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L and R ENG SOV CLSD advisory (green)
Indicates that respective engine fuel shut--off
valve is closed and an engine fire is detected.
APU SOV CLSD advisory (green)
Indicates that APU shut--off valve is
closed and an APU fire is detected.
APU SOV OPEN status (white)
Indicates that APU shut--off valve is
open with APU not ready to load
and no APU fire detected.
APU SOV FAIL caution (amber)
Indicates that APU shut--off valve is
not in commanded position.
L and R ENG SOV FAIL caution (amber)
Indicates that respective engine fuel shut--off
valve is not in commanded position.
L and R ENG SOV CLSD caution (amber)
Indicates that respective engine fuel shut--off
valve is closed and no engine fire is detected.
L and R ENG SOV OPEN caution (amber)
Indicates that respective engine fuel shut--off
valve is open and an engine fire is detected.
APU SOV OPEN caution (amber)
Indicates that APU shut--off valve is open
with APU ready to load and an APU fire
is detected.
APU SOV FAIL
APU SOV OPEN
L ENG SOV FAIL
R ENG SOV FAIL
L ENG SOV OPEN
R ENG SOV OPEN
L ENG SOV CLSD
R ENG SOV CLSD
L FUEL LO PRESS
R FUEL LO PRESS
L ENG SOV CLSD
R ENG SOV CLSD
APU SOV CLSD
APU SOV OPEN
L and R FUEL LO PRESS caution (amber)
Indicates that a low fuel pressure condition
exists at the respective engine inlet.
Primary Page
Status Page
Vol. 1 13--40--7
FUEL SYSTEM
Fuel Distribution REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
A. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
L FUEL PUMP BATTERY
BUS 1 M6
Pumps R FUEL PUMP DC BUS 2 2 G9
APU FUEL
PUMP BATTERY
1
N10
Fuel
Pump Control
L FUEL PUMP
CONT
BUS M7
Distribution
R FUEL PUMP
CONT DC BUS 2 2 G10
FUEL SOV R
ENG R7
Shut-off
Valves
FUEL SOV L
ENG
DC
EMERGENCY 1 R8
FUEL SOV
APU R9
Vol. 1 13--40--8
FUEL SYSTEM
Fuel Distribution REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE IS INTENTIONALLY LEFT BLANK
Vol. 1 13--50--1
FUEL SYSTEM
Refueling and Defueling REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. REFUELING AND DEFUELING
The refuel/defuel system is controlled by the Fuel Quantity and Gauging Computer (FQGC)
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 are installed at various low points in the tanks. The water drain valves are used
to drain out any accumulated water in the tanks and to take fuel samples for testing of the
fuel for contamination.
Vol. 1 13--50--2
FUEL SYSTEM
Refueling and Defueling REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Refuel/ Defuel Components <2224>
Figure 13---50---1
Refuel/Defuel Control Panel
Gravity filler caps for the wing
tanks are located below the
maximum fuel level. Never
remove gravity filler caps if the
tanks are full or fuel quantity is
not known.
WARNING
Refuel/Defuel Adapter
Remove protective cap
to connect refuel/defuel
hose adapter.
Water Drain Valves (8)
Push and rotate water drain
valve core with fuel sampler
to drain fuel into fuel sampler.
Gravity Filler Caps (2)
Lift latch and turn
counterclockwise to unlock.
BOTTOM VIEW OF WING
ON
TEST
LAMP
POWER
FAULT FUEL QTY
ANNUNC.
OFF
H.LEVEL
ON
CL OP SOV CL OP CL OP
OFF
DETECTOR
RIGHT LEFT
ON
SOV
BITE
INITIA.
DEFUEL TEST
OFF
FUEL AUTO
FUEL
MANUAL
PRES. TOTAL QTY
INC. ON
DEC.
Vol. 1 13--50--3
FUEL SYSTEM
Refueling and Defueling REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
A. Control Panel
The aircraft is fitted with a refuel/defuel control panel installed adjacent to the
refuel/defuel adapter on the right wing--to--fuselage fairing. Fuel quantity indications on
the panel are displayed in kilograms (kg). <1001>
The refueling operation can be initiated in automatic or manual mode. Automatic mode
　
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