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• STALL WARN ADVANCE EICAS advisory message
• ADVANCE on EMS/CDU
STALL SYSTEM PILOT-ACTIVATED TEST
The pilot-activated test is initiated by the pilot during pre-flight. It takes approximately
20 seconds to complete the test. The test is initiated through the EMS/CDU. Please
refer to Chapter 6, ELECTRICAL for the pilot-activated testing procedure.
The pilot-activated test will accomplish the following system results:
• Test can be accomplished on either pilot’s or copilot’s EMS CDU
• Select TEST, press the STALL TEST button and note the following
• Pilot’s stick shaker only is activated along with STALL annunciator on PFD
• Copilot’s stick shaker only is activated along with STALL annunciator on PFD
• Both stick shakers are activated along with STALL annunciator on both PFDs,
IGN annunciated on EICAS and STALL aural
• Stick pusher is activated and both control columns move full forward and then
return to neutral (twice)
• After the above test is complete, press and hold the MASTER DISC button on
either the pilot’s or copilot’s control wheel (hold for not less than 12 seconds) and
note the following
• That the following messages are displayed while holding the button
• AP 1-2 FAIL advisory message
• STAB TRIM caution message
• STALL PROTECT FAIL caution message
• All messages go out once the MASTER DISC button is released
GX_10_062
STALL TEST
(duration approximately
20 seconds)
Press the STALL TEST
activation button to initiate
test.
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUS
PREV
PAGE
NEXT
PAGE
CNTL TEST
BUS
EMER
CONT
TEST CONTROL 1/2
FIRE TEST
AURAL WARNING TEST 1
AURAL WARNING TEST 2
LAMP TEST 1
LAMP TEST 2
STALL TEST
OFF
OFF
OFF
OFF
OFF
OFF
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-64 For Training Purposes Only
Sept 04
SYSTEM INTEGRATION
The integrated nature of the Global extends to the operation of the Primary Flight
Control, Secondary Flight Control and Stall Protection Systems. The integration of the
Flight Control System in this manner enhances aircraft control and optimizes the
operation of other aircraft systems.
PRIMARY FLIGHT CONTROLS
The Primary Flight Controls provide the means by which the AFCS effects flightpath
control. It follows, then, that malfunctions in this portion of the Flight Control System
may impact autopilot operations. These conditions include:
• Jamming of the copilot’s aileron control circuit renders the autopilot inoperable.
The aileron autopilot servo cannot input the required aileron control surface
• Jamming of the copilot’s elevator control circuit renders the autopilot inoperable
as the associated servo is again unable to input the system
• Jamming of the pilot’s elevator control circuit renders the stick pusher inoperative
• Loss of both yaw dampers renders the autopilot inoperable as these rudder
components are used to input AFCS directional commands
SECONDARY FLIGHT CONTROLS
The Secondary Flight Control System is integrated with other aircraft systems through
transmission of flap position information. Results of this interaction include:
• The immediate and automatic deployment of the RAT upon the loss of all AC
power when the flaps are out of the zero position. This is not the case when the
flaps are in the fully retracted position, at which time a 14-second delay is
introduced to the automatic RAT deployment cycle
• Modification of Enhanced Ground Proximity and landing gear warning systems
settings and indications on the basis of flap position. As is the case with RAT
deployment, modification logic is premised on the fact that the aircraft is likely in
departure or approach operations and closer to the ground when flaps are extended
STALL PROTECTION SYSTEM
The Stall Protection portion of the Flight Control system is integrated with the EMS
CDU for pilot-activated system test purposes and the manual advancement of stall
warning thresholds. In addition, it is integrated with the Bleed Management Computer
system to effect the automatic advancement of stall warning thresholds and indications
when icing conditions are detected concurrently with a failure in the wing anti-ice
system.
For Training Purposes Only
Sept 04
10-65
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
PRIMARY/SECONDARY FLIGHT CONTROL EICAS MESSAGES
789
CONFIG AIL TRIM
　
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