Set of flashcards Ppla 030 Flight performance (Page 1 of 2)

Flashcards	55
Language	English
Category	Technology
Level	Other
Created / Updated	19.04.2022 / 25.04.2022
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Barometric error occurs when:

Sea level pressure (Mean Sea Level) is different from the 1013.25hPa.

Pressure gradient is different from QNH .

Pressure gradient is different from the ISA.

The altimeter was heated (eg. sunshine) to high temperature.

Temperature error occurs when:

Calibrated according to the altimeter ISA atmosphere.

The altimeter is calibrated by QNH.

The altimeter is calibrated by QFE.

Is calibrated according to the altimeter QNE.

Component weight 55 kg, arm = 2.3 m. The moment [kgm] ?

126.5.

23.9.

6957.

0.0418.

If the center of gravity is near the extreme forward position, this shall:

Decrease in force on the stick.

Increase in force on the stick.

The plane is unstable sedately.

Will occur less force on the stick.

The international standard atmosphere (International Standard Atmosphere) defines the following conditions at the sea level: temperature / pressure / density / temperature gradient:

15°C / 1013,25 hPa / 1.225 kg/m3 / -6.5°C per 1000 m.

15°C / 1013,25 mb / 1.225 kg/m3 / 1.98°C per 1000 m.

0°C / 1.013 Bar / 1225 g/m3 / 1.98°C per 1000 ft.

15°C / 29.92 in.Hg / 1013 kg/m3 / 1.98°C per 1000 ft.

The center of gravity can be defined as:

The percent mean aerodynamic chord (% MAC) or distance (mm, cm, inch) CG the measuring point "DATUM".

Percentage of dynamic chord severity (% MAC).

As a percentage of the fuselage aerodynamic chord (% MAC).

Percentage of dynamic chord counted in the average range (% MAC).

The center of gravity can be defined as:

The point where the concentrated mass of the aircraft is.

Point to which they are applied all the forces acting on the aircraft.

The point to which the applied forces are supporting and gravity - acting on the aircraft.

Point to which they are applied drag force acting on the aircraft.

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?

1.88m .

2.92m .

3.2m .

1.68m .

Weighing 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?

2.04 m.

3.12 m.

1.88 m.

2.09 m.

Formula fo the moment ?

Force (weight) multiplied by the arm of force.

Force (weight) divided by the arm of force.

Strength (w) x distance from the center of gravity datum.

Arm of force divided by the force (weight).

The pressure altitude of the airport on a particular day can be determined:

By reading the amount indicated by the altimeter set to 1013.2 hPa.

Read the height of the altimeter driven 1013.2hPa, and then we correct it, because it reads the ambient temperature.

Better observations of the environment by the pilot because of the wider field of view close to the ground.

Achieving greater thrust to the ground - this effect disappears at a height approximately equal to the span of the aircraft.

"The influence of the earth" allows:

The separation of aircraft at the lower speed, but the phenomenon disappears at an altitude of approximately equal span and performance decline.

Achieve greater engine power to the ground (for engines without compressor).

Better observations of the environment by the pilot because of the wider field of view close to the ground.

Achieving greater thrust to the ground - this effect disappears at a height approximately equal to the span of the aircraft.

"The influence of the earth " is a phenomenon consisting in:

Reduction of induced drag and angle of attack required for level flight (at a given speed), which is due to the proximity of the ground.

Withstanding the significant shortening of the landing phase.

Achieving greater power by internal combustion engines near the ground (for naturally aspirated engines).

Achieving greater thrust to the ground - this effect disappears at a height approximately equal to the span of the aircraft.

For the hydroplaning phenomenon (dynamic) to take place during the run / roll of the airplane the following factors are necessary:

The 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.

Aircraft tire treads must heat up to high temperatures during intense braking on wet runway.

One of the wheels plane must be locked (e.g. failure of anti-skid) on the wet runway.

"Hydroplaning '"is a term for only a seaplane landing on a smooth surface.

What is VX?

Best Angle of Climb. This is the speed at which the best climb gradient is achieved. Best Angle of Climb.

This is the speed at which achieves the best rate of climb Rate of Climb Best.

To speed the decision at which the conditions are safe and continue to break off.

Is the speed at which the best value is achieved for the lift force.

What is VY?

Best Rate of Climb. Best Rate of Climb.

Best Angle of Climb. Best Angle of Climb.

To speed the decision at which the conditions are safe and continue to break off.

Is the speed at which the best value is achieved for the lift force.

Does high humidity contribute to decrease in the aircraft performance?

Yes.

False - it cools the engine and thus improves performance.

Humidity has no effect on performance.

All the answers are wrong.

For each combination of the altitude of the flight and aircraft weight, in the scale of minimum to maximum speed there is:

An approach angle at which the lift force is equal to the weight and it is possible to level flight.

Such a tilt that ensures that the lift force is equal to the weight and it is possible to level flight.

Such an approach angle at which the resistance force is equal to the string generated by the engines and it is possible to level flight.

Such 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.

High density altitude (in relation to low density altitude) means:

Low air density and low aircraft performance.

High air density and low aircraft performance.

High air density and high aircraft performance.

Low air density and high aircraft performance.

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?

Increasing the length of the run.

Reducing the length of the run.

The ambient temperature does not affect the length of the run.

All the answers are wrong.

How will the plane take-off from an airport located in the mountains influence the lengh 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?

Start from the highly situated airport - greater long run.

Reducing the length of run.

Elevation of the airport does not affect the length of the run.

All the answers are wrong.

How will the use of higher flap setting (than usual) influence the length of the take-off run?

Reducing the length of the take-off run.

