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An aeroplane is equipped with 2 basic yaw dampers that operate independently of the flight controls. Due to a hydraulic leak, one of the yaw dampers becomes unserviceable. The aeroplane is allowed to fly as long as one yaw damper is operational, however the pilots must not commence flight if both yaw dampers are unserviceable. Why must the aeroplane have at least one serviceable yaw damper?

The yaw damper enables the aeroplane to perform an Autoland since it uses rudder in order to maintain direction during landing.

The yaw damper reduces the pilots workload by coordinating turns and improving the static lateral stability of the aeroplane.

The aeroplane suffers from Dutch roll but remains controllable if the remaining yaw damper fails during flight.

The aeroplane becomes uncontrollable if there is NO yaw damper to improve slightly weak static directional stability.

Assuming constant speed, induced drag is:

proportional to the lift coefficient.

directly proportional to the airspeed.

inversely proportional to the square of the lift coefficient.

proportional to the square of the lift coefficient.

A multi-engine jet aircraft is fitted with underslung engines. The engines are mounted to the wing via a forward pylon. What effect does this have?

It aggravates aerodynamic flutter

It alleviates aerodynamic flutter

It decreases the maximum speed at which the aircraft can be safely operated

It has no effect on the aerodynamic flutter characteristics of the wing

Behind the transition point in a boundary layer:

the boundary layer gets thicker and the mean speed decreases.

the mean speed increases and the friction drag decreases.

the mean speed and friction drag increase.

the boundary layer gets thinner and the mean speed increases.

You are flying straight and level, with the rudder neutral. You deflect the rudder to the right and maintain the deflection. How does the resulting sideslip act on the moment about the normal axis?

Decreases the moment

Increases the moment

Leads to a constant rate of turn

Has no effect

Given a constant load factor, which of these statements about the variation of induced drag with changes of speed and mass are correct or incorrect? 1. When speed decreases, induced drag decreases. 2. When mass decreases, induced drag increases.

1 is incorrect, 2 is correct.

1 is correct, 2 is incorrect.

1 is incorrect, 2 is incorrect.

1 is correct, 2 is correct.

The correct definition of VS1 is:

the stall speed or the minimum steady flight speed obtained in a specified configuration.

the minimum steady flight speed obtained in a specified configuration.

the stall speed in the clean configuration.

the stall speed obtained in a specified configuration.

While flying a propeller aircraft flying straight and level with idle power and whilst maintaining constant airspeed, pushing the propeller lever forward will result in (1) _____ blade pitch and (2) _____ RPM.

(1) increased; (2) decreased

(1) increased; (2) increased

(1) decreased; (2) increased

(1) decreased; (2) decreased

What is/are the force(s) acting on a symmetrical aerofoil element when the upstream airflow is parallel to the chord line?

Lift and drag.

Weight and drag.

Zero force because zero lift is generated.

Weight only.

When the elevator is deflected upwards, it creates a moment around the centre of (1) _____ which will result in the aeroplane pitching (2) _____.

(1) pressure; (2) up

(1) gravity; (2) up

(1) gravity; (2) down

(1) pressure; (2) down

Comparing the differences between a horizontal trimmable stabiliser and an elevator trim tab which of these statements are correct or incorrect? I. When trimmed for zero elevator stick force a horizontal trimmable stabiliser causes more drag. II. An elevator trim tab enables a larger CG range.

I is correct, II is correct.

I is incorrect, II is incorrect.

I is incorrect, II is correct.

I is correct, II is incorrect.

In any given airflow, rho x A x V = constant, where: rho = density, A = cross-sectional area of the flow, V = Velocity. What is this principle known as?

Magnus effect.

Equation of continuity.

Venturi effect.

Bernoulli's principle.

What happens to the airflow’s static temperature (T), Mach number (M), and total pressure (Pt) when passing through a normal shock wave?

T decreases, M increases, Pt decreases.

T decreases, M increases, Pt increases.

T increases, M decreases, Pt decreases.

T increases, M decreases, Pt increases.

A pilot is flying an aeroplane whose clean configuration stall speed is 60 kt. While cruising at 95 kt the pilot has to take avoiding action against another aeroplane. The pilot banks the aeroplane sharply and during this manoeuvre, the aeroplane stalls. Why did the aeroplane stall at 95 kt?

In a turn, the aeroplane weight increases, which increases the stall speed.

A large movement of the ailerons causes both wings to stall at the tips.

The change in airflow due to rapid rolling causes the up-moving wing to stall.

