Airworthiness directives › 2009-08-06
AD 2009-08-06 Airworthiness Directives; General Electric Company (GE) CF6-80A Series Turbofan Engines
Applicability*9
This AD applies to General Electric Company (GE) CF6-80A series turbofan engines with any of the following stage 1 high-pressure turbine (HPT) rotor disk part numbers (P/Ns), installed: (1) 1380M69G01; 1380M69G02; 1380M69G04; 1380M69G05; or 1380M69G06; or (2) 9234M67G12; 9234M67G13; 9234M67G14; 9234M67G15; or 9234M67G16; or (3) 9362M58G04; or (4) 9367M45G01; 9367M45G03; 9367M45G05; 9367M45G06; 9367M45G07; or 9367M45G08. (d) These CF6-80A series turbofan engines are installed on, but not limited to, Airbus A310-200 series and Boeing 767-200 and -300 series airplanes.
Compliance
You are responsible for having the actions required by this AD performed within 30 days after the effective date of this AD, unless the actions have already been done. (g) Remove from service HPT stage 1 rotor disks identified by P/N in paragraph (c) of this AD. Prohibition of HPT Stage 1 Rotor Disks (h) After the effective date of this AD, do not install any of the HPT stage 1 rotor disks, listed by P/N in paragraph (c) of this AD into any engine. Alternative Methods of
Unsafe condition
This AD results from the FAA learning that those disks are susceptible to cracks developing at the aft chamfer of the blade dovetail slots. We are issuing this AD to prevent cracks developing at the aft chamfer of the blade dovetail slots that could propagate to a failure of the disk and cause an uncontained engine failure and damage to the airplane.
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