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4. Systems > 24. Electrical > Flashcards

24. Electrical Flashcards

1
Q

What are the specifications of the DC System?

A

28 Volts

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2
Q

What are the ratings of the Engine & APU Driven Gens and the Emergency Gen?

A

Engine & APU Driven : 90 kVA

Emergency Generator : 5 kVA

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3
Q

How is the Emergency Generator driven?

A

By the Blue Hydraulic System.

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4
Q

How is constant frequency obtained from the Engine & APU Driven Generators?

A

IDGs : Integrated (Constant Speed) Drive Units

APU : Constant Speed APU

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5
Q

The Static Inverter can supply the AC ESS Busbar.

What is its Source & what does it supply?

A

Source : Battery 1

Supplies : (part of) the AC ESS Bus

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6
Q

When will the Static Inverter be Energised from the Battery even if the Battery Switch is OFF?

A

If Aircraft speed exceeds 50 kts AND the only source of power is the Batteries,

Battery 1 will supply the Static Inverter irrespective of Battery p/b position.

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7
Q

How many TRs are there?

A

3

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8
Q

How many amps can a TR supply?

A

200 Amps

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9
Q

In Normal Operations which TRs are in use?

A

TR1 and TR2 only.

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10
Q

How many batteries are there?

A

2

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11
Q

What is a BCL?

A

Battery Charge Limiter

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12
Q

What do the following colours on Cb collars mean:

  • Green
  • Black
  • Red
  • Yellow?
A

Green - Monitored by ECAM

Black - Not ECAM Monitored

Red - Must not be pulled

Yellow - may be pulled when on batteries only (Early A320 only.)

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13
Q

At any one time there my be 4 main sources of AC Power available :

  • GEN1, GEN2, APU GEN & EXT PWR.

What is the order of Preference of Supply?

A

To either AC Bus,

  1. Onside GEN, then
  2. EXT PWR (if EXT PWR p/b pressed), then
  3. APU, finally
  4. Offside GEN.
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14
Q

Can any of the electrical sources be connected in parallel?

A

NO.

The Bus Ties will prevent this.

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15
Q

In Normal Operations, which AC Busbars are supplied by GEN1 and GEN2?

A

GEN1: AC1 and through AC1 the ESS AC.

GEN2 : AC2

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16
Q

In Normal Operations, how are the TRs supplied?

A

TR1 supplied from AC1

TR2 supplied from AC2

ESS TR is not in use.

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17
Q

In Normal Operations what do the TRs supply?

A

TR1 supplies : DC Bus 1, Battery Bus (through DC1) and ESS DC (through Battery Bus)

TR2 supplies : DC Bus 2

ESS TR supplies : nothing

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18
Q

In Normal Operations, what do the Batteries supply?

A

Just the Hot Battery Busbars.

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19
Q

What is the Normal Source of supply of the “Battery” Busbar?

A

TR1

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20
Q

When the AC and DC GROUND/FLIGHT busses are being supplied directly from EXT PWR, does EXT PWR also power the rest of the aircraft Electrical System?

&

What component of the Electrical System is also required to enable DC GROUND/FLIGHT to be energised?

A

NO

&

TR2

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21
Q

In Normal Operations are the AC and DC GROUND/FLIGHT busses powered and if so from what source?

A

YES

AC from AC2

DC from DC BUS 2

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22
Q

If GEN1 or GEN2 fails in flight, what pilot action is required to ensure that Supplies are maintained to the Electrical System?

A

None.

The opposite generator, or the APU Gen will replace the failed generator automatically.

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23
Q

If AC1 Fails, what pilot action is required to regain supply to it?

A

If it does not automatically recover, Use the AC ESS FEED p/b.

This connects AC ESS to AC2 rather than AC1 and hopefully restores it.

AC BUS 1 normally supplies the AC ESS BUS, and, via the TR1, the DC ESS BUS.
In the case of an AC BUS 1 FAULT, the AC ESS BUS and the DC ESS BUS will automatically recover, due to the fact that the AC BUS 2 will automatically supply the AC ESS BUS.
If AC BUS 2 does not automatically supply the AC ESS BUS, the flight crew can recover the AC ESS BUS and the DC ESS BUS by setting the AC ESS FEED pb-sw to ALTN, as requested by the AC ESS BUS FAULT ECAM procedure.

