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If flying at the speed labelled 2, what will happen if the pilot applies full and sudden nose-up elevator input?

The aircraft will experience an accelerated stall at a load factor greater than 2g.

The aircraft will exceed the positive structural limit load factor before stalling.

The aircraft can safely reach the manoeuvring limit load factor without stalling.

The aircraft will suffer immediate structural damage.

A Cessna Skyhawk has a VA of 123 kt when its mass is 2 300 lbs. Determine its VA at a mass of 1 900 lbs.

112 kt

102 kt

149 kt

135 kt

What happens to the blade angle and RPM of a constant speed propeller when the aeroplane wing's angle of attack decreases in level flight?

Both the blade angle and the RPM increase.

Blade angle remains constant, whilst the RPM increases.

The RPM decreases and the blade angle increases.

The blade angle increases and the RPM remains constant.

Which of the following situations describes the most favourable situation in case of an engine failure on a twin engine aeroplane?

Failure of the left engine if both engines are rotating in the same direction.

Failure of the right engine if both engines are counter rotating outwards.

Failure of the left engine if both engines are counter rotating outwards.

Failure of the right engine if both engines are counter rotating inwards.

The attached figure shows an aeroplane in cruise flight suffering an engine failure with significant damage. The aircraft speed is reducing, and the pilot needs to increase the rudder input to counteract the asymmetric yawing moment. Why is this?

The right sideslip is causing the vertical stabiliser to stall.

As airspeed reduces, the live engine produces a stronger yawing moment.

The left sideslip is causing the vertical stabiliser to stall.

Rudder effectiveness is reduced due to a higher fin AoA at low speeds.

In a sideslip condition, increasing the sweep angle of a vertical stabiliser has what effect on static directional stability and the fin's critical angle of attack?

(1) positive; (2) decreases

(1) negative; (2) decreases

(1) negative; (2) increases

(1) positive; (2) increases

For any propeller:

the force contributing to propeller torque is perpendicular to the propeller plane of rotation.

thrust is the component of the total aerodynamic force on the propeller parallel to the rotational axis.

thrust is the component of the total aerodynamic force on the propeller in the plane of rotation.

the total aerodynamic force on a blade element may be resolved into two components, torque and lift.

You are the pilot flying of a single engine tailwheel aircraft with a strong propeller turning right on a wet grass runway. During acceleration for take-off, you are forced to use considerable right rudder to keep the aircraft straight. This is because during the early part of the take-off run the propeller produces...

gyroscopic precession before the tail is lifted, and slipstream effect after the tail is lifted.

slipstream effect before the tail is lifted, and asymmetric blade effect after the tail is lifted.

gyroscopic precession as the tail is lifted, and asymmetric blade effect only after the tail is lifted.

asymmetric blade effect before the tail is lifted, and gyroscopic precession as the tail is lifted.

In a steady glide, the rate of descent can be determined by multiplying (1) _____ with the (2) _____ of the descent angle.

(1) TAS; (2) Cos

(1) TAS; (2) Sin

(1) IAS; (2) Cos

(1) IAS; (2) Sin

The boundary layer of a wing is:

created by the normal shock wave at transonic speeds.

a turbulent flow around the wing.

a layer on the wing in which the stream velocity is lower than the free stream velocity.

caused by suction on the upper wing surface.

Consider an aerofoil section. The relative thickness is the ratio of...

maximum thickness to maximum camber.

maximum thickness to chord length.

average thickness to chord length.

average thickness to medium camber-line length.

An aircraft has been parked outside overnight, in freezing conditions. The crew decides to depart WITHOUT having the airframe de-iced/anti-iced. What could be the principal danger during take-off?

Uncommanded roll due to frozen deposits on the wings, which increase CLMAX.

Loss of control due to frozen deposits on the wings, which reduce CLMAX.

A lower stall speed due to wing contamination and increased drag.

A higher stall speed due to wing contamination and reduced drag.

Refer to figure. On approach, the aircraft's ECAM display shows "Flaps Locked", but with slats working normally. What will the pilots experience in this case, compared to landing with a clean wing.

Greater lift production but a lower AoA at CLMAX.

