Abstract: A method and electronic device for providing an optimal quantity of aircraft fuel. The method comprises collecting recorded flight data from past flights of an aircraft; determining aircraft specific performance correction parameters per flight phase, using the recorded flight data; collecting a flight plan of the aircraft; determining the total fuel required for the given flight plan, using the aircraft specific performance correction parameters; determining a single synthetic drag factor (?DFMS) and a single synthetic fuel factor (?FFFMS) that, when used by the aircraft FMS, yield the said total fuel required for the given flight plan; receiving an estimated total fuel required determined by the aircraft FMS based on the flight plan, the single synthetic drag factor (?DFMS) and the single synthetic fuel factor (?FFFMS). The method allows reducing the fuel weight and total flight cost, and is particularly advantageous for FMS which only admit one single drag factor and one single fuel factor.

Abstract: A method and electronic device for providing an optimal quantity of aircraft fuel. The method comprises collecting recorded flight data from past flights of an aircraft; determining aircraft specific performance correction parameters per flight phase, using the recorded flight data; collecting a flight plan of the aircraft; determining the total fuel required for the given flight plan, using the aircraft specific performance correction parameters; determining a single synthetic drag factor (?DFMS) and a single synthetic fuel factor (?FFFMS) that, when used by the aircraft FMS, yield the said total fuel required for the given flight plan; receiving an estimated total fuel required determined by the aircraft FMS based on the flight plan, the single synthetic drag factor (?DFMS) and the single synthetic fuel factor (?FFFMS). The method allows reducing the fuel weight and total flight cost, and is particularly advantageous for FMS which only admit one single drag factor and one single fuel factor.

Abstract: A cabin pressure assessment system for an aircraft includes a plurality of polling devices within an internal cabin of the aircraft. The plurality of polling devices are associated with passenger seats onboard the aircraft. A cabin pressure assessment control unit is communicatively coupled to the plurality of polling devices. The cabin pressure assessment control unit is configured to receive cabin pressure comfort data from the plurality of polling devices.