activated. A thermal circuit breaker is installed in the motor case to safeguard the control circuit. An electromagnetic
interference filter is also installed in the motor case. A grounding cable with one end to fit the aircraft receptacle is also
stored on the shelf.
Table 1-1. Equipment Data
32 inches (in) (812.8 millimeters (mm)) (overall)
24 in (609.6 mm)
45 in (1143.0 mm) (including handle)
225 pounds (102.04 kilograms) (dry, excluding hoses)
Metal, weather resistant
Two semi-pneumatic tires for moving the cart.
Tiedown holes provided in legs at front corners.
-25 Deg. F (-32 Deg. C) to 125 Deg. F (52 Deg. C)
-65 Deg. F (-54 Deg. C) to 160 Deg. F (71 Deg. C)
200 Deg. F (93 Deg. C) (maximum)
1.2 gpm at 1,000 psi (minimum)
0.4 gpm at 3,000 psi (minimum)
5 gallons (18.925 liters)
MIL-H-5606 or MIL-H-83282
+24 vdc supplied by aircraft auxiliary power unit or batteries.
SECTION III. TECHNICAL PRINCIPLES OF OPERATION
1-10. Functional Description. Activating the pump toggle switch S4 (Figure 1-4) to ON position energizes the start relay
K1 and closes its contacts allowing the 24 vdc supply to energize the pump motor B1 (3, Figure 1-3). The motor drives
the gear pump (2) which takes hydraulic fluid from oil reservoir tank (14) and pumps to the filter (4). The 1 micron filtered
fluid flows through the check valves (5) to the three solenoid valves (7) (L1, L3, and L5). Under normal conditions the
solenoid valves (7) are closed while solenoid valve (11) should be in open position. This allows the fluid to recirculate
through solenoid valve (11) back to the oil reservoir tank (14) to prevent overheating of fluid. To remove air from
hydraulic hoses, connect one end of hose to the cart disconnect (9) and the other to the bleed adapter. Insert the bleed
adapter into the filler/breather and observe the fluid flow after activating and holding the respective switch (S1, S2, or S3)
in RAISE direction for duration of flow. Fluid flow should be continuous and without air bubbles. When that is