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approximately 75% Fan Speed (Ni). The thrust reverser is stowed by
first returning the thrust reverser lever to the idle/deploy stop and then
moving the lever to the stow (full down) position at engine idle speed.
PM-121
2-19
Change 3
Pilot's Manual
Learjet 31A
AIRCRAFT FUEL SYSTEM
The aircraft fuel system consists of two wing tanks, a fuselage fuel
tank, a fuel supply system, a fuel quantity indicating system, a fuel
transfer system and a fuel vent system. Fuel fillers are located outboard
near each wing tip. An optional single-point refuel (SPPR) systemmayalso
be installed.
WING TANKS
The wing is divided by a center bulkhead into two separate fuel-tight
compartments which serve as fuel tanks. Each tank extends from the
center bulkhead outboard to the wing tip rib, thus providing a separate
fuel supply for each engine. A tank crossflow valve is installed to
permit fuel transfer between wing flanks . Center bulkhead relief
valves prevent wing tank over-pressurization during fuel crossflow
operations. Flapper-type check valves, located in the various wing
ribs, allow free fuel flow inboard but restrict outboard fuel flow. Ajet
pump and an electric standby pump are mounted in each wing tank
near the center bulkhead to supply fuel under pressure to the respective
engine fuel system . An electric scavenge pump, located in the forward
inboard section of each wing tank, is used to transfer fuel to the
section containing the main fuel pumps and is operated by the lowfuel
float switch. Alet type transfer pump, located outboard of the
wheel well in the aft portion of each wing tank, transfers fuel to the
section containing the main fuel pumps. A filler cap, located in the
outer section of the wing tank, is used for fuel servicing.
FUSELAGE TANK
The standard fuselage tank consists of two bladder-type cells located
in the aft fuselage . The tank is equipped with a fuel probe, float
switch and transfer pump. When the airplane is being refueled
through the wing fillers, the tank is filled by the wing standbypumps
through two transfer lines and two transfer valves. When the tank is
full, the float switch deenergizes the wing standby pumps and closes
the transfer valves. Fuel can be transferred to the wing tanks by two
methods: normal transfer and gravity transfer. During the normal
fuel transfer, the fuselage tank transfer pump will pump fuel into
both wing tanks. During gravity transfer, fuel will flow to both wing
tanks through both transfer lines. The extended range (ER) fuselage
tank incorporates two additional bladder-type cells installed immediately
forward of the main fuselage fuel cells. Fuel from the ER fuel
cells gravity flows into the main fuselage fuel cells through interconnecting
tubes.
2-20
PM-121
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Learjet 31A
Pilot's Manual
FUEL CONTROL PANEL SWITCHES AND INDICATORS
The fuel control panel (Figure 2-7) incorporates all the necessary
switches and indicators to fuel the aircraft (when using the over-thewing
method) and to maintain proper fuel management.
JET PUMP SWITCHES
The JET PUMP switches, on the fuel control panel, control the motive
flow valves. Setting a JETPUMP switch to ON opens the corresponding
motive flow valve and allows high-pressure fuel from the corresponding
engine-driven fuel pump to flow to the corresponding jet
pumps. The JET PUMP switches normally remain ON at all times.
　
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