DSC Electric Flashcards

1
Q

Can you explain the sources of electrical generations and their priorities ?

A

In normal config the electrical system provide AC power
the system is composed of :
- 2 Eng generator and 1 APU
- 1 external power
Part of this AC power is converted into DC power

The priorities are :
GEN 1 and 2
then external power if available
then APU gen

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2
Q

Elect, in normal configuration how are supplied each bus ?

A

GEN 1 => AC BUS 1 => AC ESS
AC BUS 1 => TR1 => DC BUS 1 => DC BAT BUS and DC ESS BUS

GEN 2 => AC BUS 2 => TR2 => DC BUS 2

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3
Q

How is the elect system reconfigured in case of AC BUS 1 fault ?

A

AC ess is supplied by AC BUS 2
DC ESS is supplied by ESS TR
AC BUS 2 supplies DC BUS 2 and DC BAT BUS via TR 2.
DC BAT BUS supplies DC BUS 1

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4
Q

What elect bus do you lose in case of TR1 & TR2 failure ?

A

DC BUS 1&2 and DC BAT BUS

DC ESS is supplied by ESS TR from AC ESS

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5
Q

When will the RAT extend automatically ?

A

AC bus 1 & 2 lost and speed above 100kt

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6
Q

When will you be in the battery only configuration ?

A

When the RAT stall and on the ground below 100kt
If the emer gen is not connected

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7
Q

When in Battery only configuration what bus are powered and how ?

A

AC ess but part of it is shed (AC ESS bus shed) and DC ess with part of it shed (DC ESS shed)

DC ESS is supplied by BAT 2
AC ESS is supplied by the AC static inverter from BAT 1

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8
Q

In battery only config when will the AC ESS stop being powered ?

A

On ground with speed less than 50kt

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9
Q

In Emer elec what bus are supplied and how ?

A

AC ESS and DC ESS with the emer gen powered from RAT
AC ESS directly and DC ESS from ESS TR

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10
Q

What are the associated landing capability downgrade in case of loss of elect bus ?

A

Loss of bus and associated downgrade:

DC1:
A/C is technically CAT IIIA but since the Windshield heat on captain side is lost, the highest capability is the one from the right-hand seat so CAT I.

DC ESS:
A/C is technically CAT IIIA but the A/THR is inop so the highest capability is CAT 2

DC2:
A/C is CAT IIIA and doesn’t have any additional systems failure that have an impact on landing capability.

AC1:
A/C is technically CAT II but since the Windshield heat on captain side is lost, the highest capability is the one from the right-hand seat so CAT I.

AC ESS:
A/C is CAT I

AC2:
A/C is CAT I

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11
Q

In case of electrical bus failure is there a quick way to know if your landing capability is impacted due to windshield heat being inop ?

A

Any bus 1 failure (DC&AC) lead to the L windshield and window heat being inop with the associated landing capability downgrade (CAT I).

Any bus 2 failure (DC&AC) lead to the R windshield and window heat being inop but doesn’t affect the landing capability due to easyJet policy of FO being only CAT I.

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12
Q

In case of electrical bus loss, when will you lose the reverser ?

A

Any bus 1 failure (DC&AC) lead to the loss of REV 1

Any bus 2 failure (DC&AC) lead to the loss of REV 2

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13
Q

To which bus are connected the FO and CAPT screens ?

A

FO => AC BUS 2
CAPT => AC ESS BUS

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14
Q

What are the systems associated with any AC BUS ?

A

Fuel pump
HYD pumps (AC BUS 1 => BLUE elect pump, AC BUS 2 => YELLOW elect pump)
ADR (ADR 3 AC bus 1, ADR 2 AC bus 2, ADR 1 AC ESS BUS)
Brake systems/BSCU Channel (1 for Bus 1, 2 for bus 2)
Screens PFD, ND, ECAM (FO => AC BUS 2, CAPT => AC ESS BUS)
RA
Windshield Heat
Reversers

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15
Q

What are the systems associated with any DC BUS ?

A

Reversers
Flight computer (FAC2 with DC BUS2, FAC 1 DC ESS)
AP (AP1 DC ESS BUS, AP2 DC BUS 2)
A/THR (only DC ESS bus)
FCU (FCU1 DC ESS, FCU2 DC BUS 2)
Windshield heat (L with DC BUS 1, R with DC BUS 2)
VHF1 DC ESS BUS, VHF2 DC BUS 2, VHF3 DC BUS 1

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16
Q

What are the main operational consequence of loosing AC BUS 1 ?

A
  • Limited impact
  • AC ESS auto transfer
  • landing distance
  • loss of BLUE HYD and pump
  • CAT I Only
  • Single fuel pump in all tanks
  • Loss of one ADR => Consider if loss of another one or MEL => Alternate law
17
Q

What are the main operational consequences of loosing AC BUS 2 ?

A
  • FO has no screen and no lower ECAM
  • CAT I Only
  • Y elect pump
  • Single fuel pump in all tanks
  • Loss of one ADR => Consider if loss of another one or MEL => Alternate law
18
Q

What are the main operational consequences of loosing AC ESS BUS ?

A
  • CAPT has no screens so FO has control
  • No mask for PAX in case of decompression => descend? 10000ft
  • CAT I only
  • Airport in TERR ?
  • Loss of one ADR => Consider if loss of another one or MEL => Alternate law
19
Q

What are the main operational consequences of loosing DC ESS BUS ?

A

Com issue, ACP1 and ACP2 are lost and VHF1.
=> Com recovered via ACP3 (ausio swtg rotary selector) with VHF2 or 3
Speaker 1 is also lost so both pilot can hear only when speaker 2 at high volume and switch to FO3.

20
Q

How long does it takes for the emer gen to come online ?

A

8sec

21
Q

While the emer gen comes online, what power the AC?

A

Batteries with BAT1 => Static inverter => AC ESS which is shed
BAT 2 => DC ess which is shed

22
Q

In flight with battery only what is available in the flight deck ?

A

PFD1 and upper ecam (TBC)

23
Q

What is the purpose of GEN 1 line on the OVHD panel ?

A

Pressing the GEN 1 LINE button on the emergency electrical panel has much the same effect as pressing the GEN1 button on the main electrical panel, with the difference that GEN1 continues to supply its associated fuel pumps.

24
Q

What speed should be maintained for the RAT ?

A

In Emer Elect the speed of 140kt should be maintained.
The emer gen can be supplied down to 125kt below the RAT stalls.

25
Q

What is the difference between switching GEN OFF and IDG OFF ?

A

Gen Can be reconnected
IDG cannot until on the ground by engineers

26
Q

After applying the Smoke QRH check list, what is the purpose of selecting GEN2 and GEN 1 Line on prior to land ?

A

if successful allow to recover normal braking capabilities

27
Q

At what altitude can the APU be started on the EMER ELECT Config and why ?

A

Below FL 250 because of the BAT only start limit.