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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. The EASA approved Airplane Flight Manual consists of the FAA approved Airplane Flight Manual, associated POH Supplements, and this Title Page.
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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.
Cirrus Design Pilot’s Operating Handbook SR20 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 4-10 Original Issue 6-11 Original Issue 7-54 Original Issue 4-11 Original Issue 6-12 Original Issue 7-55 Original Issue 4-12...
Cirrus Design Pilot’s Operating Handbook SR20 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 8-23 Original Issue 8-24 Original Issue 8-25 Revision 1 8-26 Original Issue 8-27 Revision 1 8-28 Original Issue 8-29...
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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 11934-004E Revision 1...
Foreword Foreword This Pilot’s Operating Handbook (POH or Handbook) has been prepared by Cirrus Design Corporation to familiarize operators with the aircraft. Read this Handbook 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”...
Section Front Matter Cirrus Design Foreword SR20 The 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. The Handbook is presented in loose-leaf form for ease in inserting revisions and is sized for convenient storage.
Original issue pages will be identified by the words “Original Issue” at this location. In the event that the majority of pages in the Handbook are revised, Cirrus may determine that it is more effective to reissue the Handbook. Reissued pages will be identified by the word “Reissue”...
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 Handbook and that the supplement is properly recorded on the “Log of...
Cirrus Design Section Front Matter SR20 Foreword Retention of Data In the event a new title page is issued, the weight and balance data changes, equipment list changes, or the “Log of Supplements” is replaced, the owner must ensure that all information applicable to the airplane is transferred to the new pages and the aircraft records are current.
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................
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.
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).
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.
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..........
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.
Section 1 Cirrus Design General SR20 Stalling Speed is the minimum steady flight speed at which aircraft controllable landing configuration (100% flaps) at the most unfavorable weight and balance. Best Angle of Climb Speed is the speed at which the airplane will obtain the highest altitude in a given horizontal distance.
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.
Section 1 Cirrus Design General SR20 NMPG Nautical Miles Per Gallon is the distance (in nautical miles) which can be expected per gallon of fuel consumed at a specific engine power setting and/or flight configuration. • Unusable Fuel is the quantity of fuel that cannot be safely used in flight.
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).
Cirrus Design Section 2 SR20 Limitations Introduction The limitations included in this Section of the Pilot’s Operating Handbook (POH) are approved by the Federal Aviation Administration. This section provides operating limitations, instrument markings and basic placards required by regulation and necessary for the safe operation of the aircraft and its standard systems and equipment.
Section 2 Cirrus Design Limitations SR20 Airspeed Limitations The indicated airspeeds in the following table are based upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
Cirrus Design Section 2 SR20 Limitations Airspeed Indicator Markings The airspeed indicator markings are based upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
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...........
60°. • Note • Because the aircraft has not been certified for spin recovery, the Cirrus Airframe Parachute System (CAPS) must be deployed if the airplane departs controlled flight. Refer to Section 3 – Emergency Procedures, Spins.
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.
Cirrus Design Section 2 SR20 Limitations Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions ALT 1 Annunciator ALT 2 Annunciator — — Circuit Breakers As required. Equipment & Furnishings Emergency Locator Trans- mitter Restraint System One seat belt for each occupant.
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...
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 13772-118 is required. Maximum Occupancy Occupancy of this airplane is limited to four persons (the pilot and three passengers).
Systems and Equipment Limits Cirrus Perspective Integrated Avionics System 1. The Cirrus Perspective by Garmin Integrated Avionics System Quick Reference Guide for the SR20 and SR22, P/N 190-00821- 02 Rev A or later must be immediately available to the pilot during flight.
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).
Section 2 Cirrus Design Limitations SR20 10. 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.
Cirrus Design Section 2 SR20 Limitations Elevator and Rudder, both sides: NO PUSH Left fuselage, on external power supply door: EXTERNAL POWER 28 V DC Doors, above and below latch: PUSH OPEN SR20_FM02_3002 Figure 2-3 Placards (Sheet 2 of 6)
Section 2 Cirrus Design Limitations SR20 Engine control panel: CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT RICH TURN BOOST PUMP ON DURING TAKE OFF, CLIMB, LANDING AND SWITCHING FUEL TANKS. BOOST FUEL PUMP...
MUST BE WORN AT ALL TIMES USE OF THIS DEVICE COULD RESULT IN INJURY OR DEATH MAXIMUM DEMONSTRATED DEPLOYMENT SPEED 133 KIAS CIRRUS AIRFRAME PARACHUTE SYSTEM ACTIVATION PROCEDURE 1. FUEL MIXTURE........CUT-OFF 2. THIS COVER..........REMOVE 3. ACTIVATION HANDLE..PULL STRAIGHT DOWN BOTH HANDS, MAXIMUM FORCE, STEADY PULL DO NOT JERK HANDLE 4.
Section 3 Cirrus Design Emergency Procedures SR20 Low Fuel Quantity ................. 23 Electrical System Emergencies............24 Alternator Failure ................24 High Voltage on Main Bus 1 or Main Bus 2 ........24 Low Voltage on Essential Bus ............25 Low Voltage on Main Bus 1 or Main Bus 2 ........25 Low Alternator 1 Output ..............
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.
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.
121.500 MHz. If the display is available, it will also show it in the “Active” frequency window. The Cirrus Airframe Parachute System (CAPS) should be activated in the event of a life-threatening emergency where CAPS deployment is determined to be safer than continued flight and landing. Refer to Section 10, Safety Information, for CAPS deployment information and landing considerations.
Cirrus Design Section 3 SR20 Emergency Procedures Engine Failures Engine Failure On Takeoff (Low Altitude) If the engine fails immediately after becoming airborne, abort on the runway if possible. If altitude precludes a runway stop but is not sufficient to restart the engine, lower the nose to maintain airspeed and establish a glide attitude.
Section 3 Cirrus Design Emergency Procedures SR20 Engine Failure In Flight If the engine fails at altitude, pitch as necessary to establish best glide speed. While gliding toward a suitable landing area, attempt to identify the cause of the failure and correct it. If altitude or terrain does not permit a safe landing, CAPS deployment may be required.
Cirrus Design Section 3 SR20 Emergency Procedures Airstart Engine Airstart The following procedures address the most common causes for engine loss. Switching tanks and turning the fuel pump on will enhance starting if fuel contamination was the cause of the failure.
Section 3 Cirrus Design Emergency Procedures SR20 Smoke and Fire Engine Fire In Flight If an engine fire occurs during flight, do not attempt to restart the engine. 1. Mixture ................CUTOFF 2. Fuel Pump................OFF 3. Fuel Selector ................OFF 4. Airflow Selector ................OFF 5.
