C) M 0,74 / 290 KIAS D) M 0,70 / 280 KIAS 12561. (AIR: atpl) (Refer to figure 033-39)
Using the above table, in ISA conditions and at a speed of M 0,70/280 KIAS, in an elapsed time of 90 minutes an aircraft with mass at point of diversion 48.000 kg could divert
a distance of: #A) 584 NM B) 563 NM C) 603 NM D) 608 NM 12562. (AIR: atpl) (Refer to figure 033-39)
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 40.000 kg at the most critical point, the maximum air distance to the relevant alternate is: #A) 735 NM B) 794 NM C) 810 NM D) 875 NM 14551. (AIR: atpl)
(Refer to figure 033-41 and 033-42)
An aircraft is planned to fly a LRC at FL350, ISA -10 °C, at an average gross cruise weight of 55.000 kg and a Landing
is -30 kts and the trip distance 1.600 NGM. Calculate the Break Even Fuel Price Destination Airport if the Fuel Price at Departure Airport is 75 cents/US Gallon.
#A) 90 cents B) 80 cents C) 95 cents D) 85 cents
14553. (AIR: atpl)
(Refer to figure 033-41 and 033-42)
An aircraft is tasked to fly a 0,74 Mach cruise at FL310, ISA +15 °C with a Landing Weight(Without Tankered Fuel) of
40.000 kg. The sector distance is 1.050 NGM, wind component +35 kts.
Calculate the Break Even Fuel Price at Destination if the Fuel price at Departure is 85 cents/US Gallon.
A) 85 cents #B) 92 cents C) 98 cents D) 80 cents
033-05 JET AEROPLANES FLIGHT PLANNING 63
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17198 (B) 17199 (B) 17200 (A) 22884 (A) 22885 (A) 22886 (D) 22887 (A) 17198. (AIR: atpl)
(Refer to figures 033-48, 033-60, 033-62)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
Flight leg ground distance: 4.000 NM Flight Level 370
Long range flight regime
Effective wind at this level: 50 kts head Temperature: ISA
Centre of Gravity (CG): 37% Pack Flow: LOW (LO)
Anti Ice: OFF
Reference Landing mass: 140.000 kg Taxi Fuel: 500 kg
Final Reserve Fuel: 2.400 kg
The fuel quantity which must be loaded on board the aircraft is: A) 41.590 kg #B) 51.860 kg C) 52.060 kg D) 46.340 kg 17199. (AIR: atpl)
(Refer to figure 033-43 and 033-63)
A turbojet aeroplane is prepared for a 1.300 NM flight at FL350, with a true airspeed of 460 kts and a headwind of 160 kts. The takeoff runway limitation is 174.000 kg, the planned departure mass is 160.000 kg. The departure fuel
price is equal to 0,92 times the arrival fuel price (fuel price ratio = 0,92). In order for the airline to optimize its savings, the additional fuel quantity that must be loaded onboard
is: A) 0 kg
#B) 14.000 kg C) 30.000 kg D) 12.000 kg
17200. (AIR: atpl)
(Refer to figure 033-43 and 033-63)
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: FL350
Air distance to be covered: 2.500 NM
Planned takeoff 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 kg Maximum takeoff mass: 205.000 kg Maximum tank capacity: 40.000 kg The additional fuel quantity will be: #A) 0 kg
B) 3.000 kg C) 2.000 kg D) 5.000 kg
22884. (AIR: atpl)
(Refer to figures 033-45 and 033-46)
In standard atmosphere, assuming a mass of 197.000 kg, in order to fly at FL370 and to be at the optimum altitude, your Mach number should be:
#A) 0,82. B) 0,84. C) 0,80.
