SERVICE BULLETIN NO. 1244C

The correct unit of measure is inch-pounds (in-lb), not foot-pounds (ft-lb): • For 5/16 inch diameter bolts, the correct torque is 160 to 200 in-lb. • For 3/8 inch diameter bolts, the correct torque is 360 to 390 in-lb. 1. Examine the aircraft maintenance records and/or logbook entries to determine if Kit P/N 764-998 (instructions labeled DWG 87584) has been installed on either wing of the aircraft. • If Kit P/N 764-998 has not been installed, then continue the inspection. Proceed to Step 2. • If Kit P/N 764-998 has been installed, determine the revision level of the kit instructions used prior to con- tinuing the inspection. • If one of the following are true, then proceed to Step 2: • The kit instructions used were DWG 87584 Rev. E or later. • The kit instructions used were DWG 87584 Rev. New, A or B. • The kit was installed on or before July 16, 2013. • If the kit instructions used were DWG 87584 Rev. C or D, or the revision cannot be determined, then: a) Remove the aft spar attach bolt. Discard the nut. Examine all of the hardware and the adjacent structure for any damage. b) Replace the nut and any damaged hardware; repair or replace any damaged mating surfaces. c) Reinstall the hardware (existing and/or replacements) using the correct torque values: • 5/16 inch diameter bolts – 160 to 200 in-lb • 3/8 inch diameter bolts – 360 to 390 in-lb d) Proceed to Step 2. SERVICE BULLETIN NO. 1244C PAGE 4 of 8 2. Remove wing inspection plates and fairings, as required, to gain visual access to the aft wing attach fittings. NOTE: The access and inspection provisions for the airplane are typically shown in the applicable maintenance/service manual. In maintenance manuals, see Chapter 6. In service manuals, see Section II. All access plates and panels are secured by either metal fasteners or screws. “Access plates and panels” includes all forms of covers, cowlings, fairings, plates, panels, tips, etc., which may be removed for access to any component or space. For the affected aircraft listed in Table 1 below, examine the lower wing skin, in the area aft of the main wing spar, and inboard of the main landing gear, for the presence of an access panel. See Figure 1. • If an access panel already exists in the area identified in Figure 1, proceed to Step 3. • If no access panel exists in the area identified in Figure 1, order and install Piper kit, Inspection Access Hole, P/N 765-106. Proceed to Step 3. NOTE: Some of the aircraft listed in Table 1 may not have an access panel that provides direct access to the inspection area. This access panel, if installed, will be located on the lower wing skin, between the main wing spar and the aft wing spar, and inboard of the main landing gear. This region is depicted by the shaded area shown in Figure 1. This access panel will be oval shaped, roughly eight (8) inches long and 5.50 inches wide. If no access panel is installed at this location, then access panels may be installed by ordering and installing Piper Kit – Inspection Access Hole, P/N 765-106. Each kit provides parts and instructions to install one access panel under both left and right wings, at a location that provides direct visual access to the inspection area. 3. Identify the aft wing attach fittings which are riveted to the aft wing spars. See Figure 2. Using a solvent- based degreaser spray that conforms to SAE AMS 1525 (such as LPS Presolve Orange Degreaser) and/or an alkaline cleaner that complies with SAE AMS 1526 (such as Chemetall Ardrox 6333A), thoroughly clean the aft wing attach fittings and the adjacent wing spar structure (fore and aft sides of each wing spar), removing surface oil, grease, loose paint, and soil, followed by a clean water rinse and dry. 4. Carefully inspect for evidence of corrosion. The initial stages of corrosion are often masked by paint coatings and hidden under faying surfaces such as riveted lap joints. Since corrosion products occupy more volume than the original metal, carefully inspect these areas for irregularities such as blisters, flakes, chips, lumps, bulging skins and missing rivets. • If no corrosion is present, proceed to Part III. • If superficial corrosion is detected, remove per FAA Advisory Circular AC 43.12-1B, Chapter 6, Section 