AD 84-20-51
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | Honeywell International Inc. | ATF3-6 | GARRETT TURBINE ENGINE COMPANY (GTEC) (formerly AiResearch Manufacturing Company of Arizona) Models ATF3-6-4C, -6A-3C, and -6A- 4C Engines |
| engine | Honeywell International Inc. | ATF3-6A | GARRETT TURBINE ENGINE COMPANY (GTEC) (formerly AiResearch Manufacturing Company of Arizona) Models ATF3-6-4C, -6A-3C, and -6A- 4C Engines |
Unsafe Condition
The possibility of an uncontained engine failure due to seal/rotor contact and/or seal looseness in the stationary seal/sixth stage low pressure turbine rotor assembly area.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the stationary seal/sixth stage low pressure turbine rotor assembly area for evidence of seal/rotor contact and/or seal looseness using specified maintenance manuals. Disassemble engines with unsuccessful inspection results to modify the exhaust deflector liner and seal assembly and inspect the sixth stage turbine rotor assembly. Incorporate the exhaust deflector liner and seal assembly bolted flange system within 200 operating hours after the effective date or prior to April 15, 1985.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to the accumulation of an additional 5 hours in service after the effective date of this AD, and at intervals not to exceed 25 operational hours thereafter, until incorporation of the exhaust deflector liner and seal assembly bolted flange system.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
GARRETT TURBINE ENGINE COMPANY (GTEC) models ATF3-6-4C, -6A-3C, and -6A-4C engines with exhaust deflector liner and seal assembly, Garrett part number 3001313-11 through -14 installed.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Exhaust Deflector Liner and Seal Assembly
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_84-20-51.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 84-20-51 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: GARRETT TURBINE ENGINE COMPANY (GTEC) (formerly AiResearch Manufacturing Company of Arizona) Models ...Show more Subject: Exhaust Deflector Liner and Seal Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/26/1984 Make: Honeywell International Inc. Model: ATF3-6 | ATF3-6A Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 84-20-51 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4965 AD NUMBER: 84-20-51 SUBJECT HEADING: GARRETT TURBINE ENGINE COMPANY (GTEC) (formerly AiResearch Manufacturing Company of Arizona) Models ATF3-6-4C, -6A-3C, and -6A- 4C Engines ACTION: SUMMARY: DATES: Effective December 26, 1984. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 84-20-51 GARRETT TURBINE ENGINE COMPANY (GTEC) (formerly AiResearch Manufacturing Company of Arizona): Amendment 39-4965. Applicable to all engine models ATF3-6-4C, -6A-3C, and -6A-4C with exhaust deflector liner and seal assembly, Garrett part number (P/N) 3001313-11 through -14, installed. Compliance required as indicated unless already accomplished. To prevent the possibility of an uncontained engine failure, accomplish the following: A. Prior to the accumulation of an additional 5 hours in service, after the effective date of this AD, and at intervals not to exceed 25 operational hours thereafter, until incorporation of the exhaust deflector liner and seal assembly bolted flange system as specified in Section 2.A., "Accomplishment Instructions," of GTEC SB ATF3-72-6092, dated May 25, 1984, or equivalent approved by the Manager, Western Aircraft Certification Office, visually inspect the stationary seal/sixth stage low pressure turbine rotor assembly area of all affected engines for evidence of seal/rotor contact and/or seal looseness as specified in the following GTEC Light Maintenance Manual Revisions, or equivalent approved by the Manager, Western Aircraft Certification Office: ENGINE MODEL MANUAL REFERENCE ATF3-6-4C Light Maintenance Manual Report No. 72-00-52, Revision 6 dated November 15, 1983; Temporary Revision No. 72-88, 72-00-00, Trouble Shooting dated April 16, 1984; and Temporary Revision No. 72-89, 72-00-00, Trouble Shooting dated April 16, 1984. ATF3-6A-3C Light Maintenance Manual Report No. 72-03-32, Revision 3 dated November 15, 1983; Temporary Revision No. 72-43, 72-00-00, Trouble Shooting dated April 16, 1984; and Temporary Revision No. 72-44, 72-00-00, Trouble Shooting dated April 16, 1984. ATF3-6A-4C Light Maintenance Manual Report No. 72-03-42, Revision 4 dated November 15, 1983; Temporary Revision No. 72-44, 72-00-00, Trouble Shooting dated April 16, 1984; and Temporary Revision No. 72-45, 72-00-00, Trouble Shooting dated April 16, 1984. B. Engines with unsuccessful inspection results found during the accomplishment of paragraph A above are to be disassembled as required to modify the exhaust deflector liner and seal assembly and to inspect the sixth stage turbine rotor assembly. C. Upon removal of the sixth stage low pressure turbine rotor assembly from an affected engine for any reason or within 200 operating hours after the effective date of this AD or prior to April 15, 1985, whichever comes first, incorporate the new exhaust deflector liner and seal assembly bolted flange system as specified in Section 2.A., "Accomplishment Instructions," of GTEC SB ATF3-72-6092, dated May 25, 1984, or equivalent approved by the Manager, Western Aircraft Certification Office. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FARs) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request of an operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Western Aircraft Certification Office, Northwest Mountain Region, P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All person affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Garrett Turbine Engine Company, P.O. Box 5217, Phoenix, Arizona 85010; telephone (602) 231-1000. These documents also may be examined at Office of the Regional Counsel, New England Region, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment supersedes Amendment 39-4900 (49 FR 35614), AD 84-11-51. This amendment becomes effective December 26, 1984, to all persons except those persons to whom it was made immediately effective by telegraphic AD T84-20-51, issued October 4, 1984. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_84-20-51.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 84-20-51 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: GARRETT TURBINE ENGINE COMPANY (GTEC) (formerly AiResearch Manufacturing Company of Arizona) Models ...Show more Subject: Exhaust Deflector Liner and Seal Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/26/1984 Make: Honeywell International Inc. Model: ATF3-6 | ATF3-6A Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 84-20-51 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4965 AD NUMBER: 84-20-51 SUBJECT HEADING: GARRETT TURBINE ENGINE COMPANY (GTEC) (formerly AiResearch Manufacturing Company of Arizona) Models ATF3-6-4C, -6A-3C, and -6A- 4C Engines ACTION: SUMMARY: DATES: Effective December 26, 1984. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 84-20-51 GARRETT TURBINE ENGINE COMPANY (GTEC) (formerly AiResearch Manufacturing Company of Arizona): Amendment 39-4965. Applicable to all engine models ATF3-6-4C, -6A-3C, and -6A-4C with exhaust deflector liner and seal assembly, Garrett part number (P/N) 3001313-11 through -14, installed. Compliance required as indicated unless already accomplished. To prevent the possibility of an uncontained engine failure, accomplish the following: A. Prior to the accumulation of an additional 5 hours in service, after the effective date of this AD, and at intervals not to exceed 25 operational hours thereafter, until incorporation of the exhaust deflector liner and seal assembly bolted flange system as specified in Section 2.A., "Accomplishment Instructions," of GTEC SB ATF3-72-6092, dated May 25, 1984, or equivalent approved by the Manager, Western Aircraft Certification Office, visually inspect the stationary seal/sixth stage low pressure turbine rotor assembly area of all affected engines for evidence of seal/rotor contact and/or seal looseness as specified in the following GTEC Light Maintenance Manual Revisions, or equivalent approved by the Manager, Western Aircraft Certification Office: ENGINE MODEL MANUAL REFERENCE ATF3-6-4C Light Maintenance Manual Report No. 72-00-52, Revision 6 dated November 15, 1983; Temporary Revision No. 72-88, 72-00-00, Trouble Shooting dated April 16, 1984; and Temporary Revision No. 72-89, 72-00-00, Trouble Shooting dated April 16, 1984. ATF3-6A-3C Light Maintenance Manual Report No. 72-03-32, Revision 3 dated November 15, 1983; Temporary Revision No. 72-43, 72-00-00, Trouble Shooting dated April 16, 1984; and Temporary Revision No. 72-44, 72-00-00, Trouble Shooting dated April 16, 1984. ATF3-6A-4C Light Maintenance Manual Report No. 72-03-42, Revision 4 dated November 15, 1983; Temporary Revision No. 72-44, 72-00-00, Trouble Shooting dated April 16, 1984; and Temporary Revision No. 72-45, 72-00-00, Trouble Shooting dated April 16, 1984. B. Engines with unsuccessful inspection results found during the accomplishment of paragraph A above are to be disassembled as required to modify the exhaust deflector liner and seal assembly and to inspect the sixth stage turbine rotor assembly. C. Upon removal of the sixth stage low pressure turbine rotor assembly from an affected engine for any reason or within 200 operating hours after the effective date of this AD or prior to April 15, 1985, whichever comes first, incorporate the new exhaust deflector liner and seal assembly bolted flange system as specified in Section 2.A., "Accomplishment Instructions," of GTEC SB ATF3-72-6092, dated May 25, 1984, or equivalent approved by the Manager, Western Aircraft Certification Office. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FARs) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request of an operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Western Aircraft Certification Office, Northwest Mountain Region, P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All person affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Garrett Turbine Engine Company, P.O. Box 5217, Phoenix, Arizona 85010; telephone (602) 231-1000. These documents also may be examined at Office of the Regional Counsel, New England Region, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment supersedes Amendment 39-4900 (49 FR 35614), AD 84-11-51. This amendment becomes effective December 26, 1984, to all persons except those persons to whom it was made immediately effective by telegraphic AD T84-20-51, issued October 4, 1984. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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