Hydraulic System Operation
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What is the purpose of pressurizing hydraulic reservoirs?

  • To maintain a constant fluid volume
  • To increase the temperature of the hydraulic fluid
  • To prevent fluid contamination
  • To ensure positive fluid flow to all hydraulic pumps (correct)

    • What visual indications are present when foaming occurs in the hydraulic system during flight?

  • Flashing MASTER CAUTION light
  • Steady green hydraulic pressure indicators
  • Blinking LOW PRESSURE lights for both pumps (correct)
  • Continuous low pressure lights for both pumps

    • Which components are shared between Hydraulic System A and B?

  • Flaps and slats
  • Landing gear and thrust reversers
  • Throttle controls and wing flaps
  • Ailerons, rudder, elevators, and flight spoilers (correct)

    • Which system components are unrecoverable with the loss of Hydraulic System A?

    <p>Ground spoilers and landing gear retraction</p> Signup and view all the answers

    What is a key difference in fluid volume output between the Engine-Driven Pump (EDP) and Electric Motor-Driven Pump (EMDP)?

    <p>EDP supplies approximately six times the fluid volume of EMDP</p> Signup and view all the answers

    When is the RF (refill) next to the hydraulic quantity display valid?

    <p>Only when the airplane is on the ground with engines off</p> Signup and view all the answers

    What should be done upon seeing the RF (refill) indication during the preliminary preflight procedure?

    <p>Make M300 writeup and call maintenance control</p> Signup and view all the answers

    What are the normal and maximum pressures for hydraulic systems?

    <p>Normal Pressure: 3000 psi, Maximum Pressure: 3500 psi</p> Signup and view all the answers

    What is a possible cause for the ELEC 2 OVERHEAT light to illuminate?

    <p>Overheating of the EMDP associated with System A or overheating of hydraulic fluid</p> Signup and view all the answers

    What is the minimum amount of fuel required in each main wing tank for adequate hydraulic fluid cooling during ground operation of Electric Motor-Driven Pumps?

    <p>1675 lbs</p> Signup and view all the answers

    What is required when pushback is needed without using a nose gear steering lockout pin?

    <p>Select both System A hydraulic pumps to OFF</p> Signup and view all the answers

    What is the main function of the Power Transfer Unit (PTU)?

    <p>Supply additional hydraulic fluid for Autoslats and Flaps when System B is down</p> Signup and view all the answers

    When does the Power Transfer Unit (PTU) become operational?

    <p>When System B engine-driven pump pressure drops below specified limits</p> Signup and view all the answers

    Under what conditions does the Landing Gear Transfer Unit (LGTU) function?

    <p>No. 1 Engine RPM is below a limit and landing gear lever is UP</p> Signup and view all the answers

    What triggers the use of the Standby Hydraulic System?

    <p>Pressure loss in both System A and B</p> Signup and view all the answers

    What manual action can activate the Standby Hydraulic System?

    <p>Moving either FLT CONTROL A or B switch to STBY RUD position</p> Signup and view all the answers

    What conditions must be met for the Standby Hydraulic System to activate automatically?

    <p>Airborne with wheel speed over 60 knots and flaps extended</p> Signup and view all the answers

    What does illumination of the Master Caution, FLT CONT annunciator, and STBY RUD ON lights at FL350 indicate?

    <p>Active Standby Hydraulic System due to pressure loss</p> Signup and view all the answers

    What powers the primary flight controls normally?

    <p>Hydraulic Systems A and B</p> Signup and view all the answers

    The Trailing Edge (TE) Flaps operate electrically when there is a loss of Hydraulic System B.

    <p>True</p> Signup and view all the answers

    How is roll controlled with a jammed Aileron System?

    <p>Roll control is achieved from the spoilers via force applied to the First Officer's control wheel.</p> Signup and view all the answers

    The _____ light indicates excessive differential pressure in the Elevator Feel Computer.

    <p>FEEL DIFF PRESS</p> Signup and view all the answers

    Match the flight control systems to their functions:

    <p>Ailerons = Mechanically through cables in manual reversion Elevator = Mechanically through cables in manual reversion Rudder = Powered by Standby Hydraulic System LE Flaps and Slats = Operated by Standby Hydraulic System</p> Signup and view all the answers

    Which of the following statements about aileron trim with the autopilot engaged is correct?

