F2000EX EASY
ATA 24 – ELECTRICAL POWER
CODDE 1
TABLE OF CONTENTS
DGT94085
02-24-00
PAGE 1 / 2
ISSUE 3
02-24 ATA 24 – ELECTRICAL POWER
02-24-00 TABLE OF CONTENTS
02-24-05 GENERAL
Introduction
Sources
Equipment location
02-24-10 DESCRIPTION
Generation
Distribution
Operation
02-24-15 CONTROL AND INDICATION
Control
Indication
02-24-20 SYSTEM PROTECTION
Introduction
Batteries
Generators and APU
Circuit breakers
02-24-25 NORMAL OPERATION
Introduction
Ground operation with GPU plugged (MINI LOAD MASTER ON)
Ground operation with APU operating (LH AV, RH AV and MINI LOAD
MASTER ON)
Normal flight operation
02-24-30 ABNORMAL OPERATION
Introduction
BUS tieding and untieding policy
Erroneous indication
Battery 1 overheat
GEN 2 failure
CAS messages
DASSAULT AVIATION Proprietary Data
02-24-00
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ATA 24 – ELECTRICAL POWER
TABLE OF CONTENTS
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
INTENTIONALLY LEFT BLANK
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 24 – ELECTRICAL POWER
GENERAL
DGT94085
02-24-05
PAGE 1 / 4
ISSUE 3
INTRODUCTION
The F2000EX EASy uses DC power for control, operation and indication of the various
systems installed in the airplane.
The electrical power supply system consists of a 28 VDC on-board generation system
designed to minimize electrical fluctuation and power interruption. It supplies, controls and
distributes DC power to the on-board electrical equipment through three main buses (LH, ESS
and RH buses).
Most of the avionics equipment is master switched on these respective buses:
LH AV MASTER, MINI LOAD MASTER and RH AV MASTER.
The Median (MD) bus is used for liaison purpose.
The system is powered by two engine-driven generators and two batteries.
It can also be supplied by an Auxiliary Power Unit (APU) driven generator.
On ground, it can be supplied by an external DC Ground Power Unit (GPU).
DASSAULT AVIATION Proprietary Data
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ATA 24 – ELECTRICAL POWER
GENERAL
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
Master switches
Circuit breakers
overhead panel
DC supply
overhead panel
CAS windows
ELEC, STAT
and TEST
synoptics
FIGURE 02-24-05-00 FLIGHT DECK OVERVIEW
DASSAULT AVIATION Proprietary Data
F2000EX EASY
ATA 24 – ELECTRICAL POWER
CODDE 1
GENERAL
DGT94085
02-24-05
PAGE 3 / 4
ISSUE 3
SOURCES
DC SOURCES
-
two 36 Ah batteries
-
two
12
generators
-
one 9 kW (300 A) APU-driven
starter generator
-
1 Secondary Flight Display (SFD)
battery: HORIZ BAT
-
1 auxiliary battery: AUX BAT
(option)
-
3 batteries for the emergency
lighting system
-
4 buffer batteries for LH DU, UP
DU, MAU1 and MAU2.
-
4 NIC batteries, one batterie per
NIC/PROC module of each
channel of MAU.
-
Ground Power Unit (GPU)
INTERNAL
EXTERNAL
kW
AC SOURCES
-
equipment requiring alternating
current is equipped with built-in
inverters
-
passenger convenience items
can be powered by inverters on a
dedicated network
engine-driven
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ATA 24 – ELECTRICAL POWER
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GENERAL
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
EQUIPMENT LOCATION
FIGURE 02-24-05-01 EQUIPMENT LOCATION
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F2000EX EASY
CODDE 1
ATA 24 – ELECTRICAL POWER
DESCRIPTION
DGT94085
02-24-10
PAGE 1 / 10
ISSUE 3
GENERATION
MAIN BATTERIES
On ground, two 24 V (36 Ah) Ni-Cad batteries provide the primary source of DC power to
the entire distribution system prior to APU starting. The BAT 1 supplies electrical power for
starting the APU.
As soon as one generator is connected, batteries are reloading and flatten generator
electrical spikes.
They are also capable of an emergency in-flight source of power for a limited period if all
engine-driven generators fail. In that case, battery autonomy would be around 78 min
(including 5 troubleshooting minutes) with maximum load shedding.
The batteries are located in the forward servicing compartment accessible through the
forward servicing compartment door.
The batteries are ventilated, on the ground, by a battery-powered blower and by
aerodynamic air flow in flight. During ground operation, the battery blower is operational
when the BAT 1 switch is on.
NOTE
Very low-charged batteries cannot be connected to the buses, as their contactors need at least
18 VDC to close.
OTHER BATTERIES
Three batteries supply the emergency lights.
One HORIZ BAT battery supplies Secondary Flight Display (SFD) in case of loss of LH bus
for approximately 2 h 40 min.
One AUX BAT battery when installed, may supply dedicated equipment.
Four MAU-DU BAT buffer batteries supply the LH DU, UP DU, MAU1 and MAU2 so as to
prevent them from dimming when the APU starts due to voltage drop . One of these supplies
the Centralized Maintenance Computer (CMC) during shutdown.
