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filter.
Half Intensity Magenta
-- Invalid data.
BOOST PUMPS
White -- Respective
pump is off.
Green -- Respective
pump is operating
Amber -- Respective
pump has failed or has
no power.
Half intensity Magenta
-- Invalid data.
Both pumps come on
by selecting either pump
switch/light to in.
Both pumps are in
standby mode when
both engines are
operating.
During single engine
operations, both pumps
will come on automatically,
provided both boost
pump switch/lights are
pressed in.
NOTE
FUEL Page
P
XFLOW/APU PUMP
White -- Pump is off.
Green -- Pump is
operating.
Amber -- Pump has
failed.
Half Intensity Magenta
-- Invalid data.
Vol. 1 13--40--5
REV 56, Jan 31/03
FUEL SYSTEM
Fuel Distribution
Flight Crew Operating Manual
CSP A--013
MASTER
A. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
L FUEL PUMP M6
Fuel Pumps
L FUEL PUMP
CONT
DC BAT 1
M7
and Control R FUEL PUMP G10
Fuel System
R FUEL PUMP
CONT
DC BUS 2 2
G11
FUEL SOV L
ENG S2
Fuel Control
FUEL SOV R
ENG
DC
EMERGENCY 1 S1
FUEL SOV
APU S3
REV 56, Jan 31/03
Vol. 1 13--40--6
FUEL SYSTEM
Fuel Distribution
Flight Crew Operating Manual MASTER
CSP A--013
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 13--50--1
REV 56, Jan 31/03
FUEL SYSTEM
Refueling and Defueling
Flight Crew Operating Manual
CSP A--013
MASTER
1. REFUELING AND DEFUELING
The refuel/defuel system is controlled by the Fuel System Computer (FSC) through selection
on a refuel/defuel control panel. Pressure refueling and suction defueling of the aircraft are
accomplished using a refuel/defuel adapter located in the right wing, leading edge, root
fairing.
Gravity refueling is carried out through filler caps installed on the upper wing surface. The
fuel quantity can be monitored using magnetic level indicators installed in the tanks. Water
drain valves, installed at various low points, permit testing of fuel for contamination and
provide the means of draining any accumulated water.
WARNING
The gravity filler caps are located below themaximum
pressure refueling level. Never remove the gravity
filler caps if the wing tanks are full or if the fuel quantity
is unknown.
REV 56, Jan 31/03
Vol. 1 13--50--2
FUEL SYSTEM
Refueling and Defueling
Flight Crew Operating Manual MASTER
CSP A--013
Refuel/Defuel System <MST>
Figure 13---50---1
Right Wing Top View
BottomView of Left Wing
Refuel/Defuel
Control Panel
<0017>
NOTE
Right side is shown.
Left side is opposite.
Gravity Filler Cap (3)
Lift latch and turn
counterclockwise
to unlock.
Refuel/Defuel
Control Panel
NOTE
Left side is shown.
Right side is opposite.
TANK FUEL DRAIN
VALVE (3)
remove plug.
Insert gravity defueler
adapter to start gravity
defueling.
Lift latch and turn
counterclockwise to
WATER DRAIN VALVE (16)
Push and rotate water drain
valve core with fuel sampler
to drain fuel into fuel sampler.
PUSH TO
UNLOCK
Refuel/Defuel Adapter
Bayonet type pressure
fueling adapter. Remove
protective cap to connect
refuel/defuel hose adapter.
Vol. 1 13--50--3
REV 56, Jan 31/03
FUEL SYSTEM
Refueling and Defueling
Flight Crew Operating Manual
CSP A--013
MASTER
Fuel System Computer <MST>
Figure 13---50---2
FUEL SYSTEM
COMPUTER
QUANTITY
SENSORS
FUEL
QTY
QTY SENSORS
CENTRE TANK
28 VDC
BATT BUS
28 VDC
ESS BUS
TO
EICAS
Refuel/Defuel
Control Panel
RIGHT/LEFT
COMPENSATORS
AHRS
CHANNEL 2
CHANNEL 1
PSEU
REFUEL/DEFUEL
SOV’S
FUEL TRANSFER
SOV’S
X--FLOW/APU
PUMP
FUEL X--FLOW
SOV’S
FUEL TEMP
SENSOR
FAULT
ANNUNCIATION
REFUEL/DEFUEL
PANEL
HIGH LEVEL
SENSORS
HIGH LEVEL
SENSOR
LEFT MAIN TANK RIGHT MAIN TANK
SAME AS 1
<0025> IRS
P
REV 56, Jan 31/03
Vol. 1 13--50--4
FUEL SYSTEM
Refueling and Defueling
Flight Crew Operating Manual MASTER
CSP A--013
A. Control Panel
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Bombardier_CRJ_00-Fuel_System(6)
