Garmin G1000 Manual

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 85077
FLIGHT INSTRUMENTS
WIND DATA
Wind	direction	 and	speed	 in	knots	 can	be	displayed	 relative	to	the	 aircraft	 in	a	window	 to	the	 upper	 left	of	
the	HSI.		 When	 the	window	 is	selected	 for	display,	 but	wind	 information	 is	invalid	 or	unavailable,	 the	window	
shows	NO	WIND	DATA.		Wind	data	can	be	displayed	in	three	different	ways.
Figure 2-35  Wind Data
No Data
Option 2
Option 1
Option 3
Displaying wind data:
1) Press the PFD Softkey.
2) Press the WIND Softkey to display wind data to the left of the HSI.
3) Press one of the OPTN softkeys to change how wind data is displayed:
	 •	OPTN 1: Wind direction arrows with numeric headwind/tailwind and crosswind compo\
nents
	 •	OPTN 2: Wind direction arrow with numeric speed
	 •	OPTN 3: Wind direction arrow with numeric direction and speed
4) To remove the window, select the OFF Softkey.  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A78
FLIGHT INSTRUMENTS
VERTICAL NAVIGATION (VNV) INDICATIONS
When	a	VNV	 flight	 plan	has	been	 activated,	 VNV	indications	 (VNV	Target	 Altitude,	 RVSI,	VDI)	appear	 on	the	
PFD	 in	conjunction	 with	the	“TOD	 within	 1	minute	 message”	 and	“Vertical	 track”	voice	alert.	 	 See	the	Flight	
Management	 and	AFCS	 sections	 for	details	 on	VNV	 features.	 	 VNV	indications	 are	removed	 from	the	PFD	
according	to	the	criteria	listed	in	Table	2-2.
Required 
Vertical 
Speed 
Indicator
Vertical 
Deviation 
Indicator
Enroute 
Phase of 
Flight
VNV Target 
Altitude
GPS is 
Selected 
Navigation  Source
Top of Descent Message
Figure 2-36  Vertical Navigation Indications (PFD)
Criteria VNV Indication Removed
Required Vertical  Speed (RVSI) Vertical 
Deviation (VDI) VNV Target 
Altitude
Aircraft > 1 min before the next TOD due to flight plan change XXX
VNV cancelled (CNCL VNV Softkey selected on MFD) XXX
Distance to active waypoint cannot be computed due to 
unsupported flight plan leg type (see Flight Management 
Section) X
XX
Aircraft > 250 feet below active VNV Target Altitude XXX
Current crosstrack or track angle error has exceeded limit XXX
Active altitude-constrained waypoint can not be reached within 
maximum allowed flight path angle and vertical speed X
X
Table 2-2  VNV Indication Removal Criteria  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 85079
FLIGHT INSTRUMENTS
2.3 PFD ANNUNCIATIONS AND ALERTING FUNCTIONS
The	 following	 annunciations	 and	alerting	 functions	 are	displayed	 on	the	 PFD.	 	 Refer	to	the	 Engine/Airframe	
Systems	 Section	for	information	 on	the	 Crew	 Alerting	 System	(CAS)	and	to	Appendix	 A	for	 more	 information	 on	
alerts and annunciations.
SYSTEM ALERTING
The System Messages Window conveys messages to the flight crew regarding problems with the G1000 
System.  When a new message is issued, the MSG	Softkey	 flashes	to	alert	 the	flight	 crew.		 It	continues	 to	flash	
until	 pressed,	 which	opens	the	System	 Messages	 Window	and	acknowledges	 the	message(s)	 which	initiated	 the	
flashing.  When the window is open, messages for conditions which are no longer active turn gray.  Messages 
generated while the window is open are not automatically displayed, but cause the MSG	Softkey	 to	begin	
flashing again.  Pressing the MSG	Softkey	 while	the	System	 Messages	 Window	is	open	 closes	 the	window	 unless	
the MSG	Softkey	is	flashing.
Critical values generated by redundant sensors are monitored by comparators.  If differences in the sensors 
exceed a specified amount, the Comparator Window appears in the upper right corner of the PFD and the 
discrepancy	 is	annunciated	 in	the	 Comparator	 Window	as	a	MISCOMP	 (miscompare).	 	 If	one	 or	both	 of	the	
sensed	values	are	unavailable,	it	is	annunciated	as	a	NO	COMP	(no	compare).
