88-06-01 BRITISH AEROSPACE: Amendment 39-5870. Applies to all Model H.S. 748 series airplanes, on which Modification 6175 has been accomplished (post Mod 6175), certificated in any category. Compliance required as indicated, unless previously accomplished.
To detect cracks and prevent collapse of the main landing gear, accomplish the following:
A. Prior to accumulating 25,000 landings or within the next 750 flight hours after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,500 landings, perform an inspection of inboard main pivot bracket assemblies in accordance with paragraph 2A of the British Aerospace H.S. 748 Service Bulletin 57/59, Revision No. 1, dated April 1984. Any assembly found to exhibit corrosion, loose bolts, and/or cracks must be repaired in accordance with paragraph 2D of the above mentioned service bulletin. If corrosion to a depth greater than 0.060-inch is found, repair in accordance with a method approved by the FAA.
B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region.
C. 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.
All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414 Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.
This amendment becomes effective April 18, 1988.