CLIMB AND DESCENDING – Air – DGCA Question Bank For Politics

#1. What speed is required to achieve maximum endurance in a piston engine powered and jet engine powered aircraft respectively?

VMD VMP

VMP VMD

VMO VMP

VMP VMO

#2. Select the appropriate words to complete the following statement. Fuel flow in a piston engine aircraft is proportional to .......... whilst that in a jet powered aircraft is proportional to ......... Thrust output of a jet engine .................. with increasing airspeed whilst that of a piston engine ............ I. Is approximately constant 2. Thrust 3. Reduces rapidly 4. Power 5. RPM

5,2,1,3

4,2,3,1

4,2,1,3

2,4,3,1

#3. Select the correct words to complete the following statement. To achieve the maximum possible glide range it is necessary to fly at ........... This is achieved by flying the aircraft in a .................... condition and at .........

. BEST L:D RATIO 20° FLAPS VMP

BEST L2:D RATIO FLAPS UP VMD

BEST L:D RATIO FLAPS UP VMD

BEST L2:D RATIO FLAPS UP VMP

#4. What speed is required to achieve maximum angle of climb in a jet aircraft and a piston aircraft respectively and for what purpose might this be required?

VMD Minimum safe speed obstacle clearance after take-off.

VMP Minimum safe speed obstacle clearance after take-off.

Minimum safe speed VMD Gain height rapidly.

VMD Minimum safe speed Gain height rapidly.

#5. An aircraft of mass 200000 Kg is able to achieve a maximum climb gradient of 5%. At what mass would it be able to achieve a maximum gradient of 4%? An aircraft of mass 200000 Kg is able to achieve a maximum climb gradient of 5%. At what mass would it be able to achieve a maximum gradient of 4%?

250000 Kg.

150000 Kg.

300000 Kg.

275000 Kg.

#6. What happens to the range between minimum and maximum flight speeds for a subsonic aircraft as altitude increases?

It increases.

It decreases.

It remains constant.

It decreases then increases.

#7. Select the appropriate words to complete the following statement. Thrust horsepower output of a propeller aircraft ...... with increasing airspeed whilst that of a jet .. . 1. Is approximately constant. 2. Is unchanged. 3. lncreases rapidly then decreases rapidly. 4. Reduces slowly. 5. lncreases approximately linearly.

5,2

4,1

4,2

3,5

#8. When flying at VMD an aircraft has a C, of 0.45 and a CD of 0.0225. if its engines fail when flying at 36000 feet what will be its maximum glide range?

100 nm.

200 nm.

120 nm.

175 nm.

#9. When flying at VMD an aircraft weighing 400000 Ibf has a CL of 0.45 and a CD of 0.0225. If its engines fail when fljling at 36000 feet what will be its maximum glide range if the pilot immediately dumps 100000 Ibf of fuel? What effect will the reduced weight have on VMD?

100 nm Reduce VMD by 25%.

200 nm. Increase VMD by 25%.

120 nm. No change in VMD

120 nm. Reduce VMD

#10. What is the available rate of climb at service ceiling for a piston and jet aircraft respectively?

500 fpm 100 fpm.

100 fpm 500 fpm.

50 fpm 100 fpm.

250 fpm 500 fpm.

#11. What speed is required to achieve best rate of climb in a jet and piston aircraft respectively?

VMD VMP.

VMP VMD

Between VMP and VMD Between VMD and VNE

Greater than VMD Less than VNE.

#12. How is the absolute ceiling indicated on a power available i power required graph for a piston and jet aircraft respectively?

The power available curve will be tangential to the power required curve.

The distance between power available and power required will be just sufficient to give rates of climb of 100 fprn and 500 fprn respectively.

For a piston aircraft the power available curve will be tangential to the power required curve. A thrust available i thrust required curve must be used for a jet aircraft.

At VMD and VMP respectively.

#13. What will be the effect of a headwind on glide range and glide angle respectively?

Decrease Decrease.

No effect Increase.

Decrease Increase.

Increase No effect.

#14. What will be the effect of a tailwind on glide range and rate of descent respectively?

Increase Decrease.

No effect Increase.

Decrease Increase.

Increase No effect

#15. Which of the following best describes the effect of flap deployment?

lncreased lift at any given speed, reduced L;D ratio, increased take-off speed and landing speeds, increased angle of climb.

lncreased lift at any given speed, increased L;D ratio, reduced take-off speed and landing speeds, reduced angle of climb.

lncreased lift at any given speed, reduced L;D ratio, reduced take-off speed and landing speeds, reduced angle of climb.

lncreased lift at any given speed, reduced L;D ratio, increased take-off speed and landing speeds, no effect on angle of climb.

#16. Best endurance for a piston aircraft is achieved at VMP, whilst that for a jet aircraft is achieved at (VMD). Why is this so?

Fuel consumption in a piston aircraft is proportional to power output, whereas that of a jet aircraft is proportional to thrust and hence drag.

Fuel consumption in a piston aircraft is proportional to rpm, whereas that of a jet aircraft is proportional to power and hence drag.

Fuel consumption in a piston aircraft is proportional to thrust, whereas that of a jet aircraft is proportional to power and hence drag.

Fuel consumption in a piston aircraft is proportional to power output, whereas that of a jet aircraft is proportional to rpm.