Four NIC batteries supply the NIC/PROC module of each chanel of MAU.
Except for the batteries of emergency lights and NIC/PROC module, all battery voltages are
monitored and indicated in the TEST synoptic page.
The batteries of emergency lights can be checked by a three-position OFF-ON-ARM
EMERG LIGHTS switch located on the overhead panel.
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ATA 24 – ELECTRICAL POWER
DESCRIPTION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
ENGINE-DRIVEN GENERATORS
Engine-driven rectifier alternators are driven by the accessory gear box of each engine. A
shear shaft in the generator prevents damages to the accessory gearbox in case of
generator seizure. A damper in the generator shaft prevents from vibrations.
They are rated at 12 kW and regulated at 28.5 VDC by their associated Generator Control
Unit (GCU).
APU GENERATOR
The Auxiliary Power Unit (APU) is equipped with a starter-generator. On ground, it is
capable of power the entire DC electrical system, in addition to charging batteries.
It is rated at 9 kW and regulated at 28.5 VDC by its associated GCU.
ENGINE-DRIVEN GCU
The two Generator Control Units (GCU) provide current and voltage control and protection
for their associated generator:
- Control: the GCU regulates the voltage at 28.5 VDC. It monitors the output current in
order to comply with peak power protection (above 400 A). It also provides generator
output control in order to balance the voltage between several generators, when
connected in parallel.
- Protection: the GCU automatically disconnects its associated generator after debounce
when the electric load limit is reached or overvoltage.
APU-DRIVEN GCU
The APU Generator Control Units (GCU) provides current and voltage control and protection
for its associated generator:
- Control: the GCU regulates the voltage at 28.5 VDC and monitors the output current to
300 A, with a maximum of 350 A for one minute. It also provides generator output
control in order to balance the voltage between several generators, when connected in
parallel.
- Protection: the GCU automatically disconnects the generator when the electric load limit
is reached or overvoltage.
It also controls APU start sequence.
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 24 – ELECTRICAL POWER
DESCRIPTION
DGT94085
02-24-10
PAGE 3 / 10
ISSUE 3
GPU
An approved 28 VDC Ground Power Unit (GPU) may be used for prolonged periods to power
the DC system in order to facilitate maintenance and servicing.
The GPU may also be used for APU starting (recommended power is 1,000 A).
When the GPU is connected and operating, generators and batteries are automatically
disconnected from buses. If the airplane is equipped by the option charging batteries by
GPU then it is possible to connect batteries to the buses when GPU is connected.
FIGURE 02-24-10-00 GPU RECEPTACLE LOCATION
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ATA 24 – ELECTRICAL POWER
DESCRIPTION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
DISTRIBUTION
GENERAL
DC power distribution is separated into three independent buses, allowing redundantly
powered systems to continue to safely operate if one bus fails.
The distribution system consists of 5 distinct buses:
- battery bus,
- ESSential bus (A5, ESS),
- MD bus (connects battery 2 to RH or ESS buses),
- LH bus (A1, A2, A3, CABIN),
- RH bus (B1, B2, B3, GALLEY).
FIGURE 02-24-10-01 ELECTRICAL SYSTEM DIAGRAM
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 24 – ELECTRICAL POWER
DESCRIPTION
DGT94085
02-24-10
PAGE 5 / 10
ISSUE 3
The battery bus is powered as soon as the battery 1 is installed and plugged in. Regardless
of battery switch position, the battery bus provides electrical power directly to:
- the fueling panel,
- the emergency slat control circuit,
- the APU starter circuit,
- the engine FIRE extinguishers secondary discharge,
- the fuel shut-off valves,
- LIGHT 1 and LIGHT 2, main access door, available if at least one of the five trip
magnetic switches is selected to on.
