Cartes mémoires 081 POF Fragen (Seite 1 von 3)

Cartes-fiches	119
Langue	Deutsch
Catégorie	Technique
Niveau	Autres
Crée / Actualisé	05.06.2025 / 06.06.2025
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A downward adjustment of a trim tab in the longitudinal control system has the following effect:

The stick position stability increases

The stick position stability remains constant

The stick force stability remains constant

The stick force stability decreases

A negative tail stall is:

Flow reversal on the fin leading to flow re-attachment

Flow separation at the rear of the lower surface of the wing

A typical aerodynamic problem for canards

A sudden reduction in the downward aerodynamic force on the tailplane

A pitch up could be caused by:

Forward movement of the centre of pressure

A reduction in varying loads due to g-force

Lateral movement of the centre of gravity

Forward movement of the centre of gravity

A wing stalling angle is:

Increased in a high rate of turn.

Decreased in any turn.

Unaffected by a turn.

Decreased in a high rate of turn.

An aeroplane climbs to cruising level with a constant pitch attitude and maximum climb thrust (assume no supercharger). How do the following variables change during the climb? (gamma = flight path angle)

Gamma remains constant, angle of attack remains constant, IAS decreases

Gamma decreases, angle of attack increases, IAS remains constant

Gamma decreases, angle of attack increases, IAS decreases

Gamma decreases, angle of attack remains constant, IAS decreases

An aeroplane has static directional stability in a side-slip to the right, initially the:

Nose of the aeroplane tends to move to the left.

Nose of the aeroplane tends to move to the right.

Nose of the aeroplane will remain in the same direction.

Right wing tends to go down.

An aeroplane performs a right turn, the slip indicator is left of neutral. One way to co-ordinate the turn is to apply:

Less right bank

More right rudder

A higher turn-rate

More left rudder

An aeroplane's sideslip angle is defined as the angle between the:

Speed vector and normal axis

Speed vector and the horizontal plane

Speed vector and the plane of symmetry

Lateral axis and the horizontal plane

An aircraft has a stick force/g of 4 lb/g with the CG on the aft limit. With the CG on the forward limit it's at 12 lb/g. To perform a 3g turn with the CG in the middle of the CG range the stick force would be:

16 lb

18 lb

24 lb

8 lb

Blade angle of a propeller is defined as the angle between:

The thrust line and propeller torque

The chord line and plane of rotation

The angle of attack and chord line

The angle of attack and line of thrust

By what percentage does VA (EAS) change when the aeroplane's weight decreases by 10%?

10% lower

No change

19% higher

5% lower

C.P. of wing is forward of C.G. In which direction must the stabiliser be deflected for level flight?

Between 125 to 236 Kt up, from 237 Kt and higher down

Up

No influence

Down

Dihedral angle is the ...

upward and outward inclination of the main planes to the horizontal datum

angle between the main plane and the longitudinal axis

angle between the quarter chord line and the horizontal datum

angle measured between the main plane and the normal axis

Due to a vertical up-gust, the gust load factor increases when:

Altitude increases.

The gradient of the CL-alpha graph increases.

Wing loading increases.

Weight increases.

During a climbing turn to the right, which statement is correct?

The angle of attack of both wings is the same.

The angle of attack of the left wing is smaller than the angle of attack of the right wing.

The stall angle of attack of the left wing will be larger than the corresponding angle for the right wing.

The angle of attack of the left wing is larger than the angle of attack of the right wing.

From the options below, choose what the correct spin recovery technic involves:

2, 4, 5, 6

2, 3, 5

1, 4, 5

1, 4, 5, 6

Given is an initial condition in straight and level flight with a speed of 1.4 Vs. The maximum bank angle attainable without stalling in a steady coordinated turn, whilst maintaining speed and altitude, is approximately:

30°

60°

32°

44°

If a turbulent gust causes an aeroplane to roll, the ...

down-going wing experiences a decrease in angle of attack

down-going wing has no angle of attack

angle of attack depends on whether the aeroplane changes speed

down-going wing experiences an increase in angle of attack

If flaps are slightly asymmetric this would cause a ...

roll to a given bank angle which may be correctable with rudder

steady rate of roll which may be correctable with ailerons

roll to a given bank angle which may be correctable with ailerons

steady rate of pitch which may be correctable with elevators

If the aspect ratio of a wing increases whilst all other relevant factors remain constant, the critical angle of attack will:

Decrease.

Remain constant.

Increase.

Remain constant only for a wing consisting of symmetrical aerofoils.

If the elevator trim tab is deflected up, the cockpit trim indicator shows:

Nose left

Nose down

Neutral

Nose up

If the static lateral stability of an aeroplane is increased, whilst its static directional stability remains constant:

Its sensitivity to dutch roll increases

The nose-down pitching moment in a turn increases

Turning flight becomes more difficult

Its spiral stability decreases

If the sum of the moments in flight is not zero, a movement would take place about the ...

CP.

CG.

neutral point.

manoeuvre point.

If the total sum of moments about one of its axis is not zero, an aeroplane would:

Fly a path with a constant curvature.

Be difficult to control.

Experience an angular acceleration about that axis.

Not be affected because the situation is normal.

In a developed spin, the ...

angle of attack of both wings will be negative.

down going wing will be stalled and the upgoing wing will not be stalled.

angle of attack of one wing will be positive and the other will be negative.

angle of attack of both wings will be positive.

In a slipping turn (nose pointing outwards) compared with a co-ordinated turn, the bank angle (i) and the "ball" or slip indicator (ii) are respectively:

(i) too small; (ii) displaced towards the low wing.

(i) too large; (ii) displaced towards the high wing.

(i) too small; (ii) displaced towards the high wing.

(i) too large; (ii) displaced towards the low wing.

In a steady climb:

If the angle of climb is 20°, lift equals weight times sin 20°.

Thrust equals drag plus the weight component perpendicular to the flight path and lift equals the weight component along the flight path.

Thrust equals drag plus the weight component along the flight path and lift equals the weight component perpendicular to the flight path.

Thrust equals the weight component along the flight path and lift equals the sum of the components of drag and weight along the flight path.

In a straight steady descent, which of the following statements is correct?

Lift is equal to weight, load factor is less than 1.

Lift is less than weight, load factor is less than 1.

Lift is less than weight, load factor is equal to 1.

Lift is equal to weight, load factor is equal to 1.

In a twin-engined jet-powered aeroplane with engines mounted below the wing, the thrust is suddenly increased. Which elevator deflection will be required to maintain the pitching moment at zero?

Up

No elevator movement will be required because the thrust line of the engines remain unchanged

It depends on the position of the centre of gravity

Down

In order to perform a steady level turn at constant speed in an aeroplane, the pilot must increase ...

thrust/power and keep angle of attack un-changed

thrust/power and decrease angle of attack

thrust/power and angle of attack

angle of attack and keep thrust/power un-changed

Load factor is increased by:

Upward gusts

Forward CG movement

An increase in aeroplane mass

A decrease in air density

Mass balancing of control surfaces is used to ...

ensure that the control surfaces are in the mid-position during taxiing.

increase the stick force stability.

limit the stick forces.

prevent flutter of control surfaces.

MMO can be exceeded in a climb at a constant IAS because:

As altitude increases the local speed of sound increases

Maintaining a constant IAS requires an increase in TAS

Position error increases

At reduced density the Machmeter will under read

Near to a stall when increasing power, the vertical component produced

will oppose the weight thus giving a slightly lower stalling speed.

will oppose lift giving a smaller stalling angle.

induces a stall immediately.

will give a higher sink rate.

One advantage of mounting the horizontal tailplane on top of the vertical fin is:

To decrease the susceptibility to deep stall

To decrease fuel consumption by creating a tail-heavy situation

To improve the aerodynamic efficiency of the vertical fin

That it does not require a de-icing system

Positive static lateral stability is the tendency of an aeroplane to roll to the ...

left in case of a sideslip (nose pointing right of flow)

right in a right turn

left in case of a sideslip (nose pointing left of flow)

left in a right turn

Propeller efficiency may be defined as the ratio between:

Usable power of the propeller (power available) and shaft power.

The usable (power available) power and the maximum power.

The thrust and the maximum thrust.

The thermal power of fuel-flow and shaft power.

Static lateral stability should not be too small because:

The stick force per g would become unacceptably small

The aeroplane would show a too strong tendency to Dutch roll

The aeroplane would show a too strong tendency to spiral dive

The aeroplane would show a too strong tendency to return to the original attitude

The "normal" stall recovery procedure for a light single engined aeroplane is:

full power and stick roll-neutral nose-down, correcting for angle of bank with rudder

full power and stick roll-neutral nose-down, correction for angle of bank with stick

idle power and stick neutral, waiting for the natural nose down tendency

idle power and stick roll-neutral nose-down and no other corrections

The aerodynamic centre of the wing is the point, where:

aerodynamic forces are constant

the aeroplane's lateral axis intersects with the centre of gravity

change of lift due to variation of angle of attack is constant

pitching moment coefficient does not vary with angle of attack

081 POF Fragen

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