#17. Which of the following best describes the effect of increasing altitude on maximum rate of climb?

Both power available and power required increase with increasing altitude but the gap between them narrows so rate of climb reduces.

Both power available and power required decrease with altitude but the gap between them narrows so rate of climb reduces.

Power available increases with altitude whilst power required reduces so the gap between them and hence rate of climb increases.

Power available reduces with altitude whilst power required increases so the gap between them and hence rate of climb decreases.

#18. Which of the following best describes the manner in which best climb speed varies with altitude?

Best climb €AS increases whilst best climb TAS reduces with increasing altitude for both piston and jet aircraft. The effect on TAS is of the same magnitude in both cases.

Best climb EAS and best climb TAS both increase with increasing altitude for both piston and jet aircraft. The effect on TAS is greater for a piston than for a jet.

Best climb EAS and TAS both decrease with increasing altitude for both piston and jet aircraft. The effect on TAS is greater for a jet than for a piston.

Best climb EAS reduces whilst best clirr~b TAS increases with increasing altitude for both piston and jet aircraft. The effect on TAS is greater for a piston than for a jet.

#19. How will a headwind and a tailwind respectively affect best range glide speed?

Decrease lncrease

Decrease Decrease

lncrease Decrease

lncrease lncrease

#20. If an aircraft enters a banked turn whilst climbing to cruising altitude what effect will this have on rate of climb at constant power setting?

Climbing and turning occur in different planes and hence are not related, so rate of climb will remain constant regardless of bank angle.

Banking will increase load factor and hence induced drag. This will reduce the rate of climb.

Although banking wiil increase load factor and hence induced drag, rate of climb depends only on excess thrust. Rate of climb will therefore remain unchanged.

Banking will reduce the climb gradient, so more power will be available to increase rate of climb.

#21. Select the appropriate words to complete the following statement. Fuel flow in a piston engine aircraft is proportional to .......... whilst that in a jet powered aircraft is directly proportional to ......... Thrust available from a jet engine .................. with increasing airspeed whilst that of a piston engine ................ 1. Is approximately constant 2. Thrust 3. Reduces rapidly 4. Power 5. Increases approximately linearly

5,2,1,5

4,2,1,3

4,2,5,3

2,4,5,1,

#22. An aircraft weighing 200000 Ibf has a maximum excess power available of 1500 Thrust Horse Power. What will be its maximum rate of climb?

512 fpm.

753 fpm.

248 fpm.

358 fpm.

#23. An aircraft weighing 50000 Ibf requires a thrust of 20000 Ibf when flying straight and level at 250 Kts IAS. What will be its maximum climb gradient at this speed assuming its maximum thrust at this speed is 40000 Ibf and the total drag force does not change during the climb?

20%

30%

40%

50%

#24. When does the second segment climb begin?

At the start of flap retraction.

At the start of acceleration from VLOF to V2.

At the end of landing gear retraction.

At the start of acceleration from V2 to flap retraction speed.

#25. When does the third segment begin?

When the flaps are fully retracted.

400 ft gross height minimum.

At the start of acceleration from VLOF to V2.

At the start of acceleration to flap retraction speed.

#26. In a constant mach descent the pitch angle will?

Decrease.

Remain constant.

Increase.

Increase then decrease.

#27. An aircraft weighing 50000 Ibf requires a thrust of 20000 Ibf when flying straight and level at 250 Kts IAS. If it were to climb to 40000 ft what would be its power available in comparison to that at ISA msl?

1/4.

1/3.

1/2.

1/5.

#28. What would be the effect of sweeping back the wings of a variable geometry aircraft in gliding flight?

Profile drag would reduce unless glide angle was reduced.

Induced drag would increase unless glide angle was increased.

Glide range and rate of descent would be increased.

Glide range and rate of descent would be decreased.

#29. How is maximum rate of emergency descent achieved in a high speed jet aircraft?

Pitch down, retract flaps, spoilers and undercarriage and increase thrust,

Deploy spoilers, reduce thrust to idle, use pitch to maintain speed within limits

Deploy high lift device, retract undercarriage and spoilers. Increase thrust to maximum, pitch 45 degrees nose down.

Thrust to idle, increase pitch to stalling angle, maintain nose up attitude to hold aircraft in the stall.

#30. What do points A and B represent on the whole aircraft polar diagram right?

Best L;D ratio Minimum drag.

Minimum drag Minimum power

Best L:D ratio Stalling.

Stalling Best L:D ratio.

#31. Why must there be an acceptable approach climb gradient?

To maintain control in turbulence.

To maintain altitude on the approach.

To retain speed stability on the approach.

To ensure adequate go-around performance.

#32. An aircraft weighing 50000 Ibf is able to achieve a maximum rate of climb of 1500 ft / min when climbing at 250 Kts TAS. What will be the maximum all up weight at which it can achieve a 5% climb gradient at this speed assuming its power available and total drag do not change during the climb?

40000 ibf.

50000 ibf.

60000 ibf.

70000 ibf.

#33. Increased weight reduces the rate of climb and climb gradient but?

VX increases and VY decreases.

VX and VY increase.

VX and VY decrease.

VX decrease and VY increase.

#34. Best climb gradient is achieved by flying at approximately?

