AD 2007-21-03

Unless already done, do the following actions.

(1) For Model A310 series airplanes, having received Airbus Modification 05911 and/or Airbus Modification 05910, or having received application of Airbus Service Bulletin A310-24-2014 or A310-24-2099 in service; and Model A300-600 series airplanes having received in production Airbus Modification 06213, or having received application of Airbus Service Bulletin A300-24-6008 (Airbus Modification 06214) in service; except airplanes on which Airbus Modification 10510 has been embodied in production or airplanes on which Airbus Service Bulletin A310-24-2056, dated June 8, 1993; Revision 1, dated November 28, 1994; or Revision 02, dated June 9, 2006; or Airbus Service Bulletin A300-24-6045, dated June 8, 1993; Revision 1, dated June 2, 1994; Revision 2, dated August 11, 1994; Revision 3, dated November 28, 1994; Revision 4, dated May 5, 1995; or Revision 05, dated June 9, 2006; has been embodied in service: Within 36 months after the effective date of this AD, modify the emergency power electrical routing under floor at pressure seal interface plates between FR (frame) 52 and FR53, in accordance with the instructions given in Airbus Service Bulletin A310-24-2056, Revision 02, dated June 9, 2006; or A300-24-6045, Revision 05, dated June 9, 2006; as applicable.

(2) For Model A310 series airplanes, manufacturing serial number (MSN) 0162 up to 0706 included, and Model A300-600 series airplanes, MSN 0252 up to 0794 included; except airplanes on which the one-time detailed visual inspection in accordance with Airbus Service Bulletin A310-24-2079, dated March 28, 2000; or Revision 01, dated April 27, 2006; or Airbus Service Bulletin A300-24-6069, dated March 28, 2000; or Revision 01, dated April 27, 2006; has been performed in service: Within 36 months after the effective date of this AD, perform a one-time detailed visual inspection of the electrical routes 1P and 2P between the rear panel 120VU (volt unit) and the circuit breaker panel 800VU located in the forward compartment and in case of finding, before further flight, repair chafed or burned wiring, damaged clamps and introduce self-vulcanizing silicone tape for wrapping the cable bundle of each clamping position, in accordance with the instructions given in Airbus Service Bulletin A310-24-2079, Revision 01, dated April 27, 2006; or Airbus Service Bulletin A300-24-6069, Revision 01, dated April 27, 2006; as applicable.

(3) For Model A310 series airplanes, equipped with Eaton (formerly Vickers) electrical pumps, except airplanes on which Airbus Modification 10017 has been embodied in production or airplanes on which Airbus Service Bulletin A310-29-2036, dated August 10, 1992; Revision 1, dated December 16, 1992; Revision 2, dated September 20, 1993; or Revision 03, dated June 9, 2006; have been embodied in service: Within 36 months after the effective date of this AD, secure the electrical routing 1P, 2P, and the hydraulic line running to pump 11GE, in the hydraulic bay at FR54 by changing the routes and by adding a spacer and a clamp to prevent any chafing between them, in accordance with the instructions given in Airbus Service Bulletin A310-29-2036, Revision 03, dated June 9, 2006.

(4) For Model A310 series airplanes, except airplanes on which Airbus Modification 06447 has been embodied in production or airplanes on which Airbus Service Bulletin A310-36-2010, Revision 2, dated September 26, 1989; or Revision 03, dated May 24, 2006; have been embodied in service: Within 36 months after the effective date of this AD, relocate the temperature sensors and modify the associated wires in accordance with the instructions of Airbus Service Bulletin A310-36-2010, Revision 03, dated May 24, 2006.

(5) Actions done before the effective date of this AD in accordance with any applicable service bulletin in Table 1 of this AD are acceptable for compliance with the corresponding provisions of paragraph (f) of this AD.

Note: This AD differs from the MCAI and/or service information as follows: No differences.