Quiz
Flight Performance & Planning
Questions in this quiz (55)
1 Barometric error occurs when:
- ASea level pressure (Mean Sea Level) is different from the 1013.25hPa.
- BPressure gradient is different from QNH .
- CPressure gradient is different from the ISA.
- DThe altimeter was heated (eg. sunshine) to high temperature.
2 Temperature error occurs when:
- AAmbient temperature differs from ISA
- BThe altimeter is calibrated by QNH.
- CThe altimeter is calibrated by QFE.
- DPressure gradient is different from QNH .
3 Component weight 55 kg, arm = 2.3 m. The moment [kgm] ?
- A126.5.
- B23.9.
- C6957.
- D0.0418.
4If the center of gravity is near the extreme forward position, this shall:
- ADecrease in force on the stick.
- BIncrease in force on the stick.
- CThe plane is unstable sedately
- DWill occur less force on the stick.
5The international standard atmosphere (International Standard Atmosphere) defines the following conditions at the sea level: temperature / pressure / density / temperature gradient:
- A15°C / 1013,25 hPa / 1.225 kg/m3 / -6.5°C per 1000 m.
- B15°C / 1013,25 mb / 1.225 kg/m3 / 1.98°C per 1000 m.
- C0°C / 1.013 Bar / 1225 g/m3 / 1.98°C per 1000 ft.
- D15°C / 29.92 in.Hg / 1013 kg/m3 / 1.98°C per 1000 ft.
6The center of gravity can be defined as:
- AThe percent mean aerodynamic chord (% MAC) or distance (mm, cm, inch) CG the measuring point "DATUM".
- BPercentage of dynamic chord severity (% MAC).
- CAs a percentage of the fuselage aerodynamic chord (% MAC).
- DPercentage of dynamic chord counted in the average range (% MAC).
7 The center of gravity can be defined as:
- AThe point where the concentrated mass of the aircraft is.
- BPoint to which they are applied all the forces acting on the aircraft.
- CThe point to which the applied forces are supporting and gravity - acting on the aircraft.
- DPoint to which they are applied drag force acting on the aircraft.
8 Weighing of the aircraft (SP): readout on the scales under the front gear - 155 kg, readout - the sum on the main 320 kg. Distance SP front - front gear 0.8 m, front SP - main 2.4 m. What is the distance between the front SP and the center of gravity?
- A1.88 m.
- B2.92 m.
- C3.2 m.
- D1.68 m.
9Weighing of the aircraft: the readout on the scales under the front gear 205 kg, the readout - the sum of the main 420 kg. Front gear arm - 0.9m front, main 2.6 m. What is the distance between the front CG - the center of gravity?
- A2.04 m.
- B3.12 m.
- C1.88 m.
- D2.09 m.
10 Moment = ? Formula fo the moment ?
- AForce (weight) multiplied by the arm of force.
- BForce (weight) divided by the arm of force.
- CStrength (w) x distance from the center of gravity datum.
- DArm of force divided by the force (weight).
11 The pressure altitude of the airport on a particular day can be determined:
- ABy reading the amount indicated by the altimeter set to 1013.2 hPa.
- BRead the height of the altimeter driven 1013.2hPa, and then we correct it, because it reads the ambient temperature.
- CBetter observations of the environment by the pilot because of the wider field of view close to the ground.
- DAchieving greater thrust to the ground - this effect disappears at a height approximately equal to the span of the aircraft.
12 "The influence of the earth" allows:
- AThe separation of aircraft at the lower speed, but the phenomenon disappears at an altitude of
approximately equal span and performance decline. - BAchieve greater engine power to the ground (for engines without compressor).
- CBetter observations of the environment by the pilot because of the wider field of view close to the ground.
- DAchieving greater thrust to the ground - this effect disappears at a height approximately equal to the span of the aircraft.
- AThe separation of aircraft at the lower speed, but the phenomenon disappears at an altitude of
13 "The influence of the earth " is a phenomenon consisting in:
- AReduction of induced drag and angle of attack required for level flight (at a given speed), which is due to the proximity of the ground.
- BWithstanding the significant shortening of the landing phase.
- CAchieving greater power by internal combustion engines near the ground (for naturally aspirated engines).
- DAchieving greater thrust to the ground - this effect disappears at a height approximately equal to the span of the aircraft.
