"'"' . . 

No. 528D 

. ~er Aircraft Corporation 

.. _io Beach, Florida. U.S.A. 

SERVICE 

BULLETIN 

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: P!PER CONSIDERS ! .. : CON1PLJANCE MANDATORY ! ·* * ********************************** 

Date October 19, 1990 S 

S~rvice Bulletin No . 5280 supersedes and voids Service Sull~~in No. 528C, 

dated October 11, 1989) 

This Service Bulletin is divided into Two (2) PARTS. Check each PART for 

Purpose, Instructions, and Cc:npl ia.ncs Time. 

SUBJECT: 

REASON FOR REVISION : 

MODELS AFFECTED: 

All aircraft incorporating 

stee·l wing 1 i ft struts (See note) 

J-2 Series, Cub 

J-3, NE-1, L-4 Cub 

J-4 Series Coupe 

J-5, J-SC, L-14, AE-1 , HE-1, Series 

Cub Cruiser 

PA-11 Series, Cub Special 

PA-12 Series, Super Cruiser 

PA-14 Series, Family Cruiser 

PA-15 Vagabond 

PA-16 Clipper 

PA-17 Vagabond 

PA-20 Series, Pacer 

PA-22 Series, Tri-Pacer/Colt 

PA-25 Series, Pawnee 

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- . NOTE: 

Wing Lift Strut Assemb ly 

Inspection/Replacement 

To revise Compliance Time, 

Purpose, Instructions, and to 

announce the availability of new 

sealed lift struts 

SERIAL NUMBERS AFFECTED: 

ALL 

500 through 1975 

ALL 

4-401 through 4-1649 

5-1 through 5-1389 

11-1 through 11-1678 

12-1 through 12-4036 

14- 1 through 14-523 

15-1 through 15-388 

16-1 through 16-736 

17-1 through 17-215 

20-1 through 20-1121 

22-1 through 22-9848 

25-1 through 25-8156024 

Al1 variations of the PA-18 Series and PA-19 Series are no longer 

Affected by this Service Bulletin and are covered by Piper Service 

Bul letin No . 910A (or latest revision). 

APPROVAL: The technical contents of this Service Bulletin have 

been approved by the· F.A.A. 

(OVER) 

ATA: 5701 

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SERVICE BULLETIN NO. 5280 PAGE 2 OF 6 ... - -: ...,_ -::_· - ;;~ 

PART I : :::.-- :. ( • J • ~ - • ,· 

PURPOSE: The five (5) year repetitive inspection interv~l . ·=·· .-.= -. -

_ required by compliance with Service Bu]letin N.o. 528C may not be adequate for 

timely detection of serious wing lift strut corrosion. Eventually, undetected 

corrosion ~ill reduce the .strength of the lift strut, and could possibly lead 

to failure of the strut. In Service Bulletin No. 528C, the compliance time for 

the existing corrosion inspection and treatment procedure was reduced, and is 

currently at intervals not to exceed twelve (12) months from the last 

inspect ion or the first use of a new 7 ift strut. 

PART I of s Serv i ce 3ul et~ n prcv i des an inspection and treatment procedure 

to detect and treat the corrosion which may be present in the wing lift s~rut 

assemblies. 

COMPLIANCE TIME: 

thereafter. 

Before next flight and each twelve (12) month period 

NOTE 

If the inspection requi rements of Service Bulletin No. 910A or 528C have 

been accomplished with i n the last twelve ( 12) months or if the wing lift 

struts are new, and have been installed within the last twe lve (12) 

months, the repetitive inspection will be required no later than twelve 

(12) months after the last inspection or new lift strut installation as 

the case may be . Upon reaching (24) months from the effective date of 

this Service Bu lletin, proceed to PART II. Compliance with PART II of 

this Service Bulletin will relieve the repetitive inspection requirements 

of PART I. 

INSTRUCTIONS : 

1. Prepare the aircraft for the removal of old wing lift struts by supporting 

the wing as necessary. 

2. Remove wing lift s~r uts and accomplish the inspection per "Inspection 

Procedure" on Sketch "A". 

,...--- --- ------- - CAUTION: 

All aircraft u~ilizing "cuffs" at the wing lift strut roots (top 

and/o bottom) shou ld take extra care in inspection for external 

corrosion in the areas covered by the cuffs. 

3. Inspect forks, clamps, hardware, fairleads and jury struts for condition 

and replace as necessary. 

4. Turn each wing lift strut upside down and tap gently. This procedure is 

necessary to remove any water, debris or corrosion particles. 

5. Inspect 1 ift struts according to ·rnspection Procedure" in Sketch .. A. 

Lift struts indicating presence of internal corrosion or which fail the 

·rnspection Procedure· must be rep laced with new sealed wing lift struts. 

