Cirrus SR20 Information Manual
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Cirrus SR20 Information Manual

Aircraft serials 2016 and subsequent with cirrus perspective avionics system
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Download this manual See also: Pilot Operating Handbook, Information Manual
AIRPLANE INFORMATION MANUAL
for the
CIRRUS DESIGN SR20
A i r c r a f t S e r i a l s 2 0 1 6 a n d S u b s e q u e n t w i t h
C i r r u s P e r s p e c t i v e A v i o n i c s S y s t e m
At the time of issuance, this Information Manual was harmo-
nized with the SR20 Pilot's Operating Handbook September
2011 (P/N 11934-004), 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 13999-004
September 2011
Information Manual

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  • Page 1 C i r r u s P e r s p e c t i v e A v i o n i c s S y s t e m At the time of issuance, this Information Manual was harmo- nized with the SR20 Pilot's Operating Handbook September 2011 (P/N 11934-004), and will not be kept current.
  • 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 ..................3 The Airplane..................7 Engine..................... 7 Propeller ..................7 Fuel....................8 Oil ....................8 Maximum Certificated Weights ............8 Cabin and Entry Dimensions ............8 Baggage Spaces and Entry Dimensions ........8 Specific Loadings................
  • Page 4 Section 1 Cirrus Design General SR20 Intentionally Left Blank P/N 13999-004 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 ft 7.92 m 8.9 ft 2.71 m 9 inches (minimum) 23 cm (minimum) NOTE: • Wing span includes position and strobe lights. • Prop ground clearance at 3050 lb - 9 inches (23 cm).
  • Page 7 Cirrus Design Section 1 SR20 General 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 SR22_FM06_1019 Location Length Width Height Volume 122” 49.3” 49.7 137 cu ft Cabin 36”...
  • Page 8 Section 1 Cirrus Design General SR20 GROUND TURNING CLEARANCE 24.3 ft. (7.41 m) RADIUS FOR WING TIP 7.0 ft. (2.16 m) RADIUS FOR NOSE GEAR 0.5 ft. (0.15 m) RADIUS FOR INSIDE GEAR 9.1 ft. (2.77 m) RADIUS FOR OUTSIDE GEAR TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER.

  • Page 9: The Airplane

    Cirrus Design Section 1 SR20 General 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..........

  • Page 10: Fuel

    Section 1 Cirrus Design General SR20 Fuel Total Capacity ..........58.5 U.S. Gallons (221.0 L) Total Usable ..........56.0 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 11: Symbols, Abbreviations And Terminology

    Cirrus Design Section 1 SR20 General 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 12: Meteorological Terminology

    Section 1 Cirrus Design General SR20 Stalling Speed is the minimum steady flight speed at which aircraft controllable 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 13: Engine Power Terminology

    Cirrus Design Section 1 SR20 General • 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 14: Weight And Balance Terminology

    Section 1 Cirrus Design General SR20 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 15 Cirrus Design Section 1 SR20 General • 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 16 Section 1 Cirrus Design General SR20 Intentionally Left Blank 1-14 P/N 13999-004 Info Manual September 2011...
  • Page 17 Environmental Conditions ..............17 Maximum Occupancy ..............17 Systems and Equipment Limits............18 Cirrus Perspective Integrated Avionics System ......18 L-3 Skywatch Traffic Advisory System (Optional)......21 L-3 Stormscope Weather Information System (Optional) ..... 21 Max Viz Enhanced Vision System (Optional) ....... 21 Air Conditioning System (Optional)..........
  • Page 18 Section 2 Cirrus Design Limitations SR20 Smoking ..................22 Placards ................... 23 P/N 13999-004 Info Manual September 2011...

  • Page 19: Introduction

    Cirrus Design Section 2 SR20 Limitations Introduction The limitations included in this Section of the Pilot’s Operating Handbook (POH) are approved by the Federal Aviation Administration. This section provides operating limitations, instrument markings and basic placards required by regulation and necessary for the safe operation of the aircraft and its standard systems and equipment.

  • Page 20: 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 21: 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 22: Powerplant Limitations

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

  • Page 23: 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 24: Engine Instrument Markings & Annunciations

    Section 2 Cirrus Design Limitations SR20 Engine Instrument Markings & Annunciations The following describes the engine instrument markings. Associated Warning and Caution Annunciations are shown in capitalized text. PowerPlant Yellow Green Arc/ Yellow Arc/ Arc/Bar Arc/Bar Arc/Bar Instrument (Range & Units)

  • Page 25: Fuel

    Cirrus Design Section 2 SR20 Limitations Fuel Yellow Green Yellow Arc/Bar Arc/Bar Arc/Bar Arc/Bar Arc/Bar Instrument (Range & Units) Minimum Maximum Caution Normal Caution Minimum Range Range Range Maximum Fuel Flow –– –– 0 – 20 –– –– (0 – 20 U.S. Gal/Hr) Fuel Totalizer N <...

  • Page 26: Center Of Gravity Limits

    Section 2 Cirrus Design Limitations SR20 Center of Gravity Limits Reference Datum ........100 inches forward of firewall Forward..............Refer to Figure 2-1 Aft ................Refer to Figure 2-1 3100 3050 FS 148.1 FS 140.7 3000 3050 lb 3050 lb 2950 2900 2850 2800 FS 139.1...

  • Page 27: Maneuver Limits

    60°. • Note • Because the aircraft 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, Spins.

  • Page 28: Kinds Of Operation

    Section 2 Cirrus Design Limitations SR20 Kinds of Operation The aircraft 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 29 Cirrus Design Section 2 SR20 Limitations Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions ALT 1 Annunciator ALT 2 Annunciator — — Circuit Breakers As required. Equipment & Furnishings Emergency Locator Trans- mitter Restraint System One seat belt for each occupant.
  • Page 30 Section 2 Cirrus Design Limitations SR20 Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions Ice & Rain Protection Alternate Engine Air Induc- tion System Alternate Static Air Source Pitot Heater — — Landing Gear Wheel Pants —...
  • Page 31 Cirrus Design Section 2 SR20 Limitations Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions Altimeter Magnetic Compass Pitot System Static System, Normal Attitude Indicator — — Clock — — Gyroscopic Directional Indi- — — cation (HSI) Magnetometer —...

  • Page 32: Icing

    Oil Pressure Indication Oil Quantity Indicator (Dip- stick) Oil Temperature Indication Engine Speed Special Equipment Cirrus Airframe Parachute (CAPS) Icing Flight into known icing conditions is prohibited. Runway Surface This airplane may be operated on any smooth runway surface. 2-16...

  • Page 33: Taxi Power

    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 34: Systems And Equipment Limits

    Systems and Equipment Limits Cirrus Perspective Integrated Avionics System 1. The appropriate revision of the Cirrus Perspective Cockpit Reference Guide (p/n 190-00821-XX, where X can be any digit from 0 to 9) must be immediately available to the pilot during flight.
  • Page 35 The Perspective Integrated Avionics System is compliant with AC 90-100A. As such, the Cirrus Perspective system is eligible to fly RNAV 'Q' or 'T' routes, RNAV SID/STAR/ODPs and eligible to use RNAV substitution or RNAV alternate means of navigation (US Only).
  • Page 36 Section 2 Cirrus Design Limitations SR20 5. Navigation using the Perspective Integrated Avionics System is not authorized in the following geographic areas: a. north of 70°North latitude (northern polar region), b. south of 70°South latitude (southern polar region), c. north of the 65°North latitude between longitude 75°W and 120°W (Northern Canada),...

  • Page 37: Skywatch Traffic Advisory System (Optional)

    Cirrus Design Section 2 SR20 Limitations 12. Use of use of portable electronic devices during takeoff and landing is prohibited. L-3 Skywatch Traffic Advisory System (Optional) 1. Traffic information shown on the Perspective Integrated Avionics System displays is provided as an aid in visually acquiring traffic.

  • Page 38: Inflatable Restraint System

    Airplane Maintenance Manual. Refer to Airplane Maintenance Manual (AMM), Chapter 51, for specific paint requirements. Cirrus Airframe Parachute System (CAPS) Maximum Demonstrated Deployment Speed....133 KIAS • Note •...
  • Page 39 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:...
  • Page 40 Section 2 Cirrus Design Limitations SR20 Elevator and Rudder, both sides: NO PUSH Left fuselage, on external power supply door: EXTERNAL POWER 28 V DC Doors, above and below latch: PUSH OPEN SR20_FM02_3002 Figure 2-3 Placards (Sheet 2 of 6)
  • Page 41 Cirrus Design Section 2 SR20 Limitations Engine control panel: CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT RICH TURN BOOST PUMP ON DURING TAKE OFF, CLIMB, LANDING AND SWITCHING FUEL TANKS. BOOST FUEL PUMP...
  • Page 42 Section 2 Cirrus Design Limitations SR20 Wing, flap aft edge and fuselage vortex generator: 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...
  • Page 43 Cirrus Design Section 2 SR20 Limitations Instrument Panel, center: DISPLAY BACKUP Bolster Panel, both sides: GRAB HERE Baggage Compartment, aft edge: ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Instrument Panel: FASTEN SEATBELTS • NO SMOKING Cabin Window, above door latch:...
  • Page 44 MUST BE WORN AT ALL TIMES USE OF THIS DEVICE COULD RESULT IN INJURY OR DEATH MAXIMUM DEMONSTRATED DEPLOYMENT SPEED 133 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 45 Cirrus Design Section 3 SR20 Emergency Procedures Section 3 Emergency Procedures Table of Contents Introduction ..................3 Emergency Procedures Guidance ............. 4 Preflight Planning................4 Preflight Inspections/Maintenance ..........4 Methodology ................... 4 Circuit Breakers ................5 Memory Items ................. 5 Airspeeds for Emergency Operations ..........
  • Page 46 Section 3 Cirrus Design Emergency Procedures SR20 High Fuel Flow ................22 Electrical System Emergencies............23 High Voltage on Main Bus 1 ............23 High Voltage on Main Bus 2 ............24 High or Low Voltage on Essential Bus.......... 25 Environmental System Emergencies ..........

  • Page 47: 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 aircraft. 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 48: Emergency Procedures Guidance

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

  • Page 49: Circuit Breakers

    121.500 MHz. If the display is available, it will also show it in the “Active” frequency window. 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. Refer to Section 10, Safety Information, for CAPS deployment information and landing considerations.

  • Page 50: Airspeeds For Emergency Operations

    Section 3 Cirrus Design Emergency Procedures SR20 Airspeeds for Emergency Operations Maneuvering Speed: 3050 lb ................130 KIAS 2600 lb ................120 KIAS 2200 lb ................110 KIAS Best Glide: 3050 lb ................99 KIAS 2500 lb ................95 KIAS Emergency Landing (Engine-out): Flaps Up................87 KIAS Flaps 50% ................82 KIAS...

  • Page 51: Engine Failures

    Cirrus Design Section 3 SR20 Emergency Procedures Engine Failures Engine Failure On Takeoff (Low Altitude) 1. Best Glide or Landing Speed (as appropriate) ... ESTABLISH 2. Mixture ................CUTOFF 3. Fuel Selector................OFF 4. Ignition Switch................OFF 5. Flaps ..............AS REQUIRED If time permits: 6.

