Document ID: chunk:federal_register_of_legislation:F2006B09365:body:0:p2
Version: federal_register_of_legislation:F2006B09365
Segment Type: other
Provision Reference: 
Character Range: 2857–4385

tail rotor hub pitch change plate bearing which could have to 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 1999-085-076(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 been issued to reflect replacement of Eurocopter Service Bulletin No. 05.00.29 R2 with Eurocopter Alert Service Bulletin No. 05.00.29 Revision 3.
           The Service Bulletin was updated to Alert status with no change to the technical content of the Service Bulletin.

           Amendment 3 of this Airworthiness Directive became effective on 31 October 2002.

           Amendment 4 of this Airworthiness Directive is raised to correct a typographical error in Amendment 3.

           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.