Garmin G1000 Manual

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850467
HAZARD AVOIDANCE
Traffic Map Page 
AnnunciationDescription
NO DATAData is not being received from the TAS unit
DATA FAILEDData is being received from the TAS unit, but the 
unit is self-reporting a failure
FAILEDIncorrect data format received from the TAS unit
Table 6-38  TAS Failure Annunciations
The	annunciations	 to	indicate	 the	status	 of	traffic	 information	 appear	in	a	banner	 at	the	 lower	 left	corner	 of	
maps	on	which	traffic	can	be	displayed.
Traffic Status Banner 
AnnunciationDescription
TA OFF SCALE
A Traffic Advisory is outside the selected display range* 
Annunciation is removed when traffic comes within the 
selected display range
TA X.X ± XX ↕
System cannot determine bearing of Traffic Advisory** 
Annunciation indicates distance in nm, altitude 
separation in hundreds of feet, and altitude trend 
arrow (climbing/descending)
TRFC FAILTAS unit has failed (unit is self-reporting a failure or 
sending incorrectly formatted data)
NO TRFC  DATAData is not being received from the TAS unit
  *Shown as symbol on Traffic Map Page**Shown in center of Traffic Map Page
Table  6-39   TAS Traffic  Status Annunciations  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A468
HAZARD AVOIDANCE
Blank Page  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850469
AUTOMATIC FLIGHT CONTROL SYSTEM
SECTION 7  AUTOMATIC FLIGHT CONTROL SYSTEM
 NOTE: The approved Pilot’s Operating Handbook (POH) always supersedes this Pilot’s Guide.
The GFC 700 is a digital Automatic Flight Control System (AFCS), fully integrated within the G1000 System 
avionics architecture.  The System Overview section provides a block diagram to support this system description.  
GFC 700 AFCS functionality in the Socata TBM 850 is distributed across the following Line Replaceable Units 
(LRUs):
•	 GDU
The GFC 700 AFCS can be divided into these main operating functions:
•	Flight Director (FD)	—	 The	 Socata	 TBM	850	has	two	 flight	 directors,	 each	operating	 within	an	IAU	 and	
referred	 to	as	pilot-side	 and	copilot-side.		 Commands	for	the	 selected	 flight	director	 are	displayed	 on	both	 PFDs.		
The flight directors provide:
   – Command Bars showing pitch/roll guidance
    – Vertical/lateral mode selection and processing
  –  Autopilot communication
•	Autopilot (AP) — Autopilot operation occurs within the pitch, roll, and pitch trim servos and yaw trim 
adapter.		 It	also	 provides	 servo	monitoring	 and	automatic	 flight	control	 in	response	 to	flight	 director	 steering	
commands, Attitude and Heading Reference System (AHRS) attitude and rate information, and airspeed.
•	Yaw Damper (YD)	—	 The	 yaw	 servo	 is	self-monitoring	 and	provides	 Dutch	roll	damping	 and	turn	 coordination	
in response to yaw rate, roll angle, lateral acceleration, and airspeed.
•	Manual Electric Pitch Trim (MEPT) — The pitch trim servo provides manual electric pitch trim capability 
when the autopilot is not engaged.
•	Manual Electric Yaw Trim (MEYT) — The yaw trim adapter provides manual electric yaw trim capability 
when the autopilot is not engaged.  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A470
AUTOMATIC FLIGHT CONTROL SYSTEM
7.1 AFCS CONTROLS
The	AFCS	Control	Unit	is	positioned	above	the	MFD,	and	has	the	following	controls:
1HDG KeySelects/deselects Heading Select Mode
2APR KeySelects/deselects Approach Mode
3NAV KeySelects/deselects Navigation Mode
4FD KeyActivates/deactivates the flight director only
Pressing	once	turns	 on	the	 selected	 flight	director	 in	the	 default	 vertical	 and	lateral	
modes.		 Pressing	 again	deactivates	 the	flight	 director	 and	removes	 the	Command	
Bars.		If	the	autopilot	is	engaged,	the	key	is	disabled.
