Abstract: A suspension arrangement for use with aircraft landing gear, including an upper strut, a lower strut that is assembled with and telescopes relative to the upper strut and an oil reservoir within the struts. An adjustable valve assembly includes two interacting relatively movable members which divide the oil reservoir into two distinct sections and provides a restricted flow path for the flow of oil from one section of the oil reservoir to the other. Each of the relatively movable members includes apertures for the flow of oil from one section of the oil reservior to the other thereby to provide that flow path, the aperture being a series of windows in one member registrable with ports in the other member. A drive motor is mounted internally within at least one of the struts and moves the adjustable valve assembly so as to adjust the flow path area, which thus varies the flow of oil through the valve assembly and thereby varies the response of the suspension arrangement.

Abstract: A propeller blade assembly which enables the mounting of a propeller blade in a hub assembly includes a bearing arrangement that circumferentially surrounds and engages with a section of the propeller blade. The bearing arrangement comprises an inner race assembly of angular contact bearings, and an outer race assembly of roller bearings. The roller bearings being arranged so that the axis of rotation thereof is substantially parallel to the longitudinal axis of the propeller blade.

Abstract: A bladed rotor assembly and a control means therefor, which comprises a bladed rotor, a fluid-pressure-operable actuator for effecting a change of blade pitch, a first valve member connect to, and movable with the actuator and a second valve member co-operable with the first valve member, both valve mebmers having fluid passageways therein for supplying fluid to the actuator, and override means being provided to control the position of the second valve member relative to the first valve member, wherein safety means are provided to cause, in the event of failure of the over-ride means, the actuator to effect increased blade pitch.

Abstract: A counterrotatable bladed rotor assembly drivable by a rotatable shaft comprises a leading propeller, a trailing propeller, and a gearbox located axially between the two propellers and enclosed by a non-rotatable casing having an end for attachment to a support structure. The gearbox has a first output shaft to the leading propeller and a second output shaft to the trailing propeller. A first fluid-pressure operable actuator is provided to vary the pitch of the blades of the leading propeller, and a second fluid-pressure operable actuator is provided to vary the pitch of the blades of the trailing propeller. In addition passageways are provided to connect the first and second actuators to a source of fluid under pressure. The casing rotatably supports the second output shaft at a position between the gearbox and the leading propeller and rotatably supports the first output shaft at a position between the gearbox and the trailing propeller.