AD 2004-06-11 Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, and -342 Series Airplanes; and Model A340-211, -212, 213, -311, -312, and -313 Series Airplanes

The airplanes listed in Table 1 of this AD, certificated in any category. Table 1.—Applicability Model— Except those modified by Airbus modification— Or Airbus service bulletin— A330-301, -321, -322, -341, and -342 series airplanes 43503 A330-57-3055, dated November 28, 2001, or Revision 01, dated May 2, 2002. A340-211, -212, 213, -311, -312, and -313 series airplanes 43692 A340-57-4062, dated November 28, 2001, or Revision 01, dated May 2, 2002.

Required as indicated, unless accomplished previously. To prevent cracking of the wire harness slot on the inner rear spar of the wing, which could result in reduced structural integrity of the wing, accomplish the following: Modification (a) At the time specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD: Modify the inner rear spars of the wings in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3055 or A340-57-4062, both Revision 01, both dated May 2, 2002, as applicable. The modification involves an eddy current surface crack inspection of the wire harness slots in the rear spars of the wings between ribs 4 and 5, a high-frequency eddy current rototest inspection for cracks in the area around the bolt holes that attach the support plates of the electrical connectors, and cold-expansion of the wire harness slots and the bolt holes. (1) For Model A330 series airplanes: Inspect before the accumulation of 16,500 total flight cycles or 51,400 total flight hours, whichever occurs first. (2) For Model A340 series airplanes, pre-Modification 41300: Inspect before the accumulation of 14,500 total flight cycles or 75,400 total flight hours, whichever occurs first. (3) For Model A340 series airplanes, post-Modification 41300: Inspect before the accumulation of 13,400 total flight cycles or 70,000 total flight hours, whichever occurs first. (b) A modification done before the effective date of this AD in accordance with Airbus Service Bulletin A330-57-3055 or A340-57-4062, both dated November 28, 2001, is acceptable for compliance with the applicable requirements of this AD. Repair (c) If any crack is found during an inspection required by paragraph (a) of this AD: Before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (or its delegated agent). Alternative Methods of Compliance (d) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (e) Unless otherwise specified in this AD, the actions must be done in accordance with Airbus Service Bulletin A330-57-3055, Revision 01, dated May 2, 2002; or Airbus Service Bulletin A340-57-4062, Revision 01, dated May 2, 2002; as applicable. 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, 1 Rond Point Maurice Bellonte, 31701 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 1: The subject of this AD is addressed in French airworthiness directives 2001-578(B) and 2001-579(B), both dated November 28, 2001. Effective Date (f) This amendment becomes effective on April 30, 2004. Issued in Renton, Washington, on March 17, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-6578 Filed 3-25-04; 8:45 am] BILLING CODE 4910-13-P