D) the same as for LRC (Long Range Cruise). 22885. (AIR: atpl)
(Refer to figures 033-47, 033-50 and 033-62) Given:
Mass at brake release: 210.000 kg Selected cruise speed: Mach 0,82 Flight leg distance: 3.000 NM Cruise level: optimum
Air conditioning: standard Anti-icing: OFF
Temperature: ISA CG: 37
Assuming zero wind, the planned landing mass at destination will be: #A) 172.300 kg B) 170.400 kg C) 171.300 kg D) 176.100 kg 22886. (AIR: atpl)
(Refer to figures 033-47, 033-49 and 033-62) Given:
Mass at brake release: 190.000 kg Selected cruise speed: Mach 0,82 Flight leg distance: 1.500 NM Cruise level: optimum
Air conditioning: standard Anti-icing: OFF
Temperature: ISA CG: 37%
Assuming zero wind, the planned landing mass at destination will be:
#A) 169.200 kg B) 170.200 kg C) 174.800 kg
#D) 171.200 kg 22887. (AIR: atpl)
(Refer to figures 033-47, 033-49 and 033-62) Given:
Mass at brake release: 190.000 kg Selected cruise speed: Mach 0,82 Flight leg distance: 1.500 NM Cruise level: optimum
Air conditioning: standard Anti-icing: OFF
Temperature: ISA CG: 37%
Assuming zero wind, the planned flight time from takeoff to landing needed to complete this flight will be:
#A) 209 minutes B) 191 minutes C) 198 minutes D) 203 minutes
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22888 (C) 22889 (C) 22890 (A) 22891 (B) 22892 (A) 22893 (C) 22888. (AIR: atpl)
(Refer to figures 033-47, 033-50 and 033-62) Given:
Mass at brake release: 210.000 kg Selected cruise speed: Mach 0,82 Air distance: 3.000 NM
Cruise level: optimum Air conditioning: standard Anti-icing: OFF
Temperature: ISA CG: 37%
Assuming zero wind, the planned flight time from takeoff to landing needed to complete this flight will be:
A) 394 minutes B) 389 minutes #C) 400 minutes D) 381 minutes 22889. (AIR: atpl) (Refer to figures 033-48)
For a long distance flight at FL370, Long Range regime,
divided into four flight legs with the following specifications: Leg 1 - Ground distance: 2.000 NM, headwind component:
50 kts
Leg 2 - Ground distance: 1.000 NM, headwind component: 30 kts
Leg 3 - Ground distance: 500 NM, tailwind component: 70 kts
Leg 4 - Ground distance: 1.000 NM, headwind component: 20 kts
The total air distance is approximately: A) 4.580 NM B) 4.820 NM #C) 4.800 NM D) 4.940 NM 22890. (AIR: atpl) (Refer to figures 033-45)
For a turbojet aeroplane flying with a mass of 190.000 kg, at Mach 0,82, and knowing that the temperature at flight level FL370 is - 35 °C, the optimum flight altitude calculated using the annex is:
#A) 37.400 ft B) 37.800 ft C) 34.800 ft D) 38.600 ft 22891. (AIR: atpl) (Refer to figure 033-55)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
Takeoff mass: 168.500 kg
Flight leg ground distance: 2.000 NM
Flight level FL370; Long Range flight regime Tailwind component at this level: 30 kts
Total anti-ice set on ON
Fixed taxi fuel: 500 kg; final reserve: 2.000 kg Ignore alternate fuel
The effects of climb and descent are not corrected for consumption. The prescribed quantity of trip fuel for the flight
leg is: A) 23.300 kg #B) 20.500 kg C) 23.000 kg D) 22.500 kg 22892. (AIR: atpl) (Refer to figure 033-57)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
Takeoff mass: 210.500 kg
Flight leg ground distance: 2.500 NM FL330
Long Range flight regime
Tailwind component at this level: 70 kts Total anti-ice set on ON
Fixed taxi fuel: 500 kg; final reserve: 2.400 kg Ignore alternate fuel.
The effects of climb and descent are not corrected for consumption. The quantity of fuel that must be loaded at the
parking area is: #A) 31.840 kg B) 31.340 kg C) 30.200 kg D) 39.750 kg 22893. (AIR: atpl) (Refer to figure 033-52)
A turbojet aeroplane flies using the following data: Flight level: FL330
Flight regime: Long Range (LR) Mass: 156.500 kg
Tailwind component at this level: 40 kts
With a remaining flight time of 1 hrs 10 min the ground distance that can be covered by the aeroplane at cruising
speed is: A) 471 NM B) 518 NM #C) 539 NM D) 493 NM
033-05 JET AEROPLANES FLIGHT PLANNING 65 © 2008 AVIATIONEXAM.com 22894 (B) 22895 (D) 22896 (B) 22897 (B) 22899 (B) 22900 (A) 22901 (B) 22894. (AIR: atpl)
(Refer to figure 033-44 and 033-63)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
Flight leg air distance: 2.700 NM
Flight level FL310, true airspeed: 470 kts Tailwind component at this level: 35 kts
Initially planned takeoff mass (without extrafuel on board): 195.000 kg
Fuel price: 0,28 Euro/l at departure; 0,26 Euro/l at destination To maximize savings, the commander chooses to carry extra
fuel in addition to that which is necessary. The optimum quantity of fuel which should be carried in addition to the prescribed quantity is:
A) 10.000 kg.
