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EN Flight Performance and Planning - EASA PPL(A) - Private Pilot Licence (Aeroplane)
Questions Flight Performance and Planning - EASA PPL(A) aeroplane theory
Given the following information, what range can be achieved? Outside air temperature: 22° C Pressure altitude: 2000 ft Power: 55 % See annex (PFP-013)
Given the following conditions, the TAS equals... Outside air temperature: 10° C Pressure altitude: 6000 ft Power: 65 % See annex (PFP-014)
Given the following conditions, the TAS equals... Outside air temperature: -2° C Pressure altitude: 8000 ft Power: 75 % See annex (PFP-014)
Which maximum rate of climb can the aircraft reach at 9000 ft pressure altitude and OAT 12° C? See annex (PFP-011)
Which is the maximum rate of climb for the aircraft at 6500 ft pressure altitude and an OAT of 0° C? See annex (PFP-011)
Using linear interpolation in PFP-012, what TAS and fuel flow correspond to 60% power at pressure altitude 6000 ft and temperature ISA −20 °C?
Using PFP-012, what TAS and fuel flow correspond to 70% power at pressure altitude 6000 ft and temperature ISA −20 °C?
What is the fuel flow and the true airspeed for cruise flight with 60 % power in flight level 85 at an OAT of -25° C? See annex (PFP-014)
At which airspeed do you climb to flight level (FL) 75 after a departure from an airfield which is located at a pressure altitude of 3000 ft with an initial mass of 3000 lbs? OAT at airfield: 25° C OAT in FL 75: 0° C See annex (PFP-023)
What is the required fuel to climb from FL 65 to FL 95 under the following conditions? Aircraft mass: 3000 lb. OAT in FL 65: -5° C OAT in FL 95: -15° C See annex (PFP-023)
