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Section 5 - Performance
No Change.
Section 6 - Weight & Balance
No Change.
Section 7 - System Description
Fully integrated with the S-Tec System 55X Autopilot, the Flight
Director system replaces the “flying W” aircraft reference symbol on
the PFD with the Flight Director Steering Command Bars and Wedge.
The system consists of two lighted push-buttons installed on the
upper, LH side of the instrument panel and associated relays and
wiring between the PFD and autopilot. The remaining portion of the
Flight Director system is entirely software dependant.
When a vertical mode of the autopilot is being used, a set of flight
director command bars will indicate the required steering of the aircraft
to achieve the commanded tracking from the autopilot. In autopilot
mode, “AP” will be in the autopilot annunciation field, the command
bars will be visible and magenta and the aircraft should track the bars.
In flight director only mode, “FD” will be displayed in the autopilot
annunciation field, the command bars will be visible and green, and
Revision 2: 12-15-07
4 of 4 P/N 11934-S34
Section 9 Cirrus Design
Supplements SR20
the pilot is expected to actuate the flight controls as required to track
the bars.
The following describes push-button annunciation and related
Autopilot and Flight Director status:
The Flight Director system is powered by 28 VDC through the 5-amp
AUTOPILOT circuit breaker on the Essential Bus.
Refer to Avidyne FlightMax Entegra-Series PFD Pilot’s Guide, for a
more complete description of the Flight Director, its operating modes,
and additional detailed operating procedures.
No
Annunciation
• Autopilot off.
or
• Autopilot not active in either roll or pitch control.
Green
AP ON
Annunciation
• Autopilot active in roll and/or pitch control.
• If Autopilot active in roll and pitch control, “AP”
annunciation appears on top edge of PFD, and
Flight Director Steering Command Bars
MAGENTA.
Amber
AP OFF
FD ON
Annunciation
• Autopilot uncoupled.
• If Autopilot active in roll and pitch control, Flight
Director ON, “FD” annunciation appears on top
edge of PFD, and Flight Director Steering
Command Bars GREEN.
Revision 2: 12-15-07:
P/N 11934-S36 1 of 8
Cirrus Design Section 9
SR20 Supplements
Pilot’s Operating Handbook and
FAA Approved Airplane Flight Manual
Supplement
for
Artex ME406 406 MHz ELT System
When Artex ME406 406 MHz ELT System is installed in the Cirrus
Design SR20, this POH 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.
This POH Supplement Change, dated Revision 01: 12-18-08,
supersedes and replaces the Original release of this POH
Supplement dated 08-15-07.
Revision 01: 12-18-08
2 of 8 P/N 11934-S36
Section 9 Cirrus Design
Supplements SR20
Section 1 - General
The 406 MHz emergency locator transmitter (ELT) is a radio-frequency
transmitter that generates a signal to assist in search and rescue for
missing aircraft. The ELT automatically transmits the standard sweep
tone on 121.5 MHz if rapid deceleration is detected. In addition, for the
first 24 hours of operation, a 406 MHz signal containing aircraft
specific information is transmitted at 50 seconds for 440 milliseconds.
8
CIRCUIT
BREAKER
PANEL
(REF)
4
MOUNTING
TRAY (REF)
SR20_FM09_2676
1
2
3
7
6
1
5
WARNING FORWARD
LEGEND
1. LED Annunciator
2. Remote Switch
3. Antenna
4 Remote Cable
5. Main Control Switch
6. Antenna Jack
7. Attach Straps
8. Artex ME406 ELT
Artex ME406 ELT System
Revision 01: 12-18-08
Figure - 1
P/N 11934-S36 3 of 8
Cirrus Design Section 9
SR20 Supplements
Section 2 - Limitations
No Change.
Section 3 - Emergency Procedures
Forced Landing
Before performing a forced landing activate the ELT transmitter
manually by turning the ELT remote switch to the 'ON'-position.
Immediately after a forced landing, perform the following procedure:
• Note •
The ELT Remote Switch and Control Panel Indicator could be
inoperative in the event of a forced landing. If inoperative, the
　
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