Page 1
The EASA approved Airplane Flight Manual consists of the FAA approved Airplane Flight Manual, associated POH Supplements, and this Title Page. Model - Serial Num. SR22 _____________ Registration Num. _ __________________ EASA Approved Under Approval Number P-EASA.IM.A.S.01663 Date of Approval: June 25, 2008...
Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages Use this page to determine the current effective date for each page in the POH. Supplements are issued individually and are controlled by the Log of Supplements Page in Section 9.
Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 7-110 Revision A10 7-111 Revision A10 7-112 Revision A10 Revision A9 Revision A9 Reissue A Reissue A Reissue A...
Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status Intentionally Left Blank P/N 13772-001E Revision A10...
Page 7
This Pilot’s Operating Handbook (POH or Handbook) has been prepared by Cirrus Design Corporation to familiarize operators with the Cirrus Design SR22 airplane. Read this Handbook carefully. It provides operational procedures that will assure the operator obtains the performance published in the manual, data designed to allow the most efficient use of the airplane, and basic information for maintaining the airplane in a “like new”...
Pilot’s Operating Handbook Cirrus Design Foreword SR22 The Handbook This Pilot’s Operating Handbook has been prepared using GAMA Specification #1 for Pilot’s Operating Handbook, Revision 2, dated 18 October 1996 as the content model and format guide. However, some deviations from this specification were made for clarity. The Handbook is presented in loose-leaf form for ease in inserting revisions and is sized for convenient storage.
Original issue pages will be identified by the words “Original Issue” at this location. In the event that the majority of pages in the Handbook are revised, Cirrus may determine that it is more effective to reissue the Handbook. Reissued pages will be identified by the word “Reissue”...
Design Supplements produced for this airplane. The “Log of Supplements” page can be utilized as a “Table of Contents” for Section 9. If the airplane is modified at a non Cirrus Design facility through an STC or other approval method, it is the owner’s responsibility to ensure that the proper supplement, if applicable, is installed in the Handbook and that the supplement is properly recorded on the “Log of...
Page 11
Cirrus Design Pilot’s Operating Handbook SR22 Foreword Retention of Data In the event a new title page is issued, the weight and balance data changes, equipment list changes, or the “Log of Supplements” is replaced, the owner must ensure that all information applicable to the airplane is transferred to the new pages and the aircraft records are current.
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 16
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 17
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.
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...
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.
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.
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.
Cirrus Design Section 1 SR22 General Nautical Miles Per Gallon is the distance (in nautical miles) NMPG 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 24
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 25
Altitude Limits................2-16 Environmental Conditions ............. 2-16 Maximum Occupancy ..............2-16 Systems and Equipment Limits............. 2-17 Cirrus Airframe Parachute System (CAPS) ....... 2-17 Primary Flight Display ..............2-17 Multi-Function Display ............... 2-19 Oxygen System ................. 2-20 Inflatable Restraint System............2-20 Flap Limitations................
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.
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.
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.
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 ––...
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...
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.
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 36
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...
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).
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.
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.
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.
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 46
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 47
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 48
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 49
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 50
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 51
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 USE OF THIS DEVICE COULD RESULT IN INJURY OR DEATH Serials 0210 &...
Page 54
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 P/N 13772-001 Revision A7...
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.
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.
Follow them and use good pilot judgment. The Cirrus Airframe Parachute System (CAPS) should be activated in the event of a life-threatening emergency where CAPS deployment is determined to be safer than continued flight and landing.
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.
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.
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.
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.
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.
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.
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. Air Conditioner (if installed) ............OFF 2. Fuel Pump................BOOST...
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.
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.
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.
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.
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).
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 • CAPS deployment is expected to result in loss of the airframe...
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.
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.
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.
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.
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.
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.
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.
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.
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 •...
Section 3A Cirrus Design Abnormal Procedures SR22 In-Flight Procedures Inadvertent Icing Encounter Flight into known icing conditions is prohibited. However, If icing is inadvertently encountered: 1. Pitot Heat .................. ON 2. Exit icing conditions. Turn back or change altitude. 3. Cabin Heat ..............MAXIMUM 4.
