{"id":"F2005L01306","name":"AD/JT8D/22 Amdt 5 - Combustion Chamber Outer Case","slug":"ad-jt8d-22-amdt-5-combustion-chamber-outer-case","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":35047,"registerId":"commonwealth-F2005L01306-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Pratt and Whitney Turbine Engines - JT8D","sectionType":"division","heading":"Pratt and Whitney Turbine Engines - JT8D Series","content":"### Pratt and Whitney Turbine Engines - JT8D Series\n\n| AD/JT8D/22 Amdt 5 | Combustion Chamber Outer Case | 7/2005 |\n| ----------------- | ----------------------------- | ------ |\n\n| Applicability: | Pratt & Whitney (PW) Models JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15,-15A, -17, -17A, -17R, and -17AR turbofan engines, with combustion chamber outer case (CCOC) part numbers (P/Ns) 490547, 542155, 616315, 728829, 728829-001, 730413, 730413-001, 730414, 730414-001, 767197, 767279, 767279-001 installed.                                                                                                                                                                                                                                                                                          |\n| -------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | To prevent CCOC flange cracks that could result in uncontained engine failure, in-flight engine shutdown, engine cowl release, and airframe damage, comply with the Requirements of FAA Airworthiness Directive (AD) 96-23-14 Amendment 39-9820.Note: FAA AD 96-23-14 Amendment 39-9820 refers.                                                                                                                                                                                                                                                                                                                   |\n| Compliance:    | Unless previously accomplished, as per compliance schedule of the FAA AD96-23-14 Amendment 39-9820.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               |\n|                | This Amendment becomes effective on 7 July 2005.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  |\n| Background:    | There have been reports of crack origins in the forward face of the rear flange of the CCOC. These cracks, if undetected, may cause CCOC failure leading to uncontained engine failure, in-flight engine shutdown, engine cowl release, and airframe damage. The actions specified by this AD are intended to address the unsafe condition identified above.The current amendment deletes reference to the manufacturer’s document and refers to the FAA AD as part of the harmonisation with the engine certificating Authority requirements.Original issue of this Directive became effective on 25 April 1996. |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n25 May 2005","sortOrder":0},{"sectionNumber":"AD/JT8D/22 Amdt 5","sectionType":"part","heading":"AD/JT8D/22 Amdt 5","content":"## AD/JT8D/22 Amdt 5","sortOrder":1},{"sectionNumber":"Combustion Chamber Outer Case","sectionType":"part","heading":"Combustion Chamber Outer Case","content":"## Combustion Chamber Outer Case","sortOrder":2},{"sectionNumber":"7/2005","sectionType":"part","heading":"7/2005","content":"## 7/2005","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"},"flash_summary":{"complexity_score":2,"scope_assessment":{"changed":false,"description":"This amendment does not materially expand the original safety scope. The original AD targeted the same unsafe condition (CCOC flange cracks). The current amendment deletes a reference to the manufacturer’s document and instead refers directly to the FAA AD for the required actions, so it harmonises the reference and centralises the technical requirements in the FAA document rather than adding new obligations or widening applicability."},"complexity_factors":["Short instrument (single-page AD-style), limited text","Single operative requirement: adopt FAA AD 96-23-14 Amendment 39-9820","Applicability limited to specific JT8D models and an explicit list of CCOC part numbers","No nested exceptions or alternative compliance routes set out in this document","Key procedural details and schedules are externalised to the FAA AD (cross-reference increases operational dependency but keeps this instrument simple)","Amendment is administrative in nature (removes manufacturer document reference) rather than substantive"],"plain_english_summary":"This instrument requires operators and maintenance organisations of certain Pratt & Whitney JT8D engines with specified combustion‑chamber outer case part numbers to follow FAA Airworthiness Directive 96‑23‑14 (Amendment 39‑9820) for inspection and repair. It matters because the FAA AD aims to prevent flange cracks that can lead to uncontained engine failure, in‑flight shutdown or airframe damage; affected operators bear inspection, repair, parts and downtime costs."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This amendment maintains the original scope of the 1996 airworthiness directive. The only change is administrative: replacing manufacturer document references with direct reference to the FAA directive to harmonise with the certificating authority. The safety objective (preventing combustion chamber outer case failures) and affected engine population remain unchanged."},"complexity_factors":["Single technical requirement: compliance with an external FAA directive","Limited applicability: specific engine models and part numbers listed exhaustively","No nested exceptions or conditional logic — straightforward 'unless previously accomplished' compliance","Short document with minimal defined terms (only standard aviation abbreviations like CCOC, P/N, FAA AD)","Clear compliance deadline (effective date specified)","Background section provides plain explanation of safety risk"],"plain_english_summary":"This is an **Australian aviation safety rule** that applies to specific Pratt & Whitney jet engines used in aircraft. It requires airlines and aircraft operators to inspect and maintain the **combustion chamber outer case** — a critical engine component — to prevent dangerous cracks from developing.\n\n**What it does:**\n- Mandates compliance with an American safety directive (FAA AD 96-23-14) for certain JT8D engine models\n- Requires inspections to detect cracks in the rear flange of the combustion chamber outer case\n- Aims to prevent **uncontained engine failure** (when engine parts break off and fly out, potentially damaging the aircraft)\n\n**Who it affects:**\n- Aircraft operators using Pratt & Whitney JT8D engines with specific part numbers\n- Maintenance organisations servicing these engines\n- The Civil Aviation Safety Authority (CASA) as the regulator\n\n**Why it matters:**\nCracks in this engine part, if undetected, can cause catastrophic engine failure during flight, potentially leading to engine shutdown, parts damaging the aircraft body, or even loss of the aircraft. This amendment updates the original 1996 rule by removing references to manufacturer documents and instead pointing directly to the FAA directive — a process called **harmonisation** (aligning Australian rules with those of the engine's certifying authority, the US Federal Aviation Administration)."}},"importantCases":[],"_links":{"self":"/api/acts/ad-jt8d-22-amdt-5-combustion-chamber-outer-case","history":"/api/acts/ad-jt8d-22-amdt-5-combustion-chamber-outer-case/history","analysis":"/api/acts/ad-jt8d-22-amdt-5-combustion-chamber-outer-case/analysis","conflicts":"/api/acts/ad-jt8d-22-amdt-5-combustion-chamber-outer-case/conflicts","importantCases":"/api/acts/ad-jt8d-22-amdt-5-combustion-chamber-outer-case/important-cases","documents":"/api/acts/ad-jt8d-22-amdt-5-combustion-chamber-outer-case/documents"}}