AD 2008-17-02 Airworthiness Directives; Airbus Model A310 Airplanes

Models named: A310. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A310 airplanes, certificated in any category, all certified models, all serial numbers; except for those where LH (left-hand) and RH (right-hand) wing MLG (main landing gear) rib 5 forward lugs have been repaired by installation of oversized interference fit bushes as per Airbus A310 Repair Instruction R572-49121, or which have had Airbus Service Bulletin A310-57-2090 (Airbus modification 13329) embodied in service.

Unless already done, before the accumulation of 12,000 total flight cycles or before the accumulation of 12,000 flight cycles on MLG Rib 5, or within 14 days after the effective date of this AD, whichever occurs latest: Perform either a detailed visual inspection (DVI) or an ultrasonic inspection of the LH and RH MLG Rib 5 aft bearing forward lug for cracks, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007. If a MLG Rib 5 has been replaced on one side only, then the RH and LH must be considered separately. Doing this inspection ends the requirements of paragraph (f) for that MLG Rib 5 only. Note 1: The ultrasonic inspection will detect any crack at an early stage and will limit the risk of extensive repairs. This earlier crack detection is not possible with the DVI. (1) If no crack is detected during any inspection required by paragraph (g) of this AD: Repeat the applicable inspection at the time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Repeat the DVI thereafter at intervals not to exceed 100 flight cycles. (ii) Repeat the ultrasonic inspection thereafter at intervals not to exceed 825 flight cycles. (2) Replacement of the MLG Rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG Rib 5, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007, ends the repetitive inspections required by paragraph (g)(1) of this AD for that MLG Rib 5 only. (3) If any crack is detected during the DVI required by paragraph (g) of this AD: Before further flight, contact Airbus for replacement instructions and replace the MLG Rib 5 bushes before further flight. Repeat the applicable inspection in paragraph (g) of this AD at the time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. Accomplishing the replacement of the MLG Rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG Rib 5, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007, ends the repetitive inspections required by paragraph (g)(1) of this AD for that MLG Rib 5 only. (4) If any crack is detected during the ultrasonic inspection required by paragraph (g) of this AD, before further flight, accomplish the actions specified in paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as applicable. (i) If any crack is not visible on MLG Rib 5: Before further flight, repair MLG Rib 5 using Airbus A310 Repair Instruction R572-49121, Issue C, dated May 2007. After embodiment of the repair instruction, no further actions are necessary as required by this AD and specified in Airbus Service Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007, for that MLG Rib 5 only. (ii) If any crack is visible on MLG Rib 5: Before further flight, contact Airbus for rib replacement instructions, and replace before further flight. Repeat the applicable inspection in paragraph (g) of this AD at the time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. Accomplishing the replacement of the MLG Rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG Rib 5, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007, ends the repetitive inspections required by paragraph (g) of this AD for that MLG Rib 5 only. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: (1) Although the MCAI or service information allows flight with cracks on aft bearing forward lugs for a certain period of time, this AD requires replacing MLG Rib 5 before further flight if any crack is found. (2) Although the MCAI or service information specifies submitting an inspection report sheet to Airbus, this AD would not require that action. Other FAA AD Provisions (h) 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 (i) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2007-0195, dated July 19, 2007; and Airbus Service Bulletins A310-57-2090, Revision 01, dated December 19, 2007; and A310-57-2091, including Appendix 01, dated May 22, 2007; for related information. Material Incorporated by Reference (j) You must use the applicable service information specified in Table 1 of this AD to do the actions required by this AD, unless the AD specifies otherwise. Table 1—All Material Incorporated by Reference Airbus service information Revision/issue level Date Service Bulletin A310-57A2088, excluding Appendix 01 Original November 6, 2006. Service Bulletin A310-57-2090 01 December 19, 2007. Service Bulletin A310-57-2091, excluding Appendix 01 Original May 22, 2007. A310 Repair Instruction R572-49121 C May 2007. (1) The Director of the Federal Register approved the incorporation by reference of the service information specified in Table 2 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51. Table 2—New Material Incorporated by Reference Airbus service information Revision/issue level Date Service Bulletin A310-57-2090 01 December 19, 2007. Service Bulletin A310-57-2091, excluding Appendix 01 Original May 22, 2007. A310 Repair Instruction R572-49121 C May 2007. (2) The Director of the Federal Register previously approved the incorporation by reference of Airbus Service Bulletin A310-57A2088, excluding Appendix 01, dated November 6, 2006, on February 6, 2007 (72 FR 2612, January 22, 2007). (3) For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. (4) 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 . Issued in Renton, Washington, on July 31, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-18561 Filed 8-12-08; 8:45 am] BILLING CODE 4910-13-P

