Document ID: chunk:federal_register_of_legislation:F2005L01315:body:0:p2
Version: federal_register_of_legislation:F2005L01315
Segment Type: other
Provision Reference: 
Character Range: 2641–4319

modify the lateral control trim actuator assembly as required by Requirement 1(b) of this Directive.

                   2. For Model 269D, Configuration A, S/N 0044 through 0050 with a suffix of A.

                    Modify the lateral control trim actuator assembly by following the Procedures in Schweizer Service Bulletin DB-012, paragraphs a through i, dated 8 February 2005.

             Note:  FAA AD 2005-10-12 Amdt 39-14089 refers.
Compliance:  For Requirement 1(a) Before further flight after the effective date of this AD.

             For Requirement 1(b) Before further flight after the effective date of this AD.

             For Requirement 1(c) Within the next 25 hours time-in-service (TIS) following the inspection as detailed in Requirement 1(a) of this Directive.

             For Requirement 2 Within the next 50 hours TIS after the effective date of this Directive.
             This Airworthiness Directive becomes effective on 2 June 2005.
Background:  This Directive requires inspecting, modifying, and testing the lateral control trim actuator assembly on certain serial-numbered helicopters following three reported incidents of the inner spring tube separating from the lateral trim control housing resulting in a lateral cyclic control restriction.  The actions specified in this Directive are intended to prevent separation of the inner spring tube from the lateral trim control housing and the associated loss of trim control, increased local resistance to right cyclic stick movement, and an emergency landing or subsequent loss of control of the helicopter.

James Coyne
Delegate of the Civil Aviation Safety Authority

30 May 2005