Airworthiness Directive · Amendment 39-17394 · Tail rotor system
Agusta S.p.A. Helicopters
This AD applies to Agusta Model A109, A109A, A109A II, A109C, A109K2, A109E, A109S, and A119 helicopters, with a tail rotor pitch control link assembly (link assembly), part number (P/N) 109-0130-05-117, with less than 100 hours time-in-service (TIS) and with a serial number (S/N) with a prefix of “MO” and S/N 001 through 773 and without the letter “T” suffix after the S/N, installed, certificated in any category.
We are adopting a new airworthiness directive (AD) for all Agusta S.p.A. (Agusta) Model A109, A109A, A109A II, A109C, A109K2, A109E, A109S, and A119 helicopters. This AD was prompted by a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that a Model A109E helicopter experienced a failure of the tail rotor pitch control link assembly caused by a production defect. The actions of this AD are intended to prevent failure of a tail rotor pitch control link and subsequent loss of control of the helicopter.
You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(1) Before further flight, inspect the link assembly for freedom of movement while it is installed on the helicopter. If rotation resistance or binding occurs, before further flight, remove the link assembly from the helicopter, and either:
(i) Replace it with an airworthy link assembly with a “T” marked after the serial number, or
(ii) Inspect the link assembly for the torsion value force of the ball bearing rotation, in accordance with paragraph (e)(2) of this AD.
(2) If there is no rotation resistance or binding found during the inspection required by paragraph (e)(1) of this AD that required an immediate torsion value force inspection, within 5 hours TIS, remove the link assembly from the helicopter and inspect the torsion value force of the ball bearing rotation by referring to Figure 1 and following the Compliance Instructions, Part II, paragraphs 3. through 3.2, of Agusta Alert Bollettino Tecnico (ABT) No. 109S-5, dated July 26, 2006, for Model A109S helicopters; ABT No. 109EP-70, dated July 27, 2006, for Model A109E helicopters; ABT No. 109K-47, dated July 27, 2006, for Model A109K2 helicopters; ABT No. 109-122, dated July 27, 2006, for Model A109, A109A, A109A II, and A109C helicopters; or ABT No. 119-15, dated July 27, 2006, for Model A119 helicopters.
(i) If the torsion value force of the ball bearing in either end of the link assembly is greater than 7.30 N, the link assembly is unairworthy.
(ii) If the torsion value force of the ball bearing in both ends of the link assembly is equal to or less than 7.30 N, after cleaning the link assembly stem using aliphatic naphtha, or equivalent, and a soft non-metallic bristle brush, inspect all 4 (four) faces of the stem of the link assembly for a crack using a 10x or higher magnifying glass. If you cannot determine whether there is a crack in the stem of the link assembly by using a 10x or higher magnifying glass, conduct a dye penetrant inspection by referring to Figure 1 and following the Compliance Instructions, Part II, paragraphs 6. through 6.7, of the ABT that is applicable to your model helicopter. If a crack is found, the link assembly is unairworthy.
(3) For a link assembly which has been inspected in accordance with paragraph (e)(2) of this AD and determined to be unairworthy, before further flight, replace the link assembly with an airworthy link assembly. Only a link assembly with a “T” marked after the serial number, documenting that the link assembly has been inspected for a crack, is eligible for installation.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
