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a manual control valve. As the lever is moved towards UP, outside
static air pressure is vented to the outflow valve control chamber
causing the valve to open. When the lever is moved towards DN, cabin
pressure is vented to the outflow valve control chamber causing
the valve to dose.
CABIN ALT/DIFF PRESS GAGE
The cabin altimeter/differential pressure gage, on the pressurization
control panel, is vented to both outside air pressure and cabin air
pressure. The indicator has two pointers, each travels over a separate
calibrated scale. The large pointer sweeps over the outside scale to indicate
cabin altitude. The CABIN ALT scale is marked from 0 to
50,000 feet in 1000-foot increments. The small pointer sweeps over the
inside scale to indicate differential pressure in psi. The DIFF PRESS
scale is marked from 0 to 10 psi in 02-psi increments.
CABIN CLIMB INDICATOR
The rate of change in cabin pressure altitude is indicated in feet per
minute on theCABIN CLIMB indicator located on the pressurization
control panel. The indicator face is marked from 0 to 6000 feet per
minute in both UP and DOWN directions. The instrument functions
similarly to the aircraft vertical speed indicator but is vented to cabin
pressure only.
EMER PRESS OVERRIDE SWITCHES
Emergency pressurization override switches are provided to allow
takeoffs and landings at field elevations higher than the emergency
pressurization aneroid switch settings (9500 [+1.50] feet). The switches
are located on the copilot's switch panel and are labeled EMER PRESS
OVERRIDE -NORMAL L and R. With the switches in OVERRIDE position,
the emergency pressurization aneroid switches are electrically
isolated from the emergency pressurization valves; thus preventing
the valves from opening when the aneroid switches activate. When
the override switches are in the NORMAL position, actuation of the
aneroid switches will open the emergency pressurization valves. The
switches will have no effect if the BLEED AIRswitches are in the OFF
or EMER position.
6- 24
PM-121
Original
Learjet 31A
Pilot's Manual
CAS ALT LIGHT
Should the cabin altitude exceed 8750 (±250) feet, an aneroid switch
will close to illuminate the amberCABALT light on the glareshield annunciator
panel. The aneroid switch will also deactivate the AUTO
pressurization mode to stop the cabin altitude from rising any higher if
the malfunction was in that control system . The aneroid switch will reset
at a lower cabin altitude, reenergizing the automatic control system
and extinguishing the CAB ALTlight.
CABIN ALTITUDE WARNING HORN
Acabin altitude aural warning horn will sound to alert the crew should
the cabin altitude reach 10,100 (±250) feet. Thehomis controlled by an
aneroid switch which will apply a ground to the warning horn circuit
when actuated. The cabin altitude warning horn circuit is tested
through the system test switch on the pilot's instrument panel. The
MUTE switch on the right thrust lever may be used to interrupt the
horn for approximately 60 seconds in the event the horn sounds. The
cabin altitude warning horn is operative during EMER BUSmode.
SYSTEM TEST SWITCH-CABIN ALTFUNCTION
The rotary-type system test switch on the pilot's instrument panel is
used to test the cabin altitude warning system. Rotating the switch to
CABIN ALT and depressing the switch PRESS TEST button will provide
a ground simulating the 10,100-foot aneroid switch actuation.
During the test sequence,MUTE switch operation mayalso bechecked.
AIR CONDITIONING AND HEATING
Primary heating and cooling is accomplished by controlling the temperature
of the bleed air entering the cabin air distribution systems. On
aircraft 31-035 thru 31-190, an R12 freon-based cooling system is installed
to provide additional cooling at altitudes below 35,000 feet and
during ground operations . On aircraft 31-191 and subsequent, an R134A
refrigerant-type cooling system is installed to provide additional cooling.
Anauxiliary (electrical) cabin heating system is installed toprovide
additional cabin heating, if required.
Pilot's Manual
Learjet 31A
PRIMARY HEATING AND COOLING- BLEED AIR
Cockpit and cabin temperature is regulated by controlling the temperature
of the pressurization bleed air entering the cabin air distribution
system. With the BLEED AIR switches ON and the CAB AIR switch
ON, engine bleed air is admitted to the ram air heat exchanger
through a flow control valve. The bleed air is cooled in the heat exchanger
by ramair entering the dorsal inlet, passing through the exchanger,
and then exiting into the tailcone. The conditioned bleed air
　
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