1.1 VS.

1.2 VS.

Best CL : CD2.

Best CL : CD.

#35. Absolute ceiling occurs when?

ROC is 300 ft/min.

ROC is 750 ft/min.

For a jet ROC is 100 ft/min and 500 ft/min for a propeller aircraft.

ROC is zero for both jets and propeller aircraft.

#36. What airspeed will produces the greatest glide endurance?

VMP which is higher than VMD.

VMP which is lower than VMD.

VMD.

VMP or VMD depending on engine type.

#37. What factors determine maximum glide range?

Wind, CL:CD ratio and weight.

Wind, CL:CD ratio and height.

Wind, Speed and weight.

Wind, CL:CD and altitude.

#38. What are VMGA and VMDR?

Maximum and minimum speeds for gliding,

Minimum and maximum speeds for gliding.

Speed for shallowest glide path and speed for lowest rate of descent.

Speed for maximum glide range and speed for minimum glide range.

#39. How do VMGA and VMDR compare?

VMGA is greater than VMDR.

VMGA is less than VMDR.

VMGA isthe same as VMDR.

Depends on aspect ratio.

#40. Which of the following is equal to lift in a steady climb or descent?

W Cos angle of climb or descent.

W Sin angle of climb or descent.

W Tan angle of climb or descent.

None of the above.

#41. What proportion of thrust is employed in supporting the weight of an aircraft in a steady climb?

W Sin angle of climb.

W Cos angle of climb.

W Tan angle of climb.

None of the above.

#42. What provides maximum glide range?

Strong headwind.

Light headwind.

Strong tailwind.

Light tailwind.

#43. What would give maximum glide range in a headwind?

Flying faster than VMD.

Flying slower than VMP.

Flying slower than VMD.

Flying faster than VMP.

#44. What would give maximum glide range in a tailwind?

Flying faster than VMD.

Flying slower than VMD.

Flying faster than VMP.

Flying slower than VS.

#45. Which of the points on the CL:CD polar would give maximum glide range?

A.

B.

C.

D.

#46. In a steady climb?

Lift is less than weight and thrust is less than drag

Lift is less than drag and weight is less than thrust.

Weight is less than lift and drag is more than thrust.

Weight is more than lift and drag is less than thrust.

#47. What is the speed for minimum sink rate'?

VMSR.

VMD.

VMP.

VNE.

#48. What flap position would give maximum glide range?

Max°

Min°

25°

40°

#49. What speed gives best angle of climb in a jet aircraft?

VMP.

VMD.

VMCL.

VMCA.

#50. Which of the following occur at VMD? 1. L:D Max. 2. Max jet endurance. 3. Max prop range. 4. Max jet climb angle. 5. Max glide range all types.

1, 2, 3.

2, 3, 4.

3, 4, 5.

All of the above.

#51. What will be the effect of an increase in weight? 1. VMD will increase. 2. Glide range will decrease. 3. Glide angle will increase. 4. Glide range and angle win be unaffected.

1, 2, 3.

2 , 3, 4.

None of the above.

1,4.

#52. In what direction does lift act in a steady climb?

Upwards.

Vertically.

At right angles to the Right path.

None of the above.

#53. What is the absolute ceiling of an aircraft? 1. The altitude where the low speed and high speed stall lines cross. 2. The altitude at which power required is equal to power available. 3. The altitude at which thrust available is equal to drag. 4. The altitude at which rate of climb is zero.

1, 2, 3.

2, 3, 4.

None of the above.

All of the above.

#54. Increasing aircraft weight.. .. . ..... glide speed and.. . .. ..rate of descent?

Increases, Decreases.

Increases, Increases.

Decreases, Decreases.

Decreases, increases.

#55. To descend at constant glide angle and IAS, the pitch attitude must................?

Increase.

Decrease.

lncrease then decrease.

Remain constant.

#56. For a constant mach number descent, gradient must.. . . . .?

Decrease.

Increase.

lncrease then decrease.

Remain constant.

#57. For a constant IAS descent, gradient must.. . . . .?

Decrease.

Increase.

lncrease then decrease.

Remain constant.

#58. A headwind in a constant mach nurnber climb will ............ angle of climb?

Decrease.

Increase.

Not affect.

lncrease or decrease depending on mach number.

#59. For maximum glide range, TAS must . . ... ?

Decrease in a headwind.

Decrease in a tailwind.

lncrease in a tailwind.

Remain constant.

#60. To descend at constant IAS the ............ must be.. . ... . . .. . ?

pitch down, Increased.

pitch down, Maintained constant.

Pitch up, Increased.

Pitch up, Decrease.

#61. Best climb angle is achieved at ............ ?

VMP.

VMD.

VX.

VY.

#62. Maximum rate of climb occurs at ........... speed?

Maximum excess thrust.

Minimum drag.

Minimum thrust.

Maximum excess power.

#63. Maximum glide range is achieved at ............ ?

CL4: CD Max.

CL3 : CD Max.

CL : CD Max.

CL2 : CD Max.

#64. A steady climb requires ...... thrust and ..... power compared with constant speed level flight?

Less less.

Less more.

More more.

More Less.

#65. Increasing altitude at constant weight and mach number requires?

lncreased TAS.

lncreased IAS.

lncreased A of A.

