FCTM Sistemas ATR-600 PDF [PDF]

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PRODUCT SUPPORT & SERVICES



SYSTEMS SCAN YOUR AIRCRAFT



42 PEC 72 PEC Glass cockpit - 600



Introduction



Introduction This Systems guide is an essential tool for all ATR flight crews and engineers to learn or review ATR systems operation. To make learning process easier, systems are introduced in a user-friendly and efficient training method, including diagrams and schematics and displays as appropriate. This guide is a comprehensive document that efficiently complements FCOM 1st part – Systems description. Systems are organized as per FCOM chapters, including their ATA classification along with cockpit location. Cockpit panels familiarisation is presented with each relevant system description in a separate annex. This new guide release is intended for training on ATR 42-500 and 72-212A New Avionics Suite (42-600 and 72-600). It presents a generic aircraft not customized to your own aircraft systems. Should you find any discrepancy between Systems guide and your customized ATR operational documentation (AFM, FCOM & QRH), the latter takes precedence. NB: This Systems guide is also available for ATR 42-300, 72-200 not PEC, 42-500 and 72-212A.



The Training and Flight Operations support team.



S y s t e m s 4 2/72 - 6 0 0 Chapter A. Aircraft general 1. Doors location .....................................................................................................................................................................................................................................................8 2. Cargo door panel ...........................................................................................................................................................................................................................................9 3. Doors panel ...........................................................................................................................................................................................................................................................9 4. External lights ................................................................................................................................................................................................................................................10 5. EXT LT panel .....................................................................................................................................................................................................................................................11 6. Memo panel display .................................................................................................................................................................................................................................11 7. Signs panel .........................................................................................................................................................................................................................................................11 8. Internal lighting ............................................................................................................................................................................................................................................12 9. LT panel ...................................................................................................................................................................................................................................................................13 10. ANN LT panel ...............................................................................................................................................................................................................................................13 11. Side panel .........................................................................................................................................................................................................................................................13 12. FLT COMPT LT panel .........................................................................................................................................................................................................................13



Chapter B. Integrated systems 1. Integrated Modular Avionics (IMA)......................................................................................................................................................................................16 2. Multi Function Computer (MFC)..............................................................................................................................................................................................17 3. Multi Purpose Computer (MPC) ..............................................................................................................................................................................................18 4. Schematic..............................................................................................................................................................................................................................................................19



Chapter C. Flight warning system 1. Cockpit colors philosophy ............................................................................................................................................................................................................22 2. FWS description ..........................................................................................................................................................................................................................................24 3. Alert window ....................................................................................................................................................................................................................................................25 4. EMER audio cancel & TO config test .............................................................................................................................................................................28 5. Aural alarms ......................................................................................................................................................................................................................................................29



Chapter D. Air 1. Pneumatic system......................................................................................................................................................................................................................................32 1.1. Schematic .................................................................................................................................................................................................................................................32 1.2. AIR BLEED panel.............................................................................................................................................................................................................................33 2. Air conditionning ........................................................................................................................................................................................................................................39 2.1. Schematic .................................................................................................................................................................................................................................................39 2.2. COMPT TEMP panel ...................................................................................................................................................................................................................40 3. Avionics ventilation .................................................................................................................................................................................................................................44 3.1. Schematic .................................................................................................................................................................................................................................................44 3.2. AVIONICS VENT panel .............................................................................................................................................................................................................44 4. Pressurization ................................................................................................................................................................................................................................................45 4.1. Schematic .................................................................................................................................................................................................................................................45 4.2. Cabin pressure indicators ..................................................................................................................................................................................................46 4.3. AUTO PRESS panel .....................................................................................................................................................................................................................46 4.4. MAN RATE KNOB and CABIN PRESS panel..............................................................................................................................................46



Chapter E. Automatic flight control system 1. Schematic ............................................................................................................................................................................................................................................................50 2. FMA ..............................................................................................................................................................................................................................................................................51 3. FGCP (Flight Guidance and Control Panel) ............................................................................................................................................................56 4. ICP (Index Control Panel) .................................................................................................................................................................................................................56



Chapter F. Communications 1. Schematic............................................................................................................................................................................................................................................................. 58 2. PTT selector and NOSE WHEEL STEERING CONTROL SW.............................................................................................................58 3. Audio control panel ..................................................................................................................................................................................................................................59 4. VHF control ..........................................................................................................................................................................................................................................................59 5. AUDIO SEL pb..................................................................................................................................................................................................................................................60 6. Loudspeaker volume knobs .........................................................................................................................................................................................................60



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Contents 7. TCAS control box ........................................................................................................................................................................................................................................60 8. EMER LOC XMTR panel .....................................................................................................................................................................................................................61 9. Cabin attendant handset...................................................................................................................................................................................................................61 10. Handmike and handset....................................................................................................................................................................................................................61 11. CALLS panel ...................................................................................................................................................................................................................................................61 12. Head set / boom set / hand mike panels ...................................................................................................................................................................61 13. ATC control.......................................................................................................................................................................................................................................................62 14. CVR panel...........................................................................................................................................................................................................................................................62 15. Crew oxygen mask ................................................................................................................................................................................................................................62



Chapter G. Electrical systems 1. Sources of power ........................................................................................................................................................................................................................................64 2. DC-AC schematic .......................................................................................................................................................................................................................................66 2.1. Normal supply: On ground with battery only ............................................................................................................................................66 2.2. Normal Supply: On ground with external power .........................................................................................................................................67 2.3. Hotel mode or DC GEN 1 FAULT ................................................................................................................................................................................68 2.4. Normal supply: with two generators on line..............................................................................................................................................69 2.5. Emergency supply: In dual DC GEN LOSS with the battery toggle switch on OVRD .......................70 2.6. Emergency supply: In dual DC GEN LOSS with the battery toggle switch on OVRD and second OVRD selected ..........................................................................................................................................................................................................71 2.7. Emergency supply: In dual DC GEN LOSS with TRU ....................................................................................................................72 3. DC-AC panel ......................................................................................................................................................................................................................................................73 4. Elec SD ......................................................................................................................................................................................................................................................................74 5. ACW schematic .............................................................................................................................................................................................................................................78 6. ACW panel ............................................................................................................................................................................................................................................................80 7. SD page ....................................................................................................................................................................................................................................................................81 8. Breaker panels ................................................................................................................................................................................................................................................82 8.1. Overhead panel .................................................................................................................................................................................................................................82 8.2. Electric rack behind F/O .......................................................................................................................................................................................................83



Chapter H. Emergency equipment 1. Emergency equipment situation.............................................................................................................................................................................................86 2. Emergency lighting system ...........................................................................................................................................................................................................86 3. First aid kit ............................................................................................................................................................................................................................................................87 4. Crash axe ...............................................................................................................................................................................................................................................................87 5. Megaphone ..........................................................................................................................................................................................................................................................87 6. Flashing light .....................................................................................................................................................................................................................................................87 7. Life jacket ..............................................................................................................................................................................................................................................................87 8. Escape rope ........................................................................................................................................................................................................................................................87 9. Gloves .........................................................................................................................................................................................................................................................................88 10. Water extinguisher .................................................................................................................................................................................................................................88 11. Halon extinguisher .................................................................................................................................................................................................................................88 12. Oxygen schematic..................................................................................................................................................................................................................................88 13. Oxygen panel and display ............................................................................................................................................................................................................89 14. Cockpit crew oxygen mask .......................................................................................................................................................................................................89 15. Portable oxygen bottle......................................................................................................................................................................................................................90 16. Passenger oxygen mask ................................................................................................................................................................................................................90 17. Protective breathing equipment ..........................................................................................................................................................................................90



Chapter I. Fire protection 1. Schematic..............................................................................................................................................................................................................................................................92 2. Avionics FWD and AFT smoke detection ...................................................................................................................................................................92 3. Fire handle ............................................................................................................................................................................................................................................................93 4. EWD (Engine and Warning Display)....................................................................................................................................................................................93 5. Condition levers fuel light ................................................................................................................................................................................................................93 6. Compartment smoke panel...........................................................................................................................................................................................................94 7. SD cabin...................................................................................................................................................................................................................................................................94 3



