System for an aircraft, the system comprising: a turbine engine (2) with a hydraulic lubrication circuit (30); and a fuel cell (28) with a hydraulic circuit (40) for setting and maintaining the operating temperature of the fuel cell (28); wherein the hydraulic lubrication circuit (30) and the hydraulic circuit (40) form a single and common oil circuit and the oil circuit comprises a pump (50) with a heating element integrated in the pump for heating the oil.
The pump may be an electric pump with an electric motor, wherein the electric motor comprises a coil fed with DC current forming a heating element for heating the oil.
The pump may comprise a body and the heating element may be an electric resistor embedded into the body of the pump and in direct contact with the oil.