Piper Arrow IV Turbo Maintenance Manual page 337

CHART 2902. LEADING PARTICULARS, HYDRAULIC SYSTEM
Hydraulic Pump
High Pressure
Low Pressure
Flow Rate @ 1000 psi
High Pressure Control
Thermal Relief
Hydraulic Fluid
Pressure Switch
Open (OFF) Pressure
Close (ON) Pressure
MAIN.
HYDRAULIC PUMP.
REMOVAL OF HYDRAULIC PUMP.
The hydraulic pump with reservoir incorporated is located in the aft section of the fuselage. Access to the
pump is through the access panel in the aft wall of the baggage compartment.
1. Disconnect the pump electrical leads from the pump solenoid relays and the ground wire from the
battery shelf.
2. Disconnect the hydraulic lines from the pump. Cap the line ends to prevent contamination.
3. Remove the pump by removing the pump attaching bolts.
DISASSEMBLY OF HYDRAULIC PUMP. (Refer to Figure 29-5.)
After the hydraulic pump has been removed from the airplane, cap or plug all ports and clean the exterior
of the pump with a dry type solvent to remove accumulated dust or dirt. To disassemble any one of the three
main components of the pump, proceed as follows:
1. The base of the pump may be removed from the case as follows:
A. Cut the safety wire and remove the bolts with washers that secure the base to the pump case.
B. The shuttle valve within the base should be removed for cleaning purposes only. To remove the
valve, cut safety wire. Remove plug with spring and valve.
The shuttle valve and pump base are matched, lapped parts.
Should it be necessary to replace, replace as an assembly only.
PIPER AIRCRAFT
PA-28RT-201 / 201T
MAINTENANCE MANUAL
67509
1600 to 2000 psi
650 ± 150 psi
45 cu. in. per min.
1600 to 2000 psi
4000 psi
MIL-H-5606
1400 ± 100 psi
400 ± 200 psi below
opening pressure
—NOTE—
2C10
67509-02
2000 to 2500 psi
650 ± 150 psi
45 cu. in. per min.
2000 to 2500 psi
2000 to 2500 psi
MIL-H-5606A
1800 ± 100 psi
300 ± 100 psi below
opening pressure
29-10-03
Page 29-16
Revised: November 6, 1979