95-17-15: Engine Mount Pylon

95-17-15 General Electric Company: Amendment 39-9346. Docket 95-ANE-10. Applicability: General Electric Company (GE) CF6-45/-50 series turbofan engines installed on, but not limited to, Airbus A300 series, Boeing 747 series, and McDonnell Douglas DC-10 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 side link fracture, which could result in failure of the second side link, or the forward engine mount pylon attachment bolts, and possible separation of the engine from the aircraft, accomplish the following: (a) Inspect left-hand side links, Part Numbers (P/N) 9204M94P01, 9204M94P03, and 9346M99P01, and right-hand side links, P/N's 9204M94P02, 9204M94P04, and 9346M99P02, that have not had the side link refurbishment done in accordance with GE CF6-50 Task Numbered Shop Manual, GEK 50481, Chapter 72-23-11, including Temporary Revision No. 72-0821 and 72-0822, both dated November 1, 1994, as follows: (1) For side links that have not been previously inspected inaccordance with GE Aircraft Engines (GEAE) CF6-50 Service Bulletin (SB) No. 72-1092, dated November 18, 1994, inspect in accordance with paragraph 2.A of GEAE CF6-50 SB No. 72-1092, dated November 18, 1994, prior to accumulating 350 cycles in service (CIS), or 750 hours time in service (TIS), after the effective date of this AD, whichever occurs earlier. (2) For side links that have been previously inspected in accordance with GEAE CF6- 50 SB No. 72-1092, dated November 18, 1994, inspect in accordance with paragraph 2.A of GEAE CF6-50 SB No. 72-1092, dated November 18, 1994, prior to accumulating 350 CIS, or 750 hours TIS since inspected in accordance with GEAE CF6-50 SB No. 72-1092, dated November 18, 1994, whichever occurs earlier. (3) Thereafter, inspect in accordance with paragraph 2.A of GEAE CF6-50 SB No. 72-1092, dated November 18, 1994, at intervals not to exceed 350 CIS, or 750 hours TIS since the last inspection, whichever occurs earlier. (4) If side links arefound cracked, replace the cracked side links and pylon attachment bolts with serviceable parts, and inspect the fail-safe bolt and platform lug in accordance with paragraph 2.B of GEAE CF6-50 SB No. 72-1092, dated November 18, 1994, prior to further flight. (b) Refurbish the left-hand and right-hand side links identified in paragraph (a) of this AD at the next engine shop visit after the effective date of this AD in accordance with paragraph 2.C of GEAE CF6-50 SB No. 72-1092, dated November 18, 1994. Refurbishment of side links in accordance with this paragraph constitutes terminating action to the on-wing inspection requirements of paragraph (a) of this AD. (c) For the purpose of this AD, an engine shop visit is defined as the induction of an engine into a shop for maintenance involving the separation of the fan and core modules. (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) The actions required by this AD shall be done in accordance with the following service bulletin: Document No. Pages Date GEAE CF6-50 SB No. 72-1092 1-7 November 18, 1994 Total Pages: 7. 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. (f) This amendment becomes effective on October 10, 1995.