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cabin altitude
• Green below 14,000-foot cabin altitude
MANUAL CABIN PRESSURE
DUMP
Manually actuate the CABIN DUMP switch
(see Figure 12-3) at any time DC or EMER
power is available to reduce cabin pressure
and rapidly ventilate the cabin. The maximum
altitude limit valves override the climb solenoid
valves to prevent complete cabin depressurization
above 14,300 ± 300 feet altitude.
EMERGENCY/
ABNORMAL
For specific information on emergency/abnormal
procedures, refer to the appropriate abbreviated
checklists or the FAA-approved Airplane
Flight Manual (AFM).
CABIN PRESS
X1000
+1
ALT FT RATE FPM
DEST ELV
DIFF PSI
0 5 10
9930 0
0.0
9930
0
0 -1
5
10
15
Figure 12-6. Cabin Pressure Display
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CHAPTER 13
HYDRAULIC POWER SYSTEMS
CONTENTS
Page
INTRODUCTION ................................................................................................................ 13-1
GENERAL ............................................................................................................................ 13-1
DESCRIPTION .................................................................................................................... 13-3
COMPONENTS.................................................................................................................... 13-3
Reservoir ........................................................................................................................ 13-3
Pump............................................................................................................................. 13-3
Hydraulic Accumulator ................................................................................................ 13-3
Pressure Switches ......................................................................................................... 13-3
System Relief Valve....................................................................................................... 13-5
Filters ............................................................................................................................. 13-5
CONTROLS AND INDICATIONS...................................................................................... 13-5
HYD PRESS LO Message ............................................................................................ 13-5
HYD PUMP ON Message............................................................................................. 13-5
Hydraulic Reservoir Sight Gauge.................................................................................. 13-5
Hydraulic Accumulator Pressure Gauge ....................................................................... 13-5
Manual Accumulator Bleed Valve................................................................................. 13-6
OPERATION........................................................................................................................ 13-6
Preflight ......................................................................................................................... 13-6
In Flight ......................................................................................................................... 13-6
EMERGENCY/ABNORMAL .............................................................................................. 13-6
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ILLUSTRATIONS
Figure Title Page
13-1 Hydraulic System Schematic ................................................................................. 13-2
13-2 Hydraulic Reservoir and Location ......................................................................... 13-4
13-3 Hydraulic Reservoir Sight Gauge .......................................................................... 13-4
13-4 Hydraulic Accumulator Pressure Gauge................................................................ 13-6
13-5 Manual Accumulator Bleed Valve ......................................................................... 13-6
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GENERAL
The hydraulic system permits the application
of substantial force by converting a volume of
fluid flow into pressure on a hydraulic piston.
Hydraulic fluid lines provide the capability to
transmit that force wherever it is required in
the aircraft without heavy or complex mechanical
　
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