{"id":"F2006B08471","name":"AD/CF6/28 - CF6-80C2 Stage 1 High Pressure Turbine Disc Inspection","slug":"ad-cf6-28-cf6-80c2-stage-1-high-pressure-turbine-disc-inspection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":51133,"registerId":"commonwealth-F2006B08471-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/CF6/28 - CF6-80C2 Stage 1 High Pressure Turbine Disc Inspection","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\nAD/CF6/28 CF6-80C2 Stage 1 High Pressure Turbine Disc Inspection\n\n\n7/94\n\n \n\nApplicability: CF6-80C2 Engines.\n\n \n\nRequirement: Action in accordance with the technical requirements of FAA AD 94-06-03.\n\n \n\nNote: General Electric Service Bulletin No 72-614 Revision 1 and All Operator’s Wire 92-80C-16 of 22 April 1992 refer.\n\n \n\nCompliance: This directive is effective from 27 Jun 1994.\n\n \n\nBackground:  This directive requires an inspection for cracks in the stage 1 high pressure turbine disc rim bolt holes and replacement as necessary with serviceable parts.\n\n \n\nIt originates from an uncontained stage 1 high pressure turbine failure.\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":3,"scope_assessment":{"changed":false,"description":"The instrument’s scope remains focused on CF6-80C2 engines and the inspection/replacement of stage 1 HPT disc rim bolt holes as set out in the directive. The AD prescribes compliance with FAA AD 94-06-03 and references GE Service Bulletin No. 72-614 Rev 1 and All Operator’s Wire 92-80C-16. The source text does not indicate any expansion or narrowing of scope beyond those elements (Applicability; Requirement; Note; Background; Compliance)."},"complexity_factors":["External technical dependency: the AD requires actions “in accordance with the technical requirements of FAA AD 94-06-03,” so operators must consult another regulator’s document for procedural detail (Requirement).","Narrow technical scope: applies only to CF6-80C2 engines and a specific component (stage 1 HPT disc rim bolt holes), limiting applicability but requiring specialised inspection (Applicability; Background).","Reference to manufacturer guidance: the AD points to GE Service Bulletin No. 72-614 Rev 1 and All Operator’s Wire 92-80C-16, adding documents to be reviewed (Note).","Binary compliance action: the required actions are inspection and replacement as necessary — straightforward in substance but potentially variable in execution depending on findings and FAA AD detail (Requirement; Background).","Legacy effective date: the directive is effective from a historical date (27 Jun 1994), which may require operators to verify historical compliance records (Compliance)."],"plain_english_summary":"This AD requires operators of General Electric CF6-80C2 engines to inspect the stage‑1 high‑pressure turbine disc rim bolt holes for cracks and replace any cracked parts, following the technical steps in FAA AD 94‑06‑03 (with GE Service Bulletin No. 72‑614 Rev 1 and AO‑Wire 92‑80C‑16 as guidance). Effective 27 June 1994, it aims to prevent uncontained HPT failures and shifts inspection and replacement costs to operators."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a discrete, time-limited safety directive issued in response to a specific incident. It has not expanded beyond its original purpose of mandating inspection and replacement of a specific engine component following an uncontained failure event."},"complexity_factors":["Extremely short document — only 8 substantive lines of regulatory text","No defined terms section — relies entirely on external references (FAA AD 94-06-03, GE Service Bulletin 72-614)","Single, clear applicability criterion (CF6-80C2 Engines)","Single compliance date with no conditional logic or phased implementation","No cross-references to other Australian legislation beyond the enabling regulation (CAR 1998 Part 39)","Incorporates by reference rather than restating technical requirements"],"plain_english_summary":"This is an **Airworthiness Directive (AD)** — essentially a mandatory safety order for aircraft engines. It applies to **General Electric CF6-80C2 jet engines**, commonly used on wide-body aircraft like Boeing 747s and Airbus A300s.\n\n**What it does:**\n- Requires airlines and maintenance crews to **inspect specific parts of the engine** — namely, the bolt holes in the rim of the stage 1 high pressure turbine disc\n- If cracks are found, the damaged disc **must be replaced** with a serviceable (airworthy) part\n\n**Why it exists:**\n- The directive was triggered by an **\"uncontained engine failure\"** — a serious incident where engine parts broke apart and escaped the engine casing, potentially damaging the aircraft or injuring people\n- The specific risk is **fatigue cracks** developing in the turbine disc bolt holes, which could lead to catastrophic failure\n\n**Who must comply:**\n- Any Australian operator (airline, cargo carrier, or private owner) with aircraft using CF6-80C2 engines\n- Compliance became mandatory from **27 June 1994**\n\n**Key point:** This isn't optional maintenance advice — it's **legally enforceable**. Non-compliance means the aircraft cannot legally fly in Australian airspace."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cf6-28-cf6-80c2-stage-1-high-pressure-turbine-disc-inspection","history":"/api/acts/ad-cf6-28-cf6-80c2-stage-1-high-pressure-turbine-disc-inspection/history","analysis":"/api/acts/ad-cf6-28-cf6-80c2-stage-1-high-pressure-turbine-disc-inspection/analysis","conflicts":"/api/acts/ad-cf6-28-cf6-80c2-stage-1-high-pressure-turbine-disc-inspection/conflicts","importantCases":"/api/acts/ad-cf6-28-cf6-80c2-stage-1-high-pressure-turbine-disc-inspection/important-cases","documents":"/api/acts/ad-cf6-28-cf6-80c2-stage-1-high-pressure-turbine-disc-inspection/documents"}}