1. Which statement is true regarding the Ailerons ?
    1.   Hydraulic Systems A and B power the ailerons with Standby System backup.
    2.   Hydraulic Systems A and B power the ailerons with manual backup.
    3.   Hydraulic Systems A or B power the ailerons with automatic backup from the operating system.
    4.   Hydraulic System A powers the ailerons with backup from System B.
  2. Which statement is true regarding the Elevator ?
    1.   Hydraulic Systems A and B power the elevator with manual backup.
    2.   Hydraulic Systems A and B power the elevator with Standby System backup.
    3.   Hydraulic Systems A or B power the elevator with automatic backup from the operating system.
    4.   Hydraulic System B powers the elevator with backup from System A.
  3. Which statement is true regarding the Rudder ?
    1.   Hydraulic Systems A and B power the rudder with Standby System backup.
    2.   Hydraulic Systems A and B power the rudder with manual backup.
    3.   Hydraulic Systems A or B power the rudder with automatic backup from the operating system.
    4.   Hydraulic System B powers the rudder with backup from System A and the Standby System.
  4. How is the aircraft trimmed in pitch ?
    1.   By means of an electric trim motor or manual trim wheel which sets the Horizontal Stabilizer.
    2.   By means of an electric trim motor or manual trim wheel which set the elevator trim tabs.
    3.   By means of a hydraulic trim motor or manual trim wheel which sets the Horizontal Stabilizer.
  5. Which statement is true regarding the Flight Spoilers ?
    1.   There are four flight spoilers on each wing used for roll control and speed brakes.
    2.   There are six flight spoilers on each wing used for roll control and speed brakes.
    3.   There are four flight spoilers on each wing used for roll control only.
    4.   There are four flight spoilers on each wing used for roll control only and two spoilers used for speed brakes.
  6. Which hydraulic system(s) power the Flight Spoilers ?
    1.   System A and B power two symmetrical flight spoilers on each wing.
    2.   System A powers the flight spoilers on the left wing and System B powers the flight spoilers on the right wing.
    3.   Either System A or System B power all the flight spoilers on each wing.
    4.   System A with backup from the Standby System.
  7. Which control column DIRECTLY actuates the Ailerons ?
    1.   Captain's control column.
    2.   First Officer's control column.
    3.   Either Captain's control column or First Officer's control column.
    4.   Both Captain's control column and First Officer's control column.
  8. Which control column DIRECTLY actuates the Flight Spoilers ?
    1.   First Officer's control column.
    2.   Captain's control column.
    3.   Either Captain's control column or First Officer's control column.
    4.   Both Captain's control column and First Officer's control column.
  9. With a loss of both System A and System B, how is the aircraft controlled in roll ?
    1.   The ailerons and flight spoilers are manually controlled by cables.
    2.   The ailerons are manually controlled by cables and the flight spoilers are inoperative.
    3.   The ailerons are manually controlled by cables and the flight spoilers are powered by the Standby System.
    4.   The ailerons and the flight spoilers are powered by the Standby System.
  10. With a loss of both System A and System B, how is the aircraft controlled in pitch ?
    1.   The Elevator is manually controlled by cables.
    2.   The Elevator is powered by the Standby System.
    3.   The aircraft is controlled in pitch with the Horizontal Stabilizer trim motor only.
  11. What immediate crew action is required If the FFM ( Force Flight Monitor) detects opposing pressure between System A and System B ?
    1.   None, the Standby System is automatically activated and the Standby Rudder shutoff valve opens.
    2.   The crew must manually position both FLT CONTROL switches to SBY RUD.
    3.   The crew must monitor the FEEL DIF PRESS warning light and switch either A or B FLT CONTROL switch to SBY RUD if necessary.
  12. What indication(s) are activated if the FFM (Force Flight Monitor) senses opposing pressure in System A and System B ?
