Document ID: chunk:federal_register_of_legislation:F2006B03891:body:0
Version: federal_register_of_legislation:F2006B03891
Segment Type: other
Provision Reference: 
Character Range: 0–1799

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

 Beechcraft 36 (Bonanza) Series Aeroplanes

 AD/BEECH 36/36
 Amdt 1

 Rudder Forward Spar 5/98

 Applicability: Models Serial Numbers

            36, A36 E-1 through E-2518

            A36TC, B36TC EA-1 through EA-500

             Requirement: 1. Inspect the rudder forward spar in accordance with Beech Service Bulletin SB 2333 Revision 1 dated Nov 1991.

            Note: FAA AD 93-24-03 Amendment 39-8752 refers.

             Compliance: 1. Before exceeding 1000 hrs component TIS or 100 hrs TIS after 1 Nov 1990, whichever occurs later and thereafter at intervals not to exceed 500 hrs TIS.

             The following are considered terminating actions for this Directive:

                1. Installation of repair kit 33-6001-1S in accordance with the Beech SB 2333 Revision 1;

b.   Replacement of the rudder assembly with the applicable part number in accordance with Beech SB2333 Revision 1;

c.    Installation of rudder spar reinforcements in accordance with FAA STC SA4899NM; and,

d.   Installation of rudder spar reinforcements in accordance with FAA STC SA00044LA.

            This amendment becomes effective on 23 April 1998.

            Background: This AD was raised as a result of eight reports of cracks at the hinge bracket attachments in the rudder forward spar. The cause is fatigue initiating at holes drilled to install nut plates. Failure to correct this condition may result in loss of aircraft control. This amendment calls up the latest FAA AD information and highlights the presence of other terminating action.

            The original issue of this airworthiness directive became effective in August 1990.