AD 2009-19-01 Airworthiness Directives; Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C Airplanes

Models named: A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes, certificated in any category, all serial numbers, except airplanes which have been modified in accordance with Airbus Mandatory Service Bulletin A300-57-0252 (Airbus Modification 13400).

Unless already done, do the following actions. (1) At the times specified in Table 1 or Table 2 of this AD, as applicable, perform a high frequency eddy current inspection to detect fatigue cracks of the center hinge bracket of the center flap inner tab (on both wings), in accordance with Airbus Mandatory Service Bulletin A300-57-0250, Revision 01, dated September 29, 2008. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 850 flight cycles. Table 1—Airplanes on which Airbus Service Bulletin A300-57-0205 Has Not Been Done Flight cycles accumulated since first flight as of the effective date of this AD Compliance time Less than 6,000 flight cycles Prior to accumulating 6,000 flight cycles since first flight or within 90 days after the effective date of this AD, whichever occurs later. 6,000 flight cycles or more, but less than 12,000 flight cycles Within 850 flight cycles after the effective date of this AD. 12,000 flight cycles or more Within 500 flight cycles after the effective date of this AD. Table 2—Airplanes on Which Airbus Service Bulletin A300-57-0205 Has Been Done Flight cycles accumulated since Airbus Service Bulletin A300-57-0205 modification as of the effective date of this AD Compliance time Less than 6,000 flight cycles Prior to accumulating 6,000 flight cycles since Airbus Service Bulletin A300-57-0205 modification or within 90 days after the effective date of this AD, whichever occurs later. 6,000 flight cycles or more, but less than 12,000 flight cycles Within 850 flight cycles after the effective date of this AD. 12,000 flight cycles or more Within 500 flight cycles after the effective date of this AD. (2) If any crack is detected during any inspection required by this AD, before further flight, replace the center hinge bracket in the accordance with Airbus Mandatory Service Bulletin A300-57-0250, Revision 01, dated September 29, 2008. Within 6,000 flight cycles after replacing the center hinge bracket, do the inspection required by paragraph (f)(1) of this AD, and if no cracking is found, repeat the inspection thereafter at intervals not to exceed 850 flight cycles. (3) Modifying the inboard tab of the center flaps in accordance with Airbus Mandatory Service Bulletin A300-57-0252, dated August 27, 2008, terminates the requirements of this AD. (4) Actions accomplished before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A300-57-0250, dated November 2, 2007, are considered acceptable for compliance with the corresponding actions specified in this AD. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: Although the European Aviation Safety Agency AD 2007-0299R2, dated October 28, 2008 and Airbus Mandatory Service Bulletin A300-57-0250, dated November 2, 2007, specify to submit certain information to the manufacturer, this AD does not include that requirement. Other FAA AD Provisions (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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2125; 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. Related Information (h) Refer to MCAI Airworthiness Directive 2007-0299R2, dated October 28, 2008; Airbus Mandatory Service Bulletin A300-57-0250, Revision 01, dated September 29, 2008; and Airbus Mandatory Service Bulletin A300-57-0252, dated August 27, 2008; for related information. Material Incorporated by Reference (i) You must use Airbus Mandatory Service Bulletin A300-57-0250, Revision 01, excluding Appendix 1, dated September 29, 2008, to do the actions required by this AD, unless the AD specifies otherwise. If you do the optional terminating modification specified by this AD, you must use Airbus Service Bulletin A300-57-0252, dated August 27, 2008, to perform that action, 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 SAS—EAW (Airworthiness Office), 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. Issued in Renton, Washington, on August 31, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-21411 Filed 9-8-09; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. (1) At the times specified in Table 1 or Table 2 of this AD, as applicable, perform a high frequency eddy current inspection to detect fatigue cracks of the center hinge bracket of the center flap inner tab (on both wings), in accordance with Airbus Mandatory Service Bulletin A300-57-0250, Revision 01, dated September 29, 2008. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 850 flight cycles. Table 1—Airplanes on which Airbus Service Bulletin A300-57-0205 Has Not Been Done Flight cycles accumulated since first flight as of the effective date of this AD Compliance time Less than 6,000 flight cycles Prior to accumulating 6,000 flight cycles since first flight or within 90 days after the effective date of this AD, whichever occurs later. 6,000 flight cycles or more, but less than 12,000 flight cycles Within 850 flight cycles after the effective date of this AD. 12,000 flight cycles or more Within 500 flight cycles after the effective date of this AD. Table 2—Airplanes on Which Airbus Service Bulletin A300-57-0205 Has Been Done Flight cycles accumulated since Airbus Service Bulletin A300-57-0205 modification as of the effective date of this AD Compliance time Less than 6,000 flight cycles Prior to accumulating 6,000 flight cycles since Airbus Service Bulletin A300-57-0205 modification or within 90 days after the effective date of this AD, whichever occurs later. 6,000 flight cycles or more, but less than 12,000 flight cycles Within 850 flight cycles after the effective date of this AD. 12,000 flight cycles or more Within 500 flight cycles after the effective date of this AD. (2) If any crack is detected during any inspection required by this AD, before further flight, replace the center hinge bracket in the accordance with Airbus Mandatory Service Bulletin A300-57-0250, Revision 01, dated September 29, 2008. Within 6,000 flight cycles after replacing the center hinge bracket, do the inspection required by paragraph (f)(1) of this AD, and if no cracking is found, repeat the inspection thereafter at intervals not to exceed 850 flight cycles. (3) Modifying the inboard tab of the center flaps in accordance with Airbus Mandatory Service Bulletin A300-57-0252, dated August 27, 2008, terminates the requirements of this AD. (4) Actions accomplished before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A300-57-0250, dated November 2, 2007, are considered acceptable for compliance with the corresponding actions specified in this AD. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: Although the European Aviation Safety Agency AD 2007-0299R2, dated October 28, 2008 and Airbus Mandatory Service Bulletin A300-57-0250, dated November 2, 2007, specify to submit certain information to the manufacturer, this AD does not include that requirement. Other FAA AD Provisions (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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2125; 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. Related Information (h) Refer to MCAI Airworthiness Directive 2007-0299R2, dated October 28, 2008; Airbus Mandatory Service Bulletin A300-57-0250, Revision 01, dated September 29, 2008; and Airbus Mandatory Service Bulletin A300-57-0252, dated August 27, 2008; for related information. Material Incorporated by Reference (i) You must use Airbus Mandatory Service Bulletin A300-57-0250, Revision 01, excluding Appendix 1, dated September 29, 2008, to do the actions required by this AD, unless the AD specifies otherwise. If you do the optional terminating modification specified by this AD, you must use Airbus Service Bulletin A300-57-0252, dated August 27, 2008, to perform that action, 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 SAS—EAW (Airworthiness Office), 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. Issued in Renton, Washington, on August 31, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-21411 Filed 9-8-09; 8:45 am] BILLING CODE 4910-13-P