcraft and where the helicopter has sufficient OEI hover capability to ensure safety of the rotorcraft, the persons on the hook and third parties or property in case of critical engine failure during the cargo hook operation.
O N
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–
N
HEC requiring OEI performance:
Intended opening of the hook release to drop the load.
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–
O N
Jettisonable:
ST
Personnel-Carrying Device System. The entire attached or suspended system used to carry HEC (harness, litter, karabiners, baskets, cages, longline, Y-rope, etc).
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PCDS:
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OPERATIONAL RULES
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1.2
The categorization of ”rotorcraft-load combinations” is given for guidance/information only, since it is an operational requirement defined in FAR Part 133 which may not be applicable in other countries and is subject to change and interpretation by the national operational authorities. The dual hook system described in this flight manual supplement was certified in accordance with Title 14 CFR 29, requirement 865. The dual hook can be used for: –
“Class B” rotorcraft-load combination when NHEC is carried.
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“Class B” rotorcraft-load combination when HEC is carried, but the requirements for hook operations requiring OEI performance are not fulfilled and/or no voice communication between the rotorcraft crew and the external occupants is possible.
9.2-6 – 6
APPROVED Rev. 3
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–
“Class D” rotorcraft-load combination when HEC is carried and the requirements for hook operations requiring OEI performance are fulfilled and voice communication between the rotorcraft crew and the external occupants is possible.
The following information pertaining to air operations in accordance with EU regulation 965/2012 (up to amendment 7) is provided for guidance/information only and is subject to change and interpretation by the national operational authorities: – The helicopter dual cargo hook installation satisfies the airworthiness criteria for human external cargo (HEC) operations. The BK117 D–2 dual cargo hook system was certificated in accordance with the following standards: FAR 29.865 amendment 47.
2.1
TYPE OF OPERATION
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LIMITATIONS
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– When the procedures and weight limits for HEC hook operations requiring OEI performance are used, the aircraft is capable of sustaining a critical engine failure with the remaining engine at the appropriate power setting without hazard to the suspended person(s)/cargo, third parties or property.
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Operations with a load attached to the (dual) cargo hook shall be conducted in accordance with the appropriate operating rules for external loads. Operations with Human External Cargo (HEC) require approval of the National Authority. Operation of the helicopter with cargo suspended from the hook is approved for the lifting of loads free of land or water under VFR (day/night incl. NVIS). The load jettisoning system (i.e. electrical and mechanical/hydraulic release) must be installed and operational. Towing of loads on land or water is prohibited. Immersion of a cable/rope attached to the cargo hook into water for the purpose of picking up loads is permissible within the hover speed range if obstacle clearance is ensured.
–
Non-human external cargo (NHEC) may be carried on the main hook (hook 1) using a single cargo suspension rope. If single hook operations with loads over 800 kg are intended, then hook 2 must be covered.
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Human or non-human external cargo (HEC or NHEC) may be carried, provided it is attached to both hooks simultaneously by means of a Y-rope. These operations are limited to a maximum external load of 800 kg.
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2.2
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Operation of the helicopter with no load suspended from the external cargo hook is permitted. The basic flight manual limitations apply.
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Category A VTOL take-off and landing with the cargo hook mirror installed in front of the pilot flying is prohibited.
OCCUPANTS The minimum flight crew for operation of the dual external cargo hook consists of one pilot on the right seat. If a load observer is carried on board, the observer must be secured to the attachment point in the helicopter with an approved PCDS.
APPROVED Rev. 3
9.2-6 – 7
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2.3
MASS AND LOAD LIMITS Maximum combined gross mass (H/C plus jettisonable external load) . . . . . . . 3700 kg Maximum external load mass for single hook operation (hook 1) . . . . . . . . . . . . 1600 kg Max. external load mass for dual hook operation via Y-rope (hook1 and 2) . . . 800 kg
2.4
CENTER OF GRAVITY LIMITATIONS
ED
During cargo hook operations, the CG envelope of the basic helicopter applies. The load charts given in Para 6.1 of this supplement may be used to determine compliance with this limitation.
THE MAXIMUM SPEED WITH SUSPENDED EXTERNAL LOAD MAY BE LIMITED BY FACTORS OTHER THAN VNE SUCH AS AERODYNAMIC DRAG, TENDENCY FOR OSCILLATIONS, ETC. THE MAXIMUM AIRSPEED SHALL NOT EXCEED THE AIRSPEED THAT IS SAFELY ACHIEVABLE WITH MAXIMUM 1000 FT/MIN RATE OF DESCENT.
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WARNING
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AIRSPEED LIMITATIONS
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2.5
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When using asymmetric Y-ropes to connect the load to hook 1 (main hook) and hook 2, the short leg shall be connected to hook 1 (main hook) and the long leg to hook 2.
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For unloaded cargo hook operation the basic helicopter airspeed limitations remain unchanged.
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VNE with external cargo operations is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 120 kt or indicated VNE, whichever is less
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VNE with human external cargo operations (HEC) is . . . . . . . . . . . . . . . . . . . . . . . . 70 kt or indicated VNE, whichever is less
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NOTE D For maximum airspeed during operation with open/removed doors refer to FMS 9.1–2.
FO
D If defined, the maximum approved airspeed of the PCDS shall be observed.
2.6
BANK ANGLE The max. bank angle during loaded cargo hook operation is : Below 50 KIAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . $ 20_. At or above 50 KIAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . $ 30_.
9.2-6 – 8
APPROVED Rev. 3
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2.7
EXTERNAL LOAD OPERATIONAL LIMITATIONS
WARNING D HELICOPTER HANDLING CHARACTERISTICS MAY BE AFFECTED BY THE SIZE, MASS, AND SHAPE OF THE EXTERNAL LOAD BEING CARRIED. IN PARTICULAR, LOADS OF RELATIVELY LOW MASS GENERATING SIGNIFICANT AERODYNAMIC REACTIONS ON ACCOUNT OF THEIR SIZE AND/OR SHAPE MAY BECOME UNSTABLE.
ED
D ANY UNSTABLE LOAD MAY JUMP, OSCILLATE OR ROTATE RESULTING IN LOSS OF CONTROL, UNDUE STRESS ON AND/OR CONTACT WITH THE HELICOPTER CAUSING POSSIBLE CATASTROPHIC RESULTS.
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D THEREFORE, EACH OPERATOR SHALL ESTABLISH ADEQUATE OPERATIONAL LIMITS AND PROCEDURES THAT PRECLUDE THE POSSIBILITY OF LOSING CONTROL OR OF THE LOAD CONTACTING THE HELICOPTER.
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D OPERATIONAL LIMITATIONS AND PROCEDURES SHALL BE ESTABLISHED TO PROVIDE THE PILOT WITH ADEQUATE MEANS OF CONTINUOUSLY MONITORING THE LOAD DURING FLIGHT.
IN SOME CASES, THE EXTERNAL LOAD MAY INTERACT WITH THE AUTOPILOT BASIC MODE (ATTITUDE MODE). THIS CAN RESULT IN NOTICEABLE VERTICAL BOUNCING. IN THIS CASE, THE A.TRIM SHALL BE DISENGAGED AND FLIGHT SHALL BE CONTINUED IN DSAS MODE.
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CAUTION
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D OPERATIONS WITH AN UNBALASTED SLING OR LIGHT WEIGHT CARGO (E.G. EMPTY BASKET) CAN BE EXTREMELY DANGEROUS, ESPECIALLY IN FORWARD FLIGHT WHERE THE LOAD IS DRAGGED BEHIND THE HELICOPTER AND CAN CONTACT THE HELICOPTER. WHEN HANDLING SUCH LOADS, CAUTION SHALL BE USED AND SPECIAL OPERATIONAL LIMITS SHALL BE ESTABLISHED.
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Use of autopilot upper modes is prohibited.
FO
Operations with an external load attached only to the forward hook (hook 2) are prohibited, except in emergency. For operations requiring on–board visual monitoring of the load, one of the following means can be used: –
External mirror;
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Camera system displayed on MFD 4 which allows monitoring the cargo hook load and cable/rope;
–
Load observer in the cabin or standing on the skids, with cabin sliding door opened and locked. For flight with open doors, a certified locking device for the sliding door must be installed.
APPROVED Rev. 3
9.2-6 – 9
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2.8
NIGHT OPERATIONS For night operation with the Fixed Landing Light (cross tube) and/or the Search and Landing Light (right side installation) in use, the cargo hook mirrors must be covered or removed.
2.9
COMPATIBILITY WITH OTHER OPTIONAL EQUIPMENT The protective capability of the Wire Strike Protection System is significantly degraded in combination with the external mirror assy. LOAD ATTACHING MEANS
ED
2.10
C
For HEC dual cargo hook operations requiring OEI performance, the maximum speed and the reduction in OEI climb performance at MCP of the PCDS plus HEC must be considered.
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HEC operations with the external cargo hook require the use of a Personnel Carrying Device System (PCDS), which must be approved by the local Aviation Authority. TSO-C167 provides one such acceptable means of approval. The PCDS also includes the attachment means (rings, Y-rope and rope).
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The load shall only be attached to the hook using an appropriate load attachment means capable of safely carrying the load and unable to jam.
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Refer to chapter 8.2 for detailed information.
9.2-6 – 10
APPROVED Rev. 3
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2.11
COMMUNICATION If a load observer is carried on board, intercommunication shall be maintained between the pilot(s) and the observer. The observer shall use the WINCH intercom connector. For HEC operations, verbal or non-verbal (i.e. hand signals) communication between the external occupants (HEC) and pilot(s)/onboard load observer must be maintained. If operational rules require verbal communication or if no load observer is on board, one of the following means of communication shall be used: Approved VHF or FM radio selectable on the crew intercom system and a portable radio carried by the external occupant (connected to a helmet/headset worn by an external occupant).
–
Polycon radio (see FMS 9.2–45).
PLACARDS AND DECALS
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2.12
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Placard:
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Placard:
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Location: RH cockpit windshield frame
Location: Collective pitch
APPROVED Rev. 3
9.2-6 – 11
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Placard:
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Location: Cargo hook RH side
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Placard:
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Location: Beam LH/RH and lower side (yellow)
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Placard:
Location: Beam LH/RH and lower side near hook 2 (red)
9.2-6 – 12
APPROVED Rev. 3.1
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Placard:
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Location: Beam LH/RH and lower side near main hook
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Placard:
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Location: Rear end of the beam (LH/RH)
APPROVED Rev. 0
9.2-6 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
Placard:
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Location: Rear end of the beam (LH/RH)
9.2-6 – 14
APPROVED Rev. 0
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3
EMERGENCY AND MALFUNCTION PROCEDURES In case of malfunction of the electrical release mechanism, the external load may be released via the backup release system (mechanical/hydraulic). A mechanical/hydraulic release is mounted on the pilot’s collective lever.
3.1
EXTERNAL LOAD JETTISONING Condition/Indications
LL
ED
Certain helicopter inflight emergencies (e.g. single-engine failure or loss of power) may dictate jettisoning of the external load.
N TR
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In general, the external load is to be jettisoned before contacting the ground. No minimum weight is needed to open the hook.
C
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Procedure
– Press
O C
2. Safety guard (on collective)
PY
if unsuccessful:
HOOK UNLOADED
– Push down – Pull – Check
HOOK UNLOADED
O N
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3. Mechanical/hydraulic release levers (2)
O N
Additionally confirm the load is released (mirror/load observer)
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NOTE
– Check
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1. HOOK 1 and HOOK 2 sw (cyclic stick)
APPROVED Rev. 3
9.2-6 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
3.2
ENGINE FAILURE
EFFECTIVITY 3.2.1
NHEC or HEC cargo hook operations not requiring OEI performance
Single engine failure This procedure shall be used if NHEC is attached to the hook or if HEC is attached and the required OEI hover capability is not given. Procedure
When necessary to safely complete the procedure:
C
Single engine failure – cargo close to the ground
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3.2.2
HEC hook operations requiring OEI performance
O
EFFECTIVITY
– Perform
N TR
2. External load jettisoning procedure
LL
ED
– Perform in accordance with basic flight manual
O
1. Single engine failure procedure
N
O
This procedure shall be used if:
The cargo (HEC) attached to the cargo hook is on or close to the ground/deck and can be safely lowered back to the ground/deck.
–
The aircraft gross mass is at or below the gross mass required for cargo hook operations requiring OEI performance (see 5.4.1).
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Procedure
O N
1. Hover position
– Descend vertically
C
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2. Helicopter
– Maintain
R
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When hook load is safe on ground: – Perform
IN
To avoid injuring the HEC, it may be necessary to descend and reposition slightly before jettisoning the cargo hook cable.
FO
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NOTE
ST
3. External load jettisoning procedure
4. Airspeed
– Accelerate to 30 kt, using 15_ nose down
5. Upon reaching 30 kt
– Select 2 min power – Accelerate to and VTOSS (45 KIAS)
climb
at
6. Upon reaching safe height
– Accelerate to VY
7. Collective lever
– Adjust to OEI MCP
8. Climb
– Continue with VY to 1000 ft AGL or desired flight altitude.
9.2-6 – 16
APPROVED Rev. 0
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9. Single engine emergency shutdown
– Perform
10. LAND AS SOON AS PRACTICABLE 3.2.3
Single engine failure This procedure shall be used if: The cargo (HEC) attached to the cargo hook is safely off the ground/deck.
–
The aircraft gross mass is at or below the gross mass required for cargo hook operations requiring OEI performance (see 5.4.1).
LL
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–
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Procedure
– Maintain
2. Collective lever
– Adjust to OEI 30 sec power
O
N TR
1. Hover position
O N
3. When red OEI counter starts flashing
T
C
– Climb vertically
C
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4. When HEC load is at least 35 ft (10 m) above obstacle height
– Maintain 45 kt
O N
At the discretion of the pilot, the climb at VTOSS and OEI 2 min power can be continued above 200 ft AGL, maximum until the amber OEI counter starts flashing.
TI
O N
NOTE
– Accelerate to and climb at VVTOSS (45 KIAS) using initially about 9_ nose down.
LY
–
5. Upon reaching at least 200 ft AGL
– Select 2 min power
ST
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6. Collective lever
– Accelerate to maximum approved airspeed – Perform
R
IN
7. Single engine emergency shutdown
– Reduce to MCP
FO
8. LAND AS SOON AS PRACTICABLE (see landing procedure)
APPROVED Rev. 2
9.2-6 – 17
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3.2.4
Single engine landing with load attached This procedure shall be used if: The aircraft is in forward flight in OEI with HEC attached to the cargo hook.
–
The aircraft gross mass is at or below the gross mass required for cargo hook operations requiring OEI performance (see 5.4.1).
–
The landing area shall be sufficiently large to deposit the HEC and land the helicopter.
ED
–
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THE APPROACH AND LANDING PROCEDURE USES HEC LOAD HEIGHT AND NOT AIRCRAFT HEIGHT. THE HEC LOAD HEIGHT IS OBTAINED BY SUBTRACTING THE LENGTH OF THE CABLE/PCDS FROM THE AIRCRAFT HEIGHT.
T
C
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WARNING
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Procedure
– Initiate 30 KIAS with HEC load at 150 ft AGL, 200 ft/min rate of descent.
LY
–
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1. Landing approach
O N
O N
2. HEC load
– Check safe on ground – Perform
U
To avoid injuring the HEC, it may be necessary to descend and move forward slightly before jettisoning the cargo hook cable.
ST
R
NOTE
– Lower to the ground
C
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3. External load jettisoning procedure
– Gradually reduce to hover with HEC load at 20 ft AGL, 100 ft/ min rate of descent.
– Perform
FO
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4. Single engine landing
EFFECTIVITY
9.2-6 – 18
All
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3.3
MASTER LIST INDICATIONS
CARGO HOOK OFF
ED
Conditions/Indications
O
LL
– Cargo hook is switched off (i.e. electrical load jettisoning is inoperative), although a weight on the hook is detected.
N TR
Procedure
– ARM
O
1. CARGO HOOK sw (overhead panel)
CARGO HOOK
N
PY
All
O N
O N
LY
–
EFFECTIVITY
This caution may appear temporarily during the start–up procedure.
O
NOTE
Before Helionix Maintenance Release 1
C
EFFECTIVITY
O
T
C
– Check
ST
R
U
C
TI
HOOK UNLOADED
IN
Conditions/Indications
FO
R
– The cargo hook is unloaded or the hook load is less than 5 kg. Procedure 1. Cargo hook
APPROVED Rev. 2
– Visually check that hook is unloaded (use mirror, camera or load observer)
9.2-6 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
NORMAL PROCEDURES WRONG INSTALLATION AND WRONG SECURING OF THE EXTERNAL CARGO HOOK ATTACHMENTS CAN CAUSE UNRECOVERABLE LOSS OF CONTROLLABILITY OR LOSS OF THE LOAD WHEN AN ATTACHMENT UNLOCKS IN FLIGHT.
4.1
PREFLIGHT CHECK
4.1.1
Cargo Hook
Cargo hooks and beam
– Condition
LL
For further details refer to Onboard Systems CMM 120–217–00.
NOTE
ED
WARNING
O
4
N TR
– Check hooks free to move – Condition, secured
Cargo hooks connectors (mechanical 2, electrical 2, hydraulic hoses)
– Condition, fixed
O
T
C
O
Quick release pins
PY
N
Cargo hook electrical release
–
C
O
CARGO HOOK sw (overhead panel)
U
C
TI
O N
O N
LY
Hook 1 (main hook)
FO
R
IN
ST
R
Hook 2
– ARM – Check
– Attach load of min. 5kg – Check HOOK UNLOADED goes off – Press HOOK 1 on cyclic – Check hook open – Check
HOOK UNLOADED
– Attach load of min. 5 kg – Check goes off
HOOK UNLOADED
– Press HOOK 2 sw on cyclic – Check hook open – Check
9.2-6 – 20
CARGO HOOK
HOOK UNLOADED
APPROVED Rev. 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
Cargo hook mechanical release Oil reservoir (on collective lever)
– Check oil level (between max/ min range) – No leakage
Hook 1 (main hook)
– Attach load of min. 5kg – Open lever guard on collective lever – Pull lever HOOK 1
LL
ED
– Check green mark is visible while firmly pulling lever (refer to Fig. 11, para 7.1)
O
– Check hook open – Attach load of min. 5kg
N TR
Hook 2
O
– Pull lever HOOK 2
C
– Check hook open
N
O
T
– Close lever guard on collective lever
– OFF – Check
CARGO HOOK
O N
External mirror (if installed)
– Condition, secured
External mirror
– Check electrical functions
TI
O N
External mirror, attachments and connectors
FO
R
IN
ST
R
U
C
4.1.2
– Close and check locked (refer to para 7.1)
LY
–
C
CARGO HOOK sw (overhead panel)
O
PY
Hooks 1 and 2
APPROVED Rev. 3
9.2-6 – 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
4.2
OPERATION WARNING D DURING FLIGHT, A STATIC ELECTRICITY CHARGE ACCUMULATES IN THE HELICOPTER. TO AVOID INJURY TO GROUND PERSONNEL, THE LOAD AND/OR HELICOPTER SHALL BE DISCHARGED BY ALLOWING THE LOAD AND/OR HELICOPTER TO TOUCH WATER OR GROUND BEFORE IT IS TOUCHED BY GROUND PERSONNEL.
LL
ED
D WHEN FLYING AT LOW HEIGHT, THE PILOT SHALL CONSIDER THE CABLE LENGTH TO DETERMINE THE MINIMUM SAFE HEIGHT. IT IS GOOD PRACTISE TO ADUST THE DECISION HEIGHT TO THE LENGTH OF THE CABLE PLUS SAFETY MARGIN.
N TR
O
CAUTION D SHOCK LOADS, JERKS AND SNAPS DURING CARGO HOOK OPERATION SHALL BE AVOIDED.
O
Load attachment and lifting the load
C
4.2.1
PY
N
O
T
C
O
D THE CARGO HOOK ELECTRICAL RELEASE SOLENOID IS INTENDED TO BE ENERGIZED ONLY INTERMITTENTLY. ACTUATING THE ELECTRICAL RELEASE SWITCH CONTINUOUSLY IN EXCESS OF 20 SECONDS WILL CAUSE THE SOLENOID TO OVERHEAT, POSSIBLY CAUSING PERMANENT DAMAGE.
LY
–
The cargo hook can be controlled/operated by the pilot or by the ground crew.
O N
O N
NOTE D Prior to external load pick up in flight, make sure hook is in OPEN position by momentarily depressing cyclic CARGO REL switch.
TI
Procedure
ST
R
U
C
1. CARGO HOOK sw (overhead panel)
– Check
CARGO HOOK
– Establish
FO
R
IN
2. Helicopter on ground or in hover at sufficient height to allow ground crew to attach cargo sling to the hook.
– ARM
CAUTION
DO NOT PASS THE LOAD ATTACHMENT CABLES OVER THE LANDING GEAR SKID TUBE WHEN ATTACHING THE LOAD WHEN THE HELICOPTER IS ON THE GROUND.
3. Hook lock indicator (refer Fig. 9) CAUTION
– Check fully locked position
GROUND PERSONNEL MUST MAKE SURE LATCHED CLOSED AFTER LOAD IS APPLIED.
LOAD HOOK
4. External mirror, camera or load observer
– Check load attached
5. To lift cargo from surface
– Climb slowly vertically
9.2-6 – 22
IS
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
6.
– Check off
HOOK UNLOADED
7. While lifting load and hovering
– Check power is within limits (on FLI.) If too high set down the load. – Note position of “blue line” – Check for satisfactory controllability and adequate directional control
ED
O
Setting down the load
N TR
4.2.2
– Perform
LL
8. Enter into slow speed forward flight and determine that no excessive oscillations occur
– Gradually reduce speed to arrive in hover with the load approximately 10 ft above the ground.
O
T
C
O
1. Landing approach
C
O
PY
N
2. To settle load
until
load
– Check load is safe on ground – Press – Check
HOOK UNLOADED
O N
LY
–
3. HOOK1 and HOOK2 sw (on cyclic stick)
– Descend vertically touches surface
TI
O N
NOTE D To avoid damage to the load or injuring HEC, it may be necessary to descend and reposition slightly before releasing the cargo hook cable.
IN
ST
R
U
C
D In some cases (e.g. Bambi Bucket), it may be necessary to land without releasing the load. In this case, the pilot can move forward or rearward carefully and land with the load attached.
FO
R
4. Load release
– Confirm visually (mirror/camera/ load operator)
If load is not released: 5. Safety guard on collective
– Push down
6. Mechanical levers
– Pull
7. Load release
– Confirm visually (mirror/camera/ load operator)
APPROVED Rev. 2
9.2-6 – 23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
4.3
RECORDING EXTERNAL CARGO HOOK OPERATIONS In order to comply with airworthiness and maintenance requirements, the following information has to be recorded in a manner which allows for subsequent monitoring of the achieved average numbers of the various cargo hook operation cycles in relation to external cargo flight hours: The number of load pick ups, duration and load mass of external cargo flights. – An external cargo flight is defined as a flight whereby an external load is attached at least once. – A load pickup is defined as the lifting of more than 300 kg. Each time the load weight is below 300 kg and is loaded again above 300 kg (e.g. placing down a load and picking it up again or emptying and refilling a bambi bucket), a new load pickup needs to be counted.
–
The load mass is defined as the mass which acts on the cargo hook just after picking up the load in hover.
–
Duration of external load operations should be interpreted to be (1) anything is attached to the cargo hook (whether or not a useful load is being transported) and (2) the aircraft is flying. If these conditions are not met, time does not need to be tracked. In case an asymmetric Y-rope is used, the duration for Hook 2 needs to be counted only if the load was really suspended from hook 2.
O
PY
N
O
T
C
O
N TR
O
LL
ED
–
O N
Observe limitations concerning total numbers, load mass and duration of dual cargo hook operation, as stated in the Maintenance Manual.
FO
R
IN
ST
R
U
C
TI
O N
NOTE
LY
–
C
If the weighing system is installed report any load release in flight > 400 kg. Maintenance of the weighing system is required.
9.2-6 – 24
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
5
PERFORMANCE DATA
5.1
CARGO HOOK OPERATION When determining climb and hover performances using the graphs in section 5 (of basic Flight Manual), any takeoff gross mass used to select the appropriate climb chart – or obtained from the hover ceiling chart – is to be considered as combined takeoff gross mass for the helicopter-load combination. NOTE
ED
WIND INFORMATION
LL
5.2
Climb performances are slightly reduced due to aerodynamic drag when carrying an external load, depending on size and shape of the load.
AEO AND OEI MAXIMUM RATE OF CLIMB
C
5.3
No change to the basic Flight Manual data.
O
–
N TR
O
Loaded cargo hook operations have been demonstrated with a compact heavy load under the following wind conditions:
PY
N
O
T
All results obtained from the respective diagram, contained in section 5 of the basic Flight Manual, are to be corrected as follows:
O
With dual cargo hook installed:
–
C
Helicopter gross mass below 2600 kg: . . . . . . . . . . . . . . . . . . . . . . . Subtract 15 ft/min
LY
Helicopter gross mass between 2600 kg and below 3200 kg: . . . Subtract 10 ft/min
O N
With mirrors installed:
O N
Helicopter gross mass of 3200 kg and above: . . . . . . . . . . . . . . . . . Subtract 10 ft/min
C
TI
Helicopter gross mass below 2600 kg: . . . . . . . . . . . . . . . . . . . . . . . Subtract 35 ft/min
R
U
Helicopter gross mass between 2600 kg and below 3200 kg: . . . Subtract 25 ft/min
IN
ST
Helicopter gross mass of 3200 kg and above: . . . . . . . . . . . . . . . . . Subtract 20 ft/min
FO
R
For the combined installation of both the dual cargo hook and the mirrors, the reductions sum up: Helicopter gross mass below 2600 kg: . . . . . . . . . . . . . . . . . . . . . . . Subtract 50 ft/min Helicopter gross mass between 2600 kg and below 3200 kg: . . . Subtract 35 ft/min Helicopter gross mass of 3200 kg and above: . . . . . . . . . . . . . . . . . Subtract 30 ft/min
APPROVED Rev. 0
9.2-6 – 25
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
5.4
CARGO HOOK OPERATION REQUIRING OEI PERFORMANCE
5.4.1
Hover OEI performance for HEC operations The hover OEI performance chart for HEC operations requiring OEI performance is based on the hover out of ground effect performance achievable with the OEI 30 sec rating with consideration given to the maximum aircraft height loss of 4 ft after an engine failure and with consideration given to the minimum vertical climb rate required for safe obstacle clearance. The hover performance chart is valid only if used in conjunction with the following emergency procedure: HEC hook operations requiring OEI performance – Single engine failure
ED
N TR
O
LL
HEC CARGO HOOK OEI 30 SEC Wind accountability is UNFACTORED
2000
O
NOTE
T
C
2100
N
O
2200
PY
2300 2400
C
O
MAX. DENSITY ALTITUDE 12000 FT
LY
–
2500
O N
2600
MAX. OAT
O N
2700 2800 2900
R
U
C
TI
MIN. OAT
1900
ST
3000
GROSS MASS – kg
–
IN
3100
FO
R
3200 3300 3400 REFERENCE LINE
–40
–30
Fig. 1
9.2-6 – 26
–20
–10
0
10
20
30
40
50
HEC cargo hook operation OEI 30
60 0
3600 3700
10
20
3800 30 [kt]
BK117D2709_1_r1
GROSS MASS LIMIT 3700 KG –50
3500
0 10 20 30 40 50 60 [km/h] sec HEADWIND
APPROVED Rev. 2
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HEC CARGO HOOK OEI 30 SEC – IBF INSTALLED 1900
Wind accountability is UNFACTORED
NOTE
2000 2100
MAX. DENSITY ALTITUDE 12000 FT
2200 2300
N PY O –
C
3200
O N
LY
3300
0
10
20
30
40
50
60 0
3600 3700
10
20
3800 30 [kt]
BK117D2709_1_IBF_3_r1
–10
3500
REFERENCE LINE
O N
3400
TI –20
GROSS MASS – kg
2900
O
T
C
O
2800
3100
C U FO APPROVED Rev. 2
Fig. 2
–30
2600
3000
GROSS MASS LIMIT 3700 KG
R ST
–40
R
IN
–50
2500
2700
MAX. OAT
MIN. OAT
N TR
O
LL
ED
2400
0 10 20 30 40 50 60 [km/h] HEADWIND
HEC cargo hook operation OEI 30 sec – IBF installed
9.2-6 – 27
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
5.4.2
Obstacle clearance Safe obstacle clearance can be determined in accordance with Fig 3 as follows: Acceleration distance (hover to VTOSS): No obstacles above 5 ft shall be present in the area required for acceleration from hover to VTOSS. Up to 2000 ft DA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 m / 660 ft
–
Above 2000 ft DA and up to 7000 ft: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 300 m / 980 ft
–
Above 7000 ft DA: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 400 m / 1310 ft
O
LL
ED
–
The climb rate and distance covered during the Segment I climb at VTOSS from the 40 ft HEC load height to (at least) 200 ft HEC load height (AGL) can be determined using the Segment I climb rates given in the Cat A flight manual supplement (FMS 9.1–1). If the Segment 1 climb is extended above 200 ft HEC load height (AGL), the maximum Segment 1 distance shall not exceed 6800 ft / 2100 m.
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
–
N TR
Segment 1 distance (VTOSS):
FO
200 ft
40ft Acceleration distance Fig. 3
9.2-6 – 28
Segment I distance
Obstacle clearance during HEC cargo hook operation with OEI performance APPROVED Rev. 3
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5.5
OEI TRAINING Training of the following single engine emergency procedures may be conducted using the procedures detailed in FLM supplement 9.1–3 and: – HEC cargo hook operation requiring OEI performance – Single engine failure The maximum weight of the rotorcraft–load combination to be used for OEI training shall be obtained from the respective charts with IBF INSTALLED (Fig. 2). It is good practice to perform all OEI training with an NHEC load only.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
NOTE
APPROVED Rev. 2
9.2-6 – 29
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6
MASS AND BALANCE
6.1
CARGO HOOK LOADING CHARTS Refer to Equipment List entries in Section 6 of the basic FlightManual. The point of application of the external load in longitudinal direction (X-STA) is: – 4427 mm for single cargo hook operation (hook 1) or for dual cargo hook operation with an asymmetric Y-rope. – 4279 mm for dual cargo hook operation with a symmetric Y-rope.
ED
The point of application of the external load in lateral direction (Y-BL) is 0 mm.
N TR
O
LL
To determine if the helicopter will remain within the longitudinal C.G. limits when a load is picked up, first calculate the helicopter inflight C.G. and gross mass (without consideration of the cargo load). Then select the applicable chart:
O
– NHEC load attached to hook 1 only: Fig. 4
C
– HEC or NHEC load attached to hook 1 and hook 2 with a symmetrical Y-rope: Fig. 5
O
T
– HEC or NHEC load attached to hook 1 and hook 2 with an asymmetrical Y-rope: Fig. 6
O
PY
N
Enter the weight and C.G. in the correct figure and directly read the maximum allowed cargo hook weight.
O N
LY
–
C
To determine if the lateral C.G. will remain within the allowed range, a simplified consideration can be made: if the lateral C.G. is within the range between –80 and +80 mm without consideration of the cargo load, the C.G. will automatically remain within the permissible range after load pick-up.
O N
Example for reading the chart (Fig. 4): Max. permissible NHEC load
Known:
Gross mass C.G.
Solution:
Max. permissible NHEC load = 1110 kg Enter chart (Fig. 4) at known gross mass (2538 kg) and move horizontally right . Enter chart (Fig. 4) at known x-sta (4379) move vertically up . The cross point is the resulting max. NHEC load of 1110 kg.
2538 kg 4379 mm
FO
R
IN
ST
R
U
C
TI
Determine:
Example for reading the chart (Fig. 5): Determine:
Max. permissible HEC load
Known:
Gross mass C.G.
Solution:
Max. permissible HEC load = 490 kg Enter chart (Fig. 5) at known gross mass (2538 kg) and move horizontally right . Enter chart (Fig. 5) at known x-sta (4379) move vertically up . The cross point is the resulting max. HEC load of 490 kg.
9.2-6 – 30
2538 kg 4379 mm
MANUFACTURER’S DATA APPROVED Rev. 0
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3800
A
X–STA – mmGM – kg A 4380 3700 B 4535 3700 C 4700 2000 D 4347 2400 Load on hook1 at: STA=4427mm
B
3600 3400 500 kg (max.)
3000 2800 1000 kg (max.)
2400
D
1400 kg (max.)
N TR
BKD2_FLH_0368_R
2200
LL
ED
2600
O
GROSS MASS – kg
3200
C
C
O
2000 1800 4400
4450
4500
4550
T
4350
O
4300
4600
4650
4700
4750
N
X–STA – mm
PY
Basic C.G. envelope for single cargo hook operation (MTOW=3700kg, load path only to hook 1 (aft))
3800
O N
LY
–
C
O
Fig. 4
A
O N
3600
C
TI
3400
U R ST
3000
IN
800 kg (max.)
R
2600
500 kg (max.)
FO
GROSS MASS – kg
3200
2800
X–STA – mmGM – kg A 4380 3700 B 4535 3700 C 4700 2000 D 4347 2400 Load on hook1 and 2 at: STA=4279mm
B
2400
D
BKD2_FLH_0378_R
2200 2000
C
1800 4300
4350
4400
4450
4500
4550
4600
4650
4700
4750
X–STA – mm
Fig. 5 Basic C.G. envelope for dual cargo hook operation (MTOW=3700kg, symmetric Y-rope: load path to hook 1+2)
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-6 – 31
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3800
A
B
A B C D
3600 3400
3000 800 kg (max.) 2800
ED
2600 2400
LL
GROSS MASS – kg
Load on hook1 and (2) at: STA=4427mm
500 kg (max.)
3200
O
D
N TR
2200
C
C
O
2000
4350
4400
4450
4500
4550
4650
4700
4750
Basic C.G. envelope for dual cargo hook operation (MTOW=3700kg, asymmetric Y-rope: load path to hook 1 and long leg to hook 2)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
Fig. 6
4600
PY
X–STA – mm
O
4300
T
1800
N
BKD2_FLH_0379_R
X–STA – mm GM – kg 4380 3700 4535 3700 4700 2000 4347 2400
9.2-6 – 32
MANUFACTURER’S DATA APPROVED Rev. 0
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7
SYSTEM DESCRIPTION
7.1
EXTERNAL CARGO HOOK ASSY The double cargo hook consists of a retrofitable beam with two identical hooks, attached between the crosstubes of the landing gear. HOOK 1 (main hook) is located towards the rear and HOOK 2 is located towards the front. Each hook can be opened by the normal electrical release (Fig. 12) and by an independent mechanical/hydraulic release (Fig. 10).
LL
ED
The electrical hook release switches for HOOK 1 (main hook) and HOOK 2 are installed on the cyclic stick. The electrical release is only available when the electrical cargo hook release mechanism is armed. To arm the cargo hook, the CARGO HOOK switch in the overhead panel must be set to ARM and the green information message CARGO HOOK (ML) must be displayed.
N
O
T
C
O
N TR
O
A guarded mechanical/hydraulic emergency release for HOOK 1 (main hook) and HOOK 2 is located underneath the collective pitch lever for use in case of malfunction of the electrical release system (Fig. 10 and 11). To release the cargo hooks (with hydraulic support), a lever guard has to be opened before the levers can be pulled. Note that the lever for HOOK 1 is on the right hand side and the lever for HOOK 2 is on the left hand side.
PY
A manual cargo hook release for use by the ground crew to release the external cargo hooks is located at the RH-side on the hooks (Fig. 7).
–
C
O
The cargo hook will be extended from stowed position if a load of app. 5 kg is applied. This will cause the hook to rotate into vertical position and triggers the load switch.
O N
LY
A white advisory indication HOOK UNLOADED (ML) illuminates as long as no load (or a load less than 5 kg) is attached to HOOK 1 (main hook) and HOOK 2. Manual release lever
IN
ST
R
U
C
TI
O N
Cargo hook attachment point
FO
R
Hydraulic release line dry break coupler
Hook locked indicator
Load beam Fig. 7 MANUFACTURER’S DATA APPROVED Rev. 0
Cargo hook – Manual release side
9.2-6 – 33
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Electrical connector
N TR
O
LL
ED
Electrical compartment cover
Cargo hook – Electrical release side
C
O
Fig. 8
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
Hook lock indicator
NOT ACCEPTABLE
R
IN
ACCEPTABLE
FO
LOCK INDICATOR DIAMOND IS ALIGNED WITH ENGRAVED LINES ON THE COVER. Fig. 9
9.2-6 – 34
LOCK INDICATOR DIAMOND IS VISIBLE BUT IS NOT ALIGNED WITH ENGRAVED LINES ON THE COVER.
Cargo hook lock indication
MANUFACTURER’S DATA APPROVED Rev. 0
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–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Mechanical release and safety guard on collective lever
O N
LY
Mechanical/hydraulic emergency release HOOK 1 (main hook)
Mechanical release on collective lever
TI
O N
Fig. 10
Mechanical/hydraulic emergency release HOOK 2
FO
R
IN
ST
R
U
C
Collective lever
Safety guard
Green mark Fig. 11
MANUFACTURER’S DATA APPROVED Rev. 0
Safety guard
9.2-6 – 35
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Electrical release on cyclic stick
Release switch HOOK 1 (main hook) – aft hook
C
CARGO HOOK HELIONIX INDICATIONS
PY
N
O
T
7.2
Electrical release on cyclic stick
O
Fig. 12
N TR
O
LL
ED
Release switch HOOK 2 – fwd hook
NAVD
VMS
DMAP
MISC
+ C T R S –
EFB
O N TI C U
–
TOT
710 N1
B A R
103
2 h 30 min
94.0 %
ENG OIL B A R
ENG OIL B A R
72
72
9.0
FUEL Kg
IN
100
R
FF Kg/h
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47
314
54
30 %
MGB OIL B A R
9.0
N U M
IBF
N1
94.0 %
10 %
HYD
103
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55.0 %
TOT
IBF
B A R
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55.0 %
700
R C N F
30
3.0
G1
B A R 3.0
G2
FF Kg/h
137
D A T A
Textual data area and data area
101. 0
S E L
BKD2_FLH_0469_R
for cargo hook load indication + L U M –
Fig. 13
9.2-6 – 36
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101. 0 % N2 101. 0 % CPL
REPORT
EPC
STATUS
CONF
WEIGHT
+ B R T –
Cargo hook load indication on VMS MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
The following parameters are displayed in the data area (if configured): –
Cargo hook state and weight value (see below, weight unit is configurable, 2kg/4lb resolution see Fig. 14)
The different states are shown in the figure below:
Single/Double cargo hook loaded (in case of double hook: at least one loaded)
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Single/Double cargo hook unloaded(in case of double hook: both unloaded) If the weight signal is invalid, the cargo hook is always shown as unloaded (even if it is loaded).
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Single/Double cargo hook loaded including weight sensing information
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No valid hook information (e.g. due to HELIONIX internal problems) or at least one load/unload information is invalid 300 kg
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Cargo hook indication in the data area of VMD-format
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Fig. 14
MANUFACTURER’S DATA APPROVED Rev. 3
9.2-6 – 37
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
7.3
POWER SUPPLY The external cargo hook assy electrical power is supplied from the shedding bus via circuit breakers LOAD HOOK PWR in the overhead panel and PWR LD HOOK in the additional circuit breaker panel. The external mirror assy electrical power is supplied from the shedding bus via the circuit breaker HOOK MIRROR. Both systems are electrically supplied when cargo switch is in ARM position.
7.4
WEIGHING SYSTEM (OPTIONAL)
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CAUTION D THE WEIGHT UNIT IS ONLY OPERATIONAL ON HOOK 1. FOR DOUBLE HOOK OPERATIONS WITH A SYMMETRIC Y-ROPE, THE WEIGHT INDICATION WILL BE INCORRECT.
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D THE WEIGHT OF THE CARGO HOOK LOAD IS NOT AUTOMATICALLY INCLUDED IN THE TOTAL AIRCRAFT WEIGHT. THE PILOT MUST ENTER THE WEIGHT ON THE CARGO HOOK (INDICATED ON THE MFD), ON THE VMS WEIGHT PAGE AT EACH LOAD PICKUP AND DROP-OFF. FAILURE TO INCLUDE THE CARGO HOOK WEIGHT MAY RESULT IN AN INCORRECT VNE INDICATION.
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D In case of attached external loads less than 200 kg, the tolerance of the weighing system may possibly exceed $ 40 kg.
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The weight measuring system consists of the following main parts:
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– Load measurement pin
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– Electronic box
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For the weight measurement the load measurement pin is installed in HOOK 1. An electronic box – which processes the weight information for indication on the MFDs – is installed in the beam body on the LH side closed to the HOOK 1 (see Fig. 15 )
9.2-6 – 38
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
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Flight direction
Weighing system – typical installation
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Fig. 15
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Installation weighing system
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-6 – 39
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
7.5
CARGO HOOK MIRROR (OPTIONAL) The cargo hook mirror assy is attached to the fuselage in front of the lower right-hand nose area by means of a quickly removable four-strut construction (Fig. 16). Two external mirrors are provided: An electrically adjustable mirror with an integrated heating and a fixed mirror. Two electrically driven actuators are installed in the adjustable mirror housing to provide fully cardanic inflight adjustment by means of a 4-way toggle switch, located on the collective lever. The cargo hook mirror assy receives power from the No. 1 shedding bus via the LOAD HOOK MIR circuit breaker, located on the overhead panel.
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The 4-way toggle switch, having switch positions FWD, AFT, L and R, can be used for orientation control of the adjustable mirror if selected by the 3-position switch HISL-MIR-S/L LT (Fig. 17).
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An electrically operated mirror heating is provided within the adjustable mirror for inflight de-icing and de-misting. The heating is automatically controlled by a temperature sensor located within the mirror housing.
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Normally, the fixed mirror is adjusted so that the pilot has a permanent view of the cargo hook. This enables the pilot to check visually that the load is correctly latched or released.
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The adjustable mirror is normally adjusted so that the external load can be observed. Especially in forward flight, this allows the pilot to check for possible load oscillations or excessive rotations.
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1 Electrically adjustable mirror 2 Fixed mirror
2
Fig. 16
9.2-6 – 40
Cargo hook mirror assy – typical installation MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
1
CABLE CUT
S/L LT M I R HISL
DIM/FOC
L D G L T
S/L LT ON
OFF
STOW
2
BAMBI IR/ VIS DUMP
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BEEP TRIMORIENT CTL
Mirror controls on collective lever – typical installation
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Fig. 17
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SWITCH
S/L LT/MIR/HISL (3-way toggle switch)
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ORIENT CTL/IR/VIS (4-way toggle switch with push function)
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MANUFACTURER’S DATA APPROVED Rev. 0
9.2-6 – 41
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
8
HANDLING, SERVICING, AND MAINTENANCE
8.1
ATTACHMENT OF THE EXTERNAL CARGO HOOK ASSY
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The external cargo hook assy is attached to the forward crosstube via one fixed clamp and to the aft crosstube via two fixed clamps. The retrofitable beam is attached to each clamp with quick release pins.
Fig. 18
External cargo hook beam
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Flight direction
9.2-6 – 42
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
8.2
CARGO HOOK LOADING
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Cargo hook rigging – recommended
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Fig. 19
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The cargo hook can easily be loaded with one hand. A load is attached to the hook by pushing the ring upward against the upper portion of the load beam throat (see Fig. 19) until an internal latch engages the load beam and latches it in the closed position.
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In order to allow a clean separation of the rigging devices attached to the cargo hook, the following dimensions are recommended to avoid damaging the beam body:
Fig. 20
Cargo hook rigging dimensions
Rigid steel load rings are recommended to provide consistent release performance and resistance to fouling. MANUFACTURER’S DATA APPROVED Rev. 0
9.2-6 – 43
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
8.2.1
Y–Rope Asymmetric Y-Rope: If Y-rope with different leg lengths is used, the short leg must be attached to hook 1 (normal load path) and the long leg must be attached to hook 2 (back–up load path). The rope leg attached to hook 2 must have a damper or damping properties. Symmetric Y-Rope: Use of a symmetric Y–Rope is not recommended. The symmetric Y–Rope is incompatible with the weighing unit. Usage data gathered through the weighing unit will therefore be inaccurate if a symmetric Y–Rope is used. Sling load rope swivel
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8.2.2
Additional rigging information
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Many loads have a tendency to rotate. To avoid torque on the cable/rope due to rotation of the external load, a swivel between the load and load attachment is recommended.
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CAUTION D MULTIPLE LOAD RINGS, NYLON TYPE STRAPS (OR SIMILAR MATERIAL) OR ROPE MUST NOT BE USED DIRECTLY ON THE CARGO HOOK LOAD BEAM. IF THIN NYLON STRAPS OR THIN ROPE ARE USED THEY SHOULD BE FIRST ATTACHED TO A STEEL PRIMARY RING. VERIFY THAT THE RING WILL FREELY SLIDE OFF THE LOAD BEAM WHEN IT IS OPENED. ONLY THE PRIMARY RING SHOULD BE IN CONTACT WITH THE CARGO HOOK LOAD BEAM.
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D SOME COMBINATIONS OF SMALL PRIMARY RINGS/SHACKLES AND LARGE SECONDARY RINGS/SHACKLES COULD CAUSE FOULING/JAMMING DURING RELEASE.
9.2-6 – 44
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL EXTERNAL CARGO HOOK AND/OR EXTERNAL MIRROR
Avoid!!!
–
Recommended cargo hook rigging – example
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Fig. 21
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Recommended
Fig. 22
MANUFACTURER’S DATA APPROVED Rev. 2
Jamming
9.2-6 – 45/(9.2-6 – 46 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
F M S 9.2-7
SUPPLEMENT FOR
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SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
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System/Equipment Designation
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This supplement shall be attached to the BK117 D-2 Flight Manual (Section 9.2) when the sling type cargo hook (keeperless) and/or external mirror are installed.
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Sling type cargo hook (keeperless)
All All
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External mirror
Effectivity
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-7 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA ref. EASA.21J.700, “DOA”.
App.
Page
9.2-7 -7
2
EASA
9.2-7 -13
9.2-7 -2
2.1
9.2-7 -3
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9.2-7 -8
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EASA
2
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9.2-7 -9
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9.2-7 -4
2.1
DOA
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LEP – approved (part 1):
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LOG OF REVISION
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(see page 9.2-7-1)
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FIRST ISSUE
DEC 18, 2017
REVISION 2 EASA approval no.: 10067961
DEC 12, 2018
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REVISION 1 EASA approval no.: 10064108
REVISION
2.1
(see entry below)
Date: NOV 20, 2019
Revision 2.1 is approved under the authority of the DOA ref. EASA.21J.700
9.2-7 – 2
APPROVED Rev. 2.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
TABLE OF CONTENTS
Page GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 5
2
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 5
2.1 2.2 2.3 2.4 2.5 2.6 2.7 2.8 2.9 2.10 2.11 2.12 2.13
TYPE OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OCCUPANTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MASS AND LOAD LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CENTER OF GRAVITIY LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . AIRSPEED LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BANK ANGLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTERNAL LOAD OPERATIONAL LIMITATIONS . . . . . . . . . . . . . . . . . . OTHER LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NIGHT OPERATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMBATIBILITY WITH OTHER OPTIONAL EQUIPMENT . . . . . . . . . . . LOAD ATTACHING MEANS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMMUNICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PLACARDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
EMERGENCY AND MALFUNCTION PROCEDURES . . . . . . . . . . . . . 9.2-7 – 10
3.1 3.2 3.2.1 3.3
EXTERNAL LOAD JETTISONING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGINE FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SINGLE ENGINE FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MASTER LIST INDICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 12
4.1 4.2 4.2.1 4.2.2 4.3
9.2-7 – 5 9.2-7 – 5 9.2-7 – 5 9.2-7 – 5 9.2-7 – 6 9.2-7 – 6 9.2-7 – 7 9.2-7 – 8 9.2-7 – 8 9.2-7 – 8 9.2-7 – 8 9.2-7 – 8 9.2-7 – 8
9.2-7 – 10 9.2-7 – 10 9.2-7 – 10 9.2-7 – 10
PREFLIGHT CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Load attachment and lifting the load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Setting down the load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RECORDING EXTERNAL CARGO HOOK OPERATIONS . . . . . . . . . .
5
PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 16
5.1 5.2 5.3 5.4
OPERATION WITH CARGO HOOK IN STOWED POSITION . . . . . . . CARGO HOOK OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . WIND INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AEO and OEI maximum rate of climb . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6
MASS AND BALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 17
6.1
CENTER OF GRAVITY LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 17
7
SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 18
7.1
CARGO HOOK ASSEMBLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 18
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APPROVED Rev. 2
9.2-7 – 12 9.2-7 – 13 9.2-7 – 13 9.2-7 – 14 9.2-7 – 15 9.2-7 – 16 9.2-7 – 16 9.2-7 – 16 9.2-7 – 16
9.2-7 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
7.2
CARGO HOOK HELIONIX INDICATIONS . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 21
7.2
WEIGHING SYSTEM (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 22
7.3
CARGO HOOK MIRROR (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 24
7.4
BAMBI BUCKET (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 25
LIST OF FIGURES
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Fig. 1 Basic C.G. envelope for single cargo hook operation . . . . . . . . . . . . . . . . 9.2-7 – 18
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Fig. 2 Cargo hook assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 19
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Fig. 3 Cargo hook . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 19 Fig. 4 Cargo hook controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 20
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Fig. 5 Cargo hook load indication on VMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 22
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Fig. 6 Cargo hook indication in the data area of VMD-format . . . . . . . . . . . . . . 9.2-7 – 23
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Fig. 7 Weighing systemWeighing system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-7 – 23
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Fig. 9 Bambi bucket control switches – typical installation . . . . . . . . . . . . . . . . . 9.2-7 – 25
9.2-7 – 4
APPROVED Rev. 2.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
1
GENERAL The cargo hook assembly is provided for transportation of non-human external cargo.