    <p>Aileron trim is prohibited to prevent abrupt rolling movement.</p> Signup and view all the answers

    What happens when either the Captain's or First Officer's control column is jammed?

    <p>Force applied against the jam can breakout one control column to regain elevator control.</p> Signup and view all the answers

    What is the function of the Rudder Trim control switch?

    <p>It electrically repositions the Rudder Feel and Centering Unit.</p> Signup and view all the answers

    The Standby Yaw Damper is available during manual reversion when both FLT CONTROL switches are positioned to ON.

    <p>False</p> Signup and view all the answers

    Which yaw damper provides turn coordination?

    <p>Main Yaw Damper</p> Signup and view all the answers

    When electrical power is lost to the Spoilers Control Electronics (SCE) Unit, all spoilers are inoperative and will ______ if extended.

    <p>retract</p> Signup and view all the answers

    Match the following yaw damper protections with their functions:

    <p>Dutch roll prevention = Stability during yaw Gust damping = Reduces abrupt altitude changes Turn coordination = Maintains coordinated flight Yaw damper system fault = Switch moves to OFF automatically</p> Signup and view all the answers

    What condition must be met for MCAS to activate?

    <p>AOA above threshold</p> Signup and view all the answers

    MCAS can activate when the autopilot is engaged.

    <p>False</p> Signup and view all the answers

    What speed does MCAS control the stabilizer trim motor?

    <p>High rate</p> Signup and view all the answers

    The Flight Control Computer (FCC) activates MCAS using data from both _______ vanes.

    <p>AOA</p> Signup and view all the answers

    How can MCAS stabilizer operation be inhibited?

    <p>By using pilot Main Electric Stabilizer Trim switches</p> Signup and view all the answers

    Match the MCAS function outcome with its corresponding event:

    <p>MCAS reaches command limit = SPEED TRIM FAIL light illuminates Failure in Speed Trim System = Speed Trim System is inhibited Pilot overrides MCAS commands = Stabilizer trim commands are reversed</p> Signup and view all the answers

    MCAS and Speed Trim functions must both operate successfully at all times.

    <p>False</p> Signup and view all the answers

    After using Main Electric Stabilizer Trim, how long is the delay before MCAS can operate again if needed?

    <p>5 seconds</p> Signup and view all the answers

    If the SPEED TRIM FAIL light illuminates, it indicates a failure in the _________ System.

    <p>Speed Trim</p> Signup and view all the answers

    Which condition must be satisfied to activate the Elevator Jam Landing Assist system?

    <p>Elevator Jam Landing Assist switch must be selected ON</p> Signup and view all the answers

    Pulling on the control column causes the spoilers to extend further.

    <p>False</p> Signup and view all the answers

    How is stabilizer trim accomplished when the autopilot is disengaged?

    <p>Manual trim through stabilizer trim wheels.</p> Signup and view all the answers

    The __________ is responsible for interrupting the operation of Main Electric Stabilizer Trim when control column movement opposes trim direction.

    <p>Control Column Actuated Stabilizer Trim Cutout switch</p> Signup and view all the answers

    Match the following trim functions with their modes:

    <p>High Speed Mode = Flaps Extended Low Speed Mode = Flaps Retracted</p> Signup and view all the answers

    What happens when the STAB TRIM Cutout switches are set to CUTOUT?

    <p>All trim inputs are disconnected.</p> Signup and view all the answers

    The Flight Control Computer (FCC) can override stabilizer trim commands.

    <p>True</p> Signup and view all the answers

    What should you do to manually trim the stabilizer if the STAB TRIM Cutout switches are in CUTOUT position?

    <p>Rotate the stabilizer trim wheel.</p> Signup and view all the answers

    What occurs when the stabilizer trim is out of the green band during takeoff?

    <p>Both A and B</p> Signup and view all the answers

    Which trim system is active when the autopilot is engaged?

    <p>Both A and C</p> Signup and view all the answers

    The Speed Trim System (STS) operates when the autopilot is engaged.

