An aircraft of the type disclosed here includes an aircraft fuselage, a wing assembly, a tail assembly, and a surface structure containing a lightning protection device. The surface structure is arranged on the aircraft fuselage, the wing assembly, and the tail assembly. The lightning protection device has a plurality of electrically conductive elements, which are arranged at least as a group of elements in the surface structure. The electrically conductive elements belonging to a group are arranged parallel to one another, at least in some section or sections, and have different spacings with respect to one another, at least in two regions.

An isolator includes a first fluid-carrying member and a second fluid-carrying member; and a resistive, semi-conductive or non-conductive component located between the first and the second fluid-carrying member. The component conveys fluid flowing from the first fluid-carrying member to the second fluid-carrying member. The isolator further has a reinforcing composite encircling the first fluid-carrying member, the second fluid-carrying member and the component. The reinforcing composite having first fibers extending at an angle of between −30 degrees and +30 degrees to a longitudinal axis (A-A) of the resistive, semi-conductive or non-conductive component; second fibers interwoven with the first fibers and extending around the first fluid-carrying member, the second fluid-carrying member and the component at an angle of between +60 degrees and +90 degrees and/or between −60 degrees and −90 degrees to the longitudinal axis (A-A); and a resin.

An isolator includes a first fluid-carrying member and a second fluid-carrying member; and a resistive, semi-conductive or non-conductive component located between the first and the second fluid-carrying member. The component conveys fluid flowing from the first fluid-carrying member to the second fluid-carrying member. The isolator further has a reinforcing composite encircling the first fluid-carrying member, the second fluid-carrying member and the component. The reinforcing composite having first fibers extending at an angle of between −30 degrees and +30 degrees to a longitudinal axis (A-A) of the resistive, semi-conductive or non-conductive component; second fibers interwoven with the first fibers and extending around the first fluid-carrying member, the second fluid-carrying member and the component at an angle of between +60 degrees and +90 degrees and/or between −60 degrees and −90 degrees to the longitudinal axis (A-A); and a resin.

A system includes a fuel level sensing probe inside a fuel tank and an exciter wire bundle to connect the fuel level sensing probe to a power source outside the tank. The exciter wire bundle includes an excitation wire and a grounded guard wire. The excitation wire and the grounded guard wire each include a resistive non-metallic wire. The system also includes a return signal wire bundle to connect the fuel level sensing probe to a device configured to measure a quantity of fuel within the tank. The return signal wire bundle includes a return signal wire and a grounded guard wire. The grounded guard wire of the return signal wire bundle and the grounded guard wire of the exciter wire bundle are configured to shield the return signal wire from electromagnetic interference. The return signal wire and the grounded guard wire each include a resistive non-metallic wire.

A thermoplastic surfacer for providing lightning strike protection to a composite component of an aircraft, methods of manufacturing the surfacer, and methods of applying the surfacer to a composite part. The thermoplastic surfacer includes a broadgood having an amorphous thermoplastic resin, one or more fillers embedded into the broadgood, and a lightning strike protection mesh or foil embedded into the broadgood. When applying the surfacer to a composite part of an aircraft, the method includes draping the surfacer on an at least partially unconsolidated composite part, consolidating the at least partially unconsolidated composite part by heating the part to a temperature at or above a melt temperature of a resins used in the part and in the surfacer, and filling at least one surface defect in the consolidated part using the amorphous thermoplastic polymer resin and milled fibers provided in the thermoplastic surfacer.

A thermoplastic surfacer for providing lightning strike protection to a composite component of an aircraft, methods of manufacturing the surfacer, and methods of applying the surfacer to a composite part. The thermoplastic surfacer includes a broadgood having an amorphous thermoplastic resin, one or more fillers embedded into the broadgood, and a lightning strike protection mesh or foil embedded into the broadgood. When applying the surfacer to a composite part of an aircraft, the method includes draping the surfacer on an at least partially unconsolidated composite part, consolidating the at least partially unconsolidated composite part by heating the part to a temperature at or above a melt temperature of a resins used in the part and in the surfacer, and filling at least one surface defect in the consolidated part using the amorphous thermoplastic polymer resin and milled fibers provided in the thermoplastic surfacer.

Lightning-dissipative A/C assemblies are provided, as are valve frames utilized within lightning-dissipative A/C assemblies. In embodiments, the lightning-dissipative A/C assembly includes a base dielectric component having a mount interface, a strike-susceptible metallic component coupled to the base dielectric component, and mounting hardware configured to engage the mount interface to attach the base dielectric component to an A/C. An electrically-conductive coating overlies or is formed over at least a portion of the base dielectric component to complete a lightning strike dissipation path. The lightning strike dissipation path extends from the strike-susceptible metallic component, through the electrically-conductive coating, through the mounting hardware, and to an A/C electrical ground plane when the lightning-dissipative A/C assembly is installed on the A/C. In one implementation, the base dielectric component assumes the form of a valve frame, while the strike-susceptible metallic component assumes the form of a valve door movably mounted to the valve frame.

Lightning-dissipative A/C assemblies are provided, as are valve frames utilized within lightning-dissipative A/C assemblies. In embodiments, the lightning-dissipative A/C assembly includes a base dielectric component having a mount interface, a strike-susceptible metallic component coupled to the base dielectric component, and mounting hardware configured to engage the mount interface to attach the base dielectric component to an A/C. An electrically-conductive coating overlies or is formed over at least a portion of the base dielectric component to complete a lightning strike dissipation path. The lightning strike dissipation path extends from the strike-susceptible metallic component, through the electrically-conductive coating, through the mounting hardware, and to an A/C electrical ground plane when the lightning-dissipative A/C assembly is installed on the A/C. In one implementation, the base dielectric component assumes the form of a valve frame, while the strike-susceptible metallic component assumes the form of a valve door movably mounted to the valve frame.

A laminate structure is disclosed including a fibre laminate impregnated with a laminate matrix material, and a veil of carbon nanotubes impregnated with a veil matrix material. The laminate matrix material and the veil matrix material doped with carbon particles. The veil provides lightning strike protection. The structure is manufactured by co-curing the laminate matrix material and the veil matrix material to bond the veil of carbon nanotubes to the fibre laminate.

A laminate structure is disclosed including a fibre laminate impregnated with a laminate matrix material, and a veil of carbon nanotubes impregnated with a veil matrix material. The laminate matrix material and the veil matrix material doped with carbon particles. The veil provides lightning strike protection. The structure is manufactured by co-curing the laminate matrix material and the veil matrix material to bond the veil of carbon nanotubes to the fibre laminate.