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CIRRUS DESIGN SR20 Pilot Operating Handbook

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Download this manual See also: Maintenance Manual

PILOT'S OPERATING HANDBOOK

AND FAA APPROVED

AIRPLANE FLIGHT MANUAL

for the

CIRRUS DESIGN SR20

A l l - E l e c t r i c S R 2 0

A i r c r a f t S e r i a l s 1 2 6 8 a n d S u b s e q u e n t

FAA Approved in Normal Category based on FAR 23. This document must be carried in

the airplane at all times and be kept within the reach of the pilot during all flight

operations.

THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO

THE PILOT BY FAR PART 23 AND ADDITIONAL INFORMATION PROVIDED BY

CIRRUS DESIGN AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT

MANUAL

Model - Serial Num. SR20-_____________ Registration Num. _ __________________

P/N 11934-003

Reissue A: 10-10-03

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Summary of Contents for CIRRUS DESIGN SR20

Page 1 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 Model - Serial Num. SR20-_____________ Registration Num. _ __________________ P/N 11934-003 Reissue A: 10-10-03...
Page 2 Copyright © 2003 - All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811...
Page 3 This Pilot’s Operating Handbook (POH or Handbook) has been prepared by Cirrus Design Corporation to familiarize operators with the Cirrus Design SR20 airplane. 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”...
Page 4 Pilot’s Operating Handbook 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.
Page 5 Cirrus Design Pilot’s Operating Handbook SR20 Foreword Revising the Handbook Two types of revisions may be issued for this Handbook: Numbered and Temporary. Temporary revisions are printed on yellow paper, normally cover only one topic or procedure, and are issued to provide safety related information or other time sensitive information where the rigor of providing a numbered revision is not possible in the time allowed.
Page 6 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...
Page 7 Cirrus Design Pilot’s Operating Handbook 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.
Page 8 Pilot’s Operating Handbook Cirrus Design Foreword SR20 Intentionally Left Blank P/N 11934-003 Reissue A...
Page 9: Table Of Contents
Cirrus Design Section 1 SR20 General Section 1 General Table of Contents Introduction ..................1-3 The Airplane..................1-6 Engine..................1-6 Propeller ..................1-6 Fuel....................1-7 Oil ....................1-7 Maximum Certificated Weights ............ 1-7 Cabin and Entry Dimensions ............1-7 Baggage Spaces and Entry Dimensions ........1-7 Specific Loadings.................
Page 10 Section 1 Cirrus Design General SR20 Intentionally Left Blank P/N 11934-003 Revision A3...
Page 11: Introduction
Cirrus Design Section 1 SR20 General Introduction This section contains information of general interest to pilots and owners. You will find the information useful in acquainting yourself with the airplane, as well as in loading, fueling, sheltering, and handling the airplane during ground operations.
Page 12 Section 1 Cirrus Design General SR20 26.0' 9.2' 7" NOTE: • Wing span includes position and strobe lights. • Prop ground clearance at 3000 lb - 7" (2 blade), 8" (3 blade). • Wing Area = 135.2 sq. ft. 35.5' 76"...
Page 13 Cirrus Design Section 1 SR20 General GROUND TURNING CLEARANCE 11" -RADIUS FOR WING TIP 11" -RADIUS FOR NOSE GEAR 6" -RADIUS FOR INSIDE GEAR 2" -RADIUS FOR OUTSIDE GEAR TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER. ACTUAL TURNING RADIUS MAY VARY A S MUCH AS THREE FEET.
Page 14: The Airplane
Section 1 Cirrus Design General SR20 The Airplane Engine Number of Engines................1 Number of Cylinders................6 Engine Manufacturer ........... Teledyne Continental Engine Model................ IO-360-ES Fuel Metering..............Fuel Injected Engine Cooling ..............Air Cooled Engine Type........Horizontally Opposed, Direct Drive Horsepower Rating..........200 hp @ 2700 rpm...
Page 15: Fuel
Cirrus Design Section 1 SR20 General Fuel Total Capacity..........60.5 U.S. Gallons (229.0 L) Total Usable...........56 U.S. Gallons (212.0 L) Approved Fuel Grades: 100 LL Grade Aviation Fuel (Blue) 100 (Formerly 100/130) Grade Aviation Fuel (Green) Oil Capacity (Sump) ..........8 U.S. Quarts (7.6 L) Oil Grades: All Temperatures ..........SAE 15W-50 or 20W-50...
Page 16: Symbols, Abbreviations And Terminology
Section 1 Cirrus Design General SR20 Symbols, Abbreviations and Terminology General Airspeed Terminology and Symbols KCAS Knots Calibrated Airspeed is the indicated airspeed corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level.
Page 17: Meteorological Terminology
Cirrus Design Section 1 SR20 General Stalling Speed is the minimum steady flight speed at which the aircraft is controllable in the landing configuration (100% flaps) at the most unfavorable weight and balance. Best Angle of Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance.
Page 18: Engine Power Terminology
Section 1 Cirrus Design General SR20 • Standard Temperature is the temperature that would be found at a given pressure altitude in the standard atmosphere. It is 15° C (59° F) at sea level pressure altitude and decreases approximately 2° C (3.6° F) for each 1000 feet of altitude increase.
Page 19: Weight And Balance Terminology
Cirrus Design Section 1 SR20 General • Unusable Fuel is the quantity of fuel that cannot be safely used in flight. • Usable Fuel is the fuel available for flight planning. Weight and Balance Terminology c.g. Center of Gravity is the point at which an airplane would balance if suspended.
Page 20 Section 1 Cirrus Design General SR20 • Reference Datum is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. • Tare is the weight of all items used to hold or position the airplane on the scales for weighing. Tare includes blocks, shims, and chocks.
Page 21 Cirrus Design Section 2 SR20 Limitations Section 2 Limitations Table of Contents Introduction ..................2-3 Certification Status ................2-3 Airspeed Limitations................ 2-4 Airspeed Indicator Markings ............2-5 Power Plant Limitations ..............2-6 Engine..................2-6 Propeller ..................2-7 Weight Limits .................. 2-7 Instrument Markings ...............
Page 22 Section 2 Cirrus Design Limitations SR20 Placards ..................2-21 P/N 11934-003 Revision A6...
Page 23: Introduction
This section provides operating limitations, instrument markings and basic placards required by regulation and necessary for the safe operation of the SR20 and its standard systems and equipment. Refer to Section 9 of this handbook for amended operating limitations for airplanes equipped with optional equipment.
Page 24: Airspeed Limitations
Section 2 Cirrus Design Limitations SR20 Airspeed Limitations The indicated airspeeds in the following table are based upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
Page 25: Airspeed Indicator Markings
Cirrus Design Section 2 SR20 Limitations Airspeed Indicator Markings The airspeed indicator markings are based upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
Page 26: Power Plant Limitations
Section 2 Cirrus Design Limitations SR20 Power Plant Limitations Engine Teledyne Continental ............IO-360-ES Power Rating ............200 hp @ 2700 rpm Maximum RPM ...............2700 rpm Oil: Oil Temperature........240° F (115° C) maximum Oil Pressure: Minimum................10 psi Maximum................100 psi...
Page 27: Propeller
Cirrus Design Section 2 SR20 Limitations Propeller • Note • Two-blade propellers are not EASA approved for use on this airplane. Airplanes registered in the European Union should ignore all references to the two-blade propeller in this POH. Hartzell Propeller Type ............. Constant Speed Two-Blade Propeller: Model Number...........
Page 28: Instrument Markings
Section 2 Cirrus Design Limitations SR20 Instrument Markings Red Line Green Arc Yellow Arc Red Line Instrument (Range) Minimum Normal Caution Maximum Power Plant Instrumentation Tachometer/ –– 500 - 2700 –– 2700 Engine Speed (0 - 3500 RPM) Cylinder Head ––...
Page 29: Center Of Gravity Limits
Cirrus Design Section 2 SR20 Limitations Center of Gravity Limits Reference Datum ........100 inches forward of firewall Forward ..............Refer to Figure 2-4 Aft ................Refer to Figure 2-4 FORWARD LIMIT - The forward limit is FS 138.7 (12.0% MAC) at 2110 lb., with straight line taper to FS 141.0 (16.7% MAC) at 2694 lb., and to FS 144.1 (23.1% MAC) at 3000 lb.
Page 30: Maneuver Limits
Maneuver Limits Aerobatic maneuvers, including spins, are prohibited. • Note • Because the SR20 has not been certified for spin recovery, the Cirrus Airframe Parachute System (CAPS) must be deployed if the airplane departs controlled flight. Refer to Section 3 – Emergency Procedures, Inadvertent Spiral/Spin Entry.
Page 31: Kinds Of Operation
Section 2 SR20 Limitations Kinds of Operation The SR20 is equipped and approved for the following type operations: • VFR day and night. • IFR day and night. Serials 1337 and subsequent with SRV configuration: The airplane is equipped and approved for the following type operations: •...
Page 32 Section 2 Cirrus Design Limitations SR20 System, Kinds of Operation Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Amp Meter/Indication Low Volts Annunciator ALT 1 Annunciator ALT 2 Annunciator Serials 1337 and subsequent with SRV standard configuration: ALT 2 Annunciator not applicable.
Page 33 Cirrus Design Section 2 SR20 Limitations System, Kinds of Operation Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Auxiliary Boost Pump Fuel Quantity Indicator Fuel Selector Valve Ice & Rain Protection Alternate Engine Air Induction System Alternate Static Air Source Pitot Heater —...
Page 34 Section 2 Cirrus Design Limitations SR20 System, Kinds of Operation Remarks, Instrument, Notes, and/or and/or Equipment Exceptions PFD Altimeter Serials 1337 & subs w/ PFD only. Standby Altimeter Serials 1337 & subs w/ PFD only. PFD Heading Serials 1337 & subs w/ PFD only.
Page 35: Icing
Cirrus Design Section 2 SR20 Limitations System, Kinds of Operation Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Manifold Pressure Indication Oil Pressure Indication Oil Quantity Indicator (Dipstick) Oil Temperature Indication Engine Speed Special Equipment Cirrus Airframe Parachute (CAPS) Airplane Flight Manual Included w/ POH.
Page 36: Taxi Power
Refer to Oxygen System Limitations in this Section. Environmental Conditions For operation of the airplane below an outside air temperature of -10°F (-23° C), use of cowl inlet covers approved by Cirrus Design and listed in the Winterization Kit AFM Supplement P/N 11934-S25 is required. Maximum Occupancy Occupancy of this airplane is limited to four persons (the pilot and three passengers).
Page 37: Systems And Equipment Limits
Cirrus Design Section 2 SR20 Limitations Systems and Equipment Limits Cirrus Airframe Parachute System (CAPS) Maximum Demonstrated Deployment Speed ....135 KIAS • Note • Refer to Section 10 – Safety Information, for additional CAPS guidance. Primary Flight Display 1. The PFD integrates with separately approved sensor installations.
Page 38 Section 2 Cirrus Design Limitations SR20 8. Flaps must be set to 50% for autopilot operation in Altitude Hold at airspeeds below 95 KIAS. 9. Flap deflection is limited to 50% during autopilot operations. 10. The autopilot must be disconnected in moderate or severe turbulence.
Page 39: Multi-Function Display
Cirrus Design Section 2 SR20 Limitations The flaps should be extended in the approach configuration prior to the Outer Marker. No further changes in the flap configuration should be made throughout the autopilot- coupled approach. The glideslope is approached in such a manner to allow automatic arming of the glideslope, or if the glideslope is manually armed no more than 15% above the glideslope.
Page 40: Oxygen System
Oxygen System Whenever the operating rules require the use of supplemental oxygen, the pilot must: • Use an oxygen system approved by Cirrus Design and listed in the Oxygen System AFM Supplement Part Number 11934- S09. • Secure the oxygen bottle in the right front seat as described in the AFM Supplement noted above.
Page 41 Cirrus Design Section 2 SR20 Limitations Placards Figure 2-5 Placards (Sheet 1 of 7) P/N 11934-003 2-21 Revision A5...
Page 42 Section 2 Cirrus Design Limitations SR20 Figure 2-5 Placards (Sheet 2 of 7) 2-22 P/N 11934-003 Revision A5...
Page 43 Cirrus Design Section 2 SR20 Limitations Figure 2-5 Placards (Sheet 3 of 7) P/N 11934-003 2-23 Revision A5...
Page 44 Section 2 Cirrus Design Limitations SR20 Wing, flap aft edge: NO STEP Cabin Door Window, lower edge, centered, applied upside down : RESCUE: FRACTURE AND REMOVE WINDOW Bolster Switch Panel, left edge: THIS AIRCRAFT IS CERTIFIED FOR THE FOLLOWING FLIGHT OPERATIONS:...
Page 45 Cirrus Design Section 2 SR20 Limitations Instrument Panel Upper Right: Bolster Panel, both sides: NO SMOKING GRAB HERE FASTEN SEATBELTS Serials 1351 & subs. Above MFD (on one line): FASTEN SEATBELTS NO SMOKING Cabin Window, above door latch: EMERGENCY EXIT...
Page 46 Section 2 Cirrus Design Limitations SR20 Baggage Compartment, aft edge: ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Baggage Compartment Door, inside: DISTRIBUTED FLOOR LIMIT 130 LBS BAGGAGE STRAP CAPACITY IS 35 LBS EACH MAXIMUM SEE AIRPLANE FLIGHT MANUAL FOR BAGGAGE TIE-DOWN...
Page 47 Cirrus Design Section 2 SR20 Limitations CAPS Deployment Handle Cover, above pilot's right shoulder : WARNING USE FOR EXTREME EMERGENCIES ONLY SEAT BELT AND SHOULDER HARNESS MUST BE WORN AT ALL TIMES USE OF THIS DEVICE COULD RESULT IN INJURY OR DEATH...
Page 48 Section 2 Cirrus Design Limitations SR20 Intentionally Left Blank 2-28 P/N 11934-003 Revision A5...
Page 49 Cirrus Design Section 3 SR20 Emergency Procedures Section 3 Emergency Procedures Table of Contents Introduction ..................3-3 Airspeeds for Emergency Operations ..........3-4 Emergency Procedures Guidance ..........3-5 Preflight Planning................. 3-5 Preflight Inspections/Maintenance ..........3-5 Methodology ................3-5 Memory Items ................3-6 Ground Emergencies ..............3-7...
Page 50 Section 3 Cirrus Design Emergency Procedures SR20 Exit IMC..................3-25 PFD - Loss of Attitude Data ............3-25 Exit IMC..................3-25 Power Lever Linkage Failure .............3-26 P/N 11934-003 Revision A5...
Page 51: Introduction
Emergency Procedures Introduction This section provides procedures for handling emergencies and critical flight situations that may occur while operating the SR20. Although emergencies caused by airplane, systems, or engine malfunctions are extremely rare, the guidelines described in this section should be considered and applied as necessary should an emergency arise.
Page 52: Airspeeds For Emergency Operations
Section 3 Cirrus Design Emergency Procedures SR20 Airspeeds for Emergency Operations Maneuvering Speed: 3000 lb ................131 KIAS 2600 lb ................122 KIAS 2200 lb ................111 KIAS Best Glide: 3000 lb ................96 KIAS 2500 lb ................87 KIAS Emergency Landing (Engine-out): Flaps Up................86 KIAS Flaps 50% ................81 KIAS...
Page 53: Emergency Procedures Guidance
Emergency Procedures Guidance Although this section provides procedures for handling most emergencies and critical flight situations that could arise in the SR20, it is not a substitute for thorough knowledge of the airplane and general aviation techniques. A thorough study of the information in this handbook while on the ground will help you prepare for time-critical situations in the air.
Page 54: Memory Items
Section 3 Cirrus Design Emergency Procedures SR20 Take Appropriate Action — In most situations, the procedures listed in this section will either correct the aircraft problem or allow safe recovery of the aircraft. Follow them and use good pilot judgment.
Page 55: Ground Emergencies
Cirrus Design Section 3 SR20 Emergency Procedures Ground Emergencies Engine Fire During Start A fire during engine start may be caused by fuel igniting in the fuel induction system. If this occurs, attempt to draw the fire back into the engine by continuing to crank the engine.
Page 56: Emergency Ground Egress
Section 3 Cirrus Design Emergency Procedures SR20 Emergency Ground Egress • WARNING • While exiting the airplane, make sure evacuation path is clear of other aircraft, spinning propellers, and other hazards. 1. Engine................SHUTDOWN • Note • If the engine is left running, set the Parking Brake prior to evacuating the airplane.
Page 57: In-Flight Emergencies
Cirrus Design Section 3 SR20 Emergency Procedures In-Flight Emergencies Engine Failure On Takeoff (Low Altitude) If the engine fails immediately after becoming airborne, abort on the runway if possible. If altitude precludes a runway stop but is not sufficient to restart the engine, lower the nose to maintain airspeed and establish a glide attitude.
Page 58: Maximum Glide
Section 3 Cirrus Design Emergency Procedures SR20 Maximum Glide Conditions Example: Power Altitude 7,000 ft. AGL Propeller Windmilling Airspeed Best Glide Flaps 0% (UP) Wind Zero Glide Distance 12.5 NM Best Glide Speed 3000 lb 96 KIAS 2500 lb 87 KIAS Maximum Glide Ratio ~ 10.9 : 1...
Page 59: Engine Failure In Flight
Cirrus Design Section 3 SR20 Emergency Procedures Engine Failure In Flight If the engine fails at altitude, pitch as necessary to establish best glide speed. While gliding toward a suitable landing area, attempt to identify the cause of the failure and correct it.
Page 60: Engine Airstart
Section 3 Cirrus Design Emergency Procedures SR20 Engine Airstart The following procedures address the most common causes for engine loss. Switching tanks and turning the fuel pump on will enhance starting if fuel contamination was the cause of the failure.
Page 61: Engine Partial Power Loss
Cirrus Design Section 3 SR20 Emergency Procedures Engine Partial Power Loss Indications of a partial power loss include fluctuating RPM, reduced or fluctuating manifold pressure, low oil pressure, high oil temperature, and a rough-sounding or rough-running engine. Mild engine roughness in flight may be caused by one or more spark plugs becoming fouled.
Page 62: Fuel Pump (If Used)
Section 3 Cirrus Design Emergency Procedures SR20 The following procedure provides guidance to isolate and correct some of the conditions contributing to a rough running engine or a partial power loss: 1. Fuel Pump................BOOST Selecting BOOST on may clear the problem if vapor in the injection lines is the problem or if the engine-driven fuel pump has partially failed.
Page 63: Low Oil Pressure
Cirrus Design Section 3 SR20 Emergency Procedures Low Oil Pressure If low oil pressure is accompanied by a rise in oil temperature, the engine has probably lost a significant amount of its oil and engine failure may be imminent. Immediately reduce engine power to idle and select a suitable forced landing field.
