ELECTRICAL SYSTEM A320

If the battery voltages are below the minimum, how do you charge them?. You have to call a mechanic because the batteries can lonly be charged by maintenance. I have to check that the BAT pushbuttons are on and switch the external power on.

In cruise, you have suddenly a Master Warning and caution comes on with ELEC EMER CONFIG and APP OFf. You notice a red FAULT light on the RAT & EMER GEN pushbutton. What do you think of this indication?. The EMER GEN is not yet supplying the system. The RAT has failed. You will have to turn the batteries to OFF. The FAULT light is always on when are in SLEC EMER CONFIG. The RAT has failed. you have to try to reconnect both IDC/s.

When are the Essential Sheed buses powered by his battery?. Never. The purpose of the shed buses is to reduce the load on the batteries. In case of double generator failure. After every IDG connection.

The AC Essential bus is powered by the battery at speed above 50 kt. True. False.

While operating on Emergency Electrical Power (EMER CEN powering the system) what should the crew accomplish prior to lowering the landing gear?. Check to see that the FMGC has auto tuned the appropriate NAV facility for the approach to be accomplished. Depress the guarded RMP NAV push button and tune the appropriate NAV facility and course for the approach to be accomplished. Both are correct.

While operating on Emergency Electrical Power (EMIR GEN powering the system) how is it possible to properly complete the ECAM checklist with only an upper display?. Depress and hold the specific ECAM page push button on the ECAM control panel. Transfer occurs automatically. This is not possible. Use the cockpit operating manual.

The GALLEY FAULT light illuminates when any generator is exceeding 80% of its rated output. True. False.

What is the meaning of the green AVAIL light?. External power is plugged in and parameters are normal. You must push the external power to connect it. External power is available to the batteries only. The external power panel door has been opened. External power is supplying the aircraft systems.

After IDG disconnection why do you get a GALLEY SHED indication on the SD?. It is a reminder to push the GALLEY pushbutton to manually shed the main galley. It is a reminder to get the flight attendants to switch off galley equipment to decrease the load on the remaining generator. If it is a reminder that the main galley has been shed automatically following the loss of one generator.

Which busses will be powered after the RAT is extended and the EMER GEN begins producing power?. BATT HOT busses, ESS DC, ESS DC SHED, ESS AC and 3SS AC SHED. The STATIC INVERTER would power both HOT The STATIC INVERTER would power both HOT BATT busses, ESS DC and ESS AC through the ESS AC SHED busses. The BATTERIES would power both HOT BATT busses, ESS DC and ESS AC through the STATIC INVERTER. ESS DC, ESS DC SHED, ESS AC and ESS AC SXED.

What does the blue EXT PWR ON light mean?. External power is plugged in and parameters are normal. External power is supplying the aircraft s electrical system. There is a fault with the external power.

If EXTERNAL POWER is available and within limits: It will automatically close the bus tie contactors when connected by the ground crew. The green AVAIL light will illuminate on the EXT PWR push button. The BUS TIE push button illuminates.

Both batteries are charged by the external power unit. Approximately how long does the charging process take?. l0 minutes. 20 minutes. 30 minutes. between 30 & 45 minutes.

While operating on Emergency Electrical Power (EMER GEN powering the system, FAC #l reset) which of the following control laws are in effect?. Manual. Alternate. Backup. Manual and backup.

On the cockpit overhead panel, there is a three positions EMERGENCY EXIT LIGHT SWITCH. What lights are associated with this switch. Exit signs, emergency ligths, and escape path lighting. Exit signs, emergency lights, main panel flood lights, and escape path lighting. Exit signs, emergency lights, dome lights, main panel flood lights, and the standby compass lights.

Which radios are inoperative with gear extension while in the emergency electrical configuration?. DME 1 and transponder 1. DME 1, DDRM1, and transponder 1. DME, and transponder. ILS 2 DME, and ADF.

If during a normal flight the BUS TIE push button is depressed to OFF, what effect would this have on power to the busses?. None. All power would be lost and the aircraft would be powered by the batteries until the RAT was up to speed. The power transfer would switch to the opposite bus. This is not possible as the bus tie contactors are locked out during flight.

Which communication and navigation radios are operational in the Emergency Electrical Configuration with the EMER GEN powering the system?. ACP l and 2, VHF 1, HF, RMP l, VOR l, and lLS l. VHF l, RMP l, VOR l. RMP #t &. #2, VHF #1, HF (if equipped), ACP #1, VOR#1 and ILS #:. All radios are lost.

While operating on Emergency Electrical Power with the landing gear lowered witch of the following statements is correct?. If the APU is not operating it should be started at this time. The APU will not start until the aircraft has come to a complete stop and all power has been removed for 15 seconds. On the ground at 100 knots, the DC BATTERY BUS automatically reconnects to the batteries allowing APU start. At 70 Knots ESS AC is disconnected from the batteries.

Which flight control computers are operational in the emergency electrical power configuration (gear down and batteries powering the system)?. All are operational. ELAC 1, SEC 1 and FAC 1. ELAC 1 and 2, SEC 1 and 2 FAC 1. ELAC 1 and SEC 1.

