A rotary wing aircraft and a rotor assembly of a rotary wind aircraft is disclosed. The rotary wing aircraft includes at least one engine, and the rotor assembly is coupled to the at least one engine. The rotor assembly includes a first rotor hub, a second rotor hub, and a shaft fairing between the first rotor hub to the second rotor hub, the shaft fairing defined by a chord that varies between the first rotor hub and the second rotor hub.

An aircraft has a vertical stabilizer with a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has front longitudinal lugs, rear longitudinal lugs, and opposing middle longitudinal lugs. Front clevises corresponding to the front longitudinal lugs are secured to frame members of the fuselage of the aircraft and each has a first, second, and third mounting arms. Rear clevises corresponding to the rear longitudinal lugs are secured to frame members and each has a first, second, and third mounting arms. Middle clevises corresponding to the middle longitudinal lugs are secured to frame members and each has only first and second mounting arms. Retaining members inserted through mounting holes in each longitudinal lug and mounting holes in each corresponding clevis secures the vertical stabilizer to the fuselage.

An aircraft has a vertical stabilizer with a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has front longitudinal lugs, rear longitudinal lugs, and opposing middle longitudinal lugs. Front clevises corresponding to the front longitudinal lugs are secured to frame members of the fuselage of the aircraft and each has a first, second, and third mounting arms. Rear clevises corresponding to the rear longitudinal lugs are secured to frame members and each has a first, second, and third mounting arms. Middle clevises corresponding to the middle longitudinal lugs are secured to frame members and each has only first and second mounting arms. Retaining members inserted through mounting holes in each longitudinal lug and mounting holes in each corresponding clevis secures the vertical stabilizer to the fuselage.

A hinge assembly 8a for an aircraft component comprises first and second hinge plates 9, 10, each hinge plate including a plurality of fingers 13 to 17. The fingers of the first and second hinge plates are interleaved. A seal assembly 28 to 32 is provided between at least some of the fingers. The provision of a hinge including interposed fingers allows for a hinge assembly having a complex aerodynamic profile to be made, while the sealing function is performed by the seals filling the gaps between the fingers.

A hinge assembly 8a for an aircraft component including first and second hinge plates 9, 10, having an aerodynamic surface. A first seal assembly 28 to 32 is provided and arranged to seal between the aerodynamic surfaces of the hinge plates. A second seal assembly 38 to 42 is arranged to seal between the undersides of the hinge plates in order to reduce pressure leakage between voids under the hinge. The provision of two seal assemblies, each having a dedicated function, addresses the competing demands made on the sealing arrangement of an aircraft hinge assembly in use.

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 fastening system includes a first fastening element attachable to a structure and which has a base portion for plugging through a structural opening, a second fastening element, and a plastically deformable funnel element. The funnel element has a funnel-like basic shape with a funnel opening. The second fastening element can be introduced through the funnel opening into a receiving opening of the base portion and fastened therein and has a collar which faces away from the receiving opening and which is larger than the funnel opening. The funnel element is designed to be deformed from the funnel-like basic shape into a flat, disk-like final shape by the collar of the second fastening element during the fastening of the second fastening element.

A fastening system includes a first fastening element attachable to a structure and which has a base portion for plugging through a structural opening, a second fastening element, and a plastically deformable funnel element. The funnel element has a funnel-like basic shape with a funnel opening. The second fastening element can be introduced through the funnel opening into a receiving opening of the base portion and fastened therein and has a collar which faces away from the receiving opening and which is larger than the funnel opening. The funnel element is designed to be deformed from the funnel-like basic shape into a flat, disk-like final shape by the collar of the second fastening element during the fastening of the second fastening element.

A seal is disclosed for a wing for providing an aerodynamic seal between a fixed aerofoil and a movable control surface.

A seal is disclosed for a wing for providing an aerodynamic seal between a fixed aerofoil and a movable control surface.