Airbus A320
ELECTRICALS
(*Please refer the latest A320 Fcom, If any suggestion for improvement then please send us in comment box )
(Smart Aviator Android App users and Mobile Browser users please swipe left or right for next topic)
1.
Captain & F/O’s seats
in the cockpit.
·
Electrically and mechanically operated.
·
Only mechanically operated.
·
Only electrically operated.
·
As in (b) and shoulder harness has locking
facility.
2.
What happens to DC busses
when TR 1 fails ?
·
All busses are available by auto reconfiguration by using
TR 2 and ESS TR
·
DC BUS 1 DC BAT BUS are
lost
·
DC BUS 1 is lost.
·
DC BAT BUS is lost till
100 KTS
3.
Which busses are lost if
TR 1, TR 2 had failed?
·
No bus is lost.
·
DC BUS 1, DC BUS 2
·
DC BUS 1, DC BAT BUS, DC BUS 2
·
DC BAT BUS after landing
gear extension.
4.
After loss of all normal
generators when would SHED indication for AC & DC ESS
Busses appear on ELEC ECAM page ?
·
From the time all normal
generators had failed.
·
When landing gear is
extended.
·
During RAT extension
time.
·
When (b) and (c) are correct.
5.
In a flight, where APU is
not working what happens when GEN 1 falls.?
·
Most of the busses are
lost; only NO. 2 busses are available.
·
GEN 2 can feed all
busses.
·
As in (b) but main galley is shed automatically.
·
As in (a) and ESS TR will
come into use.
6.
In normal electrical
configuration (GEN 1, GEN 2 are ON) is there any of us that is not
energized.
·
Yes; AC STAT INV BUS
·
Yes; AC STAT INV BUS, AC
GND FLT BUS, DC GND FLT BUS
·
Yes; AC STAT INV BUS, AC
S
·
No.
7.
Which of the following is
NOT possible ?
·
APU GEN powering AC BUS 1 and the same time GPU powering
AC BUS
·
GEN 1 powering both AC
BUS 1 and AC BUS 2
·
GEN 1 powering AC BUS 1
and APU GEN powering AC BUS 2
·
GPU powering AC BUS 1 and
GEN 2 powering AC BUS 2.
8.
Out of the four possible
sources (GEN1 , 2, APU, GEN, EXT PWR) which has the least
·
priority to power AC BUS
2
·
APU GEN
·
EXT PWR
·
GEN 1
·
Whichever source is
selected last.
9. The engine generators and APU generator are
rated at _____ KVA.
·
50
·
70
·
90
·
110
10. The number 1 AC bus channel normally supplies
power to _____ and to the _____ bus which supplies power 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
11. The normal priority for supplying electrical
power to the AC busses is:
·
External power, engine generators then APU
·
External power, APU, then engine generators
·
APU, external power then engine generators
·
Engine
generators, external power then APU
12. 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.
13. The A-320 has _______ batteries in its main
electrical system.
·
1
·
2
·
3
·
3 (4 when ETOPS capable)
14. 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
·
BAT1 DC / AC ESS bus / DC ESS
15. An AC ESS FEED switch located on the overhead
panel shifts the power source for the AC ESS bus from:
·
AC bus1
to AC bus 2
·
AC bus 1 to AC Grnd/Flt bus
·
AC bus 2 to AC bus 1
16. 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
17. The RAT is connected directly (mechanically)
to the Emergency Generator
·
True
·
False
18. The emergency generator supplies power as long
as:
·
The
landing gear is down.
·
The RAT is deployed.
·
The RAT is deployed and the landing gear is
down
·
The landing gear is up.
19. After landing, in the emergency electrical
configuration: the batteries automatically connect to the DCBAT bus when speed
decreases below _______ knots.
·
50
·
70
·
90
·
100
20. The BAT FAULT light will illuminate when:
·
Battery voltage is low
·
Charging
current increases at an abnormal rate
·
Charging current decreases at an abnormal
rate.
21. Do not depress the IDG DISCONNECT switch for
more than _______ to prevent damage to the disconnect mechanism.
