PILOT’S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL for the CIRRUS DESIGN SR20 Aircraft Serials 2016 and Subsequent with Cirrus Perspective Avionics System 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.
Copyright © 2008 - All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811
Cirrus Design SR20 Pilot’s Operating Handbook List of Effective Pages List of Effective Pages Use this page to determine the current effective date for each page in the POH. Supplements are issued individually and are controlled by the Log of Supplements Page in Section 9. Dates of original issue and revised pages are: Original Issue.......... ................... 18 Dec 2008 Revision .................. 1 .................
Cirrus Design SR20 Pilot’s Operating Handbook List of Effective Pages List of Effective Pages (Cont.
Cirrus Design SR20 Pilot’s Operating Handbook List of Effective Pages List of Effective Pages (Cont.
Cirrus Design SR20 Pilot’s Operating Handbook List of Effective Pages List of Effective Pages (Cont.
Cirrus Design SR20 Section Front Matter Foreword Foreword This Pilot’s Operating Handbook (POH or Handbook) has been prepared by Cirrus Design Corporation to familiarize operators with the aircraft. Read this Handbook carefully. It provides operational procedures that will assure the operator obtains the performance published in the manual, data designed to allow the most efficient use of the airplane, and basic information for maintaining the airplane in a “like new” condition.
Section Front Matter Foreword Cirrus Design 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. Tabbed dividers throughout the Handbook allow quick reference to each section.
Cirrus Design SR20 Section Front Matter 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.
Section Front Matter Foreword Cirrus Design SR20 Revision Service Revision service for this Handbook is provided at no cost for the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual assigned to an airplane. Additional copies of the Handbook and revision service can be obtained from Customer Service at Cirrus Design at the address below.
Cirrus Design SR20 Section Front Matter 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. It is not a requirement that owners retain information, such as supplements, that is not applicable to their airplane.
Section Front Matter Foreword Cirrus Design SR20 Intentionally Left Blank Front Matter-6 P/N 11934-004 Original Issue
Cirrus Design SR20 Section 1 General Section 1 General Table of Contents Introduction ........................................................................................ 3 The Airplane....................................................................................... 7 Engine............................................................................................. 7 Propeller ......................................................................................... 7 Fuel.......................
Section 1 General Cirrus Design SR20 Intentionally Left Blank 1-2 P/N 11934-004 Original Issue
Cirrus Design SR20 Section 1 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. Additionally, this section contains definitions or explanations of symbols, abbreviations, and terminology used throughout this handbook.
Section 1 General Cirrus Design SR20 26.0 ft 7.92 m 8.9 ft 2.71 m 9 inches (minimum) 23 cm (minimum) NOTE: • Wing span includes position and strobe lights. • Prop ground clearance at 3050 lb - 9 inches (23 cm). • Wing Area = 144.9 sq. ft. 38.3 ft 11.67 m 74 inches 3-BLADE 188 cm 9.1 ft 2.
Cirrus Design SR20 Section 1 General 49.3" 39.8" 100 120 140 160 180 49.7" 200 38.5" 220 240 Fuselage Station FS 222 25.0" 16.0" 20.0" 10.5" 32.0" 33.4" 39.0" 20.0" 33.3" 5.0" CABIN DOOR OPENING 21.0" BAGGAGE DOOR OPENING SR22_FM06_1019 Location Length Width Height Volume Cabin 122” 49.3” 49.7 137 cu ft Baggage Compartment 36” 39.8” 38.
Section 1 General Cirrus Design SR20 GROUND TURNING CLEARANCE RADIUS FOR WING TIP 24.3 ft. (7.41 m) RADIUS FOR NOSE GEAR 7.0 ft. (2.16 m) RADIUS FOR INSIDE GEAR 0.5 ft. (0.15 m) RADIUS FOR OUTSIDE GEAR 9.1 ft. (2.77 m) TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER. ACTUAL TURNING RADIUS MAY VARY AS MUCH AS THREE FEET.
Cirrus Design SR20 Section 1 General The Airplane Engine Number of Engines.............................................................................. 1 Number of Cylinders............................................................................ 6 Engine Manufacturer ............................................Teledyne Continental Engine Model ....................................................................... IO-360-ES Fuel Metering ...............................................................
Section 1 General Cirrus Design 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 .............................................
Cirrus Design SR20 Section 1 General Symbols, Abbreviations and Terminology General Airspeed Terminology and Symbols KCAS Knots Calibrated Airspeed is the indicated airspeed corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator. The IAS values published in this handbook assume no instrument error.
Section 1 General Cirrus Design SR20 VSO 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. VX 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.
Cirrus Design SR20 Section 1 General • Pressure Altitude is the altitude read from the altimeter when the altimeter’s barometric adjustment has been set to 29.92 in.Hg (1013 mb) corrected for position and instrument error. In this Handbook, altimeter instrument errors are assumed to be zero. • 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.
Section 1 General Cirrus Design SR20 NMPG Nautical Miles Per Gallon is the distance (in nautical miles) which can be expected per gallon of fuel consumed at a specific engine power setting and/or flight configuration. • Unusable Fuel is the quantity of fuel that cannot be safely used in flight. • Usable Fuel is the fuel available for flight planning. Weight and Balance Terminology CG Center of Gravity is the point at which an airplane would balance if suspended.
Cirrus Design SR20 Section 1 General • Station is a location along the airplane fuselage measured in inches from the reference datum and expressed as a number. For example: A point 123 inches aft of the reference datum is Fuselage Station 123.0 (FS 123). • 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.
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Cirrus Design SR20 Section 2 Limitations Section 2 Limitations Table of Contents Introduction ........................................................................................ 3 Certification Status ............................................................................. 3 Airspeed Limitations........................................................................... 4 Airspeed Indicator Markings .............................................................. 5 Powerplant Limitations ..........
Section 2 Limitations Cirrus Design SR20 Placards ...........................................................................................
Cirrus Design SR20 Section 2 Limitations Introduction The limitations included in this Section of the Pilot’s Operating Handbook (POH) are approved by the Federal Aviation Administration. This section provides operating limitations, instrument markings and basic placards required by regulation and necessary for the safe operation of the aircraft and its standard systems and equipment. Refer to Section 9 of this handbook for amended operating limitations for airplanes equipped with optional equipment.
Section 2 Limitations Cirrus Design 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. Speed KIAS KCAS Remarks VNE 200 204 Never Exceed Speed is the speed limit that may not be exceeded at any time.
Cirrus Design SR20 Section 2 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. Marking Value (KIAS) White Arc 61 - 104 Full Flap Operating Range. Lower limit is the most adverse stall speed in the landing configuration.
Section 2 Limitations Cirrus Design SR20 Powerplant Limitations Engine Teledyne Continental ............................................................ IO-360-ES Power Rating ........................................................ 200 hp @ 2700 rpm Maximum RPM .......................................................................2700 rpm Oil Temperature .......................................... 240° F (115° C) maximum Oil Pressure: Minimum...............................................................
Cirrus Design SR20 Section 2 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................................................... BHC-J2YF-1BF/F7694 Diameter........................................................
Section 2 Limitations Cirrus Design SR20 Engine Instrument Markings & Annunciations The following describes the engine instrument markings. Associated Warning and Caution Annunciations are shown in capitalized text.
Cirrus Design SR20 Section 2 Limitations Fuel 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.
Section 2 Limitations Cirrus Design SR20 Center of Gravity Limits Reference Datum ....................................100 inches forward of firewall Forward....................................................................Refer to Figure 2-1 Aft ............................................................................Refer to Figure 2-1 3100 3050 3000 FS 140.7 3050 lb FS 148.1 3050 lb Weight - Pounds 2950 2900 2850 2800 2750 2700 2650 2600 FS 139.
Cirrus Design SR20 Section 2 Limitations 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°.
Section 2 Limitations Cirrus Design 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.
Cirrus Design SR20 System, Instrument, and/ or Equipment Section 2 Limitations Kinds of Operation (Continued) VFR Day VFR Nt. IFR Day IFR Nt.
Section 2 Limitations System, Instrument, and/ or Equipment Cirrus Design SR20 Kinds of Operation (Continued) VFR Day VFR Nt. IFR Day IFR Nt.
Cirrus Design SR20 System, Instrument, and/ or Equipment Section 2 Limitations Kinds of Operation (Continued) Remarks, Notes, and/or Exceptions VFR Day VFR Nt. IFR Day IFR Nt.
Section 2 Limitations System, Instrument, and/ or Equipment Cirrus Design SR20 Kinds of Operation (Continued) VFR Day VFR Nt. IFR Day IFR Nt.
Cirrus Design SR20 Section 2 Limitations Taxi Power Maximum continuous engine speed for taxiing is 1000 RPM on flat, smooth, hard surfaces. Power settings slightly above 1000 RPM are permissible to start motion, for turf, soft surfaces, and on inclines. Use minimum power to maintain taxi speed. Fuel Limits Approved Fuel ............... Aviation Grade 100 LL (Blue) or 100 (Green) Total Fuel Capacity..................................... 58.5 U.S. gallons (229.0 L) Total Fuel Each Tank .....................
Section 2 Limitations Cirrus Design SR20 Systems and Equipment Limits Cirrus Perspective Integrated Avionics System 1. The Cirrus Perspective by Garmin Integrated Avionics System Quick Reference Guide for the SR20 and SR22, P/N 190-0082102 Rev A or later must be immediately available to the pilot during flight. The software status stated in the pilot's guide must match that displayed on the equipment. 2. The Avionics System integrates with separately approved sensor installations.
Cirrus Design SR20 f. Section 2 Limitations RNAV approaches must be conducted utilizing the GPS sensor. g. When conducting missed approach procedures, autopilot (if installed) coupled operation is prohibited until the pilot has established a rate of climb that ensures all altitude requirements of the procedure will be met. h. The Perspective Integrated Avionics System is compliant with AC 90-100A.
Section 2 Limitations Cirrus Design SR20 10. The SYNTHETIC VISION SYSTEM (SVS) cannot be used for flight guidance, navigation, traffic avoidance, or terrain avoidance. Maneuvering the airplane in any phase of flight such as taxi, takeoff, approach, landing, or roll out shall not be predicated on SVS imagery. The synthetic vision system is not intended to be used independently of traditional attitude instrumentation. Consequently, SVS is disabled when traditional attitude instrumentation is not available.
Cirrus Design SR20 Section 2 Limitations L-3 Stormscope Weather Information System 1. Use of the Stormscope is not intended for hazardous weather penetration (thunderstorm penetration). Stormscope information, as displayed on the Perspective Integrated Avionics System, is to be used only for weather avoidance, not penetration. 2. The L-3 Avionics Systems WX500 Stormscope Series II Weather Mapping Sensor User’s Guide, P/N 009-11501-001 revision C or later must be available to the pilot during flight.
Section 2 Limitations Cirrus Design SR20 Placards Engine compartment, inside oil filler access: ENGINE OIL GRADE ABOVE 40° F SAE 50 OR 20W50 BELOW 40° F SAE 30 OR 10W30, 15W50, OR 20W50 REFER TO AFM FOR APPROVED OILS Wing, adjacent to fuel filler caps: Upper fuselage, either side of CAPS rocket cover: WARNING! ROCKET FOR PARACHUTE DEPLOYMENT INSIDE STAY CLEAR WHEN AIRPLANE IS OCCUPIED SR20_FM02_3001A Figure 2-2 Placards (Sheet 1 of 6) 2-22 P/N 11934-004 Revision 1
Cirrus Design SR20 Section 2 Limitations Elevator and Rudder, both sides: NO PUSH Left fuselage, on external power supply door: EXTERNAL POWER 28 V DC Doors, above and below latch: PUSH TO OPEN SR20_FM02_3002 Figure 2-3 Placards (Sheet 2 of 6) P/N 11934-004 Original Issue 2-23
Section 2 Limitations Cirrus Design SR20 Engine control panel: CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT RICH MAX M P F I TURN BOOST PUMP ON DURING TAKE OFF, CLIMB, LANDING AND SWITCHING FUEL TANKS. O X R I C W T T I BOOST U E FUEL PUMP R O N R E PRIME IDLE CUTOFF RIGHT 28 U.S. GALLONS USABLE LEFT 28 U.S.
Cirrus Design SR20 Section 2 Limitations Wing, flap aft edge and fuselage vortex generator: NO STEP Cabin Door Window, lower edge, centered, applied upside down: RESCUE: FRACTURE AND REMOVE WINDOW Bolster Switch Panel, left edge: THIS AIRCRAFT IS CERTIFIED FOR THE FOLLOWING FLIGHT OPERATIONS: DAY - NIGHT - VFR - IFR (WITH REQUIRED EQUIPMENT) FLIGHT INTO KNOWN ICING IS PROHIBITED OPERATE PER AIRPLANE FLIGHT MANUAL Instrument Panel, left : MANEUVERING SPEED: Vo 130 KIAS NORMAL CATEGORY AIRPLANE NO ACR
Section 2 Limitations Cirrus Design SR20 Instrument Panel, center: DISPLAY BACKUP Bolster Panel, both sides: GRAB HERE Baggage Compartment, aft edge: ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Instrument Panel: FASTEN SEATBELTS • NO SMOKING FIRE EXTINGUISHER FORWARD LEFT OF PILOT SEAT Cabin Window, above door latch: EMERGENCY EXIT REMOVE EGRESS HAMMER FROM WITHIN CENTER ARMREST LID. STRIKE CORNER OF WINDOW.
Cirrus Design SR20 Section 2 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 MAXIMUM DEMONSTRATED DEPLOYMENT SPEED 133 KIAS CIRRUS AIRFRAME PARACHUTE SYSTEM ACTIVATION PROCEDURE 1. FUEL MIXTURE.......................................CUT-OFF 2. THIS COVER............................................REMOVE 3. ACTIVATION HANDLE.......
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Cirrus Design SR20 Section 3 Emergency Procedures Section 3 Emergency Procedures Table of Contents Introduction ........................................................................................ 3 Emergency Procedures Guidance ..................................................... 4 Preflight Planning............................................................................ 4 Preflight Inspections/Maintenance .................................................. 4 Methodology .........................
