PILOT’S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL for the CIRRUS DESIGN SR20

7-82 Revision A1 7-83 Revision A1 7-84 Revision A1 7-85 Revision A1 7-86 Revision A1 7-87 Revision A1 7-88 Revision A1 7-89 Revision A1 7-90 Revision A1 7-91 Revision A1 7-92 Revision A1 7-93 Revision A1 7-94 Revision A1 7-95 Revision A1 Revision A1 P/N 11934-004 C Cirrus Design Pilot’s Operating Handbook SR20 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 7-96 Revision A1 7-97 Revision A1 7-98 Revision A1 7-99 Revision A1 7-100 Revision A1 7-101 Revision A1 7-102 Revision A1 7-103 Revision A1 7-104 Revision A1 7-105 Revision A1 7-106 Revision A1 7-107 Revision A1 7-108 Revision A1 8-1 Revision A1 8-2 Reissue A 8-3 Revision A1 8-4 Revision A1 8-5 Reissue A 8-6 Reissue A 8-7 Reissue A 8-8 Reissue A 8-9 Reissue A 8-10 Reissue A 8-11 Reissue A 8-12 Reissue A 8-13 Reissue A 8-14 Revision A1 8-15 Reissue A 8-16 Revision A1 8-17 Revision A1 8-18 Revision A1 8-19 Revision A1 8-20 Revision A1 8-21 Revision A1 8-22 Revision A1 8-23 Revision A1 8-24 Revision A1 8-25 Revision A1 8-26 Revision A1 8-27 Revision A1 8-28 Revision A1 8-29 Revision A1 8-30 Revision A1 8-31 Revision A1 8-32 Revision A1 8-33 Revision A1 8-34 Revision A1 8-35 Revision A1 8-36 Revision A1 9-1 Revision A1 9-2 Reissue A 10-1 Reissue A 10-2 Reissue A 10-3 Revision A1 10-4 Revision A1 10-5 Revision A1 10-6 Revision A1 10-7 Revision A1 10-8 Revision A1 10-9 Reissue A 10-10 Reissue A 10-11 Revision A1 10-12 Revision A1 Revision A1 D P/N 11934-004 Cirrus Design Pilot’s Operating Handbook SR20 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status Reissue A Intentionally Left Blank Cirrus Design Front Matter SR20 Foreword P/N 11934-004 Front Matter-1 P/N 11934-004 Front Matter-1 Foreword This Pilot’s Operating Handbook (POH) has been prepared by Cirrus Design Corporation to familiarize operators with the aircraft. Read this POH carefully. It provides operational procedures that will assure the operator obtains the performance published in the manual, data designed to allow the most efficient use of the airplane, and basic information for maintaining the airplane in a “like new” condition. • Note • All limitations, procedures, maintenance & servicing requirements, and performance data contained in this POH are mandatory for compliance with FAA operating rules and for continued airworthiness of the airplane. This POH includes the material required to be furnished to the pilot by the Federal Aviation Regulations (FARs) and additional information provided by Cirrus Design Corporation and constitutes the FAA Approved Airplane Flight Manual for the aircraft. Revision A1 Front Matter-2 P/N 11934-004 Front Matter Cirrus Design Foreword SR20 The Pilot’s Operating Handbook This Pilot’s Operating Handbook has been prepared using GAMA Specification #1 for Pilot’s Operating Handbook, Revision 2, dated 18 October 1996 as the content model and format guide. However, some deviations from this specification were made for clarity. The POH is presented in loose-leaf form for ease in inserting revisions and is sized for convenient storage. Tabbed dividers throughout the POH allow quick reference to each section. Logical and convenient Tables of Contents are located at the beginning of each section to aid in locating specific data within that section. The POH is divided into ten sections as follows: Section 1................................................................................... General Section 2...............................................................................Limitations Section 3.......................................................... Emergency Procedures Section 3A .......................................................... Abnormal Procedures Section 4................................................................. Normal Procedures Section 5...................................................................Performance Data Section 6...........................................Weight & Balance/Equipment List Section 7..............................................Airplane & Systems Description Section 8........................................ Handling, Servicing & Maintenance Section 9........................................................................... Supplements Section 10.................................................................Safety Information The data presented in this POH is the result of extensive flight tests and is approved by the Federal Aviation Administration. However, as new procedures or performance data are developed, the POH will be revised. • Note • It is the responsibility of the owner to ensure that the Pilot’s Operating Handbook is current at all times. Therefore, it is very important that all revisions be properly incorporated into this POH as soon as they are available. Revision A1 Cirrus Design Front Matter SR20 Foreword P/N 11934-004 Front Matter-3 P/N 11934-004 Front Matter-3 Revising the Pilot’s Operating Handbook Two types of revisions may be issued for this Handbook: Temporary and Numbered. 