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.
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.
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.
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.
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.
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.
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.
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.
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. P/N 13772-001 Revision A5...
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.
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;...
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 ..............
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.
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.
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.
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.
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.
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...
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.
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 109
Cirrus Design Section 4 SR22 Normal Procedures b. Navigation Lights ..............ON c. Landing Light...............ON d. Annunciator Lights............CHECK • Verify both ALT 1 and ALT 2 caution lights out and positive amps indication for each alternator. If necessary, increase RPM to extinguish ALT 2 caution light.
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.
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.
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.
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.
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,...
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.
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%.
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.
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.
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 120
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 •...
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.
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)
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. P/N 13772-001 4-29 Revision A5...
Page 124
Section 4 Cirrus Design Normal Procedures SR22 Intentionally Left Blank 4-30 P/N 13772-001 Revision A5...
Page 125
Cirrus Design Section 5 SR22 Performance Data Section 5 Performance Data Table of Contents Introduction ..................5-3 Associated Conditions Affecting Performance......5-3 Demonstrated Operating Temperature ........5-3 Airspeed Calibration................ 5-4 Normal Static Source ..............5-4 Airspeed Calibration................ 5-5 Alternate Static Source ..............5-5 Altitude Correction ................
Page 126
Section 5 Cirrus Design Performance Data SR22 Intentionally Left Blank P/N 13772-001 Revision A10...
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 &...
Section 5 Cirrus Design Performance Data SR22 Airspeed Calibration - Normal Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Note • • Indicated airspeed values assume zero instrument error. KCAS KIAS Flaps Flaps...
Page 129
Cirrus Design Section 5 SR22 Performance Data Airspeed Calibration - Alternate Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster & Vents .................. ON • Note • • Indicated airspeed values assume zero instrument error.
Section 5 Cirrus Design Performance Data SR22 Altitude Correction Normal Static Source: Standby Altimeter 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.
Cirrus Design Section 5 SR22 Performance Data Altitude Correction Alternate Static Source: Standby Altimeter 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.
Section 5 Cirrus Design Performance Data SR22 Temperature Conversion To convert from Celsius (°C) to Fahrenheit (°F), find, in the shaded columns, the number representing the temperature value (°C) to be converted. The equivalent Fahrenheit temperature is read to the right.
Cirrus Design Section 5 SR22 Performance Data Outside Air Temperature for ISA Condition Press ISA-40°C ISA-20°C ISA+10°C ISA+20°C Feet °C °F °C °F °C °F °C °F °C °F 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000...
Section 5 Cirrus Design Performance Data SR22 Stall Speeds Conditions: • Weight ......................3400 LB • CG ........................Noted • Power......................... Idle • Bank Angle .....................Noted • Note • Altitude loss during wings level stall may be 250 feet or more.
Section 5 Cirrus Design Performance Data SR22 Takeoff Distance Conditions: • Winds........................ Zero • Runway..................Dry, Level, Paved • Flaps......................... 50% • Air Conditioner....................OFF • Power: • Throttle ....................Full Open • Mixture ..................Set per Placard Set prior to brake release for short field takeoff.
Page 137
Cirrus Design Section 5 SR22 Performance Data 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% tailwind up to 10 knots.
Section 5 Cirrus Design Performance Data 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% tailwind up to 10 knots.
Cirrus Design Section 5 SR22 Performance Data Takeoff Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps .........................50% • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
Section 5 Cirrus Design Performance Data SR22 Takeoff Rate of Climb Conditions: • Power....................Full Throttle • Mixture.................... Set per Placard • Flaps......................... 50% • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude for unit time expended expressed in Feet per Minute.
Cirrus Design Section 5 SR22 Performance Data Enroute Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .......................Full Rich • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
Section 5 Cirrus Design Performance Data SR22 Enroute Rate of Climb Conditions: • Power....................Full Throttle • Mixture....................As Required • Flaps......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude in feet per unit time expressed in Feet per Minute.
