The invention relates to a system for regulating a temperature of hydraulic fluid in at least one hydraulic circuit of an aircraft, wherein, in a periphery of the aircraft, additional hydraulic consumption units are each provided with at least one controllable valve for heating the hydraulic fluid above an adjustable minimum temperature limit value (T.sub.min), wherein the controllable valve is closed during a maneuver of the aircraft, wherein the controllable valves of the additional hydraulic consumption units are closed when the temperature of the hydraulic fluid exceeds an adjustable theoretical temperature value (T.sub.soll), and wherein a temperature control system is connected to a temperature sensor for adjusting the controllable valve on the basis of a local temperature of the hydraulic fluid, the temperature sensor being near the hydraulic consumption units which are arranged in wings and tail of the aircraft.
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