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An aircraft with swept wings is better suited to cruising at higher Mach numbers due to reduced speed in the direction (1) _____ to the wing span, compared to the (2) _____. The reduced velocity varies with the (3) _____ of the sweep angle.

(1) perpendicular; (2) free stream flow; (3) cosine

(1) perpendicular; (2) free stream flow; (3) sine

(1) parallel; (2) free stream flow; (3) tangent

(1) parallel; (2) free stream flow; (3) sine

In comparison to elevator deflection, all-flying tailplanes require (1) _____ force to change the aircraft's pitch attitude and cause (2) _____ drag.

(1) more; (2) less

(1) more; (2) more

(1) less; (2) more

(1) less; (2) less

The movement of the aerodynamic centre of the wing when an aeroplane accelerates through the transonic range causes:

a decrease in static directional stability.

an increase in static longitudinal stability.

an increase in static directional stability.

a decrease in static longitudinal stability.

What impact does an increase in spoiler deflection have on the stall angle of attack and stall speed at a constant mass? The stall angle of attack (1) _____ and the stall speed (2) _____.

(1) increases; (2) decreases.

(1) decreases; (2) decreases.

(1) increases; (2) increases.

(1) decreases; (2) increases.

Yaw is followed by roll because the:

rolling motion generated by rudder deflection causes a speed increase of the outer wing which increases the lift on that wing so the aeroplane starts to roll in the direction of the turn.

rudder is located above the longitudinal axis and when it is deflected, it causes a rolling moment in the same direction as the yaw.

yawing motion generated by rudder deflection causes a speed increase of the outer wing, which increases the lift on that wing so that the aeroplane starts to roll in the same direction as the yaw.

yawing motion generated by rudder deflection causes a speed increase of the inner wing, which increase the lift on that wing so that the aeroplane starts to roll in the same direction as the yaw.

An aeroplane is flying in steady, straight and level flight at its 1g stall speed. If the pilot intends to turn left using the ailerons, the aeroplane will...

bank to the right, because the wing with the down going aileron will exceed the critical angle of attack.

bank to the left provided the speed does NOT decrease below the stalling speed.

yaw to the left, because of increased drag due to flow separation on the down going aileron.

maintain straight and level flight because the ailerons will be unresponsive due to flow separation.

The Never Exceed Speed (VNE) is set...

below VD.

never above VD.

at 0.9 of VD.

equal to VD.

An aeroplane where its CG is located forward of its Centre of Pressure suffers a premature tailplane stall as a result of ice contamination. Provided the wings do NOT stall, the outcome will be a(n)...

uncommanded nose down pitch that will be accompanied by the activation of the stall warning system.

nose up pitch upset, the magnitude of which will depend on the location of the aeroplane’s CG.

nose down pitch upset, the magnitude of which will depend on the location of the aeroplane’s CG.

uncommanded nose up pitch that will be accompanied by the activation of the stall warning system.

Which of these statements about the buffet free range in a buffet onset boundary graph are correct or incorrect?1. When speed increases the buffet free range does not change.2. When altitude decreases the buffet free range decreases.

1 is incorrect, 2 is correct.

1 is correct, 2 is correct.

1 is incorrect, 2 is incorrect.

1 is correct, 2 is incorrect.

Which statement concerning sweepback is correct?

A disadvantage of sweepback is that it decreases MCRIT.

Sweepback provides a positive contribution to static lateral stability.

Sweepback increases speed stability at Mach numbers above MCRIT.

Sweepback is mainly intended to increase static directional stability.

For a given CG position, the aeroplane has an MCRIT of Mach 0.82. With an aft movement of the CG, the MCRIT would (1) _____, as the local air velocity on the top surface of the wing would (2) _____, due to the (3) _____ angle of attack required to maintain level flight.

(1) decrease; (2) increase; (3) increased.

(1) decrease; (2) decrease; (3) increased.

(1) increase; (2) decrease; (3) decreased.

(1) increase; (2) increase; (3) decreased.

Considering low and high speed airflow regimes, what is the effect of flow speed on the use of Bernoulli's Principle?

The effects of high speed are visible, as compressibility starts to be promoted.

Bernoulli's principle can be used at all speeds, but compressibility is promoted at speeds above Mach 0.3 - 0.4.

