6) At a given altitude, when a turbojet aeroplane mass is increased by 5% - assuming the engines specific consumption remains unchanged -, its hourly consumption is approximately increased by:
10%
2.5%
5%
7.5%
17) The point at which a tangent out of the origin touches the power required curve
is the point where Drag coefficient is a minimum.
is the point where the Lift to Drag ratio is a minimum.
is the maximum drag speed.
is the point where the Lift to Drag ratio is a maximum.
5) Given that: VEF= Critical engine failure speed VMCG= Ground minimum control speed VMCA= Air minimum control speed VMU= Minimum unstick speed V1= T ake-off decision speed VR= Rotation speed V2 min.= Minimum take-off safety speed The correct formula is:
1.05 VMCA<= VEF<= V1
1.05 VMCG< VEF<= VR
V2min<= VEF<= VMU
VMCG<=VEF < V1
19) Which statement related to a take-off from a wet runway is correct?
In case of a reverser inoperative the wet runway performance information can still be used
Screenheight reduction can not be applied because of reduction in obstacle clearance.
A reduction of screen height is allowed in order to reduce weight penalties
The use of a reduced Vr is sufficient to maitain the same safety margins as for a dry runway
20) Reduced take-off thrust should normally not be used when:
it is dark.
the runway is dry.
the runway is wet.
windshear is reported on the take-off path.
21) The long range cruise speed is in relation to the speed for maximum range cruise.
Lower
Depending on the OAT and net mass.
Depending on density altitude and mass.
Higher
23) The rate of climb
is approximately climb gradient times true airspeed divided by 100.
is the downhill component of the true airspeed.
is angle of climb times true airspeed.
is the horizontal component of the true airspeed.
24) The maximum horizontal speed occurs when:
The thrust is equal to minimum drag.
The thrust does not increase further with increasing speed.
The maximum thrust is equal to the total drag.
The thrust is equal to the maximum drag.
26) The required Take-off Distance (TOD) and the field length limited Take-off Mass (TOM) are different for the zero flap case and take-off position flap case. What is the result of flap setting in take-off position compared to zero flap position?
Increased TOD required and decreased field length limited TOM.
Increased TOD required and increased field length limited TOM.
Decreased TOD required and decreased field length limited TOM.
Decreased TOD required and increased field length limited TOM.
75) Regarding take-off, the take-off decision speed V1:
is the airspeed of the aeroplane upon reaching 35 feet above the take-off surface.
is the airspeed on the ground at which the pilot is assumed to have made a decision to continue or discontinue the take- off.
is always equal to VEF (Engine Failure speed).
is an airspeed at which the aeroplane is airborne but below 35 ft and the pilot is assumed to have made a decision to continue or discontinue the take-off .
16) Assuming that the required lift exists, which forces determine an aeroplane's angle of climb?
Thrust and drag only.
Weight and thrust only.
Weight, drag and thrust.
Weight and drag only.
361) If the field length limited take off mass has been calculated using a Balanced Field Length technique, the use of any additional clearway in take off performance calculations may allow
a greater field length limited take off mass but with a higher V1
the obstacle clearance limit to be increased with no effect on V1
the obstacle clearance limit to be increased with an higher V1
a greater field length limited take off mass but with a lower V1
350) Which statement is correct for a descent without engine thrust at maximum lift to drag ratio speed?
A tailwind component increases fuel and time to descent.
A tailwind component decreases the ground distance.
A tailwind component increases the ground distance.
A headwind component increases the ground distance.
351) Which of the following is true according to JAA regulations for turbopropeller powered aeroplanes not performing a steep approach?
Maximum Take-off Run is 0,5 x runway.
Maximum use of clearway is 1,5 x runway.
Maximum Landing Distance at the destination aerodrome and at any alternate aerodrome is 0,7 x LDA (Landing Distance Available).
Maximum Landing Distance at destination is 0,95 x LDA (Landing Distance Available).
352) Under which condition should you fly considerably lower (4 000 ft or more) than the optimum altitude ?
If at the lower altitude either more headwind or less tailwind can be expected.
If at the lower altitude either considerably less headwind or considerably more tailwind can be expected.
If the maximum altitude is below the optimum altitude.
If the temperature is lower at the low altitude (high altitude inversion).
353) Which of the following statements is applicable to the acceleration height at the beginning of the 3rd climb segment ?
The minimum legally allowed acceleration height is at 1500 ft.
There is no requirement for minimum climb performance when flying at the acceleration height.
The minimum one engine out acceleration height must be maintained in case of all engines operating.
The maximum acceleration height depends on the maximum time take-off thrust may be applied.
354) Which statement regarding V1 is correct?
V1 is not allowed to be greater than VMCG.
When determining the V1, reverse thrust is only allowed to be taken into account on the remaining symmetric engines.
The V1 correction for up-slope is negative.
V1 is not allowed to be greater than VR.
355) The 'maximum tyre speed' limits:
VR, or VMU if this is lower than VR.
V1 in kt ground speed.
VLOF in terms of ground speed.
V1 in kt TAS.
356) The result of a higher flap setting up to the optimum at take-off is
a higher V1.
a longer take-off run.
a shorter ground roll.
an increased acceleration.
357) Which of the following provides maximum obstacle clearance during climb?
1.2Vs.
The speed for maximum rate of climb.
The speed, at which the flaps may be selected one position further UP.
The speed for maximum climb angle Vx.
358) In relation to the net take-off flight path, the required 35 ft vertical distance to clear all obstacles is
based on pressure altitudes.
the height by which acceleration and flap retraction should be completed.
the height at which power is reduced to maximum climb thrust.
the minimum vertical distance between the lowest part of the aeroplane and all obstacles within the obstacle corridor.
7) Which of the following statements is correct?
The performance limited take-off mass is independant of the wind component.
The accelerate stop distance required is independant of the runway condition.
The take-off distance with one engine out is independant of the wind component.
The climb limited take-off mass is independant of the wind component.
