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SERVICE MANUAT

Model FlFixed-P itch Propel lers

INTRODUCTION

This manual contains routine inspection, meintenenee,overhaul, and minor repair procedures which can be aecomplishedby propeller servicing faci l i t ies. These instruct ions are intendedto suPplement the cri tet ia set forth in Civi l Air Regulat ions part 18and Civil Aeronautics Manual 18. In no case ere they to be construedor interpreted es overriding or contradictory to the material in theregulat ions or manual.

The use of this manual by any propeller servicing faci l i ty shal lnot, under eny circrrmstances be lnterpreted or construed as en approvalof the facility by Flottorp Manufacturing Coupany.

manual revised September 26, 1962, and the following addendabeen approved by the FAA.

FAA Approrred.

Chief , Engr. & Ivlfg, Braneh

Thishave

\*-

- 1 -

Approval Date

SECTION I

SECTION II

SECTION I I I

SECTION IV

SECTION V-- Par ts L i s t

TABLE OF CONTENTS

Page

Speci f icat ions and Deser ipt ion. . . . . . 3

A . G e n e r a l S p e c i f i c a t i o n s . . . . . . . . . . 3B . I n s t a l l a t i o n s . . . . . . . . . . . . . . . . . . . 3

S e r v i c e T o o l s a n d E q u i p m e n t . . . . . . . . . 3

P g r i o d i c I n s p e c t i o n . . . . . . . . . . . . . . . . 4

M a i n t e n g n c e a n d R e p a i r . . . . . . . . . . . . . 4

A . P rope l le r Ins ta l l a t ion ,0 - 3 2 0 - D 2 B E n g i n e . . . . . . . . . . . . 4

B. Propel ler Removal ,0 - 3 2 0 - D 2 B E r g i n e . . . . . . . . . . . . 5

C . C l e a n i n g . . . . . . . . . . . . . . . . . . . . . . . 5

D . I n s p e c t i o n . . . . . . . . . . . . . . . . . . . . . 6E . R e p a i r s . . . . . . . . . . . . . . . . . . . o 6F. Checking Propeller Track in Shop 7G. Checking Prope1ler Track on the

A i r c r a f t . . . . . . . . . . . . . . . . . . . 7

H . P a i n t i n g . . . . . . . o . . . . . . . . . . . . . . . l

I . B a l a n e i n g . . . . . . . o . . . . . . . . . . . . . . 8

9

-2 -September 26, L962

.{L

-l

SECTION I

SPECIFICATIONS ATID DESCRIPTION

A. General Speci f icat ions

Type Fixed-Pi tchMaterial Aluminuur Al loyEngine Shaft SAE Flanged

AS L27 No. 2P i tch Range 50 in . to 70 in .W e i g h t 3 0 . 5 l b .

B . Ins ta l la t ions

Prope l le rPropel ler Diameter

Aircraft Engine Rating Model fr

Beeeh Lycoming 160 HP FlC 7660-2 74 74Musketeer 23 O-320-D2B 2700 RPM

SECTION II

SERVTCE TOOLS Ar{D EQUIPMENT

No special tools are required for maintenance and overhaulof these propellers. Standard equipment necessary is:

Propel ler Assembly Tab1eSuspension Type Propeller Balancer

t---

September 26, 1962

- 3 -

SECTION I I I

PERIODIC INSPECTION

NATURE OF INSPECTION

Secur i ty of mount ing and mount ingb o l t s s a f e t i e d

Minor n icks , sc ra tches , and c racks

C o r r o s i o n , c r a c k s n i c k s , a n ddents beyond permiss ib le l im i ts

Overhaul

CAUTION

Due to the h igh s t resses to wh ich thep r o p e l l e r b l a d e s e r e s u b j e e t e d , t h e i rcare fu l ma in tenance is v i ta l l y impor tan t ,par t i cu la r ly on the lead ing edge o f eachblade from the t ip inboard for approximately8 i n c h e s . A 1 1 n i c k s a n d s c r a t c h e s m u s t b erepa i red be fore the a i rp lane is f lo r^nr . N icksand scra tches se t up coneent ra t ions o f s t resswhich can exceed the s t rength o f the b ladem a t e r i a l ; t h e r e s u l t w i l l b e a c r a c k a n d p r e -mature fa i lu re o f the b lade

