A330 FLIGHT CONTROL SYSTEM

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WAT
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162070
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A330 FLIGHT CONTROL SYSTEM
Updated:
2012-07-12 06:31:10
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A330 FLIGHT CONTROL SYSTEM
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  1. The sidestick inputs results in adjusting :

    A. The pitch and roll only.
    B. The pitch and roll and yaw (for turn coordination).
    C. The elevators, ailerons and nosewheel steering (during ground operation).
    B
  2. The A 330 is in a slight climb in normal law; immediatly after the pilot releases the stickto neutral, the flight controls will :

    A. Lower the nose to regain a level flight path.
    B. Maintain the current flight path.
    C. Raise the nose to a steeper flight path.
    B
  3. All flight controls are actuated by hydraulic servos which are controlled by computers :

    A. Or cables.
    B. But the THS and rudder trim may also be controlled by cables.
    C. But the THS and rudder servo may also be controlled by cables.
    C
  4. All flight controls are :

    A. Electrically controlled and hydraulically actuated.
    B. Electrically controlled with mechanical back up control and hydraulically actuated.
    C. Electrically controlled with and hydraulically actuated with mechanicalreversion capability.
    A
  5. The A 330 is being hand flown in normal law. It is established in a 20° left bank turn,to maintain the altitude, the pilot :

    A. Must continually apply after pressure to the sidestick.
    B. Does not need to make an additionnal pitch inputs; the flight control systemwill maintain a level flight path.
    C. Is required to apply minor forward sticks inputs.
    B
  6. Your A 330 is in level flight in normal law, with stick released and airspeed slowed by 20 kt, the flight controls will :

    A. Raise the nose as necessary to maintain the current flight path.
    B. Lower the nose to maintain the current air speed.
    C. Maintain the current pitch attitude and allow the aircraft to begin to sink.
    A
  7. THS auto trim function is active :

    A.When the A 330 is handflown.
    B.When either AP is engaged.
    C.Both answers.
    C
  8. THS auto trim function is neutralized when :

    A. AP in engaged.
    B. Trim wheel is used in the cockpit, or high speed protection is active.
    C. G Load becomes greater than 0.5 g.
    B
  9. On A 330, pitch attitude protection limits pitch attitude of the aircraft to :

    A. 30° nose up (reduced to 25° nose up on low speed) - 20° nose down.
    B. 25° nose up - 30° nose down.
    C. 30° nose up (reduced to 25° nose up on low speed) - 15° nose down.
    C
  10. On A 330, G Load protection limits G Load of the A/C to :

    A. -1g to +2.5g.
    B. -1g to +2.5g in clean configuration - 0g to +2g when slats extended.
    C. 0g to +2g.
    B
  11. Your A 330 is in a 45° bank turn and has entered high speed protection; if the stick is released to neutral protection, the A/C will :

    A. Maintain 45° of bank.
    B. Roll to 33° of bank.
    C. Roll to 0° of bank.
    C
  12. You fly your A 330 in a high pitch climb (AP disengaged); airspeed is dropping close to alpha max; if you maintain the sidestick in the full aft position :

    A. Airspeed will decrease and the aircraft will stall.
    B. Airspeed will increase because of alpha floor protection.
    C. Airspeed will stabilize and the aircraft will not stall.
    C
  13. If alarm " SPEED SPEED SPEED " sounds in the cockpit :

    A. High speed protection is active.
    B. Thrust is not high enough to fly the A/C on a positive slope.
    C. You must reduce speed to idle when landing.
    B
  14. You fly your A 330 in level flight (AP disengaged) in alternate law 1 ; idle power is selected and sidestick is free :

    A. Airspeed decreases and will stabilize at VLS, and A/C will maintain flight level.
    B. A/C will pitch down to maintain speed between VSW and VLS.
    C. A/C will stall if the sidestick is not pushed forward.
    B
  15. You fly your A 330 in descent (AP disengaged) in alternate law 1 ; airspeed becomes greater than VMO/MMO :