14For the hydroplaning phenomenon (dynamic) to take place during the run / roll of the airplane the following factors are necessary:
- AThe thickness of the layer of water on the belt must be greater than the critical (about 3 mm) and the aircraft must obtain the appropriate pull rates.
- BAircraft tire treads must heat up to high temperatures during intense braking on wet runway.
- COne of the wheels plane must be locked (e.g. failure of anti-skid) on the wet runway.
- D"Hydroplaning '"is a term for only a seaplane landing on a smooth surface.
15 What is VX?
- AThis is the speed at which the best climb gradient is achieved. Best Angle of Climb.
- BThis is the speed at which achieves the best rate of climb Rate of Climb Best.
- CTo speed the decision at which the conditions are safe and continue to break off.
- DIs the speed at which the best value is achieved for the lift force.
16 What is VY?
- ABest Rate of Climb.
- BBest Angle of Climb.
- CTo speed the decision at which the conditions are safe and continue to break off.
- DIs the speed at which the best value is achieved for the lift force.
17 Does high humidity contribute to decrease in the aircraft performance?
- AYes.
- BFalse - it cools the engine and thus improves performance.
- CHumidity has no effect on performance.
- DAll the answers are wrong.
18 For each combination of the altitude of the flight and aircraft weight, in the scale of minimum to maximum speed there is:
- AAn approach angle at which the lift force is equal to the weight and it is possible to level flight.
- BSuch a tilt that ensures that the lift force is equal to the weight and it is possible to level flight.
- CSuch an approach angle at which the resistance force is equal to the string generated by the engines and it is possible to level flight.
- DSuch an approach angle at which the lift force equals the weight times the cosine of the angle of attack, and it is possible to level flight.
19 High density altitude (in relation to low density altitude) means:
- ALow air density and low aircraft performance.
- BHigh air density and low aircraft performance.
- CHigh air density and high aircraft performance.
- DLow air density and high aircraft performance.
20 How will high ambient temperature influence the aircraft take-off run (at a given airport) in comparison with the case when the ambient temperature is low?
- AIncreasing the length of the run.
- BReducing the length of the run.
- CThe ambient temperature does not affect the length of the run.
- DAll the answers are wrong.
21 How will the plane take-off from an airport located in the mountains influence the length of the take-off run in comparison with the take-off in the same temperature , aircraft weigh and wind conditions and with the setting of the flaps from the airport at 0 m above the sea level?
- AStart from the highly situated airport - greater long run.
- BReducing the length of run.
- CElevation of the airport does not affect the length of the run.
- DAll the answers are wrong.
22How will the use of higher flap setting (than usual) influence the length of the take-off run?
- AReducing the length of the take-off run.
- BIncreasing the length of the take-off run.
- CIt has no effect on the length of the take-off run.
- DAll the answers are wrong.
23 How will increase of the weigh of the aircraft influence the length of the take-off run?
- AIncreasing the length of the take-off run.
- BReducing the length of run.
- CIt has no effect on the length of the run.
- DAll the answers are wrong.
24What shall be the effects of changes in ambient temperature on the performance of the aircraft if all other parameters remain unchanged?
- AThe temperature drop will increase the gradient of the climb.
- BThe increase in temperature would reduce the distance required for takeoff.
- CThe temperature drop will increase the distance required for takeoff.
- DThe increase in temperature would reduce the distance required for takeoff and landing.
25What shall be the effects of changes in ambient temperature on the performance of the aircraft if all other parameters remain unchanged?
- AThe temperature drop will reduce the distance required for takeoff.
- BThe increase in temperature would reduce the distance required for takeoff.
- CThe temperature drop will increase the distance required for takeoff.
- DChanges in ambient temperature do not change the distance required for takeoff.
26 If the center of gravity is near the extreme front position:
- AThis will reduce the rate of climb.
- BBecause of the need to lower the amount of rudder - Supporting decreases the force required to slice - it reduces the stall speed.
- CA reduction of fuel consumption during the flight due to less resistance.
- DA reduction of induced drag.
27 If the center of gravity is maximum forward position the aircraft among others shall:
- ADue to the need for a greater amount of rudder - increases the required lift force on the panel -
increases induced drag, which negatively affects performance. - BBecause of the need to lower the amount of rudder - decreases the lift on the rudder, which requires carriers to increase the panel which reduces induced drag and has a negative effect on performance.