Page 64: Smoke And Fume Elimination
Section 3 Cirrus Design Emergency Procedures SR20 Smoke and Fume Elimination If smoke and/or fumes are detected in the cabin, check the engine parameters for any sign of malfunction. If a fuel leak has occurred, actuation of electrical components may cause a fire. If there is a strong smell of fuel in the cockpit, divert to the nearest suitable landing field.
Page 65: Cabin Fire In Flight
Cirrus Design Section 3 SR20 Emergency Procedures Cabin Fire In Flight If the cause of the fire is readily apparent and accessible, use the fire extinguisher to extinguish flames and land as soon as possible. Opening the vents may feed the fire, but to avoid incapacitating the crew from smoke inhalation, it may be necessary to rid cabin of smoke or fire extinguishant.
Page 66: Emergency Descent
Section 3 Cirrus Design Emergency Procedures SR20 • WARNING • If airplane is in day VFR conditions and turning off the master switches eliminated the fire situation, leave the master switches OFF. Do not attempt to isolate the source of the fire by checking each individual electrical component.
Page 67: Spins
SR20 Emergency Procedures Spins The SR20 is not approved for spins, and has not been tested or certified for spin recovery characteristics. The only approved and demonstrated method of spin recovery is activation of the Cirrus Airframe Parachute System (See CAPS Deployment, this section).
Page 68: Caps Deployment
Section 3 Cirrus Design Emergency Procedures SR20 CAPS Deployment The Cirrus Airframe Parachute System (CAPS) should be activated in the event of a life-threatening emergency where CAPS deployment is determined to be safer than continued flight and landing. • WARNING •...
Page 69 Cirrus Design Section 3 SR20 Emergency Procedures The maximum demonstrated deployment speed is 135 KIAS. Reducing airspeed allows minimum parachute loads and prevents structural overload and possible parachute failure. 2. Mixture (If time and altitude permit) ........CUTOFF Generally, a distressed airplane will be safer for its occupants if the engine is not running.
Page 70 Section 3 Cirrus Design Emergency Procedures SR20 All occupants must have seat belts and shoulder harness securely fastened. 12. Loose Items ..............SECURE If time permits, all loose items should be secured to prevent injury from flying objects in the cabin at touchdown.
Page 71: Landing Emergencies
Cirrus Design Section 3 SR20 Emergency Procedures Landing Emergencies Forced Landing (Engine Out) If all attempts to restart the engine fail and a forced landing is imminent, select a suitable field and prepare for the landing. A suitable field should be chosen as early as possible so that maximum time will be available to plan and execute the forced landing.
Page 72: Landing Without Elevator Control
Section 3 Cirrus Design Emergency Procedures SR20 Landing Without Elevator Control The pitch trim spring cartridge is attached directly to the elevator and provides a backup should you lose the primary elevator control system. Set elevator trim for a 80 KIAS approach to landing.
Page 73: System Malfunctions
Cirrus Design Section 3 SR20 Emergency Procedures System Malfunctions Primary Flight Display System In the unlikely event of a PFD failure, the pilot may lose the ability to control the autopilot through the PFD controls. If this malfunction occurs, the PFD circuit breakers may be pulled and the airplane flown using the mechanical standby instruments.
Page 74: Power Lever Linkage Failure
Section 3 Cirrus Design Emergency Procedures SR20 • WARNING • Aircraft equipped with Software Version 530-00123-000 Rev 00 or higher; Any power interruption to the PFD will result in loss of attitude information until the PFD can be restarted on the ground.
Page 75 Cirrus Design Section 3A SR20 Abnormal Procedures Section 3A Abnormal Procedures Table of Contents Introduction .................. 3A-3 Abnormal Procedures Guidance ..........3A-4 Ground Procedures..............3A-5 Brake Failure During Taxi ............3A-5 Aborted Takeoff ................ 3A-5 In-Flight Procedures..............3A-6 Inadvertent Icing Encounter ............3A-6 Inadvertent IMC Encounter............
Page 76 Section 3A Cirrus Design Abnormal Procedures SR20 Intentionally Left Blank 3A-2 P/N 11934-003 Revision A5...
Page 77: Section 3A
Cirrus Design Section 3A SR20 Abnormal Procedures Introduction This section provides procedures for handling abnormal system and/or flight conditions which, if followed, will maintain an acceptable level of airworthiness or reduce operational risk. The guidelines described in this section are to be used when an abnormal condition exists and should be considered and applied as necessary.
Page 78: Abnormal Procedures Guidance
Abnormal Procedures Guidance Although this section provides procedures for handling most abnormal system and/or flight conditions that could arise in the SR20, it is not a substitute for thorough knowledge of the airplane and general aviation techniques. A thorough study of the information in this handbook while on the ground will help you prepare for time-critical situations in the air.
Page 79: Ground Procedures
Cirrus Design Section 3A SR20 Abnormal Procedures Ground Procedures Brake Failure During Taxi Ground steering is accomplished by differential braking. However, increasing power may allow some rudder control due to increased groundspeed and airflow over the rudder. 1. Engine Power............AS REQUIRED •...
Page 80: In-Flight Procedures
3. Heading..........Reset to initiate 180° turn Door Open In Flight The doors on the SR20 will remain 1-3 inches open in flight if not latched. If this is discovered on takeoff roll, abort takeoff if practical. If already airborne: 1.
Page 81: Landing Procedures
Cirrus Design Section 3A SR20 Abnormal Procedures Landing Procedures Landing With Failed Brakes One brake inoperative 1. Land on the side of runway corresponding to the inoperative brake. 2. Maintain directional control using rudder and working brake. Both brakes inoperative 1.
Page 82 Section 3A Cirrus Design Abnormal Procedures SR20 AMMETER BAT 1 ALT 1 ALT 2 BATT MAIN DISTRIBUTION ESSENTIAL ALT 1 ALT 2 DISTRIBUTION BUS BAT 2 NON-ESSENTIAL MAIN BUS 2 ESSENTIAL ANNUN/ENGINE INST SKYWATCH/ FUEL PUMP TAWS TURN TURN COORD. #1 COORD.
Page 83: System Malfunctions
Cirrus Design Section 3A SR20 Abnormal Procedures System Malfunctions Alternator Failure Steady illumination of either ALT caution light in the annunciator panel indicates a failure of the corresponding alternator. The most likely the cause of the alternator failure is a wiring fault, a malfunctioning alternator, or a malfunctioning control unit.
Page 84 Section 3A Cirrus Design Abnormal Procedures SR20 ALT 1 Light Steady Steady illumination indicates a failure of ALT 1. Attempt to bring alternator back on line. If alternator cannot be brought back, reduce loads and use Main Bus or Non-Essential loads only as necessary for flight conditions.
Page 85: Engine Indicating System Failure
Cirrus Design Section 3A SR20 Abnormal Procedures 2. Alternator 2 Circuit Breaker ......CHECK and RESET 3. ALT 2 Master Switch ..............ON If alternator does not reset: 4. Switch off unnecessary equipment on Main Bus 1, Main Bus 2, and Non-Essential Buses to reduce loads.
Page 86: Communications Failure
Section 3A Cirrus Design Abnormal Procedures SR20 Communications Failure Communications failure can occur for a variety of reasons. If, after following the checklist procedure, communication is not restored, proceed with FAR/AIM lost communications procedures. • Note • In the event of an audio panel power failure the audio panel connects COM 1 to the pilot’s headset and speakers.
Page 87: Pitot Static Malfunction
Cirrus Design Section 3A SR20 Abnormal Procedures Pitot Static Malfunction Static Source Blocked If erroneous readings of the static source instruments (airspeed, altimeter and vertical speed) are suspected, the alternate static source valve, on side of console near pilot’s right ankle, should be opened to supply static pressure from the cabin to these instruments.
Page 88: Electric Trim/Autopilot Failure
Section 3A Cirrus Design Abnormal Procedures SR20 Electric Trim/Autopilot Failure Any failure or malfunction of the electric trim or autopilot can be over- ridden by use of the control yoke. If runaway trim is the problem, de- energize the circuit by pulling the circuit breaker (PITCH TRIM, ROLL TRIM, or AUTOPILOT) and land as soon as conditions permit.
Page 89 Cirrus Design Section 4 SR20 Normal Procedures Section 4 Normal Procedures Table of Contents Introduction ..................4-3 Airspeeds for Normal Operation ............. 4-4 Normal Procedures ................. 4-5 Preflight Inspection ..............4-5 Preflight Walk-Around ..............4-6 Before Starting Engine............... 4-10 Starting Engine ................4-11 Before Taxiing................
Page 90 Section 4 Cirrus Design Normal Procedures SR20 Intentionally Left Blank P/N 11934-003 Revision A5...
Page 91: Introduction
Cirrus Design Section 4 SR20 Normal Procedures Introduction This section provides amplified procedures for normal operation. Normal procedures associated with optional systems can be found in Section 9. • Note • Serials 1337 subsequent with standard configuration: The airplane is equipped with a single alternator, dual battery electrical system.
Page 92: Airspeeds For Normal Operation
Section 4 Cirrus Design Normal Procedures SR20 Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3000 lb. and may be used for any lesser weight. However, to achieve the performance specified in Section 5 for takeoff distance, the speed appropriate to the particular weight must be used.
Page 93: Normal Procedures
Cirrus Design Section 4 SR20 Normal Procedures Normal Procedures Preflight Inspection Before carrying out preflight inspections, ensure that all required maintenance has been accomplished. Review your flight plan and compute weight and balance. • Note • Throughout the walk-around: check all hinges, hinge pins, and bolts for security;...
Page 94: Preflight Walk-Around
Section 4 Cirrus Design Normal Procedures SR20 Preflight Walk-Around 1. Cabin a. Required Documents..........On Board b. Avionics Power Switch............OFF c. Bat 2 Master Switch ............ON d. PFD - Serials 0435 and subsequent with PFD ..Verify On e. Avionics Cooling Fan ............ Audible Voltmeter ..............
Page 95 Cirrus Design Section 4 SR20 Normal Procedures d. Baggage Door ........... Closed and Secure e. Static Button ..........Check for Blockage Parachute Cover........Sealed and Secure 3. Empennage a. Tiedown Rope .............Remove b. Horizontal and Vertical Stabilizers......Condition c. Elevator and Tab....... Condition and Movement d.
Page 96 Section 4 Cirrus Design Normal Procedures SR20 • Caution • Serials 1005 through 1592 after Service Bulletin SB 2X-32-14 and airplane serials 1593 and subsequent: Clean and inspect temperature indicator installed to piston housing. If indicator center is black, the brake assembly has been overheated. The brake linings must be inspected and O-rings replaced.
Page 97 Cirrus Design Section 4 SR20 Normal Procedures 10. Nose, Left Side a. Landing Light............. Condition b. Engine Oil..Check 6-8 quarts, Leaks, Cap & Door Secure c. Cowling.............Attachments Secure d. External Power ............. Door Secure e. Exhaust Pipe .....Condition, Security, and Clearance 11.
Page 98: Before Starting Engine
Section 4 Cirrus Design Normal Procedures SR20 Before Starting Engine 1. Preflight Inspection ..........COMPLETED 2. Emergency Equipment..........ON BOARD 3. Passengers ..............BRIEFED • Note • Ensure all the passengers have been fully briefed on smoking, the use of the seat belts, doors, emergency exits, egress hammer, and CAPS.
Page 99: Starting Engine
Cirrus Design Section 4 SR20 Normal Procedures Starting Engine If the engine is warm, no priming is required. For the first start of the day and in cold conditions, prime will be necessary. Weak intermittent firing followed by puffs of black smoke from the exhaust stack indicates over-priming or flooding.
Page 100 Section 4 Cirrus Design Normal Procedures SR20 4. Strobe Lights ................ON 5. Mixture ................. FULL RICH 6. Power Lever ............FULL FORWARD 7. Fuel Pump............. PRIME, then BOOST • Note • On first start of the day, especially under cool ambient conditions, holding Fuel Pump switch to PRIME for 2 seconds will improve starting.
Page 101: Before Taxiing
Cirrus Design Section 4 SR20 Normal Procedures Before Taxiing 1. Flaps ................. UP (0%) 2. Radios/Avionics ............. AS REQUIRED 3. Cabin Heat/Defrost ..........AS REQUIRED 4. Fuel Selector............SWITCH TANK Taxiing When taxiing, directional control is accomplished with rudder deflection and intermittent braking (toe taps) as necessary. Use only as much power as is necessary to achieve forward movement.
Page 102: Before Takeoff
Section 4 Cirrus Design Normal Procedures SR20 Before Takeoff During cold weather operations, the engine should be properly warmed up before takeoff. In most cases this is accomplished when the oil temperature has reached at least 100° F (38° C). In warm or hot weather, precautions should be taken to avoid overheating during prolonged ground engine operation.
Page 103 Cirrus Design Section 4 SR20 Normal Procedures 15. Voltage ................CHECK 16. Pitot Heat ............... AS REQUIRED • Note • Pitot heat should be turned ON prior to flight into IMC or flight into visible moisture and OAT of 40° F (4° C) or less.
Page 104: Takeoff
Section 4 Cirrus Design Normal Procedures SR20 Takeoff • Note • The engine is equipped with an altitude compensating fuel pump that automatically provides the proper full rich mixture. Because of this, the mixture should be left full rich for takeoff, even at high altitude airfields.
Page 105: Normal Takeoff
Cirrus Design Section 4 SR20 Normal Procedures Normal Takeoff 1. Power Lever ............FULL FORWARD 2. Engine Instruments............CHECK 3. Brakes........RELEASE (Steer with Rudder Only) 4. Elevator Control ......ROTATE Smoothly at 65-70 KIAS 5. At 85 KIAS, Flaps............... UP Short Field Takeoff 1.
Page 106: Climb
Section 4 Cirrus Design Normal Procedures SR20 Climb Normal climbs are performed flaps UP (0%) and full power at speeds 5 to 10 knots higher than best rate-of-climb speeds. These higher speeds give the best combination of performance, visibility and engine cooling.
Page 107: Cruise
Cirrus Design Section 4 SR20 Normal Procedures Cruise Normal cruising is performed between 55% and 75% power. The engine power setting and corresponding fuel consumption for various altitudes and temperatures can be determined by using the cruise data in Section 5.
Page 108: Cruise Leaning
Section 4 Cirrus Design Normal Procedures SR20 Cruise Leaning The engine is equipped with an altitude compensating fuel pump that automatically provides the proper full rich mixture. Because of this, the mixture should be set to full rich to allow the aneroid to provide auto leaning for the engine during all flight conditions.
Page 109: Descent
Cirrus Design Section 4 SR20 Normal Procedures Descent 1. Altimeter................... SET 2. Cabin Heat/Defrost ..........AS REQUIRED 3. Landing Light ................ON 4. Fuel System ............... CHECK 5. Mixture ..............AS REQUIRED 6. Brake Pressure ..............CHECK Before Landing 1. Seat Belt and Shoulder Harness ........SECURE 2.
Page 110: Balked Landing/Go-Around
Section 4 Cirrus Design Normal Procedures SR20 Short Field Landing For a short field landing in smooth air conditions, make an approach at 75 KIAS with full flaps using enough power to control the glide path (slightly higher approach speeds should be used under turbulent air conditions).
Page 111: After Landing
Cirrus Design Section 4 SR20 Normal Procedures After Landing 1. Power Lever ..............1000 RPM 2. Fuel Pump ................OFF 3. Flaps ..................UP 4. Transponder ................STBY 5. Lights ..............AS REQUIRED 6. Pitot Heat ................. OFF • Note •...
Page 112: Stalls
Normal Procedures SR20 Stalls SR20 stall characteristics are conventional. Power-off stalls may be accompanied by a slight nose bobbing if full aft stick is held. Power-on stalls are marked by a high sink rate at full aft stick. Power-off stall speeds at maximum weight for both forward and aft C.G.
Page 113: Environmental Considerations
Cirrus Design Section 4 SR20 Normal Procedures Environmental Considerations Cold Weather Operation Starting If the engine has been cold soaked, it is recommended that the propeller be pulled through by hand several times to break loose or limber the oil. This procedure will reduce power draw on the battery if a battery start is made.
Page 114: Propeller Area
Section 4 Cirrus Design Normal Procedures SR20 as the cylinders, air intake and oil cooler. Because excessively hot air can damage non-metallic components such as composite parts, seals, hoses, and drives belts, do not attempt to hasten the preheat process.
Page 115: Hot Weather Operation
Cirrus Design Section 4 SR20 Normal Procedures 15. Avionics Power Switch ...............ON 16. Engine Parameters ............MONITOR 17. External Power (If applicable) ......... DISCONNECT 18. Amp Meter/Indication ............CHECK 19. Strobe Lights................ON Hot Weather Operation Avoid prolonged engine operation on the ground.
Page 116: Noise Characteristics/Abatement
Section 4 Cirrus Design Normal Procedures SR20 Noise Characteristics/Abatement The certificated noise levels for the Cirrus Design SR20 established in accordance with FAR 36 Appendix G are: Configuration Actual Maximum Allowable Two-blade Propeller 84.79 dB(A) 87.6 dB(A) Three-blade Propeller 83.42 dB(A) 87.6 dB(A)
Page 117: Fuel Conservation
Cirrus Design Section 4 SR20 Normal Procedures Fuel Conservation Minimum fuel use at cruise will be achieved using the best economy power setting described under cruise. P/N 11934-003 4-29 Revision A5...
Page 118 Section 4 Cirrus Design Normal Procedures SR20 Intentionally Left Blank 4-30 P/N 11934-003 Revision A5...
Page 119 Cirrus Design Section 5 SR20 Performance Data Section 5 Performance Data Table of Contents Introduction ..................5-3 Associated Conditions Affecting Performance......5-3 Flight Planning ................5-4 Sample Problem ................5-4 Takeoff..................5-5 Climb.................... 5-6 Cruise ..................5-7 Fuel Required ................5-8 Landing ..................
Page 120 Section 5 Cirrus Design Performance Data SR20 Range / Endurance Profile ............5-29 Range / Endurance Profile ............5-30 Balked Landing Climb Gradient ............5-31 Balked Landing Rate of Climb............5-32 Landing Distance ................5-33 Landing Distance ................5-34 P/N 11934-003 Revision A5...
Page 121: Introduction
Cirrus Design Section 5 SR20 Performance Data Introduction Performance data in this section are presented for operational planning so that you will know what performance to expect from the airplane under various ambient and field conditions. Performance data are presented for takeoff, climb, and cruise (including range &...
