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AIRPLANE INFORMATION MANUAL

for the

CIRRUS DESIGN SR20

All-Electric SR20

Aircraft Serials 1268 and Subsequent

• NOTE •

At the time of issuance, this Information Manual was

harmonized with the SR20 Pilot's Operating Handbook Rev

A9 (P/N 11934-003), and will not be kept current. Therefore,

this Information Manual is for reference only and cannot be

used as a substitute for the official Pilot's Operating Handbook

and FAA Approved Airplane Flight Manual.

Information Manual

P/N 13999-003 March 2010

Summary of content (474 pages)

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AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR20 All-Electric SR20 Aircraft Serials 1268 and Subsequent • NOTE • At the time of issuance, this Information Manual was harmonized with the SR20 Pilot's Operating Handbook Rev A9 (P/N 11934-003), and will not be kept current. Therefore, this Information Manual is for reference only and cannot be used as a substitute for the official Pilot's Operating Handbook and FAA Approved Airplane Flight Manual.
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Cirrus Design SR20 Section 1 General Section 1 General Table of Contents Introduction ..................................................................................... 1-3 The Airplane.................................................................................... 1-6 Engine.......................................................................................... 1-6 Propeller ...................................................................................... 1-6 Fuel...........................
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Section 1 General Cirrus Design SR20 Intentionally Left Blank 1-2 Information Manual March 2010
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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.
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Section 1 General Cirrus Design SR20 26.0' 9.2' 7" NOTE: • Wing s pan includes position and strobe lights. • Prop ground clearance at 3000 lb - 7" (2 blade), 8" (3 blade). • Wing Area = 135.2 sq. ft. 35.5' 76" 2-BLADE 74" 3-BLADE 11.
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Cirrus Design SR20 Section 1 General GROUND TURNING CLEARANCE -RADIUS FOR WING TIP -RADIUS FOR NOSE GEAR 23' 11" 9' 11" 6" -RADIUS FOR INSIDE GEAR -RADIUS FOR OUTSIDE GEAR 12' 2" TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER. ACTUAL TURNING RADIUS MAY VARY AS MUCH AS THREE FEET.
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Section 1 General Cirrus Design SR20 The Airplane Engine Number of Engines.............................................................................. 1 Number of Cylinders............................................................................ 6 Engine Manufacturer ........................................... Teledyne Continental Engine Model........................................................................ IO-360-ES Fuel Metering................................................................
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Cirrus Design SR20 Section 1 General Fuel Total Capacity.............................................60.5 U.S. Gallons (229.0 L) Total Usable...................................................56 U.S. Gallons (212.0 L) Approved Fuel Grades: 100 LL Grade Aviation Fuel (Blue) 100 (Formerly 100/130) Grade Aviation Fuel (Green) Oil Oil Capacity (Sump) ............................................. 8 U.S. Quarts (7.6 L) Oil Grades: All Temperatures ............................................
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Section 1 General Cirrus Design SR20 Symbols, Abbreviations and Terminology General Airspeed Terminology and Symbols KCAS Knots Calibrated Airspeed is the indicated airspeed corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator. The IAS values published in this handbook assume no instrument error.
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Cirrus Design SR20 Section 1 General 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.
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Section 1 General Cirrus Design SR20 • 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.
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Cirrus Design SR20 Section 1 General 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 c.g. Center of Gravity is the point at which an airplane would balance if suspended.
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Section 1 General Cirrus Design SR20 • 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 ..................................................................................... 2-3 Certification Status .......................................................................... 2-3 Airspeed Limitations........................................................................ 2-4 Airspeed Indicator Markings ........................................................... 2-5 Power Plant Limitations .............
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Section 2 Limitations Cirrus Design SR20 Placards ........................................................................................
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Cirrus Design SR20 Section 2 Limitations Introduction • Note • Limitations associated with optional equipment are not described in this section. For optional equipment limitations, refer to Section 9, Supplements The limitations included in this Section of the Pilot’s Operating Handbook (POH) are approved by the Federal Aviation Administration.
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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 VNE 200 200 Never Exceed Speed is the speed limit that may not be exceeded at any time.
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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) Remarks White Arc 56 - 100 Full Flap Operating Range. Lower limit is the most adverse stall speed in the landing configuration.
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Section 2 Limitations Cirrus Design SR20 Power Plant Limitations Engine Teledyne Continental ............................................................ IO-360-ES Power Rating ........................................................ 200 hp @ 2700 rpm Maximum RPM .......................................................................2700 rpm Oil: Oil Temperature..................................... 240 F (115 C) maximum Oil Pressure: Minimum...............................................................
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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........................................................
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Section 2 Limitations Cirrus Design SR20 Instrument Markings Instrument (Range) Red Line Green Arc Yellow Arc Red Line Minimum Normal Caution Maximum Power Plant Instrumentation Tachometer/ Engine Speed (0 - 3500 RPM) –– 500 - 2700 –– 2700 Cylinder Head Temperature (200 F - 500 F) –– 240 - 420 F 420 - 460 F 460 F Exhaust Gas Temp. (1250 - 1650 F) –– –– –– –– Manifold Pressure (10 – 35 Inches Hg) –– 15 - 29.5 in. Hg 29.5 – 35 in. Hg –– Fuel Flow (0 – 18 U.S. Gal./ Hr.
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Cirrus Design SR20 Section 2 Limitations Center of Gravity Limits Reference Datum ....................................100 inches forward of firewall Forward ................................................................... Refer to Figure 2-4 Aft ............................................................................ Refer to Figure 2-4 23.1 % MAC FS 144.1 3000 lb 3000 31.3 % MAC FS 148.0 3000 lb Weight - Pounds 2800 31.5 % MAC FS 148.1 2900 lb 16.7 % MAC FS 141.0 2694 lb 2600 30.
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Section 2 Limitations Cirrus Design SR20 Maneuver Limits Aerobatic maneuvers, including spins, are prohibited. • Note • Because the SR20 has not been certified for spin recovery, the Cirrus Airframe Parachute System (CAPS) must be deployed if the airplane departs controlled flight. Refer to Section 3 – Emergency Procedures, Inadvertent Spiral/Spin Entry. This airplane is certified in the normal category and is not designed for aerobatic operations.
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Cirrus Design SR20 Section 2 Limitations Kinds of Operation The SR20 is equipped and approved for the following type operations: • VFR day and night. • IFR day and night. Serials 1337 and subsequent with SRV configuration: The airplane is equipped and approved for the following type operations: • VFR 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.
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Section 2 Limitations Cirrus Design SR20 System, Instrument, and/or Equipment VFR Day VFR Nt. IFR Day IFR Nt.
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Cirrus Design SR20 Section 2 Limitations System, Instrument, and/or Equipment Kinds of Operation VFR Day VFR Nt. IFR Day IFR Nt.
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Section 2 Limitations System, Instrument, and/or Equipment Cirrus Design SR20 Kinds of Operation Remarks, Notes, and/or Exceptions VFR Day VFR Nt. IFR Day IFR Nt. Nav Radio — — 1 1 Gyroscopic Directional Indication (HSI) — — 1 1 Serials 1005 & subs w/o PFD. Turn Coordinator — — 1 1 Serials 1005 & subs w/o PFD. PFD Attitude Indication — — 1 1 Serials 1337 & subs w/ PFD. PFD Airspeed Indication — — 1 1 Serials 1337 & subs w/ PFD.
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Cirrus Design SR20 System, Instrument, and/or Equipment Section 2 Limitations Kinds of Operation VFR Day VFR Nt. IFR Day IFR Nt.
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Section 2 Limitations Cirrus Design SR20 Instrument Procedures Due to the possibility of CDI needle oscillation, in aircraft configured with a 2 blade propeller, while conducting instrument procedures that use a localizer or Simplified Directional Facility (SDF) navaid, engine speed above 2600 rpm is prohibited. Taxi Power Maximum continuous engine speed for taxiing is 1000 RPM on flat, smooth, hard surfaces.
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Cirrus Design SR20 Section 2 Limitations Systems and Equipment Limits Cirrus Airframe Parachute System (CAPS) VPD Maximum Demonstrated Deployment Speed ................. 135 KIAS • Note • Refer to Section 10 – Safety Information, for additional CAPS guidance. Primary Flight Display 1. The PFD integrates with separately approved sensor installations. Adherence to limitations in appropriate installation POH supplements is mandatory. 2.
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Section 2 Limitations Cirrus Design SR20 8. Flaps must be set to 50% for autopilot operation in Altitude Hold at airspeeds below 95 KIAS. 9. Flap deflection is limited to 50% during autopilot operations. 10. The autopilot must be disconnected in moderate or severe turbulence. 11. Minimum engage height for the autopilot is 400 ft AGL. • WARNING • Autopilot may not be able to maintain all selectable vertical speeds.
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Cirrus Design SR20 Section 2 Limitations i. The flaps should be extended in the approach configuration prior to the Outer Marker. No further changes in the flap configuration should be made throughout the autopilotcoupled approach. j. The glideslope is approached in such a manner to allow automatic arming of the glideslope, or if the glideslope is manually armed no more than 15% above the glideslope. Multi-Function Display 1.
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Section 2 Limitations Cirrus Design SR20 8. Serials with Avidyne MFD installed: The Avidyne FlightMax EX5000C Pilot’s Guide, P/N 600-00108-000, Revision 03 or later, must be available to the pilot during all flight operations. Oxygen System Whenever the operating rules require the use of supplemental oxygen, the pilot must: • Use an oxygen system approved by Cirrus Design and listed in the Oxygen System AFM Supplement Part Number 11934S09.
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Cirrus Design SR20 Section 2 Limitations 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: AVGAS MIN GRADE 100LL OR 100 28 U.S. GALS. TOTAL USABLE CAP 13 U.S. GALS. USABLE TO TAB Serials 1005 thru 1099. AVGAS MIN GRADE 100LL OR 100 28 U.S. GALS. (106 LITERS) TOTAL USABLE CAP 13 U.S. GALS. (49 LITERS) USABLE TO TAB Serials 1100 thru 1326.
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Section 2 Limitations Cirrus Design SR20 Upper fuselage, either side of CAPS rocket cover: WARNING! ROCKET FOR PARACHUTE DEPLOYMENT INSIDE STAY CLEAR WHEN AIRPLANE IS OCCUPIED Left fuselage, on external power supply door: EXTERNAL Rudder, and elevator, both sides: NO PUSH POWER 28 V DC Doors, above and below latch: C L O SE CLOSE O P OPEN E N Serials 1317 thru 1422. Serials 1005 thru 1316. PUSH TO OPEN Serials 1423 & subs.
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Cirrus Design SR20 Section 2 Limitations Engine control panel: UP 50% 120 KIAS FLAPS 100% 100 KIAS CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT MAX FULL RICH P O W BOOST E M I X T U R FUEL PUMP PRIME LEFT 28 GALLONS USABLE OFF R IDLE F R I C T I O N E CUTOFF RIGHT 28 GALLONS USABLE OFF SR20_FM02_1602A Information Manual March 2010 Figure 2-5 Placards (Sheet 3 of 7) 2-23
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Section 2 Limitations Cirrus Design SR20 Wing, flap aft edge: NO STEP Cabin Door Window, lower edge, centered, applied upside down: RESCUE: FRACTURE AND REMOVE WINDOW Bolster Switch Panel, left edge: THIS AIRCRAFT IS CERTIFIED FOR THE FOLLOWING FLIGHT OPERATIONS: DAY - NIGHT - VFR - IFR (WITH REQUIRED EQUIPMENT) FLIGHT INTO KNOWN ICING IS PROHIBITED OPERATE PER AIRPLANE FLIGHT MANUAL Serials 1005 & subs w/o SRV option.
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Cirrus Design SR20 Section 2 Limitations Bolster Panel, both sides: GRAB HERE Serials 1351 & subs. Instrument Panel: NO SMOKING FASTEN SEATBELTS FIRE EXTINGUISHER UNDER PILOT SEAT FRONT Serials 1005 thru 1638. FASTEN SEAT BELT • NO SMOKING FIRE EXTINGUISHER FORWARD LEFT OF PILOT SEAT Serials 1639 & subs. Cabin Window, above door latch: EMERGENCY EXIT REMOVE EGRESS HAMMER FROM ARMREST LID STRIKE CORNER OF WINDOW, KICK OR PUSH OUT AFTER FRACTURING Serials 1005 thru 1178.
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Section 2 Limitations Cirrus Design SR20 Baggage Compartment, aft edge: ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Baggage Compartment Door, inside: DISTRIBUTED FLOOR LIMIT 130 LBS BAGGAGE STRAP CAPACITY IS 35 LBS EACH MAXIMUM SEE AIRPLANE FLIGHT MANUAL FOR BAGGAGE TIE-DOWN AND WEIGHT AND BALANCE INFORMATION 12378-001 REV A SR20_FM02_1224 2-26 Figure 2-5 Placards (Sheet 6 of 7) Information Manual March 2010
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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 135 KIAS CIRRUS AIRFRAME PARACHUTE SYSTEM ACTIVATION PROCEDURE 1. FUEL MIXTURE.......................................CUT-OFF 2. THIS COVER............................................REMOVE 3. ACTIVATION HANDLE.......
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Section 2 Limitations Cirrus Design SR20 Intentionally Left Blank 2-28 Information Manual March 2010
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Cirrus Design SR20 Section 3 Emergency Procedures Section 3 Emergency Procedures Table of Contents Introduction ..................................................................................... 3-3 Airspeeds for Emergency Operations ............................................. 3-4 Emergency Procedures Guidance .................................................. 3-5 Preflight Planning......................................................................... 3-5 Preflight Inspections/Maintenance ........
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Section 3 Emergency Procedures Cirrus Design SR20 PFD - Loss of Air Data ...............................................................3-26 PFD - Loss of Attitude Data .......................................................3-26 Power Lever Linkage Failure .....................................................
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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 SR20. Although emergencies caused by airplane, systems, or engine malfunctions are extremely rare, the guidelines described in this section should be considered and applied as necessary should an emergency arise. • Note • Emergency procedures associated with optional systems can be found in Section 9.
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Section 3 Emergency Procedures Cirrus Design SR20 Airspeeds for Emergency Operations Maneuvering Speed: 3000 lb .............................................................................131 KIAS 2600 lb .............................................................................122 KIAS 2200 lb .............................................................................111 KIAS Best Glide: 3000 lb ...............................................................................96 KIAS 2500 lb .........
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Cirrus Design SR20 Section 3 Emergency Procedures Emergency Procedures Guidance Although this section provides procedures for handling most emergencies and critical flight situations that could arise in the SR20, it is not a substitute for thorough knowledge of the airplane and general aviation techniques. A thorough study of the information in this handbook while on the ground will help you prepare for time-critical situations in the air.
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Section 3 Emergency Procedures Cirrus Design SR20 Take Appropriate Action — In most situations, the procedures listed in this section will either correct the aircraft problem or allow safe recovery of the aircraft. Follow them and use good pilot judgment. 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.
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Cirrus Design SR20 Section 3 Emergency Procedures Ground Emergencies Engine Fire During Start A fire during engine start may be caused by fuel igniting in the fuel induction system. If this occurs, attempt to draw the fire back into the engine by continuing to crank the engine. 1. Mixture ..............................................................................CUTOFF 2. Fuel Pump ............................................................................... OFF 3. Fuel Selector......................
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Section 3 Emergency Procedures Cirrus Design SR20 Emergency Ground Egress • WARNING • While exiting the airplane, make sure evacuation path is clear of other aircraft, spinning propellers, and other hazards. 1. Engine........................................................................SHUTDOWN • Note • If the engine is left running, set the Parking Brake prior to evacuating the airplane. 2. Seat belts ....................................................................... RELEASE 3. Airplane...........
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Cirrus Design SR20 Section 3 Emergency Procedures In-Flight Emergencies Engine Failure On Takeoff (Low Altitude) If the engine fails immediately after becoming airborne, abort on the runway if possible. If altitude precludes a runway stop but is not sufficient to restart the engine, lower the nose to maintain airspeed and establish a glide attitude. In most cases, the landing should be made straight ahead, turning only to avoid obstructions.
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Section 3 Emergency Procedures Cirrus Design SR20 Maximum Glide Conditions Example: Power Propeller Flaps Wind OFF Windmilling 0% (UP) Zero Altitude Airspeed 7,000 ft. AGL Best Glide Glide Distance 12.5 NM Best Glide Speed 3000 lb 96 KIAS 2500 lb 87 KIAS Maximum Glide Ratio ~ 10.
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Cirrus Design SR20 Section 3 Emergency Procedures Engine Failure In Flight If the engine fails at altitude, pitch as necessary to establish best glide speed. While gliding toward a suitable landing area, attempt to identify the cause of the failure and correct it. 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.
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Section 3 Emergency Procedures Cirrus Design SR20 Engine Airstart The following procedures address the most common causes for engine loss. Switching tanks and turning the fuel pump on will enhance starting if fuel contamination was the cause of the failure. 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 ................
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Cirrus Design SR20 Section 3 Emergency Procedures Engine Partial Power Loss Indications of a partial power loss include fluctuating RPM, reduced or fluctuating manifold pressure, low oil pressure, high oil temperature, and a rough-sounding or rough-running engine. Mild engine roughness in flight may be caused by one or more spark plugs becoming fouled. A sudden engine roughness or misfiring is usually evidence of a magneto malfunction.
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Section 3 Emergency Procedures Cirrus Design SR20 The following procedure provides guidance to isolate and correct some of the conditions contributing to a rough running engine or a partial power loss: 1. Fuel Pump.......................................................................... BOOST Selecting BOOST on may clear the problem if vapor in the injection lines is the problem or if the engine-driven fuel pump has partially failed.
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Cirrus Design SR20 Section 3 Emergency Procedures Low Oil Pressure If low oil pressure is accompanied by a rise in oil temperature, the engine has probably lost a significant amount of its oil and engine failure may be imminent. Immediately reduce engine power to idle and select a suitable forced landing field. • WARNING • Prolonged use of high power settings after loss of oil pressure will lead to engine mechanical damage and total engine failure, which could be catastrophic.
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Section 3 Emergency Procedures Cirrus Design SR20 Smoke and Fume Elimination If smoke and/or fumes are detected in the cabin, check the engine parameters for any sign of malfunction. If a fuel leak has occurred, actuation of electrical components may cause a fire. If there is a strong smell of fuel in the cockpit, divert to the nearest suitable landing field. Perform a Forced Landing pattern and shut down the fuel supply to the engine once a safe landing is assured. 1. Heater .............................
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Cirrus Design SR20 Section 3 Emergency Procedures Wing Fire In Flight 1. Pitot Heat Switch ..................................................................... OFF 2. Navigation Light Switch............................................................ OFF 3. Landing Light ........................................................................... OFF 4. Strobe Light Switch .................................................................. OFF 5.
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Section 3 Emergency Procedures Cirrus Design SR20 • WARNING • Halon gas used in the fire extinguisher can be toxic, especially in a closed area. After extinguishing fire, ventilate cabin by opening air vents and unlatching door (if required). If airflow is not sufficient to clear smoke or fumes from cabin: 5. Cabin Doors ...................................................... PARTIALLY OPEN Airspeed may need to be reduced to partially open door in flight. 6. When fire extinguished, Air Vents ..............