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24
Q

What are the specifications of the AC System?

A

3 phase

115/200 Volts

400 Hz

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25
Q

How is DC power generated?

A

Two transformer rectifiers one from each AC BUS supply up to 200A of DC current.
A third TR (ESS TR) can power DC circuit from the emergency generator.
Batteries connected permanently to two hot buses.

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26
Q

Which CB’s are monitored?

A

Green monitored, black not.
Be aware that other tripped Cb’s may not cause additional warnings.

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27
Q

Minimum battery voltage before recharge required.

A

25.5V

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28
Q

How is the AC generated?

A

2 engine driven generators, 90kVa 115/200V 400 hz
APU gen and external power
Emergency generator 5 kva 115/200V 400hz
Static inverter transforms from battery 1, 1kva 115/200V to AC ESS BUS.

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29
Q

Can you reengage a C/B in flight which has tripped by itself?

Which C/Bs can you never re-engage?

A

Green c/b’s monitored, black not.

In flight, do not reengage a C/B that has tripped by itself, unless the Captain judges it necessary to do so for the safe continuation of the flight. This procedure should be adopted only as a last resort, and only one reengagement should be attempted.
On ground, do not reengage the C/B of the fuel pump(s) of any tank. For all other C/Bs, if the flight crew coordinates the action with maintenance, the flight crew may reengage a tripped C/B, provided that the cause of the tripped C/B is identified.
Also the wing tip brakes have red caps to stop them being reset.

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30
Q

How many generators (including APU) can power all electrical needs?

A

1

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31
Q

In flight, during generator failure, what is automatically shed?

A

Main galley power

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32
Q

What is the main difference between when Gen 1 fails versus Gen 2?

A

Gen 1 is connected to the Essential Bus and Shed while Gen 2 requires the AC ESS FEED button depressed

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33
Q

When RAT deploys, what does it power?

A

AC and DC ESS BUS and SHED

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34
Q

In an emergency what does BATT 1 power?

A

AC ESS BUS through inverter

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35
Q

In an emergency what does BATT 2 power?

A

DC ESS BUS

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36
Q

What are the electrical priorities?

A

G enerators
E xternal Power
A pu generator
R am air turbine
B atteries

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37
Q

What are the capacities of the generators and the APU?

A

90 KVA
3 phase
115-200 V
400 Hz

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38
Q

What are the capacities of the emergency generator?

A

5 KVA
3 phase
115-200 V
400 Hz

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39
Q

What do the (TR) transformer-rectifiers do?

A

Convert AC to DC

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40
Q

When will you see a green arrow connected to the battery?

A

only when current is >1 amp

41
Q

What are the limitations for the IDG FAULT buttons?

A

Do not depress more than 3 seconds.
Engine must be running or windmilling
Can be reset on ground only

42
Q

When will you get the IDG FAULT light on?

A

High IDG oil temp
Low IDG oil pressure

43
Q

When will the batteries start charging?

A

<26.5V

44
Q

When will the battery contactors close?

A

AC BUS 1&2 not powered by other sources (no EMER GEN during flight, worst case)

45
Q

When will the auto batt cut-off?

A

Ground
BAT in AUTO
AC power source N/A
Batt voltage low
(reset by cycling BAT buttons)

46
Q

How long are batteries prevented from charging after APU start?

A

30 minutes

47
Q

During preflight, what white lights should be present on the ELEC panel?

A

None!

48
Q

When you turn on the battery what is the max charging current allowed?

A

<60A and decreasing within 10 seconds

49
Q

What tells you that the APU is powering the AC?

A

AVAIL light on the APU START button AND AVAIL light on the EXT POWER button

50
Q

When you start engine 2, what happens to the bus tie?

A

Opens, APU now powers BUS 1 and Generator powers BUS 2

51
Q

RAT & EMER GEN FAULT light is on, what does this mean?

A

The RAT takes 8 seconds to spool up before coming on-line, during this time you are running off the batteries.

52
Q

What is the min speed for the RAT to function?

A

140kts

53
Q

During landing, at what speed does the EMER GEN become unavailable?

