A system comprising: an aircraft component, wherein the aircraft component includes a hydraulic line, and wherein the hydraulic line is configured to carry an electrical charge; an aircraft object, wherein the aircraft object includes a fuel tank of an aircraft, wherein the fuel tank is constructed of fiber reinforced composite material, and wherein the aircraft component is operatively fastened to the aircraft object; and an aircraft mounting assembly for mounting the aircraft component to the aircraft object, the aircraft mounting assembly comprising a fastener and an electrically conductive bushing for positioning within a mounting hole defined by the aircraft object, the bushing comprising: a tubular body that defines a through-bore, wherein the tubular body includes end regions and a plurality of spring elements spaced circumferentially around the tubular body and extending longitudinally along the tubular body between the end regions; wherein the aircraft mounting assembly is configured such that the mounting of the aircraft component to the aircraft object comprises the fastener extending through the through-bore and the fastener applying a longitudinally compressive force to the bushing to compress the bushing, the bushing having a compressed length that is less than an uncompressed length and wherein the bushing provides an electric current flow path between the hydraulic line and the fuel tank. an aircraft component, wherein the aircraft component includes a hydraulic line, and wherein the hydraulic line is configured to carry an electrical charge; an aircraft object, wherein the aircraft object includes a fuel tank of an aircraft, wherein the fuel tank is constructed of fiber reinforced composite material, and wherein the aircraft component is operatively fastened to the aircraft object; and an aircraft mounting assembly for mounting the aircraft component to the aircraft object, the aircraft mounting assembly comprising a fastener and an electrically conductive bushing for positioning within a mounting hole defined by the aircraft object, the bushing comprising: a tubular body that defines a through-bore, wherein the tubular body includes end regions and a plurality of spring elements spaced circumferentially around the tubular body and extending longitudinally along the tubular body between the end regions; wherein the aircraft mounting assembly is configured such that the mounting of the aircraft component to the aircraft object comprises the fastener extending through the through-bore and the fastener applying a longitudinally compressive force to the bushing to compress the bushing, the bushing having a compressed length that is less than an uncompressed length and wherein the bushing provides an electric current flow path between the hydraulic line and the fuel tank. a tubular body that defines a through-bore, wherein the tubular body includes end regions and a plurality of spring elements spaced circumferentially around the tubular body and extending longitudinally along the tubular body between the end regions; wherein the aircraft mounting assembly is configured such that the mounting of the aircraft component to the aircraft object comprises the fastener extending through the through-bore and the fastener applying a longitudinally compressive force to the bushing to compress the bushing, the bushing having a compressed length that is less than an uncompressed length and wherein the bushing provides an electric current flow path between the hydraulic line and the fuel tank.