CIRRUS DESIGN SR22 Information Manual Download Page 131

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Information Manual

5-17

Cirrus Design

Section 5

SR22

Performance Data

Wind Components

• Note •

• The maximum demonstrated crosswind is 20 knots. Value not considered limiting.

Conditions:

Example:

• Runway Heading ...........................10°

Wind/Flight Path Angle ................. 50°

• Wind Direction...............................60°

Crosswind Component .........12 Knots

• Wind Velocity........................ 15 Knots

Headwind Component ..........10 Knots

10°

wind

Tailwi

0°

20°

30°

40°

50°

60°

70°

80°

90°

100°

110°

120°

130°

140°

150°

160°

170°

180°

CIT

ND COMPON

TS ~

KNOTS

CROSSWIND COMPONENT ~ KNOTS

-20

-10

SR22_FM05_1014

Figure 5-8

March 2010

Summary of Contents for SR22

Page 1: ...TE At the time of issuance this Information Manual was harmo nized with the SR22 Pilot s Operating Handbook Rev A9 P N 13772 001 and will not be kept current Therefore this Infor mation Manual is for reference only and cannot be used as a substitute for the official Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Information Manual P N 20880 001 March 2010 ...

Page 3: ...7 Maximum Certificated Weights 1 7 Cabin and Entry Dimensions 1 7 Baggage Spaces and Entry Dimensions 1 7 Specific Loadings 1 7 Symbols Abbreviations and Terminology 1 8 General Airspeed Terminology and Symbols 1 8 Meteorological Terminology 1 9 Engine Power Terminology 1 10 Performance and Flight Planning Terminology 1 10 Weight and Balance Terminology 1 11 March 2010 ...

Page 4: ...1 2 Information Manual Section 1 Cirrus Design General SR22 Intentionally Left Blank March 2010 ...

Page 5: ...ding fueling sheltering and handling the airplane during ground operations Additionally this section contains definitions or explanations of symbols abbreviations and terminology used throughout this handbook Note For specific information regarding the organization of this Handbook revisions supplements and procedures to be used to obtain revision service for this handbook refer to the Foreword im...

Page 6: ... 1 78 inches 3 BLADE 198 cm 38 3 ft 11 67 m 10 8 ft 3 29 m 7 inches 18 cm 26 0 ft 7 92 m SR22_FM01_1371A 8 8 ft 2 70 m NOTE Wing span includes position and strobe lights Prop ground clearance at 3400 lb 7 inches 18 cm Wing Area 144 9 sq ft Airplane Three View March 2010 ...

Page 7: ...54 m 7 0 ft 2 16 m RADIUS FOR NOSE GEAR RADIUS FOR OUTSIDE GEAR RADIUS FOR INSIDE GEAR RADIUS FOR WING TIP PARTIAL POWER ACTUAL TURNING RADIUS MAY VARY AS MUCH AS THREE FEET TURNING RADII ARE CALCULATED USING ONE BRAKE AND GROUND TURNING CLEARANCE SR22_FM01_1370 Figure 1 2 Turning Radius March 2010 ...

Page 8: ...ed Direct Drive Horsepower Rating 310 hp 2700 rpm Propeller Hartzell Propeller Type Constant Speed Three Blade Model Number PHC J3YF 1RF F7694 B Diameter 78 0 76 0 Minimum Model Number PHC J3YF 1RF F7693DF B Diameter 78 0 76 0 Minimum or McCauley Propeller Type Constant Speed Three Blade Model Number D3A34C443 78CYA 0 Diameter 78 0 76 0 Minimum or MT Propeller Propeller Type Constant Speed Three B...

Page 9: ...AE 50 Maximum Certificated Weights Maximum Gross for Takeoff 3400 lb 1542 Kg Maximum Baggage Compartment Loading 130 lb 59 Kg Standard Empty Weight 2250 lb 1021 Kg Maximum Useful Load 1150 lb 522 Kg Full Fuel Payload 676 lb 307 Kg Cabin and Entry Dimensions Dimensions of the cabin interior and entry door openings are illustrated in detail in Section 6 Baggage Spaces and Entry Dimensions Dimensions...

Page 10: ...e greatest flight distance is attained per unit of altitude lost with power off VO Operating Maneuvering Speed is the maximum speed at which application of full control movement will not overstress the airplane VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position VNO Maximum Structural Cruising Speed is the speed that should not be exce...

Page 11: ...iling less than the minima for visual flight defined in FAR 91 155 ISA International Standard Atmosphere standard day is an atmosphere where 1 the air is a dry perfect gas 2 the temperature at sea level is 15 C 3 the pressure at sea level is 29 92 in Hg 1013 2 millibars and 4 the temperature gradient from sea level to the altitude at which the temperature is 56 5 C is 0 00198 C per foot and zero a...

Page 12: ...ntinuous Power is the maximum power that can be used continuously MAP Manifold Pressure is the pressure measured in the engine s induction system expressed as in Hg RPM Revolutions Per Minute is engine rotational speed Static RPM is RPM attained during a full throttle engine runup when the airplane is on the ground and stationary g One g is a quantity of acceleration equal to that of earth s gravi...

Page 13: ... arm is obtained by adding the airplane s individual moments and dividing the sum by the total weight Basic Empty Weight is the actual weight of the airplane including all operating equipment that has a fixed location in the airplane The basic empty weight includes the weight of unusable fuel and full oil MAC Mean Aerodynamic Chord is the chord drawn through the centroid of the wing plan area LEMA...

Page 14: ...t 123 inches aft of the reference datum is Fuselage Station 123 0 FS 123 Reference Datum is an imaginary vertical plane from which all horizontal distances are measured for balance purposes Tare is the weight of all items used to hold or position the airplane on the scales for weighing Tare includes blocks shims and chocks Tare weight must be subtracted from the associated scale reading March 2010...

Page 15: ...s 2 10 Flight Load Factor Limits 2 10 Minimum Flight Crew 2 10 Kinds of Operation 2 11 Kinds of Operation Equipment List 2 11 Icing 2 15 Runway Surface 2 15 Taxi Power 2 16 Fuel Limits 2 16 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 Oxy...

Page 16: ...2 2 Information Manual Section 2 Cirrus Design Limitations SR22 Intentionally Left Blank March 2010 ...

Page 17: ...erating 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 Compliance with the operating limitations in this section and in Section 9 is required by Federal Aviation Regula...

Page 18: ...me VNO 178 180 Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution VO 3400 Lb 133 135 Operating Maneuvering Speed is the maximum speed at which full control travel may be used Below this speed the airplane stalls before limit loads are reached Above this speed full control movements can damage the airplane VFE 50 Flaps 100 Flap...

Page 19: ...ite Arc 59 104 Full Flap Operating Range Lower limit is the most adverse stall speed in the landing configuration Upper limit is the maximum speed permissible with flaps extended Green Arc 70 178 Normal Operating Range Lower limit is the maximum weight stall at most forward C G with flaps retracted Upper limit is the maximum structural cruising speed Yellow Arc 178 201 Caution Range Operations mus...

Page 20: ...oil must be added to the factory installed oil add only MIL L 6082 straight mineral oil After Engine Break In Use only oils conforming to Teledyne Continental Specification MHS 24 Ashless Dispersant Lubrication Oil or MHS 25 Synthetic Lubrication Oil Refer to Section 8 Oil Servicing Oil viscosity range as follows All Temperatures 15W 50 20W 50 or 20W 60 Above 40 F 4 C SAE 50 20W50 or 20W60 Below 4...

Page 21: ...umber PHC J3YF 1RF F7693DF B Diameter 78 0 76 0 Minimum or McCauley Propeller Type Constant Speed Three Blade Model Number D3A34C443 78CYA 0 Diameter 78 0 76 0 Minimum or MT Propeller Propeller Type Constant Speed Three Blade Model Number MTV 9 D 198 52 Diameter 78 0 76 0 Minimum Weight Limits Maximum Takeoff Weight 3400 lb 1542 Kg Maximum Weight in Baggage Compartment 130 lb 59 Kg March 2010 ...

Page 22: ...2700 Cylinder Head Temperature 200 F 500 F 240 420 F 420 460 F 460 F Exhaust Gas Temp 1250 1650 F Manifold Pressure 10 30 Inches Hg 15 29 5 in Hg Fuel Flow 0 30 U S Gal Hr 10 20 GPH Oil Temperature 50 240 F 100 240 F 240 F Oil Pressure 0 100 PSI 10 psi Idle 30 60 psi 10 30 psi 60 100 psi 100 psi Cold Fuel Quantity 0 90 U S Gallon 0 gal 0 14 gal Miscellaneous Instrumentation Voltmeter 16 32 Volts 2...

Page 23: ...haded 138 136 140 142 144 146 148 150 SR22_FM02_3216 FORWARD LIMIT The forward limit is FS 137 8 9 8 MAC at 2100 lb with straight line taper to FS 139 1 12 5 MAC at 2700 lb to FS 142 3 19 2 MAC at 3400 lb AFT LIMIT The aft limit is FS 148 1 31 5 MAC at all weights from 2100 lb to 3400 lb LANDING LIMITATION The Landing Limitation is FS 141 4 17 4 MAC at 3210 lb to FS 142 3 19 2 MAC at 3400 lb to FS...

Page 24: ... Section 3 Emergency Procedures Inadvertent Spiral Spin Entry This airplane is certified in the normal category and is not designed for aerobatic operations Only those operations incidental to normal flight are approved These operations include normal stalls chandelles lazy eights and turns in which the angle of bank is limited to 60 Flight Load Factor Limits Flaps UP 0 3400 lb 3 8g 1 9g Flaps 50 ...

Page 25: ...essary under the operating rules are defined in FAR Part 91 and FAR Part 135 as applicable Note All references to types of flight operations on the operating limitations placards are based upon equipment installed at the time of Airworthiness Certificate issuance System Instrument and or Equipment Kinds of Operation Remarks Notes and or Exceptions VFR Day VFR Nt IFR Day IFR Nt Communications VHF C...

Page 26: ... 1 1 1 Pitch Trim System 1 1 1 1 Roll Trim Indicator 1 1 1 1 Roll Trim System 1 1 1 1 Rudder Trim and Indicator 1 1 1 1 Rudder Trim System and or Indicator may be inoperative provided the trim tab is fixed in the streamlined position the indicator is placarded Rudder Trim Inop and the system is electrically disabled Stall Warning System 1 1 1 1 Fuel Auxiliary Boost Pump 1 1 1 1 Fuel Quantity Indic...

Page 27: ... Lights Must be operative Navigation Lights 2 2 Landing Light 1 1 For hire operations Navigation Pitot Static Airspeed Indicator 1 1 1 1 Altimeter 1 1 1 1 Magnetic Compass 1 1 1 1 Pitot System 1 1 1 1 Static System Normal 1 1 1 1 Attitude Indicator 1 1 Clock 1 1 Nav Radio 1 1 Gyroscopic Directional Indication HSI 1 1 Serials 0002 subs w o PFD System Instrument and or Equipment Kinds of Operation R...

Page 28: ...w PFD PFD Slip Skid Indication 1 1 Serials 0435 subs w PFD Magnetometer 1 1 Serials 0435 subs w PFD Vertical Speed Indicator Multi Function Display Serials 1602 1644 and 1663 thru 2750 before PFD Release 7 0 Software Update Oil Temperature Indication must be operative Engine Indicating Cylinder Head Temperature Indication Exhaust Gas Temperature Indication Fuel Flow Indication 1 1 1 1 System Instr...

Page 29: ...equire additional maintenance or inspection Refer to the Airplane Maintenance Manual Manifold Pressure Indication 1 1 1 1 Oil Pressure Indication 1 1 1 1 Oil Quantity Indicator Dipstick 1 1 1 1 Oil Temperature Indication 1 1 1 1 Engine Speed 1 1 1 1 Special Equipment Cirrus Airframe Parachute CAPS 1 1 1 1 Airplane Flight Manual 1 1 1 1 Included w POH System Instrument and or Equipment Kinds of Ope...