#B) the fuel transport operation is not recommended in this case.
C) 5.000 kg. D) 8.000 kg.
22895. (AIR: atpl)
(Refer to figure 033-44 and 033-63)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
Flight leg air distance: 2.700 NM FL310
True airspeed: 470 kts
Tailwind component at this level: 35 kts
Initially planned takeoff mass (without extra fuel on board): 180.000 kg
Fuel price: 0,28 Euro/l at departure; 0,26 Euro/l at destination To maximize savings, the commander chooses to carry extra
fuel in addition to that which is necessary. The optimum quantity of fuel which should be carried in addition to the prescribed quantity is:
A) 4.000 kg. B) 6.000 kg. C) 10.000 kg.
#D) the fuel transport operation is not recommended in this case.
22896. (AIR: atpl)
(Refer to figure 033-52, 033-58 and 033-59) Given:
Takeoff mass: 150.000 kg Planned cruise at FL350 Long range MACH
Standard Atmosphere (ISA) CG: 37%
You have to cover an air distance of 2.000 NM. Your flight time will be:
A) 359 minutes #B) 304 minutes C) 288 minutes D) 298 minutes 22897. (AIR: atpl) (Refer to figures 033-48)
For a long distance flight at FL390, Long Range regime,
divided into four flight legs with the following characteristics: Leg 1 - Ground distance: 2.000 NM, head wind component:
50 kts
Leg 2 - Ground distance: 1.000 NM, head wind component: 30 kts
Leg 3 - Ground distance: 500 NM, tail wind component: 100 kts
Leg 4 - Ground distance: 1.000 NM, head wind component: 70 kts
The air distance of the entire flight is approximately: A) 5.040 NM
#B) 4.900 NM C) 5.120 NM D) 4.630 NM
22899. (AIR: atpl)
(Refer to figures 033-47, 033-49, 033-50 and 033-62)
Planning a MACH 0,82 cruise at FL390, the estimated landing mass is 160.000 kg. The ground distance is
2.800 NM and the mean wind is equal to zero. ISA conditions. Fuel consumption will be:
A) 30.371 kg #B) 32.657 kg C) 30.117 kg D) 27.577 kg
22900. (AIR: atpl)
(Refer to figures 033-47, 033-49, 033-50 and 033-62)
Planning a Mach 0,82 cruise at FL390, the estimated landing mass is 160.000 kg, the ground distance is 2.800 NM
and the mean tailwind is 100 kt, ISA conditions. Fuel consumption will be: #A) 26.950 kg B) 22.860 kg C) 24.900 kg D) 30.117 kg 22901. (AIR: atpl) (Refer to figure 033-54)
A turbojet aeroplane, weighing 200.000 kg, initiates its cruise at the optimum level at M 0,84 (ISA, CG=37%, Total Anti Ice ON). A head wind of 30 kts is experienced and, after a distance of 500 NM, severe icing is encountered and
this requires an immediate descent. The aeroplane mass at start of descent is:
A) 193.800 kg #B) 192.500 kg C) 193.000 kg D) 193.400 kg
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22902 (B) 22903 (A) 22904 (D) 22905 (C) 22906 (A) 22907 (A) 23735 (A) 22902. (AIR: atpl)
(Refer to figure 033-52, 033-58 and 033-59) Given:
Takeoff mass: 150.000 kg Planned cruise at FL350 Long range Mach
CG: 37%
Covering an air distance of 2.000 NM, your trip fuel from takeoff to landing will be:
A) 20.260 kg #B) 22.360 kg C) 19.660 kg D) 21.760 kg 22903. (AIR: atpl) (Refer to figure 033-51)
A turbojet aeroplane is flying using the following data: Flight level FL250, Long Range (LR) cruise, mass of 150.000 kg
Temperature: ISA
Head wind component: 100 kts
Remaining flight time: 1 hrs 40 min
The ground distance that can be covered during the cruise flight is: #A) 445 NM B) 612 NM C) 841 NM D) 2.031 NM 22904. (AIR: atpl) (Refer to figure 033-53)
A turbojet aeroplane is flying using the following data: Optimum flight level, Mach 0,80, mass of 190.000 kg Temperature: ISA
Tailwind component: 100 kts
The fuel mileage and the fuel consumption per hour are: A) 105 NM / 1.000 kg; 6.515 kg/hrs.
