AD 2005-19-12 Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, and -342 Airplanes; and Model A340-200 and A340-300 Series Airplanes

Models named: A330-301, -321, -322, -341, -342, A340-211, -212, -213, -311, -312. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A330-301, -321, -322, -341, and -342 airplanes; and Model A340-211, -212, -213, -311, -312, and -313 airplanes; certificated in any category; on which Airbus Modification 42418 has not 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. Repetitive Inspections (f) At the applicable times in paragraph (f)(1) or (f)(2) of this AD: Do high-frequency eddy current inspection for cracks of the inboard lower flange and radius of the left-hand and right-hand outboard floor beams at FR48. Do all inspections in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 1 of this AD. Doing the action in paragraph (h) of this AD terminates the repetitive inspection requirements of this paragraph. (1) For Airbus Model A330-301, -321, -322, -341, and -342 airplanes: Do the first inspection before the accumulation of 8,400 flight cycles since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness, or within 6 months after the effective date of this AD, whichever occurs later; and repeat the inspection thereafter at intervals not to exceed 3,860 total flight cycles or 15,050 flight hours, whichever occurs earlier. (2) For Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes: Do the first inspection before the accumulation of the earlier of 9,200 flight cycles or 70,000 flight hours since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness, or within 6 months after the effective date of this AD, whichever occurs later; and repeat the inspection thereafter at intervals not to exceed 3,070 flight cycles. Table 1.—Service Bulletins For airbus model— Airbus service bulletin— A330-301, -321, -322, -341, and -342 airplanes A330-53-3014, Revision 05, dated June 20, 2003. A340-211, -212, -213, -311, -312, and -313 airplanes A340-53-4022, Revision 05, dated June 16, 2003. Related Investigative and Corrective Actions (g) If any crack is found during any inspection required by paragraph (f) of this AD: Do the applicable actions in paragraph (g)(1) and (g)(2) of this AD. (1) For cracks at the radius: Before further flight, repair the crack according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Geáneárale de l'Aviation Civile (DGAC) (or its delegated agent). (2) For cracks at the flange: Before further flight, measure the total length of the crack and do the applicable action in paragraph (g)(2)(i) and (g)(2)(ii) of this AD. (i) If the crack is less than 12 mm (0.472 inch) in length: Before further flight, stop-drill the crack and, within 500 flight cycles after stop-drilling the crack, do the action in paragraph (h) of this AD. (ii) If the crack is greater than or equal to 12 mm (0.472 inch) in length: Before further flight, repair the crack according to a method approved by either the Manager, International Branch, ANM-116; or the Direction Geáneárale de l'Aviation Civile (DGAC) (or its delegated agent). Optional Terminating Action (h) Installing a stainless steel doubler in accordance with Airbus Service Bulletin A330-53-3013, Revision 03, December 23, 1999; or Airbus Service Bulletin A340-53-4021, Revision 05, dated January 27, 2003; as applicable; terminates the repetitive inspection requirements of paragraph (f) of this AD. If any crack is found during this installation while doing the rotating probe inspection of the fastener holes: Before further flight, repair the crack according to a method approved by either the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent). No Reporting Required (i) Although the Accomplishment Instructions of the service bulletins identified in Table 1 of this AD describe procedures for reporting certain information to the manufacturer, this AD would not require those actions. Alternative Methods of Compliance (AMOCs) (j) 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. Related Information (k) French airworthiness directives 2001-506(B) and 2001-507(B), both dated October 17, 2001, also address the subject of this AD. Material Incorporated by Reference (l) You must use the service information identified in Table 2 of this AD 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 these documents 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/cfr/ibr-locations.html . Table 2.—Material Incorporated by Reference Service Bulletin Revision level Date A330-53-3013 03 December 23, 1999. A330-53-3014 05 June 20, 2003. A340-53-4021 05 January 27, 2003. A340-53-4022 05 June 16, 2003. Issued in Renton, Washington, on September 9, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-18522 Filed 9-20-05; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports that cracks were found during fatigue tests at the attachment between the canted lower flange of the floor beam and the pressure diaphragm in front of frame (FR) 48 on both left- and right-hand floor beams; and that an additional crack was found in the flange radius of the floor beam. The FAA is issuing this AD to detect and correct such cracking, which could propagate and result in reduced structural integrity of the fuselage.