Aircraft comprising a structural part for lightning strike protection, wherein the structural part comprises: a first structure element, wherein the first structure element comprises a conducting material and is adapted to conduct electric currents into a grounded conducting airframe structure, a second structure element, wherein the second structure element comprises an outer layer with a first surface, wherein the outer layer comprises a composite, preferably carbon-fibre reinforced plastic, CFRP or glass-fibre reinforced plastic GFRP, a first elongated, preferably wedge-shaped, electrical conductor, with a first end and a second end, wherein the first end of the first elongated electrical conductor is connected to the first structure element and extends through the second structure element to the first surface, so that the second end of the first elongated electrical conductor serves as a lightning receptor without impairing the radar cross section of the aircraft, and further comprising a second elongated, preferably wedge-shaped, electrical conductor with a first end and a second end, wherein the first end of the second elongated electrical conductor is connected to the first structure element and extends through the second structure element to the first surface, so that the second end of the second elongated electrical conductor serves as a lightning receptor without impairing the radar cross section of the aircraft, wherein the first elongated electrical conductor is arranged in the second structure element in a first orientation, wherein the first orientation is adapted to be aligned parallel to the rolling axis of the aircraft, and wherein the second elongated electrical conductor is arranged in the second structure element in a second orientation, wherein the second orientation is adapted to be aligned parallel to the yaw axis of the aircraft. a first structure element, wherein the first structure element comprises a conducting material and is adapted to conduct electric currents into a grounded conducting airframe structure, a second structure element, wherein the second structure element comprises an outer layer with a first surface, wherein the outer layer comprises a composite, preferably carbon-fibre reinforced plastic, CFRP or glass-fibre reinforced plastic GFRP, a first elongated, preferably wedge-shaped, electrical conductor, with a first end and a second end, wherein the first end of the first elongated electrical conductor is connected to the first structure element and extends through the second structure element to the first surface, so that the second end of the first elongated electrical conductor serves as a lightning receptor without impairing the radar cross section of the aircraft, and further comprising a second elongated, preferably wedge-shaped, electrical conductor with a first end and a second end, wherein the first end of the second elongated electrical conductor is connected to the first structure element and extends through the second structure element to the first surface, so that the second end of the second elongated electrical conductor serves as a lightning receptor without impairing the radar cross section of the aircraft, wherein the first elongated electrical conductor is arranged in the second structure element in a first orientation, wherein the first orientation is adapted to be aligned parallel to the rolling axis of the aircraft, and wherein the second elongated electrical conductor is arranged in the second structure element in a second orientation, wherein the second orientation is adapted to be aligned parallel to the yaw axis of the aircraft.