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>1800 psi.
• Amber – Low
pressure < 1800 psi.
Outboard Brake
Pressure Readout
Displays pressure in the
outboard brake system.
• NORM Green –
>1400 psi.
• LO PRESS Amber –
<1400 psi.
Inboard Brake
Pressure Readout
Displays in increments
of 50 psi, pressure in
the inboard brake system.
• Green - between 1800
and 3200 psi.
• Amber – 1800 psi.
• White – 3200 psi.
<
>
P I LOT T R A I N I N G GU I D E
HYDRAULICS
12-8 For Training Purposes Only
Sept 04
HYDRAULIC SYNOPTIC PAGE (Cont)
RUD
L ELEV
L AIL
FLT SPLRS
GND SPLRS
L REVERSER
RUD
ELEV R
AIL R
FLT SPLRS
GEAR
REVERSER R
RUD
L ELEV R
L AIL R
GND SPLRS
GEAR
NOSE STEER
PARK/EMER BRAKE
INBD
BRAKES
PSI
3000
OUTBD
BRAKES
NORM
3A 3B 2B
HYDRAULIC
3000
PSI
3000
PSI
2A
3000
PSI
45 °C
1B
60%
45 °C
54%
45 °C
60%
1A
GX_12_008
Fluid Quantity
Symbol and readout
Displays, increments
of 2%, reservoir fluid
quantity in the
corresponding
system.
System Distribution Table
Displays status of
corresponding airplane
systems powered by
system 1, 2, or 3.
• White – Adequate pressure
>1800 psi to operate.
• Amber – Hydraulic supply to
system inoperative <1800 psi.
Hydraulic Pressure Readout
Displays, increments of 50, hydraulic
pressure in the corresponding system,
Normal operating pressure is 2950 to
3050 psi.
• White – Hydraulic pressure >3200 psi.
• Green – Hydraulic pressure >1800 psi
and 3200 psi.
• Amber – Hydraulic pressure 1800 psi.
<
<
Shutoff Valve to
Engine Flow Line
The flow line from the
fire wall SOV to the
engine will display red
if the SOV fails to close,
when the fire handle
is pulled.
Hydraulic Shutoff Valve
Position Indicator
Displays valve open,
closed and invalid data.
Hydraulic Fluid Temperature
Readout
Displays, increments of 2°C,
reservoir fluid temperature in
the corresponding system.
• Green <96 C (205 F).
• Amber 96 C (205 F).
° °
> ° °
For Training Purposes Only
Sept 04
12-9
P I LOT T R A I N I N G GU I D E
HYDRAULICS
HYDRAULIC SYNOPTIC PAGE SYMBOLS
The following represents the EICAS symbols and flow line logic for the hydraulic
synoptic page. The symbols are shown in serviceable and failure conditions.
EICAS PHILOSOPHY
GX_12_009
VALVE AND FLOW LINE LOGIC
DIRECTION OF FLOW
VALVE
NOT FAILED
VALVE
FAILED
OPEN
CLOSED
TRANSIT
INVALID
PUMP AND FLOW LINE LOGIC
INVALID
OFF
ON
PUMP
FAILED
OFF
PUMP
FAILED
ON
DIRECTION OF FLOW
P
P
P
P
P
VALVE FAILED
FIRE HANDLE PULLED
VALVE FAILED TRANSIT
FIRE HANDLE PULLED
P I LOT T R A I N I N G GU I D E
HYDRAULICS
12-10 For Training Purposes Only
Sept 04
DESCRIPTION
HYDRAULIC SYSTEM 1 AND 2
Each system comprises an EDP, reservoir, ACMP, manifolds with pressure, return and
case drain filters, hydraulic shutoff valve, heat exchanger, and ground servicing panel.
Hydraulic overfill bottles for system 1 and 2 are provided and located near their
system components.
ENGINE-DRIVEN PUMPS
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 hydraulically-actuated components.
AFT EQUIPMENT BAY COMPONENTS
GX_12_010
Engine-Driven Pump
Located on the accessory
drive of each engine
GX_12_011
Reservoirs
ACMPs
Direct
Reading
Gauge
Filter
Manifolds
For Training Purposes Only
Sept 04
12-11
P I LOT T R A I N I N G GU I D E
HYDRAULICS
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.
AC-MOTOR PUMPS (ACMP’S)
The backup ACMPs 1B and 2B pumps are normally operated in the AUTO mode and
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