![Sense Nich [PDF]](https://pdfs.asia/img/200x200/sense-nich.jpg)
18 0 4 MB
ATP INDEX COPYRIGHT
2006
COPYRIGHT IS NOT CLAIMED AS TO ANY PART OF AN ORIGINAL WORK PREPARED BY A UNITED STATES GOVERNMENT OFFICER OR EMPLOYEE AS PART OF THAT PERSONS OFFICIAL DUTIES OR BY ANY OTHER THIRD PARTY OFFICER OR EMPLOYEE AS PART OF THAT PERSONS DUTIES. "ATP" is a registered trademark of Aircraft Technical Publishers. All original authorship of ATP is protected under U.S. and foreign copyrights and is subject to written license agreements between ATP and its Subscribers. ALL RIGHTS RESERVED. NO PART OF THIS PUBLICATION MAY BE REPRODUCED, STORED IN A RETRIEVAL SYSTEM, OR TRANSMITTED IN ANY FORM BY ANY MEANS, ELECTRONIC, MECHANICAL, PHOTOCOPYING, RECORDING OR OTHERWISE, WITHOUT PRIOR WRITTEN PERMISSION OF THE PUBLISHER.
Customer Service
Aircraft Technical Publishers 101 South Hill
6AM-5PM PST M-F
Drive
(800)227-4610
Brisbane, CA 94005
ATP Grid Index to Manufacturer’s Publications:
Sensenich Sensenich
Corp. Propellers: Wood, Aluminum
Splined Hub(Jacobs)
Collection of Maintenance Information Section General
Topic Information
Title
Page
Record of Revisions Record of
Temporary
Revisions
03
Propeller Repair Manual (FAA-DER Approved) Fixed-Pitch Aluminum Propellers Fixed-Pitch Wooden Prope~lers
04
Service Information
01
Metal
01
02
Metal
Propeller Repair
Manual
(FAA-DER
Approved)
Introduction
Definitions, Common Types of Service Damage Installation Instructions
Repair
Instructions
Method to Measure Degree of Bend in
a
Blade
Approved Techniques for Repair of Blade Damage Allowable Tip Mod at Min Chord, Thickness Dia Blade Angle Templates Repair Specifications: 69C Series Propellers 72C Series Propellers 74C Series Propellers 740 Series Propellers 76A Series Propellers 76E Series Propellers Appendices 02
07/22/2005
Fixed-Pitch Aluminum
Copyright
Propellers Aircraft Technical Publishers SS
0501
MP)
Page
1 of
3
Section
Topic Installation List No. 393A
Propeller Price List Aluminum Propeller Bolt Kits Metal
03
Fixed-Pitch Wooden
Instl, Oper Instl
Propellers Maint Integral Flange Crankshafts
Maint Instructions (W98AB,W963B.W90T6JB)
Installation List No. Wood
07/22/2005
Propeller
1291
Price List
Copyright
Aircraft Technical Publishers SS
0501
MP)
Page
2 of
3
Section
Topic
End of Index
07/22/2005
Copyright
Aircraft Technical SS
0501
MP)
Publishers
Page
3 of
3
MFG. INTRO
RECORD OF REVISIONS
MFG REV NO
DESCRIPTION
ISSUEDATE
ATPREVDA
INSERTED BY
RECORD:O F T~M PORPIRY REVIS I ON S
TEMP REV NO
DESCRIPTION
ISSUE DATE
ATP REV
INSERT
DATE
REV
REMOVE
DATE
BY
REMOVED
INCOR
BY
01
SPRM 590
METAL PROPELLER REPAIR MANUAL FAA-DER APPROVED
SENSENICH PROPELLER CO.
P.O. BOX 5100
LANCASTER, PA 17601-0100
EAST AIRPORT ROAD
717-560-3711 OUTSIDE PA
1-800-462-3412
INDEX
]NTRODUCTION.
DEFINITIONS,
1 COMMON TYPES OF
INSTALLATION REPAIR
.......2
DAMAGE
SERVICE
.................3
INSTRUCTIONS
.................4-
INSTRUCTIONS.
FIGURE r: METHOD TO MEASURE DEGREE OF BEND IN A BLADE FIGURE 2: APPROVED TECHN1QUES FOR
FIGURE 3: ALLOWABLE FIGURE 4: BLADE
TIP
ANGLE
REPAIR OF BLADE
MODIFICATION,
AT MINIMUM
.....6
DAMAGE-.....,... ......7
CHORD, THICKNESS, Bi DfA....... 8 9.
TEMPLATES.
690 SERIES
PROPELLERS, REPAIR SPECIFICATIONS
720 SERIES
PROPELLERS, REPAIR SPECIFICATIONS
14
740 SERIES
PROPELLERS, REPAIR SPECIFICATIONS
18
740 SERIES
PROPELLERS, REPAIR SPECIFICATIONS Serial
without letter
A31171 Bi
Serial
1~0,
prstix,
hiOher,
a
It
"A’’ pretiIt
Ik)l, (18~1,
or
PROPELLERS,
Iower than A311t1......22
IleK" pefbt Serial Numbert.....26
76LISERIES PROPELLERSi REPAIR SPECIFICATIONS. 765 SERIES
~a
REPAIR SPECIFICATIONS
....30
..34
APPeNDrCES AIRWORTHINESS
Al
DIRECTIVES
SERVICE BULLETIN
NO.R-2.............
SERVICE
BULLETIN
NO. 8-3.
SERVICE
BULLETIN NO. 8-8-1
A3 .........A3 A4
SERVICE BULLETIN
NO.
R-LL.............
Ab
SERVICEBULLETIN
NO.
R-12A
A6
SERVICE BULLETIN
NO. 8-13
..........Af
SERVICE
8ULLETIN NO. 8-14
AB
USE AND
CARE-INSTRUCTIONS, FIXEPPITCH
SERVICE LETTER
ENGINE~RING SERVICE
A9
80-1(added 1-15-80).
MEMO
MEMO
METAL PROPELLERS.
4781(added
Jon,198O)
#86-~1(3 September 1986)
SERVICE BULLETIN NO. R15A SERVICE BULLETIN NO. R16
A12 ..A13 ............A14
A15
s iW c2N
C
-=12~-, METAL PROPELLER REPA1R MANUAL 1NTROM)CTION The purpose of this Service Manual is´• to
provide
the
natdy
to loads which tend to stretch the metal ad then
repair information necessary to maintain a fixebpitch metal propeller in on airworthy cocldih’on. The types of service-domage which may render a fixebpitch metal propeller unairworthy are mainly mechanical injuries such a arts, nides, ad dents caused by the impact of stones, gravel, sand, etc. Usually a
The time which elapses Qring a cycle is called the period of v~ralon. The number of cydes pa second, a other
dlsplacensnt
unit of
of the metal is involved and the void
is
roughly V-shaped in crosi-section with the shap point of the
~’L’ pointing inward, away
metal. There is olso
a
franlthe surface of the
type of chemicaldanage which
involves carosion at the intafaces of the
to canpress it. The sequence d events which occur os the load on a portion of the blade section varies fran hw
of maximum tension thru maximun canprsssia, ad bade to maximum tension is called a cycle ot vibration.
po’nt
time,
b called m~´•
fre(Fracy of dm vibrotkh The
number of cydes ptr revolution of me propeller is called the ada of the vibration. The forces which shake
a
propeller end
case
it to
propeller is subjected to two kinds of loads A stress is merely the load or force which
mainly in the pista, sgine which drives it. vibrate A piston engine does not produce a smooth and camstat torque. The rated torque of a direct-drive engine is merely the mean value of the´•to~que mplbestoka, ova The ordas a paiod of ae revokrtia of dm aaJuhoft. of me torque impulses ae determined by me numba of engine cylindas and their arangement. These ordas as usually integer multiples of the nunber of firing impulses per revolution of tt~e engine aonkshaft. For example, a fourccyinndr engine, with the cylinders in two banks,a-
across a unit aeo of the blade aoss-section. The first of these stresses is steady ad continuous and due to the combination of the Centrifugol forces ’ossocioted
raged at an cngle of 1600 to each other, will produce torque impulses at frequencies which as 2, 4, 6,8,... Rmes the rotational speed of the engine.
with the rototion of the propeller, and forces which ae the reaction of the airlood on the blade. These cen-
natural
main
struc-
ture of the metal.
pitting.
In this manual it is celled corrosion The -mechanical affect of this on me strength of a "V" notch with the sharpest objective of all repair techniques V-shaped notch and to leave the repairarea
the metal is like that of
possible edge. to
in
remove
this
It is the
rounded well-faired condition. It is worthwhile to aderstad me reasas behind these procedures. a
smooth,
A metal or
stresses.
acts
trifugal forces ore very large when a typical light-plane A propeller is operating at its rated rotational speed. particle of metal nea the tip of the blade My exert an outward pullroughly 7500 times greater than its own weight.
The forces due to the reaction of the blade to
the airlaod tend to bend it out of the plane of rotation and the centrifugal faces fend to straighten me blade
bring it back into the plane of rotation, so that in operation the blade will seek some intermediate a equF librium position. The sum of the stresses caused by these steady forces constitutes ew total steady stress to which a blade is subjected at a given rotational speed, power input, ad fotword speed of the propeller. It varies, of course, along the radius of the blade in a mcnner which is determined by the shape ot the blade. At rated conditions of power, rotational speed, and forward speed it is possible, by proper design of me blade, to hold the maximum value of these steady stresses below a value of and
about 7500 pounds per squae inch. This is about oneyield strengtR of aluminum alloy 2025, heat-
fourth of the
Specification T6, which is the metal universally throughout the light-plone propeller industry. The second type of stress is an o)tenating a vibfatocr stress. In this type of stress,the Made is subjected alterheated to
used
aise
A metal
propeller, like a tuning fork, ha a set of frequencies of vibratoon’These frequencies ore determined by the shape of the blade its length, thlckWhen an, of the ness distribution, and width dstribution. notwal
frequencies of the propeller coincides with the frequency of a shaking force put out by the engine, a !esonancs peek occurs. At this oondition, degendng ema the magnitude of the shaking faces coming from dm engine ad the damping faces in the prapelC, vibratay stresses may become very large. I~wing the de~igl of a metal propeller intended for use on engines of a portic~br model, an effat is mads to tune the propeller so that donge~oos resonance pedo will fall outside the operating range of engine rototionol speed, Over the period of mayyyeors in which forged aluminum alloy propellers have been in use, service recads have shown that a propeller con operate safely, provided the values of steady stress and vikatay stress
ae
held to certain well-established levels. When a combinotion of steady ad v~otay stresses is dlowed to exceed
these levels, otter the acarmulatia of a sufficient nunba cycles, or fatigue cycles a we may call them, the strngth of the metal begins to deteriorate and a fatigue erode may develop which can quickly lead to a failure of the propella. Much test wak ha been daw, to determine the numba of fatigue cycles required, at a of vibratia
given level propellers
of
produce a fatigue failure. Metal type certificated until it has been
strtss, not
ore
to
demonstrated that the es
for each
steady stresses and vibratory stress propeller-engine combination ore at a satis-
factory revel. The ´•values of allowable steady and vibratory stress which experience has shown to be satisfactory apply to
well-faked
undamaged
blades.
