PF ELEC
EMER CONFIGPNF
FL 240
ELEC EMER
AC BUSES 1 & 2
FAULT
LAND ASAP
ECAM ACTIONS
DECISION
CONFIGURATION
LANDING GEAR EXTENSION
FINAL APPR
LANDING & DECELERATION
A320 - Version 03
PF
PNF
1. ELEC EMER CONFIG
DETECTION
CM1  PF
FLIES THE AIRCRAFT  LOSS OF AP, A/THR
NAVIGATES  LAND ASAP…Short term decision
CONSIDER AUTOMATION USE
ECAM ACTIONS
PF
COMMUNICATES
MAYDAY
ECAM PROCEDURE
CFM :
IAE :
SYSTEM DISPLAY
STATUS
USE SUMMARY…………..….……..CRUISE part
RETURN TO NORMAL TASK SHARING
DECISION
ST AT US, or
SUMM ARY
WE ATHER
WEATHER
LDG DIS
DIST
T
OPERATIONAL
OPERATIONALAND
AND
COMME
COMMERCIAL
RCIAL
CONS IDERATIONS
CONSIDERATIONS
ATC
DECISION
DECISIO N
NOT IFY
PURSER
PURSER/ PAX
/ PAX
OPS …
OPS …
FLIGHT IS FROZEN TO PERMIT THE PROCEDURE APPLICATION ON THE M/FTD
PF
PNF
2. APPROACH PREPARATION
ECAM STATUS………………………...REVIEW
SUMMARY…………..……………………….USE
FMGS………………………………….PREPARE
APPR BRIEFING ............…………..PERFORM
FMGS PREPARATION :
Done upon PF request
STANDARD
+
MANUAL INSERTION OF VAPP
APP BRIEFING :
STANDARD
+
STATUS
+
QRH
ELEC EMER CONFIG summary :
APP, LDG & G/A parts
1.00
FLIGHT IS FROZEN TO PERMIT THE PROCEDURE APPLICATION ON THE M/FTD
PF
PNF
3. APPROACH
When landing gear down :
ECAM ACTIONS
Approach synthesis
FLIGHT IS FROZEN TO PERMIT THE PROCEDURE APPLICATION ON THE M/FTD
PF ELEC
FL 240
EMER CONFIGPNF
Electrical Emergency configuration = loss of all AC BUSES
ELEC EMER
AC BUSES 1 & 2
FAULT
LAND ASAP
It may be caused
by :
the loss ECAM
of oneACTIONS
engine and the failure of the opposite generator
OR
DECISION
the loss of all GEN
OR
the loss of all engines
 simultaneous loss of all GEN
suspect a short-circuit
CONFIGURATION
Probability of a successful
APU GEN coupling is low
LANDING GEAR EXTENSION
FINAL APPR
Be aware that each APU start attempt reduces the battery time availability by approx. 3.5 mn.
LANDING & DECELERATION
A320 - Version 03
PF
PNF
1. ELEC EMER CONFIG
DETECTION
CM1  PF
FLIES THE AIRCRAFT  LOSS OF AP, A/THR
NAVIGATES  LAND ASAP…Short term decision
CONSIDER AUTOMATION USE
Single Chime
ENG THRUST
(every 5 sec)
LOCKED
PF
Move the trust levers to
theCOMMUNICATES
actual thrust position
MAYDAY
ECAM ACTIONS
•••
•••
ECAM PROCEDURE
CFM :
IAE :
SYSTEM DISPLAY
STATUS
USE SUMMARY…………..….……..CRUISE part
RETURN TO NORMAL TASK SHARING
DECISION
ST AT US, or
SUMM ARY
WE ATHER
WEATHER
LDG DIS
DIST
T
OPERATIONAL
OPERATIONALAND
AND
COMME
COMMERCIAL
RCIAL
CONS IDERATIONS
CONSIDERATIONS
ATC
DECISION
DECISIO N
NOT IFY
PURSER
PURSER/ PAX
/ PAX
OPS …
OPS …
FLIGHT IS FROZEN TO PERMIT THE PROCEDURE APPLICATION ON THE M/FTD
PF
PNF
1. ELEC EMER CONFIG
DETECTION
The electrical
network is powered by batteries
PF
CM1 only
during 3-5 sec while the RAT extends and
FLIES THE AIRCRAFT  LOSS the
OF EMER
AP, A/THR
GEN comes in line
NAVIGATES  LAND ASAP…Short term decision
CONSIDER AUTOMATION USE
3-5 sec later
ECAM ACTIONS
PF
COMMUNICATES
MAYDAY
ECAM PROCEDURE
CFM :
IAE :
SYSTEM DISPLAY
STATUS
USE SUMMARY…………..….……..CRUISE part
RETURN TO NORMAL TASK SHARING
DECISION
ST AT US, or
SUMM ARY
WE ATHER
WEATHER
LDG DIS
DIST
T
OPERATIONAL
OPERATIONALAND
AND
COMME
COMMERCIAL
RCIAL
CONS IDERATIONS
CONSIDERATIONS
ATC
DECISION
DECISIO N
NOT IFY
PURSER
PURSER/ PAX
/ PAX
OPS …
OPS …
FLIGHT IS FROZEN TO PERMIT THE PROCEDURE APPLICATION ON THE M/FTD
PF
ECAM PROCEDURE
PNF
QRH
GRAVITY FUEL FEEDING

