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power switch position (system may be selected to OFF or ARM).
3. Controls and Indications:
A. Circuit Breakers:
There are no circuit breakers for the external emergency exit lights. The
lights are protected by fuses on each battery.
B. Advisory (Blue) CAS Messages:
CAS Message Cause or Meaning
E BATT 1-2-3*-4* FAIL Indicated Emergency Battery has failed.
E BATT 1-2-3*-
4*DISCH
Indicated Emergency Battery is discharging.
NOTE(S):
Asterisk * items in above table apply to SN 1467 and subs.
NOTE:
If the emergency power system is activated and an
emergency power system fault message (E BATT
FAIL) is displayed on CAS, the battery pack may have
an overcurrent trip condition due to the charging cycle.
Attempt to restore normal operation by selecting the
switch ON (if switch is in ARMED position). If the
overcurrent fault clears, the battery will reset and the
fault message on CAS will extinguish.
4. Limitations:
There are no limitations established at the time of this revision.
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ORDINANCE LIGHTS
Panel (SN 1000 - 1466)
Figure 9
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ORDINANCE LIGHTS Panel (SN 1467 & Subs)
Figure 10
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NAVIGATION
2A-34-10: General
The navigation system provides the flight crew with indications of position in three
dimensions and vector information for management of the flight environment,
supplemented with aural and visual alerts to prevent Controlled Flight into Terrain (CFIT)
and collision with other airborne traffic.
Flight environment data, aircraft attitude and direction are integrated with the SPZ-8000
(or SPZ-8400) Digital Automatic Flight Control System (DAFCS) and the Integrated
Automatic Tuning System (Collins RTU-4200 Series Radio Tuning Unit (RTU)). The
DAFCS is described in Honeywell’s SPZ-8000 (or SPZ-8400) Digital Automatic Flight
Control System Pilot’s Manual for the Gulfstream IV. The Integrated Automatic Tuning
System (Collins RTU-4200 Series Radio Tuning Unit (RTU)) is described in Section
2A-23-40, Integrated Automatic Tuning System and Collins’ RTU-4200 Series Pilot’s
Guide. This section details the sensor systems used to determine airspeed and altitude,
the integration functions of the Digital Air Data Computers that supply sensor data to the
DAFCS and the onboard systems that provide alerts and warnings to prevent hazardous
flight conditions.
The Enhanced Ground Proximity Warning System (EGPWS) is a terrain awareness and
warning system incorporating alerting and display functions. The system uses aircraft
geographic position, altitude, climb and descent rate, and a terrain database to
determine potential conflicts between the aircraft flight path and terrain, and provide
aural alerts and visual depictions (in conjunction with the DAFCS) of hazardous terrain
clearance. (Visual cues generated by the TERRAIN DISPLAY feature of the EGPWS are
shown and described in Honeywell’s SPZ-8000 (or SPZ-8400) Digital Automatic Flight
Control System Pilot’s Manual for the Gulfstream IV.
The Traffic Collision Avoidance System / Aircraft Collision Avoidance System (TCAS /
ACAS) uses transponder signal information to detect and plot the tracks of other airborne
traffic and formulate flight guidance for maneuvers to avoid potential collisions.
The navigation system is divided into the following subsystems:
• 2A-34-20: Flight Environment Data System
• 2A-34-30: Attitude and Direction System
• 2A-34-40: Radio Altimeter System
• 2A-34-50: Enhanced Ground Proximity Warning System (EGPWS)
• 2A-34-60: Traffic / Aircraft Alert and Collision Avoidance System (TCAS / ACAS)
2A-34-20: Flight Environment Data System
1. General Description:
The flight environment data systems incorporate navigational sensors that sample
environmental conditions to determine airplane attitude, speed and direction.
The systems include the following components:
• Pitot-Static System
• Standby Airspeed Indicator
• Standby Altimeter
• Static Air Temperature / Total Air Temperature (SAT / TAT) System
• Digital Air Data Computer System
　
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