Garmin GFC 500 User manual

AFMS –GFC 500 Autopilot in Textron 182 Series 190-02291-06 Rev. 2
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190-02291-06 Rev. 2 AFMS –GFC 500 Autopilot in Textron 182 Series
Page i
Garmin International, Inc
Log of Revisions
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GFC 500 Autopilot with ESP
Installed in
Textron Aviation 182E / 182F / 182G / 182H / 182J / 182K / 182L / 182M /
182N / 182P / 182Q / 182R / 182S / 182T / T182 / T182T
And
Cessna F182P / F182Q
REV
NO.
PAGE NO(S)
DESCRIPTION
DATE OF
APPROVAL
FAA APPROVED
1
ALL
Original Issue
12/21/2017
Robert G. Murray
Garmin ODA STC
Unit Administrator
2
ALL
Added VNAV
See Cover
See Cover

AFMS –GFC 500 Autopilot in Textron 182 Series 190-02291-06 Rev. 2
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190-02291-06 Rev. 2 AFMS –GFC 500 Autopilot in Textron 182 Series
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Table of Contents
Section 1 –General....................................................................................................1-1
USE OF THE SUPPLEMENT ................................................................................................................1-1
ABBREVIATIONS AND TERMINOLOGY.............................................................................................1-2
INSTALLED EQUIPMENT INTERFACES.............................................................................................1-3
INSTALLED FEATURES CHECKLIST.................................................................................................1-4
Section 2 –Limitations..............................................................................................2-1
Section 3 –Emergency Procedures .........................................................................3-1
AUTOPILOT MALFUNCTION / PITCH TRIM RUNAWAY....................................................................3-1
AUTOPILOT FAILURE / ABNORMAL DISCONNECT.........................................................................3-2
PITCH TRIM FAILURE ..........................................................................................................................3-2
ESP ACTIVATION .................................................................................................................................3-2
OVERSPEED PROTECTION (MAXSPD)..............................................................................................3-3
UNDERSPEED PROTECTION (MINSPD) ............................................................................................3-3
Section 3A –Non-Normal Procedures......................................................................3-5
AUTOPILOT ABNORMAL DISCONNECT............................................................................................3-5
AUTOPILOT PRE-FLIGHT TEST FAIL.................................................................................................3-5
LOSS OF NAVIGATION INFORMATION..............................................................................................3-5
LOSS OF AIRSPEED DATA .................................................................................................................3-6
LOSS OF ALTITUDE DATA..................................................................................................................3-6
LOSS OF GPS INFORMATION.............................................................................................................3-6
HEADING DATA SOURCE FAILURE...................................................................................................3-7
ELEVATOR MISTRIM (AUTOTRIM).....................................................................................................3-7
Section 4 –Normal Procedures ................................................................................4-1
GFC 500 POWER UP ............................................................................................................................4-1
FLIGHT DIRECTOR / AUTOPILOT NORMAL OPERATING PROCEDURES.....................................4-1
MANUAL AUTOPILOT DISCONNECT.................................................................................................4-1
VERTICAL MODES ...............................................................................................................................4-2
VERTICAL SPEED (VS) MODE.........................................................................................................4-2
INDICATED AIRSPEED (IAS) MODE................................................................................................4-2
ALTITUDE HOLD (ALT) MODE, MANUAL CAPTURE......................................................................4-2
VERTICAL NAVIGATION (VNAV)......................................................................................................4-3
GO AROUND......................................................................................................................................4-4
MANUAL PITCH TRIM WITH AUTOPILOT ENGAGED ....................................................................4-4
LATERAL MODES.................................................................................................................................4-5
HEADING MODE (HDG)....................................................................................................................4-5

