AD 91-11-05

91-11-05 GENERAL ELECTRIC COMPANY: Amendment 39-7001. Docket No. 90-ANE- 35. Applicability: General Electric Company (GE) CF6-80A and CF6-80C2 series engines installed on, but not limited to, Airbus A300 and A310; and Boeing 747 and 767 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent aborted takeoff and uncontained engine failure, accomplish the following: (a) Ultrasonic inspect the inertia weld of affected high pressure compressor rotor (HPCR) stages 11-14 spool-shafts at the next engine shop visit after the effective date of this AD but no later than 5,000 cycles in service (CIS) after the effective date of this AD, according to the following: (1) Inspect CF6-80A HPCR stages 11-14 spool-shafts, Part Numbers (P/N) 9225M37G11, 9225M37G14, 9225M37G16, 9225M37G18, 9225M37G19, 9225M37G20, 9225M37G21, and 1509M71G01, in accordance with the Accomplishment Instructions in GE CF6-80A Service Bulletin (SB) 72-531, Revision 2, dated May 18, 1990. (2) Inspect CF6-80C2 HPCR stages 11-14 spool-shafts, P/N 9380M30G07, 9380M30G08, 9380M30G09, 9380M30G10, 1531M21G01, 1509M71G02, 1509M71G03, 1509M71G04, 1509M71G05, and 1509M71G06, in accordance with the Accomplishment Instructions in GE CF6-80C2 SB 72-314, Revision 2, dated June 20, 1990. (3) Remove from service prior to further flight and replace with serviceable parts, HPCR stages 11-14 spool-shafts with ultrasonic indications greater than or equal to 50 percent full-screen height. (4) For the purpose of this AD, an engine shop visit is defined as the induction of the engine into a shop where the subsequent maintenance entails removal of the high pressure turbine module. (5) For the purpose of this AD, definition of ultrasonic indication is provided in GE CF6-80A SB 72-531, Revision 2, dated May 18, 1990, and GE CF6-80C2 SB 72-314, Revision 2, dated June 20, 1990, for the CF6-80A and CF6-80C2 engine models, respectively. (b) Aircraft may be ferried inaccordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate) an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. The ultrasonic inspections shall be done in accordance with the following GE documents:

DOCUMENT PAGE NO. ISSUE/REVISION DATE GE CF6-80A 2-12, 15, 17-27, Rev. 1 4/3/89 SB 72-531 30, 31

1, 13, 14, 16, 28, 29 Rev. 2 5/18/90 GE CF6-80C2 2-12, 15, 17-27, Rev. 1 4/19/89 SB 72-314 30, 31

1, 13, 14, 16, 28, 29 Rev. 2 6/20/90

This incorporation by reference was approved bythe Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, Ohio 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, D.C. This amendment (39-7001, AD 91-11-05) becomes effective on July 5, 1991.