AD/BELL 222/37 - 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) 222 Series Helicopters AD/BELL 222/37 Tail Rotor Pitch Change Mechanism 8/2007

Applicability: Bell Helicopter Textron Canada (BHTC) Models: 222, serial number 47006 through 47089; 222B, serial number 47131 through 47156; 222U, All. Requirement: 1. Verify the existing rigging of the tail rotor pitch change mechanism in accordance with the Accomplishment Instructions provided in the applicable Alert Service Bulletin (ASB) listed below, or later NAA approved revisions. Helicopter Model Applicable Alert Service Bulletin 222 and 222B 222-07-104 issued 9 January2007 222U 222U-07-75 issued 9 January2007

2. Verify if the tail rotor yoke replacement is required, as per Item 3 of Accomplishment Instructions of applicable ASB. If required; replace the yoke with airworthy part.

3. Perform a new rigging procedure as per Accomplishment Instructions of the applicable ASB or later NAA approved revisions.

Note: Transport Canada AD CF 2007-07 dated 11 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 2 August 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.