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firewire, the FDCU responds by triggering the fire warnings and
providing a signal to the Data Acquisition Unit (DAU). Fire warnings
include:
• Both upper and lower segments (LOOP A and LOOP B) of
the affected engine FIRE TEST switchlight illuminate red
• The affected engine FIRE handle illuminates red. The
handle’s safety solenoid is activated, allowing the handle to
be pulled. (Manual release of the handle is still available in
the event of solenoid failure.)
• The affected engine HP fuel cock illuminates red
• Red ENG FIRE LOOP ALRT and warning message is
displayed on CAS
• Red L FIRE DET LOOP capsule illuminates on the Standby
Warning Lights Panel (SWLP), if the SWLP is in manual
mode, or if in automatic mode coupled with CAS failure
• Both red MASTER WARN lights illuminate, with
corresponding aural warning tone
• The ENGINE FIRE checklist is displayed on the lower center
portion of the copilot’s navigation display (DU 5) in MAP or
COMP or PLAN mode (airplanes SN 1144 and subsequent
and SN 1000 through 1143 with ASC 178 incorporated)
As the temperature drops, (e.g., after the fire is extinguished), semiconductor
resistance rises, capacitance drops and the FDCU
OPERATING MANUAL
2A-26-00 PRODUCTION AIRCRAFT SYSTEMS
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January 31/02
Revision 6
deactivates the fire warnings.
(5) Fault Annunciations:
If resistance and capacitance changes fall outside the
predetermined bounds for a fire alarm, a fault alarm is generated.
Additional protection against false alarms is achieved by requiring
fire signals from both LOOP A and LOOP B before all cockpit fire
alarm warnings are activated. A fire signal from either LOOP A or
LOOP B only results in the following faulty loop annunciations,
unless one of the loops has been selected off:
• Upper (FAULT) segment of the affected LOOP switchlight
illuminates amber
• An amber ENG FLT LOOP ALRT caution message is
displayed on CAS
• Both amber MASTER WARN lights illuminate, with
corresponding aural caution tone
The flight crew would then isolate the faulty loop by selection of the
illuminated switch to OFF. This restores the system to operation on
the remaining good loop.
(6) Engine Fire Detection Test:
The flight crew normally performs the following engine fire detection
test in the course of their normal procedures:
(a) Depress and hold the L ENG FIRE TEST switch. Verify the
following:
• LOOP A and LOOP B segments of the L ENG FIRE
TEST switchlight illuminate red
• Left (L) FIRE handle illuminates red
• Left engine HP fuel cock illuminates red
• Red ENG FIRE LOOP ALRT and L ENGINE HOT
warning messages are displayed on CAS
• Red L ENGINE HOT and FIRE DET LOOP capsules
illuminate on the Standby Warning Lights Panel
(SWLP), if the SWLP is in manual mode
• Both red MASTER WARN lights illuminate, with
corresponding aural warning tone
• The ENGINE FIRE checklist is displayed on the lower
center portion of the copilot’s navigation display (DU 5)
in MAP or COMP or PLAN mode (airplanes SN 1144
and subsequent and SN 1000 through 1143 with ASC
178 incorporated)
(b) Release the L ENG FIRE TEST switch.
(c) Depress and hold the R ENG FIRE TEST switch. Verify the
same annunciations are present, corresponding to the right
engine.
(d) Release the R ENG FIRE TEST switch.
(7) Engine Fire Detection Fault Test:
The flight crew normally performs the following engine fire detection
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-26-00
Page 9
January 31/02
Revision 6
fault test in the course of their normal procedures:
(a) Depress and hold the FIRE DETECTION FAULT TEST
switch. Verify the following:
• Upper (FAULT) segment of the all four (4) LOOP
switchlights illuminate amber
• An amber ENG FLT LOOP ALRT caution message is
displayed on CAS
• Both amber MASTER WARN lights illuminate, with
corresponding aural caution tone
(b) Release the FIRE DETECTION FAULT TEST switch.
B. APU Fire Detection System:
The APU is installed in a titanium and stainless steel enclosure in the tail
compartment. The enclosure serves to isolate the APU from the aircraft
structure and provide fire containment. Fire detection is provided by three
thermal switches strategically located on the APU enclosure, with the
sensing portion of the switches inside the enclosure. A fourth thermal
sensing switch is placed in the air inlet duct. Placement and trip points of
the sensors are:
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湾流4操作手册 Gulfstream IV Operating Manual 2(2)
