Document ID: chunk:federal_register_of_legislation:F2007L04015:body:0
Version: federal_register_of_legislation:F2007L04015
Segment Type: other
Provision Reference: 
Character Range: 0–2137

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) 222 Series Helicopters
AD/BELL 222/42  Tail Rotor Pitch Change Mechanism  11/2007

Applicability:  Bell Helicopter Textron Canada (BHTC) Model 230 helicopters.
Requirement:       1. Verify the existing rigging of the tail rotor pitch change mechanism in accordance with Accomplishment Instructions provided in Alert Service Bulletin (ASB) 230-07-36 dated 9 January 2007 or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada.

                   2. Verify if the tail rotor yoke needs to be replaced as per Item 3 of Accomplishment Instructions provided in above ASB.  If required, replace the yoke with airworthy part.

                   3. Perform a new rigging procedure as per Accomplishment Instructions provided in above ASB.

                Note:  Transport Canada AD CF-2007-12 dated 17 September 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 25 October 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.  This AD mandates verification of the tail rotor pitch change mechanism, and new rigging procedures.

Charles Lenarcic
Delegate of the Civil Aviation Safety Authority

14 September 2007