S y s t e m s 4 2/72 - 6 0 0 Chapter J. Flight control 1. Roll schematic.................................................................................................................................................................................................................................................96 2. Pitch schematic .............................................................................................................................................................................................................................................96 3. Yaw schematic ................................................................................................................................................................................................................................................97 4. Gust lock .................................................................................................................................................................................................................................................................97 5. Stick Shaker/Stick Pusher push button and display ..................................................................................................................................97 6. Spoilers position indicator..............................................................................................................................................................................................................98 7. Pitch trim asym light ...............................................................................................................................................................................................................................98 8. Trim position indicator .........................................................................................................................................................................................................................98 9. Trim controls ......................................................................................................................................................................................................................................................99 10. Flaps schematic .................................................................................................................................................................................................................................... 100 11. Flaps position indicator............................................................................................................................................................................................................... 100 12. Flaps control lever .............................................................................................................................................................................................................................. 101



Chapter K. Flight instruments 1. Schematic.......................................................................................................................................................................................................................................................... 104 2. PFD (Primary Fight Display) ...................................................................................................................................................................................................... 105 3. MFD (Multi Function Display) .................................................................................................................................................................................................. 106 4. EWD (Engine and Warning Display)................................................................................................................................................................................ 107 5. ND - ARC MODE with terrain or weather radar information ...................................................................................................... 108 6. Source failure alert ................................................................................................................................................................................................................................ 108 7. Switching panel ......................................................................................................................................................................................................................................... 109 8. EFCP (control panel) ........................................................................................................................................................................................................................... 109 9. MCP (Multipurpose Control Panel) ................................................................................................................................................................................. 110 10. Weather radar control ................................................................................................................................................................................................................... 111 Primus 660 ........................................................................................................................................................................................................................................................ 111 11. TAT/SAT indicator ............................................................................................................................................................................................................................... 112 12. CLOCK................................................................................................................................................................................................................................................................ 112 13. RCDR panel ................................................................................................................................................................................................................................................. 113 14. STBY instruments ............................................................................................................................................................................................................................... 113 15. Airspeed indicator .............................................................................................................................................................................................................................. 114 16. Altimeter........................................................................................................................................................................................................................................................... 115 17. Vertical speed indicator and TCAS .............................................................................................................................................................................. 116



Chapter L. Fuel system 1. Schematic.......................................................................................................................................................................................................................................................... 118 2. Electrical fuel pump OFF............................................................................................................................................................................................................... 119 3. Starting procedure................................................................................................................................................................................................................................. 120 4. Normal procedure................................................................................................................................................................................................................................... 121 5. Cross feed procedure........................................................................................................................................................................................................................ 122 6. Engine feed jet pump low pressure................................................................................................................................................................................ 124 7. Low level ............................................................................................................................................................................................................................................................. 125 8. Engine fire procedure ........................................................................................................................................................................................................................ 126 9. Fuel panel........................................................................................................................................................................................................................................................... 127 10. SD Engine ....................................................................................................................................................................................................................................................... 127 11. Fuel QTY indication ........................................................................................................................................................................................................................... 128 12. XFEED advisory on memo panel display ............................................................................................................................................................. 128



Chapter M. Hydraulic system 1. Schematic.......................................................................................................................................................................................................................................................... 130 3. SD ACW and hydraulic ..................................................................................................................................................................................................................... 131 2. HYD PWR panel ......................................................................................................................................................................................................................................... 131 4. Pressure indication ............................................................................................................................................................................................................................... 132 5. AUX pump pedestal switch ....................................................................................................................................................................................................... 132 6. Hydraulic on Ramp (only on battery) ............................................................................................................................................................................ 133 7. Hydraulic on Ramp (aux pump P/B selected on the pedestal) ................................................................................................. 133 8. Hydraulic system normal operation............................................................................................................................................................................... 134



4



Contents 9. Hydraulic system failures ............................................................................................................................................................................................................. 135 10. Hydraulic system crossfeed operation .................................................................................................................................................................. 135 11. Both main hydraulic pumps loss .................................................................................................................................................................................... 136 12. Both hydraulic systems loss ................................................................................................................................................................................................ 137



N. Ice and rain protection 1. Schematic.......................................................................................................................................................................................................................................................... 140 2. Probes and windshield HTG ..................................................................................................................................................................................................... 141 3. Rain protection ........................................................................................................................................................................................................................................... 141 4. Ice detector panel and icing AOA ..................................................................................................................................................................................... 141 5. Aircraft Performance Monitoring (APM) .................................................................................................................................................................. 142 6. De-icing schematic............................................................................................................................................................................................................................... 143 7. Airframe air bleed FAULT .............................................................................................................................................................................................................. 144 8. Anti-icing & de-icing panel ......................................................................................................................................................................................................... 145 9. De-icing/anti-icing indication (memo panel display) .............................................................................................................................. 145



O. Landing gear 1. Landing gear description ............................................................................................................................................................................................................. 148 2. Brakes schematic ................................................................................................................................................................................................................................... 148 3. LDG GEAR position indicators .............................................................................................................................................................................................. 149 4. Landing gear handles ........................................................................................................................................................................................................................ 149 5. Brakes temperatureand antiskid ....................................................................................................................................................................................... 149 6. Emergency parking brake handle..................................................................................................................................................................................... 150 7. Steering handwheel ............................................................................................................................................................................................................................. 150



P. Navigation system 1. Nav control ....................................................................................................................................................................................................................................................... 152 2. Marker sensibility setting ............................................................................................................................................................................................................. 152 3. ADF control ...................................................................................................................................................................................................................................................... 152 4. TAWS alert modes .................................................................................................................................................................................................................................. 153 5. TAWS pb............................................................................................................................................................................................................................................................... 157 6. TAWS panel...................................................................................................................................................................................................................................................... 157 7. ND OVERLAY ................................................................................................................................................................................................................................................. 158 8. FMS ............................................................................................................................................................................................................................................................................ 159



Q. Power plant 1. Engine schematic/72 .......................................................................................................................................................................................................................... 162 2. Power and propeller controls/72 ....................................................................................................................................................................................... 163 3. Engine indication ..................................................................................................................................................................................................................................... 166 4. ENG START panel/72 .......................................................................................................................................................................................................................... 168 5. ENG control panel/72......................................................................................................................................................................................................................... 168 6. PWR MGT panel/72............................................................................................................................................................................................................................... 169 7. ATPCS test panel/72 ........................................................................................................................................................................................................................... 169 8. Idle gate/72 ...................................................................................................................................................................................................................................................... 169



Annexes Annex 1. Cockpit panels ....................................................................................................................................................................................................................... 173 Annex 2. Abbreviations ........................................................................................................................................................................................................................... 187



5



A. Aircraft general FCOM 1.00



7



S y s t e m s 4 2/72 - 6 0 0



1. Doors location



Cargo door



Pilot communication hatch



8



Emergency exit type III



Rear entry door / emergency exit type I



ATA 52



Service door / emergency exit type I



Pilot emergency hatch



Aft avionics compartment door



Forward avionics access hatch



A. Aircraft general



2. Cargo door panel



ATA 52



ARMED light – Selector armed green light is ON, when actuator selection switch working conditions are met: – cover panel opened – door unlocked by operating handle: all hooks are disengaged and FWD latchlock is unfastened



LCHD light blue light is ON when all door hooks and latch locks are fully engaged



GND HDL light Ground handling bus ON BAT red light is ON when ground handling bus is directly supplied by HOT main bat bus: means that the battery is discharging even if the BAT toggle switch is in OFF position (visible even when the cover panel is closed) This red light is ON when: – The refueling panel is open – The cargo door control panel is open – The passenger door is open and alert, that the battery is discharging before leaving the aircraft



Actuator selection switch is used to operate the door (OPEN or CLOSE) when the CARGO DOOR ARMED green light is on



Panel cover switch connects the ground handling bus on line when the panel cover is opened and allows operation of cargo door. During the opening, a self test of the MFC 1A and 2A is performed to initiate the control system of the cargo door.



CARGO LIGHT switch allows activation of the cargo bay light from outside



3. Doors panel



ATA 52



CAB OK and SVCE OK Light on when SW TEST depressed and check microswitches operation



UNLK At least 1 micro switch is opened SW TEST Tests continuity of microswitch system (on ground, doors opened)



9



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4. External lights



ATA 33



ABCDE F GH-



Navigation lights Taxi and T/O lights Landing lights Wing lights Beacon lights Strobe lights Logo lights Emergency light



Cabin panel



Memo panel display



10



A. Aircraft general



5. EXT LT panel



ATA 33



BEACON and NAV supplied by SVCE BUS and BUS 1 LOGO supplied by SVCE BUS



STROBE, LAND supplied by ACW BUS 1 (Left Hand), ACW BUS 2 (Right Hand) TAXI & T.O Supplied by ACW BUS 2 WING Supplied by DC BUS 2



6. Memo panel display



ATA 33



SEAT BELT displayed in cyan when associated switch is selected ON



NO DEVICE displayed in cyan when associated switch is selected ON



SEAT BELT displayed in amber crossed when the signal is invalid.



