Document ID: chunk:federal_register_of_legislation:F2006B06741:body:0:p2
Version: federal_register_of_legislation:F2006B06741
Segment Type: other
Provision Reference: 
Character Range: 2928–4364

AIRWORTHINESS DIRECTIVES

            Background:  The FAA received a report of a cracked main rotor shaft assembly, found during an inspection of the main transmission oil seal. The shaft had accrued 477 hours time in service when the crack was found. A cracked main rotor shaft assembly could result in failure of the shaft assembly and subsequent loss of control of the helicopter.

            Amendment 1 required repeat visual and NDI inspections. Additionally, the FAA has determined that certain shafts must be removed from service because the three cracked shafts discovered so far came from the same manufacturing lot.

            Amendment 2 was a re-issue of amendment 1 due to a gazette administration issue.

            Amendment 3 introduced the latest revision of the Requirement document which isolated certain main rotor shafts for further inspection and replacement.

            Amendment 4 is issued to reference the related FAA AD.

            Amendment 3 of this Airworthiness Directive became effective on 18 January 2001.

            Amendment 1 of this Airworthiness Directive became effective on 13 November 2000.

            The original issue of this Airworthiness Directive became effective on 7 November 2000.

 David Alan Villiers
 Delegate of the Civil Aviation Safety Authority 9 February 2001

 The above AD is notified in the Commonwealth of Australia Gazette on 21 February 2001.