The airplane has three hydraulic systems: A, B, and standby.
Standby system is used if system A and/or B pressure is lost.
Each hydraulic system has a fluid reservoir located in the main wheel well area.
System A and B reservoirs are pressurized by bleed air.
Both A and B hydraulic systems have an engine-driven pump and an AC electric motor-driven pump.
The system A engine-driven pump is powered by the No.1 engine and the system B engine-driven pump is powered by the No.2 engine.
An engine-driven hydraulic pump supplies approximately 6 times the fluid volume of the related electric motor-driven hydraulic pump.
The ENG 1 or ENG 2 pump ON/OFF switch controls the engine-driven pump output pressure.
The ELEC 2 or ELEC 1 pump ON/OFF switch controls the related electric motor-driven pump.
If an overheat is detected in either system, the related OVERHEAT light illuminates.

Test your knowledge of airplane hydraulic systems with this informative quiz! From the function of the standby system to the location of the fluid reservoirs, this quiz covers it all. Challenge yourself to remember which engine powers each system's pump and which switch controls the pump output pressure. Don't miss out on the opportunity to show off your hydraulic system expertise!