Part 6 Hydraulics

  1. What common units are powered by a combination of system 1 & 3?
    • Nosewheel steering.
    • Stabilizer trim.
    • Slats.
    • Brakes.
  2. What common units are powered by a combination of systems 1 & 2?
    • Flaps.
    • Autopilot.
    • Rudder.
  3. What common units are powered by all three systems?
    • Spoilers.
    • Elevators.
    • Ailerons.
  4. What units are powered by System 3 only?
    Landing gear.
  5. Which systems are connected by reversible motor pump operation?
    • 1 and 3 through 1-3 rmp.
    • 2 and 3 through 2-3 rmp.
  6. What conditions will cause the RMP's to automatically come on?
    • A. Auto slat extend signal.
    • B. N2 less than 45% on takeoff or approach.
    • C. System pressure low during takeoff or approach.
    • D. Loss of a second engine in flight.
    • E. Pulling a Fire T-Handle on approach or takeoff.
    • F. Selecting MANUAL on the hydraulic system control panel.
  7. What does RMP symbol on the hydraulic synoptic indicate?
    Commanded position.
  8. How do the RMP's operate?
    A pressurized system drives a motor pump to provide an alternate source of pressure for another system without transfer of fluid.
  9. The 3-2 non-reversible motor pump provides backup power for which control surfaces?
    Lower rudder.
  10. The 2-1 non-reversible motor pump provides backup power for which control surfaces?
    Upper rudder and stabilizer trim.
  11. What is the hydraulic source of fluid required to operate the NRMP's?
    A compensator in the failed system acts as a mini reservoir and stores fluid to operate the NRMP.
  12. When does the HYD_QTY LO level 2 alert illuminate?
    If Reservoir quantity is less than 4.75 gallons prior to engine 1 or 2 start or less than 6 gallons in system 3.
  13. When are the NRMP's arm to operate?
    At all times unless the compensator fluid is low.
  14. What are the three methods of turning on the #1 aux pump?
    • A. Aux pump switch on.
    • B. Deploy the ADG.
    • C. Aux hydraulic pump switch on the brake panel.
  15. When are the aux pumps controlled and operated by the hydraulic system controller?
    Only during the preflight test.
  16. When is the #1 aux pump automatically de-energized during engine start?
    When any fuel switch is moved to on and the hydraulic system control panel is in auto.
  17. What is the significance of the cyan line on hydraulic Reservoir?
    Represents the hydraulic quantity after engine reaches idle.
  18. When will the level 1 "HYD_QTY LO "alert be displayed with the system controller in auto
    • System 1 & 2 level 1 (HYD_QTY LO) alert is displayed if less than 4.75 gallons on the ground prior to engine start, or <2.5 gallons after engine start.
    • System 3 level 1 (HYD_QTY LO) alert is displayed if less than 6.0 gallons on the ground prior to engine start, or <2.5 gallons after engine start.
  19. When are the reversible motor pumps inhibited from operating?
    Associated reservoir quantity less than 1 gallon. Anytime the ADG is powering up Aux pump 1.
  20. How is the hydraulic pressure test performed in Auto mode?
    Push the Test switch.
  21. What is the indication of a test failure?
    There will be a level 1 Hyd press Test fail alert.
  22. What would cause the hydraulic pressure test to fail?
    • A. Hydraulic Reservoir fluid quantity low.
    • B. Any RMP or Aux pump pressure low or excessive time to reach required system pressure.
    • C. Hydraulic Aux pump switch on.
  23. Can the hydraulic pressure test be performed in flight?
    No, the aircraft must be on the ground, all fuel switch is off.
  24. What are the primary and Alternate sources for the upper rudder?
    • Primary: Hydraulic system one.
    • Alternate: Hydraulic system 2 through the 2-1 NRMP.
  25. What are the primary and Alternate sources for the lower rudder?
    • Primary: Hydraulic system 2.
    • Alternate: Hydraulic system 3 through the 3-2 NRMP.
  26. Which engine driven pump is operating and which one is armed during normal operations?
    Left pump operates and the right pump is armed.
  27. When will the right engine-driven pump be activated?
    Anytime a fault (temperature or pressure) is detected in the left pump.
  28. When will the engine-driven pumps not be commanded off for any reason?
    When in the takeoff or approach configuration.
  29. Describe the hydraulic test that is automatically performed when the engines reach idle.
    Left EDP is turned off and the right EDP is turned on. The pressure is checked, then the system is returned to normal, left pump on, right pump armed.
  30. When does the HYD SYS 3 ISOL alert mean when displayed during pre-flight?
    The flight control isolation valve is not in the normal, open position. Maintenance is required.
  31. What will happen if an active hydraulic system controller (HSC) Channel fails?
    Control will be transferred automatically to the other HSC Channel.
  32. What will occur if both HSC channels fail?
    The system automatically revert to the manual mode.
  33. What would happen if any combination of hydraulic systems and/or aircraft abnormal operation would require more than four engine driven hydraulic pumps to be commanded off?
    The hydraulic system revert to the manual mode of operation.
  34. Which hydraulic power source operates in conjunction with autopilot 1?
    Hydraulic system 2.
  35. What does the "HYD 3 ELEV OFF" alert indicate?
    Hydraulic system 3 has decreased to less than 4.75 gallons and the enhancement system shut-off valve has closed. Hydraulic system 3 is not powering the elevators. 3-2 NRMP inop.
  36. What condition will cause the engine pump "FAULT" light to illuminate?
    Pump case drain temp high or pressure low.
  37. What condition will cause the system "PRESS" light to illuminate?
    LOW or HIGH system pressure. In addition, the pressure indication on the Hydraulics synoptic turns amber and is boxed in amber.
  38. How will aircraft operation be affected if HYD SYS 1 has failed (less than a gallon of fluid)?
    Limited nose wheel steering to the left.
  39. How will the aircraft operation be affected if HYD SYS 2 has failed?
    There is no affect.
  40. How will the aircraft be affected if HYD SYS 3 has failed (less than a gallon of fluid)?
    Limited nose wheel steering to the right and unable to raise the landing gear if down.
  41. If hydraulic system 1 & 3 have failed, what effect will it have on aircraft operations?
    Nose wheel steering.
Author
SFT
ID
340561
Card Set
Part 6 Hydraulics
Description
MD11 Hydraulics
Updated