98-25-05: Inner Rear Spar Of Wings

98-25-05 AIRBUS INDUSTRIE: Amendment 39-10928. Docket 98-NM-264-AD. Applicability: Model A321-111, -112, and -131 series airplanes; except those on which Airbus Modification 24977 has been accomplished during production, or on which the action described in Airbus Service Bulletin A320-57-1100, dated July 28, 1997 (Airbus Modification 26010) has 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 (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafecondition 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 detect and correct fatigue cracking on the inner rear spar of the wings, 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 120 days after the effective date of this AD, whichever occurs later, perform an ultrasonic inspection to detect fatigue cracking in the area surrounding certain attachment holes of the forward pintle fittings of the main landing gear (MLG) and the actuating cylinder anchorage fittings on the inner rear spar, in accordance with Airbus Service Bulletin A320-57-1101, dated July 24, 1997. (1) If no cracking is detected, prior to further flight, repair the sealant in the inspected areas and repeat the ultrasonic inspections thereafter at intervals not to exceed 7,700 flight cycles. (2) If any cracking is detected, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction G n rale de l'Aviation Civile (DGAC) (or its delegated agent). (b) Accomplishment of visual and eddy current inspections to detect cracking in the area surrounding certain attachment holes of the forward pintle fittings of the MLG and the actuating cylinder anchorage fittings on the inner rear spar; follow-on corrective actions, as applicable; and rework of the attachment holes; in accordance with Airbus Service Bulletin A320-57-1100, dated July 28, 1997, constitutes terminating action for the repetitive inspection requirements of this AD. If any cracking is detected during accomplishment of any inspection described in the service bulletin, and the service bulletin specifies to contact Airbus for appropriateaction: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, or the DGAC (or its delegated agent). (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. 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 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. (e) Except as provided by paragraphs (a)(2) and (b) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A320-57-1101, dated July 24, 1997. 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 98-212-116(B), dated June 3, 1998. (f) This amendment becomes effective on December 18, 1998.