Cirrus DESIGN SR20 Information Manual
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Cirrus DESIGN SR20 Information Manual

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Download this manual See also: Pilot Operating Handbook, Maintenance Manual
AIRPLANE INFORMATION MANUAL
for the
CIRRUS DESIGN SR20
A i r c r a f t S e r i a l s 1 1 4 8 t h r u 1 2 6 7 a n d A i r c r a f t S e r i a l s
1 0 0 5 t h r u 1 1 4 7 a f t e r 3 0 0 0 P o u n d G r o s s W e i g h t
M o d i f i c a t i o n
At the time of issuance, this Information Manual was harmo-
nized with the SR20 Pilot's Operating Handbook Rev A10 (P/N
11934-002), and will not be kept current.
Therefore, this Information Manual is for reference only and can-
not be used as a substitute for the official Pilot's Operating
Handbook and FAA Approved Airplane Flight Manual.
P/N 13999-002
September 2011
Information Manual

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  • Page 1 CIRRUS DESIGN SR20 A i r c r a f t S e r i a l s 1 1 4 8 t h r u 1 2 6 7 a n d A i r c r a f t S e r i a l s...
  • Page 2 Copyright © 2011 - All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811...

  • Page 3: Table Of Contents

    Cirrus Design Section 1 SR20 General Section 1 General Table of Contents Introduction ..................1-3 The Airplane..................1-6 Engine..................1-6 Propeller ..................1-6 Fuel....................1-7 Oil ....................1-7 Maximum Certificated Weights ............ 1-7 Cabin and Entry Dimensions ............1-7 Baggage Spaces and Entry Dimensions ........1-7 Specific Loadings.................
  • Page 4 Section 1 Cirrus Design General SR20 Intentionally Left Blank P/N 13999-002 Info Manual September 2011...

  • Page 5: Introduction

    Cirrus Design Section 1 SR20 General Introduction This section contains information of general interest to pilots and owners. You will find the information useful in acquainting yourself with the airplane, as well as in loading, fueling, sheltering, and handling the airplane during ground operations.
  • Page 6 Section 1 Cirrus Design General SR20 26.0' 9.2' 7" NOTE: • Wing s pan includes position and strobe lights. • Prop ground clearance at 3000 lb - 7" (2 blade), 8" (3 blade). • Wing Area = 135.2 sq. ft.
  • Page 7 Cirrus Design Section 1 SR20 General GROUND TURNING CLEARANCE 11" -RADIUS FOR WING TIP 11" -RADIUS FOR NOSE GEAR 6" -RADIUS FOR INSIDE GEAR 2" -RADIUS FOR OUTSIDE GEAR TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER. ACTUAL TURNING RADIUS MAY VARY AS MUCH AS THREE FEET.

  • Page 8: The Airplane

    Section 1 Cirrus Design General SR20 The Airplane Engine Number of Engines................1 Number of Cylinders................6 Engine Manufacturer ........... Teledyne Continental Engine Model................ IO-360-ES Fuel Metering..............Fuel Injected Engine Cooling ..............Air Cooled Engine Type........Horizontally Opposed, Direct Drive Horsepower Rating..........200 hp @ 2700 rpm...

  • Page 9: Fuel

    Cirrus Design Section 1 SR20 General Fuel Total Capacity..........60.5 U.S. Gallons (229.0 L) Total Usable...........56 U.S. Gallons (212.0 L) Approved Fuel Grades: 100 LL Grade Aviation Fuel (Blue) 100 (Formerly 100/130) Grade Aviation Fuel (Green) Oil Capacity (Sump) ..........8 U.S. Quarts (7.6 L) Oil Grades: All Temperatures ..........SAE 15W-50 or 20W-50...

  • Page 10: Symbols, Abbreviations And Terminology

    Section 1 Cirrus Design General SR20 Symbols, Abbreviations and Terminology General Airspeed Terminology and Symbols KCAS Knots Calibrated Airspeed is the indicated airspeed corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level.

  • Page 11: Meteorological Terminology

    Cirrus Design Section 1 SR20 General Stalling Speed is the minimum steady flight speed at which the aircraft is controllable in the landing configuration (100% flaps) at the most unfavorable weight and balance. Best Angle of Climb Speed is the speed at which the airplane will obtain the highest altitude in a given horizontal distance.

  • Page 12: Engine Power Terminology

    Section 1 Cirrus Design General SR20 • Pressure Altitude is the altitude read from the altimeter when the altimeter’s barometric adjustment has been set to 29.92 in.Hg (1013 mb) corrected for position and instrument error. In this Handbook, altimeter instrument errors are assumed to be zero.

  • Page 13: Weight And Balance Terminology

    Cirrus Design Section 1 SR20 General NMPG Nautical Miles Per Gallon is the distance (in nautical miles) which can be expected per gallon of fuel consumed at a specific engine power setting and/or flight configuration. • Unusable Fuel is the quantity of fuel that cannot be safely used in flight.
  • Page 14 Section 1 Cirrus Design General SR20 • Station is a location along the airplane fuselage measured in inches from the reference datum and expressed as a number. For example: A point 123 inches aft of the reference datum is Fuselage Station 123.0 (FS 123).
  • Page 15 Fuel Limits..................2-15 Altitude Limits................2-15 Environmental Conditions ............. 2-15 Maximum Occupancy ..............2-15 Systems and Equipment Limits............. 2-16 Cirrus Airframe Parachute System (CAPS) ....... 2-16 Multi-Function Display ............... 2-16 Oxygen System ................. 2-17 Inflatable Restraint System............2-17 Flap Limitations................2-17 Paint...................
  • Page 16 Section 2 Cirrus Design Limitations SR20 Intentionally Left Blank P/N 13999-002 Info Manual September 2011...

  • Page 17: Introduction

    Section 9 is required by Federal Aviation Regulations. Certification Status The Cirrus SR20 is certificated under the requirements of Federal Aviation Regulations (FAR) Part 23 as documented by FAA Type Certificate TC A00009CH.

  • Page 18: Airspeed Limitations

    Section 2 Cirrus Design Limitations SR20 Airspeed Limitations The indicated airspeeds in the following table are based upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.

  • Page 19: Airspeed Indicator Markings

    Cirrus Design Section 2 SR20 Limitations Airspeed Indicator Markings The airspeed indicator markings are based upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.

  • Page 20: Power Plant Limitations

    Section 2 Cirrus Design Limitations SR20 Power Plant Limitations Engine Teledyne Continental ............IO-360-ES Power Rating ............200 hp @ 2700 rpm Maximum RPM ...............2700 rpm Oil: Oil Temperature........240° F (115° C) maximum Oil Pressure: Minimum................10 psi Maximum................100 psi...

  • Page 21: Propeller

    Cirrus Design Section 2 SR20 Limitations Propeller • Note • Two-blade propellers are not EASA approved for use on this airplane. Airplanes registered in the European Union should ignore all references to the two-blade propeller in this POH. Hartzell Propeller Type ............. Constant Speed Two-Blade Propeller: Model Number...........

  • Page 22: Instrument Markings

    Section 2 Cirrus Design Limitations SR20 Instrument Markings Red Line Green Arc Yellow Arc Red Line Instrument (Range) Minimum Normal Caution Maximum Power Plant Instrumentation Tachometer –– 500 - 2700 –– 2700 (0 - 3500 RPM) Cylinder Head –– 240° - 420°...

  • Page 23: Center Of Gravity Limits

    Cirrus Design Section 2 SR20 Limitations Center of Gravity Limits Reference Datum ........100 inches forward of firewall Forward ..............Refer to Figure 2-4 Aft ................Refer to Figure 2-4 23.1 % MAC FS 144.1 3000 lb 3000 31.3 % MAC FS 148.0...

  • Page 24: Maneuver Limits

    Aerobatic maneuvers, including spins, are prohibited. • Note • Because the SR20 has not been certified for spin recovery, the Cirrus Airframe Parachute System (CAPS) must be deployed if the airplane departs controlled flight. Refer to Section 3 – Emergency Procedures, Inadvertent Spiral/Spin Entry.

  • Page 25: Kinds Of Operation

    Cirrus Design Section 2 SR20 Limitations Kinds of Operation The SR20 is equipped and approved for the following type operations: • VFR day and night. • IFR day and night. Kinds of Operation Equipment List The following listing summarizes the equipment required under Federal Aviation Regulations (FAR) Part 23 for airworthiness under the listed kind of operation.
  • Page 26 Section 2 Cirrus Design Limitations SR20 Kinds of Operation System, Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Emergency Locator Transmitter Restraint System One Seat Belt for each occupant. Fire Protection Fire Extinguisher Flight Controls Flap Position Lights Flap System Pitch Trim Indicator...
  • Page 27 Cirrus Design Section 2 SR20 Limitations Kinds of Operation System, Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Wheel Pants — — — — May be removed. Lights Anticollision Lights    - Must be operative. Instrument Lights — —...

  • Page 28: Icing

    Section 2 Cirrus Design Limitations SR20 Kinds of Operation System, Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Cylinder Head — — — — Temperature Gage Exhaust Gas — — — — Temperature Gage Fuel Flow Gage Manifold Pressure Gage Oil Pressure Gage...

  • Page 29: Taxi Power

    Refer to Oxygen System Limitations in this Section. Environmental Conditions For operation of the airplane below an outside air temperature of -10°F (-23° C), use of cowl inlet covers approved by Cirrus Design and listed in the Winterization Kit AFM Supplement P/N 11934-S25 is required. Maximum Occupancy Occupancy of this airplane is limited to four persons (the pilot and three passengers).

  • Page 30: Systems And Equipment Limits

    Section 2 Cirrus Design Limitations SR20 Systems and Equipment Limits Cirrus Airframe Parachute System (CAPS) Maximum Demonstrated Deployment Speed....135 KIAS • Note • Refer to Section 10 – Safety Information, for additional CAPS guidance. Multi-Function Display 1. The moving map display must not be used as the primary navigation instrument.

  • Page 31: Oxygen System

    Oxygen System Whenever the operating rules require the use of supplemental oxygen, the pilot must: • Use an oxygen system approved by Cirrus Design and listed in the Oxygen System AFM Supplement Part Number 11934- S09. • Secure the oxygen bottle in the right front seat as described in the AFM Supplement noted above.

  • Page 32: Other Limitations

    Section 2 Cirrus Design Limitations SR20 Other Limitations Smoking Smoking is prohibited in this airplane. 2-18 P/N 13999-002 Info Manual September 2011...

  • Page 33: Placards

    Cirrus Design Section 2 SR20 Limitations Placards Engine compartment, inside oil filler access: ENGINE OIL GRADE ABOVE 40° F SAE 50 OR 20W50 BELOW 40° F SAE 30 OR 10W30, 15W50, OR 20W50 REFER TO AFM FOR APPROVED OILS Wing, adjacent to fuel filler caps: AVGAS MIN GRADE 100LL OR 100 28 U.S.
  • Page 34 Section 2 Cirrus Design Limitations SR20 Upper fuselage, either side of CAPS rocket cover: WARNING! ROCKET FOR PARACHUTE DEPLOYMENT INSIDE STAY CLEAR WHEN AIRPLANE IS OCCUPIED Left fuselage, on external Rudder, and elevator, both sides: power supply door: EXTERNAL NO PUSH...
  • Page 35 Cirrus Design Section 2 SR20 Limitations Engine control panel: 120 KIAS FLAPS FLAPS 100% 100% 100 KIAS Airplane serials 1020 and subsequent and airplane serials 1005 thru 1019 incorporating SB 20-11-01. OPEN RICH FULL RICH OPEN BOOST FUEL BOOST PUMP...
  • Page 36 Section 2 Cirrus Design Limitations SR20 Engine control panel (cont): 120 KIAS 120 KIAS FLAPS FLAPS 100% 100% 100 KIAS 100 KIAS CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT FULL RICH FULL RICH...
  • Page 37 Cirrus Design Section 2 SR20 Limitations Wing, flap aft edge: NO STEP Cabin Door Window, lower edge, centered, applied upside down: RESCUE: FRACTURE AND REMOVE WINDOW Bolster Switch Panel, left edge: THIS AIRCRAFT IS CERTIFIED FOR THE FOLLOWING FLIGHT OPERATIONS:...
  • Page 38 Section 2 Cirrus Design Limitations SR20 Bolster Panel, both sides: GRAB HERE Serials 1351 & subs. Instrument Panel: NO SMOKING FASTEN SEATBELTS Serials 1005 thru 1638. FASTEN SEAT BELT • NO SMOKING FIRE EXTINGUISHER FORWARD LEFT OF PILOT SEAT Serials 1639 & subs.
  • Page 39 Cirrus Design Section 2 SR20 Limitations Baggage Compartment, aft edge: ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Baggage Compartment Door, inside: DISTRIBUTED FLOOR LIMIT 130 LBS BAGGAGE STRAP CAPACITY IS 35 LBS EACH MAXIMUM SEE AIRPLANE FLIGHT MANUAL FOR BAGGAGE TIE-DOWN...
  • Page 40 5. MASTER SWITCH......OFF 6. RESTRAINT SYSTEM....SECURE WARNING THIS AIRCRAFT IS EQUIPPED WITH A 12390-001 CIRRUS AIRFRAME PARACHUTE SYSTEM USE FOR EXTREME EMERGENCIES ONLY SEAT BELT AND SHOULDER HARNESS MUST BE WORN AT ALL TIMES Serials 1005 thru 1099. USE OF THIS DEVICE COULD RESULT...
  • Page 41 MUST BE WORN AT ALL TIMES USE OF THIS DEVICE COULD RESULT IN INJURY OR DEATH MAXIMUM DEMONSTRATED DEPLOYMENT SPEED 135 KIAS CIRRUS AIRFRAME PARACHUTE SYSTEM ACTIVATION PROCEDURE 1. FUEL MIXTURE........CUT-OFF 2. THIS COVER..........REMOVE 3. ACTIVATION HANDLE..PULL STRAIGHT DOWN BOTH HANDS, MAXIMUM FORCE, STEADY PULL DO NOT JERK HANDLE 4.
  • Page 42 Section 2 Cirrus Design Limitations SR20 Intentionally Left Blank 2-28 P/N 13999-002 Info Manual September 2011...
  • Page 43 Cirrus Design Section 3 SR20 Emergency Procedures Section 3 Emergency Procedures Table of Contents Introduction ..................3-3 Airspeeds for Emergency Operations ..........3-4 Emergency Procedures Guidance ..........3-5 Preflight Planning................. 3-5 Preflight Inspections/Maintenance ..........3-5 Methodology ................3-5 Memory Items ................3-6 Ground Emergencies ..............3-7...
  • Page 44 Section 3 Cirrus Design Emergency Procedures SR20 Vacuum System Failure.............3-27 P/N 13999-002 Info Manual September 2011...

