Abstract: An aircraft landing gear shock absorber strut including a damping pin and a flow restricting plate having an orifice through which the metering pin axially moves as the sliding tube moves between the extended and compressed positions, wherein the damping pin or the flow restricting plate is coupled to a separator piston so as to move with the separator piston.

Abstract: An aircraft landing gear assembly including a first structural member; a second structural member pivotally coupled to the first structural member to be movable between a first angular condition and a second angular condition; a down-lock spring having a first end region pivotally coupled to a mounting structure under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly including an arm member pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having an first end region pivotally coupled to a second end region of the down-lock spring; and a control link pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point.

Abstract: An aircraft landing gear shock absorber strut including an outer cylinder having a bore defining an opening; an inner cylinder having a first end region movably coupled within the bore and a second end region which projects out of the opening. The inner cylinder being arranged to move along a longitudinal axis of the bore between a first condition and a second condition and is biased by a spring force to assume the second condition. A mechanical outstop is arranged to engage an abutment surface of the inner cylinder to limit extension of the shock absorber strut; and a rotatable member drives the out stop axially to move the inner cylinder from the second condition towards the first condition. The rotatable member is arranged such that the spring force cannot rotate the rotatable member to allow the shock absorber strut to extend.

Abstract: An attachment assembly for an aircraft strut mounting joint. The attachment assembly includes a tubular structure having a central axis and at least one open end. The attachment assembly further includes at least one mounting pin arranged at least partially within the at least one open end of the tubular structure and moveable along the central axis between a retracted position and an extended position. In the extended position, a portion of the at least one mounting pin protrudes for engagement with a lug and in the retracted position the at least one mounting pin is withdrawn for disengagement with the lug. The attachment assembly further includes a retraction mechanism arranged to convert a rotary input motion into linear motion of the at least one mounting pin along the central axis to drive the at least one mounting pin between the extended position and the retracted position.

Abstract: An aircraft landing gear assembly including a first structural member; a second structural member pivotally coupled to the first structural member to be movable between a first angular condition and a second angular condition; a down-lock spring having a first end region pivotally coupled to a mounting structure under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly including an arm member pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having an first end region pivotally coupled to a second end region of the down-lock spring; and a control link pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point.

Abstract: An attachment assembly for an aircraft strut mounting joint. The attachment assembly includes a tubular structure having a central axis and at least one open end. The attachment assembly further includes at least one mounting pin arranged at least partially within the at least one open end of the tubular structure and moveable along the central axis between a retracted position and an extended position. In the extended position, a portion of the at least one mounting pin protrudes for engagement with a lug and in the retracted position the at least one mounting pin is withdrawn for disengagement with the lug. The attachment assembly further includes a retraction mechanism arranged to convert a rotary input motion into linear motion of the at least one mounting pin along the central axis to drive the at least one mounting pin between the extended position and the retracted position.

Abstract: An aircraft landing gear shock absorber strut including an outer cylinder having a bore defining an opening; an inner cylinder having a first end region movably coupled within the bore and a second end region which projects out of the opening. The inner cylinder being arranged to move along a longitudinal axis of the bore between a first condition and a second condition and is biased by a spring force to assume the second condition. A mechanical outstop is arranged to engage an abutment surface of the inner cylinder to limit extension of the shock absorber strut; and a rotatable member drives the out stop axially to move the inner cylinder from the second condition towards the first condition. The rotatable member is arranged such that the spring force cannot rotate the rotatable member to allow the shock absorber strut to extend.

Abstract: An aircraft landing gear shock absorber strut including a damping pin and a flow restricting plate having an orifice through which the metering pin axially moves as the sliding tube moves between the extended and compressed positions, wherein the damping pin or the flow restricting plate is coupled to a separator piston so as to move with the separator piston.

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.