AD 2005-20-35 Airworthiness Directives; Airbus Model A320-111 Airplanes

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

This AD applies to Airbus Model A320-111 airplanes, certificated in any category, having manufacturer serial number 002 through 021 inclusive.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Initial Inspection (f) Prior to the accumulation of 6,500 total flight cycles or within 50 flight cycles after the effective date of this AD, whichever occurs later, except as provided by paragraph (g) of this AD, perform a detailed inspection for cracking in the front and rear faces and at the crown fittings of the upper stringers of the center wing box between frame (FR) 36 and FR42, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1030, Revision 03, dated August 28, 2002. Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” (1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 5,500 flight cycles, in accordance with the service bulletin. (2) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) or its delegated agent. Previous Initial Inspection (g) Airplanes that received an initial inspection prior to the effective date of this AD using any service information specified in paragraph (h) of this AD must receive the next inspection within 2,000 flight cycles after the effective date of this AD or 7,500 flight cycles since the last inspection, whichever occurs first; in accordance with paragraph (f) of this AD. Previous Revisions of Service Bulletins (h) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A320-57-1030, dated August 12, 1991; Revision 1, dated September 16, 1996; or Revision 02, dated February 20, 1998; are considered acceptable for compliance with the corresponding actions specified in paragraph (f) of this AD, except as provided by paragraph (g) of this AD. No Reporting Requirement (i) Although Airbus Service Bulletin A320-57-1030, Revision 03, dated August 28, 2002, describes procedures for reporting inspection findings to Airbus, this AD does not require such a report. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM-116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) AMOCs approved previously according to AD 93-16-10 are not approved as AMOCs for this AD. Related Information (k) French airworthiness directive 2002-341(B), dated June 26, 2002, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus Service Bulletin A320-57-1030, Revision 03, dated August 28, 2002, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov ; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . Issued in Renton, Washington, on September 28, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-20069 Filed 10-11-05; 8:45 am] BILLING CODE 4910-13-P

This AD results from a manufacturer survey of airplanes affected by the inspection program required by AD 93-16-10 and the consequent revision of the thresholds and intervals of the repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the upper stringers of the center wing box, which could lead to loss of structural integrity of the wing.