1AD/GROB 115/12 Amdt 1 - Elevator Trim Tab

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Image unavailable in extracted text
Image unavailable in extracted text
Grob G115 Series Aeroplanes

AIRWORTHINESS DIRECTIVE

Image unavailable in extracted text

Image unavailable in extracted text
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/GROB 115/12 and issues the following 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/GROB 115/12

Amdt 1

Elevator Trim Tab 6/2000

Applicability: All Grob 115 aircraft which have not been modified in accordance with a scheme approved by the Authority.

Note 1: Aeronautical Engineers Australia Engineering Order EO4796/1 is an approved scheme for the purposes of this Directive.

Requirement: Clean the area around the Elevator Trim Tab Hinges including in the space between the Tab and Elevator.

Inspect using a x 10 magnifying glass around all Elevator Trim Tab hinges for cracking or debonding between the hinge tabs and the resin (See Figure 1). Not only the upper surface of the tab is to be examined, but close attention is to be paid to the junction between the sides/lower surface of the hinge flap and the forward edge of the elevator trim tab.

Image unavailable in extracted text

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

This AD may be carried out by a pilot. A copy of the AD is to be kept in the Flight Manual.

Note 2: The flap segment of the hinge attached to the trim tab runs under the upper surface of the tab.

Note 3: The debonding of the hinges appears as ‘cracking’ along the line joining the resin and hinge tabs. The growth rate of any cracking will be extremely fast.

Further, the crack progression will not be uniform nor similar to fatigue cracking. Therefore, any cracking found is indicative that the entire hinge has debonded.