AD 2007-06-05 Airworthiness Directives; Airbus Model A318, A319, A320 and A321 Airplanes

This AD applies to Airbus Model A318-111 and -112; A319-111, -112, -113, -114, and -115; A320-111, -211, -212, and -214; and A321-111, -112, -211, -212, and -213 airplanes; certificated in any category; all serial numbers, which have CFM International CFM56-5A or CFM56-5B series engines installed.

Unless already done, do the following actions. (1) As of the effective date of this AD: (i) Any maintenance on the engine mounts must be performed in accordance with correct instructions as identified in the Airbus All Operators Telex (AOT) A320-71A1042, Revision 01, dated February 12, 2007; or Goodrich All Operators Letter (AOL) CFM56-074, Revision 1, dated February 1, 2007; and (ii) Any forward engine mount support assemblies fitted on an engine which is used as replacement must be fitted in accordance with correct instructions as identified in Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007; or Goodrich AOL CFM56-074, Revision 1, dated February 1, 2007. (2) For aircraft on which any forward engine mount support assembly has been installed or maintained since May 2006 using erroneous torque values given in the maintenance data identified in paragraph 1. of the Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007, or where the use of correct torque values cannot be established: Within 20 days after the effective date of this AD, accomplish the actions in paragraphs (f)(2)(i), (f)(2)(ii), (f)(2)(iii), and (f)(2)(iv) of this AD, as applicable, in accordance with the instructions of Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007. Aircraft on which no engine removal has been performed since aircraft delivery are not affected by this paragraph. The alternative procedure given in paragraph 4.2.3 of the AOT is acceptable, provided that the nominal torque values specified in paragraphs 4.2.1 and 4.2.2 are restored within 120 flight cycles after accomplishing paragraph 4.2.3 of the AOT. (i) Remove and inspect the following forward engine mount bolts: 77710-5H6 (AMM item 90) and NAS2815C15H (AMM item 85). (ii) If any bolts, 77710-5H6 (AMM item 90), are found broken during the above inspection, before further flight, replace the affected forward engine mount support assembly (AMM item 75). (iii) Replace bolts, 77710-5H6 (AMM item 90) and NAS2815C15H (AMM item 85), with new items and torque them to the correct value. (iv) Re-torque 77458-7H21 bolts (AMM item 95) and NAS2816C7H (AMM item 50) to the correct value. (3) Actions done before the effective date of this AD in accordance with Airbus AOT A320-71A1042, dated February 5, 2007, are acceptable for compliance with the corresponding provisions of paragraph (f)(2) of this AD. (4) Within 7 days after the inspection, report all findings to Airbus Customer Services, Engineering and Technical Support, Attention: Mr. J-P Pourtau SEE11; telephone +33 (0) 5 62 11 04 48; fax +33 (0) 5 61 93 36 14. 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, 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: Tim Dulin, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2141; fax (425) 227-1149. Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding 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 European Aviation Safety Agency (EASA) Airworthiness Directive 2007-0036R1, dated February 27, 2007; Airbus All Operators Telex A320-71A1042, Revision 01, dated February 12, 2007; and Goodrich All Operators Letter CFM56-074, Revision 1, dated February 1, 2007, for related information. Material Incorporated by Reference (i) You must use Airbus All Operators Telex A320-71A1042, Revision 01, dated February 12, 2007; or Goodrich All Operators Letter CFM56-074, Revision 1, dated February 1, 2007; as applicable; 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 . Issued in Renton, Washington, on March 7, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-4535 Filed 3-14-07; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. (1) As of the effective date of this AD: (i) Any maintenance on the engine mounts must be performed in accordance with correct instructions as identified in the Airbus All Operators Telex (AOT) A320-71A1042, Revision 01, dated February 12, 2007; or Goodrich All Operators Letter (AOL) CFM56-074, Revision 1, dated February 1, 2007; and (ii) Any forward engine mount support assemblies fitted on an engine which is used as replacement must be fitted in accordance with correct instructions as identified in Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007; or Goodrich AOL CFM56-074, Revision 1, dated February 1, 2007. (2) For aircraft on which any forward engine mount support assembly has been installed or maintained since May 2006 using erroneous torque values given in the maintenance data identified in paragraph 1. of the Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007, or where the use of correct torque values cannot be established: Within 20 days after the effective date of this AD, accomplish the actions in paragraphs (f)(2)(i), (f)(2)(ii), (f)(2)(iii), and (f)(2)(iv) of this AD, as applicable, in accordance with the instructions of Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007. Aircraft on which no engine removal has been performed since aircraft delivery are not affected by this paragraph. The alternative procedure given in paragraph 4.2.3 of the AOT is acceptable, provided that the nominal torque values specified in paragraphs 4.2.1 and 4.2.2 are restored within 120 flight cycles after accomplishing paragraph 4.2.3 of the AOT. (i) Remove and inspect the following forward engine mount bolts: 77710-5H6 (AMM item 90) and NAS2815C15H (AMM item 85). (ii) If any bolts, 77710-5H6 (AMM item 90), are found broken during the above inspection, before further flight, replace the affected forward engine mount support assembly (AMM item 75). (iii) Replace bolts, 77710-5H6 (AMM item 90) and NAS2815C15H (AMM item 85), with new items and torque them to the correct value. (iv) Re-torque 77458-7H21 bolts (AMM item 95) and NAS2816C7H (AMM item 50) to the correct value. (3) Actions done before the effective date of this AD in accordance with Airbus AOT A320-71A1042, dated February 5, 2007, are acceptable for compliance with the corresponding provisions of paragraph (f)(2) of this AD. (4) Within 7 days after the inspection, report all findings to Airbus Customer Services, Engineering and Technical Support, Attention: Mr. J-P Pourtau SEE11; telephone +33 (0) 5 62 11 04 48; fax +33 (0) 5 61 93 36 14. 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, 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: Tim Dulin, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2141; fax (425) 227-1149. Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding 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 European Aviation Safety Agency (EASA) Airworthiness Directive 2007-0036R1, dated February 27, 2007; Airbus All Operators Telex A320-71A1042, Revision 01, dated February 12, 2007; and Goodrich All Operators Letter CFM56-074, Revision 1, dated February 1, 2007, for related information. Material Incorporated by Reference (i) You must use Airbus All Operators Telex A320-71A1042, Revision 01, dated February 12, 2007; or Goodrich All Operators Letter CFM56-074, Revision 1, dated February 1, 2007; as applicable; 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 . Issued in Renton, Washington, on March 7, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-4535 Filed 3-14-07; 8:45 am] BILLING CODE 4910-13-P