SECTION I (con' t.)
hold the test stand in a fixed position during operations. The trail-
are provided for lifting or lashing down the test stand.
1-4.2.Engine. The engine (3-Fig.7) is a V-type, 4 cylinder, 4 stroke
A 12 volt battery (4-Fig.7) is employed to
cycle, air cooled unit.
Engine speed is held automatically at the select-
power the starter.
ed rpm (Revolutions per minute) by a centrifugal fly-weight governor
which adjusts the throttle to compensate for changes in engine load.
This reservoir (7-Fig.7A) is mounted in
l-4.3.Fluid Oil Reservoir.
the upper rear of the housing assembly with the reservoir fill cap
(7-Fig.6) accessible through the fluid tank overhead access door
A reservoir shutoff valve (18-Fig.8) is provided
for isolating the test stand reservoir from the hydraulic system
when using fluid from the aircraft reservoir or when the test stand
is utilized to drain the hydraulic system of the aircraft. Door
assemblies (3&4-Fig.1) provide access to the reservoir for service
The hydraulic pump (6-Fig.7) incorporates the
following features: a fluid volume control (3-Fig.3) providing regul-
ation of pump delivery from 0 to 10 gpm (gallons per minute) at oper-
ating pressures ranging from 400 to 5000 psi (pounds per square inch)
output, an adjustable compensating control (20-Fig.8) mounted on the
control panel, which at the predetermined pressure, reduces pump
delivery to the minimum requirements to maintain pressure in the
system. The pump is protected from overheating by a thermoswitch
the engine when the fluid in the pump exceeds 160 degrees F.