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their appearance) inside the nose cowl distribute the bleed air along the
circumference of the nose cowl leading edge, heating the leading edge
skin and preventing ice formation. The air is vented overboard through the
engine air inlet.
3. Controls and Indications:
(See Figure 4 and Figure 5.)
A. Circuit Breakers (CBs):
Circuit Breaker Name: CB Panel: Location: Power Source:
L COWL ANTI-ICE CP J-13 ESS DC Bus
R COWL ANTI-ICE CP K-13 ESS DC Bus
L COWL A/I PRESS CP J-12 ESS DC Bus
R COWL A/I PRESS CP K-12 ESS DC Bus
B. Caution (Amber) CAS Messages:
CAS Message: Cause or Meaning:
L-R COWL A/I OVHT Engine cowl temperature is above 662°F (350°C).
L-R COWL PRESS
LOW(1)
Cowl anti-ice pressure is less than 10±1 psi or 4±1 psi (2).
NOTE(S):
(1) SN 1060 and subs; SN 1000-1059 having ASC 51A.
(2) SN 1190 and subs; SN 1000-1189 having ASC 243.
C. Advisory (Blue) CAS Messages:
CAS Message: Cause or Meaning:
L-R COWL A/I ON Cowl anti-ice is ON.
NOTE:
A description of the Engine Instruments and Crew
Alerting System (EICAS) can be found in Section 5 of
Honeywell’s SPZ-8000 (or SPZ-8400) Digital
Automatic Flight Control System Pilot’s Manual for the
Gulfstream IV.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-30-00
Page 11
October 11/02
Revision 8
4. Limitations:
A. Flight Manual Limitations:
(1) Requirements of Use:
Operation of the cowl anti-icing system is required for taxi and
takeoff when Static Air Temperature (SAT) is below +8° C and visible
moisture, precipitation, or wet runway are present. Engine operation
at 85% LP for one (1) minute is recommended just prior to takeoff
and at intervals of not more than sixty (60) minutes under these
temperature and moisture conditions.
(2) Low Cowl Anti-Ice Pressure:
Depart icing conditions if COWL PRESSURE LOW message
illuminates and cowl anti-ice pressure cannot be maintained at or
above 4 psi.
NOTE:
The COWL PRESSURE LOW message illuminates at
4 psi on SN 1190 and Subs, and SN 1000 through
1189 with ASC 243. It illuminates at 10 psi on SN 1000
through 1189 without ASC 243. Cowl anti-ice is
effective at 4 psi or greater.
(3) Use In Flight:
Use of cowl anti-icing system is required in flight as indicated in
Figure 6: Temperature Range For Cowl Anti-Icing, when visible
moisture or precipitation is present, or when signs of icing are
observed. Ice accretion may be observed on wings or windshield
edges.
B. System Notes:
(1) Ice Formation During Idle Descents:
Although adequate bleed air for cowl anti-icing is available under all
normal operating conditions, flight crews may note a limited amount
of ice formation on the nose cowl during idle descents. When power
is increased, some of this ice will be shed into the engine inlet.
Shedding this limited amount of ice will not cause any adverse
effects on engine operation.
(2) Icing and Engine Vibration:
Increases in engine vibration level above 1.25 inches per second LP
may develop in icing conditions. To assist in shedding ice, if
sustained vibration is indicated and operational circumstances
permit, retard one power lever at a time to IDLE for five (5) seconds
and then restore to required thrust. Should the vibration still persist
after doing so, momentarily adjust the thrust levels to 85% LP.
OPERATING MANUAL
2A-30-00 PRODUCTION AIRCRAFT SYSTEMS
Page 12
October 11/02
Revision 8
Cowl Anti-Ice System Layout
Figure 3
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-30-00
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October 11/02
Revision 8
Cowl Anti-Ice System Simplified Block Diagram
Figure 4
OPERATING MANUAL
2A-30-00 PRODUCTION AIRCRAFT SYSTEMS
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October 11/02
Revision 8
Anti-Ice Control Panel
Figure 5
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-30-00
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October 11/02
Revision 8
2A-30-40: Windshield Ice and Rain Protection System
1. General Description:
The windshield ice and rain protection system provides deicing and defogging for
the front windshields and side windows through the use of embedded electrical
heating elements. Rain removal (front windshields only) is provided by a pair of
electrically operated windshield wipers. The windshield ice and rain protection
system is divided into the following subsystems:
• Windshield Heat System
• Windshield Wiper System
Temperature Range For Cowl Anti-Icing
Figure 6
OPERATING MANUAL
2A-30-00 PRODUCTION AIRCRAFT SYSTEMS
　
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