CIRRUS DESIGN SR22 Information Manual

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AIRPLANE INFORMATION MANUAL

CIRRUS DESIGN SR22

A i r c r a f t S e r i a l s 0 0 0 2 a n d s u b s w i t h A n a l o g

o r A v i d y n e A v i o n i c s S y s t e m

At the time of issuance, this Information Manual was harmo-

nized with the SR22 Pilot's Operating Handbook Rev A9 (P/N

13772-001), and will not be kept current. Therefore, this Infor-

mation 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.

P/N 20880-001

Information Manual

for the

• NOTE •

March 2010

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Summary of Contents for CIRRUS DESIGN SR22

Page 1 • NOTE • At the time of issuance, this Information Manual was harmo- nized with the SR22 Pilot's Operating Handbook Rev A9 (P/N 13772-001), and will not be kept current. Therefore, this Infor- mation 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.
Page 3: Table Of Contents
Cirrus Design Section 1 SR22 General Section 1 General Table of Contents Introduction ..................1-3 The Airplane..................1-6 Engine..................1-6 Propeller ..................1-6 Fuel....................1-6 Oil ....................1-7 Maximum Certificated Weights ............ 1-7 Cabin and Entry Dimensions ............1-7 Baggage Spaces and Entry Dimensions ........1-7 Specific Loadings.................
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Page 5: Introduction
Cirrus Design Section 1 SR22 General Introduction This section contains information of general interest to pilots and owners. You will find the information useful in acquainting yourself with the airplane, as well as in loading, fueling, sheltering, and handling the airplane during ground operations.
Page 6 Section 1 Cirrus Design General SR22 26.0 ft 7.92 m 8.8 ft 2.70 m 7 inches 18 cm NOTE: • Wing span includes position and strobe lights. • Prop ground clearance at 3400 lb - 7" inches (18 cm). • Wing Area = 144.9 sq. ft.
Page 7 Cirrus Design Section 1 SR22 General GROUND TURNING CLEARANCE 24.8 ft. (7.54 m) -RADIUS FOR WING TIP 7.0 ft. (2.16 m) -RADIUS FOR NOSE GEAR 0.5 ft. (.15 m) -RADIUS FOR INSIDE GEAR 10.8 ft. (3.30 m) -RADIUS FOR OUTSIDE GEAR TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER.
Page 8: The Airplane
Section 1 Cirrus Design General SR22 The Airplane Engine Number of Engines................1 Number of Cylinders................6 Engine Manufacturer ........... Teledyne Continental Engine Model................IO-550-N Fuel Metering..............Fuel Injected Engine Cooling ..............Air Cooled Engine Type........Horizontally Opposed, Direct Drive Horsepower Rating..........310 hp @ 2700 rpm...
Page 9: Fuel
Cirrus Design Section 1 SR22 General Fuel Total Capacity..........84.0 U.S. Gallons (318.0 L) Total Usable..........81.0 U.S. Gallons (306.6 L) Approved Fuel Grades: 100 LL Grade Aviation Fuel (Blue) 100 (Formerly 100/130) Grade Aviation Fuel (Green) Oil Capacity (Sump) ..........8 U.S. Quarts (7.6 L) Oil Grades: All Temperatures ......
Page 10: Symbols, Abbreviations And Terminology
Section 1 Cirrus Design General SR22 Symbols, Abbreviations and Terminology General Airspeed Terminology and Symbols KCAS Knots Calibrated Airspeed is the indicated airspeed corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level.
Page 11: Meteorological Terminology
Cirrus Design Section 1 SR22 General Stalling Speed is the minimum steady flight speed at which the aircraft is controllable in the landing configuration (100% flaps) at the most unfavorable weight and balance. Best Angle of Climb Speed is the speed at which the airplane will obtain the highest altitude in a given horizontal distance.
Page 12: Engine Power Terminology
Section 1 Cirrus Design General SR22 • 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.
Page 13: Weight And Balance Terminology
Cirrus Design Section 1 SR22 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.
Page 14 Section 1 Cirrus Design General SR22 • 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).
Page 15 Cirrus Design Section 2 SR22 Limitations Section 2 Limitations Table of Contents Introduction ..................2-3 Certification Status ................2-3 Airspeed Limitations................ 2-4 Airspeed Indicator Markings ............2-5 Power Plant Limitations ..............2-6 Engine..................2-6 Propeller ..................2-7 Weight Limits .................. 2-7 Instrument Markings ...............
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Page 17: Introduction
This section provides operating limitations, instrument markings and basic placards required by regulation and necessary for the safe operation of the SR22 and its standard systems and equipment. Refer to Section 9 of this handbook for amended operating limitations for airplanes equipped with optional equipment.
Page 18: Airspeed Limitations
Section 2 Cirrus Design Limitations SR22 Airspeed Limitations The indicated airspeeds in the following table are based upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
Page 19: Airspeed Indicator Markings
Cirrus Design Section 2 SR22 Limitations Airspeed Indicator Markings The airspeed indicator markings are based upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
Page 20: Power Plant Limitations
Section 2 Cirrus Design Limitations SR22 Power Plant Limitations Engine Teledyne Continental .............. IO-550-N Power Rating ............310 hp @ 2700 RPM Maximum RPM ..............2700 RPM Oil: Oil Temperature........240 F (115 C) maximum Oil Pressure: Minimum................10 psi Maximum................
Page 21: Propeller
Cirrus Design Section 2 SR22 Limitations Propeller Hartzell Propeller Type ........Constant Speed, Three Blade Model Number..........PHC-J3YF-1RF/F7694(B) Diameter.............78.0” (76.0” Minimum) Model Number......... PHC-J3YF-1RF/F7693DF(B) Diameter.............78.0" (76.0" Minimum) McCauley Propeller Type ........Constant Speed, Three Blade Model Number............ D3A34C443/78CYA-0 Diameter.............78.0" (76.0" Minimum) MT Propeller Propeller Type ........Constant Speed, Three Blade...
Page 22: Instrument Markings
Section 2 Cirrus Design Limitations SR22 Instrument Markings Red Line Green Arc Yellow Arc Red Line Instrument (Range) Minimum Normal Caution Maximum Power Plant Instrumentation Tachometer/ –– 500 - 2700 –– 2700 Engine Speed (0 - 3500 RPM) Cylinder Head ––...
Page 23: Center Of Gravity Limits
Cirrus Design Section 2 SR22 Limitations Center of Gravity Limits Reference Datum ........100 inches forward of firewall Forward ..............Refer to Figure 2-4 Aft ................Refer to Figure 2-4 3600 Landing Limitation 31.5% MAC 19.2% MAC (Shaded) FS 148.1 FS 142.3...
Page 24: Maneuver Limits
Maneuver Limits Aerobatic maneuvers, including spins, are prohibited. • Note • Because the SR22 has not been certified for spin recovery, the Cirrus Airframe Parachute System (CAPS) must be deployed if the airplane departs controlled flight. Refer to Section 3 – Emergency Procedures, Inadvertent Spiral/Spin Entry.
Page 25: Kinds Of Operation
Section 2 SR22 Limitations Kinds of Operation The SR22 is equipped and approved for the following type operations: • VFR day and night. • IFR day and night. Kinds of Operation Equipment List The following listing summarizes the equipment required under Federal Aviation Regulations (FAR) Part 23 for airworthiness under the listed kind of operation.
Page 26 Section 2 Cirrus Design Limitations SR22 System, Kinds of Operation Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Circuit Breakers As Required. Equipment & Furnishingss Emergency Locator Transmitter One Seat Belt for Restraint System each occupant. Fire Protection Fire Extinguisher Flight Controls...
Page 27 Cirrus Design Section 2 SR22 Limitations System, Kinds of Operation Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Ice & Rain Protection Alternate Engine Air Induction System Alternate Static Air Source Pitot Heater — — Landing Gear Wheel Pants — —...
Page 28 Section 2 Cirrus Design Limitations SR22 System, Kinds of Operation Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Serials 0002 & subs Turn Coordinator — — w/o PFD. Serials 0435 & subs PFD Attitude Indication — — w/ PFD. Serials 0435 & subs PFD Airspeed Indication —...
Page 29: Icing
Cirrus Design Section 2 SR22 Limitations System, Kinds of Operation Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Manifold Pressure Indication Oil Pressure Indication Oil Quantity Indicator (Dipstick) Oil Temperature Indication Engine Speed Special Equipment Cirrus Airframe Parachute (CAPS) Airplane Flight Manual Included w/ POH.
Page 30: Taxi Power
Refer to Oxygen System Limitations in this Section. Environmental Conditions For operation of the airplane below an outside air temperature of -10°F (-23° C), use of cowl inlet covers approved by Cirrus Design and listed in the Winterization Kit AFM Supplement P/N 13772-118 is required. Maximum Occupancy Occupancy of this airplane is limited to four persons (the pilot and three passengers).
Page 31: Systems And Equipment Limits
Cirrus Design Section 2 SR22 Limitations Systems and Equipment Limits Cirrus Airframe Parachute System (CAPS) Maximum Demonstrated Deployment Speed ....133 KIAS • Note • Refer to Section 10 – Safety Information, for additional CAPS guidance. Primary Flight Display 1. The PFD integrates with separately approved sensor installations.
Page 32 Section 2 Cirrus Design Limitations SR22 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.
Page 33: Multi-Function Display
Cirrus Design Section 2 SR22 Limitations 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. The moving map display must not be used as the primary navigation instrument.
Page 34: 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 13772-109. • Secure the oxygen bottle in the right front seat as described in the AFM Supplement noted above.
Page 35: Placards
Cirrus Design Section 2 SR22 Limitations Placards Engine compartment, inside oil filler access: ENGINE OIL GRADE ABOVE 40° F SAE 50 OR 20W50 OR 20W60 BELOW 40° F SAE 30 OR 10W30, 15W50, OR 20W50 REFER TO AFM FOR APPROVED OILS...
Page 36 Section 2 Cirrus Design Limitations SR22 Elevator, Rudder, & Elec. Trim Tab (if installed), both sides: NO PUSH Left fuselage, on external power supply door: DE-ICING FLUID EXTERNAL REFER TO AFM FOR APPROVED POWER DE-ICING FLUIDS 28 V DC Serials 0334 & subs w/ Ice Protection.
Page 37 Cirrus Design Section 2 SR22 Limitations Engine control panel: 119 KIAS FLAPS 100% 104 KIAS RICH NORMAL TURN BOOST ICE PROTECTION PUMP ON BEFORE SWITCHING Serials 0334 thru 0434. FUEL TANKS BOOST FUEL PUMP IDLE CUTOFF PRIME CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT Serials 0410 &...
Page 38 Section 2 Cirrus Design Limitations SR22 Wing, flap aft edge and fuselage vortex generator: NO STEP Cabin Door Window, lower edge, centered, applied upside down: RESCUE: FRACTURE AND REMOVE WINDOW Bolster Switch Panel, left edge: THIS AIRCRAFT IS CERTIFIED FOR THE...
Page 39 Cirrus Design Section 2 SR22 Limitations Bolster Panel, both sides: GRAB HERE Serials 0656 & subs. 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...
Page 40 Section 2 Cirrus Design Limitations SR22 Instrument Panel: FASTEN SEATBELTS NO SMOKING Serials 0002 thru 1862. FASTEN SEAT BELT • NO SMOKING FIRE EXTINGUISHER FORWARD LEFT OF PILOT SEAT Serials 1863 & subs. Cabin Window, above door latch: EMERGENCY EXIT...
Page 41 Cirrus Design Section 2 SR22 Limitations CAPS Deployment Handle Cover, above pilot's right shoulder: WARNING THIS AIRCRAFT IS EQUIPPED WITH A CIRRUS AIRFRAME PARACHUTE SYSTEM USE FOR EXTREME EMERGENCIES ONLY SEAT BELT AND SHOULDER HARNESS MUST BE WORN AT ALL TIMES...
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Page 43 Cirrus Design Section 3 SR22 Emergency Procedures Section 3 Emergency Procedures Table of Contents Introduction ..................3-3 Airspeeds for Emergency Operations ..........3-4 Emergency Procedures Guidance ..........3-5 Preflight Planning................. 3-5 Preflight Inspections/Maintenance ..........3-5 Methodology ................3-5 Memory Items ................3-6 Ground Emergencies ..............3-7...
Page 44 Section 3 Cirrus Design Emergency Procedures SR22 PFD - Loss of Air Data ...............3-26 PFD - Loss of Attitude Data ............3-26 Power Lever Linkage Failure .............3-27 Information Manual March 2010...
Page 45: Introduction
Emergency Procedures Introduction This section provides procedures for handling emergencies and critical flight situations that may occur while operating the SR22. Although emergencies caused by airplane, systems, or engine malfunctions are extremely rare, the guidelines described in this section should be considered and applied as necessary should an emergency arise.
Page 46: Airspeeds For Emergency Operations
Section 3 Cirrus Design Emergency Procedures SR22 Airspeeds for Emergency Operations Maneuvering Speed: 3400 lb ................133 KIAS Best Glide: 3400 lb ................88 KIAS 2900 lb ................87 KIAS Emergency Landing (Engine-out): Flaps Up................90 KIAS Flaps 50% ................85 KIAS Flaps 100% ................80 KIAS...
Page 47: Emergency Procedures Guidance
Emergency Procedures Guidance Although this section provides procedures for handling most emergencies and critical flight situations that could arise in the SR22, it is not a substitute for thorough knowledge of the airplane and general aviation techniques. A thorough study of the information in this handbook while on the ground will help you prepare for time-critical situations in the air.
Page 48: Memory Items
Section 3 Cirrus Design Emergency Procedures SR22 Take Appropriate Action — In most situations, the procedures listed in this section will either correct the aircraft problem or allow safe recovery of the aircraft. Follow them and use good pilot judgment.
Page 49: Ground Emergencies
Cirrus Design Section 3 SR22 Emergency Procedures Ground Emergencies Engine Fire During Start A fire during engine start may be caused by fuel igniting in the fuel induction system. If this occurs, attempt to draw the fire back into the engine by continuing to crank the engine.
Page 50: Emergency Ground Egress
Section 3 Cirrus Design Emergency Procedures SR22 Emergency Ground Egress • WARNING • While exiting the airplane, make sure evacuation path is clear of other aircraft, spinning propellers, and other hazards. 1. Engine................SHUTDOWN • Note • If the engine is left running, set the Parking Brake prior to evacuating the airplane.
Page 51: In-Flight Emergencies
Cirrus Design Section 3 SR22 Emergency Procedures In-Flight Emergencies Engine Failure On Takeoff (Low Altitude) If the engine fails immediately after becoming airborne, abort on the runway if possible. If altitude precludes a runway stop but is not sufficient to restart the engine, lower the nose to maintain airspeed and establish a glide attitude.
Page 52: Maximum Glide
Section 3 Cirrus Design Emergency Procedures SR22 Maximum Glide Conditions Example: Power Altitude 10,000 ft. AGL Propeller Windmilling Airspeed Best Glide Flaps 0% (UP) Wind Zero Glide Distance 15.8 NM Best Glide Speed 3400 lb 88 KIAS Maximum Glide Ratio ~ 9.6 : 1...
Page 53: Engine Failure In Flight
Cirrus Design Section 3 SR22 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.
Page 54: Engine Airstart
Section 3 Cirrus Design Emergency Procedures SR22 Engine Airstart The following procedures address the most common causes for engine loss. Switching tanks and turning the fuel pump on will enhance starting if fuel contamination was the cause of the failure.
Page 55: Engine Partial Power Loss
Cirrus Design Section 3 SR22 Emergency Procedures Engine Partial Power Loss Indications of a partial power loss include fluctuating RPM, reduced or fluctuating manifold pressure, low oil pressure, high oil temperature, and a rough-sounding or rough-running engine. Mild engine roughness in flight may be caused by one or more spark plugs becoming fouled.
Page 56: Fuel Pump (If Used)
Section 3 Cirrus Design Emergency Procedures SR22 The following procedure provides guidance to isolate and correct some of the conditions contributing to a rough running engine or a partial power loss: 1. Fuel Pump................BOOST Selecting BOOST on may clear the problem if vapor in the injection lines is the problem or if the engine-driven fuel pump has partially failed.
Page 57: Low Oil Pressure
Cirrus Design Section 3 SR22 Emergency Procedures Low Oil Pressure If low oil pressure is accompanied by a rise in oil temperature, the engine has probably lost a significant amount of its oil and engine failure may be imminent. Immediately reduce engine power to idle and select a suitable forced landing field.
Page 58: Smoke And Fume Elimination
Section 3 Cirrus Design Emergency Procedures SR22 Smoke and Fume Elimination If smoke and/or fumes are detected in the cabin, check the engine parameters for any sign of malfunction. If a fuel leak has occurred, actuation of electrical components may cause a fire. If there is a strong smell of fuel in the cockpit, divert to the nearest suitable landing field.
Page 59: Wing Fire In Flight
Cirrus Design Section 3 SR22 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. If possible, side slip to keep flames away from fuel tank and cabin.
Page 60: Emergency Descent
Section 3 Cirrus Design Emergency Procedures SR22 • 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.
Page 61: Inadvertent Spiral Dive During Imc Flight