Constant A of A.

#66. The correct procedure for an emergency descent is?

Maximise drag, minimise thrust, push the nose hard down.

Minimise drag, maximise thrust, push the nose hard down.

Maximise drag, minimise thrust, control speed with pitch attitude.

Maximise drag, minimise thrust, bank steeply.

#67. What is the correct equation?

V2 < VMD < VMP = VX < VY.

V2 < VX < VY = VMP < VMD.

V2 < VMP <VMD = VX < VY.

VMP < V2 < VX = VY < VMP.

#68. Rate of climb is .......... by a headwind?

Increased.

Decreased.

Not affected.

lncreased or decreased depending on load factor.

#69. Angle of climb is .......... by a headwind?

Increased.

Decreased.

Not affected.

lncreased or decreased depending on load factor.

#70. Climb gradient is ........ by a headwind?

Increased.

Decreased.

Not affected.

lncreased or decreased depending on load factor.

#71. Power required is .......... as altitude increases in a steady climb?

Increased.

Decreased.

Not affected.

lncreased or decreased depending on load factor.

#72. When climbing to cruise altitude with a headwind?

Climb time is decreased.

Ground distance is decreased.

Climb time is increased.

Ground distance is increased.

#73. If excess power is 25000 ft Ibf/min and aircraft weight is 10000 Ibf what will be the maximum rate of climb?

2.5 ft/min.

25 ft/min.

250 ft/min.

2500 ft/min.

#74. If maximum thrust is 25000 Ibf, drag is 15000 Ibf and weight is 10000 Ibf what will be the maximum climb gradient?

100%.

50%.

70%.

Infinite ( or vertical).

#75. If at 250 Kts, excess power is 50,000,000 ft Ibf/min, and weight is 10000 Ibf, what is maximum angle of climb?

1.5°

11.5°

21.5°

31.5°

#76. What might the points C and D represent on the whole aircraft polar Diagram right?

Best L;D ratio Minimum drag.

Jet aircraft VY Prop aircraft VY.

Best L:D ratio Stalling.

Prop aircraft VY Jet aircraft VY.

#77. What might points C and D represent on the whole aircraft polar Diagram right?

Prop aircraft VY Prop aircraft VX.

Prop aircraft VX VMP.

VMD Prop aircraft VX.

Prop aircraft VY VMD.

#78. Increasing weight will ........ glide speed and ........ maximum glide endurance?

Increase Increase.

Increase Decrease.

Decrease Decrease.

Decrease Increase.

#79. Increasing weight will ......... VMD and .......... rate of descent for best glide range?

Increase Increase.

Increase Decrease.

Decrease Decrease.

Decrease Increase.

#80. Deploying landing flap will ........ VX and .......... maximum angle of climb?

Increase Increase.

Increase Decrease.

Decrease Decrease.

Decrease Increase.

#81. Use of reheat in a climb will ........ maximum angle of climb, and ..... maximum rate of climb?

Increase Increase.

Increase Decrease.

Decrease Decrease.

Decrease Increase.

#82. If use of reheat doubles thrust available this will .......... the maximum angle of climb?

Half.

Double.

More than double.

Less than double.

#83. If TAS is 200 Kts and rate of climb is 1000 ft/min, what is the climb gradient?

5%.

10%.

50%.

15%.

#84. If climb gradient is 15% and TAS is 250 Kts, what is the rate of climb?

1750 ft/min.

2750 ft/min.

3750 ft/min.

4750 ft/min.

#85. For maximum rate of descent use .... thrust, .......... Drag, and ........... to maintain airspeed within limits?

Maximum Minimum Spoilers.

Maximum Minimum Attitude.

Minimum Maximum Spoilers.

Minimum Maximum Attitude.

#86. In a constant IAS climb ... . ... might be inadvertently exceeded?

VMO

VNE.

VS.

MMO.

#87. In a constant TAS climb . . . . . ... might be inadvertently exceeded?

VMO.

VNE.

VS.

MMO.

#88. In a constant mach climb . . . . . . . might be inadvertently exceeded?

VMO.

VNE.

VS.

MMO.

#89. In a constant mach descent . . . . . . . might be inadvertently exceeded?

VMO.

VNE.

VS.

MMO.

#90. When climbing at constant 1/2B V2 IAS will ....... . ?

increase.

Decrease

Remain constant.

Increase up to 36000 ft then remain constant.

#91. If at 40000 feet altitude air density is 1/4 of its sea level value, how will best climb TAS compare with best climb IAS?

The same.

Double.

Quadruple.

Less than.

#92. If maximum thrust is 10000 Ibf, drag is 500 Ibf and weight is 5000 Ibf , what will be the maximum rate of climb at the absolute ceiling?

100 ft/min.

500 ft/min.

zero.

More than 500 ft/min.

#93. How does VX compare with VY at the absolute ceiling?

The same.

More than.

Less than.

More or less than depending on aircraft type.

#94. How does the angle of climb of a propeller aircraft vary with increasing airspeed?

Decreases

Increases

Remains constant.

lncreases up to VMD then decreases.

#95. How does maximum angle of climb for a jet aircraft vary with increasing airspeed?

Decreases

Increases

Remains constant.

lncreases up to VMD then decreases.

