AD 2007-22-05 Airworthiness Directives; Airbus Model A300-600 Series Airplanes

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

This AD applies to Airbus Model A300-600 series airplanes, manufacturing serial numbers (MSN) 0815 up to MSN 0821 inclusive, certificated in any category.

Unless already done, do the following actions. (1) Action No. 1, for the center wing box: (i) At the later of the times in paragraphs (f)(1)(i)(A) and (f)(1)(i)(B) of this AD: Do an external ultrasonic inspection for cracking of the taperlocks fasteners of the center wing box, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. If any crack is detected: Before further flight, contact Airbus for repair instructions, and repair. (A) Before the accumulation of 19,800 total flight cycles or 41,200 total flight hours, whichever occurs first. (B) Within 3 months after the effective date of this AD. (ii) Repeat the inspection thereafter at intervals not to exceed 3,300 flight cycles or 6,900 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. (iii) The repetitive interval specified in paragraph (f)(1)(ii) of this AD is valid until the threshold of Airbus A300-600 Airworthiness Limitation Items (ALI) Task 571006-02-1 is reached. After reaching this threshold, the ultrasonic inspection is to be done according to Task 571006-02-1, “Special detailed inspection (Ultrasonic) of wing junction at rib 1 horizontal flange of lower T section, between FR40 and FR47 inboard side, LH/RH,” of Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. (2) Action No. 2, for the outer wing box: (i) At the later of the times in paragraphs (f)(2)(i)(A) and (f)(2)(i)(B) of this AD: Do an external ultrasonic inspection for cracking of the taperlocks fasteners of the outer wing box, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. If any crack is detected: Before further flight, contact Airbus for repair instructions, and repair. (A) Before the accumulation of 15,200 total flight cycles or 31,700 total flight hours, whichever occurs first. (B) Within 3 months after the effective date of this AD. (ii) Repeat the inspection thereafter at intervals not to exceed 3,700 flight cycles or 7,700 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. (iii) The repetitive interval specified in paragraph (f)(2)(ii) of this AD is valid until reaching the threshold of Airbus A300-600 Airworthiness Limitation Items (ALI) Task 571022-01-2, “Special detailed inspection (Ultrasonic) of wing-fuselage lower skin splice at rib 1 (wing side).” After reaching this threshold, the ultrasonic inspection is to be done according to Task 571022-01-2 of Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. (3) Action No. 3, for the outer wing box: (i) At the later of the times in paragraphs (f)(3)(i)(A) and (f)(3)(i)(B) of this AD: Do an internal x-ray inspection for cracking of the taperlocks fasteners of the outer wing box, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. If any crack is detected: Before further flight, contact Airbus for repair instructions, and repair. (A) Before the accumulation of 20,900 total flight cycles or 43,400 total flight hours, whichever occurs first. (B) Within 3 months after the effective date of this AD. (ii) Repeat the inspection thereafter at intervals not to exceed 1,800 flight cycles or 3,700 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. (iii) The repetitive interval specified in paragraph (f)(3)(ii) of this AD is valid until reaching the threshold of Airbus A300-600 Airworthiness Limitation Items (ALI) Task 571022-02-2, “Special detailed inspection (XRAY) of wing-fuselage lower skin splice at rib 1 (wing side).” After reaching this threshold, the x-ray inspection is to be done according to Task 571022-02-2 of Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. 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, 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 2006-0257, dated August 24, 2006; Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006; and Airbus A300-600 Airworthiness Limitations Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006; for related information. Material Incorporated by Reference (i) You must use the service information specified in Table 1 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 Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of Airbus A300-600 Airworthiness Limitations Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006, on October 31, 2007 (72 FR 54536, September 26, 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. Table 1.—Material Incorporated by Reference Service information Revision level Date Airbus Service Bulletin A300-53-6154, excluding Appendix 01 Original June 20, 2006. Airbus A300-600 Airworthiness Limitations Items Document AI/SE-M2/95A.0502/06 Issue 11 April 2006. Issued in Renton, Washington, on October 12, 2007. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-20815 Filed 10-23-07; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. (1) Action No. 1, for the center wing box: (i) At the later of the times in paragraphs (f)(1)(i)(A) and (f)(1)(i)(B) of this AD: Do an external ultrasonic inspection for cracking of the taperlocks fasteners of the center wing box, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. If any crack is detected: Before further flight, contact Airbus for repair instructions, and repair. (A) Before the accumulation of 19,800 total flight cycles or 41,200 total flight hours, whichever occurs first. (B) Within 3 months after the effective date of this AD. (ii) Repeat the inspection thereafter at intervals not to exceed 3,300 flight cycles or 6,900 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. (iii) The repetitive interval specified in paragraph (f)(1)(ii) of this AD is valid until the threshold of Airbus A300-600 Airworthiness Limitation Items (ALI) Task 571006-02-1 is reached. After reaching this threshold, the ultrasonic inspection is to be done according to Task 571006-02-1, “Special detailed inspection (Ultrasonic) of wing junction at rib 1 horizontal flange of lower T section, between FR40 and FR47 inboard side, LH/RH,” of Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. (2) Action No. 2, for the outer wing box: (i) At the later of the times in paragraphs (f)(2)(i)(A) and (f)(2)(i)(B) of this AD: Do an external ultrasonic inspection for cracking of the taperlocks fasteners of the outer wing box, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. If any crack is detected: Before further flight, contact Airbus for repair instructions, and repair. (A) Before the accumulation of 15,200 total flight cycles or 31,700 total flight hours, whichever occurs first. (B) Within 3 months after the effective date of this AD. (ii) Repeat the inspection thereafter at intervals not to exceed 3,700 flight cycles or 7,700 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. (iii) The repetitive interval specified in paragraph (f)(2)(ii) of this AD is valid until reaching the threshold of Airbus A300-600 Airworthiness Limitation Items (ALI) Task 571022-01-2, “Special detailed inspection (Ultrasonic) of wing-fuselage lower skin splice at rib 1 (wing side).” After reaching this threshold, the ultrasonic inspection is to be done according to Task 571022-01-2 of Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. (3) Action No. 3, for the outer wing box: (i) At the later of the times in paragraphs (f)(3)(i)(A) and (f)(3)(i)(B) of this AD: Do an internal x-ray inspection for cracking of the taperlocks fasteners of the outer wing box, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. If any crack is detected: Before further flight, contact Airbus for repair instructions, and repair. (A) Before the accumulation of 20,900 total flight cycles or 43,400 total flight hours, whichever occurs first. (B) Within 3 months after the effective date of this AD. (ii) Repeat the inspection thereafter at intervals not to exceed 1,800 flight cycles or 3,700 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006. (iii) The repetitive interval specified in paragraph (f)(3)(ii) of this AD is valid until reaching the threshold of Airbus A300-600 Airworthiness Limitation Items (ALI) Task 571022-02-2, “Special detailed inspection (XRAY) of wing-fuselage lower skin splice at rib 1 (wing side).” After reaching this threshold, the x-ray inspection is to be done according to Task 571022-02-2 of Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. 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, 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 2006-0257, dated August 24, 2006; Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006; and Airbus A300-600 Airworthiness Limitations Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006; for related information. Material Incorporated by Reference (i) You must use the service information specified in Table 1 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 Airbus Service Bulletin A300-53-6154, excluding Appendix 01, dated June 20, 2006, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of Airbus A300-600 Airworthiness Limitations Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006, on October 31, 2007 (72 FR 54536, September 26, 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. Table 1.—Material Incorporated by Reference Service information Revision level Date Airbus Service Bulletin A300-53-6154, excluding Appendix 01 Original June 20, 2006. Airbus A300-600 Airworthiness Limitations Items Document AI/SE-M2/95A.0502/06 Issue 11 April 2006. Issued in Renton, Washington, on October 12, 2007. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-20815 Filed 10-23-07; 8:45 am] BILLING CODE 4910-13-P