92-12-01 AIRBUS INDUSTRIE: Amendment 39-8261. Docket No. 91-NM-264-AD. Supersedes AD 88-22-08, Amendment 39-6049.
Applicability: Airbus Industrie Model A300 series airplanes, certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent the installation of incorrectly sized bolts, which could lead to loss of tension in the aft attachment of the flap beams, accomplish the following:
(a) Within 350 landings after December 1, 1988 (the effective date of AD 88-22-08, Amendment 39-6049), perform a detailed visual inspection of flap beam numbers 2, 3, 4, 5, and 6 aft attachment on both wings to detect damage. Repeat this inspection within 700 landings after December 1, 1988. If damaged parts are found, replace in accordance with Airbus Industrie Service Bulletin A300-57-150, Revision 1, dated September 18, 1987, or in accordance with Airbus Industrie Service Bulletin A300-57-145, Revision 3, dated February 10, 1988.(b) For airplanes on which Modification 3553 has not been accomplished: Within 700 landings after December 1, 1988 (the effective date of AD 88-22-08, Amendment 39-6049), replace the bolts on flap beam number 2 with 3/8-inch diameter bolts in accordance with Airbus Industrie Service Bulletin A300-57-145, Revision 3, dated February 10, 1988.
(c) For airplanes on which Modification 3553 has been accomplished: Within 1,000 landings after December 1, 1988 (the effective date of AD 88-22-08, Amendment 39-6049), replace the bolts on flap beam number 2 with 7/16-inch diameter bolts in accordance with Airbus Industrie Service Bulletin A300-57-145, Revision 3, dated February 10, 1988.
(d) For all airplanes: Within 1,000 landings after the effective date of this AD, replace the bolts on flap beam numbers 3, 4, 5, and 6 with 3/8-inch diameter bolts, in accordance with Airbus Service Bulletin A300-57-145, Revision 3, dated February 10, 1988.
(e) Replacement of the flap beam bolts in accordance with Airbus Service Bulletin A300-57-145, Revision 3, dated February 10, 1988, constitutes terminating action for the inspections required by paragraph (a) of this AD.
(f) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113.
NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Standardization Branch, ANM-113.
(g) 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.
(h) The inspectionsand modifications shall be done in accordance with Airbus Industrie Service Bulletin A300-57-150, Revision 1, dated September 18, 1987; or in accordance with Airbus Industrie Service Bulletin A300-57-145, Revision 3, dated February 10, 1988, as applicable. These service bulletins contain the following list of effective pages:
Service Bulletin
Page Number
Revision Level
Date
A300-57-150
1-2, 4-9,
1
September 18, 1987
Revision 1
3, 10-12
Original
July 10, 1987
A300-57-145
1-3, 6-18
3
February 10, 1988
Revision 3
4-5
2
November 13, 1987
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, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, 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., 7th Floor, Suite 700, Washington, DC.
(i) This amendment becomes effective on September 28, 1992.