A 320 Electrical System

When external power is available and within limits, the green AVAIL light will illuminate on the EXT PWR button. This indicates that the external power source is connected and ready to be used. The BUS TIE push button illuminates to indicate that the bus tie contractors have automatically closed, allowing power to flow between the different bus systems.

After the loss of Gen 2 and the subsequent start of the APU, Eng gen 1 will continue to power AC bus 1 and downstream systems. The APU will power AC bus 2 and downstream systems. This means that the electrical system will be divided between the two power sources, with each powering a different bus and its associated systems. The RAT (Ram Air Turbine) will need to be restored to ensure normal operation of all systems.

The correct answer is Gen 1 or Gen 2, External power (if selected), APU. This means that the priority of electrical sources is first given to the generators (Gen 1 or Gen 2), then to external power if it is selected, and finally to the APU (Auxiliary Power Unit).

The correct answer states that the battery power will be available between 22 and 30 minutes, depending on the equipment in use. This suggests that the duration of battery power in flight is limited and can vary based on the power consumption of different equipment.

Green collared circuit breakers are significant because they are monitored by the ECAM. This means that the ECAM system keeps track of the status and condition of these circuit breakers. Monitoring the circuit breakers is important for the overall safety and functionality of the electrical system in an aircraft. By being able to monitor the green collared circuit breakers, the ECAM can detect any faults or malfunctions in the electrical system and alert the crew to take appropriate action.

The correct answer is Yes, press the ECAM ELEC, push button and view the electrical schematic on the ECAM. This suggests that it is possible to determine the source of power for the Aircraft busses by pressing the ECAM ELEC button and viewing the electrical schematic on the ECAM.

Reconnecting an IDG (Integrated Drive Generator) in flight is not possible.

When operating on Emergency Electrical Power (EMER GEN), it is possible to properly complete the ECAM checklist only on the upper display by depressing and holding the specific ECAM page push button on the ECAM control panel. This action triggers an automatic transfer of the checklist to the upper display, allowing the pilot to access and complete it. Using the cockpit operating manual or any other method is not necessary or applicable in this situation.

When operating on Emergency Electrical Power (EMER GEN powering the system, FAC 1 reset), the control laws that are in effect are the Alternate control laws. This means that the system is being controlled by an alternate set of rules or regulations specifically designed for emergency situations. The Alternate control laws take over when the primary control laws are not available or not functioning properly.

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The function of the GEN 1 LINE push button is to remove generator 1 from all buses but still continue to power one fuel pump in each wing. When the push button is selected to OFF, the generator is disconnected from all electrical systems but remains operational to provide power to the fuel pumps. This allows for the continued operation of the fuel pumps even if the generator is not supplying power to other systems.

Disconnecting an IDG (Integrated Drive Generator) should only be done when the engine is running, and the IDG disconnect push button should not be pushed for more than 3 seconds. This is because disconnecting the IDG in flight or for an extended period of time can lead to loss of power generation, which can affect the aircraft's electrical systems and potentially cause a hazardous situation. Therefore, it is important to follow the specified limitations to ensure the safe operation of the IDG.

The correct answer is "Once, if authorized by the procedure". This means that typically, a circuit breaker can only be reset once. However, if there is a specific procedure in place and authorization is granted, it may be possible to reset it a second time. This implies that there are certain protocols and guidelines that need to be followed when resetting a circuit breaker, and it should not be done without proper authorization.

During an emergency electrical situation, the cockpit light that is available is the right side dome light, main panel flood lights (left two columns only), and the standby compass light.

The RAT (Ram Air Turbine) automatically deploys when both AC BUS 1 and 2 lose electrical power and the aircraft speed is at or below 100 knots. Additionally, the loss of two hydraulic systems may also trigger the automatic deployment of the RAT.

The minimum voltage when conducting a BATTERY CHECK should be greater than 25 volts. This implies that the battery should have a voltage level higher than 25 volts in order to pass the battery check.

When operating on Emergency Electrical Power with the landing gear lowered, the law in effect is the "Direct" law. In this mode, the flight control system directly commands the control surfaces based on the pilot's input, without any assistance or augmentation. This law provides a direct and immediate response to the pilot's commands, ensuring that the aircraft can be controlled even in emergency situations when normal electrical power is unavailable.