Cirrus Design Section 3 SR22 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.
Page 62: Spins
Emergency Procedures SR22 Spins The SR22 is not approved for spins, and has not been tested or certified for spin recovery characteristics. The only approved and demonstrated method of spin recovery is activation of the Cirrus Airframe Parachute System (See CAPS Deployment, this section).
Page 63: Caps Deployment
Cirrus Design Section 3 SR22 Emergency Procedures CAPS Deployment The Cirrus Airframe Parachute System (CAPS) should be activated in the event of a life-threatening emergency where CAPS deployment is determined to be safer than continued flight and landing. • WARNING •...
Page 64 Section 3 Cirrus Design Emergency Procedures SR22 The maximum demonstrated deployment speed is 133 KIAS. Reducing airspeed allows minimum parachute loads and prevents structural overload and possible parachute failure. 2. Mixture (If time and altitude permit) ......... CUTOFF Generally, a distressed airplane will be safer for its occupants if the engine is not running.
Page 65 Cirrus Design Section 3 SR22 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.
Page 66: Landing Emergencies
Section 3 Cirrus Design Emergency Procedures SR22 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.
Page 67: Ditching
Cirrus Design Section 3 SR22 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.
Page 68: System Malfunctions
Section 3 Cirrus Design Emergency Procedures SR22 System Malfunctions Primary Flight Display System In the unlikely event of a PFD failure, the pilot may lose the ability to control the autopilot through the PFD controls. If this malfunction occurs, the PFD circuit breakers may be pulled and the airplane flown using the mechanical standby instruments.
Page 69 Cirrus Design Section 3 SR22 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.
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Page 71 Cirrus Design Section 3A SR22 Abnormal Procedures Section 3A Abnormal Procedures Table of Contents Introduction .................. 3A-3 Abnormal Procedures Guidance ..........3A-4 Ground Procedures..............3A-5 Brake Failure During Taxi ............3A-5 Aborted Takeoff ................ 3A-5 In-Flight Procedures..............3A-6 Inadvertent Icing Encounter ............3A-6 Inadvertent IMC Encounter............
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Page 73: Section 3A
Cirrus Design Section 3A SR22 Abnormal Procedures Introduction This section provides procedures for handling abnormal system and/or flight conditions which, if followed, will maintain an acceptable level of airworthiness or reduce operational risk. The guidelines described in this section are to be used when an abnormal condition exists and should be considered and applied as necessary.
Page 74: Abnormal Procedures Guidance
Abnormal Procedures Guidance Although this section provides procedures for handling most abnormal system and/or flight conditions that could arise in the SR22, it is not a substitute for thorough knowledge of the airplane and general aviation techniques. A thorough study of the information in this handbook while on the ground will help you prepare for time-critical situations in the air.
Page 75: Ground Procedures
Cirrus Design Section 3A SR22 Abnormal Procedures Ground Procedures Brake Failure During Taxi Ground steering is accomplished by differential braking. However, increasing power may allow some rudder control due to increased groundspeed and airflow over the rudder. 1. Engine Power............AS REQUIRED •...
Page 76: In-Flight Procedures
3. Heading..........Reset to initiate 180° turn Door Open In Flight The doors on the SR22 will remain 1-3 inches open in flight if not latched. If this is discovered on takeoff roll, abort takeoff if practical. If already airborne: 1.
Page 77: Landing Procedures
Cirrus Design Section 3A SR22 Abnormal Procedures Landing Procedures Landing With Failed Brakes One brake inoperative 1. Land on the side of runway corresponding to the inoperative brake. 2. Maintain directional control using rudder and working brake. Both brakes inoperative 1.
Page 78 Section 3A Cirrus Design Abnormal Procedures SR22 AMMETER BAT 1 ALT 1 ALT 2 BATT MAIN DISTRIBUTION ESSENTIAL ALT 1 ALT 2 DISTRIBUTION BUS BAT 2 NON-ESSENTIAL MAIN BUS 2 ESSENTIAL ANNUN/ENGINE INST SKYWATCH/ FUEL PUMP TAWS TURN TURN COORD. #1 GPS 2 COORD.
Page 79: System Malfunctions
Cirrus Design Section 3A SR22 Abnormal Procedures System Malfunctions Alternator Failure Steady illumination of either ALT caution light in the annunciator panel indicates a failure of the corresponding alternator. The most likely the cause of the alternator failure is a wiring fault, a malfunctioning alternator, or a malfunctioning control unit.
Page 80 Section 3A Cirrus Design Abnormal Procedures SR22 ALT 1 Light Steady Steady illumination indicates a failure of ALT 1. Attempt to bring alternator back on line. If alternator cannot be brought back, reduce loads and use Main Bus or Non-Essential loads only as necessary for flight conditions.
Page 81: Engine Indicating System Failure
Cirrus Design Section 3A SR22 Abnormal Procedures 2. Alternator 2 Circuit Breaker ......CHECK and RESET 3. ALT 2 Master Switch ..............ON If alternator does not reset: 4. Switch off unnecessary equipment on Main Bus 1, Main Bus 2, and Non-Essential Buses to reduce loads.
Page 82: Communications Failure
Section 3A Cirrus Design Abnormal Procedures SR22 Communications Failure Communications failure can occur for a variety of reasons. If, after following the checklist procedure, communication is not restored, proceed with FAR/AIM lost communications procedures. • Note • In the event of an audio panel power failure the audio panel connects COM 1 to the pilot’s headset and speakers.
Page 83: Pitot Static Malfunction
Cirrus Design Section 3A SR22 Abnormal Procedures Pitot Static Malfunction Static Source Blocked If erroneous readings of the static source instruments (airspeed, altimeter and vertical speed) are suspected, the alternate static source valve, on side of console near pilot’s right ankle, should be opened to supply static pressure from the cabin to these instruments.
Page 84: Electric Trim/Autopilot Failure
Section 3A Cirrus Design Abnormal Procedures SR22 Electric Trim/Autopilot Failure Any failure or malfunction of the electric trim or autopilot can be over- ridden by use of the control yoke. If runaway trim is the problem, de- energize the circuit by pulling the circuit breaker (PITCH TRIM, ROLL TRIM, or AUTOPILOT) and land as soon as conditions permit.
Page 85 Cirrus Design Section 4 SR22 Normal Procedures Section 4 Normal Procedures Table of Contents Introduction ..................4-3 Airspeeds for Normal Operation ............. 4-4 Normal Procedures ................. 4-5 Preflight Inspection ..............4-5 Preflight Walk-Around ..............4-6 Before Starting Engine............... 4-10 Starting Engine ................4-11 Before Taxiing................
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Page 87: Introduction
Cirrus Design Section 4 SR22 Normal Procedures Introduction This section provides amplified procedures for normal operation. Normal procedures associated with optional systems can be found in Section 9. Information Manual March 2010...
Page 88: Airspeeds For Normal Operation
Section 4 Cirrus Design Normal Procedures SR22 Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3400 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.
Page 89: Normal Procedures
Cirrus Design Section 4 SR22 Normal Procedures Normal Procedures Preflight Inspection Before carrying out preflight inspections, ensure that all required maintenance has been accomplished. Review your flight plan and compute weight and balance. • Note • Throughout the walk-around: check all hinges, hinge pins, and bolts for security;...
Page 90: Preflight Walk-Around
Section 4 Cirrus Design Normal Procedures SR22 Preflight Walk-Around 1. Cabin a. Required Documents..........On Board b. Avionics Power Switch............OFF c. Bat 2 Master Switch ............ON d. PFD - Serials 0435 and subsequent with PFD ..Verify On e. Avionics Cooling Fan ............ Audible Voltmeter ..............
Page 91 Cirrus Design Section 4 SR22 Normal Procedures d. COM 2 Antenna (underside) ...Condition and Attachment e. Baggage Door ........... Closed and Secure Static Button ..........Check for Blockage g. Parachute Cover........Sealed and Secure 3. Empennage a. Tiedown Rope .............Remove b.
Page 92 Section 4 Cirrus Design Normal Procedures SR22 7. Right Wing Forward and Main Gear a. Leading Edge and Stall Strips ........Condition b. Fuel Cap ........Check Quantity and Secure c. Fuel Drains (2 underside) ......Drain and Sample d. Wheel Fairings...... Security, Accumulation of Debris e.
Page 93 Cirrus Design Section 4 SR22 Normal Procedures e. Propeller ......Condition (indentations, nicks, etc.) Spinner ....... Condition, Security, and Oil Leaks g. Air Inlets ..............Unobstructed h. Alternator..............Condition 10. Nose, Left Side a. Landing Light............. Condition b. Engine Oil..Check 6-8 quarts, Leaks, Cap & Door Secure c.
Page 94: Before Starting Engine
Section 4 Cirrus Design Normal Procedures SR22 c. Strobe, Nav Light and Lens ....Condition and Security d. Tip ................Attachment 13. Left Wing Trailing Edge a. Flap And Rub Strips (If installed)..Condition and Security b. Aileron ..........Freedom of movement c. Aileron Gap Seal ............Security d.
Page 95: Starting Engine
Cirrus Design Section 4 SR22 Normal Procedures Starting Engine If the engine is warm, no priming is required. For the first start of the day and in cold conditions, prime will be necessary. Weak intermittent firing followed by puffs of black smoke from the exhaust stack indicates over-priming or flooding.
Page 96 Section 4 Cirrus Design Normal Procedures SR22 4. Strobe Lights ................ON 5. Mixture ................. FULL RICH 6. Power Lever ............FULL FORWARD 7. Fuel Pump............. PRIME, then BOOST • Note • Serials 0002 - 0278 before SB 22-73-01: On first start of the...
Page 97: Before Taxiing
Cirrus Design Section 4 SR22 Normal Procedures Before Taxiing 1. Flaps ................. UP (0%) 2. Radios/Avionics ............. AS REQUIRED 3. Cabin Heat/Defrost ..........AS REQUIRED 4. Fuel Selector............SWITCH TANK Taxiing When taxiing, directional control is accomplished with rudder deflection and intermittent braking (toe taps) as necessary. Use only as much power as is necessary to achieve forward movement.
Page 98: Before Takeoff
Section 4 Cirrus Design Normal Procedures SR22 Before Takeoff During cold weather operations, the engine should be properly warmed up before takeoff. In most cases this is accomplished when the oil temperature has reached at least 100° F (38° C). In warm or hot weather, precautions should be taken to avoid overheating during prolonged ground engine operation.
Page 99 Cirrus Design Section 4 SR22 Normal Procedures to extinguish ALT 2 caution light. ALT 2 caution light should go out below 2200 RPM. 16. Voltage ................CHECK 17. 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°...
Page 100: Maximum Power Fuel Flow
Section 4 Cirrus Design Normal Procedures SR22 Maximum Power Fuel Flow Leaning for Takeoff and Maximum Climb is accomplished at full throttle by leaning the mixture from full rich to the target fuel flow for the given pressure altitude. The fuel flow values in the table below were demonstrated to obtain the takeoff and climb performance presented in Section 5.
Page 101: Takeoff
Cirrus Design Section 4 SR22 Normal Procedures Takeoff 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. Discontinue takeoff at any sign of rough operation or sluggish acceleration. Make a thorough full-throttle static run-up before attempting another takeoff.
Page 102: Short Field Takeoff
Section 4 Cirrus Design Normal Procedures SR22 Short Field Takeoff 1. Flaps ..................50% 2. Brakes .................. HOLD 3. Power Lever ............FULL FORWARD 4. Mixture ..................SET 5. Engine Parameters ............CHECK 6. Brakes ........RELEASE (Steer with Rudder Only) 7. Elevator Control ......ROTATE Smoothly at 70 KIAS 8.
Page 103: Cruise
Cirrus Design Section 4 SR22 Normal Procedures Cruise Normal cruising is performed between 55% and 85% power. The engine power setting and corresponding fuel consumption for various altitudes and temperatures can be determined by using the cruise data in Section 5.
Page 104: Cruise Leaning
Section 4 Cirrus Design Normal Procedures SR22 Cruise Leaning Exhaust gas temperature (EGT) may be used as an aid for mixture leaning in cruise flight. For “Best Power” use 75% power or less. For “Best Economy” use 65% power or less. To adjust the mixture,...
Page 105: Landing
Cirrus Design Section 4 SR22 Normal Procedures Landing • Caution • Landings should be made with full flaps. Landings with less than full flaps are recommended only if the flaps fail to deploy or to extend the aircraft’s glide distance due to engine malfunction.
Page 106: Balked Landing/Go-Around
Section 4 Cirrus Design Normal Procedures SR22 as required. The maximum allowable crosswind velocity is dependent upon pilot capability as well as aircraft limitations. Operation in direct crosswinds of 20 knots has been demonstrated. Balked Landing/Go-Around In a balked landing (go around) climb, disengage autopilot, apply full power, then reduce the flap setting to 50%.
Page 107: Shutdown
Cirrus Design Section 4 SR22 Normal Procedures Shutdown 1. Fuel Pump (if used) ..............OFF 2. Throttle..................IDLE 3. Ignition Switch..............CYCLE • Caution • Note that the engine hesitates as the switch cycles through the “OFF” position. If the engine does not hesitate, one or both magnetos are not grounded.
Page 108: Stalls
Normal Procedures SR22 Stalls SR22 stall characteristics are conventional. Power-off stalls may be accompanied by a slight nose bobbing if full aft stick is held. Power-on stalls are marked by a high sink rate at full aft stick. Power-off stall speeds at maximum weight for both forward and aft C.G.
Page 109: Environmental Considerations
Cirrus Design Section 4 SR22 Normal Procedures Environmental Considerations Cold Weather Operation Starting If the engine has been cold soaked, it is recommended that the propeller be pulled through by hand several times to break loose or limber the oil. This procedure will reduce power draw on the battery if a battery start is made.
Page 110 Section 4 Cirrus Design Normal Procedures SR22 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 •...
Page 111: Hot Weather Operation
Cirrus Design Section 4 SR22 Normal Procedures 11. Ignition Switch....... START (Release after engine starts) • Caution • Limit cranking to intervals of 20 seconds with a 20 second cooling period between cranks. This will improve battery and contactor life 12.
Page 112: Noise Characteristics/Abatement
Section 4 Cirrus Design Normal Procedures SR22 Noise Characteristics/Abatement The certificated noise levels for the Cirrus Design SR22 established in accordance with FAR 36 Appendix G are: Configuration Actual Maximum Allowable Hartzel 3-blade Propeller 83.65 dB(A) 88.00 dB(A) PHC-J3YF-1RF/F7694 Hartzel 3-blade Propeller 84.81 dB(A)
Page 113: Fuel Conservation
Cirrus Design Section 4 SR22 Normal Procedures Fuel Conservation Minimum fuel use at cruise will be achieved using the best economy power setting described under cruise. Information Manual 4-29 March 2010...
Page 114 Section 4 Cirrus Design Normal Procedures SR22 Intentionally Left Blank 4-30 Information Manual March 2010...
Page 115 Cirrus Design Section 5 SR22 Performance Data Section 5 Performance Data Table of Contents Introduction ..................5-3 Associated Conditions Affecting Performance......5-3 Flight Planning ................5-4 Sample Problem ................5-4 Takeoff..................5-5 Climb.................... 5-6 Cruise ..................5-7 Fuel Required ................5-8 Landing ..................
Page 116 Section 5 Cirrus Design Performance Data SR22 Cruise Performance ..............5-29 Range / Endurance Profile ............5-30 Range / Endurance Profile ............5-31 Range / Endurance Profile ............5-32 Balked Landing Climb Gradient ............5-33 Balked Landing Rate of Climb............5-34 Landing Distance ................5-35 Landing Distance ................5-36...
Page 117: Introduction
Cirrus Design Section 5 SR22 Performance Data Introduction Performance data in this section are presented for operational planning so that you will know what performance to expect from the airplane under various ambient and field conditions. Performance data are presented for takeoff, climb, and cruise (including range &...
Page 118: Flight Planning
Section 5 Cirrus Design Performance Data SR22 Flight Planning The performance tables in this section present sufficient information to predict airplane performance with reasonable accuracy. However, variations in fuel metering, mixture leaning technique, engine & propeller condition, air turbulence, and other variables encountered during a particular flight may account for variations of 10% or more in range and endurance.
Page 119: Takeoff
Cirrus Design Section 5 SR22 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 ..........2000 Feet •...
Page 120: Climb
