Abstract: A landing gear, including an elongate axle pivotally connected to a bogie beam, the landing gear further including a locking device for locking the axle at a substantially fixed orientation with respect to the bogie beam, the locking device including first and second barrier arms that are movable between a first configuration, in which they define a barrier so as to maintain the maintain the axle in the substantially fixed orientation with respect to the bogie beam, and a second configuration, in which the axle may pivot about the bogie beam.

Abstract: A main landing gear assembly for an aircraft comprising: an elongate beam pivotally coupled about its longitudinal axis to the aircraft such that the axis of rotation of the elongate beam is generally parallel to the longitudinal axis of the aircraft fuselage; a shock strut pivotally coupled at a first end to the elongate beam and coupled at a second end to a wheel assembly; a folding forward stay pivotally coupled at a first end to the elongate beam and pivotally coupled at a second end to the shock strut; and a rigid rear stay pivotally coupled at a first end to the aircraft and pivotally coupled at a second end to the shock strut, the rigid rear stay being arranged to restrain the path of the shock strut when moving between a deployed and a retracted position such that the wheel assembly is located forward and inboard in the retracted position in comparison with its location in the deployed position.

Abstract: A proximity sensor for detecting non-contact detection of a target using a fibre optic strain sensor and a system for operating multiple such proximity sensors is disclosed. The proximity sensor includes an optic fibre that has an optic fibre strain sensor that is coupled to a mass that moves in response to the target. The mass can be a magnet that moves when a ferrous target is within the magnetic field of the magnet causing the magnet to move and apply strain to the optic fibre strain sensor. The optic strain sensor can include periodic variation in the refractive index of the optic fibre, such as a fibre Bragg grating. The proximity sensor can include a second fibre optic sensor that is sensitive to temperature or a second fibre optic strain sensor coupled to a second magnet that operates in opposition to the first magnet. A system coupling multiple proximity sensors can include an interrogator that has an optical power source and a detector, each coupled to a processor.

Abstract: An overload detecting assembly comprising a lateral probe (18) which cooperates with a first load bearing member (10) as it moves towards a second load bearing member (11) and in turn deflects an indicator member (20) which may take a permanent set when a yield point is exceeded. Ready inspection of the indicator member reveals whether or not it has been bent. The indicator member may comprise a cantilevered beam (24) formed in a sleeve (20) coaxial with the load bearing members (10, 11). Alternatively, an extension (25) of the probe (18) may deflect laterally at a midpoint under overload conditions. Alternatively, the probe (18) may form an impression in an indicator member (30) under overload conditions.

Abstract: A locking mechanism for locking an actuator piston within an actuator cylinder housing is disclosed. The locking mechanism comprises a locking pin that is moveable between extended and retracted positions. The locking pin can be moved using a controller, such as a hydraulic controller, for example. In the extended position the locking pin engages the actuator piston thereby locking the actuator piston in a specific position. The locking mechanism includes a mechanical bias (such as a spring or other mechanical system) that biases the locking pin towards an extended position to lock the actuator piston when counter-pressure on the locking pin is lower than the pressure provided by the mechanical bias. The locking pin can be hydraulically operated so that hydraulic pressure that forces the actuator piston to retract also exerts force on the locking pin to move it from a locked position to an unlocked position.

Abstract: A switch assembly is disclosed having a switch with an actuator moveable from an armed position to a disarmed position. A housing is attached to the switch and contains a cam that holds the switch actuator in the armed position. A trigger makes contact with the cam causing it to rotate within the housing and allowing the actuator to extend to move to a disarmed position. In some variants the cam can be shaped to prevent manually rotation against the bias force of the actuator in the disarmed position. The switch assembly can be positioned on an aircraft landing gear to detect an over-steer occurrence where the landing gear may become damaged. The state of the switch can be visibly or audibly indicated by an indicator in the aircraft cockpit or other location visible/audible to the ground operators.

Abstract: A bearing assembly (2?) comprising a housing (3?) supporting first and second bearing ring portions (4, 4?) with bearing surfaces to engage an inner tubular member (1?) at axially spaced regions, characterized in that either: the bearing ring portions are provided by separate bearing rings (4?) supported in the housing member (3?) with bearing surfaces of different diameters; or the bearing ring portions are provided by a single bearing ring (4?) that is free to flex radially and is supported so that the second bearing ring portion is free to flex radially under load and its bearing surface than assumes a position with a greater diameter than that of the first bearing ring portion (4?).

Abstract: Aircraft landing gear including: a bogie beam coupled to a main strut; a first and second axles mounted on the bogie beam, each axle having a respective brake assembly and wheel assembly; and first and second stabilising arms mechanically coupling the first and second brake assemblies to respective first and second anchor points on the landing gear so as to react respective first and second brake torques generated as respective brake assembly applies a braking force to the respective wheel assembly. The first and second stabilising arms couple the respective first and second brake assemblies to the respective first and second anchor points such that the first and second brake torques result in both stabilising arms experiencing a tensile force or both stabilising arms experiencing a compressive force.

Abstract: A landing gear assembly for an aircraft, the landing gear assembly including: an elongate bogie beam; a first axle bearing having an outer part rotatably coupled to an inner part, the outer part being coupled to the bogie beam, the inner part including a mounting aperture; and an elongate axle provided through the mounting aperture of the inner part and coupled thereto, wherein the axle is coupled to the inner part of the first axle bearing in a configuration such that the longitudinal axis of the axle is spaced from the axis of rotation of the inner part, such that rotation of the inner part causes a change in the orientation of the axle relative to the bogie beam.