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...
Cirrus Design Section 5 SR22 Performance Data Cruise Performance Conditions: • Cruise Weight..................... 2900 LB • Winds ....................... Zero • Shaded Cells: Cruise Pwr above 85% not recommended. • Note • Subtract 10 KTAS if nose wheel pant and fairing removed. Lower KTAS by 10% if nose and main wheel pants &...
Cirrus Design TPOH SR22 POH Temporary Change SR22 Airplane Flight Manual (AFM) Temporary Change Affected Publication: SR22 POH Part Number: • 13772-001 Revision A10 Filing Instructions: Insert this temporary change in Section 5 - Performance adjacent to the Range / Endurance tables on page 7-23 and retain until further notice.
Page 148
TPOH Cirrus Design POH Temporary Change SR22 Range / Endurance Profile Conditions: • Weight ......................3400 LB • Temperature ..................Standard Day • Winds........................ Zero • Mixture....................Best Economy • Total Fuel ....................81 Gallons • Note • Fuel Remaining For Cruise is equal to 81.0 gallons usable, less climb fuel, less 9.8 gallons for 45 minutes IFR reserve fuel at 47% power (ISA @ 10,000...
Page 149
Cirrus Design TPOH SR22 POH Temporary Change Range / Endurance Profile (Continued) 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...
Cirrus Design Section 5 SR22 Performance Data Range / Endurance Profile Conditions: • Weight ......................3400 LB • Temperature ..................Standard Day • Winds ....................... Zero • Mixture ....................Best Economy • Total Fuel....................92 Gallons • Note • Fuel Remaining For Cruise is equal to 92.0 gallons usable, less climb fuel, less 9.8 gallons for 45 minutes IFR reserve fuel at 47% power (ISA @ 10,000...
Page 152
Section 5 Cirrus Design Performance Data SR22 Range / Endurance Profile (Continued) 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...
Cirrus Design Section 5 SR22 Performance Data Balked Landing Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps ...................... 100% (DN) • Climb Airspeed....................V REF • Note • Balked Landing Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
Section 5 Cirrus Design Performance Data SR22 Balked Landing Rate of Climb Conditions: • Power....................Full Throttle • Mixture.................... Set per Placard • Flaps...................... 100% (DN) • Climb Airspeed ....................V REF • Note • Balked Landing Rate of Climb values shown are the full flaps change in altitude for unit time expended expressed in Feet per Minute.
Cirrus Design Section 5 SR22 Performance Data Landing Distance Conditions: • Winds ....................... Zero • Runway ..................Dry, Level, Paved • Flaps.......................100% • Power ..................3° Power Approach to 50 FT obstacle, then reduce power passing the estimated 50 foot point and smoothly continue power reduction to reach idle just prior to touchdown.
Page 156
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% Tailwind: Add 10% for each 2 knots Power: Idle tailwind up to 10 knots.
Page 157
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 Weight & Balance Loading Form ..........6-14 Loading Data.................
Page 158
Section 6 Cirrus Design Weight and Balance SR22 Intentionally Left Blank P/N 13772-001 Revision A10...
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 160
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...
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...
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 164
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 165
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.
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...
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 169
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. P/N 13772-001 6-13...
Cirrus Design Section 6 SR22 Weight & Balance 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...
Section 6 Cirrus Design Weight & Balance SR22 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.
Cirrus Design Section 6 SR22 Weight & Balance Equipment List This list will be determined after the final equipment has been installed in the aircraft. P/N 13772-001 6-17 Revision A10...
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.
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.
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.
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.
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.
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 187
Cirrus Design Section 7 SR22 Airplane Description SR22_FM07_1463 Figure 7-3 Rudder Control System P/N 13772-001 7-13 Revision A5...
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.
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.
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...
