SENSORIZACIÓN
5.3. Pruebas a los potenciómetros y elección final
C) BERMUDAS.
D) either GANDER or BERMUDAS.
23863. (AIR: atpl, ir; HELI: atpl, ir)
(Refer to Jeppesen Student Route Manual chart E(HI)1)
An aircraft has to fly from the airport at Aberdeen (57°19 N
002°16 W) to the airport at Benbecula (57°29 N 007°22 W).
Given:
Time to climb: 11 min Time to descend: 9 min TAS: 170 kts
W/V: 230/50
What is the flight time during the cruise?
A) 16 min B) 47 min C) 28 min
#D) 54 min
28322. (AIR: atpl)
LFPG ILS Rwy 09: The ILS localizer course is:
A) 100°
#B) 088°
C) 118°
D) 268°
28344. (AIR: atpl, ir; HELI: atpl, ir)
Which approach segment starts at the point were you report established ?
A) Final approach.
B) Initial approach.
C) Go around.
#D) Intermediate approach.
28345. (AIR: atpl, ir; HELI: atpl, ir)
Which approach segment starts at the FAF and ends at the MAP?
A) Initial approach.
#B) Final approach.
C) Go around.
D) Intermediate approach.
033-05 JET AEROPLANES FLIGHT PLANNING 50
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1128 (B) 1136 (D) 1140 (B) 1143 (B) 1148 (A) 1149 (C) 1151 (D) 1152 (B) 1160 (C) 1162 (D)
033-05-01 Advanced flight planning aspects for jet aeroplanes 1128. (AIR: atpl)
What is decision point procedure? It is a procedure to reduce the amount of fuel carried on a flight by:
A) reducing contingency fuel from 10% to 5% of trip fuel.
#B) reducing contingency fuel to only that required from decision point to destination.
C) reducing trip fuel to only that required from decision aerodrome to destination.
D) reducing trip distance.
1136. (AIR: atpl)
(Refer to figures 033-23) Given:
Brake release mass: 62.000 kg Temperature: ISA + 15 °C
The fuel required for a climb from Sea Level to FL330 is:
A) 1.800 kg B) 1.650 kg C) 1.750 kg
#D) 1.700 kg 1140. (AIR: atpl)
(Refer to figure 033-21)
The fuel required for 30 minutes holding, in a racetrack pattern, at PA 1.500 ft, at mean gross mass of 45.000 kg, is:
A) 1.010 kg
#B) 1.090 kg C) 1.310 kg D) 2.180 kg
1143. (AIR: atpl)
(Refer to figures 033-25 and 033-36) Given:
Distance B - C: 350 NM
Cruise 300 KIAS at FL210 Temperature: - 40 °C Tailwind component: 70 kts
Gross mass at B: 53.200 kg
The fuel required from B - C is?
A) 1.810 kg
#B) 1.940 kg C) 2.800 kg D) 2.670 kg
1148. (AIR: atpl)
(Refer to figure 033-21)
The fuel required for 45 minutes holding, in a racetrack pattern, at PA 5.000 ft, mean gross mass 47.000 kg, is:
#A) 1.635 kg B) 1.090 kg C) 1.690 kg D) 1.125 kg
1149. (AIR: atpl)
(Refer to figure 033-19) Given:
Head wind component 50 kts Temperature ISA + 10 °C Brake release mass 65.000 kg Trip fuel available 18.000 kg
What is the maximum possible trip distance?
A) 3.480 NM B) 3.100 NM
#C) 2.740 NM D) 2.540 NM
1151. (AIR: atpl)
(Refer to figure 033-15)
For a flight of 2.800 ground nautical miles the following applies:
Head wind component: 15 kts Temperature: ISA + 15 °C Cruise altitude: 35.000 ft Landing mass: 50.000 kg
The trip fuel and trip time respectively are:
A) 20.000 kg; 7 hrs 00 min.
B) 16.200 kg; 6 hrs 20 min.
C) 17.000 kg; 6 hrs 10 min.
#D) 17.600 kg; 6 hrs 50 min.
1152. (AIR: atpl)
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/hrs. 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 takeoff?