NO DEVICE displayed in amber crossed when the signal is invalid.



7. Signs panel



ATA 33 ON emergency exit lights illuminates. Supply: DC STBY or 6 V BAT packs



NO DEVICE and SEAT BELTS Cyan message on memo panel display when ON. (DC BUS 2)



ARM Emergency lights illuminate when 20V on STBY bus and at least 1 GEN operating



DISARM system deactivated



11



S y s t e m s 4 2/72 - 6 0 0



8. Internal lighting



ATA 33



0,33('



29+'



The STORM switch overrides the MIP/PED rotary selector to put in the maximum intensity setting



12



A. Aircraft general



9. LT panel



ATA 33



MIP / PED Selects activation and intensity of integral lighting of the main instrument panels (MIP) and pedestal (PED)



0,33('



29+'



OVHD rotary selector selects activation and intensity of overhead panels integral lighting



10. ANN LT panel



FLOOD knob selects activation and intensity panel flood lighting. (OFF TO BRT)



ATA 33 To check and control the intensity of: – the annunciator lights on the overhead and pedestal panels – the overhead panel flow bars TEST: All the associated lights come on bright BRT: associated light illuminate bright DIM: associated light are dimmed



11. Side panel



ATA 33 CAPT READING LT knob selects activation and intensity of the respective spot light



CAPT CONSOLE LT knob selects activation and intensity of the respective lateral console



12. FLT COMPT LT panel DOME switch BRT: dome lights are supplied with maximum intensity DIM: dome lights are dimmed OFF: both dome are off DOME light: the F/O dome light becomes BRT when the switch in BRT or DIM if: – dual DC GEN loss – or on ground, with BAT supply only



ATA 33



STORM switch On position, it overrides the MIP/ PED rotary selector to put in the maximum intensity setting



STBY COMPASS switch to illuminate the STBY COMPASS ON and OFF position



13



B. Integrated systems FCOM 1.01



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1. Integrated Modular Avionics (IMA)



ATA 42



The Integrated Modular Avionic (IMA) provides computation, memory and Input/Output data processing resources, shared between several avionics applications. The Integrated Modular Avionic is mainly composed of the dual Core Avionic Cabinets (CAC 1&2). The term CAC (Core Avionic Cabinet) designs the whole equipment composed of the rack and the set of cards. In the basic configuration, each CAC is composed of: – 1 CPM (Core Processing Module) The CPMs provide shared memory and computation resources to execute hosted avionics applications. – 1 IOM-S (Input/Output Module) This IO Module is dedicated to provide ARINC and discrete I/O for all functions – 1 IOM-AP (Input/Output Module) This IO Module is dedicated to provide discrete and analog I/O for the Auto-Flight application. – 2 IOM-DC (Input/Output Module) The IOM-DC provide discrete and analog I/O for Data Concentration Application (DCA) . – 1 SWM (gateway and SWitch Module) This module is dedicated to connect together CPM and other Avionics Data Network subscribers. The communication means is based on AFDX network, linking network subscribers through SWM. The main applications hosted by the Core Avionic Cabinets are : – Flight Warning (FWA) – Auto-Flight (AFCA) – Centralized Maintenance (CMA) (only on CAC 1) – Data Concentration (DCA) The CAC 1 & 2, communicate with five display units and systems through different data bus formats: – AFDX: Avionics Full DupleX switched ethernet – A429: ARINC 429 – Analogic – Discretes Two of the five displays units (DU2 and DU4) are dedicated to two other functions: – Flight Management Application (FMA) – Radio Management Application (RMA)



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6 OVERHEAT – If not ––> UNDERPRESSURE



In case of overheat, the ENG P/B is deselected, the AFR AIR BLEED is selected again to isolate the affected engine.



144



N. Ice and rain protection



8. Anti-icing & de-icing panel PROP ACW supply. Inhibited below NP 63%



HORNS ACW supply. Inhibited on ground. Either horn activates AOA Lt



FAULT power loss on at least 1 blade. A-ICING PROP 1 (2) on FWS



DE ICING air is always available regardless of bleed pb. NORM: 60’’ / cycle SLOW: 240’’ / cycle



MODE SEL AUTO Automatic selection of cycle depending on ADC1/2 to MFC1B/2B FAULT when ADC or MFC fail: Fast mode is automatically selected for ENG and AIRFRAME DEICING and High Power for PROP ANTI-ICE. A-ICING AUTO on FWS. MAN: manual selection of cycles depending on SAT



FAULT both MFC modules have failed to control boots cycles. The monitoring is preformed by the stby controller. A-ICING SEL on FWS AFR AIR BLEED OVRD: no MFC. Boots inflated by separate stantby controller (cycle 60’’)



ENG FAULT: distribution valve opened but no air pressure. OR valve closed and pressure detected OR AFR AIR BLEED off and air temp above deice valve >230°C for more than 6’’. A-ICING ENG 1 ( 2) on FWS



MODE SEL ENG AND AIRFRAME SLOW: 240’’/cycle FAST: 60’’/cycle



HORNS FAULT Power loss. A-ICING HORNS 1 (2) on FWS



SIDE WINDOWS Defog only. FAULT for power loss. A-ICING WINDOWS on FWS. (DC BUS)



MODE SEL PROP NORM: 10’’ on per 3 blades; then 10’’ off between cycles. ON (HIGH POWER): 20’’ on per 3 blades. No stop between cycles.



ENG ON: signal sent to MFC to start deice cycle on the engine air intake, deice valve opened even if AFR AIR BLEED off



ATA 30



AIR FRAME FAULT: valve opened but no downstream pressure. Or valve closed and downstream pressure detected. A-ICING FRAME on FWS



AIR FRAME ON: signal sent to MFC to start deice cycle on the airframe AFR AIR BLEED FAULT: air dowstream deice valve < 14 psi more than 10’’ OR Air upstream of the deice valve > 230°C. A-ICING BLEED on FWS



9. De-icing/anti-icing indication (memo panel display)



OFF : isol valves closed. Deice valves closed unless ENG 1 / 2 deice on.



ATA 30



CYAN When selected ON AMBER When FAULT



145



O. Landing gear FCOM 1.14



147



S y s t e m s 4 2/72 - 6 0 0



1. Landing gear description



ATA 32



The landing gear is hydraulically operated. In case of hydraulic failure, it may be extended by gravity.



LANDING GEAR CONTROL



STEERING HANDWHEEL



2. Brakes schematic



EMERGENCY / PARKING BRAKE HANDLE



148



ATA 32



PILOT BRAKE PEDALS



O. Landing gear



3. LDG GEAR position indicators



ATA 32



System 2 UNLK gear not locked in selected position or (on GND) uplock box not opened. Green Lt down lock engaged



System 1 UNLK gear not locked in selected position or (on GND) uplock box not opened. Green Lt down lock engaged.



4. Landing gear handles LDG GEAR EMERGENCY EXTENSION HANDLE permits to unlock the landing gear



5. Brakes temperature and antiskid BRK TEMP WHEELS BRK HOT on FWS for any brake T° >160°C (42) T° >150°C (72)



OFF Pb released, system deactivated



ATA 32 GEAR HANDLE RED LIGHT any gear not sensed down and locked with some conditions. FWS.



