Cirrus SR20 Pilot Operating Handbook
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Cirrus SR20 Pilot Operating Handbook

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Download this manual See also: Maintenance Manual, Information Manual
PILOT'S OPERATING HANDBOOK
AND FAA APPROVED
AIRPLANE FLIGHT MANUAL
for the
CIRRUS SR20
Airplanes Registered in Brazil and Operating Under
the Agência Nacional de Aviação Civil Requirements
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
FAA Approved in Normal Category based on FAR Part 23. This document must be
carried in the airplane at all times and be kept within the reach of the pilot during all flight
operations.
THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO
THE PILOT BY FAR PART 23 AND ADDITIONAL INFORMATION PROVIDED BY
CIRRUS DESIGN AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT
MANUAL.
This Pilot's Operating Handbook/Airplane Flight Manual is approved by the FAA on
behalf of the Agência Nacional de Aviação Civil for Brazilian registered aircraft, in accor-
dance with the "Regulamentos Brasileiros de Homologação Aeronáutica" (RBHA) 21,
Section 21.29.
Model - Serial Num. SR20 _____________ Registration Num. _ __________________
This Aircraft shall be operated in accordance with the limitation and instructions herein established.
P/N 21399-004
Reissue A: March 05, 2013

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Alan
February 19, 2025

Max cross wind for a cirrus 20

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1 comments:
Mr. Anderson
February 19, 2025

The maximum demonstrated crosswind component for a Cirrus SR20 is 21 knots.

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Summary of Contents for Cirrus SR20

  • Page 1 Agência Nacional de Aviação Civil for Brazilian registered aircraft, in accor- dance with the “Regulamentos Brasileiros de Homologação Aeronáutica” (RBHA) 21, Section 21.29. Model - Serial Num. SR20 _____________ Registration Num. _ __________________ This Aircraft shall be operated in accordance with the limitation and instructions herein established. P/N 21399-004...
  • Page 2 Copyright © 2013 - All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811...
  • Page 3 Cirrus Design Pilot’s Operating Handbook SR20 List of Effective Pages List of Effective Pages Use this page to determine the current effective date for each page in the POH. Supplements are issued individually and are controlled by the Log of Supplements Page in Section 9.

  • Page 4: Table Of Contents

    Cirrus Design Pilot’s Operating Handbook SR20 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status Revision A1 5-28 Revision A1 7-41 Revision A1 Reissue A 5-29 Revision A1 7-42 Revision A1 Revision A1 5-30...

  • Page 5: Revision A1

    Cirrus Design Pilot’s Operating Handbook SR20 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 7-96 Revision A1 10-5 Reissue A 7-97 Revision A1 10-6 Revision A1 7-98 Revision A1 10-7 Revision A1 7-99...

  • Page 6: Reissue A

    Cirrus Design Pilot’s Operating Handbook SR20 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status Intentionally Left Blank P/N 21399-004 Reissue A...

  • Page 7: Revision A1

    SR20 Foreword Foreword This Pilot’s Operating Handbook (POH) has been prepared by Cirrus Design Corporation to familiarize operators with the aircraft. Read this POH carefully. It provides operational procedures that will assure the operator obtains the performance published in the manual, data designed to allow the most efficient use of the airplane, and basic information for maintaining the airplane in a “like new”...

  • Page 8: Revision A1

    Front Matter Cirrus Design Foreword SR20 The Pilot’s Operating Handbook This Pilot’s Operating Handbook has been prepared using GAMA Specification #1 for Pilot’s Operating Handbook, Revision 2, dated 18 October 1996 as the content model and format guide. However, some deviations from this specification were made for clarity.

  • Page 9: Reissue A

    Original issue pages will be identified by the words “Original Issue” at this location. In the event that the majority of pages in the POH are revised, Cirrus may determine that it is more effective to reissue the POH. Reissued pages will be identified by the word “Reissue”...

  • Page 10: Revision A1

    Design Supplements produced for this airplane. The “Log of Supplements” page can be utilized as a “Table of Contents” for Section 9. If the airplane is modified at a non Cirrus Design facility through an STC or other approval method, it is the owner’s responsibility to ensure that the proper supplement, if applicable, is installed in the POH and that the supplement is properly recorded on the “Log of...
  • Page 11 Cirrus Design Front Matter SR20 Foreword In the event a new POH is purchased, the owner must ensure that all information applicable to the airplane is transferred to the new POH and the aircraft records are current. Warnings, Cautions, and Notes...

  • Page 12: Reissue A

    Front Matter Cirrus Design Foreword SR20 Intentionally Left Blank Front Matter-6 P/N 21399-004 Reissue A...

  • Page 13: Reissue A

    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 14: Reissue A

    Section 1 Cirrus Design General SR20 Intentionally Left Blank P/N 21399-004 Reissue A...

  • Page 15: 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 16 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 17 Cirrus Design Section 1 SR20 General 49.3" 39.8" Fuselage Station 49.7" 38.5" 27.0" 16.0" 20.0" 32.0" 10.5" 33.4" 39.0" 20.0" 33.3" 5.0" 21.0" CABIN DOOR BAGGAGE DOOR OPENING OPENING SR20_FM01_1019A Location Length Width Height Volume Cabin 122” 49.3” 49.7 137 cu ft Baggage 36”...
  • Page 18 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 19: 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 20: 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 ..........

  • Page 21: 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 22: Meteorological Terminology

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

  • Page 23: 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 24: 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 specific engine power setting and/or flight configuration. • Unusable Fuel is the quantity of fuel that cannot be safely used in flight.

  • Page 25: Reissue A

    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 26: Reissue A

    Section 1 Cirrus Design General SR20 Intentionally Left Blank 1-14 P/N 21399-004 Reissue A...
  • Page 27 Environmental Conditions ..............17 Maximum Occupancy ..............17 Systems and Equipment Limits............19 Cirrus Perspective Integrated Avionics System ......19 L-3 Skywatch Traffic Advisory System (Optional)......22 L-3 Stormscope Weather Information System (Optional) ..... 22 Max Viz Enhanced Vision System (Optional) ....... 23 MD302 Standby Attitude Module (Optional) .........

  • Page 28: Revision A1

    Section 2 Cirrus Design Limitations SR20 Other Limitations ................25 Smoking ..................25 Placards ................... 26 P/N 21399-004 Revision A1...

  • Page 29: Section 2: Limitations

    Cirrus Design Section 2 SR20 Limitations Introduction The limitations included in this Section of the Pilot’s Operating Handbook (POH) approved 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 30: Airspeed Limitations

    Section 2 Cirrus Design Limitations SR20 Airspeed Limitations The indicated airspeeds in the following table are based on Section 5, Airspeed Calibration - Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.

  • Page 31: Airspeed Indicator Markings

    Cirrus Design Section 2 SR20 Limitations Airspeed Indicator Markings The airspeed indicator markings are based on Section 5, Airspeed Calibration - Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.

