AD 99-01-18 Airworthiness Directives; Airbus Model A320 Series Airplanes

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

Model A320 series airplanes, having manufacturer's serial numbers 002 through 008 inclusive, 010 through 014 inclusive, 016 through 039 inclusive, 041 through 052 inclusive, 054, 056, and 057; on which Airbus Modification 21905 (reference Airbus Service Bulletin A320-53-1056, Revision 02, dated February 16, 1998) has 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 of the fuselage, 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 6 months after the effective date of this AD, whichever occurs later, perform a visual or eddy current inspection to detect cracking in the upper rivet row of the longitudinal lap joint, in accordance with Airbus Service Bulletin A320-53-1057, Revision 2, dated July 5, 1996. (1) Thereafter, repeat the inspection at one of the following intervals: (i) If the immediately preceding inspection was conducted using visual techniques, conduct the next inspection within 4,000 flight cycles. (ii) If the immediately preceding inspection was conducted using eddy current techniques, conduct the next inspection within 12,000 flight cycles. (2) If any crack is found, prior to further flight, repair in accordance with the service bulletin, except as provided by paragraph (b) of this AD. Accomplishment of a repair in accordance with the service bulletin [[Page 1118]] terminates the repetitive inspection requirements for the area repaired. (b) If any crack is found during any inspection required by paragraph (a) of this AD, and the service bulletin specifies to contact Airbus for appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. (c) Accomplishment of Airbus Modification 21905 in accordance with Airbus Service Bulletin A320-53-1056, Revision 02, dated February 16, 1998, prior to the accumulation of 20,000 total flight cycles constitutes terminating action for the repetitive inspection requirements specified in paragraph (a)(1)(i) and (a)(1)(ii) 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) Except as provided by paragraph (b) of this AD, the inspections and repairs shall be done in accordance with Airbus Service Bulletin A320-53-1057, Revision 2, dated July 5, 1996, which contains the following list of effective pages: ------------------------------------------------------------------------ Revision level shown on Page No. page Date shown on page ------------------------------------------------------------------------ 1, 3-4................. 2...................... July 5, 1996. 2, 8................... 1...................... June 28, 1995. 5-7, 9-17.............. Original............... December 9, 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 97-312-106(B), dated October 22, 1997. (g) This amendment becomes effective on February 12, 1999. Issued in Renton, Washington, on December 30, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-181 Filed 1-7-99; 8:45 am] BILLING CODE 4910-13-U