86-05-03 DeHAVILLAND AIRCRAFT OF CANADA, LTD.: Amendment 39-5247. Applies to Model DHC-8-101 airplanes, serial numbers 1 through 24, certificated in any category. To assure structural integrity of the elevator and spring tab, accomplish the following within the next 200 flight hours or 30 days after the effective date of this AD, whichever comes first, unless already accomplished:
A. For airplanes, serial numbers 1 through 14, accomplish Modification No. 8/0478 to the elevator mass balance weights as described in deHavilland Aircraft of Canada, Ltd., Service Bulletin No. A8-55-4, dated January 15, 1986.
B. For airplanes, serial numbers 15 through 24, the limitation imposed by telegraphic AD T85-26-52, issued January 3, 1986, may be removed from the Airplane Flight Manual when Modification No. 8/0468 to the spring tab and elevator mass balance weights, as described in deHavilland Aircraft of Canada, Ltd., Service Bulletin No. A8-55-3, dated January 3, 1986, has been incorporated.
C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region.
D. 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 deHavilland Aircraft of Canada, Ltd., Garrett Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.
This supersedes telegraphic AD T85-26-52, dated January 3, 1986.
This amendment becomes effective March 24, 1986.