AD 69-08-12

69-08-12 DEHAVILLAND: Amdt. 39-867. Amdt. 39-756 as amended by Amdt. 39-867. Applies to de Havilland DHC-6 type airplanes certificated in all categories except airplanes altered in accordance with de Havilland Service Bulletin 6/181.

To prevent loss of the flight controls compliance is required prior to the next flight and at daily intervals thereafter as follows:

(a) Visually inspect the elevator rudder pulley bracket assembly at F.S. 106 specifically at the forward flange on the top and bottom beams P/Ns C6FS1263-27 and -29 outboard of the outboard lightening hole for cracks or deformation. Replace cracked or deformed parts before further flight.

(b) The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA Maintenance Inspector.

This directive effective April 30, 1969 and was effective upon receipt by all recipients of the telegram dated February 14, 1969, which contained amendment 39-756.

Revised November 15, 1969.