When
a
blade
propeller
sustains damage in the form of a shatp-bottamed notch, the stress level at the root of the notch may be increased
by
an
same
amount many times greater than~the stress at the location in an undamaged blade. The notch effect
stress concentration
factor,is dependent Ilpon the depth and the sharpness of the bottom of the notch. This local stress may increase to a level at which very little more or
:iil
flight time is required to initiate a crack which may prop~ gate rapidly and lead to an early blade failure. It is far this reason that frequent inspectior~s and prompt repair of damage of this type ore urgently recommended. There is another way in which, during the service life of the propeller, the vibration characteristics of an engine propeller combination stresses rise to
?1
may be altered
so
that
vibratory
levels. This situation is
bought by a shift of one or more of the resonance peaks a frequently used range of engine rotational speeds. dangerous
about into
When. the thickness and width of the blade have been
_1
by repeated repairs, natural frequencies of
duced
the stiffness and
the
vibration
are
re-
therefore,
also -reduced.
CORROSION FITTING
Tiny deep cavities extending inward from the surface of the metal; may tunnel under the surface, re-appear at anofher~locotion. CRACK- Physical separation of adjacent portions of the metal, which may extend far below the surface of the blade. Usually initiated by a nick, scratch, or corrosion pits in an area of the blade subjected to coritinuous vibration. Loss of metal
over
a
relatively long
area, sometimes extending to
on
and
narrow
appreciable depth,
by a sharp-edged object striking glancing blow.
caused
the blade
A depression in the blade surface produced direct impact of a hard object.
EDGE ALIGNMENT- Blades out of edge alignment so
that
blades
EROSION
a no
an
axis
nearly perpendicular corresponding stations of the
by are
twa
cuts the center of the hub bore.
Loss of metol from the surface
action of smell
a
to the chard
line through
longer
foreign objects
usually found in the side of the blade.
original blade dimensions large enough significant shift, either up or down, away from the set of natural frequencies originally designed into the propeller, may bring an undesirable resonance peak into the cruising range of engine rotational speeds. This is why minimum repair dimensions and diameter limits are established far each engine-propeller combination. Alternating stresses are the cause of metalfotigue. It is the number of fatigue cycles and the stress level at ta
cause a
which they have been accumulated which determines the endurance life of a Propeller. Research haj Shown that the life expectancy of metal specimens, which have been fatigue-cycled to 50% of their endurance life. con be
extended by the removal of a thin layer of surface metal. It is good practice then, periodically to remove the layer.
fatigued surface metal and the accumulation of small by ~econditioning the entire blade. In summary then, it may be said that the general poC icy behind safe blade repairs is to hold reductions from tha original blade dimensions to a minimum, and to remove any IIV´ notch type of damage as promptly as possible by rounding-out, fairing, and polishing the area of domage. Itis intended that the methods, techniques, and practices af FAA Advisory Circular 43.I3-1A be followed, however minimum blade dimensions after repair shall be governed by the ~dato in this manual. of
cuts and scratches
area
of the
by mechanical
grit or sand; leeding edge and flat such
os
FACE AL1GIJMENT- Blades out of face alignment bent about
an
axis
the blades do not
nearlr~ parallel
Iltrack
to the
chard
so
me
that
.I
FRETTING- Breakdown or deterioration of a metal surface by a vibratory or chafing type of action.
GOUGE
Deep grooves in a blade caused by contact with foreign object under heavy pressure. INCLUSION Scale or other foreign material embedded a
in the metal. NICK- A sharp bottomed notch involving displacement of metal, usually found on the leeding and trailing
edges of
DENT
bent about
alteration of the
COMMON TYPES OF SERVICE DAMAGE TO ALUMINUM ALLOY PROPELLERS
DEFINITIONS;
CUT
The effect of a diameter reduction of the propeller is to increase the natural frequencies of the blades. Any
a
propeller blade.
or break in the metal surface intermediate in size and depth between a gauge and a scratch.
SCORE
A tear
SCRATCH-A small and superficial cut in the metal face.
Usually found
on
the flat side of the
sur-
propeller
blade.
SURFACE CORROS1ON- Loss of metal from the face by chemical or electro-chemical action. The rosion products
can
surcar-
easily be removed by sanding.
rNSTALLAfION ~NSTRUCTIONS FIXEDIQITCH METAL PROPELLERS Before
installing
a
propeller, thoroughly
clean
the
surfaces of the crankshaft flange and pilot rear face of the propeller hub boss, and the
Carefully
examine each
surface,
the
stub, pilot bo~e. especially examine
and
the end of the crankshaft pilot stub. Even minor nicks burrs must be smoothed.
or
The
propeller attaching bolts, and the threads in the drive bushings or retaining nuts, must be clean and dry. When installing the attaching bolts apply torque in small increments, working diagonally across the bolt circle until reaching the recommended wrench torque. WRENCH TORQUE NOTE:
1
kilogram-meter
is
ATTACHING BOLT DIAMETER
RECOMMENDED WRENCH TORQUE
inch.............. .280 to 300 pound-inches (31.6 to 33.9 newton-meters)
I inch .........,480 to 540 pound-inches 16 154.2 to 61.0 newton-meters)
3 inch equivalent
..............720 to 780 pound-inches
(81.3
to 9.806
to 88.1
newton-meters
86.80
newton-meters)
pound-inches
SENSENICH METAL PROPELLER MODEL DESIGNATION Metal propellers manufactured after May 1, 1968
are
identified by basic diameter, blade desigrCand hub design. A specific model designation includes spacer length, diameter reduction
("cut-offll),
and
The propeller
attaching kit propeller designotion includinp EXAMPLE of
pitch
as
shown below.
is identified spocer
by the basic lenpth.
PROPELLER MODEL CROSS-REFERENCE CHART
Propeller Model 69CK
Propeller Models
74 D M6 SS
2
LT
-CISpecified
904 iP2
74CK-2
M74CK-2
1P2
740C
M74DC M740M
886 886
M74DR
886 886
+740R-1
M74DR-1
886
76AK-2
M76AK-2
1P2
76AM6-2
M76AM-2
1P2
.76EMB
M76EMM
P4EA
808M8
MBOBMM
PLIEA
2 inches di.mcter
74DM6
Designates integral spacer, 5/4 inches
doweled
design,
hub
740M7 7408
see
design
Basic diameter (inches)
ATTACHING KIT for EXAMPLE
Ropller:14DMGSS
NOTE:
Before May was
CODE, Sensenich
Metal
Propellers
"C"-SAE ARP-502 crankshaft flange "Kn- SAE Number 1 crankshaft flange IM6"- SAE Number 2 Standard flange, 6/16(=3/8) inch diameter attaching bolts and 5/8 inch diameter drive bushings.
ter
flange, 7/16 inch diameter at5/8 inch diameter drive bushings. Number 2 flange, 8/16(-1/2) inch diame-
SAE Number 2
"R"-
SAE
90 4 M74CK
Ireduction
Blade
"MB"
No.9O4
74CK
below:
taching bolts
T.C.
72CC
pitchlinches)
Designates
IMf"
M69CK
72CK
60
L--lOe.ignote.
HUB DESIGN
Equilrolent Model (Mfr d before Hoy 1, 1968)
(Current)
and
attaching bolts and 3/4
inch dia. drive
SAE Number 3 crankshaft
flange
bushings.
76EM8S5
~No
1,~1968 only
were
longer
in
one
spacer
length
Models 74DM6S5 and
available.
M740MS and M76EMMS.
production
REPAIR lbISTRUCTIONS 1. CLEANING: Before a damaged propeller con be properly examined to determine whether it is re-
After the
pairable, it should be cleaned and the paint removed, Cleaning may be accomplished with soap and water,
brought into face alignment, blade Blade Angle Templates checked. angles should be
soft bristle
(availoble from the Sensenich factory) should be
or
with
suitable mineral solvent and
a
The point able commercial paint
a
a
must be soaked free with
brush.
soft bristle brush
scraped off with a wire brush.
remover
or
a
suit-
with
It should not be
rag.
steel tool
a
a
and removed
nor
brushed oft with The purpose of
a
pre-repair inspection is to avoid investment of labor, only to later discovir unrepairable damage had been suttafned by the propeller. When ured
a
blade is
bent,
the bend must be
meas-
by Figure 4 os indicated by the oppropriote repair specifications, which list the proper blade angles and tolerance for each spec-
used
os
shown
pitch. The blades should be twisted to agree specifications. Note that bending a blade into face alignment and twisting to obtain ified
the proper blade angles are not independent ope~-´• otions. After blade angles have been corrected,
face
must be
alignment
until both
checked,
and
vice-versa
within tolerance.
are
by the method shown in Figure 1 of this and compared to the appropriate graph
a EDGE ALIGNMENT: Inspection of edge alignment should not be attempted before face alignment and
blade radius. Be-
Edge alignment con then be measured on a propeller checking stand by setting height gauges to touch the leading edge of each blade at corresponding stations, then remaving the propeller~ from the stand and ratating it
manual,
of maximum allowable bend
vs,
which, by
shape at
ware
ot repairing bend, indicate pre-straightened
bends
the
that the blade may have been to bring it within allowable
limits.
20-7J!August, 1972).
See A.C.
the
The depth of a cut or gauge should be measured to determine whether repair is possible within the limits of the appropriate minimum blade dimensions, A pre-repair examination must include a visual
inspection’
with
a
magnifying glass
of at least three-
An power for the presence of fatigue crocks. indispensable aid to visual inspection is either an
etching or dye-penetrant process. 3. STRAIGHTENING A BENT BLADE: If the bend is within allowable limits, this should be the first
repair operation. Using a suitable bending tool or repair bench, the blade should be straightened in smollinc~ements proceeding from the portion of the bend nearest the hub, where the blade is thicker, outward along the blade until the fairing and appearance of the blade ore reasonably good. At this point, the results can be judged by sighting along the blade. Blade contours should flow smoothly from the tip inward, without apparent waves or curvature reversal. The propeller should then be placed on a propeller checking stand, and its face alignment checked by comparing correspending stations of the repaired blade with those of the undamaged blade. If is not feasible, in this
complete
face
alignment
manual,
data for each
the correct elevation of the blade
hub face is
given
blade
propeller.
tip
with the repair
from
the
specifications
angles
are
correct.
degrees before replacing it on the stand. It permissible to straighten a blade which has been bent out of edge alignment. If it is not possible to achieve proper 180 degree index of the blades by removal of metal from the leading edge of one blade and from the trailing edge of the apposite blade within allowable blade dimensions, the propeller must be removed from service. 180
is
never
6. REPAIR OF BLADE DAMAGE: Approved techniques for repair of damage to metal propeller blades are
shown, by Figures 2 and 3 of this manual. or cuts into the leading dr trailing edge of
Nicks
blade may be individually repaired as shown by Figure 2, Illustration B. The repair should be a
accomplished by roundjng out and fairing with a file to slightly deeper than the apparent depth of
damage, to ensure that the bottom of the injury is removed, and polishing with a fine
the
abrasive cloth.
