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A320-Electric > FCOM > Flashcards

FCOM Flashcards

1
Q

The electrical power system consists of

A

three-phase 115/200 V 400 Hz constant-frequency AC

system and a 28 V DC system.

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2
Q

The electrical power system is constituted

A

2 engine generators and 1 APU generator

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3
Q

GCU

A

Generators Control Units

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4
Q

The main functions of each GCU are :

A
  • Control the frequency and voltage of the generator output.

‐ Protect the network by controlling the associated generator line contactor.

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5
Q

GPCU

A

Ground Power Control Unit

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6
Q

What is the main function of GPCU?

A

Protects the network by controlling the external power contactor

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7
Q

GAPCU

A

Ground and Auxiliary Power Control Unit

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8
Q

What is the main function of GAPCU ?

A

Regulates, via the APU Electronic Control Box, the frequency and voltage of the APU generator.
Protects the network by controlling the external power contactor and the APU generator line contactor.

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9
Q

Which hydraulic system drives the emergency generator?

A

blue hydraulic circuit

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10
Q

What are the specific of emergency generator?

A

generator supplies 5 KVA of three-phase 115 and 200 V 400 Hz power

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11
Q

GCU

A

Generator Control Unit

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12
Q

/What are the main functions of GCU

A
  • Keeps the emergency generator at a constant speed,
  • Controls the generator’s output voltage,
  • Protects the network by the controlling the emergency generator line contactor, and
  • Controls the emergency generator start-up.
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13
Q

What STATIC INVERTER does?

A

A static inverter transforms DC power from Battery 1 into one KVA of single-phase 115 V 400 Hz AC power, which is then supplied to part of the AC essential bus

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14
Q

At what speed STATIC INVERTER activate?

A

When the aircraft speed is above 50 kt, the inverter is automatically activated, if only the batteries are supplying electrical power to the aircraft, regardless of the BAT 1 and BAT 2 pushbutton positions.

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15
Q

When the aircraft speed is below 50 kt, the inverter is activated, if

A

only the batteries are supplying electrical power to the aircraft, and both BAT 1 and BAT 2 pushbuttons are on

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16
Q

Explain TRs

A

Two main transformer rectifiers, TR 1 and TR 2, supply the aircraft’s electrical system, with up to 200 A of DC current.

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17
Q 
A third (identical) Transformer Rectifier, the ESS TR, can power the essential DC circuit from the
emergency generator, if
A

the engine and APU generators all fail, or if TR 1 or TR 2 fails.

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18
Q

How many batteries are installed?

A

Two main batteries, each with a normal capacity of 23 Ah, are permanently connected to the two hot buses.

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19
Q

BCL

A

Each battery has an associated Battery Charge Limiter

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20
Q

What is the main function of BCL?

A

The BCL monitors battery charging and controls its battery contactor

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21
Q

Monitored Green CBs

A

When out for more than 1 min, the C/B TRIPPED warning is triggered on the ECAM

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22
Q

Black CBs

A

Non-monitored

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23
Q

Yellow ring on CBs

A

there are yellow rings on the C/B’s, which must be pulled when flying on batteries only

24
Q

Wing Tip Brake (WTB) C/Bs

A

The Wing Tip Brake (WTB) C/Bs have red caps on them to prevent them from being reset.

25
Q

The flight crew can clear the ECAM C/B TRIPPED caution by pressing:

A

The EMER CANC pb: When pressed, this pushbutton clears and inhibits the ECAM C/B TRIPPED caution for the remainder of the flight, or
‐ The CLR pb: When pressed, this pushbutton only clears the ECAM C/B TRIPPED caution. If the C/B remains pulled, any additional tripped circuit breakers on the same panel will not be detected, and the ECAM will not trigger the caution. However, if the C/B is pushed, any additional tripped circuit breakers will be detected, and the ECAM will trigger the caution again.

26
Q

Priority of Generators ?

A

GEN 1 and 2 when operating have priority over the APU generator and over external power.
External power has priority over the APU generator when the EXT PWR pb switch is ON

27
Q

Each engine-driven generator supplies

A

its associated AC BUS (1 and 2) via its generator line

contactor (GLC 1 and GLC 2)

28
Q

AC BUS 1 normally supplies

A

the AC ESS BUS via a contactor

29
Q

TR 1 normally supplies

A

DC BUS 1, DC BAT BUS, and DC ESS BUS.

