Garmin G1000 Manual

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850477
AUTOMATIC FLIGHT CONTROL SYSTEM
PITCH HOLD MODE (PIT)
When	the	flight	 director	 is	activated	 (the	FD Key is pressed) or switched (the XFR	Key	 is	pressed),	 Pitch	Hold	
Mode	 is	selected	 by	default.		 Pitch	Hold	Mode	 is	indicated	 as	the	 active	 vertical	 mode	by	the	 ‘PIT’	 annunciation.		
This mode may be used for climb or descent to the Selected Altitude (shown above the Altimeter), since 
Selected Altitude	Capture	Mode	is	automatically	armed	when	Pitch	Hold	Mode	is	activated.
In	Pitch	 Hold	Mode,	 the	flight	 director	 maintains	 a	constant	 pitch	attitude,	 the	pitch	 reference.	 	 The	pitch	
reference	 is	set	 to	the	 aircraft	 pitch	attitude	 at	the	 moment	 of	mode	 selection.	 	 If	the	 aircraft	 pitch	attitude	
exceeds	 the	flight	 director	 pitch	command	 limitations,	 the	flight	 director	 commands	 a	pitch	 angle	 equal	 to	the	
nose-up/down limit.
CHANGING THE PITCH REFERENCE
When	operating	in	Pitch	Hold	Mode,	the	pitch	reference	can	be	adjusted	by:
•	 Using	the	NOSE UP/DN	Wheel
•	 Pressing	 the	CWS Button, hand-flying the aircraft to establish a new pitch reference, then releasing the 
CWS Button
Figure 7-6  Pitch Hold Mode
Selected 
Altitude
Selected Altitude 
Capture Mode ArmedPitch Hold 
Mode Active
Command Bars Maintain Desired Pitch Reference  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A478
AUTOMATIC FLIGHT CONTROL SYSTEM
SELECTED ALTITUDE CAPTURE MODE (ALTS)
Selected Altitude Capture Mode is automatically armed with activation of the following modes:
•	 Pitch
The	white	 ‘ALTS’	 annunciation	 indicates	Selected	Altitude	Capture	Mode	is	armed	 (see	Figure	 7-6	for	example).		
The ALT SEL Knob is used to set the Selected Altitude (shown above the Altimeter)\
 until Selected Altitude 
Capture Mode becomes active.
As the aircraft nears the Selected Altitude, the flight director automatically transitions to Selected Altitude 
Capture Mode with Altitude Hold Mode armed (Figure 7-7).  This automatic transition is indicated by the green 
‘ALTS’	 annunciation	 flashing	for	up	to	10	 seconds	 and	the	appearance	 of	the	 white	 ‘ALT’	annunciation.	 	 The	
Selected Altitude is shown as the Altitude	Reference	beside	the	‘ALTS’	annunciation.
At 50 feet from the Selected Altitude, the flight director automatically transitions from Selected Altitude 
Capture to Altitude Hold Mode and holds the Selected Altitude (shown as the A\
ltitude Reference).  As Altitude 
Hold	Mode	 becomes	 active,	the	white	 ‘ALT’	annunciation	 moves	to	the	 active	 vertical	 mode	field	and	flashes	
green for 10 seconds to indicate the automatic transition.
Figure 7-7  Automatic Mode Transitions During Altitude Capture
Altitude Reference 
(in this case, equal to  Selected Altitude)
Flash up to 10 sec, Indicating Automatic Transition
CHANGING THE  SELECTED ALTITUDE
 NOTE: Pressing the CWS Button while in Selected Altitude Capture Mode does not cancel the mode.
Use of the ALT SEL Knob to change the Selected Altitude while Selected Altitude Capture Mode is active 
causes	 the	flight	 director	 to	revert	 to	Pitch	 Hold	Mode	 with	Selected	 Altitude	Capture	Mode	armed	 for	the	
new Selected Altitude.  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850479
AUTOMATIC FLIGHT CONTROL SYSTEM
ALTITUDE HOLD MODE (ALT)
Altitude Hold Mode can be activated by pressing the A LT Key; the flight director maintains the current aircraft 
altitude (to the nearest 10 feet) as the Altitude Reference.  The flight director’s Altitude Reference, shown in the 
AFCS	Status	 Box,	is	independent	 of	the	 Selected	 Altitude,	 displayed	 above	the	Altimeter.		 Altitude	Hold	Mode	
active	is	indicated	by	a	green	‘ALT’	annunciation	in	the	AFCS	Status	Box.
Altitude Hold Mode is automatically armed when the flight director is in Selected Altitude Capture Mode (see 
Figure 7-7).  Selected Altitude Capture Mode automatically transitions to Altitude Hold Mode when the altitude\
 
error	is	less	than	50	feet.		In	this	case,	the	Selected	Altitude	becomes	the	flight	director’s	Altitude	Reference.