  • Page 45: Introduction

    Cirrus Design Section 3 SR20 Emergency Procedures Introduction This section provides procedures for handling emergencies and critical flight situations that may occur while operating the SR20. Although emergencies caused by airplane, systems, or engine malfunctions are extremely rare, the guidelines described in this section should be considered and applied as necessary should an emergency arise.

  • Page 46: Airspeeds For Emergency Operations

    Section 3 Cirrus Design Emergency Procedures SR20 Airspeeds for Emergency Operations Maneuvering Speed: 3000 lb ................131 KIAS 2600 lb ................122 KIAS 2200 lb ................111 KIAS Best Glide: 3000 lb ................96 KIAS 2500 lb ................87 KIAS Emergency Landing (Engine-out): Flaps Up................86 KIAS Flaps 50% ................81 KIAS...

  • Page 47: Emergency Procedures Guidance

    Cirrus Design Section 3 SR20 Emergency Procedures Emergency Procedures Guidance Although this section provides procedures for handling most emergencies and critical flight situations that could arise in the SR20, it is not a substitute for thorough knowledge of the airplane and general aviation techniques.

  • Page 48: Memory Items

    Follow them and use good pilot judgment. 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.

  • Page 49: Ground Emergencies

    Cirrus Design Section 3 SR20 Emergency Procedures Ground Emergencies Engine Fire During Start A fire during engine start may be caused by fuel igniting in the fuel induction system. If this occurs, attempt to draw the fire back into the engine by continuing to crank the engine.

  • Page 50: Emergency Ground Egress

    Section 3 Cirrus Design Emergency Procedures SR20 Emergency Ground Egress • WARNING • While exiting the airplane, make sure evacuation path is clear of other aircraft, spinning propellers, and other hazards. 1. Engine................SHUTDOWN • Note • If the engine is left running, set the Parking Brake prior to evacuating the airplane.

  • Page 51: In-Flight Emergencies

    Cirrus Design Section 3 SR20 Emergency Procedures In-Flight Emergencies Engine Failure On Takeoff (Low Altitude) If the engine fails immediately after becoming airborne, abort on the runway if possible. If altitude precludes a runway stop but is not sufficient to restart the engine, lower the nose to maintain airspeed and establish a glide attitude.

  • Page 52: Maximum Glide

    Section 3 Cirrus Design Emergency Procedures SR20 Maximum Glide Conditions Example: Power Altitude 7,000 ft. AGL Propeller Windmilling Airspeed Best Glide Flaps 0% (UP) Wind Zero Glide Distance 12.5 NM Best Glide Speed 3000 lb 96 KIAS 2500 lb 87 KIAS Maximum Glide Ratio ~ 10.9 : 1...

  • Page 53: Engine Failure In Flight

    Cirrus Design Section 3 SR20 Emergency Procedures Engine Failure In Flight If the engine fails at altitude, pitch as necessary to establish best glide speed. While gliding toward a suitable landing area, attempt to identify the cause of the failure and correct it. If altitude or terrain does not permit a safe landing, CAPS deployment may be required.

  • Page 54: Engine Airstart

    Section 3 Cirrus Design Emergency Procedures SR20 Engine Airstart The following procedures address the most common causes for engine loss. Switching tanks and turning the fuel pump on will enhance starting if fuel contamination was the cause of the failure.

  • Page 55: Engine Partial Power Loss

    Cirrus Design Section 3 SR20 Emergency Procedures Engine Partial Power Loss Indications of a partial power loss include fluctuating RPM, reduced or fluctuating manifold pressure, low oil pressure, high oil temperature, and a rough-sounding or rough-running engine. Mild engine roughness in flight may be caused by one or more spark plugs becoming fouled.

  • Page 56: Fuel Pump (If Used)

    Section 3 Cirrus Design Emergency Procedures SR20 The following procedure provides guidance to isolate and correct some of the conditions contributing to a rough running engine or a partial power loss: 1. Fuel Pump................BOOST Selecting BOOST on may clear the problem if vapor in the injection lines is the problem or if the engine-driven fuel pump has partially failed.

  • Page 57: Low Oil Pressure

    Cirrus Design Section 3 SR20 Emergency Procedures Low Oil Pressure If low oil pressure is accompanied by a rise in oil temperature, the engine has probably lost a significant amount of its oil and engine failure may be imminent. Immediately reduce engine power to idle and select a suitable forced landing field.

  • Page 58: Smoke And Fume Elimination

    Section 3 Cirrus Design Emergency Procedures SR20 Smoke and Fume Elimination If smoke and/or fumes are detected in the cabin, check the engine parameters for any sign of malfunction. If a fuel leak has occurred, actuation of electrical components may cause a fire. If there is a strong smell of fuel in the cockpit, divert to the nearest suitable landing field.

  • Page 59: Cabin Fire In Flight

    Cirrus Design Section 3 SR20 Emergency Procedures Cabin Fire In Flight If the cause of the fire is readily apparent and accessible, use the fire extinguisher to extinguish flames and land as soon as possible. Opening the vents or doors may feed the fire, but to avoid incapacitating the crew from smoke inhalation, it may be necessary to rid cabin of smoke or fire extinguishant.

  • Page 60: Emergency Descent

    Section 3 Cirrus Design Emergency Procedures SR20 switches OFF. Do not attempt to isolate the source of the fire by checking each individual electrical component. 10. Bat-Alt Master Switches ............ON 11. Avionics Power Switch .............. ON 12. Activate required systems one at a time. Pause several seconds between activating each system to isolate malfunctioning system.

  • Page 61: 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).

  • Page 62: Caps Deployment

    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...
  • Page 63 Cirrus Design Section 3 SR20 Emergency Procedures The maximum demonstrated deployment speed is 135 KIAS. Reducing airspeed allows minimum parachute loads and prevents structural overload and possible parachute failure. 2. Mixture (If time and altitude permit) ........CUTOFF Generally, a distressed airplane will be safer for its occupants if the engine is not running.
  • Page 64 Section 3 Cirrus Design Emergency Procedures SR20 All occupants must have seat belts and shoulder harness securely fastened. 12. Loose Items ..............SECURE If time permits, all loose items should be secured to prevent injury from flying objects in the cabin at touchdown.

  • Page 65: Landing Emergencies

    Cirrus Design Section 3 SR20 Emergency Procedures Landing Emergencies If all attempts to restart the engine fail and a forced landing is imminent, select a suitable field and prepare for the landing. If flight conditions or terrain does not permit a safe landing, CAPS deployment may be required.

  • Page 66: Ditching

    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.

  • Page 67: Landing Without Elevator Control

    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.

  • Page 68: System Malfunctions

    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.
  • Page 69 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...
  • Page 70 Section 3 Cirrus Design Emergency Procedures SR20 Intentionally Left Blank 3-28 P/N 13999-002 Info Manual September 2011...
  • Page 71 Cirrus Design Section 3A SR20 Abnormal Procedures Section 3A Abnormal Procedures Table of Contents Introduction .................. 3A-3 Abnormal Procedures Guidance ..........3A-4 Ground Procedures..............3A-5 Brake Failure During Taxi ............3A-5 Aborted Takeoff ................ 3A-5 In-Flight Procedures..............3A-6 Inadvertent Icing Encounter ............3A-6 Inadvertent IMC Encounter............
  • Page 72 Section 3A Cirrus Design Abnormal Procedures SR20 Intentionally Left Blank 3A-2 P/N 13999-002 Info Manual September 2011...

  • Page 73: Section 3A

    Cirrus Design Section 3A SR20 Abnormal Procedures Introduction This section provides procedures for handling abnormal system and/or flight conditions which, if followed, will maintain an acceptable level of airworthiness or reduce operational risk. The guidelines described in this section are to be used when an abnormal condition exists and should be considered and applied as necessary.

  • Page 74: Abnormal Procedures Guidance

    Section 3A Cirrus Design Abnormal Procedures SR20 Abnormal Procedures Guidance Although this section provides procedures for handling most abnormal system and/or flight conditions that could arise in the SR20, it is not a substitute for thorough knowledge of the airplane and general aviation techniques.

  • Page 75: Ground Procedures

    Cirrus Design Section 3A SR20 Abnormal Procedures Ground Procedures Brake Failure During Taxi Ground steering is accomplished by differential braking. However, increasing power may allow some rudder control due to increased groundspeed and airflow over the rudder. 1. Engine Power............AS REQUIRED •...

  • Page 76: In-Flight Procedures

    Section 3A Cirrus Design Abnormal Procedures SR20 In-Flight Procedures Inadvertent Icing Encounter Flight into known icing conditions is prohibited. However, If icing is inadvertently encountered: 1. Pitot Heat .................. ON 2. Exit icing conditions. Turn back or change altitude. 3. Cabin Heat ..............MAXIMUM 4.

  • Page 77: Landing Procedures

    Cirrus Design Section 3A SR20 Abnormal Procedures Landing Procedures Landing With Failed Brakes One brake inoperative 1. Land on the side of runway corresponding to the inoperative brake. 2. Maintain directional control using rudder and working brake. Both brakes inoperative 1.

  • Page 78: System Malfunctions

    Section 3A Cirrus Design Abnormal Procedures SR20 System Malfunctions Alternator Failure Abnormal ammeter indications and illumination of the LOW VOLTS warning light indicate electrical power supply system malfunctions. A broken alternator drive belt, wiring fault or a defective alternator control unit is most likely the cause of the alternator failure.

  • Page 79: Low Volts Warning Light Illuminated

    Cirrus Design Section 3A SR20 Abnormal Procedures should be completed. Battery power must be conserved for later operation of the wing flaps, lights, and other essential equipment. • Note • Ammeter discharge indications and illumination of the LOW VOLTS warning light can occur during low RPM conditions with a heavy electrical load, such as during taxi.

  • Page 80: Communications Failure

    Section 3A Cirrus Design Abnormal Procedures SR20 Communications Failure Communications failure can occur for a variety of reasons. If, after following the checklist procedure, communication is not restored, proceed with FAR/AIM lost communications procedures. • Note • In the event of an audio panel power failure the audio panel connects COM 1 to the pilot’s headset and speakers.

  • Page 81: Pitot Static Malfunction

    Cirrus Design Section 3A SR20 Abnormal Procedures Pitot Static Malfunction Static Source Blocked If erroneous readings of the static source instruments (airspeed, altimeter and vertical speed) are suspected, the alternate static source valve, on side of console near pilot’s right ankle, should be opened to supply static pressure from the cabin to these instruments.

  • Page 82: Electric Trim/Autopilot Failure

    Section 3A Cirrus Design Abnormal Procedures SR20 Electric Trim/Autopilot Failure Any failure or malfunction of the electric trim or autopilot can be over- ridden by use of the control yoke. If runaway trim is the problem, de- energize the circuit by pulling the circuit breaker (PITCH TRIM, ROLL TRIM, or AUTOPILOT) and land as soon as conditions permit.
  • Page 83 Cirrus Design Section 4 SR20 Normal Procedures Section 4 Normal Procedures Table of Contents Introduction ..................4-3 Airspeeds for Normal Operation ............. 4-4 Normal Procedures ................. 4-5 Preflight Inspection ..............4-5 Preflight Walk-Around ..............4-6 Before Starting Engine............... 4-10 Starting Engine ................4-11 Before Taxiing................
  • Page 84 Section 4 Cirrus Design Normal Procedures SR20 Intentionally Left Blank P/N 13999-002 Info Manual September 2011...

  • Page 85: Introduction

    Cirrus Design Section 4 SR20 Normal Procedures Introduction This section provides amplified procedures for normal operation. Normal procedures associated with optional systems can be found in Section 9. P/N 13999-002 Info Manual September 2011...

  • Page 86: Airspeeds For Normal Operation

    Section 4 Cirrus Design Normal Procedures SR20 Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3000 lb. and may be used for any lesser weight. However, to achieve the performance specified in Section 5 for takeoff distance, the speed appropriate to the particular weight must be used.

  • Page 87: Normal Procedures

    Cirrus Design Section 4 SR20 Normal Procedures Normal Procedures Preflight Inspection Before carrying out preflight inspections, ensure that all required maintenance has been accomplished. Review your flight plan and compute weight and balance. • Note • Throughout the walk-around: check all hinges, hinge pins, and bolts for security;...

  • Page 88: Preflight Walk-Around

    Section 4 Cirrus Design Normal Procedures SR20 Preflight Walk-Around 1. Cabin a. Required Documents..........On Board b. Avionics Power Switch............OFF c. Bat 2 Master Switch ............ON d. Avionics Cooling Fan ............ Audible e. Voltmeter ..............23-25 Volts Flap Position Light ............OUT g.
  • Page 89 Cirrus Design Section 4 SR20 Normal Procedures e. Baggage Door ........... Closed and Secure Static Button ..........Check for Blockage g. Parachute Cover........Sealed and Secure 3. Empennage a. Tiedown Rope .............Remove b. Horizontal and Vertical Stabilizers......Condition • Note •...
  • Page 90 Section 4 Cirrus Design Normal Procedures SR20 c. Fuel Drains (2 underside) ......Drain and Sample d. Wheel Fairings...... Security, Accumulation of Debris e. Tire ..........Condition, Inflation, and Wear • Note • Serials 1005 through 1592 after Service Bulletin SB 2X-32-14 and airplane serials 1593 and subsequent: Clean and inspect temperature indicator installed to piston housing.
  • Page 91 Cirrus Design Section 4 SR20 Normal Procedures 10. Nose, Left Side a. Landing Light............. Condition b. Engine Oil..Check 6-8 quarts, Leaks, Cap & Door Secure c. Cowling.............Attachments Secure d. External Power ............. Door Secure e. Exhaust Pipe .....Condition, Security, and Clearance 11.

  • Page 92: Before Starting Engine

    Section 4 Cirrus Design Normal Procedures SR20 Before Starting Engine 1. Preflight Inspection ..........COMPLETED • WARNING • Ensure that the airplane is properly loaded and within the AFM’s weight and balance limitations prior to takeoff. 2. Weight and Balance ..........Verify within limits 3.

  • Page 93: Starting Engine

    Cirrus Design Section 4 SR20 Normal Procedures Starting Engine If the engine is warm, no priming is required. For the first start of the day and in cold conditions, prime will be necessary. Weak intermittent firing followed by puffs of black smoke from the exhaust stack indicates over-priming or flooding.
  • Page 94 Section 4 Cirrus Design Normal Procedures SR20 3. Bat Master Switch ..........ON (Check Volts) 4. Strobe Lights ................ON 5. Vacuum System ..............CHECK a. VACUUM Annunciator ............ON b. AUX Vac Annunciator ........ON (Pump Green) c. Suction Gage............GREEN ARC d.

