Document ID: chunk:federal_register_of_legislation:F2006B04673:body:0:p2
Version: federal_register_of_legislation:F2006B04673
Segment Type: other
Provision Reference: 
Character Range: 2745–5114

OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

                (c)     If requirements 3(a) and 3(b) are accomplished in accordance with this Directive, remove the 120 KIAS redline from the pilot and copilot airspeed indicators; remove the Vne airspeed restriction placard; and remove the Bell Helicopter Textron Temporary Revision, dated 16 August 1996, from the Rotorcraft Flight Manual.

             4.    Inspect the yoke assembly and tail rotor flapping stop in accordance with Part III, Recurring 25-Hour Special Inspection and Conditional Inspection Requirement, of Bell Helicopter Textron ASB 412-96-89, Revision A, dated 17 October 1996, or ASB 412CF-96-01, dated 3 September 1996, as applicable.

           Note: FAA AD 2001-09-11 Amdt 39-12217 refers.

 Compliance: 1. Unless already accomplished, before further flight after 29 April 1998.

             2.    Unless Requirement 3 is already accomplished, before further flight after 29 April 1998.

             3.    Unless already accomplished, before 30 Oct 1998.

             4.    After accomplishment of Requirement 3; at intervals not to exceed 25 hours time in service.

           The compliance times of the original issue of this Directive remain unchanged by this issue.

           This amendment becomes effective on 9 August 2001.

           Background: The actions required by the FAA are prompted by laboratory tests and engineering analysis that indicated that the yoke assembly is susceptible to fatigue damage due to unforeseen static and dynamic loading of the tail rotor against the original flapping stop. Failure of the yoke could result in loss of the tail rotor and subsequent loss of control of the helicopter.

               Amendment 1 is issued in response to a new FAA AD which expands applicability to all Model 412 helicopters. This action was prompted by the determination that the unsafe condition exists on all Model 412 helicopters, regardless of serial number.

               The original issue of this Airworthiness Directive became effective on 29 April 1998.

    David Alan Villiers
    Delegate of the Civil Aviation Safety Authority 3 July 2001

    The above AD is notified in the Commonwealth of Australia Gazette on 11 July 2001.