  • Page 52: Engine Failure In Flight

    Section 3 Cirrus Design Emergency Procedures SR20 Engine Failure In Flight 1. Best Glide Speed ............ESTABLISH 2. Mixture ..............AS REQUIRED 3. Fuel Selector ............SWITCH TANKS 4. Fuel Pump................BOOST 5. Alternate Induction Air............... ON 6. Air Conditioner (if installed) ............OFF 7.

  • Page 53: Airstart

    Cirrus Design Section 3 SR20 Emergency Procedures Airstart Engine Airstart 1. Bat Master Switches ..............ON 2. Power Lever ..............½” OPEN 3. Mixture ..............RICH, AS REQ’D 4. Fuel Selector............SWITCH TANKS 5. Ignition Switch............... BOTH 6. Fuel Pump ................. BOOST 7.

  • Page 54: Smoke And Fire

    Section 3 Cirrus Design Emergency Procedures SR20 Smoke and Fire Cabin Fire In Flight 1. Bat-Alt Master Switches ........OFF, AS REQ’D 2. Fire Extinguisher ............ACTIVATE If airflow is not sufficient to clear smoke or fumes from cabin: 3. Cabin Doors ............PARTIALLY OPEN Airspeed may need to be reduced to partially open door in flight.

  • Page 55: Engine Fire In Flight

    Cirrus Design Section 3 SR20 Emergency Procedures 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. If the cause of fire is not...

  • Page 56: Wing Fire In Flight

    Section 3 Cirrus Design Emergency Procedures SR20 Wing Fire In Flight 1. Pitot Heat Switch..............OFF 2. Navigation Light Switch............OFF 3. Landing Light ................OFF 4. Strobe Light Switch ..............OFF 5. If possible, side slip to keep flames away from fuel tank and cabin.

  • Page 57: Smoke And Fume Elimination

    Cirrus Design Section 3 SR20 Emergency Procedures Smoke and Fume Elimination 1. Air Conditioner (if installed)............OFF 2. Temperature Selector............COLD 3. Vent Selector......FEET/PANEL/DEFROST POSITION 4. Airflow Selector .......SET AIRFLOW TO MAXIMUM If source of smoke and fume is firewall forward: a.

  • Page 58: Emergency Descent

    Section 3 Cirrus Design Emergency Procedures SR20 Emergency Descent Emergency Descent 1. Power Lever ................IDLE 2. Mixture ..............AS REQUIRED 3. Airspeed ..............V (200 KIAS) Amplification • Caution • If significant turbulence is expected do not descend at indicated airspeeds greater than V (163 KIAS).

  • Page 59: Forced Landings

    Cirrus Design Section 3 SR20 Emergency Procedures Forced Landings Emergency Landing Without Engine Power 1. Best Glide Speed ............ESTABLISH 2. Radio ..........Transmit (121.5 MHz) MAYDAY giving location and intentions 3. Transponder ............SQUAWK 7700 4. If off airport, ELT ............ACTIVATE 5.

  • Page 60: 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 4. Airplane................ EVACUATE 5. Flotation Devices.....INFLATE WHEN CLEAR OF AIRPLANE Amplification If available, life preservers should be donned and life raft should be prepared for immediate evacuation upon touchdown.

  • Page 61: Engine System Emergencies

    Cirrus Design Section 3 SR20 Emergency Procedures Engine System Emergencies Engine Partial Power Loss 1. Air Conditioner (if installed)............OFF 2. Fuel Pump ................. BOOST 3. Fuel Selector............SWITCH TANKS 4. Mixture ......CHECK appropriate for flight conditions 5. Power Lever ............... SWEEP 6.
  • Page 62 Section 3 Cirrus Design Emergency Procedures SR20 may prevent a fire at altitude. However, as the Power Lever is reduced during descent and approach to landing the cooling air may not be sufficient to prevent an engine fire. 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 63: Oil Pressure Out Of Range

    Cirrus Design Section 3 SR20 Emergency Procedures Oil Pressure Out of Range OIL PRESS Warning OIL PRESS 1. Oil Pressure Gage ............. CHECK If pressure low: a. Power ...... REDUCE to minimum for sustained flight b. Land as soon as possible.

  • Page 64: High Cylinder Head Temperature

    Section 3 Cirrus Design Emergency Procedures SR20 High Cylinder Head Temperature CHT Caution and Warning On-Ground 1. Power Lever ..............REDUCE 2. Annunciations and Engine Temperatures ...... MONITOR If Caution or Warning annunciation is still illuminated: 3. Power Lever ..........MINIMUM REQUIRED 4.

  • Page 65: Propeller System Emergencies

    Cirrus Design Section 3 SR20 Emergency Procedures Propeller System Emergencies Engine Speed High RPM Warning: Engine Speed High 1. Tachometer ................ CHECK If engine speed normal: a. If On-Ground ......CORRECT PRIOR TO FLIGHT b. If In-Flight ........... CONTINUE, MONITOR If engine speed high: a.

  • Page 66: Fuel System Emergencies

    Section 3 Cirrus Design Emergency Procedures SR20 Fuel System Emergencies Low Fuel Quantity FUEL QTY Warning FUEL QTY 1. Fuel Quantity Gages ............CHECK If fuel quantity indicates less than or equal to 7 gallons: a. If On-Ground.......REFUEL PRIOR TO FLIGHT b.

  • Page 67: Electrical System Emergencies

    Cirrus Design Section 3 SR20 Emergency Procedures Electrical System Emergencies High Voltage on Main Bus 1 M BUS 1 Warning M BUS 1 1. ALT 1 Master Switch ............CYCLE 2. M Bus 1 Voltage (M1) ............CHECK If M Bus 1 Voltage is greater than 32 volts 3.
  • Page 68 Section 3 Cirrus Design Emergency Procedures SR20 High Voltage on Main Bus 2 M BUS 2 Warning M BUS 2 1. Main Bus 1 Voltage (M1)............ CHECK If M Bus 1 Voltage is greater than 32 volts 2. Perform M Bus 1 Warning Checklist 3.

  • Page 69: High Or Low Voltage On Essential Bus

    Cirrus Design Section 3 SR20 Emergency Procedures High or Low Voltage on Essential Bus ESS BUS Warning ESS BUS 1. Essential Bus Voltage (ESS)..........CHECK If Essential Bus Voltage is greater than 32 volts: 2. Main Bus 1 and Main Bus 2 Voltages (M1 and M2)... CHECK 3.

  • Page 70: Environmental System Emergencies

    Section 3 Cirrus Design Emergency Procedures SR20 Environmental System Emergencies Carbon Monoxide Level High CO LVL HIGH Warning CO LVL HIGH 1. Air Conditioner (if installed) ............OFF 2. Temperature Selector............COLD 3. Vent Selector......FEET/PANEL/DEFROST POSITION 4. Airflow Selector ......SET AIRFLOW TO MAXIMUM 5.

  • Page 71: Integrated Avionics System Emergencies

    Cirrus Design Section 3 SR20 Emergency Procedures Integrated Avionics System Emergencies A “Red X” through any electronic display field, such as COM frequencies, NAV frequencies, or engine data, indicates that display field is not receiving valid data. Attitude & Heading Reference System (AHRS) Failure 1.

  • Page 72: Unusual Attitude Emergencies

    The aircraft 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 73: Inadvertent Spiral Dive During Imc Flight

    Cirrus Design Section 3 SR20 Emergency Procedures Inadvertent Spiral Dive During IMC Flight 1. Power Lever ................IDLE 2. Stop the spiral dive by using coordinated aileron and rudder control while referring to the attitude indicator and turn coordinator to level the wings.

  • Page 74: Other Emergencies

    Section 3 Cirrus Design Emergency Procedures SR20 Other Emergencies Power Lever Linkage Failure 1. Power Lever Movement............VERIFY 2. Power ................SET if able 3. Flaps ................ SET if needed 4. Mixture ........AS REQUIRED (full rich to cut-off) 5. Land as soon as possible.

  • Page 75: Left/Right Brake Over-Temperature Annunciation

    Cirrus Design Section 3 SR20 Emergency Procedures Left/Right Brake Over-Temperature Annunciation BRAKE TEMP Warning BRAKE TEMP 1. Stop aircraft and allow the brakes to cool. Amplification Annunciation indicates brake temperature is greater than 293°F. Refer to Section 10 - Safety Information: Taxiing, Steering, and Braking...

  • Page 76: Emergency Ground Egress

    Section 3 Cirrus Design Emergency Procedures SR20 Amplification • WARNING • Use extreme caution after shutdown if STARTER circuit breaker required pull (failed relay or solenoid). If breaker is unknowingly or unintentionally reset, starter will instantly engage if Battery 1 power is supplied; creating a hazard for ground personnel.

  • Page 77: Caps Deployment

    Cirrus Design Section 3 SR20 Emergency Procedures CAPS Deployment 1. Airspeed............MINIMUM POSSIBLE The maximum demonstrated deployment speed is 133 KIAS. 2. Mixture (If time and altitude permit) ........CUTOFF 3. Activation Handle Cover...........REMOVE 4. Activation Handle (Both Hands)....PULL STRAIGHT DOWN After Deployment: 5.
  • Page 78 Cirrus Design Emergency Procedures SR20 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. Expected impact in a fully stabilized deployment is equivalent to a drop from approximately 10 feet.
  • Page 79 Cirrus Design Section 3A SR20 Abnormal Procedures Section 3A Abnormal Procedures Table of Contents Introduction ..................3 Abnormal Procedures Guidance ............3 Circuit Breakers ................3 Flight Environment ................4 Inadvertent Icing Encounter ............4 Inadvertent IMC Encounter............. 4 Door Open In Flight ................ 4 Abnormal Landings ................
  • Page 80 Section 3A Cirrus Design Abnormal Procedures SR20 Landing Gear System ..............18 Brake Failure During Taxi ............. 18 Left/Right Brake Over-Temperature..........18 Other Conditions ................19 Aborted Takeoff ................19 Parking Brake Engaged Annunciation .......... 20 Communications Failure ............... 20...

  • Page 81: 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 82: Flight Environment

    Section 3A Cirrus Design Abnormal Procedures SR20 Flight Environment Inadvertent Icing Encounter 1. Pitot Heat .................. ON 2. Exit icing conditions. Turn back or change altitude. 3. Cabin Heat ..............MAXIMUM 4. Windshield Defrost ............FULL OPEN 5. Alternate Induction Air............... ON Amplification Flight into known icing conditions is prohibited.

  • Page 83: Abnormal Landings

    Cirrus Design Section 3A SR20 Abnormal Procedures Abnormal Landings 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 84: Engine System

    Section 3A Cirrus Design Abnormal Procedures SR20 Engine System Low Idle Oil Pressure OIL PRESS Caution OIL PRESS 1. If In-Flight ..........LAND as soon as practical Amplification Oil pressure between 10 psi and 30 psi at or above 1000 RPM This message will appear prior to engine start and should clear after engine start.

  • Page 85: Starter Engaged Annunciation

    Cirrus Design Section 3A SR20 Abnormal Procedures Starter Engaged Annunciation STARTER ENGAGED Caution START ENGAGE On-Ground 1. Ignition Switch......DISENGAGE prior to 20 Seconds 2. Battery Switches ...Wait 20 seconds before next start attempt If starter does not disengage (relay or solenoid failure): 3.

