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to returning it to the reservoir.
SYSTEM 2 HEAT
EXCHANGER HEAT EXCHANGER
SYSTEM 1 HEAT
EXCHANGER
GF1310_009a
If the fluid temperature is sufficiently cooled, a bypass of the exchanger will allow the fluid to go
directly to the reservoir. Fuel in the wing feed tank is the cooling medium.
HYDRAULICS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
13−10−7
HYDRAULIC SHUTOFF VALVE CONTROL PANEL (CONT'D)
System 2 Accumulator
The brake control system uses an accumulator from hydraulic system 2 for brake operations.
SYSTEM 2 BRAKE ACCUMULATOR DIRECT READING GAUGE
GF1310_010
There is a direct reading gauge to check the precharge condition of the accumulator. Refer to the
LANDING GEAR Chapter for more information on the brake control system.
Ground Service Panel
The ground service panel for systems 1 and 2 is located in the aft equipment bay.
HYDRAULICS
Flight Crew Operating Manual Rev 3, Apr 25, 2005
CSP 700−5000−6
Volume 2
13−10−8
HYDRAULIC CONTROL PANEL (1B/2B SWITCHES)
The HYDRAULIC control panel is located on the overhead panel in the flight compartment and
contains the ACMPs switches for hydraulic systems 1 and 2.
Hydraulic 1B and 2B Pump Switches
AC−motor Pump 1B and 2B
Controls the operation of each pump in the following conditions
ON
pump will operate at normal operating pressure.
OFF
AUTO
energize when its system primary pump fails in flight or when the
correct logic is set with slats/flaps not at zero degree position
GF1310_011
− When the correct electrical logic is set the applicable
− Pump is inoperative.
− Pump is in automatic/standby mode. Each pump will
HYDRAULIC
ON
OFF
AUTO
ON
OFF
ON
OFF
AUTO
ON
OFF
AUTO
1B 3A 3B 2B
Manual Mode
Manual mode is accomplished by placing the respective ACMP control switch into either the “OFF”
or “ON” position. Hydraulic pumps 1B and 2B will run when selected to “ON” and their respective
bus is powered. In the “OFF” position each pump is inoperative for all operating conditions.
Auto Mode
When the pump switch is set to “AUTO” the respective pump automatically starts under one of the
following conditions:
· When the correct electrical logic is determined by the Alternating Current Power Center
(ACPC), either slats or flaps are not at the zero degree position and at least one Variable
Frequency Generator (VFG) operating.
· When the primary pump falls below normal system pressure (£ 1800 psi) in flight.
Ground Operation Inhibits
On ground with the APU as the single source of electrical power, only one ACMP is allowed to
operate.
Start inhibit is provided for 1B and 2B “AUTO” mode of operation (no engines running), to enhance
system safety during normal maintenance operations. For normal operation on the ground, the
applicable system 1 or 2 ACMP requires at least one engine to be operating, with “AUTO” mode
selected.
The 1B or 2B pump will not come on automatically (“AUTO” mode selected and flap less than zero
degrees), in support of a primary pump failure on the ground.
HYDRAULICS
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
13−10−9
HYDRAULIC CONTROL PANEL (1B/2B SWITCHES) (CONT'D)
Flight Operation
The normal pump switch configuration for in flight hydraulic systems 1 and 2 operation is “AUTO”
mode of operation.
The 1B or 2B pump will come on automatically (“AUTO” mode selected) in support of the
applicable primary pump failure in flight. When an ACMP is commanded on due to a low pressure
condition of the primary pump, that ACMP will remain on for a minimum of 5 minutes (including
touchdown) unless “ON” or “OFF” is selected. This is required to prevent ACMP overheating due
to continuous restarts if the low pressure alternates above and below 1800 psi.
During single VFG operation, ACMPs 1B and 2B are load shed since their respective busses are
disconnected from the remaining good generator.
HYDRAULICS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
13−10−10
HYDRAULIC SYSTEM 1 SCHEMATIC
AC
PUMP
1B
LEFT ENGINE
DRIVEN PUMP
M
FIREWALL
VALVE
System pressure
Suction pressure
HEAT EXCHANGER
CASE DRAIN FLUID
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