TEST A320 SERIES

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 pouwer or the APU generator is activated. True. False.

When will the RAT & EMER GEN red FAULT light illuminate?. When the EMER GEN is not supplying electrical power, AC busses #1 & #2 are unpowered and the nose gear is up. When the RAT is deployed using hydraulic RAT MAN ON push button. Both are correct.

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

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

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

On the cockpit overhead panel, there is a three position EMERGENCY EXIT Light switch. What lights are associated with this switch?. Exit signs, emergency lights, 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 light.

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

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

While operating on Emergency Electrical Power with the landing gear lowered which of the following statements is correct?. 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. The APU will not start until the aircraft has come to a complete stop and all power has been removed for 15 seconds. If the APU is not operating it should be started at this time.

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.

While operating on Emergency Electrical Power (EMER GEN powering the system, FAC #1 reset) which of the following control laws are in effect?. Alternate. Manual and backup. Backup. Manual.

Can you reconnect an IDG in flight?. No, it is not possible. Yes, push and hold the IDG pb until the GEN fault light is no longer illuminated. Yes, but only after contacting maintenance control.

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

Which condition will automatically illuminate the escape lights?. DC ESS BUS not powered. DC ESS SHED bus not powered. Loss of power to the AC bus 1. AC ESS SHED bus not powered.

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.

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

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

Is it possible to determine the source of power for aircraft busses. Yes, press the ECAM ELEC push button and view the electrical schematic on the ECAM. Only when operating in the Emergency Electrical Configuration. No it is not possible. It is indicated on the electrical schematic overhead.

Both batteries are charged by the external power unit. Approximately how long does the charging process take?. 20 minutes. 30 minutes. 35 minutes. Between 30 and 45 minutes.

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

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

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

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

While operating on Emergency Electrical Power (EMER 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.

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

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 ESS AC SHED. ESS DC, ESS DC SHED, ESS AC and ESS AC SHED. The BATTERIES would power both HOT BATT busses, ESS DC and ESS AC through the STATIC INVERTER. The STATIC INVERTER would power both HOT BATT busses, ESS DC and ESS AC through the ESS AC SHED busses.

Engine #1 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?. Gen #1 supplies AC bus #1 and (generally) the downstream systems; Ext power supplies AC bus #2 . Engine Gen #1 is supplying AC bus #1 and the downstream systems, and AC bus #2 through the bus tie contactors. External power is supplying all electrical needs.

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 ELEC EMER CONFIG. The RAT has failed, you have to try to reconnect both IDG's.

When are the Essential Shed buses powered by the 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.

In normal electrical configuration, how is DC ESS bus supplied: From TR 1 via DC Bus 1 and DC Bat Bus. From ESS TR. From TR 2. From Bat 2.

What happens in case of total loss of main generators?. The RAT is automatically extended and powers the blue system which drives the emergency generator. The RAT is automatically extended and powers the yellow system which drives the emergency generator. The RAT is extended and mechanically connected to the emergency generator.

DC Bat Bus can be supplied by: DC Bus 1, DC Bus 2 or batteries. DC Bus 1 only. DC Bus 2 or batteries. DC Bus 1 or batteries.

Normal minimum battery voltage before APU start is: 25.5 Volts. 22.5 Volts. 27.5 Volts. No minimum.

When disconnecting the IDG the button should be pressed: For no more than 3 seconds. For longer than 3 seconds. Until the fault light goes out. For no more than 5 seconds.

Where can the battery voltage be checked?. On the elec. overhead panel and ECAM elec. Page. On the elec. overhead panel only. On the elec. overhead panel and ECAM E/WD. On the ECAM elec. Page only.

In flight on batteries only, the AC Ess Shed bus and DC Ess Shed bus are lost. Only D/C Ess Shed Bus is lost. Only A/C Ess Shed Bus is lost. Yes. No.

The static inverter works: When aircraft speed is > 50 kt and on batteries only. Only when generator 2 fails. When one main generator fails. Always.

If a TR fails: The other TR automatically replaces the faulty one and the ESS TR supplies the DC Ess Bus. The Emergency generator supplies DC power on the faulty side. The DC Bus on the faulty side is lost. The static inverter replaces the faulty TR.

In flight in case of loss of all main generators, emergency generator not running, the DC ESS Bus is supplied by: Hot bus 2. Ess TR. Hot Bus and Ess TR. Hot Bus 1.

If AC Bus 1 fails the AC Ess bus is supplied by. AC Bus 2. Static Inverter. The RAT. Emer Gen.