Most of the avionics equipment is connected to the main buses through master-switches
located on the overhead panel:
FIGURE 02-24-10-02 OVERHEAD PANEL
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F2000EX EASY
ATA 24 – ELECTRICAL POWER
CODDE 1
DESCRIPTION
ISSUE 3
LH BUS
DGT94085
ESS BUS
RH BUS
-
ACP 3
-
ADF 1
-
ADF 2
-
Data loader
-
ADM 1
-
ADM 2
-
LSS (option)
-
ATC 1
-
ATC 2
-
RAD ALT 1
-
CCD LH (one channel)
-
AFCS channels A+B
-
TCAS
-
CCD RH (one channel)
-
AP servomotors
-
Weather Radar
-
DME 1
-
CCD LH (one channel)
-
GP LH
-
CCD RH (one channel)
-
LH DU
-
DME 2
-
MAU 2 channel B
-
GP RH
-
MKB LH
-
LW DU
-
UP DU
-
MAU 1 channel B
-
VOR 1
-
MAU 2 channel A
-
MKB RH
-
RAD ALT 2
-
RH DU
-
VHF 3 (option)
-
VOR 2
-
Yaw Damper
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F2000EX EASY
CODDE 1
02-24-10
ATA 24 – ELECTRICAL POWER
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DESCRIPTION
DGT94085
ISSUE 3
LH BUS
-
a1
AOA HEAT (LH)
BOOST 1
CAB LAV MASTER
CABIN PRESS
COND'G CABIN
ENG 1 EDU
EXT LIGHTS (LH)
FLAP A/B INDIC
FUEL 2 SHUT OFF
HUD HGS (option)
HUD OHU (option)
HYDR 1 INDIC
INSTR BAT (ST BY)
L/G CONTROL
LANDING LH
LO FUEL
NAV
NOSE WHL 1
O2 BOX LH
OIL LH
PITOT HEAT (LH)
READING CKPT (LH)
REVERSE 1 ARM
REVERSE 1 DEPLOY
STATIC HEAT (LH)
TRIM AILERON
WSHLD FRONT LH
ESS BUS
ESS
A/B CONTROL
ADF 1
ADM 1
ANTICOL FIN
APU
APU DETECT
APU EXTING
ATC 1
BLEED HP 1
BLEED HP 2
BLEED MONIT (ST BY)
BOOST 2
BRAKE CMPTR 1
CCD LH (one channel)
CCD RH (one channel)
COND'G MAN
DETECT 1
DETECT 2
DME 1
DU LH
DU UP
FADEC A LH
FLAP CONTROL
FUEL CMPTR (LH)
GP LH
HYDR ISOL
ICS LH
ICS RH (ST BY)
IGNITION 1 A
IGNITION 2 A
IRS 1
L/G EMERG
MAU 1 CH A
MKB LH
MRC 1 NIM
O2 BOX RH
OVERHEAD LH
…/…
RH BUS
b1
ADF 2
- ADM 2
- AOA HEAT (RH)
- AFT SIDE WINDOW
- AIL FEEL
- ATC 2
- AUTO SLAT (RH)
- BAG COMPT
- BOOST 2 (ST BY)
- BRAKE CMPTR 2
- CAB AC MASTER
- CCD LH (one channel)
- CCD RH (one channel)
- COND'G CREW
- CREW CALL
- ENG 2
- ENG 2 EDU
- ENG VIBR
- EXTING 1
- FADEC A RH
- FLIGHT RECORDER
- FUEL CMPTR (RH)
- GP RH
- IRS2
- L/G INDIC
- MAU 1 CH B
- MAU 2 BAT
- MKB RH
- OIL RH
- OVERHEAD RH
- READING CKPT (RH)
- STAB NORMAL
- STROBE
- TAXI
- TCU RH
- VALANCE
- WARN B AUDIO
- WARN B EXT
- WARN RH ESS/B (*)
- WIPER RH
(*) backup powered breakers (red extension on circuit breakers panel)
-
-
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ATA 24 – ELECTRICAL POWER
DESCRIPTION
ISSUE 3
-
CODDE 1
DGT94085
LH BUS
-
F2000EX EASY
ESS BUS
a2
AUTO SLAT (LH)
AV MASTER (LH)
BELTS NO SMK'G
BRAKE 2 ST BY
DU BAT (LH)
DU BAT (UP)
DV WINDOW
ENG1
ENTRY/CEILING
EXTING 2
FADEC B LH
FLIGHT RECORDER (ST
BY)
HF 1
ICS 3
IGNITION 1 B
IRS 3
MAU 1 BAT
PRV1
RAD ALT 1
REV PANEL
SHIELD
TCAS
TEMP PROBE
WARN A
-
ESS (cont'd)
PITCH FEEL
PITOT (ST BY)
PRESS MONIT
PUMP (ST BY)
STAB EMERG
START 1
START 2
TCU LH
TRANSFER
TRIM RUDDER
VDR 1
VHF 1
VOICE RECORDER
WARN ESS AUDIO
WARN ESS EXT
WARN LH ESS/B*
WINGS
WIPER LH
XBP
RH BUS
-
b2
AFCS CH A
AFCS CH B
ANTICOL BELLY
AP TRIM
AP SERVO
AV MASTER (RH)
BLEED MONIT
BOOST 1 (ST BY)
CREW SEATS
DRAIN HEAT
DU RH
EMERG LIGHT (*)
EXT LIGHTS (RH)
FADEC B RH
FLASH LIGHT
FUEL 1 SHUT OFF
FUEL APU SHUT OFF
GALLEY MASTER
HF 2
HYDR 2 INDIC
ICS RH
IGNITION 2 B
INSTR
LANDING RH
MAU 2 CH A
ML MASTER (RH)
MRC 2 NIM
NOSE CONE FAN
NOSE WHL 2
PITOT HEAT (RH)
PRESSURE FUELING
PRINTER
PRV 2
RAD ALT 2
REVERSE 2 ARM
REVERSE 2 DEPLOY
ROLL EMERG
STATIC HEAT (RH)
VHF 2
WSHLD FRONT RH
YD
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
02-24-10
ATA 24 – ELECTRICAL POWER
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DESCRIPTION
DGT94085
-
ISSUE 3
LH BUS
ESS BUS
RH BUS
a3
a5
b3
WINDSHIELD (LH)
-
ST-BY PUMP
-
WINDSHIELD (RH)
a4
-
AC SYSTEM (option)
No breakers are connected to MD bus.
OPERATION
ON GROUND
When GPU is connected, all buses are automatically tied. RH and LH buses could be untied
by selecting LH or RH ISOL pushbutton.