  • Page 95: Before Taxiing

    Cirrus Design Section 4 SR20 Normal Procedures 15. Alt Master Switches ..............ON 16. Avionics Power Switch ...............ON 17. Engine Parameters ............MONITOR 18. External Power (If applicable) ......... DISCONNECT 19. Amp Meter/Indication ............CHECK Before Taxiing 1. Flaps ................. UP (0%) 2.

  • Page 96: Before Takeoff

    Section 4 Cirrus Design Normal Procedures SR20 Before Takeoff During cold weather operations, the engine should be properly warmed up before takeoff. In most cases this is accomplished when the oil temperature has reached at least 100° F (38° C). In warm or hot weather, precautions should be taken to avoid overheating during prolonged ground engine operation.
  • Page 97 Cirrus Design Section 4 SR20 Normal Procedures 16. Pitot Heat ............... AS REQUIRED • Note • Pitot Heat should be turned ON for flight into IMC, flight into visible moisture, or whenever ambient temperatures are 41° F (5° C) or less.

  • Page 98: Takeoff

    Section 4 Cirrus Design Normal Procedures SR20 Takeoff • Note • The engine is equipped with an altitude compensating fuel pump that automatically provides the proper full rich mixture. Because of this, the mixture should be left full rich for takeoff, even at high altitude airfields.

  • Page 99: Normal Takeoff

    Cirrus Design Section 4 SR20 Normal Procedures Normal Takeoff 1. Brakes........RELEASE (Steer with Rudder Only) 2. Power Lever ............FULL FORWARD 3. Engine Parameters ............CHECK 4. Elevator Control ......ROTATE Smoothly at 65-70 KIAS 5. At 85 KIAS, Flaps............... UP Short Field Takeoff 1.

  • Page 100: Climb

    Section 4 Cirrus Design Normal Procedures SR20 Climb Normal climbs are performed flaps UP (0%) and full power at speeds 5 to 10 knots higher than best rate-of-climb speeds. These higher speeds give the best combination of performance, visibility and engine cooling.

  • Page 101: Cruise

    Cirrus Design Section 4 SR20 Normal Procedures Cruise Normal cruising is performed between 55% and 75% power. The engine power setting and corresponding fuel consumption for various altitudes and temperatures can be determined by using the cruise data in Section 5.

  • Page 102: Cruise Leaning

    Section 4 Cirrus Design Normal Procedures SR20 Cruise Leaning The engine is equipped with an altitude compensating fuel pump that automatically provides the proper full rich mixture. Because of this, the mixture should be set to full rich to allow the aneroid to provide auto leaning for the engine during all flight conditions.

  • Page 103: Descent

    Cirrus Design Section 4 SR20 Normal Procedures Descent 1. Altimeter................... SET 2. Cabin Heat/Defrost ..........AS REQUIRED 3. Landing Light ................ON 4. Fuel System ............... CHECK 5. Mixture ..............AS REQUIRED 6. Brake Pressure ..............CHECK Before Landing 1. Seat Belt and Shoulder Harness ........SECURE 2.

  • Page 104: Balked Landing/Go-Around

    Section 4 Cirrus Design Normal Procedures SR20 Short Field Landing For a short field landing in smooth air conditions, make an approach at 75 KIAS with full flaps using enough power to control the glide path (slightly higher approach speeds should be used under turbulent air conditions).

  • Page 105: After Landing

    Cirrus Design Section 4 SR20 Normal Procedures After Landing 1. Power Lever ..............1000 RPM 2. Fuel Pump ................OFF 3. Flaps ..................UP 4. Transponder ................STBY 5. Lights ..............AS REQUIRED 6. Pitot Heat ................. OFF • Note •...

  • Page 106: Stalls

    Section 4 Cirrus Design Normal Procedures SR20 Stalls SR20 stall characteristics are conventional. Power-off stalls may be accompanied by a slight nose bobbing if full aft stick is held. Power-on stalls are marked by a high sink rate at full aft stick. Power-off stall speeds at maximum weight for both forward and aft C.G.

  • Page 107: Environmental Considerations

    Cirrus Design Section 4 SR20 Normal Procedures Environmental Considerations Cold Weather Operation Starting If the engine has been cold soaked, it is recommended that the propeller be pulled through by hand several times to break loose or limber the oil. This procedure will reduce power draw on the battery if a battery start is made.
  • Page 108 Section 4 Cirrus Design Normal Procedures SR20 Hot air must be applied directly to the oil sump and external oil lines as well as the cylinders, air intake and oil cooler. Because excessively hot air can damage non-metallic components such as composite parts, seals, hoses, and drives belts, do not attempt to hasten the preheat process.

  • Page 109: Hot Weather Operation

    Cirrus Design Section 4 SR20 Normal Procedures (Continued on following page) 11. Power Lever ............OPEN ¼ INCH 12. Ignition Switch....... START (Release after engine starts) • Caution • Limit cranking to intervals of 20 seconds with a 20 second cooling period between cranks.

  • Page 110: Noise Characteristics/Abatement

    Section 4 Cirrus Design Normal Procedures SR20 Noise Characteristics/Abatement The certificated noise levels for the Cirrus Design SR20 established in accordance with FAR 36 Appendix G are: Configuration Actual Maximum Allowable Two-blade Propeller 84.79 dB(A) 87.6 dB(A) Three-blade Propeller 83.42 dB(A) 87.6 dB(A)
  • Page 111 Cirrus Design Section 5 SR20 Performance Data Section 5 Performance Data Table of Contents Introduction ..................5-3 Associated Conditions Affecting Performance......5-3 Flight Planning ................5-4 Sample Problem ................5-4 Takeoff..................5-5 Climb.................... 5-6 Cruise ..................5-7 Fuel Required ................5-8 Landing ..................
  • Page 112 Section 5 Cirrus Design Performance Data SR20 Range / Endurance Profile ............5-29 Range / Endurance Profile ............5-30 Balked Landing Climb Gradient ............5-31 Balked Landing Rate of Climb............5-32 Landing Distance ................5-33 Landing Distance ................5-34 P/N 13999-002 Info Manual September 2011...

  • Page 113: Introduction

    Cirrus Design Section 5 SR20 Performance Data Introduction Performance data in this section are presented for operational planning so that you will know what performance to expect from the airplane under various ambient and field conditions. Performance data are presented for takeoff, climb, and cruise (including range &...

  • Page 114: Flight Planning

    Section 5 Cirrus Design Performance Data SR20 Flight Planning The performance tables in this section present sufficient information to predict airplane performance with reasonable accuracy. However, variations in fuel metering, mixture leaning technique, engine & propeller condition, air turbulence, and other variables encountered during a particular flight may account for variations of 10% or more in range and endurance.
  • Page 115 Cirrus Design Section 5 SR20 Performance Data Cruise Conditions: • Total distance ..........560 Nautical Miles • Pressure altitude ............6500 Feet • Temperature ..........20° C (ISA + 17° C) • Expected wind enroute........10 Knot Headwind Landing Conditions: • Field pressure altitude ..........2000 Feet •...

  • Page 116: Climb

    Section 5 Cirrus Design Performance Data SR20 • Decrease in total distance (2734 feet x 0.092) ....252 feet • Corrected total distance to clear 50-foot obstacle ..2482 feet Corrections for grass runways and sloped runways are also applicable and should be applied.

  • Page 117: Cruise

    Cirrus Design Section 5 SR20 Performance Data climb performance is to increase the time, fuel, and distance to climb by approximately 10% for each 10° C above ISA. In our example, using a temperature of ISA + 13° C, the correction to be applied is 13%.

  • Page 118: Fuel Required

    Section 5 Cirrus Design Performance Data SR20 Fuel Required The total fuel requirement for the flight may be estimated using the performance information obtained from Figures 5-15 and 5-16. The resultant cruise distance is: • Total distance (from sample problem) ......560.0 NM •...

  • Page 119: Landing

    Cirrus Design Section 5 SR20 Performance Data Landing A procedure similar to takeoff should be used for estimating the landing distance at the destination airport. Figure 5-20 presents landing distance information for the short field technique. The distances corresponding to 2000 feet and 20° C are as follows: •...

  • Page 120: Airspeed Calibration

    Section 5 Cirrus Design Performance Data SR20 Airspeed Calibration Normal Static Source Conditions: Example: • Power for level flight or maximum Flaps ........... 50% continuous, whichever is less. Indicated Airspeed ....85 Knots • Weight ........3000 LB Calibrated Airspeed ..... 86 Knots •...

  • Page 121: Airspeed Calibration

    Cirrus Design Section 5 SR20 Performance Data Airspeed Calibration Alternate Static Source Conditions: Example: • Power for level flight or maximum Flaps..........50% continuous, whichever is less. Indicated Airspeed....85 Knots • Weight ........3000 LB • Heater, Defroster & Vents .....ON Calibrated Airspeed ....84 Knots •...

  • Page 122: Altitude Correction

    Section 5 Cirrus Design Performance Data SR20 Altitude Correction Normal Static Source Conditions: Example: • Power for level flight or maximum Flaps ........... 50% continuous, whichever is less. Indicated Airspeed ....85 Knots • Weight ........3000 LB Desired Altitude....12,000 FT Altitude Correction .....-7 FT...

  • Page 123: Altitude Correction

    Cirrus Design Section 5 SR20 Performance Data Altitude Correction Alternate Static Source Conditions: Example: • Power for level flight or maximum Flaps..........0% continuous, whichever is less. Indicated Airspeed....120 Knots • Weight ........3000 LB Desired Altitude ....12,000 FT • Heater, Defroster, & Vents.....ON Altitude Correction....

  • Page 124: Temperature Conversion

    Section 5 Cirrus Design Performance Data SR20 Temperature Conversion • Note • • To convert from Celsius (°C) to Fahrenheit (°F), find, in the shaded columns, the number representing the temperature value (°C) to be converted. The equivalent Fahrenheit temperature is read to the right.

  • Page 125: Outside Air Temperature For Isa Condition

    Cirrus Design Section 5 SR20 Performance Data Outside Air Temperature ISA Condition Example: Pressure Altitude....8000 FT Outside Air Temp....... 48° F ISA Condition ....ISA + 10° C Press ISA-40°C ISA-20°C ISA+10°C ISA+20°C Feet °C °F °C °F °C °F °C...

  • Page 126: Stall Speeds

    Section 5 Cirrus Design Performance Data SR20 Stall Speeds Conditions: Example: • Weight ........3000 LB Flaps ........Up (0%) • C.G........... Noted Bank Angle........15° • Power..........Idle • Bank Angle ....... Noted Stall Speed..66 KIAS | 68 KCAS •...

  • Page 127: Wind Components

    Cirrus Design Section 5 SR20 Performance Data Wind Components Conditions: Example: • Runway Heading ......10° Wind/Flight Path Angle ....50° • Wind Direction.......60° Crosswind Component ..12 Knots • Wind Velocity......15 Knots Headwind Component..10 Knots • Note • • The maximum demonstrated crosswind is 21 knots. Value not considered limiting.

  • Page 128: Takeoff Distance

    Section 5 Cirrus Design Performance Data SR20 Takeoff Distance Conditions: Example: • Winds.......... Zero Outside Air Temp ....... 25°C • Runway....Dry, Level, Paved Weight........3000 LB • Flaps........... 50% Pressure Altitude....2000 FT • Power........Maximum Headwind ......12 Knots set before brake release Runway ......
  • Page 129 Cirrus Design Section 5 SR20 Performance Data Takeoff Distance WEIGHT = 3000 LB Headwind: Subtract 10% for each 12 Speed at Liftoff = 68 KIAS knots headwind. Speed over 50 Ft. Obstacle = 75 KIAS Tailwind: Add 10% for each 2 knots Flaps - 50% ·...

  • Page 130: Takeoff Distance

    Section 5 Cirrus Design Performance Data SR20 Takeoff Distance WEIGHT = 2500 LB Headwind: Subtract 10% for each 12 Speed at Liftoff = 65 KIAS knots headwind. Speed over 50 Ft Obstacle = 70 KIAS Tailwind: Add 10% for each 2 knots Flaps - 50% ·...

  • Page 131: Takeoff Climb Gradient

    Cirrus Design Section 5 SR20 Performance Data Takeoff Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ......... Full Rich Weight ........3000 LB • Flaps ........... 50% Pressure Altitude ....1750 FT •...

  • Page 132: Takeoff Rate Of Climb

    Section 5 Cirrus Design Performance Data SR20 Takeoff Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 20° C • Mixture........Full Rich Weight........3000 LB • Flaps........... 50% Pressure Altitude....1750 FT • Airspeed ....Best Rate of Climb Climb Airspeed.....

  • Page 133: Enroute Climb Gradient

    Cirrus Design Section 5 SR20 Performance Data Enroute Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ......... Full Rich Weight ........3000 LB • Flaps ........0% (UP) Pressure Altitude ....4200 FT •...

  • Page 134: Enroute Rate Of Climb

    Section 5 Cirrus Design Performance Data SR20 Enroute Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 10° C • Mixture........Full Rich Weight........3000 LB • Flaps........0% (UP) Pressure Altitude....6500 FT • Airspeed ....Best Rate of Climb Climb Airspeed.....

  • Page 135: Enroute Rate Of Climb Vs Density Altitude

    Cirrus Design Section 5 SR20 Performance Data Enroute Rate of Climb Vs Density Altitude Conditions: • Power ....................Full Throttle • Mixture ....................... Full Rich • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb 15,000 14,000 13,000 12,000...

  • Page 136: Time, Fuel And Distance To Climb

    Section 5 Cirrus Design Performance Data SR20 Time, Fuel and Distance to Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ......ISA • Mixture........Full Rich Weight........3000 LB • Fuel Density..... 6.0 LB/GAL Airport Press ......1000 FT • Weight ........3000 LB Pressure Altitude....

  • Page 137: Cruise Performance

    Cirrus Design Section 5 SR20 Performance Data Cruise Performance Conditions: Example: • Mixture ......Best Power Outside Air Temp ....29° C • Cruise Weight......2600 LB RPM ......2700 RPM • Winds ..........Zero Cruise Press Alt....8000 FT Note: Subtract 10 KTAS if nose wheel pant and fairing removed.
  • Page 138 Section 5 Cirrus Design Performance Data SR20 Cruise Performance 8000 Feet Pressure Altitude ISA - 30° C (-31° C) ISA (-1° C) ISA + 30° C (29° C) KTAS KTAS KTAS 2700 22.2 12.9 11.6 11.4 2500 22.2 11.4 11.0 10.6...
  • Page 139 Cirrus Design Section 5 SR20 Performance Data Range / Endurance Profile Conditions: Example: • Weight ........3000 LB Power Setting ......75% • Temperature ....Standard Day Takeoff Press Alt ....2000 FT • Winds ..........Zero Cruise Press Alt....6000 FT • Mixture ......See Tables •...
  • Page 140 Section 5 Cirrus Design Performance Data SR20 Range / Endurance Profile 65% POWER Mixture = Best Power Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 46.3 10.5 13.0 2000 45.7 10.5 13.1...