Page 30: ...ance 10 0 U S Gallon tank The fuel system BOOST pump must be on for takeoff climb landing and for switching fuel tanks Altitude Limits Maximum Takeoff Altitude 10 000 Feet MSL Maximum Operating Altitude 17 500 Feet MSL The operating rules FAR Part 91 and FAR Part 135 require the use of supplemental oxygen at specified altitudes below the maximum operating altitude Refer to Oxygen System Limitation...

Page 31: ...s not permitted with the PFD or any standby indicator attitude indicator or magnetic compass inoperative Refer to Kinds of Operation Equipment List Note The Avidyne PFD software version is displayed on the PFD during system startup 4 Serials 0002 and subsequent before installation of PFD software version 530 00123 XXX REV05 where X can be any digit from 0 to 9 Backcourse approaches are prohibited ...

Page 32: ...ted during approach if course deviation exceeds 50 The approach should only be continued by hand flying the airplane c The autopilot must be disengaged at the Decision Height d 12 knot maximum crosswind component between the missed approach point and outer marker e The intercept of the localizer shall occur at least 5 miles outside of the outer marker f If the crosswind component is greater than 1...

Page 33: ... Operating Handbook checklists and is advisory only The electronic checklists must not be used as the primary set of on board airplane checklists 5 The MFD interfaces with separately approved sensor installations Adherence to limitations in the appropriate sensor installation POH Supplements is mandatory 6 Traffic information shown on the Map page display is provided to the pilot as an aid to visu...

Page 34: ... child safety seat with the inflatable restraint system is prohibited Flap Limitations Serials 0002 through 0227 before accomplishment of Service Bulletin SB 22 27 02 Simultaneous Flap operation and COM transmission is prohibited Approved Takeoff Settings UP 0 or 50 Approved Landing Settings Up 0 50 or 100 Paint To ensure that the temperature of the composite structure does not exceed 150 F 66 C t...

Page 35: ... A P A C E L B A S U L A T O T S R E T I L 3 5 1 S L A G S U 40 5 4 0 0 8 4 6 5 1 0 0 1 R O L L 0 0 1 E D A R G N I M S A G V A AVGAS MIN GRADE 100LL OR 100 40 5 U S GALS 153 LITERS TOTAL USABLE CAP 23 5 U S GALS 89 LITERS USABLE TO TAB Serials 0002 thru 0549 Wing adjacent to fuel filler caps SR22_FM02_1372C Engine compartment inside oil filler access ENGINE OIL GRADE ABOVE 40 F SAE 50 OR 20W50 OR...

Page 36: ...age on external power supply door EXTERNAL POWER 28 V DC Serials 0334 subs w Ice Protection E S O L C E P O N Serials 0522 thru 0820 L E U F ON L E U F O N L E U F O N Serials 0002 thru 0521 OPEN CLOSE Serials 0334 subs w Ice Protection Elevator Rudder Elec Trim Tab if installed both sides NO PUSH SR22_FM02_1373A Doors above and below latch Placards Sheet 2 of 7 March 2010 ...

Page 37: ...serials 0002 thru 0409 after incorporating SA 02 13 MAX NORMAL ICE PROTECTION OFF CONTROL HANDLES FULLY DOWN BEFORE FLIGHT CREW SEATS MUST BE LOCKED IN POSITION AND OFF LIFT BUTTON FOR OFF POSITION OFF TURN BOOST PUMP ON BEFORE SWITCHING FUEL TANKS RIGHT 40 5 U S GALLONS USABLE LEFT 40 5 U S GALLONS USABLE 13614 001 FUEL PUMP PRIME BOOST P O W E R CUTOFF IDLE RICH MAX FLAPS Figure 2 5 Placards She...

Page 38: ...NS ACROBATIC MANEUVERS 133 KIAS SPEED Vo MANEUVERING Bolster Switch Panel left edge OPERATE PER AIRPLANE FLIGHT MANUAL FLIGHT INTO KNOWN ICING IS PROHIBITED WITH REQUIRED EQUIPMENT DAY NIGHT VFR IFR FOLLOWING FLIGHT OPERATIONS THIS AIRCRAFT IS CERTIFIED FOR THE Cabin Door Window lower edge centered applied upside down RESCUE FRACTURE AND REMOVE WINDOW Wing flap aft edge and fuselage vortex generat...

Page 39: ...T LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Baggage Compartment aft edge DISTRIBUTED FLOOR LIMIT 130 LBS BAGGAGE STRAP CAPACITY IS 35 LBS EACH MAXIMUM SEE AIRPLANE FLIGHT MANUAL FOR BAGGAGE TIE DOWN AND WEIGHT AND BALANCE INFORMATION Baggage Compartment Door inside 12378 001 REV A Figure 2 5 Placards Sheet 5 of 7 March 2010 ...

Page 40: ...RMREST LID STRIKE CORNER OF WINDOW KICK OR PUSH OUT AFTER FRACTURING Cabin Window above door latch Instrument Panel FIRE EXTINGUISHER UNDER PILOT SEAT FRONT FASTEN SEATBELTS NO SMOKING EMERGENCY EXIT REMOVE EGRESS HAMMER FROM WITHIN CENTER ARMREST LID STRIKE CORNER OF WINDOW KICK OR PUSH OUT AFTER FRACTURING Cabin Window above door latch Serials 0169 subs Serials 1863 subs Serials 0002 thru 1862 P...

Page 41: ...CIES ONLY WARNING 6 RESTRAINT SYSTEM SECURE 5 MASTER SWITCH OFF 4 FUEL SELECTOR HANDLE OFF DO NOT JERK HANDLE BOTH HANDS MAXIMUM FORCE STEADY PULL 3 ACTIVATION HANDLE PULL STRAIGHT DOWN 2 THIS COVER REMOVE 1 FUEL MIXTURE CUT OFF ACTIVATION PROCEDURE CIRRUS AIRFRAME PARACHUTE SYSTEM 133 KIAS MAXIMUM DEMONSTRATED DEPLOYMENT SPEED IN INJURY OR DEATH USE OF THIS DEVICE COULD RESULT MUST BE WORN AT ALL...

Page 42: ...2 28 Information Manual Section 2 Cirrus Design Limitations SR22 March 2010 Intentionally Left Blank ...

Page 43: ...In Flight Emergencies 3 9 Engine Failure On Takeoff Low Altitude 3 9 Maximum Glide 3 10 Engine Failure In Flight 3 11 Engine Airstart 3 12 Engine Partial Power Loss 3 13 Low Oil Pressure 3 15 Propeller Governor Failure 3 15 Smoke and Fume Elimination 3 16 Engine Fire In Flight 3 16 Wing Fire In Flight 3 16 Cabin Fire In Flight 3 17 Emergency Descent 3 18 Inadvertent Spiral Dive During IMC Flight 3...

Page 44: ...3 2 Information Manual 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 March 2010 ...

Page 45: ... 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 Note Emergency procedures associated with optional systems can be found in Section 9 March 2010 ...

Page 46: ...s Design Emergency Procedures SR22 Airspeeds for Emergency Operations Maneuvering Speed 3400 lb 133 KIAS Best Glide 3400 lb 88 KIAS 2900 lb 87 KIAS Emergency Landing Engine out Flaps Up 90 KIAS Flaps 50 85 KIAS Flaps 100 80 KIAS March 2010 ...

Page 47: ...no damage occurred during the previous flight or while the airplane was on the ground Pay special attention to any oil leaks or fuel stains that could indicate engine problems Methodology Aircraft emergencies are very dynamic events Because of this it is impossible to address every action a pilot might take to handle a situation However four basic actions can be applied to any emergency They are M...

Page 48: ...nt is determined to be safer than continued flight and landing Refer to Section 10 Safety Information for CAPS deployment information and landing considerations Land as soon as Conditions Permit Once you have handled the emergency assess your next move Handle any non critical clean up items in the checklist and put the aircraft on the ground Remember even if the airplane appears to be in sound con...

Page 49: ...the fire back into the engine by continuing to crank the engine 1 Mixture CUTOFF 2 Fuel Pump OFF 3 Fuel Selector OFF 4 Power Lever FORWARD 5 Starter CRANK 6 If flames persist perform Emergency Engine Shutdown on Ground and Emergency Ground Egress checklists Emergency Engine Shutdown On Ground 1 Power Lever IDLE 2 Fuel Pump if used OFF 3 Mixture CUTOFF 4 Fuel Selector OFF 5 Ignition Switch OFF 6 Ba...

Page 50: ...r of other aircraft spinning propellers and other hazards 1 Engine SHUTDOWN Note If the engine is left running set the Parking Brake prior to evacuating the airplane 2 Seat belts RELEASE 3 Airplane EXIT Note If the doors cannot be opened break out the windows with egress hammer located in the console between the front seats and crawl through the opening March 2010 ...

Page 51: ...ish a glide attitude In most cases the landing should be made straight ahead turning only to avoid obstructions After establishing a glide for landing perform as many of the checklist items as time permits WARNING If a turn back to the runway is elected be very careful not to stall the airplane 1 Best Glide or Landing Speed as appropriate ESTABLISH 2 Mixture CUTOFF 3 Fuel Selector OFF 4 Ignition S...

Page 52: ...Glide Ratio 9 6 1 Conditions Example Power OFF Altitude 10 000 ft AGL Propeller Windmilling Airspeed Best Glide Flaps 0 UP Wind Zero Glide Distance 15 8 NM 14000 12000 10000 8000 6000 2000 4000 0 6 8 10 12 14 16 18 4 2 20 0 GROUND DISTANCE NAUTICAL MILES HEIGHT ABOVE GROUND FEET SR22_FM03_1391 Figure 3 1 Maximum Glide March 2010 ...

Page 53: ... fuel fumes in the cockpit or if internal engine damage is suspected move Mixture Control to CUTOFF and do not attempt a restart 1 Best Glide Speed ESTABLISH Note With a seized or failed engine the distance that the airplane will glide will be more than the distance it would glide with the engine at idle such as during training If the propeller is windmilling some additional glide range may be ach...

Page 54: ... mixture may correct faulty mixture control Note Engine airstarts may be performed during 1g flight anywhere within the normal operating envelope of the airplane 1 Bat Master Switches ON 2 Power Lever OPEN 3 Mixture RICH AS REQ D 4 Fuel Selector SWITCH TANKS 5 Ignition Switch BOTH 6 Fuel Pump BOOST 7 Alternate Induction Air ON 8 Alt Master Switches OFF 9 Starter Propeller not Windmilling ENGAGE 10...

Page 55: ...f a partial engine failure permits level flight land at a suitable airfield as soon as conditions permit If conditions do not permit safe level flight use partial power as necessary to set up a forced landing pattern over a suitable landing field Always be prepared for a complete engine failure and consider CAPS deployment if a suitable landing site is not available Refer to Section 10 Safety Info...

Page 56: ...r flight conditions 4 Power Lever SWEEP Sweep the Power Lever through range as required to obtain smooth operation and required power 5 Alternate Induction Air ON A gradual loss of manifold pressure and eventual engine roughness may result from the formation of intake ice Opening the alternate engine air will provide air for engine operation if the normal source is blocked or the air filter is ice...

Page 57: ...nalysis of the low oil pressure indication to confirm oil pressure has actually been lost If low oil pressure is accompanied by normal oil temperature it is possible that the oil pressure sensor gage or relief valve is malfunctioning In any case land as soon as practical and determine cause 1 Power Lever MINIMUM REQUIRED 2 Land as soon as possible Propeller Governor Failure If the RPM does not res...

Page 58: ...l supply to the engine once a safe landing is assured 1 Heater OFF 2 Air Vents OPEN FULL COLD 3 Prepare to land as soon as possible If airflow is not sufficient to clear smoke or fumes from cabin 4 Cabin Doors PARTIALLY OPEN Airspeed may need to be reduced to partially open door in flight Engine Fire In Flight If an engine fire occurs during flight do not attempt to restart the engine 1 Mixture CU...

