AD 2008-06-18 Airworthiness Directives; Airbus Model A300 Series Airplanes and Airbus Model A300-600 Series Airplanes

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

This AD applies to Airbus Model A300 series airplanes and Model A300-600 series airplanes; certificated in any category; all certified models, all serial numbers.

Unless already done, do the following actions. (1) Except as provided by paragraphs (f)(1)(i), (f)(1)(ii), (f)(1)(iii), and (f)(1)(iv) of this AD: At the threshold specified in paragraph 1.E.(2) of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06, dated March 23, 2007; as applicable; perform the inspection of the wing lower skin panel and associated internal support structure aft of the rear spar and inboard of rib 9 and apply applicable corrective measures in accordance with Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06, dated March 23, 2007; as applicable. All applicable corrective measures must be done at the applicable times specified in paragraph 1.E.(2) and the Accomplishment Instructions of the applicable service bulletin. (i) Where the tables in paragraph 1.E.(2), “Accomplishment Timescale,” of the service bulletins specify a grace period for doing the actions, this AD requires that the actions be done within the specified grace period relative to the effective date of this AD. (ii) Where the tables in paragraph 1.E.(2)(e), “Config 04,” of Airbus Service Bulletin A300-57-0177, Revision 05, specify an inspection interval but not an initial threshold, this AD requires that the actions be done within the specified interval after inspecting in accordance with Table 1A or 1B, as applicable, for Configuration 01 airplanes described in the service bulletin and thereafter at the inspection interval specified in the tables in paragraph 1.E.(2)(e), “Config 04,” of Airbus Service Bulletin A300-57-0177, Revision 05. (iii) Where the tables in paragraph 1.E.(2)(f), “Config 05,” of Airbus Service Bulletin A300-57-6029, Revision 06, specify an inspection interval but not an initial threshold, this AD requires that the actions be done within the specified interval after inspecting in accordance with Table 1A or 1B, as applicable, for configuration 01 of the service bulletin and thereafter at the inspection interval specified in the tables in paragraph 1.E.(2)(f), “Config 05,” of A300-57-6029, Revision 06. (iv) All crack lengths specified in Airbus Service Bulletin A300-57-0177, Revision 05, and A300-57-6029, Revision 06, are considered “not to exceed” lengths. (2) Repeat the inspection at the intervals in, and according to the instructions defined in, Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06, dated March 23, 2007; as applicable; except where Service Bulletin A300-57-0177, Revision 05, specifies repetitive inspections for cracking if Airbus Service Bulletin A300-57-022 has not been embodied, this AD requires doing repetitive inspections for cracking if Airbus Service Bulletin A300-57-0222 (modification 11178H5410) has not been embodied. (3) Report to Airbus the first inspection results, whatever they may be, at the applicable time specified in paragraph (f)(3)(i) or (e)(f)(ii) of this AD. (i) If the inspection was done after the effective date of this AD, submit the report within 30 days after the inspection. (ii) If the inspection was accomplished prior to the effective date of this AD, submit the report within 30 days after the effective date of this AD. (4) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A300-57-0177, Revision 03, dated May 29, 2006; Airbus Service Bulletin A300-57-0177, Revision 04, dated January 5, 2007; Airbus Service Bulletin A300-57-6029, Revision 04, dated May 29, 2006; or Airbus Service Bulletin A300-57-6029, Revision 05, dated October 23, 2006; are considered acceptable for compliance with the corresponding action specified in this AD. FAA AD Differences Note: 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, FAA, Transport Airplane Directorate, 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 European Aviation Safety Agency Airworthiness Directive 2006-0282, dated September 12, 2006; and the service information in Table 1 of this AD; for related information. Table 1.—Service Information Airbus Service Bulletin Revision level Date A300-57-0177 05 March 23, 2007. A300-57-0222 01 March 13, 2006. A300-57-6029 06 March 23, 2007. A300-57-6064 04 March 9, 2006. 