2001-16-13: Fuselage Joints

2001-16-13 Airbus Industrie: Amendment 39-12382. Docket 2001-NM-70-AD. \n\n\tApplicability: Model A330 airplanes, serial numbers 301, 321, 322, 323, 341, 342, and 343, certificated in any category; except airplanes on which Airbus Industrie Modification 46636 has been accomplished in production or which have been modified in service in accordance with Airbus Service Bulletin A330-53-3090, dated March 9, 1999; Revision 01, dated July 6, 1999; or Revision 02, dated January 9, 2001. \n\n\tNote 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 request approval for an alternative method of compliance in accordance with paragraph (d) 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. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent fatigue cracking of the fuselage longitudinal buttstrap, which could result in reduced structural integrity of the fuselage, accomplish the following: \n\nInspection \n\n\t(a) Prior to the accumulation of 15,000 total flight cycles: Perform a roto-test inspection to detect cracks of the fastener holes at frame 31, frame 37.1, and stringer 9, in accordance with Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 2001. \n\nReinforcement \n\n\t(b) If no cracks are detected during the inspection performed in accordance with paragraph (a) of this AD, prior to further flight, reinforce the fuselage structure between frames 31 and 37.1, in accordance with Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 2001. \n\nFollow-up Inspection \n\n\t(c) If any crack is detected during the inspection performed in accordance with paragraph (a) of this AD, prior to further flight, perform a high frequency eddy current (HFEC) inspection to determine the crack length, in accordance with Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 2001. Prior to further flight, repair the crack in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Generale de l'Aviation Civile (or its delegated agent). \n\nAlternative Methods of Compliance \n\n\t(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, International Branch, ANM-116. 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. \n\n\tNote 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. \n\nSpecial Flight Permits \n\n\t(e) Special flight permits may be issued in accordance with Secs. 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. \n\nIncorporation by Reference \n\n\t(f) Except as required by paragraph (c) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 2001. 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. \n\n\tNote 3: The subject of this AD is addressed in French airworthiness directive 2001-075(B), dated March 17, 2001. \n\nEffective Date \n\n\t(g) This amendment becomes effective on September 7, 2001.