INSPECTION TIME

P o s t f l i g h t

Pos t f 1 igh t

30 hours

At engine overhaul

SECTION IV

MAINTENANCE AI\D REPAIR

In genera l , a l l ins t rue t ions and procedures ou t l ined in CAM 18 fo ra l l inspec t ion , ma in tenanee, and repa i r shou ld be adhered to . Ba lanc ingthe prope l le r shou ld be per fo rmed by an FAA cer t i f i ca ted prope l le r repa i rs ta t ion s inee equ ipment neeessary to accompl ish the aecuracy requ i red isno t normal ly ava i lab le to l ine main tenance personne l .

A . P r o p e l l e r I n s t a l l a t i o n , 0 - 3 2 0 - D 2 B E n g i n e

1. Wi thout Sp inner

a. Rotate the engine unt i l the TC #L mark on the starter gear a-l igns w i th the do t on the eng ine s ta r te r hous ing .

b . S l ide the prope l le r on to the eng ine shaf t index ing i t so tha tt h e b l a d e s l i e a P p r o x . a t t h e 5 o ' c l o c k a n d 1 1 o ' c l o c k p o s i t i o n s .

c . Ins ta l l the 6 p rope l le r re ta in ing bo l ts and washers , t igh tenevenly, and torque to 300 ineh-pounds.

d . Secure the bo l ts w i th sa fe ty w i re .

September 26, L962

-4-

2 . Wi th Beech 169-910030 Sp inner Assy .

a. Rotate the engine unt i l the TC #L mark on the star ter gear a l ignswi th the dot on the engine star ter housing.

Sl ide the spinner rear bulkhead onto the engine shaft indexing i tso that the tabs which have the corners cut of f l ie approx. att h e 6 o ' c 1 o c k a n d t h e L 2 o ' c l o c k p o s i t i o n s .

Sl ide the propel ler onto the engine shaft indexing i t so thatt h e b l a d e s 1 i e a p p r o x . a t t h e 5 o ' c l o c k a n d 1 1 o ' c l o c k p o s i t i o n s .

Inser t the 6 p rope l le r re ta in ing bo l ts and washers in to theholes in the spinner f ront bulkhead, and sl ide the assemblyonto the prope l le r , a l ign ing the bu lkhead cu tou ts w i th theb lades . T igh ten the bo l ts even ly and to rque to 300 inch-pounds.

Secure the bo l ts w i th sa fe ty w i re .

s l ide the sp inner dome onto the bu lkheads, and ins ta l l the10 retaining screws and washers.

Prope l le r Remova l , 0 -320-D2B Eng ine

1. Wi thout Sp inner

a . Remove the 6 p rope l le r re ta in ing bo l ts and washers .

b . Remove the prope l le r f rom the eng ine shaf t .

W i t h B e e c h 1 6 9 - 9 1 0 0 3 0 S p i n n e r A s s y .

Remove the 10 spinner dome retaining screws and washers,and remove the dome.

Remove the 6 p rope l le r re ta in ing bo l ts and washers , and thespinner f ront bulkhead.

Remove the propel ler and the spinner rear bulkhead from the engines h a f t .

C . C l e a n i n g

For e lean i tg , use warm f resh water and soap, un leaded gaso l ine , o rkerosene, and su i tab le b rushes or c lo ths . A f te r the b lades have beencleaned, al l c leaning substances must be immediately removed. Soap inany form should be removed by thoroughly r insing with f resh water,a f te r wh ich a l l s tee l sur faces shou ld be dr ied and eoated w i th c leanengine oi l . Scrapers , por^rer buf f ers , steel brushes, and any other toolsor subs tances tha t w i l l sc ra tch or o therw ise mar the sur face must no tb e u s e d o n b l a d e s . I n s p e c i a l e e s e s w h e r e a h i g h p o l i s h i s d e s i r e d , agood meta l a i rc ra f t po l i sh may be used, however , upon comple t ion o f thepo l ish ing , a l l t raees o f po l i sh shou ld be immedia te ly removed. In noins tance sha l1 the b lades be po l i shed w i th a power bu f fe r .

b .

c .

d .

e .

f .

