Document ID: chunk:federal_register_of_legislation:F2006B02505:body:0:p2
Version: federal_register_of_legislation:F2006B02505
Segment Type: other
Provision Reference: 
Character Range: 2807–4362

have revealed deterioration of the tail rotor hub pitch change plate bearing may result in the seizure of the bearing and loss of control of the aircraft.
           This Directive introduces measures to check for correct rotational torque, and regular maintenance checks to ensure the integrity of the assembly.

           Amendment 1 was issued to correct Compliance Statement 2 to reflect the DGAC repetitive inspection requirements and to include the more stringent compliance requirements of DGAC 1999-084-057(A) R1 dated 14 May 1999.

           Amendment 2 provides terminating action for this Directive and adds reference to disposition of components subject to the required inspections.
           Amendment 2 of this Airworthiness Directive became effective on 15 June 2000. Amendment 3 was issued to reflect replacement of Eurocopter Service Bulletin No.
           05.00.30 R2 with Eurocopter Alert Service Bulletin No. 05.00.30 Revision 3. The
           Service Bulletin was upgraded to Alert status with no change to the technical content of the Service Bulletin.

           Amendment 4 of this Airworthiness Directive has been issued to correct a typographical error in Amendment 3.

           Amendment 3 of this Airworthiness Directive became effective on 31 October 2002. The original issue of this Airworthiness Directive became effective on 20 May 1999.

 James Coyne
 Delegate of the Civil Aviation Safety Authority 18 November 2002

 The above AD is notified in the Commonwealth of Australia Gazette on 4 December 2002.