Garmin Cessna Caravan G1000 Technical specifications

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
ISSUED 11 - 2004 1of33
REVISION A 06--2005 FAA APPROVEDREVISION B 03--2006
MOONEY AIRPLANE COMPANY, INC.
LOUIS SCHREINER FIELD KERRVILLE, TEXAS 78028
FAA APPROVED
AIRPLANE FLIGHT MANUAL SUPPLEMENT
FOR
GARMIN G1000
INTEGRATED AVIONICS SYSTEM
INSTALLED IN MOONEY M20R
REG. NO. _____________________________________________
SERIAL NO. ____________________________________________
This Supplement must be attached to the FAA Approved Airplane Flight
Manual when the GARMIN G1000 Integrated Avionics System is
installed in accordance with Mooney Drawing Number 950300. The in-
formation contained herein supplements and / or replaces the informa-
tion of the basic Airplane Flight Manual. For Limitations, Procedures
and Performance information not contained in this Supplement, consult
the basic Airplane Flight Manual.
FAA APPROVED
Michele M. Owsley
Manager, Aircraft Certification Office
FEDERAL AVIATION ADMINISTRATION
2601 Meacham Boulevard
Fort Worth, Texas 76137-0150
CopyrightE2006 All Rights Reserved Mooney Airplane Company -- Louis Schreiner Field Kerrville, Texas 78028
SUPP0001B

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
2of33 ISSUED 11 - 2004
REVISION A 06--2005
FAA APPROVED REVISION B 03--2006
LOG OF REVISIONS
REV.
NUMBER
PAGE
NUMBER(S)
DESCRIPTION FAA
APPROVED
APR’VD
DATE
A7, 17, 29,
30
Add following components
from Garmin G1000 Cockpit
Reference Guide:
GDL 69A
DME
ADF
B17, 30 Add SKYWATCHt
Capability
THE REVISED PORTIONS OF AFFECTED PAGES ARE INDICATED BY VERTICAL
LINES IN THE MARGIN.

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
ISSUED 11 - 2004 3of33
REVISION A 06--2005 FAA APPROVEDREVISION B 03--2006
TABLE OF CONTENTS
SECTION PAGE
I GENERAL 5...........................................
II LIMITATIONS 7........................................
III EMERGENCY PROCEDURES 15.........................
IV NORMAL PROCEDURES 21.............................
V PERFORMANCE 27.....................................
VI WEIGHT AND BALANCE 27..............................
VII AIRPLANE AND SYSTEM DESCRIPTIONS 27..............
VIII HANDLING AND SERVICING 33..........................
IX SUPPLEMENTAL DATA 33...............................
X SAFETY TIPS 33........................................

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
4of33 ISSUED 11 - 2004
REVISION A 06--2005
FAA APPROVED REVISION B 03--2006
INTENTIONALLY LEFT BLANK

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
ISSUED 11 - 2004 5of33
REVISION A 06--2005 FAA APPROVEDREVISION B 03--2006
SECTION I -- GENERAL
1. The GARMIN G1000 Integrated Avionics System is a fully integrated
flight, engine, communication, navigation and surveillance instru-
mentation system. The system consists of a Primary Flight Display
(PFD), Multi--Function Display (MFD), audio panel (GMA), Air Data
Computer (ADC), Attitude and Heading Reference System (AHRS),
engine / airframe processing unit (GEA), and integrated avionics
(GIA) containing VHF communications, VHS navigation, and GPS
navigation.
2. The primary function of the PFD is to provide attitude, heading, air
data, navigation, and alerting information to the pilot. The PFD may
also be used for flight planning. The primary function of the MFD is to
provide engine information, mapping terrain information and for
flight planning. The audio panel is used for selection of radios for
transmitting and listening, intercom functions, and marker beacon
functions.
3. The primary function of the VHF Communication portion of the
G1000 is to enable external radio communication. The primary func-
tion of the VOR/ILS Receiver portion of the equipment is to receive
and demodulate VOR, localizer, and Glide Slope signals. The prima-
ry function of the GPS portion of the system is to acquire signals from
the GPS satellites, recover orbital data, make range and Doppler
measurements, and process this information in real time to obtain
the user’s position, velocity, and time.
4. Provided the GARMIN G1000 GPS receivers are receiving ade-
quate and usable GPS and/or VHF navigation signals, it has been
demonstrated capable of and meets the accuracy specifications for
the following types of flight operations:
VFR/IFR en--route, oceanic, and terminal operations as well as non-
precision instrument approach (GPS, Loran--C, VOR, VOR--DME,
TACAN, NDB, NDB--DME, RNAV) operation within the U.S. National
Airspace System in accordance with AC20--138A.
Navigation in the North Atlantic Minimum Navigation Performance
Specification (MNPS) Airspace in accordance with AC91--49 and AC
120--33.
The GARMIN G1000 system meets RNP5 airspace (BRNAV) re-
quirements of AC 90--96 and in accordance with AC 20--138A, JAA
AMJ 20X2 Leaflet 2 Revision 1, and FAA Order 8110.60 for oceanic
and remote

