Aircraft landing gear assemblies, aircraft including the landing gear assemblies, and methods of deploying landing gear assemblies. The landing gear assemblies include an elongate landing gear strut, a wheel assembly, and a deployment structure. The elongate landing gear strut includes a first strut end region, an opposed second strut end region, and a wheel assembly mount. The wheel assembly is coupled to the wheel assembly mount. The deployment structure is configured to selectively transition the landing gear assembly between a stowed state and a deployed state.

A method of making an aircraft includes steps of: assembling a subfloor assembly, including a panel support and plurality of transport elements; coupling a wheel well assembly to an airframe of the aircraft to form a nose landing gear bay of the aircraft; forming a pressure boundary delimiting a pressurized space and a non-pressurized space with the wheel well assembly and the airframe; coupling the subfloor assembly to the wheel well assembly, in the pressurized space, to form a portion of a floor of the aircraft so that the plurality of transport elements is located between the panel support and the wheel well assembly; and coupling the plurality of transport elements to at least one high-level system of the aircraft.

A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.

A system for use with a landing gear of an aircraft includes a drag brace assembly having an upper end configured to be rotatably coupled to the aircraft and a lower end configured to be rotatably coupled to a shock strut of the landing gear. The system further includes a jury linkage having a brace portion configured to be pivotally coupled to the drag brace assembly and a strut portion pivotally coupled to the brace portion and configured to be rotatably coupled to the shock strut.

Landing gear monitoring systems and methods for an aircraft include a landing gear timing analysis control unit that is configured to analyze one or both of landing gear motion of one or more landing gears of the aircraft or door motion of one or more doors proximate to the landing gear(s) to determine an operational status of one or both of the landing gear(s) or the door(s).

Landing gear monitoring systems and methods for an aircraft include a landing gear timing analysis control unit that is configured to analyze one or both of landing gear motion of one or more landing gears of the aircraft or door motion of one or more doors proximate to the landing gear(s) to determine an operational status of one or both of the landing gear(s) or the door(s).

A landing gear assembly for an aircraft includes a landing member and an actuation mechanism coupled to the landing member. The actuation mechanism is configured to selectively actuate the landing member into a first landing position and a second landing position. The landing member is configured to support the aircraft in either the first landing position or the second landing position.

A landing gear assembly for an aircraft includes a landing member and an actuation mechanism coupled to the landing member. The actuation mechanism is configured to selectively actuate the landing member into a first landing position and a second landing position. The landing member is configured to support the aircraft in either the first landing position or the second landing position.

A device configured to deploy a retractable landing gear having a main landing gear and a secondary landing gear is provided. The device includes an electrical motor in driving connection with a drive shaft connecting the secondary landing gear with the main landing gear. A retractable landing gear including the device and an aircraft having the landing gear are also provided.

A nose landing gear system is disclosed. In various embodiments, the nose landing gear system includes an electro-hydraulic actuator configured to raise and lower a nose shock strut assembly; a first electro-mechanical actuator configured to steer the nose shock strut assembly; and a second electro-mechanical actuator configured to open and close a fairing door.