ATA 32



ANTISKID Operative if speed > 10 kts. Activates when speed > 23 kts + 50% diff between wheels (locked wheel protection). Braking action inhibited at touchdown as long as wheel spin up speed < 35 kts or 5 sec. (touchdown protection). CAUTION: THE TEST INHIBITS BRAKES



TEST pb (inhibited if speed > 17 kts) = MC + SC+ FWS. Test duration: 3 sec. in flight and 6 sec. on ground



F (FAULT) wheel channel failure + WHEELS A-SKID on FWS



149



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6. Emergency parking brake handle EMERGENCY BRAKE HANDLE permits to apply a metered pressure. The brake accumulator allows at least six braking applications without any antiskid operation if the blue hydraulic system is not available (Springloaded to the off position)



7. Steering handwheel N/W STEERING SW activates or deactivates the nose wheel steering system (guarded type in the ON position) OFF: unpressurizes the steering system (91° of deflection)



150



ATA 32 PARKING BRAKE permits a full pressure on the brakes. When brake handle is not in the fully released position, amber PRKG BRK caution light is displayed on FWS and is taken into account by the T/O CONFIG. (Springloaded to the off position)



ATA 32 THE STEERING HAND WHEEL controls the nose wheel angle up to 60° in either direction: – clockwise: steering to the right – counter clockwise: steering to the left



P. Navigation system FCOM 1.15



151



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1. Nav control



ATA 34 VCP



MCDU



MCP



MCP and MCDU allow: – to tune VOR/ILS/DME frequencies – to set tune mode (AUTO/ MAN) – to do DME HOLD In AUTO tuning, the NAV source has to be on FMS (Inhibited on V/ILS)



2. Marker sensibility setting



ATA 34 MCDU



MCDU allows to set MKR sensibility (LO/HI position)



3. ADF control



ATA 34 VCP



MCDU



MCP



MCP and MCDU allow: – to tune ADF frequencies – to set mode (ADF/ANT) – to set tone (OFF/ON)



152



P. Navigation system



4. TAWS alert modes



ATA 34



The Terrain Awareness Warning System provides visual and aural alerts in case of dangerous flight path conditions which would result inadvertent ground contact if maintained. The TAWS performs the following alert modes: – Reactive warning modes * Mode 1: excessive descent rate * Mode 2: excessive terrain closure rate * Mode 3: altitude loss after take-off * Mode 4: unsafe terrain clearance * Mode 5: below glideslope * Mode 6: altitude callouts – Predictive warning modes: * Terrain Caution and Warning * Obstacle Caution and Warning



MODE 1 excessive descent rate



MODE 2 excessive terrain closure rate



153



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MODE 3 altitude loss after take-off



MODE 4 unsafe terrain clearance



MODE 5 below glideslope



154



P. Navigation system



MODE 6 altitude callouts



TERRAIN CLEARANCE FLOOR (TCF)



The Terrain Clearance Floor (TCF) mode creates an increasing terrain clearance envelope around the airport runway directly related to the distance from the runway.



Runway Field Clearance Floor (RFCF)



155



S y s t e m s 4 2/72 - 6 0 0



TERRAIN AND OBSTACLE AWARENESS



This function use the aircraft geographic position from the GPS, aircraft altitude and a worldwide terrain database to predict potential conflict between the aircraft flight path and the terrain, and to provide aural alert and graphic displays of the conflicting terrain.



The terrain advisory line is drawn along the points where a terrain caution alert will occur if the aircraft continues along its current trajectory.



“TERRAIN AHEAD” or “OBSTACLE AHEAD”



When a terrain caution or warning occurs, the terrain advisory line is removed from the display and the terrain display is changed to identify the terrain that caused the alert.



“TERRAIN AHEAD, PULL UP” Or “OBSTACLE AHEAD PULL UP”



The Pull-Up Warning is generated as long as the current aircraft trajectory will not safely clear the terrain, and the aircraft performances are able to clear the terrain in climb



156



P. Navigation system



“AVOID TERRAIN”



The Pull-Up maneuver will not allow for a safe clearance with terrain, and the crew has to immediately initiate an appropriate vertical and/or turning escape maneuver in order to avoid terrain



5. TAWS pb



ATA 34



6. TAWS panel



ATA 34 TAWS selector is guarded in the norm position. FLAP OVRD mode 4 alert caused by flap extension is inhibited to avoid nuisance in case of reduced flaps landing



157



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7. ND OVERLAY



The MCP allows to set ND OVLY – Traffic – Weather radar – Terrain – Navaid – Airport



158



ATA 31



P. Navigation system



8. FMS



ATA 34



The dual THALES Flight Management System (FMS) installed on ATR 72/42-600 aircraft is composed of two identical sets of software applications, called FMS1 and FMS2. Each FMS is hosted within the DU2 and DU4, normally used with the MFD format.This dual FMS is built on dual cockpit system architecture. It is used to be normally handled with both FMS, synchronized by the cross talk function.



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160



Q. Power plant FCOM 1.16



161



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1. Engine schematic



ATA 61/72



Aircraft fitted with – two Pratt &Whitney, PW 127 M (72-600/42-600) – two, six blades propellers (Hamilton) It is a free turbines engine, composed of 3 concentric shafts of spools: – The shaft of the HP spool composed of the HP turbine and the HP compressor (rotation speed of the HP spool: NH). The HP spool drives the accessory gear box (AGB) – The shaft of the LP spool composed of the LP turbine and the LP compressor (rotation speed of the LP spool: NL) – The Power shaft composed of 2 power turbines (Free turbines). This 2 power turbines drive the propeller through the reduction gear box (RGB) (rotation speed of the propeller NP)



REDUCTION GEAR BOX These equipments are fitted on the RGB – the ACW generator – the Propeller Valve Module (PVM) – the propeller pump (HP) and overspeed governor – the auxiliary feathering pump – the propeller brake (on RH engine only)



HIGH PRESSURE COMPRESSOR centrifugal type



LOW PRESSURE COMPRESSOR centrifugal type



HIGH PRESSURE TURBINE



POWER TURBINE



ACCESSORY GEAR BOX driven by the HP spool. Drives – the DC starter/generator – the HP fuel pump – the engine oil pumps



DIFFUSER PIPES



ANNULAR COMBUSTION CHAMBER



6 blades propeller



162



LOW PRESSURE TURBINE



Q. Power plant



2. Power and propeller controls



ATA 61/72



The different powers ratings for the engine are: (SHP: Shaft Horse Power) – RTO (Reserve Take Off) (maximum power) Used in case of an engine flame out during take off (up trim) or in case of go around (ramp) – MCT (Maximum continuous) – TO (Take Off 0,9 RTO) – Climb – Cruise



72-600 2750 SHP



42-600 2400 SHP



2500 SHP 2475 SHP 2192 SHP 2132 SHP



2400 SHP 2160 SHP 2160 SHP 2132 SHP



Power (PWR) = Torque (TQ) x NP For the same power: If TQ increases, NP decreases If TQ decreases, NP increases Power setting is characterized by constant power lever (PL) and condition lever (CL) positions. The power adapted to the flight phase is selected by the pilot through a power management selector (PWR MGT). – With input coming from the PWR MGT and the position of the PL, the EEC (Engine Electronic Control) control the fuel flow to the engine.



MAX PWR (Full stop): Maximum Power → TQ up to115% (On emergency only) GO around position (Beginning of the ramp): RTO → TQ up to100% NOTCH position: PWR MGT in – TO: – MCT – CLB – CRZ



→ NP 100% and 0,9 RTO → TQ up to 90% → NP 100% and TQ up to 90,9% (72-600) → NP 100% and TQ up to 100% (42-600) → NP 82% and TQ up to 97% (72-600) → NP 82% and TQ up to 109,7% (42-600) → NP 82% and TQ up to 94,5% (72-600) → NP 82% and TQ up to 108,3% (42-600)



Reversion in manual mode when EEC FAULT (green band 66%) FTR (Feather position). The fuel governing mode is cancelled (No ACW generator) Fuel Shut Off position: Close the shut off valve on the HMU



164



Q. Power plant – The PWR MGT has four positions: TO, MCT, CLB, CRZ – Considering that CLs are in AUTO and the PLs are in the notch, the control system delivers max rated power corresponding to the mode selected (the max rated power is delivered only when the engine is not thermodynamically limited)



ATR 72-600 NORMAL OPERATION, EEC ON, ISA CONDITIONS SHP



115% TQ



A



102% TQ 100% TQ



RTO (UP TRIM)



2750 2500 2475 2192 2132



MCT OR TO



B



TO 90% TQ



C



D



LINE A: One engine out operation LINE B: Normal TO or MCT LINE C: CLB LINE D: CRZ NOTE: Sensible sector designed to allow for fix throttle engine control.



