Airworthiness Directive · Amendment 39-11440 · General Electric Company CF6 Series Turbofan Engines
General Electric Company CF6 Series Turbofan Engines
Superseded. A later AD replaced this one: AD 2002-25-08. Comply with the one in force.
General Electric Company (GE) CF6-45, -50, -80A, -80C2 and -80E1 series turbofan engines, with High Pressure Compressor Rotor (HPCR) stage 3-9 spools, part numbers (P/Ns) 1333M66G01, 1333M66G03, 1333M66G07, 1333M66G09, 1333M66G10, 1669M22G01, 1669M22G03, 1781M52P01, 1781M53G01, 1782M22G01, 1782M22G02, 1782M22G04, 1854M95P01, 1854M95P02, 1854M95P03, 1854M95P04, 1854M95P05, 1854M95P06, 1854M95P07, 1854M95P08, 9136M89G02, 9136M89G03, 9136M89G06, 9136M89G07, 9136M89G08, 9136M89G09, 9136M89G10, 9136M89G11, 9136M89G17, 9136M89G18, 9136M89G19, 9136M89G20, 9136M89G21, 9136M89G22, 9136M89G27, 9136M89G28, 9136M89G29, 9253M85G01, 9253M85G02, 9273M14G01, 9331M29G01, and 9380M28P05 installed. These engines are installed on but not limited to Airbus A300, A310, and A330 series, Boeing 747 and 767 series, and McDonnell Douglas DC-10 and MD-11 series aircraft.
This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Company (GE) CF6 series turbofan engines, that currently requires initial and repetitive ultrasonic and eddy current inspections of high pressure compressor rotor (HPCR) stage 3-9 spools for cracks. This amendment defines more aggressive inspection intervals for certain HPCR stage 3-9 spools, adds CF6-80E1 engines to the inspection program, adds inspection requirements for spools manufactured from 8 inch diameter billet, adds inspection requirements for stage 3-5 blade slot bottoms, and adds inspection requirements for web and hub-to-web transition areas. This amendment is prompted by analysis of recent HPCR stage 3-9 spool inspection results and separations, and assessment of the adequacy of the existing program to prevent HPCR stage 3-9 spool cracking and separation. As a result of that assessment, the FAA has determined there is a need to make changes to the existing AD. The actions specified by this AD are intended to prevent HPCR stage 3-9 spool cracking and separation, which can result in an uncontained engine failure and aircraft damage.