A) 13.000 kg
#B) 13.230 kg
C) 14.730 kg D) 11.730 kg 1160. (AIR: atpl)
(Refer to figure 033-19)
For a flight of 2.800 ground nautical miles the following applies:
Head wind component: 20 kts Temperature: ISA + 15 °C Brake release mass: 64.700 kg
The trip fuel and trip time respectively are:
A) 16.200 kg; 6 hrs 20 min.
B) 15.800 kg; 6 hrs 15 min.
#C) 17.000 kg; 6 hrs 45 min.
D) 18.400 kg; 7 hrs 00 min.
1162. (AIR: atpl)
A turbo-jet AC is enroute to an isolated destination. On top of taxi, trip and contingency fuel, what fuel is required?
A) Greater of 45 mins + 15% of trip or 2 hours.
B) 30 mins holding at 450 m AMSL.
C) 30 mins holding at 450 m AAL.
#D) 2 hours at normal cruise consumption.
033-05 JET AEROPLANES FLIGHT PLANNING 51
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1163 (B) 1178 (D) 1179 (B) 1184 (A) 1186 (C) 1189 (B) 1196 (B) 1197 (B) 1198 (A)
1163. (AIR: atpl)
(Refer to figures 033-25 and 033-28) Given:
Distance C-D: 680 NM
Long Range Cruise at FL340
Temperature Deviation from ISA: 0 °C Headwind component: 60 kts
Gross mass at C: 44.700 kg
The fuel required from C - D is:
A) 3.400 kg
#B) 3.700 kg C) 3.100 kg D) 4.000 kg
1178. (AIR: atpl)
(Refer to figure 033-19) The following apply:
Temperature ISA +15 °C
Brake release mass 62.000 kg Trip time 5 hrs 20 min
What is the trip fuel?
A) 13.800 kg.
B) 13.000 kg.
C) 13.200 kg.
#D) 13.500 kg.
1179. (AIR: atpl)
Which is true regarding a balanced field?
A) Provides largest gap between net and gross margins.
#B) Provides minimum field length required in the case of an engine failure.
C) Takeoff distance will always be more than stopping distance.
D) Distances will remain equal, even if engine failure speed is changed.
1184. (AIR: atpl)
(Refer to figure 033-15)
For a flight of 2.400 ground nautical miles the following apply:
Tail wind component: 25 kts Temperature: ISA -10 °C Cruise altitude: 31.000 ft Landing mass: 52.000 kg
The trip fuel and trip time respectively are:
#A) 14.200 kg; 5 hrs 30 min.
B) 16.200 kg; 5 hrs 45 min.
C) 13.600 kg; 6 hrs 30 min.
D) 12.000k g; 5 hrs 15 min.
1186. (AIR: atpl)
(Refer to figure 033-19) The following apply:
Tail wind component 10 kts Temperature ISA +10 °C
Brake release mass 63.000 kg Trip fuel available 20.000 kg
What is the maximum possible trip distance?
A) 3.500 NM B) 3.640 NM
#C) 3.740 NM D) 3.250 NM
1189. (AIR: atpl)
(Refer to figures 033-25 and 033-35) Given:
Distance B-C: 1.200 NM Cruise Mach 0,78 at FL300
Temperature Deviation from ISA: -14 °C Tailwind component: 40 kts
Gross mass at B: 50.200 kg
The fuel required from B to C is:
A) 5.850 kg
#B) 6.150 kg C) 7.300 kg D) 7.050 kg
1196. (AIR: atpl)
(Refer to figures 033-25 and 033-36) Given:
Distance C-D: 540 NM Cruise 300 KIAS at FL210
Temperature Deviation from ISA: +20 °C Headwind component: 50 kts
Gross mass at C: 60.000 kg
The fuel required from C to D is:
A) 3.680 kg
#B) 4.200 kg C) 3.350 kg D) 4.620 kg
1197. (AIR: atpl) Given:
Dry operating mass (DOM): 33.510 kg Load: 7.600 kg
Trip fuel (TF): 2.040 kg Final reserve fuel: 983 kg Alternate fuel: 1.100 kg
Contingency fuel: 5% of trip fuel
Which of the listed estimated masses is correct?
A) Estimated takeoff mass is 45.233 kg.
