Garmin | G1000: Mooney M20M | Garmin G1000: Mooney M20M Aircraft Flight Manual Supplement (M20M)

Garmin G1000: Mooney M20M Aircraft Flight Manual Supplement (M20M)
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
Table of Contents
SECTION
PAGE
GENERAL ............................................................................................................. 4
LIMITATIONS ...................................................................................................... 6
EMERGENCY PROCEDURES ............................................................................ 13
NORMAL PROCEDURES.................................................................................... 20
PERFORMANCE .................................................................................................. 28
WEIGHT AND BALANCE .................................................................................. 28
AIRPLANE & SYSTEM DESCRIPTIONS .......................................................... 29
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 3 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
SECTION 1
GENERAL
1.
The G1000 Integrated Avionics System is a fully integrated flight, engine,
communication, navigation and surveillance instrumentation 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, VHF 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 function of the VOR/ILS
Receiver portion of the equipment is to receive and demodulate VOR,
Localizer, and Glide Slope signals. The primary 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 realtime to obtain the user's position, velocity, and time.
4.
Provided the GARMIN G1000 GPS receivers are receiving adequate 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:
x
VFR/IFR enroute, oceanic, and terminal, operations as well
and non-precision instrument approach (GPS, Loran-C,
VOR, VOR-DME, TACAN, NDB, NDB-DME, RNAV)
190-00453-04 Rev. B
Page 4 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
x
x
operations within the U.S. National Airspace System in
accordance with AC 20-138A.
Navigation in the North Atlantic Minimum Navigation
Performance Specification (MNPS) Airspace, in accordance
with AC 91-49 and AC 120-33.
The G1000 system meets RNP5 airspace (BRNAV)
requirements of AC 90-96 and in accordance with AC 20138A, JAA AMJ 20X2 Leaflet 2 Revision 1, and FAA Order
8110.60 for oceanic and remote airspace operations,
provided it is receiving usable navigation information 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 airspace you are operating in to determine
if this GPS prediction software 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 MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 5 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
SECTION 2
LIMITATIONS
GENERAL
G1000 System:
1.
The GARMIN G1000 Cockpit Reference Guide for the M20M Series aircraft,
P/N 190-00450-00, Revision A or later appropriate revision must be
immediately available to the flight crew.
2.
The G1000 must utilize the following or later FAA approved software
versions:
Sub-System
PFD
MFD
GMA
AHRS
ADC
GIA
GEA
GPS
Software Version
3.04
3.04
2.04
2.03
2.03
2.05
2.04
3.01
The database version is displayed on the MFD power-up page immediately
after system power-up and must be acknowledged. The remaining 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 currency of the database or
verifies each selected waypoint for accuracy by reference to current approved
data.
190-00453-04 Rev. B
Page 6 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
4.
Instrument approach navigation predicated upon the G1000 GPS Receiver
must be accomplished in accordance with approved instrument approach
procedures that are retrieved from the GPS equipment database. The GPS
equipment database must incorporate 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 Approach 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 approved for
GPS require VOR/ILS navigation data to be valid on the PFD display.
(d) When an alternate airport is required by the applicable operating 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 required navigation aid must be operational.
(e) VNAV information may be utilized for advisory information only. Use of
VNAV information for Instrument Approach Procedures does not
guarantee step-down fix altitude protection, or arrival at approach
minimums in a normal position to land. VNAV also does not guarantee
compliance with intermediate altitude constraints between the top of
descent and the waypoint where the VNAV path terminates in terminal or
enroute operations.
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 7 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
5.