    <p>False</p> Signup and view all the answers

    What is the main function of the Maneuvering Characteristics Augmentation System (MCAS)?

    <p>To increase control column forces by commanding the stabilizer in the nose down direction at elevated angles of attack.</p> Signup and view all the answers

    The Speed Trim function controls the stabilizer trim motor at a __________ rate with flaps extended.

    <p>high</p> Signup and view all the answers

    Match the following terms with their descriptions:

    <p>Speed Trim System = Provides speed and pitch stability augmentation Control Column Actuated Stabilizer Trim Cutout = Cuts out automatic stabilizer commands beyond cutout position Maneuvering Characteristics Augmentation System = Increases control column forces at high angles of attack STAB TRIM switch = Allows operation of Main Electric Stabilizer Trim regardless of control column position</p> Signup and view all the answers

    What conditions must be met for the Speed Trim function to operate?

    <p>Trim requirement must be sensed</p> Signup and view all the answers

    The STAB TRIM switch operates normally when positioned to OVERRIDE.

    <p>True</p> Signup and view all the answers

    What is the primary purpose of the Speed Trim function?

    <p>To improve flight characteristics during operations with low gross weight and aft center of gravity.</p> Signup and view all the answers

    The Speed and pitch stability augmentation provided by the STS includes __________ function.

    <p>MCAS</p> Signup and view all the answers

    Under what maximum speed does the Speed Trim function operate?

    <p>Mach 0.68</p> Signup and view all the answers

    What should be done if the RF (refill) indication is observed during the preliminary preflight procedure?

    <p>Contact Maintenance Control via Dispatch</p> Signup and view all the answers

    The Electric Motor-Driven Pump (EMDP) provides greater fluid volume output compared to the Engine-Driven Pump (EDP).

    <p>False</p> Signup and view all the answers

    What occurs when the hydraulic quantity drops below 76%?

    <p>RF (refill) is displayed next to the hydraulic quantity.</p> Signup and view all the answers

    With the loss of Hydraulic System B, the ________ components are unrecoverable.

    <p>Leading Edge Flaps &amp; Slats retraction</p> Signup and view all the answers

    Match the hydraulic system components to their corresponding system.

    <p>Ailerons = System A and B Rudder = System A and B Thrust Reversers = Standby Hydraulic System Autobrakes = System B</p> Signup and view all the answers

    What indicates the presence of foaming in the hydraulic system during flight?

    <p>Blinking LOW PRESSURE lights for both pumps</p> Signup and view all the answers

    Hydraulic reservoirs are pressurized primarily to ensure negative fluid flow to all hydraulic pumps.

    <p>False</p> Signup and view all the answers

    How many psi is the normal pressure for hydraulic systems?

    <p>3000 psi</p> Signup and view all the answers

    If the ELEC 2 OVERHEAT light illuminates, it indicates that the System A Electric Motor-Driven Pump (EMDP) ________ or its hydraulic fluid has overheated.

    <p>has overheated</p> Signup and view all the answers

    What is a consequence of having a hydraulic reservoir that is below the normal level?

    <p>Potential malfunction of hydraulic systems</p> Signup and view all the answers

    What is the minimum fuel in each main wing tank required for adequate cooling of hydraulic fluid during ground operation?

    <p>1675 lbs</p> Signup and view all the answers

    The Power Transfer Unit (PTU) operates when the system B Engine-Driven Pump pressure is above the limits.

    <p>False</p> Signup and view all the answers

    What must be done if pushback is required without the use of a nose gear steering lockout pin?

    <p>Both System A hydraulic pumps must be selected OFF.</p> Signup and view all the answers

    The Landing Gear Transfer Unit (LGTU) operates primarily to supply fluid needed to raise the _____ at a normal rate.

    <p>landing gear</p> Signup and view all the answers

    Match the following hydraulic units with their primary functions:

    <p>Power Transfer Unit (PTU) = Supplies hydraulic fluid for Autoslats and Flaps Landing Gear Transfer Unit (LGTU) = Supplies hydraulic fluid to raise landing gear Standby Hydraulic System = Provides backup pressure if A or B is lost Electric Motor-Driven Pumps (EMDP) = Operates hydraulic fluid for ground operations</p> Signup and view all the answers

    What triggers the automatic activation of the Standby Hydraulic System?