30
Q

TR 2 normally supplies

A

DC BUS 2.

31
Q

The two batteries are connected to the

A

DC BAT BUS, if they need charging. When they are fully charged, the battery charge limiter disconnects them.

32
Q

The system automatically replaces the failed generator, with the

A

APU GEN, if available, or

Other engine generator.

33
Q

FAILURE OF AC BUS 1

A

AC BUS 2 can supply AC ESS BUS, and ESS TR can supply DC ESS BUS, both via the AC ESS FEED pb. This is done automatically with the ACESS FEED Auto Switching
DC BUS 2 supplies DC BUS 1 and DC BAT BUS automatically after 5 s.

34
Q

FAILURE OF ONE TR

A

The other TR automatically replaces the faulty one.

The ESS TR supplies the DC ESS BUS

35
Q

The contactor of each TR opens automatically, in case of :

A

Overheat

Minimum current

36
Q

FAILURE OF TR 1 AND TR 2

A

DC BUS 1, DC BUS 2, and DC BAT BUS are lost. The DC ESS BUS is supplied by the ESS TR.

37
Q

If both AC BUS 1 and AC BUS 2 are lost and the aircraft speed is above 100 kt,

A

the Ram Air Turbine (RAT) extends automatically. This powers the blue hydraulic system, which drives the emergency generator by means of a hydraulic motor.

38
Q

The emergency generator supplies

A

the AC ESS BUS, and the DC ESS BUS via the ESS TR.

39
Q

What happen to emergency generator if we lower the landing gear?

A

the emergency generator is no longer powered, and the emergency generation network is automatically transferred to the batteries and the static inverter, and the system automatically sheds the AC SHED ESS and DC SHED ESS buses

40
Q

When the aircraft is on ground :

‐ Below 100 kt, DC BAT BUS is automatically connected to

A

the batteries

41
Q

When the aircraft is on ground :

Below 50 kt, AC ESS BUS is automatically

A

shed, leading to the loss of all display units

42
Q

On ground, if only the batteries are powering the emergency generation network, APU start is only available when the speed is

A

below 100 kt.

43
Q

SMOKE CONFIGURATION

A

In this configuration the main busbars are shed

44
Q

In smoke configuration the fuel pumps are connected upstream of the

A

GEN 1 line connector

45
Q

The batteries are connected to the DC BAT BUS in the following cases

A
  • APU starting (MASTER SW pb-sw at ON and N < 95 %).
  • Battery voltage below 26.5 V (battery charge). The charging cycle ends when battery charge current goes below 4 A.
  • Loss of AC BUS 1 and 2 when below 100 kt (EMER GEN not supplying).
46
Q

If AC BUS 1 and 2 are not energized and the EMER GEN is not supplying:

A
  • Battery 1 supplies the AC STAT INV BUS, and, if speed is greater than 50 kt, the AC ESS BUS.
  • Battery 2 supplies the DC ESS BUS.
47
Q

Automatic battery contactors open when:

A

‐ The aircraft is on the ground
‐ The BAT pb switches are at AUTO
‐ The main power supply (EXT PWR + GEN) is cut off
‐ Battery voltage is low.

48
Q

IDG oil outlet overheats (above

A

185 °C)

49
Q

GEN 1 (2) pb-sw FAULT light illimunated

A

Lights up amber, and an ECAM caution comes on, if:

  • The associated generator control unit (GCU) trips it.
  • Opening of the line contactor
50
Q

Battery voltage is normally green, but becomes amber if

A

V > 31 V or V < 25 V

51
Q

Battery current is normally green, but becomes amber if

A

discharge current > 5 A.

52
Q

DC BAT indication is normally in green. It becomes amber, if

A

DC BAT voltage ≤ 25 V

53
Q

The TR voltage is normally in green. It becomes amber, if

A

V > 31 V, or V < 25 V

54
Q

The TR current is normally in green. It becomes amber, when the

A

TR current ≤ 5 A.

55
Q

The IDG legend is normally white, but becomes amber, if:

A

Oil outlet temperature > 185 °C.
Oil pressure gets too low.
IDG becomes disconnected.

A320-Electric (1 decks)

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