AD 2005-20-07 Airworthiness Directives; Airbus Model A330-300 Series Airplanes

Models named: A330-301, -321, -322, -323, -341, -342, -343 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Model A330-301, -321, -322, -323, -341, -342, and -343 series airplanes, certificated in any category, except those on which Airbus Modification 41652 has been accomplished in production.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Installation (f) At the later of the times in paragraphs (f)(1) and (f)(2) of this AD: Install the butt straps at FR53.3 on the fuselage skin between left- and right-hand stringer 13, and do all related investigative and corrective actions before further flight. Except as provided by paragraph (g) of this AD, do all actions in accordance with Airbus Service Bulletin A330-53-3127, Revision 01, dated November 21, 2003. (1) Before the accumulation of 14,700 total flight cycles or 51,400 total flight hours, whichever occurs earlier. (2) Within 6 months after the effective date of this AD. Contact the FAA/Direction Générale de l'Aviation Civile (DGAC) for Certain Repair Instructions (g) If any crack is detected during the related investigative actions (rototest) required by paragraph (f) of this AD: Before further flight, repair the crack according to a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the DGAC (or its delegated agent). Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, 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 § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (i) French airworthiness directive F-2003-415, dated November 12, 2003, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Airbus Service Bulletin A330-53-3127, Revision 01, dated November 21, 2003, 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 20, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-19333 Filed 10-3-05; 8:45 am] BILLING CODE 4910-13-U

This AD results from a report that, during fatigue tests of the fuselage, cracks initiated and grew at the circumferential joint of frame (FR) 53.3. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage.