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into impending bypass or the LOP switch is failed (flight only)
4
APU FIRE FAULT APU fire detection element system fault (one channel of the system is
unreliable, other channel is still operational 4
APU GEN FAIL APU generator has failed 4
APU IN BITE Annunciated after Run is selected from the APU switch until prestart BITE is
complete and the inlet door is positioned (ground only) 4
APU NOT AVAILABLE Annunciated when the APU cockpit selector switch is set to Start or Run and the
FADEC NVM is being downloaded or the door rigging test is active 4
APU OIL LO QTY Annunciated when APU oil level drops below 2 quarts and WOW is true 4
7-54 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
ELECTRONIC DISPLAY SYSTEM
APU SHUTDOWN Annunciated when an APU protective shutdown occurs other than overspeed or
overtemperature 4
APU SQUIB 1 (2) FAIL Fire bottle 1-2 is not available to APU 4/9
ASCB CTLR 1 (2) (3) FAIL Loss of communication with the bus controller 7
ASCB FAULT An LRU transmitting on the ASCB is able only to transmit on one of its busses
(displayed on-ground only) 7
ATS ENVELOPE FADEC has determined that the aircraft is within the starter assisted envelope 17
AUTO PRESS FAULT Automatic control of cabin pressure from one controller is inoperative 13
AUX FUEL PUMP L (R) Left and/or right auxiliary (DC) fuel pump failure 11
AV BATT CHGR FAIL Avionics battery charger has detected a fault and shutdown 6
AV FANS FAIL Both fans failed in flight (Global 5000 only) 13
AV RACK FAN FAIL Avionics rack fan failed (Global 5000 only) 13
AVIONIC FAN FAIL Avionics fan failed in the underfloor avionics bay 13
BATT BUS XFER FAULT Transfer of alternative power supply to BATT BUS may be lost 6
BATT EMER PWR ON The batteries are the only source of electrical power 6
BLEED FAULT L (R) Loss of redundancy on left and/or right bleed system (but PRV is already open) 3
BLEED MISCONFIG Improper bleed configuration for engine start 13
BRAKE FAULT Loss of redundancy in brake control system 14
BRAKE TEMP One or more brake indications are in the white brake temperature indication
band 14
CAB ALT LEVEL HI Message displayed when the warning or the caution level have been set higher
than their normal values due to landing or takeoff at high altitude 13
CB TRIP A circuit breaker has tripped 6
CHECKLIST MISMATCH Checklists are not identical in all IACs (message active on ground only) 7
COWL A/ICE FAULT L (R) Left/right cowl anti-icing degradation has occurred but operationally safe 3
CTR XFER FAULT Center Fuel Transfer Fault (either left or right fuel transfer not working or
management fault) 11
DAU 1A-1B FAIL Loss of communication with DAU, or DAU is indicating a failure 7
DAU 2A-2B FAIL Loss of communication with DAU, or DAU is indicating a failure 7
DAU 3A-3B FAIL Loss of communication with DAU, or DAU is indicating a failure 7
DAU 4A-4B FAIL Loss of communication with DAU, or DAU is indicating a failure 7
DC BUS 1 (2) XFER FAULT Transfer of alternative power supply to DC BUS 1-2 may be lost 6
DC ESS XFER FAULT Transfer of alternative power supply to DC ESS may be lost 6
DU 1 (2) (3) (4) (5) (6) FAN DUs cooling fans have failed, resulting in possible loss of function 6
ADVISORY MESSAGES (CYAN)
CAS MESSAGE DESCRIPTION CH.
For Training Purposes Only
Sept 04
7-55
P I LOT T R A I N I N G GU I D E
ELECTRONIC DISPLAY SYSTEM
ELEC SYS FAULT Loss of redundancy on EPGDS logic 6
ENG FIRE FAULT L (R) Left and/or right engine fire detection element system fault (one channel of the
corresponding system is unreliable, other channel is still operational) 9
ENG SQUIB 1 (2) FAIL L(R) Fire bottle 1-2 is not available to LH/RH engine 9
ENG SYNC FAIL Selected Sync system is unavailable due to a detected failure 17
ENG SYNC LIMIT
Selected Sync system is unable to perform the pilot selected sync function due
to an authority limit. Engine sync unavailable due to engine split greater than
engine sync authority
17
ESS TRU 1 (2) FAIL Ess TRU 1/2 has failed 6
EXT AC PWR AVAIL External AC power is available 6
EXT DC PWR AVAIL DC external power is available 6
FADEC FAULT L (R) Minor FADEC fault. Engine operation should not be affected 17
FDR ACCEL FAIL Flight Data Recorder (FDR) accelerometer has failed 7
FDR FAIL Flight Data Recorder failure 7
FIRE SYS FAULT
FIDEEX System fault: Fire + Smoke detection + Fire extinguishing are still
operational. Fire loop, smoke detector and squib pressure bottle failures can no
longer be annunciated. EMS CDU “FIRE TEST” will operate normally
9
FLAP DRIVE OVHT
System shutdown due to overheat on at least one channel. Message self-clears
　
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