SERVICE BULLETIN NO. 1375A

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Date: November 29, 2022 (S) SERVICE BULLETIN NO. 1375A PIPER CONSIDERS COMPLIANCE MANDATORY Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, FL, U.S.A. 32960 (OVER) ATA/JASC: 3210 Service Bulletin (SB) 1375A supersedes SB 1375 in its entirety. Aircraft that were previously made compliant with SB 1375 are in compliance with SB 1375A. SUBJECT: PERIODIC REPLACEMENT OF MAIN LANDING GEAR ATTACHMENT HARDWARE REASON FOR REVISION: SB 1375A adds a bolt hole inspection. MODELS AFFECTED: SERIAL NUMBERS AFFECTED: PA-28-140 Cherokee Cruiser 28-20001 through 28-26946; 28-7125001 through 28-7725290 PA-28-150 Cherokee 28-03; 28-1 through 28-4377, and 28-1760A PA-28-160 Cherokee 28-03; 28-1 through 28-4377, and 28-1760A PA-28-180 Cherokee 28-03; 28-671 through 28-5859; 28-7105001 through 28-7205318 PA-28-235 Cherokee Pathfinder 28-10001 through 28-11378; 28-7110001 through 28-7710089; 28E-11 PA-28-236 Dakota 28-7911001 through 28-8611008; 2811001 through 2811050 PA-28-151 Warrior 28-7415001 through 28-7715314 PA-28-161 Cadet 2841001 through 2841365 PA-28-161 Warrior II 28-7716001 through 28-8616057; 2816001 through 2816109 PA-28-161 Warrior III 2816110 through 2816119; 2842001 and up PA-28-180 Archer 28-E13; 28-7305001 through 28-7505260 PA-28-181 Archer II 28-7690001 through 28-8690056; 28-8690061; 28-8690062; 2890001 through 2890205 PA-28-181 Archer III 2890206 through 2890231; 2843001 through 2843999; 2881001 and up PA-28-181 Piper Pilot 100i 28020001 and up PA-28-201T Turbo Dakota 28-7921001 through 28-7921095 PA-32-260 Cherokee Six 32-03; 32-04; 32-1 through 32-1297; 32-7100001 through 32-7800008 PA-32-300 Cherokee Six 32-15; 32-21; 32-40000 through 32-40974; 32-7140001 through 32-7940290 SERVICE BULLETIN NO. 1375A PAGE 2 of 6 PA-32-301 Saratoga 32-8006002 through 32-8606023; 3206001 through 3206019; 3206042 through 3206044; 3206047; 3206050 through 3206055; 3206060 PA-32-301T Turbo Saratoga 32-8024001 through 32-8424002 PA-32-301FT Piper 6X 3232001 through 3232074 PA-32-301XTC Piper 6XT 3255001 through 3255051 COMPLIANCE TIME: For affected aircraft which have accrued 2,000 hours time in service (TIS) or seven (7) calendar years TIS, initial compliance is to coincide with the next regularly scheduled maintenance event, but not to exceed the next 100 hours TIS. Thereafter, compliance shall be at a recurring interval of 2,000 operating hours TIS or 7 calendar years TIS, whichever occurs first. 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 for the affected aircraft, the landing gear mounting hardware is subject to metal fatigue and corrosion. Failure of this hardware could result in a landing gear collapse. This service bulletin provides instructions for the recurring replacement of this hardware. INSTRUCTIONS: NOTES: • Temporary removal of some interior components and/or access panels may be required in order to accomplish the instructions described in this service letter. • Prior to inspection, wipe surfaces clean using a soft cloth dampened with isopropyl alcohol, mineral spirits, naphtha, or other suitable cleaning agent compatible with cured paints and primers. • Refer to the appropriate section of the applicable Airplane Maintenance Manual or Service Manual for the procedures to jack the airplane and for model-specific instructions for the removal and installation of the main landing gear. • These instructions apply to both the left and right sides of the aircraft. The main landing gear (MLG) are attached to the aircraft with threaded fasteners that pass through mounting flanges on the strut cylinder and the upper and lower flanges of the main wing spar, as depicted in the illustration below. On some of the affected aircraft, additional threaded fasteners pass through the web of the main wing spar. Replace the MLG mounting hardware as described below. 1. Place the aircraft on jacks. 2. Remove the fairing from around the strut cylinder housing and the access plate located on the bottom of the wing and to the rear of the housing by removing attaching screws. 3. Remove and discard all of the threaded fastener stack ups (which includes screws and bolts, as well as nuts and washers) that attach the MLG to the main wing spar. (See “Figure 1” on page 5.) SERVICE BULLETIN NO. 1375A PAGE 3 of 6 4. Bolt Hole Inspection NOTE: Unless stated otherwise, all dimensions are in inches. a. Measure the bolt holes common to the main wing spar and the landing gear cylinder (four holes through the lower spar flange and two through the spar web). Compare measured holes sizes against the acceptable maximum hole sizes shown in Table 1. • If all bolt holes do not exceed the values shown in Table 1, then no modification is required. Proceed to Step 5. • If one or more bolt holes exceed the values shown in Table 1, it may be possible to replace the factory original hardware with a 1/64 or 1/32 oversize repair bolt. provided the minimum dimensional requirements as out-lined in 4 b. 1) and / or 4 b. 2) are complied with Proceed to Step 4. b. NOTE: If bolts have signs of damage, they must be replaced and an eddy current inspection by a qualified NDT level III inspector is required to ensure the spar does not have crack indications. TABLE 2 PART NUMBERS AND HOLE SIZES OVERSIZE REPAIR BOLTS OR SCREWS Nominal Bolt Size Repair Bolt Size Repair Bolt Code (Through Web) Repair Screw Code (Through Flange) Minimum Bolt Hole Size Maximum Bolt Hole Size 1/4 1/64 oversize shank NAS6204-*X NAS7404-*X 0.2654 0.2664 1/32 oversize shank NAS6204-*Y NAS7404-*Y 0.2810 0.2820 3/8 1/64 oversize shank NAS6205-*X 0.3279 0.3289 1/32 oversize shank NAS6205-*Y 0.3435 0.3445 * Grip dash number in 0.625 inch increments. TABLE 1 MAXIMUM BOLT HOLE SIZES FACTORY SUPPLIED, CLOSE TOLERANCE BOLTS OR SCREWS Nominal Bolt Size Maximum Allowable