CHANGING THE ALTITUDE  REFERENCE
 NOTE: Turning the ALT SEL Knob while in Altitude Hold Mode changes the Selected Altitude, but not the 
flight director’s Altitude Reference, and does not cancel the mode.
With	 the	CWS	Button	 depressed,	 the	aircraft	 can	be	hand-flown	 to	a	new	 Altitude	 Reference.		 When	the	
CWS Button is released at the desired altitude, the new altitude is established as the Altitude Reference.
Figure 7-8  Altitude Hold Mode
Selected 
Altitude
Selected  Altitude  Bug
Command Bars Hold Pitch Attitudeto Maintain Altitude Reference
Altitude Hold Mode ActiveAltitude 
Reference  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A480
AUTOMATIC FLIGHT CONTROL SYSTEM
VERTICAL SPEED MODE (VS)
In	Vertical	 Speed	Mode,	 the	flight	 director	 acquires	 and	maintains	 a	Vertical	 Speed	Reference.		 Current	aircraft	
vertical speed (to the nearest 100 fpm) becomes the Vertical Speed Reference at the moment of Vertical Speed 
Mode activation.  This mode may be used for climb or descent to the Selected Altitude (shown above the 
Altimeter) since Selected Altitude Capture Mode is automatically armed when Vertical Speed Mode is selected.
When	Vertical	 Speed	Mode	is	activated	 by	pressing	 the	VS	Key,	 ‘VS’	is	annunciated	 in	green	 in	the	 AFCS	 Status	
Box	along	 with	the	Vertical Speed Reference.  The Vertical Speed Reference is also displayed above the Vertical 
Speed	 Indicator.	 	 A	Vertical	 Speed	Reference	 Bug	corresponding	 to	the	 Vertical	 Speed	Reference	 is	shown	 on	
the indicator.
CHANGING THE VERTICAL  SPEED  REFERENCE
The	Vertical	 Speed	Reference	 (shown	both	in	the	 AFCS	 Status	 Box	and	above	 the	Vertical	 Speed	Indicator)	
may be changed by:
•	 Using	the	NOSE UP/DN	Wheel
•	 Pressing	 the	CWS Button, hand-flying the aircraft to attain a new Vertical Speed Reference, then releasing 
the CWS Button
 NOTE: If the Selected Altitude is reached during CWS maneuvering, the Altitude Reference is not changed.  
To adjust the Altitude Reference in this case, the CWS Button must be pressed again after the Selected 
Altitude is reached.
Figure 7-9  Vertical Speed Hold Mode
Command Bars Indicate Climb to 
Attain Vertical Speed Reference
SelectedAltitudeVertical
Speed
Reference
Vertical
Speed 
Reference
Bug
Selected 
Altitude Capture  Mode ArmedVertical Speed Mode ActiveVertical Speed 
Reference  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850481
AUTOMATIC FLIGHT CONTROL SYSTEM
FLIGHT LEVEL CHANGE MODE (FLC)
 NOTE: The Selected Altitude should be set before selecting Flight Level Change Mode.
Flight Level Change Mode is selected by pressing the FLC Key.  This mode acquires and maintains the 
Airspeed	Reference	 (in	IAS	 or	Mach)	 while	climbing	 or	descending	 to	the	Selected Altitude (shown above 
the	 Altimeter).		 When	Flight	Level	Change	 Mode	is	active,	 the	flight	 director	 continuously	 monitors	Selected	
Altitude, airspeed, Mach, and altitude.
The Airspeed Reference is set to the current airspeed upon mode activation.  Flight Level Change Mode is 
indicated	 by	a	green	 ‘FLC’	annunciation	 beside	the	Airspeed	 Reference	 in	the	 AFCS	 Status	 Box.		The	Airspeed	
Reference	 is	also	 displayed	 directly	above	the	Airspeed	 Indicator,	 along	with	a	bug	 corresponding	 to	the	 Airspeed	
Reference along the tape.
Engine power must be adjusted to allow the autopilot to fly the aircraft at a pitch attitude corresponding 
to the desired flight profile (climb or descent) while maintaining the Airspeed Reference.  The flight director 
maintains the current altitude until either engine power or the Airspeed Reference are adjusted and does not 
allow the aircraft to climb or descend away from the Selected Altitude.
Figure 7-10  Flight Level Change Mode (IAS)
Airspeed 
Reference
Airspeed 
Reference  Bug
Command Bars Indicate Climbto attain Selected Altitude
Selected 
Altitude Capture  Mode ArmedFlight Level 
Change Mode  ActiveAirspeed 
Reference  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A482
AUTOMATIC FLIGHT CONTROL SYSTEM
CHANGING THE AIRSPEED  REFERENCE
The	Airspeed	 Reference	 (shown	in	both	 the	AFCS	 Status	 Box	and	above	 the	Airspeed	 Indicator)	 may	be	
adjusted by:
•	 Using	the	NOSE UP/DN	Wheel
•	 Pressing	 the	CWS Button, hand-flying the aircraft to attain a new Airspeed Reference, then releasing the 
CWS Button
 NOTE: If the Selected Altitude is reached during CWS maneuvering, the Altitude Reference is not changed.  
