Figure 28-6. Fuel Gauge
28-40-00
Page 28-24
Issued: April 1, 1997
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FUEL PRESSURE GAUGE CHECK .
1.
With electrical power off, the fuel pressure gauge shall indicate the dot ± 1/2 needle width.
2.
Apply positive 14 VDC to the electrical buss. Each needle should move to a position below the red line at 1/2 pounds per square inch.
3.
Place the electrical fuel pump switches in the “ON” position. With fuel in the tanks, the gauge should indicate between the 1/2 and 8 PSI radial lines.
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28-40-00 Page 28-25 Issued: April 1, 1997
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28-40-00 Page 28-26 Issued: April 1, 1997
THE NEW PIPER AIRCRAFT, INC.
PA-44-180
AIRPLANE MAINTENANCE MANUAL
CHAPTER
29
HYDRAULIC POWER
THE NEW PIPER AIRCRAFT, INC.
PA-44-180
AIRPLANE MAINTENANCE MANUAL
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THE NEW PIPER AIRCRAFT, INC.
PA-44-180
AIRPLANE MAINTENANCE MANUAL
CHAPTER 29 - HYDRAULIC POWER
TABLE OF CONTENTS / EFFECTIVITY
CHAPTER/ SECTION SUBJECT GRID NO. EFFECTIVITY
29-00-00 GENERAL 2F2
Description Troubleshooting 2F2 2F4 2R1202
29-10-00 MAIN 2F7 2R1202
Hydraulic Pump Removal Field Service Disassembly from Bracket Disassembly of Motor Assembly from Pump Adapter Assembly Disassembly of Reservoir From Pump-Adapter Assembly Assembly of Reservoir To Pump-Adapter Assembly Installation of Motor Assembly To Pump-Adapter Assembly Installation of Piper Bracket to Pump Assembly Installation of Hydraulic Pump 2F7 2F7 2F7 2F7 2F7 2F8 2F8 2F8 2F8 2F11 2R1202
— Note 2R1202 —
Landing Gear Free-Fall Valve Assembly, Nose and Main Gear Actuating Cylinder removal, inspection, and installation information moved to 32-30-00, Extension and Retraction.
Hydraulic Lines Removal and Installation Testing Hydraulic System 2F12 2F12 2F12
29-Cont./Effec. Page 29-3 Revised: December 6, 2002
THE NEW PIPER AIRCRAFT, INC.
PA-44-180
AIRPLANE MAINTENANCE MANUAL
GRIDS 2E22 THRU 2E24
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29-Cont./Effec. Page 29-4 Revised: December 6, 2002
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AIRPLANE MAINTENANCE MANUAL
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29-00-00 Page 29-5 Revised: December 6, 2002
THE NEW PIPER AIRCRAFT, INC.
PA-44-180
AIRPLANE MAINTENANCE MANUAL
GENERAL
The airplane is equipped with an Oildyne hydraulic pump.
The hydraulic components covered in this chapter consist of the combination hydraulic pump and reservoir, free fall valve, actuating cylinders and hydraulic lines. The brake system, although hydraulically operated, is not included in this chapter as it has its own hydraulic system independent of the gear retraction system. Refer to Chapter 32 for information on the brake system.
— CAUTION —
PRIOR TO STARTING ANY INVESTIGATION OF THE HYDRAULIC SYSTEM, PLACE THE AIRPLANE ON JACKS (REFER TO JACKING, CHAPTER 7).
DESCRIPTION.
Hydraulic fluid to the landing gear actuating cylinders is supplied by an electrically powered reversible pump located in the aft fuselage on the battery shelf between stations 156 and 191. A reservoir is an integral part of the pump. The pump is controlled by a selector switch on the instrument panel to the left of the control quadrant. As the switch is placed in either the up or down position, the pump directs fluid through the particular pressure line to each individual actuating cylinder. Both lines serve either as pressure or return passages depending on the rotation of the pump to retract or extend the gear (Refer to Figure 29-1).
A pressure switch is installed on a cross fitting connected to the pump mount assembly. During retraction the pressure switch is the primary means to shut down the pump. This switch opens the electrical circuit to the pump solenoid when the gear fully retracts and the pressure in the system increases to 1800 ± 100 psi. The switch will continue to hold the circuit open until pressure in the system drops to 200 to 400 psi. At that time the pump will again operate to build up pressure as long as the gear selector handle is in the up position. The down position of the selector does not affect the pressure switch. (For specific pressure refer to Chart 2901.)
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