is used as one of the possible minimum data sets for the calculation although more and or different data can be utilized to calculate the same parameters and or improve the precision of the calculation v air u2014 air speed p lb p rb u2014 left and right brake pressure v g u2014 ground speed a x u2014 longitudinal acceleration a c u2014 vertical acceleration e rpm u2014 engine rpm s spoiler u2014 spoiler setting s airbrake u2014 airbrake setting s aileron u2014 aileron setting c flap u2014 flap configuration o pitch u2014 pitch s rt u2014 reverse thrust setting s t u2014 engine thrust setting t air u2014 air temp p alt u2014 pressure altitude p air u2014 air pressure h u2014 relative humidity u03b4 runway u2014 runway elevation m landing u2014 landing mass e type u2014 engine type n engine u2014 number of engines ty tire u2014 tire type ty aircraft u2014 aircraft type 6 2 u2014 the method calculates through a three dimensional dynamic model all relevant physical processes involved in the aircraft landing maneuver and separates them so they are individually available for use the first intermediate result of the method is the time or distance history of all relevant separated interdependent decelerations generated by the different systems in an aircraft these decelerations are cumulatively measured by the onboard measurement system and reported in the flight data stream the separated decelerations calculated from the different physical processes make.