Federal Register of Legislation - Australian Government

Primary content

AD/BELL 222/37 - Tail Rotor Pitch Change Mechanism

Authoritative Version
AD/BELL/222/37 Airworthiness Directives/Pt 105 — Aircraft as made
Tail Rotor Pitch Change Mechanism
Administered by: Infrastructure, Transport, Cities and Regional Development
Exempt from sunsetting by the Legislation (Exemptions and Other Matters) Regulation 2015 s12 item 15
Registered 06 Jul 2007
Tabling HistoryDate
Tabled HR07-Aug-2007
Tabled Senate07-Aug-2007

 

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.


David Punshon
Delegate of the Civil Aviation Safety Authority

21 June 2007