CRUISE – Air – DGCA Question Bank For Politics

#1. On a reciprocating engined aeroplane, with increasing altitude at constant gross mass, constant angle of attack and configuration, the power required:

remains unchanged but the TAS increases

increases and the TAS increases by the same percentage

increases but TAS remains constant

decreases slightly because of the lower air density

#2. Moving the centre of gravity from the forward to the aft limit: (gross mass, altitude and airspeed remain unchanged)

increases the power required

affects neither drag nor power required

increases the induced drag

decreases slightly because of the lower air density

#3. For jet-engined aeroplanes operating below the optimum altitude, what is the effect of increased altitude on specific range?

It does not change

Increases only if there is no wind

Increases

Decreases

#4. If the thrust available exceeds the thrust required for level flight:

the aeroplane accelerates if the altitude is maintained

the aeroplane descends if the airspeed is maintained

the aeroplane decelerates if it is in the region of reversed command

the aeroplane decelerates if the altitude is maintained

#5. Given a jet aircraft. Which order of speeds is correct?

Vs, Maximum range speed, Vx

Maximum endurance speed, Maximum range speed, VX

Vs, Vx Maximum range speed

Maximum endurance speed, Long range speed, Maximum range speed

#6. The pilot of a light twin engine aircraft has calculated a 4,000 m service ceiling with a take-off mass 3,250 kg, based on the general forecast conditions for the flight. If the take-off mass is 3,000 kg the service ceiling will be:

less than 4,000 m

unchanged, equal to 4,000 m

only a new performance analysis will determine if the service ceiling is higher or lower than 4,000 m

higher than 4,000 m

#7. Consider the graphic representation of the power required for a jet aeroplane versus true air speed (TAS). When drawing the tangent out of the origin, the point of contact determines the speed of:

critical angle of attack

maximum endurance

minimum power

maximum specific range

#8. In the drag versus speed curve for a jet aeroplane, the speed for maximum range corresponds with:

the point of contact of the tangent from the origin to the drag curve

the point of intersection of the parasite drag curve and the induced drag curve

the point of contact of the tangent from the origin to the parasite drag curve

the point of contact of the tangent from the origin to the induced drag curve

#9. The speed VS is defined as the:

speed for best specific range

stalling speed or minimum steady flight speed at which the aeroplane is controllable

safety speed for take-off in case of a contaminated runway

#10. What is the effect of a head wind component, compared to still air, on the maximum range speed for maximum climb angle respectively?

Maximum range speed decreases and maximum climb angle speed decreases

Maximum range speed increases and maximum climb angle speed increases

Maximum range speed increases and maximum climb angle speed stays constant

#11. A jet aeroplane is flying at the long range cruise speed at the optimum altitude. How does the specific range / fuel flow change over a given time period?

Decrease / decrease

Increase / decrease

Increase / increase

Decrease / increase

#12. The maximum indicated air speed of a piston engined aeroplane, in level flight, is reached:

at the service ceiling

at the practical ceiling

at the lowest possible altitude

at the optimum cruise altitude

#13. The optimum cruise altitude increases:

if the aeroplane mass is decreased

if the temperature (OAT) is increased

if the tailwind component is decreased

if the aeroplane mass is increased

#14. What affect has a tailwind on the maximum endurance speed?

No affect

Tailwind only affects holding speed

The IAS will be increased

The IAS will be decreased

#15. Which of the equations below defines specific air range (SR)?

SR=Groundspeed / Total Fuel Flow

SR=True Airspeed / Total Fuel Flow

SR=Indicated Airspeed / Total Fuel Flow

SR=Mach Number / Total Fuel Flow

#16. Which of the following statements, with regard to the optimum altitude (best fuel mileage), is correct?

An aeroplane usually flies above the optimum cruise altitude, as this provides the largest specific range

An aeroplane sometimes flies above the optimum cruise altitude, because ATC normally does not allow to fly continuously at the optimum cruise altitude.

An aeroplane always flies below the optimum cruise altitude, as otherwise Mach buffet can occur

An aeroplane always flies on the optimum cruise altitude, because this is most attractive from an economy point of view

#17. The optimum altitude:

is the altitude up to which cabin pressure of 8 000 ft can be maintained

increases as mass decreases and is the altitude at which the specific range reaches its maximum

decreases as mass decreases

is the altitude at which the specific range reaches its minimum

#18. A lower airspeed at constant mass and altitude requires:

less thrust and a lower coefficient of lift

more thrust and a lower coefficient of lift

more thrust and a lower coefficient of drag

a higher coefficient of lift

#19. 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 of Drag ratio is a minimum

is the maximum drag speed

is the point where the Lift to Drag ratio is a maximum

#20. The long range cruise speed (LRC) is in relation to the speed for maximum range cruise (MRC)?

Lower

Depending on the OAT and net mass

Depending on density altitude and mass

Higher

#21. 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

#22. 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.

#23. The optimum cruise altitude is:

the pressure altitude up to which a cabin altitude of 8,000 ft can be maintained

the pressure altitude at which the TAS for high speed buffet is a maximum

the pressure altitude at which the best specific range can be achieved

the pressure altitude at which the fuel flow is a maximum

#24. Maximum endurance for a prison engined aeroplane is achieved at:

The speed that approximately corresponds to the maximum rate of climb speed

The speed for maximum lift coefficient

The speed for minimum drag

The speed that corresponds to the speed for maximum climb angle

#25. On a long distance flight the gross mass decreases continuously as a consequence of the fuel consumption. The result is:

The speed must be increased to compensate the lower mass

The specific range increases and the optimum altitude decreases

The specific range decreases and the optimum altitude increases

The specific range and the optimum altitude increases

#26. A jet aeroplane is climbing at constant Mach number below the tropopause. Which of the following statements is correct?

