Electrical

Question 1

Electrical 3 areas:

Answer 1

Components, Controls and indications, Power supply priority

Question 2

Electrical system AC three phase 115/ 200 v AC DC

Answer 2

28v

Question 3

If all electrical power sources inoperative,

Answer 3

A STAT INV will convert battery DC to AC power

Question 4

Priority order for AC BUS 1 / AC BUS 2 – highest priority

Answer 4

Corresponding Engine Generators, APU generator / external power A, external power B, opposite engine generator

Question 5

APU battery is reserved for

Answer 5

APU starting

Question 6

All of circuit breakers on aircraft are located on

Answer 6

The electronic equipment bay

Question 7

IDG power is

Answer 7

AC system

Question 8

IDG = GEN (on ECAM) driven constant speed by

Answer 8

Integrated drive, supply electrical system with up to 115 kVa of three phase 115/200v power at 400Hz

Question 9

IDG – power normal electrical components at 115v and higher load such as hydraulic pumps at

Answer 9

200v

Question 10

APU GEN =

Answer 10

GEN 1 = 2

Question 11

Generator Control Unit GCU

Answer 11

Controls generator output, controls generator priority, protects generator and network, supplies indications and warnings

Question 12

Overhead switches control

Answer 12

Engine driven generators, their respective GCU and GLC Generator Line Contactors

Question 13

If GLC opens with Gen ON

Answer 13

FAULT displayed

Question 14

If IDG disconnected

Answer 14

Only AzulTec reconnects on ground

Question 15

Do not disconnect IDG if

Answer 15

Engine not running or windmilling

Question 16

ECAM Low oil pressure IDG inhibited low

Answer 16

N3 less than 52% and N3 less than 52%

Question 17

APU doesn’t supply electrical system powered by

Answer 17

Engine Driven Generators

Question 18

When aircraft on ground, engine not running, an amber FAULT on GEN 1 or 2 sw means

Answer 18

That generators are not operating, amber FAULT is normal on ground

Question 19

When IDG 1 or IDG2 malfunctions, it can be disconnected from the engine through the

Answer 19

Use of the respective IDG pb

Question 20

AC Power system:

Answer 20

AC power busses and Bus Tie Contactor, electrical contactor management unit ECMU, no break power transfer control NBPTC, controls and indicators

Question 21

ECMUs electrical Contactor Management Units are computers that enable electrical system

Answer 21

to reconfigure itself depending on availability of various power sources

Question 22

Synchronization may take up to

Answer 22

15 seconds for APU Gen with GPU

Question 23

The LAND Recovery AC BUS is powered by Emergency Operations when

Answer 23

LAND Recovery pb sw is ON

Question 24

If AC BUS 1 fails, the AC ESS BUS

Answer 24

is powered by AC BUS 2

Question 25

Bus TIE pb sw is normally in

Answer 25

AUTO position

Question 26

DC power systems are

Answer 26

Transformer rectifiers, aircraft batteries, static inverter, controls and indicators

Question 27

Transformer rectifiers convert

Answer 27

115v AC to 28v DC

Question 28

Fault light on BAT1 (2) pb sw illuminates when

Answer 28

Charging current for corresponding battery is outside limits

Question 29

A static inverter transforms DC power int

Answer 29

AC power which is supplied to part of AC ESS BUS

Question 30

APU TR voltage indication on ECAM ELEC DEC page remains green,

Answer 30

Even if abnormal, during the engine start

Question 31

HOT BUS 1 and HOT BUS 2 are permanently

Answer 31

Connected to BAT 1 and 2 respectively

Question 32

When DC BUS 1 / 2 are not powered, indication on ECAM ELEC DC page

Answer 32

Is amber

Question 33

DC LAND RCVRY BUS is normally

Answer 33

Supplied by DC ESS BUS

Question 34

When aircraft on ground, if EXT A or EXT B pb sw shows AVAIL illuminated in green

Answer 34

external power is connected, but not in use.

Question 35

Aircraft ground power connectors are located

Answer 35

Aft of the nose wheel

Question 36

MAINT BUS sw is used to power only the electrical systems used

Answer 36

for ground servicing.

Question 37

If both AC BUS 1 and AC BUS 2 are lost and both engines lose power,

Answer 37

The RAT automatically extends. RAT powers EMER GEN through green hydraulic system

Question 38

When RAT is being deployed EMER GEN light will indicate

Answer 38

FAULT in red momentarily

Question 39

EMER GEN TEST pb on EMER ELEC panel is used to

Answer 39

Test the Emergency Electrical system, for maintenance purposes only

Question 40

When in use, emergency generator is powered by

Answer 40

The green hydraulic system

Question 41

Preliminary cockpit preparation – aircraft not electrically supplied for 6 hours or more, check BAT 1, 2, APU BAT voltages for greater than

Answer 41

25.5v

Question 42

To check battery voltage for Bat 1, 2, APU bat, respective BAT switch must be

Answer 42

Switched off before checking voltage

Question 43

When disconnecting IDG when prompted by ECAM, IDG pb should be

Answer 43

Pressed for no more than 3 seconds

Question 44

When the electrical emergency configuration fault occurs, the lower ECAM, Captain’s ND and FO’s

Answer 44

PFD and ND displays are lost.