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
6of33 ISSUED 11 - 2004
REVISION A 06--2005
FAA APPROVED REVISION B 03--2006
airspace operations, provided it is receiving usable navigation infor-
mation from the GPS receiver. (A separate software application for
prediction of GPS navigation availability may be required for oceanic
and remote operations. Refer to appropriate limitations for the air-
space you are operating in to determine if this GPS prediction soft-
ware is required.)
Navigation is accomplished using the WGS--84 (NAD--83) coordinate
reference datum. GPS navigation data is based upon use of only the
Global Positioning System (GPS) operated by the United States of
America.

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
ISSUED 11 - 2004 7of33
REVISION A 06--2005 FAA APPROVEDREVISION B 03--2006
SECTION II -- LIMITATIONS
GENERAL
G1000 System:
1. The GARMIN G1000 Cockpit Reference Guide for the M20R Series
aircraft, P/N 190--00450--01, Revision A or later approved revision
must be immediately available to the flight crew.
2. The GARMIN G1000 must utilize the following or later FAA approved
software versions:
SUB--SYSTEM SOFTWARE VERSION
PFD 4.06
MFD 4.06
GMA 2.08
AHRS 2.03
ADC 2.05
GIA 2.08
GEA 2.04
GPS 3.01
The database version is displayed on the MFD power--up page immedi-
ately after system power--up and must be acknowledged. The remain-
ing system software versions can be verified on the AUX group sub--
page 5, “AUX – SYSTEM STATUS”.
3. IFR enroute, oceanic and terminal navigation predicated upon the
G1000 GPS Receiver is prohibited unless the pilot verifies the cur-
rency of the database or verifies each selected waypoint for accura-
cy by reference to current approved data.

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
8of33 ISSUED 11 - 2004
REVISION A 06--2005
FAA APPROVED REVISION B 03--2006
4. Instrument approach navigation predicated upon the G1000 GPS
Receiver must be accomplished in accordance with approved in-
strument approach procedures that are retrieved from the GPS
equipment database. The GPS equipment database must incorpo-
rate the current update cycle.
(a) Instrument approaches utilizing the GPS receiver must be
conducted in the approach mode and Receiver Autonomous
Integrity Monitoring (RAIM) must be available at the Final Ap-
proach Fix.
(b) Accomplishment of ILS, LOC, LOC--BC, LDA, SDF, MLS or
any other type of approach not approved for GPS overlay with
the G1000 GPS receiver is not authorized.
(c) Use of the G1000 VOR/ILS receiver to fly approaches not ap-
proved for GPS require VOR/ILS navigation data to be valid
on the PFD display.
(d) When an alternate airport is required by the applicable operat-
ing rules, it must be served by an approach based on other
than GPS navigation, the aircraft must have the operational
equipment capable of using that navigation aid, and the re-
quired navigation aid must be operational.
(e) VNAV information may be utilized for advisory information
only. Use of VNAV information for Instrument Approach Pro-
cedures does not guarantee step--down fix altitude protec-
tion, or arrival at approach minimums in a normal position to
land. VNAV also does not guarantee compliance with inter-
mediate altitude constraints between the top of descent and
the waypoint where the VNAV path terminates in terminal or
enroute operations.
5. If not previously defined, the following default settings must be made
in the “SYSTEM SETUP” menu of the G1000 prior to operation (refer
to Pilot’s Guide for procedure, if necessary.
(a) DIS, SPD…..nmkt(sets navigation units to “nautical miles”
and “knots”)
(b) ALT, VS……..ftfpm (sets altitude units to “feet” and “feet per
minute”)

