Abstract: In one embodiment, an apparatus may comprise: a floor panel for a rotorcraft; one or more puck fasteners in the floor panel, wherein each puck fastener comprises an attachment fitting and a plurality of internal flanges, wherein the plurality of internal flanges within each puck fastener are adjacent; and one or more seating fixtures coupled to the floor panel using the one or more puck fasteners.

Abstract: In one embodiment, an apparatus may comprise: a floor panel for a rotorcraft; one or more puck fasteners in the floor panel, wherein each puck fastener comprises an attachment fitting and a plurality of internal flanges, wherein the plurality of internal flanges within each puck fastener are adjacent; and one or more seating fixtures coupled to the floor panel using the one or more puck fasteners.

Abstract: In one embodiment, an apparatus may comprise: a floor panel for a rotorcraft; one or more puck fasteners in the floor panel, wherein each puck fastener comprises an attachment fitting and a plurality of internal flanges, wherein the plurality of internal flanges within each puck fastener are adjacent; and one or more seating fixtures coupled to the floor panel using the one or more puck fasteners.

Abstract: In one embodiment, an apparatus may comprise: a floor panel for a rotorcraft; one or more puck fasteners in the floor panel, wherein each puck fastener comprises an attachment fitting and a plurality of internal flanges, wherein the plurality of internal flanges within each puck fastener are adjacent; and one or more seating fixtures coupled to the floor panel using the one or more puck fasteners.

Abstract: A skid landing gear assembly is provided. One embodiment of the landing gear assembly may include a first and a second skid member, and a forward and an aft cross member. The forward and aft cross-members may have integrated attachment members coupled to a forward portion and an aft portion of the first and second skid members. In more particular embodiments, the cross-members may be beam members with open cross-sections, and the skid members may be beam members with a closed cross-section.

Abstract: An easily removable and lightweight horizontal stabilizer configured to provide aerodynamic stability for a rotorcraft. The horizontal stabilizer comprising a spar removably coupled to a tailboom with a removable spar attachment means, the spar being located transversely through a tailboom opening and configured to provide structural support for at least a first horizontal airfoil and a second horizontal airfoil. The first and second horizontal airfoils are configured to fittingly receive the spar so that the spar fits at least partially inside the first and second horizontal airfoils. The first and second horizontal airfoils extend outboard from the tailboom to provide aerodynamic pitch stability.

Abstract: An easily removable and lightweight horizontal stabilizer configured to provide aerodynamic stability for a rotorcraft. The horizontal stabilizer comprising a spar removably coupled to a tailboom with a removable spar attachment means, the spar being located transversely through a tailboom opening and configured to provide structural support for at least a first horizontal airfoil and a second horizontal airfoil. The first and second horizontal airfoils are configured to fittingly receive the spar so that the spar fits at least partially inside the first and second horizontal airfoils. The first and second horizontal airfoils extend outboard from the tailboom to provide aerodynamic pitch stability.

Abstract: An easily removable and lightweight horizontal stabilizer configured to provide aerodynamic stability for a rotorcraft. The horizontal stabilizer comprising a spar removably coupled to a tailboom with a removable spar attachment means, the spar being located transversely through a tailboom opening and configured to provide structural support for at least a first horizontal airfoil and a second horizontal airfoil. The first and second horizontal airfoils are configured to fittingly receive the spar so that the spar fits at least partially inside the first and second horizontal airfoils. The first and second horizontal airfoils extend outboard from the tailboom to provide aerodynamic pitch stability.

Abstract: A skid landing gear assembly is provided. One embodiment of the landing gear assembly may include a first and a second skid member, and a forward and an aft cross member. The forward and aft cross-members may have integrated attachment members coupled to a forward portion and an aft portion of the first and second skid members. In more particular embodiments, the cross-members may be beam members with open cross-sections, and the skid members may be beam members with a closed cross-section.

Abstract: An easily removable and lightweight horizontal stabilizer configured to provide aerodynamic stability for a rotorcraft. The horizontal stabilizer comprising a spar removably coupled to a tailboom with a removable spar attachment means, the spar being located transversely through a tailboom opening and configured to provide structural support for at least a first horizontal airfoil and a second horizontal airfoil. The first and second horizontal airfoils are configured to fittingly receive the spar so that the spar fits at least partially inside the first and second horizontal airfoils. The first and second horizontal air-foils extend outboard from the tailboom to provide aerodynamic pitch stability.