Section 5 Cirrus Design Performance Data SR22 • Decrease in total distance (2107 feet x 0.092) ....194 feet • Corrected total distance to clear 50 foot obstacle ..1913 feet Corrections for grass runways and sloped runways are also applicable and should be applied.
Page 121: Cruise
Cirrus Design Section 5 SR22 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%.
Page 122: Fuel Required
Section 5 Cirrus Design Performance Data SR22 Fuel Required The total fuel requirement for the flight may be estimated using the performance information obtained from Figures 5-14 and 5-15. The resultant cruise distance is: • Total distance (from sample problem) ......560.0 NM •...
Page 123: Landing
Cirrus Design Section 5 SR22 Performance Data Landing A procedure similar to takeoff should be used for estimating the landing distance at the destination airport. Figure 5-19 presents landing distance information for the short field technique. The distances corresponding to 2000 feet and 20 C are as follows: •...
Page 124: Airspeed Calibration
Section 5 Cirrus Design Performance Data SR22 Airspeed Calibration Normal Static Source Conditions: Example: • Power for level flight or maximum Flaps ........... 50% continuous, whichever is less. Indicated Airspeed ....85 Knots Calibrated Airspeed ..... 85 Knots • Note •...
Page 125: Airspeed Calibration
Cirrus Design Section 5 SR22 Performance Data Airspeed Calibration Alternate Static Source Conditions: Example: • Power for level flight or maximum Flaps..........50% continuous, whichever is less. Indicated Airspeed....85 Knots • Heater, Defroster & Vents .....ON Calibrated Airspeed ....86 Knots • Note •...
Page 126: Altitude Correction
Section 5 Cirrus Design Performance Data SR22 Altitude Correction Normal Static Source Conditions: Example: • Power for level flight or maximum Flaps ..........0% continuous, whichever is less. Indicated Airspeed ..... 120 Knots Desired Altitude....12,000 FT Altitude Correction ....-13 FT Altitude to Fly .....
Page 127: Altitude Correction
Cirrus Design Section 5 SR22 Performance Data Altitude Correction Alternate Static Source Conditions: Example: • Power for level flight or maximum Flaps..........0% continuous, whichever is less. Indicated Airspeed....120 Knots • Heater, Defroster, & Vents.....ON Desired Altitude ....12,000 FT Altitude Correction..... -4 FT Altitude to Fly.....
Page 128: Temperature Conversion
Section 5 Cirrus Design Performance Data SR22 Temperature Conversion • Note • • To convert from Celsius (°C) to Fahrenheit (°F), find, in the shaded columns, the number representing the temperature value (°C) to be converted. The equivalent Fahrenheit temperature is read to the right.
Page 129: Outside Air Temperature For Isa Condition
Cirrus Design Section 5 SR22 Performance Data Outside Air Temperature ISA Condition Example: Pressure Altitude....8000 FT Outside Air Temp....... 48° F ISA Condition ....ISA + 10° C Press ISA-40°C ISA-20°C ISA+10°C ISA+20°C Feet °C °F °C °F °C °F °C...
Page 130: Stall Speeds
Section 5 Cirrus Design Performance Data SR22 Stall Speeds Conditions: Example: • Weight ........3400 LB Flaps ........Up (0%) • C.G........... Noted Bank Angle........15° • Power..........Idle C.G........Forward • Bank Angle ....... Noted Stall Speed..71 KIAS | 70 KCAS •...
Page 131: Wind Components
Cirrus Design Section 5 SR22 Performance Data Wind Components Conditions: Example: • Runway Heading ......10° Wind/Flight Path Angle ....50° • Wind Direction.......60° Crosswind Component ..12 Knots • Wind Velocity......15 Knots Headwind Component..10 Knots • Note • • The maximum demonstrated crosswind is 20 knots. Value not considered limiting.
Page 132: Takeoff Distance
Section 5 Cirrus Design Performance Data SR22 Takeoff Distance Conditions: Example: • Winds.......... Zero Outside Air Temp ....... 20°C • Runway....Dry, Level, Paved Weight........3400 LB • Flaps........... 50% Pressure Altitude....2000 FT • Power.......Full Throttle Headwind ........Zero •...
Page 133 Cirrus Design Section 5 SR22 Performance Data Takeoff Distance WEIGHT = 3400 LB Headwind: Subtract 10% for each 12 Speed at Liftoff = 73 KIAS knots headwind. Speed over 50 Ft. Obstacle = 78 KIAS Tailwind: Add 10% for each 2 knots Flaps - 50% ·...
Page 134: Takeoff Distance
Section 5 Cirrus Design Performance Data SR22 Takeoff Distance WEIGHT = 2900 LB Headwind: Subtract 10% for each 12 Speed at Liftoff = 70 KIAS knots headwind. Speed over 50 Ft Obstacle = 74 KIAS Tailwind: Add 10% for each 2 knots Flaps - 50% ·...
Page 135: Takeoff Climb Gradient
Cirrus Design Section 5 SR22 Performance Data Takeoff Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ...... Set per Placard Weight ........3400 LB • Flaps ........... 50% Pressure Altitude ....4000 FT •...
Page 136: Takeoff Rate Of Climb
Section 5 Cirrus Design Performance Data SR22 Takeoff Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 10° C • Mixture.......Set per Placard Weight........3400 LB • Flaps........... 50% Pressure Altitude....6000 FT • Airspeed ....Best Rate of Climb Climb Airspeed.....
Page 137: Enroute Climb Gradient
Cirrus Design Section 5 SR22 Performance Data Enroute Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ......... Full Rich Weight ........3400 LB • Flaps ........0% (UP) Pressure Altitude ....4000 FT •...
Page 138: Enroute Rate Of Climb
Section 5 Cirrus Design Performance Data SR22 Enroute Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 10° C • Mixture......As Required Weight........3400 LB • Flaps........0% (UP) Pressure Altitude....6000 FT • Airspeed ....Best Rate of Climb Climb Airspeed.....
Page 139: Enroute Rate Of Climb Vs Density Altitude
Cirrus Design Section 5 SR22 Performance Data Enroute Rate of Climb Vs Density Altitude Conditions: • Power ....................Full Throttle • Mixture ......... Per Schedule - Section 4, Max Power Fuel Flow • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb...
Page 140: Time, Fuel And Distance To Climb
Section 5 Cirrus Design Performance Data SR22 Time, Fuel and Distance to Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ......ISA • Mixture..Per Schedule, Section 4 Weight........3400 LB • Fuel Density..... 6.0 LB/GAL Airport Press ......1000 FT •...
Page 141: Cruise Performance
Cirrus Design Section 5 SR22 Performance Data Cruise Performance Conditions: Example: • Mixture ......Best Power Outside Air Temp ....29° C • Cruise Weight......2900 LB RPM ......2700 RPM • Winds ..........Zero Cruise Press Alt....8000 FT Note: Subtract 10 KTAS if nose wheel pant and fairing removed.
Page 142 Section 5 Cirrus Design Performance Data SR22 Cruise Performance 8000 Feet Pressure Altitude ISA - 30° C (-31° C) ISA (-1° C) ISA + 30° C (29° C) KTAS KTAS KTAS 2700 21.7 19.7 18.6 17.7 2600 21.7 18.8 17.8 17.0...
Page 143: Cruise Performance
Cirrus Design Section 5 SR22 Performance Data Cruise Performance 16,000 Feet Pressure Altitude ISA - 30° C (-47° C) ISA (-17° C) ISA + 30° C (13° C) KTAS KTAS KTAS 2700 15.8 14.5 13.7 13.0 2600 15.8 13.8 13.1 12.5...
Page 144: Range / Endurance Profile
Section 5 Cirrus Design Performance Data SR22 Range / Endurance Profile Conditions: Example: • Weight ........3400 LB Power Setting ......75% • Temperature ....Standard Day Takeoff Press Alt ....2000 FT • Winds.......... Zero Cruise Press Alt ....6000 FT •...
Page 145: Range / Endurance Profile
Cirrus Design Section 5 SR22 Performance Data Range / Endurance Profile 65% POWER Mixture = Best Power Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 70.8 15.4 10.3 2000 69.0 15.4 10.5...
Page 146 Section 5 Cirrus Design Performance Data SR22 Range / Endurance Profile 55% POWER Mixture = Best Economy Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 70.8 11.3 13.1 2000 69.0 11.3 13.4...
Page 147: Balked Landing Climb Gradient
Cirrus Design Section 5 SR22 Performance Data Balked Landing Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ...... Set per Placard Weight ........3400 LB • Flaps ........ 100% (DN) Pressure Altitude ....4000 FT •...
Page 148: Balked Landing Rate Of Climb
Section 5 Cirrus Design Performance Data SR22 Balked Landing Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 20° C • Mixture.......Set per Placard Weight........3400 LB • Flaps.........100% (DN) Pressure Altitude....4000 FT • Climb Airspeed ......V Climb Airspeed.....
Page 149: Landing Distance
Cirrus Design Section 5 SR22 Performance Data Landing Distance Conditions: Example: • Winds ..........Zero Outside Air Temp ......10°C • Runway ....Dry, Level, Paved Weight ........3400 LB • Flaps......... 100% Pressure Altitude ....2000 FT • Power ....3° Power Approach Headwind ........
Page 150 Section 5 Cirrus Design Performance Data SR22 Landing Distance WEIGHT = 3400 LB Headwind: Subtract 10% for each 13 Speed over 50 Ft Obstacle = 77 KIAS knots headwind. Flaps - 100%· Idle · Dry, Level Paved Surface Tailwind: Add 10% for each 2 knots tailwind up to 10 knots.
Page 151 Cirrus Design Section 6 SR22 Weight and Balance Section 6 Weight and Balance Table of Contents Introduction ..................6-3 Airplane Weighing Form ..............6-6 Airplane Weighing Procedures ............6-7 Weight & Balance Record ............. 6-10 Loading Instructions ..............6-12 Center of Gravity Limits ..............6-14 Weight &...
Page 152 Section 6 Cirrus Design Weight and Balance SR22 Intentionally Left Blank Information Manual March 2010...
Page 153: Introduction
Cirrus Design Section 6 SR22 Weight & Balance Introduction This section describes the procedure for establishing the basic empty weight and moment of the airplane. Sample forms are provided for reference. Procedures for calculating the weight and moment for various operations are also provided. A comprehensive list of all equipment available for this airplane is included at the back of this section.
Page 154 Section 6 Cirrus Design Weight & Balance SR22 WATER LINE (WL) 350.2 165.5 222.0 100.0 150.0 55.6 38.3 WL 100.0 NOTE Reference datum located at 50.0 fuselage station 0.0. (FS) 157.5 FUSELAGE STATION LEMAC BUTTOCK LINE (BL) FS 133.1 230.0 RBL 229.5...
Page 155 Cirrus Design Section 6 SR22 Weight & Balance Spirit Level LONGITUDINAL LEVELING Spirit Level Straight Edge Straight Edge Straight Edge Spacer Spacer Block Block Door Sill Door Sill LATERAL LEVELING SR22_FM06_1440A Figure 6-2 Airplane Leveling Information Manual March 2010...
Page 156: Airplane Weighing Form
Section 6 Cirrus Design Weight & Balance SR22 Airplane Weighing Form REF DATUM FS 0.0 FS 100.0 FS 145.0 WL 100.0 A = x + 100 B = A - y y = ____________ Measured x = ____________ Measured SR22_FM06_1441...
Page 157: Airplane Weighing Procedures
Cirrus Design Section 6 SR22 Weight & Balance Airplane Weighing Procedures A basic empty weight and center of gravity were established for this airplane when the airplane was weighed just prior to initial delivery. However, major modifications, loss of records, addition or relocation of...
Page 158 Section 6 Cirrus Design Weight & Balance SR22 4. Measuring (Figure 6-3): a. Obtain measurement ‘x’ by measuring horizontally along the airplane center line (BL 0) from a line stretched between the main wheel centers to a plumb bob dropped from the forward side of the firewall (FS 100).
Page 159 Cirrus Design Section 6 SR22 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.
Page 160: Weight & Balance Record
Section 6 Cirrus Design Weight & Balance SR22 Weight & Balance Record Use this form to maintain a continuous history of changes and modifications to airplane structure or equipment affecting weight and balance: Serial Num: Reg. Num: Page Item Weight Change...
Page 161 Cirrus Design Section 6 SR22 Weight & Balance 49.3" 39.8" Fuselage Station 49.7" 38.5" 25.0" 16.0" 20.0" 10.5" 32.0" 39.0" 33.4" 20.0" 33.3" 5.0" 21.0" CABIN DOOR BAGGAGE DOOR OPENING OPENING SR22_FM06_1019 Location Length Width Height Volume Cabin 122” 49.3”...
Page 162: Loading Instructions
Section 6 Cirrus Design Weight & Balance SR22 Loading Instructions It is the responsibility of the pilot to ensure that the airplane is properly loaded and operated within the prescribed weight and center of gravity limits. The following information enables the pilot to calculate the total weight and moment for the loading.
Page 163 Cirrus Design Section 6 SR22 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). Information Manual...
Page 164: Center Of Gravity Limits
Section 6 Cirrus Design Weight & Balance SR22 Center of Gravity Limits The charts below depict the airplane center-of-gravity envelope in terms of inches aft of the reference datum and as a percentage of the Mean Aerodynamic Cord (MAC). The relationship between the two is detailed in the weighing instructions.
Page 165: Weight & Balance Loading Form
Cirrus Design Section 6 SR22 Weight & Balance Weight & Balance Loading Form Serial Num: ________________ Date: ________________________ Reg. Num: _________________ Initials: ______________________ Weight Moment/ Item Description 1000 Basic Empty Weight Includes unusable fuel & full oil Front Seat Occupants Pilot &...
Page 166: Loading Data
Section 6 Cirrus Design Weight & Balance SR22 Loading Data Use the following chart or table to determine the moment/1000 for fuel and payload items to complete the Loading Form. Fuel Fwd Pass Loading Chart Aft Pass Baggage 0.00 20.0 40.0...
Page 167: Moment Limits
Cirrus Design Section 6 SR22 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 are within limits. • Caution • Before landing, verify aircraft weight and moment do not fall in the Landing Limitation Zone.
Page 168: Equipment List
Section 6 Cirrus Design Weight & Balance SR22 Equipment List This list will be determined after the final equipment has been installed in the aircraft. 6-18 Information Manual March 2010...
Page 169 Cirrus Design Section 7 SR22 Airplane Description Section 7 Airplane and Systems Description Table of Contents Introduction ..................7-5 Airframe ..................7-6 Fuselage ..................7-6 Wings................... 7-6 Empennage ................. 7-7 Flight Controls ................. 7-8 Elevator System................7-8 Aileron System................7-10 Rudder System ................
Page 170 Section 7 Cirrus Design Airplane Description SR22 Baggage Compartment..............7-36 Seats..................7-36 Windshield and Windows............7-37 Cabin Safety Equipment ............7-38 Engine ...................7-41 Engine Oil System ..............7-41 Engine Cooling................7-42 Engine Fuel Injection ..............7-42 Engine Air Induction System............7-42 Engine Fuel Ignition ..............7-42 Engine Exhaust................7-43 Engine Controls .................7-43 Alternate Air Control..............7-44...
Page 171 Section 7 Cirrus Design Airplane Description SR22 Instrument Lights ............... 7-75 Panel Flood Lights ..............7-75 Reading Lights................7-75 Overhead Dome Light..............7-75 Environmental System ..............7-76 Description and Operation ............7-76 Description and Operation ............7-79 Pitot-Static System................ 7-82 Pitot Heat Switch ...............
Page 172 Section 7 Cirrus Design Airplane Description SR22 Intentionally Left Blank Information Manual March 2010...
Page 173: Introduction
Cirrus Design Section 7 SR22 Airplane Description Introduction This section provides a basic description and operation of the standard airplane and its systems. Optional equipment described within this section is identified as optional. • Note • Some optional equipment, primarily avionics, may not be described in this section.
Page 174: Airframe
SR22 Airframe Fuselage The SR22 monocoque fuselage is constructed primarily of composite materials and is designed to be aerodynamically efficient. The cabin area is bounded on the forward side by the firewall at fuselage station 100, and on the rear by the aft baggage compartment bulkhead at fuselage station 222.
Page 175: Empennage
Cirrus Design Section 7 SR22 Airplane Description fuselage. The main wing spar passes under the fuselage below the two front seats and is attached to the fuselage in two locations. The rear shear webs are attached to the fuselage sidewalls just aft of the rear seats.
Page 176: Flight Controls
Airplane Description SR22 Flight Controls The SR22 uses conventional flight controls for ailerons, elevator and rudder. The control surfaces are pilot controlled through either of two single-handed side control yokes mounted beneath the instrument panel. The location and design of the control yokes allow easy, natural use by the pilot.
Page 177 Cirrus Design Section 7 SR22 Airplane Description SR22_FM07_1461 Figure 7-1 Elevator Control System Information Manual March 2010...
Page 178: Aileron System
Section 7 Cirrus Design Airplane Description SR22 Aileron System The ailerons provide airplane roll control. The ailerons are of conventional design with skin, spar and ribs manufactured of aluminum. Each aileron is attached to the wing shear web at two hinge points.
Page 179 Cirrus Design Section 7 SR22 Airplane Description SR22_FM07_1462 Figure 7-2 Aileron Control System Information Manual 7-11 March 2010...
Page 180: Rudder System
Control Locks The Cirrus SR22 control system is not equipped with gust locks. The trim spring cartridges have sufficient power to act as a gust damper without rigidly locking the position.
Page 181 Cirrus Design Section 7 SR22 Airplane Description SR22_FM07_1463 Figure 7-3 Rudder Control System Information Manual 7-13 March 2010...
Page 182: Trim Systems
