AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section. General Electric Turbine Engines - CF6 Series AD/CF6/71 Life Limited Parts 4/2009 Applicability: General Electric Company CF6-80A, CF6-80C2, and CF6-80E1 series turbofan engines. Note 1: These engines are installed on, but not limited to, Airbus A300, A310, and A330 series, Boeing 747 and 767 series, and McDonnell Douglas MD-11 series aeroplanes. Requirement: 1. Revise the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA), and for air carrier operations revise the approved continuous airworthiness maintenance program, by adding the following: ''MANDATORY INSPECTIONS'' as detailed in Table 1 of this AD. Table 1 Part Nomenclature Part Number (P/N) Inspect per Engine Manual Inspection Chapter For CF6-80A Engines: Disk, Fan Rotor, All 72-21-03 Paragraph 3. Fluorescent-Penetrant Inspect, and 72-21-03 Paragraph 4. Eddy Current Inspect Stage 1 Fan Forward Shaft All 72-21-05 Paragraph 2. Magnetic Particle Inspect Fan Mid Shaft All 72-24-01 Paragraph 2. Magnetic Particle Inspect Disk, HPC Rotor, All 72-31-04 Paragraph 3. Fluorescent-Penetrant Inspect Stage One ** Disk, HPC Rotor, Stage Two All 72-31-05 Paragraph 4. Fluorescent-Penetrant Inspect Spool, HPC Rotor, Stage3-9 All 72-31-06 Paragraph 3. Fluorescent-Penetrant Inspect Disk, HPC Rotor, All 72-31-07 Paragraph 3. Fluorescent-Penetrant Inspect Stage 10 Spool, HPC Rotor, All 72-31-08 Paragraph 3.A. Fluorescent-Penetrant Inspect Stage 11-14 Rotating CDP Seal All 72-31-10 Paragraph 3. Fluorescent-Penetrant Inspect Disk Shaft, HPT Rotor Stage One All 72-53-02 Paragraph 3. Fluorescent-Penetrant-Inspect per 70-32-02, and 72-53-02 Paragraph 6.C. Disk Rim Bolt Hole Eddy Current Inspection, and 72-53-02 Paragraph 6.D. Disk Bore Eddy Current Inspection * Disk Shaft, HPT Rotor Stage One All 72-53-02 Paragraph 6.E. Disk Dovetail Slot Bottom Eddy Current Inspection * Disk Shaft, HPT Rotor, Stage One P/Ns 2047M33G01 thru G10, and P/N 9362M58G11 72-53-02 Paragraph 7. Disk Dovetail Slot Bottom Aft Corner Chamfers Eddy Current Inspection Disk, HPT Rotor, All 72-53-06 Paragraph 3. Fluorescent-Penetrant Inspection, and Stage Two 72-53-06 Paragraph 6. Eddy Current Inspection of Rim Bolt Holes for Cracks, and 72-53-06 Paragraph 7. Disk Bore Eddy Current Inspection Disk, LPT Rotor All 72-57-02 Paragraph 3. Fluorescent-Penetrant Inspection Stage 1-4 Shaft, LPT Rotor All 72-57-03 Paragraph 3. Fluorescent-Penetrant Inspection, and 72-57-03 Paragraph 6. Eddy Current Inspection For All CF6-80C2 Engines: Disk, Fan Rotor, All Task 72-21-03-200-000-004 Fluorescent-Penetrant Inspection, and Stage 1 Task 72-21-03-200-000-008 Eddy Current Inspect Fan Rotor Disk Stage 1 Bore, Forward and Aft Hub Faces, and Bore Radii Shaft, Fan Forward All Task 72-21-05-200-000-001 Fluorescent Penetrant Inspection, and Task 72-21-05-200-000-005 Vent Hole Eddy Current Inspection Fan Mid Shaft All Task 72-24-01-200-000-003 Magnetic Particle Inspection HPCR Stage 1 Disk All Task 72-31-04-200-000-002 Fluorescent Penetrant Inspection HPCR Stage 2 Disk All Task 72-31-05-200-000-002 Fluorescent Penetrant Inspection HPCR Stage 3-9 Spool All Task 72-31-06-200-000-001 Fluorescent Penetrant Inspection HPCR Stage 10 Disk All Task 72-31-07-200-000-001 Fluorescent Penetrant Inspection HPCR Stage 11-14 Spool/Shaft All Task 72-31-08-200-000-002 Fluorescent Penetrant Inspection No. 4 Bearing Rotating (CDP) Air Seal All Task 72-31-10-200-000-001 Fluorescent Penetrant Inspection or Task 