Engine - TM-55-4920-341-140010

SECTION I (con' t.)

hold the test stand in a fixed position during operations. The trail-

er rolls on pneumatic tires (9-Fig. 1). Tie-down rings (11-Fig.1)

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

assembly (4-Fig.1).

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

and maintenance.

The hydraulic pump (6-Fig.7) incorporates the

l-4.4.Hydraulic Pump.

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

(16-Fig.7) mounted in the pump header block (14-Fig.7) which stops

the engine when the fluid in the pump exceeds 160 degrees F.

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