Garmin G1000 Manual

							190-00709-04  Rev.  AGarmin G1000 Pilot’s Guide for the Socata TBM 85097
ENGINE & AIRFRAME SYSTEMS
ELECTRICAL SYSTEM
The Electrical Synoptics Page uses a diagram of the aircraft’s electrical system to display the system status.  The 
generators, ground power supply (GPU), batteries, and buses are shown in green to denote normal operation.    
Color of the units change depending on the condition.
Figure 3-16  Electrical Synoptics Page
1Standby Generator
2Main Generator
3Ground Power Unit Door
4Battery
5Amperage
6Battery Bus
7Essential Bus
8Battery Bus Voltage
9Essential Bus Voltage
10DC Buses 1 through 4
11Main Bus
32
9
7
41
8
5
11
6
10  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev.  A98
ENGINE & AIRFRAME SYSTEMS
Active generator currents are displayed below the generator icons.  A disconnected generator is indi\
cated in 
gray; the current is removed from the display and the switch symbol is closed.
ConnectedDisconnectedConnectedDisconnected
Figure 3-17  Generator Status
GPU status information is removed from the electrical diagram when the GPU door is closed.  If the GPU door \
is open and selected, the GPU status is shown in green; when the door is open, but not selected, the status is 
shown in gray with the switch closed.  A CAS message, ‘GPU DOOR’ i\
s generated if the GPU door is open.
Selected Not Selected
GPU Door OpenGPU Door Closed
Figure 3-18  GPU Door Status
Battery connection status to the main bus is indicated in green; direction of current flow is indicated with 
an arrow next to the current readout.  If the battery is disconnected from the main bus, the switch is closed.  
Battery overheating is indicated in red with a ‘BAT OVHT’ annunciation; a CAS message is also generated.
Figure 3-19  Battery Status
ConnectedDisconnectedBattery Overheat  
						

							190-00709-04  Rev.  AGarmin G1000 Pilot’s Guide for the Socata TBM 85099
ENGINE & AIRFRAME SYSTEMS
Battery and essential bus voltages are displayed using gauges.  DC buses are shown in green when energized.  
When not energized, the connection line to the main bus is removed and the bus label is displayed in red.
Figure 3-20  Battery and Essential Bus Low Voltage
Figure 3-21  DC Bus Status
Bus Not Energized
The Emergency Buses switch has two positions, UP (open) and DN (ground).  If the switch is in the UP 
position, the essential bus is connected to the battery bus.  If the switch is in the DN position, the essential bus 
is connected to the main bus.
Figure 3-22  Essential Bus Connections
Essential Bus Connected 
to the Battery Bus
Essential Bus Connected  to the Main Bus
A red “X” over a component indicates invalid data or a failed unit.  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev.  A100
ENGINE & AIRFRAME SYSTEMS
FUEL SYSTEM
The Fuel Synoptics Page displays the status of the fuel tanks and feed s\
ystem.  Fuel quantity is depicted 
graphically; the color changes to yellow if the fuel quantity drops below the threshold level.
Figure 3-23  Fuel Synoptics Page
1Left Fuel Tank
2Left Fuel Line
3Fuel Pressure
4Engine Driven Boost Pump
5Auxiliary Boost Pump
6Fuel Selector
7Right Fuel Tank
8Right Fuel Line
9Fuel Flow Data
5
4
8
71
2
3
6
9
Fuel Pressure is displayed using a gauge.  If fuel pressure is low the readout is displayed in red.
Figure 3-24  Fuel Pressure Low  
						