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. All the information needed to properly file a temporary revision is included on the revision itself. Typically, a temporary revision is superseded and replaced by the next numbered revision. Numbered revisions are printed on white paper, normally cover several subjects, and are issued as general updates to the POH. Each numbered revision includes an “Instruction Sheet,” a “List of Effective Pages”, and a “Revision Highlights” page. The “Instruction Sheet” is intended to assist the manual holder in removing superseded pages and inserting new or superseding pages. The “List of Effective Pages” shows the issue or revision status of all pages in the POH. The “Revision Highlights” page gives a brief description of changes made to each page in the current revision. Identifying Revised Material Each page in the POH has revision identification at the lower inside corner opposite the page number. Original issue pages will be identified by the words “Original Issue” at this location. In the event that the majority of pages in the POH are revised, Cirrus may determine that it is more effective to reissue the POH. Reissued pages will be identified by the word “Reissue” followed by a letter indicating the reissue level; for example, “Reissue A” Revised pages will be identified by the word “Revision” followed by the revision number at this location; for example, “Revision 2” (Original Issue, Revision 2) or “Revision B1” (Reissue B, Revision 1). Revised material on a page can be identified by a change bar located at the outside page margin. Revision bars are not used at reissues of the POH. Revision A1 Front Matter-4 P/N 11934-004 Front Matter Cirrus Design Foreword SR20 Revisions to the Pilot’s Operating Handbook POH revisions, temporary revisions, and supplements can be downloaded from Cirrus Design at www.cirrusaircraft.com, or from the Authorized Service Center website. Paper copies of POH revisions and supplements can be purchased from Cirrus Connection at www.cirrusconnection.com. • Note • If at any time it is found that the POH is not current, temporary revisions are missing, or applicable supplements are not included, contact Cirrus Design. Supplements The Supplements section (Section 9) of this POH contains FAA Approved Supplements necessary to safely and efficiently operate the airplane when equipped with optional equipment not provided with the standard airplane or not included in the POH. Supplements are essentially “mini-handbooks” and may contain data corresponding to most sections of the POH. Data in a supplement either adds to, supersedes, or replaces similar data in the basic POH. Section 9 includes a “Log of Supplements” page preceding all Cirrus Design Supplements produced for this airplane. The “Log of Supplements” page can be utilized as a “Table of Contents” for Section 9. If the airplane is modified at a non Cirrus Design facility through an STC or other approval method, it is the owner’s responsibility to ensure that the proper supplement, if applicable, is installed in the POH and that the supplement is properly recorded on the “Log of Supplements” page. FAA Approved POH Supplements must be in the airplane for flight operations when the subject optional equipment is installed or the special operations are to be performed. Retention of Data In the event a new title page is issued, the weight and balance data changes, the 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. It is not a requirement that owners retain information, such as supplements, that is not applicable to their airplane. Revision A1 Cirrus Design Front Matter SR20 Foreword P/N 11934-004 Front Matter-5 P/N 11934-004 Front Matter-5 In the event a new POH is purchased, the owner must ensure that all information applicable to the airplane is transferred to the new POH and the aircraft records are current. Warnings, Cautions, and Notes Warnings, Cautions, and Notes are used throughout this POH to focus attention on special conditions or procedures as follows: • WARNING • Warnings are used to call attention to operating procedures which, if not strictly observed, may result in personal injury or loss of life. • Caution • Cautions are used to call attention to operating procedures which, if not strictly observed, may result in damage to equipment. • Note • Notes are used to highlight specific operating conditions or steps of a procedure. Revision A1 Front Matter-6 P/N 11934-004 Front Matter Cirrus Design Foreword SR20 Reissue A Intentionally Left Blank P/N 11934-004 1-1 Cirrus Design Section 1 SR20 General Introduction ........................................................................................ 