98-04-49: Inspect Wing/Fuselage Joint Cruciform Fittings

98-04-49 AIRBUS INDUSTRIE: Amendment 39-10360. Docket 97-NM-152-AD. Applicability: Model A320-111, -211, -212, -214, -231, -232, and -233 series airplanes, all serial numbers, 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 (b) 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, unlessaccomplished previously. To detect and correct fatigue cracks on the wing/fuselage joint cruciform fittings, which could result in reduced structural integrity of the wing/fuselage, accomplish the following: (a) Prior to the accumulation of 28,000 total landings, or within 60 days after the effective date of this AD, whichever occurs later, perform an ultrasonic inspection to detect fatigue cracking in the wing/fuselage joint cruciform fittings, in accordance with Airbus Service Bulletin A320-57-1051, Revision 01, dated March 21, 1996. (1) If no cracking is detected, repeat the inspection thereafter at intervals not to exceed 20,000 landings. (2) If any crack is detected, prior to further flight, repair it in accordance with the service bulletin. Thereafter, repeat the inspection at the times specified in paragraph (a)(2)(i) or (a)(2)(ii) of this AD, as applicable. (i) If the crack that was detected and repaired was greater than 2.5 mm: Repeat the inspection priorto the accumulation of 32,000 landings since accomplishment of the repair; and thereafter at intervals not to exceed 32,000 landings. (ii) If the crack that was detected and repaired was less than or equal to 2.5 mm: Repeat the inspection prior to the accumulation of 28,000 landings since accomplishment of the repair; and thereafter at intervals not to exceed 20,000 landings. (b) 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 request 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. (c) 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. (d) The actions shall be done in accordance with Airbus Service Bulletin A320-57- 1051, Revision 01, dated March 21, 1996, which contains the specified effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1-29, 31-37, 39-40 1 March 21, 1996 30, 38 Original March 30, 1993 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 96-299- 094(B), dated December 18, 1996. (e) This amendment becomes effective on April 3, 1998.