Should corrosion be apparent from the outside (rust pin hol es or large rust 

stained areas), strut must be replaced even if strut passes the Minspection 

Procedure". 

NOTE 

The new sea1ed lift struts may be installed one at a time during the 

(24) months compliance time (PART II) provided the repetitive 

· inspecti on requirements above are met for the lift struts that have not 

been replaced. Replacement of all lift struts with the new sealed lift 

struts will relieve the repetitive inspection requirements of PART I of 'this se'r,i'i ce. au 11 et in. . 
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SERVICE BULLETIN NO. 5280 PAGE 3 OF 6 

INSTRUCTIONS {CONT'O): 

6. Treat 

Procedure" (corrosion 

note on 

impediment) 

Sketch 

each wing lift strut per the "Inspection "A".. Treatment (corrosion 

coincide with each

impediment) must 

- inspection as required by the compliance 7 t ime above. . Upon completion of the "Inspection Procedure" and treatment

serviceable lift struts 

, rei nstall 

on the aircraft. 8. 

Service 

Check aircraft 

Memo and 

rigg

Owner 

i ng 

Handbook 

and adjust as necessary . (Use appropriate Piper 

as required to accomp lish pr~oer rigg ing.) 

9. Make a logbook entry of compliance ~ ?ART ! of th s Service aul1et in. 

MAT:RIAL R~QUIRED: Not applicable 

PART II 

PURPOSE: 

will eliminate the concern 

Piper has developed an improved wing lift strut which 

for internal corrosion in wing lift str~ts. The new struts a1so feature an improvement in the =esi gn cf t he lift strut fork which el iminates the requirements of Piper Service Bul letin No . 1570. 

It wil l be necessary to replace existing wing lift struts with new sea led wing 

l ift struts at a date not to exceed (24) months from the effective date of this Serv i ce Bulletin. 

COMPLIANCE TIME: Upon reaching (24) months from the effective date of 

this Service Bulletin or as required by PART I inspection. 

INSTRUCTIONS: 

1. Prepare the aircraft for the removal of wing lift struts by supporting wing as necessary. the 

2. Remove the old wing lift struts. 3. Inspect 

replace as 

clamps, 

necessary

hardware, fairleads and jury struts for condition and . Note that the new Piper sealed lift strut assemblies incorporate 

4. Refer 

the latest configuration fork bolt assembly. 

to the Part Number Supplement on Page 5 of this Service Bulletin to 

aircraft

determine ~he proper wi ng lift strut part number for the appropriate . 

5. 

Note: 

Install, 

Use 

rig, 

appropriate 

and adjust the new ·Sealed lift strut assemb li es as required. 

Piper Service Memo and Owners Handbook as required to accomp lish proper rigging. 6. 

strut 

Install 

approx

"No Step" 

imately 

Decal, Piper Part Number 80944-02, on each wing lift 

six (5) inches from the bottom of the struts, or paint the statement "NO STEP" in one (1) inch minimum high letters, which contrasts with in a color 

approximately six 

the airplane color, on each wing lift strut (5) inches from the bottom of the struts, and in such a direction that the "No Step" caution can be read when enteri ng and l eaving the airplane. 

7. Make appropriate 

Bulletin for strut

logbook 

(s) replaced. 

entry of compliance with PART II of this Servi ce 
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SERVICE BULLETIN NO. 5280 PAGE 4 OF 6 ·_· ,:-·.(-

MATERIAL REQUIRED: As required by inspect ion, refer to the Part Numb~r .. '- , ...... 

Supplement on Page 6 ~f this Service Bulletin when ordering the new sealed lift · : 

struts; four (4) eac.h pe_rwaircraft, "No Step" Decal, Piper Part Number 80944- 02. 

AVAILABILITY OF PARTS : Your Piper Field Service Facility. 

This Service Bulletin is effective upon receipt. 

SUMMARY: 

Service Bulletin. 

listed on the Part 

from the effective 

There is no factory participation applicable to this 

Special pricing is in effect for the sealed lift struts as 

Number Supplement sheet on Page 6, for at least 180 days 

date of this Service Bulletin. 

Please contact your Factory Authorized Piper Field Service Faci l ity to make 

arrangements for compliance with this Service Bulletin in accoraance 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, serial number, current owner's name and address. 

Corrections/changes should be directed to: 

Piper Aircraft Corporation 

Attn: Customer Service 

P. 0. Box 1328 

Vera Beach, Florida 32961-1328 

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SERVICE BULLETIN NO. 5280 PAGE 5 OF 6 

~ NA$1, 311&4-4 (()-, C.aatt• OF -pACrOirf T'AL4n!T Sitr\al 

sa.. .... Scnw WS51111 .. (On~ Cl ~ 'T'M.ln.c" Strut) 

~II::: .., , , w vn er ••• LJIIIT mna •WMax 

1. Securely tape a sheet of thin 1/4 inch graph paper to the lower 11 inches 

of the top and bottom surfaces on all wing lift struts. 