2
LIMITATIONS
2.1
TYPE OF OPERATION
ED
The information contained herein supplements the information in the basic Flight Manual. For limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
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Operations with a load attached to the external cargo hook shall be conducted in accordance with the appropriate operating rules for external loads. Operation of the helicopter with cargo suspended from the hook is approved for the lifting of loads free of land or water under VFR (day/night incl. NVIS). The load jettisoning system (i.e. electrical and mechanical/hydraulic release) must be installed and operational. Towing of loads on land or water is prohibited. Immersion of a cable/rope attached to the cargo hook into water for the purpose of picking up loads is permissible within the hover speed range if obstacle clearance is ensured.
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The sling type cargo hook is approved for Non-Human External Cargo (NHEC) only. Operations with a person(s) suspended from the hook are prohibited.
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Operation of the helicopter with no load suspended from the external cargo hook is permitted. The basic flight manual limitations apply.
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Category A VTOL takeoff and landing with the cargo hook mirror installed in front of the pilot flying is prohibited.
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The minimum flight crew for operation of the external cargo hook consists of one pilot on the right seat.
2.3
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If a load observer is carried on board, the observer must be secured to the attachment point in the helicopter with an approved PCDS (Personal-Carrying Device System).
MASS AND LOAD LIMITS Maximum combined gross mass (Helicopter plus jettisonable external load): . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3700kg
Maximum external load mass: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1500kg 2.4
CENTER OF GRAVITY LIMITATIONS During cargo hook operations, the CG envelope of the basic helicopter applies. The load charts given in Para 6.1 of this supplement may be used to determine compliance with this limitation.
APPROVED Rev. 1
9.2-7 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
2.5
AIRSPEED LIMITATIONS WARNING
THE MAXIMUM SPEED WITH SUSPENDED EXTERNAL LOAD MAY BE LIMITED BY FACTORS OTHER THAN VNE SUCH AS AERODYNAMIC DRAG, TENDENCY FOR OSCILLATIONS, ETC. THE MAXIMUM AIRSPEED SHALL NOT EXCEED THE AIRSPEED THAT IS SAFELY ACHIEVABLE WITH MAXIMUM 1000 FT/MIN RATE OF DESCENT.
ED
VNE with external cargo operations is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100 kt
LL
Max operating speed without load on the hook (hook stowed): . . . . . . . . . . VNE basic H/C
For maximum airspeed during operation with open/removed doors refer to the respective FMS 9.1–2.
O
BANK ANGLE
N
2.6
T
C
O
NOTE
N TR
O
Max operating speed without load on the hook (hook unstowed): . . . . . . . . . . . . . . . . 70 kt
PY
The max. bank angle during loaded cargo hook operation is :
C
O
Below 50 KIAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . $ 20_.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
At or above 50 KIAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . $ 30_.
9.2-7 – 6
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
2.7
EXTERNAL LOAD OPERATIONAL LIMITATIONS WARNING D HELICOPTER HANDLING CHARACTERISTICS MAY BE AFFECTED BY THE SIZE, MASS, AND SHAPE OF THE EXTERNAL LOAD BEING CARRIED. IN PARTICULAR, LOADS OF RELATIVELY LOW MASS GENERATING SIGNIFICANT AERODYNAMIC REACTIONS ON ACCOUNT OF THEIR SIZE AND/OR SHAPE MAY BECOME UNSTABLE.
LL
ED
D ANY UNSTABLE LOAD MAY JUMP, OSCILLATE OR ROTATE RESULTING IN LOSS OF CONTROL, UNDUE STRESS ON AND/OR CONTACT WITH THE HELICOPTER CAUSING POSSIBLE CATASTROPHIC RESULTS.
T
C
O
N TR
O
D THEREFORE, EACH OPERATOR SHALL ESTABLISH ADEQUATE OPERATIONAL LIMITS AND PROCEDURES THAT PRECLUDE THE POSSIBILITY OF LOSING CONTROL OR OF THE LOAD CONTACTING THE HELICOPTER.
O
PY
N
O
D OPERATIONAL LIMITATIONS AND PROCEDURES SHALL BE ESTABLISHED TO PROVIDE THE PILOT WITH ADEQUATE MEANS OF CONTINUOUSLY MONITORING THE LOAD DURING FLIGHT.
TI
O N
O N
LY
–
C
D OPERATIONS WITH AN UNBALASTED SLING OR LIGHT WEIGHT CARGO (E.G. EMPTY BASKET) CAN BE EXTREMELY DANGEROUS, ESPECIALLY IN FORWARD FLIGHT WHERE THE LOAD IS DRAGGED BEHIND THE HELICOPTER AND CAN CONTACT THE HELICOPTER. WHEN HANDLING SUCH LOADS, CAUTION SHALL BE USED AND SPECIAL OPERATIONAL LIMITS SHALL BE ESTABLISHED.
FO
R
IN
ST
R
U
C
CAUTION D IN SOME CASES, THE EXTERNAL LOAD MAY INTERACT WITH THE AUTOPILOT BASIC MODE (ATTITUDE MODE). THIS CAN RESULT IN NOTICEABLE VERTICAL BOUNCING. IN THIS CASE, THE A.TRIM SHALL BE DISENGAGED AND FLIGHT SHALL BE CONTINUED IN DSAS MODE. Use of autopilot upper modes with load attached is prohibited. For operations requiring on-board visual monitoring of the load, one of the following means can be used: –
External mirror;
–
Camera system displayed on MFD 4 which allows monitoring of the cargo hook load and cable/rope.
–
Load observer in the cabin or standing on the skids, with cabin sliding door opened and locked. For flight with open doors, a certified locking device for the sliding door must be installed.
APPROVED Rev. 2
9.2-7 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
2.8
OTHER LIMITATIONS CAUTION
2.9
RUNNING LANDINGS WITH THE HOOK UNSTOWED SHALL BE AVOIDED.
NIGHT OPERATIONS For night operation with the Fixed Landing Light (cross tube) and/or the Search and Landing Light (right side installation) in use, the cargo hook mirrors must be covered or removed. COMPATIBILITY WITH OTHER OPTIONAL EQUIPMENT
ED
2.10
N TR
O
LL
The protective capability of the Wire Strike Protection System is significantly degraded in combination with the external mirror assy.
C
LOAD ATTACHING MEANS
T
2.11
O
The sling type cargo hook is not compatible with the dual beam cargo hook.
PY
N
O
The load shall only be attached to the hook using an appropriate load attachment means capable of safely carrying the load and unable to jam.
2.12
O N
LY
–
C
O
Some combinations of small primary rings and large secondary rings could cause fouling during release. It is the responsibility of the operator to assure the cargo hook will function properly with each rigging. COMMUNICATION
U
PLACARDS
IN
FO
R
Placard:
ST
R
2.13
C
TI
O N
If a load observer is carried on board, intercommunication shall be maintained between the pilot(s) and the operator. The operator shall use the WINCH intercom connector.
Location: Near cargo hook Placard:
Location: On collective lever
9.2-7 – 8
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
Placard:
O
LL
ED
Location: Cockpit
O N
O N
Location: Near cargo hook
LY
–
C
O
PY
N
O
T
C
O
N TR
Placard:
R
IN
ST
R
U
C
TI
Placard:
FO
Location: Cargo hook stowage bracket on LH fuselage side.
APPROVED Rev. 0
9.2-7 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
3
EMERGENCY AND MALFUNCTION PROCEDURES In case of malfunction of the electrical release mechanism, the external load may be released via the backup release system (mechanical/hydraulic). A mechanical/hydraulic release is mounted on the pilot’s collective lever. If one engine fails, the external load may have to be jettisoned (see diagrams for single-engine operation, Section 5 of basic Flight Manual). EXTERNAL LOAD JETTISONING
LL
ED
3.1
N TR
O
Condition/Indications
C
O
Certain helicopter inflight emergencies (e.g. single-engine failure or loss of power) may dictate jettisoning of the external load.
O
T
Procedure
– Press
PY
N
1. CARGO REL pb
O
if unsuccessful:
–
C
2. Safety guard (on collective)
– Pull – Check
HOOK UNLOADED
O N
Additionally confirm the load is released (mirror/load observer)
C
TI
NOTE
O N
LY
3. Mechanical/hydraulic release lever
– Push down
ENGINE FAILURE
3.2.1
Single engine failure
IN
ST
R
U
3.2
FO
R
This procedure shall be used if load is attached to the hook and the required OEI hover capability is not given. Procedure 1. Single engine failure procedure
– Perform in accordance with basic flight manual
When necessary to safely complete the procedure: 2. External load jettisoning procedure (see para 3.1)
9.2-7 – 10
– Perform
APPROVED Rev. 2
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3.3
MASTER LIST INDICATIONS
CARGO HOOK OFF
ED
Conditions/Indications
O
LL
– Cargo hook is switched off (i.e. electrical load jettisoning is inoperative), although a weight on the hook is detected.
N TR
Procedure
– ARM
O
1. CARGO HOOK sw (overhead panel)
CARGO HOOK
N
PY
All
O N
O N
LY
–
EFFECTIVITY
This caution may appear temporarily during the start-up procedure.
O
NOTE
Before SB MBB–BK117 D–2–42–003 (Helionix Maintenance Release 1)
C
EFFECTIVITY
O
T
C
– Check
ST
R
U
C
TI
HOOK UNLOADED
IN
Conditions/Indications
R
– The cargo hook is unloaded.
FO
Procedure 1. Cargo hook
APPROVED Rev. 2
– Visually check that hook is unloaded (use mirror, camera or load observer)
9.2-7 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
NORMAL PROCEDURES WARNING
PREFLIGHT CHECK NOTE
For further details refer to Onboard Systems CMM 120–217–00.
Cargo hook, cables and attachments mechanical/hydraulic
release
– Connected, function
secured
O
Electrical and mechanism
– Condition, secured
ED
4.1
WRONG INSTALLATION AND WRONG SECURING OF THE EXTERNAL CARGO HOOK ATTACHMENTS CAN CAUSE UNRECOVERABLE LOSS OF CONTROLLABILITY OR LOSS OF THE LOAD WHEN AN ATTACHMENT UNLOCKS IN FLIGHT.
LL
4
– Press, monitor sequence
self
test
O
N TR
TEST push button on weight indicator (if weighing system installed)
and
T
C
Cargo hook electrical release
– ARM
O
CARGO HOOK sw (overhead panel)
– Check
PY
N
CARGO HOOK
O N
O N
LY
–
C
O
Hook
– Attach load or pull the hook – Check HOOK UNLOADED goes off – Press HOOK 1 on cyclic – Check hook open – Check
HOOK UNLOADED
TI
Cargo hook mechanical/hydraulic release
IN
FO
R
Hook
ST
R
U
C
Oil reservoir (on collective lever)
– Check oil level (between max/ min range) – No leakage – Attach load or pull the hook – Open lever guard on collective lever – Pull lever HOOK – Check green mark is visible while firmly pulling lever (refer to para 7.1) – Check hook open
Hook
– Close and check locked
CARGO HOOK sw (overhead panel)
– OFF – Check goes off
Cargo hook
9.2-7 – 12
CARGO HOOK
– Safely stow under fuselage APPROVED Rev. 0
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4.2
OPERATION WARNING D DURING FLIGHT, A STATIC ELECTRICITY CHARGE ACCUMULATES IN THE HELICOPTER. TO AVOID INJURY TO GROUND PERSONNEL, THE LOAD AND/OR HELICOPTER SHALL BE DISCHARGED BY ALLOWING THE LOAD AND/OR HELICOPTER TO TOUCH WATER OR GROUND BEFORE IT IS TOUCHED BY GROUND PERSONNEL.
LL
ED
D WHEN FLYING AT LOW HEIGHT, THE PILOT SHALL CONSIDER THE CABLE LENGTH TO DETERMINE THE MINIMUM SAFE HEIGHT. IT IS GOOD PRACTISE TO ADUST THE DECISION HEIGHT TO THE LENGTH OF THE CABLE PLUS SAFETY MARGIN.
N TR
O
CAUTION D SHOCK LOADS, JERKS AND SNAPS DURING CARGO HOOK OPERATION SHALL BE AVOIDED.
Load attachment and lifting the load
–
4.2.1
C
O
PY
N
O
T
C
O
D THE CARGO HOOK ELECTRICAL RELEASE SOLENOID IS INTENDED TO BE ENERGIZED ONLY INTERMITTENTLY. ACTUATING THE ELECTRICAL RELEASE SWITCH CONTINUOUSLY IN EXCESS OF 20 SECONDS WILL CAUSE THE SOLENOID TO OVERHEAT, POSSIBLY CAUSING PERMANENT DAMAGE.
O N
LY
The cargo hook can be controlled/operated by the pilot or by the ground crew. Procedure
C
TI
O N
1. CARGO HOOK sw (overhead panel)
– Check
CARGO HOOK
– Establish
IN
ST
R
U
2. Helicopter on ground or in hover at sufficient height to allow ground crew to attach cargo sling to the hook.
– ARM
FO
R
CAUTION
DO NOT PASS THE LOAD ATTACHMENT CABLES OVER THE LANDING GEAR SKID TUBE WHEN ATTACHING THE LOAD WHEN THE HELICOPTER IS ON THE GROUND.
3. Hook lock indicator CAUTION
– Check fully locked position
GROUND PERSONNEL MUST MAKE SURE LOAD HOOK IS LATCHED AFTER LOAD IS APPLIED.
4. External mirror or load observer
– Check load attached
5. To lift cargo from surface
– Climb slowly vertically
6.
– Check HOOK UNLOADED goes off
APPROVED Rev. 2
HOOK UNLOADED
9.2-7 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
7. While lifting load and hovering
– Check power is within limits (on FLI.) If too high set down the load. – Note position of “blue line” – Check for satisfactory controllability and adequate directional control
O
LL
Setting down the load
– Gradually reduce speed to arrive in hover with the load approximately 10 ft above the ground.
2. To settle load
– Descend vertically touches surface
N TR
1. Landing approach
until
load
N
O
T
C
O
4.2.2
– Perform
ED
8. Enter into slow speed forward flight and determine that no excessive oscillations occur
O
PY
– Check load is safe on ground – Press – Check
HOOK UNLOADED
LY
–
C
3. HOOK
O N
O N
NOTE D To avoid damage to the load, it may be necessary to descend and reposition slightly before releasing the cargo hook cable.
ST
R
U
C
TI
D In some cases (e.g. Bambi Bucket), it may be necessary to land without releasing the load. In this case, the pilot can move forward or rearward carefully and land with the load attached. – Confirm visually operator)
(mirror/load
R
IN
4. Load release
FO
If load is not released: 5. Safety guard on collective
– Push down
6. Mechanical lever
– Pull
7. Load release
– Confirm visually operator)
9.2-7 – 14
(mirror/load
APPROVED Rev. 0
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4.3
RECORDING EXTERNAL CARGO HOOK OPERATIONS In order to comply with airworthiness and maintenance requirements, the following information has to be recorded in a manner which allows for subsequent monitoring of the achieved average numbers of the various cargo hook operation cycles in relation to external cargo flight hours: The number of load pick ups, duration and load mass of external cargo flights. – An external cargo flight is defined as a flight whereby an external load is attached at least once. – A load pickup is defined as the lifting of more than 300 kg. Each time the load weight is below 300 kg and is loaded again above 300 kg (e.g. placing down a load and picking it up again or emptying and refilling a bambi bucket), a new load pickup needs to be counted.
–
The load mass is defined as the mass which acts on the cargo hook just after picking up the load in hover.
–
Duration of external load operations should be interpreted to be: – anything is attached to the cargo hook (whether or not a useful load is being transported) and – the aircraft is flying. If these conditions are not met, time does not need to be tracked.
O
PY
N
O
T
C
O
N TR
O
LL
ED
–
Observe limitations concerning total numbers, load mass and duration of cargo hook operation, as stated in the Maintenance Manual.
FO
R
IN
ST
R
U
C
TI
O N
NOTE
O N
LY
–
C
If the weighing system is installed, report any load release in flight > 400 kg (i.e. all load releases where the load was not in full contact with the ground before opening the hook). Maintenance of the weighing system is required.
APPROVED Rev. 0
9.2-7 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
5
PERFORMANCE DATA
5.1
OPERATION WITH CARGO HOOK IN STOWED POSITION For flights with the cargo hook in the stowed position at the rear LH side of the fuselage the performance data given in Section 5 of the basic Flight Manual remain unchanged.
5.2
CARGO HOOK OPERATION
N TR
C
WIND INFORMATION
T
5.3
Climb performances are slightly reduced due to aerodynamic drag when carrying an external load, depending on size and shape of the load.
O
NOTE
O
LL
ED
When determining climb and hover performances using the graphs in section 5 (of basic Flight Manual), any takeoff gross mass used to select the appropriate climb chart – or obtained from the hover ceiling chart – is to be considered as combined takeoff gross mass for the helicopter-load combination.
O
AEO AND OEI MAXIMUM RATE OF CLIMB
–
5.4
No change to the basic Flight Manual data.
C
–
PY
N
O
Loaded cargo hook operations have been demonstrated with a compact heavy load under the following wind conditions:
O N
LY
All results obtained from the respective diagram, contained in section 5 of the basic Flight Manual, are to be corrected as follows:
O N
Cargo hook mirror assembly with and without sling type cargo hook:
C
TI
Helicopter gross mass below 2600 kg: . . . . . . . . . . . . . . . . . . . . . . . . Subtract 35 ft/min
R
U
Helicopter gross mass between 2600 kg and below 3200 kg: . . . . . Subtract 25 ft/min
FO
R
IN
ST
Helicopter gross mass of 3200 kg and above: . . . . . . . . . . . . . . . . . . Subtract 20 ft/min
9.2-7 – 16
APPROVED Rev. 0
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6
MASS AND BALANCE Refer to Equipment List entries in Section 6 of the basic Flight Manual.
6.1
CENTER OF GRAVITY LIMITATIONS During cargo hook operations, the C.G. envelope of the basic helicopter applies. The load charts given in Para 6.1 of this supplement may be used to determine compliance with this limitation.
LL
ED
The permissible over-all C.G. envelope of the helicopter before load pick-up depending on the external load mass is shown in Figure 1.
N TR
O
The point of application of the external load in lateral direction (Y-BL) is 0 mm.
O
T
C
O
The helicopter gross mass used in the example below comprises basic helicopter gross mass as well as mission equipment, crew, other persons and fuel on board.
(see Figure 1)
Determine:
Maximum external load mass
Known:
H/C gross mass
LY
O N
C.G.
2700 kg 4380 mm
Maximum external load mass = 1000 kg
O N
Solution:
–
C
O
PY
N
EXAMPLE:
U
C
TI
1. Enter chart at known H/C gross mass (2700 kg) and move horizontally right.
R
2. Enter chart at known x-sta (4380) and move vertically up.
FO
R
IN
ST
3. The cross point is the resulting max. load of 1000 kg.
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-7 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
3800
A
B
X–STA – mm GM – kg A 4380 3700 B 4535 3700 C 4700 2000 D 4347 2400
3600 3400
3000 2800
1000 kg (max.)
1500 kg (max.)
2200
O
2000
O
D
C
C
4350
4400
4450
4500
4550
4600
4650
4700
4750
O
PY
X–STA – mm
N
4300
O
T
1800
BKD2_FLH_0386_R
2400
LL
ED
2600
N TR
GROSS MASS – kg
Hook at: STA=4385mm
500 kg (max.)
3200
7.1
CARGO HOOK ASSEMBLY
O N
SYSTEM DESCRIPTION
TI
O N
7
LY
–
C
Fig. 1 Basic C.G. envelope for single cargo hook operation
IN
ST
R
U
C
The cargo hook is attached by means of four cables on the cross tubes next to the connecting points to the airframe. The electrical hook release is operated by a guarded pushbutton labelled CARGO REL on the pilot’s (and copilot’s) cyclic stick grip.
FO
R
A mechanical/hydraulic release is mounted on the pilot’s collective lever; it is provided for use in the case of a malfunction of electrical release system. A white advisory indication HOOK UNLOADED (ML) illuminates as long as no load (or a load less than 7 kg) is attached to the HOOK. If the cargo hook is not in use, it can be stowed by attaching it to a bracket mounted under the fuselage rear LH side.
9.2-7 – 18
MANUFACTURER’S DATA APPROVED Rev. 0
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O
T
C
O
N TR
O
LL
ED
SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
Fig. 2 Cargo hook assembly
Flight direction
Fig. 3 Cargo hook MANUFACTURER’S DATA APPROVED Rev. 0
9.2-7 – 19
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BKD2_FLH_0387_R
BKD2_FLH_0388_R
SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
2
SYS1
EXT
SYS2
BATT MSTR
OFF
EXT/ WARN
1
HYD OFF
OFF
FIRE TEST
OFF
ARM
CC TEST
CARGO HOOK
TEST
ON
EMER FLOATS
FUZZ BURN
T
HOIST CBL CUT
C
A R M
O N
N
O
OFF
ON
3
2
O
ENGAGE
3
OFF N O R M
O N
N TR
OFF
O
LL
ED
1
1
LAVCS
2
C –
O N
LY
1 Mechanical/hydraulic release lever 2 Electrical release pushbutton 3 Cargo hook electrical system ARM switch
O
PY
COPILOT PILOT PT/STATIC HTG
CLOSE O P E N NORM
FO
R
IN
ST
R
U
C
TI
O N
Fig. 4 Cargo hook controls
9.2-7 – 20
MANUFACTURER’S DATA APPROVED Rev. 0
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7.2
CARGO HOOK HELIONIX INDICATIONS
FND
NAVD
VMS
DMAP
TRQ
S Y S T
MISC
TRQ
55.0 %
55.0 %
TOT
TOT
700
710 94.0 %
10 %
103
B A R
72
103
2 h 30 min
94.0 %
ENG OIL B A R
ENG OIL B A R
9.0
72
FUEL Kg
9.0
3.0
G1
3.0 G2
314
54
FF Kg/h
PY
N
137
O
101. 0
101. 0 % N2 101. 0 %
LY
O N
+ L U M –
CPL
REPORT
EPC
STATUS
CONF
WEIGHT
+ B R T –
Fig. 5 Cargo hook load indication on VMS
R
U
C
TI
O N
BKD2_FLH_0469_R
–
for cargo hook load indication
30
C
S E L
47
T
137
O
FF Kg/h
Textual data area and data area
B A R
C
O
100
D A T A
30 %
MGB OIL B A R
O
B A R
HYD
N U M
IBF
N1
ED
N1
LL
IBF
N TR
R C N F
+ C T R S –
EFB
Cargo hook status (see Fig. 6)
FO
R
–
IN
ST
The following parameter is displayed in the data area (if configured):
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-7 – 21
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Cargo hook loaded
–
Cargo hook unloaded
–
No valid hook information (e.g. due to HELIONIX internal problems) or at least one load/unload information is invalid
O
N TR
O
LL
ED
–
PY
N
O
T
C
Fig. 6 Cargo hook indication in the data area of VMD-format
C
WEIGHING SYSTEM (OPTIONAL)
LY
–
7.3
O
300 kg
O N
For further details refer to Onboard Systems owner’s manual120–039–00.
ST
R
U
C
TI
O N
The weighing system can be attached to the cargo hook assembly to provide external cargo weight information to the pilot during cargo hook operation. The weighing system consists of a weight sensor installed on the cargo hook and a weight indicator mounted at the pilot’s door lower frame. System operation is possible when CARGO HOOK switch is set to ARM.
FO
R
IN
The weight indicator displays the weight on the cargo hook. The ZERO pushbutton allows the pilot to zero the indicator reading, e.g. to eliminate the weight of a cargo net or long line. The zeroed number is stored in memory. The UN-ZERO pushbutton is used to add the zeroed value back into the current indicator reading.
9.2-7 – 22
MANUFACTURER’S DATA APPROVED Rev. 0
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O
LL
ED
1
2
N TR
Hook Load
T O N PY O C –
Weight sensor Digital weight indication ZERO pushbutton UN–ZERO pushbutton
Ø LB KG
UN–ZERO
SETUP
ZERO
4
3
Weight indicator
Fig. 7 Weighing system
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1 2 3 4
CAL DAMP
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Flight direction
EC145_FLH_0190_R
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x 10
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-7 – 23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
7.4
CARGO HOOK MIRROR (OPTIONAL) The cargo hook mirror assy is attached to the fuselage in front of the lower right-hand nose area by means of a quickly removable four-strut construction (Fig. 8). Two external mirrors are provided: An electrically adjustable mirror with an integrated heating and a fixed mirror. Two electrically driven actuators are installed in the adjustable mirror housing to provide fully cardanic inflight adjustment by means of a 4-way toggle switch, located on the collective lever.
ED
The cargo hook mirror assy receives power from the No. 1 shedding bus via the LOAD HOOK MIR circuit breaker, located on the overhead panel.
N TR
O
LL
The 4-way toggle switch, having switch positions FWD, AFT, L and R, can be used for orientation control of the adjustable mirror if selected by the 3-position switch HISL-MIR-S/L LT (Fig. 17).
O
T
C
O
An electrically operated mirror heating is provided within the adjustable mirror for inflight de-icing and de-misting. The heating is automatically controlled by a temperature sensor located within the mirror housing.
O
PY
N
Normally, the fixed mirror is adjusted so that the pilot has a permanent view of the cargo hook. This enables the pilot to check visually that the load is correctly latched or released.
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–
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The adjustable mirror is normally adjusted so that the external load can be observed. Especially in forward flight, this allows the pilot to check for possible load oscillations or excessive rotations.
1
1 Electrically adjustable mirror 2 Fixed mirror
2
Fig. 8 Cargo hook mirror assy – typical installation
9.2-7 – 24
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLING TYPE CARGO HOOK AND/OR EXTERNAL MIRROR
7.5
BAMBI BUCKET MAX (OPTIONAL) The bambi bucket dump release is operated by a pushbutton labelled BAMBI DUMP on the collective lever and/or on the operator’s control pendant (if installed). The system receives power from the No. 1 shedding bus via the BAMBI BUCKET circuit breaker and a BAMBI BUCKET OFF–ARM switch located on the overhead panel .
S/L LT ON
O
CUT
L D G L T
C
CABLE
DIM/FOC
S/L LT M I R HISL
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O
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ED
After pressing the BAMBI DUMP pushbutton the water is dumped from the bucket. To stop the water flow at any moment during dumping, push the BAMBI DUMP pushbutton again. This can be repeated several times until the bucket is empty. The weight of the water inside the bucket will cause the fabric dump valve to turn inside-out through the bottom of the bucket, thereby giving obstruction-free passage to the escaping water.
OFF
STOW
T
2
N
1
O
BAMBI
DUMP
PY
IR/ VIS
OFF
ARM
BAMBI BUCKET
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R
BKD2_FLH_0014_R
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O N
O N
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–
C
O
BEEP TRIMORIENT CTL
Fig. 9 Bambi bucket control switches – typical installation SWITCH 1
BAMBI DUMP sw (collective)
2
BAMBI BUCKET OFF–ARM sw (OVHP)
MANUFACTURER’S DATA APPROVED Rev. 2.1
9.2-7 – 25/(9.2-7 – 26 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
FMS
9.2-8
SUPPLEMENT FOR
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WEATHER RADAR SYSTEM RDR 2000
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System/Equipment Designation
PY
N
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This supplement shall be attached to the BK 117 D-2 Flight Manual (Section 9.2) when the WEATHER RADAR SYSTEM RDR 2000 is installed.
All
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–
Weather radar system RDR-2000
Effectivity
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971
APPROVED Rev. 0
9.2-8 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
EASA
R
9.2-8 -2
2
EASA
R
9.2-8 -3
2
EASA
R
9.2-8 -4
2
EASA
9.2-8 -5
1
EASA
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9.2-8 -6
2
EASA
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9.2-8 -7
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EASA
Rev.No
ED
0
App.
Page
Rev.No.
App.
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9.2-8 -1
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LEP – approved (part 1):
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LEP – manufacturer‘s data (part 2): Page
Rem
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2
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9.2-8 -9
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Page
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LOG OF REVISIONS
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FIRST ISSUE
IN
ORIGINAL
(see page 9.2-8-1) REVISION JUN 08, 2016
REVISION
1.1
MAR 20, 2017
REVISION
1.2
JUL 21, 2017
FO
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REVISION 1 EASA approval no.: 10058347
Date: JUL 23, 2018
2
(see entry below)
Approved by EASA:
EASA approval no.: 10066279
9.2-8 – 2
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
1
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
PRECAUTIONS
LL
2.1
O
LIMITATIONS
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2
ED
Additional information about the operation of the weather radar system as well as about the correct interpretation of weather maps must be obtained from the pilot’s guide and other additional vendor documentation (see para 8.2).
O
– As a rule, the national safety regulations for the operation of radar systems must be observed.
O
T
C
The weather radar should not be operated below 50 ft AGL unless the following precautions are observed:
PY
N
– During refueling the weather radar system must be switched off.
C
O
– The weather radar system must not be used during starting and shutting down of the engines.
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O N
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–
– On ground, the weather radar system may only be put into operation if the following safety distances are observed (see Fig.1)
Safety distance from personnel and containers of flammable or explosive material . . . . . . . . . . . . . . . . . . . . . . . 10 ft Fig. 1 APPROVED Rev. 2
Safety Distances
9.2-8 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
2.2
OPERATIONAL SAFETY Never fly into radar shadow and never believe that the full extent of heavy rain is being seen on radar unless another cell or a ground target can be seen beyond the heavy cell. WARNING
2.3
NEVER RELY UPON WEATHER RADAR AS A PROXIMITY WARNING DEVICE OR FOR ANTI-COLLISION-PROTECTION WARNING.
OPERATIONAL LIMITATIONS
ED
The limit for the antenna stabilisation function is $30_ combined for pitch, roll and tilt axis.
EFFECTIVITY
O
COMPATIBILITY
Up to S/N 20229, except S/N 20195, S/N 20212, S/N 20225
C
2.4
N TR
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The Vertical profile (VP) and Track (TRK) functions are inactive.
All
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–
C
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EFFECTIVITY
PY
N
O
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The weather radar system (i.e. radome) significantly degrades the protective capability of an optionally installed Wire Strike Protection System (FMS 9.2–15).
9.2-8 – 4
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
3
EMERGENCY AND MALFUNCTION PROCEDURES
3.1
WXR FAILURE OR INHIBITED TRANSMISSION
FAILURE INDICATIONS
FAIL
and
WXR
WXR FAIL
WXR sk WXR fail indication on NAVD
LL
ED
WXR failure indication on FND
N TR
O
Conditions/Indications – WXR switched off or failed
C
If MFD 4 fails weather radar is no longer available.
O
T
NOTE
O
– No WXR data displayed
PY
N
Procedure
–
C
If weather radar is operating normal
– Check ON
O
WXR
O N
LY
Continue flight
O N
If failure indication remains
OFF
C
WXR TX INHIB
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Continue flight
–
TI
Weather radar
WXR indication for inhibited transmission on FND and NAVD
Conditions/Indications – Weather radar mode selector is on when aircraft is below 50 ft radar altitude. Weather radar does not transmit. Procedure Function selector sw
APPROVED Rev. 1
– OFF
9.2-8 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
DON’T PUT THE FUNCTION SELECTOR SWITCH IN ON POSITION UNLESS THE PRECAUTIONS / SAFETY DISTANCES OF PARA 2.1 ARE OBSERVED.
CAUTION
IN CASE OF A FAILED RADAR ALTIMETER THE AUTOMATIC INHIBIT FUNCTION < 50 FT IS DISABLED. THEREFORE THE CREW HAS TO SELECT THE STBY OR OFF MODE MANUALLY IN ORDER TO PREVENT THE WXR SYSTEM FROM TRANSMITTING WHILE OPERATING NEAR THE GROUND.
ED
WARNING
SYSTEM CHECKS (AFTER STARTING ENGINES) Avionic master sw
–
O
ON
Function selector sw
– STBY
T
O
4.2
– Condition
N TR
Radome
LL
PREFLIGHT CHECK
O
4.1
NORMAL PROCEDURES
C
4
– Select 80 nm
PY
N
MFD range
O
NOTE D Allow 1 minute warmup time for the radar system.
LY
–
C
D If the WXR is switched OFF by executing preflight test the advisory AVIONIC TEST FAIL will be displayed.
O N
Function selector sw
– Bsk WXR select
O N
MFDs 1, 2, 4 (Sector Mode select)
– TST
TI
– The test pattern will appear.
IN
ST
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C
– The color bands in the test pattern must correspond to WXR Test Pattern, see picture below.
30 33
FO
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W
80
80
TEST T –0.3 40
EDPR
Fig. 2
9.2-8 – 6
STAB OFF 40
Safety Distances APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
4.3
Contrast of the display
– Adjust as required
Range of MFD 4 and MFD 2
– Select equal range
Function selector sw
– STBY or ON
OPERATION
LL
ED
CAUTION D WHEN WEATHER RADAR IS DISPLAYED ON THE NAVD PAGE, HEIGHT ABOVE TERRAIN (HAT), OBSTACLES, AND HTAWS CAUTION AND WARNING ICONS ARE NO LONGER DISPLAYED. TO USE HTAWS AND WXR SIMULTANEOUSLY, WXR MUST BE SELECTED ON THE FND.
T
If the radar altimeter has detected a height below 50 ft AGL, the Weather Radar System will be set to STBY mode automatically, which is displayed with WXR TX INHIB indication on NAVD and FND if the WXR depiction was selected previously.
O
PY
N
O
NOTE
C
O
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O
D WHEN APPROACHING TO A HOVER ABOVE 50 FT GND/SEA IN THE VICINITY OF PERSONNEL (E.G. WIND POWER PLANT) THE WXR MUST BE MANUALLY SWITCHED OFF OR SET TO STBY.
Above 50 ft:
O N
O N
WXR function selector sw
LY
–
C
After-Takeoff check:
– Select
TI
WXR on FND (SCT) or NAVD page
– ON; operate the system as described in the pilot’s guide.
U
C
Pre-landing check:
IN
ST
R
In case of approaching personnel (e.g. marshaller) – Check on (NAVD or FND)
FO
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WXR TX INHIB
If not indicated: WXR function selector sw
– STBY or OFF
After landing check: WXR function selector sw
5
– STBY or OFF
PERFORMANCE DATA No change in the basic Flight Manual data.
APPROVED Rev. 2
9.2-8 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
6
MASS AND BALANCE Refer to Equipment List entries in Section 6 of the basic Flight Manual.
7
SYSTEM DESCRIPTION
7.1
GENERAL For detailed information refer to the RDR 2000 Pilot‘s Guide (vendor documentation).
ED
The helicopter’s weather radar system is mainly used to recognize and avoid “meteorological danger areas”, e.g. storm fronts or areas of great turbulences.
Ground mapping mode
O
Weather Alert Mode
C
Weather mode
ON
Wx
WxA
GND MAP
O
TST
TRK INACTIVE
TI
O N
O N
GAIN
R
U
C
GAIN adjustment (typical installation)
inactive
UP TILT DN PULL STAB OFF
Disabling of antenna stabilization
Control panel CP 466A – typical installation
FO
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IN
ST
Fig. 3
TRK
LY
VP
Tilt control
–
OFF
C
STBY
BKD2_FLH_0470_R
PY
N
O
T
Function selector sw
N TR
O
LL
The RDR 2000 weather radar system consists of the ART 2000 (Antenna/Transceiver unit) installed in the nose section of the helicopter, the CP466A WX–radar control panel installed in the center console (see Fig. 2) and the configuration module CM2000. The weather radar data is displayed on the MFD’s.
9.2-8 – 8
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
Switch
Position
Function
Primary modes OFF / STANDBY / TEST / ON – (WXR function selector sw) Communication between Receiver/Transmitter and HELIONIX is stopped, but the radar still has power applied. The radar will remain active with no radar transmissions occurring, for up to a maximum time of 30 s, allowing the antenna to park at 0_ azimuth, 30_ tilt down. Afterwards the primary power is removed from the radar Receiver/Transmitter.
STANDBY
Fully energizes the system circuitry but no radar transmission occurs in STBY mode. The antenna is parked at 0_ azimuth and 30_ tilt down with the antenna drive motors locked. WXR STANDBY will appear on the display.
TST
A multi-coloured arc display test pattern is displayed in this mode of operation. The test pattern (typical 5–colour test pattern) is initialized and sized to fit the 80 NM range and can also be scaled with the range select buttons. No radar transmissions occur while TST is selected. TEST will appear on the display and STAB OFF is always displayed. An internal test is performed not only when the TEST mode is activated, but also in STANDBY, and ON. This internal test is monitoring receiver/transmitter, antenna drive, control panel and transmission.
ON
Selects the normal condition of operation for weather detection and/or other modes of operation. The system will transmit after a 60 s warm– up time is completed. NOTE When the knob is switched directly from OFF to ON mode, the display will blank.
LL
ED
OFF
–
C
O
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N
O
T
C
O
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O
OFF STANDBY TST ON
LY
Secondary modes Wx / WxA / GND MAP –
Normal weather mode
WXA pb
–
Weather Alert (WXA) mode enables to highlight storm areas for easier detection. It also enables the target alert [TGT] function if detected beyond the selected range.
GND MAP pb
–
The GND MAP function sets the radar system in ground mapping mode. Gain control capability is enabled in this mode. The Ground map (GND MAP) colours are: – Green for weak returns
IN
ST
R
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C
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O N
O N
WX pb
R
– Yellow for moderate returns and
FO
– Red for intense returns. The indication GND MAP will appear on the display in cyan.
VP pb
–
Inactive
TRK pbs (2)
–
Inactive
MANUFACTURER’S DATA APPROVED Rev. 2
9.2-8 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
GAIN
–
The gain knob (GAIN) adjusts the radar gain. Only usable in GND MAP mode. EFFECTIVITY NOTE
Maximum GAIN will be achieved in the mid-position. Any setting left or right of the mid–position will reduce antenna gain.
EFFECTIVITY
ED
Antenna stabilization mode selection and manual antenna tilt adjustment: refer to para 7.2.2
O
LL
–––––– UP / DN
O
HELIONIX INTERFACE AND DISPLAY INDICATIONS OF THE WXR
C
7.2
–
All
N TR
PULL STAB OFF –––––– TILT
Before HELIONIX Maintenance release 1
N
O
T
For activation of the WXR superimposition function the crew has to use the MFD bottom softkey (see Fig. 5). Conditions necessary to allow WXR video mixing on the FND are:
PY
– FND in SECTOR mode
O
– WXR function has been activated by the crew
C
– The heading compass rose is visible and WXR equipment available
LY
–
– The local range is equal to the range selected by the master MFD
O N
A range selection is available via softkey access on the MFD, refer to para 7.2.4.
O N
Helionix provides the following indication capabilities:
U
C
TI
– Indication of weather video information on MFD NAVD in ROSE and SECTOR format (see Fig. 5).
ST
R
– Indication of weather video information in the navigation area of the FND page in SECTOR format (see Fig. 4)
R
IN
– Weather radar status/mode information on MFD in NAVD and FND page (see Fig 4 and Fig. 5).
FO
– Reduced weather radar status information on MFD VMD page, SYSTEM format (see Fig 6) Information is also provided to crew members about the stabilization mode status of the weather radar equipment selected on the Radar control panel (e.g. STAB OFF), refer to para 7.2.2. The weather radar tilt indication (refer to para 7.2.2) provides crew members with the tilt value of the weather radar antenna selected by the crew members on the Radar control panel (see Fig 2). The WXR comprises the target alert (TGT) feature. This feature enhances situational awareness of the flightcrew for strong returns (at least of red intensity) behind the selected range of at least 80NM, refer to para 7.2.3.
9.2-8 – 10
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
DMAP
NAV
IAS
101
4
2
18
120
20
20
17
17
10
10
16
16
1500
15
14
14
13
13
100 80
10
10
20
20
VY
N
1013 200 hPa DH
B A R O
C
T
20
O 10
10
PY
DTK
N
WXA T+ 2.0 FSD
A C K
C
O
354 1.0 FMS GPS
–
LFMH
LY
20.0 NM 12 min
HSI
O N
DCPL
415 Kg WXR
SVS
OAT
25
+ B R G –
O N
BKD2_FLH_0397_R
3
20
C R S
+ L U M –
600 DA
D H
O
R N G
N A V
3
D A
N TR
6
+ C T R S –
CLOCK
ED
ALT
MISC
LL
VMS
O
NAVD
FO
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IN
ST
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C
TI
Weather data superimposed on SECTOR mode
R N G
C R S
N
CHECK RANGE
20
WXA T+ 2.0
3
10
20 TGT STAB OFF
10
WXR check range, target alert, stabilization and tilt information
Fig. 4
MANUFACTURER’S DATA APPROVED Rev. 2
WXR FND indication
9.2-8 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
ASBAG 116 /
VMS
3.3 NM
DTK 294
DMAP
FMS
GS TAS
0 6 M A P
12
6
16
R N G
D H
3 ASBAG DEP80 1720FT REDVO
0.1 NM
N
E
V O R 1
30
N TR
O
24 W
F M S
PY
N
O
T
C
O F R T
21
20
O
10
33
+ C T R S –
EFB
NPA MSG
E
N A V
MISC
ED
NAVD
LL
FND
– FMS
PLS
SCT
WX
WXR
ACAS
FLTA
HTAWS
+ B R T –
O N
O N
CPL
LY
+ L U M –
Fig. 5
WXR NAVD indication
R
IN
ST
R
U
C
TI
BKD2_FLH_0225_R
C
O
D A T A
FO
Indication Area Indication Bsk of NAVD
Description
Primary mode
FAIL WXR
STBY
The WXR is not detected by HELIONIX MFDs. It means the WXR is switched OFF or it has failed. There is no difference between OFF and a total WXR bus failure. In both cases the message WXR FAIL is displayed in amber inside compass aera. WXR in STBY mode
WXR
TEST
9.2-8 – 12
TEST modus of the WXR
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
Indication Area Indication Bsk of NAVD
Description
Secondary mode Normal weather mode
WX
WXR Weather Alert Mode. When WXA mode is selected, red areas of storms flash between red and black at a 1 HZ rate.
WXR Primary NAVD / FND compass rose
LL
WXR TX INHIB
Is displayed if the WXR is switched ON while the HC is on ground or when in flight the WXR has automatically set to STBY while passing below 50 FT RA.
ED
WXA
O
N TR
WXR STANDBY
WXR in STBY mode (FND only)
C
O
The WXR is not detected by HELIONIX MFDs. It means the WXR is switched OFF or it has failed. There is no difference between OFF and a total WXR bus failure. In both cases the message WXR FAIL is displayed in amber inside compass area (FND only).
N
O
T
WXR FAIL
PY
LY O N
O N TI
R
U
C
GND MAP
ST
O Normal weather mode
WX
Weather Alert mode. When WXA mode is selected, red areas of storms flash between red and black at a 1 HZ rate. Target alert is activated as well. The status WXA is indicated in cyan. Ground MAP mode The ground map colours are: – Green for light ground returns – Yellow for medium ground returns and – Red for heavy ground returns.
FO
R
IN
–
Secondary mode
WXA
Refer to para 7.2.4
C
CHECK RANGE
MANUFACTURER’S DATA APPROVED Rev. 2
9.2-8 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
7.2.1
WXR display state The display provides an indication on top of BSK3 containing information if WXR is selected for display on the MFD or not.
WXR layer selected for display (left) and WXR layer unselected (right) 7.2.2
Antenna stabilisation / tilt indication
ED
The following antenna stabilization modes are available:
N TR
O
LL
– Manual (tilt turning knob pulled): Permits manual adjustment of antenna tilt 15_ up or down for best indicator presentation. The tilt angle is indicated on the display.
C
O
– Automatic (tilt turning knob pushed): The weather radar antenna tilt angles are automatically compensated for helicopter roll and pitch angle. The tilt can still be set in this mode.
O
T
Stabilisation indication
PY
N
– No antenna stabilisation is provided
O
STAB OFF
LY
–
C
on FND (see Fig. 4) and NAVD STAB OFF when in manual stabilisation.
TI
O N
– Example for tilt indication
O N
The WXR tilt indication provides the tilt value of the WXR antenna selected by the crew members on the radar control panel.
C
T+12.3
ST
Target Alert
IN
7.2.3
R
U
on FND (see Fig. 4) and NAVD.
R
TGT
FO
The message will be displayed on the FND (sector page) and on the NAVD (directly below the compass rose). Target alert makes the pilot aware of the presence of a significant weather cell that exists beyond the currently selected range. For this mode to be active the WXR needs to be in WXA mode. The TGT symbol is indicated if a weather cell: – has at least red intensity, and – is located within $10_ of aircraft heading, and – has a minimum size of 2 NM in range and 2 degrees in azimuth, and – is located within a range of 80 to 240 NM.
9.2-8 – 14
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
Target alert is not active in ground map mode. Target Alert is applied to each scan independent of the other when the radar is in alternating scan. If TGT message appears proceed as follows:
7.2.4
Selected range
– Increase until TGT message disappears
Display
– Check for intensive weather areas
Range selection
LL
ED
A range selection is available via sk access on the MFD (see Fig. 4 and 5) . The WXR range selection and display on pilot side MFD 2 and 4 is independent from the WXR range selection on the copilot’s side MFD 1.
O
MFD 2 / 4 requires identical range selection.
O
N TR
If the range selection on MFD 2 and 4 is not identical the following indication will be provided on NAVD and FND:
O
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CHECK RANGE
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CHECK RANGE is also displayed when selecting ranges different than the RDR 2000 display ranges 10, 20, 40, 80, 160, and 240 NM.
MANUFACTURER’S DATA APPROVED Rev. 2
9.2-8 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
7.3
VMD INDICATIONS The presence and status of the WXR is indicated on the system format of the VMD page:
LL
ED
WXR is recognized and valid on all MFDs:
O
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N
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WXR is recognized but invalid on MFD 4 (connection failure):
Fig. 6
WXR status on VMD SYSTEM page
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WXR invalid on all MFDS, no WXR detected:
9.2-8 – 16
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM RDR 2000
8
HANDLING, SERVICING AND MAINTENANCE
8.1
HANDLING AND MAINTENANCE 1. Operation on ground is only permitted when the safety distances are observed. 2. During refueling, the weather radar system must be switched off.
LL
VENDOR DOCUMENTATION
O
8.2
ED
3. Make sure that the radar nose is clean and that the antenna components are clean and dry.
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PILOT’S GUIDE RDR-2000: 006–08755–0001
MANUFACTURER’S DATA APPROVED Rev. 2
9.2-8 – 17/(9.2-8 – 18 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY FLOATATION SYSTEM
FMS
9.2-9
SUPPLEMENT FOR
O
LL
ED
EMERGENCY FLOATATION SYSTEM
Effectivity All
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Emergency floatation system
–
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System/Equipment Designation
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This supplement shall be attached to the BK117 D-2 flight manual (subsection 9.2) when the EMERGENCY FLOATATION SYSTEM is installed.
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 1055971
APPROVED Rev. 0
9.2-9 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY FLOATATION SYSTEM
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are new, revised or deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the record of supplement-revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
EASA
R
9.2-9 -2
1
EASA
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9.2-9 -3
1
EASA
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9.2-9 -4
1
EASA
9.2-9 -5
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LEP – approved data (part 1):
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LOG OF REVISION
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FIRST ISSUE
R ST IN
1
(see entry below)
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REVISION
(see page 9.2-9-1)
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ORIGINAL
Revision 1
Date: JUN 21, 2017
Approved by EASA:
EASA approval no.: 10062303
9.2-9 – 2
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY FLOATATION SYSTEM
1
GENERAL The information contained herein supplements the information in the basic flight manual. For limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual.
2
LIMITATIONS
LL
ED
NOTE D The system enables an emergency landing on water and keeps the helicopter afloat even on rough sea. It is not approved for normal water landings. Takeoff after ditching is prohibited.
O
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D For over-water flights (open sea) the operating regulations of the country concerned or of the country in which the helicopter is registered must be applied. This may require the carriage of additional emergency equipment such as life jackets, rubber dinghy, signalling equipment etc.
CERTIFICATION CRITERIA
O
2.1
PY
N
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D The stowed floats are not to be stepped on except by one person during the performance of his duties (i.e. hoist/fast roping/rappelling operator). Do not step on the end caps of the floats.
LY
–
C
The emergency floatation system is certified as ditching provision in accordance with FAR 29.
O N
O N
The helicopter may be certificated for ditching provided the following additional equipment are fitted and approved in accordance with the relevant airworthiness requirements:
C
TI
– survival type emergency locator transmitter
U
– life raft installation
For a ditching certification a maximum of 9 passengers is permissible.
SEA STATE LIMITATION
FO
2.2
R
IN
NOTE
ST
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– life preserver
The emergency floatation has been demonstrated up to sea state 6. NOTE D The above information must be accounted for when assessing the helicopter dispatch on any sea state conditions. D World Meteorological Organization standards describe sea state 6 as a ”Very Rough” sea with significant wave height between 4 and 6 meters.
2.3
COMPATIBILITY The emergency floatation system is not compatible with sharp-angled equipment or antennas mounted in a defined area on either side of the fuselage.
APPROVED Rev. 1
9.2-9 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY FLOATATION SYSTEM
2.4
ALTITUDE LIMITATION Max. operating altitude for inflation of emergency floats . . . . . . . . . . . . . . . . . . . . . . 5000 ft
2.5
AIRSPEED LIMITATION With floats inflated the airspeed indication is 5 kts higher than actual in level flight and descent.
1. Max. permissible airspeed during inflation process of emergency floats in all flight conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
80 kts
ED
NOTE
80 kts
LL
2. Max. permissible airspeed with emergency floats inflated . . . . . . . . . . . . . . . . .
N TR
on calm water . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 kts GS on waves:
O
a) b)
O
3. Max. recommended touchdown speed with emergency floats inflated
PY
MEASURES FOLLOWING AN INFLIGHT FLOAT INFLATION
C
2.6
Adapt airspeed for lowest possible forward ground speed.
