曝光臺(tái) 注意防騙 網(wǎng)曝天貓店富美金盛家居專營(yíng)店坑蒙拐騙欺詐消費(fèi)者

for system 1 and 2 are provided and located near their system components.
Engine Driven Pump
EDP − Located on the accessory
drive of each engine.
GF1310_005
The EDPs 1A and 2A are used as primary pumps and draw fluid from the reservoirs through
hydraulic shutoff
valves. Fluid is delivered to the applicable manifold, filtered and distributed to
the airplane’s hydraulicallyactuated
components.
Aft Equipment Bay Components
RESERVOIR 2
FILTER
ACMP’S
DIRECT
READING
GAUGE
GF1310_006a
RESERVOIR 1
MANIFOLDS
Reservoir
System 1 and 2 reservoirs are located at the top of the aft equipment bay. Fluid quantity and
temperature transducers are located on the reservoir and are indicated on the HYDRAULIC
synoptic page.
HYDRAULICS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
13−10−5
HYDRAULIC SYSTEM 1 AND 2 (CONT'D)
ACMotor
Pumps (ACMPs)
The backup
ACMPs 1B and 2B are normally operated in the AUTO mode and come on
automatically during takeoff,
approach and landing or in support of a primary pump failure.
ACMPs 1B and 2B are powered from AC bus 3 and AC bus 2, respectively. Both pumps are
controlled by separate toggle switches on the flight compartment HYDRAULIC control panel. Refer
to External and APU Electrical Pump operation in this Chapter for external/APU ground services.
Filter manifold
The filter manifold for system 1 is located on the left side of the aft equipment bay and on the right
side for system 2. Each hydraulic system accommodates pressure, return and case drain (pump
lubrication fluid) filters and a system pressure relief valve. They also contain filter “popup”
indicators to show when the filters are clogged. Two pressure switches and a transducer are part
of the pressure manifold and are used to provide EICAS displays for pump failures and loss of
system pressure. Fluid quantity and temperature transducers are located on the reservoir and are
indicated on the HYDRAULIC synoptic page.
HYDRAULIC SHUTOFF VALVE CONTROL PANEL
Two switches are provided on the HYDRAULIC shutoff valve panel to isolate the applicable shutoff
valve in the event of a hydraulic overtemperature. These switches should not be selected closed with
the engine running except for isolation in the event of system overtemp. The engine driven pump will
cavitate and greatly reduce the efficiency and life of the pump.
Left/Right Hydraulic Shutoff
Valve Switches
GF1310_007
Controls the operation of the hydraulic shutoff
valve in the following condition:
CLOSED − When the switch is selected it isolates the hydraulic fluid to the
respective engine driven pump by closing the hydraulic shutoff
valve.
L HYD SOV
HYDRAULIC
CLOSED
R HYD SOV
CLOSED
The purpose of hydraulic fluid isolation is to permit the fluid to cool and control the overtemperature,
without having to shut down the engine. These switches are normally not closed. They operate in
parallel with the switch in the fire handle to control the operation of the applicable hydraulic shutoff
valve.
HYDRAULICS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
13−10−6
HYDRAULIC SHUTOFF VALVE CONTROL PANEL (CONT'D)
Hydraulic Shutoff Valves
Electricallyoperated
shutoff valves (normally open) are installed on the suction lines for the
enginedriven
pumps 1A and 2A and their position is indicated on the HYDRAULIC synoptic page.
GF1310_008
70°C 68°C 70°C
HYDRAULIC
1B 3A 3B 2B
62 % 64 % 62 %
HYDRAULIC SYNOPTIC PAGE
R HYD SOV
CLOSED
DISCH
PULL
1 2
The corresponding hydraulic shutoff valve is motored closed during an engine fire condition (fire
handle pulled) or selection of a HYD SOV switch. Selection of a HYD SOV switch will illuminate
a “CLOSED” legend on the switch to indicate the switch position. When the hydraulic shutoff valve
is closed, a “L− R HYD SOV CLSD” white status message (described in FIRE PROTECTION
Chapter 9) is displayed on EICAS. Deselection
of either the fire handle or HYD SOV switch will
command the SOV open and extinguish the message. Deselecting
the HYD SOV switch will
extinguish the “CLOSED” legend.
Heat Exchanger
System 1 heat exchanger is positioned within the left fuel feed tank and system 2 in the right. The
purpose of each exchanger is to cool the case drain fluid (lubrication fluid within each pump), prior
　
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：Bombardier_Global_000-Hydraulics(3)