82-20-03: Inspect First Stage HPT Disks

82-20-03 GENERAL ELECTRIC COMPANY: Amendment 39-4464. Applies to CF6-45 series and -50 series model turbofan engines. Compliance required as indicated unless already accomplished. Inspect all first stage HPT disks, P/Ns 9045M34P07 and 9045M34P09, for cracks in accordance with General Electric CF6-45/50 Engine Service Bulletin 72-700, dated November 20, 1980, or Alert Service Bulletin 72-709 dated February 19, 1981, or later revision approved by the Manager, Engine Certification Branch, FAA, New England Region, per the following schedule utilizing two complete independent inspections, hereafter referred to as "double inspections." A. Disks not previously inspected shall be "double inspected" prior to reaching 2,000 cycles in service for MTU serial number disks and 3,200 cycles in service for MPO serial number disks. All disks removed from service for inspection shall be reinspected every 750 cycles in service thereafter. B. Disks previously inspected shall be reinspected using the "double inspection" procedure prior to reaching 750 cycles in service since last inspection and every 750 cycles in service thereafter. C. All first stage turbine disks exposed at each high pressure rotor disassembly shall be "double inspected" prior to further flight per General Electric CF6-45/50 Service Bulletins 72-700 or 72-709. D. Disks with crack indications must be removed from service prior to further flight. E. First stage HPT disks, P/Ns 9045M34P07 and 945M34P09, shall not be returned to service after February 1, 1984. NOTE: For the purposes of this AD, "return to service" is defined as installation on an aircraft. F. All MTU prefix serial numbered disks reworked per General Electric CF6-45/50 Service Bulletin 72-700 at zero cycles of service may follow the initial inspection limits for MPO prefix serial numbers. Established life limits of first stage HPT disks are not to be exceeded. Airplanes may be ferried in accordancewith the provisions of Federal Aviation Regulation 21.197 to a base where the AD can be accomplished. Upon request of an operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Branch, FAA, New England Region. The manufacturer's specifications and procedures identified and described in this directive may be obtained upon request to General Electric Company, Neumann Way, Cincinnati, Ohio 45215. These documents may also be examined at the FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts. A historical file on this AD is maintained by the FAA, New England Region Office, Burlington, Massachusetts. This airworthiness directive supersedes AD's T80-16-51, T81-05-51, T82-05-51, and T82-08-51. This Amendment 39-4464 becomes effective on October 31, 1982.