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TM 1-4920-458-13&P
1-8. LOCATION AND DESCRIPTION OF MAJOR COMPONENTS (CONT)
1-8.1.
Cover Assembly.
The Tester is 16.6 inches long, 14.5 inches deep and 17.0 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.
1-8.2.
Frame Assembly.
The frame assembly of the Pitot and Static Systems Tester contains three aircraft instruments: rate of climb, altimeter
and airspeed indicator. Vacuum and pressure controls, bleed needle values, 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, press to test button, and 5 amp fuse. A
spare fuse is mounted on top of the frame assembly.
1-8.3.
Back Plate.
The back plate contains two ports: A "Static" port and a "Pitot" port for hook-up to the same respective ports on the
aircraft. Hoses and adapters are provided in the accessory storage compartment. Also, a power connector is provided
through which AC and DC power is supplied to the tester.
1-8.4.
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 the side of the box is a clear window, which permits observation of fluid level in the oil reservoir.
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