The JAA
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
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| Sample Questions
from the JAA ATPL
Flight Planning and Monitoring
Test Bank |
- Which is true regarding a balanced field?
- (Refer to CAP 697 figure 4.5.3.2)Find the SPECIFIC RANGE for the twin jet aeroplane flying below the optimum altitude (range loss = 6%) and using the following data:MACH .74 CRUISEFlight level 310Gross mass: 50 000 kgISA conditions
- The following fuel consumption figures are given for a jet aeroplane:Standard taxi fuel: 600 kgAverage cruise consumption: 10 000 kg/hHolding fuel consumption at 1500 ft above alternate airfield elevation: 8 000 kg/hFlight time from departure to destination: 6 hoursFuel for diversion to alternate: 10 200 kgThe minimum ramp fuel load is:
- (Refer to CAP 697 figure 4.3.3A)Given:Cruise M0.78FL 28050,000 kg200 nmWind component 30 kt HeadFind the fuel required.
- (Refer to CAP 697 - figure 4.7.1a)An aircraft at a weight of 50000 kg has an engine and pressurisation failure simultaneously. The forecast is icing conditions at FL100, -15° C and a 60 kt tailwind and for the 750 NM distance from the CP to the diversion airfield.Calculate the LRC Critical Fuel Reserve needed.
- (Refer to CAP 697 - figure 4.3.1C)Wind Component: -50 ktsTemperature Deviation: +15° CAltitude: 25 000 feetLanding Mass: 40 000 kgTrip Distance: 2000 NMWhat is the fuel required and trip time?
- (Refer to CAP 697 - figure 4.2.2)The aircraft has to fly a leg of 100 NM with a brake release weight of 55 000 kg. What is the cruise altitude?
- (Refer to CAP 697 figures 4.5.2 & 4.5.3.1)Long range cruise at FL340Distance C-D: 3200 nmTemperature: deviation from ISA +12CTailwind component: 50 ktGross mass at C: 55,000 kgThe fuel required C-D is:
- (Refer to CAP697 - figure 4.4)Mean Gross Mass: 53 000 kgAltitude: 20 000 feetWhat is the fuel required for 60 minutes holding in a racetrack pattern?
- (Refer to CAP 697 - table 4.2.1)For the MRJT 1 the fuel mileage penalty for operating 12 000 ft below OPTMUM altitude using long range cruise is:
- (Refer to CAP697 figure 4.4)Given: Mean gross mass = 47 000 kgThe fuel required for 45 minutes holding in a racetrack pattern at 5000ft is:
- (Refer to Flight Planning Manual figure 4.7.2)An aircraft on an extended range operation is required never to be more than 120 minutes from an alternate, based on 1 engine inoperative LRC conditions in ISA. Using the above table and a given mass of 40000 kg at the most critical point, the maximum air distance to the relevant alternate is:
- (Refer to figures 033_209A, 033_209B)Assuming a departure/destination fuel price ratio of 0.91, the commander decides to optimize fuel tankering by using the following data:Cruise flight level: FL 350Air distance to be covered: 2 500 NMPlanned take-off mass: 200 000 Kg (with the minimum prescribed fuel quantity of 38 000 Kg that includes a trip fuel of 29 000 Kg)Maximum landing mass: 180 000 KgMaximum take-off mass: 205 000 KgMaximum tank capacity: 40 000 KgThe additional fuel quantity will be:
- Following in-flight depressurisation, a turbine powered aeroplane is forced to divert to an en-route alternate airfield. If actual flight conditions are as forecast, the minimum quantity of fuel remaining on arrival at the airfield will be:
- (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: .74M/330Diversion Weight: 38,000 kgApproved time: 135 min
- Given:DOM: 33 000 kgTraffic load: 8 100 kgFinal fuel reserve: 983 kgAlternate fuel: 1 100 kgContingency fuel: 102 kgThe estimated landing mass at an alternate airport is:
- (Refer to CAP 697 - figure 4.5.3.1)A twin-engine jet aeroplane (both engines operating) commences cruise phase of the flight at FL 350 with a mass of 44 000 kg. Temperature is ISA +10° C (remains constant for the entire flight). After 2 hours of cruise at mach number corresponding to most economical cruise the aircraft mass will be:
- (Refer to CAP 697 - figure 4.2.1)For the MRJT 1, what is the optimum altitude for a cruise at 0.74M with a brake release weight of 66 000 Kg?
