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to Section 2, Limitations.
Primary Flight Display - Serials 0435 and Subsequent
The Primary Flight Display (PFD) provides the functions of the attitude
indicator, heading indicator, airspeed indicator, altimeter, vertical
speed indicator, directional gyro, course deviation indicator, and
altitude pre-select controller onto a single electronic display. In
addition, the PFD communicates with GPS1, GPS2, NAV1, NAV2, the
Multifunction Display, and Autopilot System.
An integral air data/attitude and heading reference system (ADAHRS)
uses a 3-axis solid state gyro and accelerometer system combined
with a magnetometer to replace the vertical and directional gyros.
ADAHRS also provides roll, pitch, heading data and continually
updates the winds aloft and true airspeed (TAS) indications on the
PFD. The magnetometer assembly mounted in the wing also provides
outside air temperature (OAT) data.
The airplane’s Pitot-Static system is connected to the PFD to provide
airspeed, altitude, and vertical speed.
Standby instruments for airspeed, attitude and altitude are mounted on
the LH bolster panel and are on separate power sources than the PFD.
Redundant power sources provide 28 VDC for system operation.
Power is supplied through the 10-amp PFD1 circuit breaker on the
Essential Bus and the 10-amp PFD2 circuit breaker on Main Bus 2.
Either circuit is capable of powering the PFD. System start-up is
automatic once power is applied. The display presents the Initialization
Display immediately after power is applied. Power-on default is 75%
brightness. Typical alignment times are 3 minutes from battery turn on.
June 2007
7-22 Information Manual
Section 7 Cirrus Design
Airplane Description SR22
Figure 7-5
MAIN BUS 2
ESSENTIAL BUS
Avidyne PFD
SR22_FM07_1607B
PFD 1
10
PFD 2
10
PITOT
STATIC
Avidyne MFD
STEC System 55x
Autopilot
Data Aquisition Unit
OAT Sensor /
Magnetometer
#2 GNS-430
GPS
#1 GNS-430
GPS
AP ON
Flight Director System
(Optional)
AP OFF
FD ON
PFD System - Simplified Schematic
June 2007
Information Manual 7-23
Cirrus Design Section 7
SR22 Airplane Description
Attitude Direction Indicator (ADI)
Air Data
The airspeed tape to the left of the main ADI begins indicating at 20
Knots Indicated Airspeed (KIAS) and is color-coded to correspond
with airspeeds for VSO, VFE, VS, VNO, and VNE. An altitude tape is
provided to the right of the main ADI and also displays a symbol for the
Altitude preselect (Altitude bug). The Vertical Speed Indicator (VSI) is
displayed to the right of the altitude tape. The displayed scale of the
VSI is +/- 2000 FPM and for rates above 2000 FPM, the needle will
peg just outside the scale and a digital readout of actual VSI up to
4000 FPM is then displayed. An additional data block is provided for
display of outside air temperature (OAT), true airspeed (TAS), and
groundspeed (GS). Controls for selecting bug and barometric
correction values are along the right side of the PFD. A wind indicator
is also provided beneath the altitude tape.
Attitude Data
Attitude is depicted on the main ADI using an aircraft reference symbol
against a background of labeled pitch ladders and an arced scale
along the top of the ADI to indicate bank angle. A skid/slip indicator is
attached to the bottom edge of the bank angle pointer.
June 2007
7-24 Information Manual
Section 7 Cirrus Design
Airplane Description SR22
Figure 7-6
10
20 20
ILS
ILS
TAS110 KTS
GS 98 KTS
OAT 11°C
SAV
DTK 020°
62.2 NM
00:26:18
KLWH
BRG 352°
43.6 NM
00:17:52
ILS
108.10
CRS 020°
Nav
VLOC 1
Bearing
GPS 1
Aux
GPS 2
Range
View
10 10
10
Power 20 20
74
24.0
M-BUS V
V
%
E-BUS
24.0
80
90
110
120
9
10
1
037°/ 7
VSI Bug
-500 FPM
Alt Bug
4900 FT
Baro Set
29.92"
Hdg Bug
005°
Hdg Sync
AP RDY VS
-20
-10
-5
0
5
10
20
4900 FT
5000
4900
4700
4600
29.92"
48
20
00
80
006
W
E
N
S
15
12
24
30
33
6
3
21
0
LEGEND
1. Navigation & Avionics Configuration Buttons
2. Percent Power
　
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本文鏈接地址：AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(57)