Airworthiness Directive · Amendment 39-11691 · Agusta Model A109C and A109K2 Helicopters
Agusta Model A109C and A109K2 Helicopters
Model A109C and A109K2 helicopters, with main rotor pitch control link assemblies, part number (P/N) 109-0110-71-103 or -105, installed, certificated in any category.
Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment supersedes an existing airworthiness directive (AD), applicable to Agusta Model A109C and A109K2 helicopters, that currently requires removing the main rotor pitch control link assemblies, measuring the radial play of each upper and lower spherical rod-end bearing (bearing), and replacing any unairworthy bearing. This amendment requires replacing the pitch control link assembly with an assembly that has increased durability and wear resistance. This amendment is prompted by reports of increased helicopter vibration caused by wear of bearings on certain pitch control link assemblies. The actions specified by this AD are intended to eliminate the need for recurring bearing inspections and to prevent failure of a bearing, increased helicopter vibration, and subsequent reduced controllability of the helicopter.
To prevent failure of a main rotor pitch control link rod-end spherical bearing, increased vibration level, and subsequent reduced controllability of the helicopter, accomplish the following:
(a) Rework each main rotor pitch control link assembly, P/N 109-0110-71-103 or -105, and reidentify as pitch control link assembly, P/N 109-0110-71-107, in accordance with the Compliance Instructions of Agusta Bollettino Tecnico 109K-10 or 109-103, both dated November 22, 1995, as applicable.
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.
Aircraft
