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CAS Color Description
FUEL PRESS LOW Red Fuel pressure is low at the associated (L or
R) engine’s fuel pump inlet.
FUEL XFLO Amber The fuel crossflow valve is not fully opened or
closed as commanded.
FUEL XFLO OPEN White The fuel crossflow valve is open.
STBY PUMP ON White The associated (L or R) standby fuel pump is
receiving electrical power.
Pilot’s Manual
PM-132A 2-35
FUEL QUANTITY SIGNAL CONDITIONER AND PROBES
The fuel quantity signal conditioner is based on two independently
powered left and right wing channels. Each channel receives DC inputs
from their respective wing probes. Both channels independently monitor
the fuselage probe and receive aircraft pitch information from the
AHRS #1 unit. This data significantly increases the accuracy of the fuel
indicating system during climb and descent. Each channel monitors the
data output of the other for calculating total fuel quantity for transmittal
to the DAUs. Although each channel outputs the same fuel quantity
information, the DAUs will only read specific information. DAU #1
reads left quantity and total quantity. DAU #2 reads right quantity and
fuselage quantity. A weight-on-wheels input allows for separate calculation
software to operate “on the ground” or “in the air”, making the
system more accurate in both environments.
A fuel imbalance of 200 pounds or more, will generate the FUEL
IMBALANCE amber CAS. The fuel quantity signal conditioner software
determines low fuel conditions from the filtered fuel quantity. The
L or R FUEL QTY LOW amber CAS is generated when fuel quantity is
less than 350 pounds.
The following CAS illuminations are specific to the fuel quantity indicating
system:
CAS Color Description
FUEL IMBALANCE Amber A fuel imbalance exists between the left and
right wing tanks.
FUEL QTY LOW Amber The fuel quantity in the associated (L or R)
wing tank is approaching a minimum desired
level for flight.
FUEL QTY FAULT White - When message preceded by L or R:
A fault is detected in the associated channel
of the fuel quantity indicating system.
- When message not preceded by
L or R:
The fuselage fuel probe is invalid or attitude
input from the AHRS to the fuel quantity
indicating system is invalid.
Pilot’s Manual
2-36 PM-132A
FUEL INDICATING SYSTEM SCHEMATIC
Figure 2-7
PWR ON
LBS
OFF
OFF
READY
TOTAL FUEL QTY
F
U
E
L
S
Y
S
P
A
N
E
L
D
E
F
U
E
L
PANEL POWER "ON"
DEFUEL SW TCH "OFF"
L GHT SHOULD LLUM NATE
FUEL
PROBE
SIGNAL
L QTY
28 VDC
FUSELAGE
TANK
LEFT
WOW
RELAY
PANEL
FUEL
PROBE
SIGNAL
FUEL QUANTITY
SIGNAL CONDITIONER
DAU
#1
MAINTENANCE
INTERFACE
ADAPTER
FLIGHT
MANAGEMENT
SYSTEM
DAU
#2
RIGHT
WING
TANK
28 VDC
R QTY SPPR
REFUELING
CONTROL PANEL
EICAS
FUEL IMBALNCE (amber)
L R FUEL QTY LOW (amber)
L R FUEL QTY FAULT (white)
LEFT
WING
TANK
FUEL
PROBE
SIGNAL
Pilot’s Manual
PM-132A 2-37
RAM AIR FUEL VENT SYSTEM
The fuel vent system provides ram air pressure to all interconnected
components of the fuel system to ensure positive pressure during all
flight conditions. A flush mounted ram air scoop (NACA vent scoop)
located on the left side of the fuselage (forward of the engine) admits
pressure to the fuselage tank main vent system. The main vent system
pressurizes the wing tanks through the fuel vent/expansion lines. The
fuselage fuel vent/expansion lines are each connected to a separate
sump that has a moisture drain valve. Overpressurization due to thermal
expansion in the wing tanks is relieved through the left and right
expansion lines to the fuselage tank. Overpressurization of the fuselage
tank is relieved overboard through the NACA vent scoop. The vacuum/
pressure relief valve is a backup for the NACA vent scoop.
SINGLE-POINT PRESSURE REFUELING (SPPR) SYSTEM
The Single-Point Pressure Refueling (SPPR) system allows the entire
fuel system to be serviced through a SPPR adapter located on the right
side of the aircraft below the engine pylon. The SPPR incorporates a
precheck system which allows the operator to check the operation of
the system shutoff valves before commencing refuel operations. The
major system components are the refueling adapter, refueling panel,
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