Syst test 2023

If green system pressure is lost, nosewheel steering is still available. True. False.

Which of the following information about the landing gear is received by the LGCIUs from the proximity detectors?. The 3 gear are locked down or are up. The shock absorbers are compressed or extended. The landing gear doors are open or closed. All of these answers are correct.

Auto brakes are available with the alternate brake system. True. False.

When there is an electrical failure of one of the LGCIUs. The system does not modify the outputs of the failed LGCIU to the fail safe "flight mode". The system modifies the outputs of the failed LGCIU to the fail safe "flight mode".

Anti-skid normally operates only when the green hydraulic system is providing brake pressure. False. True.

After takeoff, the Autobrakes automatically disarm after the aircraft has been in flight for more than __________. 10 sec. 5 secs. 8 secs. 15 secs.

The Autobrake LO mode sends progressive pressure to the brakes _________ after Ground Spoiler deployment. 4 secs. 2 secs. 6 secs. 5 secs.

Anti-skid protection is not available during use of the alternate brakes. False. True.

The Auto brake system uses green hydraulic system pressure and is only available through the normal brake system. True. False.

Prior to pushback, ground personnel will set the towing control lever to the TOW position, and this condition is displayed as a green Memo of NW STRG DISC. True. False.

Autobrake arming requires all of the following EXCEPT. Yellow syst press. Normal pressure in the green hyd system. Anti skid must be powered. At least one functioning ADIRU.

To extend the landing gear with the Gravity Extension Handcrank requires ______ turns of the handle. 3 counter-clockwise. 2 counter-clockwise. 3 clockwise.

The maximum degrees of nosewheel steering available when using the handwheel iS. +/- 60. +/- 75. +/- 95.

The green DECEL light on the Autobrake switch illuminates when the actual airplane deceleration corresponds to ______ % of the selected rate. 80. 95. 100. 110.

Which hydraulic systems have engine driven pumps?. Green and blue. Green and yellow. Blue and yellow.

Fluid can be transferred between hydraulic systems. True. False.

Which hydraulic systems have engine driven pumps?. Green and blue. Green and yellow. Blue and yellow.

The RAT pressurizes the Blue hydraulic system to approximately _____ psi. 1500. 2500. 3000.

The brakes pressure indication on TRIPLE PRESSURE INDICATOR reads which system pressure?. Yellow. Green. Blue.

The PTU is automatically activated when the differential pump pressure output between the ________ and _______ systems is greater than __________ psi. Blue yellow 1000. Green yellow 500. Green yellow 1000.

The PTU Fault light illuminates when the. PTU is inop. Green or yellow reservoir has low air pressure. PTU pump has overheated.

The A-320's three hydraulic systems are normally pressurized by. Two engine driven pumps and one elecrectric pump. Two electric pumps and one PTU. Two electric pumps and one engine driven pump. One electric pump and one engine driven pump.

For hydraulic system malfunctions, when will the RAT deploy. Automatically with the failure of both the green and blue hydraulic systems. Automatically with the failure of both the green and yellow hydraulic systems. Only when the guarded RAT MAN ON push button is selected by the crew. When airspeed drops below 100 knots with the gear up.

A few seconds after selecting reverse, the amber REV indication changes to green. What does this mean?. The reversers have been re-stowed. The reversers are now fully deployed. The reverse thrust selection has been acknowledged. The reversers are unlocked.

During engine start the amber FAULT light on the ENG MASTER panel illuminates. This indicates: A failure in the automatic start sequence. A failure of the ENG MODE SELECTOR. C.- A failure in the engine fire extinguishing system.

Which steps of a manual start are being taken care of by the FADEC. Starter valve closure and ignition cut off. Starter valve opening and ignition start. Starter valve closure and ignition start. Starter valve opening and ignition cut off.

Can Alpha-floor be disengaged while in Alpha Protection. Yes, by manually disengaging the auto throttles. No, the system is designed to avoid such a disengagement. Yes, by reducing at idle one of the throttles (for more than 5 seconds).

