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You are in the transonic speed range and compressibility comes into effect. Which of the following factors is affected?

Static pressure.

Dynamic pressure.

Density.

Temperature.

A student pilot is flying with an instructor in a single engine aircraft. The instructor is demonstrating the effects of a stall shortly after take-off, specifically the effects of a stall during a turn. What are the initial effects of the stall in this scenario, and correct recovery procedures?

Increased roll towards the stalled wing; recover by increasing power and rolling wing level

Increased yaw towards the stalled wing; recover by reducing the angle of attack and applying the opposite rudder

Decreased yaw towards the stalled wing; recover by applying opposite aileron and reducing power

Increased pitch up; recover by reducing power and leveling the wings

The mean geometric chord of a wing is the...

wing area divided by the wing span.

wing area divided by the mean aerodynamic chord.

wingspan divided by the gross wing area.

wingspan squared divided by the wing area.

What will happen to the rate of descent if an aircraft descending at VMD slows down? VMD: speed for minimum drag. VMP: speed for minimum power required.

it will increase until VMP is reached, and then decrease.

It will increase.

It will decrease until VMP is reached, and then increase.

it will decrease.

The pitch up tendency of an aeroplane with swept back wings during a stall is caused by the...

forward movement of the centre of pressure.

aft movement of the centre of gravity.

forward movement of the centre of gravity.

aft movement of the centre of pressure.

You are the pilot flying of a medium jet aeroplane and you are using the autopilot to maintain a constant vertical speed and the autothrust is maintaining a constant airspeed (CAS) while flying a Continuous Descent Approach (CDA). As the aeroplane is gradually slowing down from minimum clean speed of 213 kt to 180 kt, you selected approach flaps. Disregarding any other factors, the...

vertical speed must be reduced to maintain the trajectory, and when the approach speed stabilises, the autothrust will demand more thrust to maintain the speed.

trajectory will initially become steeper as the flaps are extended but this reduction is offset by the slower airspeed, provided the vertical speed is maintained constant.

trajectory will become more shallow as the flaps are extended and the speed reduces, which require a higher vertical speed to be selected.

vertical speed must be increased to offset the greater lift produced when the flaps are extended, and the autothrust will demand less thrust due to lower airspeed.

Refer to figure. What is the effect of spoilers on the angle of attack and stall speed at a constant mass?

With decreasing spoilers, the angle of attack decreases and the stall speed increases.

With increasing spoilers, the angle of attack increases and the stall speed decreases.

With increasing spoilers, both the angle of attack and stall speed increase.

With increasing spoilers, both the angle of attack and stall speed decrease.

Regarding deep stall characteristics, identify whether the following statements are correct or incorrect: I. The combination of a wing with sweepback and a T-tail make an aeroplane prone to deep stall II. A stick shaker system is fitted to an aeroplane to resolve deep stall problems

I is incorrect, II is incorrect.

I is correct, II is correct.

I is correct, II is incorrect.

I is incorrect, II is correct.

Assuming ISA conditions and an aircraft which is travelling at the same IAS, what happens to the drag of the aircraft at 6 000 ft, compared to the drag at sea level?

It will increase by 21%.

It will increase by 10%.

It will not change.

It will decrease by 21%.

The load factor is less than 1 (one):

when weight is greater than lift.

in steady wings level horizontal flight.

during a steady horizontal turn.

during recovery after a wings level stall.

Consider a single engine aeroplane with a clockwise rotating propeller flying at a negative AoA. The P factor will move the thrust to the (1) _____ blade creating a (2) _____ yaw moment.

(1) upgoing; (2) left

(1) downgoing; (2) right

(1) downgoing; (2) left

(1) upgoing; (2) right

An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 10 kt. Assuming the angle of attack remains constant, the load factor will initially:

remain unchanged, since the angle of attack does not change.

decrease to 0.99.

decrease to 0.90.

decrease to 0.95.

Calculate the turn radius for an aircraft with a TAS of 120 kt and a 45° bank angle. (Assume g = 10 m/s²)

1440 m

220 m

381 m

5429 m

An aircraft with a far aft CG location enters a spin, which becomes fully developed. Which of the following aircraft attitudes would be most likely in this scenario?

