Summary
The FAA proposes to adopt a new airworthiness directive (AD) for General Electric Company (GE) CF6-80C2 and CF6-80E1 series turbofan engines with high-pressure compressor rotor (HPCR) spool shaft stage 14 disks, part number (P/N) 1703M49G02, 1703M49G03, or 1509M71G10 installed. This proposed AD would require a one-time eddy current inspection (ECI) of the HPCR spool shaft stage 14 disk web for crack indications, and removing from service any parts with web cracks. This proposed AD results from reports of 12 HPCR spool shaft stage 14 disks with web cracks discovered to date. We are proposing this AD to prevent cracks from propagating to an uncontained failure of the disk and damage to the airplane.