AD/BELL 430/10 - Tail Rotor Pitch Change Mechanism (Cth)

AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Bell Helicopter Textron Canada (BHTC) 430 Series Helicopters AD/BELL 430/10 Tail Rotor Pitch Change Mechanism 7/2007

Applicability: Bell Helicopter Textron Canada (BHTC) Model 430 helicopters serial numbers 49001 through 49122. Requirement: 1. Verify the existing rigging of the tail rotor pitch change mechanism in accordance with the Accomplishment Instructions detailed in Alert Service Bulletin (ASB) 430-07-39 dated 9 January 2007 or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada.

2. Determine whether the tail rotor yoke is to be replaced in accordance with ASB 430-07-39, item 3 of Accomplishment Instructions. If required, replace the yoke with an airworthy part.

3. Perform a new rigging procedure as per Accomplishment Instructions provided in ASB 430-07-39.

Note: Transport Canada AD CF-2007-04 dated 5 April 2007 refers. Compliance: At the next 150 hour or annual inspection but no later than 31 December 2007, unless already accomplished. This Airworthiness Directive becomes effective on 5 July 2007. Background: It has been determined that the existing rigging procedures for the tail rotor pitch change mechanism have to be changed due to possibility of parts interference.