The chordwise depth of the fin-
ished repair must not be greater than 3/16 inch (0.48 cm.) and- the final chord must equal or ex-
ceed the minimum specified by this manual. The radius of curvature in the area of the repair must be
to include
However, if both blades of a propeller have been bent, and if an undamaged propeller of the same model and pitch is not available for comparison, rear
blades have been
with these
2. PRE-REPAIR INSPECTION:
I
for each pmpellet model.
4.BLADE ANGLES CORRECTION:
3/8 inch (0.95 cm.) minimum. The faked length inches(3.8 cm.). repoir should not exceed
13
of the
repairs is permissible only if the repair areas do not overlap. Dents or gauges in blade faces may be individually repaired os shown by Figure 2, Illustration A. This repair shouid be accomplished by rounding out
More than
and
one
fairing
of these
with suitable abrasive paper
or
cloth to
depth sufficient to ensve complete removal of the damagedmetal and polish~g with a fine abrasive cloth. The finished repair mustnot exceed 1/16 inch~0.l6cml)in depth and curvature of the surface in the aea of the repair must be 3/8 a
inch(O.95an.) radiusminimum.
pair
should not exceed
The
finished
re-
yS inch(0.95cm.) chordwise
by 1 inch[2.54 cm.) long. More thon~ one of these repairs per blade is permissible only it the repair areas do not overlap a common blade radius, Longitudinal cuts, as shown by Illustration C of Figure 2, may be repaired in the same mamer os repair of a dent or gauge ina Made face. A transverse (chordwise) crack in a blode
face,
or
at the
leading
a
repaired.
be
trailing edge
The presence of that blade failure is ’anminent.
a
cannot
aack ’ndicates
The propeller immediately removed from service. WARNING: Repair of nicks, cuts, or cracks by must be
peening over the adfacent edges is not permissible. This procedure will induce a tensile pre-stress at the bottom of the damage and will almost certainly initiate the development of a fatigue crock. Such a crock will Irsually progress rapidly and lead to an early fatigue failure. The use of weld material to fill damaged areas is This will result in substitution never permissible. of low-strength cast material for the original high´•strength forged aluminum. I,PROPELLER RECOIYD1TtONING: It is recommended.that the blades of a metal propeller should
periodically. Flight-time intervals reconditioning are recommended in note 5 of the repair specifications. More frequent reconditioning is advisable when minor repairs, and accumulated scratches and nicks, as numerous, The reconditioning operation includes removal of the anodize coating from the entire surface of the propella by 20% caustic soda etch, followed by 20CYo nitric acid rinse ad inspection for cracks,
B.POST REPAIR INSPECTION:
Repaired blades visually inspected, using a magnifying
mtstbe
glass
of a) least
three-power, to
ensure
bottom of the natch has been removed.
incipisnt notch, a
inspection
act
employed.
should be
U~balance
for specifications. on a
If
crack is suspected at the root of the local etch a dye-penetrant method of
9. BALANCE:
once
that the
The maximum allowable Moment of each propeller is shown by the repair
This isthe maximum static unbal-
which is allowed when the propeller is placed leveled propeller balancing stand with hardened
ground cylindricol rails, using a hardened ad ground steel mondrd of diom~ter equal to the
and
diameter of a standard mounting flange pilot stub inserted through dw propeller pilot bore. The room in which
propeller
balance
free from air currents~
isinspected
should be
With this
type of equipment, a balanced propeller will remain in any position with no tendency to rotate. Horizontal balance may be corrected by removal of small amount~ of metal from the beavy blade at
locations where chard and thickness exceed the dimensions of the light Made. Vertical balam, may be corrected by removal of metal from the heavy side of the hub.
10. REFINISHING: Repaired propellers should be
prepared
for
pointingby chromic-acid
[MIL-A-862581
or
ALODINE chemicalconversion
coating(MIL-C-5541). U.S. PAINT CO. ALUMIin GF~IP or equivalent products may’ be used manufacturer’s instructions.
be reconditioned
accordance with the
between
color pattern is recommended: blade The rear(Thrust) face ofeoch should be finished dull block to reduce glare into
and repair of all damage to the blade surface. Metal removal during blade reconditioning should be at least 0.004 inch (O.Olan. over
ical
per
surface
the entire Mode. or
mechanical,
removed.
Tn any case, whether chemall traces of damage must be
Total removal of
damage can only be dye-penetront inspection.
by etching a a propeller has been reworked to minimum chord, thickness, and diameter but does not clean upin the lost inch of leeding edge adjacent to the tip, it is permissible to round the tip as shown by Figure 3. assured
When
The
the
following
cockpit, the tip.
from about
5 inchet(na) radius
The remainder of the propeller should painted gray, except for two 2-inch wide tipstripes added on the camber(front) face of each to
be
blade. A decal
showing propeller model, Type
Certificate
and attaching bolt wrench torque should be applied near the trailing edge on the front face with the inner edge at 1
6a
inches
(1’6 cm) blade radius.
90
sO
Iclhch--
Linch--tl
(2.54 cm.) Measure Bend at Points of Tangency on each side of
taken at One Inch
Center of Bend
ANGLE
OF BEND
C
ON0,’ THICKNESS OF BLADE
FIGURE 1 MEASUREMENT OF BEND(DEGREES PER 2 lNCHES BLADE LENGTH) Adapted
from
Fiq 12.6, A.C.43.13-1A
,8
A o
o
o
o
AFTER REPAIR
BEFORE REPAIR
1 inch
1~1 Typical
inch R. Min.
i~ inch Max.
110 Dent
or
Depth
inch
Illustration A in a Blade Face
Gouge
Maintain
original radius
3
R. B inch
I
Do not destroy max. of section If possible
Minimum
inch Max.
Nick
or
Depth
Illustration B Cut Into Blade Leading Edge
inch R. Min.
1 inch
Typical Max.
Illustration
Longitudinal
Note: I inch
2.54
Depth
C Cut into Blade Face
cm.
FtGURE 2 APPROVED TECHNfQUES FOR REPAIR OF BLADE DAMAGE Adapted from FIO. 12.2,12.3, A.C. 43.13-14
11 7 3 3
LEADING EDGE OF REPAIRED BLADE
~1
1 inch(2.54 cm.) MAXIMUM RADIUS
i
1
.j
;j -j
Y
yir
j FIGURE 3
ALLOWABLE TIP MODlFICATION PROPELLER AT MIN~MUM CHORD, THICKNESS, AND DfAMETER (Does
8
not
opply
to Sensenlch
74C, 784
~erle,
propsller~)
Metal Propsllets, BLADE ANGLE TEMPLATES repairing fixed-pitch metal propellers, the angles must be chedted to assure conformance The purto the specifications given by this manual. of blade into is to bringing conformity angles pose balance the thrust forces produced by the two blades. Aerodynamic balance of a propeller is just as important to smoothness of operation os is propeller mass balance. Those propeller models which incorporate the Rose airfoil, with a convex surface on the thrust When
blade
BLADE ANGLE TEMPLATES sets for the folloning propellsr~:
are
face, require to
accurately
the
use
measure
of BLADE ANGLE TEMPLATES blade angles. These templates
tavoilable from the factory)
Figure 4. Propeller performance
are
used os’ shown
will be altered if the thrust
angle
modern propeller is ground flat to facilitate measurement. Repairs should be made to con-
form
as
face of
a
nearly
as
possible to the original airfoil
shape.
available
69C Sefies.........See page 10 72C Series.......See page 14
11_1 1
74DM Series......See page 22 74DR 74DM 74DC
Series:......See page 26
P~ 76E Series....... See page 34 Note: Model series 74C, and 76A do not use of blade angle templates.
by
require
FIGURE 4
REPAIR 69C SERIES PROPELLERS
-3
Weight Pounds(lO.S
24.0
Maximum Out-of-Balance Moment 0.048 Pound-Inches(55 Cram-Centimeters]
Kilograms)
69CK attaching kit adds approximately 0.15 pounds to installed
(Inches)
BLADE RADIUS
6.90
(cm.)lT,53
10.35 26.29
15.53
20,70
39.43
52.58
weight.
25.88 65,’72
31,05 t8,BT
34.50 87.63
MlNIMUM BLADE DIMENSIONS
(inchee) 4.56 (cm.) 11.58
Chard
Thickneee
(inchee) (cm.)
1.35 3.43
4.79
4.89
4.69
4.15
3. 17
2. 10
12. 17
12.42
11.91
10.54
8.05
5.33
0.97 2.47
0.68 1.73
0.50 1.27
0.31 0.94
0.24 0.61
0.14 0.36
PITCH (inchee)
BLADE. ANGLES(
Degrees)
48
31.85
25.25
20.40
16.55
13.70
12.20
49
31.85
25.55
20.70
16,85
14.00
12.50
50
31.85
25.85
21.00
17.15
14.30
12.80
51.
31.85
26.15
21.30
11.45
14.60
13.10
52
31.85
26.45
21.60
17. 75
14.90
13.40
53
.3 1.85
26.75
21.90
18.05
15.20
13.70
54
31.85
27.05
22.20
18.35
15,50
14.00
55
31.85
27.35
22.50
18.65
15.80
14.30
56
31.85
27.65
22.80
18.95
16. 10
14.60
NOTES:
(1) Minimum thickness repair dimensions should be approached uniformly over the entire blade length. (2) 8lode Angles tolerance is t0.ldegee. This will permit 0.2 degree maximum variation between blades.
Templates
are
required for blade angle
(3) Tip elevation, measured from the plane of the
See page 9. hub face to the blade tip of the center of
measurement. rear
inches equols S.OB(~c0.08) centimetets, within track each ´•0.063 inch [O. 16 cm.), measured at corresponding blade shall other Blades (4) stations from 6.90 inches radius (17. 53 cm. radius) to tip. the
chord,
shell be
(5) Recommended time between reconditioning: 1000 hours
10
ORIGINAL As Received
ORIGINAL
By
As Received
ATP
By
ATP I
ul
BLADE- Of i
´•:I
:;i
r
6.00:~1-
:i
´•.:1
i i
14X
3-C~N: FIMEiERS´•~-I:-’-- --I-~-j
;i
rf"-----’-i-)i t -I-i-
I.i 1
I
i
´•I
ii
I
i
:-_
i::-I: i
t~il
’ilii~il
i1
´•-q-~nns----´•--; i-i-iC__L~.