To adjust the Altitude Reference in this case, the CWS Button must be pressed again after the Selected 
Altitude is reached.
Airspeed	Reference	 units	can	be	manually	 toggled	between	 IAS	and	 Mach	 units	using	 the	SPD	Key.		 When	
the FLC Airspeed Reference is displayed in Mach, the Airspeed Reference Bug is displayed on the Airspeed 
Indicator	 at	the	 IAS	 corresponding	 to	the	 selected	 Mach	target	 speed	 and	the	current	 Mach	number	 is	shown	
below	the	Airspeed	Indicator.
Figure 7-11  Flight Level Change Mode (Mach)
Selected 
Altitude Capture  Mode ArmedFlight Level 
Change Mode  ActiveAirspeed 
Reference  (Mach)
Command Bars Indicate Climb to Attain Selected AltitudeCurrentMach 
Number
Airspeed 
Reference Bug
Airspeed 
Reference  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850483
AUTOMATIC FLIGHT CONTROL SYSTEM
VERTICAL NAVIGATION MODES (VPTH, ALTV)
 NOTE: VNV is disabled when parallel track or Dead Reckoning Mode is active.  Refer to the Flight Management 
Section for more information on VNV flight plans.
 NOTE: The Selected Altitude takes precedence over any other vertical constraints.
Vertical Navigation (VNV) flight control is available for enroute/terminal cruise and descent operations when 
VNV flight planning is available.  Conditions for availability include\
, but are not limited to:
•	 The	selected	navigation	source	is	GPS.
•	 A	VNV	flight	plan	(with	at	least	one	altitude-constrained	waypoint)	or	vertical	direct-to	is	active.
•	 VNV	is	enabled	(VNV ENBL	Softkey	pressed	on	the	MFD).
•	 Crosstrack	error	is	valid	and	within	certain	limits.
•	 Desired/actual	track	are	valid	or	track	angle	error	is	within	certain	limits.
•	 The	VNV	Target	Altitude	of	the	active	waypoint	is	no	more	than	250	ft	above	the	current	aircraft	altitude.
The flight director may be armed for VNV at any time, but no target altitudes are captured during a climb.  
The Command Bars provide vertical profile guidance based on specified altitudes (entered manually or loaded 
from the database) at waypoints in the active flight plan or vertical d\
irect-to.  The appropriate VNV flight control 
modes are sequenced by the flight director to follow the path defined by the vertical profile.  Upon reaching 
the last waypoint in the VNV flight plan, the flight director transitions to Altitude Hold Mode and cancels any 
armed VNV modes.
VERTICAL PATH TRACKING MODE (VPTH)
 NOTE: If another vertical mode key is pressed while Vertical Path Tracking Mode is selected, Vertical Path 
Tracking Mode reverts to armed.
 NOTE: Pressing the CWS Button while Vertical Path Tracking Mode is active does not cancel the mode.  The 
autopilot guides the aircraft back to the descent path upon release of t\
he CWS Button.
When	a	vertical	 profile	(VNV	flight	plan)	is	active	 and	the	VNV	Key	 is	pressed,	 Vertical	Path	Tracking	
Mode	 is	armed	 in	preparation	 for	descent	 path	capture.		 ‘VPTH’	(or	‘/V’	 when	 Glidepath	 or	Glideslope	 Mode	
is	concurrently	 armed)	is	annunciated	 in	white	 in	addition	 to	previously	 armed	modes.	 	 If	applicable,	 the	
appropriate altitude	capture	mode	is	armed	 for	capture	 of	the	 next	VNV Target Altitude (ALTV) or the Selected 
Altitude (ALTS), whichever is greater.
Figure  7-12   Vertical  Path Tracking Armed Annunciations  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A484
AUTOMATIC FLIGHT CONTROL SYSTEM
Prior	to	descent	 path	interception,	 the	Selected	 Altitude	must	be	set	 below	 the	current	 aircraft	altitude	
by	at	least	 75	feet.	 	 For	the	flight	 director	 to	transition	 from	Altitude	 Hold	to	Vertical	 Path	Tracking	 Mode,	
acknowledgment is required within five minutes of descent path interception by:
•	 Pressing	the	VNV Key
•	 Adjusting	the	Selected	Altitude
If	acknowledgment	 is	not	 received	 within	1	minute	 of	descent	 path	interception,	 the	white	 ‘VPTH’	
annunciation	 starts	to	flash.	 	 Flashing	 continues	 until	acknowledged	 or	the	 descent	 path	is	intercepted.	 	 If	
the	descent	 is	not	 confirmed	 by	the	 time	 of	interception,	 Vertical	Path	Tracking	 Mode	remains	 armed	and	the	
descent is not captured.
