Airworthiness Directive · Amendment 39-12233 · General Electric Co. CF6-80C2 Turbofan Engines
General Electric Co. CF6-80C2 Turbofan Engines
Superseded. A later AD replaced this one: AD 2002-07-12, AD 2004-04-07. Comply with the one in force.
This airworthiness directive (AD) is applicable to General Electric Company (GE) CF6-80C2 series turbofan engines with stage 1 high pressure turbine (HPT) rotor disks, part numbers (P/N's) 1531M84G02, 1531M84G06, 1531M84G08, 1531M84G10, 9392M23G10, 9392M23G12, 9392M23G21, and 1862M23G01 installed. These engines are installed on, but not limited to Airbus Industrie A300 and A310 series, Boeing 747 and 767 series, and McDonnell Douglas MD-11 series airplanes.
This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric Co. (GE) CF6-80C2 turbofan engines with certain stage 1 high pressure turbine (HPT) rotor disks installed. This amendment requires initial and repetitive inspections of certain HPT rotor disks for cracks in the bottom of the dovetail slot. This amendment is prompted by a report of an uncontained failure of an engine during a high-power ground run for maintenance. The actions specified by this AD are intended to detect cracks in the bottoms of the dovetail slots that could propagate to failure of the disk and cause an uncontained engine failure.
