Abstract: A mechanical fastener system for EME protection, including at least one plated component, wherein the at least one plated component includes a base material, a bonding layer disposed over the base material, and a metal plating disposed over the bonding layer.

Abstract: Apparatuses and methods for aircraft wings, including fuel tank access panel assemblies, are disclosed. For example, an aircraft wing comprises a skin and a load bearing fuel tank access panel assembly fastened to the skin. The skin comprises a fuel tank access panel hole and a first fastener hole. The load bearing fuel tank access panel is configured to bear at least some of a wing bending load and comprises an access panel, a fastener, and a self-locking fastener mating assembly. The access panel comprises a body portion configured to be received in the fuel tank access panel hole, and a lip portion extending over an interior surface of the skin. The lip portion comprises a second fastener hole, and the fastener extends through the first fastener hole and the second fastener hole into the self-locking fastener mating assembly.

Abstract: Systems and methods are provided for fabricating fasteners. One embodiment is an apparatus that includes a fastener. The fastener includes a head, a cylindrical shank that extends from the head and is dimensioned to engage in a fit with a corresponding hole, and a coating that is discontinuously speckled around a circumference of the shank and extends axially along the shank, leaving irregular portions of a surface of the shank exposed. The coating exhibits a higher lubricity than the surface, and the coating exhibits a higher dielectric withstand voltage than the surface.

Abstract: Apparatuses and methods for aircraft wings, including fuel tank access panel assemblies, are disclosed. For example, an aircraft wing comprises a skin and a load bearing fuel tank access panel assembly fastened to the skin. The skin comprises a fuel tank access panel hole and a first fastener hole. The load bearing fuel tank access panel is configured to bear at least some of a wing bending load and comprises an access panel, a fastener, and a self-locking fastener mating assembly. The access panel comprises a body portion configured to be received in the fuel tank access panel hole, and a lip portion extending over an interior surface of the skin. The lip portion comprises a second fastener hole, and the fastener extends through the first fastener hole and the second fastener hole into the self-locking fastener mating assembly.

Abstract: A mechanical fastener system for EME protection, including at least one plated component, wherein the at least one plated component includes a base material, a bonding layer disposed over the base material, and a metal plating disposed over the bonding layer.

Abstract: Systems and methods are provided for fabricating fasteners. One embodiment is an apparatus that includes a fastener. The fastener includes a head, a cylindrical shank that extends from the head and is dimensioned to engage in a fit with a corresponding hole, and a coating that is discontinuously speckled around a circumference of the shank and extends axially along the shank, leaving irregular portions of a surface of the shank exposed. The coating exhibits a higher lubricity than the surface, and the coating exhibits a higher dielectric withstand voltage than the surface.

Abstract: Systems and methods are provided for fabricating fasteners. One embodiment is an apparatus that includes a fastener. The fastener includes a head, a cylindrical shank that extends from the head and is dimensioned to engage in a fit with a corresponding hole, and a coating that is discontinuously speckled around a circumference of the shank and extends axially along the shank, leaving irregular portions of a surface of the shank exposed. The coating exhibits a higher lubricity than the surface, and the coating exhibits a higher dielectric withstand voltage than the surface.

Abstract: A method and apparatus for forming a seal over a hole in a structure. The apparatus comprises a washer, a sleeve, and a fastener. The washer has a first channel. The sleeve has a second channel and an expandable section. The sleeve is positioned inside the first channel in the washer. The fastener has an elongate portion positioned inside the second channel of the sleeve to cause at least a portion of the expandable section of the sleeve to form a first interference fit with the washer.

Abstract: Disclosed herein is a seal assembly for sealing a gap between a first component and a second component is disclosed. The second component is movable relative to the first component. The seal assembly includes a rub strip and a seal strip. The rub strip includes a seal strip engagement surface having a convex shape. Additionally, the rub strip includes a first component engagement surface that is opposite the seal strip engagement surface and has a concave shape. The seal strip includes a rub strip engagement surface having a convex shape. Furthermore, the seal strip includes a second component engagement surface that is opposite the rub strip engagement surface and has a concave shape. The seal strip engagement surface is harder than the rub strip engagement surface.

