AD 2007-16-02 Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, -243, -301, -321, -322, -323, -341, -342, and -343 Airplanes; and Model A340-200 and -300 Series Airplanes

Models named: A330-201, -202, -203, -223, -243, -301, -321, -322, -323, -341. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD; certificated in any category; except as provided by paragraph (c)(3) of this AD. (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -321, -322, -323, -341, -342, and -343 airplanes, all serial numbers, except those on which Airbus modification 49202 has been embodied in production, or Airbus Service Bulletin A330-57-3090 has been embodied in service. (2) Airbus Model A340-200 and -300 series airplanes, all certified models, all serial numbers, except those on which Airbus modification 49202 has been embodied in production or Airbus Service Bulletin A340-57-4098 has been embodied in service. (3) This AD does not apply to Model A340-200 and -300 series airplanes repaired in accordance with Airbus Repair Drawing R57115053, R57115051, or R57115047 (installation of titanium doubler). These airplanes are covered by European Aviation Safety Agency (EASA) airworthiness directive 2006-0314, dated October 13, 2006. On May 25, 2007, we issued AD 2007-12-08, amendment 39-15086 (72 FR 31171, June 6, 2007), which is the parallel FAA AD to EASA airworthiness directive 2006-0314. Reason (d) The mandatory continuing airworthiness information (MCAI) states that during the A330 and A340 aircraft fatigue test, cracks appeared on the right and left sides between the crossing area of the keel beam fitting and the front spar on the center wing box (CWB). This situation if not corrected can lead in the worst case to keel beam rupture which affects the structural integrity of the area. In order to maintain the structural integrity of the aircraft, the MCAI requires a repetitive special detailed inspection on the horizontal flange of the keel beam in the area of the first fastener hole aft of FR (frame) 40, follow-up actions, and repair if necessary. The MCAI also includes an optional terminating action for the repetitive inspections.

Unless already done, do the following actions. (1) Within the mandatory threshold (flight cycles or flight hours) mentioned in the paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision 02; or A330-57-3081, Revision 02; both dated January 24, 2006, depending on the configuration of the aircraft model; or within 3 months after the effective date of this AD; whichever occurs later: Carry out the NDT (non-destructive test) inspection of the hole(s) of the horizontal flange of the keel beam located on FR 40 datum on RH (right-hand) and/or LH (left-hand) side of the fuselage, in accordance with the instructions of Airbus Service Bulletin A340-57-4089, Revision 02; or A330-57-3081, Revision 02; as applicable. Inspection in accordance with Airbus A330/A340 Technical Disposition F57D03012810, Issue B, dated August 18, 2003; or 582.0651/2002, Issue A, dated October 17, 2002; satisfies the inspection requirements for the first rotating probe inspection which is specified at the inspection threshold of this AD. Note 1: In order to prevent large repairs or heavy maintenance, Airbus recommends to perform the above inspection according to recommended thresholds mentioned in paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision 02; or Airbus Service Bulletin A330-57-3081, Revision 02; both dated January 24, 2006. (2) In case of any crack finding, before further flight, contact Airbus in order to get repair instructions before next flight, and repair before further flight. (3) Should no crack be detected: (i) Before further flight: Follow up the actions indicated in the flow charts, figure 7, 8, or 9, of Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02, dated January 24, 2006; or figure 5, 6, or 7, of Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006; in accordance with the instructions of the applicable service bulletin. (ii) Within 30 days after the effective date of this AD, or within 30 days after doing the inspection required by paragraph (e)(1) of this AD, whichever occurs later: Send the report of actions carried out in paragraph (e)(3)(i) of this AD to Airbus. (iii) Renew the inspection at mandatory intervals given in paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330-57-3081, Revision 02, dated January 24, 2006; as applicable; in accordance with the instructions of Service Bulletin A340-57-4089, Revision 02, or Service Bulletin A330-57-3081, Revision 02; as applicable, and send the inspection results to Airbus. Note 2: In order to prevent large repairs or heavy maintenance, Airbus recommends to perform the above repetitive inspection according to recommended intervals mentioned in paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330-57-3081, Revision 02, dated January 24, 2006. (4) Upon detection of a crack during a repetitive inspection, before further flight, contact Airbus to get repair instructions, and repair before further flight. (5) No additional work is required for aircraft inspected in accordance with the instructions of Airbus Service Bulletin A330-57-3081, dated October 30, 2003, or Revision 01, dated May 18, 2004; or Airbus Service Bulletin A340-57-4089, dated October 30, 2003, or Revision 01, dated March 2, 2004. Nevertheless, the operators must check that their inspection program is in accordance with paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330-57-3081, Revision 02, dated January 24, 2006; as applicable; for the repetitive inspection. (6) For aircraft on which Airbus Modification 41652 is not embodied: When the aircraft has been modified in accordance with Airbus Service Bulletin A330-57-3090, dated March 27, 2006; or Airbus Service Bulletin A340-57-4098, dated March 27, 2006; as applicable; the repetitive inspections required by this AD are cancelled. In case of any crack finding during the modification: Where the applicable service bulletin specifies to contact Airbus, before further flight, contact Airbus to get repair instructions, and repair. FAA AD Differences Note: This AD differs from the MCAI and/or service information as follows. The MCAI did not have a required action if cracks are found during a repetitive inspection. This AD requires contacting Airbus for repair instructions and repairing before further flight. Other FAA AD Provisions (f) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, 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: Tim Backman, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 98057-3356. 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 (g) Refer to MCAI EASA Airworthiness Directive 2006-0315 R1, dated October 26, 2006, and the service information listed in Table 1 of this AD, for related information. Table 1.