NORMAL FLIGHT
The bus tied rotary switch is in vertical position, ESS and MD buses are untied.
RH and LH ISOL pushbuttons are set to tied (status light unlighted), LH bus is tied to ESS
bus, RH buses tied to MD bus.
ABNORMAL CONDITIONS
In case of one generator failure, the battery supplies that bus.
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ATA 24 – ELECTRICAL POWER
DESCRIPTION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
INTENTIONALLY LEFT BLANK
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F2000EX EASY
02-24-15
ATA 24 – ELECTRICAL POWER
CODDE 1
PAGE 1 / 12
CONTROL AND INDICATION
DGT94085
ISSUE 3
CONTROL
FIGURE 02-24-15-00 OVERHEAD PANEL DURING NORMAL FLIGHT CONFIGURATION
SYNTHETIC TABLE
CONTROL
FUNCTION
-
GEN 1 connects
generator 1 to the LH
bus
-
GEN 2 connects
generator 2 to the RH
bus
two-position
trip magnetic
switch
-
two-position
trip magnetic
switch
-
TO ACTIVATE
On: contactor is
closed
Connected
trip automatically to
down position when the
GCU detects an
anomaly (over voltage,
over current)
act as reset switches
when the fault is
cleared (only one reset
attempt is allowed)
SYNOPTIC
TO DEACTIVATE
Off: contactor is
open and
engine stopped
or GPU is On
Disconnected
Abnormal
situation:
contactor is open
and engine is
running and
there is no GPU
DASSAULT AVIATION Proprietary Data
GEN1
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ATA 24 – ELECTRICAL POWER
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F2000EX EASY
CODDE 1
CONTROL AND INDICATION
ISSUE 3
DGT94085
CONTROL
FUNCTION
-
TO ACTIVATE
Contactor
closed and
GPU is off
(except GPUpowered APU
starting)
BAT 1 connects battery 1
to the ESS bus
NOTE
Battery 1 supplies the
battery bus whatever
battery switch position
two-position
trip magnetic
switch
-
two-position
trip magnetic
switch
SYNOPTIC
TO DEACTIVATE
Connected
Contactor open
and GPU is on
(except during
APU starting)
Abnormal
situation:
BAT 2 connects battery 2
to the MD bus
-
trip automatically to down
position when the system
detects an anomaly (high
reverse current)
-
act as reset switches
when the fault is cleared
BAT1
contactor open
without GPU
Abnormal
situation:
contactor is
closed and
GPU is on
Disconnected
DASSAULT AVIATION Proprietary Data
Abnormal
situation:
overheating
BAT1
F2000EX EASY
02-24-15
ATA 24 – ELECTRICAL POWER
CODDE 1
PAGE 3 / 12
CONTROL AND INDICATION
DGT94085
ISSUE 3
CONTROL
FUNCTION
TO ACTIVATE
SYNOPTIC
TO DEACTIVATE
contactor
closed
(below
35,500 ft)
two-position
trip magnetic
switch
contactor
closed
-
connects the APU
generator to the ESS
bus
-
trips automatically to
down position when the
GCU detects an overvoltage,
35,500 ft)
-
acts as a reset switch
when the fault is cleared
(only one reset attempt
is allowed)
contactor open
(APU stopped
or GPU is on)
Connected
(above
Disconnected
Abnormal
situation:
contactor open
with APU
running and no
GPU
ON GROUND ONLY:
-
light
pushbutton
-
-
disconnects the batteries
from their respective
buses, independently
from BAT magnetic
switch position
On: airplane
powered by
GPU on ground
Push On
ties up all buses
whatever BUS TIED
rotary switch position
allows GPU to supply all
buses
Off: airplane
not powered by
GPU
Push Off
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ATA 24 – ELECTRICAL POWER
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CODDE 1
CONTROL AND INDICATION
ISSUE 3
DGT94085
CONTROL
FUNCTION
TO ACTIVATE
SYNOPTIC
TO DEACTIVATE
Contactor
normally tied
Turn horizontally
-
Abnormally untied
(rotary switch
horizontal or
EXT POWER
pushed on)
ties up ESS (left
side) and MD (right
side) buses
BUS TIED
rotary switch
Contactor
normally untied
Turn
vertically
Abnormally tied
(rotary switch
vertical with no
GPU)
Contactor
closed
-
isolates LH bus
from ESS bus
or RH bus from MD
bus
Push on
Contactor
abnormally isolated
Contactor
normally isolated
Push off
Contactor
abnormally closed
DASSAULT AVIATION Proprietary Data
F2000EX EASY
ATA 24 – ELECTRICAL POWER
CODDE 1
CONTROL AND INDICATION
DGT94085
02-24-15
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ISSUE 3
CONTROL
FUNCTION
TO ACTIVATE
TO DEACTIVATE
SYNOPTIC
Push on
(connected)
-
sheds cabin optional
equipment load from
the LH bus
No specific indication
on the ELEC synoptic
Push off
(shed)
Push on
(connected)
-
No specific indication
on the ELEC synoptic
supplies power to LH
AV equipment
Push off
(shed)
Push on
(connected)
-
No specific indication
on the ELEC synoptic
supplies power to MINI
LOAD equipment
Push off
(shed)
Push on
(connected)
-
supplies power to RH
AV equipment
No specific indication
on the ELEC synoptic
Push off
(shed)
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CONTROL AND INDICATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
CONTROL
FUNCTION
TO ACTIVATE
TO DEACTIVATE
SYNOPTIC
Push on
(connected)
-
No specific indication
on the ELEC synoptic
sheds galley equipment
load from the RH bus
Push off
(shed)
Switch
ARM
(in flight
normal
position)
-
switch
ON:
Illuminates EMERG
lights and checks their
three batteries
Switch
ON
(test
position)
Switch
OFF
DASSAULT AVIATION Proprietary Data
No specific indication
on the ELEC synoptic
F2000EX EASY
CODDE 1
ATA 24 – ELECTRICAL POWER
CONTROL AND INDICATION
DGT94085
Electrical system indications are displayed on two pages on the MDU:
ELEC synoptic,
-
STAT synoptic.