#B) Estimated landing mass at destination is 43.295 kg.
C) Estimated landing mass at destination is 43.193 kg.
D) Estimated takeoff mass is 43.295 kg.
1198. (AIR: atpl)
What is the purpose of decision point procedure?
#A) Carry minimum fuel to increase Traffic Load.
B) Increase safety of the flight.
C) Reduce landing mass to avoid stressing the aircraft.
D) To assist in decision making at refuelling.
033-05 JET AEROPLANES FLIGHT PLANNING 52
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1201 (C) 1203 (D) 1204 (D) 1206 (D) 1207 (D) 1225 (C) 2181 (A) 2251 (B) 1201. (AIR: atpl)
Turbo-jet AC:
Taxi fuel: 600 kg
Fuel flow cruise: 10.000 kg/hrs Fuel flow hold: 8.000 kg/hrs Alternate fuel: 10.200 kg Flight time: 6 hours
Visibility at destination: 2.000 m What is the minimum ramp fuel?
A) 80.500 kg B) 79.200 kg
#C) 77.800 kg D) 76.100 kg 1203. (AIR: atpl) Given:
Maximum allowable takeoff mass: 64.400 kg Maximum landing mass: 56.200 kg
Maximum zero fuel mass: 53.000 kg Dry operating mass: 35.500 kg Estimated load: 14.500 kg Estimated trip fuel: 4.900kg Minimum takeoff fuel: 7.400 kg
Find the maximum allowable takeoff fuel:
A) 8.600 kg B) 11.400 kg C) 14.400 kg
#D) 11.100 kg 1204. (AIR: atpl)
Following in-flight depressurisation, a turbine powered
aeroplane is forced to divert to an enroute alternate airfield.
If actual flight conditions are as forecast, the minimum
quantity of fuel remaining on arrival at the airfield will be:
A) at least equivalent to 45 minutes flying time.
B) at least equivalent to the quantity required to fly to another aerodrome in the event that weather conditions so
require.
C) laid down by the operator, with the quantity being specified in the operating manual.
#D) at least equivalent to 30 minutes flying time.
1206. (AIR: atpl)
(Refer to figure 033-15)
For a flight of 2.400 ground nautical miles the following apply:
Temperature: ISA -10 °C Cruise altitude: 29.000 ft Landing mass: 45.000 kg
Trip fuel available: 16.000 kg
What is the maximum headwind component which may be accepted?
A) zero B) 15 kts C) 70 kts
#D) 35 kts
1207. (AIR: atpl)
(Refer to figure 033-20) Given:
Distance to Alternate: 450 NM
Landing mass at Alternate: 45.000 kg Tailwind component: 50 kts
The Alternate fuel required is:
A) 2.900 kg B) 2.750 kg C) 3.050 kg
#D) 2.500 kg 1225. (AIR: atpl) Given:
Maximum allowable takeoff mass: 64.400 kg Maximum landing mass: 56.200 kg
Maximum zero fuel mass: 53.000 kg Dry operating mass: 35.500 kg Estimated load: 14.500 kg Estimated trip fuel: 4.900 kg Minimum takeoff fuel: 7.400 kg Find maximum additional load:
A) 7.000 kg B) 4.000 kg
#C) 3.000 kg D) 5.600 kg
2181. (AIR: atpl)
An aeroplane has the following masses:
Estimated LM: 50.000 kg Trip fuel: 4.300 kg Contingency fuel: 215 kg
Alternate fuel (final reserve included): 2.100kg Taxi: 500 kg
Block fuel: 7.115 kg
Before departure the captain orders to make the block fuel 9 000 kg. The trip fuel in the operational flight plan should read:
#A) 4.300 kg B) 6.185 kg C) 9.000 kg D) 6.400 kg
2251. (AIR: atpl)
(Refer to figure 033-12)
Find the optimum altitude for the twin jet aeroplane, given:
Cruise mass: 50.000 kg MACH 0,78
A) 36.200 ft.
#B) 35.500 ft.
C) 36.700 ft.
D) maximum operating altitude.
