AD/X-TS/5 Amdt 2 Flap Hinge Support Bracket (Cth)

AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/X-TS/5 Amdt 1 and issues the following 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/5 Amdt 2 Flap Hinge Support Bracket 5/2006

Applicability:

All Model X-TS, X-TS 150 and 150B Aircraft.

Requirement:

Perform a visual inspection of the canard starboard inboard flap hinge support brackets p/n: 5731D01-05 and the canard port inboard flap hinge support brackets p/n: 5731D01-02 for cracking, according to the following procedure:

1.    Visually inspect the gusset weld area for cracks. See figure 1 for the typical crack location.  If there is any cracked, lifted or missing paint in the area of the weld, or a crack is suspected, then perform a further detailed inspection in accordance with requirement 2.

2.    (a)   Remove paint in the weld area shown in figure 1.

(b)   Visually inspect the weld area for cracks using a bright light and magnifying glass.

(c)   If doubt still exists as to whether a crack is present, confirm using Fluorescent Penetrant Inspection (FPI).

(d)   If the bracket is cracked, repair or replace the cracked bracket.  Any repairs must be in accordance with manufacturer’s instructions or a repair scheme approved by a CAR 35 Authorised Person.

Embodiment of Eagle Aircraft (M) Sdn. Bhd. Service Bulletin 1120 Original or later approved issue is terminating action for the requirements of this AD.

Note:  Malaysian DCA Airworthiness Directive CAM AD 001-01-2004 R1, issued
23 December 2005, and Eagle Aircraft S/B 1109 issued 29 August 2003 refer.  Service Bulletin 1109 contains an inspection report form, which must be completed and returned to Eagle Aircraft, if any cracks are found.

Typical crack along weld line. Cracked, lifted or missing paint may indicate cracking.

 

      Figure 1: Inspection Location  

Compliance:

1.    At each daily inspection of the aircraft.

2.    Before further flight.

This directive shall be entered on the maintenance release as maintenance required.  The required visual inspection per Requirement 1 may be performed and certified by a Pilot in Command who has been trained to do the inspection by an appropriately qualified person.

This Amendment becomes effective on 11 May 2006.

Background:

A defect was reported where an inner flap attachment bracket was found cracked along the gusset weld line.  Failure of this bracket may result in asymmetric flap deployment and/or inability to lower or raise the flaps.  A failure of this type would most probably result in loss of control, with catastrophic consequences.

Amendment 1 was issued to reference the Malaysian AD that was raised to reflect the requirements of the original issue of this AD.  There was no change to the requirements or compliance, other than clarification of part numbers.

Amendment 2 is issued in response to a revision of the related DCA AD, which introduces an optional modification as terminating action for the repetitive inspections required by this Directive.

The original issue of this AD became effective on 2 October 2003.

David Villiers
Delegate of the Civil Aviation Safety Authority

29 March 2006