AD 2009-20-06 Airworthiness Directives; Airbus Model A310-203 and -222 Airplanes and Model A300 B4-620 Airplanes

Models named: A310-203, -222, A300 B4-620. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A310-203 and -222 airplanes, and Model A300 B4-620 airplanes; certificated in any category; all serial numbers except airplanes on which Airbus Modification 05526 has been incorporated in production.

Unless already done, do the following actions. Modification (1) Except as required by paragraph (f)(2) of this AD: Before the accumulation of 12,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later, modify the aft pressure bulkhead to improve the fatigue life of the attachment angles at frame 80/82 and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6006, Revision 3, dated March 24, 1989; or Airbus Mandatory Service Bulletin A310-53-2025, Revision 06, dated August 3, 2006; as applicable. Do all applicable related investigative and corrective actions before further flight. (2) For airplanes identified in paragraph (c) of AD 2006-22-03, amendment 39-14800: At the earlier of the compliance times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, do the actions specified in paragraph (f)(1) of this AD. (i) Before the accumulation of 12,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later. (ii) At the compliance time specified in paragraph (h) of AD 2006-22-03. Inspections and Corrective Action (3) For airplanes on which the modification required by paragraph (f)(1) or (f)(2) of this AD is done after the accumulation of 6,000 total flight cycles since first flight: At the times specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, do an eddy current inspection for any cracking in the critical area of the rear pressure bulkhead between stringers 8 and 18, and repair all cracking before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-6005, Revision 04, dated July 18, 2007; or Airbus Mandatory Service Bulletin A310-53-2024, Revision 05, dated October 13, 2006; as applicable. (i) Before or concurrently with the modification required by paragraph (f)(1) or (f)(2) of this AD, as applicable; and (ii) Before the accumulation of 18,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 9,000 flight cycles. Note 1: For airplanes on which the modification required by paragraph (f)(1) or (f)(2) of this AD is done at or before the accumulation of 6,000 total flight cycles since first flight: No action is required by this AD. For these airplanes, refer to Airbus A300-600 ALI Task 531919-01-1A or Airbus A310 ALI Task 531919-01-1A, as applicable, for guidance on the normal inspection program. (4) Modifications done before the effective date of this AD in accordance with the service bulletins identified in Table 1 of this AD are acceptable for compliance with the requirements of paragraph (f)(1) and (f)(2) of this AD. Table 1—Modifications Done Using Previous Service Bulletins Model— Airbus Service Bulletin— Revision— Dated— A300 B4-620 airplanes A300-53-6006 Original May 6, 1986.   A300-53-6006 1 September 19, 1986.   A300-53-6006 2 August 11, 1988. A310-203 and -222 airplanes A310-53-2025 Original April 21, 1986.   A310-53-2025 1 September 19, 1986.   A310-53-2025 2 February 16, 1987.   A310-53-2025 3 April 7, 1987.   A310-53-2025 4 October 20, 1987.   A310-53-2025 5 March 24, 1989. (5) Inspections done before the effective date of this AD in accordance with the service bulletins identified in Table 2 of this AD are acceptable for compliance with the requirements of paragraph (f)(3) of this AD. Table 2—Inspections Done With Previous Service Bulletins Model— Airbus Service Bulletin— Revision— Dated— A300 B4-620 airplanes A300-53-6005 Original May 6, 1986.   A300-53-6005 1 June 20, 1986.   A300-53-6005 2 September 22, 1986.   A300-53-6005 3 April 22, 1987. A310-203 and -222 airplanes A310-53-2024 Original April 21, 1986.   A310-53-2024 1 June 20, 1986.   A310-53-2024 2 October 2, 1986.   A310-53-2024 3 February 17, 1987.   A310-53-2024 4 February 2, 1988. (6) Modification of the aft pressure bulkhead to improve the fatigue life of the attachment angles at frame (FR) 80/82 in accordance with paragraph (h) of AD 2006-22-03 is acceptable for compliance with the corresponding requirement of paragraphs (f)(1) and (f)(2) of this AD. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows. This AD includes a compliance time specified in paragraph (f)(2) of this AD for airplanes that are also affected by AD 2006-22-03. We realize that the requirements of this AD will necessitate that some operators do the modification required by paragraph (h) of AD 2006-22-03 early. However, accomplishing the modification within the compliance time specified in this AD is required to address cracking in the attachment angles of the rear pressure bulkhead, which could result in failure of the rear pressure bulkhead. 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 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. Related Information (h) Refer to MCAI EASA Airworthiness Directive 2007-0297R1, dated September 17, 2008, and the service bulletins listed in Table 3 of this AD, for related information. Table 3—Related Service Bulletins Airbus Service Bulletin Revision Date Airbus Mandatory Service Bulletin A300-53-6005 04 July 18, 2007. Airbus Mandatory Service Bulletin A310-53-2024 05 October 13, 2006. Airbus Mandatory Service Bulletin A310-53-2025 06 August 3, 2006. Airbus Service Bulletin A300-53-6006 3 March 24, 1989. Material Incorporated by Reference (i) You must use the service information contained in Table 4 of this AD to do the actions required by this AD, unless the AD specifies otherwise. Table 4—Material Incorporated by Reference Airbus Service Bulletin Revision Date Airbus Mandatory Service Bulletin A300-53-6005 04 July 18, 2007. Airbus Mandatory Service Bulletin A310-53-2024 05 October 13, 2006. Airbus Mandatory Service Bulletin A310-53-2025 06 August 3, 2006. Airbus Service Bulletin A300-53-6006 3 March 24, 1989. Airbus Service Bulletin A300-53-6006, Revision 3, dated March 24, 1989, contains the following effective pages:   Page Nos. Revision level shown on page Date shown on page 1, 29, 47, 48 3 March 24, 1989. 