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Cirrus Design SR20 Section 3 Emergency Procedures 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.
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Section 3 Emergency Procedures Cirrus Design SR20 Spins The SR20 is not approved for spins, and has not been tested or certified for spin recovery characteristics. The only approved and demonstrated method of spin recovery is activation of the Cirrus Airframe Parachute System (See CAPS Deployment, this section). Because of this, if the aircraft “departs controlled flight”, the CAPS must be deployed.
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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.
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Section 3 Emergency Procedures Cirrus Design SR20 The maximum demonstrated deployment speed is 135 KIAS. Reducing airspeed allows minimum parachute loads and prevents structural overload and possible parachute failure. 2. Mixture (If time and altitude permit) ................................. CUTOFF Generally, a distressed airplane will be safer for its occupants if the engine is not running. 3. Activation Handle Cover..................................................
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Cirrus Design SR20 Section 3 Emergency Procedures All occupants must have seat belts and shoulder harness securely fastened. 12. Loose Items ..................................................................... SECURE If time permits, all loose items should be secured to prevent injury from flying objects in the cabin at touchdown. 13. Assume emergency landing body position.
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Section 3 Emergency Procedures Cirrus Design SR20 Landing Emergencies 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.
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Cirrus Design SR20 Section 3 Emergency Procedures 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.
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Section 3 Emergency Procedures Cirrus Design SR20 System Malfunctions Primary Flight Display System In the unlikely event of a PFD failure, the pilot may lose the ability to control the autopilot through the PFD controls. If this malfunction occurs, the PFD circuit breakers may be pulled and the airplane flown using the mechanical standby instruments.
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Cirrus Design SR20 Section 3 Emergency Procedures loss of attitude information until the PFD can be restarted on the ground. Aircraft equipped with Software Version 530-00159-000 Rev 00 or higher; When subjected to a power loss of less than 20 seconds, the PFD is capable of performing a warm start. In this event, a “PLEASE STANDBY” message will be displayed for 2 seconds followed by a “ATTEMPTING QUICK RESTART” message.
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Section 3 Emergency Procedures Cirrus Design SR20 Intentionally Left Blank 3-28 Information Manual March 2010
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Cirrus Design SR20 Section 3A Abnormal Procedures Section 3A Abnormal Procedures Table of Contents Introduction .................................................................................. 3A-3 Abnormal Procedures Guidance .................................................. 3A-4 Ground Procedures...................................................................... 3A-5 Brake Failure During Taxi ......................................................... 3A-5 Aborted Takeoff ...........................
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Section 3A Abnormal Procedures Cirrus Design SR20 Intentionally Left Blank 3A-2 Information Manual March 2010
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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.
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Section 3A Abnormal Procedures Cirrus Design SR20 Abnormal Procedures Guidance Although this section provides procedures for handling most abnormal system and/or flight conditions that could arise in the SR20, it is not a substitute for thorough knowledge of the airplane and general aviation techniques. A thorough study of the information in this handbook while on the ground will help you prepare for time-critical situations in the air.
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Cirrus Design SR20 Section 3A Abnormal Procedures Ground Procedures Brake Failure During Taxi Ground steering is accomplished by differential braking. However, increasing power may allow some rudder control due to increased groundspeed and airflow over the rudder. 1. Engine Power......................................................... AS REQUIRED • To stop airplane - REDUCE • If necessary for steering - INCREASE 2. Directional Control ............................... MAINTAIN WITH RUDDER 3.
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Section 3A Abnormal Procedures Cirrus Design SR20 In-Flight Procedures 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 ............................................
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Cirrus Design SR20 Section 3A Abnormal Procedures Landing Procedures Landing With Failed Brakes One brake inoperative 1. Land on the side of runway corresponding to the inoperative brake. 2. Maintain directional control using rudder and working brake. Both brakes inoperative 1. 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.
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Section 3A Abnormal Procedures Cirrus Design SR20 AMMETER BAT 1 ALT 1 ALT 2 BATT MAIN DISTRIBUTION BUS ALT 1 ESSENTIAL DISTRIBUTION BUS ALT 2 BAT 2 NON-ESSENTIAL SKYWATCH/ TAWS MAIN BUS 2 FUEL PUMP GPS 2 TURN COORD. #2 COM 2 ATTITUDE #2 ENCODER/ XPONDER HSI/PFD #2 WEATHER/ STORMSCOPE ESSENTIAL ANNUN/ENGINE INST TURN COORD.
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Cirrus Design SR20 Section 3A Abnormal Procedures System Malfunctions Alternator Failure Steady illumination of either ALT caution light in the annunciator panel indicates a failure of the corresponding alternator. The most likely the cause of the alternator failure is a wiring fault, a malfunctioning alternator, or a malfunctioning control unit. Usually, electrical power malfunctions are accompanied by an excessive rate of charge or a discharge rate shown on the ammeter.
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Section 3A Abnormal Procedures Cirrus Design SR20 ALT 1 Light Steady Steady illumination indicates a failure of ALT 1. Attempt to bring alternator back on line. If alternator cannot be brought back, reduce loads and use Main Bus or Non-Essential loads only as necessary for flight conditions. 1. ALT 1 Master Switch ................................................................OFF 2. Alternator 1 Circuit Breaker............................ CHECK and RESET 3. ALT 1 Master Switch ...........................
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Cirrus Design SR20 Section 3A Abnormal Procedures 2. Alternator 2 Circuit Breaker ........................... CHECK and RESET 3. ALT 2 Master Switch ..................................................................ON If alternator does not reset: 4. Switch off unnecessary equipment on Main Bus 1, Main Bus 2, and Non-Essential Buses to reduce loads. 5. ALT 2 Master Switch ................................................................ OFF 6. Land as soon as practical.
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Section 3A Abnormal Procedures Cirrus Design SR20 Communications Failure Communications failure can occur for a variety of reasons. If, after following the checklist procedure, communication is not restored, proceed with FAR/AIM lost communications procedures. • Note • In the event of an audio panel power failure the audio panel connects COM 1 to the pilot’s headset and speakers. Setting the audio panel ‘Off’ will also connect COM 1 to the pilot’s headsets and speakers. 1. Switches, Controls .............
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Cirrus Design SR20 Section 3A Abnormal Procedures Pitot Static Malfunction Static Source Blocked If erroneous readings of the static source instruments (airspeed, altimeter and vertical speed) are suspected, the alternate static source valve, on side of console near pilot’s right ankle, should be opened to supply static pressure from the cabin to these instruments.
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Section 3A Abnormal Procedures Cirrus Design SR20 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 circuit breaker (PITCH TRIM, ROLL TRIM, or AUTOPILOT) and land as soon as conditions permit. 1. Airplane Control ......................................... MAINTAIN MANUALLY 2. Autopilot (if engaged) ....................................................
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Cirrus Design SR20 Section 4 Normal Procedures Section 4 Normal Procedures Table of Contents Introduction ..................................................................................... 4-3 Airspeeds for Normal Operation ..................................................... 4-4 Normal Procedures ......................................................................... 4-5 Preflight Inspection ......................................................................4-5 Preflight Walk-Around ............
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Section 4 Normal Procedures Cirrus Design SR20 Intentionally Left Blank 4-2 Information Manual March 2010
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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. • Note • Serials 1337 and subsequent with SRV standard configuration: The airplane is equipped with a single alternator, dual battery electrical system. References to Alternator 2 in the following section do not apply.
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Section 4 Normal Procedures Cirrus Design SR20 Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3000 lb. and may be used for any lesser weight. However, to achieve the performance specified in Section 5 for takeoff distance, the speed appropriate to the particular weight must be used. Takeoff Rotation: • Normal, Flaps 50% ........................................................67 KIAS • Short Field, Flaps 50% .....................................
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Cirrus Design SR20 Section 4 Normal Procedures Normal Procedures Preflight Inspection Before carrying out preflight inspections, ensure that all required maintenance has been accomplished. Review your flight plan and compute weight and balance.
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Section 4 Normal Procedures Cirrus Design SR20 Preflight Walk-Around 1. Cabin a. Required Documents................................................ On Board b. Avionics Power Switch.......................................................OFF c. Bat 2 Master Switch ........................................................... ON d. PFD - Serials 1337 and subsequent with PFD .......... Verify On e. Avionics Cooling Fan .................................................... Audible f. Voltmeter ..............
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Cirrus Design SR20 Section 4 Normal Procedures d. COM 2 Antenna (underside) ...........Condition and Attachment e. Baggage Door ........................................... Closed and Secure f. Static Button .............................................. Check for Blockage g. Parachute Cover........................................ Sealed and Secure 3. Empennage a. Tiedown Rope .............................................................Remove b. Horizontal and Vertical Stabilizers......................
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Section 4 Normal Procedures Cirrus Design SR20 b. Fuel Cap ....................................... Check Quantity and Secure c. Fuel Drains (2 underside) ............................ Drain and Sample d. Wheel Fairings...................... Security, Accumulation of Debris e. Tire ............................................
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Cirrus Design SR20 Section 4 Normal Procedures e. Propeller ........................... Condition (indentations, nicks, etc.) f. Spinner ............................... Condition, Security, and Oil Leaks g. Air Inlets ..............................................................Unobstructed h. Alternator Belt........................................Condition and Tension 10. Nose, Left Side a. Landing Light............................................................. Condition b. Engine Oil.........
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Section 4 Normal Procedures Cirrus Design SR20 d. Tip ..........................................................................Attachment 13. Left Wing Trailing Edge a. Flap And Rub Strips (If installed)..........Condition and Security b. Aileron .................................................. Freedom of movement c. Hinges, actuation arm, bolts, and cotter pins ............... Secure Before Starting Engine 1. Preflight Inspection ..................................................
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Cirrus Design SR20 Section 4 Normal Procedures Starting Engine If the engine is warm, no priming is required. For the first start of the day and in cold conditions, prime will be necessary. Weak intermittent firing followed by puffs of black smoke from the exhaust stack indicates over-priming or flooding. Excess fuel can be cleared from the combustion chambers by the following procedure: • Turn fuel pump off. • Allow fuel to drain from intake tubes.
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Section 4 Normal Procedures Cirrus Design SR20 4. Strobe Lights ............................................................................. ON 5. Mixture ......................................................................... FULL RICH 6. Power Lever ........................................................FULL FORWARD 7. Fuel Pump.....................................................
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Cirrus Design SR20 Section 4 Normal Procedures Before Taxiing 1. Flaps ................................................................................. UP (0%) 2. Radios/Avionics ..................................................... AS REQUIRED 3. Cabin Heat/Defrost ............................................... AS REQUIRED 4. Fuel Selector...........................................................
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Section 4 Normal Procedures Cirrus Design SR20 Before Takeoff During cold weather operations, the engine should be properly warmed up before takeoff. In most cases this is accomplished when the oil temperature has reached at least 100° F (38° C). In warm or hot weather, precautions should be taken to avoid overheating during prolonged ground engine operation. Additionally, long periods of idling may cause fouled spark plugs.
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Cirrus Design SR20 Section 4 Normal Procedures to extinguish ALT 2 caution light. ALT 2 caution light should go out below 2200 RPM. 15. Voltage ............................................................................... CHECK 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 .................
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Section 4 Normal Procedures Cirrus Design SR20 Takeoff • Note • The engine is equipped with an altitude compensating fuel pump that automatically provides the proper full rich mixture. Because of this, the mixture should be left full rich for takeoff, even at high altitude airfields. 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.
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Cirrus Design SR20 Section 4 Normal Procedures Normal Takeoff 1. Brakes.................................... RELEASE (Steer with Rudder Only) 2. Power Lever ........................................................ FULL FORWARD 3. Engine Parameters ............................................................ CHECK 4. Elevator Control ........................ ROTATE Smoothly at 65-70 KIAS 5. At 85 KIAS, Flaps....................................................................... UP Short Field Takeoff 1.
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Section 4 Normal Procedures Cirrus Design SR20 Climb Normal climbs are performed flaps UP (0%) and full power at speeds 5 to 10 knots higher than best rate-of-climb speeds. These higher speeds give the best combination of performance, visibility and engine cooling. 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.
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Cirrus Design SR20 Section 4 Normal Procedures Cruise Normal cruising is performed between 55% and 75% power. The engine power setting and corresponding fuel consumption for various altitudes and temperatures can be determined by using the cruise data in Section 5. The selection of cruise altitude is made on the basis of the most favorable wind conditions and the use of low power settings. These significant factors should be considered on every trip to reduce fuel consumption.
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Section 4 Normal Procedures Cirrus Design SR20 Cruise Leaning The engine is equipped with an altitude compensating fuel pump that automatically provides the proper full rich mixture. Because of this, the mixture should be set to full rich to allow the aneroid to provide auto leaning for the engine during all flight conditions. 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.
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Cirrus Design SR20 Section 4 Normal Procedures Descent 1. Altimeter................................................................................... SET 2. Cabin Heat/Defrost ................................................ AS REQUIRED 3. Landing Light .............................................................................ON 4. Fuel System ....................................................................... CHECK 5. Mixture ...................................................................
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Section 4 Normal Procedures Cirrus Design SR20 Short Field Landing For a short field landing in smooth air conditions, make an approach at 75 KIAS with full flaps using enough power to control the glide path (slightly higher approach speeds should be used under turbulent air conditions). After all approach obstacles are cleared, progressively reduce power and maintain the approach speed by lowering the nose of the airplane. Touchdown should be made power-off and on the main wheels first.
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Cirrus Design SR20 Section 4 Normal Procedures After Landing 1. Power Lever ................................................................... 1000 RPM 2. Fuel Pump ............................................................................... OFF 3. Flaps .......................................................................................... UP 4. Transponder ...........................................................................STBY 5. Lights ....................................................
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Section 4 Normal Procedures Cirrus Design SR20 Stalls SR20 stall characteristics are conventional. Power-off stalls may be accompanied by a slight nose bobbing if full aft stick is held. Power-on stalls are marked by a high sink rate at full aft stick. Power-off stall speeds at maximum weight for both forward and aft C.G. positions are presented in Section 5 – Performance Data.
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Cirrus Design SR20 Section 4 Normal Procedures Environmental Considerations Cold Weather Operation Starting If the engine has been cold soaked, it is recommended that the propeller be pulled through by hand several times to break loose or limber the oil. This procedure will reduce power draw on the battery if a battery start is made.
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Section 4 Normal Procedures Cirrus Design SR20 cylinders, air intake and oil cooler. Because excessively hot air can damage non-metallic components such as composite parts, seals, hoses, and drives belts, do not attempt to hasten the preheat process. 1. Ignition Switch ..........................................................................OFF • WARNING • Use extreme caution when pulling the propeller through by hand.
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Cirrus Design SR20 Section 4 Normal Procedures 15. Avionics Power Switch ...............................................................ON 16. Engine Parameters ........................................................ MONITOR 17. External Power (If applicable) ................................. DISCONNECT 18. Amp Meter/Indication ......................................................... CHECK 19. Strobe Lights..............................................................................
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Section 4 Normal Procedures Cirrus Design SR20 Noise Characteristics/Abatement The certificated noise levels for the Cirrus Design SR20 established in accordance with FAR 36 Appendix G are: Configuration Actual Maximum Allowable Two-blade Propeller 84.79 dB(A) 87.6 dB(A) Three-blade Propeller 83.42 dB(A) 87.
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Cirrus Design SR20 Section 4 Normal Procedures Fuel Conservation Minimum fuel use at cruise will be achieved using the best economy power setting described under cruise.
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Section 4 Normal Procedures Cirrus Design SR20 Intentionally Left Blank 4-30 Information Manual March 2010
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Cirrus Design SR20 Section 5 Performance Data Section 5 Performance Data Table of Contents Introduction ..................................................................................... 5-3 Associated Conditions Affecting Performance............................. 5-3 Flight Planning ................................................................................ 5-4 Sample Problem ............................................................................. 5-4 Takeoff..................................
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Section 5 Performance Data Cirrus Design SR20 Range / Endurance Profile ............................................................5-29 Range / Endurance Profile ............................................................5-30 Balked Landing Climb Gradient ....................................................5-31 Balked Landing Rate of Climb.......................................................5-32 Landing Distance ..........................................................................
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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).
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Section 5 Performance Data Cirrus Design SR20 Flight Planning The performance tables in this section present sufficient information to predict airplane performance with reasonable accuracy. However, variations in fuel metering, mixture leaning technique, engine & propeller condition, air turbulence, and other variables encountered during a particular flight may account for variations of 10% or more in range and endurance.
