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2004-25-02 Airbus: Amendment 39-13889. Docket No. FAA-2004-18773; Directorate Identifier 2002-NM-312-AD. \n\nEffective Date \n\n\t(a) This AD becomes effective February 10, 2005. \n\nAffected ADs \n\n\t(b) This AD supersedes AD 99-01-19, amendment 39-10987. \n\nApplicability \n\n\t(c) This AD applies to Airbus Model A320-111, -211, -212, and - 231 series airplanes on which Airbus Modification 21346 has not been done, certificated in any category. \n\nUnsafe Condition \n\n\t(d) This AD was prompted by a full-scale fatigue survey on the Model A320 fleet. We are issuing this AD to detect and correct fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane. \n\nCompliance \n\n\t(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. \n\nRepetitive Inspections \n\n\t(f) At the applicable time specified in paragraph (f)(1) or (f)(2) of this AD: Do a detailed inspection to find cracking on the outboard flanges around the fastener holes of frames 38 through 41, between stringers 12 and 21, using Airbus Service Bulletin A320-53- 1032, Revision 02, dated December 5, 2001. Accomplishment of the inspection required by this paragraph ends the requirements of AD 99-01-19. \n\n\t(1) For airplanes on which the inspection specified in Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998; or Revision 02, dated December 5, 2001; has been done as of the effective date of this AD: Do the next inspection within 4,900 flight cycles after accomplishment of the last inspection, or within 1,100 flight cycles after the effective date of this AD, whichever is later. \n\n\t(2) For airplanes on which no inspection specified in Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998; or Revision 02, dated December 5, 2001; has been done as of the effective date of this AD: Do the inspection at the earlier of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. \n\n\t(i) Before the accumulation of 30,000 total flight cycles. \n\n\t(ii) Before the accumulation of 24,800 total flight cycles, or within 3,500 flight cycles after the effective date of this AD, whichever is later. \n\n\t(g) If no crack is found during the inspection required by paragraph (f)(1) or (f)(2) of this AD: Repeat the inspection thereafter at intervals not to exceed 4,900 flight cycles. \n\n\tNote 1: For the purposes of this AD, a detailed inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required." \n\nCorrective Action \n\n\t(h) If any crack is found during any inspection required by paragraph (f) of this AD, before further flight, repair using Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998; or Revision 02, dated December 5, 2001. Accomplishment of a repair using the service bulletin ends the repetitive inspection requirements for the area repaired. If any crack is found during any inspection required by this AD, and the service bulletin specifies to contact Airbus for appropriate action: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. \n\nOptional Terminating Action \n\n\t(i) Accomplishment of Airbus Modification 21346 using Airbus Service Bulletin A320-53-1031, dated December 9, 1994; or Revision 02, dated December 5, 2001; constitutes terminating action for the repetitive inspection requirements of this AD. \n\n\t(j) Accomplishment of the optional terminating action specified in AD 99-01-19 before the effective date of this AD, using Airbus Service Bulletin A320-53-1031, dated December 9, 1994; or Revision 02, dated December 5, 2001; is considered acceptable for compliance with paragraph (i) of this AD. \n\nAlternative Methods of Compliance (AMOCs) \n\n\t(k) The Manager, International Branch, ANM-116, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. \n\nRelated Information \n\n\t(l) French airworthiness directive 2002-259(B), dated May 15, 2002, also addresses the subject of this AD. \n\nMaterial Incorporated by Reference \n\n\t(m) You must use Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998; or Airbus Service Bulletin A320-53-1032, Revision 02, dated December 5, 2001; to perform the actions that are required by this AD, unless the AD specifies otherwise. \n\n\t(1) The Director of the Federal Register approves the incorporation by reference of Airbus Service Bulletin A320-53-1032, Revision 02, dated December 5, 2001,in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. \n\n\t(2) On February 12, 1999 (64 FR 1114, January 8, 1999), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998. \n\n\t(3) For copies of the service information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. For information on the availability of this material at the National Archives and Records Administration (NARA), call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. \n\n\tYou may view the AD docket at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC.