AFMS –GFC 500 Autopilot in Textron 182 Series 190-02291-06 Rev. 2
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TRACK MODE (TRK) .........................................................................................................................4-5
NAVIGATION (VOR)...........................................................................................................................4-5
NAVIGATION (GPS)...........................................................................................................................4-6
APPROACHES ......................................................................................................................................4-7
ILS APPROACH .................................................................................................................................4-7
LOC APPROACH (GS out).................................................................................................................4-8
GPS APPROACH (LPV, LNAV/VNAV, LP+V, or LNAV+V) ...............................................................4-9
GPS APPROACH (LP, LNAV)............................................................................................................4-9
LOC BC APPROACH .......................................................................................................................4-10
VOR APPROACH.............................................................................................................................4-11
DISABLING ESP..................................................................................................................................4-12
Section 5 –Performance........................................................................................... 5-1
Section 6 –Weight and Balance............................................................................... 6-1
Section 7 –System Description................................................................................ 7-1
AFCS OVERVIEW .................................................................................................................................7-1
AUTOPILOT CONTROL UNIT AND DISPLAY.....................................................................................7-4
PREFLIGHT TEST.................................................................................................................................7-7
MESSAGES AND ANNUNCIATIONS...................................................................................................7-7
LIGHTING...............................................................................................................................................7-8

190-02291-06 Rev. 2 AFMS –GFC 500 Autopilot in Textron 182 Series
Page 1–1
SECTION 1 – GENERAL
The information in this supplement is FAA-approved material and must be attached to the Pilot’s Operating
Handbook and FAA Approved Airplane Flight Manual (POH/AFM) when the airplane has been modified by
installation of the Garmin GFC 500 Autopilot system in accordance with Garmin International, Inc. approved data.
The information in this supplement supersedes or adds to the basic POH/AFM only as set forth below. Users of
the manual are advised to always refer to the supplement for possibly superseding information and placarding
applicable to operation of the airplane.
USE OF THE SUPPLEMENT
The following definitions apply to WARNINGS, CAUTIONS and NOTES found throughout the supplement:
Operating procedures, techniques, etc., which may result in personal injury or loss of life if not
carefully followed.
CAUTION
Operating procedures, techniques, etc., which may result in damage to equipment if not
carefully followed.
NOTE
Operating procedures, techniques, etc., which is considered essential to emphasize.
WARNING

AFMS –GFC 500 Autopilot in Textron 182 Series 190-02291-06 Rev. 2
Page 1–2
ABBREVIATIONS AND TERMINOLOGY
The following glossary is applicable within the airplane flight manual supplement
AFCS Automatic Flight Control System
AFM Airplane Flight Manual
AFMS Airplane Flight Manual Supplement
AGL Above Ground Level
AHRS Attitude and Heading Reference
System
ALT Altitude
AP Autopilot
APR Approach
ATC Air Traffic Control
BC Back Course Approach
CDI Course Deviation Indicator
DA Decision Altitude
DISC Disconnect
DWG Drawing
ESP Electronic Stability and Protection
FAA Federal Aviation Administration
FAF Final Approach Fix
FD Flight Director
GA Go Around
GFC 500 Garmin Autopilot
GMC 507 Autopilot Mode Control Panel
GNSS Global Navigation Satellite System
GPS Global Positioning System
GS Glideslope
GSA Garmin Servo Actuator
HDG AFCS heading mode
IAS Indicated Airspeed
ILS Instrument Landing System
INT Interrupt
KIAS Knots Indicated Airspeed
LNAV Lateral Navigation
LNAV+V Lateral Navigation with Advisory
Vertical Guidance
LNAV/VNAV Lateral Navigation / Vertical
Navigation Approach
LOC Localizer (no glideslope available)
LP Localizer Performance
LP+V Localizer Performance with Advisory
Vertical Guidance
LPV Localizer Performance with Vertical
Guidance
LVL Level
MDA Minimum Descent Altitude
PFT Preflight Test
POH Pilot’s Operating Handbook
STC Supplemental Type Certificate
TO Takeoff
TRK Track
VHF Very High Frequency
VOR VHF Omni-directional Range
VS Vertical Speed

190-02291-06 Rev. 2 AFMS –GFC 500 Autopilot in Textron 182 Series
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INSTALLED EQUIPMENT INTERFACES
The following is the list of installed equipment and functions associated with the GFC 500 Autopilot installation in
this airplane.
Table 1-1: Table of Installed Equipment Interfaces
DEVICE TYPE
Manufacturer / Model
If not installed, note N/A
Additional Information
GPS Navigator #1
Is Navigator #1 interfaced to GFC 500?
YES NO
VHF Nav Radio #1
Is VHF Nav Radio #1 interfaced to GFC 500?
YES NO
VHF Nav Radio #2
Pitch Trim Servo