7. After removal of the corrosion, verify that all the affected areas meet or exceed the minimum thicknesses in Table 2. If the affected areas meet the minimums, then treat the corrosion with guidance from AC 43.13-1B, Chapter 6, Section 8 or 10. Then, paint the affected areas using a good quality aircraft primer that complies with MIL-PRF-23377 (such as Akzo-Nobel 10P30-5). Proceed to Part III. TABLE 1 MODELS THAT MAY NOT HAVE SUBJECT ACCESS PANEL PA-28-140 Cherokee Cruiser PA-28-150 Cherokee PA-28-160 Cherokee PA-28-180 Cherokee PA-28S-160 Cherokee PA-28S-180 Cherokee PA-28-235 Cherokee Pathfinder PA-28-180 Archer PA-32-260 Cherokee Six PA-32-300 Cherokee Six PA-32S-300 Cherokee Six Seaplane SERVICE BULLETIN NO. 1244C PAGE 5 of 8 • If corrosion is detected, and removal of corrosion in the affected areas will result in a part thickness in any loca- tion that is less than the minimum values shown in Table 2, structural repair is required. Proceed to Part II. NOTE: Thickness measurements shall be accomplished using a nondestructive inspection method, such as ultrasound, eddy current, or equivalent, provided that such method achieves a measurement accuracy of +/- 0.005 inches or better. Part II. Structural Repair 1. Order and install Kit, Corrosion – Aft Spar Rework, Piper P/N 764-998. Verify that the kit instructions are marked 87584, revision F or later. This kit provides parts and instructions to replace (via a splicing operation) the aft spar fitting, as well as the inboard 10.80 inches of the aft wing spar on both left and right hand sides. Corrosion damage beyond these areas may require additional and/or different repairs. Contact Piper Customer Service for guidance at (+1) 772-299-2141 or CustomerService@piper.com. Piper’s normal business hours are Monday through Friday, 7:30 a.m. to 4:30 p.m. (Eastern). 2. Proceed to Part III. Part III. Corrosion Protection 1. Treat the area identified in Figure 2, View A–A, with Ardrox (Dinitrol) AV8, or other MIL-PRF-16173 Class I or II, Grade 1 or 4 compliant Corrosion Preventive Compound (procure locally, or order Piper P/N 89500-800). The treatment may be brushed or sprayed. NOTE: Verify that all drain holes and drain passages are clear before proceeding. 2. Reinstall inspection plates and fairings. Perform a functional test of any system or component that may have been disconnected or removed. 3. Proceed to Part IV. Part IV. Make a logbook entry documenting compliance with this service bulletin. TABLE 2 PART DESCRIPTION MINIMUM THICKNESS Aft wing spar (aluminum) 0.060 inches Aft wing attach fitting (steel) 0.117 inches SERVICE BULLETIN NO. 1244C PAGE 6 of 8 Figure 1 Access Panel Location SEE DETAIL A WS 24.240 WS 36.920 WS 49.250 WS 64.590 VIEW LOOKING UP LEFT WING SHOWN (RIGHT WING OPPOSITE) DETAIL A INSPECTION AREA (CROSS HATCHED) WING SKIN PENETRATION FOR MAIN LANDING GEAR ACCESS PANEL, IF PRESENT OUTBD FWD MAIN WING SPAR SERVICE BULLETIN NO. 1244C PAGE 7 of 8 Figure 2 Aft Wing Attach Fitting OUTBD UP AFT WING SPAR AFT WING ATTACH FITTING APPLY CORROSION PREVENTATIVE COMPOUND TO FORE AND AFT SIDES OF FAYING SURFACES SHOWN BY CROSSHATCH VIEW A−A LOOKING AFT AT LEFT HAND SIDE A A WING ATTACH FITTING LOCATION SERVICE BULLETIN NO. 1244C PAGE 8 of 8 MATERIAL REQUIRED: Per aircraft: • LPS Presolve Orange Degreaser (SAE AMS 1525) or equivalent • Chemetall Ardrox 6333A (SAE AMS 1526) or equivalent • Akzo-Nobel 10P30-5 (MIL-PRF-23377) or equivalent NOTE: Verify that the instructions for Kit P/N 764-998 are marked DWG 87584, revision F or later. AVAILABILITY OF PARTS: Your Piper Approved Service Center (in table); procure locally (bullet list) EFFECTIVITY DATE: This service bulletin is effective upon receipt. SUMMARY: Please contact your Piper Approved Service Center 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. Att’n: Customer Service 2926 Piper Drive Vero Beach, FL 32960 or: CustomerService@piper.com Please include in subject line: “Aircraft ownership update” Quantity Piper P/N Nomenclature A/R * 89500-800 Ardrox (Dinitrol) AV 8 Corrosion Preventative Compound 1 † 764-998 (See note) Kit, Corrosion – Aft Spar Rework 1 ‡ 765-106 Kit, Inspection Access Hole * Quantity is as required † On condition, if required ‡ On condition, at the operator’s discretion