B) 86 NM / 1.000 kg; 6.515 kg/hrs. C) 71 NM / 1.000 kg; 5.330 kg/hrs. #D) 105 NM / 1.000 kg; 5.330 kg/hrs. 22905. (AIR: atpl)
(Refer to figures 033-49 and 033-62) Assuming the following data:
Ground distance to be covered: 2.600 NM Cruise flight level: FL370
Cruising speed: Mach 0,82 (true airspeed: 470 kt) Wind: zero wind during flight
Planned destination landing mass: 140.000 kg Temperature: ISA +15 °C
CG: 37%
Total anti-ice: ON
Air conditioning: normal
Fuel consumption for such a flight is: A) 29.400 kg
B) 27.400 kg #C) 31.500 kg D) 29.100 kg
22906. (AIR: atpl)
(Refer to figures 033-49 and 033-62) Assuming the following data:
Ground distance to be covered: 2.500 NM Cruise flight level: FL350
Cruising speed: Mach 0,82 (true airspeed: 470 kt) Tailwind component: 40 kts
Planned destination landing mass: 150.000 kg Temperature: ISA
CG: 37%
Air conditioning: normal
Fuel consumption for such a flight is: #A) 27.800 kg
B) 27.000 kg C) 28.300 kg D) 29.200 kg
22907. (AIR: atpl)
(Refer to figures 033-49 and 033-62) Assuming the following data:
Ground distance to be covered: 1.500 NM Cruise flight level: FL310
Cruising speed: Mach 0,82 (true airspeed: 470 kts) Head wind component: 40 kts
Planned destination landing mass: 140.000 kg Temperature: ISA +15 °C
CG: 37%
Total anti-ice: ON Pack flow: HI
Fuel consumption for such a flight is: #A) 23.500 kg
B) 21.500 kg C) 21.700 kg D) 19.900 kg
23735. (AIR: atpl)
(Refer to figure 033-43 and 033-63)
Assuming a departure/destination fuel price ratio of 0,92, the commander decides to optimize fuel tankering by using the following data:
Cruise flight level: FL350
Air distance to be covered: 1.830 NM
Planned takeoff mass: 190.000 kg (with a minimum prescribed fuel quantity of 30.000 kg that includes a trip fuel
of 22.000 kg)
Maximum landing mass: 180.000 kg Maximum takeoff mass: 205.000 kg Maximum tank capacity: 40.000 kg The additional fuel quantity will be: #A) 10.000 kg
B) 20.000 kg C) 12.000 kg D) 15.000 kg
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23736 (D) 23740 (B) 23741 (D) 23742 (D) 23743 (B) 23744 (B) 23736. (AIR: atpl)
(Refer to figures 033-49 and 033-62) Assuming the following data:
Ground distance to be covered: 2.000 NM Cruise flight level: FL330
Cruising speed: Mach 0,82 (true airspeed: 470 kts) Head wind component: 30 kts
Planned destination landing mass: 160.000 kg Temperature: ISA
CG: 37%
Total anti-ice: ON Pack flow: HI
A) 4 hrs 26 min B) 5 hrs 02 min C) 4 hrs 10 min #D) 4 hrs 43 min 23740. (AIR: atpl)
(Refer to figure 033-44 and 033-63)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
Flight leg distance: 3.500 NM
Flight level FL310, true airspeed: 450 kts Headwind component at this level: 5 kts
Initially planned takeoff mass (without extra fuel on board): 180.000 kg
Fuel price: 0,35 $/l at departure; 0,315 $/l at destination To maximize savings, the commander chooses to carry extra
fuel in addition to that which is necessary. Using the appended annex, the optimum quantity of fuel which should
be carried in addition to the prescribed quantity is: A) 8.000 kg.
