Airworthiness Directive · Amendment 39-15141 · 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
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
Superseded. A later AD replaced this one: AD 2011-24-05. Comply with the one in force.
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.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as keel beam rupture, which affects the structural integrity of the area. We are issuing this AD to require actions to correct the unsafe condition on these products.
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.
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.
