Abstract: A fuel line coupling component (e.g., for aircraft fuel lines) allow for axial, rotational and radial displacements. The fuel line coupling component includes outer and inner tubular members with each having coaxially aligned pairs of coaxially sleeved tubular sections that are coaxially displaceable relative to one another. A pair of terminal end connectors includes a journalled connection assembly with the respective opposed distal ends of the outer and inner tubular members to thereby allow simultaneous rotational movements of the outer and inner tubular members about a longitudinal axis thereof and simultaneous radial displacements of outer an inner tubular members relative to a reference plane. C-clamps associated with fuel tank fittings and band clamps allow coupling of the fuel line coupling component to the fuel tank fittings and thereby fluid-connect aircraft fuel tanks (e.g., the aircraft main and auxiliary fuel tanks).

Abstract: Protective devices are provided subjacent to the filler port within an aircraft's wing fuel tank so as to protect the lower wing skin from being struck by a nozzle associated with refueling equipment. When inserted into the filler port, the nozzle is brought into contact with the protective device which serves to deflect the nozzle in laterally (e.g., in an inboard direction) to thereby prevent the nozzle from striking the lower wing skin. Thus, when initially inserted into the filler port in a generally perpendicular orientation relative to a horizontal plane, the terminal end of the nozzle will contact with the arcuately concave inner surface of the device such that continued insertion of the nozzle into the filler port will cause the nozzle to assume an angularly canted condition in an inboard direction (i.e., a direction toward the aircraft's fuselage).

Abstract: Protective devices are provided subjacent to the filler port within an aircraft's wing fuel tank so as to protect the lower wing skin from being struck by a nozzle associated with refueling equipment. In this regard, when inserted into the filler port, the nozzle is brought into contact with the protective device which serves to deflect the nozzle in laterally (e.g., in an inboard direction to thereby prevent the nozzle from striking the lower wing skin. Thus, when initially inserted into the filler port in a generally perpendicular orientation relative to a horizontal plane, the terminal end of the nozzle will contact with the arcuately concave inner surface of the device. Since the protective device's surface slopes downwardly and laterally in an inboard direction, continued insertion of the nozzle into the filler port will cause the nozzle to assume an angularly canted condition in an inboard direction (i.e., a direction toward the aircraft's fuselage).