  • Page 86: Fuel System

    Section 3A Cirrus Design Abnormal Procedures SR20 Fuel System Low Fuel Quantity FUEL QTY Caution FUEL QTY 1. Fuel Quantity Gages ............CHECK If fuel quantity indicates less than or equal to 8 gallons: a. Land as soon as practical.

  • Page 87: Right Fuel Tank Quantity

    Cirrus Design Section 3A SR20 Abnormal Procedures Right Fuel Tank Quantity R FUEL QTY Advisory R FUEL QTY 1. Right Fuel Quantity Gage ..........CHECK If right fuel quantity indicates less than or equal to 8 gallons: a. If On-Ground ......REFUEL PRIOR TO FLIGHT b.

  • Page 88: Low Voltage On Main Bus 1

    Section 3A Cirrus Design Abnormal Procedures SR20 Electrical System Low Voltage on Main Bus 1 M BUS 1 Caution M BUS 1 1. Perform Alt 1 Caution (Failure) Checklist. Amplification Main Bus 1 Voltage is low, indicates Alt 1 failure; will typically be associated with low M1 voltage Alt 1 current indications, Battery 1 discharge and ALT 1 Caution message.

  • Page 89: Low Alternator 1 Output

    Cirrus Design Section 3A SR20 Abnormal Procedures Low Alternator 1 Output ALT 1 Caution (Failure) ALT 1 1. ALT 1 Circuit Breaker ..........CHECK & SET 2. ALT 1 Master Switch ............CYCLE If alternator does not reset (low A1 Current and M1 voltage): 3.

  • Page 90: Low Alternator 2 Output

    Section 3A Cirrus Design Abnormal Procedures SR20 Low Alternator 2 Output ALT 2 Caution (Failure) ALT 2 1. ALT 2 Circuit Breaker ..........CHECK & SET 2. ALT 2 Master Switch ............CYCLE If alternator does not reset (low A2 Current and M2 voltage less than M1 voltage): 3.

  • Page 91: Integrated Avionics System

    Cirrus Design Section 3A SR20 Abnormal Procedures Integrated Avionics System Avionics Switch Off AVIONICS OFF Caution AVIONICS OFF 1. AVIONICS Switch ........... ON, AS REQUIRED Amplification The AVIONICS master switch is off. PFD Cooling Fan Failure PFD 1 FAN FAIL Advisory PFD 1 FAN FAIL 1.

  • Page 92: Flight Displays Too Dim

    Section 3A Cirrus Design Abnormal Procedures SR20 Flight Displays Too Dim 1. INSTRUMENT dimmer knob ....OFF (full counter-clockwise) If flight displays do not provide sufficient brightness: 2. Revert to standby instruments. Amplification The instrument dimmer knob provides manual dimming control of the display screens, key and text backlighting, flap and Environmental Control System (ECS) status indicators, and standby instruments.

  • Page 93: Pitot Static System

    Cirrus Design Section 3A SR20 Abnormal Procedures Pitot Static System Pitot Static Malfunction Static Source Blocked 1. Pitot Heat ...................ON 2. Alternate Static Source ............OPEN Amplification 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...

  • Page 94: Pitot Heat Current Sensor Annunciation

    Section 3A Cirrus Design Abnormal Procedures SR20 Pitot Heat Current Sensor Annunciation PITOT HEAT FAIL Caution PITOT HEAT FAIL 1. Pitot Heat Circuit Breaker............ CYCLE 2. Pitot Heat ............. CYCLE OFF, ON If inadvertent icing encountered, perform Inadvertent Icing Encounter Emergency Checklist and: a.

  • Page 95: Flight Control System

    Cirrus Design Section 3A SR20 Abnormal Procedures Flight Control System Electric Trim/Autopilot Failure 1. Airplane Control ..........MAINTAIN MANUALLY 2. Autopilot (if engaged)..........DISENGAGE If Problem Is Not Corrected: 3. Circuit Breakers ........... PULL AS REQUIRED • PITCH TRIM • ROLL TRIM •...

  • Page 96: Landing Gear System

    Section 3A Cirrus Design Abnormal Procedures SR20 Landing Gear System Brake Failure During Taxi 1. Engine Power ............AS REQUIRED • To stop airplane - REDUCE • If necessary for steering - INCREASE 2. Directional Control .......MAINTAIN WITH RUDDER 3. Brake Pedal(s)..............PUMP If directional control can not be maintained: 4.

  • Page 97: Other Conditions

    Cirrus Design Section 3A SR20 Abnormal Procedures Other Conditions Aborted Takeoff 1. Power Lever ................IDLE 2. Brakes..............AS REQUIRED Amplification Use as much of the remaining runway as needed to safely bring the airplane to a stop or to slow the airplane sufficiently to turn off runway.

  • Page 98: Parking Brake Engaged Annunciation

    Section 3A Cirrus Design Abnormal Procedures SR20 Parking Brake Engaged Annunciation PARK BRAKE Caution PARK BRAKE 1. Parking Brake..............RELEASE 2. Monitor CAS for BRAKE TEMP Caution. Stop aircraft and allow the brakes to cool if necessary. Amplification Parking brake is set.
  • Page 99 Cirrus Design Section 4 SR20 Normal Procedures Section 4 Normal Procedures Table of Contents Introduction ..................3 Airspeeds for Normal Operation ............3 Normal Procedures ................4 Preflight Inspection ................. 4 Preflight Walk-Around ..............4 Before Starting Engine..............9 Starting Engine ................10 Before Taxiing................
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  • Page 101: 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. Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3050 lb.

  • Page 102: Normal Procedures

    Section 4 Cirrus Design Normal Procedures SR20 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 103 Cirrus Design Section 4 SR20 Normal Procedures 1. Cabin a. Required Documents..........On Board b. Avionics Power Switch............OFF c. Bat 2 Master Switch ............ON d. PFD ................Verify On e. Essential Bus Voltage..........23-25 Volts Flap Position Light ............OUT g.
  • Page 104 Section 4 Cirrus Design Normal Procedures SR20 3. Empennage a. Tiedown Rope .............Remove b. Horizontal and Vertical Stabilizers ......Condition • Note • Verify tape covering the forward and aft inspection holes located on outboard ends of horizontal stabilizer is installed and securely attached.
  • Page 105 Cirrus Design Section 4 SR20 Normal Procedures e. Tire ..........Condition, Inflation, and Wear • Caution • Clean and inspect temperature indicator installed to piston housing. If indicator center is black, the brake assembly has been overheated. The brake linings must be inspected and O- rings replaced.
  • Page 106 Section 4 Cirrus Design Normal Procedures SR20 d. External Power .............Door Secure e. Exhaust Pipe(s) ....Condition, Security, and Clearance 11. Left Main Gear and Forward Wing a. Wheel fairings ....... Security, Accumulation of Debris b. Tire ..........Condition, Inflation, and Wear •...

  • Page 107: Before Starting Engine

    Cirrus Design Section 4 SR20 Normal Procedures 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 108: Starting Engine

    Section 4 Cirrus Design Normal Procedures SR20 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 109 Cirrus Design Section 4 SR20 Normal Procedures 6. Power Lever ............FULL FORWARD 7. Fuel Pump ............ PRIME, then BOOST • Note • On first start of the day, especially under cool ambient conditions, holding Fuel Pump switch to PRIME for 2 seconds will improve starting.

  • Page 110: Before Taxiing

    Section 4 Cirrus Design Normal Procedures SR20 Before Taxiing 1. Flaps ................. UP (0%) 2. Radios/Avionics............AS REQUIRED 3. Cabin Heat/Defrost ..........AS REQUIRED 4. Fuel Selector ............SWITCH TANK Taxiing When taxiing, directional control is accomplished with rudder deflection and intermittent braking (toe taps) as necessary. Use only as much power as is necessary to achieve forward movement.

  • Page 111: Before Takeoff

    Cirrus Design Section 4 SR20 Normal Procedures 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 112 Section 4 Cirrus Design Normal Procedures SR20 c. Landing Light ..............ON d. Annunciator Lights............CHECK - Verify both ALT 1 and ALT 2 caution lights out and positive amps indication for each alternator. 16. Voltage ................CHECK 17. Pitot Heat ............... AS REQUIRED •...

  • Page 113: Takeoff

    Cirrus Design Section 4 SR20 Normal Procedures 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 114: Normal Takeoff

    Section 4 Cirrus Design Normal Procedures SR20 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 115 Cirrus Design Section 4 SR20 Normal Procedures 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 116: Cruise

    Section 4 Cirrus Design Normal Procedures SR20 Cruise Normal cruising is performed between 55% and 85% 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 117: Cruise Leaning

    Cirrus Design Section 4 SR20 Normal Procedures 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 118: Before Landing

    Section 4 Cirrus Design Normal Procedures SR20 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.

  • Page 119: Landing

    Cirrus Design Section 4 SR20 Normal Procedures Landing • Caution • Landings should be made with full flaps. Landings with less than full flaps are recommended only if the flaps fail to deploy or to extend the aircraft’s glide distance due to engine malfunction.

  • Page 120: Balked Landing/Go-Around

    Section 4 Cirrus Design Normal Procedures SR20 Balked Landing/Go-Around In a balked landing (go-around) climb, disengage autopilot, apply full power, then reduce the flap setting to 50%. If obstacles must be cleared during the go-around, climb at the best angle of climb with 50% flaps.

  • Page 121: Shutdown

    Cirrus Design Section 4 SR20 Normal Procedures Shutdown 1. Fuel Pump (if used) ..............OFF 2. Throttle..................IDLE • Caution • Note that the engine hesitates as the switch cycles through the “OFF” position. If the engine does not hesitate, one or both magnetos are not grounded.

  • Page 122: Environmental Considerations

    Section 4 Cirrus Design Normal Procedures SR20 Environmental Considerations Cold Weather Operation • Caution • An engine that has been superficially warmed, may start and appear to run satisfactorily, but can be damaged from lack of lubrication due to the congealed oil blocking proper oil flow through the engine.
  • Page 123 Cirrus Design Section 4 SR20 Normal Procedures 1. Ignition Switch................OFF • WARNING • Use caution when pulling the propeller through by hand. Make sure ignition switch is OFF, keys are out of ignition, and then act as if the engine will start.

  • Page 124: Hot Weather Operation

    Section 4 Cirrus Design Normal Procedures SR20 Hot Weather Operation Avoid prolonged engine operation on the ground. Fuel BOOST must be ON for engine start and takeoff, and should be ON during climb for vapor suppression which could occur under hot ambient conditions or after extended idle.

  • Page 125: Noise Characteristics/Abatement

    Cirrus Design Section 4 SR20 Normal Procedures Noise Characteristics/Abatement The certificated noise levels for the aircraft 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)
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  • Page 127 Cirrus Design Section 5 SR20 Performance Data Section 5 Performance Data Table of Contents Introduction ..................3 Associated Conditions Affecting Performance........ 3 Demonstrated Operating Temperature ........... 3 Airspeed Calibration - Normal Static Source........4 Airspeed Calibration - Alternate Static Source........5 Altitude Correction Normal Static Source: Primary Flight Display ........
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  • Page 129: 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 130: Airspeed Calibration - Normal Static Source

    Section 5 Cirrus Design Performance Data SR20 Airspeed Calibration - Normal Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Note • Indicated airspeed values assume zero instrument error. KCAS KIAS Flaps Flaps Flaps...