100% Np 100% Np



MCT 90.9% TQ



RAMP



100% Np



WALL



NOTCH



0



50



67



81



100



POWER LEVER ANGLE



– TO – MCT – CLB – CRZ



PWR = 2475 SHP PWR = 2500 SHP PWR = 2192 SHP PWR = 2132 SHP



NP=100% NP=100% NP=82% NP=82%



TQ = 90% TQ = 90,9% TQ = 97% TQ = 94,5%



The RTO (Reserve Take-Off) is obtained in case of up trim (one engine out during take off) or with the PL to the ramp – RTO



PWR = 2750 SHP



ATR 42-600



NP=100%



TQ = 100%



NORMAL OPERATION, EEC ON, ISA CONDITIONS SHP



115% TQ



A 2400



MCT OR TO



2160



102% TQ 100% TQ



RTO (UP TRIM)



B



90% TQ



100% Np 100% Np



C



2132



LINE A: One engine out operation LINE B: Normal TO or MCT LINE C: CRZ NOTE: Sensible sector designed to allow for fix throttle engine control.



RAMP



WALL



NOTCH



0



– TO – MCT – CLB – CRZ



PWR = 2160 SHP PWR = 2400 SHP PWR = 2160 SHP PWR = 2132 SHP



50



NP=100% NP=100% NP=82% NP=82%



67



TQ = 90% TQ = 100% TQ = 109,7% TQ = 108,3%



81



100



POWER LEVER ANGLE



The RTO (Reserve Take-Off) is obtained in case of up trim (one engine out during take off) or with the PL to the ramp – RTO



PWR = 2400 SHP



NP=100%



TQ = 100%



165



S y s t e m s 4 2/72 - 6 0 0



3. Engine indication



ATA 31



Power Management selection Analogic indication



RTO Torque at TO Objective TQ in MCT CLB CRZ



hWdZ/D



ATPCS uptrim activation



GO Around Torque



ϵϭ͘ ϭ ϭϬϮ ͘ ϱ ϭϮϱ ͘ ϲ ͲͲͲ ͘ Ͳ ,s >  >KW/d, >KW/d, EK Zs



Normal Abnormal Over-limit Invalid numeric torque HBV failure Discrepancy between EEC and aircraft configuration



Lo Pitch Normal operation on ground Lo Pitch Abnormal operation in flight No Lo Pitch on ground with PL before FI



Lost of propeller control by one PEC channel



hdK&dZ



Auto Feather activation



Propeller brake is applied



Red line for “S”: limit during engine start



ͲͲͲ͘Ͳ



EW й



Red line for “H”: limit during Hotel Mode



ͲͲͲ͘Ͳ



NP information



ϵϬ ͘Ϭ ϭϭϬ ͘Ϭ ϭϮϮ ͘Ϭ ͲͲͲ ͘ Ͳ



166



Normal operation Abnormal operation Red limit NP invalid signal



ϱϬϬ



ϴϬϬ ͲͲͲ ͘ Ͳ



ϵϵϵ



ITT numeric counter ITT invalid signal



Q. Power plant



ϲϬ



Normal Ϭ



ϵϬ



ϭϵ͘ϱ



Normal transient range



ϴϭ͘Ϭ



Normal operating range



ϲϬ Ϭ



ϭϯϳ



Amber exceedance



ϲϬ Ϭ



Amber exceedance range



ϭϭϬ͘Ϭ



Red limit



ͲͲͲ͘Ͳ



Invalid data



ϲϬ



ʹϯϱ Ϭ



ϭϵϬ



ϭϬϰ͘Ϭ



ϲϬ



Red limit Ϭ



ϭϬϬ͘Ϭ ϭϬϱ ϭϲϰ ͘Ϭ ͲͲͲ ͘ Ͳ



ͲͲͲ͘Ͳ



Normal ϯϭ



ϲϯ



ϭϬϬ



Amber exceedance range Red limit Invalid data



E> й



ͲͲͲ͘Ͳ



NL information Amber exceedance



Red limit



KG/H or LBS/H



>  &h> ʹʹ ʹ



Normal operating range



Invalid data



ϭнϮ



ϯϵϰ ͲͲͲ Ͳ > 



^dZd



Start in progress



^dZd



Fault occurs during a start sequence



^dZd



Start invalid signal



y^dZd&/> Cross start failed flag y^dZd&/> Cross start failed invalid signal



&>Kt 25 PSI. Filter blocked and by-passed when ΔPSI>45 PSI



Normal indication Invalid data Unit or type discrepancy



ϱϬϬ



ϴϬϬ ͲͲͲ ͘ Ͳ



ϵϵϵ



ITT numeric counter ITT invalid signal



/'E ITT is displayed only during start sequence



Red line for “S”: limit during engine start



Red line for “H”: limit during Hotel Mode



167



S y s t e m s 4 2/72 - 6 0 0



4. ENG START panel CRANK dry motoring (no ignition)



ON starter engaged. At 45% NH, light goes off and the starter is disconnected



START A OR B on ground, only exciter A or B is supllied (except for the position A&B) In flight regardless of start selection (A, B or A+B) both exciters are energized



UNLOCK PROP BRAKE not fully locked or not fully released. After 15 sec: FWS alarm. Also used to check lock/unlock time: – 5 sec. to unlock – 10 sec. to lock



ATA 61/72 FAULT Illuminates when: – remains ON with NH >45% or – GCU failure during start or – starter failure or – ENG 2 only: ENG START selector on start position + PROP BRK ON + GUST lock not engaged ON Continuous ignition (both A & B). Memo panel light.



42/72 PEC



READY engagement or disengag. conditions are met: – A/C on ground – gust lock engaged – CL on FTH or FUEL S/O – blue hyd press available on the prop brake input >2100psi – Fire handle not pulled



PROP BRK Brake fully locked same indication on the memo panel



5. ENG control panel ARMING CONDITIONS PWR MGT sel on TO +ATPCS pb in +both PL > 49° +both TQ > 46% (72) and > 53% (42) = (arm green LT illuminated)



ATPCS – ARM on ground = uptrim + auto FTR (2.15’’ delay) – ARM in flight (In case of go around) = auto FTR only



ATA 61/72 TRIGGER one TQ below 18% Cancel: PWR MGT out of TO or ATPCS pb OFF or at least one PL retarded below 49° or both TQ 2.5° aileron travel. Lt ON=Spoiler not fully retracted (BLUE HYD PWR). Light on when SW TEST depressed and all door microsws opened. (Passengers and service doors opened) At least 1 microsw is opened. (DC BUS 2) Tests continuity of microsw. System (on ground, doors opened). Fuel delivery pressure below 4 PSI. Pump failure or fuel starvation. FWS.



ENGINE FIRE HANDLE Pulled: on the respective engine Prop Feather Fuel LP valve closed Air Bleed valve closed Deice Deice & shutoff valve closed Elect DC & ACW gen. disconnected Squibs Armed (Lts illuminated) Hydraulic Hyd prop brake (eng 2 only)



Fire test MW+CRC+ ENG 1 FIRE on EWD and FWS +Fire handle illuminated +FUEL S/O Lt on CL (if out of Fuel S/O position) Fault test MC+SC+ loop on FWS FAULT Lts on A/B Loop pb. OFF Takes respective loop out of parallel circuit. Allows other loop to activate fire signal.



The opening of the cargo door control panel cover. Self Test of MFC 1A/2A. FAULT Malfunction or electrical supply fault: AUTO disengagement – FWS



Gear position secondary system as sensed by MFC 2. UNLK gear not in selected position or uplock not opened (on Gnd) Green Lt down lock engaged



Controls XFEED valve. Activates both elect fuel pumps. Controls elect pump power supply and jet pump motive flow valve. Runs automatically if: Jet pump press 92°C. FWS. Pack valve will not auto close. MAN Compt temp knob controls directly temp control valve. Selects the zone where T° check is desired. PACK VALVE Spring loaded closed. Must have air pressure and select power to open (6 sec delay on RH pack for pax comfort). FAULT pack valve disagreement with PB or Ovht downstream of pack comp (>204°C). FWS. Valve auto closed. LEAK activates when temperature detected by bleed loop exceeds 156°C. FWS. Auto closure after 1 sec of following valves: Bleed, HP, PACK and GND XFeed. DO NOT RESET BLEED.



Tests all lights. Ldg Elev indicators show all 8 segments.



Annexes



Menu P/B Enable sub function selection menu



Brightness



SEL P/B Change cursor selection between VHF COM, VHF NAV, BARO SETTING and COURSE when VOR mode.