2-28, 30-46, 49-52 2 August 11, 1988. (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 September 16, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-23094 Filed 9-28-09; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. Modification (1) Except as required by paragraph (f)(2) of this AD: Before the accumulation of 12,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later, modify the aft pressure bulkhead to improve the fatigue life of the attachment angles at frame 80/82 and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6006, Revision 3, dated March 24, 1989; or Airbus Mandatory Service Bulletin A310-53-2025, Revision 06, dated August 3, 2006; as applicable. Do all applicable related investigative and corrective actions before further flight. (2) For airplanes identified in paragraph (c) of AD 2006-22-03, amendment 39-14800: At the earlier of the compliance times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, do the actions specified in paragraph (f)(1) of this AD. (i) Before the accumulation of 12,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later. (ii) At the compliance time specified in paragraph (h) of AD 2006-22-03. Inspections and Corrective Action (3) For airplanes on which the modification required by paragraph (f)(1) or (f)(2) of this AD is done after the accumulation of 6,000 total flight cycles since first flight: At the times specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, do an eddy current inspection for any cracking in the critical area of the rear pressure bulkhead between stringers 8 and 18, and repair all cracking before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-6005, Revision 04, dated July 18, 2007; or Airbus Mandatory Service Bulletin A310-53-2024, Revision 05, dated October 13, 2006; as applicable. (i) Before or concurrently with the modification required by paragraph (f)(1) or (f)(2) of this AD, as applicable; and (ii) Before the accumulation of 18,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 9,000 flight cycles. Note 1: For airplanes on which the modification required by paragraph (f)(1) or (f)(2) of this AD is done at or before the accumulation of 6,000 total flight cycles since first flight: No action is required by this AD. For these airplanes, refer to Airbus A300-600 ALI Task 531919-01-1A or Airbus A310 ALI Task 531919-01-1A, as applicable, for guidance on the normal inspection program. (4) Modifications done before the effective date of this AD in accordance with the service bulletins identified in Table 1 of this AD are acceptable for compliance with the requirements of paragraph (f)(1) and (f)(2) of this AD. Table 1—Modifications Done Using Previous Service Bulletins Model— Airbus Service Bulletin— Revision— Dated— A300 B4-620 airplanes A300-53-6006 Original May 6, 1986.   A300-53-6006 1 September 19, 1986.   A300-53-6006 2 August 11, 1988. A310-203 and -222 airplanes A310-53-2025 Original April 21, 1986.   A310-53-2025 1 September 19, 1986.   A310-53-2025 2 February 16, 1987.   A310-53-2025 3 April 7, 1987.   A310-53-2025 4 October 20, 1987.   A310-53-2025 5 March 24, 1989. (5) Inspections done before the effective date of this AD in accordance with the service bulletins identified in Table 2 of this AD are acceptable for compliance with the requirements of paragraph (f)(3) of this AD. Table 2—Inspections Done With Previous Service Bulletins Model— Airbus Service Bulletin— Revision— Dated— A300 B4-620 airplanes A300-53-6005 Original May 6, 1986.   A300-53-6005 1 June 20, 1986.   A300-53-6005 2 September 22, 1986.   A300-53-6005 3 April 22, 1987. A310-203 and -222 airplanes A310-53-2024 Original April 21, 1986.   A310-53-2024 1 June 20, 1986.   A310-53-2024 2 October 2, 1986.   A310-53-2024 3 February 17, 1987.   A310-53-2024 4 February 2, 1988. (6) Modification of the aft pressure bulkhead to improve the fatigue life of the attachment angles at frame (FR) 80/82 in accordance with paragraph (h) of AD 2006-22-03 is acceptable for compliance with the corresponding requirement of paragraphs (f)(1) and (f)(2) of this AD. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows. This AD includes a compliance time specified in paragraph (f)(2) of this AD for airplanes that are also affected by AD 2006-22-03. We realize that the requirements of this AD will necessitate that some operators do the modification required by paragraph (h) of AD 2006-22-03 early. However, accomplishing the modification within the compliance time specified in this AD is required to address cracking in the attachment angles of the rear pressure bulkhead, which could result in failure of the rear pressure bulkhead. 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 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. Related Information (h) Refer to MCAI EASA Airworthiness Directive 2007-0297R1, dated September 17, 2008, and the service bulletins listed in Table 3 of this AD, for related information. Table 3—Related Service Bulletins Airbus Service Bulletin Revision Date Airbus Mandatory Service Bulletin A300-53-6005 04 July 18, 2007. Airbus Mandatory Service Bulletin A310-53-2024 05 October 13, 2006. Airbus Mandatory Service Bulletin A310-53-2025 06 August 3, 2006. Airbus Service Bulletin A300-53-6006 3 March 24, 1989. Material Incorporated by Reference (i) You must use the service information contained in Table 4 of this AD to do the actions required by this AD, unless the AD specifies otherwise. Table 4—Material Incorporated by Reference Airbus Service Bulletin Revision Date Airbus Mandatory Service Bulletin A300-53-6005 04 July 18, 2007. Airbus Mandatory Service Bulletin A310-53-2024 05 October 13, 2006. Airbus Mandatory Service Bulletin A310-53-2025 06 August 3, 2006. Airbus Service Bulletin A300-53-6006 3 March 24, 1989. Airbus Service Bulletin A300-53-6006, Revision 3, dated March 24, 1989, contains the following effective pages:   Page Nos. Revision level shown on page Date shown on page 1, 29, 47, 48 3 March 24, 1989. 2-28, 30-46, 49-52 2 August 11, 1988. (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 September 16, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-23094 Filed 9-28-09; 8:45 am] BILLING CODE 4910-13-P