An aircraft landing gear shock absorber assembly having: an outer cylinder having a bore which extends into the outer cylinder, the bore defining an opening in the outer cylinder; a sliding tube having a first end region slidably coupled within the bore and a second end region which projects out of opening; a ground fitting distinct from the sliding tube; and a mechanical fixing arranged to mechanically couple the ground fitting to the second end region of the sliding tube, wherein the sliding tube comprises a tubular body portion formed from a ceramic coated fibre composite tube.

A vertical landing apparatus comprises a body, at least three legs, and at least three leg locks coupled to the body. The body comprises a body lower end and at least three leg housings. Each leg housing comprises a passage extending longitudinally upwardly from a leg housing lower opening. Each leg is translatable within the passage of a respective leg housing between deployed and leg locking positions. Each leg comprises a leg lower end that is longitudinally outboard of the body lower end. Each leg comprises a longitudinally outboard extent from the body lower end to the lower leg end that is longer when in the deployed position than the leg locking position. Each leg lock is associated with a respective leg and configured to move between a locked position in which translation of the leg is prevented and a disengaged position in which translation of the leg is allowed.

A snubber assembly may comprise a snubber having a snubber body with an inner diameter surface and an outer diameter surface, the snubber including a plurality of valve receptacles disposed in the outer diameter surface, the snubber including a plurality of radial apertures disposed through the snubber body, each radial aperture in the plurality of radial apertures disposed in a respective valve receptacle in the plurality of valve receptacles; and a plurality of restrictor valves, each restrictor valve in the plurality of restrictor valves disposed in a respective valve receptacle in the plurality of valve receptacles, each restrictor valve in the plurality of restrictor valves including an orifice disposed through a blade.

A snubber assembly may comprise a snubber having a snubber body with an inner diameter surface and an outer diameter surface, the snubber including a plurality of valve receptacles disposed in the outer diameter surface, the snubber including a plurality of radial apertures disposed through the snubber body, each radial aperture in the plurality of radial apertures disposed in a respective valve receptacle in the plurality of valve receptacles; and a plurality of restrictor valves, each restrictor valve in the plurality of restrictor valves disposed in a respective valve receptacle in the plurality of valve receptacles, each restrictor valve in the plurality of restrictor valves including an orifice disposed through a blade.

A method for pressurizing and depressurizing a shock absorber of an aircraft. More specifically, it relates to a method in which an aircraft weight and ambient temperature are used to calculate a required pressurization level of a shock absorber. As such, the shock absorber may be pressurized to the correct level without applying an iterative approach, greatly reducing initialization time.

A method for pressurizing and depressurizing a shock absorber of an aircraft. More specifically, it relates to a method in which an aircraft weight and ambient temperature are used to calculate a required pressurization level of a shock absorber. As such, the shock absorber may be pressurized to the correct level without applying an iterative approach, greatly reducing initialization time.

A method of operating an electromechanical actuator includes coupling an inner portion of a split ball screw with an outer portion of the split ball screw, rotating the split ball screw about an axis to drive a ball nut in a first axial direction, in response to a failure mode of the electromechanical actuator, decoupling the outer portion of the split ball screw from the inner portion of the split ball screw, and translating the outer portion of the split ball screw and the ball nut in a second axial direction.

A method of operating an electromechanical actuator includes coupling an inner portion of a split ball screw with an outer portion of the split ball screw, rotating the split ball screw about an axis to drive a ball nut in a first axial direction, in response to a failure mode of the electromechanical actuator, decoupling the outer portion of the split ball screw from the inner portion of the split ball screw, and translating the outer portion of the split ball screw and the ball nut in a second axial direction.

A method for monitoring a shock strut may comprise measuring a first shock strut pressure, measuring an ambient temperature, measuring a shock strut stroke, measuring a second shock strut pressure, and determining a servicing condition of the shock strut based upon the first shock strut pressure, the ambient temperature, the shock strut stroke, and the second shock strut pressure, wherein the servicing condition indicates whether it is desirable for the shock strut to be serviced with at least one of a liquid and a gas. The first shock strut pressure and the shock strut stroke may be measured before the takeoff event with a weight of an aircraft supported by the shock strut.

A method for monitoring a shock strut may comprise measuring a first shock strut pressure, measuring an ambient temperature, measuring a shock strut stroke, measuring a second shock strut pressure, and determining a servicing condition of the shock strut based upon the first shock strut pressure, the ambient temperature, the shock strut stroke, and the second shock strut pressure, wherein the servicing condition indicates whether it is desirable for the shock strut to be serviced with at least one of a liquid and a gas. The first shock strut pressure and the shock strut stroke may be measured before the takeoff event with a weight of an aircraft supported by the shock strut.