O
NOTE
N
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for sea state up to and including 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . GS < 15 kts for sea state up to and including 6 . . . . . . . . . . . . . . . . . . . . . . . . . . . GS = 0 kts
O N
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–
After any inflight inflation without ditching, the helicopter has to return to a landing field in the shortest way possible.
TI
PLACARDS
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2.7
O N
After any inflight inflation of the floats, the floats have to undergo a careful inspection by an authorized service station prior further utilization.
EMERGENCY FLOATS
DO NOT INFLATE ABOVE 5000 FT AND 80 KTS
R
IN
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Placard:
FO
Location: Cockpit in pilot‘s field of view
9.2-9 – 4
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY FLOATATION SYSTEM
EMERGENCY AND MALFUNCTION PROCEDURES NOTE
INFLATION PROCEDURES 1. Airspeed
– Reduce to 80 kts or less
2.
– Check on
FLOATS ARMED
– Push
4. Landing
– Perform
ED
3. DEPLOY pb
O
3.1
In case of an emergency requiring ditching (e.g. low fuel, MGB low pressure), ditching should be performed in AEO whenever possible. Ditching in OEI or autorotation is to be used as a last resort only.
LL
3
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DO NOT EVACUATE THE AIRCRAFT BEFORE THE ROTOR IS COMPLETELY STOPPED.
O
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WARNING
O
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The landing procedures to be used (AEO, single engine or AR-landing) should be taken from section 3 of the basic flight manual.
PY
O
REMOVE SHOES BEFORE LEAVING THE HELICOPTER. SHARP OBJECTS WILL PUNCTURE FLOATS.
–
C
CAUTION
– Perform
N
5. Emergency evacuation
LY
LANDING ON CALM WATER
O N
3.2
O N
Forward speed up to . . . . . . . . . . . . . . 30 kts.
TI
Rate of descent up to . . . . . . . . . . . . . 300 ft/min.
U
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Nose-up attitude between . . . . . . . . . 05 and 105.
The rate of descent should be kept to a minimum at the instant of touchdown. The angles of roll and yaw should be kept to a minimum. At 5° nose-up attitude, yaw angles up to 15° can be tolerated at forward speeds up to 30 kts, with a rate of descent of 300 ft/min.
FO
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IN
NOTE
ST
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Preferable nose-up attitude . . . . . . . 55.
APPROVED Rev. 0
9.2-9 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY FLOATATION SYSTEM
3.3
LANDING ON WAVES Across wave crest: Forward speed: for sea state up to 4 . . . . . . . . . . . . GS < 15 kts for sea state above 4 and up to 6 GS = 0 kts NOTE
Adapt airspeed for lowest possible forward ground speed.
Rate of descent up to . . . . . . . . . . . . . 300 ft/min.
Avoid ditching in the trough or the rising face of a wave. The landing should be made so that the helicopter contacts the crest or back of a wave.
O
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NOTE
ED
Nose-up attitude . . . . . . . . . . . . . . . . . 10°.
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In case of strong wind, the helicopter should be presented at a 30° to 45° angle with respect to the swell.
IN
ST
Crest
BKD2_FLH_0292_R
FO
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Trough
3.4
FLOATATION STABILITY The helicopter is most stable when heading into the waves. However, with large, breaking waves best stability is achieved when heading diagonally into the waves.
9.2-9 – 6
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY FLOATATION SYSTEM
3.5
GENERAL CONSIDERATIONS 1. After water touchdown, maintain the collective pitch setting (do not lower) until the ditching procedure is completed or rotor RPM has dropped below 85 %. 2. The helicopter will normally maintain a nose-into-the-wind position after ditching.
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3. Ditching in shallow waters (e.g. near sandbanks, etc.) increases the possibility of capsizing compared to ditching in open seas.
APPROVED Rev. 0
9.2-9 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY FLOATATION SYSTEM
4
NORMAL PROCEDURES
4.1
PREFLIGHT CHECK 1. Floats
– Stowed
2. Float covers and lashings
– Check
3. Supply lines
– Firm
4. Gas cylinder
– Check correct operating pressure
– Check
LL
5. Condition of overall system
ED
– Check correct mounting and condition of clamps
6. EMER FLOATS sw
– TEST, check: –
N TR
O
In addition, before each flight over water the following checks shall be made:
O
T
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FLOATS ARMED indicates that both electrical systems are functioning
7. EMER FLOATS sw
–
OFFSHORE OPERATIONS
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– OFF, check: – FLOATS ARMED extinguished
O N
Before take-off from an offshore helipad or when flying offshore: – ARM, check
FLOATS ARMED
O N
1. EMER FLOATS sw
TI
After landing on an offshore helipad or when returning onshore: – OFF, check: – FLOATS ARMED extinguished
IN
PERFORMANCE DATA
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5
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2. EMER FLOATS sw
FO
The installed emergency floats will slightly decrease flight performance. The following information applies to stowed floats only. 5.1
MAXIMUM RATE OF CLIMB (AEO AND OEI) All results obtained from the appropriate diagrams in section 5 of the basic flight manual are to be reduced as follows: Helicopter gross mass below 2600 kg: . . . . . . . . . . . . . . . . . . . . . . . Subtract 45 ft/min Helicopter gross mass between 2600 kg and below 3200 kg: . . . Subtract 35 ft/min Helicopter gross mass of 3200 kg and above: . . . . . . . . . . . . . . . . . Subtract 30 ft/min NOTE
9.2-9 – 8
The reduction in climb rate is not depending on power settings. APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EMERGENCY FLOATATION SYSTEM
6
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
SYSTEM DESCRIPTION
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BKD2_FLH_0277_R
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7
Emergency floatation system – typical installation
IN
ST
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Fig. 1
FO
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The emergency floatation system is provided for forced landing or ditching, even on rough sea. The emergency floats are designed to keep the helicopter afloat for as long as it takes to complete the evacuation. Especially in rough sea conditions, it is not recommended to remain in the helicopter after ditching. The system consists of two inflatable floats on each side of the helicopter, a helium-filled pressure bottle with a GO / NO GO-scale and fixed supply lines. The stowed floats are arranged on a special pair of lengthened skid tubes. For redundancy reasons, the system is controlled by two independent electrical systems. It is supplied with 28 VDC through two circuit breakers (FLOATS) located on the overhead panel. The EMER FLOATS master switch (OFF – ARM – TEST) is located on the overhead panel (pos. TEST spring loaded). Upon arming of the system, the HISL (optional, refer to FMS 9.2–14) will be brought into its neutral position.
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-9 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
BKD2_FLH_0013_R
EMERGENCY FLOATATION SYSTEM
SYS1
OFF
ENGAGE
SYS2
BAT MSTR
OFF
N O R M
O N
HYD
OFF
P–FLT
1
OFF
EXT/ WARN
OFF
OFF
A R M
S L O W
OFF
OFF
ON DC GND RECEPT PWR
OFF P I L
OFF
ON
LAMP
FIRE 2 TEST
OFF
O N
OFF
O F F
EXT
OFF
OFF
ON
ON
INV
STBY BAT
ON
1 2 AVIO MSTR
OFF LO/ OFF
HI
MIN/
MAX
ON CC TEST ARM TEST PAX FAST ON ON AIR CKPT PAX OFF HOIST/ CARGOEMER FUZZ LAVCS WIPERCOND BLD HTG VENTILATION CBL CUT HOOKFLOATSBURN CLOSE O P E N NORM
ON
COPILOTPILOT 1 PT/STATIC HTG MUTE N O R M TEST
OFF
OFF
OFF O N
ACAS TAWS AUDIO
ON
HISL
OFF
TAIL FLD
OFF P A X
ON
ON
N O R M EMERG
OFF
OFF
ON
ON
RECALL 1 2 A F RECALLAUX TK PRIME PUMP XFER PUMP FUEL
2 IBF
MUTE N O R M STBY
OFF
OFF
OFF
OFF
ON
ON
ON
IR STROBE POS FLASHEXT LIGHTS DAY
OFF A R M
ON
OFF
ON
A RD MI M
INSTR
NVG
ON
ACOL
N I G H T
O
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BLT/SMK CARGO EM/EX HEEL PAX INT LIGHTS
B R T
OFF
ED
OFF
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OFF
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A R M
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TEST
PY O
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EMER FLOATS master sw – typical installation
–
Fig. 2
N
EMER FLOATS
O N
O N
LY
In “ARM” and “TEST” position a green “FLOATS ARMED” information message is displayed on the FND Master list. If the test was not successful the “FLOATS ARMED” information message will extinguish.
IN
HANDLING, SERVICING, AND MAINTENANCE
R
8
ST
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A DEPLOY pb, is located underneath each collective stick, is installed to inflate the emergency floatation system. The inflation process will be completed within approximately 4 seconds.
FO
For installation and removal as well as for filling of the pressure bottle refer to the maintenance manual BK117 D-2. Stowage of the emergency floats must be performed according to the stowage procedure provided by the manufacturer.
9.2-9 – 10
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SETTLING PROTECTORS
F M S 9.2-10
SUPPLEMENT FOR
N TR
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SETTLING PROTECTORS
N
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This Supplement shall be attached to the BK117 D-2 Flight Manual (Section 9.2) when the SETTLING PROTECTORS are installed.
O
Settling protectors
PY
System/Equipment Designation
All All
FO
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Settling protectors (installed in conjunction with emergency floats)
Effectivity
Date: DEC 11, 2015
Approved by EASA
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-10 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SETTLING PROTECTORS
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. LEP – approved (part 1): Page
9.2-10 -1
0
EASA
9.2-10 -2
0
EASA
9.2-10 -3
0
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Rev.No
App.
Rev.No
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Rev.No
App.
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App.
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Rem
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LEP – manufacturer‘s data (part 2):
C
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LOG OF REVISIONS
O N
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–
FIRST ISSUE
(see page 9.2-10-1)
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ORIGINAL
9.2-10 – 2
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SETTLING PROTECTORS
1
GENERAL The information contained herein supplements the information in the basic Flight Manual. For limitations, procedures, and performance data not contained in this Supplement, refer to the basic Flight Manual.
LIMITATIONS
2.1
COMPATIBILITY WITH OTHER OPTIONAL EQUIPMENT
ED
2
O O
EMERGENCY AND MALFUNCTION PROCEDURES
4.1
PREFLIGHT CHECK
O
– LY O N
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PERFORMANCE DATA
U
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5
– Condition
O N
1. Settling protectors
O
NORMAL PROCEDURES
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4
PY
N
No change in the basic Flight Manual data
T
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3
(FMS 9.2 -13)
N TR
– Snow skids
LL
The Settling protectors are not compatible with:
FO
R
IN
ST
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No change in the basic Flight Manual data.
APPROVED Rev. 0
9.2-10 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SETTLING PROTECTORS
6
MASS AND BALANCE
6.1
EQUIPMENT LIST ENTRIES Refer to equipment list entries in section 6 of the basic flight manual.
SYSTEM DESCRIPTION
7.1
STRUCTURE OF THE SETTLING PROTECTORS
ED
7
O
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Settling protectors are installed to prevent the helicopter from settling into soft or unstable ground during landing or parking.
BKD2_FLH_0076_R
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O N
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–
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N
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The settling protectors are constructed of machined solid metal with cover and installation hardware. They are installed to the rear end of the skid tubes with three thread bolts and secured with locknuts.
Fig. 1 Settling protectors - typical installation
9.2-10 – 4
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FMS
9.2-11
SUPPLEMENT FOR
C
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NIGHT VISION IMAGING SYSTEMS (NVIS) / NVG
O
–
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System/Equipment Designation
PY
N
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NOTE
O N
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Effectivity
9.2-11 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
LIST OF EFFECTIVE PAGES NOTE
NRD LEP – approved (part 1):
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Rev.No.
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Page
Rev.No.
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FIRST ISSUE
LOG OF REVISION
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9.2-11 – 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
GENERAL “aided” “Unaided”
LIMITATIONS CAUTION
ED
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KINDS OF OPERATION
N TR
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N
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O N
APPROVED CONFIGURATION
O N
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–
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The Operator must have an approval from his or the appropriate civil aviation authority to operate with NVGs.
R
FO
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CAUTION
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C
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– – NOTE
EFFECTIVITY NOTE EFFECTIVITY
After SB MBB–BK117 D–2–33–07 All
9.2-11 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
– – – – –
MINIMUM FLIGHT CREW
ED
O
OPERATIONAL LIMITATIONS
N TR
LL
N
C
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CAUTION
O
APPROVED NVGs
PY
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O N
NOTE
INCOMPATIBLE LIGHTS
TI
O N
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9.2-11 – 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
EMERGENCY AND MALFUNCTION PROCEDURES NOTE
FAILURE OF NVIS LIGHTING Condition/ Indication
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NEAR THE GROUND
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Procedure
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AT SAFE HEIGHT
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CAUTION
9.2-11 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FAILURE OF NVG Condition/ Indication
NEAR THE GROUND Procedure
ED
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NOTE
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AT SAFE HEIGHT
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Procedure
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BATTERY POWER SUPPLY FOR NVG’S OR DEGRADED OR LOSS OF NVG IMAGE
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Condition/ Indication
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Procedure
NOTE
9.2-11 – 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
NORMAL PROCEDURES
NVIS NIGHT OPERATION
L Preparation for flight
NOTE
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L Preflight check (to be performed during system checks acc. to Basic FLM/ Sec. 4 )
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Pre– T/O and Pre–Landing check
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L To be checked before each flight
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PERFORMANCE DATA
9.2-11 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
MASS AND BALANCE
SYSTEM DESCRIPTIONFMA 11
INSTRUMENT LIGHTING SWITCH
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
INSTR LIGHTS sw w
HANDLING, SERVICING, AND MAINTENANCE
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
FMS
9.2-12
SUPPLEMENT FOR
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ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
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System/Equipment Designation
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This supplement shall be attached to the BK 117 D-2 Flight Manual (Section 9.2) when the following equipment is installed. Effectivity All
Supplementary Air Conditioning System
All
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Environmental Control System (ECS) / Air Conditioning System (ACS)
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971
APPROVED Rev. 2
9.2-12 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
Rev.No
App.
Page
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9.2-12-28
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REVISION
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FIRST ISSUE
9.2-12-32
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LEP – manufacturer‘s data (part 2):
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LEP – approved (part 1):
(see page 9.2-12-1) 0.1
REVISION 1 EASA approval no.: 10064108
REVISION
2
(see entry below)
NOV 07, 2016 DEC 18, 2017
Revision 2 Date: MAY 24, 2018
Approved by EASA: EASA approval no.: 10065622
9.2-12 – 2
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
TABLE OF CONTENTS Page GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 5
1.1
ABBREVATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 5
2
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 5
2.1
CONFIGUARTION REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 5
3
EMERGENCY AND MALFUNCTION PROCEDURES . . . . . . . . . . . . . 9.2-12 – 6
3.1
ECS/ACS MALFUNCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 6
3.1.1
CHCU failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 6
3.1.2
Cockpit fan failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 7
3.1.3
Heating Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 7
3.1.4
Supplementary Air Conditioning System Failure . . . . . . . . . . . . . . . . . . 9.2-12 – 8
3.2
CAUTION INDICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 9
3.2.1
Generator Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 9
3.2.2
ELEC OVERLIMIT if SACS is installed . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 10
4
NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 13
4.1
SYSTEM CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 13
4.1.1
Interior check (if SACS installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 13
4.1.2
Ventilation and heating check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 13
4.2
OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 13
4.2.1
Normal operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 13
4.2.2
Heating system on / off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 14
4.2.3
Maximum defrosting/defogging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 14
4.2.4
Maximum Ventilation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 15
4.2.5
Maximum Cooling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 15
4.2.6
Maximum heating in cockpit/cabin . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 16
–
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Selecting recirculated air . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 16
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Use of electrical heater with EPU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 16
4.2.9
Use of SACS (if installed) with EPU . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 17
5
PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 18
5.1
POWER CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 18
5.2
PERFORMANCE WITH HEATING ON . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 18
5.3
PERFORMANCE WITH ACS COOLING ON . . . . . . . . . . . . . . . . . . . . 9.2-12 – 18
5.4
PERFORMANCE WITH ACS&SACS COOLING ON . . . . . . . . . . . . . 9.2-12 – 19
6
MASS AND BALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 27
7
SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 27
7.1
ENVIRONMENTAL CONTROL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 27
FO
4.2.8
APPROVED Rev. 2
9.2-12 – 3
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Page 7.2
AIR CONDITIONING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 28
7.3
CONTROL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 29
7.3.1
Control function description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 31
7.3.2
System failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 34
7.4
POWER SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 35
7.5
SUPPLEMENTARY AIR CONDITIONING SYSTEM (OPTIONAL) . 9.2-12 – 36
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ED
LIST OF FIGURES
Hover ceiling in ground effect (AEO, TOP, IBF installed, clean bypass closed, SACS on) . . . . . 9.2-12 – 20
Fig. 2
Hover ceiling in ground effect (AEO, TOP, IBF installed, clog trend bypass closed, SACS on) . 9.2-12 – 21
Fig. 3
Hover ceiling in ground effect (AEO, TOP, IBF installed, bypass open, SACS on) . . . . . . . . . . . 9.2-12 – 22
Fig. 4
Hover ceiling out of ground effect (AEO, TOP, IBF installed, clean bypass closed, SACS on) . . . . . 9.2-12 – 23
Fig. 5
Hover ceiling out of ground effect (AEO, TOP, IBF installed, clog trend bypass closed, SACS on) . 9.2-12 – 24
Fig. 6
Hover ceiling out of ground effect (AEO, TOP, IBF installed, bypass open, SACS on) . . . . . . . . . . . 9.2-12 – 25
Fig. 7
Hover ceiling out of ground effect (AEO, MCP, IBF installed, bypass closed or open, SACS on . . . 9.2-12 – 26
Fig. 8
Cooling Heating Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 31
Fig. 9
Optional Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-12 – 31
Fig. 10
Schematic of the ACS with SACS – typical installation . . . . . . . . . . . 9.2-12 – 36
Fig. 11
SACS switch (overhead panel) – typical installation . . . . . . . . . . . . . 9.2-12 – 37
Fig. 12
SACS EXT.ACT switch (EPU receptable) – typical installation . . . . 9.2-12 – 38
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Fig. 1
9.2-12 – 4
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
1
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual. Environmental Control System (ECS) is installed for heating, demisting and ventilation the cockpit and cabin. An Air Conditioning System (ACS) aims to cool the aircraft. This supplement also includes the optional Supplementary Air Conditioning System (SACS).
ED
ABBREVATIONS – Air Conditioning System
BAMV
– Bleed Air Mixing Valve
CHCU
– Cooling Heating Control Unit
ECS
– Environmental Control System
HVAC
– Heating, Ventilation and air conditioning
OCP
– Optional Control Panel
SACS
– Supplementary Air Conditioning System
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ACS
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1.1
LIMITATIONS
2.1
CONFIGURATION REQUIREMENTS
TI
SACS (IF INSTALLED) SHALL BE SWITCHED OFF DURING HOIST OPERATION. SIMULTANEOUS OPERATION OF THE SACS AND THE HOIST COULD LEAD TO AN ELEC OVERLIMIT OR GEN OVERHEAT.
ST
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CAUTION
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– Operation of the SACS is only allowed when the IBF (refer to FMS 9.2–5) is installed.
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– The SACS is incompatible with the operation of the external hoist (refer to FMS 9.2–4). Whenever the hoist is used, the SACS must be switched to OFF.
APPROVED Rev. 2
9.2-12 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
3
EMERGENCY AND MALFUNCTION PROCEDURES
3.1
ECS/ACS MALFUNCTIONS NOTE
3.1.1
For failure codes description refer to Para 7.3.2 of this supplement.
CHCU failure Conditions/Indications
ED
– CHCU inoperative (no indications) or failure code -.- is shown.
LL
– Ventilation, cooling and heating not available
N TR
IN SUNNY AND/OR HIGH OAT CONDITIONS, THE LACK OF VENTILATION/COOLING MAY CAUSE THE COCKPIT TEMPERATURE TO INCREASE RAPIDLY. IN SUCH CONDITIONS, THE BAD WEATHER WINDOW SHALL BE OPENED AND AIR DEFLECTORS (IF INSTALLED) SHALL BE USED. IF THIS IS INSUFFICIENT TO MAINTAIN AN ACCEPTABLE TEMPERATURE, LANDING AS SOON AS PRACTICABLE SHALL BE CONSIDERED.
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CAUTION
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Procedure
– Avoid, if possible
LY
–
1. Environmental conditions where windshield fogging/frosting may occur
O N
2. Bad weather window
O N
If windshield fogging/frosting occurs:
– As required to maintain visual references
U
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3. Sideslip
– Open
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4. LAND AS SOON AS POSSIBLE
9.2-12 – 6
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
3.1.2
Cockpit fan failure Conditions/Indications – Failure code FI is shown on the CHCU – The cockpit fan is inoperative – SACS (if installed) continues to operate Procedure IN SUNNY AND/OR HIGH OAT CONDITIONS, THE LACK OF VENTILATION/COOLING MAY CAUSE THE COCKPIT TEMPERATURE TO INCREASE RAPIDLY. IN SUCH CONDITIONS, THE BAD WEATHER WINDOW SHALL BE OPENED AND AIR DEFLECTORS (IF INSTALLED) SHALL BE USED. IF THIS IS INSUFFICIENT TO MAINTAIN AN ACCEPTABLE TEMPERATURE, LANDING AS SOON AS PRACTICABLE SHALL BE CONSIDERED.
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CAUTION
– Avoid, if possible
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1. Environmental conditions where windshield fogging/frosting may occur
C
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If windshield fogging/frosting conditions cannot be fully avoided:
–
1. DEMIST pb
– Push, check ON
O N
Heating Failure
TI
3.1.3
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2. LAND AS SOON AS PRACTICABLE
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Conditions/Indications
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– Failure code HC or HE is shown on the CHCU
IN
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– No warm/hot air coming out of the demisting or heating outlets
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Procedure 1. DEMIST pb
– Push, check ON
If Heating Failure persists: 2. Environmental conditions where windshield fogging/frosting may occur
– Avoid, if possible
If windshield fogging/frosting occurs: 2
Bad weather window
3. Sideslip
– Open – As required to maintain visual references
4. LAND AS SOON AS POSSIBLE APPROVED Rev. 2
9.2-12 – 7
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3.1.4
Supplementary Air Conditioning System Failure Conditions/Indications – No additional cool air coming out of the air SACS outlets in the upper cockpit area or in the cabin (temperature increase in the cockpit/cabin) Procedure 1. SACS sw
– OFF
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2. Continue flight
9.2-12 – 8
APPROVED Rev. 2
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CAUTION INDICATIONS NOTE
Generator Failure
EFFECTIVITY
For helicopters up to S/N 20108
GEN1
ED
3.2.1
The caution indications listed below replace the emergency procedures of the basic flight manual (refer to basic FLM para 3.4).
DISCONNECTED
LL
3.2
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or
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and audio tone
GEN2
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DISCONNECTED
PY
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Conditions/Indications
C
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– Failure code PS is shown on the CHCU.
LY
–
– ECS/ACS is in power saving mode.The ventilation and air conditioning are inoperative. DEMIST function is available with limited performance.
O N
Procedure
TI
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1. GEN DISCONNNECTED procedure Refer to basic FLM, section 3.
– Perform
FO
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2. Cockpit fan failure procedure
– Perform
APPROVED Rev. 2
9.2-12 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
EFFECTIVITY
For helicopters with S/N 20109 and subsequent
GEN1
DISCONNECTED or
DISCONNECTED
GEN2
LL
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and audio tone
N TR
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Conditions/Indications
O
– Failure code PS is shown on the CHCU.
O
T
C
– ECS/ACS is in power saving mode. The ventilation and air conditioning are inoperative.
O
– Perform
C
1. GEN DISCONNNECTED procedure Refer to basic FLM, section 3.
PY
N
Procedure
LY
–
To restore the functionality of the cockpit fan:
O N
O N
1. CHCU main sw
C
TI
2. CHCU main sw
– Wait 5 secoonds – CKPT – Wait for self test to complete – Adjust as required
All
FO
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EFFECTIVITY
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3. CHCU
– OFF
9.2-12 – 10
APPROVED Rev. 2
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3.2.2
ELEC OVERLIMIT if SACS is installed
ELEC OVERLIMIT and audio tone Conditions/Indications
ED
– DC parameters are outside normal operating range
O
LL
– May occur on ground if battery voltage < 24 V. Engine starting is allowed even if battery voltage is only 23.5 V (refer to Sect. 4).
C
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– May occur on ground if the EPU is connected and the indicated battery current exceeds 125 A.
T
Procedure
N
O
1. VMS page
PY
2. Electrical parameters
– Select
– Check
C
O
If indication of GEN AMPS exceeds limits (amber or red):
–
3. SACS sw
O N
– Check
O N
5. GEN AMPS
– Reduce as much as possible, or until GEN AMPS normal
LY
4. Electrical load
– OFF
TI
If indication of GEN AMPS is normal:
C
6. Continue flight with reduced load
R
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If indication of GEN AMPS is still amber or red: – OFF, GENi indicated
DISCONNECTED
7. LAND AS SOON AS PRACTICABLE
FO
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6. Affected GEN sw
If indication of GEN VOLTS exceeds limits (amber or red): 3. Affected BUS TIE sw
– OFF, SYSi BUS TIE OPEN indicated
4. Affected GEN sw
– OFF, GENi indicated
DISCONNECTED
5. LAND AS SOON AS PRACTICABLE If indication of BAT AMPS exceeds red limits: 3. LAND AS SOON AS PRACTICABLE continued: APPROVED Rev. 2
9.2-12 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
If indication of BAT AMPS exceeds amber limits (value > +125 A) and EPU is not connected: 3. Electrical load
– Reduce as much as possible
4. BAT AMPS
– Check
If indication of BAT AMPS is normal: 5. Continue flight If indication of BAT AMPS is still amber:
LL
If the EPU is connected and no parameters are shown in red or amber on the VMS page:
ED
5. LAND AS SOON AS PRACTICABLE
– Check EPU indicated
CONNECTED
N TR
O
3. Master list
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
4. Continue operation on ground.
9.2-12 – 12
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
4
NORMAL PROCEDURES
4.1
SYSTEM CHECK NOTE D This check replaces the system checks for ventilation and bleed air heating from the standard start-up procedure in the basic FLM.
ED
D This check replaces the system check for ventilation from the starting phase of the quick start-up procedure. The heating check from the pre-flight test of the quick start-up procedure is not possible without running engines.
Interior check (if SACS installed)
N TR
4.1.1
O
LL
D Heating test (DEMIST function) is required only if flight is intended in OAT< 10_C
– NORM
C
O
SACS sw
O
T
Ventilation and heating check
N
4.1.2
–
C
O
PY
CHCU main sw
O N
LY
VENT knob
R ST
– Check self test completed (after 15 sec) – Adjust to max (3bars) – Check ventilation is operating – Press – Check ON illuminates – Check
on
– Set temperature/ventilation as required
IN
CHCU
U
C
TI
O N
DEMIST pb
– CKPT
4.2 4.2.1
Maximum ventilation/cooling required if OAT > 35_C
FO
R
NOTE
OPERATION Normal operation CHCU main sw
– CKPT or CAB
AUTO / RECIRC / DEMIST pbs
– Push as desired
T_ knob
– Set as desired
VENT knob
– Set as desired
Cockpit and pax vent nozzles
– Open as desired
APPROVED Rev. 2
9.2-12 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
NOTE D SACS ventilation will not start until 10 seconds after engagement of the system. SACS cooling will take approximately 40 seconds to be fully operational. D SACS (if installed) will only operate, if CAB VENT is ON. 4.2.2
Heating system on / off To switch the heating system on: – CKPT or CAB
T_ knob
– Set to HI or as desired
T_ knob
– Push
N TR
O
To switch the heating system off:
on
LL
– Check
ED
CHCU main sw
C
O
– Check T_ display off
N
Maximum defrosting/defogging
PY
4.2.3
off
O
T
– Check
C
O
CHCU main sw
– Push, check ON
LY
–
DEMIST pb
– CKPT
O N
O N
NOTE D Once the central part of the windshield has cleared, the VENT knob can be increased to clear the rest of the windshield.
C
TI
D Demisting is most effective at high engine power settings.
ST
R
U
D If OAT y –10_C demisting automatically selects fresh air.
FO
R
IN
D If OAT t –10_C demisting automatically selects recirculated air (RECIRC ON).
9.2-12 – 14
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
4.2.4
Maximum Ventilation To set maximum ventilation without air conditioning, proceed as follows CHCU main sw
– CKPT
VENT knob
– 3 bars
RECIRC pb
– OFF
T_ knob
– Push
VENT knob
– 3 bars
Cockpit and pax vent nozzles
– Open
LL
– CAB
N TR
O
CHCU main sw
O
Maximum Cooling
C
4.2.5
ED
– Check T_ display off
– CKPT
O
T
CHCU main sw
PY
N
T_ knob
– Open
C
O
Cockpit and pax vent nozzles
– LO
LY
–
NOTE D Fan speed is automatically set to maximum in the CKPT zone. It may need to be manually adjusted to 3 bars in the CAB zone.
C
For helicopters up to S/N 20108
U
EFFECTIVITY
TI
O N
O N
D Use of the Supplementary Air Conditioning System (if installed) is recommended. The SACS will automatically switch on when CAB VENT is ON (at least 1 bar) and the SACS switch in the overhead console is set to NORM.
FO
R
IN
ST
R
D Depending on the measured temperature, fresh air or recirculated air (RECIRC ON or off) is automatically selected.
EFFECTIVITY
D To adjust maximum cooling without automatic recirculation, adjust the requested temperature to 10_C, set ventilation to maximum and de–activate RECIRC. For helicopters with S/N 20109 and subsequent D Depending on the measured temperature, fresh air or recirculated air (RECIRC ON or off) is automatically selected. This selection can be changed by the pilot.
EFFECTIVITY
APPROVED Rev. 2
All
9.2-12 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
4.2.6
Maximum heating in cockpit/cabin CHCU main sw
– CKPT
T_ knob
– HI – Check
Cockpit vent and cabin heating outlets
on
– Open
CKPT fan speed is automatically set to maximum, RECIRC is ON, CAB fan speed is automatically set to minimum, heating is activated. Selecting recirculated air
ED
4.2.7
RECIRC pb
– Push
N TR
O
LL
To prevent outside air from entering the ventilation system (e.g. during landings in sand/dust, during very cold conditions), select recirculated air as follows:
C
O
– ON illuminates
N
O
T
For helicopters up to S/N 20108
EFFECTIVITY
In automatic or demisting mode, RECIRC ON/OFF is automatically controlled. It may be necessary to leave this mode to select recirculated air.
LY
–
All
EFFECTIVITY
Use of electrical heater with EPU
O N
4.2.8
C
O
PY
NOTE
O N
AUTO / RECIRC / DEMIST pbs
– Push as desired
The electrical heater, if installed, can be used on the ground to slightly pre–heat the windshields, if an EPU is connected. The heating capacity of the electrical heater, however, is insufficient to fully heat the aircraft in cold conditions.
ST
R
U
C
TI
NOTE
IN
EPU
FO
R
BAT MSTR
– Connected – ON, wait 20 seconds – Check
CHCU main sw
– CKPT
T_ knob
– HI
9.2-12 – 16
on VMS page
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
Use of SACS (if installed) with EPU NOTE
The SACS can be used to pre-cool the cabin without powering up the aircraft if an EPU is connected. The EPU must be capable of delivering a continuous current of at least 150 AMP (200 AMP recommended). – OFF
EPU circuit breaker (EPU panel)
– Check in
EPU
– Connected
SACS EXT.ACT. sw (EPU panel)
– ON
LL
SACS ventilation will not start until 10 seconds after engagement of the system. SACS cooling will take approximately 40 seconds to be fully operational.
N TR
NOTE
ED
BAT MSTR sw
O
4.2.9
C
O
If the SACS shall be stopped without starting the aircraft:
– Disconnect
C
O
IN CASE THE ACS/SACS IS SWITCHED ON (CHCU SWITCH IN CKPT OR CAB POSITION AND SACS SWITCH IN NORM POSITION) BEFORE ENGINE START, THE SACS MUST BE SWITCHED TO OFF DURING ENGINE START, TO AVOID OVERLOADING THE EPU. AFTER STARTING BOTH ENGINES, THE SACS CAN BE SWITCHED BACK TO NORM.
O N
O N
LY
–
CAUTION
PY
If the aircraft shall be started using the EPU:
N
O
T
EPU
C
TI
A normal start–up with EPU shall be performed in accordance with the basic flight manual:
R
U
– After switching BAT MSTR to ON and ENGAGE, the SACS will stop automatically.
FO
R
IN
ST
– After both engines have been started, the ACS/SACS can be switched back on using the procedure for ACS normal operation.
APPROVED Rev. 2
9.2-12 – 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
5
PERFORMANCE DATA NOTE D The performance reductions for the ECS/ACS only have to be applied when the cooling or heating system is operative. Therefore, to maximize performance in critical flight phases (e.g. takeoff, landing, hoisting), it may be useful to temporarily switch the cooling or heating OFF as follows (while maintaining ventilation): T_ knob – Push – Check T_ display off
O
POWER CHECK
N TR
5.1
LL
ED
D Whenever the heating is on (heating symbol indicated in FND), cooling shall be considered inoperative.
C
O
Engine power check shall be performed in accordance with the procedures from the basic FLM (refer to section 5.1.4) or the Inlet Barrier Filter Supplement (if installed).
T
The power check must be performed with:
N PY
PERFORMANCE WITH HEATING ON
O
5.2
O
– CHCU set to OFF
PERFORMANCE WITH ACS COOLING ON (SACS OFF or not installed)
LY
5.3
indicated) are available in the basic FLM.
–
C
Performance charts for heating on conditions (
O N
O N
Aircraft performance in AEO is affected by the cooling function of the air conditioning system due to the power off-take at the gearbox.
U
C
TI
All AEO hover performance charts (in and out of ground effect) shall be corrected as follows when the cooling function is operative:
IN
The AEO HIGE & HOGE performance on the VMS WEIGHTS & PERFORMANCE page shows the performance with ACS cooling OFF. To obtain the performance with ACS ON, the penalty must be subtracted manually.
FO
R
NOTE
ST
R
– GM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . subtract 30 kg
All AEO climb performance charts shall be corrected as follows when the cooling function is operative: – GM < 2600 kg . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . subtract 35 ft/min – 2600 kg v GM < 3200 kg . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . subtract 30 ft/min – GM w 3200 kg . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . subtract 25 ft/min
9.2-12 – 18
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
5.4
PERFORMANCE WITH ACS&SACS COOLING ON (IBF installed) NOTE
When using the hover performance and rate of climb decrements below, the ACS decrements (para 5.3) shall not be taken into account.
The AEO MCP climb performance charts (FMS 9.2–5) shall be corrected as follows when the cooling function is operative: – up to 6000 ft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . subtract 100 ft/min . . . . . . . . . . . . . . . . . . . . . . . . . . . . . subtract 150 ft/min
– above 6000 ft and OATw 25_C
ED
– above 6000 ft and OAT< 25_C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . subtract 400 ft/min
The AEO HIGE & HOGE performance on the VMS WEIGHTS & PERFORMANCE page shows the performance with ACS&SACS cooling OFF. To obtain the performance with ACS&SACS ON, the flight manual charts from this supplement shall be used instead.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
NOTE
N TR
O
LL
For the use/reading of the following HOGE/HIGE charts refer to section 5 of the basic FLM.
APPROVED Rev. 2
9.2-12 – 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
HOVER CEILING IN GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
CLEAN BYPASS CLOSED SACS ON 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
LL
ED
2400
O
2500
N TR
MAX. DENSITY ALTITUDE 20000 FT
C
O
2600
MAX. OAT
O C –
TI
O N
3100
LY
3000
O N
2900
PY
MIN. OAT BYPASS CLOSED
2800
GROSS MASS – kg
N
O
T
2700
ST
R
U
C
3200
FO
3400
R
IN
3300
3500
BK117D2001_12_IBF_1
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 1
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (AEO, TOP, IBF installed, clean bypass closed, SACS on)
9.2-12 – 20
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
HOVER CEILING IN GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
CLOG TREND BYPASS CLOSED SACS ON 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
ED
2400
N TR
O
LL
MAX. DENSITY ALTITUDE 20000 FT
2500
O
2600
O N
MAX. OAT
PY O C
O N
3000
3100
O N
GROSS MASS – kg
2900
–
2800
LY
MIN. OAT BYPASS CLOSED
T
C
2700
U
C
TI
3200
ST
R
IN
3400
R
3300
FO
3500
BK117D2001_12_IBF_2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 2
APPROVED Rev. 2
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (AEO, TOP, IBF installed, clog trend bypass closed, SACS on)
9.2-12 – 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
HOVER CEILING IN GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
BYPASS OPEN SACS ON 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
LL
ED
2400
N TR
O
MAX. DENSITY ALTITUDE 20000 FT
2500
C
O
2600
N
O
T
2700
MAX. OAT
– LY O N
3000
C
MIN. OAT
2900
O N
3100
TI
GROSS MASS – kg
O
PY
2800
R
U
C
3200
IN
ST
3300
FO
R
3400
3500
BK117D2001_12_IBF_3
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 3
9.2-12 – 22
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling in ground effect (AEO, TOP, IBF installed, bypass open, SACS on) APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
CLEAN BYPASS CLOSED SACS ON 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300 MAX. DENSITY ALTITUDE 20000 FT
LL
ED
2400
N TR
O
2500
O
2600
3100
MAX. OAT
PY O C – LY
3000
O N
GROSS MASS – kg
2900
O N
MIN. OAT BYPASS CLOSED
2800
N
O
T
C
2700
U
C
TI
3200
ST
R
3300
FO
R
IN
3400
3500
BK117D2005_12_IBF_1
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 4
APPROVED Rev. 2
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, TOP, IBF installed, clean bypass closed, SACS on)
9.2-12 – 23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
CLOG TREND BYPASS CLOSED SACS ON 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300 MAX. DENSITY ALTITUDE 20000 FT
LL
ED
2400
N TR
O
2500
O
2600
3100
O N
MAX. OAT
PY O C –
3000
O N
GROSS MASS – kg
2900
LY
2800
O N
MIN. OAT BYPASS CLOSED
T
C
2700
U
C
TI
3200
ST IN
FO
R
3400
R
3300
3500
BK117D2005_12_IBF_2
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 5
9.2-12 – 24
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, TOP, IBF installed, clog trend bypass closed, SACS on) APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
HOVER CEILING OUT OF GROUND EFFECT 2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND
TAKEOFF POWER
BYPASS OPEN SACS ON 2200
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
2300
LL
ED
MAX. DENSITY ALTITUDE 20000 FT
2400
N TR
O
2500
C
O
2600
N
O
T
2700
MAX. OAT
LY
–
C
MIN. OAT
2900
O N
3000
O N
3100
TI
GROSS MASS – kg
O
PY
2800
ST
IN
3300
R
U
C
3200
FO
R
3400
3500
BK117D2005_12_IBF_3
3600
3700 GROSS MASS LIMIT 3700 KG 3800 –50
Fig. 6
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, TOP, IBF installed, bypass open, SACS on)
APPROVED Rev. 2
9.2-12 – 25
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
HOVER CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER
2 X TURBOMECA ARRIEL 2E ZERO WIND OR HEADWIND OR CROSSWIND BYPASS CLOSED OR OPEN SACS ON
2100 MAX. DENSITY ALTITUDE 20000 FT
2200
ED
2300
N TR
O
LL
2400
O
2500
O
T
C
2600
PY
N
2700
O
MAX. OAT
C – LY
C
TI
3100
O N
3000
O N
MIN. OAT
2900 GROSS MASS – kg
MIN. OAT BYPASS CLOSED
2800
ST
R
U
3200
FO
3400
R
IN
3300
3500
3600
BK117D2006_12_IBF_2
For altitude/oat combinations not shown, the GROSS MASS LIMIT line is applicable
3700 GROSS MASS LIMIT 3700 KG 3800
–50
Fig. 7
9.2-12 – 26
–40
–30
–20
–10
0
10
20
30
40
50
60
Hover ceiling out of ground effect (AEO, MCP, IBF installed, bypass closed or open, SACS on) APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
6
MASS AND BALANCE Refer to Equipment List entries in Section 6 of the basic Flight Manual.
7
SYSTEM DESCRIPTION
7.1
ENVIRONMENTAL CONTROL SYSTEM
ED
The aim of the ECS is to ensure a comfortable temperature inside the cabin by providing functions such as heating, demisting and ventilation for crew and passengers.
LL
The ECS is consists of
N TR
O
– one cockpit fan and one cabin fan
C
O
– one cockpit air distributor flap selects comfort mode (crew vent) or demisting mode (windscreen)
O
T
– one cockpit air inlet flap selects fresh air (outside air) or recirculation air (cabin air)
PY
N
– a cockpit air distribution circuit with outlets located in the instrument panel, the door frame, and near the windshield
–
C
O
– a cabin air distribution circuit with ventilation outlets located in the cabin ceiling and heating outlets located above the floor at mid-cabin
O N
LY
– a set of temperature sensors including:
O N
– two temperature sensors to monitor cabin and cockpit temperature, located in the mid–cabin ceiling and in the cockpit recirculation intake.
C
TI
– one temperature sensor in heating duct, to regulate heating temperature
ST
R
U
– two temperature switches in heating system to switch off heating system in case of overheating
IN
– a main control panel (CHCU) hosting a dedicated ECS control logic
FO
R
– a remote cabin control panel (OCP)
MANUFACTURER’S DATA APPROVED Rev. 2
9.2-12 – 27
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
7.2
AIR CONDITIONING SYSTEM To control the cockpit and cabin compartment environment within the helicopter a R134a vapor cycle system is used. It consists of: – A low pressure circuit (including expansion valve and evaporators) – A high pressure circuit (vapor cycle machine consisting of a compressor, two evaporators, one condensor, sensors and ducting) – A set of refrigerant pipes (rigid and flexible)
O
LL
ED
The helicopter has two main separate air circuits: one for the cabin and one for the cockpit. Some parts of the air conditioning circuit are shared between the cockpit and the cabin.
C
O
– Fan
N TR
Each main circuit contains a set of the following elements:
T
– Corresponding refrigerant pipes
N
O
Cold air generator / vapor cycle system:
O
PY
– 1 condenser (heat exchanger)
C
– 2 condenser fans
LY
–
– Evaporator module
O N
– 1 compressor
O N
– 1 receiver drier
R
U
– 1 Shut off Valve
C
TI
– 1 pressure temperature sensor
IN
ST
The shut off valve closes the circuit which feeds the cabin HVAC. This allows 100% of the system power to feed the cockpit HVAC.
FO
R
The ACS does not provide any avionics cooling. This is provided by a separate system.
9.2-12 – 28
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
7.3
CONTROL SYSTEM The control system consists of two main components: – The main controller and control panel CHCU – The remote control panel OCP The control logic is hosted within the CHCU and allows to manage following functions : – Heating – Demisting – Ventilation
ED
– Air conditioning (cooling)
N TR
O
LL
Switching between the functions is done automatically depending on the requested temperature and as a function of the internal and external environmental conditions
O
In case of detected failure, failure codes are displayed on the CHCU display.
O
T
C
The ECS as well as ACS is controlled by the CHCU located in the cockpit on the centre console allowing easy access for the pilot and the co-pilot.
PY
N
In addition, the remote control panel OCP can be installed in the cabin front compartment allowing the passenger partial control over the cabin compartment settings.
–
C
O
The CHCU can fully control both the cockpit and cabin environments. The OCP, which is normally controlled by the passengers, can perform limited functions only:
C
TI
O N
O N
LY
– When the CHCU main switch is set to CKPT, the cockpit crew can use the CHCU to set the common cockpit/cabin temperature, select AUTO, DEMIST and RECIRC modes and control the cockpit ventilation. At the same time, the passengers using the OCP, can only adjust the cabin ventilation. When passengers try to adjust an unavailable mode (e.g. temperature), this will be indicated by a blinking of the indication.
FO
R
IN
ST
R
U
– When the CHCU main switch is set to CAB mode, the cockpit crew can use the CHCU to set the common cockpit/cabin temperature, select the AUTO, DEMIST and RECIRC modes and control the cabin ventilation. At the same time, the passengers using the OCP, can control the common cabin/cockpit temperature, select AUTO mode and adjust the cabin ventilation. The modes RECIRC and DEMIST can not be selected from the OCP. The control system provides three main modes of operation: – In automatic mode, the control system automatically selects the requested function (ventilation, heating or cooling) and controls the fans and recirculation. The appropriate function is selected depending on the requested temperature and environmental parameters. – In manual mode, the system automatically selects the function, but fans and recirculation are set by the operator. Manual mode is selected by adjusting the ventilation or selecting RECIRC (AUTO is then cancelled automatically). – In demisting mode, available only on the CHCU the control system controls the ECS/ACS in such a way that maximum demisting performance is achieved.
MANUFACTURER’S DATA APPROVED Rev. 2
9.2-12 – 29
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
The function selection is made through the temperature request (T_ knob) as follows: – A temperature between 10_C and 30_C (50_F and 86_F) can be adjusted in 1_C/2_F steps. – Below 10_C (50_F), the special ”LO” mode is triggered for maximum cooling performance. – Above 30_C (86_F), the specific ”HI” mode is triggered for maximum heating performance.
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The control system allows ground operation of the cockpit and cabin fans if electrical power is provided by an EPU. The cooling and heating function are not available until both engines are operative.
9.2-12 – 30
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
7.3.1
Control function description The CHCU and OCP control functions are shown in Fig 8 and Fig. 9. 3
4
AUTO
T_
22
CKPT
DEMIST
ON
RECIRC
VENT
OFF
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ON
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8
ON
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BKD2_FLH_0264_R
CAB
5
ED
2
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1
4 AUTO mode ON/OFF pb 5 DEMIST mode ON/OFF pb 6 RECIRC mode ON/OFF pb
7 Adjust ventilation level or PUSH to switch on/off ventilation for the selected zone. 8 Ventilation level display low, medium, high
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1 CHCU main switch 2 Temperature / failure message display 3 Set temperature or PUSH to switch on/off ventilation mode
Cooling Heating Control Unit T_
22
AUTO ON
BKD2_FLH_0265_R
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Fig. 8
VENT
ON
Fig. 9
MANUFACTURER’S DATA APPROVED Rev. 2
RECIRC
Optional Control Panel
9.2-12 – 31
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
Pos.
Function
Description
OFF mode
ECS/ACS system off.
CKPT mode
Cockpit/cabin temperature can only be adjusted on the CHCU. Cockpit ventilation can be set on the CHCU; cabin ventilation can be set on the OCP.
CAB mode
Cockpit/cabin temperature can be adjusted on the CHCU and OCP. Cabin ventilation can be set on the CHCU and OCP.
Failure codes
Messages and failure codes are displayed. Refer to 7.3.2 for failure code details.
Requested temperature
The T_ knob allows the requested common cockpit/cabin temperature to be set between 10_C and 30_C. The system automatically selects air conditioning or heating. When heating is selected, the bleed air mixing valve is opened and the heating symbol appears on the FND.
HI mode
When the T_ knob is turned fully right, the HI mode is selected. In this case, maximum heating is provided. – Maximum CKPT and CAB zone ventilation, – Air conditioning off, – CKPT zone recirculation air, – Maximum bleed air heating.
LO mode
When the T_ knob is turned fully left, the LO mode is selected. In this case, maximum cooling is provided. – Maximum CKPT zone ventilation, – Maximum cooling power, – CKPT zone recirculation air, – Bleed air heating off.
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Ventilation mode
9.2-12 – 32
The ventilation mode is selected by pushing the T_ knob. In this case, heating and air conditioning are switched off and only ventilation is provided. The ventilation mode can be exited by: – Pushing the T_ knob, – Switching DEMIST to ON, – Switching AUTO to ON.
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
Pos.
Function
Description
AUTO mode
Pressing AUTO selects the automatic mode (ON indicated): – Ventilation is automatically managed, – Air recirculation is automatically managed, – Air distribution is automatically managed, – A temperature request can be adjusted.
DEMIST mode
Pressing DEMIST on the CHCU activates the demisting mode (ON indicated): – Cockpit air outlet directed onto the windshields, – Maximum heating selected, – Maximum air conditioning selected in cockpit, – Air intake is selected based on the OAT (above –10_C outside air is selected, below –10_C recirculated air is selected).
Recirculation air mode
Pressing RECIRC selects recirculation mode (ON indicated). In this case, the air in the cockpit/cabin is circulated without using outside fresh air.
Zone switch off
When the VENT knob is pressed (VENT display off), the selected zone is completely de-activated (no ventilation, no heating, no air conditioning). NOTE: Heating of the cabin zone cannot be switched off independently. If SACS is installed: When the cabin zone ventilation is switched off, the SACS will also be de-activated.
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The VENT knob can be used to adjust the fans in cockpit or cabin zone between low, medium and high setting. If SACS is installed: The cabin zone VENT adjustment also adjusts the SACS ventilation fans.
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Ventilation adjustment
O N
7
MANUFACTURER’S DATA APPROVED Rev. 2
9.2-12 – 33
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
7.3.2
System failures In case of failure of the ECS, the system is automatically set in fail safe mode and the control unit displays a two digit failure message in green. Failure messages can be acknowledged by pressing the T_ knob (except 8.8, –.–, EE, and PS). NOTE
Failures of the SACS (if installed) are not indicated on the CHCU.