If not previously defined, the following default settings must be made in the
“SYSTEM SETUP” menu of the G10000 prior to operation (refer to Pilot's
Guide for procedure if necessary):
(a)
(b)
(c)
(d)
DIS, SPD ..... kt (sets navigation units to “nautical miles” and “knots”)
ALT, VS ......ft fpm (sets altitude units to “feet” and “feet per minute”)
MAP DATUM WGS 84 (sets map datum to WGS-84, see note below)
POSITION ...deg-min (sets navigation grid units to decimal minutes)
example: dd.mm.ss: 45q 30’ 30” in decimal minutes are: 45q 30.5’
NOTE: In some areas outside the United States, datums other than WGS84 or NAD-83 may be used. If the G1000 is authorized for use by the
appropriate Airworthiness authority, the required geodetic datum must be
set in the G1000 prior to its use for navigation.
6.
Operation is prohibited north of 70qN and south of 70qS latitudes. In addition,
operation is prohibited in the following two regions: 1) north of 65qN between
75qW and 120qW longitude and 2) south of 55qS between 120qE and 165qE
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 the autopilot 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.
190-00453-04 Rev. B
Page 8 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
2.1 AIRSPEED MARKINGS
Marking
Red band
IAS
20 KIAS – 59 KIAS
White band
59 KIAS – 110 KIAS
Green band
Yellow band
66 KIAS – 174 KIAS
174 KIAS – 195 KIAS
Red band
195 KIAS and greater
Significance
Low speed awareness –
stall is imminent
Operating range with
flaps fully extended
Normal operating range
Caution range – smooth
air only
Lower limit of 195 KIAS
is the maximum speed for
all operations
The airspeed indicator is marked in IAS values.
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 9 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
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.
Indication
Engine RPM
Manifold
Pres.
in. Hg.
Oil Temp qF
Cylinder Head
Temp qF
Oil Pressure
PSI
Fuel Pressure
Turbine Inlet
Temperature
Red
arc or bar
=
Lower
prohibited
range
--
Yellow
arc or
bar
=
Caution
range
--
--
Yellow
arc or bar
=
Caution
range
--
Green
arc or bar
=
Normal
operating
range
2200 2575
10 – 38
---
---
0 - 25
0 - 15
--
Red
arc or bar
=
Upper
prohibited
range
2500 - 2700*
--
>38
100 - 245
250 - 500
---
>245
>500
25 - 55
55 - 95
95 – 115
>115
15 - 24
25 - 55
0 - 1750
--
>55
>1750
* To prevent nuisance alerts during normal takeoffs: the “RPM” will not turn red
or flash until the RPM exceeds 2620.
190-00453-04 Rev. B
Page 10 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
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
Primary Flight Display
Multi-Function Display
Audio panel
Air data computer
Attitude and Heading Reference
System
Engine/Airframe Interface Unit
GPS
*
Number
installed
1
1
1
1
1
VFR
Day
*
1
-
VFR
Night
1
1
1
1
IFR
1
2
1
-
1
1
1
2
1
1
1
1
1
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 (reversionary) 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 contain detailed
descriptions of the annunciator system and all advisory messages. These messages
appear on the PFD for flight crew awareness.
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 11 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
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 each annunciation as necessary.
Annunciation
AHRS Aligning – Keep
Wings Level
ATTITUDE FAIL
AIRSPEED FAIL
ALTITUDE FAIL
VERT SPEED FAIL
HDG
Red X
190-00453-04 Rev. B
Page 12 of 35
Cause
Attitude and Heading Reference System is aligning.
Keep wings level using standby attitude indicator.
Display system is not receiving attitude reference
information from the AHRS; accompanied by the
removal of sky/ground presentation and a red X over
the attitude area.
Display system is not receiving airspeed input from
the air data computer; accompanied by a red X
through the airspeed display
Display system is not receiving airspeed input from
the air data computer; accompanied by a red X
through the altimeter display
Display system is not receiving vertical speed input
from the air data computer; accompanied by a red X
through the vertical speed display
Display system is not receiving valid heading input
from the AHRS; accompanied by a red X through the
digital heading display
A red X through any display field, such as com
frequencies, nav frequencies, or engine data, indicates
that display field is not receiving valid data.
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
SECTION 3
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 procedures in the POH
remain in effect.
2.
These checklists assume that the aircraft is equipped with dual alternator
systems installed by Mooney Aircraft Corporation.
