Garmin G1000 Manual

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A607
ADDITIONAL FEATURES
 Or:
1) Press the MENU Key to display the Page Menu.
2) Turn either FMS Knob to place the cursor on ‘Sort By Address’.
3) Press the ENT Key.  The sorting selection is indicated at the bottom center of the list windo\
w.
Viewing the content of a text message:
1) While viewing the AUX-TEXT MESSAGING Page, select the desired message box.
2) Press the FMS Knob to activate the cursor.
3) Turn either FMS Knob to select the desired message.
4) Select the VIEW Softkey.
 Or:
   Press the ENT Key.
 Or:
a) Press the MENU Key to display the Page Menu.
b) Turn either FMS Knob to place the cursor on ‘View Selected Message’.
c) Press the ENT Key.
   Message content is displayed as shown in Figure 8-104.
Figure 8-104  Veiwing Message Content
5) To close the text message, select the CLOSE Softkey.  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A608
ADDITIONAL FEATURES
 Or:
a) Press the MENU Key to display the Page Menu.
b) Turn either FMS Knob to place the cursor on ‘Close Message’.
c) Press the ENT Key.
Marking selected message as read:
1) While viewing the Inbox on the AUX-TEXT MESSAGING Page, press the FMS Knob to activate the cursor.
2) Turn either FMS Knob to select the desired message.
3) Select the MRK READ Softkey.
 Or:
a) Press the MENU Key to display the Page Menu.
b) Turn either FMS Knob to place the cursor on ‘Mark Selected Message As Read’.
c) Press the ENT Key.
   The message symbol now indicates the message has been opened.
Marking all messages as read:
1) While viewing the Inbox on the AUX-TEXT MESSAGING Page, press the MENU Key to display the Page Menu.
2) Turn either FMS Knob to place the cursor on ‘Mark All New Messages As Read’.
3) Press the ENT Key.  A confirmation window is displayed.
4) With cursor highlighting ‘YES’, press the ENT Key.  The message symbols now indicate all the message have 
been opened.
Delete a message:
1) While viewing the Inbox on the AUX-TEXT MESSAGING Page, press the FMS Knob to activate the cursor.
2) Turn either FMS Knob to select the desired message.
3) Select the DELETE Softkey.
 Or:
a) Press the MENU Key to display the Page Menu.
b) Turn either FMS Knob to place the cursor on ‘Delete Selected Message’.
c) Press the ENT Key.  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A609
ADDITIONAL FEATURES
8.11 ABNORMAL OPERATION
SVS TROUBLESHOOTING
SVS	is	intended	 to	be	 used	 with	traditional	 attitude,	heading,	 obstacle,	 terrain,	and	traffic	 inputs.	 	 SVS	is	
disabled	 when	valid	attitude	 or	heading	 data	is	not	 available	 for	the	 display.		 In	case	 of	invalid	 SVS	data,	 the	PFD	
display	reverts	to	the	standard	blue-over-brown	attitude	display.
SVS	becomes	disabled	without	the	following	data	resources:
•	 Attitude	data
•	 Heading	data
•	 GPS	position	data
•	 9	Arc-second	Terrain	data
•	 Obstacle	data
•	 TAWS	function	is	not	available,	in	test	mode,	or	failed
•	 The	position	of	the	aircraft	exceeds	the	range	of	the	terrain	database.
REVERSIONARY MODE
SVS	 can	be	displayed	 on	the	 Multifunction	 Display	(MFD)	in	Reversionary	 Mode.		If	it	is	 enabled	 when	switching	
to	Reversionary	 Mode,	SVS	will	take	 up	to	30	 seconds	 to	be	 displayed.		 The	standard,	 non-SVS	PFD	display	 will	
be	shown	in	the	interim.
Figure 8-105  SVS Reversionary Mode  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A610
ADDITIONAL FEATURES
UNUSUAL ATTITUDES
Unusual attitudes are displayed with red chevrons overlaid on the display indicating the direction to fly to 
correct	the	unusual	 attitude	condition.	 	 The	display	 shows	either	a	brown	 or	blue	 colored	 bar	at	the	 top	 or	
bottom	 of	the	 screen	 to	represent	 earth	or	sky.		 This	is	intended	 to	prevent	 losing	sight	of	the	 horizon	 during	
extreme	pitch	attitudes.
