AD 2009-05-10

(a) This AD becomes effective April 14, 2009.

(b) This AD supersedes AD 2006-26-12.

(c) This AD applies to all Airbus Model A330 airplanes, and Model A340-200 and A340-300 series airplanes; certificated in any category; except those airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD.

(1) Airplanes on which Airbus Modification 53446 has been incorporated in production.

(2) Model A330 airplanes on which Airbus Mandatory Service Bulletin A330-25-3249, Revision 01, dated July 10, 2007, has been embodied in service.

(3) Model A340-200 and -300 series airplanes on which Airbus Mandatory Service Bulletin A340-25-4245, Revision 01, dated July 10, 2007, has been embodied in service.

(d) This AD results from a report that incorrect torque values could damage a certain bracket that attaches the flight deck instrument panel to the airplane structure. 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.

(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.

(f) At the applicable time specified in paragraph (f)(1) or (f)(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 the airplane structure, in accordance with Airbus Mandatory Service Bulletin A330-25-3227 or A340-25-4230, both Revision 01, both dated May 3, 2005, as applicable.

(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cycles, or within 60 days after April 25, 2005 (the effective date of AD 2005-06-08, amendment 39-14016, which was superseded by AD 2006-26-12), whichever is later.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.”

(g) If no crack is found during the initial inspection required by paragraph (f) of this AD: Repeat the inspection thereafter at the applicable interval specified in paragraph (g)(1) or (g)(2) of this AD, in accordance with Airbus Mandatory Service Bulletin A330-25-3227 or A340-25-4230, both Revision 01, both dated May 3, 2005, as applicable, until the replacement specified in paragraph (j) 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.

(h) If any crack is found during any inspection required by paragraph (f) or (g) of this AD: Do the actions in paragraphs (h)(1) and (h)(2) of this AD, except as provided by paragraph (i) of this AD, in accordance with Airbus Mandatory Service Bulletin A330-25-3227 or A340-25-4230, both Revision 01, both dated May 3, 2005, as applicable, until accomplishment of the replacement required by paragraph (j) of this AD.

(1) Before further flight: Replace the cracked bracket with a new, improved bracket having P/N F2511012920095, in accordance with Airbus Mandatory Service Bulletin A330-25-3227 or A340-25-4230, both Revision 01, both dated May 3, 2005, as applicable.

(2) Repeat the inspection of the replaced bracket as required by paragraph (f) of this AD, at the time specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD. Then, do repetitive inspections or replace the bracket as specified in paragraph (g) or (h) 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.

(i) 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 (h) 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).

(j) Except as required by paragraph (h)(1) of this AD: Within 72 months after February 8, 2007 (the effective date of AD 2006-26-12), 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 Airbus Service Bulletin A330-25-3249 or A340-25-4245, both dated May 3, 2005; or Airbus Mandatory Service Bulletin A330-25-3249 or A340-25-4245, both Revision 01, both dated July 10, 2007; as applicable. After the effective date of this AD, use only Revision 01 of Airbus Mandatory Service Bulletin A330-25-3249 or A340-25-4245, both dated July 10, 2007; as applicable. If any crack is found, before further flight, repair in accordance with Airbus Service Bulletin A330-25-3249 or A340-25-4245, both dated May 3, 2005; or Airbus Mandatory Service Bulletin A330-25-3249 or A340-25-4245, both Revision 01, both dated July 10, 2007; as applicable. After the effective date of this AD, use only Revision 01 of Airbus Mandatory Service Bulletin A330-25-3249 or A340-25-4245, both dated July 10, 2007; as applicable. Replacement of the affected bracket with a titanium-reinforced bracket having P/N F2511305220096 ends the repetitive inspections required by paragraph (g) or (h) of this AD. Although Airbus Service Bulletin A330-25-3249 and A340-25-4245, both dated May 3, 2005; and Airbus Mandatory Service Bulletin A330-25-3249 and A340-25-4245, both Revision 01, both dated July 10, 2007; specify to submit certain information to the manufacturer, this AD does not include that requirement.

(k) For airplanes on which the actions required by paragraph (j) of this AD have been accomplished before the effective date of this AD: At the applicable time in paragraph (k)(1) or (k)(2) of this AD, remove the fasteners of the titanium-reinforced bracket and, if a fastener is broken, do a detailed inspection for cracking of the horizontal beam. Do all applicable corrective actions before further flight. Do all actions in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-25-3249 or A340-25-4245, both Revision 01, both dated July 10, 2007, as applicable. Where Airbus Mandatory Service Bulletin A330-25-3249 or A340-25-4245, both Revision 01, both dated July 10, 2007, specifies to contact Airbus, before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA (or its delegated agent).

(1) For Model A330 series airplanes: Prior to the accumulation of 16,500 total flight cycles, or within 20 months after the effective date of this AD, whichever occurs first.

(2) For Model A340-200 and -300 series airplanes: Prior to the accumulation of 12,400 total flight cycles, or within 20 months after the effective date of this AD, whichever occurs first.

(l) This AD provides credit for actions performed in accordance with the service bulletins identified in paragraphs (1)(1) and (l)(2) of this AD.

(1) Accomplishing the actions specified in paragraphs (f), (g), and (h) of this AD before February 8, 2007, in accordance with Airbus Service Bulletin A330-25-3227 or A340-25-4230, both including Appendix 01, both dated June 17, 2004, as applicable, is acceptable for compliance with the requirements of those paragraphs.

(2) Accomplishing the actions specified in paragraphs (j) and (k) of this AD before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A330-25-3249 or A340-25-4245, both dated May 3, 2005, as applicable, is acceptable for compliance with the requirements of those paragraphs.

(m)(1) The Manager, International Branch, ANM-116, 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(2) AMOCs approved previously in accordance with AD 2006-26-12 are approved as AMOCs for the corresponding provisions of this AD.

(n) EASA airworthiness directives 2007-0281 and 2007-0282, both dated November 6, 2007, also address the subject of this AD.

(o) You must use the service information contained in Table 1 of this AD to do the actions required by this AD, as applicable, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of the service information contained in Table 2 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) The Director of the Federal Register previously approved the incorporation by reference of the service information contained in Table 3 of this AD on February 8, 2007 (72 FR 256, January 4, 2007).

(3) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 45 80, e-mail airworthiness.A330-A340@airbus.com.

(4) You may review copies of the service information 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.

(5) You may also review copies of the service information that is incorporated by reference 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.