The EASA
ATPL Flight Planning and Monitoring
test bank contains questions pertaining to
033-06-01 Extraction of data
. The following list contains only a relatively small percentage of the pertinent
questions. Our software, which you are free to download now at no cost, will
generally contain a much more complete set of questions associated with this
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the questions of the
Flight Planning and Monitoring
test bank.
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That said, while the following questions are intended
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| Sample Questions
from the EASA ATPL
Flight Planning and Monitoring
Test Bank |
- (Refer to figure 4.3.1C)For a flight of 2000 ground nautical miles, cruising at 30000 ft, within the limits of the data given, a headwind component of 25 kt will affect the trip time by approximately:
- (Refer to CAP 697 figure 4.4)Given for the twin jet aeroplane:Estimated mass on arrival at the alternate: 50 000 kgElevation at destination aerodrome: 3 500 ftElevation at alternate aerodrome: 30 ftFind: Final reserve fuel.
- (Refer to Jeppesen Manual MUNICH ILS Rwy 26R (11-4) or figure AP-01)The ILS frequency and identifier are:
- (Refer to CAP 697 - figure 3.2)Cruising Level: 15 000 ftOutside Air Temperature: -20° CPower: High SpeedWhat is the range with 45 minutes reserve fuel at 45% power?
- Given:Distance X to Y: 2700 NMMach Number: 0.75Temperature: -45° CMean wind component ON: 10 ktTailwind Mean wind component BACK: 35 kt tailwindThe distance from X to the point of equal time (PET) between X and Y is:
- (Refer to CAP 697 figure 4.5.3.1)The aeroplane gross mass at top of climb: 61 500 kgThe distance to be flown: 385 NM at FL 350OAT: -54° CWind component: 40 kt tailwindUsing long range cruise procedure what fuel is required?
- (Refer to CAP 697 figure 4.2.1)Given:Cruise mass: 54 000 kgLong Range Cruise or 0.74 MachFind the OPTIMUM ALTITUDE for the twin - jet aeroplane.
- (Refer to Jeppesen Manual - LONDON HEATHROW ILS DME Rwy 09R (11-1) or figure AP-12)The Minimum Descent Altitude (MDA) for an ILS approach, glide slope out, is:
- Given the following:D = flight distanceX = distance to Point of Equal TimeGSo = groundspeed outGSr = groundspeed returnThe correct formula to find distance to Point of Equal Time is:
- (Refer to Route Manual chart E(HI)4 or figure HI-11 and CAP 697 figure 4.3.2A)Planning a flight from Paris Charles de Gaulle (N49 00.9 E002 36.9) to London Heathrow (N51 29.2 W000 27.9) for a twin-jet aeroplane. Preplanning:Power setting: Mach= 0.74Planned flight level: FL 280Landing Mass in the fuel graph: 50 000 kgTrip distance used for calculation: 200 NMWind from Paris to London: 280° /40 ktFind the estimated trip fuel.
- (Refer to figure 4.4)Planning a flight from Paris Charles de Gaulle to London Heathrow for a twin-jet aeroplane.Preplanning:Dry Operating Mass (DOM): 34 000 kgTraffic Load: 13 000 kgThe holding is planned at 1 500 ft above alternate elevation (256 ft)The holding is planned for 30 minutes with no reductionsDetermine the Estimated Landing Mass at alternate Manchester:
- (Refer to CAP 697 figure 4.5.1C)Find: Time, Fuel, Still Air Distance and TAS for an enroute climb 280/.74 to FL 350.Given:Brake release mass: 64 000 kgISA +10° CAirport elevation 3 000 ft
- Given the following data find the distance and time to the PSR:Leg Distance: 1190 NMTAS Out: 210 knotsWind Component Out: - 30 knotsFuel Flow Out: 2400 kg/hrTAS Home: 210 knotsWind Component: + 30 knotsFuel Flow Home: 2000 kg/hrFlight Plan Fuel: 20 500 kgReserves: 6000 kg
- If CAS is 190 kts, Altitude 9000 ft. Temp. ISA - 10° C, True Course (TC) 350° , W/V 320/40, distance from departure to destination is 350 NM, endurance 3 hours, and actual time of departure is 1105 UTC. The Point of Equal Time (PET) is reached at:
- (Refer to CAP 697 - figure 3.4)Given:Cruise altitude: 19 000 ftOAT: -14° CPower setting: 45%Find TAS:
- (Refer to CAP 697 figure 4.2.1 and table 4.2.1)Given:Cruise weight: 53 000 kgLRC/ M0.74Cruise at FL310What is the fuel penalty?