B .

2 .

a .

b .

C .

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D . Inspec t ion

In add i t ion to the methods d iscussed in CAM 18, another sa t is fac to rvmethod fo r de tec t ing c raeks in b lades is as fo l lows:

2 .

3 .

C l e a n t h e b l a d e c a r e f u l l ythorough ly , us ing a c lean

Prepare ? so lu t ion o f SWohas f l , t r ,oreseent qual i ty ,

w i th carbon te t raeh lo r ide and drva i r b l a s t i f n e c e s s a r v .

n o n - t o x i c , n o n - c o r r o s i v e o r l w h i c hand 50% kerosene.

4 .

Comple te ly immerse the b lade in the so lu t ion and a l low i t toremain f o r a min imum of th i r ty minu tes . A f te r th is per iod ,remove the b lade f rom the ba th and a l low the excess f lu id tod r a i n . S p r a y t h e b l a d e w i t h c a r b o n t e t r a c h l o r i d e t o c o m p l e t e l yremove the remain ing so lu t ion . A11ow the b lade to s tand fo rf i f t e e n m i n u t e s s o t h a t t h e s o l u t i o n w i l l b l e e d o u t o f a n vc r a c k s p r e s e n t .

C a r e f u l l y i n s p e e t t h e e n t i r e b l a d e u n d e r a n e a r - u l t r a v i o l e t l i g h tsource . The inspec t ion must be conducted in a darkened booth orroom. So lu t ion b leed ing f rom a sur face c rack w i l l show up undert h e l i g h t a s a b r i g h t f l u o r e s c e n t I i n e .

Repa i rs

Major and minor repa i rs on ly w i th in the l im i ta t ions o f CAD{ 18a r e p e r m i s s i b l e . I n a n y c a s e , d o n o t e x c e e d t h e r e p a i r l i m i t sfo r w id th o r th ickness as spec i f ied in Tab le I .

TABLE IB],ADE REPAIR LIMITS

E .

B lade S ta t ion(Distance from hubcenter l ine , in . )

7 13 /3211 3 /321 6 2 t / 3 222 L3 /6427 3/433 19/64

damage are no t permiss ib le .

September 26 , L962

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s -szo - * 5 ' ) sqs . r++o - - ' - f . t ( 'F A ' t . / S )

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- 3. J>E

Min imumRepaired Thickness

1 . 5 0 01 . 1 0 0

. 7 g o

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.443

.294

Min imumRepaired l^ / idth

5 . 2 7 04 . 7 5 03 . 7 4 0

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3 ' i /a l o i

T h e o n l y a e c e p t a b l e m e t h o d s o f r e p a i r i n g c u t s , n i c k s , c r a c k s , e t c . ,are those by which the damaged popt ion is removed to leave a smoothwel l - fa i red sur faee. Methods wh ich a t tempt to re loca te meta l bycold-working to eover or conceal the defect rather than remove the

- 6 -

F. Cheeking Propeller Track in the Shop

1. Mount i t on a protractor beneh mandrel.

2. Plaee e stat ionary object at the t ip of one of the blades andmake a mark on the objeet where the eenter of the blade touchesi t .

3. Rotate the propeller 180 degrees and repeat the above operationwi th th is b lade.

4. Measure the distance between the centerlines of the two marks.The al lowable dif ference is L/8 inch.

5. I f the distance is greater than I/8 inch, the propeller shouldbe sent to an FAA cert i f icated propell .er repair stat ion forfurther inspection and repair.