,I-:U~:li;
:I
i--i
i
i
i-i i:
ii
1
1~1
f~i´•j´•il’
i.j
1~
1
r
-ii:
ii_i:
i
.i.i ii
I
ji!
ri_
i ii-;-;i-!-.´•t:I::X::l -::::-:i i~_ilCtT,1 ji
-’;7:-.1´•7
i’-i
!iji
i-;-i
´•´•!ii:I (-i-:i-I
-1:
i
i
I:
-~i-´•
c ~1..i
i
i
-3~iCM
R
i-iH-ir
I
;i?’" i
i-i.iS
:I:
It1ii: i:
i
iIi
i-i´•´•i´•-i i
r
:i-
i:
:j
i-i-i-i
i..
ii i:
!j ii !i!tf’´•fi
´•i i-´•
i
.i"; i
i´•,
ii,
i-f,t-iici-ii-t;ii i
1Yt~
iit-;--
I:l-i i:
i´•
:i
1
j--
::i:i
_i; ii-i-;
ij
L.
i: --i
I/
i:
.L ´•´•~;;i
i;:
.!iL
j´•´•-i
1.-: t--i:.
j
,i:
I
i
i..;
i
1: i
.1
ii ~Y i~i i;
;i; i
i´•i
i
;ii _iLi
1
..ii.i
i;
i
:,A
iiiiiv´•
i
TT-
1
-´•-i
---i-´•
I
jfi
~li
iiS;´•L’
i
i
F"
ti’Fi i-r:d
-"U~;
i
t"-;
i
,;sJi
d?~
i
;ii
i´•i
Nt i-
i
:li:ii ii’::I::
i´•
.´•I"’:-
t
ii´•’
ii
111;
:~-i-j
t
I
1-’i
:al"!ci::i´•. "-i-´•i
jii;
1
liitlr ii
ii
i-;
j-ll
Ir~
i i
:i
ii ;i iti-
i
,,,_,
i´•"i´•
t-i:rii
i -;:iii.
i
ii-i
,r
i
~lf:0;51
"i
y:l
ili_i
~iiL
i
t~ i;li
;i-+i-;
I-?
d:r~f
´•:--.-t-+pn1.L1
i,,
-rr
i-i -I:.´•-
;c!
I Aircraft Technical Publishers
HFi
-f:
t:
c
i
:i.i i;-
_T
I!
:-I~-I
iii
ii---
-A’L~nl
LLi;:
r´•
i 1II
I;
-~--:r;:il. i_
’il-i-1
Ii
I
i Aircraft Technical Publishers
i´•
i
i
i
I
I
I~
;~i;
I Aircraft Technical Publishers
ORIGINAL As Received
By
ATP
´•_L.._.-...~, 1Li:.-~. :‘.\1:1-.-:-´•´•-- I:~I^.--II-´•:´•lri -:--:´•´•i ´•´•YAXTM13~ r
cn--
3
Qd
-1J´•~.
_i^~____L.
~.i :.i]:::.]´• I:-~:.1
B~NO: FOBI COlia’ 69CISERIES PROPEUERS
UL: 01-´•
oP;1
1 :´•´•":_
’.:1 __..__-11__
´•16~-
´•rt~
Wi -----rz-~
~i ~r-
~´•Bc---´•--´• ´•r--_--
W;
oc._.~i
.8F:--li---
U): IJ´•PC:
6;
c3
Wd~ 0L-
w´•m.:
qr
AsReceived Bli 2~
21
r´•;----/-’-_´•-´•´•-
Z
i
’S
1E-
1L---.---e
-----I-----.--´•
------------´•-----!Q:
I_.-.._
4s
r
z-
t
i
B o
Aircraft Technical Publishers
Aircraft Technical Publishers
REPAlR SPECIFICATIONS 69C SER1ES PROPELLERS
"NOTE: These specifications applynto 69C Series propellsrs to pitch dssignotion (example: 69CK-0-50L#). 24.0
0.048 Pound-inches
69CK attaching kit adds approximately 0.75 KSr2 spacer and 69CKS12 attaching kit adds
(inches) 6.90 (cm.) 17.53
M1N1MUM BLADE D1MENSiONS Chard (inches)
Thickness
´•L´•
(55 Gram-Centimet(3rs)
pound to installed weight. approximately 5.9 pounds to
installed
weight.
10.35
15.53
20.10
25.88
31.05
34.50
26.29
39.43
52.58
65,72
78.87
81.63
4.56
4.79
4.89
4.69
4.15
3. 17
2.10
(cm.) 11.58
12.17
12.42
1 1.91
10.54
8.05
5.33
0.91 2.47
0.68 1.73
0.50 1.21
0.37 0.94
0.24 0.61
0. 14 0.36
(inches) (cm.)
1.35
3.45
added
Maximum Out-of-Balance Moment
Weight Pounds(~O.S Kilograms)
BLADE RADIUS
with suffix
PITCH (inches)
BLADE
ANGLES(Degrees)
48
31.85
25.20
19.75
16.45
13.80
11.45
50
31.85
25.85
20.40
17. 10
14.45
12.10
52
31.85
26.50
21.05
17.75
15.10
12.75
NOTES:
(1) Minimum thickness repair dimensi~ns should be approached uniformly over the entire blade length. (2) Blade Angles tolerance is ~0.1 degree. This will permit 0.2 degree maximum variation between blades. Templates are required for Mode angle measurement. See page 9. (3) Tip elevation, measured from the plane of the rear hub face to the Made tip at the center of the chord; shall be 2.00(~ 0.031) inches equals 5.08(t0.08) centimeters. (4) Blades shall track each other within 0.063 inch (0.16 cm.), measured at corresponding blade stations from 6.90 inches rodius(17.53 cm. radius) to tip. (5) Recommended time between reconditioning: 1000 hours.
13
REPAlR t2C SERrES PROPELLERS Weight 24.8 Poundstil.2
Maximum Out-at-Balance Moment 0.050 Pound-inches (57 Gram-Centimeters)
I(ifograms)
72CK attaching kit addS approximately 0.75 pounds to installed weight. KS8 spacer and 72CKSB attaching kit adds approximately 4.3 pounds to installed weight. KS12 spacer and 72CKS12 attaching kit adds approximately 5.9 pounds to installed weight.
(inches)
BLADE RAD1US
1.20
10.80
16. 20
21.60
27.00
32.40
36.00
[om.) 18.29
21,43
41.15
54.86
68.58
82,30
9).44
MINIMUM BLADE DIMENSIONS
(inches) 4.60 (em.) 11.68
Chard
Thickness
(tnches) (cm.
4.83
4.93
4.72
4.18
3. 18
2. 11
12.27
12.52
11.99
10.62
8.08
5.36
1~.353
0.969
0.677
0.502
0.368
0.243
O. 145
3.452
2.462
1.720
1.275
0.935
0.617
0.368
PITCH( inches)
BLADE
ANGLES(Degrees)
48
31.55
24.35
19.60
15.80
12.95
11.50
49
31.55
24.65
19.90
16.10
13.25
11.80
50
31.55
24.95
20.20
16.40
13.55
12, 10;´•
51
31.55
25.30
20.55
16.75
13.90
12.45
52
31.55
25.60
20.85
17.05
14.20
12.75
53
31.55
25.90
21.15
17.35
14.50
13.05
54
31.55
26.25
21.50
17.70
14.85
13.40
55
31.55
26.50
21.75
17.95
15.10
13.65
56
31.55
26.80
22.05
18.25
15.40
13.95
NOTES: (1) Minimum thickness repair dimensions should be approached uniformly- over the entire blade length. (2) Blade Angles tolerance is ~0.1 degree. This will permit 0.2 degree maximum variation between blades. Templates are required for blade angle measurement. See page 9 (3) Tip elevation, measured from the plane of the rear hub face to the blade tip at the the chord, shall be 2.03(~0.031) inches equals 5.16(~0.08) centimeters.
(4) Blades shall track each other within 0.063 inch (0. 16 cm.), measured stations from 7.20 inches radius (18.29 cm. radius) to tip. (5) Recommended time between reconditioning: 1000 hours.
19
at
center of
corresponding blade
ORIGINAL i Received By AfP
i
CSLADr
I:ere
10 p 10
iI
j,
I
:::::-i
i
i:
i:
i
!e
:li
’i.j
i’;t
B,OO 5f(CN0S i
1
i.
~.i
.i
"´•i;
ii
14.00 CM
i.:i:´•i(-~
----i
´•li
5.00
´•i-
I
12.00-
7,M,’El!,"r~((UM;I=H0)7P
i
i ii´•l ;-.I Ili::---(i--:~-?j-´•
i
1.60 INCHES C‘
´•,´•:i:´•,
mljl~
4.00´•
10.00-
I´•
i´•,? ;´•´•ii
i
ii
II
´•i::´•i:i_
i i!
t,c;
1
-´•j:eM !(i..: i.
ii:;1i.i.l 1.:
i.
i
i´•´•
1~20
Ln :r.
:.UIYI
8,00-
I
:_r::.~Tv::-:
r 1
ii’l
I:i L~3:
1
3.00
:i
I
1´•?
T:
-3~0
,..:.i.
i; i
ii C
.e-i
Cs
11.1!1
:i
ii
1
i
j
r
:’I
:?-_--B
u> :´•u, ´•´•-t-;:tr..i
:-L
i
i
6.OD-
f
WNIMUM THfC)SNESS
O
I
i´•-iy
i
´•I"i
i
L;:~i
:´•:;.i-::j C-0~´•8
-?L´•~V, U
:1
2.00
u
i:: i
1;.;I.Tii..:i.
I i 1 i-´•
:11
-i.
-O.s-j= -´•1~;5: )L
i´•
:TI"1’´•
(I.oQ0,40 i: I?
:ij
~,015
I
-ia:
~..1.
.;i.
tS~
:´•I
35~r´•
i;7-:.
.,i-
I
’3
:-I
:i:
2.00-
´•i:L:!"T i
3 ~ri
´•.,,ti
::I
12:
i_l_-.__l_
’.t
~II-
t‘;
-´•i)lh´• ;´•-´•rr´•
"?´•i’
r:i i
io
,´•,;´•)´•i´•´•´•-i -i.
.1.
T-.
i
i i
‘i:-, r ;--It:i,--.-´•-
8
1’
nnULV3(I
i-i
i!
i I‘
36 ~NCHES
i-:
´•i-
Ii´•
i’
r
i:i,,7,,,i
,´•´•I
i,j
^II,
i:!~´•´•´•i´•-e:f30:
i..:.iil
ORIGINAL
I’
I
I
I
I
i
As Received
i.
ATP
:i MAXIMUM ALLOWABLE BEND FQf!: lec SERSES PROPEL;C;f~RS‘ri
E;
.:l=L
20
i
20
I
iT: ~I´•´•
m
;-i
´•-I
c>I~
;._
18
´•1----:-.
~:ff
´•ii;.
il~-i-ti-
:---i---:::
i
.-.i_.._,
_.I-ii~iiil:
.....e
1
i
^T
i
iii.
.iili´•i:~1
i
´•.i
I~ I
´•-~-´•--r-
´•i´•L-
i
i
i
~I
-ti
i
i
i
iiii-i
:i.i~fi
i
i i~
i.-i
´•!´•li-; i-i
:-ri----
i i:
’i--t
1
..~a
iL_i
li:iT.
-r´•´•--
:-t# ’;i
i
I i ,1
i.ii.i
i-~-j´•- i-: ii
´•-i-i~ID! ´•i;´•l-1-ij
-:i_iili
-i
i
f-;;k
i. I´•i;it
ii:;i
I;.
:i
j
1
i
i
i
r:I:
li:ilr-r:
:m: Li i
i-
i!rjii´•’
...i
;ii
’’I
1.
i-
i´•,-i~
~--´•s-li------
i
I:
j!