  • Page 32: 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 • Note • Due to the mechanical design of the propeller governor, it is normal for the engine to temporarily exceed 2700 RPM during some phases of flight.

  • Page 33: 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 34: 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 Instrument Yellow Green Arc/ Yellow Arc/ (Range & Units) Arc/Bar Arc/Bar...

  • Page 35: Fuel

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

  • Page 36: 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...

  • Page 37: 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, Inadvertent Spin Entry.

  • Page 38: 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 39: Reissue A

    Cirrus Design Section 2 SR20 Limitations Kinds of Operation Remarks, Notes, (Continued) System, Instrument, and/ and/or or Equipment Exceptions Low Volts Annunciator ALT 1 Annunciator ALT 2 Annunciator — — Circuit Breakers As required. Equipment & Furnishings Emergency Locator Trans-...
  • Page 40 Section 2 Cirrus Design Limitations SR20 Kinds of Operation Remarks, Notes, (Continued) 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 41: Reissue A

    Cirrus Design Section 2 SR20 Limitations Kinds of Operation Remarks, Notes, (Continued) 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 42: 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 43: 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...

  • Page 44: Reissue A

    Section 2 Cirrus Design Limitations SR20 three rear seat passengers cannot meet these requirements, occupancy is limited to four persons. SR20_FM02_3490 Figure 2-2 Rear Passenger Seat Arrangement Child Restraint System 1. Rear seat configuration for LATCH / ISOFIX compliant child seats is limited to two seats in the outboard positions.

  • Page 45: 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 46 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 47: Revision A1

    Cirrus Design Section 2 SR20 Limitations n. Serials w/ system software load 0764.21 or later: Barometric vertical navigation (Baro-VNAV) operations may be conducted if SBAS is unavailable or disabled. The Perspective Integrated Avionics System will provide automatic, temperature- compensated glidepath vertical guidance and has been...

  • Page 48: Skywatch Traffic Advisory System (Optional)

    Section 2 Cirrus Design Limitations SR20 11. The SYNTHETIC VISION SYSTEM (SVS) cannot be used for flight guidance, navigation, traffic avoidance, or terrain avoidance. Maneuvering the airplane in any phase of flight such as taxi, takeoff, approach, landing, or roll out shall not be predicated on SVS imagery.

  • Page 49: Max Viz Enhanced Vision System (Optional)

    Cirrus Design Section 2 SR20 Limitations User’s Guide, (p/n 009-11501-001) must be available to the pilot during flight. Max Viz Enhanced Vision System (Optional) 1. The Enhanced Vision System (EVS) cannot be used for flight guidance, navigation, traffic avoidance, or terrain avoidance.

  • Page 50: Paint

    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 51: Reissue A

    Cirrus Design Section 2 SR20 Limitations Other Limitations Smoking Smoking is prohibited in this airplane. P/N 21399-004 P/N 21399-004 2-25 2-25 Reissue A...

  • Page 52: Revision A1

    Section 2 Cirrus Design Limitations SR20 Placards Engine compartment, inside oil filler access: TIPO DE ÓLEO DO MOTOR ACIMA DE 4° C (40° F): SAE 50 OU 20W50 ABAIXO DE 4° C (40° F): SAE 30 OU 10W30, 15W50 OU 20W50 CONSULTE O AFM PARA ÓLEOS APROVADOS...

  • Page 53: Revision A1

    Cirrus Design Section 2 SR20 Limitations Upper fuselage, either side of CAPS rocket cover: ATENÇÃO! FOGUETE PARA LANÇAMENTO DE PARAQUEDAS NO INTERIOR DA FUSELAGEM MANTENHA-SE AFASTADO QUANDO EXISTIREM PESSOAS NA CABINE Left fuselage, on external power supply door: ENERGIA EXTERNA...
  • Page 54 Section 2 Cirrus Design Limitations SR20 Engine control panel: 120 KIAS FLAPS 100% 100 KIAS FULL RICH OS ASSENTOS DOS TRIPULANTE DEVEM ESTAR TRAVADOS NA POSIÇÃO E AS ALAVANCAS TOTALMENTE BAIXADAS ANTES DO VÔO BOOST FUEL PUMP IDLE CUTOFF PRIME...
  • Page 55 Cirrus Design Section 2 SR20 Limitations Wing, flap aft edge: NÃO PISE Cabin Door Window, lower edge, centered, applied upside down: PARA SALVAMENTO: QUEBRE E REMOVA A JANELA Bolster Switch Panel, left edge: THIS AIRCRAFT IS CERTIFIED FOR THE FOLLOWING FLIGHT OPERATIONS:...
  • Page 56 Section 2 Cirrus Design Limitations SR20 Instrument Panel: NÃO FUME APERTE OS CINTOS EXTINTOR DE INCÊNDIO DEBAIXO DO ASSENTO DO PILOTO NÃO FUME APERTE OS CINTOS Serials 1005 thru 1638. NÃO FUME • APERTE OS CINTOS EXTINTOR DE INCÊNDIO A ESQUERDA E A FRENTE DO ACENTO DO PILOTO Serials 1639 &...
  • Page 57 Cirrus Design Section 2 SR20 Limitations CAPS Deployment Handle Cover, above pilot's right shoulder: ATENÇÃO USE SOMENTE EM EXTREMA EMERGÊNCIA CINTO DE SEGURANÇA DEVE SER UTILIZADO DURANTE TODO O TEMPO O USO DESTE SISTEMA PODE RESULTAR EM DANOS CORPORAIS OU MORTE VELOCIDADE MÁXIMA DE ABERTURA TESTADA...
  • Page 58 Section 2 Cirrus Design Limitations SR20 Intentionally Left Blank 2-32 P/N 21399-004 Reissue A...
  • Page 59 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 60: Revision A1

    Section 3 Cirrus Design Emergency Procedures SR20 Fuel Imbalance ................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 ..........26 Carbon Monoxide Level High............

  • Page 61: 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 62: 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 63: 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...

  • Page 64: 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 65: 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 66: Engine Failure In Flight

    If altitude or terrain does not permit a safe landing, CAPS deployment may be required. Refer to Section 10, Cirrus Airframe Parachute System (CAPS) for CAPS deployment scenarios and landing considerations. P/N 21399-004...

  • Page 67: 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. Alternate Induction Air ...............ON 8.

  • Page 68: 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 69: Engine Fire In Flight

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

  • Page 70: 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 71: 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 72: 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 73: Cirrus Airframe Parachute System (Caps)

    If flight conditions or terrain does not permit a safe landing, CAPS deployment may be required. Refer to Section 10, Cirrus Airframe Parachute System (CAPS) for CAPS deployment scenarios and landing considerations.

