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. <EOS>