Document ID: chunk:federal_register_of_legislation:F2006B02564:body:0
Version: federal_register_of_legislation:F2006B02564
Segment Type: other
Provision Reference: 
Character Range: 0–1949

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

 Auster/Beagle A.61 Series Aeroplanes

 AD/AUS/12
 Amdt 1

 Applicability: All models.

      Tailplane Attachment Stubs and Leading Edge Tubes

 3/96

             Requirement: 1. Install a tailplane safety tube and safety split pin in accordance with Auster Modification numbers 2555 and 3234.

             2.    Remove the tailplane and sufficient fabric to ensure complete access to the area to be inspected and inspect :

                1. the tailplane attachment stubs for cracking in the vicinity of the bolt holes, and

b.   on tailplanes of brazed construction, which are those with serial numbers before AUS 697 GD/W and AUS 698 GD/W, inspect the root ends of the leading edge tubes for cracking, particularly in the vicinity of the brazed saddle washers at the attachment bolt holes.

            Note: It is strongly recommended that the inspections be carried out using the dye penetrant method and that suitable tear-off patches be provided at the areas to be inspected.

 Compliance: 1. Prior to 30 September 1959.

             2.    Unless already accomplished within the two ysears prior to 29 February 1996, before 30 May 1996, thereafter:

                1. for Auster J5F - at intervals not exceeding 100 hours time in service or two years, which ever occurs first; and

b.   for all other models - at intervals not exceeding 250 hours time in service or two years, whichever occurs first.

            The effective date of the initial issue of this Directive was 30 September 1959, and remains unchanged for Requirement paragraph 1.

            Background: Amendment 1 is raised to include a calendar based periodicity for this Directive due to the current low utilisation of this Type, and following the inflight failure of a forward attachment tube due to corrosion.