  • Page 74: 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 75: P/N 21399-004

    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 76: Revision A1

    Section 3 Cirrus Design Emergency Procedures SR20 which 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 77: 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 78: 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 79: Propeller System Emergencies

    Cirrus Design Section 3 SR20 Emergency Procedures Propeller System Emergencies Engine Speed High RPM Warning: Engine SpeedHigh 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 80: 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 81: Revision A1

    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 82: Revision A1

    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 83: 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 84: 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) ...... NOT IN RECIRC MODE 2. Temperature Selector............COLD 3. Vent Selector......FEET/PANEL/DEFROST POSITION 4. Airflow Selector ......SET AIRFLOW TO MAXIMUM 5.

  • Page 85: 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 86: Unusual Attitude Emergencies

    CAPS deployment be attempted. The aircraft is not approved for spins, and has not been certified for traditional spin recovery characteristics. The only approved and demonstrated method of spin recovery is activation of the Cirrus Airframe Parachute System (see CAPS Deployment Checklist, this section).

  • Page 87: Inadvertent Spiral Dive During Imc Flight

    7. Exit IMC conditions as soon as possible. Amplification In all cases, if the aircraft enters an unusual attitude from which recovery is not assured, immediately deploy CAPS. Refer to Section Cirrus Airframe Parachute System (CAPS) for CAPS deployment information. P/N 21399-004...

  • Page 88: 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.

  • Page 89: 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, Taxiing, Steering, and Braking Practices...

  • Page 90: Emergency Ground Egress

    Section 3 Cirrus Design Emergency Procedures SR20 Amplification • WARNING • Use 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 91: Revision A1

    – a “chin-up” type pull ensures successful activation. The Cirrus Airframe Parachute System (CAPS) should be activated immediately in the event of a spin. It should also be used in other life- threatening emergencies where CAPS deployment is determined to be safer than continued flight and landing.

  • Page 92: Revision A1

    Section 3 Cirrus Design Emergency Procedures SR20 Expected impact in a fully stabilized deployment is equivalent to a drop from approximately 10 feet. • Caution • CAPS deployment will likely result in damage or loss to the airframe. Several possible scenarios in which the activation of the CAPS would...

  • Page 93: Revision A1

    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 94: Revision A1

    Section 3A Cirrus Design Abnormal Procedures SR20 Flap System Exceedance ............. 18 Landing Gear System ..............19 Brake Failure During Taxi ............. 19 Left/Right Brake Over-Temperature..........19 Other Conditions ................20 Aborted Takeoff ................20 Parking Brake Engaged Annunciation .......... 21 Communications Failure ...............

  • Page 95: Introduction

    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 96: 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 97: 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 98: 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 99: 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 10 Seconds 2. Battery Switches ...Wait 20 seconds before next start attempt If starter does not disengage (relay or solenoid failure): 3.

  • Page 100: 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 left & right fuel quantities indicate less than or equal to 8 gallons per side: a. Land as soon as practical.

  • Page 101: 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 102: Fuel Imbalance

    Section 3A Cirrus Design Abnormal Procedures SR20 Fuel Imbalance FUEL IMBALANCE Caution FUEL IMBALANCE 1. Fuel Quantity Gages ............CHECK 2. Fuel Pump................BOOST If HIGH BOOST already in use for vapor suppression, pump should be left in this position for tank switch.

  • Page 103: Electrical System

    Cirrus Design Section 3A SR20 Abnormal Procedures 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 and will typically be associated with low M1 voltage Alt 1 current indications, Battery 1 discharge and ALT 1 Caution message.

  • Page 104: Low Alternator 1 Output

    Section 3A Cirrus Design Abnormal Procedures SR20 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 105: Low Alternator 2 Output

    Cirrus Design Section 3A SR20 Abnormal Procedures 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 106: Integrated Avionics System

    Section 3A Cirrus Design Abnormal Procedures SR20 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 FAN FAIL Advisory PFD 1 FAN FAIL 1.

  • Page 107: Flight Displays Too Dim

    Cirrus Design Section 3A SR20 Abnormal Procedures 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 108: Pitot Static System

    Section 3A Cirrus Design Abnormal Procedures SR20 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 109: Pitot Heat Current Sensor Annunciation

    Cirrus Design Section 3A SR20 Abnormal Procedures 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...

  • Page 110: Flight Control System

    Section 3A Cirrus Design Abnormal Procedures SR20 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 •...

  • Page 111: Landing Gear System

    Cirrus Design Section 3A SR20 Abnormal Procedures 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 112: Other Conditions

    Section 3A Cirrus Design Abnormal Procedures SR20 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 113: Parking Brake Engaged Annunciation

    Cirrus Design Section 3A SR20 Abnormal Procedures 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 114 Section 3A Cirrus Design Abnormal Procedures SR20 Intentionally Left Blank 3A-22 P/N 21399-004 Revision A1...
  • Page 115 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 117: 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: Log of Supplements. Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3050 lb.

  • Page 118: 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 119 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 120 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 121 Cirrus Design Section 4 SR20 Normal Procedures • Caution • Serials 2016 thru 2240 before SB2X-32-21: 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 122 Section 4 Cirrus Design Normal Procedures SR20 11. Left Main Gear and Forward Wing a. Wheel fairings....... Security, Accumulation of Debris b. Tire..........Condition, Inflation, and Wear • Caution • Serials 2016 thru 2240 before SB2X-32-21: Clean and inspect temperature indicator installed to piston housing. If indicator center is black, the brake assembly has been overheated.

  • Page 123: 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 124: 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 125 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 126: 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 127: 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 128 Section 4 Cirrus Design Normal Procedures SR20 a. Pitot Heat................ON b. Navigation Lights ..............ON 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.

  • Page 129: 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 130: Normal Takeoff

    Section 4 Cirrus Design Normal Procedures SR20 Normal Takeoff 1. Brakes ........RELEASE (Steer with Rudder Only) 2. Power Lever ............FULL FORWARD • Note • Abrupt full range throttle movement may result in a slight engine hesitation or stumble before maximum power is attained.

  • Page 131: Climb

    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 132: 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 133: 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 134: Descent

    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 135: 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 136: After Landing

    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 137: 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 138: 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 139 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 140: 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 141: Lead Reduction Before Shut Down

    Cirrus Design Section 4 SR20 Normal Procedures Lead Reduction Before Shut Down Complete the following procedure before shutdown to reduce potential for lead build-up in the combustion chamber, spark plugs, and engine oil. • Caution • The airplane must be stationary before the following procedure is completed.

  • Page 142: Fuel Conservation

    Section 4 Cirrus Design Normal Procedures SR20 • Note • Do not follow these noise abatement procedures where they conflict with Air Traffic Control clearances or instructions, weather considerations, or wherever they would reduce safety. 1. When operating VFR over noise-sensitive areas, such as outdoor...
  • Page 143 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 145: 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 146: 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 147: 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 148: 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 149: 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 150: 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 151: 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 152: 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 153: Outside Air Temperature For Isa Condition

    Cirrus Design Section 5 SR20 Performance Data Outside Air Temperature for ISA Condition Press ISA-30°C ISA-15°C ISA+15°C ISA+30°C Feet °C °F °C °F °C °F °C °F °C °F 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000...

