A 320 ELECTRICAL SYSTEM

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

2.- 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?. A.- The EMER GEN is not yet supplying the system. B.- The RAT has failed. You will have to turn the batteries to OFF. C.- The FAULT light is always on when are in SLEC EMER CONFIG. D.- The RAT has failed. you have to try to reconnect both IDC/s.

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

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

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

6.- 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?. A.- Depress and hold the specific ECAM page push button on the ECAM control panel. B.- Transfer occurs automatically. C.- This is not possible. Use the cockpit operating manual.

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

22.- 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. A.- True. B.- False.

23.- How many times can you reset a circuit breaker?. A.- Once. B.- Once, if authorized by the procedures. C.- Twice. D.- Twice, if authorized by the procedures.

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

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

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

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

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

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

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

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

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

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

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

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

36.- Which flight control computer will be inoperative with gear extension while in the Emergency electrical Configuration?. A.- FAC 1 and ELAC 1. B.- SEC 1. C.- SEC 1 and ELAC 1. D.- FAC 1.

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

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

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

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

41.- An ACC ESSFEED switch located on the overhead panel shifts the power source for the AC ESS bus from: A.- AC bus 1 to AC bus 2. B.- AC bus 1 to AC Grnd/Fit bus. C.- AC bus 2 to AC bus 1.

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

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

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

45.- What is the priority of electrical sources?. A.- External power, Gen #1 and #2, APU. B.- APU, External power (if selected), Gen #1 and #2. C.- APU, Gen #2 or #2 or #1, External power (if selected). D.- Gen #1 or #2, External power (if selected), APU.

46.- Which of the following AC busses the emergency generator can power?. A.- AC bus 1. B.- AC bus 2. C.- AC ESS bus.

47.- The RAT is connected directly (mechanically) to the Emergency Generator. A.- True. B.- False.

48.- The engine generators and APU generator are rated at _______ KVA. A.- 50. B.- 90. C.- 45.

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

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

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

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

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

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

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

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

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

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

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

60.- The number 1 AC bus channel normally supplies power to ____ and to the _____ bus. A.- TR2/AC ESS SHED/DC ESS SHED. B.- TR1/AC ESS SHED / DC ESS. C.- TR1/AC ESS / AC ESS SHED. D.- TR1 /AC ESS / DC ESS SHED.

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

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

63.- Which of the following AC busses can be powered by the emergency generator?. A.- AC bus 1. B.- AC bus 2. C.- AC ESS bus / AC ESS SHED bus.

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

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

66.- The BATTERY BUS is normally powered by: A.- DC BUS 2. B.- DC BUS 1 and DC BUS 2. C.- DC bus 1 through a DC the control relay. D.- DC bus 2 through a DC the control relay.

67.- Which voltage requires recharging or replacing the batteries?. A.- 20 volts. B.- 24 volts or less. C.- 25 volts or less. D.- 26 volts or less.

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

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

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

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

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

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

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

75.- 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?. A.- External power is supplying ail electrical needs. B.- Engine Gen #l is supplying AC bus #l and the downstream systems, and AC bus #2 through the bus tie contactors. C.- Gen #I supplies AC bus #I and (generally) the downstream systems; Ext power supplies AC bus #2 .