Cirrus Design Section 3 SR20 Emergency Procedures 2. Fire Extinguisher ............ACTIVATE • WARNING • Halon gas used in the fire extinguisher can be toxic, especially in a closed area. After extinguishing fire, ventilate cabin by and unlatching door (if required).
Cirrus Design Section 3 SR20 Emergency Procedures Smoke and Fume Elimination If smoke and/or fumes are detected in the cabin, check the engine parameters for any sign of malfunction. If a fuel leak has occurred, actuation of electrical components may cause a fire. If there is a strong smell of fuel in the cockpit, divert to the nearest suitable landing field.
Section 3 Cirrus Design Emergency Procedures SR20 Emergency Descent Emergency Descent 1. Power Lever ................IDLE 2. Mixture ..............AS REQUIRED • Caution • If significant turbulence is expected do not descend at indicated airspeeds greater than V (163 KIAS).
Cirrus Design Section 3 SR20 Emergency Procedures Forced Landings If all attempts to restart the engine fail and a forced landing is imminent, select a suitable field and prepare for the landing. If flight conditions or terrain does not permit a safe landing, CAPS deployment may be required.
Section 3 Cirrus Design Emergency Procedures SR20 Ditching 1. Radio..........Transmit (121.5 MHz) MAYDAY giving location and intentions 2. Transponder ............SQUAWK 7700 3. CAPS ................ACTIVATE If available, life preservers should be donned and life raft should be prepared for immediate evacuation upon touchdown.
Cirrus Design Section 3 SR20 Emergency Procedures Engine System Emergencies Oil Pressure Out of Range OIL PRESS Warning OIL PRESS Oil pressure below 10 psi or above 100 psi. If low oil pressure is low, the engine has probably lost a significant amount of its oil and engine failure may be imminent.
Section 3 Cirrus Design Emergency Procedures SR20 Oil Temperature High OIL TEMP Warning OIL TEMP Oil temperature is greater than 240°F. 1. Oil Temperature Gage............CHECK If temperature normal: a. If On-Ground......CORRECT PRIOR TO FLIGHT b. If In-Flight..........CONTINUE, MONITOR If temperature high: a.
Cirrus Design Section 3 SR20 Emergency Procedures High Cylinder Head Temperature CHT Caution and Warning CHT Warning: Temperature of one or more cylinder heads has exceeded 460°F. CHT Caution: Temperature of one or more cylinder heads has exceeded 420°F. On-Ground 1.
Section 3 Cirrus Design Emergency Procedures SR20 Engine Partial Power Loss Indications of a partial power loss include fluctuating RPM, reduced or fluctuating manifold pressure, low oil pressure, high oil temperature, and a rough-sounding or rough-running engine. Mild engine roughness in flight may be caused by one or more spark plugs becoming fouled.
Cirrus Design Section 3 SR20 Emergency Procedures 1. Fuel Pump ................. BOOST Selecting BOOST on may clear the problem if vapor in the injection lines is the problem or if the engine-driven fuel pump has partially failed. The electric fuel pump will not provide sufficient fuel pressure to supply the engine if the engine-driven fuel pump completely fails.
Section 3 Cirrus Design Emergency Procedures SR20 Propeller System Emergencies Propeller Governor Failure If the RPM does not respond to power lever movement or overspeeds, the most likely cause is a faulty governor or an oil system malfunction. If moving the power lever is difficult or rough, suspect a power lever linkage failure and perform the Power Lever Linkage Failure checklist.
Section 3 Cirrus Design Emergency Procedures SR20 Electrical System Emergencies Alternator Failure The most likely the cause of the alternator failure is a wiring fault, a malfunctioning alternator, or a malfunctioning control unit. Usually, electrical power malfunctions are accompanied by an excessive rate of charge or a discharge rate shown on the ammeter.
Cirrus Design Section 3 SR20 Emergency Procedures Low Voltage on Essential Bus ESS BUS Warning ESS BUS Illumination of ESS BUS Warning indicates that the voltage output for alternator 1 or alternator 2 is less than 24.5v for more than 20 seconds or greater than 32.0v.
Section 3 Cirrus Design Emergency Procedures SR20 Low Alternator 1 Output ALT 1 Caution ALT 1 Illumination of ALT 1 indicates that the ampere output is less than 2 amps for 20 seconds or more. Attempt to reset alternator. If alternator cannot be reset, reduce loads and use Main Bus or Non-Essential loads only as necessary for flight conditions.
Cirrus Design Section 3 SR20 Emergency Procedures Integrated Avionics System Emergencies • Note • 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.
Section 3 Cirrus Design Emergency Procedures SR20 Emergency Exit Emergency Ground Egress • WARNING • While exiting the airplane, make sure evacuation path is clear of other aircraft, spinning propellers, and other hazards. 1. Engine................SHUTDOWN • Note • If the engine is left running, set the Parking Brake prior to evacuating the airplane.
The aircraft is not approved for spins, and has not been tested or certified for spin recovery characteristics. The only approved and demonstrated method of spin recovery is activation of the Cirrus Airframe Parachute System (See CAPS Deployment, this section).
Section 3 Cirrus Design Emergency Procedures SR20 Inadvertent Spiral Dive During IMC Flight In all cases, if the aircraft enters an unusual attitude from which recovery is not assured, immediately deploy CAPS. Refer to Section 10, Safety Information, for CAPS deployment information.
Cirrus Design Section 3 SR20 Emergency Procedures Other Emergencies Power Lever Linkage Failure If the Power Lever linkage fails in flight, the engine will not respond to power lever control movements. Use power available and flaps as required to safely land the airplane.
Section 3 Cirrus Design Emergency Procedures SR20 Left/Right Brake Over-Temperature Annunciation BRAKE TEMP Warning BRAKE TEMP Brake temperature is greater than 293°F. Refer to Section 10 - Safety Information: Taxiing, Steering, and Braking Practices for additional information 1. Stop aircraft and allow the brakes to cool.
Section 3 SR20 Emergency Procedures CAPS Deployment The Cirrus Airframe Parachute System (CAPS) should be activated in the event of a life-threatening emergency where CAPS deployment is determined to be safer than continued flight and landing. • WARNING • CAPS deployment is expected to result in loss of the airframe...
Section 3 Cirrus Design Emergency Procedures SR20 2. Mixture (If time and altitude permit) ......... CUTOFF Generally, a distressed airplane will be safer for its occupants if the engine is not running. 3. Activation Handle Cover..........REMOVE The cover has a handle located at the forward edge. Pull cover down to expose activation T-handle.
Cirrus Design Section 3 SR20 Emergency Procedures 13. Assume emergency landing body position. The emergency landing body position is assumed by placing both hands on the lap, clasping one wrist with the opposite hand, and holding the upper torso erect and against the seat backs.
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.
