AD 2008-11-05 Airworthiness Directives; Airbus Model A310 and A300-600 Series Airplanes

Models named: A310, A300-600 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to AIRBUS Model A310 and A300-600 series airplanes, certificated in any category, all certified models, all serial numbers, on which rudder Part Number (P/N) A55471500 series is fitted, except for those airplanes on which AIRBUS modification number 08827 has been incorporated in production.

Unless already done, do the following actions. (1) Within 500 flight cycles or 6 months after the effective date of this AD, whichever occurs first, perform a special detailed one-time inspection in the areas of rudder hoisting points and trailing edge screws, in accordance with the instructions given in Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, both dated December 20, 2007, as applicable. (i) If no damage is found, within 30 days after the inspection or 30 days after the effective date of this AD, whichever occurs later, report to Airbus using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable. (ii) If any damage is found, within the timescale(s) indicated in Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable, report to Airbus using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable, to get further instructions for repair. Accomplish the repair within the timescale(s) indicated in, and in accordance with, the instructions given in paragraph 3.B.(1)(a) or 3.B.(2)(a), as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable. (2) Within 500 flight cycles or 6 months after the effective date of this AD, whichever occurs first, perform a special detailed inspection along the rudder Z-profile, in accordance with the instructions given in Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, both dated December 3, 2007, as applicable. For airplanes identified as Configuration 01 in the service bulletins, repeat the inspection thereafter at intervals not to exceed 1,400 flight cycles. For airplanes identified as Configuration 02 in the service bulletins, repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles. For temporary repair along the rudder Z-profile for both airplanes identified as Configurations 01 and 02, refer to paragraph 3.C.(1) of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable. (i) If no damage is found, within 30 days after the inspection or 30 days after the effective date of this AD, whichever occurs later, report to AIRBUS using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable. (ii) If any damage is found, verify the findings and apply all applicable corrective actions within the timescale(s) indicated in, and in accordance with instructions given in paragraph 3.B.(1)(a) or 3.B.(2)(a), as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable. Within 30 days after the inspection or corrective action or 30 days after the effective date of this AD, whichever occurs later, submit a report to Airbus using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable. Note 1: For rudder configuration identification, refer to Appendices 3 and 4 of Airbus Service Bulletin A310-55-2044, A310-55-2045, A300-55-6043, and A300-55-6044, as applicable to the airplane model and configuration. (3) As of 30 days after the effective date of this AD: No person shall install a P/N A55471500 series rudder on any airplane as a replacement, unless it has been inspected and repaired, as applicable, in accordance with the instructions of Airbus Service Bulletins A310-55-2045, Revision 01, dated December 20, 2007, and A310-55-2044, Revision 01, dated December 3, 2007; or Airbus Service Bulletins A300-55-6044, Revision 01, dated December 20, 2007, and A300-55-6043, Revision 01, dated December 3, 2007; as applicable. (4) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A300-55-6044 or A310-55-2045, both dated July 23, 2007, are considered acceptable for compliance with the corresponding actions specified in paragraph (f)(1) of this AD. (5) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A300-55-6043 or A310-55-2044, both dated July 23, 2007, are considered acceptable for compliance with the corresponding actions specified in paragraph (f)(2) of this AD. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: No differences. 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: Tom Stafford, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1622; 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) 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. Related Information (h) Refer to MCAI EASA Airworthiness Directive 2007-0266, dated October 8, 2007, and the service bulletins listed in Table 1 of this AD, for related information. Table 1.—Airbus Service Information Airbus service bulletin Revision Date A300-55-6043 01 December 3, 2007. A300-55-6044 01 December 20, 2007. A310-55-2044 01 December 3, 2007. A310-55-2045 01 December 20, 2007. Material Incorporated by Reference (i) You must use the service information specified in Table 2 of this AD 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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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/cfr/ibr-locations.html . Table 2.—Material Incorporated by Reference Airbus service bulletin Revision Date A300-55-6043, including Appendices 1 through 4 01 December 3, 2007. A300-55-6044, including Appendices 1 through 4 01 December 20, 2007. A310-55-2044, including Appendices 1 through 4 01 December 3, 2007. A310-55-2045, including Appendices 1 through 4 01 December 20, 2007. Issued in Renton, Washington, on May 6, 2008. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-10978 Filed 5-20-08; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. (1) Within 500 flight cycles or 6 months after the effective date of this AD, whichever occurs first, perform a special detailed one-time inspection in the areas of rudder hoisting points and trailing edge screws, in accordance with the instructions given in Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, both dated December 20, 2007, as applicable. (i) If no damage is found, within 30 days after the inspection or 30 days after the effective date of this AD, whichever occurs later, report to Airbus using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable. (ii) If any damage is found, within the timescale(s) indicated in Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable, report to Airbus using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable, to get further instructions for repair. Accomplish the repair within the timescale(s) indicated in, and in accordance with, the instructions given in paragraph 3.B.(1)(a) or 3.B.(2)(a), as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable. (2) Within 500 flight cycles or 6 months after the effective date of this AD, whichever occurs first, perform a special detailed inspection along the rudder Z-profile, in accordance with the instructions given in Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, both dated December 3, 2007, as applicable. For airplanes identified as Configuration 01 in the service bulletins, repeat the inspection thereafter at intervals not to exceed 1,400 flight cycles. For airplanes identified as Configuration 02 in the service bulletins, repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles. For temporary repair along the rudder Z-profile for both airplanes identified as Configurations 01 and 02, refer to paragraph 3.C.(1) of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable. (i) If no damage is found, within 30 days after the inspection or 30 days after the effective date of this AD, whichever occurs later, report to AIRBUS using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable. (ii) If any damage is found, verify the findings and apply all applicable corrective actions within the timescale(s) indicated in, and in accordance with instructions given in paragraph 3.B.(1)(a) or 3.B.(2)(a), as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable. Within 30 days after the inspection or corrective action or 30 days after the effective date of this AD, whichever occurs later, submit a report to Airbus using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable. Note 1: For rudder configuration identification, refer to Appendices 3 and 4 of Airbus Service Bulletin A310-55-2044, A310-55-2045, A300-55-6043, and A300-55-6044, as applicable to the airplane model and configuration. (3) As of 30 days after the effective date of this AD: No person shall install a P/N A55471500 series rudder on any airplane as a replacement, unless it has been inspected and repaired, as applicable, in accordance with the instructions of Airbus Service Bulletins A310-55-2045, Revision 01, dated December 20, 2007, and A310-55-2044, Revision 01, dated December 3, 2007; or Airbus Service Bulletins A300-55-6044, Revision 01, dated December 20, 2007, and A300-55-6043, Revision 01, dated December 3, 2007; as applicable. (4) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A300-55-6044 or A310-55-2045, both dated July 23, 2007, are considered acceptable for compliance with the corresponding actions specified in paragraph (f)(1) of this AD. (5) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A300-55-6043 or A310-55-2044, both dated July 23, 2007, are considered acceptable for compliance with the corresponding actions specified in paragraph (f)(2) of this AD. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: No differences. 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: Tom Stafford, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1622; 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) 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. Related Information (h) Refer to MCAI EASA Airworthiness Directive 2007-0266, dated October 8, 2007, and the service bulletins listed in Table 1 of this AD, for related information. Table 1.—Airbus Service Information Airbus service bulletin Revision Date A300-55-6043 01 December 3, 2007. A300-55-6044 01 December 20, 2007. A310-55-2044 01 December 3, 2007. A310-55-2045 01 December 20, 2007. Material Incorporated by Reference (i) You must use the service information specified in Table 2 of this AD 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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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/cfr/ibr-locations.html . Table 2.—Material Incorporated by Reference Airbus service bulletin Revision Date A300-55-6043, including Appendices 1 through 4 01 December 3, 2007. A300-55-6044, including Appendices 1 through 4 01 December 20, 2007. A310-55-2044, including Appendices 1 through 4 01 December 3, 2007. A310-55-2045, including Appendices 1 through 4 01 December 20, 2007. Issued in Renton, Washington, on May 6, 2008. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-10978 Filed 5-20-08; 8:45 am] BILLING CODE 4910-13-P