ATPL Flight Planning and Monitoring
test bank contains questions pertaining to
033-05-01 Advanced flight planning aspects for jet aeroplanes
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Flight Planning and Monitoring
Flight Planning and Monitoring
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from the EASA ATPL
Flight Planning and Monitoring
- (Refer to CAP 697 - figure 4.2.2)Sector distance: 150 NMTemperature at MSL take-off: 30° CBrake release weight: 42500 kgCalculate the maximum short distance cruise pressure altitude:
- (Refer to CAP 697 - figure 4.5.1A)For the MRJT calculate the time, fuel, distance and TAS for an aircraft climbing to 23 000 ft with a brake release weight of 65 000 kg. Assume that the temperature is ISA – 10° C:
- (Refer to CAP 697 figure 4.3.1)For a flight of 2400 ground nautical miles the following apply:Temperature: ISA -1 deg CCruise altitude: 29 000 ftLanding mass: 45 000 kgTrip fuel available: 16 000 kgWhat is the maximum headwind component which may be accepted?
- (Refer to CAP 697 - figure 4.3.3C)An aircraft is to fly 2500 nm at 0.78M at an altitude of 35 000 ft. What is the fuel required and leg time. Assume that the aircraft (TOM 57 500 kg) will have a 50 knot tailwind and the temperature is ISA +10° .
- (Refer to CAP 697 - figure 4.3.3B)An aircraft is to fly 1000 nm at 0.78M at an altitude of 39 000 ft. What is the fuel required and leg time. Assume that the aircraft (TOM 45 000 kg) will have a 25 knot headwind and the temperature is ISA.
- The Final Reserve Fuel for aircraft with turbine power units should be:
- When the MRJT is holding which of the following assumptions are made:
- (Refer to CAP 697 - figure 4.3.1C)Given:Distance: 2000 NGMWind component: zeroLanding weight: 50000 kgIf an aircraft planned its initial cruise at FL370 and was then cleared to FL290 the effect on the fuel required is:
- What is the purpose of Decision Point Procedure?
- (Refer to CAP 697 - figure 4.4)The MRJT has to hold at a VOR at an altitude of 8 000 ft and a weight of 45 000 kg, what is the fuel flow?
- (Refer to CAP 697 - figure 4.2.1 table)For the MRJT the fuel mileage penalty for operating 2000 ft below OPTIMUM altitude using long range cruise is:
- The purpose of the decision point procedure is?
- (Refer to CAP 697 - figures 4.8.1 + 4.8.2)An aircraft is planned to fly a LRC at FL350, ISA -10° C, at an average gross cruise weight of 55000 kg and a Landing Weight (Without Tankered Fuel) of 47500 kg; the wind component is -30 kts and the trip distance 1600 NGM.Calculate the Break Even Fuel Price Destination Airport if the Fuel Price at Departure Airport is 75 cents/US Gallon.
- (Refer to CAP 697 - figure 4.4)Mean Gross Mass: 57 000 kgAltitude: 10 000 feetWhat is the fuel required for 45 minutes holding in a racetrack pattern?
- Given:Maximum allowable take-off mass: 64400 kgMaximum landing mass: 56200 kgMaximum zero fuel mass: 53000 kgDry operating mass: 35500 kgTraffic load: 14500 kgTrip fuel: 4900 kgTake-off fuel: 7400 kgFind: Maximum additional load.
- (Refer to CAP 697 figure 4.3.1C)Wind Component: +50 ktsTemperature Deviation: +10° CAltitude: 29 000 ftLanding Mass: 50 000 kgTrip Distance: 2000 NMWhat is the fuel required and trip time?
- An aeroplane has the following masses:Estimated LM = 50 000 kgTrip fuel = 4 300 kgContingency fuel = 215 kgAlternate fuel (final reserve included) = 2 100kgTaxi = 500 kgBlock fuel = 7 115 kgBefore departure the captain orders to make the block fuel 9 000 kg. The trip fuel in the operational flight plan should read:
- (Refer to CAP697 figure 4.5.4)A descent is planned at 0.74M/250KIAS from 35,000 ft to 5,000 ft.How much fuel will be consumed during this descent?
- (Refer to CAP 697 figures 4.5.2 & 184.108.40.206)Given:Distance C - D: 540 NMCruise 300 KIAS at FL 210Temperature Deviation from ISA: +20° CHeadwind component: 50 ktGross mass at C: 60 000 kgThe fuel required from C to D is:
- (Refer to CAP697 figures 4.5.2 & 220.127.116.11)For a flight from B to C:FL3100.74 MISA - 12° C957 NGM40kt tailwindWeight 50,100kgHow much fuel is required to fly to C?
