Document ID: chunk:federal_register_of_legislation:F2006B02545:body:0:p1
Version: federal_register_of_legislation:F2006B02545
Segment Type: other
Provision Reference: 
Character Range: 20–3063

AIRWORTHINESS DIRECTIVE
 For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/AT/17 Amdt 2 and issues the following AD under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

 Airtractor AT 300, 400 and 500 Series Aeroplanes

 AD/AT/17
 Amdt 3

 Vertical Fin Front and Rear Spars 3/2003

            Applicability:  All Airtractor models AT-300, 400 and 500 series which do not incorporate the fin front spar attachment fitting steel reinforcement plate in accordance with Snow Engineering Service Letter SL #138, SL#155 and SL #196, as applicable. AT301 model S/Ns 301-0100 to 301-0736 must comply with SL#196.

              Requirement: 1. Inspect the vertical fin front spar attachment fitting as detailed in Snow Engineering Service Letters SL #138, SL#155 and SL #196, as applicable.

              2.        For aircraft listed in the Models and Serial Numbers section of SL#138, SL #155 or SL#196, modify by installing the fin front spar steel reinforcement plate in accordance with SL#138, SL #155 or SL#196, respectively.

            Note 1: FAA ADs 97-14-05, 2000-11-05 and NPRM No. 2000-CE-59-AD refer.

            Note 2: FAA AD 2000-11-05 added additional serial numbers to the applicability of SL# 196.

 Compliance: For Requirement 1:

                  1. If SL #138 is applicable, then unless already accomplished, initially inspect within the next 25 hours time in service, thereafter, re-inspect at intervals not exceeding 25 hours time in service.

b.        If SL#155 is applicable, then unless already accomplished, initially inspect prior to exceeding 2000 hours time in service, or within 25 hours time in service after 20 March 2003, whichever occurs later. Thereafter, re-inspect at intervals not exceeding 100 hours time in service.

c.         If SL#196 is applicable, then unless already accomplished, initially inspect prior to exceeding 4000 hours time in service, or within 25 hours time in service after 20 March 2003, whichever occurs later. Thereafter, re-inspect at intervals not exceeding 100 hours time in service.

            For requirement 2: Before further flight following the discovery of cracking. This Amendment becomes effective on 20 March 2003.

 Airtractor AT 300, 400 and 500 Series Aeroplanes

 AD/AT/17 Amdt 3 (Continued)

            Background: The initial issue of this AD was the result of in-flight incidents in the USA resulting in partial separation of the fin from the aircraft. Investigations found that the 3/16 inch thick aluminium alloy front