Identification Of Power Pack - Piper Navajo PA-31 Service Manual

200
P I
P E R A
I R C R A F
T C O .
PIPER AIRCRAFT CORP.
LOCK HAVEN, PENNSYLVANIA
LOCK HAVEN, PA
PART NO.
SER NO.
PART NO. WTC2135-1
SER. NO. WTC
CONF. OAS 2930.3
WEIGHT 10.5 POUNDS
REVISION
ASSY
DATE
REVISION I
ASSY DATE
REVISION
ASSY DATE
PRESS. 1800 PSI FLUID MIL-H-5606
VOLTAGE 24 3V DC RESISTIVE AMPS 5
VOLTAGE 24±3 VDC RESISTIVE AMP 5
RESERVOIR CAPACITY 109 CU INCHES MIN
RESERVOIR CAPACITY
109 CU INCHES MIN.
RESERVOIR CAPACITY
109
CPRIMARY RELIEF VALVE SETTING 1900 PSI
PRIM
REL
VALVE SETTING 1800 PSI
FULL
FLOW MAX. UNIT WEIGHT 9.5 LB DRY
DESIGNED AND
MANUFACTURED
BY
DESIGNED AND
MANUFACTURED BY:
OZONE AIRCRAFT SYSTEMS
INC. WIEBEL TOOL CO., INC.
101.32 101ST ST. OZONE PARK 16. N. Y.
P.O. BOX 26 PORT JEFFERSON, N.Y. 11777
Figure 6-8. Identification of Power Pack
6-17. DISCONNECTING TEST UNIT.
a. Ascertain that the landing gear selector handle is in the down neutral position, and that the
landing gear is down and locked.
b. Shut down the test unit per instruction supplied with unit.
c. On early model airplanes disconnect the test unit suction and/or pressure hoses at the fire wall
and/or filter fittings. Ascertain that there is fluid in the suction and/or pressure hoses from the airplane's
hydraulic pump before reconnecting the hoses to the respective fittings.
d. On later model airplanes close the suction, fill and drain valve in the airplane by placing the
control lever in the down position and disconnecting the test unit hose from the fitting. Reinstall the
protective cap over the fitting. Also disconnect and remove the test unit pressure hose from the pressure
fitting in the airplane if previously connected. Reinstall the protective cap on the fitting.
e. Check fluid level in the Power Pack reservoir and check system for leaks.
f. Install the engine cowl if removed (refer to Installation of Engine Cowl, Section VIII), or right
access panel of nose section on later models.
6-18. HYDRAULIC TEST UNIT (OPTIONAL). Multi-purpose hydraulic test units can be used to provide
the same functions as the Piper unit; however, the test unit must be capable of duplicating and monitoring
the operating pressures and flow rate given in Table VI-I or VI-II.
6-19. IDENTIFICATION OF POWER PACKS. The manufacturer's identification placard located on the
Power Pack reservoir body as shown in Figure 6-8 should be used to determine which Power Pack is in the
airplane being serviced. The placard furnishes the part number, revision letter, and serial number of each
unit, plus the operating pressure of the Power Pack.
Reissued: 10/12/79
HYDRAULIC SYSTEM
2B7
PIPER NAVAJO SERVICE MANUAL