TM 55-4920-432-13&P
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LOCATION AND DESCRIPTION OF MAJOR COMPONENTS (CONT.)
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b.
Case Assembly: The Tester is 16.6 inches long, 17.00 inches deep and 15.5 inches high when
contained within its removable cover for transit. The cover contains accessories necessary for
proper operation of the Tester. When the Cover is removed, all operating controls, indicators, and
accessories are accessible for immediate use.
c.
Control Panel: The control panel of the Pitot and Static Systems Tester contains three aircraft
instruments: Rate of climb, altimeter, and the airspeed indicator. Vacuum and pressure controls,
bleed needle valves, a vacuum selector valve, a pressure selector valve, and an "ON-OFF" valve
for each of the three respective instruments are also clearly marked on the control panel. Also
contained on the control panel are the on-off power switch, power indicator light, and 5 amp fuse.
A spare fuse is mounted underneath the operator panel and is accessible when the panel is Open.
d.
Chassis-Base: The back of the chassis contains two ports: A "Static" port and a "'Pitot"' port for
hook-up to the same respective ports on the aircraft. Hoses and adaptors are provided in the
accessory storage compartment. Also, a power connector is provided through which AC and DC
power is supplied to the tester.
e.
Interior Components: For access to interior components of Tester, captive fasteners on the control
panel are released and the panel is then swung upward to the Open," position; with the panel open,
the motor-pump assembly oil, reservoir assembly and electrical power supply components are
easily accessible as are adjustable pressure/vacuum relief valves, a system pressure relief safety
valve, and all fittings and hoses. In addition, rigid pressure lines could be removed if necessary.
Located on rear of box is a clear window, which permits observation of fluid level in the oil reservoir
and an access door, which permits access to the reservoir drain-fill and run valve, allowing
hydraulic fluid.
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