User Guide

190-00442-00 Rev. AGarmin G1000 System Overview for Mooney M20M & M20R
2-10
SYSTEM OVERVIEW
2.6 DISPLAY BACKLIGHTING
The G1000 PFD and MFD displays use photocell tech-
nology to automatically adjust for ambient lighting con
-
ditions. Photocell calibration curves are pre-configured
to optimize display appearance through a broad range of
cockpit lighting conditions. PFD, MFD, and GMA 1347
bezel/key lighting is normally controlled directly by the
existing instrument panel dimmer bus.
If desired, the PFD and MFD display backlights may
be adjusted manually. PFD, MFD, and GMA 1347 be-
zel/key brightness can also be adjusted manually as well.
GMA 1347 bezel/key brightness is directly tied to the
MFD bezel/key adjustment.
Refer to the G1000 Primary Flight Display Pilot’s
Guide for instructions on how to manually adjust
the backlighting.
2.7 G1000 REVERSIONARY MODE
G1000 PFD and MFD are connected together on a sin-
gle Ethernet bus, allowing communication between the
two units to occur at a high rate of speed. Each GIA 63
Integrated Avionics Units is connected to a single display,
as shown in Figure 2.2.1. This allows the units to share
information, enabling true integration of the system.
In normal operating mode, the PFD displays graphical
flight instrumentation in lieu of traditional gyro instru-
ments. Attitude, heading, airspeed, altitude, and vertical
speed are all shown on one display. The MFD shows a
full-color moving map with navigation information. Both
displays offer control over COM and NAV frequency selec-
tors, as well as heading, course/baro and altitude reference
functions. On the left of the MFD display, an Engine Indi-
cation System (EIS) cluster shows graphical depictions of
engine and airframe instrumentation. Figure 2.7.1 gives
an example of the G1000 system in normal mode.
Should a failure occur in either display, the G1000 au-
tomatically enters reversionary mode. Figure 2.7.2 shows
an example where the PFD fails. In reversionary mode,
critical flight instrumentation is combined with engine in-
strumentation on the remaining display. Minimal naviga-
tion capability is also available on the reversionary mode
display.
It should be noted that if a display fails, the
GIA 63-GDU 1040 Ethernet interface is cut off. Thus the
GIA can no longer communicate with the remaining dis-
play (refer to Figure 2.2.1). Because of this, the NAV and
COM functions provided by the GIA to the failed display
are flagged invalid on the remaining display. The system
reverts to using backup paths for the GRS 77, GDC 74A,
GEA 71 and GTX 33, as required. The change to backup
paths is completely automated for all LRUs and no pilot
action is required.
NOTE: The system alerts the pilot when backup
paths are utilized by LRUs. Refer to the Annun-
ciations & Alerts Pilot’s Guide for further informa-
tion regarding these and other system alerts.
Reversionary display mode may also be manually ac-
tivated by the pilot, if the system fails to detect a display
problem. The reversionary mode is activated manually
by pressing the large red button on the bottom of the
GMA 1347. Pressing the red reversionary mode button
again deactivates reversionary mode.