AD/B767/117 - Landing Gear Control Lever Module Adjacent Wiring Inspection (Cth)

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

Boeing 767 Series Aeroplanes

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 CAR 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.

AD/B767/117 Landing Gear Control Lever Module Adjacent Wiring Inspection

5/2000

Applicability: Model 767 aeroplanes listed in Boeing Service Bulletin (SB) 767-32A0163 Revision 1 dated 1 October 1998.

Requirement: 1. Perform a one-time detailed visual inspection to detect damage (ie cut, abrasion, fraying, and arcing) of the wire expando sleeve of the wire bundles adjacent to the landing gear control lever module, in accordance with Boeing Alert Service Bulletin (ASB) 767-32A0163, dated 5 March 1998, or SB 767-32A0163, Revision 1, dated 1 October 1998.

Note 1: For the purposes of this Directive, a detailed visual inspection is defined as: "An intensive examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate by the inspector. Inspection aids such as mirrors, magnifying lenses, etc. may be used. Surface cleaning and elaborate access procedures may be required."