Q1. Which of the following statements is correct?I. When the critical engine fails during take-off the speed VMCA can be limiting.II. The speed VMCA is always limited by maximum rudder deflection.
Q2. Compared with level flight, the angle of attack must be increased in a steady, coordinated, horizontal turn:
Q3. In a steady coordinated horizontal turn, lift is:
Q4. A jet aeroplane is rolled into a turn, while maintaining airspeed and holding altitude. In such a case, the pilot has to:
Q5. A light twin is in a turn at 20 degrees bank and 150 kt TAS. A heavier aeroplane at the same bank and the same speed will:
Q6. The turn indicator shows a right turn. The slip indicator is left of neutral. To co-ordinate the turn:
Q7. Which statement about minimum control speed is correct?
Q8. VMCA is certified with a bank angle of not more than 5 degrees towards the operating engine because:
Q9. During the take-off roll with a strong crosswind from the left, a four engine jet aeroplane with wing mounted engines experiences an engine failure. The greatest control problem is caused by the loss of which engine?
Q10. During a take-off roll with a strong crosswind from the right: a four-engine jet aeroplane with wing-mounted engines experiences an engine failure. The failure of which engine will cause the greatest control problem?
Q11. VMCL can be limited by: (i) engine failure on take-off (ii) roll rate
Q12. Which of the following statements is correct?l. VMCL is the minimum control speed in the landing configurationll. The speed VMCL is always limited by maximum rudder deflection
Q13. Which of the following statements is correct?I. When the critical engine fails during take-off the speed VMCL can be limitingII. The speed VMCL is always limited by maximum rudder deflection
Q14. Which of the following statements is correct?I. When the critical engine fails during take-off the speed VMCL can be limitingII. The speed VMCL can be limited by the available maximum roll rate
Q15. Which of the following statements is correct?I. VMCL is the minimum control speed in the landing configurationII. The speed VMCL can be limited by the available maximum roll rate
Q16. When is a turn coordinated?
Q17. The speed of minimum glide angle occurs at an angle of attack that corresponds to: (assume zero thrust)
Q18. In general, directional controllability with one engine inoperative on a multiengine aeroplane is adversely affected by:1) High temperature2) Low temperature3) Aft CG location4) Forward CG location5) High altitude6) Low altitudeThe combination that regroups all of the correct statements is:
Q19. In general, directional controllability with one engine inoperative on a multiengine aeroplane is favourably affected by:1) High temperature2) Low temperature3) Aft CG location4) Forward CG location5) High altitude6) Low altitudeThe combination that regroups all of the correct statements is:
Q20. What is the correct relation of the True Air Speed (TAS) for minimum sink rate (VR/Dmin) and best glide angle (V Best glide) at a given altitude?
Q21. The maximum ground distance during a glide with zero thrust decreases:
Q22. The maximum ground distance during a glide with zero thrust increases:
Q23. The descent angle of a given aeroplane in a steady wings level glide has a fixed value for a certain combination of (ignore compressibility effects and assume zero thrust)
Q24. In a straight steady descent, which of the following statements is correct?
Q25. During a straight steady descent, lift is:
Q26. During a straight steady climb and with the thrust force parallel to the flight path:
Q27. In a coordinated horizontal turn: the magnitude of the centripetal force at 45 degrees of bank:
Q28. In order to fly a rate one turn at a higher airspeed, the bank angle must be:
Q29. In a straight, steady climb the thrust must be:
Q30. Which of the following increases the maximum duration of a glide?
Q31. What % increase in lift is required to maintain altitude while in a 45o bank turn?
Q32. What is the percentage increase in stall speed in a 45o bank turn?
Q33. By what approximate percentage will the stall speed increase in a horizontal co-ordinated turn with a bank angle of 45o?