A

125kts

54
Q

What happens below 50kts during total electrical failure?

A

All displays blank
Braking and engine control
VHF1
NO nosewheel steering

55
Q

How long is the APU start inhibit when going into emergency electric configuration?

A

45 seconds

56
Q

What does the electrical system consist of?

A

Three phase 115/200V 400Hz AC system

And 28V DC system

57
Q

How long does RAT extension and coupling take?

A

8 seconds

58
Q

What is the minimum offline battery voltage?

A

25,5V

59
Q

How long can the batteries provide emergency power

A

Approximately 30 minutes

60
Q

What will happen if a single engine driven generator is lost and no APU generator available?

A

Shed part of the galley load and route power from other engine driven generator.

61
Q

At what speed will the rat stall?

A

140kts

62
Q

What are the functions of the GCUs? (Generators control units)

A

Control the output (freq and voltage) of their generator.

Protect the network by controlling the generator line contractor (GLC)

63
Q
  1. (DSC-24-10) In normal electrical configuration, how is DC ESS bus supplied;
    (a) From TR 1 via DC bus 1 and DC Bat Bus
    (b) From ESS TR. (c) From TR 2. (d) From Batt 2.
A

(a) From TR 1 via DC bus 1 and DC Bat Bus

64
Q
  1. (DSC-24-10) What happens in case of total loss of main generators;
    (a) The Rat is automatically extended and powers the yellow system which drives the emergency generator.
    (b) The Rat is automatically extended and powers the blue system which drives the emergency generator.
    (c) The Rat has to be manually extended.
    (d) The Rat is extended and mechanically connected to the emergency generator.
A

(b) The Rat is automatically extended and powers the blue system which drives the emergency generator.

65
Q
  1. (DSC-24-10) the electrical power system consists of
    (a) A three phase 115/200 volt 400 hertz constant frequency AC system and a 28 DC system
    (b) A three phase 180/220 volt 400 hertz constant frequency system and a 28 volt DC system

(c) A three phase 115/220 volt 400 hertz constant frequency system and a 28 volt DC system
(d) A three phase 115/200 volt 400 hertz constant frequency DC system and a 28 volt AC system

A

(a) A three phase 115/200 volt 400 hertz constant frequency AC system and a 28 DC system

66
Q
  1. (DSC-24-10) Dc Bat bus can be supplied by;
    (a) DC Bus 1 or batteries. (b) DC Bus 1, DC Bus 2 or batteries.
    (c) DC Bus 2 or batteries. (d) DC Bus 1 only.
A

(b) DC Bus 1, DC Bus 2 or batteries.

67
Q
  1. (DSC-24-20/30) AC Bus tie contactors enable the electrical system;
    (a) To be connected in parallel. (b) To be supplied by any generator or external power.
    (c) To be supplied by apu gen or external power only
    (d) To be tied to external dc power.
A

(b) To be supplied by any generator or external power.

68
Q
  1. (DSC-24-20/30) What happens during the emergency gen. test;
    (a) The ram air turbine is extended.
    (b) The blue system is pressurised and the emergency generator comes on line.

(c) The green system is pressurised and the emergency generator comes on line, supplied by hot bus 2.
(d) The emergency generator comes on line and the yellow system is pressurised.

A

(b) The blue system is pressurised and the emergency generator comes on line.

69
Q
  1. (PRO-NOR-SOP-04) Normal minimum battery voltage before apu start is ;
    (a) 22v. (b) 25.5v. (c) 27.5v. (d) No Minimum.
A

(b) 25.5v.

70
Q
  1. (DSC-24-20/30) When disconnecting the IDG the button should be pressed;
    (a) For no more than 3 secs.
    (b) For longer than 3 secs. (c) Until the fault light goes out.
    (d) For no more than 5secs.
A

(a) For no more than 3 secs.

