SERVICE LETTER NO. 1327G

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Piper Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, FL, U.S.A. 32960 SERVICE NO. 1327G LETTER Date: September 18, 2024 Service Letter (SL) 1327G supersedes SL 1327F in its entirety. Aircraft that were previously made compliant with SL 1327F are in compliance with SL 1327G. SUBJECT: REASON FOR REVISION: MODELS AFFECTED: PA-28-140 Cherokee 140 (S) WING WALK MODIFICATION AND INSPECTION To add models and serial numbers. To correct model name. | SERIAL NUMBERS AFFECTED: 28-20001 thru 28-26946 28-7125001 thru 28-7725290 28-1 thru 28-4377 PA-28-150 Cherokee 150 PA-28-160 Cherokee 160 28-1 thru 28-4377 PA-28-180 Cherokee 180 PA-28-235 Cherokee 235 PA-28-151 Cherokee Warrior PA-28-161 Cadet PA-28-161 Warrior II PA-28-161 Warrior III PA-28-181 Archer II PA-28-181 Archer III PA-28-181 Piper Pilot 100i PA-28-201T Turbo Dakota PA-28R-180 Arrow 28-671 thru 28-5859, 28-7105001 thru 28-7205318 28-E13, 28-7305001 thru 28-7505260 28-10001 thru 28-11378, 28-7110001 thru 28-7210023, 28E-11, 28-7310001 thru 28-7710089 28-7415001 thru 28-7715314 2841001 thru 2841365 28-7716001 thru 28-8216300, 28-8316001 thru 28-8616057 2816001 thru 2816109 2816110 thru 2842420 28-7690001 thru 28-8690056, 28-8690061, 28-8690062, 2890001 thru 2890205 2890206 thru 2890231, 2843001 and up 2881041, 28020001 and up 28-7921001 thru 28-7921095 28R-30002 thru 28R-31270, PA-28R-200 Arrow 28R-7130001 thru 28R-7130013 28R-35001 thru 28R-35820, PA-28R-200 Arrow II PA-28R-201 Arrow III PA-28RT-201 Arrow IV PA-28R-201T Turbo Arrow III 28R-7135001 thru 28R-7135229 28R-7235001 thru 28R-7635545 28R-7737002 thru 28R-7837317, 2837001 thru 2837061 2844001 thru 2844185 28R-7918001 thru 28R-8218026 28R-7703001 thru 28R-7803373, 2803001 thru 2803012 ATA/JASC: 5720 (OVER) | SERVICE LETTER NO. 1327G PAGE 2 of 7 PA-28RT-201T Turbo Arrow IV PA-28-236 Dakota PA-32-260 Cherokee Six 260 PA-32-300 Cherokee Six 300 PA-32S-300 Cherokee Six Seaplane PA-32R-300 Lance PA-32RT-300 Lance II PA-32RT-300T Turbo Lance II PA-32-301 Saratoga PA-32-301T Turbo Saratoga PA-32-301FT Piper 6X PA-32-301XTC Piper 6XT PA-32R-301 Saratoga SP PA-32R-301 Saratoga II HP PA-32R-301T Turbo Saratoga SP PA-32R-301T Saratoga II TC PA-34-200 Seneca PA-34-200T Seneca II PA-34-220T Seneca III 28R-7931001 thru 28R-8631005, 2831001 thru 2831038 28-7911001 thru 28-8611008, 2811001 thru 2811050 32-1 thru 32-14, 32-16 thru 32-20, 32-22 thru 32-1297, 32-7100001 thru 32-7800008 32-15, 32-21, 32-40000 thru 32-40974, 32-7140001 thru 32-7940290 32S-15, 32S-40000 thru 32S-40974, 32S-7140001 thru 32S-7240137 32R-7680001 thru 32R-7880068 32R-7885002 thru 32R-7985106 32R-7787001, 32R-7887002 thru 32R-7987126 32-8006002 thru 32-8606023,3206001 thru 3206019, 3206042 thru 3206044,3206047, 3206050 thru 3206055, 3206060 32-8024001 thru 32-8424002 3232001 thru 3232074 3255001 thru 3255051 32R-8013001 thru 32R-8613006, 3213001 thru 3213028, 3213020 thru 3213041 3213029, 3213042 thru 3213103, 3246001 thru 3246244 32-8029001 thru 32-8629008, 3229001 thru 3229003 3257001 thru 3257493 34-E4, 34-7250001 thru 34-7450220 34-7570001 thru 34-8170092 34-8133001 thru 34-8633031, PA-34-220T Seneca IV 3433001 thru 3433172, 3448001 thru 3448037 3448038 thru 3448079, 3447001 thru 3447029 3449001 thru 3449514 PA-34-220T Seneca V COMPLIANCE TIME: APPROVAL: PURPOSE: Initial compliance with Part I is to coincide with the next regularly scheduled maintenance event, but not to exceed the next 50 hours time in service. Thereafter, recurring compliance with Part II is required at an interval of 50 hours time in service. Compliance with Part III is required upon discovery of cracks in the wing skin pan. The engineering aspects of this service document have been shown to comply with the applicable Federal Aviation Regulations and are FAA approved. Cracks may be discovered in the doublers (aka wing skin pan) that reinforce the wing skin, localized around the wing walkway. Aircraft with this condition are considered airworthy and may continue to operate, provided that a recurring inspection is performed on the adjacent upper wing skin. However, cracks may appear in areas normally obscured by the wing walkway material. This service letter provides a modification to the wing walkway by removing and replacing part of the wing walkway material to facilitate the required recurring inspection. SERVICE LETTER NO. 1327G INSTRUCTIONS: Part I. 1. 2. Initial Inspection Locate the wing skin pan, as shown in Figure 1. Inspect the pan from below for cracks. • If cracks are found in the pan, proceed to Part III. • If no cracks are found, no modification is required at this time. • Make a logbook entry documenting compliance with Part I of this service letter. PAGE 3 of 7 Part II. 1. 2. Recurring Inspection If the modification described in Part III of this service letter has not been performed, locate and inspect the pan from below for cracks, as shown in Figure 1. Otherwise, proceed to step 2. • If cracks are found in the wing skin pan, proceed to Part III. • If no cracks are found, no modification is required at this time. Proceed to step 3. If the modification described in Part III has been performed on this aircraft, inspect the wing skin at the location(s) where the clear tape has been applied. • • Verify there is no cracking/damage in the wing skin local to the walkway. Verify there is no permanent contour deformation in the wing skin. 3. If cracks or other damage are discovered in the wing skin, replacement of the wing skin and doublers is required. Make a logbook entry documenting the external inspection of wing walk area per Part II of this service letter. Part III. Modification 1. Locate the wing walk, as shown in Figure 2. 2. 3. 4. Remove two (2) inches of wing walk material at the location(s) indicated in Figure 2 where cracking has been discovered. While the wing walk material is removed, inspect the wing skin for cracks. If cracks are found, replacement of the wing skin and pan is required. Otherwise proceed to step 3.