Document ID: chunk:federal_register_of_legislation:F2008L01342:body:0:p1
Version: federal_register_of_legislation:F2008L01342
Segment Type: other
Provision Reference: 
Character Range: 0–3051

AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/AT/22 Amdt 1 and issues the following AD under subregulation 39.001(1) of CASR 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/22 Amdt 2  Wing Centreline Splice Joint  7/2008 DM

Applicability:  Models AT-300, AT-301, AT-302, and AT-400A aircraft, all serial numbers, that have aluminium spar caps;

                Models AT-400 aircraft, serial numbers 400-0244 through 400-0415, that have aluminium spar caps;

                Models AT-300 and AT-301 aircraft, all serial numbers, that have aluminium spar caps, and have been converted to turbine power.
Requirement:       1. For all affected aircraft without steel web plates, part numbers 20990-1 or
                   20990-2, or steel spar caps installed, eddy-current inspect the left and right wing spar lower cap outboard holes for cracks in accordance with Snow Engineering Co. Process Specification 197, revised 4 June 2002, or later FAA approved revision:

                     a. For all aircraft:

                     Initially inspect upon reaching 3,500 total hours time in service on the wing spar lower cap or within 10 hours time in service after 8 May 2008, whichever occurs later;

                     Repetitively inspect thereafter at intervals not to exceed 450 hours time in service until the wing spar centre splice joint modification or the required wing spar lower cap replacement is done.  After each replacement, initially inspect upon reaching 3,500 total hours time in service on either wing spar lower cap, and repetitively inspect thereafter at intervals not to exceed 450 hours time in service until the wing spar centre splice joint modification or the required wing spar lower cap replacement is done.

                     b. For aircraft that have had an eddy-current inspection carried out on the wing spar lower cap within the last 450 hours time in service before 8 May 2008:

                     Credit may be taken for that inspection;

        Repetitively inspect thereafter at intervals not to exceed 450 hours time in service from the time of the last inspection until the wing spar centre splice joint modification or the required wing spar lower cap replacement is done.  After each replacement, initially inspect upon reaching 3,500 total hours time in service on either wing spar lower cap, and repetitively inspect thereafter at intervals not to exceed 450