Section 3A Cirrus Design Abnormal Procedures SR20 Flight Environment Inadvertent Icing Encounter Flight into known icing conditions is prohibited. However, if icing is inadvertently encountered: 1. Pitot Heat .................. ON 2. Exit icing conditions. Turn back or change altitude. 3. Cabin Heat ..............MAXIMUM 4.
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.
Section 3A Cirrus Design Abnormal Procedures SR20 Engine System Low Idle Oil Pressure OIL PRESS Caution OIL PRESS Oil pressure between 10 psi and 30 psi at or above 1000 RPM • Note • This message will appear prior to engine start and should clear after engine start.
Cirrus Design Section 3A SR20 Abnormal Procedures Fuel System Left Fuel Tank Quantity L FUEL QTY Advisory L FUEL QTY Left fuel quantity is less than or equal to 7 gallons. 1. Left Fuel Quantity Gage............. CHECK If left fuel quantity indicates less than or equal to 7 gallons: a.
Section 3A Cirrus Design Abnormal Procedures SR20 Fuel System (Cont) Fuel Filter in Bypass Mode FUEL FILTER Advisory FUEL FILTER The fuel filter is in bypass mode. The fuel filter element must be replaced. 1. If In-Flight ........LAND AS SOON AS PRACTICAL 2.
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Cirrus Design Section 3A SR20 Abnormal Procedures AVIONICS STDBY ALT1 ALT2 ATTD #2 ENGINE MFD #2 INSTR STALL CABIN CAMERA WARNING LIGHTS 12V DC ROLL FUEL QTY OUTLET TRIM CABIN AIR PITCH MFD #1 AP SERVOS CONTROL TRIM CABIN ESSENTIAL...
Section 3A Cirrus Design Abnormal Procedures SR20 Integrated Avionics System Avionics Switch Off AVIONICS OFF Caution AVIONICS OFF The AVIONICS master switch is off. 1. AVIONICS Switch..........ON, AS REQUIRED Flight Displays Too Dim • Note • Photocell backlighting for the flight displays, bezel, audio panel, and FMS keyboard is manually controlled through the dimmer control on the instrument panel bolster.
Cirrus Design Section 3A SR20 Abnormal Procedures MFD Cooling Fan Failure MFD FAN FAIL Advisory MFD FAN FAIL The cooling fan for the MFD is inoperative. 1. AVIONICS FAN 1 Circuit Breaker ........CYCLE If annunciation does not extinguish: a. High cabin temperatures ..LAND AS SOON AS PRACTICAL b.
Section 3A Cirrus Design Abnormal Procedures SR20 Pitot Static System Pitot Static Malfunction Static Source Blocked If erroneous readings of the static source instruments (airspeed, altimeter and vertical speed) are suspected, the alternate static source valve, on side of console near pilot’s right ankle, should be opened to supply static pressure from the cabin to these instruments.
Section 3A Cirrus Design Abnormal Procedures SR20 Flight Control System Electric Trim/Autopilot Failure Any failure or malfunction of the electric trim or autopilot can be over- ridden by use of the control yoke. If runaway trim is the problem, de- energize the circuit by pulling the appropriate circuit breakers and land as soon as conditions permit.
Cirrus Design Section 3A SR20 Abnormal Procedures Landing Gear System Brake Failure During Taxi Ground steering is accomplished by differential braking. However, increasing power may allow some rudder control due to increased groundspeed and airflow over the rudder. 1. Engine Power............AS REQUIRED •...
Section 3A Cirrus Design Abnormal Procedures SR20 Other Conditions Aborted Takeoff 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. 1. Power Lever ................IDLE 2.
Cirrus Design Section 3A SR20 Abnormal Procedures Parking Brake Engaged Annunciation PARK BRAKE Caution PARK BRAKE Parking brake is set. 1. Parking Brake ..............RELEASE 2. Monitor CAS for BRAKE TEMP Caution. Stop aircraft and allow the brakes to cool if necessary.
Cirrus Design Section 4 SR20 Normal Procedures Introduction This section provides amplified procedures for normal operation. Normal procedures associated with optional systems can be found in Section 9. Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3050 lb.
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;...
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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.
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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.
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Cirrus Design Section 4 SR20 Normal Procedures e. Tire ..........Condition, Inflation, and Wear • Caution • Clean and inspect temperature indicator installed to piston housing. If indicator center is black, the brake assembly has been overheated. The brake linings must be inspected and O- rings replaced.
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Section 4 Cirrus Design Normal Procedures SR20 d. External Power .............Door Secure e. Exhaust Pipe(s) ....Condition, Security, and Clearance 11. Left Main Gear and Forward Wing a. Wheel fairings ....... Security, Accumulation of Debris b. Tire ..........Condition, Inflation, and Wear •...
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.
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.
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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.
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.
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.
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Section 4 Cirrus Design Normal Procedures SR20 16. Pitot Heat ............... AS REQUIRED • Note • Pitot Heat should be turned ON for flight into IMC, flight into visible moisture, or whenever ambient temperatures are 41° F (5° C) or less.
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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.
Section 4 Cirrus Design Normal Procedures SR20 Normal Takeoff 1. Brakes ........RELEASE (Steer with Rudder Only) 2. Power Lever ............FULL FORWARD 3. Engine Parameters ............CHECK 4. Elevator Control ......ROTATE Smoothly at 65-70 KIAS 5. At 85 KIAS, Flaps............... UP Short Field Takeoff 1.
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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.
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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.
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.
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.
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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.
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.
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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.
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.
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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.
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.
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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 ........
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Section 5 Cirrus Design Performance Data SR20 Intentionally Left Blank P/N 11934-004 Original Issue...
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 &...
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...
Section 5 Cirrus Design Performance Data SR20 Altitude Correction - Normal Static Source 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.
Cirrus Design Section 5 SR20 Performance Data Altitude Correction - Alternate Static Source 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.
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.
Cirrus Design Section 5 SR20 Performance Data Outside Air Temperature for ISA Condition Press ISA-40°C ISA-20°C ISA+10°C ISA+20°C Feet °C °F °C °F °C °F °C °F °C °F 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000...
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.
Section 5 Cirrus Design Performance Data SR20 Takeoff Distance Conditions: • Winds........................ Zero • Runway..................Dry, Level, Paved • Flaps......................... 50% • Power....................Full Throttle • Mixture.................... Set per Placard • Note • The following factors are to be applied to the computed takeoff distance for the noted condition: •...
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.
Section 5 Cirrus Design Performance Data SR20 Takeoff Rate of Climb Conditions: • Power....................Full Throttle • Mixture.................... Set per Placard • Flaps......................... 50% • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude for unit time expended expressed in Feet per Minute.
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.
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.
