Differential aileron deflection is used to...

avoid a stall at low angles of attack.

Which constructive feature reduces adverse yaw?

Differential aileron deflection

The right aileron deflects upwards, the left downwards. How does the aircraft react?

Rolling to the right, yawing to the left

Rolling to the left, yawing to the right

Rolling to the right, yawing to the right

Rolling to the right, yawing to the left

The aerodynamic rudder balance...

reduces the control stick forces.

improves the rudder effectiveness.

Which constructive feature provides less stick forces?

Differential aileron deflection

What is the function of the static rudder balance?

To prevent control surface flutter

To limit the control stick forces

To increase the control stick forces

To trim the controls almost without any force

During cruise flight with constant power setting, an aircraft shows a permanent tendency to raise the nose. How can this tendency be eliminated?

By deflecting the elevator trim tab upwards

By shifting the center of gravity backwards

By deflecting the elevator trim tab downwards

By deflecting the elevator trim tab upwards

What is a bendable trim tab?

A fixed tab attached to the rudder or the aileron

A balance mass at a control surface

A trim device adjustable in flight

A fixed tab attached to the rudder or the aileron

card2brain.ch

What is the task of trim tabs?

Reduction of adverse yaw

Ensuring dynamic stability

Avoiding permanent stick forces

Adjusting bank angle to center of gravity position

Reduction of adverse yaw

Ensuring dynamic stability

Avoiding permanent stick forces

Adjusting bank angle to center of gravity position

The trim tab at the elevator is deflected upwards. In which position is the corresponding indicator?

Neutral position

Laterally trimmed

Nose-up position

Nose-down position

Neutral position

Laterally trimmed

Nose-up position

Nose-down position

What describes "wing loading"?

Wing area per weight

Drag per wing area

Drag per weight

Weight per wing area

Wing area per weight

Drag per wing area

Drag per weight

Weight per wing area

What has to be considered regarding VNE?

It must not be exceeded in any case

It may be exceeded only in smooth air

It may be briefly exceeded in turbulent air

It depends on loading and turbulence whether it may be exceeded

It must not be exceeded in any case

It may be exceeded only in smooth air

It may be briefly exceeded in turbulent air

It depends on loading and turbulence whether it may be exceeded

Through which factor listed below does the load factor increase during cruise flight?

An upward gust

Higher aeroplane weight

A forward centre of gravity

Lower air density

An upward gust

Higher aeroplane weight

A forward centre of gravity

Lower air density

Through which factor listed below does the load factor decrease during cruise flight?

A downward gust

An aft centre of gravity

Higher air density

Lower aeroplane weight

A downward gust

An aft centre of gravity

Higher air density

Lower aeroplane weight

Which statement regarding the "constant-speed propeller" is correct?

The propeller keeps the airspeed constant

The pitch of the propeller rises with higher speeds

The RPM decreases with lower speeds

The set RPM is kept constant by the motor power (MAP)

The propeller keeps the airspeed constant

The pitch of the propeller rises with higher speeds

The RPM decreases with lower speeds

The set RPM is kept constant by the motor power (MAP)

What is the advantage of a "constant-speed propeller" compared to a "fixed-pitch propeller"?

It is more efficient over a greater speed range

It is less susceptible to interference by technical defects

It is designed to generate a higher thrust

It has a larger surface area and produces more thrust

It is more efficient over a greater speed range

It is less susceptible to interference by technical defects

It is designed to generate a higher thrust

It has a larger surface area and produces more thrust

The change in pitch at a propeller blade from the root to the tip ensures...

a nearly constant load by a constant effective angle of attack over the entire length of the blade.

the largest possible angle of attack at the blade tip.

that the most thrust is produced at the blade root.

that the most thrust is produced at the blade tip.

a nearly constant load by a constant effective angle of attack over the entire length of the blade.

the largest possible angle of attack at the blade tip.

that the most thrust is produced at the blade root.

that the most thrust is produced at the blade tip.

After an engine failure, the windmilling propeller...

generates drag rather than thrust.

generates neither thrust nor drag.

improves the properties of the glide.

has a greater pitch in feathered position.

generates drag rather than thrust.

generates neither thrust nor drag.

improves the properties of the glide.

has a greater pitch in feathered position.

During a descent at idle power with constant speed, the propeller lever is moved backwards. How do the propeller pitch and sink rate change?

