Nose landing gear arrangements for aircrafts, aircrafts including such nose landing gear arrangements, and methods for making such nose landing gear arrangements are provided. In one example, a nose landing gear arrangement includes a wheel assembly and a main strut. The main strut is operatively coupled to the wheel assembly and is configured to move between an extended position and a retracted position. The main strut in the extended position extends outside of the fuselage substantially along a generally vertical plane to position the wheel assembly for takeoff and/or landing of the aircraft. The main strut in the retracted position is disposed inside the fuselage. A flexible sheet is disposed adjacent to the main strut and is configured such that when the main strut is in the extended position the flexible sheet is positioned substantially around the main strut.

A noise abatement system for an aircraft landing gear is provided. The system may have a retention member and a covering member. In this regard, the system may be configured to block the airflow through a structural void to abate noise. Moreover, the system may be shaped to diminish aerodynamic drag.

A tow bar fitting for towing an aircraft is disclosed. The tow bar fitting includes a mount, a pin support, and a tow pin. The mount includes an upper attachment and a lower attachment for affixing the tow bar fitting to a landing gear of the aircraft. The pin support extends from the mount away from the landing gear. The tow pin is positioned in the pin support such that a tow pin plane that horizontally bisects the tow pin is lower than a mount plane that horizontally bisects the upper attachment and the lower attachment when the aircraft is right-side-up on the ground.

Shield assemblies for an aircraft landing gear include an aerodynamic shield, a first support bracket assembly, and a second support bracket assembly. The first support bracket assembly is configured to couple with a structural member of the aircraft landing gear, to support a first end of the aerodynamic shield, and to have a first position that is fixed relative to the structural member in an x-direction, a y-direction, and a z-direction. The first support bracket assembly has a first clamp that is configured to fix the first support bracket assembly relative to the structural member in the x-direction. The second support bracket assembly is configured to support a second end of the aerodynamic shield and to have a second position that is fixed relative to the structural member in the y-direction and the z-direction.

An aircraft landing gear assembly has a longitudinally elongated frame coupled to a lower portion of a fuselage of an aircraft, the frame being capable of supporting at least a portion of the weight of the aircraft. A fairing encloses substantially all of the frame. An optional integrated step can be carried by the frame, and a longitudinally elongated aperture would be formed in the fairing adjacent the step. The step allows a user to place a foot into the aperture and onto the step. An optional door can cover the aperture, and an optional secondary step can be carried by the door.

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 set of doors includes two front doors and two rear doors to open or close the front landing gear bay of the aircraft to enable lowering or retraction of a landing gear, each of the front doors including at least one deflector arranged on an internal face of the front door near a rear leading edge thereof, the deflector extending along the rear leading edge, the set therefore enabling action on an aerodynamic flow between the front doors to disturb it in such a manner as significantly to attenuate undesirable transitory vibratory phenomena that can arise in a particular configuration in which the front doors are open and the rear doors are closed.

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.

An aircraft landing gear assembly includes a main fitting comprising having a main barrel and a cross beam fixedly positioned relative to the main barrel and extending radially from the main barrel. The main fitting further includes a drag arm with a first end pivotally coupled to the cross beam by a first pivotal connection and a second end pivotally coupled to the main barrel by a second pivotal connection.

A landing gear assembly is also provided. The landing gear assembly may include a thin-skin support member defining a cavity and a cylindrical cavity. A cylinder may extend from the cylindrical cavity with an axle extending from the cylinder. A torsion link may be coupled to the axle and a torsion interface of the thin-skin support member.