  • Page 154: 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 155: 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 156: 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 157: Takeoff Distance - 3050 Lb

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

  • Page 158: Takeoff Distance - 2500 Lb

    Section 5 Cirrus Design Performance Data SR20 Takeoff Distance - 2500 LB WEIGHT = 2500 LB Headwind: Subtract 10% for each 12 knots Speed at Liftoff = 68 KIAS headwind. Speed over 50 Ft Obstacle = 75 KIAS Tailwind: Add 10% for each 2 knots tailwind up Flaps - 50% ·...

  • Page 159: 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 160: Takeoff Rate Of Climb

    Section 5 Cirrus Design Performance Data SR20 Takeoff Rate of Climb Conditions: • Power ....................Full Throttle • Mixture....................... Full Rich • 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 161: 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 162: 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 163: 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 11,000 10,000...
  • Page 164 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 165: 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 and fairings are removed.
  • Page 166 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 167 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 168 Section 5 Cirrus Design Performance Data SR20 Range / Endurance Profile (Continued) 65% POWER Mixture = Best Power Airspee Press Climb Fuel Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise Hours Nm/Gal KTAS 46.3 10.5 13.0 2000 45.7 10.5...

  • Page 169: 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 170: 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 171: Landing Distance

    Cirrus Design Section 5 SR20 Performance Data Landing Distance Conditions: • Winds ....................... Zero • Runway ..................Dry, Level, Paved • Flaps..................100%, 50%, or 0% • 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 172 Section 5 Cirrus Design Performance Data SR20 Landing Distance Table - Flaps 100% WEIGHT: 3050 LB Headwind: Subtract 10% per each 13 Speed over 50 Ft Obstacle: 78 KIAS knots headwind. Flaps: 100% Tailwind: Add 10% for each 2 knots tail- Power: Idle wind up to 10 knots.
  • Page 173 Cirrus Design Section 5 SR20 Performance Data Landing Distance Table - Flaps 50% WEIGHT: 3050 LB Headwind: Subtract 10% per each 13 Speed over 50 Ft Obstacle: 82 KIAS knots headwind. Flaps: 50% Tailwind: Add 10% for each 2 knots tail- Power: Idle wind up to 10 knots.
  • Page 174 Section 5 Cirrus Design Performance Data SR20 Landing Distance Table - Flaps 0% WEIGHT: 3050 LB Headwind: Subtract 10% per each 13 Speed over 50 Ft Obstacle: 87 KIAS knots headwind. Flaps: 0% Tailwind: Add 10% for each 2 knots tail- Power: Idle wind up to 10 knots.
  • Page 175 Cirrus Design Section 6 SR20 Weight and Balance Data Section 6: Weight and Balance Data Table of Contents Introduction ..................3 Loading Instructions ................4 Weight and Balance Loading Form............ 5 Loading Data..................6 Moment Limits..................7 Weight & Balance Record ..............8 Equipment List ...................
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  • Page 177 Cirrus Design Section 6 SR20 Weight and Balance Data Introduction This section describes the procedure for calculating the weight and moment for various operations. A comprehensive list of all equipment available for this airplane is included at the back of this section.

  • Page 178: 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 179: 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 180: 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 181: 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 6-1) are within limits. 3200 3000 2800...
  • Page 182 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 183: 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 21399-004 P/N 21399-004 Revision A1...
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  • Page 185 Cirrus Design Section 7 SR20 Airplane and Systems Description Section 7: Airplane and Systems Description Introduction ..................5 Airframe ..................... 6 Fuselage ..................6 Wings....................6 Empennage ..................7 Flight Controls ..................8 Elevator System................8 Aileron System................10 Rudder System ................12 Control Locks................
  • Page 186 Section 7 Cirrus Design Airplane and Systems Description SR20 Engine ....................35 Engine Controls ................35 Engine Indicating ................36 Engine Lubrication System ............40 Ignition and Starter System............40 Air Induction System ..............40 Engine Exhaust................41 Engine Fuel Injection ..............41 Engine Cooling................
  • Page 187 Emergency Locator Transmitter ..........100 Fire Extinguisher................. 101 Hour Meters ................102 Emergency Egress Hammer............102 Convenience Outlet(s) ..............102 Cirrus Airframe Parachute System ..........104 System Description ..............104 Activation Handle ................ 105 Deployment Characteristics ............106 P/N 21399-004...
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  • Page 189 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 190: 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 191: 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 192: 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 193 Cirrus Design Section 7 SR20 Airplane and Systems Description SR20_FM07_1461 Figure 7-1 Elevator System P/N 21399-004 P/N 21399-004 Reissue A...

  • Page 194: 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 195 Cirrus Design Section 7 SR20 Airplane and Systems Description SR20_FM07_1462 Figure 7-2 Aileron System P/N 21399-004 P/N 21399-004 7-11 7-11 Reissue A...

  • Page 196: 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 197 Cirrus Design Section 7 SR20 Airplane and Systems Description SR20_FM07_1463 Figure 7-3 Rudder System P/N 21399-004 P/N 21399-004 7-13 7-13 Reissue A...

  • Page 198: 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 199 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 200 Section 7 Cirrus Design Airplane and Systems Description SR20 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 201: Flight Instruments

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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 202 Section 7 Cirrus Design Airplane and Systems Description SR20 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 203: Attitude Indicator

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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 204: Airspeed Indicator

    Section 7 Cirrus Design Airplane and Systems Description SR20 Serials 2273 & subs w/ MD302 Standby Attitude Module: The MD302 Standby Attitude Module is mounted on the LH bolster panel and gives backup indication of flight attitude. Bank attitude is indicated by a pointer at the top of the indicator relative to the bank scale with index marks at 0°...

  • Page 205: Altimeter

    Cirrus Design Section 7 SR20 Airplane and Systems Description precision airspeed indicator installed in the pilot's instrument panel. The instrument senses difference in static and Pitot pressures and displays the result in knots on an airspeed scale. A single pointer sweeps an indicated airspeed scale calibrated from 40 to 220 knots.
  • Page 206 Section 7 Cirrus Design Airplane and Systems Description SR20 Standby Altimeter Serials w/o MD302 Standby Attitude Module: Airplane altitude is depicted on a conventional, three-pointer, internally lit barometric altimeter installed on the LH bolster panel. The instrument senses the local barometric pressure adjusted for altimeter setting and displays the result on the instrument in feet.