Section 3 Emergency Procedures Cirrus Design SR20 Low Fuel Quantity ......................................................................... 23 Electrical System Emergencies........................................................ 24 Alternator Failure .......................................................................... 24 High Voltage on Main Bus 1 or Main Bus 2 .................................. 24 Low Voltage on Essential Bus ......................................................
Cirrus Design SR20 Section 3 Emergency Procedures Introduction This section provides procedures for handling emergencies and critical flight situations that may occur while operating the aircraft. Although emergencies caused by airplane, systems, or engine malfunctions are extremely rare, the guidelines described in this section should be considered and applied as necessary should an emergency arise. • Note • Emergency procedures associated with optional systems can be found in Section 9.
Section 3 Emergency Procedures Cirrus Design SR20 Emergency Procedures Guidance Although this section provides procedures for handling most emergencies and critical flight situations that could arise in the aircraft, it is not a substitute for thorough knowledge of the airplane and general aviation techniques. A thorough study of the information in this handbook while on the ground will help you prepare for time-critical situations in the air.
Cirrus Design SR20 Section 3 Emergency Procedures 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. • Note • In an in-flight emergency, pressing and holding the COM transfer button for 2 seconds will tune the emergency frequency of 121.500 MHz. If the display is available, it will also show it in the “Active” frequency window.
Section 3 Emergency Procedures Cirrus Design SR20 Airspeeds for Emergency Operations Maneuvering Speed: 3050 lb .............................................................................130 KIAS 2600 lb .............................................................................120 KIAS 2200 lb .............................................................................110 KIAS Best Glide: 3050 lb ...............................................................................99 KIAS 2500 lb .........
Cirrus Design SR20 Section 3 Emergency Procedures Engine Failures Engine Failure On Takeoff (Low Altitude) If the engine fails immediately after becoming airborne, abort on the runway if possible. If altitude precludes a runway stop but is not sufficient to restart the engine, lower the nose to maintain airspeed and establish a glide attitude. In most cases, the landing should be made straight ahead, turning only to avoid obstructions.
Section 3 Emergency Procedures Cirrus Design SR20 Engine Failure In Flight If the engine fails at altitude, pitch as necessary to establish best glide speed. While gliding toward a suitable landing area, attempt to identify the cause of the failure and correct it. If altitude or terrain does not permit a safe landing, CAPS deployment may be required. Refer to Section 10, Safety Information, for CAPS deployment scenarios and landing considerations.
Cirrus Design SR20 Section 3 Emergency Procedures Airstart Engine Airstart The following procedures address the most common causes for engine loss. Switching tanks and turning the fuel pump on will enhance starting if fuel contamination was the cause of the failure. Leaning the mixture and then slowly enriching mixture may correct faulty mixture control. • Note • Engine airstarts may be performed during 1g flight anywhere within the normal operating envelope of the airplane. 1. Bat Master Switches .......
Section 3 Emergency Procedures Cirrus Design SR20 Smoke and Fire Engine Fire In Flight If an engine fire occurs during flight, do not attempt to restart the engine. 1. Mixture ............................................................................. CUTOFF 2. Fuel Pump................................................................................OFF 3. Fuel Selector ............................................................................OFF 4. Airflow Selector ....................................
Cirrus Design SR20 Section 3 Emergency Procedures 2. Fire Extinguisher ............................................................ ACTIVATE • WARNING • Halon gas used in the fire extinguisher can be toxic, especially in a closed area. After extinguishing fire, ventilate cabin by and unlatching door (if required). If airflow is not sufficient to clear smoke or fumes from cabin: 3. Cabin Doors .......................................................
Section 3 Emergency Procedures Cirrus Design SR20 Wing Fire In Flight 1. Pitot Heat Switch......................................................................OFF 2. Navigation Light Switch............................................................OFF 3. Landing Light ...........................................................................OFF 4. Strobe Light Switch ..................................................................OFF 5.
Cirrus Design SR20 Section 3 Emergency Procedures Smoke and Fume Elimination If smoke and/or fumes are detected in the cabin, check the engine parameters for any sign of malfunction. If a fuel leak has occurred, actuation of electrical components may cause a fire. If there is a strong smell of fuel in the cockpit, divert to the nearest suitable landing field. Perform a Forced Landing and shut down the fuel supply to the engine once a safe landing is assured. 1. Temperature Selector........................
Section 3 Emergency Procedures Cirrus Design SR20 Emergency Descent Emergency Descent 1. Power Lever ............................................................................ IDLE 2. Mixture ................................................................... AS REQUIRED • Caution • If significant turbulence is expected do not descend at indicated airspeeds greater than VNO (163 KIAS). 3. Airspeed .................................................................
Cirrus Design SR20 Section 3 Emergency Procedures Forced Landings If all attempts to restart the engine fail and a forced landing is imminent, select a suitable field and prepare for the landing. If flight conditions or terrain does not permit a safe landing, CAPS deployment may be required. Refer to Section 10, Safety Information, for CAPS deployment scenarios and landing considerations.
Section 3 Emergency Procedures Cirrus Design SR20 Ditching 1. Radio............................................. Transmit (121.5 MHz) MAYDAY giving location and intentions 2. Transponder ........................................................... SQUAWK 7700 3. CAPS ............................................................................. ACTIVATE If available, life preservers should be donned and life raft should be prepared for immediate evacuation upon touchdown.
Cirrus Design SR20 Section 3 Emergency Procedures Engine System Emergencies Oil Pressure Out of Range OIL PRESS Warning OIL PRESS Oil pressure below 10 psi or above 100 psi. If low oil pressure is low, the engine has probably lost a significant amount of its oil and engine failure may be imminent. Immediately reduce engine power to idle and select a suitable forced landing field.
Section 3 Emergency Procedures Cirrus Design SR20 Oil Temperature High OIL TEMP Warning OIL TEMP Oil temperature is greater than 240°F. 1. Oil Temperature Gage........................................................ CHECK If temperature normal: a. If On-Ground........................... CORRECT PRIOR TO FLIGHT b. If In-Flight............................................ CONTINUE, MONITOR If temperature high: a. Oil Pressure Gage .......................................................
Cirrus Design SR20 Section 3 Emergency Procedures High Cylinder Head Temperature CHT Caution and Warning CHT CHT Warning: Temperature of one or more cylinder heads has exceeded 460°F. CHT Caution: Temperature of one or more cylinder heads has exceeded 420°F. On-Ground 1. Power Lever ..................................................................... REDUCE 2. Annunciations and Engine Temperatures ...................... MONITOR If Caution or Warning annunciation is still illuminated: 3. Power Lever ....
Section 3 Emergency Procedures Cirrus Design SR20 Engine Partial Power Loss Indications of a partial power loss include fluctuating RPM, reduced or fluctuating manifold pressure, low oil pressure, high oil temperature, and a rough-sounding or rough-running engine. Mild engine roughness in flight may be caused by one or more spark plugs becoming fouled. A sudden engine roughness or misfiring is usually evidence of a magneto malfunction.
Cirrus Design SR20 Section 3 Emergency Procedures 1. Fuel Pump ......................................................................... BOOST Selecting BOOST on may clear the problem if vapor in the injection lines is the problem or if the engine-driven fuel pump has partially failed. The electric fuel pump will not provide sufficient fuel pressure to supply the engine if the engine-driven fuel pump completely fails. 2. Fuel Selector........................................................
Section 3 Emergency Procedures Cirrus Design SR20 Propeller System Emergencies Propeller Governor Failure If the RPM does not respond to power lever movement or overspeeds, the most likely cause is a faulty governor or an oil system malfunction. If moving the power lever is difficult or rough, suspect a power lever linkage failure and perform the Power Lever Linkage Failure checklist. Propeller RPM will not increase: 1. Oil Pressure .......................................................................
Cirrus Design SR20 Section 3 Emergency Procedures Fuel System Emergencies High Fuel Flow FUEL FLOW Warning FUEL FLOW Fuel flow greater than 20 GPH. On-Ground 1. Correct prior to flight. In-Flight 1. Mixture .............................................................................. ADJUST Adjust engine operation to correct condition. Check engine instruments to verify HIGH FLOW Warning is not erroneous, i.e. abnormal engine temperatures or engine roughness after mixture adjustment.
Section 3 Emergency Procedures Cirrus Design SR20 Electrical System Emergencies Alternator Failure The most likely the cause of the alternator failure is a wiring fault, a malfunctioning alternator, or a malfunctioning control unit. Usually, electrical power malfunctions are accompanied by an excessive rate of charge or a discharge rate shown on the ammeter.
Cirrus Design SR20 Section 3 Emergency Procedures Low Voltage on Essential Bus ESS BUS Warning ESS BUS Illumination of ESS BUS Warning indicates that the voltage output for alternator 1 or alternator 2 is less than 24.5v for more than 20 seconds or greater than 32.0v. This is usually associated with an alternator 1 or alternator 2 failure and will be displayed in combination with a M BUS 1 or M BUS 2 voltage annunciation for the corresponding alternator.
Section 3 Emergency Procedures Cirrus Design SR20 Low Alternator 1 Output ALT 1 Caution ALT 1 Illumination of ALT 1 indicates that the ampere output is less than 2 amps for 20 seconds or more. Attempt to reset alternator. If alternator cannot be reset, reduce loads and use Main Bus or Non-Essential loads only as necessary for flight conditions. 1. ALT 1 Master Switch ................................................................OFF 2. ALT 1 Circuit Breaker ..............................................
Cirrus Design SR20 Section 3 Emergency Procedures Integrated Avionics System Emergencies • Note • A “Red X” through any electronic display field, such as COM frequencies, NAV frequencies, or engine data, indicates that display field is not receiving valid data. Attitude & Heading Reference System (AHRS) Failure Failure of the Attitude and Heading Reference System (AHRS) is indicated by removal of the sky/ground presentation and a “Red X” and a yellow “ATTITUDE FAIL” shown on the PFD.
Section 3 Emergency Procedures Cirrus Design SR20 Emergency Exit Emergency Ground Egress • WARNING • While exiting the airplane, make sure evacuation path is clear of other aircraft, spinning propellers, and other hazards. 1. Engine........................................................................SHUTDOWN • Note • If the engine is left running, set the Parking Brake prior to evacuating the airplane. 2. Seat belts ....................................................................... RELEASE 3.
Cirrus Design SR20 Section 3 Emergency Procedures Unusual Attitude Emergencies Spins The aircraft is not approved for spins, and has not been tested or certified for spin recovery characteristics. The only approved and demonstrated method of spin recovery is activation of the Cirrus Airframe Parachute System (See CAPS Deployment, this section). Because of this, if the aircraft “departs controlled flight,” the CAPS must be deployed.
Section 3 Emergency Procedures Cirrus Design SR20 Inadvertent Spiral Dive During IMC Flight In all cases, if the aircraft enters an unusual attitude from which recovery is not assured, immediately deploy CAPS. Refer to Section 10, Safety Information, for CAPS deployment information. 1. Power Lever ............................................................................ IDLE 2.
Cirrus Design SR20 Section 3 Emergency Procedures Other Emergencies Power Lever Linkage Failure If the Power Lever linkage fails in flight, the engine will not respond to power lever control movements. Use power available and flaps as required to safely land the airplane. If the power lever is stuck at or near the full power position, proceed to a suitable airfield. Fly a forced landing pattern. With landing assured, shut down engine by moving mixture control full aft to CUTOFF.
Section 3 Emergency Procedures Cirrus Design SR20 Left/Right Brake Over-Temperature Annunciation BRAKE TEMP Warning BRAKE TEMP Brake temperature is greater than 293°F. Refer to Section 10 - Safety Information: Taxiing, Steering, and Braking Practices for additional information 1. Stop aircraft and allow the brakes to cool. Starter Engaged Annunciation STARTER ENGAGED Warning START ENGAGE Starter stuck engaged. MCU detects 24 VDC to Starter 30 seconds after initial engagement. On-Ground 1.
Cirrus Design SR20 Section 3 Emergency Procedures CAPS Deployment The Cirrus Airframe Parachute System (CAPS) should be activated in the event of a life-threatening emergency where CAPS deployment is determined to be safer than continued flight and landing.
Section 3 Emergency Procedures Cirrus Design SR20 2. Mixture (If time and altitude permit) ................................. CUTOFF Generally, a distressed airplane will be safer for its occupants if the engine is not running. 3. Activation Handle Cover.................................................. REMOVE The cover has a handle located at the forward edge. Pull cover down to expose activation T-handle. 4. Activation Handle (Both Hands) .............
Cirrus Design SR20 Section 3 Emergency Procedures 13. Assume emergency landing body position. The emergency landing body position is assumed by placing both hands on the lap, clasping one wrist with the opposite hand, and holding the upper torso erect and against the seat backs. 14. After the airplane comes to a complete stop, evacuate quickly and move upwind. As occupants exit the airplane, the reduced weight may allow winds to drag the airplane further. As a result of landing impact, the doors may jam.
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Cirrus Design SR20 Section 3A Abnormal Procedures Section 3A Abnormal Procedures Table of Contents Introduction ........................................................................................ 1 Abnormal Procedures Guidance ........................................................ 1 Circuit Breakers .............................................................................. 1 Flight Environment .............................................................................
Section 3A Abnormal Procedures Cirrus Design SR20 Other Conditions .............................................................................. 14 Aborted Takeoff ............................................................................ 14 Parking Brake Engaged Annunciation .......................................... 15 Communications Failure ...............................................................
Cirrus Design SR20 Section 3A Abnormal Procedures Introduction This section provides procedures for handling abnormal system and/or flight conditions which, if followed, will maintain an acceptable level of airworthiness or reduce operational risk. The guidelines described in this section are to be used when an abnormal condition exists and should be considered and applied as necessary.
