SO1115 - Hydraulics.txt

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SO1115 - Hydraulics.txt
2013-11-19 20:37:14

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  1. Why does the T-38C aircraft have two hydraulic reservoirs
    To allow for two independent hydraulic systems
  2. What are the minimum, normal range, and maximum hydraulic system pressure limitations
    • 1500
    • 2850-3200
    • 3200
  3. When will the hydraulic caution light illuminate
    The hydraulic caution light illuminates when there is a hydraulic overtemp and hydraulic low pressure. It will NOT illuminate for an overpressure, but an overpressure will often lead to an overtemp
  4. Can you maneuver the T-38C with the left engine frozen and the right gearbox failed
    No, immediate ejection is recommended. A frozen engine produces no hydraulic pressure along with a gear box fail. With no pressure, you get not control
  5. Which of the following statements about the airframe mounted gearbox are true
    When you lose the airframe mounted gearbox, you lose the generator and the hydraulic pump. A gearbox fail to shift does not affect the hydraulics on that side
  6. If the left airframe mounted gearbox shaft shears
    the gear must be lowered with the alternate system
  7. With 0 hydraulic pressure will you have control of the primary flight controls
  8. The flight control hydarulic system is which side and controls what
    Right, ailerons, rudder, horizontal stabilizer
  9. The utility hydraulic system is which side and controls what
    • Left
    • flight controls
    • landing gear
    • NWS
    • stability augmentor
    • speed brake
  10. With both hydraulic systems inop, can you move the flight controls
  11. What are the main components of each hydraulic system?
    • Reservoir
    • Pump
    • indicating and warning system
  12. Where are the hydraulic reservoirs mounted in the engine bay
    above the hydraulic pumps
  13. How are the hydraulic reservoirs pressurized?
    bleed air from the engine
  14. The hydraulic pump is driven by what?
    By the engine through the airframe mounted gearbox
  15. When the airframe mounted gearbox fails to shift, how does this affect the hydraulic system?
    No effect, the hydraulic pump compensates for both low and high engine speeds
  16. How is the hydraulic pressure indicating system powered?
    AC for each respective side
  17. After the MASTER CAUTION and the respective hydraulic light illuminate, when will both lights extinguish?
    When hydraulic pressure rises above 1800psi
  18. What distinguishes a hydraulic overtemp vs low pressure indications?
    Both will give MASTER CAUTION and respective hydraulic light but overtemp will indicate normal hydraulic pressure
  19. If caution light illuminate due to hydraulic overtemp, when will the lights extinguish?
    when the hydraulic temp drops below the high-temperature point (the temp at which the lights went on)
  20. Will a leak in one hydraulic system affect the other?
  21. With a leak in a hydraulic system, the hydraulic pressure ___ with control movements and eventually ___.
    fluctuates wildly, drops to zero
  22. With Low hydraulic pressure avoid ___ and then ___
    avoid zero and negative-G flight, land as soon as possible
  23. What can cause zero hydraulic pressure?
    engine seizure and airframe mounted gearbox failure
  24. With zero hydraulics, land as soon as ___.
    land as soon as possible
  25. What can cause high hydraulic pressure?
    faulty pressure regulator or a line restriction
  26. What can cause high hydraulic temp?
    • continued operation at high hydraulic pressure
    • engine fire
    • hydraulic pump malfunction
  27. Continued operation with high hydraulic temp will affect the flight controls how?
    eventually flight controls will get sluggish and may bind
  28. Indication of airframe mounted gearbox failure
    Both genertor and hydraulic light illumination on a side
  29. With a rudder system failure, the rudder may defelect a full __ degrees
  30. With a rudder system failure, the rudder will reach the full 30 degree position in __ to __ seconds
  31. Indications of rudder system failure
    increasing yaw followed by a violent roll and departure from controlled flight
  32. Can the aircraft be controlled with a rudder system failure?
    only for the first two seconds, but the 30 degree deflection will lead to an accelerated stall and become completely uncontrollable
  33. If rudder system failure in flight occurs, what actions are taken?
    immediate ejection
  34. If rudder system failure is suspected on takeoff roll, what actions are taken?
    high speed abort or ejection
  35. What is the difference between Rudder system malfunction and flap and aileron malfunction?
    Aircraft is controllable with flap or aileron malfunction
  36. With a stability augmentor malfunction, the rudder can move a maximum of _ degrees in as little as _seconds
    4, 0.25
  37. If in highspeed and high AOA a stability augmentor malfuntion can cause ___
    an abrupt uncommanded roll
  38. If a stability augmentor malfuction occurs, what action is taken?
    turn the stab-aug system OFF
  39. If turning the stability augmentor system off due to a malfunction, can you continue your mission?
  40. If the yaw damper switch disengages in flight, can you turn it back on?
  41. if you reset the yaw damper and it immediately disengages but rudder response is normal, can you continue your mission?
