A control system for a gas turbine engine comprising an engine core comprising combustion equipment, a first turbine, a second turbine, a first compressor, a second compressor, a first core shaft connecting the first turbine to the first compressor, and second core shaft connecting the second turbine to the second compressor, the second turbine, second compressor, and second core shaft are arranged to rotate at a higher rotational speed than the first core shaft; the first compressor comprising at least one variable stator vane configured to move between an open position and a closed position for controlling the angle at which gas enters the engine core; and a bypass passage provided within the engine core for directing gas flow from the second compressor to the second turbine to bypass the combustion equipment, comprising at least one valve for controlling the amount of air that enters the bypass passage; wherein the control system is configured to adjust the at least one variable stator vane according to a nominal schedule so as to control the angle at which gas enters the engine core, the nominal schedule being dependent on the semi-dimensional rotational speed of the first compressor, wherein the adjustment of the at least one variable stator vane is configured to be biased to a more open position from the nominal schedule in response to a first input which indicates that the engine core temperature T41 is above or at a first predetermined threshold; and wherein the control system is configured to adjust the at least one valve according to a nominal schedule so as to control the amount of air that enters the bypass passage, the nominal schedule being dependent on a power setting parameter and/or the altitude of the gas turbine engine, wherein the control system is configured to bias biased the at least one valve from the nominal schedule in response to a second input; wherein the second input indicates that the compressor delivery temperature T30 is above or at a second predetermined threshold. the first compressor comprising at least one variable stator vane configured to move between an open position and a closed position for controlling the angle at which gas enters the engine core; and a bypass passage provided within the engine core for directing gas flow from the second compressor to the second turbine to bypass the combustion equipment, comprising at least one valve for controlling the amount of air that enters the bypass passage; wherein the control system is configured to adjust the at least one variable stator vane according to a nominal schedule so as to control the angle at which gas enters the engine core, the nominal schedule being dependent on the semi-dimensional rotational speed of the first compressor, wherein the adjustment of the at least one variable stator vane is configured to be biased to a more open position from the nominal schedule in response to a first input which indicates that the engine core temperature T41 is above or at a first predetermined threshold; and wherein the control system is configured to adjust the at least one valve according to a nominal schedule so as to control the amount of air that enters the bypass passage, the nominal schedule being dependent on a power setting parameter and/or the altitude of the gas turbine engine, wherein the control system is configured to bias biased the at least one valve from the nominal schedule in response to a second input; wherein the second input indicates that the compressor delivery temperature T30 is above or at a second predetermined threshold.