PAGE 7 / 12
ISSUE 3
INDICATION
-
02-24-15
FIGURE 02-24-15-01 ELECTRICAL SYNOPTIC
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F2000EX EASY
ATA 24 – ELECTRICAL POWER
CODDE 1
CONTROL AND INDICATION
ISSUE 3
DGT94085
EXAMPLES OF BATTERY TEMPERATURE INDICATION
Warm temperature:
indication displayed
on amber background
Hot temperature:
indication displayed
on red background
Invalid data
FIGURE 02-24-15-02 BATTERY TEMPERATURE INDICATION
For each battery, temperature indication is given by the pointer position on an analog scale
and by digital readout.
When the airplane is not equipped with temperature control (lead acid batteries), none of the
above symbols and indication are displayed (option).
The scale is colored in white below 49°C, in amber between 49°C and 71°C and in red
above 71°C.
EXAMPLES OF BATTERY AMMETER
Normal values
displayed in green
Abnormal values
displayed in amber
Invalid data
FIGURE 02-24-15-03 BATTERY AMMETER
For each battery, current indication is given by the pointer position on an analog scale and
by digital readout.
The scale is colored in amber below – 300 A and, when APU is not starting, above + 45 A ;
otherwise in white.
NOTE
A negative current designates a charging current.
DASSAULT AVIATION Proprietary Data
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CODDE 1
ATA 24 – ELECTRICAL POWER
CONTROL AND INDICATION
DGT94085
02-24-15
PAGE 9 / 12
ISSUE 3
EXAMPLES OF DC GENERATOR AMMETER
Normal values
displayed in green
Abnormal values
displayed in amber
Invalid data
FIGURE 02-24-15-04 DC GENERATOR AMMETER
NOTE
For any generator or battery, 0 A is displayed on synoptic ammeters when actual current is
between - 10 A and + 10 A.
Current indication is displayed by the pointer position on an analog scale and by digital
readout.
For both engine-driven generators, indication is permanent and the scale is colored in
amber:
- on ground, above 300 A,
- in flight, above 400 A.
For the APU generator, the ammeter is displayed in grey when the APU MASTER
pushbutton is ON. Then, above 99% APU N1, the colored indication is displayed.
Amber limitations are displayed:
- up to 10,000 ft, above 300 A,
- between 10,000 ft and 25,000 ft, above 250 A,
- above 25,000 ft, above 200 A.
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ATA 24 – ELECTRICAL POWER
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CONTROL AND INDICATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
EXTERNAL POWER AMMETER
Normal values
displayed in green
Abnormal values
displayed in amber
Invalid data
FIGURE 02-24-15-05 DC EXTERNAL POWER AMMETER
For the external power ammeter, current indication is displayed on a digital readout when,
on ground, EXT POWER light pushbutton is pushed on.
The green display turns amber if current exceeds 300 A, except during GPU-powered APU
starting (thresholds are modified with GPU batteries charging option).
STARTING PHASE
White START is placed under the APU ammeter during APU start. Amber START is placed
under the APU in case of abnormal electric power supply.
FIGURE 02-24-15-06 STARTING PHASE
During the APU starting phase, the battery color code of the ELEC synoptic is specific:
-
, BAT 1 contactor opens during APU start, whenever another electrical power is
connected to buses (though contactor is open, ammeter deviates during APU start) and
GPU is not connected. The symbol turns amber to indicate abnormal closed contactor.
DASSAULT AVIATION Proprietary Data
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CODDE 1
02-24-15
ATA 24 – ELECTRICAL POWER
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CONTROL AND INDICATION
DGT94085
-
BAT1
ISSUE 3
, BAT 1 contactor closes if none electrical power is connected or during GPU
assisted APU start. The symbol turns amber to indicate abnormal open contactor.
-
, BAT 2 contactor opens during APU start. The symbol turns amber to indicate
abnormal closed contactor.
EXAMPLES OF LH AND RH BUSES VOLTMETER
Normal values
displayed in green
Abnormal values
displayed in amber
Invalid data
FIGURE 02-24-15-07 BUSES VOLTMETER
LH and RH buses are permanently monitored through two voltmeters displayed in the
synoptic page.
