MOONEY INTERNATIONAL CORPORATION
M20V SERVICE AND MAINTENANCE MANUAL
Date
MAR 2017
Rev Date
Page
6
39-00-00 - GENERAL
The G1000 Integrated Avionics System (Figure 39- 1 &
Figure 39- 2) is a fully integrated flight, engine, commu-
nication, navigation and surveillance instrumentation
system. The system consists of a Primary Flight Dis-
play (PFD), Multi- Function Display (MFD), audio panel
(GMA), Air Data Computer (ADC), Attitude and Head-
ing Reference System (AHRS), engine/airframe proc-
essing unit (GEA), and integrated avionics (GIA) con-
taining VHF communications, VHS navigation, and
GPS navigation.
For Operation, Maintenance and Troubleshooting, re-
fer to Garmin publications (available in aircraft docu-
mentation):
G1000 Instructions for Continued Airworthiness
G1000 Cockpit Reference Guide
G1000 Configuration Manual
G1000 System Maintenance Manual
G1000 Airplane Flight Manual Supplement
G1000 Avionics Wiring Diagram
G1000 Master Data List
G1000 Required Equipment List
G1000 Post Installation Checkout Procedure
EQUIPMENT LOCATION
The G1000 ADC and GEA modules 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 landing light. The AHRS, and
remaining modules are located in the tailcone on the
Avionics Rack (Figure 39- 2).
Circuit breakers/switches for standard and/or optional
accessories and equipment are located on upper/mid
left and bottom of flight instrument panel.
The Circuit Breaker Panel is located in a removable
panel at the far right of instrument panel.
The annunciator is located at top right center of instru-
ment panel.
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 plan-
ning. The primary function of the MFD is to provide en-
gine information, mapping terrain information and for
flight planning. The audio panel is used for selection of
radios for transmitting and listening, intercom func-
tions, and marker beacon functions.
The primary function of the VHF Communication por-
tion of the G1000 is to enable external radio commu-
nication. 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 real time to obtain the user’s position,
velocity, and time.
See Chapter 91 for Electrical System Hardware Identi-
fication Charts and Schematics.
39-10-00 - INSTRUMENT AND CONTROL
PANELS
-NOTE-
The illustration in Figure 39- 1 depicts a standard
panel configuration. Th e location of instruments,
switches, and avionics may be relocated in each
aircraft, dependant upon the optional equipment
selected by the customer and available panel
space.
1. MAGNETIC COMPASS
Magnetic compass dial is graduated in five- de-
gree increments and is encased in liquid- filled
glass and metal case. It is equipped with com-
pensating magnets, adjustable from front of
case. Access to compass light and compensat-
ing magnets is provided by pivoted covers. No
maintenance is required on magnetic compass
except an occasional check on a compass rose,
adjustment of the compensation screws (if nec-
essary) and replacement of the lamp.
2. HOUR METER (NOT SHOWN)
Hour meter - located on baggage compartment
bulkhead indicates actual flight time and is trig-
gered by the G1000 airspeed indication setting.
Location may vary depending on installed sys-
tems.
3. STANDBY ATTITUDE MODULE (SAM)
Digital standby instrument to provide attitude,
altitude, airspeed and slip information in an ad-
vanced 2- inch format. The self- contained, re-
chargeable, emergency battery offers pilots an
increased level of security. In Pre- flight mode,
the introduction screen will be displayed for ap-
proximately five seconds and will transition to
Flight Mode when complete. In Flight Mode, the
unit operates normally by displaying all four ma-
jor functions: Attitude, Altitude, Airspeed and Slip
Information.
ATTITUDE Indicator portion of the display
will always appear on t he top display. The Atti-
tude Indicator consists of seven parts: Horizon
Line, Sky (blue), Ground (brown), Symbolic Air-
plane, Roll Scale, Pitch Scale and Slip Indicator.
SLIP Indicator portion of the display will al-
ways appear at the bottom of the Attitude Display.
The Slip Indicator is represented by a shaded
translucent background with two white lines
around center and a white ball. When the ball is
maintained between the vertical lines during
banking maneuvers, the turn is considered “co-
ordinated” without slip.
ALTIMETER Indicator portion of the display
will always appear on the bottom display. The Al-
39-00-00
To Next Page
Loading...
