SERVICE BULLETIN NO. 1423A

If the bolt is secured, no further action is required. Proceed to step 4. If the bolt is not secured, further action is required. Proceed to step b. b. If the bolt head or nut has a missing/broken torque stripe or the bolt fails the off-torque test described in step a, perform the following: 1) Remove the attachment hardware (bolt, washer, and nut – retain/replace hardware on condition) to inspect the holes in the fittings for size and make sure no out-of-round condition exists outside of allowable limits. The specified hole size is as follows: • For 5/16 inch diameter bolts, the specified hole size is 0.3115–0.3135 inch diameter. • For 3/8 inch diameter bolts, the specified hole size is 0.3745–0.3765 inch diameter. If the holes meet the requirements specified above, proceed to step 2). If the holes do not meet the requirements specified, proceed to step 3). SERVICE BULLETIN NO. 1423A PAGE 4 of 8 2) If the holes meet the requirements specified above, inspect gap between the fittings. a) If gap is below 0.032 inches, reinstall the attachment hardware. Refer to chapter 57-40-00 of the applicable Piper AMM/SM for installation instructions. Then proceed to step 4. b) If gap is above 0.032 inches, but does not exceed 0.15 inches (before shimming with washers), install replacement hardware as required per Chart 1. Ensure that 1 1/2 threads of the bolt protrude from the nut. Then proceed to step 4. c) If the measured gap (before shimming with washers) exceeds 0.15 inches, contact an FAA designated engineering representative (DER) (or the equivalent authorized by civil aviation regulators outside the U.S.) for an approved repair before returning the airplane to service. The FAA website provides a DER directory that lists designees by their location and lists their credentials. Visit https://designee.faa.gov/#/designeeLocator for more details. 3) If the holes do not meet the requirements of step 1), perform the following action: a) Group A: If your aircraft is in Group A and does not meet the 5/16 hole requirements of step 1), contact an FAA designated engineering representative (DER) (or the equivalent authorized by civil aviation regulators outside the U.S.) for an approved repair before returning the airplane to service. The FAA website provides a DER directory that lists designees by their location and lists their credentials. Visit https://designee.faa.gov/#/designeeLocator for more details. b) Group B: (1) For 5/16 inch diameter bolt holes: If a 0.3724–0.3765 inch diameter reamed hole will clean out an out-of-round hole, open up the hole to 0.3724–0.3765 inch diameter and install 3/8 inch diameter replacement hardware, as specified in Chart 1. (2) For 3/8 inch diameter bolt holes, as well as 5/16 inch diameter bolt holes that do not meet the above criteria: If a 0.437–0.438 inch diameter reamed hole will clean out an out-of-round hole, order and install Piper Kit - Wing Aft Spar/Fuselage Attach FTG, Piper Part Number (P/N) 88365-002 (767-383), revision A or later. (3) If the above criteria cannot be met, contact an FAA designated engineering representative (DER) (or the equivalent authorized by civil aviation regulators outside the U.S.) for an approved repair before returning the airplane to service. The FAA website provides a DER directory that lists designees by their location and lists their credentials. Visit https:// designee.faa.gov/#/designeeLocator for more details. 4. Reinstall the fairings and make a logbook entry documenting compliance with this service bulletin. SERVICE BULLETIN NO. 1423A PAGE 5 of 8 CHART 1 ACCEPTABLE REPLACEMENT HARDWARE Model / Group Bolt Washer Nut Torque (in-lbs) Group A (Excluding PA-32S-300) AN5-6A or AN5-7A (1) NAS1149F0516P and / or AN960-516 (1) MS210045-5 200–225 Group A (PA-32S-300 Only) NAS1105-7 NAS1149F0516P and / or AN960-516 (1) MS210045-5 200–225 Group B (5/16 Inch Bolt) AN5-6A or AN5-7A (1) NAS1149F0516P and / or AN960-516 (1) MS210045-5 200–225 Group B (3/8 Inch Bolt) NAS464P6LA6 or NAS464P6LA4 (1) (2) NAS1149F0632P and / or NAS1149F0663P (1) MS21042-6 360–390 (1) Use bolt and thick or thin washer options listed as required to ensure that gap between fuselage and wing fittings is less than 0.032 inches, and 1 1/2 threads of the bolt protrude from the nut. (2) For PA-28-181 aircraft only, if a NAS464P6LA4 bolt is required, installation is only permissible when no gap exists between the fuselage and wing fittings. If a gap of 0.015 inch or greater exists, installation of a NAS464P6LA6 bolt, along with washers as required to ensure 1 1/2 threads protrude from the nut, is required. SERVICE BULLETIN NO. 1423A PAGE 6 of 8 Figure 1 Typical Panel Location (Under RH Wing) TYPICAL ACCESS PANEL LOCATION LOOKING UP AT INBOARD SECTION OF RH WING SERVICE BULLETIN NO. 1423A PAGE 7 of 8 Figure 2 Wing-to-Fuselage Attachment Bolt Location A A ATTACHMENT BOLT LOCATION LOOKING DOWN AT INBOARD SECTION OF RH WING VIEW A-A LOOKING FWD AT AFT SPAR ATTACHMENT RIGHT WING SHOWN (LEFT WING OPPOSITE) OUTBD UP INSPECT HERE AFT SPAR PLATE 0.56R MIN. AFT SPAR FITTING SERVICE BULLETIN NO. 1423A PAGE 8 of 8 MATERIAL REQUIRED: Per aircraft, as required: • Up to two (2) each, AN or NAS Series Bolts, see Chart 1 for applicable P/Ns • As required, AN or NAS Series Washer(s), see Chart 1 for applicable P/Ns • Up to two (2) each, MS Series Nuts, see Chart 1 for applicable P/Ns AVAILABILITY OF PARTS: Procure from your General Aviation Supplier or your Piper Approved Service Center – Find your local service center at https://www.piper.com/ EFFECTIVITY DATE: This service bulletin is effective on May 14, 2025. SUMMARY: There is no warranty participation for the accomplishment of the additional one hundred (100) hour re-torquing of the aft spar-to-fuselage attach hardware inspection introduced in this service bulletin. If the wing aft spar-to-fuselage attachment nut and bolt have loosened and any of the Instruction steps 1) through 3) are required, contact the Piper Warranty department for warranty compensation. 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. Attn: Customer Service 2926 Piper Drive Vero Beach, FL 32960 or: CustomerService@piper.com Please include in subject line: “Aircraft ownership update”