Cirrus Design Section 5 SR20 Performance Data Cruise Performance Conditions: • Cruise Weight..................... 2600 LB • Winds ....................... Zero • Note • Subtract 10 KTAS if nose wheel pant and fairing removed. Lower KTAS by 10% if nose and main wheel pants & fairings are removed.
Section 5 Cirrus Design Performance Data SR20 Cruise Performance (Continued) 8000 Feet Pressure Altitude ISA - 30° C (-31° C) ISA (-1° C) ISA + 30° C (29° C) KTAS KTAS KTAS 2700 22.2 12.9 11.6 11.4 2500 22.2 11.4 11.0...
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.
Section 5 Cirrus Design Performance Data SR20 Range / Endurance Profile (Continued) 65% POWER Mixture = Best Power Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 46.3 10.5 13.0 2000 45.7 10.5...
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.
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.
Cirrus Design Section 5 SR20 Performance Data Landing Distance Conditions: • Winds ....................... Zero • Runway ..................Dry, Level, Paved • Flaps.......................100% • Power ..................3° Power Approach to 50 FT obstacle, then reduce power passing the estimated 50 foot point and smoothly continue power reduction to reach idle just prior to touchdown.
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Section 5 Cirrus Design Performance Data SR20 Landing Distance WEIGHT = 3050 LB Headwind: Subtract 10% per each Speed over 50 Ft Obstacle = 77 KIAS 13 knots headwind. Flaps - 100% · Idle · Dry, Level Paved Surface Tailwind: Add 10% for each 2 knots tailwind up to 10 knots.
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Cirrus Design Section 6 SR20 Weight and Balance Data Section 6 Weight and Balance Data Table of Contents Introduction ..................3 Airplane Weighing Form ..............4 Airplane Weighing Procedures ............5 Loading Instructions ................8 Weight and Balance Loading Form............ 9 Loading Data..................
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Cirrus Design Section 6 SR20 Weight and Balance Data Introduction This section describes the procedure for establishing the basic empty weight and moment of the airplane. Sample forms are provided for reference. Procedures for calculating the weight and moment for various operations are also provided.
Section 6 Cirrus Design Weight and Balance Data SR20 Airplane Weighing Form REF DATUM FS 0.0 FS 100.0 FS 142.5 WL 100.0 A = x + 100 B = A - y y = ____________ Measured x = ____________ Measured...
Cirrus Design Section 6 SR20 Weight and Balance Data Airplane Weighing Procedures A basic empty weight and center of gravity were established for this airplane when the airplane was weighed just prior to initial delivery. However, major modifications, loss of records, addition or relocation of...
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Section 6 Cirrus Design Weight and Balance Data SR20 side of the firewall (FS 100). Add 100 to this measurement to obtain left and right weighing point arm (dimension ‘A’). Typically, dimension ‘A’ will be in the neighborhood of 157.5.
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Cirrus Design Section 6 SR20 Weight and Balance Data Airplane Leveling Spirit Level LONGITUDINAL LEVELING Spirit Level Straight Edge Straight Edge Straight Edge Spacer Spacer Block Block Door Sill Door Sill LATERAL LEVELING SR22_FM06_1440A Figure 6-2 P/N 11934-004 Original Issue...
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.
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.
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...
Cirrus Design Section 6 SR20 Weight and Balance Data Moment Limits Use the following chart or table to determine if the weight and moment from the completed Weight and Balance Loading Form (Figure 6-3) are within limits. Moment/1000 Moment/1000 Weight...
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.
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 11934-004 6-13 Original Issue...
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Cirrus Design Section 7 SR20 Airplane and Systems Description Section 7 Airplane and Systems Description Table of Contents Introduction ..................5 Airframe ..................... 6 Fuselage ..................6 Wings....................6 Empennage ..................7 Flight Controls ..................8 Elevator System................8 Aileron System................10 Rudder System ................
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.
Section 7 Cirrus Design Airplane and Systems Description SR20 Airframe Fuselage The aircraft’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.
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.
Section 7 Cirrus Design Airplane and Systems Description SR20 Flight Controls The aircraft 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.
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Cirrus Design Section 7 SR20 Airplane and Systems Description Figure 7-1 Elevator System P/N 11934-004 Original Issue...
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.
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Cirrus Design Section 7 SR20 Airplane and Systems Description SR20_FM07_1462 Figure 7-2 Aileron System P/N 11934-004 7-11 Original Issue...
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.
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Cirrus Design Section 7 SR20 Airplane and Systems Description SR20_FM07_1463 Figure 7-3 Rudder System P/N 11934-004 7-13 Original Issue...
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.
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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.
Section 7 Cirrus Design Airplane and Systems Description SR20 Flight Instruments Flight instruments and annunciations are displayed on the Primary Flight Display (PFD) located directed in front of the pilot. The PFD presents the primary flight instruments arranged in the conventional basic “T”...
Section 7 Cirrus Design Airplane and Systems Description SR20 Attitude Indicator The primary attitude indicator is show on the upper center of the PFD and displays pitch, roll, and slip/skid information provided by the Attitude and Heading Reference System (AHRS).
Cirrus Design Section 7 SR20 Airplane and Systems Description Airspeed Indicator Primary airspeed data is provided by the Air Data Computer and is shown as a vertical tape along the upper left side of the PFD. The airspeed scale is graduated with major tick marks at intervals of 10 knots and minor tick marks at intervals of 5 knots.
Section 7 Cirrus Design Airplane and Systems Description SR20 Altimeter Primary altitude data is provided by the Air Data Computer and is shown as a vertical tape along the upper right side of the PFD. The altimeter scale is graduated with major tick marks at intervals of 100 feet and minor tick marks at intervals of 20 feet.
Cirrus Design Section 7 SR20 Airplane and Systems Description The HSI presents heading, turn rate, course deviation, bearing, and navigation source information in a 360° compass-rose format. The HSI contains a Course Deviation Indicator (CDI) with a course pointer arrow, a To/From arrow, a sliding deviation bar, and scale. The course...
Section 7 Cirrus Design Airplane and Systems Description SR20 Wing Flaps The electrically controlled, single-slotted flaps provide low-speed lift enhancement. Each flap is manufactured of aluminium and connected to the wing structure at three hinge points. Rub strips are installed on the top leading edge of each flap to prevent contact between the flap and wing flap cove.
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Cirrus Design Section 7 SR20 Airplane and Systems Description SR20_FM07_1460 Figure 7-6 Wing Flaps P/N 11934-004 7-23 Original Issue...
Section 7 Cirrus Design Airplane and Systems Description SR20 Landing Gear Main Gear The main landing gear are bolted to composite wing structure between the wing spar and shear web. The landing gear struts are constructed of composite material for fatigue resistance. The composite construction is both rugged and maintenance free.