Page 122: Flight Planning
Section 5 Cirrus Design Performance Data SR20 Flight Planning The performance tables in this section present sufficient information to predict airplane performance with reasonable accuracy. However, variations in fuel metering, mixture leaning technique, engine & propeller condition, air turbulence, and other variables encountered during a particular flight may account for variations of 10% or more in range and endurance.
Page 123: Takeoff
Cirrus Design Section 5 SR20 Performance Data • Expected wind enroute........10 Knot Headwind Landing Conditions: • Field pressure altitude ..........2000 Feet • Temperature ..........20° C (ISA + 10° C) • Field length..............3000 Feet Takeoff The takeoff distance tables, Figure 5-9, show the takeoff ground roll and horizontal distance to reach 50 feet above ground level.
Page 124: Climb
Section 5 Cirrus Design Performance Data SR20 manner as the wind correction above. Refer to Figure 5-9 for correction factors to be applied. Climb The takeoff and enroute rate-of-climb and climb gradient tables, Figures 5-10 through 5-13, present maximum rate of climb and climb gradient for various conditions.
Page 125 Cirrus Design Section 5 SR20 Performance Data The fuel estimate for climb is: • Fuel to climb (standard temperature) ......2.1 Gal. • Increase due to non-standard temp. (2.1 x 0.13) ..0.3 Gal. • Corrected fuel to climb (2.1 + 0.3) ......... 2.4 Gal.
Page 126: Fuel Required
Section 5 Cirrus Design Performance Data SR20 Fuel Required The total fuel requirement for the flight may be estimated using the performance information obtained from Figures 5-14 and 5-15. The resultant cruise distance is: • Total distance (from sample problem) ......560.0 NM •...
Page 127: Landing
Cirrus Design Section 5 SR20 Performance Data Landing A procedure similar to takeoff should be used for estimating the landing distance at the destination airport. Figure 5-19 presents landing distance information for the short field technique. The distances corresponding to 2000 feet and 20° C are as follows: •...
Page 128: Airspeed Calibration
Section 5 Cirrus Design Performance Data SR20 Airspeed Calibration Normal Static Source Conditions: Example: • Power for level flight or maximum Flaps ........... 50% continuous, whichever is less. Indicated Airspeed ....85 Knots • Weight ........3000 LB Calibrated Airspeed ..... 86 Knots •...
Page 129: Airspeed Calibration
Cirrus Design Section 5 SR20 Performance Data Airspeed Calibration Alternate Static Source Conditions: Example: • Power for level flight or maximum Flaps..........50% continuous, whichever is less. Indicated Airspeed....85 Knots • Weight ........3000 LB • Heater, Defroster & Vents .....ON Calibrated Airspeed ....84 Knots •...
Page 130: Altitude Correction
Section 5 Cirrus Design Performance Data SR20 Altitude Correction Normal Static Source Conditions: Example: • Power for level flight or maximum Flaps ........... 50% continuous, whichever is less. Indicated Airspeed ....85 Knots • Weight ........3000 LB Desired Altitude....12,000 FT Altitude Correction .....-7 FT...
Page 131: Altitude Correction
Cirrus Design Section 5 SR20 Performance Data Altitude Correction Alternate Static Source Conditions: Example: • Power for level flight or maximum Flaps..........0% continuous, whichever is less. Indicated Airspeed....120 Knots • Weight ........3000 LB Desired Altitude ....12,000 FT • Heater, Defroster, & Vents.....ON Altitude Correction....
Page 132: Temperature Conversion
Section 5 Cirrus Design Performance Data SR20 Temperature Conversion • Note • • To convert from Celsius (°C) to Fahrenheit (°F), find, in the shaded columns, the number representing the temperature value (°C) to be converted. The equivalent Fahrenheit temperature is read to the right.
Page 133: Outside Air Temperature For Isa Condition
Cirrus Design Section 5 SR20 Performance Data Outside Air Temperature ISA Condition Example: Pressure Altitude....8000 FT Outside Air Temp....... 48° F ISA Condition ....ISA + 10° C Press ISA-40°C ISA-20°C ISA+10°C ISA+20°C Feet °C °F °C °F °C °F °C...
Page 134: Stall Speeds
Section 5 Cirrus Design Performance Data SR20 Stall Speeds Conditions: Example: • Weight ........3000 LB Flaps ........Up (0%) • C.G........... Noted Bank Angle........15° • Power..........Idle • Bank Angle ....... Noted Stall Speed..66 KIAS | 68 KCAS •...
Page 135: Wind Components
Cirrus Design Section 5 SR20 Performance Data Wind Components Conditions: Example: • Runway Heading ......10° Wind/Flight Path Angle ....50° • Wind Direction.......60° Crosswind Component ..12 Knots • Wind Velocity......15 Knots Headwind Component..10 Knots • Note • • The maximum demonstrated crosswind is 21 knots. Value not considered limiting.
Page 136: Takeoff Distance
Section 5 Cirrus Design Performance Data SR20 Takeoff Distance Conditions: Example: • Winds.......... Zero Outside Air Temp ....... 25°C • Runway....Dry, Level, Paved Weight........3000 LB • Flaps........... 50% Pressure Altitude....2000 FT • Power........Maximum Headwind ......12 Knots set before brake release Runway ......
Page 137 Cirrus Design Section 5 SR20 Performance Data Takeoff Distance WEIGHT = 3000 LB Headwind: Subtract 10% for each Speed at Liftoff = 68 KIAS 12 knots headwind. Speed over 50 Ft. Obstacle = 75 KIAS Tailwind: Add 10% for each 2 knots Flaps - 50% ·...
Page 138: Takeoff Distance
Section 5 Cirrus Design Performance Data SR20 Takeoff Distance WEIGHT = 2500 LB Headwind: Subtract 10% for each Speed at Liftoff = 65 KIAS 12 knots headwind. Speed over 50 Ft Obstacle = 70 KIAS Tailwind: Add 10% for each 2 knots Flaps - 50% ·...
Page 139: Takeoff Climb Gradient
Cirrus Design Section 5 SR20 Performance Data Takeoff Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ......... Full Rich Weight ........3000 LB • Flaps ........... 50% Pressure Altitude ....1750 FT •...
Page 140: Takeoff Rate Of Climb
Section 5 Cirrus Design Performance Data SR20 Takeoff Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 20° C • Mixture........Full Rich Weight........3000 LB • Flaps........... 50% Pressure Altitude....1750 FT • Airspeed ....Best Rate of Climb Climb Airspeed.....
Page 141: Enroute Climb Gradient
Cirrus Design Section 5 SR20 Performance Data Enroute Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ......... Full Rich Weight ........3000 LB • Flaps ........0% (UP) Pressure Altitude ....4200 FT •...
Page 142: Enroute Rate Of Climb
Section 5 Cirrus Design Performance Data SR20 Enroute Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 10° C • Mixture........Full Rich Weight........3000 LB • Flaps........0% (UP) Pressure Altitude....6500 FT • Airspeed ....Best Rate of Climb Climb Airspeed.....
Page 143: Enroute Rate Of Climb Vs Density Altitude
Cirrus Design Section 5 SR20 Performance Data Enroute Rate of Climb Vs Density Altitude Conditions: • Power ....................Full Throttle • Mixture ....................... Full Rich • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb 15,000 14,000 13,000 12,000...
Page 144: Time, Fuel And Distance To Climb
Section 5 Cirrus Design Performance Data SR20 Time, Fuel and Distance to Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ......ISA • Mixture........Full Rich Weight........3000 LB • Fuel Density..... 6.0 LB/GAL Airport Press ......1000 FT • Weight ........3000 LB Pressure Altitude....
Page 145: Cruise Performance
Cirrus Design Section 5 SR20 Performance Data Cruise Performance Conditions: Example: • Mixture ......Best Power Outside Air Temp .......29° C • Cruise Weight......2600 LB RPM .........2700 RPM • Winds ..........Zero Cruise Press Alt....8000 FT Note: Subtract 10 KTS if nose wheel fairings % Power (22.2 MAP) ....73%...
Page 146 Section 5 Cirrus Design Performance Data SR20 Cruise Performance 8000 Feet Pressure Altitude ISA - 30° C (-31° C) ISA (-1° C) ISA + 30° C (29° C) KTAS KTAS KTAS 2700 22.2 12.9 11.6 11.4 2500 22.2 11.4 11.0 10.6...
Page 147 Cirrus Design Section 5 SR20 Performance Data Range / Endurance Profile Conditions: Example: • Weight ........3000 LB Power Setting ......65% • Temperature ....Standard Day Takeoff Press Alt ....2000 FT • Winds ..........Zero Cruise Press Alt....6000 FT • Mixture ......See Tables •...
Page 148 Section 5 Cirrus Design Performance Data SR20 Range / Endurance Profile 65% POWER Mixture = Best Power Airspee Press Climb Fuel Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 46.3 10.5 13.0 2000 45.7 10.5 13.1...
Page 149: Balked Landing Climb Gradient
Cirrus Design Section 5 SR20 Performance Data Balked Landing Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ......... Full Rich Weight ........2500 LB • Flaps ........ 100% (DN) Pressure Altitude ....2000 FT •...
Page 150: Balked Landing Rate Of Climb
Section 5 Cirrus Design Performance Data SR20 Balked Landing Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 20° C • Mixture........Full Rich Weight........2500 LB • Flaps.........100% (DN) Pressure Altitude....4000 FT • Climb Airspeed ......Noted Climb Airspeed.....
Page 151: Landing Distance
Cirrus Design Section 5 SR20 Performance Data Landing Distance Conditions: Example: • Technique ......Normal Outside Air Temp ......10°C • Winds ..........Zero Weight ........2900 LB • Runway ........Paved Pressure Altitude ....2000 FT • Flaps......... 100% Headwind ........Zero •...
Page 152 Section 5 Cirrus Design Performance Data SR20 Landing Distance WEIGHT = 2900 LB Headwind: Subtract 10% per each Speed over 50 Ft Obstacle = 75 KIAS 13 knots headwind. Flaps - 100% · Idle · Dry, Level Paved Tailwind: Add 10% for each 2 knots Surface tailwind up to 10 knots.
Page 153 Cirrus Design Section 6 SR20 Weight and Balance Section 6 Weight and Balance Table of Contents Introduction ..................6-3 Airplane Weighing Form ..............6-6 Airplane Weighing Procedures ............6-7 Weight & Balance Record ............. 6-10 Loading Instructions ..............6-12 Center of Gravity Limits ..............6-14 Weight &...
Page 154 Section 6 Cirrus Design Weight and Balance SR20 Intentionally Left Blank P/N 11934-003 Revision A3...
Page 155: Introduction
Cirrus Design Section 6 SR20 Weight & Balance Introduction This section describes the procedure for establishing the basic empty weight and moment of the airplane. Sample forms are provided for reference. Procedures for calculating the weight and moment for various operations are also provided. A comprehensive list of all equipment available for this airplane is included at the back of this section.
Page 156 Section 6 Cirrus Design Weight & Balance SR20 350.2" WATER LINE (WL) 165.5" 222.0" 100.0" 55.6" 38.3" WL100 NOTE Reference Datum located at fuselage station 0.0". 157.5" (FS) FUSELAGE STATION LEMAC FS 132.9" RBL 210.9" RBL 87.7" MAC 48.4" Typical LBL RBL 77.3"...
Page 157 Cirrus Design Section 6 SR20 Weight & Balance Spirit Level LONGITUDINAL LEVELING Spirit Level Straight Edge Straight Edge Straight Edge Spacer Spacer Block Block Door Sill Door Sill LATERAL LEVELING SR20_FM06_1021A Figure 6-2 Airplane Leveling P/N 11934-003 Revision A2...
Page 158: Airplane Weighing Form
Section 6 Cirrus Design Weight & Balance SR20 Airplane Weighing Form REF DATUM FS 0.0 FS 100.0 FS 145.0 WL 100.0 A = x + 100 B = A - y y = ____________ Measured x = ____________ Measured SR20_FM06_1441...
Page 159: Airplane Weighing Procedures
Cirrus Design Section 6 SR20 Weight & Balance Airplane Weighing Procedures A basic empty weight and center of gravity were established for this airplane when the airplane was weighed just prior to initial delivery. However, major modifications, loss of records, addition or relocation of...
Page 160 Section 6 Cirrus Design Weight & Balance SR20 4. Measuring (Figure 6-3): a. Obtain measurement ‘x’ by measuring horizontally along the airplane center line (BL 0) from a line stretched between the main wheel centers to a plumb bob dropped from the forward side of the firewall (FS 100).
Page 161 Cirrus Design Section 6 SR20 Weight & Balance The above procedure determines the airplane Basic Empty Weight, moment, and center of gravity in inches aft of datum. C.G. can also be expressed in terms of its location as a percentage of the airplane Mean Aerodynamic Cord (MAC) using the following formula: ÷...
Page 162: Weight & Balance Record
Section 6 Cirrus Design Weight & Balance SR20 Weight & Balance Record Use this form to maintain a continuous history of changes and modifications to airplane structure or equipment affecting weight and balance: Serial Num: Reg. Num: Page Item Weight Change...
Page 163 38.5" 25.0" 16.0" 20.0" 10.5" 32.0" 39.0" 33.4" 20.0" 33.3" 5.0" 21.0" CABIN DOOR BAGGAGE DOOR OPENING OPENING SR20 FM06 1019 Location Length Width Height Volume Cabin 122” 49.3” 49.7 137 cu ft Baggage 36” 39.8” 38.5” 32 cu ft...
Page 164: Loading Instructions
Section 6 Cirrus Design Weight & Balance SR20 Loading Instructions It is the responsibility of the pilot to ensure that the airplane is properly loaded and operated within the prescribed weight and center of gravity limits. The following information enables the pilot to calculate the total weight and moment for the loading.
Page 165 Cirrus Design Section 6 SR20 Weight & Balance • The total moment/1000 must not be above the maximum or below the minimum moment/1000 for the Takeoff Condition Weight as determined from the Moment Limits chart or table (Figure 6-9). P/N 11934-003...
Page 166: Center Of Gravity Limits
Section 6 Cirrus Design Weight & Balance SR20 Center of Gravity Limits The charts below depict the airplane center-of-gravity envelope in terms of inches aft of the reference datum and as a percentage of the Mean Aerodynamic Cord (MAC). The relationship between the two is detailed in the weighing instructions.
Page 167: Weight & Balance Loading Form
Cirrus Design Section 6 SR20 Weight & Balance Weight & Balance Loading Form Serial Num: ________________ Date: ________________________ Reg. Num: _________________ Initials: ______________________ Weight Moment/ Item Description 1000 Basic Empty Weight Includes unusable fuel & full oil Front Seat Occupants Pilot &...
Page 168: Loading Data
Section 6 Cirrus Design Weight & Balance SR20 Loading Data Use the following chart or table to determine the moment/1000 for fuel and payload items to complete the Loading Form (Figure 6-7). Fuel Fwd Pass Loading Chart Aft Pass Baggage...
Page 169: Moment Limits
Cirrus Design Section 6 SR20 Weight & Balance Moment Limits Use the following chart or table to determine if the weight and moment from the completed Weight and Balance Loading Form (Figure 6-7) are within limits. 3000 2800 2600 2400...
Page 170: Equipment List
Section 6 Cirrus Design Weight & Balance SR20 Equipment List This list will be determined after the final equipment has been installed in the aircraft. 6-18 P/N 11934-003 Reissue A...
Page 171 Cirrus Design Section 7 SR20 Airplane Description Section 7 Airplane and Systems Description Table of Contents Introduction ..................7-5 Airframe ..................7-6 Fuselage ..................7-6 Wings................... 7-6 Empennage ................. 7-7 Flight Controls ................. 7-8 Elevator System................7-8 Aileron System................7-10 Rudder System ................
Page 172 Section 7 Cirrus Design Airplane Description SR20 Cabin Doors ................7-36 Baggage Compartment..............7-38 Seats..................7-38 Windshield and Windows............7-39 Cabin Safety Equipment ............7-40 Engine ...................7-43 Engine Oil System ..............7-43 Engine Cooling................7-43 Engine Fuel Injection ..............7-44 Engine Air Induction System............7-44 Engine Fuel Ignition ..............7-44 Engine Exhaust................7-45...
Page 173 Section 7 Cirrus Design Airplane Description SR20 Interior Lighting ................7-76 Instrument Lights ............... 7-76 Panel Flood Lights ..............7-76 Reading Lights................7-76 Overhead Dome Light..............7-77 Environmental System ..............7-77 Cabin Heat Control ..............7-79 Cabin Cooling Control..............7-79 Cabin Air Selector..............
Page 174 Section 7 Cirrus Design Airplane Description SR20 Intentionally Left Blank P/N 11934-003 Revision A5...
Page 175: Introduction
Cirrus Design Section 7 SR20 Airplane Description Introduction This section provides a basic description and operation of the standard airplane and its systems. Optional equipment described within this section is identified as optional. • Note • Some optional equipment, primarily avionics, may not be described in this section.
Page 176: Airframe
SR20 Airframe Fuselage The SR20 monocoque fuselage is constructed primarily of composite materials and is designed to be aerodynamically efficient. The cabin area is bounded on the forward side by the firewall at fuselage station 100, and on the rear by the aft baggage compartment bulkhead at fuselage station 222.
Page 177: Empennage
Cirrus Design Section 7 SR20 Airplane Description fuselage. The main wing spar passes under the fuselage below the two front seats and is attached to the fuselage in two locations. The rear shear webs are attached to the fuselage sidewalls just aft of the rear seats.
Page 178: Flight Controls
Airplane Description SR20 Flight Controls The SR20 uses conventional flight controls for ailerons, elevator and rudder. The control surfaces are pilot controlled through either of two single-handed side control yokes mounted beneath the instrument panel. The location and design of the control yokes allow easy, natural use by the pilot.
Page 179 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1461 Figure 7-1 Elevator Control System P/N 11934-003 Revision A5...
Page 180: Aileron System
Section 7 Cirrus Design Airplane Description SR20 Aileron System The ailerons provide airplane roll control. The ailerons are of conventional design with skin, spar and ribs manufactured of aluminum. Each aileron is attached to the wing shear web at two hinge points.
Page 181 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1462 Figure 7-2 Aileron Control System P/N 11934-003 7-11 Revision A5...
Page 182: Rudder System
Control Locks The Cirrus SR20 control system is not equipped with gust locks. The trim spring cartridges have sufficient power to act as a gust damper without rigidly locking the position.
Page 183 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1463 Figure 7-3 Rudder Control System P/N 11934-003 7-13 Revision A5...
Page 184: Trim Systems
Section 7 Cirrus Design Airplane Description SR20 Trim Systems Roll and pitch trim are provided by adjusting the neutral position of a compression spring cartridge in each control system by means of an electric motor. The electric roll trim is also used by the autopilot to position the ailerons.
Page 185: Yaw Trim System
Cirrus Design Section 7 SR20 Airplane Description Yaw Trim System Yaw trim is provided by spring cartridge attached to the rudder pedal torque tube and console structure. The spring cartridge provides a centering force regardless of the direction of rudder deflection. The yaw trim is ground adjustable only.
