庞巴迪挑战者手册9(39)

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Fuselage Tank....................................................................................... 2-20
Fuel System Schematic
Aircraft without Fuel Heaters (Figure 2-5)................................... 2-21
Aircraft with Fuel Heaters (Figure 2-6)......................................... 2-23
Fuel Control Panel Switches and Indicators.................................... 2-25
JET PUMP Switches ........................................................................ 2-25
STANDBY PUMP Switches .................................................... ........ 2-25
CROSSFLOW Switch............................................ ........................... 2-26
FUS TANK XFR-FILL Switch . ........................................................ 2-26
FUS TANK GRAV XFR Switch....................................................... 2-27
FUS TANK Switch Priority ............................................................. 2-27
FUS TANK FULL Light.... ............................... ................................ 2-28
FUS TANK EMPTY Light ......................................... ...................... 2-28
Standby Pump Lights ................... .................................................. 2-28
Fuel Control Panel (Figure 2-7) ............ ........ .................................. 2-28
Fuel Valve Lights......................................................... ..................... 2-29
WING FULL Lights .. ................................................ ........ ............... 2-29
Fuel Quantity Indicator and Selector Switch........ ........ ............... 2-29
Fuel Counter ..................................................................................... 2-29
Fuel System Glareshield Lights ......................................................... 2-30
FUEL PRESS Lights .................... ............ ......................................... 2-30
FUEL FILTER Light ...................................................................... ... 2-30
LOW FUEL Light ............. ............................................................... 2-31
FUEL XFLO Light .......... ........... .......... .. ..................................... ..... 2-31
Ram Air Fuel Vent System.......... .... ...... .. ................................. ........... 2-31
Single-Point Pressure Refuel (SPPR) System .......... ......................... 2-31
Wing and Fuselage Precheck Valves ........ ..................................... 2-32
Single-Point Refuel System Schematic (Figure 2-8) .................... 2-33
Learjet 31A
Pilot's Manual
TABLE OF CONTENTS (Cont)
Refuel Selector Switch .. ........... ...... .. ............... .. .. .. ...... .. .... .. .. .. .. .. .. .. . 2-35
Remote Battery Switch . ......... .. ...... .. ............... ...... ...... .. .... .... .... .. .. ...2-35
FUS FULL Light....... .... .. ................... .. ...... .. ........... ...... .. .. .. ...... .. .. .. ... 2-35
VENT OPEN Light .. .... .. ................... .. ................... ...... .. .... .. .... .. .... ...2-35
Fuel Additive.. .. ........... .......... ............... ........ .. ..................... .. ............ ... 2-36
Refueling ..... .... .. ................... .. .. .... .. ....... ........ .. .......... . . ..... .. .. .. ........ .... ... 2-36
Fuel Drains (Figure 2-9) ..... .. ........ ........... ...... .. ........ ........... .. ...... .. .......2-37
Learjet31A
Pilot's Manual
ENGINES
SECDOnN OD
ENGINES & FUEL
The aircraft is powered by two TFE731-2-3B turbofan engines manufactured
by Garrett Division of Allied Signal. These engines are twospool,
geared transonic-stage, front-fan, jet-propulsion engines. Each
engine is rated at 3500 pounds thrust at sea level.
A spinner and an axial-flow fan are located at the forward end of the
engine and are gear driven by the low-pressure rotor. The fan gearbox
output-to-input speed ratio is 0.556. The low-pressure rotor consists
of a four-stage low-pressure axial compressor and a three-stage
low-pressure axial turbine, mounted on a common shaft. The highpressure
rotor consists of a single-stage high-pressure centrifugal
compressor and a single-stage high-pressure axial turbine, mounted
on a common shaft. The high-pressure rotor drives the accessory
gearbox through a transfer gearbox. The rotor shafts are concentric, so
that the low-pressure rotor shaft passes through the high-pressure rotor
shaft.
An annular duct serves to bypass fan air for direct thrust and also diverts
a portion of the fan air to the low-pressure compressor. Air from
the low-pressure compressor flows through the high-pressure compressor
and is discharged into the annular combustor. Combustion
products flow through the high- and low-pressure turbines and are
　
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