DSC Electric Flashcards
Can you explain the sources of electrical generations and their priorities ?
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
Elect, in normal configuration how are supplied each bus ?
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
How is the elect system reconfigured in case of AC BUS 1 fault ?
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
What elect bus do you lose in case of TR1 & TR2 failure ?
DC BUS 1&2 and DC BAT BUS
DC ESS is supplied by ESS TR from AC ESS
When will the RAT extend automatically ?
AC bus 1 & 2 lost and speed above 100kt
When will you be in the battery only configuration ?
When the RAT stall and on the ground below 100kt
If the emer gen is not connected
When in Battery only configuration what bus are powered and how ?
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
In battery only config when will the AC ESS stop being powered ?
On ground with speed less than 50kt
In Emer elec what bus are supplied and how ?
AC ESS and DC ESS with the emer gen powered from RAT
AC ESS directly and DC ESS from ESS TR
What are the associated landing capability downgrade in case of loss of elect bus ?
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
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 ?
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.
In case of electrical bus loss, when will you lose the reverser ?
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
To which bus are connected the FO and CAPT screens ?
FO => AC BUS 2
CAPT => AC ESS BUS
What are the systems associated with any AC BUS ?
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
What are the systems associated with any DC BUS ?
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
