5863315
Description
Quiz by tsampikos pompou, updated more than 1 year ago
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Created by tsampikos pompou
almost 8 years ago
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Question 1
Question
11 In order for a propeller driven aircraft to achieve maximum range it should be flown at a speed:
Answer
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O which gives the max L/D ratio.
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O equal to V2.
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O slightly higher than stalling speed.
-
O equal to V1.
Question 2
Question
20 How will the density altitude change by an increase in temperature from -4C to +10C if the pressure altitude remains the same.(Fig. FPP01)
Answer
-
O It will increase by 1.650 ft.]
-
O it will increase by 1.400 ft.]
-
O It will increase by 1.200 ft.]
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O It will decrease by 1.000 ft.]
Question 3
Question
21 What will the density altitude be if the airport elevation is 5.250 ft ,temperature 27C and altimeter setting 29.25 inHg? (Fig FPP01)
Answer
-
O '8.500 ft.
-
O '5.850 ft.
-
O '4.900 ft.
-
O '7.700 ft.
Question 4
Question
25 How does high density altitude affect propeller efficiency?
Answer
-
O It decreases propeller efficiency.
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O It improves propeller efficiency.
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O It does not affect propeller efficiency.
Question 5
Question
26 What is the crosswind component for a landing on runway 18,if the wind is 220 degrees 30 knots?(Fig FPP02)
Answer
-
O '19 kts
-
O '16 kts
-
O '22 kts.
-
O '24 kts
Question 6
Question
27 If the wind direction is forming a 45 degree angle with the runway, what is the maximum wind speed during landing so as not to exceed a maximum demonstrated crosswind component of 25 kts? (Fig FPP02)
Answer
-
O '35 kts
-
O '27 kts
-
O '30 kts
-
O '40 kts
Question 7
Question
28 If the wind direction is forming a 30 degree angle with the runway,what is the maximum wind speed during landing so as not to exceed a max demonstrated crosswind component of 12 kts?(Fig FPP02)
Answer
-
O '24 kts.
-
O '17 kts.
-
O '21 Kts.
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O '28 kts.
Question 8
Question
29 If the wind is from 180 degrees 20 kts which runway should be used by an aircraft with a max demonstrated crosswind component of 13 kts? (Fig FPP02)
Answer
-
O Runway 14.
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O Runway 32.
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O Runway 24.
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O Runway 06.].
Question 9
Question
30 How much fuel is required for a flight of 1.000 NM under the following conditions: Pressure altitude 8.000 ft,outside air temperature -19 C,manifold pressure 19.5 inHg, wind calm. (Fuel reserves are not included) (Fig FPP03)
Answer
-
O '73.2 USG.
-
O '63,5 USG
-
O '70.1 USG.
-
O '78.2 USG.
Question 10
Question
31 How much fuel required for a flight of 1.000 NM under the following conditions: Pressure altitude 8.000ft.outside air temperature +22 C,manifold pressure 20.8 inHg,wind calm.(Fuel reserves are not included) (Fig FPP03)
Answer
-
O '70.1 USG.
-
O '73.2 USG.
-
O '60,2 USG.
-
O '78,2 USG.
Question 11
Question
32 What is the estimated fuel consumption for a 500 NM flight under the following conditions: Pressure altitude 4.000 ft,outside air temperature +29 C,manifold pressure 21.3 inHg,wind calm. (Fig FPP03)
Answer
-
O '36.1 USG.
-
O '31.4 USG.
-
O '40,1 USG.
-
O '43,2 USG.
Question 12
Question
33 What is the fuel flow of an aircraft which flies at 11.000 ft,in standard atmosphere,with 65% power? (Fig FPP03)
Answer
-
O '11,2 USG/hr.
-
O '11,8 USG/hr
-
O '12,1 USG/hr.
-
O '10,9 USG/hr
Question 13
Question
34 What manifold pressure will you use at 6.500 ft ,2.450 RPM ,with 65% power and a temperature of 20C above standard? (Fig FPP03)
Answer
-
O '21,0 inHg.
-
O '19,8 inHg.
-
O '20,8 inHg.
-
O '20,4 inHg.
Question 14
Question
35 What will the true air speed be if you are flying at 9.500 ft,with 65% power and a temperature of 20 C (36 F) below standard? (Fig FPP03)
Answer
-
O '159 kts.
-
O '157 kts
-
O '154 kts.
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O '162 kts.
Question 15
Question
36 Calculate the landing distance (ground roll) of the aircraft under the following conditions (Fig FPP04): Temperature standard ,Pressure altitude 2.000 ft ,weight 2.300 lbs,wind calm.
Answer
-
O '900 ft.
-
O '1.250 ft.
-
O '1.450 ft.
-
O '700 ft..
