Abstract: An aircraft landing gear assembly having a reinstating geometry in which a lock link can be moved to assume a first locking condition to inhibit movement of a stay when a main strut is in a deployed condition and a second locking condition to inhibit movement of the main strut when in a stowed condition. An unlock actuator is coupled between a first element of the stay and the lock link such that the actuator can break the lock link from the first locking condition and force it to assume the second locking condition by operational force in a single direction.

Abstract: A bearing arrangement having: a first element having an inner race and a first bearing surface; a second element, pivotable relative to the first element about a first axis, and having an outer race and a second bearing surface that cooperates with the first bearing surface to form a plain bearing. The bearing arrangement also includes a roller element disposed between the inner and outer races to form a rolling bearing. The inner and outer races are arcuate and subtend an angle of less than 360° about the first axis.

Abstract: An aircraft landing gear assembly having a reinstating geometry in which a lock link can be moved to assume a first locking condition to inhibit movement of a stay when a main strut is in a deployed condition and a second locking condition to inhibit movement of the main strut when in a stowed condition. An unlock actuator is coupled between a first element of the stay and the lock link such that the actuator can break the lock link from the first locking condition and force it to assume the second locking condition by operational force in a single direction.

Abstract: An aircraft landing gear assembly having a reinstating geometry in which a lock link can be moved to assume a first locking condition to inhibit movement of a stay when a main strut is in a deployed condition and a second locking condition to inhibit movement of the main strut when in a stowed condition. An unlock actuator is coupled between a first element of the stay and the lock link such that the actuator can break the lock link from the first locking condition and force it to assume the second locking condition by operational force in a single direction.

Abstract: A mechanical lock for a vehicle assembly such as an aircraft landing gear assembly. The lock is either pivotally mounted and substantially mass balanced, or part of an aircraft landing gear assembly and arranged to be mechanically operated from the ground by a mechanical actuation device.

Abstract: An aircraft landing gear assembly having a bogie beam pivotally coupled to a support member, and a pitch trimmer assembly including a pitch trimmer actuator configured to exert a biasing force in a first direction and a bias force transmission assembly configured to receive the biasing force in the first direction and bias the bogie beam towards a predetermined neutral position relative to the support member irrespective of the initial position of the bogie beam.

Abstract: An aircraft assembly having a bush mounted within a lug and a recess which extends along a portion of the lug-bush interface to create a relatively wide cavity for receiving sealant.

Abstract: A dynamic bearing for an aircraft landing gear. The bearing comprises a lug, a shaft comprising a first material, and a bearing surface comprising 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 bearing arrangement having: a first element having an inner race and a first bearing surface; a second element, pivotable relative to the first element about a first axis, and having an outer race and a second bearing surface that cooperates with the first bearing surface to form a plain bearing. The bearing arrangement also includes a roller element disposed between the inner and outer races to form a rolling bearing. The inner and outer races are arcuate and subtend an angle of less than 360° about the first axis.

Abstract: An aircraft landing gear assembly having a bogie beam pivotally coupled to a support member, and a pitch trimmer assembly including a pitch trimmer actuator configured to exert a biasing force in a first direction and a bias force transmission assembly configured to receive the biasing force in the first direction and bias the bogie beam towards a predetermined neutral position relative to the support member irrespective of the initial position of the bogie beam.

Abstract: An aircraft landing gear assembly having a reinstating geometry in which a lock link can be moved to assume a first locking condition to inhibit movement of a stay when a main strut is in a deployed condition and a second locking condition to inhibit movement of the main strut when in a stowed condition. An unlock actuator is coupled between a first element of the stay and the lock link such that the actuator can break the lock link from the first locking condition and force it to assume the second locking condition by operational force in a single direction.

Abstract: A mechanical lock for a vehicle assembly such as an aircraft landing gear assembly. The lock is either pivotally mounted and substantially mass balanced, or part of an aircraft landing gear assembly and arranged to be mechanically operated from the ground by a mechanical actuation device.

Abstract: A mechanical lock (10) for a vehicle assembly such as an aircraft landing gear assembly. The lock is either pivotally mounted and substantially mass balanced, or part of an aircraft landing gear assembly (30) and arranged to be mechanically operated from the ground by a mechanical actuation device.

Abstract: A dynamic bearing for an aircraft landing gear. The bearing comprises a lug, a shaft comprising a first material, and a bearing surface comprising 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: An aircraft assembly having a bush mounted within a lug and a recess which extends along a portion of the lug-bush interface to create a relatively wide cavity for receiving sealant.

Abstract: A mechanical lock (10) for a vehicle assembly such as an aircraft landing gear assembly. The lock is either pivotally mounted and substantially mass balanced, or part of an aircraft landing gear assembly (30) and arranged to be mechanically operated from the ground by a mechanical actuation device.

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?).