2.00
ADIRS 2 & 3 remain supplied by batteries for 5 minutes after the loss of both engine generators.
Therefore, switching them off will save battery charge
Limit speeds & speed trend are recovered
SPD
LIM
FAC 1 reset
The rudder trim is recovered although no
indication is available
A320 CFM
PF
ECAM PROCEDURE
PNF
QRH
GRAVITY FUEL FEEDING

2.00
ADIRS 2 & 3 remain supplied by batteries for 5 minutes after the loss of both engine generators.
Therefore, switching them off will save battery charge
Limit speeds & speed trend are recovered
SPD
LIM
FAC 1 reset
The rudder trim is recovered although no
indication is available
Setting N1 MODE to ON changes the thrust control from
EPR mode to N1 rated mode.
Overhead
panel
A320 IAE
PF
SYSTEM DISPLAY
PNF
Optional
Only EWD available :
If needed, analyse SYSTEM page displayed on the upper ECAM screen:
OTHER SYSTEM PAGES
ELEC
ELEC key on ECP…………PRESS and HOLD
ELEC PAGE DISPLAYED.………....ANALYSE
REQUEST…………………..”CLEAR ELEC ?”
CONFIRM…………………….”CLEAR PRESS”
PRESS key on ECP..…….…………...RELEASE
PF
PNF
STATUS
To display the status :
ANNOUNCE………………………………”STATUS ?”
CONFIRM………………………”READ STATUS”
QRH
1.00
STATUS key on ECP…………….PRESS and HOLD
ELEC EMER CONFIG –
SYS REMAINING
Status overflow :
STATUS
PAGE
… release the STATUS key on ECP and push it
again within 2 sec to display the next STATUS page
QRH
1.00
Compute the LDG DIST with the SUMMARY,
according to the estimated weight at DEST
Review FCOM 3.02 procedure (If time permits)
!
Important note regarding
• fuel consumption
• speed indication reliability
FCOM
3.02.24
PF
USE OF SUMMARY
PNF
XX
1
3
DECISION
5
VAPP
2
4
8
A
P
STATUS
7
P
PR
E
P
IN
C
R
Z
E/WD
PROC
AP
P
6
BRIEFING
PF
USE OF SUMMARY
PNF
XX
1
3
DECISION
5
VAPP
2
4
8
A
P
STATUS
7
P
PR
E
P
IN
C
R
Z
E/WD
PROC
AP
P
6
BRIEFING
PF
APPROACH SPEED COMPUTATION
Check that NEW DEST
has been entered
PNF
Ensure that VLS & VAPP are based
on the proper weight at destination
VAPP = VREF + VREF (10 kt) + wind correction
VREF is given:


MCDU PERF APPR
page

On the ECAM, and
On the QRH
Select CONF FULL
Read VREF = VLS CONF FULL
LDG CONF
VAPP
VLS
FULL
Add 10 kts (VREF) to VREF
Add the wind correction
Enter VAPP manually
(Check minimum RAT speed)
LDG CONF
CONF 3
VAPP
VLS
FULL
LDG in CONF 3 :
 Select CONF 3
PF
PNF
APPROACH SYNTHESIS
Approach flown manually
with raw data : no AP
ALTN LAW FD
A/THR
CONF 1
CONF 2
GO AROUND
FINAL APPR
 BACK TO ALTERNATE LAW
 NO AUTO CALLOUTS
CONF 3
LANDING GEAR
EXTENSION
F/CTL DIRECT LAW
 MANUAL PITCH TRIM USE
LANDING & DECELERATION
BE AWARE OF :
 NO REVERSER
 NO NWS
 NO ANTISKID
(BRK PRESSURE MONITORED BY PNF)
 PARTIAL LOSS OF GRND SPOILERS