{"id":"F2005L01307","name":"AD/JT8D/27 Amdt 2 - First Stage Compressor Hub","slug":"ad-jt8d-27-amdt-2-first-stage-compressor-hub","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":35049,"registerId":"commonwealth-F2005L01307-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/27 Amdt 2 | First Stage Compressor Hub | 7/2005 |\n| ----------------- | -------------------------- | ------ |\n\n| Applicability: | Pratt & Whitney (PW) Model JT8D-9, -9A, -11, -15, -15A, -17, -17A, -17R, and-17AR turbofan engines containing front compressor fan hub Part Number (P/N) 817401 with the following serial numbers: J78892 through J80538, K32019 through K34018, L32197 through L34133, or M05722 through M07296; and all serial numbers of fan hubs P/N 594301, 640601, 743301, 749801, 750101, 791801, 806001.                                                                                       |\n| -------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Inspect and / or shotpeen and / or remove from service front compressor fan hub as per Requirements of FAA Airworthiness Directive (AD) 95-10-10.Note: FAA AD 95-10-10 Amendment 39-9227refers.                                                                                                                                                                                                                                                                                        |\n| Compliance:    | Unless previously accomplished, as per compliance schedule of the FAA AD95-10-10 Amendment 39-9227.                                                                                                                                                                                                                                                                                                                                                                                    |\n|                | This Amendment becomes effective on 7 July 2005.                                                                                                                                                                                                                                                                                                                                                                                                                                       |\n| Background:    | Fracture of the front compressor fan hub can result in an uncontained engine failure and damage to the aircraft. The requirements of this AD are aimed at prevention of the hub fracture and resultant uncontained engine failure.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.Amendment 1 of this Directive became effective on 9 December 1993. |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n25 May 2005","sortOrder":0},{"sectionNumber":"AD/JT8D/27 Amdt 2","sectionType":"part","heading":"AD/JT8D/27 Amdt 2","content":"## AD/JT8D/27 Amdt 2","sortOrder":1},{"sectionNumber":"First Stage Compressor Hub","sectionType":"part","heading":"First Stage Compressor Hub","content":"## First Stage Compressor Hub","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":4,"scope_assessment":{"changed":false,"description":"The amendment harmonises references by deleting the manufacturer's document and adopting FAA AD 95‑10‑10 (Background). It does not broaden the listed engine/part/serial‑number applicability nor add new mandatory actions beyond those in the FAA AD; the substantive safety measures remain the same."},"complexity_factors":["Applicability lists multiple engine models, specific part numbers and several serial‑number ranges, creating a narrow but detailed scope (Applicability).","The AD does not specify detailed procedures or intervals itself but incorporates FAA AD 95‑10‑10 by reference, adding a cross‑jurisdictional dependency (Requirement; Compliance).","Multiple remedy options are allowed (inspect, shotpeen, or remove from service), which require technical assessment and maintenance decisions by operators (Requirement).","Amendment updates references (deletes manufacturer's document reference and refers to FAA AD) rather than changing substantive measures, which affects document provenance and traceability (Background).","Compliance timing and enforcement rest on an external schedule and on CASA's adoption, requiring operators to follow another instrument's timelines (Compliance)."],"plain_english_summary":"This instrument requires operators of specified Pratt & Whitney JT8D turbofan engines to inspect, shot‑peen or remove from service certain first‑stage compressor fan hubs (listed by part and serial number) to prevent hub fracture and uncontained engine failure. It adopts the procedures and compliance timing set out in FAA Airworthiness Directive 95‑10‑10, making those actions mandatory for the affected engines from 7 July 2005. Operators pay for inspections, repairs or replacement; CASA enforces compliance."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This amendment maintains the original safety purpose of preventing fan hub fractures. The only change is administrative: replacing manufacturer document references with direct FAA AD references to harmonise with the certificating authority. The substantive safety scope remains unchanged."},"complexity_factors":["Short, single-purpose directive with one primary requirement","Heavy reliance on external document (FAA AD 95-10-10) — the actual detailed requirements are not reproduced in the Australian text","Specific but limited applicability criteria: 8 engine models, 7 part numbers, and specific serial number ranges","No nested exceptions or conditional logic within the Australian text itself","Simple compliance structure: 'do what the FAA says, when the FAA says to do it'","Minimal defined terms (only standard aviation abbreviations like P/N for Part Number)"],"plain_english_summary":"This is an **Australian airworthiness directive** — a legally binding safety order issued by the Civil Aviation Safety Authority (CASA). It applies to specific Pratt & Whitney jet engines used in aircraft.\n\n**What it does:**\n- Requires owners and operators of certain JT8D model turbofan engines to inspect, treat, or replace a critical part called the **first stage compressor fan hub** (the central component that holds the fan blades at the front of the engine).\n- The directive references an American safety order (FAA AD 95-10-10) and tells Australian operators to follow those same requirements.\n\n**Who it affects:**\n- Airlines and aircraft operators using Pratt & Whitney JT8D-9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR engines with specific fan hub part numbers and serial numbers.\n- These engines are commonly found on older Boeing 727 and 737 aircraft, as well as McDonnell Douglas DC-9 and MD-80 series planes.\n\n**Why it matters:**\n- A cracked or fractured fan hub can break apart during flight, causing **uncontained engine failure** — where engine parts burst out of the engine casing and potentially strike the aircraft fuselage, fuel tanks, or passengers.\n- This directive prevents catastrophic accidents by mandating inspections and maintenance before the hub reaches a dangerous condition.\n\n**Key change in this version:**\n- This amendment removes references to the manufacturer's own documents and instead points directly to the US Federal Aviation Administration's safety order. This **harmonises** (aligns) Australian rules with American standards, making it easier for international operators to comply with one set of requirements."}},"importantCases":[],"_links":{"self":"/api/acts/ad-jt8d-27-amdt-2-first-stage-compressor-hub","history":"/api/acts/ad-jt8d-27-amdt-2-first-stage-compressor-hub/history","analysis":"/api/acts/ad-jt8d-27-amdt-2-first-stage-compressor-hub/analysis","conflicts":"/api/acts/ad-jt8d-27-amdt-2-first-stage-compressor-hub/conflicts","importantCases":"/api/acts/ad-jt8d-27-amdt-2-first-stage-compressor-hub/important-cases","documents":"/api/acts/ad-jt8d-27-amdt-2-first-stage-compressor-hub/documents"}}