    A. If the sidestick is held full forward, airspeed will decrease to VMO/MMO.
    B. If the sidestick is released to neutral, the A/C will pitch up automatically.
    C. If the sidestick is released to neutral, airspeed will increase unchecked.
    B
  16. If red message " MAN PITCH TRIM ONLY " appears on PFD :

    A. The A/C can be controlled using the sidesticks.
    B. The A/C can be controlled using the THS and the rudder (mechanical back up).
    C. The A/C can be controlled only by the THS.
    B
  17. When the A 330 is hand flown, on normal law, with A/THR on speed mode, high angle attack protection :

    A. Can be overriden by the pilot.
    B. Cannot be overriden by the pilot.
    C. Is not available.
    B
  18. Amber message " USE MAN PITCH TRIM " appears on PFD :

    A. The A/C is in alternate law 2.
    B. The A/C is operated in direct law, but reduced high angle of attack is available.
    C. The A/C is operated in direct law, and all flight protection are inoperative.
    C
  19. Loss of hydraulic power to one of the single spoiler servos will cause that surface to :

    A. Retract.
    B. Remain in the position at time of failure or less.
    C. Extend fully.
    B
  20. Aileron droop :

    A. Occurs when the slats and flaps are extended.
    B. Occurs when the flaps are extended and at a single droop setting.
    C. Occurs when flaps are extended with a double droop setting.
    C
  21. In case of loss of electrical power on PRIM 1, the corresponding spoiler(s) will :

    A. Retract.
    B. Fully extend.
    C. Remain in the position at time of failure or less.
    A
  22. You select FLAP 1 in TAKE OFF PERF page in the MCDU, and you select flaps 2 selector :

    A. No alarm will happen.
    B. A master caution will happen.
    C. A master caution, a single chime gong, and E/WD warnimg
    "FLAP/MCDU DISAGREE" will happen.
    C
  23. When the RAT is extended to recover hydraulic or electrical power, the servo jacks that revert to damping mode, control :

    A. The outboard ailerons.
    B. The inboard ailerons.
    C. Spoilers 1 to 5.
    A
  24. Normal pitch control uses :

    A. PRIM 1, the elevator green hydraulic jacks, and the n°1 THS electric control motor.
    B. PRIM 1, the elevator green hydraulic jacks, and the n°2 THS electric control motor.
    C. PRIM 2, the elevator blue and yellow hydraulic jacks, and the n°2 THS electric
    control motor.
    A
  25. If neither PRIM 1 or PRIM 2 are available, pitch control is transferred to :

    A. SEC 2 for elevator control and PRIM 3 using the n°2 electrical motor for THS control.
    B. SEC 1 for elevator control and PRIM 3 using the n°3 electrical motor for THS control.
    C. PRIM 3 for elevator control and SEC 2 using the n°2 electrical motor for THS control.
    B
  26. If all three PRIM computors are failed :

    A. The THS is controlled by the manual trim wheel only.
    B. The THS is controlled by the manual trim wheel and n°2 electrical motor.
    C. The THS is controlled by the manual trim wheel and n°3 electrical motor.
    A
  27. With yaw damping or turn coordination functions :

    A. You can feel the inputs with rudder pedal movement.
    B. No feedback to the rudder pedals are provided.
    C. Feedback is provided only when the A/P is off.
    B
  28. You fly your A330 in steady FL, with ADR 1 + 2 failure :

    A. Turn coordination is still available.
    B. Yaw damping is no more available.
    C. Turn coordination is still available, except in clean configuration.
    C
  29. When hydraulic failure occurs, the associated slats and flaps :

    A. Extend at half speed.
    B. Extend normally.
    C. Are jammed.
    A
  30. When retracting slats from 1 to 0 position, if A - LOCK message appears on EW/D, it means :