71
Q
  1. (DSC-24-20/30) On the emergency electrical power panel, a fault light illuminates under the ‘ RAT and Emer.Gen.’ label. What does it mean ;
    (a) Rat is not extended.
    (b) Emergency generator is not supplying when AC bus 1 and 2 are not powered or Dc Bat bus is not powered.
    (c) Emergency generator is supplying but AC Ess bus is not powered.
    (d) Emergency generator is not supplying when AC Bus 1 and 2 are not powered.
A

(d) Emergency generator is not supplying when AC Bus 1 and 2 are not powered

72
Q
  1. (DSC-24-20/30) What happens when the Gen 1 line Pb. is set to off;
    (a) AC Bus one and 2 are not powered and emergency generator is automatically connected.
    (b) AC Bus 1 is powered by the gen. 2 because the gen 1 is deactivated.
    (c) AC Bus 1 is powered by the gen.2 because the gen.1 line contactor is opened.

(d) AC Bus 1 is not powered because the gen. 1 line contactor is opened and transfer contactor is not closed.

A

(c) AC Bus 1 is powered by the gen.2 because the gen.1 line contactor is opened.

73
Q

11 (DSC-24-20/30) Where can the battery voltage be checked;

(a) On the ECAM elec page only
(b) On the elec overhead panel and the ECAM elec page
(c) On the elec overhead panel and the ECAM E/WD
(d) On the elec overhead panel only

A

(b) On the elec overhead panel and the ECAM elec page

74
Q
  1. (DSC-24-10) AC essential bus is normally supplied by;
    (a) AC Bus 1. (b) AC Bus 2. (c) Static inverter.
    (d) Emer. gen.
A

(a) AC Bus 1.

75
Q
  1. (DSC-24-10) In flight on batteries only, the AC Ess Shed bus and DC Ess Shed bus are lost;
    (a) Yes. (b) No. (c) Only A/C Ess Shed Bus is lost.
    (d) Only D/C Ess Shed Bus is lost.
A

(a) Yes.

76
Q
  1. (DSC-24-10)The static inverter works;
    (a) Always. (b) When A/C speed is > 50kts and on batteries only.
    (c) When one main generator fails. (d) Only when gen. 2 fails.
A

(b) When A/C speed is > 50kts and on batteries only.

77
Q
  1. (DSC-24-20/30) On ground what happens if the RAT and Emer. Gen. Man On Pb. Is pressed
    (a) The Rat is extended. (b) The emergency generator is activated. (c) Nothing. (d) The blue hydraulic system is pressurised and this causes the RAT to extend and rotate.
A

(a) The Rat is extended.

78
Q
  1. (DSC-24-10)The static inverter transforms the DC voltage from the battery bus into;
    (a) Single phase 115v - 400 Hz. A/C current. (b) Three phase 115/200v - 400hz. A/C current. (c) 28v D/C current.
    (d) 25.5v D/C current.
A

(a) Single phase 115v - 400 Hz. A/C current.

79
Q
  1. (DSC-24-10) In flight in case of loss of all main generators, emergency generator not yet running (batteries only), the static inverter supplies ;
    (a) A/C Ess bus and Engine Ignition A (b) Eng Ignition & A/C Ess Bus & A/C Ess Shed Bus (c) Eng Ignition Only.
    (d) Hot bus 1.
A

(a) A/C Ess bus and Engine Ignition A

80
Q
  1. (DSC-24-20/30) The external power has priority over the Apu. gen.;
    (a) Yes. (b) No. (c) Only in flight. (d) No, Apu. gen. has priority over external power always.
A

(a) Yes.

81
Q
  1. (DSC-24-10) Gen 1 and Gen 2 when operating have priority over the Apu gen;
    (a) Yes. (b) No. (c) Only in flight. (d) Only on the ground.
A

(a) Yes

82
Q
  1. (DSC-24-10) With Apu gen. available, if one main generator fails, the failed generator is replaced by;
    (a) The Apu. (b) The other computer. (c) Bus tie takes place and the remaining main generator supplies both channels.
    (d) The RAT.
A

(a) The Apu.

83
Q
  1. (DSC-24-10) If a TR fails;
    (a) The other TR automatically replaces the faulty one & the Ess TR supplies the DC Ess Bus.
    (b) The Static inverter replaces the faulty TR.
    (c) The DC Bus on the faulty side is lost.
    (d) The Emergency generator supplies DC power on the faulty side.
A

(a) The other TR automatically replaces the faulty one & the Ess TR supplies the DC Ess Bus.