AFMS –GFC 500 Autopilot in Textron 182 Series 190-02291-06 Rev. 2
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INSTALLED FEATURES CHECKLIST
The checked autopilot modes and features are available on this aircraft.
Basic AP Features
Flight Director
Electric Pitch Trim
Overspeed Protection
Underspeed Protection
Vertical Autopilot Modes
Pitch (PIT)
Level (Zero vertical speed)
Go Around (GA)
Altitude Hold
Vertical Speed
Altitude Capture via Altitude Preselect
Indicated Airspeed (IAS)
Vertical Navigation (VNAV)
GPS Approach Glidepath
ILS Glideslope
Electronic Stability and Protection
Pitch/Roll Attitude
High Speed Protection
Low Speed Protection
Lateral Autopilot Modes
Roll (ROL)
Level (Wings Level)
Go Around (GA)
Heading
Track
GPS Navigation
VHF Navigation
Approach Mode
GPS
VOR/LOC

190-02291-06 Rev. 2 AFMS –GFC 500 Autopilot in Textron 182 Series
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SECTION 2 – LIMITATIONS
The Garmin G5 Electronic Flight Instrument Pilot’s Guide for Certified Aircraft, part number 190-01112-12 Rev A
(or later approved revisions), must be immediately available to the flight crew.
This AFMS is applicable to the software versions shown below:
Software Item
Software Version
(or later FAA Approved version for this STC)
G5 Software Version
5.50
A pilot must be seated in the left pilot’s seat, with seatbelt fastened, during all autopilot operations.
Do not use autopilot during takeoff and landing.
The GFC 500 AFCS preflight test must complete successfully prior to use of the autopilot, flight director or manual
electric trim.
The maximum fuel imbalance with the autopilot engaged is 10 gallons.
Autopilot maximum engagement speed is 165 KIAS.
The autopilot must be disengaged below 200 feet AGL during approach operations and below 800 feet AGL
during all other operations.
The GFC 500 autopilot is approved for Category 1 precision approaches and non-precision approaches only.

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SECTION 3 – EMERGENCY PROCEDURES
Some emergency situations require immediate memorized corrective action. These steps are printed in bold in the
emergency procedures and should be accomplished without the aid of the checklist.
AUTOPILOT MALFUNCTION / PITCH TRIM RUNAWAY
If the airplane deviates unexpectedly from the planned flight path:
1. Control Wheel............................................................................................................GRIP FIRMLY
2. AP DISC / TRIM INT Button .............................................................................PRESS AND HOLD
CAUTION
Be prepared for high elevator control forces.
3. Aircraft Attitude.......................................................MAINTAIN / REGAIN AIRCRAFT CONTROL
4. Elevator Trim........................................................ RE-TRIM if necessary using Elevator Tab Wheel
5. AUTOPILOT Circuit Breaker.....................................................................................................PULL
NOTE
Do not release the AP DISC / TRIM INT Button until after pulling the AUTOPILOT Circuit Breaker.
Pulling the AUTOPILOT circuit breaker will render the autopilot and ESP inoperative.
6. AP DISC / TRIM INT Button.............................................................................................. RELEASE
In flight, do not overpower the autopilot. The trim will operate in the direction opposing the
overpower force, which will result in large out-of-trim forces.
Do not attempt to re-engage the autopilot or use manual electric pitch trim until the cause of the
malfunction has been corrected.
WARNING