    A. Slats cannot retract, speed is too slow.
    B. Slats retracting normally but alarm appears to set the engines in TOGA mode .
    C. Slats cannot retract and alarm appears to set the engines in TOGA mode.
    A
  31. The sidesticks are used to :

    A. Control the A/C in pitch and roll and are spring loaded to the neutral position.
    B. Control the A/C in pitch roll and yaw and are manually returned to the neutral position.
    C. Control the A/C in pitch roll and indirectly yaw and are spring loaded
    to the neutral position.
    C
  32. The " RESET " p/b on the rudder trim control panel, when pushed :

    A. Resets the rudder trim to zero degrees.
    B. Resets the rudder trim to the value displayed on the position indicator.
    C. Resets the rudder trim to the last position prior to AP activation.
    A
  33. The use of the manual trim wheel is :

    A. Always possible.
    B. Impossible in case of total hydraulic loss.
    C. Impossible in case of total electric loss.
    B
  34. In normal operations, roll control is made by :

    A. The ailerons and spoilers 1 to 6.
    B. Spoilers 3 to 6.
    C. The ailerons and spoilers 2 to 6.
    C
  35. Which are required for Manoeuver Load Alleviation (MLA) ?

    A. The ailerons and spoilers 1 to 6.
    B. The ailerons and spoilers 3 to 6.
    C. The ailerons and spoilers 4 to 6.
    C
  36. Amber ECAM message " F/CTL FLAPS LOCKED " means :

    A. Further flap operation is not possible.
    B. Further slat and flap operation is not possible.
    C. Further slat operation is not possible.
    A
  37. Pitch control is provided by :

    A. 2 independent elevators and a trimmable horizontal stabilizer.
    B. 2 interconnected elevators and a trimmable horizontal stabilizer.
    C. 2 interconnected elevators with trim tabs and a trimmable horizontal stabilizer.
    A
  38. The ailerons are each actuated by :

    A. 2 hydraulic servos, each powered by one of two hydraulic systems.
    B. 2 hydraulic servos, each powered by one of three hydraulic systems.
    C. 3 hydraulic servos, each powered by one of two hydraulic systems.
    B
  39. The speed brakes surfaces are :

    A. Spoilers 1 to 5.
    B. Spoilers 2 to 6.
    C. Spoilers 1 to 6.
    C
  40. Each ELEVATOR servo jack has :

    A. 2 control modes :active and damping.
    B. 2 control modes :active and centering.
    C. 3 control modes :active,damping and centering.
    C
  41. ON elevators, if an active servo jack fails, the damped one becomes active. What happens to the failed jack ?

    A. It is automatically switched to damping mode.
    B. It is manually switched to damping mode.
    C. It is automatically switched to centering mode.
    A
  42. The AP function is lost in case of :

    A. PRIM 1 + 2 failure.
    B. PRIM 1 and SEC 1 + 2 failure.
    C. PRIM 1 + 2 + 3 failure.
    C
  43. Each SEC provides at least :

    A. Normal control laws and characteristics speed computations.
    B. Alternate control laws and characteristics speed computations.
    C. Direct control laws including yaw damper function.
    C
  44. If one hydraulic system is inoperative :

    A. The slats flaps are operating at half speed.
    B. The wing tip brakes (WTB) are activated and the corresponding surfaces remain at previous position.
    C. The slats flaps are normally operating.
    A
  45. Ground spoilers extension may be done :

    A. Automatically or manually.
    B. Automatically.
    C. Only if speedbrakes lever has been set to armed position.
    B
  46. The SIDE STICK PRIORITY signal is flashing green, it means :

    A. This side stick has the priority.
    B. Both side sticks are not in a neutral position.
    C. The other side stick has been " killed ".
    B
  47. Speed brakes lever has been set to " ARM " position; during an abort take off over 72 kts, to extend the speed brakes, it is necessary for the pilot to :

