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Airworthiness directives › 2009-07-03

AD 2009-07-03 Airworthiness Directives; General Electric Company CF6-80C2 and CF6-80E1 Series Turbofan Engines

2009-04-30
2009-03-26
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Engine
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Applicability*9

This AD applies to General Electric Company (GE) CF6-80C2 and CF6-80E1 series turbofan engines with high-pressure compressor rotor (HPCR) spool shaft stage 14 disks, part number (P/N) 1703M49G02, 1703M49G03, or 1509M71G10 installed. These engines are installed on, but not limited to, Airbus A300-600R/F, A310-200/300, and A330-200/300, and Boeing 747-200B/300/400/400D/400F, 767-200/300/400F/400ER, and MD-11 airplanes.

Compliance

You are responsible for having the actions required by this AD performed at the next engine shop visit where the separation of a major engine flange will occur after the effective date of this AD, unless the actions have already been done. (f) For the purpose of this AD, introduction of an engine into a shop solely for the following maintenance actions is not considered an engine shop visit: (1) Removal of a compressor case for airfoil or variable stator vane bushing maintenance. (2) Removal or replacement of the stage 1 fan disk. (3) Replacement of the turbine rear frame. (4) Removal or replacement of the accessory and/or transfer gearbox. (5) Removal or replacement of the fan forward case. (6) Any combination of the maintenance actions listed above. One-Time Eddy Current Inspection (ECI) (g) Using the following Alert Service Bulletin (ASB) instructions, perform a one-time ECI of the HPCR spool shaft stage 14 disk web for crack indications, and remove from service those parts found to be cracked. (1) Use paragraphs 3.B.(1) through 3.B.(5) of the Accomplishment Instructions of GE ASB No. CF6-80C2 S/B 72-A1122, Revision 1, dated June 19, 2006, to ECI the CF6-80C2 series engine HPCR spool shaft stage 14 disk web at the module level. (2) Use paragraph 3.C.(1) of the Accomplishment Instructions of GE ASB No. CF6-80C2 S/B 72-A1122, Revision 1, dated June 19, 2006, to ECI the CF6-80C2 series engine HPCR spool shaft stage 14 disk web at the piece-part level. (3) Use paragraphs 3.B.(1) through 3.B.(5) of the Accomplishment Instructions of GE ASB No. CF6-80E1 S/B 72-A0258, Revision 1, dated June 15, 2006, to ECI the CF6-80E1 series engine HPCR spool shaft stage 14 disk web at the module level. (4) Use paragraph 3.C.(1) of the Accomplishment Instructions of GE ASB No. CF6-80E1 S/B 72-A0258, Revision 1, dated June 15, 2006, to ECI the HPCR spool shaft stage 14 disk web at the piece-part level. Previous Credit (h) Performance of a one-time ECI of the HPCR spool shaft stage 14 disk web for crack indications, done before the effective date of this AD and following the procedures defined in GE ASB No. CF6 80C2 S/B 72-A1122, dated January 19, 2004, for CF6-80C2 series engines or GE ASB No. CF6 80E1 S/B 72-A0258, dated January 19, 2004, for CF6-80E1 series engines satisfies the compliance requirements specified in this AD. Alternative Methods of

Unsafe condition

This AD results from reports of 12 cracked HPCR spool shaft stage 14 disk webs discovered to date. We are issuing this AD to prevent cracks from propagating to an uncontained failure of the disk and damage to the airplane.

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