### Piper Aircraft Corporation Vero Beach, Florida, 

### U.S.A. 

# SERVICE No. 910A 

# I 

# BULLETIN ********************************** 

# * .. * * PIPER CONSIDERS .. . :- 

# * : -· COIV1PLIANCE MANDATOflY : **********************************

_________________________________ o_a_t_a

______ **Qctobe~Q~8~------- --**  **~s~-----** 

### (Service gulietin No. 910A supersedes and

**vc cs**  

### Service

**~:l ~t**  **n** 

### N o. 910, dated May 15, 1989 and the affect::d pcrticr:s of Ser·1ice 5:!.! ll etin

**~ic .**  

### 5288, dated March 10, 1978) T

his Service Bulletin is divided in two Parts. Check each Par: for applicable compliance time, purpose and instructions. SUBJECT : Wing Lift Strut Assembly Inspection/Replacement REASON FOR REVISION : To revise models affected, serial numbers affected, compliance time, purpose, instructions and to add Part II. 

### APPROVAL : . The technical contents of this Service Bulletin have been approved by· the F.A. A.· - · --


### MODELS AFFECTED:

_ ,_. ·. ·· - 

### PA
- 18/18A Series. Super Cub · NOTE: Includes All Serial No. L
- 21A, L
- 218, 

### & L
- 18, Seaplane, Agricultural, and Military Versions PA-19 Super Cub PART I 

### SERIAL NUMBERS AFFECTED: 18-1 through 18-8309025, 1809001 through 1809032, 1809034 through 1809040 19-1, 19
- 2 and 19-3 COMPLIANCE TIME: Before next flight and each twelve (1 2) month period thereafter. · · NOTE:· If the inspection requirements of Service Bulletins No. 5288 or No. 910 have been accomplished within the last twelve (12) months or if the wing lift struts are new and were installed within the last twelve (12) 

### months, inspection is required no later than twelve (12) 

### months after the last inspection or new lift strut installation as the case may be. If the aircraft is new with original 

### lift struts installed, the repetitive inspection begins when the 

### aircraft is twelve (1 2) months old . (OVER) ATA: 

### 5701,.**J.** · - • - - SERVICE BULLETIN NO. 910A PAGE 2 - OF 5 - .. , _ : "f!," .i**~, .**  ' > ' : - . - - ·'":"':.. ' :. .: ·- .. :**~** : : ' ': ' PURPOSE: Piper Aircraft has determined that the five (5)**y~ar** repetitive fnspection interial ' reciuired in service Bulletins No. 528B and 910 may be inadequate for the timely detection of serious wing lift strut corrosion. This corrosion, · if allowed to progress, may lead to failure of the wing lift strut, and the possibility of loss of wing structure integrity.

The compliance time for the corrosicn inspect i on and treatment is reduced to an interva l not to exceed twelve (12) months frcm the last insp-ect i on or the first use of new 1 i ft struts . Initially Piper deems i t necessary to rep l ace existing w i ng lift strut with new sealed wing l i ft struts a1:. a date not to exceed twenty
- four (24) months. (See Part II ) Part I of this Service Bulletin provides an inspection an corrosion impediment procedure to detect and t reat possible wing lift strut corrosion . INSTRUCTIONS: 1. Remove wing lift struts and accomplish the inspection per i nspecti on procedures on Sketch "A". Caution: All aircraft utilizing "cuffs" at the wing lift strut roots (top and/or bottom) should take extra care in inspection for external corrosion in the areas covered by the cuffs. 2. Inspect forks, clamps, fairleads and jury struts for condition and replace as necessary . All attaching hardware should be replaced. 3. After completion of the inspection procedure, but prior to the corrosion impediment procedure of the wing lift struts, turn each wing lift strut upside down and tap gently. This procedure is necessary to remove any water, debris, or corrosion particles which may have accumulated.· ;-- . 4. Lift strut tubes indicating presence of internal corrosion and which fail the inspection procedure must be replaced with new wing lift struts called for in PART II of this Service Bulletin. Note: Should corrosion be apparent from the outside, (rust pin holes or large rust stains) strut must be rep 1 aced even if strut passes the inspection procedure. _=. ,5:.:: · · 5. Treat (corrosion impediment) each w ing lift strut per the instruction procedure note on Sketch-"A". Treatment must coincide with each i nspection as outlined in the compliance t ime above. 6. Lift strut assemblies which have been factory treated with corrosion preventive measures are identified by the installation of a cherry lock_ rivet installed at the upper (wing attachment) end . 7 . Alternate oreservative materials : In addition to the "Val oil" and ''Lionoil" (preservatives), it is permissib le to use the following alternate preservatives
- Paralketone, linseed oil or any alternate**preservative~** that satisfy the requirements of Federal Specification TT -S-1 760 . NOTE: Upon successful complet i on of the inspection procedure and treatment, - reinstall lift struts on aircraft. 8. Check aircraft rigging and adjust as necessary, use P iper Service Memo 19 (attachment A) as required to accomplish the proper rigging. 9. Make an appropriate logbook entry · of compliance with this Service Bulletin .

