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small-volume, high-pressure motive flow at
the throat of the ejector into large-volume,
low-pressure output at the ejector nozzle.
MAIN EJECTORS
Fuel is supplied from the collector tanks to the
low-pressure side of each engine-driven pump
by a main ejector located within the tank. Mo-
tive flow for operation of the main ejectors is
supplied by the high-pressure side of each en-
gine-driven fuel pump (Figure 5-3 and 5-4).
Each main ejector provides continuous fuel
flow to its own engine through firewall shut-
off valves. Flow to the opposite engine is not
possible because of one-way check valves in
the feed lines. Failure of a main ejector will
POWERED CROSSFEED
GRAVITY FLOW LINES
FLAPPER
VALVES
SCAVENGE
EJECTOR
LEGEND
SCAVENGE EJECTOR/OVERFLOW PRESSURE
MOTIVE FLOW PRESSURE
MAIN EJECTOR PRESSURE
STANDBY PUMP PRESSURE
5-4 CL 601-3R
OVERFLOW LINE
SHUTOFF VALVE
EJECTOR
COLLECTOR
TANK
FLOAT
VALVE
TO ENGINE
ENGINE
DRIVEN
PUMP
LOW
PRESSURE
SWITCH
Figure 5-3. Fuel Distribution—Engine Start
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
CL-600-2B16 PILOT TRAINING MANUAL
cause illumination of an amber caution light
in the cockpit, and will activate both standby
electric pumps as long as the standby pump on
the same side as the main ejector failure is se-
lected on.
TRANSFER EJECTORS
When main tank fuel quantity drops below
the 93% full level, float valves open, allow-
ing the transfer ejectors to draw fuel from the
auxiliary tank to the inboard sections of the
main tanks. Motive flow for the transfer ejec-
tors is provided by the output of the associated
main ejector. No cockpit indication of fuel
transfer or transfer ejector failure is provided.
MAIN
MAIN
CROSSFLOW
OVERFLOW LINE
VALVE
EJECTOR
FLAPPER
VALVE
STANDBY
PUMPS
FIREWALL SOV
APU SOV
TO APU
LOW
PRESSURE
SWITCH
POWERED CROSSFEED
SHUTOFF VALVE
COLLECTOR
TANK
GRAVITY FLOW LINES
FLAPPER
VALVES
FLOAT
VALVE
TRANSFER
EJECTOR
FIREWALL
TO ENGINE
ENGINE
DRIVEN
PUMP
L té e
L td .
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