{"id":"F2011L00236","name":"AD/CF6/70 Amdt 1 - Low Pressure Turbine Case","slug":"ad-cf6-70-amdt-1-low-pressure-turbine-case","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":86486,"registerId":"commonwealth-F2011L00236-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"General Electric Turbine Engines - CF6 S","sectionType":"division","heading":"General Electric Turbine Engines - CF6 Series","content":"### General Electric Turbine Engines - CF6 Series\n\n| AD/CF6/70 Amdt 1 | Low Pressure Turbine Case | 3/2011 |\n| ---------------- | ------------------------- | ------ |\n\n```html\n

Applicability:

General Electric Company (GE) CF6-80C2 and CF6-80E1 engines specified in the following Table 1 of this AD.

Note 1: These engines are installed on, but not limited to, Airbus A300, A310, and A330 series aeroplanes, Boeing 747 and 767 series airplanes, and McDonnell Douglas MD11 series aeroplanes.

Table 1 - Applicable Engines by Engine Model

Engine Model

With Low-Pressure Turbine (LPT)
Case Part No. (P/N) Installed

CF6-80C2A1, -80C2A2, -80C2A3,
-80C2A5, -80C2A5F, -80C2A8,
-80C2B1, -80C2B1F, -80C2B1F1,
-80C2B1F2, -80C2B2, -80C2B2F,
-80C2B3F, -80C2B4, -80C2B4F,
-80C2B5F, -80C2B6, -80C2B6F,
-80C2B6FA, -80C2B7F,
-80C2B8F, -80C2D1F, and
-80C2L1F

1336M99G01, 1336M99G02, 1336M99G03, 1336M99G04, 1336M99G06, 1336M99G07, 1336M99G08, 1336M99G09, 1336M99G10, 1336M99G12, 1336M99G13, or 1336M99G15

1647M68G05, 1647M68G08, 1647M68G09, or 1647M68G15


1713M73G01, 1713M73G02, or 1713M73G05

9367M99G11or 9367M99G17

CF6-80E1A1, -80E1A2, -80E1A3,
-80E1A4, -80E1A4/B

1647M68G02, 1647M68G04, 1647M68G07, 1647M68G12, or 1647M68G13

Requirement:

1. CF6-80C2 Engines:

For CF6-80C2 engines specified in Table 1 of this AD that have an LPT case with a P/N specified in Table 1 of this AD, do either of the following:

(a) Rework the LPT case to install skin doubler pads and deflectors. Use the Accomplishment Instructions of GE Service Bulletin (SB) No. CF6-80C2 S/B 72-1171, Revision 1, dated 1 February 2006, and Repair Document (RD) No. 935-314-S4, dated 28 January 2008, to rework the LPT case; or

(b) Install an LPT case that has skin doubler pads and deflectors.