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2252 (A) 2260 (A) 2261 (A) 2262 (D) 2264 (B) 2265 (D) 2267 (B) 2272 (C) 2273 (C) 2274 (B)
2252. (AIR: atpl)
(Refer to figure 033-12 and 033-65)
Find the fuel mileage penalty for the twin jet aeroplane with regard to the given flight level. Given:
Long range cruise Cruise mass: 53.000 kg FL310
#A) 4%
B) 1%
C) 10%
D) 0%
2260. (AIR: atpl)
(Refer to figure 033-15)
For a flight of 2.400 ground nautical miles the following apply:
Temperature: ISA -1° C Cruise altitude: 29.000 ft Landing mass: 45.000 kg
Trip fuel available: 16.000 kg
What is the maximum headwind component which may be accepted?
#A) 35 kts B) 15 kts C) 0 kts D) 70 kts
2261. (AIR: atpl)
(Refer to figure 033-39)
ETOPS - AC can not travel more than 120 minutes from a suitable (should read adequate) airfield. Assume LRC and
diversion weight of 40.000 kg, what is the still air diversion distance?
#A) 735 B) 794 C) 810 D) 875
2262. (AIR: atpl)
(Refer to figures 033-25 and 033-28) Long range cruise at FL340
Distance C-D: 3.200 NM
Temperature: deviation from ISA +12 °C Tailwind component: 50 kts
Gross mass at C: 55.000 kg
The fuel required from C to D is:
A) 17.500 kg B) 14.200 kg C) 17.800 kg
#D) 14.500 kg 2264. (AIR: atpl)
Mark the correct statement.
If a decision point procedure is applied for flight planning:
A) the trip fuel to the destination aerodrome is to be calculated via the suitable enroute alternate.
#B) the trip fuel to the destination aerodrome is to be calculated via the decision point.
C) a destination alternate is not required.
D) the fuel calculation is based on a contingency fuel from departure aerodrome to the decision point.
2265. (AIR: atpl)
(Refer to figure 033-15)
Tail wind component: 45 kts Temperature: ISA -10 °C Cruise altitude: 29.000 ft Landing mass: 55.000 kg
For a flight of 2.800 ground nautical miles, the trip fuel and trip time respectively are:
A) 16.000 kg; 6 hrs 25 min.
B) 18.000 kg; 5 hrs 50 min.
C) 20.000 kg; 6 hrs 40 min.
#D) 17.100 kg; 6 hrs 07 min.
2267. (AIR: atpl)
(Refer to figure 033-20) Distance to alternate: 400 NM
Landing mass at alternate: 50.000kg Headwind component: 25 kts
The alternate fuel required is:
A) 2.550 kg
#B) 2.800 kg C) 2.900 kg D) 2.650 kg
2272. (AIR: atpl)
The quantity of fuel which is calculated to be necessary for a jet aeroplane to fly IFR from departure aerodrome to the destination aerodrome is 5.352 kg. Fuel consumption in holding mode is 6.000 kg/hrs. Alternate fuel is 4.380 kg.
Contingency should be 5% of trip fuel. What is the minimum required quantity of fuel which should be on board
at takeoff?
A) 13.370 kg B) 14.500 kg
#C) 13.000 kg D) 13.220 kg 2273. (AIR: atpl)
(Refer to figure 033-27) Given:
LRC FL330
Temp -63 °C Mass 54.100 kg Time 29 min
Find the fuel consumed.
A) 1.207 kg B) 1.197 kg
#C) 1.100 kg D) 1.000 kg
2274. (AIR: atpl)
The required time for final reserve fuel for turbojet aeroplane is:
A) 45 min.
#B) 30 min.
C) 60 min.
D) variable with wind velocity.
033-05 JET AEROPLANES FLIGHT PLANNING 54
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2276 (D) 2277 (A) 2280 (A) 2285 (C) 2287 (D) 2294 (B) 2295 (B) 2299 (D) 2276. (AIR: atpl)
(Refer to figure 033-40)
Given:
Diversion distance: 650 NM
Diversion pressure altitude: 16.000 ft Mass at point of diversion: 57.000 kg Head wind component: 20 kts
Temperature: ISA + 15 °C
The diversion fuel required and time are approximately:
A) 4.400 kg; 1 hrs 35 min.
B) 3.900 kg; 1 hrs 45 min.