During the five seconds it takes for the RAT to extend: the BATTERIES power both BATT HOT busses, 3SS DC SHED, and ESS AC SHFD through the STATIC INVERTER. The BATTERIES power both BATT HOT busses, ESS DC, and ESS AC through the STATIC INVERTER. The STATIC INVERTER powers both BATT HOT busseso ESS DC, and ESS AC through the ESS AC SHED busses. The BATTERIES power both BATT HOT busses.

The purpose of the AUTO BUS TIE is to allow either engine-driven IDG to automatically power both main AC buses in the event of a generator loss until either ground power or the APU generator is activated. True. False.

How many times can you reset a circuit breaker?. Once. Once, if authorized by the procedures. Twice. Twice, if authorized by the procedures.

When does the RAT automatically deploy?. With the loss of two hydraulic systems. Electrical power to both AC BUS #l & #2 is lost and the aircraft speed is above 100 knots. Both are correct.

What is the significance of the circuit breakers on the overhead panel?. They are not monitored by ECAM. Cannot be reset. They may be operational in the Emergency Electrical Configuration.

If both engine generators are powering the system, and one subsequently fails are any busses unpowered?. Only the AC ESS shed bus. No, but some loads are shed in both main galleys. Yes, those associated with the failed generator.

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

During a routine flight, wich of the following would result after the loss of Gen #2 and the subsequend start of the APU?. The APU would now power both sides of the electrical system. All systems return to normal and the RAT must be restored. Eng gen #1 continues to power AC bus #1 and downstream systems. The APU powers AC bus #2 and downstream systems.

Is it possible to parallel generators?. Of course yes. Only with the RAT deployed. The electrical system will not allow "paralleling" of generators. Only one engine generator may be paralleled with the APU.

While operatig on Emergency Electrical Power with the landing gear lowered wich of the fllowing control laws is in effect?. Backup. Direct. Alternate. Backup or alternate.

A batteryfault light will illuminate when: The batteries have auto disconnected due to low voltage. Battery voltage drops below a predetermined level. Battery charging current increases at an abnormal rate.

What is the function of APU GEN push button located on the overhead electrical panel?. Push this button to automatically start the APU. When selected to OFF the APU generator field is de-energized. Both are correct.

After landing, in the emergency electrical configuration: the batteries automatically connect to the DC BAT bus when speed decreases below _____ knots. 50. 70. 90. 100.

If normal electrical power is lost; essential cockpit lighting is maintanired for the: Captain\'s instrument panel. Standby compass. Right dome light (provided the dome selector is not off). All of the above.

You enter a dark cockpit, what action is necessary before checking the battery voltages?. You have to check that the external power is on. You have to ensure that at least one battery is on. You have to ensure that both batteries are on. You have to verify that both batteries are off.

Which flight control computer will be inoperative with gear extension while in the Emergency electrical Configuration?. FAC 1 and ELAC 1. SEC 1. SEC 1 and ELAC 1. FAC 1.

Are there any limitations associated with disconnecting an IDG?. Never disconnect an IDG in flight, or push the IDG disconnect push button for more then 30 seconds. There is no limitations. Never disconnect an IDG in flight, or push the IDG disconnect push button for more then 5 seconds. Never disconnect an IDG unless the engine is running nor push the IDG disconnect push button for more then 3 seconds.

If batteries are the only source of power in flight, how long will battery power be available?. Between 22 and 30 minutes depending on equipment in use. Until the APU is started. Two hours and 30 minutes dependent on equipment in use. 45 minutes dependent on equipment in use.

If the battery voltages are below the minimum, how do you charge them?. You have to call a mechanic because the batteries can only be charged by maintenance. I have to check that the BAT pushbuttons are on and switch the external power on.

Which flight control computers are operational in the emergency electrical power configuration (gear down and batteries powering the system)?. All are operational. ELAC 1, SEC 1 and FAC 1. ELAC 1 and 2, SEC 1 and 2 FAC 1. ELAC 1 and SEC 1.

An ACC ESSFEED 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.

The number 1 AC bus channel normally supplies power to __________, and to the __________ bus. TR1, DC 1. TR1, AC ESS. None of above.

The normal priority for supplying electrical power to the AC busses is: External power, engine generators, APU. APU, external power, engine generators. Engine generators, external power, APU.

The A-320 has _______ batteries in its main electrical system. 1. 2. 3.

What is the priority of electrical sources?. External power, Gen #1 and #2, APU. APU, External power (if selected), Gen #1 and #2. APU, Gen #2 or #2 or #1, External power (if selected). Gen #1 or #2, External power (if selected), APU.

Which of the following AC busses the emergency generator can power?. AC bus 1. AC bus 2. AC ESS bus.

The RAT is connected directly (mechanically) to the Emergency Generator. True. False.

The engine generators and APU generator are rated at _______ KVA. 50. 90. 45.

The DC BAT BUS is normally powered by: The A-320 has ______ batteries in its main electrical system. DC BUS 2. Batteries. DC BUS 1.