    A. Retard thrust levers to idle.
    B. Retard thrust levers to idle and select reverse thrust on at least one engine.
    C. Retard thrust levers to idle and apply wheel brakes.
    A
  48. The pilot forgot to set Speed brakes Lever to " ARM " position; when landing, ground spoilers will :

    A. Extend automatically at touch down.
    B. Extend when the pilot selects reverse thrust on 1 Engine (remaining other engine at idle).
    C. Not extend, no matter what the pilot does with the thrust levers.
    B
  49. In flight, with FLAP 1 configuration, in order to select FLAPS 2 :

    A. You must decrease speed below " S " speed.
    B. You must decrease speed below " = " symbol.
    C. You must decrease speed below " F " speed.
    B
  50. Today, your A 330 is very heavy, and " S " speed is above 215 kts; during initial climb, when airspeed reaches 200 kts, if you don't touch the flap handle :

    A. A flap overspeed will occur.
    B. Autothrust will prevent acceleration beyond 200 kts.
    C. Flaps will automatically retract to prevent a flap overspeed.
    C
  51. When landing, reverse thrust selected at least on 1 Engine (other thrust at idle),
    if one main landing gear is compressed :

    A. Ground spoilers will not extend.
    B. Ground spoilers will partially extend.
    C. Ground spoilers will fully extend.
    B
  52. If " RELIEF " appears blinking on the EW/D :

    A. Flaps will automatically retract to the next position because the flap load relief
    function is active.
    B. You have to retract flaps otherwise a flap overspeed will occur.
    C. You may extend flaps to the next position.
    A
  53. In flight, speed brakes cannot be detend if :

    A. Flaps are in Full position.
    B. Flaps are in Conf 3 position.
    C. Both answers are right.
    A
  54. All A330 flight controls are actuated by hydraulic servos which are controlled by computers:

    A. Or cables.
    B. But the stabilizer and rudder trim may also be controlled by cables.
    C. But the stabilizer and rudder servos may also be controlled by cables.
    C
  55. The autopilot will disconnect if the side stick takeover push button is depressed.

    A. True.
    B. False.
    A
  56. Ailerons are deflected down when flaps are:

    A. Extended.
    B. Retracted.
    A
  57. Flight control normal law provides:

    A. 3 axis control
    B. Flight envelope protection
    C. Maneuver load alleviation
    D. All of the above
    D
  58. The rudder is actuated by _____ independent hydraulic jacks which operate in parallel.

    A. Two
    B. Three
    C. Four
    D. Five including the emergency standby rudder
    B
  59. Which of the following statements is correct concerning the side stick takeover push button?

    A. The last pilot to depress the push button has priority.
    B. If a takeover push button is depressed for more than 30 seconds, the onside system will retain priority after the push button is released.
    C. Both are correct.
    A
  60. Are there any control surfaces with a mechanical backup?

    A. Yes, the ailerons.
    B. Yes, the spoilers
    C. Yes, the THS and the rudder.
    D. No, there aren't any control surfaces with mechanical backup.
    C
  61. Which of the following will automatically reset after landing?

    A. THS.
    B. Rudder trim.
    C. Both are correct.
    C
  62. The alpha speed lock function:

    A. Will inhibit flap retraction during an inadvertent movement of the flap selector at high AOA or low speeds.
    B. Will inhibit slat retraction during an inadvertent movement of the flap selector at high AOA or low speeds.
    C. Automatically raises the flaps if retraction has not been accomplished by 210kts.
    B
  63. In normal law, if one stick is rapidly pulled fully back, can the aircraft's maximum allowable 'G' load be exceeded?

    A. Yes. Rapid side stick deflection must never be made.
    B. Yes, until maximum pitch attitude is reached.
    C. No. At Maximum 'G' load, the side sticks are de-activated for 5 seconds.
    D. No. The load factor limitation overrides side stick commands to avoid excessive 'G' loads.
    D
  64. Each aileron hydraulic servojack has two control modes: active and damping.

