An aircraft comprising: a first support structure and a second support structure , wherein the first support structure comprises a first bracket and the second support structure comprises a second bracket ; a gap between the first support structure and the second support structure ; a number of transport elements running parallel to the support structures within the gap between the support structures , wherein each of the number of transport elements is configured for moving a medium, for example a fluid, fuel or electricity, from one place in the aircraft to another; and a transport element clamp system comprising: a lower portion having a first number of cutouts and configured to bridge the gap between the support structures in the aircraft ; an upper portion having a second number of cutouts and configured to interlock with the lower portion , wherein the lower portion and the upper portion are comprised of a dielectric material ; and a channel system formed by the first number of cutouts and the second number of cutouts , wherein the channel system is configured to receive the number of transport elements when the upper portion and the lower portion are coupled to each other, and wherein the transport element clamp system electrically isolates the number of transport elements from the two support structures , and wherein a first end of the transport element clamp system is fastened to the first bracket on the first support structure , and a second end of the transport element clamp system is fastened to the second bracket on the second support structure . a first support structure and a second support structure , wherein the first support structure comprises a first bracket and the second support structure comprises a second bracket ; a gap between the first support structure and the second support structure ; a number of transport elements running parallel to the support structures within the gap between the support structures , wherein each of the number of transport elements is configured for moving a medium, for example a fluid, fuel or electricity, from one place in the aircraft to another; and a transport element clamp system comprising: a lower portion having a first number of cutouts and configured to bridge the gap between the support structures in the aircraft ; an upper portion having a second number of cutouts and configured to interlock with the lower portion , wherein the lower portion and the upper portion are comprised of a dielectric material ; and a channel system formed by the first number of cutouts and the second number of cutouts , wherein the channel system is configured to receive the number of transport elements when the upper portion and the lower portion are coupled to each other, and wherein the transport element clamp system electrically isolates the number of transport elements from the two support structures , and a lower portion having a first number of cutouts and configured to bridge the gap between the support structures in the aircraft ; an upper portion having a second number of cutouts and configured to interlock with the lower portion , wherein the lower portion and the upper portion are comprised of a dielectric material ; and a channel system formed by the first number of cutouts and the second number of cutouts , wherein the channel system is configured to receive the number of transport elements when the upper portion and the lower portion are coupled to each other, and wherein the transport element clamp system electrically isolates the number of transport elements from the two support structures , and wherein a first end of the transport element clamp system is fastened to the first bracket on the first support structure , and a second end of the transport element clamp system is fastened to the second bracket on the second support structure . <EOS>