Message
CHCU is booting/initializing. Automatically completes after 15 seconds. No action required
CHCU failed / inoperative
This message appears when a failure is preventing all functions from being used. Refer to emergency procedures or MMEL
CKPT fan failure
CKPT ventilation inoperative Demisting and heating function is degraded CKPT and CAB cooling is inoperative Refer to emergency procedures or MMEL
CAB fan failure
CAB ventilation inoperative CAB cooling inoperative Heating fully functional Refer to MMEL
CKPT & CAB cooling failure
Aircondition compressor failure, cold generation lost (airconditioning). Demisting function slightly degraded. CKPT and CAB ventilation not affected. Refer to MMEL
ED
None
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–.–
Description
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8.8
Failure
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F1
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CAB cooling failure
CAB cooling inoperative
P0
ECS/ACS degraded
Cooling performance is degraded.
R
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FO
Power saving mode
PS
Electrical power use is reduced to due a power supply degradation (e.g. due to generator failure). DEMIST function is available. CKPT zone can be re–activated by switching the CHCU to OFF and back to CKPT. EFFECTIVITY
For helicopters up to S/N 20108
Cockpit fan power is limited to maximum 3.5 Amps. EFFECTIVITY
9.2-12 – 34
All
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
Message
Failure
Description
EE
Internal Temp Sensors failed
Automatic temperature control inoperative. Ventilation mode is automatically selected. Heating and cooling can be selected by setting the T_ to HI or LO.
Heating closed
Appears when heating is automatically inhibited in OEI 30 sec rating or in OEI 2 min rating. Refer to emergency procedure or MMEL
Heating Fail
Heating function failed (e.g. BAMV failure, electrical heater failure). Demisting function can be operated with air conditioning/ventilation function.
Flotation inflated
Emergency floatation system was activated. CKPT and CAB Zone inactive
HC
O
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T
For helicopters up to S/N 20108
O
EFFECTIVITY
C
POWER SUPPLY
N
7.4
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Power supply for the ECS/ACS is as follows:
–
C
O
– CHCU: HTG-C (ESS BUS 1, Overhead Panel)
O N
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– ACS: COND FAN (NON ESS BUS 1, Service connector panel LH)
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– Cockpit fan: BLOWER (NON ESS BUS 1, Service connector panel LH), or in case of generator failire: CKPT BLW (ESS BUS 1, Dachkonsole)
IN
ST
– Cabin fan: PAX BLW (NON ESS BUS 2, Service Connector Panel RH) For helicopters with S/N 20109 and subsequent
FO
R
EFFECTIVITY
Power supply for the ECS/ACS is as follows: – CHCU: HTG-C (ESS BUS 1, Overhead Panel) – ACS: COND FAN (NON ESS BUS 1, Service connector panel LH) – Cockpit fan: BLOWER (SHED BUS 1, Service connector panel LH) – Cabin fan: PAX BLW (NON ESS BUS 2, Service Connector Panel RH)
EFFECTIVITY
All
MANUFACTURER’S DATA APPROVED Rev. 2
9.2-12 – 35
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
7.5
SUPPLEMENTARY AIR CONDITIONING SYSTEM (OPTIONAL) The SACS consists of : – Evaporator and fan – Condenser and fan – Interface control box and converter – Cooling fan – Compressor and inverter
ED
– Inverter box ventilation fan
Mechanical Compressor
ON VENT
OFF
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AUTO DEMIST ON
RECIRC
Evapo CKP
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Cond fan: SPAL fan * 2
Receiver dryer
–
T?
22
CAB CKPT
Evap fan
O
Evap fan
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Evapo CAB
Condenser
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ACS
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– Receiver drier
O N
Aircraft Electrical Network
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28VDC Compressor
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Interface Control Board
Evap fan
Evapo
Cond fan
Condenser
BKD2_FLH_0548_R
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SACS
ST
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Pressure release Valves & Sensors
Receiver dryer
Fig. 10
Schematic of the ACS with SACS – typical installation
The SACS is installed above the forward cabin area on top the hydraulic actuator assembly. The SACS is electrically powered and consumes approximately 140 AMPS at maximum power. The circuit breakers for the SACS are installed on the Service Connector panel LH and on an additional service connector panel RH.
9.2-12 – 36
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
The SACS provides the following functions: – Supplementary ventilation and cooling of the upper cockpit area – Supplementary ventilation and cooling of the forward passenger compartment area – Pre-condition of cockpit and cabin (ventilation and cooling) on ground when helicopter is connected to External Power Unit
– The SACS operates in re-circulation mode only (no external air)
ED
– Supplementary cooling function is recommended when operating in very hot and hot/humid areas permanently (guideline OAT > 40_C). The SACS is used as a complementary system to the Air Conditioning System.
N TR
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The SACS is installed additionally to the main air conditioning system to provide more thermal cooling power.
T
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O
The cold air is distributed partly to the cockpit to improve the climate for the crew and partly to all individual outlets in the cabin (plus two outlets at the sliding doors) to improve the climate for the passengers.
N
O
The SACS is a vapor cycle machine, like the main air conditioning system.
PY
The cooling agent is circling in a closed loop in the vapor cycle machine.
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The compressor sucks in the gaseous cooling agent and compresses it. Then it is pumped through the condenser where the cooling agent condenses from gas to liquid and it is cooled down a bit further more in liquid phase. The latent heat of the condensation process is transported into the crossing air stream (which is propelled by the condenser fan respectively the total pressure due to the aircraft’s forward speed). The liquid cooling agent is guided through a receiver drier. Then the liquid cooling agent enters the evaporator. At the entrance of the evaporator the thermal expansion valve serves as a pressure reducer and it dissipates the pressure down to a value closely above the evaporation pressure. Still in liquid phase, the cooling agent enters the heat exchanger and it is heated up by the crossing airstream which it evaporates in the process. Thereby it cools down the crossing air stream, which is the recirculation air taken from the cabin. The cooling fluid is now in gaseous phase, the ventilation air is cooled down. The cooling agent is sucked into the compressor again where the cycle starts over again. For engine start the SACS switch is in OFF position. When the engines are running and EPU is disconnected the SACS can be turned on via SACS switch (overhead panel) and is powered by the helicopter’s electrical system.
OFF
OFF
OFF
L
I
O
L ON
PAX
FUZZ BURN
LAVCS
Fig. 11 MANUFACTURER’S DATA APPROVED Rev. 2
OFF S
P
W FAST
WIPER
NORM
SACS
SACS switch (overhead panel) – typical installation
9.2-12 – 37
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENVIRONMENTAL CONTROL SYSTEM / AIR CONDITIONING SYSTEM
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SACS EXT.ACT switch (EPU receptable) – typical installation
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Fig. 12
ED
BKD2_FLH_0549_R
The SACS can be turned on for pre-cooling on ground separately via SACS EXT.ACT momentary switch installed beside the EPU receptable when an external power unit is connected to the helicopter. The SACS cannot be switched off by the SACS EXT.ACT switch. In order to switch off the SACS, the EPU has to be disconnected.
9.2-12 – 38
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SNOW SKIDS
F M S 9.2-13
SUPPLEMENT FOR
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SNOW SKIDS
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This supplement shall be attached to the BK117 D-2 flight manual (subsection 9.2) when the SNOW SKIDS are installed.
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System/Equipment Designation
All
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Snow skids
Effectivity
Date: DEC 11, 2015
Approved by EASA
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-13 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SNOW SKIDS
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are new, revised or deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the record of supplement-revisions as necessary. LEP – approved (part 1): Page
9.2-13 -1
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9.2-13 – 2
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SNOW SKIDS
1
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual. Snow skids are installed to prevent the helicopter from settling into soft snow during landing or parking. During landing on hard surfaces the landing forces act on the skids – the snow skids will only be stressed during landing on soft surfaces like snow.
LIMITATIONS
2.1
COMPATIBILITY WITH OTHER OPTIONAL EQUIPMENT
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OPERATIONAL LIMITATION
C
2.2
N TR
The snow skids are not compatible with settling protectors (FMS 9.2 –10).
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PY
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Landing with forward speed on soft surfaces (e.g. snow) is prohibited, except in case of emergency.
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No change to the basic flight manual data.
NORMAL PROCEDURES
4.1
PREFLIGHT CHECK
U
– Condition, securely attached
PERFORMANCE DATA
5.1
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Snow skids
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AEO AND OEI MAXIMUM RATE OF CLIMB All results obtained from the respective diagram, contained in section 5 of the basic flight manual, are to be corrected as follows: GM t 2600 kg:
subtract 35 ft/min
2600 kg v GM t 3200 kg:
subtract 25 ft/min
GM w 3200 kg:
subtract 20 ft/min
NOTE
APPROVED Rev. 0
The reduction in climb rate is not depending on power settings.
9.2-13 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SNOW SKIDS
6
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
7
SYSTEM DESCRIPTION
BKD2_FLH_0075_R
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The snow skids consist of flat duraluminum sheet bodies which are tightly fitted to the skid tubes with clamps and struts. For rescue winch operation cable deflectors are mounted to both snow skids.
Fig. 1 Snow skids - typical installation
9.2-13 – 4
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
FMS
9.2-14
SUPPLEMENT FOR
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This supplement shall be attached to the BK17 D-2 Flight Manual (Section 9.2) when the High Intensity Searchlight (HISL) is installed.
Date: DEC 11, 2015
Approved by EASA
EASA approval no.: 10055971
APPROVED Rev. 0
9.2-14 − 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA ref. EASA.21J.700, “DOA”.
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LOG OF REVISION
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(see page 9.2-14-1)
REVISION 1 EASA approval no.: 10057989
MAY 04, 2016
REVISION
JUN 24, 2016
1.1
REVISION 2 EASA approval no.: 10061641
APR 24, 2017
REVISION 3 DEC 18, 2017 EASA approval no.: 10064108 REVISION
3.1
APR 08, 2019
REVISION
3.2
OCT 01, 2019
REVISION 4 DEC 20, 2019 EASA approval no.: 10072151 REVISION
4.1
(see entry below)
Revision 4.1 Date: MAY 14, 2020 Revision 4.1 is approved under authority of DOA ref. EASA.21J.700.
9.2-14 − 2
APPROVED Rev. 4.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
TABLE OF CONTENTS
Page GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 5
1.1
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 5
1.2 1.3
Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 5 Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 5
2
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 6
2.1
Compatibility . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 6
2.2
Airspeed limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 6
2.3 2.3.1
Operational Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 6 Operational limitations for HISL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 6
2.3.2
Operational limitations for laser pointer . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 7
2.3.3
Operational limitations for IR mode operation . . . . . . . . . . . . . . . . . . . . 9.2-14 − 7
2.4
Placards and decals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 7
3
EMERGENCY AND MALFUNCTION PROCEDURES . . . . . . . . . . . . . 9.2-14 − 9
3.1
CAUTION INDICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 9
3.2
Emergency landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 10
4
NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 10
4.1
Preflight check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 11
4.1.1 4.1.2
Exterior check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 11 Operational test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 12
4.2
HISL Searchlight operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 14
4.2.1
Switching on the system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 14
4.2.2 4.2.3
Inflight operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 15 Switching off the system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 16
LL
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LY
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PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 17
FO
5
ED
1
5.1
Rate of climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 17
6
MASS AND BALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 18
7
SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 18
7.1 7.1.1
HISL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 18 Controls on collective lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 20
7.1.2
Controls on HCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 21
7.1.3
Controls on HCCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 24
7.1.4 7.1.5
Controls on TCP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 25 HISL Master List messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 28
7.1.6
HISL Line-of-Sight display on EuroNav 7 DMAP . . . . . . . . . . . . . . . . . 9.2-14 − 29
APPROVED Rev. 4.1
9.2-14 − 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
Page 7.2
Laser pointer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 30
7.2.1
Laser pointer limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 31
7.2.2
laser pointer Pre-flight check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 31
7.2.3
Laser pointer operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 31
ED
LIST OF FIGURES HISL − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 19
Fig. 2
Controls on collective lever − typical installation . . . . . . . . . . . . . . . . . . 9.2-14 − 20
Fig. 3
Functions of controls on collective grips . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 20
Fig. 4
HCU − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 21
Fig. 5
HCU functions and indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 23
Fig. 6
HCCU − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 24
Fig. 7
HCCU functions and indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 25
Fig. 8
TCP − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 25
Fig. 9
TCP functions and indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 28
Fig. 10
HISL Line−of−Sight display on EuroNav 7 DMAP . . . . . . . . . . . . . . . 9.2-14 − 29
Fig. 11
Laser safety panel − typical installation . . . . . . . . . . . . . . . . . . . . . . . . 9.2-14 − 30
Fig. 12
HISL − CONF/NORM LSR−TEST sw − typical installation . . . . . . . . 9.2-14 − 30
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Fig. 1
9.2-14 − 4
APPROVED Rev. 4.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
1
GENERAL
1.1
INTRODUCTION The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
− Control Interface Unit
EOS
− Electro-Optical System
HCCU
− HISL Central Control Unit
HCU
− Hand Controller Unit
HISL
− High Intensity Searchlight
HMI
− Human Machine Interface
ML
− Helionix Master List
PCIU
− Power Conditioning Interface Unit
POST
− Power-On Self Test
TCP
− Trakka Control Panel
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CIU
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1.3
ABBREVIATIONS
DEFINITIONS
LY
1.2
O N
The HISL can be controlled by means of the HCCU on center console
−
HCU or
−
TCP on center console
−
Collective lever control panel
ST
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O N
−
FO
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IN
The controls are either switches (sw) or pushbuttons (pb). In this FMS only the label ”sw” is used. Version 1
− This wording will be used for the HISL with standard hardstop and softstop settings.
Version 2
− This wording will be used for the HISL with alternative hardstop and softstop settings.
APPROVED Rev. 4.1
9.2-14 − 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
2
LIMITATIONS
2.1
COMPATIBILITY The effectiveness of the Wire Strike Protection System (FMS 9.2−15) may be degraded when the HISL is installed.
EFFECTIVITY
Version 1
Is not compatible with centerline EOS installed.
ED O
AIRSPEED LIMITATIONS
N TR
2.2
All
LL
EFFECTIVITY
O
Maximum speed, HISL in STOW position . . . . . . . . . . . . . . . . . . . . . VNE of the basic aircraft
O
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C
Maximum speed, HISL operating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 140 kt
O
Operational limitations for HISL
C
2.3.1
–
OPERATIONAL LIMITATIONS
LY
2.3
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N
Maximum speed, POST (if HISL was not stowed before system OFF) . . . . . . . . . . . . 40 kt
C
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O N
O N
WARNING D THE VISIBLE LIGHT BEAM (WHITE, AMBER, RED) MUST NOT BE DIRECTED AT PERSONS, AIRCRAFT, OR VEHICLES AT DISTANCES LESS THAN 165 FT (50 M) AS THIS COULD CAUSE SERIOUS EYE DAMAGE OR BLINDNESS.
IN
ST
R
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D DO NOT POINT THE HISL BEAM AT FLAMMABLE MATERIAL (E.G. DRY VEGETATION) AT LESS THAN 10 FT (3 M); THE LIGHT ENERGY COULD SET THE MATERIAL ON FIRE.
−
FO
R
It is prohibited:
for the pilot flying to operate the HISL HCU.
EFFECTIVITY
Version 2
If the cargo hook system is installed the HISL is only allowed to be used in flight direction (max. azimuth +90_ to −90_). EFFECTIVITY
9.2-14 − 6
All
APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
2.3.2
Operational limitations for laser pointer Installation of laser pointer does not include or imply approval for laser pointer operation. Except for state aircraft, operating under special permission, the use of the laser is prohibited. This is due to the fact that no EASA / FAA certification basis exists for the use of laser in civil certified aircraft. If the helicopter is operated as a state aircraft, the activation and use of the laser may be regulated by the operating state. For further information regarding the laser pointer, refer to Para. 7.2 up to Para. 7.2.3.
LL
ED
NOTE
O
Operational limitations for IR mode operation
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2.3.3
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Therefore the laser pointer is disabled by means of a removed laser safety dongle or laser safety key (refer to Para. 7.2.).
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WARNING D THE IR LIGHT BEAM MUST NOT BE DIRECTED AT PERSONS, AIRCRAFT, OR VEHICLES AT DISTANCES LESS THAN 50 FT (15 M) AS THIS COULD CAUSE SERIOUS EYE DAMAGE OR BLINDNESS.
FAA registered helicopters
O N
EFFECTIVITY
O N
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–
C
O
D WHEN OPERATING IN FOG, MIST, STRONG RAIN, CLOUD, OR SNOW, REFLECTIONS OF THE INVISIBLE IR LIGHT COULD BLIND THE CREW OR PASSENGERS. DO NOT OPERATE IN THESE CONDITIONS IN IR MODE UNLESS EYE PROTECTION IS USED.
TI
IR searchlight operation is not FAA approved for civil aircraft operations.
IN
PLACARDS AND DECALS
FO
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2.4
All
ST
EFFECTIVITY
R
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The IR mode is disabled by means of an IR safety dongle.
EFFECTIVITY
Version 1 (standard hardstop settings)
Placard:
HARDSTOP-SETTINGS EC145 MULTIFUNCTIONSTEP LH LEFT: −155_ RIGHT: 80_ UP: 13_ DOWN: −105_ Location: HISL gimbal
APPROVED Rev. 4
9.2-14 − 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
EFFECTIVITY
Version 2 (alternative hardstop settings)
Placard:
HARDSTOP-SETTINGS EC145 MULTIFUNCTIONSTEP LH LEFT: −150_ RIGHT: 150_ UP: −18_ DOWN: −122_
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All
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EFFECTIVITY
ED
Location: HISL gimbal
9.2-14 − 8
APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
3
EMERGENCY AND MALFUNCTION PROCEDURES
3.1
CAUTION INDICATIONS
LL
ED
HISL LASER ON
O
Conditions/Indications
O
The laser should switch off automatically below 100 ft AGL.
C
NOTE
N TR
− The HISL laser function is switched on and the aircraft is operated below 80 ft.
O
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Procedure
− OFF
–
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N
1. LASER ON/OFF sw
O N
O N
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HISL IR ON
U
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Conditions/Indications
R
EFFECTIVITY
Before Helionix Maintenance Release 1
IN
ST
− The HISL IR function is on and the aircraft is operated below 500 ft.
R
EFFECTIVITY
After Helionix Maintenance Release 1
FO
− The HISL IR function is on and the aircraft is operated below 50 ft. EFFECTIVITY
CAUTION
All
BE AWARE WHERE BEAM IS POINTED WHEN OPERATING IN IR MODE IN CLOSE PROXIMITY TO PERSONS AS LOOKING INTO THE BEAM COULD RESULT IN EYE INJURY.
Procedure 1. Rad−Alt
− Monitor
2. HISL or SYS sw (depending on installation)
− OFF (unless used intentionally)
APPROVED Rev. 4
9.2-14 − 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
3.2
EMERGENCY LANDING Procedure If HISL is switched on: 1. STOW sw
− Press − Check searchlight extinguishes − Check HISL STOWED on ML
LL
NORMAL PROCEDURES
O
4
− Continue
ED
2. Emergency landing
O
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WARNING D MAKE CERTAIN THAT HISL HAS COOLED BEFORE HANDLING ON GROUND.
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D IGNITING THE HISL WHILE THE HELICOPTER IS ON THE GROUND MAY IGNITE DRY VEGETATION OR FLAMMABLE OBJECTS. AVOID STATIONARY FOCUSING AT OBJECTS WHILE ON THE GROUND.
EFFECTIVITY
O N
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D EVEN BRIEF EXPOSURE TO THE LIGHT BEAM COULD CAUSE SERIOUS DAMAGE TO EYES AND SKIN. DO NOT AIM THE LIGHT BEAM TOWARD PEOPLE, AIRCRAFT OR VEHICLES AT RANGES OF LESS THAN 165 FT (50 M). ALL, except civil aircraft operations of FAA registered helicopters.
R
Civil aircraft operations of FAA registered helicopters
FO
EFFECTIVITY
IN
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D THE IR LIGHT BEAM IS INVISIBLE AND POTENTIALLY HAZARDOUS TO THE EYES. DO NOT AIM THE LIGHT BEAM TOWARDS PEOPLE, AIRCRAFT OR VEHICLES AT A DISTANCE OF LESS THAN 50 FT (15 M) WHEN THE HISL IS OPERATED IN IR MODE. DO NO TEST OR OPERATE THE IR MODE ON GROUND WITH THE HISL SWITCHED ON.
EFFECTIVITY
D THE FAA HAS NOT ASSESSED THE EYE HAZARDS ASSOCIATED WITH IR SEARCHLIGHTS, AND THE FAA HAS NOT VALIDATED THE MANUFACTURER’S SAFETY OR HAZARD ASSESSMENTS.
All FAA registered helicopters. D THE FAA HAS NOT ASSESSED THE EYE HAZARDS ASSOCIATED WITH THE LASER FEATURE, AND THE FAA HAS NOT VALIDATED THE MANUFACTURER’S SAFETY OR HAZARD ASSESSMENTS.
EFFECTIVITY NOTE
9.2-14 − 10
All IR filter and laser pointer are inoperative if the respective safety dongles are not installed. APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
4.1
PREFLIGHT CHECK
4.1.1
Exterior check NOTE
The following checks shall be carried out before every flight with the HISL installed.
Multifunction step assy
− Condition
Searchlight quick-mount hardware
− Secured, condition
Dovetail mount
− Secured
searchlight
assembly
ED
to
− No excessive play
Searchlight support structure
− Condition
Searchlight glass front window
− Condition
Electrical cables
− Condition
Electrical connectors
− Tight
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Searchlight / dovetail connection
− Check for foreign objects
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Searchlight fan
APPROVED Rev. 4
9.2-14 − 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
4.1.2
Operational test NOTE D For full operational test, refer to the Trakka Corp. “Grip Hand Control Operation Guide” or to the “Trakka Control Panel Operation Guide”. D If not otherwise stated the switches mentioned below are located either on the HCU, on the HCCU or on the TCP, whichever is installed. If “HCU” or “HCU and HCCU” is / are installed
HISL sw (overhead panel)
− ARM
ED
EFFECTIVITY
POST takes 12 seconds for normal initialisation, extended POST takes 60 seconds for extended initialisation.
C
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NOTE
N TR
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− Wait until “P” displayed on grip hand controller display (POST completed)
− Press, check searchlight moves to deploy position
N
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DEPLOY sw
PY
− Check HISL EXTENDED on ML
C
O
− Check filter number on HCU displayed
O N
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STOW sw
− Check “P” on HCU display − Check HISL STOWED on ML − OFF
If TCP is installed
IN
EFFECTIVITY
ST
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HISL sw
− Press, check searchlight moves to stow position
FO
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SYS sw (control panel)
NOTE
− ON − “POST” is displayed on LED display while searchlight is initialising
POST takes 12 seconds for normal initialisation, extended POST takes 60 seconds for extended initialisation.
DEPLOY sw
− Press, check searchlight moves to deploy position − Check DEPLOY status LED on TCP illuminated − Check HISL EXTENDED on ML
DEPLOY status LED
9.2-14 − 12
− Check on APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
STOW sw
− Press, check searchlight moves to stow position − Check STOW status LED on control panel illuminated − Check HISL STOWED on ML
SYS sw
If TCP and HCU are installed
SYS sw (control panel)
− ON
ED
EFFECTIVITY
− OFF
N TR
O
LL
− “POST” is displayed on LED display while searchlight is initialising.
T
POST takes 12 seconds for normal initialisation, extended POST takes 60 seconds for extended initialisation.
N
O
NOTE
C
O
− Wait until “P” displayed on HCU display (POST completed)
− Press, check searchlight moves to deploy position
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DEPLOY sw
IN
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STOW sw
− Check filter number on HCU displayed − Check HISL EXTENDED on ML − Press, check searchlight moves to stow position − Check STOW status LED on TCP illuminated − Check “P” on HCU display − Check HISL STOWED on ML − OFF
FO
R
SYS sw
− Check DEPLOY status LED on control panel illuminated
EFFECTIVITY
APPROVED Rev. 4
All
9.2-14 − 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
4.2
HISL SEARCHLIGHT OPERATION CAUTION D THE INDICATIONS OF THE STANDBY MAGNETIC COMPASS MAY BE UNRELIABLE DURING SEARCHLIGHT OPERATION. D THE HISL IS INSTALLED QUITE CLOSE TO THE GROUND. DURING LANDINGS ON VERY UNEVEN TERRAIN, THE HISL MAY BE DAMAGED DUE TO GROUND CONTACT.
4.2.1
Switching on the system POST takes 12 seconds for normal initialisation, extended POST takes 60 seconds for extended initialisation.
HISL sw (overhead console)
O
If “HCU” or “HCU and HCCU” is / are installed − ARM
N TR
EFFECTIVITY
LL
ED
NOTE
If TCP is installed
PY
EFFECTIVITY
N
O
T
C
O
− Wait until “P” displayed on grip hand controller display (POST completed)
R
IN
ST
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SYS sw (control panel)
− ON or ARM as required − “POST” is displayed on LED display while searchlight is initialising. − Wait until “P” displayed on HCU display (POST completed)
All
FO
EFFECTIVITY
− “POST” is displayed on LED display while searchlight is initialising.
If TCP and HCU are installed
O N
EFFECTIVITY
− ON or ARM as required
O N
LY
–
C
O
SYS sw (control panel)
DEPLOY sw
− Press − Check HISL EXTENDED on ML
HISL/MIRROR/S/L-LT sw (collective lever) 4.2.2
− HISL
Inflight operation LAMP sw
− Press, check lamp turns on − Check HISL on ML
Joystick/directional control sw (TCP, HCU or − Operate as desired collective grip)
9.2-14 − 14
APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
If directional control of the search/landing light is activated on the collective grip, directional control of the HISL is still possible by means of the HISL HCU and/or joystick on the TCP.
NOTE
ZOOM toggle sw (HCU, TCP) or HISL FOCUS sw (if installed on collective lever)
− Operate as desired
FILTER SEL/ENG sw
− Operate as desired
DIM sw
− Operate as desired
ED
EOS and searchlight slave function
O
With SLAVE ON and the EOS installed, the searchlight is automatically boresighted to the EOS platform. The horizontal and vertical control of the searchlight can only be performed using the EOS controls.
O
N TR
NOTE
− Operate as desired
LL
SLAVE sw
O
T
C
Whilst in slave mode any direction control e.g. joystick on TCP or HCU or collective control will trim the searchlight therefore the searchlight wiil follow the EOS with an offset.
FO
R
IN
ST
R
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TI
O N
O N
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–
C
O
PY
N
As the searchlight rotating range is limited the searchlight is only slaved in its own range limits. If the EOS continues beyond this limits the searchlight will stop at the limit. If EOS re-enters the rotating range of the searchlight, the searchlight will immediately start turning until it is boresighted again to the EOS.
APPROVED Rev. 4
9.2-14 − 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
Switching off the system CAUTION
NOTE
EFFECTIVITY
THE HISL POWER SHOULD NOT BE SWITCHED OFF FOR AT LEAST TWO MINUTES AFTER EXTINGUISHING THE LAMP TO ALLOW THE COOLING FAN TO PROPERLY COOL THE LAMP ASSEMBLY.
The HISL shall be in STOW position before landing.
If “HCU” or “HCU and HCCU” is / are installed
STOW sw
− Press
O
LL
− Check lamp off
ED
4.2.3
N TR
− Check searchlight stow position
moves
to
O
− Check “P” on HCU display
T
C
− Check HISL STOWED on ML − OFF
O
If TCP is installed
C
EFFECTIVITY
PY
N
O
HISL sw (overhead panel)
R
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TI
O N
O N
LY
–
STOW sw
R
IN
ST
SYS sw (control panel)
FO
HISL sw (overhead panel)
9.2-14 − 16
− Press − Check lamp off − Check searchlight stow position
moves
to
− Check STOW status LED TCP illuminated − Check HISL STOWED on ML − OFF − Check STOW status LED TCP off − OFF
APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
EFFECTIVITY
If TCP and HCU are installed
STOW sw
− Press − Check lamp off − Check searchlight stow position
moves
to
− Check STOW status LED TCP illuminated − Check “P” on HCU display SYS sw (control panel)
ED
− Check HISL STOWED on ML − OFF
N TR
O
LL
− Check STOW status LED TCP off − Check “P” on HCU display
C
O
All
5.1
RATE OF CLIMB
N
PERFORMANCE DATA
C
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5
O
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EFFECTIVITY
O N
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–
All results obtained from the respective diagram, contained in section 5 of the basic Flight Manual, are to be corrected as follows: GM t 2600 kg:
Subtract 30 ft/min
R
The reduction in climb rate is not depending on power settings.
FO
R
IN
ST
NOTE
Subtract 35 ft/min
U
C
GM w 3200 kg:
TI
O N
2600 kg v GM t 3200 kg:
Subtract 45 ft/min
APPROVED Rev. 4
9.2-14 − 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
6
MASS AND BALANCE Refer to Equipment List entries in Section 6 of the basic Flight Manual.
7
SYSTEM DESCRIPTION
7.1
HISL
ED
The HISL assembly (see Fig. 1) comprises a lamp assembly mounted in a gimbal, a power conditioning interface unit (PCIU) and a control interface unit (CIU). The PCIU and CIU are mounted in a power/control box. The gimbal and the power/control box are mounted on a multifunction carrier on the left side of the helicopter. The mounting structures provide a quick disconnection of the gimbal and power/control box.
N TR
O
LL
The HISL is equipped with a high-intensity (800 Watt) xenon short arc lamp. Several filters for white, red, and yellow light and a zoom mechanism are installed inside the lamp assembly. Further optional filters can be installed to use the HISL in IR mode.
C
O
The IR mode may be disabled by removing an IR safety dongle (mandatory for civil aircraft operations of FAA registered helicopters).
T
The power/control box is the central power and control hub for the entire system.
PY
N
O
The control of the HISL is provided by switches on the collective grips (see Fig. 2), by an HCU in the center console (see Fig. 6 or Fig. 8), and, if installed, by the HCCU (see Fig. 4).
C
O
The searchlight receives power from the electrical master box No.2 via a 50A fuse.
O N
LY
–
The control functions are supplied by the essential bus II via one circuit breaker in the overhead panel. EFFECTIVITY If “HCU” or “HCU and HCCU” is / are installed
If TCP or TCP and HCU is/ are installed
TI
EFFECTIVITY
O N
The HISL is powered by switching the HISL sw to ARM. The HISL performs a power-on self test (approx. 12 sec).
R
U
C
The HISL is powered by switching the SYS sw to ON. The LED display will display “POST” on the top line and the HISL performs a power-on self test (approx. 12 sec). EFFECTIVITY
IN
ST
To allow to turn on the lamp the SYS sw has to be set to ARM. All
FO
R
An extended power-on self test (approx. 60 sec) is launched automatically if an event during the previous HISL operation may have caused a loss of the elevation / azimuth position of the HISL. Pushing LAMP sw turns the lamp on, respectively off. The HISL can be switched off and placed in the STOW position by pressing the STOW sw on the HCU, the HCCU or TCP on center console or on the collective lever. The default STOW position is looking forward. CAUTION
9.2-14 − 18
CAUTION WHEN USING STOW POSITIONS OTHER THAN THE DEFAULT HORIZONTAL POSITION, THE CLEARANCE BETWEEN THE HISL AND THE GROUND MAY BE SIGNIFICANTLY REDUCED. IN THIS CASE, DAMAGE MAY OCCUR WHEN LANDING ON UNEVEN TERRAIN OR SLOPES. MANUFACTURER’S DATA APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
O N
BKD2_FLH_0267_R
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
In combination with the emergency floatation system (EFS), the HISL is automatically switched off when the EFS will be filled.
U
C
TI
1
ST
R
2
1 Power/control box 2 Gimbal 3 Lamp assembly
IN
3
FO
R
Maximum rotating range, operational limits (relative longitudinal axis): EFFECTIVITY Left: Up:
−151_ 9_
EFFECTIVITY Left: Up:
Version 1 (softstop settings) Right: Down:
Version 2 (softstop settings)
−146_ −14_
EFFECTIVITY
76_ −101_
Right: Down:
146_ −118_
All
Fig. 1 MANUFACTURER’S DATA APPROVED Rev. 4.1
HISL − typical installation
9.2-14 − 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
7.1.1
Controls on collective lever 1
2
S/L LT M I R HISL
CABLE CUT
DIM/FOC
L D G L T
S/L LT ON
COLLECTIVE LEVER CONTROL PANEL PILOT / COPILOT (typical)
OFF
STOW
3
BAMBI IR/ VIS DUMP
LY
–
C
O
PY
BKD2_FLH_0014_R
N
O
T
C
O
N TR
O
LL
ED
BEEP TRIMORIENT CTL
Controls on collective lever − typical installation
O N
O N
Fig. 2
FUNCTION
1
HISL/ MIRROR/ S/L-LT selector sw
HISL
Selects the HISL for directional control by collective 4-way switch labeled ORIENT CTL and for the DIM/FOC/STOW sw.
2
DIM/FOC/ STOW sw
DIM/FOC forward
HISL lamp beam increases.
DIM/FOC backwards
HISL lamp beam decreases.
STOW (press)
HISL lamp and laser turns off and HISL moves to stow position.
FWD/AFT
Controls vertical elevation axis of the searchlight.
L/R
Controls azimuth axis of the searchlight.
FO
R
IN
ST
R
U
C
TI
SWITCH/LIGHT POSITION
3
4-way directional control sw ORIENT CTL
Fig. 3
9.2-14 − 20
Functions of controls on collective grips MANUFACTURER’S DATA APPROVED Rev. 4.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
7.1.2
Controls on HCU
A
12 1
2
3 13
4
10
5
LL
11
ED
A
8
N TR
O
9 16
O
6
T
C
14
N
O
7
Fig. 4
HCU − typical installation
FO
R
IN
ST
R
U
C
TI
O N
EC135_FLH_0454_R
O N
LY
–
C
O
PY
15
1
SWITCH/LIGHT FUNCTION SLAVE sw
Engages/disengages EOS system slaving. Short press to toggle between slave/non-slave mode. The slave LED will be on to indicate slave mode. Press for a minimum of 3 seconds to activate slave calibration mode. The slave LED will flash during calibration mode. Press once to exit slave calibration mode. During slave or slave calibration mode hold SLAVE sw down for a minimum of 3 seconds to save current calibration position. New settings will be confirmed.
MANUFACTURER’S DATA APPROVED Rev. 4.1
9.2-14 − 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
2
Seven segment Displays status and error messages. display Status messages: − during power-up: combination of En/Er and An/Ar flashing twice to indicate joystick control direction of elevation and azimuth − rotating segments when lamp is starting − 1 up to 6 for selected filter − P flashing while moving into stow position − P steady when in stow position
LL
N TR
O
C
T
O
N
PY
Not for FAA registered helicopters with disabled laser pointer, not for civil aircraft operations of FAA registered helicopters Indicates laser status: On: Laser is on Off: Laser is off.
–
Laser LED
All
O N
EFFECTIVITY
O N
LY
3
C
O
EFFECTIVITY
POST not completed Lamp will not start Over temperature fault Under voltage fault Filter mechanism failed Gimbal will not move in elevation and/or azimuth Camera not found
O
0 1 2 3 4 5 C
ED
Error messages: − “E” alternatively flashing with:
DIM sw
5
STOW sw
Brightens or dims the searchlight by changing lamp power. Press switch once to dim the searchlight. Press switch again to revert to full brightness.
FO
R
IN
ST
R
U
C
TI
4
6
FILTER SEL/ENG sw
Moves searchlight to stow position and turns lamp and laser pointer off. Press for a minimum of 3 seconds to set current position as new stow position. This is only possible using the STOW sw on the Grip Controller. Additionally the HISL sw on Co-Pilot side has to be switched and held in CONF Position (open Flip−Guard first). New settings will be confirmed. Selects and then engages the required filter. Press switch up to scroll through filter numbers. Filter number will flash on seven segment display. When required filter number is displayed, press the switch down to engage filter. If filters are scrolled but not engaged within 5 seconds, the system will remain at the current selection.
9.2-14 − 22
MANUFACTURER’S DATA APPROVED Rev. 4.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
LAMP sw
Turns lamp on or off.
8
Joystick
Controls azimuth and vertical elevation axis of searchlight. In slave mode:Trimms the searchlight with EOS (change offset to EOS).
9
Unit status LED Displays the system status: On: System is deployed Off: System is not deployed Flashing: System is deploying
10
DEPLOY sw
Deploys the searchlight system. Press for a minimum of 3 seconds to set current position as new deploy position. New settings will be confirmed.
11
Lamp ON/OFF LED
Indicates system status. On: Lamp is on Off: Lamp is off. Flashing off briefly: searchlight in reduced power mode Flashing: Lamp starting period
12
Slave LED
Indicates camera slaving mode status. On: Slave mode is on Off: Slave mode is off Flashing: Slave calibration mode
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
7
Not for FAA registered helicopters with disabled laser pointer, not for civil aircraft operations of FAA registered helicopters
O N
Turns the laser pointer on or off. NOTE
If the TCP is installed the TCP LASER sw has to be switched ON for operation of the laser.
R
U
C
TI
LASER ON/ OFF sw
O N
13
LY
EFFECTIVITY
All
IN
ZOOM toggle sw
Zooms lamp beam in and out.
Panel dim sw
Dims facia panel back lighting. Holding FILTER sw in ENG position and then operate Panel dim sw activates ”day” mode intensity. Holding FILTER sw in ENG position and press DIM sw on the front side activates the grip hand controller lamp test.
FO
R
14
ST
EFFECTIVITY
15
Fig. 5
HCU functions and indications
NOTE D Unit status LED, Lamp On LED and Seven segment display will flash off once to indicate that new settings have been confirmed. MANUFACTURER’S DATA APPROVED Rev. 4.1
9.2-14 − 23
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
Controls on HCCU 4
LAMP ON/OFF
STOW
DIM
FILTER VIS
FILTER NO
IR
LASER ON
OPER
OPER OFF
O
HISL
SLAVE ON
ED
DEPLOY
6
5
LL
3
2
BKD2_FLH_0270_R
1
HCCU − typical installation
C
O
Fig. 6
N TR
7.1.3
FUNCTION
STOW/ DEPLOY sw
DEPLOY
HISL moves automatically to the deploy position
STOW
HISL switches off the lamp and laser pointer automatically and moves automatically to the stow position. This procedure cannot be interrupted.
2
LAMP ON / OFF sw
ON / OFF
If Searchlight lamp is off then it is switched on else off.
3
FILTER VIS VIS sw (only active if a HISL with an IR filter is installed)
O
N
PY
LY
O N
The lowest filter position with a visible filter installed is selected and the filter wheel moves to this filter position in the shortest way (forward or backward). In normal case the lowest filter position which is equipped with no filter (white light) is filter position 1, but this depends on Searchlight configuration.
O N TI C
U
R ST 9.2-14 − 24
FO
FILTER NO sw
R
IN
IR HISL
4
–
C
O
1
T
SWITCH/LIGHT POSITION
The lowest filter position with an IR filter installed is selected and the filter wheel moves to this filter position in the shortest way.
n (UP)
The filter position is incremented by 1. That means the filter wheel turns one step forward.
o (DOWN)
The filter position is decremented by 1. That means the filter wheel turns one step backward.
MANUFACTURER’S DATA APPROVED Rev. 4.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
ON
Searchlight is in slave mode to an EOS. Trimming is possible with the joystick of the grip hand controller or the ORIENT CTL switch of the collective. Saving (=Calibration position) of the trimming position is not possible. Controls via SLAVE switch of the grip hand controller are ignored.
OPER
If Searchlight was in slave mode (SLAVE ON position) then the slave mode is deactivated. In OPER position the control of the SLAVE ON/OFF function is given to the grip hand controller (OPERator)
ON
Turns the laser pointer on, whilst this input is active the laser cannot be turned off by the grip hand controller.
OPER / OFF
The control of the laser function is given to the grip hand controller (OPERator). If in addition the LASER switch on grip hand controller is. − in OFF position: The laser pointer is off.
LL
O
LASER ON sw
ED
SLAVE ON sw
O
T
C
O
6
FUNCTION
N TR
5
SWITCH/LIGHT POSITION
PY
N
− in ON position: The laser pointer is on. For test on ground additionally the HISL sw on Co−Pilot side has to be switched and held in LSR−TEST Position (open Flip−Guard first).
–
C
O
NOTE
O N
Controls on TCP
O N
7.1.4
HCCU functions and indications
LY
Fig. 7
U
C
TI
The Trakka control panel with integrated joystick allows full operational control of the Trakka searchlight system and provides an interface to an optional hand grip controller. 2
5
4
3
TRAKKA
ON
FO
OFF
OFF
STOW
SLAVE
BKD2_FLH_0490_R
13
ARM ON
IR
14
SYS
LASER
R
IN
ST
R
1
LAMP
WIDE NAR
ZOOM
12
11 Fig. 8
MANUFACTURER’S DATA APPROVED Rev. 4.1
10
9
DIM
6
ENT SEL
FILTER
8
7
TCP − typical installation
9.2-14 − 25
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
SWITCH/LIGHT POSITION
FUNCTION
1
IR MODE LED
Illuminates to indicate that an IR filter has been selected
2
LASER status LED
Indicates laser status: On: Laser is on Off: Laser is off.
3
Laser ON / OFF sw
OFF
Turn laser pointer OFF
ON
Turn laser pointer ON If the HCU is installed the HCU LASER sw has to be switched ON for operation of the laser.
O
N TR
SYS ARM / ON / OFF sw
OFF
System power is OFF
ON
System power is turned ON but the lamp is not armed.
ARM
Lamp is armed and can be turned on.
O
5
Displays system status, filter selection and error messages
C
Alpha-numeric LED display
N
Primary function: Press to reduce lamp power output to 70-75% of full power. Press switch again to return to full power.
PY
DIM sw
–
C
O
6
O
T
4
LL
ED
NOTE
R
LAMP sw
FO
7
IN
ST
R
U
C
TI
O N
O N
LY
NOTE
9.2-14 − 26
The SYS switch must be in the ARM position to enable the lamp to turn on. If the switch is not in the ARM position a not armed message will display.
Alternative function: Hold FILTER sw in ENT position and press LAMP sw to activate the control panel lamp test. All LED annunciators and all pixels in the alpha-numeric LED display will illuminate with day mode brightness. Primary function: Press to turn the lamp on. When lamp is turned on the LAMP LED will be on. Press again to switch lamp off. Alternative function: Hold FILTER sw in ENT position and press LAMP sw to display control panel’s run time in hours.
MANUFACTURER’S DATA APPROVED Rev. 4.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
FUNCTION
FILTER ENT / SEL sw
SEL
Increments the filter number and enters the filter select mode. Scrolling is possible by pressing SEL again.
ENT
Primary function: When in filter select mode moving the FILTER switch into the ENT position engages the new filter number and exits the filter select mode. Alternative function: When not in filter select mode holding the FILTER switch in the ENT position enables alternative function selection of the other switches. Primary function: Press to enable/disable the EOS slaving mode. When enabled the SLAVE LED will be on. Alternative function:
O
SLAVE sw
O
T
C
O
N TR
9
LL
ED
8
SWITCH/LIGHT POSITION
O
PY
N
Not in slave or calibration mode: Hold FILTER sw in ENT position and press SLAVE sw to enter CALIBRATION MODE.
O N
LY
–
C
In slave or calibration mode: Hold FILTER sw in ENT positon and press SLAVE sw to save current calibration position (offset between HISL and EOS)
ZOOM WIDE WIDE / NAR sw NAR
TI
O N
10
DEPLOY sw
FO
R
IN
ST
R
U
C
11
12
Joystick
MANUFACTURER’S DATA APPROVED Rev. 4.1
Beam will zoom out (Wide field of view) Beam will zoom in (Narrow field of view) Primary function: Press to deploy the searchlight to the pre-defined deploy position. DEPLOYING status message on the display whilst searchlight is moving to the DEPLOY position. When system has DEPLOYED, the DEPLOY LED annunciator will be on. Alternative function: Hold FILTER sw in ENT position and press DEPLOY sw to set current position as new deploy position. Deflect in any direction to move the searchlight in the corresponding direction. The greater the pressure on the joystick, the faster the gimbal movement.
9.2-14 − 27
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
STOW sw
Primary function: Press to stow the searchlight in the pre-defined stow position. The lamp will turn off if it has been left on. STOWING status message on display whilst searchlight is moving to the STOW position. When in STOW position the STOW LED annunciator will be on. Alternative function: Hold FILTER sw in ENT position and press STOW sw to set current position as new stow position. This is only possible if HISL sw on Co-Pilot side is switched and held in CONF Position (open Flip−Guard first).
Status LED
Illuminates if corresponding operation has been finished (e.g. DEPLOY)
N TR
O
O
HISL Master List messages
N
7.1.5
TCP functions and indications
C
Fig. 9
T
14
O
LL
ED
13
Description
O
PY
ML cautions
HISL laser is on below 80ft
–
C
HISL LASER ON
EFFECTIVITY
O N
LY
HISL IR ON
Before Helionix Maintenance Release 1
EFFECTIVITY
IN
ST
R
U
C
TI
O N
HISL IR is on below 500ft
FO
R
ML information messages
EFFECTIVITY
All
Description HISL lamp is on
HISL LASER
HISL laser is on
HISL STOWED
9.2-14 − 28
HISL IR is on below 50ft
HISL
HISL IR
After Helionix Maintenance Release 1
HISL lamp is on in IR mode HISL is stowed
HISL EXTENDED
HISL is extended and operational
HISL ON+LASER
HISL laser and lamp are on
HISL IR+LASER
HISL laser and lamp are on in IR mode MANUFACTURER’S DATA APPROVED Rev. 4.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
7.1.6
HISL Line−of−Sight display on EuroNav 7 DMAP The HISL line of sight can be shown on the EuroNav 7 DMAP.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
For more details refer to the OEM manual.
Fig. 10
HISL Line−of−Sight display on EuroNav 7 DMAP − typical
MANUFACTURER’S DATA APPROVED Rev. 4.1
9.2-14 − 29
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
7.2
LASER POINTER An optional IR laser pointer can be installed on the lamp assembly housing.
O
T
Laser safety panel − typical installation
N
Fig. 11
C
O
N TR
O
LL
ED
Depending on configuration, the laser pointer can be enabled by installing a laser safety dongle, or by inserting a laser safety key in the laser safety panel (see Fig. 11) and switching it to ARMED.
C
O
PY
With the laser pointer switched on, the view direction of the searchlight can be observed with night vision goggles, while the searchlight lamp is off. The LASER status LED on the HCU and on the TCP are on and the HISL LASER is on.
TI
O N
O N
LY
–
The laser pointer is coupled to the radar altimeter and will be automatically switched off below 100 ft AGL. The LASER status LED on the HCU and on the TCP are off and HISL LASER is off. Above 100 ft AGL, the laser pointer will be automatically switched on again if it was not switched off on the HCU or TCP, and the LASER status LED and the HISL LASER is on.
FO
R
IN
ST
R
U
C
For test on ground additionally the HISL sw on Co-pilot side has to be switched and held in LSR−TEST position (open the flip guard first).
Fig. 12 HISL − CONF/NORM/LSR−TEST sw (located in the footwell (RH) of the co-pilot ) − typical installation
9.2-14 − 30
MANUFACTURER’S DATA APPROVED Rev. 4.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HIGH INTENSITY SEARCHLIGHT (HISL) (LH MOUNTED)
7.2.1
Laser pointer limitations The laser pointer must not be operated below 100ft AGL.
7.2.2
Laser pointer Pre-flight check A laser pointer pre-flight check is to be performed acc. to the Trakka Corp. “Grip Hand Control Operation Guide” or to the “Trakka Control Panel Operation Guide” before each flight with laser pointer operation intended. Laser pointer operation THE IR LASER POINTER BEAM IS INVISIBLE AND HAZARDOUS TO THE EYES. DO NOT AIM THE TOWARDS PEOPLE, AIRCRAFT OR VEHICLES AT A LESS THAN 98 FT (30 M). DO NOT TEST OR OPERATE POINTER ON GROUND.
POTENTIALLY LASER BEAM DISTANCE OF THE IR LASER
O
N TR
O
LL
WARNING
ED
7.2.3
− Switch on/off as desired
C
LASER ON/OFF sw
PY
N
O
T
− LASER status LED and HISL LASER is on if laser pointer is in operation
C
O
NOTE D The laser pointer is switched off automatically below 100 ft AGL.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
D Before switching off the HISL on ground, check that the laser pointer is switched off on the HCU and/or on the TCP/HCCU.
MANUFACTURER’S DATA APPROVED Rev. 4.1
9.2-14 − 31/(9.2-14 − 32 blank)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WIRE STRIKE PROTECTION SYSTEM
FMS
9.2-15
SUPPLEMENT FOR
N TR
O
LL
ED
WIRE STRIKE PROTECTION SYSTEM
T
C
O
This supplement shall be attached to the BK117 D-2 flight manual (subsection 9.2) when the WIRE STRIKE PROTECTION SYSTEM is installed.
N
O
System/Equipment Designation
All
For approving authorities and respective dates of approval refer to the log of supplements.
FO
R
IN
ST
R
U
C
TI
O N
NOTE
O N
LY
–
C
O
PY
Wire strike protection system
Effectivity
Date: DEC 11, 2015
Approved by EASA
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-15 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WIRE STRIKE PROTECTION SYSTEM
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are new, revised or deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the record of supplement-revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
0
EASA
R
9.2-15 -2
1
EASA
R
9.2-15 -3
1
EASA
9.2-15 -4
0
EASA
App.
Rev.No
Rem
App.
0
O
Page
Page
Rev.No
Rem
PY
9.2-15 -5
Rem
N
Rev.No
Rev.No
T
LEP – manufacturer‘s data (part 2): Page
Page
O
9.2-15 -1
Rev.No
LL
Page
N TR
App.
O
Rev.No
C
Page
ED
LEP – approved (part 1):
LY
–
C
O
/-6 blank
O N
O N
LOG OF REVISIONS
C
TI
FIRST ISSUE
(see page 9.2-15-1)
1
(see entry below)
FO
R
IN
ST
REVISION
R
U
ORIGINAL
Date: JUL 23, 2018
Approved by EASA:
EASA approval no.: 10066279
9.2-15 – 2
APPROVED Rev. 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WIRE STRIKE PROTECTION SYSTEM
1
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual.
