1-13. HIGH PRESSURE FILTER. The high pressure filter (5,
from the aircraft system when using fluid from the aircraft
figure 1-3) is placed in the line between the high pressure
reservoir or when draining the aircraft reservoir. A hydraulic
pump and the relief valve assembly to micronically filter the
fluid level indicator mounted on the control is connected to the
hydraulic fluid coming from the high pressure pump. The filter
reservoir to indicate fluid content. The top plate of the
uses a replaceable type element AN6235-4A.
reservoir may be removed for access to the interior.
1-14. LOW PRESSURE FILTER. The low pressure filter (7,
1-17. ELECTRICAL SYSTEM. Major components of the
figure 1-3) is located in the suction line between the manifold
electrical system are : 12 volt battery (10, figure 1-3), generator
and pressure pump to micronically filter the hydraulic fluid from
the Test Stand and aircraft reservoirs.
It contains a
electrical system is shown schematically in figure 1-5.
replaceable type element AN6236-3.
1-18. SIMPLIFIED PRINCIPLES OF OPERATION. (Refer to
1-15. FUEL TANK. The fuel tank (4, figure 1-4) will hold 13
hydraulic schematic, figure 1-6.) The hydraulic fluid may be
gallons of fuel conforming to Military Specifications MIL-G-
taken from either the Test Stand reservoir (1) or the reservoir
3056 or MIL-F-5572. The tank is equipped with strainer in the
in the aircraft being tested through the suction inlet. The
fill neck, a drain plug in the bottom, and a fuel level sending
hydraulic fluid thus obtained is then forced under pressure by
the high pressure pump (12) through checkvalve (14), high
pressure filter (12), relief valve (20), and a four-way outlet
1-16. HYDRAULIC RESERVOIR. The hydraulic reservoir (1,
selector valve (23) to the selected pressure outlet (26 or 27)
figure 1-4) has a maximum capacity of 28 gallons. A reservoir
shutoff valve is provided for isolating the Test Stand reservoir
1. Hydraulic Reservoir
3. Voltage Regulator
4. Fuel Tank
Figure 1-4. Test Stand - Right Side