AD 2009-06-13 Airworthiness Directives; Airbus Model A321-131 Airplanes

Models named: A321-131. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A321-131 airplanes, certificated in any category, manufacturer serial numbers (MSNs) 364 and 385.

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 (g) At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD, do an ultrasonic inspection to detect cracks of the left-hand and right-hand wing inner rear spars at the attachment holes of the main landing gear (MLG) forward pintle fitting, the actuator cylinder anchorage fitting, and gear rib 5 fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1126, dated August 8, 2003. Repeat the inspection thereafter at intervals not to exceed 3,600 flight cycles or 5,600 flight hours, whichever occurs first. (1) Before the accumulation of 24,000 total flight cycles or 39,400 total flight hours from first flight, whichever occurs first. (2) Within 6 months after the effective date of this AD. Repair (h) If no crack is detected during any inspection required by paragraph (g) of this AD, before further flight, repair the sealant in the inspected areas in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1126, dated August 8, 2003. (i) If any crack is detected during any inspection required by paragraph (g) of this AD, before further flight, repair the crack using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Alternative Methods of Compliance (AMOCs) (j) The Manager, International Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tim Dulin, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-4056; telephone 425-227-2141; fax 425-227-1320. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. Related Information (k) EASA airworthiness directive 2007-0162, dated June 12, 2007, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus Service Bulletin A320-57-1126, dated August 8, 2003, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet http://www.airbus.com. (3) You may review copies of the service information that is incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152. (4) You may also review copies of the service information 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 . Issued in Renton, Washington, on February 27, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-5009 Filed 3-13-09; 8:45 am] BILLING CODE 4910-13-P

This AD results from a finding that certain A321-131 airplanes may not reach the design life goal due to differences in thickness of the inner rear spars and that fatigue cracks may develop on inner rear spars starting from the fastener holes for the attachment of gear rib 5, the forward pintle fitting, and the actuating cylinder anchorage on these airplanes. We are issuing this AD to detect and correct fatigue cracks on the wing inner rear spars, which could result in reduced structural integrity of the airplane.