Section 7 Cirrus Design Airplane Description SR22 Trim Systems Roll and pitch trim are provided by adjusting the neutral position of a compression spring cartridge in each control system by means of an electric motor. The electric roll trim is also used by the autopilot to position the ailerons.
Page 183: Yaw Trim System
Cirrus Design Section 7 SR22 Airplane Description Yaw Trim System Yaw trim is provided by spring cartridge attached to the rudder pedal torque tube and console structure. The spring cartridge provides a centering force regardless of the direction of rudder deflection. The yaw trim is ground adjustable only.
Page 184: Flight Deck Arrangement
A large color multifunction display is located between the flight instruments and the engine instruments. Temperature controls are located on the right side below the engine instruments. The SR22 uses standard flight instruments arranged in the 'basic-six' pattern. They include: Airspeed Indicator Attitude Gyro...
Page 185: Center Console
Cirrus Design Section 7 SR22 Airplane Description Serials 0435 and subsequent with PFD: The airplane is equipped with an Avidyne FlightMax Entegra-Series Primary Flight Display (PFD). The PFD is a 10.4” landscape-oriented display intended to be the primary display of primary flight parameter information (attitude, airspeed, heading, and altitude) to the pilot.
Page 186 Section 7 Cirrus Design Airplane Description SR22 LO HI TRIM TURN COORDINATOR 2 MIN Legend 1. Flight Instrument Panel 18. Rudder Trim Switch/Indicator 11. Conditioned Air Outlet 2. Annunciator Panel 19. Avionics Panel 12. Rudder Pedals 3. Overhead Light & Switch 20.
Page 187 Cirrus Design Section 7 SR22 Airplane Description FASTEN SEATBELTS NO SMOKING ALTITUDE GPH 16000 12000 8000 4000 MAX POWER FUEL FLOWS AMMETER SELECT ALT 1 ALT 2 BATT ALT AIR PULL ON ALT STATIC SOURCE NORMAL PARK BRAKE PULL ON...
Page 188 Section 7 Cirrus Design Airplane Description SR22 ALT AIR PULL ON ALT STATIC SOURCE NORMAL PARK BRAKE PULL ON FUEL L L L Legend 1. Start/Ignition Key Switch 9. Temperature/Ventilation Controls 18. Left Side Console 2. Annunciator Panel · Circuit Breaker Panel 10.
Page 189: Flight Instruments
Cirrus Design Section 7 SR22 Airplane Description Flight Instruments • Note • For additional information on instrument limit markings, refer to Section 2, Limitations. Primary Flight Display - Serials 0435 and Subsequent The Primary Flight Display (PFD) provides the functions of the attitude...
Page 190 Section 7 Cirrus Design Airplane Description SR22 PFD 2 MAIN BUS 2 PFD 1 ESSENTIAL BUS #1 GNS-430 PITOT STATIC Avidyne PFD #2 GNS-430 OAT Sensor / Magnetometer Data Aquisition Unit Flight Director System (Optional) STEC System 55x Autopilot Avidyne MFD...
Page 191 Cirrus Design Section 7 SR22 Airplane Description Attitude Direction Indicator (ADI) Air Data The airspeed tape to the left of the main ADI begins indicating at 20 Knots Indicated Airspeed (KIAS) and is color-coded to correspond with airspeeds for V , and V .
Page 192: Primary Flight Display
Section 7 Cirrus Design Airplane Description SR22 13 14 AP RDY 24.0 M-BUS 4900 FT 24.0 E-BUS 5000 4900 4700 Power 4600 29.92" Hdg Bug 037°/ 7 108.10 VLOC 1 005° CRS 020° Alt Bug Bearing DTK 020° 4900 FT GPS 1 62.2 NM...
Page 193 Cirrus Design Section 7 SR22 Airplane Description Horizontal Situation Indicator (HSI) Heading Data Magnetic heading is represented in boxed numeric form at the top of the compass rose. Heading rate (Rate of Turn Indicator) takes the form of a blue arcing arrow that begins behind the magnetic heading indicator and moves left or right accordingly.
Page 194: Attitude Indicator
Section 7 Cirrus Design Airplane Description SR22 Attitude Indicator • Note • Serials 0435 and subsequent with PFD: The attitude indicator is mounted on the LH bolster panel. The attitude indicator gives a visual indication of flight attitude. Bank attitude is indicated by a pointer at the top of the indicator relative to the bank scale with index marks at 10°, 20°, 30°, 60°, and 90°...
Page 195: Vertical Speed Indicator
Cirrus Design Section 7 SR22 Airplane Description temperature correction is set in the correction window. A knob in the lower left corner of the instrument is used to rotate the pressure altitude scale in the correction window to align the current pressure altitude with the outside air temperature.
Page 196: Turn Coordinator
Section 7 Cirrus Design Airplane Description SR22 (mb). The barometric altimeter settings are input through the barometric adjustment knob at the lower left of the instrument. Turn Coordinator • Note • Serials 0435 and subsequent with PFD: Turn Coordinator function and roll data display is integrated into the PFD.
Page 197: Horizontal Situation Indicator
Cirrus Design Section 7 SR22 Airplane Description the azimuth card to the desired bearing. 28 VDC for lighting is supplied through the 2-amp INST LIGHTS circuit breaker on Main Bus 1. Serials with Avionics Configuration B - 0002 through 1601, 1603...
Page 198 Section 7 Cirrus Design Airplane Description SR22 autopilot to allow NAV/LOC/GPS course tracking or to track a preset heading. The HSI incorporates conventional warning flags. The HDG (Heading) flag will be out of view whenever the instrument is receiving sufficient electrical power for operation.
Page 199: Magnetic Compass
Cirrus Design Section 7 SR22 Airplane Description Up to two bearing pointers can be displayed and switched to any NAV receiver including GPS1, GPS2, NAV1, or NAV2. GPS2 and NAV2 can only be displayed as bearing pointers, not as a primary navigation source.
Page 200: Wing Flaps
Section 7 Cirrus Design Airplane Description SR22 Wing Flaps The electrically controlled, single-slotted flaps provide low-speed lift enhancement. Each flap is manufactured of aluminium and connected to the wing structure at three hinge points. Rub strips are installed on the top leading edge of each flap to prevent contact between the flap and wing flap cove.
Page 201 Cirrus Design Section 7 SR22 Airplane Description SR22_FM07_1460 Figure 7-7 Wing Flaps Information Manual 7-33 March 2010...
Page 202: Landing Gear
Section 7 Cirrus Design Airplane Description SR22 Landing Gear Main Gear The main landing gear are bolted to composite wing structure between the wing spar and shear web. The landing gear struts are constructed of composite material for fatigue resistance. The composite construction is both rugged and maintenance free.
Page 203 Cirrus Design Section 7 SR22 Airplane Description DEFROST AIR OUTLETS STALL WARNING HORN FIRE EXTINGUISHER (UNDER PILOT'S SEAT) OVERHEAD LIGHT AND SWITCH DOOR HANDLE EGRESS HAMMER (IN ARMREST) CABIN SPEAKER PASSENGER FRESH AIR OUTLET OVERHEAD LIGHT AND SWITCH TIEDOWN LOOPS...
Page 204: Baggage Compartment
Section 7 Cirrus Design Airplane Description SR22 Baggage Compartment The baggage compartment door, located on the left side of the fuselage aft of the wing, allows entry to the baggage compartment. The baggage door is hinged on the forward edge and latched on the rear edge.
Page 205: Windshield And Windows
Cirrus Design Section 7 SR22 Airplane Description adjusted through the seat position control located below the forward edge of the seat cushion. The seat track is angled upward for forward travel so that shorter people will be positioned slightly higher as they adjust the seat forward.
Page 206: Cabin Safety Equipment
Section 7 Cirrus Design Airplane Description SR22 Cabin Safety Equipment Passenger Restraints Integrated seat belt and shoulder harness assemblies with inertia reels are provided for the pilot and each passenger. The rear seat belts are attached to fittings on the floorboard and the forward seat belts are attached to the seat frame.
Page 207 Cirrus Design Section 7 SR22 Airplane Description 2. Hold the buckle and firmly insert the link. 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.
Page 208 Section 7 Cirrus Design Airplane Description SR22 • WARNING • Halon gas used in the fire extinguisher can be toxic, especially in a closed area. After discharging fire extinguisher, ventilate cabin by opening air vents and unlatching door. Close vents and door after fumes clear.
Page 209: Engine
SR22 Airplane Description Engine The SR22 is powered by a Teledyne Continental IO-550-N, six- cylinder, normally aspirated, fuel-injected engine rated to 310 hp at 2700 RPM. The engine has a 2000-hour Time Between Overhaul (TBO). Dual, conventional magnetos provide ignition.
Page 210: Engine Cooling
Section 7 Cirrus Design Airplane Description SR22 Engine Cooling Engine cooling is accomplished by discharging heat to the oil and then to the air passing through the oil cooler, and by discharging heat directly to the air flowing past the engine. Cooling air enters the engine compartment through the two inlets in the cowling.
Page 211: Engine Exhaust
Cirrus Design Section 7 SR22 Airplane Description right spark plugs. Normal operation is conducted with both magnetos, as more complete burning of the fuel-air mixture occurs with dual ignition. Engine Exhaust Engine exhaust gases are routed through a tuned exhaust system.
Page 212: Alternate Air Control
Engine Indicating The SR22 is equipped with engine instrumentation and warning lights to monitor the engine performance. • Note • For additional information on instrument limit markings, refer to Section 2, Limitations.
Page 213 Cirrus Design Section 7 SR22 Airplane Description Serials 0002 through 1601, 1603 through 1643 and 1645 through 1662: The engine instruments are located on the right side of the instrument panel and the oil temperature/pressure warning light is located in the annunciator panel immediately in front of the pilot.
Page 214 Section 7 Cirrus Design Airplane Description SR22 FUEL Start / Ignition Switch Serials 0002 thru 0434: Controls Switch is located on the left bolster panel. Alternate Air Control Serials 0002 thru 1601, LEGEND 1603 thru 1643, 1645 thru 1662. 1. Power Lever 6.
Page 215 Cirrus Design Section 7 SR22 Airplane Description LOW VOLTS FUEL PITOT HEAT ALT 1 ALT 2 Annunciator Panel Primary Flight Display 4,9,8 LEGEND 4. Tachometer Multifunction Display 5. EGT ( shown w ith EM ax ) 6. CHT (shown with EMax) 7.
Page 216 Section 7 Cirrus Design Airplane Description SR22 Tachometer Serials 0002 through 1601, 1603 through 1643 and 1645 through 1662: A 2¼” tachometer is mounted on the right instrument panel adjacent to the other engine instruments. The tachometer pointer sweeps a scale marked from 0 to 3500 RPM in 100 RPM increments.
Page 217 Cirrus Design Section 7 SR22 Airplane Description signal from a temperature sensor mounted in the #6 cylinder head on the left side of the engine. Serials 1602, 1644, 1663 and subsequent: Exhaust Gas Temperature (EGT) and Cylinder Head Temperature (CHT) readings are displayed on the MFD as vertical bars that ascend and descend respective to increasing and decreasing temperatures.
Page 218 Section 7 Cirrus Design Airplane Description SR22 The Oil Pressure pointer sweeps a scale marked from 0 psi to 100 psi. The Oil Pressure indicator receives a pressure signal from an oil pressure sensor mounted at the aft end of the engine below the oil cooler.
Page 219 Cirrus Design Section 7 SR22 Airplane Description tachometer. The indicator is internally lighted. 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.
Page 220 Section 7 Cirrus Design Airplane Description SR22 28 VDC for the digital instrument operation is supplied through the 2- amp ANNUN / ENGINE INST circuit breaker on the Essential Bus. Oil Warning Light The red OIL warning light in the annunciator panel comes on to indicate either high oil temperature or low oil pressure.
Page 221: Propeller
Cirrus Design Section 7 SR22 Airplane Description Propeller The airplane is equipped with a constant-speed, aluminum-alloy propeller with a three-blade (78" diameter) propeller and governor. The propeller governor automatically adjusts propeller pitch to regulate propeller and engine RPM. The propeller governor senses...
Page 222: Fuel System
Section 7 Cirrus Design Airplane Description SR22 Fuel System An 81-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 42-gallon capacity (40.5- 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.
Page 223 Cirrus Design Section 7 SR22 Airplane Description ANNUNCIATOR FUEL FUEL QUANTITY VENT VENT FILLER FILLER INDICATOR L. WING TANK R. WING TANK R. WING L. WING COLLECTOR COLLECTOR SELECTOR VALVE FLAPPER FLAPPER VALVE VALVE DRAIN FIREWALL (5 PLACES) SELECTOR VALVE...
Page 224: Fuel Selector Valve
Section 7 Cirrus Design Airplane Description SR22 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 23.5 gallons usable in each tank (47 gallons total usable in all flight conditions).
Page 225: Fuel Quantity Indicator
Cirrus Design Section 7 SR22 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 41 U.S.
Page 226 Section 7 Cirrus Design Airplane Description SR22 Serials 0002 thru 1601, 1603 thru 1643, 1645 thru 1662. LEGEND 1. Fuel Pump Switch 2. Fuel Quantity Gage 3. Fuel Selector Valve 4. Fuel Flow SR22_FM07_2226 Figure 7-11 Fuel System Controls and Indicating (Sheet 1 of 2)
Page 227 Cirrus Design Section 7 SR22 Airplane Description LOW VOLTS FUEL PITOT HEAT ALT 1 ALT 2 Annunciator Panel Primary Flight Display LEGEND Multifunction Display 4. Fuel Flow 5. Fuel Used (EMax only) 6. Fuel Remaining (EMax only) 7. Time Remaining (EMax only) 8.
Page 228: Fuel Flow Indication
Section 7 Cirrus Design Airplane Description SR22 Fuel Flow Indication Serials 0002 through 1601, 1603 through 1643 and 1645 through 1662: Fuel flow indication is integral to the combination Fuel Flow/ Manifold Pressure Gage. Refer to preceding discussion on Fuel Flow and Manifold Pressure Gage for complete description of fuel flow indication.
Page 229: Boost Pump Switch
Cirrus Design Section 7 SR22 Airplane Description Boost Pump Switch Boost pump operation and engine prime is controlled through the Fuel Pump BOOST-PRIME switch located adjacent to the fuel selector valve. The PRIME position is momentary and the BOOST position is selectable.
Page 230: Brake System
Section 7 Cirrus Design Airplane Description SR22 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 brakes for parking.
Page 231 Cirrus Design Section 7 SR22 Airplane Description Parking Brake • Caution • Do not pull the PARK BRAKE knob in flight. If a landing is made with the parking brake valve set, the brakes will maintain any pressure applied after touchdown.
Page 232 Section 7 Cirrus Design Airplane Description SR22 RESERVOIR MIL-H-5606 FLUID ONLY RUDDER PEDAL(4) MASTER CYLINDER(4) PARKING PARKING BRAKE BRAKE VALVE KNOB CALIPER CALIPER ASSEMBLY ASSEMBLY ROTOR ROTOR (DISK) (DISK) SR22_FM07_1015 Figure 7-12 Brake System 7-64 Information Manual March 2010...
Page 233: Electrical System
Power Generation Primary power for the SR22 is supplied by a 28-VDC, negative-ground electrical system. The electrical power generation system consists of two alternators controlled by a Master Control Unit (MCU) mounted on the left side of the firewall and two batteries for starting and electrical power storage.
Page 234: Power Distribution
Distribution Bus unless ALT 2 fails. Power Distribution The power distribution system for the SR22 consists of the Main Distribution Bus and the Essential Distribution Bus in the MCU and associated buses in the Circuit Breaker panel. The circuit breaker panel is located on the left side of the console next to the pilots right knee.
Page 235 Cirrus Design Section 7 SR22 Airplane Description ALT 1 RELAY ALT 1 VOLT REG ALT 1 LANDING SWITCH 100A LIGHT EXTERNAL POWER LANDING LIGHT SWITCH 125A BAT 1 BAT 1 SWITCH STARTER ALT 2 VOLT REG FUEL VOLTS PITOT ALT 1...
Page 236: Bat & Alt Master Switches
Section 7 Cirrus Design Airplane Description SR22 BAT & ALT Master Switches The rocker type electrical system MASTER switches are ON in the up position and OFF in the down position. The switches, labeled BAT 2, BAT 1, ALT 1, ALT 2 are located in the bolster switch panel immediately below the instrument panel.
Page 237: Avionics Power Switch
Cirrus Design Section 7 SR22 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.
Page 238 Section 7 Cirrus Design Airplane Description SR22 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.
Page 239: Ammeter Select Switch
Cirrus Design Section 7 SR22 Airplane Description Ammeter Select Switch Serials 0002 through 1601, 1603 through 1643 and 1645 through 1662: 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.
Page 240: Circuit Breakers And Fuses
Section 7 Cirrus Design Airplane Description SR22 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.
Page 241: Ground Service Receptacle
Cirrus Design Section 7 SR22 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.
Page 242: Exterior Lighting
Section 7 Cirrus Design Airplane Description SR22 Exterior Lighting The airplane is equipped with standard wing tip navigation lights with integral anti-collision strobe lights. The separately controlled landing light is located in the lower cowl. Navigation Lights The airplane is equipped with standard wing tip navigation lights. The lights are controlled through the NAV light switch on the instrument panel bolster.
Page 243: Instrument Lights
Cirrus Design Section 7 SR22 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.
Page 244: Environmental System
Section 7 Cirrus Design Airplane Description SR22 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 heater muff (heat exchanger) around the right engine exhaust muffler, fresh air inlets(s),...
Page 245 Cirrus Design Section 7 SR22 Airplane Description AIR INLET HEAT EXCHANGER HVAC CABIN HEAT/ PLENUM HEAT DEFROST SELECT TEMP. CONTROL COLD WINDSHIELD DEFROST DIFFUSER AIR GASPER FRESH AIR FRESH AIR INTAKE INTAKE FOOT-WARMER DIFFUSER CONDITIONED FRESH AIR MECHANICAL SR22_FM07_1012B CONNECTION...