  • Page 207: 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 208: 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 209: Wing Flaps

    Cirrus Design Section 7 SR20 Airplane and Systems Description Wing Flaps The electrically controlled, single-slotted flaps provide low-speed lift enhancement. Each flap is manufactured of aluminium and connected to the wing structure at three hinge points. Rub strips are installed on the top leading edge of each flap to prevent contact between the flap and wing flap cove.
  • Page 210 Section 7 Cirrus Design Airplane and Systems Description SR20 SR20_FM07_1460 Figure 7-6 Wing Flaps 7-26 P/N 21399-004 Revision A1...

  • Page 211: Landing Gear

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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 212 Section 7 Cirrus Design Airplane and Systems Description SR20 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 (left or right) main wheel brake.

  • Page 213: Baggage Compartment

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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 214: Seats

    Section 7 Cirrus Design Airplane and Systems Description SR20 Seats The seating arrangement consists of two individually adjustable seats for the pilot and front seat passenger and, Serials w/o 2+1 Rear Seat: two individual rear seats with fold-down seat backs or, Serials w/ 2+1 Rear Seat: a “2+1”...

  • Page 215: Seat Belt And Shoulder Harness

    Cirrus Design Section 7 SR20 Airplane and Systems Description bulky cargo extending forward from the baggage compartment. The detent pins are located at the base of the backrest. To fold seat back forward: 1. From the baggage access, lift the carpet panel at lower aft edge of seat to reveal the seat back locking pins (attached to lanyards).
  • Page 216 Section 7 Cirrus Design Airplane and Systems Description SR20 Front Seat Inflatable Restraints An inflatable shoulder harness is integral to each front seat harness. The electronic module assembly, mounted below the cabin floor, contains a crash sensor, battery, and related circuitry to monitor the deceleration rate of the airplane.
  • Page 217 Cirrus Design Section 7 SR20 Airplane and Systems Description installed using the center seat belt. Three top tether anchors for the child seats are located on the rear bulkhead. To install a child seat: 1. Fasten lower seat attachments to bench seat: a.

  • Page 218: Cabin Doors

    Section 7 Cirrus Design Airplane and Systems Description SR20 Cabin Doors Two large forward hinged doors allow crew and passengers to enter and exit the cabin. The door handles engage latching pins in the door frame receptacles at the upper aft and lower aft door perimeter. Gas charged struts provide assistance in opening the doors and hold the doors open against gusts.

  • Page 219: Engine

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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 220: Engine Indicating

    Section 7 Cirrus Design Airplane and Systems Description SR20 control, depress the center lock button, pull the knob to the open position, and then release the lock button. Pulling the knob opens the alternate air induction door on the engine induction air manifold, bypasses the air filter, and allows warm unfiltered air to enter the engine.
  • Page 221 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 222 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 223 Cirrus Design Section 7 SR20 Airplane and Systems Description Oil Pressure Oil Pressure is shown in the upper right corner of the ENGINE page, opposite the oil temperature scale, as both a simulated pressure gage and as a digital value. The gage pointer sweeps a scale range from 0 to 90 PSI in 10 PSI increments.

  • Page 224: 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, through the one-quart, full-flow oil filter, and then directed to the engine-mounted oil cooler.

  • Page 225: 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 226: 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 227: 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 228: Fuel Selector Valve

    Section 7 Cirrus Design Airplane and Systems Description SR20 The airplane may be serviced to a reduced capacity to permit heavier cabin loadings. This is accomplished by filling each tank to a tab visible below the fuel filler, giving a reduced fuel load of 13.0 gallons usable in each tank (26 gallons total usable in all flight conditions).
  • Page 229 Cirrus Design Section 7 SR20 Airplane and Systems Description ANNUNCIATOR FUEL FUEL QUANTITY VENT VENT FILLER FILLER INDICATOR L. WING TANK R. WING TANK R. WING L. WING COLLECTOR COLLECTOR CHECK CHECK VALVE VALVE SELECTOR VALVE FLAPPER FLAPPER VALVE VALVE...

  • Page 230: Fuel Indicating

    Section 7 Cirrus Design Airplane and Systems Description SR20 Fuel Indicating Fuel quantity is measured by float-type quantity sensors installed in each fuel tank and displayed on the Fuel Quantity Gage. • Caution • When the fuel tanks are 1/4 full or less, prolonged uncoordinated flight such as slips or skids can uncover the fuel tank outlets.
  • Page 231 Cirrus Design Section 7 SR20 Airplane and Systems Description 0 to 8.2 U.S. gallons and a green band from 8.2 to 28 U.S. gallons. The indicators are calibrated to read 0 gallons when no usable fuel remains. Fuel quantity is measured by a float type quantity sensors installed in the fuel tanks.
  • Page 232 Section 7 Cirrus Design Airplane and Systems Description SR20 Fuel System Annunciations Fuel system health, caution, and warning messages are displayed in color-coded text in the Crew Alerting System (CAS) window located to the right of the Altimeter and Vertical Speed Indicator. In combination...
  • Page 233 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 234 Section 7 Cirrus Design Airplane and Systems Description SR20 Fuel System Indication LEGEND 1. Fuel Flow Gage 2. Fuel Calculations: ·Fuel Used (Totalizer) ·Fuel Remaining (Totalizer) ·Time Remaining (Totalizer) ·Fuel Range (Totalizer) ·Nautical Miles Per Gallon (Totalizer) 3. Fuel Quantity Gage (Float Sensor) 4.

  • Page 235: Mixture Management

    Cirrus Design Section 7 SR20 Airplane and Systems Description Mixture Management The mixture control needs to be carefully monitored and managed during all phases of flight to avoid damage to the engine or possible loss of power. After engine start, and during taxiing operations, lean the mixture until maximum engine RPM is attained to prevent possible spark plug fouling and ensure smooth engine operation.

  • Page 236: 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 237 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 SWITCH RELAY...
  • Page 238 Section 7 Cirrus Design Airplane and Systems Description SR20 LANDING 100A ALT 1 LIGHT ALT 1 7.5A VOLT REG RELAY LANDING LIGHT EXTERNAL SWITCH POWER RELAY ALT 1 EXTERNAL SWITCH POWER 125A BAT 1 BAT 1 BAT 1 SWITCH RELAY...

  • Page 239: Power Distribution

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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 240: Electrical System Protection

    Section 7 Cirrus Design Airplane and Systems Description SR20 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 241 Cirrus Design Section 7 SR20 Airplane and Systems Description through 30-amp fuses inside the MCU and also by BAT 2 through the 20-amp BAT 2 circuit breaker. In the event of ALT 1 or ALT 2 failure, the Essential Buses in the circuit breaker panel will be powered by the remaining alternator through the Main Distribution Bus 1 or Main Distribution Bus 2 in the MCU.
  • Page 242 Section 7 Cirrus Design Airplane and Systems Description SR20 AVIONICS A/C COND LIGHTS STDBY ALT 1 ALT2 ATTD #2 ENGINE MFD #2 INSTR STALL CABIN CAMERA WARNING LIGHTS 12V DC ROLL FUEL QTY OUTLET TRIM PITCH A/C COMPR MFD #1...
  • Page 243 Cirrus Design Section 7 SR20 Airplane and Systems Description AVIONICS LIGHTS RECOG STDBY ALT2 LIGHTS ATTD #2 CONV ENGINE MFD #2 LIGHTS INSTR STALL CABIN A/C COND CAMERA WARNING LIGHTS 12V DC ROLL ALT 1 FUEL QTY OUTLET TRIM PITCH...

