Summary
The Federal Aviation Administration (FAA) proposes to supersede three existing airworthiness directives (AD's), that are applicable to GE CF6-45, -50, -80A, -80C2, and -80E1 turbofan engines. Those AD's currently require specific handling of the GE CF6 series high pressure compressor rotor (HPCR) stage 3-9 spools during a fluorescent penetrant inspection process, and an initial and repetitive ultrasonic and eddy current inspections of certain HPCR stage 3-9 spools for cracks. This proposal would remove the AD that requires special handling of the spools during fluorescent-penetrant inspection, and would adjust and combine the initial and repetitive inspection requirements, currently listed in two AD's, into one AD for the HPCR stage 3-9 spool. This proposal aligns repetitive inspection requirements with the more stringent initial inspection requirements required by AD 2000-16-12, Amendment 39-11868 (65 FR 50623, August 21, 2000) and terminates AD 95-18-14, Amendment 39-9361 (60 FR 46216, September 6, 1995) that is no longer necessary. The actions specified in the proposed AD are intended to prevent cracks which can cause separation of the HPCR stage 3-9 spool and possible uncontained engine failure.