2
LIMITATIONS
2.1
COMPATIBILITY
O
N TR
Radome (WXR RDR 2000, refer to FMS 9.2–8)
N C
O
EMERGENCY AND MALFUNCTION PROCEDURES
–
3
All
PY
EFFECTIVITY
O
T
–
Up to S/N 20229, except S/N 20195, S/N 20212, S/N 20225
O
EFFECTIVITY
Radome (WXR RDR 1600, refer to FMS 9.2–30)
C
–
LL
ED
The protective capability of the wire strike protection system is significantly degraded in combination with:
FO
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IN
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In the event of a wire strike, LAND AS SOON AS POSSIBLE and perform engine shutdown. Do not attempt further flight until an inspection and repair is carried out by qualified personnel.
APPROVED Rev. 1
9.2-15 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WIRE STRIKE PROTECTION SYSTEM
4
NORMAL PROCEDURES
4.1
PREFLIGHT CHECK
4.1.1
Exterior Check – Condition, security of attachment (apply hand pressure to the component to check for looseness), deformation or mechanical damage.
Lower cutter assembly
– Condition, evidence and indication of ground contact
Cutter blades
– Condition, evidence and indication of wire strike (paint chips on deflector; damaged, missing or broken protective coating on blades, notches, etc).
If a wire strike has occurred, inspect the wire strike protection system fixed provisions (upper and lower) as well as surrounding cell structure for evidence of damage. Maintenance action is required (refer to appropriate BK 117 D-2 maintenance manual).
C
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NOTE
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ED
WSPS components
LY
–
DURING TRANSITION TO FORWARD FLIGHT, AN EXCESSIVE NOSE-LOW ATTITUDE MAY RESULT IN THE WSPS LOWER CUTTER CONTACTING THE GROUND. WHEN TAKING OFF AND LANDING ON UNEVEN TERRAIN, EXTREME CARE SHOULD BE EXERCISED TO PREVENT CONTACT OF LOWER CUTTER WITH THE GROUND.
R
PERFORMANCE DATA
ST
5
U
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O N
O N
WARNING
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No change to the basic flight manual data.
9.2-15 – 4
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WIRE STRIKE PROTECTION SYSTEM
6
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
7
SYSTEM DESCRIPTION
ED
The wire strike protection system consists of an upper cutter assembly mounted on the roof, a lower cutter assembly mounted below the nose, windshield wiper assambly (optional) and two skid gear deflectors mounted to the skid tubes and a windshield wiper post deflector to prevent threading of wires at the driveshaft of the windshield wiper.
C U
skid gear deflector
BKD2_FLH_0077_R
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upper cutter assy
TI
O N
O N
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–
C
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PY
N
O
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C
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O
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The wire strike protection system is designed to provide a measure of protection against horizontally strung wire impact between cockpit roof and main rotor blades and between bottom shell and skids. The protection will be achieved by deflecting or cutting the wires. Cutting the wires will be done by rigidly mounted converging blades using the kinetic energy of the flying helicopter. Deflecting the wires will be done by the skid gear deflectors and the windshield wiper post deflector.
lower cutter assy
Fig. 1
MANUFACTURER’S DATA APPROVED Rev. 0
Wire strike protection system – typical installation
9.2-15 – 5/(9.2-15 – 6 blank)
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N
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FMS
9.2-16
SUPPLEMENT FOR
ED
COMFORT SEAT INSTALLATION
N TR
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System/Equipment Designatione
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Effectivity
T
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PY C
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NOTE
O N
O N
O
N
O
9.2-16 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
LIST OF EFFECTIVE PAGES NOTE
N R D
Page
R
R
Rev.No.
Rem
Page
Rev.No.
Rev.No.
Rem
Page
Rem
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Rem
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Rev.No.
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LEP – approved (part 1):
Rem
Page
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Rev.No.
Rem
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Rev.No.
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Page
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LEP – manufacturer‘s data (part 2):
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LOG OF REVISIONS
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FIRST ISSUE
IN
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9.2-16 – 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
GENERAL
LIMITATIONS
OPERATIONAL LIMITATIONS
O
COMPATIBILITY
N TR
LL
ED
C
O
C
–
NOTE
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N
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CONFIGURATION REQUIREMENTS
O N
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PLACARDS AND DECALS
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EFFECTIVITY
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O N
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IN
Placard:
FO
TRAY TABLE MUST BE FOLDED UPWARDS FOR TAKE OFF AND LANDING Location:
EFFECTIVITY
EMERGENCY AND MALFUNCTION PROCEDURES
9.2-16 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
NORMAL PROCEDURES
PREFLIGHT CHECK WARNING
LL
ED
NOTE
O
Exterior check, fuselage RH side:
O
T
PERFORMANCE DATA
N
C
O
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9.2-16 – 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
MASS AND BALANCE
SYSTEM DESCRIPTION
ED
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N
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SEAT LAYOUT
CAUTION
–
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O N
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9.2-16 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
PASSENGER SEAT CONFIGURATION (STANDARD 8 - PASSENGERS)
NOTE
LL O
ED
Club version – configuration and passenger seats C.G.
N TR
* )
O
NOTE
PY
N
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* * * * * * * * *
– LY O N
O N
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*
Y–BL
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ST
*
IN
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FO
X–STA
C
CG of passengers
9.2-16 – 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
N TR
O
All forward facing version – configuration and passenger seats C.G.
N
PY
O
T
C
ED
*
LL
*
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*
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Y–BL
C
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X–STA
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CG of passengers
LY
O N
–
C
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9.2-16 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
PASSENGER SEAT CONFIGURATION (STANDARD 6 - PASSENGERS)
LL
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ED
Club version – configuration and passenger seats C.G.
T
C
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PY
N
O
NOTE D *)
–
C
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D * )
* * * * * * *
O N
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*
ST
*
Y–BL
IN
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FO
X–STA
LY
CG of passengers
9.2-16 – 8
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
All forward facing version – configuration and passenger seats C.G.
ED
* * *
N TR C T
O N
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PY O C
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O N
Y–BL
TI
X–STA
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CG of passengers
O
LL
NOTE D * )
9.2-16 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
PASSENGER SEATS CONFIGURATION (OFFSHORE) Variant 1 (8 Pax, main aisle right side) – configuration and passenger seats C.G.
O
C
N
O
T
O
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LL
ED
X–STA
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LY O N
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–
O N
O
Y–BL
PY
C.G. of passengers
R
ST
FO
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IN
U
9.2-16 – 10
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Variant 2 (8 Pax, main aisle left side) – configuration and passenger seats C.G.
N
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O N
PY
C
Y–BL
–
LY
O
O N
O
C
X–STA
T
C.G. of passengers
O
LL
O
ED
N TR
9.2-16 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Variant 3 (4 Pax, forward seat left side) – configuration and passenger seats C.G.
ED
O
T
N
O
PY
Y–BL
O
X–STA
C
C.G. of passengers
N TR
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–
C
O N
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Variant 4 (4 Pax, forward seat right side) – configuration and passenger seats C.G.
TI
O N
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IN
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FO
C.G. of passengers
X–STA
Y–BL
9.2-16 – 12
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Variant 5 (4 Pax, main aisle right side) – configuration and passenger seats C.G.
ED
LL
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–
C
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PY
O
Y–BL
C
X–STA
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C.G. of passengers
N TR
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Variant 6 (4 Pax, main aisle left side) – configuration and passenger seats C.G.
TI
O N
ST
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IN
FO
C.G. of passengers
X–STA
Y–BL
9.2-16 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Variant 7 (5 Pax, main aisle right side) – configuration and passenger seats C.G.
O
C
X–STA
N TR
C.G. of passengers
O
LL
ED
O N
Variant 8 (5 Pax, main aisle left side) – configuration and passenger seats C.G.
O N
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Y–BL
IN
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C.G. of passengers
X–STA
Y–BL
9.2-16 – 14
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLIDING DOOR JETTISONING
FMS
9.2-19
SUPPLEMENT FOR
N TR
O
LL
ED
SLIDING DOOR JETTISONING
C
O
This supplement shall be attached to the BK 117 D-2 Flight Manual (Section 9.2) when the kit for Sliding door jettisoning is installed. System/Equipment Designation
O
T
Effectivity
O
All All
O N
For approving authorities and respective dates of approval refer to the log of supplements.
FO
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NOTE
O N
LY
–
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Installation jettisoning sliding doors
PY
N
Jettisoning sliding doors
Date: DEC 11, 2015
Approved by EASA
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-19 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLIDING DOOR JETTISONING
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. LEP – approved (part 1): Page
9.2-19 -1
0
EASA
9.2-19 -2
0
EASA
9.2-19 -3
0
EASA
9.2-19 -4
0
EASA
Rev.No.
App.
Rev.No.
Rem
Page
Page
Page
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Rem
Rev.No.
Rem
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9.2-19 -5
App.
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Rev.No.
N TR
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Rev.No.
ED
App.
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Rev.No.
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–
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LOG OF REVISION
O N
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FIRST ISSUE
(see page 9.2-19–1)
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ORIGINAL
9.2-19 – 2
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLIDING DOOR JETTISONING
1
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
2
LIMITATIONS Sliding door jettison is only allowed after touchdown.
ED
PLACARDS AND DECALS
LL
2.1
N TR
O
Placard:
EMERGENCY EXIT
N
O
T
C
O
PULL EMERGENCY HANDLE TO FULL STOP TURN DOOR HANDLE AT LEAST 90_ PUSH DOOR OUTWARDS
C
O
PY
Location: Sliding doors inside
LY
–
Placard:
O N
EMERGENCY EXIT
U
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TI
O N
PULL EMERGENCY HANDLE TO FULL STOP TURN DOOR HANDLE AT LEAST 90_ TOWARDS THE “OPEN” POSITION PULL DOOR OUTWARDS
FO
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IN
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Location: Sliding doors outside
APPROVED Rev. 0
9.2-19 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLIDING DOOR JETTISONING
3
EMERGENCY AND MALFUNCTION PROCEDURES No change in the basic Flight Manual data.
4
NORMAL PROCEDURES
4.1
PREFLIGHT INTERIOR CHECK – Check correct safety wired
Rear sliding door
– Check correct position of red marked logging pin (most forward position)
LL
O N TR C
PERFORMANCE DATA
T
5
To be checked before each flight
O
L
position and
ED
Emergency handle of jettisoning device
FO
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O N
O N
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–
C
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PY
N
O
No change in the basic Flight Manual data.
9.2-19 – 4
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SLIDING DOOR JETTISONING
6
MASS AND BALANCE
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N
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Refer to Equipment List entries in Section 6 of the basic Flight Manual.
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-19 – 5/(9.2-19 – 6 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL LOUDSPEAKERS
FMS
9.2-20
SUPPLEMENT FOR
N TR
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ED
EXTERNAL LOUDSPEAKERS
T
C
O
This supplement shall be attached to the BK117 D-2 flight manual (subsection 9.2) when the EXTERNAL LOUDSPEAKERS is installed. System/Equipment Designation
N
O
Effectivity All
For approving authorities and respective dates of approval refer to the log of supplements.
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O N
NOTE
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External loudspeakers
Date: DEC 11, 2015
Approved by EASA
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-20 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL LOUDSPEAKERS
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are new, revised or deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the record of supplement-revisions as necessary. LEP – approved (part 1): App.
Page
9.2-20 -1
0
EASA
9.2-20 -4
9.2-20 -2
0
EASA
9.2-20 -3
0
EASA
Rev.No.
App.
0
EASA
Rev.No.
Rem
Page
Rev.No.
App.
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Rev.No.
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9.2-20 -6
0
Page
Rev.No.
Rem
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9.2-20 -5
Rem
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Rev.No.
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LEP – manufacturer‘s data (part 2):
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–
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FIRST ISSUE (see page 9.2-20-1)
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ORIGINAL
9.2-20 – 2
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL LOUDSPEAKERS
1
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual.
LIMITATIONS Maximum continuous siren operating time
EMERGENCY AND MALFUNCTION PROCEDURES
4.1.1
Exterior check
O
PREFLIGHT CHECK
C
4.1
O
PY
N
O
T
NORMAL PROCEDURES
– Tightened
TI
– OFF
R
BEFORE PERFORMING A SYSTEM CHECK BE SURE NO ONE WILL BE DANGEROUSLY SURPRISED BY THE LOUD AUDIO FROM THE EXTERNAL LOUDSPEAKER SYSTEM.
IN
ST
CAUTION
U
C
System check
O N
POWER sw (control unit) 4.1.3
– Condition, secured
O N
Interior check
LY
Electric plug connections
–
C
External horn speakers
4.1.2
N TR
No change to the basic flight manual data.
4
ED
3
Apply 15 s cool down after each siren operation (SIREN sw OFF).
LL
NOTE
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 s
O
2
4.2 4.2.1
FO
R
For system check procedure refer to 4.2 Operation. OPERATION Public address operation COMM CONTROL selector knob (pilot/copilot/operator)
– LS or PA
POWER sw (control unit)
– ON; Check POWER ON light comes on
PA/RADIO sw (control unit)
– Check in position PA
When pressing the ICS RADIO button on the cyclic stick, any message spoken to the head set microphone will be delivered through the horn speakers for external paging. APPROVED Rev. 0
9.2-20 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL LOUDSPEAKERS
When system operation is no longer intended: – OFF
COMM CONTROL selector knob (pilot/copilot/operator)
– As desired
Siren operation – LS or PA
PA/RADIO sw (control unit)
– Check in position PA
SIREN sw
– Set as required
ED
COMM CONTROL selector knob (pilot/copilot/operator)
LL
4.2.2
POWER sw
O
When system operation is no longer intended: – OFF
POWER sw
– OFF
COMM CONTROL selector knob (pilot/copilot/operator)
– As desired
PY
N
O
T
C
O
N TR
SIREN sw
PERFORMANCE DATA
5.1
AEO AND OEI MAXIMUM RATE OF CLIMB
LY
–
C
O
5
O N
All results obtained from the respective diagram, contained in section 5 of the basic flight manual, are to be corrected as follows:
O N
Helicopter gross mass below 2600 kg: . . . . . . . . . . . . . . . . . . . . . . . . . . . . subtract 75 ft/min
TI
Helicopter gross mass from 2600 kg up to 3200 kg: . . . . . . . . . . . . . . . . . subtract 60 ft/min
ST
The reduction in climb rate is not depending on power settings.
FO
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NOTE
R
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Helicopter gross mass above 3200 kg: . . . . . . . . . . . . . . . . . . . . . . . . . . . . subtract 50 ft/min
9.2-20 – 4
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL LOUDSPEAKERS
6
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
7
SYSTEM DESCRIPTION
O N
RADIO
OFF
PY
10
NAT OFF POWER
C
O
0
ON
YELP
WAIL
AA22–495
O
SIREN
C
PA
T
VOL
N TR
O
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ED
The external loudspeaker system consists of two loudspeakers, mounted in a common pod, a control unit mounted in the center or slant console (see fig. 1), an audio power amplifier mounted underneath the cockpit floor and associated wiring and switches (see fig. 2). The loudspeakers are installed underneath the helicopter, attached at the forward crosstube, pointing forward and 30° downward with regard to the longitudinal axis of the helicopter. The control unit provides a central adjustment for external aircraft paging functions. When it is turned on, an activation signal is sent to the audio power amplifier.
POWER
ON
O N
Switches the system on.
OFF
Switches the system off.
YELP
Activates a fast rate sweeping alarm signal for external paging via horn speakers
WAIL
Activates a slow rate sweeping alarm signal for external paging via horn speakers
OFF
Siren signal switched off
IN
ST
R
U
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TI
O N
SIREN
PA RADIO
VOL
0 - 10
FO
R
PA/RADIO sw
FUNCTION
–
POSITION
LY
SWITCH
Public address Function not active Rotary control knob for volume control of the siren and voice output signal. Normal position for external paging is 5–10. Fig. 1
MANUFACTURER’S DATA APPROVED Rev. 0
Control unit
9.2-20 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EXTERNAL LOUDSPEAKERS
HORN SPEAKER
CONTROL UNIT VOL
PA
SIREN WAIL
AA22–495
0
10
RADIO
AUDIO POWER AMPLIFIER
ON YELP
OFF
NAT POWER
LL
System configuration
FO
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–
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PY
N
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C
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Fig. 2
ED
+28V DC
9.2-20 – 6
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VISION 1000 COCKPIT CAMERA
FMS
9.2-21
SUPPLEMENT FOR
C
O
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O
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ED
VISION 1000 COCKPIT CAMERA
O
–
Effectivity All
FO
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IN
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O N
LY
Vision 1000 Cockpit Camera
C
System/Equipment Designation
PY
N
O
T
This supplement shall be attached to the BK117 D-2 Flight Manual (Section 9.2) when the Vision 1000 Cockpit Camera is installed.
Date: DEC 11, 2015
Approved by EASA
EASA approval no.: 10055971
APPROVED Rev. 0
9.2-21 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VISION 1000 COCKPIT CAMERA
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary.
App.
Page
9.2-21 -1
0
EASA
9.2-21 -2
0
EASA
9.2-21 -3
0
EASA
Rev.No
App.
Page
Rev.No
Rem
9.2-21 -5 ((-6 6 blank)
0
Page
Rev.No
Rem
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Page
PY
N
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9.2-21 -4
Rem
O
Rev.No
App.
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LEP – manufacturer‘s data (part 2): Page
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APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VISION 1000 COCKPIT CAMERA
1
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
Cockpit Voice and Flight Data Recorder
CMOS
Complementary Metal Oxide Semiconductors
IMU
Inertial Measurement Unit
MEMS
Micro–Electro–Mechanical Systems
SDHC
Secure Digital High Capacity
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CVFDR
LIMITATIONS
The Vision 1000 cockpit camera is mission equipment and does not replace a CVFDR.
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EMERGENCY AND MALFUNCTION PROCEDURES
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NORMAL PROCEDURES
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ABBREVIATIONS AND DEFINITIONS
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For detailed information refer to the Vision 1000 pilots guide. PREFLIGHT CHECK
4.1.1
Interior check with BAT MSTR sw OFF
O N
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4.1
– Check inserted
ST
Although this is not recommended, the system can be operated without a memory card inserted. In this case, the data are recorded on the internal memory only.
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NOTE
– Open
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Memory Card
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Access door
4.1.2
5
Access door
– Close
CAMERA cb
– Check in
Pre start check with BAT MSTR sw ON Access door
– Open
LED status light
– Check solid green
Access door
– Close
PERFORMANCE DATA No change in the basic Flight Manual data.
APPROVED Rev. 0
9.2-21 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VISION 1000 COCKPIT CAMERA
6
MASS AND BALANCE Refer to Equipment List entries in Section 6 of the basic Flight Manual.
7
SYSTEM DESCRIPTION For detailed information refer to the Vision 1000 pilots guide.
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The Vision 1000 is a video and audio recording device augmented with an independent inertial measurement based data acquisition system. The system contains a 5 megapixel CMOS digital image sensor, an ambient cockpit audio recording device and several MEMS components for IMU data. The MEMS parts include: MEMS gyroscopes, MEMS accelerometers, and a three axis magnetoresistive flux compass. Other major components include internal flash memory, SDHC memory, and a sixteen channel WAAS–enabled GPS module. The unit contains an Ethernet interface for external communications. Data are automatically recorded to the internal memory and to the SDHC card in real–time. Typical data recorded includes: 2 megapixel imagery of the cockpit recorded at 4 Hz, IMU data recorded at 4 Hz, and audio stored at 22 kHz. The SDHC memory card can be removed for further analysis on a computer station equipped with a specific software tool. All recorded data are encrypted and can only be read with the specific software tool. Indicates status
LY
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LED status light
The Vision 1000 is powered on, functioning properly, and is ready to record flight data
Solid Yellow
An error has occurred. This error may be field–serviceable
O N TI
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Solid Red
O N
Solid Green
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Solid Blue
A critical error has occurred The Vision 1000 is powering on The Vision 1000 is currently updating its embedded software
No color (LED dark)
The Vision 1000 is not powered on
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Flashing green/blue
Vision 1000 LED status light conditions
9.2-21 – 4
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) VISION 1000 COCKPIT CAMERA
GPS ANTENNA CONNECTION
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POWER PORT
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ETHERNET PORT
ACCESS DOOR
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EC145_FLH_0208_R
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LED
Fig. 1
Vision 1000 – typical installation
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SD CARD
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-21 – 5/(9.2-21 – 6 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL CONTROL PEDAL COVER
FMS
9.2-22
SUPPLEMENT FOR
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This supplement shall be attached to the BK117 D-2 flight manual (subsection 9.2) when the DUAL CONTROL PEDAL COVER is installed. System/Equipment Designation
N
O
Effectivity All
For approving authorities and respective dates of approval refer to the log of supplements.
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Dual control pedal cover
Date: DEC 11, 2015
Approved by EASA
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-22 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL CONTROL PEDAL COVER
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are new, revised or deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the record of supplement-revisions as necessary.
App.
Page
9.2-22 -1
0
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9.2-22 -2
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9.2-22 -3
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APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL CONTROL PEDAL COVER
1
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual.
2
LIMITATIONS
EMERGENCY AND MALFUNCTION PROCEDURES
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PREFLIGHT CHECK
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NORMAL PROCEDURES
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No change to the basic flight manual data.
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No change to the basic flight manual data.
– Condition/fixing
–
PERFORMANCE DATA
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Pedal cover
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No change to the basic flight manual data.
APPROVED Rev. 0
9.2-22 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) DUAL CONTROL PEDAL COVER
6
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
7
SYSTEM DESCRIPTION The dual control pedal cover protects the tail rotor control system from unintentional control inputs by a person occupying the copilot’s seat.
HANDLING, SERVICING, AND MAINTENANCE
ED
8
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The pedals must be adjusted to the most forward position prior to installation of the cover.
9.2-22 – 4
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FMS
9.2-23
SUPPLEMENT FOR
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FIXED LANDING LIGHT(S) (CROSS TUBE)
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Effectivity
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System/Equipment Designation
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
LIST OF EFFECTIVE PAGES NOTE
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
GENERAL
LIMITATIONS
OPERATION
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EMERGENCY AND MALFUNCTION PROCEDURES
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PREFLIGHT CHECK
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NORMAL PROCEDURES
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OPERATION
Collective control panel
ST
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NOTE
Center console control panel (optional)
NOTE
FXD LIGHT
FXD LIGHT
PERFORMANCE DATA
9.2-23 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
MASS AND BALANCE
SYSTEM DESCRIPTION
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PILOT / COPILOT DOOR JETTISONING
FMS
9.2-24
SUPPLEMENT FOR
LL
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PILOT / COPILOT DOOR JETTISONING
O
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This supplement shall be attached to the BK 117 D-2 Flight Manual (Section 9.2) when the kit for Door Jettisoning is installed. Effectivity/Remarks
C
System/Equipment Designation
O
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Kit for pilot/copilot door jettisoning
PY
N
or
C
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Installation pilot/copilot door jettisoning
–
Pilot door jettisoning assy
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For approving authorities and respective dates of approval refer to the log of supplements.
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Copilot door jettisoning assy
Date: DEC 11, 2015
Approved by EASA
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-24 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PILOT / COPILOT DOOR JETTISONING
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
0
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DOA
0.1
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9.2-24 -3
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0.1
Approved Rev by No.
9.2-24 -4
EASA
Remarks/ Effectivity
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Remarks/ Effectivity
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(see page 9.2-24-1)
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(see entry below)
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REVISION
Revision: 0.1
Date: APR 11, 2018
Revision No. 0.1 to FMS reference revision 0 is approved under authority of DOA No. EASA.21J.700.
9.2-24 – 2
APPROVED Rev. 0.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PILOT / COPILOT DOOR JETTISONING
1
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
2
LIMITATIONS Door jettison is only allowed after touchdown.
ED
PLACARDS AND DECALS
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2.1
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Placard:
TUER NOTABWURF DOOR JETTISON OPEN DOOR THEN PUSH JETTISON LEVER DOWNWARDS
C
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Location: In front of pilot and copilot door
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TUERE OEFFNEN DANN ABWURFHEBEL NACH UNTEN DRUECKEN
–
Placard:
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WITH INFLATED FLOATS DO NOT USE DOOR JETTISON MIT AUFGEBLASENEN NOTSCHWIMMER TUERNOTABWURF NICHT BENUTZEN
EMERGENCY AND MALFUNCTION PROCEDURES
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3
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Location: Pilot’s and Copilt’s view
Jettisoning Cockpit Doors 1. Door
– Open
2. Jettison lever
– Push downwards
3. Door
– Push outwards
APPROVED Rev. 0.1
9.2-24 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PILOT / COPILOT DOOR JETTISONING
4
NORMAL PROCEDURES
4.1
PREFLIGHT INTERIOR CHECK – Check full upright position and safety wired
Quick release pins (upper and lower)
– Check correct installation
PERFORMANCE DATA
ED
5
Door jettisoning release lever
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9.2-24 – 4
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PILOT / COPILOT DOOR JETTISONING
6
MASS AND BALANCE
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Refer to equipment list entries in section 6 of the basic flight manual.
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-24 – 5/(9.2-24 – 6 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
FMS
9.2-27
SUPPLEMENT FOR
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EQUIPMENT FOR OFFSHORE OPERATION
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This supplement shall be attached to the BK117 D-2 Flight Manual (subsection 9.2) when HEELS, ADELT and/or Push out window is installed.
PY
N
System/Equipment Designation
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HEELS
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ADELT
All All All
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For approving authorities and respective dates of approval refer to the log of supplements.
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NOTE
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Push out window
Effectivity
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971
APPROVED Rev. 0
9.2-27 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
EASA
9.2-27 -2
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0.1
see below
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Date: SEP 30, 2016 Revision No. 0.1 to FLM reference revision 0 is approved under authority of DOA No. EASA.21J.700.
9.2-27 – 2
APPROVED Rev. 0.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
1
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual.
1.1
INTRODUCTION This supplement contains equipment used for Offshore Operation.
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One or more of the following equipment could be installed. In addition to the equipment described in this supplement, some other optional equipment (e.g. emergency floatation system (FMS 9.2-9), life rafts, etc.) may be mandatory, depending on national regulations.
N TR
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Equipment for Offshore operation: – Push-out window
2.1
PLACARDS AND DECALS
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LIMITATIONS
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N
– Helicopter emergency egress lights – HEEL
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– Automatic Deployable Emergency Locator Transmitter – ADELT
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Placard:
Location: Near the Push Out Window (outside the H/C)
APPROVED Rev. 0
9.2-27 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
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Placard:
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Location: Near the Push Out Window (inside the H/C)
EMERGENCY AND MALFUNCTION PROCEDURES
3.1
ADELT
3.1.1
Off–shore emergency
C
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N
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3
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Conditions/Indications – The ELT will automatically deploy (release and transmit) following a crash or ditching. Manual deployment of the ADELT, however, is possible at the pilot’s discretion.
O N
Procedure
– On – Check TX/TEST and BEACON GONE lights illuminate
On–shore emergency
R
3.1.2
– Lift
IN
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DEPLOY sw
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DEPLOY sw guard
FO
Conditions/Indications – The ELT will automatically deploy (release and transmit) following a crash. Manual activation (transmit) of the ADELT without releasing the unit, however, is possible at the pilot’s discretion. Procedure TRANSMIT sw guard
– Lift
TRANSMIT sw
– On – Check TX/TEST light illuminates
NOTE
9.2-27 – 4
The transmission may be stopped by returning the transmit switch to the original position and pressing the TEST/RESET pushbutton. APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
3.2
HEELS Conditions/Indications – Unintended illumination of the orange/white lights (squares) near the pilot/copilot jettison handles (if installed). At night, the pilot may be disturbed by these lights. Procedure HEEL LIGHT sw
– OFF
If the lights do not go off:
PUSH–OUT WINDOW
LL
3.3
– place over lights
ED
Cover
C
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CAUTION D THE PUSH–OUT WINDOW IS INTENDED AS AN UNDERWATER EMERGENCY ESCAPE. PERSONS USING THE PUSH–OUT WINDOW MUST BE SPECIFICALLY INSTRUCTED AND TRAINED TO USE THIS ESCAPE.
PY
N
O
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D THE PUSH–OUT WINDOW CAN ONLY BE OPENED IF THE SLIDING DOOR IS CLOSED.
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Procedure
C
1. Sliding door
LY
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2. Red cap
O N
3. Red strap
– Remove, red strap falls out – Pull, all the way out – Push forcefully until window gives way
TI
O N
4. Red/white markings on window
– Check closed
NORMAL PROCEDURES
4.1
ADELT
IN
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4
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An ADELT built in test has to be performed once a month. For details see para 8.1. Before the first flight of the day (once a day for aircraft on 24 hrs duty): F On system interface unit (Fig. 2)
ARM/OFF sw
– Check ARM
NOTE D When the System Interface Unit is not readily accessible, alternative procedures for checking that the switch is in ARM position may be used (e.g. by ensuring that the ADELT built–in test is performed each time after installation of equipment that prevents access to the ARM/OFF switch). D When the aircraft is not in service, it is recommended to switch the ARM/OFF switch on the System Interface Unit to OFF. This prevents inadvertent activation of the ELT, e.g. as a result of maintenance actions. APPROVED Rev. 0.1
9.2-27 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
4.2
HEELS
4.2.1
HEELS test Exterior check - fuselage (left and right): Perform the following test once a day for each fuselage side: HEEL TEST pb on sliding door (inside)
– Press, check egress lights in the sliding doors illuminate
ED
Pre–start check
N TR
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Add the following to the normal procedures lamp test (basic FLM para 4.4.1.1. or 4.4.2.1): TEST sw
– LAMP and hold, check
T
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O
– All HEEL lights illuminate (except in sliding doors)
PY
N
O
System checks
C
O
If an off-shore flight is planned, add the following to the normal procedures after INT LIGHTS EM/EX sw – ARM (basic FLM para 4.4.1.3 or 4.4.2.2):
LY
The push–out window may not be appropriate for some passengers (e.g. untrained or very big persons). Such passengers shall be seated near the standard emergency exit.
R
IN
ST
NOTE
U
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PUSH–OUT WINDOW
O N
O N
Switching the HEEL LIGHTs to ARM without generators on will cause the lights to illuminate and drain the battery.
R
4.3
– ARM
TI
NOTE
–
HEEL LIGHT
FO
Pre–flight check Passenger briefing ”push–out window”
5
– Perform
PERFORMANCE DATA No change to the basic flight manual data.
9.2-27 – 6
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
6
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
7
SYSTEM DESCRIPTION
7.1
ADELT
LL
ED
The Crash Position Indicator (CPI) is designed as a primary radio location aid to alert Search and Rescue forces and assist location in the event of an aircraft distress situation. The beacon transmits on international distress frequencies at 121.5MHz and 406.025Mhz and is compatible with the COSPAS/ SARSAT system. With the GPS input, the beacon will also transmit the last known position of the aircraft in distress.
N TR
O
After the CPI system shut-off sw (Fig. 2) has been set to ARM (see para 4.1), the system is in a standby mode, ready for operation.
C
O
The system automatically boots when the aircraft is powered up. Two beep tones indicate that the system is ready for operation.
T
The system is activated by any single or multiple combination of the following commands:
N
O
– The automatic g–switch sensing an excess load.
O
PY
– The operator, switching the system to TRANSMIT or DEPLOY at cockpit control panel.
C
– The water activated switch being immersed in water.
O N
ADELT cockpit control panel
FO
R
IN
ST
R
U
C
TI
O N
7.1.1
LY
–
In addition a second water activated switch is integrated inside the beacon release unit.
2
1 Fig. 1
3
4
5
ADELT cockpit control panel
1 TRANSMIT sw: Lifted guard and switch in up position initiates beacon transmission, but not deployment. The TX/TEST annunciator illuminates and an audio tone will be generated (the audio signal is not available via the intercom system). 2 TRANSMIT annunciator: Indicates that the beacon transmitts a distress signal when illuminated. 3 TEST/RESET sw: TEST initiates a self test. For details see para 8.1. RESET switches off all beacon transmissions and resets the system if TRANSMIT is selected. Reset is inoperative if the beacon has been deployed. MANUFACTURER’S DATA APPROVED Rev. 0
9.2-27 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
4 BEACON GONE annunciator: Indicates that the beacon has been deployed and is transmitting a distress signal when illuminated. 5 BEACON DEPLOY sw: Lifted guard and switch in up position deployes the beacon. The TX/TEST and the BEACON GONE annunciators illuminate and an audio tone will be generated (the audio signal is not available via the intercom system). System Interface Unit
FO
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IN
ST
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O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
7.1.2
1 Fig. 2
System Interface Unit (installed in aft cabin)
1. CPI system shut–off sw: – ARM: The unit is ready for automatic deployment or operation through the Cockpit Control Panel. Recommended when the aircraft is in service. – OFF: ADELT unit is switched off. Recommended when the aircraft is not in service.
9.2-27 – 8
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
7.2
HEEL CAUTION SUCCESSFUL ESCAPE FROM A SUBMERGED AND/OR CAPSIZED HELICOPTER NORMALLY REQUIRES SPECIFIC SURVIVAL TRAINING AND PERSONAL EQUIPMENT. THE HEEL SYSTEM IS NO SUBSTITUTE FOR SUCH TRAINING/EQUIPMENT. The HEEL system comprises illuminated markings which guides the occupants to the exits/handles when the rotorcraft is capsized and the cabin is submerged. The system is watertight up to 50 feet and has a 20 minutes operation capability.
ED
Three different types of lights are used:
O
Optional:
O
– Orange lights near the door opening/jettison handles
N TR
– Green lights at the corners of the emergency exit windows
LL
– Green strip lights surrounding the doors used as emergency exits
T
C
– Orange/white lights (squares) near the pilot/copilot door jettison handles are installed.
–
C
O
PY
N
O
The HEEL system is controlled by the HEEL LIGHT switch located on the overhead panel.
O N
LY
ON
O N
ARM
Fig. 3
HEEL LIGHT HEEL system sw (overhead panel)
IN
– activates the HEEL system and the HEEL with push out window (excluding sliding doors)
FO
R
ON
ST
R
U
C
TI
OFF
ARM – arms the HEEL system and the HEEL with push out window (excluding sliding doors) so that the system is automatically activated in case of a total power loss, a crash landing or contact with water OFF – deactivates the HEEL system and the HEEL with push out window (excluding sliding doors) For testing purpose the LAMP TEST sw, located on the overhead panel activates the HEEL system and HEEL with push out windows (excluding sliding doors). The HEEL of each sliding door has its own power supply and a TEST pb located on the inner side of the sliding door. The sliding door HEEL activates automatically upon contact with water.
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-27 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
7.3
PUSH OUT WINDOW The standard rear cabin windows are replaced by windows of the push out type. This window is no emergency exit but is designed as an additional escape facility using CAA AIL/0124 as a guideline. This guideline states that for this type of exit underwater escape is possible by persons of a size believed to cover 95% of male person wearing representative survival clothing and uninflated lifejackets.
Flight direction
FO
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ST
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O N
O N
LY
–
C
O
PY
N
O
T
C
O
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O
LL
ED
This option should only be used by instructed and trained persons which are familiar with this type of exit.
9.2-27 – 10
Fig. 1
Typical push out window installation
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
7.4
HEELS OF THE PUSH OUT WINDOW (OPTION) If HEEL is installed on the aircraft, the following additional lights can be optionally installed: – Green strip lights surrounding the push out window
ED
If installed, the HEEL for push out window is an integral part of the HEEL system (see HEEL description).
Fig. 2
HEELS for push out window
FO
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IN
ST
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TI
O N
O N
LY
–
C
O
PY
N
O
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N TR
O
LL
4 x HEELs
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-27 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) EQUIPMENT FOR OFFSHORE OPERATION
8
HANDLING, SERVICING, AND MAINTENANCE
8.1
ADELT BUILT IN TEST (TO BE PERFORMED ONCE A MONTH) TEST/RESET pb (ADELT control panel)
– Press; check TX/TEST and BEACON GONE annunciator illuminate – Check TX/TEST annunciator flashes in synchronisation with a sweeping tone
LL
ED
– Check TX/TEST and BEACON GONE annunciator disappear
O
T
C
O
N TR
O
NOTE D If the test failed (TX/TEST and BEACON GONE annunciator remain illuminated) press TEST/RESET pb for minum 5 seconds to reset the system and repeat the test. If the test failed three times, maintenance action is required. Proceed in accordance with national regulations.
FO
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IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
D The CPI Beacon battery has a recommended BIT frequency of once per month. Each use of the TEST/RESET pb will deplete the battery and if used more than once per month then the battery will not last for the specified 24/48 hours at the end of its 5 year life.
9.2-27 – 12
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FMS
9.2-28
SUPPLEMENT FOR
N TR
O
LL
ED
ELECTRO-OPTICAL SYSTEM − WESCAM MX15 SERIES (CENTERLINE)
N
O
T
C
O
O
Effectivity
–
C
PY
System/Equipment Designation
FO
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IN
ST
R
U
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TI
O N
O N
LY
9.2-28 − 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
LIST OF EFFECTIVE PAGES NOTE
NRD
App.
Page
Rev.No
Rem
R
R
R
R
Rev.No
Rem
O
Page
N
N
C
O
N
Page
PY
Rem
LY
–
O N
R
Rev.No
App.
T
LEP − manufacturer‘s data (part 2): Page
Rev.No
LL
Rev.No
O
Page
N TR
App.
O
R
Rev.No
C
Page
ED
LEP − approved (part 1):
O N
LOG OF REVISION
U
C
TI
FIRST ISSUE
ST
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IN
FO
9.2-28 − 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
GENERAL
INTRODUCTION ABBREVIATIONS
D
E
F
H
I
L
N
U
LL O N TR O C T O N
PY
O
–
C
ST
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TI
O N
O N
LY
FO
R
IN
W
ED
A
9.2-28 − 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
LIMITATIONS
COMPATIBILITY
EFFECTIVITY
If EOS Wescam MX15D is installed
All
ED
EFFECTIVITY
O C
O
OPERATIONAL LIMITATIONS
T
N TR
LL
O
PY
N
O
WARNING D
O N
LY
–
C
D
IN
ST
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U
C
TI
O N
D
FO
R
9.2-28 − 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
O
LL
ED
N TR
N
O
T
C
O
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
9.2-28 − 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
APPROVED SEAT CONFIGURATION
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
O N
O N
FO
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IN
ST
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C
TI
9.2-28 − 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
O C
N
FO
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IN
ST
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TI
O N
O N
LY
–
C
O
PY
O
T
N TR
O
LL
ED
9.2-28 − 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
PLACARDS AND DECALS Placard: MONITOR BRIDGE HAS TO BE IN MID POSITION FOR TAKEOFF AND LANDING
Location:
O
LL
ED
Placard:
C
O
N TR
MONITOR HAS TO BE PARALLEL WITH BRIDGE FOR TAKEOFF AND LANDING
N
O
T
Location:
C
O
PY
Placard:
O N
LY
–
10“ MONITOR HAS TO BE IN FWD POSITION FOR TAKEOFF AND LANDING
O N
Location:
R
U
C
TI
Placard:
R
IN
ST
SEAT MUST BE IN MOST AFT POSITION FOR TAKE-OFF AND LANDING
FO
Location:
9.2-28 − 8
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
EMERGENCY AND MALFUNCTION PROCEDURES
UNCONTROLLED EOS MOVEMENTS Conditions/Indications Procedure
ED
_
_
O
_
N TR
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N
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–
C
O
O N
U
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CAUTION
O N
FO
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IN
ST
R
9.2-28 − 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
NORMAL PROCEDURES
PREFLIGHT CHECK
Exterior check
LL
ED
WARNING
N TR
N
O
T
NOTE
O
Interior check
C
O
O
PY
IN
ST
R
U
NOTE
TI
SYSTEM CHECKS
C
O N
O N
LY
–
C
FO
R
9.2-28 − 10
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
PRE-T/O CHECK
NOTE
ED
O
N TR
O
C
PRE-LANDING CHECK
O
T
LL
PY
N
C
O
LY
O N
O N
NOTE
–
U
C
TI
FO
R
IN
ST
R
ENGINE SHUTDOWN
9.2-28 − 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
PERFORMANCE DATA
AEO AND OEI MAXIMUM RATE OF CLIMB
LL
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
NOTE
ED
9.2-28 − 12
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
MASS AND BALANCE
SYSTEM DESCRIPTION For additional information on the system refer to the EOS “Operation Manual”.
LL
ED
N TR
O
C
O
T
N
O
PY
O
O N
LY
–
C
R
U
C
TI
O N
FO
R
IN
ST
9.2-28 − 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
EOS TURRET
N TR
O
LL
ED
O N
PY
A
T
C
O
C
O
LY
–
C
TI
ST
R
U
A
FO
R
IN
O N
O N
Description
9.2-28 − 14
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
COPILOT 10” EOS MONITOR (OPTIONAL) NOTE D
ED
D
O
LL
D
N TR
LY
–
C
O
PY
N
O
T
C
O
O N
TI
O N
Power
FO
R
IN
ST
R
U
C
Source select Freeze/Zoom Window Format Menu Day/Night Luminance
9.2-28 − 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
HAND CONTROLLER UNIT (HCU) (OPTIONAL)
ED
CAUTION
O
N TR
O
LL
PY
N
O
T
C
FO
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IN
ST
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TI
O N
O N
LY
–
C
O
Description
9.2-28 − 16
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
EOS MISSION GRIP (OPTIONAL) NOTE
LL
ED
N TR
O
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
IN
FO
R
R
Description
ST
Pos.
U
C
9.2-28 − 17
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
OPERATOR WORKSTATION (OPTIONAL)
LL
ED
NOTE
O
N TR
T
O
PY
N
O
C
O
FO
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IN
ST
R
U
C
TI
O N
O N
LY
–
C
9.2-28 − 18
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
DOWNLINK RACK (OPTIONAL)
O
C
PY
N
O
T
C
O
N TR
O
LL
ED
–
DIGITAL VIDEO RECORDING SYSTEM
LY
TI
O N
O N
R
U
C
FO
R
IN
ST
NOTE D D
9.2-28 − 19
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Control
Ctrl Name
Function
Clear
Rewind
Play/Pause
Fast Forward
Day/Night
Luminance
Record
Stop
Line Select keys 1 and 2
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
Enter
O N
ST
R
U
C
TI
Soft keys 1 to 4 (left to right)
FO
R
IN
PWR LED
Menu select knob
Release latch
9.2-28 − 20
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
AUDIO SELECTOR SWITCH
LL
ED
–
O N
GPS ANTENNA
O N
LY
C
O
PY
N
O
T
C
O
N TR
O
FO
R
IN
ST
R
U
C
TI
9.2-28 − 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
LASER PANEL(S)
Laser safety panel (optional) NOTE
O
N
T
C
O
N TR
O
LL
ED
NOTE
–
Laser control panel (optional)
LY
C
O
PY
U
C
TI
O N
O N
inactive
IN
R
ST
R
FO
9.2-28 − 22
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FMS
9.2-29
SUPPLEMENT FOR
O
T
C
O
N TR
O
LL
ED
ELECTRO-OPTICAL SYSTEM – STAR SAFIRE 380-HD/HDC
C
O
PY
N
LY
–
System/Equipment Designation
FO
R
IN
ST
R
U
C
TI
O N
O N
Effectivity
9.2-29 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
LIST OF EFFECTIVE PAGES NOTE
NRD
ED
Page
Rev.No.
App.
Page
Rev.No.
App.
Rev.No.
Rem
Rev.No.
Rem
LL
App.
O
R
Rev.No.
N TR
Page
N
LEP – approved (part 1):
O
Page
Page
PY
Rem
–
C
R
Rev.No.
O
Page
T
C
O
LEP – manufacturer‘s data (part 2):
O N
LY
LOG OF REVISION
TI
C
R
O N
U
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IN
ST
9.2-29 – 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
GENERAL
ABBREVIATIONS
E
I
L
U
LL
COMPATIBILITY
O
LIMITATIONS
C
N TR
O
C
ED
PY
N
O
T
C
OPERATIONAL LIMITATIONS
LY
–
O
O N
C
U
TI
O N
IN
ST
R
R
FO
9.2-29 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
EFFECTIVITY
If Laser is installed
Operational limitations for lasers (optional)
ED
NOTE D
N TR
O
LL
D
O
D
T O
APPROVED SEAT CONFIGURATION
PY
All
N
EFFECTIVITY
C
LY
–
C
O
O N
O N
FO
R
IN
ST
R
U
C
TI
z
9.2-29 – 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
N
PY
–
FO
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IN
ST
R
U
C
TI
O N
O N
LY
C
O
z
O
T
C
O
N TR
O
LL
ED
9.2-29 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
O PY
C
N
O
z
T
C
O
N TR
O
LL
ED
–
PLACARDS AND DECALS
LY
O N
O N
Placard:
R
U
C
TI
MONITOR BRIDGE HAS TO BE IN MID POSITION FOR TAKEOFF AND LANDING
IN
ST
Location:
FO
R
Placard:
MONITOR HAS TO BE PARALLEL WITH BRIDGE FOR TAKEOFF AND LANDING
Location:
9.2-29 – 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Placard: 10“ MONITOR HAS TO BE IN FWD POSITION FOR TAKEOFF AND LANDING
Location:
ED
Placard:
N TR
O
LL
SEAT MUST BE IN MOST AFT POSITION FOR TAKE-OFF AND LANDING
C
O
Location:
O
T
EMERGENCY AND MALFUNCTION PROCEDURES
N
PY C
EOS LASER ARMED
LY
–
If Laser is installed
O
EFFECTIVITY
O N
Conditions/Indications
O N
EOS LASER ARMED
U
C
IN
ST
R
NOTE
TI
FO
R
Procedure
EFFECTIVITY
All
9.2-29 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
NORMAL PROCEDURES For additional information on the operations of the system incl. optional subsystems, refer to the EOS “Operation Manual”.
NOTE
PREFLIGHT CHECK
Exterior check
ED
C
O
N TR
O
LL
WARNING
–
C
O
NOTE
N
Interior check
PY
O
T
LY
TI
O N
O N
C
PRE-T/O CHECK
R
U
FO
NOTE
R
IN
ST
9.2-29 – 8
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
PRE-LANDING CHECK
ED
C
AFTER LANDING CHECK
O
T
O
N TR
O
LL
C
O
PY
N
PERFORMANCE DATA
AEO AND OEI MAXIMUM RATE OF CLIMB
O N
LY
–
TI
O N
U
C
ST
R
FO
R
IN
9.2-29 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
MASS AND BALANCE
SYSTEM DESCRIPTION
EOS STAR SAFIRE 380-HD/HDC SYSTEM
ED
GPS Antenna
O
Multisensor System consisting of:
LL
L–3 communications downlink system
O
C
O
T
SYSTEM POWER SUPPLY
N
N TR
LY
TYPICAL INSTALLATION OF THE EOS
FO
R
IN
ST
R
U
C
TI
O N
O N
–
C
O
PY
9.2-29 – 10
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Operator workstation (optional)
LL
ED
NOTE
N TR
O
C
O
N
O
T
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
9.2-29 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Copilot’s 10” EOS monitor (optional) NOTE D
O
LL
ED
D D
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O N
Power
ST
R
U
C
TI
Source select
FO
R
IN
Freeze/Zoom Window Format Menu Day/Night Luminance
9.2-29 – 12
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
EFFECTIVITY
If Laser is installed
EOS Laser systems CAUTION
ED
C
O
N TR
O
LL
All
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
EFFECTIVITY
PY
N
O
T
9.2-29 – 13/(9.2-29 – 14 blank)
FO
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IN
ST
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TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
FMS
9.2-30
SUPPLEMENT FOR
C
O
N TR
O
LL
ED
WEATHER RADAR SYSTEM – RDR 1600
O
C
System/Equipment Designation
PY
N
O
T
This supplement shall be attached to the BK 117 D-2 Flight Manual (Section 9.2) when the WEATHER RADAR SYSTEM RDR 1600 is installed.
All
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
Weather radar system RDR-1600
Effectivity
Date: JUN 08, 2016
Approved by EASA
EASA approval no.: 10058347
APPROVED Rev. 0
9.2-30 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
0
EASA
9.2-30 -2
0.1
DOA
9.2-30 -3
0
EASA
9.2-30 -4
0
EASA
R
App.
9.2-8 -5
0
EASA
9.2-8 -6
0
EASA
9.2-8 -7
0.1
DOA
Rev.No.
Rem
App.
0
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Rem
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Rev.No.
Rev.No.
T
LEP – manufacturer‘s data (part 2): Page
Page
LL
9.2-30 -1
Rev.No.
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Page
N TR
App.
O
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Rev.No.
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Page
ED
LEP – EASA approved (part 1):
0
LOG OF REVISIONS
R
U
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TI
O N
O N
LY
–
0
IN FO
R
ORIGINAL REVISION
ST
FIRST ISSUE
0.1
(see page 9.2-30-1) (see entry below),
Revision 0.1 Date: MAR 20, 2017 Revision No. 0.1 to FLM reference revision 0 is approved under authority of DOA No. EASA.21J.700.
9.2-30 – 2
APPROVED Rev. 0.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
1
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
LIMITATIONS
2.1
PRECAUTIONS
LL
2
ED
Additional information about the system layout, the operation of the WXR as well as about the correct interpretation of weather maps can be obtained from the RDR 1600 Pilot‘s Guide and other additional vendor documentation (see para 8.2).
C
O
PY
N
O
T
C
O
N TR
O
If operation of the WXR on ground is required the following safety distances are to be observed (see Fig. 1):
LY
–
A
R
IN
ST
R
U
C
TI
O N
C
BKD2_FLH_0056_R
O N
B
Safety distance from personnel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 ft (7,5 m)
B
Safety distance from fuel trucks, other aircraft . . . . . . . . . . . . . . . . . . . . . . 50 ft (15 m)
C
Safety distance from refueling operations and large metallic objects (e.g. hangar doors) – tilt antenna upward to the maximum . . . . . .
