System and method for controlling a gas turbine engine supplying power to an aircraft

A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft, where the engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control system (102), which issues commands for controlling engine parameters comprising an acceleration reference signal, load shedding, variable geometry positioning, and fuel flow. The control system (102) may further issue commands for controlling the amount of power drawn. The control system may further use the reading to monitor the engine's condition.