Airworthiness Directive · Amendment 39-15527 · Stabilizers
Airbus Model A310 and A300-600 Series Airplanes
This AD applies to AIRBUS Model A310 and A300-600 series airplanes, certificated in any category, all certified models, all serial numbers, on which rudder Part Number (P/N) A55471500 series is fitted, except for those airplanes on which AIRBUS modification number 08827 has been incorporated in production.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Unless already done, do the following actions.
(1) Within 500 flight cycles or 6 months after the effective date of this AD, whichever occurs first, perform a special detailed one-time inspection in the areas of rudder hoisting points and trailing edge screws, in accordance with the instructions given in Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, both dated December 20, 2007, as applicable.
(i) If no damage is found, within 30 days after the inspection or 30 days after the effective date of this AD, whichever occurs later, report to Airbus using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable.
(ii) If any damage is found, within the timescale(s) indicated in Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable, report to Airbus using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable, to get further instructions for repair. Accomplish the repair within the timescale(s) indicated in, and in accordance with, the instructions given in paragraph 3.B.(1)(a) or 3.B.(2)(a), as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as applicable.
(2) Within 500 flight cycles or 6 months after the effective date of this AD, whichever occurs first, perform a special detailed inspection along the rudder Z-profile, in accordance with the instructions given in Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, both dated December 3, 2007, as applicable. For airplanes identified as Configuration 01 in the service bulletins, repeat the inspection thereafter at intervals not to exceed 1,400 flight cycles. For airplanes identified as Configuration 02 in the service bulletins, repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles. For temporary repair along the rudder Z-profile for both airplanes identified as Configurations 01 and 02, refer to paragraph 3.C.(1) of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable.
(i) If no damage is found, within 30 days after the inspection or 30 days after the effective date of this AD, whichever occurs later, report to AIRBUS using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable.
(ii) If any damage is found, verify the findings and apply all applicable corrective actions within the timescale(s) indicated in, and in accordance with instructions given in paragraph 3.B.(1)(a) or 3.B.(2)(a), as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable. Within 30 days after the inspection or corrective action or 30 days after the effective date of this AD, whichever occurs later, submit a report to Airbus using Appendix 1 or 2, as applicable to the airplane configuration, of Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as applicable.
Note 1: For rudder configuration identification, refer to Appendices 3 and 4 of Airbus Service Bulletin A310-55-2044, A310-55-2045, A300-55-6043, and A300-55-6044, as applicable to the airplane model and configuration.
(3) As of 30 days after the effective date of this AD: No person shall install a P/N A55471500 series rudder on any airplane as a replacement, unless it has been inspected and repaired, as applicable, in accordance with the instructions of Airbus Service Bulletins A310-55-2045, Revision 01, dated December 20, 2007, and A310-55-2044, Revision 01, dated December 3, 2007; or Airbus Service Bulletins A300-55-6044, Revision 01, dated December 20, 2007, and A300-55-6043, Revision 01, dated December 3, 2007; as applicable.
(4) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A300-55-6044 or A310-55-2045, both dated July 23, 2007, are considered acceptable for compliance with the corresponding actions specified in paragraph (f)(1) of this AD.
(5) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A300-55-6043 or A310-55-2044, both dated July 23, 2007, are considered acceptable for compliance with the corresponding actions specified in paragraph (f)(2) of this AD.
Note 2: This AD differs from the MCAI and/or service information as follows: No differences.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