3 The Airplane....................................................................................... 7 Engine............................................................................................. 7 Propeller ......................................................................................... 7 Fuel................................................................................................. 8 Oil .................................................................................................. 8 Maximum Certificated Weights ....................................................... 8 Cabin and Entry Dimensions .......................................................... 8 Baggage Spaces and Entry Dimensions ........................................ 8 Specific Loadings............................................................................ 8 Symbols, Abbreviations and Terminology.......................................... 9 General Airspeed Terminology and Symbols ................................. 9 Meteorological Terminology.......................................................... 10 Engine Power Terminology........................................................... 11 Performance and Flight Planning Terminology............................. 11 Weight and Balance Terminology................................................. 12 Reissue A Section 1: General Table of Contents 1-2 P/N 11934-004 Section 1 Cirrus Design General SR20 Reissue A Intentionally Left Blank Cirrus Design Section 1 SR20 General P/N 11934-004 1-3 P/N 11934-004 1-3 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. Additionally, this section contains definitions or explanations of symbols, abbreviations, and terminology used throughout this handbook. • Note • For specific information regarding the organization of this Handbook, revisions, supplements, and procedures to be used to obtain publications, see the “Foreword” section. All liquid volumes referenced in this publication are expressed in United States Customary Units, e.g., U.S. Gallons. Revision A1 1-4 P/N 11934-004 Section 1 Cirrus Design General SR20 Figure 1-1 Airplane Three View 74 inches 3-BLADE 188 cm 38.3 ft 11.67 m 9.1 ft 2.8 m 9 inches (minimum) 23 cm (minimum) 26.0 ft 7.92 m 8.9 ft 2.71 m NOTE: • Wing span includes position and strobe lights. • Prop ground clearance at 3050 lb - 9 inches (23 cm). • Wing Area = 144.9 sq. ft. SR20_FM01_2415 Reissue A Cirrus Design Section 1 SR20 General P/N 11934-004 1-5 P/N 11934-004 1-5 Location Length Width Height Volume Cabin 122” 49.3” 49.7 137 cu ft Baggage Compartment 36” 39.8” 38.5” 32 cu ft Figure 1-2 Airplane Interior Dimensions 39.8" 49.3" 240 220 200 180 160 140 120 16.0" 49.7" 27.0" 38.5" FS 10.5" 33.4" 39.0" 20.0" 33.3" 32.0" SR20_FM01_1019A 100 222 CABIN DOOR OPENING BAGGAGE DOOR OPENING 20.0" 21.0" 5.0" Station Fuselage Reissue A 1-6 P/N 11934-004 Section 1 Cirrus Design General SR20 Figure 1-3 Turning Radius 9.1 ft. (2.77 m) 0.5 ft. (0.15 m) 24.3 ft. (7.41 m) 7.0 ft. (2.16 m) RADIUS FOR NOSE GEAR RADIUS FOR OUTSIDE GEAR RADIUS FOR INSIDE GEAR RADIUS FOR WING TIP TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER. ACTUAL TURNING RADIUS MAY VARY AS MUCH AS THREE FEET. GROUND TURNING CLEARANCE SR20_FM01_2413 Reissue A Cirrus Design Section 1 SR20 General P/N 11934-004 1-7 P/N 11934-004 1-7 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 Propeller Hartzell Propeller Type ............................................................. Constant Speed Two-Blade Propeller: Model Number................................................... BHC-J2YF-1BF/F7694 Diameter.............................................................76.0” (73.0” Minimum) Three-Blade Propeller: Model Number............................................... PHC-J3YF-1MF/F7392-1 Diameter.............................................................74.0” (72.0” Minimum) Model Number............................................... PHC-J3YF-1RF/F7392-1 Diameter.............................................................74.0” (72.0” Minimum) Reissue A 1-8 P/N 11934-004 Section 1 Cirrus Design General SR20 Fuel Total Capacity ............................................ 58.5 U.S. Gallons (221.0 L) Total Usable.............................................. .56.0 U.S. Gallons (212.0 L) Approved Fuel Grades: 100 LL Grade Aviation Fuel (Blue) 100 (Formerly 100/130) Grade Aviation Fuel (Green) Oil Oil Capacity (Sump) .............................................8 U.S. Quarts (7.6 L) Oil Grades: All Temperatures ............................................ SAE 15W-50 or 20W-50 Below 40 °F (4° C)................................................... SAE 30 or 10W-30 Above 40 °F (4° C) ....................................................................SAE 50 Maximum Certificated Weights Maximum Gross for Takeoff...................................... 3050 lb (1383 Kg) Maximum Baggage Compartment Loading .................... 130 lb (59 Kg) Maximum Useful Load................................................ 1000 lb (454 Kg) Full Fuel Payload.......................................................... 671 lb (304 Kg) Cabin and Entry Dimensions Refer to the preceding figures for dimensions of the cabin interior and entry door openings. Baggage Spaces and Entry Dimensions Refer to the preceding figures for dimensions of the baggage area and baggage door opening. Specific Loadings Wing Loading..................................................... 22.2 lb per square foot Power Loading................................................................. 15.0 lb per hp Revision A1 Cirrus Design Section 1 SR20 General P/N 11934-004 1-9 P/N 11934-004 1-9 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. KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator. The IAS values published in this handbook assume no instrument error. KTAS Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature. V G Best Glide Speed is the speed at which the greatest flight distance is attained per unit of altitude lost with power off. V O Operating Maneuvering Speed is the maximum speed at which application of full control movement will not overstress the airplane. V FE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. V NO Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air, and then only with caution. V NE Never Exceed Speed is the speed that may not be exceeded at any time. V PD Maximum Demonstrated Parachute Deployment Speed is the maximum speed at which parachute deployment has been demonstrated. V S Stalling Speed is minimum steady flight speed at which the aircraft is controllable. V S 50% Stalling Speed is minimum steady flight speed at which the aircraft is controllable with 50% flaps. Reissue A 1-10 P/N 11934-004 Section 1 Cirrus Design General SR20 Meteorological Terminology V SO 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. V X Best Angle of Climb Speed is the speed at which the airplane will obtain the highest altitude in a given horizontal distance. The best angle-of-climb speed normally increases slightly with altitude. V Y Best Rate of Climb Speed is the speed at which the airplane will obtain the maximum increase in altitude per unit of time. The best rate-of-climb speed decreases slightly with altitude. IMC Instrument Meteorological Conditions are meteorological conditions expressed in terms of visibility, distance from cloud, and ceiling less than the minima for visual flight defined in FAR 91.155. ISA International Standard Atmosphere (standard day) is an atmosphere where (1) the air is a dry perfect gas, (2) the temperature at sea level is 15°C, (3) the pressure at sea level is 29.92 in.Hg (1013.2 millibars), and (4) the temperature gradient from sea level to the altitude at which the temperature is -56.5°C is -0.00198°C per foot and zero above that altitude. MSL Mean Sea Level is the average height of the surface of the sea for all stages of tide. In this Handbook, altitude given as MSL is the altitude above the mean sea level. It is the altitude read from the altimeter when the altimeter’s barometric adjustment has been set to the altimeter setting obtained from ground meteorological sources. OAT Outside Air Temperature is the free air static temperature obtained from inflight temperature indications or from ground meteorological sources. It is expressed in either degrees Celsius or degrees Fahrenheit. Reissue A Cirrus Design Section 1 SR20 General P/N 11934-004 1-11 P/N 11934-004 1-11 Engine Power Terminology Performance and Flight Planning Terminology • Pressure Altitude is the altitude read from the altimeter when the altimeter’s barometric adjustment has been set to 29.92 in.Hg (1013 mb) corrected for position and instrument error. In this Handbook, altimeter instrument errors are assumed to be zero. • 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. See ISA definition. HP Horsepower is the power developed by the engine. MCP Maximum Continuous Power is the maximum power that can be used continuously. MAP Manifold Pressure is the pressure measured in the engine’s induction system expressed as in. Hg. RPM Revolutions Per Minute is engine rotational speed. • Static RPM is RPM attained during a