  • Page 141: Balked Landing Climb Gradient

    Cirrus Design Section 5 SR20 Performance Data Balked Landing Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ......... Full Rich Weight ........2500 LB • Flaps ........ 100% (DN) Pressure Altitude ....2000 FT •...

  • Page 142: Balked Landing Rate Of Climb

    Section 5 Cirrus Design Performance Data SR20 Balked Landing Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 20° C • Mixture........Full Rich Weight........2500 LB • Flaps.........100% (DN) Pressure Altitude....4000 FT • Climb Airspeed ......Noted Climb Airspeed.....

  • Page 143: Landing Distance

    Cirrus Design Section 5 SR20 Performance Data Landing Distance Conditions: Example: • Technique ......Normal Outside Air Temp ......10°C • Winds ..........Zero Weight ........2900 LB • Runway ........Paved Pressure Altitude ....2000 FT • Flaps......... 100% Headwind ........Zero •...
  • Page 144 Section 5 Cirrus Design Performance Data SR20 Landing Distance WEIGHT = 2900 LB Headwind: Subtract 10% per each Speed over 50 Ft Obstacle = 75 KIAS 13 knots headwind. Flaps - 100% · Idle · Dry, Level Paved Surface Tailwind: Add 10% for each 2 knots tailwind up to 10 knots.
  • Page 145 Cirrus Design Section 6 SR20 Weight and Balance Section 6 Weight and Balance Table of Contents Introduction ..................6-3 Airplane Weighing Form ..............6-6 Airplane Weighing Procedures ............6-7 Weight & Balance Record ............. 6-10 Loading Instructions ..............6-12 Weight & Balance Loading Form ..........6-14 Loading Data.................
  • Page 146 Section 6 Cirrus Design Weight and Balance SR20 Intentionally Left Blank P/N 13999-002 Info Manual September 2011...

  • Page 147: Introduction

    Cirrus Design Section 6 SR20 Weight & Balance Introduction This section describes the procedure for establishing the basic empty weight and moment of the airplane. Sample forms are provided for reference. Procedures for calculating the weight and moment for various operations are also provided. A comprehensive list of all equipment available for this airplane is included at the back of this section.
  • Page 148 Section 6 Cirrus Design Weight & Balance SR20 350.2" WATER LINE (WL) 165.5" 222.0" 100.0" 55.6" 38.3" WL100 NOTE Reference Datum located at fuselage station 0.0". 157.5" (FS) FUSELAGE STATION LEMAC FS 132.9" RBL 210.9" MAC 48.4" RBL 87.7" Typical LBL RBL 77.3"...
  • Page 149 Cirrus Design Section 6 SR20 Weight & Balance Spirit Level LONGITUDINAL LEVELING Spirit Level Straight Edge Straight Edge Straight Edge Spacer Spacer Block Block Door Sill Door Sill LATERAL LEVELING SR20_FM06_1021A Figure 6-2 Airplane Leveling P/N 13999-002 Info Manual September 2011...

  • Page 150: Airplane Weighing Form

    Section 6 Cirrus Design Weight & Balance SR20 Airplane Weighing Form REF DATUM FS 0.0 FS 100.0 FS 145.0 WL 100.0 A = x + 100 B = A - y y = ____________ Measured x = ____________ Measured SR20_FM06_1441...

  • Page 151: Airplane Weighing Procedures

    Cirrus Design Section 6 SR20 Weight & Balance Airplane Weighing Procedures A basic empty weight and center of gravity were established for this airplane when the airplane was weighed just prior to initial delivery. However, major modifications, loss of records, addition or relocation of...
  • Page 152 Section 6 Cirrus Design Weight & Balance SR20 4. Measuring (Figure 6-3): a. Obtain measurement ‘x’ by measuring horizontally along the airplane center line (BL 0) from a line stretched between the main wheel centers to a plumb bob dropped from the forward side of the firewall (FS 100).
  • Page 153 Cirrus Design Section 6 SR20 Weight & Balance The above procedure determines the airplane Basic Empty Weight, moment, and center of gravity in inches aft of datum. C.G. can also be expressed in terms of its location as a percentage of the airplane Mean Aerodynamic Cord (MAC) using the following formula: C.G.

  • Page 154: Weight & Balance Record

    Section 6 Cirrus Design Weight & Balance SR20 Weight & Balance Record Use this form to maintain a continuous history of changes and modifications to airplane structure or equipment affecting weight and balance: Serial Num: Reg. Num: Page Item Weight Change...
  • Page 155 Cirrus Design Section 6 SR20 Weight & Balance 49.3" 39.8" Fuselage Station 49.7" 38.5" 25.0" 16.0" 20.0" 32.0" 10.5" 39.0" 33.4" 20.0" 33.3" 5.0" 21.0" CABIN DOOR BAGGAGE DOOR OPENING OPENING SR20_FM06_1019 Location Length Width Height Volume Cabin 122” 49.3”...

  • Page 156: Loading Instructions

    Section 6 Cirrus Design Weight & Balance SR20 Loading Instructions It is the responsibility of the pilot to ensure that the airplane is properly loaded and operated within the prescribed weight and center of gravity limits. The following information enables the pilot to calculate the total weight and moment for the loading.
  • Page 157 Cirrus Design Section 6 SR20 Weight & Balance • The total moment/1000 must not be above the maximum or below the minimum moment/1000 for the Takeoff Condition Weight as determined from the Moment Limits chart or table. P/N 13999-002 Info Manual...

  • Page 158: Weight & Balance Loading Form

    Section 6 Cirrus Design Weight & Balance SR20 Weight & Balance Loading Form Serial Num:_________________Date: _________________________ Reg. Num: _________________Initials: _______________________ Weight Moment/ Item Description 1000 Basic Empty Weight Includes unusable fuel & full oil Front Seat Occupants Pilot & Passenger (total)

  • Page 159: Loading Data

    Cirrus Design Section 6 SR20 Weight & Balance Loading Data Use the following chart or table to determine the moment/1000 for fuel and payload items to complete the Loading Form. Fuel Fwd Pass Loading Chart Aft Pass Baggage Moment/1000 SR20_FM06_1942...

  • Page 160: Moment Limits

    Section 6 Cirrus Design Weight & Balance SR20 Moment Limits Use the following chart or table to determine if the weight and moment from the completed Weight and Balance Loading Form are within limits. 3000 2800 2600 2400 2200 2000...

  • Page 161: Equipment List

    Cirrus Design Section 6 SR20 Weight & Balance Equipment List This list will be determined after the final equipment has been installed in the aircraft. P/N 13999-002 Info Manual 6-17 September 2011...
  • Page 162 Section 6 Cirrus Design Weight & Balance SR20 Intentionally Left Blank 6-18 P/N 13999-002 Info Manual September 2011...
  • Page 163 Cirrus Design Section 7 SR20 Airplane Description Section 7 Airplane and Systems Description Table of Contents Introduction ..................7-5 Airframe ..................7-6 Fuselage ..................7-6 Wings................... 7-6 Empennage ................. 7-7 Flight Controls ................. 7-8 Elevator System................7-8 Aileron System................7-10 Rudder System ................
  • Page 164 Section 7 Cirrus Design Airplane Description SR20 Baggage Compartment..............7-27 Seats..................7-29 Windshield and Windows............7-30 Cabin Safety Equipment ............7-30 Engine ...................7-33 Engine Oil System ..............7-33 Engine Cooling................7-33 Engine Fuel Injection ..............7-34 Engine Air Induction System............7-34 Engine Fuel Ignition ..............7-34 Engine Exhaust................7-35 Engine Controls .................7-35 Alternate Air Control..............7-36...
  • Page 165 Transponder ................7-74 Audio System................7-75 Emergency Locator Transmitter ..........7-76 Hour Meter ................. 7-77 Digital Clock................7-78 Cirrus Airplane Parachute System ..........7-80 System Description ..............7-80 Activation Handle ............... 7-81 Deployment Characteristics ............7-82 P/N 13999-002 Info Manual...
  • Page 166 Section 7 Cirrus Design Airplane Description SR20 Intentionally Left Blank P/N 13999-002 Info Manual September 2011...

  • Page 167: Introduction

    Cirrus Design Section 7 SR20 Airplane Description Introduction This section provides a basic description and operation of the standard airplane and its systems. Optional equipment described within this section is identified as optional. • Note • Some optional equipment, primarily avionics, may not be described in this section.

  • Page 168: Airframe

    Section 7 Cirrus Design Airplane Description SR20 Airframe Fuselage The SR20 monocoque fuselage is constructed primarily of composite materials and is designed to be aerodynamically efficient. The cabin area is bounded on the forward side by the firewall at fuselage station 100, and on the rear by the aft baggage compartment bulkhead at fuselage station 222.

  • Page 169: Empennage

    Cirrus Design Section 7 SR20 Airplane Description Empennage The empennage consists of a horizontal stabilizer, a two-piece elevator, a vertical fin and a rudder. All of the empennage components are conventional spar (shear web), rib, and skin construction. The horizontal stabilizer is a single composite structure from tip to tip.

  • Page 170: Flight Controls

    Section 7 Cirrus Design Airplane Description SR20 Flight Controls The SR20 uses conventional flight controls for ailerons, elevator and rudder. The control surfaces are pilot controlled through either of two single-handed side control yokes mounted beneath the instrument panel. The location and design of the control yokes allow easy, natural use by the pilot.
  • Page 171 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1461 Figure 7-1 Elevator Control System P/N 13999-002 Info Manual September 2011...

  • Page 172: Aileron System

    Section 7 Cirrus Design Airplane Description SR20 Aileron System The ailerons provide airplane roll control. The ailerons are of conventional design with skin, spar and ribs manufactured of aluminum. Each aileron is attached to the wing shear web at two hinge points.
  • Page 173 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1462 Figure 7-2 Aileron Control System P/N 13999-002 Info Manual 7-11 September 2011...

  • Page 174: Rudder System

    Control Locks The Cirrus SR20 control system is not equipped with gust locks. The trim spring cartridges have sufficient power to act as a gust damper without rigidly locking the position.
  • Page 175 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1463 Figure 7-3 Rudder Control System P/N 13999-002 Info Manual 7-13 September 2011...

  • Page 176: Trim Systems

    Section 7 Cirrus Design Airplane Description SR20 Trim Systems Roll and pitch trim are provided by adjusting the neutral position of a compression spring cartridge in each control system by means of an electric motor. The electric roll trim is also used by the autopilot to position the ailerons.

  • Page 177: Yaw Trim System

    Cirrus Design Section 7 SR20 Airplane Description Yaw Trim System Yaw trim is provided by spring cartridge attached to the rudder pedal torque tube and console structure. The spring cartridge provides a centering force regardless of the direction of rudder deflection. The yaw trim is ground adjustable only.

  • Page 178: Flight Deck Arrangement

    Section 7 Cirrus Design Airplane Description SR20 Flight Deck Arrangement The following paragraphs are a general description of the flight deck, instruments, and controls. Details relating to the instruments, switches, circuit breakers, and controls on the instrument panel, bolster, and center console are located with the description of the affected system.
  • Page 179 3. Overhead Light & Switch 20. Control Yoke 4. Magnetic Compass 14. Passenger Audio Jacks 21. Start/Ignition Key Switch 5. Cirrus Airframe Parachute System 15. Armrest 16. Engine & Fuel System Controls (CAPS) Activation T-Handle Cover 6. Multifunction Display 17. Left Side Console 7.

  • Page 180: Flight Instruments

    Section 7 Cirrus Design Airplane Description SR20 Flight Instruments • Note • For additional information on instrument limit markings, refer to Section 2, Limitations. Attitude Indicator The attitude gyro 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°...

  • Page 181: Vertical Speed Indicator

    Cirrus Design Section 7 SR20 Airplane Description Vertical Speed Indicator 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 minute (FPM).

  • Page 182: Directional Gyro

    Section 7 Cirrus Design Airplane Description SR20 indicated. Power for gyro operation is supplied through the 5-amp TURN COORDINATOR circuit breaker on the Essential Bus. Back-up power for turn coordinator gyro operation is supplied by a 27-volt battery pack. Turn Coordinator Power Switch...

  • Page 183: Course Deviation Indicator

    Cirrus Design Section 7 SR20 Airplane Description Course Deviation Indicator The Course Deviation Indicator (CDI) displays course deviation from a VOR, Localizer (LOC) or Glideslope when 'VLOC' is the selected navigation source on the GNS 430 and displays GPS track deviation when 'GPS' is the selected navigation source.
  • Page 184 Section 7 Cirrus Design Airplane Description SR20 course and heading outputs provided to the autopilot to allow NAV/ LOC/GPS course tracking or to track a preset heading. The HSI incorporates conventional warning flags. The HDG (Heading) flag will be out of view whenever the instrument is receiving sufficient electrical power for operation.

  • Page 185: Magnetic Compass

    Cirrus Design Section 7 SR20 Airplane Description can be displayed and switched to any NAV receiver including GPS1, GPS2, NAV1, or NAV2. GPS2 and NAV2 can only be displayed as bearing pointers, not as a primary navigation source. The display is color-coded to indicate which navigation source is selected: green for NAV1, yellow for NAV2, and cyan for GPS.

  • Page 186: Wing Flaps

    Section 7 Cirrus Design Airplane Description SR20 Wing Flaps The electrically controlled, single-slotted flaps provide low-speed lift enhancement. Each flap is manufactured of aluminium and connected to the wing structure at three hinge points. Rub strips are installed on the top leading edge of each flap to prevent contact between the flap and wing flap cove.
  • Page 187 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1460 Figure 7-5 Flap Control System P/N 13999-002 Info Manual 7-25 September 2011...

  • Page 188: Landing Gear

    Section 7 Cirrus Design Airplane Description SR20 Landing Gear Main Gear The main landing gear are bolted to composite wing structure between the wing spar and shear web. The landing gear struts are constructed of composite material for fatigue resistance. The composite construction is both rugged and maintenance free.

  • Page 189: Airplane Cabin

    Cirrus Design Section 7 SR20 Airplane Description Airplane Cabin Cabin Doors Two large forward hinged doors allow crew and passengers to enter and exit the cabin. The door handles engage latching pins in the door frame receptacles at the upper aft and lower aft door perimeter. Gas charged struts provide assistance in opening the doors and hold the doors open against gusts.
  • Page 190 Section 7 Cirrus Design Airplane Description SR20 DEFROST AIR OUTLETS STALL WARNING HORN FIRE EXTINGUISHER (UNDER PILOT'S SEAT) OVERHEAD LIGHT AND SWITCH DOOR HANDLE EGRESS HAMMER (IN ARMREST) CABIN SPEAKER PASSENGER FRESH AIR OUTLET OVERHEAD LIGHT AND SWITCH TIEDOWN LOOPS...