Propeller pitch is increased, sink rate is decreased

Propeller pitch is increased, sink rate is increased

Propeller pitch is decreased, sink rate is decreased

Propeller pitch is decreased, sink rate is increased

Propeller pitch is increased, sink rate is decreased

Propeller pitch is increased, sink rate is increased

Propeller pitch is decreased, sink rate is decreased

Propeller pitch is decreased, sink rate is increased

Point number 4 in the figure indicates which flight state? See figure (PFA-008)

Minimum drag

Best gliding angle

Inverted flight

Stall

Minimum drag

Best gliding angle

Inverted flight

Stall

Point number 1 in the figure indicates which flight state? See figure (PFA-008)

Minimum drag

Best gliding angle

Inverted flight

Stall

Minimum drag

Best gliding angle

Inverted flight

Stall

Point number 3 in the figure indicates which flight state? See figure (PFA-008)

Minimum drag

Best gliding angle

Inverted flight

Stall

Minimum drag

Best gliding angle

Inverted flight

Stall

To keep speed and altitude constant during a turn, compared to horizontal flight, the pilot has to...

increase the angle of attack and increase the thrust.

keep the angle of attack constant and increase the thrust.

decrease the angle of attack and increase the thrust.

increase the angle of attack and keep the thrust constant.

increase the angle of attack and increase the thrust.

keep the angle of attack constant and increase the thrust.

decrease the angle of attack and increase the thrust.

increase the angle of attack and keep the thrust constant.

The bank in a two-minute turn (rate one turn) depends on the...

TAS.

weight.

load factor.

wind.

TAS.

weight.

load factor.

wind.

In a co-ordinated turn, how is the relation between the load factor (n) and the stall speed (Vs)?

N is greater than 1, Vs is greater than in straight and level flight.

N is greater than 1, Vs is smaller than in straight and level flight.

N is smaller than 1, Vs is smaller than in straight and level flight.

N is smaller than 1, Vs is greater than in straight and level flight.

N is greater than 1, Vs is greater than in straight and level flight.

N is greater than 1, Vs is smaller than in straight and level flight.

N is smaller than 1, Vs is smaller than in straight and level flight.

N is smaller than 1, Vs is greater than in straight and level flight.

Which statement concerning a flight during a turn is correct?

More lift than in straight and level flight is needed

The same amount of lift as in straight and level flight is needed

Less lift than in straight and level flight is needed.

Less lift than in a descent is needed.

More lift than in straight and level flight is needed

The same amount of lift as in straight and level flight is needed

Less lift than in straight and level flight is needed.

Less lift than in a descent is needed.

How is the balance of forces affected during a turn?

Lift force must be increased to compensate for the sum of centrifugal and gravitational force

A lower lift force compensates for a lower net force as compared to level flight

The horizontal component of the lift force during a turn is the centrifugal force

The net force results from superposition of gravity and centripetal forces

Lift force must be increased to compensate for the sum of centrifugal and gravitational force

A lower lift force compensates for a lower net force as compared to level flight

The horizontal component of the lift force during a turn is the centrifugal force

The net force results from superposition of gravity and centripetal forces

The elevator deflection during take-off rotation...

is increased for a front centre of gravity.

is increased at high speeds.

is increased for a rear centre of gravity.

is independent of the speed.

is increased for a front centre of gravity.

is increased at high speeds.

is increased for a rear centre of gravity.

is independent of the speed.

With regard to the forces acting, how can stationary gliding be described?

The sum of air forces acts along the direction of air flow

The sum of air forces acts along with the lift force

The lift force compensates the drag force

The sum of air forces compensates the gravity force

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

The sum of air forces acts along the direction of air flow

The sum of air forces acts along with the lift force

The lift force compensates the drag force

The sum of air forces compensates the gravity force

What is the result of extending flaps with increasing aerofoil camber?

Maximum permissible speed increases

Minimum speed increases

Minimum speed decreases

C.G. position moves forward

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

Maximum permissible speed increases

Minimum speed increases

Minimum speed decreases

C.G. position moves forward

Following a single-wing stall and pitch-down moment, how can a spin be prevented?

Deflect all rudders opposite to lower wing

Rudder opposite lower wing, releasing elevator to build up speed

Pushing the elevator to build up speed to re-attach airflow on wings

Pulling the elevator to bring the plane back to normal attitude

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

Deflect all rudders opposite to lower wing

Rudder opposite lower wing, releasing elevator to build up speed

Pushing the elevator to build up speed to re-attach airflow on wings

Pulling the elevator to bring the plane back to normal attitude

Considering longitudinal stability, which C.G. position is most dangerous with a normal gliding plane?

