99-21-17: Fuselage Structure

99-21-17 AIRBUS INDUSTRIE: Amendment 39-11362. Docket 99-NM-193-AD. Applicability: Model A321 series airplanes, certificated in any category; except those on which Airbus Modification 25791 has been incorporated in production, or on which Airbus Service Bulletin A320-53-1130, dated June 17, 1997, or Revision 01, dated July 8, 1998, has been accomplished in service. NOTE 1: This AD applies to each airplane 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 airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent the loss of structural integrity of the rear part of the fuselage structure in the event of an undetected tail scrape during landing or takeoff, accomplish the following: (a) Except as required by paragraph (b) of this AD: Within six years after the effective date of this AD, accomplish all specified actions, including the reinforcement of the fuselage structure between frames 62 and 64, rotating probe inspections, and repairs, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1130, Revision 01, dated July 8, 1998. NOTE 2: Accomplishment of the reinforcement actions, in accordance with Airbus Service Bulletin A320-53-1130, dated June 17, 1997, is acceptable for compliance with the requirements of paragraph (a) of this AD. (b) Where Airbus Service Bulletin A320-53-1130, dated June 17, 1997, and Revision 01, dated July 8, 1998, state that the manufacturer should be contacted for the repair of certain conditions detected during the reinforcement procedure, such repairs must be accomplished prior to further flight in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the DGAC (or its delegated agent). Alternative Methods of Compliance (c) 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, International Branch, ANM-116, 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, International Branch, ANM-116. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, ifany, may be obtained from the International Branch, ANM-116. Special Flight Permits (d) 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. Incorporation by Reference (e) Except as provided by paragraph (b) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A320-53-1130, Revision 01, dated July 8, 1998. 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. NOTE 4: The subject of this AD is addressed in French airworthiness directive 1999-051-125(B), dated February 10, 1999. (f) This amendment becomes effective on October 28, 1999.