C) 6.200 kg; 2 hrs 10 min.
#D) 4.800 kg; 2 hrs 03 min.
2277. (AIR: atpl)
(Refer to figure 033-20)
In order to find alternate fuel and time to alternate, the aeroplane operating manual shall be entered with:
#A) distance in nautical miles (NM), wind component, landing mass at alternate.
B) distance in nautical air miles (NAM), wind component, landing mass at alternate.
C) distance in nautical miles (NM), wind component, zero fuel mass.
D) distance in nautical miles (NM), wind component, dry operating mass plus holding fuel.
2280. (AIR: atpl)
(Refer to figures 033-25 nad 033-36) Given:
Distance C-D: 540 NM Cruise: 300 KIAS at FL210 Temperature: ISA +2 °C Headwind component: 50 kts Gross mass at C: 60.000 kg
The fuel required from C to D is:
#A) 4.200 kg B) 4.620 kg C) 3.680 kg D) 3.350 kg
2285. (AIR: atpl)
The purpose of the decision point procedure is?
A) To increase the safety of the flight.
B) To reduce the landing weight and thus reduce the structural stress on the aircraft.
#C) To reduce the minimum required fuel and therefore be able to increase the traffic load.
D) To increase the amount of extra fuel.
2287. (AIR: atpl)
When using decision point procedure, you reduce the:
A) holding fuel by 30%.
B) contingency fuel by adding contingency only from the burn off between the decision airport and destination.
C) reserve fuel from 10% down to 5%.
#D) contingency fuel by adding contingency only from the burn off between decision point and destination.
2294. (AIR: atpl)
Planning a flight from Paris (Charles de Gaulle) to London (Heathrow) for a twin - jet aeroplane. Preplanning:
Maximum Takeoff Mass: 62.800 kg Maximum Zero Fuel Mass: 51.250 kg Maximum Landing Mass: 54.900 kg Maximum Taxi Mass: 63.050 kg
Assume the following preplanning results:
Trip fuel: 1.800 kg Alternate fuel: 1.400 kg
Holding fuel (final reserve): 1.225 kg Dry Operating Mass: 34.000 kg
Traffic Load: 13.000 kg Catering: 750 kg
Baggage: 3.500 kg
Find the Takeoff Mass (TOM):
A) 55.765 kg
#B) 51.515 kg C) 51.425 kg D) 52.265 kg 2295. (AIR: atpl)
(Refer to figure 033-12) Given:
Cruise mass: 54.000 kg
Long Range Cruise or Mach 0,74
Find the optimum altitude for the twin-jet aeroplane.
A) 35.300 ft.
#B) 34.500 ft.
C) maximum operating altitude.
D) 33.800 ft.
2299. (AIR: atpl)
(Refer to figure 033-21) Given:
Dry operating mass: 35.500 kg Estimated load: 12.000 kg
Contingency approach and landing fuel: 2.500 kg Elevation at departure aerodrome: 500 ft
Elevation at alternate aerodrome: 30 ft
Find the final reserve fuel for a jet aeroplane (holding) and give the elevation which is relevant.
A) 2.360 kg; destination elevation.
B) 2.360 kg; alternate elevation.
C) 1.180 kg; destination elevation.
#D) 1.180 kg; alternate elevation.
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2301 (C) 2304 (B) 2305 (A) 2307 (D) 2312 (A) 2314 (B) 2315 (B) 2316 (D) 2301. (AIR: atpl)
(Refer to figure 033-13) Given:
Brake release mass: 45.000 kg Temperature: ISA + 20 °C
Trip distance: 50 Nautical Air Miles (NAM)
Find the short distance cruise altitude for the twin-jet aeroplane.
A) 11.000 ft B) 12.500 ft
#C) 10.000 ft D) 7.500 ft
2304. (AIR: atpl)
(Refer to figure 033-40) Given:
Diversion distance: 720 NM Tail wind component: 25 kts
Mass at point of diversion: 55.000 kg Temperature: ISA
Diversion fuel available: 4.250 kg
What is the minimum pressure altitude at which the above conditions may be met?
