Cartes mémoires Ppla 030 Flight performance

Cartes-fiches	55
Langue	English
Catégorie	Technique
Niveau	Autres
Crée / Actualisé	19.04.2022 / 25.04.2022
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When performing the right steep turn with proper bank of 60 degrees:

Stall pull rates will rise by about 40%.

Stall pull rates will fall by about 20%.

Stall pull rates will increase by around 60%.

Stall speed does not change in the corner.

Stall pull rates will rise by about 40%.

Stall pull rates will fall by about 20%.

Stall pull rates will increase by around 60%.

Stall speed does not change in the corner.

While turning:

There is centripetal force, and overload.

The force of gravity is exactly balanced by the lift.

Deceleration occurs.

Pull rates decreases drag.

There is centripetal force, and overload.

The force of gravity is exactly balanced by the lift.

Deceleration occurs.

Pull rates decreases drag.

The gravity load occurring in the turn (load factor) is:

The total lift force divided by weight.

Weight divided by the lift.

Lift divided by weight.

Weight divided by a string.

The total lift force divided by weight.

Weight divided by the lift.

Lift divided by weight.

Weight divided by a string.

At the start from an inclined runway - uphill - acceleration during the take-off run shall be .... and the take-of run shall ....:

Smaller, increases.

Smaller, decreases.

There is no difference, does not affect the length of the run.

Larger, will decrease.

Smaller, increases.

Smaller, decreases.

There is no difference, does not affect the length of the run.

Larger, will decrease.

At the start from the runway of a favourable slope - from the top the aircraft tke-off run shall:

Decrease.

Increase.

The slope of the runway has no effect on the length of the take-of run.

All the answers are wrong.

Decrease.

Increase.

The slope of the runway has no effect on the length of the take-of run.

All the answers are wrong.

Service ceiling is the pressure height of at which:

Rate of climb of the aircraft reaches a certain, regulated by law value.

Rate of climb of the aircraft reaches zero.

Stall speed and critical speed of Mach aircraft are equal.

Speed of the aircraft does not allow any horizontal maneuvers.

Rate of climb of the aircraft reaches a certain, regulated by law value.

Rate of climb of the aircraft reaches zero.

Stall speed and critical speed of Mach aircraft are equal.

Speed of the aircraft does not allow any horizontal maneuvers.

The longest take-of run shall be from an airstrip of the following surface:

High grass.

Low grass.

Concrete.

Asphalt.

High grass.

Low grass.

Concrete.

Asphalt.

The plane has to be balanced in order to maintain stability:

Longitudinal.

Lateral.

Static lateral.

Lateral and longitudinal dynamic.

Longitudinal.

Lateral.

Static lateral.

Lateral and longitudinal dynamic.

The plane has to be balanced due to:

Longitudinal stability.

Lateral stability.

Need to maintain even load landing gear leg.

Protection against exceeding the critical angle of attack in all flight conditions.

Longitudinal stability.

Lateral stability.

Need to maintain even load landing gear leg.

Protection against exceeding the critical angle of attack in all flight conditions.

The effects of toverloading are:

Increase 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.

Lowering the speed and the speed safe takeoff, there is no change in performance engines.

Lowering the speed takeoff and safe speed and the possibility of damage to the airplane structure.

The increase in take-off speed and increased range and endurance.

Increase 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.

Lowering the speed and the speed safe takeoff, there is no change in performance engines.

Lowering the speed takeoff and safe speed and the possibility of damage to the airplane structure.

The increase in take-off speed and increased range and endurance.

Extending flaps reduces:

Lift to drag ratio.

Induced drag.

Restricts pilot view due to increased angle of attack.

Lift required for horizontal flight.

Lift to drag ratio.

Induced drag.

Restricts pilot view due to increased angle of attack.

Lift required for horizontal flight.

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:

10.

0.

The position of the flaps has no influence on the lengh of the ground roll.

All the answers given are false.

10.

0.

The position of the flaps has no influence on the lengh of the ground roll.

All the answers given are false.

In a standard configuration centre of gravity (counting from the front) is:

Before the aerodynamic centre.

Exactly in the aerodynamic centre.

Always exactly under the aerodynamic centre.

Behind the aerodynamic centre.

Before the aerodynamic centre.

Exactly in the aerodynamic centre.

Always exactly under the aerodynamic centre.

Behind the aerodynamic centre.

Weighing 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?

0.91 m.

0.75 m.

9.1 m.

0.81 m.

0.91 m.

0.75 m.

9.1 m.

0.81 m.

The phenomenon consisting in the horizontal stabilizer icing:

May lead to the stall of the horizontal stabilizer and the entry aircraft in an uncontrolled dive.

Once there, it requires the same actions on the part of the remote control - pass the control to another pilot, adding power.

Occurs only on large passenger jets.

It is the most dangerous high-speed flight, when the tilt control effectiveness is greatest.

May lead to the stall of the horizontal stabilizer and the entry aircraft in an uncontrolled dive.

Once there, it requires the same actions on the part of the remote control - pass the control to another pilot, adding power.

Occurs only on large passenger jets.

It is the most dangerous high-speed flight, when the tilt control effectiveness is greatest.

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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).

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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 .

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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).

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.