AD 98-09-20 Airworthiness Directives; Airbus Model A310 Series Airplanes

Models named: A310 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A310 series airplanes on which Airbus Modifications 8888 and 8889 have not been accomplished; certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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.

Required as indicated, unless accomplished previously. To detect and correct fatigue cracking and corrosion around and under chafing plates of the wing root between fuselage frame (FR) 36 and FR 39, which could result in reduced structural integrity of the airplane, accomplish the following: (a) Except as provided by paragraph (b) of this AD: Within 4 years since date of manufacture, or within 12 months after the effective date of this AD, whichever occurs later, perform an inspection to detect discrepancies around and under the chafing plates of the wing root, in accordance with paragraph B. of the Accomplishment Instructions of Airbus Service Bulletin A310-53-2069, Revision 1, dated September 19, 1995. If any discrepancy is found, prior to further flight, accomplish follow-on corrective actions (i.e., removal of corrosion, corrosion protection, high frequency eddy current inspection, x-ray inspection), as applicable, in accordance with the service bulletin. Repeat the inspections, as applicable, thereafter, at intervals specified in the service bulletin. (b) If any discrepancy is found as a result of an inspection required by paragraph (a) of this AD, and Airbus Service Bulletin A310-53-2069, Revision 1, dated September 19, 1995, specifies to contact Airbus for an appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Where differences in the compliance times or corrective actions exist between the service bulletin and this AD, the AD prevails. (c) Accomplishment of the replacement of the chafing plates in accordance with Airbus Service Bulletin A310-53-2070, dated October 3, 1994, constitutes terminating action for the repetitive inspection requirement 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. 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 2: 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 Airbus Service Bulletin A310-53-2069, Revision 1, dated September 19, 1995 and Airbus Service Bulletin A310-53-2070, dated October 3, 1994. 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 3: The subject of this AD is addressed in French airworthiness directive 96-008-175(B), dated January 3, 1996. (g) This amendment becomes effective on June 3, 1998. Issued in Renton, Washington, on April 21, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-11070 Filed 4-28-98; 8:45 am] BILLING CODE 4910-13-U