The ESS bus voltmeter is displayed when essential and LH buses are untied.
The MD bus voltmeter is displayed when MD bus (and its battery 2) is isolated from both
ESS and RH buses.
When a generator supplies the bus, the range of the analog scale is colored in amber below
25 V and above 30 V. This range is different in case of other electric configuration (bus
supplied by batteries only, APU starting, …).
NOTE
Electrical information is also available on the STAT synoptic.
DASSAULT AVIATION Proprietary Data
02-24-15
PAGE 12 / 12
ATA 24 – ELECTRICAL POWER
F2000EX EASY
CODDE 1
CONTROL AND INDICATION
ISSUE 3
DGT94085
STATUS SYNOPTIC
System failure area
Failure consequence area
Buses voltage
and
generators
current
indications
FIGURE 02-24-15-08 STATUS SYNOPTIC
TEST SYNOPTIC
FIGURE 02-24-15-09 TEST SYNOPTIC
To check MAU / DU BAT or HORIZ BAT, ..., place the CCD cursor on the respective soft
key and keep the <enter> button pressed to have indications displayed.
Normal values appear in green while too low or too high values appear in amber.
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 24 – ELECTRICAL POWER
SYSTEM PROTECTION
02-24-20
PAGE 1 / 4
DGT94085
ISSUE 3
INTRODUCTION
Feeder cables are protected by current fuses located inside the two main electrical boxes.
Circuit protection is provided by conventional trip-free circuit breakers located on the circuit
breakers panel.
The circuit breakers panel is divided into different sections. Each section, delimited by
different colored frames, corresponds to airplane major systems.
In case of failure of one engine-driven generator, certain items, not essential for the flight, are
automatically load-shed.
The auto load-shed system is disabled when the airplane is on the ground, allowing normal
operation of all cabin facilities.
The BUS TIED rotary switch normal flight position is vertical, isolating left side buses from
right ones. In case of overvoltage or short-circuit on one side, the other side is not affected.
The ESS and MD buses can be temporary tied, for ground operations with no engine-driven
generator assistance for example.
When ESS and MD buses are tied, the contactor provides protection between them in case of
overload on one side.
BATTERIES
The batteries are protected against excessive load by a trip magnetic switch, which opens
and disconnects the battery when the charging (reverse) current exceeds 330 A for more than
3 sec.
The BAT magnetic switch trips off and BAT ..
CAS message appears.
NOTE
Only two reset attempts permitted.
Batteries are ventilated on ground and in flight to protect them (hydrogen accumulation,
heating). On ground, the ventilation by an electrical blower is operational when the BAT 1 trip
magnetic switch is up and the position of the EXT POWER pushbutton is off. In flight,
ventilation is provided by the effect of dynamic air flowing through a venting duct and blowing
on the batteries.
DASSAULT AVIATION Proprietary Data
02-24-20
ATA 24 – ELECTRICAL POWER
PAGE 2 / 4
SYSTEM PROTECTION
ISSUE 3
CODDE 1
DGT94085
GENERATORS AND APU
The engine-driven generators and the APU are each monitored by a GCU.
Main protections are:
-
voltage control (at 28.5 VDC) and protection,
-
electric load protection,
-
reverse current, ...
The magnetic switch may trip off the corresponding generator.
GEN ..
F2000EX EASY
CAS message will appear.
CIRCUIT BREAKERS
FIGURE 02-24-20-00 CIRCUIT BREAKERS PANEL
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 24 – ELECTRICAL POWER
SYSTEM PROTECTION
DGT94085
02-24-20
PAGE 3 / 4
ISSUE 3
CIRCUIT BREAKER COLOR CODE
ESS BUS
A1 and A2 BUS
B1 and B2 BUS
EMERG LIGHTS
WARNING RH ESS / B
WARNING LH ESS / B
To be pulled if all generators fail
NOTE
Red breakers are backup powered by another bus.
DASSAULT AVIATION Proprietary Data
02-24-20
PAGE 4 / 4
ATA 24 – ELECTRICAL POWER
SYSTEM PROTECTION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
INTENTIONALLY LEFT BLANK
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 24 – ELECTRICAL POWER
NORMAL OPERATION
DGT94085
02-24-25
PAGE 1 / 6
ISSUE 3
INTRODUCTION
In the following, typical ground and in-flight situations have been selected to help the crew to
understand the symbols provided in the various panels and displays.
DASSAULT AVIATION Proprietary Data
02-24-25
PAGE 2 / 6
ATA 24 – ELECTRICAL POWER
F2000EX EASY
NORMAL OPERATION
ISSUE 3
CODDE 1
DGT94085
GROUND OPERATION WITH GPU PLUGGED (MINI LOAD MASTER ON)
FIGURE 02-24-25-00 OVERHEAD PANEL DURING GPU OPERATION
DASSAULT AVIATION Proprietary Data
F2000EX EASY
ATA 24 – ELECTRICAL POWER
CODDE 1
NORMAL OPERATION
02-24-25
PAGE 3 / 6
DGT94085
ISSUE 3
FIGURE 02-24-25-01 ELECTRICAL SYNOPTIC DURING GPU OPERATION
ACTION
RESULT
Plug in the GPU which is not running.