- Given flight details:Distance: 1825 NMAll engines TAS: 300 ktOne engine inoperative TAS: 250 ktW/C outbound: 10 kt headW/C Inbound: 20 kt headWhat is the time and distance to the one engine inoperative PET?
- (Refer to figure 4.7.3)Given:Diversion distance: 720 NMTail wind component: 25 ktMass at point of diversion: 55 000 kgTemperature: ISADiversion fuel available: 4 250 kgWhat is the minimum pressure altitude at which the above conditions may be met?
- (Refer to Route Manual chart SID PARIS Charles-De-Gaulle (20-3) or figure AP-03)Planning a IFR flight from Paris (Charles de Gaulle) to London (Heathrow).Find the elevation of the departure aerodrome.
- (Refer to CAP 697 - pages 26 & 27 - or figure 10-12)The Simplified Planning graphs require a fuel of 6000 kg. Given:Estimated taxi time: 20 minutesAPU running time: 60 minutesEngine and wing anti-icing: 40 minutesThe total fuel required is:
- (Refer to CAP 697 - figure 3.3)At 65%, 2400 rpm power what is the fuel flow and MAP at 9000 ft?
- (Refer to CAP 697 figure 4.3.1)Trip distance: 1900 NMFuel on board: 15 000 kgLanding weight: 50 000kgWhat is the minimum pressure altitude for this flight?
- (Refer to Jeppesen Manual LONDON HEATHROW ILS DME Rwy 09L (11-2) or figure AP-05).The decision altitude for an ILS straight-in landing is:
- (Refer to figure 4.5.3.1)Given:Flight time from top of climb to the enroute point in FL280: 48 minCruise procedure is long range cruise (LRC)Temp: ISA -5° CTake-off mass: 56 000 kgClimb fuel: 1 100 kgFind: distance in nautical air miles (NAM) for this leg and fuel consumption:
- (Refer to CAP697 figure 4.5.3.1)Given:FL330OAT -63° CWeight 50 500 kgWhat is TAS?
- (Refer to figure 2-1)Given:FL 75OAT: +5° CDuring climb: average head wind component 20 ktTake-off from MSL with the initial mass of 3 650 lbsFind the still air distance (NAM) and ground distance (NM) using the graph TIME, FUEL, DISTANCE TO CLIMB:
- (Refer to figure 4.5.1C)Given:Brake release mass: 62 000 kgTemperature: ISA + 15° CThe fuel required for a climb from Sea Level to FL330 is:
- (Refer to CAP 697 - figure 3.5)Calculate the Endurance with and without reserves, given:Cruise Pressure Altitude: 14 000 ft65% power
- (Refer to CAP 697 figure 4.5.4)Planning an IFR-flight from Paris to London for the twin jet aeroplane.Given:Estimated Landing Mass: 49 700 kgFL 280W/V 280° /40 ktAverage True Course: 320° Procedure for descent: .74 M/250 KIASDetermine the distance from the top of descent to London (elevation 80 ft).
- (Refer to CAP 697 - figures 3.3 & 3.4)Calculate the fuel used in lbs, the Manifold Pressure and the time taken in the cruise, given:55% power set at 2200 rpmCruise Pressure Altitude: 12 000 ftAmbient Temperature: -6° CLeg Distance: 287 NMWind Component: – 16 kts
- If CAS is 190 kts, Altitude 9000 ft, Temp. ISA - 10° C, True Course (TC) 350° , W/V 320/40, distance from departure to destination is 350 NM, endurance 3 hours and actual time of departure is 1105 UTC.The distance from departure to Point of Equal Time (PET) is:
- (Refer to CAP697 figure 4.2.1)Given:Cruise mass 54 000 kgLRC / 0.74MFind Optimum Altitude.
- (Refer to figure 4.2.2)Find the SHORT DISTANCE CRUISE ALTITUDE for the twin jet aeroplane.Given:Brake release mass: 40 000 kgTemperature: ISA +20° CTrip distance: 150 Nautical Air Miles (NAM)
- (Refer to figure 2-2-3)Given:FL 75OAT +10° CLean mixture @ 2300 RPMFind the Fuel flow in gallons per hour (GPH) and TAS.
- (Refer to CAP 697 - figure 3.4)For the MEP, if the OAT is -20° C at 19 000 ft the TAS at 45% power is:
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