93-14-04 AIRBUS INDUSTRIE: Amendment 39-8628. Docket 92-NM-216-AD.
Applicability: Model A320 series airplanes; manufacturer's serial numbers 002 through 008, inclusive, 010 through 078, inclusive, and 080 through 107, inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced structural integrity of the fuselage, accomplish the following:
(a) Prior to the accumulation of 12,000 total landings, or 6 months after the effective date of this AD, whichever occurs later, accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD, in accordance with Airbus Industrie Service Bulletin A320-53-1024, dated September 23, 1992:
(1) Conduct an eddy current inspection to detect cracking around the fastener bolt holes at the inboard flange of the floor beam, in the side box-beams, at the two sides of the pressure floor, and at the vertical integral stiffener between frame 42 and frame 43; and
(2) Conduct a detailed visual inspection to detect cracking of the fillet radius of the top outboard flange and the flange corner-radius of the slanted inboard flange of the side box-beam between frame 42 and frame 43.
(b) If no crack is detected during either inspection required by paragraph (a) of this AD, repeat the inspections at intervals not to exceed 6,000 landings.
(c) If a crack is detected during the inspections required by paragraph (a) or (b) of this AD, prior to further flight, repair the crack in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(d) Prior to the accumulation of 18,000 total landings, accomplish Modification 21202, in accordance with Airbus Industrie Service Bulletin A320-53-1023, dated September 23, 1992, as amended by Service Bulletin Change Notice 0A, dated January 20, 1993; or Revision 1, dated March 23, 1993. Accomplishment of this modification constitutes terminating action for the inspection requirements of this AD.
(e) 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113.
NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.
(f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(g) The inspections shall be done in accordance with Airbus Industrie Service Bulletin A320-53-1024, dated September 23, 1992. The modification shall be done in accordance with Airbus Industrie Service Bulletin A320-53-1023, dated September 23, 1992, which includes Appendix 1, dated September 23, 1992; Service Bulletin Change Notice 0A, dated January 20, 1993, for Airbus Industrie Service Bulletin A320-53-1023, dated September 23, 1992; or Airbus Industrie Service Bulletin A320-53-1023, Revision 1, dated March 23, 1993, which includes Appendix 1, dated September 23, 1992. 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.
(h) This amendment becomes effective on August 23, 1993.