81-14-03 R1 BRITISH AEROSPACE: Amendment 39-4151 as amended by Amendment 39- 4241. Applies to British Aerospace (formerly Armstrong Whitworth) Model AW-650 series 100 and series 200 aircraft, serial numbers 6651, 6652, 6653, 6654, 6656, 6660, 6801, 6802, 6083, and 6805, certified in all categories. Compliance required as indicated.
To prevent possible loss of the vertical fin, accomplish the following: Within the next ten days after the effective date of this AD, unless previously accomplished, visually inspect the tail boom frame 28 on the left and right booms for cracks in accordance with paragraph 2C(1) of British Aerospace Service Bulletin Number 55/39 dated June 1981 or in a manner approved by the Chief, Seattle Area Aircraft Certification Office, FAA, Northwest Mountain Region.
A. If no cracks are found, reinspect at intervals not to exceed 75 flight hours after the initial inspection by visual and eddy current methods in accordance with paragraphs 2C(1) and 2C(2)of British Aerospace Service Bulletin Number 55/39 dated June 1981 or in a manner approved by the Chief, Seattle Area Aircraft Certification Office, FAA, Northwest Mountain Region.
B. Within 150 flight hours from the time of the initial visual inspection and thereafter at intervals not to exceed 150 flight hours, X-ray inspect in accordance with paragraph 2C(3) of British Aerospace Service Bulletin Number 55/39 dated June 1981 or in a manner approved by the Chief, Seattle Area Aircraft Certification Office, FAA, Northwest Mountain Region.
C. If cracks are found, evaluate the damage in accordance with paragraph 2E of British Aerospace Service Bulletin Number 55/39 dated June 1981. If the airplane can continue to fly, reinspect in accordance with the inspection intervals contained in paragraph A and B of this ZD. If the cracks are such that the airplane cannot continue to fly after evaluation of the damage in accordance with paragraph 2E of the service bulletin, the modification as described in paragraph 2F of the service bulletin must be made prior to further flight.
D. Prior to the accumulation of 600 flight hours after the initial visual inspection or within 50 flight hours after the effective date of this Amendment, whichever comes later, the modification described in paragraph 2F of British Aerospace Service Bulletin 55/39 dated June 1981 must be accomplished. Upon the accomplishment of the modification, no further AD inspections are required.
E. Airplanes may be flown in accordance with FAR 21.197 and 21.199 to a maintenance base for accomplishment of the inspection required by this AD.
F. Alternate methods of compliance may be used which provide an equivalent level of safety when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region.
The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the addresses listed above. These documents may also be examined at FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108.
Amendment 39-4151 became effective July 8, 1981.
This amendment 39-4241 becomes effective November 12, 1981.