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is capable of maintaining actuator load capacity. In the event of total loss of hydraulic
pressure in both hydraulic systems, the primary flight controls revert to manual operation.
Mechanical pitch, roll and yaw trim systems allow the flight crew to trim the aircraft. The
pitch trim system can also be controlled electrically by pitch trim switches on the control
wheels.
A gust lock secures the elevators, ailerons and rudder to prevent wind gust damage to
the surfaces.
Secondary flight controls, shown in Figure 1, include flaps, ground spoilers and
speedbrakes. These flight controls are hydraulically powered and electrically or
mechanically controlled. The mechanically operated horizontal stabilizer moves in
conjunction with the flaps to maintain longitudinal trim.
An Angle-of-Attack (AOA) system provides outputs to the control column shakers, control
column pusher, approach indexers, normalized AOA display and stall barrier system. The
control column shakers provides early warning of a stall scenario by vibrating the control
column before the stall while the control column pusher automatically initiates lowering
the nose if the stall is imminent.
The Gulfstream IV uses an aircraft configuration warning system to monitor landing gear,
flap, speed brake and power lever position. If an unsafe configuration is detected, the
system provides a visual and / or aural warning.
On CAA certified aircraft, a flight control automatic failure detection system compares
control inputs to actuator outputs. If a malfunction is detected, the system shuts off power
to the affected actuator.
The flight controls system is divided into the following subsystems:
• 2A-27-20: Pitch Flight Control System
• 2A-27-30: Yaw Flight Control System
• 2A-27-40: Roll Flight Control System
• 2A-27-50: Horizontal Stabilizer System
• 2A-27-60: Flaps System
• 2A-27-70: Spoiler System
• 2A-27-80: Gust Lock System
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-27-00
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October 11/02
Revision 8
OPERATING MANUAL
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2A-27-00 PRODUCTION AIRCRAFT SYSTEMS
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October 11/02
GIV Flight Controls /
Aerodynamic Axes
Figure 1
OPERATING MANUAL
2A-27-00
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October 11/02
GIV Flight Controls Fluid
Power Diagram
Figure 2
OPERATING MANUAL
2A-27-00
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2A-27-20: Pitch Flight Control System
1. General Description:
Aircraft movement about the lateral axis (pitch) is controlled by the position of the
elevators. The elevators are manually controlled, mechanically actuated and
hydraulically boosted airfoils mounted on the trailing edge of the horizontal
stabilizer. Total elevator travel ranges from 24° trailing edge up to 13° trailing edge
down.
The elevators are positioned by a tandem type hydraulic actuator. The actuator
receives hydraulic operating pressure simultaneously from both the Combined
and Flight hydraulic systems during normal operations. Loss of a single hydraulic
system has no effect on operation of the elevators, as the remaining system is
capable of maintaining actuator load capacity. In the event of total loss of
hydraulic pressure in both systems, the elevators revert to manual operation.
Manual reversion is also possible through use of a flight power shutoff valve and
its pedestal-mounted control handle.
A pitch trim system is used to position a trim tab attached to the trailing edge of
each elevator. The tabs are positioned either manually by a pedestal-mounted
control wheel or electrically by pitch trim switches on the control wheels.
An Angle-of-Attack (AOA) system provides outputs to the control column shakers,
control column pusher, approach indexers, normalized AOA display and stall
barrier system. The control column shakers provides early warning of a stall
scenario by vibrating the control column before the stall while the control column
pusher automatically initiates lowering the nose if the stall is imminent.
On CAA certified aircraft, a flight control automatic failure detection system
compares control column inputs to elevator actuator outputs. If a malfunction is
detected, the system shuts off either or both hydraulic power sources to the
affected actuator.
The pitch flight control system consists of the following subsystems, units and
components:
• Control column system
• Mechanical actuation system
• Hydraulic boost system
• Manual reversion system
• Pitch trim system
• Angle-of-attack / stall barrier system
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湾流4操作手册 Gulfstream IV Operating Manual 2(7)