Reversionary sensor selection is annunciated in a window on the right side of the P\
FD.  These annunciations 
reflect reversionary sensors selected on one or both PFDs.  Pressing the SENSOR	Softkey	 accesses	 the	ADC1, 
ADC2, AHRS1, and AHRS2	softkeys.	 	 These	softkeys	 allow	switching	 of	the	 sensors	 being	viewed	 on	each	
PFD.		 With	certain	 types	of	sensor	 failures,	 the	system	 may	make	 some	sensor	 selections	 automatically.		 The	GPS	
sensor cannot be switched manually.
Softkey 
Flashes for 
New System 
Message
Messages 
Window
Reversionary 
Sensor
Window
Comparator 
Window
Figure 2-37  G1000 Alerting System  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A80
FLIGHT INSTRUMENTS
MARKER BEACON ANNUNCIATIONS
Marker	Beacon	Annunciations	 are	displayed	 on	the	 PFD	 to	the	 left	of	the	 Selected	 Altitude.	 	 Outer	marker	
reception	 is	indicated	 in	blue,	 middle	 in	amber,	 and	inner	 in	white.		 Refer	to	the	 Audio	 Panel	and	CNS	 Section	
for	more	information	on	Marker	Beacon	Annunciations.
Figure 2-38  Marker Beacon Annunciations
Outer Marker
Middle Marker
Inner Marker
Altimeter
TRAFFIC ANNUNCIATION
Traffic	is	displayed	 symbolically	 on	the	 Inset	 Map	(PFD),	 the	Navigation	 Map	Page	 (MFD),	 and	various	 other	
MFD	page	maps.		 Refer	to	the	 Hazard	 Avoidance	 Section	and	Appendix	 F	for	 more	 details	 about	Traffic	 alerts.		
When a Traffic	Advisory	(TA)	is	detected,	the	following	automatically	occurs:
•	 The	PFD	Inset	Map	is	enabled,	displaying	traffic
•	 A	flashing	 black-on-yellow	 TRAFFIC	annunciation	 appears	to	the	 top	 left	of	the	 Attitude	 Indicator	 for	five	
seconds	and	remains	displayed	until	no	TAs	are	detected	in	the	area
•	 The	aural	alert	“TRAFFIC”	is	generated
If	additional	TAs	appear,	new	aural	and	visual	alerts	are	generated.
Figure 2-39  Traffic Annunciation and Inset Map with Traffic Displayed
PFD Traffic Annunciation
Traffic 
Symbols
PFD Inset Map with Traffic Displayed  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 85081
FLIGHT INSTRUMENTS
TERRAIN ANNUNCIATIONS
Terrain	Awareness	 and	Warning	 System	(TAWS)	or	TERRAIN-SVS	 annunciations	appear	on	the	 PFD	 to	the	
upper	 left	of	the	 altimeter.		 Refer	to	the	 Hazard	 Avoidance	 Section	and	Appendix	 A	for	 information	 on	terrain	
alerts and annunciations.
Figure 2-40  Traffic and Example Terrain Annunciations  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A82
FLIGHT INSTRUMENTS
ALTITUDE ALERTING
The	Altitude	Alerting	function	provides	visual	alerts	when	approaching	the	Selected	Altitude,	and	visual	and	
aural	alerts	when	deviating	from	the	selected	altitude.		Whenever	the	Selected	Altitude	on	the	PFD	is	changed,	
Altitude	Alerting	is	reset.		Altitude	Alerting	is	independent	of	the	AFCS.
The	following	occur	when	approaching	the	Selected	Altitude:
•	 Upon	passing	through	 1000	feet	of	the	 Selected	 Altitude,	 the	Selected	 Altitude	Box	changes	 to	black	 text	on	
a	light	blue	background	and	flashes	for	five	seconds.
•	 When	 the	aircraft	 passes	within	 200	feet	of	the	 Selected	 Altitude,	 the	Selected	 Altitude	changes	to	light	 blue	
text	on	a	black	background	and	flashes	for	five	seconds.
•	 After	 reaching	 the	Selected	 Altitude,	 if	the	 aircraft	 flies	outside	 the	deviation	 band	(±200	 feet	of	the	 Selected	
Altitude),	 the	Selected	 Altitude	Box	changes	 to	yellow	 text	on	a	black	 background,	 flashes	for	five	 seconds,	
and an aural tone is generated.
Figure  2-41   Altitude Alerting Visual Annunciations
Within 1000 feetWithin 200 feetDeviation of ±200 feet
LOW ALTITUDE ANNUNCIATION
 NOTE:  This Low Altitude Annunciation is available only for aircraft with GIA 63W Integrated Avionics Units 
when SBAS is available.  This annunciation is not shown for systems with TAWS, unless TAWS is inhibited.
When	 the	Final	 Approach	 Fix	(FAF)	 is	the	 active	 waypoint	 in	a	GPS	 SBAS	 approach	 using	vertical	 guidance,	
a	Low	 Altitude	 Annunciation	 may	appear	 if	the	 current	 aircraft	altitude	 is	at	 least	 164	feet	below	 the	prescribed	
altitude	 at	the	 FAF.		 A	black-on-yellow	 LOW	ALT	annunciation	 appears	to	the	 top	 right	 of	the	 Altimeter,	 flashing	
for several seconds then remaining displayed until the condition is resolved.
Figure 2-42  Low Altitude on GPS SBAS Approach
Altimeter  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 85083
FLIGHT INSTRUMENTS
MINIMUM DESCENT ALTITUDE/DECISION HEIGHT ALERTING
For	altitude	 awareness,	 a	Minimum	 Descent	Altitude	 (MDA)	or	Decision	 Height	(DH),	based	on	barometric	
altitude or radar altitude, can be set.  When active, the altitude setting is displayed to the lower left of the 
altimeter and with a bug at the corresponding altitude along the altimeter (once the altitude is within the\
 visible 
range	of	the	tape).		The	following	visual	annunciations	alert	the	pilot	when	approaching	the	MDA	or	DH:
•	 When	 the	aircraft	 altitude	 descends	 to	within	 2500	feet	of	the	 MDA/DH	 setting,	a	box	 labeled	 BARO	MIN	or	
RA	MIN	 (based	 on	the	 selected	 altitude	source)	appears	 with	the	altitude	 in	light	 blue	text.		 The	bug	appears	
in light blue on the altitude tape at the corresponding altitude once in range.
•	 When	the	aircraft	passes	through	100	feet	of	the	MDA	or	DH,	the	bug	and	text	turn	white.
•	 Once	 the	aircraft	 reaches	 the	MDA/DH,	 the	bug	 and	text	turn	 yellow	 and	the	aural	 alert,	 “Minimums	
Minimums”,	 is	generated.	 	 When	the	radar	 altimeter	 is	selected	 as	the	 altitude	 source	for	the	 Minimum	
Descent	Altitude	alerting	function,	the	color	of	the	current	radar	height	changes	to	yellow.
Figure 2-43  Barometric MDA/DH Alerting Visual Annunciations
Altitude ReachedWithin 100 feet
MDA/DH 
Setting
MDA/DH  Bug
Within 2500 feet
Alerting	 is	inhibited	 while	the	aircraft	 is	on	 the	 ground	 and	until	 the	aircraft	 reaches	 150	feet	above	 the	setting	
for	the	 alert.		 If	the	 aircraft	 proceeds	 to	climb	 after	having	 reached	 the	MDA/DH,	 once	it	reaches	 50	feet	 above	
the	MDA/DH,	alerting	is	disabled.
The	 MDA/DH	 may	be	set	 from	 either	 PFD	and	is	synchronized	 on	both	 PFDs.		 The	function	 is	reset	 when	 the	
power is cycled.
Setting the barometric minimum descent altitude and bug:
1) Press the TMR/REF Softkey.
2) Turn the large FMS Knob to highlight the Minimums field.
3) Turn the small FMS Knob to select the desired altitude source: barometric (BARO)  or radar altimeter (RAD ALT).  
OFF is selected by default.  Press the ENT Key or turn the large FMS Knob to highlight the next field.
4) Use the small FMS Knob to enter the desired altitude (from zero to 16,000 feet).
5) To remove the window, press the CLR Key or press the TMR/REF Softkey.