- The Trip Fuel for a jet aeroplane to fly from the departure aerodrome to the destination aerodrome is 5 350 kg.Fuel consumption in holding mode is 6 000 kg/h. The quantity of fuel which is needed to carry out one go- around and land on the alternate airfield is 4 380 kg. The destination aerodrome has a single runway. What is the minimum quantity of fuel which should be on board at take-off?
- (Refer to CAP 697 figures 4.5.2 & 18.104.22.168)Given:Distance C - D: 680 NMLong Range Cruise at FL340Temperature Deviation from ISA: 0° CHeadwind component: 60 ktGross mass at C: 44 700 kgThe fuel required from C - D is:
- The final reserve fuel for aeroplanes with turbine engines is:
- (Refer to CAP 697 - figure 4.7.2)Determine the Diversion Distances to a diversion airfield from any point on track for the following:Speed: .70M/280Diversion Weight: 45,000 kgApproved time: 135 min
- Contingency fuel is carried to compensate for:deviation of an aircraft from the expected fuel consumption deviations from the forecast meteorological conditions deviations from the planned route and/or cruising levels/altitudes the extra fuel needed for Extended Range Twin OperationsThe correct combination is:
- (Refer to CAP 697 figure 22.214.171.124)Find the FUEL FLOW for the twin jet aeroplane with regard to the following data. Given:MACH .74 cruiseFlight level 310Gross mass 50000 kgISA conditions
- (Refer to CAP 697 - figure 4.5.1C)Given:Airfield elevation: 1982 mQNH: 996 mbTemperature: ISA +7° CCruise at: FL330Climb WC: +60 ktBrake Release Weight: 63000 kgThe airfield pressure altitude is:
- (Refer to CAP 697 - figure 4.6.1)Calculate the trip time and fuel required for a Gear Down Ferry Flight from the following:Sector distance 850 NMWind component 75 kt TailFL 240Landing weight 40000 kgOAT - 43° C
- Given:Maximum allowable take-off mass: 64 400 kgMaximum landing mass: 56 200 kgMaximum zero fuel mass: 53 000 kgDry operating mass: 35 500 kgEstimated load: 14 500 kgEstimated trip fuel: 4 900kgMinimum take-off fuel: 7 400 kgFind the maximum allowable take-off fuel:
- (Refer to CAP 697 - figure 4.2.2)If the gross brake release weight is 46000 kg, trip distance 150 NAM and temperature ISA +10° C, what is the short distance cruise?
- (Refer to CAP 697 - figures 4.3.5 + 4.4 + figure 10-12)The distance departure (MSL) to destination (MSL) 2000 NM, Wind Component 60kts Head, ISA -5° C, Brake release weight 57500 kg. Destination holding fuel, normal race track pattern, for 45 min at pressure altitude of 2500 ft at an estimated start weight of 44000 kg.Departure APU usage 50 min, Taxi time estimated at 15 min before take-off and 10 min at destination or alternate; all descents straight in. Air Conditioning packs at high flow from the departure to destination and for the diversion.Wing and engine anti-icing fuel for departure to destination, plus an hour during the diversion; climb and descent to be counted as cruising. Destination to Alternate distance is 300 NM, WC 20kts Tail; estimated landing weight at diversion is 42000 kg.Calculate the total fuel for this route:
- (Refer to CAP 697 - figures 4.8.1 + 4.8.2)An aircraft is planned to fly a LRC at FL350, ISA -10° C, at an average gross cruise weight of 55000 kg and a Landing Weight (Without Tankered Fuel) of 47500 kg; the wind component is -30 kts and the trip distance 1600 NGM.Calculate the % Surplus Fuel Burn:
- Given:Maximum allowable take-off mass: 64 400 kgMaximum landing mass: 56200 kgMaximum zero fuel mass: 53 000 kgDry operating mass: 35 500 kgEstimated load: 14 500 kgEstimated trip fuel: 4 900 kgMinimum take-off fuel: 7 400 kgFind: maximum additional load
- (Refer to figure 4.3.1C)For a flight of 2800 ground nautical miles the following applies:Head wind component: 15 ktTemperature: ISA + 15° CCruise altitude: 35000 ftLanding mass: 50000 kgThe (a) trip fuel and (b) trip time respectively are:
- (Refer to figure 4.3.5)The following apply:Temperature ISA +15° CBrake release mass 62000kgTrip time 5hr 20 minWhat is the trip fuel?
- (Refer to CAP697 - figure 4.5.1A)For the MRJT calculate the time, fuel, distance and TAS for an aircraft climbing to 33 000 ft from an airfield at an elevation of 3 000 ft with a brake release weight of 57 000 kg. Assume that the temperature is ISA -10° C.
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