Patent ID: 8876045

Claim:
An aircraft actuator control apparatus comprising: a plurality of hydraulically operated actuators that drive a control surface of an aircraft; and a plurality of control systems that respectively control operation of the plurality of actuators, wherein each of the plurality of control systems comprises: a control valve that controls operation of a corresponding actuator by switching a path of pressure oil that is supplied to and discharged from each of a pair of oil chambers of the actuator; a state switching valve that is installed between the control valve and the corresponding actuator so as to provide communication between the control valve and the actuator, that includes an orifice that can be in communication with the pair of oil chambers, and that switches an operating state of the actuator; and a test orifice circuit that includes a test orifice used for testing a performance of the orifice and that can be in communication with the actuator via the state switching valve, the state switching valve is provided such that its position can be switched between: an actuator connection position to connect the actuator to the control valve so as to allow the pressure oil to flow between each of the pair of oil chambers and the control valve; a damping position to allow the pressure oil discharged from each of the pair of oil chambers to pass through the orifice; and a test orifice position to provide communication between each of the pair of oil chambers and the test orifice circuit so as to allow the pressure oil discharged from each of the pair of oil chambers to pass through the test orifice, in a state where the control surface is driven by at least one of the plurality of actuators, a performance test for the orifice can be executed in a the control system of under test that corresponds to another one of the actuators that is different from said corresponding the actuator that drives the control surface, and the performance test for the orifice can be executed by comparing, for the control system under test and the actuator corresponding thereto, an operating speed of the actuator when the state switching valve is switched to the damping position with an operating speed of the actuator when the state switching valve is switched to the test orifice position.