AD 2006-26-12 Airworthiness Directives; Airbus Model A330, A340-200, and A340-300 Series Airplanes

Models named: A330, A340-200, A340-300 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A330, A340-200, and A340-300 series airplanes; certificated in any category; except airplanes on which Airbus Modification 53446 has been incorporated 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. Restatement of Certain Requirements of AD 2005-06-08 Service Bulletin Reference (f) The term “service bulletin,” as used in paragraphs (g), (h), and (i) of this AD, means the Accomplishment Instructions of Airbus Service Bulletins A330-25-3227 (for Model A330 series airplanes) and A340-25-4230 (for Model A340-200 and -300 series airplanes), both Revision 01, both dated May 3, 2005; as applicable. Accomplishment before the effective date of this AD of Airbus Service Bulletins A330-25-3227 and A340-25-4230, both including Appendix 01, both dated June 17, 2004, as applicable, is an acceptable means of compliance for paragraphs (g), (h), and (i) of this AD. Initial Inspection (g) At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, perform a detailed inspection of the bracket having part number (P/N) F2511012920000, which attaches the flight deck instrument panel to airplane structure, in accordance with the applicable service bulletin. (1) For Model A330 series airplanes: Prior to the accumulation of 16,500 total flight cycles, or within 60 days after April 25, 2005 (the effective date of AD 2005-06-08), whichever is later. (2) For Model A340-200 and -300 series airplanes: Prior to the accumulation of 9,700 total flight cycles, or within 2,700 flight cycles after April 25, 2005, whichever is later. Note 1: 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.” No Cracking/Repetitive Inspections (h) If no crack is found during the initial inspection required by paragraph (g) of this AD: Repeat the inspection thereafter at the applicable interval specified in paragraph (h)(1) or (h)(2) of this AD, until the replacement specified in paragraph (k) of this AD has been accomplished. (1) For Model A330 series airplanes: Intervals not to exceed 13,800 flight cycles. (2) For Model A340-200 and -300 series airplanes: Intervals not to exceed 7,000 flight cycles. Crack Found/Replacement and Repetitive Inspections (i) If any crack is found during any inspection required by paragraph (g) or (h) of this AD: Do the actions in paragraphs (i)(1) and (i)(2) of this AD, except as provided by paragraph (j) of this AD, until accomplishment of the replacement required by paragraph (k) of this AD. (1) Before further flight: Replace the cracked bracket with a new, improved bracket having P/N F2511012920095, in accordance with the service bulletin. (2) Repeat the inspection of the replaced bracket as required by paragraph (g) of this AD, at the time specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD. Then, do repetitive inspections or replace the bracket as specified in paragraph (h) or (i) of this AD, as applicable. (i) For Model A330 series airplanes: Within 16,500 flight cycles after replacing the bracket. (ii) For Model A340-200 and -300 series airplanes: Within 9,700 flight cycles after replacing the bracket. (j) If both flanges of a bracket are found broken during any inspection required by this AD: Before further flight, replace the bracket as specified in paragraph (i) of this AD and perform any applicable related investigative and corrective actions (which may include inspections for damage to surrounding structure caused by the broken bracket, and corrective actions for any damage that is found), in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). New Requirements of This AD Replacement of Brackets/Investigative and Corrective Actions (k) Except as required by paragraph (i)(1) of this AD: Within 72 months after the effective date of this AD, replace existing brackets having P/N F2511012920000 or P/N F2511012920095 with titanium-reinforced brackets having P/N F2511305220096; and perform any related investigative and corrective actions (which may include detailed inspections for cracking of the bracket or damage to surrounding structure caused by a broken bracket, and applicable corrective actions for any damage that is found); in accordance with the Accomplishment Instructions of Airbus Service Bulletins A330-25-3249 and A340-25-4245, excluding Appendix 01, both dated May 3, 2005, as applicable. If any crack is found, before further flight, repair in accordance with the applicable service bulletin. Replacement of the affected bracket with a titanium-reinforced bracket having P/N F2511305220096 ends the repetitive inspections required by paragraph (h) or (i) of this AD. Although the service bulletins specify to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (l)(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 (m) EASA airworthiness directives 2006-0045 and 2006-0047, both dated February 16, 2006, also address the subject of this AD. Material Incorporated by Reference (n) You must use the applicable service bulletin specified in Table 1 of this AD 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 the service bulletins specified in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On April 25, 2005 (70 FR 13345, March 21, 2005), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A330-25-3227, including Appendix 01, dated June 17, 2004; and Airbus Service Bulletin A340-25-4230, including Appendix 01, dated June 17, 2004. (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 . Table 1.—All Material Incorporated by Reference Airbus service bulletin Revision level Date A330-25-3227, including Appendix 01 Original June 17, 2004. A330-25-3227, excluding Appendix 01 01 May 3, 2005. A330-25-3249 Original May 3, 2005. A340-25-4230, including Appendix 01 Original June 17, 2004. A340-25-4230, excluding Appendix 01 01 May 3, 2005. A340-25-4245 Original May 3, 2005. Table 2.—New Material Incorporated by Reference Airbus service bulletin Revision level Date A330-25-3227, excluding Appendix 01 01 May 3, 2005. A330-25-3249 Original May 3, 2005. A340-25-4230, excluding Appendix 01 01 May 3, 2005. A340-25-4245 Original May 3, 2005. Issued in Renton, Washington, on December 21, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-22473 Filed 1-3-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of cracking damage found on certain brackets that were replaced to address an unsafe condition. We are issuing this AD to prevent a cracked bracket. Failure of this bracket, combined with failure of the horizontal beam, could result in collapse of the left part of the flight deck instrument panel, and consequent reduced controllability of the airplane.