### SERVICE BULLETIN NO. 910A
MODELS AFFECTED: PA-18/18-A Series Super Cub N

OTE: Includes All Serial No . L-21A, L-218, & 

### L-18, Seaplane, Agricult ural, and M i litary V ersions PA- 19 Super Cub PART II 

### PAGE 3 OF 5
SERIAL N U

MBERS AFFECTED: 18-1 through 18-8309025, 1809001 through 1809032, 1809034 t hrcugh

**~80~0 40**  19
- 1 , 19-2 

### an d 19-3 COMPLIANCE TIME: To coincide w ith the n ext regularly scheduled inspection event or at next replacement of the wing lift strut, but not to exceed twenty-four (2 4) months from the initial inspection as called for in Part I of this Service Bulletin. PURPOSE: Part II of this Service Bulletin announces the availability of new sealed w ing lift struts which, when installed, will relieve inspection requi rements of Part I of this Service Bu 11etin INSTRUCTIONS; 1. Remove old wing l ift strut. 2. Prepare, prime and paint new sealed wing lif t struts to match aircraft before assembly. 3. Inspect clamps, fairleads and jury struts for condition and replace as necessary. All attaching hardware should be replaced. 4. Install new Sealed Wing Lift Strut Assemblies, Piper Part Number 89497-02 (front) and Piper Part Number 89498-02 (rear) on each wing. 5. Install "No Step" Decal , Piper Part Number 80944-02, at the base of each wing lift strut 1n the approximate location of the original "No Step" deca1. 6. Check aircraft ri gging and adjust as necessary. Use Piper Service Memo 19 (attachment A) as required to accomplish the proper rigging. 7. Upon successful completion of Part II of this Service Bulletin, make an appropri ate logbook entry of compliance. MATERIAL REQUIRED: As required by inspection for Part I or as required by Part II , two (2) each Front Wing Strut Assemblies, Piper Part Number 89497-02, two (2) each Rear W ing Strut Assemblies, Piper Part Number 89498-02, and four (4) each "No Step" Decal, Piper Part Number 80944-02. AVAILABILITY OF PARTS: Your Piper Field Service Facility . 

# I EFFECTIVITY DATE: Thi s Service Bulletin is effective upon receipt. (OVER)SERVICE BULLETIN NO. 910A PAGE 4 OF 5 : SUMMARY: Any applicable factory participation will remain in

affect for a period of time not to exceed 180 days from the effective date of this Service _ BulJetin • . ___ : . . _ _ . _ - - - - - ... - - ._ __ __ ·: .. : Special pricing is in effect for the Front Wing Lift Strut, Piper Part Number 89497-02 and for the Rear Wing Lift Strut, Piper Part Number 89498 -02, for twenty
- four (2 4) months from the effect ive date of this Serv ic e Bulletin. Please **c~ntact** your Factory Piper F i e ld Service Facility to make arrangments for compliance with this Service Bulletin in accordance with the compliance time indicated. NOTE : If you are no longer in possession of this aircraft, please forward this information to the present owner/operator and notify the factory of address/ownership corrections. Changes should include aircraft model, ser i al number, current owner's name and address. Corrections/changes should be directed to: ·.

Piper Aircraft Corporation Attn: Customer Services

P.O. Box 1328 Vera Beach, Florida 32961-1328 0 • -;; _ . **~** •••

### SERVICE BULLETINN O. 910A P A

GE 5 OF 5



# ~~~=r VIEW OF MAULE FABRIC TESTER 

# ;-1 Rivet NAS1738B4-4 (On Centerline Of •fACTORY TREATED• Strut)



### r:?.~ Shee:



### ~~~al **Scr~ M~1861-44**  (On Cerrtenine :



### ~"FIELD TREATED" Strut) 

## r:Il• . ..... , -rlt' ' I I I I I ' ' ' I o •, o I 1 I , I o I I I I I f • '

**~** • • "T-> 

# ' em:

**~** I It • • o! 1 • f I lo j o I 0 f I 

# - ' I I W I I I r I 1 If I 1 I I j I I • t o o I I • !

**~** C I I • I I o f I • • o 1 t , 1 o t ! • I • I 1 I • • 0 o I o I ij I • t I 1' • , • I +I I f t t to I •' • o • J It • 1 t SOTTOM VIEW OF FRONT 