FO
A
Fig. 1
APPROVED Rev. 0
100 ft (30 m)
Safety Distances
9.2-30 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
2.2
OPERATIONAL SAFETY WARNING
2.3
NEVER RELY UPON WXR AS A PROXIMITY WARNING DEVICE OR FOR ANTI-COLLISION-PROTECTION WARNING.
COMPATIBILTY
EMERGENCY AND MALFUNCTION PROCEDURES
3.1
WXR FAILURE OR INHIBITED TRANSMISSION
N TR
O
LL
3
FAIL
T
C
O
FAILURE INDICATIONS
WXR FAIL
PY
N
O
and
WXR
WXR failure indication on FND
–
C
O
WXR sk WXR fail indication on NAVD
O N
– No WXR data displayed
O N
– WXR switched off or failed
LY
Conditions/Indications
TI
If MFD 4 fails weather radar is no longer available.
C
NOTE
ED
The WXR (i.e. radome) degrades significantly the protective capability of an optionally installed Wire Strike Protection System (FMS 9.2–15).
R
U
Procedure
– Check ON
IN
ST
WXR
R
If weather radar is operating normal
FO
Continue flight If failure indication remains Weather radar
–
OFF
Continue flight
9.2-30 – 4
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
WXR TX INHIB WXR indication for inhibited transmission on FND and NAVD Conditions/Indications – Weather radar mode selector is on when aircraft is below 50 ft radar altitude. Weather radar does not transmit.
LL
– OFF
INVERTER FAILURE
N
O
T
C
O
3.2
N TR
O
Function selector sw
ED
Procedure
C
Caution appears without audio tone.
O N
– Inverter failed
O N
Conditions/Indications
LY
–
NOTE
O
PY
INVERTER 2 FAIL
ST
R
Procedure
U
C
TI
– WXR stabilization system is lost.
IN
WXR function selector sw
– OFF
FO
R
Continue flight
APPROVED Rev. 0
9.2-30 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
NORMAL PROCEDURES WARNING
DON’T PUT THE FUNCTION SELECTOR SWITCH IN ON POSITION UNLESS THE PRECAUTIONS / SAFETY DISTANCES OF PARA 2.1 ARE OBSERVED.
CAUTION
IN CASE OF A FAILED RADAR ALTIMETER THE AUTOMATIC INHIBIT FUNCTION < 50 FT IS DISABLED. THEREFORE THE CREW HAS TO SELECT THE STBY OR OFF MODE MANUALLY IN ORDER TO PREVENT THE WXR SYSTEM FROM TRANSMITTING WHILE OPERATING NEAR THE GROUND.
ED
4
No WXR transmit inhibition indication will be provided in case that no WXR overlay is selected. If no WXR overlay is selected either on MFD1/2/4 and WXR is switched on, the WXR must be manually switched OFF or set to STBY when descending through 50 ft.
T
PREFLIGHT CHECK
O
4.1
C
O
N TR
O
LL
NOTE
PY
O
SYSTEM CHECKS (AFTER STARTING ENGINES)
C
4.2
– Condition
N
Radome
–
AVIO MSTR 1 and 2 sw
O N
MFD range
O N
WXR function selector sw
LY
INV sw
– ON – ON – STBY – Select 80 NM
U
C
TI
NOTE D Allow 1 minute warmup time for the radar system.
IN
ST
R
D If the WXR is switched OFF by executing the preflight test the advisory AVIONIC TEST FAIL will be displayed.
R
WXR function selector sw
– TST – Set in acc. with table in para 7.2.1
MFDs 1, 2, 4
– Bsk WXR select
FO
MFDs 1, 2, 4
– The test pattern will appear. – The color bands in the test pattern must correspond to those described in the respective vendor documentation (see para 8.2). TEST appears on the screen. Transparency of the WXR overlay
– Adjust to enhance readabibilty of WPT and ACAS information
Range of MFD 4 and MFD 2
– Select identical range
WXR function selector sw
– OFF or STBY
9.2-30 – 6
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
4.3
OPERATION WHEN WEATHER RADAR IS DISPLAYED ON THE NAVD PAGE, HEIGHT ABOVE TERRAIN (HAT), OBSTACLES, AND HTAWS CAUTION AND WARNING ICONS ARE NO LONGER DISPLAYED. TO USE HTAWS AND WXR SIMULTANEOUSLY, WXR MUST BE SELECTED ON THE FND.
CAUTION
After-Takeoff check: Above 50 ft: – ON; operate the system as described in the pilot’s guide.
WXR on FND sector or NAVD page
– Select
4.4
N TR
O
LL
ED
WXR function selector sw
PRE-LANDING CHECK
C
O
Approaching 50 ft:
– Check on
N
O
T
WXR
PY
If not:
– STBY
LY
AFTER LANDING CHECK
O N
4.5
–
C
O
WXR function selector sw
– OFF
U
PERFORMANCE DATA
R
5
C
TI
O N
WXR function selector sw
FO
R
IN
ST
No change in the basic Flight Manual data.
APPROVED Rev. 0.1
9.2-30 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
6
MASS AND BALANCE Refer to Equipment List entries in Section 6 of the basic Flight Manual.
7
SYSTEM DESCRIPTION
7.1
GENERAL The WXR RDR1600 provides the following main functions:
O
LL
ED
– Weather detection: To recognize in time “meteorological danger areas”, e.g. storm fronts and areas of great turbulences.
C
N
O
T
– Beacon mode The RDR1600 enables to detect and show beacons.
O
N TR
– Ground mapping/search mode: The operator can adapt the WXR gain, enabling adjustment of the WXR sensitivity to detect objects in several different backgrounds.
O
PY
It consists of a control panel CP113K (see Fig. 2), a receiver/transmitter, an antenna drive unit incl. antenna and an indicator.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
With the WX image displayed on the FND sector mode and on the NAVD page with different ranges selected a short pop up message ”NO VALID VIDEO” will appear.
Fig. 2
9.2-30 – 8
Control panel CP 113K
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
Switch
Position
Function
Primary modes OFF / STANDBY / TEST / ON – (WXR function selector sw) OFF STANDBY TST ON 60_
OFF
Removes WXR system power. Communication between Receiver/Transmitter and HELIONIX is Stopped.
STANDBY
Fully energizes the system circuitry but no radar transmission occurs in STBY mode. WXR STANDBY will appear on the display (if selected as overlay). A multi-coloured arc display test pattern is displayed in this mode of operation. The test pattern (typical 4-color test pattern is initialized and sized to fit the 80 NM range and can also be scaled with the range select buttons. No radar transmission occurs while TST is selected. TEST will appear on the display and STAB OFF is displayed. An internal test is performed not only when the TEST mode is activated, but also in STANDBY, ON and 60 degrees. This internal test is monitoring receiver/transmitter, antenna drive and control panel.
ON
Selects the normal condition of operation for weather detection and/or other modes of operation. The system will transmit after a 60 second warm-up time is completed. NOTE When the knob is switched directly from OFF to ON mode, the display will blank. No radar transmissions occur until the warm up period is complete.
60_
Directs the antenna to sector scan 60_ about the boresight of the aircraft. This position will work in weather, search (map), and beacon modes.
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
TST
LY
–
Secondary modes Wx / WxA / SRCH / BCN –
Normal weather mode
WXA pb
–
The weather alert (WXA) mode enables to highlight storm areas for easier detection.
SRCH pb
–
O N
O N
WX pb
TI C
U R ST IN R
– Search 2 – Short range precision mapping. Active on the ten-mile range or less. – Search 3 – Normal surface mapping.
FO BCN pb
The SEARCH (or map) function sets the radar system in ground mapping mode. Three Search modes are sequentially available when pressing the SRCH button: – Search 1 – Sea clutter rejection. Active on the ten-mile range or less.
Gain control is enabled in this mode. –
MANUFACTURER’S DATA APPROVED Rev. 0
Beacon mode may be operated alone (beacon only mode) or in combination with weather or search modes. Sequentially pressing the beacon button will select different beacon modes. NOTE Indication of the BCN mode on MFD2 and 4 will show different distances to the beacon if different ranges are chosen. To obtain correct and identical distance to the beacon, select identical ranges on both MFD’s.
9.2-30 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
–
The Beacon Gain is a rotary potentiometer that controls the gain of the beacon receiver (counter-clockwise (CCW) rotation reduces gain).
PUSH CODE
–
Selects the desired beacon code by sequentially pressing the beacon gain push button.
SRCH GAIN
–
The gain knob (GAIN) adjusts the radar gain (CCW rotation reduces gain). The gain knob will only function when in the SEARCH mode.
PULL STAB OFF –––––– TILT
–
The following antenna stabilization modes are available: – Manual (gain turning knob pulled): Permits manual adjustment of antenna tilt 15_ up or down for best indicator presentation. The tilt angle is indicated on the display.
LL
ED
BCN GAIN
O
T
C
O
N TR
O
– Automatic (gain turning knob pushed): The weather radar antenna attitude angles are automatically compensated for helicopter roll and pitch angle. The TILT can still be set in this mode.
HELIONIX INTERFACE AND DISPLAY INDICATIONS OF THE WXR
7.2.1
Indications
C
O
PY
N
7.2
Display
SECTOR
NAVD/FND
ROSE
NAVD
WXR presentation WXR
O N
Mode
LY
–
To display the WXR overlay the WXR bsk 4 (see Fig. 3 and 4) has to be pressed.
O N
only WXR as overlay
C
TI
WXR (overlay) + DMAP (underlay) NAVD/FND
DMAP (Helionix)
–
DMAP (EuroNav7)
MFD 1 and/or 4
ST
R
FO
HAT layer (HTAWS)
9.2-30 – 10
N/A
R
PLAN
U
N/A
IN
FND
NAVD
N/A WXR N/A
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
The FND format indicates WXR information as overlay in the navigation display main part in SCT mode only:
DMAP
NAV
IAS
101 20
17
10
10
16
16
1500
15
100 10
20
20
N
600 DA
13
B A R O
1013 200 hPa DH
N PY C
O
20
FSD
354 1.0 FMS GPS
10
LY
10
A C K
O N
DTK
–
WXA T+ 2.0
LFMH
415 Kg HSI
WXR
SVS
OAT
25
+ B R G –
ST
R
U
C
TI
DCPL
O N
20.0 NM 12 min
+ L U M –
14
13
3
20
C R S
Weather data superimposed on SECTOR mode
FO
R
IN
BKD2_FLH_0397_R
14
VY
R N G
N A V
3
O
80
10
D H
N TR
20
D A
C
2
120
17
T
4
18
O
6
+ C T R S –
CLOCK
ED
ALT
MISC
LL
VMS
O
NAVD
N R N G
C R S
CHECK RANGE
20
WXA T+ 2.0
3
10
20 TGT STAB OFF
10
WXR check range, target alert, stabilization and tilt information
Fig. 3 MANUFACTURER’S DATA APPROVED Rev. 0
WXR FND indication
9.2-30 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
ASBAG 116 /
VMS
3.3 NM
DTK 294
DMAP
FMS
GS TAS
0 6 M A P
12
6
16
R N G
D H
3 ASBAG DEP80 1720FT REDVO
0.1 NM
N
E
V O R 1
30
N TR
O
24 W
F M S
PY
N
O
T
C
O F R T
21
20
O
10
33
+ C T R S –
EFB
NPA MSG
E
N A V
MISC
ED
NAVD
LL
FND
– FMS
PLS
SCT
WX
WXR
ACAS
FLTA
HTAWS
+ B R T –
O N
O N
CPL
LY
+ L U M –
Fig. 4
WXR NAVD indication
R
IN
ST
R
U
C
TI
BKD2_FLH_0225_R
C
O
D A T A
FO
Indication Area Indication Bsk of NAVD
Description
Primary mode
FAIL WXR
STBY
The WXR is not detected by HELIONIX MFDs. It means the WXR is switched OFF or it has failed. There is no difference between OFF and a total WXR bus failure. In both cases the message WXR FAIL is displayed in amber inside compass aera. WXR in STBY mode
WXR
TEST
9.2-30 – 12
TEST modus of the WXR
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
Indication Area Indication Bsk of NAVD
Description
Secondary mode mode Normal weather mode
WX
WXR Weather Alert Mode. When WXA mode is selected, red areas of storms flash between red and black at a 1 HZ rate.
WXR STANDBY
ED
WXR TX INHIB
Is displayed if the WXR is switched ON while the HC is on ground or when in flight the WXR has automatically set to STBY while passing below 50 FT RA.
LL
Primary NAVD / FND compass rose
WXR in STBY mode (FND only)
O
WXR
N TR
WXA
O
The WXR is not detected by HELIONIX MFDs. It means the WXR is switched OFF or it has failed. There is no difference between OFF and a total WXR bus failure. In both cases the message WXR FAIL is displayed in amber inside compass aera (FND only).
N
O
T
C
WXR FAIL
PY
O –
Secondary mode mode
Normal weather mode
TI
O N
O N
LY
WX WXA
FO
R
IN
ST
R
U
C
SEARCH 1
BCN 0 STD BCN 1 DO172
MANUFACTURER’S DATA APPROVED Rev. 0
C
CHECK RANGE
Refer to para 7.2.5
Weather Alert mode. When WXA mode is selected, red areas of storms flash between red and black at a 1 HZ rate. Target alert is activated as well. The status WXA is indicated in cyan. Search “1/2/3” The SEARCH (or ground map) colours are: – Green for light ground returns – Yellow for medium ground returns and – Red for heavy ground returns. BCN “0/1/2/3” If beacon mode is activated a BCN indication is provided together with the beacon mode STD (standard beacons) or DO172 (DO 172 beacons) and the beacon code ) e.g. “BCN 1 DO172”. NAV source selection is possible to set CDI NOTE The distance in the BCN mode is wrong if different ranges on the MFD’s are selected.
9.2-30 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
7.2.2
WXR display state The display provides an indication on top of BSK3 containing information if WXR is selected for display on the MFD or not.
WXR layer selected for display (left) and WXR layer unselected (right) 7.2.3
Antenna stabilisation / tilt indication Stabilisation indication
ED
– No antenna stabilisation is provided
LL
STAB OFF
N TR
O
on FND (see Fig. 3) and NAVD STAB OFF when in manual stabilisation.
C
O
NOTE D Proper antenna stabilisation is provided up to $30_ (on pitch and roll axis).
N
O
T
D If MFD 4 or the inverter has failed the stabilisation of the antenna will not longer be provided.
PY
Tilt indication:
–
C
O
The WXR tilt indication provides the tilt value of the WXR antenna selected by the crew members on the radar control panel.
O N
T+12.3
O N
on FND (see Fig. 3) and NAVD.
Target Alert
TI
7.2.4
LY
– Example for tilt indication
R
U
C
The TGT message will be displayed on the FND (sector page) and on the NAVD (directly below the compass rose).
FO
R
IN
ST
Target alert makes the pilot aware of the presence of a significant weather cell that exists beyond the currently selected range. For this mode to be active the WXR needs to be in WXA mode. The TGT symbol is indicated if a weather cell: – has red intensity, and – the echo is located within 25 miles beyond the displayed range. –
TGT
flag adjacent to the weather image is displayed.
If TGT message appears proceed as follows: Selected range
– Increase until TGT message disappears
Display
– Check for intensive weather areas
9.2-30 – 14
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
7.2.5
Range selection A range selection is available via sk access on the MFD (see Fig. 3 and 4) . The WXR range selection and display on pilot side MFD 2 and 4 is independent from the WXR range selection on the copilot’s side MFD 1. MFD 2 / 4 requires identical range selection. If the range selection on MFD 2 and 4 is not identical the following indication will be provided on NAVD and FND:
O
VMD INDICATIONS
N TR
7.3
LL
ED
CHECK RANGE
O
The presence and status of the WXR is indicated on the system format of the VMD page:
O N
LY
–
C
O
PY
N
O
T
C
WXR is recognized and valid on all MFDs:
FO
R
IN
ST
R
U
C
TI
O N
WXR is recognized but invalid on MFD 4 (connection failure):
WXR invalid on all MFDS, no WXR detected:
Fig. 5 MANUFACTURER’S DATA APPROVED Rev. 0
WXR status on VMD SYSTEM page
9.2-30 – 15
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) WEATHER RADAR SYSTEM – RDR 1600
7.4
AC POWER SUPPLY OF THE RDR 1600 The AC system consists of the following main components: – Static inverter with a 5A circuit breaker – Circuit breaker for the power supply of 26 VAC or 115 VAC (depending on configuration)
HANDLING, SERVICING AND MAINTENANCE
8.1
HANDLING, MAINTENANCE
N TR
O
LL
8
ED
– INV switch (two position toggle switch) located on the overhead panel with position “ON” and “OFF”
O
1. Operation on ground is only permitted when the safety distances are observed.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
PILOT’S GUIDE RDR-1600: TM106101
O
PY
VENDOR DOCUMENTATION
C
8.2
N
O
T
C
2. Make sure that the radar nose is clean and that the antenna components are clean and dry.
9.2-30 – 16
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PULSED CHIP DETECTOR SYSTEM (FUZZ BURN)
FMS
9.2-31
SUPPLEMENT FOR
N TR
O
LL
ED
PULSED CHIP DETECTOR SYSTEM (FUZZ BURN)
O
T
C
O
This supplement shall be attached to the BK 117 D-2 Flight Manual (Section 9.2) when the PULSED CHIP DETECTOR SYSTEM is installed.
N
System/Equipment Designation
All
C
O
Pulsed chip detector
PY
Pulsed chip detector common kit
Effectivity
LY
–
Engines
O N
Main Gearbox (MGB)
All All
FO
R
IN
ST
R
U
C
TI
O N
Tail Gearbox (TGB)
All
Date: DEC 11, 2015
Approved by EASA
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-31 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PULSED CHIP DETECTOR SYSTEM (FUZZ BURN)
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary.
App.
Page
Rev.No.
9.2-31 -1
0
EASA
9.2-31 -4
0
9.2-31 -2
0
EASA
9.2-31 -5
0
9.2-31 -3
0
EASA
9.2-31 -6
0
App.
Page
Rem
Page
Rev.No.
Page
Rev.No.
Rem
C
0
PY
N
O
T
9.2-31 -7 (- 8 blank)
Rem
O
Rev.No.
App.
O
LEP – manufacturer‘s data (part 2): Page
Rev.No.
ED
Rev.No.
LL
Page
N TR
LEP – approved (part 1):
C
O
LOG OF REVISIONS
LY
–
FIRST ISSUE
(see page 9.2-31–1)
FO
R
IN
ST
R
U
C
TI
O N
O N
ORIGINAL
9.2-31 – 2
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PULSED CHIP DETECTOR SYSTEM (FUZZ BURN)
1.
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual. The pulsed chip detector system is designed to clear the oil chip detectors from non–critical “normal” wear debris collection, when the relevant switch is operated. In order to monitor abnormal wear behaviour of the MGB, TGB and engines, record, in the helicopter logbook and in the logcard of the affected engine, the chip pulse activations (operation of the FUZZ BURN sw) and CHIP indications (for each engine separately).
LIMITATIONS
N TR
2.
O
LL
ED
NOTE
C
O
Maximum number of FUZZ BURN activations per flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2
PY
N
O
T
Each time a chip detector caution of a specific system (ENG 1/2, MGB, TGB) illuminates (including on ground), it is allowed to activate the pulsed chip detector system. If the caution extinguishes but a chip detector caution (ENG 1/2, MGB, TGB) illuminates subsequently at a later time in flight, a second activation of the system is permitted.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
After activation of the FUZZ BURN sw, a logbook entry and maintenance action is required after the flight.
APPROVED Rev. 0
9.2-31 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PULSED CHIP DETECTOR SYSTEM (FUZZ BURN)
3.
EMERGENCY AND MALFUNCTION PROCEDURES CAUTION INDICATION
ENG1
CHIP or
CHIP
ENG2
ED
and audio tone
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Conditions/Indications
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Metal particles detected in engine oil. Procedure
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If the caution extinguishes but a chip detector caution illuminates subsequently at a later time in flight, a second activation of the system is permitted.
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NOTE
– On (approximately 1 second) – Record – Monitor
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FUZZ BURN sw (spring loaded) Chip pulse event Engine parameter
–
1. 2. 3.
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F ON GROUND
After 1 min, if no further CHIPs are detected and no unusual behaviour of engine is noticed, follow normal takeoff procedure.
O N
NOTE
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If ENG CHIP caution indication goes off:
– Perform
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4. Takeoff
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Proceed in accordance with the basic Flight Manual.
ST
4.
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If ENG CHIP caution indication remains on:
FUZZ BURN sw (spring loaded)
– On (approximately 1 second)
2.
Chip pulse event
– Record
3.
Engine parameter
– Monitor
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1.
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IN
F IN FLIGHT
If ENG CHIP caution indication remains on: 4. Proceed in accordance with the basic Flight Manual. If ENG CHIP caution indication goes off: 4.
9.2-31 – 4
Continue flight
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PULSED CHIP DETECTOR SYSTEM (FUZZ BURN)
CAUTION INDICATION
MGB CHIP and audio tone Conditions/Indications Metal particles detected in MGB oil.
LL
If the caution extinguishes but a chip detector caution illuminates subsequently at a later time in flight, a second activation of the system is permitted.
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NOTE
ED
Procedure
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F ON GROUND
FUZZ BURN sw (spring loaded)
– On (approximately 1 second)
2.
Chip pulse event
– Record
3.
MGB parameter
– Monitor
PY
N
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1.
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If MGB CHIP caution indication goes off:
– Perform
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4. Takeoff
Proceed in accordance with the basic Flight Manual.
O N
4.
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–
If MGB CHIP caution indication remains on: F IN FLIGHT
FUZZ BURN sw (spring loaded)
– On (approximately 1 second)
2.
Chip pulse event
– Record
3.
MGB parameter
– Monitor
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1.
ST
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If MGB CHIP caution indication remains on:
IN
4. Proceed in accordance with the basic Flight Manual.
FO
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If MGB CHIP caution indication goes off:
APPROVED Rev. 0
4.
Continue flight
9.2-31 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PULSED CHIP DETECTOR SYSTEM (FUZZ BURN)
CAUTION INDICATION
TGB CHIP and audio tone Conditions/Indications Metal particles detected in TGB oil.
LL
If the caution extinguishes but a chip detector caution illuminates subsequently at a later time in flight, a second activation of the system is permitted.
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NOTE
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Procedure
– On (approximately 1 second) – Record
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FUZZ BURN sw (spring loaded) Chip pulse event
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1. 2.
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F ON GROUND
N
If TGB CHIP caution indication goes off:
– Perform
Both engines
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F IN FLIGHT
O N
FUZZ BURN sw (spring loaded) Chip pulse event
– Shut down
– On (approximately 1 second) – Record
O N
1. 2.
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–
3.
C
If TGB CHIP caution indication remains on:
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3. Takeoff
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If TGB CHIP caution indication remains on:
C
3. Proceed in accordance with the basic Flight Manual.
ST
Continue flight
IN
3.
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If TGB CHIP caution indication goes off:
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NORMAL PROCEDURES
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4.
No change in the basic Flight Manual data.
5.
PERFORMANCE DATA No change in the basic Flight Manual data.
9.2-31 – 6
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) PULSED CHIP DETECTOR SYSTEM (FUZZ BURN)
6.
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
7.
SYSTEM DESCRIPTION When enough metal particles collect on the magnetic detectors to close the circuit, the appropriate CHIP caution indication (ENG, MGB, TGB) comes on. The pulsed chip detector system is designed to eliminate spurious CHIP caution indications caused by ”normal” wear conditions.
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Normal wear (due to gear meshing, bearing rotation, etc.) creates fine metal particles. These fine metal particles collect on the magnetic chip detectors. Activation of the pulsed chip detector system sends an electrical pulse to the chip detectors to burn off these fine metal particles. However, larger metal particles, which may indicate component failure, are not burned off by the system and in this case the CHIP caution indication will remain on.
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The CHIP caution indications are indicated on the FND master list.
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The chip detector system comprises 5 pulsed chip detectors (one per engine, two on the MGB and one on the TGB). The pulsed chip detector system supplies all chip detectors in parallel, because only the shortened contact absorbs electrical energy. Additionally it comprises a power module and a spring-loaded FUZZ BURN switch (see Fig. 1), which is located on the overhead panel.
OFF
O N
O N CC TEST
ARM
CARGO HOOK
OFF
OFF
OFF
A R M TEST
EMER FLOATS
S L O W
P I L ON
FUZZ BURN
PAX
LAVCS
FAST
WIPER
Fig. 1
FUZZ BURN switch
FO
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HOIST/ CBL CUT
OFF
O N
BKD2_FLH_0263_R
OFF
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-31 – 7/(9.2-31 – 8 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
FMS
9.2-32
SUPPLEMENT FOR
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HELIONIX DIGITAL MAP SYSTEM (DMAP)
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System/Equipment Designation
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This supplement shall be attached to the BK117 D-2 flight manual (subsection 9.2) when the HELIONIX DIGITAL MAP SYSTEM (DMAP) is installed.
Before Helionix Maintenance Release 1
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HELIONIX DIGITAL MAP SYSTEM (DMAP)
Effectivity
Date: DEC 11, 2015
Approved by EASA
EASA approval no.: 10055971
APPROVED Rev. 3
9.2-32 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are new, revised or deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the record of supplement-revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
Page
Rev.No.
App.
Page
9.2-32 -1
3
EASA
9.2-32 -2
4
9.2-32 -3
3
9.2-32 -4
3
EASA
9.2-32 -7
EASA
9.2-32 -5
2.1
DOA
EASA
9.2-32 -6
2.1
DOA
Rev.No.
Rem
9.2-32 -19
2.1
9.2-32 -11
2.1
9.2-32 -20
2.1
9.2-32 -12
2.1
9.2-32 -21
3
9.2-32 -13
2.1
9.2-32 -22
9.2-32 -14
2.1
9.2-32 -23
9.2-32 -15
2.1
9.2-32 -16
2.1
9.2-32 -17
2.1
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9.2-32 -26
4
9.2-32 -18
2.1
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DOA
9.2-32 -8
2.1
DOA
9.2-32 -9
2.1
DOA
Rev.No.
Rem
Page
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9.2-32 -28
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R
9.2-32 -29
4
R
9.2-32 -30
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2.1
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9.2-32 -31
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3
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9.2-32 -32
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9.2-32 -24
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4
9.2-32 -25
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9.2-32 -34
ORIGINAL
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LOG OF RREVISIONS
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9.2-32 -10
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Page
App.
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LEP – manufacturer‘s data (part 2):
Rev.No.
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App.
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LEP – approved (part 1):
REVISION
(see page 9.2-32–1) 1
REVISION 2 EASA approval no.: 10060585 Date: DEC 12, 2018
MAY 04, 2016 DEC 22, 2016
REVISION
2.1
MAR 20, 2017
REVISION 3 DEC 18, 2017 EASA approval no.: 10064108 REVISION
4
(see entry below)
Approved by EASA:
EASA approval no.: 10067961
9.2-32 – 2
APPROVED Rev. 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
TABLE OF CONTENTS
Page GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 5
2
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 5
3
EMERGENCY AND MALFUNCTION PROCEDURE . . . . . . . . . . . . . . 9.2-32 – 6
3.1
DMAP failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 6
3.2
Loss of DMAP position . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 8
3.3
Terrain database malfunction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 7
3.4
Other database malfunction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 7
4
NORMAL PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 8
5
PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 8
6
MASS AND BALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 9
7
SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 9
7.1
DMAP format . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 10
7.2
DMAP control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 10
7.1.2
DMAP display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 12
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7.1.2.1 Basic symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 13
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7.1.2.2 Base map background displays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 15 7.1.2.3 Navigational data overlays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 17
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7.1.2.4 Obstacle indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 21
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7.1.2.5 Static user waypoints . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 23
ST
7.1.2.6 DMAP database (INFORMATION and DATABASE window) . . . . . . 9.2-32 – 23
IN
7.1.2.7 SVS horizontal field of view indication on DMAP (if SVS installed) . 9.2-32 – 27
R
7.1.2.8 ACAS overlay (if ACAS installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 27
FO
7.1.3
DMAP mode selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 28
7.1.3.1 Overlay selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 28 7.1.3.2 Range selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 29 7.1.3.3 Configuration mode selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 29 7.1.3.4 Map type selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 30 7.1.3.5 Pointer selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 30 7.1.3.6 Map mode selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 31 7.1.3.7 HTAWS selection (if HTAWS installed) . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 31 7.2
NAVD with a DMAP layer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 32
7.2.1
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 32
7.2.2
Control and display indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 32
APPROVED Rev. 3
9.2-32 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
3LIST OF FIGURES Page DMAP control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 10
Fig. 2
DMAP display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 12
Fig. 3
TOPOGRAPH & VECTOR mode . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 15
Fig. 4
NONE & RASTER mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 16
Fig. 5
SAS mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 16
Fig. 6
DMAP database . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 23
Fig. 7
Access to information window . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 24
Fig. 8
Navigation inside the DMAP database . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 25
Fig. 9
SVS on DMAP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-32 – 28
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Fig. 1
9.2-32 – 4
APPROVED Rev. 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
1
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual.
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LIMITATIONS
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The Helionix Digital Map system (DMAP) function uses the available Helionix avionics to compute and display the navigation environment, geographical features, aeronautical data, and obstacle data. Hence, it is also referred to as the “internal DMAP”. This DMAP is not to be confused with “external DMAP“ systems, such as e.g. Euronav 7.
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WARNING D NOT ALL OBSTACLES AND WIRES ARE INCLUDED IN THE DMAP DATA BASE. WHEN AN OBSTACLE, WIRES, OR TERRAIN IS NOT IN THE DATABASE, AN ALERT WILL NOT BE PRODUCED. IT IS THE PILOT’S RESPONSIBILITY TO MAINTAIN A PROPER LOOKOUT.
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D GROUPED OBSTACLES MAY APPEAR AS ONE OBSTACLE. THEREFORE, INDIVIDUAL OBSTACLES IN A GROUP MAY NOT BE LOCATED AT THE DISPLAYED POSITION.
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D IN AREAS WITH A PARTICULAR HIGH DENSITY OF OBSTACLES, SOME GROUPED OBSTACLES MAY NOT BE DISPLAYED OR THE DMAP MAY TEMPORARILY FAIL ( MAP FAIL INDICATED).
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– The Helionix DMAP information shall not be used as a primary means of navigation.
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– The Helionix DMAP is intended to increase the pilot’s situational awareness in VFR and IFR. Navigation and terrain/obstacle avoidance shall not be based on the DMAP information. – Use of the DMAP PLAN (North up) mode shall be limited to pre-flight planning. Do not use the PLAN mode in flight. – Selecting DMAP on the NAVD page is prohibited when WXR is displayed on the NAVD.
APPROVED Rev. 2.1
9.2-32 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
2.1
PLACARDS AND DECALS
EFFECTIVITY
FAA registered helicopters
Placard: DO NOT USE DMAP PLAN MODE IN FLIGHT Instrument panel between MFD1 and MFD4
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Location:
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Placard:
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DO NOT SELECT DMAP ON NAVD WHEN WXR IS DISPLAYED
Instrument panel between MFD1 and MFD4 (when WXR is installed)
N PY
All
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Location:
9.2-32 – 6
APPROVED Rev. 2.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
3
EMERGENCY AND MALFUNCTION PROCEDURES
3.1
DMAP FAILURE
FAILURE INDICATIONS
MAP FAIL
LL O
Conditions/Indications – DMAP display is black. Other MFD pages can be selected.
ED
(on MFD)
N TR
– May be caused in areas of high obstacle density if specific DMAP ranges are used.
C
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Procedure
– Deselect
O
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1. DMAP
PY
N
2. Continue flight
–
MFD power sw
– Wait at least 10 sec – Push
TI
LOSS OF DMAP POSITION
FAILURE INDICATIONS
MAP POSITION
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3.2
– Push
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3.
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If DMAP is required for the mission, it is possible to reboot the MFD as follows, when flight conditions permit:
(on MFD)
Conditions/Indications – GPS position, altitude, or magnetic heading is not available or latitude is beyond 80°N or 80°S. – Other MFD pages are available. Procedure 1. DMAP
– Deselect
2. Continue flight APPROVED Rev. 2.1
9.2-32 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
3.3
TERRAIN DATABASE MALFUNCTION
FAILURE INDICATIONS OR (DMAP area black)
(DMAP area red when HAT (HTAWS) is selected)
ED
Conditions/Indications
N TR
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Terrain database is corrupted, missing, or out of coverage (black background). When Height Above Terrain (HTAWS) is selected, the actual height above terrain cannot be determined and the HAT layer will be shown in red.
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NOTE D A black background is normal when the map format NONE is selected. Aeronautical and HTAWS layers, however, work normally in the NONE map format.
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D A black DMAP background can also result if the display brightness was reduced to zero. Push the BRT+ pb to recover a normal brightness setting.
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OTHER DATABASE MALFUNCTION
FAILURE INDICATIONS
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2. Continue flight
– Deselect
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OBS MISSING
(on DMAP)
OR
AERO DB MISCOMP
(on DMAP)
Conditions/Indications – Obstacle database is missing, or – Aeronautical database is incorrect (DMAP and HTAWS used different database) Procedure 1. Continue flight NOTE
9.2-32 – 8
The data base can be checked on the VMS/SYST page, by selecting DATAB. APPROVED Rev. 2.1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
4
NORMAL PROCEDURES CAUTION D HEIGHT ABOVE TERRAIN (HAT) INDICATION IS AUTOMATICALLY INHIBITED WHEN THE TOPOGRAPHIC MAP IS SELECTED. D WHEN CHANGING BETWEEN THE TOPOGRAPHIC AND OTHER MAP FORMATS, THE PILOT MUST CHECK THAT THE HAT INDICATION IS AS REQUIRED. IF NECESSARY, THE HAT INDICATION MUST BE RE-SELECTED.
ED
ACAS information can be displayed on the DMAP. The ACAS Virtual Control Panel (VCP), however, should not be selected from the DMAP page. Switch to the NAVD page to select the ACAS VCP.
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NOTE
Before night flight:
– Adjust BRT
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PERFORMANCE DATA
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DMAP display
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No change in the basic Flight Manual data.
APPROVED Rev. 2.1
9.2-32 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
6
MASS AND BALANCE The Helionix DMAP has no effect on mass and balance.
7
SYSTEM DESCRIPTION The intended purpose of the DMAP function is to provide situational awareness with respect to the surrounding environment: – Navigation environment (flight plan, waypoints),
ED
– Geographical features (natural or manmade features),
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– Aeronautical data (Airports, Heliports, Runways, NAVAIDS, Enroute Airways, Controlled Areas, Restricted Areas and FIR), – Obstacle data.
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The DMAP function uses the available Helionix avionics resources (such as MFD, Operative System (OS), Mass Memory Storage (MMS) and internal partitions)
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PY
N
The DMAP database to be used in the helicopter is prepared in a dedicated ground station which uses special data conversion tools to convert the database to the DMAP readable format.
LY
–
The HELIONIX DMAP function is available in two formats (selected via MSK):
O N
– DMAP page
FO
R
IN
ST
R
U
C
TI
O N
– NAVD page (NAVD with selectable map background)
9.2-32 – 10
MANUFACTURER’S DATA APPROVED Rev. 2.1
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DMAP FORMAT
7.1.1
DMAP Control
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
7.1
Fig. 1
DMAP control
ITEM
LABEL
1
MAP
Map type selection: TOPOGRAPH, VECTOR, NONE, RASTER, SAS.
2
ALTN
inactive.
3
DB
4
PNTR
5
BRT
MANUFACTURER’S DATA APPROVED Rev. 2.1
FUNCTION
Open / close the DMAP database window. Switch pointer: ON or OFF. Adjustment of the basic map brightness to allow more contrast between the map and the overlaid symbols.
9.2-32 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
ITEM
LABEL
FUNCTION
6
–
7
HTAWS
8
ACAS
Clutter/declutter ACAS traffic (all traffic / no traffic /PA+TA+RA only). Use NAVD control to filter UNRST/BELOW/ABOVE.
9
PLN ROS SECT
Map mode: – PLN = North up, centered – ROS = Heading up, centered – SECT = Heading up, offset NOTE: Although obstacles are shown in PLAN mode, this information shall not be used for navigation. PLAN mode should be used for pre–flight planning only. In flight, a north-up orientation does not allow obstacles and terrain to be properly recognized.
10
CNFG
Configuration of the preselected layers: IFR, VFR, USER, SET USER (user customization).
Knob: – Inner/outer rotation to move selection or pointer. – Short press to validate a list selection or open a control window. – Long press to validate the selection.
N
PY
HC To center on present position. ENDRTE To center on FMS point, DMAP is set to PLN display.
C
O
11
O
T
C
O
N TR
O
LL
ED
– Short press: HTAWS layer and terrain coloration. – Long press: HTAWS control window.
RNG
Range selection (0.1NM – 40NM) NOTE: When a range value ”R” is selected, distance from top to bottom of MFD screen corresponds to 4 x ”R” NM (if virtual control panel is not displayed).
13
LAYR
– Short press: access to layer selection menu – Long press: access to aeronautic layer sub-selection menu.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
12
9.2-32 – 12
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DMAP DISPLAY
Fig. 2
DMAP display
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
7.1.2
DESCRIPTION
FO
R
ITEM 1
Heading indication (Magnetic or True)
2
North symbol
3
Map ring range
4
Own aircraft position
5
FMS data of the current leg (if flight plan is active)
MANUFACTURER’S DATA APPROVED Rev. 2.1
9.2-32 – 13
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7.1.2.1 Basic symbols Helicopter SYMBOL
DESCRIPTION Own aircraft position.
ED
Helicopter alternate own aircraft position (when helicopter position is outside the displayed area (i.e. in pointer mode with map panning), it indicates the direction towards own aircraft position).
O
DESCRIPTION
N TR
SYMBOL
LL
North
C
O
True north detection.
N
O
T
Heading
DESCRIPTION
PY
SYMBOL
C –
O N
LY
True heading.
O
Magnetioc heading.
FO
R
IN
ST
R
U
C
TI
O N
Leg Data Window
ITEM
9.2-32 – 14
DESCRIPTION
1
To waypoint. Waypoint name from flight plan in cyan or green (when AFCS is coupled).
2
Waypoint bearing and distance to go.
3
Time to go to the waypoint (at current groundspeed).
4
Ground speed.
5
Desired track.
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Pointer SYMBOL
DESCRIPTION Active pointer.
Secondary inactive pointer.
ED
Active pointer (screen limit).
N TR
O
LL
Secondary inactive pointer (screen limit).
T
C
O
Pointer coordinates (when pointer is active).
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
Wind
MANUFACTURER’S DATA APPROVED Rev. 2.1
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7.1.2.2 Base map background displays The DMAP can display different base maps as background (depending on the maps loaded and pilot’s choice): – TOPOGRAPH: A map colored according to absolute elevation and sun angle shade to provide a 3–D effect. This display includes bodies of water (lakes, oceans) and major rivers. – VECTOR: A vector based image depicting geographic boundaries, bodies of water and rivers, roads, railroads, populated areas and names of towns.
ED
– NONE: No map background (black background) intended for use in combination with the navigational data overlays.
LL
– RASTER: Scanned topographic maps of different scales.
O
HTAWS height above terrain indication is not available with the TOPOGRAPH map.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
NOTE
N TR
O
– SAS: Grey sun angle shaded map to provide a 3–D effect and including bodies of water and major rivers.
Fig. 3
9.2-32 – 16
TOPOGRAPH & VECTOR mode
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–
NONE & RASTER mode
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
Fig. 4
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
HELIONIX DIGITAL MAP SYSTEM (DMAP)
Fig. 5 MANUFACTURER’S DATA APPROVED Rev. 2.1
SAS mode
9.2-32 – 17
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7.1.2.3 Navigational data overlays The following aeronautical layers can be displayed: Airports, Heliports, Runways, NAVAIDS, en-route airways, waypoints, controlled areas, restricted areas, and FIR. The pilot can individually declutter each layer or have 3 different presets for the aeronautical layers: VFR, IFR and customizable appearance (USER). The DMAP provides automatic decluttering of the different layers when the range is increased in order to avoid displaying clutter and to provide smooth map operation (e.g. airport/heliport/runway are not displayed in the maximum range of 160NM (top to bottom of MFD screen).
RANGE LIMIT
IFR Airport
10 NM
O
LL
AIRPORT TYPE
N TR
SYMBOL
ED
Airport/Heliport/Runway
10 NM
O
T
C
O
VFR Airport
10 NM
C
O
PY
N
Runway
Airports with a runway above 4000 ft are displayed in all map ranges (in particular 20 NM and 40 NM)
O N
LY
–
NOTE
O N
Heliport
HELIPORT TYPE
RANGE LIMIT
IFR Heliport
10 NM
VFR Heliport
10 NM
FO
R
IN
ST
R
U
C
TI
SYMBOL
NOTE
9.2-32 – 18
Airports with an IFR capability are displayed in all map ranges (in particular 20 NM and 40 NM)
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Navaids RANGE LIMIT
VOR
40 NM
DME
40 NM
VOR/DME
40 NM
ILS/DME
40 NM
ED
NAVAIDS
LL
SYMBOL
N TR
O
TACAN
40 NM
O
5 NM
PY
N
NDB
T
C
O
VORTAC
40 NM
5 NM
C
O
NDB/DME
5 NM
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
Oriented localizer
MANUFACTURER’S DATA APPROVED Rev. 2.1
9.2-32 – 19
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Restricted and controlled areas SYMBOL
AREA TYPE – Restricted Airspace Type P (Prohibited). – Restricted Airspace Type R (Restricted). – Restricted Airspace Type T (Temporary). Restricted Restricted Restricted Restricted
Airspace Airspace Airspace Airspace
Type A (Alert). Type M (Military). Type W (Warning). Type D (Danger).
ED
– – – –
N
O
T
C
O
N TR
O
LL
The DMAP displays the restricted airspace label in three rows: – The top row displays the type and designation. – The second row displays the maximum altitude of the zone. – The bottom row displays the minimum altitude of the zone.
PY
SYMBOL
AREA TYPE
O N
LY
–
C
O
– Airspace Class B – Airspace Class TMA
Airspace Class D
FO
R
IN
ST
R
U
C
TI
O N
Airspace Class C
9.2-32 – 20
FIR deliminations
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Enroute and airway routes SYMBOL
TYPE Airway Intersection Waypoint Enroute Waypoint
ED
Enroute Marker (only in ranges of up to 20 NM)
LL
7.1.2.4 Obstacle indication
N TR
O
The DMAP provides the pilot with an indication of point and line obstacles.
O
Point obstacles are colored according to their altitude relative to that of the helicopter:
C
– Red: above current helicopter altitude,
O
T
– Amber: between current helicopter altitude and 250ft below,
N
– Blue: more than 250ft below current helicopter altitude.
O
PY
Line obstacles are always displayed in red independent of their relative height.
–
C
Depending on the selected range, obstacles close to each other may be automatically regrouped under a single symbol in the middle of the actual group of obstacles:
LY
– When viewing range is up to 2NM, all obstacles are displayed.
FO
R
IN
ST
R
U
C
TI
O N
O N
– When viewing range is above 2NM, all obstacles inside a circle of 4NM radius centered on the helicopter position are displayed. Obstacles outside this area can be grouped and displayed with a single ”Grouped” symbol in the middle of the actual group. As a result, some group obstacles may disappear around 4NM and be gradually replaced with individual obstacles.
MANUFACTURER’S DATA APPROVED Rev. 3
9.2-32 – 21
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OBSTACLE TYPE
SYMBOL ISOLATED
GROUPED
Obstacle < 1000 ft AGL Blue Obstacle < 1000 ft AGL Amber
LL
ED
Obstacle < 1000 ft AGL Red
N TR
O
Obstacle > 1000 ft AGL Blue
C
O
Obstacle > 1000 ft AGL Amber
N
O
T
Obstacle > 1000 ft AGL Red
C
O
PY
Obstacle < 1000 ft AGL Lighted Blue
LY
–
Obstacle < 1000 ft AGL Lighted Amber
O N
O N
Obstacle < 1000 ft AGL Lighted Red
C
TI
Obstacle > 1000 ft AGL Lighted Blue
ST
R
U
Obstacle > 1000 ft AGL Lighted Amber
FO
R
IN
Obstacle > 1000 ft AGL Lighted Red
9.2-32 – 22
Line obstacles
MANUFACTURER’S DATA APPROVED Rev. 2.1
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7.1.2.5 Static user waypoints Static user waypoints are waypoints with a predefined position and category, which can be created using the ground station. This allows the customer to create a database with specific user waypoints, which are not part of the standard aeronautical data (e.g. hospitals, police stations, off shore wind generators, etc.). THE USER WAYPOINTS ARE NOT SUBJECT TO INDEPENDENT VERIFICATION. USER WAYPOINTS SHALL BE USED FOR INFORMATION ONLY.
CAUTION
SYMBOL
USER WAYPOINT TYPE
LL O
N TR
Static User Wpt Cat 2
ED
Static User Wpt Cat 1
C
O
Static User Wpt Cat 3
N
O
T
Static User Wpt Cat 4
C
O
PY
Static User Wpt Cat 5
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
7.1.2.6 DMAP database (INFORMATION and DATABASE window)
Fig. 6
DMAP database
The information window can be accessed in two ways: – Select the object displayed in the map using the PNTR function. – Navigate inside the DB (database) window.
MANUFACTURER’S DATA APPROVED Rev. 3
9.2-32 – 23
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Obtaining information about a displayed object: To access the information window of a displayed object (airport, navaid, airspace, etc.), select the pointer by pressing PNTR, then move the pointer to the desired object using the rotary knob on the display. short press on the knob
long press on the knob
i.e.: when difficult to select because many objects in the same area:
N TR
O
LL
ED
Opening of a selection window, i.e.:
O
Select the desired object (if multiple co–located objects are shown). Validate selection by a long press.
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
Opening of the “select point” window, 8 objects maximum classified per type, i.e.:
ST
R
U
If the pointer is not near any object, a long press on the rotary knob will display:
IN
Information of free point:
FO
R
– coordinates and altitude – Minimum Of Route Altitude (MORA)
Fig. 7
9.2-32 – 24
Access to information window
MANUFACTURER’S DATA APPROVED Rev. 4
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Navigating inside the DMAP database:
O
Navigation inside DMAP DB
T
C
Fig. 8
N TR
O
LL
ED
To access the database window, push the DB key and navigate as follows:
DATABASE WINDOW DESCRIPTION
N
O
ITEM
Number of pages for the selected categroy/filtering.
2
Object category, use outer knob to select: ALL, ARPRT(airport), HLPRT (heliport), NVAID (navaid), INTRS (intersections, USRWP (user waypoints), ALTFP or ACTFP (alternate/active flight plan from FMS if any).
LY
–
C
O
PY
1
O N
Push consecutively the related LSK to display the objects: or
O N
– the more recently used:
TI
3
(green color) or
U
C
– the nearest neerest
(if any, amber color)
Push related LSK to filter (FLTR) the list. DATABASE window becomes:
FO
R
IN
ST
R
– the nearest with filtering criteria
4
Enter first digits of the object with knob. Push OK LSK to activate filter and return to the previous view. 5
Selected object (turn inner knob to select).
6
Other objects in following page(s) (press related key to get access).
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When the desired object is found and selected: – A short press on the rotary knob opens a window with possible actions (e.g. CENTER DMAP)
O
T
C
O
N TR
O
LL
ED
– A long press on the rotary knob displays the related object information page (see below). The outer knob can then be used to select a category (COMM, AREAS,...).
category with the outer rotary knob and,
O
PY
– Select
–
C
– Activate
LY
AIRWAYS and AIRSPACE information cannot be retrieved from DATABASE window. To consult this information, select it on the map (it may be necessary to change the range to display the object).
O N
O N
NOTE
N
To exit from INFORMATION window:
C
– GNRL : General
TI
The outer knob allows selecting the following information categories:
R
U
– COMM : Radio communication data
ST
– AREAS: Restricted or controlled areas
IN
– RNWYS : Runway data
FO
R
– HLIPD: Helipad data – NVAID : Navaids – PRCDR : Procedures – USRFL : User files. Not all categories are present for every type of object.
9.2-32 – 26
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7.1.2.7 SVS horizontal field of view indication on DMAP (if SVS installed)
C
O
N TR
O
LL
ED
If Synthetic Vision System (SVS) is installed (refer to Basic FLM), its horizontal field of View and range can be depicted on DMAP. This provides an easier correlation between the outside and DMAP view. The SVS field of view is depicted as alternating black and white lines, reflecting the actual SVS range at zero pitch.
SVS on DMAP
N
O
T
Fig. 9
PY
7.1.2.8 ACAS overlay (if ACAS installed)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
The ACAS symbols on the DMAP are identical to the symbols on NAVD (refer to FMS 9.2–3, Airborne Collision Avoidance System (ACAS)).
MANUFACTURER’S DATA APPROVED Rev. 4
9.2-32 – 27
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7.1.3
DMAP mode selection
AVAILABLE OPTIONS
Control for the display modes:
1. ALL
all layers are displaeyd
2. AERONAUTIC
aeronautical data layer
3. OVERLAY
overlay layer
4. OBSTACLE
obstacle layer
5. USE
user way points
6. NONE
disable all layers
If long press:
Allows the user to customize the layers:
TI
O N
LY
If short press:
C U
LAYR
FO
R
IN
ST
R
L1
COMMENTS
O N
Label on the left side of the screen
C
LABEL
–
KEY NO.
O
PY
N
O
T
C
O
N TR
O
LL
ED
7.1.3.1 Overlay selection
Layer data window
AERO: aeronautical data layer OVERLAY: overlay layer
9.2-32 – 28
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7.1.3.2 Range selection
KEY NO.