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Cirrus Design Section 7 SR20 Airplane and Systems Description each brake assembly which transmit signals via the Engine Airframe Unit to the Engine Indicating System for brake temperature caution/ warning annunciation. Should any of these symptoms occur, immediate maintenance is required.
Section 7 Cirrus Design Airplane and Systems Description SR20 Baggage Compartment The baggage compartment door, located on the left side of the fuselage aft of the wing, allows entry to the baggage compartment. The baggage door is hinged on the forward edge and latched on the rear edge.
Cirrus Design Section 7 SR20 Airplane and Systems Description Seats The seating arrangement consists of two individually adjustable seats for the pilot and front seat passenger and two individual seats with fold down seat backs for the rear seat passengers.The front seats are adjustable fore and aft and the seat backs can be reclined for passenger comfort or folded forward for rear seat access.
Section 7 Cirrus Design Airplane and Systems Description SR20 Seat Belt and Shoulder Harness Integrated seat belt and shoulder harness assemblies with inertia reels are provided for the pilot and each passenger. The rear seat belts are attached to fittings on the floorboard and the forward seat belts are attached to the seat frame.
Cirrus Design Section 7 SR20 Airplane and Systems Description 4. Restraint harnesses should fit snug against the shoulder with the lap buckle centered and tightened around the hips. To release the restraints: 1. Grasp the top of the buckle opposite the link and pull outward. The link will slip free of buckle.
Section 7 Cirrus Design Airplane and Systems Description SR20 Engine The aircraft 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).
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Cirrus Design Section 7 SR20 Airplane and Systems Description Mixture Control The mixture control lever, labeled RICH-MIXTURE-CUTOFF, on the console adjusts the proportion of fuel to air for combustion. The Mixture Control Lever is mechanically linked to the mixture control valve in the engine-driven fuel pump.
Section 7 Cirrus Design Airplane and Systems Description SR20 Engine Indicating Engine information is displayed as analog-style gages, bar graphs, and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), all essential engine information is displayed along the LH edge of the display.
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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.
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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.
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Cirrus Design Section 7 SR20 Airplane and Systems Description Oil Temperature Oil temperature is shown in the upper right corner of the ENGINE page, opposite the oil pressure scale, as both a simulated temperature gage and as a digital value. The gage pointer sweeps a scale range from 75°F to 250°F in 50°F increments.
Section 7 Cirrus Design Airplane and Systems Description SR20 Engine Lubrication System The engine is provided with a wet-sump, high-pressure oil system for engine lubrication and cooling. Oil for engine lubrication is drawn from an eight-quart capacity sump through an oil suction strainer screen and directed to the engine-mounted oil cooler.
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.
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.
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.
Section 7 Cirrus Design Airplane and Systems Description SR20 contamination and grade. The fuel must be sampled prior to each flight. A sampler cup is provided to drain a small amount of fuel from the wing tank drains, the collector tank drains, and the gascolator drain.
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Cirrus Design Section 7 SR20 Airplane and Systems Description ANNUNCIATOR FUEL FUEL QUANTITY VENT VENT FILLER FILLER INDICATOR L. WING TANK R. WING TANK L. WING R. WING COLLECTOR COLLECTOR CHECK CHECK VALVE VALVE SELECTOR VALVE FLAPPER FLAPPER VALVE VALVE...
Section 7 Cirrus Design Airplane and Systems Description SR20 Fuel Indicating Fuel system information is displayed as analog-style gages and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), fuel flow is displayed along the LH edge of the display.
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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.
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Section 7 Cirrus Design Airplane and Systems Description SR20 Each indicator also provides an output signal to the Engine Airframe Unit that is processed and transmitted to the CAS window for display when the fuel quantity goes below approximately 7 gallons indicated.
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Cirrus Design Section 7 SR20 Airplane and Systems Description Fuel Totalizer and Calculated Information Fuel totalizer calculations are located in the lower right section of the ENGINE page and are separate and independent of the fuel quantity gage and float sensor system. The fuel totalizer monitors fuel flow and calculates fuel-to-destination, fuel used, fuel remaining, time remaining, fuel range, and nautical miles per gallon.
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.
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Cirrus Design Section 7 SR20 Airplane and Systems Description LANDING 100A ALT 1 LIGHT ALT 1 7.5A VOLT REG RELAY LANDING LIGHT SWITCH EXTERNAL ALT 1 POWER RELAY SWITCH EXTERNAL POWER 125A BAT 1 BAT 1 BAT 1 RELAY SWITCH...
Section 7 Cirrus Design Airplane and Systems Description SR20 Power Distribution Power is supplied to the airplane circuits through three distribution buses contained in the MCU; Main Distribution Bus 1, Main Distribution Bus 2, and the Essential Distribution Bus. The three distribution buses power the associated buses on the circuit breaker panel.
Cirrus Design Section 7 SR20 Airplane and Systems Description Main Distribution Bus 2 The output from ALT 2 is connected to the Main Distribution Bus 2 in the MCU through an 80-amp fuse. Main Distribution Bus 2 powers three circuit breaker buses through 30-amp fuses located in the MCU;...
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Section 7 Cirrus Design Airplane and Systems Description SR20 Main Distribution Bus 1 or Main Distribution Bus 2 in the MCU. In the case of both alternators failing, BAT 1 is connected directly to the Essential Distribution Bus in the MCU and will power ESS BUS 1 and ESS BUS 2.
Cirrus Design Section 7 SR20 Airplane and Systems Description Electrical System Control The rocker type electrical system MASTER switches are ‘on’ in the up position and ‘off’ in the down position. The switches, labeled BAT 2, BAT 1, ALT 1, ALT 2 are located in the bolster switch panel immediately below the instrument panel.
Section 7 Cirrus Design Airplane and Systems Description SR20 AVIONICS Master Switch A rocker switch, labeled AVIONICS, controls electrical power from the circuit breaker panel (MAIN BUS 1) to the Avionics Bus. The switch is located next to the ALT and BAT Master switches. Typically, the switch is used to energize or de-energize all non-essential avionics on the AVIONICS bus simultaneously.
Cirrus Design Section 7 SR20 Airplane and Systems Description Electrical Indicating Electrical system information is displayed as bar graphs and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), Battery 1 ampere output and Essential Bus voltage output are displayed along the LH edge of the display.
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Section 7 Cirrus Design Airplane and Systems Description SR20 Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Electrical System Indication 8 9 10 Electrical and Lighting Controls LEGEND 1. Essential & Main Bus Voltage 7. Avionics 8. Navigation 2. Alternator & Battery Current 9.
Cirrus Design Section 7 SR20 Airplane and Systems Description Lighting Systems Exterior Lighting The airplane is equipped with wing tip navigation lights with integral anti-collision strobe lights and recognition Lights. The landing light is located in the lower cowl. Navigation Lights The airplane is equipped with standard wing tip navigation lights.