84
Q
  1. (DSC-24-10) In flight in case of loss of all main generators, emergency generator not running, the DC Ess Bus is supplied by;
    (a) Hot bus 2. (b) Ess TR. (c) Both. (d) Hot Bus 1.
A

(a) Hot bus 2.

85
Q
  1. (DSC-24-10) In flight in case of loss of all main generators, emergency generator running , the DC Ess Bus is supplied by the;
    (a) Hot bus. (b) Ess TR. (c) Both. (d) DC Bat bus.
A

(b) Ess TR.

86
Q
  1. (DSC-24-10) The IDG regulates the …….. of the generator;

(a) Speed. (b) Voltage. (c) Frequency. (d) GLC (generator line contactor)

A

(a) Speed.

87
Q
  1. (DSC-24-20/30) When switched to ALTN the AC Ess Feed p/b causes the AC Ess Bus to be;
    (a) Supplied from AC bus 1 (b) Supplied from AC bus 2 (c) Supplied from DC bus 1
    (d) Supplied from DC bus 2
A

(b) Supplied from AC bus 2

88
Q
  1. (DSC-24-10) If AC bus 1 fails the AC Ess bus is supplied by;
    (a) Emer Gen.
    (b) AC Bus 2. (c) Static inverter.
    (d) The RAT.
A

(b) AC Bus 2.

89
Q
  1. (DSC-24-10) In case of total electrical loss the AC Ess bus is supplied by;
    (a) Static inverter.
    (b) Emer Gen. (c) Both. (d) TR 1.
A

(a) Static inverter.

90
Q
  1. (DSC-24-10) In Emergency configuration, AC Ess shed bus is automatically shed;
    (a) If the RAT stalls or aircraft is on ground with speed<100kts
    (b) When the landing gear is down.
    (c) When in emergency configuration

(d) When AC Bus 1 is lost

A

(a) If the RAT stalls or aircraft is on ground with speed<100kts

91
Q
  1. (DSC-24-10) If one main generator fails in flight (and the APU generator is not being used)
    (a) Part of the galley load is automatically shed
    (b) All galley load is automatically shed once the APU generator becomes available.
    (c) All galleys are shed.

(d) Galleys are not shed.

A

(a) Part of the galley load is automatically shed

92
Q
  1. (DSC-24-20/30) Can you reconnect the IDG in flight;
    (a) Yes. (b) No. (c) No. 1 idg only.
    (d) No. 2 idg only.
A

(b) No.

93
Q
  1. (DSC-24-20/30) When Gen. 1 or Gen. 2 is selected to off;
    (a) The Generator field is de-energised and the line contactor is open.
    (b) The Generator is still energised and line contactor is open. (c) Cannot select off in flight. (d) Can only be reset on ground.
A

(a) The Generator field is de-energised and the line contactor is open.

94
Q
  1. (DSC-24-20/30) When the EXT Pwr Pb green avail is illuminated;
    (a) The external power is connected to the a/c.
    (b) The A/C network is supplied. (c) Ground services are supplied. (d) D/C network supplied.
A

(a) The external power is connected to the a/c.

95
Q
  1. (DSC-24-10) Emergency generation, the D/C bat bus is automatically connected to the batteries:
    (a) below ‘s’ speed (b) below green dot speed (c) below 50kts
    (d) below 100 kts
A

(d) below 100 kts

96
Q
  1. (PRO-NOR-SOP-04) When you want to check battery voltage, you must set the Bat Pb to:
    (a) Auto position. (b) Off position. (c) Norm position.
    (d) On position.
A

(b) Off position.

97
Q
  1. (DSC-24-20/30) The Bat fault light illuminates when;
    (a) Battery voltage < 25v. (b) Battery Pb switch is at off in flight. (c) Charging current increases at an abnormal rate.
    (d) Charging current is low.
A

(c) Charging current increases at an abnormal rate.

98
Q
  1. (DSC-24-10) In certain cases the static inverter is supplied by;
    (a) Hot bus 1 and Hot bus 2.
    (b) Hot bus 1. (c) D/C Bat bus. (d) A/C Ess bus.
A

(b) Hot bus 1.

4. Systems (19 decks)

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