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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.

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Drive

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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

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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

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pitch. be

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60)

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propeller

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location

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effceed

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must

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when

of

propeller

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limits

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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