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
ISSUED 11 - 2004 9of33
REVISION A 06--2005 FAA APPROVEDREVISION B 03--2006
(c) MAP DATUM….WGS 84 (sets map datum to WGS--84, [see
note below])
(d) POSITION……..deg--min (sets navigation grid units to deci-
mal minutes)
example: dd.mm.ss: 45_30’ 30” in decimal minutes are: 45_
30.5’
NOTE:
In some areas outside the United States, datums other than
WGS--84 or NAD--83 may be used. If the G1000 is authorized
for use by the appropriate Airworthiness authority, the re-
quired geodetic datum must be set in the G1000 prior to its
use for navigation.
6. Operation is prohibited north of 70oN and south of 70oS latitudes. In
addition, operation is prohibited in the following two regions: 1) north
of 65o N between 75oW and 120oW longitude and 2) south of 55oS
between 120oE and 165oE longitude.
7. CAUTION: CDI automatic source switching to the ILS on Nav 1 or 2
must be set to manual for instrument approaches conducted with the
autopilot coupled. If the CDI navigation source is changed when au-
topilot is engaged in GPSS mode, the S--Tec 55x autopilot lateral
mode will revert to wings level mode and indicate GPSS FAIL. NAV
mode must be manually reselected by the pilot in order to track the
ILS or Localizer.
8. Display of autopilot operational mode on the PFD is supplemental to
the data which is presented on the display of the S--Tec 55X autopilot
control unit.
2.1 AIRSPEED MARKINGS – M20R
Marking IAS Significance
Red band 20 KIAS – 59 KIAS Low speed awareness -- stall is
imminent
White band 59 KIAS – 110 KIAS Operating range with flaps fully ex-
tended
Green band 66 KIAS – 174 KIAS Normal operating range
Yellow band 174 KIAS -- 195 KIAS Caution range -- smooth air only
Red band 195 KIAS and greater Lower limit of 195 KIAS is the maxi-
mum speed for all operations
The airspeed indicator is marked in IAS values.

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
10 of 33 ISSUED 11 - 2004
REVISION A 06--2005
FAA APPROVED REVISION B 03--2006
2.2 POWER PLANT INSTRUMENT MARKINGS
Power plant instrument markings and their color code significance are
shown in the table below.
NOTE:
When an indication lies in the caution range, the legend for
that display will change to the color of the caution range.
When an indication lies in the upper or lower prohibited
range, the legend for that display will change to the color of
the prohibited range and will begin flashing as well.
MOONEY M20R
Indication Red
arc / bar
=
Lower
prohibited
range
Yellow
arc / bar
=
Caution
range
Green
arc / bar
=
Normal
operating
range
Yellow
arc / bar
=
Caution
range
Red
arc / bar
=
Upper
prohibited
range
Engine RPM -- -- -- -- 2200 – 2500 -- -- 2500 – 2600*
Manifold
Press. In. Hg
-- -- -- -- 10 – 35** -- -- -- --
Oil Temp oF-- -- -- -- 75 – 240 -- -- >240
Oil Press PSI 0–10 10–30 30 – 100 -- -- >100
Cyl. Head
Temp oF
-- -- -- -- 250 – 460 -- -- >460
Fuel Flow
gal/hr
-- -- -- -- 0--30 -- -- -- --
* To prevent nuisance alerts during normal takeoffs: the “RPM” and
“MAP” data will not turn red or flash until the RPM exceeds 2540.
** No color scale is depicted, and manifold pressure should be within
this range.

