{"id":"F2005L01313","name":"AD/JT8D/34 Amdt 1 - 4th Stage LPT Hub Inspection","slug":"ad-jt8d-34-amdt-1-4th-stage-lpt-hub-inspection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":35056,"registerId":"commonwealth-F2005L01313-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/34 Amdt 1 | 4th Stage LPT Hub Inspection | 7/2005 |\n| ----------------- | ---------------------------- | ------ |\n\n| Applicability: | Pratt & Whitney (PW) Models JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -17, and -17R turbofan engines, as identified in FAA Airworthiness Directive (AD)97-19-12 Amendment 39-10133.                                                                                                                                                                                                                                                                                                                                                |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | To prevent 4th stage Low Pressure Turbine (LPT) blade failure due to the hub cracking, comply with the Requirements of FAA AD (AD) 97-19-12 Amendment39-10133.Note: FAA AD 97-19-12 Amendment 39-10133 refers.                                                                                                                                                                                                                                                                                                                              |\n| Compliance:    | Unless previously accomplished, as per compliance schedule of the Requirement Document.                                                                                                                                                                                                                                                                                                                                                                                                                                                     |\n|                | This Amendment becomes effective on 7 July 2005.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            |\n| Background:    | There has been a report of an uncontained 4th stage LPT blade release due to the hub cracking. Such an event can result in an uncontained engine failure and damage to the aircraft. 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 29 January 1998. |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n25 May 2005","sortOrder":0},{"sectionNumber":"AD/JT8D/34 Amdt 1","sectionType":"part","heading":"AD/JT8D/34 Amdt 1","content":"## AD/JT8D/34 Amdt 1","sortOrder":1},{"sectionNumber":"4th","sectionType":"part","heading":"Stage LPT Hub Inspection","content":"## 4th Stage LPT Hub Inspection","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":3,"scope_assessment":{"changed":false,"description":"This amendment does not materially broaden the Directive’s substantive scope. It replaces a reference to the manufacturer’s document with a direct reference to the FAA AD (harmonisation with the engine certificating authority). The unsafe condition addressed (4th-stage LPT hub cracking and potential blade release) and the set of affected engine models remain the same as the original Directive."},"complexity_factors":["Short, single-issue instrument focused on one inspection requirement","Direct cross-reference to one external document: FAA AD 97-19-12 Amendment 39-10133","Applicability list contains multiple engine model variants (12 variants listed)","Compliance timing and technical detail are externalised to the FAA AD (adds dependency on another document)","Minimal conditional logic, no nested exceptions or multiple Parts"],"plain_english_summary":"This instrument adopts FAA AD 97-19-12 Amendment 39-10133, requiring operators of certain Pratt & Whitney JT8D series engines to perform FAA-prescribed inspections and corrective actions on the 4th‑stage low‑pressure turbine (LPT) hub to detect and address cracking that can cause an uncontained blade release. \n\nIt affects aircraft owners/operators and maintenance organisations for the listed JT8D models, who bear inspection, repair and downtime costs; effective 7 July 2005."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This amendment maintains the original scope of inspecting 4th stage LPT hubs for cracking. The only change is procedural: replacing a reference to the manufacturer's document with a direct reference to the FAA Airworthiness Directive. This is a harmonisation measure that does not expand or alter the substantive safety requirements."},"complexity_factors":["Very short document (approximately 250 words)","Only 2 substantive requirements: (1) inspect for hub cracks, (2) comply with referenced FAA directive","No defined terms section — all technical terms are explained in context or use standard aviation abbreviations","Single cross-reference to external document (FAA AD 97-19-12)","No conditional logic or nested exceptions — compliance is straightforward unless already done","Clear applicability table listing specific engine models"],"plain_english_summary":"This is an **Australian aviation safety directive** that requires specific inspections on certain Pratt & Whitney jet engines used in aircraft.\n\n**What it does:**\n- Orders airlines and aircraft operators to inspect the **4th stage Low Pressure Turbine (LPT) hub** on specific Pratt & Whitney JT8D engine models\n- The inspection looks for **cracks in the turbine hub** that could cause blades to break off and damage the aircraft\n\n**Who it affects:**\n- Airlines and operators using Pratt & Whitney JT8D engines (models -1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -17, and -17R)\n- These engines are commonly used on older Boeing 727 and 737 aircraft, plus McDonnell Douglas DC-9 and MD-80 series planes\n\n**Why it matters:**\n- A cracked hub can cause **uncontained engine failure** — where broken parts fly out of the engine casing and potentially damage the aircraft or injure passengers\n- This directive was triggered by an actual incident where a blade broke loose due to hub cracking\n- This amendment (Update 1) simplifies the rules by directly referencing the US Federal Aviation Administration (FAA) directive instead of the manufacturer's documents, making it easier for international operators to comply\n\n**Key change in this amendment:**\n- Previously, operators had to follow the manufacturer's instructions\n- Now they follow the **FAA Airworthiness Directive 97-19-12** directly — this \"harmonisation\" means Australian and American safety requirements now match"}},"importantCases":[],"_links":{"self":"/api/acts/ad-jt8d-34-amdt-1-4th-stage-lpt-hub-inspection","history":"/api/acts/ad-jt8d-34-amdt-1-4th-stage-lpt-hub-inspection/history","analysis":"/api/acts/ad-jt8d-34-amdt-1-4th-stage-lpt-hub-inspection/analysis","conflicts":"/api/acts/ad-jt8d-34-amdt-1-4th-stage-lpt-hub-inspection/conflicts","importantCases":"/api/acts/ad-jt8d-34-amdt-1-4th-stage-lpt-hub-inspection/important-cases","documents":"/api/acts/ad-jt8d-34-amdt-1-4th-stage-lpt-hub-inspection/documents"}}