Page 246 Section 7 Cirrus Design Airplane Description SR22 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.
Page 247 Cirrus Design Section 7 SR22 Airplane Description Description and Operation -Serials 1602, 1821, 1840, 1863 & 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...
Page 248 Section 7 Cirrus Design Airplane Description SR22 VENTS INLET HEAT EXCHANGER TEMPERATURE WINDSHIELD AIRFLOW HOT AIR DIFFUSER VALVE PANEL AIRFLOW FLOOR AIRFLOW DISTRIBUTION MANIFOLD AIR GASPER AIR MIXING PLENUM FRESH AIR INTAKE FRESH AIR VALVE FOOT-WARMER ASSEMBLY DIFFUSER NOTE: Illustration depicts maximum...
Page 249 Cirrus Design Section 7 SR22 Airplane Description When the selector is in the far right position, the cabin floor butterfly valve is closed providing maximum airflow to the windshield diffuser. Temperature Selection The temperature selector is mechanically linked to the hot air valve and fresh air intake valve.
Page 250: Pitot-Static System
Section 7 Cirrus Design Airplane Description SR22 Pitot-Static System The Pitot-Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage. The Pitot heat is pilot controlled through a panel-mounted switch. An internally mounted alternate static pressure source provides backup static pressure should that the primary static source becomes blocked.
Page 251 Cirrus Design Section 7 SR22 Airplane Description Serials 0002 thru 0434 ,0435 Serials 0435 & subs w/ PFD. thru 0820 w/o PFD. PRIMARY FLIGHT DISPLAY AIRSPEED VERTICAL SPEED INDICATOR INDICATOR ALTIMETER ALTITUDE ENCODER ALTITUDE TRANSDUCER ALTERNATE (OPTIONAL) STATIC AIR SOURCE...
Page 252: Alternate Static Source
Section 7 Cirrus Design Airplane Description SR22 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...
Page 253: Standard Avionics
Airplane Description Standard Avionics The following paragraphs and equipment descriptions describe all standard avionic installations offered for the SR22. The avionics navigation and communication equipment are mounted in the center console and are easily accessible from either pilot seat. For detailed descriptions of specific avionic equipment, operating...
Page 254: Multi-Function Display
Section 7 Cirrus Design Airplane Description SR22 • Two VHF Communications Transceivers (Garmin GNS 430) • Two Navigation (VOR/LOC/GS) Receiver (GNS 430) • Mode C Transponder with Altitude Encoder (Garmin GTX 327) • Electronic Navigation Display (Sandel SN3308) • Course Deviation Indicator...
Page 255 Cirrus Design Section 7 SR22 Airplane Description • Generate and display a moving map based on GPS position data with obstacle and terrain data. • Display Stormscope lightning strike bearing and distance. • Display Skywatch traffic advisory information. (EX5000C only) •...
Page 256: Autopilot
Section 7 Cirrus Design Airplane Description SR22 Autopilot Serials with Avionics Configuration A - 0002 through 1601, 1603 through 1643 and 1645 through 1662 without PFD: These airplanes are equipped with an S-TEC System Thirty Autopilot with GPSS. This airplane is equipped with an S-TEC System Thirty Autopilot.
Page 257 The SR22 installation of the S-Tec System 55X Autopilot features: • Heading Hold and Command; • NAV/LOC/GPS/GS tracking, high and low sensitivity, and automatic 45°...
Page 258 Section 7 Cirrus Design Airplane Description SR22 autopilot mode, full guidance is provided, including smooth transitions to altitude and heading captures. If not in an active autopilot mode (i.e., “hand-flying”), there is no guidance other than the position of the appropriate bugs, as set by the pilot.
Page 259: Gps Navigation
Cirrus Design Section 7 SR22 Airplane Description • NAV Mode • GPSS (GPS Steering) Mode The following three modes of the System 55SR are supported by the Entegra PFD: • ALT (Altitude Hold) Mode • HDG (Heading Capture/Hold Mode) • NAV Mode 28 VDC for autopilot and altitude selector/alerter is supplied through the 5-amp AUTOPILOT circuit breaker on the Essential Bus.
Page 260 Section 7 Cirrus Design Airplane Description SR22 longitude, and altitude) and the altitude encoder to enhance the altitude calculation. The GPS1 antenna is located above the headliner along the airplane centerline. The GPS2 antenna is located below the glareshield and behind the MFD.
Page 261: Communication (Com) Transceivers
Cirrus Design Section 7 SR22 Airplane Description 1 and 7.5-amp COM 1 circuit breakers on the Avionics Essential Bus. The secondary GPS navigator is powered by 28 VDC through the 5- amp GPS 2 and the 7.5-amp COM 2 circuit breaker on the Avionics Non-Essential Bus.
Page 262: Navigation (Nav) Receiver
Section 7 Cirrus Design Airplane Description SR22 Navigation (Nav) Receiver Serials with Avionics Configuration A - 0002 through 1601, 1603 through 1643 and 1645 through 1662 without PFD: The airplane is equipped with one NAV receiver integrated into the Garmin GNS 430 GPS Navigators (the GNS 420 does not incorporate a NAV receiver).
Page 263: Transponder
Cirrus Design Section 7 SR22 Airplane Description NAV 1 – The upper GARMIN GNS 430 is designated NAV 1. 28 VDC for navigation receiver operation is controlled through the Avionics Master Switch on the bolster switch panel and supplied through the 5- amp GPS1 circuit breaker on the Avionics Essential Bus row.
Page 264: Emergency Locator Transmitter
Section 7 Cirrus Design Airplane Description SR22 Headset/Microphone Installation The airplane is equipped with provisions for four noise-canceling headsets with integrated microphones. forward microphone-headsets use remote Push-To-Talk (PTT) switches located on the top of the associated control yoke grip. The rear headsets do not have COM transmit capabilities and do not require PTT switches.
Page 265 Cirrus Design Section 7 SR22 Airplane Description batteries contained within the transmitter unit power the ELT transmitter. The batteries must be replaced at specified intervals based upon the date appearing on the battery (refer to Airplane Maintenance Manual). ELT Remote Switch and Indicator Panel...
Page 266: Hour Meter(S)
Section 7 Cirrus Design Airplane Description SR22 Hour Meter(s) Serials 0002 through 1820, 1822 through 1839, and 1841 through 1862: The airplane is equipped with an hour meter located inside the armrest storage compartment between the pilot and copilot seats.
Page 267: Digital Clock
Cirrus Design Section 7 SR22 Airplane Description Digital Clock Serials 0002 through 0434; The airplane is equipped with a 2¼” Davtron M803 digital clock located on the left instrument panel immediately outboard of the airspeed indicator. The clock provides Universal Time (UT), Local Time (LT), Elapsed Time (ET), Outside Air Temperature (OAT) in C or F, and Voltmeter functions.
Page 268 Section 7 Cirrus Design Airplane Description SR22 2. Press Control to activate count-up timer. Elapsed time counts up to 59 minutes, 59 seconds, and then switches to hours and minutes. Pressing the Control button again will reset the timer to zero.
Page 269: Cirrus Airplane Parachute System
Airplane Description Cirrus Airplane Parachute System The SR22 is equipped with a Cirrus Airplane Parachute System (CAPS) designed to bring the aircraft and its occupants to the ground in the event of a life-threatening emergency. The system is intended to...
Page 270: Activation Handle
Section 7 Cirrus Design Airplane Description SR22 sequence the slider limits the initial diameter of the parachute and the rate at which the parachute inflates. As the slider moves down the suspension lines the canopy inflates. A three-point harness connects the airplane fuselage structure to the parachute.
Page 271: Deployment Characteristics
Cirrus Design Section 7 SR22 Airplane Description • Note • Jerking or rapidly pulling on the activation T-handle greatly increases the pull forces required to activate the rocket. Attempting to activate the rocket by pushing the activation T- handle forward and down limits the force that can be applied.
Page 272 Section 7 Cirrus Design Airplane Description SR22 forth or oscillate slightly as it hangs from the parachute. Descent rate is expected to be less than 1700 feet per minute with a lateral speed equal to the velocity of the surface wind. In addition, surface winds may continue to drag the aircraft after ground impact.
Page 273 Airworthiness Directives..............8-6 Airplane Inspection Periods ............8-6 Annual Inspection ................ 8-6 100-Hour Inspection ..............8-7 Cirrus Design Progressive Inspection Program ......8-7 Pilot Performed Preventative Maintenance ......... 8-8 Ground Handling ................8-10 Application of External Power ............ 8-10 Towing ..................8-11 Taxiing ..................
Page 274 Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Information Manual March 2010...
Page 275: Introduction
Introduction This section provides general guidelines for handling, servicing and maintaining your Cirrus Design SR22. In order to ensure continued safe and efficient operation of your airplane, keep in contact with your Authorized Cirrus Service Center to obtain the latest information pertaining to your aircraft.
Page 276 SR22 publications, revision service, service publication subscription service may be obtained by contacting Customer Service at Cirrus Design as follows: Cirrus Design Corporation Customer Service 4515 Taylor Circle Duluth, MN 55811 Phone: 218 727-2737 FAX: 218 727-2148 Make sure to include airplane serial number and owner’s name in all correspondence for accurate processing of your documentation needs.
Page 277: Airplane Records And Certificates
Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance Airplane Records and Certificates The Federal Aviation Administration (FAA) requires that certain data, certificates, and licenses be displayed or carried aboard the airplane at all times. Additionally, other documents must be made available upon request.
Page 278: Airworthiness Directives
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Airworthiness Directives The Federal Aviation Administration (FAA) publishes Airworthiness Directives (AD’s) that apply to specific aircraft and aircraft appliances or accessories. AD’s are mandatory changes and must be complied with within a time limit set forth in the AD. Operators should periodically check with Cirrus Service Centers or A&P mechanic to...
Page 279: 100-Hour Inspection
Progressive Inspection Program in accordance with the Federal Aviation Regulation Part 91.409. The Cirrus Design Progressive Inspection Program provides for the complete inspection of the airplane utilizing a five-phase cyclic inspection program. A total of eight inspections are accomplished over the course of 400 flight hours, with an inspection occurring every 50 flight hours.
Page 280: Pilot Performed Preventative Maintenance
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Pilot Performed Preventative Maintenance The holder of a Pilot Certificate issued under FAR Part 61 may perform certain preventive maintenance described in FAR Part 43, Appendix A. This maintenance may be performed only on an aircraft that the pilot owns or operates and which is not used in air carrier service.
Page 281 Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance • Replace any hose connection, except hydraulic connections, with replacement hoses. • Clean or replace fuel and oil strainers, as well as replace or clean filter elements. • Replace prefabricated fuel lines.
Page 282: Ground Handling
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Ground Handling Application of External Power A ground service receptacle, located just aft of the cowl on the left side of the airplane, permits the use of an external power source for cold weather starting and maintenance procedures.
Page 283: Towing
Cirrus Design Section 8 SR22 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.
Page 284: Taxiing
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Taxiing Before attempting to taxi the airplane, ground personnel should be instructed and authorized by the owner to taxi the airplane. Instruction should include engine starting and shutdown procedures in addition to taxi and steering techniques.
Page 285: Parking
Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance Parking The airplane should be parked to protect the airplane from weather and to prevent it from becoming a hazard to other aircraft. The parking brake may release or exert excessive pressure because of heat buildup after heavy braking or during wide temperature swings.
Page 286: Tiedown
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Tiedown The airplane should be moored for immovability, security and protection. FAA Advisory Circular AC 20-35C, Tiedown Sense, contains additional information regarding preparation for severe weather, tiedown, and related information. The following procedures should be used for the proper mooring of the airplane: 1.
Page 287: Jacking
Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance Jacking Two jacking points are provided: one at each wing tiedown. Jack points (pads) are stowed in the baggage compartment. The airplane may be jacked using two standard aircraft hydraulic jacks at the wing jacking points and a weighted tailstand attached to the tail tiedown.
Page 288: Servicing
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Servicing Landing Gear Servicing The main landing gear wheel assemblies use 15 x 6.00 x 6, six-ply rating tires and tubes. The nose wheel assembly uses a 5.00 x 5 four- ply rating, type III tire and tube. Always keep tires inflated to the rated pressure to obtain optimum performance and maximum service.
Page 289 Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance The aircraft should not be operated with overheated, damaged, or leaking brakes. Conditions include, but are not limited to: • Leaking brake fluid at the caliper. This can be observed by checking for evidence of fluid on the ground or deposited on the underside of the wheel fairing.
Page 290: Tire Inflation
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 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.
Page 291: Oil Servicing
Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance Oil Servicing The oil capacity of the Teledyne Continental IO-550-N engine is 8 quarts. It is recommended that the oil be changed every 50 hours and sooner under unfavorable operating conditions. The following grades...
Page 292 • Caution • MIL-C-6529, Type II straight mineral oil with corrosion preventive can cause coking with extended use and is not recommended by Cirrus Design for break-in or post break-in use. After 25 hours of operation and after oil consumption has stabilized,...
Page 293 Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance Product Supplier Aeroshell (R) W Shell Australia Aeroshell Oil W Shell Canada Ltd. Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50 Aeroshell Oil W Shell Oil Company Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50...
Page 294: Fuel System Servicing
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Fuel System Servicing Fuel Filtration Screen/Element Airplane serials 0002 thru 2709, 2710 thru 3420 after SB 2X-28-08 R1, and 3421 and subsequent; 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.
Page 295 Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance Do not fill tank within 100 feet (30.5 meters) of any energized electrical equipment capable of producing a spark. Permit no smoking or open flame within 100 feet (30.5 meters) of airplane or refuel vehicle.
Page 296: Fuel Contamination And Sampling
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 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.
Page 297: Draining Fuel System
The remainder of the fuel may be drained by opening the drain valves. Use the same precautions as when refueling airplane. Refer to the SR22 Maintenance Manual for specific procedures.
Page 298: Cleaning And Care
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Cleaning and Care Cleaning Exterior Surfaces • Caution • Airplane serials 0334 and subsequent with Ice Protection System; Do not wax leading edge porous panels. Refer to Section 9, Supplements for specific servicing information on the Ice Protection System.
Page 299 Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance Cleaning Product Cleaning Application Supplier Mild Dishwasher Soap Fuselage Exterior and Any Source (abrasive free) Landing Gear Pure Carnauba Wax Fuselage Exterior Any Source Mothers California Gold Fuselage Exterior Wal-Mart Stores Pure Carnauba Wax...
Page 300 Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Windscreen and Windows Before cleaning an acrylic window, rinse away all dirt particles before applying cloth or chamois. Never rub dry acrylic. Dull or scratched window coverings may be polished using a special acrylic polishing paste.
Page 301 Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance Engine Compartment Before cleaning the engine compartment, place a strip of tape on the magneto vents to prevent any solvent from entering these units. 1. Place a large pan under the engine to catch waste.
Page 302: Cleaning Interior Surfaces
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Cleaning Interior Surfaces Seats, carpet, upholstery panels, and headliners should be vacuumed at regular intervals to remove surface dirt and dust. While vacuuming, use a fine bristle nylon brush to help loosen particles.
Page 303 Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance Cleaning Product Cleaning Application Supplier Interior Windscreen and Prist Prist Aerospace Windows Optimax Display Screens PhotoDon Mild Dishwasher Soap Cabin Interior Any Source (abrasive free) Leather Care Kit Leather Upholstery Cirrus Design...
Page 304 Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Instrument Panel and Electronic Display Screens The instrument panel, control knobs, and plastic trim need only to be wiped clean with a soft damp cloth. The multifunction display, primary flight display, and other electronic display screens should be cleaned with Optimax - LCD Screen Cleaning Solution as follows: •...
Page 305 2. Wipe leather upholstery with a soft, damp cloth. 3. Soiled upholstery, may be cleaned with the approved products available from Cirrus Design. Avoid soaking or harsh rubbing. Carpets To clean carpets, first remove loose dirt with a whiskbroom or vacuum.
Page 306 Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Intentionally Left Blank 8-34 Information Manual March 2010...
Page 307 Supplements This section of the handbook contains FAA Approved Supplements necessary to safely and to efficiently operate the SR22 when equipped with optional systems or equipment not provided with the standard airplane or for special operations or not included in the handbook.
Page 308 Section 9 Cirrus Design Supplements SR22 Intentionally Left Blank Information Manual March 2010...
Page 309 12-15-07 ___ 13772-127 R1 Air Conditioning System 03-27-07 ___ 13772-129 R2 Hartzell Compact Series Propeller w/ Composite Blades 08-26-09 ___ 13772-130 R2 SR22 Airplanes Equipped with the “G3 Wing” 08-26-09 ___ 13772-131 R1 Artex ME406 406 MHz ELT System 05-13-08...
Page 310 This Log of Supplements shows all Cirrus Design Supplements available for the aircraft at the cooresponding 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.
Page 311 Includes Optional XM Radio System When the Garmin GMA 340 Audio Panel and the optional XM Radio System are installed in the Cirrus Design SR22, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook (Handbook).
Page 312 Section 9 Cirrus Design Supplements SR22 Section 1 - General This supplement provides detailed operating instructions for the Garmin GMA 340 Audio Selector Panel/Intercom System with internal Marker Beacon. This supplement covers the basic operating areas of the Audio Control Panel.
Page 313 Cirrus Design Section 9 SR22 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...
Page 314 Section 9 Cirrus Design Supplements SR22 A fail-safe circuit connects the pilot’s headset directly to the COM1 transceiver in the event of a power failure to the audio control panel or the panel is switched ‘OFF.’ Test Pressing the TEST button illuminates all Panel LEDs and the Marker Beacon Annunciators full bright.
Page 315 Cirrus Design Section 9 SR22 Supplements the copilot mic/audio source. The pilot has receive and transmit capabilities on COM1 and the copilot has receive and transmit capabilities on COM2. While split COM is active, simultaneous transmission from COM1 and COM2 is not possible.The pilot and copilot can still listen to COM3, NAV1, NAV2, DME, ADF, and MKR.
Page 316 Section 9 Cirrus Design Supplements SR22 The Audio Control Panel has provisions for up to two separate personal entertainment input (music) devices. These devices are plugged into the AUDIO INPUT jacks in the center console jack panels. Music1 is connected at the AUDIO INPUT jack near the convenience outlet.
Page 317 Cirrus Design Section 9 SR22 Supplements • Right Outer Knob – Copilot and passenger mic VOX level. CW rotation increases the amount of mic audio (VOX level) required to break squelch. Full CCW is the ‘hot mic’ position. Each microphone input has a dedicated VOX circuit to assure that only the active microphone(s) is/are heard when squelch is broken.
Page 318 Section 9 Cirrus Design Supplements SR22 button. ALL mode is active when neither PILOT or CREW have been selected. PILOT The pilot is isolated from the intercom. The pilot can hear radio and sidetone only during radio transmissions. Copilot and passengers can hear the intercom and music but not the airplane radio receptions or pilot transmissions.
Page 319 Cirrus Design Section 9 SR22 Supplements Marker beacon controls and lights are located at the extreme left of the Audio Control Panel. Marker beacon audio is selected by pressing the MKR push-button. If no marker beacon signal is being received, pressing the MKR push- button a second time deselects marker beacon audio.
Page 320 Section 9 Cirrus Design Supplements SR22 XM Radio System (Optional Installation) • Note • For a detailed operating instructions, refer to the XM Radio Wireless Controller User Instructions, Document XMC050-4, original release later. software partnumber 530-00162-000 or later is required for installation of XM Radio System.
Page 321 FAA Approved Airplane Flight Manual Supplement Garmin GTX 327 Transponder When a Garmin GTX 327 Transponder is installed in the Cirrus Design SR22, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook.
Page 322 Section 9 Cirrus Design Supplements SR22 Section 1 - General The airplane is equipped with a single Garmin GTX 327 ATC Mode A/ C (identification and altitude) transponder with squawk capability. This supplement provides complete operating instructions for the GTX 327 and does not require any additional data be carried in the airplane.
Page 323 Cirrus Design Section 9 SR22 Supplements Section 2 - Limitations No Change Section 3 - Emergency Procedures No Change Section 4 - Normal Procedures • Note • Expected coverage from the GTX 327 is limited to “line of sight.” Low altitude or aircraft antenna shielding by the airplane itself may result in reduced range.
Page 324 • Note • This supplement provides specific procedures for use of the GTX 327 Transponder in the SR22 and a general description of the unit. For a detailed description of the GTX 327, refer to GARMIN GTX 327 Mode A/C Transponder Pilots Guide, p/n 190-00187-00 Revision A (Feb 2000) or later revision.
Page 325 Cirrus Design Section 9 SR22 Supplements Mode Selector Keys The mode selector keys are located in a circular arrangement immediately to the left of the display window. The selected mode is annunciated at the left side of the display immediately adjacent to the selector keys.
Page 326 Section 9 Cirrus Design Supplements SR22 Code Selector Keys Code selection is accomplished by depressing the eight selector keys (numbered 0 - 7) located immediately below the display. Any of 4096 active identification codes can be selected. The selected code must be in accordance with instructions for IFR flight or rules applicable to transponder utilization for VFR flight.
Page 327 Cirrus Design Section 9 SR22 Supplements Reply Light The reply light is the small reverse video “R” immediately below the mode annunciation in the display window. The reply light will blink each time the transponder replies to ground interrogations. The light will remain on during the 18-second IDENT time interval.
Page 328 Section 9 Cirrus Design Supplements SR22 COUNT DOWN TIMER - The count down timer is controlled by the START / STOP key. The CRSR and “0 - 9” keys are used to set the initial time. Pressing the CLR key resets the timer to the initial value.
Page 329 Altitude Selector/Alerter When the S-Tec System Fifty Five X (55X) Autopilot with Altitude Selector / Alerter is installed in the Cirrus Design SR22, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot's Operating Handbook.
Page 330 The autopilot makes roll changes through the aileron trim motor and spring cartridge and makes pitch changes for altitude hold through the elevator trim motor. The SR22 installation of the S-Tec System 55X Autopilot features: • Heading Hold and Command;...
Page 331 Cirrus Design Section 9 SR22 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.
Page 332 Section 9 Cirrus Design Supplements SR22 b. The autopilot must be disconnect during approach if course deviation exceeds 50%. The approach should only be continued by “hand-flying” the airplane. c. The autopilot must be disengaged at the Decision Height. d. 12 knot maximum crosswind component between the missed approach point and outer marker.
Page 333 Cirrus Design Section 9 SR22 Supplements SR22_FM09_1502A Figure - 1 System 55X Altitude Selector/Alerter & Autopilot Computer P/N 13772-108 5 of 24 Revision 05: 08-15-07...
Page 334 SR22 Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the SR22 POH. Do not reengage the autopilot until the malfunction has been identified and corrected. The autopilot may be disconnected by: 1. Pressing the A/P DISC/Trim switch on the control yoke handle.
Page 335 Cirrus Design Section 9 SR22 Supplements System Failure and Caution Annunciations If any of the following failure annunciations occur at low altitude or during an actual instrument approach, disengage the autopilot, execute a go-around or missed approach as appropriate. Inform ATC of problem.
Page 336 Section 9 Cirrus Design Supplements SR22 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot and altitude selector and their respective modes. The Autopilot is integrated with the Altitude Selector/Alerter and can be operated with or without data inputs from the Altitude Selector/ Alerter.
Page 337 Cirrus Design Section 9 SR22 Supplements c. Rotate altitude selector input knob to set BARO to the nearest 0.1 inch Hg. d. Push ALT button to display ALT SEL. With a flashing SEL annunciator, rotate the selector knob to input an altitude 300 to 400 feet lower or higher than the indicated altitude.
Page 338 Section 9 Cirrus Design Supplements SR22 c. Altitude Hold ..............TEST 1.) Depress ALT button on autopilot programmer/computer. Note that ALT annunciator comes on, VS annunciator goes out, and yoke does not move. d. Overpower Test: 1.) Grasp control yoke and input left aileron, right aileron, nose up, and nose down to overpower autopilot.
Page 339 Cirrus Design Section 9 SR22 Supplements 3. Use HSI HDG bug to make heading changes as desired. Autopilot Altitude Hold Mode 1. Manually fly the airplane to the desired altitude and level off. • Note • For smoothest transition to altitude hold, the airplane rate of climb or descent should be less than 100 FPM when Altitude Hold is selected.
Page 340 Section 9 Cirrus Design Supplements SR22 3. Press the VS button on the autopilot programmer/computer to engage the vertical speed mode. When the mode is engaged, the autopilot will synchronize to and hold the vertical speed at the time the mode was engaged.
Page 341 Cirrus Design Section 9 SR22 Supplements 4. Press DTA again to accept altitude entry, the ENT annunciator will go out and the SEL annunciator will stop flashing and illuminate steady indicating that the system is in the ‘operate’ mode. • Note •...
Page 342 Section 9 Cirrus Design Supplements SR22 BARO Selection Upon initial start-up, the altitude selector enters BARO select immediately after the self-test if it is receiving a valid altitude signal. The setting can easily be entered at this time. At other times, it is necessary to select the DTA entry and BARO modes in order to adjust the BARO setting.
Page 343 Cirrus Design Section 9 SR22 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.
Page 344 Section 9 Cirrus Design Supplements SR22 intercept course in NAV mode or twice to intercept course in GPSS mode on the autopilot programmer/computer. When the on-course intercept turn begins the HDG mode will disengage and the annunciator will go out.
Page 345 Cirrus Design Section 9 SR22 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.
Page 346 Section 9 Cirrus Design Supplements SR22 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.
Page 347 Cirrus Design Section 9 SR22 Supplements HDG (Heading) Mode – When HDG is selected, the autopilot will engage the HDG mode, fly the airplane to, and hold the heading set on the HSI. Subsequent heading changes are made using the HDG knob on the HSI.
Page 348 Section 9 Cirrus Design Supplements SR22 GS (Glideslope) – The autopilot GS function will capture and track an ILS glideslope. To arm the GS function, the following conditions must be met: (1) the NAV receiver must be tuned to the appropriate ILS frequency;...
Page 349 Cirrus Design Section 9 SR22 Supplements Altitude Selector / Alerter The altitude selector / alerter provides the autopilot with an altitude preselect function, a programmable vertical speed function, as well as provides altitude alert, decision height alert, and baro corrected altitude display.
Page 350 Section 9 Cirrus Design Supplements SR22 DTA (Data) – The data entry button is used to select data entry mode. The first time the DTA button is pressed the selector will enter the data entry mode, the ENT annunciator will come on, and the SEL annunciator will flash to indicate the system is ready to accept an altitude entry.
Page 351 Cirrus Design Section 9 SR22 Supplements ALT (Altitude) – The ALT button has two functions: Altitude Pre-select and Altitude readout. Pre-select - When the ALT button is pressed while the system is in the Data Entry (DTA) mode the SEL annunciator will flash and a new altitude can be selected by rotating the input knob CW to increase altitude and CCW to decrease altitude in thousands of feet.
Page 352 Section 9 Cirrus Design Supplements SR22 DH (Decision Height) – The DH button allows entry and arming of altitude alerting at a set decision height. To set a DH, first enter the data (DTA) entry (ENT) mode, press the DH button, and rotate the selector knob to input the desired decision height to the nearest 100 feet above the specified decision height.
Page 353 Basic Ice Protection System When the Ice Protection System is installed on the Cirrus Design SR22, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 354 Section 9 Cirrus Design Supplements SR22 Section 1 - General The airplane is equipped with an Ice Protection System. This system allows a pilot who inadvertently enters icing conditions, to initiate de- icing fluid flow along the wing, horizontal stabilizer, and propeller blades.
Page 355 Cirrus Design Section 9 SR22 Supplements Placards Serials 22-0334 thru 22-2333, 22-2335 thru 22-2419, 22-2421 thru 22-2437; LH Fuselage, above de-icing fluid filler cap: Serials 22-2334, 22-2420, 22-2438 & subs Left wing, above de-icing fluid filler cap: DE-ICING FLUID REFER TO AFM FOR APPROVED...
Page 356 Section 9 Cirrus Design Supplements SR22 Section 3 - Emergency Procedures Inadvertent Icing Encounter • WARNING • The Ice Protection System may not remove significant accumulations of ice if accretions are permitted to form with the Ice Protection System off. Ensure system start time and system mode is noted while exiting icing conditions to aid in estimating de-icing fluid reserve.
Page 357 Cirrus Design Section 9 SR22 Supplements Section 3A - Abnormal Procedures The following Crew Alerting System (CAS) annuciations are available only on Serial Numbers 2979 and subsequent with Cirrus Perspective Integrated Avionics System installed. Response to De-icing Fluid Low CAS Annunciation Red ANTI ICE QTY Warning: The Ice Protection System is operating in NORMAL or MAX mode and de-icing fluid quantity is less than 0.5...
Page 358 Section 9 Cirrus Design Supplements SR22 Section 4 - Normal Procedures Pre-Flight Inspection 1. Battery Master Switch ............... ON 2. Ice Protection Switch ............ MAXIMUM 3. Anti-Icing Fluid Quantity ..........Check Full 4. Fluid Vent (underside) ..........Unobstructed 5. Porous Panels ..........Condition and Security •...
Page 359 Cirrus Design Section 9 SR22 Supplements Section 6 - Weight & Balance De-icing fluid weight is 9.2 pounds per U.S gallon. Refer to Section 6 - Weight and Balance of the basic POH for weight and balance equipment data. Loading Data...
Page 360 Section 9 Cirrus Design Supplements SR22 Loading Data (Continued) Wing De-Icing Fluid Reservoir - Serials with G3 Wing Weight Moment/1000 Weight Moment/1000 Fluid Reservoir Fluid Reservoir FS 148.0 FS 148.0 0.07 18.0 2.66 0.15 19.0 2.81 0.30 20.0 2.96 0.44 21.0...
Page 361 Cirrus Design Section 9 SR22 Supplements Section 7 - System Description • Caution • Prolonged operation of the system in clear air, at very high altitudes, and very cold temperatures can result in “flash” evaporation of water and alcohol from the de-icing fluid. This evaporation results in a glycol rich fluid that could become “gel”...
Page 362 Section 9 Cirrus Design Supplements SR22 system operation through ON and OFF positions, the second switch controls system flow rate through MAXIMUM and NORMAL positions. Serials with G3 Wing; Two switches are mounted on the bolster panel. The ON/OFF switch energizes both the priming pump and the metering pump simultaneously, the second switch controls system flow rate through MAXIMUM and NORMAL positions.
Page 363: System Operation
Cirrus Design Section 9 SR22 Supplements System Operation Serials before G3 Wing; Upon activation, a two-speed metering pump supplies fluid pressure to the system. Low pump speed provides the required flow during NORMAL operation and high pump speed during MAXIMUM operation.
Page 364 Section 9 Cirrus Design Supplements SR22 SLINGER RING POROUS PANELS POROUS PANELS PROPORTIONING PROPORTIONING PROPORTIONING UNIT UNIT UNIT VENT FILTER FITTING FINGER STRAINER FLUID TANK METERING PUMP PROPORTIONING UNIT POROUS PANEL VENT DRAIN POROUS PANEL SR22_FM09_1527 Figure - 2(Sheet 1 of 2)
