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/24

Main Landing Gear Drag Strut Pivot Bolt

6/2006
 
Applicability:
GENERAL DYNAMICS (Convair) Models 340 and 440 aeroplanes  including all such model airplanes converted to turbo- propeller power, equipped with main landing gear drag strut pivot bolt assembly Part Numbers (P/N) 340-5110105, or
340-5110105-1, or 340-5110105-3.
Requirement:
1.    Unless previously accomplished, inspect the main landing gear drag strut pivot bolt assembly P/N 340-5110105 or 340-5110105-1 or 340- 5110105-3, using magnetic particle inspection procedures, in accordance with Paragraph 2., "Accomplishment Instructions" of General Dynamics, Convair Division, Service Bulletin 640(340D)32-14, dated 10 October 1986, or later FAA approved revision. 2.    If no cracks are found, reinstall the bolt and repeat the bolt inspection in accordance with Requirement 1 of this AD. 3.    If any crack is found, replace main landing gear drag strut pivot bolt assembly with P/N 340-5110105, 340-5110105-1, 340-5110105-3, 340- 5110105-5 or approved equivalent. 4.    If a new P/N 340-5110105 or 340-5110105-1 main landing gear drag strut pivot bolt assembly is used as a replacement, repeat the bolt inspection in accordance with Requirement 1 of this AD. 5.    If a new main landing gear drag strut pivot bolt assembly P/N 340-5110105-3 is used as a replacement part, repeat bolt inspection in accordance with Requirement 1 of this AD. Terminating Action Installation of main landing gear drag strut pivot bolt assembly P/N 340-5110105-5 constitutes terminating action for the repetitive inspections required by this AD. Note:  FAA AD 87-17-10 Amdt 39-5715 refers.
     
Compliance:
1.    Within 500 hours time-in-service after the effective date of this AD. 2.    At intervals not to exceed 500 hours time-in-service since last bolt inspection. 3.    Prior to further flight. 4.    Within 3,000 hours time-in-service after bolt installation and thereafter at intervals not to exceed 500 hours time-in-service since last bolt inspection. 5.    Within 8,000 hours time-in-service after bolt installation and thereafter at intervals not to exceed 500 hours time-in-service since last bolt inspection.
 
This Airworthiness Directive becomes effective on 8 June 2006.
Background:
This actions detailed in this AD are intended to prevent failure of the main landing gear drag strut pivot bolt and possible subsequent main landing gear collapse.
James Coyne
Delegate of the Civil Aviation Safety Authority 28 April 2006