No result
Turn on GPU (at 28 VDC)
-
green light on
Push on EXT PWR light pushbutton
-
all MASTER: OFF lights on
-
MINI LOAD MASTER: OFF light off
-
Push on MINI LOAD MASTER
-
GPU ON: BUS TIED CAS message
symbol
-
all GEN and BAT isolated (grey synoptic
symbols)
-
BUS TIED amber indication
-
LH and RH buses voltage indications
DASSAULT AVIATION Proprietary Data
02-24-25
PAGE 4 / 6
ATA 24 – ELECTRICAL POWER
F2000EX EASY
NORMAL OPERATION
ISSUE 3
CODDE 1
DGT94085
GROUND OPERATION WITH APU OPERATING (LH AV, RH AV AND MINI LOAD
MASTER ON)
FIGURE 02-24-25-02 OVERHEAD PANEL DURING APU OPERATION
DASSAULT AVIATION Proprietary Data
F2000EX EASY
ATA 24 – ELECTRICAL POWER
CODDE 1
NORMAL OPERATION
02-24-25
PAGE 5 / 6
DGT94085
ISSUE 3
FIGURE 02-24-25-03 ELECTRICAL SYNOPTIC DURING APU OPERATION
ACTION
BAT overhead panel trip magnetic switches
up position
MINI LOAD MASTER overhead panel
pushbutton pushed on
BUS TIED rotary switch in horizontal position
APU starting procedure
LH and RH AV MASTER overhead panel
pushbuttons pushed on
RESULT
No result
-
BAT symbols in green
-
LH and RH buses voltage indications
-
GEN in stand-by + symbol in grey
-
BUS TIED contactor symbol in green,
closed
-
BUS TIED amber indication on the ELEC
synoptic
-
APU synoptic symbol in green when
connected to ESS bus
-
LH and RH AV MASTER: OFF lights off
DASSAULT AVIATION Proprietary Data
02-24-25
PAGE 6 / 6
ATA 24 – ELECTRICAL POWER
NORMAL OPERATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
NORMAL FLIGHT OPERATION
FIGURE 02-24-25-04 OVERHEAD PANEL DURING NORMAL FLIGHT OPERATION
FIGURE 02-24-25-05 ELECTRICAL SYNOPTIC DURING NORMAL FLIGHT OPERATION
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 24 – ELECTRICAL POWER
ABNORMAL OPERATION
02-24-30
PAGE 1 / 10
DGT94085
ISSUE 3
INTRODUCTION
In the following, typical abnormal situations have been selected to help the crew to
understand the symbols provided in the various panels and displays.
BUS TIEDING AND UNTIEDING POLICY
NORMAL FLIGHT CONDITION
FIGURE 02-24-30-00 NORMAL FLIGHT CONDITION
-
GEN 1 and BAT 1 supply LH and ESS coupled buses,
GEN 2 and BAT 2 supply RH and MD coupled buses.
GENERATOR FAILURE
-
At GEN 1 failure (or engine 1), LH bus is maintained coupled to ESS bus,
All the equipment supplied by LH bus and ESS bus are available.
FIGURE 02-24-30-01 GENERATOR FAILURE WITH SLATS EXTENDED
the ESS and MD buses must be tied via the bus tied rotary switch.
FIGURE 02-24-30-02 BUS TIED
-
GEN 2, BAT 1 and BAT 2 (eventually APU as required) supply the four buses.
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02-24-30
ATA 24 – ELECTRICAL POWER
PAGE 2 / 10
F2000EX EASY
ABNORMAL OPERATION
ISSUE 3
CODDE 1
DGT94085
SECOND GENERATOR FAILURE
FIGURE 02-24-30-03 ONE GEN FAILED
At second generator failure :
- LH bus is automatically isolated from ESS bus, :
o LH ISOL status light displayed,
- RH bus is automatically isolated from MD bus:
o RH ISOL status light displayed.
FIGURE 02-24-30-04 SECOND GENERATOR FAILURE
BAT 1 and BAT 2 (eventually APU as required) supply ESS and MD buses.