Page 186: Flight Deck Arrangement
Temperature controls are located on the right side below the engine instruments. The SR20 uses standard flight instruments arranged in the 'basic-six' pattern. They include: Airspeed Indicator Attitude Gyro...
Page 187: Center Console
Cirrus Design Section 7 SR20 Airplane Description Serials 1337 and subsequent: The airplane is equipped with an Avidyne FlightMax Entegra-Series Primary Flight Display (PFD). The PFD is a 10.4” landscape-oriented display intended to be the primary display of primary flight parameter information (attitude, airspeed, heading, and altitude) to the pilot.
Page 188 Section 7 Cirrus Design Airplane Description SR20 TEMP 1500 1400 AIRSPEED ALTIMETER 3 KNOTS CIRRUS TRIM VERTICAL TURN COORDINATO R SPEED 2 MIN ALT AIR PULL ON ALT STATIC SOURCE NORMAL PARK BRAKE PULL ON FUEL Legend 1. Flight Instrument Panel 11.
Page 189 Cirrus Design Section 7 SR20 Airplane Description FASTEN SEATBELTS NO SM OKING ALTITUDE GPH 16000 12000 8000 4000 MAX POWER FUEL FLOWS AMMETER SELECT ALT 1 ALT 2 BATT ALT AIR PULL ON ALT STATIC SOURCE NORMAL PARK BRAKE PULL ON...
Page 190 Section 7 Cirrus Design Airplane Description SR20 ALT AIR PULL ON ALT STATIC SOURCE NORMAL PARK BRAKE PULL ON FUEL Legend 1. Start/Ignition Key Switch 9. Temperature/Ventilation Controls 18. Left Side Console 2. Annunciator Panel 10. Control Yoke · Circuit Breaker Panel 3.
Page 191: Flight Instruments
Cirrus Design Section 7 SR20 Airplane Description Flight Instruments • Note • For additional information on instrument limit markings, refer to Section 2, Limitations. Primary Flight Display - Serials 1337 and Subsequent The Primary Flight Display (PFD) provides the functions of the attitude...
Page 192 Section 7 Cirrus Design Airplane Description SR20 PFD 2 MAIN BUS 2 PFD 1 ESSENTIAL BUS #1 GNS-430 PITOT STATIC Avidyne PFD #2 GNS-430 OAT Sensor / Magnetometer Data Aquisition Unit Flight Director System (Optional) STEC System 55x Autopilot Avidyne MFD...
Page 193 Cirrus Design Section 7 SR20 Airplane Description Attitude Direction Indicator (ADI) Air Data The airspeed tape to the left of the main ADI begins indicating at 20 Knots Indicated Airspeed (KIAS) and is color-coded to correspond with airspeeds for V , and V .
Page 194 Section 7 Cirrus Design Airplane Description SR20 13 14 AP RDY 24.0 M-BUS 4900 FT 24.0 E-BUS 5000 4900 4700 Power 4600 29.92" Hdg Bug 037°/ 7 108.10 VLOC 1 005° CRS 020° Alt Bug Bearing DTK 020° 4900 FT GPS 1 62.2 NM...
Page 195 Cirrus Design Section 7 SR20 Airplane Description Horizontal Situation Indicator (HSI) Heading Data Magnetic heading is represented in boxed numeric form at the top of the compass rose. Heading rate (Rate of Turn Indicator) takes the form of a blue arcing arrow that begins behind the magnetic heading indicator and moves left or right accordingly.
Page 196: Attitude Indicator
Section 7 Cirrus Design Airplane Description SR20 Attitude Indicator • Note • Serials 1337 subsequent with standard configuration: The airplane is not equipped with a standby attitude indicator. Serials 1337 and subsequent without SRV configuration: The standby attitude indicator is mounted on the LH bolster panel.
Page 197: Airspeed Indicator
Cirrus Design Section 7 SR20 Airplane Description Airspeed Indicator • Note • Serials 1337 and subsequent: The standby airspeed indicator is mounted on the LH bolster panel and shows only indicated airspeed. Indicated and true airspeeds are indicated on a dual-scale, internally lit precision airspeed indicator installed in the pilot’s instrument panel.
Page 198: Altimeter
Section 7 Cirrus Design Airplane Description SR20 Altimeter • Note • Serials 1337 and subsequent: The standby altimeter is mounted on the LH bolster panel. Airplane altitude is depicted on a conventional, three-pointer, internally lit barometric altimeter installed in the pilot's instrument panel. The instrument senses the local barometric pressure adjusted for altimeter setting and displays the result on the instrument in feet.
Page 199: Directional Gyro
Cirrus Design Section 7 SR20 Airplane Description Avionics Configuration 2.2: The electric turn coordinator, installed in the instrument panel, displays roll information and provides roll data to the System 55X autopilot. The instrument and power supplies are as described above.
Page 200: Course Deviation Indicator
Section 7 Cirrus Design Airplane Description SR20 Course Deviation Indicator • Note • Serials 1337 and subsequent: The Course Deviation Indicator is integrated into the PFD. Avionics Configuration 2.0 and 2.1: The Course Deviation Indicator (CDI) displays navigation information from the GPS navigator. The CDI displays GPS track deviation on a single deviation bar instrument.
Page 201: Horizontal Situation Indicator
Cirrus Design Section 7 SR20 Airplane Description Horizontal Situation Indicator • Note • Serials 1337 and subsequent: The Horizontal Situation Indicator is integrated into the PFD. Avionics Configuration 2.1: The Century NSD-1000 is a conventional HSI that provides gyro stabilized, magnetically slaved, heading information, a pictorial VOR/ LOC display with a conventional course arrow, and glideslope presentation.
Page 202 Section 7 Cirrus Design Airplane Description SR20 Avionics Configuration 2.2: The Sandel SN3308 combines the functions of an HSI, an RMI, a full color moving map, a Stormscope display, GPS annunciator, and 3- light marker beacon indicators. Compass information is derived from a remote directional gyro and a flux detector.
Page 203: Magnetic Compass
Cirrus Design Section 7 SR20 Airplane Description The SN3308 detects and warns of abnormal conditions such as flagged navigation receivers and failed directional gyro or flux detector. It also monitors its own internal temperature and provides warnings for over-temperature or loss of cooling conditions.
Page 204: Wing Flaps
Section 7 Cirrus Design Airplane Description SR20 Wing Flaps The electrically controlled, single-slotted flaps provide low-speed lift enhancement. Each flap is manufactured of aluminium and connected to the wing structure at three hinge points. Rub strips are installed on the top leading edge of each flap to prevent contact between the flap and wing flap cove.
Page 205 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1460 Figure 7-7 Wing Flaps P/N 11934-003 7-35 Revision A5...
Page 206: Landing Gear
Section 7 Cirrus Design Airplane Description SR20 Landing Gear Main Gear The main landing gear are bolted to composite wing structure between the wing spar and shear web. The landing gear struts are constructed of composite material for fatigue resistance. The composite construction is both rugged and maintenance free.
Page 207 Cirrus Design Section 7 SR20 Airplane Description DEFROST AIR OUTLETS STALL WARNING HORN FIRE EXTINGUISHER (UNDER PILOT'S SEAT) OVERHEAD LIGHT AND SWITCH DOOR HANDLE EGRESS HAMMER (IN ARMREST) CABIN SPEAKER PASSENGER FRESH AIR OUTLET OVERHEAD LIGHT AND SWITCH TIEDOWN LOOPS...
Page 208: Baggage Compartment
Section 7 Cirrus Design Airplane Description SR20 Baggage Compartment The baggage compartment door, located on the left side of the fuselage aft of the wing, allows entry to the baggage compartment. The baggage door is hinged on the forward edge and latched on the rear edge.
Page 209: Windshield And Windows
Cirrus Design Section 7 SR20 Airplane Description adjusted through the seat position control located below the forward edge of the seat cushion. The seat track is angled upward for forward travel so that shorter people will be positioned slightly higher as they adjust the seat forward.
Page 210: Cabin Safety Equipment
Section 7 Cirrus Design Airplane Description SR20 Cabin Safety Equipment Passenger Restraints Integrated seat belt and shoulder harness assemblies with inertia reels are provided for the pilot and each passenger. The rear seat belts are attached to fittings on the floorboard and the forward seat belts are attached to the seat frame.
Page 211 Cirrus Design Section 7 SR20 Airplane Description 3. Grasp the seat belt tabs outboard of the link and buckle and pull to tighten. Buckle should be centered over hips for maximum comfort and safety. 4. Restraint harnesses should fit snug against the shoulder with the lap buckle centered and tightened around the hips.
Page 212 Section 7 Cirrus Design Airplane Description SR20 cabin by opening air vents and unlatching door. Close vents and door after fumes clear. The extinguisher must be visually inspected before each flight to assure that it is available, charged, and operable. The preflight inspection consists of ensuring that the nozzle is unobstructed, the pin has not been pulled, and the canister has not been damaged.
Page 213: Engine
SR20 Airplane Description Engine The SR20 is powered by a Teledyne Continental IO-360-ES, six- cylinder, normally aspirated, fuel-injected engine de-rated to 200 hp at 2,700 RPM. The engine has a 2000-hour Time Between Overhaul (TBO). Dual, conventional magnetos provide ignition.
Page 214: Engine Fuel Injection
Section 7 Cirrus Design Airplane Description SR20 the engine compartment through two vents in the aft portion of the cowling. No movable cowl flaps are used. Engine Fuel Injection The multi-nozzle, continuous-flow fuel injection system supplies fuel for engine operation. An engine driven fuel pump draws fuel from the selected wing tank and passes it to the mixture control valve integral to the pump.
Page 215: Engine Exhaust
Cirrus Design Section 7 SR20 Airplane Description Engine Exhaust Engine exhaust gases are routed through a dual tuned exhaust system. After leaving the cylinders, exhaust gases are routed through the exhaust manifold, through mufflers located on either side of the engine, and then overboard through exhaust pipes exiting through the lower cowling.
Page 216: Alternate Air Control
Engine Indicating The SR20 is equipped with engine instrumentation and warning lights to monitor the engine performance. • Note • For additional information on instrument limit markings, refer to Section 2, Limitations.
Page 217 Cirrus Design Section 7 SR20 Airplane Description Serials 1268 through 1581: The engine instruments are located on the right side of the instrument panel and the oil temperature/pressure warning light is located in the annunciator panel immediately in front of the pilot.
Page 218 Section 7 Cirrus Design Airplane Description SR20 FUEL Start / Ignition Switch Serials 1005 thru 1336: Controls Switch is located on the left bolster panel. Alternate Air Control Serials 1005 thru 1581. LEGEND 1. Power Lever 6. CHT 2. Mixture Control 7.
Page 219 Cirrus Design Section 7 SR20 Airplane Description LOW VOLTS FUEL PITOT HEAT ALT 1 ALT 2 Annunciator Panel Primary Flight Display 4,9,8 LEGEND 4. Tachometer Multifunction Display 5. EGT (shown with EMax) 6. CHT (shown with EMax) 7. Oil Temperature 8.
Page 220 Section 7 Cirrus Design Airplane Description SR20 Tachometer Serials 1268 through 1581: A 2¼” tachometer is mounted on the right instrument panel adjacent to the other engine instruments. The tachometer pointer sweeps a scale marked from 0 to 3500 RPM in 100 RPM increments.
Page 221 Cirrus Design Section 7 SR20 Airplane Description signal from a temperature sensor mounted in the #6 cylinder head on the left side of the engine. Serials 1582 and subsequent: Exhaust Gas Temperature (EGT) and Cylinder Head Temperature (CHT) readings are displayed on the MFD as vertical bars that ascend and descend respective to increasing and decreasing temperatures.
Page 222 Section 7 Cirrus Design Airplane Description SR20 The Oil Pressure pointer sweeps a scale marked from 0 psi to 100 psi. The Oil Pressure indicator receives a pressure signal from an oil pressure sensor mounted at the aft end of the engine below the oil cooler.
Page 223 Cirrus Design Section 7 SR20 Airplane Description 28 VDC for instrument operation is supplied through the 5-amp ENGINE INST circuit breaker on Main Bus #1. The Fuel Flow pointer sweeps a scale marked from 0 to 30 Gal/Hr. The electrically operated Fuel Flow indicator receives a fuel-flow rate...
Page 224 Section 7 Cirrus Design Airplane Description SR20 28 VDC for the digital instrument operation is supplied through the 2- amp ANNUN / ENGINE INST circuit breaker on the Essential Bus. Oil Warning Light The red OIL warning light in the annunciator panel comes on to indicate either high oil temperature or low oil pressure.
Page 225: Propeller
Cirrus Design Section 7 SR20 Airplane Description Propeller The airplane is equipped with a constant-speed, aluminum-alloy propeller with a governor. The airplane is available with the standard two-blade (76” diameter) propeller or an optional three-blade (74” diameter) propeller. The propeller governor automatically adjusts propeller pitch to regulate propeller and engine RPM.
Page 226: Fuel System
Section 7 Cirrus Design Airplane Description SR20 Fuel System A 56-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 30.3-gallon capacity (28- gallon usable) vented integral fuel tank in each wing, a fuel collector/ sump in each wing, a three-position selector valve, an electric boost pump, and an engine-driven fuel pump.
Page 227 Cirrus Design Section 7 SR20 Airplane Description ANNUNCIATOR FUEL FUEL QUANTITY VENT VENT FILLER FILLER INDICATOR L. WING TANK R. WING TANK R. WING L. WING COLLECTOR COLLECTOR SELECTOR VALVE FLAPPER FLAPPER VALVE VALVE DRAIN (5 PLACES) FIREWALL ELECTRIC BOOST...
Page 228: Fuel Selector Valve
Section 7 Cirrus Design Airplane Description SR20 The airplane may be serviced to a reduced capacity to permit heavier cabin loadings. This is accomplished by filling each tank to a tab visible below the fuel filler, giving a reduced fuel load of 13 gallons usable in each tank (26 gallons total usable in all flight conditions).
Page 229: Fuel Quantity Indicator
Cirrus Design Section 7 SR20 Airplane Description Fuel Quantity Indicator A dual reading 2¼” fuel quantity indicator is installed on the console immediately forward of the fuel selector valve. The LEFT pointer indicates left tank fuel quantity and sweeps a scale marked from 0 to 28 U.S.
Page 230 Section 7 Cirrus Design Airplane Description SR20 Serials 1005 thru 1581. LEGEND 1. Fuel Pump Switch 2. Fuel Quantity Gage 3. Fuel Selector Valve 4. Fuel Flow SR20_FM07_2225 Figure 7-11 Fuel System Controls and Indicating (Sheet 1 of 2) 7-60...
Page 231 Cirrus Design Section 7 SR20 Airplane Description LOW VOLTS FUEL PITOT HEAT ALT 1 ALT 2 Annunciator Panel Primary Flight Display LEGEND Multifunction Display 4. Fuel Flow 5. Fuel Used (EMax only) 6. Fuel Remaining (EMax only) 7. Time Remaining (EMax only) 8.
Page 232: Fuel Flow Indication
Section 7 Cirrus Design Airplane Description SR20 Fuel Flow Indication Serials 1268 through 1581: Fuel flow indication is integral to the combination Fuel Flow/Manifold Pressure Gage. Refer to preceding discussion on Fuel Flow and Manifold Pressure Gage for complete description of fuel flow indication.
Page 233: Boost Pump Switch
Cirrus Design Section 7 SR20 Airplane Description Boost Pump Switch Boost pump operation and engine prime is controlled through the Fuel Pump BOOST-PRIME switch located adjacent to the fuel selector valve. The PRIME position is momentary and the BOOST position is selectable.
Page 234: Brake System
Section 7 Cirrus Design Airplane Description SR20 Brake System The main wheels have hydraulically operated, single-disc type brakes, individually activated by floor mounted toe pedals at both pilot stations. A parking brake mechanism holds induced hydraulic pressure on the disc brake for parking.
Page 235 Cirrus Design Section 7 SR20 Airplane Description Parking Brake • Caution • Do not pull the PARK BRAKE knob in flight. If a landing is made with the parking brake valve set, the brakes will maintain any pressure applied after touchdown.
Page 236 Section 7 Cirrus Design Airplane Description SR20 RESERVOIR MIL-H-5606 FLUID ONLY RUDDER PEDAL(4) MASTER CYLINDER(4) PARKING PARKING BRAKE BRAKE VALVE KNOB CALIPER CALIPER ASSEMBLY ASSEMBLY ROTOR ROTOR (DISK) (DISK) SR20_FM07_1015 Figure 7-12 Brake System 7-66 P/N 11934-003 Revision A5...
Page 237: Electrical System
Power Generation Primary power for the SR20 is supplied by a 28-VDC, negative-ground electrical system. The electrical power generation system consists of two alternators controlled by a Master Control Unit (MCU) mounted on the left side of the firewall and two batteries for starting and electrical power storage.
Page 238: Power Distribution
Distribution Bus unless ALT 2 fails. Power Distribution The power distribution system for the SR20 consists of the Main Distribution Bus and the Essential Distribution Bus in the MCU and associated buses in the Circuit Breaker panel. The circuit breaker panel is located on the left side of the console next to the pilots right knee.
Page 239 Cirrus Design Section 7 SR20 Airplane Description RELAY ALT 1 VOLT REG 100A ALT 1 SWITCH EXTERNAL LANDING POWER LIGHT 125A LANDING LIGHT SWITCH BAT 1 BAT 1 SWITCH STARTER ALT 2 VOLT REG FUEL VOLTS PITOT ALT 1 ALT 2...
Page 240: Bat & Alt Master Switches
Section 7 Cirrus Design Airplane Description SR20 BAT & ALT Master Switches The rocker type electrical system MASTER switches are ON in the up position and OFF in the down position. The switches, labeled BAT 2, BAT 1, ALT 1, ALT 2 are located in the bolster switch panel immediately below the instrument panel.
Page 241: Avionics Power Switch
Cirrus Design Section 7 SR20 Airplane Description remove power from the alternator field, and prevent alternator restart. Avionics Power Switch A rocker switch, labeled AVIONICS, controls electrical power from the circuit breaker panel bus to the Avionics Bus. The switch is located next to the ALT and BAT Master switches.
Page 242: Ammeter Select Switch
Section 7 Cirrus Design Airplane Description SR20 outside typical operating parameters. The MFD and PFD receive the voltage signals via the DAU as measured directly off the Main and Essential Buses. In the event Main Bus voltage is less than 24.5v or exceeds 32.0v the MFD will display “Check Main Bus”...
Page 243: Alt Fail Caution Lights
Cirrus Design Section 7 SR20 Airplane Description and illuminates the warning light when the voltage is less than approximately 24.5 volts. • Note • The LOW VOLTS warning light may come on during extended low RPM operation with heavy electrical loads. Under these conditions, the light will go out at higher RPM.
Page 244: Ground Service Receptacle
Section 7 Cirrus Design Airplane Description SR20 prevented from powering the Main Buses by the isolation diode interconnecting the MCU distribution buses. Loads on circuit breaker panel Main Buses are shed by pulling the individual circuit breakers. The 15-amp AVIONICS circuit breaker on Main Bus 1 powers all loads on the Non-Essential Avionics Bus.
Page 245: Exterior Lighting
Cirrus Design Section 7 SR20 Airplane Description Exterior Lighting The airplane is equipped with standard wing tip navigation lights with integral anti-collision strobe lights. The separately controlled landing light is located in the lower cowl. Navigation Lights The airplane is equipped with standard wing tip navigation lights. The lights are controlled through the NAV light switch on the instrument panel bolster.
