ATPL question bank Exam Questions and
Answers with Verified Solutions | Latest
Updated 2026
Which aeroplane behaviour Dutch Roll
will be corrected by a yaw
damper? Spiral dive. Buffeting.
Dutch roll. Tuck under.
One disadvantage of the tip stall will occur first, which
swept back wing is it's stalling produces a pitch-up moment
characteristics. At the stall:
wing root stall will occur first,
which produces a rolling
moment tip stall will occur
first, which produces a
nose-down moment leading
edge stall will occur first,
which produces a nose-down
moment tip stall will occur
first, which produces a
pitch-up moment
lf an aeroplane flies in the the lift is increase and the drag is
ground effect the lift is decreased
increased and the drag is
decreased the effective angle
of attack is decreased. the
induced angle of attack is
increased. drag and lift are
reduced.
,Compared with stalling Greater than VS
airspeed (VS) in a given
configuration, the airspeed at
which stick shaker will be. 1.30
VS. 1.12 VS. greater than VS.
1.20 VS.
Which one of the following Yaw Damper
systems suppresses the
tendency to "Dutch roll"?
Rudder limiter. Yaw damper.
Roll spoilers. Spoiler mixer.
The high speed buffet is boundary layer separation due to
induced by boundary layer shock waves
separation due to shock
waves. boundary layer control.
expansion waves on the wing
upper side. a shift of the
center of gravity.
When "spoilers" are used as at same AoA, CD is increased and CL
speed brakes: CLmax of the is decreased
polar curve is not affected.
they do not affect wheel
braking action during landing
at same angle of attack, CL
remains unaffected. at same
angle of attack, CD is
increased and CL is decreased
What factors determine the The wind and the L/D ratio, which
distance travelled over the changes the AoA
ground of an aeroplane in a
,glide? The wind and the
aeroplane's mass The wind
and CLmax The wind and
weight together with power
loading, which is the ratio of
power output to the weight
The wind and the lift/drag
ratio, which changes with
angle of attack
The center of gravity moving increase the elevator up
aft will: increase the elevator effectiveness
up effectiveness. decrease the
elevator up effectiveness. not
affect the elevator up or down
effectiveness. increase or
decrease the elevator up
effectiveness, depending on
wing location.
Which of the following Decreasing the angle of sweep of
statements about stall speed the wing will decrease the stall
is correct? Decreasing the speed
angle of sweep of the wing will
decrease the stall speed.
Increasing the angle of sweep
of the wing will decrease the
stall speed. Use of a T-tail will
decrease the stall speed.
Increasing the anhedral of the
wing will decrease the stall
speed.
, The flight Mach number is 0.8 500kts M= v/c > v/M=c 400/.8=500
and the TAS is 400 kts. The
speed of sound is: 500 kts 320
kts 480 kts 600 kts
When the trailing edge flaps nose down
are deflected in level flight,
the change in pitch moment
will be: nose up. zero.
dependent on c.g. location.
nose down.
Which Statement with respect At constant IAS the Mach number
to the climb is correct? At increases
constant Mach number the lAS
increases At constant TAS the
mach number decreases At
constant lAS the mach number
increases At constant lAS the
TAS decreases
The stalling speed in lAS will May increase during turbulence and
change according to the will always increase when banking in
following factors: Will increase a turn
during turn, increased mass
and an aft c.g. location Will
decrease with a forward c.g.
location, lower altitude and
due to the slip stream from a
propeller on an engine located
forward of the wing Will
increase with increased load
factor, icing conditions and
more flaps May increase
Answers with Verified Solutions | Latest
Updated 2026
Which aeroplane behaviour Dutch Roll
will be corrected by a yaw
damper? Spiral dive. Buffeting.
Dutch roll. Tuck under.
One disadvantage of the tip stall will occur first, which
swept back wing is it's stalling produces a pitch-up moment
characteristics. At the stall:
wing root stall will occur first,
which produces a rolling
moment tip stall will occur
first, which produces a
nose-down moment leading
edge stall will occur first,
which produces a nose-down
moment tip stall will occur
first, which produces a
pitch-up moment
lf an aeroplane flies in the the lift is increase and the drag is
ground effect the lift is decreased
increased and the drag is
decreased the effective angle
of attack is decreased. the
induced angle of attack is
increased. drag and lift are
reduced.
,Compared with stalling Greater than VS
airspeed (VS) in a given
configuration, the airspeed at
which stick shaker will be. 1.30
VS. 1.12 VS. greater than VS.
1.20 VS.
Which one of the following Yaw Damper
systems suppresses the
tendency to "Dutch roll"?
Rudder limiter. Yaw damper.
Roll spoilers. Spoiler mixer.
The high speed buffet is boundary layer separation due to
induced by boundary layer shock waves
separation due to shock
waves. boundary layer control.
expansion waves on the wing
upper side. a shift of the
center of gravity.
When "spoilers" are used as at same AoA, CD is increased and CL
speed brakes: CLmax of the is decreased
polar curve is not affected.
they do not affect wheel
braking action during landing
at same angle of attack, CL
remains unaffected. at same
angle of attack, CD is
increased and CL is decreased
What factors determine the The wind and the L/D ratio, which
distance travelled over the changes the AoA
ground of an aeroplane in a
,glide? The wind and the
aeroplane's mass The wind
and CLmax The wind and
weight together with power
loading, which is the ratio of
power output to the weight
The wind and the lift/drag
ratio, which changes with
angle of attack
The center of gravity moving increase the elevator up
aft will: increase the elevator effectiveness
up effectiveness. decrease the
elevator up effectiveness. not
affect the elevator up or down
effectiveness. increase or
decrease the elevator up
effectiveness, depending on
wing location.
Which of the following Decreasing the angle of sweep of
statements about stall speed the wing will decrease the stall
is correct? Decreasing the speed
angle of sweep of the wing will
decrease the stall speed.
Increasing the angle of sweep
of the wing will decrease the
stall speed. Use of a T-tail will
decrease the stall speed.
Increasing the anhedral of the
wing will decrease the stall
speed.
, The flight Mach number is 0.8 500kts M= v/c > v/M=c 400/.8=500
and the TAS is 400 kts. The
speed of sound is: 500 kts 320
kts 480 kts 600 kts
When the trailing edge flaps nose down
are deflected in level flight,
the change in pitch moment
will be: nose up. zero.
dependent on c.g. location.
nose down.
Which Statement with respect At constant IAS the Mach number
to the climb is correct? At increases
constant Mach number the lAS
increases At constant TAS the
mach number decreases At
constant lAS the mach number
increases At constant lAS the
TAS decreases
The stalling speed in lAS will May increase during turbulence and
change according to the will always increase when banking in
following factors: Will increase a turn
during turn, increased mass
and an aft c.g. location Will
decrease with a forward c.g.
location, lower altitude and
due to the slip stream from a
propeller on an engine located
forward of the wing Will
increase with increased load
factor, icing conditions and
more flaps May increase
