Figure 2. Aircraft hydraulic test stand, three-quarter, left rear view.

Dust protective cap, in.

Hose support hook

Left front door assembly

Dust protective cap, 1 in.

Coupling half, in.

Front top door assembly

Left rear door assembly

Coupling half, in.

Rear top door assembly

Tie rod

Coupling half, 1 in.

Reservoir fill cap

Dust protective cap, in.

Rear door assembly

Figure 2. Aircraft hydraulic test stand, three-quarter, left rear view.

volume control providing regulation of pump

door assembly (3). A reservoir shutoff valve

delivery from 0 to 10 gpm (gallons per min-

is provided for isolating the test stand reservoir

ute ) at operating pressures ranging from 200

from the hydraulic system when using fluid

from the aircraft reservoir or when the test

to 5000 psi (pounds per square inch) output,

stand is utilized to drain the hydraulic system

and to 100 psi maximum input: an adjustable

of the aircraft. Door assemblies (3 and 13)

compensating control mounted on the control

provide access to the reservoir for service and

panel, which at the predetermined pressure,

maintenance.

reduces pump delivery to the minimum require-

e. Hydraulic Pump. The hydraulic pump

ment to maintain pressure in the system.

incorporates the following features: a pump

AGO 5742A