95-24-08: Thrust Reverser

95-24-08 AIRBUS: Amendment 39-9440. Docket 94-NM-141-AD. Applicability: Model A320 series airplanes; as listed in Airbus Industrie Service Bulletin A320-29-1048, Revision 1, dated December 4, 1992, and Revision 2, dated September 1, 1994; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes 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 (b) of this AD to request approval from the 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 thechanged configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent deployment of a thrust reverser during flight, which could adversely affect the controllability of the airplane, accomplish the following: (a) Within 5 months after the effective date of the AD, accomplish the requirements of paragraph (a)(1) or (a)(2) of this AD, as applicable, in accordance with Airbus Industrie Service Bulletin A320-29-1048, Revision 1, dated December 4, 1992, or Revision 2, dated September 1, 1994. (1) For airplanes equipped with CFM series engines: Replace the Engine 1 and Engine 2 check valves of the thrust reverser in the nacelle with modified valves as specified in the service bulletin. (2) For airplanes equipped with International Aero Engines (IAE): Replace the Engine 1and Engine 2 manual control valves of the thrust reverser on the pylon with modified valves as specified in the service bulletin. (b) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) 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 airplane to a location where the requirements of this AD can be accomplished. (d) The replacements shall be done in accordance with the following Airbus service bulletins, which contain the specified list of effective pages: Service Bulletin Number and Date Page Number Revision Level Shown on Page Date Shown on Page A320-29-1048 Revision 2 September 1, 1994 1-5 7-8, 11 6, 9-10, 12-15 2 1 Original September 1, 1994 December 4, 1992 April 7, 1992 A320-29-1048 Revision 1 December 4, 1992 1-3, 5, 7-8, 11 4, 6, 9-10, 12-15 1 Original December 4, 1992 April 7, 1992 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 27, 1995.