Increasing nose down pitch with increasing speed.

A nose up attitude, reducing the spin rate.

The CG position does not affect the spin attitude of the aeroplane.

Nose level, making recovery difficult.

How does the location of the CG influence VMC?

A forward CG reduces VMC.

The CG location does NOT influence VMC if within the permissible CG limits.

The CG location does NOT influence VMC.

A forward CG increases VMC.

For an aeroplane in straight and level flight, deflecting the flaps (1) _____ wing tip vortices, because the production of lift moves closer to the (2) _____.

(1) decreases; (2) root

(1) decreases; (2) tip

(1) increases; (2) tip

(1) increases; (2) root

An aeroplane with mechanical flight controls is fitted with an electronic stabiliser trim system. During the cruise, with the autopilot maintaining straight and level flight, the pilot notices that the trim wheel is continuously running in one direction and the control column is slowly moving in the opposite direction. It is essential that the pilot...

keeps the autopilot and electric trim engaged as the pilot may be overcome by the out-of-trim forces that are normal when using automatic systems.

prevents any further movement of the CG before the static longitudinal stability of the aeroplane reaches a state that is outside of its limits.

disengages the electric trim function as the autopilot is masking the problem and controllability may become compromised.

disconnects the autopilot and takes manual control since the pilot can counteract any trim movement by using the elevator in manual flight.

The subsonic speed range...

ends at M=1.

implies both subsonic and supersonic speeds exist in the flow around the aeroplane.

ends at MCRIT.

ends at a Mach number just above M=1.

A pilot flies two similar aeroplanes, with the same aerofoil, and flies them at the same altitude, mass, speed and configuration. Aeroplane 2 has a longer fuselage and has been fitted with a larger wing area than aeroplane 1. Which of the following statements is correct, if both aeroplanes experience the same upward gust?

Aircraft 2 will experience a lower gust load because of higher wing area and higher aspect ratio.

Aircraft 1 will experience a lower gust load because of lower wing area and lower aspect ratio.

Aircraft 2 will experience a lower gust load because it has a larger wing area.

Aircraft 1 will experience a lower gust load because it has a smaller wing area and therefore a higher wing loading.

During a straight and steady climb, with constant RPM and climb angle...

drag is equal to weight.

thrust is less than drag.

thrust is greater than drag.

lift is greater than weight.

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 large, (ii) displaced towards the low wing.

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

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

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

You are flying at VMD, when you decide to increase your speed while maintaining straight and level flight. What is the effect?

You will be speed stable because drag decreases.

You will be speed stable because drag increases.

You will be speed unstable because drag increases.

You will be speed unstable because drag decreases.

Given:p = pressurerho = densityT = absolute temperatureThe relationship between pressure, density and absolute temperature of a given mass of air can be expressed as follows...

p × rho / T = constant

rho / (T × p) = constant

p / (rho × T) = constant

p × T / rho = constant

Flying a jet transport aircraft, your fuel consumption is higher than expected. You calculate that you have enough to arrive safely, so decide to keep flying to your destination. ATC clears you to descend at your discretion. Whilst calculating your top of descent, what speed would you choose to descend at and why?

Minimum drag speed: For minimum rate of descent.

Minimum drag speed: To maximise distance in the descent

Minimum power speed: For more time in the air.

Minimum power speed: For the minimum rate of descent (increasing time at higher altitude).

After take-off, the pilot monitoring retracts the flaps prematurely instead of the landing gear. Which of the following speed limitations may be broken?

VFE

VMO

VLE

VS

As altitude increases, an aircraft is subject to a(n) (1) _____ in aerodynamic damping, contributing to a(n) (2) _____ in dynamic stability.

(1) increase; (2) decrease

(1) decrease; (2) decrease

(1) increase; (2) increase

(1) decrease; (2) increase

The critical Mach number of an aeroplane is the free stream Mach number at which for the first time, somewhere on the aeroplane, the following occurs:

buffet.

supersonic flow.

local sonic flow.

a shock wave.

