{"id":"F2006B08467","name":"AD/CF6/23 - High Pressure Turbine Rotor Stage 1 Disc/Shaft Inspection and Removal From Service","slug":"ad-cf6-23-high-pressure-turbine-rotor-stage-1-disc-shaft-inspection-and-removal-from-service","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":51122,"registerId":"commonwealth-F2006B08467-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/CF6/23 - High Pressure Turbine Rotor Stage 1 Disc/Shaft Inspection and Removal From Service","content":"---\nmeta-content-style-type: text/css\nmeta-content-type: application/xhtml+xml; charset=utf-8\nmeta-generator: Aspose.Words for .NET 22.10.0\n---\n\n?xml version=\"1.0\" encoding=\"utf-8\" standalone=\"no\"?>\n\nCOMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n \n\n![](image.001.png)  General Electric Turbine Engines - CF6 Series\n\n \n\n# AD/CF6/23 High Pressure Turbine Rotor Stage 1 Disc/Shaft\n\nInspection and Removal From Service\n\nApplicability: CF6-80A Series.\n\n \n\nRequirement: Action in accordance with the technical requirements of FAA AD 92-04-08.\n\nNote: GE Service Bulletin 72-605 refers.\n\n# 10/92\n\n \n\nCompliance: As specified in the Requirement Document with an effective date of 17 September 1992.\n\n \n\nBackground: The FAA AD was prompted by a report of an uncontained separation of a CF6-80A high pressure turbine rotor stage 1 disk/shaft. It requires removal from service of certain disk/shafts that may have surface damage in the bore area and a one time eddy current and fluorescent penetration of other discs/shafts.\n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The directive adopts the FAA AD 92‑04‑08 requirements for CF6‑80A stage‑1 high‑pressure turbine disc/shaft inspection and removal without adding or narrowing scope in the text provided; compliance follow the FAA technical requirements and GE Service Bulletin as specified (effective 17 September 1992)."},"complexity_factors":["Cross-reference to FAA AD 92-04-08 requires implementing another regulator's technical text rather than standalone rules.","Technical non‑destructive testing specified (eddy‑current and fluorescent‑penetrant) requires specialist capability and interpretation.","Removal‑from‑service criterion depends on detection of ‘‘bore‑area surface damage’’, which can require judgement and documented inspection records.","Applicability limited to CF6‑80A series—operators must identify affected fleet and schedule inspections within the compliance timeline (effective 17 Sep 1992).","Reference to GE Service Bulletin 72‑605 creates an additional manufacturer technical source operators must follow."],"plain_english_summary":"This Airworthiness Directive requires operators of General Electric CF6‑80A engines to inspect the stage‑1 high‑pressure turbine rotor disc/shaft and to remove affected parts, implementing the technical requirements of FAA AD 92‑04‑08 (see GE Service Bulletin 72‑605). It mandates a one‑time eddy‑current and fluorescent‑penetrant inspection and removal from service of discs/shafts with bore‑area surface damage (compliance as at 17 September 1992), placing inspection and removal obligations on engine operators to address a reported uncontained separation."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This AD maintains its original narrow scope: addressing a specific safety defect in a specific engine model. It has not expanded beyond its original purpose of preventing uncontained turbine failures in CF6-80A engines."},"complexity_factors":["Very short document (approximately 150 words of substantive content)","Only 1 defined applicability (CF6-80A Series)","Single requirement referencing external technical document (FAA AD 92-04-08)","No nested exceptions or conditional logic — binary compliance (inspect or remove)","No cross-references to other Australian legislation beyond Civil Aviation Regulations 1998 Part 39","Background provides clear safety rationale without legal ambiguity"],"plain_english_summary":"This is an **Airworthiness Directive (AD)** — essentially a mandatory safety order for aircraft. It applies to **General Electric CF6-80A series jet engines**, which are commonly used on commercial aircraft like the Boeing 767 and Airbus A300.\n\n**What it does:**\n- Requires airlines and aircraft operators to **inspect or remove from service** specific high-pressure turbine parts (the \"Stage 1 disc/shaft\" — a critical rotating component in the engine's hot section)\n- Mandates two types of inspection for some parts: **eddy current testing** (using electromagnetic fields to detect cracks) and **fluorescent penetrant inspection** (using dye and UV light to find surface defects)\n- Requires immediate **removal from service** of certain disc/shafts that may have **surface damage in the bore area** (the inner hole of the disc where it mounts on the shaft)\n\n**Why it matters:**\nAn **uncontained engine failure** occurred — meaning a rotating part broke apart and escaped the engine casing. This is extremely dangerous as shrapnel can damage the aircraft, injure passengers, or cause catastrophic failure. The FAA (US regulator) issued this directive first, and Australia adopted it to ensure the same safety standard applies here.\n\n**Who must comply:**\nAny Australian operator using CF6-80A engines — typically airlines, cargo operators, or maintenance organisations. Compliance was required from **17 September 1992**."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cf6-23-high-pressure-turbine-rotor-stage-1-disc-shaft-inspection-and-removal-from-service","history":"/api/acts/ad-cf6-23-high-pressure-turbine-rotor-stage-1-disc-shaft-inspection-and-removal-from-service/history","analysis":"/api/acts/ad-cf6-23-high-pressure-turbine-rotor-stage-1-disc-shaft-inspection-and-removal-from-service/analysis","conflicts":"/api/acts/ad-cf6-23-high-pressure-turbine-rotor-stage-1-disc-shaft-inspection-and-removal-from-service/conflicts","importantCases":"/api/acts/ad-cf6-23-high-pressure-turbine-rotor-stage-1-disc-shaft-inspection-and-removal-from-service/important-cases","documents":"/api/acts/ad-cf6-23-high-pressure-turbine-rotor-stage-1-disc-shaft-inspection-and-removal-from-service/documents"}}