  • Page 191: Seats

    Cirrus Design Section 7 SR20 Airplane Description To loosen tie-down straps: 1. Lift buckle release and pull on buckle to loosen strap. 2. Lift hook ends free of loop fittings. Seats The seating arrangement consists of two individually adjustable seats for the pilot and front seat passenger and two individual seats with fold down seat backs for the rear seat passengers.

  • Page 192: Windshield And Windows

    Section 7 Cirrus Design Airplane Description SR20 To fold seat back forward: 1. From the baggage access, lift the carpet panel at lower aft edge of seat to reveal the seat back locking pins (attached to lanyards). 2. Remove the locking pins and fold seat forward.
  • Page 193 Cirrus Design Section 7 SR20 Airplane Description • Caution • No slack may exist between the occupant’s shoulder and restraint harness shoulder strap. Stow the seat belts in the latched position when not in use. To use the restraints: 1. Slip arms behind the harness so that the harness extends over shoulders.
  • Page 194 Section 7 Cirrus Design Airplane Description SR20 1. Loosen retaining clamp and remove the extinguisher from its mounting bracket. 2. Hold the extinguisher upright and pull the pin. 3. Get back from the fire and aim nozzle at base of fire at the nearest edge.

  • Page 195: Engine

    Cirrus Design Section 7 SR20 Airplane Description Engine The SR20 is powered by a Teledyne Continental IO-360-ES, six- cylinder, normally aspirated, fuel-injected engine de-rated to 200 hp at 2,700 RPM. The engine has a 2000-hour Time Between Overhaul (TBO). Dual, conventional magnetos provide ignition.

  • Page 196: Engine Fuel Injection

    Section 7 Cirrus Design Airplane Description SR20 the engine compartment through two vents in the aft portion of the cowling. No movable cowl flaps are used. Engine Fuel Injection The multi-nozzle, continuous-flow fuel injection system supplies fuel for engine operation. An engine driven fuel pump draws fuel from the selected wing tank and passes it to the mixture control valve integral to the pump.

  • Page 197: Engine Exhaust

    Cirrus Design Section 7 SR20 Airplane Description Engine Exhaust Engine exhaust gases are routed through a dual tuned exhaust system. After leaving the cylinders, exhaust gases are routed through the exhaust manifold, through mufflers located on either side of the engine, and then overboard through exhaust pipes exiting through the lower cowling.

  • Page 198: Alternate Air Control

    Section 7 Cirrus Design Airplane Description SR20 Start/Ignition Switch A rotary-type key switch, located on the left bolster panel, controls ignition and starter operation. The switch is labeled OFF-R-L- BOTH- START. In the OFF position, the starter is electrically isolated, the magnetos are grounded and will not operate.
  • Page 199 Cirrus Design Section 7 SR20 Airplane Description FUEL Start / Ignition Switch Serials 1005 thru 1336 : Controls Switch is located on the left bolster panel. Alternate Air Control Serials 1005 thru 1581. LEGEND 1. Power Lever 6. CHT 2. Mixture Control 7.
  • Page 200 Section 7 Cirrus Design Airplane Description SR20 Tachometer A 2¼” tachometer is mounted on the right instrument panel adjacent to the other engine instruments. The tachometer pointer sweeps a scale marked from 0 to 3500 RPM in 100 RPM increments. Refer to Section 2 (Limitations) for instrument limit markings.
  • Page 201 Cirrus Design Section 7 SR20 Airplane Description Pressure indicator receives a pressure signal from an oil pressure sensor on the left side of the engine. Normally, oil pressure may drop to 10 psi at idle but will be in the 30 - 60 psi range at higher RPM.

  • Page 202: Propeller

    Section 7 Cirrus Design Airplane Description SR20 Propeller The airplane is equipped with a constant-speed, aluminum-alloy propeller with a governor. The airplane is available with the standard two-blade (76” diameter) propeller or an optional three-blade (74” diameter) propeller. The propeller governor automatically adjusts propeller pitch to regulate propeller and engine RPM.

  • Page 203: Fuel System

    Cirrus Design Section 7 SR20 Airplane Description Fuel System A 56-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 30.3-gallon capacity (28- gallon usable) vented integral fuel tank in each wing, a fuel collector/ sump in each wing, a three-position selector valve, an electric boost pump, and an engine-driven fuel pump.
  • Page 204 Section 7 Cirrus Design Airplane Description SR20 ANNUNCIATOR FUEL FUEL QUANTITY VENT VENT FILLER FILLER INDICATOR L. WING TANK R. WING TANK R. WING L. WING COLLECTOR COLLECTOR SELECTOR VALVE FLAPPER FLAPPER VALVE VALVE DRAIN FIREWALL (5 PLACES) SELECTOR VALVE...

  • Page 205: Fuel Selector Valve

    Cirrus Design Section 7 SR20 Airplane Description The airplane may be serviced to a reduced capacity to permit heavier cabin loadings. This is accomplished by filling each tank to a tab visible below the fuel filler, giving a reduced fuel load of 13 gallons usable in each tank (26 gallons total usable in all flight conditions).

  • Page 206: Fuel Flow Indication

    Section 7 Cirrus Design Airplane Description SR20 When the fuel tanks are 1/4 full or less, prolonged uncoordinated flight such as slips or skids can uncover the fuel tank outlets. Therefore, if operating with one fuel tank dry or if operating on LEFT or RIGHT tank when 1/4 full or less, do not allow the airplane to remain in uncoordinated flight for periods in excess of 30 seconds.
  • Page 207 Cirrus Design Section 7 SR20 Airplane Description mode to deliver a continuous 4-6 psi boost to the fuel flow for vapor suppression in a hot fuel condition. Serials 1228 and subs, 1005 thru 1227 after SB 20-73-02: An oil pressure based system is used to control boost pump operation. The oil pressure/oil temperature gauge provides a signal to the starting circuit to generate a ground for the oil annunciator and the fuel system.

  • Page 208: Brake System

    Section 7 Cirrus Design Airplane Description SR20 Brake System The main wheels have hydraulically operated, single-disc type brakes, individually activated by floor mounted toe pedals at both pilot stations. A parking brake mechanism holds induced hydraulic pressure on the disc brake for parking.
  • Page 209 Cirrus Design Section 7 SR20 Airplane Description RESERVOIR MIL-H-5606 FLUID ONLY RUDDER PEDAL(4) MASTER CYLINDER(4) PARKING PARKING BRAKE BRAKE VALVE KNOB CALIPER CALIPER ASSEMBLY ASSEMBLY ROTOR ROTOR (DISK) (DISK) SR20_FM07_1015 Figure 7-9 Brake System P/N 13999-002 Info Manual 7-47 September 2011...
  • Page 210 Section 7 Cirrus Design Airplane Description SR20 Parking Brake • Caution • Do not pull the PARK BRAKE knob in flight. If a landing is made with the parking brake valve set, the brakes will maintain any pressure applied after touchdown.

  • Page 211: Electrical System

    Cirrus Design Section 7 SR20 Airplane Description Electrical System The standard airplane is equipped with 28-volt direct current (VDC) single alternator electrical system. The system provides uninterrupted power for avionics, flight instruments, lighting and other electrically operated and controlled systems during normal operation. The system also allows load shedding in the event of an electrical system failure.
  • Page 212 Section 7 Cirrus Design Airplane Description SR20 ANNUNC. LANDING LOW VOLTS LIGHT AMPS VOLTS CLOCK LANDING LIGHT BATTERY LANDING LIGHT RELAY ALTERNATOR EXTERNAL POWER ALT. RECEPTACLE RELAY ALT. CNTL. CURRENT UNIT GND. BATTERY SENSOR MASTER RELAY PWR. ALT. RELAY STARTER BAT.

  • Page 213: Power Distribution

    Cirrus Design Section 7 SR20 Airplane Description Power Distribution Power distribution for the SR20 consists of the electrical power bus in the Master Control Unit (MCU), Main Buses, Essential and Non- Essential buses in the circuit breaker panel, as well as associated fuses, circuit breakers and switches.

  • Page 214: Avionics Power Switch

    Section 7 Cirrus Design Airplane Description SR20 Avionics Power Switch A rocker switch, labeled AVIONICS POWER, controls electrical power from the airplane primary bus to the avionics bus. The switch is located next to the ALT and BAT Master switches and is ON in the up position and off in the down position.

  • Page 215: Low Volts Warning Light

    Cirrus Design Section 7 SR20 Airplane Description Low Volts Warning Light The airplane is equipped with a red LOW VOLTS warning light in the annunciator panel located on the left side of the instrument panel. The alternator control unit (ACU) located within the master control unit (MCU), which is mounted on the engine side of the firewall, operates the warning light.

  • Page 216: Circuit Breakers And Fuses

    Section 7 Cirrus Design Airplane Description SR20 Circuit Breakers and Fuses Individual electrical circuits connected to the Main, Essential, and Non-Essential buses in the airplane are protected by re-settable circuit breakers mounted on the left side of the center console. The airplane Essential bus is supplied from the Main Buses through the 20-amp ESSENTIAL 1 and ESSENTIAL 2 circuit breakers.

  • Page 217: Exterior Lighting

    Cirrus Design Section 7 SR20 Airplane Description Exterior Lighting The airplane is equipped with standard wing tip and tail-mounted navigation lights with integral anti-collision strobe lights. The separately controlled landing light is located in the left cowl inlet. Navigation Lights The airplane is equipped with standard wing tip navigation lights.

  • Page 218: Interior Lighting

    Section 7 Cirrus Design Airplane Description SR20 Interior Lighting Interior lighting for the airplane consists of separately controlled incandescent overhead lights for general cabin lighting, individual lights for the pilots and passengers, and dimmable panel floodlights. The flight instruments and avionics equipment lights are dimmable.

  • Page 219: Environmental System

    Cirrus Design Section 7 SR20 Airplane Description Environmental System Cabin heating and ventilation is accomplished by supplying conditioned air for heating and windshield defrost and fresh air for ventilation. The conditioned air system consists of a heater muff (heat exchanger) around the right engine exhaust muffler, an air mixing plenum, air ducting for distribution, a windshield diffuser, forward outlet valves, and cable controls for selecting temperature and flow.

  • Page 220: Heating And Ventilation

    Section 7 Cirrus Design Airplane Description SR20 AIR INLET HEAT EXCHANGER HVAC CABIN HEAT/ PLENUM HEAT DEFROST SELECT TEMP. CONTROL COLD WINDSHIELD DEFROST DIFFUSER AIR GASPER FRESH AIR FRESH AIR INTAKE INTAKE FOOT-WARMER DIFFUSER CONDITIONED FRESH AIR MECHANICAL SR20_FM07_1012B CONNECTION...

  • Page 221: Cabin Heat Control

    Cirrus Design Section 7 SR20 Airplane Description Cabin Heat Control The amount of heated air allowed into the air mixing plenum is controlled by rotating the Cabin Heat Control, located inboard of the Cabin Air Selector. The control is mechanically linked to a door in a heater box between the heater muff and the mixing plenum.
  • Page 222 Section 7 Cirrus Design Airplane Description SR20 Serials 1005 thru 1336 ,1337 Serials 1337 & subs w/ PFD. thru 1422 w/o PFD. PRIMARY FLIGHT DISPLAY AIRSPEED VERTICAL SPEED INDICATOR INDICATOR ALTIMETER ALTITUDE ENCODER ALTITUDE TRANSDUCER ALTERNATE (OPTIONAL) STATIC AIR SOURCE...

  • Page 223: Pitot-Static System

    Cirrus Design Section 7 SR20 Airplane Description Pitot-Static System The Pitot-Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage. The Pitot heat is pilot controlled through a panel-mounted switch. An internally mounted alternate static pressure source provides backup static pressure should that the primary static source becomes blocked.

  • Page 224: Vacuum System

    Section 7 Cirrus Design Airplane Description SR20 static pressure source is selected, refer to Section 5 airspeed calibration and altitude for corrections to be applied. Vacuum System The airplane vacuum system provides the vacuum necessary to operate the attitude gyro and directional gyro. The system consists of...
  • Page 225 Cirrus Design Section 7 SR20 Airplane Description FUSE ELECTRIC ENGINE-DRIVEN (Standby) VACUUM PUMP STANDBY VACUUM VACUUM PUMP (CB PANEL) VACUUM VACUUM SWITCHES AUX VAC CHECK VALVES VACUUM REGULATOR CIRRUS ATTITUDE GYRO FOAM FILTER SUCTION GAGE INSTRUMENT AIR FILTER (PAPER) DIRECTIONAL...

  • Page 226: Suction Gauge

    Section 7 Cirrus Design Airplane Description SR20 Suction Gauge The suction gauge, located on the far right side of the instrument panel, is calibrated in inches of Mercury (Hg). The gauge indicates suction available for operation of the attitude and directional gyros.

  • Page 227: Stall Warning System

    Cirrus Design Section 7 SR20 Airplane Description Stall Warning System The airplane is equipped with an electro-pneumatic stall warning system to provide audible warning of an approach to aerodynamic stall. The system consists of an inlet in the leading edge of the right wing, a pressure switch and associated plumbing, and a piezo- ceramic horn behind the instrument panel.

  • Page 228: Standard Avionics

    Section 7 Cirrus Design Airplane Description SR20 Standard Avionics The following paragraphs and equipment descriptions describe all standard avionic installations offered for the SR20. The avionics navigation and communication equipment are mounted in he center console and are easily accessible from either pilot seat.
  • Page 229 Cirrus Design Section 7 SR20 Airplane Description • Mode C Transponder with altitude encoder (Garmin GTX 320 or GTX 327) - An altitude digitizer provides altitude information to transponder and GPS receiver. • Multi-Function Display - Either an ARNAV ICDS 2000 or an Avidyne FlightMax EX-Series moving map display is installed.

  • Page 230: Multi-Function Display

    Section 7 Cirrus Design Airplane Description SR20 Multi-Function Display This airplane is equipped with an Avidyne FlightMax EX5000C 700- 00004-XXX-() Multi-Function Flight Display (MFD). The MFD is a 10.4- inch landscape-oriented display mounted in the instrument panel. The MFD provides supplemental display of situational and navigation information to the pilot.
  • Page 231 Cirrus Design Section 7 SR20 Airplane Description Power for the MCU is 28 VDC supplied through the 5-amp MFD circuit breaker on the Avionics Non-Essential Bus. • Note • Serials 1005 through 1472 before MFD software version 530- 00162-000 Revision 02; Do not use the Garmin 420 or 430 Navigators to display Stormscope lightning data when the Avidyne MFD’s Lightning mode is set to either DATALINK or...