Abstract: Systems and methods are provided for fabricating fasteners. One embodiment is an apparatus that includes a fastener. The fastener includes a head, a cylindrical shank that extends from the head and is dimensioned to engage in a fit with a corresponding hole, and a coating that is discontinuously speckled around a circumference of the shank and extends axially along the shank, leaving irregular portions of a surface of the shank exposed. The coating exhibits a higher lubricity than the surface, and the coating exhibits a higher dielectric withstand voltage than the surface.

Abstract: Disclosed herein is a seal assembly for sealing a gap between a first component and a second component is disclosed. The second component is movable relative to the first component. The seal assembly includes a rub strip and a seal strip. The rub strip includes a seal strip engagement surface having a convex shape. Additionally, the rub strip includes a first component engagement surface that is opposite the seal strip engagement surface and has a concave shape. The seal strip includes a rub strip engagement surface having a convex shape. Furthermore, the seal strip includes a second component engagement surface that is opposite the rub strip engagement surface and has a concave shape. The seal strip engagement surface is harder than the rub strip engagement surface.

Abstract: A method and apparatus for forming a seal over a hole in a structure. The apparatus comprises a washer, a sleeve, and a fastener. The washer has a first channel. The sleeve has a second channel and an expandable section. The sleeve is positioned inside the first channel in the washer. The fastener has an elongate portion positioned inside the second channel of the sleeve to cause at least a portion of the expandable section of the sleeve to form a first interference fit with the washer.

Abstract: A method and apparatus for forming a seal over a hole in a structure. The apparatus comprises a washer, a sleeve, and a fastener. The washer has a first channel. The sleeve has a second channel and an expandable section. The sleeve is positioned inside the first channel in the washer. The fastener has an elongate portion positioned inside the second channel of the sleeve to cause at least a portion of the expandable section of the sleeve to form a first interference fit with the washer.

Abstract: A method and apparatus for forming a seal over a hole in a structure. The apparatus comprises a washer, a sleeve, and a fastener. The washer has a first channel. The sleeve has a second channel and an expandable section. The sleeve is positioned inside the first channel in the washer. The fastener has an elongate portion positioned inside the second channel of the sleeve to cause at least a portion of the expandable section of the sleeve to form a first interference fit with the washer.

Abstract: A method of installing a door in an access opening in a skin of an aircraft. A composite inner door panel is positioned against an inside face of the skin. A composite outer door panel is positioned against an outside face of the skin. A plurality of fasteners is installed through fastener openings in the composite outer door panel. The plurality of fasteners is tightened to form a chamfered interface between the skin and the composite outer door panel.

Abstract: A method of installing a door in an access opening in a skin of an aircraft. A composite inner door panel is positioned against an inside face of the skin. A composite outer door panel is positioned against an outside face of the skin. A plurality of fasteners is installed through fastener openings in the composite outer door panel. The plurality of fasteners is tightened to form a chamfered interface between the skin and the composite outer door panel.

Abstract: A door for an aircraft wing fuel tank access opening includes an outer impact resistant composite door panel, and an inner composite door panel. Double seals on the inner door panel prevent fuel leakage, and a chamfered outer edge on the outer door panel transfers a component of impact loads laterally into the wing skin to increase kinetic energy absorption.

Abstract: An aircraft joint comprises a wing structure and a wing tip. The wing structure has a first part of a clevis and lug fastening system located around an outer end of the wing structure. The wing tip has a second part of the clevis and lug fastening system located around an end of the wing tip. The wing tip is capable of being joined to the outer end of the wing structure. An upper aerodynamic surface and a lower aerodynamic surface are formed by joining the wing structure and the wing tip. The first part and the second part are located about a center between the upper aerodynamic surface and the lower aerodynamic surface. The first part and the second part engage each other such that a moment reaction occurs around the upper aerodynamic surface and the lower aerodynamic surface.

Abstract: An innovative wing structure provides fibs to support skin panels without an attachment between the rib and the stringer free flange or the web. The support is provided by rib shear ties installed directly to the stringer skin flange. The rib incorporates a cut away to allow the stringer to pass through the rib. The composite stringer is an ‘I’ section and is stable under compression, not requiring mechanical methods to prevent rolling over.

Abstract: A method and apparatus for an aircraft structure. In one advantageous embodiment, the aircraft structure may have a rib, a plurality of stringers, and a set of shear ties. The plurality of stringers may have skin flanges at ends of the plurality of stringers capable of being fastened to skin for the aircraft structure. The set of shear ties may extend from the rib and have a set of elongate members in which the set of elongate members are attached to the plurality of stringers.