A) 26.000 ft
#B) 20.000 ft C) 16.000 ft D) 14.500 ft 2305. (AIR: atpl)
(Refer to figures 033-25 and 033-33) For a flight from B to C:
FL310 M 0,74 ISA - 12 °C 957 MGN
40 kts tailwind Weight 50.100 kg
How much fuel is required to fly to C?
#A) 4.600 kg B) 4.500 kg C) 5.000 kg D) 4.100 kg
2307. (AIR: atpl)
(Refer to figure 033-33)
Find the FUEL FLOW for the twin jet aeroplane with regard to the following data. Given:
Mach 0,74 cruise Flight level 310 Gross mass 50.000 kg ISA conditions
A) 1.497 kg/hrs B) 1.150 kg/hrs C) 2.994 kg/hrs
#D) 2.300 kg/hrs 2312. (AIR: atpl)
The following fuel consumption figures are given for a jet aeroplane:
Standard taxi fuel: 600 kg
Average cruise consumption: 10.000 kg/hrs
Holding fuel consumption at 1.500 ft above alternate air- field elevation: 8.000 kg/hrs
Flight time from departure to destination: 6 hours Fuel for diversion to alternate: 10.200 kg
Forecast visibility at destination: 2.000 m The minimum ramp fuel load is:
#A) 77.800 kg B) 74.800 kg C) 79.800 kg D) 77.200 kg 2314. (AIR: atpl)
(Refer to figure 033-20) Given:
Estimated dry operation mass: 35.500 kg Estimated load: 14.500 kg
Final reserve fuel: 1.200 kg Distance to alternate: 95 NM Average true track: 219°
Head wind component: 10 kts Find fuel and time to alternate.
A) 1.100 kg; 44 min.
#B) 1.100 kg; 25 min.
C) 800 kg; 24 min.
D) 800 kg; 40 min.
2315. (AIR: atpl)
(Refer to figure 033-17) Given:
Cruise M 0,78 FL280
50.000 kg 200 NM
Headwind component 30 kts Find the fuel required.
A) 1.470 kg
#B) 1.740 kg C) 1.620 kg D) 1.970 kg
2316. (AIR: atpl)
(Refer to figures 033-23) Given:
Brake release mass: 58.000 kg Temperature: ISA + 15 °C
The fuel required to climb from an airfield at elevation 4.000 ft to FL300 is:
A) 1.350 kg B) 1.400 kg C) 1.450 kg
#D) 1.250 kg
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2318 (C) 2320 (A) 2321 (B) 2322 (D) 2323 (A) 2324 (A) 2331 (C) 2332 (C) 2334 (D) 2336 (A)
2318. (AIR: atpl)
The final reserve fuel for aeroplanes with turbine engines is:
A) fuel to fly for 45 minutes at holding speed at 1.000 ft (300 m) above aerodrome elevation in standard conditions.
B) fuel to fly for 45 minutes at holding speed at 1.500 ft (450 m) above aerodrome elevation in standard conditions.
#C) fuel to fly for 30 minutes at holding speed at 1.500 ft (450 m) above aerodrome elevation in standard conditions.
D) fuel to fly for 60 minutes at holding speed at 1.500 ft (450 m) above aerodrome elevation in standard conditions.
2320. (AIR: atpl)
Which of the following statements is relevant for forming route portions in integrated range flight planning?
#A) The distance from takeoff up to the top of climb has to be known.
B) No segment shall be more than 30 minutes of flight time.
C) Each reporting point requires a new segment.
D) A small change of temperature (2 °C) can divide a segment.
2321. (AIR: atpl)
A jet aeroplane is to fly from A to B. The minimum final reserve fuel must allow for:
A) 20 minutes hold over alternate airfield.
#B) 30 minutes hold at 1.500 ft above destination aerodrome elevation, when no alternate is required.
C) 30 minutes hold at 1.500 ft above mean sea level.
D) 15 minutes hold at 1.500 ft above destination aerodrome
elevation.
2322. (AIR: atpl)
(Refer to figure 033-19) Given:
Headwind: 50 kts
Temperature: ISA +1 °C
Brake release mass: 65.000 kg Trip fuel: 18.000 kg
What is the maximum possible trip distance?