Question 16
Question
37 Calculate the landing distance (ground roll) of the aircraft under the following conditions (Fig FPP04):Temperature 32 C (90 F) ,pressure altitude 4.000 ft ,weight 2.800 lbs ,headwind 10 kts.
Answer
-
O '1.100 ft.
-
O '1.350 ft.
-
O '1.500 ft.
-
O '900 ft.
Question 17
Question
38 Calculate the total landing distance over 50 ft obstacle under the following conditions (Fig FPP04):Temperature 32 C (90 F), pressure altitude 3.000 ft ,Weight 2.900 lbs ,tailwind 10 kts.
Answer
-
O '2.850 ft.
-
O '2.500 ft.
-
O '1.900 ft.
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O '3.200 ft.
Question 18
Question
39 Calculate the landing distance (ground roll) of the aircraft under the following conditions (Fig 5):Pressure altitude sea level ,headwind 4 kts ,temperature standard.
Answer
-
O '401 ft.
-
O '356 ft..
-
O '490 ft.
-
O '534 ft.
Question 19
Question
40 Calculate the landing distance (ground roll) of the aircraft under the following conditions (Fig FPP04):Pressure altitude 7.500 ft ,headwind 4 kts ,temperature standard.
Answer
-
O '468 ft.
-
O '520 ft.
-
O '655 ft.
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O '820 ft.
Question 20
Question
41 What is the landing distance (ground roll) of the aircraft under the following conditions (Fig FPP05):Pressure altitude 3.750 ft ,headwind 12 kts ,temperature standard.
Answer
-
O '338 ft.
-
O '310 ft.
-
O '424 ft.
-
O '470 ft.
Question 21
Question
42 What is the landing distance over 50ft obstacle under the following conditions (Fig FPP05):Pressure altitude 5.000 ft ,headwind 8 kts ,temperature 5 C (41 F),asphalt runway.
Answer
-
O '956 ft.
-
O '830 ft.
-
O '1.076 ft.
-
O '1.554 ft.
Question 22
Question
43 What is the landing distance over 50 ft obstacle under the following conditions (Fig FPP05):Pressure altitude 5.000 ft ,wind calm ,temperature 41 C (101 F).
Answer
-
O '1.315 ft.
-
O '1.075 ft.
-
O '545 ft.
-
O '1.195 ft.
Question 23
Question
44 What is the landing distance (ground roll) under the following conditions (Fig FPP05):Pressure altitude 1.250 ft ,headwind 8 kts ,temperature standard.
Answer
-
O '366 ft.
-
O '275 ft.
-
O '470 ft.
-
O '549 ft.
Question 24
Question
45 What is the landing distance of the aircraft under the following conditions (Fig FPP05): Pressure altitude 7.500 ft, temperature 0 C (32 F), headwind component 20 kts ,obstacle 50 ft.
Answer
-
O '628 ft.
-
O '852 ft.
-
O '567 ft.
-
O '1.136 ft.
Question 25
Question
46 Calculate the total take off distance over 50 ft obstacle under the following conditions (Fig FPP06):Pressure altitude 4.000 ft temperature standard ,weight 2.600 lbs ,wind calm.
Answer
-
O '1.520 ft.
-
O '1.150 ft.
-
O '1.020 ft.
-
O '1.850 ft.
Question 26
Question
47 What is the take off distance under the following conditions (Fig FPP06):Pressure altitude 2.000 ft ,temperature 38 C ,take off weight 2.750 lbs .wind calm ,obstacle 0 ft.
Answer
-
O '1.100 ft.
-
O '900 ft.
-
O '1.350 ft.
-
O '1.600 ft.
Question 27
Question
48 Calculate the total take off distance over 50 ft obstacle under the following conditions (Fig FPP06):Temperature standard ,pressure altitude sea level ,weight 2.500 lbs ,wind calm.
Answer
-
O '1.130 ft.
-
O '1.500 ft.
-
O '880 ft.
-
O '700 ft.
Question 28
Question
49 What is the take off distance of the aircraft under the following conditions (Fig FPP06):temperature 32 C ,pressure altitude 2.000 ft ,take off weight 2.900 lbs headwind component 20 kts ,obstacle 0 ft.
Answer
-
O '910 ft.
-
O '1220 ft.
-
O '1.470 ft.
-
O '670 ft.
Question 29
Question
50 Which of the following are included in the term "basic empty weight"?
Answer
-
O unusable fuel and optional equipment.
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O Hydraulic fluids and usable fuel.
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O Only the airframe, the engine and the equipment, which have been installed by the manufacturer.
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O full fuel and oil tanks.
Question 30
Question
51 If an aircraft is overloaded by 110 lbs (55 kgs),how much fuel does the pilot have to remove so that the aircraft loading will be within limits?]
Answer
-
O '18,3 USG.
-
O '16,2 USG.
-
O '15,7 USG.
-
O '17,1 USG.
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