- CBecause of the need to lower the amount of rudder - Supporting decreases the force required to slice - it reduces the stall speed.
- DDue to the need for a greater amount of rudder - Supporting decreases the force required to slice - the stall speed increases.
- ADue to the need for a greater amount of rudder - increases the required lift force on the panel -
28The direction of the airstrip 040 °, wind 270/18 kt (ATIS). What are the components of the wind?
- AThe tail: 12 kt, cross - left 14 kt.
- B12 kt, cross - the right of 14 kt.
- CHead: 16 kt, cross - the right of 16 kt.
- DThe tail: 8 kt, cross - left 21 kt.
29The direction of the airstrip 150 °, wind 220/22 kt (ATIS). What are the components of the wind?
- AHead: 8 kt, cross - the right of 21 kt.
- BHead: 14 kt, cross - the right of 17 kt.
- CHead: 4 kt, cross - right 22 kt.
- DThe tail: 8 kt, cross - left 21 kt.
30The direction of the airstrip 200 °, wind 080/13 kt (ATIS). What are the components of the wind?
- AThe tail: 7 kt, cross - left 11 kt.
- BHead: 7 kt, cross- right 11 kt.
- CHead: 4 kt, cross - right 12 kt.
- DThe tail: 8 kt, cross - left 12 kt.
31The direction of the airstrip 220 °, wind 160/26 kt (ATIS). What are the components of the wind?
- AHead: 13 kt, cross - left 23 kt.
- BHead: 14 kt, cross - the right of 17 kt.
- CHead: 9 kt, cross - the right of 23 kt.
- DThe tail: 13 kt, cross - left 22 kt.
32The direction of the airstrip 330 °, wind 250/15 kt (ATIS). What are the components of the wind?
- AHead: 3 kt, cross - left 15 kt.
- BHead: 8 kt, cross - left 13 kt.
- CThe tail: 3 kt, cross - left 15 kt.
- DThe tail: 3 kt, cross - the right of 15 kt.
33Which of the given combinations of weather conditions prevailing at the airport at the start shall contribute to the largest drop of the aircraft performance:
- AHigh temperature, high density altitude, high humidity.
- BLow temperature, high density altitude, low humidity.
- CHigh temperature, low density altitude, low humidity.
- DLow temperature, low density altitude, low humidity.
34Which of the given combinations of weather conditions prevailing at the airport at the start shall contribute to the largest drop of the aircraft performance:
- AHigh density altitude and high ambient temperature.
- BStrong wind front.
- CPoor rainfall and low, but positive temperature.
- DLow ambient temperature.
35Mach number is the ratio of the:
- ATAS-speed and local speed of sound.
- BIAS-speed and local speed of sound.
- CIAS speed and the speed of sound at a given height referred to the ISA.
- DTAS speed and the speed of sound at sea level.
36The Maximum structural landing mass (Maximum Structural Landing Mass) is:
- AMaximum weight for landing under normal circumstances.
- BMaximum landing mass-impassable - even in emergency situations because of the certainty of destruction of the structure.
- CMaximum weight for landing in emergency situations (1.3 times the normal weight for landing).
- DMaximum weight for takeoff and landing in an emergency (1.3 times the normal weight for landing).
37 Low density altitude means that:
- AThe air density is high - the aircraft's performance will be better than in the case of high density altitude.
- BThe air density is high - the aircraft's performance will be much worse than in the case of high density altitude.
- CThe air density is low, which causes a drop in airplane performance compared to the case of high density altitude.
- DThe air density is high, which causes a drop in airplane performance compared to the case of high density altitude.
38 The most economical angle in terms of fuel use/range is the one which produces:
- AThe best ratio of carrier power to resist - that the most economical approach angle is fixed for each combination of altitude and aircraft weight.
- BThe best ratio of carrier power to resist - that the most economical approach angle increases with the mass of the airplane and the flight altitude.
- CThe best value for the resistance forces.
- DThe best ratio of lift to the string.
39With reference to the influence of "ground effect" it is true that:
- AThis phenomenon disappears at an altitude of approximately equal span of aircraft / glider and performance decline.