—Related Service Information Airbus Service Bulletin Revision level Date A330-57-3081 02 January 24, 2006. A330-57-3090 Original March 27, 2006. A340-57-4089 02 January 24, 2006. A340-57-4098 Original March 27, 2006. Material Incorporated by Reference (h) You must use the applicable service information specified in Table 2 of this AD to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the optional terminating modification specified in this AD, you must use the applicable service information specified in Table 3 of this AD. Table 2.—Required Material Incorporated by Reference Airbus Service Bulletin Revision Date A330-57-3081, including Appendix 01 02 January 24, 2006. A340-57-4089, including Appendix 01 02 January 24, 2006. Table 3.—Optional Material Incorporated by Reference Airbus Service Bulletin Date A330-57-3090 March 27, 2006. A340-57-4098 March 27, 2006. (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 July 24, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-14866 Filed 8-8-07; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. (1) Within the mandatory threshold (flight cycles or flight hours) mentioned in the paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision 02; or A330-57-3081, Revision 02; both dated January 24, 2006, depending on the configuration of the aircraft model; or within 3 months after the effective date of this AD; whichever occurs later: Carry out the NDT (non-destructive test) inspection of the hole(s) of the horizontal flange of the keel beam located on FR 40 datum on RH (right-hand) and/or LH (left-hand) side of the fuselage, in accordance with the instructions of Airbus Service Bulletin A340-57-4089, Revision 02; or A330-57-3081, Revision 02; as applicable. Inspection in accordance with Airbus A330/A340 Technical Disposition F57D03012810, Issue B, dated August 18, 2003; or 582.0651/2002, Issue A, dated October 17, 2002; satisfies the inspection requirements for the first rotating probe inspection which is specified at the inspection threshold of this AD. Note 1: In order to prevent large repairs or heavy maintenance, Airbus recommends to perform the above inspection according to recommended thresholds mentioned in paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision 02; or Airbus Service Bulletin A330-57-3081, Revision 02; both dated January 24, 2006. (2) In case of any crack finding, before further flight, contact Airbus in order to get repair instructions before next flight, and repair before further flight. (3) Should no crack be detected: (i) Before further flight: Follow up the actions indicated in the flow charts, figure 7, 8, or 9, of Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02, dated January 24, 2006; or figure 5, 6, or 7, of Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006; in accordance with the instructions of the applicable service bulletin. (ii) Within 30 days after the effective date of this AD, or within 30 days after doing the inspection required by paragraph (e)(1) of this AD, whichever occurs later: Send the report of actions carried out in paragraph (e)(3)(i) of this AD to Airbus. (iii) Renew the inspection at mandatory intervals given in paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330-57-3081, Revision 02, dated January 24, 2006; as applicable; in accordance with the instructions of Service Bulletin A340-57-4089, Revision 02, or Service Bulletin A330-57-3081, Revision 02; as applicable, and send the inspection results to Airbus. Note 2: In order to prevent large repairs or heavy maintenance, Airbus recommends to perform the above repetitive inspection according to recommended intervals mentioned in paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330-57-3081, Revision 02, dated January 24, 2006. (4) Upon detection of a crack during a repetitive inspection, before further flight, contact Airbus to get repair instructions, and repair before further flight. (5) No additional work is required for aircraft inspected in accordance with the instructions of Airbus Service Bulletin A330-57-3081, dated October 30, 2003, or Revision 01, dated May 18, 2004; or Airbus Service Bulletin A340-57-4089, dated October 30, 2003, or Revision 01, dated March 2, 2004. Nevertheless, the operators must check that their inspection program is in accordance with paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330-57-3081, Revision 02, dated January 24, 2006; as applicable; for the repetitive inspection. (6) For aircraft on which Airbus Modification 41652 is not embodied: When the aircraft has been modified in accordance with Airbus Service Bulletin A330-57-3090, dated March 27, 2006; or Airbus Service Bulletin A340-57-4098, dated March 27, 2006; as applicable; the repetitive inspections required by this AD are cancelled. In case of any crack finding during the modification: Where the applicable service bulletin specifies to contact Airbus, before further flight, contact Airbus to get repair instructions, and repair. FAA AD Differences Note: This AD differs from the MCAI and/or service information as follows. The MCAI did not have a required action if cracks are found during a repetitive inspection. This AD requires contacting Airbus for repair instructions and repairing before further flight. Other FAA AD Provisions (f) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, 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: Tim Backman, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 98057-3356. 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 (g) Refer to MCAI EASA Airworthiness Directive 2006-0315 R1, dated October 26, 2006, and the service information listed in Table 1 of this AD, for related information. Table 1.—Related Service Information Airbus Service Bulletin Revision level Date A330-57-3081 02 January 24, 2006. A330-57-3090 Original March 27, 2006. A340-57-4089 02 January 24, 2006. A340-57-4098 Original March 27, 2006. Material Incorporated by Reference (h) You must use the applicable service information specified in Table 2 of this AD to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the optional terminating modification specified in this AD, you must use the applicable service information specified in Table 3 of this AD. Table 2.—Required Material Incorporated by Reference Airbus Service Bulletin Revision Date A330-57-3081, including Appendix 01 02 January 24, 2006. A340-57-4089, including Appendix 01 02 January 24, 2006. Table 3.—Optional Material Incorporated by Reference Airbus Service Bulletin Date A330-57-3090 March 27, 2006. A340-57-4098 March 27, 2006. (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 July 24, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-14866 Filed 8-8-07; 8:45 am] BILLING CODE 4910-13-P