曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
Simplified Block Diagram
Figure 10
OPERATING MANUAL
2A-28-00
Page 37 / 38
October 11/01
Fuel Low Level System
Simplified Block Diagram
Figure 11
OPERATING MANUAL
2A-28-00
Page 39 / 40
October 11/01
HYDRAULICS
2A-29-10: General
The hydraulic system for the Gulfstream IV (Figure 1) provides a means to store
hydraulic fluid and deliver hydraulic fluid under pressure to using systems. Two enginedriven
main hydraulic systems are installed in the aircraft. They are the Combined
system (left engine) and the Flight system (right engine). System design is such that a
single hydraulic system failure will not result in loss of the entire hydraulic system.
In addition to the main hydraulic systems, two auxiliary hydraulic systems are
incorporated to provide operational redundancy and to perform various utility functions,
in some cases without the need for operating engines or external power sources. The
two auxiliary hydraulic systems are the hydraulically-driven Utility system and the
electrically-driven Auxiliary system.
Each primary flight control actuator (aileron, elevator and rudder) and each spoiler
actuator are termed “dual-tandem actuators”, in that both Combined system and Flight
system power is used through independent load paths, yet summed for output. Thus, if a
loss of either hydraulic system input to actuator did occur, the remaining hydraulic
system continues to allow actuator function.
The system is designed for use with Type IV phosphate ester-based hydraulic fluid (Hy-
Jet IV, Hy-Jet IV-A, Skydrol LD-4 and Skydrol 500B-4).
The hydraulic system is divided into 2 subsystems:
• 2A-29-20: Main Hydraulic Systems
• 2A-29-30: Auxiliary Hydraulic Systems
A master table of component availability by hydraulic system is shown on the following
page.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-29-00
Page 1
October 11/02
Revision 8
Master Table of Component Availability
Table 1
SYSTEM/COMPONENT:
HYDRAULIC SYSTEM:
COMB FLT UTIL AUX
Elevators X X
Stall Barrier X X
Ailerons X X
Speed Brakes X X
Flight Spoilers X X
Ground Spoilers X X (1)
Rudder X X
Yaw Damper X
Left Thrust Reverser X
Right Thrust Reverser X
Utility Pump Motor X
Wing Flaps X X X
Landing Gear and Doors X X X (2)
Nosewheel Steering X X
Brakes X X X (3)
STBY ELEC PWR SYS Motor X
Parking Brake Pressure X
Main Entrance Door X
Cargo Door (4) X
NOTE(S):
(1) If servo pressure signal from COMB, UTIL or AUX is present.
(2) Ground use only, through ground service valve.
(3) Automatic (if armed) on ground with COMB and UTIL failure.
(4) Aircraft with Aircraft Service Change (ASC) 213 or 354 incorporated.
OPERATING MANUAL
2A-29-00 PRODUCTION AIRCRAFT SYSTEMS
Page 2
October 11/02
Revision 8
Hydraulic Schematic Block
Diagram
Figure 1
OPERATING MANUAL
2A-29-00
Page 3 / 4
October 11/02
2A-29-20: Main Hydraulic Systems
1. General Description:
The main hydraulic systems provide the primary means to store hydraulic fluid
and deliver hydraulic fluid under pressure to the using systems. Each of the main
hydraulic systems (Combined system and Flight system) is supplied pressurized
fluid by a dedicated engine-driven pump. The left engine-driven pump provides
pressurized fluid at 3000 ±50 psi (static) to the Combined system and its using
components. The right engine-driven pump provides pressurized fluid at 3000 ±50
psi (static) to the Flight system and its using components. The systems’ fluids do
not intermix. Each reservoir is pressurized by its own hydraulic system at a 50:1
ratio. With hydraulic system pressure at 3000 psi, the respective reservoir
pressurizes to 60 psi.
A. Combined Hydraulic System:
The Combined system (Figure 2) performs the majority of hydraulic
functions for the aircraft, thus it has the largest fluid quantity of the two
systems. Its pump is located on the left engine, and its reservoir and
manifold are located on the left side of the aft equipment (tail)
compartment.
Total system capacity is approximately 15.5 gallons (58.6 liters). This
includes the reservoir, lines and all system components. Pressurized fluid
is provided to the following systems, units and components:
• Ailerons
• Speed Brakes
• Flight Spoilers
• Ground Spoilers
• Rudder
• Elevator
• Stall Barrier
• Landing Gear and Gear Doors
• Left Thrust Reverser
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
湾流4操作手册 Gulfstream IV Operating Manual 2(40)