#B) the fuel transport operation is not recommended in this case.
C) 22.000 kg. D) 15.000 kg. 23741. (AIR: atpl)
(Refer to figure 033-44 and 033-63)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
Flight leg distance: 4.000 NM
Flight level FL310, true airspeed: 450 kts Headwind component at this level: 50 kts
Initially planned takeoff mass (without extra fuel on board): 170.000 kg
Fuel price: 0,27 Euro/l at departure; 0,30 Euro/l at destination To maximize savings, the commander chooses to carry extra
fuel in addition to that which is necessary. Using the appended annex, the optimum quantity of fuel which should
be carried in addition to the prescribed quantity is: A) the fuel transport operation is not recommended in this case.
B) 18.000 kg. C) 32.000 kg. #D) 8.000 kg. 23742. (AIR: atpl)
(Refer to figure 033-44 and 033-63)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
Flight leg distance: 3.500 NM
Flight level FL310, true airspeed: 450 kts Headwind component at this level: 55 kts
Initially planned takeoff mass (without extra fuel on board): 180.000 kg
Fuel price: 0,30 Euro/l at departure; 0,27 Euro/l at destination To maximize savings, the commander decides to carry extra
fuel in addition to that which is necessary. Using the appended annex, the optimum quantity of fuel which should
be carried in addition to the prescribed quantity is: A) 22.000 kg.
B) 15.000 kg. C) 8.000 kg.
case.
23743. (AIR: atpl)
(Refer to figure 033-56)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
FL370 at Long Range (LR) cruise regime Mass at brake release: 212.800 kg
Flight leg ground distance: 2.500 NM Temperatures: ISA
CG: 37%
Headwind component: 30 kts
Total anti-ice set on ON for the entire flight
No requested climb and descent correction of the fuel consumption The fuel consumption (from takeoff to landing) is:
A) 30.440 kg #B) 34.430 kg C) 32.480 kg D) 28.720 kg
23744. (AIR: atpl)
(Refer to figure 033-44 and 033-63)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
Flight leg distance: 3.500 NM FL310
True airspeed: 450 kts
Headwind component at this level: 55 kts
Initially planned takeoff mass (without extra fuel on board): 180.000 kg
Fuel price: 0,27 $/l at destination
The commander may carry on board 8.000 kg more fuel than that which is necessary. For this fuel transport operation to be cost effective, the maximum fuel price at departure must be:
A) 0,38 $/l #B) 0,30 $/l C) 0,24 $/l D) 0,21 $/l
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23745 (A) 23746 (D) 23888 (B) 24754 (D) 24756 (A) 24759 (C) 24770 (D) 24793 (C) 23745. (AIR: atpl)
(Refer to figure 033-44 and 033-63)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
Flight leg distance: 3.500 NM
Flight level FL310, true airspeed: 450 kts Headwind component at this level: 55 kts
Initially planned takeoff mass (without extra fuel on board): 180.000 kg
Fuel price: 0,30 $/l at departure
The commander may carry a fuel quantity of 8.000 kg in
addition to that which is necessary. For this fuel transport operation to be cost effective, the maximum fuel price at arrival must be:
#A) 0,27 $/l B) 0,26 $/l C) 0,28 $/l
D) 0,33 $/l
23746. (AIR: atpl)
(Refer to figure 033-56)
The flight crew of a turbojet aeroplane prepares a flight using the following data:
FL370 at Long Range (LR) cruise regime
(Prescribed) mass at brake release: 204.500 kg Flight leg ground distance: 2.000 NM
Temperatures: ISA
Headwind component: 70 kts
Total anti-ice set on ON for the entire flight
No requested climb and descent correction of the fuel consumption The fuel required from takeoff to landing is:
