gas turbine engine 10 includes in serial flow communication a fan section 14 a low pressure compressor 18 a high pressure compressor 22 a combustor 26 a high pressure turbine 30 and a low pressure turbine 34 the gas turbine engine 10 is circumferentially disposed about an engine centerline x during operation air is pulled into the gas turbine engine 10 by the fan section 14 pressurized by the compressors 18 and 22 mixed with fuel and burned in the combustor 26 the turbines 30 and 34 extract energy from the hot combustion gases flowing from the combustor 26 in a two spool design the high pressure turbine 30 utilizes the extracted energy from the hot combustion gases to power the high pressure compressor 22 through a high speed shaft 38 the low pressure turbine 34 utilizes the extracted energy from the hot combustion gases to power the low pressure compressor 18 and the fan section 14 through a low speed shaft 42 referring now to fig2 with continuing reference to fig1 a monitoring system 50 is secured to the engine 10 in this example the monitoring system 50 communicates with a multiple of data sources the sensors 54 distributed within the aircraft 12 facilitate communicating between the monitoring system 50 and data sources of the aircraft 12 in this example some of the sensors 54 are located outside the engine 10 near components of the aircraft 12 other than the engine 10 the examples described in this disclosure relating to the gas turbine engine 10 are not limited to the two spool architecture described and may be used in other architectures such as a single spool axial design a three spool axial design and still other architectures.