Page 59: ...ening the vents or doors may feed the fire but to avoid incapacitating the crew from smoke inhalation it may be necessary to rid cabin of smoke or fire extinguishant If the cause of fire is not readily apparent is electrical or is not readily accessible proceed as follows WARNING Serials 0435 and subsequent with PFD If the airplane is in IMC conditions turn ALT 1 ALT 2 and BAT 1 switches OFF Power...

Page 60: ...is in night weather or IFR conditions WARNING If airplane is in day VFR conditions and turning off the master switches eliminated the fire situation leave the master switches OFF Do not attempt to isolate the source of the fire by checking each individual electrical component 10 Bat Alt Master Switches ON 11 Avionics Power Switch ON 12 Activate required systems one at a time Pause several seconds ...

Page 61: ...ployment information 1 Power Lever IDLE 2 Stop the spiral dive by using coordinated aileron and rudder control while referring to the attitude indicator and turn coordinator to level the wings 3 Cautiously apply elevator back pressure to bring airplane to level flight attitude 4 Trim for level flight 5 Set power as required 6 Use autopilot if functional otherwise keep hands off control yoke use ru...

Page 62: ...never abusing the flight controls with accelerated inputs when close to the stall see Stalls Section 4 If at the stall the controls are misapplied and abused accelerated inputs are made to the elevator rudder and or ailerons an abrupt wing drop may be felt and a spiral or spin may be entered In some cases it may be difficult to determine if the aircraft has entered a spiral or the beginning of a s...

Page 63: ... activated when any other means of handling the emergency would not protect the occupants from serious injury Caution Expected impact in a fully stabilized deployment is equivalent to a drop from approximately 13 feet Note Several possible scenarios in which the activation of the CAPS would be appropriate are discussed in Section 10 Safety Information of this Handbook These include Mid air collisi...

Page 64: ...lder Clasp both hands around the handle and pull straight down in a strong steady and continuous motion Maintain maximum pull force until the rocket activates Pull forces up to or exceeding 45 pounds may be required Bending of the handle housing mount is to be expected WARNING Jerking or rapidly pulling the activation T handle will greatly increase the pull forces required to activate the rocket U...

Page 65: ...g body position is assumed by placing both hands on the lap clasping one wrist with the opposite hand and holding the upper torso erect and against the seat backs 14 After the airplane comes to a complete stop evacuate quickly and move upwind As occupants exit the airplane the reduced weight may allow winds to drag the airplane further As a result of landing impact the doors may jam If the doors c...

Page 66: ...ces use full flaps if possible Land on the main gear and hold the nose wheel off the ground as long as possible If engine power is available before attempting an off airport landing fly over the landing area at a low but safe altitude to inspect the terrain for obstructions and surface conditions Note Use of full 100 flaps will reduce glide distance Full flaps should not be selected until landing ...

Page 67: ...essure on the doors If the doors cannot be opened break out the windows with the egress hammer and crawl through the opening 5 Flotation Devices INFLATE WHEN CLEAR OF AIRPLANE Landing Without Elevator Control The pitch trim spring cartridge is attached directly to the elevator and provides a backup should you lose the primary elevator control system Set elevator trim for a 80 KIAS approach to land...

Page 68: ...f air data the affected indicator is removed from the display and replaced with a red X If loss of air data occurs refer to the mechanical standby instruments altitude airspeed and perform the following procedure 1 Land as soon as practical 2 Standby Instruments altitude airspeed MONITOR If failure occurs while flying in IMC 3 Exit IMC PFD Loss of Attitude Data In the event the PFD detects a loss ...

Page 69: ...lever control movements Use power available and flaps as required to safely land the airplane If the power lever is stuck at or near the full power position proceed to a suitable airfield Fly a forced landing pattern With landing assured shut down engine by moving mixture control full aft to CUTOFF If power is needed again return mixture control to full RICH and regain safe pattern parameters or g...

Page 70: ...3 28 Information Manual Section 3 Cirrus Design Emergency Procedures SR22 March 2010 Intentionally Left Blank ...

Page 71: ...f 3A 5 In Flight Procedures 3A 6 Inadvertent Icing Encounter 3A 6 Inadvertent IMC Encounter 3A 6 Door Open In Flight 3A 6 Landing Procedures 3A 7 Landing With Failed Brakes 3A 7 Landing With Flat Tire 3A 7 System Malfunctions 3A 9 Alternator Failure 3A 9 Engine Indicating System Failure 3A 11 LOW VOLTS Warning Light Illuminated 3A 11 Communications Failure 3A 12 Pitot Static Malfunction 3A 13 Elec...

Page 72: ...3A 2 Information Manual Section 3A Cirrus Design Abnormal Procedures SR22 March 2010 Intentionally Left Blank ...

Page 73: ...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 March 2010 ...

Page 74: ...orough study of the information in this handbook while on the ground will help you prepare for time critical situations in the air Sound judgement as well as thorough knowledge of the aircraft its characteristics and the flight manual procedures are essential in the handling of any abnormal system and or flight condition In addition to the outlined items in the Abnormal Procedures the following st...

Page 75: ... airplane sufficiently to turn off the runway 1 Power Lever IDLE 2 Brakes AS REQUIRED Caution For maximum brake effectiveness retract flaps hold control yoke full back and bring the airplane to a stop by smooth even application of the brakes to avoid loss of control and or a blown tire After a high speed aborted takeoff brake temperatures will be elevated subsequent aborted takeoffs or other high ...

Page 76: ...n entering IMC a pilot who is not completely proficient in instrument flying should rely upon the autopilot to execute a 180 turn to exit the conditions Immediate action should be made to turn back as follows 1 Airplane Control Establish Straight and Level Flight 2 Autopilot Engage to hold Heading and Altitude 3 Heading Reset to initiate 180 turn Door Open In Flight The doors on the SR22 will rema...

Page 77: ...ce Note Rudder effectiveness will decrease with decreasing airspeed 4 Perform Emergency Engine Shutdown on Ground checklist Landing With Flat Tire If a flat tire or tread separation occurs during takeoff and you cannot abort land as soon as conditions permit Main Gear 1 Land on the side of the runway corresponding to the good tire 2 Maintain directional control with the brakes and rudder 3 Do not ...

Page 78: ...AL COM 2 ENCODER XPONDER WEATHER STORMSCOPE AUDIO PANEL MFD AVIONICS FUEL QTY HOBBS INST LIGHTS PITCH TRIM ICE PROTECTION BATT SKYWATCH TAWS ROLL TRIM ALT 1 ALT 2 AMMETER BAT 2 BAT 1 ALT 2 ALT 1 MAIN DISTRIBUTION BUS ESSENTIAL DISTRIBUTION BUS NON ESSENTIAL ESSENTIAL MAIN BUS 1 ALT 1 CABIN LIGHTS HSI PFD 2 ATTITUDE 2 TURN COORD 2 MAIN BUS 2 FUEL PUMP NON ESSENTIAL GPS 2 SR22_FM03_1453D Serials 160...

Page 79: ... flashing ALT 1 light indicates an excessive charging rate This could occur with a very low BAT 1 and heavy equipment loads Since the loads on ALT 2 are much lower it is unlikely that a flashing ALT 2 light could occur even with a very low BAT 2 The Power Distribution Schematic shows the electrical system power distribution Individual loads on each circuit breaker panel bus are shown in the same o...

Page 80: ... thru 1666 The most likely cause is a severely discharged battery along with heavy equipment loads In this event reduce loads on Main and Non Essential buses and monitor amperage until charging rate is within normal limits Then loads can be added as required 1 Ammeter Switch BATT 2 If charging rate is greater than 30 amps reduce load on Main Bus 1 Main Bus 2 and Non Essential buses 3 Monitor ammet...

Page 81: ... readouts will display as three white dashes the CHT and EGT bar graphs will be removed and indicator needles displayed on the simulated gages will be removed In the event of DAU failure pull and reset the ANNUN ENGINE INST circuit breaker If the engine indicating system fails to reset land as soon as practical 1 ANNUN ENGINE INST Circuit Breaker Cycle 2 Land as soon as practical LOW VOLTS Warning...

Page 82: ...ation is not restored proceed with FAR AIM lost communications procedures Note In the event of an audio panel power failure the audio panel connects COM 1 to the pilot s headset and speakers Setting the audio panel Off will also connect COM 1 to the pilot s headsets and speakers 1 Switches Controls CHECK 2 Frequency CHANGE 3 Circuit Breakers CHECK 4 Headset CHANGE 5 Hand Held Microphone CONNECT Ma...

Page 83: ...hrough the vertical speed indicator the vertical speed UP DOWN indications will be reversed i e the needle will indicate UP for descent and DOWN for climb With the alternate static source on adjust indicated airspeed slightly during climb or approach according to the Airspeed Calibration Alternate Static Source table in Section 5 as appropriate for vent heater configuration 1 Pitot Heat ON 2 Alter...

Page 84: ...naway 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 1 Airplane Control MAINTAIN MANUALLY 2 Autopilot if engaged Disengage If Problem Is Not Corrected 3 Circuit Breakers PULL AS Required PITCH TRIM ROLL TRIM AUTOPILOT 4 Power Lever AS REQUIRED 5 Control Yoke MANUALLY HOLD PRESSURE 6 Land as soon as ...

Page 85: ...g Engine 4 11 Before Taxiing 4 13 Taxiing 4 13 Before Takeoff 4 14 Maximum Power Fuel Flow 4 16 Takeoff 4 17 Normal Takeoff 4 17 Short Field Takeoff 4 18 Climb 4 18 Cruise 4 19 Cruise Leaning 4 20 Descent 4 20 Before Landing 4 20 Landing 4 21 Balked Landing Go Around 4 22 After Landing 4 22 Shutdown 4 23 Stalls 4 24 Environmental Considerations 4 25 Cold Weather Operation 4 25 Hot Weather Operatio...

Page 86: ...4 2 Information Manual Section 4 Cirrus Design Normal Procedures SR22 Intentionally Left Blank March 2010 ...

Page 87: ...al 4 3 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 March 2010 ...

Page 88: ... Normal Flaps 50 70 KIAS Obstacle Clearance Flaps 50 78 KIAS Enroute Climb Flaps Up Normal 110 120 KIAS Best Rate of Climb SL 101 KIAS Best Rate of Climb 10 000 95 KIAS Best Angle of Climb SL 78 KIAS Best Angle of Climb 10 000 82 KIAS Landing Approach Normal Approach Flaps Up 90 95 KIAS Normal Approach Flaps 50 85 90 KIAS Normal Approach Flaps 100 80 85 KIAS Short Field Flaps 100 VREF 77 KIAS Go A...

Page 89: ...damage condition and evidence of delamination check all control surfaces for proper movement and excessive free play check area around liquid reservoirs and lines for evidence of leaking In cold weather remove all frost ice or snow from fuselage wing stabilizers and control surfaces Ensure that control surfaces are free of internal ice or debris Check that wheel fairings are free of snow and ice a...

Page 90: ...ion j Stall Warning Test Note Test stall warning system by applying suction to the stall warning system inlet and noting the warning horn sounds k Fuel Quantity Check l Fuel Selector Select Fullest Tank m Flaps 100 Check Light ON n Oil Annunciator On o Bat 1 and 2 Master Switches OFF p Alternate Static Source NORMAL q Circuit Breakers IN r Fire Extinguisher Charged and Available s Emergency Egress...

Page 91: ...urely attached c Elevator and Tab Condition and Movement d Rudder Freedom of Movement e Rudder Trim Tab Condition and Security f Attachment hinges bolts and cotter pins Secure 4 Right Fuselage a Static Button Check for Blockage b Wing Fuselage Fairings Check c Door Lock Unlock 5 Right Wing Trailing Edge a Flap and Rub Strips if installed Condition and Security b Aileron and Tab Condition and Movem...

Page 92: ...mbly has been overheated The brake linings must be inspected and O rings replaced f Wheel and Brakes Fluid Leaks Evidence of Overheating General Condition and Security g Chocks and Tiedown Ropes Remove h Cabin Air Vent Unobstructed 8 Nose Right Side a Vortex Generator Condition b Cowling Attachments Secure c Exhaust Pipe Condition Security and Clearance d Transponder Antenna underside Condition an...

