{"id":"F2006B08491","name":"AD/CF6/53 - Forward Engine Mount Platforms","slug":"ad-cf6-53-forward-engine-mount-platforms","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":51184,"registerId":"commonwealth-F2006B08491-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\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 CASR 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\n![](image.001.png)  \n\nGeneral Electric Turbine Engines \\- CF6 Series","sortOrder":0},{"sectionNumber":"AD/CF6/53 Forward Engine Mount Platforms","sectionType":"part","heading":"AD/CF6/53 Forward Engine Mount Platforms 13/2003","content":"# AD/CF6/53 Forward Engine Mount Platforms 13/2003\n\nApplicability: General Electric Company (GE) CF6-80E1A2 turbofan engines with forward engine mount platform part numbers (P/Ns) 1520M53G04 and 1846M24G15 installed.\n\nNote 1: These engines are installed on, but not limited to Airbus Industrie A330 aeroplanes.\n\nRequirement: Perform a fluorescent penetrant inspection (FPI) of the forward engine mount platform in accordance with CF6 component maintenance manual GEK 99410, section 71-21-02.\n\nNote 2: FAA AD 2003-20-07 Amdt 39-13325 refers.\n\nCompliance: For platforms not previously inspected using an FPI before the effective date of this Directive, at the next exposure or before exceeding 6,360 cycles since new (CSN), whichever occurs first, thereafter at intervals not to exceed 4,000 cycles since last inspection (CSLI).\n\nFor platforms previously inspected using an FPI before the effective date of this Directive, within 4,000 CSLI, thereafter at intervals not to exceed 4,000 CSLI.\n\nThis Airworthiness Directive becomes effective on 25 December 2003.\n\nBackground: The aeroplane manufacturer has conducted analysis of the aeroplane engine mount loads and has found that engine mounts made from cast material require a reduction in their low cycle fatigue life.\n\nThis Directive requires FPI of the engine mount platform to prevent failure of the engine mount platform and loss of control of the aeroplane.\n\n![Signature of Jim Coyne Delegate of the Civil Aviation Safety Authority](image.002.png)  \n\nJim Coyne\n\n![](image.001.png)Delegate of the Civil Aviation Safety Authority 14 November 2003","sortOrder":1}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"This directive aligns with its original, stated purpose: to address a reduced low-cycle fatigue life in cast forward engine mount platforms by requiring periodic fluorescent penetrant inspections. It does not expand beyond that technical remedy (no new part bans, design changes, or operator categories added). The scope remains limited to the specified CF6-80E1A2 engines and the two listed forward engine mount platform part numbers, consistent with the background analysis cited in the AD."},"complexity_factors":["Short, focused document limited to two specific part numbers and one engine model series","One primary required action (fluorescent penetrant inspection) with a single referenced maintenance manual section (GEK 99410, section 71-21-02)","Timing logic with two branches: (a) platforms never inspected before effective date — initial inspection at next exposure or before 6,360 CSN, then every 4,000 CSLI; (b) platforms previously inspected — within 4,000 CSLI, then every 4,000 CSLI","Uses two operational metrics that operators must track: CSN (cycles since new) and CSLI (cycles since last inspection)","Cross-reference to FAA AD 2003-20-07 (Note 2) introduces an external document for optional additional context","Few defined terms but relies on industry-standard terms (CSN, CSLI, FPI) whose interpretation in practice requires operational records"],"plain_english_summary":"**What this directive does (mechanically):**\n\n- **Applies to:** General Electric CF6-80E1A2 turbofan engines that have forward engine mount platforms with part numbers 1520M53G04 or 1846M24G15 installed. (Applicability)\n- **Action required:** Operators must perform a fluorescent penetrant inspection (FPI) of the forward engine mount platform, following the CF6 component maintenance manual GEK 99410, section 71-21-02. (Requirement)\n- **When to do it (timing):**\n  - If the platform has never had an FPI before the directive’s effective date, inspect it at the next exposure or before it exceeds 6,360 cycles since new (CSN), whichever comes first, and then repeat every 4,000 cycles since last inspection (CSLI). (Compliance)\n  - If the platform was inspected by FPI before the effective date, inspect within 4,000 CSLI and then repeat every 4,000 CSLI. (Compliance)\n- **Effective date:** 25 December 2003.