Document ID: chunk:federal_register_of_legislation:F2005L04019:body:0
Version: federal_register_of_legislation:F2005L04019
Segment Type: other
Provision Reference: 
Character Range: 0–2217

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) 206 and Agusta Bell 206 Series Helicopters
AD/BELL 206/162  Main Rotor Blade Grip Plate Tang  2/2006 DM

Applicability:  Model AB 206A/B helicopters equipped with main rotor blades part number
                206-010-200-(all dash numbers) having a serial number with the prefix A-xxxx; except the following serial numbers:

                A-3586, A-3915, A-4044, A-4087, A-4095, A-4130, A-4132, A-4133, A-4134,
                A-4135, A-4137, A-4143, A-4145, A-4146, A-4147, A-4150, A-4154, A-4155,
                A-4157, A-4163, A-4167, A-4174, A-4175, A-4179, A-4202, A-4206, A-4217,
                A-4221, A-4224, A-4277, A-4302, A-4363, A-4366, A-4375, A-4398, A-4400,
                A-4403, A-4411, A-4414, A-4423, A-4446, A-4497, A-4503, A-5714, and subsequent serial numbers.
Requirement:    Action in accordance with Agusta Technical Bulletin No. 206-239, dated
                7 September 2005.

                Note:  ENAC AD 2005-406 refers.
Compliance:     Within 50 flight hours after 13 December 2005 or before 31 January 2006, whichever occurs first.
                This Airworthiness Directive becomes effective on 13 December 2005.
Background:     Reports were received of tool mark damage discovered on the affected main rotor blades.  The tool marks are on the edges of the grip plate tangs and had resulted from manufacture.  Undetected tool marks could lead to cracking of the grip plate tang.

David Villiers
Delegate of the Civil Aviation Safety Authority

8 December 2005