#96. How does maximum rate of climb for a jet aircraft vary with increasing airspeed?

Decreases.

lncreases up to VMP then decreases.

Remains constant.

lncreases up to 1.3VMD then decreases.

#97. If weight is 15000 Ibf, maximum thrust is 25000 Ibf and drag is 5000 Ibf, what will be the maximum climb angle?

13.6°.

23.6°.

33.6°,

90°.

#98. If excess power is 350 THP when TAS is 250 Kts and weight is 10000 Ibf, what will be the maximum rate of climb at that speed?

1155 ft/min.

2155 ft/min.

3155 ft/min.

4155 ft/min.

#99. If the weight of the aircraft in question 98 is doubled how will this affect maximum rate of climb?

Double it.

Half it.

Increase it.

Decrease it by 41%.

#100. If airspeed is maintained constant as aircraft weight reduces due to fuel use the aircraft will be in a .. ..?

Constant rate climb.

Cruise climb.

Zoom climb.

Constant altitude flight.

#101. When climbing to cruise altitude with a headwind?

Climb rate is decreased.

Climb rate is increased.

Ground speed is decreased.

Ground speed is increased.

#102. An aircraft of mass 120000 Kg is at a pressure altitude of 10000 ft, with an OAT of + 13°C. If its IAS is 90 Kts and its climb gradient is 3.5%, which of the options below is closest to its ROC?

245 ft/min.

360 ft/min.

945 ft/min.

300 ft/min.

#103. When descending from FL400 to FL360, then from FL360 to FL 200 at constant mach number, the descent gradient will?

lncrease all the way.

lncrease then decrease.

lncrease then remain constant.

Constant all the way.

#104. When descending from FL360 to FL260 at constant mach number, then from FL260 to FL 100 at constant CAS, the descent gradient will?

lncrease all the way.

lncrease then decrease.

lncrease then remain constant.

Constant all the way.

#105. A small twin prop aircraft is climbing from a screen height of 50 ft at a gradient of 10%. By how much will it clear an obstacle 850 m above field elevation at a distance of 10000 m from the screen?

180 m.

150 m.

170 m.

200 m.

#106. The climb schedule for an aircraft is 300 Kts /mach 0.84. At the crossover altitude?

If the aircraft is at the correct CAS it will automatically be at the correct mach number.

The must be accelerated or decelerated to the correct mach number.

If the CAS is correct and the mach number is too low that is acceptable, but if the mach number is too high the aircraft must be decelerated to the correct mach number.

It the aircraft is at the correct CAS it will always be necessary to decelerate to the correct mach number.

#107. The climb schedule for an aircraft is 300 Kts / mach 0.84. When climbing from the crossover altitude?

Climb gradient will increase.

The must be accelerated or decelerated to the correct mach number to maintain constant ROC.

Climb gradient will decrease.

It the aircraft is at the correct CAS it will always be necessary to decelerate to the correct ROC.

#108. The climb schedule for an aircraft is 300 Kts / mach 0.84. When climbing from the crossover altitude?

Pitch attitude must be reduced to maintain constant gradient.

Pitch attitude must be increased to maintain constant gradient.

Pitch attitude must be increased to increase gradient.

Pitch must be increased to maintain mach number but gradient will increase.

#109. An aircraft is conducting certification glide test flights. For the first test its mass is 100000 Kg and it achieves a maximum glide range of 100 nm from an altitude of 36000 ft. If it then climbs back to 36000 ft to repeat the test, its best glide speed will be . . . .. and its glide range will be.. . . . . . compared to the first test?

Higher greater.

Higher less.

Lower The same.

Lower greater.

#110. An aircraft is conducting certification glide test flights. For the first test its mass is 100000 Kg and it achieves a maximum glide range of 100 nm from an altitude of 36000 ft. If it then climbs back to 36000 ft to repeat the test, its best glide L:D ratio will be . .... and its glide angle will be.. . . ... compared to the first test?

Higher less.

The same greater

Lower The same.

The same the same.

#111. An aircraft is conducting certification glide test flights. For the first test its mass is 100000 Kg and it achieves a maximum glide range of 100 rim from an altitude of 36000 ft. If it then climbs back to 36000 ft to repeat the test?

It will need to fly faster to achieve the same glide angle and ROD as in the first test.

It will need to fly faster to achieve the same glide angle but at a higher ROD than in the first test.

It will need to fly slower to achieve the same glide angle, but will have a lower ROD and glide range than in the first test.

It will need to fly slower to achieve the same glide angle and glide range, but will have a lower ROD than in the first test.

#112. When conducting a type B noise abatement procedure ........ must be maintained up to ............?

V2 1500 ft.

V2 1000 ft.

V2 + 10-20 Kts 1500 ft.

V2 + 10-20 Kts 1000 ft.

#113. Decreasing nose down pitch angle in a glide will?

lncrease range and endurance.

Decrease range and endurance.

lncrease range and decrease endurance.

Decrease range and increase endurance.

#114. What would reduce glide range by the greatest degree?

Tailwind.

Weight increase.

Weight decrease.

Gear deployment.

#115. What would increase glide range by the greatest degree?

Tailwind.

Weight increase.

Weight decrease.

Flap deployment.

