Q1. Flaperons are controls which are used simultaneously as:
Q2. The flaperon is a control that operates simultaneously as:
Q3. The type of flap which extends rearward from the trailing edge of the wing as it is lowered is called:
Q4. Manoeuvrability is best at:
Q5. The range of control surface movements is limited by:
Q6. Over tensioned cables in a flying control system could result in:
Q7. The axes of an aircraft by definition must all pass through the:
Q8. The normal axis of an aircraft is:
Q9. A cable operated control system has external locks:
Q10. The aerodynamic force on a control surface:
Q11. Control surface flutter:
Q12. Power assisted flying controls:
Q13. The primary flight controls:
Q14. The expression ‘primary flight control’ applies to the:1. Stabilizer2. Rudder3. Speed brake4. AileronThe combination regrouping all of the correct statements is:
Q15. An aeroplane equipped with irreversible flight controls:
Q16. A flight control surface actuator is said to be irreversible when:
Q17. Which of these statements regarding most gust lock systems is correct?
Q18. Which of these statements about a gust lock system are correct or incorrect?1. There is no need for a gust lock on irreversible flight controls2. Manual flight controls should have a gust lock`
Q19. Which of these statements about a gust lock system are correct or incorrect?1. Irreversible flight controls should have a gust lock2. There is no need for a gust lock on manual flight controls
Q20. Which of these statements about a gust lock system are correct or incorrect?I. A gust lock can be used in flight to reduce the effects of turbulenceII. There is no need for a gust lock on reversible flight controls
Q21. Which of these statements about a gust lock system are correct or incorrect?I. There should be suitable design precautions to prevent flight with the gust lock engaged.II. Reversible flight controls should have a gust lock.
Q22. Given an aeroplane with irreversible primary flight controls: how is control maintained if one hydraulic system is lost due to a hydraulic leak?
Q23. Flutter results from two deformation modes which are:
Q24. During initiation of a turn with speed brakes extended, the roll spoiler function induces a spoiler deflection:
Q25. Yaw is followed by roll because:
Q26. In general, control forces are reduced by:
Q27. Rotation about the longitudinal axis of an aeroplane can be achieved by:
Q28. A jet aeroplane equipped with inboard and outboard ailerons as well as spoilers is cruising at its normal Mach number. In this case:
Q29. The function of ailerons is to rotate the aeroplane about the:
Q30. Extension of FOWLER type trailing edge lift augmentation devices, will produce:
Q31. In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack will:
Q32. Which statement is correct?I. On fully hydraulic powered flight controls there is no need for mass balancing2. On fully hydraulic powered flight controls there is no need for trim tabs
Q33. In straight flight, as speed is increased, whilst trimming to keep the stick forces zero:
Q34. Stick forces, provided by an elevator feel system, depend on:
Q35. Examples of aerodynamic balancing of control surfaces are:
Q36. Examples of aerodynamic balancing of control surfaces are:
Q37. Examples of aerodynamic balancing of control surfaces are:
Q38. If the nose of an aeroplane yaws left, this causes:
Q39. Flutter control of surfaces is:
Q40. Which three aerodynamic means decrease maneuvering stick forces?
Q41. Which of the following statements concerning control is correct?
Q42. Outboard ailerons (if fitted) are normally used:
Q43. What are the primary roll controls on a conventional aeroplane?
Q44. When a turn is initiated, adverse yaw is:
Q45. When roll spoilers are extended, the part of the wing on which they are mounted:
Q46. A modern jet aeroplane equipped with inboard and outboard ailerons plus roll control spoilers is cruising at its normal cruise Mach number:
Q47. An aeroplane is provided with spoilers and both inboard and outboard ailerons. Roll control during cruise is provided by:
Q48. When are outboard ailerons (if present) de-activated?
Q49. In what phase of flight are the outboard ailerons (if fitted) not active?
Q50. Aileron deflection causes a rotation around the longitudinal axis by:
Q51. On a jet aeroplane (engines mounted below the low wing) the thrust is suddenly increased. Which of these statements is correct about the elevator deflection required to maintain zero pitching moment?
Q52. Low speed pitch up is caused by the:
Q53. The elevator deflection required for a given maneuver will be:
Q54. A jet transport aeroplane exhibits pitch up when thrust is suddenly increased from an equilibrium condition, because the thrust line is below the:
Q55. Which statement about CG limits is correct?
Q56. The elevator deflection required for a given maneuver will be:
Q57. Which statement about elevators is correct?
Q58. When the CG position is moved forward, the elevator deflection to achieve a given load factor greater than 1 will be:
Q59. With forward CG movement the elevator deflection required for a manoeuvre with load factor greater than one will:
Q60. Which of the following is the reason for putting the horizontal stabilizer (tailplane) on top of the (vertical) fin, known as a T-tail?
Q61. Rotation about the normal axis is called:
Q62. Aeroplane maneuverability decreases for a given control surface deflection when
Q63. For a given elevator deflection, aeroplane longitudinal maneuverability decreases when:
Q64. For a given elevator deflection, aeroplane longitudinal maneuverability increases when:
Q65. Aeroplane maneuverability increases for a given control surface deflection when
Q66. The elevator deflection required for a given maneuver will be:
Q67. The elevator deflection required for a given maneuver will be:
Q68. What is the purpose of a slat on the leading edge?
Q69. Which of the following devices is used to counter adverse yaw on rolling into or out of a turn?
Q70. The centre of gravity moving aft will:
Q71. In a mechanically controlled aeroplane, the most forward allowable position of the centre of gravity could be limited by the: