Abstract: A hydraulic actuator includes a piston and a cylinder. The piston is axially movable within the cylinder. A stroke end damping valve is provided in a hydraulic fluid flow passage of the actuator and adjacent an end of the cylinder. The stroke end damping valve comprises a damping orifice and a valve element for selectively varying the area of the damping orifice and thereby changing the damping provided by the orifice. The valve element projects from a wall of the cylinder into the cylinder and is engageable by the piston as the piston moves towards the end of the cylinder. This reduces the area of the damping orifice and thereby increases the damping effect on the piston towards the end of its stroke in the cylinder.

Abstract: A hydraulic actuator includes a piston and a cylinder. The piston is axially movable within the cylinder. A stroke end damping valve is provided in a hydraulic fluid flow passage of the actuator and adjacent an end of the cylinder. The stroke end damping valve comprises a damping orifice and a valve element for selectively varying the area of the damping orifice and thereby changing the damping provided by the orifice. The valve element projects from a wall of the cylinder into the cylinder and is engageable by the piston as the piston moves towards the end of the cylinder. This reduces the area of the damping orifice and thereby increases the damping effect on the piston towards the end of its stroke in the cylinder.

Abstract: A Stability and Command Augmentation System (SCAS) for an aircraft, the SCAS including, a first input shaft providing a first rotational input; a second input shaft providing a second rotational input; and a device for summing the first and second rotational inputs to give a rotational output for controlling an actuator. A method of operating a SCAS on an aircraft, the method including providing a pilot input order in the form of a rotating first shaft, providing an augmentation input order in the form of a rotating second shaft, summing the rotation of the pilot input order and the augmentation input order to give an output order; and using the output order to control an actuator.

Abstract: An assembly comprises a component and a spherical bearing mounted in a bore of the component. The spherical bearing comprises an outer race received within the component bore, an inner spherical member mounted for rotation within the outer race and a releasable retaining element for releasably retaining the outer race in the component bore. The outer race and the component comprise interengaging indexing formations whereby said outer race may be mounted within said component bore in a plurality of angular positions relative to the longitudinal axis (A) of the component bore.

Abstract: An assembly comprises a component and a spherical bearing mounted in a bore of the component. The spherical bearing comprises an outer race received within the component bore, an inner spherical member mounted for rotation within the outer race and a releasable retaining element for releasably retaining the outer race in the component bore. The outer race and the component comprise interengaging indexing formations whereby said outer race may be mounted within said component bore in a plurality of angular positions relative to the longitudinal axis (A) of the component bore.

Abstract: A Stability and Command Augmentation System (SCAS) for an aircraft, the SCAS including, a first input shaft providing a first rotational input; a second input shaft providing a second rotational input; and a device for summing the first and second rotational inputs to give a rotational output for controlling an actuator. A method of operating a SCAS on an aircraft, the method including providing a pilot input order in the form of a rotating first shaft, providing an augmentation input order in the form of a rotating second shaft, summing the rotation of the pilot input order and the augmentation input order to give an output order; and using the output order to control an actuator.