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Inhibits prevent certain CAS messages from being displayed if the message is triggered during the following conditions:
• Aircraft on ground (GROUND)• Emergency bus power (EMER)• Engine start (Engine Start Inhibit, ESI)• Takeoff (TOPI)• Aircraft in air (AIR)• Landing (LOPI)• Engine shutdown (Engine Shutdown Inhibit, ESDI)
Inhibits affecting each CAS message are indicated with an “X” under the corresponding inhibit column in Table 3-4. Alerts affected by an inhibit are not displayed while the inhibit is enabled. If an alert is displayed prior to the activation of an inhibit affecting it, the alert continues to be displayed normally until the condition causing the alert ceases to exist.
Takeoff and Landing Operation Phase inhibits (TOPI and LOPI) are implemented to reduce flight crew workload and distractions during takeoff and landing. The following tables list the criteria which must be met to activate or deactivate TOPI or LOPI; only one criterion must be met for activation or deactivation to occur.
Activation
Deactivation
Transitions from on-ground to in-air
Airborne > 25 sec
IAS transitions > 50 knots (on either PFD)
IAS > 40 knots (on either PFD)
IAS invalid (on both PFDs)
Pressure altitude > 400 ft above field elevation*
TOPI active > 90 sec
* Pressure altitude captured when the aircraft transitions from on-ground to in-air
Table 3-2 Takeoff Operation Phase Inhibit (TOPI) Activation/Deactivation Criteria
Activation
Deactivation
Transitions from in-air to on-ground
On-ground > 25 sec
IAS < 40 knots (on either PFD)
IAS invalid (on both PFDs)
GPS altitude transitions < 400 ft above field elevation*
GPS altitude > 600 ft above field elevation*
LOPI active > 90 sec
* Stored in terrain database
Table 3-3 Landing Operation Phase Inhibit (LOPI) Activation/Deactivation Criteria
In order to prevent nuisance messages in the event of a dual generator failure, most messages are inhibited when the emergency bus is powering the aircraft. Failure of a bus or processor also triggers an inhibit to prevent invalid data from triggering a message. Most messages are not generated based upon invalid data; however, there may be exceptions.
92 Garmin G1000 Pilot’s Guide for the Cessna Citation Mustang 190-00494-02 Rev. B
Engine Indication ndication & Crew Alerting System ystem
SYSTEM
OVERVIEW
FLIGHT
AUDIO PANEL EICAS INSTRUMENTS
& CNS
FLIGHT
MANAGEMENT
HAZARD
ADDITIONAL AFCS AVOIDANCE
INDEX APPENDICES FEATURES
Messages
Description
Inhibits
Warning
Caution
Advisory
ESI
TOPI
AIR
LOPI
ESDI
EMER
GND
AFT DOOR
Tailcone baggage door not fully secured
X
AFT JBOX CB L-R*
Start control circuit breaker (located in aft j-box) tripped
X
AFT JBOX LMT L-R*
Current limiter blown (located in aft j-box)
X
ANTISKID FAIL
Antiskid Control Unit cannot perform anti-skid functions
X
BATTERY O’TEMP
BATTERY O’TEMP
Overheated NiCad battery (optional)
BATT TEMP FAIL
Battery temperature sensor failure
X
X
CABIN ALT
CABIN ALT
CABIN ALT
Cabin altitude potentially unsafe
X
X
X
CABIN DOOR
Cabin door not fully secured
X
CHECK DOORS
A door monitor has not been properly tested or has failed
X
X
X
X
DUCT O’HEAT L-R*
Duct temperature too high or sensor disconnected
X
X
ENG A/I COLD L-R*
ENG A/I COLD L-R*
Engine anti-ice system ON and inlet temperature is cold
X
X
ENG CTRL SYS L-R*
FADEC has a fault that requires maintenance
ENGINE FAIL L-R*
An engine has failed
F/W SHUTOFF L-R*
Fuel firewall shutoff valve fully closed
X
FLAPS FAIL
A flap system failure has occurred.
X
FUEL BOOST L-R*
FUEL BOOST L-R*
Electric fuel boost pump ON. Caution condition is displayed when the boost pump is operating in abnormal conditions.
X
FUEL FLTR BP L-R*
Engine fuel filter impending bypass switch closed
X
FUEL LO INOP L-R*
Fuel low level function failure
X
X
FUEL LVL LO L-R*
Fuel level in tank is too low
X
FUEL PRES LO L-R*
Fuel pressure too low
X
X
FUEL TRANSFER
Fuel transfer valve open
X
GEN OFF L-R
GEN OFF L-R*
One or both electrical generators offline
HYD PRESS LO
Hydraulic system pressure too low
X
X
HYD PUMP ON
Hydraulic pump running too long
X
X
　
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