Abstract: A hydraulic system for aircraft operating devices provides a secondary pressure source for direction and deceleration control in case of loss of pressure from a primary pressure source. The system includes multiple pressure accumulators that include a primary accumulator, which supplies pressurized fluid to a first actuator, and first and second secondary accumulators, which supply pressurized fluid to second and third actuators, respectively. If the primary accumulator is disabled, the first secondary accumulator will supply pressurized fluid to the first actuator. If the first secondary accumulator is disabled, the second secondary accumulator will supply pressurized fluid to the second actuator. By providing multiple, substantially independent accumulators, direction and deceleration control is maintained even in the event of loss of the primary accumulator.

Abstract: An aircraft actuator is provided that can achieve a significant weight reduction, while securing a sufficient tensile strength and a sufficient buckling strength, even if it is provided with a reaction link in which large bent portions are formed. A reaction link is made of fiber reinforced plastic, and includes a pair of linear portions, a coupling portion, and a pair of bent portions. The cross section at the pair of linear portions, the coupling portion, and the pair of bent portions is formed as a hollow cross section. The outer cross sectional area of the hollow cross section at each of the pair of bent portions is configured to be larger than the outer cross sectional area of the hollow cross section at each of the pair of linear portions.