A) 3.480 NGM B) 2.540 NGM C) 3.100 NGM
#D) 2.740 NGM 2323. (AIR: atpl)
(Refer to figure 033-21)
The final reserve fuel taken from the holding planning table for the twin-jet aeroplane is based on the following parameters:
#A) pressure altitude, aeroplane mass and flaps up with minimum drag airspeed.
B) pressure altitude, aeroplane mass and flaps down with maximum range speed.
C) pressure altitude, aeroplane mass and flaps up with maximum range speed.
D) pressure altitude, aeroplane mass and flaps down with minimum drag airspeed.
2324. (AIR: atpl)
(Refer to figure 033-15)
Within the limits of the data given, a mean temperature increase of 30 °C will affect the trip time by approximately:
#A) -5%
B) +5%
C) +8%
D) -7%
2331. (AIR: atpl)
(Refer to figure 033-37)
A descent is planned at 0,74M/250 KIAS from 35.000 ft to 5.000 ft.
How much fuel will be consumed during this descent?
A) 278 kg B) 290 kg
#C) 150 kg D) 140 kg
2332. (AIR: atpl)
An operator (turbojet engine) shall ensure that calculation of usable fuel for a flight for which no destination alternate is required includes, taxi fuel, trip fuel, contingency fuel and fuel to fly for:
A) 45 minutes plus 15% of the flight time planned to be spent at cruising level or two hours whichever is less.
B) 2 hours at normal cruise consumption.
#C) 30 minutes at holding speed at 450 m above aerodrome elevation in standard conditions.
D) 30 minutes at holding speed at 450 m above MSL in standard conditions.
2334. (AIR: atpl)
(Refer to figure 033-22) Given:
Track 340° (T) W/V 280/40 kts
Aerodrome elevation: 387 ft
ISA -10 °C
Brake release mass: 52.000 kg Cruise at FL280
What are the climb fuel and time?
A) 15 min, 1.100 kg.
B) 12 min, 1.100 kg.
C) 10 min, 1.000 kg.
#D) 11 min, 1.000 kg.
2336. (AIR: atpl)
(Refer to figure 033-13, 033-30, 033-31 and 033-34) Given:
Estimated takeoff mass: 57.000 kg Ground distance: 150 NM
Temperature: ISA -10 °C Cruise at Mach 0,74
Find cruise altitude and expected true air speed
#A) 25.000 ft, 435 kts.
B) 24.000 ft, 445 kts.
C) 33.500 ft, 430 kts.
D) 33.900 ft, 420 kts.
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2891 (C) 2894 (B) 4283 (C) 4284 (A) 4285 (C) 4286 (A) 4287 (A) 4288 (A) 2891. (AIR: atpl)
(Refer to figures 033-74)
The planned flight is over a distance of 440 NM. Based on the wind charts at altitude the following components are found:
FL50: -30 kts FL100: -50 kts FL180: -70 kts
The Operations Manual in appendix details the aircraft performances.
Which of the following flight levels (FL) gives the best range performance?
A) FL050
B) Either FL050 or FL100
#C) FL180 D) FL100
2894. (AIR: atpl)
(Refer to figure 033-15)
For a flight of 2.000 ground nautical miles, cruising at 30.000 ft, within the limits of the data given, a headwind component of 25 kts will affect the trip time by approximately:
A) +5,3%
#B) +7,6%
C) -3,6%
D) +2,3%
4283. (AIR: atpl)
(Refer to figure 033-18) Given:
Ground distance to destination aerodrome: 1.600 NM Headwind component: 50 kts
FL330
Cruise Mach 0,78 ISA +20 °C
Estimated landing weight: 55.000 kg
Find simplified flight planning to determine estimated trip
fuel and trip time.
A) 12.400 kg, 04 hrs 12 min.
B) 11.400 kg, 04 hrs 12 min.
#C) 12.400 kg, 03 hrs 55 min.
D) 11.400 kg, 03 hrs 55 min.
4284. (AIR: atpl)
(Refer to figure 033-29) Long Range Cruise at FL350 OAT: -45 °C
Gross mass at the beginning of the leg: 40.000 kg Gross mass at the end of the leg: 39.000 kg
Find: True airspeed (TAS) and cruise distance (NAM) for a twin jet aeroplane.