\n\n**Who is affected:**\n\n- Aircraft operators and maintenance organisations responsible for aeroplanes (for example, Airbus A330) fitted with GE CF6-80E1A2 engines that use the listed forward engine mount platform part numbers. Maintenance providers who perform FPIs on these engine components are also affected. (Applicability & Requirement)\n\n**Why it matters (stated purpose and practical implications):**\n\n- The aeroplane manufacturer analysed engine-mount loads and concluded that mount platforms made from cast material have a reduced low-cycle fatigue life. The directive states its purpose is to detect fatigue cracking by requiring FPI so as to prevent platform failure and potential loss of control of the aeroplane. (Background)\n\n**Who pays and who decides:**\n\n- Operators/owners pay for the inspections and any follow-up maintenance or replacements discovered by the inspection. The Civil Aviation Safety Authority (CASA) delegate issues the directive; the inspections must be carried out following the GE component maintenance manual. (Requirement & Background)\n\n**Compliance and operational effects (incentives, costs, trade-offs):**\n\n- Direct costs: labour, equipment and aircraft downtime to perform FPIs at the specified intervals; possible parts replacement if defects are found. These are typically borne by the aircraft operator or their maintenance contractor. (Compliance & Requirement)\n- Record-keeping and scheduling: operators must track cycles since new (CSN) and cycles since last inspection (CSLI) to meet the timing conditions; failure to maintain accurate records increases implementation risk. (Compliance)\n- Implementation reliance: the directive depends on following the GE maintenance manual procedures for FPI; differences in local maintenance capability or interpretation could affect consistency of inspection outcomes. (Requirement)\n- Substitution/avoidance: operators may choose more frequent inspections, replacement of the platform with a different part or material if available, or accelerated retirement of affected engines to manage risk — each option has distinct cost and operational trade-offs. (Background & Requirement)\n- Competitive/market effects: the rule imposes a compliance cost on operators using the specified parts/engines; manufacturers or MROs that offer replacement parts or inspections may see increased demand. There is no change to ownership or contracting freedom — operators remain free to contract inspections or replacements to third parties. (Applicability & Requirement)\n\n**Implementation risks and practical notes:**\n\n- The inspection’s effectiveness depends on correct FPI technique and adherence to the GE manual (GEK 99410, section 71-21-02). (Requirement)\n- The AD references FAA AD 2003-20-07, so operators may need to consult that document for related guidance or cross-referenced procedures. (Note 2)\n\n**Source-claimed purpose vs. concrete mechanism:**\n\n- The directive’s stated goal is to prevent mount platform failure by detecting cracking early (Background). Mechanically, it does this by mandating scheduled FPIs for specific part numbers and setting firm cycle-based deadlines for initial and repeat inspections (Requirement & Compliance). The concrete cost is inspection and any resulting repairs or replacements; the concrete benefit is earlier detection of fatigue-related defects. The directive does not mandate replacement of the parts as a first step; it mandates inspection and leaves corrective action to maintenance procedures that follow detection.\n\n(References: Applicability; Requirement; Compliance; Background; Note 2.)"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This Airworthiness Directive maintains its original narrow scope. It addresses a specific unsafe condition identified in specific engine mount platform part numbers. There is no evidence of scope creep; the directive remains tightly focused on the fatigue life issue and the required inspection protocol."},"complexity_factors":["Single, clearly defined applicability (two specific part numbers on one engine model)","Straightforward two-path compliance structure (previously inspected vs. not previously inspected)","Minimal cross-referencing (only one external reference to FAA AD 2003-20-07 in a non-binding note)","No defined terms section — technical terms (FPI, CSN, CSLI) are industry standard or explained by context","Single requirement with clear, time-based triggers","Short document (approximately 250 words of substantive text)"],"plain_english_summary":"This CASA safety order addresses fatigue cracking in cast forward engine mount platforms on certain GE CF6-80E1A2 engines (used on Airbus A330 and similar types). It requires operators to perform fluorescent penetrant inspections (FPI) at specified intervals (initial check or before ~6,360 flight cycles, then every ~4,000 cycles) to detect cracks early.  \n\nThe measure affects airlines/operators of the specified engines and prevents catastrophic engine separation by catching fatigue damage before 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-cf6-53-forward-engine-mount-platforms","history":"/api/acts/ad-cf6-53-forward-engine-mount-platforms/history","analysis":"/api/acts/ad-cf6-53-forward-engine-mount-platforms/analysis","conflicts":"/api/acts/ad-cf6-53-forward-engine-mount-platforms/conflicts","importantCases":"/api/acts/ad-cf6-53-forward-engine-mount-platforms/important-cases","documents":"/api/acts/ad-cf6-53-forward-engine-mount-platforms/documents"}}