95-17-16: Compressor Rear Frame

95-17-16 General Electric Company: Amendment 39-9347. Docket 94-ANE-41. Applicability: General Electric Company (GE) CF6-80A series turbofan engines installed on, but not limited to, Airbus A310 series and Boeing 767 series aircraft. NOTE: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (d) to request approval from the Federal Aviation Administration (FAA). This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any engine from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent a compressor rear frame (CRF) separation, which could result in a rejected takeoff and damage to the aircraft, accomplish the following: (a) Inspect CRF, Part Numbers (P/N) 9283M77G07, 9283M77G08, 9283M77G09, 9283M77G11, 9283M77G14, 7283M77G15, 9283M77G16, 9283M77G17, 9283M77G18, 9283M77G19, 1338M77G01, 1338M77G02, 1338M77G03, 1338M77G04, 1338M77G05, and 1338M77G06, that have not accomplished the midflange rework or replacement in accordance with any revision level of GE CF6-80A Service Bulletin (SB) No. 72-600 or 72-611, prior to the effective date of this AD, as follows: (1) Perform an on-wing eddy current inspection (ECI) or an on-wing spot fluorescent penetrant inspection (FPI) of the CRF midflange for cracks in accordance with the Accomplishment Instructions and the schedule outlined in Table 1 of GE CF6-80A SB No. 72-593, Revision 2, dated March 19, 1992, or within 1,000 cycles in service since the last shop level FPI, whichever occurs later, after the effective date of this AD. (2) Thereafter, reinspect the CRF midflange for cracks in accordance with the Accomplishment Instructions and schedule outlined in Table 2 of GE CF6-80A SB No. 72-593, Revision 2, dated March 19, 1992. (3) Remove from service prior to further flight CRF's with cracked midflanges that exceed the on-wing serviceable limits specified in Table 2 of GE CF6-80A SB No. 72-593, Revision 2, dated March 19, 1992, and replace with a serviceable part. (b) Remove from service CRF's identified in paragraph (a) of this AD at the next piece-part exposure, or by December 31, 1996, whichever occurs earlier, and replace with a serviceable part. Removal and replacement of CRF's in accordance with thisparagraph constitutes terminating action to the on-wing inspection requirements of paragraph (a) of this AD. (c) For the purpose of this AD, a serviceable part is defined as a CRF that has accomplished the midflange rework or replacement in accordance with any revision level of GE CF6- 80A SB No. 72-600 or 72-611. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (f) The actions required by this AD shall be done in accordance with the following SB: Document No. Pages Revision Date GE CF6-80A SB No. 72-593 1-4 2 March 19, 1992 5-8 1 October 30, 1991 9 2 March 19, 1992 10-12 1 October 30, 1991 13-15 2 March 19, 1992 16-22 1 October 30, 1991 Total Pages: 22 This incorporation by reference was approved by the 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, OH 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (g) This amendment becomes effective on November 7, 1995.