A) 27.770 kg B) 20.900 kg C) 22.160 kg #D) 29.440 kg 23888. (AIR: atpl) Given: FL370 M 0,74 OAT - 47 °C The TAS is: A) 424 kts #B) 434 kts C) 417 kts D) 428 kts
24754. (AIR: atpl)
(Refer to figures 033-25 and 033-28) Given:
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) 14.400 kg 24756. (AIR: atpl) (Refer to figure 033-29) Given:
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 433 kts, 1.163 NAM. D) TAS 423 kts, 936 NAM. 24759. (AIR: atpl) (Refer to figure 033-22) Given: Aerodrome at MSL Cruise at FL280 ISA -10 °C
What is the climb fuel required? A) 1.100 kg B) 1.150 kg #C) 1.138 kg D) 2.200 kg 24770. (AIR: atpl)
(Refer to figure 033-37 and Jeppesen Student Manual - LONDON Heathrow 10-2 STAR or figure AP-08)
Given:
Aircraft mass: 49.700 kg FL280
Plan a descent to Heathrow elevation. What is the descent time? A) 8 min B) 10 min C) 17 min #D) 19 min 24793. (AIR: atpl) (Refer to figure 033-27) Given:
Long range cruise: temp. -63 °C at FL330 Initial gross mass enroute: 54.100 kg Leg flight time: 29 min
Find fuel consumption for this leg: A) 1.100 kg
B) 1.107 kg #C) 1.093 kg D) 1.000 kg
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24872 (A) 24890 (A) 24893 (D) 24898 (D) 25023 (C) 25025 (D) 25032 (B) 25052 (A) 25057 (A) 25072 (D) 25102 (C) 25103 (C) 24872. (AIR: atpl) (Refer to figure 033-15) Given: Trip distance: 1.900 NM Fuel on board: 15.000 kg Landing weight: 50.000 kg
What is the minimum pressure altitude for this flight? #A) 17.000 ft B) 10.000 ft C) FL370 D) FL250 24890. (AIR: atpl) (Refer to figure 033-20)
Alternate airfield is 300 NGM, 50 kts tailwind and a landing weight of 50.000 kg, what is the fuel and time to the alternate? #A) 1.950 kg, 48 min. B) 1.650 kg, 48 min. C) 2.100 kg, 57 min. D) 1.950 kg, 57 min. 24893. (AIR: atpl) (Refer to figure 033-37)
What is the time, fuel required and nautical air miles to descend from FL350 to sea level in turbulent air given an estimated
landing weight of 50.000 kg? A) 20 min, 325 kg, 99 NAM.
B) 22 min, 290 kg, 108 NAM. C) 22 min, 290 kg, 105 NAM. #D) 20 min, 275 kg, 99 NAM. 24898. (AIR: atpl)
(Refer to figure 033-38)
After suffering undercarriage and pressurISAtion problems the aircraft is to be flown, undercarriage down, 400 NGM at FL100 for repairs. The estimated landing weight is 30.000 kg, the temperature is ISA+20 °C and a 50 kts headwind is expected. What is the fuel and time required for the trip? A) 7.500 kg, 2 hrs. B) 6.400 kg, 2 hrs 5 min. C) 4.600 kg, 1 hrs 40 min. #D) 5.800 kg, 2 hrs. 25023. (AIR: atpl) (Refer to figure 033-12)
With a cruise weight of 50.000 kg, Cruising at Mach 0,78, what is the optimum altitude?
A) 36.200 ft B) 35.800 ft #C) 35.400 ft D) 36.700 ft 25025. (AIR: atpl) (Refer to figure 033-24)
An aircraft climbs out from an aerodrome at MSL to FL250, under ISA +20 °C conditions. If the brake release weight is 60.000 kg, what is the fuel and ground distance covered with a 40 kts tailwind? A) 1.100 kg, 62 NGM. B) 1.100 kg, 48 NGM. C) 1.300 kg, 64 NGM. #D) 1.300 kg, 81 NGM. 25032. (AIR: atpl) (Refer to figure 033-21)
An aircraft weighing 56.000 kg is required to carry on an enroute straight and level hold at FL350 for 50 minutes. How
much fuel will be used in the hold? A) 2.017 kg #B) 1.917 kg C) 2.133 kg D) 2.027 kg 25052. (AIR: atpl) (Refer to figure 033-29)
An aircraft cruising at FL350 in light and variable winds turn at waypoint ALPHA weighing 53.500 kg and later turns waypoint BRAVO now weighing 50.200 kg. Assuming standard conditions what is the TAS, distance and specific fuel consumption between Alpha and BRAVO?