  • Page 232: Autopilot

    Section 7 Cirrus Design Airplane Description SR20 Autopilot The airplane may be equipped with the standard S-TEC System Twenty Autopilot, an optional S-TEC System Thirty Autopilot, or an optional S-TEC System 55X autopilot. Refer to the applicable FAA Approved Airplane Flight Manual Supplement and the applicable Pilot's Guide for additional description as well as specific limitations and operating procedures for the SR20.
  • Page 233 Cirrus Design Section 7 SR20 Airplane Description control switches on the control yoke handles. The control knob provides mode selection, disengage, and turn command functions. The autopilot makes roll changes through the aileron trim motor and spring cartridge and makes pitch changes for altitude hold through the pitch trim motor and spring cartridge.

  • Page 234: Gps Navigation

    Section 7 Cirrus Design Airplane Description SR20 GPS Navigation The airplane is equipped with two GPS navigators. The Garmin GNS 430 navigator is the primary system, is IFR certified, and is coupled to the airplane's CDI and Multi-Function display. The Garmin GNC 250XL provides backup and is approved for VFR use only.

  • Page 235: Communication (Com) Transceivers

    Cirrus Design Section 7 SR20 Airplane Description Communication (COM) Transceivers Two VHF communications (COM) transceivers are installed to provide VHF communication. The transceivers and integrated controls are mounted in the Garmin GNS 430 and GNC 250XL units. The transceivers receive all narrow- and wide-band VHF communication transmissions transmitted within range of the selected frequency.

  • Page 236: Navigation (Nav) Receiver

    Section 7 Cirrus Design Airplane Description SR20 Navigation (Nav) Receiver The Garmin GNS 430 provides an integrated Navigation (NAV) receiver with VHF Omnirange/Localizer (VOR/LOC) and Glideslope (G/S) capability. The VOR/LOC receiver receives VOR/LOC on a frequency range from 108.000 Mhz to 117.950 Mhz with 50 kHz spacing.

  • Page 237: Audio System

    Cirrus Design Section 7 SR20 Airplane Description Audio System The Garmin GMA 340 audio control unit, located in the center console, provides audio amplification, audio selection, marker beacon control, and a voice activated intercom system for the cabin speaker, headsets, and microphones. The system allows audio switching for up to three transceivers (COM 1, COM 2, and COM 3) and five receivers (NAV 1, NAV2, ADF, DME, and MKR).

  • Page 238: Emergency Locator Transmitter

    Section 7 Cirrus Design Airplane Description SR20 Emergency Locator Transmitter The airplane is equipped with a self-contained emergency locator transmitter (ELT). The transmitter and antenna are installed immediately behind the aft cabin bulkhead to the right of the airplane centerline. The main transmitter control switch, labeled ON-OFF- ARMED, on the transmitter is in the armed position for normal operations.

  • Page 239: Hour Meter

    Cirrus Design Section 7 SR20 Airplane Description Portable use of ELT: 3. Remove access at lower aft center of baggage compartment. 4. Disconnect fixed antenna lead from front of unit. 5. Disconnect lead from remote switch and indicator unit. 6. Loosen attach straps and remove transmitter unit and portable antenna.

  • Page 240: Digital Clock

    Section 7 Cirrus Design Airplane Description SR20 Digital Clock The airplane is equipped with a 2¼” Davtron M803 digital clock located on the left instrument panel immediately outboard of the airspeed indicator. The clock provides Universal Time (UT), Local Time (LT), Elapsed Time (ET), Outside Air Temperature (OAT) in ° C or °...
  • Page 241 Cirrus Design Section 7 SR20 Airplane Description 2. Press Control to activate count-up timer. Elapsed time counts up to 59 minutes, 59 seconds, and then switches to hours and minutes. Pressing the Control button again will reset the timer to zero.

  • Page 242: Cirrus Airplane Parachute System

    Airplane Description SR20 Cirrus Airplane Parachute System The SR20 is equipped with a Cirrus Airplane Parachute System (CAPS) designed to bring the aircraft and its occupants to the ground in the event of a life-threatening emergency. The system is intended to...

  • Page 243: Activation Handle

    Cirrus Design Section 7 SR20 Airplane Description sequence the slider limits the initial diameter of the parachute and the rate at which the parachute inflates. As the slider moves down the suspension lines the canopy inflates. A three-point harness connects the airplane fuselage structure to the parachute.

  • Page 244: Deployment Characteristics

    Section 7 Cirrus Design Airplane Description SR20 Attempting to activate the rocket by pushing the activation T- handle forward and down limits the force that can be applied. Pulling the activation T-handle straight down generates the greatest force. A maintenance safety pin is provided to ensure that the activation handle is not pulled during maintenance.
  • Page 245 Cirrus Design Section 7 SR20 Airplane Description equal to the velocity of the surface wind. In addition, surface winds may continue to drag the aircraft after ground impact. • Caution • Ground impact is expected to be equivalent to touchdown from a height of approximately 10 feet.
  • Page 246 Section 7 Cirrus Design Airplane Description SR20 Intentionally Left Blank 7-84 P/N 13999-002 Info Manual September 2011...
  • Page 247 Airworthiness Directives..............8-6 Airplane Inspection Periods ............8-6 Annual Inspection ................ 8-6 100-Hour Inspection ..............8-7 Cirrus Design Progressive Inspection Program ......8-7 Pilot Performed Preventative Maintenance ......... 8-8 Ground Handling ................8-10 Application of External Power ............ 8-10 Towing ..................8-11 Taxiing ..................
  • Page 248 Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Intentionally Left Blank P/N 13999-002 Info Manual September 2011...

  • Page 249: Introduction

    Introduction This section provides general guidelines for handling, servicing and maintaining your Cirrus Design SR20. In order to ensure continued safe and efficient operation of your airplane, keep in contact with your Authorized Cirrus Service Center to obtain the latest information pertaining to your aircraft.

  • Page 250: Ordering Publications

    SR20 publications, revision service, service publication subscription service may be obtained by contacting Customer Service at Cirrus Design as follows: Cirrus Design Corporation Customer Service 4515 Taylor Circle Duluth, MN 55811 Phone: 218 727-2737 FAX: 218 727-2148 Make sure to include airplane serial number and owner’s name in all correspondence for accurate processing of your documentation needs.

  • Page 251: Airplane Records And Certificates

    Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Airplane Records and Certificates The Federal Aviation Administration (FAA) requires that certain data, certificates, and licenses be displayed or carried aboard the airplane at all times. Additionally, other documents must be made available upon request.

  • Page 252: Airworthiness Directives

    AD’s are mandatory changes and must be complied with within a time limit set forth in the AD. Operators should periodically check with Cirrus Service Centers or A&P mechanic to verify receipt of the latest issued AD for their airplane.

  • Page 253: 100-Hour Inspection

    Progressive Inspection Program in accordance with the Federal Aviation Regulation Part 91.409. The Cirrus Design Progressive Inspection Program provides for the complete inspection of the airplane utilizing a five-phase cyclic inspection program. A total of eight inspections are accomplished over the course of 400 flight hours, with an inspection occurring every 50 flight hours.

  • Page 254: Pilot Performed Preventative Maintenance

    Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Pilot Performed Preventative Maintenance The holder of a Pilot Certificate issued under FAR Part 61 may perform certain preventive maintenance described in FAR Part 43, Appendix A. This maintenance may be performed only on an aircraft that the pilot owns or operates and which is not used in air carrier service.
  • Page 255 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance 12. Replace any hose connection, except hydraulic connections, with replacement hoses. 13. Clean or replace fuel and oil strainers, as well as replace or clean filter elements. 14. Replace prefabricated fuel lines.

  • Page 256: Ground Handling

    Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Ground Handling Application of External Power A ground service receptacle, located just aft of the cowl on the left side of the airplane, permits the use of an external power source for cold weather starting and maintenance procedures.

  • Page 257: Towing

    Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed in the rear baggage compartment or by power equipment that will not damage or excessively strain the nose gear assembly.

  • Page 258: Taxiing

    Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Taxiing Before attempting to taxi the airplane, ground personnel should be instructed and authorized by the owner to taxi the airplane. Instruction should include engine starting and shutdown procedures in addition to taxi and steering techniques.

  • Page 259: Parking

    Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Parking The airplane should be parked to protect the airplane from weather and to prevent it from becoming a hazard to other aircraft. The parking brake may release or exert excessive pressure because of heat buildup after heavy braking or during wide temperature swings.

  • Page 260: Tiedown

    Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Tiedown The airplane should be moored for immovability, security and protection. FAA Advisory Circular AC 20-35C, Tiedown Sense, contains additional information regarding preparation for severe weather, tiedown, and related information. The following procedures should be used for the proper mooring of the airplane: 1.

  • Page 261: Jacking

    Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Jacking Two jacking points are provided: one at each wing tiedown. Jack points (pads) are stowed in the baggage compartment. The airplane may be jacked using two standard aircraft hydraulic jacks at the wing jacking points and a weighted tailstand attached to the tail tiedown.

  • Page 262: Servicing

    Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Servicing Landing Gear Servicing The main landing gear wheel assemblies use 15 x 6.00 x 6, six-ply rating tires and tubes. The nose wheel assembly uses a 5.00 x 5 four- ply rating, type III tire and tube. Always keep tires inflated to the rated pressure to obtain optimum performance and maximum service.
  • Page 263 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Brake Inspection The brake assemblies and linings should be checked at every oil change (50 hours) for general condition, evidence of overheating, and deterioration.Serials 1005 thru 1147 before SB 2X-05-01: At every annual/100-hour inspection the brakes should be disassembled, the brake linings should be checked and the O-rings replaced.

  • Page 264: Tire Inflation

    Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Tire Inflation For maximum service from the tires, keep them inflated to the proper pressure. When checking tire pressure, examine the tires for wear, cuts, nicks, bruises and excessive wear. To inflate tires: 1.

  • Page 265: Oil Servicing

    Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Oil Servicing The oil capacity of the Teledyne Continental IO-360-ES engine is 8 quarts. It is recommended that the oil be changed every 50 hours and sooner under unfavorable operating conditions. The following grades...
  • Page 266 • Caution • MIL-C-6529, Type II straight mineral oil with corrosion preventive can cause coking with extended use and is not recommended by Cirrus Design for break-in or post break-in use. After 25 hours of operation and after oil consumption has stabilized,...
  • Page 267 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Product Supplier Aeroshell (R) W Shell Australia Aeroshell Oil W Shell Canada Ltd. Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50 Aeroshell Oil W Shell Oil Company Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50...

  • Page 268: Fuel System Servicing

    Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Fuel System Servicing After the first 25 hours of operation, then every 50-hours or as conditions dictate, the fuel filtration screen in the gascolator must be cleaned. After cleaning, a small amount of grease applied to the gascolator bowl gasket will facilitate reassembly.
  • Page 269 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance 2. Connect ground wire from refuel nozzle to airplane exhaust, from airplane exhaust to fuel truck or cart, and from fuel truck or cart to a suitable earth ground. 3. Place rubber protective cover over wing around fuel filler.

  • Page 270: Fuel Contamination And Sampling

    Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Fuel Contamination and Sampling Typically, fuel contamination results from foreign material such as water, dirt, rust, and fungal or bacterial growth. Additionally, chemicals and additives that are incompatible with fuel or fuel system components are also a source of fuel contamination.

  • Page 271: Battery Service

    Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Battery Service Access to the 24 volt battery is gained by removing the upper cowl. It is mounted to the forward right side of the firewall. The battery vent is connected to an acid resistant plastic tube that vents gases and electrolyte overflow overboard.

  • Page 272: Cleaning And Care

    Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Cleaning and Care Cleaning Exterior Surfaces • Note • Prior to cleaning, place the airplane in a shaded area to allow the surfaces to cool. The airplane should be washed with a mild soap and water. Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause corrosion of metal.
  • Page 273 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Cleaning Product Cleaning Application Supplier Mild Dishwasher Soap Fuselage Exterior and Any Source (abrasive free) Landing Gear Pure Carnauba Wax Fuselage Exterior Any Source Mothers California Gold Fuselage Exterior Wal-Mart Stores Pure Carnauba Wax...
  • Page 274 Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Windscreen and Windows Before cleaning an acrylic window, rinse away all dirt particles before applying cloth or chamois. Never rub dry acrylic. Dull or scratched window coverings may be polished using a special acrylic polishing paste.
  • Page 275 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Engine Compartment Before cleaning the engine compartment, place a strip of tape on the magneto vents to prevent any solvent from entering these units. 1. Place a large pan under the engine to catch waste.