  • Page 131: Airspeed Calibration - Alternate Static Source

    Cirrus Design Section 5 SR20 Performance Data Airspeed Calibration - Alternate Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster & Vents .................. ON • Note • Indicated airspeed values assume zero instrument error.

  • Page 132: Altitude Correction Normal Static Source: Primary Flight Display

    Section 5 Cirrus Design Performance Data SR20 Altitude Correction Normal Static Source: Primary Flight Display Conditions: • Power for level flight or maximum continuous, whichever is less. • 3050 LB • Note • Add correction to desired altitude to obtain indicated altitude to fly.

  • Page 133: Altitude Correction Normal Static Source: Standby Altimeter

    Cirrus Design Section 5 SR20 Performance Data Altitude Correction Normal Static Source: Standby Altimeter Conditions: • Power for level flight or maximum continuous, whichever is less. • 3050 LB • Note • Add correction to desired altitude to obtain indicated altitude to fly.

  • Page 134: Altitude Correction Alternate Static Source: Primary Flight Display

    Section 5 Cirrus Design Performance Data SR20 Altitude Correction Alternate Static Source: Primary Flight Display Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster, & Vents .................. ON • Note • Add correction to desired altitude to obtain indicated altitude to fly.

  • Page 135: Altitude Correction Alternate Static Source: Standby Altimeter

    Cirrus Design Section 5 SR20 Performance Data Altitude Correction Alternate Static Source: Standby Altimeter Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster, & Vents.................. ON • Note • Add correction to desired altitude to obtain indicated altitude to fly.

  • Page 136: Temperature Conversion

    Section 5 Cirrus Design Performance Data SR20 Temperature Conversion 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 137: Outside Air Temperature For Isa Condition

    Cirrus Design Section 5 SR20 Performance Data Outside Air Temperature for ISA Condition Press ISA-40°C ISA-20°C ISA+10°C ISA+20°C Feet °C °F °C °F °C °F °C °F °C °F 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000...

  • Page 138: Stall Speeds

    Section 5 Cirrus Design Performance Data SR20 Stall Speeds Conditions: • Weight ......................3050 LB • CG ........................Noted • Power......................... Idle • Bank Angle .....................Noted • Note • Altitude loss during wings level stall may be 250 feet or more.

  • Page 139: Wind Components

    Cirrus Design Section 5 SR20 Performance Data Wind Components Example: • Runway Heading ....................10° • Wind Direction....................60° • Wind Velocity....................15 Knots • Note • The max demonstrated crosswind is 20 knots. Value not considered limiting. 0° 10° 20°...

  • Page 140: Takeoff Distance

    Section 5 Cirrus Design Performance Data SR20 Takeoff Distance Conditions: • Winds........................ Zero • Runway..................Dry, Level, Paved • Flaps......................... 50% • Air Conditioner....................OFF • Power....................Full Throttle • Mixture.................... Set per Placard • Note • The following factors are to be applied to the computed takeoff distance for the noted condition: •...

  • Page 141: Takeoff Distance - 3050 Lb

    Cirrus Design Section 5 SR20 Performance Data Takeoff Distance - 3050 LB WEIGHT = 3050 LB Headwind: Subtract 10% for each 12 Speed at Liftoff = 71 KIAS knots headwind. Speed over 50 Ft. Obstacle = 77 KIAS Tailwind: Add 10% for each 2 knots tail- Flaps - 50% ·...

  • Page 142: Takeoff Distance - 2500 Lb

    Section 5 Cirrus Design Performance Data SR20 Takeoff Distance - 2500 LB WEIGHT = 2500 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 tail- Flaps - 50% ·...

  • Page 143: Takeoff Climb Gradient

    Cirrus Design Section 5 SR20 Performance Data Takeoff Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps .........................50% • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.

  • Page 144: Takeoff Rate Of Climb

    Section 5 Cirrus Design Performance Data SR20 Takeoff Rate of Climb Conditions: • Power....................Full Throttle • Mixture.................... Set per Placard • Flaps......................... 50% • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude for unit time expended expressed in Feet per Minute.

  • Page 145: Enroute Climb Gradient

    Cirrus Design Section 5 SR20 Performance Data Enroute Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .......................Full Rich • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.

  • Page 146: Enroute Rate Of Climb

    Section 5 Cirrus Design Performance Data SR20 Enroute Rate of Climb Conditions: • Power....................Full Throttle • Mixture....................As Required • Flaps......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude in feet per unit time expressed in Feet per Minute.

  • Page 147: 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 148: Time, Fuel And Distance To Climb

    Section 5 Cirrus Design Performance Data SR20 Time, Fuel and Distance to Climb Conditions: • Power....................Full Throttle • Mixture....................... Full Rich • Fuel Density...................6.0 LB/GAL • Weight ......................3050 LB • Winds........................ Zero • Climb Airspeed ....................Noted • Note •...

  • Page 149: Cruise Performance

    Cirrus Design Section 5 SR20 Performance Data Cruise Performance Conditions: • Mixture ....................Best Power • Weight ......................2600 LB • Winds ....................... Zero • Shaded Cells: Cruise Pwr above 85% not recommended. • Note • Subtract 10 KTAS if nose wheel pant and fairing removed. Lower KTAS by 10% if nose and main wheel pants &...
  • Page 150 Section 5 Cirrus Design Performance Data SR20 ISA - 30°C ISA + 30°C Press RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH 8000 2700 22.2 12.9 11.6 11.4 2500 22.2 11.4 11.0 10.6 2500 21.2 10.9 10.5 10.2...

  • Page 151: Range / Endurance Profile

    Cirrus Design Section 5 SR20 Performance Data Range / Endurance Profile Conditions: • Weight ......................3000 LB • Temperature ..................Standard Day • Winds ....................... Zero • Mixture ....................See Tables • Total Fuel....................56 Gallons • Note • Fuel Remaining For Cruise accounts for 10.1 gallons for 45 minutes IFR reserve fuel at 75% power and fuel burn for descent.

  • Page 152: Range / Endurance Profile (Continued)

    Section 5 Cirrus Design Performance Data SR20 Range / Endurance Profile (Continued) 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...

  • Page 153: Balked Landing Climb Gradient

    Cirrus Design Section 5 SR20 Performance Data Balked Landing Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .......................Full Rich • Flaps ...................... 100% (DN) • Airspeed ..................Best Rate of Climb • Note • Balked Landing Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.

  • Page 154: Balked Landing Rate Of Climb

    Section 5 Cirrus Design Performance Data SR20 Balked Landing Rate of Climb Conditions: • Power....................Full Throttle • Mixture....................... Full Rich • Flaps...................... 100% (DN) • Climb Airspeed ....................Noted • Note • Balked Landing Rate of Climb values shown are the full flaps change in altitude for unit time expended expressed in Feet per Minute.

  • Page 155: Landing Distance

    Cirrus Design Section 5 SR20 Performance Data Landing Distance Conditions: • Winds ....................... Zero • Runway ..................Dry, Level, Paved • Flaps.......................100% • Power ..................3° Power Approach to 50 FT obstacle, then reduce power passing the estimated 50 foot point and smoothly continue power reduction to reach idle just prior to touchdown.
  • Page 156 Section 5 Cirrus Design Performance Data SR20 Landing Distance WEIGHT = 3050 LB Headwind: Subtract 10% per each Speed over 50 Ft Obstacle = 78 KIAS 13 knots headwind. Flaps - 100% · Idle · Dry, Level Paved Surface Tailwind: Add 10% for each 2 knots tailwind up to 10 knots.
  • Page 157 Cirrus Design Section 6 SR20 Weight and Balance Data Section 6 Weight and Balance Data Table of Contents Introduction ..................3 Airplane Weighing Form ..............4 Airplane Weighing Procedures ............5 Loading Instructions ................8 Weight and Balance Loading Form............ 9 Loading Data..................
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  • Page 159: Introduction

    Cirrus Design Section 6 SR20 Weight and Balance Data 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.

  • Page 160: Airplane Weighing Form

    Section 6 Cirrus Design Weight and Balance Data SR20 Airplane Weighing Form REF DATUM FS 0.0 FS 100.0 FS 142.5 WL 100.0 A = x + 100 B = A - y y = ____________ Measured x = ____________ Measured...

  • Page 161: Airplane Weighing Procedures

    Cirrus Design Section 6 SR20 Weight and Balance Data 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 162 Section 6 Cirrus Design Weight and Balance Data SR20 side of the firewall (FS 100). Add 100 to this measurement to obtain left and right weighing point arm (dimension ‘A’). Typically, dimension ‘A’ will be in the neighborhood of 157.5.
  • Page 163 Cirrus Design Section 6 SR20 Weight and Balance Data Airplane Leveling Spirit Level LONGITUDINAL LEVELING Spirit Level Straight Edge Straight Edge Straight Edge Spacer Spacer Block Block Door Sill Door Sill LATERAL LEVELING SR22_FM06_1440A Figure 6-2 P/N 13999-004 Info Manual...

  • Page 164: Loading Instructions

    Section 6 Cirrus Design Weight and Balance Data 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 165: Weight And Balance Loading Form

    Cirrus Design Section 6 SR20 Weight and Balance Data Weight and Balance Loading Form • Note • For Center of Gravity Envelope, refer to Section 2, Limitations. The Takeoff Condition Weight must not exceed 3050 lb. The Takeoff Condition Moment must be within the Minimum Moment to Maximum Moment range at the Takeoff Condition Weight.

  • Page 166: Loading Data

    Section 6 Cirrus Design Weight and Balance Data SR20 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 Aft Pass Loading Chart Baggage 20.0 40.0...

  • Page 167: Moment Limits

    Cirrus Design Section 6 SR20 Weight and Balance Data Moment Limits Use the following chart or table to determine if the weight and moment from the completed Weight and Balance Loading Form (Figure 6-3) are within limits. 3200 3000 2800...

  • Page 168: Weight & Balance Record

    Section 6 Cirrus Design Weight and Balance Data 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 Weight Change Running Basic Item No.

  • Page 169: Equipment List

    Cirrus Design Section 6 SR20 Weight and Balance Data Equipment List This list will be determined after the final equipment has been installed in the aircraft. P/N 13999-004 Info Manual 6-13 September 2011...
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  • Page 171 Cirrus Design Section 7 SR20 Airplane and Systems Description Section 7 Airplane and Systems Description Table of Contents Introduction ..................5 Airframe ..................... 6 Fuselage ..................6 Wings....................6 Empennage ..................7 Flight Controls ..................8 Elevator System................8 Aileron System................10 Rudder System ................
  • Page 172 Section 7 Cirrus Design Airplane and Systems Description SR20 Ignition and Starter System............36 Air Induction System ..............36 Engine Exhaust................37 Engine Fuel Injection ..............37 Engine Cooling................37 Propeller ................... 38 Fuel System ..................39 Fuel Selector Valve............... 40 Fuel Pump Operation..............
  • Page 173 Cirrus Design Section 7 SR20 Airplane and Systems Description Convenience Outlet ..............85 Cirrus Airplane Parachute System ........... 86 System Description ............... 86 Activation Handle ................87 Deployment Characteristics ............89 P/N 13999-004 Info Manual September 2011...
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  • Page 175: Introduction

    Cirrus Design Section 7 SR20 Airplane and Systems 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 may not be described in this section.

