AD 82-20-03
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric Company | CF6-45A | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-45A2 | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-50A | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-50C | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-50C1 | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-50C2 | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-50C2B | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-50C2D | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-50CA | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-50E | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-50E1 | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-50E2 | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
| engine | General Electric Company | CF6-50E2B | GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines |
Unsafe Condition
Cracks in first stage HPT disks (P/Ns 9045M34P07 and 9045M34P09) could result in engine failure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect first stage HPT disks using 'double inspections' per GE Service Bulletins 72-700 or 72-709. Disks not previously inspected must be inspected before reaching 2,000 cycles (MTU serial) or 3,200 cycles (MPO serial). Reinspect every 750 cycles thereafter. Remove cracked disks from service. Disks with P/Ns 9045M34P07 and 945M34P09 cannot be returned to service after February 1, 1984.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to reaching specified cycles in service as outlined in the schedule (e.g., 2,000 cycles for MTU, 3,200 for MPO, then every 750 cycles).
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
General Electric Company CF6-45A, CF6-45A2, CF6-50A, CF6-50C, CF6-50C1, CF6-50C2, CF6-50C2B, CF6-50C2D, CF6-50CA, and other CF6-45 and -50 series engines listed in the AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Inspect First Stage HPT Disks
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_82-20-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-20-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines Subject: Inspect First Stage HPT Disks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/31/1982 Make: General Electric Company Model: CF6-45A | CF6-45A2 | CF6-50A | CF6-50C | CF6-50C1 | CF6-50C2 | CF6-50C2B | CF6-50C2D | CF6-50CA | CF...Show more 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: 82-20-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4464 AD NUMBER: 82-20-03 SUBJECT HEADING: GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines ACTION: SUMMARY: DATES: Effective October 31, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-20-03 GENERAL ELECTRIC COMPANY: Amendment 39-4464. Applies to CF6-45 series and -50 series model turbofan engines. Compliance required as indicated unless already accomplished. Inspect all first stage HPT disks, P/Ns 9045M34P07 and 9045M34P09, for cracks in accordance with General Electric CF6-45/50 Engine Service Bulletin 72-700, dated November 20, 1980, or Alert Service Bulletin 72-709 dated February 19, 1981, or later revision approved by the Manager, Engine Certification Branch, FAA, New England Region, per the following schedule utilizing two complete independent inspections, hereafter referred to as "double inspections." A. Disks not previously inspected shall be "double inspected" prior to reaching 2,000 cycles in service for MTU serial number disks and 3,200 cycles in service for MPO serial number disks. All disks removed from service for inspection shall be reinspected every 750 cycles in service thereafter. B. Disks previously inspected shall be reinspected using the "double inspection" procedure prior to reaching 750 cycles in service since last inspection and every 750 cycles in service thereafter. C. All first stage turbine disks exposed at each high pressure rotor disassembly shall be "double inspected" prior to further flight per General Electric CF6-45/50 Service Bulletins 72-700 or 72-709. D. Disks with crack indications must be removed from service prior to further flight. E. First stage HPT disks, P/Ns 9045M34P07 and 945M34P09, shall not be returned to service after February 1, 1984. NOTE: For the purposes of this AD, "return to service" is defined as installation on an aircraft. F. All MTU prefix serial numbered disks reworked per General Electric CF6-45/50 Service Bulletin 72-700 at zero cycles of service may follow the initial inspection limits for MPO prefix serial numbers. Established life limits of first stage HPT disks are not to be exceeded. Airplanes may be ferried in accordance with the provisions of Federal Aviation Regulation 21.197 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, Engine Certification Branch, FAA, New England Region. The manufacturer's specifications and procedures identified and described in this directive may be obtained upon request to General Electric Company, Neumann Way, Cincinnati, Ohio 45215. These documents may also be examined at the FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts. A historical file on this AD is maintained by the FAA, New England Region Office, Burlington, Massachusetts. This airworthiness directive supersedes AD's T80-16-51, T81-05-51, T82-05-51, and T82-08-51. This Amendment 39-4464 becomes effective on October 31, 1982. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_82-20-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-20-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines Subject: Inspect First Stage HPT Disks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/31/1982 Make: General Electric Company Model: CF6-45A | CF6-45A2 | CF6-50A | CF6-50C | CF6-50C1 | CF6-50C2 | CF6-50C2B | CF6-50C2D | CF6-50CA | CF...Show more 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: 82-20-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4464 AD NUMBER: 82-20-03 SUBJECT HEADING: GENERAL ELECTRIC COMPANY Models CF6-45 and -50 Series Engines ACTION: SUMMARY: DATES: Effective October 31, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-20-03 GENERAL ELECTRIC COMPANY: Amendment 39-4464. Applies to CF6-45 series and -50 series model turbofan engines. Compliance required as indicated unless already accomplished. Inspect all first stage HPT disks, P/Ns 9045M34P07 and 9045M34P09, for cracks in accordance with General Electric CF6-45/50 Engine Service Bulletin 72-700, dated November 20, 1980, or Alert Service Bulletin 72-709 dated February 19, 1981, or later revision approved by the Manager, Engine Certification Branch, FAA, New England Region, per the following schedule utilizing two complete independent inspections, hereafter referred to as "double inspections." A. Disks not previously inspected shall be "double inspected" prior to reaching 2,000 cycles in service for MTU serial number disks and 3,200 cycles in service for MPO serial number disks. All disks removed from service for inspection shall be reinspected every 750 cycles in service thereafter. B. Disks previously inspected shall be reinspected using the "double inspection" procedure prior to reaching 750 cycles in service since last inspection and every 750 cycles in service thereafter. C. All first stage turbine disks exposed at each high pressure rotor disassembly shall be "double inspected" prior to further flight per General Electric CF6-45/50 Service Bulletins 72-700 or 72-709. D. Disks with crack indications must be removed from service prior to further flight. E. First stage HPT disks, P/Ns 9045M34P07 and 945M34P09, shall not be returned to service after February 1, 1984. NOTE: For the purposes of this AD, "return to service" is defined as installation on an aircraft. F. All MTU prefix serial numbered disks reworked per General Electric CF6-45/50 Service Bulletin 72-700 at zero cycles of service may follow the initial inspection limits for MPO prefix serial numbers. Established life limits of first stage HPT disks are not to be exceeded. Airplanes may be ferried in accordance with the provisions of Federal Aviation Regulation 21.197 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, Engine Certification Branch, FAA, New England Region. The manufacturer's specifications and procedures identified and described in this directive may be obtained upon request to General Electric Company, Neumann Way, Cincinnati, Ohio 45215. These documents may also be examined at the FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts. A historical file on this AD is maintained by the FAA, New England Region Office, Burlington, Massachusetts. This airworthiness directive supersedes AD's T80-16-51, T81-05-51, T82-05-51, and T82-08-51. This Amendment 39-4464 becomes effective on October 31, 1982. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
2023-04-11
final ruleAirworthiness Directives; General Electric Company Turbofan Engines
Unsafe Condition: Separation of the low-pressure turbine (LPT) rotor assembly, resulting in the LPT rotor assembly departing the rear of the engine.
2011-23-04 Recurring
final ruleAirworthiness Directives; General Electric Company (GE) CF6 Turbofan Engines
Unsafe Condition: Failure of the side links and possible engine separation from the airplane.
2011-07-01
final ruleAirworthiness Directives; General Electric Company CF6-45 and CF6-50 Series Turbofan Engines
Unsafe Condition: The forward and aft centerbody of the LFCEN assembly may separate from the engine, causing damage to the engine, and damage to the airplane.
2007-19-06
final ruleAirworthiness Directives; General Electric Company Aircraft Engine Group (GEAE) CF6-45A Series, CF6-50A, CF6-50C Series and CF6-50E Series Turbofan Engines
Unsafe Condition: Reports of five events involving fractured compressor discharge pressure (CDP) restoring spring assembly, which could lead to loss of engine thrust control and loss of control of the airplane.