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 192
13. Flap Control & Position Indicators 20. Bolster Switch Panel 4. Magnetic Compass 21. Control Yoke 14. Passenger Audio Jacks 5. Cirrus Airframe Parachute System 15. Armrest 22. Start/Ignition Key Switch (CAPS) Activation T-Handle Cover 16. Engine & Fuel System Controls 6.
Page 193
· Parking Brake 12. Conditioned Air Outlet 5. Magnetic Compass · Alternate Static Source 13. Rudder Pedals 6. Cirrus Airframe Parachute System 14. Flap Control & Position Indicators 19. Avionics Panel (CAPS) Activation T-Handle Cover 20. Bolster Switch Panel 15. Passenger Audio Jacks 7.
Page 194
· Parking Brake 12. Conditioned Air Outlet 5. Magnetic Compass · Alternate Static Source 13. Rudder Pedals 6. Cirrus Airframe Parachute System 14. Flap Control & Position Indicators 19. Avionics Panel (CAPS) Activation T-Handle Cover 20. Bolster Switch Panel 15. Passenger Audio Jacks 7.
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 196
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 197
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 198
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 199
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.
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°...
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.
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.
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 204
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.
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.
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.
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.
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.
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.
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 213
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 214
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.
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.
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.
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.
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 219
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 220
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 221
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 222
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 223
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 224
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 225
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 226
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.
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...
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 229
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...
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).
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.
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.
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.
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 237
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.
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.
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 241
Cirrus Design Section 7 SR22 Airplane Description ALT 1 RELAY VOLT REG ALT 1 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...
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.
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 244
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.
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.
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.
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.
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. and Serials 1863 & subs; recognition lights. The separately controlled landing light is located in the lower cowl..
Cirrus Design Section 7 SR22 Airplane Description Interior Lighting Interior lighting for the airplane consists of separately controlled incandescent overhead lights for general cabin lighting, individual lights for the pilots and passengers, and dimmable panel floodlights. The flight instrumentation and avionics equipment lights are dimmable.
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. Ventilation air is provided by ducting ram air from air inlets to eyeball outlets for each occupant.
Page 251
Cirrus Design Section 7 SR22 Airplane Description the passenger air distribution system and allows maximum airflow to the windshield diffuser. Rotating the knob full clockwise shuts off airflow to the windshield diffuser and allows maximum airflow to the passenger air distribution system. The control can be positioned to allow any proportion of windshield and passenger air.
Page 252
Section 7 Cirrus Design Airplane Description SR22 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 253
Cirrus Design Section 7 SR22 Airplane Description Serials 1602, 1821, 1840, 1863 and subsequent* Serials 1602, 1821, 1840, 1863 thru 2437: The environmental system consists of a fresh air inlet in the RH upper cowl, a heat exchanger around the RH engine exhaust muffler, one fresh air inlet located in the...
Page 254
Section 7 Cirrus Design Airplane Description SR22 Distribution Ventilation and cooling is provided by ducting fresh air from a NACA inlet on the RH cowl to the mixing chamber located on the lower RH portion of the firewall. Depending on operating mode and temperature...
Page 255
Cirrus Design Section 7 SR22 Airplane Description Cooling Standard cabin cooling is provided by ram air admitted through the NACA inlet on the RH cowl to the fresh air valve, mounted to the forward side of the firewall. When the fresh air valve is open, the air flows into the cabin mixing chamber.
Page 256
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 257
Cirrus Design Section 7 SR22 Airplane Description 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...
Page 258
Section 7 Cirrus Design Airplane Description SR22 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...
Page 259
Cirrus Design Section 7 SR22 Airplane Description 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...
Page 260
Section 7 Cirrus Design Airplane Description SR22 Airflow Selection Serials 1602, 1821, 1840, 1863 thru 2437: The airflow selector regulates the volume of airflow allowed into the cabin distribution system through mechanical linkage to a butterfly valve in the distribution manifold. If option installed, the blower fan is turned on when the selector dial exceeds the full open position.
