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TM 10-4930-240-13
SECTION III. PRINCIPLES OF OPERATION
1-12. SYSTEM TECHNICAL PRINCIPLES OF OPERATION.
NOTE
The AFARE system described in this manual is configured for a typical
mission. Your specific mission and operating requirements will determine
how many of the system components must be connected and in what
configuration. The type of fuel nozzle used at the refueling points will be
determined by the type of aircraft being refueled.
a.
The Arctic Forward Area Refueling Equipment (AFARE) is comprised of three fuel drums, a fueling
manifold, a turbine powered fuel pump, filter separator, pressure reducing valve, two types of aircraft
refueling nozzles and the necessary hoses and valves required to assemble and distribute fuel
through the system. The AFARE has two modes of operation, refuel and defuel. In the refuel mode,
fuel is removed from the 500 gallon drums and delivered to the aircraft. In the defuel mode, fuel is
removed from the aircraft and pumped to the 500 gallon drums for storage.
b.
Fuel required to operate the AFARE is stored in three 500 gallon collapsible drums. The drums may
be filled at the site or transported to the site while full. The drums expand as they are filled and
collapse as they empty. Each drum is connected to the AFARE system by a hand operated coupler.
As the coupler handle is set to open, a poppet valve inside the fuel drum coupling is unseated and
fuel is allowed to flow from the drum. For additional information on principles of operation for the 500
gallon drums, refer to TM 10-8110-203-12&P.
c.
Fuel flows from the 500 gallon drums, through 3-inch suction hoses, to the skid mounted fueling
manifold. Two hand operated gate valves are installed on the manifold to control fuel flow through
the manifold In the refuel mode, the manifold directs fuel from the 500 gallon drums to the 200 GPM
pump for distribution to the aircraft. In defuel mode, the manifold directs fuel from the aircraft,
through the 200 GPM pump, back to the 500 gallon drums.
d.
The turbine powered 200 GPM pump supplies fuel under pressure to the skid mounted filter
separator. Hot exhaust from the pump is collected and routed to the filter separator through
collapsible air ducts. For additional information on principles of operation for the 200 GPM pump,
refer to TM 10-4320-342-10.
e.
Fuel from the 200 GPM pump is processed by the filter separator to remove solid contaminants and
water from the fuel before delivery to the aircraft. A heat shroud, mounted below the filter separator
tank, receives hot air from the air ducts and disperses it around the tank to prevent freezing of
trapped water. For additional information on principles of operation for the filter separator, refer to
TM 10-4330-236-13.
f.
Clean fuel from the filter separator is distributed through 2-inch discharge hoses to the Closed Circuit
Refueling (CCR) nozzle and Single point refueling nozzle (D1).
g.
The CCR nozzle is a hand operated refueling nozzle that controls system fuel pressure to prevent
over filling and over-pressuring of the aircraft fuel system. The adapter on the outlet end of the
nozzle contains an orifice sized to provide a predetermined fuel flow rate. A gravity fill adapter is
used with the CCR nozzle to refuel gravity fed, non-pressurized fuel systems. The adapter is
1-9
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