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59 Cards in this Set
- Front
- Back
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Complete loss of system 'B' pressure will deactivate
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The outboard flight spoilers.
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If an electric hydraulic pump OVERHEAT light comes on
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Turn the associated system electric hydraulic pump OFF.
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A leak in the hydraulic system B engine driven pump or its associated lines would be indicated by
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System B contents falling to half full (conventional engine instruments) or 40% (EIS).
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The standby system LOW PRESSURE light is armed
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Only when the standby pump operation has been selected or automatic standby function is activated.
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The standby hydraulic pump only supplies pressure to the
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Standby rudder actuator, leading edge devices and thrust reversers.
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If either Flight Control switch is moved to the STBY RUD position
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The standby pump will be activated and the standby hydraulic LOW PRESSURE light will be armed.
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Low fluid quantity in the A system reservoir can be indicated by one of the following
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Mechanical indication on the reservoir.
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If a total failure of both pumps supplying system B pressure occurs, which of the primary flight controls will be totally inoperative
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None
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The A and B hydraulic reservoirs are pressurised by
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Air from the pneumatic manifold.
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Selecting an engine driven hydraulic pump switch to OFF will
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Activate the solenoid-held blocking valve and isolate fluid from the using unit.
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The normal and maximum readings on the hydraulic system pressure indicator are
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3000 : 3500psi
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The Standby hydraulic reservoir is kept topped up from
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The system B reservoir.
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Hydraulic system A power sources are
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One engine driven pump (ENG 1) and one electrical motor pump (ELECT 2).
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Illumination of a Hydraulic Electric Pump OVERHEAT light indicates
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An overheat condition in the case drain line or the pump housing.
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Illumination of a electric hydraulic pump OVERHEAT light will
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Not shut down the associated pump.
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The maximum hydraulic system A or B pressure is
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3500psi
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Loss of the A hydraulic system will result in the complete loss of the following
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Ground spoilers. Inboard flight spoilers. Alternate brakes. Autopilot A.
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Loss of the B hydraulic system will result in the complete loss of the following
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Outboard flight spoilers. Autopilot B. Normal brakes. Yaw damper.
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The standby hydraulic pump is automatically activated on the loss of system A or B hydraulic pressure
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During the take-off or landing with a wheel speed greater than 60 Kts and the wing flaps extended.
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The indications of a leak in the standby reservoir are
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Illumination of the standby hydraulic LOW QUANTITY light and the B system reservoir quantity decreasing and stabilising between 1/2 and the RFL indications (conventional engine instruments) or approximately 64% full (EIS).
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A leak in the hydraulic system A engine driven pump or its associated lines would be indicated by
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System A contents falling to one quarter full (conventional engine instruments) or 22% (EIS).
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The 'B' system reservoir has
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Two standpipes.
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Placing the A Flt Control switch to STBY RUD position will
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Start the standby pump, arm the standby hydraulic LOW PRESSURE light, close the A system Flight Control Shutoff valve and the A system Flt Control LOW PRESSURE light is de-activated when the standby rudder shutoff valve opens.
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Using the Standby Hydraulic power for thrust reverser deployment will cause
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Deployment time to increase.
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The standby system low quantity light is
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Armed at all times and will illuminate whenever the reservoir is approximately half empty.
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The Standby hydraulic fluid
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Is not cooled.
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Pulling NO.1 Engine Fire switch will
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Stop the fluid to the No. 1 Engine Driven hydraulic pump by closing the Hydraulic Shutoff valve and de-activate the associated low pressure light.
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The engine driven hydraulic pump switch
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Is left in the ON position on shutdown to prolong the life of the blocking valve solenoid.
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Why are the engine hydraulic switches left on at engine shutdown?
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To prolong blocking valve solenoid life.
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System A hydraulics has ___ standpipes which saves _____ % of A system fluid for use by the A system electric pump to move flight controls.
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1; 25
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If there is a leak in system A in or down stream of the electric pump, the fuel gauge will indicate the standpipe quantity.
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False.
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There are ____ standpipes in system B. It saves ____ % for use by B system electric pump.
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2; 50
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The balance line to the standby reservoir is at 64% of system B.
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True.
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When does the Stdby Hyd Low Quantity light illuminate?
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Less than 50%in the standby reservoir.
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What is the purpose of leaving B system electric pumps on during through flight?
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Maintains brake pressure.
Reduces pump cycles. Provides a hydraulic gust lock buffer. |
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How are the hydraulic fluids cooled?
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By a fuel tank heat exchanger.
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The reason system A pumps are turned off at engine start is to prevent getting nose wheel steering pressure, which might swing a tow bar.
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True.
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Which hydraulic system is used to run the PTU?
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System A.
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When taxi speed decreases below 60 knots, the STBY pump will automatically stop.
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True.
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The electric hydraulic pump A is marked electric 2 and the electric pump B is marked electric 1. This indicates which _______ bus is its power source. In addition, should you lose an engine, the pump will continue to work since it is powered by the opposite _______ bus.
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GEN
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How many standpipes are in the Standby reservoir?
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None.
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An S/B DO NOT ARM light involves a _______ restriction.
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Allowable landing weight.
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If you put one of the FLT CONTROL switches to STBY RUDDER, the FLT Control LOW PRESSURE light becomes a valve position indicator.
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True.
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After liftoff, you lose -A- system pressure. What will bring the gear up?
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You can't bring it up.
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The LGTU kicks in if the system senses N1 tack below approximately 56% RPM.
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False.
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What conditions are necessary to get auto speed brake after landing?
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Speed brake lever in ARM.
Throttles to idle. Wheel spin up. |
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When you place the speed brake lever into the ARM position, what is checked by the system?
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Speed brake actuator reset.
At least one A/S system operative. No false wheel spin ups. |
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The gear handle won't come up after rotation. When can you override with the trigger?
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Not until after the flaps are up.
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An A/S INOP light involves a _________ restriction.
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Runway limit
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What are the requirements for auto slat operation?
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Flaps between 1 and 5.
Airborne. An impeding stall. |
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What will cause the Anti-Skid system to deactivate?
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Gear lever up.
Parking brake set Taxi speed less than approximately 18 knots. |
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What will cause the STDBY pump to come on automatically?
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Loss of A or B system.
Trailing edge flaps not up. In flight or on ground with wheel speed greater than 60 knots. |
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The Speed Brake light flashes right after touchdown. This indicates a failure of the air/ground switch in the flight mode.
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True.
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What hydraulic system powers each reverser?
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L reverser - System A with STBY pump backup. R reverser - System B with STBY pump backup.
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The PTU is meant for the autoslat system in the event of a loss of pressure to system B.
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True.
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When does the PTU kick in?
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When system B pressure is lost.
When the aircraft is airborne. |
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A PMC INOP light involves a _______ restriction.
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Takeoff.
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If the STBY pump is automatically activated, the FLT Control LOW PRESSURE light becomes a valve position indicator.
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False.
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During start, you must monitor A system pressure for no increases. Starter cutout at 46% checks the N2 tach operation for LGTU activation
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True.
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