1
The stopway is an area which allows an increase only in the:
accelerate-stop distance available.
landing distance available.
take-off distance available.
take-off run available.
2
VR cannot be lower than:
1.15 Vs for turbo-prop with three or more engines.
V1 and 105% of VMCA.
1.2 Vs for twin and three engine jet aeroplane.
105% of V1 and VMCA
3
The effects of an increased ambient air temperature beyond the flat rating cut-off temperature of the engines on (i) the fieldlength-limited take-off mass and (ii) the climb-limited take-off mass are:
(i) Decrease (ii) Decrease.
(i) Increase (ii) Increase
(i) Increase (ii) Decrease
(i) Decrease (ii) Increase.
4
The one engine out take-off run is the distance between the brake release point and:
the point half way between V1 and V2.
the lift-off point.
the middle of the segment between VLOF point and 35 ft point.
the point where V2 is reached.
5
The decision speed at take-off (V1) is the calibrated airspeed
below which take-off must be rejected if an engine failure is recognized, above which take-off should be continued.
below which the take-off must be continued.
at which the failure of the critical engine is expected to occur.
at which the take-off must be rejected.
6
Regarding unaccelerated horizontal flight, Minimum Drag is:
proportional to aircraft mass.
a function of the density altitude
independent of the aircraft mass
a function of the pressure altitude.
7
Which of the following statements is correct?
VR should not be higher than V1.
VR should not be higher than 1.05 VMCG
VR is the speed at which the pilot should start to rotate the aeroplane.
VR is the speed at which, during rotation, the nose wheel comes off the runway
8
If the aircraft mass, in a horizontal unaccelerated flight, decreases:
the minimum drag decreases and the IAS for minimum drag increases.
the minimum drag decreases and the IAS for minimum drag decreases
the minimum drag increases and the IAS for minimum drag decreases
the minimum drag increases and the IAS for minimum drag increases
9
The tangent from the origin to the power required against true airspeed curve, for a jet aeroplane, determines the speed for:
maximum specific range
critical angle of attack
minimum power.
maximum endurance.
10
For a jet aeroplane, the speed for maximum range is:
that corresponding to the point of the minimum power required at the Drag versus TAS curve
that corresponding to the point of contact of the tangent from the origin to the Power required versus TAS curve.
that corresponding to the point of contact of the tangent from the origin to the Drag versus TAS curve
that corresponding to the point of the minimum drag at the Drag versus TAS curve.
11
Which cruise system gives minimum fuel consumption during cruise between top of climb and top of descent? (still air, no turbulence)?
Long range.
Maximum range.
Holding
Maximum endurance.
12
A twin jet aeroplane is in cruise, with one engine inoperative, and has to overfly a high terrain area. In order to allow the greatest clearance height, the appropriate airspeed must be the airspeed
giving the highest Cd/Cl ratio.
for long-range cruise.
of greatest lift-to-drag ratio
giving the lowest Cl/Cd ratio
13
A four jet-engine aeroplane (mass = 150 000 kg) is established on climb with all engines operating. The lift-to-drag ratio is 14. Each engine has a thrust of 75 000 Newton. The gradient of climb is: (given: g= 10 m/s
12.86%
1.286%.
27%.
7.86%.
14
Density altitude is the:
altitude reference to the standard datum plane
pressure altitude corrected for 'non standard' temperature
height above the surface
altitude read directly from the altimeter
15
The Density Altitude:
is used to calculate the FL above the Transition Altitude
is equal to the pressure altitude.
is used to establish minimum clearance of 2.000 feet over mountains.
is used to determine the aeroplane performance.
16
Which of the following combinations adversely affects take-off and initial climb performance ?
Low temperature and low relative humidity
High temperature and high relative humidity
High temperature and low relative humidity
Low temperature and high relative humidity
17
What effect has a downhill slope on the take-off speeds? The slope
has no effect on the take-off speed V1.
decreases the TAS for take-off
decreases the take-off speed V1.
increases the IAS for take-off
18
During climb to the cruising level, a headwind component:
decreases the ground distance flown during that climb.
decreases the climb time.
increases the climb time.
increases the amount of fuel for the climb.
19
The effect that a tailwind has on the value of the maximum endurance speed is:
that a tailwind only affects the holding speed.
that the IAS must be increased.
that the IAS must be decreased.
none
20
During climb with all engines, the altitude where the rate of climb reduces to 100 ft/min is called:
Absolute ceiling.
Thrust ceiling.
Aerodynamic ceiling.
Service ceiling.
21
What will be the influence on the aeroplane performance if aerodrome pressure altitude is increased?
It will increase the accelerate-stop distance available
It will increase the take-off distance available
It will decrease the take-off distance
It will increase the take-off distance
22
2. Which class of aeroplane describes all multi-engine turbojet aeroplanes?
Class B
Class C
Unclassified
Class A
23
3. The take-off distance available is:
the length of the take-off run available plus any length of clearway available, up to a
maximum of 50% of TORA
the total runway length, without clearway even if one exists
the runway length plus half of the clearway
the runway length minus stopway
24
What will be the effect on an aeroplane’s performance if aerodrome pressure altitude is decreased?
It will decrease the take-off distance required
It will increase the accelerate-stop distance
It will increase the take-off distance required
It will increase the take-off ground run
25
Can a clearway be used in the accelerate-stop distance calculations?
Only if there is no clearway
Only if the clearway is shorter than the stopway
Yes
No
26
Which of the following are to be taken into account for the runway in use for take-off?
Airport elevation, runway slope, outside air temperature, pressure altitude and wind
components
Airport elevation, runway slope, standard temperature, pressure altitude and wind
components
Airport elevation, runway slope, outside air temperature, standard pressure and wind
components
Airport elevation, runway slope, standard temperature, standard pressure and wind
components
27
With contamination on the aircraft wings and fuselage only:
the TODR will be unaffected
the ASDR will decrease
stalling speed is not affected
the lift-off speed will be increased
28
The stopway is:
as strong as the main runway
no less than 500 ft wide
no less than 152 m wide
at least as wide as the runway
29
The result of a higher flap setting up to the optimum at take-off is:
a shorter ground roll
a higher VR
a longer take-off run
an increased acceleration
30
During take-off:
total drag decreases
wheel drag increases
thrust increases
the acceleration force decreases
31
The main purpose for taking off into wind is to:
decrease the true ground speed
decrease the aeroplane performance
increase the true ground speed
increase the take-off distance
32
A propeller aeroplane with nine or less passenger seats and with a maximum take-off mass of 5700 kg or less is described as:
Class C
unclassified
Class B
Class A
33
Which of the following statements is correct?
A clearway is an area beyond the runway which can be used for a rejected take-off
An under-run is an area beyond the runway end which can be used for a rejected take-off
If a clearway or a stopway is used, the lift-off point must be attainable at least by the end of
the permanent runway surface
A stopway means an area beyond the take-off run available, able to support the aeroplane
during a rejected take-off
34
A ‘balanced field length’ is said to exist where:
the accelerate-stop distance available is equal to the take-off distance available
the clearway does not equal the stopway
the one engine out take-off distance is equal to the all engine take-off distance
the accelerate-stop distance is equal to the all engine take-off distance
