AD 96-18-06 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 104 inclusive; on which Airbus Modification 21282P01497 (reference Airbus Service Bulletin A320-57-1029) has not been installed; 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 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 prevent fatigue cracking on the pressurized floor fitting at frame 36 under the lower surface panel, which could result in failure of a fitting and subsequent depressurization of the fuselage, accomplish the following: Note 2: Inspections and replacement(s) that were performed prior to the effective date of this AD in accordance with Airbus Service Bulletin A320-57-1028, dated April 12, 1996, are considered acceptable for compliance with this AD. (a) Prior to the accumulation of 16,000 total landings, or within 6 months after the effective date of this AD, whichever occurs later, perform a visual inspection to detect cracks of the 6 fittings of the pressurized floor at frame 36 under the lower surface panel, in accordance with Airbus Service Bulletin A320-57- 1028, Revision 1, dated April 19, 1996. (1) If no cracking is found, prior to further flight, renew the zone protective finish in accordance with the service bulletin. Repeat the visual inspection thereafter at intervals not to exceed 12,000 landings. (2) If only 1 of the 6 fittings is found to be cracked and that crack is less than or equal to 0.59 inch (15 mm) in length, prior to further flight, replace the cracked fitting with a new fitting in accordance with the service bulletin. Thereafter, prior to the accumulation of 500 landings following accomplishment of this replacement, replace the remaining 5 fittings with new fittings in accordance with the service bulletin. (3) If only 1 of the 6 fittings is found to be cracked and that crack is greater than 0.59 inch (15 mm) in length, prior to further flight, replace all six fittings with new fittings in accordance with the service bulletin. (4) If 2 or more fittings are found to be cracked, prior to further flight, replace all 6 fittings with new fittings in accordance with the service bulletin. (b) Replacement of all 6 fittings with new fittings in accordance with Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996, constitutes terminating action for the inspection requirements of this AD. (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, 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 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) The actions shall be done in accordance with Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996, which contains the following list of effective pages: ------------------------------------------------------------------------ Revision level Page number shown on page Date shown on page ------------------------------------------------------------------------ 1-3............................ 1.............. Apr. 19, 1996. 4-15........................... Original....... Aug. 12, 1991. ------------------------------------------------------------------------ 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. (e) This amendment becomes effective on October 10, 1996. Issued in Renton, Washington, on August 23, 1996. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 96-22144 Filed 9-4-96; 8:45 am] BILLING CODE 4910-13-U