In	conjunction	 with	the	“TOD	 [top	of	descent]	 within	1	minute”	 annunciation	 in	the	 PFD	 Navigation	 Status	
Box	and	the	“Vertical	 track”	voice	message,	 VNV	indications	 (VNV	Target	 Altitude,	 vertical	deviation,	 and	
vertical	speed	required)	appear	on	the	PFDs	in	magenta	(Figure	7-13).
Figure 7-13  Vertical Path Capture
Required
Vertical
Speed Bug
Vertical
Deviation Indicator
VNV Target  Altitude
Enroute
Phase of FlightGPS is Selected  NavigationSource
Vertical Path Tracking 
Armed, (Flashing Indicates 
Acknowledgment Required)Altitude Hold  Mode Active  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850485
AUTOMATIC FLIGHT CONTROL SYSTEM
When	a	descent	 leg	is	captured	 (i.e.,	vertical	 deviation	 becomes	valid),	Vertical	 Path	Tracking	 becomes	
active	and	tracks	 the	descent	 profile	(Figure	 7-14).		An	altitude	 capture	mode	(‘ALTS’	 or	‘ALTV’)	 is	armed	 as	
appropriate.
Figure 7-14  Vertical Path Tracking Mode
Command Bars Indicate Descent to 
Maintain Required Vertical SpeedTerminal
Phase of FlightGPS is Selected  NavigationSource
VNV Target Altitude  Capture ArmedVertical Path 
Tracking Active
VNV Target  Altitude
Vertical
Deviation
Indicator (VDI)
Required VerticalSpeed
Indication (RVSI)
If	 the	 altimeter	 barometric	 setting	is	adjusted	 while	Vertical	 Path	Tracking	 is	active,	 the	flight	 director	
increases/decreases the descent rate by up to 500 fpm to re-establish the aircraft on the descent path (without 
commanding a climb).  Adjusting the altimeter barometric setting creates discontinuities in VNV vertical 
deviation, moving the descent path.  For large adjustments, it may take several minutes for the aircraft to re-
establish	 on	the	 descent	 path.		If	the	 change	 is	made	 while	nearing	 a	waypoint	 with	a	VNV	 Target	 Altitude,	
the aircraft may not re-establish on the descent path in time to meet the vertical constraint.\
  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A486
AUTOMATIC FLIGHT CONTROL SYSTEM
aUtOmatic ReveRsiOn tO Pitch hOlD mODe
Several	 situations	 can	occur	 while	Vertical	 Path	Tracking	 Mode	is	active	 which	 cause	the	flight	 director	 to	
revert	to	Pitch	Hold	Mode:
•	 Vertical	deviation	exceeds	200	feet	during	an	overspeed	condition.
•	 Vertical	 deviation	experiences	 a	discontinuity	 that	both	 exceeds	 200	feet	in	magnitude	 and	results	 in	the	
vertical	 deviation	 exceeding	 200	feet	in	magnitude.		 Such	discontinuities	 are	usually	 caused	by	flight	 plan	
changes that affect the vertical profile.
•	 Vertical	deviation	becomes	invalid	(the	Vertical	Deviation	Indicator	is	removed	from	the	PFD).
•	 A	display	enters	Reversionary	Mode	(this	does	not	apply	to	an	active	vertical	direct-to).
Unless	 VNV	is	disabled,	 Vertical	Path	Tracking	 Mode	and	the	appropriate	 altitude	capture	mode	become	
armed	following	the	reversion	to	Pitch	Hold	Mode	to	allow	for	possible	profile	recapture.
nOn-Path Descents
Pitch	Hold,	 Vertical	 Speed,	and	Flight	 Level	Change	 modes	can	also	 be	used	 to	fly	 non-path	 descents	
while	VNV	flight	control	is	selected.		If	the	VS or FLC	Key	is	pressed	while	Vertical	Path	Tracking	Mode	is	
selected,	Vertical	Path	Tracking	 Mode	reverts	 to	armed	 along	with	the	appropriate	 altitude	capture	mode	to	
allow profile re-capture.
Figure 7-15  Flight Level Change VNV Non-Path Descent
To prevent immediate profile re-capture, the following must be satisfied:
•	 At	least	10	seconds	have	passed	since	the	non-path	transition	was	initiated
•	 Vertical	deviation	from	the	profile	has	exceeded	250	feet,	but	is	now	less	than	200	feet
Pressing	the	VNV	Key	twice	re-arms	Vertical	Path	Tracking	for	immediate	profile	re-capture.