Document ID: chunk:federal_register_of_legislation:F2006B04591:body:0:p2
Version: federal_register_of_legislation:F2006B04591
Segment Type: other
Provision Reference: 
Character Range: 2725–4098

flapping stop and replace the yoke assembly and flapping stop, if required, in accordance with Part III, Paragraphs 1, 2, and 3, of ASB 212-96-100, whichever is applicable.

               Note 3: FAA Priority Letter AD 98-11-15 refers.

    Compliance: 1. Before further flight after 10 June 1998.

2.    Before 10 December 1998.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

             3.    After accomplishing the requirements of Requirement 2, thereafter at intervals not to exceed 25 hours time in service, or before further flight after any incident as described in Requirement 1.

           This airworthiness directive becomes effective on 10 June 1998.

           Background:  This Directive reflects the issue of a Priority Letter AD by the FAA, which was prompted by an accident involving a BTHI Model 205A-1 helicopter in which the tail rotor yoke failed during flight. The Model 205A-1 helicopter is similar in design to the Model 212 helicopter. Investigation of the accident revealed that the tail rotor yoke assembly service life may be reduced due to unforeseen static and dynamic loading of the tail rotor. This condition, if not corrected, could lead to failure of the yoke, loss of the tail rotor, and subsequent loss of control of the helicopter.