An increased landing distance, as the pilot must use a higher approach speed.

The aircraft will behave exactly like a clean wing but with more drag.

A higher AoA and increased drag, leading to an increased risk of tailstrike but a shorter landing distance.

On approach you are flying at VMD, but decide to increase your speed slightly. You are now flying in the so-called speed (1) _____ region and the total drag has (2) _____.

(1) unstable; (2) decreased

(1) unstable; (2) increased

(1) stable; (2) decreased

(1) stable; (2) increased

A flight instructor is teaching a student of a multi-engine piston airplane the practice of an engine failure. What is the most favourable configuration during the first engine failure exercise?

An airplane mass of 3 800 lbs so that the resultant yaw from the engine failure is minimized.

An airplane mass of 4 400 lbs so that the resultant yaw from the engine failure is minimized.

An airplane mass of 3 800 lbs so that the rudder has greater effectiveness.

An airplane mass of 4 400 lbs so that the rudder has greater effectiveness.

When speed is increased in straight and level flight on a positively cambered aerofoil, what happens to the: 1. centre of pressure and 2. the magnitude of the total lift force?

1 moves aft and 2 remains constant.

1 moves forward and 2 decreases.

1 moves forward and 2 remains constant.

1 moves aft and 2 increases.

During a demonstration of the effect of controls, the pilot manoeuvres the aeroplane applying aileron input only. This control input will make the aeroplane roll...

and sideslip towards the lower wing due to the sideways components of lift, and gravity and the sideslip angle will increase with the increasing bank angle.

and skid towards the higher wing due to the inertia of the aeroplane, and the amount of skid is dependent on the relationship between the bank angle and speed.

towards the wing with the upward deflecting aileron, and the rolling motion will stop at a bank angle that is directly related to the stick position.

towards the wing with the downward deflecting aileron, and the roll rate will be proportional to the movement of the control column.

Moving the CG of an aircraft forward will have what effect on the stall speed, VS?

None, the CG position has NO influence of VS.

VS decreases, due to an increase in critical angle of attack.

Equivalent to the effect of an increase in mass.

Equivalent to the effect of a decrease in mass.

Considering the effect of wing downwash on the direction of the airflow approaching the tailplane, when flaps are extended the tailplane’s negative angle of attack...

increases, increasing the tailplane’s effectiveness.

increases, decreasing the tailplane’s effectiveness.

decreases, increasing the tailplane’s effectiveness.

decreases, decreasing the tailplane’s effectiveness.

Refer to figure. The correct sequence that represents the ordering of the aerofoils by increasing CL is...

2, 4, 1, 3.

1, 2, 3, 4.

4, 2, 1, 3.

4, 1, 2, 3.

What effect will shockwave induced separation have on a T-Tail horizontal stabiliser?

Decrease downwash.

Increase downwash.

No noticeable effect.

Airflow separation will cause it to buffet.

An aircraft is taking off, its VA is 260 kt. If weight decreases by 20%, the new VA will be...

285 kt

233 kt

311 kt

208 kt

For a given gust velocity, by how much would the gust load increase for an aircraft flying at 40 000 ft, compared to the same aircraft flying at sea level, if the EAS remains the same? The gust load would increase by...

twice as much.

zero, there will be no increase at all.

a quarter.

half as much.

An aircraft is flying with NO POWER after losing all engines at a height of 10 000 ft. Considering the data below, what will the maximum glide range be? L/D: 15 Average TAS: 200 kt Wind component: 20 kt headwind (Use 1 NM = 6080 ft)

27.1 NM

24.7 NM

22.2 NM

27.4 NM

While performing a take-off under icing conditions, the pilot rotates the aircraft at the correct speed and rate, but notices that the aircraft does NOT lift off as expected. What could be the cause?

Ice can distort the flow of air over the wing, increasing the angle of attack for maximum lift and significantly increasing drag.

The angle of attack during rotation exceeds the lower, icing-induced critical angle of attack, preventing the aircraft from becoming airborne.

The rotation rate is too fast, increasing the critical angle of attack and preventing the aircraft to lift off.