#A) TAS 433 kts, 227 NAM.
B) TAS 423 kts, 227 NAM.
C) TAS 431 kts, 1.163 NAM.
D) TAS 423 kts, 936 NAM.
4285. (AIR: atpl)
(Refer to figure 033-21) Given:
Mean gross mass: 47.000 kg
The fuel required for 45 minutes holding in a racetrack pattern at 5.000 ft is:
A) 1.690 kg B) 1.090 kg
#C) 1.635 kg D) 1.125 kg
4286. (AIR: atpl)
(Refer to figure 033-15)
For a flight of 1.900 ground nautical miles the following conditions apply:
Head wind component: 10 kts Temperature: ISA -5 °C
Trip fuel available: 15.000 kg Landing mass: 50.000 kg
What is the minimum cruise level (pressure altitude) which may be planned?
#A) 17.000 ft B) 10.000 ft C) 14.000 ft D) 22.000 ft 4287. (AIR: atpl)
(Refer to figure 033-18)
Using the following information, find fuel required and trip time with simplified flight planning for twin-jet aeroplane:
Ground distance to destination: 1.600 NM Headwind component: 50 kts
FL330
Cruise Mach 0,78 ISA Deviation +2 °C Landing mass: 55.000 kg
#A) 12.250 kg, 04 hrs 00 min.
B) 11.400 kg, 04 hrs 12 min.
C) 11.600 kg, 04 hrs 15 min.
D) 12.000 kg, 03 hrs 51 min.
4288. (AIR: atpl)
(Refer to figure 033-14) Given:
Estimated zero fuel mass: 50.000 kg
Estimated landing mass at alternate: 52.000 kg
Final reserve fuel: 2.000 kg Alternate fuel: 1.000 kg
Flight to destination, distance 720 NM: TC 030°, W/V 340/30
Cruise: long range FL330, OAT -30 °C Find: estimated trip fuel and time.
#A) 4.800 kg; 01:45.
B) 4.400 kg; 02:05.
C) 4.750 kg; 02:00.
D) 4.600 kg; 02:05.
033-05 JET AEROPLANES FLIGHT PLANNING 58
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AVIATIONEXAM.com
4289 (A) 4290 (B) 4294 (B) 4296 (B) 4298 (D) 4299 (B) 4301 (C) 4303 (D) 4289. (AIR: atpl)
(Refer to figure 033-40) Given:
Distance to alternate: 950 NM Head wind component: 20 kts
Mass at point of diversion: 50.000 kg Diversion fuel available: 5.800 kg
The minimum pressure altitude at which the above conditions may be met is:
#A) 22.000 ft B) 20.000 ft C) 26.000 ft D) 18.000 ft 4290. (AIR: atpl)
(Refer to figure 033-16)
Planning a flight from Paris (CDG) to London (Heathrow) for a twin-jet aeroplane.
Power setting: M 0,74 FL280
Landing Mass: 50.000 kg Distance to use: 200 NM
W/V from Paris to London: 280/40 Mean track: 340° (T)
Find the estimated trip fuel.
A) 1.550 kg
#B) 1.740 kg C) 1.900 kg D) 1.450 kg
4294. (AIR: atpl)
A jet aeroplane has a cruising fuel consumption of 4.060 kg/hrs, and 3.690 kg/hrs during holding. If the destination is an isolated airfield, the aeroplane must carry, in addition to contingency reserves, additional fuel of:
A) 7.380 kg
#B) 8.120 kg C) 1.845 kg D) 3.500 kg
4296. (AIR: atpl)
Which of the following is correct?
Given:
DOM: 33.510 kg
Traffic load: 7.600 kg Trip fuel: 2.040 kg Final reserve: 983 kg
Alternative fuel: 1.100 kg Contingency: 5% of trip fuel
A) Est landing mass at destination is 43.193 kg.
#B) Est landing mass at destination is 43.295 kg.
C) Est takeoff mass is 43.295 kg.
D) Est takeoff mass is 45.233 kg.
4298. (AIR: atpl)
(Refer to figure 033-33)
Find the specific range for the twin jet aeroplane flying below
Find the specific range for the twin jet aeroplane flying below