I
~i’t
-i
i:
.1.
itL--1T:
!ii i
1.
i-i
i?
ilii
--i-; t~-i
i
i ii i!
i
:´•ri v;
I -f~-t-:
?i-
i--Ci-!-i-
i
i=Zi!.L-~i
i-n-!
d
´•r
1-;
I
i´•
H
~I
t; c-;
i’ :.i
.I..i I
i.!: ii:´•
:i
i--.~;-
r~r´•-,e
´•-i--
i!; :i-i i
!’1
I
i i
.?.::f
i
~--i i
i i
I-´• i
:ii
ii
I:
i
---´•1
i
i
´•i;
t’’
,i.-
i.
riii.:l-
i
(b
i.
i
L-i i i
i
iili
;1
ii´•
i;if
i
i’ii´•i
--:-:.i-; i
Y
:t
~?-´•t"-
’’T
:Li ii
;I-r
i IIt-i-l
,iii;
~--c-i
-i
ii" -:tt--i
i-i: :-I
I:
;:-i-.´•--
ii
~-T
I
ri´•il
i;
i:i
r-l
it
I
i--i
i
i--:-i-i---´•i: ii-i-i
.i
i--
::ii
i
I´•
ii.’i
-ii
-i
ci-i i
´•t
;i´•i´•i
’ii~i i i
1 j
:i
;i
:J? -i-:
r
I -I-i
´•;1.-;
;I-i-’-i-?
i) :-iii :i!
Y.i
iiji~
tii´•l;
~i-´•i-iF.
-i----
i;
IW-ii:i
´•r .~.I-
i;
I;
1:;’
i I;:
iiLt:
it´•
;i
L_T
:ir’
ir-’I-i-P-
-~i
ii,
ijil
h
1 iti
1
i:-i:r:
i
!i--i--t:
I!-
i
t
isi
t
i
.i
;i
i
Lb-:-´•
;:I
itii;
~t-tc;
Is
j-:I~ii.i::i
11i´•
i-I aR1
~R
is
4>
in
it
No
not
twisting than
more
several
8
rules
higher
much
a
the
at
given
ertpense
here
than
at
one
be
inches
to~change
steps
to
reduce a
locations
is
evidence
Previoud
appearance
blade
radius
the
For
pitch set
at
be
may to
a
SEI~SENICH
a
however
than
to
64
twisted
to
58
higher
blade
a
between
pitch,
further
no
in
aluminum
an
difference
inches
76EMB-0-63) been
of
example,
66
shown
range
re-pitching
to
the
stations.
pitch
the
of
pitch.
section
which
thick.
should Laroe
Robert
not
be
twists
between
SEI\1SENI~H
Propeller
for
of
accomplished
pitch
time.
history
hub
the
wavy
minus
set
previously
shall
1.100
in
overstampina).
pitch. be
may
(originally been
propeller’s
Also,
inches,
median
60)
permissable
had
l’wists
the
pitch
propeller
oreater
location
be
then
series.
effceed
a
stamping
remainwithin
must
propeller not
’/6EM3-0-63(median it
the
the
airplane’s
to
climb
will
than
slower
the
when
of
propeller
or
e~ample, 6
limits
Re-pitch
the
if
or
then
necessary
verifiable
a
available,
Propeller
478
allowable
take-off
previous re-pitching(possibly shown by re-pitching may also be indicated by a trailing edge between the 30# and 4511
SCRM
about
faster
purchased, for
PROPELLERS
only
changed(for
compromise
ME’rAL
propellers.
beneficial
significantly
operation
re-pitch
concern
aluminum
originally
was
of
FIXED-PITCH
much
SCRn478
198~
followed.
be
usually
may
requiring
cruise).
should
be
airplane
an
it
base
principal ct
on
which
for
one
SENSENICH
of
propeller
installed
OF
indicate
inouiries
pitch-change
~86-1 MANUAL
September
RE-PITCH
FOR
MEMO
REPAlR
30~
in
and
made a
at
blade
45K
the
should
blade
radius
same
be
made
radius
CORPOHA’I’ION
E.
Bristbl
Engineering
Manager
A1;3
AIRCRAFT PRIIPEI.I.ERS ANO LAMINATED woon PROnll~TS FnR HoMF ANn INOIISTRIAL I~SE
3rnm
3~V
SENSENICH PROPELLER CO. A Division of t)le
Philadelphia Bourse.
Inc.
EAST AlnPOAr ROAD
I\FIFA CODE 7(7
nlotte
560371(
G~RVfCE
BULLETIN
SENSENICR
DISTRIBUTORS,
AFFECTED SUBJECT:
AIRCRAFT
INSPECTION ALL
COMPLIANCE
1 IM)1-0100
717´•56i0-3725
FAX
TO:
PO BOX 5155
,e
1-800-462-3412
BLADE
PROPELLER
OF
bT
APPROVED
REPAIR
1919
October
GTATIONSI
OVNERS
SENSENICH
DATE:
FAA
I
R--ISA
NO.
FIXED
OR
ANNUAL
100
CORROSION
FOR
AREAS
nETAL
PITCH
PROPELLERS
INSPECTION
HR.
13I9CU59~0N: Corrosion c~ndition
of
the
of
surfaces
blade
propeller
aluminum
protective finish and
varying rates, depending
at
occurs
in
prevalent
conditions
atmospheric powder on the
on
the
the
on
aircraft
blade surface or, in later stages, as It may appear as a white basing area. The mechanical tiny black specks or cavities e´•tending inward from the surface of the metal. effect of corrosion damage is similar to that of sharp-bottom impact damage, adversely Particular concern is that older praplcll´•r~, still affecting propeller airworthines~. finished with anodixe and clear wear-coat finish, do not have the corrosion retarding Howcv~r, flaked or blistered capability of modern hLODlhl9 treatment and polyurethane tfnlsh. also may
paint
ACTLON:
REQUIRED A)
Carefully
soretch
less
be
must
all
remove
aluminum
the
corrosion.
indicate e´•istlng
or
repaired I)
Sand
removed.
2)
Polish
the
area
the
310
with
area
(an
the
area
´•tra
of
a
folded
bill)
dollar
instruction~:
wet-or-dry abrasive paper until all evidence of corrosion
120
with
to
that
blader
in
is
propeller surface, taking care not for corrosion. Propeller blades
from
square -inches of total corrosion accordance with the following
d
than
blistered
paint inspect propeller
flaked
surface.
grit
finer)
tar
to
all scratches.
remove
thoroughly, apply an approved penetrant! and inspect with a iOX II e´•tremely important that all corrosion be completely removed. cavfties reappear during penetrant inspection, the repair operation must be repeated. Clean
3)
the
area
NOTE:
glass.
It
4)
Remove
J)
Apply ALODINE
from
penetrant
instructions aluminum
is
or
(proper
surface
affected
area
equivalent treatment ALODINE
after
the
treatment
AtODlNE
If
C>
er
7>
Spray
blades
The
is
InnEDI~TE nir~s
area
show
FAA
and
Note and
with
manufacturer’s
smooth~´•mbcr/Slald
been that
rinsed
some
primers In
result
may
tint
on
the
off). are
intended
far
of
adhesion
of
loss
1000
with
to
the
corrosion.
protect against
better
PROVIDED
Hours,
The
must
be
flight-ttmo between reconditloning of SENSENICH fiied-pltch
ATTENTION.
cuts.
matching paint
greater than d square inches of corrosion, the propeller Propeller Repair Station for reoonditionlng.
recommended
prnpsllers
has
a
coat.
out
approved
an
leave
solution
Apply a primer over the repaired area. pratrea?ed aluminum, while others are not
to
accordance
in
will
d)
8)
n.E.K.
with
this
SENSENICH
ITHAS
removes
SERVICE
NOT
fatigued MEnO
RECEIVED
surface
dated
metal
April 8,
PRIOR and
1970
1´•
the
DAnACE
returned
metal
REOUIRINC
accumulation
superseded by
of
small
this
rccommendat ion.
Refer
to
the
infnrmation.
A14
SENSENICH
518338
PROPELLER
REPAlR
nANUAL
(80811
478)
and
AC
20-378
for
further
SENSENICH PROPELLER CO. A
Divbbn d ne Phifede(phla 9ouse, Inc.
AREA COM 117
EAST A)RPOFIT 9099
~L
PHONE
500,7711
btlW
1-800-461L-5412
P.O. 80)( S100
I
UNCA87EA. PI llff)lQ100
9ER V-I I-
Ita E Pt
Pa a
TO:
PAA
C E~
APPROVED
SVBJECT:
BVLkETIN
A B p a o v
BROPeLtER
AIRCRAFT
nODeL
~ODEL
dPCE
with
An
´•I´•:´•:i
series been
ilaproved
blade-angle
propellers
installed
revised inches.
ienoing
shows
that,
airplanes)
to
lift-off
increased the 10
(Far
less
those
interested
radius
In
design
propeller
a
fhls
repair
manual
indicated
by
SeRM
the
idenei88caQaon
on
identification
deeap
propellers
obtained
incbrporDta~lhe "t" of
suglia the
reYis´•d
gr~palIQr
is
inrorp~rating
69
"E"
be
propeller and
"0"
the
of
Pt
[wbPh
steel
All
pen).
is
and Po
of
natural
and
Be
and
inches
pitch the
and
ha’iia
a~
An
incorporates
"69CK-D-99t"’. 50
on
gsoondl4BboR´•6
Pd´•ntBft~ePBon.
the
of
will
distribution
which
the
propeller
ePamp) new
999
by of
SENSENZCH
shall
the
facility
propeller
Bi´•~sP´•r revision
and
poo´•tbl´•to
pro9´•tl´•r
1993,
after
BEIUSENICH
a
at
the
at
clliB
incorporated
any
page
on
August
i
distribution
inches
eh´•
aakes
may
4B´•ad´•-e~ngBa the pitch of
a
takeoff
when
after
designation
blad´•-ang9e
of
incorporation
ink
the
cruise
knot
propeller
83
Pace
(´•wlth
Iroa
which
loverhauled).
sufff´•
a
hub
revised
included
~bdal.
of
addition
be
nap
upon
(´•hown
dated
590),
time
energy.)
stations
distribution
35
an
knowledge
oowltnp
CEBZJN~
blade-angle
pitch
blade-angles
repair
airplane
standard
bmprave´•
less
waste
In
reconditioned
is
series
blade-angle
the
accurate
more
aircraft
to
revision
propeller
approved 6909
the
the
revised
a
in
oould
station
of
front
"why"
in
OCllfl~l
flow
with
data
on
distribution,
the
showed
tested
was
Feet
2
without
rate-of-orine
159; and
of
oliaah
standard
1´•
blede-angle
about
deorease
a
blade
Plot
the
of
and
has
the
reduction
a
takeoff
BPCK
aircraft,
incoPpor´•tang
pitch
about
by
required
was
and 3/4
pitch
propeller
than
(32
S9N9ENICM
for
series
p´•rgoP1´•no´•.
cruise
revised
reduced
be
factor
a
prototypp rpm
the
and
may
by
"50"
a
PRit
fmgcoslng
of
reduot ion
a
with
150
possible
makes
pitch,
propeller
gSRrg~
850
CE99NA
found
been
has
distribution
angle in
@aper
150
it
developed.