Page 93: ...tion Inflation and Wear Caution Serials 0002 through 1727 after Service Bulletin SB 2X 32 14 and airplane serials 1728 and subsequent Clean and inspect temperature indicator installed to piston housing If indicator center is black the brake assembly has been overheated The brake linings must be inspected and O rings replaced c Wheel and Brakes Fluid Leaks Evidence of Overheating General Condition ...

Page 94: ...TED WARNING Ensure that the airplane is properly loaded and within the AFM s weight and balance limitations prior to takeoff 2 Weight and Balance Verify within limits 3 Emergency Equipment ON BOARD 4 Passengers BRIEFED Note Ensure all the passengers have been fully briefed on smoking the use of the seat belts doors emergency exits egress hammer and CAPS Verify CAPS handle safety pin is removed 5 S...

Page 95: ... the engine is under primed especially with a cold soaked engine it will not fire and additional priming will be necessary As soon as the cylinders begin to fire open the power lever slightly to keep it running Refer to Cold Weather Operation in this section or additional information regarding cold weather operations WARNING If airplane will be started using external power keep all personnel and p...

Page 96: ...ent On first start of the day especially under cool ambient conditions holding Fuel Pump switch to PRIME for 2 seconds will improve starting 8 Propeller Area CLEAR 9 Power Lever OPEN INCH 10 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 11 Power Lever RE...

Page 97: ...ion in power will result in increased brake temperature Taxi over loose gravel at low engine speed to avoid damage to the propeller tips WARNING Maximum continuous engine speed for taxiing is 1000 RPM on flat smooth hard surfaces Power settings slightly above 1000 RPM are permissible to start motion for turf soft surfaces and on inclines Use minimum power to maintain taxi speed If the 1000 RPM tax...

Page 98: ...ice snow or other contamination on the fuselage wing stabilizers and control surfaces 1 Doors LATCHED 2 CAPS Handle Verify Pin Removed 3 Seat Belts and Shoulder Harness SECURE 4 Fuel Quantity CONFIRM 5 Fuel Selector FULLEST TANK 6 Fuel Pump BOOST 7 Mixture AS REQUIRED 8 Flaps SET 50 CHECK 9 Transponder SET 10 Autopilot CHECK 11 Navigation Radios GPS SET for Takeoff 12 Cabin Heat Defrost AS REQUIRE...

Page 99: ...note RPM then BOTH b Ignition Switch L note RPM then BOTH Note RPM drop must not exceed 150 RPM for either magneto RPM differential must not exceed 75 RPM between magnetos If there is a doubt concerning operation of the ignition system RPM checks at higher engine speeds will usually confirm whether a deficiency exists An absence of RPM drop may indicate faulty grounding of one side of the ignition...

Page 100: ...trated to obtain the takeoff and climb performance presented in Section 5 Note Excessively rich mixture will occur if the Mixture control is set to FULL RICH above 7500 feet pressure altitude Pressure Altitude Target Fuel Flow Pressure Altitude Target Fuel Flow Pressure Altitude Target Fuel Flow 0 27 1 7000 21 4 14 000 17 5 1000 26 2 8000 20 5 15 000 16 9 2000 25 1 9000 19 9 16 000 16 7 3000 24 3 ...

Page 101: ...ot approved Soft or rough field takeoffs are performed with 50 flaps by lifting the airplane off the ground as soon as practical in a tail low attitude If no obstacles are ahead the airplane should be leveled off immediately to accelerate to a higher climb speed Takeoffs into strong crosswinds are normally performed with the flaps set at 50 to minimize the drift angle immediately after takeoff Wit...

Page 102: ...ity and engine cooling For maximum rate of climb use the best rate of climb speeds shown in the rate of climb chart in Section 5 If an obstruction dictates the use of a steep climb angle the best angle of climb speed should be used Climbs at speeds lower than the best rate of climb speed should be of short duration to avoid engine cooling problems 1 Climb Power SET 2 Flaps Verify UP 3 Mixture LEAN...

Page 103: ...ise at a minimum of 75 power until the engine has been operated for at least 25 hours or until oil consumption has stabilized Operation at this higher power will ensure proper seating of the rings is applicable to new engines and engines in service following cylinder replacement or top overhaul of one or more cylinders 1 Fuel Pump OFF Note The Fuel Pump may be used for vapor suppression during cru...

Page 104: ...ons engine roughness may occur while operating at best economy If this occurs enrich mixture as required to smooth engine operation Any change in altitude or Power Lever position will require a recheck of EGT indication Descent 1 Altimeter SET 2 Cabin Heat Defrost AS REQUIRED 3 Landing Light ON 4 Fuel System CHECK 5 Mixture AS REQUIRED 6 Brake Pressure CHECK Before Landing 1 Seat Belt and Shoulder...

Page 105: ...n the main wheels first to reduce the landing speed and subsequent need for braking Gently lower the nose wheel to the runway after airplane speed has diminished This is especially important for rough or soft field landings Short Field Landing For a short field landing in smooth air conditions make an approach at 77 KIAS with full flaps using enough power to control the glide path slightly higher ...

Page 106: ...he flap setting to 50 If obstacles must be cleared during the go around climb at 75 80 KIAS with 50 flaps After clearing any obstacles retract the flaps and accelerate to the normal flaps up climb speed 1 Autopilot DISENGAGE 2 Power Lever FULL FORWARD 3 Flaps 50 4 Airspeed 75 80 KIAS After clear of obstacles 5 Flaps UP After Landing 1 Power Lever 1000 RPM 2 Fuel Pump OFF 3 Flaps UP 4 Transponder S...

Page 107: ...through the OFF position If the engine does not hesitate one or both magnetos are not grounded Prominently mark the propeller as being Hot and contact maintenance personnel immediately 4 Mixture CUTOFF 5 All Switches OFF 6 Magnetos OFF 7 ELT TRANSMIT LIGHT OUT Note After a hard landing the ELT may activate If this is suspected press the RESET button 8 Chocks Tie downs Pitot Covers AS REQUIRED Marc...

Page 108: ... reduced you will notice a slight airframe buffet and hear the stall speed warning horn sound between 5 and 10 knots before the stall Normally the stall is marked by a gentle nose drop and the wings can easily be held level or in the bank with coordinated use of the ailerons and rudder Upon stall warning in flight recovery is accomplished by immediately by reducing back pressure to maintain safe a...

Page 109: ...es in strength the spark plugs have probably frosted over Preheat must be used before another start is attempted WARNING If airplane will be started using external power keep all personnel and power unit cables well clear of the propeller rotation plane Caution Inadequate application of preheat to a cold soaked engine may warm the engine enough to permit starting but will not de congeal oil in the...

Page 110: ...loose or broken ground wire on either magneto could cause the engine to fire 2 Propeller Hand TURN several rotations 3 External Power If applicable CONNECT 4 Brakes HOLD 5 Bat Master Switches ON check voltage 6 Mixture FULL RICH 7 Power lever FULL FORWARD 8 Fuel Pump PRIME then BOOST Note Serials 0002 0278 before SB 22 73 01 In temperatures down to 20 F hold Fuel Pump switch to PRIME for 60 120 se...

Page 111: ...RETARD to maintain 1000 RPM 13 Oil Pressure CHECK 14 Alt Master Switches ON 15 Avionics Power Switch ON 16 Engine Parameters MONITOR 17 External Power If applicable DISCONNECT 18 Amp Meter Indication CHECK 19 Strobe Lights ON Hot Weather Operation Avoid prolonged engine operation on the ground Note Fuel BOOST must be ON for engine start and takeoff and should be ON during climb for vapor suppressi...

Page 112: ...ures minimize environmental noise when operating the SR22 Note Do not follow these noise abatement procedures where they conflict with Air Traffic Control clearances or instructions weather considerations or wherever they would reduce safety 1 When operating VFR over noise sensitive areas such as outdoor events parks and recreational areas fly not less than 2000 feet above the surface even though ...

Page 113: ...nformation Manual 4 29 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 March 2010 ...

Page 114: ...4 30 Information Manual Section 4 Cirrus Design Normal Procedures SR22 March 2010 Intentionally Left Blank ...

Page 115: ...Calibration 5 11 Alternate Static Source 5 11 Altitude Correction 5 12 Normal Static Source 5 12 Altitude Correction 5 13 Alternate Static Source 5 13 Temperature Conversion 5 14 Outside Air Temperature for ISA Condition 5 15 Stall Speeds 5 16 Wind Components 5 17 Takeoff Distance 5 18 Takeoff Distance 5 19 Takeoff Distance 5 20 Takeoff Climb Gradient 5 21 Takeoff Rate of Climb 5 22 Enroute Climb ...

Page 116: ...ormance Data SR22 Cruise Performance 5 29 Range Endurance Profile 5 30 Range Endurance Profile 5 31 Range Endurance Profile 5 32 Balked Landing Climb Gradient 5 33 Balked Landing Rate of Climb 5 34 Landing Distance 5 35 Landing Distance 5 36 March 2010 ...

Page 117: ...e piloting techniques Unless specifically noted in the Conditions notes presented with each table ambient conditions are for a standard day refer to Section 1 Flap position as well as power setting technique is similarly noted with each table The charts in this section provide data for ambient temperatures from 20 C 4 F to 40 C 104 F If ambient temperature is below the chart value use the lowest t...

Page 118: ...erations and compliant with the Federal Aviation Regulations FARs or governing regulations as applicable Note Whenever possible select the most conservative values from the following charts to provide an extra margin of safety and to account for events that could occur during a flight Sample Problem The following sample flight problem uses information derived from the airplane performance charts a...

Page 119: ... sample problem the takeoff distance information presented for a weight of 3400 pounds takeoff field pressure altitude of 2000 feet and a temperature of 30 C should be used Using the conservative values results in the following Ground roll 1385 Feet Total distance to clear a 50 foot obstacle 2107 Feet Since the takeoff distance tables are based upon a zero wind conditions a correction for the effe...

Page 120: ...lues to be used for flight planning the start of climb time fuel and distance values are subtracted from the end of climb cruise altitude values Again conservative values are obtained by using the next lower altitude value for start of climb or next higher altitude values for end of climb Using conservative values for the sample data the following calculations are made Start of climb values SL to ...

Page 121: ...nce trip length and winds aloft A typical cruise altitude and the expected winds aloft are given for this sample problem Power selection for cruise should be based upon the cruise performance characteristics tabulated in Figure 5 15 and the range endurance profile for maximum power is presented in Figure 5 16 The relationship between power and range as well as endurance is shown in the range endur...

Page 122: ... ground speed for cruise is expected to be 147 knots Therefore the time required for the cruise portion of the trip is 549 3 NM 147 knots 3 7 hours The fuel required for cruise is 3 7 hours x 15 3 GPH 56 6 gallons From the 6000 ft Cruise Table Figure 5 15 a 45 minute IFR reserve at approximately 55 power requires 45 60 x 15 3 GPH 11 5 gallons The total estimated fuel required is as follows Engine ...

Page 123: ...r a 50 foot obstacle 2476 Feet A correction for the effect of wind may be made based on the headwind and tailwind corrections presented with the landing chart using the same procedure as outlined for takeoff Corrections for runway slope and dry grass may also be applied in like manner Demonstrated Operating Temperature Satisfactory engine cooling has been demonstrated for this airplane with an out...

Page 124: ...ots Indicated Airspeed KCAS Knots Calibrated Airspeed Conditions Example Power for level flight or maximum continuous whichever is less Flaps 50 Indicated Airspeed 85 Knots Calibrated Airspeed 85 Knots KIAS KCAS Flaps 0 Flaps 50 Flaps 100 60 58 70 68 69 80 79 80 80 90 90 91 90 100 100 101 100 110 110 111 120 121 121 130 131 140 142 150 152 160 162 170 172 180 183 190 193 200 203 March 2010 ...

