{"id":"F2006B08485","name":"AD/CF6/47 - Low Pressure Turbine Shaft - Life Limit","slug":"ad-cf6-47-low-pressure-turbine-shaft-life-limit","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":51169,"registerId":"commonwealth-F2006B08485-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"AIRWORTHINESS DIRECTIVE","sectionType":"part","heading":"AIRWORTHINESS DIRECTIVE","content":"# AIRWORTHINESS DIRECTIVE\n\n![](image.001.png)\n\n![](image.001.png)  \nFor the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.\n\nGeneral Electric Turbine Engines \\- CF6 Series","sortOrder":0},{"sectionNumber":"AD/CF6/47 Low Pressure Turbine Shaft - L","sectionType":"part","heading":"AD/CF6/47 Low Pressure Turbine Shaft - Life Limit 2/2003","content":"# AD/CF6/47 Low Pressure Turbine Shaft \\- Life Limit 2/2003\n\nApplicability: General Electric CF6-80E1A2 Engines. Requirement: Action per the requirements of FAA AD 2002-10-04.\n\nNote: FAA AD 2002-10-04, Amdt 39-12750 refers.\n\nCompliance: As detailed in the requirement document with a revised effective date of 20 February 2003.\n\nThis Airworthiness Directive becomes effective on 20 February 2003.\n\nBackground: This directive mandates a reduced low cycle fatigue life limit for the Low Pressure Turbine Shafts to prevent un-contained engine failures.\n\n![Signature of Neville James Probert Delegate of the Civil Aviation Safety Authority](image.002.jpeg)  \n\nNeville James Probert\n\nDelegate of the Civil Aviation Safety Authority 9 January 2003\n\n![](image.001.png)  \n\nThe above AD is notified in the Commonwealth of Australia Gazette on 29 January 2003.","sortOrder":1}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This AD maintains its original narrow scope — addressing a specific mechanical failure mode in a specific engine series. It does not expand beyond its original safety purpose."},"complexity_factors":["Very short document (under 300 words)","Only 1 defined applicability (specific engine model)","Single requirement: comply with external FAA directive","No nested conditions or exceptions","No cross-references to other Australian legislation beyond the enabling regulation (CAR 1998 subreg 39.1(1))","Straightforward compliance date structure"],"plain_english_summary":"This CASA Airworthiness Directive makes mandatory the FAA’s AD 2002-10-04 for GE CF6-80E1A2 engines, imposing shorter life limits and required inspections/replacements for the Low Pressure Turbine shaft. It affects Australian airlines and operators using these engines and aims to prevent shaft cracking and uncontained engine failures. Compliance was required from 20 February 2003."},"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The instrument adopts the requirements of FAA AD 2002-10-04 for General Electric CF6-80E1A2 engines and sets a revised effective date (20 February 2003). The AD does not indicate any expansion or narrowing of applicability beyond adopting the FAA requirements."},"complexity_factors":["Cross-reference to an external instrument (FAA AD 2002-10-04) — compliance requires consulting another document.","Technical engineering content (low‑cycle fatigue life limits) — requires specialist maintenance/engineering assessment.","Timing/effective date revision (20 February 2003) — creates a compliance deadline.","Narrow applicability (specific engine model CF6-80E1A2) — reduces scope but requires operators to confirm applicability.","Regulatory formality: issued under CAR 1998 subregulation 39.1(1) by CASA delegate — legal force is administrative and mandatory."],"plain_english_summary":"This directive requires operators and maintainers of General Electric CF6‑80E1A2 engines to comply with FAA Airworthiness Directive 2002‑10‑04, imposing a reduced low‑cycle fatigue life limit on low‑pressure turbine shafts. \n\nCASA issued the AD with a revised effective date (20 February 2003). Engine owners/operators must inspect, retire or replace affected shafts per the FAA instructions, which shifts the compliance and replacement costs to those operators to reduce the risk of un-contained engine failures."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cf6-47-low-pressure-turbine-shaft-life-limit","history":"/api/acts/ad-cf6-47-low-pressure-turbine-shaft-life-limit/history","analysis":"/api/acts/ad-cf6-47-low-pressure-turbine-shaft-life-limit/analysis","conflicts":"/api/acts/ad-cf6-47-low-pressure-turbine-shaft-life-limit/conflicts","importantCases":"/api/acts/ad-cf6-47-low-pressure-turbine-shaft-life-limit/important-cases","documents":"/api/acts/ad-cf6-47-low-pressure-turbine-shaft-life-limit/documents"}}