DISTRIBUT~OW
sEN8ENICH
distribution, on
P e
BERIIES
CPSSNA
AFFECTED:
11
STATIOHS
BLADE-ANGLE
PROPEttLR
AFFECTED:
a hy C aU S a
i
REPAfR
BROPELLER
In9ROVED
B\IO
D
the
"Phis
pitch,
blade-angle
ddaeetbuPlan
a
02
BE_1
AL
DESIGNED F-08 MAXIMUM
$EW~BRMANCP
o
SENSENICH PROPELLER 14 CITATION LANE
LITITZ,
PA
MANU FACTURING
17543
INTEPNET
(717) 569-0435 (717) 560-3725 http://www.sensenich.com
E-MAIL
denisen@sensenich. com
INS TAL LAT: ION
LIST
PHONE
FAX
NO.
198
COMPANY
SENSENICH FIXED-PITCH ALUMINUM PROPELLERS INSTALLATION LIST One otherwise
attaching kit is furnished with each propeller. An attaching kit for the hanged shaft specified. Tapered shaft installation must be speciRed. When ordering for Lycoming
wilt be 0-145
supplied
for all installations unless
installation, specify 74CKL attaching Dlk
AIRCRAFT
ENGINE
STANDARD
’STATICRPM
kit. ’MiN.DIA
CLIMB
Aaro Commander 100
Lycwning Q320/
74DM~060
74 Inches
Aeronca IIAC
Continental AdS 165
74CK-048
74 inches
2100-2250
72.5 inches
119
Aeronca ffBC
Continental C-B5 185
74CK-2-46
72 inches
21602380
70 inches
1/9
Aeronce 11CC
Continental C-8I 1 85
74CK-2-46
72 inches
23002485
70 inches
1/9
Aeronca 15AC
Continental C146D
74DR-~52
74 inches
22402490
72 inches
Aeronca 65TAC. L3. 058. YO58
Continental A-65 165
74CK-0-46
74 inches
20502250
72 inches
Aeronce 65TL. 65LA. 65L8. 65TAL
Lycoming 0145´•8
74Cl(-2-36
72 Inches
2250-2550
68 inches
Aemnca Sf1AC
ContinentalA-65 165
74CK040
74 inches
20702170
72.5 Inches
1/9
150 HP
740R-054
74CK-0-44
119 2
Aeronca S1fBC
ConlinentelCgSIBS
74CK-2-40
72 inches
22802380
70 Inches
1/9
Aeronca S1ICC
Continental C-85 1 85
74CK-2-40
72 inches
23002465
70 inches
1/9
Aeronca S1SAC
Cont~enta) C-115
740R048
74 inches
23802590
72 Inches
Aeronce S65TC. SO-58D
ConUnentalA-65 1SS
74CK040
74 inches
20502250
72 Inches
American General AA5
Lycoming 0-360/188
7SEMBS1~0´•63
Avions Piena Robin DR400 1118
Lycomlng 0-235~LZC
Avions Pierre Robin DR400 I 120
Lycomlng 0-235L2A
Avlons Plerre Robin DR400/1408
Lycoming O-320D2A H40
7iDM6SS´•2-64
Avions Pierre Robin DR4M~IM)
Lycomlng 0-32002A 1160
740M855-2-64
Avions Plane Robin DR400/180
Lycomlng 0-360´•A3A/180
76881885-061
Avions Pierre Robin DR400/180R
Lycomlng C-360A3O
H80
76EMBS5058
Avlons Plane Robin R 2160
Lycoming O-320-DZA
AvMns PiMe Robin R 30891 180
Lycomlng 0-360A3A IfBO
Beagle
8121
Lycomlng
0-320 H50
74081685-060
74 inches
72 inches
Beagle
8121
74DMBS~082
74 Lnehas
72 Inches
Pup 150 Pup (M)
78EM8S10-a65
76lnches
T8Lnches
72CKS6-0-56
72 inches
70 inches
72CKS60-56.
72 Inches
70 inches
740146859-66
76EMBSS058
72 Inches
72 Inches
72 Inches
72 Inches
76 Inches
78 inches
76 inches
78 inches
74DM6Sf~2-64
74 Inches
72 inches
76814815-064
78 inches
Is inches
Lycomlng
0-320 1160
Beach Model 19A. M19A
Lycomlng
0-320 1150
74DMB058
8eech Model 23
Lycomlng 0-320 If 60
740MBOBO
72CKS12052
Beach Model 77 SKIPPER’
Lycoming
8eech Model A-23-19
cvcomcne o-3za nso
74DM6O-58
Baach Model 819 SPORT
LycMnhg
0320 H50
74DMBS5-0-54
Beech Model 823
Q235 If 15
76EMBS100gl
76EM8SS~O-6)
74DM6058
74DM6SSO-58
1/9
14 Inches
23002400
74 Inches
23002400
74 inches
72 Inches
22152375
70 Inches
74\nchas
23002488
74 inches
74 inches
2300-2550
74 inches
3
76. Inches
2250-2350
78 Inches
8
78inchas
22502350
76 inches
6
74 Inches
23002400
74 Inches
74 inches
Lycoming
0360 1180
76EMBSbOM)
Beach Model C23 SUNDOWNER’
Lycomlng
0-360 HBO
76EMBSS-060
Beach Models A23. A23A
Continental 1O-346A
74DCQ60
Bellanca 7AC
Continental A65
74CK046
74CKM4
74 Inches
1960-2550
72 Inches
119
Bellanca T8CM
Continental C-BS
74CK-2~6
74CK-2-44
IZ inches
2200-2450
70ind\es
f14
BeLlanca’lCCM
ConUnental C-g0
78AK-2-46
76AK-2~4
74 inches
2150-2410
72.5 inches
1/9
8ellanca 7DC
Conlinental CgS
74CK-2-44
74CK-2-42
72inches
2300-2465
70 inches
119
BeUanca 7EC. 7FC. 7JC
Continental C-g0
76AK-2-46
76AK-2-44
74 inches
21502350
72.5 Inches
119
Bellanca 7EC. 7FC. 7JC. 7CCM
Conlinental C-g0
78AK-2-4Z
74 inches
72.5 inches
1/9
Bellanca’lECA
Lycoming 0-235L2C H15
72CKSS~SZ
72LKhes
2215´•2530
70 Inches
Bellanca IGC
LycMnlng 0-29002 1135
740M6-057
740M8-050
74 inches
23602566
72.5 inches
Betlanca’lGCA.’IGCB
Lytormng
0-320 H50
740M60-57
740M8052
74 inches
23802618
72.5 inches
Bellanca‘lGCAA. ’IGCBC
Lycoming
0-320 1150
74DM6SS1-56
74DM8SB1-52
73inches
23002648
72 inches
Bellanca TGCBA
Lycoming 0-320 1150
74DM6~52
74 Inches
23602616
72.5 Inches
Bellanca 7HC
Lycomlng 0-29002 1135
14DMBOST
74 inches
23002500
72.5 inches
8ellanca 7KC
LycMning
Bellanca 7KCnB
Lycoming (AE)IO-320 1150
74DM6SB1-56
BeUenea sKCnB
LycMning AEIO-320
gellanca S’IAC
Continental A65
Ballanca S7CCM
0-320 1150
740C-056
74DM6)-57
76AK-2-48
76AK-2-48
4
74 Inches
23002610
72.5 inches
73 Inches
2300-2540
72 Lnchas
74DM6SBO58
74 Inches
2200-2450
72 Inches
14CKQ-40
74 inches
19602550
72 inches
119
Continental C-90
76AK-2-42
74 Inches
21502410
72.5 Inches
119
23042400
72.5 Inches
1/9
74DM6S81-52
Bellanca S’IEC
Continental C-90
76AK-2-42
14 Inches
Call A-4
Lycoming 0-29002
740M8~50
74 Inches
Cell A-5. A5T
Lycomlng 0-320 1150
740816;052
74 Inches
HP
AIRCRAFT
ENGINE
STANDARD
CUMB
Cessna 120. (40
Continental C-85
78AK-144
78AK-2-42
74 inches
2190-2290
72.5 inches
Cessna 120S, 140S
Continental Cg5
76AK-2-40
74 inches
2190-2290
72.5 inches
Cessna 150(ALL)1150
Lycoming
74DM6S50´•58
74 inches
Cessna 150
S.P.(ALL)I
Cessna 150,
thru
150
150K
Cessna (50L, A1SOL, 150M, A150M
0-320 150
CRU)SE 119 (19
7/D
Lycommg 0-320 150
74DM6S5~
ConlinenW 0-200
69CK-0-50L
69CK048L
69CK052L
69 inches
2320~2410
67.5 inches
5
Continental 0-200
69CKS12-050L
69CKS12-~8L
69CKS12-0-SZL
69lnches
23202470
67.5 inches
7Xj TIE
74 Inches
7/D
Cessna 152
(110)1 STC Alrmods NW
Lycoming 0-235L2CI
72CKS60-4(
72CKS6)-52
72CKSB-058
12inches
2150´•2350
70 inches
Cessna 152
(125)1 STC Ainmods
Lycoming 0-23CLZCI 125
HP
72CKS&Q54
72CKSB052
72CKSBO-56
12 Inches
21502350
70 inches
7~
Lycominp 0-235LZCI 110
HP
72CKSg~54
72CKS6056
72 Inches
2100-2275
70 inches
7/G
76 inches
710
22202320
12 Inches
NW
Cessna 152 1 STC Sensenlch
110 HP
Cessna 1701180 HP
Lycoming 0-36) 1180 HP
76EM8S5056
76EMBS5054
76EMBS~60
76 inches
Cessna 170 series
Continenlal C145
7409-056
14DRQ54
14DRQ58
74 Inches
Cessna I’lZ 1180 HPI Perm Yen
Lymming a36Y
I8OHP
76EMBSPY-0´•60
~6 Inches
76 inches
7/F
Cessne 1TZ 1180 HPIAnon Conv.