    1.   The STBY RUD ON warning light.
    2.   The STBY RUD ON warning light, Master Caution light and FLT CONT annunciator.
    3.   The FEEL DIFF PRESSURE warning light.
    4.   The FEEL DIFF PRESSURE warning light, Master Caution light and FLT CONT annunciator.
  13. Which flight control is associated with the FEEL DIF PRESSURE warning light ?
    1.   Elevator
    2.   Rudder
    3.   Ailerons
    4.   Flight Spoilers
  14. How is the rudder trimmed ?
    1.   By electrically repositioning the Rudder Feel and Centering Unit with the Rudder Trim.
    2.   By electrically positioning the Rudder Trim Tab with the Rudder Trim.
    3.   By electrically positioning the Rudder Pedals with the Rudder Trim.
  15. How may the crew determine the amount of rudder trim that has been selected ?
    1.   Displacement of the rudder pedals.
    2.   Displacement of the rudder pedals and Rudder Trim Indicator.
    3.   Displacement of the Rudder Trim Indicator.
  16. Which hydraulic system powers the Main Yaw Damper ?
    1.   System A.
    2.   System B.
    3.   System A and B.
    4.   System A or B.
  17. Under which condition(s) can the Yaw Damper switch NOT be positioned to ON ?
    1.   The SMYD ( Stall Management Yaw Damper) computer has sensed a fault.
    2.   The SMYD ( Stall Management Yaw Damper) computer senses that the yaw damper is not responding to a command.
    3.   The B FLT CONTROL switch is positioned to OFF or STBY RUD.
    4.   Any of the three conditions named.
  18. With a loss of System A and System B (Manual Reversion), which statement is true regarding the Rudder.
    1.   Rudder assist is available when moving the ailerons through the Standby Yaw Damper.
    2.   The Yaw Damper system is not available.
    3.   Rudder trim is unavailable.
  19. Which statement is true with regard to the stabilizer trim motor ?
    1.   The motor operates at a higher speed when flaps are extended.
    2.   The motor operates at a lower speed when flaps are extended.
    3.   Flap setting has no effect on stabilizer trim motor operation.
  20. Moving the Stabilizer Trim AUTOPILOT cutout switch located on the Control Stand to CUT OUT will disconnect the autopilot, if engaged.
    1.   True
    2.   False
  21. What will occur when moving a control column in opposition to the stabilizer trim motor direction ?
    1.   The stabilizer trim motor will stop if the autopilot is providing inputs to the motor.
    2.   The stabilizer trim motor will stop regardless of input source.
    3.   The stabilizer trim motor will stop if the control column trim switches are providing inputs to the motor.
  22. Moving a control column in opposition to the stabilizer trim motor direction will stop the stabilizer trim motor unless ?
    1.   The STAB TRIM switch on the Aft Electronic Panel is switched to OVERRIDE.
    2.   The autopilot is providing inputs to the stabilizer trim motor.
    3.   The control column trim switches are providing inputs to the stabilizer trim motor.
  23. The stabilizer trim motor may be stopped by firmly holding either manual trim wheel and preventing it from moving.
    1.   True
    2.   False
  24. May the stabilizer trim setting be moved out of the range of the green band ?
    1.   No.
    2.   Yes, by using the control column actuated trim switches.
    3.   Yes, by using the manual trim wheels.
  25. Movement of the trim wheels when the autopilot is not engaged or the control column trim switches are not being activated indicates ?
