An aircraft comprising: - at least one control system for the aircraft, and - a first control surface, a second control surface and a third control surface; the control system comprising: - a hydraulic pump, - a first hydraulic line, - a second hydraulic line, - at least one first actuator coupled with the first control surface, - at least one second actuator coupled with the second control surface, - at least one third actuator coupled with the third control surface, wherein the aircraft comprises a longitudinal axis as symmetry axis (x) in plan view; wherein the first control surface and the second control surface are arranged at a distance to each other and symmetrically relative to the symmetry axis (x), wherein the third control surface is arranged substantially aligned with the symmetry axis (x), wherein the first hydraulic line and the second hydraulic line are connected to different ports of the hydraulic pump, wherein the at least one first actuator is connected to the first hydraulic line at a junction point, at which the at least one first actuator is supplied with hydraulic fluid, wherein the at least one second actuator is connected to the second hydraulic line, wherein the at least one third actuator is connected to the first hydraulic line downstream of the junction point of the at least one first actuator, and wherein the first hydraulic line at least partially comprises a larger diameter than the second hydraulic line; wherein the at least one first actuator is connected to the junction port through a first branch line, wherein the first hydraulic line comprises a larger diameter than the first branch line; and wherein the at least one third actuator is connected to the first hydraulic line through a second branch line, wherein the diameter of the first hydraulic line exceeds a diameter of the second branch line. - at least one control system for the aircraft, and - a first control surface, a second control surface and a third control surface; the control system comprising: - a hydraulic pump, - a first hydraulic line, - a second hydraulic line, - at least one first actuator coupled with the first control surface, - at least one second actuator coupled with the second control surface, - at least one third actuator coupled with the third control surface, - a hydraulic pump, - a first hydraulic line, - a second hydraulic line, - at least one first actuator coupled with the first control surface, - at least one second actuator coupled with the second control surface, - at least one third actuator coupled with the third control surface, wherein the aircraft comprises a longitudinal axis as symmetry axis (x) in plan view; wherein the first control surface and the second control surface are arranged at a distance to each other and symmetrically relative to the symmetry axis (x), wherein the third control surface is arranged substantially aligned with the symmetry axis (x), wherein the first hydraulic line and the second hydraulic line are connected to different ports of the hydraulic pump, wherein the at least one first actuator is connected to the first hydraulic line at a junction point, at which the at least one first actuator is supplied with hydraulic fluid, wherein the at least one second actuator is connected to the second hydraulic line, wherein the at least one third actuator is connected to the first hydraulic line downstream of the junction point of the at least one first actuator, and wherein the first hydraulic line at least partially comprises a larger diameter than the second hydraulic line; wherein the at least one first actuator is connected to the junction port through a first branch line, wherein the first hydraulic line comprises a larger diameter than the first branch line; and wherein the at least one third actuator is connected to the first hydraulic line through a second branch line, wherein the diameter of the first hydraulic line exceeds a diameter of the second branch line.