B737 ng eec
Hi
I think i have figured out why the EEC needs static and ambient pressures to compute the mach number being the mach number TAS / LSS, TAS = EAS square root of the ratio of density at sea level in isa to ambient density and thus affected by temperature and pressure and LSS equal to 39 square root of temperature in degrees kelvin.
The question about why it needs the mach number still stands.
Many yhanks