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8. Ignition Switch..........................................................................OFF
9. Fuel Pump ...............................................................................OFF
10. Flaps (when landing is assured) ............................................100%
11. Master Switches ......................................................................OFF
12. Seat Belt(s) ................................................................... SECURED
March 2010
3-24 Information Manual
Section 3 Cirrus Design
Emergency Procedures SR20
Ditching
1. Radio............................................. Transmit (121.5 MHz) MAYDAY
giving location and intentions
2. Transponder ........................................................... SQUAWK 7700
3. CAPS ............................................................................. ACTIVATE
If available, life preservers should be donned and life raft should
be prepared for immediate evacuation upon touchdown.
Consider unlatching a door prior to assuming the emergency
landing body position in order to provide a ready escape path.
4. Airplane........................................................................ EVACUATE
It may be necessary to allow some cabin flooding to equalize
pressure on the doors. If the doors cannot be opened, break out
the windows with the egress hammer and crawl through the
opening.
5. Flotation Devices.............INFLATE WHEN CLEAR OF AIRPLANE
March 2010
Information Manual 3-25
Cirrus Design Section 3
SR20 Emergency Procedures
Landing Without Elevator Control
The pitch trim spring cartridge is attached directly to the elevator and
provides a backup should you lose the primary elevator control
system. Set elevator trim for a 80 KIAS approach to landing.
Thereafter, do not change the trim setting until in the landing flare.
During the flare, the nose-down moment resulting from a power
reduction may cause the airplane to hit on the nosewheel. At
touchdown, bring the power lever to idle.
1. Flaps ................................................................................SET 50%
2. Trim ............................................................................SET 80 KIAS
3. Power ....................................AS REQUIRED FOR GLIDE ANGLE
March 2010
3-26 Information Manual
Section 3 Cirrus Design
Emergency Procedures SR20
System Malfunctions
Power Lever Linkage Failure
If the Power Lever linkage fails in flight, the engine will not respond to
power lever control movements. Use power available and flaps as
required to safely land the airplane.
If the power lever is stuck at or near the full power position, proceed to
a suitable airfield. Fly a forced landing pattern. With landing assured,
shut down engine by moving mixture control full aft to CUTOFF. If
power is needed again, return mixture control to full RICH and regain
safe pattern parameters or go-around. If airspeed cannot be
controlled, shut engine down and perform the Forced Landing
checklist. After landing, bring the airplane to a stop and complete the
Emergency Engine Shutdown on Ground checklist.
If the power lever is stuck at or near the idle position and straight and
level flight cannot be maintained, establish glide to a suitable landing
surface. Fly a forced landing pattern.
1. Power Lever Movement.....................................................VERIFY
2. Power ............................................................................ SET if able
3. Flaps ........................................................................SET if needed
4. Mixture ..................................... AS REQUIRED (full rich to cut-off)
5. Land as soon as possible.
March 2010
Information Manual 3-27
Cirrus Design Section 3
SR20 Emergency Procedures
Vacuum System Failure
Failure of the engine driven vacuum pump is indicated by illumination
of the red VACUUM warning light. If the engine driven vacuum pump
fails, the electric standby vacuum pump will automatically energize
and the amber AUX VAC caution light will illuminate indicating that the
electric pump is operating and supplying vacuum for instrument
operation.
In the event both vacuum pumps fail in flight, the attitude gyro,
directional gyro (if installed) or optional vacuum operated HSI (if
installed) will be inoperative. The optional electric powered HSI (if
installed) is unaffected by a vacuum system failure. The remaining
gyroscopic instrument will be the electric turn coordinator. The
autopilot uses the turn coordinator gyro for roll attitude information.
1. Consider using the autopilot roll axis to reduce workload. Engage
　
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