Try your hand at another one of our many aircraft unit review exercises, as we put you to the test against a series of questions regarding Aircraft Fuel Systems. How do they work? You tell us!
1 percent.
3 percent.
5 percent.
7 percent.
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Direction of fuel flow.
Direction of restricted flow.
Location of the drilled hole in the valve.
Location of the manufacturer’s data block.
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Operate the component while looking for leaks.
Pressurize the manifold with fuel and look for leaks
Stand-test with fuel for 30 minutes and look for leaks
Pressurize the manifold with air and listen for leaks.
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Forward body tank.
Crossfeed manifold.
Transfer manifold.
Center wing tank.
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The DUMP switch cover is safety-wired closed.
The landing gear must be in the airborne position.
The DUMP switch is spring-loaded to the OFF position.
A shorting plug must be connected for the dump valve to open.
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Float valves.
Float switches.
Toggle switches.
Pressure switches.
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Signal the refueling monitor when to stop the fuel flow.
Shut down the refueling vehicle if the tanks start to overflow.
Provide an automatic refueling of a tank to any desired level.
Automatically stop the flow of fuel into a tank prior to overflow.
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Requires special tools to install.
It isn’t possible to install the wrong pump.
Shortens the time required for pump changes.
Does not require either physically entering or completely defueling the tank.
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Pressure relief valves
Thermal relief valves.
One-way check valves.
Spring-loaded check valves.
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In the vent box.
At the boil port.
In No. 2 main tank.
At the ram air duct
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Wire bus.
Cannon plug.
Wire junction.
Multiple ground.
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A two-way check valve.
A one-way check valve.
An impeller screen.
An inlet screen.
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Spring pressure.
Hydromechanical action.
Gravity flow or pump pressure.
An electrical impulse to the flapper mechanism.
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Disc.
Butterfly.
Sliding gate.
Rotary plug.
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Two.
Three.
Four
Six.
The external centerline tank will transfer first.
The left wing external tank will transfer first.
The right wing external tank will transfer first.
Both wing external tanks will transfer first.
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Flame arrestor screen.
Safety wire device.
Check valve.
Flapper.
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Static.
Venturi.
Pressure.
Hydromechanical.
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F–1.
Left wing.
Right wing.
FWD reservoir.
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The faulty system or subsystem only.
A fault isolation diagram is provided.
The faulty component within the system
Corrective action required to fix problem.
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6,000 pounds.
12,000 pounds.
18,000 pounds.
24,000 pounds.
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Power to the boost pump.
A pressure switch reading
Continuity of the pressure switch.
A direct pressure reading of the pump.
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Ejector-type; located in the F–2 tank
Turbine-type; located in the F–2 tank.
Ejector-type; located in the F–1 tank.
Turbine-type; located in the F–1 tank.
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Hydromechanically and controlled by fuel pressure.
Hydromechanically and controlled by a solenoid.
And controlled hydromechanically.
And controlled by a solenoid.
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Vent.
Refuel.
Transfer.
Dump.
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The float
A spring.
A pilot valve.
The diaphragm
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With fuel pressure and closed by spring tension.
With fuel pressure and closed by the refueling nozzle.
The lever on the refueling nozzle and closed by fuel pressure.
The lever on the refueling nozzle and closed by spring tension.
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Single point receptacle drain valve must be open.
Center separation valve must be open.
Refuel isolation valve must be open.
Right separation valve must be open.
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CITS control and display panel in the aft crew station.
CITS control and display panel on the windshield center post.
System status panel on the windshield center post.
System status panel in the aft crew station.
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Gravity flow.
Ejector pump.
Rotary vane pump.
Poppet drain valve.
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Relay.
Resistor.
Solenoid.
Toggle switch.
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140ºF
160ºF.
180ºF
200ºF
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Provide an ample supply of fuel in case of a single pump failure.
Prevent fuel boiling and evaporation in the wing tanks at high altitudes.
Provide fuel to the engines during negative Gs or inverted flight conditions.
Prevent the reverse flow of fuel from a pump with a greater pressure output.
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A stuck open check valve.
A malfunctioning boost pump.
An inoperative pressure transmitter
Foreign object damage stuck in a shutoff valve.
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Pressure gauge.
Fuel no-flow light
Fuel quantity indicator.
Low-level warning light
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Gauge.
Switch.
Transmitter.
Sensing element.
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Ballast tank isolation valve only.
Forward weapons bay vent disconnect valve only.
Ballast tank isolation valve and forward weapons bay vent disconnect valve.
Main pressure actuated vent valve and forward weapons bay vent disconnect valve.
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Amber DISC light.
Blue STATUS light.
Green LATCHED light.
Blue READY/NWS light.
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Vacuum relief valve.
Hot air check valve.
Vent system.
Float valve.
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Probe.
Control unit.
Fuel level sensor
Fuel flow switch.
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Dual-impeller, turbine-driven.
Single-impeller, turbine-driven.
Dual-impeller, electrically driven.
Single-impeller, electrically driven
A rotary-vane centrifugal pump is used.
A dual-impeller centrifugal pump is used.
An in-line ejector centrifugal pump is used.
A top-mounted pump centrifugal pump is used.
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Low pressure condition exists.
Boom travel limits are exceeded.
Fuel center of gravity is off balance.
Reset trigger on pilot’s stick is pressed.
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Cycling the slipway door closed and open.
Pressing the aerial refueling RESET button.
Placing the MODE switch to the NORM position.
Placing the pilot trigger switch to the first detent.
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Fuse and relay.
Diode and solenoid
Fuse and circuit breaker
Circuit breaker and relay
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Pressure indicator reads 20 pounds per square inch (psi).
PRESS LOW light extinguishes.
Pressure indicator reads 16 psi.
PRESS LOW light illuminates.
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Refuel shuttle valve.
Refuel/transfer control valve.
Poppet-type refuel shutoff valve.
Manually operated fuel shutoff valve.
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Surge boxes.
Check valves.
Float valves.
Vent boxes.
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