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
ISSUED 11 - 2004 11 of 33
REVISION A 06--2005 FAA APPROVEDREVISION B 03--2006
2.3 -- TYPES OF OPERATION
The airplane is approved for the following operations when equipped in
accordance with FAR 91 or FAR 135.
(a) Day V.F.R.
(b) Night V.F.R
(c) Day I.F.R.
(d) Night I.F.R.
(e) Non Icing
Minimum Operational Equipment for flight operations listed:
Equipment Number
installed
VFR
Day
VFR
Night
IFR
Primary Flight Display 1 * 1 1
Multi--Function Display 1-- 1 1
Audio panel 1-- -- 1
Air data computer 1 1 1 1
Attitude and Heading Reference System 1-- 1 1
GPS 2-- 1 2
* If the PFD is inoperative or removed for service, the MFD may be
used as the PFD. The MFD display must be operated in PFD (reversion-
ary) mode by depressing the reversionary button on the Audio Panel.
When operating in reversionary mode the system is limited to DAY VFR
operations only.
2.4 -- ADVISORY MESSAGES
The G1000 Cockpit Reference Guide and the G1000 Pilot’s Guide con-
tain detailed descriptions of the annunciator system and all advisory
messages. These messages appear on the PFD for flight crew aware-
ness.
The following warnings and cautions may appear in various locations
on the PFD or MFD. Consult the G1000 Cockpit Reference Guide and
the G1000 Pilot’s Guide for detailed descriptions of each annunciation
as necessary.

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
12 of 33 ISSUED 11 - 2004
REVISION A 06--2005
FAA APPROVED REVISION B 03--2006
Annunciation Cause
AHRS Aligning – Keep
Wings Level
Attitude and Heading Reference System is
aligning. Keep wings level using standby
attitude indicator.
ATTITUDE FAIL Display system is not receiving attitude
reference information from the AHRS; ac-
companied by the removal of sky/ground
presentation and a red X over the attitude
area.
AIRSPEED FAIL Display system is not receiving airspeed
input from the air data computer; accom-
panied by a red X through the airspeed dis-
play
ALTITUDE FAIL Display system is not receiving airspeed
input from the air data computer; accom-
panied by a red X through the altimeter dis-
play
VERT SPEED FAIL Display system is not receiving vertical
speed input from the air data computer;
accompanied by a red X through the verti-
cal speed display
HDG Display system is not receiving valid head-
ing input from the AHRS; accompanied by
a red X through the digital heading display
Red X A red X through any display field, such as
com frequencies, nav frequencies, or en-
gine data, indicates that display field is not
receiving valid data.

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
ISSUED 11 - 2004 13 of 33
REVISION A 06--2005 FAA APPROVEDREVISION B 03--2006
DECALS AND PLACARDS
M20R FLIGHT PANEL - PLACARD LOCATIONS
1 150056-1001 SPEEDBRAKE EQUIPPED FOR OPERATING...
2 150056-1004 N NUMBER
3 150056-1012 14V RECEPTACLE
4 800399-007 PANEL LIGHTS/GLARESHIELD
5 150056-1010 MIXTURE PUSH RICH
6 150056-1007 PROP PUSH INCREASE
7 150056-1008 THROTTLE PUSH INCREASE
8 150056-3017 LIGHTING DETECTION EQUIP. OPT...
9 150056-1009 PULL FOR ALTERNATE STATIC SOURCE
10 150056-3038 [STD] GEAR UP/DOWN /BYPASS
10 150085-038 [OPT] GEAR UP/DOWN /BYPASS
11 150056-1003 AVOID CONTINOUS OPERATION....2100 RPM...
12 150056-3039 MIC <CWS A/P DISC TRIM INTR>
REF
LOCATION
PART
NUMBER
DECAL/PLACARD
NOMENCLATURE
1
2
3456789
11
10
12
RSPL--01
NOTE:
150056--1003 Decal is required only when the McCauley 2
Blade Propeller is installed.