2. Using a Maule "Fabric Tester" and holding tool normal to strut contour, 

apply pressure at a scale reading of 80 in each of the grid blocks. 

3. Remove the paper and inspect the lift strut tubes. A perceptible dent will 

appear if internal corrosion is present. If any dents are found, be 

certain the dents are in the metal by carefully removing the paint. 

a. Lift strut tubes indicating the presence of any perceptible dent in 

the metal must be rep laced with new lift strut assembly before further 

flight. 

b. If no dents appear in the metal, the lift strut may be considered 

airworthy. 

· NOTE: 

Further internal corrQsion may be impeded per the fol lowing procedure: 

a. Remove lift strut from aircraft. 

b. Inject one quart of Valoil, Lionoil Multi- Purpose L-1, Linseed 

Oil, Paralketone or any alternate preservati ve conforming to 

Federal Specification TT- S-1760, into the bo lt hole at the top of 

the strut. 

c. Plug the bolt holes and slosh oil until interior of strut is 

thoroughly coated. 

d. Drain oil from strut (through bolt holes) and install MS51861 -44 

sheet metal screw, as shown, for future identification. 

e. Reinstall strut to aircraft and rig. 

4. Record lift strut inspection in aircraft logbook. 

SKETCH "A·· 
BULLETIN NO. 5280 PAGE 6 OF 6 

PART NUMBER SUPPLEMENT 

E-2 Series 

J-2 Series, Cub .-:-.;;.·:. -. 500 through 1975 '··· _ -_.., _ .-85546-2 Rear 1, 2 - -... :;·'t ;-....;. :.~ = ·· =·=· :.: ... ~~ .i:.: :- ... . -;;.;, :..;.. .. :~ ~~ 85545-2 Fwd ~.=;: .. ·- 1,2 

J- 3, NE-1, L-4 Cub 

J-4 Series Coupe 

J-5, J-5C, L-14, AE-1, 

HE-1 Series Cub Cruiser 

PA- 11 Series, 

Cub Special 

PA- 12 Series, 

Super Cruiser 

PA-14 Series, 

Fami 1 y Cruiser 

PA-15 Vagabond 

ALL 

4-401 through 4-1649 

5- 1 through 5-1389 

11-1 through 11-1678 

12-1 through 12-4036 

14-1 through 14-523 

15-1 through 15-388 - .. .. -

85548-2 Rear 1 t 2 

85547-2 Fwd 1, 2 

85550- 2 Rear 1, 2 

85549-2 Fwd 1 t 2 

85553-2 Rear 1 '2 

85552-2 Fwd 1, 2 

85555-2 Rear ·1 t 2 

85554-2 Fwd 1, 2 

85553-2 Rear 1, 2 

85552-2 Fwd 1, 2 

85553-2 Rear 1 '2 

85552-2 Fwd 1 '2 

85557-2 Rear 1 t 2 

85556-2 Fwd 1 t 2 -.. . - --- . . - ~ -· PA-16 Clipper - - - · - - - ¥ 

16-1 through 16-736 . -=-- · :._ 85559-2. Rear -- . .- 1,2 

PA-17 Vagabond 

PA-20 Series, Pacer 

PA-22 Series, _ Tri-Pacer/ Colt 

PA- 25- 150 Pawnee 

17-1 through 17-215 

20-1 through 20-1121 

22-1 through 22-9848 

25-1 through 25-731 

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,.. ~ ,_ 85558-2· Fwd : ;;..::~~ ~ 1 , 2 ;.-J 

· -- ··. 85557-2 Rear~ ' ··:: 1, -- ~ 

- - 85556-2' Fwd ~ -' 1", 2 ·'='• · .·oJ - - ~ .-- ., - ... _ ,. _.,.. ~~4r-- ,...; t. .. ~-.!• • 

- -- ., ... -' ·" ' .. ... ~ - ·- -- -·: 85559-2' Rear ": --:.. 1,2 

:.- 85560-2 Fwd·--, __ ; · .-._ 1 , 2 

' 85559-2 Rear , '2 

85560- 2 Fwd , ., t'-

61046-6 2,4 

PA-25-235/260 .Pawnee 25~2000 through 25-8156024 640'38-2 2,4 

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1. All strut assemblies include forks. 

2. Struts come painted with prime coat only. 

3. Owners/ operators must call or write Piper Customer Services for quotes on 

price and delivery date. 

4. PA- 25 Series lift struts are single piece for each side of aircraft. 

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