#116. If ROC = 250 ft/min and TAS = 150 Kts, which of the following best describes climb gradient in still air? (Assume 1 Kt = 100 fpm)

16.67%.

1.67%.

1.65%.

1.5%.

#117. As a flight progresses, how do best ROC and speed for best ROC vary?

lncrease decrease.

lncrease increase.

Decrease decrease.

Decrease increase.

#118. When climbing at a constant mach number in the troposphere what is the effect on CAS and TAS?

Decrease decrease.

Decrease increase.

Increase decrease.

Increase increase.

#119. What is the effect of increased weight on best ROC and speed for best ROC?

Increase decrease.

Increase increase.

Decrease decrease.

Decrease increase.

#120. When gliding at constant mach number pitch angle and gradient will?

Increase increase.

Decrease decrease.

Increase then decrease increase.

Decrease then remain constant. Decrease.

#121. When conducting a type A noise abatement climb procedure ........ must be maintained up to ............?

V2 + 10 to 20 Kts 1500 ft.

V2 1500 ft.

V2 1000 ft,

V2 + 10 to 20 kts 4000 ft.

#122. The first segment of a type B noise abatement climb procedure is from ..... to ..... with flaps and thrust at ....... and gear ........?

Screen height 1000 fi take-off setting UP

VLOF 1000 ft climb setting UP.

End of TORR 1500 ft take-off setting down.

Screen height 1500 ft climb setting UP.

#123. When would a type A noise abatement climb be used?

For all take-offs after 2300

For all take-offs between 2300 and 0700 the next day.

When the noise sensitive area is very close to the airport.

When the noise sensitive area is some distance from the airport.

#124. When would a type B noise abatement climb be used?

For all take-offs after 2300

For all take-offs between 2300 and 0700 the next day.

When the noise sensitive area is some distance from the airport.

When would a type A noise abatement climb be used?

#125. A noise abatement climb procedure comprises of ...... segments, the first of which starts at ...... .., and the third of which ends at .........?

3 screen height cruise altitude.

3 screen height 3000 ft.

2 VLOF 3000 ft.

2 End of the TORR 1500 ft.

#126. The second segment of a type B noise abatement procedure take-off commences at ...... from where the aircraft is ............., then climbed to ....... ft, whilst being ........?

1000ft accelerated to V4 3000ft accelerating to V4 + 10 kts.

Screen height accelerated to VZF 1500 ft accelerated to VZF + 10 Kts.

1000 ft accelerated to VZF 3000 ft accelerated to VZF + 10 Kts.

1500ft accelerated to VX 2000 ft accelerated to VY.

#127. The second segment of a type A noise abatement procedure take-off commences at ...... from where the aircraft ....... to .......?

1000ft climbs at climb power 3000ft.

Screen height climbs at take-off power 1500ft.

1500 ft climbs at climb power 3000ft.

1500ft climbs at max continuous power 2000ft.

#128. An aircraft climbing to cruising altitude after take-off has a thrust td weight ratio of 1:3. What will be its climb gradient if its lift : drag ratio at climb speed is 20:1 It may be assumed that lift = weight in this climb

8%.

18%.

28%.

38%.

#129. If an aircraft climbs to altitude at a constant IAS considerably lower than MCRIT?

Drag will be constant but climb gradient will decrease.

Drag and climb gradient will decrease.

Drag will increase causing climb gradient to decrease.

Both drag and climb gradient will remain constant.

#130. An aircraft climbing to cruising altitude after take-off has a thrust to weight ratio of 1:5. What will be its climb gradient if its lift : drag ratio at climb speed is 25:1? It may be assumed that lift equals weight in this question.

6%.

16%.

26%.

36%.

#131. Descending at constant mach number might cause?

MMO to be exceeded.

VMO to be exceeded.

Shock stall.

Tuck under.

#132. Climbing at constant IAS might cause?

MMO to be exceeded.

VMO to be exceeded.

Low speed stall.

TAS to reduce.

#133. Increasing IAS in a climb will .. . . . . . .. the altitude at which the mach limit is reached?

Decrease.

Increase

Not affect.

lncrease or decrease depending on temperature.

#134. When descending at constant IAS a headwind will?

lncrease distance covered over ground.

Decrease descent time

Increase descent time

Decrease distance covered over ground.

#135. When descending at constant TAS a headwind will?

Decrease gradient.

Decrease descent time.

lncrease descent time.

lncrease gradient.

#136. VMCL will not be affected by ..........?

Weight.

Altitude.

Power setting.

Humidity.

#137. When descending at constant mach number below 35000 feet angle of attack must?

Increase.

Decrease.

Remain constant.

lncrease or decrease depending on temperature.

#138. When descending at constant IAS below 35000 feet angle of attack must?

Increase.

Decrease

Remain constant.

lncrease or decrease depending on temperature.

#139. When descending at constant TAS below 35000 feet, angle of attack must?

Increase.

Decrease.

Remain constant.

lncrease or decrease depending on temperature.

#140. When climbing at constant Mach number above the tropopause IAS will ..... and TAS will .......?

Decrease, Remain constant.

Decrease, Decrease.

Increase, Remain constant.

Increase, Increase.

#141. In a constant mach number climb in the troposphere true airspeed?

Increases then decreases.

Decreases.

Remains constant.

Increases.