3.
If GARMIN G1000 GPS navigation information is not available or invalid,
utilize remaining operational navigation equipment as required.
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 navigate 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 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 approach while maintaining course guidance on the final
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 13 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
approach course. Then the system will flag and no longer provide course
guidance 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 final 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 occurs.
7.
In an in-flight emergency, depressing and holding the Comm transfer 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 the pilot will be required to use the standby
instrumentation. In this instance, the PFD will not provide altitude, airspeed,
attitude, or navigation information
190-00453-04 Rev. B
Page 14 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
3.1 EMERGENCY PROCEDURE CHECKLISTS
Use the electrical fire checklists found in the M20M POH and appropriate AFM
supplements.
ELECTRICAL FIRE – IN FLIGHT
If electrical power is essential for the flight, attempt to isolate the faulty circuit.
Cabin Ventilation……………………………………………….OPEN
Heating Controls…………………………………………….CLOSED
Circuit Breakers……….…CHECK to identify fault circuit if possible
Land as soon as practical.
If smoke in the cockpit continues, press the EMER BUS switch to shed the nonessential equipment.
NOTE: If the autopilot is engaged and the EMER BUS is activated, it will
disengage without annunciation.
If smoke in the cockpit continue, then:
Left and Right Alternator Switches……………………………….OFF
Master Switch……………………………………………………..OFF
Note: The standby instrumentation will remain powered with the EMER BUS
switch on.
If power must be reestablished to navigation equipment to continue flight:
If the faulty component can be determined, pull the associated circuit breaker if not
tripped already. Do not close the open breaker to reestablish power to the failed
circuit.
If the faulty component cannot be determined, pull all essential circuit breakers,
switch the Master switch ON and L&R Alternator switches ON, then close circuit
breakers one at a time. Permit a short time period to elapse before closing the next
circuit breaker.
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 15 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
ELECTRICAL SYSTEM FAILURES
Left/Right Alternator Failure
1.
All electrical systems will remain powered and functional.
2.
Reduce electrical load if the ammeter indicates a battery discharge.
3.
Turn off the affected alternator field switch. Land as soon as practical.
Note: It is permissible to cycle the alternator field switch to attempt to reset
the alternator.
4.
If both alternators fail and cannot be restored, then:
5.
Reduce the load by pressing the EMER BUS switch. This load sheds the nonessential bus. The following systems remain powered by the essential bus.
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
L/R ALT SENSE
L/R ALT FIELD
LEFT ALT
AUX PANEL
BAT
AUX OVHD
RIGHT ALT
BOOST PUMP
GLRSHIELD LIGHT
PFD
MFD
AHRS
ADC
ENGINE INST
STBY GYRO
ICE PROT SYS (as installed)
COM 1
190-00453-04 Rev. B
Page 16 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
ƒ
ƒ
ƒ
ƒ
ƒ
NAV 1 / GPS 1
AUDIO
XPONDR
ICE LITE (as installed)
PITOT HEAT
The following systems on the non-essential bus will be unpowered:
ƒ
ƒ
ƒ
ƒ
ƒ
TURN COORDINATOR (AUTOPILOT INOP)
COM 2
NAV 2 / GPS 2
WX STORMSCOPE
DIMMER CONTROL
CAUTION: If the autopilot is engaged, when the EMER BUS switch is activated
the autopilot will disconnect without annunciation.
6.
7.
Terminate flight as soon as practical.
If using battery power only and the primary battery has been depleted
(minimum of 18 VDC), the pilot may select the alternate battery using the
main battery selection switch. There will be no change in available equipment
when changing battery sources. All equipment powered previously will
remain powered.
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 17 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
AVIONICS EMERGENCIES
a) PFD OR MFD DISPLAY FAILURE
1. DISPLAY BACKUP button on audio panel ................................................ PUSH
b) AHRS FAILURE
NOTE
A 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.
2.
3.