Bernoulli's principle applies at subsonic speeds, but not supersonic speeds.

Bernoulli's principle can be used between Mach 0.4 up to Mach 0.8.

Refer to figure.Ignoring any change in altitude (not significant), an aircraft is flying with autopilot engaged, idle power set, and using pitch to control speed. How will MCRIT (Critical Mach Number) change according to the positions on the diagram above?

MCRIT is constant at positions 1 and 4, considering that mass is the same at these positions.

MCRIT will decrease between positions 3 and 4 due to decreasing AoA.

MCRIT is constant from positions 1 to 2, and another MCRIT is constant from positions 3 to 4.

MCRIT is constant at positions 2 and 3, due to a decrease in Mach Number.

An example of a combined lateral and directional aperiodic motion is a:

Dutch roll.

short period oscillation.

spiral dive.

phugoid.

When flying icing conditions, which of the following may occur to cause a stall without any prior warning in the cockpit?

Pitot tubes frozen over in the descent, giving erroneous indications of very low speed.

The AoA sensor frozen in a position with extremely high angle of attack.

Clear ice on the wing, reducing the critical angle of attack by disturbing the airflow over the aerofoil.

Ice formation on the horizontal stabiliser leading edge.

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.

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

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.

Greater lift production but a lower AoA at CLMAX.

Why should excessive use of rudder be avoided when turning on a swept-wing aircraft?

The aircraft will tend to roll in the wrong direction.

“Rudder reversal” may occur. The aircraft will yaw the wrong way.

The aircraft will tend to pitch-up.

To avoid excessive structural loads on the fin.

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

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

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

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

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

Refer to figure.The dotted line represents how a lift curve changes when a high-lift device is deployed. To which of these devices could the curve apply to?I. Variable camber flapII. Fowler flapIII. Slats and slots

III

I

II and III

I and II

Which design characteristic is typical for a supercritical aerofoil when compared to a conventional positive-cambered aerofoil?

A smaller leading edge radius.

A flatter upper surface.

A thinner trailing edge.

A smaller thickness.

A pilot is flying a twin engine aircraft, with clockwise rotating propellers, when viewed from behind. In this aircraft, which of the following options is most likely to contribute to the development of a spin?

Too little rudder is used during the turn from base to final.

The lateral stability is much greater than the directional stability.

The asymmetric blade effect during a go-around.

The slipstream effect when flying at low AoA.

The lift- and drag forces, acting on an aerofoil:

vary linearly with the angle of attack.

are proportional to each other, independent of angle of attack.

depend on the pressure distribution around the aerofoil.

are normal to each other at just one angle of attack.

1 - CLMAX2 - long range cruise (zero wind)3 - maximum lift to drag ratio4 - minimum rate of descent (assume zero thrust)5 - maximum range cruise (zero wind)Arrange these points in order of increasing angle of attack:

1, 2, 4, 3, 5.

3, 2, 5, 1, 4.

4, 5, 2, 3, 1.

2, 5, 3, 4, 1.

A light aircraft flying straight and level has a stall speed of 114 kt. It banks to an angle of 25°. Calculate the load factor and stall speed in this turn:

Load factor = 1.10; Stall speed = 132 kt.

Load factor = 1.10; Stall speed = 126 kt.

Load factor = 1.15; Stall speed = 107 kt.

Load factor = 1.10; Stall speed = 120 kt.

In order to fly a steady co-ordinated horizontal rate one turn at a lower airspeed, the bank angle must be:

decreased and the turn radius will increase.

increased and the turn radius will increase.

decreased and the turn radius will decrease.

increased and the turn radius will decrease.

What is the effect of ice accretion on a propeller?

Icing forms on the outer part of the propeller and reduces efficiency by 30%.

Icing forms on the inner part of the propeller and reduces its efficiency by 20%.

Icing forms on the outer part of the propeller and reduces efficiency by 25%.

Icing does not form on a propeller and has no impact on its efficiency.

The extension of fowler flaps will cause the centre of pressure to move...

aft, producing a pitch down moment.

aft, producing a pitch up moment.

forward, producing a pitch up moment.

forward, producing a pitch down moment.

