AD 2005-20-27 Airworthiness Directives; Airbus Model A340-211, -212, -311, and -312 Airplanes

Models named: A340-211, -212, -311, -312. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A340-211, -212, -311, and -312 airplanes, certificated in any category, serial numbers 0006, 0007 (right-hand side only), 0008, 0013, 0020, 0024 (left-hand side only), 0027 through 0029 inclusive, 0031, 0033, 0035, 0038 through 0040 inclusive, 0043, 0047, 0049, and 0052.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Note 1: Airbus Service Bulletin A340-57-4087, dated November 21, 2003, cites Airbus Service Bulletin A340-57-4036, Revision 05, dated March 14, 2000, as the source of service information for accomplishing Airbus Modification 43577. Initial/Repetitive Nondestructive Test Inspections/Repair (f) Within 5,420 flight cycles or 26,200 flight hours after accomplishing Airbus Modification 43577, whichever is first: Perform an initial rotating probe inspection for discrepancies of the first fastener hole of the horizontal flange of the keel beam by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4087, dated November 21, 2003. If no cracking is found, before further flight, inspect for correct fastener diameter tolerance; if the fastener diameter is out-of-tolerance, before further flight, ream to oversize the fastener holes and install oversize fasteners in accordance with the Accomplishment Instructions of the service bulletin. (g) If no cracking is found during any inspection required by paragraph (f) of this AD: Within 1,480 flight cycles or 7,400 flight hours, whichever is first, after accomplishing the inspection: Perform an initial ultrasonic inspection for discrepancies of the first fastener hole of the horizontal flange of the keel beam by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4087, dated November 21, 2003. If no cracking is found, repeat the ultrasonic inspection thereafter at intervals not to exceed 1,480 flight cycles or 7,400 flight hours, whichever is first. Repair Per the FAA or the Direction Générale De L'Aviation Civile (DGAC) (h) If any cracking is found during any inspection required by this AD: Before further flight, repair per a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent). Within 1,480 flight cycles or 7,400 flight hours, whichever is first, after repair of any cracking, perform an ultrasonic inspection as required by paragraph (g) of this AD. Repeat the ultrasonic inspection thereafter at intervals not to exceed 1,480 flight cycles or 7,400 flight hours, whichever is first. No Reporting Required (i) Although Airbus Service Bulletin A340-57-4087, dated November 21, 2003, specifies submitting an inspection report to the manufacturer, this AD does not include that requirement. 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. Related Information (k) French airworthiness directive F-2005-007, dated January 5, 2005, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus Service Bulletin A340-57-4087, including Appendix 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/cfr/ibr-locations.html . Issued in Renton, Washington, on September 28, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-20073 Filed 10-11-05; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report that certain inspections done before accomplishing the modification of the lower keel beam fitting and forward lower shell connection revealed cracking that was outside the modification limits specified in the service bulletin; the cracking was repaired by installing a titanium doubler. The FAA is issuing this AD to find and fix discrepancies of the fastener holes of the horizontal flange of the keel beam, which could result in reduced structural integrity of the fuselage.