320 electrical power

ENHANCED. Each DMC (Display Management Computer) in the Enhanced System is able to supply: Two EFIS displays and two ECAM displays. All EFIS displays and all ECAM displays. Two EFIS displays and one ECAM display.

In normal condition the A C ESS BUS is supplied by .... The AC Bus 2. The AC Bus 1. the Static Inverter.

Which type of BITE system is able to memorize failure informations over 64 flight legs?. Type 2. Type 1. Type 3.

If FWC 1 fails, what happens to the attention getters?. Only the visual warnings are lost. Only the aural warnings are lost. Only half of the bulbs in each MASTER WARNING and MASTER CAUTION lights are lost.

The Smoke in the Avionics compartment is detected by ... AEVC. FWC. Avionics smoke detector.

What is the reason or the ECAM Message ENG 1 FIRE LOOP A FAULT?. Loop A of Engine 1 detected a fault of electrical failure. Loop A and Loop B of Engine detected a fault whin less than five seconds. Loop A and B of Engine detected a fire.

The FAULT light in the IDG DISC P/B illuminates when…. the IDG is not turning. the iDG oil outlet temp. is too low. the IDG oil pressure is too low or the oil outlet temp, is too high.

High oil APU generator temperature. What is the consequence?. The APU GCU de_energize the generator field excitation via GCR. The ECB commands an APU shut down. The APU GCU commands an APU shutdown.

The DMC 1 is inoperative, which display is lost?. The Capt. ND and the stand by indicator. The Capt. PFD, ND and upper ECAM. The lower ECAM and the Capt. clock.

The crew detect a DMC # 1 failure, so... The EIS - DMC switch must be manually switched from Normal to Capt. DMC # 3 replace DMC # 1 function automatically.. The transter pushbutton PFD/ND must be pressed.

Which CFDS-menu function allows access to detailed failure informations of an A/C system?. Avionics Status. System Report/Test. Post Flight Report.

ENHANCED. At the enhanced system the Cabin Intercommunication Data System (CIDS) director fulfills... the Smoke Detection Function (SDF). the power supply function of the reading lights. the control of the lavatory fire extinguisher bottles.

From the following, which case will trigger an engine fire warning?. When Loop A has detected a fire and Loop B a fault. When Loop A and Loop B have detected a fault within a time above ten seconds one after the other. When Loop A has detected an electrical failure and Loop B has detected a fault ten seconds later.

What is the function of the GEN 1 LINE push button?. When selected OFF the avionics compartment isolation valves close. When selected OFF generator # 1 removed from all busses bus continues to power one fuel pump in each wing. When selected OFF the #1 generator powers all AC busses.

How is the TAT probe heated?. Heated in flight, not on ground. Only heated on icing conditions. Heated on ground, not in flight.

When a white ADV message pulses on the EW/D?. When any value drifts from the normal range, with both DU operative. When a parameter drifts out of its normal range and there is only one DU available. When any class 2 failures are stored.

After a loss of TR 2... the BAT BUS is lost. the DC BUS 2 is lost. the DC ESS BUS will be supplied via ESS TR.

What happens if the ElU and/or PHC C/B are pulled?. Nothing. The related probes and static ports will be heated. The related probes and static ports will be de-energized.

The normal order to supply electrical power to the AC busses Is: External power engine generators then APU. APU, external power then engine generators. Engine generators, external power then APU.

An AC ESS FEED switch located on the overhead panel shifts the power source for the AC ESS bus from: AC Bus 1 to AC Bus 2. AC bus 1 to AC Grnd/Fit bus. AC bus 2 to AC bus 1.

Which of the following AC busses can be powered by the emergency generator?. AC Bus 2. AC Bus 1. AC ESS bus / AC ESS SHED bus.

When a Display Unit does not receive input data, it displays... a black screen with a white diagonal stroke. the last page frozen. a blank screen.

The STS reminder on the ECAM - E/WD (engine and warning display) indicates... ...that the engine/warning display is faulty. ..that there is only a maint status information on the status page of the system display. ...that there is a message on the status page of the system display.

What happens when a fire is detected in a Lavatory waste-bin?. Warning are sent to the cockpit and cabin. Warning are sent to the cabin. An automatic extinguishing occurs.

ENHANCED. On the Enhanced System, the lavatory smoke detectors are connected... direct to the SDF (Smoke Detection Function) in the CIDS Director. to the SDF (Smoke Detection Function) in the CIDS Director via DEU - B (Decoder Encoder Unit). to the SDCU (Smoke Detection Control Unit).

What is the function of the EGIU (Electrical Generation Interface Unit)?. To protect the gen. system and ext. power from abnormal operation. To gather various data from the gen. and ext. power system and transmit them to the CFDIU. To gather varlous data from the gen, and ext. power systems convert them to digital datawords and transmit them to the ECAM for indication.

Where are the class 3 failures shown?. They are shown on the ECAM EW/D. The fight crew can see them on the status page. They are available on the MCDU.

In case of APU fire on ground which additional warnings are activated?. The red APU fire light will iluminate on the external power control panel and external horn is activated. Only external hor is activated. On overhead panel the SQUIB light comes on.

Mention some of the functions of FWC: To record the SELCAL communications. To generate the Flight Phase, Heading/Attitude/Altitude comparison. To store the flight data for event investigation.

When do the batteries supply their own side Hot Bus?. Whenever the batteries are connected. Only in fight, during an emergency configuration. On ground with a speed below 50 Knots.

ENHANCED. The Display Management Computer (DMC) receives the operating software by: A flash card. software loading. An On Board Replaceable Memory (OBRM).

What can happen if the Window Heat Computer #1 is inoperative?. The WHC 2 is switched automatically. The F/O side remains inoperative. The Cap. side remains inoperative.

Is the function of the SACs, acquisition of malfunction and failure data... to be displayed directly on the display units. corresponding to caution situation (amber). corresponding to warning situation (red).

Is it possible to parallel generators?. of course yes. the electrical system will not allow “paralleling” of generator. Only engine generator may be paralleled with the APU.

You move the Maint Bus Sw to the ON position, and it does not engage. What is going on?. The Bat 1 & Bat 2 switches are in OFF position. The TR-2 Is in Overheat condition. The GCU 1 is inoperative.

How many types of failures can you see on the E/WD?. Passive and inactive fallures. Independent, Primary and Secondary failures. Isolated and recorded failures.

The APU Gen Fault light is ON. What does it mean?. A protection trip was initiated by APU GCU. The APU is shut down. The APU Gen pushbutton is set to OFF.

Select the correct statement about Alert levels: Level 3 alert is shown in the avionics status only. Level 1 alert generates a master warning light and an aural warning. Level 2 alert generates a single chime and a master caution light.