Section 7 Cirrus Design Airplane and Systems Description SR20 Interior Lighting Interior lighting for the airplane consists of separately controlled incandescent overhead lights for general cabin lighting, individual lights for the pilots and passengers, and dimmable panel floodlights. The flight instrumentation and avionics equipment lights are dimmable.
Cirrus Design Section 7 SR20 Airplane and Systems Description Environmental System 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. The environmental system...
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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...
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Cirrus Design Section 7 SR20 Airplane and Systems Description Distribution From the mixing chamber, the air is distributed by either ram air or by optional blower fan to the distribution manifold mounted to the center, aft side of the firewall. The distribution manifold uses butterfly valves to control airflow to the floor and defrost vents.
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Section 7 Cirrus Design Airplane and Systems Description SR20 Pressing the Panel-Foot selector button opens the cabin floor butterfly valve allowing airflow to the rear seat foot warmer diffusers and the front seat outlets mounted to the underside of each kickplate.
Cirrus Design Section 7 SR20 Airplane and Systems Description Stall Warning System The airplane is equipped with an electro-pneumatic stall warning system to provide audible warning of an approach to aerodynamic stall. The system consists of an inlet in the leading edge of the right wing, a pressure switch and associated plumbing.
Section 7 Cirrus Design Airplane and Systems Description SR20 Pitot-Static System The Pitot-Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage. The Pitot heat is pilot controlled through a panel-mounted switch. An internally mounted alternate static pressure source provides backup static pressure should that the primary static source becomes blocked.
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Cirrus Design Section 7 SR20 Airplane and Systems Description AIR DATA COMPUTER PFD Air Data AIRSPEED INDICATOR ALTIMETER ALTERNATE PITOT-STATIC STATIC WATER TRAPS AIR SOURCE PITOT MAST STATIC HEATER BUTTONS Annunciation PITOT HEAT CURRENT SENSOR LOGIC PITOT 7.5A HEAT PITOT HEAT SW...
Section 7 Cirrus Design Airplane and Systems Description SR20 Avionics Perspective Integrated Avionics System The Perspective Integrated Avionics System provides advanced cockpit functionality and improved situational awareness through the use of fully integrated flight, engine, communication, navigation and monitoring equipment. The system consists of the following components: •...
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Cirrus Design Section 7 SR20 Airplane and Systems Description XM RADIO RECEIVER (optional) SATELLITE DATA LINK RECEIVER (optional) FMS KEYBOARD MAG 2 MAG 1 AHRS 1 AUTOPILOT MODE CONTROLLER (optional) AHRS 2 (optional) AIR DATA COMPUTER INTEGRATED INTEGRATED AVIONICS UNIT 1...
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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.
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Cirrus Design Section 7 SR20 Airplane and Systems Description MAIN BUS 3 and the 5-amp MFD PWR 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.
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Section 7 Cirrus Design Airplane and Systems Description SR20 Figure 7-15 Perspective Integrated Avionics System (Sheet 1 of 2) 7-68 P/N 11934-004 Original Issue...
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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...
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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...
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Cirrus Design Section 7 SR20 Airplane and Systems Description GMA 347 Audio Panel with Integrated Marker Beacon Receiver The Audio Panel, installed on the center console below the Flight Management System Keyboard, integrates NAV/COM digital audio, intercom and marker beacon controls. The VHF communications...
Section 7 Cirrus Design Airplane and Systems Description SR20 Optional Avionics GFC 700 3-Axis Autopilot and GMC 705 Autopilot Controller Refer to Section 9, Supplements for GFC 700 3-Axis Autopilot operating information. GTX 33 Mode S Transponder The GTX 33 Mode S solid-state transponder communicates with the primary Integrated Avionics Unit and provides Modes A, C, and S interrogation/reply capabilities.
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Cirrus Design Section 7 SR20 Airplane and Systems Description information is displayed on the MFD and indicates the relative range, bearing, and altitude of intruder aircraft. The Traffic Advisory System consists of a Transmitter Receiver Computer installed under the copilot’s seat just forward of the spar tunnel and a directional antenna installed on the airplane exterior.
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Section 7 Cirrus Design Airplane and Systems Description SR20 information. 28 VDC for ADF System operation is supplied through the 3-amp 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 ADF System Pilot’s Guide for a detailed discussion of the...
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Cirrus Design Section 7 SR20 Airplane and Systems Description • Flight path marker, • Terrain warning system, • Field of view depiction on the MFD Navigation Page. Refer to the Perspective Integrated Avionics System Pilot’s Guide for a complete description of the system, its operating modes, and...
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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 8. GFC 705 Mode Controller (opt) 9.
Cirrus Design Section 7 SR20 Airplane and Systems Description Avionics Support Equipment Antennas Two rod-type COM antennas are mounted to the aircraft’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.
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Section 7 Cirrus Design Airplane and Systems Description SR20 Headset and Microphone Installation The airplane is equipped with provisions for four noise-canceling headsets with integrated microphones. forward microphone-headsets use remote Push-To-Talk (PTT) switches located on the top of the associated control yoke grip. The rear headsets do not have COM transmit capabilities and do not require PTT switches.
Cirrus Design Section 7 SR20 Airplane and Systems Description Cabin Features Emergency Locator Transmitter The airplane is equipped with a self-contained emergency locator transmitter (ELT). The transmitter and antenna are installed immediately behind the aft cabin bulkhead, slightly to the right of the airplane centerline.
Section 7 Cirrus Design Airplane and Systems Description SR20 b. Disconnect fixed antenna lead from front of unit. c. Disconnect lead from remote switch and indicator unit. d. Loosen attach straps and remove transmitter unit and portable antenna. e. Attach portable antenna to antenna jack on front of unit.
Cirrus Design Section 7 SR20 Airplane and Systems Description Hour Meters The airplane is equipped with two hour meters located inside the armrest storage compartment between the pilot and copilot seats. The #1 hour meter, labeled HOBBS begins recording when the BAT 1 switch is ON and either the ALT 1 or ALT 2 switch is ON.
Airplane and Systems Description SR20 Cirrus Airplane Parachute System The aircraft is equipped with a Cirrus Airplane Parachute System (CAPS) designed to bring the aircraft and its occupants to the ground in the event of a life-threatening emergency. The system is intended to...
Cirrus Design Section 7 SR20 Airplane and Systems Description rate at which the parachute inflates. As the slider moves down the suspension lines the canopy inflates. A three-point harness connects the airplane fuselage structure to the parachute. The aft harness strap is stowed in the parachute canister and attached to the structure at the aft baggage compartment bulkhead.
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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;...
Cirrus Design Section 7 SR20 Airplane and Systems Description Deployment Characteristics When the rocket launches, the parachute assembly is extracted outward due to rocket thrust and rearward due to relative wind. In approximately two seconds the parachute will begin to inflate.