Section 3A Abnormal Procedures Cirrus Design SR20 Flight Environment Inadvertent Icing Encounter Flight into known icing conditions is prohibited. However, if icing is inadvertently encountered: 1. Pitot Heat .................................................................................. ON 2. Exit icing conditions. Turn back or change altitude. 3. Cabin Heat .................................................................... MAXIMUM 4. Windshield Defrost ..............................................
Cirrus Design SR20 Section 3A Abnormal Procedures Abnormal Landings Landing With Failed Brakes One brake inoperative 1. Land on the side of runway corresponding to the inoperative brake. 2. Maintain directional control using rudder and working brake. Both brakes inoperative 1. Divert to the longest, widest runway with the most direct headwind. 2. Land on downwind side of the runway. 3. Use the rudder for obstacle avoidance. • Note • Rudder effectiveness will decrease with decreasing airspeed. 4.
Section 3A Abnormal Procedures Cirrus Design SR20 Engine System Low Idle Oil Pressure OIL PRESS Caution OIL PRESS Oil pressure between 10 psi and 30 psi at or above 1000 RPM • Note • This message will appear prior to engine start and should clear after engine start. 1. If In-Flight .................................. LAND AS SOON AS PRACTICAL Starter Engaged Annunciation STARTER ENGAGED Caution START ENGAGE Starter stuck engaged. MCU detects 24 VDC to Starter 15 seconds after initial engagement.
Cirrus Design SR20 Section 3A Abnormal Procedures Fuel System Left Fuel Tank Quantity L FUEL QTY Advisory L FUEL QTY Left fuel quantity is less than or equal to 7 gallons. 1. Left Fuel Quantity Gage..................................................... CHECK If left fuel quantity indicates less than or equal to 7 gallons: a. If On-Ground ..............................REFUEL PRIOR TO FLIGHT b. If In-Flight ...........................................
Section 3A Abnormal Procedures Cirrus Design SR20 Fuel System (Cont) Fuel Filter in Bypass Mode FUEL FILTER Advisory FUEL FILTER The fuel filter is in bypass mode. The fuel filter element must be replaced. 1. If In-Flight .................................. LAND AS SOON AS PRACTICAL 2. Replace fuel filter element prior to next flight. Electrical System Battery 1 Current Sensor BATT 1 Caution BATT 1 Battery 1 current is discharging at a rate greater than 4 amps for 30 seconds or more. 1.
Cirrus Design SR20 Section 3A Abnormal Procedures AVIONICS ALT2 STDBY ATTD #2 ENGINE INSTR MFD #2 EVS CAMERA STALL WARNING CABIN LIGHTS 12V DC OUTLET ROLL TRIM FUEL QTY MFD #1 PITCH TRIM AP SERVOS ESSENTIAL POWER KEYPADS / AP CTRL ALT1 CABIN AIR CONTROL CABIN FAN STARTER AVIONICS FAN 2 BAT 2 AVIONICS FAN 1 GPS NAV GIA 2 GPS NAV GIA 1 DME / ADF RECOG LIGHTS COM 2 COM 1 AUDIO PANEL NAV LIGHTS AHRS 2 ADC 1 WEATHER AHRS 1 XPONDER TRAFFIC STROBE LIGHTS PITOT HEAT FUEL PUMP
Section 3A Abnormal Procedures Cirrus Design SR20 Integrated Avionics System Avionics Switch Off AVIONICS OFF Caution AVIONICS OFF The AVIONICS master switch is off. 1. AVIONICS Switch............................................ON, AS REQUIRED Flight Displays Too Dim • Note • Photocell backlighting for the flight displays, bezel, audio panel, and FMS keyboard is manually controlled through the dimmer control on the instrument panel bolster.
Cirrus Design SR20 Section 3A Abnormal Procedures MFD Cooling Fan Failure MFD FAN FAIL Advisory MFD FAN FAIL The cooling fan for the MFD is inoperative. 1. AVIONICS FAN 1 Circuit Breaker ....................................... CYCLE If annunciation does not extinguish: a. High cabin temperatures .... LAND AS SOON AS PRACTICAL b. Low cabin temperatures .....................
Section 3A Abnormal Procedures Cirrus Design SR20 Pitot Static System Pitot Static Malfunction Static Source Blocked If erroneous readings of the static source instruments (airspeed, altimeter and vertical speed) are suspected, the alternate static source valve, on side of console near pilot’s right ankle, should be opened to supply static pressure from the cabin to these instruments.
Cirrus Design SR20 Section 3A Abnormal Procedures Pitot Heat Required Annunciation PITOT HEAT REQUIRED Caution PITOT HT RQD Displayed 20 seconds after system detects OAT is less than 41°F (5°C) and Pitot Heat Switch is OFF. 1. Pitot Heat ...................................................................................ON Pitot Heat Required Annunciation PITOT HEAT OFF Caution PITOT HT OFF Displayed when system detects OAT is above 41°F (5°C) and Pitot Heat Switch is OFF. 1. Pitot Heat ................
Section 3A Abnormal Procedures Cirrus Design SR20 Flight Control System Electric Trim/Autopilot Failure Any failure or malfunction of the electric trim or autopilot can be overridden by use of the control yoke. If runaway trim is the problem, deenergize the circuit by pulling the appropriate circuit breakers and land as soon as conditions permit. 1. Airplane Control ......................................... MAINTAIN MANUALLY 2. Autopilot (if engaged) .................................................
Cirrus Design SR20 Section 3A Abnormal Procedures Landing Gear System Brake Failure During Taxi Ground steering is accomplished by differential braking. However, increasing power may allow some rudder control due to increased groundspeed and airflow over the rudder. 1. Engine Power......................................................... AS REQUIRED • To stop airplane - REDUCE • If necessary for steering - INCREASE 2. Directional Control ............................... MAINTAIN WITH RUDDER 3.
Section 3A Abnormal Procedures Cirrus Design SR20 Other Conditions Aborted Takeoff Use as much of the remaining runway as needed to safely bring the airplane to a stop or to slow the airplane sufficiently to turn off runway. 1. Power Lever ............................................................................ IDLE 2. Brakes ....................................................................
Cirrus Design SR20 Section 3A Abnormal Procedures Parking Brake Engaged Annunciation PARK BRAKE Caution PARK BRAKE Parking brake is set. 1. Parking Brake ................................................................ RELEASE 2. Monitor CAS for BRAKE TEMP Caution. Stop aircraft and allow the brakes to cool if necessary. Communications Failure If, after following the checklist procedure, communication is not restored, proceed with FAR/AIM lost communications procedures.
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Cirrus Design SR20 Section 4 Normal Procedures Section 4 Normal Procedures Table of Contents Introduction ........................................................................................ 3 Airspeeds for Normal Operation ........................................................ 3 Normal Procedures ............................................................................ 4 Preflight Inspection ......................................................................... 4 Preflight Walk-Around .......
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Cirrus Design SR20 Section 4 Normal Procedures Introduction This section provides amplified procedures for normal operation. Normal procedures associated with optional systems can be found in Section 9. Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3050 lb. and may be used for any lesser weight.
Section 4 Normal Procedures Cirrus Design SR20 Normal Procedures Preflight Inspection Before carrying out preflight inspections, ensure that all required maintenance has been accomplished. Review your flight plan and compute weight and balance.
Cirrus Design SR20 Section 4 Normal Procedures 1. Cabin a. Required Documents.................................................On Board b. Avionics Power Switch....................................................... OFF c. Bat 2 Master Switch ...........................................................ON d. PFD ........................................................................... Verify On e. Essential Bus Voltage............................................. 23-25 Volts f. Flap Position Light ...
Section 4 Normal Procedures Cirrus Design SR20 3. Empennage a. Tiedown Rope .............................................................Remove b. Horizontal and Vertical Stabilizers .............................Condition • Note • Verify tape covering the forward and aft inspection holes located on outboard ends of horizontal stabilizer is installed and securely attached. c. Elevator and Tab............................... Condition and Movement d. Rudder................................................
Cirrus Design SR20 Section 4 Normal Procedures e. Tire ............................................Condition, Inflation, and Wear • Caution • Clean and inspect temperature indicator installed to piston housing. If indicator center is black, the brake assembly has been overheated. The brake linings must be inspected and Orings replaced. f. Wheel and Brakes ....... Fluid Leaks, Evidence of Overheating, General Condition, and Security. g. Chocks and Tiedown Ropes........................................
Section 4 Normal Procedures Cirrus Design SR20 d. External Power .....................................................Door Secure e. Exhaust Pipe(s) .................Condition, Security, and Clearance 11. Left Main Gear and Forward Wing a. Wheel fairings ....................... Security, Accumulation of Debris b. Tire ............................................Condition, Inflation, and Wear • Caution • Clean and inspect temperature indicator installed to piston housing.
Cirrus Design SR20 Section 4 Normal Procedures Before Starting Engine 1. Preflight Inspection ...................................................COMPLETED • WARNING • Ensure that the airplane is properly loaded and within the AFM’s weight and balance limitations prior to takeoff. 2. Weight and Balance............................................Verify within limits 3. Emergency Equipment ................................................ ON BOARD 4. Passengers ................................................
Section 4 Normal Procedures Cirrus Design SR20 Starting Engine If the engine is warm, no priming is required. For the first start of the day and in cold conditions, prime will be necessary. Weak intermittent firing followed by puffs of black smoke from the exhaust stack indicates over-priming or flooding. Excess fuel can be cleared from the combustion chambers by the following procedure: • Turn fuel pump off. • Allow fuel to drain from intake tubes.
Cirrus Design SR20 Section 4 Normal Procedures 6. Power Lever ........................................................ FULL FORWARD 7. Fuel Pump .................................................... PRIME, then BOOST • Note • On first start of the day, especially under cool ambient conditions, holding Fuel Pump switch to PRIME for 2 seconds will improve starting. 8. Propeller Area ..................................................................... CLEAR 9. Power Lever ....................................
Section 4 Normal Procedures Cirrus Design SR20 Before Taxiing 1. Flaps ................................................................................. UP (0%) 2. Radios/Avionics...................................................... AS REQUIRED 3. Cabin Heat/Defrost ............................................... AS REQUIRED 4. Fuel Selector ...........................................................
Cirrus Design SR20 Section 4 Normal Procedures Before Takeoff During cold weather operations, the engine should be properly warmed up before takeoff. In most cases this is accomplished when the oil temperature has reached at least 100°F (38°C). In warm or hot weather, precautions should be taken to avoid overheating during prolonged ground engine operation. Additionally, long periods of idling may cause fouled spark plugs.
Section 4 Normal Procedures Cirrus Design SR20 16. Pitot Heat ............................................................... AS REQUIRED • Note • Pitot Heat should be turned ON for flight into IMC, flight into visible moisture, or whenever ambient temperatures are 41° F (5° C) or less. 17. Navigation Lights.................................................... AS REQUIRED 18. Landing Light ......................................................... AS REQUIRED 19. Magnetos ...................................
Cirrus Design SR20 Section 4 Normal Procedures Takeoff • Note • The engine is equipped with an altitude compensating fuel pump that automatically provides the proper full rich mixture. Because of this, the mixture should be left full rich for takeoff, even at high altitude airfields. Power Check: Check full-throttle engine operation early in takeoff run. The engine should run smoothly and turn approximately 2700 RPM. All engine parameters should read in the green.
Section 4 Normal Procedures Cirrus Design SR20 Normal Takeoff 1. Brakes ....................................RELEASE (Steer with Rudder Only) 2. Power Lever ........................................................FULL FORWARD 3. Engine Parameters ............................................................ CHECK 4. Elevator Control ........................ ROTATE Smoothly at 65-70 KIAS 5. At 85 KIAS, Flaps....................................................................... UP Short Field Takeoff 1.
Cirrus Design SR20 Section 4 Normal Procedures Climb Normal climbs are performed flaps UP (0%) and full power at speeds 5 to 10 knots higher than best rate-of-climb speeds. These higher speeds give the best combination of performance, visibility and engine cooling. For maximum rate of climb, use the best rate-of-climb speeds shown in the rate-of-climb chart in Section 5. If an obstruction dictates the use of a steep climb angle, the best angle-of-climb speed should be used.
Section 4 Normal Procedures Cirrus Design SR20 Cruise Normal cruising is performed between 55% and 85% power. The engine power setting and corresponding fuel consumption for various altitudes and temperatures can be determined by using the cruise data in Section 5. The selection of cruise altitude is made based on the most favorable wind conditions and the desired power settings. These significant factors should be considered on every trip to reduce fuel consumption.
Cirrus Design SR20 Section 4 Normal Procedures Cruise Leaning The engine is equipped with an altitude compensating fuel pump that automatically provides the proper full rich mixture. Because of this, the mixture should be set to full rich to allow the aneroid to provide auto leaning for the engine during all flight conditions. If additional cruise leaning beyond that provided by the aneroid is desired, be advised that there may not be a 75° temperature rise from full rich to peak.
Section 4 Normal Procedures Cirrus Design SR20 Descent 1. Altimeter ................................................................................... SET 2. Cabin Heat/Defrost ................................................ AS REQUIRED 3. Landing Light ............................................................................ ON 4. Fuel System ....................................................................... CHECK 5. Mixture ...................................................................
Cirrus Design SR20 Section 4 Normal Procedures Landing • Caution • Landings should be made with full flaps. Landings with less than full flaps are recommended only if the flaps fail to deploy or to extend the aircraft’s glide distance due to engine malfunction. Landings with flaps at 50% or 0%; power should be used to achieve a normal glide path and low descent rate. Flare should be minimized. Normal Landing Normal landings are made with full flaps with power on or off.
Section 4 Normal Procedures Cirrus Design SR20 Balked Landing/Go-Around In a balked landing (go-around) climb, disengage autopilot, apply full power, then reduce the flap setting to 50%. If obstacles must be cleared during the go-around, climb at the best angle of climb with 50% flaps. After clearing any obstacles, retract the flaps and accelerate to the normal flaps-up climb speed. 1. Autopilot .....................................................................DISENGAGE 2. Power Lever .................