A wing stalls when its critical angle of attack is exceeded, regardless of speed.

Which considerations have to be taken into account by the pilot when flying a multi-engine aircraft with a failed left engine, causing a sideslip, and the nose pointed to the right?

Throttle should be reduced on the operating engine to correct the sideslip.

The pilot should apply full rudder input to the left to counteract the sideslip and nose deviation to the right caused by the left engine failure.

The pilot should apply full power on the operating engine to counteract the left engine failure, without any additional consequences.

The angle of attack AoA of the fin increases when there is an increase in rudder input to the operating engine side of the aircraft.

Load factor is increased by:

forward CG movement.

an increase in aeroplane mass.

upward gusts.

a decrease in air density.

Consider the resultant force caused by pressure distribution around an aerofoil moving through the air, its originating point is the (1)_____ and its direction forms a(n) (2)_____ angle with the relative air flow.

(1) Aerodynamic Centre (AC); (2) acute (small)

(1) Aerodynamic Centre (AC); (2) 90 degrees

(1) Centre of Pressure (CP); (2) acute (small)

(1) Centre of Pressure (CP); (2) 90 degree

What happens when a pilot moves the flight controls backwards?

The elevator deflects downwards and increases the tailplane's positive angle of attack.

The elevator deflects downwards and increases the tailplane's negative angle of attack.

The elevator deflects upwards and increases the tailplane's positive angle of attack.

The elevator deflects upwards and increases the tailplane's negative angle of attack.

Consider a twin propeller aeroplane with wing-mounted engines that has suffered an engine failure. Which of the following situations and engine configurations would result in the least asymmetric yaw and roll being developed?

The failure of the right engine on a twin with counter-rotating propellers that rotate outwards.

The failure of the right engine on a twin with counter-rotating propellers that rotate inwards.

The failure of the left engine on a twin with counter-rotating propellers that rotate outwards.

The failure of the left engine on a twin with two right-hand propellers.

Skin friction drag is caused by the...

difference in pressure acting on the aerofoil's surface in the direction of flight.

air's viscosity producing shear forces within the boundary layer.

friction between the surface and the air molecules in direct contact with the surface.

loss of momentum within an airflow caused by the aerofoil changing the flow direction.

According to the pilot operating handbook, an aerobatic aeroplane has a flaps-down stall speed (Vs0) at its maximum certified operating mass of 48 kt. Its flaps-up stall speed (Vs1) is 57 kt. What is the value of VA?

101 kt

140 kt

120 kt

118 kt

Refer to figure. Which statement is correct regarding the pitching moment coefficient CM versus angle of attack diagram?

Line 4 shows an aeroplane with reducing static longitudinal stability at very high angles of attack.

Line 3 shows an aeroplane with reducing static longitudinal stability at high angles of attack.

Line 1 shows an aeroplane with increasing static longitudinal instability at very high angles of attack.

Line 4 shows an aeroplane with greater static longitudinal stability at low angles of attack than that in shown line 3.

Refer to figure. Which of the following arrows points to the camber line?

3

1

2

4

Choose the correct answers. In a balanced coordinated turn, with the same bank angle, an increase in speed will: 1. Increase Rate of Turn. 2. Decrease Rate of Turn. 3. Increase Radius of Turn. 4. Decrease Radius of Turn.

2, 4.

1, 3.

1, 4.

2, 3.

Two identical aeroplanes A and B, with the same mass, are flying steady level co-ordinated 20 degree bank turns. If the TAS of A is 130 kt and the TAS of B is 200 kt:

the lift coefficient of A is less than that of B.

the turn radius of A is less than that of B.

the load factor of A is greater than that of B.

the rate of turn of A is less than that of B.

Which of the following statements is correct with regards to aircraft certified under CS-23 and CS-25?

VNE applies to all aircraft with an MTOW less than 5 670 kg.

Only jet aeroplanes have a VMO.

VMO only applies to CS-25 aircraft but NOT to CS-23 aircraft.

VNE only applies to CS-23 aircraft but NOT to CS-25 aircraft.

Regarding airflow around a wing, there are several specific points which can be defined. One of these is the separation point, which is where the...

velocity of the boundary layer becomes zero at the surface, and after which the boundary layer detaches from the wing surface.

boundary layer breaks down and disappears due to the turbulent flow that follows behind the separation point.

laminar airflow becomes turbulent, which creates a stall due to the rapid increase of the adverse pressure gradient.

boundary layer becomes turbulent and thickens, and this point will move forward along the upper surface if the angle of attack is reduced.

