AD/AS 355/85 Amdt 1 Sliding Door Rear Fitting Pin (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/AS 355/85 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.

Eurocopter AS 355 (Twin Ecureuil) Series Helicopters

AD/AS 355/85 Amdt 1 Sliding Door Rear Fitting Pin 10/2005

Applicability:

Model AS 355 helicopters, versions E, F, F1, F2, and N; equipped with sliding door(s).

Requirement:

Check the support shaft of the rear roller and the rear fitting of the sliding door(s) for cracks, in accordance with paragraph 2.B. of Eurocopter AS 355 Alert Telex No. 05.00.45 R1.

Note:  DGAC AD F-2005-136 refers.

Compliance:

For aircraft equipped with sliding doors that have logged less than 90 flight hours:

Upon reaching 110 flight hours, and thereafter at intervals not to exceed 110 flight hours.

For aircraft equipped with sliding doors that have logged 90 or more flight hours:

Unless already accomplished, action in accordance with the original issue of the Requirement document within 20 flight hours after 22 February 2005.  In accordance with Revision 1 of the Requirement document, repeat within 110 flight hours following last compliance, and thereafter at intervals not to exceed 110 flight hours.

This Amendment becomes effective on 29 September 2005.

Background:

The manufacturer received a report of failure and a report of cracking of the sliding door rear roller support pin.  Investigation revealed that the cracks started from a spring pin bore and grew due to fatigue.  Metallurgical analysis revealed heat treatment non-conformity of the pin material.

Amendment 1 is issued in response to a new DGAC AD, which was prompted by reports of cracking and failure of the roller support shaft rear attaching fitting.

David Punshon
Delegate of the Civil Aviation Safety Authority

18 August 2005