Page 261
Cirrus Design Section 7 SR22 Airplane Description If optional air condition system installed, when the full/max defrost position is selected, the air-conditioner is activated to provide conditioned, dry air to the diffuser to facilitate windshield defogging. Temperature Selection The temperature selector is mechanically linked to the hot air valve and fresh air intake valve.
Page 262
Section 7 Cirrus Design Airplane Description 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...
Page 263
Cirrus Design Section 7 SR22 Airplane Description 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...
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.
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...
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 269
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) •...
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 271
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 272
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.
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 274
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.
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.
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).
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.
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 279
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...
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.
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 °...
Page 282
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.
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...
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.
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 286
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 287
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 ..................
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.
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.
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.
AD’s are mandatory changes and must be complied with within a time limit set forth in the AD. Operators should periodically check with Cirrus Service Centers or A&P mechanic to verify receipt of the latest issued AD for their airplane.
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.
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 295
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.
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.
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.
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.
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.
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.
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.
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 303
Cirrus Design Section 8 SR22 Handling, Servicing, Maintenance Brake Inspection The brake assemblies and linings should be checked at every oil change (50 hours) for general condition, evidence of overheating, and deterioration. Serials 0002 thru 3450 before SB 2X-05-01: At every annual/100-hour inspection the brakes should be disassembled, the brake linings should be checked and the O-rings replaced.
Section 8 Cirrus Design Handling, Servicing, Maintenance SR22 Tire Inflation For maximum service from the tires, keep them inflated to the proper pressure. When checking tire pressure, examine the tires for wear, cuts, nicks, bruises and excessive wear. To inflate tires: 1.
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 306
• 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 307
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...
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 309
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.
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.
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.
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 313
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 314
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 315
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.
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 318
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 319
For deeper cleaning, start with mix of mild detergent and water then, if necessary, work your way up to the products available from Cirrus for more stubborn marks and stains. Do not use soaps as they contain alkaline which will alter the leather’s pH balance and cause the leather to age prematurely.
Page 321
Cirrus Design Supplements produced for this airplane. The Log of Supplements page can be utilized as a “Table of Contents” for this section. In the event the airplane is modified at a non Cirrus Design facility through an STC or other approval method, it is the...
Page 323
Garmin GTX 330 Mode S Transponder 07-03-04 ___ 13772-121 R1 Honeywell KGP 560 Terrain Awareness/Warning System12-15-07 ___ 13772-122 R1 SR22 / SR22T Airplanes Registered in European Union 07-07-10 ___ 13772-123 R1 Avidyne Flight Director 12-15-07 ___ 13772-124 R1 Avidyne EMax™ Engine Instrumentation 12-15-07 ___ 13772-125 R1 Avidyne CMax™...
Page 324
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 325
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 326
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 327
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 328
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 329
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 330
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 331
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 332
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 333
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 334
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 335
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 336
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 337
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.
• 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 339
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 340
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 341
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 342
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 343
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 344
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 345
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 346
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 348
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.
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 350
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 351
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 352
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 353
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 354
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 355
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 356
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 357
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 358
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 359
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 360
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 361
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 362
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 363
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 364
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 365
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 366
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 367
Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the Basic Ice Protection System When the Basic Ice Protection System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements Section of the Pilot’s Operating Handbook.
Page 368
Section 9 Cirrus Design Supplements SR22 / SR22T 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 370
Section 9 Cirrus Design Supplements SR22 / SR22T 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 system off. Ensure system start time and system mode is noted while exiting icing conditions to aid in estimating ice protection fluid quantity.
Page 371
SR22 / SR22T Supplements Section 3A - Abnormal Procedures The following Crew Alerting System (CAS) annuciations are available only on aircraft equipped with the Cirrus Perspective Integrated Avionics System. Ice Protection System CAS Annunciation Low Fluid Quantity Warning, Caution, and Advisory ANTI ICE QTY PFD Alerts Window: “Fluid quantity is low (TKS)”...