Use Standby Attitude Indicator and Magnetic compass
Course...........................................................................Set using digital window
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 airspeed and wind
calculations, will also be lost.
1.
2.
Use Standby Airspeed Indicator and Altimeter
Land as soon as practical at a suitable airport
190-00453-04 Rev. B
Page 18 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
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 indications 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.
2.
3.
4.
Set power based on throttle lever position, engine noise and speed.
Monitor other indications to determine the health of the engine.
Use known power settings in the POH Chapter V for approximate fuel flow
values.
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.
2.
If an annunciator appears, treat it as if the condition exists. Refer to the
POH/AFM Emergency or Abnormal procedures or the procedures contained in
this AFMS.
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 MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 19 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
SECTION 4
NORMAL PROCEDURES
NOTE
View ability of the PFD and MFD displays may be degraded when wearing
polarized sunglasses.
The following normal procedures have been modified as the result of the
G1000 installation. Procedures which have not been modified as a result of
the G1000 installation should be used as written in the POH/AFM.
DETAILED OPERATING PROCEDURES
Normal operating procedures for the G1000 are described in the GARMIN
G1000 Cockpit Reference Guide and the GARMIN G1000 Pilot's Guide.
190-00453-04 Rev. B
Page 20 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
4.5 NORMAL PROCEDURES CHECKLISTS
BEFORE STARTING CHECK
Preflight Inspection ..................................................................................... Complete
Seats, Seatbelt, Shoulder Harness ................................................Adjust and Secured
Magneto/Starter Switch......................................................................................... Off
Master Switch......................................................................................................... On
Alternator Field Switches...................................................................................... Off
Fuel Boost Pump Switch ....................................................................................... Off
Circuit Breaker Switches........................................................................Check-All In
ELT Switch ......................................................................................................Armed
Rocker Switches.................................................................................................... Off
Alternate Static Source................................................................................. Push Off
Throttle.............................................................................................................Closed
Propeller ............................................................................Full Forward (High RPM)
Mixture.................................................................................................... Idle Cut Off
Cowl Flaps ...................................................................................... Verify Full Open
Brakes.....................................................................................................................Set
Wing Flap Switch......................................................................................... Flaps Up
Defrost.......................................................................................................... Push Off
Cabin Heat.................................................................................................... Push Off
Cabin Vent ................................................................................................ As Desired
Fuel Selector............................................................................................Fullest Tank
Landing Gear Switch........................................................................... Down Position
Red Emergency Gear Extension Handle ...................................... Down and Latched
Internal Lights ....................................................................................................... Off
Passenger Briefing .................................................................................... Completed
Refer to Section IX Supplements for other Optional Equipment Procedures and
Checks.
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 21 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
BEFORE TAXI
Engine Start Checklist ............................................................................... Completed
Elevator Trim Switch..............................................................................................On
Internal/External Lights.............................................................................As Desired
PFD/MFD ........................................................................... Check Normal Operation
Comm/Nav Radios ...........................................................................Checked and Set
Altimeter................................................................................................................ Set
Fuel Selector.....................................Switch Tanks, verify engine runs on other tank
Cowl Flaps............................................................................. Full Open or as desired
Cabin Heat .................................................................................................As Desired
Defroster....................................................................................................As Desired
Cabin Vent.................................................................................................As Desired
Flight Plan .................................................................................................As Desired
Optional Equipment Checks..................................................... Reference Section IX
NOTE: During cold weather, ground operations may be conducted with cowl flaps
positioned partially or fully closed to help keep engine temperatures in normal
operational ranges prior to takeoff. However, if cowl flaps are fully closed,
monitor engine temperatures to avoid exceeding maximum allowable limits.
190-00453-04 Rev. B
Page 22 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
TAXI
Before Taxi Checklist................................................................................ Completed
Rudder Trim .............................................................................................. As Desired
CAUTION: With Rudder Trim in the full right position the aircraft will
tend to steer to the right during taxi.
Parking Brake................................................................................................. Release
Brakes............................................................................................. Check during taxi
Heading Indicator..................................................... Proper Indication During Turns
PFD/MFD....................................................................................... No Flags/Red X’s
Throttle.............................................................................................Minimum Power
Propeller ............................................................................Full Forward (High RPM)
CAUTION: To prevent battery depletion in prolonged taxi or holding
position before takeoff, increase RPM until the “AMPS” indication on the
G1000 indicates a positive number.
BEFORE TAKEOFF
Taxi Checklist ............................................................................................. Complete
Parking Brake.........................................................................................................Set
Fuel Selector............................................................................................Fullest Tank
Throttle...................................................................................................... 1000 RPM
Cowl Flaps .................................................................................... Open or as desired
Propeller .................................................................................................... High RPM
Mixture...................................................................................................Full Forward
Alternate Air......................................................................................... Verify Closed
Alternator Field Switches...........................................................................Verify ON
Throttle...................................................................................................... 2000 RPM
Parking Brake.........................................................................................................Set
Magneto Switch ........................................Check – BOTH to L, BOTH to R, BOTH
Verify engine operates smoothly on each magnet separately
(150 RPM MAX drop on each magneto, 50 RPM MAX difference)
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 23 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
NOTE:
An absence of RPM drop may be an indication of faulty magneto grounding or
improper timing. If there is doubt concerning ignition system operation, RPM
checks at a leaner mixture setting or higher engine speed will usually confirm
whether a deficiency exists.
Propeller ..........................................................................Cycle/Return to High RPM
Ammeter .............................................................CHECK Positive Charge Indication
Main Battery Voltage ............................................................. Greater than 26.5VDC
Select the other battery using the BAT 1/2 selector
Ammeter .............................................................CHECK Positive Charge Indication
Main Battery Voltage ............................................................. Greater than 26.5VDC
Select desired Main Battery for use during flight using BAT 1/2 selector
Throttle ................................................................................. RETARD to 1000 RPM
Fuel Boost Pump Switch ................. ON-Verify annunciator light illuminates BLUE
Fuel Boost Pump Switch ..................................................................................... OFF
Elevator Trim........................................................................... TAKEOFF SETTING
Rudder Trim ............................................................................ TAKEOFF SETTING
Wing Flaps .................................................................................... CHECK operation
SET AT TAKEOFF POSITION (10 degrees)
Flight Controls................................................... CHECK free and correct movement
Cabin Door ................................................................................. CHECK SECURED
Seats, Seat Belts and Shoulder Harness.................................................... SECURED
Avionics and Autopilot............................................. CHECK – (Refer to section IX)
Annunciator Lights........................................................................................ CHECK
Internal/External Lights........................................................................AS DESIRED
Strobe Lights/Rotating Beacon..............................................................................ON
Pilots Window ............................................................................................. CLOSED
Emergency Gear Extension (RED) Handle ..........................DOWN and LATCHED
Oil Temperature..................................................................... 100qF(38qC) minimum
CHT ..................................................................................... 250qF(121qC) minimum
Parking Brake ............................................................................................ RELEASE
190-00453-04 Rev. B
Page 24 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
TAKEOFF
Proper engine operation should be checked early in the takeoff roll. Any
significant indication of rough or sluggish engine response is reason to discontinue
takeoff. When takeoff must be made over a gravel surface, it is important that the
throttle be applied SLOWLY. This will allow the aircraft to start rolling before
high RPM is developed, and gravel or loose material will be blown back from the
propeller area instead of being pulled into it.
If the turbocharger and its controlling system are properly rigged, manifold
pressure will increase to approximately 34 to 38 in. Hg, when the throttle is full
open. However, engine operation with oil temperature below 100qF (38qC) will
result in an overboost (manifold pressure above 38 in. Hg). If an overboost occurs,
retart throttle to lower manifold pressure below 38 in. Hg, and continue flight. As
the oil warms above 100qF (38qC) the throttle can be moved to full throttle open
and the turbocharger controller will maintain proper manifold pressure for
maximum continuous power.