Unless already done, before the accumulation of 12,000 total flight cycles or before the accumulation of 12,000 flight cycles on MLG Rib 5, or within 14 days after the effective date of this AD, whichever occurs latest: Perform either a detailed visual inspection (DVI) or an ultrasonic inspection of the LH and RH MLG Rib 5 aft bearing forward lug for cracks, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007. If a MLG Rib 5 has been replaced on one side only, then the RH and LH must be considered separately. Doing this inspection ends the requirements of paragraph (f) for that MLG Rib 5 only. Note 1: The ultrasonic inspection will detect any crack at an early stage and will limit the risk of extensive repairs. This earlier crack detection is not possible with the DVI. (1) If no crack is detected during any inspection required by paragraph (g) of this AD: Repeat the applicable inspection at the time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Repeat the DVI thereafter at intervals not to exceed 100 flight cycles. (ii) Repeat the ultrasonic inspection thereafter at intervals not to exceed 825 flight cycles. (2) Replacement of the MLG Rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG Rib 5, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007, ends the repetitive inspections required by paragraph (g)(1) of this AD for that MLG Rib 5 only. (3) If any crack is detected during the DVI required by paragraph (g) of this AD: Before further flight, contact Airbus for replacement instructions and replace the MLG Rib 5 bushes before further flight. Repeat the applicable inspection in paragraph (g) of this AD at the time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. Accomplishing the replacement of the MLG Rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG Rib 5, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007, ends the repetitive inspections required by paragraph (g)(1) of this AD for that MLG Rib 5 only. (4) If any crack is detected during the ultrasonic inspection required by paragraph (g) of this AD, before further flight, accomplish the actions specified in paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as applicable. (i) If any crack is not visible on MLG Rib 5: Before further flight, repair MLG Rib 5 using Airbus A310 Repair Instruction R572-49121, Issue C, dated May 2007. After embodiment of the repair instruction, no further actions are necessary as required by this AD and specified in Airbus Service Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007, for that MLG Rib 5 only. (ii) If any crack is visible on MLG Rib 5: Before further flight, contact Airbus for rib replacement instructions, and replace before further flight. Repeat the applicable inspection in paragraph (g) of this AD at the time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. Accomplishing the replacement of the MLG Rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG Rib 5, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007, ends the repetitive inspections required by paragraph (g) of this AD for that MLG Rib 5 only. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: (1) Although the MCAI or service information allows flight with cracks on aft bearing forward lugs for a certain period of time, this AD requires replacing MLG Rib 5 before further flight if any crack is found. (2) Although the MCAI or service information specifies submitting an inspection report sheet to Airbus, this AD would not require that action. Other FAA AD Provisions (h) 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 (i) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2007-0195, dated July 19, 2007; and Airbus Service Bulletins A310-57-2090, Revision 01, dated December 19, 2007; and A310-57-2091, including Appendix 01, dated May 22, 2007; for related information. Material Incorporated by Reference (j) You must use the applicable service information specified in Table 1 of this AD to do the actions required by this AD, unless the AD specifies otherwise. Table 1—All Material Incorporated by Reference Airbus service information Revision/issue level Date Service Bulletin A310-57A2088, excluding Appendix 01 Original November 6, 2006. Service Bulletin A310-57-2090 01 December 19, 2007. Service Bulletin A310-57-2091, excluding Appendix 01 Original May 22, 2007. A310 Repair Instruction R572-49121 C May 2007. (1) The Director of the Federal Register approved the incorporation by reference of the service information specified in Table 2 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51. Table 2—New Material Incorporated by Reference Airbus service information Revision/issue level Date Service Bulletin A310-57-2090 01 December 19, 2007. Service Bulletin A310-57-2091, excluding Appendix 01 Original May 22, 2007. A310 Repair Instruction R572-49121 C May 2007. (2) The Director of the Federal Register previously approved the incorporation by reference of Airbus Service Bulletin A310-57A2088, excluding Appendix 01, dated November 6, 2006, on February 6, 2007 (72 FR 2612, January 22, 2007). (3) For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. (4) 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 . Issued in Renton, Washington, on July 31, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-18561 Filed 8-12-08; 8:45 am] BILLING CODE 4910-13-P