A door fairing for a retractable landing gear leg of an aircraft is disclosed having an outer member which covers a portion of a landing gear bay of the aircraft when the landing gear leg is retracted. An inner member of the door fairing is coupled to the outer member via a number of configurable couplings which allow adjustment of the position of the outer member with respect to the inner member. The inner member has mounting points for mounting the door fairing to the landing gear leg. Prior to fitting the door fairing at the aircraft, measured or derived dimensional parameters of the landing gear bay are used to adjust the configurable couplings such that the door fairing is preconfigured to fit the landing gear bay of the aircraft.

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.

A system for extracting energy for landing gear retraction may comprise a wheel pump rotationally coupled to a wheel via a pinion gear. A landing gear control valve assembly may be fluidly coupled to an output of the wheel pump. A secondary pump may be fluidly coupled to the landing gear control valve assembly, and an electric motor may be operationally coupled to the secondary pump.

A factory for assembling aircraft or other systems includes a factory floor with multiple build stations. The factory floor includes a hub-and-spoke tool track having radial track sections connected to and extending radially from a circular center hub section. Each track section terminates at a respective build station. A mobile transport travels along the track to the build stations, transforms into different join tools at a predetermined build station, and thereafter engages and supports the components. An overhead crane may perform another task at each build station. The factory floor may include a first floor positioned below a smaller diameter second floor with ramps interconnecting the floors. A center tower is surrounded by the floor(s), with the center tower defining rooms. An aircraft may be assembled via a method using the above-noted factory.

A factory for assembling aircraft or other systems includes a factory floor with multiple build stations. The factory floor includes a hub-and-spoke tool track having radial track sections connected to and extending radially from a circular center hub section. Each track section terminates at a respective build station. A mobile transport travels along the track to the build stations, transforms into different join tools at a predetermined build station, and thereafter engages and supports the components. An overhead crane may perform another task at each build station. The factory floor may include a first floor positioned below a smaller diameter second floor with ramps interconnecting the floors. A center tower is surrounded by the floor(s), with the center tower defining rooms. An aircraft may be assembled via a method using the above-noted factory.

A wheel well fairing for reducing drag on an aircraft fuselage configured with an open wheel well for stowing landing gear of the aircraft. The wheel well fairing includes a Coanda fairing having a convex-shaped lower portion and an upper portion. The upper portion is configured for positioning adjacent an interior vertically-orientated sidewall of the wheel well, and the convex-shaped lower portion has a bottom surface configured to extend substantially parallel to and positioned adjacent with an outer hull surface of the fuselage. The convex-shaped lower portion is curved inwardly within the wheel well between the upper portion and bottom surface. The Coanda fairing is positioned at an aft portion of the wheel well to redirect airflow out of the wheel well in a rearward direction along the bottom hull surface of the fuselage.

A component alignment system for an aircraft includes a first component having a first surface including first shaped projections that repeat in at least two directions along the first surface. The component alignment system also includes a second component having a second surface including second shaped projections that repeat in at least two directions along the second surface. The first shaped projections are complementary to the second shaped projections such that the first surface is translationally and rotationally constrained relative to the second surface when the first and second shaped projections are in an interlocked position.

An assembly for an aircraft having a propeller, including a wheel well configured for receiving a retracted landing gear, the wheel well including walls and a closable bottom opening for deploying the landing gear therethrough, an engine assembly having an engine shaft configured for driving engagement with the propeller, and a mount assembly for supporting the engine assembly, the mount assembly connected to at least one of the walls of the wheel well. A method of supporting an engine assembly in an aircraft having a retractable landing gear and a propeller driven by the engine assembly is also discussed.

An assembly for an aircraft having a propeller, including a wheel well configured for receiving a retracted landing gear, the wheel well including walls and a closable bottom opening for deploying the landing gear therethrough, an engine assembly having an engine shaft configured for driving engagement with the propeller, and a mount assembly for supporting the engine assembly, the mount assembly connected to at least one of the walls of the wheel well. A method of supporting an engine assembly in an aircraft having a retractable landing gear and a propeller driven by the engine assembly is also discussed.