  • Page 176: Airframe

    Section 7 Cirrus Design Airplane and Systems Description SR20 Airframe Fuselage The airplane’s 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 177: Empennage

    Cirrus Design Section 7 SR20 Airplane and Systems 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.

  • Page 178: Flight Controls

    Section 7 Cirrus Design Airplane and Systems Description SR20 Flight Controls The airplane 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.
  • Page 179 Cirrus Design Section 7 SR20 Airplane and Systems Description SR20_FM07_1461 Figure 7-1 Elevator System P/N 13999-004 Info Manual September 2011...

  • Page 180: Aileron System

    Section 7 Cirrus Design Airplane and Systems 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 181 Cirrus Design Section 7 SR20 Airplane and Systems Description SR20_FM07_1462 Figure 7-2 Aileron System P/N 13999-004 Info Manual 7-11 September 2011...

  • Page 182: Rudder System

    Section 7 Cirrus Design Airplane and Systems Description SR20 Rudder System The rudder provides airplane directional (yaw) control. The rudder is of conventional design with skin, spar and ribs manufactured of aluminum. The rudder is attached to the aft vertical stabilizer shear web at three hinge points and to the fuselage tailcone at the rudder control bell crank.
  • Page 183 Cirrus Design Section 7 SR20 Airplane and Systems Description SR20_FM07_1463 Figure 7-3 Rudder System P/N 13999-004 Info Manual 7-13 September 2011...

  • Page 184: Instrument Panel

    Section 7 Cirrus Design Airplane and Systems Description SR20 Instrument Panel The instrument panel is of all metal construction and is installed in sections so equipment can be easily removed for maintenance. The surrounding glareshield is made of composite material and projects over the instrument panel to reduce reflections on the windshield from lighted equipment and to shield the panel equipment from glare.
  • Page 185 Cirrus Design Section 7 SR20 Airplane and Systems Description Legend 1. Cirrus Airframe Parachute System 13. Left Side Console (CAPS) Activation T-Handle Cover · Circuit Breaker Panel 2. Magnetic Compass · Alternate Engine Air 3. Multifunction Display · ELT Remote Switch 4.

  • Page 186: Flight Instruments

    Section 7 Cirrus Design Airplane and Systems Description SR20 Flight Instruments Flight instruments and annunciations are displayed on the Primary Flight Display (PFD) located directed in front of the pilot. The PFD presents the primary flight instruments arranged in the conventional basic “T”...
  • Page 187 Cirrus Design Section 7 SR20 Airplane and Systems Description 125° LEGEND 1. True Airspeed TERM 2. Airspeed Indicator 3. Horizontal Situation Indicator (HSI) 4. Attitude Indicator 5. Slip/Skid Indicator 1.01NM 6. Vertical Deviation Indicator (VDI) 7. Selected Altitude Bug 8. Current Altitude 9.

  • Page 188: Attitude Indicator

    Section 7 Cirrus Design Airplane and Systems Description SR20 Attitude Indicator The primary attitude indicator is show on the upper center of the PFD and displays pitch, roll, and slip/skid information provided by the Attitude and Heading Reference System (AHRS).

  • Page 189: Airspeed Indicator

    Cirrus Design Section 7 SR20 Airplane and Systems Description Airspeed Indicator Primary airspeed data is provided by the Air Data Computer and is shown as a vertical tape along the upper left side of the PFD. The airspeed scale is graduated with major tick marks at intervals of 10 knots and minor tick marks at intervals of 5 knots.

  • Page 190: Altimeter

    Section 7 Cirrus Design Airplane and Systems Description SR20 Altimeter Primary altitude data is provided by the Air Data Computer and is shown as a vertical tape along the upper right side of the PFD. The altimeter scale is graduated with major tick marks at intervals of 100 feet and minor tick marks at intervals of 20 feet.

  • Page 191: Horizontal Situation Indicator

    Cirrus Design Section 7 SR20 Airplane and Systems Description Horizontal Situation Indicator The horizontal situation indicator is displayed along the lower center of the PFD. Heading data is provided by the Attitude and Heading Reference System (AHRS) and the onboard magnetometers. The HSI displays a rotating compass card in a heading-up orientation.

  • Page 192: Magnetic Compass

    Section 7 Cirrus Design Airplane and Systems Description SR20 Vertical speed must exceed 100 feet/min before digits will appear in the VSI pointer. If the rate of ascent/descent exceeds 2000 fpm, the pointer appears at the corresponding edge of the tape and the rate appears inside the pointer.
  • Page 193 Cirrus Design Section 7 SR20 Airplane and Systems Description SR20_FM07_1460 Figure 7-6 Wing Flaps P/N 13999-004 Info Manual 7-23 September 2011...

  • Page 194: Landing Gear

    Section 7 Cirrus Design Airplane and Systems 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 195 Cirrus Design Section 7 SR20 Airplane and Systems Description wheel, temperature sensors, and associated hydraulic plumbing and wring. Braking pressure is initiated by depressing the top half of a rudder pedal (toe brake). The brakes are plumbed so that depressing either the pilot’s or copilot’s left or right toe brake will apply the respective...

  • Page 196: Baggage Compartment

    Section 7 Cirrus Design Airplane and Systems Description SR20 Baggage Compartment The baggage compartment door, located on the left side of the fuselage aft of the wing, allows entry to the baggage compartment. The baggage door is hinged on the forward edge and latched on the rear edge.

  • Page 197: Seats

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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.The front seats are adjustable fore and aft and the seat backs can be reclined for passenger comfort or folded forward for rear seat access.

  • Page 198: Seat Belt And Shoulder Harness

    Section 7 Cirrus Design Airplane and Systems Description SR20 Seat Belt and Shoulder Harness Integrated seat belt and shoulder harness assemblies with inertia reels are provided for the pilot and each passenger. The rear seat belts are attached to fittings on the floorboard and the forward seat belts are attached to the seat frame.

  • Page 199: Cabin Doors

    Cirrus Design Section 7 SR20 Airplane and Systems Description 4. Restraint harnesses should fit snug against the shoulder with the lap buckle centered and tightened around the hips. To release the restraints: 1. Grasp the top of the buckle opposite the link and pull outward. The link will slip free of buckle.

  • Page 200: Engine

    Section 7 Cirrus Design Airplane and Systems Description SR20 Engine The airplane 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).
  • Page 201 Cirrus Design Section 7 SR20 Airplane and Systems Description Mixture Control The mixture control lever, labeled RICH-MIXTURE-CUTOFF, on the console adjusts the proportion of fuel to air for combustion. The Mixture Control Lever is mechanically linked to the mixture control valve in the engine-driven fuel pump.

  • Page 202: Engine Indicating

    Section 7 Cirrus Design Airplane and Systems Description SR20 Engine Indicating Engine information is displayed as analog-style gages, bar graphs, and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), all essential engine information is displayed along the LH edge of the display.
  • Page 203 Cirrus Design Section 7 SR20 Airplane and Systems Description Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Engine Instruments LEGEND 1. Percent Power 2. CHT 3. Tachometer 4. EGT 5. Manifold Pressure 6. Oil Temperature and Pressure 7. Alternate Air Control 8.
  • Page 204 Section 7 Cirrus Design Airplane and Systems Description SR20 Tachometer Engine speed (RPM) is shown in the upper mid-left corner of the ENGINE page as both a simulated tachometer and as a digital value. The tachometer pointer sweeps a scale range from 0 to 3000 RPM in 100 RPM increments.
  • Page 205 Cirrus Design Section 7 SR20 Airplane and Systems Description Oil Temperature Oil temperature is shown in the upper right corner of the ENGINE page, opposite the oil pressure scale, as both a simulated temperature gage and as a digital value. The gage pointer sweeps a scale range from 75°F to 250°F in 50°F increments.

  • Page 206: Engine Lubrication System

    Section 7 Cirrus Design Airplane and Systems Description SR20 Engine Lubrication System The engine is provided with a wet-sump, high-pressure oil system for engine lubrication and cooling. Oil for engine lubrication is drawn from an eight-quart capacity sump through an oil suction strainer screen and directed to the engine-mounted oil cooler.

  • Page 207: Engine Exhaust

    Cirrus Design Section 7 SR20 Airplane and Systems Description finally through the cylinder intake ports into the combustion chambers. Should the dry induction filter become clogged, a pilot controlled alternate induction air door can be opened, allowing engine operation to continue. For additional information on the Alternate Air Control, refer to Engine Controls - Alternate Air Control description in this section.

  • Page 208: Propeller

    Section 7 Cirrus Design Airplane and Systems 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.

  • Page 209: Fuel System

    Cirrus Design Section 7 SR20 Airplane and Systems Description Fuel System An 56-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 29.3-gallon capacity (28 gallon usable) vented integral fuel tank and a fuel collector/sump in each wing, a three position selector valve, an electric fuel pump, and an engine-driven fuel pump.

  • Page 210: Fuel Selector Valve

    Section 7 Cirrus Design Airplane and Systems Description SR20 contamination and grade. The fuel must be sampled prior to each flight. A sampler cup is provided to drain a small amount of fuel from the wing tank drains, the collector tank drains, and the gascolator drain.
  • Page 211 Cirrus Design Section 7 SR20 Airplane and Systems Description ANNUNCIATOR FUEL FUEL QUANTITY VENT VENT FILLER FILLER INDICATOR L. WING TANK R. WING TANK L. WING R. WING COLLECTOR COLLECTOR CHECK CHECK VALVE VALVE SELECTOR VALVE FLAPPER FLAPPER VALVE VALVE...

  • Page 212: Fuel Indicating

    Section 7 Cirrus Design Airplane and Systems Description SR20 Fuel Indicating Fuel system information is displayed as analog-style gages and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), fuel flow is displayed along the LH edge of the display.
  • Page 213 Cirrus Design Section 7 SR20 Airplane and Systems Description Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) 3 4 5 6 Fuel System Indication LEGEND 1. Fuel Flow 2. Fuel Used (Totalizer) 3. Fuel Remaining (Totalizer) 4. Time Remaining (Totalizer) 5.
  • Page 214 Section 7 Cirrus Design Airplane and Systems Description SR20 Fuel Quantity Gage A dual reading 2¼” fuel quantity gage is installed on the console immediately forward of the fuel selector valve. The LEFT pointer indicates left tank fuel quantity and sweeps a scale marked from 0 to 28 U.S.
  • Page 215 Cirrus Design Section 7 SR20 Airplane and Systems Description Fuel Totalizer and Calculated Information Fuel totalizer calculations are located in the lower right section of the ENGINE page and are separate and independent of the fuel quantity gage and float sensor system. The fuel totalizer monitors fuel flow and calculates fuel-to-destination, fuel used, fuel remaining, time remaining, fuel range, and nautical miles per gallon.

  • Page 216: Electrical System

    Section 7 Cirrus Design Airplane and Systems Description SR20 Electrical System The airplane is equipped with a two-alternator, two-battery, 28-volt direct current (VDC) electrical system designed to reduce the risk of electrical system faults. The system provides uninterrupted power for avionics, flight instrumentation, lighting, and other electrically operated and controlled systems during normal operation.
  • Page 217 Cirrus Design Section 7 SR20 Airplane and Systems Description LANDING 100A ALT 1 LIGHT ALT 1 7.5A VOLT REG RELAY LANDING LIGHT SWITCH EXTERNAL ALT 1 POWER RELAY SWITCH EXTERNAL POWER 125A BAT 1 BAT 1 BAT 1 RELAY SWITCH...