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
14 of 33 ISSUED 11 - 2004
REVISION A 06--2005
FAA APPROVED REVISION B 03--2006
INTENTIONALLY LEFT BLANK

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
ISSUED 11 - 2004 15 of 33
REVISION A 06--2005 FAA APPROVEDREVISION B 03--2006
SECTION III -- EMERGENCY PROCEDURES
GENERAL
1. These checklists supercede those in the POH as a result of the
installation of the G1000 avionics system. All other emergency pro-
cedures in the POH remain in effect.
2. These checklists assume that the aircraft is equipped with a standby
alternator system installed by Mooney Airplane Company, Inc.
3. If GARMIN G1000 GPS navigation information is not available or in-
valid, utilize remaining operational navigation equipment as re-
quired.
4. If the ”POSN ERROR” annunciation is displayed the system will flag
and no longer provide GPS based navigational guidance. The crew
should revert to the G1000 VOR/ILS receivers or an alternate
means of navigation other than the G1000 GPS receivers.
5. If the ”POSN ERROR” annunciation is displayed in the enroute,
oceanic, terminal, or initial approach phase of flight, continue to nav-
igate using the GPS equipment or revert to an alternate means of
navigation other than the G1000 GPS receiver appropriate to the
route and phase of flight. When continuing to use GPS navigation,
position must be verified every 15 minutes using the G1000 VOR/
ILS receiver or another IFR--approved primary navigation system.
6. CAUTION: If the ”POSN ERROR” annunciation is displayed while
on the final approach segment (between the Final Approach Fix and
the Missed Approach Point), GPS based navigation will continue for
up to 5 minutes with approach CDI sensitivity set at 0.3 nautical mile.
It is recommended that the pilot initiate the missed approach upon
receipt of this message from the G1000. Navigation guidance will
continue for 5 minutes allowing the pilot to initiate the missed ap-
proach while maintaining course guidance on the final approach
course. Then the system will flag and no longer provide course guid-
ance with approach sensitivity. Missed approach course guidance
may still be available with 1 nautical mile CDI sensitivity by executing
the missed approach. This is typically caused by the GPS sensor’s
inability to provide adequate horizontal position accuracy for the fi-
nal approach segment. It is possible, however unlikely, that the GPS
position may degrade to the point where terminal operations cannot
be supported for the missed approach segment. Navigate using
other primary navigation equipment (VOR receivers, etc) if this oc-
curs.

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
16 of 33 ISSUED 11 - 2004
REVISION A 06--2005
FAA APPROVED REVISION B 03--2006
7. In an in--flight emergency, depressing and holding the Comm trans-
fer button for 2 seconds will select the emergency frequency of
121.500 MHz, and will show it in the ”Active” frequency window.
8. The Attitude, Heading and Reference System (AHRS) requires at
least one GPS or air data input to function properly. In the unlikely
event that both GPS position sources fail, and the air data computer
fails, the AHRS will subsequently lose attitude and heading and the
pilot will be required to use the standby instrumentation. In this
instance, the PFD will not provide altitude, airspeed, attitude, or nav-
igation information
3.1 -- EMERGENCY PROCEDURE CHECKLISTS
Use the electrical fire checklists found in the M20R POH and appropri-
ate AFM supplements.
Electrical System Failures
Alternator Failure
If the Main Alternator fails, indicated by the Master Warning “ALT
VOLTS” is flashing:
Perform the Standby Alternator Emergency Checklist (repeated below)
1. Push the “Stdby Alt/Emergency Bus” switch ON. (This activates the
emergency bus circuitry & Standby Alternator system) Verify:
(a) The AMBER “EMERG BUS” annunciator illuminates, and
(b) The RED “ALT VOLTS” flashing annunciator extinguishes.
NOTE:
The most efficient operating RPM is 2500 RPM when operat-
ing on the Standby Alternator System.
2. All electrical systems will remain powered and functional.
3. If the RED “ALT VOLTS” annunciator remains illuminated, then:
-CAUTION-
If the RED “ALT VOLTS” annunciation remains illuminated, then
the standby alternator has failed, and only main battery power re-
mains.
4. Reduce the electrical load by pulling the “BAT” circuit breaker. This
load sheds the non--essential bus. The following systems remain
powered by the essential bus.