    1.   Activation of the Speed Trim System (STS).
    2.   A runaway stabilizer.
    3.   A fault in the stabilizer trim system.
  26. What is the crew's indication if a fault exists in the Speed Trim System (STS) ?
    1.   The SPEED TRIM FAIL light illuminates.
    2.   The SPEED TRIM FAIL light, Master Caution and FLT CONT annunciator illuminate.
    3.   The stabilizer trim wheels do not rotate when the control column trim switch is activated.
  27. When moving a FLT CONTROL switch to STBY RUD the associated LOW PRESSURE light is deactivated.
    1.   True
    2.   False
  28. When is the Standby System LOW PRESSURE light activated ?
    1.   If low hydraulic pressure exists in the Standby System at any time.
    2.   If low hydraulic pressure exists in the Standby System and the standby pump has been activated.
    3.   If the Standby System reservoir is low on fluid.
  29. Which flight control is NOT associated with the Flight Control System A or B LOW PRESSURE warning light.
    1.   Ailerons
    2.   Elevator
    3.   Rudder
    4.   Flight Spoilers
  30. How are the leading edge devices extended during alternate flap extension ?
    1.   By momentarily positioning the Alternate Flaps position switch to DOWN using Standby hydraulic pressure.
    2.   By momentarily positioning the Alternate Flaps position switch to DOWN using System A hydraulic pressure.
    3.   Electrically by positioning the Alternate Flaps position switch to DOWN.
    4.   Leading edge devices are not available when using the Alternate Flap extension system.
  31. How are the leading edge devices retracted when using the Alternate Flap extension system ?
    1.   Electrically by positioning the Alternate Flaps position switch to UP.
    2.   By momentarily positioning the Alternate Flaps position switch to UP using Standby hydraulic pressure.
    3.   Leading edge devices cannot be retracted once they are extended by using the Alternate Flap extension system.
  32. Does the Alternate Flap extension system provide protection for asymmetric flaps or skew ?
    1.   No
    2.   Yes
  33. Two pitot tubes mounted on the vertical stabilizer provide input for ?
    1.   The Mach Trim System.
    2.   The Speed Trim System.
    3.   The Elevator Feel System.
    4.   The Standby Airspeed Indicator.
  34. Will the FEEL DIFF PRESS light illuminate with a loss of System A or B ?
    1.   No, the light is disarmed with a loss of System A or B.
    2.   Yes, the light is always armed.
  35. Which Flight Control system is activated if the aircraft approaches a stall condition ?
    1.   Autoslats.
    2.   Speed Trim System.
    3.   Mach Trim System.
  36. Is the Autoslat system dependent on trailing flap position ?
    1.   No, Autoslats will activate regardless of trailing edge flap position.
    2.   Yes, Autoslats will only activate at trailing edge flaps 1, 2 and 5.
    3.   Yes, Autoslats will only activate if the trailing edge flaps are retracted.
  37. The AUTO SLAT FAIL light illuminated indicates ?
    1.   Failure of the Autoslat system when approaching a stall.
    2.   A fault in the Autoslat system or failure of one or both Stall Management Computers (SMYD).
    3.   A fault in the Autoslat system.
  38. Which hydraulic system powers the Trailing Edge Flaps ?
    1.   System A.
    2.   System B
    3.   System A or B.
    4.   System B and the Standby System.
  39. What is the maximum allowable airspeed for use of the Alternate Flap extension system ?
    1.   230 Knots.
    2.   210 Knots.
    3.   250 Knots.
    4.   200 Knots.
  40. How is a trailing edge flap skew or asymmetry indicated to the crew ?
    1.   A split in the left and right Trailing Edge Flap indicator pointers.
    2.   The Master Caution light and FLT CONT annunciator.
    3.   One or more illuminated indicators in the LE Devices panel on the Aft Overhead.
  41. Trailing edge flap skew and asymmetry protection is provided by ?
    1.   The Flaps / Slat Electronics Unit (FSEU).
    2.   The Flap Load Relief system.
    3.   The Trailing Edge Flap Indicator.
  42. Are the Leading Edge Flaps protected for asymmetry and skew ?
    1.   No
    2.   Yes
  43. Flap load relief as provided by the FSEU (Flap / Slat Electronic Unit) is provided at trailing edge flap settings of ?
