Document ID: chunk:federal_register_of_legislation:F2008L04555:body:0:p2
Version: federal_register_of_legislation:F2008L04555
Segment Type: other
Provision Reference: 
Character Range: 2804–4047

velocities visually inspect the remainder of the elevator control circuit for damage in accordance with de Havilland SB No.3/35 Revision A, or later Transport Canada approved revision.

                Note:  Transport Canada AD CF-85-04 refers.

Compliance:     1. Unless already accomplished, within 50 flight hours after 15 January 2009.

                2. Unless already accomplished, within 100 flight hours after 15 January 2009.

                3. As specified in Requirement 3.
             This Amendment becomes effective on 15 January 2009.
Background:  In-service damage has occurred to the elevator pushrod and attachment bolt to the elevator quadrant in the stub fin.  The damage usually takes the form of bowing of the pushrod and bending of the attachment bolt, caused by high external loads applied to the elevator due to strong gust loading while the aircraft is parked.  Similar problems could develop with the rudder pushrod to rear quadrant attachment bolt.

             Amendment 1 is issued to introduce the requirements of Transport Canada AD
             CF-85-04, which supersedes the original requirements of this Directive.

David Villiers
Delegate of the Civil Aviation Safety Authority

27 November 2008