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080 – PRINCIPLES OF FLIGHT
081-01

SUBSONIC AERODYNAMICS
081-01-01 Basics, laws and definitions

2625
...
Assuming ISA conditions, which statement with respect to the climb is correct?
A – At constant TAS the Mach number decreases
B – At constant Mach number the IAS increases
C – At constant IAS the TAS decreases
D – At constant IAS the Mach number increases
Ref: AIR: atpl, cpl;
Ans: D
3848
...
The point about which the wing pitching moment is independent of angle of
attack is called:
A – the pitching centre
B – the centre of gravity
C – the centre of pressure
D – the aerodynamic centre
Ref: AIR: atpl, cpl;
Ans: D
4184
...
The unit of density is:
A – Bar
B – psi
C – kg/cm2
D – kg/m3
Ref: AIR: atpl, cpl;
Ans: D
4199
...
The term angle of attack is defined as:
A – the angle that determines the magnitude of the lift force
B – the angle between the wing chord line and the relative wind
C – the angle between the relative airflow and the horizontal axis
D – the angle between the wing and tailplane incidence
Ref: AIR: atpl, cpl;
Ans: B
4202
...
At a constant IAS, induced drag is affected by:
A – aircraft weight
B – changes in thrust
C – angle between chord line and longitudinal axis
D – wing location
Ref: AIR: atpl, cpl;
Ans: A
4213
...
At a constant CAS when flying below sea level an aircraft will have:
A – a higher TAS than at sea level
B – a lower TAS than at sea level at ISA conditions
C – the same TAS as at sea level
D – the same TAS, but an increased IAS
Ref: AIR: atpl, cpl;
Ans: B
4232
...
The units of wing loading (i) W / S and (ii) dynamic pressure q are:
A – (i) N/m2; (ii) kg/m2
B – (i) kg/m; (ii) N/m2
C – (i) N/m; (ii) kg
D – (i) N/m2; (ii) N/m2
Ref: AIR: atpl, cpl;
Ans: D
4252
...
The units of the density of the air (i) and the force (ii) are:
A – (i) kg/m3; (ii) N
B – (i) kg/m3; (ii) kg
C – (i) N/m3; (ii) N
D – N/kg; (ii) kg
Ref: AIR: atpl, cpl;
Ans: A
7643
...
The dynamic pressure in the undisturbed flow and in the throat are equal
2
...
A symmetrical aerofoil section at CL = 0 will produce?
A – A negative (nose down) pitching moment
B – A positive (nose up) pitching moment
C – Zero pitching moment
D – No aerodynamic force
Ref: AIR: atpl, cpl;
Ans: C
7650
...
What is the SI unit that results from multiplying kg and m/s2?
A – Joule
B – Psi
C – Newton
D – Watt
Ref: AIR: atpl, cpl;
Ans: C
7658
...
What happens to total drag when accelerating from CL MAX to maximum
speed?
A – Increases
B – Increases then decreases
C – Decreases
D – Decreases then increases
Ref: AIR: atpl, cpl;
Ans: D
7689
...
4 times the lift
B - twice the lift
C – four times the lift
D – the same lift
Ref: AIR: atpl, cpl;
Ans: D

7691
...
Which of the following is the correct description of the method for measuring
the dihedral angle?
A – The angle between the wing plane and the horizontal
B – The angle between a line which passes through the 25% wing chord and
the horizontal axis
C – The angle between the 25% chord line and the horizontal axis
D – The angle between 25% chord and the lateral axis
Ref: AIR: atpl, cpl;
Ans: A
7700
...
What phenomena causes induced drag?
A – Wing tip vortices
B – Wing tanks
C – The increased pressure at the leading edge
D – The spanwise flow, inward below the wing and outward above
Ref: AIR: atpl, cpl;
Ans: A