    1.   Flaps 15, 25, 30, 40
    2.   Flaps 30, 40
    3.   Flaps 25, 30, 40
    4.   Flaps 40
  44. Uncommanded trailing edge flap motion protection as provided by the FSEU (Flap / Slat Electronic Unit) protects against ?
    1.   Movement away from the commanded position.
    2.   Continued movement beyond a commanded position.
    3.   Movement in a direction opposite to the commanded position.
    4.   All three of the conditions named.
  45. If flap load relief is activated by the FSEU (Flap / Slat Electronic Unit) what will occur ?
    1.   The flaps will not extend to the selected position.
    2.   The flaps will retract to the next lower position from the selected setting.
    3.   The flaps will retract to a setting that corresponds to maximum allowable setting for the existing airspeed.
  46. What is the crew's indication that flap load relief has been activated by the FSEU (Flap / Slat Electronic Unit) ?
    1.   No indication to the crew is available.
    2.   The Flap Position Indicator will show pointer movement.
    3.   The Master Caution and FLT CONT annunciator illuminate until the condition is corrected.
  47. After flap load relief activation by the FSEU (Flap / Slat Electronic Unit), the trailing edge flaps will re-extend to the selected position when the excessive air load condition no longer exists.
    1.   True
    2.   False
  48. Which indication would be correct if the FSEU (Flap / Slat Electronic Unit) has detected a Trailing Edge Flap asymmetry condition ?
    1.   The Flap Indicator pointers are split.
    2.   The Flap Indicator pointers disagree with the Flap Lever position.
  49. Which indication would be correct if the FSEU (Flap / Slat Electronic Unit) has detected Trailing Edge Flap uncommanded motion ?
    1.   The Flap Indicator pointers are split.
    2.   The Flap Indicator pointers disagree with the Flap Lever position.
  50. If the FSEU (Flap / Slat Electronic Unit) has detected uncommanded motion at a flap setting less than flaps 15, are trailing edge flaps available for landing ?
    1.   No, this condition prevents flaps from being used because the Trailing Edge Flap Bypass Valve has been closed by the FSEU.
    2.   The Alternate Flap extension system may be used if this condition exists.
  51. What is the position of the Leading Edge Flaps when the Trailing Edge Flaps are in the 1, 2 or 5 position ?
    1.   Extend
    2.   Full Extend
    3.   Up
  52. What is the position of the Leading Edge Slats when the Trailing Edge Flaps are in the 1, 2 or 5 position ?
    1.   Extend
    2.   Full Extend
    3.   Up
  53. At what Trailing Edge Flap position will the Leading Edge Slats move to the full extend position ?
    1.   Greater than Flaps 5.
    2.   Greater than Flaps 10.
    3.   Greater than Flaps 15.
  54. During Autoslat operation, which leading edge devices are extended ?
    1.   The Leading Edge Flaps.
    2.   The Leading Edge Flaps and Slats.
    3.   The Leading Edge Slats.
  55. Which warnings are available if a Leading Edge Slat skew or asymmetry condition exists ?
    1.   The Master Caution and FLT CONT annunciator will illuminate.
    2.   The LE FLAPS TRANSIT warning light will remain on.
    3.   The Master Caution and FLT CONT annunciator will illuminate and the LE FLAPS TRANSIT warning light will remain on.
  56. Are all Leading Edge Devices protected for asymmetry and skew ?
    1.   Yes.
    2.   No, only the Leading Edge Slats are protected.
    3.   No, only the Leading Edge Flaps are protected.
    4.   No, only Leading Edge Slats 2 through 7are protected.
  57. Are all leading edge devices protected for uncommanded motion ?
    1.   Yes.
    2.   No, only the Leading Edge Slats are protected.
    3.   No, only the Leading Edge Flaps are protected.
  58. If the LE FLAPS TRANSIT light on the Center Forward panel illuminates and no Trailing Edge flaps have been selected, what condition exists ?