5XFR KeyTransfers between the pilot and copilot flight directors and controls which flight 
director the autopilot is tracking
6ALT KeySelects/deselects Altitude Hold Mode
7VS KeySelects/deselects Vertical Speed Mode
8FLC KeySelects/deselects Flight Level Change Mode
9  17CRS KnobsAdjust the Selected Course (while in VOR, LOC, or OBS Mode) in 1° i\
ncrements on 
the	Horizontal	Situation	Indicator	(HSI)	of	the	corresponding	PFD
Press	 to	re-center	 the	Course	 Deviation	 Indicator	(CDI)	and	return	 course	 pointer	
directly TO the bearing of the active waypoint/station
10SPD KeyToggles Airspeed	Reference	between	IAS	and	Mach	for	Flight	Level	Change	Mode
11NOSE UP/DN 
Wheel
Adjusts	 the	reference	 in	Pitch	 Hold,	 Vertical	 Speed,	and	Flight	 Level	Change	
modes
12VNV KeySelects/deselects	Vertical	Path	Tracking	Mode	for	Vertical	Navigation	flight	control
13ALT SEL KnobControls the Selected Altitude in 100-ft increments (a finer resolution of 10 feet is 
available under approach conditions)
14YD KeyEngages/disengages the yaw damper
15AP KeyEngages/disengages the autopilot
16BANK KeyManually selects/deselects Low Bank Mode
18BC KeySelects/deselects Backcourse Mode
19HDG KnobAdjusts	the	Selected	Heading	and	bug	in	1°	increments	on	the	HSI	(both	PFDs)
Press	to	synchronize	the	Selected	Heading	to	the	current	heading	on	the	pilot-side	PFD
12345678Annunciator Light
109171615141312111819
Figure 7-1  GMC 710 AFCS Control Unit  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850471
AUTOMATIC FLIGHT CONTROL SYSTEM
The following AFCS controls are located separately from the AFCS Control Unit:
AP DISC Switch 
(Autopilot 
Disconnect)
Disengages	the	autopilot,	 yaw	damper,	 and	flight	 director	 and	interrupts	 pitch	trim	
operation
An AP DISC Switch is located on each control wheel.
This switch may be used to acknowledge an autopilot disconnect alert and mute the 
associated aural tone.
CWS Button 
(Control Wheel 
Steering)
While	 pressed,	 allows	manual	 control	of	the	 aircraft	 while	the	autopilot	 is	engaged	 and	
synchronizes the flight director’s Command Bars with the current aircraft pitch (if 
not in a Vertical Navigation, Glideslope, or Glidepath Mode) and roll (if in Roll Hold 
Mode)
A CWS Button is located on each control wheel.
Upon release of the CWS Button, the flight director may establish new pitch and roll 
references,	 depending	 on	the	 current	 vertical	and	lateral	 modes.	 	 CWS	operation	
details are discussed in the respective mode sections of this manual.
GA Switch 
(Go Around)
Disengages	 the	autopilot	 and	selects	 flight	director	 Takeoff	(on	ground)	 or	Go	 Around	
(in air) Mode
If	an	 approach	 procedure	 is	loaded	 this	switch	 also	activates	 the	missed	 approach	 when	
the	selected	 navigation	 source	is	GPS	 or	when	 the	navigation	 source	is	VOR/LOC	 and	
a valid frequency has been tuned.
The GA Switch is located on the throttle.
MEPT Switch 
(Manual Electric 
Pitch Trim)
Used to command manual electric pitch trim
An MEPT Switch is located on each control wheel.
This composite switch is split into left and right sides.  The left swit\
ch is the ARM 
contact	and	the	right	 switch	 controls	 the	DN	 (forward)	 and	UP	(rearward)	 contacts.		
Pushing	the	MEPT ARM Switch disengages the autopilot, if currently engaged, but 
does not affect yaw damper operation.  The MEPT ARM Switch may be used to 
acknowledge an autopilot disconnect alert and mute the associated aural \
tone.
Manual trim commands are generated only when both sides of the switch are operated 
simultaneously.	 	 If	either	 side	of	the	 switch	 is	active	 separately	 for	more	 than	three	
seconds,	 MEPT	function	 is	disabled	 and	‘PTRM’	 (Pitch	Trim	Failure)	 is	displayed	 as	
the	AFCS	 Status	 Annunciation	 on	the	 PFDs.	 	 The	function	 remains	disabled	 until	
both sides of the switch are inactivated.
MEYT Switch 
(Manual Electric 
Yaw Trim)
Used to command manual electric yaw trim
An MEYT Switch is located on each control wheel.  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A472
AUTOMATIC FLIGHT CONTROL SYSTEM
7.2 FLIGHT DIRECTOR OPERATION
The	flight	 director	 function	 provides	 pitch	and	roll	commands	 to	the	 AFCS	 and	displays	 them	on	the	 PFDs.		
With	 the	flight	 director	 active,	the	aircraft	 can	be	hand-flown	 to	follow	 the	path	 shown	 by	the	 Command	 Bars.		
Maximum	commanded	 pitch	(-15°,	 +25°)	and	roll	(25°)	 angles,	 vertical	 acceleration,	 and	roll	rate	 are	limited	 to	
values established during AFCS certification.  The flight director also provides commands to the autopilot.