Full throttle operations during hot weather conditions may also result in manifold
pressure over 38 in. Hg. If this occurs, retard throttle below 38 in. Hg, and
continue flight.
TAKEOFF (NORMAL)
Power ........................................................................FULL THOTTLE (2575 RPM)
DO NOT EXCEED 38” MAP
Annunciator................................................................................................... CHECK
Blue Boost Pump Light ON
Engine Instruments.....................................................CHECK for proper indications
Lift Off/Climb Speed ..................... As specified in SECTION V (Takeoff Distance)
Landing Gear.................................... RETRACT IN CLIMB after clearing obstacles
Wing Flaps .............................................................................................................UP
Fuel Pressure ................................................................................. 24 PSI (minimum)
NOTE: If maximum performance takeoffs are desired, obtain full power before
brake release. Use lift off and climb speed as specified in section V.
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 25 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
CLIMB
NOTE: If applicable, use noise abatement procedures as required. See section V,
for rate of climb graph.
CLIMB (CRUISE)
Power......................................................................................................... 2400 RPM
Manifold Pressure........................................................................................ 34 Inches
Mixture .............................................................................................................. RICH
Cowl Flaps............................................................................. Full Open or as desired
Rudder Trim .........................................................................................AS DESIRED
Airspeed...................................................................................................... 120 KIAS
CLIMB (BEST RATE)(Vy)
Power.......................................................................FULL THROTTLE / 2575 RPM
Do Not Exceed 38” MAP
Mixture .............................................................................................................. RICH
Cowl Flaps............................................................................. Full Open or as desired
Rudder Trim ..............................................................................................As Desired
Airspeed...................................................................................................... 105 KIAS
CLIMB (BEST ANGLE)(Vx)
Power.......................................................................FULL THROTTLE / 2575 RPM
Do Not Exceed 38” MAP
Mixture .............................................................................................................. RICH
Cowl Flaps............................................................................. Full Open or as desired
Rudder Trim ..............................................................................................As Desired
Airspeed........................................................................................................ 85 KIAS
190-00453-04 Rev. B
Page 26 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
SHUTDOWN
CAUTION
Operate the engine at idle (below 1000 RPM) for 5 minutes to allow the
turbocharger to cool. Taxi time after landing may be considered as part of the
5 minutes.
Parking Brake.........................................................................................................Set
Throttle........................................................................................................ Idle RPM
Interior/Exterior Lights ......................................................................................... Off
Pitot Heat............................................................................................................... Off
Magneto/Starter Switch.................................................................. Grounding Check
Mixture.................................................................................................... Idle Cut-Off
Alternator Field Switches...................................................................................... Off
Master Switch........................................................................................................ Off
Magneto/Starter Switch......................................................................................... Off
SECURING AIRCRAFT
Magneto/Starter Switch...................................................... Verify Off/Key Removed
Master Switch.............................................................................................Verify Off
Electrical Switches .....................................................................................Verify Off
Interior Light Switches...............................................................................Verify Off
Emergency Bus Switch ..............................................................................Verify Off
Parking Brake........................................................... Release – Install Wheel Chocks
Extended Parking .................................................................. Control Wheel Secured
Cabin Windows and Doors .......................................................... Closed and Locked
Tie down aircraft at wing and tail points.
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 27 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
SECTION 5
PERFORMANCE
No change.
SECTION 6
WEIGHT AND BALANCE
See current weight and balance data.
190-00453-04 Rev. B
Page 28 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
SECTION 7
SYSTEM DESCRIPTIONS
The Garmin G1000 Integrated Avionics System consists of a Primary Flight
Display (PFD), a Multi-Function Display (MFD), an Audio Panel, and Attitude and
Heading Reference System (AHRS), an Air Data Computer (ADC), and the sensors
and computers to process flight and engine information for display to the pilot.
