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• 28 VDC power, supplied by the DC BATTERY BUS (the AVIONICS BATTERY
DIRECT BUS is used as a backup)
• Environmental Control System, fuel and engine start
• Inlet door position
• Feedback of all applicable parameters during start, acceleration, run and shut down
• Fuel, bleed/air conditioning, anti-icing, engine start and electrical control panels
• APU FIRE DISCH handle, APU SHUTOFF (external services panel and APU
bay), and WOW status
The following are outputs generated by the FADEC:
• APU start and fuel feed shutoff
• Door opening and closing operations
• On speed loading of pneumatics and electrics
• ARINC 429 Communication signals to EICAS
• Interface with CAIMS
4-24 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
AUXILIARY POWER UNIT
FADEC SCHEMATIC
ELECTRICAL
EXT AC
AVAIL
ON
FAIL
OFF
GEN 1
FAIL
OFF
EXT DC
AVAIL
ON
GEN 3 GEN 4
FAIL
OFF
GEN 2
FAIL
OFF
PUSH OFF/RESET
PUSH
OFF/RESET
APU GEN
FAIL
OFF
RAT GEN
ON
OFF
BATT MASTER
EMS
OFF
ON
ASTE
E
OF
APU
RUN
OFF START
L ENG BLEED R ENG BLEED
APU BLEED
AUTO
CLSD OPEN
XBLEED
AUTO
OFF ON
AUTO
OFF ON
AUTO
OFF ON
INPUTS OUTPUTS
INLET DOOR
ECS
FUEL
ENGINE START
-FEED BACK PARAMETERSSTART
ACCELERATION
RUN
SHUTDOWN
APU START
FUEL SOV
DOOR
OPENED/CLOSED
COMMANDS
ON SPEED
PNEU/ELECTRICAL
LOADING
AVAILABLE
INPUT
OUTPUT
APU
LOAD
CONTROL
VALVE
WARNING
AND
CAUTION
MESSAGES
EICAS STATUS
DISPLAYS
DOOR
RPM
EGT
CAIMS
BITE CODES
OPERATING HOURS
429 COMMUNICATION
COMPARTMENT
SHUTDOWN BUTTON
SHUTDOWN BUTTON
EXTERNAL
SERVICES PANEL
APU BAY
WOW
E
L
E
C
T
R
O
N
I
C
C
O
N
T
R
O
L
U
N
I
T
GX_04_013
PULL
A
P
U
DISCH
1 2
For Training Purposes Only
Sept 04
4-25
P I LOT T R A I N I N G GU I D E
AUXILIARY POWER UNIT
EICAS MESSAGES
789
1 . 55 APU FIRE
APU OVERTEMP
APU OVERSPEED
APU BLEED SYS FAIL
APU OIL LO PRESS
APU OIL HI TEMP
APU EGT SENSORS
APU DOOR FAIL
APU REVERSE FLOW
APU FUEL SOV
APU OIL LO PRESS
Indicates that a low
pressure condition
exists.
APU DOOR FAIL
Indicates that the APU
door position does not
match command
position.
APU REVERSE FLOW
Indicates that a reverse
flow from the engine
bleed(s) to the APU
exists.
APU OVERSPEED
Indicates that an APU
overspeed protective
shutdown has
occurred.
APU BLEED SYS FAIL
Indicates that the APU
LCV does not match
command position.
APU OIL HI TEMP
Indicates that a high oil
temperature condition
exists.
APU EGT SENSORS
Indicates both
thermocouples have
failed.
GX_04_014
APU OVERTEMP
Indicates that an EGT
overtemperature
exists.
APU FIRE
Indicates that an
APU fire has
occured.
APU FUEL SOV
Indicates that the APU
fuel shutoff valve has
failed open.
4-26 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
AUXILIARY POWER UNIT
EICAS MESSAGES (Cont)
789
1 . 55
APU OIL LO QTY
Indicates that the APU
oil level has reached
3.5 quarts (2 quarts
low).
APU BLEED DISABLED
Indicates that the LCV
command has been
received, and either:
• The inlet pressure is less
than 3.3 psia (35,000 ft).
The 60 second warm-up
period (on ground only)
is in progress.
•
The Airplane Flight Manual
limits the use of APU bleed
extraction to 30,000 ft.
Note:
APU FAULT
Indicates a failure in
one of the following:
•single speed sensor,
•EGT thermocouple,
•fuel solenoid (failed to
Close),
•fuel/oil filters in
impending bypass,
•low oil pressure switch
has failed (in flight).
APU BLEED ON
Indicates that the APU
BLEED switch is in the
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Bombardier global AUXILIARY POWER UNIT(10)
