AD 2000-11-23

Applicability: All Model A300, A310, and A300-600 series airplanes, certificated in any category.

Note 1:

This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent electrical arcing/discharge in the fuel tank due to damaged electrical bonding leads or inadequate electrical bonding of the fuel pipe couplings, which could result in fuel ignition and consequent uncontained rupture of the fuel tank, accomplish the following:

(a) Within 36 months after the effective date of this AD, perform a one-time inspection to detect damage (i.e., breakage, fraying, abrasion damage, looseness of the outer metal braid protection in the end crimp, looseness of the outer metal braid protection on the bonding lead inner core, corrosion, or missing leads) of the electrical bonding leads in specified locations of the fuel tanks, in accordance with the Accomplishment Instructions of Airbus Service Bulletins A300-28-0072, Revision 01, dated October 01, 1998, including Appendix 1, dated October 01, 1998, and Appendix 2, dated February 20, 1998 (for Model A300 series airplanes); A310-28-2128, Revision 01, dated October 01, 1998, including Appendix 1, dated October 01, 1998, and Appendix 2, dated February 20, 1998 (for Model A310 series airplanes); or A300-28-6057, Revision 01, dated October 01, 1998, including Appendix 1, dated October 01, 1998, and Appendix 2, dated February 20, 1998 (for Model A300-600 series airplanes); as applicable.

Note 2:

Inspection of the area specified in paragraph (a) of this AD accomplished prior to the effective date of this AD in accordance with Airbus Service Bulletins A300-28-0072, A310-28-2128, or A300-28-6057; all dated February 20, 1998; as applicable; is considered acceptable for compliance with the requirements of paragraph (a) of this AD.

(b) If any electrical bonding lead is damaged, prior to further flight, replace the bonding lead with a serviceable bonding lead in accordance with the applicable service bulletin specified in paragraph (a) of this AD.

(c) For airplanes on which Airbus Industrie Modification 11847 (for Model A310 series airplanes) or 11848 (for Model A300/A300-600 series airplanes) has not been accomplished, within 36 months after the effective date of this AD, modify the fuel pipe couplings in the specified locations of the fuel tank in accordance with the Accomplishment Instructions of Airbus Service Bulletins A300-28-0073, Revision 01, dated October 01, 1998 (for Model A300 series airplanes); A310-28-2130, Revision 01, dated October 01, 1998 (for Model A310 series airplanes); or A300-28-6058, Revision 01, dated October 01, 1998 (for Model A300-600 series airplanes); as applicable.

Note 3:

Modification of the fuel pipe couplings accomplished prior to the effective date of this AD in accordance with Airbus Service Bulletins A300-28-0073, A310-28-2130, or A300-28-6058; all dated February 20, 1998; as applicable; is considered acceptable for compliance with the requirements of paragraph (c) of this AD.

(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.

Note 4:

Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

(f) The actions shall be done in accordance with the following Airbus service bulletins, as applicable:

This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Note 5:

The subject of this AD is addressed in French airworthiness directive 98-174-248(B), dated April 22, 1998.

(g) This amendment becomes effective on July 18, 2000.