·
3
seconds
·
7 seconds
·
10 seconds
·
15 seconds
22. The IDG Fault light indicates:
·
An IDG oil overheat
·
IDG low oil pressure.
·
IDG low
oil pressure or IDG oil overheat
·
IDG has been disconnected
23. If normal electrical power is lost; essential
cockpit lighting is maintained for the:
·
Captain's instrument panel.
·
Standby compass
·
Right
dome light (provided the dome selector is not off).
·
All of the above.
24. 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.
25. 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.
26. 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 limitation
·
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 than 3 seconds.
27. Which voltage requires recharging or replacing
the batteries?
·
20 volts or less.
·
24 volts or less.
·
25
volts or less.
·
26 volts or less.
28. The APU is supplying the electrical system.
What is the order of priority for the different generators?
·
Engines,
external power, APU.
·
APU, engines, external power.
·
External power, engines, APU.
·
APU, external power, engines.
29. What is the significance of the green collared
circuit breakers?
·
Green collared circuit breakers are pulled
when flying on battery power only.
·
Green
collared circuit breakers are monitored by the ECAM.
·
Green collared circuit breakers are not to be
reset.
·
Green collared circuit breakers are AC
powered.
30. With the EMER EXIT LT selector in the ARM
position, which situation will activate the emergency lights and exit signs?
·
AC SHED bus unpowered
·
AC bus
#1 unpowered
·
DC ESS SHED bus unpowered
·
DC bus #2 unpowered
31. 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.
32. What is the minimum voltage when conducting a
BATTERY CHECK?
·
28 volts.
·
Less than 60 amps in 10 seconds.
·
Greater
than 25 volts.
·
Greater than 25 volts.
33. 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.
34. 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
35. 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.
·
I have to switch the external power to ON and
switch the batteries off.
·
I have to start the APU as the batteries can
only be charged by the APU generator.
36. 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.
37. 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.
38. While operating on Emergency Electrical Power
with the landing gear lowered which of the following control laws is in effect?
·
Backup.
·
Direct.
·
Alternate.
·
Backup or alternate
39. 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.
40. 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 busses.
·
When
selected OFF generator # 1 is removed from all busses but continues to power
one fuel pump in each wing.
41. During a routine flight, which of the
following would result after the loss of Gen #2 and the subsequent 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 restowed.
·
Eng gen #1 continues to power AC bus
#1 and downstream systems. The APU powers AC bus #2 and downstream systems.
42. 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.
43. During the five seconds it takes for the RAT
to extend:
·
the BATTERIES power both BATT HOT busses, ESS
DC SHED, and ESS AC SHED 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
busses, ESS DC, and ESS AC through the ESS AC SHED busses.
·
The BATTERIES power both BATT HOT busses.
44. 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.
45. 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.
46. 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.
·
They are mainly AC powered.
47. 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.
48. How many times can you reset a circuit
breaker?
·
Once.
·
Once,
if authorized by the procedures.
·
Twice.
·
Twice, if authorized by the procedures.
49. 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.
50. 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.
51. 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.
52. While operating on Emergency Electrical Power
with the landing gear lowered which 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.
53. 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.
54. While operating on Emergency Electrical Power
(EMER GEN powering the system, FAC #1 reset) which of the following control
laws are in effect?
·
Manual
·
Alternate.
·
Backup
·
Manual and backup
55. 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, it
is not possible.
56. 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.
57. Which condition will automatically illuminate
the escape lights?
·
AC ESS SHED bus not powered.
·
Loss of power to the AC bus 1.
·
DC ESS
BUS not powered.
·
DC ESS SHED bus not powered.
58. 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
59. 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.
60. If EXTERNAL power is available and within
limits:
·
It will automatically close the bus tie
contactors's when connected by the ground crew.
·
The
green AVAIL light will illuminate on the EXT PWR push button.
·
The BUS TIE push button illuminates.
61. Is it possible to determine the source of
power for aircraft busses
·
It is indicated on the electrical schematic
overhead.
·
No it is not possible.