AFMS –GFC 500 Autopilot in Textron 182 Series 190-02291-06 Rev. 2
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AUTOPILOT FAILURE / ABNORMAL DISCONNECT
(Red AP in autopilot status box on display, continuous aural disconnect tone.)
1. AP DISC / TRIM INT Button or G5 Knob.................................................... PRESS AND RELEASE
(to cancel disconnect tone)
2. Aircraft Attitude...........................................................MAINTAIN / REGAIN AIRCRAFT CONTROL
NOTE
The autopilot disconnect may be accompanied by a red AFCS in the autopilot status box,
indicating the automatic flight control system has failed. The flight director will not be available
and the autopilot cannot be re-engaged with this annunciation present.
If the disconnect is accompanied by an amber AP with a red X, the autopilot will not be available
however the flight director will still be functional.
In the event of a GMC failure, pressing the G5 knob will acknowledge the disconnect tone.
PITCH TRIM FAILURE
(Red PTRIM on G5 display.)
This failure will only occur if the optional pitch trim servo is installed.
1. Indicates a failure of the pitch trim servo.
2. Control Wheel .............................................................................................................GRIP FIRMLY
3. AP DISC / TRIM INT Button..........................................................................PRESS and RELEASE
(Be prepared for high elevator control forces)
4. Elevator Trim...................................................... AS REQUIRED USING ELEVATOR TAB WHEEL
NOTE
The autopilot may be re-engaged. Refer to the normal procedures section of this AFMS,
MANUAL PITCH TRIM WITH AUTOPILOT ENGAGED.
ESP ACTIVATION
1. Throttle.....................................................................................................................AS REQUIRED
2. Aircraft Attitude.......................................................MAINTAIN / REGAIN AIRCRAFT CONTROL
NOTE
If ESP is active for approximately 10 seconds, the autopilot will automatically engage in LVL
mode, an aural ‘ENGAGING AUTOPILOT’ will be played, (or a Sonalert tone will sound for
installations without a supported audio panel) and the autopilot will roll the wings level and fly at
zero-vertical speed. Refer to Section 7, System Description for further information.
ESP will be disabled by pressing and holding the AP DISC / TRIM INT button. Releasing the
button will allow ESP to function.

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OVERSPEED PROTECTION (MAXSPD)
(MAXSPD displayed on G5, AIRSPEED –AIRSPEED Aural sounds.)
1. Throttle...............................................................................................................................REDUCE
2. Aircraft Attitude and Altitude.........................................................................................MONITOR
After overspeed condition is corrected:
3. Autopilot .......................................RESELECT VERTICAL AND LATERAL MODES (if necessary)
4. Throttle...........................................................................................................ADJUST as necessary
NOTE
Overspeed protection mode provides a pitch up command to decelerate the airplane at or below
the maximum autopilot operating speed.
UNDERSPEED PROTECTION (MINSPD)
(MINSPD displayed on G5, AIRSPEED –AIRSPEED Aural sounds.)
1. Throttle............................... INCREASE POWER AS REQUIRED TO CORRECT UNDERSPEED
2. Aircraft Attitude and Altitude.........................................................................................MONITOR
After underspeed condition is corrected:
3. Autopilot.........................................RESELECT VERTICAL AND LATERAL MODES (if necessary)
4. Throttle...........................................................................................................ADJUST as necessary
NOTE
Autopilot Underspeed Protection Mode provides a pitch down command to maintain 65 KIAS.

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SECTION 3A – NON-NORMAL PROCEDURES
AUTOPILOT ABNORMAL DISCONNECT
(Red AP in the G5 autopilot status box, continuous aural disconnect tone.)
1. AP DISC / TRIM INT Button.........................................................................PRESS AND RELEASE
(to cancel disconnect tone)
2. Aircraft Attitude...........................................................MAINTAIN / REGAIN AIRCRAFT CONTROL
NOTE
The autopilot disconnect may be accompanied by a red AFCS in the autopilot status box,
indicating the automatic flight control system has failed. The flight director will not be available
and the autopilot cannot be re-engaged with this annunciation present.
If the disconnect is accompanied by an amber AP with a red X, the autopilot will not be available
however the flight director will still be functional.
AUTOPILOT PRE-FLIGHT TEST FAIL
(Amber AP with a red X in G5 autopilot status box.)
1. Indicates the AFCS system failed the automatic Pre-Flight test.
NOTE
The autopilot, ESP, and electric elevator trim are inoperative. Flight director will still function.
LOSS OF NAVIGATION INFORMATION
(Amber GPS, VOR, LOC, or BC flashes for 10 seconds on G5.)
NOTE
If a navigation signal is lost while the autopilot is tracking it, the autopilot will roll the aircraft
wings level and default to roll mode (ROL).
1. GMC 507 Mode Panel.............................................SELECT HDG mode and SET desired heading
2. NAV Source ......................................................................................... SELECT a valid NAV source
3. NAV Key.................................................................................................................................PRESS
If on an instrument approach at the time the navigation signal is lost:
4. Missed Approach Procedure.................................................................... EXECUTE (as applicable)

