Document ID: chunk:federal_register_of_legislation:F2006B02532:body:0
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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.

 Eurocopter AS 355 (Twin Ecureuil) Series Helicopters

AD/AS 355/83 Tail Rotor Blade Trailing Edge Tab 1/2005

            Applicability: AS 355 helicopters, versions E, F, F1, F2, and N, fitted with tail rotor blades part number 355A 12.0040 all dash numbers, and part number 355A 12.0050 all dash numbers, with serial numbers from 8400 through 9224, before incorporation of Repair Sheet FR No. 238 or incorporation of Work Card 64.10.00.872 (Refer to equipment log card (FME)).

            Note: Eurocopter AS 355 Alert Service Bulletin No. 64.00.04 corresponds to Repair Sheet FR No. 238.

            Requirement: Install additional rivets on the trailing edge tab of blades in accordance with paragraph 2.B. of Eurocopter Alert Service Bulletin No.64.00.04 or later EASA approved revision.

            Note: DGAC AD F-2004-176 refers.

 Compliance: Within 100 flight hours or 3 months after 20 January 2005, whichever occurs first.

            This Airworthiness Directive becomes effective on 20 January 2005.

 Background: Reports were received of significant tail rotor blsade trailing edge tab debonding.
            Reduced security of the trailing edge tab due to debonding could lead to loss of the tab if it is not monitored, and result in a significant increase in the vibration level.

 David Villiers
 Delegate of the Civil Aviation Safety Authority 3 December 2004

 The above AD is notified in the Commonwealth of Australia Gazette on 22 December 2004.

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