Q34. If an aeroplane performs a steady coordinated horizontal turn at a TAS of 200kts, and a turn radius of 2000m, the load factor (n) will be approximately:
Q35. An aeroplane is in a steady turn, at a constant TAS of 300 kt, and a bank angle of 45°. Its turning radius is equal to: (given: g= 10 m/s²)
Q36. In a slipping turn (nose pointing outwards), compared with a co-ordinated turn, the bank angle (i) and the “ball” or slip indicator (ii) are respectively:
Q37. In a skidding turn (the nose pointing inwards), compared with a coordinated turn, the bank angle (1) and the ball’ or slip indicator (2) are respectively:
Q38. In order to perform a steady level turn at constant speed in an aeroplane, the pilot must:
Q39. Two identical aircraft A and B, with the same mass, are flying steady level co-ordinated 20 degree bank turns. If the TAS of A is 130 kt and that of B is 200kt:
Q40. Two identical aeroplanes, A and B, with the same mass, are flying steady level coordinated 20 degree bank turns. If the TAS of A is 130KT and the TAS of B is 200KT:
Q41. An aeroplane enters a horizontal turn with a load factor n=2 from straight and level flight whilst maintaining constant indicated airspeed. The:
Q42. An aeroplane performs a steady, horizontal, coordinated turn with 45 degrees of bank at 230KT TAS. The same aeroplane with the same bank angle and speed, but with a lower mass will turn with:
Q43. An aeroplane performs a steady horizontal, co-ordinated turn with 45 degrees of bank at 230 kts TAS. The same aeroplane with the same bank angle and speed, but at a higher mass:
Q44. In a steady, horizontal, coordinated turn:
Q45. How does VMCG change with increasing field elevation and temperature?
Q46. For a given aeroplane which two main variables determine the value of VMCG
Q47. Given the following characteristic points on a jet engine aeroplane’s Polar curve:1. CLMAX2. Long range cruise (zero wind)3. Maximum lift to drag ratio4. Minimum Rate of Descent (assume zero thrust)5. Maximum range cruise (zero wind)The correct combinations are:
Q48. Given the following characteristic points on a jet engine aeroplane’s polar curve:1) CLMAX2) Long range cruise (zero wind).3) Maximum lift to drag ratio.4) Minimum rate of descent (assume zero thrust).5) Maximum range cruise (zero wind).Arrange these points in order of increasing angle of attack:
Q49. Two identical aeroplanes A and B are flying horizontal steady turns. Further data are:A: W=1500 kg Bank=20o TAS=130 ktB: W=1500 kg Bank=20o TAS=200 ktWhich of the following statements is correct?
Q50. An aeroplane is straight and level flight at 300kts is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially, and the load factor reaches a value of approximately 1.2:
Q51. On an asymmetrical, single curve aerofoil, in subsonic airflow, at low angle of attack, when the angle of attack is increased, the centre of pressure will (assume a conventional transport aeroplane):
Q52. The value of the manoeuvre stability of an aeroplane is 150 N/g. The load factor in straight and level flight is 1. The increase of stick force necessary to achieve the load factor of 2.5 is:
Q53. The bank angle in a rate-one turn depends on:
Q54. When a pilot makes a turn in horizontal flight, the stall speed:
Q55. Which has the effect of increasing load factor (all other relevant factors being constant)?
Q56. What factors determine the distance travelled over the ground of an aeroplane in a glide?
Q57. Load factor is:
Q58. What is the approximate value of the lift of an aeroplane at a gross weight of 50.000 N, in a horizontal co-ordinated 45 degrees banked turn?
Q59. The positive manoeuvring limit load factor for a light aeroplane in the utility category in the clean configuration is:
Q60. The lift of an aeroplane of weight W in a constant linear climb with a climb angle (gamma) is approximately:
Q61. The theoretical best range speed for a jet aircraft at low level is:
Q62. Propeller aircraft flown at medium altitude at the recommended EAS will have a better specific air range (SAR) than at sea level because:
Q63. For an aircraft in level flight, if the wing centre of pressure is aft of the centre of gravity and there is no thrust-drag couple, the tailplane load must be:
Q64. In a steady climb:
Q65. In a steady turn at constant height:
Q66. An aeroplane performs a steady horizontal turn with 20 degrees bank and 150 kt TAS. The same aeroplane with the same bank angle and the same speed, but at a lower mass will:
Q67. Weight acts:
Q68. For a jet aircraft the best rate of climb is achieved:
Q69. In order to achieve the maximum rate of climb, aircraft should be flown at the indicated airspeed which:
Q70. An aircraft in flight is affected by loads. These may be classified as:
Q71. During a correctly balanced turn:
Q72. The angle of climb of an aircraft is proportional to ___ and ___ as weight increases:
Q73. Which of the following will give an increase of ground range when gliding at VDmin?
Q74. From the polar diagram of the entire aeroplane one can read:
Q75. Which of the following statements is correct?
Q76. The greatest gliding range would be obtained from a wing at:
Q77. Flying horizontally in a turn:
Q78. n a steady banked turn the lift will:
Q79. The margin between the power available and the power required:
Q80. A pitch up could be caused by:
Q81. In a level banked turn, the stalling speed will: