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January 31/02
Revision 6
A thermal switch is installed downstream of each engine’s anti-ice
valve. The switch closes when air temperature downstream of the
valve reaches 662 ±15° F (350 ±8° C), triggering an amber L-R
COWL A/I OVHT caution message on CAS.
(5) Wing Anti-Icing:
Each wing leading edge plenum contains three thermal switches.
The switches monitor wing leading edge temperature at the inboard,
mid-wing and outboard areas to provide overheat warnings.
Normally, wing leading edge temperature with anti-icing operating is
approximately 130° F (54° C).
Each wing’s three switches are wired in parallel and will close at 180
±5° F (82 ±3° C), triggering an amber L-R WING HOT caution
message on CAS.
(6) Radio Racks and Nose Avionics Bay:
Ten thermal switches, eight installed in the left and right avionics
bays and two in the nose avionics bay, monitor temperatures in
these areas. The switches, wired in parallel, close at 200 ±5° F (93
±3° C), triggering an amber FWD RADIO RACK HOT caution
message on CAS.
(7) Under Floor (Aircraft 1280 and Subsequent):
Eight thermal switches are mounted under the floor in the aft cabin.
The switches, wired in parallel, close between 120-135° F (49-58°
C) to trigger an amber UNDER FLOOR O’HEAT caution message
on CAS.
(8) Pressure Bulkhead Inspection Window:
An inspection window is installed in the center of the aft pressure
dome bulkhead to permit visual inspection of the tail compartment
from within the baggage compartment.
3. Controls and Indications:
A. Circuit Breakers (CBs):
Circuit Breaker Name: CB Panel: Location: Power Source:
APU FIRE WARN P A-4 ESS DC Bus
FIRE BELL P B-4 ESS DC Bus
L ENG O’HT P G-9 ESS DC Bus
R ENG O’HT P H-9 ESS DC Bus
L FIRE DET LOOP A P I-6 ESS DC Bus
L FIRE DET LOOP B P G-6 ESS DC Bus
R FIRE DET LOOP A P J-6 ESS DC Bus
R FIRE DET LOOP B P H-6 ESS DC Bus
B. Warning (Red) Messages and Annunciations:
CAS Message: SWLP Indication Cause or Meaning:
AFT EQUIP HOT AFT EQUIP HOT Aft equipment area temperature
above 200° F (93° C).
Possibility exists that high
pressure duct has blown or that
fire is in progress.
OPERATING MANUAL
2A-26-00 PRODUCTION AIRCRAFT SYSTEMS
Page 12
January 31/02
Revision 6
CAS Message: SWLP Indication Cause or Meaning:
APU FIRE APU FIRE APU fire detected.
ENG FIRE LOOP ALRT FIRE DET LOOP Engine fire loop senses fire.
L-R ENGINE HOT L ENGINE HOT Engine cooling air temperature
R ENGINE HOT above 860° F (460° C).
L-R PYLON HOT L PYLON HOT Pylon temperature is above
R PYLON HOT 325° F (163° C).
Annunciation: Cause or Meaning:
Red LOOP A or LOOP B segments of L
ENG or R ENG FIRE TEST switches
illuminated.
Red light in L / R Fire Handle. An engine fire loop senses fire.
Red light in L / R HP FUEL COCK
handle.
Red APU FIRE light on the APU control
panel. APU fire sensors detect fire.
Nosewheel well APU fire bell or speaker
tone sounds. APU fire sensors detect fire.
C. Caution (Amber) Messages and Annunciations:
CAS Message: Cause or Meaning:
L-R BLEED AIR HOT Bleed air temperature is above 550° F (288° C).
L-R COWL A/I OVHT Engine cowl temperature is above 662° F (350° C).
ENG FLT LOOP ALRT Engine fire detection loop fault detector active.
FWD RADIO RACK
HOT
Inside radome, left or right equipment bay temperature
has exceeded 200° F (93° C).
L-R WING HOT Wing anti-ice exhaust duct temperature is greater than
180° F (82° C).
UNDER FLOOR
O’HEAT
Bleed air leak detected under cabin floor.
4. Limitations:
There are no limitations established for this system as of this revision.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-26-00
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January 31/02
Revision 6
Engine / APU FIRE TEST Switches
Figure 4
OPERATING MANUAL
2A-26-00 PRODUCTION AIRCRAFT SYSTEMS
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January 31/02
Revision 6
Engine FIRE DETECTION TEST Switches
Figure 5
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-26-00
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January 31/02
Revision 6
APU Fire Annunciator / APU FIRE EXT Switch
Figure 6
OPERATING MANUAL
2A-26-00 PRODUCTION AIRCRAFT SYSTEMS
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January 31/02
Revision 6
2A-26-40: Fire Extinguishing System
1. General Description:
The fire extinguishing system provides the flight crew with fixed and portable
methods to suppress fire in each engine nacelle, the APU compartment or
　
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