    1.   Uncommanded motion of a Leading Edge Device.
    2.   An asymmetry or skew condition exists.
    3.   The Autoslat function has been activated.
  59. What protection is provided to prevent uncommanded motion of the Leading Edge Devices during cruise ?
    1.   Positive hydraulic pressure on the retract lines and depressurization of the extend and full extend lines.
    2.   Depressurization of the extend and full extend lines.
    3.   Positive hydraulic pressure on the retract lines.
    4.   Mechanical uplocks.
  60. Which hydraulic systems power the Leading Edge Devices ?
    1.   System A with backup from the Standby System through the Alternate Flap Position switch.
    2.   System B with backup from the Standby System through the Alternate Flap Position switch.
    3.   System A and B.
    4.   System A or B.
  61. Which answer best describes the Power Transfer Unit ?
    1.   The PTU uses system A fluid to power the PTU for Autoslats and LE Device operation if System B engine hydraulic pump volume is lost.
    2.   The PTU uses system B fluid to power the PTU for Autoslats and LE Device operation if System A engine hydraulic pump volume is lost.
    3.   The PTU uses system B pressure to power the PTU for Autoslats and LE Device operation if System A pressure is lost.
    4.   The PTU uses system A pressure to power the PTU for Autoslats and LE Device operation if System B pressure is lost.
  62. How many ground spoiler panels are located on each wing ?
    1.   One
    2.   Two
    3.   Four
    4.   Six
  63. Which hydraulic system powers the Ground Spoilers ?
    1.   System B.
    2.   System A.
    3.   System A and System B.
    4.   System A or System B.
  64. How many panels are extended on each wing during ground spoiler operation ?
    1.   Two
    2.   Four
    3.   Six
    4.   One
  65. May the Flight Spoilers be extended beyond the FLIGHT DETENT while airborne ?
    1.   No, it is prohibited.
    2.   Yes, however buffeting may occur.
  66. Is manual Speed Brake deployment possible before touchdown ?
    1.   Yes, with a radio altitude of less than 10 feet RA.
    2.   No, landing gear strut compression is required.
    3.   No, main landing gear wheel spinup greater than 60 knots is required.
  67. Will the Speed Brakes automatically deploy during a rejected takeoff if the Speed Brake Lever is in the DOWN Detent ?
    1.   Yes, above 60 knots wheel speed.
    2.   Yes, if the thrust levers are retarded to idle.
    3.   No, the Speed Brakes must manually deployed during a rejected takeoff.
    4.   Yes, above 60 knots wheel speed, thrust levers idle and reverse thrust applied.
  68. If forward thrust is applied after the Speed Brakes have automatically deployed on landing, which answer is correct ?
    1.   All spoiler panels retract and the Speed Brake lever moves to the DOWN detent.
    2.   All spoiler panels retract.
    3.   The Speed Brake handle must be manually positioned to the DOWN detent.
    4.   Forward thrust cannot not be applied after the Speed Brakes are deployed.
  69. If the Speed Brakes are deployed when the aircraft is in the landing configuration, which warning indication(s) activate(s) ?
    1.   The SPEEDBRAKES EXTENDED warning on the Right Forward (FO) panel illuminates.
    2.   The Master Caution, FLT CONT annunciator and the SPEEDBRAKES EXTENDED warning on the Right Forward (FO) panel illuminates.
    3.   The SPEED BRAKE ARMED warning on the Left Forward (CA) panel illuminates.
    4.   The SPEED BRAKE DO NOT ARM warning on the Left Forward (CA) panel illuminates.
  70. The SPEEDBRAKE EXTENDED warning light illuminated on the ground with the Speed Brake lever in the DOWN detent indicates ?
    1.   Hydraulic pressure is sensed in the Ground Spoiler shutoff valve.
    2.   The Speed Brakes are in disagreement with the Speed Brake lever.
    3.   A fault exists in the automatic Speed Brake system.
    4.   The automatic Speed Brake system has armed on the ground.