Cirrus Design SR20 Section 4 Normal Procedures Shutdown 1. Fuel Pump (if used) ................................................................ OFF 2. Throttle.................................................................................... IDLE • Caution • Note that the engine hesitates as the switch cycles through the “OFF” position. If the engine does not hesitate, one or both magnetos are not grounded. Prominently mark the propeller as being “Hot,” and contact maintenance personnel immediately. 3.
Section 4 Normal Procedures Cirrus Design SR20 Environmental Considerations Cold Weather Operation • Caution • An engine that has been superficially warmed, may start and appear to run satisfactorily, but can be damaged from lack of lubrication due to the congealed oil blocking proper oil flow through the engine. The amount of damage will vary and may not become evident for many hours. However, the engine may be severely damaged and may fail shortly following application of high power.
Cirrus Design SR20 Section 4 Normal Procedures 1. Ignition Switch.......................................................................... OFF • WARNING • Use caution when pulling the propeller through by hand. Make sure ignition switch is OFF, keys are out of ignition, and then act as if the engine will start. 2. Propeller .......................................... Hand TURN several rotations 3. External Power (If applicable) ....................................... CONNECT 4. Brakes ....................
Section 4 Normal Procedures Cirrus Design SR20 Hot Weather Operation Avoid prolonged engine operation on the ground. Fuel BOOST must be ON for engine start and takeoff, and should be ON during climb for vapor suppression which could occur under hot ambient conditions or after extended idle. Noise Characteristics/Abatement The certificated noise levels for the aircraft established in accordance with FAR 36 Appendix G are: Configuration Actual Maximum Allowable Two-blade Propeller 84.79 dB(A) 87.
Cirrus Design SR20 Section 5 Performance Data Section 5 Performance Data Table of Contents Introduction ........................................................................................ 3 Associated Conditions Affecting Performance................................ 3 Demonstrated Operating Temperature ........................................... 3 Airspeed Calibration - Normal Static Source...................................... 4 Airspeed Calibration - Alternate Static Source..........................
Section 5 Performance Data Cirrus Design SR20 Intentionally Left Blank 5-2 P/N 11934-004 Original Issue
Cirrus Design SR20 Section 5 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 & endurance).
Section 5 Performance Data Cirrus Design SR20 Airspeed Calibration - Normal Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Note • Indicated airspeed values assume zero instrument error.
Cirrus Design SR20 Section 5 Performance Data Airspeed Calibration - Alternate Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster & Vents .................................................................................. ON • Note • Indicated airspeed values assume zero instrument error.
Section 5 Performance Data Cirrus Design SR20 Altitude Correction - Normal Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • 3050 LB • Note • Add correction to desired altitude to obtain indicated altitude to fly. Indicated airspeed values assume zero instrument error. KIAS: Knots Indicated Airspeed. CORRECTION TO BE ADDED - FEET Flaps Press Alt Normal Static Source - KIAS 60 70 80 90 100 120 140 160 180 200 S.
Cirrus Design SR20 Section 5 Performance Data Altitude Correction - Alternate Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster, & Vents.................................................................................. ON • Note • Add correction to desired altitude to obtain indicated altitude to fly. Indicated airspeed values assume zero instrument error. KIAS: Knots Indicated Airspeed.
Section 5 Performance Data Cirrus Design SR20 Temperature Conversion To convert from Celsius (°C) to Fahrenheit (°F), find, in the shaded columns, the number representing the temperature value (°C) to be converted. The equivalent Fahrenheit temperature is read to the right. EXAMPLE: 38°C = 100°F. To convert from Fahrenheit (°F) to Celsius (°C), find in the shaded columns area, the number representing the temperature value (°F) to be converted. The equivalent Celsius temperature is read to the left.
Cirrus Design SR20 Section 5 Performance Data Outside Air Temperature for ISA Condition Press Alt Feet ISA-40°C ISA-20°C ISA+10°C ISA+20°C °C °F °C °F °C °F °C °F °C °F SL -25 -13 -5 23 15 59 25 77 35 95 1000 -27 -18 -7 18 13 54 23 72 33 90 2000 -29 -20 -9 16 11 52 21 70 31 88 3000 -31 -24 -11 12 9 48 19 66 29 84 4000 -33 -27 -13 9 7 45 17 63 27 81 5000 -35 -31 -15 5 5 41 15 59 25 77 6000 -37 -34 -17 2 3 38 13 56 23
Section 5 Performance Data Cirrus Design SR20 Stall Speeds Conditions: • Weight ........................................................................................................ 3050 LB • CG ..................................................................................................................Noted • Power................................................................................................................. Idle • Bank Angle .....................................................
Cirrus Design SR20 Section 5 Performance Data Wind Components Example: • Runway Heading ................................................................................................ 10° • Wind Direction.................................................................................................... 60° • Wind Velocity..............................................................................................15 Knots • Note • The max demonstrated crosswind is 20 knots.
Section 5 Performance Data Cirrus Design SR20 Takeoff Distance Conditions: • Winds................................................................................................................ Zero • Runway.........................................................................................Dry, Level, Paved • Flaps................................................................................................................. 50% • Power...............................................................
Cirrus Design SR20 Section 5 Performance Data Takeoff Distance - 3050 LB WEIGHT = 3050 LB Speed at Liftoff = 71 KIAS Speed over 50 Ft. Obstacle = 77 KIAS Flaps - 50% · Takeoff Pwr · Dry Paved PRESS ALT FT DISTANCE Headwind: Subtract 10% for each 12 knots headwind. Tailwind: Add 10% for each 2 knots tailwind up to 10 knots. Runway Slope: Ref. Factors. Dry Grass: Add 20% to Ground Roll. Wet Grass: Add 30% to Ground Roll.
Section 5 Performance Data Cirrus Design SR20 Takeoff Distance - 2500 LB WEIGHT = 2500 LB Speed at Liftoff = 68 KIAS Speed over 50 Ft Obstacle = 75 KIAS Flaps - 50% · Takeoff Pwr · Dry Paved PRESS ALT FT DISTANCE Headwind: Subtract 10% for each 12 knots headwind. Tailwind: Add 10% for each 2 knots tailwind up to 10 knots. Runway Slope: Ref. Factors. Dry Grass: Add 20% to Ground Roll. Wet Grass: Add 30% to Ground Roll.
Cirrus Design SR20 Section 5 Performance Data Takeoff Climb Gradient Conditions: • Power ....................................................................................................Full Throttle • Mixture ............................................................................................ Set per Placard • Flaps .................................................................................................................50% • Airspeed ....................................................
Section 5 Performance Data Cirrus Design SR20 Takeoff Rate of Climb Conditions: • Power.................................................................................................... Full Throttle • Mixture............................................................................................ Set per Placard • Flaps................................................................................................................. 50% • Airspeed ......................................................
Cirrus Design SR20 Section 5 Performance Data Enroute Climb Gradient Conditions: • Power ....................................................................................................Full Throttle • Mixture .......................................................................................................Full Rich • Flaps .......................................................................................................... 0% (UP) • Airspeed ..................................................
Section 5 Performance Data Cirrus Design SR20 Enroute Rate of Climb Conditions: • Power.................................................................................................... Full Throttle • Mixture................................................................................................. As Required • Flaps...........................................................................................................0% (UP) • Airspeed ........................................................
Cirrus Design SR20 Section 5 Performance Data Enroute Rate of Climb Vs Density Altitude Conditions: • • • • Power .................................................................................................... Full Throttle Mixture ....................................................................................................... Full Rich Flaps ...........................................................................................................0% (UP) Airspeed ............................
Section 5 Performance Data Cirrus Design SR20 Time, Fuel and Distance to Climb Conditions: • Power.................................................................................................... Full Throttle • Mixture....................................................................................................... Full Rich • Fuel Density...........................................................................................6.0 LB/GAL • Weight .................................................
Cirrus Design SR20 Section 5 Performance Data Cruise Performance Conditions: • Cruise Weight............................................................................................. 2600 LB • Winds ............................................................................................................... Zero • Note • Subtract 10 KTAS if nose wheel pant and fairing removed. Lower KTAS by 10% if nose and main wheel pants & fairings are removed.
Section 5 Performance Data Cirrus Design SR20 Cruise Performance (Continued) 8000 Feet Pressure Altitude ISA - 30° C (-31° C) ISA (-1° C) ISA + 30° C (29° C) RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH 2700 22.2 82% 157 12.9 77% 157 11.6 73% 154 11.4 2500 22.2 73% 150 11.4 69% 150 11.0 65% 147 10.6 2500 21.2 69% 146 10.9 65% 146 10.5 62% 143 10.2 2500 20.1 64% 142 10.4 60% 142 10.0 57% 139 9.7 2500 18.9 59% 136 9.8 55% 136 9.
Cirrus Design SR20 Section 5 Performance Data Range / Endurance Profile Conditions: • Weight ........................................................................................................ 3000 LB • Temperature ....................................................................................... Standard Day • Winds ............................................................................................................... Zero • Mixture ......................................................
Section 5 Performance Data Cirrus Design SR20 Range / Endurance Profile (Continued) 65% POWER Press Climb Alt Fuel Mixture = Best Power FT Gal Fuel Remaining For Cruise Gal Airspeed Fuel Flow Endurance KTAS GPH Hours NM Nm/Gal 0 0.0 46.3 137 10.5 4.4 608 13.0 2000 0.6 45.7 139 10.5 4.4 620 13.1 4000 1.3 45.0 141 10.5 4.4 628 13.2 6000 2.0 44.3 143 10.5 4.4 635 13.2 8000 2.9 43.4 145 10.5 4.4 645 13.3 10000 3.8 42.5 147 10.5 4.4 654 13.
Cirrus Design SR20 Section 5 Performance Data Balked Landing Climb Gradient Conditions: • Power ....................................................................................................Full Throttle • Mixture .......................................................................................................Full Rich • Flaps ...................................................................................................... 100% (DN) • Airspeed .............................................
Section 5 Performance Data Cirrus Design SR20 Balked Landing Rate of Climb Conditions: • Power.................................................................................................... Full Throttle • Mixture....................................................................................................... Full Rich • Flaps...................................................................................................... 100% (DN) • Climb Airspeed .........................................
Cirrus Design SR20 Section 5 Performance Data Landing Distance Conditions: • Winds ............................................................................................................... Zero • Runway ........................................................................................ Dry, Level, Paved • Flaps. ..............................................................................................................100% • Power ..............................................................
Section 5 Performance Data Cirrus Design SR20 Landing Distance WEIGHT = 3050 LB Headwind: Subtract 10% per each Speed over 50 Ft Obstacle = 77 KIAS 13 knots headwind. Flaps - 100% · Idle · Dry, Level Paved Surface Tailwind: Add 10% for each 2 knots tailwind up to 10 knots. Runway Slope: Ref. Factors.
Cirrus Design SR20 Section 6 Weight and Balance Data Section 6 Weight and Balance Data Table of Contents Introduction ........................................................................................ 3 Airplane Weighing Form .................................................................... 4 Airplane Weighing Procedures .......................................................... 5 Loading Instructions ...........................................................................
Section 6 Weight and Balance Data Cirrus Design SR20 Intentionally Left Blank 6-2 P/N 11934-004 Original Issue
Cirrus Design SR20 Section 6 Weight and Balance Data Introduction This section describes the procedure for establishing the basic empty weight and moment of the airplane. Sample forms are provided for reference. Procedures for calculating the weight and moment for various operations are also provided. A comprehensive list of all equipment available for this airplane is included at the back of this section.
Section 6 Weight and Balance Data Cirrus Design SR20 Airplane Weighing Form REF DATUM FS 0.0 FS 100.0 FS 142.5 WL 100.
Cirrus Design SR20 Section 6 Weight and Balance Data Airplane Weighing Procedures A basic empty weight and center of gravity were established for this airplane when the airplane was weighed just prior to initial delivery. However, major modifications, loss of records, addition or relocation of equipment, accomplishment of service bulletins, and weight gain over time may require re-weighing to keep the basic empty weight and center of gravity current.
Section 6 Weight and Balance Data Cirrus Design SR20 side of the firewall (FS 100). Add 100 to this measurement to obtain left and right weighing point arm (dimension ‘A’). Typically, dimension ‘A’ will be in the neighborhood of 157.5. b. Obtain measurement ‘y’ by measuring horizontally and parallel to the airplane centerline (BL 0), from center of nosewheel axle, left side, to a plumb bob dropped from the line stretched between the main wheel centers. Repeat on right side and average the measurements.
Cirrus Design SR20 Section 6 Weight and Balance Data Airplane Leveling Spirit Level LONGITUDINAL LEVELING Spirit Level Straight Edge Straight Edge Spacer Block Straight Edge Door Sill Door Sill LATERAL LEVELING Spacer Block SR22_FM06_1440A Figure 6-2 P/N 11934-004 Original Issue 6-7
Section 6 Weight and Balance Data Cirrus Design 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. The calculated moment is then compared to the Moment Limits chart or table (Figure 6-5) for a determination of proper loading.
Cirrus Design SR20 Section 6 Weight and Balance Data Weight and Balance Loading Form • Note • For Center of Gravity Envelope, refer to Section 2, Limitations. The Takeoff Condition Weight must not exceed 3050 lb. The Takeoff Condition Moment must be within the Minimum Moment to Maximum Moment range at the Takeoff Condition Weight. (Refer to Moment Limits). Serial Num: __________________________ Date: ______________ Reg. Num: ___________________________ Initials:_____________ Item Description 1.
Section 6 Weight and Balance Data Cirrus Design SR20 Loading Data Use the following chart or table to determine the moment/1000 for fuel and payload items to complete the Loading Form. 600 Fuel 500 Fwd Pass Weight - Pounds Loading Chart Aft Pass 400 300 200 Baggage 100 0 0.0 20.0 40.0 60.0 80.0 Moment/1000 Weight LB Fwd Aft Pass Pass FS 143.5 FS 180.0 Baggage Fuel Weight FS 208.0 FS 153.8 LB SR20_FM06_3029 Fwd Aft Fuel Pass Pass FS 143.5 FS 180.0 FS 153.8 20 2.87 3.60 4.16 3.
