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.

A process for manufacturing a metal part (10), is described said part extending in a first direction (Y) and having a section comprising a central member (14) and at least a first side member (16) extending in a second direction. The process comprises the following steps: supply of a metal blank (30); removing material from the blank so as to form an intermediate part (32) comprising the central member (14), a junction zone (12) and at least first (116) and second (118) intermediate side members, with a space (34) between the first and second intermediate side members; and hot forming (104) the intermediate part, including spreading the first and second intermediate side members apart by inserting a first punch (212) between said members.

Systems and methods are provided for enforcing contours onto parts of an aircraft. One embodiment is a method for enforcing a contour onto aircraft parts. The method includes removably attaching segmented ring details to aircraft skin details, attaching stringers to skin details to create skin assemblies, positioning skin assemblies at a support structure defining a contour, and fastening frames to the skin assemblies to create a panel. The method also includes removably installing a spreader section onto the panel to complete assembly of a brace prior to removal of the panel, transporting the panel while the brace enforces the contour, attaching the brace to braces for other panels to form a barrel section of a fuselage for an aircraft while the brace enforces the contour, and removing the brace from the barrel section after the barrel section has been formed.

A replaceable web structure for an aircraft frame is described and includes a plurality of structural members fabricated from a first type of material, the replaceable web structure comprising a plurality of web members fabricated from thin sheets of a second type of material, wherein each of the web members is fastened to a web frame of one of the structural members to replace a web portion of the one of the structural members; wherein the second type of material is stronger than the first type of material such that one of the sheets of the second type of material is lighter weight than a sheet of equal strength of the first type of material.

A vehicle, such as an aircraft, structural architecture for supporting a horizontal stabilizer with a back up beam having an upper longeron fitting connected to the front side and secured with a back up fitting on the back side, a lower longeron fitting connected to the front side and secured with a back up fitting on the back side, and a pivot fitting connected to the front side of the first back up beam in between the upper longeron fitting and the lower longeron fitting and secured with a third back up fitting on the back side of the back up beam.

A system and method of a structural panel includes a first outer sheet and a second outer sheet, the first outer sheet and second outer sheet including a polygon shape; a core arrangement sandwiched between the first outer sheet and the second outer sheet, the core arrangement comprising two or more discrete members arranged adjacent each other, the discrete members shaped or structured to reduce crack initiation and propagation within the core arrangement.

Applicant discloses a two part polymer mix for use in the aircraft industry that is applied with pneumatic mix and spray gun. The two part cartridge is used in the mix and spray gun so the mix is applied immediately upon mixing, but the two components are kept separated unless the gun is applying the mix. The mix cures to form a clear sealant that allows for inspection of cracks and corrosion beneath the sealant. It cures quickly so that the coated part may be further processed, for example in the assembly line during aircraft build.

An elastic structure anti-impact frame body for use in ships, automobiles, aircraft, trains, railcars and other moving vehicles, said frame body being a wholly or partially elastic frame, the bearing components constituting the frame body forming an arc-shape or a wave-shaped curve, and the frame body being made of an elastic material. The whole or part of the structure of the elastic structure anti-impact frame body has an elastic deformation function; on the premise that the elastic structure does not affect normal driving or bearing capacity, under the force of an impact on said frame, the frame body will elastically deform within a corresponding safe range, and can cushion and absorb the energy of the impact; the frame body, when releasing the energy of the impact, returns to the original shape, greatly improving the anti-impact security factor.

Applicant discloses a two part polymer mix for use in the aircraft industry that is applied with pneumatic mix and spray gun. The two part cartridge is used in the mix and spray gun so the mix is applied immediately upon mixing, but the two components are kept separated unless the gun is applying the mix. The mix cures to form a clear sealant that allows for inspection of cracks and corrosion beneath the sealant. It cures quickly so that the coated part may be further processed, for example in the assembly line during aircraft build.