Abstract: By utilizing compensating parameters required for steady state operation of a gas turbine engine with processed variables of compressor speed, compressor pressure and altitude a derivative of the variable desired is synthesized and compared to the actual value in a closed-loop system for limiting the rate of change of fuel flow in an engine transient condition. In a twin spool engine a function generator responding to speed of the low pressure compressor and altitude generates a signal indicative of rate of change of the speed of the high pressure compressor. The signal is compensated for time constants consistant with the dynamics of the engine and compared with a compensated actual high pressure compressor speed. The error produced with a gain generated from corrected high pressure compressor speed inputs the main electronic digital fuel control.