Cirrus Design SR20 Section 6 Weight and Balance Data Moment Limits Use the following chart or table to determine if the weight and moment from the completed Weight and Balance Loading Form (Figure 6-3) are within limits.
Section 6 Weight and Balance Data Cirrus Design 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: In Out of Weight Change Running Basic Added (+) or Removed (-) Empty Weight Item No. Date Page Description of Article or Modification WT LB ARM IN.
Cirrus Design SR20 Section 6 Weight and Balance Data Equipment List This list will be determined after the final equipment has been installed in the aircraft.
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Cirrus Design SR20 Section 7 Airplane and Systems Description Section 7 Airplane and Systems Description Table of Contents Introduction ........................................................................................ 5 Airframe ............................................................................................. 6 Fuselage ......................................................................................... 6 Wings........................................................................
Section 7 Airplane and Systems Description Cirrus Design SR20 Ignition and Starter System........................................................... 36 Air Induction System ..................................................................... 36 Engine Exhaust............................................................................. 37 Engine Fuel Injection .................................................................... 37 Engine Cooling.............................................................
Cirrus Design SR20 Section 7 Airplane and Systems Description Introduction This section provides a basic description and operation of the standard airplane and its systems. Optional equipment described within this section is identified as optional. • Note • Some optional equipment may not be described in this section. For description and operation of optional equipment not described in this section, refer to Section 9, Supplements.
Section 7 Airplane and Systems Description Cirrus Design SR20 Airframe Fuselage The aircraft’s monocoque fuselage is constructed primarily of composite materials and is designed to be aerodynamically efficient. The cabin area is bounded on the forward side by the firewall at fuselage station 100, and on the rear by the aft baggage compartment bulkhead at fuselage station 222. Comfortable seating is provided for four adults.
Cirrus Design SR20 Section 7 Airplane and Systems Description Empennage The empennage consists of a horizontal stabilizer, a two-piece elevator, a vertical fin and a rudder. All of the empennage components are conventional spar (shear web), rib, and skin construction. The horizontal stabilizer is a single composite structure from tip to tip. The two-piece elevator, attached to the horizontal stabilizer, is aluminum.
Section 7 Airplane and Systems Description Cirrus Design SR20 Flight Controls The aircraft uses conventional flight controls for ailerons, elevator and rudder. The control surfaces are pilot controlled through either of two single-handed side control yokes mounted beneath the instrument panel. The location and design of the control yokes allow easy, natural use by the pilot. The control system uses a combination of push rods, cables and bell cranks for control of the surfaces.
Cirrus Design SR20 Section 7 Airplane and Systems Description SR20_FM07_1461 Figure 7-1 Elevator System P/N 11934-004 Original Issue 7-9
Section 7 Airplane and Systems Description Cirrus Design 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. Aileron control motion is generated through the pilot's control yokes by rotating the yokes in pivoting bearing carriages. Push rods link the pivoting carriages to a centrally located pulley sector.
Cirrus Design SR20 Section 7 Airplane and Systems Description SR20_FM07_1462 Figure 7-2 Aileron System P/N 11934-004 Original Issue 7-11
Section 7 Airplane and Systems Description Cirrus Design SR20 Rudder System The rudder provides airplane directional (yaw) control. The rudder is of conventional design with skin, spar and ribs manufactured of aluminum. The rudder is attached to the aft vertical stabilizer shear web at three hinge points and to the fuselage tailcone at the rudder control bell crank.
Cirrus Design SR20 Section 7 Airplane and Systems Description SR20_FM07_1463 Figure 7-3 Rudder System P/N 11934-004 Original Issue 7-13
Section 7 Airplane and Systems Description Cirrus Design SR20 Instrument Panel The instrument panel is of all metal construction and is installed in sections so equipment can be easily removed for maintenance. The surrounding glareshield is made of composite material and projects over the instrument panel to reduce reflections on the windshield from lighted equipment and to shield the panel equipment from glare.
Cirrus Design SR20 Section 7 Airplane and Systems Description 1 20 2 19 3 4 18 5 6 6 17 16 15 14 4 7 13 9 12 10 8 11 Legend 1. Cirrus Airframe Parachute System (CAPS) Activation T-Handle Cover 2. Magnetic Compass 3. Multifunction Display 4. Fresh Air “Eyeball” Outlet 5. Temperature/Ventilation Controls 6. Control Yoke 7. Air Outlet 8. Rudder Pedals 9. Flap Control & Position Indicators 10. Armrest 11. Passenger Audio Jacks 12. Engine & Fuel System Controls 13.
Section 7 Airplane and Systems Description Cirrus Design SR20 Flight Instruments Flight instruments and annunciations are displayed on the Primary Flight Display (PFD) located directed in front of the pilot. The PFD presents the primary flight instruments arranged in the conventional basic “T” configuration. Standby instruments for airspeed, attitude and altitude are mounted on the LH bolster panel and are on separate power sources than the PFD.
Cirrus Design SR20 3 4 5 6 7 8 25 10 11 12 125° 24 12 E 23 13 13 14 6 S 22 16 1.01NM N 33 19 15 24 XTK 20 TERM 3 21 GPS 21 LEGEND 1. True Airspeed 2. Airspeed Indicator 3. Horizontal Situation Indicator (HSI) 4. Attitude Indicator 5. Slip/Skid Indicator 6. Vertical Deviation Indicator (VDI) 7. Selected Altitude Bug 8. Current Altitude 9. Altimeter 10. Selected Altitude 11. Vertical Speed Indicator (VSI) 12. Current Heading 13. Lubber Line 14. Selected Heading Bug 15.
Section 7 Airplane and Systems Description Cirrus Design SR20 Attitude Indicator The primary attitude indicator is show on the upper center of the PFD and displays pitch, roll, and slip/skid information provided by the Attitude and Heading Reference System (AHRS). Above and below the horizon line, major pitch marks and labels are shown for every 10°, up to 80°. Between 25° below and 45° above the horizon line, the pitch index scale is graduated in 5° increments with every 10° of pitch labeled.
Cirrus Design SR20 Section 7 Airplane and Systems Description Airspeed Indicator Primary airspeed data is provided by the Air Data Computer and is shown as a vertical tape along the upper left side of the PFD. The airspeed scale is graduated with major tick marks at intervals of 10 knots and minor tick marks at intervals of 5 knots. Speed indication starts at 20 knots, with 60 knots of airspeed viewable at any time. The actual airspeed is displayed inside the black pointer.
Section 7 Airplane and Systems Description Cirrus Design SR20 Altimeter Primary altitude data is provided by the Air Data Computer and is shown as a vertical tape along the upper right side of the PFD. The altimeter scale is graduated with major tick marks at intervals of 100 feet and minor tick marks at intervals of 20 feet. Six hundred (600) feet of barometric altitude is viewable at any time. The local barometric pressure is set using the barometric adjustment knob on the PFD.
Cirrus Design SR20 Section 7 Airplane and Systems Description The HSI presents heading, turn rate, course deviation, bearing, and navigation source information in a 360° compass-rose format. The HSI contains a Course Deviation Indicator (CDI) with a course pointer arrow, a To/From arrow, a sliding deviation bar, and scale. The course pointer is a single line arrow (GPS, VOR1, and LOC1) or a double line arrow (VOR2 and LOC2) which points in the direction of the set course.
Section 7 Airplane and Systems Description Cirrus Design 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. The flaps are selectively set to three positions: 0%, 50% (16°) and 100% (32°) by operating the FLAP control switch.
Cirrus Design SR20 Section 7 Airplane and Systems Description SR20_FM07_1460 Figure 7-6 Wing Flaps P/N 11934-004 Original Issue 7-23
Section 7 Airplane and Systems Description Cirrus Design 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. The main wheels and wheel pants are bolted to the struts. Each main gear wheel has a 15 x 6.00 x 6 tire with inner-tube installed.
Cirrus Design SR20 Section 7 Airplane and Systems Description each brake assembly which transmit signals via the Engine Airframe Unit to the Engine Indicating System for brake temperature caution/ warning annunciation. Should any of these symptoms occur, immediate maintenance is required. If, during taxi or landing roll, braking action decreases, let up on the toe brakes and then reapply the brakes with heavy pressure.
Section 7 Airplane and Systems Description Cirrus Design 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. The door is locked from the outside with a key lock. The baggage compartment key will also open the cabin doors. The baggage compartment extends from behind the rear passenger seat to the aft cabin bulkhead.
Cirrus Design SR20 Section 7 Airplane and Systems Description Seats The seating arrangement consists of two individually adjustable seats for the pilot and front seat passenger and two individual seats with fold down seat backs for the rear seat passengers.The front seats are adjustable fore and aft and the seat backs can be reclined for passenger comfort or folded forward for rear seat access. Integral headrests are provided.
Section 7 Airplane and Systems Description Cirrus Design SR20 Seat Belt and Shoulder Harness Integrated seat belt and shoulder harness assemblies with inertia reels are provided for the pilot and each passenger. The rear seat belts are attached to fittings on the floorboard and the forward seat belts are attached to the seat frame. The shoulder harnesses are attached to inertia reels mounted in the seat back for the front seats and on the baggage compartment rear bulkhead for the rear seats.
Cirrus Design SR20 Section 7 Airplane and Systems Description 4. Restraint harnesses should fit snug against the shoulder with the lap buckle centered and tightened around the hips. To release the restraints: 1. Grasp the top of the buckle opposite the link and pull outward. The link will slip free of buckle. 2. Slip arms from behind the harness. Cabin Doors Two large forward hinged doors allow crew and passengers to enter and exit the cabin.
Section 7 Airplane and Systems Description Cirrus Design SR20 Engine The aircraft is powered by a Teledyne Continental IO-360-ES, sixcylinder, 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. The engine is attached to the firewall by a four-point steel mount structure.
Cirrus Design SR20 Section 7 Airplane and Systems Description Mixture Control The mixture control lever, labeled RICH-MIXTURE-CUTOFF, on the console adjusts the proportion of fuel to air for combustion. The Mixture Control Lever is mechanically linked to the mixture control valve in the engine-driven fuel pump. Moving the lever forward (towards RICH) repositions the valve allowing greater proportions of fuel and moving the lever aft (towards CUTOFF) reduces (leans) the proportion of fuel.
Section 7 Airplane and Systems Description Cirrus Design SR20 Engine Indicating Engine information is displayed as analog-style gages, bar graphs, and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), all essential engine information is displayed along the LH edge of the display.
Cirrus Design SR20 1 Section 7 Airplane and Systems Description 2 3 4 5 6 Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Engine Instruments 7 8 9 10 LEGEND 1. Percent Power 2. CHT 3. Tachometer 4. EGT 5. Manifold Pressure 6. Oil Temperature and Pressure 7. Alternate Air Control 8. Power Lever 9. Friction Control 10.
Section 7 Airplane and Systems Description Cirrus Design SR20 Tachometer Engine speed (RPM) is shown in the upper mid-left corner of the ENGINE page as both a simulated tachometer and as a digital value. The tachometer pointer sweeps a scale range from 0 to 3000 RPM in 100 RPM increments. The digital RPM value is displayed in increments of 10 RPM in white numerals below the gage.
Cirrus Design SR20 Section 7 Airplane and Systems Description Oil Temperature Oil temperature is shown in the upper right corner of the ENGINE page, opposite the oil pressure scale, as both a simulated temperature gage and as a digital value. The gage pointer sweeps a scale range from 75°F to 250°F in 50°F increments. The digital temperature value is displayed in white numerals below the gage.
Section 7 Airplane and Systems Description Cirrus Design SR20 Engine Lubrication System The engine is provided with a wet-sump, high-pressure oil system for engine lubrication and cooling. Oil for engine lubrication is drawn from an eight-quart capacity sump through an oil suction strainer screen and directed to the engine-mounted oil cooler.
Cirrus Design SR20 Section 7 Airplane and Systems Description finally through the cylinder intake ports into the combustion chambers. Should the dry induction filter become clogged, a pilot controlled alternate induction air door can be opened, allowing engine operation to continue. For additional information on the Alternate Air Control, refer to Engine Controls - Alternate Air Control description in this section. Engine Exhaust Engine exhaust gases are routed through a tuned exhaust system.
Section 7 Airplane and Systems Description Cirrus Design SR20 Propeller The airplane is equipped with a constant-speed, aluminum-alloy propeller with a governor. The airplane is available with the standard two-blade (76” diameter) propeller or an optional three-blade (74” diameter) propeller. The propeller governor automatically adjusts propeller pitch to regulate propeller and engine RPM.
Cirrus Design SR20 Section 7 Airplane and Systems Description Fuel System An 56-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 29.3-gallon capacity (28 gallon usable) vented integral fuel tank and a fuel collector/sump in each wing, a three position selector valve, an electric fuel pump, and an engine-driven fuel pump.
Section 7 Airplane and Systems Description Cirrus Design SR20 contamination and grade. The fuel must be sampled prior to each flight. A sampler cup is provided to drain a small amount of fuel from the wing tank drains, the collector tank drains, and the gascolator drain. If takeoff weight limitations for the next flight permit, the fuel tanks should be filled after each flight to prevent condensation.
Cirrus Design SR20 VENT Section 7 Airplane and Systems Description ANNUNCIATOR FUEL FUEL QUANTITY INDICATOR FILLER VENT FILLER L. WING TANK R. WING TANK L. WING COLLECTOR R.
Section 7 Airplane and Systems Description Cirrus Design SR20 Fuel Indicating Fuel system information is displayed as analog-style gages and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), fuel flow is displayed along the LH edge of the display. Fuel data is acquired by the Engine Airframe Unit which transmits the data to the Engine Indicating System for display as described in the following pages.
Cirrus Design SR20 Section 7 Airplane and Systems Description 1 Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) 2 3 4 5 6 Fuel System Indication 7 LEGEND 1. Fuel Flow 2. Fuel Used (Totalizer) 3. Fuel Remaining (Totalizer) 4. Time Remaining (Totalizer) 5. Fuel Range (Totalizer) 6. Nautical Miles Per Gallon (Totalizer) 7. Fuel Pump Switch 8. Fuel Quantity Gage (Float Sensor) 9.