### LifT SJEUT ASSEMBLY Rivet NAS173884-4 (On Canter1ine OF ·FACTORY TREATED• Strut) Sheet MetaJ Screw M$51861-44 (On Canter1ine Of ·etEL.O TREATED· Strut)

BOTTOM VIEW Of BEAR 

### LifT STRUT ASSEMBLY INSPECTION PROCEDURE 1. Securely tape a sheet of thin 1 

# 1• inch graph paperto the lower 11 inches of the top and bottom surfaca on all wing lift struts. 2. Using a Maule •Fabric Tester- and holding tool normaJ to strut contour, apply pressure at a scaie raading of SO in in each of the grid blocks. 3. Remove the paper and inspect the r ift strut tubes. A

**pe~ible** dent will appear if internal corrosion is present If any dents are found, be C8rtain the dent are in the metal by carefully removing the paint. a. Lift strut tubas indicating the presence of any precptible dent in the metal must be replaced with a new lift strut a5$embly be fore further flight. b. If no dents appear in the metal, the lift strut may be considered airwothy. NOTE Further internal corrosion may be impeded perthe following procedure: a. Remove lift strutfrom aircratt. b. Inject

**o~e** quart of V aioil, **Uono~** Multi-Purpose L-1. U nseed Oil, Paralketone or any alternate preservative ccnf04'ming to Fadera !Specification TT-S- 1760 , into the bolt hole atthe top of the

**~rut.** c. Plug the bolt holes and slosh oil until interior of strut is throughfy coated. d. Drain oil from strut ( through bolt holes) and install MS5 1 861-44 sheet metal screw, as shown, for futu re identification. e. Reinstal l strut to aircraft and rig. 4. Record lift strut inspect ion in aircraft logbook. SKETCH "A"**~-:=~- ··**  ·· - · '-::.. - · - · 4 **i~** - · ·'

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## .

**~** .. .
., R EFERE!'!CE SERVICE BULLETIN 91 OA 

# SERVICE

**RIGG~** PROCEDURE Piper PA-18 and PA·l9 

### ATIACHnENT "A" 

# MEMO

Sernce Memo No. 19

R.!GGING
**PROC~Dl'1tE:** Rz!se

**~e** forward part of the airplane eo that the wheels are just

**c~ear** o! the ground and st:;)port it by preps under c::e z_ ::=.c r.a:lciing

**g-e~=** fit:ing-3.

**R~ise** the 

### t.aU to approximate level fligilt position and support it

**~!'e .**  LEVELING: Level the ai:rplane as f ollows: Drop plumb bob from P. K. Screw in door frame top chaxmel to intersect punch maJ:X in

**e:~closure** door rear binge. OIHEDR.!L ANGLE: To checl: dihedral angle at the froat spar proceed as follows: Stretch 

### a stri..ng along the top of the wt.o.p above the front spar, f:'om wing tip to wing tip, aDd draw it tight. CheCk the dimension vertically from the string to cop offuselage front spar wing hinge fitting. For correct d!.hedral this dimension should be 3 f.l/8 iDches. To check !or equal dibed.ra1 iD each wingproceed as follows: Usingthe 30 inch level (witbour any spacer blocks) bold it spanwtse against the bottom of the wingunder the front spar iD the space between the jury struts and lift strut attachments. Noce the position of the bubble aDd do the same on the other wing. Re-adjust the front struts aDt1l both wings show the same amOtllJt off level, being careful with each adjustment to set tbe lett strut out the same num.ber of turns as tbe r1gfx one is sec in. and vice versa . WASH 

## our: To adjU8C the wash

**o~** in the wings (dlbedral of the rear spar) proceed as follows: Set a 3/8 iDch spacer bloCk 011 

### top 

### ot the 30 inch level at one end. Working on the rib adjacent to tbe outer eud of the ailerou. hold tbe level fore and att along the bottom of the rib with the spacer block at tbe rear and the front end of the location of tbe front spar. The correct wash out wtll exist wbeD the bubble is centered. Adjust the rear sttl%S in or out to obtain this condition. TAIL ASSEMBLY: With the airp!me in level position the sta.bill%ers should be leveled at their 

### rear spars. The

**hin~** line should be straight from tip tu tip. Plumb the !in at the rudder hinges.


## PIPER AIRCRAFT
-CORPORATIO-N.
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