    A. True.
    B. False.
    A
  65. Which controls are used for the mechanical backup?

    A. Ailerons and rudder.
    B. THS and rudder.
    C. Elevators and ailerons.
    D. THS and elevator.
    B
  66. Mechanically backed-up control surfaces:

    A. Require hydraulic power for actuation.
    B. Are mechanically connected to the cockpit controls.
    C. Both are correct.
    A
  67. Selection of flaps one prior to takeoff will select which of the following?

    A. Slats 1 and flaps 1 (1+F).
    B. Slats 0 and flaps 1 (0+F).
    C. Slats 1 and flaps 0 (1).
    D. Slats 1 and flaps 5 (1).
    A
  68. Which of the following statements best describes the Maneuver Load Alleviation function (MLA)?

    A. Helps the pilot control the airplane.
    B. Relieves wing structure loads by deflecting the ailerons and spoilers.
    C. Relieve wing structure loads by deflecting only the spoilers.
    D. Relieves wing structure loads by deflecting the ailerons.
    B
  69. When ground spoilers deploy automatically:

    A. All ten spoilers panels fully deploy.
    B. Four spoilers panels on each wing deploy.
    C. All ten spoilers panels deploy half way.
    D. Six spoilers panels on each wing deploy.
    D
  70. The slats alpha / speed lock function inhibits slats retraction at high angle-of-attack and/or low speed.

    A. True.
    B. False.
    A
  71. Each SEC provides at least:

    A. Direct control law, rudder trim, yaw damper, rudder and rudder pedals travel limits.
    B. Direct control law, speed brake and ground spoiler control logic.
    C. Alternate control laws, characteristic speed computations.
    A
  72. Which altitude limitation is associated with high lift devices?

    A. Max altitude for extension is 20, 000 ft.
    B. Max altitude for extension is 22, 000 ft.
    C. Max altitude for extension is 25, 000 ft
    D. Max altitude for extension is 27, 000 ft.
    A
  73. The message WING TIP BRK ON appears on the E/WD. What does it mean?

    A. A hydraulic device locks the flaps in their present position.
    B. To reduce structural stress, the slats movement is being slowed down through the wing tip brakes.
    C. To avoid asymmetry, the outer slats are locked in their present position.
    D. Because of the locked flaps, the wing tip brakes also lock the slats.
    A
  74. Where does the SFCCs obtain AOA and air data information from?

    A. SEC
    B. ELAC
    C. ADIRU
    D. ADC
    C
  75. The wing tip brakes, once activated:

    A. Lock both the slats and flaps in their current position
    B. Lock only the flaps in their current position.
    C. Lock only the slats in their current position.
    D. Lock only the affected high lift system surfaces in their current position
    D
  76. Which of the following controls and monitors flaps and slats?

    A. Two Flight Control Primary Computer PRIM's.
    B. Wing tip brakes.
    C. One slat flap control computer (SFCC).
    D. Two slat flap control computers (SFCC's).
    D
  77. The spoiler panels are the only flight control surfaces with no redundant control.

    A. True.
    B. False.
    A
  78. What happens in the side stick-neutral high speed protection mode?

    A. The autopilot disengages, bank angle limit is 30° and the aircraft is 25° roll limited.
    B. The autopilot disengages, bank angle limit is 45° and the aircraft is 25° roll limited.
    C. The autopilot disengages, bank angle limit is 45° and the aircraft rolls wings level and pitches up to slow down to VMO/MMO.
    D. The autopilot disengages, bank angle limit is 35° and the aircraft rolls wings level and pitches to 10° to slow down to VMO/MMO - 20 kt.
    C
  79. Can the crew make a flight control input that will over-stress the airplane in direct law?

