Airworthiness directives › 2007-24-07
AD 2007-24-07 Airworthiness Directives; General Electric Company (GE) CF6-80C2B1 Turbofan Engine
Applicability*9
This AD applies to GE CF6-80C2B1 turbofan engine, serial number 690203, with fan disk, part number (P/N) 1703M78P11, SN RPMDA662, installed. This engine is installed on, but not limited to, a Boeing 747-300 airplane.
Compliance
You are responsible for having the actions required by this AD performed within 3,500 cycles-since-last Cu-Ni-In thermal spray coating of the dovetail slots, but no later than March 31, 2008, unless the actions have already been done. Stripping, Inspecting and Recoating the Stage 1 Fan Disk (f) Strip the Cu-Ni-In thermal coating from the pressure faces and slot bottoms of the stage 1 fan disk, and perform a microstructure evaluation. Use 3.A.(2)(a) through 3.A.(2)(b) of GE Service Bulletin (SB) No. CF6-80C2 S/B 72-1121, dated January 23, 2004, to strip the thermal coating and perform the microstructure evaluation. (g) Ultrasonic inspect, fluorescent penetrant inspect, and eddy current inspect stage 1 fan disk. Use 3.A.(2)(c) of GE SB No. CF6-80C2 S/B 72-1121, dated January 23, 2004, to inspect the disk. (h) Apply Cu-Ni-In thermal coating to the pressure faces and slot bottoms of the stage 1 fan disks, using 3.A.(2)(d) of GE SB No. CF6-80C2 S/B 72-1121, dated January 23, 2004. Alternative Methods of
Unsafe condition
This AD results from a report that a repair shop did not meet the process requirements when applying copper-nickel-indium (Cu-Ni-In) thermal coating to certain stage 1 fan disks. We are issuing this AD to prevent possible uncontained release of multiple fan blades, resulting in damage to the airplane.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1