							190-00709-04  Rev.  AGarmin G1000 Pilot’s Guide for the Socata TBM 850101
ENGINE & AIRFRAME SYSTEMS
Status of the fuel selector is indicated between the fuel tank symbols.  The mode, automatic (AUTO) or 
manual (MAN) is shown beneath the fuel selector symbol.
Left  Fuel Tank 
Selected
Switching Fuel 
Tank Selection
Right  Fuel Tank 
Selected
Manual or 
Unknown Fuel 
Tank Selection
Fuel Selector
Off
Table 3-1  Fuel Selector Status
If the auxiliary fuel boost pump is on, the symbol is displayed in green.  The mode, automatic (AUTO) or 
manual (MAN) is displayed next to the pump symbol.  If the boost pump \
is off, the symbol is shown in light 
blue (automatic mode) or red (manual mode).
Fuel Boost Pump 
On
Fuel Boost Pump 
Off (Auto)
Fuel Boost Pump 
Off (Manual)
Table 3-2  Auxiliary Boost Pump Status
Fuel used and remaining are based on the fuel flow.  The aircraft’s gross weight (GW) is entered on the  
AUX - Weight Planning Page (see the Flight Management Section).
Figure 3-25  Fuel Flow Data
A red “X” over a component indicated invalid data or a failed unit.  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev.  A102
ENGINE & AIRFRAME SYSTEMS
GENERAL SYSTEMS
The General Synoptics Page aircraft diagram displays open doors in red (CAS messages also generated).  
Statuses of stall sensor, propeller, pitot probes, and windshield heat are also indicated on the diagram:
•	 White	indicates	that	heat	is	off	(propeller	and	windshield)
•	 Light	blue	indicates	heat	has	been	selected	(windshield)
•	 Green	indicates	heat	is	on
•	 Yellow	indicates	heat	has	failed	(stall	sensor,	propeller	and	pitot	tube).
Invalid sensor information is indicated with a red ‘X’.
Figure 3-26  General Synoptics Page
1Rear Cargo Door Open
2Cabin Door Open
3Pilot Door Open
4Pitot Probe 1
5Forward Cargo Door Open
6Propeller Heaters
7Right Windshield Heat On
8Pitot Probe 2
9Stall Warning Sensor
5
48
7
1
2
3
6
9
Figure 3-27  Windshield Heat Status
WindshieldHeat OnWindshieldHeat OffLeft Windshield Heat On
Right Windshield Heat Selected  
						

							190-00709-04  Rev.  AGarmin G1000 Pilot’s Guide for the Socata TBM 850103
ENGINE & AIRFRAME SYSTEMS
3.3 CREW ALERTING SYSTEM (CAS)
 NOTE: Refer to the Pilot’s Operating Handbook (POH) for emergency procedures.
 NOTE: Aural alerts associated with abnormal conditions and advisories are mana\
ged through the audio 
panels.  Refer to the Audio Panel and CNS Section for more information.
The Crew Alerting System (CAS) Display is located in the lower left corner of the EICAS Display (on the MFD) 
under normal display conditions.  Up to 14 messages can be displayed; wh\
en more than 14 messages accumulate, 
the scrolling CAS softkeys become available.
When CAS messages are present while in Reversionary Mode, the CAS Window appears on the display along 
with the flight instruments and EIS.  The window size increases to fit up to 14 CAS messages; if more than 14 
messages are generated, the messages can be scrolled through using the CAS softkeys (two left-most softkeys).
Figure 3-28  CAS Messages
Reversionary Mode
CAS 
Window
Normal Mode
CAS 
Display  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev.  A104
ENGINE & AIRFRAME SYSTEMS
CAS DISPLAY INHIBITS
Inhibits prevent certain CAS messages from being displayed during one or more of the following conditions:
•	 Engine
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 f\
or activation or deactivation to occur.
ActivationDeactivation
Transitions from on-ground to in-airAirborne > 25 sec
IAS transitions > 50 knots (on either PFD)IAS < 40 knots (on either PFD)
IAS invalid (on both PFDs)
Radar altitude (if available) > 400 ft AGL
Pressure altitude > 400 ft above field elevation*
Active > 90 sec
* Pressure altitude captured when the aircraft transitions from on-groun\
d to in-air
Table 3-3  Takeoff Operation Phase Inhibit (TOPI) Activation/Deactivation Criteria
ActivationDeactivation
Transitions from in-air to on-groundOn-ground > 25 sec
IAS < 40 knots (on either PFD)
IAS invalid (on both PFDs)
Radar altitude (if available) transitions < 400 ft AGL
GPS altitude transitions < 400 ft above field elevation*
Radar altitude (if available) > 600 ft AGL
GPS altitude > 600 ft above field elevation*
Active > 90 sec
* Stored in terrain database
Table 3-4  Landing Operation Phase Inhibit (LOPI) Activation/Deactivation Criteria
Inhibits affecting each warning and caution message are indicated with an “X” under the corresponding inhibit 
column in tables 3-5 and 3-6.  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.
If a GEA or GIA fails, all CAS messages depending on sensors associated \
with that LRU are automatically 
inhibited.  Inhibits cannot be activated by invalid sensor data.  
						