BOOST (if installed) ON The boost can be selected on ground with the PL below FI, or in flight after an engine failure. When the torque is thermodynamically limited, the boost increase the torque: – With PWR MGT in TO by: – 4.5% up to 4000ft – 4% above 4000ft – With PWR MGT in MCT by 4% The selection of the boost is latched when the PLs are advanced above FI, and can not be changed during flight (except in case of engine failure). FAULT For any disagreement between the position of the push button and the rating of both EEC (MC+SC+FAULT+ENG BOOST on FWS).



FAULT stick shaker or pusher failure. OFF turns off both shaker and pusher



STD P/B Reset at 1013.25Hpa, when pushed more than 0.2 sec.



IESI (Integrated Electronic Stantby Instrument) displays the following information: – Attitude – Airspeed – Altitude – Baro pressure setting – VHF 1 – VOR/ILS 1



SET ROTARY SWITCH – Sub fonction menu scroller – Baro setting – VHF com tuning – VHF nav tuning – Course setting in VOR mode



PWR MGT 2 co-axial sw, (LH: Bottom/RH: Top) providing FDAU (MPC), PEC, PIU and EEC with basic power requirements.



FAULT: illuminates when both PEC channels are lost FWS. OFF: PEC is deactivated and Np is limited at 102.5% by the overspeed governor if power is sufficient.



APM FAULT Failure in the APM function computation APM Test PTT performed daily



PTT pb press for 3 sec. – icing will flash on the display if system works correctly (steady if ice detector failure is detected). – FAULT LT illuminate. A-ICING DETECT is displayed steady on the FWS. ICING AOA Lt illuminates green as soon as 1 horn anti-icing ON. Stall alarm (stick shaker threshold lowered). It can be extinguished manually only by releasing ICING AOA Pb (DC EMER) provided both Horns anti-icing selected OFF.



177



S y s t e m s 4 2/72 - 6 0 0 Panel with EWD format.



Arming conditions: PWR MGT sel on TO +ATPCS pb in + both PL >49° + both TQ > 53%(42) both TQ > 46% (72) ARM green LT on.



ATPCS – ARM on ground = uptrim + auto FTR (2.15” delay) – ARM in flight (In case of go around) = auto FTR only.



UPTRIM signal sent to respective eng during ATPCS sequence. Eng power = RTO.



ATPCS Trigger one TQ 23 kts + 50% diff between wheels (locked wheel protection). Braking action inhibited at touchdown as long as wheel spin up speed 17 kts) = MC + SC EWD 4 amber F on EWD. Test duration: 3 sec. in flight and 6 sec. on ground



Gear handle red Lt any gear not sensed down and locked with the further conditions: a) Any gear not down and locked + flaps normal landing configuration + Zra -1500 ft/mn



NORM AUTO mode selection MAN digital controller out of operation. No more digits in landing elevation display



TEST displays alternatively 18800 and –8800, FAULT appears on MAN pb (Test inhibited in FLT)



FAULT digital controller failure. FWS



DUMP ON (guarded) both outflow valves fully open in AUTO mode only



ON both outflow valves forced to fully closed



CABIN RATE KNOB NORM AUTO MODE position. When used in MAN mode, cabin rate selection +2500/–1500 ft/mn



179



S y s t e m s 4 2/72 - 6 0 0 MCDUs (Multifunction Control Display Unit) Access to the FMS, MPC, and ACARS (Data Link) when the ACARS is installed.



WEATHER RADAR CONTROL PANEL



COCKPIT DOOR CONTROL PANEL Allows to control CDLS (Cockpit Door Locking System)



MULTIPURPOSE CONTROL PANEL (MCP) Allows cockpit crew to control the virtual control panel format (VCP) on MFD



POWER LEVER ( PL )



EMER & PARKING BRAKE CONDITION LEVER (CL) GA push button when depressed the GA FD mode is selected with: – HDG HOLD lateral mode with the wings level – GA vertical mode



EMER AUDIO CANCEL This SW cancels an undue aural alert. Cancelled aural warning will be reactivated: – at next A/C energization – after MFC 1B/2B reset – after pressing RCL pb – following TO config test The alerts here after are rearmed as soon as the triggering condition disappears – landing gear – VMO, VFE, VLE – Stall warning – Pitch trim whooler – AP disconnect



HYD AUX PUMP CONTROL (HOT MAIN BAT BUS) – Aux pump stopped 30” after p/b released (MFC supplied) – Aux pump stopped after p/b released (MFC not supplied)



IDLE GATE IDLE GATE FAIL activated when the gate does not engage automatically in flight or does not extend automatically on ground In this case the idle gate lever enables manual override in case of failure of the automatic logic – In flight: push – On ground pull (an amber band appears)



F/O AUDIO CONTROL PANEL



Manual recording on DFDR or CVR (when supplied by GPU) Manual recording stopped with the reset P/B



EFis Control Panel (EFCP) Allows to control: -Display of the MFD pages (ND, SYST, PERF, MISC, VID and MAP) -Navigation Display (ND) functionalities -Warning Display (WD)



CAPT AUDIO CONTROL PANEL



180



FLAPS



TO CONFIG TEST pb: Check if the TO configuration is correct for take off: – PWR MGT TO – Flaps 15° – Pitch trim in the green band – TLU LO SPD – no AIL LOCK light The same test is performed when advancing the PL with this additional requirement: – Parking Brake released



ACARS & MPC PRINTER



Panel & flood light control



Aileron, rudder & stby pitch trims



ATPCS test (static or dynamic)



Annexes



FD lateral mode



FD vertical mode



NAV SOURCE Selector CAPT side Selects the NAV SOURCE for CAPT EHSI and/or ND depending on display configuration



ALT knob controls the preselected altitude on the PFD



NAV SOURCE Selector F/O side Selects the NAV SOURCE for F/O EHSI and/or ND depending on display configuration



FD bars ON/OFF switch



Chrono P/B Start/Stop/Zero



Chrono P/B Start/Stop/Zero



CRS 1 knob selects Course on CAPT EHSI



STBY COMPASS Hidden in up position. Compass Control should be place on DN For use. The compass rose is graduated in 10 degrees increments



Pitch wheel to adjust – VS or – Pitch attitude in basic mode



CRS 2 knob selects Course on F/O EHSI and ND



– AP pb engages autopilot and yaw damper and disengages only autopilot



HDG knob selects HDG bug on both EHSI and ND



– YD pb engages yaw damper and disengages yaw damper and autopilot if engaged – CPL pb permit to couple AP/FD On CAPT or F/O side In CAT 2 (ILS selected on NAV 1&2) – 1200 ft RA: Dual coupling < > – 800 ft RA: CAT 2 invalid if still in single coupling – 500 ft RA: ILS excess dev activated – 100 ft RA: GS excess dev deactivated



181



S y s t e m s 4 2/72 - 6 0 0



TAWS



TAWS visual alert GPWS If any TAWS mode is activated PULL UP Alert triggered after the GPWS alert in mode 1, 2 and terrain and obstacle awareness modes



GPWS switch and associated lights: ON: All basic GPWS modes are operative FLAP OVRD: In reduced flaps landing, to inhib the mode 4 alert OFF: All basic GPWS modes inhibited. OFF: light come on FAULT: GPWS FAULT —— > some or all GPWS basic modes are lost FAULT: TERR FAULT —— > some or all enhanced modes are lost OFF: All enhanced (TCF&TAD) modes inhibited



AHRS switching P/B To select the opposite side AHRS source. When depressed, SYS 2 is illuminated on CAPT side, while CAPT / 2 is illuminated green on F/O side The CAPT P/B has priority



ACARS message ATC DLK (ATC Data LinK) is illuminated when a message is received through the ACARS. The message can be read on the MCDU



MASTER WARNING MASTER CAUTION



Display P/B The P/B allows to switch formats (PFD/EWD/MFD) on the DU2, or on DU1 if DU2 is OFF.



ADC switching P/B To select the opposite side ADC source. When depressed, SYS 2 is illuminated on CAPT side, while CAPT / 2 is illuminated green on F/O side The CAPT P/B has priority



MFD upper window Displays the different pages selected on the EFCP: – ND page (Navigation Display: shown here) – SYST page (System) – PERF page (Performance) – MAP page (airport mapping) – MISC page (in provision) – VD page (Video in provision)



ND page (Navigation Display) Different mode selected on the EFCP: – ARC mode – ROSE mode – PLAN mode



STEEP APP P/B (optional) When selected ON, moves the mode 1 threshold, to avoid TAWS triggering in steep slope approach



AUDIO 1 SEL FAULT: When the associated RCAU part is failed. ALTN: Affected crew station is connected directly to VHF1 if CAPT station is affected.