The system contains dual GPS receivers, dual VOR/ILS receivers, dual VHF
communications transceivers, a transponder, and an integrated annunciation system
to alert the pilot of certain abnormal conditions.
The Primary Flight Display (PFD) typically displays airspeed, attitude, altitude,
and heading information in a traditional format. Slip information is shown as a
trapezoid under the bank pointer. One width of the trapezoid is equal to a one ball
width slip. Rate of turn information is shown on the scale above the compass rose;
full scale deflection is equal to a standard rate turn. The following controls are
available on the PFD (clockwise from top right):
x
x
x
x
x
x
x
x
x
x
x
x
x
Communications frequency volume and squelch knob
Communications frequency set knobs
Communications frequency transfer button
Altimeter setting knob (baro/QNH set)
Course knob
Map range knob and cursor control
FMS control buttons and knob
PFD softkey buttons, including master warning/caution acknowledgement
Altitude reference set knob
Heading bug control
Navigation frequency transfer button
Navigation frequency set knobs
Navigation frequency volume and Identifier knob
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 29 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
The PFD displays the crew alerting (annunciator) system. When an alert message
is received, an aural tone will be heard. Selecting the Alert button will allow the
flight crew to see additional information regarding the alert message.
Trend vectors are shown on the airspeed and altimeter displays as a magenta line
predicting 6 seconds at the current rate. The turn rate indicator also functions as a
trend indicator on the compass scale.
The PFD can be displayed in a composite format for emergency use by pressing the
DISPLAY BACKUP button on the audio panel. In the composite mode, the crew
alerting function remains operative, but no map functions are available.
The Multi-Function Display (MFD) typically displays engine data, maps, terrain,
traffic and topography displays, and flight planning and progress information. The
display unit is identical to the PFD and contains the same controls as previously
listed.
The audio panel contains traditional transmitter and receiver selectors, as well as an
integral intercom and marker beacon system. The marker beacon lights appear on
the PFD. In addition, a clearance recorder records the last 2 ½ minutes of received
audio. Lights above the selections indicate what selections are active. Pressing the
red DISPLAY BACKUP button on the audio panel causes both the PFD and MFD
to display a composite mode.
190-00453-04 Rev. B
Page 30 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
The Attitude and Heading Reference System (AHRS) uses GPS, rate sensors, air
data, and magnetic variation to determine pitch and roll attitude, sideslip and
heading. Operation is possible in a degraded mode if the system loses any of these
inputs, but the AHRS must have at least the ADC or GPS input to function. Status
messages alert the crew of the loss of any of these inputs. The AHRS will align
while the aircraft is in motion, but will align quicker if the wings are kept level
during the alignment process.
The Air Data Computer (ADC) provides airspeed, altitude, vertical speed, and air
temperature to the display system. In addition to the primary displays, this
information is used by the FMS and TIS systems.
Engine instruments are displayed on the MFD. Discrete engine sensor information
is processed by the Garmin Engine Airframe (GEA) sub-system. When an engine
sensor indicates a value outside the normal operating range, the legend will turn
yellow for caution range, and turn red and flash for warning range.
The G1000 also interfaces to the STEC 55x autopilot and repeats the autopilot
mode annunciators on the G1000 PFD. This provides easy viewing of the autopilot
operating mode and status, but remains a supplemental display of autopilot
operating modes.
Refer to the Garmin G1000 Cockpit Reference Guide for the Mooney Series
aircraft, Garmin P/N 190-00450-00 for complete descriptions of the G1000 system
and operating procedures.
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 31 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
Electrical System
The M20M has a 28 Volt DC system, powered by dual 70-amp alternators which
are mounted on the front of the engine. Both are driven by V belts on the ring gear
and both alternators charge the main batteries. The alternators are the primary
source of aircraft power and are connected to the aircraft electrical system at the
main bus. In the event of an alternator failure, the remaining alternator has
sufficient capability to power all aircraft systems.