Page 372
Section 9 Cirrus Design Supplements SR22 / SR22T Section 4 - Normal Procedures • 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 373
Cirrus Design Section 9 SR22 / SR22T Supplements a. Slinger Ring......EVIDENCE OF DEICING FLUID 5. Left Wing Forward and Main Gear a. Serials with G3 Wing; (1) Fluid Tank......VERIFY DESIRED QUANTITY (a) Filler Cap ......CONDITION / SECURITY (b)Vent (underside of wing)UNOBSTRUCTED b.
Page 374
Section 9 Cirrus Design Supplements SR22 / SR22T Section 5 - Performance Cruise speed is lower by approximately three knots and range is reduced by a maximum of 2%. Experience with your airplane’s power settings may result in more accurate performance numbers than those given above.
Page 375
Cirrus Design Section 9 SR22 / SR22T Supplements Section 6 - Weight & Balance Refer to Section 6 - Weight and Balance of the basic POH for current weight and balance data. Use the following table to determine the Moment/1000 for deicing fluid to complete the Loading Form in the Weight and Balance Section of the basic POH.
Page 377
Cirrus Design Section 9 SR22 / SR22T Supplements Section 7 - System Description The Ice Protection System can prevent, and in certain conditions, remove ice accumulation on the flight surfaces by distributing a thin film of glycol-based fluid on the wing, horizontal stabilizer, and propeller.
Page 378
Section 9 Cirrus Design Supplements SR22 / SR22T 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...
Page 379
Cirrus Design Section 9 SR22 / SR22T Supplements • A cabin floor-forward proportioning unit distributes fluid to the propeller slinger ring assembly. In addition to distributing fluid to the porous panels and propeller slinger ring, the proportioning units provide an additional, distinct pressure drop to the supply lines such that a specific flow rate is provided to each protected surface.
Page 380
Section 9 Cirrus Design Supplements SR22 / SR22T Ice Protection System - Serials with G3 Wing The system consists of six porous panels, propeller slinger ring, two proportioning units, metering pump, priming pump, filter, in-line strainer, fluid tank, filler cap and neck, test port assembly, electrical switching, system plumbing, and (Serials w/ Perspective Avionics) deicing fluid level sensor.
Page 381
Cirrus Design Section 9 SR22 / SR22T 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...
Page 382
Section 9 Cirrus Design Supplements SR22 / SR22T • The empennage proportioning unit distributes fluid to the LH and RH horizontal panels. In addition to distributing fluid to the porous panels and propeller slinger ring, the proportioning units provide an additional, distinct pressure drop to the supply lines such that a specific flow rate is provided to each protected surface.
Page 383
Cirrus Design Section 9 SR22 / SR22T Supplements Fluid Quantity Sensing Serials w/ Perspective Avionics: Fluid quantity is measured by a float type quantity sensor installed in the deicing fluid tank. System Indicating Serials w/ Perspective Avionics: System Indicating is displayed as a dial gauge and text in the lower left corner of the MFD ENGINE page.
Page 384
Section 9 Cirrus Design Supplements SR22 / SR22T Section 8 – Handling, Service, & Maintenance • Caution • 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 385
Cirrus Design Section 9 SR22 / SR22T Supplements Metering Pump Priming - Serials before G3 Wing If air enters the system due to the fluid tank running dry during system operation, the metering pump may not be capable of priming itself. To...
Page 386
Section 9 Cirrus Design Supplements SR22 / SR22T 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 387
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 388
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 389
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 390
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 391
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 392
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 394
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 395
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 396
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 397
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 398
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 399
Supplement SR22 / SR22T Airplanes Registered in the European Union 1. This supplement is required for operation of Cirrus Design SR22 serial numbers 0002 and subsequent and SR22T serial numbers 0001 and subsequent when registered in the European Union. This supplement must be attached to the applicable SR22 and SR22T EASA/FAA-approved Airplane Flight Manuals.
Page 400
Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General No Change. Section 2 - Limitations No Change. Section 3 - Emergency Procedures No Change. Section 4 - Normal Procedures Noise Characteristics/Abatement Serials 22T-0001 and subsequent: The certificated noise levels for the...