Index Control Panel (ICP) Baro setting control



Index Control Panel (ICP) Speed target control



DISPLAY UNIT 1 (DU1) In the normal configuration, with CAPT as PF, the PFD format is displayed



182



Memo Panel Display Displays the following system information when selected FUEL XFEED PROP HORN SIDE WINDOW ENG AIFRAME NO DEVICE SEAT BELT



VCP window (Vitual Control Panel) Displays the informations about: The COM selection The NAV selection (shown here) The SURV (surveillance) selection DISPLAY UNIT 2 (DU2) In the normal configuration, with CAPT as PF, the MFD format is displayed with the ND page. The FMA 1 (Flight Management Application 1) and the RMA 1 (Radio Management Application 1) are included in the DU2 functions



Annexes MFD upper window Displays the different pages selected on the EFCP: – ND page (Navigation Display) – SYST page (System: shown here) – PERF page (Performance) – MAP page (airport mapping) – MISC page (in provision) – VD page (Video in provision)



Display P/B The P/B allows to switch formats (PFD/EWD/MFD) on the DU4, or on DU5 if DU4 is OFF.



Airspeed Indicator (ASI)



Flight Mode Annuciator (FMA)



MASTER WARNING MASTER CAUTION



ELAPSED TIME P/B When the ELAPS TM P/B is depressed ON the flight time starts automatically, on the EWD, when airborne



Attitude Display Indicator (ADI)



Altimeter



ADC switching P/B To select the opposite side ADC source. When depressed, SYS 1 is illuminated on F/O side, while F/O /1 is illuminated green on CAPT side The CAPT P/B has priority



Vertical Speed Indicator (VSI)



SYST page (System page) Different mode selected on the EFCP: – ACW-HYDRAULIC – ENGINE (secondary engine display) – CABIN (shown here) – AC-DC ELECTRIC



CLOCK



AHRS switching P/B To select the opposite side AHRS source. When depressed, SYS 1 is illuminated on F/O side, while F/O /1 is illuminated green on CAPT side The CAPT P/B has priority



LOUDSPEAKERS VOLUME KNOBS Individual knob for each loudspeaker



VCP window (Vitual Control Panel) Displays the informations about: The COM selection (shown here) The NAV selection The SURV (surveillance) selection



DISPLAY UNIT 4 (DU4) In the normal configuration, with F/O as PM, the MFD format is displayed with the SYST page. The FMA 2 (Flight Management Application 2) and the RMA 2 (Radio Management Application 2) are included in the DU4 functions



DISPLAY UNIT 5 (DU5) In the normal configuration, with F/O as PM, the PFD format is displayed.



Navigation Area With the ND on the MFD, the EHSI is displayed on the PFD. With an other page on the MFD, a mini ND is displayed on the PFD. The mini ND can be in ARC mode or ROSE mode, selected on the EFCP.



Index Control Panel (ICP) Speed target control: – Speed target selection Selection of the speed bug between: – AUTO: Speed bug managed by the FMS (Magenta) – MAN: Speed bug set manually by the speed knob (Cyan) – Speed knob Used to set the speed bug In MAN mode (Cyan)



Index Control Panel (ICP) Baro setting control: – Barometric setting knob The knob is used to set the barometric reference. Pushing the knob sets standard barometric reference (29.92 INHG / 1013.25 Hpa) – DH / MDA knob Outer knob permits to select between DH (Decision Height) or MDA (Minimum Descent Altitude). Inner knob is used to set DH or MDA values, depending of the outer knob position.



READING LT knob Control the respective spot light



CONSOLE LT knob Control the lights of the associated lateral console



AUDIO 2 SEL FAULT: When the associated RCAU part is failed. ALTN: Affected crew station is connected directly to VHF2 if F/O station is affected.



183



S y s t e m s 4 2/72 - 6 0 0



Parking/emergency braking accumulator pressure indicator This indicator is used when the MFDs are not energized, to check brake accumulator pressure. When the switch is activated, the indicator is energized for two minutes When the accumulator pressure is 3100 psi, the indicator displays blinks.



N/W STEERING ON: The steering solenoid valve is electrically armed. The steering is available with an angle up to 60° in either direction OFF: The steering system is unpressurized. Should be OFF for towing and push back The steering is disconnected with an angle up to 91° in either direction



Nose wheel steering Push To Talk When depressed, BOOM SET or OXY mike is connected for transmission over the selected communication facility



Test & Reset slider



Blinker indicator



Normal/100% selector



RH red grips (inflate harness)



Emergency rotaty knob



Position of the selector: EXT PWR DC panel indicates the DC GPU voltage & current AC panel indicates the AC GPU voltage, load & current GEN 1/ 2 DC panel indicates the DC Generator voltage & current AC panel indicates the ACW Generator voltage, load & current INV 1/ 2 No indication on DC panel AC panel indicates the AC Inverter voltage, load & current MAIN and EMER BAT DC panel indicates the DC Main & Emer Battery voltage & current No indication on AC panel



PRELIMINARY COCKPIT PREPARATION: OXYGEN MASK TEST INT/RAD SELECTOR (On AUDIO CONTROL PANEL) .................................SET TO INT PRESS TO TEST AND RESET PB ............................................. DEPRESS AND HOLD



NOTE: Hose and mask charged with oxygen. Observe blinker momentarily turns yellow and must turn dark if there is no leak PRESS TO TEST AND RESET PB ...................................................................... HOLD RED GRIPS ON EACH SIDE OF THE HOSE ......................................................PRESS



NOTE: Oxygen pressure inflates the harness. Observe blinker momentarily turns yellow and must turn dark PRESS TO TEST AND RESET PB ...................................................................... HOLD EMERGENCY KNOB ....................................................................................... SELECT



NOTE: Emergency flow is tested. Observe blinker momentarily turns yellow during oxygen flow and must turn dark when the knob is released. NOTE: In this 3 cases, check that oxygen flow sounds though loudspeakers OXY LO PR LIGHT ................................................................. CHECK EXTINGUISHED N/100% Selector ..................................................................................... SET to 100%



184



Annexes



FLIGHT DECK VENTILATION ISOLATION EXTRACT AIR FLOW CAUTION: Close only in case of FWD COMPT smoke Enables, in case of smoke in the forward cargo compartment, to isolate the flight deck ventilation preventing smoke to enter the flight compartment



BITE LOADED magnetic indicator Indicates that a failure has been recorded by the maintenance system. Report to maintenance



MAIN PNL Before the flight, check that all the switch and selector are in the normal position. If not, the MAIN PANEL is displayed on the FWS



BRK TEMP TEST When depressed, MC, SC, WHEELS BRK HOT on FWS



185



Annexes



Annex 2. Abbreviations A AAS AC A/C ACARS AC BTC AC BTR ACW ADC ADF ADI ADN ADS AFCS AFDX A/FEATH AFCA AFT AFU AGB AHRS AHRU AIL ALT ALTM ALTN AMP AOA AP APP APU APAU ARINC A 429 ARM ASI ASYM ATC ATPCS ATT ATTND AUTO AUX AVAIL



Anti-icing Advisory System Alternating Current Aircraft ARINC Communication Addressing and Reporting System AC Bus Tie Contactor AC Bus Tie Relay Alternating Current Wild Frequency Air Data Computer Automatic Direction Finder Attitude Director Indicator Avionic Data Network Air Data System Automatic Flight Control System Avionic Full DupleX Auto Feathering Auto Flight Control Application Rear Part Auto Feather Unit Accessory Gear Box Attitude and Heading Reference System Attitude and Heading Reference Unit Aileron Altitude Altimeter Alternate Ampere Angle of Attack Auto-Pilot Approach Auxiliary Power Unit AutoPilot Actuator Unit Aeronautical Radio INCorporated ARINC 429 Armed Air Speed indicator Asymmetry Air Traffic Control Automatic Take off Power Control System Attitude Attendant Automatic Auxiliary Available



B BARO BAT BC BITE BPCU BPU



Barometric Battery Back Course Built in Test Equipment Bus Power Control Unit Battery Protection Unit