7707
...
The following unit of measurement kgm/s? is expressed in the SI-system as:
A – Pascal
B – Newton
C – Joule
D – Watt
Ref: AIR: atpl, cpl;
Ans: B
7715
...
Which of the following is the speed that would activate the stick shaker:
A – 1
...
05 VS
C – 1
...
If the IAS is increased by a factor of 4, by what factor would the drag increase?
A–4
B–8
C – 12
D – 16
Ref: AIR: atpl, cpl;
Ans: D
7724
...
If a stick force of 20 lbs is required to pull 4g from the position of trim, the
stick force gradient is:
A – 6
...
When an aircraft’s forward CG limit is exceeded, it will affect the flight
characteristics of the aircraft by producing:
A – very light elevator control forces
B – higher stalling speeds and more longitudinal stability
C – improved performance since it reduces the induced drag
D – an extremely high tail down force
Ref: AIR: atpl, cpl;
Ans: B
23543
...
Which of the following components provides longitudinal stability?
A – engines
B – wing
C – fuselage
D – tail plane
Ref: AIR: atpl, cpl;
Ans: D
23574
...
Forward and aft movement of the CG effect on stability and control will be:
A – rearward movement of the CG will reduce control and stability
B – rearward movement of the CG will reduce control and increase stability
C – forward movement of the CG will increase stability and reduce control
D – forward movement of the CG will reduce stability and increase control
Ref: AIR: atpl, cpl;
Ans: C
23583
...
Rearward movement of the CG will:
A – give increased tendency for spiral instability
B – increase Vmcg
C – give greater tendency to dutch roll
D – increase elevator stick force gradient
Ref: AIR: atpl, cpl;
Ans: C
23596
...
Long period (phugoid) oscillations are characterised by:
A – oscillations will take 5 seconds to damp out
B – speed is constant
C – long period of damping
D – rapid and repeated changes in effective angle of attack
Ref: AIR: atpl, cpl;
Ans: C
23693
...
What happens if CG moves behind the aft limit?
A – stick forces become excessive
B – lateral stability will be decreased
C – insufficient manoeuvre stability
D – longitudinal stability increases
Ref: AIR: atpl, cpl;
Ans: C
23705
...
The sum of the moments in flight are not zero, therefore movement would take
place about:
A – the CG
B – the neutral point
C – the manoeuvre point
D – the CP
Ref: AIR: atpl, cpl;
Ans: A
24080
...
The forward and aft CG limits are determined respectively by:
A – roll response, control forces
B – minimum control response, decreasing stability
C – dutch roll, increasing stability
D – control forces, increasing stability
Ref: AIR: atpl, cpl;
Ans: B

081-04-04 Static directional stability
3872
...
An aerolplane that has positive static stability:
A – is never dynamically stable
B – is always dynamically stable
C – can be dynamically stable, neutral or unstable
D – is always dynamically unstable
Ref: AIR: atpl, cpl;
Ans: C
3881
...
Directional static stability is determined by:
A – aircraft weight
B – tail volume
C – fin volume
D – elevator angle for trim
Ref: AIR: atpl, cpl;
Ans: C
3944
...
An aeroplane has static directional stability; in a sideslip to the right, initially
the:
A – nose of the aeroplane tends to move to the left
B – right wing tends to go down
C – nose of the aeroplane will remain in the same direction
D – nose of the aeroplane tends to move to the right
Ref: AIR: atpl, cpl;
Ans: D
3966
...
Positive static stability of an aeroplane means that once it has been displaced
the:
A – tendency will be to move with an oscillating motion of decreasing
amplitude
B – tendency will be to move with an oscillating motion of increasing
amplitude
C – initial tendency to move is towards its equilibrium position
D – initial tendency to move is away from its equilibrium position
Ref: AIR: atpl, cpl;
Ans: C
21080
...
The contribution of swept back wings to static directional stability:
A – is nil
B – is negative
C – is positive
D – decreases as the sweepback increases
Ref: AIR: atpl, cpl;
Ans: C
21113
...
The effect of a wing with sweepback on static directional stability is as
follows:
A – Destabilising dihedral effect
B – No effect
C – Stabilising effect
D – Negative dihedral effect
Ref: AIR: atpl, cpl;
Ans: C
23388
...
With a swept wing aircraft, with an increase in altitude, which of the following
statements about lateral stability is correct?
A – Static lateral stability increases, dynamic lateral stability increases
B – Static lateral stability remains the same, dynamic lateral stability decreases
C – Static lateral stability decreases, dynamic lateral stability increases
D – Static lateral stability increases, dynamic lateral stability decreases
Ref: AIR: atpl, cpl;
Ans: B
3870
...
The short period mode is an:
A – oscillation about the vertical axis
B – oscillation about the lateral axis
C – oscillation about the longitudinal axis
D – unstable movement of the aeroplane, induced by the pilot
Ref: AIR: atpl, cpl;
Ans: B
3886
...
The effect of a high wing with zero dihedral is as follows:
A – its only purpose is to ease aeroplane loading
B – Negative dihedral effect
C – Positive dihedral effect
D – Zero dihedral effect
Ref: AIR: atpl, cpl;
Ans: C
3901
...
After a disturbance about the lateral axis, an aeroplane oscillates about the
lateral axis at a constant amplitude
...
What happens to lateral stability when flaps are extended?
A – Lateral stability is decreased
B – Lateral stability is increased as lift is increased
C – Lateral stability is unaffected, as the wings are symmetrical
D – Lateral stability is increased as the centre of pressure moves inboard
Ref: AIR: atpl, cpl;
Ans: A
3942
...
Which type of wing arrangement decreases the static lateral stability of an
aeroplane?
A – Increased wing span
B – Dihedral
C – High wing
D – Anhedral
Ref: AIR: atpl, cpl;
Ans: D

