AD/X-TS/8 Flap Hinge and Flap Hinge Support Bracket (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.

Eagle X-TS Series Aeroplanes

AD/X-TS/8 Flap Hinge and Flap Hinge
Support Bracket 10/2007 DM

Applicability:

Model X-TS, X-TS 150 and 150B aircraft.

Requirement:

Action in accordance with CTRM Aviation Service Bulletin 1126 original issue, or later Malaysia DCA approved revision.

Note:  Malaysia DCA CAM AD 001-07-2007 refers.

Compliance:

Within 25 flight hours after 15 August 2007, unless already accomplished.

This Airworthiness Directive becomes effective on 15 August 2007.

Background:

A report was received of severe exfoliation corrosion on wing/canard flap hinges, part number 5731D01-16 (middle and outboard hinges) on a Model 150B aircraft; that was detected during a 100-hour inspection.  The aircraft had accumulated more than 1,000 flight hours.  The corrosion was so severe that the thickness of one of the flap hinges was reduced by 50%, and was not easily detected because the flap hinge is sandwiched between the flap hinge support bracket part number 5731D01-01.  Failure of the hinge bracket could result in disintegration of flap canard/wing with consequent loss of control.

David Villiers
Delegate of the Civil Aviation Safety Authority

13 August 2007