Page 125: ...KCAS Knots Calibrated Airspeed Conditions Example Power for level flight or maximum continuous whichever is less Flaps 50 Indicated Airspeed 85 Knots Heater Defroster Vents ON Calibrated Airspeed 86 Knots KIAS KCAS Flaps 0 Flaps 50 Flaps 100 60 62 70 71 73 80 80 81 82 90 90 91 92 100 100 101 101 110 110 111 120 120 121 130 130 140 140 150 150 160 160 170 170 180 180 190 190 200 199 Figure 5 2 Marc...

Page 126: ...ximum continuous whichever is less Flaps 0 Indicated Airspeed 120 Knots Desired Altitude 12 000 FT Altitude Correction 13 FT Altitude to Fly 11 987 FT Flaps Press Alt CORRECTION TO BE ADDED FEET Normal Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 8 6 3 0 9 19 31 44 56 5000 10 7 4 0 10 23 36 51 65 10000 11 8 5 0 12 26 42 59 76 15000 13 10 5 0 14 31 50 70 90 50 S L 14 3 6 12 6 5000 1...

Page 127: ... whichever is less Flaps 0 Indicated Airspeed 120 Knots Heater Defroster Vents ON Desired Altitude 12 000 FT Altitude Correction 4 FT Altitude to Fly 11 996 FT Flaps Press Alt CORRECTION TO BE ADDED FEET Normal Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 1 0 1 1 3 3 1 4 13 5000 2 0 1 2 3 3 1 5 15 10000 2 1 1 2 4 4 1 6 18 15000 2 1 1 2 4 4 1 7 21 50 S L 7 6 5 5 9 5000 8 7 6 6 10 10...

Page 128: ...6 17 62 144 49 56 69 16 4 39 18 64 147 48 54 65 14 6 43 19 66 151 47 52 62 13 8 46 20 68 154 46 50 58 12 10 50 21 70 158 44 48 54 11 12 54 22 72 162 43 46 51 10 14 57 23 74 165 42 44 47 9 16 61 24 76 169 41 42 44 8 18 64 26 78 172 40 40 40 7 20 68 27 80 176 39 38 36 6 22 72 28 82 180 38 36 33 4 24 75 29 84 183 37 34 29 3 26 79 30 86 187 36 32 26 2 28 82 31 88 190 34 30 22 1 30 86 32 90 194 33 28 1...

Page 129: ... 31 88 3000 31 24 11 12 9 48 19 66 29 84 4000 33 27 13 9 7 45 17 63 27 81 5000 35 31 15 5 5 41 15 59 25 77 6000 37 34 17 2 3 38 13 56 23 74 7000 39 38 19 2 1 34 11 52 21 70 8000 41 42 21 6 1 30 10 48 20 66 9000 43 45 23 9 3 27 7 45 17 63 10000 45 49 25 13 5 23 5 41 15 59 11000 47 52 27 16 7 20 3 38 13 56 12000 49 56 29 20 9 16 1 34 11 52 13000 51 59 31 23 11 13 1 31 9 49 14000 53 63 33 27 13 9 3 2...

Page 130: ...oted Bank Angle 15 Power Idle C G Forward Bank Angle Noted Stall Speed 71 KIAS 70 KCAS Weight LB Bank Angle Deg STALL SPEEDS Flaps 0 Full Up Flaps 50 Flaps 100 Full Down KIAS KCAS KIAS KCAS KIAS KCAS 3400 Most FWD C G 0 70 69 67 64 59 59 15 71 70 68 65 62 60 30 75 74 72 69 66 64 45 84 82 80 76 73 70 60 99 97 95 90 87 84 3400 Most AFT C G 0 68 67 66 62 61 59 15 69 68 67 63 62 60 30 73 72 71 67 65 6...

Page 131: ...le 50 Wind Direction 60 Crosswind Component 12 Knots Wind Velocity 15 Knots Headwind Component 10 Knots 10 Headwind Tailwind 0 A N G L E B E T W E E N W I N D D I R E C T I O N A N D F L I G H T P A T H 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 V E L O C I T Y K N O T S W IND 40 40 30 20 10 WIND COMPONENTS KNOTS CROSSWIND COMPONENT KNOTS 20 10 0 10 20 40 30 SR22_FM05_1014 10 20 3...

Page 132: ...ve corrections for runway slope are required to be included herein These corrections should be used with caution since published runway slope data is usually the net slope from one end of the runway to the other Many runways will have portions of their length at greater or lesser slopes than the published slope lengthening or shortening takeoff ground roll estimated from the table If brakes are no...

Page 133: ...813 1939 2069 1728 2000 Grnd Roll 1116 1206 1299 1395 1496 1215 50 ft 1732 1861 1995 2133 2276 1874 3000 Grnd Roll 1234 1332 1435 1542 1653 1323 50 ft 1907 2049 2196 2349 2507 2035 4000 Grnd Roll 1365 1474 1588 1706 1829 1441 50 ft 2102 2259 2422 2590 2764 2212 5000 Grnd Roll 1512 1633 1758 1889 2025 1572 50 ft 2320 2493 2673 2858 3051 2407 6000 Grnd Roll 1676 1810 1950 2095 2245 1717 50 ft 2564 2...

Page 134: ... 1066 1146 1228 1313 1401 1170 2000 Grnd Roll 743 802 864 929 995 809 50 ft 1173 1260 1351 1444 1541 1269 3000 Grnd Roll 821 887 955 1026 1100 880 50 ft 1292 1388 1487 1590 1697 1378 4000 Grnd Roll 908 981 1057 1135 1217 959 50 ft 1424 1530 1639 1753 1871 1498 5000 Grnd Roll 1006 1086 1170 1257 1348 1046 50 ft 1571 1688 1809 1935 2065 1630 6000 Grnd Roll 1116 1205 1298 1394 1494 1143 50 ft 1736 18...

Page 135: ... warmer than this table provides use extreme caution Conditions Example Power Full Throttle Outside Air Temp 20 C Mixture Set per Placard Weight 3400 LB Flaps 50 Pressure Altitude 4000 FT Airspeed Best Rate of Climb Climb Airspeed 89 Knots Gradient 654 FT NM Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile Temperature C 20 0 20 40 ISA 3400 SL 91 939 896 853 811 864 200...

Page 136: ... this table provides use extreme caution Conditions Example Power Full Throttle Outside Air Temp 10 C Mixture Set per Placard Weight 3400 LB Flaps 50 Pressure Altitude 6000 FT Airspeed Best Rate of Climb Climb Airspeed 88 Knots Rate of Climb 948 FPM Weight LB Press Alt FT Climb Speed KIAS RATE OF CLIMB Feet per Minute Temperature C 20 0 20 40 ISA 3400 SL 91 1326 1317 1300 1277 1304 2000 90 1214 12...

Page 137: ...ottle Outside Air Temp 20 C Mixture Full Rich Weight 3400 LB Flaps 0 UP Pressure Altitude 4000 FT Airspeed Best Rate of Climb Climb Airspeed 98 Knots Gradient 639 FT NM Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile Temperature C 20 0 20 40 ISA 3400 SL 101 911 867 823 781 834 2000 100 813 771 729 689 748 4000 98 720 679 639 600 665 6000 97 630 590 552 515 584 8000 96...

Page 138: ...emp 10 C Mixture As Required Weight 3400 LB Flaps 0 UP Pressure Altitude 6000 FT Airspeed Best Rate of Climb Climb Airspeed 97 Knots Rate of Climb 1030 FPM Weight LB Press Alt FT Climb Speed KIAS RATE OF CLIMB Feet per Minute Temperature C 20 0 20 40 ISA 3400 SL 101 1428 1414 1392 1366 1398 2000 100 1311 1292 1267 1238 1279 4000 98 1193 1170 1141 1108 1160 6000 97 1074 1046 1013 977 1041 8000 96 9...

Page 139: ...Max Power Fuel Flow Flaps 0 UP Airspeed Best Rate of Climb 1 000 2 000 3 000 4 000 5 000 6 000 7 000 8 000 9 000 10 000 11 000 12 000 13 000 14 000 15 000 16 000 17 000 4 0 0 5 0 0 6 0 0 7 0 0 8 0 0 9 0 0 1 0 0 0 1 1 0 0 1 2 0 0 1 3 0 0 1 4 0 0 1 5 0 0 1 6 0 0 1 7 0 0 1 8 0 0 3 4 0 0 L B 2 9 0 0 L B Rate of Climb Feet Per Minute Figure 5 14 March 2010 Density Altitude Feet ...

Page 140: ...3400 LB Pressure Altitude 12000 FT Winds Zero Climb Airspeed Noted Time to Climb 11 3 Minutes Fuel to Climb 5 6 Gallon Distance to Climb 20 5 NM Press Alt FT OAT ISA C Climb Speed KIAS Rate Of Climb FPM TIME FUEL DISTANCE From Sea Level Time Minutes Fuel U S Gal Distance NM SL 15 101 1398 0 0 0 0 0 0 1000 13 100 1339 0 7 0 3 1 0 2000 11 100 1279 1 5 0 7 2 5 3000 9 99 1220 2 5 1 0 4 0 4000 7 98 116...

Page 141: ...4 4 80 170 19 0 76 170 18 0 72 165 18 8 2500 23 4 76 167 18 0 72 167 17 0 68 162 18 1 4000 Feet Pressure Altitude ISA 30 C 23 C ISA 7 C ISA 30 C 37 C RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH 2700 25 4 96 185 22 9 91 185 21 6 87 180 20 8 2600 25 4 92 182 21 9 87 182 20 7 83 177 20 6 2500 25 4 87 178 20 6 82 178 19 5 78 173 19 9 2500 24 4 82 175 19 5 78 175 18 5 74 170 19 2 2500 23 4 78 172 18...

Page 142: ...2500 20 0 67 173 16 0 64 173 15 1 61 167 14 4 2500 19 0 63 168 14 9 59 168 14 1 56 163 13 4 2500 18 0 58 163 13 8 55 163 13 1 52 158 12 5 2500 17 0 54 158 12 8 51 158 12 1 48 153 11 5 12 000 Feet Pressure Altitude ISA 30 C 39 C ISA 9 C ISA 30 C 21 C RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH 2700 18 5 71 180 16 9 67 180 16 0 64 175 15 2 2600 18 5 68 177 16 2 64 177 15 3 61 172 14 5 2500 18 5 6...

Page 143: ...58 173 13 8 55 173 13 1 52 167 12 5 2500 15 8 55 168 13 0 52 168 12 3 49 163 11 7 2500 14 8 50 162 11 9 47 162 11 3 45 156 10 7 17 000 Feet Pressure Altitude ISA 30 C 49 C ISA 19 C ISA 30 C 9 C RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH 2700 15 2 59 175 13 9 55 175 13 2 53 169 12 5 2600 15 2 56 171 13 3 53 171 12 6 50 166 12 0 2500 15 2 53 167 12 5 50 167 11 9 47 162 11 3 2500 14 2 48 160 11 4...

Page 144: ... by 15 if nose and main wheel pants and fairings removed Conditions Example Weight 3400 LB Power Setting 75 Temperature Standard Day Takeoff Press Alt 2000 FT Winds Zero Cruise Press Alt 6000 FT Mixture Best Economy Total Fuel 81 Gallons Fuel to Climb 2 0 Gal Cruise Fuel Flow 17 8 GPH Endurance 3 9 Hr Range 689 NM True Airspeed 177 Knots 75 POWER Mixture Best Power Press Alt FT Climb Fuel Gal Fuel...

Page 145: ...0 8000 2 7 63 5 171 15 4 4 4 765 11 2 10000 3 5 61 6 174 15 4 4 4 775 11 5 12000 4 4 59 8 178 15 4 4 3 785 11 8 55 POWER Mixture Best Power Press Alt FT Climb Fuel Gal Fuel Remaining For Cruise Gal Airspeed KTAS Fuel Flow GPH Endurance Hours Range NM Specific Range Nm Gal SL 0 0 70 8 149 13 1 5 4 806 11 4 2000 0 7 69 0 152 13 1 5 4 815 11 6 4000 1 3 67 2 154 13 1 5 3 825 11 9 6000 2 0 65 3 157 13 ...