- BSignificantly reduces the phenomenon of withstanding the landing phase.
- CImproves gradient of climb at an altitude of 150 m.
- DSignificantly increases the stall speed.
40With reference to the influence of icing on the aircraft's performance it is true that:
- AEven minor pollution such as "sandpaper" surface of the carrier may have a dangerous effect on performance.
- BIce on the upper surface of the wing / rotor blades is less dangerous than the bottom.
- CThe main factor influencing the performance of aircraft is the mass deposited on them ice.
- DFor aircraft icing appeared to affect the performance he must move in the clouds.
41When performing the right steep turn with proper bank of 60 degrees:
- AStall pull rates will rise by about 40%.
- BStall pull rates will fall by about 20%.
- CStall pull rates will increase by around 60%.
- DStall speed does not change in the corner.
42 While turning:
- AThere is centripetal force, and overload.
- BThe force of gravity is exactly balanced by the lift.
- CDeceleration occurs.
- DPull rates decreases drag.
43The gravity load occurring in the turn (load factor) is:
- AThe total lift force divided by weight.
- BWeight divided by the lift.
- CLift divided by weight.
- DWeight divided by a string.
44At the start from an inclined runway - uphill - acceleration during the take-off run shall be .... and the take-off run shall ....:
- ASmaller, increases.
- BSmaller, decreases.
- CThere is no difference, does not affect the length of the run.
- DLarger, will decrease.
45 At the start from the runway of a favorable slope - from the top the aircraft take-off run shall:
- ADecrease.
- BIncrease.
- CThe slope of the runway has no effect on the length of the take-of run.
- DAll the answers are wrong.
46 Service ceiling is the pressure height of at which:
- ARate of climb of the aircraft reaches a certain, regulated by law value.
- BRate of climb of the aircraft reaches zero.
- CStall speed and critical speed of Mach aircraft are equal.
- DSpeed of the aircraft does not allow any horizontal maneuvers.
47The longest take-of run shall be from an airstrip of the following surface:
- AHigh grass.
- BLow grass.
- CConcrete.
- DAsphalt.
48 The plane has to be balanced in order to maintain stability:
- ALongitudinal.
- BLateral.
- CStatic lateral.
- DLateral and longitudinal dynamic.
49 The plane has to be balanced due to:
- ALongitudinal stability.
- BLateral stability.
- CNeed to maintain even load landing gear leg.
- DProtection against exceeding the critical angle of attack in all flight conditions.
50The effects of overloading are:
- AIncrease the speed of takeoff speed and secure, longer distance to takeoff and landing, reducing the rate of climb, the possibility of damage to the airplane structure.
- BLowering the speed and the speed safe takeoff, there is no change in performance engines.
- CLowering the speed takeoff and safe speed and the possibility of damage to the airplane structure.
- DThe increase in take-off speed and increased range and endurance.
51Extending flaps reduces:
- ALift to drag ratio.
- BInduced drag.
- CRestricts pilot view due to increased angle of attack.
- DLift required for horizontal flight.
52 In a given aircraft we have two possible landing flaps positions: 0 and 10. In order to obtain a shorter ground roll the following should be used:
- A10.
- B0.
- CThe position of the flaps has no influence on the length of the ground roll.
- DAll the answers given are false.
53 In a standard configuration center of gravity (counting from the front) is:
- ABefore the aerodynamic center.
- BExactly in the aerodynamic center.
- CAlways exactly under the aerodynamic center.
- DBehind the aerodynamic center.
54Weighing of the aircraft: front wheel 1000kg, left and right wheels 5000 kg each. The distance between the front wheel and the main one is 10 m. How many meters from the wheels of the main chassis is the centre of gravity?
- A0.91 m.
- B0.75 m.
- C9.1 m.
- D0.81 m.
55The phenomenon consisting in the horizontal stabilizer icing:
- AMay lead to the stall of the horizontal stabilizer and the entry aircraft in an uncontrolled dive.
- BOnce there, it requires the same actions on the part of the remote control - pass the control to another pilot, adding power.
- COccurs only on large passenger jets.
- DIt is the most dangerous high-speed flight, when the tilt control effectiveness is greatest.
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- Passed Exams Quiz on Flight Performance & Planning, created by Roman Eidia on 26/04/2018.
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- Roman Eidia
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