full-throttle engine runup when the airplane is on the ground and stationary. g One “g” is a quantity of acceleration equal to that of earth’s gravity. • Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during taxi, takeoff, and landing was actually demonstrated during certification testing. Demonstrated crosswind is not considered to be limiting. • Service Ceiling is the maximum altitude at which the aircraft at maximum weight has the capability of climbing at a rate of 100 feet per minute. GPH Gallons Per Hour is the amount of fuel (in gallons) consumed by the aircraft per hour. Reissue A 1-12 P/N 11934-004 Section 1 Cirrus Design General SR20 Weight and Balance Terminology NMPG Nautical Miles Per Gallon is the distance (in nautical miles) which can be expected per gallon of fuel consumed at a specific engine power setting and/or flight configuration. • Unusable Fuel is the quantity of fuel that cannot be safely used in flight. • Usable Fuel is the fuel available for flight planning. CG Center of Gravity is the point at which an airplane would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. • Arm is the horizontal distance from the reference datum to the center of gravity (CG) of an item. The airplane’s arm is obtained by adding the airplane’s individual moments and dividing the sum by the total weight. • Basic Empty Weight is the actual weight of the airplane including all operating equipment that has a fixed location in the airplane. The basic empty weight includes the weight of unusable fuel and full oil. MAC Mean Aerodynamic Chord is the chord drawn through the centroid of the wing plan area. LEMAC Leading Edge of Mean Aerodynamic Chord is the forward edge of MAC given in inches aft of the reference datum (fuselage station). • Maximum Gross Weight is the maximum permissible weight of the airplane and its contents as listed in the aircraft specifications. • Moment is the product of the weight of an item multiplied by its arm. • Useful Load is the basic empty weight subtracted from the maximum weight of the aircraft. It is the maximum allowable combined weight of pilot, passengers, fuel and baggage. Reissue A Cirrus Design Section 1 SR20 General P/N 11934-004 1-13 P/N 11934-004 1-13 • Station is a location along the airplane fuselage measured in inches from the reference datum and expressed as a number. For example: A point 123 inches aft of the reference datum is Fuselage Station 123.0 (FS 123). • 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. Tare weight must be subtracted from the associated scale reading. Reissue A 1-14 P/N 11934-004 Section 1 Cirrus Design General SR20 Reissue A Intentionally Left Blank P/N 11934-004 2-1 Cirrus Design Section 2 SR20 Limitations Introduction ........................................................................................ 3 Certification Status ............................................................................. 3 Airspeed Limitations........................................................................... 4 Airspeed Indicator Markings .............................................................. 5 Powerplant Limitations ....................................................................... 6 Engine............................................................................................. 6 Propeller ......................................................................................... 7 Weight Limits ..................................................................................... 7 Engine Instrument Markings & Annunciations ................................... 8 PowerPlant ..................................................................................... 8 Fuel................................................................................................. 9 Electrical ......................................................................................... 9 Center of Gravity Limits ................................................................... 10 Maneuver Limits............................................................................... 11 Flight Load Factor Limits.................................................................. 11 Minimum Flight Crew ....................................................................... 11 Kinds of Operation ........................................................................... 12 Kinds of Operation Equipment List ............................................... 12 Icing .............................................................................................. 16 Runway Surface ........................................................................... 16 Taxi Power.................................................................................... 