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main and scavenge ejectors are powered by pressurized fuel tapped from the motive flow
line of the respective engine fuel pump.
For engine start, a boost pump connected to each collector tank, is selected ON from the
fuel control panel. The boost pumps supply fuel to their respective engines. The control
panel is used to control and monitor boost pump operation.
The fuel output pressure from the main ejector is monitored by a pressure switch and when
the output pressure is sufficient to supply the engines, the boost pumps are automatically
turned off. The boost pumps will remain in standby mode with the engines running, as a
back up to the main ejectors in the event of a failure. Each boost pump is capable of
feeding both engines.
The XFLOW/APU pump supplies fuel to the APU when the PWR FUEL switch on the APU
control panel is selected. In the event of a XFLOW/APU pump failure, the APU can be
supplied fuel from the right engine fuel feed manifold.
In the event of a fire, fuel flow to the engine or APU is terminated by the closure of a fuel
shut-off valve when the associated fire push switchlight is selected.
REV 56, Jan 31/03
Vol. 1 13--40--2
FUEL SYSTEM
Fuel Distribution
Flight Crew Operating Manual MASTER
CSP A--013
Standby Fuel Feed System
Figure 13--40--1
PWR FUEL
Used to control APU fuel pump.
PUMP FAIL (amber) light Indicates
that APU fuel pump has failed.
SOV FAIL (amber) light Indicates
that the APU fuel shut--off
valve has failed.
XFLOW/APU
PUMP
TO LEFT
ENGINE
COLLECTOR
TANK
BOOST
PUMP
COLLECTOR
TANK
Fuel Control Panel
Overhead Panel
TO RIGHT
ENGINE
TO
APU
PRESSURE
SWITCH
FROM THE
SCAVENGE
EJECTORS
FROM THE
SCAVENGE
EJECTORS
PRESSURE
SWITCH
MAIN
EJECTOR
APU Control Panel
Overhead Panel
L/R BOOST PUMP
switch/lights
Pressed in -- For engine start, both
boost pumps are activated. With both
engines running, the pumps remain armed,
but will automatically come on, when low
fuel pressure is detected in any engine
feed line. The switch/lights show ON
when the pumps are operating.
Pressed out -- The boost pump is
disarmed on the respective side.
INOP light comes on to indicate that a
low pump pressure has been detected,
the respective boost pump has not been
armed, or has failed.
Vol. 1 13--40--3
REV 56, Jan 31/03
FUEL SYSTEM
Fuel Distribution
Flight Crew Operating Manual
CSP A--013
MASTER
Standby Fuel Feed System -- EICAS Messages <MST>
Figure 13--40--2
L,R ENG SOV CLSD caution (amber)
Comes on to indicate that respective
engine fuel feed SOV is closed with
no engine--fire condition.
Status Page
<0039>
<0039>
L,R SCAV EJECTOR caution (amber)
Comes on to indicate low fuel pressure
at respective scavenge ejector with
respective engine running.
L,R ENG SOV CLSD advisory (green)
Comes on to indicate that respective
engine fuel feed SOV is closed with
no engine--fire condition.
L,R FUEL PUMP ON advisory (green)
Comes on to indicate that respective
fuel boost pump is operating.
L,R ENG SOV FAIL caution (amber)
Comes on to indicate that respective
engine fuel feed SOV has failed.
L,R ENG SOV OPEN caution (amber)
Comes on to indicate that respective
engine fuel feed SOV is not closed 10
seconds after an engine--fire condition.
L,R FUEL PUMP caution (amber)
Comes on to indicate that respective
engine boost pump has failed.
L,R FUEL LO PRESS caution (amber)
Comes on at 5 psig to indicate that
a low fuel pressure condition (at the
engine inlet) has been detected.
L,R FUEL FILTER caution (amber)
Comes on to indicate that a fuel
pressure drop exists across respective
fuel filter.
Primary Page
<0039> <0006>
REV 56, Jan 31/03
Vol. 1 13--40--4
FUEL SYSTEM
Fuel Distribution
Flight Crew Operating Manual MASTER
CSP A--013
Standby Fuel Feed System --- Fuel Synoptic Page Indications <MST>
Figure 13--40--3
APU Fuel Feed SOV
Controlled by the PWR
FUEL switch/light.
Controlled by the APU FIRE
PUSH switch/light.
LH/RH Engine Fuel Feed
SOV
Controlled by the respective
FIRE PUSH switch/light.
Fuel Filter
Green -- Indicates
normal fuel flow
through respective fuel
filter.
Amber -- Fuel
pressure drop exists
across respective fuel
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