Pilot’s Manual Learjet 60
6-2 PM-123
Change 6
BLEED AIR WARNING LIGHT
Engine pylon, bleed-air duct, and tailcone overheat indication is pro-
vided by the red BLEED AIR L and BLEED AIR R warning lights. Each
light is operated by thermoswitches installed in the pylon structure and
in the bleed-air ducting. Activation of either thermoswitch will illumi-
nate the associated light. The thermoswitch in the pylon structure will
cause the associated light to illuminate if the pylon structure tempera-
ture reaches approximately 250°F. The thermoswitch in the pylon
bleed-air ducting will cause the associated light to illuminate if the duct
temperature reaches approximately 600°F. In addition to the
thermoswitches, a tailcone sensing element is installed to detect elevat-
ed tailcone temperatures caused by a leak in the bleed-air ducting. If
both the BLEED AIR L and BLEED AIR R warning lights illuminate
simultaneously, the tailcone overheat sensor has tripped the lights. The
lights operate on 28 VDC supplied through the 7.5-amp WARN LTS cir-
cuit breakers on the pilot’s and copilot’s circuit breaker panels. The tail-
cone overheat detection system operates on 28 VDC supplied through
the 2-amp BLEED AIR OV HT circuit breaker on the pilot’s circuit
breaker panel. Warning lights and tailcone overheat detection is opera-
tive during EMER BUS mode.
ANTI-ICE SYSTEMS
Aircraft anti-ice protection is provided through the use of electrically
heated anti-ice systems, engine bleed-air heated anti-ice systems, and
an alcohol anti-ice system. Electrically heated systems include the
pitot-static probes, total air temperature probe, engine inlet air
temperature/pressure sensors, stall warning vanes, and horizontal sta-
bilizer leading edge. Electrically-heated windshields provide defog-
ging for the windshield interior. Engine bleed air is utilized to provide
anti-icing for the wing leading edge, windshield, nacelle inlets, low-
pressure compressor inner stator, and engine fan spinners. The alcohol
system is installed to provide backup anti-ice protection for the pilot’s
windshield in event of normal anti-icing system malfunction.
ROSEMOUNT ICE DETECTOR SYSTEM (OPTIONAL)
The optional Rosemount Ice Detector system is installed to detect an
icing condition and notifies the pilots by illumination of the amber or
white ICE DET lights, in the glareshield annunciator panel, and both
Master CAUT lights. A self-test of the Rosemount Ice Detector system
is conducted every time aircraft power is turned on, and the ICE
DETECTOR circuit breaker is engaged. The ice detector system self-test
will show a failed self-test if the amber ICE DET light and both Master
CAUT lights are illuminated. The Rosemount Ice Detection System
Change 6
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