Additional battery power is stored in two 11 amp-hour lead acid battery which are
mounted in the tailcone of the aircraft, and either battery may feed both the
essential and non-essential busses. In the event of both alternators failing, the
EMER BUS switch can be activated and the selected main battery will power the
following:
x A reduced subset of the G1000 system, which is comprised of the PFD/MFD,
AHRS, ADC, Com1, Nav1, GPS1, Transponder, Audio Panel, and Engine
Instruments;
x An independent, standby attitude indicator (artificial horizon)
x Lighting for the attitude indicator, altimeter, airspeed indicator, and compass.
x Aux Overhead Equipment, Aux Panel Equipment, and Ice Protection System.
When the EMER BUS switch is set to ON, the Emergency Bus annunciator is
activated, and non essential equipment is shed from the bus. A single operating
alternator will provide enough current to supply all electrical equipment needed for
safe flight, but if both alternators have failed, the battery voltage should be
monitored, and additional load shedding may be required. Activating the EMER
BUS switch bypasses the master switch and electrically feeds the standby attitude
indicator and all standby lighting using both main batteries.
The circuit breaker panel is located on the right side of the instrument panel. Each
breaker is clearly marked to show which circuit it protects. Also, circuit provisions
are made to handle the addition of communications and navigation equipment.
190-00453-04 Rev. B
Page 32 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
Standard electrical accessories include the starter, the electric fuel pump, and the
stall warning horn. Electrical accessories include the navigation lights, anticollision strobe lights, instrument panel lighting, and cabin courtesy lights. Make
sure the lighting and Emergency Bus switch are off when leaving the aircraft.
Leaving the lights on for an extended period of time could cause depletion of the
battery.
Two lights, mounted in the overhead panel, provide instrument and cockpit lighting
for night flying, in addition glare shield lighting may be controlled via a dimmer
switch on the lower right side of the instrument panel. Wing tip recognition lights
and landing / taxi lights are operated by rocker type switches mounted in the
overhead switch panel. Landing and taxi lights are mounted on the wing leadings
edges on both wings.
The M20M electrical system is divided into two power buses. A simplified
schematic of the electrical system is shown in the diagram which follows.
Essential bus
The Essential bus is tied directly to the main aircraft battery via the selected battery
contactor. When the master switch is turned on, power is immediately supplied to
the Essential and non-Essential busses. The Essential bus provides power to the
G1000 equipment and to the backup instruments. When the Emergency Bus
switch is activated by the pilot, the non essential bus is shed from the essential bus.
The selected main battery (two main batteries are available) remains online.
Non-Essential bus
The non-essential bus powers the autopilot, turn coordinator required for the
autopilot, the Stormscope, and GIA #2. This bus is load shed when the EMER
BUS switch is activated.
Equipment Location
The G1000 ADC and GEA LRU’s are located behind the instrument panel. The
PFD, MFD, and Audio Panel are mounted to the panel and may be removed using
a hexagonal tool. The magnetometer is located in the right wing outboard of the
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 33 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
landing light. The AHRS, and remaining LRU’s are located behind the cabin near
the main batteries.
190-00453-04 Rev. B
Page 34 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
M20M POWER SUMMARY
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
190-00453-04 Rev. B
Page 35 of 35
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
IN A MOONEY MODEL M20M
VACUUM SYSTEM
RESERVED
INSTRUMENT PANEL
The instrument panel has been designed to incorporate the G1000 Integrated
Cockpit. All Communications, Navigation, Engine Instruments, and System
annunciations have been integrated into a custom design package specifically for
the M20M series aircraft.
Engine and electrical switches are located on the left side of the switch panel. Nav,
strobe, recognition / landing and taxi light switches are located on the overhead
switch panel.
Instrument panel lighting is provided by internal lighting, overhead panel lights and
the G1000 Integrated Cockpit System. Optimum cockpit panel lighting for night
flying is achieved by using a combination of panel lights and overhead map lights.
190-00453-04 Rev. B
Page 36 of 35
MOONEY MODEL M20M
FAA APPROVED
DATE: Nov 16, 2004
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