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If the Bus Tie push button is depressed to OFF during a normal flight, it would have no effect on power to the busses.

The battery fail light will illuminate when the battery charging current increases at an abnormal rate. This means that the rate at which the battery is being charged is not within the normal range, indicating a potential issue with the charging system. This could be caused by a malfunctioning charger or a problem with the battery itself. It is important to address this issue promptly to prevent further damage to the battery or the electrical system.

When the EMER GEN is not supplying electrical power, AC busses 1 and 2 are unpowered, and the nose gear is up, the RAT and EMER GEN red FAULT light will illuminate.

The APU GEN push button is located on the overhead electrical panel and its function is to de-energize the APU generator field when selected to OFF. This means that when the button is pushed and set to OFF, the APU generator will stop supplying electrical power. This can be useful in situations where the APU is not needed or when maintenance work is being carried out on the generator.

The circuit breakers on the overhead panel may be operational in the Emergency Electrical Configuration. This means that in the event of an emergency where the normal electrical systems fail, these circuit breakers can still provide power to essential systems. It is important to note that they are not monitored by ECAM, which means that their status and functionality need to be manually checked and monitored by the pilots. While they cannot be reset, they play a crucial role in ensuring the availability of electrical power during emergency situations.

The Flight Augmentation Computer (FAC) 1 will be inoperative with gear extension while in the Emergency Electrical Configuration.

When both engine generators are powering the system and one of them fails, the system does not experience a complete loss of power. However, to compensate for the loss of one generator, some loads are shed in both main galleys. This means that certain electrical loads are temporarily disconnected or turned off to ensure that the remaining generator can handle the power demand without overloading. Therefore, while no buses are left unpowered, there is a reduction in the overall load to maintain system stability.

The correct answer is that Gen 1 supplies AC bus 1 and (generally) the downstream system, while Ext Pwr supplies AC bus 2. This means that the engine generator 1 is providing power to AC bus 1 and the downstream system, while external power is supplying AC bus 2. The fact that the EXT PWR push button blue ON light is illuminated indicates that external power is being used to supply AC bus 2.

When the load on any generator exceeds its rated output of 100%, it can cause the GALLEY fault light to illuminate. This indicates that there is an issue with the galley system, most likely due to the excessive load on the generator.

In the EMERGENCY ELECTRICAL CONFIGURATION, with the EMER GEN powering the system, the operational communication and navigation radios are ACP 1, ACP 2, VHF 1, HF1, RMP 1, VOR 1, and ILS 1.

The correct answer is "Exit sign, emergency lights, and scape path lighting." This means that when the EMERGENCY EXIT light switch is in any of its three positions, the associated lights that are activated or controlled by this switch are the exit sign, emergency lights, and scape path lighting.

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When the EMER EXIT LT selector is in the ARM position, the emergency lights and exit lights will be activated if the AC bus 1 is unpowered. This means that if there is a loss of power to AC bus 1, the emergency and exit lights will automatically turn on to provide illumination in case of an emergency or evacuation. The other two situations mentioned, AC shed bus and DECESS SHED bus being unpowered, do not affect the activation of the emergency and exit lights.

In the Emergency electrical configuration, DME 1 and Transponder 1 are inoperative with gear extension. This means that these radios cannot be used or operated when the gear is being extended.

In the Emergency electrical Power configuration with gear down and batteries powering the system, only ELAC 1 and SEC 1 flight control computers are operational. The other options, ELAC 1 and 2 SEC 1 and 2, and FAC 1, are not correct as they include additional flight control computers that are not operational in this specific configuration.

The crew should depress the guarded RMP NAV push button and tune the appropriate NAV facility and course for the approach to be accomplished. This is necessary in order to ensure that the navigation system is properly set up for the approach and that the aircraft will be able to navigate to the correct destination.

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The scape lights will automatically illuminate when the DC ESS SHED bus is not powered. This means that if there is a loss of power to the DC ESS SHED bus, the scape lights will turn on automatically.