# AD 86-08-06 R1: Second Stage Turbine Rotor Assembly - Type: Airworthiness directive - Status: Current - Products: Honeywell International TPE331-25AA, TPE331-25AB, TPE331-25DA, TPE331-25DB, TPE331-25FA, TPE331-43-A, TPE331-43-B, TPE331-47-A, TPE331-55-B and TPE331-61-A - Effective: December 21, 1987 - Superseded by: Nothing supersedes this AD - Product type: Engine - Amendment: 39-5726 - Registered aircraft: 520 may be affected, by airframe or engine model (OpenAirDocs) - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/562FE15BBC5D7D508625683F005FE13D.0001 - DRS record last changed: May 30, 2024 - Page: https://openairdocs.org/ad/86-08-06-R1 ## The airworthiness directive 86-08-06 R1 GARRETT TURBINE ENGINE COMPANY (GTEC): Amendment 39-5275 as amended by amendment 39-5726. Applies to GTEC Model TPE331-25AA, -25AB, -25DA, -25DB, -25FA, -43A, -43BL, -47A, -55B, and -61A turboprop engines. Compliance is required as indicated unless already accomplished. To prevent uncontained failure of the second stage turbine rotor assembly, accomplish the following: (a) Radiographically inspect Part Number 865037-10 through -70 second stage turbine stator seal plate assemblies installed in TPE331-25AA, -25AB, -25DA, -25DB, -25FA, -43A, -43BL, -47A, and -55B turboprop engines within the next 200 engine hours time in service after April 18, 1986, or prior to the next 500 engine hours time in service since the last engine overhaul, whichever comes later, and at intervals not to exceed 300 engine hours thereafter in accordance with the accomplishment instructions of Garrett Alert Service Bulletin TPE331-A72-0522, Revision 2, dated July 1, 1987, except that useof prior issues of this service bulletin are acceptable for inspections conducted before the effective date of this amendment. (b) Radiographically inspect Part Number 865037-80 second stage turbine stator seal plate assemblies installed in TPE331-25AA, -25AB, -25DA, -25DB, -25FA, -43A, -43BL, -47A, and -55B turboprop engines and Part Number 865037-10 through -80 stator assemblies installed in TPE331-61A turboprop engines within the next 200 engine hours time in service after the effective date of this amendment, or prior to the next 500 engine hours time in service since the last engine overhaul, whichever comes later, and at intervals not to exceed 300 engine hours thereafter in accordance with the accomplishment instructions of Garrett Alert Service Bulletin TPE331-A72-0522, Revision 2, dated July 1, 1987. (c) Radiographically inspect Part Number 865037-10 through -80 second stage turbine stator seal plate assemblies installed in TPE331-25AA, -25AB, -25DA, -25DB, -25FA, -43A, -43BL, -47A, -55B, and -61A turboprop engines within the next 200 engine hours time in service after the effective date of this amendment, to determine cooling jet orientation in accordance with the accomplishment instructions of Garrett Alert Service Bulletin TPE331-A72-0560, dated July 1, 1987. This is a one-time requirement. NOTE: The radiographic film obtained from a previously inspected engine can be used to determine compliance with paragraph (c) of this amendment. (d) Remove the engine from service prior to further flight if the second stage turbine stator seal plate assembly fails to meet the above service bulletin radiographic inspection standards for misassembly or warpage. Repair the engine per the accomplishment instructions of the applicable service bulletin before return to service. NOTE: GTEC has also provided instructions for accomplishing an interim rotational check of the engine in paragraph 2.A. in Garrett Alert Service Bulletin TPE331-A72-0522,dated July 1, 1987. The FAA has approved and encourages operators to perform this inspection at 25 hour intervals until the radiographic inspection is accomplished; however, the rotational check is not mandatory. Aircraft may be ferried in accordance with the provisions of FAR's 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Los Angeles Aircraft Certification Office, Federal Aviation Administration, Northwest Mountain Region, 4344 Donald Douglas Drive, Long Beach, California 90808. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Los Angeles Aircraft Certification Office, may adjust the compliance time specified in this AD. Garrett Alert Service Bulletins TPE331-A72-0522, Revision 2, dated July 1, 1987, "Engine - Turbine Section - Inspect Second Stage Stator Assembly" andTPE331-A72-0560, dated July 1, 1987, "Engine - Turbine Section - Inspect Second Stage Stator Assembly" identified and described in this document, are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Garrett Airline Service Division, Technical Publications Department 65-70, P.O. Box 29003, Phoenix, Arizona 85072; telephone (602) 225-2969/2973. These documents also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket No. 86-ANE-10, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment 39-5726 amends Amendment 39-5275 (51 FR 12989; April 17, 1986), AD 86-08-06. This amendment 39-5726 becomes effective on December 21,1987. ## Affected data sheets (1) (OpenAirDocs) The type certificate data sheets whose models the AD names. - [TCDS E2WE](https://openairdocs.org/tcds/E2WE): Honeywell Aerospace US LLC; names 10 of 27 models: TPE331-25DB, TPE331-25FA, TPE331-61-A, TPE331-43-A, TPE331-43-B, TPE331-25AA, TPE331-25AB, TPE331-55-B… ## Registered aircraft it may apply to (OpenAirDocs) Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment. - Aircraft: 520 (0 by airframe model, 520 by engine model) - Makers: Cessna 104, Mitsubishi 102, Ayres 52, Rockwell International 46, Fairchild 39, Swearingen 39, Gulfstream AM Corp Comm Div 19, Aero Commander 14, Beech 14, Construcciones Aeronauticas 13 Models with the most aircraft: - [AiResearch TPE331 series](https://openairdocs.org/engine/airesearch-tpe331-series): 492 aircraft (engine model) - [Honeywell TPE331-SER series](https://openairdocs.org/engine/honeywell-tpe331-ser-series): 28 aircraft (engine model) All 3 models: https://openairdocs.org/ad/86-08-06-R1/models.md Every aircraft: https://openairdocs.org/ad/86-08-06-R1/aircraft.md Its text cites no advisory circulars or STCs. ## NTSB investigations that cite this AD (2) From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [NTSB NYC05LA126](https://openairdocs.org/ntsb/NYC05LA126), Aug 1, 2005: Grumman G-164A (N5495), Felton, DE, substantial damage. Probable cause: The mechanic's inadequate annual inspection, and failure to comply with an airworthiness directive, which resulted in a total failure of the second stage turbine rotor. - [NTSB LAX92LA131](https://openairdocs.org/ntsb/LAX92LA131), Feb 29, 1992: Grumman G-164A (N5408), Vernalis, CA, substantial damage. Probable cause: THE OPERATOR'S FAILURE TO PROPERLY COMPLY WITH AN AIRWORTHINESS DIRECTIVE AFFECTING THE SECOND-STAGE TURBINE WHEEL ASSEMBLY. CONTRIBUTING TO THIS ACCIDENT WAS THE UNCONTAINED FAILURE OF THE… --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.