17 Fuel Limits........................................................................................ 17 Altitude Limits................................................................................... 17 Environmental Conditions ................................................................ 17 Maximum Occupancy ...................................................................... 17 Systems and Equipment Limits........................................................ 19 Cirrus Perspective Integrated Avionics System ............................ 19 L-3 Skywatch Traffic Advisory System (Optional)......................... 22 L-3 Stormscope Weather Information System (Optional) ............. 22 Max Viz Enhanced Vision System (Optional) ............................... 23 MD302 Standby Attitude Module (Optional) ................................. 23 Air Conditioning System (Optional)............................................... 23 Inflatable Restraint System........................................................... 23 Flap Limitations............................................................................. 23 Paint.............................................................................................. 24 Cirrus Airframe Parachute System (CAPS) .................................. 24 Revision A1 Section 2: Limitations Table of Contents 2-2 P/N 11934-004 Section 2 Cirrus Design Limitations SR20 Other Limitations .............................................................................. 25 Smoking ........................................................................................ 25 Placards ........................................................................................... 26 Revision A1 Cirrus Design Section 2 SR20 Limitations P/N 11934-004 2-3 P/N 11934-004 2-3 Introduction The limitations included in this Section of the Pilot’s Operating Handbook (POH) are approved by the Federal Aviation Administration. This section provides operating limitations, instrument markings and basic placards required by regulation and necessary for the safe operation of the aircraft and its standard systems and equipment. Refer to Section 9: Log of Supplements of this handbook for amended operating limitations for airplanes equipped with optional equipment. Compliance with the operating limitations in this section and in Section 9 is required by Federal Aviation Regulations. • Note • Limitations associated with optional equipment are not described in this section. For optional equipment limitations, refer to Section 9: Log of Supplements. Certification Status The aircraft is certificated under the requirements of Federal Aviation Regulations (FAR) Part 23 as documented by FAA Type Certificate TC A00009CH. Reissue A 2-4 P/N 11934-004 Section 2 Cirrus Design Limitations SR20 Airspeed Limitations The indicated airspeeds in the following table are based on Section 5, Airspeed Calibration - Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources. Speed KIAS KCAS Remarks VNE 200 204 Never Exceed Speed is the speed limit that may not be exceeded at any time. VNO 163 166 Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air, and then only with caution. VO 3050 Lb 130 131 Operating Maneuvering Speed is the maxi- mum speed at which full control travel may be used. Below this speed the airplane stalls before limit loads are reached. Above this speed, full control movements can damage the airplane. VFE 50% Flaps 100% Flaps 119 104 120 104 Maximum Flap Extended Speed is the high- est speed permissible with wing flaps extended. VPD 133 135 Maximum Demonstrated Parachute Deployment Speed is the maximum speed at which parachute deployment has been demonstrated. Reissue A Cirrus Design Section 2 SR20 Limitations P/N 11934-004 2-5 P/N 11934-004 2-5 Airspeed Indicator Markings The airspeed indicator markings are based on Section 5, Airspeed Calibration - Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources. Marking Value (KIAS) Remarks White Arc 61 - 104 Full Flap Operating Range. Lower limit is the most adverse stall speed in the landing configuration. Upper limit is the maximum speed permissible with flaps extended. Green Arc 69 - 163 Normal Operating Range. Lower limit is the maximum weight stall at most forward C.G. with flaps retracted. Upper limit is the maximum structural cruising speed. Yellow Arc 163 - 200 Caution Range. Operations must be conducted with cau- tion and only in smooth air. Red Line 200 Never exceed speed. Maximum speed for all operations. Reissue A 2-6 P/N 11934-004 Section 2 Cirrus Design Limitations SR20 Powerplant Limitations Engine Teledyne Continental ............................................................ IO-360-ES Power Rating ........................................................ 200 hp @ 2700 rpm Maximum RPM .......................................................................2700 rpm • Note • Due to the mechanical design of the propeller governor, it is normal for the engine to temporarily exceed 2700 RPM during some phases of flight. If necessary, a slight reduction in throttle setting will decrease the RPM to keep the engine operating at or below 2700 RPM. Oil Temperature ........................................... 240 °F (116 °C) maximum Minimum Oil Temperature for Takeoff...............................75 °F (24 °C) Oil Pressure: Minimum ............................................................................... 10 psi Maximum ............................................................................ 100 psi Approved Oils: Engine Break-In: For first 25 hours of operation or until oil consumption stabilizes use straight mineral oil conforming to MIL- L-6082. If engine oil must be added to the factory installed oil, add only MIL-L-6082 straight mineral oil. After Engine Break-In: Use only oils conforming to Teledyne Continental Specification MHS-24 (Ashless Dispersant Lubrication Oil) or MHS-25 (Synthetic Lubrication Oil). Refer to Section 8 - Oil Servicing. Oil viscosity range as follows: All Temperatures ..............................................15W-50 or 20W-50 Above 40 °F (4 °C)............................................. SAE 50 or 20W50 Below 40 °F (4 °C) ................ SAE 30, 10W-30, 15W50, or 20W50 Fuel Grade ................Aviation Grade 100 LL (Blue) or 100 (green) • Note • Refer to Fuel Limits in this Section for operational limitations regarding fuel and fuel storage. Reissue A Cirrus Design Section 2 SR20 Limitations P/N 11934-004 2-7 P/N 11934-004 2-7 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................................................... BHC-J2YF-1BF/F7694 Diameter.............................................................76.0” (73.0” Minimum) Three-Blade Propeller: Model Number............................................... PHC-J3YF-1MF/F7392-1 Diameter.............................................................74.0” (72.0” Minimum) Model Number............................................... PHC-J3YF-1RF/F7392-1 Diameter.............................................................74.0” (72.0” Minimum) Weight Limits Maximum Takeoff Weight ......................................... 3050 lb (1383 Kg) Maximum Landing Weight ....................................... 3050 lb (1383 Kg) Maximum Weight in Baggage Compartment.................. 130 lb. (59 kg) Reissue A 2-8 P/N 11934-004 Section 2 Cirrus Design Limitations SR20 Engine Instrument Markings & Annunciations The following describes the engine instrument markings. Associated Warning and Caution Annunciations are shown in capitalized text. PowerPlant *Engine Speed Warning when RPM between 2710 and 2730 for more than 10 seconds OR when RPM greater than 2730 for more than 5 seconds. **Oil Pressure Caution when oil pressure is between 10 and 29 psi and RPM is greater than 1000. Oil Pressure Warning when oil pressure is below 10 psi, OR oil pressure is above 100 psi. Instrument (Range & Units) Red Arc/Bar Yellow Arc/Bar Green Arc/ Bar Yellow Arc/ Bar Red Arc/Bar Lower Warning Range Minimum Caution Range Normal Range Maximum Caution Range Upper Warning Range Cylinder Head Temperature (100°F – 500°F) –– –– 240 – 420 420 – 460 CHT > 460 CHT Engine Speed (0 – 3000 RPM) –– –– 500 – 2700 –– > 2700* RPM Exhaust Gas Temperature (500°F – 1750°F) –– –– 1000–1600 –– –– Manifold Pressure (10 – 35 Inch Hg) –– –– 15 – 29.5 –– –– Oil Pressure (0 – 100 PSI) 0 – 10** OIL PRESS 10 – 30** OIL PRESS 30 – 60 60 – 100 > 100** OIL PRESS Oil Temperature (75°F – 250°F) –– –– 100 – 240 > 240 OIL TEMP Percent Power (0 – 100%) –– –– 0 – 100 –– –– Reissue A Cirrus Design Section 2 SR20 Limitations P/N 11934-004 2-9 P/N 11934-004 2-9 Fuel * Serials 2016 thru 2155 ** Serials 2156 and subs Electrical *20 seconds delay. **30 second delay. Instrument (Range & Units) Red Arc/Bar Yellow Arc/Bar Green Arc/Bar Yellow Arc/Bar Red Arc/Bar Minimum Minimum Caution Range Normal Range Maximum Caution Range Maximum Fuel Flow (0 – 20 U.S. Gal/Hr) –– –– 0 – 20 –– –– Fuel Totalizer (U.S. Gallon) N < 7 FUEL QTY 7 – 14 > 14 –– –– Fuel Quantity Gage* (0 – 28 U.S. Gallon) 0 0 – 8.2 –– –– Fuel Quantity Gage** (0 – 28 U.S. Gallon) 0 0 – 8.2 8.2 – 28 –– –– Instrument (Range & Units) Red Arc/Bar Yellow Arc/Bar Green Arc/Bar Yellow Arc/Bar Red Arc/Bar Minimum Minimum Caution Range Normal Range Maximum Caution Range Maximum Essential Bus Volts (0 – 36 Volts) 0 – 24.4 ESS BUS –– 24.5 – 32 –– > 32 ESS BUS Main Bus 1 Voltage (0 – 36 Volts) –– 0 – 24.4 M BUS 1 24.5 – 32 –– > 32 M BUS 1 Main Bus 2 Voltage (0 – 36 Volts) –– 0 – 24.4 M BUS 2 24.5 – 32 –– > 32 M BUS 2 Alternator 1 Current (0 – 75 Amps) –– –– 2 – 100 0 – 1* ALT 1 –– Alternator 2 Current (0 – 40 Amps) –– –– 2 – 100 0 – 1* ALT 2 –– Battery 1 Current (-59 to 59 Amps) –– –– -4 – 59 -59 to -5** BATT 1 –– Reissue A 2-10 P/N 11934-004 Section 2 Cirrus Design Limitations SR20 Center of Gravity Limits Reference Datum ................................... 