3958
...
Lateral static stability is determined by:
A – aircraft response to sideslip
B – aspect ratio
C – wingspan
D – cg position
Ref: AIR: atpl, cpl;
Ans: A
15777
...
Positive static lateral stability is the tendency of an aeroplane to:
A – roll to the left in the case of a sideslip angle (with the aeroplane nose
pointing to the right of the incoming flow)
B – roll to the left in the case of a sideslip (with the aeroplane nose pointing to
the left of theincoming flow)
C – roll to the right in a right turn
D – roll to the left in a right turn
Ref: AIR: atpl, cpl;
Ans: B

21103
...
Static lateral stability should not be too small because:
A – the aeroplane would show too strong a tendency to spiral dive
B – after a disturbance around the longitudinal axis the aeroplane would show
too strong a tendency to return to the original attitude
C – the stick force per g would become unacceptably small
D – the aeroplane would show too strong a tendency to Dutch roll
Ref: AIR: atpl, cpl;
Ans: A
21120
...
Which statement concerning sweepback is correct?
A – Sweepback provides a positive contribution to static lateral stability
B – Sweepback increases speed stability at Mach numbers above Mcrit
C – Sweepback is mainly intended to increase static directional stability
D – A disadvantage of sweepback is that it decreases Mcrit
Ref: AIR: atpl, cpl;
Ans: A

23384
...
Which of the following does not increase lateral stability:
A – large fin area
B – large keel surface with low CG
C – anhedral
D – dihedral
Ref: AIR: atpl, cpl;
Ans: C
23568
...
Which of the following increases the tendency for Dutch roll?
A – increased anhedral
B – increased keel surface aft of the CG
C – increased static lateral stability
D – decreased dihedral
Ref: AIR: atpl, cpl;
Ans: C

23692
...
The tendency for Dutch roll increases with:
A – increased static directional stability
B – forward CG position
C – increased anhedral
D – increased static lateral stability
Ref: AIR: atpl, cpl;
Ans: D

081-04-06 Dynamic lateral stability
3882
...
Longitudinal dynamic oscillation takes two forms
...
Which of the following statements about static lateral and directional stability is
correct?
A – The effects of static lateral and static directional stability are completely
ind
23398
...
Which of the following is true with regard to inboard ailerons?
A – used during low speed flight only
B – used during low and high speed flight
C – used during high speed flight
D – activated by the GPWS
Ref: AIR: atpl, cpl;
Ans: B