Figure 8-106  Unusual Attitude Display
The	blue	colored	bar	is	also	displayed	when	terrain	gradient	is	great	enough	to	completely	fill	the	display.
Blue Band
Figure 8-107  Blue Sky Bar with Full Display Terrain 
Terrain 
Completely 
Fills Display  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A611
ADDITIONAL FEATURES
GDL 69/69A DATA LINK RECEIVER TROUBLESHOOTING
Some	quick	troubleshooting	steps	listed	below	can	be	performed	to	find	the	possible	cause	of	a	failure.
•	 Ensure	the	owner/operator	 of	the	 aircraft	 in	which	 the	Data	 Link	 Receiver	 is	installed	 has	subscribed	 to	
SiriusXM
•	 Ensure	the	SiriusXM	subscription	has	been	activated
•	 Perform	a	quick	check	of	the	circuit	breakers	to	ensure	that	power	is	applied	to	the	Data	Link	Receiver
•	 Ensure	that	nothing	 is	plugged	 into	the	MUSIC	 1	or	 MUSIC	 2	jacks	 because	 that	would	 prevent	 XM	radio	
from	being	heard
For	troubleshooting	 purposes,	check	the	LRU	 Information	 Box	on	the	 AUX	 -	System	 Status	Page	for	Data	 Link	
Receiver	 (GDL	69/69A)	 status,	serial	number,	 and	software	 version	number.		 If	a	failure	 has	been	 detected	 in	the	
GDL	69/69A	the	status	is	marked	with	a	red	X.
Selecting the AUX - System Status Page:
1) Turn the large FMS Knob to select the AUX Page Group.
2) Turn the small FMS Knob to select the AUX - System Status Page.
Figure 8-108  LRU Information Window on System Status Page  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A612
ADDITIONAL FEATURES
If	a	failure	still	exists,	the	following	messages	may	provide	insight	as	to	the	possible	problem:
MessageMessage LocationDescription
CHECK ANTENNAXM Radio Page - active channel fieldData Link Receiver antenna error; service required
UPDATINGXM Radio Page - active channel fieldData Link Receiver updating encryption code
NO SIGNALXM Radio Page - active channel field
Weather Datalink Page - center of pageLoss of signal; signal strength too low for receiver
LOADINGXM Radio Page - active channel fieldAcquiring channel audio or information
OFF AIRXM Radio Page - active channel fieldChannel not in service
---XM Radio Page - active channel fieldMissing channel information
WEATHER DATA LINK FAILUREWeather Datalink Page - center of pageNo communication from Data Link Receiver 
within last 5 minutes
ACTIVATION REQUIREDWeather Datalink Page - center of pageSiriusXM subscription is not activated
Table 8-7  GDL 69/69A Data Link Receiver Error Messages  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850 613
APPENDIX A
ANNUNCIATIONS AND ALERTS
CAS MESSAGES
See the Pilot’s Operating Handbook (POH) for recommended pilot actions.
•	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
Inhibits prevent certain CAS messages from being displayed during the following conditions:
•	 Engine	off
•	 Engine	on
•	 Aircraft	on	ground	(Ground)
•	 Takeoff	Operation	Phase	Inhibit	(TOPI)
•	 Aircraft	in	air	(AIR)
•	 Landing	Operation	Phase	Inhibit	(LOPI)
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 selectors 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
Warning Messages  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A614
APPENDIX A
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 baggage 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 USGAL 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 HT 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
Caution Messages  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850 615
APPENDIX A
COMPARATOR ANNUNCIATIONS
The	Comparator monitors critical values generated by redundant sensors.  If differences in the sensors exceed 
a specified amount, this discrepancy is annunciated in the Comparator Window as a ‘MISCOMP’ (miscompare) 
as seen in Figure A-1.  If one or both of the sensed values are unavailable, it is annunciated as a ‘NO COMP’ (no 
compare).		The	following	is	a	list	of	the	possible	annunciations:
Figure A-1   Sensor  Comparator Window
Comparator
Window
Comparator Window TextCondition
ALT MISCOMPDifference in altitude sensors is > 200 ft.