Page 365 Cirrus Design Section 9 SR22 Supplements POROUS POROUS SLINGER FILLER FLUID PANELS PANELS RING NECK TANK VENT OUTLET STRAINER DRAIN VALVE PROPORTIONING TEST UNIT PORT STRAINER TUBE CHECK VALVE PRIMING PROPORTIONING PUMP UNIT FILTER METERING PUMP POROUS PANELS SR22_FM09_2591 Figure - 2(Sheet 1 of 2)
Page 366 Section 9 Cirrus Design Supplements SR22 Section 8 – Handling, Service, & Maintenance Storage • Note • During long periods of non-use, the porous panel membranes may dry out which could cause uneven fluid flow during subsequent operation. Perform the Pre-Flight Inspection every 30 days to keep porous panel membranes wetted.
Page 367 Cirrus Design Section 9 SR22 Supplements System Priming - Serials before G3 Wing only If allowed to run dry, the metering pump may fail to prime because of air trapped in the system. If no de-icing fluid is evident during the Pre- Flight Inspection, perform the following procedure: 1.
Page 368 Section 9 Cirrus Design Supplements SR22 Section 10 – Safety Information The Ice Protection System is not intended to remove ice from the aircraft on the ground. Do not attempt to take off with frost, ice, or snow on flying surfaces.
Page 369 Awareness/Warning System When the Honeywell KGP 560 Terrain Awareness and Warning System is installed in the Cirrus Design SR22, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 370 Section 9 Cirrus Design Supplements SR22 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.
Page 371 Cirrus Design Section 9 SR22 Supplements Section 2 - Limitations 1. Do not use the Terrain Awareness Display for navigation of the aircraft. The KGP 560 Terrain Awareness and Warning System is intended to serve as a situational awareness tool only and may not provide the accuracy fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions.
Page 372 Section 9 Cirrus Design Supplements SR22 Activate TAWS • Note • If the aircraft horizontal position derived from the Garmin Navigator (GPS 1) is invalid, TAWS will be inoperative and the TERR INOP annunciator will illuminate. 1. SKYWATCH/TAWS Circuit Breaker..........IN 2.
Page 373 Cirrus Design Section 9 SR22 Supplements Response To Awareness Alerts Aural “TERRAIN AHEAD” Alert Aural “OBSTACLE AHEAD” Alert Amber TERR CAUT Annunciation 1. Take positive corrective action until the alert ceases. Stop descending, or initiate a climb turn as necessary, based on analysis of all available instruments and information.
Page 374 Section 9 Cirrus Design Supplements SR22 Section 7 - Systems Description The Honeywell KGP 560 Terrain Awareness and Warning System compares GPS information from the Garmin Navigator (GPS 1) to the integrated Terrain/Obstacle Database to produce a real-time model of the surrounding terrain.
Page 375 Cirrus Design Section 9 SR22 Supplements GNS-430 TAWS Annunciator Panel GMA 340 Audio Panel Avidyne PFD KGP 560 Processor Transponder Avidyne MFD TAWS AVIONICS NON-ESSENTIAL Configuration Module SR20_FM09_2031 Figure - 1 Honeywell KGP 560 TAWS Simplified Schematic P/N 13772-121 7 of 12...
Page 376 Section 9 Cirrus Design Supplements SR22 TAWS Annunciator Panel TAWS terrain annunciations and control functions are incorporated into the Annunciator Panel. The panel consists of a momentary pushbutton switch (SELF TEST), an illuminated pushbutton switch (TERR INHIBIT), and three LEDS for Terrain Warning (TERR WARN), Terrain Caution (TERR CAUT), Terrain Inoperative (TERR INOP).
Page 377 Cirrus Design Section 9 SR22 Supplements TAWS SELF TERR TERR TERR TERR TEST INHIBIT INOP CAUT WARN SR22_FM09_2032 Annunciator Color Function SELF TEST Provides test function for TAWS TERR INHIBIT AMBER All TAWS alerting functions inhibited TERR INOP AMBER Indicates TAWS inoperative...
Page 378 Section 9 Cirrus Design Supplements SR22 MFD Terrain Awareness Display • WARNING • Do not use the Terrain Awareness Display for navigation of the aircraft. The TAWS is intended to serve as a situational awareness tool only and may not provide the accuracy fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions.
Page 379 Cirrus Design Section 9 SR22 Supplements Geometric Altitude versus Measured Sea Level An indication of MSL-G or Geometric Altitude may appear on the left side of the MFD indicating the height above Measured Sea Level (MSL) calculated from the GPS.
Page 380 Section 9 Cirrus Design Supplements SR22 Self Test Proper operation of the TAWS can be verified when the aircraft is on the ground as follows: 1. Select the TAWS page on the MFD 2. Clear all caution messages in the lower right corner 3.
Page 381 Avidyne Flight Director When the Avidyne Flight Director is installed in the Cirrus Design SR22, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 382 Section 9 Cirrus Design Supplements SR22 Section 1 - General The Flight Director system enhances situational awareness by reducing cockpit workload through providing a visual cue for the pilot to follow as indicated by the PFD’s Flight Director Steering Command Bar.
Page 383 1. The Flight Director System integrates with the Primary Flight Display (PFD) System. Adherence to the PFD imitations in the basic SR22 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.
Page 384 Section 9 Cirrus Design Supplements SR22 the pilot is expected to actuate the flight controls as required to track the bars. The following describes push-button annunciation and related Autopilot and Flight Director status: • Autopilot off. Annunciation • Autopilot not active in either roll or pitch control.
Page 385 Instrumentation When the Avidyne EMax™ Engine Instrumentation system is installed in the Cirrus Design SR22, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 386 Section 9 Cirrus Design Supplements SR22 Section 1 - General EMax™ Engine Instrumentation provides the pilot with engine parameters depicted on simulated gauges and electrical system parameters located in a dedicated region within in the EX5000C MFD display. Figure - 1 Avidyne EMax™...
Page 387 Cirrus Design Section 9 SR22 Supplements Section 2 - Limitations No Change. Section 3 - Emergency Procedures No Change. Section 4 - Normal Procedures No Change. Section 5 - Performance No Change. Section 6 - Weight & Balance Installation of the Avidyne Engine Instruments adds the following optional (Sym = O) equipment at the weight and arm shown in the following table.
Page 388 Section 9 Cirrus Design Supplements SR22 providing full-time recording critical engine performance parameters. The Engine Instruments system is powered by 28 VDC supplied through the 5-amp Engine Instruments breaker on the Main Bus 1. Refer to Avidyne FlightMax EX5000C Pilot’s Guide for a more complete description of EMax Engine Instruments, its operating modes, and additional detailed operating procedures.
Page 389 Approach Charts When the Avidyne CMax™ Electronic Approach Charts system is installed in the Cirrus Design SR22, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 390 Section 9 Cirrus Design Supplements SR22 Section 1 - General Avidyne CMax™ Electronic Approach Charts allows the pilot to view terminal procedure chart data on the EX5000C MFD. If the chart is geo-referenced, an ownship symbol and flight plan legs can be overlaid on the chart to further enhance the pilot’s situational...
Page 391 Cirrus Design Section 9 SR22 Supplements Section 2 - Limitations 1. Do not use the CMax Approach Charts function for navigation of the aircraft. The CMax Approach Charts function is intended to serve as a situational awareness tool only. 2. The Avidyne FlightMax EX5000C Pilot’s Guide, P/N 600-00108- 000, Revision 03 or later, must be available to the pilot during all flight operations.
Page 392 Section 9 Cirrus Design Supplements SR22 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. 4 of 4 P/N 13772-125 Revision 01: 12-15-07...
Page 393 XM Satellite Weather System When the XM Satellite Weather System system is installed in the Cirrus Design SR22, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 394 Section 9 Cirrus Design Supplements SR22 Section 1 - General The XM Satellite Weather System enhances situational awareness by providing the pilot with real time, graphical weather information depicted on the MAP page of the EX5000C MFD display. Figure - 1...
Page 395 Cirrus Design Section 9 SR22 Supplements Section 2 - Limitations 1. Do not use the XM Satellite Weather System for navigation of the aircraft. The XM Satellite Weather System is intended to serve as a situational awareness tool only. Section 3 - Emergency Procedures No Change.
Page 396 Section 9 Cirrus Design Supplements SR22 • 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.
Page 397 Air Conditioning System When the Air Conditioning System is installed in the Cirrus Design SR22, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 398 Section 9 Cirrus Design Supplements SR22 Section 1 - General The Air Conditioning System is designed to heat and cool the cabin to desired temperature settings and maintain comfortable humidity levels. The system consists of an engine driven compressor, condenser assembly, evaporator assembly, exhaust heat exchanger,...
Page 399 Cirrus Design Section 9 SR22 Supplements VENTS COMPRESSOR INLET HEAT EXCHANGER TEMPERATURE WINDSHIELD AIRFLOW HOT AIR DIFFUSER VALVE PANEL AIRFLOW FLOOR AIRFLOW DISTRIBUTION MANIFOLD AIR GASPER AIR MIXING CHAMBER FRESH AIR INTAKE FRESH AIR VALVE EVAPORATOR FOOT-WARMER ASSEMBLY DIFFUSER RECIRCULATION...
Page 400 Section 9 Cirrus Design Supplements SR22 RAM AIR RAM AIR HOT AIR VALVE AIRFLOW MIXING CHAMBER HEAT EXCHANGER COMPRESSOR FRESH AIR VALVE AIR FLOW VALVE SERVO MOTOR TEMPERATURE VENTS FLOOR AIRFLOW WINDSHIELD DIFFUSER PANEL AIRFLOW AIR GASPER DISTRIBUTION MANIFOLD EVAPORATOR...
Page 401 Cirrus Design Section 9 SR22 Supplements Section 2 - Limitations There is no change to the basic POH Limitations Section when the Air Conditioning System is installed. Section 3 - Emergency Procedures Engine Failure In Flight 1. Air-conditioner................OFF Engine Airstart 1.
Page 402 Section 9 Cirrus Design Supplements SR22 Cabin Fire In Flight 1. Air-conditioner ................OFF Section 3A - Abnormal Procedures Alternator Failure 1. Air-conditioner ................OFF Engine Indicating System Failure 1. Air-conditioner ................OFF LOW VOLTS Warning Light Illuminated 1. Air-conditioner ................OFF 6 of 14...
Page 403 Cirrus Design Section 9 SR22 Supplements Section 4 - Normal Procedures Preflight Walk-Around 1. System Vents .............Unobstructed 2. System Drains............Unobstructed Ground Operation • Note • To facilitate faster cabin cooling, prior to engine start leave the cabin doors open for a short time to allow hot air to escape cabin.
Page 404 Section 9 Cirrus Design Supplements SR22 Section 5 - Performance When the air-conditioner is operating the following performance changes will result: 1. Brake Horsepower is reduced by approximately 6 BHP. 2. Takeoff Distance: Add 100 feet to ground roll and 150 feet to distance over 50 foot obstacle.
Page 405 Cirrus Design Section 9 SR22 Supplements Section 7 - System Description The Air Conditioning System is powered by 28 VDC supplied through the 15-amp Condenser breaker on the A/C Bus 1, and the 15-amp Evaporator Fan breaker and 7.5-amp Compressor/Control Panel breaker on Main A/C Bus 2.
Page 406 Section 9 Cirrus Design Supplements SR22 evaporator through the expansion valve - a temperature controlled metering valve which regulates the flow of liquid refrigerant to the evaporator. Inside the evaporator, the liquid refrigerant changes state to a gas and in doing so, absorbs heat. The evaporator then absorbs...
Page 407 Cirrus Design Section 9 SR22 Supplements Vent Selection Conditioned air from the distribution manifold can be proportioned and directed to passengers and/or the windshield by manipulating the cabin vent selector. The selector is mechanically linked to butterfly valves at the entrances to the windshield diffuser and the cabin floor ducting.
Page 408 Section 9 Cirrus Design Supplements SR22 Maximum airflow to Shared airflow to the Air conditioning the rear seat foot warmer defroster, cabin floor, mode. diffusers and the front and panel outlets. AC ON illuminated. seat kickplate outlets. Maximum air conditioning (recirculation) mode.
Page 409 Cirrus Design Section 9 SR22 Supplements Maximum airflow to Shared airflow to the Air conditioning the rear seat foot warmer defroster, cabin floor, mode. diffusers and the front and panel outlets. AC ON illuminated. seat kickplate outlets. Maximum air conditioning (recirculation) mode.
Page 410 Section 9 Cirrus Design Supplements SR22 Intentionally Left Blank 14 of 14 P/N 13772-127 Revision 01: 03-27-07...
Page 411 PHC-J3Y1F-1N/N7605(B) is installed in the Cirrus Design SR22, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 412 Section 9 Cirrus Design Supplements SR22 Section 1 - General For additional information on Hartzell Compact Series Propeller with Composite Blades refer to Hartzell Propeller Owner’s Manual, p/n 145, revision 1 or later. Section 2 - Limitations Power Plant Limitations Hartzell Compact Series Propeller with Composite Blades Propeller Type........
Page 413 Cirrus Design Section 9 SR22 Supplements Maximum Glide Conditions Example: Power Altitude 10,000 ft. AGL Propeller Windmilling Airspeed Best Glide Flaps 0% (UP) Wind Zero Glide Distance 13.9 NM Best Glide Speed 3400 lb 88 KIAS Maximum Glide Ratio ~ 8.5 : 1...
Page 414 For climb, follow basic AFM procedure but use performance data in Section 5 of this supplement. Noise Characteristics/Abatement The certificated noise levels for the Cirrus Design SR22 established in accordance with FAR 36 Appendix G are: Configuration...
Page 415 Cirrus Design Section 9 SR22 Supplements Enroute Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp ......20°C • Mixture ...... Set Per Placard Weight ........3400 LB • Flaps ........0% (UP) Pressure Altitude ....4000 FT • Airspeed ....Best Rate of Climb Climb Airspeed ....109 Knots...
Page 416 Section 9 Cirrus Design Supplements SR22 Enroute Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ....... 20°C • Mixture.......Set Per Placard Weight........3400 LB • Flaps........0% (UP) Pressure Altitude....6000 FT • Airspeed ....Best Rate of Climb Climb Airspeed....
Page 417 Cirrus Design Section 9 SR22 Supplements Section 6 - Weight & Balance Installation of the subject propeller adds the following optional (Sym = O) equipment at the weight and arm shown in the following table. ATA / Unit Description Part Number...
Page 418 Section 9 Cirrus Design Supplements SR22 Section 8 - Handling, Servicing & Maintenance Propeller Servicing The spinner and backing plate should be cleaned and inspected for cracks frequently. Before each flight the propeller should be inspected for nicks, scratches, and gouges. If found, they should be repaired as...
Page 419 SR22 Airplanes Equipped with the “G3 Wing” When the G3 Wing is installed on the Cirrus Design SR22 serials 2334, 2420, 2438 and subsequent, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook.
Page 420 Section 9 Cirrus Design Supplements SR22 Intentionally Left Blank 2 of 58 13772-130 Revision 02: 08-26-09...
Page 421 Cirrus Design Section 9 SR22 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.
Page 422 Section 9 Cirrus Design Supplements SR22 GROUND TURNING CLEARANCE 24.3 ft. (7.41 m) RADIUS FOR WING TIP 7.0 ft. (2.16 m) RADIUS FOR NOSE GEAR 0.5 ft. (0.15 m) RADIUS FOR INSIDE GEAR 9.1 ft. (2.77 m) RADIUS FOR OUTSIDE GEAR TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER.
Page 423 Cirrus Design Section 9 SR22 Supplements 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 3400 lb - 9" inches (23 cm).
Page 424 Section 9 Cirrus Design Supplements SR22 The Airplane Fuel Total Capacity ..........94.5 U.S. Gallons (358.0 L) Total Usable ..........92.0 U.S. Gallons (348.0 L) 6 of 58 13772-130 Revision 02: 08-26-09...
Page 425 Cirrus Design Section 9 SR22 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.
Page 426 Section 9 Cirrus Design Supplements SR22 Airspeed Indicator Markings The airspeed indicator markings are based upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
Page 427 Cirrus Design Section 9 SR22 Supplements Center of Gravity Limits Reference Datum ........100 inches forward of firewall Forward ..............Refer to Figure 3 Aft ................Refer to Figure 3 3600 31 .5% M A C 1 9.2% M A C FS 1 48.1...
Page 428 Section 9 Cirrus Design Supplements SR22 Fuel Limits Approved Fuel ....Aviation Grade 100 LL (Blue) or 100 (Green) Total Fuel Capacity ........94.5 U.S. Gallon (358.0 L) Total Fuel Each Tank ......... 47.25 U.S. Gallon (179.0 L) Total Usable Fuel (all flight conditions) ..92.0 U.S. Gallon (348.0 L) Maximum Allowable Fuel Imbalance .....10.0 U.S.
Page 429 Cirrus Design Section 9 SR22 Supplements Placards Wing, adjacent to fuel filler caps: Engine control panel: 119 KIAS FLAPS 100% 104 KIAS CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT RICH Airplanes Registered in Brazil and Operating Under the Agência...
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Page 431 Cirrus Design Section 9 SR22 Supplements Section 3 - Emergency Procedures Emergency Descent 1. Power Lever ................IDLE 2. Mixture ..............AS REQUIRED • Caution • If significant turbulence is expected do not descend at indicated airspeeds greater than V (177 KIAS) 3.
Page 432 Section 9 Cirrus Design Supplements SR22 Engine Fire In Flight If an engine fire occurs during flight, do not attempt to restart the engine. 1. Mixture ................CUTOFF 2. Fuel Pump................OFF 3. Fuel Selector ................OFF 4. Airflow Selector ................OFF 5. Power Lever ................IDLE 6.
