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|  MIL-G-81737A(AS)
To verify conformance to the leakage requirements
4,6.5.1 Procedure.
proceed as follows:
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a. Turn the Solution A and B regulator valves to the 20 F settings on
the dials and open the discharge valve to full open.
b. Supply hydraulic fluid as specified in MIL-H-83282 at a pressure
of 150 5 psig to the solution A and B quick disconnect fittings and to the
fuel fitting.
Close the discharge valve when an uninterrupted flow exists from
c.
the valve.
d. Shut off hydraulic fluid source, read the fluid pressure gage
(capable of being read in 1-pound increments and located between fluid supply
shut off valve and unit), and record reading. After a 10 minute period, read
pressure gage and record reading.
4.6.6 Pressure switch testing. With the unit producing gelled fuel under
the standard conditions (4.3) and in accordance with procedures described in
NAVAIR 19-1-112, the probe shall be removed from the supply of Solution A
simultaneously with the starting of a stopwatch. Stop the watch and record
the pressure when the switch stops the operation of the unit.
4.6.7 Temperature switch testing. Prior to installation of the
temperature switch to the unit, calibrate switch by simulating actual working
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installation to function at 175 2 F, install into unit and proceed with
test. With the unit producing gelled fuel under the standard conditions (4.3)
and in accordance with procedures described in NAVAIR 19-1-112, the delivery
nozzle shall be closed and remain closed to provide continuous recirculation
of fuel, Solution A, and Solution B within the unit. Determination of the
recirculating fuel temperature shall be made on the exterior of the plumbing
at a point immediately downstream from the (automatic) temperature sensing
device to ensure correct knowledge of the fuel temperature within. The
temperature of the recirculating fuel shall be recorded upon automatic
shutdown of the unit.
4.6.8 Low temperature. The following low temperature test procedures
shall be performed in the order given.
Place the unit in a test chamber at standard conditions (4.3).
a.
b. Lower test chamber temperature to - 65 3F and stabilize unit
(4.3.1).
The temperature shall then be raised to +20 3F and the unit
stabilized (4.3.1). The unit shall then be operated with aviation gasoline or
turbine fuel and Solutions A and B supplied at +20 3F.
d. A sample shall be tested according to test procedures specified in
4.6.3.3.
Stabilize unit and solution at 20F.
e.
f. Operate "A" probe with kerosene.
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