Abstract: An aircraft landing gear assembly includes a bogie beam, a landing gear strut and a stop. The landing gear strut has a first end arranged to be pivotally coupled to an aircraft and a second end pivotally coupled to the bogie beam. The stop is arranged to limit pivotal movement of the bogie beam relative to the landing gear strut The stop includes an elongate member arranged to be deflectable in bending when the bogie beam reaches a pivotal limit.

Abstract: An overload detecting assembly comprises a first load bearing member (10) adapted to flex laterally in response to a load to be monitored, a second load bearing member (11) spaced from the first under normal load conditions and which is contacted and loaded by the first load bearing member (10) when it is loaded beyond a load limit. Preferably, the first load bearing member (10) has a yield point below the load limit and takes a permanent set once the yield point has been exceeded. A lateral probe (18) cooperates with the first load bearing member as it moves towards the second load bearing member and in turn deflects an indicator member (20) which takes a permanent set when a yield point is exceeded. Ready inspection of the indicator member then reveals whether or not it has been bent.

Abstract: A mechanical position indicator for providing a visual indication that a first part of an aircraft landing gear has assumed a predetermined position relative to a second part, the position indicator being arranged to be coupled to a first one of the first and second parts and in a first state arranged to hold an indicator element in a deployed position, the position indicator being arranged such that upon the first part assuming the predetermined position relative to the second part, a second one of the first and second parts changes the position indicator from the first state to a second state in which the indicator element is displaced from the deployed position, the position indicator being arranged to inhibit the indicator element thereafter returning to the deployed position.

Abstract: There is described a landing gear having a bogie including a elongated beam (2) for accommodating at least two axles receiving each a pair of ground engaging wheels, at least one axle (5) being pivotally mounted on the elongated beam. The landing gear further includes axle travel limitation means (10) extending between said pivotable axle and said elongated beam to be hitched up thereto, said travel limitation means being deformable one way starting from an stable and lockable state thereof corresponding to a landing position of said pivotable axle. There are also described independently lockable and actuatable telescopic struts.

Abstract: An aircraft landing gear assembly comprising a bogie beam (2), an axle (4) extending through the bogie beam and a jacking dome fitting (6) extending through a sidewall (8) of the bogie beam and arranged to transfer vertical loads applied to the jacking dome fitting to the axle.

Abstract: An uplock assembly for retaining and releasing landing gear systems, said uplock assembly comprising: a thermal actuator comprising: a chamber configured to contain expansible material therein; a heating mechanism coupled to said chamber for heating said expansible material and causing volumetric expansion thereof; a piston slidably coupled to said chamber and adapted to extend in response to said volumetric expansion; and an uplock release mechanism releasably engaged by said piston when extended such that said engaged uplock release mechanism causes the release of said landing gear.

Abstract: A load indicator comprises a load bearing assembly of first and second load bearing members (23, 22) connected together to bear a lateral load applied to the first member (23), the first load bearing member defining a cavity (25) with the second load bearing member such that it is frangible above an indicator load, and the cavity (25) containing an indicator liquid which escapes from the cavity once the first load bearing member is fractured by said load. The load bearing members (22, 23) comprise cylindrical members arranged concentrically with the outer member (23) having a portion of reduced thickness to render it frangible and to define the cavity (25). The cavity (25) includes an internal volume within the second load bearing member (22). The load indicator may be configured as a load bearing pin to connect two components.

Abstract: A hydraulic shimmy damper that resolves drawbacks in several known shimmy dampers, such as damping characteristics that are dependent on oil temperature variations. The disclosed shimmy damper includes a hydraulic compensator (40) having an internal fluid volume that is significantly more important than a fluid volume expelled from the body of the shimmy damper when its piston moves fore and aft. The shimmy damper also includes a hydraulic manifold (30) arranged between the body and the hydraulic compensator and defining a transfer channel between chambers in the piston that is connected to the hydraulic compensator. The manifold receives interchangeable hydraulic cartridge-type valves (CV1,RV1;CV2,RV2) for metering the fluid flowing from the chambers to the transfer channel, and allows the fluid to freely enter the chambers from the transfer channel. The present shimmy damper is therefore much less sensitive to oil temperature variation under intense shimmy.

Abstract: A landing gear, including an elongate axle pivotally connected to a bogie beam, the landing gear further including a locking device for locking the axle at a substantially fixed orientation with respect to the bogie beam, the locking device including first and second barrier arms that are movable between a first configuration, in which they define a barrier so as to maintain the maintain the axle in the substantially fixed orientation with respect to the bogie beam, and a second configuration, in which the axle may pivot about the bogie beam.

Abstract: There is described a landing gear having a bogie including a elongated beam (2) for accommodating at least two axles receiving each a pair of ground engaging wheels, at least one axle (5) being pivotally mounted on the elongated beam. The landing gear further includes axle travel limitation means (10) extending between said pivotable axle and said elongated beam to be hitched up thereto, said travel limitation means being deformable one way starting from an stable and lockable state thereof corresponding to a landing position of said pivotable axle. There are also described independently lockable and actuatable telescopic struts.

Abstract: The present invention provides a double hook door mechanism for use in opening and closing aircraft landing gear bay doors.