Section 7 Airplane and Systems Description Cirrus Design SR20 Each indicator also provides an output signal to the Engine Airframe Unit that is processed and transmitted to the CAS window for display when the fuel quantity goes below approximately 7 gallons indicated. 28 VDC for fuel quantity system operation is supplied through the 3amp FUEL QTY circuit breaker on MAIN BUS 1.
Cirrus Design SR20 Section 7 Airplane and Systems Description Fuel Totalizer and Calculated Information Fuel totalizer calculations are located in the lower right section of the ENGINE page and are separate and independent of the fuel quantity gage and float sensor system. The fuel totalizer monitors fuel flow and calculates fuel-to-destination, fuel used, fuel remaining, time remaining, fuel range, and nautical miles per gallon.
Section 7 Airplane and Systems Description Cirrus Design SR20 Electrical System The airplane is equipped with a two-alternator, two-battery, 28-volt direct current (VDC) electrical system designed to reduce the risk of electrical system faults. The system provides uninterrupted power for avionics, flight instrumentation, lighting, and other electrically operated and controlled systems during normal operation.
Cirrus Design SR20 Section 7 Airplane and Systems Description LANDING LIGHT 100A F ALT 1 B 7.
Section 7 Airplane and Systems Description Cirrus Design SR20 Power Distribution Power is supplied to the airplane circuits through three distribution buses contained in the MCU; Main Distribution Bus 1, Main Distribution Bus 2, and the Essential Distribution Bus. The three distribution buses power the associated buses on the circuit breaker panel. Master Control Unit The Master Control Unit (MCU) is located on the left firewall.
Cirrus Design SR20 Section 7 Airplane and Systems Description Main Distribution Bus 2 The output from ALT 2 is connected to the Main Distribution Bus 2 in the MCU through an 80-amp fuse. Main Distribution Bus 2 powers three circuit breaker buses through 30-amp fuses located in the MCU; • NON ESS BUS, • MAIN BUS 1, • MAIN BUS 2.
Section 7 Airplane and Systems Description Cirrus Design SR20 Main Distribution Bus 1 or Main Distribution Bus 2 in the MCU. In the case of both alternators failing, BAT 1 is connected directly to the Essential Distribution Bus in the MCU and will power ESS BUS 1 and ESS BUS 2. In the event of both alternators and BAT 1 failing, BAT 2 is connected directly to ESS BUS 1.
Cirrus Design SR20 Section 7 Airplane and Systems Description Electrical System Control The rocker type electrical system MASTER switches are ‘on’ in the up position and ‘off’ in the down position. The switches, labeled BAT 2, BAT 1, ALT 1, ALT 2 are located in the bolster switch panel immediately below the instrument panel. These switches, along with the AVIONICS master switch, control all electrical power to the airplane. Battery Switches The BAT 1 and BAT 2 switches control the respective battery.
Section 7 Airplane and Systems Description Cirrus Design SR20 AVIONICS Master Switch A rocker switch, labeled AVIONICS, controls electrical power from the circuit breaker panel (MAIN BUS 1) to the Avionics Bus. The switch is located next to the ALT and BAT Master switches. Typically, the switch is used to energize or de-energize all non-essential avionics on the AVIONICS bus simultaneously.
Cirrus Design SR20 Section 7 Airplane and Systems Description Electrical Indicating Electrical system information is displayed as bar graphs and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), Battery 1 ampere output and Essential Bus voltage output are displayed along the LH edge of the display.
Section 7 Airplane and Systems Description Cirrus Design SR20 Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) 1 2 Electrical System Indication 3 4 5 6 7 8 9 10 12 11 Electrical and Lighting Controls LEGEND 1. Essential & Main Bus Voltage 2. Alternator & Battery Current 3. Battery 2 4. Battery 1 5. Alternator 1 6. Alternator 2 7. Avionics 8. Navigation 9. Strobe 10. Landing Light 11. Instrument Dimmer 12.
Cirrus Design SR20 Section 7 Airplane and Systems Description Lighting Systems Exterior Lighting The airplane is equipped with wing tip navigation lights with integral anti-collision strobe lights and recognition Lights. The landing light is located in the lower cowl. Navigation Lights The airplane is equipped with standard wing tip navigation lights. The lights are controlled through the NAV light switch on the instrument panel bolster.
Section 7 Airplane and Systems Description Cirrus Design SR20 Interior Lighting Interior lighting for the airplane consists of separately controlled incandescent overhead lights for general cabin lighting, individual lights for the pilots and passengers, and dimmable panel floodlights. The flight instrumentation and avionics equipment lights are dimmable.
Cirrus Design SR20 Section 7 Airplane and Systems Description Environmental System Standard cabin heating and ventilation is accomplished by supplying conditioned air from the heat exchanger for heating and windshield defrost and fresh outside air for ventilation.
Section 7 Airplane and Systems Description Cirrus Design SR20 RAM AIR RAM AIR HOT AIR VALVE HEAT EXCHANGER MIXING CHAMBER FRESH AIR VALVE AIR FLOW VALVE CONTROL PANEL SERVO MOTOR FLOOR AIRFLOW WINDSHIELD DIFFUSER PANEL AIRFLOW DISTRIBUTION MANIFOLD AIR GASPER FAN ASSEMBLY FOOT-WARMER DIFFUSER NOTE: Illustration depicts maximum cabin cooling airflows and selector settings with optional Fan installation.
Cirrus Design SR20 Section 7 Airplane and Systems Description Distribution From the mixing chamber, the air is distributed by either ram air or by optional blower fan to the distribution manifold mounted to the center, aft side of the firewall. The distribution manifold uses butterfly valves to control airflow to the floor and defrost vents. Airflow is ducted directly to all panel air vents.
Section 7 Airplane and Systems Description Cirrus Design SR20 Pressing the Panel-Foot selector button opens the cabin floor butterfly valve allowing airflow to the rear seat foot warmer diffusers and the front seat outlets mounted to the underside of each kickplate. Selecting Panel-Foot-Windshield button opens the windshield diffuser butterfly valve which permits shared airflow to the defrosting mechanism and cabin floor outlets.
Cirrus Design SR20 Section 7 Airplane and Systems Description Stall Warning System The airplane is equipped with an electro-pneumatic stall warning system to provide audible warning of an approach to aerodynamic stall. The system consists of an inlet in the leading edge of the right wing, a pressure switch and associated plumbing. As the airplane approaches a stall, the low pressure on the upper surface of the wings moves forward around the leading edge of the wings.
Section 7 Airplane and Systems Description Cirrus Design SR20 Pitot-Static System The Pitot-Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage. The Pitot heat is pilot controlled through a panel-mounted switch. An internally mounted alternate static pressure source provides backup static pressure should that the primary static source becomes blocked.
Cirrus Design SR20 Section 7 Airplane and Systems Description AIR DATA COMPUTER PFD Air Data AIRSPEED INDICATOR ALTIMETER ALTERNATE STATIC AIR SOURCE PITOT-STATIC WATER TRAPS PITOT MAST STATIC BUTTONS HEATER Annunciation PITOT HEAT CURRENT SENSOR 7.
Section 7 Airplane and Systems Description Cirrus Design SR20 Avionics Perspective Integrated Avionics System The Perspective Integrated Avionics System provides advanced cockpit functionality and improved situational awareness through the use of fully integrated flight, engine, communication, navigation and monitoring equipment.
Cirrus Design SR20 Section 7 Airplane and Systems Description PFD MFD XM RADIO RECEIVER (optional) SATELLITE DATA LINK RECEIVER (optional) FMS KEYBOARD MAG 2 MAG 1 AHRS 1 AUTOPILOT MODE CONTROLLER (optional) AHRS 2 (optional) AIR DATA COMPUTER INTEGRATED AVIONICS UNIT 1 AUDIO PANEL PITCH SERVO TRANSPONDER INTEGRATED AVIONICS UNIT 2 ENGINE AIRFRAME UNIT ROLL SERVO (optional) PITCH TRIM ADAPTER (optional) SR20_FM07_2914 Figure 7-14 Perspective Integrated Avionics System Schematic P/N 11934-0
Section 7 Airplane and Systems Description Cirrus Design SR20 GDU Primary Flight Display The Primary Flight Display, located directly in front of the pilot, is intended to be the primary display of flight parameter information (attitude, airspeed, heading, and altitude) during normal operations. The PFD accepts data from a variety of sources, including the MFD and the Integrated Avionics Units through a high-speed data bus connection.
Cirrus Design SR20 Section 7 Airplane and Systems Description MAIN BUS 3 and the 5-amp MFD PWR 2 circuit breaker on MAIN BUS 1. Either circuit is capable of powering the MFD. System start-up is automatic once power is applied. Power-on default brightness is determined by ambient lighting and is user adjustable.
Section 7 Airplane and Systems Description 1 2 3 4 5 6 13 14 15 16 Cirrus Design SR20 7 8 9 17 Legend 1. Soft Keys 2. PFD 3. PFD Range/Pan Joystick 4. Barometric Pressure 5. COM Transceiver Selection & Tune 6. COM Frequency Transfer (& 121.5 Emer Tune) 7. COM Volume and Squelch 8. Display Backup Selection 9. NAV and ID Audio Volume 10. NAV Frequency Transfer 10 11 18 12 1 19 20 21 11. NAV Transceiver Selection & Tune 12. MFD 13. PFD Direct-to-Course 14. PFD Flight Plan Page 15.
Cirrus Design SR20 Section 7 Airplane and Systems Description 22 23 24 25 26 27 28 29 GARMIN HDG D MENU FPL PROC 30 31 IDENT FMS/XPDR COM/NAV FMS XPDR COM NAV RANGE - 40 PUSH SYNC CLR A PUSH ENT PUSH CRSR/1-2 B G C H D I L M 38 S R PUSH SYNC W N E J X O T Y 35 33 34 F 1 2 3 4 5 6 7 8 9 0 +/- K P U Z PAN EMERG PUSH CTR ALT SEL 32 DFLT MAP CRS 39 + 35 Q V SPC BKSP 37 36 Flight Management System Keyboard Legend 22.
Section 7 Airplane and Systems Description Cirrus Design SR20 GIA 63W Integrated Avionics Units The Integrated Avionics Units, located behind the MFD and instrument panel, function as the main communication hub, linking all Integrated Avionics System components with the PFD. Each Integrated Avionics Unit contains a GPS WAAS receiver, VHF COM/NAV/GS receivers, system integration microprocessors, and flight director if the optional AFCS is installed.
Cirrus Design SR20 Section 7 Airplane and Systems Description GMA 347 Audio Panel with Integrated Marker Beacon Receiver The Audio Panel, installed on the center console below the Flight Management System Keyboard, integrates NAV/COM digital audio, intercom and marker beacon controls. The VHF communications portion of the unit interfaces with both Integrated Avionics Units to provide external radio communication, receive and demodulate VOR, Localizer, and Glide Slope signals.
Section 7 Airplane and Systems Description Cirrus Design SR20 Optional Avionics GFC 700 3-Axis Autopilot and GMC 705 Autopilot Controller Refer to Section 9, Supplements for GFC 700 3-Axis Autopilot operating information. GTX 33 Mode S Transponder The GTX 33 Mode S solid-state transponder communicates with the primary Integrated Avionics Unit and provides Modes A, C, and S interrogation/reply capabilities.
Cirrus Design SR20 Section 7 Airplane and Systems Description information is displayed on the MFD and indicates the relative range, bearing, and altitude of intruder aircraft. The Traffic Advisory System consists of a Transmitter Receiver Computer installed under the copilot’s seat just forward of the spar tunnel and a directional antenna installed on the airplane exterior.
Section 7 Airplane and Systems Description Cirrus Design SR20 information. 28 VDC for ADF System operation is supplied through the 3-amp DME/ADF circuit breaker on AVIONICS BUS. Refer to the Perspective Integrated Avionics System Pilot’s Guide for a general description of the system and its operating modes. Refer to the Bendix/King ADF System Pilot’s Guide for a detailed discussion of the system.
Cirrus Design SR20 Section 7 Airplane and Systems Description • Flight path marker, • Terrain warning system, • Field of view depiction on the MFD Navigation Page. Refer to the Perspective Integrated Avionics System Pilot’s Guide for a complete description of the system, its operating modes, and additional detailed operating procedures Max Viz Enhanced Vision System The Enhanced Vision System is an electro-optical system that uses a Long-Wave Infrared (IR) camera.
Section 7 Airplane and Systems Description 3 2 1 Cirrus Design SR20 4 5 6 4 7 4 29 8 28 27 9 26 12 10 11 13 14 15 16 23 17 25 24 18 23 22 19 20 21 LEGEND 1. AHRS 1 2. Integrated Avionics Unit 1 3. AHRS 2 4. Avionics Cooling Fan 5. Integrated Avionics Unit 2 6. Engine Airframe Unit 7. Air Data Computer 8. GFC 705 Mode Controller (opt) 9. ADF (Opt) 10. CAPS Activation Handle (Cabin Ceiling) 11. Hour Meters 12. Egress Hammer 13. Telephone and Audio Jacks 14. Cabin Speaker 15.
Cirrus Design SR20 Section 7 Airplane and Systems Description Avionics Support Equipment Antennas Two rod-type COM antennas are mounted to the aircraft’s exterior; COM 1 is mounted directly above the passenger compartment, COM 2 is mounted directly below the baggage compartment. These antennas are connected to the two VHF communication transceivers contained in the Integrated Avionics Units. The optional blade-type DME antenna is mounted on the aircraft underside just aft, right of the firewall.
Section 7 Airplane and Systems Description Cirrus Design SR20 Headset and Microphone Installation The airplane is equipped with provisions for four noise-canceling headsets with integrated microphones. The forward microphone-headsets use remote Push-To-Talk (PTT) switches located on the top of the associated control yoke grip. The rear headsets do not have COM transmit capabilities and do not require PTT switches.
Cirrus Design SR20 Section 7 Airplane and Systems Description Cabin Features Emergency Locator Transmitter The airplane is equipped with a self-contained emergency locator transmitter (ELT). The transmitter and antenna are installed immediately behind the aft cabin bulkhead, slightly to the right of the airplane centerline. The main transmitter control switch, labeled ONOFF-ARMED, on the transmitter is in the armed position for normal operations.
Section 7 Airplane and Systems Description Cirrus Design SR20 b. Disconnect fixed antenna lead from front of unit. c. Disconnect lead from remote switch and indicator unit. d. Loosen attach straps and remove transmitter unit and portable antenna. e. Attach portable antenna to antenna jack on front of unit. f. Set main control switch to ON. g. Hold antenna upright as much as possible.
Cirrus Design SR20 Section 7 Airplane and Systems Description Hour Meters The airplane is equipped with two hour meters located inside the armrest storage compartment between the pilot and copilot seats. The #1 hour meter, labeled HOBBS begins recording when the BAT 1 switch is ON and either the ALT 1 or ALT 2 switch is ON. The #2 hour meter records flight time and is labeled FLIGHT. Recording begins when the airplane reaches a speed of approximately 35 KIAS and is controlled by the Engine Airframe Unit.
Section 7 Airplane and Systems Description Cirrus Design SR20 Cirrus Airplane Parachute System The aircraft is equipped with a Cirrus Airplane Parachute System (CAPS) designed to bring the aircraft and its occupants to the ground in the event of a life-threatening emergency. The system is intended to save the lives of the occupants but will most likely destroy the aircraft and may, in adverse circumstances, cause serious injury or death to the occupants.
Cirrus Design SR20 Section 7 Airplane and Systems Description rate at which the parachute inflates. As the slider moves down the suspension lines the canopy inflates. A three-point harness connects the airplane fuselage structure to the parachute. The aft harness strap is stowed in the parachute canister and attached to the structure at the aft baggage compartment bulkhead. The forward harness straps are routed from the canister to firewall attach points just under the surface of the fuselage skin.
Section 7 Airplane and Systems Description Cirrus Design SR20 Pulling the activation T-handle straight down generates the greatest force. A maintenance safety pin is provided to ensure that the activation handle is not pulled during maintenance.
Cirrus Design SR20 Section 7 Airplane and Systems Description Deployment Characteristics When the rocket launches, the parachute assembly is extracted outward due to rocket thrust and rearward due to relative wind. In approximately two seconds the parachute will begin to inflate. When air begins to fill the canopy, forward motion of the airplane will dramatically be slowed. This deceleration increases with airspeed but in all cases within the parachute envelope should be less than 3 g’s.
Section 7 Airplane and Systems Description Cirrus Design SR20 Intentionally Left Blank 7-86 P/N 11934-004 Original Issue
Cirrus Design SR20 Section 8 Handling, Servicing, & Maintenance Section 8 Handling, Servicing, & Maintenance Table of Contents Introduction ........................................................................................ 3 Operator’s Publications ...................................................................... 3 Service Publications ....................................................................... 3 Ordering Publications .................................................................
Section 8 Handling, Servicing, & Maintenance Cirrus Design SR20 Intentionally Left Blank 8-2 P/N 11934-004 Original Issue
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance Introduction This section provides general guidelines for handling, servicing and maintaining your aircraft. In order to ensure continued safe and efficient operation of your airplane, keep in contact with your Authorized Cirrus Service Center to obtain the latest information pertaining to your aircraft. Operator’s Publications The FAA Approved Airplane Flight Manual and Pilot’s Operating Handbook (POH) is provided at delivery.
Section 8 Handling, Servicing, and Maintenance Cirrus Design SR20 • Service Advisory Notices – are used to notify you of optional Service Bulletins, supplier Service Bulletins or Service Letters affecting your airplane, and maintenance data or corrections not requiring a Service Bulletin. Give careful attention to the Service Advisory Notice information.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance Airplane Records and Certificates The Federal Aviation Administration (FAA) requires that certain data, certificates, and licenses be displayed or carried aboard the airplane at all times. Additionally, other documents must be made available upon request. The mnemonic acronym “ARROW” is often used to help remember the required documents.
Section 8 Handling, Servicing, and Maintenance Cirrus Design 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 verify receipt of the latest issued AD for their airplane.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance only be performed by a licensed Airframe and 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 Aircraft Maintenance Manual.
Section 8 Handling, Servicing, and Maintenance Cirrus Design 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. The regulation also stipulates that the pilot must also complete the appropriate logbook entries.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance • Replace any hose connection, except hydraulic connections, with replacement hoses. • Clean or replace fuel and oil strainers, as well as replace or clean filter elements. • Replace prefabricated fuel lines. • Replace the battery and check fluid level and specific gravity. Logbook Entry After any of the above work is accomplished, appropriate logbook entries must be made.
Section 8 Handling, Servicing, and Maintenance Cirrus Design 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. • WARNING • If external power will be used to start engine, keep yourself, others, and power unit cables well clear of the propeller rotation plane.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed in the rear baggage compartment or by power equipment that will not damage or excessively strain the nose gear assembly. The steering bar is engaged by inserting it into lugs just forward of the nose wheel axle. • Caution • While pushing the aircraft backward, the tow bar must be installed to keep the nose wheel from turning abruptly.
Section 8 Handling, Servicing, and Maintenance Cirrus Design 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. • Caution • Verify that taxi and propeller wash areas are clear before beginning taxi.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance Parking The airplane should be parked to protect the airplane from weather and to prevent it from becoming a hazard to other aircraft. The parking brake may release or exert excessive pressure because of heat buildup after heavy braking or during wide temperature swings. Therefore, if the airplane is to be left unattended or is to be left overnight, chock and tie down the airplane. 1. For parking, head airplane into the wind if possible. 2.
Section 8 Handling, Servicing, and Maintenance Cirrus Design 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. Head the airplane into the wind if possible. 2. Retract the flaps. 3. Chock the wheels. 4.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance Raise Airplane • Caution • Do not jack the aircraft outside or in open hangar with winds in excess of 10 mph. The empty CG is forward of the wing jacking points. To prevent airplane from tipping forward during maintenance or jacking, use a weighted tailstand (300-lb minimum) attached to the tail tiedown. Jacks must be used in pairs. Do not attempt to jack only one side of aircraft. Keep the airplane as level as possible when jacking. 1.
Section 8 Handling, Servicing, and Maintenance Cirrus Design 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 fourply rating, type III tire and tube. Always keep tires inflated to the rated pressure to obtain optimum performance and maximum service. The landing gear struts do not require servicing.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance • Leaking brake fluid at the caliper. This can be observed by checking for evidence of fluid on the ground or deposited on the underside of the wheel fairing. Wipe the underside of the fairing with a clean, white cloth and inspect for red colored fluid residue. • Overheated components, indicated by discoloration or warping of the disk rotor.
Section 8 Handling, Servicing, and Maintenance Cirrus Design SR20 Tire Inflation For maximum service from the tires, keep them inflated to the proper pressure. When checking tire pressure, examine the tires for wear, cuts, nicks, bruises and excessive wear. To inflate tires: 1. Remove inspection buttons on wheel pants to gain access to valve stems. It may be necessary to move airplane to get valve stem aligned with the access hole. 2.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance sooner under unfavorable operating conditions.
Section 8 Handling, Servicing, and Maintenance Cirrus Design SR20 Product Supplier Aeroshell (R) W Shell Australia Aeroshell Oil W Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50 Shell Canada Ltd. Aeroshell Oil W Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50 Shell Oil Company Aviation Oil Type A Phillips 66 Company BP Aero Oil BP Oil Corporation Castrolaero AD Oil Castrol Ltd. (Australia) Chevron Aero Oil Chevron U.S.A. Inc.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance Fuel System Servicing Fuel Filtration Screen/Element After the first 25 hours of operation, then every 100-hours or as conditions dictate, the fuel filter element in the gascolator must be replaced. At every oil change, Verify red pop-up tab on gascolator is not visible. If tab is visible, the fuel filter element must be replaced and the pop-up tab manually reset. Refer to the AMM for Fuel Screen/Element servicing information.
Section 8 Handling, Servicing, and Maintenance Cirrus Design SR20 • Note • Do not permit fuel nozzle to come in contact with bottom of fuel tanks. Keep fuel tanks at least half full at all times to minimize condensation and moisture accumulation in tanks. In extremely humid areas, the fuel supply should be checked frequently and drained of condensation to prevent possible distribution problems. 4. Remove fuel filler cap and fuel airplane to desired level.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance The gascolator incorporates a filter bypass that activates a red, pop-up tab when pressure drop across the gascolator reaches 0.8 ± 0.2 PSI. The filter is bypassed when the pressure drop reaches 1.20 ± 0.2 PSI. Once the pop-up tab is activated, the fuel filter element must be replaced and the pop-up tab manually reset. Do not attempt to clean the filter element.
Section 8 Handling, Servicing, and Maintenance Cirrus Design SR20 Battery Service The aircraft is delivered with a maintenance free, rechargeable, sealed, lead acid primary battery. Battery #1 is mounted to the forward right side of the firewall and access is gained by removing the upper cowl.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance Cleaning and Care Cleaning Exterior Surfaces • Note • Prior to cleaning, place the airplane in a shaded area to allow the surfaces to cool. The airplane should be washed with a mild soap and water. Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause corrosion of metal. Cover static ports and other areas where cleaning solution could cause damage.
Section 8 Handling, Servicing, and Maintenance Cirrus Design SR20 Cleaning Product Cleaning Application Supplier Pure Carnauba Wax Fuselage Exterior Any Source Mothers California Gold Pure Carnauba Wax Fuselage Exterior Wal-Mart Stores RejeX Fuselage Exterior Corrosion Technologies WX/Block System Fuselage Exterior Wings and Wheels AeroShell Flight Jacket Plexicoat Fuselage Exterior ShellStore Online XL-100 Heavy-Duty Cleaner/Degreaser Fuselage Exterior and Landing Gear Buckeye Interna
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance Windscreen and Windows Before cleaning an acrylic window, rinse away all dirt particles before applying cloth or chamois. Never rub dry acrylic. Dull or scratched window coverings may be polished using a special acrylic polishing paste. • Caution • Clean acrylic windows with a solvent free, none abrasive, antistatic acrylic cleaner.
Section 8 Handling, Servicing, and Maintenance Cirrus Design SR20 Do not use abrasive cleansers or cleaning pads on the germanium window. Abrasive cleaning can damage the sensor window coating. Do not use any cleansers containing ammonia. Ammonia will remove the sensor window coating. 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. 2.
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance 3. Allow the solvent to remain on the gear from five to ten minutes. Then rinse the gear with additional solvent and allow to dry. 4. Remove the cover from the wheel and remove the catch pan. 5. Lubricate the gear in accordance with the Lubrication Chart. Cleaning Interior Surfaces Seats, carpet, upholstery panels, and headliners should be vacuumed at regular intervals to remove surface dirt and dust.
Section 8 Handling, Servicing, and Maintenance Cirrus Design SR20 Cleaning Product Cleaning Application Supplier Prist Interior Windscreen and Windows Prist Aerospace Optimax Display Screens PhotoDon Mild Dishwasher Soap (abrasive free) Cabin Interior Any Source Leather Care Kit 50689-001 Leather Upholstery Cirrus Design Leather Cleaner 50684-001 Leather Upholstery Cirrus Design Ink Remover 50685-001 Leather Upholstery Cirrus Design Leather Conditioner 50686-001 Leather Upholstery C
Cirrus Design SR20 Section 8 Handling, Servicing, and Maintenance Instrument Panel and Electronic Display Screens The instrument panel, control knobs, and plastic trim need only to be wiped clean with a soft damp cloth.
Section 8 Handling, Servicing, and Maintenance Cirrus Design SR20 Leather Upholstery and Seats For routine maintenance, occasionally wipe leather upholstery with a soft, damp cloth. For deeper cleaning, start with mix of mild detergent and water then, if necessary, work your way up to the products available from Cirrus for more stubborn marks and stains. Do not use soaps as they contain alkaline which will alter the leather’s pH balance and cause the leather to age prematurely.
Cirrus Design SR20 Section 9 Supplements Section 9 Supplements This section of the handbook contains FAA Approved Supplements necessary to safely and to efficiently operate the aircraft when equipped with optional systems or equipment not provided with the standard airplane or for special operations or not included in the handbook. Basically, supplements are mini-handbooks and will contain data corresponding to most sections of the handbook.
Section 9 Supplements Cirrus Design SR20 Intentionally Left Blank 9-2 P/N 11934-004 Original Issue
Cirrus Design SR20 Section 9 Log of Supplements Section 9 Log of Supplements Part Number ___ 11934-S17 Title Date SR20 Airplanes Registered in Canada 10-10-01 ___ 11934-S25 R1 Winterization Kit 12-07-04 ___ 11934-S29 05-27-04 SR20 Airplanes Registered in the European Union ___ 11934-S36 R1 Artex ME406 406 MHz ELT System 12-18-08 ___ 11934-S39 S-Tec Fifty Five X Autopilot w/ Optional Flight Director 12-18-08 ___ 11934-S40 S-Tec Fifty Five SR Autopilot 12-18-08 ___ 11934-S41 R1 Garmin GFC
Section 9 Log of Supplements Cirrus Design SR20 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. This Log of Supplements shows all Cirrus Design Supplements available for the aircraft at the corresponding date of the revision level shown in the lower left corner. A mark (x) in the Part Number column indicates that the supplement is installed in the POH.
Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for Artex ME406 406 MHz ELT System When Artex ME406 406 MHz ELT System is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Section 9 Supplements Cirrus Design SR20 Section 1 - General The 406 MHz emergency locator transmitter (ELT) is a radio-frequency transmitter that generates a signal to assist in search and rescue for missing aircraft. The ELT automatically transmits the standard sweep tone on 121.5 MHz if rapid deceleration is detected. In addition, for the first 24 hours of operation, a 406 MHz signal containing aircraft specific information is transmitted at 50 seconds for 440 milliseconds.