#142. In a constant mach number climb true airspeed?

Increases then remains constant.

Decreases then remains constant.

Decreases then decreases less slowly.

Decreases then decreases more slowly.

#143. In a constant TAS climb in the troposphere?

IAS increases.

IAS decreases.

IAS increases then remains constant.

IAS decreases then remains constant.

#144. In a constant IAS climb in the troposphere?

TAS increases.

TAS decreases.

TAS increases then remains constant.

TAS decreases then remains constant.

#145. In a constant TAS climb?

IAS increases.

IAS decreases.

IAS increases then increases more slowly.

IAS decreases then decreases more quickly.

#146. In a constant IAS climb in the troposphere?

TAS increases and mach number decreases.

TAS increases and mach number increases.

TAS decreases and mach number increases.

TAS decreases and mach number decreases.

#147. In a constant mach number descent there is a danger that?

MMO will be exceeded.

MCRIT will be exceeded.

VMO will be exceeded.

VS will be exceeded.

#148. As altitude increases?

VX and VY both increase.

VX and VY both decrease.

VX decreases and VY remains constant.

VY decreases and VX remains constant.

#149. What happens as a propeller aircraft climbs to its absolute ceiling?

VS VMax, VMin, and VY converge on VX.

VMin, VMax, VMP and VMD converge on VX.

VMin, VMax and VY converge on VX.

The CAS values equating to VX and VY both decrease.

#150. What happens to the CAS values of VX and VMD as a propeller aircraft climbs to its absolute ceiling?

Increase.

Decrease.

Remain constant.

Increase and decrease respectively.

#151. Climb gradient is closest to?

Height gained divide by distance moved through the air.

Distance moved through the air divided by height gained.

TAS divided by ROC.

ROC divided by ground speed.

#152. Climb gradient is proportional to?

(T-D)/W.

(T+D)/W.

TAS/W.

Mach number/W.

#153. If the climb schedule for an aircraft is changed from 275/0.81 to 300/0.81, how will the crossover altitude be affected?

Increase.

Decrease

No change because it depends only on CAS.

No change because it depends only on Mach number.

#154. The climb schedule for an aircraft is 280/0.81. When climbing above the tropopause TAS will?

Increase

Decrease

Remain constant.

Decrease then increase at very high altitude.

#155. If the climb schedule for an aircraft is 280/0.75 what will happen to the crossover altitude if temperature increases?

Increase.

Decrease

Remain constant because TAS is not affected by temperature.

Remain constant because mach number is not affected by temperature.

#156. When gliding the speed giving minimum rate of descent will be?

VMP

VMD

VX

VY

#157. When climbing the mach number for low speed buffet will?

Increase.

Decrease.

Remain constant because low speed buffet is not caused by mach number.

Remain constant because mach number is not affected by altitude.

#158. What happens to climb gradient as an aircraft climbs through the crossover altitude?

Increases.

Decreases.

Remains constant.

Increases or decreases depending on mass.

#159. What happens to speed as an aircraft climbs through its crossover altitude?

It changes from constant TAS to constant mach.

It changes from constant CAS to constant TAS.

It changes from constant CAS to constant mach.

It changes from constant mach to constant CAS.

#160. Why must the speed of an aircraft change when it climbs through its crossover altitude?

To avoid exceeding VMO.

To avoid exceeding MMO.

To avoid exceeding MCRIT.

To avoid low speed stall.

Dgca Question Bank For Pilots

Results

#1. What speed is required to achieve maximum endurance in a piston engine powered and jet engine powered aircraft respectively?

#3. Select the correct words to complete the following statement. To achieve the maximum possible glide range it is necessary to fly at ........... This is achieved by flying the aircraft in a .................... condition and at .........

#4. What speed is required to achieve maximum angle of climb in a jet aircraft and a piston aircraft respectively and for what purpose might this be required?

#5. An aircraft of mass 200000 Kg is able to achieve a maximum climb gradient of 5%. At what mass would it be able to achieve a maximum gradient of 4%? An aircraft of mass 200000 Kg is able to achieve a maximum climb gradient of 5%. At what mass would it be able to achieve a maximum gradient of 4%?

#6. What happens to the range between minimum and maximum flight speeds for a subsonic aircraft as altitude increases?

#8. When flying at VMD an aircraft has a C, of 0.45 and a CD of 0.0225. if its engines fail when flying at 36000 feet what will be its maximum glide range?

#9. When flying at VMD an aircraft weighing 400000 Ibf has a CL of 0.45 and a CD of 0.0225. If its engines fail when fljling at 36000 feet what will be its maximum glide range if the pilot immediately dumps 100000 Ibf of fuel? What effect will the reduced weight have on VMD?

#10. What is the available rate of climb at service ceiling for a piston and jet aircraft respectively?

#11. What speed is required to achieve best rate of climb in a jet and piston aircraft respectively?

#12. How is the absolute ceiling indicated on a power available i power required graph for a piston and jet aircraft respectively?

#13. What will be the effect of a headwind on glide range and glide angle respectively?

#14. What will be the effect of a tailwind on glide range and rate of descent respectively?

#15. Which of the following best describes the effect of flap deployment?

#16. Best endurance for a piston aircraft is achieved at VMP, whilst that for a jet aircraft is achieved at (VMD). Why is this so?