The rotation speed is too fast, significantly increasing drag and preventing the aircraft to lift off.

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

speed vector and the horizontal plane.

lateral axis and the horizontal plane.

speed vector and normal axis.

speed vector and the plane of symmetry.

Which definition of propeller parameters is correct?

Angle of attack is the angle between the blade chord line and the propeller vertical plane.

Blade angle is the angle between the blade chord line and the propeller axis.

Geometric pitch is the actual distance a propeller would advance in one revolution.

Helix angle is the angle between the actual path of the propeller and the plane of rotation.

During landing, the pilot flares using a 5° pitch-up technique, intending to utilise ground effect to touchdown softly. Which of the following statements is most correct?

This is an inappropriate technique for this aircraft and may lead to a tailstrike or hard landing.

This is an inappropriate technique for all aircraft, as it may stall during the pull-up manoeuvre.

This technique is only appropriate for this aircraft as long as the wing does not exceed the critical α due to the ground effect.

This is an appropriate technique for all aircraft to touchdown, but it increases the landing distance.

Frise ailerons are used to reduce adverse aileron yaw. To achieve this the...

down-going aileron moves through a larger angle than the up-going aileron.

up-going aileron moves through a larger angle than the down-going aileron.

leading edge of the down-going aileron protrudes above the upper surface of the wing, causing more drag.

leading edge of the up-going aileron protrudes below the lower surface of the wing, causing more drag.

The maximum angle of bank which can be achieved with a 0.13 g buffet margin is:

40°

28°

59°

53°

After a new software update, the engineer has changed the crossover data from 250 kt / M0.75 to 250 kt / M0.78. The pilot now must make sure he/she does not exceed...

VNE

MMO

VMO

VNO

When is a runway considered to be contaminated? When...

Only if the contaminant covers a connected 25% of the runway surface area (patches of contaminants can add up to more than 25% of the surface area without effects).

Less than 25% of the runway surface area (whether in isolated areas or not) is covered with water more than 3 mm deep.

More than 25% of the runway surface area (whether in isolated areas or not) is covered with slush equivalent to 2 mm of water.

More than 25% of the runway surface area (whether in isolated areas or not) is covered with wet ice 1.5 mm thick.

For a multi-engine aircraft in the class B performance category, what is the minimum all engine take-off climb gradient?

3.3%

2.5%

4%

2.8%

What is VS1g?

The stall speed or the minimum steady flight speed at which the aeroplane is controllable in 1-g conditions.

The speed at which onset of artificial stall warning occurs with the aeroplane NOT exceeding 1-g conditions.

The 1-g stall speed at which the aeroplane can develop lift equal to its weight.

The speed at which onset of natural stall warning occurs with the aeroplane NOT exceeding 1-g conditions.

Refer to figure. What does the part marked 'a' represent?

VA

VS1G

VC

VMO

Refer to figure. If the two aircraft in the figure were flying at the same weight and airspeed, which would be more affected by flying through the same up-gust?

Aeroplane B

Aeroplane A

There is not enough information to say

Both would react the same as they have the same weight

Refer to figure. Given the wing planform represented in the diagram with the following dimensions, calculate the aspect ratio: Wingspan: 12.5 m Tip chord: 1 m Root chord: 1.5 m

8.3

12.5

10

Refer to figure. When extending spoilers, what will happen to the stall speed and critical AOA?

Lower critical AOA and lower stall speed

Lower critical AOA and higher stall speed

Higher critical AOA and higher stall speed

Higher critical AOA and lower stall speed

A multi engined commercial jet with underslung wing mounted engines is flying at the stall speed with idle power. If power is increased, CLMAX will (1) _____ and the stall speed will (2) _____.

(1) remain the same; (2) increase

(1) remain the same; (2) decrease

(1) decrease; (2) remain the same

(1) increase; (2) remain the same

Swept wings have the following properties:

Less affected by turbulence and steeper slope of lift curve vs AOA.

More affected by turbulence and steeper slope of lift curve vs AOA.

More affected by turbulence and shallower slope of lift curve vs AOA.

Less affected by turbulence and shallower slope of lift curve vs AOA.

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