AD 2004-12-01 Airworthiness Directives; Airbus Model A330-202, -203, -223, and -243 Airplanes, and A330-300 Series Airplanes

A330-202, -203, -223, and -243 airplanes, and A330-300 series airplanes; certificated in any category; on which Airbus Modification 49404 has not been done.

Required as indicated, unless accomplished previously. To prevent fatigue cracking, which could result in reduced structural integrity of the fuselage, accomplish the following: Modification (a) Modify the center box junction and upper bent sections of the center fuselage, between frame (FR) 40.3 and FR 45 at stringers 26 through 29, on the left and right sides of the airplane, by doing all the actions per the Accomplishment Instructions of Airbus Service Bulletin A330-53-3126, Revision 01, dated March 19, 2003. Do the modification at the times specified in paragraphs (a)(1) and (a)(2) of this AD. (1) For Model A330-301, -322, -321, -341, and -342 airplanes: Do the modification at the later of the times specified in paragraphs (a)(1)(i) and (a)(1)(ii) of this AD. (i) Before the accumulation of 13,500 total flight cycles or 39,200 total flight hours since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever is first. (ii) Within 6 months after the effective date of this AD. (2) For Model A330-202, -203, -223, -243, -323, and -343 airplanes: Do the modification at the later of the times specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. (i) Before the accumulation of 11,400 total flight cycles or 33,100 total flight hours since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever is first. (ii) Within 6 months after the effective date of this AD. Previously Accomplished Actions (b) Accomplishment of the modification per Airbus Service Bulletin A330-53-3126, dated October 18, 2002, is considered acceptable for compliance with the modification required by paragraph (a) this AD. Repair (c) If any crack is found during accomplishment of the modification required by paragraph (a) of this AD, and the service bulletin recommends contacting Airbus for appropriate action: Before further flight, repair per a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; 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 provided in this AD, the actions shall be done in accordance with Airbus Service Bulletin A330-53-3126, Revision 01, dated March 19, 2003. 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, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Note 1: The subject of this AD is addressed in French airworthiness directive 2002-528(B), dated October 30, 2002. Effective Date (f) This amendment becomes effective on July 14, 2004. Issued in Renton, Washington, on May 28, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-12822 Filed 6-8-04; 8:45 am] BILLING CODE 4910-13-P