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Copilot’s Overhead, B-10
• STALL BARR VALVE #1:
Copilot’s Overhead, A-13
• STALL BARR VALVE #2:
Copilot’s Overhead, B-13
(2) Pull faulty barrier CBs.
Stall barrier protection is still
available with one (1) system
operative.
STALL BARRIER OFF STALL BARRIER switch
is OFF or system not
powered.
(1) Check STALL BARRIER
switch is ON (amber OFF
legend extinguished).
(2) If STALL BARRIER switch
is ON, check associated
CB:
• STALL BARRIER #1:
Copilot’s Overhead, A-10
• STALL BARRIER #2:
Copilot’s Overhead, B-10
• STALL BARR VALVE #1:
Copilot’s Overhead, A-13
• STALL BARR VALVE #2:
Copilot’s Overhead, B-13
OPERATING MANUAL
04-03-00 MESSAGES AND ANNUNCIATIONS PROCEDURES
Page 12
October 11/02
Revision 8
CAS Message: Possible Cause(s): Corrective Action:
STBY PITOT HT FAIL Standby pitot heater
elements not energized.
(1) Check STBY PITOT switch
is ON (amber OFF legend
extinguished).
(2) Check standby pitot heater
CBs:
• STBY PITOT HT CONT:
Copilot’s Aft Panel, L-13
• STBY PITOT HT PWR:
Copilot’s Aft Panel, M-13
STEER BY WIRE FAIL Both steering channels
have failed: steering not
available. System is in
shimmy damp mode.
(1) Check CBs:
• STEER BY WIRE #1:
Copilot’s Overhead, C-12
• STEER BY WIRE #2:
Copilot’s Overhead, D-12
(2) Cycle NOSE WHEEL
STEER ON/OFF switch.
(3) If message is not
extinguished, use rudder,
brakes and/or differential
power for steering.
If message is displayed on
ground with no hydraulic power
available:
(1) Select NOSE WHEEL
STEER ON/OFF switch to
OFF until engines are
running.
(2) Return NOSE WHEEL
STEER ON/OFF switch to
ON.
With ASC 176
incorporated, a switch
position/system status
miscompare is
detected.
If message is displayed in flight,
see Section 05-19-30,
Nosewheel Steering Failure.
TAT PROBE HT FAIL TAT probe heater has
failed.
TAT inputs to DADCs may be
inaccurate. DADC outputs and
FMS readouts may be
inaccurate. Check CB:
• TOTAL TEMP PROBE HTR:
Copilot’s Aft Panel, L-10
• TOTAL TEMP VALVE:
Copilot’s Aft Panel, M-10
TRIM LIMIT Autopilot elevator trim
has reached electrical
trim limits.
(1) Cycle PITCH TRIM switch
to DISEN (disengaged)
position.
(2) Manually trim as required.
OPERATING MANUAL
MESSAGES AND ANNUNCIATIONS PROCEDURES 04-03-00
Page 13
October 11/02
Revision 8
CAS Message: Possible Cause(s): Corrective Action:
TRU FAIL Transformer rectifier
unit has no output.
(1) Verify L MAIN or R MAIN
AC BUS is powered.
(2) Verify L MAIN or R MAIN
DC BUS TRU/EXT switch
is illuminated. If not
illuminated:
(a) Depress TRU/EXT
switch.
(3) Check both TRU CBs on
PDB.
(4) If still no power:
(a) Reduce load to below
250 amps.
(b) Return TRU/EXT
switch to AUTO.
TRU HOT Transformer rectifier
unit temperature above
374° F (190° C).
(1) Reduce load on TRU.
(2) If message is still displayed
after two (2) minutes:
(a) Select another
available DC power
source.
(b) Pull TRU (RIGHT AC
section) CB on PDB.
UTILITY HYD OFF Utility hydraulic pump
has been selected off.
Select utility hydraulic pump to
ON or ARM if desired.
OPERATING MANUAL
04-03-00 MESSAGES AND ANNUNCIATIONS PROCEDURES
Page 14
October 11/02
Revision 8
CAS Message: Possible Cause(s): Corrective Action:
L-R WING HOT Wing anti-ice exhaust
duct temperature is
greater than 180° F
(82° C).
(1) Select applicable WING
ANTI ICE switch to OFF.
Wait two (2) MINUTES.
(2) If message remains
displayed:
(a) First verify
ISOLATION valve is
CLOSED.
(b) Then select
associated ENG
BLEED AIR switch to
OFF.
(3) If message remains
displayed, indication is
false and flight may be
continued with normal use
of wing anti-icing.
Re-select associated ENG
BLEED AIR switch to ON.
(4) If message is extinguished
in Step (2):
(a) Leave associated
ENG BLEED AIR
switch in OFF.
(b) Select associated
ECS PACK switch to
OFF.
(c) Verify again that
ISOLATION valve is
CLOSED.
(d) Descend to 41,000 ft.
　
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