    <p>Airborne or wheel speed greater than 60 kts</p> Signup and view all the answers

    The Standby Hydraulic System will activate after a loss of pressure in either System A or B.

    <p>False</p> Signup and view all the answers

    How can you manually activate the Standby Hydraulic System?

    <p>Moving either FLT CONTROL A or B switch to the STBY RUD position.</p> Signup and view all the answers

    The PTU uses system A pressure to power a hydraulic _____ that pressurizes system B hydraulic fluid.

    <p>Motor-Driven Pump</p> Signup and view all the answers

    Match the following conditions for the LGTU operation:

    <p>Airborne = Condition for LGTU to activate No. 1 Engine RPM drops = Condition for LGTU to engage Landing Gear lever positioned UP = Condition for LGTU to work Either main gear not up and locked = Condition for LGTU engagement</p> Signup and view all the answers

    Study Notes

    Hydraulic System Operation

    • Hydraulic reservoirs are pressurized to ensure positive fluid flow to hydraulic pumps.
    • Foaming in flight indicates low pressure in both hydraulic pumps, triggering a MASTER CAUTION and HYD warning.
    • Common components between hydraulic systems A and B include: ailerons, rudder, elevators, and half of the flight spoilers.
    • Unrecoverable components in system A with a loss include landing gear retraction and ground spoilers.
    • Unrecoverable components in system B with a loss include leading edge flaps and slats retraction and autobrakes.
    • Standby Hydraulic System powers the rudder, thrust reversers, and leading edge flaps and slats (extension only).
    • Engine-Driven Pump (EDP) supplies approximately six times the fluid volume of an Electric Motor-Driven Pump (EMDP).
    • "RF" (refill) is displayed next to hydraulic quantity when below 76% and the airplane is on the ground with both engines shut down or after landing with flaps up during taxi.
    • Low hydraulic quantity is indicated by "RF" next to the A or B quantity display during preliminary preflight.
    • The appropriate action when seeing "RF" during preflight is to make an M300 writeup and contact maintenance.
    • Normal hydraulic pressure is 3000 psi, with a maximum of 3500 psi.

    Hydraulic System Issues

    • System A Electric Motor-Driven Pump (EMDP) overheating or hydraulic fluid used to cool and lubricate the pump overheating can cause the ELEC 2 OVERHEAT light to illuminate.
    • Standby hydraulic system is primarily used as a backup if system A and/or B pressure is lost.
    • System A or B pressure loss alone does not automatically activate the standby hydraulic system; it needs additional activation methods such as moving the FLT CONTROL A or B switch to STBY RUD position or moving the ALTERNATE FLAPS Master switch to ARM position.
    • Standby hydraulic system automatically activates in airborne or wheel speed over 60 kts, flaps extended, and loss of either hydraulic system A or B, which is then indicated by Master Caution, Flight Control annunciator and STBY RUD ON lights illuminating.
    • Standby hydraulic system low quantity light illuminates when the standby reservoir is approximately half empty.
    • Standby hydraulic system low pressure (amber) light indicates low output pressure of the standby pump and is armed when standby pump operation is selected or automatic function is activated.
    • Elevator, ailerons, and rudder are powered by hydraulic system B if FLT CONTROL A is set to STBY RUD.
    • In case of hydraulic system A and/or B failure, the #1 reverser can be pressurized by standby hydraulic system causing reverse thrust operation from both engines.
    • If hydraulic system A or B fails, the Standby Hydraulic System provides alternate operation for the affected thrust reverser.
    • The Power Transfer Unit (PTU) uses system A pressure to power a hydraulic motor-driven pump, pressurizing system B hydraulic fluid.
    • The Landing Gear Transfer Unit (LGTU) supplies hydraulic fluid to raise the landing gear when system A's engine-driven pump (EDP) volume is low.

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    Description

    Test your knowledge on the operation of hydraulic systems in aviation. This quiz covers essential components, pressures, and functionalities relevant to hydraulic reservoirs, pumps, and system failures. Ensure you're familiar with how these systems affect flight safety and control.

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