Piper SB 528: Revision D, text

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Page 1OCROpen in PDF

PIPER -per Aircraft Corporation

•uro Beach, Florida, U.S.A.

SERVICE No. 528D

BULLETIN ************* *******

PIPER CONSIDERS

COMPLIANCE MANDATORY ********************** *** Date October 19, 1990 S (Service Bulletin No. 528D supersedes and voids Service Bulletin No. 528C, dated October 11, 1989) This Service Bulletin is divided into Two (2) PARTS. Check each PART for Purpose, Instructions, and Compliance Time.

SUBJECT: Wing Lift Strut Assembly Inspection/Replacement REASON FOR REVISION: To revise Compliance Time, Purpose, Instructions, and to announce the availability of new sealed lift struts MODELS AFFECTED: SERIAL NUMBERS AFFECTED:

All aircraft incorporating ALL steel wing lift struts (See note) J-2 Series, Cub 500 through 1975 J-3, NE-1, L-4 Cub ALL J-4 Series Coupe 4-401 through 4-1649 J-5, J-5C, L-14, AE-1, HE-1, Series 5-1 through 5-1389 Cub Cruiser PA-11 Series, Cub Special 11-1 through 11-1678 PA-12 Series, Super Cruiser 12-1 through 12-4036 PA-14 Series, Family Cruiser 14-1 through 14-523 PA-15 Vagabond 15-1 through 15-388 PA-16 Clipper 16-1 through 16-736 PA-17 Vagabond 17-1 through 17-215 PA-20 Series, Pacer 20-1 through 20-1121 PA-22 Series, Tri-Pacer/Colt 22-1 through 22-9848 PA-25 Series, Pawnee 25-1 through 25-8156024 All variations of the PA-18 Series and PA-19 Series are no longer Affected by this Service Bulletin and are covered by Piper Service Bulletin 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. 528D PAGE 2 OF 6 PART I 015" PURPOSE: The five (5) year repetitive inspection interval, required by compliance with Service Bulletin No. 528C may not be adequate for timely detection of serious wing lift strut corrosion. Eventually, undetected corrosion will 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 inspection or the first use of a new lift strut.

PART I of this Service Bulletin provides an inspection and treatment procedure to detect and treat the corrosion which may be present in the wing lift strut assemblies.

COMPLIANCE IIME: Before next flight and each twelve (12) month period therearter.

If the inspection requirements of Service Bulletin No. 910A or 528C have been accomplished within the last twelve (12) months or if the wing lift struts are new, and have been installed within the last twelve (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 Bulletin, 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 struts and accomplish the inspection per "Inspection Procedure" on Sketch "A"

- CAUTION:

All aircraft utilizing "cuffs" at the wing lift strut roots (top and/o bottom) should 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.

Turn each wing lift strut upside down and tap gently. This procedure is necessary to remove any water, debris or corrosion particles.

Inspect lift struts according to "Inspection Procedure" in Sketch "A Lift struts indicating presence of internal corrosion or which fail the "Inspection Procedure" must be replaced with new sealed wing lift struts.

Should corrosion be apparent from the outside (rust pin holes or large rust stained areas), strut must be replaced even if strut passes the "Inspection Procedure" NOTE The new sealed lift struts may be installed one at a time during the

(24) months compliance time (PART II) provided the repetitive inspection 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 Service Bulletin.

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SERVICE BULLETIN NO. 528D PAGE 3 OF 6 INSTRUCTIONS (CONT'D):

Upon completion of the "Inspection Procedure" and treatment, reinstall Treat (corrosion impediment) each wing lift strut per the "Inspection Procedure" note on Sketch "A" coincide with each inspection as required by the compliance time above. Treatment (corrosion impediment) must

8. Check aircraft rigging and adjust as necessary. (Use appropriate Piper

9. Make a logbook entry of compliance with PART I of this Service Bulletin. Service Memo and Owner Handbook as required to accomolish proper rigging.)

MATERIAL REQUIRED: Not applicable

PART II PURPOSE: will eliminate the concern for internal corrosion in wing lift struts. struts also feature an improvement in the design of the lift strut fork which Piper has developed an improved wing lift strut which The new eliminates the requirements of Piper Service Bulletin No. 1570.

Service Bulletin. lift struts at a date not to exceed (24) months from the effective date of this It will be necessary to replace existing wing lift struts with new sealed wing COMPLIANCE TIME: this Service Bulletin or as required by PART I inspection. Upon reaching (24) months from the effective date of INSTRUCTIONS:

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

Remove the old wing lift struts.

