Summary
The FAA proposes to adopt a new airworthiness directive (AD) for GE CF6-80C2B5F turbofan engines. This proposed AD would require removing certain part number (P/N) high-pressure compressor rotor (HPCR) 11-14 spool/shafts before they exceed a new, reduced life limit. This proposed AD results from an internal GE audit that compared the life limited parts certification documentation to the airworthiness limitations section (ALS) of the instructions for continuing airworthiness (ICA). We are proposing this AD to prevent HPCR 11-14 spool/shaft fatigue cracks caused by exceeding the life limit, which could result in a possible uncontained failure of the HPCR spool/shaft and damage to the airplane.