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LOSS OF AIRSPEED DATA
(Red X through airspeed tape on the G5 display, amber AP with a red X in autopilot status box.)
NOTE
If airspeed data is lost while the autopilot is tracking airspeed, the flight director will default to
pitch mode (PIT).
1. AP DISC / TRIM INT Button........................................................................ PRESS AND RELEASE
(to cancel disconnect tone)
2. Aircraft Attitude...........................................................MAINTAIN / REGAIN AIRCRAFT CONTROL
3. Manual Elevator Trim.............................................................................................TRIM as required
NOTE
The autopilot cannot be re-engaged. The flight director is available however IAS mode cannot
be selected. Loss of airspeed will be accompanied by a red PTRIM indication on the G5 (if a
pitch trim servo is installed).
LOSS OF ALTITUDE DATA
(Red X through altitude tape on the G5 display.)
NOTE
If altitude data is lost while the autopilot is tracking altitude, the autopilot will default to pitch mode
(PIT).
1. Autopilot .......................................................................................... SELECT different vertical mode
LOSS OF GPS INFORMATION
(GPS position information is lost to the autopilot.)
NOTE
If GPS position data is lost while the autopilot is tracking a GPS, VOR, LOC or BC course, the
autopilot will default to roll mode (ROL). The autopilot will default to pitch mode if GPS
information is lost while tracking an ILS. The autopilot uses GPS aiding in VOR, LOC and BC
modes.
1. Autopilot ................................................SELECT different lateral and vertical mode (as necessary)
If on an instrument approach:
•AP DISC / TRIM INT button ...................................PRESS, Continue the approach manually
Or
•Missed Approach Procedure.......................................................... EXECUTE (as applicable)

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HEADING DATA SOURCE FAILURE
1. Autopilot............................................................................................SELECT different lateral mode
NOTE
Track information will be displayed on the G5.
Without a heading source to the navigator, GPSS will not be provided to the autopilot for
heading legs. Navigator map cannot be oriented heading up.
ELEVATOR MISTRIM (AUTOTRIM)
(Amber TRIM UP or TRIM DOWN displayed on the G5.)
Do not attempt to overpower the autopilot in the event of a pitch mistrim. The autopilot servo
will oppose pilot input and will cause pitch trim to run opposite the direction of pilot input. This
will lead to a significant out-of-trim condition, resulting in large control wheel force when
disengaging the autopilot.
NOTE
Indicates a mistrim of the elevator while the autopilot is engaged.
If a pitch trim servo is not installed, refer to the normal procedures section of this AFMS, MANUAL
PITCH TRIM WITH AUTOPILOT ENGAGED. If a pitch trim servo is installed, the autopilot will
normally trim the airplane as required. However, during rapid acceleration, deceleration,
configuration changes, or near either end of the elevator trim limits, momentary illumination of
this message may occur. If the autopilot is disconnected while this message is displayed, high
elevator control forces are possible.
If a pitch trim servo is not installed:
1. Refer to the normal procedures section of this AFMS, MANUAL PITCH TRIM WITH AUTOPILOT
ENGAGED.
If a pitch trim servo is installed:
NOTE
Momentary display of the TRIM UP or TRIM DOWN message during configuration changes or
large airspeed changes is normal.
1. Control Wheel .............................................................................................................GRIP FIRMLY
Be prepared for significant sustained control forces in the direction of the mistrim annunciation.
For example, TRIM DOWN indicates nose down control wheel force will be required upon
autopilot disconnect.
2. AP DISC / TRIM INT Button.........................................................................PRESS AND RELEASE
WARNING
WARNING

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3. Manual Elevator Trim.......................................................................................RE-TRIM as required
Electric pitch trim should be considered inoperative until the cause of the mistrim has been investigated and
corrected.