Document ID: chunk:federal_register_of_legislation:F2005L02370:body:0:p2
Version: federal_register_of_legislation:F2005L02370
Segment Type: other
Provision Reference: 
Character Range: 2839–4345

accordance with the applicable FAA-approved installation instructions.

                     b. Visually inspect each door hinge on each door assembly to determine if the cotter pins, P/N MS24665-136, are installed in accordance with the "Cotter Pin Installation" section of SB No. TTP2005-01 Revision A.  If a cotter pin is not installed in accordance with the "Cotter Pin Installation" section of the service bulletin, before further flight, install the cotter pins in accordance with the "Cotter Pin Installation" section of the service bulletin.

                Note 1:  The installation of nylon adjustment screws and the trimming of door assembly edges are important maintenance actions that may reduce the strength of the door assembly if not done correctly.

                Note 2:  FAA AD 2005-16-05 Amdt 39-14210 refers.
Compliance:     Within 30 days after 26 August 2005.  Thereafter, inspect in accordance with Requirement 1, at intervals not to exceed 100 hours time in service.
                This Airworthiness Directive becomes effective on 26 August 2005.
Background:     Reports of a fatal accident and an incident prompted the FAA to require the actions specified in this Directive.  The actions specified in this Directive are intended to prevent separation of a door window or door assembly from the helicopter, which could damage the tail rotor during flight and result in loss of the helicopter.

David Punshon
Delegate of the Civil Aviation Safety Authority

24 August 2005