  • Page 244: Electrical System Control

    Section 7 Cirrus Design Airplane and Systems Description SR20 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 245: Ground Service Receptacle

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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 246: Electrical Indicating

    Section 7 Cirrus Design Airplane and Systems Description SR20 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 247 Cirrus Design Section 7 SR20 Airplane and Systems Description Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Electrical System Indication 8 9 10 Electrical and Lighting Controls LEGEND 7. Avionics 1. Essential & Main Bus Voltage 2. Alternator & Battery Current 8.

  • Page 248: Lighting Systems

    Section 7 Cirrus Design Airplane and Systems Description SR20 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 249: Interior Lighting

    Cirrus Design Section 7 SR20 Airplane and Systems Description Interior Lighting Interior lighting for the airplane consists of 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 250 Section 7 Cirrus Design Airplane and Systems Description SR20 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 251: Convenience Lighting

    Cirrus Design Section 7 SR20 Airplane and Systems Description Convenience Lighting Serials 2303 & subs w/ Convenience Lighting: The convenience lighting option consists of the overhead dome light, overhead baggage compartment lights, interior footwell lights, exterior entry step lights, and a key fob.
  • Page 252 Section 7 Cirrus Design Airplane and Systems Description SR20 Convenience Lighting Operation When the cabin light switch is in the ON position: • Dome light and footwell lights will turn on. • Entry step lights will turn on when either cabin door is opened or...

  • Page 253: Environmental System

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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 254 Section 7 Cirrus Design Airplane and Systems Description SR20 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 255 Cirrus Design Section 7 SR20 Airplane and Systems Description 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 256: Distribution

    Section 7 Cirrus Design Airplane and Systems Description SR20 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 257: Cooling

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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 258: Vent Selection

    Section 7 Cirrus Design Airplane and Systems Description SR20 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 259 Cirrus Design Section 7 SR20 Airplane and Systems Description 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 260: Stall Warning System

    Section 7 Cirrus Design Airplane and Systems Description SR20 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 261: Pitot Heat Switch

    Cirrus Design Section 7 SR20 Airplane and Systems Description Pitot-Static System The Pitot-Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage. The Pitot heat is pilot controlled through a panel-mounted switch. An internally mounted alternate static pressure source provides backup static pressure should that the primary static source becomes blocked.
  • Page 262 Section 7 Cirrus Design Airplane and Systems Description SR20 AIR DATA COMPUTER 2 (optional) 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...
  • Page 263 Cirrus Design Section 7 SR20 Airplane and Systems Description AIR DATA COMPUTER 2 (optional) AIR DATA COMPUTER PFD Air Data MD302 STANDBY ATTITUDE MODULE ALTERNATE PITOT-STATIC STATIC WATER TRAPS AIR SOURCE PITOT MAST STATIC HEATER BUTTONS Annunciation PITOT HEAT CURRENT...

  • Page 264: 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, and consists of the following components: •...
  • Page 265 Cirrus Design Section 7 SR20 Airplane and Systems Description XM RADIO RECEIVER (optional) XM SATELLITE DATA LINK RECEIVER (optional) FMS KEYBOARD MAG 1 MAG 2 AHRS 1 AHRS 2 AUTOPILOT (optional) MODE CONTROLLER (optional) IRIDIUM GLOBAL SATELLITE DATALINK AIR DATA...
  • Page 266 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 267 Cirrus Design Section 7 SR20 Airplane and Systems Description 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 268 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 269 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 270 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 271 Cirrus Design Section 7 SR20 Airplane and Systems Description GMA 347 or 350 Audio Panel with Marker Beacon Receiver The 347 or 350 Audio Panel, installed on the center console below the Flight Management System Keyboard, integrates NAV/COM digital audio,...

  • Page 272: 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 latest revision of AFM Supplement 11934-S41 GFC 700 Automatic Flight Control System for operating information. GTX 33 Mode S and GTX 33 ES Mode S Transponders...
  • Page 273 Cirrus Design Section 7 SR20 Airplane and Systems Description GDL 69/69A XM Satellite Weather and Radio The XM Datalink Satellite Receiver, mounted in the empennage avionics compartment, receives and transmits near real-time weather information to the MFD and PFD. If GDL 69A option is installed, this...
  • Page 274 Section 7 Cirrus Design Airplane and Systems Description SR20 Stormscope WX-500 Weather Mapping Sensor The Stormscope WX-500 System detects electrical discharges associated with thunderstorms and displays the activity on the MFD. The system consists of an antenna located on top of the fuselage and a processor unit mounted under the aft baggage floor.
  • Page 275 Cirrus Design Section 7 SR20 Airplane and Systems Description DME/ADF circuit breaker on AVIONICS BUS. Refer to the Perspective Integrated Avionics System Pilot’s Guide for a general description of the system and its operating modes. Refer to the Bendix/King DME System Pilot’s Guide for a detailed discussion of the system.
  • Page 276 Section 7 Cirrus Design Airplane and Systems Description SR20 Max Viz Enhanced Vision System The Enhanced Vision System is an electro-optical system that uses a Long-Wave Infrared (IR) camera. Infrared is particularly effective at night, smoke, haze, and smog in addition to a broad spectrum of rain, snow, and radiation-type fog.
  • Page 277 Cirrus Design Section 7 SR20 Airplane and Systems Description Approach Baro-VNAV Serials w/ system software load 0764.21 or later: While executing an LNAV/VNAV approach with SBAS unavailable, Baro-VNAV is used for vertical approach guidance. This occurs due to any of the following conditions: •...
  • Page 278 Section 7 Cirrus Design Airplane and Systems Description SR20 supported using Baro-VNAV. If Baro-VNAV can be supported, the “APR ADVISORY - SBAS VNAV not available. Using Baro VNAV.” message will be displayed on the PFDs and the vertical deviation indicator (VDI) will be flagged. If SBAS is required for the approach, the approach mode (e.g.
  • Page 279 Cirrus Design Section 7 SR20 Airplane and Systems Description 29.92 NOTE LEGEND While Baro-VNAV is being utilized, 1.Excessive Deviation the Glidepath Indicator appears as Indicator a magenta pentagon. 2.Glidepath Indicator SR20_FM02_3685 Figure 7-20 Baro-VNAV Vertical Deviation Indicator P/N 21399-004 P/N 21399-004...
  • Page 280 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 281: 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 282 Section 7 Cirrus Design Airplane and Systems Description SR20 Headset and Microphone Installation Serials 2016 thru 2126: The airplane is equipped with provisions for four Active Noise Reduction (ANR) and four conventional (MIC/ HEADPHONES) headsets. Headset jacks for the pilot and front seat passenger are located in the map case and on the aft portion of the center console for the rear passengers.
  • Page 283 Cirrus Design Section 7 SR20 Airplane and Systems Description Cell Phone Input Jack Serials w/ GMA 347: One 2.5 mm cell phone jack (CELL PHONE INPUT) is provided on the aft portion of the center console near the convenience outlet and is distributed by the TEL selection on the audio panel.