    A. No. The system is designed to avoid such an attempt.
    B. Yes, there are no protections provided in direct law.
    B
  80. The stabilizer is actuated by a screw jack driven by two hydraulic motors, which in turn are controlled by:

    A. One of three electric motors
    B. A mechanical trim wheel
    C. Both are correct.
    C
  81. Can you manually trim the rudder with the autopilot engaged?

    A. Yes.
    B. No.
    B
  82. When is the Flight Mode active?

    A. From takeoff until landing.
    B. From liftoff when passing 100 ft RA until flare mode engages at 50 ft RA.
    C. From liftoff when passing 50 ft RA until flare mode engages at 100 ft RA.
    D. From takeoff until passing 50 kt on landing (main shock absorbers depressed)
    C
  83. OVERSPEED ECAM warning is provided at:

    A. VMO and MMO.
    B. VMO + 4kt. and MMO + 0.006
    C. VMO + 15kt. and MMO + 0.04
    D. None of the above.
    B
  84. Automatic pitch trim is provided both on ground and in flight.

    A. True.
    B. False.
    B
  85. The Ground Mode is different in Alternate Law.

    A. True.
    B. False.
    B
  86. In normal law, what is the maximum bank angle you can reach with the side stick fully deflected?

    A. 33°
    B. 49°
    C. 67°
    D. 70°
    C
  87. Failure to retract the flaps after takeoff will:

    A. Activate the wing tip brakes.
    B. Result in automatic flap and slat retraction.
    C. Result in automatic flap retraction.
    C
  88. MLA (maneuver load alleviation) becomes active when side stick is pulled less than 8 degrees and the load factor is more than 2 g.

    A. True
    B. False.
    A
  89. SFCC generated slat and flap extension, retraction, and limiting speeds are visually displayed on which of the following?

    A. The MCDU perf page.
    B. The lower ECAM F/CTL page.
    C. Both pilot's PFD airspeed displays.
    D. All of the above.
    C
  90. The wing tip brakes are:

    A. Pneumatically actuated.
    B. Electric brakes.
    C. Hydraulically actuated.
    D. Mechanically controlled, hydraulically actuated.
    C
  91. Selection of flaps 1 in flight will select which of the following configurations?

    A. Slats 1 and flaps 1 (1+F).
    B. Slats 0 and flaps 1 (0+F).
    C. Slats 1 and flaps 0 (1).
    D. Slats 1 and flaps 5 (1+F).
    C
  92. The aircraft rudder can be manually trimmed with the autopilot engaged.

    A. True.
    B. False.
    B
  93. What happens if you release the stick at 40 degrees of bank?

    A. The bank stays at 40°
    B. The aircraft rolls back to 25°
    C. The aircraft rolls back to 33° and resumes flight path stability.
    D. The aircraft rolls back to a bank angle less than 29°
    C
  94. The elevators are ______ controlled.

    A. Mechanically.
    B. Electrically.
    B
  95. When is alpha floor not available?

    A. Out of normal law.
    B. Below 100 feet RA in landing configuration.
    C. If the A/THR is deactivated or unavailable.
    D. All of the above.
    D
  96. What kinds of protections are provided if the aircraft is in Alternate Law?

    A. G-load protection with a reduced factor.
    B. Speed Stability
    C. Full G load protection and speed stability
    D. G-load protection and speed stability if the ADIRS and elevators are working.
    D
  97. In Normal Law, what are the limits of Pitch Attitude protections with flaps Full

    A. 30° nose up.
    B. 30° nose up progressively reduced to 25°
    C. 25° nose up.
    D. There is no limit.
    C
  98. The rudder trim rotary switch is not active when autopilot is engaged.

    A. True
    B. False.
    A
  99. You can degrade directly from Normal Law to Direct Law with gear down and a dual radio altimeter fault.

