Piper SB 1289: Revision A

(OVER)

SERVICE

BULLETIN Date: July 21, 2016 (M) NO. 1289 SUBjECT: BULkhEad INSpECTIoN, FUSELagE STaTIoN

332.00 ModELS aFFECTEd: SERIaL NUMBERS aFFECTEd:

PA-31/PA-31-300/325 Navajo 31-2 through 31-900; 31-7300901 through 31-8312019 PA-31-350 Chieftain/T -1020 31-5001 through 31-5004;

31-7305005 through 31-8553002 CoMpLIaNCE TIME:

part I. Inspection For aircraft with 3,000 or more hours of time in service (TIS), initial compliance to occur within the next 500 hours TIS. Thereafter, a recurring inspection shall take place every 200 hours TIS.

part II. Modification Upon discovery of a crack during compliance with Part I, compliance with Part II must be accomplished prior to next flight.

NOTE: At owner/operator discretion, Part II of this service bulletin may be accomplished on an uncracked bulkhead. Compliance with Part II will relieve the recurring inspection requirements mandated by Part I, regardless of crack history.

appRoVaL: The engineering aspects of this service document have been shown to comply with the applicable Federal Aviation Regulations and are FAA approved.

pURpoSE: A review of service history reveals that cracks may develop in the bulkhead assembly located at FS 332.00, Piper part number (P/N) 40655-000. This service bulletin provides instructions to inspect this bulkhead for cracks. It also announces a modification kit, which, within the limits stated in this service bulletin, can be used to repair a cracked bulkhead.

pIpER CoNSIdERS CoMpLIaNCE MaNdaToRY ATA: 5312 Piper Aircraft, Inc.

2926 Piper Drive Vero Beach, FL, U.S.A. 32960

SERVICE BULLETIN No. 1289 pagE 2 of 7 SaFETY INTENT:

The safety intent of this service bulletin is twofold:

• The safety intent of Part I is to detect cracks in the FS 332.00 bulkhead which, if not identified and repaired, could propagate to a critical length. Such cracks could compromise the structural component’s capability to carry flight loads, with the potential to overload and fail adjacent structure, leading to the loss of control of the airplane.

• The safety intent of Part II is to provide a means to repair any cracks discovered in the FS 332.00 bulkhead, and, for an uncracked bulkhead, to provide a modification that will greatly reduce the likelihood of the specified cracks.

CoNFIgURaTIoN dESCRIpTIoN:

The incorporation of Part II of this service bulletin will result in reinforcing plates installed on the web of the FS

332.00 bulkhead, in an area that is common to the forward spar of the horizontal stabilizer. If cracks are present in the FS 332.00 bulkhead, it has been determined that these plates are a suitable repair. If no cracks are present in the FS 332.00 bulkhead, installation of these plates will greatly reduce the likelihood of the specified cracks.

INSTRUCTIoNS:

NOTE: Some steps in these instructions are identified as “Required for Compliance” (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), the steps identified as RC must be done to comply with the AD. Steps not identified as RC are recommended and may be deviated from, done as a part of other actions, or done with accepted methods different from those given in SB, if the RC steps can be done and the airplane can be put back in a serviceable condition.

NOTE: Temporary removal of some interior components and/or access panels may be required in order to accomplish the instructions described in this service bulletin.

NOTE: These instructions utilize the templates shown in Figure 2 for two purposes: In Part I, the templates are used to identify the area to be inspected for cracks; in Part II, the templates are used to determine whether Piper Kit P/N 88578-001 (Kit – Sta 332 Bulkhead Reinforcement – PA-31) is an acceptable repair for any cracks that are discovered.

part I. Inspection WaRNINg: FLIGHT WITH KNOWN CRACKS IN THE AIRCRAFT STRUCTURE IS NOT ALLOWED. AN

AIRPLANE WITH A CRACK IN STRUCTURE MAY NO LONGER MEET ITS TYPE DESIGN AND MAY NO LONGER POSSESS ITS TYPE DESIGN STRENGTH. ANY CRACKS DISCOVERED IN THE AIRCRAFT STRUCTURE MUST BE REPAIRED PRIOR TO THE NEXT FLIGHT.

1. RC – Print a copy of Figure 2 (at actual size, 100% scale); verify that the grid squares measure one (1) inch vertically and horizontally. Cut out “Template Top” and “Template Bottom.”

2. RC – Gain access to the aft face of the FS 332.00 bulkhead, as shown in Figure 1, View A–A. Completely remove all of the paint from the areas labeled “Inspection Area,” which is the area that the applicable template completely covers.

The paint must be removed using only chemical processes. Abrasives or other mechanical methods for paint removal will hide the existence of any cracks, making it impossible to do an accurate inspection. Use isopropyl alcohol to wipe clean the areas where paint was removed.

As shown in Figure 1, View A–A: position each template against the FS 332.00 bulkhead, with one horizontal edge making contact with the existing doubler, and the outboard curved edge of template aligned with outboard edge of doubler.

SERVICE BULLETIN No. 1289 pagE 3 of 7

3. RC – At the locations in Figure 1, View A–A labeled “Inspection Area,” perform a dye penetrant inspection of the FS 332.00 bulkhead for cracks using procedures described in Chapter 5, Section 5, of FAA Advisory Circular AC 43.13-1B.

• If a crack is found, proceed to Part II, Modification.

• If no cracks are detected during the inspection, wipe area of inspection clean with isopropyl alcohol.

Apply primer to the areas where paint was removed for inspection using MIL-PRF-85582D Type I Class C2 primer, or any of the epoxy primers shown in Table 1.

NOTE: At owner/operator discretion, installation of Kit 88578-001 may be accomplished on an uncracked bulkhead. This will relieve the recurring inspection requirements mandated by Part I.

4. Upon completion, make a logbook entry documenting compliance with Part I of this service bulletin.

TaBLE 1 aCCEpTaBLE EpoxY pRIMERS piper part No. Vendor product Name Vendor product Number 170-748 (was 279-179) PPG Aerospace PRC-DeSoto EWDE072A/B 279-506 Akzo Nobel Aerospace Coatings 10P8-10NF / EC-283 279-108 Akzo Nobel Aerospace Coatings 10P30-5 / EC-275 N/A Deft, Inc 44GN036 279-240 Axalta (formerly DuPont) Axalta Epoxy 13550S

SERVICE BULLETIN No. 1289 pagE 4 of 7 Figure 1 Inspection Location WL 0 FS

332.00 A A FWD UP WL

20.00 VIEW A−A LOOKING FORWARD AT FS 332.00

INSPECTION AREA ‘TEMPLATE TOP’

INSPECTION AREA ‘TEMPLATE BOTTOM’

INSPECTION AREA ‘TEMPLATE TOP’

INSPECTION AREA ‘TEMPLATE BOTTOM’

BULKHEAD

SERVICE BULLETIN No. 1289 pagE 5 of 7 Figure 2 Inspection Area Templates NOTE: Verify that the grid squares measure one (1) inch vertically and horizontally.

1.00 TYP

TEMPLATE TOP

1.00 TYP

TEMPLATE BOTTOM

SERVICE BULLETIN No. 1289 pagE 6 of 7 part II. Modification

1. RC – If any crack is found in the FS 332.00 bulkhead, print a copy of Figure 2 (at actual size, 100% scale); verify that the grid squares measure one (1) inch vertically and horizontally. Cut out the paper templates marked “Template Top” and/or “Template Bottom,” as applicable. Place the template(s) over the crack(s) as shown in Figure 1, View A–A: against the FS 332.00 bulkhead, with one horizontal edge making contact with the existing doubler, and the outboard curved edge of template aligned with outboard edge of doubler.

If each crack is completely covered by the applicable template, proceed as follows: Measure distance “D” from each crack tip to the edge of the nearest hole, as shown in Figure 3. Compare the distance “D” against the values shown in Table 2 for each crack tip.

a. If the measured distance “D” is at least as long as the value shown in Table 2 for all cracks, follow repair instructions described in Piper Kit 88578-001 Rev. B, dated Jun 23, 2016, “Bulkhead Reinforcement and Drag Angle Installation.” Upon completion, proceed to Step 2.

b. If the measured distance “D” is less than the value shown in Table 2 for any crack, or if any crack extends beyond the applicable template, Piper Kit 88578-001 Rev. B, dated Jun 23, 2016, is not a valid repair.

Some other FAA approved repair must be accomplished prior to next flight. At the operator’s discretion, contact Piper Customer Service at (+1) 772-299-2141 or customer.service@piper.com to request that a suitable repair be developed. Piper’s normal business hours are 7:30 am to 4:30 pm (Eastern US), Monday through Friday.

NOTE: At owner/operator discretion, installation of Piper Kit 88578-001 Rev. B, dated Jun 23, 2016, may be accomplished on an uncracked bulkhead. This will relieve the recurring inspection requirements mandated by Part I.

2. RC – Make a logbook entry documenting compliance with Part II of this service bulletin.

HOLE CRACK D Figure 3 Acceptable Distance from Crack to Drill Hole TaBLE 2

FEaTURE Minimum distance d Crack to Edge of drill hole 5/16 inch bolt hole 0.80 in MS20426AD4 series rivet hole 0.62 in

0.44 inch diameter light wires hole 0.80 in

SERVICE BULLETIN No. 1289 pagE 7 of 7 MaTERIaL REQUIREd: On condition, one (1) each, Kit – Sta 332 Bulkhead Reinforcement – PA-31, Piper P/N 88578-001, per aircraft aVaILaBILITY oF paRTS: Y our Factory Authorized Piper Service Facility EFFECTIVITY daTE: This service bulletin is effective upon receipt.

SUMMaRY: Please contact your Factory Authorized Piper Service Facility to make arrangements for compliance with this service bulletin in accordance with the compliance time indicated.

NoTE: Please notify the factory of any address/ownership corrections. Changes should include aircraft model, serial number, and current owner’s name and address.

Corrections and/or changes should be directed to:

PIPER AIRCRAFT, INC.

Attn: Customer Service 2926 Piper Drive Vero Beach, FL 32960