#A) 429 kts, 627 NM, 5,26 kg/NM. B) 426 kts, 631 NM, 5,22 kg/NM. C) 429 kts, 627 NM, 6,25 kg/NM. D) 429 kts, 573 NM, 5,24 kg/NM. 25057. (AIR: atpl) (Refer to figure 033-42)
The surplus burn off for tankering fuel is 20%, if the price at the departure airfield is 100 cents/gallon, what is the breakeven price at the destination airfield?
#A) 125 cents/gallon. B) 100 cents/gallon. C) 80 cents/gallon.
D) 103 cents/gallon. 25072. (AIR: atpl)
(Refer to figure 033-14)
Given a distance of 1.000 NGM, 50 kts tailwind, ISA +0 °C, cruise FL370 and landing weight of 35.000 kg. What is the fuel and time for the trip?
A) 4.950 kg, 2 hrs 15 mins. B) 5.350 kg, 2 hrs 15 mins. C) 4.300 kg, 2 hrs 40 mins. #D) 4.300 kg, 2 hrs 15 mins. 25102. (AIR: atpl)
Given Mach number 0,82 and COAT -50 °C, TAS is: A) 466 kts
B) 470 kts #C) 476 kts D) 496 kts
25103. (AIR: atpl)
Given TAS 500 kts and COAT -40 °C, Mach number is: A) 0,80
B) 0,82 #C) 0,84 D) 0,88
033-05 JET AEROPLANES FLIGHT PLANNING 70 © 2008 AVIATIONEXAM.com 25116 (B) 25118 (B) 25119 (D) 25125 (D) 25126 (D) 25157 (C) 25167 (D) 25169 (A) 25116. (AIR: atpl) (Refer to figure 033-20) Given:
Estimated dry operating 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 to alternate 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. 25118. (AIR: atpl) (Refer to figure 033-37)
Assume M0,74/250 KIAS descent profile. How much time
will elapse from top of descent (FL350) to level off at 5.000 feet? A) 6 minutes. #B) 16 minutes. C) 22 minutes. D) 23 minutes. 25119. (AIR: atpl) (Refer to figure 033-27) Given:
Long range cruise at FL330 OAT -63 °C
Gross mass: 50.500 kg
Find the true air speed (TAS): A) 433 kts
C) 431 kts #D) 420 kts
25125. (AIR: atpl)
(Refer to figure 033-29) Given:
Long range cruise OAT -45 °C
FL350
Headwind component: 40 kts Start mass: 60.000 kg End mass: 55.000 kg
Find the TAS at the end of the leg and the distance (NGM): A) 429 kts, 864 NGM. B) 430 kts, 864 NGM. C) 440 kts, 864 NGM. #D) 440 kts, 785 NGM. 25126. (AIR: atpl) (Refer to figure 033-20)
Planning a flight from Paris (Charles de Gaulle) to London (Heathrow) for a twin jet aeroplane with alternate Manchester. Given:
Headwind component from London to Manchester: 10 kts Distance from London to Manchester: 160 NM
Assume the Estimated Landing Mass at the alternate is 50.000 kg
Find the alternate fuel and the corresponding time: A) 1.200 kg, 26 minutes. B) 1.300 kg, 28 minutes. C) 1.600 kg, 36 minutes. #D) 1.450 kg, 33 minutes. 25157. (AIR: atpl) (Refer to figure 033-26)
What would be the required change in fuel required if the temperature at FL280 was -31 °C? A) + 0,3% B) - 0,3% #C) + 0,6% D) - 0,6% 25167. (AIR: atpl) (Refer to figure 033-15) Given: Cruising altitude: 29.000 ft Temperature: ISA -10 °C Tailwind component: 45 kts Landing Mass: 55.000 kg
Distance: 2.800 nautical ground miles Find trip time and fuel burn:
A) 6 hrs 25 min, 16.000 kg. B) 6 hrs 40 min, 20.000 kg. C) 5 hrs 50 min, 18.000 kg. #D) 6 hrs 7 min, 17.100 kg. 25169. (AIR: atpl) (Refer to figure 033-20) Given:
Estimated Dry Operating Mass: 35.500 kg