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2. Mixture ................................................................... AS REQUIRED
• Caution •
If significant turbulence is expected do not descend at
indicated airspeeds greater than VNO (165 KIAS)
3. Airspeed.................................................................VNE (200 KIAS)
Inadvertent Spiral Dive During IMC Flight
In all cases, if the aircraft enters an unusual attitude from which
recovery is not assured, immediately deploy CAPS. Refer to Section
10, Safety Information, for CAPS deployment information.
1. Power Lever ............................................................................IDLE
2. Stop the spiral dive by using coordinated aileron and rudder
control while referring to the attitude indicator and turn coordinator
to level the wings.
3. Cautiously apply elevator back pressure to bring airplane to level
flight attitude.
4. Trim for level flight.
5. Set power as required.
6. Use autopilot if functional otherwise keep hands off control yoke,
use rudder to hold constant heading.
7. Exit IMC conditions as soon as possible.
March 2010
Information Manual 3-19
Cirrus Design Section 3
SR20 Emergency Procedures
Spins
The SR20 is not approved for spins, and has not been tested or
certified for spin recovery characteristics. The only approved and
demonstrated method of spin recovery is activation of the Cirrus
Airframe Parachute System (See CAPS Deployment, this section).
Because of this, if the aircraft “departs controlled flight”, the CAPS
must be deployed.
While the stall characteristics of the SR20 make accidental entry into a
spin extremely unlikely, it is possible. Spin entry can be avoided by
using good airmanship: coordinated use of controls in turns, proper
airspeed control following the recommendations of this Handbook, and
never abusing the flight controls with accelerated inputs when close to
the stall (see Stalls, Section 4).
If, at the stall, the controls are misapplied and abused accelerated
inputs are made to the elevator, rudder and/or ailerons, an abrupt wing
drop may be felt and a spiral or spin may be entered. In some cases it
may be difficult to determine if the aircraft has entered a spiral or the
beginning of a spin.
• WARNING •
In all cases, if the aircraft enters an unusual attitude from
which recovery is not expected before ground impact,
immediate deployment of the CAPS is required.
The minimum demonstrated altitude loss for a CAPS
deployment from a one-turn spin is 920 feet. Activation at
higher altitudes provides enhanced safety margins for
parachute recoveries. Do not waste time and altitude trying to
recover from a spiral/spin before activating CAPS.
Inadvertent Spin Entry
1. CAPS ................................................................................. Activate
March 2010
3-20 Information Manual
Section 3 Cirrus Design
Emergency Procedures SR20
CAPS Deployment
The Cirrus Airframe Parachute System (CAPS) should be activated in
the event of a life-threatening emergency where CAPS deployment is
determined to be safer than continued flight and landing.
• WARNING •
CAPS deployment is expected to result in loss of the airframe
and, depending upon adverse external factors such as high
deployment speed, low altitude, rough terrain or high wind
conditions, may result in severe injury or death to the
occupants. Because of this, CAPS should only be activated
when any other means of handling the emergency would not
protect the occupants from serious injury.
• Caution •
Expected impact in a fully stabilized deployment is equivalent
to a drop from approximately 10 feet.
• Note •
Several possible scenarios in which the activation of the
CAPS would be appropriate are discussed in Section 10 -
Safety Information, of this Handbook. These include:
• Mid-air collision
• Structural failure
• Loss of control
• Landing in inhospitable terrain
• Pilot incapacitation
All pilots should carefully review the information on CAPS
activation and deployment in Section 10 before operating the
airplane.
Once the decision is made to deploy CAPS, the following actions
should be taken:
1. Airspeed.......................................................MINIMUM POSSIBLE
(Continued on following page)
March 2010
Information Manual 3-21
Cirrus Design Section 3
SR20 Emergency Procedures
The maximum demonstrated deployment speed is 135 KIAS.
Reducing airspeed allows minimum parachute loads and prevents
　
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