23417
...
In a differential aileron system:
A – the aileron moves further up than down
B – the aileron moves further down than up
C – the leading edge of the up going aileron projects below the wing
D – the ailerons are inter-connected with the rudder
Ref: AIR: atpl, cpl;
Ans: A
23422
...
When rolling out of a steep banked turn, what causes the lowered aileron to
create more drag than when rolling into the turn?
A – the wing being raised is travelling faster through the air than the wing
being lowered
B – the wing being lowered is travelling faster through the air and producing
more lift than the wing being raised
C – the angle of attack of the wing being raised is greater as the rollout is
started
D – none of the above
Ref: AIR: atpl, cpl;
Ans: C
23424
...
Which of the following is a true statement with regard to inboard ailerons?
A – inboard ailerons are used during low speed flight only
B – inboard ailerons are used during low speed and high speed flight
C – inboard ailerons are used during high speed flight only
D – inboard ailerons are activated by the GPWS
Ref: AIR: atpl, cpl;
Ans: B
23427
...
On an aircraft with a differential aileron control system, when the control
wheel is turned to the right:
A – the right aileron moves up, and the left aileron moves down through a
greater angle
B – the right aileron moves down and the left aileron moves up through a
greater angle
C – the left aileron moves down and the right aileron moves up through a
greater angle
D – the left aileron moves up and the right aileron moves down through a
greater angle
Ref: AIR: atpl, cpl;
Ans: C
23496
...
Spoilers are normally extended:
A – on the upper and lower wing surfaces in flight
B – on the upper wing surfaces on the down going wing
C – on the lower wing surface on the up going wing
D – on the upper surface of both wings to roll the aircraft
Ref: AIR: atpl, cpl;
Ans: B
23601
...
In a turn with speed brakes extended, roll control spoilers:
A – move on the down going wing only
B – move on the up going wing only
C – move up on the down going wing, down on the up going wing
D – move down on the down going wing, up on the up going wing
Ref: AIR: atpl, cpl;
Ans: C
23637
...
Which of the following is the correct example of differential aileron deflection
to initiate a left turn?
A – left aileron up 5o/right aileron down 2o
B – right aileron up 5o/left aileron down 2o
C – left aileron up 2o/right aileron down 5o
D – right aileron up 2o/left aileron down 5o
Ref: AIR: atpl, cpl;
Ans: A
23657
...
When are outboard ailerons locked out?
A – flaps retracted
B – landing gear retracted
C – landing gear extended
D – flaps extended
Ref: AIR: atpl, cpl;
Ans: A
24064
...
An aeroplane fitted with spoilers is rolling to the right, which way do the
spoilers move?
A – down on the downgoing wing
B – up on the downgoing wing
C – up on the upgoing wing
D – down on the upgoing wing
Ref: AIR: atpl, cpl;
Ans: B
24078
...

Which of the following statements is correct?
A – the left aileron moves up more than the right aileron moves down
B – the left aileron moves down more than the right aileron moves up
C – the right aileron moves up more than the left aileron moves down
D – theright aileron moves down more than left aileron moves up
Ref: AIR: atpl, cpl;
Ans: C

081-05-05 Interaction in diffeent planes
(yaw/roll)
4000
...
When an aircraft is rolled to port, adverse yaw will be reduced by:
A – the leading edge of the down going aileron protruding into the airflow
B – Frise ailerons producing increased profile leading edge drag on both
surfaces
C – a Frise aileron being effective on the port wing
D – the down going aileron producing a greater angle of deflection than the up
going aileron
Ref: AIR: atpl, cpl;
Ans: C
4017
...
When a jet aircraft enters a turn or straightens-up from a turn, what device
ensures correct response?
A – Dorsal fin
B – Yaw damper
C – Aileron – rudder coupling
D – Vortex generators
Ref: AIR: atpl, cpl;

