SERVICE BULLETIN NO. 1354
Piper PA-44 Seminole · Service Bulletins
Overview
This Service Bulletin No. 1354 addresses potential cracks in the fuselage station 247 bulkhead of the Piper PA-44-180 Seminole and PA-44-180T Turbo Seminole aircraft. Compliance with this bulletin is mandatory for affected aircraft, particularly those with 2,400 or more hours of time in service. The bulletin outlines inspection procedures and modification requirements to ensure the structural integrity of the aircraft. If cracks are found during inspection, a replacement kit is available to rectify the issue. The document emphasizes the importance of addressing any structural cracks before flight to maintain safety and compliance with FAA regulations.
- Initial inspection compliance required within 100 hours for aircraft with 2,400+ hours TIS.
- Recurring inspections every 500 hours TIS until modification is completed.
- Cracks in the bulkhead must be repaired before the next flight.
- Installation of the replacement kit eliminates further inspection requirements.
- Logbook entries are mandatory for compliance documentation.
Document
Source
Originally published by s3.amazonaws.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Service Bulletins
- Year
- 2023
- Pages
- 4
- File size
- 297 KB
- Publisher
- s3.amazonaws.com
Most owners only have the POH. Here's the essential set for the Piper PA-44 Seminole.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
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- PIPER PA-44 SEMINOLEChecklist
- TYPE-CERTIFICATE DATA SHEET No. EASA.IM.A.232 For Piper PA-44Pilot's Operating Handbook
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- PIPER PA-44 SEMINOLEAvionics Manual
In this document
Compliance Time
For affected aircraft with 2,400 or more hours time in service (TIS), initial compliance with the inspection is required within the next 100 hours. Following this, a recurring inspection must occur every 500 hours TIS until compliance with the modification is achieved.
Inspection Procedures
The inspection involves gaining visual access to the forward face of the FS 247 bulkhead and examining the specified inspection area for cracks, particularly near rivet heads. If cracks are found, the aircraft must not be flown until repairs are made.
Modification Requirements
If cracks are discovered, the aircraft owner must order and install the Frame Assy Replacement Kit (P/N 88686-701) to eliminate the recurring inspection requirement. A logbook entry must be made to document compliance.
Warnings and Safety Notes
The bulletin includes critical warnings against flying with known structural cracks and emphasizes that any discovered cracks must be repaired before the next flight.
Material Required
One Kit – Frame Assy Replacement – Aft Fuselage, Piper P/N 88686-701 is required per aircraft for compliance.
Safety notes
- Flight with known cracks in the aircraft structure is not allowed.
- An airplane with a crack in its structure does not meet its type design nor possess its type design strength.
Full document text
(OVER) Date: October 16, 2023 (M) SERV I CE B U L L ETIN NO. 1354 PIPER CONSIDERS COMPLIANCE MANDATORY ATA/JASC: 5310 Piper Aircraft, I nc. 2926 Piper Drive Vero Beach, FL, U.S.A. 32960 SUBJECT: FUSELAGE STATION 247 BULKHEAD INSPECTION MODELS AFFECTED: SERIAL NUMBERS AFFECTED: PA-44-180 Seminole 44-7995001 through 44-8195026; 4495001 through 4495013; 4496001 through 4496561 PA-44-180T Turbo Seminole 44-8107001 through 44-8207020 COMPLIANCE TIME: Part I. Inspection For affected aircraft with 2,400 or more hours time in service (TIS), initial compliance is to occur within the next 100 hours. Thereafter, a recurring inspection shall occur every 500 hours TIS, until compliance with Part II has been accomplished. NOTE: Installation of the Kit – Frame Assy Replacement – Aft Fuselage, Piper part number (P/N) 88686-701, in accordance with Part II, will relieve the recurring inspection requirement in Part I. Part II. Modification Compliance with Part II will relieve the recurring inspection requirements described in Part I. APPROVAL: The engineering aspects of this service document have been shown to comply with the applicable Federal Aviation Regulations and are FAA approved. PURPOSE: Cracks may develop in the bulkhead assembly Piper P/N 86462-002, located at fuselage station (FS) 247, on the affected aircraft. This service bulletin provides instructions to inspect the affected bulkhead for cracks. If cracks are discovered, a kit is available to replace the frame assembly. NOTE: Installation of the kit will eliminate the recurring inspection requirement in Part I of this service bulletin. SERVICE BULLETIN NO. 1354 PAGE 2 of 4 INSTRUCTIONS: 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. Part I. Inspection WARNING: FLIGHT WITH KNOWN CRACKS IN THE AIRCRAFT STRUCTURE IS NOT ALLOWED. WARNING: AN AIRPLANE WITH A CRACK IN ITS STRUCTURE DOES NOT MEET ITS TYPE DESIGN NOR POSSESS ITS TYPE DESIGN STRENGTH. ANY CRACKS DISCOVERED IN THE AIRCRAFT STRUCTURE MUST BE REPAIRED PRIOR TO THE NEXT FLIGHT. NOTE: Before inspecting, wipe inspection surfaces clean using a soft cloth dampened with isopropyl alcohol, mineral spirits, naphtha, or other suitable cleaning agent. NOTE: Perform the inspections described in this service bulletin using a 10X magnifier, a mirror and a suitable light source, or other equipment capable of providing equal or better resolution. 1. Gain visual access to the forward face of the FS 247 bulkhead, as shown in Figure 1. Carefully examine the area identified as the “inspection area,” with emphasis on the two rivet locations specifically identified. Inspect for cracks near rivet heads. Additionally, inspect the formed radius of the bulkhead directly above these rivets for cracks. • If no cracks are found, proceed to Step 2. • If cracks are found, then comply with Part II prior to next flight. 2. Make a logbook entry documenting compliance with Part I of this service bulletin. Part II. Modification 1. Order and install Kit – Frame Assy Replacement – Aft Fuselage, Piper P/N 88686-701. 2. Make a logbook entry documenting compliance with Part II this service bulletin. SERVICE BULLETIN NO. 1354 PAGE 3 of 4 Figure 1 PA-44-180/T Seminole Aft Fuselage Frame Inspection FS 247.125 A A SIDE VIEW PA-44-180 (TYPICAL) VIEW A−A LOOKING AFT AT F.S. 247.125 (TYPICAL) INSPECTION AREA INSPECTION AREA SERVICE BULLETIN NO. 1354 PAGE 4 of 4 MATERIAL REQUIRED: One (1) each, as required, Kit – Frame Assy Replacement – Aft Fuselage, Piper P/N 88686-701, per aircraft. AVAILABILITY OF PARTS: Your Piper Approved Service Center EFFECTIVITY DATE: This service bulletin is effective on October 18, 2023. 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. Attn: Customer Service 2926 Piper Drive Vero Beach, FL 32960 or: CustomerService@piper.com Please include in subject line: “Aircraft ownership update”