AD/Convair/15 Nose Landing Gear Aluminium Uplock Quadrant Lug (Cth)

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/15 Nose Landing Gear Aluminium
Uplock Quadrant Lug 5/2006

Applicability:

Model 240, 340, and 440 aircraft, and all such aircraft converted to turbopropellor power.

Requirement:

1.    Accomplish the following requirements:

a.     Remove the AN3-21 bolt attaching the nose landing gear uplock release cable clevis and the emergency release cylinder to the uplock assembly.

b.    Inspect the part number (P/N) 240-5250109-6 nose landing gear uplock quadrant for cracks in the AN3 bolt attach lug using a 2x or stronger magnifying glass, or dye penetrant method.

c.     If cracks are detected, before further flight, replace the quadrant with either a new aluminium quadrant P/N 240-5250109-6, or a steel quadrant P/N
240-5250109-9.  If a new aluminium quadrant is installed, accomplish Requirements 1.a. through 1.d. at the intervals specified in Compliance 1.c.

d.    Reinstall the AN3 bolt attaching release cable and emergency release cylinder and check rigging of the nose landing gear uplock installation in accordance with the applicable maintenance manual.

2.    Retire P/N 240-5250109-6 aluminium quadrants at specified interval.

Note 1:  Installation of steel quadrant P/N 240-5250109-9 constitutes terminating action for the requirements of this Directive.

Note 2:  FAA AD 77-10-11 Amdt 39-2905 refers.

Compliance:

1.    Within 60 hours time in service after 11 May 2006, and thereafter at intervals not to exceed 60 hours time in service; until a P/N 240-5250109-9 steel quadrant is installed.

1.c. Accomplish Requirements 1.a. through 1.d. at intervals not to exceed 600 hours time in service.

2.    Before accumulating 1,200 hours time in service.

This Airworthiness Directive becomes effective on 11 May 2006.
Background:	The FAA requires certain actions to detect stress corrosion cracking in the aluminium uplock quadrant lug on the nose landing gear.

David Villiers
Delegate of the Civil Aviation Safety Authority

31 March 2006