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attempt re-engagement.
AT 1-2 FAIL Indicated autothrottle
has failed, autothrottle
will disconnect.
Check appropriate CBs. Select
opposite A/T computer and
reengage.
AT NOT IN HOLD Airplane speed has
exceeded 60 KCAS
with autothrottle
engaged on takeoff and
autothrottle servos are
not in HOLD mode.
Disengage autothrottle and
manually adjust power levers to
takeoff EPR.
BC 1-2-3 TEST FAIL Bus Controller power-up
self test has failed.
NOTE
This message is only
enabled on the ground.
The Bus Controller test
will fail if power is
momentarily removed
from both Fault Warning
Computers after the
Bus Controllers are
powered. If this
condition occurs, the
TEST FAIL message
can be cleared by
reapplying airplane
power in the normal
power-up sequence or
by pulling and resetting
all three of the following
CBs:
• BUS CONT #1:
Copilot’s Aft Panel,
K-2
• BUS CONT #2:
Copilot’s Aft Panel,
L-2
• BUS CONT #3:
Copilot’s Aft Panel,
M-2
Verify power was applied to the
Bus Controllers and Fault
Warning Computers in the
normal power-up sequence. Full
system capabilities are
maintained on a single Bus
Controller.
OPERATING MANUAL
04-04-00 MESSAGES AND ANNUNCIATIONS PROCEDURES
Page 2
May 30/02
Revision 7
CAS Message: Possible Cause(s): Corrective Action:
BRAKE MAINT REQ’D
(Brake-By-Wire)
For airplanes SN 1000
through 1213 with ASC
190, ASC 266 or ASC
296.
If message is displayed
after landing gear
retraction and
extinguishes
approximately five (5)
seconds later, the auto
spin-down feature has
failed.
See procedures for takeoff with
anti-skid inoperative or off
(wheel spin-down function
disabled) contained in Section
05-02-10, Anti-Skid Failure
(Brake-By-Wire).
BRAKE MAINT REQ’D
(HMAB)
For airplanes SN 1214
and subsequent.
If message is displayed
during takeoff, during
landing ground roll or
during flight with landing
gear extended, a wheel
speed sensor
miscompare lasting
more than five (5)
seconds has been
detected.
Notify maintenance to check for
wheel speed sensor faults or
possible dragging brakes.
If message is displayed
momentarily during flight with
landing gear extended, no
action is required. See Section
05-06-30, BRAKE
MAINTENANCE REQUIRED
Message (HMAB).
BUS CTLR 1-2-3 FAIL Indicated Bus Controller
has failed.
(1) Check CBs:
• BUS CONT #1: Copilot’s
Aft Panel, K-2
• BUS CONT #2: Copilot’s
Aft Panel, L-2
• BUS CONT #3: Copilot’s
Aft Panel, M-2
(2) Cycle CB of failed bus
controller.
Full system capabilities are
maintained on a single bus
controller.
CALL Incoming call from
SELCAL, cabin/galley/
lavatory interphone or
telephone.
Answer appropriate caller.
CDU 1-2 FAIL FMS Central Display
Unit (CDU) has failed.
Verify failure and, if failed, use
remaining FMS for navigation.
CHECKLIST
MISMATCH
Different checklists
installed in FWC 1 and
FWC 2.
Do not use checklist until
correct checklists are installed.
CMB HYD HOT Combined hydraulic
system fluid
temperature above 220°
F (104° C).
Proceed with flight and
investigate after landing.
L-R CONT IGN (SPZ
8400 equipped option)
Continuos ignition is on. (1) Select off if not required.
(2) Observe duty cycle
limitations in GIV AOM
Section 1, Expanded
Limitations.
L-R COWL A/I ON Indicated Cowl Anti-Ice
is ON.
Select OFF after exiting icing
conditions.
OPERATING MANUAL
MESSAGES AND ANNUNCIATIONS PROCEDURES 04-04-00
Page 3
May 30/02
Revision 7
CAS Message: Possible Cause(s): Corrective Action:
CPL DATA INVALID Lateral or vertical mode
cannot be selected or
canceled automatically
due to invalid source
and/or invalid required
sensors. Message is
also displayed anytime
selected course
changes by greater
than 3° when in LNAV/
VOR, except when over
station.
Check validity of coupled
source.
DADC 1-2 FAIL A DADC has failed. (1) Verify failure and, if failed,
select opposite DADC.
(2) Verify DADC selection for
pressurization.
DADC MISCOMPARE The priority FGC has
　
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