G. Checking Propeller Track on the Aircraft

The following precedure should not be attempted unless it isknourn that the engine shaf t is not out of l ine. The airplanemust be in a hangar where air currents will. not rock it. Usethe fol lowing procedure:

1. Place a stat ionary object at the t ip of one of the bladesand make a mark on the object where the center of the bladetouches i t .

2. Rotate the propeller 180 degrees and repeat the above operationwi th th is b lade.

3. Measure the distance between the eenterl ines of the two marks.The al lowable dif ference is I /8 ineh.

4. I f the distance is greater than L/8 inch, the propellershould be sent to an FAA cert i f icated propeller repairstat ion for further inspection and repair.

H. Pa int ing

Careful ly touch up minor paint damage due to repair operationor hlear. Propellers requir ing complete repaint ing shal1 f i rst bestripped of their remaining paint and then painted according tothe fol lowing instruct ions :

l . Al l surfaces to be painted shal l be thoroughly cleanedinnnediately before the application of the primary coat.Use benzol, carbon tetrachloride or some other suitableorganic solvent. Use same care when applying second topcoat,that preceding topcoat has not become soi led.

2, The f lat face of the blade wil l receive a three-coat appl icat ion;one Primary coat and two topcoats. Mask-off the camber face ofthe blade, using any suitable method.

September 26, L9627 -

The pr imer sha1 l be z inc chromate th inned w i th to1uo1.Apply i t evenly over the surfaee of b lade avoiding a heavycoat. A11ow to dry for at least 30 minutes at room temperaturein a dus t f ree a tmosphere .

I . Ba lanc ing

Fo l low ing any apprec iab le b lade repa i r , the prope l le r must bebalanced. The suspension type balancer is recommended beeauseof the d i rec t ind ica t ion o f the d i rec t ion in wh ich the prope l le ris ou t o f ba lance, to de l iea te ly ad jus ted ba lance ways arenecesssry , and because o f i t s ease o f in te rpre ta t ion .

sma11 amounts of unbalance can be corrected by spraying anadd i t iona l l igh t coa t o f b lack pa in t on the f la t face o f thel igh t b lade. Do no t use heavy app l ica t ions o f pa in t fo r th ispurpose, s ince unba lance w i l l re -occur as soon as the pa in t e rodesaway.

" Appreciable unbalance can be corrected only by removing mater ia l .Th is ean bes t be accompl ished by abras ive gr ind ing and po l i sh ing ,and should be done only on the camber s ide of each blade and on thesides of the hub. Metal removed must be held wi th in the l isr i ts inTable I . Sideways unbalance can of ten be best corrected by removalof metal on the camber s ide c lose to the leading edge of one bladeand to the t ra i l ing edge of the other blade on the heavy side.

I t i s impor tan t no t to leave any abras ive sera tches across the b lade.A lways f in ish the po l i sh ing opera t ion so tha t any abras ive marks tha tmay remain run along the blades, not across them. In any case,remove a l l deep scra tehes .

For those who have convent ional balancing arbors, adapter cones, andpara l le l kn i fe edges , the proeedure is iden t ica l to the preced inginstruct ions. However, instead of unbalance being indicated by ad isc ind ica tor , i t i s ind ica ted by a tendency o f the prope l le r torotate toward the heavy side. I t should be noted that the kni feedges, a rbors , and adapters must be f ree f rom a l l fo re ign mat te r , andmust be smooth and true. The ways should be checked for paral le l ismpr io r to ba lanc ing the prope l le r .

3 .

September 26 , L962-8 -

I tem No.

SECTION V

PARTS LIST

Par t No .

FlC7660-2#* 169-910030-5#* 169-910030-3# * 1 6 9 - 9 1 0 0 3 0 - 1

@ 336AN960-616

# AIi t525-10R8# AIi t960-10

MS20995C41

Nomenclature

Propel lerRear Spinner BulkheadFront Spinner BulkheadSp inner DomeB o I tWasherSerewWasherSafety Wire

1234567

:

No. Req .

111166

1 01 0

as req.

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#

Beech A i rc ra f t Corp . Par t No.F l o t t o r p M f g . C o . P a r t N o .Opt ional Equipment

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