AD 98-12-18 Airworthiness Directives; Airbus Model A320-111, -211, and -231 Series Airplanes

Models named: A320-111, -211, -231 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A320-111, -211, and -231 series airplanes, manufacturer's serial numbers 002 through 008 inclusive, 010 through 014 inclusive, 016 through 078 inclusive, and 080 through 107 inclusive; 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.

Required as indicated, unless accomplished previously. To detect and correct reduced structural integrity of the wing- fuselage support and fuselage pressure vessel resulting from structural fatigue cracking in the transition and pick-up angles, accomplish the following: (a) Prior to the accumulation of 16,000 total landings, or within 6 months after the effective date of this AD, whichever occurs later, accomplish paragraphs (a)(1) and (a)(2) of this AD, in accordance with Airbus Service Bulletin A320-53-1028, dated March 1, 1994. (1) Perform a visual inspection to detect cracks of the transition angle, in accordance with the service bulletin. (i) If no crack is detected during the visual inspection required by paragraph (a)(1) of this AD, accomplish either paragraph (a)(1)(i)(A) or paragraph (a)(1)(i)(B) of this AD. (A) Repeat the visual inspection thereafter at intervals not to exceed 12,000 landings. Or (B) Prior to further flight, modify the center fuselage in accordance with Airbus Service Bulletin A320-53-1027, Revision 2, dated June 8, 1995. Accomplishment of the modification constitutes terminating action for the repetitive inspection requirements of paragraph (a)(1)(i)(A) of this AD. (ii) If any crack is detected during the visual inspection required by paragraph (a)(1) of this AD, prior to further flight, replace the transition angle with a new transition angle, in accordance with Airbus Service Bulletin A320-53-1027, Revision 2, dated June 8, 1995. (2) Perform a rotating probe inspection to detect cracks of the pick-up angle, in accordance with the service bulletin. (i) If no crack is detected during the rotating probe inspection required by paragraph (a)(2) of this AD, accomplish either paragraph (a)(2)(i)(A) or (a)(2)(i)(B) of this AD. (A) Repeat the rotating probe inspection thereafter at intervals not to exceed 12,000 landings. Or (B) Prior to further flight, modify the center fuselage in accordance with Airbus Service Bulletin A320-53-1027, Revision 2, dated June 8, 1995. Accomplishment of the modification constitutes terminating action for the repetitive inspection requirements of paragraph (a)(2)(i)(A) of this AD. (ii) If any crack is detected and it is less than 1.9 mm in length, prior to further flight, accomplish the applicable corrective actions specified in the service bulletin. For holes that have not been modified in accordance with the service bulletin, repeat the rotating probe inspection thereafter at intervals not to exceed 12,000 landings. (iii) If any crack is detected and it is 1.9 mm or greater in length, prior to further flight, repair it in accordance with the method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Note 2: Accomplishment of the modification or replacement required by paragraph (a) of this AD in accordance with Airbus Service Bulletin A320-53-1027, dated March 1, 1994, or Revision 1, dated September 5, 1994, prior to the effective date of this AD, is acceptable for compliance with this paragraph. (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. 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 3: 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 inspections shall be done in accordance with Airbus Service Bulletin A320-53-1028, dated March 1, 1994. The modification and replacement shall be done in accordance with Airbus Service Bulletin A320-53-1027, Revision 2, dated June 8, 1995. Airbus Service Bulletin A320-53-1027, Revision 2, dated June 8, 1995, contains the following list of effective pages: ------------------------------------------------------------------------ Revision Page No. level shown Date shown on page on page ------------------------------------------------------------------------ 1-6, 8, 10-16, 19............. 2............ June 8, 1995. 7, 17, 18, 20................. Original..... March 1, 1994. 9............................. 1............ September 5, 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 4: The subject of this AD is addressed in French airworthiness directive 95-097-065(B), dated May 24, 1995. (e) This amendment becomes effective on July 14, 1998. Issued in Renton, Washington, on June 2, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-15134 Filed 6-8-98; 8:45 am] BILLING CODE 4910-13-P