{"id":"F2009L01971","name":"AD/CF6/75 - High Pressure Turbine Rotor Stage 1 Disc","slug":"ad-cf6-75-high-pressure-turbine-rotor-stage-1-disc","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":79165,"registerId":"commonwealth-F2009L01971-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"General Electric Turbine Engines - CF6 S","sectionType":"division","heading":"General Electric Turbine Engines - CF6 Series","content":"### General Electric Turbine Engines - CF6 Series\n\n| AD/CF6/75 | High Pressure Turbine Rotor Stage 1 Disc | 6/2009 |\n| --------- | ---------------------------------------- | ------ |\n\n| Applicability: | General Electric Co. (GE) CF6-80A, CF6-80A1, CF6-80A2, and CF6-80A3 turbofan engines with a high-pressure turbine rotor (HPTR) stage 1 disc, part number (P/N) 9367M45G06, installed.Note 1: These engines are installed on, but not limited to, Airbus A310 series and Boeing 767 series aeroplanes.                                                                                                                                                                             |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Remove HPTR stage 1 discs, P/N 9367M45G06, from service before exceeding the new, reduced life limit of 2,075 cycles-since-new.Note 2: FAA AD 2009-07-10 Amdt 39-15869 dated 25 March 2009 refers.                                                                                                                                                                                                                                                                                |\n| Compliance:    | From the effective date of this AD, unless previously accomplished.                                                                                                                                                                                                                                                                                                                                                                                                               |\n|                | This Airworthiness Directive becomes effective on 4 June 2009.                                                                                                                                                                                                                                                                                                                                                                                                                    |\n| Background:    | This AD results from an error by GE that incorrectly cited a cyclic life of 12,600 CSN in the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) for the HPTR stage 1 disc, P/N 9367M45G06. The issuing of this AD is to prevent the HPTR stage 1 disk from exceeding its part life, which could cause fatigue cracks to start and grow. These cracks could result in a possible uncontained disc failure and damage to the aeroplane. |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n17 April 2009","sortOrder":0},{"sectionNumber":"AD/CF6/75","sectionType":"part","heading":"AD/CF6/75","content":"## AD/CF6/75","sortOrder":1},{"sectionNumber":"High Pressure Turbine Rotor Stage 1 Disc","sectionType":"part","heading":"High Pressure Turbine Rotor Stage 1 Disc","content":"## High Pressure Turbine Rotor Stage 1 Disc","sortOrder":2},{"sectionNumber":"6/2009","sectionType":"part","heading":"6/2009","content":"## 6/2009","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This AD maintains its original narrow, safety-critical purpose: correcting a specific manufacturer's error regarding a single engine component's life limit. There is no evidence of scope creep — it targets precisely the affected part numbers and engine models necessary to address the identified safety risk."},"complexity_factors":["Single, unambiguous requirement: remove specific part before cycle limit","Only one defined term of note: 'cycles-since-new' (CSN)","No nested exceptions or conditional logic — applies to all listed engine models uniformly","No cross-references to other legislation (only a non-binding reference to the corresponding FAA AD)","Extremely short document — essentially a one-page safety bulletin with standard AD formatting","Clear applicability table with explicit part numbers and engine models"],"plain_english_summary":"This CASA Airworthiness Directive mandates removal of a specific GE CF6-80A high‑pressure turbine stage 1 disc (P/N 9367M45G06) and imposes a new life limit of 2,075 flight cycles, correcting an earlier, incorrect 12,600‑cycle figure.\n\nIt affects operators of Airbus A310, Boeing 767 and other aircraft using these engines; it prevents fatigue cracking and the risk of uncontained engine failure by forcing earlier retirement of the part."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"The AD narrows the allowable life of the specified HP turbine stage‑1 disc from the life cited in GE's Airworthiness Limitations (which incorrectly showed 12,600 CSN) to a reduced life limit of 2,075 CSN, and requires removal before that limit. It does not expand the set of affected engine models beyond the listed CF6 variants, but it shortens service life and therefore increases replacement and maintenance obligations for operators."},"complexity_factors":["Very narrow technical scope: single part number (P/N 9367M45G06) and specific CF6 engine variants require precise CSN tracking.","Immediate compliance date imposes operational scheduling and logistics for affected operators and maintenance providers.","Cross-reference to FAA AD 2009-07-10 creates dependency on an external regulatory document for background/validation.","Safety-critical consequence elevates urgency and replacement supply risk (parts, shop capacity).","Low statutory drafting complexity but non-trivial administrative burden to identify all affected engines and update maintenance records."],"plain_english_summary":"This directive requires removal of the CF6 high‑pressure turbine stage‑1 disc (P/N 9367M45G06) before it exceeds 2,075 cycles‑since‑new. It applies to GE CF6‑80A/80A1/80A2/80A3 engines (installed on Airbus A310, Boeing 767 and other aeroplanes). The AD says GE previously misstated the disc's life in its maintenance limits; the reduced limit is intended to prevent fatigue cracking and possible uncontained disc failure."},"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"}},"importantCases":[],"_links":{"self":"/api/acts/ad-cf6-75-high-pressure-turbine-rotor-stage-1-disc","history":"/api/acts/ad-cf6-75-high-pressure-turbine-rotor-stage-1-disc/history","analysis":"/api/acts/ad-cf6-75-high-pressure-turbine-rotor-stage-1-disc/analysis","conflicts":"/api/acts/ad-cf6-75-high-pressure-turbine-rotor-stage-1-disc/conflicts","importantCases":"/api/acts/ad-cf6-75-high-pressure-turbine-rotor-stage-1-disc/important-cases","documents":"/api/acts/ad-cf6-75-high-pressure-turbine-rotor-stage-1-disc/documents"}}