Page 146: ...Gal Airspeed KTAS Fuel Flow GPH Endurance Hours Range NM Specific Range Nm Gal SL 0 0 70 8 149 11 3 6 2 930 13 1 2000 0 7 69 0 152 11 3 6 2 941 13 4 4000 1 3 67 2 154 11 3 6 1 951 13 7 6000 2 0 65 3 157 11 3 6 1 962 14 0 8000 2 7 63 5 160 11 3 6 0 974 14 3 10000 3 5 61 6 163 11 3 5 9 985 14 6 12000 4 4 59 8 166 11 3 5 9 995 15 0 14000 5 3 57 8 169 11 3 5 8 1006 15 4 Sheet 3 of 3 March 2010 ...

Page 147: ...e Go Around Balked Landing procedure in Section 4 Conditions Example Power Full Throttle Outside Air Temp 20 C Mixture Set per Placard Weight 3400 LB Flaps 100 DN Pressure Altitude 4000 FT Climb Airspeed VREF Climb Airspeed 77 Knots Rate of Climb 633 FT NM Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet Nautical Mile Best Rate of Climb KIAS Temperature C 20 0 20 40 ISA 3400 SL 77 834 8...

Page 148: ...g the Go Around Balked Landing procedure in Section 4 Conditions Example Power Full Throttle Outside Air Temp 20 C Mixture Set per Placard Weight 3400 LB Flaps 100 DN Pressure Altitude 4000 FT Climb Airspeed VREF Climb Airspeed 77 Knots Rate of Climb 878 FT NM Weight LB Press Alt FT Climb Speed KIAS RATE OF CLIMB Feet per Minute Best Rate of Climb KIAS Temperature C 20 0 20 40 ISA 3400 SL 77 996 1...

Page 149: ...ctions should be used with caution since published runway slope data is usually the net slope from one end of the runway to the other Many runways will have portions of their length at greater or lesser slopes than the published slope lengthening or shortening landing ground roll estimated from the table For operation in outside air temperatures colder than this table provides use coldest data sho...

Page 150: ...2317 2374 2433 2492 2551 2391 2000 Grnd Roll 1163 1206 1248 1291 1334 1210 Total 2375 2436 2497 2559 2621 2441 3000 Grnd Roll 1207 1251 1295 1339 1384 1247 Total 2437 2501 2565 2630 2696 2493 4000 Grnd Roll 1252 1298 1344 1390 1436 1285 Total 2503 2569 2637 2705 2774 2548 5000 Grnd Roll 1300 1348 1395 1443 1490 1324 Total 2572 2642 2713 2785 2857 2605 6000 Grnd Roll 1350 1399 1449 1498 1547 1365 T...

Page 151: ...and Balance Table of Contents Introduction 6 3 Airplane Weighing Form 6 6 Airplane Weighing Procedures 6 7 Weight Balance Record 6 10 Loading Instructions 6 12 Center of Gravity Limits 6 14 Weight Balance Loading Form 6 15 Loading Data 6 16 Moment Limits 6 17 Equipment List 6 18 March 2010 ...

Page 152: ...6 2 Information Manual Section 6 Cirrus Design Weight and Balance SR22 Intentionally Left Blank March 2010 ...

Page 153: ...t for various operations are also provided A comprehensive list of all equipment available for this airplane is included at the back of this section It should be noted that specific information regarding the weight arm moment and installed equipment for this airplane as delivered from the factory can only be found in the plastic envelope carried in the back of this handbook It is the responsibilit...

Page 154: ...NOTE Reference datum located at fuselage station 0 0 MAC 47 7 50 0 100 0 150 0 200 0 50 0 100 0 150 0 230 0 LEMAC FS 133 1 RBL 87 7 Typical LBL RBL 63 1 LBL 63 1 RBL 77 3 BL 0 0 LBL 77 3 RBL 229 5 LBL 229 5 200 0 50 0 150 0 WL 100 0 100 0 50 0 0 0 150 0 200 0 250 0 300 0 350 0 BUTTOCK LINE BL BL 0 0 WATER LINE WL SR22_FM06_1439 Airplane Dimensional Data March 2010 ...

Page 155: ...Section 6 SR22 Weight Balance SR22_FM06_1440A Spirit Level LONGITUDINAL LEVELING LATERAL LEVELING Spirit Level Straight Edge Door Sill Door Sill Spacer Block Straight Edge Straight Edge Spacer Block Figure 6 2 Airplane Leveling March 2010 ...

Page 156: ...ghed CG CG Total Moment Total Weight Space below provided for additions or subtractions to as weighed condition Empty Weight CG Engine Oil if oil drained 15 lb at FS 78 4 moment 1176 Unusable Fuel 18 0 154 9 2788 Basic Empty Weight CG SR22_FM06_1441 x WL 100 0 y A B FS 100 0 FS 145 0 A x 100 B A y y ____________ Measured x ____________ Measured REF DATUM FS 0 0 Airplane Weighing Form March 2010 ...

Page 157: ...ng pressures b Service brake reservoir c Drain fuel system d Service engine oil e Move crew seats to the most forward position f Raise flaps to the fully retracted position g Place all control surfaces in neutral position h Verify equipment installation and location by comparison to equipment list 2 Leveling Figure 6 2 a Level longitudinally with a spirit level placed on the pilot door sill and la...

Page 158: ...the nosewheel weighing point arm dimension B 5 Determine and record the moment for each of the main and nose gear weighing points using the following formula Moment Net Weight x Arm 6 Calculate and record the as weighed weight and moment by totaling the appropriate columns 7 Determine and record the as weighed C G in inches aft of datum using the following formula C G Total Moment Total Weight 8 A...

Page 159: ...es the airplane Basic Empty Weight moment and center of gravity in inches aft of datum C G can also be expressed in terms of its location as a percentage of the airplane Mean Aerodynamic Cord MAC using the following formula C G MAC 100 x C G Inches LEMAC MAC Where LEMAC 133 1 MAC 47 7 March 2010 ...

Page 160: ...uous history of changes and modifications to airplane structure or equipment affecting weight and balance Serial Num Reg Num Page of Date Item No Description of Article or Modification Weight Change Added or Removed Running Basic Empty Weight In Out WT LB ARM IN MOM 1000 WT LB MOM 1000 As Delivered Weight and Balance Record March 2010 ...

Page 161: ...abin 122 49 3 49 7 137 cu ft Baggage Compartment 36 39 8 38 5 32 cu ft 39 8 49 3 240 220 200 180 160 140 120 16 0 49 7 25 0 38 5 FS 10 5 33 4 39 0 20 0 33 3 32 0 SR22_FM06_1019 100 222 CABIN DOOR OPENING BAGGAGE DOOR OPENING 20 0 21 0 5 0 Station Fuselage Figure 6 5 Airplane Interior Dimensions March 2010 ...

Page 162: ...the Loading Data Figure 6 8 3 Rear Seat Occupants Enter the total weight and moment 1000 for the rear seat occupants from the Loading Data Figure 6 8 4 Baggage Enter weight and moment for the baggage from the Loading Data Figure 6 8 If desired subtotal the weights and moment 1000 from steps 1 through 4 This is the Zero Fuel Condition It includes all useful load items excluding fuel 5 Fuel Loading ...

Page 163: ...s Design Section 6 SR22 Weight Balance The total moment 1000 must not be above the maximum or below the minimum moment 1000 for the Takeoff Condition Weight as determined from the Moment Limits chart or table Figure 6 9 March 2010 ...

Page 164: ...C FS 1 42 3 3400 lb 31 5 M AC FS 1 48 1 3400 lb 1 7 4 M AC FS 1 41 4 321 0 lb 20 5 M AC FS 1 42 6 3400 lb Landing Limitation Shaded FORWARD LIMIT The forward limit is FS 137 8 9 8 MAC at 2100 lb with straight line taper to FS 139 1 12 5 MAC at 2700 lb to FS 142 3 19 2 MAC at 3400 lb AFT LIMIT The aft limit is FS 148 1 31 5 MAC at all weights from 2100 lb to 3400 lb LANDING LIMITATION The Landing L...

Page 165: ...eoff Condition Weight Refer to Figure 6 9 Moment Limits Item Description Weight LB Moment 1000 1 Basic Empty Weight Includes unusable fuel full oil 2 Front Seat Occupants Pilot Passenger total 3 Rear Seat Occupants 4 Baggage Area 130 lb maximum 5 Zero Fuel Condition Weight Sub total item 1 thru 4 6 Fuel Loading 81 Gallon 6 0 lb gal Maximum 7 Ramp Condition Weight Sub total item 5 and 6 8 Fuel for ...

Page 166: ...7 20 8 32 6 20 280 40 18 50 40 43 37 60 8 61 10 80 12 48 9 29 300 43 05 54 00 46 47 80 11 48 14 40 16 64 12 39 320 45 92 57 60 49 57 100 14 35 18 00 20 80 15 49 340 48 79 61 20 52 67 120 17 22 21 60 24 96 18 59 360 51 66 64 80 55 76 140 20 09 25 20 27 04 21 69 380 54 53 68 40 58 86 160 22 96 28 80 24 78 400 57 40 72 00 61 96 180 25 83 32 40 27 88 420 60 27 75 60 65 06 200 28 70 36 00 30 98 440 63 ...

Page 167: ...oment 1000 Weight LB Moment 1000 Minimum Maximum Minimum Maximum 2200 304 326 2850 398 422 2250 311 333 2900 406 430 2300 318 341 2950 414 437 2350 326 348 3000 421 444 2400 333 355 3050 429 452 2450 340 363 3100 437 459 2500 347 370 3150 444 467 2550 354 378 3200 452 474 2600 362 385 3250 460 481 2650 369 392 3300 467 489 2700 375 400 3350 475 496 2750 383 407 3400 483 504 2800 390 415 2000 2200 ...

Page 168: ...6 18 Information Manual Section 6 Cirrus Design Weight Balance SR22 Equipment List This list will be determined after the final equipment has been installed in the aircraft March 2010 ...

Page 169: ...em 7 14 Roll Trim Control System 7 14 Yaw Trim System 7 15 Flight Deck Arrangement 7 16 Instrument Panel 7 16 Center Console 7 17 Flight Instruments 7 21 Primary Flight Display 7 21 Attitude Indicator 7 26 Airspeed Indicator 7 26 Vertical Speed Indicator 7 27 Altimeter 7 27 Turn Coordinator 7 28 Course Deviation Indicator 7 28 Horizontal Situation Indicator 7 29 Magnetic Compass 7 31 Wing Flaps 7 ...

Page 170: ...Fuel System 7 54 Fuel Selector Valve 7 56 Fuel Quantity Indicator 7 57 Fuel Flow Indication 7 60 Fuel Caution Light 7 60 Boost Pump Switch 7 61 Brake System 7 62 Electrical System 7 65 Power Generation 7 65 Power Distribution 7 66 BAT ALT Master Switches 7 68 Avionics Power Switch 7 69 Volts and Ampere Meter Indication 7 69 Ammeter Select Switch 7 71 Low Volts Warning Light 7 71 ALT Fail Caution L...

Page 171: ...l Warning System 7 84 Standard Avionics 7 85 Multi Function Display 7 86 Autopilot 7 88 GPS Navigation 7 91 Communication COM Transceivers 7 93 Navigation Nav Receiver 7 94 Transponder 7 95 Audio System 7 95 Emergency Locator Transmitter 7 96 Hour Meter s 7 98 Digital Clock 7 99 Cirrus Airplane Parachute System 7 101 System Description 7 101 Activation Handle 7 102 Deployment Characteristics 7 103...

Page 172: ...7 4 Information Manual Section 7 Cirrus Design Airplane Description SR22 March 2010 Intentionally Left Blank ...

Page 173: ...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 For description and operation of optional equipment not described in this section refer to Section 9 Supplements March 2010 ...

