Composite tubes for a fluid transport system

A method for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle, the method performed by an apparatus comprising:

• a first transport member configured for use in a fluid transport system, wherein the first transport member is comprised of a material configured to reduce voltages and currents, induced in response to an electromagnetic event, along the first transport member;
• a second transport member configured for use in the fluid transport system, wherein the second transport member is comprised of the material configured to reduce voltages and currents, induced in response to the electromagnetic event, along the second transport member, and wherein the second transport member is separated from the first transport member by an interface;
• a coupling assembly connecting the first transport member and the second transport member, the coupling assembly including a first ferrule that connects to the first transport member and a second ferrule that connects to the second transport member, the first ferrule including a first groove in which is a first O-ring and a second groove in which is a second O-ring, the second ferrule including a third groove in which is a third O-ring and a fourth groove in which is a fourth O-ring, the coupling assembly further including a clamshell device connected to a sleeve, wherein when the coupling assembly is in a closed position:
• the first O-ring creates a first seal and a first conductive pathway between the first ferrule and the clamshell device, the second O-ring creates a second seal and a second conductive pathway between the first ferrule and the sleeve, the third O-ring creates a third seal and a third conductive pathway between the second ferrule and the sleeve, and the fourth O-ring creates a fourth seal and a fourth conductive pathway between the second ferrule and the clamshell device;
• and the method comprising:
• operating the aerospace vehicle;
• and
• reducing voltages and currents, induced in response to an electromagnetic event that occurs during operation of the aerospace vehicle, along the first transport member, then across the interface, and then along the second transport member, to within selected tolerances by an electrical resistance of the first transport member.