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Cirrus Design SR20 Section 5 Performance Data Cruise Conditions: • Total distance ................................................560 Nautical Miles • Pressure altitude ........................................................ 6500 Feet • Temperature ................................................20 C (ISA + 17 C) • Expected wind enroute..................................10 Knot Headwind Landing Conditions: • Field pressure altitude ................................................
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Section 5 Performance Data Cirrus Design SR20 • Decrease in total distance (2734 feet x 0.092) .............. 252 feet • Corrected total distance to clear 50-foot obstacle ....... 2482 feet Corrections for grass runways and sloped runways are also applicable and should be applied. These corrections are calculated in the same manner as the wind correction above. Refer to Figure 5-9 for correction factors to be applied.
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Cirrus Design SR20 Section 5 Performance Data climb performance is to increase the time, fuel, and distance to climb by approximately 10% for each 10 C above ISA. In our example, using a temperature of ISA + 13 C, the correction to be applied is 13%. The fuel estimate for climb is: • Fuel to climb (standard temperature) ............................ 2.1 Gal. • Increase due to non-standard temp. (2.1 x 0.13) .......... 0.3 Gal. • Corrected fuel to climb (2.1 + 0.3) ................................. 2.
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Section 5 Performance Data Cirrus Design SR20 Fuel Required The total fuel requirement for the flight may be estimated using the performance information obtained from Figures 5-15 and 5-16. The resultant cruise distance is: • Total distance (from sample problem) ........................ 560.0 NM • Climb distance (corrected value from climb table)........ 17.0 NM • Cruise distance (total distance – climb distance) ....... 543.
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Cirrus Design SR20 Section 5 Performance Data Landing A procedure similar to takeoff should be used for estimating the landing distance at the destination airport. Figure 5-20 presents landing distance information for the short field technique. The distances corresponding to 2000 feet and 20 C are as follows: • Ground roll ................................................................. 1110 Feet • Total distance to land over a 50-foot obstacle ...........
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Section 5 Performance Data Cirrus Design SR20 Airspeed Calibration Normal Static Source Conditions: Example: • Power for level flight or maximum continuous, whichever is less. • Weight .................................. 3000 LB Flaps ........................................... 50% Indicated Airspeed ............... 85 Knots Calibrated Airspeed ............. 86 Knots • Note • • Indicated airspeed values assume zero instrument error.
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Cirrus Design SR20 Section 5 Performance Data Airspeed Calibration Alternate Static Source Conditions: Example: • Power for level flight or maximum continuous, whichever is less. • Weight ...................................3000 LB • Heater, Defroster & Vents .............ON Flaps............................................50% Indicated Airspeed................85 Knots Calibrated Airspeed ..............84 Knots • Note • • Indicated airspeed values assume zero instrument error.
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Section 5 Performance Data Cirrus Design SR20 Altitude Correction Normal Static Source Conditions: Example: • Power for level flight or maximum continuous, whichever is less. • Weight .................................. 3000 LB Flaps ........................................... 50% Indicated Airspeed ............... 85 Knots Desired Altitude.................. 12,000 FT Altitude Correction .....................-7 FT Altitude to Fly .....................
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Cirrus Design SR20 Section 5 Performance Data Altitude Correction Alternate Static Source Conditions: Example: • Power for level flight or maximum continuous, whichever is less. • Weight ...................................3000 LB • Heater, Defroster, & Vents.............ON Flaps..............................................0% Indicated Airspeed..............120 Knots Desired Altitude ................. 12,000 FT Altitude Correction................... -11 FT Altitude to Fly.....................
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Section 5 Performance Data Cirrus Design SR20 Temperature Conversion • Note • • To convert from Celsius (°C) to Fahrenheit (°F), find, in the shaded columns, the number representing the temperature value (°C) to be converted. The equivalent Fahrenheit temperature is read to the right.  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.
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Cirrus Design SR20 Section 5 Performance Data Outside Air Temperature for ISA Condition Example: Pressure Altitude...................8000 FT Outside Air Temp....................... 48° F ISA Condition ..................
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Section 5 Performance Data Cirrus Design SR20 Stall Speeds Conditions: • • • • Example: Weight .................................. 3000 LB C.G. .......................................... Noted Power............................................Idle Bank Angle ............................... Noted Flaps ..................................... Up (0%) Bank Angle....................................15° Stall Speed..........
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Cirrus Design SR20 Section 5 Performance Data Wind Components Conditions: Example: • Runway Heading ...........................10° • Wind Direction...............................60° • Wind Velocity........................ 15 Knots Wind/Flight Path Angle ................. 50° Crosswind Component .........12 Knots Headwind Component..........10 Knots • Note • • The maximum demonstrated crosswind is 21 knots. Value not considered limiting.
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Section 5 Performance Data Cirrus Design SR20 Takeoff Distance Conditions: • Winds.......................................... Zero • Runway................... Dry, Level, Paved • Flaps........................................... 50% • Power.................................. Maximum set before brake release Example: Outside Air Temp ....................... 25°C Weight................................... 3000 LB Pressure Altitude................... 2000 FT Headwind .............................
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Cirrus Design SR20 Section 5 Performance Data Takeoff Distance WEIGHT = 3000 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.
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Section 5 Performance Data Cirrus Design SR20 Takeoff Distance WEIGHT = 2500 LB Speed at Liftoff = 65 KIAS Speed over 50 Ft Obstacle = 70 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.
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Cirrus Design SR20 Section 5 Performance Data Takeoff Climb Gradient Conditions: • • • • Example: Power .............................. Full Throttle Mixture ................................. Full Rich Flaps ........................................... 50% Airspeed ............... Best Rate of Climb Outside Air Temp .......................20° C Weight .................................. 3000 LB Pressure Altitude .................. 1750 FT Climb Airspeed .....................85 Knots Gradient..............
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Section 5 Performance Data Cirrus Design SR20 Takeoff Rate of Climb Conditions: • • • • Example: Power...............................Full Throttle Mixture..................................Full Rich Flaps........................................... 50% Airspeed ...............Best Rate of Climb Outside Air Temp ...................... 20° C Weight................................... 3000 LB Pressure Altitude................... 1750 FT Climb Airspeed..................... 85 Knots Rate of Climb .............
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Cirrus Design SR20 Section 5 Performance Data Enroute Climb Gradient Conditions: • • • • Example: Power .............................. Full Throttle Mixture ................................. Full Rich Flaps .....................................0% (UP) Airspeed ............... Best Rate of Climb Outside Air Temp .......................20° C Weight .................................. 3000 LB Pressure Altitude .................. 4200 FT Climb Airspeed .....................94 Knots Gradient.................
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Section 5 Performance Data Cirrus Design SR20 Enroute Rate of Climb Conditions: • • • • Example: Power...............................Full Throttle Mixture..................................Full Rich Flaps..................................... 0% (UP) Airspeed ...............Best Rate of Climb Outside Air Temp ...................... 10° C Weight................................... 3000 LB Pressure Altitude................... 6500 FT Climb Airspeed..................... 93 Knots Rate of Climb ...............
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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 ............................
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Section 5 Performance Data Cirrus Design SR20 Time, Fuel and Distance to Climb Conditions: • • • • • • Example: Power...............................Full Throttle Mixture..................................Full Rich Fuel Density..................... 6.0 LB/GAL Weight .................................. 3000 LB Winds.......................................... Zero Climb Airspeed ......................... Noted Outside Air Temp ......................... ISA Weight...................................
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Cirrus Design SR20 Section 5 Performance Data Cruise Performance Conditions: • Mixture ............................. Best Power • Cruise Weight........................2600 LB • Winds ..........................................Zero Note: Subtract 10 KTAS if nose wheel pant and fairing removed. Lower KTAS by 10% if nose & main wheel pants & fairings removed. Cruise Pwr above 85% not recommended. Example: Outside Air Temp29° C RPM 2700 RPM Cruise Press Alt8000 FT % Power (22.
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Section 5 Performance Data Cirrus Design SR20 Cruise Performance 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 9.5 52% 134 9.
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Cirrus Design SR20 Section 5 Performance Data Range / Endurance Profile Conditions: • • • • • Example: Weight ...................................3000 LB Temperature ................. Standard Day Winds ..........................................Zero Mixture ............................. See Tables Total Fuel........................... 56 Gallons Power Setting .............................75% Takeoff Press Alt .................. 2000 FT Cruise Press Alt....................
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Section 5 Performance Data Cirrus Design SR20 Range / Endurance Profile 65% POWER Press Climb Alt Fuel Mixture = Best Power FT Gal Fuel Remaining For Cruise Gal Airspeed Fuel Flow Endurance Range Specific Range 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.
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Cirrus Design SR20 Section 5 Performance Data Balked Landing Climb Gradient Conditions: • • • • Example: Power .............................. Full Throttle Mixture ................................. Full Rich Flaps ................................ 100% (DN) Airspeed ............... Best Rate of Climb Outside Air Temp .......................20° C Weight .................................. 2500 LB Pressure Altitude .................. 2000 FT Climb Airspeed .....................74 Knots Rate of Climb.......
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Section 5 Performance Data Cirrus Design SR20 Balked Landing Rate of Climb Conditions: • • • • Example: Power...............................Full Throttle Mixture..................................Full Rich Flaps.................................100% (DN) Climb Airspeed ......................... Noted Outside Air Temp ...................... 20° C Weight................................... 2500 LB Pressure Altitude................... 4000 FT Climb Airspeed..................... 73 Knots Rate of Climb .......
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Cirrus Design SR20 Section 5 Performance Data Landing Distance Conditions: • • • • • Example: Technique .............................. Normal Winds ..........................................Zero Runway .................................... Paved Flaps. ........................................ 100% Power .................. 3° Power Approach to 50 FT obstacle, then reduce power passing the estimated 50 foot point and smoothly continue power reduction to reach idle just prior to touchdown.
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Section 5 Performance Data Cirrus Design SR20 Landing Distance WEIGHT = 2900 LB Headwind: Subtract 10% per each Speed over 50 Ft Obstacle = 75 KIAS 13 knots headwind. Flaps - 100% · Idle · Dry, Level Paved Surface Tailwind: Add 10% for each 2 knots tailwind up to 10 knots. Runway Slope: Ref. Factors.
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Cirrus Design SR20 Section 6 Weight and Balance Section 6 Weight and Balance Table of Contents Introduction ..................................................................................... 6-3 Airplane Weighing Form ................................................................. 6-6 Airplane Weighing Procedures ....................................................... 6-7 Weight & Balance Record ............................................................. 6-10 Loading Instructions ..................
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Section 6 Weight and Balance Cirrus Design SR20 Intentionally Left Blank 6-2 Information Manual March 2010
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Cirrus Design SR20 Section 6 Weight & Balance Introduction This section describes the procedure for establishing the basic empty weight and moment of the airplane. Sample forms are provided for reference. Procedures for calculating the weight and moment for various operations are also provided. A comprehensive list of all equipment available for this airplane is included at the back of this section.
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Section 6 Weight & Balance Cirrus Design SR20 FS 350.2" WATER LINE (WL) FS 55.6" 150 WL 165.5" FS 222.0" FS 100.0" FS 38.3" WL100 350 250 200 150 100 0.0 50 FS 157.5" 300 NOTE Reference Datum located at fuselage station 0.0". 50 (FS) FUSELAGE STATION LEMAC FS 132.9" 220 RBL 210.9" 200 150 100 RBL 87.7" Typical LBL MAC 48.4" RBL 77.3" RBL 66.3" 50 BL 0.0" BL 0.0 50 LBL 66.3" LBL 77.3" 100 150 200 BUTTOCK LINE (BL) LBL 210.
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Cirrus Design SR20 Section 6 Weight & Balance Spirit Level LONGITUDINAL LEVELING Spirit Level Straight Edge Straight Edge Spacer Block Straight Edge Door Sill Door Sill LATERAL LEVELING Information Manual March 2010 Figure 6-2 Airplane Leveling Spacer Block SR20_FM06_1021A 6-5
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Section 6 Weight & Balance Cirrus Design SR20 Airplane Weighing Form REF DATUM FS 0.0 FS 100.0 FS 145.0 WL 100.
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Cirrus Design SR20 Section 6 Weight & Balance Airplane Weighing Procedures A basic empty weight and center of gravity were established for this airplane when the airplane was weighed just prior to initial delivery. However, major modifications, loss of records, addition or relocation of 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. The frequency of weighing is determined by the operator.
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Section 6 Weight & Balance Cirrus Design SR20 4. Measuring (Figure 6-3): a. Obtain measurement ‘x’ by measuring horizontally along the airplane center line (BL 0) from a line stretched between the main wheel centers to a plumb bob dropped from the forward side of the firewall (FS 100). 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.
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Cirrus Design SR20 Section 6 Weight & Balance The above procedure determines the airplane Basic Empty Weight, moment, and center of gravity in inches aft of datum. C.G. can also be expressed in terms of its location as a percentage of the airplane Mean Aerodynamic Cord (MAC) using the following formula: C.G. % MAC = 100 x (C.G. Inches – LEMAC) / MAC Where: LEMAC = 132.9 MAC = 48.
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Section 6 Weight & Balance 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: Item No. Date Reg. Num: Description of Article or Modification In Out Page Weight Change Added (+) or Removed (-) WT LB ARM IN.
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Cirrus Design SR20 Section 6 Weight & Balance 49.3" 39.8" 100 120 140 160 200 180 49.7" 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" 21.0" BAGGAGE DOOR OPENING CABIN DOOR OPENING SR20_FM06_1019 Location Length Width Height Volume Cabin 122” 49.3” 49.7 137 cu ft Baggage Compartment 36” 39.8” 38.
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Section 6 Weight & Balance 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 6-9) for a determination of proper loading.
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Cirrus Design SR20 Section 6 Weight & Balance • The total moment/1000 must not be above the maximum or below the minimum moment/1000 for the Takeoff Condition Weight as determined from the Moment Limits chart or table (Figure 6-9).
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Section 6 Weight & Balance Cirrus Design SR20 Center of Gravity Limits The charts below depict the airplane center-of-gravity envelope in terms of inches aft of the reference datum and as a percentage of the Mean Aerodynamic Cord (MAC). The relationship between the two is detailed in the weighing instructions. 23.1 % MAC FS 144.1 3000 lb 3000 31.3 % MAC FS 148.0 3000 lb Weight - Pounds 2800 31.5 % MAC FS 148.1 2900 lb 16.7 % MAC FS 141.0 2694 lb 2600 30.0 % MAC FS 147.4 2570 lb 2400 12.
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Cirrus Design SR20 Section 6 Weight & Balance Weight & Balance Loading Form Serial Num: ________________ Date: ________________________ Reg. Num: _________________ Initials: ______________________ Item Description 1. Basic Empty Weight Includes unusable fuel & full oil 2. Front Seat Occupants Pilot & Passenger (total) 3. Rear Seat Occupants 4. Baggage Area 130 lb maximum 5. Zero Fuel Condition Weight Sub total item 1 thru 4 6. Fuel Loading 56 Gallon @ 6.0 lb/gal. Maximum 7.
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Section 6 Weight & Balance 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 (Figure 6-7). 500 Fuel Fwd Pass Loading Chart Aft Pass Weight - Pounds 400 300 200 Baggage 100 0 0 Weight LB 10 20 Fwd Aft Pass Pass FS 143.5 FS 180.0 3.60 30 40 50 Moment/1000 Baggage Fuel Weight FS 208.0 FS 153.8 LB 4.16 3.08 220 60 70 80 90 SR20_FM06_1942 Fwd Aft Fuel Pass Pass FS 143.5 FS 180.
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Cirrus Design SR20 Section 6 Weight & Balance Moment Limits Use the following chart or table to determine if the weight and moment from the completed Weight and Balance Loading Form (Figure 6-7) are within limits.
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Section 6 Weight & Balance Cirrus Design SR20 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 Description Section 7 Airplane and Systems Description Table of Contents Introduction ..................................................................................... 7-5 Airframe .......................................................................................... 7-6 Fuselage ...................................................................................... 7-6 Wings.......................................................................................
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Section 7 Airplane Description Cirrus Design SR20 Cabin Doors ...............................................................................7-36 Baggage Compartment..............................................................7-38 Seats..........................................................................................7-38 Windshield and Windows...........................................................7-39 Cabin Safety Equipment ............................................................
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Section 7 Airplane Description Cirrus Design SR20 Interior Lighting ............................................................................. 7-76 Instrument Lights ....................................................................... 7-77 Panel Flood Lights ..................................................................... 7-77 Reading Lights........................................................................... 7-77 Overhead Dome Light........................................................
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Section 7 Airplane Description Cirrus Design SR20 Intentionally Left Blank 7-4 Information Manual March 2010
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Cirrus Design SR20 Section 7 Airplane Description Introduction This section provides a basic description and operation of the standard airplane and its systems. Optional equipment described within this section is identified as optional. • Note • Some optional equipment, primarily avionics, may not be described in this section.
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Section 7 Airplane Description Cirrus Design SR20 Airframe Fuselage The SR20 monocoque fuselage is constructed primarily of composite materials and is designed to be aerodynamically efficient. The cabin area is bounded on the forward side by the firewall at fuselage station 100, and on the rear by the aft baggage compartment bulkhead at fuselage station 222. Comfortable seating is provided for four adults.
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Cirrus Design SR20 Section 7 Airplane Description fuselage. The main wing spar passes under the fuselage below the two front seats and is attached to the fuselage in two locations. The rear shear webs are attached to the fuselage sidewalls just aft of the rear seats. 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.
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Section 7 Airplane Description Cirrus Design SR20 Flight Controls The SR20 uses conventional flight controls for ailerons, elevator and rudder. The control surfaces are pilot controlled through either of two single-handed side control yokes mounted beneath the instrument panel. The location and design of the control yokes allow easy, natural use by the pilot. The control system uses a combination of push rods, cables and bell cranks for control of the surfaces.
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Cirrus Design SR20 Section 7 Airplane Description SR20_FM07_1461 Information Manual March 2010 Figure 7-1 Elevator Control System 7-9
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Section 7 Airplane 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.
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Cirrus Design SR20 Section 7 Airplane Description SR20_FM07_1462 Information Manual March 2010 Figure 7-2 Aileron Control System 7-11
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Section 7 Airplane 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.
