Document ID: chunk:federal_register_of_legislation:F2008L04479:body:0:p2
Version: federal_register_of_legislation:F2008L04479
Segment Type: other
Provision Reference: 
Character Range: 2729–4367

this AD.

                Note:  EASA AD 2008-0184 dated 6 October 2008 refers.  This AD supersedes EASA AD 2006-0079.
Compliance:     For Requirement 1 - Within 110 flight hours or 9 months after the effective date of this AD, whichever occurs first, unless previously accomplished.

                For Requirement 2 - Pending replacement of the twist grip drive tube as detailed in Requirement 1 of this AD.

                For Requirement 3 - After the effective date of this AD.

                For Requirement 4 - Before installation on a helicopter after the effective date of this AD.
                This Amendment becomes effective on 18 December 2008.
Background:     This AD was issued following a case experienced during an autorotation training procedure during which the engine remained at idle rating although the twist grip had been turned back to the flight position.

                Analysis has revealed failure of the twist grip drive tube and control pinion bonded attachment due to non-compliant surface preparation.

                Amendment 1 corrected a typographical error in Requirement 3 of this AD.  The statement should have read "paragraph 2.B.3" instead of "paragraph 2.8.3".  There were no changes to the compliance periods.

                This amendment requires the replacement of certain twist grips and to check other twist grips before installation.

                Amendment 1 of this AD became effective on 3 August 2006.

                The original issue of this AD became effective on 6 July 2006.

James Coyne
Delegate of the Civil Aviation Safety Authority

6 November 2008