Page 246: Interior Lighting
Section 7 Cirrus Design Airplane Description SR20 Interior Lighting Interior lighting for the airplane consists of separately controlled incandescent overhead lights for general cabin lighting, individual lights for the pilots and passengers, and dimmable panel floodlights. The flight instrumentation and avionics equipment lights are dimmable.
Page 247: Overhead Dome Light
Cirrus Design Section 7 SR20 Airplane Description Overhead Dome Light General cabin lighting is provided by a dome light located in the headliner at the approximate center of the cabin. The dome light is controlled through the OVERHEAD light control on the instrument panel bolster.
Page 248 Section 7 Cirrus Design Airplane Description SR20 AIR INLET HEAT MUFF HVAC PLENUM CABIN HEAT/ HEAT DEFROST SELECT TEMP. CONTROL COLD WINDSHIELD DEFROST DIFFUSER FRESH AIR FRESH AIR CREW INTAKE INTAKE OUTLETS CREW OUTLETS PASSENGER PASSENGER OUTLET OUTLET FRESH AIR...
Page 249: Cabin Heat Control
Cirrus Design Section 7 SR20 Airplane Description Cabin Heat Control The amount of heated air allowed into the air mixing plenum is controlled by rotating the Cabin Heat Control, located inboard of the Cabin Air Selector. The control is mechanically linked to a door in a heater box between the heater muff and the mixing plenum.
Page 250 Section 7 Cirrus Design Airplane Description SR20 Serials 1005 thru 1336 ,1337 Serials 1337 & subs w/ PFD. thru 1422 w/o PFD. PRIMARY FLIGHT DISPLAY AIRSPEED VERTICAL SPEED INDICATOR INDICATOR ALTIMETER ALTITUDE ENCODER ALTITUDE TRANSDUCER ALTERNATE (OPTIONAL) STATIC AIR SOURCE...
Page 251: Pitot-Static System
Cirrus Design Section 7 SR20 Airplane Description Pitot-Static System The Pitot-Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage. The Pitot heat is pilot controlled through a panel-mounted switch. An internally mounted alternate static pressure source provides backup static pressure should that the primary static source becomes blocked.
Page 252: Stall Warning System
Section 7 Cirrus Design Airplane Description SR20 static pressure source is selected, refer to Section 5 airspeed calibration and altitude for corrections to be applied. Stall Warning System The airplane is equipped with an electro-pneumatic stall warning system to provide audible warning of an approach to aerodynamic stall.
Page 253: Standard Avionics
Airplane Description Standard Avionics The following paragraphs and equipment descriptions describe all standard avionic installations offered for the SR20. The avionics navigation and communication equipment are mounted in he center console and are easily accessible from either pilot seat. For detailed descriptions of specific avionic equipment, operating...
Page 254 Section 7 Cirrus Design Airplane Description SR20 • Single Navigation (VOR/LOC/GS) Receiver (GNS 430) • Mode C Transponder with Altitude Encoder (Garmin GTX 327) • Horizontal Situation Indicator • Course Deviation Indicator Avionics Configuration 2.2 - Serials 1268 through 1336: •...
Page 255: Multi-Function Display
Cirrus Design Section 7 SR20 Airplane Description • Integrated Audio System with Intercom (Garmin GMA 340) • Marker Beacon Receiver (Garmin GMA 340) • One IFR Certified GPS (Garmin GNC 420) • One VHF Communications (Garmin GNC 420) • Mode C Transponder with Altitude Encoder (Garmin GTX 327)
Page 256: Autopilot
Autopilot Avionics Configuration 2.0: The standard SR20 is equipped with an S-TEC System Twenty Autopilot. This single-axis autopilot system is a rate-based system, deriving roll axis control inputs from its electric turn coordinator. The programmer, computer, annunciators, and servo amplifier are contained entirely within the turn coordinator case.
Page 257 Cirrus Design Section 7 SR20 Airplane Description The S-Tec System Twenty Autopilot features: • Roll Stabilization. • Turn Command. • Heading Hold interfaced with DG coupled heading bug. • NAV/LOC/GPS tracking, HI and LO sensitivity. Avionics Configuration 2.1: These airplanes are equipped with an S-TEC System Thirty Autopilot.
Page 258 Section 7 Cirrus Design Airplane Description SR20 supplement for a more complete description of the autopilot, its operating modes, and additional detailed operating procedures. Refer to S-TEC-Meggit Global Positioning System Steering (GPSS) Converter Pilot’s Operating Handbook (P/N 8799) dated 8 Feb 2001 or...
Page 259: Gps Navigation
Cirrus Design Section 7 SR20 Airplane Description Refer to S-Tec Altitude Selector / Alerter (P/N 0140) Pilot’s Operating Handbook (POH), P/N 8716 (no revision or later) for full operational procedures and detailed description of operational modes of the Altitude Selector / Alerter.
Page 260 Section 7 Cirrus Design Airplane Description SR20 navigator is powered by 28 VDC through the 5-amp GPS 1 and 7.5- amp COM 1 circuit breakers on the Avionics Essential Bus. The secondary GPS navigator is powered by 28 VDC through the 7.5-amp COM 2 circuit breaker on the Avionics Non-Essential Bus.
Page 261: Communication (Com) Transceivers
Cirrus Design Section 7 SR20 Airplane Description Standard SRV configuration: The airplane is equipped with one GPS navigator. The Garmin GNS 420 navigator is designated GPS 1, and is coupled to the airplane’s Multi-Function display. The GPS navigator is powered by 28 VDC through the 5-amp GPS 1 and 7.5-amp COM 1 circuit breakers on the Avionics Essential Bus.
Page 262: Navigation (Nav) Receiver
Section 7 Cirrus Design Airplane Description SR20 panel and supplied through the 7.5-amp COM 2 circuit breaker on the Non-Essential Avionics Bus. Avionics Configuration SRV: Optional SRV configuration: An optional Garmin GNS 430 GPS transceiver is available as an upgrade to the Garmin GNS 420. The system description is identical to the Garmin GNS 420 described below.
Page 263 Cirrus Design Section 7 SR20 Airplane Description receivers and integrated controls are mounted in the Garmin GNS 430 control display. The receiver controls provide active and standby frequency indication, frequency memory storage, and knob-operated frequency selection. IDENT audio output for VOR and LOC is provided to the audio system.
Page 264: Transponder
Section 7 Cirrus Design Airplane Description SR20 Transponder The airplane is equipped with a single Garmin GTX 327 ATC Mode C (identification and altitude) transponder with squawk capability. The transponder system consists of the integrated receiver/transmitter control unit, an antenna, and an altitude encoder. The receiver/...
Page 265: Emergency Locator Transmitter
Cirrus Design Section 7 SR20 Airplane Description headsets is controlled by the individual audio selector switches on the audio control panel and adjusted for volume level by using the selected receiver volume controls. Audio Input Jack Two audio input jacks are provided on the aft portion of the center console.
Page 266: Hour Meter
Section 7 Cirrus Design Airplane Description SR20 the maintenance manual procedures. The RESET button can be used to cancel an inadvertent transmission. A 6-volt Lithium battery mounted in the panel powers the LED. The battery must be replaced at regular intervals (refer to Airplane Maintenance Manual).
Page 267: Digital Clock
Cirrus Design Section 7 SR20 Airplane Description Digital Clock Serials 1268 through 1337; The airplane is equipped with a 2¼” Davtron M803 digital clock located on the left instrument panel immediately outboard of the airspeed indicator. The clock provides Universal Time (UT), Local Time (LT), Elapsed Time (ET), Outside Air Temperature (OAT) in °C or °F, and Voltmeter functions.
Page 268 Section 7 Cirrus Design Airplane Description SR20 2. Press Control to activate count-up timer. Elapsed time counts up to 59 minutes, 59 seconds, and then switches to hours and minutes. Pressing the Control button again will reset the timer to zero.
Page 269: Cirrus Airplane Parachute System
Airplane Description Cirrus Airplane Parachute System The SR20 is equipped with a Cirrus Airplane Parachute System (CAPS) designed to bring the aircraft and its occupants to the ground in the event of a life-threatening emergency. The system is intended to...
Page 270: Activation Handle
Section 7 Cirrus Design Airplane Description SR20 deployment sequence the slider limits the initial diameter of the parachute and the rate at which the parachute inflates. As the slider moves down the suspension lines the canopy inflates. A three-point harness connects the airplane fuselage structure to the parachute.
Page 271: Deployment Characteristics
Cirrus Design Section 7 SR20 Airplane Description Attempting to activate the rocket by pushing the activation T- handle forward and down limits the force that can be applied. Pulling the activation T-handle straight down generates the greatest force. A maintenance safety pin is provided to ensure that the activation handle is not pulled during maintenance.
Page 272 Section 7 Cirrus Design Airplane Description SR20 equal to the velocity of the surface wind. In addition, surface winds may continue to drag the aircraft after ground impact. • Caution • Ground impact is expected to be equivalent to touchdown from a height of approximately 10 feet.
Page 273 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Section 8 Handling, Servicing, Maintenance Table of Contents Introduction ..................8-3 Operator’s Publications ..............8-3 Service Publications ..............8-3 Ordering Publications ..............8-4 Airplane Records and Certificates ..........8-5 Airworthiness Directives..............8-6 Airplane Inspection Periods ............8-7 Pilot Performed Preventative Maintenance .........
Page 274 Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Instrument Panel and Electronic Display Screens .....8-31 Headliner and Trim Panels ............8-31 Leather Upholstery and Seats ...........8-32 Carpets ..................8-32 P/N 11934-003 Revision A6...
Page 275: Introduction
Introduction This section provides general guidelines for handling, servicing and maintaining your Cirrus Design SR20. In order to ensure continued safe and efficient operation of your airplane, keep in contact with your Authorized Cirrus Service Center to obtain the latest information pertaining to your aircraft.
Page 276: Duluth, Mn
SR20 publications, revision service, service publication subscription service may be obtained by contacting Customer Service at Cirrus Design as follows: Cirrus Design Corporation Customer Service 4515 Taylor Circle Duluth, MN 55811 Phone: 218 727-2737 FAX: 218 727-2148 Make sure to include airplane serial number and owner’s name in all correspondence for accurate processing of your documentation needs.
Page 277: Airplane Records And Certificates
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Airplane Records and Certificates The Federal Aviation Administration (FAA) requires that certain data, certificates, and licenses be displayed or carried aboard the airplane at all times. Additionally, other documents must be made available upon request.
Page 278: Airworthiness Directives
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Airworthiness Directives The Federal Aviation Administration (FAA) publishes Airworthiness Directives (AD’s) that apply to specific aircraft and aircraft appliances or accessories. 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...
Page 279: Airplane Inspection Periods
Powerplant (A&P) mechanic holding an Inspection Authorization (IA). All Cirrus Authorized Service Centers can perform annual inspections. The inspection is listed, in detail, in Chapter 5 of the Cirrus Design SR20 Maintenance Manual. If the airplane is used commercially, in addition to the annual inspection requirement, the regulation requires that the airplane undergo a 100-hour inspection each 100 hours of flight operation.
Page 280: Pilot Performed Preventative Maintenance
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Pilot Performed Preventative Maintenance The holder of a Pilot Certificate issued under FAR Part 61 may perform certain preventive maintenance described in FAR Part 43, Appendix A. This maintenance may be performed only on an aircraft that the pilot owns or operates and which is not used in air carrier service.
Page 281 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance • Replace any hose connection, except hydraulic connections, with replacement hoses. • Clean or replace fuel and oil strainers, as well as replace or clean filter elements. • Replace prefabricated fuel lines.
Page 282: Ground Handling
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Ground Handling Application of External Power A ground service receptacle, located just aft of the cowl on the left side of the airplane, permits the use of an external power source for cold weather starting and maintenance procedures.
Page 283 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed in the rear baggage compartment or by power equipment that will not damage or excessively strain the nose gear assembly.
Page 284: Taxiing
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Taxiing Before attempting to taxi the airplane, ground personnel should be instructed and authorized by the owner to taxi the airplane. Instruction should include engine starting and shutdown procedures in addition to taxi and steering techniques.
Page 285: Parking
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Parking The airplane should be parked to protect the airplane from weather and to prevent it from becoming a hazard to other aircraft. The parking brake may release or exert excessive pressure because of heat buildup after heavy braking or during wide temperature swings.
Page 286: Tiedown
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Tiedown The airplane should be moored for immovability, security and protection. FAA Advisory Circular AC 20-35C, Tiedown Sense, contains additional information regarding preparation for severe weather, tiedown, and related information. The following procedures should be used for the proper mooring of the airplane: 1.
Page 287: Jacking
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Jacking Two jacking points are provided: one at each wing tiedown. Jack points (pads) are stowed in the baggage compartment. The airplane may be jacked using two standard aircraft hydraulic jacks at the wing jacking points and a weighted tailstand attached to the tail tiedown.
Page 288: Servicing
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Servicing Landing Gear Servicing The main landing gear wheel assemblies use 15 x 6.00 x 6, six-ply rating tires and tubes. The nose wheel assembly uses a 5.00 x 5 four- ply rating, type III tire and tube. Always keep tires inflated to the rated pressure to obtain optimum performance and maximum service.
Page 289: Tire Inflation
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance The aircraft should not be operated with overheated, damaged, or leaking brakes. Conditions include, but are not limited to: • 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.
Page 290: Propeller Servicing
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 2. Remove valve stem cap and verify tire pressure with a dial-type tire pressure gage. 3. Inflate nose tire to 40 +2/-0 psi (276 +15/-0 kPa) and main wheel tires to 53 +2/-0 psi (365 +15/-0 kPa).
Page 291 • Caution • MIL-C-6529, Type II straight mineral oil with corrosion preventive can cause coking with extended use and is not recommended by Cirrus Design for break-in or post break-in use. After 25 hours of operation and after oil consumption has stabilized,...
Page 292 Section 8 Cirrus Design Handling, Servicing, 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 Anti-Wear Formulation Aeroshell 15W50...
Page 293: Fuel System Servicing
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Fuel System Servicing After the first 25 hours of operation, then every 50-hours or as conditions dictate, the fuel filtration screen in the gascolator must be cleaned. After cleaning, a small amount of grease applied to the gascolator bowl gasket will facilitate reassembly.
Page 294 Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 2. Connect ground wire from refuel nozzle to airplane exhaust, from airplane exhaust to fuel truck or cart, and from fuel truck or cart to a suitable earth ground. 3. Place rubber protective cover over wing around fuel filler.
Page 295: Fuel Contamination And Sampling
The remainder of the fuel may be drained by opening the drain valves. Use the same precautions as when refueling airplane. Refer to the SR20 Maintenance Manual for specific procedures. P/N 11934-003 8-23...
Page 296: Battery Service
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Battery Service Access to the 24 volt Battery 1 is gained by removing the upper cowl. It is mounted to the forward right side of the firewall. The battery vent is connected to an acid resistant plastic tube that vents gases and electrolyte overflow overboard.
Page 297: Cleaning And Care
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Cleaning and Care Cleaning Exterior Surfaces • Note • Prior to cleaning, place the airplane in a shaded area to allow the surfaces to cool. The airplane should be washed with a mild soap and water. Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause corrosion of metal.
Page 298: Windscreen And Windows
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Windscreen and Windows Before cleaning an acrylic window, rinse away all dirt particles before applying cloth or chamois. Never rub dry acrylic. Dull or scratched window coverings may be polished using a special acrylic polishing paste.
Page 299: Engine Compartment
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Engine Compartment Before cleaning the engine compartment, place a strip of tape on the magneto vents to prevent any solvent from entering these units. 1. Place a large pan under the engine to catch waste.
Page 300: Landing Gear
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Landing Gear Before cleaning the landing gear, place a plastic cover or similar material over the wheel and brake assembly. 1. Place a pan under the gear to catch waste. 2. Spray or brush the gear area with solvent or a mixture of solvent and degreaser, as desired.
Page 301 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Cleaning Product Cleaning Application Supplier Mild Dishwasher Soap Fuselage Exterior and Any Source (abrasive free) Landing Gear Pure Carnauba Wax Fuselage Exterior Any Source Mothers California Gold Fuselage Exterior Wal-Mart Stores Pure Carnauba Wax...
Page 302: Cleaning Interior Surfaces
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Cleaning Interior Surfaces Seats, carpet, upholstery panels, and headliners should be vacuumed at regular intervals to remove surface dirt and dust. While vacuuming, use a fine bristle nylon brush to help loosen particles.
Page 303: Instrument Panel And Electronic Display Screens