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Section 7 Cirrus Design Airplane and Systems Description SR20 Intentionally Left Blank 7-86 P/N 11934-004 Original Issue...
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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 ..................
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Section 8 Cirrus Design Handling, Servicing, & Maintenance SR20 Intentionally Left Blank P/N 11934-004 Original Issue...
Operator’s Publications The FAA Approved Airplane Flight Manual and Pilot’s Operating Handbook (POH) is provided at delivery. Additional or replacement copies may be obtained from Cirrus Design by contacting the Customer Service Department. Service Publications The following service publications are available for purchase from Cirrus Design: •...
Service Bulletin. Give careful attention to the Service Advisory Notice information. Ordering Publications Aircraft publications subscription service may be obtained by contacting Customer Service at Cirrus Design as follows: Cirrus Design Corporation Customer Service 4515 Taylor Circle Duluth, MN 55811...
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.
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.
Progressive Inspection Program in accordance with the Federal Aviation Regulation Part 91.409. The Cirrus Design Progressive Inspection Program provides for the complete inspection of the airplane utilizing a five-phase cyclic inspection program. A total of eight inspections are accomplished over the course of 400 flight hours, with an inspection occurring every 50 flight hours.
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.
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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.
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.
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.
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.
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.
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.
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Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance Raise Airplane • Caution • Do not jack the aircraft outside or in open hangar with winds in excess of 10 mph. The empty CG is forward of the wing jacking points. To prevent...
Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Servicing Landing Gear Servicing The main landing gear wheel assemblies use 15 x 6.00 x 6, six-ply rating tires and tubes. The nose wheel assembly uses a 5.00 x 5 four- ply rating, type III tire and tube.
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Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance • Leaking brake fluid at the caliper. This can be observed by checking for evidence of fluid on the ground or deposited on the underside of the wheel fairing. Wipe the underside of the fairing with a clean, white cloth and inspect for red colored fluid residue.
Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Tire Inflation For maximum service from the tires, keep them inflated to the proper pressure. When checking tire pressure, examine the tires for wear, cuts, nicks, bruises and excessive wear. To inflate tires: 1.
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Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance sooner under unfavorable operating conditions. The following grades are recommended for the specified temperatures at sea level (SL): Ambient Air Temperature (SL) Single Viscosity Multi-Viscosity All Temperatures -— 20W-60 20W-50 15W-50 Below 40°F...
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Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Product Supplier Aeroshell (R) W Shell Australia Aeroshell Oil W Shell Canada Ltd. Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50 Aeroshell Oil W Shell Oil Company Aeroshell Oil W 15W-50...
Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance Fuel System Servicing Fuel Filtration Screen/Element 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.
Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 • Note • Do not permit fuel nozzle to come in contact with bottom of fuel tanks. Keep fuel tanks at least half full at all times to minimize condensation and moisture accumulation in tanks. In...
Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance The gascolator incorporates a filter bypass that activates a red, pop-up tab when pressure drop across the gascolator reaches 0.8 ± 0.2 PSI. The filter is bypassed when the pressure drop reaches 1.20 ± 0.2 PSI.
Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Battery Service The aircraft is delivered with a maintenance free, rechargeable, sealed, lead acid primary battery. Battery #1 is mounted to the forward right side of the firewall and access is gained by removing the upper cowl.
Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance Cleaning and Care Cleaning Exterior Surfaces • Note • Prior to cleaning, place the airplane in a shaded area to allow the surfaces to cool. The airplane should be washed with a mild soap and water. Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause corrosion of metal.
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Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Cleaning Product Cleaning Application Supplier Pure Carnauba Wax Fuselage Exterior Any Source Mothers California Gold Fuselage Exterior Wal-Mart Stores Pure Carnauba Wax RejeX Fuselage Exterior Corrosion Technologies WX/Block System Fuselage Exterior...
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Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance Windscreen and Windows Before cleaning an acrylic window, rinse away all dirt particles before applying cloth or chamois. Never rub dry acrylic. Dull or scratched window coverings may be polished using a special acrylic polishing paste.
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Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Do not use abrasive cleansers or cleaning pads on the germanium window. Abrasive cleaning can damage the sensor window coating. Do not use any cleansers containing ammonia. Ammonia will remove the sensor window coating.
Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance 3. Allow the solvent to remain on the gear from five to ten minutes. Then rinse the gear with additional solvent and allow to dry. 4. Remove the cover from the wheel and remove the catch pan.
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Section 8 Cirrus Design Handling, Servicing, and Maintenance SR20 Cleaning Product Cleaning Application Supplier Prist Interior Windscreen and Prist Aerospace Windows Optimax Display Screens PhotoDon Mild Dishwasher Soap Cabin Interior Any Source (abrasive free) Leather Care Kit Leather Upholstery Cirrus Design...
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Cirrus Design Section 8 SR20 Handling, Servicing, and Maintenance Instrument Panel and Electronic Display Screens The instrument panel, control knobs, and plastic trim need only to be wiped clean with a soft damp cloth. The multifunction display, primary flight display, and other electronic display screens should be cleaned with Optimax - LCD Screen Cleaning Solution as follows: •...
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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.
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Cirrus Design Supplements produced for this airplane. The Log of Supplements page can be utilized as a “Table of Contents” for this section. In the event the airplane is modified at a non Cirrus Design facility through an STC or other approval method, it is the...
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Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank P/N 11934-004 Original Issue...
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Cirrus Design Section 9 SR20 Log of Supplements Section 9 Log of Supplements Part Number Title Date ___ 11934-S17 SR20 Airplanes Registered in Canada 10-10-01 ___ 11934-S25 R1 Winterization Kit 12-07-04 ___ 11934-S29 SR20 Airplanes Registered in the European Union...
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This Log of Supplements shows all Cirrus Design Supplements available for the aircraft at the corresponding date of the revision level shown in the lower left corner. A mark (x) in the Part Number column indicates that the supplement is installed in the POH.
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Supplement SR20 Airplanes Registered in the European Union 1. This supplement is required for operation of Cirrus Design SR20 airplane serial numbers 1005 and subsequent when registered in the European Union. This supplement must be attached to the applicable SR20 EASA/FAA-approved Airplane Flight Manual.
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Section 9 Cirrus Design Supplements SR20 Section 1 - General No Change. Section 2 - Limitations Two-blade propellers are not EASA approved for use on this airplane. Ignore all references to the two-blade propeller in this Pilot’s Operating Handbook. Amend “Propeller” limitation to read as follows: Hartzell Propeller Type..............
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Cirrus Design Section 9 SR20 Supplements Section 8 - Handling, Servicing & Maintenance No Change. Section 9 - Supplements No Change. Section 10 - Safety Information No Change. P/N 11934-S29 3 of 4 Original: 05-27-04...
