Airworthiness Directive · Amendment 39-8851 · General Electric Company Engines
General Electric Company Engines
This AD applies to General Electric Company CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-80C2B1, CF6-80C2B1F, CF6-80C2B1F1, CF6-80C2B1F2, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B3F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B6, CF6-80C2B6F, CF6-80C2B7F, CF6-80C2D1F.
The models as the FAA's AD index lists them. The serial ranges, installed parts and exceptions are in the AD itself: read it at the FAA.
This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-80C2 series turbofan engines, that requires an inspection for cracks in the stage 1 high pressure turbine (HPT) disk rim bolt holes, and replacement, if necessary, with serviceable parts. This amendment is prompted by a report of an uncontained stage 1 HPT disk failure which resulted in an aborted takeoff. The actions specified by this AD are intended to prevent an uncontained stage 1 HPT disk failure, which could result in an inflight engine shutdown, rejected takeoff, or damage to the aircraft.