ACTIVATING THE FLIGHT DIRECTOR
An initial press of a key listed in Table 7-1 (when the flight director is not active) activates the pilot-side flight 
director in the listed modes.  The flight director may be turned off and the Command Bars removed from the 
displays by pressing the FD Key again.  The FD Key is disabled when the autopilot is engaged.
Control PressedModes Selected
LateralVertical
FD KeyRoll Hold (default)ROLPitch Hold (default)PIT
AP KeyRoll Hold (default)ROLPitch Hold (default)PIT
CWS ButtonRoll Hold (default)ROLPitch Hold (default)PIT
GA SwitchTakeoff (on ground)
Go Around (in air)
TO
GA
Takeoff (on ground)
Go Around (in air)
TO
GA
A LT KeyRoll Hold (default)ROLAltitude HoldA LT
VS KeyRoll Hold (default)ROLVertical SpeedVS
VNV KeyRoll Hold (default)ROLVertical  Path Tracking*VPTH
NAV KeyNavigation**
GPS 
VOR 
LOC
Pitch Hold (default)PIT
BC KeyBackcourse***BCPitch Hold (default)PIT
APR KeyApproach**
GPS 
VOR 
LOC
Pitch Hold (default)PIT
HDG KeyHeading SelectHDGPitch Hold (default)PIT
*Valid VNV flight plan must be entered before VNV Key press activates flight director.
**The selected navigation receiver must have a valid VOR or LOC signal o\
r active GPS course before NAV or APR Key press activates flight director.
***The selected navigation receiver must have a valid LOC signal before \
BC Key press activates flight director.
Table 7-1  Flight Director Activation  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850473
AUTOMATIC FLIGHT CONTROL SYSTEM
AFCS STATUS BOX
Flight	director	 mode	annunciations	 are	displayed	 on	the	 PFDs	 when	 the	flight	 director	 is	active.	 	 Flight	
director selection and autopilot and yaw damper statuses are shown in the center of the AFCS	Status	 Box.		
Lateral flight director modes are displayed on the left and vertical on the right.  Armed modes are displayed in 
white and active in green.
GPS is
Selected 
Navigation Source
Command Bars
VerticalSpeed 
Reference
Selected Altitude 
Figure 7-2  PFD AFCS Display
AFCS Status Box
Flight Director 
Indicator ArrowActiveActive
Yaw 
Damper  Status
Lateral ModesAutopilot  StatusVertical Modes
Mode 
ReferenceArmedArmed  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A474
AUTOMATIC FLIGHT CONTROL SYSTEM
FLIGHT DIRECTOR MODES
Flight	director	 modes	are	normally	 selected	independently	 for	the	 pitch	 and	roll	axes.	 	 Unless	 otherwise	
specified,	 all	mode	 keys	are	alternate	 action	(i.e.,	press	 on,	press	 off).		In	the	 absence	 of	specific	 mode	selection,	
the flight director reverts to the default pitch and/or roll mode(s).  Mode keys on the AFCS controller are 
accompanied by annunciator lights (Figure 7-1) which are illuminated when their respective modes are armed 
or active.
Armed	 modes	are	annunciated	 in	white	 and	active	 in	green	 in	the	 AFCS	 Status	 Box.		Under	 normal	 operation,	
when the control for the active flight director mode is pressed, the flight director reverts to the default mode(s) 
for	the	 axis(es).	 	 Automatic	 transition	from	armed	 to	active	 mode	is	indicated	 by	the	 white	 armed	 mode	
annunciation moving to the green active mode field and flashing for 10 seconds.
If	the	 information	 required	to	compute	 a	flight	 director	 mode	becomes	 invalid	or	unavailable,	 the	flight	
director	 automatically	 reverts	to	the	 default	 mode	for	that	 axis.	 	 A	flashing	 yellow	mode	annunciation	 and	
annunciator	light	indicate	 loss	of	sensor	 (ADC)	 or	navigation	 data	(VOR,	 LOC,	GPS,	VNV,	 SBAS)	 required	 to	
compute	 commands.		 When	such	a	loss	 occurs,	 the	system	 automatically	 begins	to	roll	 the	wings	 level	(enters	
Roll	Hold	 Mode)	 or	maintain	 the	pitch	 angle	 (enters	 Pitch	Hold	Mode),	 depending	 on	the	 affected	 axis.		The	
flashing	 annunciation	 stops	when	 the	affected	 mode	key	is	pressed	 or	another	 mode	for	the	 axis	 is	selected.		 If	
after 10 seconds no action is taken, the flashing annunciation stops.