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Cirrus Design SR20 Section 7 Airplane Description SR20_FM07_1463 Information Manual March 2010 Figure 7-3 Rudder Control System 7-13
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Section 7 Airplane Description Cirrus Design SR20 Trim Systems Roll and pitch trim are provided by adjusting the neutral position of a compression spring cartridge in each control system by means of an electric motor. The electric roll trim is also used by the autopilot to position the ailerons. It is possible to easily override full trim or autopilot inputs by using normal control inputs.
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Cirrus Design SR20 Section 7 Airplane Description Yaw Trim System Yaw trim is provided by spring cartridge attached to the rudder pedal torque tube and console structure. The spring cartridge provides a centering force regardless of the direction of rudder deflection. The yaw trim is ground adjustable only.
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Section 7 Airplane Description Cirrus Design SR20 Flight Deck Arrangement The following paragraphs are a general description of the flight deck, instrumentation, and controls. The instrument panel is designed for glare-free use in all flight conditions. The instrument panel is arranged primarily for use by the pilot in the left seat; however, it can be viewed from either seat.
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Cirrus Design SR20 Section 7 Airplane Description Serials 1337 and subsequent: The airplane is equipped with an Avidyne FlightMax Entegra-Series Primary Flight Display (PFD). The PFD is a 10.4” landscape-oriented display intended to be the primary display of primary flight parameter information (attitude, airspeed, heading, and altitude) to the pilot.
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Section 7 Airplane Description TEMP C 30 + - 30 P.
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Cirrus Design SR20 1 2 3 Section 7 Airplane Description 6 5 4 FASTEN SEATBELTS 7 FIRE EXTINGUISHER UNDER PILOT SEAT FRONT 8 9 NO SMOKING ALTITUDE GPH 16000 17 12000 18 8000 21 4000 24 SL 27 MAX POWER FUEL FLOWS 10 AMMETER SELECT ALT 1 ALT2 BATT 22 21 20 L R 11 ALT AIR PULL ON 19 ALT STATIC SOURCE NORMAL PARK BRAKE PULL ON 12 FUEL LLFE T R GI 13 18 17 Legend 1. Start/Ignition Key Switch 2. Annunciator Panel 3. Primary Flight Display 4. Overhead Light & Switch 5.
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Section 7 Airplane Description 1 2 3 Cirrus Design SR20 6 5 4 7 8 9 10 22 21 20 11 ALT AIR PULL ON 19 ALT STATIC SOURCE NORMAL PARK BRAKE PULL ON 12 FUEL LLFE T R GI 13 18 17 Legend 1. Start/Ignition Key Switch 2. Annunciator Panel 3. Primary Flight Display 4. Overhead Light & Switch 5. Magnetic Compass 6. Cirrus Airframe Parachute System (CAPS) Activation T-Handle Cover 7. Multifunction Display 8. Glove Box 16 15 9. Temperature/Ventilation Controls 10. Control Yoke 11.
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Cirrus Design SR20 Section 7 Airplane Description Flight Instruments • Note • For additional information on instrument limit markings, refer to Section 2, Limitations. Primary Flight Display - Serials 1337 and Subsequent The Primary Flight Display (PFD) provides the functions of the attitude indicator, heading indicator, airspeed indicator, altimeter, vertical speed indicator, directional gyro, course deviation indicator, and altitude pre-select controller onto a single electronic display.
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Section 7 Airplane Description Cirrus Design SR20 PFD 2 MAIN BUS 2 10 PFD 1 ESSENTIAL BUS 10 #1 GNS-430 GPS PITOT STATIC Avidyne PFD #2 GNS-430 GPS OAT Sensor / Magnetometer Data Aquisition Unit OFF AP ON FD ON AP Flight Director System (Optional) STEC System 55x Autopilot Avidyne MFD SR20_FM07_1607B 7-22 Figure 7-5 PFD System - Simplified Schematic Information Manual March 2010
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Cirrus Design SR20 Section 7 Airplane Description Attitude Direction Indicator (ADI) Air Data The airspeed tape to the left of the main ADI begins indicating at 20 Knots Indicated Airspeed (KIAS) and is color-coded to correspond with airspeeds for VSO, VFE, VS, VNO, and VNE. An altitude tape is provided to the right of the main ADI and also displays a symbol for the Altitude preselect (Altitude bug). The Vertical Speed Indicator (VSI) is displayed to the right of the altitude tape.
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Section 7 Airplane Description 2 3 4 Cirrus Design SR20 5 6 7 8 9 10 11 12 13 14 15 AP RDY M-BUS 24.0 V E-BUS 24.0 V 20 20 5000 110 10 10 4900 1 10 0 9 20 48 00 10 4700 ILS Power 20 80 20 4600 ILS VLOC 1 Bearing GPS 1 Aux GPS 2 ILS 108.10 CRS 020° 1 17 N 037°/ 7 3 33 -5 -10 -20 Hdg Bug 005° Alt Bug 6 4900 FT 30 VSI Bug E KLWH BRG 352° 43.6 NM 00:17:52 W -500 FPM 12 24 TAS110 KTS GS 98 KTS OAT 11°C 22 5 0 29.92" 006 SAV DTK 020° 62.
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Cirrus Design SR20 Section 7 Airplane Description Horizontal Situation Indicator (HSI) Heading Data Magnetic heading is represented in boxed numeric form at the top of the compass rose. Heading rate (Rate of Turn Indicator) takes the form of a blue arcing arrow that begins behind the magnetic heading indicator and moves left or right accordingly. Graduations are provided on the rate-of-turn indicator scale to indicate half and full standard-rate turns. A heading bug is also provided on the compass rose.
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Section 7 Airplane Description Cirrus Design SR20 Attitude Indicator • Note • Serials 1337 and subsequent with SRV standard configuration: The airplane is not equipped with a standby attitude indicator. Serials 1337 and subsequent without SRV configuration: The standby attitude indicator is mounted on the LH bolster panel. The attitude indicator gives a visual indication of flight attitude.
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Cirrus Design SR20 Section 7 Airplane Description Airspeed Indicator • Note • Serials 1337 and subsequent: The standby airspeed indicator is mounted on the LH bolster panel and shows only indicated airspeed. Indicated and true airspeeds are indicated on a dual-scale, internally lit precision airspeed indicator installed in the pilot’s instrument panel. The instrument senses difference in static and Pitot pressures and displays the result in knots on an airspeed scale.
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Section 7 Airplane Description Cirrus Design SR20 Altimeter • Note • Serials 1337 and subsequent: The standby altimeter is mounted on the LH bolster panel. Airplane altitude is depicted on a conventional, three-pointer, internally lit barometric altimeter installed in the pilot's instrument panel. The instrument senses the local barometric pressure adjusted for altimeter setting and displays the result on the instrument in feet.
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Cirrus Design SR20 Section 7 Airplane Description Avionics Configuration 2.2: The electric turn coordinator, installed in the instrument panel, displays roll information and provides roll data to the System 55X autopilot. The instrument and power supplies are as described above. Directional Gyro Avionics Configuration 2.0: The airplane is equipped with a directional gyro in the standard configuration. If a directional gyro is not installed the airplane will be equipped with an HSI.
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Section 7 Airplane Description Cirrus Design SR20 Course Deviation Indicator • Note • Serials 1337 and subsequent: The Course Deviation Indicator is integrated into the PFD. Avionics Configuration 2.0 and 2.1: The Course Deviation Indicator (CDI) displays navigation information from the GPS navigator. The CDI displays GPS track deviation on a single deviation bar instrument. A vertical line displays GPS track deviation against a 5-dot scale. The indicator incorporates TO/FROM annunciation and NAV flag.
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Cirrus Design SR20 Section 7 Airplane Description Horizontal Situation Indicator • Note • Serials 1337 and subsequent: The Horizontal Situation Indicator is integrated into the PFD. Avionics Configuration 2.1: The Century NSD-1000 is a conventional HSI that provides gyro stabilized, magnetically slaved, heading information, a pictorial VOR/ LOC display with a conventional course arrow, and glideslope presentation.
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Section 7 Airplane Description Cirrus Design SR20 Avionics Configuration 2.2: The Sandel SN3308 combines the functions of an HSI, an RMI, a full color moving map, a Stormscope display, GPS annunciator, and 3-light marker beacon indicators. Compass information is derived from a remote directional gyro and a flux detector. Redundant power sources provide 28 VDC for system operation.
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Cirrus Design SR20 Section 7 Airplane Description The SN3308 detects and warns of abnormal conditions such as flagged navigation receivers and failed directional gyro or flux detector. It also monitors its own internal temperature and provides warnings for over-temperature or loss of cooling conditions. Redundant circuits paralleled through diodes at the indicator supply DC electrical power for gyro operation.
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Section 7 Airplane 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.
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Cirrus Design SR20 Section 7 Airplane Description SR20_FM07_1460 Information Manual March 2010 Figure 7-7 Wing Flaps 7-35
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Section 7 Airplane 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.
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Cirrus Design SR20 Section 7 Airplane Description DEFROST AIR OUTLETS STALL WARNING HORN FIRE EXTINGUISHER (UNDER PILOT'S SEAT) OVERHEAD LIGHT AND SWITCH A DOOR HANDLE EGRESS HAMMER (IN ARMREST) CABIN SPEAKER PASSENGER FRESH AIR OUTLET OVERHEAD LIGHT AND SWITCH TIEDOWN LOOPS (4 PLACES, BAGGAGE FLOOR) TIEDOWN LOOPS (6 PLACES, AFT BULKHEAD) DETAIL A CAPS ACTIVATION T-HANDLE (OVERHEAD) SR20_FM07_1064 Information Manual March 2010 Figure 7-8 Cabin Arrangement 7-37
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Section 7 Airplane 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.
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Cirrus Design SR20 Section 7 Airplane Description adjusted through the seat position control located below the forward edge of the seat cushion. The seat track is angled upward for forward travel so that shorter people will be positioned slightly higher as they adjust the seat forward. Recline position is controlled through levers located on each side of the seat backs. Depressing the recline release control while there is no pressure on the seat back will return the seat back to the full up position.
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Section 7 Airplane Description Cirrus Design SR20 Cabin Safety Equipment Passenger Restraints Integrated seat belt and shoulder harness assemblies with inertia reels are provided for the pilot and each passenger. The rear seat belts are attached to fittings on the floorboard and the forward seat belts are attached to the seat frame. 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.
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Cirrus Design SR20 Section 7 Airplane Description 3. Grasp the seat belt tabs outboard of the link and buckle and pull to tighten. Buckle should be centered over hips for maximum comfort and safety. 4. Restraint harnesses should fit snug against the shoulder with the lap buckle centered and tightened around the hips. 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.
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Section 7 Airplane Description Cirrus Design SR20 cabin by opening air vents and unlatching door. Close vents and door after fumes clear. The extinguisher must be visually inspected before each flight to assure that it is available, charged, and operable. The preflight inspection consists of ensuring that the nozzle is unobstructed, the pin has not been pulled, and the canister has not been damaged. Additionally, the unit should weigh approximately 1.5 lb (0.7 kg).
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Cirrus Design SR20 Section 7 Airplane Description Engine The SR20 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.
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Section 7 Airplane Description Cirrus Design SR20 the engine compartment through two vents in the aft portion of the cowling. No movable cowl flaps are used. Engine Fuel Injection The multi-nozzle, continuous-flow fuel injection system supplies fuel for engine operation. An engine driven fuel pump draws fuel from the selected wing tank and passes it to the mixture control valve integral to the pump.
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Cirrus Design SR20 Section 7 Airplane Description Engine Exhaust Engine exhaust gases are routed through a dual tuned exhaust system. After leaving the cylinders, exhaust gases are routed through the exhaust manifold, through mufflers located on either side of the engine, and then overboard through exhaust pipes exiting through the lower cowling. A muff type heat exchanger, located around the right muffler, provides cabin heat.
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Section 7 Airplane Description Cirrus Design SR20 Start/Ignition Switch • Note • Serials 1337 and subsequent: The Start/Ignition Switch is located on the instrument panel. A rotary-type key switch, located on the left bolster, controls ignition and starter operation. The switch is labeled OFF-R-L- BOTH-START. In the OFF position, the starter is electrically isolated, the magnetos are grounded and will not operate.
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Cirrus Design SR20 Section 7 Airplane Description Serials 1268 through 1581: The engine instruments are located on the right side of the instrument panel and the oil temperature/pressure warning light is located in the annunciator panel immediately in front of the pilot. Serials 1582 and subsequent: The engine instrumentation is displayed on the MFD’s Engine Page.
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Section 7 Airplane Description Cirrus Design SR20 1 3 2 FUEL R I G L E F T Start / Ignition Switch Serials 1005 thru 1336 : Switch is located on the left bolster panel. Controls 4 5,6 7,8 9 Alternate Air Control LEGEND 1. Power Lever 2. Mixture Control 3. Friction Control 4. Tachometer 5. EGT 7-48 Serials 1005 thru 1581. 6. CHT 7. Oil Temperature 8. Oil Pressure 9.
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Cirrus Design SR20 Section 7 Airplane Description OIL 11 LOW VOLTS FUEL PITOT HEAT ALT 1 ALT 2 Annunciator Panel 10 Primary Flight Display 4 LEGEND 4. Tachometer 5. EGT ( shown w ith EM ax ) 6. CHT (shown with EMax) 7. Oil Temperature 8. Oil Pressure 9. Manifold Pressure 10. Percent Power 11. Oil Warning Light 9 11 5 7 4,9,8 8 6 Multifunction Display Engine Instruments Serials 1582 & subs.
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Section 7 Airplane Description Cirrus Design SR20 Tachometer Serials 1268 through 1581: A 2¼” tachometer is mounted on the right instrument panel adjacent to the other engine instruments. The tachometer pointer sweeps a scale marked from 0 to 3500 RPM in 100 RPM increments. The electrically operated tachometer receives a speed signal from a magnetic pickup on the right hand magneto. 28 VDC for instrument operation is supplied through the 5-amp ENGINE INST circuit breaker on Main Bus 1.
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Cirrus Design SR20 Section 7 Airplane Description signal from a temperature sensor mounted in the #6 cylinder head on the left side of the engine. Serials 1582 and subsequent: Exhaust Gas Temperature (EGT) and Cylinder Head Temperature (CHT) readings are displayed on the MFD as vertical bars that ascend and descend respective to increasing and decreasing temperatures. The EGT indicator receives a temperature signal via the DAU from a sensor mounted in the exhaust stream of the #4 cylinder exhaust pipe.
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Section 7 Airplane Description Cirrus Design SR20 The Oil Pressure pointer sweeps a scale marked from 0 psi to 100 psi. The Oil Pressure indicator receives a pressure signal from an oil pressure sensor mounted at the aft end of the engine below the oil cooler. Normally, oil pressure may drop to 10 psi at idle but will be in the 30 - 60 psi range at higher RPM. Serials 1582 and subsequent: Oil temperature is shown in the upper right corner of the MFD as both a simulated temperature gage and as text.
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Cirrus Design SR20 Section 7 Airplane Description 28 VDC for instrument operation is supplied through the 5-amp ENGINE INST circuit breaker on Main Bus #1. The Fuel Flow pointer sweeps a scale marked from 0 to 30 Gal/Hr. The electrically operated Fuel Flow indicator receives a fuel-flow rate signal from a fuel-flow transducer on the right side of the engine in the fuel line between the engine driven fuel pump and throttle body metering valve.
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Section 7 Airplane Description Cirrus Design SR20 28 VDC for the digital instrument operation is supplied through the 2amp ANNUN / ENGINE INST circuit breaker on the Essential Bus. Oil Warning Light The red OIL warning light in the annunciator panel comes on to indicate either high oil temperature or low oil pressure. The light is illuminated by a switch in the oil temperature gage/DAU if the oil temperature reaches 240°F or if the oil pressure drops to 10 psi or less.
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Cirrus Design SR20 Section 7 Airplane Description Propeller The airplane is equipped with a constant-speed, aluminum-alloy propeller with a governor. The airplane is available with the standard two-blade (76” diameter) propeller or an optional three-blade (74” diameter) propeller. The propeller governor automatically adjusts propeller pitch to regulate propeller and engine RPM.
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Section 7 Airplane Description Cirrus Design SR20 Fuel System A 56-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 30.3-gallon capacity (28gallon usable) vented integral fuel tank in each wing, a fuel collector/ sump in each wing, a three-position selector valve, an electric boost pump, and an engine-driven fuel pump.
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Cirrus Design SR20 VENT Section 7 Airplane Description ANNUNCIATOR FUEL FUEL QUANTITY INDICATOR FILLER VENT FILLER L. WING TANK R. WING TANK R. WING COLLECTOR L. WING COLLECTOR SELECTOR VALVE FLAPPER VALVE DRAIN (5 PLACES) FLAPPER VALVE FIREWALL ELECTRIC AUXILIARY PUMP SELECTOR VALVE OPERATION FUEL RELAY BOOST FUEL PUMP PRIME RIGHT RETURN FEED RETURN FEED GASCOLATOR OIL PRESSURE SENSOR (LOW PRESSURE) LEFT ENGINE DRIVEN FUEL PUMP MIXTURE CNTL.
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Section 7 Airplane Description Cirrus Design SR20 The airplane may be serviced to a reduced capacity to permit heavier cabin loadings. This is accomplished by filling each tank to a tab visible below the fuel filler, giving a reduced fuel load of 13 gallons usable in each tank (26 gallons total usable in all flight conditions). Drain valves at the system low points allow draining the system for maintenance and for examination of fuel in the system for contamination and grade.
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Cirrus Design SR20 Section 7 Airplane Description Fuel Quantity Indicator A dual reading 2¼” fuel quantity indicator is installed on the console immediately forward of the fuel selector valve. The LEFT pointer indicates left tank fuel quantity and sweeps a scale marked from 0 to 28 U.S. gallons in 2½-gallon increments. The RIGHT pointer sweeps an identical scale for the right tank. Each scale is marked with a yellow arc from 0 to 8.2 gallon.
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Section 7 Airplane Description Cirrus Design SR20 4 Serials 1005 thru 1581. 1 2 3 1. 2. 3. 4.
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Cirrus Design SR20 Section 7 Airplane Description OIL LOW VOLTS FUEL 9 PITOT HEAT ALT 1 ALT 2 Annunciator Panel Primary Flight Display 4 4 5 6 7 8 4. 5. 6. 7. 8. 9. LEGEND Fuel Flow Fuel Used (EMax only) Fuel Remaining (EMax only) Time Remaining (EMax only) Fuel Economy (EMax only) Fuel Caution Light Multifunction Display Serials 1582 & subs.
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Section 7 Airplane Description Cirrus Design SR20 Fuel Flow Indication Serials 1268 through 1581: Fuel flow indication is integral to the combination Fuel Flow/Manifold Pressure Gage. Refer to preceding discussion on Fuel Flow and Manifold Pressure Gage for complete description of fuel flow indication.
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Cirrus Design SR20 Section 7 Airplane Description Boost Pump Switch Boost pump operation and engine prime is controlled through the Fuel Pump BOOST-PRIME switch located adjacent to the fuel selector valve. The PRIME position is momentary and the BOOST position is selectable. A two-speed prime allows the fuel pressure to rapidly achieve proper starting pressure. An oil pressure based system is used to control boost pump operation.
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Section 7 Airplane Description Cirrus Design SR20 Brake System The main wheels have hydraulically operated, single-disc type brakes, individually activated by floor mounted toe pedals at both pilot stations. A parking brake mechanism holds induced hydraulic pressure on the disc brake for parking.
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Cirrus Design SR20 Section 7 Airplane Description Parking Brake • Caution • Do not pull the PARK BRAKE knob in flight. If a landing is made with the parking brake valve set, the brakes will maintain any pressure applied after touchdown. The main wheel brakes are set for parking by using the PARK BRAKE knob on the left side of the console near the pilot’s right ankle. Brake lines from the toe brakes to the main wheel brake calipers are plumbed through a parking brake valve.
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Section 7 Airplane Description Cirrus Design SR20 RESERVOIR MIL-H-5606 FLUID ONLY RUDDER PEDAL(4) MASTER CYLINDER(4) PARKING BRAKE KNOB PARKING BRAKE VALVE CALIPER ASSEMBLY CALIPER ASSEMBLY ROTOR (DISK) ROTOR (DISK) SR20_FM07_1015 7-66 Figure 7-12 Brake System Information Manual March 2010
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Cirrus Design SR20 Section 7 Airplane Description 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 instruments, lighting, and other electrically operated and controlled systems during normal operation.
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Section 7 Airplane Description Cirrus Design SR20 222) below the parachute canister. BAT 2 is charged from the circuit breaker panel Essential Bus. The Master Control Unit (MCU) is located on the left firewall. The MCU controls ALT 1, ALT 2, starter, landing light, external power, and power generation functions.
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Cirrus Design SR20 Section 7 Airplane Description ALT 1 RELAY VOLT REG F ALT 1 B ALT 1 SWITCH LANDING LIGHT 100A EXTERNAL POWER MAIN DIST 15A 125A LANDING LIGHT SWITCH 25A 25A BAT 1 SWITCH BAT 1 25A 25A STARTER F ALT 2 B VOLT REG OIL ALT 1 ALT 2 40A LOW VOLTS PITOT HEAT 50A 50A ESSENTIAL DIST FUEL 25A 25A MASTER CONTROL UNIT BAT 2 30A BAT 2 SWITCH ANNUN/ENGINE INST SKYWATCH/ TAWS GPS 2 FUEL PUMP COM 2 TURN COORD.
