How many pumps power hydraulic systems 1 and 2?

The correct answer indicates that each of the hydraulic systems 1 and 2 on the aircraft is powered by one electric pump and one engine-driven pump. This dual-pump configuration ensures reliability and redundancy in the hydraulic system, allowing for continued operation even if one pump fails.

The electric pump provides the ability to operate the hydraulic systems on the ground or during low-thrust conditions, while the engine-driven pump maintains hydraulic pressure during normal flight operations when the engines are running. This combination is crucial for ensuring that basic flight controls and essential systems receive continuous hydraulic power, enhancing both safety and operational reliability.

In the context of hydraulic system design for aircraft, having both electric and engine-driven pumps allows for a backup option, ensuring that if one power source becomes inoperative, the other can still maintain hydraulic pressure. Redundant systems are a standard practice in aviation safety protocols to minimize the impact of component failures on flight operations.