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
ISSUED 11 - 2004 17 of 33
REVISION A 06--2005 FAA APPROVEDREVISION B 03--2006
-CAUTION-
If the autopilot is engaged, when the BAT circuit breaker is pulled,
the autopilot will disconnect without annunciation.
SALT SENSE
SEMER ALT BUS
SALT FIELD
SEMER ALT FIELD
SALT OUT
SSTBY ALT
SBAT
SAUX PANEL
SAUX OVHD
SGLRSHIELD LIGHT
SPFD
SMFD
SAHRS
SADC
SENGINE INST
SSTBY GYRO
SICE PROT SYS
SSTBY BUS BAT
SCOM 1
SNAV1/GPS1
SAUDIO
SXPONDR
SSTALL WARN
SICE LITE
SPITOT HEAT
The following systems on the non--essential bus will be unpowered:
SCom 2
SNav 2 / GPS 2
SAll lighting on the Overhead Panel
SFuel Pumps
SAutopilot
SElectric Trim
SLanding Gear Motor and Indicators
SDefrost Blower
SWX Stormscope
SADF/DME/DATA LINK
STRAFFIC ALERT
SSKYWATCH

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
18 of 33 ISSUED 11 - 2004
REVISION A 06--2005
FAA APPROVED REVISION B 03--2006
5. Terminate flight as soon as practical.
6. On approach, the pilot may engage the “BAT” circuit breaker to rees-
tablish power to all systems if necessary.
7. If using battery power only and the primary battery has been de-
pleted (minimum of 18 VDC), the pilot may select the alternate bat-
tery using the main battery selection switch. There will be no change
in available equipment when changing battery sources. All equip-
ment powered previously will remain powered
AVIONICS EMERGENCIES
a) PFD OR MFD DISPLAY FAILURE
1. DISPLAY BACKUP button on audio panel PUSH.....
b) AHRS FAILURE
NOTE:
Failure of the Attitude and Heading Reference System (AHRS)
is indicated by a removal of the sky/ground presentation and
a red X and a yellow “AHRS FAILURE” shown on the PFD. The
digital heading presentation will be replaced with a yellow
“HDG” and the compass rose digits will be removed. The
course pointer will indicate straight up and course may be set
using the digital window.
1. Use Standby Attitude Indicator and Magnetic compass.
2. Course Set using digital window
3. Land as soon as practical.
c) AIR DATA COMPUTER (ADC) FAILURE
NOTE:
Complete loss of the Air Data Computer is indicated by a red X
and yellow text over the airspeed, altimeter, vertical speed,
TAS and OAT displays. Some FMS functions, such as true air-
speed and wind calculations, will also be lost.
1. Use Standby Airspeed Indicator and Altimeter
2. Land as soon as practical at a suitable airport

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
ISSUED 11 - 2004 19 of 33
REVISION A 06--2005 FAA APPROVEDREVISION B 03--2006
d) ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS
NOTE:
Loss of an engine parameter is indicated by a red X through
the data field. Erroneous information may be identified by in-
dications which do not agree with other system information.
Erroneous indications may be determined by comparing a
display with other displays and other system information.
1. Set power based on throttle lever position, engine noise and speed.
2. Monitor other indications to determine the health of the engine.
3. Use known power settings in the POH Chapter V for approximate
fuel flow values.
4. Use other system information, such as annunciator messages, fuel
quantity and flow, to safely complete the flight.
e) ERRONEOUS OR LOSS OF WARNING/CAUTION
ANNUNCIATORS
NOTE:
Loss of an annunciator may be indicated when engine or fuel
displays show an abnormal or emergency situation and the
annunciator is not present. An erroneous annunciator may
be identified when an annunciator appears which does not
agree with other displays or system information.
1. If an annunciator appears, treat it as if the condition exists. Refer to
the POH/AFM Emergency or Abnormal procedures or the proce-
dures contained in this AFMS.
2. If a display indicates an abnormal condition but no annunciator is
present, use other system information, such as engine displays, fuel
quantity and flow, to determine if the condition exists. If it cannot be
determined that the condition does not exist, treat the situation as if
the condition exists. Refer to the POH/AFM Emergency or Abnormal
procedures or the procedures contained in this AFMS.

MOONEY
M20R
AFM SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
20 of 33 ISSUED 11 - 2004
REVISION A 06--2005
FAA APPROVED REVISION B 03--2006
INTENTIONALLY LEFT BLANK