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Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 4 of 4 P/N 11934-S29 Original: 05-27-04...
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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.
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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.
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Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations No Change. Section 3 - Emergency Procedures Forced Landing Before performing a forced landing activate the ELT transmitter manually by turning the ELT remote switch to the 'ON'-position. Immediately after a forced landing, perform the following procedure: •...
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Section 9 Cirrus Design Supplements SR20 Portable Use of ELT The ELT transmitter can be removed from the airplane and used as a personal locating device if it is necessary to leave the airplane after an accident. Access the unit as described below and set the ELT transmitter control switch to the 'ON'-position.
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Cirrus Design Section 9 SR20 Supplements Section 7 - Systems Description This airplane is equipped with a self-contained Artex ME406 406 MHz ELT System. The transmitter unit is automatically activated upon sensing a change of velocity along its longitudinal axis exceeding 4 to 5 feet per second.
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Section 9 Cirrus Design Supplements SR20 Section 8 - Handling, Servicing & Maintenance ELT and RCPI batteries must be inspected in accordance with the Airplane Maintenances Manual, 5-20 - Scheduled Maintenance Checks. The ELT and RCPI batteries must be replaced upon reaching the date...
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Cirrus Design Section 9 SR20 Supplements system or provide the same level of confidence as does an AM radio. 1. Tune aircraft receiver to 121.5 MHz. 2. Turn the ELT aircraft panel switch "ON" for about 1 second, then back to the "ARM" position. The receiver should transmit about 3 audio sweeps.
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Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 8 of 8 P/N 11934-S36 Revision 01: 12-18-08...
Cirrus Design Section 9 SR20 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement Garmin GFC 700 Automatic Flight Control System When the GFC 700 Automatic Flight Control System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the basic Pilot’s Operating...
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Section 1 - General The aircraft is equipped with a Garmin GFC 700 digital Automatic Flight 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 Automatic Flight Control System and operating procedures.
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Cirrus Design Section 9 SR20 Supplements 7. The autopilot and flight director will not command pitch or roll beyond the Command Limits. Axis Autopilot Command Limit FD Pitch Command Limits +20°, -15° FD Roll Command Limits ± 25° 8. Use of VNAV is not supported during an approach with a teardrop course reversal.
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Section 9 Cirrus Design Supplements SR20 Section 3A - Abnormal Procedures Autopilot Miscompare AP MISCOMP Caution AP MISCOMP Autopilot miscompare, autopilot is not available. 1. Continue flight without autopilot. 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.
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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 Automatic Flight Control System.
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Section 9 Cirrus Design Supplements SR20 Before Taxiing 1. Manual Electric Trim...............TEST Press the AP DISC button down and hold while commanding trim. Trim should not operate either nose up or nose down. 2. Autopilot ..........ENGAGE (press AP button) 3. Autopilot Override ..............TEST Move flight controls fore, aft, left and right to verify that the autopilot can be overpowered.
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Cirrus Design Section 9 SR20 Supplements 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...
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Section 9 Cirrus Design Supplements SR20 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...
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Cirrus Design Section 9 SR20 Supplements 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.
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Section 9 Cirrus Design Supplements SR20 view, will deactivate the Flight Director and remove the command bars unless the autopilot is engaged. If the autopilot is engaged, the FD button is deactivated. UP/DN - Pitch Wheel The Pitch UP/DN Wheel on the controller is used to change the flight director pitch mode reference value.
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Cirrus Design Section 9 SR20 Supplements 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.
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Section 9 Cirrus Design Supplements SR20 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.
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Cirrus Design Section 9 SR20 Supplements 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.
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Section 9 Cirrus Design Supplements SR20 Autopilot Disconnect Switch The yoke mounted Autopilot Disconnect Switch disengages the autopilot and may also be used to mute the aural alert associated with an AP disconnect. Take Off / Go Around Button The remote TO/GA switch, located on the left side of the power lever, disengages the autopilot and selects the Takeoff or Go Around mode on the Flight Director.
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SR20 Supplements Annunciation System • Note • Refer to the Cirrus Perspective Pilot’s Guide for a detailed description of the annunciator system and all warnings, cautions and advisories. Crew Alerting System AFCS alerts are displayed in the Crew Alerting System (CAS) window located to the right of the altimeter and VSI.
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Section 9 Cirrus Design Supplements SR20 Section 8 – Handling, Service, & Maintenance No Change. Section 10 – Safety Information No Change. 16 of 16 P/N 11934-S41 Revision 01: 08-26-09...
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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.
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System that performs the functions of a Class C Terrain Awareness and Warning System (TAWS) in accordance with TSO C151b. Refer to the Cirrus Perspective Integrated Flight Deck Pilot’s Guide for a additional information on the system and its operating modes.
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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...
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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...
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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.
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Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 6 of 6 P/N 11934-S42 Original Issue: 12-18-08...
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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 ...............
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Cirrus Design Section 10 SR20 Safety Information Introduction This aircraft is designed to operate safely and efficiently in a flight environment. However, like any other aircraft, pilots must maintain proficiency to achieve maximum safety, utility, and economy. As the pilot you must be thoroughly familiar with the contents of this...
Safety Information SR20 Cirrus Airframe Parachute System (CAPS) The Cirrus Airframe Parachute System (CAPS) is designed to lower the aircraft and its passengers to the ground in the event of a life- threatening emergency. However, because CAPS deployment is expected to result in damage to the airframe and, depending upon...
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Cirrus Design Section 10 SR20 Safety Information Loss of Control Loss of control may result from many situations, such as: a control system failure (disconnected or jammed controls); severe wake turbulence, severe turbulence causing upset, severe airframe icing, or sustained pilot disorientation caused by vertigo or panic; or a spiral/ spin.
Section 10 Cirrus Design Safety Information SR20 General Deployment Information Deployment Speed The maximum speed at which deployment has been demonstrated is 133 KIAS. Deployment at higher speeds could subject the parachute and aircraft to excessive loads that could result in structural failure.
Cirrus Design Section 10 SR20 Safety Information Landing Considerations After a CAPS deployment, the airplane will descend at less than 1700 feet per minute with a lateral speed equal to the velocity of the surface wind. The CAPS landing touchdown is equivalent to ground impact from a height of approximately 13 feet.
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Section 10 Cirrus Design Safety Information SR20 • If a door is open prior to touchdown in a CAPS landing, the door will most likely break away from the airplane at impact. • If the door is open and the airplane contacts the ground in a rolled condition, an occupant could be thrown forward and strike their head on the exposed door pillar.
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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.
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.
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.
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Section 10 Cirrus Design Safety Information SR20 Intentionally Left Blank 10-12 P/N 11934-004 Original Issue...