Abstract: A gas turbine engine digital electronic control is disclosed which is capable of maintaining safe, efficient engine thrust levels in the event of loss of communication with an aircraft flight computer. Specifically, a limited number of engine sensor inputs are used in combination with an engine performance schedule to derive total inlet pressure. A compressible flow calculation yields flight Mach number which is used in a power management module to control engine power settings, such as corrected fan speed in a turbofan engine. Various correction factors and scalars are provided to configure the control for a variety of installation configurations, as well as improve system accuracy.