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UTILITY HYD PUMP OFF CPO C-3 ESS 28 VDC Bus
B. Caution (Amber) Messages and Annunciations:
CAS Message: Cause or Meaning:
UTILITY HYD OFF Utility hydraulic pump has been selected off.
C. Other Indications:
A description of the Engine Instruments display, ENGINE START system
page and HYDRAULICS system page can be found in Section 5: Engine
Instruments and Crew Alerting System (EICAS), of Honeywell’s SPZ-8000
(or SPZ-8400) Digital Automatic Flight Control System Pilot’s Manual for
the Gulfstream IV.
4. Limitations:
A. Flight Manual Limitations:
There are no flight manual limitations for the Utility hydraulic system at the
time of this revision.
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Auxiliary Hydraulic System
Simplified Block Diagram
Figure 12
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Main Entrance Door Interior Control Switches
Figure 13
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Main Entrance Door Exterior Control Switch
Figure 14
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Ground Service Valve
Figure 15
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Utility Hydraulic System
Simplified Block Diagram
Figure 16
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Utility Hydraulic Pump
Control Circuit
Figure 17
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UTILITY PUMP/AUX
PUMP Control Switches
Figure 18
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ICE AND RAIN PROTECTION
2A-30-10: General Description
The Gulfstream IV uses both pneumatically and electrically powered ice and rain
protection systems to provide the flight crew with a means of removing and preventing
ice accumulation on the following structures and components:
• Wing Leading Edges
• Engine Cowl Inlet Leading Edges
• Cockpit Windows
• Pitot Probes
• Angle of Attack Probes
• Total Air Temperature Probe
The remainder of the airplane (including the empennage) is designed in a manner that
requires no anti-icing equipment.
The ice and rain protection system is divided into the following subsystems:
• 2A-30-20: Wing Anti-Ice System
• 2A-30-30: Cowl Anti-Ice System
• 2A-30-40: Windshield Ice and Rain Protection System
• 2A-30-50: Probe Anti-Ice System
Bleed air for the wing anti-ice system is supplied by the engine bleed air manifold. The
engine bleed air manifold is supplied mid-stage air from each engine’s 7th stage
compressor section through the 7th stage check valve. Depending on conditions, highstage
air may also be supplied by each engine’s 12th stage compressor through the 12th
stage air control valve (often referred to as the HP valve).
Bleed air for the cowl anti-ice system is supplied directly from the engines’ 7th and/or
12th stage compressor offtakes. Each engine also has a mechanical ice shedder on the
Low Pressure (LP) compressor (fan) spinner.
Electrically powered heating elements warm the cockpit windows to prevent fogging and
ice formation. Precipitation removal from the forward cockpit windows is provided by a
pair of electrically operated windshield wipers.
Electrically powered heating elements also warm the pitot probes, Angle of Attack (AOA)
probes and Total Air Temperature (TAT) probe.
An optional ice detector is available to provide the flight crew with visual warnings of
accumulating ice. Installed on the right forward cheek panel and powered by the AC
electrical system, the detector probe vibrates at approximately 40,000 Hertz (Hz) with no
ice accumulated. At this frequency, only ice can adhere to the probe, thus false warnings
are eliminated. If ice should begin to accumulate on the probe, the resonate frequency
will begin to drop, eventually reaching 39,867 Hz. At this threshold, an amber ICE
DETECTED caution message is prompted for display on the Crew Alerting System
(CAS) and detector probe heat is energized. Detector probe heat then melts away any
　
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