85-07-09 AIRBUS INDUSTRIE: Amendment 39-5033. Applies to Model A300 B2 and B4 series airplanes, manufacturer serial numbers 003 through 156, certificated in all categories. To prevent rapid decompression of the aircraft, accomplish the following, unless already accomplished. Compliance is required within the time schedules indicated below, or within six months after the effective date of this AD, whichever occurs later:
A. Prior to the threshold limits specified in Table 1 of Airbus Industrie Service Bulletin A300-53-148, Revision 6, dated October 10, 1984, inspect the fuselage longitudinal lap joints and circumferential joints for bonding delamination in accordance with the accomplishment instructions of the service bulletin:
1. If no delamination is detected, repeat these inspections in accordance with the schedule shown in Table 1 of the service bulletin.
2. If delamination is detected in any of the inspections above, perform the actions indicated in Figure 3,Follow-up Action, of the service bulletin.
B. Prior to the threshold limits specified in Figure 1, Inspection Program, of Airbus Industrie Service Bulletin A300-53-178, Revision 4, dated October 10, 1984, visually inspect for corrosion and cracks, and repair if necessary, the bonded longitudinal lap joints and circumferential joints specified in Figure 1 of the service bulletin, in accordance with the accomplishment instructions of the service bulletin. Repeat the inspections in accordance with the schedule shown in Figure 1 of the service bulletin.
C. Prior to the threshold limits specified in Figure 1, Inspection Frequency, of Airbus Industrie Service Bulletin A300-53-149, Revision 6, dated October 10, 1984, inspect for debonding and repair, if necessary, bonded stringers and bonded doublers in the area between frame 1 and frame 18 and between frame 40 and frame 80 on all airplanes up to and including serial number 156, and in the area between frame 18 and frame 40 on all airplanes up to and including serial number 104, in accordance with the accomplishment instructions of the service bulletin.
The inspections of stringers is divided into three areas, as indicated in Figure 2 of the service bulletin with the following options:
(1) Inspection in Area 1 is not required if Modification No. 2904, described in Airbus Industrie Service Bulletin A300-53-146, dated November 28, 1980, has been incorporated.
(2) Preventive riveting of stringers located in Area 2 in accordance with Airbus Industrie Service Bulletin A300-53-197, dated October 10, 1984, allows for an extension of the interval of subsequent repetitive inspections to the interval required for Area 3.
D. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.
E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD.
This amendment becomes effective May 13, 1985.