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Instrument Panel and Electronic Display Screens The instrument panel, control knobs, and plastic trim need only to be wiped clean with a soft damp cloth. The multifunction display, primary flight display, and other electronic display screens should be cleaned with Optimax - LCD Screen Cleaning Solution as follows: •...
Page 304: Leather Upholstery And Seats
2. Wipe leather upholstery with a soft, damp cloth. 3. Soiled upholstery, may be cleaned with the approved products available from Cirrus Design. Avoid soaking or harsh rubbing. Carpets To clean carpets, first remove loose dirt with a whiskbroom or vacuum.
Page 305 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Cleaning Product Cleaning Application Supplier Interior Windscreen and Prist Prist Aerospace Windows Optimax Display Screens PhotoDon Mild Dishwasher Soap Cabin Interior Any Source (abrasive free) Leather Care Kit Leather Upholstery Cirrus Design...
Page 306 Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Intentionally Left Blank 8-34 P/N 11934-003 Revision A3...
Page 307 Supplements This section of the handbook contains FAA Approved Supplements necessary to safely and to efficiently operate the SR20 when equipped with optional systems or equipment not provided with the standard airplane or for special operations or not included in the handbook.
Page 308 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank P/N 11934-003 Reissue A...
Page 309 This Log of Supplements shows all Cirrus Design Supplements available for the SR20 at the date shown in the lower left corner. A check mark (✓) in the Part Number column in- dicates that the corresponding supplement is installed in this POH.
Page 310 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank P/N 11934-003 Revision A5...
Page 311 Includes Optional XM Radio System When the Garmin GMA 340 Audio Panel and the optional XM Radio System are installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook (Handbook).
Page 312 Section 9 Cirrus Design Supplements SR20 Section 1 - General This supplement provides detailed operating instructions for the Garmin GMA 340 Audio Selector Panel/Intercom System with internal Marker Beacon. This supplement covers the basic operating areas of the Audio Control Panel.
Page 313 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations Use of auxillary AUDIO IN entertainment input and the optionally installed XM Radio System is prohibited during takeoff and landing. Section 3 - Emergency Procedures In the event of an audio panel power failure, the audio system will revert to COM 1 for the pilot’s mic and headphones and the pilot will...
Page 314 Section 9 Cirrus Design Supplements SR20 A fail-safe circuit connects the pilot’s headset directly to the COM1 transceiver in the event of a power failure to the audio control panel or the panel is switched ‘OFF.’ Test Pressing the TEST button illuminates all Panel LEDs and the Marker Beacon Annunciators full bright.
Page 315 Cirrus Design Section 9 SR20 Supplements the copilot mic/audio source. The pilot has receive and transmit capabilities on COM1 and the copilot has receive and transmit capabilities on COM2. While split COM is active, simultaneous transmission from COM1 and COM2 is not possible. The pilot and copilot can still listen to COM3, NAV1, NAV2, DME, ADF, and MKR.
Page 316 Section 9 Cirrus Design Supplements SR20 The Audio Control Panel has provisions for up to two separate personal entertainment input (music) devices. These devices are plugged into the AUDIO INPUT jacks in the center console jack panels. Music1 is connected at the AUDIO INPUT jack near the convenience outlet.
Page 317 Cirrus Design Section 9 SR20 Supplements • Right Outer Knob – Copilot and passenger mic VOX level. CW rotation increases the amount of mic audio (VOX level) required to break squelch. Full CCW is the ‘hot mic’ position. Each microphone input has a dedicated VOX circuit to assure that only the active microphone(s) is/are heard when squelch is broken.
Page 318 Section 9 Cirrus Design Supplements SR20 button. ALL mode is active when neither PILOT or CREW have been selected. PILOT The pilot is isolated from the intercom. The pilot can hear radio and sidetone only during radio transmissions. Copilot and passengers can hear the intercom and music but not the airplane radio receptions or pilot transmissions.
Page 319 Cirrus Design Section 9 SR20 Supplements Marker beacon audio is selected by pressing the MKR push-button. If no marker beacon signal is being received, pressing the MKR push- button a second time deselects marker beacon audio. However, if marker beacon is being received, pressing the MKR push-button a second time will mute the audio but the light will continue to flash.
Page 320 Section 9 Cirrus Design Supplements SR20 XM Radio System (Optional Installation) • Note • For a detailed operating instructions, refer to the XM Radio Wireless Controller User Instructions, Document XMC050-4, original release later. software partnumber 530-00162-000 or later is required for installation of XM Radio System.
Page 321 VHF COM When a Garmin GNC 250XL GPS Navigator with VHF COM is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 322 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a Garmin GNC 250XL GPS Navigator with VHF COM, herein referred to as the “Navigator.” The GNC 250XL utilizes the Global Positioning System (GPS) satellite network to derive the airplane’s position (latitude, longitude, and altitude) and the...
Page 323 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. The Garmin GNC 250XL Pilot's Guide and Reference, P/N 190- 00067-60, Revision A dated March 1997 (or later appropriate revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the GPS Navigator.
Page 324 • Note • This supplement provides a general description of the Garmin GNC 250XL, its operation, and SR20 interface. For a detailed description of the GNC 250XL and full operation instructions refer to the Garmin GNC 250XL Pilot's Guide and Reference, P/N 190-00067-60, Revision A dated March 1997 (or later appropriate revision).
Page 325 Cirrus Design Section 9 SR20 Supplements GNC 250XL Integrated GPS/NAV/COM System This airplane is equipped with a GNC 250XL integrated GPS navigator and COM receiver. The GPS navigator consists of a GPS receiver and a Jeppesen NavData database all contained in the GNC 250XL control unit mounted in the center console.
Page 326 Section 9 Cirrus Design Supplements SR20 Communication (COM) Transceiver 250XL includes digitally-tuned integrated communications (COM) transceiver. The transceiver and integrated controls are mounted in the Garmin GNC 250XL unit and are designated COM2. The transceiver receives all narrow- and wide- band VHF communication transmissions transmitted within a frequency range of 118.000 MHz to 136.975 MHz in 25.0 kHz steps...
Page 327 S-Tec System Twenty Autopilot When the S-Tec System Twenty Autopilot is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 328 Section 9 Cirrus Design Supplements SR20 Section 1 - General This airplane is equipped with an S-TEC System Twenty Autopilot. This single-axis autopilot system is a rate-based system, deriving roll axis control inputs from its integral electric turn coordinator. The programmer, computer/amplifier, and annunciators are contained entirely within the turn coordinator case.
Page 329 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. Autopilot operation is prohibited above 180 KIAS. 2. The autopilot must not be engaged for takeoff or landing. 3. The autopilot must be disconnected in moderate or severe turbulence.
Page 330 Section 9 Cirrus Design Supplements SR20 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot and its modes. Autopilot Pre-Flight Test 1. Battery Master Switch ............... ON 2. Avionics Power Switch .............. ON Note that all autopilot annunciators, except TRIM UP and DN, illuminate.
Page 331 Cirrus Design Section 9 SR20 Supplements c. Use Autopilot Mode Selector to engage TRK HI mode and move OBS so that VOR deviation needle moves left or right. Note that control yokes follow direction of needle movement with more authority than in TRK LO mode.
Page 332 Section 9 Cirrus Design Supplements SR20 GPS Tracking and GPS Approach 1. Begin with a reliable GPS signal and CDI course needle centered, with airplane on the suggested heading to the waypoint. • Note • The airplane must be within 5° of the desired course when TRK is selected.
Page 333 Cirrus Design Section 9 SR20 Supplements Section 7 - Systems Description The airplane is equipped with an S-Tec System Twenty single-axis Automatic Flight Control System (Autopilot). The autopilot is a pure rate autopilot that uses an inclined gyro in the turn coordinator case as the primary turn and roll rate sensor.
Page 334 Section 9 Cirrus Design Supplements SR20 Depressing either control yoke trim switch will also disengage the autopilot. ST (Stabilizer) Mode - Turning the Mode Select Knob left or right in ST (Stabilizer) mode will provide left/right steering commands to the autopilot proportional to the knob displacement.
Page 335 (FAR Part 91 or FAR Part 135), this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook (Handbook). Information in this supplement either adds to, supersedes, or deletes information in the basic Handbook.
Page 336 Section 1 - General This supplement lists the approved portable oxygen systems that may be used in the SR20 when supplemental oxygen is required by the applicable operating rules, as well as provides mounting instructions and general operating procedures for all approved systems.
Page 337 Cirrus Design Section 9 SR20 Supplements Section 3 - Emergency Procedures Smoke and Fume Elimination In addition to the procedures outlined in the basic Handbook, pilot and passengers should don cannulas or masks and use oxygen at the maximum flow rate until smoke and fumes have cleared.
Page 338 Section 9 Cirrus Design Supplements SR20 Descent After airplane descends through altitude requiring oxygen: 1. Oxygen Shutoff Valve...............OFF 2. Pilot and passengers ......Stow Masks or Cannulas Section 5 - Performance No change from basic Handbook. Section 6 - Weight & Balance The weight, arm, and moment for fully charged systems (1800 –...
Page 339 Cirrus Design Section 9 SR20 Supplements INITIAL INSTALLATION Clip strap to triangular loop as shown in Detail A. Route strap over headrest, down TUFF PACK BAG the back of the seat, and forward between the cushion and seat back. Clip strap to lower triangular loop.
Page 340 Section 9 Cirrus Design Supplements SR20 OXYGEN DURATION - HOURS Fully Charged System (1800 psig at 70° F) Number of Altitude ~ Feet System Persons Typical Using O 10,000 15,000 18,000 (Liters) 2.23 1.49 1.24 XCP-180 1.12 0.75 0.62 (134) 0.74...
Page 341 Stormscope Sensor When the L-3 Avionics Systems WX500 Stormscope Sensor is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 342 Section 9 Cirrus Design Supplements SR20 Section 1 General This airplane is equipped with a L-3 Avionics Systems WX500 Stormscope Sensor. The stormscope sensor output is displayed on the Multi-Function Display (MFD). Refer to L-3 Avionics Systems WX500 Stormscope Series II Weather Mapping Sensor User’s Guide, P/N 009-11501-001 revision C or later...
Page 343 Cirrus Design Section 9 SR20 Supplements STRK or CELL – STRK will be displayed if the Strike mode is selected. In this mode, individual strikes are plotted using the ‘X’ symbol. CELL will be displayed if the CELL mode is selected. In the Cell mode a ‘+’...
Page 344 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank P/N 11934-002 Revision 1: 07-18-05...
Page 345 FAA Approved Airplane Flight Manual Supplement Garmin GTX 327 Transponder When a Garmin GTX 327 Transponder is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
Page 346 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a single Garmin GTX 327 ATC Mode A/ C (identification and altitude) transponder with squawk capability. This supplement provides complete operating instructions for the GTX 327 and does not require any additional data be carried in the airplane.
Page 347 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations No Change Section 3 - Emergency Procedures No Change Section 4 - Normal Procedures • Note • Expected coverage from the GTX 327 is limited to “line of sight.” Low altitude or aircraft antenna shielding by the airplane itself may result in reduced range.
Page 348 • Note • This supplement provides specific procedures for use of the GTX 327 Transponder in the SR20 and a general description of the unit. For a detailed description of the GTX 327, refer to GARMIN GTX 327 Mode A/C Transponder Pilots Guide, p/n 190-00187-00 Revision A (Feb 2000) or later revision.
Page 349 Cirrus Design Section 9 SR20 Supplements Mode Selector Keys The mode selector keys are located in a circular arrangement immediately to the left of the display window. The selected mode is annunciated at the left side of the display immediately adjacent to the selector keys.
Page 350 Section 9 Cirrus Design Supplements SR20 Code Selector Keys Code selection is accomplished by depressing the eight selector keys (numbered 0 - 7) located immediately below the display. Any of 4096 active identification codes can be selected. The selected code must be in accordance with instructions for IFR flight or rules applicable to transponder utilization for VFR flight.
Page 351 Cirrus Design Section 9 SR20 Supplements Reply Light The reply light is the small reverse video “R” immediately below the mode annunciation in the display window. The reply light will blink each time the transponder replies to ground interrogations. The light will remain on during the 18-second IDENT time interval.
Page 352 Section 9 Cirrus Design Supplements SR20 COUNT DOWN TIMER - The count down timer is controlled by the START / STOP key. The CRSR and “0 - 9” keys are used to set the initial time. Pressing the CLR key resets the timer to the initial value.
Page 353 Traffic Advisory System When the L-3 Avionics Systems SkyWatch 497 is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the appropriate Cirrus Design Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 354 Section 9 Cirrus Design Supplements SR20 Section 1 - General This airplane is equipped with a L-3 Avionics Systems SkyWatch SKY497 Traffic Advisory System to advise the pilot of transponder- equipped aircraft that may pose a collision threat. SkyWatch advisory information is displayed on the GARMIN 430 display.
Page 355 Cirrus Design Section 9 SR20 Supplements Section 4 - Normal Procedures After Engine Start 1. Avionics Power Switch ...............ON 2. SkyWatch will turn on, complete a self-test, and then enter the STBY mode. • Note • During the takeoff run, SkyWatch will automatically switch to operational mode approximately 8 seconds after 35 KIAS is achieved.
Page 356 Section 9 Cirrus Design Supplements SR20 Switch to Normal from the Standby Screen SkyWatch must be switched out of STBY to display traffic information. The ability to switch out of STBY on the ground is useful for scanning the airspace around the airfield prior to takeoff. Using the GNS 430 controls: 1.
Page 357 Cirrus Design Section 9 SR20 Supplements Do not maneuver solely on traffic information shown on the display. Information shown on the display is provided as an aid in visually acquiring traffic - It is not a replacement for ATC and See &...
Page 358 Section 9 Cirrus Design Supplements SR20 SkyWatch may be pilot controlled through the GNS 430 controller. STBY (standby), OPER (operational), and SELF TEST modes as well as altitude display (ABV, look up; NRM, normal: BLW, look down; or UNR, unrestricted) can be selected.
Page 359 Supplement Cirrus Design SR20 Airplanes Registered in Canada 1. This supplement is required for operation of Cirrus Design SR20 airplane serial numbers 1100 and subsequent when registered in Canada. This supplement must be attached to the applicable SR20 FAA-approved Airplane Flight Manual (P/N 11934-001 dated 31 Mar 1999 or P/N 11934-002 dated 20 Aug 2001 or later FAA-approved Flight Manual revision).
Page 360 Section 9 Cirrus Design Supplements SR20 Weight Conversion Kilograms Into Pounds Kilograms En Livres 11.0 13.2 15.4 17.6 19.8 22.0 24.3 26.5 28.7 30.9 33.1 35.3 37.5 39.6 41.9 44.1 46.3 48.5 50.7 52.9 55.1 57.3 59.5 61.7 63.9 66.1 68.3...
Page 361 Cirrus Design Section 9 SR20 Supplements Weight Conversion Kilograms x 2.205 = Pounds Pounds x 0.454 = Kilograms POUNDS KILOGRAMS Units x 10, 100, etc SR20_FM09_1510 Figure - 1 Sheet 2 of 2 P/N 11934-S17 3 of 14 Original: 10-10-01...
Page 362 Section 9 Cirrus Design Supplements SR20 Length Conversion Metres Into Feet Metres En Pieds 13.1 16.4 19.7 23.0 26.3 29.5 32.8 36.1 39.4 42.7 45.9 49.2 52.5 55.8 59.1 62.3 65.6 68.9 72.2 75.5 78.7 82.0 85.3 88.6 91.9 95.1 98.4...
Page 363 Cirrus Design Section 9 SR20 Supplements Length Conversion Metres x 3.281 = Feet Feet x 0.305 = Metres FEET METRES Units x 10, 100, etc SR20_FM09_1511 Figure - 2 Sheet 2 of 4 P/N 11934-S17 5 of 14 Original: 10-10-01...
Page 364 Section 9 Cirrus Design Supplements SR20 Length Conversion Centimetres Into Inches Centimetres En Pouces inch inch inch inch inch inch inch inch inch inch 0.39 0.79 1.18 1.58 1.97 2.36 2.76 3.15 3.54 3.94 4.33 4.72 5.12 5.51 5.91 6.30 6.70...
Page 365 Cirrus Design Section 9 SR20 Supplements Length Conversion Centimetres x 0.394 = Inches Inches x 2.54 = Centimeters INCHES CENTIMETERS Units x 10, 100, etc SR20_FM09_1989 Figure - 2 Sheet 4 of 4 P/N 11934-S17 7 of 14 Original: 10-10-01...
Page 366 Section 9 Cirrus Design Supplements SR20 Distance Conversion Statute Miles x 1.609 = Kilometers Kilometers x 0.622 = Statute Miles Statute Miles x 0.869 = Nautical Miles Nautical Miles x 1.15 = Statute Miles Nautical Miles x 1.852 = Kilometers Kilometers x 0.54 = Nautical Miles...
Page 367 Cirrus Design Section 9 SR20 Supplements Temperature Conversion • Note • • To convert from Celsius (°C) to Fahrenheit (°F), find, in the shaded columns, the number representing the temperature value (°C) to be converted. The equivalent Fahrenheit temperature is read to the right.
Page 368 Section 9 Cirrus Design Supplements SR20 Volume Conversion Litres Into Imperial Gallons Litres En Gallons Impérial Gal. Gal. Gal. Gal. Gal. Gal. Gal. Gal. Gal. Gal. 0.22 0.44 0.66 0.88 1.10 1.32 1.54 1.76 1.98 2.20 2.42 2.64 2.86 3.08 3.30...
Page 369 Cirrus Design Section 9 SR20 Supplements Volume Conversion Imperial Gallons x 4.546 = Litres Litres x 0.22 = Imperial Gallons Imperial Gallons x 1.2 = U.S. Gal. U.S. Gal. x 0.833= Imperial Gallons U.S. Gallons x 3.785 = Litres Litres x 0.264 = U.S. Gallons...
Page 370 Section 9 Cirrus Design Supplements SR20 Volume to Weight Conversion AVGAS (Specific Gravity = 0.72) Litres x 0.72 = Kilograms Kilograms x 1.389 = Litres Litres x 1.58 = Pounds Pounds x 0.633 = Litres LITRES POUNDS LITRES KILOGRAMS Units x 10, 100, etc...
Page 371 Cirrus Design Section 9 SR20 Supplements Quick Conversions In a world of U.S., Imperial, and metric measures, below is a quick way to convert from one system to another. Follow arrow and multiply; backtrack the arrow and divide. Bear in mind that the figures are...
Page 372 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 14 of 14 P/N 11934-S17 Original: 10-10-01...
