AD 2004-25-03 Airworthiness Directives; Airbus Model A320 Series Airplanes

Models named: A320-111, -211, -212, -231 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A320-111, -211, -212, and -231 series airplanes on which Airbus Modification 21202 has not been done, certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Repetitive Inspections (f) At the applicable time specified in paragraph (f)(1) or (f)(2) of this AD: Do an ultrasonic inspection to detect cracking in the bottom panels of the keel beam (both left and right), in the area of the frame 46 and stringer 37 intersection at the pressure bulkhead, using Airbus Service Bulletin A320-53-1034, Revision 02, dated December 4, 2001. Thereafter, repeat the ultrasonic inspection at intervals not to exceed 5,200 flight cycles or 10,400 flight hours, whichever is first. Accomplishment of the inspection required by this paragraph ends the requirements of AD 99-01-17. (1) For airplanes on which the inspection specified in Airbus Service Bulletin A320-53-1034, dated March 30, 1992; or Revision 02, dated December 4, 2001; has been done as of the effective date of this AD: Do the next inspection within 5,200 flight cycles after accomplishment of the last inspection, or within 800 flight cycles after the effective date of this AD, whichever is later. (2) For airplanes on which no inspection specified in Airbus Service Bulletin A320-53-1034, dated March 30, 1992; or Revision 02, dated December 4, 2001; has been done as of the effective date of this AD: Do the inspection at the later of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. (i) Before the accumulation of 24,200 total flight cycles or 48,400 total flight hours, whichever is first. (ii) Before the accumulation of 30,000 total flight cycles, or within 3,500 flight cycles after the effective date of this AD, whichever is first. Corrective Action (g) If any crack is found during any inspection required by paragraph (f) of this AD, before further flight, repair using Airbus Service Bulletin A320-53-1034, dated March 30, 1992; or Revision 02, dated December 4, 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. Optional Terminating Action (h) Accomplishment of Airbus Modification 21202 using Airbus Service Bulletin A320-53-1033, Revision 03, dated July 4, 1994; or Revision 04, dated December 4, 2001; constitutes terminating action for the repetitive inspection requirements of this AD. (i) Accomplishment of the optional terminating action specified in AD 99-01-17 before the effective date of this AD, using Airbus Service Bulletin A320-53-1033, Revision 03, dated July 4, 1994; or Revision 04, dated December 4, 2001; is considered acceptable for compliance with paragraph (h) of this AD. Alternative Methods of Compliance (AMOCs) (j) 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. Related Information (k) French airworthiness directive 2002-260(B), dated May 15, 2002, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus Service Bulletin A320-53-1034, dated March 30, 1992; or Airbus Service Bulletin A320-53-1034, Revision 02, dated December 4, 2001; to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-53-1034, Revision 02, dated December 4, 2001, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On February 12, 1999 (64 FR 1118, January 8, 1999), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-53-1034, dated March 30, 1992. (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. You 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. Issued in Renton, Washington, on December 29, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-283 Filed 1-5-05; 8:45 am] BILLING CODE 4910-13-P

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.