Q1. When a jet transport aeroplane takes off with the CG at the aft limit and the trimmable horizontal stabilizer (THS) is positioned at the maximum allowable nose up position for take-off:
Q2. When a jet transport aeroplane takes off with the CG at the aft limit and the trimmable horizontal stabilizer (THS) is positioned at the maximum allowable nose down position for take-off:
Q3. In straight and level flight, as speed is reduced (whilst trimming to keep the stick forces zero):
Q4. If the elevator trim tab is deflected up, the cockpit trim indicator presents:
Q5. If the elevator trim tab is deflected down, the cockpit trim indicator presents:
Q6. Which statement about a primary control surface controlled by a servo tab, is correct?
Q7. A horn balance in a control system has the following purpose:
Q8. An aeroplane has a servo tab controlled elevator. What will happen if the elevator jams during flight?
Q9. When comparing a stabilizer trim system with an elevator trim system, which of these statements is correct?
Q10. What is the position of the elevator in relation to the trimmable horizontal stabilizer of an aeroplane with fully hydraulically operated flight controls that are in trim?
Q11. Which statement is correct about a spring tab?
Q12. Which three aerodynamic means decrease manoeuvring stick forces?
Q13. A servo tab on the rudder moves:
Q14. Balance tabs:
Q15. Aerodynamic balance on a flying control is used to:
Q16. A balance tab reduces aerodynamic stick forces:
Q17. What is the purpose of a balance tab?
Q18. Which direction from the primary control surface does an anti-balance tab move?
Q19. An anti-balance tab moves in the:
Q20. Which of the following devices is used to provide aerodynamic balance?
Q21. When an elevator is deflected down the balance tab will:
Q22. With the aircraft stationary, if the control column is pulled back, a sprig tab on the elevator will:
Q23. A tab fitted to zero the loads on the pilot’s control during flight is known as:
Q24. Some aircraft are fitted with fixed trimming tabs:
Q25. In a servo tab operated control system, movement of the tab:
Q26. Aerodynamic balance may be achieved by:
Q27. If servo tabs are fitted to a main control surface:
Q28. Stick force artificial feel depends on:
Q29. The inputs to the Q unit are from:
Q30. If an aircraft is fitted with powered flying controls, which of the following would be used in the case of manual reversion?
Q31. Which kind of tab is commonly used in case of manual reversion of fully powered flight controls?
Q32. On take-off with the CG at the forward limit:
Q33. What is the fundamental difference between a trim tab and a servo tab?
Q34. If the control surface hinge is placed too far back from the control surface leading edge:
Q35. An inset hinge is an example of (i) balance, and a horn balance is an example of (ii) balance
Q36. An aileron control surface is provided with an inset hinge:
Q37. Inset hinges:
Q38. A graduated horn balance:
Q39. A balance tab is an auxiliary surface fitted to a main control surface operated:
Q40. The location of mass balance weights is:
Q41. When a large modern aircraft employs a variable incidence tailplane, trim changes are made by:
Q42. If an aeroplane exhibits insufficient stick force per g, this problem can be resolved by installing:
Q43. Mass-balancing of control surfaces is used to:
Q44. Which statement is correct?l. On fully hydraulic powered flight controls there is no need for mass balancingll. On fully hydraulic powered flight controls there is no need for trim tabs
Q45. The effect of a mass balance weight is to:
Q46. If mass balance is used to reduce flutter, it should be attached to a control surface:
Q47. Mass balance to reduce control flutter is not required on:
Q48. Power assisted flying control systems have trim controls primarily in order to:
Q49. Which of the following is an advantage of engines mounted on the rear fuselage over those mounted in wing pods?
Q50. One advantage of a movable-stabilizer system compared with a fixed stabilizer system is that:
Q51. What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position?
Q52. The reason for having a trim system on powered assisted flying controls is:
Q53. Which direction from the primary control surface does an elevator adjustable trim tab move when the control surface is moved?
Q54. In order to zero the load if a rearward force on the control column is required to maintain level flight:
Q55. Down movement of the elevator trimming tab will:
Q56. If the trim tab is moved up, what is the cockpit indication?
Q57. On an aircraft with a trimming horizontal stabiliser, what is the elevator position relative to the stabilizer when the aircraft is in the trimmed condition?
Q58. When the trim tab on the elevator is deflected down the cockpit indication of trim is:
Q59. To adjust for a deceleration, the trim tab on an elevator:
Q60. In general transport aeroplanes with power assisted flight controls are fitted with an adjustable stabilizer instead of trim tabs on the elevator. This is because:
Q61. Which statement about the trim position is true related to centre of gravity and adjustable stabilizer position?
Q62. What is the position of the elevator in relation to the trimmable horizontal stabilizer of a power assisted aeroplane, which is in trim?
Q63. How would the exterior appearance of an aeroplane change, when trimming for speed increase?
Q64. How does the exterior view of an aeroplane change, when the trim is used during a speed decrease?
Q65. In the unlikely event of an aircraft becoming airborne with the elevator control lock engaged, operation of an elevator trim tab control in the normal direction to counteract a nose up tendency would:
Q66. When checking the range of movement of an elevator trim tab as part of the pre-flight check, movement of the trim wheel or trim switches will move the:
Q67. If the elevator trim tab has been moved fully to the aircraft nose up position, the available aircraft nose up pitch authority will be:
Q68. When an aileron trim control in the cockpit is moved to correct a tendency to fly left wing low, an aileron trim tab on the left aileron will move:
Q69. To counteract a right-wing low tendency, a fixed tab on the port aileron would:
Q70. An aircraft keeps yawing to the left; you would trim it by: