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When an aircraft is fitted with differential ailerons, the aileron with the greater deflection is the...

down-going aileron.

up-going aileron.

outer aileron.

inner aileron.

A shock wave on a lift generating wing will:

be situated at the greatest wing thickness when the aeroplane reaches the speed of sound.

move forward as Mach number is increased.

move slightly forward in front of an upward deflecting aileron.

reach its highest strength when flying at the critical Mach number.

Refer to figure. The two aircraft in the figure above are identical aircraft types, and are flying at the same Mach number. Their wings are not designed for sustained high speed flight. Which of the following is correct?

Aircraft 2 has a lower high-speed stall speed and therefore a higher buffet margin.

Aircraft 1 has a higher low-speed stall speed and therefore a higher buffet margin.

Aircraft 1 has a lower buffet margin.

Aircraft 2 must have a higher mass, and has a lower buffet margin.

The following is a correct design gust value factor applied in certification under EASA CS-25:

50 ft/sec at VD.

25 ft/sec at VD.

66 ft/sec at VC.

55 ft/sec at VB.

For a conventional aeroplane with the aerodynamic centre behind the aeroplane’s centre of gravity, the presence of significant ice on the leading edge of the tailplane can cause the tailplane to stall. This could cause an uncontrollable pitch...

down, and is more likely when the elevator is moved relatively up or when the wing flaps are extended.

up, and is more likely when the elevator is moved relatively down or the wing flaps are retracted.

up, and is more likely when the elevator is moved relatively down or when the wing flaps are extended.

down, and is more likely when the elevator is moved relatively up or the wing flaps are retracted.

The negative manoeuvring limit load factor for a transport aeroplane in the clean configuration at VD may not be less than:

-1.52.

0.

-3.0.

-1.

Which of these statements about the gust load factor on an aeroplane are correct or incorrect? I. When the mass decreases, the gust load factor decreases. II. When the altitude increases, the gust load factor decreases.

I is correct, II is incorrect.

I is incorrect, II is incorrect.

I is correct, II is correct.

I is incorrect, II is correct.

While performing a go-around, an aircraft with a right-hand propeller will initially tend to...

yaw to the right and roll to the right.

yaw to the right and roll to the left.

yaw to the left and roll to the left.

yaw to the left and roll to the right.

Consider a swept back wing, with a sideslip to the right. The right wing experiences (I) _____ sweep, a(n) (II)_____ in lift, and that provides (III) _____ lateral stability.

(I) less; (II) decrease; (III) negative.

(I) less; (II) increase; (III) positive.

(I) more; (II) decrease; (III) negative.

(I) more; (II) increase; (III) positive.

Refer to figure. The maximum achievable load factor without buffet onset at FL380 at a mass of 90 tons is approximately...

1.5 g at M = 0.80.

2 g at M = 0.80.

1.75 g at M = 0.80.

1 g at M = 0.80.

If the right engine fails during flight, which of the following should the pilot do to maintain control of the aircraft?

Apply right rudder; bank towards the right.

Apply left rudder; maintain wings level.

Apply right rudder; maintain wings level.

Apply left rudder; bank towards the right.

Which of the following is a cause of form drag on an object in high-speed airflow?

The pressure difference between the leading edge and trailing edge.

The energy taken from the object to produce vortices at edges and corners.

The pressure change across a shock wave that forms on the surface.

The energy taken from the object surface by the boundary layer.

Given the following aeroplane configurations: 1. Clean wing. 2. Slats only extended. 3. Flaps only extended. Place these configurations in order of increasing critical angle of attack:

2, 3, 1.

1, 3, 2.

3, 1, 2.

2, 1, 3.

An aircraft demonstrates positive static directional stability. How does this relate to the interaction between the aircraft’s yawing moment coefficient, CN, and sideslip angle, β (beta)?

CN = 0 and the aircraft experiences a negative sideslip angle.

CN is positive and the aircraft experiences a negative sideslip angle.

CN is negative and the aircraft experiences a positive sideslip angle.

CN is positive and the aircraft experiences a positive sideslip angle.

In straight and steady flight on descent, thrust is...

Equal to drag.

Less than drag.

Equal to lift.

Greater than drag.

The speed for minimum sink rate, (I) _____, is (II) _____ than the speed for minimum descent angle.

(I) VMP, (II) lower

(I) VMP, (II) higher

(I) VMD, (II) higher

(I) VMD, (II) lower

According to CS-25, how is the minimum control speed (VMC) determined by the manufacturer?

Using nose-wheel steering to maintain directional control.

At a speed not more than 1.13 VS1 in the take-off configuration.

By assuming symmetric thrust on all engines.

By limiting rudder deflection to less than maximum available deflection.

Consider an aeroplane equipped with both leading edge slats and trailing edge flaps. What is the effect of the extension of leading-edge slats?

A reduction of the stalling speed, while extension of the trailing-edge flaps will increase the stalling speed.

A greater reduction of the stalling speed, compared to the reduction achieved by the extension of the trailing-edge flaps.

A lesser reduction of the stalling speed, compared to the reduction achieved by the extension of the trailing-edge flaps.

An increase of the stalling speed, while extension of the trailing-edge flaps will reduce the stalling speed.

During a straight steady climb: 1 – lift is less than weight. 2 – lift is greater than weight. 3 – load factor is less than 1. 4 – load factor is greater than 1. 5 – lift is equal to weight. 6 – load factor is equal to 1. Which of the following lists all the correct statements?

1 and 6.

1 and 3.

2 and 4.

5 and 6.

What is the consequence of decreasing the wing's upwash?

Increase induced drag since decrease of AoA.

Increase induced drag since effective AoA increases.

Decrease induced drag since decrease of AoA.

Decrease induced drag since effective AoA increases.

Refer to figure. The line representing the effect of the tail on the longitudinal static stability of an aeroplane is line (1) _____, and it has a (2) _____ contribution.

(1) Z; (2) stabilising

(1) Y; (2) stabilising

(1) Z; (2) destabilising

(1) Y; (2) destabilising

Approaching an airport in icing conditions, a significant amount of ice builds up on the tailplane. The tail negative angle of attack is very near the critical angle. What is likely to happen when the trailing edge flaps are extended?

Downwash increases, preventing a tailplane stall.

Downwash increases, and the tailplane stalls.

Lift increases, decreasing the stall speed of the tail.

Downwash decreases, preventing a tailplane stall.

On a twin propeller aircraft, while performing a go-around, a yaw to the left would be more likely in an aircraft with (1) _____ propellers due to (2) _____.

(1) clockwise; (2) gyroscopic effect

(1) clockwise; (2) asymmetric blade effect

(1) counterclockwise; (2) gyroscopic effect

(1) counterclockwise; (2) asymmetric blade effect

Refer to figure. What does point 4 correspond to?

CLMAX at critical AoA.

CL/CD MAX.

VMP.

1.32 VMD.

When roll spoilers are extended, the part of the wing on which they are mounted:

experiences extra drag, which generates a yawing moment. The speed difference between both wings generates the desired rolling moment.

experiences a reduction in lift, which generates the desired rolling moment. In addition there is a local increase in drag, which suppresses adverse yaw.

stalls. This causes a difference in lift between both wings, which generates the desired rolling moment.

is forced downwards as a reaction to the increased drag.

Assuming no compressibility effects, the correct relationship between stall speed, limit load factor (n) and VA is:

VA <= VS * SQRT (n).

VA >= VS * SQRT (n).

VA >= VS * 1/n.

VA <= VS * 1/n.

A test pilot is examining the interaction between roll and yaw in an aeroplane. They bank the wings slightly and without using the rudder, the aircraft eventually enters an unstable descending turn. The aircraft has high (1) _____ stability, and entered a (2) _____.

(1) directional; (2) spiral dive

(1) lateral; (2) spin

(1) directional; (2) spin

(1) lateral; (2) spiral dive

Maintaining a constant Flight Level and IAS, an aircraft flies into a colder airmass. Choose the correct statement:

Mach number increases. There is a risk of a high speed warning.

Mach number stays the same, but there is an increased risk of high speed buffet and a shock stall.

Mach number stays constant.

Mach number decreases, There is a risk of a low speed warning.

Assuming no flow separation and no compressibility effects the location of the aerodynamic centre of an aerofoil section...

moves forward when the angle of attack increases.

moves backward when the angle of attack increases.

is at approximately 50% chord irrespective of angle of attack.

is independent of angle of attack.

When the air is passing through a shock wave the static temperature will:

decrease.

stay constant.

decrease and beyond a certain Mach number start increasing again.

increase.

An aeroplane slows down at high altitude towards the stall. The aircraft might be considered to have stalled even below the critical angle of attack if...

control effectiveness reduces, such that large deflection is needed to maintain wings level.

maximum continuous thrust is required to remain in level flight.

buffet is so strong that it deters the pilot from further speed reduction.

the coefficient of lift decreases with increased angle of attack.

As altitude increases, the stall speed (IAS):

initially remains constant but at higher altitudes increases.

remains constant until the tropopause but at higher altitudes increases.

initially remains constant but at higher altitudes decreases.

remains constant regardless of altitude.

The pilot of a large jet transport aircraft sets the trimmable horizontal stabiliser for take-off. The take-off is delayed due to deteriorating weather conditions at the destination airport. The commander decides to uplift additional fuel, which shifts the CG aft of the initial position used to calculate the takeoff trim setting. How should the trailing edge of the horizontal stabiliser be moved to adjust for the CG shift?

Down

Up

The position of the CG does not affect the movement of the stabiliser

It does not need to move if the CG is between the AFT and FWD limits

You are flying a crop duster in the utility category with a VSO of 45 kts and a VS1 of 58 kts. What is the VA speed?

113 kt

66 kt

94 kt

122 kt

Complete the following statement about two asymmetrical aerofoils, an aerofoil made for a low speed aircraft and one made for a high speed aircraft, and their effect on the coefficient of lift vs angle of attack graph. The high speed aerofoil intersects the CL axis at a (1) _____ position and has a (2) _____ CLMAX than the low speed aerofoil.

(1) Lower; (2) Higher

(1) Lower; (2) Lower

(1) Higher; (2) Lower

(1) Higher; (2) Higher

Following an engine failure, rudder is used to counteract yaw and aileron to bank towards the live engine. For a given airspeed, aeroplane controllability will be better at a...

low aeroplane mass, due to greater rudder effectiveness because of greater sideslip.

low aeroplane mass, due to greater rudder effectiveness because of less sideslip.

high aeroplane mass, due to greater rudder effectiveness because of less sideslip

high aeroplane mass, due to greater rudder effectiveness because of greater sideslip.

Incipient spin is the term assigned to the phase of a spin...

After the initial couple of rotations but the aerodynamic forces present are not yet fully balanced.

After the initial couple of rotations and the aerodynamic forces present are in balance.

When the initial rotation starts but the aerodynamic forces present are not yet fully balanced.

When the initial rotation starts and the aerodynamic forces present are in balance.

Calculate the climb angle: Thrust: 200 000 Drag: 50 000 Weight: 700 000

20 degrees

21 degrees

45 degrees

12 degrees

A plain flap will increase CLMAX by:

increasing angle of attack.

increasing the camber of the aerofoil.

boundary layer control.

centre of lift movement.

The pilot of a light aeroplane is flying at a speed below the normal cruising speed, in a gentle turn to allow a passenger to look at something interesting on the ground. Which of the following might occur to warn the pilot that the aircraft is approaching the stall? 1. Heavy buffet of the elevator before approaching the stall, 2. Significant pitch-up of the nose immediately before the stall, 3. The audible stall warning sounds, 4. The controls become light and less effective close to but before the stall.

3 and 4

1 and 3

2 and 3

2 and 4

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