#17. Which of the following best describes the effect of increasing altitude on maximum rate of climb?

#18. Which of the following best describes the manner in which best climb speed varies with altitude?

#19. How will a headwind and a tailwind respectively affect best range glide speed?

#20. If an aircraft enters a banked turn whilst climbing to cruising altitude what effect will this have on rate of climb at constant power setting?

#22. An aircraft weighing 200000 Ibf has a maximum excess power available of 1500 Thrust Horse Power. What will be its maximum rate of climb?

#23. An aircraft weighing 50000 Ibf requires a thrust of 20000 Ibf when flying straight and level at 250 Kts IAS. What will be its maximum climb gradient at this speed assuming its maximum thrust at this speed is 40000 Ibf and the total drag force does not change during the climb?

#24. When does the second segment climb begin?

#25. When does the third segment begin?

#26. In a constant mach descent the pitch angle will?

#27. An aircraft weighing 50000 Ibf requires a thrust of 20000 Ibf when flying straight and level at 250 Kts IAS. If it were to climb to 40000 ft what would be its power available in comparison to that at ISA msl?

#28. What would be the effect of sweeping back the wings of a variable geometry aircraft in gliding flight?

#29. How is maximum rate of emergency descent achieved in a high speed jet aircraft?

#30. What do points A and B represent on the whole aircraft polar diagram right?

#31. Why must there be an acceptable approach climb gradient?

#32. An aircraft weighing 50000 Ibf is able to achieve a maximum rate of climb of 1500 ft / min when climbing at 250 Kts TAS. What will be the maximum all up weight at which it can achieve a 5% climb gradient at this speed assuming its power available and total drag do not change during the climb?

#33. Increased weight reduces the rate of climb and climb gradient but?

#34. Best climb gradient is achieved by flying at approximately?

#35. Absolute ceiling occurs when?

#36. What airspeed will produces the greatest glide endurance?

#37. What factors determine maximum glide range?

#38. What are VMGA and VMDR?

#39. How do VMGA and VMDR compare?

#40. Which of the following is equal to lift in a steady climb or descent?

#41. What proportion of thrust is employed in supporting the weight of an aircraft in a steady climb?

#42. What provides maximum glide range?

#43. What would give maximum glide range in a headwind?

#44. What would give maximum glide range in a tailwind?

#45. Which of the points on the CL:CD polar would give maximum glide range?

#46. In a steady climb?

#47. What is the speed for minimum sink rate'?

#48. What flap position would give maximum glide range?

#49. What speed gives best angle of climb in a jet aircraft?

#50. Which of the following occur at VMD? 1. L:D Max. 2. Max jet endurance. 3. Max prop range. 4. Max jet climb angle. 5. Max glide range all types.

#51. What will be the effect of an increase in weight? 1. VMD will increase. 2. Glide range will decrease. 3. Glide angle will increase. 4. Glide range and angle win be unaffected.

#52. In what direction does lift act in a steady climb?

#53. What is the absolute ceiling of an aircraft? 1. The altitude where the low speed and high speed stall lines cross. 2. The altitude at which power required is equal to power available. 3. The altitude at which thrust available is equal to drag. 4. The altitude at which rate of climb is zero.

#54. Increasing aircraft weight.. .. . ..... glide speed and.. . .. ..rate of descent?

#55. To descend at constant glide angle and IAS, the pitch attitude must................?

#56. For a constant mach number descent, gradient must.. . . . .?

#57. For a constant IAS descent, gradient must.. . . . .?

#58. A headwind in a constant mach nurnber climb will ............ angle of climb?

#59. For maximum glide range, TAS must . . ... ?

#60. To descend at constant IAS the ............ must be.. . ... . . .. . ?

#61. Best climb angle is achieved at ............ ?

#62. Maximum rate of climb occurs at ........... speed?

#63. Maximum glide range is achieved at ............ ?

#64. A steady climb requires ...... thrust and ..... power compared with constant speed level flight?

#65. Increasing altitude at constant weight and mach number requires?

#66. The correct procedure for an emergency descent is?

#67. What is the correct equation?

#68. Rate of climb is .......... by a headwind?

#69. Angle of climb is .......... by a headwind?

#70. Climb gradient is ........ by a headwind?

#71. Power required is .......... as altitude increases in a steady climb?

#72. When climbing to cruise altitude with a headwind?

#73. If excess power is 25000 ft Ibf/min and aircraft weight is 10000 Ibf what will be the maximum rate of climb?

#74. If maximum thrust is 25000 Ibf, drag is 15000 Ibf and weight is 10000 Ibf what will be the maximum climb gradient?

#75. If at 250 Kts, excess power is 50,000,000 ft Ibf/min, and weight is 10000 Ibf, what is maximum angle of climb?

#76. What might the points C and D represent on the whole aircraft polar Diagram right?

#77. What might points C and D represent on the whole aircraft polar Diagram right?

#78. Increasing weight will ........ glide speed and ........ maximum glide endurance?

#79. Increasing weight will ......... VMD and .......... rate of descent for best glide range?

#80. Deploying landing flap will ........ VX and .......... maximum angle of climb?

#81. Use of reheat in a climb will ........ maximum angle of climb, and ..... maximum rate of climb?