Page 174: ...ubsequent The lower firewall employes a 20 bevel to improve crashworthiness In addition an avionics bay is located aft of bulkhead 222 and accessible through an access panel installed on the RH side of the aft fuselage Note Refer to Airplane Cabin description in this section for a complete description of doors windows baggage compartment seats and safety equipment Wings The wing structure is const...

Page 175: ...ntal stabilizer a two piece elevator a vertical fin and a rudder All of the empennage components are conventional spar shear web rib and skin construction The horizontal stabilizer is a single composite structure from tip to tip The two piece elevator attached to the horizontal stabilizer is aluminum The vertical stabilizer is composite structure integral to the main fuselage shell for smooth tran...

Page 176: ...ing a switch on the forward console immediately to the left of the Flaps switch Elevator System The two piece elevator provides airplane pitch control The elevator is of conventional design with skin spar and ribs manufactured of aluminum Each elevator half is attached to the horizontal stabilizer at two hinge points and to the fuselage tailcone at the elevator control sector Elevator motion is ge...

Page 177: ...Information Manual 7 9 Cirrus Design Section 7 SR22 Airplane Description SR22_FM07_1461 Figure 7 1 Elevator Control System March 2010 ...

Page 178: ...eb at two hinge points Aileron control motion is generated through the pilot s control yokes by rotating the yokes in pivoting bearing carriages Push rods link the pivoting carriages to a centrally located pulley sector A single cable system runs from the sector to beneath the cabin floor and aft of the rear spar From there the cables are routed in each wing to a vertical sector crank arm that rot...

Page 179: ...Information Manual 7 11 Cirrus Design Section 7 SR22 Airplane Description SR22_FM07_1462 Figure 7 2 Aileron Control System March 2010 ...

Page 180: ...ion to the rudder Springs and a ground adjustable spring cartridge connected to the rudder pedal assembly tension the cables and provide centering force A rudder aileron interconnect is installed to provide a maximum of 5 down aileron with full rudder deflection Right rudder input will cause right roll input and left rudder input will cause left roll input With neutral aileron trim aileron inputs ...

Page 181: ...Information Manual 7 13 Cirrus Design Section 7 SR22 Airplane Description SR22_FM07_1463 Figure 7 3 Rudder Control System March 2010 ...

Page 182: ...own trim and moving the switch aft will initiate nose up trim Neutral takeoff trim is indicated by the alignment of a reference mark on the yoke tube with a tab attached to the instrument panel bolster The elevator trim also provides a secondary means of aircraft pitch control in the event of a failure in the primary pitch control system not involving a jammed elevator Elevator pitch trim operates...

Page 183: ...uator connected to a hinged trim tab on the rudder trailing edge The actuator is installed in the rudder A RUDDER TRIM indicator with integral rocker switch is mounted in the console immediately adjacent to the FLAP control switch Pressing the left half of the switch initiates Nose L trim and pressing the right half initiates Nose R trim A needle sweeps the trim indicator scale to indicate trim po...

Page 184: ... PFD Flight instruments and annunciators are located on the left side of the panel and engine instruments are located on the right side of the instrument panel 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 t...

Page 185: ...ted on the left side of the panel and a large color multifunction display is located adjacent to the primary flight display Temperature controls are located on the right side below the glove compartment A switch panel located in the dash board bolster below the flight instruments contains the master switch avionics power switch pitot heat switch and lighting switches Center Console A center consol...

Page 186: ...1 Flight Instrument Panel 2 Annunciator Panel 3 Overhead Light Switch 4 Magnetic Compass 5 Cirrus Airframe Parachute System CAPS Activation T Handle Cover 6 Multifunction Display 7 Engine Instruments 8 Temperature Ventilation Controls 9 Control Yoke 10 Fresh Air Eyeball Outlet 11 Conditioned Air Outlet 12 Rudder Pedals 13 Flap Control Position Indicators 14 Passenger Audio Jacks 15 Armrest 16 Engi...

Page 187: ...dicators 15 Passenger Audio Jacks 16 Armrest 17 Engine Fuel System Controls Legend 1 Start Ignition Key Switch 2 Annunciator Panel 3 Primary Flight Display 4 Overhead Light Switch 5 Magnetic Compass 6 Cirrus Airframe Parachute System CAPS Activation T Handle Cover 7 Multifunction Display 8 Engine Instruments SR22_FM07_1730 18 Left Side Console Circuit Breaker Panel Alternate Engine Air Parking Bra...

Page 188: ...uel System Controls Legend 1 Start Ignition Key Switch 2 Annunciator Panel 3 Primary Flight Display 4 Overhead Light Switch 5 Magnetic Compass 6 Cirrus Airframe Parachute System CAPS Activation T Handle Cover 7 Multifunction Display 8 Glove Box 18 Left Side Console Circuit Breaker Panel Alternate Engine Air Parking Brake Alternate Static Source 19 Avionics Panel 20 Bolster Switch Panel 21 Control ...

Page 189: ... vertical and directional gyros ADAHRS also provides roll pitch heading data and continually updates the winds aloft and true airspeed TAS indications on the PFD The magnetometer assembly mounted in the wing also provides outside air temperature OAT data The airplane s Pitot Static system is connected to the PFD to provide airspeed altitude and vertical speed Standby instruments for airspeed attit...

Page 190: ...AIN BUS 2 ESSENTIAL BUS Avidyne PFD SR22_FM07_1607B PFD 1 10 PFD 2 10 PITOT STATIC Avidyne MFD STEC System 55x Autopilot Data Aquisition Unit OAT Sensor Magnetometer 2 GNS 430 GPS 1 GNS 430 GPS AP ON Flight Director System Optional AP OFF FD ON PFD System Simplified Schematic March 2010 ...

Page 191: ...he VSI is 2000 FPM and for rates above 2000 FPM the needle will peg just outside the scale and a digital readout of actual VSI up to 4000 FPM is then displayed An additional data block is provided for display of outside air temperature OAT true airspeed TAS and groundspeed GS Controls for selecting bug and barometric correction values are along the right side of the PFD A wind indicator is also pr...

Page 192: ...ation Avionics Configuration Buttons 2 Percent Power 3 Bus Voltages 4 Airspeed Window 5 Airspeed Tape 6 Autopilot Annunciations 7 Aircraft Reference Symbol 8 Bank Angle Indicator 9 Skid Slip Indicator 10 Pitch Ladder 11 Flight Director Steering Command Bars 12 Vertical Deviation Indicator VDI 13 Altitude Tape 14 Altitude Window 15 Vertical Speed Indicator VSI 16 Brightness Control BRT DIM 17 Mode ...

Page 193: ...ion data and for selecting the type of compass rose and moving map to be displayed are along the left side of the PFD The active flight plan contained in the GPS Nav Com unit selected as the primary navigation source Nav can be optionally selected for display on the HSI as well as the desired range of the optionally selectable moving map display If a localizer or ILS frequency is tuned and capture...

Page 194: ...e indicator is used for quick erection of the gyro When the caging knob is pulled the pitch and roll indications will align to within 2 of their respective fixed references The instrument is electrically driven and a red GYRO flag indicates loss of electrical power Redundant circuits paralleled through diodes at the indicator supply DC electrical power for gyro operation 28 VDC for attitude gyro o...

Page 195: ...tion The scale is calibrated from 0 to 2000 FPM in 100 FPM increments in both the UP and DOWN directions Altimeter Note Serials 0435 and subsequent with PFD The standby altimeter is mounted on the LH bolster panel Airplane altitude is depicted on a conventional three pointer internally lit barometric altimeter installed in the pilot s instrument panel The instrument senses the local barometric pre...

Page 196: ...des at the indicator supply DC electrical power 28 VDC for roll rate gyro operation is supplied through the 2 amp TURN COORD 1 circuit breaker on the Essential Bus and the 2 amp TURN COORD 2 circuit breaker on the Main Bus 2 Serials with Avionics Configuration B 0002 through 1601 1603 through 1643 and 1645 through 1662 without PFD The electric turn coordinator installed in the instrument panel dis...

Page 197: ...plied through the 2 amp INST LIGHTS circuit breaker on Main Bus 1 Horizontal Situation Indicator Note Serials 0435 and subsequent with PFD The Horizontal Situation Indicator is integrated into the PFD Serials with Avionics Configuration A 0002 through 1601 1603 through 1643 and 1645 through 1662 without PFD The Century NSD 1000 is a conventional HSI that provides gyro stabilized magnetically slave...

Page 198: ...I an RMI a full color moving map a Stormscope display GPS annunciator and 3 light marker beacon indicators Compass information is derived from a remote directional gyro and a flux detector Redundant power sources provide 28 VDC for system operation Power is supplied through the 5 amp HSI 1 circuit breaker on the Essential Bus and the 5 amp HSI 2 circuit breaker on Main Bus 2 Either circuit is capa...

Page 199: ...avigation receivers and failed directional gyro or flux detector It also monitors its own internal temperature and provides warnings for over temperature or loss of cooling conditions Redundant circuits paralleled through diodes at the indicator supply DC electrical power for gyro operation 28 VDC for the redundant power circuits is supplied through the 5 amp HSI 1 circuit breaker on the Essential...

Page 200: ...e Proximity switches in the actuator limit flap travel to the selected position and provide position indication The wing flaps and control circuits are powered by 28 VDC through the 15 amp FLAPS circuit breaker on the Non Essential Bus Flap Control Switch An airfoil shaped FLAPS control switch is located at the bottom of the vertical section of the center console The control switch is marked and h...

Page 201: ...Information Manual 7 33 Cirrus Design Section 7 SR22 Airplane Description SR22_FM07_1460 Figure 7 7 Wing Flaps March 2010 ...

Page 202: ...ount structure The nosewheel is free castering and can turn through an arc of approximately 216 degrees 108 degrees either side of center Steering is accomplished by differential application of individual main gear brakes The tube type nosewheel tire is 5 00 x 5 Airplane Cabin Cabin Doors Caution Serials 0795 0820 and subsequent The seat back must be in the fully upright or the fully reclined posi...

Page 203: ...HT AND SWITCH FIRE EXTINGUISHER TIEDOWN LOOPS 6 PLACES AFT BULKHEAD TIEDOWN LOOPS 4 PLACES BAGGAGE FLOOR STALL WARNING HORN DEFROST AIR OUTLETS DOOR HANDLE OVERHEAD LIGHT AND SWITCH PASSENGER FRESH AIR OUTLET UNDER PILOT S SEAT SR22_FM07_1064 OVERHEAD CAPS ACTIVATION T HANDLE DETAIL A A Figure 7 8 Cabin Arrangement March 2010 ...

Page 204: ... bulkhead The tie down straps should be stowed attached and tightened to the fittings If not adequately restrained baggage compartment items may pose a projectile hazard to cabin occupants in the event of rapid deceleration Secure all baggage items with tie down straps To install tie down strap 1 Position straps over baggage Thread straps through luggage handles if possible 2 Clip hook ends of str...

Page 205: ...he position control handle 2 Slide the seat into position 3 Release the handle and check that the seat is locked in place To adjust recline position 1 Actuate and hold the seat back control lever 2 Position the seat back to the desired angle 3 Release the control lever Each rear seat consists of a fixed seat bottom a folding seat back and a headrest The seat backs can be unlatched from inside the ...

Page 206: ...ials 0002 through 1499 1501 through 1519 after SB 2X 25 14 and serials 1500 1520 and subsequent An inflatable shoulder harness is integral to each crew seat harness The electronic module assembly mounted below the cabin floor contains a crash sensor battery and related circuitry to monitor the deceleration rate of the airplane In the event of a crash the sensor evaluates the crash pulse and sends ...

Page 207: ...mmed or inoperable the hammer may be used to break through the acrylic windows to provide an escape path for the cabin occupants Fire Extinguisher A liquefied gas type fire extinguisher containing Halon 1211 1301 extinguishing agent is mounted on the forward inboard side of the pilot s seat base The extinguisher is approved for use on class B liquid grease and class C electrical equipment fires Th...

