AD 98-20-30 Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped With a Bulk Cargo Door

Models named: A320 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A320 series airplanes, equipped with a bulk cargo door (Airbus Modification 20029), 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 (c) 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 prevent fatigue cracking of the upper frame flanges, which could result in reduced structural integrity of the airplane, accomplish the following: (a) Prior to the accumulation of 20,000 total flight cycles, or within 1,200 flight cycles after the effective date of this AD, whichever occurs later: Perform a high frequency eddy current inspection to detect fatigue cracking of the upper frame flanges, in accordance with Airbus Service Bulletin A320-53-1022, Revision 1, dated June 18, 1992. (1) If no cracking is detected, accomplish either paragraph (a)(1)(i) or (a)(1)(ii) of this AD. (i) Repeat the eddy current inspection thereafter at intervals not to exceed 1,200 flight cycles until accomplishment of the requirements of paragraph (b) of this AD. Or (ii) Prior to further flight, modify the upper frame flanges, in accordance with Airbus Service Bulletin A320-53-1021, Revision 1, dated April 13, 1992. This modification constitutes terminating action for the requirements of this AD. (2) If any cracking is detected, prior to further flight, repair in accordance with Airbus Service Bulletin A320-53-1021, Revision 1, dated April 13, 1992. Accomplishment of the repair constitutes terminating action for the requirements of this AD. (b) Prior to the accumulation of 26,000 total flight cycles, or within 6,000 flight cycles after the effective date of this AD, whichever occurs later: Perform a high frequency eddy current inspection to detect fatigue cracking of the upper frame flanges, in accordance with Airbus Service Bulletin A320-53-1021, Revision 1, dated April 13, 1992. (1) If no cracking is detected, prior to further flight, modify the upper frame flanges, in accordance with the service bulletin. Accomplishment of this modification constitutes terminating action for the requirements of this AD. (2) If any cracking is detected, prior to further flight, repair in accordance with the service bulletin. Accomplishment of the repair constitutes terminating action for the requirements of this AD. (c) 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 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. (d) Special flight permits may be issued in accordance with Secs. 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. (e) The inspections, repairs, and modification shall be done in accordance with the following Airbus service bulletins, which contain the specified effective pages: [[Page 51281]] ---------------------------------------------------------------------------------------------------------------- Service bulletin referenced Page number shown Revision level shown on and date on page page Date shown on page ---------------------------------------------------------------------------------------------------------------- A320-53-1022,................ 1-6 1.......................... June 18, 1992. Revision 1,.................. ......................... ................................. June 18, 1992................ 7, 8 Original................... October 17, 1991. A320-53-1021,................ 1, 4-24 1.......................... April 13, 1992 Revision 1,.................. ......................... April 13, 1992............... 2, 3 Original................... October 17, 1991 ---------------------------------------------------------------------------------------------------------------- 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 96-238-091(B), dated October 23, 1996. (f) This amendment becomes effective on October 30, 1998. Issued in Renton, Washington, on September 17, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-25473 Filed 9-24-98; 8:45 am] BILLING CODE 4910-13-P