Lycondng 0-360
160 HP
t6EM8S~056
76 Inches
16 inches
71D
CeJsne 112, 172A H80 HP
Lycomfng
76 inches
7/C
Cessne 172, Uuu 172C
ConUnenla10-30~,0
Cessne 172/ 145 HP
0-360 180 HP
768148 Series
76 Inches
74DCO58
14 inches
2300-2420
74 Inches
23002430
72.5 inches
Continental 0-300Jl -B
74DR-0-55
Lycoming 0380
180 HP
76EM8SI4-068
16 Inches
16 inches
Cessne 1721.lhru 172P 1180 HP/ (STCIIUI Plains)
Lycoming QJMY 180 HP
768M8814-068
76 Inches
76 Inches
7/A
Cessna 1721, Vhru M 1150 HP
Lycoming 0-520 1150
HP
74DM7S14-0-58
740M75140056
74DM1S14-0-8)
74inches
2100-2400
72 inches
71G
Csssna 172N, 11291 160 HP
Lycoming
0-520 It8) HP
74DM7S140-58
7~DM7S14Q56
74DM7S14-062
Cessna 175/ 180 HP
Lycoming 0-J601
Cesma 1721,
thru
(72P1180 HP
(STCIAlphin)
74DR953
74DR-0-56
72 inches 71C
741nches
2200-2500
t2 inches
7/G
180 HP
IGEMB Series
18 inches
2100-2250
16 Inches
7/0
0-360 180 HP
Cessna 177/ 189 HP
Lymming
76EM8 Series
76 inches
2100-2250
16 Inches
710
Ercoupe 415C, 415CD, 4150
Continental C-76
76AK-2-48
79 inches
20502125
72.5 inches
119
ConBnenlalC-BB
76AK-2-46
76AK-2-48
74 inches
2175-2250
72.5 Inches
1/9
69CK050L
69 Inches
2320-2470
67 inches
Erawpe 415C, 415CD, 4150, E,
G
Ercwpe 4150
Continental 0-200
89CK952L
69CK-050L
Fleet 80 Canuce
ConUnenlal CB5
78AK-2-42
76AK-2-40
Globe GC-1B
Continental C1252
74DR-1-58
74DR-1-57
73 inches
2000´•2250
Gmb
(1(5HP) Lycomfng 0-328(188 HP) LvcomlnBO-320-O1A(1M)HPJ
72CKS82-SJ
Tn Inches
MAX 2800
70 inches
74DM6S~Za4
72 inches
MAX 2700
72 inches
72 Inches
MAX 2796
72 Inches
72CK956
72CK-052
72 Inches
21252475
70 Inches
76EM8S10983
76EM8S10060
76EM8S(0Q85
76inches
207623~0
76 Inches
7/8
76EM8S10063
76EMBS10-ObO
76EM8S100-6J
7Bhches
20752350
76 Inches
7/H
Kestral KL-1 180 HP
Lycomlng 0-23Y 115 HP Lycoming 03601 180 HP Lycwning 0-360 188 HP Lycwnlng 0-320 160 HP
740M7S14-080
74 Inches
unknown
72 Inches
Msule MX-I-1M)
Lycomlng 0-320 180 HP
74DM7SSOSB
74 Inches
unknown
72 inches
115, 115A
Gmb 1158 Grob 11SC Grumman American AA1C
Gullstream American AA5/ (STCIAlr Mods NW) Gunslream American AA5/
(STC/FletchAir)
Sportplanel
Mauls MX-I-18OA
Sportplane~
Lyccming 0-38d
(ONLY)
74 inches
74DR-1-Sg
74DMTS16264
180 HP
71.5 Inches
18 Inches
unknown
76 Inches
HP
74DMISS056
74 Inches
unknmrm
72 inches
Lycomine
0-360 18OHP
76EM8S5056
76 inches
unknown
76 inches
Montana Coyote I ItiO
Lycoming
0-320 188 HP
74DM60-56
74 hches
unknown
72 inches
0-380 180 HP
Mauke MXT-7-(60 Comer"
Lycaning 0-320180
Mauls MXT-f-1BOA Comer
Montana Coyote 1180
Lycoming
76EMS056
76 inches
unknown
76 inches
One
Design 1160
Ly~wnme 0-320 (180 HP)
74DM( t~82
74 inches
23002400
72 inches
One
I 180
78EM8062
78indws
2350-2450
Parfenavla P648 oscar-B~
Lycwntng 0-380 (180 HP) Lycanh~g 0-360
fBEM6~65
76 inches
Partenevia P668
76 inches
Design
1M~
Lycwnlng 0235-C~8
~6AM62-S1
Piper JJCBd L4, (AG)
Continenlal A-65 185
74CK-0-40
Piper J3C65, L4,
ContinentalAB5/B5
74CK048
oscar
Cub
74 inches
28502258
72.5 inches
119
14 Inches
2050-2250
72.5 inches
119
74 inches
20502250
72.5 inches
lm
78AK-2-38 (AG~
74 inches
19502550
72.5 Inches
119
74CK-2-38
72 inches
22252550
68 inches
2/9
Continental Ab5 1 65
74CK-040
Piper JJC85
Continenta~ C-8y 85
76AK-2-42
Piper
L4C
55 1100
Lycoming
0-145-8
76 inches
76 Inches
74CK-044
Piper JJC65S
Piper JJL65,
119 119
Ly´•camlng 0-235 1100HP
78AMB2-48
74 inches
21502300
72 inches
Piper 35 /C-BO
Continental C-90 1 90
78AK-2-44
74 Inches
2100´•2250
72.5 Inches
Piper J5A
Continental C75 n5
78AK-2-48
74 Inches
2000-2150
72.5 inches
119
Piper J5A IC=I5
Continental C-75 nb
78AK-2-48
T4 Inches
29802158
72.5 inched
119
Piper J5A /C-85
Continental C85/85
78AK-2~4
74 Inches
2170-2430
72 Inches
119
Piper
Lycomlng O-235C 1100 HP
76AMS2-48
74 inches
22502450
72.5 inches
g
Continental A65
74CK046
74 Inches
2050-2550
72.5 Inches
119
PA11I1W HP
PiperPA11.WA
7dCK-0-44
119
AIRCRAFT
Piper PA-11.
PA181 90 HP
ENGINE
STANOARt)
Continental CgO
76AK-2~2
Continental A-65
CLIMB
CRUISE 78AK-2-46
INCHES
LIMITS
74 inches
195(r2450
72.5 inches
74CKb-42
14 inches
2100-2250
72.5 inches
119
Continental C-90
76AK-2~0
74 inches
1650-2450
72.5 Inches
119
Lytoming 0-235C 1100 HP Lycoming 0-235C1 1108 HP
76AM62-48
76AMB244
74 inches
21502425
72.5 Inches
9
Piper PA-19 Super Cruiser~lOB"
16AM6-248
78AM62-48
74 inches
2150-2500
72.5 inches
9
Piper PA-1ZS
Lycomlng 0235C 1(00 HP
16AM6-2-42
74 inches
23252425
72.5 Inches
9
16AM6244
74 inches
2150´•2500
12.5 inches
9
Piper PA-11S Piper PA-11S.
PA-1BSI 90 HP
Piper PA-12 Super CNiser
Piper PA-1ZS
1108
0-235G1 1108 HP
119
Piper PA-14 Family Cruiser 1108"
Lycaming 0-235C1
1108 HP
78AM8-2-d8
76AM62-46
78AMBO-50
74 inches
2400-2500
72.5 inches
9
Piper PAlb Clipper HOB’
Lycomlng 0-235C1
1108 HP
7BAM&2-50
78AM8-Z-48
76AMB~JZ
74 inches
215a2500
71.5 Inches
9
Piper PA-IGS 1)08
Lycomtng Q235C 1
ItDB HP
76AM62-44
14 inches
240~2501)
12.5 Inches
9
Piper PA17/ VagabonG
Conlinenlal A65
72 Inches
1850-2250
70 Inches
9
Piper
PA18 125’
Piper PA-18
L-Z1A~
155~
Piper PA18 Super
Lycomlng 0-290-D2 Cub 150~
Piper PA1B.
PA1B 105’
Piper PA18/
180
Piper PA1BA Super Cub" Piper PA-184
PA1BS 125"
Piper PA-~BA.
PA-1BS 135~
PlperPA-1BA.
PR1BSI 150HP
PlperPAIBS Piper PA-20
Pacer
Piper PA-20. Piper
PA-22 125~
PA-20. PA-22 135~
LYlwnme
Piper PA-ZOS Piper PA-POS
125~
Piper PA-20S. PA-22S 135"
PiperPA22
189" 108 Colt’
74CK-2dB
LycoinnOO1I90-D
74DMB0~50
74DM8-o-52
7qDM6-Q56
78EM8Q54
2100-2475
21002475
72.5 inches
740M6-0-SB
74 Inches
W5~2450
12.5 inches
78AMB2-50
74 inches
2100-2475
72.5 Inches
78EMBO-51
76 inches
16 inches
78AM62-44
74 inches
2100-2475
72.5 Inches
74DM6Q48
74 inches
210~2475
72.5 Inches 72.5 Inches
2(00-2415
74 Inches
2450-2550
72.5 inches
76AM6-248
74 inches
2100-2475
72.5 inches
9
74 inches
2150-2500
71.5 inches
9
74DM6Q50
74 inches
2150-2450
72.5 inches
74DM6055
76AM62-50
76AM6248
76AM62´•52
74 inches
2150-2450
72~i inches
74 inches
2499-3599
72.5 inches
Lycomlng
74DM&052
74 inches
2350-2450
72.5 inches
14 Inches
235~2450
72.5 inches
T4 inches
225a2480
125~rPches
Lycominp
0-290-D2
74DMS0~52
0-3791 1XI HP
140M6-060
740M80-58 74DM8-0-58
Lycwninp
0-320/ 18)HP
74DMM)-60
Lycoming
O-235C18
78AMB248
0-320/ 150 HP
150~
Lycoming
160~
Lyiomme 0-3201
IGAMBTX)
14 inches
22502480
72 Inches
74 inches
220~2450
72.5 Inches
74DM6058
74 Inches
24M2500
72.5 inches
160 HP
74DMBO-58
74 Inches
240~2500
72 Inches
741mhes
24152676
72.5 inches
7dDMg(Z´•58
74 inches
2(502425
72.5 Inches 72 inches
Piper PA25 Pamwe 150~
Lycomlng
O-32W 150 HP
14DMB052
Piper PA-28140 Cherokee"
Lycomlng
0-320/ 150 HP
14DMB~60
Lycomlng
0-320/ 160 HP
740M6-0-58
14DM60´•53
74 inches
23252425
150 HP
740MS0-58
74DMS(F56
74 inches
22752425
72.5 inches
Lycommg
0-320/ 150 HP
740M6~58
740M60-58
74 Inches
22152425
125 inches
Piper PA-2&150 Cherokee C~
Lycomlng
0-320/ 150 HP
14DMBS505B
7dDM6S~056
741mhes
22752375
72.5 inches
Piper PAZB-151
Lycomlng
0-320/ 150 HP
74DMB-058
74 Inches
2275-2375
72 Inches
Piper PA-2&140.9 Cherokee’
Lycomh~g 0-320/
Piper PA2&150
Cherokee 8~
Wanior
Piper PA-2&151 Wanior"l Piper
160"
PA-28-160 Cherokee B"
9
74 inches
78AM62-44
Q29~0
9 7/F
14DM8-~52
’14DM6057
PiperPA1ZS
Cherokee"l 160’
76EM8~52
74inches
74 Inches
o-zscrot
PiperPA-11S
Piper PA-2&~40
140MS0-54
78AM82-48
74DM6052 74DM6-0-54
LWoming Q~235C1
150"
PiperPAl? Piper PA-22
Lycoming 0-310/ 150 HP LycMnlng (T235C1 Lycaming 0-3WI 180 HP Lycaming 0-235-C1 Lycamlng 0-2900 Lycoming 0-29~02 Lycomlng 0-320/150 HP Lycomlnp 0-235~C1 Lycomhg Q2335C1 Lycoming 029~D
