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Figure 1-2. Hydraulic Kneeling/Erecting Cart Major Internal Components
TM-1-1730-231-13P Hydraulic Kneeling/Erecting Cart P/N: 10064-10 Manual
Figure 1-3. Hydraulic Schematic
TM 1-1730-231-13&P c. Motor and Pump Assembly.   The motor (Figures 1-2 and 1-4) receives 24 volt direct current (vdc) supply from either the aircraft,   _F auxiliary power unit or batteries. The motor is a 1.5 horse power (hp), 1,800 revolutions per minute (rpm),  totally  enclosed  non  ventilated  motor  and  drives  the  hydraulic  gear  pump  through  the  flexible  coupling  which connects the motor output to pump input shafts. The pump rotation is clockwise and it pumps out minimum of 1.2 (gpm) at  1,000  psi  and  0.4  gpm  at  3,000  psi.  The  motor/pump  adapter  attaches  the  pump  to  the  motor.  A  case  covers  the motor, start relay, circuit breaker, and electromagnetic interference filter to protect them from environment. d. Reservoir Assembly.  The reservoir assembly consists of a reservoir tank which can store 5 gallons of hydraulic fluid (MIL-H-5606 or MIL-H-83282) and supplies it for cart functions. A reservoir plate cover on top allows for reservoir clean out and incorporates the breather/filler with removable cap and the bleed adapter stored in the filler cavity. Four fluid level sight glasses are installed on the reservoir front side.  The level at lowest level sight glass indicates the least amount of fluid required to operate the pump. The level at next higher sight glass indicates the normal operating level. The level at third higher sight glass indicates that the reservoir is full. The fluid level at uppermost sight glass indicates that the reservoir is about to overflow if more fluid is taken in. A drain plug is installed at the bottom of the reservoir. A suction strainer is installed inside the reservoir and a connection from the rear of the reservoir leads to the gear pump. e. Hydraulic  Piping  Assembly.  The  hydraulic  piping  assembly  consists  of  tubes,  tees,  elbows,  and  connectors connecting between reservoir, gear pump, filter, and the manifold (Figure 1-3). The filter is located in the outlet line from the gear pump and is easily accessible by lifting up the control panel cover. A 1 micron disposable filter element within the filter gives the pressurized fluid a final cleaning before outlet to the helicopter struts. A clogging indicator on the top of  the  filter  indicates  high  differential  pressure  between  the  filter  inlet  and  outlet.  Should  the  filter  element  become clogged, a red marker will extend to show element requires replacement. f. Electrical  Wiring/Components  Assembly.    A  30  feet  (ft)(762  mm)  24  vdc  shielded  power  cable  with  power receptacle to mate with aircraft power plug is attached to the cart and stowed in the storage area. Another short cable with power plug at one end and battery clips/ connections at the other end is also stowed in storage area. Another 50 ft (1270 mm) cable with non ferrous metallic controller is stowed in the storage area. The controller has four toggle switches and a POWER ON indicating light. One toggle switch is a maintained contact switch used for pump ON/OFF  operations.    The  other  three  toggle  switches  are  momentary  contact  and  are  used  for  tall,  left,  and  right RAISE/LOWER operations to erect/kneel the helicopter struts. These toggle switches are fail-safe controls to prevent a fully loaded helicopter from lowering (kneeling) without the proper switches being 1-4

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