Ans: C
21078
...
What are the secondary effects of rudder and aileron respectively:
A – yaw and roll
B – roll and yaw
C – pitch and roll
D – yaw and pitch
Ref: AIR: atpl, cpl;
Ans: B
23495
...
The effect of a headwind is to ___ the climb gradient and to ___ the rate of
climb
A – increase; not affect
B – increase; decrease
C – decrease; increase
D – not affect; increase
Ref: AIR: atpl, cpl;
Ans: A
4130
...
With a L/D ratio of 9:1 and flying at 12000 ft the glide rane in still air would
be:
A – 15 nm
B – 20 nm
C – 14 nm
D – 18 nm
Ref: AIR: atpl, cpl;
Ans: D
15749
...
Maximum gliding distance of an aircraft is obtained when:
A – induced drag equals the coefficient of lift
B – induced drag and parasite drag are equal
C – parasite drag is the least
D – parasite drag is greatest
Ref: AIR: atpl, cpl;
Ans: B
23499
...
Which of the following will result in the maximum distance covered over the
ground when gliding?
A – headwind
B – tailwind
C – increased weight
D – decreased weight
Ref: AIR: atpl, cpl;
Ans: B
23667
...
Which wind-shear condition results in an increase in airspeed?
A – increasing tailwind
B – decreasing tailwind
C – decreasing headwind
D – none of the above
Ref: AIR: atpl, cpl;
Ans: B
23521
...
On passing through a shear line, why does the IAS change?
A – the inertia of the aircraft will initially keep it at its original speed in
relation to the ground
B – a decreased mass of air is entering the pitot tube
C – windshear alters the air density, which affects the ASI reading
D – windshear changes the static pressure, which makes the ASI miss-read
Ref: AIR: atpl, cpl;
Ans: A

082-01

HELI-SUBSONIC AERODYNAMICS

25400
...
What is the significance of Vi?
A – Along with Vr, it determines the angle of attack
B – It determines the magnitude of Vr
C – Along with Vr, it determines the pitch angle
D – It determines the magnitude of rotor drag
Ref: HELI: atpl, cpl
Ans: A
25407
...
If a steady stream of airflows through a venture its velocity will ___ and static
pressure will ___
A – increase; rise
B – decrease; fall
C – decrease; rise
D – increase; fall
Ref: HELI: atpl, cpl
Ans: D

25410
...
If the disc of a teetering rotor system with an under-slung feathering hinge is
tilted the radius of the rotor blades cedntre of gravity will:
A – increase
B – decrease
C – become elliptical
D – remain the same
Ref: HELI: atpl, cpl
Ans: D
25412
...
When air is compressed the number of molecules in a given volume ___ and
density ___
A – decreases; rises
B – decreases; drops
C – increases; drops
D – increases; rises
Ref: HELI: atpl, cpl
Ans: D

25421
...
What is the relationship between Vr and the plane of rotation:
A – They are parallel
B – They are perpendicular
C – They determine the angle of attack
D – They determine the RAF
Ref: HELI: atpl, cpl
Ans: D
25426
...
What is force?
A – Mass x pressure
B – Speed x pressure
C – Mass x speed
D – Mass x acceleration
Ref: HELI: atpl, cpl
Ans: D

25436
...
If a helicopter is on the ground and the centre of gravity is directly below the
rotor hub, where will weight be acting?
A – Vertically down along the shaft axis
B – Vertically down from the centre of the helicopter
C – Down and back, away from the shaft axis
D – Down and forward, away from the shaft axis
Ref: HELI: atpl, cpl
Ans: A
25460
...
If uncorrected, what will retreating blade stall cause?
A – The helicopter to pitch down and roll towards the retreating side
B – The helicopter to pitch up and roll towards the advancing side
C – The helicopter to pitch down and roll towards the advancing side
D – The helicopter to pitch up and roll towards the retreating side
Ref: HELI: atpl, cpl
Ans: D

25465
...
During incipient vortex ring the vortex at the root becomes ___ and creates a
very turbulent wake as the ___ stalls
A – The tip section on the advancing side
B – The root section on the retreating side
C – The root section on the advancing side
D – The tip section on the retreating side
Ref: HELI: atpl, cpl
Ans: B
25469
...
99 mach
B – 0
...
15 mach
D – 0
...
When can shock stall occur?
A – At low speed
B – At negative angles of attack
C – At any angle of attack
D – In the hover
Ref: HELI: atpl, cpl
Ans: C

25474
...
As air becomes saturated, air density ___ and rotor performance is ___
A – increases; reduced
B – decreases; reduced
C

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