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 level Date A300-57-0177 05 March 23, 2007. A300-57-6029 06 March 23, 2007. Issued in Renton, Washington, on March 7, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-5149 Filed 3-18-08; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. (1) Except as provided by paragraphs (f)(1)(i), (f)(1)(ii), (f)(1)(iii), and (f)(1)(iv) of this AD: At the threshold specified in paragraph 1.E.(2) of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06, dated March 23, 2007; as applicable; perform the inspection of the wing lower skin panel and associated internal support structure aft of the rear spar and inboard of rib 9 and apply applicable corrective measures in accordance with Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06, dated March 23, 2007; as applicable. All applicable corrective measures must be done at the applicable times specified in paragraph 1.E.(2) and the Accomplishment Instructions of the applicable service bulletin. (i) Where the tables in paragraph 1.E.(2), “Accomplishment Timescale,” of the service bulletins specify a grace period for doing the actions, this AD requires that the actions be done within the specified grace period relative to the effective date of this AD. (ii) Where the tables in paragraph 1.E.(2)(e), “Config 04,” of Airbus Service Bulletin A300-57-0177, Revision 05, specify an inspection interval but not an initial threshold, this AD requires that the actions be done within the specified interval after inspecting in accordance with Table 1A or 1B, as applicable, for Configuration 01 airplanes described in the service bulletin and thereafter at the inspection interval specified in the tables in paragraph 1.E.(2)(e), “Config 04,” of Airbus Service Bulletin A300-57-0177, Revision 05. (iii) Where the tables in paragraph 1.E.(2)(f), “Config 05,” of Airbus Service Bulletin A300-57-6029, Revision 06, specify an inspection interval but not an initial threshold, this AD requires that the actions be done within the specified interval after inspecting in accordance with Table 1A or 1B, as applicable, for configuration 01 of the service bulletin and thereafter at the inspection interval specified in the tables in paragraph 1.E.(2)(f), “Config 05,” of A300-57-6029, Revision 06. (iv) All crack lengths specified in Airbus Service Bulletin A300-57-0177, Revision 05, and A300-57-6029, Revision 06, are considered “not to exceed” lengths. (2) Repeat the inspection at the intervals in, and according to the instructions defined in, Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06, dated March 23, 2007; as applicable; except where Service Bulletin A300-57-0177, Revision 05, specifies repetitive inspections for cracking if Airbus Service Bulletin A300-57-022 has not been embodied, this AD requires doing repetitive inspections for cracking if Airbus Service Bulletin A300-57-0222 (modification 11178H5410) has not been embodied. (3) Report to Airbus the first inspection results, whatever they may be, at the applicable time specified in paragraph (f)(3)(i) or (e)(f)(ii) of this AD. (i) If the inspection was done after the effective date of this AD, submit the report within 30 days after the inspection. (ii) If the inspection was accomplished prior to the effective date of this AD, submit the report within 30 days after the effective date of this AD. (4) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A300-57-0177, Revision 03, dated May 29, 2006; Airbus Service Bulletin A300-57-0177, Revision 04, dated January 5, 2007; Airbus Service Bulletin A300-57-6029, Revision 04, dated May 29, 2006; or Airbus Service Bulletin A300-57-6029, Revision 05, dated October 23, 2006; are considered acceptable for compliance with the corresponding action specified in this AD. FAA AD Differences Note: 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, FAA, Transport Airplane Directorate, 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 European Aviation Safety Agency Airworthiness Directive 2006-0282, dated September 12, 2006; and the service information in Table 1 of this AD; for related information. Table 1.—Service Information Airbus Service Bulletin Revision level Date A300-57-0177 05 March 23, 2007. A300-57-0222 01 March 13, 2006. A300-57-6029 06 March 23, 2007. A300-57-6064 04 March 9, 2006. 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 level Date A300-57-0177 05 March 23, 2007. A300-57-6029 06 March 23, 2007. Issued in Renton, Washington, on March 7, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-5149 Filed 3-18-08; 8:45 am] BILLING CODE 4910-13-P