A method of controlling a combustor of a gas turbine engine , the method comprising the steps supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split into a pilot fuel quantity and a main fuel quantity via a scheduled pilot fuel split, the pilot fuel split is the percentage of the pilot fuel quantity to the total fuel quantity, monitoring combustion instability, applying a steady state active pilot split offset to the scheduled pilot fuel split to create a steady state pilot fuel split, the steady state active pilot split offset being adjusted automatically when a predetermined temperature of the combustor is exceeded and/or a predetermined value of combustion instability is exceeded, characterised in that the method further includes the steps of monitoring a condition of the gas turbine engine that influences an air / fuel ratio in the combustor, disabling adjustment of the steady state active pilot split offset when said condition of the gas turbine engine is indicative of a transient condition and when a threshold value of combustion instability is exceeded, and applying a transient active pilot split offset to the steady state pilot fuel split while maintaining the total fuel quantity being supplied at any point in time, the transient active pilot split offset and the steady state active pilot split offset resulting in a total split offset, the total split offset being greater than the steady state active pilot split offset and a rate of change of the transient active pilot split offset being faster than a rate of change of the steady state active pilot split offset. the method comprising the steps supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split into a pilot fuel quantity and a main fuel quantity via a scheduled pilot fuel split, the pilot fuel split is the percentage of the pilot fuel quantity to the total fuel quantity, monitoring combustion instability, applying a steady state active pilot split offset to the scheduled pilot fuel split to create a steady state pilot fuel split, the steady state active pilot split offset being adjusted automatically when a predetermined temperature of the combustor is exceeded and/or a predetermined value of combustion instability is exceeded, characterised in that the method further includes the steps of monitoring a condition of the gas turbine engine that influences an air / fuel ratio in the combustor, disabling adjustment of the steady state active pilot split offset when said condition of the gas turbine engine is indicative of a transient condition and when a threshold value of combustion instability is exceeded, and applying a transient active pilot split offset to the steady state pilot fuel split while maintaining the total fuel quantity being supplied at any point in time, the transient active pilot split offset and the steady state active pilot split offset resulting in a total split offset, the total split offset being greater than the steady state active pilot split offset and a rate of change of the transient active pilot split offset being faster than a rate of change of the steady state active pilot split offset. <EOS>