2006-02-06: Frame foot and adjacent frames

2006-02-06 Airbus: Amendment 39-14458. Docket No. FAA-2005-22810; Directorate Identifier 2005-NM-143-AD. Effective Date (a) This AD becomes effective February 24, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A310-203, -204, and -222 airplanes, and Model A310-304, -322, -324, and -325 airplanes; certificated in any category; except those airplanes on which Airbus Modification 13023 has been accomplished in production. Unsafe Condition (d) This AD results from a structural evaluation of Model A310 airplanes for widespread fatigue damage of the frame foot run-outs from frame (FR) 43 through FR 46. We are issuing this AD to prevent fatigue cracking of the frame foot run-outs, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and result in reduced structural integrity of the fuselage. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection/Repair/Modification (f) At the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD, perform a one-time rototest inspection for cracking of the frame foot and adjacent frames and skin in the area surrounding the frame foot run-outs from fuselage frame FR 43 through FR 46 by doing all the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, dated April 4, 2005. Except as required by paragraph (g) of this AD, repair any cracking before further flight in accordance with the Accomplishment Instructions of the service bulletin. Before further flight after performing the inspection, modify the fastener holes located between FR 43 and FR 46 on the center box and on the upper fuselage bent sections in accordance with the Accomplishment Instructions of the service bulletin. (1) Before the accumulation of the total flight-cycle or flight- hour threshold, whichever is first, specified in the Accomplishment Timescale table in paragraph 1.E.(2), "Compliance" of the service bulletin. (2) At the earlier of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. (i) Before the accumulation of the total flight-cycle or flight- hour threshold, whichever is first, specified in Notes 01, 02, and 03 in paragraph 1.E.(2), "Compliance" of the service bulletin, after the effective date of this AD. (ii) Within 3,000 flight cycles after the effective date of this AD. Repair Per FAA or Direction Generale de l'Aviation Civile (DGAC) (g) For any cracking found during any inspection required by this AD for which the service bulletin specifies to contact the manufacturer for an appropriate repair: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent).Alternative Methods of Compliance (AMOCs) (h)(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 (i) French airworthiness directive F-2005-078, dated May 11, 2005, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Airbus Service Bulletin A310-53-2124, dated April 4, 2005, 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.