100 inches forward of firewall Forward ...................................................................Refer to Figure 2-1 Aft ............................................................................Refer to Figure 2-1 Figure 2-1 CG Envelope FS 148.1 2100 lb FS 148.1 3050 lb FS 139.1 2700 lb FS 140.7 3050 lb FS 137.8 2100 lb 2000 2050 2100 2150 2200 2250 2300 2350 2400 2450 2500 2550 2600 2650 2700 2750 2800 2850 2900 2950 3000 3050 3100 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 C.G. - Inches Aft of Datum Weight - Pounds Reissue A Cirrus Design Section 2 SR20 Limitations P/N 11934-004 2-11 P/N 11934-004 2-11 Maneuver Limits Aerobatic maneuvers are prohibited. Spins are prohibited. This airplane is certified in the normal category and is not designed for aerobatic operations. Only those operations incidental to normal flight are approved. These operations include normal stalls, chandelles, lazy eights, and turns in which the angle of bank is limited to 60°. • Note • Because the aircraft has not been certified for spin recovery, the Cirrus Airframe Parachute System (CAPS) must be deployed if the airplane departs controlled flight. Refer to Section 3, Inadvertent Spin Entry. Flight Load Factor Limits Flaps UP (0%), 3050 lb. .....................................................+3.8g, -1.9g Flaps 50%, 3050 lb................................................................. +1.9g, 0g Flaps 100% (Down), 3050 lb. ................................................. +1.9g, 0g Minimum Flight Crew The minimum flight crew is one pilot. Revision A1 2-12 P/N 11934-004 Section 2 Cirrus Design Limitations SR20 Kinds of Operation The aircraft is equipped and approved for the following type operations: • VFR day and night. • IFR day and night. Kinds of Operation Equipment List The following listing summarizes the equipment required under Federal Aviation Regulations (FAR) Part 23 for airworthiness under the listed kind of operation. Those minimum items of equipment necessary under the operating rules are defined in FAR Part 91 and FAR Part 135 as applicable. • Note • All references to types of flight operations on the operating limitations placards are based upon equipment installed at the time of Airworthiness Certificate issuance. System, Instrument, and/ or Equipment Kinds of Operation Remarks, Notes, and/or Exceptions VFR Day VFR Nt. IFR Day IFR Nt. Placards and Markings Airplane Flight Manual (Included w/ POH) 1 1 1 1 Communications VHF COM — — 1 1 Electrical Power Battery 1 1 1 1 1 Battery 2 — — 1 1 Alternator 1 1 1 1 1 Alternator 2 — — 1 1 Amp Meter/Indication 1 1 1 1 Reissue A Cirrus Design Section 2 SR20 Limitations P/N 11934-004 2-13 P/N 11934-004 2-13 Low Volts Annunciator 1 1 1 1 ALT 1 Annunciator 1 1 1 1 ALT 2 Annunciator — — 1 1 Circuit Breakers A/R A/R A/R A/R As required. Equipment & Furnishings Emergency Locator Trans- mitter 1 1 1 1 Restraint System A/R A/R A/R A/R One seat belt for each occupant. Fire Protection Fire Extinguisher 1 1 1 1 Flight Controls Flap Position Indicator 1 1 1 1 Flap System 1 1 1 1 Pitch Trim Indicator 1 1 1 1 Pitch Trim System 1 1 1 1 Roll Trim Indicator 1 1 1 1 Roll Trim System 1 1 1 1 Stall Warning System 1 1 1 1 Fuel Auxiliary Fuel Pump 1 1 1 1 Fuel Quantity Indicators 2 2 2 2 Fuel Selector Valve 1 1 1 1 System, Instrument, and/ or Equipment Kinds of Operation (Continued) Remarks, Notes, and/or Exceptions VFR Day VFR Nt. IFR Day IFR Nt. Reissue A 2-14 P/N 11934-004 Section 2 Cirrus Design Limitations SR20 Ice & Rain Protection Alternate Engine Air Induc- tion System 1 1 1 1 Alternate Static Air Source 1 1 1 1 Pitot Heater — — 1 1 Landing Gear Wheel Pants — — — — May be removed. Lights PFD Bezel Lighting — — — 1 PFD Backlighting * 1 1 1 *Required if MFD Backlighting Fails. Engine Indicators Must Be Shown in Backup Mode. MFD Bezel Lighting — — — 1 MFD Backlighting * 1 1 1 *Required if PFD Backlighting Fails. Engine Indicators Must Be Shown in Backup Mode. Anticollision Lights 2 2 2 2 Instrument Lights — 1 — 1 Navigation Lights — 2 — 2 Landing Light — 1 — 1 For hire opera- tions. Flash Light — 1 — 1 Navigation & Pitot Static Airspeed Indicator 1 1 1 1 System, Instrument, and/ or Equipment Kinds of Operation (Continued) Remarks, Notes, and/or Exceptions VFR Day VFR Nt. IFR Day IFR Nt. Reissue A