Page 373 GPSS When the S-Tec System Thirty Autopilot with GPSS is installed in the Cirrus Design SR20, serials 1268 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 374 Section 9 Cirrus Design Supplements SR20 GPSS GPSS SWITCH TRIM ST HD TURN COORDINATOR 2 MIN SR20_FM09_1515 TURN COORDINATOR Figure - 1 System 30 Autopilot 2 of 14 P/N 11934-S19 Revision 1: 12-07-04...
Page 375 Cirrus Design Section 9 SR20 Supplements Section 1 - General This airplane is equipped with an S-TEC System Thirty Autopilot. This two-axis autopilot system receives roll axis control inputs from an integral electric turn coordinator and altitude information from an altitude transducer plumbed into the pitot-static system.
Page 376 Section 9 Cirrus Design Supplements SR20 Section 2 - Limitations 1. Autopilot operation is prohibited above 180 KIAS. 2. The autopilot must not be engaged for takeoff or landing. 3. The autopilot must be disengaged for missed approach, go- around, and balked landing.
Page 377 Cirrus Design Section 9 SR20 Supplements Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the basic Handbook. Do not reengage the autopilot until the malfunction has been identified and corrected. • Note • A GPSS malfunction will most likely affect the autopilot HD (Heading) mode, rendering it unusable.
Page 378 Section 9 Cirrus Design Supplements SR20 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot and its modes. Autopilot Pre-Flight Test 1. Battery Master Switch ............... ON 2. Avionics Power Switch .............. ON Note that all autopilot annunciators illuminate.
Page 379 Cirrus Design Section 9 SR20 Supplements Press and release the GPSS/HDG switch. GPSS will go out and HDG will come on. 5. Altitude Hold ................TEST a. Depress either pilot’s or copilot’s A/P ALT HOLD button (control yoke). Note that ALT (Altitude Hold) light illuminates.
Page 380 Section 9 Cirrus Design Supplements SR20 d. Depress either pilot’s or copilot’s A/P ALT HOLD button (control yoke). Note that ALT (Altitude Hold) light illuminates. e. Press Pilot A/P DISC/Trim Switch (control yoke). Note that the autopilot disengages. Move control yoke to confirm that pitch and roll control is free with no control restriction or binding.
Page 381 Cirrus Design Section 9 SR20 Supplements Manually flying the airplane off the selected altitude will not disengage altitude hold and the autopilot will command a pitch change to recapture the altitude when the control input is released. Illumination of either the TRIM UP or the TRIM DN annunciator indicates the airplane is out of trim and must be manually trimmed in the direction indicated.
Page 382 Section 9 Cirrus Design Supplements SR20 The autopilot will automatically track to the active waypoint anytime GPS 1 has a valid waypoint programmed and the pilot selects GPSS with the autopilot in the HD (Heading) mode. When operating in the GPSS mode, the autopilot does not use inputs from the HSI HDG knob or course control;...
Page 383 Cirrus Design Section 9 SR20 Supplements c. Lead the airplane around the procedure turn or holding pattern using the HSI HDG knob. d. When approaching the desired inbound course, once again select GPSS. e. Conduct remainder of the approach in the GPSS mode.
Page 384 Section 9 Cirrus Design Supplements SR20 Section 7 - Systems Description The airplane is equipped with an S-Tec System Thirty two-axis Automatic Flight Control System (Autopilot). The autopilot roll axis uses an inclined gyro in the turn coordinator case as the primary turn and roll rate sensor.
Page 385 Cirrus Design Section 9 SR20 Supplements RDY (Ready) Light – Illuminates green when autopilot is ready for engagement. When the airplane’s Batt Master switch is turned on and the rate gyro RPM is correct, the green RDY light comes on indicating the autopilot is ready for the functional check and operation.
Page 386 Section 9 Cirrus Design Supplements SR20 and the pilot should manually trim the airplane in the direction indicated. If the pilot fails to trim the airplane, the TRIM UP or TRIM DN light, as applicable, will flash. Both light are out if the airplane is in trim.
Page 387 Selector/Alerter is installed in the Cirrus Design SR20, serials 1268 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 388 The autopilot makes roll changes through the aileron trim motor and spring cartridge and makes pitch changes for altitude hold through the elevator trim motor. The SR20 installation of the S-Tec System 55X Autopilot features: • Heading Hold and Command;...
Page 389 Cirrus Design Section 9 SR20 Supplements Additionally, this installation does not utilize a CWS (Control Wheel Steering) switch or an AUTOPILOT MASTER switch. • Note • This installation utilizes the airplane’s roll trim actuator to affect steering changes. Therefore, the automatic trim function of the System 55X is not implemented.
Page 390 Section 9 Cirrus Design Supplements SR20 b. The autopilot must be disconnect during approach if course deviation exceeds 50%. The approach should only be continued by “hand-flying” the airplane. c. The autopilot must be disengaged at the Decision Height. d. 12 knot maximum crosswind component between the missed approach point and outer marker.
Page 391 Cirrus Design Section 9 SR20 Supplements SR20_FM09_1502A Figure - 1 System 55X Altitude Selector/Alerter & Autopilot Computer P/N 11934-S20 5 of 24 Revision 3: 07-18-05...
Page 392 SR20 Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the SR20 POH. Do not reengage the autopilot until the malfunction has been identified and corrected. The autopilot may be disconnected by: 1. Pressing the A/P DISC/Trim switch on the control yoke handle.
Page 393 Cirrus Design Section 9 SR20 Supplements System Failure and Caution Annunciations If any of the following failure annunciations occur at low altitude or during an actual instrument approach, disengage the autopilot, execute a go-around or missed approach as appropriate. Inform ATC of problem.
Page 394 Section 9 Cirrus Design Supplements SR20 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot and altitude selector and their respective modes. The Autopilot is integrated with the Altitude Selector/Alerter and can be operated with or without data inputs from the Altitude Selector/ Alerter.
Page 395 Cirrus Design Section 9 SR20 Supplements c. Rotate altitude selector input knob to set BARO to the nearest 0.1 inch Hg. d. Push ALT button to display ALT SEL. With a flashing SEL annunciator, rotate the selector knob to input an altitude 300 to 400 feet lower or higher than the indicated altitude.
Page 396 Section 9 Cirrus Design Supplements SR20 c. Altitude Hold ..............TEST 1.) Depress ALT button on autopilot programmer/computer. Note that ALT annunciator comes on, VS annunciator goes out, and yoke does not move. d. Overpower Test: 1.) Grasp control yoke and input left aileron, right aileron, nose up, and nose down to overpower autopilot.
Page 397 Cirrus Design Section 9 SR20 Supplements 3. Use HSI HDG bug to make heading changes as desired. Autopilot Altitude Hold Mode 1. Manually fly the airplane to the desired altitude and level off. • Note • For smoothest transition to altitude hold, the airplane rate of climb or descent should be less than 100 FPM when Altitude Hold is selected.
Page 398 Section 9 Cirrus Design Supplements SR20 3. Press the VS button on the autopilot programmer/computer to engage the vertical speed mode. When the mode is engaged, the autopilot will synchronize to and hold the vertical speed at the time the mode was engaged.
Page 399 Cirrus Design Section 9 SR20 Supplements 4. Press DTA again to accept altitude entry, the ENT annunciator will go out and the SEL annunciator will stop flashing and illuminate steady indicating that the system is in the ‘operate’ mode. • Note •...
Page 400 Section 9 Cirrus Design Supplements SR20 BARO Selection Upon initial start-up, the altitude selector enters BARO select immediately after the self-test if it is receiving a valid altitude signal. The setting can easily be entered at this time. At other times, it is necessary to select the DTA entry and BARO modes in order to adjust the BARO setting.
Page 401 Cirrus Design Section 9 SR20 Supplements height is set. As the airplane approaches within approximately 50 feet of the decision height, the alert will sound and the DH light will flash. As the airplane passes through approximately 50 feet beyond the decision height, the alert will sound and the light will flash again.
Page 402 Section 9 Cirrus Design Supplements SR20 pressing and holding HDG, and then pressing NAV once to intercept course in NAV mode or twice to intercept course in GPSS mode on the autopilot programmer/computer. When the on-course intercept turn begins the HDG mode will disengage and the annunciator will go out.
Page 403 Cirrus Design Section 9 SR20 Supplements 5. For increased sensitivity during approach or if desired for enroute tracking, press the APR button on the autopilot programmer/ computer. Both NAV and APR annunciators will be illuminated. Glideslope Intercept and Tracking 1. Begin with a reliable ILS signal selected on the NAV receiver.
Page 404 Section 9 Cirrus Design Supplements SR20 coordinator instrument, the roll axis computer receives signals from the HSI and the #1 NAV/GPS radio. The roll computer computes roll steering commands for turns, radio intercepts, and tracking. Roll axis steering is accomplished by autopilot steering commands to the aileron trim motor and spring cartridge.
Page 405 Cirrus Design Section 9 SR20 Supplements HDG (Heading) Mode – When HDG is selected, the autopilot will engage the HDG mode, fly the airplane to, and hold the heading set on the HSI. Subsequent heading changes are made using the HDG knob on the HSI.
Page 406 Section 9 Cirrus Design Supplements SR20 GS (Glideslope) – The autopilot GS function will capture and track an ILS glideslope. To arm the GS function, the following conditions must be met: (1) the NAV receiver must be tuned to the appropriate ILS frequency;...
Page 407 Cirrus Design Section 9 SR20 Supplements Altitude Selector / Alerter The altitude selector / alerter provides the autopilot with an altitude preselect function, a programmable vertical speed function, as well as provides altitude alert, decision height alert, and baro corrected altitude display.
Page 408 Section 9 Cirrus Design Supplements SR20 DTA (Data) – The data entry button is used to select data entry mode. The first time the DTA button is pressed the selector will enter the data entry mode, the ENT annunciator will come on, and the SEL annunciator will flash to indicate the system is ready to accept an altitude entry.
Page 409 Cirrus Design Section 9 SR20 Supplements ALT (Altitude) – The ALT button has two functions: Altitude Pre-select and Altitude readout. Pre-select - When the ALT button is pressed while the system is in the Data Entry (DTA) mode the SEL annunciator will flash and a new altitude can be selected by rotating the input knob CW to increase altitude and CCW to decrease altitude in thousands of feet.
Page 410 Section 9 Cirrus Design Supplements SR20 DH (Decision Height) – The DH button allows entry and arming of altitude alerting at a set decision height. To set a DH, first enter the data (DTA) entry (ENT) mode, press the DH button, and rotate the selector knob to input the desired decision height to the nearest 100 feet above the specified decision height.
Page 411 Garmin GNS 430 GPS Navigator When a Garmin GNS 430 GPS Navigator with NAV, ILS, and COM is installed in the Cirrus Design SR20, serials 1268 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
Page 412 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a Garmin GNS 430 GPS Navigator with VHF Nav, ILS, and VHF Com herein referred to as the “Navigator.” The GNS 430 is capable of providing IFR enroute, terminal, and approach navigation with position accuracies better than 15 meters.
Page 413 Cirrus Design Section 9 SR20 Supplements Section 2 – Limitations Provided the GPS Navigator is receiving adequate usable signals, it has been demonstrated capable of and has been shown to meet the accuracy specifications of: 1. VFR/IFR, enroute, terminal, and instrument approach (GPS, VOR) operations, that is, enroute, terminal, and instrument approach within the U.S.
Page 414 Section 9 Cirrus Design Supplements SR20 6. The aircraft must have other approved navigation equipment installed and operating appropriate to the route of flight. 7. The Garmin GNS 430 meets RNP5 (BRNAV) requirements of AC 90-96 and is in accordance with AC 20-138, and JAA AMJ 20X2 Leaflet 2 Revision 1, provided it is receiving usable navigation information from the GPS receiver.
Page 415 GNS 430 Integration The GNS 430 Navigator is integrated into the SR20 Avionics installation in three configurations: 1. Single GARMIN GNS 430 (GPS 1) interfaced with the CDI and MFD and a single GARMIN GNC 250XL (GPS 2) not integrated with a remote indicator.
Page 416 GPS 2 in this configuration is a GARMIN GNC 420 GPS Navigator interfaced with the CDI (VOR/LOC Indicator). This unit displays GPS data on the unit’s display panel and on the remote CDI (VOR/LOC Indicator). Refer to the SR20 POH Supplement for GARMIN GNC 420 GPS Navigator, P/N 11934-S23.
Page 417 • Note • This supplement provides a general description of the Garmin GNS 430, its operation, and SR20 interface. For a detailed description of the GNS 430 and full operation instructions refer to the Garmin GNS 430 Pilot's Guide and Reference, P/N 190- 00140-00, Revision F dated July 2000 (or later appropriate revision).
Page 418 Section 9 Cirrus Design Supplements SR20 This airplane is equipped with a GNS 430 integrated GPS navigator, NAV receiver, and COM transceiver. The GPS navigator consists of a GPS receiver, a navigation computer, and a Jeppeson NavData database all contained in the GNS 430 control unit mounted in the center console.
Page 419 Cirrus Design Section 9 SR20 Supplements Frequencies. North American and International databases are available. Database information is provided on a card that can be inserted into the card slot on the GPS unit. Subscription information is provided in a subscription packet provided with each system.
Page 420 Section 9 Cirrus Design Supplements SR20 operating is controlled through the Avionics Master Switch and supplied through the 7.5-amp COM1 circuit breaker on the Avionics Essential Bus. 10 of 10 P/N 11934-S22 Revision 1: 05-25-05...
Page 421 Garmin GNC 420 GPS Navigator When a GARMIN GNC 420 GPS Navigator with VHF COM is installed in the Cirrus Design SR20, serials 1268 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
Page 422 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a GARMIN GNC 420 GPS Navigator with VHF Com herein referred to as the “Navigator.” The GNC 420 is capable of providing IFR enroute, terminal, and approach navigation with position accuracies better than 15 meters.
Page 423 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. The GARMIN GNC 420 Pilot's Guide and Reference, P/N 190- 00140-20, Revision B dated August 2002 (or later appropriate revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the GPS Navigator.
Page 424 Section 9 Cirrus Design Supplements SR20 Section 3 - Emergency Procedures 1. If GPS Navigator information is not available or is invalid, utilize remaining operational navigation equipment as required. 2. If "RAIM NOT AVAILABLE…" or “RAIM POSITION WARNING” message is displayed, continue to navigate using the GPS equipment or revert to an alternate means of navigation appropriate to the route and phase of flight.
Page 425 • Note • This supplement provides a general description of the GARMIN GNC 420, its operation, and SR20 interface. For a detailed description of the GNC 420 and full operation instructions refer to the GARMIN GNC 420 Pilot's Guide and Reference, P/N 190-00140-20, Revision B dated August 2002 (or later appropriate revision).
Page 426 Section 9 Cirrus Design Supplements SR20 GPS Navigator The GARMIN GNC 420 GPS navigator is the secondary system (GPS 2), is IFR certified, and is coupled to the airplane’s CDI. The GARMIN GNC 420 GPS navigator is capable of providing IFR enroute, terminal, and approach navigation with position accuracies better than 15 meters.
Page 427 Cirrus Design Section 9 SR20 Supplements The COM frequency display window is at the upper left corner of the GNC 420 display. Auto-tuning can be accomplished by entering a frequency from a menu. The COM 2 antenna is located below the cabin on the airplane centerline.
Page 428 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 8 of 8 P/N 11934-S23 Revision 1: 05-25-05...
Page 429 Display When a Sandel Avionics SN3308 Navigation Display is installed in the Cirrus Design SR20, serials 1268 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 430 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a Sandel SN3308 navigation display. This SN3308 is a three-inch instrument installed in the pilot’s instrument panel, which performs the functions of a standard HSI combined with a two-pointer RMI.
Page 431 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. The Sandel Avionics SN3308 Navigation Display Pilot's Guide, SPN 90106-PG-C or later revision, must be immediately available to the flight crew when navigation is predicated on use of the Sandel SN3308 Navigation Display.
Page 432 Section 9 Cirrus Design Supplements SR20 3. The Navigation display will be active and capable of displaying data from either VOR-ILS or GPS. a. Selection of the primary navigation source between VOR-ILS 1 and GPS 1 is accomplished by pressing the NAV switch on the left side of the SN3308 Navigation Display to connect the navigation source to the HSI course pointer and the autopilot.
Page 433 Cirrus Design Section 9 SR20 Supplements the display. Redundant power sources provide 28 VDC for system operation. Power is supplied through the 5-amp HSI/PFD #1 circuit breaker on the Essential Bus and the 5-amp HSI/PFD #2 circuit breaker on Main Bus 2. Either circuit is capable of powering the Navigation Display.
Page 434 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 6 of 6 P/N 11934-S24 Original: 01-07-03...
Page 435 Winterization Kit When the Winterization Kit Inlet covers are installed in accordance with SB 2X-71-04 R3, Cirrus Design drawing 70027, or Cirrus Design drawing 70102, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot's Operating Handbook.
Page 436 Section 9 Cirrus Design Supplements SR20 Section 1 - General This airplane is equipped with removable cowl inlet airflow restrictors. Figure 1 shows installation instructions. Section 2 - Limitations Winterization Kit 1. The airplane must not be operated above 32°F when the Winterization Kit cowl inlet covers (airflow restrictors) are installed.
Page 437 Cirrus Design Section 9 SR20 Supplements Section 4 - Normal Procedures Install Cowl Inlet Airflow Restrictor (See Figure 1) 1. Loosen screw securing latch plate to inlet cover and slide latch plate inboard. 2. Position inlet cover in inlet. 3. Slide latch plate outward (behind edge of cowl) and tighten screw.
