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When a high AOA is reached, the control column shaker motors are
activated. When a more severe AOA is reached, the control column
pusher trip detector activates its respective stall barrier valve. The
activation signal will originate from whichever system is operating -
No. 1, No. 2 or both. When a stall barrier valve is activated,
Combined (or Utility) hydraulic system pressure is ported to the
extend side of the stall barrier actuating cylinder. As the cylinder
extends, it applies an input to the elevator actuator input sector. This
input causes the elevator actuator to drive the elevator trailing edges
down; the control column drives forward accordingly, to
approximately one inch forward of neutral. When AOA has
decreased more than one degree, the stall barrier system
disengages.
The force generated by the stall barrier system is sufficient to
overcome any autopilot force, however, the system can be manually
overcome by the flight crew.
The stall barrier system can be deactivated by pressing the BARR
DISC button on either control wheel. The BARR DISC button also
serves as the autopilot disconnect button, thus is also labeled A/P
DISC accordingly. Deactivation of the stall barrier system is also
possible through selection of the STALL BARRIER switchlight to
OFF. The switchlight is located on the cockpit center pedestal just
below the left HP fuel cock. An amber OFF legend in the switchlight
will illuminate when the system is deactivated and will extinguish
when activated.
(6) Stall Warning / Stall Barrier System Test:
The stall warning / stall barrier system is normally tested by the flight
crew on the first flight of the day or every eight hours of flight time.
The test is performed only on the ground and cannot be tested in
flight. It consists of the following steps:
(a) Select the STALL BARRIER switch to on. Verify amber OFF
legend is extinguished.
(b) On both the pilot’s and copilot’s display controllers, depress
the TEST function key.
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2A-27-00 PRODUCTION AIRCRAFT SYSTEMS
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October 11/02
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(c) On both the pilot’s and copilot’s display controllers,
simultaneously depress and hold the Sea Level (S/L) line
select key.
(d) Continue holding both S/L line select keys until the
normalized AOA indicator pointer slews to full scale and
observe the following:
• Stall warning (control column shaker) occurs between
0.70 and 0.80
• Stall barrier (control column pusher) occurs between
0.95 and 1.07
• Check that the BARR DISC button will override the
pusher
(e) On both the pilot’s and copilot’s display controllers,
simultaneously depress and hold the ALT line select key.
(f) Continue holding both ALT line select keys until the
normalized AOA indicator pointer slews to full scale and
observe the following:
• Stall warning (control column shaker) occurs between
0.54 and 0.65
• Stall barrier (control column pusher) occurs between
0.79 and 0.90
• Check that the BARR DISC button will override the
pusher
NOTE:
Both pilot’s and copilot’s sides have to be tested
simultaneously in order to activate the control column
pusher.
NOTE:
Another momentary push of the TEST function key
may be required to ensure the AOA indicator is in the
normal area prior to takeoff.
G. Failure Detection System:
CAA Certified Aircraft Only: A flight control automatic failure detection
system monitors flight control inputs from the control columns and
compares them to the elevator actuator outputs. If the system detects a
failure, it automatically shuts off hydraulic pressure to the actuator and
triggers the appropriate warning on the Crew Alerting System (CAS). Once
activated by a malfunction, hydraulic pressure is inhibited until power to the
respective monitoring system is interrupted, for instance, by pulling and
resetting the appropriate circuit breaker.
The monitoring system is a dual-channel system. One channel controls the
Combined hydraulic system pressure source while the other controls the
Flight hydraulic system pressure source. Power for the system is received
from the 28 VDC Essential DC bus.
A pair of limit switches monitor applied control column input while a pair of
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-27-00
Page 13
October 11/02
Revision 8
reed switches monitor actuator output in response to the input.
If a disagreement occurs between control column input and actuator
output, the associated limit switch and reed switch close to complete a
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湾流4操作手册 Gulfstream IV Operating Manual 2(11)
