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NOTE(S):
(1) For SPZ-8400 equipped airplanes.
(2) For airplanes 1467 & subs: E BATT 1-2-3-4 DISCH
(2) For airplanes 1467 & subs: E BATT 1-2-3-4 FAIL
Annunciation Cause or Meaning
DC EXT PWR light
(blue) illuminated on
overhead panel.
DC external power applied.
EXT BATT SW light
(blue) illuminated on
overhead panel.
OUTSIDE BATTERY switch (or EXTERNAL BATTERY
switch, if installed) has been selected to ON.
GND SVCE BUS
annunciator(amber)
illuminated on overhead
panel.
Ground service bus energized. Requires airplane electrical
power (battery power minimum) for annunciator to
illuminate.
5. Limitations:
There are no limitations for the DC electrical power system at the time of this
revision.
OPERATING MANUAL
2A-24-00 PRODUCTION AIRCRAFT SYSTEMS
Page 68
May 30/02
Revision 7
Battery Power System
Simplified Block Diagram
(SN 1000 - 1464 Not
Having ASC 54)
Figure 13
OPERATING MANUAL
2A-24-00
Page 69 / 70
May 30/02
Battery Power System
Simplified Block Diagram
(SN 1465 & Subs, SN
1000 - 1464 Having ASC
54)
Figure 14
OPERATING MANUAL
2A-24-00
Page 71 / 72
May 30/02
External Battery Switches
/ Ground Service Bus
Switch
Figure 15
OPERATING MANUAL
2A-24-00
Page 73 / 74
May 30/02
DC Electrical Power System Simplified Block Diagram
Figure 16
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-24-00
Page 75
May 30/02
Revision 7
Overhead Annunciator Panel
Figure 17
OPERATING MANUAL
2A-24-00 PRODUCTION AIRCRAFT SYSTEMS
Page 76
May 30/02
Revision 7
EMERG POWER Control Panel (SN 1000 - 1466)
Figure 18
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-24-00
Page 77
May 30/02
Revision 7
EMERG POWER Control Panel (SN 1467 & Subs)
Figure 19
OPERATING MANUAL
2A-24-00 PRODUCTION AIRCRAFT SYSTEMS
Page 78
May 30/02
Revision 7
FIRE PROTECTION
2A-26-10: General
The Gulfstream IV fire protection system provides a means to detect and indicate fire or
overheat conditions, and to store and distribute fire extinguishing agent to all protected
areas of the aircraft.
The fire detection system alerts the flight crew whenever a fire or overheat condition
develops in the engine nacelles or APU enclosure. This is accomplished presenting both
aural and visual warnings when temperatures reach an overheat condition. Area
detectors are used in large zones; spot detectors are used in more focused areas. The
engine portion of the system also provides an alert when the sensing elements (called
firewires) develop a fault.
The fire extinguishing system suppresses left engine nacelle, right engine nacelle and
APU compartment fires. Three extinguishing agent bottles are installed in the tail
compartment; two for engine fire extinguishing and one for APU fire extinguishing.
Provisions for testing the extinguishing system are also provided. In addition, two
portable fire extinguishers are provided, both accessible in flight.
The Fire Protection System is divided into the following subsystems:
• 2A-26-20: Smoke Detection and Evacuation System
• 2A-26-30: Fire Detection and Warning System
• 2A-26-40: Fire Extinguishing System
2A-26-20: Smoke Detection and Evacuation System
1. General Description:
A. Smoke Detection System:
Aircraft SN 1034, SN 1156 and Subsequent
The smoke detection system provides a photo-cell smoke detector in the
baggage compartment to detect and warn of smoke. It is operable and
capable of being tested any time 28V Essential DC bus power is available.
Aircraft with ASC 268 incorporated have an additional smoke detector
installed in the forward lavatory / radio rack area.
B. Smoke Evacuation System:
Smoke evacuation is accomplished by depressurizing the baggage
compartment door seal, allowing smoke to escape overboard. Depending
on aircraft effectivity, depressurizing the seal is accomplished using either
the baggage door handle or the smoke evacuation valve.
2. Description of Subsystems, Units and Components:
A. Smoke Detection System:
Aircraft SN 1034, SN 1156 and Subsequent
(1) Smoke Detector:
Located in the baggage compartment, the smoke detector receives
power from the Essential DC bus. It functions by passing a steady
beam of light across a white surface. Smoke particles entering the
detector interrupt the light beam, resulting in the following
annunciations, depending on effectivity:
　
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