AD 2009-09-01

(a) This airworthiness directive (AD) becomes effective May 6, 2009.

(b) None.

(c) This AD applies to Airbus Model A318-111, A318-112, A318-121, A318-122, A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, A319-133, A320-111, A320-211, A320-212, A320-214, A320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232 airplanes; certificated in any category; except airplanes identified in paragraph (c)(1), (c)(2), (c)(3), or (c)(4) of this AD.

(1) Any airplane for which the date of issuance of the original French or German airworthiness certificate or the date of issuance of the original French or German export certificate of airworthiness, is after February 24, 2009 (the effective date of European Aviation Safety Agency (EASA) Airworthiness Directive 2009-0025 [Corrected: February 11, 2009]).

(2) Any airplane for which it can be positively determined from records review that the bearing of any pendulum assembly has not been replaced or re-swaged since the date of issuance of the original French or German airworthiness certificate or the date of issuance of the original French or German export certificate of airworthiness.

(3) Any airplane inspected prior to the effective date of this AD in accordance with Airbus Service Bulletin A320-57A1146, dated September 21, 2007 (for Model A318, A319 and A320 series airplanes); or in accordance with Airbus Service Bulletin A320-57A1144, dated February 6, 2007, or A320-57-1144, Revision 01, dated June 18, 2007 (for Model A321 series airplanes), and on which it can be positively determined from a records review that thereafter no replacement with a pendulum assembly whose bearing has been replaced or re-swaged since new manufacture was performed.

(4) Any airplane inspected prior to the effective date of this AD in accordance with Airbus Service Bulletin A320-57A1146, dated September 21, 2007 (for Model A318, A319 and A320 series airplanes); or in accordance with Airbus Service Bulletin A320-57A1144, dated February 6, 2007, or A320-57-1144, Revision 01, dated June 18, 2007 (for Model A321 series airplanes), and on which it can be positively determined from a records review that thereafter no pendulum bearing replacement or re-swaging was performed.

(d) Air Transport Association (ATA) of America Code 57: Wings.

(e) The mandatory continued airworthiness information (MCAI) states:

During a routine inspection on an Airbus A321 aircraft, the operator discovered that a bearing of the flap track No.1 pendulum assembly had migrated out of position. The investigation has confirmed that the pendulum bearing migration was probably due to the methods used during in-service replacement of the bearing during maintenance, whereby the necessary special tools, fixtures and equipment were not used. This condition, if not corrected, could lead to separation of the bearing/flap track assembly, resulting in the detachment of the affected flap surface from the wing and consequent loss of control of the aircraft.

For the reasons described above, this AD requires a one-time inspection of the affected flap track No.1 pendulum assembly for bearing migration and, in case any bearing is found to have migrated, the replacement of the affected flap track pendulum assembly.

Note:

Based on this in-service experience, showing the potential safety effect of not following the TC Holder's accomplishment instructions, Airbus has removed the instructions to replace the bearing in the pendulum assembly from the A320 Family aircraft maintenance documentation. Component Maintenance Manual (CMM) references are 27-54-43 for the A318, A319 and A320, and 27-54-42 for the A321.

If no migration is found during the one-time inspection for migration, the required actions include an inspection for correct swaging of the spherical bearing in the No.1 flap track pendulum assembly. If the bearing is found incorrectly swaged, the corrective actions include contacting Airbus for repair instructions and doing the repair. You may obtain further information by examining the MCAI in the AD docket.

(f) Unless already done, do the following actions:

(1) Within 600 flight hours after the effective date of this AD, inspect for migration, and correct swaging as applicable, of the pendulum assembly of flap track number 1 in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57A1146, dated September 21, 2007 (for Model A318, A319 and A320 series airplanes); or in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1144, Revision 01, dated June 18, 2007 (for Model A321 series airplanes).

(i) If the bearing of the pendulum assembly of flap track number 1 is found to have migrated, before further flight, replace the affected pendulum assembly with a new pendulum assembly, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57A1146, dated September 21, 2007 (for Model A318, A319 and A320 series airplanes); or in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1144, Revision 01, dated June 18, 2007 (for Model A321 series airplanes).

(ii) If the bearing of the pendulum assembly of flap track number 1 is incorrectly swaged, before further flight, contact Airbus for repair instructions and accomplish the repair.

(2) After the effective date of this AD, no person shall replace the bearing in the pendulum assembly of the flap track or install a pendulum assembly, unless:

(i) The pendulum assembly is of new manufacture, or

(ii) It can be positively determined from a records review that the bearing of the pendulum assembly has not been replaced or re-swaged since new.

(3) Accomplishment of the actions required by paragraph (f)(1), (f)(2), and (f)(3) of this AD, before the effective date of this AD in accordance with Airbus Service Bulletin A320-57A1144, dated February 6, 2007, is acceptable for compliance with the corresponding requirements of paragraph (f) of this AD for Airbus Model A321 series airplanes.

Note 1:

This AD differs from the MCAI and/or service information as follows: No differences.

(g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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 98057-3356; telephone (425) 227-2141; fax (425) 227-1149. 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.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056.

(h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2009-0025, dated February 10, 2009; Airbus Service Bulletin A320-57-1144, Revision 01, dated June 18, 2007; and Airbus Service Bulletin A320-57A1146, dated September 21, 2007, for related information.

(i) You must use Airbus Service Bulletin A320-57A1146, including Appendix 01, dated September 21, 2007; or Airbus Service Bulletin A320-57-1144, including Appendix 01, Revision 01, dated June 18, 2007; as applicable; 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; telephone +33 5 61 93 36 96; 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 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 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.