72-31-10-200-000-A01 Fluorescent Penetrant Inspection HPCR Stage 10-14 Spool/Shaft All Task 72-31-22-200-000-002 Fluorescent Penetrant Inspection ** Disk/Shaft, HPT Rotor, Stage One All Task 72-53-02-200-000-001 (Inspection - Configuration 1), or Task 72-53-02-230-801 (Inspection - Configuration 2), Fluorescent-Penetrant Inspect, and Task 72-53-02-200-000-005 (Inspection - Configuration 1), or Task 72-53-02-250-802 (Inspection - Configuration 2), Disk Rim Bolt Hole Eddy Current Inspection, and Task 72-53-02-200-000-006 (Inspection - Configuration 1), or Task 72-53-02-250-803 (Inspection - Configuration 2), Disk Bore Area Eddy Current Inspection, and Task 72-53-02-200-000-007 (Inspection - Configuration 1), or Task 72-53-02-250-804 (Inspection - Configuration 2), Disk Dovetail Slot Bottom Eddy Current * Disk/Shaft, HPT Rotor, Stage One P/N 1531M84G12 and P/Ns 2047M32G01 thru G07 Task 72-53-02-250-801 (Inspection - Configuration 1), Disk Dovetail Slot Bottom Aft Corner Chamfers Eddy Current Inspection Disk, HPT Rotor, All Task 72-53-06-200-000-002 Fluorescent-Penetrant Inspect, and Stage Two Task 72-53-06-200-000-006 Disk Rim Bolt Hole Eddy Current Inspection, and Task 72-53-06-200-000-007 Disk Bore Eddy Current Inspection LPTR Stage 1-5 Disks All Task 72-57-02-200-000-001 Fluorescent-Penetrant Inspection LPTR Shaft All Task 72-57-03-200-000-002 Fluorescent-Penetrant Inspect, and Task 72-57-03-200-000-006 Eddy Current Inspection For CF6-80C2 Engines configured with the R88DT Turbine (Models CF6-80C2B2F, 80C2B4F, 80C2B6F, 80C2B7F, 80C2B8F): Disk/Shaft, HPT Rotor, Stage One (R88DT, No Rim Bolt Holes) All Task 72-53-16-200-000-001 Fluorescent-Penetrant Inspect, and Task 72-53-16-200-000-005 Disk Bore Area Eddy Current Inspection Disk, HPT Rotor, Stage Two (R88DT, No Rim Bolt Holes) All Task 72-53-18-200-000-002 Fluorescent-Penetrant Inspect, and Task 72-53-18-200-000-005 Disk Bore Area Eddy Current Inspection Rotating Interstage Seal (R88DT) All Task 72-53-17-200-000-001 Fluorescent-Penetrant Inspect, and Task 72-53-17-200-000-005 Seal Bore Area Eddy Current Forward Outer Seal (R88DT) All Task 72-53-21-200-000-001 Fluorescent-Penetrant Inspect, and Task 72-53-21-200-000-004 Seal Bore Area Eddy Current For CF6-80E1 Engines: Disk, Fan Rotor, All Sub Task 72-21-03-230-051 Fluorescent-Penetrant Inspection, and Stage One Sub Task 72-21-03-250-051 or 72-21-03-250-052 Disk Bore Eddy Current Inspection Shaft, Fan All Sub Task 72-21-05-230-051 Fluorescent Penetrant Inspection, and Sub Task 72-21-05-250-051 Vent Hole Eddy Current Inspection Compressor Rotor, All Sub Task 72-31-04-230-051 Fluorescent Penetrant Inspection, Stage 1 Disk Compressor Rotor, All Sub Task 72-31-05-230-051 Fluorescent Penetrant Inspection Stage 2 Disk Compressor Rotor, All Sub Task 72-31-06-230-051 Fluorescent Penetrant Inspection Stage 3-9 Spool Compressor Rotor, All Sub Task 72-31-07-230-051 Fluorescent Penetrant Inspection Stage 10 Disk (Pre SB 72-0150) Compressor Rotor Spool/Shaft, Stage 11-14 (Pre SB 72-0150) All Sub Task 72-31-08-230-051 Fluorescent Penetrant Inspection Compressor Rotor Spool/Shaft, Stage 10-14 (SB 72-0150) All Sub Task 72-31-23-230-052 Fluorescent Penetrant Inspection Compressor Rotor No. 4 Bearing Rotating Air Seal (CDP Rotating Seal) All Sub Task 72-31-10-230-051 Fluorescent Penetrant Inspection HPT Disk/Shaft, All Sub Task 72-53-02-230-051 Fluorescent-Penetrant Inspection, and Stage 1 Sub Task 72-53-02-250-051 Eddy Current Inspection, Rim Bolt Holes, and Sub Task 72-53-02-250-054 Eddy Current Inspection, Disk Bore HPT Disk, Stage 2 All Sub Task 72-53-06-230-051 Fluorescent-Penetrant Inspection, and Sub Task 72-53-06-250-051 Eddy Current Inspection, Rim Bolt Holes, and Sub Task 72-53-06-250-054 Eddy Current Inspection, Disk Bore LPT Rotor Shaft All Sub Task 72-55-01-240-051 Magnetic Particle Inspect LPT Disks, Stages 1-5 All Sub Task 72-57-02-230-051 Fluorescent-Penetrant Inspect LPT Rotor Torque Cone All Sub Task 72-57-03-220-051 Fluorescent-Penetrant Inspect For CF6-80E1 Engines configured with the R88DT Turbine: Disk/Shaft, HPT Rotor, Stage 1 (R88DT, No Rim Bolt Holes) All Sub Task 72-53-16-230-052 Fluorescent-Penetrant Inspect, and Sub Task 72-53-16-250-051 Disk Bore Area Eddy Current Inspection Disk, HPT Rotor, Stage 2 (R88DT, No Rim Bolt Holes) All Sub Task 72-53-18-230-051 Fluorescent-Penetrant Inspect, and Sub Task 72-53-18-250-051 Disk Bore Area Eddy Current Inspection ** HPT Rotor Rotating Interstage Seal (R88DT) All Sub Task 72-53-17-230-056 Fluorescent-Penetrant Inspect, and Sub Task 72-53-17-250-051 Seal Bore Area Eddy Current HPT Rotor Forward Outer Seal (R88DT) All Sub Task 72-53-21-230-051 Fluorescent-Penetrant Inspect, and Sub Task 72-53-21-250-051 Seal Bore Area Eddy Current 2. Perform inspections of the parts listed in Table 1 of this AD in accordance with the instructions provided in the applicable manual provisions. Definition: For the purposes of these mandatory inspections, piece-part opportunity means: a) The part is considered completely disassembled when accomplished in accordance with the disassembly instructions in the manufacturer's engine manual; and b) The part has accumulated more than 100 cycles-in-service since the last piece-part opportunity inspection, provided that the part was not damaged or related to the cause for its removal from the engine. The parts added to the table of this AD are identified by an asterisk (*) that precedes the part nomenclature. Also, parts that have an Engine Manual Inspection Task and or Sub Task Number reference updated in the table of this AD, are identified by two asterisks (**) that precede the part nomenclature. AMOC's: AMOC's previously approved for FAA AD 2002-07-12, are also approved for this AD. Note 2: FAA AD 2009-04-10 Amdt 39-15816 dated 5 February 2009 refers. Note 3: This AD supersedes AD/CF6/46. Compliance: Fro Requirement 1 - Within 180 days after the effective date of this AD. For Requirement 2 - At each piece-part opportunity after Requirement 1 of this AD is completed. This Airworthiness Directive becomes effective on 9 April 2009. Background: This AD is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF6-80A, CF6-80C2, and CF6-80E1 series turbofan engines. That AD required revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required inspection of selected critical life-limited parts at each piece-part exposure. This AD requires revisions to the CF6-80A, CF6-80C2, and CF6-80E1 series engines ALS sections of the manufacturer's manuals and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements, and to update certain Engine Manual Inspection Task and Sub Task Number references. This AD results from the need to require enhanced inspection of selected critical life-limited parts of CF6-80A, CF6-80C2, and CF6-80E1 series engines. The issuing of this AD is intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the aeroplane. James Coyne Delegate of the Civil Aviation Safety Authority 27 February 2009