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Airbus A330 > Electrical > Flashcards

Electrical Flashcards

1
Q

Electrical 3 areas:

A

Components, Controls and indications, Power supply priority

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2
Q

Electrical system AC three phase 115/ 200 v AC DC

A

28v

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3
Q

If all electrical power sources inoperative,

A

A STAT INV will convert battery DC to AC power

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4
Q

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

A

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

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5
Q

APU battery is reserved for

A

APU starting

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6
Q

All of circuit breakers on aircraft are located on

A

The electronic equipment bay

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7
Q

IDG power is

A

AC system

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8
Q

IDG = GEN (on ECAM) driven constant speed by

A

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

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9
Q

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

A

200v

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10
Q

APU GEN =

A

GEN 1 = 2

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11
Q

Generator Control Unit GCU

A

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

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12
Q

Overhead switches control

A

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

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13
Q

If GLC opens with Gen ON

A

FAULT displayed

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14
Q

If IDG disconnected

A

Only AzulTec reconnects on ground

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15
Q

Do not disconnect IDG if

A

Engine not running or windmilling

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16
Q

ECAM Low oil pressure IDG inhibited low

A

N3 less than 52% and N3 less than 52%

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17
Q

APU doesn’t supply electrical system powered by

A

Engine Driven Generators

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18
Q

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

A

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

19
Q

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

A

Use of the respective IDG pb

20
Q

AC Power system:

A

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

21
Q

ECMUs electrical Contactor Management Units are computers that enable electrical system

A

to reconfigure itself depending on availability of various power sources

22
Q

Synchronization may take up to

A

15 seconds for APU Gen with GPU

23
Q

The LAND Recovery AC BUS is powered by Emergency Operations when

A

LAND Recovery pb sw is ON

24
Q

If AC BUS 1 fails, the AC ESS BUS

A

is powered by AC BUS 2

25
Q

Bus TIE pb sw is normally in

A

AUTO position

26
Q

DC power systems are

A

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

27
Q

Transformer rectifiers convert

A

115v AC to 28v DC

28
Q

Fault light on BAT1 (2) pb sw illuminates when

A

Charging current for corresponding battery is outside limits

29
Q

A static inverter transforms DC power int

A

AC power which is supplied to part of AC ESS BUS

30
Q

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

A

Even if abnormal, during the engine start

31
Q

HOT BUS 1 and HOT BUS 2 are permanently

A

Connected to BAT 1 and 2 respectively

32
Q

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

A

Is amber

33
Q

DC LAND RCVRY BUS is normally

A

Supplied by DC ESS BUS

34
Q

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

A

external power is connected, but not in use.

35
Q

Aircraft ground power connectors are located

A

Aft of the nose wheel

36
Q

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

A

for ground servicing.

37
Q

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

A

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

38
Q

When RAT is being deployed EMER GEN light will indicate

A

FAULT in red momentarily

39
Q

EMER GEN TEST pb on EMER ELEC panel is used to

A

Test the Emergency Electrical system, for maintenance purposes only

40
Q

When in use, emergency generator is powered by

A

The green hydraulic system

41
Q

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

A

25.5v

42
Q

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

A

Switched off before checking voltage

43
Q

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

A

Pressed for no more than 3 seconds

44
Q

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

A

PFD and ND displays are lost.

Airbus A330 (33 decks)

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