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outside for the intruder aircraft. Call ATC for Guidance. If you
visually acquire the intruder aircraft, use normal right-of-way
procedures to maintain separation.
• Note •
Revision 1: 10-12-05
P/N 11934-S15 5 of 6
Cirrus Design Section 9
SR20 Supplements
Do not maneuver solely on traffic information shown on the
display. Information shown on the display is provided as an aid
in visually acquiring traffic - It is not a replacement for ATC and
See & Avoid techniques.
Section 5 - Performance
No Change
Section 6 - Weight & Balance
SkyWatch adds the following optional (Sym = O) equipment at the
weight and arm shown in the following table.
Section 7 - Systems Description
The SkyWatch model SKY497 is an airborne Traffic Advisory System
(TAS). SkyWatch monitors a radius of approximately 6 nautical miles
around the aircraft by interrogating transponders in the monitored area
and determining if a collision threat exists. To determine if a collision
threat exists, SkyWatch calculates the range, altitude, bearing, and
closure rate of all transponder equipped aircraft with the 6 nautical
mile range. When SkyWatch detects an intruder aircraft within 0.55
nautical mile horizontal distance and a ±800 ft relative altitude or
detects an intruder aircraft is on a course that will intercept the
SkyWatch airplane’s course within 20 seconds (non-altitude reporting
intruder aircraft) or 30 seconds (altitude reporting intruder aircraft),
SkyWatch will issue a Traffic Advisory (TA). Traffic Advisories are
indicated on the GNS 430 displays and aural “Traffic, Traffic” warnings
are announced in the headphones and cabin speaker.
ATA/
Item
Description Sym Qty Part Number
Unit
Wt
Arm
34-01 SkyWatch Inverter O 1 14484-001 0.5 118.0
34-02 SkyWatch Antenna Instl. O 1 14477-001 2.3 150.5
34-03 SkyWatch Track Box O 1 14477-050 10.0 140.0
34-04 SkyWatch Wiring Instl O 1 14479-001 2.0 145.0
Revision 1: 10-12-05
6 of 6 P/N 11934-S15
Section 9 Cirrus Design
Supplements SR20
SkyWatch may be pilot controlled through the GNS 430 controller.
STBY (standby), OPER (operational), and SELF TEST modes as well
as altitude display (ABV, look up; NRM, normal: BLW, look down; or
UNR, unrestricted) can be selected.
The SkyWatch System consists of a Transmitter Receiver Computer
(TRC) installed under the copilot’s seat just forward of the spar tunnel
and a directional antenna installed on the airplane exterior above the
cabin. The system also utilizes inputs from the altitude encoder, the
aircraft heading system (gyro slaving amplifier), and a speed switch
plumbed into the pitot system. Electrical power for system operation is
28 vdc supplied through the 5-amp SKYWATCH Circuit Breaker on the
Avionics Non-Essential bus.
• Note •
Refer to the L-3 Avionics Systems SkyWatch Pilot’s Guide (P/
N 009-10801-001) for a description of the SkyWatch System.
Refer to the GARMIN Addendum for “Display Interface for
Traffic and Weather Data” P/N 190-001140-10 for additional
operational information and a display description.
Revision 1: 10-12-05
P/N 11934-S27 1 of 16
Cirrus Design Section 9
SR20 Supplements
Pilot’s Operating Handbook and
FAA Approved Airplane Flight Manual
Supplement
For
S-Tec System 55SR Autopilot
When the S-Tec System Fifty Five SR (55SR) Autopilot is installed in
the Cirrus Design SR20, serials 1337 and subsequent, this
Supplement is applicable and must be inserted in the Supplements
Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating
Handbook. This document must be carried in the airplane at all times.
Information in this supplement adds to, supersedes, or deletes
information in the basic SR20 Pilot’s Operating Handbook.
• Note •
This POH Supplement Revision dated Revision 2: 07-18-05
supersedes and replaces Revision 1 of this supplement dated
12-07-04.
Revision 2: 07-18-05
2 of 16 P/N 11934-S27
Section 9 Cirrus Design
Supplements SR20
Section 1 - General
This airplane is equipped with an S-TEC System 55SR Autopilot. The
System 55SR autopilot is a two-axis autopilot system. The system
consists of a flight guidance programmer/computer, altitude
transducer, turn coordinator, and primary flight display (PFD). Mode
selection is made on the programmer/computer panel. A button on
each control yoke handle may be used to disengage the autopilot. The
autopilot makes roll changes through the aileron trim motor and spring
　
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