LABEL
AVAILABLE OPTIONS
COMMENTS
ED
Label on the left side of the screen
LL
1. 0.1 NM
O
2. 0.25 NM
N TR
3. 0.5 NM RNG
5. 2 NM
C
L2
O
4. 1 NM
O
T
6. 5 NM
Map p scale control
N
7. 10 NM
IN
O
ST
R
U
C
TI
O N
O N
LY
7.1.3.3 Configuration modes selection
–
C
9. 40 NM
PY
8. 20 NM
LABEL
AVAILABLE OPTIONS
COMMENTS
FO
R
KEY NO.
Label on the left side of the screen
L4
CNFG
MANUFACTURER’S DATA APPROVED Rev. 4
Configuration modes:
Control for the configuration modes (preselected layers):
1. IFR
to load the IFR configuration
2. VFR
to load the VFR configuration
3. USER
to load the USER configuration
4. SET USER
to save the layers currently selected in the user configuration until the end of the flight
9.2-32 – 29
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7.1.3.4 Map type selection
KEY NO.
LABEL
AVAILABLE OPTIONS
COMMENTS
2. VECTOR
vector map
3. NONE
none
4. RASTER
raster (scanned) map
5. SAS
Sun Angle Shading map
O
N TR
O
LL
colored SAS map
C
MAP
1. TOPO
T
L7
ED
Label on the right side of the screen
LABEL
AVAILABLE OPTIONS
COMMENTS
TI
KEY NO.
O N
O N
LY
–
C
O
PY
N
O
7.1.3.5 Pointer selection
U
C
Label on the right side of the screen PNTR
2. OFF
Used to activate the pointer mode
If DMAP is operated in Pointer mode, obstacles are shown around the pointer position, whereas obstacles are removed around the actual aircraft position.
FO
R
NOTE
1. ON
IN
ST
R
L10
9.2-32 – 30
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7.1.3.6 Map mode selection
KEY NO.
LABEL
AVAILABLE OPTIONS
COMMENTS
ED
Label on the bottom of the screen
LL
Direction of the map, north at top to heading at top:
O
Heading up. Own aircraft symbol is at the map center.
B3
N TR
1. ROS
North up. Own aircraft symbol is at the map center.
T
C
O
2. PLN
Heading up. Own aircraft symbol is in the lower 75% of the display.
PY
N
O
3. SCT
Use of the PLAN mode is limited to pre–flight planning only. Its use in flight is prohibited.
–
C
O
NOTE
ST
R
U
C
TI
O N
O N
LY
7.1.3.7 HTAWS selection (if installed)
IN
KEY NO.
LABEL
AVAILABLE OPTIONS
COMMENTS
FO
R
Label on the bottom of the screen
B6
Short press
To display the HTAWS layer and the terrain coloration over the 2D DMAP (refer to Basic FLM, Section 7).
Long press: HTAWS control window
To display the HTAWS virtual control pane in the bottom part of the display (refer to Basic FLM, Section 7).
HTAWS
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7.2
NAVD WITH A DMAP LAYER
7.2.1
General The NAVD format can be used with a map background (selection via MAP key). The map background is restricted to TOPOGRAPH. Map display in NAVD format comes automatically with display of obstacles, controlled areas and restricted areas. The map background can be used with weather radar and/or ACAS overlays. The DMAP background cannot be displayed simultaneously with HTAWS.
NOTE
Control and display indications
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
7.2.2
ITEM 1
9.2-32 – 32
LABEL MAP
AVAILABLE OPTIONS Map type selection: – TOPOGRAPH The control is inactive if HTAWS is selected.
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R
LABEL MAP
FO
R
IN
1
ST
ITEM
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
HELIONIX DIGITAL MAP SYSTEM (DMAP)
MANUFACTURER’S DATA APPROVED Rev. 4
AVAILABLE OPTIONS Map type selection: – NONE The control is inactive as HTAWS is selected.
9.2-32 – 33/(9.2-32 – 34 blank)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
FMS
9.2-33
SUPPLEMENT FOR
C
O
N TR
O
LL
ED
AUXILIARY FUEL TANK
O
C
System/Equipment Designation
PY
N
O
T
This supplement shall be attached to the BK 117 D-2 Flight Manual (Section 9.2) when the Auxiliary Fuel Tank is installed.
All
FO
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IN
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O N
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LY
–
Auxiliary Fuel Tank
Effectivity
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971
APPROVED Rev. 0
9.2-33 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. LEP – approved (part 1): Page
Rev.No.
App.
9.2-33 -1
0
EASA
9.2-33 -5
0
EASA
9.2-33 -2
0
EASA
9.2-33 -6
0
EASA
9.2-33 -3
0
EASA
9.2-33 -4
0
EASA
Rev.No.
Rem
Page
App.
O 0
9.2-33 -8
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9.2-33 -9
0
9.2-33 -13
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9.2-33 -7
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Page
N
Rem
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Rev.No.
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LEP – manufacturer‘s data (part 2): Page
Rev.No.
ED
App.
LL
Rev.No.
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Page
TI
O N
LOG OF REVISION
U
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FIRST ISSUE
(see 9.2-33-1)
FO
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IN
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ORIGINAL
9.2-33 – 2
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
1
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
2
LIMITATIONS
2.1
FUEL QUANTITY USABLE FUEL
UNUSABLE FUEL
TOTAL FUEL
kilograms
liters
kilograms
liters
kilograms
218.75
175
3.25
2.6
222
177.6
N TR
Fuel mass values are based on a fuel density of 0.8 kg/liter.
O
LL
ED
liters
N
PLACARDS
PY
2.2
O
T
C
O
Fuel transfer from the auxiliary fuel tank to the main fuel system has to be performed in level flight attitude. If fuel transfer is completed with the helicopter in nose up attitude (e.g. hover), the unusable fuel will be higher (up to 19kg).
C
O
Placard:
LY
–
VOR DEM BETANKEN DES AUX TANKS MUSS DER HAUPTTANK VOLL SEIN.
O N
BEI FASS- ODER KANISTERBETANKUNG SIEB VERWENDEN
O N
MAKE CERTAIN THAT THE MAIN TANK IS FULL BEFORE REFUELLING THE AUX TANK
C
TI
FOR BARREL OR GAS CAN REFUELING USE SCREEN
ST
R
U
Location: Near filler neck
FO
R
IN
Placard:
NICHT BELADEN DO NOT LOAD
Location: Upper side of auxiliary fuel tank
APPROVED Rev. 0
9.2-33 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
Placard:
JET FUEL 222 LITER / 58.7 US. GALLONS MIL - T - 5624 ASTM - D - 1655
JP5 JET A1
JET A
FOR ADDITIONAL FUEL TYPES SEE FLIGHT MANUAL
ED
FOR OPERATION BELOW –10 _C (–14 _F) ADD ANTI-ICING ADDITIVE ACCORDING TO BASIC FLIGHT MANUAL. Front side of auxiliary fuel tank
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Location:
9.2-33 – 4
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
3
EMERGENCY AND MALFUNCTION PROCEDURES IN CASE OF AN EMERGENCY LANDING, CHECK THAT AUX TK SWITCH ON OVERHEAD CONSOLE IS IN OFF POSITION.
CAUTION
CAUTION INDICATIONS
AUX FUEL XFER and audio tone Conditions/Indications
LL
ED
Fuel valve is in a position other than commanded, because:
O
– Main tank is able to receive the aux tank fuel but the fuel valve is closed; or
O
N TR
– Fuel valve allows transfer from the aux tank to the main tank, but the main tank is not ready to receive the fuel.
T
C
Procedure
O
PY
N
O
CAUTION IF NORMAL FUEL TRANSFER IS NOT POSSIBLE, THE ENDURANCE CALCULATION MUST BE PERFORMED WITHOUT THE AUX TANK FUEL QUANTITY. – NORM – Check AUX FUEL XFER disappears
O N
O N
LY
–
C
1. AUX TK switch
AUX FUEL XFER remains while an active fuel transfer is indicated: 1. AUX TK switch – Position OFF
U
C
TI
If
– EMERG – Check aux fuel tank quantity decreases
FO
1. AUX TK switch
R
IN
ST
R
If AUX FUEL XFER remains without active fuel transfer indication or when the aux tank fuel quantity is not decreasing):
If aux fuel tank quantity does not decrease: LAND AS SOON AS PRACTICABLE (calculate endurance without aux tank fuel quantity) NOTE D If AUX FUEL XFER and a fuel transfer indication appear successful fuel transfer, maintenance action is required after flight.
after
a
D If manual fuel transfer is intended, it should be started by setting the AUX TK switch to EMERG position when the main tank fuel quantity is 100kg. The fuel consumption of the helicopter during fuel transfer can be higher than the simultaneously transferred fuel quantity. APPROVED Rev. 0
9.2-33 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
NORMAL PROCEDURES The fuel should be transferred with the helicopter in nose down attitude (level flight). Nose up attitudes, e.g. hover attitude, might lead to an interruption in fuel transfer before completion with up to 19 kg fuel trapped in the aft aux tank corner.
NOTE
PREFLIGHT CHECK Vent-, drain lines
– Condition, no leakage, no fuel visible inside the lines
Auxiliary fuel tank
– Tight fit and secured, no damage, no evidence of leakage and/or spillage
Fuel supply lines and quick disconnects
– No leakage, no buckling, proper locking
Drain
– Perform (refer to para 8.2 of this supplement)
Electrical connections and GND
O
T
C
O
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O
LL
4.1
ED
4
N
– Tight – Secured
PY
L Filler cap
O
L AUX TK cb
OPERATION
LY
O N
4.2
O N
To be checked before each flight
– NORM
–
C
L AUX TK sw
– In
C
TI
In flight, when fuel quantity on FND is below the transfer level (latest at 500 kg / 625 liters / 165 gallons):
ST
R
U
1. Aux tank fuel indication
and appear
AUX FUEL XFER
disappears or fuel quantity on FND is below 200 kg / 250 liters / 66
FO
R
gallons:
IN
In flight, when
–
2. VMS page
– Select
3. Aux fuel tank level
– Check empty (fully transferred)
Fuel transfer is controlled automtically by avionics when the system is in NORM. After accomplishment of the fuel transfer procedure the aux fuel valve will be closed automatically.
5
PERFORMANCE DATA No change in the basic Flight Manual data.
9.2-33 – 6
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
6
MASS AND BALANCE Refer to Equipment List entries in Section 6 of the basic Flight Manual.
6.1
LOADING CHARTS AND TABLES
O N
O N
LY
–
C
O
PY
N
O
T
C
O
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O
LL
ED
Installation location of the tank along the longitudinal axis of the H/C (see fig. 1).
FO
R
IN
ST
R
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TI
ÏÏÏÏ ÏÏÏÏ ÏÏÏÏ ÏÏÏÏ ÏÏÏÏ ÏÏÏÏ
C.G. position: X – STA 5156
ÏÏÏÏ ÏÏÏÏ ÏÏÏÏ ÏÏÏÏ ÏÏÏÏ ÏÏÏÏ
C.G. position: Y – BL 314
Filler neck 600 mm
Fig. 1 MANUFACTURER’S DATA APPROVED Rev. 0
Typical installation
9.2-33 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
THE FUEL INDICATION IN KG IS BASED ON A STANDARD FUEL DENSITY OF 0.8 KG/LITER. IF FUELS WITH A DIFFERENT DENSITY ARE USED OR WHEN OPERATING AT EXTREME TEMPERATURES, THE INDICATED FUEL WEIGHT CAN DIFFER SIGNIFICANTLY FROM THE ACTUAL FUEL WEIGHT. IT IS THE PILOT’S RESPONSIBILITY TO PERFORM THE WEIGHT AND BALANCE CALCULATION BASED ON THE ACTUAL FUEL QUANTITY AND DENSITY. X–CG (STA)
Y–CG (BL)
50720 101940 153180 204400 255650 306900 358120 409360 460530 511800 562980 614160 665340 716520 767700 818880 870060 895650
N
PY
O C – LY
O N
O N TI C
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R ST
Table 1-1
302 305 306 307 307 307 308 308 308 308 308 308 308 308 308 308 308 308
ED
5072 5097 5106 5110 5113 5115 5116 5117 5117 5118 5118 5118 5118 5118 5118 5118 5118 5118
LL
10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 175
O
12.5 25.0 37.5 50.0 62.5 75.0 87.5 100.0 112.5 125.0 137.5 150.0 162.5 175.0 187.5 200.0 212.5 218.75
295
N TR
4976
Mass moment [kgmm]
Arm [mm]
O
2.6
Arm [mm]
[kg]
C
3.25 1)
Mass moment [kgmm] 12928
[l]
T
MASS
O
CAUTION
767
3020 6100 9180 12280 15350 18420 21560 24640 27720 30800 33880 36960 40040 43120 46200 49280 52360 53900
Fuel loading table
FO
R
IN
1) value for unusable fuel
9.2-33 – 8
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
7
SYSTEM DESCRIPTION
7.1
GENERAL The tank is of the bladder-type contained in a vapor-proof metal case attached to the seat rails in the cargo compartment on the RH side aft of the rear passenger seats. The auxiliary fuel tank shall be configured after installation and de-configured after removal on the VMS/CONFIG sub-page (refer to AMM).
ED
After changing the configuration status of the auxiliary fuel tank, the aircraft must be powered off and re-started for the configuration change to take full effect.
LL
NOTE
T
C
O
N TR
O
The fuel is gravity transferred to the main tank and occurs automatically when the fuel level in the main tank has dropped sufficiently to accept the aux tank fuel quantity (no activity required by the pilot). Therefore it is necessary that the main tank must be filled before the aux tank during refueling operations.
N
O
The auxiliary fuel tank is controlled through the AUX TK switch as follows:
PY
– OFF: The automatic fuel transfer is inoperative. No fuel transfer will take place.
C
O
– NORM: The automatic fuel transfer is active.
O N
LY
–
– EMERG: The fuel transfer is operative, even if the automatic fuel transfer would inhibit this transfer. This mode can be used in case the automatic fuel transfer is not working or fuel is left in the aux fuel tank after the automatic fuel transfer has stopped.
FO
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IN
ST
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O N
CAUTION WHEN THE CAPACITY OF THE MAIN TANK IS INSUFFICIENT TO ACCEPT THE AUX TANK FUEL QUANTITY WHILE THE SWITCH IS SET TO EMERG, THE FUEL WILL FILL UP EXPANSION BOX AND VENT LINES.
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-33 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
Auxiliary tank Roll-over vent lines
Expansion box
O
T
C
O
N TR
O
LL
ED
Refuel
PY
N
Aft main tank
Supply tank
TI
O N
O N
LY
–
C
O
Fwd main tank
AUX fuel tank installation
FO
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IN
ST
R
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C
Fig. 2
9.2-33 – 10
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
7.2
HELIONIX INDICATIONS HELIONIX (see Fig. 3): – Auxiliary fuel tank quantity as graphical level and digital value. on the VMS page.
– Aux fuel transfer flag
on the FND page.
Aux fuel tank with fuel quantity indication
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O N
O N
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–
C
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PY
N
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ED
– Fuel tank flag
Aux fuel transfer flag
Fig. 3
Aux fuel tank with fuel quantity and transfer indication on VMD page
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-33 – 11
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
Fuel tank flag
Fuel tank quantity indication
U
Fuel quantity and transfer indication on FND page
FO
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Fig. 4
C
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–
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N
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ED
AUXILIARY FUEL TANK
9.2-33 – 12
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
8
HANDLING, SERVICING, AND MAINTENANCE
8.1
REFUELING NOTE D Helicopter must be placed on level ground to fill the tank to maximum capacity.
ED
D Main tank must be full before refueling the aux tank. If this is not possible, set the AUX TK switch to OFF (instead of NORM) until the main tank has been refueled. – Check NORM – Check off
O
/
N TR
Fuel transfer indication
LL
AUX TK sw
– Condition, no leakage, no fuel visible inside the lines
Vent-, drain lines
– Check closed
T
C
O
Drain valve
O
Auxiliary fuel tank
C
If max. fuel capacity is almost reached, reduce fuel flow to avoid foaming or spillage of fuel. Spilled fuel must be cleaned immediately.
LY
–
NOTE
– Unlock and place in position, then refuel
O
PY
N
Spill deflector
– Ground
TI
Spill deflector
O N
Auxiliary fuel tank
O N
After refueling:
C
Filler cap
– Place in stow position and lock – Close and secure – Check
FO
R
IN
ST
R
U
Aux tank fuel indication
– Disconnect ground
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-33 – 13
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
8.2
DRAINAGE NOTE
8.2.1
If the auxiliary fuel tank is installed and intended to be used, perform drainage of the auxiliary fuel tank before the first flight of the day.
Drainage procedure for removal of water accululation from the auxiliary fuel tank Observe the warnings and notes for the main and supply tank draining (see basic FLM section 8.3). AUX TK sw
– Check OFF – Check off
AUX FUEL XFER
– Ground properly (see basic FLM section 8.3)
Rear clamshell doors
– Open
Sliding door (at least one)
– Open
Drain tool
– Ground to the ground receptacle on the filler neck of aux fuel tank
C
O
N TR
O
LL
ED
H/C
N
O
T
WARNING D PLACE DRAIN HOSE INTO A SUITABLE CONTAINER (AT LEAST 2 L CAPACITY) PRIOR TO THE CONNECTION OF DRAIN TOOL.
C
O
PY
D TAKE EXTREME PRECAUTION WHEN CONNECTING DRAIN TOOL TO DRAIN VALVE.
–
Drain valve
O N
LY
Drain tool
TI
O N
Drain
– Remove bayonet plug – Connect with drain hose to the drain valve. This will open the drain valve. – At least 0.4l fuel/water from the aux fuel tank
U
C
If the drained fluid does not contain any water:
R
Draining is completed.
ST
If the drained fluid contains water:
IN
Fluid
FO
R
Draining procedure
– Dispose of – Repeat until the fluid does not contain water anymore
After draining of the aux fuel tank: Drain tool
– Remove with drain hose from drain valve.
Drain valve
– Install bayonet plug
Ground connection drain tool
– Remove from ground receptacle on the filler neck of aux fuel tank and from drain tool.
Ground connection H/C
– Remove
Remove the tools and other materials and clean the work area. H/C doors
9.2-33 – 14
– Close MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AUXILIARY FUEL TANK
Auxiliary fuel tank Filler cap Drip tray
4
Drain valve
5
Drain tool
6
Drain hose
7
Bayonet plug
1
PY
N
O
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C
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ED
1
1 2 3
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2
IN
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3
FO
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4 5 6 7 Fig. 5
MANUFACTURER’S DATA APPROVED Rev. 0
System configuration – typical installation
9.2-33 – 15/(9.2-33 – 16 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MAIN ROTOR BLADE FOLDING KIT
FMS
9.2-34
SUPPLEMENT FOR
N TR
O
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ED
MAIN ROTOR BLADE FOLDING KIT
T
C
O
This supplement shall be attached to the BK 117 D-2 Flight Manual (Section 9.2) when the MAIN ROTOR BLADE FOLDING KIT is installed.
N
O
System/Equipment Designation
PY
Main Rotor Blade Folding Basic Kit
C
O
Main Rotor Blade Folding, Fixed Provisions
All All All
O N
LY
–
Main Rotor Blade Folding, Main Kit (Ground support equipment)
Effectivity
O N
For approving authorities and respective dates of approval refer to the log of supplements.
FO
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IN
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NOTE
Date: DEC11, 2015
Approved by EASA
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-34 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MAIN ROTOR BLADE FOLDING KIT
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary.
App.
Page
9.2-34 -1
0
EASA
9.2-34 -2
0
EASA
9.2-34 -3
0
EASA
Rev.No.
App.
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Rev.No.
Rem
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Rev.No.
App.
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LEP – manufacturer‘s data (part 2): Page
Rev.No.
ED
Rev.No.
LL
Page
N TR
LEP – approved (part 1):
O N
LY
LOG OF REVISION
O N
FIRST ISSUE
(see 9.2-34-1)
FO
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ORIGINAL
9.2-34 – 2
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MAIN ROTOR BLADE FOLDING KIT
1
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
2
LIMITATIONS It is not allowed to park the helicopter with folded blades without installed cradles of the ground support equipment.
PREFLIGHT CHECK
N TR
4.1
T
C
O
NORMAL PROCEDURES
N
O
L Main rotor blades
O
PY
L Safety levers of secondary bolts (6)
– Check correct installation both (see fig. 1B)
of
–
– Both locked
O N
PERFORMANCE DATA
– Unfolded
LY
(Number in brackets – see fig. 1)
C
L Safety pins (8)
5
O
No change in the basic Flight Manual data.
4
ED
EMERGENCY AND MALFUNCTION PROCEDURES
LL
3
FO
R
IN
ST
R
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TI
O N
No change in the basic Flight Manual data.
L To be checked before each flight APPROVED Rev. 0
9.2-34 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MAIN ROTOR BLADE FOLDING KIT
6
MASS AND BALANCE Refer to Equipment List entries in Section 6 of the basic Flight Manual.
7
SYSTEM DESCRIPTION The installation of the main rotor blade folding kit provides for two of the blades to be pivoted around their primary retention bolt axes allowing for a narrower overall width to ease ground handling and parking of the helicopter.
8.1
SAFETY INSTRUCTIONS
C
HANDLING, SERVICING, AND MAINTENANCE
PY
N
O
T
8
O
N TR
O
LL
ED
Two opposite blades may be folded by removing the appropriate blade folding bolt (one for each foldable blade) and pivoting one blade forward, the other aft using a handhold blade support bar. Blade cradle assemblies secure the folded rotor blades parallel with the fuselage longitudinal axis.
–
C
O
D For safe folding/unfolding operation of the rotor blades at least two persons are required.
O N
LY
D Do not dis-engage rotor brake during rotation of the main rotor blades around the main blade bolt.
O N
D Do not turn rotor when blades are folded.
U
C
TI
D Do not connect hydraulic ground power unit during folding/unfolding procedure.
ST
R
D Do not lock collective nor block stick during folding/unfolding procedure.
FO
R
IN
D Do not operate controls (neither collective nor stick) during folding/unfolding procedure or while blades are folded. D Parking the helicopter with folded blades is only permissable when cradles of ground support equipment are installed. D Before beginning flight operation, remove all ground support equipment from the H/C and check safety lever for correct installation and locked safety pin.
9.2-34 – 4
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MAIN ROTOR BLADE FOLDING KIT
8.2
FOLDING 1. Turn the main rotor until the tip of the main rotor blade with blue marking is above the tip of the RH horizontal stabilizer. 2. Apply the rotor brake. 3. Install the AFT rotor blade support (1) to the fixed provisions of the tail boom. 4. Release the rotor brake and turn the rotor until the main rotor blade with blue marking fits fully in the blade support cradle. Use the trailing bar (3) if required. Apply the rotor brake.
ED
5. Carefully move the FWD rotor blade support (2) over the main rotor blade with yellow marking and install it to the fixed provisions at the cockpit.
O
LL
6. Remove the quick release pin (8) from the the secondary bolt (6) and open the safety lever (7) of the main rotor blade with the green marking.
N TR
7. Support the blade with the trailing bar (3) and remove the secondary bolt (6).
C
O
8. Install the secondary bolt (6) to the mounting bore (5) in the main rotor head to block the bearing of the main rotor head. Safe the secondary bolt (6) with the quick release pin (8).
O
PY
N
O
T
9. Use the trailing bar to move the main rotor blade with the green marking forward until it is fully in the blade support cradle. Install the short end oft the clamp (4) into the bushing of the secondary bolt at the main rotor head and the long end of the clamp (4) into the bushing of the secondary bolt at the main rotor blade.
LY
–
C
10. Repeat the procedure for the main rotor blade with the red marking. Move this blade backwards.
FO
R
IN
ST
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TI
O N
O N
(Number in brackets – see fig. 1)
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-34 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
LL
ED
MAIN ROTOR BLADE FOLDING KIT
4
N
O
T
C
O
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O
1
3
O
PY
8
ST
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O N
7
O N
LY
–
C
2
5
FO
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IN
6
6
8 Fig. 1
9.2-34 – 6
Main rotor blade folding kit MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) MAIN ROTOR BLADE FOLDING KIT
8.3
UNFOLDING The unfolding procedure is principally in reverse order of the folding procedure. The followig points have to be observed: 1. After removal of clamp (4), the bushings of the blade attachment fork and blade fitting have to be checked for cleanliness.
NOTE D Do not remove the secondary bolt (6) from the mounting bore (5) until the blade is in completely unfolded position (bushings aligned).
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D Do not use excessive force to insert the secondary bolt (6) into the main rotor blade.
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3. Move the flap spring of the safety lever over the lower end of the secondary bolt (6) and secure with the ball lock pin. Wrap overlenght of lanyard around the safety lever (7).
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MANUFACTURER’S DATA APPROVED Rev. 0
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ELECTRO-OPTICAL SYSTEM − WESCAM MX15S (STEP MOUNTED RH)
FMS
9.2-35
SUPPLEMENT FOR
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ELECTRO-OPTICAL SYSTEM − WESCAM MX15S (STEP MOUNTED RH)
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This supplement shall be attached to the BK117 D-2 (HELIONIX STEP 2) Flight Manual (Section 9.2) when the ELECTRO-OPTICAL SYSTEM Wescam MX15S (step mounted RH) is installed.
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System/Equipment Designation
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EOS Wescam MX15S (step mounted RH)
Effectivity
Date: FEB 04, 2020
Approved by EASA
EASA approval no.: 10072374 APPROVED Rev. 0
9.2-35 − 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ELECTRO-OPTICAL SYSTEM − WESCAM MX15S (STEP MOUNTED RH)
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA ref. EASA.21J.700, “DOA”.
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(see page 9.2-35-1)
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ORIGINAL
9.2-35 − 2
APPROVED Rev. 0
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TABLE OF CONTENTS Page GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 5
1.1
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 5
1.2
Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 5
2
LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 6
2.1
Compatibility . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 6
2.2
Operational limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 6
2.2.1
Operator workstation (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 6
2.2.2
Copilot’s 10“ EOS monitor (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 6
2.3
Approved seat configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 7
2.3.1
Operator workstation forward installation . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 7
2.3.2
Operator workstation aft installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 8
2.4
Placards and decals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 9
3
EMERGENCY AND MALFUNCTION PROCEDURES . . . . . . . . . . . . 9.2-35 − 10
3.1
Uncontrolled EOS movements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 10
4
NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 11
4.1
Preflight check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 11
4.1.1
Exterior check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 11
4.1.2
Interior check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 11
4.2
System checks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 11
4.3
Pre-T/O check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 12
4.4
Pre-landing check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 12
4.5
Engine shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 12
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PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 13
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AEO and OEI maximum rate of climb . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 13
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MASS AND BALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 14
7
SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 14
7.1
EOS turret . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 15
7.2
Copilot’s 10” EOS monitor (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 16
7.3
Hand controller unit (HCU) (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 17
7.4
Operator workstation (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 18
7.5
Digital Video Recording System (optional) . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 19
7.6
GPS Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 21
7.7
Audio selector switch (optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 21
APPROVED Rev. 0
9.2-35 − 3
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LIST OF FIGURES Page Fig. 1
Approved seat configuration with operator workstation in forward position . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 7
Fig. 2
Approved seat configuration with operator workstation in forward position and additional equipment (e.g. aux fuel tank) installed in the rear RH part of the cabin . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 7
Fig. 3
Approved seat configuration with operator workstation in aft position
Fig. 4
Step mounted EOS MX15 system − typical installation . . . . . . . . . . . . 9.2-35 − 14
Fig. 5
EOS turret − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 15
Fig. 6
Copilot’s 10” EOS monitor − typical installation . . . . . . . . . . . . . . . . . . 9.2-35 − 16
Fig. 7
Hand Controller Unit (HCU) − typical installation . . . . . . . . . . . . . . . . . 9.2-35 − 17
Fig. 8
Workstation − typical installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 18
Fig. 9
Digital video recorder − typical installation . . . . . . . . . . . . . . . . . . . . . . . 9.2-35 − 19
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1
GENERAL
1.1
INTRODUCTION The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
1.2
ABBREVIATIONS AVM AVT
− Avionic Manual − Automatic Video Tracker
D
DVR
− Digital Video Recorder
E
EON EOW EOS
− Electro Optical Narrow − Electro Optical Wide − Electro Optical System
F
FoV
− Field of View
H
HCU HDIR
− Hand Control Unit − High Definition Infrared
I
IMCU IR
− Internal Master Control Unit − Infrared
L
LoS
− Line of Sight
N
NOHD
− Nominal Ocular Hazard Distance
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− Wire Strike Protection System
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APPROVED Rev. 0
9.2-35 − 5
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2
LIMITATIONS
2.1
COMPATIBILITY For installation of the EOS the respective skid deflector of the Wire strike Protection System (FMS 9.2−15) must be removed. As a result, the effectiveness of the WSPS is significantly degraded. The EOS system is not compatible with: −
OPERATIONAL LIMITATIONS
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2.2
Other EOS installations
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The EOS is not to be used for navigation.
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Minimum crew for EOS operations is one pilot and one additional trained crewmember for operating the EOS system.
Operator workstation (optional)
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The search- and landing light should not be directed toward the EOS to prevent thermal damage.
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The forward fastener of the operator workstation must be installed: Forward installation: Between stud hole 13 and 16.
−
Aft installation: Between stud hole 54 and 57.
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(Cabin rail stud holes are counted from the front and the distance between stud holes is 1 inch).
the monitor bridge has to be in mid position
−
the monitor has to be parallel with bridge
−
the 10” monitor has to be in forward position.
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For takeoff and landing the following limitations apply:
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When piloting the aircraft from the left using NVGs the copilot’s 10” monitor must be switched off and stowed for takeoff, landing and when operating low level. If a fixed glare shield is installed which results in a non-stowable 10” monitor, takeoff, landing and low level operations using NVGs must be conducted from the right hand seat. The use of the copilot’s 10” monitor without glare shield, at night, is prohibited. In case no glareshield is installed, keep monitor switched off and stowed during night flights.
9.2-35 − 6
APPROVED Rev. 0
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2.3
APPROVED SEAT CONFIGURATION With the operator workstation installed, additional seats can only be installed in positions as shown in Fig. 1, Fig. 2 and Fig. 3. Refer also to FMS 9.2-16 and FMS 9.2-40 for seat installation. The operator workstation forward installation is not compatible with the optionally installed vertical rack.
2.3.1
Operator workstation forward installation Operator seat
O N
Fig. 1
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Approved seat configuration with operator workstation in forward position
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Operator workstation
Adapter seat
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Operator workstation
Fig. 2
Flight direction
One seat only is allowed, at either position.
Approved seat configuration with operator workstation in forward position and additional equipment (e.g. aux fuel tank) installed in the rear RH part of the cabin
APPROVED Rev. 0
9.2-35 − 7
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2.3.2
Operator workstation aft installation Adapter seat
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Flight direction
N
Approved seat configuration with operator workstation in aft position
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Operator workstation
9.2-35 − 8
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2.4
PLACARDS AND DECALS Placard: MONITOR BRIDGE HAS TO BE IN MID POSITION FOR TAKEOFF AND LANDING
Location: Front side of the workstation
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Placard:
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MONITOR HAS TO BE PARALLEL WITH BRIDGE FOR TAKEOFF AND LANDING
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Location: Front side of the workstation
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Location: Front side of the workstation
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SEAT MUST BE IN MOST AFT POSITION FOR TAKE-OFF AND LANDING
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Location: Front side of the workstation
APPROVED Rev. 0
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3
EMERGENCY AND MALFUNCTION PROCEDURES For system failures presented by the system itself see “WESCAM OMM”.
3.1
UNCONTROLLED EOS MOVEMENTS Conditions/Indications EOS imagery is moving uncontrollably.
LL
If the EOS LoS was inadvertently steered above 0_ elevation while in AUTO steering mode:
ED
Procedure
Steering mode
− Switch to MANUAL
2.
LoS
− Steer below 0_ elevation
3.
Auto steering mode
− Re-activate as required
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If uncontrolled movement close to LoS at 0_ elevation:
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1.
− Check for EOS fault messages
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1. MFD with EOS video
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If none present:
− Select
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2. Fixed forward
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If EOS does not move to fixed forward: If EOS restart successful: Continue mission
O N
4.
− Re-start
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WHEN EOS IS NOT POWERED REFRAIN FROM HARSH MANOEVERING AS EOS IS NO LONGER STABILISED AND DAMAGE MAY OCCUR.
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CAUTION
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If EOS restart unsuccessful:
− Switch off
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9.2-35 − 10
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4
NORMAL PROCEDURES More detailed information on the operation of the system can be found in the EOS ”Operation Manual”.
4.1
PREFLIGHT CHECK
4.1.1
Exterior check DO NOT PROCEED NEAR THE TURRET UNLESS IT IS MADE SURE THE SYSTEM IS DE−ENERGIZED.
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ED
WARNING
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When additional optional equipment (e.g. workstation, datalink rack) is installed in the cabin, the pilot has to check that the emergency exits are accessible.
N
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NOTE
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Interior check
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4.1.2
− Condition, secured
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1. Attachment and connectors
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1. EOS components
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2. Laser Safety Key slot
O N
3. EOS cb (overhead panel)
O N
4. HCU
− Check sealed unless authorized for use. − Check pushed − Check installed − Check OFF
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SYSTEM CHECKS If EOS is switched ON before engine start OR before disconnecting the EPU, power interrupts could cause the system to fail and require a re-start of the system.
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4.2
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5. POWER sw on HCU
− Condition, secured
1. POWER sw (HCU)
− ON, − Check LED on
2. EOS functions
APPROVED Rev. 0
− Check
9.2-35 − 11
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PRE-T/O CHECK 1. Turret
NOTE
− Check in stow position if EOS not required
There are no mechanical locks to keep the turret in the stow position while powered down therefore the turret must be powered on during the entire flight, even if the system is not used.
2. Copilot’s EOS monitor, stowable (if installed)
− Stow as required (folded forward)
− Check full aft position
− Monitor
− Check stowed (parallel and mid position)
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− Operator seat
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PRE-LANDING CHECK
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4.4
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3. Operator workstation (if installed):
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4.3
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If EOS not longer required:
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1. STOW pb
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− Check in stow position
O N
Keep EOS power switched on. There are no mechanical locks to keep turret in the stow position while powered down.
O N
NOTE
–
2. Turret
− Press (turret moves in stow position)
− Stow as required (folded forward)
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3. Copilot’s EOS monitor, stowable (if installed)
ST
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4. Operator workstation (if installed): − Check full aft position
Monitor
− Check stowed (parallel and mid position)
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Operator seat
4.5
ENGINE SHUTDOWN 1. POWER sw (HCU )
9.2-35 − 12
− OFF
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5
PERFORMANCE DATA
5.1
AEO AND OEI MAXIMUM RATE OF CLIMB All results obtained from the respective diagram, contained in section 5 of the basic Flight Manual, are to be corrected as follows: Helicopter gross mass below 2600 kg: . . . . . . . . . . . . . . . . . . . . . . . . subtract 70 ft/min Helicopter gross mass between 2600 kg and below 3200 kg: . . . . subtract 50 ft/min
LL
The reduction in climb rate is not depending on power settings.
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NOTE
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Helicopter gross mass of 3200 kg and above: . . . . . . . . . . . . . . . . . . subtract 40 ft/min
APPROVED Rev. 0
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6
MASS AND BALANCE Refer to Equipment List entries in Section 6 of the basic Flight Manual.
7
SYSTEM DESCRIPTION For additional information on the system refer to the EOS “Operation Manual”. The step mounted EOS MX15 series are fully digital multi-spectral sensor systems containing a diverse payload of imaging sensors. The MX15 series are used for tactical surveillance designation from a mobile platform and deliver long standoff range day/night surveillance capabilities.
O
LL
ED
Depending on aircraft configuration, the video of the different sensors can be displayed on the MFD1 and MFD4 as digital video and as analog video as well as on optional co-pilot 10” Monitor or cabin workstation.
N TR
The MX15 series systems (Fig. 4) consist of these main components:
O
− the turret MX15 EO/IR system
C
− the MX15 Hand Controller Unit (HCU)
O
T
− a GPS antenna
PY
N
− a digital video recorder (optional)
C
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O N
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The EOS system receives power from the main load bus 2 via a 25A cb. The main load bus 2 is controlled by the EOS cb on the SHED BUS 2 located in the overhead panel.
FO
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GPS antenna
EOS MX15 turret
Fig. 4
9.2-35 − 14
Video recorder
Hand Controller Unit
Step mounted EOS MX15 system − typical installation
MANUFACTURER’S DATA APPROVED Rev. 0
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7.1
EOS TURRET The turret is a combination of the gimbal subsystem and the portion of the sensor subsystem that is physically installed within the gimbal envelope. The gimbal subsystem performs the functions of stabilization, steering and pointing while providing an environmental enclosure for a combination of sensors. The following optional sensors are available depending on the installed model: EOW − Dual channel daylight / low light digital camera with a continuous zoom lens EON − Dual Channel Spotter (DCS) sensor with daylight and low light camera with a fixed focal length lens
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HDIR − High definition thermal camera with a stepped zoom lens
1
N
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The turret itself is mounted with a special adapter plate on the EOS carrier provisions at the foremost point of the right hand step (see Fig. 5).
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EOS turret − typical installation
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Fig. 5
4
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Description
IN
3
HDIR sensor
4
Gimbal
5
Yoke
R FO
EOW/EON sensor
ST
2
Bulkhead
R
1
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7.2
COPILOT’S 10” EOS MONITOR (OPTIONAL) An optional 10” monitor can be installed on the left hand side of the instrument panel. The monitor (if foldable) shall be stowed by folding it in flight direction during takeoff and landing. The monitor is operated through pushbuttons located at the bottom of the display. NOTE D To stow the monitor with foldable glareshield, first the side part has to be folded towards the monitor and subsequently the top part until both are latched at the bottom. Stow the monitor by gentle pressing it towards the side of the instrument panel.
ED
D To un-stow, proceed in reverse order, taking care not to place fingers between the moving parts.
Version with foldable glare shield (stowable)
Copilot’s 10” EOS monitor − typical installation
O N
Fig. 6
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Version with fixed glare shield (not stowable)
O
Standard version without glare shield (stowable)
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D Prevent unfolding the glareshield with monitor in stow position as this will scratch the windshield.
TI
O N
Power − Press the button to turn the unit on or off
ST
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U
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Source select − Press the left side of this button to toggle through VGA/ DVI sources; press the right side to toggle through SD/HD video sources. The right sight is also used to select items in the menu.
FO
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IN
Freeze/Zoom − Press to freeze or zoom the display image Window − Press to select the active window when Picture-in-Picture (PIP) or Split Screen mode being utilized Format − Press to change to full screen Menu − Press to open/close the main menu Day/Night − Press to switch backlighting between day and night modes Luminance − Press right or left to increase or decrease display luminance. This button is also used to navigate through the menu.
The Avalex AVM Operation Manual of the monitor shall be consulted for further operating instructions.
9.2-35 − 16
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7.3
HAND CONTROLLER UNIT (HCU) (OPTIONAL) The Hand Controller Unit (HCU) is an integral part of the MX15 series systems. It is the main operator interface and control to the turret. The hand controller interfaces solely with the turret system and requires no electrical interface with the aircraft. The Internal Master Control Unit (IMCU) is the acting control interface for the turret and manages all operator input commands.
ED
The HCU is stored on a mount which is installed on the center console, depending on aircraft configuration (see Fig 7 − typical installation).
1
3
4
5 HCU
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KEYBOARD
Center console (rear end)
Fig. 7
Hand Controller Unit (HCU) − typical installation
Description 1
Handle
2
Joystick
3
Face plate controls
4
Top buttons
5
Position detents
MANUFACTURER’S DATA APPROVED Rev. 0
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7.4
OPERATOR WORKSTATION (OPTIONAL) An operator workstation can be installed in the cabin. The workstation consists of a crew seat mounted on an adapter plate and a console with up to two monitors and space for various optional equipment (video recorder, downlink control, intercom control) and the associated circuit breakers. Care must be taken when adjusting the operator workstation in height, to not damage workstation or cabin equipment.
22” Main monitor
Video recorder
ED
NOTE
LL
Downlink control
O
10” Side monitor (optional)
optional
N TR
Intercom control
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N
O
Keyboard
C
O
Cricuit breakers
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Downlink transmitter (optional)
Fig. 8
9.2-35 − 18
Workstation − typical installation
MANUFACTURER’S DATA APPROVED Rev. 0
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7.5
DIGITAL VIDEO RECORDING SYSTEM (OPTIONAL) The digital video recorder (DVR) allows recording and playback of multiple video sources. It can also record audio and provides the user the flexibility to save this data/video to multiple storage devices. The recorded video can be displayed on an MFD in the cockpit or on an optional workstation. For further information on the operation of the digital video recorder refer to the respective “Operation Manual” (e.g. AVR8414).
ED
NOTE D The DVR may perform an automatic restart after power interrupt, which may require a restart of the recording.
O
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D The brightness adjustment pushbuttons on the video recorder are not functional, when the videorecorder is installed in the center console.
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D On the DVR, digital or analog EOS video signals can be selected. This selection has an influence on other EOS functionalities. If an (optional) moving target indicator (MTI) is implemented for the EOS and if the digital EOS video signals are routed via DVR, the MTI is only available when on the EOS video recorder a digital EOS signal is selected.
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Power supply is derived from a 5A cb RECORDER on the Main Load Bus 2 at the workstation connector panel (refer to AVM).
R
U
Fig. 9
Ctrl Name
ST
Control
Function Press to acknowledge entries where necessary. (The user can also press the Encoder Knob to acknowledge entries.)
Clear
Press to clear or cancel an operation or backup. The Clear button is also a back button for the On-screen Display (OSD).
Rewind
Press this to skip backward in 10x, 20x, 30x, 40x, and 50x speeds
Play/Pause
Press to toggle between play and pause operation.
Fast Forward
Press to skip forward in 10x, 20x, 30x, 40x, and 50x speeds.
Day/Night
Press to switch the display between day and night modes.
IN
Enter
R FO
Digital video recorder − typical installation
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Control
Ctrl Name
Function Press to increase or decrease brightness of display and keys.
Record
Press to allow one or more video signal to be recorded.
Stop
Press this to stop recording.
Line Select keys 1 and 2
Press to access video inputs for recording/playback.
ED
Luminance
PWR LED
Indicate the color green when recorder is ready for use (Power supplied and built-in-tests successfully completed).
Menu select knob
The Menu Select Knob allows the user to highlight and select a menu option. Turn the knob to navigate through menus up and down, and right to left. Pushing the knob confirms selections and changes cursor levels. It also can be used to jog through videos in playback mode.
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N
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Soft keys 1 to 4 (left to right)
Press to 1 access the File List from the Front Display and OSD 2 access system status and detail pages 3 access live action record and playback controls 4 turn the OSD menu on and off.
O N
Slide the latch to the left to release the display panel door to access the SD card and SSD slots.
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Release latch
9.2-35 − 20
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7.6
GPS ANTENNA The GPS antenna is installed on the rear end of the tail boom (see Fig. 4) and provides the EOS turret with UTC time code, aircraft position, altitude and heading information which is displayed in the MX-series sensor overlays. This information is then utilized by the turret to determine target coordinates and target slant range values.
7.7
AUDIO SELECTOR SWITCH (OPTIONAL)
ED
Different audio recorder devices may be installed in the helicopter. For example: Video recorder, Enhanced Reality System or Downlink transceiver. The audio switching is done via a central audio record selector switch in the cockpit.
and
audio
downlinking
on
all
preselected
C
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− “REC/DL”: Audio recording recorders/transceivers
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The audio selector switch is installed typical on a miscellaneous switch panel in the center console and has three positions:
O
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− ”REC”: Audio recording on all preselected recorder
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− ”OFF”: No audio recording and audio downlinking
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-35 − 21/(9.2-35 − 22 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FMS
9.2-37
SUPPLEMENT FOR
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BALLISTIC PROTECTION KIT
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System/Equipment Designation
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9.2-37 – 1
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LIST OF EFFECTIVE PAGES NOTE
NRD
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Rev.No.
App.
Rev.No.
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LOG OF REVISION
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FIRST ISSUE
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9.2-37 – 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
GENERAL
LIMITATIONS
CONFIGURATIONS REQUIRMENTS
COMPATIBILITY WITH OTHER OPTIONAL EQUIPMENT
N TR
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ED
N
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PLACARDS AND DECALS
O N
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Placard:
–
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CHECK ARMOUR PLATES CLOSED AND LOCKED BEFORE TAKE–OFF
ST
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Location:
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Placard:
TO OPEN PULL THE STRAP
Location: Placard:
PULL UP TO RELEASE Location:
9.2-37 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Placard:
DISTANCE TO THE CABIN SEAT BACKREST (MIN. 70MM) Location:
EMERGENCY AND MALFUNCTION PROCEDURES
LL
PREFLIGHT CHECK
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NORMAL PROCEDURES
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NOTE
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CAUTION
N
PRE-TAKEOFF CHECK
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PERFORMANCE DATA
ST
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9.2-37 – 4
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MASS AND BALANCE
SYSTEM DESCRIPTION
ED
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9.2-37 – 6
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FMS
9.2-38
SUPPLEMENT FOR
C
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ELECTRO-OPTICAL SYSTEM – ULTRAFORCE 350HD
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System/Equipment Designation
PY
N
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Effectivity
9.2-38 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
LIST OF EFFECTIVE PAGES NOTE
NRD
Rev.No.
App.
Page
Rev.No.
Rem
Rev.No.
App.
Rev.No.
Rem
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Rem
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9.2-38 – 2
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GENERAL
ABBREVIATIONS
E
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LIMITATIONS
COMPATIBILITY
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OPERATIONAL LIMITATIONS
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MINIMUM CREW
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OPTIONAL EQUIPMENT LIMITATIONS
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9.2-38 – 3
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APPROVED SEAT CONFIGURATION
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9.2-38 – 4
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9.2-38 – 5
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PLACARDS AND DECALS
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Placard:
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MONITOR BRIDGE HAS TO BE IN MID POSITION FOR TAKEOFF AND LANDING
Location: Placard: MONITOR HAS TO BE PARALLEL WITH BRIDGE FOR TAKEOFF AND LANDING
Location:
9.2-38 – 6
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EMERGENCY AND MALFUNCTION PROCEDURES
NORMAL PROCEDURES For additional information on the operations of the system incl. optional subsystems, refer to the EOS “Operation Manual”.
PREFLIGHT CHECK
Exterior check
O N TR
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N
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WARNING
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NOTE
LY O N
Interior check
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NOTE
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PRE-TAKEOFF CHECK
FO
NOTE
9.2-38 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
PRE-LANDING CHECK
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AFTER LANDING CHECK
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PERFORMANCE DATA
AEO AND OEI MAXIMUM RATE OF CLIMB
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9.2-38 – 8
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
MASS AND BALANCE
SYSTEM DESCRIPTION
EOS ULTRAFORCE 350-HD SYSTEM Multisensor System consisting of:
O
GPS Antenna
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SYSTEM POWER SUPPLY
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TYPICAL INSTALLATION OF THE EOS
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9.2-38 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Operator workstation (optional) NOTE
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9.2-38 – 10
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
Copilot’s 10” EOS monitor (optional) NOTE D D
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D
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Power
FO
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Source select Freeze/Zoom Window Format Menu Day/Night Luminance
9.2-38 – 11/(9.2-38 – 12 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SELF SEALING SUPPLY TANK
FMS
9.2-39
SUPPLEMENT FOR
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SELF SEALING SUPPLY TANK
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System/Equipment Designation
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This supplement shall be attached to the BK 117 D-2 Flight Manual (Section 9.2) when a SELF SEALING SUPPLY TANK is installed.
All
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Self Sealing Supply Tank
Effectivity
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971
APPROVED Rev. 0
9.2-39 – 1
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LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary.
App.
Page
9.2-39 -1
0
EASA
9.2-39 -2
0
EASA
9.2-39 -3
0
EASA
Rev.No.
App.
Page
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Rem
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(see 9.2-39-1)
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ORIGINAL
9.2-39 – 2
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SELF SEALING SUPPLY TANK
1
GENERAL The information contained herein supplements the information of the basic Flight Manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic Flight Manual.
LIMITATIONS
2.1
FUEL QUANTITIES USABLE FUEL
UNUSABLE FUEL
TOTAL FUEL
liters
kg*
769,3
615,4
3,0
60,75
48,6
2,6
68,25
54,6
9,6
898,3
718,6
liters
kg*
Main
764,3
611,4
5,0
4,0
Supply LH
57,0
45,6
3,75
Supply RH
65,0
52,0
3,25
Total
886,3
709,0
12,0
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kg*
O
liters
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TANK
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2
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PLACARDS AND DECALS
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2.2
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* Fuel mass in kg calculated with a fuel density of 0,8kg/litre.
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Placard:
3
FO
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Location: Near filler neck
EMERGENCY AND MALFUNCTION PROCEDURES No change to the basic flight manual data.
4
NORMAL PROCEDURES No change to the basic flight manual data.
5
PERFORMANCE DATA No change in the basic Flight Manual data.
APPROVED Rev. 0
9.2-39 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SELF SEALING SUPPLY TANK
6
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
7
SYSTEM DESCRIPTION The Self–Sealing Fuel Supply Tank is basically identical with the standard supply tank despite of an additional outer layer consisting of self–sealing foam that swells when contacting fuel.
ED
In case of a bullet impact, the self–sealing foam gets in contact with the leaking fuel, swells and seals the hole in the tank.
N TR
O
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The self–sealing foam has a thickness of approx. 5mm. As the outer dimensions of the Self–Sealing Fuel Supply Tank remain unchanged compared to the standard supply tank, the inner dimensions of the tank are smaller.
C
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Due to this the fuel capacity of the Self–Sealing Supply Tank (898,3 ltr / 718,6 kg) is less than that of the standard tank (915.8 ltr / 732,6 kg).
PY
N
O
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Additional Backing Boards are installed in the tank compartment between the helicopter structure and the Self–Sealing Supply Tank. These Backing Boards are made of fibreglass reinforced polyester laminate and are fixed to the helicopter structure.
