AD 2006-04-06 Airworthiness Directives; Airbus Model A318-100 Series Airplanes, Model A319-100 Series Airplanes, Model A320-111 Airplanes, Model A320-200 Series Airplanes, and Model A321-100 Series Airplanes

Models named: A318-111, -112, A319-111, -113, -114, -115, -131, -132, -133, A320-111. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Airbus Model A318-111 and -112 airplanes on which Airbus Modification 26495 has been incorporated in production. (2) All Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, and -131 airplanes.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Certain Requirements of AD 2000-24-02 Modification (f) For Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, and -131 airplanes; except those on which Airbus Modification 26495 has been accomplished in production: Within 18 months after January 8, 2001 (the effective date of AD 2000-24-02), modify the sliding panel driving mechanism of the flap drive trunnions, in accordance with Airbus Service Bulletin A320-27-1117, Revision 02, dated January 18, 2000. Note 1: Accomplishment of the modification required by paragraph (f) of this AD before January 8, 2001, in accordance with Airbus Service Bulletin A320-27-1117, dated July 31, 1997; or Revision 01, dated June 25, 1999, is acceptable for compliance with that paragraph. Requirements of This AD Detailed Inspections (g) For all airplanes: At the latest of the applicable compliance times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, do a detailed inspection of the inboard flap trunnions for any wear marks and of the sliding panels for any cracking at the long edges, and do any corrective actions as applicable, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320-57-1133, dated July 28, 2005; except as provided by paragraph (h) of this AD. Any corrective actions must be done at the compliance times specified in Figures 5 and 6, as applicable, of the service bulletin; except as provided by paragraph (i) of this AD. Repeat the detailed inspections thereafter at intervals not to exceed 4,000 flight hours. Note 2: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” (1) Before accumulating 4,000 total flight hours on the inboard flap trunnion since new. (2) Within 4,000 flight hours after accomplishing paragraph (f) of this AD. (3) Within 600 flight hours after the effective date of this AD. No Reporting Requirement (h) Although Airbus Service Bulletin A320-57-1133, dated July 28, 2005, specifies to submit certain information to the manufacturer, this AD does not include that requirement. Compliance Times (i) Where Airbus Service Bulletin A320-57-1133, dated July 28, 2005, specifies replacing the sliding panel at the next opportunity, replace it within 600 flight hours after the inspection required by paragraph (g) of this AD. If the trunnion is found damaged during any inspection required by paragraph (g) of this AD, do the corrective actions specified in the service bulletin before further flight. Where the service bulletin specifies contacting the manufacturer for a grace period assessment after replacing the trunnion or flap, contact the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or Direction Générale de l'Aviation Civile (DGAC) for the grace period assessment. Alternative Methods of Compliance (AMOCs) (j)(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 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-2005-139, dated August 3, 2005, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus Service Bulletin A320-27-1117, Revision 02, dated January 18, 2000; and Airbus Service Bulletin A320-57-1133, excluding Appendix 01, dated July 28, 2005, as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-57-1133, excluding Appendix 01, dated July 28, 2005, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On January 8, 2001 (65 FR 75603, December 4, 2000), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-27-1117, Revision 02, dated January 18, 2000. (3) 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 February 6, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-1405 Filed 2-16-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of wear damage to the inboard flap trunnions after incorporation of the terminating modification. We are issuing this AD to detect and correct wear of the inboard flap trunnions, which could lead to loss of flap surface control and consequently result in the flap detaching from the airplane. A detached flap could result in damage to the tail of the airplane.