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terminate under the trailing edge on each side
in a flush-mounted NACA scoop. The scoop,
which has ice rejection capability, maintains
a slight positive tank pressure during flight due
to ram-air effect.
There are no valves or screens in the vent
lines, so dirt or ice accumulation does not nor-
mally occur. Any trapped fuel or moisture in
the vent lines is continuously purged from the
low points by a bleed line connected to each
scavenge ejector.
During pressure fueling, the fuel tank vent lines
are augmented with special vent valves which will
be described later under "Pressure Refueling."
REFUELING
GENERAL
All tanks are normally fueled by means of the
single-point pressure adapter located in the
right wing root (Figure 5-9). The refueling
system is controlled from a swing-out control
panel located in the fillet above the right wing.
The system has automatic fuel cutoff to pre-
vent overfilling.
Overwing or gravity fueling is also possible.
However, due to the location of the filler caps
(Figure 5-9) , it is not possible to fill the main
tanks completely. A separate gravity filler
port is provided for each main tank and the aux-
iliary tank. The forward and aft tanks are grav-
ity fueled through the auxiliary tank.
CAUTION
Never open an overwing filler cap if
that main tank contains more than
4,000 pounds or if the level is not
known. Fuel in excess of 4,000 pounds
will spew from the filler if opened.
CL-600-2B16 PILOT TRAINING MANUAL
PRESSURE REFUELING
The pressure-refueling system (Figure 5-10)
consists of a single-point adapter, a pressure
manifold containing a two-way check valve,
three shutoff valves (SOV) associated with
three float-operated, full level-control valves,
and three vent valves that can be tested during
the refueling process and are utilized as backup
to normal pressure relief during refueling.
The adapter and manifold can accept a flow
rate of up to 250 gpm at a pressure of from 20
to 55 psi. The pressure-fueling process is con-
trolled from the fuel-defuel panel.
During a normal pressure-refueling opera-
tion, the sequence of events is as follows:
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
• Move the power switch to ON and check
that the green POWER ON light illu-
minates (Figure 5-11) (powered from
battery direct bus).
• Check that all three green vent valve
(VV) lights are extinguished and that
all four green SOV CLosed lights are
illuminated.
• Connect fueling nozzle from the truck
to the single-point adapter.
• Open the fuel nozzle valve and check
that with fuel pressure applied, all three
VV OPEN lights remain off.
• Rotate the MODE selector from OFF
to TEST.
• Move the tank FUEL-DEF switch of a
tank to be filled to the FUEL position and
check that the corresponding amber SOV
OPEN light illuminates
.• Check that the appropriate VV OPEN
light illuminates within 30 seconds.
Lt é e
Lt d .
CL 601-3R 5-11
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