–
C
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They avoid that burrs from the helicopter reach into the tank and hinder the self–sealing function in case of a bullet impact.
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All other components of the fuel system (pumps, sensors, valves, lines, etc.) as well as the interfaces to the main tank and to the helicopter remain unchanged.
9.2-39 – 4
MANUFACTURER’S DATA APPROVED Rev. 0
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FMS
9.2-40
SUPPLEMENT FOR
ED
SEAT ARRANGEMENT
N TR
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Effectivity
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System/Equipment Designation
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LIST OF EFFECTIVE PAGES NOTE
N R D
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Appr.
Rev.No.
Rem
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9.2-40 – 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
GENERAL
LIMITATIONS COMPATIBILITY
ED
O
CONFIGURATION REQUIREMENTS
C
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N
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If elongated seat track (P/N 251M2013051) copilot side is installed.
LY
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EFFECTIVITY
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PLACARDS AND DECALS
C
O N
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Placard:
USE SEAT IN FORWARD LOCKED POSITIONS ONLY
DO NOT USE SEAT IN REAR UNLOCKED PARKING POSITION
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Placard:
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Location:
Location:
9.2-40 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
EFFECTIVITY
If height adjustable seat(s) (pilot and/or copilot) installed; (B251M2040051 & B251M2048051 or B251M2041051 & B251M2049051)
Placard:
DIESER SITZ DARF NUR IN FLUGRICHTUNG EINGEBAUT BETRIEBEN WERDEN THIS SEAT ONLY MAY BE OPERATED WHEN INSTALLED IN FLIGHT DIRECTION
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EMERGENCY AND MALFUNCTION PROCEDURES
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Location:
PREFLIGHT CHECK
– LY
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WARNING
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Exterior check, fuselage RH side:
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PERFORMANCE DATA
9.2-40 – 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
MASS AND BALANCE
SYSTEM DESCRIPTION
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SEAT LAYOUT
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CAUTION
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9.2-40 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
PASSENGER SEATS (CLUB VERSION)
Configuration and C.G. of passengers NOTE
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C.G. of passengers
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9.2-40 – 6
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
PASSENGER SEATS (ALL FORWARD FACINGVERSION)
Configuration and C.G. of passengers
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9.2-40 – 7/(9.2-40 – 8 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FMS
9.2-41
SUPPLEMENT FOR
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SPECIAL SEAT ARRANGEMENT
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Effectivity
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NOTE
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System/Equipment Designation
9.2-41 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
LIST OF EFFECTIVE PAGES NOTE
N R D
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App.
Rev.No.
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GENERAL
LIMITATIONS
COMPATIBILITY WITH OTHER OPTIONAL EQUIPMENT
ED
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EMERGENCY AND MALFUNCTION PROCEDURES
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Exterior check, fuselage RH side:
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PERFORMANCE DATA
9.2-41 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
MASS AND BALANCE
SYSTEM DESCRIPTION
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FORWARD SEAT CONFIGURATION:
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NOTE D
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9.2-41 – 4
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
AFT SEAT CONFIGURATION
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9.2-41 – 5/(9.2-41 – 6 blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SPECIAL CABIN EQUIPMENT
FMS
9.2-42
SUPPLEMENT FOR
ED
SPECIAL CABIN EQUIPMENT
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This supplement shall be attached to the BK117 D-2 flight manual (subsection 9.2) when the SPECIAL CABIN EQUIPMENT is installed.
O
System/Equipment Designation
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Attachment Rail System
O
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Support Belt
All All All
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For approving authorities and respective dates of approval refer to the log of supplements.
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Flight Manual Bag
Effectivity
Date: DEC 11, 2015
Approved by EASA:
EASA approval no.: 10055971 APPROVED Rev. 0
9.2-42 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SPECIAL CABIN EQUIPMENT
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are new, revised or deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the record of supplement-revisions as necessary.
App.
Page
Rev.No.
9.2-42 -1
0
EASA
9.2-42 -4
9.2-42 -2
0
EASA
9.2-42 -3
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LOG OF REVISIONS
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(see page 9.2-42-1)
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ORIGINAL
9.2-42 – 2
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SPECIAL CABIN EQUIPMENT
1.
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual.
2.
LIMITATIONS
2.1
COMPATIBILITY WITH OTHER OPTIONAL EQUIPMENT
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PLACARDS AND DECALS
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The attachment rail system is not compatible with seats installed in the second and/or third row of the cabin, e.g. the aft seat configuration of the Special Seat Arrangement (FMS 9.2–41). If the attachment rail system is installed only on one cabin side no seats can be installed on the same but only on the opposite cabin side.
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Placard:
IN
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Location: RH cabin wall below window (respective mirrored placard on the LH side)
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Placard:
MAX. LOAD 2 KG
Location: Flight manual bag - upper side Placard: DOWNWARD OR FLIGHT DIRECTION Location: Flight manual bag - upper side
APPROVED Rev. 0
9.2-42 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SPECIAL CABIN EQUIPMENT
Placard:
NICHT ZUR PERSONENSICHERUNG VERWENDEN (MAX. 10KG) DO NOT USE FOR SECURING PERSONS (MAX. 10KG)
EMERGENCY AND MALFUNCTION PROCEDURES
LL
3.
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Location: Beside attachment points at frame 3000
PREFLIGHT CHECK
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NORMAL PROCEDURES
N
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No change to the basic flight manual data.
PY
Interior check:
– Condition, secured
PERFORMANCE DATA
O N
5.
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Special cabin equipment
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No change to the basic flight manual data.
9.2-42 – 4
APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) SPECIAL CABIN EQUIPMENT
6.
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
7.
SYSTEM DESCRIPTION
7.1
ATTACHMENT RAIL SYSTEM (OPTIONAL)
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A rail system can be installed at the LH and/or RH side of the cabin. On each side two horizontal rails can be attached to brackets mounted on the multi-purpose-fittings of the airframe and secured via ball-locking-pins. A maximum of three vertical rails with a minimum distance of 25,4 cm (10 inch) each can be installed on top of the horizontal rails using quick release fittings.
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The rail system can be used to secure cargo or install equipment and can hold a maximum load of 75kg each. Detailed information about permissible load distribution is given on a respective placard at the cabin side wall (see section 2).
Fig. 1 7.2
Attachment rail system – typical installation
SUPPORT BELT (OPTIONAL) A support belt can be installed on each side of the cabin to hold and stabilize equipment used near the sliding doors, e.g. cameras. The support belt is attached at the sliding door frame to an attachment point at frame 3000 and the securing point at frame 4000. The belt consists of a textile strip sewed together with karabiners for installation, with an elastic part allowing to damp vibrations and flight movements and with an adjuster for length adjustment.
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-42 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
LL
Support belt – typical installation
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Fig. 2
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SPECIAL CABIN EQUIPMENT
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NOTE D The support belt must be stowed for takeoff and landing.
N
FLIGHT MANUAL BAG (OPTIONAL)
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7.3
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D The attachment points over the sliding doors at frame 3000 are not intended to secure people.
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In case of missing storage possibility e.g. during flight with doors removed, a special leather bag to store one Flight Manual can be installed at a suitable position on the cabin floor. The bag is attached directly to the seat rails of the floor using two single stud fittings. Alternatively, the bag can be attached with one stud in a multipurpose fitting and the other in an outer seat rail or vertically at the attachment rail system.
NOTE
9.2-42 – 6
Fig. 3
Flight manual bag – typical installation
The flight manual bag has to be installed bottom down with its opening against flight direction or, if installed vertically, with its opening at the top.
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
FMS
9.2-43
SUPPLEMENT FOR AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
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(AVIDYNE TAS 620A)
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System/Equipment Designation
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This supplement shall be attached to the BK117 D-2 Flight Manual (subsection 9.2) when the Airborne Collision Avoidance System (ACAS) is installed.
All
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For approving authorities and respective dates of approval refer to the log of supplements.
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Airborne Collision Avoidance System (Avidyne TAS 620A)
Effectivity
Date: MAR 21, 2016
Approved by EASA:
EASA approval no.: 10057321
APPROVED Rev. 0
9.2-43 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA No. EASA.21J.700, “DOA”.
0
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9.2-43 -3
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9.2-43 -4
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9.2-43 -5
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LOG OF REVISION
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(see page 9.2-43-1)
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ORIGINAL
DEC 18, 2017
REVISION
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REVISION 1 EASA approval no.: 10064108
Date: DEC 12, 2018
2
(see entry below)
Approved by EASA:
EASA approval no.: 10067961
9.2-43 – 2
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
1
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual.
– Airborne Collision Avoidance System
ATC
– Air Traffic Control
CBIT
– Continuous Built-In Test
CPA
– Closest Point of Approach
EOS
– Electro-optical sight
IBIT
– Initiated Built-In Test
LRU
– Line Replaceable Unit
OT
– Other traffic
OVHP
– Overhead panel
PBIT
– Power-up Built-In Test
PA
– Proximate Advisory
sk
– soft key
TA(S)
– Traffic Advisory (System)
LIMITATIONS
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ACAS
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ABBREVATIONS
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CAUTION D ACAS INFORMATION IS ADVISORY ONLY. D IN VFR: IF A TA OCCURS, DO NOT INITIATE A MANEUVER BASED ON THE ACAS DISPLAY WITHOUT FIRST VISUALLY ACQUIRING THE THREAT. D IN IFR: IF A TA OCCURS, DO NOT INITIATE A MANEUVER BASED ON THE ACAS DISPLAY UNLESS RECONFIRMATION IS OBTAINED FROM ATC TO AVOID THE INTRUDER AIRCRAFT. D THE ACAS IS NOT ABLE TO TRACK AND NON–TRANSPONDER EQUIPPED / OPERATED AIRCRAFT.
DISPLAY
D SOME TRANSPONDER EQUIPPED AIRCRAFT MAY NOT BE SHOWN, MAY BE SHOWN AT A WRONG AZIMUTH, OR MAY POP-UP AT CLOSE DISTANCE. APPROVED Rev. 2
9.2-43 – 3
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
D THE INTRUDER THAT YOU SEE MAY NOT BE THE INTRUDER THAT ACAS HAS DETECTED. CONTINUE TO MONITOR ACAS AND VISUALLY SCAN OUTSIDE EVEN AFTER THE TRAFFIC IS OBSERVED. D BECAUSE OF ENCODER VARIATIONS, ANY INTRUDER LESS THAN 300 FT ABOVE OR BELOW SHOULD BE CONSIDERED TO BE AT THE SAME ALTITUDE. Target duplication (a target splitting into two targets at same altitude and close to the same range) may be encountered for a few seconds. Target duplication is generally caused by reflections on the ground, on water or nearby buildings.
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NOTE
9.2-43 – 4
APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
2.1
COMPATIBILITY WITH OTHER OPTIONAL EQUIPMENT External optional systems like EOS, High Intensity Search Light (HISL), cargo hook or loudspeakers may temporarily shadow one of the ACAS antennas and/or cause signal reflections, signal drop outs and range degradation. WHEN EXTERNAL OPTIONAL SYSTEMS ARE INSTALLED, POSSIBLE UNRELIABLE ACAS INDICATION AND DEGRADED RANGE PERFORMANCE MAY BE ENCOUNTERED.
CAUTION
EMERGENCY AND MALFUNCTION PROCEDURES
3.1
ACAS FAILURE
C
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FAIL
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FAILURE INDICATIONS
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3
and
ACAS FAIL
N
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ACAS
ACAS failure indication on FND
O
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ACAS sk FAIL indication on NAVD
–
C
Conditions/Indications – ACAS failure detected (e.g. TAS processor failed).
LY
– ACAS test failed.
O N
– ACAS is not longer usable.
O N
If MFD 4 fails ACAS is no longer available.
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NOTE
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Procedure
ST
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Continue flight
NORMAL PROCEDURES
4.1
SYSTEM CHECKS
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The ACAS self test will be launched automatically (PBIT, CBIT) after switching BAT MSTR ON and AVIONIC MASTER 2 switch ON, or on pilots demand (IBIT) using the REPEAT switch. No dedicated TEST indication is provided on the Master List. A failed test will be indicated by an ACAS FAIL annunciation on the FND and NAVD. After successful completion of the self test the ACAS traffic advisories will be indicated on the FND.
4.2
OPERATION ACAS traffic indications are only available on MFD4 or MFD1 in NAVD or DMAP mode. It is recommended to select NAVD or DMAP on one of both displays to enhance situational awareness. In case of TA alert the relative bearing will be displayed on the HSI.
APPROVED Rev. 2
9.2-43 – 5
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
5
PERFORMANCE DATA No change to the basic flight manual data.
6
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
SYSTEM DESCRIPTION
7.1
GENERAL
LL O
Additional information about the system has to be obtained from the pilot’s guide.
N TR
NOTE
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7
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The system in the BK117 D-2 is an actively interrogating onbord air traffic detection system (ACAS I), that indicates, within its surveillance range, the presence and relative location of transponder equipped intruder aircraft and an aural and visual alert informing the crew of a traffic advisory (TA). It provides a maximum 30 second alert while tracking up to 50 transponder equipped aircraft.
MAIN COMPONENTS
U
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– Mounting Tray
C
– Bearing antenna kit
TI
– Transceiver TAS620A
O N
7.2
O N
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If an aircraft is on a conflicting path, the TAS620A generates a traffic advisory (intruder alert) on MFD4 or MFD1 in NAVD or DMAP mode (amber traffic symbol) and the corresponding synthesized-voice audio outputs if necessary. In case of TA alert, the relative sector will be displayed on the HSI.
ST
– Transponder coupler
R
IN
Furthermore the following components interfaced with the TAS620A can be optionally installed:
FO
– RN7 (Euroavionics) or – RN7CM (Euroavionics) 7.3
POWER SUPPLY The TAS620A transceiver is connected to the shedding 2 power bus bar supplying 28VDC. The connection is equipped with 3A circuit breaker located on the OHCP.
9.2-43 – 6
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
7.4
CONTROLS AND OPERATING MODES
7.4.1
Controls
7.4.1.1 ACAS three position switch A three position switch is located in the overhead console and allows the flight crew to select the following operating modes: MUTE
N TR
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N O R M REPEAT
C T
O
ACAS sw on OVCP - typical installation
N
Fig. 1
O
ACAS
PY
NORM:
O N
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The NORM position is the standard mode of operation and provides traffic advisory on MFD4 and MFD1 when selected in NAVD or DMAP mode. If an aircraft is on a conflicting path the respective aircraft symbol will be indicated in amber. Simultaneously a voice message is generated directing the flight crew’s attention to the potential conflict. In case of TA alert, the relative sector will be displayed on the HSI.
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REPEAT:
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Activation of the REPEAT mode provides two functionalities: Initiates a self test (IBIT, approx. 2sec)
–
Repetition of the last traffic threat in combination with an updated relative position indication with the following potential voice messages:
FO
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–
D No current active TA, TAS620A functioning normally, no higher priority aural alerts playing (e.g. HTAWS or “Hands-on“) “No advisiories” D Current active TA, TAS620A functioning normally, no higher priority aural alerts playing (e.g. HTAWS or “Hands-on”) “Traffic, XX o’clock/no bearing, high/low/same alt/Altitude unavailable, XX miles/no range” D TAS620A failure detected “TAS Altitude Data Invalid”, or “TAS Code XX“, or No audible announcement (could also be the case if higher priority aural alert is active)
MANUFACTURER’S DATA APPROVED Rev. 2
9.2-43 – 7
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
MUTE: In MUTE mode the voice messages are suppressed as long as the switch remains selcted to MUTE. A green ACAS MUTE advisory will be displayed in the Master List. 7.4.1.2 Acknowledge button on cyclic grip The crew can acknowledge a current active aural alert from ACAS by pressing the ACK (RESET) push button on either cylic stick. This will momentarily stop the aural announcement of the detected intruder. Detection of further intruders however will trigger new visual and aural alerts.
ED
Operating modes
LL
7.4.2
N TR
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7.4.2.1 Test modes
PBIT: the test routine is run after every power–on to check the ACAS system for failures.
T
C
O
CBIT: the routine continuously monitors the ACAS system for failures without interrupting the required ACAS functionality.
O
PY
N
O
IBIT: In addition the system offers the capability to perform an ACAS self–test (ACAS switch position REPEAT for >2 sec) upon crew request. The self–test mode suspends the active ACAS I interrogation of surrounding traffic.
LY
–
C
If the self-test result is OK the ACAS returns to its previous operating mode . If the test result shows a system failure, it switches to failure mode.
O N
7.4.2.2 Failure modes
O N
ACAS failure mode is entered automatically if the TAS620A detects any internal or external failure. The following failures will cause the ACAS to switch to failure mode:
U
– Antenna failure
C
TI
– Internal ACAS LRU failure
ST
R
– Unavailability of barometric altitude
IN
– Loss of communication with the MFDs
FO
R
The TAS620A detects failure by its internal PBIT and CBIT routines or by flight crew initiated IBIT routine. If the TAS620A detects a failure, the interrogation of nearby traffic is suspended. No ACAS warnings will be provided in case of a failed system. Failures are indicated as follows:
FAIL ACAS ACAS sk FAIL indication on NAVD
and
ACAS FAIL ACAS failure indication on FND
The optional installed DMAP indicates the ACAS failure mode and deactivates the traffic display.
9.2-43 – 8
MANUFACTURER’S DATA APPROVED Rev. 2
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
7.5
ACAS INDICATION ON DISPLAY
7.5.1
FND main mode The FND main mode contains the following indications related to ACAS: – Master list entry – Reduced ACAS traffic display in horizontal situation indication area of FND
O
LL
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The ACAS indications on the FND main mode cannot be suppressed or cancelled by the flight crew.
ALT
NAV
IAS
C
100
4
10
10
80
–
20
O N
3
20
LY
VY
30
33
600 DA
17
16
16
1500
15
14
14
13
13
D A
D H B A R O
Traffic advisory
1013 200 hPa DH
Master list
C
TRFC
R ST IN R BKD2_FLH_0450_R
FO
N A V
17
5
TI
5
U
C R S
+ C T R S –
N
O N
R N G
10
C
10
O
100
2
O
20
PY
120
20
T
18
N
6
CLOCK
O
OFF
N TR
ON
DTK
LVL
2.5
RNP
A C K
337 3.00 FMS2 GPS
LFMH + L U M –
30.0 NM 20 min
DCPL
Fig. 1
MANUFACTURER’S DATA APPROVED Rev. 2
550 Kg ND
HDV
WXR
SVS
OAT
13 _C
+ B R G –
FND display main mode - typical indication
9.2-43 – 9
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS)
The following symbols are used to indicate traffic information in the horizontal situation indication area of the FND display (see Fig. 1) : Traffic advisory, above, approaching from the front right–hand side
TRFC
ABV Traffic advisory, level, approaching from the front left–hand side
ED
LVL
O
LL
TRFC
C
BLW
N
O
T
TRFC
O
N TR
Traffic advisory, below, approaching from the back
C
ABV
O N
LY
–
TRFC
O
PY
Traffic advisory, no altitude information, approaching from the back left–hand side
O N
– ABV is indicated if the intruder has a relative altitude of >300ft
ST
R
U
C
TI
– LVL is indicated if the intruder has a relative altitude of –300ft v relative altitude v300ft
IN
– BLW is indicated if the intruder has a relative altitude of 1000 ft AGL Blue
C
O
Obstacle > 1000 ft AGL Amber
N
O
T
Obstacle > 1000 ft AGL Red
C
O
PY
Obstacle < 1000 ft AGL Lighted Blue
LY
–
Obstacle < 1000 ft AGL Lighted Amber
O N
O N
Obstacle < 1000 ft AGL Lighted Red
C
TI
Obstacle > 1000 ft AGL Lighted Blue
Obstacle > 1000 ft AGL Lighted Red
FO
R
IN
ST
R
U
Obstacle > 1000 ft AGL Lighted Amber
Line obstacles
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-49 – 21
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
7.1.2.5 Static user waypoints Static user waypoints are waypoints with a predefined position and category, which can be created using the ground station. This allows the customer to create a database with specific user waypoints, which are not part of the standard aeronautical data (e.g. hospitals, police stations, off shore wind generators, etc.). CAUTION
THE USER WAYPOINTS ARE NOT SUBJECT TO INDEPENDENT VERIFICATION. USER WAYPOINTS SHALL BE USED FOR INFORMATION ONLY. SYMBOL
USER WAYPOINT TYPE
LL
ED
Static User Wpt Cat 1
N TR
O
Static User Wpt Cat 2
C
O
Static User Wpt Cat 3
N
O
T
Static User Wpt Cat 4
C
O
PY
Static User Wpt Cat 5
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
7.1.2.6 DMAP database (INFORMATION and DATABASE window)
Fig. 6
DMAP database
The information window can be accessed in two ways: – Select the object displayed in the map using the PNTR function. – Navigate inside the DB (database) window.
9.2-49 – 22
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Obtaining information about a displayed object: To access the information window of a displayed object (airport, navaid, airspace, etc.), select the pointer by pressing PNTR, then move the pointer to the desired object using the rotary knob on the display. short press on the knob
long press on the knob
i.e.: when difficult to select because many objects in the same area:
N TR
O
LL
ED
Opening of a selection window, i.e.:
O
Select the desired object (if multiple co–located objects are shown). Validate selection by a long press.
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
Opening of the “select point” window, 8 objects maximum classified per type, i.e.:
ST
R
U
If the pointer is not near any object, a long press on the rotary knob will display:
IN
Information of free point:
FO
R
– coordinates and altitude – Minimum Of Route Altitude (MORA)
Fig. 7
MANUFACTURER’S DATA APPROVED Rev. 1
Access to information window
9.2-49 – 23
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Navigating inside the DMAP database:
O
Navigation inside DMAP DB
T
C
Fig. 8
N TR
O
LL
ED
To access the database window, push the DB key and navigate as follows:
DATABASE WINDOW DESCRIPTION
N
O
ITEM
Number of pages for the selected categroy/filtering.
2
Object category, use outer knob to select: ALL, ARPRT(airport), HLPRT (heliport), NVAID (navaid), INTRS (intersections, USRWP (user waypoints), ALTFP or ACTFP (alternate/active flight plan from FMS if any).
LY
–
C
O
PY
1
O N
Push consecutively the related LSK to display the objects: or
O N
– the more recently used:
TI
3
(green color) or
U
C
– the nearest neerest
(if any, amber color)
ST
R
– the nearest with filtering criteria
FO
R
IN
Push related LSK to filter (FLTR) the list. DATABASE window becomes:
4
Enter first digits of the object with knob. Push OK LSK to activate filter and return to the previous view.
9.2-49 – 24
5
Selected object (turn inner knob to select).
6
Other objects in following page(s) (press related key to get access). MANUFACTURER’S DATA APPROVED Rev. 0
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When the desired object is found and selected: – A short press on the rotary knob opens a window with possible actions (e.g. CENTER DMAP) – A long press on the rotary knob displays the related object information page (see below). The outer knob can then be used to select a category (COMM, AREAS,...). IN SOME CASES, THE INFORMATION WINDOW DOES NOT MATCH THE SELECTED DATA FIELD. THEREFORE, THE PILOT MUST ALWAYS DOUBLE CHECK THE INFORMATION RETRIEVED FROM THE DMAP DATABASE.
LY
To exit from INFORMATION window:
category with the outer rotary knob and,
O N
O N
– Select
TI
– Activate
C
AIRWAYS and AIRSPACE information cannot be retrieved from DATABASE window. To consult this information, select it on the map (it may be necessary to change the range to display the object).
IN
ST
R
U
NOTE
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
CAUTION
FO
R
Information window content: The outer knob allows selecting the following information categories: – GNRL : General – COMM : Radio communication data – AREAS: Restricted or controlled areas – RNWYS : Runway data – HLIPD: Helipad data – NVAID : Navaids – PRCDR : Procedures – USRFL : User files. Not all categories are present for every type of object. MANUFACTURER’S DATA APPROVED Rev. 0
9.2-49 – 25
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7.1.2.7 Sending a geographic location from DMAP to FMS On DMAP format, it is possible to select a point of interest and to transmit its geographic location (latitude & longitude) to the FMS. On FMS, the crew can save the position as a new user waypoint. It is possible then to use the new user waypoint in the flight plan and to navigate to the desired point of interest. There are multiple means of transferring geographic coordinates to the FMS:
T
C
O
N TR
O
LL
ED
– Using the pointer, a contextual menu can be opened by a short press on the rotary knob on a waypoint symbol or any free point on the map: command appears in this menu.
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
– Using the database window, a contextual menu can be opened by a short press on the rotary knob on any listed item (except flight plan waypoints). command appears in this menu.
FO
R
IN
ST
– By a long press on the rotary knob on a waypoint symbol on the map, or an item in the database window list, a corresponding information window opens. command appears in this menu.
When a waypoint is sent to the FMS, a new user waypoint window will pop-up. Refer to the FMS user guide to name and save this new waypoint.
9.2-49 – 26
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7.1.2.8 SVS horizontal field of view indication on DMAP (if SVS installed)
T
C
O
N TR
O
LL
ED
If Synthetic Vision System (SVS) is installed (refer to Basic FLM), its horizontal field of View and range can be depicted on DMAP. This provides an easier correlation between the outside and DMAP view. The SVS field of view is depicted as alternating black and white lines, reflecting the actual SVS range at zero pitch.
SVS on DMAP
PY
N
O
Fig. 9
O
7.1.2.9 ACAS overlay (if ACAS installed)
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
The ACAS symbols on the DMAP are identical to the symbols on NAVD (refer to FMS 9.2–3, Airborne Collision Avoidance System (ACAS)).
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-49 – 27
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7.1.2.10 Fuel range rings (optional) CAUTION
THE FUEL RANGE RING INDICATION SHALL BE USED FOR INFORMATION ONLY. IT DOES NOT REPLACE PROPER FUEL PLANNING.
Available only when fuel flow gauges are installed and configured. When fuel is selected in LAYERS SETUP/OVERLAY sub-mode, the fuel range ring provides a graphical indication of the estimated range on ground for a straight line path, in any direction.
ED
The fuel range is calculated from the endurance (as shown on the VMS page), the current airspeed, and the current estimated wind.
N TR
O
LL
The layer consists of two fuel rings: Total fuel ring and Reserve fuel ring. – The Reserve ring corresponds to the range with a 20 min reserve time.
Fuel range selection
When LOW FUEL is indicated, the fuel range rings will disappear. Strictly follow the LOW FUEL emergency procedure.
FO
R
IN
ST
R
U
C
TI
NOTE
O N
O N
Fig. 10
LY
–
C
O
PY
N
O
T
C
O
Each Ring has 2 colours, inner and outer.
Fig. 11
9.2-49 – 28
Example of Reserve fuel ring selection MANUFACTURER’S DATA APPROVED Rev. 0
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O
Example of total fuel ring selection
PY
N
Fig. 12
T
C
O
N TR
O
LL
ED
HELIONIX DIGITAL MAP SYSTEM (DMAP)
O
7.1.2.11 Airspace Auto-Filtering
–
C
Airspace filtering allows manual and automatic filtering of controlled and restricted airspace.
LY
– Auto-filter: Disables display of airspaces 2700 ft. above and below aircraft altitude,
O N
– Manual-Filter: Allows individual selection of airspaces by class (Class A to Class G).
FO
R
IN
ST
R
U
C
TI
O N
Controlled airspace can be de-cluttered by airspace class and aircraft height. Restricted airspace can be de-cluttered by aircraft height.
Fig. 13
MANUFACTURER’S DATA APPROVED Rev. 0
Layer setup window with airspace filtering selection
9.2-49 – 29
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
7.1.3
DMAP mode selection
AVAILABLE OPTIONS
Control for the display modes:
1. ALL
all layers are displaeyd
2. AERONAUTIC
aeronautical data layer
3. OVERLAY
overlay layer
4. OBSTACLE
obstacle layer
5. USE
user way points
6. NONE
disable all layers
If long press:
Allows the user to customize the layers:
TI
O N
LY
If short press:
C U
LAYR
FO
R
IN
ST
R
L1
COMMENTS
O N
Label on the left side of the screen
C
LABEL
–
KEY NO.
O
PY
N
O
T
C
O
N TR
O
LL
ED
7.1.3.1 Overlay selection
Layer data window
AERO: aeronautical data layer OVERLAY: overlay layer
NOTE D Obstacles (if selected) are removed when switching to PLN mode or POINTER mode. D The layer selection window must be closed before changing to PLN mode or POINTER mode.
9.2-49 – 30
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7.1.3.2 Range selection
KEY NO.
LABEL
AVAILABLE OPTIONS
COMMENTS
ED
Label on the left side of the screen
LL
1. 0.1 NM
O
2. 0.25 NM
N TR
3. 0.5 NM RNG
5. 2 NM
C
L2
O
4. 1 NM
O
T
6. 5 NM
Map p scale control
N
7. 10 NM
IN
O
ST
R
U
C
TI
O N
O N
LY
7.1.3.3 Configuration modes selection
–
C
9. 40 NM
PY
8. 20 NM
LABEL
AVAILABLE OPTIONS
COMMENTS
FO
R
KEY NO.
Label on the left side of the screen
L4
CNFG
MANUFACTURER’S DATA APPROVED Rev. 0
Configuration modes:
Control for the configuration modes (preselected layers):
1. IFR
to load the IFR configuration
2. VFR
to load the VFR configuration
3. USER
to load the USER configuration
4. SET USER
to save the layers currently selected in the user configuration in memory mode.
9.2-49 – 31
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) HELIONIX DIGITAL MAP SYSTEM (DMAP)
7.1.3.4 Map type selection
KEY NO.
LABEL
AVAILABLE OPTIONS
COMMENTS
2. VECTOR
vector map
3. NONE
none
4. RASTER
raster (scanned) map
5. SAS
Sun Angle Shading map
O
N TR
O
LL
colored SAS map
C
MAP
1. TOPO
T
L7
ED
Label on the right side of the screen
LABEL
AVAILABLE OPTIONS
COMMENTS
TI
KEY NO.
O N
O N
LY
–
C
O
PY
N
O
7.1.3.5 Pointer selection
U
C
Label on the right side of the screen PNTR
1. ON 2. OFF
Used to activate the pointer mode
FO
R
IN
ST
R
L10
9.2-49 – 32
MANUFACTURER’S DATA APPROVED Rev. 0
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7.1.3.6 Map mode selection
KEY NO.
LABEL
AVAILABLE OPTIONS
COMMENTS
ED
Label on the bottom of the screen
O
LL
Direction of the map, north at top to heading at top: Heading up. Own aircraft symbol is at the map center.
B3
N TR
1. ROS
North up. Own aircraft symbol is at the map center.
T
C
O
2. PLN
Heading up. Own aircraft symbol is in the lower 75% of the display.
PY
N
O
3. SCT
The PLAN mode is intended for pre-flight planning. If used in flight, the pilot must be cautious of the unusual map orientation.
LY
–
C
O
NOTE
IN
ST
R
U
C
TI
O N
O N
7.1.3.7 HTAWS selection (if installed)
LABEL
AVAILABLE OPTIONS
COMMENTS
R
KEY NO.
FO
Label on the bottom of the screen
B6
Short press
To display the HTAWS layer and the terrain coloration over the 2D DMAP (refer to Basic FLM, Section 7).
Long press: HTAWS control window
To display the HTAWS virtual control pane in the bottom part of the display (refer to Basic FLM, Section 7).
HTAWS
Refer to the basic flight manual for further details on HTAWS. NOTE
The HTAWS layer is automatically removed when switching to PLN or POINTER mode.
MANUFACTURER’S DATA APPROVED Rev. 0
9.2-49 – 33
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7.1.3.8 ACAS selection (if installed)
KEY NO.
LABEL
AVAILABLE OPTIONS
COMMENTS
LL
O
Short press
O
The ACAS layer (if selected) is removed when switching to PLN mode or POINTER mode.
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
NOTE
ACAS
To display the ACAS layer and the ttraffic display over the 2D DMAP (refer to FMS 9.2-43).
N TR
B6
ED
Label on the bottom of the screen
9.2-49 – 34
MANUFACTURER’S DATA APPROVED Rev. 0
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7.2
NAVD WITH A DMAP LAYER
7.2.1
General The NAVD format can be used with TOPO or SAS map background. The map display in NAVD format depends on the selection of HTAWS (see Table below). The map background can be used with ACAS overlays; it is not compatible with a weather radar overlay. MAP ON
HTAWS OFF
NAVD
NAVD + TOPO (without HAT and without obstacles)
HTAWS ON
NAVD + Obstacles + full HAT
NAVD + SAS DMAP + obstacles + partial HAT
LL
Height above terrain coloring with SAS map is limited to the display of amber and red colors only.
N TR
O
NOTE
O
Control and display indications
FO
R
IN
ST
R
U
C
TI
O N
O N
LY
–
C
O
PY
N
O
T
C
7.2.2
ED
MAP OFF
ITEM 1
LABEL MAP
MANUFACTURER’S DATA APPROVED Rev. 0
AVAILABLE OPTIONS Map type selection: – TOPO The control is inactive if HTAWS is selected.
9.2-49 – 35
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2)
MAP + HTAWS format
MAP
FO
R
IN
ST
R
U
1
2
9.2-49 – 36
TI
LABEL
C
ITEM
O N
O N
Fig. 14
LY
–
C
O
PY
N
O
T
C
O
N TR
O
LL
ED
HELIONIX DIGITAL MAP SYSTEM (DMAP)
HTAWS
AVAILABLE OPTIONS
Map type (auto reversion to SAS): – SAS The control is inactive if HTAWS is selected. Obstacles + partial HAT (2 colors – yellow and red) NOTE
HTAWS is orientation.
not
avaliable
in
non-heading
up
MANUFACTURER’S DATA APPROVED Rev. 0
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) ENHANCED REALITY SYSTEM (ERS)
FMS
9.2-50
SUPPLEMENT FOR
N TR
O
LL
ED
ENHANCED REALITY SYSTEM (ERS)
O
T
C
O
This supplement shall be attached to the BK117 D-2 Flight Manual (subsection 9.2) when the Enhanced Reality System is installed.
PY
N
System/Equipment Designation
All
O N
For approving authorities and respective dates of approval refer to the log of supplements.
FO
R
IN
ST
R
U
C
TI
O N
NOTE
LY
–
C
O
Enhanced Reality System (ERS)
Effectivity
The technical content of this document is approved under the authority of the DOA ref. EASA. 21J.700
Date: OCT 18, 2019
APPROVED date – 0.0 see entry above Rev.
9.2-50 – 1
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LIST OF EFFECTIVE PAGES NOTE
N, R, or D indicate pages which are New, Revised or Deleted respectively. Remove and dispose of superseded pages, insert the latest revision pages and complete the Record of Supplement-Revisions as necessary. The column “Approved by” which is only shown for approved pages shows either the approving authority (e.g. EASA) or, in case of minor changes according to DOA ref. EASA.21J.700, “DOA”.
DOA
9.2-50-2
0.0
DOA
9.2-50 -3
0.0
DOA
Rev.No
Rem
LL
–
O
9.2-50-1
ED
LEP – approved (part 1):
0.0
9.2-50 -7
0.0
9.2-50 -5
0.0
9.2-50 -8
0.0
9.2-50 -6
0.0
Rev.No
Rem
PY
N
9.2-50 -4
Page
O
Page
C
Rem
T
Rev.No
O
Page
N TR
LEP – manufacturer‘s data (part 2):
–
C
O
LOG OF REVISION
O N
LY
FIRST ISSUE
see page 9.2–50–1
FO
R
IN
ST
R
U
C
TI
O N
ORIGINAL
9.2-50 – 2
APPROVED Rev. 0.0
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1
GENERAL The information contained herein supplements the information of the basic flight manual; for limitations, procedures, and performance data not contained in this supplement, refer to the basic flight manual. ABBREVIATIONS Definition
ADDR
Adresse
BPC
Basic Platform Computer (Extension box)
ERS
Enhanced Reality System
HD
High Density
HMI
Human Machine Interface
LRF
Laser Range Finder
VSU
Video Switching Unit
WLAN
Wireless Local Area Network
C
O
N TR
O
LL
ED
Acronym
EMERGENCY AND MALFUNCTION PROCEDURES
O N
3
LY
–
C
No change in the Flight Manual data.
PY
LIMITATIONS
O
2
N
O
T
1.1
C
NORMAL PROCEDURES
R
U
4
TI
O N
No change in the Flight Manual data.
PREFLIGHT CHECK/ SYSTEM CHECK
R
4.1
IN
ST
For additional information, refer to the ERS Operators Manual.
FO
The self-test starts automatically, after the AVIO MSTR switches are switched ON.
5
PERFORMANCE DATA No change to the basic flight manual data.
APPROVED Rev. 0.0
9.2-50 – 3
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6
MASS AND BALANCE Refer to equipment list entries in section 6 of the basic flight manual.
7
SYSTEM DESCRIPTION
7.1
GENERAL For additional information, refer to the ERS Operators Manual.
O
N TR
O
LL
ED
The ERS provides real time overlay of geographic and mission related information on full HD motion videos from the aircraft’s surveillance equipment. The system features crucial topological information overlays of the operational terrain. The depiction of all overlaid detail information depends on the actual zoom factor and observation distance. It is processed seamlessly in real time.
T
C
The ERS includes the following main features:
N
O
D Information Overlay on top of video picture:
PY
– Street Level maps
O
– Tactical information
–
C
– Other sensor inputs
LY
D Performance:
O N
– Terrain information taken into account
O N
– Level of detail depending on zoom–level and distance
TI
– Fast and seamless depiction of overlays
U
C
– Damping of overlay in case of jiggling camera picture
ST
R
D Camera Interface:
IN
– Several common analog and digital interfaces are supported
FO
R
D Interoperability with EuroNav7 Situational Awareness & Mission Management System: – Access to various aircraft data via EuroNav 7 Digital Map Generator RN7 / RN7CM – Full interoperability and synchronization of data – Same databases in both systems ensure same data status – Same level of information for all crew members (support of cockpit and mission console D Integrated Video Switching Unit: – Independent output video configurations for each output picture-in-picture and picture-by-picture (split–screen) configuration
display,
with
– Switching and scaling of video signals – External control via control devices
9.2-50 – 4
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7.2
MAIN COMPONENTS AND INTERFACES The ERS installation including other linked units comprises the following components: – WLAN antenna for the ERS – ERS unit – ERS control unit – Basic Platform Computer (Extension box) – WLAN antenna for the BPC – DME and TCAS
LL O
ERS CONTROL PANEL
VS1
SRC
CLR
C
ESC
MRK
N PY
REC
VS2
–
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– MFD – Transponder
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ERS control panel – typical installation
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Fig. 1
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Functionalities of control panel buttons and keyboard function keys may depend on the ERS configuration. In the table below, a typical configuration is described.
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Control panel
Changes the Map Mode (short press MAP): – MODE 1 – Split screen – MODE 2 – Picture-in-Picture – MODE 3 – Standard ERS screen Open Tab Configurations (long press MAP)
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ESC
The ESC button is used to quit a menu, cancel input, reset screen orientation and zoom level, exit video replay.
VS1 / VS2
Changes the VPSU screen mode (VSU profile presets). For example, as a pilot, press VS1 to view the different sources (e.g., ERS, MAP (EuroNav), Multipurpose Airborne Computer, etc.). As the operator, press VS2 to go through the different sources.
SRC
Opens Main Menu (long press SRC) Opens Address Search (short press SRC)
CLR
Delete all characters in a text box (short press CLR) Make a page or give elements to a page (long press CLR)
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Set marker on map. On the main page, make sure to select the check box to the right of the main page button MARK. If not, you cannot set markers with the MRK button.
REC
Start or stop recording video.
EXAMPLE OF THE ERS HMI
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Fig. 1
Example of the ERS HMI in page configuration ’Main’
Description 1
Target Information Box: The info boxes show the target position coordinates (Tar Pos), the elevation at the target point (focal point of the camera) and distance to the target (Tar Ele, Rng).
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Target Information Box: Object Information Box This info box shows more information about a target point such as a street name (Tar Addr). If the target point is a street, the object info box shows the distance to the next known address point in the database in meter (Dist to Addr).
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Marker Symbol
9.2-50 – 6
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Description Marker Information Boxes: The info boxes show the marker ID (Mrk ID), the marker heading and range (Mrk Hdg, Rng) and the marker position coordinate (Mrk Pos).
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Map details in Picture–in–Picture Mode: Use the + and – buttons to zoom in or out. Use the circle button to go back to zoom level 0. Use the rhomb symbol (#) to toggle through the available raster maps in 2D mode.
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Video Recording Information Box
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ERS: Changes the ERS overlay modes. The following modes are available: – Show all streets, labels, markers and POIs, – Show labels, markers and POIs only, – Show street only, – Hide all overlays.
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ADDR: Starts an address search.
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Marker Buttons: Selects or cancels functions and settings that are related to markers.
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LRF: Opens the LRF Marker menu. Use this dialog to set a Laser Range Finder (LRF) marker as direct–to or to steer the camera to. Refer to section [0.23] for details.
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POINT: Opens the New Point dialogue. Use this dialogue to enter a coordinate manually.
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VSU: Opens the VSU dialogue to access the pre-defined customized screen modes. Refer to section [0.25.3] for details.
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Camera: Shows the current camera tilt angle. The angle is relative to the aircraft. At the bottom of the HMI between point callout 13 and 14, a bar shows the camera zoom level. The zoom level is shown by a white arrow: Left side for low zooming level, right side indicates a high zooming level. Refer to section [0.34] for details.
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Aircraft Camera Diagram: The symbol consists of three elements: – Camera panning angle (white line), – Geographical north (green colored arrow), – Marker position (magenta colored dot). This symbol is related to the marker information given in the marker information boxes.
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Terrain: Shows or hides the terrain map.
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Description Take Snapshot: Makes a screenshot of the camera picture.
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MAP: Changes the screen mode: – Split–screen, – Picture–in–Picture, – ERS Full–screen.
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9.2-50 – 8
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SECTION 10 OPERATIONAL TIPS TABLE OF CONTENTS
GUIDELINES FOR LOW NOISE OPERATIONS . . . . . . . . . . . . . . . . . . . . . . 10 – 1
10.1.1
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10– 1
10.1.2
Operating in sensitive areas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10– 1
10.1.3
Take–off and landing from/to a helipad in a non sensitive area but adjacent to neighbouring sensitive areas (seaside areas for example) . . . . . . . . . . . 10– 1
10.1.4
Maneuver near the ground (hovering) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10– 2
10.1.5
Atmospheric wind effect . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10– 2
10.2
GUIDELINES FOR THE USE OF OEI RATINGS . . . . . . . . . . . . . . . . . . . . . 10 – 2
10.2.1
OEI rating structure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10– 2
10.2.2
Exceedance of the certified ratings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10– 2
10.2.3
Determining the limiting factor (gearbox or engine) . . . . . . . . . . . . . . . . . . . . 10– 3
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10.1
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Limiting parameter at the OEI 30 sec limit Pressure altitude – OAT diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 – 4
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Fig. 10-1
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LIST OF FIGURES
MANUFACTURER’S DATA Rev. 9
10 – i/(10 – ii blank)
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FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected]
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATIONAL TIPS
S E C T I O N 10 OPERATIONAL TIPS
10.1
GUIDELINES FOR LOW NOISE OPERATIONS
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The following guidelines are used to operate the BK 117 D-2 in noise sensitive areas. These guidelines are recommendations only. The flight procedures remain under the pilot’s responsibility, according to flight manual limitations and local regulation restrictions. The BK117 D–2 with six or more passenger seats is compliant with the noise limits according FAA Grand Canyon National Park Quiet Aircraft Technology Designation (QATD) per Appendix A of Subpart U to 14 CFR 93.
10.1.1
General
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Adopt a flight path as far as possible from sensitive areas.
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Maintain as much as possible a steady flight avoiding large pedal movements or overcontrol.
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For flights over sensitive areas prefer a flight path along the noisiest route (motorway, railway, etc.).
Take-off and climb
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Operating in sensitive areas
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10.1.2
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Leave the sensitive area as much as possible on the left hand side of the helicopter.
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Overflights
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After the shortest possible acceleration segment, once VY is reached, climb at Take-off Power (TOP) maintaining VY to reach the best rate of climb.
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When crossing noise-sensitive areas maximum VIAS= 110 kts or VNE whichever is less.
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If possible increase the height AGL to lower the noise effect.
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Where possible fly at least 1000 ft AGL. Approach and landing on helipad
Use VY with a rate of descent approx. 1100 ft/min. Maintain VY as long as possible. Final approach according to FLM Section 4. 10.1.3
Take–off and landing from/to a helipad in a non sensitive area but adjacent to neighbouring sensitive areas (seaside areas for example) If possible select a take-off flight path opposite to the sensitive area. Accelerate until VY is reached, then start to climb at VY with TOP in order to achieve the best rate of climb. If possible for landing adopt a flight path facing the sensitive area. Use VY with a rate of descent close to 500 ft/min. Final approach according to FLM Section 4.
MANUFACTURER’S DATA Rev. 0
10 – 1
FOR INSTRUCTION ONLY - The disclosure is prohibited. Owner: [email protected] FLIGHT MANUAL BK 117 D-2 (HELIONIX STEP 2) OPERATIONAL TIPS
10.1.4
Maneuver near the ground (hovering) Avoid unnecessary hovering. Avoid quick and repetitive pedal movements Prefer left turns.
10.1.5
Atmospheric wind effect Adopt a flight path leading to the lee side of the sensitive area. GUIDELINES FOR THE USE OF OEI RATINGS
10.2.1
OEI rating structure
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The OEI rating structure for the BK117 D–2 aircraft was certified with three OEI ratings, as follows: – 30sec power. Limited to 30seconds per use.
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– Max continuous power. Unlimited in case of OEI.
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– 2min power. Limited to 2minutes per use. This can be extended up to 2:30 if the OEI 30sec power was not used.
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When an engine failure occurs, the maximum power available will be automatically limited by the engine FADEC to the maximum available power at the 30sec rating (see Section 2). If the pilot pushes the OEI topping switch on the collective lever, the automatic protection is reduced from the 30sec power limit to the 2min power limit. Pushing the topping switch again or lowering the collective below the max continuous power limit will immediately return the automatic protection to the 30sec power limit.
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Exceedance of the certified ratings
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OEI ratings are intended to be used in the case of a real engine failure or an emergency procedure ultimately resulting in an engine shut down (e.g. FADEC FAIL). For pilot training, use of the OEI training mode is recommended.
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All engine emergency procedures in the flight manual (especially Category A operations and hoist or cargo hook operations with HEC) were defined such that the procedures will normally be completed within the maximum time allowed for each OEI rating.
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In specific operational circumstances (e.g. unforeseen circumstances when operating in Category A or when operating with human external cargo), extended or multiple use of the OEI 30sec power may be required to safely cope with the emergency. For such unforeseen emergencies, the following information should be considered: – When operating at the gearbox limits: The main gearbox was designed to allow several full applications of the maximum OEI 30sec power without incurring any significant damage. When the OEI 30sec power is used for more than 30 seconds at a time, some gearbox damage may occur. However, even when used up to 5 minutes at one time this immediate damage will allow for a safe return to the nearest suitable landing area. Any exceedance of the 30sec limit will be indicated by the UMS system on the flight report page and requires aircraft maintenance thereafter (refer to the aircraft maintenance manual).
10 – 2
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Determining the limiting factor (gearbox or engine)
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– When operating at the engine limits: The engine was designed to sustain at least 3 full applications of the maximum 30sec and 2min power within a single flight (i.e. a total of 90 seconds at the 30sec power limit plus 6 minutes at the 2min power limit). Typically one application was intended to be used for the initial engine failure, one for the go-around, and one for the final landing. Uninterrupted operation at the OEI 30sec limit for more than 30 seconds at a time shall be avoided as it may lead to immediate severe engine damage. If circumstances are such that the full OEI potential of the engine was used during the initial emergency, the pilot should plan to avoid further use of the OEI 30sec or 2min ratings by selecting a landing area where a run-on landing with limited power is possible. Any use or exceedance of the 30sec limit will be indicated on the master list and by the UMS system on the flight report page and requires maintenance (refer to the engine maintenance manual).
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When power is automatically protected by the FADEC at 30sec or 2min power, all engine (TOT and N1) and gearbox (torque) limitations are considered simultaneously. Which OEI limit is being used is immediately visible on the VMS page:
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– If the digital torque values are shown in red, the gearbox 30sec power rating is being used.
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– If the digital TOT or N1 values are shown in red, the engine 30sec power rating is being used.
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– If the digital torque values are shown in red and the TOT or N1 values are shown in amber, the gearbox 30sec rating and the engine 2min power rating is being used.
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If needed for flight preparation, Fig. 10-1 shows which 30sec ratings will be used in case of OEI, depending on the altitude and temperature. This chart is based on a minimum spec engine (i.e. an engine with zero margin on the power check). If the engine is better than minimum spec, the chart will provide conservative results (i.e. the gearbox limited area will be larger).
EXAMPLES: An off-shore hoist (HEC) operation is planned at 300 ft MSL at 25_C with zero wind: – Maximum aircraft weight for Clear Area Hoist Operations is 3295 kg (see FMS 9.2–4). – The aircraft will be gearbox limited. A Cat A VTOL operation is planned at 7500 ft and +5_C with zero wind: – Maximum aircraft weight for Clear Area Hoist Operations is 3310 kg (see FMS 9.1–1). – The aircraft will be engine limited.
MANUFACTURER’S DATA Rev. 9
10 – 3
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20000 19000 18000 17000 16000 15000 14000
Engine limited
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9000 8000
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Pressure altitude (ft)
13000
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Gearbox limited
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–1000 –50 –40 –30 –20 –10
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Limiting parameter at the OEI 30 sec limit – Pressure altitude – OAT diagram
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Fig. 10-1
0 10 OAT – °C
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BKD2_FLH_0392_R
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MANUFACTURER’S DATA Rev. 9