  • Page 276: Cleaning Interior Surfaces

    Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Cleaning Interior Surfaces Seats, carpet, upholstery panels, and headliners should be vacuumed at regular intervals to remove surface dirt and dust. While vacuuming, use a fine bristle nylon brush to help loosen particles.
  • Page 277 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Cleaning Product Cleaning Application Supplier Interior Windscreen and Prist Prist Aerospace Windows Optimax Display Screens PhotoDon Mild Dishwasher Soap Cabin Interior Any Source (abrasive free) Leather Care Kit Leather Upholstery Cirrus Design...
  • Page 278 Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Instrument Panel and Electronic Display Screens The instrument panel, control knobs, and plastic trim need only to be wiped clean with a soft damp cloth. The multifunction display, primary flight display, and other electronic display screens should be cleaned with Optimax - LCD Screen Cleaning Solution as follows: •...
  • Page 279 For deeper cleaning, start with mix of mild detergent and water then, if necessary, work your way up to the products available from Cirrus for more stubborn marks and stains. Do not use soaps as they contain alkaline which will alter the leather’s pH balance and cause the leather to age prematurely.
  • Page 280 Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Intentionally Left Blank 8-34 P/N 13999-002 Info Manual September 2011...
  • Page 281 Cirrus Design Supplements produced for this airplane. The Log of Supplements page can be utilized as a “Table of Contents” for this section. In the event the airplane is modified at a non Cirrus Design facility through an STC or other approval method, it is the...
  • Page 282 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank P/N 13999-002 Info Manual September 2011...
  • Page 283 Cirrus Design Section 9 SR20 Supplements Section 9 Log of Supplements Part Number Title Date ___ 11934-S01 R2 Garmin GMA 340 Audio System 07-18-05 ___ 11934-S02 Garmin GTX 320 Transponder 03-31-99 ___ 11934-S05 Garmin GNC 250XL GPS Navigator w/ VHF COM...
  • Page 284 This Log of Supplements shows all Cirrus Design Supplements available for the aircraft at the cooresponding date of the revision level shown in the lower left corner. A mark (x) in the Part Number column indicates that the supplement is installed in the POH.
  • Page 285 Includes Optional XM Radio System When the Garmin GMA 340 Audio Panel and the optional XM Radio System are installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook (Handbook).
  • Page 286 Section 9 Cirrus Design Supplements SR20 Section 1 - General This supplement provides detailed operating instructions for the Garmin GMA 340 Audio Selector Panel/Intercom System with internal Marker Beacon. This supplement covers the basic operating areas of the Audio Control Panel.
  • Page 287 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations Use of auxiliary AUDIO IN entertainment input and the optionally installed XM Radio System is prohibited during takeoff and landing. Section 3 - Emergency Procedures In the event of an audio panel power failure, the audio system will revert to COM 1 for the pilot’s mic and headphones and the pilot will...
  • Page 288 Section 9 Cirrus Design Supplements SR20 A fail-safe circuit connects the pilot’s headset directly to the COM1 transceiver in the event of a power failure to the audio control panel or the panel is switched ‘OFF.’ Test Pressing the TEST button illuminates all Panel LEDs and the Marker Beacon Annunciators full bright.
  • Page 289 Cirrus Design Section 9 SR20 Supplements the copilot mic/audio source. The pilot has receive and transmit capabilities on COM1 and the copilot has receive and transmit capabilities on COM2. While split COM is active, simultaneous transmission from COM1 and COM2 is not possible. The pilot and copilot can still listen to COM3, NAV1, NAV2, DME, ADF, and MKR.
  • Page 290 Section 9 Cirrus Design Supplements SR20 The Audio Control Panel has provisions for up to two separate personal entertainment input (music) devices. These devices are plugged into the AUDIO INPUT jacks in the center console jack panels. Music1 is connected at the AUDIO INPUT jack near the convenience outlet.
  • Page 291 Cirrus Design Section 9 SR20 Supplements • Right Outer Knob – Copilot and passenger mic VOX level. CW rotation increases the amount of mic audio (VOX level) required to break squelch. Full CCW is the ‘hot mic’ position. Each microphone input has a dedicated VOX circuit to assure that only the active microphone(s) is/are heard when squelch is broken.
  • Page 292 Section 9 Cirrus Design Supplements SR20 button. ALL mode is active when neither PILOT or CREW have been selected. PILOT The pilot is isolated from the intercom. The pilot can hear radio and sidetone only during radio transmissions. Copilot and passengers can hear the intercom and music but not the airplane radio receptions or pilot transmissions.
  • Page 293 Cirrus Design Section 9 SR20 Supplements Marker beacon audio is selected by pressing the MKR push-button. If no marker beacon signal is being received, pressing the MKR push- button a second time deselects marker beacon audio. However, if marker beacon is being received, pressing the MKR push-button a second time will mute the audio but the light will continue to flash.
  • Page 294 Section 9 Cirrus Design Supplements SR20 XM Radio System (Optional Installation) • Note • For a detailed operating instructions, refer to the XM Radio Wireless Controller User Instructions, Document XMC050-4, original release later. software partnumber 530-00162-000 or later is required for installation of XM Radio System.
  • Page 295 FAA Approved Airplane Flight Manual Supplement Dual Alternator System When the Dual Alternator System is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
  • Page 296 Section 9 Cirrus Design Supplements SR20 Section 1 - General This airplane is equipped with a Dual Alternator System. Refer to Section 7 in this supplement for a full description of the system. Section 2 - Limitations Kinds of Operation Equipment List...
  • Page 297 Cirrus Design Section 9 SR20 Supplements Section 3 - Emergency Procedures Alternator Failure Abnormal ammeter indications and illumination of the ALT FAIL caution light(s) and/or illumination of the LOW VOLTS warning light may indicate electrical power supply system malfunctions. A broken alternator drive belt, wiring fault or a defective alternator control unit is most likely the cause of the alternator failure.
  • Page 298 Section 9 Cirrus Design Supplements SR20 1. Affected ALT Master Switch .............OFF 2. Affected ALT Circuit Breaker ..........PULL 3. Nonessential Electrical Equipment ..........OFF 4. Land as soon as practical. Battery Ammeter Indicates Discharge In the event of a failure of an alternator, the associated ALT FAIL caution light illuminates.
  • Page 299 Cirrus Design Section 9 SR20 Supplements • Note • Switch equipment ‘Off’ or pull circuit breakers for non- essential equipment until BATT amps reading is zero (0) or positive. 8. If total power failure anticipated, Turn Coordinator Power..EMER 9. Land as soon as practical.
  • Page 300 Section 9 Cirrus Design Supplements SR20 Section 7 - Systems Description Electrical System The airplane is equipped with 28-volt direct current (VDC) electrical system. The system provides uninterrupted power for avionics, flight instruments, lighting and other electrically operated and controlled systems during normal operation.
  • Page 301 Cirrus Design Section 9 SR20 Supplements Should both alternators fail, the battery will supply system current and a discharge rate will be indicated on the ammeter. Under these conditions, depending on electrical system load, the LOW VOLTS warning light will illuminate when system voltage drops below approximately 24.5 volts.
  • Page 302 Section 9 Cirrus Design Supplements SR20 avionics power switch must also be turned on. Positioning either ALT switch to the off position isolates the associated alternator from the electrical system and the entire electrical load is placed on the operative alternator. If both ALT switches are in the off position the entire electrical load is placed on the battery.
  • Page 303 Cirrus Design Section 9 SR20 Supplements • Note • Illumination of ALT FAIL caution light may occur during low RPM conditions with an electrical load on the system, such as during a low RPM taxi. Under these conditions, the light will go out at higher RPM.
  • Page 304 Section 9 Cirrus Design Supplements SR20 ESSENTIAL 1 and ESSENTIAL 2 circuit breakers. Avionics loads on the Non-essential Avionics Bus and Essential Avionics Bus are protected by 15-amp AVIONICS circuit breakers connected to the respective bus through relays energized by the AVIONICS switch.
  • Page 305 Stormscope Sensor When the L-3 Avionics Systems WX500 Stormscope Sensor is installed in the Cirrus Design SR20, 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.
  • Page 306 Section 9 Cirrus Design Supplements SR20 Section 1 General This airplane is equipped with a L-3 Avionics Systems WX500 Stormscope Sensor. The stormscope sensor output is displayed on the Multi-Function Display (MFD). Refer to L-3 Avionics Systems WX500 Stormscope Series II Weather Mapping Sensor User’s Guide, P/N 009-11501-001 revision C or later...
  • Page 307 Cirrus Design Section 9 SR20 Supplements STRK or CELL – STRK will be displayed if the Strike mode is selected. In this mode, individual strikes are plotted using the ‘X’ symbol. CELL will be displayed if the CELL mode is selected. In the Cell mode a ‘+’...
  • Page 308 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 4 of 4 P/N 11934-S11 Revision 01: 07-18-05...
  • Page 309 FAA Approved Airplane Flight Manual Supplement Garmin GTX 327 Transponder When a Garmin GTX 327 Transponder is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
  • Page 310 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a single Garmin GTX 327 ATC Mode A/ C (identification and altitude) transponder with squawk capability. This supplement provides complete operating instructions for the GTX 327 and does not require any additional data be carried in the airplane.
  • Page 311 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations No Change Section 3 - Emergency Procedures No Change Section 4 - Normal Procedures • Note • Expected coverage from the GTX 327 is limited to “line of sight.” Low altitude or aircraft antenna shielding by the airplane itself may result in reduced range.
  • Page 312 Section 9 Cirrus Design Supplements SR20 Section 5 - Performance No Change Section 6 - Weight & Balance No Change Section 7 - Systems Description • Note • This supplement provides specific procedures for use of the GTX 327 Transponder in the SR20 and a general description of the unit.
  • Page 313 Cirrus Design Section 9 SR20 Supplements Mode Selector Keys The mode selector keys are located in a circular arrangement immediately to the left of the display window. The selected mode is annunciated at the left side of the display immediately adjacent to the selector keys.
  • Page 314 Section 9 Cirrus Design Supplements SR20 Code Selector Keys Code selection is accomplished by depressing the eight selector keys (numbered 0 - 7) located immediately below the display. Any of 4096 active identification codes can be selected. The selected code must be in accordance with instructions for IFR flight or rules applicable to transponder utilization for VFR flight.
  • Page 315 Cirrus Design Section 9 SR20 Supplements Reply Light The reply light is the small reverse video “R” immediately below the mode annunciation in the display window. The reply light will blink each time the transponder replies to ground interrogations. The light will remain on during the 18-second IDENT time interval.
  • Page 316 Section 9 Cirrus Design Supplements SR20 COUNT DOWN TIMER - The count down timer is controlled by the START / STOP key. The CRSR and “0 - 9” keys are used to set the initial time. Pressing the CLR key resets the timer to the initial value.
  • Page 317 S-Tec System 55X Autopilot When the S-Tec System Fifty Five X (55X) Autopilot is installed in the Cirrus Design SR20, 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.
  • Page 318 Section 9 Cirrus Design Supplements SR20 Section 1 - General This airplane is equipped with an S-TEC System 55X Autopilot. The System 55X autopilot is a two-axis autopilot system. The system consists of a flight guidance programmer/computer, altitude encoder, altitude selector / alerter, turn coordinator, and HSI. Mode selection and vertical speed selection is made on the programmer/computer panel.
  • Page 319 Cirrus Design Section 9 SR20 Supplements Roll and pitch information are displayed on attitude indicator. Autopilot Flight Director is not implemented in this installation. Section 2 - Limitations 1. Autopilot operation is prohibited above 185 KIAS. 2. The autopilot must not be engaged for takeoff or landing.
  • Page 320 Section 9 Cirrus Design Supplements SR20 g. The ILS is flown at normal approach speeds, and within any STC or TC speed constraints and as defined in this flight manual. h. The flaps should be extended in the approach configuration prior to the Outer Marker.
  • Page 321 Cirrus Design Section 9 SR20 Supplements S-TEC FIFTY FIVE X REV TRIM SR20_FM09_1509 Figure - 1 System 55X Autopilot Programmer/Computer P/N 11934-S13 5 of 16 Revision 04: 08-15-07...
  • Page 322 Section 9 Cirrus Design Supplements SR20 Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the SR20 POH. Do not reengage the autopilot until the malfunction has been identified and corrected. The autopilot may be disconnected by: 1.

