Document ID: chunk:federal_register_of_legislation:F2006L01297:body:0:p1
Version: federal_register_of_legislation:F2006L01297
Segment Type: other
Provision Reference: 
Character Range: 0–3038

AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (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.

Kelowna Flightcraft (General Dynamics/Convair) Series Aeroplanes
AD/CONVAIR/23  Fuselage Stringer and Beltframe Attachment between Stations 140 and 889  6/2006

Applicability:  Model 340 and 440 series aircraft, including all such model aircraft converted to turbopropeller power.
Requirement:       1. For aircraft with more than 52,000 hours time in service, perform an initial detailed visual, above floor level, inspection of the stringers and beltframes for evidence of cracks at all stringer to beltframe attach points between stations 140 and 889; and,

                     a. Aircraft certificated at a maximum gross weight of 55,000 lbs or less, and without a main cargo door, perform a detailed visual inspection of all stringer to frame attachment, above and below floor level, for evidence of cracks between stations 140 and 889; and thereafter,

                        (i) Perform a detailed visual inspection of all stringer to frame attachment for evidence of cracks below the floor between stations 681 and 889; and,

                        (ii) Perform a detailed visual inspection of all stringer to frame attachment for evidence of cracks between stations140 and 889 above the floor and between stations 140 and 681 below the floor.

                     b. Aircraft with a main deck cargo door and aircraft certificated at a maximum gross weight of more than 55,000 lbs, perform a detailed visual inspection of all stringer to frame attachment, above and below floor level, for evidence of cracks between stations 140 and 889.

                   2. For aircraft with more than 42,000 hours time in service, up to and including 52,000 hours time in service, perform an initial detailed visual, above floor level, inspection of the stringers and beltframes for evidence of cracks at all stringer to beltframe attach points between stations 140 and 889.  Repetitively inspect in accordance with Requirement 1.a. or 1.b.

      3. For aircraft with more than 35,000 hours time in service, up to and including 42,000 hours time in service, perform an initial detailed visual, above floor level, inspection of the stringers and beltframes for evidence of cracks at all stringer to beltframes attach points between stations 140 and 889.  Perform a repetitive detailed visual inspection of all stringer to frame attachment, above and