Page 438 Section 9 Cirrus Design Supplements SR20 Serials 1005 through 1422. LEGEND 1. Cowl Inlet Cover Serials 1423 and subsequent. 2. Latch Plate 3. Screw 4. Wellnut SR20_FM09_1516B Figure - 1 Cowl Inlet Installation 4 of 6 P/N 11934-S25 Revision 1: 12-07-04...
Page 439 Cirrus Design Section 9 SR20 Supplements Section 5 - Performance No Change. Section 6 - Weight & Balance Change is Negligible. Section 7 - Systems Description • Caution • Use of the inlet cover airflow restrictors above 32° F (0° C) ambient temperature may result in CHT and Oil Temperatures above the red line.
Page 440 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 6 of 6 P/N 11934-S25 Revision 1: 12-07-04...
Page 441 Cirrus Design SR20, serials 1337 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 442 • Note • The SR20 implementation of the System 55SR Autopilot does not utilize the optional remote annunciator, roll servo, yaw servo. Therefore, all references to these items in the S-Tec System 55SR POH shall be disregarded.
Page 443 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. Autopilot operation is prohibited above 180 KIAS. 2. The autopilot must not be engaged for takeoff or landing. 3. The autopilot must be disengaged for missed approach, go- around, and balked landing.
Page 444 Section 9 Cirrus Design Supplements SR20 The flaps should be extended in the approach configuration prior to the Outer Marker. No further changes in the flap configuration should be made throughout the autopilot- coupled approach. 10. The S-Tec System 55SR Autopilot Pilot’s Operating Handbook (POH), P/N 87127 dated 01 September 2003 or later, must be carried in the airplane and available to the pilot while in flight.
Page 445 Cirrus Design Section 9 SR20 Supplements S-TEC FIFTY FIVE SR REV TRIM VS + VS x 100 SR20_FM09_1996 Figure - 1 System Fifty-Five SR Autopilot P/N 11934-S27 5 of 16 Revision 2: 07-18-05...
Page 446 SR20 Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the SR20 POH. Do not reengage the autopilot until the malfunction has been identified and corrected. The autopilot may be disconnected by: 1. Pressing the A/P DISC/Trim switch on the control yoke handle.
Page 447 Cirrus Design Section 9 SR20 Supplements System Failure and Caution Annunciations If any of the following failure annunciations occur at low altitude or during an actual instrument approach, disengage the autopilot, execute a go-around or missed approach as appropriate. Inform ATC of problem.
Page 448 Section 9 Cirrus Design Supplements SR20 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot modes. • WARNING • The pilot must properly monitor and control the engine power to avoid stalling the airplane in autopilot altitude hold or vertical speed modes.
Page 449 Cirrus Design Section 9 SR20 Supplements e. Altitude Hold ..............TEST 1.) Depress ALT button on autopilot programmer/computer. Note that ALT annunciator comes on, VS annunciator goes out, and yoke does not move. Overpower Test: 1.) Grasp control yoke and input left aileron, right aileron, nose up, and nose down to overpower autopilot.
Page 450 Section 9 Cirrus Design Supplements SR20 3. Use the HDG bug to make heading changes as desired. Autopilot Altitude Hold Mode 1. Manually fly the airplane to the desired altitude and level off. • Note • For smoothest transition to altitude hold, the airplane rate of climb or descent should be less than 100 FPM when Altitude Hold is selected.
Page 451 Cirrus Design Section 9 SR20 Supplements Autopilot Vertical Speed Mode 1. Begin by manually establishing the desired vertical speed. 2. Press HDG or NAV to engage a roll mode. The associated annunciator will illuminate. • Note • A roll mode must be engaged prior to engaging a pitch mode.
Page 452 Section 9 Cirrus Design Supplements SR20 • Note • If the course needle is at full-scale deviation, the autopilot will establish the airplane on a heading for a 45° intercept with the selected course. As the airplane approaches the course, the autopilot will smoothly shallow the intercept angle.
Page 453 Cirrus Design Section 9 SR20 Supplements • Note • If the HDG bug is within 5° of center and the course deviation is less than 10%, the autopilot will immediately establish the lowest level of sensitivity and limit the turn rate to a maximum of 25% of a standard rate turn.
Page 454 Section 9 Cirrus Design Supplements SR20 All Autopilot mode selection is performed by using the mode select buttons and VS knob on the autopilot programmer/computer in the center console. Annunciators in the programmer/computer display window annunciate modes. Refer to Figure 1 for an illustration of the programmer/computer.
Page 455 Cirrus Design Section 9 SR20 Supplements APR (Approach) – When APR is selected, the autopilot provides increased sensitivity for VOR or GPS approaches. APR may also be used to provide increased sensitivity for enroute course tracking. ALT (Altitude Hold), Mode – When ALT is selected, the autopilot will hold the altitude at the time the mode was selected.
Page 456 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 16 of 16 P/N 11934-S27 Revision 2: 07-18-05...
Page 457 Supplement Garmin GTX 330 Mode S Transponder When a Garmin GTX 330 Transponder is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
Page 458 Section 9 Cirrus Design Supplements SR20 GARMIN GTX 330 IDENT FLIGHT TIME CRSR FUNC 1200 01:23:20 START STOP 1. Identification Key 5. CRSR (Cursor) 2. Mode Selector Keys 6. CLR (Clear) Key a. OFF 7. START/STOP Key b. STBY (Standby) 8.
Page 459 Cirrus Design Section 9 SR20 Supplements Section 1 - General The airplane is equipped with a single Garmin GTX 330 ATC Mode S transponder with IDENT capability. This supplement provides complete operating instructions for the GTX 330 and does not require any additional data be carried in the airplane.
Page 460 • Note • This supplement provides specific procedures for use of the GTX 330 Transponder in the SR20 and a general description of the unit. For a detailed description of the GTX 330, refer to GARMIN GTX 330 Mode S Transponder Pilots Guide, p/n 190-00207-00 Revision A (Sept 2002) or later revision.
Page 461 Cirrus Design Section 9 SR20 Supplements While providing the usual identification code and pressure altitude information as Mode A and C transponders, the Mode S transponder also uses a unique aircraft address to enhance the tracking capabilities of ATC and other Mode S transponder-equipped aircraft.
Page 462 Section 9 Cirrus Design Supplements SR20 reply to any interrogations from an ATC secondary ground surveillance radar system. This is the normal position for ground operations in the SR20. • Note • Depend on the ATC environment, STBY or GND mode is automatically entered from ALT or ON mode during landing ground roll as the groundspeed decreases through 35 knots.
Page 463 Cirrus Design Section 9 SR20 Supplements CRSR key during code entry will remove the cursor and cancel the entry. • Note • When making routine code changes, avoid inadvertent selection of code 7500 and all codes within the 7600 series (7600 –...
Page 464 Section 9 Cirrus Design Supplements SR20 Flight Time, Count Up Timer, Count Down Timer, Contrast, and Display Brightness. START/STOP Key - Starts and stops the Altitude Monitor, Count Up, Count Down, and Flight timers. In Configuration Mode, steps through functions in reverse.
Page 465 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.
Page 466 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..............
Page 467 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...
Page 468 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 4 of 4 P/N 11934-S29 Original: 05-27-04...
Page 469 Awareness Warning System When the Honeywell KGP 560 Terrain Awareness and Warning System is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 470 MFD. For specific MFD operational details, refer to the Cirrus Design Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement For Avidyne EX-Series Multifunction Flight Display, P/N 11934-S18 or 11934-S21, Original Release or later.
Page 471 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. Do not use the Terrain Awareness Display for navigation of the aircraft. The KGP 560 Terrain Awareness and Warning System is intended to serve as a situational awareness tool only and may not provide the accuracy fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions.
Page 472 Section 9 Cirrus Design Supplements SR20 Activate TAWS • Note • If the aircraft horizontal position derived from the Garmin Navigator (GPS 1) is invalid, TAWS will be inoperative and the TERR INOP annunciator will illuminate. 1. SKYWATCH/TAWS Circuit Breaker..........IN 2.
Page 473 Cirrus Design Section 9 SR20 Supplements Response To Awareness Alerts Aural “TERRAIN AHEAD” Alert Aural “OBSTACLE AHEAD” Alert Amber TERR CAUT Annunciation 1. Take positive corrective action until the alert ceases. Stop descending, or initiate a climb turn as necessary, based on analysis of all available instruments and information.
Page 474 Section 9 Cirrus Design Supplements SR20 Section 7 - Systems Description The Honeywell KGP 560 Terrain Awareness and Warning System compares GPS information from the Garmin Navigator (GPS 1) to the integrated Terrain/Obstacle Database to produce a real-time model of the surrounding terrain.
Page 475 Cirrus Design Section 9 SR20 Supplements GNS-430 TAWS Annunciator Panel GMA 340 Audio Panel Avidyne PFD KGP 560 Processor Transponder Avidyne MFD TAWS AVIONICS NON-ESSENTIAL Configuration Module SR20_FM09_2031 Figure - 1 Honeywell KGP 560 TAWS Simplified Schematic P/N 11934-002 Original: 07-03-04...
Page 476 Section 9 Cirrus Design Supplements SR20 TAWS Annunciator Panel TAWS terrain annunciations and control functions are incorporated into the Annunciator Panel. The panel consists of a momentary pushbutton switch (SELF TEST), an illuminated pushbutton switch (TERR INHIBIT), and three LEDS for Terrain Warning (TERR WARN), Terrain Caution (TERR CAUT), Terrain Inoperative (TERR INOP).
Page 477 Cirrus Design Section 9 SR20 Supplements TAWS SELF TERR TERR TERR TERR TEST INHIBIT INOP CAUT WARN SR20_FM09_2033 Annunciator Color Function SELF TEST Provides test function for TAWS TERR INHIBIT AMBER All TAWS alerting functions inhibited TERR INOP AMBER Indicates TAWS inoperative...
Page 478 Section 9 Cirrus Design Supplements SR20 MFD Terrain Awareness Display • WARNING • Do not use the Terrain Awareness Display for navigation of the aircraft. The TAWS is intended to serve as a situational awareness tool only and may not provide the accuracy fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions.
Page 479 Cirrus Design Section 9 SR20 Supplements Geometric Altitude versus Measured Sea Level An indication of MSL-G or Geometric Altitude may appear on the left side of the MFD indicating the height above Measured Sea Level (MSL) calculated from the GPS.
Page 480 Section 9 Cirrus Design Supplements SR20 Self Test Proper operation of the TAWS can be verified when the aircraft is on the ground as follows: 1. Select the TAWS page on the MFD 2. Clear all caution messages in the lower right corner 3.
Page 481 Instrumentation When the Avidyne EMax™ Engine Instrumentation system is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 482 Section 9 Cirrus Design Supplements SR20 Section 1 - General EMax™ Engine Instrumentation provides the pilot with engine parameters depicted on simulated gauges and electrical system parameters located in a dedicated region within in the EX5000C MFD display. Figure - 1 Avidyne EMax™...
Page 483 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations No Change. Section 3 - Emergency Procedures No Change. Section 4 - Normal Procedures No Change. Section 5 - Performance No Change. Section 6 - Weight & Balance Installation of the Avidyne Engine Instruments adds the following optional (Sym = O) equipment at the weight and arm shown in the following table.
Page 484 Section 9 Cirrus Design Supplements SR20 providing full-time recording critical engine performance parameters. The Engine Instruments system is powered by 28 VDC supplied through the 5-amp Engine Instruments breaker on the Main Bus 1. Refer to Avidyne FlightMax EX5000C Pilot’s Guide, P/N 600-00108-...
Page 485 Approach Charts When the Avidyne CMax™ Electronic Approach Charts system is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 486 Section 9 Cirrus Design Supplements SR20 Section 1 - General Avidyne CMax™ Electronic Approach Charts allows the pilot to view terminal procedure chart data on the EX5000C MFD. If the chart is geo-referenced, an ownship symbol and flight plan legs can be overlaid on the chart to further enhance the pilot’s situational...
Page 487 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. Do not use the CMax Approach Charts function for navigation of the aircraft. The CMax Approach Charts function is intended to serve as a situational awareness tool only. 2. The Avidyne FlightMax EX5000C Pilot’s Guide, P/N 600-00108- 000, Revision 03 or later, must be available to the pilot during all flight operations.
Page 488 Section 9 Cirrus Design Supplements SR20 Refer to Avidyne FlightMax EX5000C Pilot’s Guide, P/N 600-00108- 000, Revision 03 or later for a more complete description of CMax Approach Charts, its operating modes, and additional detailed operating procedures. P/N 11934-002 Original: 10-12-05...
Page 489 XM Satellite Weather System When the XM Satellite Weather System system is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 490 Section 9 Cirrus Design Supplements SR20 Section 1 - General The XM Satellite Weather System enhances situational awareness by providing the pilot with real time, graphical weather information depicted on the MAP page of the EX5000C MFD display. Figure - 1...
Page 491 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. Do not use the XM Satellite Weather System for navigation of the aircraft. The XM Satellite Weather System is intended to serve as a situational awareness tool only. Section 3 - Emergency Procedures No Change.
Page 492 Section 9 Cirrus Design Supplements SR20 • METARs • SIGMETs • AIRMETs • TFRs • Lightning Strikes The XM Satellite Weather System is powered by 28 VDC supplied through the 3-amp Weather/Stormscope breaker on the Non-Essential Bus. Refer to Avidyne FlightMax EX5000C Pilot’s Guide, P/N 600-00108-...
Page 493 Software Version 530-00159-000 When the Avidyne Flight Director is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 494 Section 9 Cirrus Design Supplements SR20 Section 1 - General The Flight Director system enhances situational awareness by reducing cockpit workload through providing a visual cue for the pilot to follow as indicated by the PFD’s Flight Director Steering Command Bar.
Page 495 1. The Flight Director System integrates with the Primary Flight Display (PFD) System. Adherence to the PFD imitations in the basic SR20 Pilot’s Operating Handbook is mandatory. 2. The Avidyne FlightMax Entegra-Series PFD Pilot’s Guide, P/N 600-00081-000, Revision 03, or latest revision, must be available to the pilot during all flight operations.
Page 496 Section 9 Cirrus Design Supplements SR20 the pilot is expected to actuate the flight controls as required to track the bars. The following describes push-button annunciation and related Autopilot and Flight Director status: • Autopilot off. Annunciation • Autopilot not active in either roll or pitch control.
Page 497 Cirrus Design Section 10 SR20 Safety Information Section 10 Safety Information Table of Contents Introduction ................... 10-3 Cirrus Airframe Parachute System (CAPS) Deployment ....10-4 Deployment Scenarios............... 10-4 Mid-Air Collision..............10-4 Structural Failure ..............10-4 Loss of Control ............... 10-5 Landing Required in Terrain not Permitting a Safe Landing...
Page 498 Section 10 Cirrus Design Safety Information SR20 Intentionally Left Blank 10-2 P/N 11934-003 Reissue A...
Page 499: Introduction
SR20 Safety Information Introduction The Cirrus Design SR20 is a modern, advanced technology airplane designed to operate safely and efficiently in a flight environment. However, like any other aircraft, pilots must maintain proficiency to achieve maximum safety, utility, and economy.
Page 500: Cirrus Airframe Parachute System (Caps) Deployment
Instead, possible CAPS activation scenarios should be well thought out and mentally practiced by every SR20 pilot. The following discussion is meant to guide your thinking about CAPS activation.
Page 501: Loss Of Control
Cirrus Design Section 10 SR20 Safety Information continued safe flight and landing. If it is not, CAPS activation should be considered. Loss of Control Loss of control may result from many situations, such as: a control system failure (disconnected or jammed controls); severe wake turbulence, severe turbulence causing upset, severe airframe icing, or sustained pilot disorientation caused by vertigo or panic;...
Page 502: Deployment Altitude
Section 10 Cirrus Design Safety Information SR20 However, if time and altitude are critical, and/or ground impact is imminent, the CAPS should be activated regardless of airspeed. Deployment Altitude No minimum altitude for deployment has been set. This is because the actual altitude loss during a particular deployment depends upon the airplane’s airspeed, altitude and attitude at deployment as well as...
Page 503: Landing Considerations
Cirrus Design Section 10 SR20 Safety Information Landing Considerations After a CAPS deployment, the airplane will descend at less than 1500 feet per minute with a lateral speed equal to the velocity of the surface wind. The CAPS landing touchdown is equivalent to ground impact from a height of approximately 10 feet.
Page 504: Water Landings
Section 10 Cirrus Design Safety Information SR20 If the pilot elects to touchdown with a door opened, there are several additional factors the pilot must consider: loss of door, possibility of head injury, or injury from an object coming through the open door.
Page 505: Post Impact Fire
Cirrus Design Section 10 SR20 Safety Information consider unlatching a door prior to assuming the emergency landing body position in order to provide a ready escape path should the airplane begin to sink. Post Impact Fire If there is no fire prior to touchdown and the pilot is able to shut down the engine, fuel, and electrical systems, there is less chance of a post impact fire.
Page 506: Taxiing, Steering, And Braking Practices
Section 10 Cirrus Design Safety Information SR20 Taxiing, Steering, and Braking Practices Cirrus aircraft use a castering nose wheel and rely on aerodynamic forces and differential braking for directional control while taxiing. Proper braking practices are therefore critical to avoid potential damage to the brakes.
Page 507: Brake Maintenance
Cirrus Design Section 10 SR20 Safety Information • Do not “ride the brakes”. Pilots should consciously remove pressure from the brakes while taxiing. Failure to do so results in excessive heat buildup, premature brake wear, and increased possibility of brake failure or fire.
Page 508 Section 10 Cirrus Design Safety Information SR20 Intentionally Left Blank 10-12 P/N 11934-003 Revision A6...