BATTERY 1 OVERHEAT
ABNORMAL STATUS
FIGURE 02-24-30-05 OVERHEAD PANEL DURING BAT 1 OVERHEAT
DASSAULT AVIATION Proprietary Data
F2000EX EASY
02-24-30
ATA 24 – ELECTRICAL POWER
CODDE 1
PAGE 3 / 10
ABNORMAL OPERATION
DGT94085
ISSUE 3
FIGURE 02-24-30-06 ELECTRICAL SYNOPTIC DURING BAT 1 OVERHEAT
CONTEXT
RESULT
-
HOT BAT 1
CAS message
Battery temperature > 71.1°C (160°F)
-
Battery 1 overheat
-
-
MASTER
WARNING
light on
ELEC synoptic: BAT 1 symbol in red +
BAT 1 temperature indication in red
DASSAULT AVIATION Proprietary Data
02-24-30
PAGE 4 / 10
ATA 24 – ELECTRICAL POWER
F2000EX EASY
CODDE 1
ABNORMAL OPERATION
ISSUE 3
DGT94085
AFTER PROCEDURE COMPLETE
FIGURE 02-24-30-07 OVERHEAD PANEL AFTER BAT 1 SWITCHED OFF
DASSAULT AVIATION Proprietary Data
F2000EX EASY
02-24-30
ATA 24 – ELECTRICAL POWER
CODDE 1
PAGE 5 / 10
ABNORMAL OPERATION
DGT94085
ISSUE 3
FIGURE 02-24-30-18 ELECTRICAL SYNOPTIC AFTER BAT 1 SWITCHED OFF
ACTION
RESULT
-
-
BAT 1 overhead panel trip magnetic
switch set to down position
BAT 1 isolated
BAT 1
CAS message
-
Wait until
-
HOT BAT 1
CAS
message
disappears (battery temperature < 71°C)
-
WARM BAT 1
CAS message
When HOT BAT 1 disappears,
-
ELEC synoptic: BAT 1 symbol in amber
BAT 1 temperature indication in amber,
decreasing
DASSAULT AVIATION Proprietary Data
02-24-30
ATA 24 – ELECTRICAL POWER
PAGE 6 / 10
F2000EX EASY
ABNORMAL OPERATION
ISSUE 3
CODDE 1
DGT94085
GEN 2 FAILURE
ABNORMAL STATUS
FIGURE 02-24-30-08 OVERHEAD PANEL DURING GEN 2 FAILURE
DASSAULT AVIATION Proprietary Data
F2000EX EASY
ATA 24 – ELECTRICAL POWER
CODDE 1
ABNORMAL OPERATION
02-24-30
PAGE 7 / 10
DGT94085
ISSUE 3
FIGURE 02-24-30-09 ELECTRICAL SYNOPTIC DURING GEN 2 FAILURE
CONTEXT
RESULT
-
-
GEN 2 failure detected
GEN 2
CAS message
-
-
ELEC synoptic: GEN 2 symbol in amber
light on
DASSAULT AVIATION Proprietary Data
02-24-30
PAGE 8 / 10
ATA 24 – ELECTRICAL POWER
ABNORMAL OPERATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
AFTER PROCEDURE COMPLETE
FIGURE 02-24-30-10 OVERHEAD PANEL WITH GEN 2 SWITCHED OFF AND BUS TIED
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 24 – ELECTRICAL POWER
ABNORMAL OPERATION
DGT94085
02-24-30
PAGE 9 / 10
ISSUE 3
FIGURE 02-24-30-11 ELECTRICAL SYNOPTIC WITH GEN 2 SWITCH TRIPPED OFF AND BUS TIED ON
ACTION
-
GEN 2 overhead panel trip magnetic switch
set to down position
-
BUS TIED rotary switch set to tied position
(horizontal position)
RESULT
-
-
RH ISOL pushbutton depressed
symbol on ELEC synoptic
symbol on ELEC synoptic
-
RH ISOL status light off
-
BUS RH TIED and GEN 2
CAS messages
DASSAULT AVIATION Proprietary Data
02-24-30
PAGE 10 / 10
ATA 24 – ELECTRICAL POWER
F2000EX EASY
ABNORMAL OPERATION
ISSUE 3
CODDE 1
DGT94085
CAS MESSAGES
CAS MESSAGE
DEFINITION
2 GEN’S FAIL
The two electrical generator connections have failed
and at least one engine is running
HOT BAT ..
Temperature of one battery above 71°C (160°F)
APU GEN
APU generator not connected with APU running
Battery (1/2) contactor open (except during
APU starting or GPU power supply)
Battery (1/2) temperature probe inoperative (on
ground)
BAT ..
BAT .. TEMP INOP
BUS ESSENTIAL LOW VOLTAGE
Low voltage on essential bus
BUS ESSENTIAL OVERVOLTAGE
Overvoltage on essential bus
BUS XX ISOL
(LH/RH) ISOL bus contactor is open
BUS XX LOW VOLTAGE
(LH/RH) bus voltage lower than 24 V with one
generator connected
BUS XX OVERVOLTAGE
(LH/RH) bus voltage above 32 V
BUS RH TIED
GEN ..
OVHD BACKUP PWR LH+RH FAIL
BUS TIED contactor is tied while rotary switch is
turned to untied, without GPU, RH ISOL is not
pushed to ISOL
One generator failed to connect though its engine is
running, without GPU
(LH/RH) backup power supply in overhead panel not
operative on ground
STARTER APU
APU on and its starter still active
WARM BAT ..
Battery (1/2) temperature between 49°C (120°F) and
71°C
APU GEN FAIL
On ground, APU contactor failed to open
BAT .. TEMP INOP
Battery (1/2) temperature measurement invalid
BUS RH TIED
GEN .. FAIL
GPU ON: BUS TIED
OVHD BACKUP PWR XX FAIL
BUS TIED contactor is tied with rotary switch turned
to tied, without GPU, RH ISOL is not pushed to ISOL
On ground, GEN (1/2) contactor failed to open
without engine running or with GPU on
Airplane powered by GPU and bus tied is
automatically tied.
(LH/RH) backup power supply for overhead panel
fails
DASSAULT AVIATION Proprietary Data