  • Page 218: Power Distribution

    Section 7 Cirrus Design Airplane and Systems Description SR20 Power Distribution Power is supplied to the airplane circuits through three distribution buses contained in the MCU; Main Distribution Bus 1, Main Distribution Bus 2, and the Essential Distribution Bus. The three distribution buses power the associated buses on the circuit breaker panel.

  • Page 219: Electrical System Protection

    Cirrus Design Section 7 SR20 Airplane and Systems Description Main Distribution Bus 2 The output from ALT 2 is connected to the Main Distribution Bus 2 in the MCU through an 80-amp fuse. Main Distribution Bus 2 powers three circuit breaker buses through 30-amp fuses located in the MCU;...
  • Page 220 Section 7 Cirrus Design Airplane and Systems Description SR20 Main Distribution Bus 1 or Main Distribution Bus 2 in the MCU. In the case of both alternators failing, BAT 1 is connected directly to the Essential Distribution Bus in the MCU and will power ESS BUS 1 and ESS BUS 2.

  • Page 221: Electrical System Control

    Cirrus Design Section 7 SR20 Airplane and Systems Description Electrical System Control The rocker type electrical system MASTER switches are ‘on’ in the up position and ‘off’ in the down position. The switches, labeled BAT 2, BAT 1, ALT 1, ALT 2 are located in the bolster switch panel immediately below the instrument panel.

  • Page 222: Ground Service Receptacle

    Section 7 Cirrus Design Airplane and Systems Description SR20 AVIONICS Master Switch A rocker switch, labeled AVIONICS, controls electrical power from the circuit breaker panel (MAIN BUS 1) to the Avionics Bus. The switch is located next to the ALT and BAT Master switches. Typically, the switch is used to energize or de-energize all non-essential avionics on the AVIONICS bus simultaneously.

  • Page 223: Electrical Indicating

    Cirrus Design Section 7 SR20 Airplane and Systems Description Electrical Indicating Electrical system information is displayed as bar graphs and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), Battery 1 ampere output and Essential Bus voltage output are displayed along the LH edge of the display.
  • Page 224 Section 7 Cirrus Design Airplane and Systems Description SR20 Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Electrical System Indication 8 9 10 Electrical and Lighting Controls LEGEND 1. Essential & Main Bus Voltage 7. Avionics 8. Navigation 2. Alternator & Battery Current 9.

  • Page 225: Lighting Systems

    Cirrus Design Section 7 SR20 Airplane and Systems Description Lighting Systems Exterior Lighting The airplane is equipped with wing tip navigation lights with integral anti-collision strobe lights and recognition lights. The landing light is located in the lower cowl. Navigation Lights The airplane is equipped with standard wing tip navigation lights.

  • Page 226: Interior Lighting

    Section 7 Cirrus Design Airplane and Systems 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 instrumentation and avionics equipment lights are dimmable.
  • Page 227 Cirrus Design Section 7 SR20 Airplane and Systems Description The panel lights operate on 28 VDC supplied through the 5-amp CABIN LIGHTS circuit breaker on MAIN BUS 1. Reading Lights Individual eyeball-type reading lights are installed in the headliner above each passenger position. Each light is aimed by positioning the lens in the socket and is controlled by a push-button switch located next to the light.

  • Page 228: Environmental System

    Section 7 Cirrus Design Airplane and Systems Description SR20 Environmental System • Note • To facilitate faster cabin cooling, prior to engine start leave the cabin doors open for a short time to allow hot air to escape. Standard cabin heating and ventilation is accomplished by supplying conditioned air from the heat exchanger for heating and windshield defrost and fresh outside air for ventilation.
  • Page 229 Cirrus Design Section 7 SR20 Airplane and Systems Description RAM AIR RAM AIR HOT AIR VALVE MIXING CHAMBER HEAT EXCHANGER FRESH AIR VALVE AIR FLOW VALVE CONTROL PANEL SERVO MOTOR FLOOR AIRFLOW WINDSHIELD DIFFUSER PANEL AIRFLOW DISTRIBUTION MANIFOLD AIR GASPER...
  • Page 230 Section 7 Cirrus Design Airplane and Systems Description SR20 RAM AIR RAM AIR HOT AIR VALVE MIXING CHAMBER HEAT EXCHANGER COMPRESSOR FRESH AIR VALVE WINDSHIELD AIR FLOW VALVE DIFFUSER SERVO MOTOR FLOOR AIRFLOW CONTROL PANEL PANEL AIRFLOW DISTRIBUTION MANIFOLD GASPER...

  • Page 231: Distribution

    Cirrus Design Section 7 SR20 Airplane and Systems Description Distribution Ventilation and cooling is provided by ducting fresh air from a NACA inlet on the RH cowl to the mixing chamber located on the lower RH portion of the firewall. Depending on operating mode and temperature...

  • Page 232: Cooling

    Section 7 Cirrus Design Airplane and Systems Description SR20 Cooling Standard cabin cooling is provided by ram air admitted through the NACA inlet on the RH cowl to the fresh air valve, mounted to the forward side of the firewall. When the fresh air valve is open, the air flows into the cabin mixing chamber.

  • Page 233: Vent Selection

    Cirrus Design Section 7 SR20 Airplane and Systems Description Vent Selection Air from the distribution manifold is proportioned and directed to passengers and/or the windshield by pressing the cabin vent selector buttons which electrically actuate butterfly valves at the entrances to the windshield diffuser and the cabin floor ducting.
  • Page 234 Section 7 Cirrus Design Airplane and Systems Description SR20 Rotating the selector controls the volume of airflow allowed into the cabin distribution system through use of an electro-mechanical linkage to a butterfly (hot air) valve in the mixing chamber on the forward firewall.

  • Page 235: Stall Warning System

    Cirrus Design Section 7 SR20 Airplane and Systems 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.

  • Page 236: Pitot-Static System

    Section 7 Cirrus Design Airplane and Systems Description SR20 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 237 Cirrus Design Section 7 SR20 Airplane and Systems Description AIR DATA COMPUTER PFD Air Data AIRSPEED INDICATOR ALTIMETER ALTERNATE PITOT-STATIC STATIC WATER TRAPS AIR SOURCE PITOT MAST STATIC HEATER BUTTONS Annunciation PITOT HEAT CURRENT SENSOR LOGIC PITOT 7.5A HEAT PITOT HEAT SW...

  • Page 238: Avionics

    Section 7 Cirrus Design Airplane and Systems Description SR20 Avionics Perspective Integrated Avionics System The Perspective Integrated Avionics System provides advanced cockpit functionality and improved situational awareness through the use of fully integrated flight, engine, communication, navigation and monitoring equipment. The system consists of the following components: •...
  • Page 239 Cirrus Design Section 7 SR20 Airplane and Systems Description XM RADIO RECEIVER (optional) SATELLITE DATA LINK RECEIVER (optional) FMS KEYBOARD MAG 2 MAG 1 AHRS 1 AUTOPILOT MODE CONTROLLER (optional) AHRS 2 (optional) AIR DATA COMPUTER AIR DATA COMPUTER 2...
  • Page 240 Section 7 Cirrus Design Airplane and Systems Description SR20 GDU Primary Flight Display The Primary Flight Display, located directly in front of the pilot, is intended to be the primary display of flight parameter information (attitude, airspeed, heading, and altitude) during normal operations.
  • Page 241 Cirrus Design Section 7 SR20 Airplane and Systems Description BUS 3 and the 5-amp MFD 2 circuit breaker on MAIN BUS 1. Either circuit is capable of powering the MFD. System start-up is automatic once power is applied. Power-on default brightness is determined by ambient lighting and is user adjustable.
  • Page 242 Section 7 Cirrus Design Airplane and Systems Description SR20 3 4 5 6 7 8 9 13 14 15 19 20 21 Legend 1. Soft Keys 11. NAV Transceiver Selection & Tune 2. PFD 12. MFD 3. PFD Range/Pan Joystick 13.
  • Page 243 Cirrus Design Section 7 SR20 Airplane and Systems Description 22 23 25 26 27 28 29 30 31 GARMIN IDENT FMS/XPDR RANGE MENU XPDR COM/NAV PROC DFLT MAP PUSH SYNC PUSH PUSH EMERG CRSR/1-2 PUSH CTR ALT SEL BKSP PUSH SYNC...
  • Page 244 Section 7 Cirrus Design Airplane and Systems Description SR20 GIA 63W Integrated Avionics Units The Integrated Avionics Units, located behind the MFD and instrument panel, function as the main communication hub, linking all Integrated Avionics System components with the PFD. Each Integrated Avionics...
  • Page 245 Cirrus Design Section 7 SR20 Airplane and Systems Description GMA 347 Audio Panel with Integrated Marker Beacon Receiver The Audio Panel, installed on the center console below the Flight Management System Keyboard, integrates NAV/COM digital audio, intercom and marker beacon controls. The VHF communications...

  • Page 246: Optional Avionics

    Section 7 Cirrus Design Airplane and Systems Description SR20 Optional Avionics GFC 700 3-Axis Autopilot and GMC 705 Autopilot Controller Refer to Section 9, Supplements for GFC 700 3-Axis Autopilot operating information. GTX 33 Mode S Transponder The GTX 33 Mode S solid-state transponder communicates with the primary Integrated Avionics Unit and provides Modes A, C, and S interrogation/reply capabilities.
  • Page 247 Cirrus Design Section 7 SR20 Airplane and Systems Description Traffic Advisory System The Traffic Advisory System (TAS) advises the pilot of transponder- equipped airplane that may pose a collision threat. TAS information is displayed on the MFD and indicates the relative range, bearing, and altitude of intruder airplane.
  • Page 248 Section 7 Cirrus Design Airplane and Systems Description SR20 the KR 87 receiver which communicates with the Integrated Avionics System via the secondary Integrated Avionics Unit. The HSI Bearing Needle may be configured to indicate ADF tracking and homing information. 28 VDC for ADF System operation is supplied through the 3-amp DME/ADF circuit breaker on AVIONICS BUS.
  • Page 249 Cirrus Design Section 7 SR20 Airplane and Systems Description • Perspective depiction of obstacles, • Flight path marker, • Terrain warning system, • Field of view depiction on the MFD Navigation Page. Refer to the Perspective Integrated Avionics System Pilot’s Guide for a...
  • Page 250 Section 7 Cirrus Design Airplane and Systems Description SR20 LEGEND 1. AHRS 1 2. Integrated Avionics Unit 1 3. AHRS 2 4. Avionics Cooling Fan 5. Integrated Avionics Unit 2 6. Engine Airframe Unit 7. Air Data Computer 2 (opt) 8.

  • Page 251: Avionics Support Equipment

    Cirrus Design Section 7 SR20 Airplane and Systems Description Avionics Support Equipment Antennas Two rod-type COM antennas are mounted to the airplane’s exterior; COM 1 is mounted directly above the passenger compartment, COM 2 is mounted directly below the baggage compartment. These antennas are connected to the two VHF communication transceivers contained in the Integrated Avionics Units.
  • Page 252 Section 7 Cirrus Design Airplane and Systems Description SR20 Headset and Microphone Installation The airplane is equipped with provisions for four noise-canceling headsets with integrated microphones. forward microphone-headsets use remote Push-To-Talk (PTT) switches located on the top of the associated control yoke grip. The rear headsets do not have COM transmit capabilities and do not require PTT switches.

