Document ID: chunk:federal_register_of_legislation:F2005L01763:body:0
Version: federal_register_of_legislation:F2005L01763
Segment Type: other
Provision Reference: 
Character Range: 0–2265

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 222/32  Main Rotor Yoke - 2  8/2005

Applicability:  Model 222 helicopters, serial numbers 47006 through 47089,

                Model 222B helicopters, serial numbers 47131 through 47156,

                Model 222U helicopters, serial numbers 47501 through 47574,

                Model 230 helicopters, serial numbers 23001 through 23038.
Requirement:    Action in accordance with Bell Helicopter Textron Alert Service Bulletin 222-03-97, 222U-03-68, or 230-03-28, as applicable, or later revisions approved by Transport Canada.

                Note:  Transport Canada AD CF-2003-27 refers.
Compliance:     For Part I of the Requirement document:

                   Within 50 flight hours after 4 August 2005, and thereafter at intervals not to exceed 25 flight hours.

                For Part II of the Requirement document:

                   Within 50 flight hours after 4 August 2005, and thereafter at intervals not to exceed 50 flight hours.
                This Airworthiness Directive becomes effective on 4 August 2005.
Background:     Transport Canada received a report of a fatigue crack being found in a main rotor yoke, part number 222-011-102-105, in the area of the flapping bearing bushing.  It was determined that the buffer pad installed under the bushing flange during manufacture had deteriorated to the point that there was metal-to-metal contact, resulting in heavy fretting, which led to crack initiation.

David Villiers
Delegate of the Civil Aviation Safety Authority

24 June 2005