Increasing the length of the take-off run.

It has no effect on the length of the take-off run.

All the answers are wrong.

How will increase of the weigh of the aircraft influence the lengh of the take-off run?

Increasing the length of the take-off run.

Reducing the length of run.

It has no effect on the length of the run.

All the answers are wrong.

What shall be the effects of changes in ambient temperature on the performance of the aircraft if all other parameters remain unchanged?

The temperature drop will increase the gradient of the climb.

The increase in temperature would reduce the distance required for takeoff.

The temperature drop will increase the distance required for takeoff.

The increase in temperature would reduce the distance required for takeoff and landing.

What shall be the effects of changes in ambient temperature on the performance of the aircraft if all other parameters remain unchanged?

The temperature drop will reduce the distance required for takeoff.

The increase in temperature would reduce the distance required for takeoff.

The temperature drop will increase the distance required for takeoff.

Changes in ambient temperature do not change the distance required for takeoff.

If the center of gravity is near the extreme front position:

This will reduce the rate of climb.

Because of the need to lower the amount of rudder - Supporting decreases the force required to slice - it reduces the stall speed.

A reduction of fuel consumption during the flight due to less resistance.

A reduction of induced drag.

If the centre of gravity is maximum forward position the aircraft among others shall:

Due to the need for a greater amount of rudder - increases the required lift force on the panel - increases induced drag, which negatively affects performance.

Because 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.

Because of the need to lower the amount of rudder - Supporting decreases the force required to slice - it reduces the stall speed.

Due to the need for a greater amount of rudder - Supporting decreases the force required to slice - the stall speed increases.

The direction of the airstrip 040 °, wind 270/18 kt (ATIS). What are the components of the wind?

The tail: 12 kt, cross - left 14 kt.

Head: 12 kt, cross - the right of 14 kt.

Head: 16 kt, cross - the right of 16 kt.

The tail: 8 kt, cross - left 21 kt.

The direction of the airstrip 150 °, wind 220/22 kt (ATIS). What are the components of the wind?

Head: 8 kt, cross - the right of 21 kt.

Head: 14 kt, cross - the right of 17 kt.

Head: 4 kt, cross - right 22 kt.

The tail: 8 kt, cross - left 21 kt.

The direction of the airstrip 200 °, wind 080 thirteenths kt (ATIS). What are the components of the wind?

The tail: 7 kt, cross - left 11 kt.

Head: 7 kt, cross- right 11 kt.

Head: 4 kt, cross - right 12 kt.

The tail: 8 kt, cross - left 12 kt.

The direction of the airstrip 220 °, wind 160/26 kt (ATIS). What are the components of the wind?

Head: 13 kt, cross - left 23 kt.

Head: 14 kt, cross - the right of 17 kt.

Head: 9 kt, cross - the right of 23 kt.

The tail: 13 kt, cross - left 22 kt.

The direction of the airstrip 330 °, wind 250/15 kt (ATIS). What are the components of the wind?

Head: 3 kt, cross - left 15 kt.

Head: 8 kt, cross - left 13 kt.

The tail: 3 kt, cross - left 15 kt.

The tail: 3 kt, cross - the right of 15 kt.

Which of the given combinations of weather conditions prevailing at the airport at the start shall contribute to the largest drop of the aircraft performance:

High temperature, high density altitude, high humidity.

Low temperature, high density altitude, low humidity.

High temperature, low density altitude, low humidity.

Low temperature, low density altitude, low humidity.

Which of the given combinations of weather conditions prevailing at the airport at the start shall contribute to the largest drop of the aircraft performance:

High density altitude and high ambient temperature.

Strong wind front.

Poor rainfall and low, but positive temperature.

Low ambient temperature.

Mach number is the ratio of the:

TAS-speed and local speed of sound.

IAS-speed and local speed of sound.

IAS speed and the speed of sound at a given height referred to the ISA.

TAS speed and the speed of sound at sea level.

The Maximum structural landing mass (Maximum Structural Landing Mass) is:

Maximum weight for landing under normal circumstances.

Maximum landing mass-impassable - even in emergency situations because of the certainty of destruction of the structure.

Maximum weight for landing in emergency situations (1.3 times the normal weight for landing).

Maximum weight for takeoff and landing in an emergency (1.3 times the normal weight for landing).

Low density altitude means that:

The air density is high - ie the aircraft's performance will be better than in the case of high density altitude.

The air density is high - ie the aircraft's performance will be much worse than in the case of high density altitude.

The air density is low, which causes a drop in airplane performance compared to the case of high density altitude.

The air density is high, which causes a drop in airplane performance compared to the case of high density altitude.

The most economical angle in terms of fuel use/range is the one which produces:

The best ratio of carrier power to resist - that the most economical approach angle is fixed for each combination of altitude and aircraft weight.

The best ratio of carrier power to resist - that the most economical approach angle increases with the mass of the airplane and the flight altitude.

The best value for the resistance forces.

The best ratio of lift to the string.

With reference to the influence of "ground effect" it is true that:

This phenomenon disappears at an altitude of approximately equal span of aircraft / glider and performance decline.

Significantly reduces the phenomenon of withstanding the landing phase.

Improves gradient of climb at an altitude of 150 m.

Significantly increases the stall speed.

With reference to the influence of icing on the aircrafts performance it is true that:

Even minor pollution such as "sandpaper" surface of the carrier may have a dangerous effect on performance.

Ice on the upper surface of the wing / rotor blades is less dangerous than the bottom.

The main factor influencing the performance of aircraft is the mass deposited on them ice.

For aircraft icing appeared to affect the performance he must move in the clouds.

Ppla 030 Flight performance

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