  • Page 253: Cabin Features

    Cirrus Design Section 7 SR20 Airplane and Systems Description Cabin Features 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, slightly to the right of the airplane centerline.
  • Page 254 Section 7 Cirrus Design Airplane and Systems Description SR20 b. Disconnect fixed antenna lead from front of unit. c. Disconnect lead from remote switch and indicator unit. d. Loosen attach straps and remove transmitter unit and portable antenna. e. Attach portable antenna to antenna jack on front of unit.

  • Page 255: Hour Meters

    Cirrus Design Section 7 SR20 Airplane and Systems Description Hour Meters The airplane is equipped with two hour meters located inside the armrest storage compartment between the pilot and copilot seats. The #1 hour meter, labeled HOBBS begins recording when the BAT 1 switch is ON and either the ALT 1 or ALT 2 switch is ON.

  • Page 256: Cirrus Airplane Parachute System

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

  • Page 257: Activation Handle

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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. The aft harness strap is stowed in the parachute canister and attached to the structure at the aft baggage compartment bulkhead.
  • Page 258 Section 7 Cirrus Design Airplane and Systems Description SR20 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. However, there may be some circumstances where an operator may wish to safety the CAPS system;...

  • Page 259: Deployment Characteristics

    Cirrus Design Section 7 SR20 Airplane and Systems Description Deployment Characteristics When the rocket launches, the parachute assembly is extracted outward due to rocket thrust and rearward due to relative wind. In approximately two seconds the parachute will begin to inflate.
  • Page 260 Section 7 Cirrus Design Airplane and Systems Description SR20 Intentionally Left Blank 7-90 P/N 13999-004 Info Manual September 2011...
  • Page 261 Airworthiness Directives..............6 Airplane Inspection Periods ............... 6 Annual Inspection ................6 100-Hour Inspection ............... 7 Cirrus Design Progressive Inspection Program ......7 Pilot Performed Preventative Maintenance ........8 Ground Handling ................10 Application of External Power ............10 Towing ..................11 Taxiing ..................
  • Page 262 Section 8 Cirrus Design Handling, Servicing, & Maintenance SR20 Intentionally Left Blank P/N 13999-004 Info Manual September 2011...

  • Page 263: Introduction

    Operator’s Publications The FAA Approved Airplane Flight Manual and Pilot’s Operating Handbook (POH) is provided at delivery. Additional or replacement copies may be obtained from Cirrus Design by contacting the Customer Service Department. Service Publications The following service publications are available for purchase from Cirrus Design: •...

  • Page 264: Ordering Publications

    Service Bulletin. Give careful attention to the Service Advisory Notice information. Ordering Publications Aircraft publications 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...

  • Page 265: Airplane Records And Certificates

    Cirrus Design Section 8 SR20 Handling, Servicing, and 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 266: Annual Inspection

    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 267: 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 268: Pilot Performed Preventative Maintenance

    Section 8 Cirrus Design Handling, Servicing, and 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 269 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance • Replace any hose connection, except hydraulic connections, with replacement hoses. • Clean or replace fuel and oil strainers, as well as replace or clean filter elements. • Replace prefabricated fuel lines.

  • Page 270: Ground Handling

    Section 8 Cirrus Design Handling, Servicing, and 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 271: Towing

    Cirrus Design Section 8 SR20 Handling, Servicing, and 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 272: Taxiing

    Section 8 Cirrus Design Handling, Servicing, and 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 273: Parking

    Cirrus Design Section 8 SR20 Handling, Servicing, and 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 274: Tiedown

    Section 8 Cirrus Design Handling, Servicing, and 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 275 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance Raise Airplane • Caution • Do not jack the aircraft outside or in open hangar with winds in excess of 10 mph. The empty CG is forward of the wing jacking points. To prevent...

  • Page 276: Servicing

    Section 8 Cirrus Design Handling, Servicing, and 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.
  • Page 277 Cirrus Design Section 8 SR20 Handling, Servicing, and 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 2016 thru 2030 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 278: Tire Inflation

    Section 8 Cirrus Design Handling, Servicing, and 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 279 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance sooner under unfavorable operating conditions. The following grades are recommended for the specified temperatures at sea level (SL): Ambient Air Temperature (SL) Single Viscosity Multi-Viscosity All Temperatures -— 20W-60 20W-50 15W-50 Below 40°F...
  • Page 280 Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 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...

  • Page 281: Fuel System Servicing

    Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance Fuel System Servicing Fuel Filtration Screen/Element Airplane Serials 2016 thru 2031; After the first 25 hours of operation, then every 100-hours or as conditions dictate, the fuel filter element in the gascolator must be replaced. At every oil change, Verify red pop- up tab on gascolator is not visible.

  • Page 282: Fuel Contamination And Sampling

    Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 To refuel airplane: 1. Place fire extinguisher near fuel tank being filled. 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.

  • Page 283: Draining Fuel System

    Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance If sampling reveals contamination, the gascolator and tank drains must be sampled again repeatedly until all contamination is removed. It is helpful to gently rock the wings and lower the tail slightly to move contaminates to the drain points for sampling.

  • Page 284: Battery Service

    Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Battery Service The aircraft is delivered with a maintenance free, rechargeable, sealed, lead acid primary battery. Battery #1 is mounted to the forward right side of the firewall and access is gained by removing the upper cowl.

  • Page 285: Cleaning And Care

    Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance 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 286 Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Cleaning Product Cleaning Application Supplier Pure Carnauba Wax Fuselage Exterior Any Source Mothers California Gold Fuselage Exterior Wal-Mart Stores Pure Carnauba Wax RejeX Fuselage Exterior Corrosion Technologies WX/Block System Fuselage Exterior...
  • Page 287 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance 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 288 Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Do not use abrasive cleansers or cleaning pads on the germanium window. Abrasive cleaning can damage the sensor window coating. Do not use any cleansers containing ammonia. Ammonia will remove the sensor window coating.

