An uplock for use with an aircraft landing gear is disclosed having a hook configured to engage a capture pin mounted on the landing gear. The hook is mounted for movement between a closed and locked position and an open and unlocked position. A proximity detector directly detects whether the pin is “up”. An uplock hook sensor detects when the hook is in the closed and locked position. The outputs of the proximity detector and the uplock hook sensor may be used to indicate the “up and locked” condition, i.e., landing gear up, and/or to indicate a fault. Such outputs may be provided by an associated device of an avionics system.

An uplock for use with an aircraft landing gear is disclosed having a hook configured to engage a capture pin mounted on the landing gear. The hook is mounted for movement between a closed and locked position and an open and unlocked position. A proximity detector directly detects whether the pin is “up”. An uplock hook sensor detects when the hook is in the closed and locked position. The outputs of the proximity detector and the uplock hook sensor may be used to indicate the “up and locked” condition, i.e., landing gear up, and/or to indicate a fault. Such outputs may be provided by an associated device of an avionics system.

A landing gear system 100 for an aircraft including: a landing gear 130 that is movable between an extended position and a retracted position, the landing gear includes an extendible strut 136; a position sensor 140 configured to detect a position of a part of the extendible strut and output a signal indicative of the position; and a landing gear controller 150 that is communicably connected to the position sensor and is configured, in use, to: receive the signal from the position sensor; and, on the basis of the signal, determine that the strut has extended and the landing gear is in contact with the ground and automatically cause performance of at least a portion of a procedure to move the landing gear from the extended position to the retracted position.

A landing gear system 100 for an aircraft including: a landing gear 130 that is movable between an extended position and a retracted position, the landing gear includes an extendible strut 136; a position sensor 140 configured to detect a position of a part of the extendible strut and output a signal indicative of the position; and a landing gear controller 150 that is communicably connected to the position sensor and is configured, in use, to: receive the signal from the position sensor; and, on the basis of the signal, determine that the strut has extended and the landing gear is in contact with the ground and automatically cause performance of at least a portion of a procedure to move the landing gear from the extended position to the retracted position.

An adjustment tool for adjusting a maneuvering mechanism of a main landing gear of an aircraft, the landing gear having a plurality of wheels. The tool includes a telemeter, a locking system for locking the telemeter on the external face of a wheel, a wireless communication unit that is connected to the telemeter and makes it possible, when the tool is being used, to connect the telemeter with a control device provided with a display screen.

An adjustment tool for adjusting a maneuvering mechanism of a main landing gear of an aircraft, the landing gear having a plurality of wheels. The tool includes a telemeter, a locking system for locking the telemeter on the external face of a wheel, a wireless communication unit that is connected to the telemeter and makes it possible, when the tool is being used, to connect the telemeter with a control device provided with a display screen.

A method 300 for deploying an aircraft landing gear including: receiving an aircraft landing gear deployment signal 310, receiving an aircraft position signal indicative of a distance of the aircraft from an aircraft landing site 320, receiving one or more flight signals indicating one or more dynamic conditions or parameters relating to the flight of the aircraft 330, determining, based at least on the one or more flight signals, a first aircraft position, relative to the aircraft landing site, at which the landing gear deployment should commence 340, and deploying the landing gear (a) when the aircraft reaches the first aircraft position, in the event that the deployment signal is received before the aircraft reaches the first aircraft position, or (b) immediately, in the event that the deployment signal is received when the aircraft has passed the first aircraft position 350.

A method 300 for deploying an aircraft landing gear including: receiving an aircraft landing gear deployment signal 310, receiving an aircraft position signal indicative of a distance of the aircraft from an aircraft landing site 320, receiving one or more flight signals indicating one or more dynamic conditions or parameters relating to the flight of the aircraft 330, determining, based at least on the one or more flight signals, a first aircraft position, relative to the aircraft landing site, at which the landing gear deployment should commence 340, and deploying the landing gear (a) when the aircraft reaches the first aircraft position, in the event that the deployment signal is received before the aircraft reaches the first aircraft position, or (b) immediately, in the event that the deployment signal is received when the aircraft has passed the first aircraft position 350.

A lock system for a landing gear assembly may comprise a housing and a hook configured to rotate relative to the housing. A lock pin may be configured to translate into a rotational path of the hook. An electromechanical actuator may be configured to translate the lock pin.

An uplock is disclosed including a hook configured to engage a capture pin mounted on an aircraft component. The hook is mounted for movement between a closed position and an open position. The uplock further includes an indicator system configured to detect whether a pin is engaged with the hook when the hook is in the closed position.