    A. True.
    B. False.
    A
  100. Turn coordination is available in Alternate Law.

    A. True.
    B. False.
    B
  101. If both pilots deflect their side sticks fully back:

    A. The 'pitch up' order is twice as high as with only one stick deflected.
    B. The 'pitch up' order is 1.5 times higher as high as with only one stick deflected.
    C. No inputs are sent to the flight control computers unless one pilot presses the takeover pushbutton on his stick.
    D. The 'pitch up' order is equal to a single stick deflection.
    D
  102. To disable a side-stick, you have to depress the red take-over button on the active stick. Holding the button down for 40 seconds will electrically lock the other stick out until its own red take-over button is pushed again.

    A. True.
    B. False.
    A
  103. Let's assume the F/O presses his takeover pushbutton and releases it after more than 40 seconds.

    A. The Captain's side stick is de-activated unless he presses his takeover pushbutton.
    B. The Captain is unable to re-activate his side-stick for the rest of the flight
    C. Both sticks are active
    D. The Captain's side stick is active as long as the F/O's side stick is in neutral position.
    A
  104. The speed brakes are _____ controlled.

    A. Electrically
    B. Mechanically
    A
  105. Ailerons max deflection is:

    A. 15 degrees.
    B. 25 degrees.
    C. 35 degrees.
    D. 39 degrees.
    B
  106. What happens to the rudder limits if both SEC's fault?

    A. The limit freezes at the fault condition until Flaps 1 is selected.
    B. The limit freezes at the fault condition until Flaps 5 is selected.
    C. The limit freezes at the fault condition until Flaps 1 is selected. Then it resets to the low speed limits for increased control.
    C
  107. What happens to high speed (VMO/MMO) when you are in Alternate Law?

    A. VMO is reduced to 320 kt and MMO minus 10 kt.
    B. VMO is reduced to 330 kt and MMO minus 10 kt.
    C. VMO is reduced to 320 kt and MMO does not change.
    D. There is no change.
    C
  108. If all three PRIM computers are not available with B or Y hydraulic system available:

    A. The THS is controlled by the manual pitch trim wheel only.
    B. The THS is controlled by the manual pitch trim wheel and the number 2 electric motor.
    C. The THS is controlled by the manual pitch trim wheel and the number 3 electric motor.
    A
  109. In flight, spoilers max deflection is:

    A. 25° max for spoilers 1 to 6.
    B. 30° max for spoilers 2 to 6.
    C. 35° max for spoilers 1 to 6.
    D. 50° max for spoilers 2 to 6.
    C
  110. The FLAP lever sends signal to Slat Flap Control Computer (SFCC) to command movement.

    A. True.
    B. False.
    A
  111. When the RAT is extended to recover hydraulic pressure or electrical power, the servo jacks that revert to damping mode control:

    A. The outboard ailerons.
    B. The inboard ailerons.
    A
  112. The speedbrake surfaces are:

    A. Spoilers 2 to 4.
    B. Spoilers 2 to 5.
    C. Spoilers 1 to 6.
    C
  113. The autopilot function is lost in case of:

    A. PRIM 1+2 failure with SEC 1+2 available
    B. PRIM 1and SEC 1+2 available
    C. PRIM 1+2+3 failure with SEC 1+2 available
    C
  114. Each PRIM provides:

    A. Normal control law and characteristic speed computations only.
    B. Normal, alternate and direct laws, speed brake and ground spoiler control logic, characteristic speed computations.
    C. Normal and alternate laws only, speed brake and ground spoiler control logic.
    B
  115. For elevators control, each servo jack has:

    A. 2 control modes: Active and Damping.
    B. 2 control modes: Active and Centering.
    C. 3 control modes: Active, Damping and Centering.
    C
  116. When you set rudder trim, the input:

    A. Is fed back to the rudder pedals.
    B. Is not fed back to the rudder pedals.
    C. Is fed back to the rudder pedals only when you push reset.
    A
  117. Loss of hydraulic power to one of the single spoiler servos will cause that surface to:

    A. Retract.
    B. Remain at the existing deflection or less if pushed down by aerodynamic forces.
    C. Extend fully.
    B

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