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Section 7 Airplane Description Cirrus Design SR20 BAT & ALT Master Switches The rocker type electrical system MASTER switches are ON in the up position and OFF in the down position. The switches, labeled BAT 2, BAT 1, ALT 1, ALT 2 are located in the bolster switch panel immediately below the instrument panel. These switches, along with the AVIONICS power switch, control all electrical power to the airplane. Battery Switches The BAT 1 and BAT 2 switches control the respective battery.
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Cirrus Design SR20 Section 7 Airplane Description Alternator Switches The ALT 1 and ALT 2 switches control field power to the respective alternator. For ALT 1 to start, the BAT 1 switch must be ‘on.’ Setting the ALT 1 switch ’on’ energizes a relay allowing 28 VDC from the ALT 1 circuit breaker (Main Bus 2) to be applied to voltage regulator for ALT 1. For ALT 2 to start, either the BAT 1 switch or the BAT 2 switch must be ‘on.
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Section 7 Airplane Description Cirrus Design SR20 The AMP pointer sweeps a scale from -100 to +100 amps with zero at the 9 o'clock position. The amps indication is derived from current transducers located in the MCU. Output from each alternator and BAT 1 is measured. The panel mounted AMMETER SELECT switch is used to select the desired indication. When the engine is operating and the ALT 1 and ALT 2 Master switches are 'on,' the ammeter indicates the charging rate applied to the batteries.
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Cirrus Design SR20 Section 7 Airplane Description Ammeter Select Switch Serials 1268 through 1581: The AMMETER SELECT switch on the instrument panel is used to select the desired source of electrical current flow to be indicated on the ammeter. The switch has three positions: ALT 1, BATT, and ALT 2. The BATT position indicates BAT 1 current flow only. Selecting one of the switch positions will cause the amperage output from that device to be displayed on the ammeter.
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Section 7 Airplane Description Cirrus Design SR20 Circuit Breakers and Fuses Individual electrical circuits connected to the Main, Essential, and Non-Essential Buses in the airplane are protected by re-settable circuit breakers mounted in the circuit breaker panel on the left side of the center console.
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Cirrus Design SR20 Section 7 Airplane Description distribution buses. Loads on the Non-Essential Equipment Bus are shed by pulling the individual circuit breakers. Ground Service Receptacle A ground service receptacle is located just aft of the cowl on the left side of the airplane. This receptacle is installed to permit the use of an external power source for cold weather starting and maintenance procedures requiring reliable power for an extended period.
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Section 7 Airplane Description Cirrus Design SR20 Exterior Lighting The airplane is equipped with standard wing tip navigation lights with integral anti-collision strobe lights. The separately controlled landing light is located in the lower cowl. Navigation Lights The airplane is equipped with standard wing tip navigation lights. The lights are controlled through the NAV light switch on the instrument panel bolster.
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Cirrus Design SR20 Section 7 Airplane Description Instrument Lights Instrument lighting for the airplane consists of dimmable incandescent lights in the instrument bezels. The lights are controlled through the INST lights control on the instrument panel bolster. Rotating the knob clockwise energizes the lights and increases brightness. The instrument light circuits operate on 28 VDC supplied through the 2amp INST LIGHTS circuit breaker on Main Bus 1.
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Section 7 Airplane Description Cirrus Design SR20 Environmental System Cabin heating and ventilation is accomplished by supplying conditioned air for heating and windshield defrost and fresh air for ventilation. The basic environmental system consists of a heater muff (heat exchanger) around the right engine exhaust muffler, fresh air inlets(s), hot air valve, distribution manifold, air ducting for distribution windshield diffuser, vent outlets, and required actuators for selecting temperature and flow.
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Cirrus Design SR20 Section 7 Airplane Description AIR INLET HEAT EXCHANGER CABIN HEAT/ DEFROST SELECT WINDSHIELD DEFROST DIFFUSER HVAC PLENUM HEAT OFF TEMP.
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Section 7 Airplane Description Cirrus Design SR20 Cabin Air Selector “Conditioned” air from the mixing plenum can be proportioned and directed to the windshield or passengers by manipulating the cabin air selector. The control is linked to a door at the outlet end of the mixing plenum. Rotating the control full counterclockwise to the miniature windshield shuts off airflow to the passenger air distribution system and allows maximum airflow to the windshield diffuser.
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Cirrus Design SR20 Section 7 Airplane Description AIR INLET VENTS HEAT EXCHANGER TEMPERATURE COLD AIRFLOW 1 WINDSHIELD DIFFUSER HOT AIR VALVE 2 HOT OFF PANEL AIRFLOW FLOOR AIRFLOW DISTRIBUTION MANIFOLD AIR GASPER AIR MIXING PLENUM FRESH AIR INTAKE FRESH AIR VALVE FOOT-WARMER DIFFUSER FAN ASSEMBLY NOTE: Illustration depicts maximum cabin cooling airflows and selector settings.
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Section 7 Airplane Description Cirrus Design SR20 Description and Operation-Serials 1637 & subsequent Cabin heating and cooling is provided by mixing ventilation air from the wing inlet with heated air provided by the muff-type heat exchanger surrounding the right engine exhaust muffler.The conditioned air is then forced by ram air pressure or, if option installed, by blower fan into a distribution manifold which regulates system airflow and vent selection.
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Cirrus Design SR20 Section 7 Airplane Description Temperature Selection The temperature selector is mechanically linked to the hot air valve and fresh air intake valve. Rotating the selector simultaneously opens and closes the two valves, permitting hot and cold air to mix and enter the distribution system. Rotating the selector clockwise, permits warmer air to enter the system - counterclockwise, cooler air.
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Section 7 Airplane 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.
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Cirrus Design SR20 Section 7 Airplane Description Serials 1005 thru 1336 ,1337 thru 1422 w/o PFD. Serials 1337 & subs w/ PFD. PRIMARY FLIGHT DISPLAY AIRSPEED INDICATOR VERTICAL SPEED INDICATOR ALTIMETER ALTITUDE ENCODER ALTITUDE TRANSDUCER (OPTIONAL) ALTERNATE STATIC AIR SOURCE PITOT-STATIC WATER TRAPS PITOT MAST STATIC BUTTONS HEATER CURRENT SENSOR PITOT HEAT LOGIC ANNUNCIATOR 7.
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Section 7 Airplane Description Cirrus Design SR20 Alternate Static Source An alternate static pressure source valve is installed on the switch and control panel to the right of the pilot's leg. This valve supplies static pressure from inside the cabin instead of the external static port. If erroneous instrument readings are suspected due to water or ice in the pressure line going to the standard external static pressure source, the alternate static source valve should be turned on.
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Cirrus Design SR20 Section 7 Airplane Description Standard Avionics The following paragraphs and equipment descriptions describe all standard avionic installations offered for the SR20. The avionics navigation and communication equipment are mounted in he center console and are easily accessible from either pilot seat.
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Section 7 Airplane Description Cirrus Design SR20 • Single Navigation (VOR/LOC/GS) Receiver (GNS 430) • Mode C Transponder with Altitude Encoder (Garmin GTX 327) • Horizontal Situation Indicator • Course Deviation Indicator Avionics Configuration 2.
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Cirrus Design SR20 Section 7 Airplane Description • Integrated Audio System with Intercom (Garmin GMA 340) • Marker Beacon Receiver (Garmin GMA 340) • One IFR Certified GPS (Garmin GNC 420) • One VHF Communications (Garmin GNC 420) • Mode C Transponder with Altitude Encoder (Garmin GTX 327) Multi-Function Display This airplane is equipped with an Avidyne FlightMax EX5000C 70000004-XXX-() Multi-Function Flight Display (MFD). The MFD is a 10.4inch landscape-oriented display mounted in the instrument panel.
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Section 7 Airplane Description Cirrus Design SR20 • Select terrain features, such as airports and special use airspace and select color enhanced terrain. • Select and view trip data from GPS. Power for the MCU is 28 VDC supplied through the 5-amp MFD circuit breaker on the Avionics Non-Essential Bus.
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Cirrus Design SR20 Section 7 Airplane Description The S-Tec System Twenty Autopilot features: • Roll Stabilization. • Turn Command. • Heading Hold interfaced with DG coupled heading bug. • NAV/LOC/GPS tracking, HI and LO sensitivity. Avionics Configuration 2.1: These airplanes are equipped with an S-TEC System Thirty Autopilot.
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Section 7 Airplane Description Cirrus Design SR20 supplement for a more complete description of the autopilot, its operating modes, and additional detailed operating procedures. Refer to S-TEC-Meggit Global Positioning System Steering (GPSS) Converter Pilot’s Operating Handbook (P/N 8799) dated 8 Feb 2001 or later and applicable POH supplement for a more complete description of the GPSS converter, its modes, and additional operating procedures. Avionics Configuration 2.
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Cirrus Design SR20 Section 7 Airplane Description Refer to S-Tec Altitude Selector / Alerter Pilot’s Operating Handbook (POH) P/N 8716 or P/N 87110 (no revision or later) for full operational procedures and detailed description of operational modes of the Altitude Selector / Alerter. Avionics Configuration PFD: This airplane is equipped with an S-TEC System 55SR Autopilot. The System 55SR autopilot is a two-axis autopilot system.
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Section 7 Airplane Description Cirrus Design SR20 navigator is powered by 28 VDC through the 5-amp GPS 1 and 7.5amp COM 1 circuit breakers on the Avionics Essential Bus. The secondary GPS navigator is powered by 28 VDC through the 7.5-amp COM 2 circuit breaker on the Avionics Non-Essential Bus. Avionics Configuration 2.1 and 2.2: The airplane is equipped with two GPS navigators. The Garmin GNS 430 is designated GPS 1 and the Garmin GNS 420 (Configuration 2.1) or an additional GNS 430 (Configuration 2.
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Cirrus Design SR20 Section 7 Airplane Description Standard SRV configuration: The airplane is equipped with one GPS navigator. The Garmin GNS 420 navigator is designated GPS 1, and is coupled to the airplane’s Multi-Function display. The GPS navigator is powered by 28 VDC through the 5-amp GPS 1 and 7.5-amp COM 1 circuit breakers on the Avionics Essential Bus. Communication (COM) Transceivers Avionics Configuration 2.0, 2.1, 2.
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Section 7 Airplane Description Cirrus Design SR20 panel and supplied through the 7.5-amp COM 2 circuit breaker on the Non-Essential Avionics Bus. Avionics Configuration SRV: Optional SRV configuration: An optional Garmin GNS 430 GPS transceiver is available as an upgrade to the Garmin GNS 420. The system description is identical to the Garmin GNS 420 described below. One VHF communications (COM) transceiver is installed to provide VHF communication.
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Cirrus Design SR20 Section 7 Airplane Description receivers and integrated controls are mounted in the Garmin GNS 430 control display. The receiver controls provide active and standby frequency indication, frequency memory storage, and knob-operated frequency selection. IDENT audio output for VOR and LOC is provided to the audio system. The Nav antenna, mounted on top of the vertical tail, provides VOR/LOC input for both Nav receivers. NAV 1 – The upper GARMIN GNS 430 is designated NAV 1.
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Section 7 Airplane Description Cirrus Design SR20 Transponder The airplane is equipped with a single Garmin GTX 327 ATC Mode C (identification and altitude) transponder with squawk capability. The transponder system consists of the integrated receiver/transmitter control unit, an antenna, and an altitude encoder. The receiver/ transmitter receives interrogations from a ground-based secondary radar transmitter and then transmits to the interrogating Air Traffic Control Center.
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Cirrus Design SR20 Section 7 Airplane Description headsets is controlled by the individual audio selector switches on the audio control panel and adjusted for volume level by using the selected receiver volume controls. Audio Input Jack Two audio input jacks are provided on the aft portion of the center console. One jack is located near the convenience outlet for use by the pilot and forward passenger, and another is located further aft by the rear passenger ANR power jacks.
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Section 7 Airplane Description Cirrus Design SR20 the maintenance manual procedures. The RESET button can be used to cancel an inadvertent transmission. A 6-volt Lithium battery mounted in the panel powers the LED. The battery must be replaced at regular intervals (refer to Airplane Maintenance Manual). In the event of an accident: 1. Verify ELT operation by noting that the ELT indicator light on the remote panel is flashing. 2.
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Cirrus Design SR20 Section 7 Airplane Description FLIGHT. Recording begins when the airplane reaches a speed of approximately 35 KIAS and is controlled by a differential pressure switch connected to the Pitot-static system. 28 VDC for hour meter operation is supplied through the 5-amp FUEL QTY / HOBBS circuit breaker on Main Bus 1.
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Section 7 Airplane Description Cirrus Design SR20 Flight Time (FT): The flight time (FT) option is not available in this installation. If FT is selected the display will ‘zero.’ Elapsed Time (ET): The ET mode may be used either in ‘count-up’ or in ‘count-down’ modes. To set the count-up mode: 1. Select ET using the Select button; and 2. Press Control to activate count-up timer. Elapsed time counts up to 59 minutes, 59 seconds, and then switches to hours and minutes.
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Cirrus Design SR20 Section 7 Airplane Description Cirrus Airplane Parachute System The SR20 is equipped with a Cirrus Airplane Parachute System (CAPS) designed to bring the aircraft and its occupants to the ground in the event of a life-threatening emergency. The system is intended to saves 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.
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Section 7 Airplane Description Cirrus Design SR20 sequence the slider limits the initial diameter of the parachute and the rate at which the parachute inflates. As the slider moves down the suspension lines the canopy inflates. A three-point harness connects the airplane fuselage structure to the parachute. The aft harness strap is stowed in the parachute canister and attached to the structure at the aft baggage compartment bulkhead.
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Cirrus Design SR20 Section 7 Airplane Description Attempting to activate the rocket by pushing the activation Thandle forward and down limits the force that can be applied. Pulling the activation T-handle straight down generates the greatest force. A maintenance safety pin is provided to ensure that the activation handle is not pulled during maintenance.
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Section 7 Airplane Description Cirrus Design SR20 equal to the velocity of the surface wind. In addition, surface winds may continue to drag the aircraft after ground impact. • Caution • Ground impact is expected to be equivalent to touchdown from a height of approximately 10 feet. While the airframe, seats and landing gear are designed to accommodate this stress, occupants must prepare for it in accordance with the CAPS Deployment procedure in Section 3 - Emergency Procedures.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance Section 8 Handling, Servicing, Maintenance Table of Contents Introduction ..................................................................................... 8-3 Operator’s Publications ...................................................................8-3 Service Publications .................................................................... 8-3 Ordering Publications ..................................................................
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Section 8 Handling, Servicing, Maintenance 8-2 Cirrus Design SR20 Information Manual March 2010
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance Introduction This section provides general guidelines for handling, servicing and maintaining your Cirrus Design SR20. In order to ensure continued safe and efficient operation of your airplane, keep in contact with your Authorized Cirrus Service Center to obtain the latest information pertaining to your aircraft. Operator’s Publications The FAA Approved Airplane Flight Manual and Pilot’s Operating Handbook (POH) is provided at delivery.
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Section 8 Handling, Servicing, Maintenance Cirrus Design SR20 • Service Bulletins – -are of special importance. When you receive a Service Bulletin, comply with it promptly. • 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.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance Airplane Records and Certificates The Federal Aviation Administration (FAA) requires that certain data, certificates, and licenses be displayed or carried aboard the airplane at all times. Additionally, other documents must be made available upon request. The mnemonic acronym “ARROW” is often used to help remember the required documents.
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Section 8 Handling, Servicing, 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.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance last Annual Inspection. For example: If an Annual Inspection were performed on 19 November 1998, the next Annual Inspection will be due 30 November 1999. Annual Inspections must be accomplished regardless of the number of hours flown the previous year and can 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.
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Section 8 Handling, Servicing, 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.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance • Replace any hose connection, except hydraulic connections, with replacement hoses. • Clean or replace fuel and oil strainers, as well as replace or clean filter elements. • Replace prefabricated fuel lines. • 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.
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Section 8 Handling, Servicing, 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.
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Cirrus Design SR20 Section 8 Handling, Servicing, 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.
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Section 8 Handling, Servicing, 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.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance Parking The airplane should be parked to protect the airplane from weather and to prevent it from becoming a hazard to other aircraft. The parking brake may release or exert excessive pressure because of heat buildup after heavy braking or during wide temperature swings. 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.
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Section 8 Handling, Servicing, 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.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance Jacking Two jacking points are provided: one at each wing tiedown. Jack points (pads) are stowed in the baggage compartment. The airplane may be jacked using two standard aircraft hydraulic jacks at the wing jacking points and a weighted tailstand attached to the tail tiedown. 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.
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Section 8 Handling, Servicing, 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.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance The aircraft should not be operated with overheated, damaged, or leaking brakes. Conditions include, but are not limited to: • Leaking brake fluid at the caliper. This can be observed by checking for evidence of fluid on the ground or deposited on the underside of the wheel fairing. Wipe the underside of the fairing with a clean, white cloth and inspect for red colored fluid residue.
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Section 8 Handling, Servicing, Maintenance Cirrus Design SR20 5. Check brake assemblies for evidence of overheating and/or deterioration. 6. Install main gear fairing. (Refer to AMM 32-10) 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.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance Oil Servicing The oil capacity of the Teledyne Continental IO-360-ES engine is 8 quarts. It is recommended that the oil be changed every 50 hours and sooner under unfavorable operating conditions.
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Section 8 Handling, Servicing, Maintenance Cirrus Design SR20 Approved Oils For the first 25 hours of operation (on a new or rebuilt engine) or until oil consumption stabilizes, use only straight mineral oil conforming to Mil-L-6082. If engine oil must be added to the factory installed oil, add only MIL-L-6082 straight mineral oil.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance 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.
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Section 8 Handling, Servicing, Maintenance Cirrus Design SR20 Fuel System Servicing Airplane serials 1005 thru 1886; After the first 25 hours of operation, then every 50-hours or as conditions dictate, the fuel filtration screen in the gascolator must be cleaned. After cleaning, a small amount of grease applied to the gascolator bowl gasket will facilitate reassembly.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance Do not operate radios or electrical equipment during refuel operations. Do not operate any electrical switches. To refuel airplane: 1. Place fire extinguisher near fuel tank being filled. 2. Connect ground wire from refuel nozzle to airplane exhaust, from airplane exhaust to fuel truck or cart, and from fuel truck or cart to a suitable earth ground. 3. Place rubber protective cover over wing around fuel filler.
