AD/A109/54 Tail Rotor Pitch Control Link 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 A109 Series Helicopters

AD/A109/54 Tail Rotor Pitch Control Link Assembly 10/2006 TX

Applicability:

Agusta A109A, AII, C, K2, E, S, and LUH helicopters fitted with tail rotor pitch control link assembly part number (P/N) 109-0130-05-117 with serial (S/N) from MO001 up to S/N MO773 (included).

The AD does not apply to tail rotor pitch control link assembly P/N 109-0130-05-117 with S/N MOxxx and identified with the letter “T” after the S/N.

Requirement:

Action in accordance with Agusta Alert SB 109-122, 109K-47, 109EP-70, 109S-5, 109L-001, or later EASA approved revisions, as is applicable.

Note:  EASA Emergency AD 2006-0228-E dated 27 July 2006 refers.

Compliance:

Before further flight after the effective date of this AD.

For links held as spares:  Before installation on a helicopter after the effective date of this AD.

This Airworthiness Directive becomes effective on 7 August 2006.

Background:

An A109E experienced a failure of the tail rotor pitch control link assembly P/N
109-0130-05-117 with 10 FH.  Preliminary investigation made by the TCH Agusta has revealed that the failure has been caused by a production defect.

James Coyne
Delegate of the Civil Aviation Safety Authority

3 August 2006