IAS MISCOMP
If both airspeed sensors detect < 35 knots, this is inhibited.
If either airspeed sensor detects > 35 knots, and the difference in sensors is > 10 knots.
If either airspeed sensor detects > 80 knots, and the difference in sensors is > 7 knots.
HDG MISCOMPDifference in heading sensors is > 6 degrees.
PIT MISCOMPDifference in pitch sensors is > 5 degrees.
ROL MISCOMPDifference in roll sensors is > 6 degrees.
ALT NO COMPNo data from one or both altitude sensors.
IAS NO COMPNo data from one or both airspeed sensors.
HDG NO COMPNo data from one or both heading sensors.
PIT NO COMPNo data from one or both pitch sensors.
ROL NO COMPNo data from one or both roll sensors..  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A616
APPENDIX A
REVERSIONARY SENSOR ANNUNCIATIONS
Reversionary	sensor	selection	 is	annunciated	 in	the	 Reversionary	Sensor Window, as shown in Figure A-2.  
These	 annunciations	 reflect	reversionary	 sensors	selected	 on	one	 or	both	 PFDs.	 	 Selecting	 the	SENSOR Softkey 
gives access to ADC1, ADC2, AHRS1, and AHRS2	Softkeys.		 These	softkeys	 allow	manual	 switching	 of	sensors.		 In	
the	 case	 of	certain	 types	of	sensor	 failures,	 the	G1000	 may	make	 some	sensor	 selections	 automatically.		 The	GPS	
sensor cannot be switched manually.
Figure A-2  Reversionary Sensor Windows
Reversionary
Sensor
Window
Reversionary Sensor  
Window Text
Condition
BOTH  ON ADC1Both PFDs are displaying data from the number one Air Data Computer.
BOTH  ON ADC2Both PFDs are displaying data from the number two Air Data Computer.
BOTH  ON AHRS1Both PFDs are displaying data from the number one Attitude & Heading Reference System.
BOTH  ON AHRS2Both PFDs are displaying data from the number two Attitude & Heading Reference System.
BOTH ON GPS1Both PFDs are displaying data from the number one GPS receiver.
BOTH ON GPS2Both PFDs are displaying data from the number two GPS receiver.
USING ADC1PFD2 is displaying data from the #1 Air Data Computer.
USING ADC2PFD1 is displaying data from the #2 Air Data Computer.
USING AHRS1PFD2 is displaying data from the #1 AHRS.
USING AHRS2PFD1 is displaying data from the #2 AHRS.
USING GPS1PFD2 is displaying data from the #1 GPS.
USING GPS2PFD1 is displaying data from the #2 GPS.
SYSTEM ANNUNCIATIONS
When a new message is issued, the MSG	 Softkey	 flashes	to	alert	 the	flight	 crew	of	a	new	 message.		 It	continues	
to	 flash	 until	 acknowledged	 by	selecting	 the	softkey.		 Active	messages	 are	displayed	 in	white	 text.		Messages	 that	
have	become	 inactive	change	to	gray	 text.		 The	MSG	Softkey	 flashes	if	the	 state	 of	a	displayed	 message	changes	
or	a	new	 message	 is	displayed.		 The	inactive	 messages	 can	be	removed	 from	the	Message	 Window	 by	selecting	
the	flashing	MSG Softkey.
Message	 Advisories	 are	displayed	 in	the	 Messages	 Window	and	convey	 messages	 to	the	 flight	 crew	regarding	
problems	 with	the	G1000	 or	certain	 aircraft	 systems.	 	Typically,	 a	large	 red	‘X’	appears	 in	a	window	 when	a	
related	LRU	fails	or	detects	invalid	data.
The	following	 section	describes	 various	system	annunciations.		 Refer	to	the	 POH	 for	additional	 information	
regarding pilot responses to these annunciations.