Abstract: In various embodiments, a two stage shock strut for use in a landing gear assembly may comprise a first cylinder, a fill port, a first stage piston head, a second cylinder, a second stage piston head, and a bleed tube. The first cylinder may define a first volume. The fill port valve may be in fluid communication with the first cylinder and configured to receive hydraulic fluid. The first stage piston head may be in fluid communication with the first volume. The second cylinder may comprise a metering pin. The metering pin may be in fluid communication with the first volume and a second volume defined by the second cylinder. The metering pin may be configured to receive the hydraulic fluid from the first volume and purge gas from the second volume. The second stage piston head may be in fluid communication with the second volume.

Abstract: In various embodiments, a two stage shock strut for use in a landing gear assembly may comprise a first cylinder, a fill port, a first stage piston head, a second cylinder, a second stage piston head, and a bleed tube. The first cylinder may define a first volume. The fill port valve may be in fluid communication with the first cylinder and configured to receive hydraulic fluid. The first stage piston head may be in fluid communication with the first volume. The second cylinder may comprise a metering pin. The metering pin may be in fluid communication with the first volume and a second volume defined by the second cylinder. The metering pin may be configured to receive the hydraulic fluid from the first volume and purge gas from the second volume. The second stage piston head may be in fluid communication with the second volume.

Abstract: A side articulating main landing gear assembly for an aircraft 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: 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 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.