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MASTER
Hydraulic Systems Overview
Figure 14--10--2
NOSE LANDING
GEAR & STEERING
AND BRAKE CONTROL
MAIN LANDING
GEAR & INBD
BRAKES
OUTBD
BRAKES
AILERON
SPOILERON
FLIGHT
SPOILER
OUTBD
GROUND
SPOILER
INBD
GROUND
SPOILER
No. 1
ENGINE
DRIVEN
PUMP
LEGEND
SYSTEM 1
SYSTEM 2
SYSTEM 3
RUDDER
No. 3A
AC MOTOR
PUMP
No. 1B
AC MOTOR
PUMP
No. 2
ENGINE
DRIVEN
PUMP
No. 3B
AC MOTOR
PUMP
No. 2B
AC MOTOR
PUMP
REV 56, Jan 31/03
Vol. 1 14--10--4
HYDRAULIC POWER
Introduction
Flight Crew Operating Manual MASTER
CSP A--013
THIS PAGE IS INTENTIONALLY LEFT BLANK
Vol. 1 14--20--1
REV 56, Jan 31/03
HYDRAULIC POWER
Systems 1 and 2
Flight Crew Operating Manual
CSP A--013
MASTER
1. HYDRAULIC SYSTEMS NO.1 AND NO.2
Each hydraulic system consists of the following components:
S Engine driven pump (EDP)
S AC motor pump (ACMP)
S Shutoff valve
S Reservoir
S Accumulator
S Pressure and return manifolds
S Filters
S Ground servicing panel.
Both No.1 and No.2 systems share a ram air heat exchanger for fluid cooling. Fluid from
each system is not mixed with the other system as it passes through the heat exchanger. A
fan within the heat exchanger assists in cooling the hydraulic fluid when the aircraft is on the
ground.
REV 56, Jan 31/03
Vol. 1 14--20--2
HYDRAULIC POWER
Systems 1 and 2
Flight Crew Operating Manual MASTER
CSP A--013
Hydraulic Systems 1 and 2 Schematic
Figure 14---20---1 Sheet 1
P P
S S
T
RETURN
FILTER
RETURN
MANIFOLD
BYPASS
VALVE
GROUND
SERVICE
NITROGEN
ACCUMULATOR
PRESSURE RESERVOIR
RELIEF/BLEED
VALVE
CASE
DRAIN
FILTER
PRESSURE
SWITCH
PRESSURE
TRANSDUCER
FILTER
CASE DRAIN
FILTER
ACMP 1B
PRESSURE
SWITCH
PRESSURE
RELIEF
VALVE
EDP 1A
FIREWALL
SOV
TO HYDRAULIC
SERVICES
HEAT
EXCHANGER
AND FAN
GROUND
SUCTION
GROUND
PRESSURE
PRESSURE MANIFOLD
LEGEND
Pressure (Red).
Return (Green).
Case drain (Yellow).
Pump case
filter drain.
SYSTEM 1
PRESSURE
GAUGE
GROUND
SERVICE
FILLING
Vol. 1 14--20--3
REV 56, Jan 31/03
HYDRAULIC POWER
Systems 1 and 2
Flight Crew Operating Manual
CSP A--013
MASTER
Hydraulic Systems 1 and 2 Schematic
Figure 14---20---1 Sheet 2
P P
S S
T
RETURN
MANIFOLD
BYPASS
VALVE
ACCUMULATOR
RESERVOIR
PRESSURE
RELIEF/BLEED
VALVE
CASE
DRAIN
FILTER
PRESSURE
SWITCH
PRESSURE
TRANSDUCER
FILTER
CASE DRAIN
FILTER
ACMP 2B
PRESSURE
SWITCH
PRESSURE
RELIEF
VALVE
EDP 2A
FIREWALL
SOV
TO HYDRAULIC
SERVICES
TO HEAT
EXCHANGER
AT SYSTEM 1
GROUND
SUCTION
GROUND
PRESSURE
PRESSURE MANIFOLD
LEGEND
Pressure (Red).
Return (Green).
Case drain (Yellow).
Pump case
filter drain.
SYSTEM 2
FROM
OUTBOARD
BRAKE
RETURN
FILTER
GROUND
SERVICE
FILLING
PRESSURE
GAUGE
GROUND
SERVICE
NITROGEN
REV 56, Jan 31/03
Vol. 1 14--20--4
HYDRAULIC POWER
Systems 1 and 2
Flight Crew Operating Manual MASTER
CSP A--013
A. Engine Driven Pumps
EDP’s 1A and 2A draw fluid from their respective reservoirs through firewall shutoff
valves. Fluid is pumped at 3000 psi to the applicable pressure manifold, filtered and
distributed to the aircraft hydraulically actuated components.
B. AC Motor Pumps (ACMP)
Each ACMP provides a nominal outlet pressure of 3000 psi. AC motor pump 1B is
powered from AC bus 2 and AC motor pump 2B is powered from AC bus 1. Each AC
motor pump is controlled by a separate switch on the HYDRAULIC pump control panel
located on the overhead panel in the flight compartment. When a pump switch is set to
AUTO, the pump will automatically start under the following conditions:
S IDG 2 must be operating for hydraulic pump IB operation
S IDG 1 must be operating for hydraulic pump 2B operation
S IDG 1 or IDG 2 must be operating for ACMP 3B operation
　
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