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 .
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