SECTION I (Con't.)
1-12 CONTROLS AND INSTRUMENTS
This section describes, locates and furnishes the
operator with sufficient information pertaining to the various
controls and instrument provided for proper operation of the air-
craft hydraulic test stand.
The brake lever assembly (14-Fig.l),
1-14. Break Lever Assembly.
mounted on the front of the frame assembly, sets the brake shoes in
the rear wheels to secure the test stand in position for operation.
1-15. Reservoir Level Indicator. The reservoir level indicator (11-
Fig.8) is located in the upper right hand corner of the test stand
It indicates the liquid level in the reservoir. The
dial is marked E. ½, and F.
Reservoir Shutoff Valve. The reservoir shutoff valve (18-Fig.8)
located in the left center section of the test stand control panel is
a ball valve, provided to control the flow of hydraulic fluid from the
reservoir to the hydraulic system of the test stand. This valve
must be closed when the reservoir of the hydraulic system under test
is to be utilized.
1-17. Fluid Bypass Valve. The fluid bypass valve (19-Fig.8) is loc-
ated directly below the schematic plate. It provides a means of
directing the fluid discharge from the hydraulic pump into the reser-
voir. This valve must be open, creating a zero pressure condition,
while starting the engine, connecting the test stand to the aircraft
under tests and while setting the outlet selector valve.
The choke control (1-Fig.9) located on the
engine control panel, is a manually operated control that closes the
butterfly in the carburetor, enriching the fuel mixture for starting