							190-00709-04  Rev.  AGarmin G1000 Pilot’s Guide for the Socata TBM 850105
ENGINE & AIRFRAME SYSTEMS
CAS MESSAGES AND PRIORITIZATION
 NOTE: Refer to the Pilot’s Operating Handbook (POH) for corrective pilot actions.
 NOTE: Red warning messages cannot be scrolled through and remain at the top of the \
CAS display.  The 
scroll bar changes to yellow if more than ten caution messages exist to \
be scrolled through.
CAS messages are grouped by criticality (warning, caution) and sorted by order of appearance (most recent 
messages on top).  The color of the message is based on its urgency and on required action:
•	Warning (red) – Immediate crew awareness and action required; Master Warning triggered
•	Caution (yellow) – Immediate crew awareness and possible future corrective action required; Master Caution 
triggered
When a new red CAS warning message appears, it flashes (inversely red on white) in conjunction with the 
Master Warning Indicator.  Pressing the Master Warning Indicator acknowledges all flashing red messages, 
extinguishing the master warning lights, and stops warning message flashing.  Once acknowledged, CAS 
warning messages are shown in red text and are displayed until the issue is corrected.
Inhibits
MessagesComments
ENGINE OFFENGINE ONGROUNDTOPIAIRLOPI
BAT OVERHEATBattery temperature over 70°C
BLEED TEMPBleed temperature highXX
CABIN ALTITUDECabin altitude over 10,000 ftX
CABIN DIFF PRESSCabin pressure differential over 6.2 psiX
DOORPilot or cabin door open
FIREEngine compartment fire (temperature over 200°C; if installed)
FLAPS ASYMDissymmetry between left- and right-hand flaps
FUEL OFFFuel tank selector set to “Off”
FUEL PRESSFuel pressure below 10 psi
ITTEngine start: ITT over 1000°C, 870°C (5 s), or 840°C (20 s) 
Engine running: ITT over 840°C
OIL PRESSOil pressure below 60 psi
OXYGENOxygen cylinder closed
PARK BRAKEParking brake applied
TORQUETorque greater than or equal to 121.4% maximum torque
Table 3-5  Warning CAS Messages  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev.  A106
ENGINE & AIRFRAME SYSTEMS
When a new yellow caution message appears on the CAS display, it flashes (inversely black on yellow)  
in conjunction with the Master Caution Indicator.  Pressing the Master Caution Indicator acknowledges all 
flashing yellow messages, extinguishes the master caution lights, and \
stops caution message flashing.  Messages 
are displayed until the issue is corrected.
Inhibits
MessagesComments
ENGINE OFFENGINE ONGROUNDTOPIAIRLOPI
AUTO SELFuel timer off or out of serviceX
AUX BOOST PMP ONElectric fuel pump running (manual or automatic mode)
BAT AMPBattery current over 50 A while on groundXXX
BAT OFFBattery offX
BLEED OFFFlow control and shut-off valve/shut-off valve closedXXX
CHIPOil chip detector on (if installed)XX
FRONT CARGO DOORForward cargo door openX
FUEL IMBALANCEFuel tanks imbalanced by more than 15 USGAL for > 30 
seconds
FUEL LOW L-R*Fuel quantity less than or equal to 9.1 USG in specified tank
GPU DOORGPU receptacle door not closedXX
IGNITIONIgnition exciter running
INERT SEP FAILInertial separator failureXX
INERT SEP ONInertial separator extended
LOW LVL FAIL L-R*Low fuel level sensor failure for specified tank
LOW VOLTAGEBattery voltage below 26 VXX
MAIN GENStarter generator unconnectedXX
NG HIGenerator speed is more than 103%
OIL PRESSOil pressure between 60 and 100 psiX
OIL TEMPOil temperature below 0°C or above 104°CX
PITOT HEAT ON L-R*Specified pitot heat (left or right) on while engine offX
PITOT NO HT L-R*Specified pitot heat (left or right) offX
PROP DEICE FAILProp deice selected and not onXX
PROP DEICE ONProp deice on while engine offX
REAR CARGO DOORRear cargo door openX
STALL HEAT ONStall warning heat on while engine offX
STALL NO HEATStall warning heat offX
STARTERStarter generator running
VACUUM LOWVacuum pressure less than 3.75 in HgXX
* Only affected side (L, R, or L-R) displayed in CAS message; applicab\
le messages listed here display L-R for example
Table 3-6  Caution CAS Messages