BRG BRK B-RNAV BRT BTC BTR



Bearing Brake Basic Area Navigation Bright Bus Tie Contactor Bus Tie Relay



C CAB CAC CAPT CAT C/B CDI CDLS CHAN CHC CL CLA CLB CLR CMA CMS CMPTR CMU COM COMPT CONFIG CPL CPM CRC CRS CRZ CTL CVR



Cabin Core Avionic Cabinet Captain Category Circuit Breaker Course Deviation Indicator Cockpit Door Locking System Channel Charge Contactor Condition Lever Condition Lever Angle Climb Clear Centralized Maintenance Application Cabin Management System Computer Communication Management Unit (ACARS) Communication Compartment Configuration Auto Pilot Coupling Core Processing Module Continuous Repetitive Chime Course Cruise Control Cockpit Voice Recorder



D DC DCA DELTA P DEV DFDR DGR DH DIFF DISCH DIM DIST DLK DME DMU DN DSPL DU



Direct Current Data Concentration Application Differential Pressure Deviation Digital Flight Data Recorder Degraded Decision Height Differential Discharge Light Dimmer Distance Data LinK Distance Measuring Equipment Data Management Unit Down Display Display Unit



187



S y s t e m s 4 2/72 - 6 0 0 E EEC EFCP EFIS EHSI EHV ELEC ELV EMER ENG EQPT ESS ETOPS EWD EXT



H Engine Electronic Control EFis Control Panel Electronic Flight Instrument System Electronic Horizontal Situation Indicator Electro Hydraulic Valve Electrical Elevation Emergency Engine Equipment Essential Extended Twin Operations Engine & Warning Display Exterior, External



F F FAIL FAP FCOC FCU FD FDA FDAU FEATH, FTR FF FGC FGCP FGS Fl FLT FMA FMA FMS F/O FOS FQI FT FU FWD FWS



Farenheit Failed, Failure Flight Attendant Panel Fuel Cooled Oil Cooler Fuel Control Unit Flight Director Flight Data Application Flight Data Acquisition Unit Feathered, Feathering Fuel Flow Flight Guidance Computer Flight Guidance and Control Panel Flight Guidance System Flight Idle Flight Flight Management Application Flight Modes Annunciators Flight Management System First Officer Flight Operations Software Fuel Quantity Indication Foot, Feet Fuel Used Forward Flight Warning System



G GA GCU GEN GI GND GPS GPU GRD G/S GSPD



188



Go Around Generator Control Unit Generator Ground Idle Ground Global Positioning System Ground Power Unit Ground Glide Slope Ground Speed



HBV HDG HF HI HLD HMU HP HSI HTG HYD



Handling Bleed Valve Heading High Frequency High Hold Hydromechanical Unit High Pressure Horizontal Situation Indicator Heating Hydraulic



I IAS ICP IDT IESI IGN ILS IMA IND IN/HG INHI INOP INST INT INV IOM ISOL ITT



Indicated Air Speed Index Control Panel Ident Integrated Electronic Standby Instrument Ignition Instrument Landing System Integrated Modular Avionics Indicator Inches of Mercury Inhibit Inoperative Instrument Interphone Inverter Input Output Module Isolation Inter Turbine Temperature



JK KHZ KT



Kilo-Hertz Knot



L LAT LAV LB LDG L/G LH LMU LNAV LO LOC LO-PR LP LT LVL



Lateral Lavatory Pound Landing Landing Gear Left Hand Light Management Unit Lateral Navigation Low Localizer Low Pressure Low Pressure Light Level



M MAX MAP MB MC MCDU MCP



Maximum Mapping Millibar Master Caution Multifunction Control Display Unit Multifunction Control Panel



Annexes MCT MECH MFC MFCU MFD MGT MHZ MIC MLG MIN MIP MISC MKR MLW MM MMO MOD MPC MPU MSG MSN MTOW MW MZFW



Maximum Continous Mechanic Multi Function Computer Mechanical Fuel Control Unit Multi Function Display Management Megahertz Microphone Main Landing Gear Minimum Main Instrument Panel Miscellaneous Marker Maximum Landing Weight Millimeter Maximum Operating Mach Modification Multi Purpose Computer Micro Processor Unit Messages Manufacturer Serial Number Maximum lake off Weight Master Warning Maximum Zero Fuel Weight



N NAC NAV ND NDB NEG NH NIL NL NM NORM NP N/W NWS



Nacelle Navigation Navigation Display Non Directional Beacon Negative High Pressure Spool Rotation Speed Nothing, No Object Low Pressure Spool Rotation Speed Nautical Mile Normal Propeller Rotation Speed Nose Wheel Nose Wheel Steering



O OAT OVBD OVERTEMP OVHT OVRD OXY



Outside Air Temperature Overboard Overtemperature Overheat Override Oxygen



P PA PB PEC PED PERF PFD PIU PL PLA PNL



Passenger Address Push Button Propeller Electronic Control Pedestal Performance Primary Flight Display Propeller Interface Unit Power Lever Power Lever Angle Panel



POS P-RNAV PRESS PRIM PRKG PROP PSI PSU PT PT (TCAS) PTB PTT PTW PVM PWR PW



Position Precision Area Navigation Pressurization, Pressure Primary Parking Propeller Pound per Square Inch Pax Service Unit Point Proximity traffic Pitch Trim Box Push To Talk, Push To Test Pitch Thumb Wheel (same as PW) Propeller Valve Module Power Pitch Wheel (same as PTW)



Q QAR QT QTY



Quick Access Recorder Quart Quantity



R RA (TCAS) RA RAD/ALT RAD/INT RCAU RCDR RCL RCU RECIRC REV RGA RGB RH RLY RMA RMI RMS RNP RPM RTO RUD



Resolution Advisory Radio Altitude Radio Altitude Radio/Interphone Remote Control Audio Unit Recorder Recall Releasable Centering Unit Recirculation Reverse Reserve Go-Around Reduction Gear Box Right Hand Relay Radio Management Application Radio Magnetic Indicator Radio Management System Required Navigation Performance Revolution Per Minute Reserve Take-Off Rudder



S SAT SBY SC SEL SGL SGU SMK SMKG S/O (SO) SOV SPD SPLR SPLY



Static Air Temperature Stand By Single Chime, Starter Contactor Selector Single Symbol Generator Unit Smoke Smoking Shut Off Shut Off Valve Speed Spoiler Supply



189



S y s t e m s 4 2/72 - 6 0 0 STBY STRG SSFDR SURV SVCE SW SWM SYS



Stand By Steering Solid State Flight Data Recorder Surveillance Service Switch gateway and SWitch Module System



T TA (TCAS) TAD TAS TAT TAWS TCF TCS TEMP TGT TK TLU T/O (TO) TOW TQ TRU TTG



TRAFFIC Advisory Terrain Awareness Display True Air Speed Total Air Temperature Terrain Awareness Warning System Terrain Clearance Floor Touch Control Steering Temperature Target Tank Travel Limiting Unit Take off Take off weight Torque Transformer Rectifier Unit Time To Go



U U/F UHF UNCPL UNDV



190



Underfloor Ultra High Frequency Uncouple Undervoltage



UNLK UTLY



Unlock Utility



V VC VCP VENT VERT VHF VID VMO VNAV VOR VSI



Calibrated Airspeed Virtual Control Panel Ventilation Vertical Very High Frequency Video Maximum Operating Speed Vertical Navigation VHF OMNI Directional Range Vertical Speed Indicator



W WARN WOW XFEED XFR



Warning Weight On Wheel Cross feed Transfer



XY YD YDAU



Yaw Damper Yaw Damper Actuator Unit



Z ZA ZCTH ZFW ZP ZRA



Aircraft Altitude Theoretical Cabin Altitude Zero Fuel Weight Pressure Altitude Radio Altimeter Altitude



Dear Readers, Every effort has been made to ensure document quality. However please do not hesitate to share your comments and information with us by using the following address: [email protected] Yours faithfully,



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Your ATR Training and Flight Operations support team.



© ATC June 2012 All reasonable care has been taken by ATC to ensure the accuracy of the present document. However this document does not constitute any contractual commitment from the part of ATC which will offer, on request, any further information on the content of this brochure. Information in this brochure is the property of ATC and will be treated as confidential. No use or reproduction or release to a third part may be made there of other than as expressely authorised by ATC.



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