AD/AB139/3 Fin Assembly (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.

Agusta AB139 and AW139 Series Helicopters

AD/AB139/3 Fin Assembly 13/2007

Applicability:

Model AB 139 and AW 139 helicopters, all serial numbers, except 31002, 31003, 31004, and 31007, equipped with a Fin Assembly part number 3G5351A00132, 3G5351A00133, or 3G5351A00134.

Requirement:

1.    Determine the time-in-service of the fin assembly and amend the helicopter’s maintenance program to include the 6,500 flight hour fin assembly life limit in accordance with Agusta Technical Bulletin 139-020 Revision B, or later EASA approved revision.

2.    Replace any part number 3G5351A00132, 3G5351A00133, or 3G5351A00134 fin assembly that has accumulated or exceeded 6,500 flight hours time-in-service.

3.    Inspect the fin assembly in accordance with Agusta Technical Bulletin 139-020 Revision B, or later EASA approved revision.

If damage or cracks are detected, before further flight, contact Agusta S.p.A.

Note:  EASA Corrected AD 2007-0358 refers.

Compliance:

1.    Unless already accomplished, before further flight after 20 December 2007.

2.    Before further flight.

3.    Within 100 flight hours after 20 December 2007, and thereafter at intervals not to exceed 100 flight hours.

This Airworthiness Directive becomes effective on 20 December 2007.

Background:

The manufacturer has determined that the Model AB/AW 139 Fin Assembly is prone to fatigue damage.  To prevent cracks or structural failure of the fin assembly, a life limit and a repetitive inspection are introduced.

David Villiers
Delegate of the Civil Aviation Safety Authority

8 November 2007