- When the MRJT is holding which of the following assumptions are correct?
- (Refer to CAP 697 figures 4.2.1, 4.2.2, 4.5.3.2)Given:Brake release weight: 45,000 kgTrip distance: 120 nmTemperature: ISA -10° CCruise: 0.74 MFind optimum pressure altitude and TAS.
- (Refer to CAP 697 - figure 4.2.1)Long Range Cruise flight at FL370 from A to E with a nominated alternate airfield. Airfield elevation at A is 3000 ft; mean sea level at E and the Alternate. The gross take-off weight at A is 56000 kg. The estimated landing weights at E and the alternate are 46000 kg and 43000 kg.The aircraft track is 180° (T) and variation 10° E. If the variation was 10° W what is the amended lowest optimum IFR level ?
- The cost index adjustment for the MRJT 1 is used when the FMS is in:
- (Refer to CAP 697 - figure 4.5.1A)For the MRJT calculate the time, fuel, distance and TAS for an aircraft climbing to 33 000 ft with a brake release weight of 57 000 kg. Assume that the temperature is ISA – 10° C:
- (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: .74M/330Diversion Weight: 38,000 kgApproved time: 180 min
- (Refer to figures 4.5.2 & 4.5.3.4)Given:Distance B - C: 350 NMCruise 300 KIAS at FL 210 Temperature: - 40° CTailwind component: 70 ktGross mass at B: 53 200 kgThe fuel required from B - C is?
- (Refer to CAP 697 - figure 4.2.1)Given a Brake Release Mass of 56000 kg the Optimum Cruise Altitude at .78 Mach is:
- (Refer to CAP 697 - figure 4.4)The MRJT has to hold at a VOR at an altitude of 36 000 ft and a weight of 55 000 kg, what is the fuel flow?
- Reserve Fuel consists of:
- (Refer to CAP 697 figure 4.2.1 & paragraph 2.1 of MRJT1)Find the FUEL MILEAGE PENALTY for the twin jet aeroplane with regard to the given FLIGHT LEVEL.Given:Long range cruiseCruise mass = 53000 kgFL 310
- (Refer to figure 4.3.3C)Given:Ground distance to destination aerodrome: 1 600 NMHeadwind component: 50 ktFL 330Cruise 0.78 MachISA +20° CEstimated landing weight: 55 000 kgFind: simplified flight planning to determine estimated trip fuel and trip time.
- When the MRJT FMS is used in the ECON Mode:
- (Refer to CAP 697 - figure 4.3.4)Route distance 600 NMWind Component -130 ktsEstimated landing weight: 45 000 kg300kt cruise @ FL200, ISA -10° CCalculate the fuel required and flight time:
- (Refer to CAP 697 - figure 4.5.2)Given a leg distance of 650 NAM, with a TAS of 400 and wind component of – 30 kts. Calculate the NGM:
- (Refer to figure 4.3.1C)For a flight of 2400 ground nautical miles the following apply:Tail wind component: 25 ktTemperature: ISA -10° CCruise altitude: 31 000 ftLanding mass: 52 000 kgThe (a) trip fuel and (b) trip time respectively are:
- (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 destination landing weight, after holding for 20 minutes.
- The required time for final reserve fuel for turbojet aeroplane is:
- (Refer to CAP 697 - figure 4.3.1B)LRC trip distance: 1000 NMCruise: FL290Wind component: +50 ktISA - 10° CEstimated landing weight: 40,000 kgCalculate the fuel required and flight time:
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