The neutral point is located _____ the aerodynamic centre of the main wings.

forward of

behind

in the same position as

independently of

You are flying an aircraft with a fixed pitch propeller with a constant power setting. What happens to the blade AoA and thrust produced when the airspeed (TAS) decreases while in flight?

Increases; Decreases

Increases; Increases

Decreases; Increases

Decreases; Decreases

In a large jet aeroplane with swept back wings, when applying more rudder to the inside of the turn, skidding the aeroplane, one of the hazards to consider is (1) _____ in angle of attack on the (2) _____ wing due to (3) _____ roll.

(1) an increase; (2) inner; (3) adverse

(1) a decrease; (2) outer; (3) adverse

(1) a decrease; (2) outer; (3) increased

(1) an increase; (2) inner; (3) increased

An aircraft wing has a CL of 0.38. The pilot deploys a stage of flaps, then decreases speed to maintain the same altitude. Which of the following is correct?

The new CL must be greater than 0.38 to maintain the same altitude.

The new CL is greater than 0.38 because flaps always increase the CL.

The new CL is 0.38 because you're still at the same altitude.

The new CL is less than 0.38.

On an aircraft with partially powered flight controls, which of the following provides the greatest force to the control surfaces?

Servo tabs.

The pilot.

The hydraulic system.

Spring tabs.

Following a microburst encounter on approach, during the go-around...

The pilot should delay applying maximum power until the aircraft is established in the climb.

It may be necessary to increase the pitch beyond the point at which a stall warning activates.

Speed control has greater priority than reaching an optimised pitch angle.

A pitch angle may be required that is close to the point of the onset of a stall warning.

In the flight service envelope (V-N) diagram, the horizontal and vertical axes represent...

EAS and load factor.

TAS and load factor.

EAS and wing loading.

TAS and wing loading.

Which of the following are advantages associated with the use of vortex generators?1. Increase in maximum CL/CD.2. Decrease in form drag.3. Delay in the separation of the boundary layer.4. Increase in critical angle of attack.

1, 3 and 4

3 and 4

1 and 2

2, 3 and 4

Refer to figure.The annex illustrates an aeroplane suffering an engine failure, while flying at the normal cruising speed. After dealing appropriately with the failure, the pilot prepares the aeroplane for landing. The pilot maintains wings level as the aeroplane is slowing down; as the airspeed decreases, larger variations in rudder input are required to maintain direction, even if thrust remains constant. One reason for this is because the...

amount of sideslip increases as speed decreases, making the airflow arrive at the vertical stabiliser at a greater angle, thereby reducing the rudder’s effectiveness.

amount of sideslip decreases with speed, making the airflow arrive at the vertical stabiliser at a smaller angle, thereby reducing the rudder’s effectiveness.

right side of the vertical stabiliser is stalling, since the sideslip, combined with the rudder input, results in an airflow that is beyond the stabiliser’s critical angle of attack.

left side of the vertical stabiliser is stalling since the rudder increases the effective camber to the point where the airflow separates, thereby reducing the rudder’s effectiveness.

What are the fences on top of the wing used for?

To produce a spanwise flow of high energy air, in order to reduce the amount of chordwise airflow on the wing.

To prevent spanwise airflow along the wing, which could otherwise lead to tip stalling.

To produce strong vortices over the lower surface of the wing, in order to keep its boundary layer attached.

To generate a vortex from the engine nacelle, acting as a chordwise fence, reducing the spanwise airflow of the wing.

If you are flying at 1.4 VS and accelerate to 2.4 VS, by how much will the coefficient of lift decrease?

58%

34%

42%

66%

A body is placed in a certain airstream. If the density of the airstream decreases to half its original value, the parasite drag will decrease by a factor of:

8

2

1.5

4

The effect of a ventral fin on the static stability of an aeroplane is as follows: (1=longitudinal, 2=lateral, 3=directional)

1: positive, 2: negative, 3: negative.

1: no effect, 2: negative, 3: positive.

1: no effect, 2: positive, 3: negative.

1: negative, 2: positive, 3: positive.

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