Abstract: A dynamic bearing for an aircraft landing gear. The bearing includes a lug; a shaft having a first material; and a bearing surface having a second material that is softer than the first material. The bearing surface defines a bore and is arranged to support the shaft when the shaft is movably housed within the bore in use. The bearing surface is defined by the lug or a coating applied to the lug.

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: 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 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: 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: 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: 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: Landing gear (10) for an airplane including an elongate strut (12) having a first end and a second end longitudinally spaced therefrom. The first end of the strut being pivotally attached to the airplane for pivotal movement of the strut between an extended position for taxiing and landing of the airplane and a retracted position for stowage of the landing gear within a landing gear bay. The landing gear assembly also includes elongate first and second hub assemblies (70) and (72) each having first and second ends. Landing wheels (20) and (22) are journaled to each of the second ends of the hub assemblies. The first ends of the hub assemblies are attached to the second end of the strut for swinging movement thereof between an unsplayed position, wherein the wheels are parallel to each other, and a splayed position, wherein the first and second hub assemblies are spread to a predetermined angle from each other to permit stowage of the landing gear within the landing gear bay with minimal intrusion.