IAS decreases and TAS decreases

IAS increases and TAS increases

IAS decreases and TAS increases

IAS increases and TAS decreases

#27. Why are 'step climbs' used on long distance flights?

Step climbs do not have any special purpose for jet aeroplanes; they are used for piston engine aeroplanes only

ATC do not permit cruise climbs

To fly as close as possible to the optimum altitude as aeroplane mass reduces

Step climbs are only justified if at the higher altitude less headwind or more tailwind can be expected

#28. Which of the following sequences of speed for a jet aeroplane is correct? (from low to high speeds.

Maximum endurance speed, maximum range speed, maximum angle of climb speed

Maximum endurance speed, long range speed, maximum range speed

Vs, maximum angle climb speed, maximum range speed

Vs, maximum range speed, maximum angle climb speed

#29. The pilot of a jet aeroplane wants to use a minimum amount of fuel between two airfields. Which flight procedure should the pilot fly?

Maximum endurance

Holding

Long range

Maximum range

#30. Long range cruise is selected as:

the higher speed to achieve 99% of maximum specific range in zero wind

the speed for best economy (ECON)

the climbing cruise with one or two engines inoperative

specific range with tailwind

#31. The optimum long-range cruise altitude for a turbo-jet aeroplane:

is only dependent on the outside air temperature

increases when the aeroplane mass decreases

is always equal to the powerplant ceiling

is independent of the aeroplane mass

#32. Maximum endurance:

is the same as maximum specific range with wind correction

can be flown in a steady climb only

can be reached with the 'best rate of climb' speed in level flight

is achieved in unaccelerated level flight with minimum fuel consumption

#33. For a piston engined aeroplane, the speed for maximum range is:

that which gives the maximum lift to drag ratio

that which gives the minimum value of power

that which gives the maximum value of lift

1.4 times the stall speed in clean configuration

#34. The speed for maximum endurance:

is always higher than the speed for maximum specific range

is always lower than the speed for maximum specific range

is the lower speed to achieve 99% of maximum specific range

can either be higher or lower than the speed for maximum specific range

#35. The intersections of the thrust available and the drag curve are the operating points of the aeroplane:

in un-accelerated climb

in un-accelerated level flight

in descent with constant IAS

in accelerated level flight

#36. For a jet transport aeroplane,which of the following is the reason for the use of 'maximum range speed'?

Minimises specific fuel consumption

Minimises fuel flow

Longest flight duration

Minimises drag

#37. The centre of gravity moving near to, but still within, the aft limit;

increases the stalling speed

improves the longitudinal stability

decreases the maximum range

improves the maximum range

#38. A jet aeroplane is performing a maximum range flight. The speed corresponds to:

the minimum drag

the minimum required power

the point of contact of the tangent from the origin to the power required (Pr. versus TAS curve

the point of contact of the tangent from the origin to the Drag versus TAS curve

#39. During a cruise flight of a jet aeroplane at a constant flight level and at the maximum range speed, the IAS / the drag will:

increase / increase

decrease / increase

decrease / decrease

increase / decrease

#40. Which of the following is a reason to operate an aeroplane at 'long range speed'?

The aircraft can be operated close to the buffet onset speed

In order to prevent loss of speed stability and tuck-under

It offers greatly reduced time costs than with maximum range speed

In order to achieve speed stability

#41. Long range cruise is a flight procedure which gives:

an IAS which is 1% higher than the IAS for maximum specific range

a specific range which is 99% of maximum specific range and a lower cruise speed

a specific range which is about 99% of maximum specific range and higher cruise speed

a 1% higher TAS for maximum specific range

#42. The lowest point of the frag or thrust required curve of a jet aeroplane, is the point for:

minimum drag and maximum endurance

maximum specific range and minimum power

minimum power minimum specific range

#43. If other factors are unchanged, the fuel mileage or range (nautical miles per kg. is :

independent from the centre of gravity position

lower with an aft centre of gravity position

higher with a forward centre of gravity position

lower with a forward centre of gravity position

#44. To achieve the maximum range over ground with headwind the airspeed should be:

lower compared to the speed for maximum range cruise with no wind

reduced to the gust penetration speed

higher compared to the speed for maximum range cruise with no wind

equal to the speed for maximum range cruise with no wind

#45. When utilising the step climb technique, one should wait for the weight reduction, from fuel burn, to result in:

The aerodynamic ceiling to increase by approximately 2,000ft above the present altitude whereby one would climb approximately 4,000ft higher

The optimum altitude to increase by approximately 2,000ft above the present altitude, whereby one would climb approximately 4,000ft higher

The manoeuvre ceiling to increase by approximately 2,000ft above the present altitude, whereby one would climb approximately 4,000ft higher

The en-route ceiling to increase by approximately 2,000ft above the present altitude, whereby one would climb approximately 4,000ft higher

#46. Which of the following statements is true regarding the performance of an aeroplane in level flight?

The maximum level flight speed will be obtained when the power required equals the maximum power available from the engine

The minimum level flight speed will be obtained when the power required equals the maximum power available from the engine

The maximum level flight speed will be obtained when the power required equals the minimum power available from the engine

The maximum level flight speed will be obtained when the power required equals the power available from the engine

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