74CK-2-48
Lycoming 0-320/
160 HP
74DMB060
79DMM1-58
74 Inches
2350-450
IZ Inches
Lycoming 0-320/
180 HP
I4DM&OM)
740M8-0-58
74 inches
2325-2425
72.5 inches
74DM6SS058
74inches
2325~2425
12.5 inches
74 inches
2350-2450
12 inches 16 inches
9
7
Piper PA1&1M) Cherokee r
Lycoming
a32W 180 HP
74DM6SS-060
Piper
Lycoming
Q320/ 18OHP
74DM~060
Piper PA2&180 Archer
Cywnlng
0-3601 180 HP
18EMBSS060
76EMBS5~58
781mhes
23252425
Piper PA-2&180 Cherokee B~
Lycoming
O-3MY 180 HP
76EMSOM)
~6EMB05B
76 inches
2275-2450
78 inches
6
Piper PA-2&180 Cherokee C~
Lycoming
0-3601 180 HP
78EM8S50-80
78EM8S5-058
76 inches
2275-2450
78 inches
6
Piper PA-2&180 Warrior
Cycoming
0-3801 180 HP
76EMBDM)
76 inches
UNKNOWN
78 inches
7
Piper PA-P8-181 Archer II" C78)"
Lycominp
0-380/ 180 HP
18EM8S5062
’18inches
22752375
76 inches
Piper PA-2&tB1 Archer Ii"
Lycomine O-3MII 189 HP
76EM8S50-60
76 Inches
23252925
76 inches
Piper PA-2B1BI Archer 111 (’94)"
Lymmmg
78EMBS16082
76 inches
22152375
76 inches
Piper PA38
Cycomlng 0-2381 112 HP Lycaming 103Mll 180 HP Lycoming 10-360/ 180 HP Lycaming 0-320 1150 HP Lycoming 0-3201 150 HP
70 Inches
PA2&16( Warrior II~
Pins
Special" S1S"
Pins
Special"
52’
PZL Koliber 150 Socata
(Commodore) MS892A
Socata (Rallye 150GT) MS892E
0-36W 189 HP
a3201.~50 HP
72CK-a56
72imheJ
22002350
76EMS058
76EM~56
78EMSO-81
78 inches
2200-2450
76 inches
8
78EMB(F58
7SEMB~56
76EM80-61
78inches
22002450
76 inches
6
74DM6Q5B
74DM66-y4
74DM6-0´•58
74 inches
2250-2500
72 inches
74DMM)-58
74DM6~54
740MB0´•58
74 inches
22502500
12 inches
74DM6058
74 Inches
72 inches
MS893E
Socata
(Rallye 180GT)
Socata
(Rallye Comm.) MSB93A
Socala
Raltye
Socata
Rallye 150T
Socata TB-B
STANDARD
CLIMB
0-360/180 HP
76EM&060
76EMBO-56
76 inches
2300-2500
76 inches
6
180 HP
76EM8O-60
76EM&056
76 Inches
23002500
76 inches
6
Lycoming
0-3201 150 HP
740M8~56
74 inches
2200-2450
72 inches
Lycoming
0-3201 150 HP
74DM~056
74DM6060
74 inches
22002450
Lycoming
0-3201 160 HP
74DM6SB~54
74DM8S80061
74 inches
ENGINE
AIRCRAFT
1SOST
Tampico
Lycoming
Lycoming 0-36)/
74DMb054
Lycoming 10-3601 180 HP
76EMSO-58
76EMS058
Stinson In, HW15
Conlnenlal A-75
74CK-2-38
74CK-2-38
Stinson 108. -1.-2.-3
Franklin 8Ae18583
74DR-058
Stinson 108. -1.-2. -3
Franklin 8A4-16583
74DR056
Stinson 1083
Franklin6Ae165~83
740R-0-52
SUnson t08-3
Franklin 6AC165B3
Stirs SA-SA
CRUISE
LIMITS
FOR REPAIR
NOTES
72 inches 72 Inches
76 inches
22002450
76 inches
72 inches
2340-2440
70 inches
74DR058
74 inches
2300-2500
72.5 inches
74DR-058
T) Inches
23002500
72.5 inches
74lnches
2400-2500
72.5 inches
74DR-0´•52
74 inches
2400-2500
72.5 Inches
Continental 0-200-A
69CK-0-48L
69 Inches
24252525
67.5 inches
TD.FT.RG
Lycoming 05201 160 HP
70CMOS10Q77
70CMOS16~0-Is
’IOlnches
2100-2250
68 Inches
8
TD.FT.RG
Lycoming
0-3201 1M) HP
70CMOS1~77
IOCMOS1~0-79
76lnches
2100-2250
68 inches
8
Stoddard HamiltMn Glassair IIS TO.FT.RG
Cycoming
0-3201 160 HP
70CMOS1~77
70CMOS16~Q78
’I(llnches
2100´•2250
68 inches
8
SLoddard HamUton GlaS(arn0-240
Continental 10-240
72 Inches
2100-2250
70 inches 72 inches
Steen
Skyboll~
Stoddard Hamilton Glassair I Stcddard Hamilton Glassair II
72CCS15~59
72CCS150~56
76EM&061
INCHES
119
Stoddard Hamilton GlaSlar10-320
Lycoming
740MOS1BQ64
74DMOS180-g2
14incher
2100-2250
Taylonxsn BC12D85.BC12D485.(9
Continental C-85
74CK-2-46
74CK-2-44
72 Inches
21702359
70 Inches
119
Taylorcran BC65 .BC1265.8CD12D.BC1 201 Taylorcran BCS12D85.BCS12D485.
Continental A65
74CKP-48
74CK-0-46
74 Inches
1460-2210
72.5 inches
1/9
Continental C-85
74CK-2-44
72 Inches
21702350
70 Inches
119
Taylonxan BCS65.BCS12D.BCS12D1
Continental A6J
74CK-0~42
74 inches
20702210
72.5 inches
1/9
Tallwcran BL65.8L126J.L2F.LZJ
Lycoming
0-1458
74CK-2-38
72 inches
22502400
68 Inches
219
Taylorcran BLS65.BLS1265
Lycoming 0-1458
74CK-2-38
72 Inches
22502400´•
68 Inches
2/9
TaylorcraA F-21
Lvcomine O-235-L2C
72CK-0~50
72 inches
23502450
70 inches
Taylonraft F-22B Ranger
Lycomlng 0-36~A4M
76EMBSS-058
morpe T-1B/ 150
Lvconing 0-3201 150 HP
70CMOS1M)-75
70CM()S180-73
70CM()S1M)-77
70inches
21802256
68 inches
8
Thorpe T-181 160
Lycomine 0-320 180 NP
70CMOS1M)-77
70CMOS16075
70CM()S160~79
’Il)lnches
21002250
68 inches
8
Tri R
(KIS) 1 116
Lycoming
0-231LZC
72KKS16-2-70
72KKS16268
Tri R
76EM8S1C070
0-320
(KIS) Cruiser
Lycoming
0-360
Van’s ATrcran RV-3/ 150
Lyconing
0-320 150 HP
Van’s Airtraft RV-Y 160
Lycoming Q330/16)HP
74DMOS1M)-65
76 inches
78 inches
70 inches
70 inches
78 inches
78 inches
70CMOS1~75
70CM()S1MM9
‘IOinches
21802256
68 Inches
8
70CM()S16-079
70CMOS18~77
10CM()S160-81
70lnchas
21002250
68 inches
8
Van’s AircraA RV-)I 150
Lycomlng
0-320/1SOHP
70CMOS~77
70CM()S0015
70CM[)S0079
70inches
2100-2250
68 Inches
8
Van’s Alrcran RV-II 160
Lycomine 0-320/16)HP
70CM()S[)079
70CM()S()-0-77
70CMOS()O81
70lnches
21042250
68 inches
8
Van’s Aircraft RV-GIRVGAI 150
Lycoming
0-3201 150 HP
70CM()S0077
70CMOS(tQ75
70CMOS0079
70lnches
21902258
68 inches
8
Van’s AircraA RVGIRVGAI Inn
Lycoming
(1320/ 160 HP
70CM()S(t079
70CM()S(t077
70CMOS(t~81
70lndes
2100-2250
68 inches
8
Van’s Aircret RV-OI 180
Lycoming
0-3601 180 HP
72FM8S( t081
72FM8S()-079
72FM8S()Q83
721nches
20502250
70 Inches
Van’s Airuaff RV-6IRVGAI 180
Lycaning ~360/ 180
HP
72FM8S( tOB1
72FMBS()0~79
72FMBS()083
72inches
2050-2250
70 inches
Van’s Aircraft RV-BI Inn
Lycomlne 0-360/ 180 HP
72FM8S( )-081
72FMBS(~O-79
72FMBS()-083
721nches
20502250
70 Inches
Varga Z150A Kachlna~
Lycomlne 0-320 (150)
740816-061
740M6-086
74 inches
22802496
72 Inches
Wassmer WA41 baladou
Lycoming 0-380
76EMB061
Zenai Zenith CH-2000 1116
Lyccming
0-235
Zenair Zenith CH-2000AllM
Lycoming
O-320(15dHP)
(118 HP)
72CK046 740M6S5058
12CK048
78 Inches
76 inches
72 inches
70 inches
74 inches
72 inches
6
NOTES: When
PROPELLER
MODEL
Climb/Cruise
propellers are recommended, the lower pitch prop.) can be expected to offer better take-off, climb, and The higher pitch (Cru;se) propeller high-altitude performance should be chosen only if take-off and climb are not critical.
TYPE
WEIGHT
CERTIFICATE
ATTACHING
KIT
(POUNDS)
kit
attaching
Continental
for
installations
a
shaft
flanged
unless
tapered
will
shaft
be
supplied
installation
for
69CK-069CKS12-070CM6S16-0-
70CM7S16-072CK-072CKS6-072CKS8-072CKS12-0-
all
is
order.
in
74CKL
Specify
attaching
kit
when
ordering
for
Lycom;ng
0-145
904
24.0
904
P28NE P28NE
34.4 38.75 38.75
904 904 904 904
24.8 28.4 27.9 41.0
1P2
21.0
74CK-0-
69CK
69CKS12 70CM6S16 70CM7S16 72CK 72CKS6 72CKS8 72CKS12
(FLANGED) (TAPERED)
installation. .74CK-2(3)
1P2
21.0
74DM6S5-0-58
propeller eligible only on Beech Model B19, MB-481 through MB-616, at 2000 Ib. gross weight. 74DM6S5-0-54 propeller el(;g;ble on Beech Model B19 at 2150 lb. gross weight. T.C.
data
sheet
(4>
8.00-6 tires Bellanca 7GCBA.
Air
Mods
Services
74
or
-2-
liTil
Serv;ce
CERTIFICATE
Aircraft
(D>
Avcon
Conversions
(316)326-8581
(301)733-7604
(316)782-3851
(E>
40.0 42.9
’i;
hub
DESIGNATION
(KEYED
Yan
Aero
Sensenich
Service
Fletch-air
1/2 1
LB. LB.
3/4
LB.
1
LB. LB.
2
LB.
I
LB.
1
1
LB.
3/4
LB.
3/4
LB.
1
LB.
3/4
LB. LB. LB. LB. LB.
3/4 2
2 1/4 2 3/4
(MAY
1,
1968)
Designates Design Change
CROSS-REIFERENCE
641-2023
LB. LB. LB.
1/4
3/4
2
SYSTEM
tured
"R’ Penn
LB.
1
EXAMPLE)
design
Blade design Basic Propeller diameter
LENGTH
is
designoted io propeller
The 74DM6S5-2-60 5/4.;nch spacer.
’un;ts.
(H)
37.5
3/4
Blade pitch
1
(FLANGED) 74CK (SAPERED) 74CKT (LYC. 0-145) 74CKL
S/N
See
2 2 2
1/4
inch
includes
M69Ct