  • Page 284: Cabin Features

    Section 7 Cirrus Design Airplane and Systems Description SR20 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 285 Cirrus Design Section 7 SR20 Airplane and Systems Description 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 286: Hour Meters

    Section 7 Cirrus Design Airplane and Systems Description SR20 of ensuring that the nozzle is unobstructed, the pin has not been pulled, and the canister has not been damaged. Serials w/o gaged fire extinguisher: The unit should weigh approximately 1.5 lb (0.7 kg). For preflight, charge can be determined by ‘hefting’...
  • Page 287 Cirrus Design Section 7 SR20 Airplane and Systems Description center console for use by the rear passengers. The ports comply with USB Battery Charging 1.2 Compliance Plan, and are intended for USB-compatible devices only. There is no data or audio access at the ports.

  • Page 288: System Description

    Airplane and Systems Description SR20 Cirrus Airframe Parachute System The airplane is equipped with a Cirrus Airframe 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 289: Activation Handle

    Cirrus Design Section 7 SR20 Airplane and Systems Description 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 290: Deployment Characteristics

    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 291 Cirrus Design Section 7 SR20 Airplane and Systems Description seats and landing gear are designed to accommodate this stress, occupants must prepare for it in accordance with Section 3 - CAPS Deployment Checklist. • Note • The CAPS is designed to work in a variety of airplane attitudes, including spins.
  • Page 292 Section 7 Cirrus Design Airplane and Systems Description SR20 Intentionally Left Blank 7-108 P/N 21399-004 Revision A1...
  • Page 293 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 294 Section 8 Cirrus Design Handling, Servicing, & Maintenance SR20 Intentionally Left Blank P/N 21399-004 Reissue A...

  • Page 295: Introduction

    This section provides general guidelines for handling, servicing and maintaining your aircraft. In order to ensure continued safe and efficient operation of your airplane, keep in contact with your Authorized Cirrus Service Center to obtain the latest information pertaining to your aircraft. Operator’s Publications The FAA Approved Airplane Flight Manual and Pilot’s Operating...

  • Page 296: Obtaining Publications

    Service Bulletin. Give careful attention to the Service Advisory information. Obtaining Publications Pilot’s Operating Handbooks and aircraft service publications can be obtained from Cirrus Design at www.cirrusaircraft.com, or the Cirrus Connection at www.cirrusconnection.com. P/N 21399-004 Revision A1...

  • Page 297: 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 298: Airworthiness Directives

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

  • Page 299: 100-Hour Inspection

    In lieu of the above requirements, an airplane may be inspected using a 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.

  • Page 300: 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 301 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 302: 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 303: 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 304: 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 305: 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 306: 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 307 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...

  • Page 308: Servicing

    Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Servicing Landing Gear Servicing Serials 2016 thru 2240 before SB2X-32-21: The main landing gear wheel assemblies use 15 x 6.00 x 6 tires and tubes. The nose wheel assembly uses a 5.00 x 5 tire and tube.

  • Page 309: Tire Inflation

    Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance 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 310: Oil Servicing

    Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Oil Servicing The oil capacity of the Teledyne Continental IO-360-ES engine is 8 quarts. It is recommended that the oil be changed every 50 hours and sooner under unfavorable operating conditions. The following grades...
  • Page 311 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance Product Supplier Aeroshell (R) W Shell Australia Aeroshell Oil W Aeroshell Oil W 15W-50 Shell Canada Ltd. Anti-Wear Formulation Aeroshell 15W50 Aeroshell Oil W Aeroshell Oil W 15W-50 Shell Oil Company...

  • Page 312: Fuel System Servicing

    Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 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 313 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance 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 314: Battery Service

    Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 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 315: Key Fob Battery Replacement

    Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance • Note • For aircraft equipped with conventional lead acid battery requiring periodic electrolyte level check: Refer to the AMM for information on Battery Overhaul and Replacement Schedule and Scheduled Maintenance Checks.

  • Page 316: Cleaning And Care

    Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Cleaning and Care Cleaning Exterior Surfaces • Note • Prior to cleaning, place the airplane in a shaded area to allow the surfaces to cool. The airplane should be washed with a mild soap and water. Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause corrosion of metal.
  • Page 317 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance 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 318: Care Of Graphics

    Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Care of Graphics Graphics require care similar to any fine paint finish. Use high quality products designed specifically for use on automobile finishes. Use products in accordance with the manufacturer’s instructions.
  • Page 319 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance • Caution • Holding the nozzle of a pressure washer at an angle less than 90 degrees to the graphic may lift the edges of the graphic. 4. Keep the spray nozzle perpendicular to the graphic, and at a distance of at least 1 foot (30 cm).
  • Page 320 Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Cleaning Fuel Spills • Caution • Immediately clean fuel spills to avoid degrading the vinyl and adhesive used in the graphic. 1. Wipe off spilled fuel. 2. Clean graphic with a wet, non-abrasive detergent such as 3M™...
  • Page 321 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance Graphic Restoration If typical cleaning methods fail to produce satisfactory results, refer to the recommended restoration products and mixtures below to help preserve the condition of the graphics on your aircraft.
  • Page 322 Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Windscreen and Windows Before cleaning an acrylic window, rinse away all dirt particles before applying cloth or chamois. Never rub dry acrylic. Dull or scratched window coverings may be polished using a special acrylic polishing paste.
  • Page 323 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance 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 324: Cleaning Interior Surfaces

    Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 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 325 Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance Cleaning Product Cleaning Application Supplier Interior Windscreen and Prist Prist Aerospace Windows Optimax Display Screens PhotoDon Mild Dishwasher Soap Cabin Interior Any Source (abrasive free) Leather Care Kit Leather Upholstery Cirrus Design...
  • Page 326 Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Instrument Panel and Electronic Display Screens The instrument panel, control knobs, and plastic trim need only to be wiped clean with a soft damp cloth. The multifunction display, primary flight display, and other electronic display screens should be cleaned with Optimax - LCD Screen Cleaning Solution as follows: •...
  • Page 327 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 328 Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Intentionally Left Blank 8-36 P/N 21399-004 Revision A1...
  • Page 329 ___ 11934-S42 Garmin Terrain Awareness/Warning System 12-18-08 ___ 11934-S43 SR20 Airplanes Registered in Russia 01-20-09 ___ 11934-S45 R1 SR20 Airplanes Registered in Argentina 11-13-13 ___ 11934-S51 SR20 Airplanes Registered in Colombia 12-07-10 ___ 11934-S52 R1 SR20 Airplanes Registered in Chile...
  • Page 330 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 check mark in the Part Number column indicates that the supplement is applicable to the POH.
  • Page 331 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 332 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 333 Cirrus Design Section 9 SR20 Supplements containing aircraft specific information is transmitted at 50 seconds for 440 milliseconds. CIRCUIT BREAKER PANEL (REF) MOUNTING TRAY (REF) LEGEND 1. LED Annunciator 2. Remote Switch 3. Antenna 4 Remote Cable 5. Main Control Switch 6.
  • Page 334 Section 9 Cirrus Design Supplements SR20 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 335 Cirrus Design Section 9 SR20 Supplements 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 336 Section 9 Cirrus Design Supplements SR20 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 337 Cirrus Design Section 9 SR20 Supplements 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 338 Section 9 Cirrus Design Supplements SR20 does not check the integrity of the ELT 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"...
  • Page 339 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 340 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 341 Cirrus Design Section 9 SR20 Supplements 5. The Autopilot may not be engaged beyond the Engagement Limits. If the Autopilot is engaged beyond the command limits (up to engagement limits), it will be rolled or pitched to within the command limits and an altitude loss of 1000 feet or more can be expected while attitude is established in the selected mode.
  • Page 342 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 343 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 344 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 345 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 346 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 347 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 348 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 feet for 4 minutes, then to 12,500 feet thereafter.
  • Page 349 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 350 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 351 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 352 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 353 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 354 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 355 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 356 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 357 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 358 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 359 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 360 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 361 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 362 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 363 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 364 Section 9 Cirrus Design Supplements SR20 Serials w/ Discrete-Triggered Low Speed Mode (Optional) To protect against an impending stall, the Discrete-Triggered Low Speed Mode uses stick forces, similar to those used for the pitch and roll modes, to control the pitch attitude. These stick forces are triggered by the stall warning system.
  • Page 365 Cirrus Design Section 9 SR20 Supplements As described in the following table, when the aircraft reaches predetermined airspeeds a yellow MINSPD annunciation will appear above the airspeed indicator and a single aural “AIRSPEED” will sound to alert the pilot to an impending underspeed condition.
  • Page 366 Section 9 Cirrus Design Supplements SR20 Non-Altitude Critical Mode (VS, PIT, VNAV, LVL, IAS) For all non-altitude critical modes the Autopilot will maintain its original reference (VS, PIT, etc...) until airspeed decays to a minimum airspeed (MINSPD). Crew alert and annunciation during a non-altitude critical underspeed event are similar to an altitude-critical event, except that;...
  • Page 367 Cirrus Design Section 9 SR20 Supplements 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 368 Supplements SR20 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 369 Cirrus Design Section 9 SR20 Supplements Section 8 – Handling, Service, & Maintenance No Change. Section 10 – Safety Information No Change. P/N 11934-S41 31 of 32 Revision 03: 09-08-14...
  • Page 370 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 32 of 32 P/N 11934-S41 Revision 03: 09-08-14...
  • Page 371 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 372 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 373 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 374 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 375 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 376 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 6 of 6 P/N 11934-S42 Original Issue: 12-18-08...
  • Page 377 Cirrus Design Section 9 SR20 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement Artex ELT 1000 406 MHz ELT System When Artex ELT 1000 406 MHz ELT System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements section (Section 9) of the Pilot’s Operating Handbook.
  • Page 378 The ELT automatically transmits the standard sweep tone on 121.5 MHz if rapid deceleration is detected or the Cirrus Airframe Parachute System (CAPS) is deployed. CENTER CONSOLE...
  • Page 379 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations No Change. Section 3 - Emergency Procedures 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.
  • Page 380 4 to 5 feet per second, or upon sensing deployment of the Cirrus Airframe Parachute System (CAPS). Once activated, the ELT transmits VHF band audio sweeps at 121.5 MHz until battery power is gone.
  • Page 381 Cirrus Design Section 9 SR20 Supplements “ARM/OFF” - “TEST”, and a red LED annunciator. The red LED annunciator flashes when the ELT is transmitting. Section 8 - Handling, Servicing & Maintenance The ELT batteries must be inspected in accordance with the Airplane Maintenance Manual, 5-20 - Scheduled Maintenance Checks.
  • Page 382 Section 9 Cirrus Design Supplements SR20 even if the radiating ELT’s antenna is disconnected. Therefore, it does not check the integrity of the ELT system or provide the same level of confidence as does an AM radio. 1. Tune aircraft receiver to 121.5 MHz.
  • Page 383 SR20 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 384 Section 10 Cirrus Design Safety Information SR20 Intentionally Left Blank 10-2 P/N 21399-004 Reissue A...

  • Page 385: Introduction

    Cirrus strongly recommends that all pilots seek regular recurrent training and that they operate in accordance with the Cirrus Flight Operations Manual and Envelope of Safety. As the pilot you must be thoroughly familiar with the contents of this...

  • Page 386: Cirrus Airframe Parachute System (Caps)

    Its use should not be taken lightly. Instead, possible CAPS activation scenarios should be well thought out and mentally practiced by every Cirrus pilot. Pilots who regularly conduct CAPS training and think about using CAPS will often have a higher probability of deploying CAPS when necessary.
  • Page 387 CAPS activation is strongly recommended. Numerous fatalities that have occurred in Cirrus aircraft accidents likely could have been avoided if pilots had made the timely decision to deploy CAPS.

  • Page 388: General Deployment Information

    Section 10 Cirrus Design Safety Information SR20 activation by the passengers is highly recommended. This scenario should be discussed with passengers prior to flight and all appropriate passengers should be briefed on CAPS operation so they could effectively deploy CAPS if required.

  • Page 389: Landing Considerations

    Cirrus Design Section 10 SR20 Safety Information Deployment Attitude The CAPS has been tested in all flap configurations at speeds ranging from V to V . Most CAPS testing was accomplished from a level attitude. Deployment from a spin was also tested. From these tests it...
  • Page 390 Section 10 Cirrus Design Safety Information SR20 discussion below gives some specific recommendations, however, the pilot's decision will depend upon all factors, including time to impact, altitude, terrain, winds, condition of airplane, etc. There is the possibility that one or both doors could jam at impact. If...
  • Page 391 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 392: 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 393: 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 394 Section 10 Cirrus Design Safety Information SR20 • Overheated components, indicated by discoloration or warping of the disk rotor. Excessive heat can cause the caliper components to discolor or cause yellowing of the part identification label. Refer to Section 8,...

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