AD 2007-03-10 Airworthiness Directives; Airbus Model A300 Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and A310 Airplanes

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

This AD applies to all Airbus Model A300 airplanes; A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, A300 F4-605R, F4-622R, and C4-605R Variant F airplanes; and A310 airplanes; certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Action 3—Modify the Retaining and Protection System (f) For all airplanes identified in paragraphs (f)(1) and (f)(2) of this AD: Within 26 months after the effective date of this AD, modify the retaining and protection system for the electrical bundles located at the wing-to-fuselage junction, under the flap control screw jack. (1) For Model A300 airplanes: Do the actions specified in paragraph (f) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-24-0085, Revision 06, dated October 13, 2005. (2) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, A300 F4-605R, F4-622R, and C4-605R Variant F airplanes, except those on which Airbus Modification 10505 has been done: Do the actions specified in paragraph (f) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-24-6043, Revision 07, dated October 11, 2006. Action 4—Modify the Electrical Wiring of Routes 1P and 2P (g) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, A300 F4-605R, F4-622R, and C4-605R Variant F airplanes; except those on which Airbus Modification 11741 has been done: Within 26 months after the effective date of this AD, modify the electrical wiring of routes 1P and 2P (along the top panel of the shroud box and the rear spars of the wings) by extending the protective conduits up to the next support, and replace the two existing clamps on this support with new, improved clamps. Do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-28-6056, Revision 01, dated January 20, 2006. Action 5—Inspect the Wire Looms (h) For all airplanes identified in paragraphs (h)(1) and (h)(2) of this AD: Within 26 months after the effective date of this AD, do a general visual inspection of the wire looms on the wing trailing edge for improperly held wires in the clamps, restore the electrical bundles to good condition, and replace the affected nylon clamps with metallic clamps that have an elastomer lining. Do all applicable corrective action before further flight. Repeat the inspection thereafter at intervals not to exceed 26 months until all clamps have been replaced. (1) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, A300 F4-605R, F4-622R, and C4-605R Variant F airplanes; except those on which Airbus Modification 6478 has been done: Do the actions specified in paragraph (h) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-24-6004, Revision 04, dated November 15, 2005. (2) For Model A310 airplanes, except those on which Airbus Modification 6478 has been done: Do the actions specified in paragraph (h) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-24-2009, Revision 04, dated November 15, 2005. Action 6—Improve the Quality of the Electrical Routes (i) For all airplanes identified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD: Within 26 months after the effective date of this AD, replace the nylon clamps of the electrical routes in the hydraulic compartment and in the shroud box with new metallic clamps that have white silicone lining (for airplanes identified in paragraph (i)(1) of this AD); and/or replace the nylon clamps and change the location of routes 1P and 2P to improve the retention of the wiring loom (for airplanes identified in paragraphs (i)(2) and (i)(3) of this AD); as applicable. (1) For Model A300 airplanes; except those on which Airbus Modification 11763 has been done: Do the actions specified in paragraph (i) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-24-0100, dated April 7, 2005. (2) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, A300 F4-605R, F4-622R, and C4-605R Variant F airplanes; except those on which Airbus Modifications 11763 and 12995 have been done: Do the actions specified in paragraph (i) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-24-6084, Revision 01, dated June 28, 2005. (3) For Model A310 airplanes, except those on which Airbus Modification 11763 has been done: Do the actions specified in paragraph (i) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-24-2091, dated March 4, 2005. Parts Installation (j) After the effective date of this AD, no person may install on any airplane plate assemblies with part numbers A5351088000000 or A5351088000100 unless they have been modified in accordance with paragraph (f) of this AD. Actions Accomplished According to Previous Revisions of Service Bulletins (k) Actions done before the effective date of this AD in accordance with the service bulletins identified in Table 1 of this AD are acceptable for compliance with the corresponding requirements in this AD. Table 1.—Previous Revisions of Service Bulletins Airbus Service Bulletin Revision level Date A300-24-0085 Original December 12, 1994. A300-24-0085 03 January 17, 1996. A300-24-0085 04 July 23, 1996. A300-24-0085 05 March 6, 2001. A300-24-6004 1 January 28, 1988. A300-24-6004 2 February 24, 1995. A300-24-6004 03 June 30, 1998. A300-24-6043 Original December 12, 1994. A300-24-6043 01 February 7, 1995. A300-24-6043 02 May 10, 1995. A300-24-6043 03 January 17, 1996. A300-24-6043 04 March 6, 2001. A300-24-6043 05 August 30, 2001. A300-24-6043 06 October 13, 2005. A300-24-6084 Original March 4, 2005. A300-28-6056 Original February 18, 1998. A310-24-2009 Original May 31, 1985. A310-24-2009 1 January 28, 1988. A310-24-2009 2 February 24, 1995. A310-24-2009 03 June 30, 1998. Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (m) European Aviation Safety Agency airworthiness directive 2006-0074, dated April 3, 2006, also addresses the subject of this AD. Material Incorporated by Reference (n) You must use the service information specified in Table 2 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov ; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . Table 2.—Material Incorporated by Reference Airbus Service Bulletin Revision level Date A300-24-0085 06 October 13, 2005. A300-24-0100 Original April 7, 2005. A300-24-6004 04 November 15, 2005. A300-24-6043 07 October 11, 2006. A300-24-6084 01 June 28, 2005. A300-28-6056 01 January 20, 2006. A310-24-2009 04 November 15, 2005. A310-24-2091 Original March 4, 2005. Issued in Renton, Washington, on January 24, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-1602 Filed 2-2-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.