Page 401
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 402
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 403
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 404
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 405
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 406
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 407
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 408
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 409
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 410
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 411
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 412
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 413
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 414
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 415
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 416
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 417
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 418
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 419
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 420
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 421
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 422
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 423
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 424
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 425
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 426
Section 9 Cirrus Design Supplements SR22 Intentionally Left Blank 2 of 48 13772-130 Revision 03: 05-09-11...
Page 427
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 428
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 429
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 430
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) Maximum Certificated Weights Full Fuel Payload ............610 lb (277 Kg) 6 of 48 13772-130 Revision 03: 05-09-11...
Page 431
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 432
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 433
Cirrus Design Section 9 SR22 Supplements Center of Gravity Limits Reference Datum ........100 inches forward of firewall Forward ..............Refer to Figure 2-1 Aft ................Refer to Figure 2-1 3600 31 .5% M A C 1 9.2% M A C FS 1 48.1...
Page 434
Section 9 Cirrus Design Supplements SR22 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...
Page 435
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 436
Section 9 Cirrus Design Supplements SR22 Intentionally Left Blank 12 of 48 13772-130 Revision 03: 05-09-11...
Page 437
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.
Page 438
Section 9 Cirrus Design Supplements SR22 Intentionally Left Blank 14 of 48 13772-130 Revision 03: 05-09-11...
Page 439
Cirrus Design Section 9 SR22 Supplements Section 5 - Performance Airspeed Calibration - Normal Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Note • Indicated airspeed values assume zero instrument error. KCAS KIAS...
Page 440
Section 9 Cirrus Design Supplements SR22 Airspeed Calibration - Alternate Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster & Vents................... ON • Note • Indicated airspeed values assume zero instrument error.
Page 441
Cirrus Design Section 9 SR22 Supplements Altitude Correction Normal Static Source: Standby Altimeter 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 442
Section 9 Cirrus Design Supplements SR22 Altitude Correction Alternate Static Source: Standby Altimeter 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 444
Section 9 Cirrus Design Supplements SR22 Takeoff Distance Conditions: • Winds........................ Zero • Runway..................Dry, Level, Paved • Flaps......................... 50% • Power: • Throttle ....................Full Open • Mixture ..................Set per Placard Set prior to brake release for short field takeoff.
Page 445
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% tailwind up to 10 knots.
Page 446
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% tailwind up to 10 knots.
Page 447
Cirrus Design Section 9 SR22 Supplements Takeoff Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps .........................50% • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
Page 448
Section 9 Cirrus Design Supplements SR22 Takeoff Rate of Climb Conditions: • Power....................Full Throttle • Mixture.................... Set per Placard • Flaps......................... 50% • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude for unit time expended expressed in Feet per Minute.
Page 449
Cirrus Design Section 9 SR22 Supplements Enroute Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .......................Full Rich • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
Page 450
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 451
Cirrus Design Section 9 SR22 Supplements Time, Fuel and Distance to Climb Conditions: • Power ....................Full Throttle • Mixture ................Per Schedule, Section 4 • Fuel Density ..................6.0 LB/GAL • Weight ......................3400 LB • Winds ....................... Zero • Climb Airspeed....................Noted •...
Page 452
Section 9 Cirrus Design Supplements SR22 Range / Endurance Profile Conditions: • Weight ......................3400 LB • Temperature ..................Standard Day • Winds........................ Zero • Mixture....................Best Economy • Total Fuel ....................92 Gallons • Note • Fuel Remaining For Cruise is equal to 92.0 gallons usable, less climb fuel, less 9.8 gallons for 45 minutes IFR reserve fuel at 47% power (ISA @ 10,000...
Page 453
Cirrus Design Section 9 SR22 Supplements 65% POWER Mixture: Best Power Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 8000 79.0 15.4 11.2 10000 78.2 15.4 11.5 12000 77.1 15.4 11.8...
