AD 84-01-01

84-01-01 GENERAL ELECTRIC COMPANY: Amendment 39-4790. Applies to CF6-45 and CF6-50 series model turbofan engines. Unless already accomplished, to preclude the possibility of uncontained titanium fires, replace as follows prior to June 1, 1984:

(a) Compressor stator assembly, including the compressor case, and stage 6 vanes in accordance with FAA approved General Electric CF6-45 and CF6-50 Service Bulletin 72-549.

(b) Compressor inlet stator vanes and stage 1 and 2 stator vanes in accordance with FAA approved General Electric CF6-45 and CF6-50 Service Bulletin 72-550.

(c) Compressor blades, stages 3 through 9, and the stage 3-9 spool in accordance with FAA approved General Electric CF6-45 and CF6-50 Service Bulletin 72-551.

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already receivedthese documents from the manufacturer may obtain copies upon request from the 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.

Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Engine Certification Branch, FAA, New England Region, may adjust the compliance date(s) specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.

This amendment becomes effective on February 10, 1984.