Cirrus Design SR20 Section 9 Supplements Section 2 - Limitations No Change. Section 3 - Emergency Procedures Forced Landing Before performing a forced landing activate the ELT transmitter manually by turning the ELT remote switch to the 'ON'-position. Immediately after a forced landing, perform the following procedure: • Note • The ELT Remote Switch and Control Panel Indicator could be inoperative in the event of a forced landing. If inoperative, the inertia “G” switch will activate automatically.
Section 9 Supplements Cirrus Design SR20 Portable Use of ELT The ELT transmitter can be removed from the airplane and used as a personal locating device if it is necessary to leave the airplane after an accident. Access the unit as described below and set the ELT transmitter control switch to the 'ON'-position. 1. Remove avionics bay access panel along the aft portion of the RH fuselage or the lower aft center access panel of baggage compartment. 2. Disconnect fixed antenna lead from front of unit. 3.
Cirrus Design SR20 Section 9 Supplements Section 7 - Systems Description This airplane is equipped with a self-contained Artex ME406 406 MHz ELT System. The transmitter unit is automatically activated upon sensing a change of velocity along its longitudinal axis exceeding 4 to 5 feet per second. Once activated, the transmitter transmits VHF band audio sweeps at 121.5 Mhz until battery power is gone. In addition, for the first 24 hours of operation, a 406 MHz signal is transmitted at 50second intervals.
Section 9 Supplements Cirrus Design SR20 Section 8 - Handling, Servicing & Maintenance ELT and RCPI batteries must be inspected in accordance with the Airplane Maintenances Manual, 5-20 - Scheduled Maintenance Checks. The ELT and RCPI batteries must be replaced upon reaching the date stamped on the batteries, after an inadvertent activation of unknown duration, or whenever the batteries have been in use for one cumulative hour.
Cirrus Design SR20 Section 9 Supplements system or provide the same level of confidence as does an AM radio. 1. Tune aircraft receiver to 121.5 MHz. 2. Turn the ELT aircraft panel switch "ON" for about 1 second, then back to the "ARM" position. The receiver should transmit about 3 audio sweeps. 3. At turn-off (back to 'ARM' state) the panel LED and buzzer should present 1 pulse. If more are displayed, determine the problem from the list below. 4.
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Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for Garmin GFC 700 Automatic Flight Control System When the GFC 700 Automatic Flight Control System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the basic Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Section 9 Supplements Cirrus Design SR20 Section 1 - General The aircraft is equipped with a Garmin GFC 700 digital Automatic Flight Control System (AFCS) which is fully integrated within the Cirrus Perspective Integrated Avionics System architecture. Refer to Section 7 - System Description and the Cirrus Perspective Pilot’s Guide for additional description of the Automatic Flight Control System and operating procedures. Section 2 - Limitations 1.
Cirrus Design SR20 Section 9 Supplements 7. The autopilot and flight director will not command pitch or roll beyond the Command Limits. Axis Autopilot Command Limit FD Pitch Command Limits +20°, -15° FD Roll Command Limits ± 25° 8. Use of VNAV is not supported during an approach with a teardrop course reversal. VNAV will be disabled at the beginning of the teardrop.
Section 9 Supplements Cirrus Design SR20 Section 3A - Abnormal Procedures Autopilot Miscompare AP MISCOMP Caution AP MISCOMP Autopilot miscompare, autopilot is not available. 1. Continue flight without autopilot. Autopilot and PFD Using Different AHRSs AP/PFD AHRS Caution AP/PFD AHRS The autopilot and PFD are using different Attitude and Heading Reference Systems. 1. Continue flight without autopilot. Monitor Standby Instruments. Pilot may manually select other AHRS if installed.
Cirrus Design SR20 Section 9 Supplements Altitude Selection Deviation ALTITUDE SEL Advisory ALTITUDE SEL The pilot has programmed the autopilot to climb or descend away from the selected altitude. Typically done unintentionally. 1. Altitude Selection ................................
Section 9 Supplements Cirrus Design SR20 Before Taxiing 1. Manual Electric Trim...............................................................TEST Press the AP DISC button down and hold while commanding trim. Trim should not operate either nose up or nose down. 2. Autopilot ..............................................ENGAGE (press AP button) 3. Autopilot Override ..................................................................
Cirrus Design SR20 Section 9 Supplements Section 7 - System Description This airplane is equipped with a GFC 700 - a two axis, fully digital, dual channel, fail passive Automatic Flight Control System (AFCS). The system consists of the GFC 705 AFCS Mode Controller, Flight Management System Keyboard, Roll Servo, Pitch Servo, Integrated Avionics Units, Pitch Trim Adapter, Autopilot Disconnect Switch, Take Off / Go Around Button, Electric Pitch-Trim and Roll-Trim Hat Switch.
Section 9 Supplements Cirrus Design SR20 PFD MFD GFC 705 MODE CONTROLLER INTEGRATED AVIONICS UNIT 1 GO-AROUND SWITCH INTEGRATED AVIONICS UNIT 2 A/P DISC PITCH TRIM ADAPTER 4-WAY TRIM PITCH TRIM CARTRIDGE ROLL SERVO PITCH SERVO SR20_FM09_2918 Figure - 1 GFC 700 Automatic Flight Control System Schematic 8 of 16 P/N 11934-S41 Revision 01: 08-26-09
Cirrus Design SR20 Section 9 Supplements GFC 705 AFCS Mode Controller The GFC 705 AFCS Mode Controller, located in the upper section of the center console provides primary control of autopilot modes. A pitch wheel is included for adjustment of pitch mode reference. 28 VDC for GFC 705 AFCS Mode Controller operation is supplied through 5-amp KEYPADS / AP CTRL circuit breaker on MAIN BUS 1. All Autopilot mode selection is performed by using the mode select buttons and pitch wheel on the controller.
Section 9 Supplements Cirrus Design SR20 view, will deactivate the Flight Director and remove the command bars unless the autopilot is engaged. If the autopilot is engaged, the FD button is deactivated. UP/DN - Pitch Wheel The Pitch UP/DN Wheel on the controller is used to change the flight director pitch mode reference value. Each click of the wheel results in a step increase or decrease in the flight director pitch mode by the amount shown in the table below.
Cirrus Design SR20 Section 9 Supplements Flight Management System Keyboard The Flight Management System Keyboard, found in the center console below the AFCS mode controller, is the primary means for data entry for the MFD and is used to control NAV/COM Radios, transponder, and flight management system entry. Heading, course and altitude select are also provided. 28 VDC for Flight Management System Keyboard operation is supplied through the 5-amp KEYPADS / AP CTRL circuit breaker on MAIN BUS 1.
Section 9 Supplements Cirrus Design SR20 GARMIN IDENT HDG FMS/XPDR COM/NAV MENU D RANGE XPDR FMS - 1 FPL PUSH SYNC PROC COM DFLT MAP CLR PUSH ENT PUSH CRSR/1-2 CRS A 2 B G C H D I L M 3 S R PUSH SYNC W N E J X O T Y F 1 2 3 4 5 6 7 8 9 0 +/- K P U Z PAN EMERG PUSH CTR ALT SEL + NAV Q V SPC BKSP Flight Management System Keyboard 4 5 7 8 HDG NAV AP LVL APR FD 11 12 13 IAS ALT VS VNV 14 15 DN UP 6 9 GFC 705 Mode Controller Legen
Cirrus Design SR20 Section 9 Supplements Roll and Pitch Servo The Roll Servo, located below the passenger seat, and the Pitch Servo, located below the baggage compartment, position the aircraft flight controls in response to commands generated by the Integrated Avionics Units autopilot calculations. 28 VDC for Roll and Pitch Servo operation is supplied through the 5amp AP SERVOS circuit breaker on MAIN BUS 1.
Section 9 Supplements Cirrus Design SR20 Autopilot Disconnect Switch The yoke mounted Autopilot Disconnect Switch disengages the autopilot and may also be used to mute the aural alert associated with an AP disconnect. Take Off / Go Around Button The remote TO/GA switch, located on the left side of the power lever, disengages the autopilot and selects the Takeoff or Go Around mode on the Flight Director.
Cirrus Design SR20 Section 9 Supplements Annunciation System • Note • Refer to the Cirrus Perspective Pilot’s Guide for a detailed description of the annunciator system and all warnings, cautions and advisories. Crew Alerting System AFCS alerts are displayed in the Crew Alerting System (CAS) window located to the right of the altimeter and VSI. AFCS annunciations are grouped by criticality and sorted by order of appearance with the most recent message on top.
Section 9 Supplements Cirrus Design SR20 Section 8 – Handling, Service, & Maintenance No Change. Section 10 – Safety Information No Change.
Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the Garmin Terrain Awareness/Warning System When the Garmin Terrain Awareness/Warning System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Section 9 Supplements Cirrus Design SR20 Section 1 - General The airplane is equipped with the Garmin Terrain Awareness/Warning System that performs the functions of a Class C Terrain Awareness and Warning System (TAWS) in accordance with TSO C151b. Refer to the Cirrus Perspective Integrated Flight Deck Pilot’s Guide for a additional information on the system and its operating modes. Section 2 - Limitations 1.
Cirrus Design SR20 Section 9 Supplements Section 3 - Emergency Procedures To prevent unwanted aural alerting during ditching or other off-airport landings, inhibit the Terrain Awareness System functions by selecting the INHIBIT Softkey on the TAWS Page. Response To TAWS Warnings Red PULL UP Warning PULL UP Aural “PULL UP” Warning Aural “TERRAIN AHEAD” Warning Aural “OBSTACLE AHEAD” Warning 1. Level the wings, simultaneously adding full power. 2. Increase pitch attitude to 15 degrees nose up. 3.
Section 9 Supplements Cirrus Design SR20 Section 4 - Normal Procedures Normal operating procedures are outlined in the Cirrus Perspective Integrated Flight Deck Pilot’s Guide. Alert Priority When any of the TAWS aural alerts are in progress, all aural TRAFFIC alerts are inhibited. Advisory Callout The advisory callout “FIVE HUNDRED”, occurs at approximately 500 feet AGL. Section 5 - Performance No Change. Section 6 - Weight & Balance No Change.
Cirrus Design SR20 Section 9 Supplements System Constraints System test at startup: Aural tone lasting approximately one second indicates successful completion of internal system test. Red TAWS FAIL Warning TAWS FAIL Aural “TAWS SYSTEM FAILURE” Warning 1. TAWS power-up self-test has failed or TAWS has detected problems with database validity, hardware status, and/or GPS status.
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Cirrus Design SR20 Section 10 Safety Information Section 10 Safety Information Table of Contents Introduction ........................................................................................ 3 Cirrus Airframe Parachute System (CAPS) ....................................... 4 Deployment Scenarios.................................................................... 4 General Deployment Information .................................................... 6 Landing Considerations ...........................
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Cirrus Design SR20 Section 10 Safety Information Introduction This aircraft is designed to operate safely and efficiently in a flight environment. However, like any other aircraft, pilots must maintain proficiency to achieve maximum safety, utility, and economy. As the pilot you must be thoroughly familiar with the contents of this Handbook, the Handbook Supplements, Flight Checklist, and operational guides and data provided by manufacturers of equipment installed in this airplane.
Section 10 Safety Information Cirrus Design SR20 Cirrus Airframe Parachute System (CAPS) The Cirrus Airframe Parachute System (CAPS) is designed to lower the aircraft and its passengers to the ground in the event of a lifethreatening emergency.
Cirrus Design SR20 Section 10 Safety Information Loss of Control Loss of control may result from many situations, such as: a control system failure (disconnected or jammed controls); severe wake turbulence, severe turbulence causing upset, severe airframe icing, or sustained pilot disorientation caused by vertigo or panic; or a spiral/ spin. If loss of control occurs, determine if the airplane can be recovered. If control cannot be regained, the CAPS should be activated.
Section 10 Safety Information Cirrus Design SR20 General Deployment Information Deployment Speed The maximum speed at which deployment has been demonstrated is 133 KIAS. Deployment at higher speeds could subject the parachute and aircraft to excessive loads that could result in structural failure. Once a decision has been made to deploy the CAPS, make all reasonable efforts to slow to the minimum possible airspeed.
Cirrus Design SR20 Section 10 Safety Information Landing Considerations After a CAPS deployment, the airplane will descend at less than 1700 feet per minute with a lateral speed equal to the velocity of the surface wind. The CAPS landing touchdown is equivalent to ground impact from a height of approximately 13 feet. While the airframe, seats, and landing gear are designed to accommodate the stress, occupants must be prepared for the landing.
Section 10 Safety Information Cirrus Design SR20 • If a door is open prior to touchdown in a CAPS landing, the door will most likely break away from the airplane at impact. • If the door is open and the airplane contacts the ground in a rolled condition, an occupant could be thrown forward and strike their head on the exposed door pillar. Contacting the ground in a rolled condition could be caused by terrain that is not level, contacting an obstacle such as a tree, or by transient aircraft attitude.
Cirrus Design SR20 Section 10 Safety Information Post Impact Fire If there is no fire prior to touchdown and the pilot is able to shut down the engine, fuel, and electrical systems, there is less chance of a post impact fire. If the pilot suspects a fire could result from impact, unlatching a door immediately prior to assuming the emergency landing body position should be considered to assure rapid egress.
Section 10 Safety Information Cirrus Design 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. The most common cause of brake damage and/or failure is the creation of excessive heat through improper braking practices.
Cirrus Design SR20 Section 10 Safety Information • Use only as much power (throttle) as is necessary to achieve forward movement. Keep in mind, any additional power added with the throttle will be absorbed in the brakes to maintain constant speed. • Use rudder deflection and the minimum necessary inputs of differential braking to achieve directional control. • Do not “ride the brakes”. Pilots should consciously remove pressure from the brakes while taxiing.
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