    yes, but write it up
  42. Indications of rudder system failure vs a stability augmentor failure
    with a stab-aug failure the rudder can still be moved and the aircraft is still easily controlled
  43. What provides the artificial feel for the flight control system?
    System of springs for aileron/rudder and a bobweight for the stabilizer
  44. Describe the flight control system path from control stick to flight controls
    Movement of the control stick/rudder pedals actuates a cable system which in turn operates hydraulic servo valves of actuating cylinders for each flight control surface
  45. How are the flight control servo valves' operation
    Pressurized hydraulic fluid flows to the actuated valve to the appropriate side of the cylinder, which operates the control surface
  46. What electrical system operates the trim?
    Right AC
  47. When the trim system is actuated, what actually happens?
    Electric motors move the control stick position relative to the artificial feel springs which in turn moves the flight controls hydraulically
  48. Which hydraulic system(s) to aileron and stabilizer trim use?
    Utility and flight
  49. What two things can move stabilizer trim?
    Stick trim button and takeoff trim button
  50. What does it mean when the takeoff trim light is green?
    The stabilizer is correctly trimmed for takeoff
  51. What is the range of movement for the rudder using rudder trim?
  52. What must be on for the rudder trim to operate?
    Stab-aug system
  53. What must be on for the stab-aug system to operate?
    Both EGI and yaw damper must be on
  54. What directly activates the stability augmentation system (SAS)?
    EGI switch
  55. What type of power does yaw damper require and what hydraulic system does it use?
    left AC and utility
  56. What hydrualic/electrical power does the speed brake use?
  57. How can you get intermediate speed brake positions?
    Momentarily placing either switch in the desired position and returning the switch to OFF
  58. What position must the speed brake switch be in to allow it to "creep" up with airload pressure?
  59. Which speedbrake switch has priority?
  60. What would cause the speed brake to freeze in position?
    DC electrical failure
  61. What hydraulic/electrical power does NWS use?
  62. What 2 things must happen for NWS to work?
    Weight on nosegear, NWS button depressed
  63. What happens when you release the NWS button?
    Nosewheel returns to center
  64. Utility hydraulics memory acronym
    FANGS - Flight controls, Augmenter (SAS), NWS, Gear, SB
  65. Landing gear hydraulic/electrical power?
  66. Why do we open gear doors on after landing checklist?
    Allows for preflight/postflight inspection of the gear well area
  67. What are the 2 times you would use thelanding gear alternate release handle?
    DC electrical or utility hydraulic failure
  68. How does the landing gear alternate release handle work?
    disengages electrical/hydraulics and allows gravity/airstream to bring the gear down
  69. In what position must the landing gear handle be in for the alternate release handle to work?
    Either position
  70. What becomes unavailable if alternate gear extension is used?
  71. The mechanical linkage rudder limiter system restricts rudder deflection to what when the nose gear is extended 3/4 or less?
  72. The mechanical linkage rudder limiter system restricts rudder deflection to what when the nose gear is extended greater than 3/4?
  73. What three conditions cause the gear warning (HUD, red light, aural tone) to go off when the gear is up?
    210 KCAS or less, 10,000 feet or below, both throttles below 96%
  74. When the gear handle is up, what does a red light in the handle indicate?
    gear doors not up and locked
  75. When the gear handle is down, what does a red light in the handle indicate?
    all three landing gear are not down and locked
  76. What electrical system operates the flaps?
    Right AC
  77. How many right AC-powered flap motors are there?
  78. How are the flap levers interconnected and which one actuates the electrical switch?
    Mechanically; front
  79. What stops the flaps at 60% when the lever is placed that position?
    Sensing switch
  80. What stops the flaps at UP or FULL when the lever is placed that position?
    limit switches
  81. How are the flaps connected to the slab?
    Mechanically through a flexible cable in the right flap
  82. What are the 3 functions of the flap/slab interconnect?
    Reduces pitch changes with flap actuation, increases nose-down stick authority, and increases amount of slab deflection per inch of stick travel (pitch sensitivity)
  83. Does the stick move as the flap/slab interconnect repositions the slab?
    Nosewheel returns to center
  84. What will be the indications of a flap/slab interconnect failure with flaps down?
    Sudden pitchup and stall
  85. What is the best course of action to land with flap/slab interconnect failure?
    Land no-flap
  86. What intermediate flap setting should you use of a no-flap landing is not possible with flap/slab interconnect failure?
  87. What does the aux flap control allow you to do?
    Position flaps in intermediate positions
  88. How can you position flaps in intermediate positions using the aux flap switch?
    60% becomes the OFF detent