Abstract: A landing gear system comprises a bogie beam, a landing gear axle pivotally mounted to the bogie beam, a steering rack, a linear actuator assembly, and a steering control link. The steering rack is secured transversely to the bogie beam and is longitudinally spaced apart from the landing gear axle. The linear actuator assembly is operable to laterally translate the steering rack. The steering control link is longitudinally extendable and has an actuator end secured to the steering rack, and an axle end of the steering control link engaged with the landing gear axle. The steering control link and the landing gear axle are pivotable relative to the bogie beam about a common axis.

Abstract: A bias steered landing gear system comprises a bogie beam, a first landing gear axle pivotally mounted to the bogie beam, and a steering actuator assembly. The first landing gear axle is pivotable through an axle steering range which includes a maximum inboard steering angle and a maximum outboard steering angle. The steering actuator assembly is operable to apply a steering force to steer the first landing gear axle through the axle steering range between the maximum inboard steering angle and the maximum outboard steering angle. The maximum inboard steering angle is substantially larger than the maximum outboard steering angle.

Abstract: A retractable nose landing gear assembly for an aircraft is disclosed, which includes an elongated strut cylinder defining a longitudinal axis, an elongated strut piston mounted for reciprocal movement relative to the strut cylinder between a shrunk condition when the landing gear is retracted into a wheel well of an aircraft and a fully extended condition when the landing gear is deployed from the wheel well for landing the aircraft, and wherein the strut piston is mounted for rotation about the axis of the strut cylinder for steering the aircraft while taxiing on the ground, and a locking mechanism operatively associated with the strut cylinder for preventing rotation of the strut piston about the axis of the strut cylinder when the landing gear is in a shrunk condition retracted within the wheel well of the aircraft during flight.

Abstract: A retractable nose landing gear assembly for an aircraft is disclosed, which includes an elongated strut cylinder defining a longitudinal axis, an elongated strut piston mounted for reciprocal movement relative to the strut cylinder between a shrunk condition when the landing gear is retracted into a wheel well of an aircraft and a fully extended condition when the landing gear is deployed from the wheel well for landing the aircraft, and wherein the strut piston is mounted for rotation about the axis of the strut cylinder for steering the aircraft while taxiing on the ground, and a locking mechanism operatively associated with the strut cylinder for preventing rotation of the strut piston about the axis of the strut cylinder when the landing gear is in a shrunk condition retracted within the wheel well of the aircraft during flight.

Abstract: A side articulating main landing gear assembly for an aircraft is disclosed which includes a wheel axle fitting oriented in a horizontal plane when the landing gear assembly is in an extended condition deployed from a landing gear bay of the aircraft, a shock absorber adapted to stroke between an extended state and a compressed state upon landing the aircraft, a first linkage for maintaining a tire supported on the wheel axle fitting in a substantially vertical plane as the shock absorber strokes between the extended state and the compressed state, and a second linkage for maintaining the wheel axle fitting in the horizontal plane as the shock absorber strokes between the extended state and the compressed state. The first and second linkages are adapted and configured to minimize lateral tire scuffing during shock absorber stroking.

Abstract: An aircraft shock strut includes a cylinder and a piston movable within the cylinder. A lower bearing and an upper bearing provide sliding engagement between the cylinder and the piston. The upper bearing is fixed to the cylinder and provides sliding engagement with an outer surface the piston. An upper bearing that is fixed to the cylinder facilitates use of lighter weight materials for the cylinder without sacrificing durability.

Abstract: An indicator assembly for an aircraft landing gear for providing indication of a hard landing. The indicator assembly including a actuator member movable when the pressure on a shock strut of the aircraft landing gear exceeds a desired load and stroke threshold indicative of a hard landing. A shear pin is coupled to the actuator member which is configured to shear when a desired level of force is applied to at least a portion of the shear pin. A visibly recognizable indictor is moved from a non-indicating position to an indicating position upon shearing of the shear pin.

Abstract: An aircraft shock strut includes a cylinder and a piston movable within the cylinder. A lower bearing and an upper bearing provide sliding engagement between the cylinder and the piston. The upper bearing is fixed to the cylinder and provides sliding engagement with an outer surface the piston. An upper bearing that is fixed to the cylinder facilitates use of lighter weight materials for the cylinder without sacrificing durability.

Abstract: A tool for manipulating and mobilizing the patella and patellar tendon following injury to the knee or surgery thereon to reduce pain, reduce the formation of scar tissue about the patella and eliminate stiffness and loss of range of motion of the knee, is formed by an elongated, rigid bar having a first end, a second end and an elongated portion extending between the ends. The elongated portion has a central section intermediate the ends defining a V-shaped notch. The first end defines a generally rectangular flattened blade having a lateral beveled edge. The second end defines a generally triangular flattened blade having a lateral arcuate beveled edge. An elastomeric coating is provided on the central section defining the V-shaped notch, on the rectangular blade and on the triangular blade. A method for using the tool is also described.

Abstract: A motor for controlling the elevating and lowering of a load comprises a storage drum, an output drum and a spring member operatively connected therebetween to provide a spring motor therewith, and a pair of cord drums aligned with and respectively adjacent the storage drum and the output drum. A gear train including an idler gear associated with the storage drum drivingly interengages the cord drums with the output drum, whereby the elevating and lowering of a load attached to the cords on the cord drums is balanced regardless of whether the elevating or lowering force is applied centrally between the points of attachment of the cords to the load.

Abstract: A motor for controlling the elevating and lowering of a load comprises a storage drum, an output drum and a spring member operatively connected therebetween to provide a spring motor therewith, and a pair of cord drums aligned with and respectively adjacent the storage drum and the output drum. A gear train including an idler gear associated with the storage drum drivingly interengages the cord drums with the output drum, whereby the elevating and lowering of a load attached to the cords on the cord drums is balanced regardless of whether the elevating or lowering force is applied centrally between the points of attachment of the cords to the load.