Portable external oil cooler process for performing hydraulic system functional tests on unfueled airplanes

A cooling system comprising:

• an aircraft;
• and
• an external cooling system for cooling hydraulic fluid for an aircraft
• hydraulic system of the aircraft, the external cooling system comprising:
• an output side including a first hose connected to a return side of an electric motor driven pump, wherein the electric motor driven pump is a component of the aircraft hydraulic system of the aircraft;
• an input side including a second hose connected to a hydraulic fluid reservoir, wherein the hydraulic fluid reservoir is another component of the aircraft hydraulic system of the aircraft;
• and
• a number of heat exchangers configured to cool hydraulic fluid as the electric motor driven pump pumps the hydraulic fluid through the aircraft hydraulic system under conditions wherein fuel tanks in the aircraft are empty, wherein the hydraulic fluid passes from the hydraulic fluid reservoir and through the external cooling system before entering the electric motor driven pump;
• in operation, a path of the hydraulic fluid through the external cooling system includes the first hose, a heat exchanger of the number of heat exchangers, and the second hose without passing through a pump.

A cooling system comprising:

• an aircraft;
• and
• an external cooling system for cooling hydraulic fluid of the aircraft;
• the aircraft having an aircraft hydraulic system comprising an
• electric motor driven pump and a hydraulic fluid reservoir;
• the external cooling system comprising:
• a number of heat exchangers external of the aircraft;
• an input hose connected to the number of heat exchangers and directly connected to the hydraulic fluid reservoir through a first hose connection;
• and;
• an output hose connected to the number of heat exchangers and directly connected to a return side of the electric motor driven pump through a second hose connection;
• wherein the number of heat exchangers are configured to cool hydraulic fluid of the aircraft hydraulic system as the electric motor driven pump pumps the hydraulic fluid through the aircraft hydraulic system under conditions wherein fuel tanks in the aircraft are empty, wherein the hydraulic fluid passes from the hydraulic fluid reservoir and through the input hose, the number of heat exchangers, and the output hose before entering the electric motor driven pump, and wherein a path of the hydraulic fluid passes from the hydraulic fluid reservoir and through the input hose, the number of heat exchangers, and the output hose before entering the electric motor driven pump without passing through a pump external to the aircraft.