Abstract: A sensor device can include an energy storage device that provides power when charged. The sensor device can also include a first sensor coupled to the energy storage device, where the first sensor measures at least one first parameter when receiving the power. The sensor device can further include a wire having a first portion and a second portion, where the first portion of the wire is coupled to the energy storage device, where the second portion of the wire is disposed proximate to the at least one magnet, where relative motion between the second portion of the wire and the at least one magnet induces current in the wire, where the current induced in the second portion of the wire flows to the energy storage device through the first portion of the wire to charge the energy storage device.

Abstract: A sensor device can include an energy storage device that provides power when charged. The sensor device can also include a first sensor coupled to the energy storage device, where the first sensor measures at least one first parameter when receiving the power. The sensor device can further include a wire having a first portion and a second portion, where the first portion of the wire is coupled to the energy storage device, where the second portion of the wire is disposed proximate to the at least one magnet, where relative motion between the second portion of the wire and the at least one magnet induces current in the wire, where the current induced in the second portion of the wire flows to the energy storage device through the first portion of the wire to charge the energy storage device.

Abstract: A fuel line assembly for an aircraft comprises a ferrule assembly comprising a ferrule affixed to an isolation tube, which may be directly affixed to a fuel tube or affixed to an extension tube, which in turn, is affixed to the fuel tube. The ferrule assembly provides electrostatic discharge protection and lightning protection as the isolation tube maintains a separation distance from the ferrule and fuel tube, both of which are made from metal. The isolation tube is made from a dielectric material, but which may have conductive particles added to aid in the dissipation of an electrostatic charge. The electrical resistance through the isolation tube has a lower limit to arrest the flow of the induced lightning current through the assembly. The amount of lightning protection afforded can be configured. The ferrule assembly components may be affixed by using thermo-welding, adhesive, or mechanical pressure.

Abstract: A fuel line assembly for an aircraft comprises a ferrule assembly comprising a ferrule affixed to an isolation tube, which may be directly affixed to a fuel tube or affixed to an extension tube, which in turn, is affixed to the fuel tube. The ferrule assembly provides electrostatic discharge protection and lightning protection as the isolation tube maintains a separation distance from the ferrule and fuel tube, both of which are made from metal. The isolation tube is made from a dielectric material, but which may have conductive particles added to aid in the dissipation of an electrostatic charge. The electrical resistance through the isolation tube has a lower limit to arrest the flow of the induced lightning current through the assembly. The amount of lightning protection afforded can be configured. The ferrule assembly components may be affixed by using thermo-welding, adhesive, or mechanical pressure.

Abstract: A fuel line assembly for an aircraft comprises a ferrule assembly comprising a ferrule affixed to an isolation tube, which may be directly affixed to a fuel tube or affixed to an extension tube, which in turn, is affixed to the fuel tube. The ferrule assembly provides electrostatic discharge protection and lightning protection as the isolation tube maintains a separation distance from the ferrule and fuel tube, both of which are made from metal. The isolation tube is made from a dielectric material, but which may have conductive particles added to aid in the dissipation of an electrostatic charge. The electrical resistance through the isolation tube has a lower limit to arrest the flow of the induced lightning current through the assembly. The amount of lightning protection afforded can be configured. The ferrule assembly components may be affixed by using thermo-welding, adhesive, or mechanical pressure.

Abstract: A method and apparatus for conducting an electrical current between a first transport member and a second transport member. In one illustrative embodiment, a coupling assembly comprises a first fitting associated with a first end of a first transport member, a second fitting associated with a second end of a second transport member, and a seal. The seal is configured for placement around the first fitting and the second fitting when the first end of the first transport member is positioned relative to the second end of the second transport member. The seal is further configured to seal an interface between the first transport member and the second transport member. The seal is comprised of a material configured such that the seal has a level of conductivity within a selected range and such that a conductive pathway is formed between the first transport member and the second transport member.

Abstract: A mounting system for tubular structures within a wing structure provides for positioning of the tubular structure as it passes through wing ribs. The system provides for electrostatic protection from discharges between the rib and the tubular structure, and accommodates offset tubular positioning. A mounting flange is attached to an aperture in the wing rib, and the tubular structure is inserted through an aperture in the mounting flange. Once the tubular structure is positioned, a cushion mount comprising two pieces is inserted into the flange structure, holding the tubular structure in position in the mounting flange. The cushion mount may have a concentric aperture or an offset aperture to accommodate an offset positioned tubular structure in the wind rib aperture.

Abstract: A method and apparatus for conducting an electrical current between a first transport member and a second transport member. In one illustrative embodiment, a coupling assembly comprises a first fitting associated with a first end of a first transport member, a second fitting associated with a second end of a second transport member, and a seal. The seal is configured for placement around the first fitting and the second fitting when the first end of the first transport member is positioned relative to the second end of the second transport member. The seal is further configured to seal an interface between the first transport member and the second transport member. The seal is comprised of a material configured such that the seal has a level of conductivity within a selected range and such that a conductive pathway is formed between the first transport member and the second transport member.

Abstract: A fuel line assembly for an aircraft comprises a ferrule assembly comprising a ferrule affixed to an isolation tube, which may be directly affixed to a fuel tube or affixed to an extension tube, which in turn, is affixed to the fuel tube. The ferrule assembly provides electrostatic discharge protection and lightning protection as the isolation tube maintains a separation distance from the ferrule and fuel tube, both of which are made from metal. The isolation tube is made from a dielectric material, but which may have conductive particles added to aid in the dissipation of an electrostatic charge. The electrical resistance through the isolation tube has a lower limit to arrest the flow of the induced lightning current through the assembly. The amount of lightning protection afforded can be configured. The ferrule assembly components may be affixed by using thermo-welding, adhesive, or mechanical pressure.

Abstract: A mounting system for tubular structures within a wing structure provides for positioning of the tubular structure as it passes through wing ribs. The system provides for electrostatic protection from discharges between the rib and the tubular structure, and accommodates offset tubular positioning. A mounting flange is attached to an aperture in the wing rib, and the tubular structure is inserted through an aperture in the mounting flange. Once the tubular structure is positioned, a cushion mount comprising two pieces is inserted into the flange structure, holding the tubular structure in position in the mounting flange. The cushion mount may have a concentric aperture or an offset aperture to accommodate an offset positioned tubular structure in the wind rib aperture.