  • Page 323: System Failure And Caution Annunciations

    Cirrus Design Section 9 SR20 Supplements System Failure and Caution Annunciations If any of the following failure annunciations occur at low altitude or during an actual instrument approach, disengage the autopilot, execute a go-around or missed approach as appropriate. Inform ATC of problem.
  • Page 324 Section 9 Cirrus Design Supplements SR20 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot and altitude selector and their respective modes. • WARNING • The pilot must properly monitor and control the engine power to avoid stalling the airplane in autopilot altitude hold or vertical speed modes.
  • Page 325 Cirrus Design Section 9 SR20 Supplements 6. Overpower Test: a. Grasp control yoke and input left aileron, right aileron, nose up, and nose down to overpower autopilot. Overpower action should be smooth in each direction with no noise or jerky feel.
  • Page 326 Section 9 Cirrus Design Supplements SR20 Altitude Hold Mode 1. Manually fly the airplane to the desired altitude and level off. • Note • For smoothest transition to altitude hold, the airplane rate of climb or descent should be less than 100 FPM when Altitude Hold is selected.
  • Page 327 Cirrus Design Section 9 SR20 Supplements autopilot will synchronize to and hold the vertical speed at the time the mode was engaged. • Note • The vertical speed is displayed in 100-foot increments on the programmer/computer window or on the vertical speed indicator on the PFD.
  • Page 328 Section 9 Cirrus Design Supplements SR20 Turns while in GPSS mode can exceed the standard rate by 20% to 30%. In NAV mode while tracking a GPS or VOR/LOC signal, during the intercept sequence the autopilot operates at maximum gain and sensitivity (90% of standard rate turn). When the selected course is intercepted, course deviation needle centered, the course-tracking program is activated.
  • Page 329 Cirrus Design Section 9 SR20 Supplements Glideslope Intercept and Tracking 1. Begin with a reliable ILS signal selected on the NAV receiver. 2. Select autopilot NAV and APR. Airplane must be within 50% needle deviation of localizer centerline. 3. Select ALT mode. Airplane must be 60% or more below the glideslope centerline during the approach to the intercept point.
  • Page 330 Section 9 Cirrus Design Supplements SR20 steering is accomplished by autopilot steering commands to the aileron trim motor and spring cartridge. The pitch computer receives altitude data from the altitude encoder pressure transducer plumbed into the static system, an accelerometer, and glideslope information from the HSI and #1 NAV radio.
  • Page 331 Cirrus Design Section 9 SR20 Supplements autopilot automatically initiates a tracking gain program to reduce turn rate to 45% standard rate, and then 15% standard rate. REV (Reverse Course) – When REV is selected, the autopilot will automatically execute high sensitivity gain for an approach where tracking the front course outbound or tracking the back course inbound is required.
  • Page 332 Section 9 Cirrus Design Supplements SR20 (-) value indicates descent. Vertical speed can be adjusted by rotating the VS knob on the programmer/computer. Clockwise rotation increases and counterclockwise rotation decreases rate of climb (or descent) 100 FPM for each 'click.' The maximum adjustment is ±1600 FPM.
  • Page 333 Traffic Advisory System When the L-3 Avionics Systems SkyWatch 497 is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the appropriate Cirrus Design Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
  • Page 334 Section 9 Cirrus Design Supplements SR20 Section 1 - General This airplane is equipped with a L-3 Avionics Systems SkyWatch SKY497 Traffic Advisory System to advise the pilot of transponder- equipped aircraft that may pose a collision threat. SkyWatch advisory information is displayed on the GARMIN 430 display.
  • Page 335 Cirrus Design Section 9 SR20 Supplements Section 4 - Normal Procedures After Engine Start 1. Avionics Power Switch ...............ON 2. SkyWatch will turn on, complete a self-test, and then enter the STBY mode. • Note • During the takeoff run, SkyWatch will automatically switch to operational mode approximately 8 seconds after 35 KIAS is achieved.
  • Page 336 Section 9 Cirrus Design Supplements SR20 Switch to Normal from the Standby Screen SkyWatch must be switched out of STBY to display traffic information. The ability to switch out of STBY on the ground is useful for scanning the airspace around the airfield prior to takeoff. Using the GNS 430 controls: 1.
  • Page 337 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 &...
  • Page 338 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.
  • Page 339 Garmin GNS 430 GPS Navigator When a Garmin GNS 430 GPS Navigator with NAV, ILS, and COM is installed in the Cirrus Design SR20 this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
  • Page 340 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a Garmin GNS 430 GPS Navigator with VHF Nav, ILS, and VHF Com herein referred to as the “Navigator.” The GNS 430 is capable of providing IFR enroute, terminal, and approach navigation with position accuracies better than 15 meters.
  • Page 341 Cirrus Design Section 9 SR20 Supplements Section 2 – Limitations Provided the GPS Navigator is receiving adequate usable signals, it has been demonstrated capable of and has been shown to meet the accuracy specifications of: 1. VFR/IFR, enroute, terminal, and instrument approach (GPS, VOR) operations, that is, enroute, terminal, and instrument approach within the U.S.
  • Page 342 Section 9 Cirrus Design Supplements SR20 6. The aircraft must have other approved navigation equipment installed and operating appropriate to the route of flight. 7. The Garmin GNS 430 meets RNP5 (BRNAV) requirements of AC 90-96 and is in accordance with AC 20-138, and JAA AMJ 20X2 Leaflet 2 Revision 01, provided it is receiving usable navigation information from the GPS receiver.
  • Page 343 Cirrus Design Section 9 SR20 Supplements The Navigator will display a welcome page while the self-test is in progress. When the self test is successfully completed, the Navigator asks for NavData database confirmation, acquires position, and then displays the acquired position on the Navigator’s display and on the MFD.
  • Page 344 Section 9 Cirrus Design Supplements SR20 2. Single GARMIN GNS 430 (GPS 1) interfaced with the HSI and MFD and a single GARMIN GNC 420 (GPS 2) interfaced with the CDI (VOR/LOC) indicator. a. In this configuration, pressing the alternate-action CDI push-...
  • Page 345 Cirrus Design Section 9 SR20 Supplements b. GPS 2 in this configuration is a GARMIN GNS 430 GPS Navigator with VHF Com interfaced with the CDI (VOR/LOC/ ILS/GS Indicator). Pressing the alternate-action CDI push- button on GPS 2 alternately selects GPS or NAV for display in the CDI each time the button is depressed.
  • Page 346 Section 9 Cirrus Design Supplements SR20 VHF NAV is powered by 28 VDC through the Avionics Master Switch and the 5-amp GPS2 circuit breaker on the Avionics Non-essential Bus. 28 VDC for transceiver operation is supplied through the Avionics master Switch and the 7.5-amp COM2 circuit breaker on the Avionics Non-Essential Bus.
  • Page 347 Cirrus Design Section 9 SR20 Supplements Jeppesen NavData card slot in each panel. The GNS 430 navigator is powered by 28 VDC through the 5-amp GPS1 circuit breaker on the Avionics Essential Bus. The Jeppesen Navigation Database provides access to data on...
  • Page 348 Section 9 Cirrus Design Supplements SR20 side of the GNS 430 front panel. Frequency tuning is accomplished by rotating the large and small concentric knobs to select a standby frequency and then transferring the frequency to the active window. The COM frequency display window is at the upper left corner of the GNS 430 display.
  • Page 349 • Note • When a GARMIN GNC 420 GPS Navigator with VHF COM is installed in the Cirrus Design SR20 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.
  • Page 350 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a GARMIN GNC 420 GPS Navigator with VHF Com herein referred to as the “Navigator.” The GNC 420 is capable of providing IFR enroute, terminal, and approach navigation with position accuracies better than 15 meters.
  • Page 351 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. The GARMIN GNC 420 Pilot's Guide and Reference, P/N 190- 00140-20, Revision B dated August 2002 (or later appropriate revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the GPS Navigator.
  • Page 352 Section 9 Cirrus Design Supplements SR20 Section 3 - Emergency Procedures 1. If GPS Navigator information is not available or is invalid, utilize remaining operational navigation equipment as required. 2. If "RAIM NOT AVAILABLE…" or “RAIM POSITION WARNING” message is displayed, continue to navigate using the GPS equipment or revert to an alternate means of navigation appropriate to the route and phase of flight.
  • Page 353 Cirrus Design Section 9 SR20 Supplements GPS Course Remote Display GNC 420 GPS course information is displayed on the airplane CDI. • Note • Since the GNC 420 does not provide ILS outputs, the CDI utilized in this installation does not provide glideslope display.
  • Page 354 Section 9 Cirrus Design Supplements SR20 GPS Navigator The GARMIN GNC 420 GPS navigator is the secondary system (GPS 2), is IFR certified, and is coupled to the airplane’s CDI. The GARMIN GNC 420 GPS navigator is capable of providing IFR enroute, terminal, and approach navigation with position accuracies better than 15 meters.
  • Page 355 Cirrus Design Section 9 SR20 Supplements channels). The tuning controls are located at the left side of the GNC 420 front panel. Frequency tuning is accomplished by rotating the large and small concentric knobs to select a standby frequency and then transferring the frequency to the active window.
  • Page 356 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 8 of 8 P/N 11934-S23 Revision 02: 08-15-07...
  • Page 357 Awareness Warning System When the Honeywell KGP 560 Terrain Awareness and Warning System is installed in the Cirrus Design SR20, 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.
  • Page 358 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with an Honeywell KGP 560 Terrain Awareness and Warning System that performs the functions of a Class C Terrain Awareness and Warning System (TAWS) in accordance with TSO C151b.
  • Page 359 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. Do not use the Terrain Awareness Display for navigation of the aircraft. The KGP 560 Terrain Awareness and Warning System is intended to serve as a situational awareness tool only and may not provide the accuracy fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions.
  • Page 360 Section 9 Cirrus Design Supplements SR20 Activate TAWS • Note • If the aircraft horizontal position derived from the Garmin Navigator (GPS 1) is invalid, TAWS will be inoperative and the TERR INOP annunciator will illuminate. 1. SKYWATCH/TAWS Circuit Breaker..........IN 2.
  • Page 361 Cirrus Design Section 9 SR20 Supplements Response To Awareness Alerts Aural “TERRAIN AHEAD” Alert Aural “OBSTACLE AHEAD” Alert Amber TERR CAUT Annunciation 1. Take positive corrective action until the alert ceases. Stop descending, or initiate a climb turn as necessary, based on analysis of all available instruments and information.
  • Page 362 Section 9 Cirrus Design Supplements SR20 Section 7 - Systems Description The Honeywell KGP 560 Terrain Awareness and Warning System compares GPS information from the Garmin Navigator (GPS 1) to the integrated Terrain/Obstacle Database to produce a real-time model of the surrounding terrain.
  • Page 363 Cirrus Design Section 9 SR20 Supplements GNS-430 TAWS Annunciator Panel GMA 340 Audio Panel Avidyne PFD KGP 560 Processor Transponder Avidyne MFD TAWS AVIONICS NON-ESSENTIAL Configuration Module SR20_FM09_2031 Figure - 1 Honeywell KGP 560 TAWS Simplified Schematic P/N 11934-S30 7 of 12...
  • Page 364 Section 9 Cirrus Design Supplements SR20 TAWS Annunciator Panel TAWS terrain annunciations and control functions are incorporated into the Annunciator Panel. The panel consists of a momentary pushbutton switch (SELF TEST), an illuminated pushbutton switch (TERR INHIBIT), and three LEDS for Terrain Warning (TERR WARN), Terrain Caution (TERR CAUT), Terrain Inoperative (TERR INOP).
  • Page 365 Cirrus Design Section 9 SR20 Supplements TAWS SELF TERR TERR TERR TERR TEST INHIBIT INOP CAUT WARN SR20_FM09_2033 Annunciator Color Function SELF TEST Provides test function for TAWS TERR INHIBIT AMBER All TAWS alerting functions inhibited TERR INOP AMBER Indicates TAWS inoperative...
  • Page 366 Section 9 Cirrus Design Supplements SR20 MFD Terrain Awareness Display • WARNING • Do not use the Terrain Awareness Display for navigation of the aircraft. The TAWS is intended to serve as a situational awareness tool only and may not provide the accuracy fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions.
  • Page 367 Cirrus Design Section 9 SR20 Supplements Geometric Altitude versus Measured Sea Level An indication of MSL-G or Geometric Altitude may appear on the left side of the MFD indicating the height above Measured Sea Level (MSL) calculated from the GPS.
  • Page 368 Section 9 Cirrus Design Supplements SR20 Self Test Proper operation of the TAWS can be verified when the aircraft is on the ground as follows: 1. Select the TAWS page on the MFD 2. Clear all caution messages in the lower right corner 3.
  • Page 369 Instrumentation When the Avidyne EMax™ Engine Instrumentation 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.
  • Page 370 Section 9 Cirrus Design Supplements SR20 Section 1 - General EMax™ Engine Instrumentation provides the pilot with engine parameters depicted on simulated gauges and electrical system parameters located in a dedicated region within in the EX5000C MFD display. Figure - 1 Avidyne EMax™...
  • Page 371 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations No Change. Section 3 - Emergency Procedures No Change. Section 4 - Normal Procedures No Change. Section 5 - Performance No Change. Section 6 - Weight & Balance Installation of the Avidyne Engine Instruments adds the following optional (Sym = O) equipment at the weight and arm shown in the following table.
  • Page 372 Section 9 Cirrus Design Supplements SR20 providing full-time recording critical engine performance parameters. The Engine Instruments system is powered by 28 VDC supplied through the 5-amp Engine Instruments breaker on the Main Bus 1. Refer to Avidyne FlightMax EX5000C Pilot’s Guide for a more complete description of EMax Engine Instruments, its operating modes, and additional detailed operating procedures.
  • Page 373 Approach Charts When the Avidyne CMax™ Electronic Approach Charts 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.
  • Page 374 Section 9 Cirrus Design Supplements SR20 Section 1 - General Avidyne CMax™ Electronic Approach Charts allows the pilot to view terminal procedure chart data on the EX5000C MFD. If the chart is geo-referenced, an ownship symbol and flight plan legs can be overlaid on the chart to further enhance the pilot’s situational...
  • Page 375 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. Do not use the CMax Approach Charts function for navigation of the aircraft. The CMax Approach Charts function is intended to serve as a situational awareness tool only. 2. The Avidyne FlightMax EX5000C Pilot’s Guide, P/N 600-00108- 000, Revision 03 or later, must be available to the pilot during all flight operations.
  • Page 376 Section 9 Cirrus Design Supplements SR20 Refer to Avidyne FlightMax EX5000C Pilot’s Guide, for a more complete description of CMax Approach Charts, its operating modes, and additional detailed operating procedures. 4 of 4 P/N 11934-S32 Revision 01: 12-15-07...
  • Page 377 XM Satellite Weather System When the XM Satellite Weather System 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.
  • Page 378 Section 9 Cirrus Design Supplements SR20 Section 1 - General The XM Satellite Weather System enhances situational awareness by providing the pilot with real time, graphical weather information depicted on the MAP page of the EX5000C MFD display. Figure - 1...
  • Page 379 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. Do not use the XM Satellite Weather System for navigation of the aircraft. The XM Satellite Weather System is intended to serve as a situational awareness tool only. Section 3 - Emergency Procedures No Change.
  • Page 380 Section 9 Cirrus Design Supplements SR20 • METARs • SIGMETs • AIRMETs • TFRs • Lightning Strikes The XM Satellite Weather System is powered by 28 VDC supplied through the 3-amp Weather/Stormscope breaker on the Non-Essential Bus. Refer to Avidyne FlightMax EX5000C Pilot’s Guide for a more complete description of XM Satellite Weather System, its operating modes, and additional detailed operating procedures.
  • Page 381 Safety Information Section 10 Safety Information Table of Contents Introduction ................... 10-3 Cirrus Airframe Parachute System (CAPS) Deployment ....10-4 Deployment Scenarios............... 10-4 Mid-air Collision ..............10-4 Structural Failure ..............10-4 Loss of Control ............... 10-5 Landing Required in Terrain not Permitting a Safe Landing... 10-5 Pilot Incapacitation ..............
  • Page 382 Section 10 Cirrus Design Safety Information SR20 Intentionally Left Blank 10-2 P/N 13999-002 Info Manual September 2011...

  • Page 383: Introduction

    SR20 Safety Information Introduction The Cirrus Design SR20 is a modern, advanced technology airplane designed to operate safely and efficiently in a flight environment. However, like any other aircraft, pilots must maintain proficiency to achieve maximum safety, utility, and economy.

  • Page 384: Cirrus Airframe Parachute System (Caps) Deployment

    SR20 Cirrus Airframe Parachute System (CAPS) Deployment The Cirrus Airframe Parachute System (CAPS) is designed to lower the aircraft and its passengers to the ground in the event of a life- threatening emergency. However, because CAPS deployment is expected to result in damage to the airframe and, depending upon...

  • Page 385: Loss Of Control

    Cirrus Design Section 10 SR20 Safety Information continued safe flight and landing. If it is not, CAPS activation should be considered. Loss of Control Loss of control may result from many situations, such as: a control system failure (disconnected or jammed controls); severe wake turbulence, severe turbulence causing upset, severe airframe icing, or sustained pilot disorientation caused by vertigo or panic;...

  • Page 386: Deployment Altitude

    Section 10 Cirrus Design Safety Information SR20 if time and altitude are critical, and/or ground impact is imminent, the CAPS should be activated regardless of airspeed. Deployment Altitude No minimum altitude for deployment has been set. This is because the actual altitude loss during a particular deployment depends upon the airplane’s airspeed, altitude and attitude at deployment as well as...

  • Page 387: Landing Considerations

    Cirrus Design Section 10 SR20 Safety Information Landing Considerations After a CAPS deployment, the airplane will descend at less than 1500 feet per minute with a lateral speed equal to the velocity of the surface wind. The CAPS landing touchdown is equivalent to ground impact from a height of approximately 10 feet.

  • Page 388: Water Landings

    Section 10 Cirrus Design Safety Information SR20 If the pilot elects to touchdown with a door opened, there are several additional factors the pilot must consider: loss of door, possibility of head injury, or injury from an object coming through the open door.

  • Page 389: Post Impact Fire

    Cirrus Design Section 10 SR20 Safety Information consider unlatching a door prior to assuming the emergency landing body position in order to provide a ready escape path should the airplane begin to sink. Post Impact Fire If there is no fire prior to touchdown and the pilot is able to shut down the engine, fuel, and electrical systems, there is less chance of a post impact fire.

  • Page 390: Taxiing, Steering, And Braking Practices

    Safety Information SR20 Taxiing, Steering, and Braking Practices Cirrus aircraft use a castering nose wheel and rely on aerodynamic forces and differential braking for directional control while taxiing. Proper braking practices are therefore critical to avoid potential damage to the brakes.

  • Page 391: Brake Maintenance

    Cirrus Design Section 10 SR20 Safety Information • Do not “ride the brakes”. Pilots should consciously remove pressure from the brakes while taxiing. Failure to do so results in excessive heat buildup, premature brake wear, and increased possibility of brake failure or fire.
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