For the A-320 the emergency generator supplies power as logn as RAT is deployed and: The landing gear is down. If the RAT stalls or if the aircraft is on the ground with the speed below 100 kts. The landing gear is up.

If EXTERNAL power is available and within limits: It will automatically close the bus tie contactors when connected by the ground crew. The green AVAIL light will illuminate on teh EXT PWR push button. The BUS TIE push button illuminates. None of the above.

If both engine generators are powering the system, and one subsequently fails. are any busses unpowered?. Only the AC ESS shed bus. No, but some loads are shed in both main galleys. Yes, those associated with the failed generator.

Do not depress the IDG DISCONNECT switch for more than _____ to prevent damage to the disconnect mechanism. 3 seconds. 10 seconds. 15 seconds.

The IDG Fault light indicates: An IDG oil overheats. IDG low oil pressure. IDG has been disconnected. Either A or B.

Is it posible to determine the source of power for aircraft busses?. It is indicated on the electrical schematic overhead. No. Only when operating in the Emergency Electrical Configuration. Yes, press the ECAM ELEC push button and view the electrical shematic on the ECAM.

Can you reconnect an IDG in flight?. Yes, but only after contacting maintenance control. Yes,push and hold the IDG pb until the GEN fault light is no longer illuminated. No. None of the above.

If batteries are the only source of power in flight, how long will battery power be available?. Between 22 and 30 minutes depending on equipment in use. Until the APU is started. Two hours and 30 minutes dependent on equipment in use. 45 minutes dependent on equipment in use.

What is the significance of the circuit breakers on the overhead panel?. They are not monitored by ECAM. Cannot be reset. They may be operational in the Emergency Electrical Configuration.

When does the RAT automatically deploy?. With the loss of two hydraulic systems. Electrical power to both AC BUS #1 & #2 is lost and the aircraft speed is above 100 knots. Both are correct.

The number 1 AC bus channel normally supplies power to ____ and to the _____ bus. TR2/AC ESS SHED/DC ESS SHED. TR1/AC ESS SHED / DC ESS. TR1/AC ESS / AC ESS SHED. TR1 /AC ESS / DC ESS SHED.

When no other power is available in flight, the static inverter converts power to AC power for the ____ bus, and _____ powers the _____ bus. BAT1 DC /AC ESS bus /BAT2 /DC ESS. BAT1 DC / AC ESS SHED /BAT2 /DC ESS SHED. BAT1 DC / AC ESS bus /BAT2 /DC ESS SHED.

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 1. AC bus 2. AC ESS bus / AC ESS SHED bus.

The BAT FAULT light will illuminate when: Battery voltage is low. Charging current increases at an abnormal rate. Charging current decreases at an abnormal rat.

Having starting the APU, how can you get the APU generator to power the electrical system?. The APU generator must be switch on. By pushing the EXT PWR pushbutton thus disconnecting the external power. By pushing the BUS TIE pushbutton. you are unable to as the APU power output is outside normal parameters.

The BATTERY BUS is normally powered by: DC BUS 2. DC BUS 1 and DC BUS 2. DC bus 1 through a DC tie control relay. DC bus 2 through a DC tie control relay.

Which voltage requires recharging or replacing the batteries?. 20 volts. 24 volts or less. 25 volts or less. 26 volts or less.

What is the minimum voltage when consulting a BATTERY CHECK?. 28 volts. Less than 60 amps in 10 seconds. Greater than 25 volts.

A battery fault light will illuminate when: The batteries have auto disconnected due to low voltage. Battery voltage drops below a predetermined level. Battery charging current increases at an abnormal rate.

What cockpit lighting is available during an emergency electrical situation?. Emergency path lighting only. Right side Dome light, main panel flood lights (left two columns only), and the standby compass light. Located on normal circuit breaker panels. Right side dome light, main panel flood lights, and the standby compass light.

When will the RAT & EMER GEN red FAULT light momentary illuminates?. When the EMER CEN is not supplying electrical power, AC busses # I &. #2 are unpowered and the nose gear is up. When the RAT is deployed using hydraulic RAT MAN ON push button. Both are correct.

While operating on Emergency Electrical Power with the landing gear lowered witch of the following control laws is in effect?. Backup. Direct. Alternate. Manual and backup.

What would cause the GALLEY fault light to illuminate?. The flight attendants have all the coffee makers and ovens on at once. The Main Galley has shed. The load on any generator is above 100% of its rated output. The Aft Galley has shed.

If the source of power for the ESS AC bus is lost, does another source of power automatically power the bus?. Yes, transfer is automatic. Yes, only if AUTO was selected on the AC ESS FEED push button. No, this must be done by the crew.

Engine #l has just been started and the APU is inoperative. The EXT PWR push button blue ON light is illuminated. Which of the statements below is correct?. External power is supplying ail electrical needs. Engine Gen #l is supplying AC bus #l and the downstream systems, and AC bus #2 through the bus tie contactors. Gen #I supplies AC bus #I and (generally) the downstream systems; Ext power supplies AC bus #2 .