Page 454
Section 9 Cirrus Design Supplements SR22 Balked Landing Climb Gradient Conditions: • Power....................Full Throttle • Mixture.................... Set per Placard • Flaps...................... 100% (DN) • Climb Airspeed ....................V REF • Note • Balked Landing Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
Page 455
Cirrus Design Section 9 SR22 Supplements Balked Landing Rate of Climb Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps ...................... 100% (DN) • Climb Airspeed....................V REF • Note • Balked Landing Rate of Climb values shown are the full flaps change in altitude for unit time expended expressed in Feet per Minute.
Page 456
Section 9 Cirrus Design Supplements SR22 Landing Distance Conditions: • Winds........................ Zero • Runway..................Dry, Level, Paved • Flaps....................... 100% • Power..................3° Power Approach to 50 FT obstacle, then reduce power passing the estimated 50 foot point and smoothly continue power reduction to reach idle just prior to touchdown.
Page 457
Cirrus Design Section 9 SR22 Supplements Landing Distance WEIGHT: 3400 LB Headwind: Subtract 10% for each 13 Speed over 50 Ft Obstacle: 77 KIAS knots headwind. Flaps: 100% Tailwind: Add 10% for each 2 knots Power: Idle tailwind up to 10 knots.
Page 458
Section 9 Cirrus Design Supplements SR22 Intentionally Left Blank 34 of 48 13772-130 Revision 03: 05-09-11...
Page 459
Cirrus Design Section 9 SR22 Supplements Section 6 - Weight and Balance WATER LINE (WL) 350.2 165.5 55.6 100.0 142.5 222.0 150.0 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 460
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 461
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 462
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 463
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 464
Section 9 Cirrus Design Supplements SR22 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) Rear Seat Occupants...
Page 465
Cirrus Design Section 9 SR22 Supplements 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 Aft Pass Loading Chart Baggage 20.0 40.0 60.0 80.0 100.0...
Page 466
Section 9 Cirrus Design Supplements SR22 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...
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 to each flight. A sampler cup is provided to drain a small amount of fuel from the wing tank drains, the collector tank drains, and the gascolator drain. If takeoff weight limitations for the next flight permit, the fuel tanks should be filled after each flight to prevent condensation.
Page 470
Section 9 Cirrus Design Supplements SR22 Intentionally Left Blank 46 of 48 13772-130 Revision 03: 05-09-11...
Page 471
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.
Page 472
Section 9 Cirrus Design Supplements SR22 Intentionally Left Blank 48 of 48 13772-130 Revision 03: 05-09-11...
Page 473
Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement Artex ME406 406 MHz ELT System When Artex ME406 406 MHz ELT System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements Section of the Pilot’s Operating Handbook.
Page 474
Section 9 Cirrus Design Supplements SR22 / SR22T 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 475
Cirrus Design Section 9 SR22 / SR22T 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.
Page 476
Section 9 Cirrus Design Supplements SR22 / SR22T 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 477
Cirrus Design Section 9 SR22 / SR22T 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 478
Section 9 Cirrus Design Supplements SR22 / SR22T 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 479
Cirrus Design Section 9 SR22 / SR22T 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"...
Page 481
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 482
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 484
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 485
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 486
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 487
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 488
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 489
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...
Page 490
Section 9 Cirrus Design Supplements SR22 Intentionally Left Blank 10 of 10 P/N 13772-132 Revision 01: 11-11-07...
Page 491
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... 10-5 Pilot Incapacitation ..............
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.
SR22 Cirrus Airframe Parachute System (CAPS) Deployment The Cirrus Airframe Parachute System (CAPS) is designed to lower the aircraft and its passengers to the ground in the event of a life- threatening emergency. However, because CAPS deployment is expected to result in damage to the airframe and, depending upon...
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;...
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...
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.
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.
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.
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.
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.
Page 502
Section 10 Cirrus Design Safety Information SR22 Intentionally Left Blank 10-12 P/N 13772-001 Revision A6...
Need help?
Do you have a question about the SR22 and is the answer not in the manual?
Questions and answers