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Section 8 Handling, Servicing, Maintenance Cirrus Design SR20 Fuel Contamination and Sampling Typically, fuel contamination results from foreign material such as water, dirt, rust, and fungal or bacterial growth. Additionally, chemicals and additives that are incompatible with fuel or fuel system components are also a source of fuel contamination. To assure that the proper grade of fuel is used and that contamination is not present, the fuel must be sampled prior to each flight.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance Draining Fuel System The bulk of the fuel may be drained from the wing fuel tanks by the use of a siphon hose placed in the cell or tank through the filler neck. The remainder of the fuel may be drained by opening the drain valves. Use the same precautions as when refueling airplane. Refer to the SR20 Maintenance Manual for specific procedures. Battery Service Access to the 24 volt Battery 1 is gained by removing the upper cowl.
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Section 8 Handling, Servicing, Maintenance Cirrus Design SR20 Cleaning and Care Cleaning Exterior Surfaces • Note • Prior to cleaning, place the airplane in a shaded area to allow the surfaces to cool. The airplane should be washed with a mild soap and water. Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause corrosion of metal. Cover static ports and other areas where cleaning solution could cause damage.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance Cleaning Product Cleaning Application Supplier Mild Dishwasher Soap (abrasive free) Fuselage Exterior and Landing Gear Any Source 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
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Section 8 Handling, Servicing, Maintenance Cirrus Design SR20 Windscreen and Windows Before cleaning an acrylic window, rinse away all dirt particles before applying cloth or chamois. Never rub dry acrylic. Dull or scratched window coverings may be polished using a special acrylic polishing paste. • Caution • Clean acrylic windows with a solvent free, none abrasive, antistatic acrylic cleaner. Do not use gasoline, alcohol, benzene, carbon tetrachloride, thinner, acetone, or glass window cleaning sprays.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance Engine Compartment Before cleaning the engine compartment, place a strip of tape on the magneto vents to prevent any solvent from entering these units. 1. Place a large pan under the engine to catch waste. 2. Remove induction air filter and seal off induction system inlet. 3. With the engine cowling removed, spray or brush the engine with solvent or a mixture of solvent and degreaser.
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Section 8 Handling, Servicing, Maintenance Cirrus Design SR20 Cleaning Interior Surfaces Seats, carpet, upholstery panels, and headliners should be vacuumed at regular intervals to remove surface dirt and dust. While vacuuming, use a fine bristle nylon brush to help loosen particles. • Caution • Remove any sharp objects from pockets or clothing to avoid damaging interior panels or upholstery. Windshield and Windows Never rub dry acrylic.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance 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 Cirru
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Section 8 Handling, Servicing, Maintenance Cirrus Design SR20 Instrument Panel and Electronic Display Screens The instrument panel, control knobs, and plastic trim need only to be wiped clean with a soft damp cloth.
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Cirrus Design SR20 Section 8 Handling, Servicing, Maintenance 2. Soiled upholstery, may be cleaned with a good upholstery cleaner suitable for the material. Carefully follow the manufacturer's instructions. Avoid soaking or harsh rubbing. Leather Upholstery and Seats For routine maintenance, occasionally wipe leather upholstery with a soft, damp cloth.
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Section 8 Handling, Servicing, Maintenance Cirrus Design SR20 Intentionally Left Blank 8-34 Information Manual March 2010
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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 SR20 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.
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Section 9 Supplements Cirrus Design SR20 Intentionally Left Blank 9-2 Information Manual March 2010
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Cirrus Design SR20 Section 9 Supplements Section 9 Log of Supplements Part Number Title Date ___ 11934-S01 R2 Garmin GMA 340 Audio System 07-18-05 ___ 11934-S05 03-31-99 Garmin GNC 250XL GPS Navigator w/ VHF COM ___ 11934-S06 R1 S-Tec System Twenty Autopilot 12-07-04 ___ 11934-S09 R1 Approved Oxygen Systems 01-07-03 ___ 11934-S11 R1 L-3 Avionics Systems WX500 Stormscope Sensor 07-18-05 ___ 11934-S12 12-26-00 Garmin GTX 327 Transponder ___ 11934-S15 R1 L-3 Avionics Systems SkyWatch Traffic
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Section 9 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.
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Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for Garmin GMA 340 Audio System Includes Optional XM Radio System When the Garmin GMA 340 Audio Panel and the optional XM Radio System are installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook (Handbook).
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Section 9 Supplements Cirrus Design SR20 Section 1 - General This supplement provides detailed operating instructions for the Garmin GMA 340 Audio Selector Panel/Intercom System with internal Marker Beacon. This supplement covers the basic operating areas of the Audio Control Panel.
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Cirrus Design SR20 Section 9 Supplements Section 2 - Limitations Use of auxiliary AUDIO IN entertainment input and the optionally installed XM Radio System is prohibited during takeoff and landing. Section 3 - Emergency Procedures In the event of an audio panel power failure, the audio system will revert to COM 1 for the pilot’s mic and headphones and the pilot will have transmit and receive capability.
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Section 9 Supplements Cirrus Design SR20 A fail-safe circuit connects the pilot’s headset directly to the COM1 transceiver in the event of a power failure to the audio control panel or the panel is switched ‘OFF.’ Test Pressing the TEST button illuminates all Panel LEDs and the Marker Beacon Annunciators full bright. During normal operation, a photocell mounted at the approximate center of the control panel senses ambient light to allow automatic LED and annunciator intensity adjustment.
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Cirrus Design SR20 Section 9 Supplements the copilot mic/audio source. The pilot has receive and transmit capabilities on COM1 and the copilot has receive and transmit capabilities on COM2. While split COM is active, simultaneous transmission from COM1 and COM2 is not possible. The pilot and copilot can still listen to COM3, NAV1, NAV2, DME, ADF, and MKR. Pressing the COM 1/2 button a second time will deactivate the split COM function.
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Section 9 Supplements Cirrus Design SR20 The Audio Control Panel has provisions for up to two separate personal entertainment input (music) devices. These devices are plugged into the AUDIO INPUT jacks in the center console jack panels. Music1 is connected at the AUDIO INPUT jack near the convenience outlet. Music2 is connected to the jack on the aft console. Music1 is soft-muted during all airplane radio activity. Music1 and Music2 have characteristics affected by the active ICS isolation mode.
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Cirrus Design SR20 Section 9 Supplements • Right Outer Knob – Copilot and passenger mic VOX level. CW rotation increases the amount of mic audio (VOX level) required to break squelch. Full CCW is the ‘hot mic’ position. Each microphone input has a dedicated VOX circuit to assure that only the active microphone(s) is/are heard when squelch is broken. After the operator has stopped talking, the intercom channel remains momentarily open to avoid closure between words or normal pauses.
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Section 9 Supplements Cirrus Design SR20 button. ALL mode is active when neither PILOT or CREW have been selected. PILOT The pilot is isolated from the intercom. The pilot can hear radio and sidetone only during radio transmissions. Copilot and passengers can hear the intercom and music but not the airplane radio receptions or pilot transmissions. CREW Pilot and copilot are connected on one intercom channel and have exclusive access to the aircraft radios. They may also listen to Music1.
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Cirrus Design SR20 Section 9 Supplements Marker beacon audio is selected by pressing the MKR push-button. If no marker beacon signal is being received, pressing the MKR pushbutton a second time deselects marker beacon audio. However, if marker beacon is being received, pressing the MKR push-button a second time will mute the audio but the light will continue to flash. Pressing the MKR push-button a third time (while marker beacon audio is muted) deselects marker beacon audio.
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Section 9 Supplements Cirrus Design SR20 XM Radio System (Optional Installation) • Note • For a detailed operating instructions, refer to the XM Radio Wireless Controller User Instructions, Document No. XMC050-4, original release or later. MFD software partnumber 530-00162-000 or later is required for installation of XM Radio System. Subscription to a XM Radio System Service Package is required for operation. Contact XM Satellite Radio at 800.985.9200 for subscription information.
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Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for Garmin GTX 327 Transponder When a Garmin GTX 327 Transponder is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
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Section 9 Supplements Cirrus Design SR20 Section 1 - General The airplane is equipped with a single Garmin GTX 327 ATC Mode A/ C (identification and altitude) transponder with squawk capability. This supplement provides complete operating instructions for the GTX 327 and does not require any additional data be carried in the airplane. 1 2 3 10 9 1. Identification Key 2. Mode Selector Keys a. OFF b. STBY (Standby) c. ON d. ALT 3. Display Window 4. FUNC (Function) Key 4 8 7 5 6 5.
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Cirrus Design SR20 Section 9 Supplements Section 2 - Limitations No Change Section 3 - Emergency Procedures No Change Section 4 - Normal Procedures • Note • Expected coverage from the GTX 327 is limited to “line of sight.” Low altitude or aircraft antenna shielding by the airplane itself may result in reduced range. Range can be improved by climbing to a higher altitude. After Engine Start 1. Avionics Power Switch ...............................................................
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Section 9 Supplements Cirrus Design SR20 Section 5 - Performance No Change Section 6 - Weight & Balance No Change Section 7 - Systems Description • Note • This supplement provides specific procedures for use of the GTX 327 Transponder in the SR20 and a general description of the unit. For a detailed description of the GTX 327, refer to GARMIN GTX 327 Mode A/C Transponder Pilots Guide, p/n 190-00187-00 Revision A (Feb 2000) or later revision.
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Cirrus Design SR20 Section 9 Supplements Mode Selector Keys The mode selector keys are located in a circular arrangement immediately to the left of the display window. The selected mode is annunciated at the left side of the display immediately adjacent to the selector keys. The five positions are: OFF - Turns off all power to the GTX 327 transponder. The transponder should be off until the engine is started.
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Section 9 Supplements Cirrus Design SR20 Code Selector Keys Code selection is accomplished by depressing the eight selector keys (numbered 0 - 7) located immediately below the display. Any of 4096 active identification codes can be selected. The selected code must be in accordance with instructions for IFR flight or rules applicable to transponder utilization for VFR flight. The airplane’s transponder code is used to enhance tracking capability by ATC.
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Cirrus Design SR20 Section 9 Supplements Reply Light The reply light is the small reverse video “R” immediately below the mode annunciation in the display window. The reply light will blink each time the transponder replies to ground interrogations. The light will remain on during the 18-second IDENT time interval.
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Section 9 Supplements Cirrus Design SR20 COUNT DOWN TIMER - The count down timer is controlled by the START / STOP key. The CRSR and “0 - 9” keys are used to set the initial time. Pressing the CLR key resets the timer to the initial value. CONTRAST - Allows adjustment of display contrast. When CONTRAST is selected, pressing the “8” key reduces contrast and pressing “9” increases contrast. DISPLAY - The display function is not available in this installation.
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Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement For S-Tec System 55X Autopilot w/ Altitude Selector/Alerter When the S-Tec System Fifty Five X (55X) Autopilot with Altitude Selector/Alerter is installed in the Cirrus Design SR20, serials 1268 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
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Section 9 Supplements Cirrus Design SR20 Section 1 - General This airplane is equipped with an S-TEC System 55X Autopilot. The System 55X autopilot is a two-axis autopilot system. The system consists of a flight guidance programmer/computer, altitude encoder, altitude selector / alerter, turn coordinator, and HSI. Mode selection and vertical speed selection is made on the programmer/computer panel. A button on each control yoke handle may be used to disengage the autopilot.
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Cirrus Design SR20 Section 9 Supplements this installation does not utilize a CWS (Control Wheel Steering) switch or an AUTOPILOT MASTER switch. • Note • This installation utilizes the airplane’s roll trim actuator to affect steering changes. Therefore, the automatic trim function of the System 55X is not implemented. Disregard all references in the S-Tec System 55X POH to this feature. Roll information is displayed on the HSI. Autopilot Flight Director is not implemented in this installation.
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Section 9 Supplements Cirrus Design SR20 b. The autopilot must be disconnect during approach if course deviation exceeds 50%. The approach should only be continued by “hand-flying” the airplane. c. The autopilot must be disengaged at the Decision Height. d. 12 knot maximum crosswind component between the missed approach point and outer marker. e. The intercept of the localizer shall occur at least 5 miles outside of the outer marker. f.
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Cirrus Design SR20 Section 9 Supplements SR20_FM09_1502A Figure - 1 System 55X Altitude Selector/Alerter & Autopilot Computer P/N 11934-S20 Revision 04: 08-15-07 5 of 24
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Section 9 Supplements Cirrus Design SR20 Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the SR20 POH. Do not reengage the autopilot until the malfunction has been identified and corrected. The autopilot may be disconnected by: 1. Pressing the A/P DISC/Trim switch on the control yoke handle. 2. Pulling the AUTOPILOT circuit breaker on Essential Bus.
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Cirrus Design SR20 Section 9 Supplements System Failure and Caution Annunciations If any of the following failure annunciations occur at low altitude or during an actual instrument approach, disengage the autopilot, execute a go-around or missed approach as appropriate. Inform ATC of problem. Do not try to troubleshoot until a safe altitude and maneuvering area are reached or a safe landing is completed. Annunciation Condition Action Flashing RDY for 5 seconds with audible tone. Autopilot disconnect.
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Section 9 Supplements Cirrus Design SR20 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot and altitude selector and their respective modes. The Autopilot is integrated with the Altitude Selector/Alerter and can be operated with or without data inputs from the Altitude Selector/ Alerter.
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Cirrus Design SR20 c. Section 9 Supplements Rotate altitude selector input knob to set BARO to the nearest 0.1 inch Hg. d. Push ALT button to display ALT SEL. With a flashing SEL annunciator, rotate the selector knob to input an altitude 300 to 400 feet lower or higher than the indicated altitude. e. Push the VS button. Rotate the selector input knob to input the desired climb (+) or descent (-) vertical speed. f. Push ALT button, ALT SEL annunciator will illuminate. g. Engage autopilot HDG mode. h.
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Section 9 Supplements c. Cirrus Design SR20 Altitude Hold ....................................................................TEST 1.) Depress ALT button on autopilot programmer/computer. Note that ALT annunciator comes on, VS annunciator goes out, and yoke does not move. d. Overpower Test: 1.) Grasp control yoke and input left aileron, right aileron, nose up, and nose down to overpower autopilot. Overpower action should be smooth in each direction with no noise or jerky feel. e. Radio Check: 1.
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Cirrus Design SR20 Section 9 Supplements 3. Use HSI HDG bug to make heading changes as desired. Autopilot Altitude Hold Mode 1. Manually fly the airplane to the desired altitude and level off. • Note • For smoothest transition to altitude hold, the airplane rate of climb or descent should be less than 100 FPM when Altitude Hold is selected. 2. Press HDG or NAV to engage a roll mode. The associated annunciator will illuminate. • Note • A roll mode must be engaged prior to engaging a pitch mode. 3.
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Section 9 Supplements Cirrus Design SR20 3. Press the VS button on the autopilot programmer/computer to engage the vertical speed mode. When the mode is engaged, the autopilot will synchronize to and hold the vertical speed at the time the mode was engaged. • Note • The vertical speed is displayed in 100-foot increments at the far right of the programmer/computer window next to the VS annunciation. A plus (+) value indicates climb and a negative or minus (-) value indicates descent. 4.
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Cirrus Design SR20 Section 9 Supplements 4. Press DTA again to accept altitude entry, the ENT annunciator will go out and the SEL annunciator will stop flashing and illuminate steady indicating that the system is in the ‘operate’ mode. • Note • When the system is in the ‘operate’ mode, pressing the ALT button will cause the system to extinguish the SEL annunciator and display the baro corrected encoded altitude.
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Section 9 Supplements Cirrus Design SR20 BARO Selection Upon initial start-up, the altitude selector enters BARO select immediately after the self-test if it is receiving a valid altitude signal. The setting can easily be entered at this time. At other times, it is necessary to select the DTA entry and BARO modes in order to adjust the BARO setting. After initial start-up, the Baro setting can be changed at any time using the following procedure: 1.
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Cirrus Design SR20 Section 9 Supplements is set. As the airplane approaches within approximately 50 feet of the decision height, the alert will sound and the DH light will flash. As the airplane passes through approximately 50 feet beyond the decision height, the alert will sound and the light will flash again. • Note • Pressing the DH button again will disable the DH function causing the DH annunciation to go out. Repeated activation of the DH button alternately activates and deactivates the DH mode.
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Section 9 Supplements Cirrus Design SR20 intercept course in NAV mode or twice to intercept course in GPSS mode on the autopilot programmer/computer. When the on-course intercept turn begins the HDG mode will disengage and the annunciator will go out. During the intercept sequence, the autopilot operates at maximum gain and sensitivity (90% of standard rate turn). When the selected course is intercepted, course deviation needle centered, the course-tracking program is activated.
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Cirrus Design SR20 Section 9 Supplements Glideslope Intercept and Tracking 1. Begin with a reliable ILS signal selected on the NAV receiver. 2. Select autopilot NAV and APR. Airplane must be within 50% needle deviation of localizer centerline. 3. Select ALT mode. Airplane must be 60% or more below the glideslope centerline during the approach to the intercept point.
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Section 9 Supplements Cirrus Design SR20 steering is accomplished by autopilot steering commands to the aileron trim motor and spring cartridge. The pitch computer receives altitude data from the altitude encoder pressure transducer plumbed into the static system, an accelerometer, and glideslope information from the HSI and #1 NAV radio. Pitch axis command for altitude hold, vertical speed hold, and glideslope tracking is accomplished by pitch computer commands to the elevator trim motor.
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Cirrus Design SR20 Section 9 Supplements HDG (Heading) Mode – When HDG is selected, the autopilot will engage the HDG mode, fly the airplane to, and hold the heading set on the HSI. Subsequent heading changes are made using the HDG knob on the HSI. For smoothest transition to HDG mode, it is recommended that the airplane be aligned to within 10° of the selected heading before engaging HDG. The HDG mode is also used in combination with the NAV mode to set up a pilot selected intercept angle to a course.
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Section 9 Supplements Cirrus Design SR20 GS (Glideslope) – The autopilot GS function will capture and track an ILS glideslope.
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Cirrus Design SR20 Section 9 Supplements Altitude Selector / Alerter The altitude selector / alerter provides the autopilot with an altitude preselect function, a programmable vertical speed function, as well as provides altitude alert, decision height alert, and baro corrected altitude display. The altitude selector reads and decodes altitude information from the same altitude encoder that provides altitude information to the transponder.
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Section 9 Supplements Cirrus Design SR20 DTA (Data) – The data entry button is used to select data entry mode. The first time the DTA button is pressed the selector will enter the data entry mode, the ENT annunciator will come on, and the SEL annunciator will flash to indicate the system is ready to accept an altitude entry.
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Cirrus Design SR20 Section 9 Supplements ALT (Altitude) – The ALT button has two functions: Altitude Pre-select and Altitude readout. Pre-select - When the ALT button is pressed while the system is in the Data Entry (DTA) mode the SEL annunciator will flash and a new altitude can be selected by rotating the input knob CW to increase altitude and CCW to decrease altitude in thousands of feet. Pull the knob to input altitude in hundreds of feet. For example: 5500 feet is input as 5.5.
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Section 9 Supplements Cirrus Design SR20 DH (Decision Height) – The DH button allows entry and arming of altitude alerting at a set decision height. To set a DH, first enter the data (DTA) entry (ENT) mode, press the DH button, and rotate the selector knob to input the desired decision height to the nearest 100 feet above the specified decision height. For example, for a DH of 1160 feet set 1.2 (1200 feet). After setting the desired decision height, press the DTA button again to accept the entered DH.
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Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement For S-Tec System 55SR Autopilot When the S-Tec System Fifty Five SR (55SR) Autopilot is installed in the Cirrus Design SR20, serials 1337 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
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Section 9 Supplements Cirrus Design SR20 Section 1 - General This airplane is equipped with an S-TEC System 55SR Autopilot. The System 55SR autopilot is a two-axis autopilot system. The system consists of a flight guidance programmer/computer, altitude transducer, turn coordinator, and primary flight display (PFD). Mode selection is made on the programmer/computer panel. A button on each control yoke handle may be used to disengage the autopilot.
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Cirrus Design SR20 Section 9 Supplements Section 2 - Limitations 1. Autopilot operation is prohibited above 180 KIAS. 2. The autopilot must not be engaged for takeoff or landing. 3. The autopilot must be disengaged for missed approach, goaround, and balked landing. 4. Flaps must be set to 50% for autopilot operation in Altitude Hold at airspeeds below 95 KIAS. 5. Flap deflection is limited to 50% during autopilot operations. 6. The autopilot must be disconnected in moderate or severe turbulence. 7.
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Section 9 Supplements i. Cirrus Design SR20 The flaps should be extended in the approach configuration prior to the Outer Marker. No further changes in the flap configuration should be made throughout the autopilotcoupled approach. 10. The S-Tec System 55SR Autopilot Pilot’s Operating Handbook (POH), P/N 87127 dated 01 September 2003 or later, must be carried in the airplane and available to the pilot while in flight.
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Cirrus Design SR20 Section 9 Supplements FIFTY FIVE SR S-TEC HDG R D Y NAV C W S APR F A G I L P S REV TRIM ALT GS S VS + APR REV ALT VS IN C R NAV DECR VS x 100 HDG SR20_FM09_1996 P/N 11934-S27 Revision 02: 07-18-05 Figure - 1 System Fifty-Five SR Autopilot 5 of 16
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Section 9 Supplements Cirrus Design SR20 Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the SR20 POH. Do not reengage the autopilot until the malfunction has been identified and corrected. The autopilot may be disconnected by: 1. Pressing the A/P DISC/Trim switch on the control yoke handle. 2. Pulling the AUTOPILOT circuit breaker on Essential Bus.
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Cirrus Design SR20 Section 9 Supplements System Failure and Caution Annunciations If any of the following failure annunciations occur at low altitude or during an actual instrument approach, disengage the autopilot, execute a go-around or missed approach as appropriate. Inform ATC of problem. Do not try to troubleshoot until a safe altitude and maneuvering area are reached or a safe landing is completed. Annunciation Condition Action Flashing RDY for 5 seconds with audible tone. Autopilot disconnect.
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Section 9 Supplements Cirrus Design SR20 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot modes. • WARNING • The pilot must properly monitor and control the engine power to avoid stalling the airplane in autopilot altitude hold or vertical speed modes. Autopilot Pre-Flight Test 1. Battery 1 Master Switch ............................................................ ON 2. Transponder ...................................................................
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Cirrus Design SR20 Section 9 Supplements e. Altitude Hold .................................................................... TEST 1.) Depress ALT button on autopilot programmer/computer. Note that ALT annunciator comes on, VS annunciator goes out, and yoke does not move. f. Overpower Test: 1.) Grasp control yoke and input left aileron, right aileron, nose up, and nose down to overpower autopilot. Overpower action should be smooth in each direction with no noise or jerky feel. g. Radio Check: 1.
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Section 9 Supplements Cirrus Design SR20 3. Use the HDG bug to make heading changes as desired. Autopilot Altitude Hold Mode 1. Manually fly the airplane to the desired altitude and level off. • Note • For smoothest transition to altitude hold, the airplane rate of climb or descent should be less than 100 FPM when Altitude Hold is selected. 2. Press HDG or NAV to engage a roll mode. The associated annunciator will illuminate. • Note • A roll mode must be engaged prior to engaging a pitch mode. 3.
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Cirrus Design SR20 Section 9 Supplements Autopilot Vertical Speed Mode 1. Begin by manually establishing the desired vertical speed. 2. Press HDG or NAV to engage a roll mode. The associated annunciator will illuminate. • Note • A roll mode must be engaged prior to engaging a pitch mode. 3. Press the VS button on the autopilot programmer/computer to engage the vertical speed mode. When the mode is engaged, the autopilot will synchronize to and hold the vertical speed at the time the mode was engaged.
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Section 9 Supplements Cirrus Design SR20 • Note • If the course needle is at full-scale deviation, the autopilot will establish the airplane on a heading for a 45° intercept with the selected course. As the airplane approaches the course, the autopilot will smoothly shallow the intercept angle.
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Cirrus Design SR20 Section 9 Supplements • Note • If the HDG bug is within 5° of center and the course deviation is less than 10%, the autopilot will immediately establish the lowest level of sensitivity and limit the turn rate to a maximum of 25% of a standard rate turn. 5. For increased sensitivity during approach or if desired for enroute tracking, press the APR button on the autopilot programmer/ computer. Both NAV and APR annunciators will be illuminated.
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Section 9 Supplements Cirrus Design SR20 All Autopilot mode selection is performed by using the mode select buttons and VS knob on the autopilot programmer/computer in the center console. Annunciators in the programmer/computer display window annunciate modes. Refer to Figure 1 for an illustration of the programmer/computer. RDY (Ready)– Illuminates when autopilot is ready for engagement.
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Cirrus Design SR20 Section 9 Supplements APR (Approach) – When APR is selected, the autopilot provides increased sensitivity for VOR or GPS approaches. APR may also be used to provide increased sensitivity for enroute course tracking. ALT (Altitude Hold), Mode – When ALT is selected, the autopilot will hold the altitude at the time the mode was selected. Altitude hold will not engage if an autopilot roll mode is not engaged.
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Section 9 Supplements Cirrus Design SR20 Intentionally Left Blank 16 of 16 P/N 11934-S27 Revision 02: 07-18-05
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Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for Honeywell KGP 560 Terrain/ Awareness Warning System When the Honeywell KGP 560 Terrain Awareness and Warning System is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
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Section 9 Supplements Cirrus Design SR20 Section 1 - General The airplane is equipped with an Honeywell KGP 560 Terrain Awareness and Warning System that performs the functions of a Class C Terrain Awareness and Warning System (TAWS) in accordance with TSO C151b. Incorporating much of the technology found in TAWS for air transport aircraft, the KPG 560 supports: • Alerting for premature descent. • Alerting for excessive rate of climb/descent.
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Cirrus Design SR20 Section 9 Supplements Section 2 - Limitations 1. Do not use the Terrain Awareness Display for navigation of the aircraft. The KGP 560 Terrain Awareness and Warning System is intended to serve as a situational awareness tool only and may not provide the accuracy fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions. Section 3 - Emergency Procedures Off-Airport Landings 1.
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Section 9 Supplements Cirrus Design SR20 Activate TAWS • Note • If the aircraft horizontal position derived from the Garmin Navigator (GPS 1) is invalid, TAWS will be inoperative and the TERR INOP annunciator will illuminate. 1. SKYWATCH/TAWS Circuit Breaker............................................. IN 2. MFD Circuit Breaker.................................................................... IN 3. Battery Master Switch ............................................................... ON 4.
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Cirrus Design SR20 Section 9 Supplements Response To Awareness Alerts Aural “TERRAIN AHEAD” Alert Aural “OBSTACLE AHEAD” Alert Amber TERR CAUT Annunciation 1. Take positive corrective action until the alert ceases. Stop descending, or initiate a climb turn as necessary, based on analysis of all available instruments and information. Aural “TERRAIN AHEAD; PULL UP” Alert Aural “OBSTACLE AHEAD; PULL UP” Alert Red TERR WARN Annunciation 1. Level the wings, simultaneously adding full power. 2.
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Section 9 Supplements Cirrus Design SR20 Section 7 - Systems Description The Honeywell KGP 560 Terrain Awareness and Warning System compares GPS information from the Garmin Navigator (GPS 1) to the integrated Terrain/Obstacle Database to produce a real-time model of the surrounding terrain. This “virtual” picture is then sent to the MFD to provide enhanced situational awareness to the pilot.
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Cirrus Design SR20 Section 9 Supplements GNS-430 GPS TAWS Annunciator Panel GMA 340 Audio Panel Avidyne PFD KGP 560 Processor Transponder Avidyne MFD TAWS 5 AVIONICS NON-ESSENTIAL BUS Configuration Module SR20_FM09_2031 Figure - 1 Honeywell KGP 560 TAWS Simplified Schematic P/N 11934-S30 Revision 01: 12-15-07 7 of 12
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Section 9 Supplements Cirrus Design SR20 TAWS Annunciator Panel TAWS terrain annunciations and control functions are incorporated into the Annunciator Panel. The panel consists of a momentary pushbutton switch (SELF TEST), an illuminated pushbutton switch (TERR INHIBIT), and three LEDS for Terrain Warning (TERR WARN), Terrain Caution (TERR CAUT), Terrain Inoperative (TERR INOP). • SELF TEST - Provides test function for the TAWS.
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Cirrus Design SR20 Section 9 Supplements TAWS SELF TEST TERR INHIBIT TERR INOP TERR CAUT TERR WARN SR20_FM09_2033 Annunciator Color SELF TEST N/A Provides test function for TAWS TERR INHIBIT AMBER All TAWS alerting functions inhibited TERR INOP AMBER Indicates TAWS inoperative TERR CAUT AMBER Possible terrain or obstacle conflict within 40-60 seconds TERR WARN RED Possible terrain or obstacle conflict within 30 seconds P/N 11934-S30 Revision 01: 12-15-07 Function Figure - 2 TAWS
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Section 9 Supplements Cirrus Design SR20 MFD Terrain Awareness Display • WARNING • Do not use the Terrain Awareness Display for navigation of the aircraft. The TAWS is intended to serve as a situational awareness tool only and may not provide the accuracy fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions. To select the Terrain Awareness Display Page on the MFD, rotate the page knob to TAWS. Terrain and obstacle alerts are the most critical situations displayed by TAWS.
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Cirrus Design SR20 Section 9 Supplements Geometric Altitude versus Measured Sea Level An indication of MSL-G or Geometric Altitude may appear on the left side of the MFD indicating the height above Measured Sea Level (MSL) calculated from the GPS. This data serves as the reference for color-coding for the Terrain Awareness Display Page and as an input to the TAWS Look-Ahead algorithm. Because it is derived from GPS, Geometric Altitude may differ from corrected barometric altitude.
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Section 9 Supplements Cirrus Design SR20 Self Test Proper operation of the TAWS can be verified when the aircraft is on the ground as follows: 1. Select the TAWS page on the MFD 2. Clear all caution messages in the lower right corner 3. Ensure that the TERR INHIBIT switch is not engaged, and momentarily push the SELF TEST switch: a. The amber TERR INOP light should be illuminated. b. The amber TERR INOP light should extinguish. c. The red TERR WARN light should be illuminated. d.
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Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for Avidyne EMax™ Engine Instrumentation When the Avidyne EMax™ Engine Instrumentation system is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
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Section 9 Supplements Cirrus Design SR20 Section 1 - General EMax™ Engine Instrumentation provides the pilot with engine parameters depicted on simulated gauges and electrical system parameters located in a dedicated region within in the EX5000C MFD display.
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Cirrus Design SR20 Section 9 Supplements Section 2 - Limitations No Change. Section 3 - Emergency Procedures No Change. Section 4 - Normal Procedures No Change. Section 5 - Performance No Change. Section 6 - Weight & Balance Installation of the Avidyne Engine Instruments adds the following optional (Sym = O) equipment at the weight and arm shown in the following table. ATA / Item Description Sym Qty Part Number Unit Wt Arm 34-03 Engine Sensors O 11 - 1.0 75.
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Section 9 Supplements providing full-time parameters. Cirrus Design SR20 recording of critical engine performance The Engine Instruments system is powered by 28 VDC supplied through the 5-amp Engine Instruments breaker on the Main Bus 1. Refer to Avidyne FlightMax EX5000C Pilot’s Guide for a more complete description of EMax Engine Instruments, its operating modes, and additional detailed operating procedures.
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Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for Avidyne CMax™ Electronic Approach Charts When the Avidyne CMax™ Electronic Approach Charts system is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
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Section 9 Supplements Cirrus Design SR20 Section 1 - General Avidyne CMax™ Electronic Approach Charts allows the pilot to view terminal procedure chart data on the EX5000C MFD. If the chart is geo-referenced, an ownship symbol and flight plan legs can be overlaid on the chart to further enhance the pilot’s situational awareness. Most approach charts and airport diagrams are georeferenced; most arrival, departure, and miscellaneous charts are not.
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Cirrus Design SR20 Section 9 Supplements Section 2 - Limitations 1. Do not use the CMax Approach Charts function for navigation of the aircraft. The CMax Approach Charts function is intended to serve as a situational awareness tool only. 2. The Avidyne FlightMax EX5000C Pilot’s Guide, P/N 600-00108000, Revision 03 or later, must be available to the pilot during all flight operations.
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Section 9 Supplements Cirrus Design SR20 Refer to Avidyne FlightMax EX5000C Pilot’s Guide, for a more complete description of CMax Approach Charts, its operating modes, and additional detailed operating procedures.
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Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for XM Satellite Weather System When the XM Satellite Weather System system is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
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Section 9 Supplements Cirrus Design SR20 Section 1 - General The XM Satellite Weather System enhances situational awareness by providing the pilot with real time, graphical weather information depicted on the MAP page of the EX5000C MFD display.
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Cirrus Design SR20 Section 9 Supplements Section 2 - Limitations 1. Do not use the XM Satellite Weather System for navigation of the aircraft. The XM Satellite Weather System is intended to serve as a situational awareness tool only. Section 3 - Emergency Procedures No Change. Section 4 - Normal Procedures No Change. Section 5 - Performance No Change.
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Section 9 Supplements Cirrus Design SR20 • METARs • SIGMETs • AIRMETs • TFRs • Lightning Strikes The XM Satellite Weather System is powered by 28 VDC supplied through the 3-amp Weather/Stormscope breaker on the Non-Essential Bus. Refer to Avidyne FlightMax EX5000C Pilot’s Guide for a more complete description of XM Satellite Weather System, its operating modes, and additional detailed operating procedures.
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Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for Avidyne Flight Director When the Avidyne Flight Director is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
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Section 9 Supplements Cirrus Design SR20 Section 1 - General The Flight Director system enhances situational awareness by reducing cockpit workload through providing a visual cue for the pilot to follow as indicated by the PFD’s Flight Director Steering Command Bar. Through turning or pitching the airplane as “directed” by the Steering Command Bar, the pilot will follow the necessary course to arrive at a programmed destination.
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Cirrus Design SR20 Section 9 Supplements Section 2 - Limitations 1. The Flight Director System integrates with the Primary Flight Display (PFD) System. Adherence to the PFD imitations in the basic SR20 Pilot’s Operating Handbook is mandatory. 2. The Avidyne FlightMax Entegra-Series PFD Pilot’s Guide, P/N 600-00142-000, Revision 03, or latest revision, must be available to the pilot during all flight operations. Section 3 - Emergency Procedures No Change. Section 4 - Normal Procedures No Change.
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Section 9 Supplements Cirrus Design SR20 the pilot is expected to actuate the flight controls as required to track the bars. The following describes push-button annunciation and related Autopilot and Flight Director status: No Annunciation • Autopilot off. or • Autopilot not active in either roll or pitch control. Green AP ON Annunciation • Autopilot active in roll and/or pitch control.
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Cirrus Design SR20 Section 9 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for SR20 Airplanes Equipped with the “G3 Wing” When the G3 Wing is installed on the Cirrus Design SR20 Serials 1878, 1886 and subsequent, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
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Cirrus Design SR20 Section 9 Supplements Section 1 - General The G3 Wing is constructed in a conventional spar, rib, and shear section arrangement. The upper and lower skins are bonded to the spar, ribs, and aft shear web forming a torsion box that carries all of the wing bending and torsion loads. The rear shear webs are similar in construction but do not carry through the fuselage. The main spar is laminated epoxy/carbon fiber in a C-section, and is continuous from wing tip to wing tip.
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Section 9 Supplements 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.
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Cirrus Design SR20 Section 9 Supplements 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.
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Section 9 Supplements Cirrus Design SR20 The Airplane Fuel Total Capacity .............................................58.5 U.S. Gallons (221.0 L) Total Usable ................................................56.0 U.S. Gallons (212.
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Cirrus Design SR20 Section 9 Supplements Section 2 - Limitations 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 VNE 200 204 Never Exceed Speed is the speed limit that may not be exceeded at any time.
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Section 9 Supplements Cirrus Design SR20 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) Remarks White Arc 61 - 104 Full Flap Operating Range. Lower limit is the most adverse stall speed in the landing configuration.
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Cirrus Design SR20 Section 9 Supplements Center of Gravity Limits Reference Datum ....................................100 inches forward of firewall Forward ...................................................................... Refer to Figure 3 Aft ............................................................................... Refer to Figure 3 3100 3050 3000 FS 140.7 3050 lb FS 148.1 3050 lb Weight - Pounds 2950 2900 2850 2800 FS 139.
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Section 9 Supplements Cirrus Design SR20 Flight Load Factor Limits Flaps UP (0%), 3050 lb.......................................................+3.8g, -1.9g Flaps 50%, 3050 lb. ...............................................................+1.9g, -0g Flaps 100% (Down), 3050 lb. ................................................+1.9g, -0g Fuel Limits The maximum allowable fuel imbalance is 7.5 U.S. gallons (¼ tank). Approved Fuel ...............
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Cirrus Design SR20 Section 9 Supplements Placards 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.
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Cirrus Design SR20 Section 9 Supplements Section 3 - Emergency Procedures Airspeeds for Emergency Operations Maneuvering Speed: 3050 lb ............................................................................. 130 KIAS 2600 lb ............................................................................. 120 KIAS 2200 lb ............................................................................. 110 KIAS Best Glide: 3050 lb .............................................................................
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Section 9 Supplements Cirrus Design SR20 Maximum Glide Conditions Example: Power Propeller Flaps Wind OFF Windmilling 0% (UP) Zero Altitude Airspeed 8,000 ft. AGL Best Glide Glide Distance 12.
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Cirrus Design SR20 Section 9 Supplements 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.................................................................
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Section 9 Supplements Cirrus Design SR20 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 ............................................................
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Cirrus Design SR20 Section 9 Supplements • 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 .......................................................PARTIALLY OPEN Airspeed may need to be reduced to partially open door in flight. 4. Avionics Power Switch .....................................................
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Cirrus Design SR20 Section 9 Supplements Section 4 - Normal Procedures 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. However, to achieve the performance specified in Section 5 for takeoff and landing distance, the speed appropriate to the particular weight must be used. Takeoff Rotation: • Normal, Flaps 50%........................................................ 66 KIAS • Short Field, Flaps 50%..
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Cirrus Design SR20 Section 9 Supplements Section 5 - Performance Airspeed Calibration Normal Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Note • • Indicated airspeed values assume zero instrument error.
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Section 9 Supplements Cirrus Design SR20 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.
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Cirrus Design SR20 Section 9 Supplements 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. Flaps CORRECTION TO BE ADDED - FEET Press Alt Normal Static Source - KIAS 60 70 80 90 100 120 140 160 180 200 S.
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Section 9 Supplements Cirrus Design SR20 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.
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Cirrus Design SR20 Section 9 Supplements Stall Speeds Conditions: • • • • Weight ........................................................................................................ 3050 LB C.G................................................................................................................. Noted Power ................................................................................................................. Idle Bank Angle.........................................................
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Section 9 Supplements Cirrus Design SR20 Wind Components Conditions: Example: • Runway Heading .......................... 10° • Wind Direction .............................. 60° • Wind Velocity ....................... 15 Knots Wind/Flight Path Angle .................50° Crosswind Component......... 12 Knots Headwind Component ......... 10 Knots • Note • • The maximum demonstrated crosswind is 20 knots. Value not considered limiting.
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Cirrus Design SR20 Section 9 Supplements Takeoff Distance Conditions: • Winds ............................................................................................................... Zero • Runway ........................................................................................ Dry, Level, Paved • Flaps. ................................................................................................................50% • Power ..................................................................
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Section 9 Supplements Cirrus Design SR20 Takeoff Distance 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.
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Cirrus Design SR20 Section 9 Supplements Takeoff Distance 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.
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Section 9 Supplements Cirrus Design SR20 Takeoff Climb Gradient Conditions: • • • • Power.................................................................................................... Full Throttle Mixture....................................................................................................... Full Rich Flaps................................................................................................................. 50% Airspeed ....................................................
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Cirrus Design SR20 Section 9 Supplements Takeoff Rate of Climb Conditions: • • • • Power ....................................................................................................Full Throttle Mixture .......................................................................................................Full Rich Flaps .................................................................................................................50% Airspeed .....................................................
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Section 9 Supplements Cirrus Design SR20 Enroute Climb Gradient Conditions: • • • • Power.................................................................................................... Full Throttle Mixture....................................................................................................... Full Rich Flaps...........................................................................................................0% (UP) Airspeed .......................................................
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Cirrus Design SR20 Section 9 Supplements Enroute Rate of Climb Conditions: • • • • Power ....................................................................................................Full Throttle Mixture .......................................................................................................Full Rich Flaps .......................................................................................................... 0% (UP) Airspeed .......................................................
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Section 9 Supplements Cirrus Design SR20 Time, Fuel and Distance to Climb Conditions: • • • • • • Power.................................................................................................... Full Throttle Mixture....................................................................................................... Full Rich Fuel Density...........................................................................................6.0 LB/GAL Weight .................................................
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Cirrus Design SR20 Section 9 Supplements Balked Landing Climb Gradient Conditions: • • • • Power ....................................................................................................Full Throttle Mixture .......................................................................................................Full Rich Flaps ...................................................................................................... 100% (DN) Airspeed .................................................
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Section 9 Supplements Cirrus Design SR20 Balked Landing Rate of Climb Conditions: • • • • Power.................................................................................................... Full Throttle Mixture....................................................................................................... Full Rich Flaps...................................................................................................... 100% (DN) Climb Airspeed .............................................
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Cirrus Design SR20 Section 9 Supplements Landing Distance Conditions: • • • • • Technique .................................................................................................. Normal Winds.............................................................................................................. Zero Runway ......................................................................................................... Paved Flaps. ..................................................................
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Section 9 Supplements 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.
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Cirrus Design SR20 Section 9 Supplements Section 6 - Weight and Balance FS 350.2 WATER LINE (WL) FS 55.6 150.0 FS 100.0 FS 142.5 WL 165.5 FS 222.0 FS 38.3 WL 100.0 NOTE Reference datum located at fuselage station 0.0. 50.0 LEMAC FS 133.1 BUTTOCK LINE (BL) 230.0 350.0 300.0 250.0 (FS) 200.0 150.0 100.0 50.0 0.0 FS 157.4 FUSELAGE STATION RBL 229.5 200.0 150.0 100.0 50.0 RBL 87.7 Typical LBL MAC 47.7" RBL 77.3 RBL 54.8 BL 0.0 50.0 BL 0.0 LBL 54.8 LBL 77.3 100.0 200.0 150.
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Section 9 Supplements Cirrus Design SR20 Airplane Weighing Form REF DATUM FS 0.0 FS 100.0 FS 142.5 WL 100.0 A = x + 100 B=A-y y = ____________ x = ____________ x Measured Measured y B A Weighing Point SR20_FM06_2539 Scale Reading - Tare = Net Weight X Arm L Main A= R Main A= Nose B= Total CG= = Moment As Weighed CG = Total Moment / Total Weight Space below provided for additions or subtractions to as weighed condition CG= Empty Weight Engine Oil (if oil drained) 15 lb at FS 78.
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Cirrus Design SR20 Section 9 Supplements 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. The frequency of weighing is determined by the operator.
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Section 9 Supplements Cirrus Design SR20 3. Weighing: a. With the airplane level, doors closed, and brakes released, record the weight shown on each scale. Deduct the tare, if any, from each reading. 4. Measuring: a. Obtain measurement ‘x’ by measuring horizontally along the airplane center line (BL 0) from a line stretched between the main wheel centers to a plumb bob dropped from the forward side of the firewall (FS 100).
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Cirrus Design SR20 Section 9 Supplements 10. Record the new weight and C.G. values on the Weight and Balance Record. The above procedure determines the airplane Basic Empty Weight, moment, and center of gravity in inches aft of datum. C.G. can also be expressed in terms of its location as a percentage of the airplane Mean Aerodynamic Cord (MAC) using the following formula: C.G. % MAC = 100 x (C.G. Inches – LEMAC) / MAC Where: LEMAC = 133.1 MAC = 47.
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Section 9 Supplements Cirrus Design SR20 Center of Gravity Limits The charts below depict the airplane center-of-gravity envelope in terms of inches aft of the reference datum and as a percentage of the Mean Aerodynamic Cord (MAC). The relationship between the two is detailed in the weighing instructions. 3100 3050 3000 FS 140.7 3050 lb FS 148.1 3050 lb Weight - Pounds 2950 2900 2850 2800 FS 139.1 2700 lb 2750 2700 2650 2600 2550 2500 2450 2400 2350 2300 2250 2200 2150 FS 148.1 2100 lb FS 137.
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Cirrus Design SR20 Section 9 Supplements Weight & Balance Loading Form Serial Num: ________________ Date: ________________________ Reg. Num: _________________ Initials: ______________________ Item Description 1. Basic Empty Weight Includes unusable fuel & full oil 2. Front Seat Occupants Pilot & Passenger (total) 3. Rear Seat Occupants 4. Baggage Area 130 lb maximum 5. Zero Fuel Condition Weight Sub total item 1 thru 4 6. Fuel Loading 56 Gallon @ 6.0 lb/gal. Maximum 7.
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Section 9 Supplements 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 Weight - Pounds Fwd Pass Aft Pass 400 300 200 Baggage 100 0 0.0 20.0 40.0 60.0 80.0 Mom ent/1000 Weight LB Fwd Aft Pass Pass FS 143.5 FS 180.0 3.60 Baggage Fuel Weight FS 208.0 FS 153.8 LB 4.16 3.10 220 Fwd Aft Fuel Pass Pass FS 143.5 FS 180.0 FS 153.8 20 2.87 31.57 39.60 34.08 40 5.74 7.
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Cirrus Design SR20 Section 9 Supplements Moment Limits Use the following chart or table to determine if the weight and moment from the completed Weight and Balance Loading Form are within limits.
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Section 9 Supplements Cirrus Design SR20 Intentionally Left Blank 48 of 56 Revision 01: 08-26-09 11934-S37
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Cirrus Design SR20 Section 9 Supplements Section 7 - Systems Description Airframe Wings The wing structure is constructed of composite materials producing wing surfaces that are smooth and seamless. The wing cross section is a blend of several high performance airfoils. A high aspect ratio results in low drag. Each wing provides attach structure for the main landing gear and contains a 29.3-gallon fuel tank. The G3 Wing is constructed in a conventional spar, rib, and shear section arrangement.
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Section 9 Supplements Cirrus Design SR20 Fuel System A 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 boost pump, and an engine-driven fuel pump.
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Cirrus Design SR20 Section 9 Supplements Drain valves at the system low points allow draining the system for maintenance and for examination of fuel in the system for 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.
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Section 9 Supplements Cirrus Design SR20 Environmental System Cabin heating and ventilation is accomplished by supplying conditioned air for heating and windshield defrost and fresh air for ventilation. The environmental system consists of a fresh air inlet in the lower RH cowl, a heat exchanger around the RH engine exhaust muffler, an air mixing chamber, air ducting for distribution, a distribution manifold, a windshield diffuser, and crew and passenger air vents.
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Cirrus Design SR20 Section 9 Supplements RAM AIR RAM AIR HOT AIR VALVE AIRFLOW 1 OFF 2 3 HEAT EXCHANGER MIXING CHAMBER FRESH AIR VALVE AIR FLOW VALVE SERVO MOTOR TEMPERATURE VENTS COLD HOT FLOOR AIRFLOW WINDSHIELD DIFFUSER PANEL AIRFLOW AIR GASPER DISTRIBUTION MANIFOLD FOOT-WARMER DIFFUSER FAN ASSEMBLY NOTE: Illustration depicts maximum cabin cooling airflows and selector settings.
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Section 9 Supplements Cirrus Design SR20 Airflow Selection The airflow selector on the system control panel regulates the volume of airflow allowed into the cabin distribution system. When the airflow selector is moved to the ON position an electro-mechanical linkage actuates a butterfly valve in the mixing chamber on the forward firewall to the full open position.
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Cirrus Design SR20 Section 9 Supplements Section 8 - Handling, Servicing, and Maintenance Servicing Tire Inflation Inflate nose tire to 30 psi (207 kPa) and main wheel tires to 62 psi (427kPa). 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.
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Section 9 Supplements Cirrus Design SR20 Intentionally Left Blank 56 of 56 Revision 01: 08-26-09 11934-S37
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Cirrus Design SR20 Section 9 Supplements Pilots Operating Handbook and FAA Approved Airplane Flight Manual Supplement For Garmin 400W-Series GPS Navigator When a Garmin 400W-Series GPS Navigator is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot's Operating Handbook. This document must be carried in the airplane at all times.
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Section 9 Supplements Cirrus Design SR20 Section 1 - General The WAAS-enabled, Garmin 400W-Series GPS Navigator is capable of providing primary navigation information for enroute, terminal, nonprecision, and precision approaches with typical position accuracies of 1 meter horizontally and 2 meters vertically. The Wide Area Augmentation System (WAAS) consists of ground reference stations positioned across the United States that monitor GPS satellite data.
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Cirrus Design SR20 Section 9 Supplements SR20_FM09_1285 SR20_FM09_1109 Figure - 1 GNC 420W and GNS 430W 400W-Series Navigators P/N 11934-S38 Revision 01: 11-11-07 3 of 10
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Section 9 Supplements Cirrus Design SR20 Section 2 – Limitations 1. The Garmin 400W-Series GPS Navigator Pilot's Guide and Reference, P/N 190-00356-00, Revision 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.
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Cirrus Design SR20 Section 9 Supplements Section 4 - Normal Procedures Refer to the Systems Description Section of this supplement for integration differences when single and dual units are installed. Normal operating procedures are outlined in the Garmin 400W-Series GPS Navigator Pilot's Guide and Reference, P/N 190-00356-00, Revision A or later. Activate Navigator 1. Battery Master Switch................................................................ON 2. Avionics Power Switch ........................
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Section 9 Supplements Cirrus Design SR20 Section 7 - Systems Description • Note • This section provides general description and aircraft integration information for the Garmin GNC 420W and GNS 430W 400W-Series Navigators.
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Cirrus Design SR20 Section 9 Supplements GNS 430W The GNS 430W, designated as the primary navigator (GPS 1), includes all of the features of the GNC 420W with the addition of IFR certified VOR/Localizer and Glideslope receivers. In the event a second GNS 430W is installed, the second unit will function as described below except that the GPS Navigator is designated GPS 2, the NAV receiver is designated NAV 2, and the VHF communications receiver is designated COM 2.
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Section 9 Supplements Cirrus Design SR20 Communication (COM) Transceiver The GNS 430W includes a digitally-tuned integrated VHF communications (COM) transceiver. The COM 1 antenna is located above the cabin on the airplane centerline. 28 VDC for transceiver operating is controlled through the Avionics Master Switch and supplied through the 7.5-amp COM 1 circuit breaker on the Avionics Essential Bus.
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Cirrus Design SR20 Section 9 Supplements 3. Dual GNS 430W units are installed. GPS 1 in this configuration is the uppermost GNS 430W unit in the console and GPS 2 is the lower GNS 430W unit. • GPS 1 in this configuration is a GNS 430W Navigator with VHF COM interfaced with the PFD and MFD as GPS 1/VLOC 1. Select NAV Source to GPS 1 or VLOC 1 through the PFD’s NAV select button. With source set to GPS 1 or VLOC 1, it can be alternately set between GPS or VLOC by the CDI button on the navigator.
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Section 9 Supplements Cirrus Design SR20 TERRAIN Interface • Note • TERRAIN functionality is a standard feature found in GNS 430W units with main software version 5.01 or above and valid terrain and obstacle databases installed. Garmin TERRAIN is a terrain awareness system incorporated into GNS 430W units to increase situational awareness and aid in reducing controlled flight into terrain.
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Cirrus Design SR20 Section 10 Safety Information Section 10 Safety Information Table of Contents Introduction ................................................................................... 10-3 Cirrus Airframe Parachute System (CAPS) Deployment .............. 10-4 Deployment Scenarios............................................................... 10-4 Mid-Air Collision...................................................................... 10-4 Structural Failure .......................................
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Section 10 Safety Information Cirrus Design SR20 Intentionally Left Blank 10-2 Information Manual March 2010
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Cirrus Design SR20 Section 10 Safety Information Introduction The Cirrus Design SR20 is a modern, advanced technology airplane designed to operate safely and efficiently in a flight environment. However, like any other aircraft, pilots must maintain proficiency to achieve maximum safety, utility, and economy.
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Section 10 Safety Information Cirrus Design SR20 Cirrus Airframe Parachute System (CAPS) Deployment 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.
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Cirrus Design SR20 Section 10 Safety Information continued safe flight and landing. If it is not, CAPS activation should be considered. Loss of Control Loss of control may result from many situations, such as: a control system failure (disconnected or jammed controls); severe wake turbulence, severe turbulence causing upset, severe airframe icing, or sustained pilot disorientation caused by vertigo or panic; or a spiral/ spin. If loss of control occurs, determine if the airplane can be recovered.
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Section 10 Safety Information Cirrus Design SR20 if time and altitude are critical, and/or ground impact is imminent, the CAPS should be activated regardless of airspeed. Deployment Altitude No minimum altitude for deployment has been set. This is because the actual altitude loss during a particular deployment depends upon the airplane’s airspeed, altitude and attitude at deployment as well as other environmental factors.
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Cirrus Design SR20 Section 10 Safety Information Landing Considerations After a CAPS deployment, the airplane will descend at less than 1500 feet per minute with a lateral speed equal to the velocity of the surface wind. The CAPS landing touchdown is equivalent to ground impact from a height of approximately 10 feet. While the airframe, seats, and landing gear are designed to accommodate the stress, occupants must be prepared for the landing.
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Section 10 Safety Information Cirrus Design SR20 If the pilot elects to touchdown with a door opened, there are several additional factors the pilot must consider: loss of door, possibility of head injury, or injury from an object coming through the open door. • If a door is open prior to touchdown in a CAPS landing, the door will most likely break away from the airplane at impact.
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Cirrus Design SR20 Section 10 Safety Information consider unlatching a door prior to assuming the emergency landing body position in order to provide a ready escape path should the airplane begin to sink. Post Impact Fire If there is no fire prior to touchdown and the pilot is able to shut down the engine, fuel, and electrical systems, there is less chance of a post impact fire.
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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.
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Cirrus Design SR20 Section 10 Safety Information • Do not “ride the brakes”. Pilots should consciously remove pressure from the brakes while taxiing. Failure to do so results in excessive heat buildup, premature brake wear, and increased possibility of brake failure or fire. • Avoid unnecessary high-speed taxiing. High-speed taxiing may result in excessive demands on the brakes, increased brake wear, and the possibility of brake failure or fire.
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Section 10 Safety Information Cirrus Design SR20 Intentionally Left Blank 10-12 Information Manual March 2010