control the control is programmed to take in the sensed information and identify a safe operating range for the gas turbine engine based upon damage information developed from the sensed information with regard to each of the blades an aircraft jet engine system incorporating a plurality of gas turbine engines wherein safe operating ranges are developed for each of the gas turbine engines is also disclosed as is a method of operating an aircraft jet engine system application_number US 201113289322 A description an intent of this application is to expand the useful safe operation of multiple engine aircraft with damage to multiple engines beyond the current minimum regulatory requirements or beyond the capabilities of engines even if they well exceed minimum requirements a gas turbine engine 10 such as a turbofan gas turbine engine circumferentially disposed about an engine centerline 12 is shown in fig1 a the engine 10 includes a fan 14 a compressor 15 16 a combustion section 18 and turbine sections 20 as is well known in the art air compressed in the compressor 15 16 is mixed with fuel which is burned in the combustion section 18 and expanded across turbine sections 20 the turbine sections 20 include rotors that rotate in response to the expansion driving the compressor 15 16 and fan 14 this structure is shown somewhat schematically in fig1 a while one example gas turbine engine is illustrated it should be understood this invention extends to.