Figure 7-3  Loss of VOR Signal
The flight director is automatically disabled if the attitude information required to compute the default flight 
director modes becomes invalid or unavailable.
SWITCHING FLIGHT DIRECTORS
The	GFC	 700	in	the	 Socata	 TBM	850	has	two	 flight	 directors,	 each	operating	 within	an	IAU.		 The	autopilot	
follows the selected flight director only, indicated by an arrow pointing toward either the pilot or copilot side, in 
the	center	 of	the	 AFCS	 Status	 Box.		Flight	 directors	 may	be	switched	 by	pressing	 the	XFR Key.  The annunciator 
light arrow for the selected flight director is also illuminated beside the XFR	Key.		 When	 the	flight	 directors	 are	
switched, the vertical and lateral modes revert to default.
Figure 7-4  Flight Director Selection Indications
Pilot-side Flight Director
Copilot-side Flight Director  
						

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 850475
AUTOMATIC FLIGHT CONTROL SYSTEM
COMMAND BARS
Upon	activation	 of	the	 flight	 director,	 Command	 Bars	are	displayed	 in	magenta	 on	the	 PFDs	 as	a	single-cue.		
The Command Bars do not override the (yellow) Aircraft Symbol.  The single-cue Command Bars (Figure 7-5) 
move together vertically to indicate pitch commands and bank left or rig\
ht to indicate roll commands.
Figure 7-5  Single-cue Command Bars
Aircraft Symbol
Command Bars
If	 the	 attitude	 information	 being	sent	to	the	 flight	 director	 becomes	 invalid	or	unavailable,	 the	Command	 Bars	
are	removed	 from	the	display.		 The	flight	 director	 Command	 Bars	also	disappear	 if	the	 pitch	 exceeds	 +30˚/-20˚	
or	bank	exceeds	65˚.  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A476
AUTOMATIC FLIGHT CONTROL SYSTEM
7.3 VERTICAL MODES
Table	7-2	lists	 the	vertical	 modes	with	their	 corresponding	 controls	and	annunciations.		 The	mode	 reference	 is	
displayed	 next	to	the	 active	 mode	annunciation	 for	Altitude	 Hold,	Vertical	 Speed,	and	Flight	 Level	Change	 modes.		
The NOSE UP/DN	Wheel	 can	be	used	 to	change	 the	vertical	 mode	reference	 while	operating	 under	Pitch	Hold,	
Vertical	 Speed,	or	Flight	 Level	Change	 Mode.		Increments	 of	change	 and	acceptable	 ranges	of	values	 for	each	 of	
these references using the NOSE UP/DN	Wheel	are	also	listed	in	the	table.
Vertical ModeDescriptionControlAnnunciation Reference 
Range
Reference 
Change 
Increment
Pitch Hold
Holds the current aircraft pitch 
attitude; may be used to climb/
descend to the Selected Altitude
(default)PIT-15° to
+25°0.5°
Selected Altitude  CaptureCaptures the Selected Altitude*ALTS
Altitude HoldHolds the current Altitude ReferenceA LT KeyA LTnnnnn fT
Vertical Speed
Maintains the current aircraft vertical 
speed; may be used to climb/descend 
to the Selected Altitude
VS KeyVSnnnn fpm-4000 to
+3000 fpm100 fpm
Flight Level Change, IAS HoldMaintains the current aircraft 
airspeed (in IAS or Mach) while the 
aircraft is climbing/descending to the 
Selected Altitude
FLC Key
FLCnnn kT80 to
265 kts1 kt
Flight Level Change, Mach HoldFLCM .nnnM 0.20 to
0.69M 0.01
Vertical  Path TrackingCaptures and tracks descent legs of 
an active vertical profile
VNV 
KeyVPTH
VNV Target Altitude  CaptureCaptures the Vertical Navigation 
(VNV) Target Altitude**ALTV
GlidepathCaptures and tracks the WAAS 
glidepath on approachAPR 
Key
GP
GlideslopeCaptures and tracks the ILS glideslope 
on approachGS
Takeoff
Commands a constant pitch angle 
and wings level on the ground in 
preparation for takeoffGA 
Switch
TO7.5°
Go Around
Disengages the autopilot and 
commands a constant pitch angle 
and wings level in the air
GA7.5°
*   ALTS armed automatically when PIT, VS, FLC, TO, or GA active, and under VPTH when Selected Altitude is to\
 be captured instead of VNV Target Altitude
** ALTV armed automatically under VPTH when VNV Target Altitude is to be captured instead of Selected Altitude
Table 7-2  Flight Director Vertical Modes