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AUX HYD PRESS CPO D-4 ESS 28 VDC Bus
AUX HYD PUMP CPO D-5 ESS 28 VDC Bus
D. Caution (Amber) Messages and Annunciations:
CAS Message: Cause or Meaning:
AUXILIARY HYD HOT Auxiliary hydraulic pump case temperature above 300°F
(149°C).
E. 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 Auxiliary hydraulic system at
the time of this revision.
B. System Notes:
Because of the high amperage required for Aux pump operation, consider
using external electrical power during periods requiring prolonged use of
the pump.
2A-29-32: Utility Hydraulic System
1. General:
The Utility hydraulic system (Figure 16) provides operational redundancy to the
Combined hydraulic system. In the event of Combined system failure or
Combined system pressure falling to less than 800 psi (such as a windmilling
engine), a hydraulic motor powered by Flight hydraulic system pressure operates
a hydraulic pump installed in the Combined hydraulic system. The pump, in turn,
pressurizes Combined system fluid to 3000 psi for use by the following systems:
• Wing Flaps
• Landing Gear
• Brakes
• Stall Barrier
• Nosewheel Steering
OPERATING MANUAL
2A-29-00 PRODUCTION AIRCRAFT SYSTEMS
Page 28
October 11/02
Revision 8
The Utility system also supplies a servo pressure signal to the ground spoiler
system, thus enabling operation of the ground spoilers using Flight system
pressure, provided all other ground spoilers operational conditions are satisfied.
The Utility system will operate automatically if all of the following conditions are
satisfied:
• Combined system hydraulic reservoir fluid quantity is greater than one
gallon
• Flight hydraulic system pressure is greater than 2000 psi
• Flight hydraulic system fluid temperature is below 220 ±5°F (104 ±3°C)
• UTILITY PUMP OFF/ARM switch is selected to ARM
• UTILITY PUMP ON/OFF switch is selected to OFF
2. Description of Subsystems, Units and Components:
The Utility hydraulic system consists of the following units and components:
A. System Shutoff Valve:
An electrically operated solenoid shutoff valve controls Flight hydraulic
system fluid flow to the Utility hydraulic motor/pump. Normally, with the
Combined and Flight hydraulic systems operating at 3000 psi, the solenoid
energizes to the closed position to prevent motor/pump operation.
The UTILITY PUMP OFF/ARM and ON/OFF switches (cockpit overhead
panel) control the shutoff valve. With the OFF/ARM switch in the ARM
position (NOT ARM legend not illuminated) and the ON/OFF switch in the
OFF position (ON legend not illuminated), the solenoid valve energizes and
de-energizes as conditions are satisfied. Depressing the ON/OFF switch
(ON legend illuminated) de-energizes the shutoff valve. The valve then
opens, allowing Flight hydraulic system pressure to the motor/pump
regardless of the OFF/ARM switch position.
B. Priority Valve:
A priority valve is installed downstream of the shutoff valve to control fluid
flow to the motor/pump. Depending on Flight hydraulic system pressure,
the priority valve opens and closes to prevent loss of Flight hydraulic
system pressure to critical systems such as the flight controls.
When Flight hydraulic system pressure at the valve inlet is above 2000 psi,
the priority valve opens and Flight hydraulic system pressure flows to the
motor/pump. If demands on the system increase such that pressure at the
valve inlet drops below 1730 psi, the valve closes, inhibiting flow to the
motor/pump, preventing pressure starvation to critical systems. When
Flight hydraulic system pressure rises to 2000 psi, the priority valve
reopens.
C. Flow Regulating Valve:
A flow regulating valve installed between the priority valve and the motor/
pump limits the Flight hydraulic system flow rate to the motor/pump to 13
Gallons Per Minute (GPM). This prevents the motor/pump from using the
entire 22.5 GPM provided by the Flight hydraulic system. The lower volume
allowance also assists the motor/pump in reaching its maximum operating
speed.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-29-00
Page 29
October 11/02
Revision 8
D. Utility Hydraulic Motor/Pump:
　
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