Refer to the Part Number Supplement on Page 6 of this Service Bulletin to aircraft. determine the proper wing lift strut part number for the appropriate incorporate the latest configuration fork bolt assembly. Inspect clamps, hardware, fairleads and jury struts for condition and replace as necessary. Note that the new Piper sealed lift strut assemblies

5. Install, rig, and adjust the new sealed lift strut assemblies as required. Note: Use appropriate Piper Service Memo and Owners Handbook as required to accomplish proper rigging.

6. Install "No Step" Decal, Piper Part Number 80944-02, on each wing lift the airplane. direction that the "No Step" caution can be read when entering and leaving which contrasts with the airplane color, on each wing lift strut approximately six (6) inches from the bottom of the struts, and in such a the statement "NO STEP" in one (1) inch minimum high letters, in a color strut approximately six (6) inches from the bottom of the struts, or paint

7. Make appropriate logbook entry of compliance with PART II of this Service Bulletin for strut (s) replaced.

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SERVICE BULLETIN NO. 528D PAGE 4 OF 6 MATERIAL REQUIRED: Supplement on Page 6 of this Service Bulletin when ordering the new sealed lift struts: four (4) each per aircraft, "No Step" Decal, Piper Part Number 80944-02. As required by inspection, refer to the Part Number AVAILABILITY OF PARTS: Your Piper Field Service Facility.

EFFECTIVITY DATE: This Service Bulletin is effective upon receipt.

SUMMARY: listed on the Part Number Supplement sheet on Page 6, for at least 180 days Service Bulletin. Special pricing is in effect for the sealed lift struts as There is no factory participation applicable to this from the effective date of this Service Bulletin.

Please contact your Factory Authorized Piper Field Service Facility to make arrangements for compliance with this Service Bulletin in accordance with the compliance time indicated.

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 Vero Beach, Florida 32961-1328 ...

...... ...

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SERVICE BULLETIN NO. 5280 PAGE 5 OF 6

VIEW OF MALLE BARSIC TATOES | Rival NAS1738844 (On Cantarine CI FACTORY TRILATED Struc | Sheat Metal Sanse MSS1881-44 (On Centerine Of FIELD TREATED" Stru)

I VIEW OF FRONT LET STEUT ASSEMBLY Rivet NAS1738844 (On Canterine OF FACTORY TREATED Strut) Shest Matal Screw MS8186144 (On Centerine Of "FEELS TREATED* Strut)

LY W CE BRAB LIT STUT ASSEMBLY

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.

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 replaced 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 corrosion may be impeded per the following procedure:

a . Remove lift strut from aircraft.

b. Inject one quart of Valoil, Lionoil Multi-Purpose L-1, Linseed Oil, Paralketone or any alternate preservative conforming to Federal Specification TT-S-176D, into the bolt hole at the top of the strut.

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"

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ERVICE BULLETIN NO. 5280 PAGE 6 OF 6 * 0377

PART NUMBER SUPPLEMENT Mode l Serial Number * Part Number E-2 Series Cub 1] through 36 361 (Note 3) - 1,2,3 J-2 Series, Cub 500 through 1975 85546-2 Rear 1,2 = 85545-2 Fwd 23-1,2 J-3, NE-1, L-4 Cub ALL 85548-2 Rear 1,2 85547-2 Fwd 1,2 J-4 Series Coupe 4-401 through 4-1649 85550-2 Rear 1,2 85549-2 Fwd 1,2 J-5, J-5C, L-14, AE-1, 5-1 through 5-1389 85553-2 Rear 1,2 HE-1 Series Cub Cruiser 85552-2 Fwd 1,2 PA-11 Series, 11-1 through 11-1678 85555-2 Rear 1,2 Cub Special 85554-2 Fwd 1,2 PA-12 Series, 12-1 through 12-4036 85553-2 Rear 1,2 Super Cruiser 85552-2 Fwd 1,2 PA-14 Series, 14-1 through 14-523 85553-2 Rear 1,2 Family Cruiser 85552-2 Fwd 1,2 PA-15 Vagabond 15-1 through 15-388 85557-2 Rear 1,2 85556-2 Fwd 1,2 PA-16 Clipper 16-1 through 16-736 - 85559-2 Rear 1,2 = 85558-2: Fwd = 1,2 --7 PA-17 Vagabond 17-1 through 17-215 85557-2 Rear 1,2 85556-2 Fwd m 1,2 00 PA-20 Series, Pacer 20-1 through 20-1121 85559-2 Rear *- 1,2

- 85560-2 Fwd • 1,2 PA-22 Series, 22-1 through 22-9848 85559-2 Rear 1,2 Tri-Pacer/Colt 85560-2 Fwd - 1,2 PA-25-150 Pawnee 25-1 through 25-731 61046-6 2,4 PA-25-235/260 Pawnee - 25-2000 through 25-8156024 64038-2 2,4 NOTES

1. All strut assemblies include forks.

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.