Document ID: chunk:federal_register_of_legislation:F2006L01448:body:0:p4
Version: federal_register_of_legislation:F2006L01448
Segment Type: other
Provision Reference: 
Character Range: 8411–9279

stoppage.  Compliance times for replacement of parts is as detailed in the applicable paragraph of Requirement 1of this AD.

                2. Before installing the gearbox (upper).

                3. Before further flight after the effective date of this AD.

                4. Before further flight after the effective date of this AD.

                5. Within 7 work days of conducting the inspections and measuring the affected parts.
             This Airworthiness Directive becomes effective on 8 May 2006.

Background:  This AD is prompted by an accident and an incident report of fatigue cracking of a shaft.  The actions specified in this AD are intended to prevent fatigue cracking of a shaft, failure of a shaft, and subsequent loss of control of the helicopter.

James Coyne
Delegate of the Civil Aviation Safety Authority

4 May 2006