Figure 2-44  Timer/References Window, MDA/DH Setting  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A84
FLIGHT INSTRUMENTS
RADAR ALTIMETER
When the radar height (the aircraft altitude above ground level detected by the radar altimeter) is between 
zero	and	2500	 feet,	the	current	 value	is	displayed	 in	green	 to	the	 upper	 right	of	the	 HSI	 (Figure	 2-45).	Display	
of	radar	height	becomes	more	sensitive	as	the	height	above	ground	decreases	(Table	2-3).
Figure 2-45 Current Radar Height
Radar Altimeter
Radar Height Range Shown to Nearest
0 to 200 feet 5 feet
200 to 1500 feet 10 feet
1500 to 2500 feet 50 feet
Table 2-3  Radar Altimeter Sensitivity
When the radar altimeter is selected as the altitude source for the minimum descent altitude alerting function 
(Figure	2-46),	the	color	 of	the	radar	height	changes	to	 yellow	upon	reaching	(or	desending	below)	the	altitude	
entered.	(Figure	2-47).
Figure 2-46  RAD ALT Setting
(Timer/References Window)
Figure 2-47  RA as Altitude Source for MDA/DH  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 85085
FLIGHT INSTRUMENTS
A	ground	 line	(Figure	 2-48)	is	shown	 on	the	 Altimeter	 to	display	 the	aircraft’s	 height	relative	 to	the	 ground.		
If	the	 data	 becomes	 invalid,	the	message	 “RA	FAIL”	 is	displayed	 in	yellow	 in	place	 of	the	 current	 radar	height	
(Figure	 2-49).	 	The	Radar	 Altimeter	 test	is	done	 on	the	 MFD	 but	is	displayed	 on	the	 PFD	 directly	 above	the	
Radar	Altimeter	box	(Figure	2-50).
Figure 2-48  Altimeter Displaying the Ground Line (RAD ALT)
Ground
Line
Radar Altimeter
Minimums Box
Radar Altimeter
Figure 2-49  Radar Altimeter Invalid Data
Testing the Radar Altimeter (KRA 405 only):
1) Turn the FMS Knob to select the AUX - System Status Page on the MFD.
2) Select the RA TEST Softkey.
 Or:
1) Press the MENU Key.
2) Turn the FMS Knob to highlight ‘Enable RA Test Mode’ and press the ENT Key.
 The ‘RA TEST’ annunciation is displayed above the RA box (Figure 2-50).  To cancel the test, select the RA TEST 
Softkey again, or turn the FMS Knob to exit the AUX - System Status Page.
Figure 2-50  Radar Altimeter Test Display (KRA 405)  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A86
FLIGHT INSTRUMENTS
2.4 ABNORMAL OPERATIONS
ABNORMAL GPS CONDITIONS
The	 annunciations	 listed	in	Table	 2-4	can	 appear	 on	the	 HSI	 when	 abnormal	 GPS	conditions	 occur	(Figure	
2-52).		Refer	to	the	Flight	Management	Section	for	more	information	on	Dead	Reckoning	Mode.
AnnunciationLocationDescription
LOILower left of 
aircraft symbol
Loss of Integrity Monitoring–GPS integrity is insufficient for the \
current 
phase of flight
INTEG OKLower left of 
aircraft symbol
Integrity OK–GPS integrity has been restored to within normal limits \
(annunciation displayed for five seconds)
DRUpper right of 
aircraft symbol
Dead Reckoning–System is using projected position rather than GPS position 
to compute navigation data and sequence active flight plan waypoints
Table 2-4  Abnormal GPS Conditions Annunciated on HSI
Figure 2-51  Example of HSI Annunciations 
Dead	Reckoning	 (DR)	Mode	 causes	 the	following	 items	on	the	 PFD	 to	be	 shown	 in	yellow	 when	GPS	is	the	
selected navigation source:
•	 CDI	(removed	after	20	minutes)
•	 Current	Track	Bug
•	 Wind	Data	(calculated	based	on	GPS	information)
•	 Distances	in	the	Bearing	Information	windows
•	 GPS	bearing	pointers
It is important to note that estimated navigation data supplied by the G\
1000 in DR Mode may become 
increasingly unreliable and must not be used as a sole means of navigation.  See the Flight Management section 
for more information about DR mode