Page 433 Cirrus Design Section 9 SR22 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.
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Page 435 Cirrus Design Section 9 SR22 Supplements Section 4 - Normal Procedures Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3400 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.
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Page 437 Cirrus Design Section 9 SR22 Supplements Section 5 - Performance Airspeed Calibration Normal Static Source Conditions: Example: • Power for level flight or maximum Flaps..........50% continuous, whichever is less. Indicated Airspeed....90 Knots Calibrated Airspeed ....91 Knots • Note • • Indicated airspeed values assume zero instrument error.
Page 438 Section 9 Cirrus Design Supplements SR22 Airspeed Calibration Alternate Static Source Conditions: Example: • Power for level flight or maximum Flaps ........... 50% continuous, whichever is less. Indicated Airspeed ....90 Knots • Heater, Defroster & Vents..... ON Calibrated Airspeed ..... 83 Knots •...
Page 439 Cirrus Design Section 9 SR22 Supplements Altitude Correction Normal Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • 3400 LB • Note • • Add correction to desired altitude to obtain indicated altitude to fly.
Page 440 Section 9 Cirrus Design Supplements SR22 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.
Page 441 Cirrus Design Section 9 SR22 Supplements Stall Speeds Conditions: Example: • Weight ........3400 LB Flaps........Up (0%) • C.G..........Noted Bank Angle ........15° • Power ........... Idle C.G ........Forward • Bank Angle........Noted Stall Speed ..74 KIAS | 71 KCAS • Note •...
Page 442 Section 9 Cirrus Design Supplements SR22 Takeoff Distance Conditions: Example: • Winds.......... Zero Outside Air Temp ....... 20°C • Runway....Dry, Level, Paved Weight........3400 LB • Flaps........... 50% Pressure Altitude....2000 FT • Power.......Full Throttle Headwind ........Zero • Mixture.......Set per Placard Runway ......
Page 443 Cirrus Design Section 9 SR22 Supplements Takeoff Distance - 3400 Lb WEIGHT = 3400 LB Headwind: Subtract 10% for each 12 Speed at Liftoff = 73 KIAS knots headwind. Speed over 50 Ft. Obstacle = 78 KIAS Tailwind: Add 10% for each 2 knots Flaps - 50% ·...
Page 444 Section 9 Cirrus Design Supplements SR22 Takeoff Distance - 2900 Lb WEIGHT = 2900 LB Headwind: Subtract 10% for each 12 Speed at Liftoff = 70 KIAS knots headwind. Speed over 50 Ft Obstacle = 74 KIAS Tailwind: Add 10% for each 2 knots Flaps - 50% ·...
Page 445 Cirrus Design Section 9 SR22 Supplements Takeoff Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ...... Set per Placard Weight ........3400 LB • Flaps ........... 50% Pressure Altitude ....4000 FT •...
Page 446 Section 9 Cirrus Design Supplements SR22 Takeoff Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 10° C • Mixture.......Set per Placard Weight........3400 LB • Flaps........... 50% Pressure Altitude....6000 FT • Airspeed ....Best Rate of Climb Climb Airspeed.....
Page 447 Cirrus Design Section 9 SR22 Supplements Enroute Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ......... Full Rich Weight ........3400 LB • Flaps ........0% (UP) Pressure Altitude ....4000 FT • Airspeed ....Best Rate of Climb Climb Airspeed .....98 Knots...
Page 448 Section 9 Cirrus Design Supplements SR22 Enroute Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 10° C • Mixture......As Required Weight........3400 LB • Flaps........0% (UP) Pressure Altitude....6000 FT • Airspeed ....Best Rate of Climb Climb Airspeed.....
Page 449 Cirrus Design Section 9 SR22 Supplements Time, Fuel and Distance to Climb Conditions: Example: • Power ......Full Throttle Outside Air Temp ......ISA • Mixture ..Per Schedule, Section 4 Weight ........3400 LB • Fuel Density .....6.0 LB/GAL Airport Pressure Altitude ..1000 FT •...
Page 450 Section 9 Cirrus Design Supplements SR22 Range / Endurance Profile Conditions: Example: • Weight ........3400 LB Power Setting ......55% • Temperature ....Standard Day Takeoff Press Alt ....2000 FT • Winds.......... Zero Cruise Press Alt ....6000 FT •...
Page 451 Cirrus Design Section 9 SR22 Supplements Range / Endurance Profile 65% POWER Mixture = Best Power Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 81.3 15.4 10.3 2000 81.1 15.4 10.5 4000 80.4...
Page 452 Section 9 Cirrus Design Supplements SR22 Range / Endurance Profile 55% POWER Mixture = Best Economy Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 81.8 11.3 1074 13.1 2000 81.1 11.3 1088 13.4...
Page 453 Cirrus Design Section 9 SR22 Supplements Balked Landing Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ...... Set per Placard Weight ........3400 LB • Flaps ........ 100% (DN) Pressure Altitude ....4000 FT •...
Page 454 Section 9 Cirrus Design Supplements SR22 Balked Landing Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 20° C • Mixture.......Set per Placard Weight........3400 LB • Flaps.........100% (DN) Pressure Altitude....4000 FT • Climb Airspeed ......V Climb Airspeed.....
Page 455 Cirrus Design Section 9 SR22 Supplements Landing Distance Conditions: Example: • Winds ..........Zero Outside Air Temp ......10°C • Runway ....Dry, Level, Paved Weight ........3400 LB • Flaps......... 100% Pressure Altitude ....2000 FT • Power ....3° Power Approach Headwind ........
Page 456 Section 9 Cirrus Design Supplements SR22 Landing Distance - 3400 Lb WEIGHT = 3400 LB Headwind: Subtract 10% for each 13 Speed over 50 Ft Obstacle = 77 KIAS knots headwind. Flaps - 100%· Idle · Dry, Level Paved Surface Tailwind: Add 10% for each 2 knots tailwind up to 10 knots.
Page 457 Cirrus Design Section 9 SR22 Supplements Section 6 - Weight and Balance WATER LINE (WL) 350.2 55.6 100.0 142.5 222.0 165.5 150.0 38.3 WL 100.0 NOTE Reference datum located at 50.0 fuselage station 0.0. (FS) 157.4 FUSELAGE STATION LEMAC BUTTOCK LINE (BL) FS 133.1...
Page 458 Section 9 Cirrus Design Supplements SR22 Airplane Weighing Form REF DATUM FS 0.0 FS 100.0 FS 145.0 WL 100.0 A = x + 100 B = A - y y = ____________ Measured x = ____________ Measured SR22_FM06_1441 Weighing Scale...
Page 459 Cirrus Design Section 9 SR22 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...
Page 460 Section 9 Cirrus Design Supplements SR22 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...
Page 461 Cirrus Design Section 9 SR22 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...
Page 462 Section 9 Cirrus Design Supplements SR22 Center of Gravity Limits The charts below depict the airplane center-of-gravity envelope in terms of inches aft of the reference datum and as a percentage of the Mean Aerodynamic Cord (MAC). The relationship between the two is detailed in the weighing instructions.
Page 463 Cirrus Design Section 9 SR22 Supplements Weight & Balance Loading Form Serial Num: ________________ Date: ________________________ Reg. Num: _________________ Initials: ______________________ Weight Moment/ Item Description 1000 Basic Empty Weight Includes unusable fuel & full oil Front Seat Occupants Pilot & Passenger (total)
Page 464 Section 9 Cirrus Design Supplements SR22 Loading Data Use the following chart or table to determine the moment/1000 for fuel and payload items to complete the Loading Form. 20.0 40.0 60.0 80.0 100.0 Mom ent/1000 Weight Baggage Fuel Weight Fuel...
Page 465 Cirrus Design Section 9 SR22 Supplements 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. 3400 3200 3000 2800 2600 2400...
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Page 467 Cirrus Design Section 9 SR22 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.
Page 468 Section 9 Cirrus Design Supplements SR22 Fuel System An 92-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 47.25-gallon capacity (46- 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.
Page 469 Cirrus Design Section 9 SR22 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.
Page 470 Section 9 Cirrus Design Supplements SR22 Fuel Caution Light The amber FUEL caution light in the annunciator panel comes on to indicate a low fuel condition. The light is illuminated by switches in the fuel quantity indicator if the fuel quantity in both tanks drops below approximately 14 gallons (28 gallons total with tanks balanced in level flight).
Page 471 Cirrus Design Section 9 SR22 Supplements Exterior Lighting The airplane is equipped with wing tip navigation lights with integral anti-collision strobe lights and recognition Lights. The landing light is located in the lower cowl. Recognition Lights The airplane is equipped with recognition lights on the leading edge of the wing tips.
Page 472 Section 9 Cirrus Design Supplements SR22 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.
Page 473 Cirrus Design Section 9 SR22 Supplements RAM AIR RAM AIR HOT AIR VALVE AIRFLOW MIXING CHAMBER HEAT EXCHANGER FRESH AIR VALVE AIR FLOW VALVE SERVO MOTOR TEMPERATURE VENTS FLOOR AIRFLOW WINDSHIELD DIFFUSER PANEL AIRFLOW AIR GASPER DISTRIBUTION MANIFOLD FOOT-WARMER ASSEMBLY DIFFUSER Serials 2334, 2420, 2438 &...
Page 474 Section 9 Cirrus Design Supplements SR22 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.
Page 475 Cirrus Design Section 9 SR22 Supplements Section 8 - Handling, Servicing & Maintenance Servicing Tire Inflation Inflate nose tire to 30 psi (207 kPa) and main wheel tires to 62 psi (427kPa). Filling Fuel Tanks Observe all safety precautions required when handling gasoline. Fuel fillers are located on the forward slope of the wing.
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Page 477 Artex ME406 406 MHz ELT System When Artex ME406 406 MHz ELT System is installed in the Cirrus Design SR22, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 478 Section 9 Cirrus Design Supplements SR22 Section 1 - General The 406 MHz emergency locator transmitter (ELT) is a radio-frequency transmitter that generates a signal to assist in search and rescue for missing aircraft. The ELT automatically transmits the standard sweep tone on 121.5 MHz if rapid deceleration is detected.
Page 479 Cirrus Design Section 9 SR22 Supplements Section 2 - Limitations No Change. Section 3 - Emergency Procedures Forced Landing Before performing a forced landing activate the ELT transmitter manually by turning the ELT remote switch to the 'ON'-position. Immediately after a forced landing, perform the following procedure: •...
Page 480 Section 9 Cirrus Design Supplements SR22 Portable Use of ELT The ELT transmitter can be removed from the airplane and used as a personal locating device if it is necessary to leave the airplane after an accident. Access the unit as described below and set the ELT transmitter control switch to the 'ON'-position.
Page 481 Cirrus Design Section 9 SR22 Supplements Section 7 - Systems Description This airplane is equipped with a self-contained Artex ME406 406 MHz ELT System. The transmitter unit is automatically activated upon sensing a change of velocity along its longitudinal axis exceeding 4 to 5 feet per second.
Page 482 Section 9 Cirrus Design Supplements SR22 Section 8 - Handling, Servicing & Maintenance ELT and RCPI batteries must be inspected in accordance with the Airplane Maintenances Manual, 5-20 - Scheduled Maintenance Checks. The ELT and RCPI batteries must be replaced upon reaching the date...
Page 483 Cirrus Design Section 9 SR22 Supplements system or provide the same level of confidence as does an AM radio. 1. Tune aircraft receiver to 121.5 MHz. 2. Turn the ELT aircraft panel switch "ON" for about 1 second, then back to the "ARM" position. The receiver should transmit about 3 audio sweeps.
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Page 485 Garmin 400W-Series GPS Navigator When a Garmin 400W-Series GPS Navigator is installed in the Cirrus Design SR22, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot's Operating Handbook. This document must be carried in the airplane at all times.
Page 486 Section 9 Cirrus Design Supplements SR22 Section 1 - General The WAAS-enabled, Garmin 400W-Series GPS Navigator is capable of providing primary navigation information for enroute, terminal, non- precision, and precision approaches with typical position accuracies of 1 meter horizontally and 2 meters vertically.
Page 487 Cirrus Design Section 9 SR22 Supplements SR22_FM09_1285 SR22_FM09_1109 Figure - 1 GNC 420W and GNS 430W 400W-Series Navigators P/N 13772-132 3 of 10 Revision 01: 11-11-07...
Page 488 Section 9 Cirrus Design Supplements SR22 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.
Page 489 Cirrus Design Section 9 SR22 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.
Page 490 Section 9 Cirrus Design Supplements SR22 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. For detailed descriptions and operational instructions, refer to the Garmin 400W-Series...
Page 491 Cirrus Design Section 9 SR22 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...
Page 492 Section 9 Cirrus Design Supplements SR22 Communication (COM) Transceiver 430W includes digitally-tuned integrated 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.
Page 493 Cirrus Design Section 9 SR22 Supplements be alternately set between GPS or VLOC by the CDI button on the navigator. The active source is identified on the PFD. TERRAIN Interface • Note • TERRAIN functionality is a standard feature found in GNS 430W units with main software version 5.01 or above and valid...
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Page 495 Cirrus Design Section 10 SR22 Safety Information Section 10 Safety Information Table of Contents Introduction ................... 10-3 Cirrus Airframe Parachute System (CAPS) Deployment ....10-4 Deployment Scenarios............... 10-4 Mid-Air Collision..............10-4 Structural Failure ..............10-4 Loss of Control ............... 10-5 Landing Required in Terrain not Permitting a Safe Landing...
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Page 497: Introduction
SR22 Safety Information Introduction The Cirrus Design SR22 is a modern, advanced technology airplane designed to operate safely and efficiently in a flight environment. However, like any other aircraft, pilots must maintain proficiency to achieve maximum safety, utility, and economy.
Page 498: Cirrus Airframe Parachute System (Caps) Deployment
Instead, possible CAPS activation scenarios should be well thought out and mentally practiced by every SR22 pilot. The following discussion is meant to guide your thinking about CAPS activation.
Page 499: Loss Of Control
Cirrus Design Section 10 SR22 Safety Information continued safe flight and landing. If it is not, CAPS activation should be considered. Loss of Control Loss of control may result from many situations, such as: a control system failure (disconnected or jammed controls); severe wake turbulence, severe turbulence causing upset, severe airframe icing, or sustained pilot disorientation caused by vertigo or panic;...
Page 500: Deployment Altitude
Section 10 Cirrus Design Safety Information SR22 if time and altitude are critical, and/or ground impact is imminent, the CAPS should be activated regardless of airspeed. Deployment Altitude No minimum altitude for deployment has been set. This is because the actual altitude loss during a particular deployment depends upon the airplane’s airspeed, altitude and attitude at deployment as well as...
Page 501: Landing Considerations
Cirrus Design Section 10 SR22 Safety Information Landing Considerations After a CAPS deployment, the airplane will descend at less than 1700 feet per minute with a lateral speed equal to the velocity of the surface wind. The CAPS landing touchdown is equivalent to ground impact from a height of approximately 13 feet.
Page 502: Water Landings
Section 10 Cirrus Design Safety Information SR22 If the pilot elects to touchdown with a door opened, there are several additional factors the pilot must consider: loss of door, possibility of head injury, or injury from an object coming through the open door.
Page 503: Post Impact Fire
Cirrus Design Section 10 SR22 Safety Information consider unlatching a door prior to assuming the emergency landing body position in order to provide a ready escape path should the airplane begin to sink. Post Impact Fire If there is no fire prior to touchdown and the pilot is able to shut down the engine, fuel, and electrical systems, there is less chance of a post impact fire.
Page 504: Taxiing, Steering, And Braking Practices
Section 10 Cirrus Design Safety Information SR22 Taxiing, Steering, and Braking Practices Cirrus aircraft use a castering nose wheel and rely on aerodynamic forces and differential braking for directional control while taxiing. Proper braking practices are therefore critical to avoid potential damage to the brakes.
Page 505: Brake Maintenance
Cirrus Design Section 10 SR22 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.
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CIRRUS DESIGN SR22 Information Manual

Section 1 General

Section 2 Limitations

Section 3 Emergency Procedures

Ground Emergencies

Engine Fire During Start

Ground Emergencies

Emergency Engine Shutdown on Ground

Section 3A Abnormal Procedures

Abnormal Procedures

Section 4 Normal Procedures

Section 5 Performance Data

Section 6 Weight and Balance

Section 7 Airplane and Systems Description

Section 8 Handling, Servicing, Maintenance

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Summary of Contents for CIRRUS DESIGN SR22