A light aircraft with mechanical flight controls occasionally experiences uncomfortable pitch oscillations after encountering normal turbulence. The pilot does not feel any vibrations, but does notice some excessive slack or play in the elevator linkages after the flight. What potential hazards could this situation cause if not addressed by maintenance?

A poorly balanced control surface is creating excessive restoring forces and this short-period motion may cause excessive stress on the airframe.

This phugoid-type oscillation is likely to increase in magnitude and the aeroplane may enter a stall or encounter an overspeed situation if the oscillation worsens.

Compared to a phugoid, the short period motion leads to a change in pitch and speed, which, if NOT corrected, may lead to a stall or overspeed situation.

The flutter may gradually worsen, and the elevator may vibrate so vigorously that it comes off the hinges and separates from the aeroplane in flight.

Refer to figure.Consider the four tailplanes represented in the annex. Two depict fixed stabilisers with trim tabs, and two depict fully trimmable horizontal stabilisers (THS). Which shows a THS in the correctly trimmed position?

Figure 1

Figure 2

Figure 3

Figure 4

As the CG of an aircraft moves forward from the neutral point, the amount of elevator deflection required to control the aircraft...

remains the same.

decreases and then increases.

decreases.

increases.

How can spoiler deployment assist ailerons?

Improve roll control by reducing adverse yaw.

Assist in aileron reversal.

Help reduce drag during high-speed maneuvers.

Enhance lift generation on the descending wing.

During a steady glide, increasing descent angle will:

Increase difference between lift and weight

Both lift and weight will increase

Decrease difference between lift and weight

Lift and weight will remain the same for the new angle of descent

You are the pilot flying a light aeroplane with a clockwise turning propeller. While you are distracted by having to deal with a minor equipment failure, the stall warning horn activates. Which of the following would indicate that the aircraft had entered a full stall, if you do NOT respond to the warning and try to maintain level flight using the elevator?

The aileron controls give a feeling of a heavy buffet.

The nose pitching down with a full pitch-up elevator.

The nose yaws to the right regardless of the rudder input.

The effect of the rudder control being reversed.

For a right-handed propeller, in which direction does the propeller torque act for...1. A windmilling propeller2. A propeller producing reverse thrust

1. Anti-clockwise; 2. Anti-clockwise

1. Clockwise; 2. Anti-clockwise

1. Clockwise; 2. Clockwise

1. Anti-clockwise; 2. Clockwise

In a steady co-ordinated horizontal turn, lift is...

greater than in straight and level flight because it must balance the centripetal force.

greater than in straight and level flight, because it must balance the weight and generate the centripetal force.

greater than in straight and level flight, because it must generate the centrifugal force.

equal to the aeroplane weight.

The angle of attack of a fixed pitch propeller blade decreases when:

forward velocity and RPM increase.

forward velocity and RPM decrease.

forward velocity increases and RPM decreases.

forward velocity decreases and RPM increases.

The horn balance is used for aerodynamic balancing. It consists of...

a tab which moves opposite to the movement of the rudder.

a tab which is moved by control input from the pilots.

a surface area behind the hinge line to protrude into the airflow.

a surface area in front of the hinge line to protrude into the airflow.

Aileron reversal can occur at...

low speeds when the wing with the down-going aileron twists, increasing that wing’s camber.

low speeds when wing with the up-going aileron exceeds that wing’s critical Angle Of Attack.

high speeds when the wing with the up-going aileron causes sufficient drag, leading to adverse yaw.

high speeds when the wing with the down-going aileron twists, reducing that wing’s Lift Coefficient.

A firefighting aircraft is designed to fill up an onboard tank with water, then release the water in flight. Does the limit load factor change after releasing the water?

Yes, a lighter aircraft will have a higher limit load factor.

No, as the limit load factor depends on atmospheric pressure and airspeed.

No, the limit load factor is a theoretical number and does not change with aircraft weight.

Yes, a lighter aircraft will have a lower limit load factor.

Often, the tip of a wing will have a lower angle of incidence than the wing section near the root. Why?

To prevent tip stall.

To encourage the wingtip to stall first, keeping the aircraft controllable at high angles of attack.

To reduce induced drag, aiding with supersonic flight characteristics.

To extend the boundary layer towards the wingtip.

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