  • Page 289: Cleaning Interior Surfaces

    Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance 3. Allow the solvent to remain on the gear from five to ten minutes. Then rinse the gear with additional solvent and allow to dry. 4. Remove the cover from the wheel and remove the catch pan.
  • Page 290 Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Cleaning Product Cleaning Application Supplier Prist Interior Windscreen and Prist Aerospace Windows Optimax Display Screens PhotoDon Mild Dishwasher Soap Cabin Interior Any Source (abrasive free) Leather Care Kit Leather Upholstery Cirrus Design...
  • Page 291 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance 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 292 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 293 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 294 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank P/N 13999-004 Info Manual September 2011...
  • Page 295 SR20 Airplanes Registered in Canada 10-10-01 ___ 11934-S25 R1 Winterization Kit 12-07-04 ___ 11934-S29 SR20 Airplanes Registered in the European Union 05-27-04 ___ 11934-S36 R1 Artex ME406 406 MHz ELT System 12-18-08 ___ 11934-S39 S-Tec Fifty Five X Autopilot w/ Optional Flight Director...
  • Page 296 This Log of Supplements shows all Cirrus Design Supplements available for the aircraft at the corresponding 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 297 Supplement Artex ME406 406 MHz ELT System When Artex ME406 406 MHz ELT System is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
  • Page 298 Section 9 Cirrus Design Supplements SR20 Section 1 - General The 406 MHz emergency locator transmitter (ELT) is a radio-frequency transmitter that generates a signal to assist in search and rescue for missing aircraft. The ELT automatically transmits the standard sweep tone on 121.5 MHz if rapid deceleration is detected.
  • Page 299 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations No Change. Section 3 - Emergency Procedures Forced Landing Before performing a forced landing activate the ELT transmitter manually by turning the ELT remote switch to the 'ON'-position. Immediately after a forced landing, perform the following procedure: •...
  • Page 300 Section 9 Cirrus Design Supplements SR20 Portable Use of ELT The ELT transmitter can be removed from the airplane and used as a personal locating device if it is necessary to leave the airplane after an accident. Access the unit as described below and set the ELT transmitter control switch to the 'ON'-position.
  • Page 301 Cirrus Design Section 9 SR20 Supplements Section 7 - Systems Description This airplane is equipped with a self-contained Artex ME406 406 MHz ELT System. The transmitter unit is automatically activated upon sensing a change of velocity along its longitudinal axis exceeding 4 to 5 feet per second.
  • Page 302 Section 9 Cirrus Design Supplements SR20 Section 8 - Handling, Servicing & Maintenance ELT and RCPI batteries must be inspected in accordance with the Airplane Maintenances Manual, 5-20 - Scheduled Maintenance Checks. The ELT and RCPI batteries must be replaced upon reaching the date...
  • Page 303 Cirrus Design Section 9 SR20 Supplements system or provide the same level of confidence as does an AM radio. 1. Tune aircraft receiver to 121.5 MHz. 2. Turn the ELT aircraft panel switch "ON" for about 1 second, then back to the "ARM" position. The receiver should transmit about 3 audio sweeps.
  • Page 304 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 8 of 8 P/N 11934-S36 Revision 01: 12-18-08...
  • Page 305 Cirrus Design Section 9 SR20 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the GFC 700 Automatic Flight Control System (Aircraft Serials w/ Perspective Avionics Only) Including optionally installed Electronic Stability and Protection (ESP), Underspeed Protection (USP), and Hypoxia Detection and Automatic Descent functions.
  • Page 306 Control System (AFCS) which is fully integrated within the Cirrus Perspective Integrated Avionics System architecture. Refer to Section 7 - System Description and the Cirrus Perspective Pilot’s Guide for additional description of the AFCS and operating procedures. Determining status of Autopilot Underspeed Protection (USP)
  • Page 307 Cirrus Design Section 9 SR20 Supplements command limits and an altitude loss of 1000 feet or more can be expected while attitude is established in the selected mode. Axis Autopilot Engagement Limit Pitch ± 30° Roll ± 75° 6. The Autopilot and Flight Director will not command pitch or roll beyond the Command Limits.
  • Page 308 Section 9 Cirrus Design Supplements SR20 Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure abnormal procedure in the basic POH. Do not reengage the Autopilot until the malfunction has been identified and corrected. The Autopilot may be disconnected by: 1.
  • Page 309 Cirrus Design Section 9 SR20 Supplements Section 3A - Abnormal Procedures Altitude Miscompare ALT MISCOMP Caution ALT MISCOMP For dual ADC installations, altitude difference is greater than 200 feet between ADC1 and ADC2. 1. Altitude ..... CROSS-CHECK ADC1 against Standby Altimeter 2.
  • Page 310 Section 9 Cirrus Design Supplements SR20 Heading Miscompare HDG MISCOMP Caution HDG MISCOMP For dual AHRS installations, heading difference is greater than 6° between AHRS 1 and AHRS 2. 1. Heading..CROSS-CHECK AHRS1 against Magnetic Compass 2. AHRS2 ................SELECT a.
  • Page 311 Cirrus Design Section 9 SR20 Supplements advisory since backup source is not available for comparison. Flight Director, Autopilot and ESP will become available when unreliable AHRS CB is pulled. Roll Miscompare ROLL MISCOMP Caution ROLL MISCOMP For dual AHRS installations, roll (bank) difference is greater than 6°...
  • Page 312 Section 9 Cirrus Design Supplements SR20 Autopilot and PFD Using Different AHRSs AP/PFD AHRS Caution AP/PFD AHRS The Autopilot and PFD are using different Attitude and Heading Reference Systems. 1. Continue flight without Autopilot. Monitor Standby Instruments. Pilot may manually select other AHRS if installed.
  • Page 313 Cirrus Design Section 9 SR20 Supplements Course Selection Track Error COURSE SEL Advisory COURSE SEL The pilot has selected an Autopilot mode (ROL) and engaged a NAV mode (VLOC or GPS) and the current aircraft track will not intercept the selected course. Typically done unintentionally.
  • Page 314 Section 9 Cirrus Design Supplements SR20 AUTO DESCENT Warning AUTO DESCENT No pilot response to the HYPOXIA ALERT annunciation detected after one minute. Warning remains until pilot responds. Automatic descent begins after one minute of unanswered Warning. Once it begins automatic descent will commence to 14,000 for 4 minutes, then to 12,500' thereafter.
  • Page 315 Cirrus Design Section 9 SR20 Supplements Underspeed Protection Recovery (Optional) UNDERSPEED PROTECT ACTIVE Warning UNDERSPEED PROTECT ACTIVE Autopilot engaged and airspeed has fallen below minimum threshold. Recovery may be initiated in one of three ways: 1. Power Lever ..............INCREASE as required to correct underspeed condition.
  • Page 316 Section 4 - Normal Procedures • Note • Normal operating procedures for the GFC 700 Automatic Flight Control System are described in the Cirrus Perspective Pilot’s Guide. PreFlight Inspection 1. A self test is performed upon power application to the AFCS. A...
  • Page 317 Cirrus Design Section 9 SR20 Supplements Temporary Interrupt of ESP (Optional) Although ESP is only provided when AFCS Autopilot is disengaged, the AFCS and its servos are the source of ESP guidance. When the AP Disconnect button is pressed and held, the servos will provide no ESP control force feedback.
  • Page 318 Section 9 Cirrus Design Supplements SR20 Section 7 - System Description This airplane is equipped with a GFC 700 - a two axis, fully digital, dual channel, fail passive Automatic Flight Control System (AFCS). The system consists of the GFC 705 AFCS Mode Controller, Flight...
  • Page 319 Cirrus Design Section 9 SR20 Supplements GFC 705 MODE CONTROLLER INTEGRATED GO-AROUND INTEGRATED AVIONICS UNIT 2 SWITCH AVIONICS UNIT 1 A/P DISC PITCH TRIM ADAPTER 4-WAY TRIM PITCH TRIM CARTRIDGE ROLL SERVO PITCH SERVO SR20_FM09_2918 Figure - 1 GFC 700 Automatic Flight Control System Schematic...
  • Page 320 Section 9 Cirrus Design Supplements SR20 GFC 705 AFCS Mode Controller The GFC 705 AFCS Mode Controller, located in the upper section of the center console provides primary control of Autopilot modes. A pitch wheel is included for adjustment of pitch mode reference. 28 VDC for GFC 705 AFCS Mode Controller operation is supplied through 5-amp KEYPADS / AP CTRL circuit breaker on MAIN BUS 1.
  • Page 321 Cirrus Design Section 9 SR20 Supplements UP/DN - Pitch Wheel The Pitch UP/DN Wheel on the controller is used to change the Flight Director pitch mode reference value. Each click of the wheel results in a step increase or decrease in the Flight Director pitch mode by the amount shown in the table below.
  • Page 322 Section 9 Cirrus Design Supplements SR20 Flight Management System Keyboard The Flight Management System Keyboard, found in the center console below the AFCS mode controller, is the primary means for data entry for the MFD and is used to control NAV/COM Radios, transponder, and flight management system entry.
  • Page 323 Cirrus Design Section 9 SR20 Supplements GARMIN IDENT FMS/XPDR RANGE MENU XPDR COM/NAV PROC DFLT MAP PUSH SYNC PUSH PUSH EMERG CRSR/1-2 PUSH CTR ALT SEL BKSP PUSH SYNC Flight Management System Keyboard GFC 705 Mode Controller Legend 1. Heading Selection 8.
  • Page 324 Section 9 Cirrus Design Supplements SR20 Roll and Pitch Servo The Roll Servo, located below the passenger seat, and the Pitch Servo, located below the baggage compartment, position the aircraft flight controls in response to commands generated by the Integrated Avionics Units Autopilot calculations.
  • Page 325 Cirrus Design Section 9 SR20 Supplements Take Off / Go Around Button The remote TO/GA switch, located on the left side of the power lever, selects the Takeoff or Go Around mode on the Flight Director. When the aircraft is on the ground, pressing the TO/GA switch engages the Flight Director command bars in Takeoff (TO) mode.
  • Page 326 Section 9 Cirrus Design Supplements SR20 Electronic Stability and Protection (Optional) When installed, Electronic Stability and Protection (ESP) assists the pilot in maintaining the airplane in a safe flight condition. Through the use of the GFC 700 AFCS sensors, processors, and servos, ESP provides control force feedback, i.e.
  • Page 327 Cirrus Design Section 9 SR20 Supplements Roll Protection Limits: Always Protected Only Protected after cross- ing turn-on threshold 0° 15° 30° 45° 60° 75° 90° Bank Angle Engagement Limit: ..............45° Maximum Stick Force attained at..........50° Disengagement Threshold (Zero Stick Force) ......30°...
  • Page 328 Section 9 Cirrus Design Supplements SR20 Low Pitch Protection Limits Always Protected Only Protected after cross- ing turn-on threshold -0° -5° -10° -15° -20° -25° Nose Down Pitch Angle Engagement Limit: ..............-15.5° Maximum Stick Force attained at: ......... -20.5°...
  • Page 329 Cirrus Design Section 9 SR20 Supplements High Airspeed Protection Limits - Below 17,500 ft PA Always Protected Only Protected after cross- ing turn-on threshold Indicated Airspeed (KIAS) Engagement Limit: ............200 KIAS Maximum Stick Force attained at:........205 KIAS Disengagement Threshold (Zero Stick Force) ....190 KIAS...
  • Page 330 Section 9 Cirrus Design Supplements SR20 Underspeed Protection Mode (Optional) When installed, to discourage aircraft operation below minimum established airspeeds the AFCS will automatically enter Underspeed Protection Mode when the Autopilot is engaged and airspeed falls below the minimum threshold. If aircraft stall warning system is not...
  • Page 331 Cirrus Design Section 9 SR20 Supplements AFCS recognizes it via acceleration and the AP/FD will transition to a nose-up pitch to aggressively return to original altitude or glidepath/slope. 2. Disengage Autopilot via AP DISC and manually fly. 3. Change Autopilot modes to one in which the AFCS can maintain (such as VS with a negative rate).
  • Page 332 Section 9 Cirrus Design Supplements SR20 Hypoxia Detection and Automatic Descent (Optional) When installed, the AFCS Hypoxia Detection and Automatic Descent function monitors pilot inputs to the Integrated Avionics System to identify if a pilot has become incapacitated due to hypoxia, and upon determination, automatically descends to a lower altitude where pilot recovery is more probable.
  • Page 333 SR20 Supplements Annunciation System • Note • Refer to the Cirrus Perspective Pilot’s Guide for a detailed description of the annunciator system and all warnings, cautions and advisories. Crew Alerting System AFCS alerts are displayed in the Crew Alerting System (CAS) window located to the right of the altimeter and VSI.
  • Page 334 Section 9 Cirrus Design Supplements SR20 Section 8 – Handling, Service, & Maintenance No Change. Section 10 – Safety Information No Change. 30 of 30 P/N 11934-S41 Revision 02: 12-14-10...
  • Page 335 When the Garmin Terrain Awareness/Warning System is installed on the aircraft, 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 336 Section 2 - Limitations 1. The Cirrus Perspective by Garmin Integrated Avionics System Pilot’s Guide for the SR20 and SR22, P/N 190-00820-02 Rev A or later must be immediately available to the pilot during flight. The software status stated in the pilot's guide must match that displayed on the equipment.
  • Page 337 Cirrus Design Section 9 SR20 Supplements Section 3 - Emergency Procedures To prevent unwanted aural alerting during ditching or other off-airport landings, inhibit the Terrain Awareness System functions by selecting the INHIBIT Softkey on the TAWS Page. Response To TAWS Warnings...
  • Page 338 PFD. Refer to the Cirrus Perspective Integrated Flight Deck Pilot’s Guide for a additional information on the system and its operating modes. 4 of 6...
  • Page 339 Cirrus Design Section 9 SR20 Supplements System Constraints System test at startup: Aural tone lasting approximately one second indicates successful completion of internal system test. Red TAWS FAIL Warning TAWS FAIL Aural “TAWS SYSTEM FAILURE” Warning 1. TAWS power-up self-test has failed or TAWS has detected problems with database validity, hardware status, and/or GPS status.
  • Page 340 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 6 of 6 P/N 11934-S42 Original Issue: 12-18-08...
  • Page 341 Safety Information Section 10 Safety Information Table of Contents Introduction ..................3 Cirrus Airframe Parachute System (CAPS) ........4 Deployment Scenarios..............4 General Deployment Information ............ 6 Landing Considerations ..............7 Taxiing, Steering, and Braking Practices ......... 10 Operating Practices ..............10 Brake Maintenance ...............
  • Page 342 Section 10 Cirrus Design Safety Information SR20 Intentionally Left Blank 10-2 P/N 13999-004 Info Manual September 2011...

  • Page 343: Introduction

    Cirrus Design Section 10 SR20 Safety Information Introduction This aircraft is 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. As the pilot you must be thoroughly familiar with the contents of this...

  • Page 344: Cirrus Airframe Parachute System (Caps)

    Safety Information SR20 Cirrus Airframe Parachute System (CAPS) 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 345 Cirrus Design Section 10 SR20 Safety Information 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; or a spiral/ spin.

  • Page 346: General Deployment Information

    Section 10 Cirrus Design Safety Information SR20 General Deployment Information Deployment Speed The maximum speed at which deployment has been demonstrated is 133 KIAS. Deployment at higher speeds could subject the parachute and aircraft to excessive loads that could result in structural failure.

  • Page 347: Landing Considerations

    Cirrus Design Section 10 SR20 Safety Information Landing Considerations After a CAPS deployment, the airplane will descend at less than 1700 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 348 Section 10 Cirrus Design Safety Information SR20 • If a door is open prior to touchdown in a CAPS landing, the door will most likely break away from the airplane at impact. • If the door is open and the airplane contacts the ground in a rolled condition, an occupant could be thrown forward and strike their head on the exposed door pillar.
  • Page 349 Cirrus Design Section 10 SR20 Safety Information 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. If the pilot suspects a fire could result from impact, unlatching a door immediately prior to assuming the emergency landing body position should be considered to assure rapid egress.

  • Page 350: 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 351: Brake Maintenance

    Cirrus Design Section 10 SR20 Safety Information • Use only as much power (throttle) as is necessary to achieve forward movement. Keep in mind, any additional power added with the throttle will be absorbed in the brakes to maintain constant speed.
  • Page 352 Section 10 Cirrus Design Safety Information SR20 Intentionally Left Blank 10-12 P/N 13999-004 Info Manual September 2011...

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