Is it possible to disconnect Alpha floor?. No, Alpha floor protection is always available. Yes, by placing the thrust levers to IDLE. Yes, by depressing the autothrottle push button on the FCU.

The FADEC will automatically abort an abnormal start thereby providing engine limit protection, but will the FADEC also automatically dry crank the engine?. Automatic controlof the engine would be lost. The standby channel of the ECU would take over. The FADEC would now be powered using ship's power. The FADEC would now be powered using ship's battery power.

You are in the middle of a manual engine start. What are you looking for when you select ENG MASTER 2 ON?. The fuelused is reset, fuelflow is indicated and IGNITION message on the E/IVD. The fuel flow is reset, an igniter is powered and fuel used is indicated. The fuel used is reset, both igniters are powered and fuelflow is indicated. The fuel used is reset, both igniters are powered and N2 is increasing.

Each FADEC is a dual channel (A&B) computer providing full engine management. True. False.

In addition to when the engine is operating, when else will the FADEC be powered?. When the FADEC GND PWR pb on the maintenance panel is depressed, or the ENG MASTER switch is placed to ON. When the FADEC control switch is placed to the IGN/START position. For five minutes after electrical power is applied to the aircraft, when the FADEC GND PWR pb on the maintenance panel is depressed, or when the ENG MODE control switch is placed to IGN/START position. As long as electrical power is established on the aircraft, the FADEC is powered.

During an automatic start, the FADEC controls. The start valves, igniters and fuel flow. The start valves, igniters, HP and LP fuel valves. The igniters and fuel flow. The start valves, igniters, HP and LP fuel valves, and fuel flow.

How is manualarming of the A/THR system accomplished?. By pressing the A/THR pb on the FCU confirm the pushbutton illuminates green or confirm an A/THR annunciation is displayed in column 5 of the FMA. By placing the thrust levers into the active range. Advance at least one thrust lever to the TOGA or LX/I CT detent with at least one Flight Director (FD) on.

Can the wing anti-ice is tested on the ground?. No. Yes, valves only open for 30 secs. Yes, valves stay open till selected off.

When a pneumatic leak is detected, the wing anti-ice valves. Close automatically. Open automatically. Remain in position.

Probe heat comes on automatically when. Te AC ess bus is powered. Electrical power is applied to the aircraft. When at least one engine is running.

On the ground the wing ant-ice valves will: Open during a test sequence (30 seconds); provided pneumatic supply is available. Not open at anytime. Open anytime the switch is pushed ON.

What is the difference between the engine and wing anti-ice fault lights. Both indicate valve in transit, or valve position disagrees with selected position. Wing light also could indicate low pressure. Both indicate low pressure, or valve position disagrees with selected position. Wing light might indicate valve in transit. Both indicate valve in transit, or low pressure, wing light also could indicate valve position disagrees with selected position. Both indicate valve in transit, or overheat.

With reference to the probe/window heat pushbutton, which of the following is true?. Both indicate valve in transit, or valve position disagrees with selected position. Wing light also could indicate low pressure. Both indicate low pressure, or valve position disagrees with selected position. Wing light might indicate valve in transit. The system should only be selected on after first engine start. Window heating comes on automatically after first engine start.

If one engine anti-ice system fails, the second one takes over and provides anti-icing for both engines. True. False.

What happens when either engine anti-ice is open?. Maximum N 1 is limited, continuous ignition is provided, maximum idle RPM is increased. Maximum N 1 is limited, continuous ignition is provided, minimum RPM is increased. Minimum N 1 is limited, continuous ignition is provided, minimum idle RPM is increased.

With the loss of electrical power the engine anti-ice valves. Fail Inter current position. Fail to the open position. Fail to the close position.

What is the speed limit to operate the windscreen wipers?. 185 kts. 200 kts. 230 kts. 250 kts.

In the event of an electrical power loss. The engine anti-ice valves will open automatically, anti-icing is ensured. The engine anti-ice valves will close automatically, anti-icing is lost. The engine anti-ice valves will be controlled by the wing anti-ice controls. The engine anti-ice valves remain in the position they were before.