Document ID: chunk:federal_register_of_legislation:F2006B04400:body:0:p2
Version: federal_register_of_legislation:F2006B04400
Segment Type: other
Provision Reference: 
Character Range: 2779–4158

with Part III, Paragraph 1, of ASB 205-96-68, Revision A; or inspect the tail rotor flapping stop and replace the yoke assembly and flapping stop, if required, in accordance with Part III, Paragraphs 1, 2, and 3, of ASB 205-96-69 or ASB 205B-96-25, whichever is applicable.

               Note 3: FAA Priority Letter AD 98-11-14 refers.

    Compliance: 1. Before further flight after 3 June 1998.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

2.    Before 3 December 1998.

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 3 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. 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.