AD/CAP 10/6 - Lower Torque Link Attachment Weld (Cth)

COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES

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 39.1 (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.

Avions Mudry Cap Series Aeroplanes

AD/CAP 10/6 Lower Torque Link Attachment Weld 9/2004

Applicability: CAP 10B aircraft, serial number 300 and subsequent, or modified in accordance with MOD 000302 "CAP 10C wing"; and where a main landing gear has a separation zone between the chrome plated area of the moving strut and the torque link attachment of less than 1 mm (0.040-inch), as specified in Requirement document.

Requirement: Inspect in accordance with Apex Aircraft Service Bulletin No. 040506, dated 7 June 2004.

Note: DGAC AD F-2004-108 refers.

Compliance: Within 50 hours time in service after 2 September 2004. Thereafter at intervals not to exceed 100 hours time in service. These periods may be increased by up to10% to align the inspection with a scheduled maintenance check.

This Airworthiness Directive becomes effective on 2 September 2004.

Background: The main landing gear torque link attachment to the moving strut may have been welded onto the chrome plated surface, which could embrittle the weld and lead to cracks.