AD 96-12-02 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes, Excluding Model A300-600 Series Airplanes

Models named: A300 B2, B4 series, A300-600 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A300 B2 and B4 series airplanes, manufacturer serial numbers 003 through 156 inclusive; on which Airbus Modification 2611 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 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 [[Page 28498]] been eliminated, the request should include specific proposed actions to address it. Note 2: Model A300-600 series airplanes are not subject to the requirements of this AD.

Required as indicated, unless accomplished previously. To prevent stress corrosion cracking in the longitudinal lap joints of the fuselage, which could result in rapid depressurization of the airplane, accomplish the following: Note 3: Any of the inspections and measurements required by this AD that were performed before the effective date of this AD in accordance with Airbus All Operator Telex (AOT) 53-05 (original issue), dated August 16, 1995, are considered acceptable for compliance with the applicable requirements of this AD. (a) Within 60 days after the effective date of this AD, accomplish paragraphs (a)(1) and (a)(2) of this AD in accordance with Airbus All Operator Telex (AOT) 53-05, Revision 1, dated August 16, 1993. (1) Measure the thickness of the inner skin of the longitudinal lap joint from the inside of the fuselage at stringer 57 between frames 65 and 72 using the ultrasonic thickness measurement method, in accordance with the AOT. If the thickness is less than or equal to the limits specified in the AOT, prior to further flight, repair the longitudinal lap joint in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (2) Perform a high frequency eddy current (HFEC) inspection to detect cracking of the longitudinal lap joint at stringer 57 between frames 65 and 72, in accordance with the AOT. If any cracking is detected, prior to further flight, repair the longitudinal lap joint in accordance with a method approved by the Manager, Standardization Branch, ANM-113. (b) Within 6 months after the effective date of this AD, accomplish paragraphs (b)(1) and (b)(2) of this AD in accordance with Airbus AOT 53-05, Revision 1, dated August 16, 1993. (1) Measure the thickness of the inner skin of the longitudinal lap joint from the inside of the fuselage at stringer 52 (left-and right-hand) between frames 58 and 65 using the ultrasonic thickness measurement method, in accordance with the AOT. If the thickness is less than or equal to the limits specified in the AOT, prior to further flight, repair the longitudinal lap joint in accordance with a method approved by the Manager, Standardization Branch, ANM-113. (2) Perform a HFEC inspection to detect cracking of the longitudinal lap joint at stringer 52 (left- and right-hand) between frames 58 and 65, in accordance with the AOT. If any cracking is detected, prior to further flight, repair the longitudinal lap joint in accordance with a method approved by the Manager, Standardization Branch, ANM-113. (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. 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 4: 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) 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) The measurements and inspections shall be done in accordance with Airbus All Operator Telex (AOT) 53-05, Revision 1, dated August 16, 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. (f) This amendment becomes effective on July 10, 1996. Issued in Renton, Washington, on May 28, 1996. Bill R. Boxwell, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 96-13798 Filed 6-4-96; 8:45 am] BILLING CODE 4910-13-P