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on the rate-of-turn indicator scale to indicate half and full standard-rate
turns. A heading bug is also provided on the compass rose.
Navigation Data
Navigation data on the PFD takes several forms. A course deviation
indicator (CDI) is always provided on the HSI and a bearing pointer
can be optionally selected for display on the HSI by the pilot. Controls
for selecting the source of navigation data, selecting the display format
of the navigation data, and for selecting the type of compass rose and
moving map to be displayed are along the left side of the PFD. The
active flight plan contained in the GPS Nav/Com unit selected as the
primary navigation source (Nav) can be optionally selected for display
on the HSI as well as the desired range of the optionally selectable
moving map display. If a localizer or ILS frequency is tuned and
captured in the GPS Nav/Com selected as the Nav source, a vertical
deviation indicator (VDI) and horizontal deviation indicator (HDI) are
automatically displayed on the ADI.
• Note •
In the event glide slope or localizer signals are lost, the HDI
and/or VDI will be displayed as red-“X”s to indicate loss of
signal. The red-“X”-ed indicator will only be removed if the
signal is regained, the Nav Source is changed on the PFD, or
if the GPS Nav/Com is retuned to another frequency.
Appropriate action must be taken by the pilot if on an
approach.
For a detailed description of the PFD, refer to the Avidyne FlightMax
Entegra-Series PFD Pilot’s Guide.
Revision A8
7-26 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
Attitude Indicator
• Note •
Serials 0435 and subsequent with PFD: The attitude indicator
is mounted on the LH bolster panel.
The attitude indicator gives a visual indication of flight attitude. Bank
attitude is indicated by a pointer at the top of the indicator relative to
the bank scale with index marks at 10°, 20°, 30°, 60°, and 90° either
side of the center mark. A fixed miniature airplane superimposed over
a movable mask containing a white symbolic horizon bar, which
divides the mask into two sections, indicates pitch and roll attitudes.
The upper “blue sky” section and the lower “earth” sections have pitch
reference lines useful for pitch attitude control. The indicator can follow
maneuvers through 360° in roll and 360° in pitch. A knob at the bottom
of the instrument allows adjustment of the miniature airplane to the
horizon bar for a more accurate flight attitude indication.
A PULL TO CAGE knob on the indicator is used for quick erection of
the gyro. When the caging knob is pulled, the pitch and roll indications
will align to within 2° of their respective fixed references.
The instrument is electrically driven and a red GYRO flag indicates
loss of electrical power. Redundant circuits paralleled through diodes
at the indicator supply DC electrical power for gyro operation. 28 VDC
for attitude gyro operation is supplied through the 3-amp Attitude #1
circuit breaker on the Essential Bus and the 3-amp Attitude #2 circuit
breaker on the Main Bus 2.
Airspeed Indicator
• Note •
Serials 0435 and subsequent with PFD: The standby airspeed
indicator is mounted on the LH bolster panel.
Indicated and true airspeeds are indicated on a dual-scale, internally
lit precision airspeed indicator installed in the pilot's instrument panel.
The instrument senses difference in static and Pitot pressures and
displays the result in knots on an airspeed scale. A single pointer
sweeps an indicated airspeed scale calibrated from 40 to 220 knots.
The 'zero' index is at the 12 o'clock position. A sub-scale aligns true
airspeed with the corresponding indicated airspeed when the altitude/
Revision A5
P/N 13772-001 7-27
Cirrus Design Section 7
SR22 Airplane Description
temperature correction is set in the correction window. A knob in the
lower left corner of the instrument is used to rotate the pressure
altitude scale in the correction window to align the current pressure
altitude with the outside air temperature.
Vertical Speed Indicator
• Note •
Serials 0435 and subsequent with PFD: The Vertical Speed
Indicator is integrated into the PFD.
Airplane rate of climb or descent in feet per minute is displayed on the
internally lit Vertical Speed indicator installed in the pilot's instrument
panel. The instrument senses rate of change in static pressure from a
reference pressure and displays the result in climb or descent feet per
　
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