\n```\n\n| | 2. CF6-80E1 Engines:For CF6-80E1 engines specified in Table 1 of this AD that have an LPT case with a P/N specified in Table 1 of this AD, do either of the following:(a) Rework the LPT case to install skin doubler pads and deflectors. Use the Accomplishment Instructions of SB No. CF6-80E1 S/B 72-0303, Revision 1, dated 1 February 1, 2006, and RD No. 935-314-S4, dated January 28, 2008, to rework the LPT case; or(b) Install an LPT case that has skin doubler pads and deflectors.Previous CreditIf you previously performed the actions specified in Requirement 1 through Requirement 2 of this AD, using the rework procedures in the following service documents before the effective date of this AD, you have satisfied the compliance requirements of this AD:(a) GE SB No. CF6-80C2 S/B 72-1171, dated 25 May 2005 and RD No.935-314-S2, dated 4 January 2006, or RD No. 935-314-S3, dated10 August 2006.(b) GE SB No. CF6-80E1 S/B 72-0303, dated 1 June 2005 and RD No. 935-314-S2, dated 4 January 2006, or RD No. 935-314-S3, dated 10 August 2006.Later revisions to GE SB No. CF6-80C2 S/B 72-1171, Revision 1, dated 1 February 2006 or GE SB No. CF6-80E1 S/B 72-0303, Revision 1, dated 1 February 1, 2006, approved by the United States Federal Aviation Administration (FAA) as an Alternative Method of Compliance (AMOC) to FAA 2008-21-11 Amdt 39-15695, are considered acceptable for compliance with the equivalent Requirements of this AD.Parts IdentificationLPT case skin doubler pads and deflectors are distinct and separate parts. For identification purposes, a deflector pad is a square-shaped plate with no threaded stud on it, and a deflector has a threaded stud on it.Note 2: FAA AD 2008-21-11 Amdt 39-15695 dated 10 October 2008 refers. |\n| ----------- | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Compliance: | The next time the LPT module is completely disassembled to piece-part level, but not to exceed 8 years after the original effective date of this AD, unless the actions have already been done. |\n| | This Amendment becomes effective on 14 February 2011. |\n\n| Background: | This AD results from four events in which hardware fragments were liberated into the engine flowpath and wore through LPT cases on CF6-80C2 and CF6-80E1 series engines. The issuing of this AD is intended to prevent an uncontained release of engine debris and loss of the structural integrity of the mount system that supports the engine. Loss of the mount system structural integrity could result in the engine separating from the aeroplane.Amendment 1 notates the acceptability of an FAA Approved AMOC for compliance with the equivalent requirements of this AD.The original issue of this Directive became effective on 18 December 2008. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n\n![](image.001.png)\n\nDavid Villiers \nDelegate of the Civil Aviation Safety Authority\n\n8 February 2011","sortOrder":0},{"sectionNumber":"AD/CF6/70 Amdt 1","sectionType":"part","heading":"AD/CF6/70 Amdt 1","content":"## AD/CF6/70 Amdt 1","sortOrder":1},{"sectionNumber":"Low Pressure Turbine Case","sectionType":"part","heading":"Low Pressure Turbine Case","content":"## Low Pressure Turbine Case","sortOrder":2},{"sectionNumber":"3/2011","sectionType":"part","heading":"3/2011","content":"## 3/2011","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":true,"description":"Amendment 1 modifies the compliance mechanism by noting that FAA‑approved AMOCs and later FAA‑approved revisions of the cited GE service bulletins/repair documents are acceptable for meeting the AD's requirements (Amendment 1; Requirement). The amendment does not add new engine models or new mandatory corrective actions beyond accepting those alternative compliance approvals. The original AD became effective 18 December 2008; this amendment is effective 14 February 2011 (Background; Compliance)."},"complexity_factors":["Extensive list of affected engine models and multiple LPT case part numbers to match (Table 1).","Two alternative compliance routes for each engine: rework per specific GE Service Bulletins/Repair Documents or replacement with a pre‑modified LPT case (Requirement 1–2).","Cross‑references to multiple GE SBs and RDs with specific revision dates and prior‑credit provisions requiring historical compliance checks (Requirement; Previous Credit).","Timing condition tethered to maintenance state: 'next complete LPT module disassembly to piece‑part level' or an absolute 8‑year cap (Compliance).","Parts‑identification nuance distinguishing 'deflector pad' versus 'deflector' for compliance verification (Parts Identification).","Regulatory interplay: Amendment 1 accepts FAA‑approved AMOCs as alternative methods of compliance, adding inter‑jurisdictional approval dependencies (Amendment 1).","Recordkeeping and verification burden for operators and maintainers to demonstrate use of approved SB/RD revisions or AMOCs."],"plain_english_summary":"**What it does:** Requires operators of specified GE CF6‑80C2 and CF6‑80E1 engines (listed by model and LPT case P/N) to either rework the low‑pressure turbine (LPT) case to add skin doubler pads and deflectors or to install an LPT case that already has them. Compliance must occur at the next complete LPT module disassembly to piece‑part level or within eight years. \n\nThe AD says these measures are to prevent liberated hardware wearing through LPT cases and possible engine separation (Background). Operators bear the cost and downtime; FAA‑approved AMOCs and specified GE service bulletins set acceptable procedures."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This is Amendment 1 to an existing Airworthiness Directive. The amendment is narrow and technical — it simply adds flexibility by allowing later FAA-approved revisions of the service bulletins to be used for compliance. The core safety purpose (preventing LPT case penetration and potential engine separation) remains unchanged from the original December 2008 directive."},"complexity_factors":["Multiple engine model variants with specific part number combinations (Table 1 contains 23+ engine models and 20+ part numbers)","Two distinct compliance pathways for each engine type: rework existing case OR install new case","Cross-references to external technical documents (GE Service Bulletins and Repair Documents with specific revision dates)","Previous credit provisions allowing compliance via earlier versions of service documents","Conditional compliance deadline based on maintenance events ('next time LPT module is completely disassembled to piece-part level') with absolute 8-year cap","Incorporation by reference of FAA Alternative Methods of Compliance (AMOCs)","Technical identification requirements distinguishing between 'deflector pads' and 'deflectors' based on physical characteristics"],"plain_english_summary":"This AD requires operators of certain GE CF6-80C2 and CF6-80E1 engines (used on A300/A310/A330, B747/B767, MD‑11 types) to reinforce the Low Pressure Turbine (LPT) case with skin doubler pads and deflectors to prevent debris wear. It’s prompted by incidents of case wear risking uncontained engine failure and possible engine separation. Compliance is at the next LPT teardown or within 8 years. The amendment also permits later FAA‑approved service bulletin revisions as an acceptable compliance method."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-cf6-70-amdt-1-low-pressure-turbine-case","history":"/api/acts/ad-cf6-70-amdt-1-low-pressure-turbine-case/history","analysis":"/api/acts/ad-cf6-70-amdt-1-low-pressure-turbine-case/analysis","conflicts":"/api/acts/ad-cf6-70-amdt-1-low-pressure-turbine-case/conflicts","importantCases":"/api/acts/ad-cf6-70-amdt-1-low-pressure-turbine-case/important-cases","documents":"/api/acts/ad-cf6-70-amdt-1-low-pressure-turbine-case/documents"}}