Position beyond the rear C.G. limit

Position beyond the front C.G. limit

Position far back within permissible C.G. limits

Position too far aside permissible C.G. limits

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

Position beyond the rear C.G. limit

Position beyond the front C.G. limit

Position far back within permissible C.G. limits

Position too far aside permissible C.G. limits

The static pressure of gases works...

in all directions

only in flow direction

only in the direction of the total pressure

only vertical to the flow direction

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

in all directions

only in flow direction

only in the direction of the total pressure

only vertical to the flow direction

Which are the correct parameters of the International Standard Atmosphere (ISA)?

1013.25 hPa at MSL, +15° C at MSL, environmental lapse rate 2°/1000 ft

1000 hPa at MSL, +15° C at MSL, environmental lapse rate 2°/100 m

1013.25 hPa at 36000 ft, -56.5° C at the tropopause, environmental lapse rate 2°/1000 ft

1013.25 hPa at MSL, 0° C at MSL, environmental lapse rate 2°/1000 ft

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

1013.25 hPa at MSL, +15° C at MSL, environmental lapse rate 2°/1000 ft

1000 hPa at MSL, +15° C at MSL, environmental lapse rate 2°/100 m

1013.25 hPa at 36000 ft, -56.5° C at the tropopause, environmental lapse rate 2°/1000 ft

1013.25 hPa at MSL, 0° C at MSL, environmental lapse rate 2°/1000 ft

Bernoulli's equation for frictionless, incompressible gases states that...

total pressure = dynamic pressure - static pressure

total pressure = dynamic pressure + static pressure

static pressure = total pressure + dynamic pressure

dynamic pressure = total pressure + static pressure

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

total pressure = dynamic pressure - static pressure

total pressure = dynamic pressure + static pressure

static pressure = total pressure + dynamic pressure

dynamic pressure = total pressure + static pressure

If surrounded by airflow (v>0), any arbitrarily shaped body produces...

drag

constant drag at any speed

drag and lift

lift without drag

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

drag

constant drag at any speed

drag and lift

lift without drag

All aerodynamic forces can be considered to act on a single point. This point is called...

center of gravity

lift point

transition point

center of pressure

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

center of gravity

lift point

transition point

center of pressure

The center of pressure is the theoretical point of origin of...

all aerodynamic forces of the profile.

gravity forces of the profile.

all forces of the profile.

only the resulting total drag.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

all aerodynamic forces of the profile.

gravity forces of the profile.

all forces of the profile.

only the resulting total drag.

Number 1 in the drawing corresponds to the... See figure (PFA-010)

chord.

chord line.

trailing edge.

camber line.

chord.

chord line.

trailing edge.

camber line.

Number 2 in the drawing corresponds to the... See figure (PFA-010)

angle of attack.

chord line.

chord.

profile thickness.

angle of attack.

chord line.

chord.

profile thickness.

Number 3 in the drawing corresponds to the... See figure (PFA-010)

camber line.

chord line.

chord.

thickness.

camber line.

chord line.

chord.

thickness.

Number 4 in the drawing corresponds to the... See figure (PFA-010)

camber.

thickness.

chord line.

trailing edge.

camber.

thickness.

chord line.

trailing edge.

The angle between the chord line and the direction of the oncoming airflow is called...

angle of stream.

angle of incidence.

angle of attack.

angle of lift.

angle of stream.

angle of incidence.

angle of attack.

angle of lift.

Which type of boundary layer does the figure show? See figure (PFA-001) BL: Boundary layer SF: Surface

Laminar boundary layer

Turbulent boundary layer

Separated boundary layer

Interference layer

Laminar boundary layer

Turbulent boundary layer

Separated boundary layer

Interference layer

The angle of attack is the angle between...

the chord line and the oncoming airflow.

the chord line and the longitudinal axis of an aeroplane.

the undisturbed airflow and the longitudinal axis of an aeroplane.

the wing and the fuselage of an aeroplane.

the chord line and the oncoming airflow.

the chord line and the longitudinal axis of an aeroplane.

the undisturbed airflow and the longitudinal axis of an aeroplane.

the wing and the fuselage of an aeroplane.

Which type of boundary layer does the figure show? See figure (PFA-002) BL: Boundary layer SF: Surface

Laminar boundary layer

Turbulent boundary layer

Separated boundary layer

Interference layer

Laminar boundary layer

Turbulent boundary layer

Separated boundary layer

Interference layer

The ratio of span and mean chord length is referred to as...

wing sweep.

trapezium shape.

tapering.

aspect ratio.

wing sweep.

trapezium shape.

tapering.

aspect ratio.

Which point on the aerofoil is represented by number 2? See figure (PFA-009)

Transition point

Separation point

Stagnation point

Center of pressure

Transition point

Separation point

Stagnation point

Center of pressure

Principles of Flight - AC

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Principles of Flight - AC

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