{"id":"F2010L02685","name":"AD/CF6/80 - High Pressure Compressor Air Ducts","slug":"ad-cf6-80-high-pressure-compressor-air-ducts","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":84641,"registerId":"commonwealth-F2010L02685-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/CF6/80 | High Pressure Compressor Air Ducts | 21/2010 |\n| --------- | ---------------------------------- | ------- |\n\n| Applicability: | General Electric Company CF6 engines as specified in FAA AD 2001-12-20.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        |\n| -------------- | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Unless already accomplished, replace the air duct and mating hardware, and inspect in accordance with the requirements of FAA AD 2001-12-20.Repeat the inspection in accordance with the requirements of FAA AD 2001-12-20.Later revisions to GEAE ASB CF6-50 72-A1200, Revision 3, dated May 30, 2001or GEAE ASB CF6-50 72-A0958, Revision 3, dated May 25, 2001, approved by the United States Federal Aviation Administration (FAA) as an Alternate Method of Compliance (AMOC) to FAA AD 2001-12-20, are considered acceptable for compliance with the equivalent Requirements of this AD. |\n| Compliance:    | As specified in the Requirement Document with a revised effective date of11 November 2010.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     |\n|                | This Airworthiness Directive becomes effective on 11 November 2010.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            |\n| Background:    | This AD results from reports of an uncontained low pressure turbine disc failure that resulted from an air duct failure that caused a fan mid shaft separation. The actions specified by this AD are intended to prevent high pressure compressor air duct failures that could result in fan mid shaft failures.                                                                                                                                                                                                                                                                               |\n\n![](image.001.png)\n\nMike Higgins  \nDelegate of the Civil Aviation Safety Authority\n\n8 October 2010","sortOrder":0},{"sectionNumber":"AD/CF6/80","sectionType":"part","heading":"AD/CF6/80","content":"## AD/CF6/80","sortOrder":1},{"sectionNumber":"High Pressure Compressor Air Ducts","sectionType":"part","heading":"High Pressure Compressor Air Ducts","content":"## High Pressure Compressor Air Ducts","sortOrder":2},{"sectionNumber":"21/2010","sectionType":"part","heading":"21/2010","content":"## 21/2010","sortOrder":3}],"analysis":{"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"},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This AD maintains its original narrow scope — addressing a specific mechanical failure mode in specific engine models. It does not expand beyond the original safety issue of high pressure compressor air duct failures."},"complexity_factors":["Short, single-purpose directive with one primary technical requirement","Heavy reliance on external documents (FAA AD 2001-12-20 and GE service bulletins) rather than spelling out technical specifications in the text itself","Only 2 defined applicability criteria (engine model and FAA AD reference)","Simple conditional structure: 'Unless already accomplished' is the only exception clause","Cross-references to US regulatory framework (FAA AD and AMOC process) rather than standalone Australian technical standards"],"plain_english_summary":"Australia's Civil Aviation Safety Authority mandates that operators of certain General Electric CF6 engines—commonly fitted to wide-body aircraft like Boeing 747s and Airbus A300/A310—must replace specified air ducts and hardware and carry out repeated inspections to prevent hazardous fan mid-shaft separations.  \n\nThis urgent, compulsory AD follows an uncontained engine failure and takes effect 11 November 2010; it adopts the FAA requirements and permits FAA/GE‑approved alternative methods."},"flash_summary":{"complexity_score":5,"scope_assessment":{"changed":false,"description":"This instrument adopts the applicability and corrective actions of FAA AD 2001-12-20 for specified GE CF6 engines and accepts FAA‑approved later GE service bulletin revisions as AMOCs. It does not expand the stated applicability beyond the FAA AD but establishes an Australian effective date (11 November 2010) and requires compliance as specified (Applicability; Requirement; Compliance)."},"complexity_factors":["Cross-reference to an external FAA airworthiness directive for detailed requirements, creating dependency on another instrument for full compliance (Applicability; Requirement).","Allowance of later revisions of GE service bulletins as an FAA‑approved Alternate Method of Compliance, adding conditional pathways and approval dependency (Requirement).","Repeated inspection obligations (initial and recurring) increase ongoing operational and maintenance scheduling complexity for operators (Requirement).","Effective date and revised effective date specification impose a concrete compliance timeline that operators must track (Compliance).","Technical, safety‑critical nature of the parts (high‑pressure compressor air duct and mating hardware) raises the stakes for correct replacement and inspection procedures (Background).","Short, directive format leaves substantive procedural and technical detail to the FAA AD and GE service bulletins, requiring operators and maintainers to consult multiple documents (Requirement; Applicability)."],"plain_english_summary":"**What it does:** Requires operators of General Electric CF6 engines (as specified in FAA AD 2001-12-20) to replace the high‑pressure compressor air duct and mating hardware and to perform the initial and repeat inspections required by the FAA AD. Effective date: 11 November 2010.\n\n**Why it matters:** The AD responds to reported air duct failures that led to an uncontained low‑pressure turbine disc and fan mid‑shaft separation; it mandates parts replacement and inspections to prevent similar mechanical failures."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cf6-80-high-pressure-compressor-air-ducts","history":"/api/acts/ad-cf6-80-high-pressure-compressor-air-ducts/history","analysis":"/api/acts/ad-cf6-80-high-pressure-compressor-air-ducts/analysis","conflicts":"/api/acts/ad-cf6-80-high-pressure-compressor-air-ducts/conflicts","importantCases":"/api/acts/ad-cf6-80-high-pressure-compressor-air-ducts/important-cases","documents":"/api/acts/ad-cf6-80-high-pressure-compressor-air-ducts/documents"}}