Modern jet aeroplanes usually fly at speeds faster than MCRIT, since the increase in speed is more significant than the increase in drag. How is this achieved?

The aeroplanes are flown at lower altitudes where the TAS is higher for a given Mach number and therefore experience a delay in the onset of shock waves and wave drag.

The aeroplanes are capable of flying at a higher altitude where the air is less dense and therefore the effects of the shock waves are less severe and create less wave drag.

By using an advanced wing technology with a greater curvature underneath to balance the acceleration over the top and therefore reduce the severity of the shock waves.

By using a supercritical aerofoil to reduce the severity of shock waves and the amount of wave drag at a given Mach number, when compared to a conventional aerofoil.

Airflow separation is characterised by:

Airflow reversal on the surface of the body.

The transition from laminar to turbulent boundary layer.

Increased velocity on the surface of the body.

A reduction in form drag.

Which of the following have an effect on the rudder moment during asymmetric flight? 1. Rudder deflection 2. Thrust setting 3. CG 4. Mass 5. TAS 6. IAS

2, 3, 6

1, 2, 6

1, 3, 6

2, 3, 4

How do fully powered flight controls differ from power assisted flight controls? For fully powered flight controls...

all the power to the control surfaces supplied by hydraulics.

their actuators in series rather than parallel.

electrical signals relay control movements to the actuators.

control surface position set by a computer, with the computer fed by pilot input.

A pilot is teaching a student the effects of individual control inputs. First, the pilot deflects the ailerons only, holding a constant deflection. Eventually, the aircraft enters a spiral dive. After recovering, the pilot then inputs a constant rudder deflection only. This also causes a spiral dive. Which of the following statement is correct regarding aircraft stability?

The ailerons are secondary contributors to directional stability and the rudder is a secondary contributor to lateral stability.

The ailerons are the main contributors to lateral stability and the rudder is the main contributor to directional stability.

Since the aeroplane enters an un-coordinated spiral dive, it is a result of both the lateral and directional stabilities being too weak.

Lateral stability and directional stability interact through sideslip, which is created when using either aileron or rudder alone.

When spoilers are extended, the minimum drag speed (1) _____ due to an increase in (2) _____.

(1) decreases; (2) profile drag

(1) increases; (2) profile drag

(1) increases; (2) induced drag

(1) decreases; (2) induced drag

Consider that the angle of attack of a swept-back fin in a sideslip is increased. What happens to the static directional stability?

The fin will stall later due to the sweep angle but will increase the directional stability.

The fin will stall earlier due to the sweep angle but will also reduce the directional stability.

The fin will stall earlier due to the sweep angle but will increase the directional stability.

The fin will stall later due to the sweep angle but will also reduce the directional stability.

An airplane cruises with a Mach number slightly higher than MCRIT, what are the benefits?

There are no benefits and it is highly dangerous to exceed MCRIT.

A higher speed for a small increase in CD.

The lowest safety speed in relation to shock stall.

No shockwaves are present upon passing MCRIT, they don't develop until Mach 2.

Consider a fixed-pitch propeller aeroplane at take-off. When the aeroplane accelerates during the take-off run phase, the blade angle of attack will (1) _____ and the thrust produced by the propeller will (2) _____.

(1) decrease; (2) increase

(1) increase; (2) increase

(1) decrease; (2) decrease

(1) increase; (2) decrease

Which of the following occur for a wing in the clean configuration when trailing edge flaps are extended? 1. CLMAX increases 2. CL/CD increases 3. Camber increases 4. Critical angle of attack decreases

2, 4

1, 2

1, 3, 4

1, 2, 4

The pilot of jet aeroplane with swept-back wings is preparing for a right turn to intercept the final approach. To tighten the turn, he/she uses full right rudder deflection only. As a consequence...

the right wing could stall due to skid leading to an unusual position.

the left wing could stall due to slip and generate a roll to the left.

the fin could stall due to excessive rudder application.

there is an increased risk of overshooting the final approach due to adverse yaw.

An aeroplane transitions from steady straight and level flight into a horizontal co-ordinated turn with a load factor of 2, the speed remains constant and the:

induced drag increases by a factor of 4.

angle of attack increases by a factor of 1/4.

lift increases by a factor of 4.

total drag increases by a factor of 4.

Fuselage contribution to directional stability is (I)_____ when its AC is (II)_____ of the CG?

(I) neutral; (II) ahead.

(I) neutral; (II) backward.

(I) destabilising; (II) ahead.

(I) destabilising; (II) backward.

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