·
Yes,
press the ECAM ELEC push button and view the electrical schematic on the ECAM
·
Only when operating in the Emergency
Electrical Configuration.
62. Both batteries are charged by the external
power unit. Approximately how long does the charging process take?
·
10 minutes.
·
20
minutes.
·
30 minutes.
·
Between 30 and 45 minutes.
63. While operating on Emergency Electrical Power
(EMER GEN 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 beaccomplished.
·
Both are correct.
64. The GALLEY FAULT light illuminates when any
generator is exceeding 80% of its rated output.
·
True.
·
False.
65. 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.
66. 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.
67. 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.
68. 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.
·
It is a
reminder that the main galley has been shed automatically following the loss of
one generator.
69. 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.
·
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 SHED.
70. 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?
·
External power is supplying all electrical
needs.
·
Engine Gen #1 is supplying AC bus #1 and the
downstream systems, and AC bus #2 through the bus tie contactors.
·
Gen #1
supplies AC bus #1 and (generally) the downstream systems; Ext power supplies
AC bus #2 .
71. 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.
72. 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
73. The AC Essential bus is powered by the battery
at speed above 50 kt.
·
True.
·
False.
74. 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
75. What happens in case of total loss of main
generators?
·
The RAT is automatically extended and powers
the yellow system which drives the emergency generator
·
The RAT
is automatically extended and powers the blue system which drives the emergency
generator
·
The RAT has to be manually extended
·
The RAT is extended and mechanically connected
to the emergency generator.
76. DC Bat Bus can be supplied by:
·
DC Bus 1 or batteries
·
DC Bus
1, DC Bus 2 or batteries
·
DC Bus 2 or batteries
·
DC Bus 1 only
77. Normal minimum battery voltage before APU
start is:
·
No minimum
·
27.5 Volts
·
25.5
Volts
·
22.5 Volts
78. When disconnecting the IDG the button should
be pressed:
·
For no more than 5 seconds
·
Until the fault light goes out
·
For longer than 3 seconds
·
For no
more than 3 seconds
79. Where can the battery voltage be checked?
·
On the ECAM elec. Page only
·
On the elec. overhead panel and ECAM E/WD
·
On the elec. overhead panel only
·
On the
elec. overhead panel and ECAM elec. Page
80. In flight on batteries only, the AC Ess Shed
bus and DC Ess Shed bus are lost.
·
Yes
·
No
·
Only A/C Ess Shed Bus is lost
·
Only D/C Ess Shed Bus is lost
81. The static inverter works:
·
Always
·
When
aircraft speed is > 50 kt and on batteries only.
·
When one main generator fails
·
Only when generator 2 fails
82. If a TR fails:
·
The
other TR automatically replaces the faulty one and the ESS TR supplies the DC
Ess Bus
·
The static inverter replaces the faulty TR
·
The DC Bus on the faulty side is lost
·
The Emergency generator supplies DC power on
the faulty side.
83. 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
·
Emer Gen.
·
The RAT
·
Static Inverter
·
AC Bus
2
----------------------------------www.smartaviators.com-------------------------------
For Latest Updates please Download our Smart Aviators Android App.
Please click on above link to download the App.
* Instructions for installation
1. Click on➤ Smart Aviators link and Open with Google Drive.
2. Download the App in .apk extension file.
3. Find the setup file (Smart Aviators App.apk) in download folder of your phone or Tablet.
4.Open this file.
5. For Security Permission open settings then click on Unknown sources.
6. Now Click on INSTALL.
7. ENJOY Learning.
I am truly pleased to read this information which carries lots of helpful data. Shop BOGE Nitrogen Generators Ontario at the reasonable cost from Cruairgas.com.
ReplyDeleteI am amazed by the details that you have shared here about electrical. It is a great source to enhance information for us. Keep sharing this kind of articles, Thank you. commercial electrical contractor Denver
ReplyDeleteThe details you've shared here is extremely instructive because it contains some best knowledge which is extremely helpful on behalf of me. Thanks for posting it.Electrical Outlet Box
ReplyDelete