Page 208: ...latching door Close vents and door after fumes clear The extinguisher must be visually inspected before each flight to assure that it is available charged and operable The preflight inspection consists of ensuring that the nozzle is unobstructed the pin has not been pulled and the canister has not been damaged Additionally the unit should weigh approximately 1 5 lb 0 7 kg For preflight charge can ...

Page 209: ... lubrication and cooling Oil for engine lubrication is drawn from an eight quart capacity sump through an oil suction strainer screen and directed through the oil filter to the engine mounted oil cooler by a positive displacement oil pump The oil pump is equipped with a pressure relief valve at the pump output end to bypass oil back to the pump inlet should the pump exceed limits The oil cooler is...

Page 210: ...ve on the air induction system throttle body The fuel metering valve adjusts fuel flow in response to the pilot controlled Power Lever position From the metering valve fuel is directed to the fuel manifold valve spider and then to the individual injector nozzles The system meters fuel flow in proportion to engine RPM mixture setting and throttle angle Manual mixture control and idle cut off are pr...

Page 211: ...o rotation for feel and control setting stability An alternate induction air source control is also provided Power Throttle Lever The single lever throttle control labeled MAX POWER IDLE on the console adjusts the engine throttle setting in addition to automatically adjusting propeller speed The lever is mechanically linked by cables to the air throttle body fuel metering valve and to the propelle...

Page 212: ...spring loaded START position energizes the starter and activates both magnetos The switch automatically returns to the BOTH position when released Alternate Air Control An Alternate Induction Air Control knob labeled ALT AIR PULL is installed on the left console near the pilot s right ankle To operate the control depress the center lock button pull the knob to the open position and then release th...

Page 213: ... manifold pressure fuel flow and oil pressure are continuously displayed in the engine data block located in the lower right corner of the PFD System health caution and warning messages are displayed in color coded advisory boxes in the lower right corner of the MFD In addition the text of the engine parameters displayed on the PFD change to the corresponding color of advisory box during an annunc...

Page 214: ...thru 1662 G I T F E R L FUEL Controls LEGEND 1 Power Lever 2 Mixture Control 3 Friction Control 4 Tachometer 5 EGT Alternate Air Control Start Ignition Switch 3 2 1 SR22_FM07_1603A Serials 0002 thru 0434 Switch is located on the left bolster panel 6 CHT 7 Oil Temperature 8 Oil Pressure 9 Manifold Pressure Engine Controls and Indicating Sheet 1 of 2 March 2010 ...

Page 215: ...T shown with EMax 6 CHT shown with EMax 7 Oil Temperature 8 Oil Pressure 9 Manifold Pressure 10 Percent Power 11 Oil Warning Light 5 4 11 7 8 Engine Instruments 9 6 SR22_FM07_2218 Serials 1602 1644 1663 subs Multifunction Display Primary Flight Display 4 9 8 10 Annunciator Panel Figure 7 9 Engine Controls and Indicating Sheet 2 of 2 March 2010 ...

Page 216: ...gine data block located in the lower right corner of the PFD In the event engine speed exceeds 2710 RPM for five seconds the MFD will display Check RPM in a red advisory box in the lower right corner of the MFD 28 VDC for the digital instrument operation is supplied through the 2 amp ANNUN ENGINE INST circuit breaker on the Essential Bus Exhaust Gas Temp Cylinder Head Temp Gage Bar Graphs Serials ...

Page 217: ...of the cylinder is displayed above the bar in text and an up or down trend arrow appears below the temperature to indicate whether CHT is rising or falling In the event CHT exceeds 420 F the MFD will display Check CHT in a yellow advisory box in the lower right corner of the MFD In the event CHT exceeds 460 F the MFD will display Check CHT in a red advisory box in the lower right corner of the MFD...

Page 218: ...d advisory box in the lower right corner of the MFD Oil pressure is shown in the upper right most corner of the MFD as both a simulated pressure gage and as text The simulated gage receives a pressure signal from a sensor mounted below the oil cooler via the DAU and sweeps a scale marked from 0 psi to 100 psi in 5 psi increments Oil pressure is also continuously displayed in the engine data block ...

Page 219: ...th a simulated temperature gage and as text The simulated gage receives a pressure signal from a pressure sensor mounted in the induction air manifold near the throttle body via the DAU and sweeps a scale marked from 10 to 30 inches Hg in one inch Hg increments Manifold pressure is also continuously displayed in the engine data block located in the lower right corner of the PFD 28 VDC for the digi...

Page 220: ...h oil temperature or low oil pressure The light is illuminated by a switch in the oil temperature gage DAU if the oil temperature reaches 240 F or if the oil pressure drops to 10 psi or less If the OIL warning light comes on in flight refer to the oil temperature and pressure gages to determine the cause Typically low oil pressure will be accompanied by a high oil temperature indication The light ...

Page 221: ...eller governor boosts oil pressure in order to regulate propeller pitch position Moving the throttle lever forward causes the governor to meter less high pressure oil to the propeller hub allowing centrifugal force acting on the blades to lower the propeller pitch for higher RPM operation Reducing the power throttle lever position causes the governor to meter more high pressure oil to the propelle...

Page 222: ...antity indicators Positive pressure in the tank is maintained through a vent line from each wing tank Fuel from each wing tank gravity feeds through strainers and a flapper valve to the associated collector tank in each wing Each collector tank sump incorporates a flush mounted fuel drain and a vent to the associated fuel tank The engine driven fuel pump pulls filtered fuel from the two collector ...

Page 223: ...E SENSOR LOW PRESSURE STARTING CIRCUIT DAU GASCOLATOR ELECTRIC AUXILIARY PUMP R WING COLLECTOR VENT FILLER R WING TANK FILLER OFF FEED RETURN LEFT RIGHT FEED RETURN FUEL PRESSURE SWITCH SELECTOR VALVE OPERATION FUEL FLOW INDICATOR ANNUNCIATOR FUEL FUEL QUANTITY INDICATOR FUEL PUMP PRIME BOOST DRAIN 5 PLACES INJECTOR MANIFOLD FIREWALL VENT L WING TANK L WING COLLECTOR FUEL RELAY ENGINE DRIVEN FUEL ...

Page 224: ...ne Monitoring after factory installation or after Service Bulletin SB 22 77 01 The following fuel system component descriptions are the same as those listed for airplane serials 1602 1644 1663 and subsequent except MFD functionality is enhanced by displaying fuel used fuel remaining time remaining fuel economy and the addition of Initial Usable Fuel page Refer to Avidyne FlightMax EX5000C Pilot s ...

Page 225: ... gallons in each tank The fuel quantity indications are derived from float type fuel level sensors installed in each main tank and each collector tank The indicator is internally lighted Serials 0002 through 1601 1603 through 1643 and 1645 through 1662 28 VDC for fuel quantity system operation is supplied through the 5 amp ENGINE INST circuit breaker on Main Bus 1 Serials 1602 1644 1663 and subseq...

Page 226: ...rplane Description SR22 Figure 7 11 4 Serials 0002 thru 1601 1603 thru 1643 1645 thru 1662 LEGEND 1 Fuel Pump Switch 2 Fuel Quantity Gage 3 Fuel Selector Valve 4 Fuel Flow 3 2 1 SR22_FM07_2226 Fuel System Controls and Indicating Sheet 1 of 2 March 2010 ...

Page 227: ...D 4 Fuel Flow 5 Fuel Used EMax only 6 Fuel Remaining EMax only 7 Time Remaining EMax only 8 Fuel Economy EMax only 9 Fuel Caution Light SR22_FM07_2228 Serials 1602 1644 1663 subs Multifunction Display Primary Flight Display 4 Annunciator Panel 4 5 6 7 8 Figure 7 11 Fuel System Controls and Indicating Sheet 2 of 2 March 2010 ...

Page 228: ... valve In the event fuel flow exceeds 30 0 gallons per hour the MFD will display Check Fuel Flow in a red advisory box in the lower right corner of the MFD 28 VDC for the digital instrument operation is supplied through the 2 amp ANNUN ENGINE INST circuit breaker on the Essential Bus Fuel Caution Light The amber FUEL caution light in the annunciator panel comes on to indicate a low fuel condition ...

Page 229: ...ecting BOOST energizes the boost pump in low speed mode to deliver a continuous 4 6 psi boost to the fuel flow for vapor suppression in a hot fuel condition Serials 0278 and subs and serials 0002 through 0277 after SB 22 73 01 An oil pressure based system is used to control boost pump operation The oil pressure oil temperature sensor provides a signal to the starting circuit DAU to generate a grou...

Page 230: ... brakes are plumbed so that depressing either the pilot s or copilot s left or right toe brake will apply the respective left or right main wheel brake The reservoir is serviced with Mil H 5606 hydraulic fluid Brake system malfunction or impending brake failure may be indicated by a gradual decrease in braking action after brake application noisy or dragging brakes soft or spongy pedals excessive ...

Page 231: ...left side of the console near the pilot s right ankle Brake lines from the toe brakes to the main wheel brake calipers are plumbed through a parking brake valve For normal operation the knob is pushed in With the knob pushed in poppets in the valve are mechanically held open allowing normal brake operation When the handle is pulled out the parking brake valve holds applied brake pressure locking t...

Page 232: ...Design Airplane Description SR22 Figure 7 12 CALIPER ASSEMBLY CALIPER ASSEMBLY RUDDER PEDAL 4 SR22_FM07_1015 PARKING BRAKE VALVE PARKING BRAKE KNOB MASTER CYLINDER 4 RESERVOIR MIL H 5606 FLUID ONLY ROTOR DISK ROTOR DISK Brake System March 2010 ...

Page 233: ...75 volts The output from ALT 1 is connected to the Main Distribution Bus in the MCU through an 80 amp fuse The output from ALT 2 is connected to the Essential Distribution Bus in the MCU through a 40 amp fuse Both alternators are self exciting not self starting and require battery voltage for field excitation in order to start up for this reason the batteries should not be turned off in flight Bat...

Page 234: ...ibution 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 For normal operation the Essential Buses in the circuit breaker panel are powered from the Essential Distribution Bus in the MCU through 25 amp circuit breakers BAT 2 is connected directly to t...

Page 235: ...ALT 1 ALT 2 PITOT HEAT ESSENTIAL DIST MAIN DIST 25A 25A 25A 25A 25A VOLT REG ALT 2 F B ALT 1 F B 100A 40A VOLT REG GPS 2 ANNUN ENGINE INST MASTER CONTROL UNIT CIRCUIT BREAKER PANEL TURN COORD 1 AVIONICS ESSENTIAL BAT 2 ALT 1 SWITCH LOW VOLTS ATTITUDE 1 HSI PFD 1 STALL WARNING BATTERY 2 ALT 2 ESSENTIAL POWER ESSENTIAL AUTOPILOT AVIONICS COM 1 GPS 1 FUEL PUMP TURN COORD 2 MAIN BUS 2 ATTITUDE 2 HSI P...

Page 236: ...so energizing the circuit breaker panel buses and the open contacts of the starter relay Setting the BAT 2 switch on energizes a relay connecting BAT 2 to the circuit breaker panel Essential Buses Normally for flight operations all master switches will be on However the BAT 1 and BAT 2 switches can be turned on separately to check equipment while on the ground Setting only the BAT 2 switch on will...

Page 237: ...from the circuit breaker panel bus to the Avionics Bus The switch is located next to the ALT and BAT Master switches Typically the switch is used to energize or de energize all avionics on the Avionics Non Essential and Essential Buses simultaneously With the switch in the OFF position no electrical power will be applied to the avionics equipment regardless of the position of the master switch or ...

Page 238: ... in the upper left corner of the PFD when voltages fall outside typical operating parameters The MFD and PFD receive the voltage signals via the DAU as measured directly off the Main and Essential Buses In the event Main Bus voltage is less than 24 5v or exceeds 32 0v the MFD will display Check Main Bus in a yellow advisory box in the lower right corner of the MFD In the event Essential Bus voltag...

Page 239: ...ng light in the annunciator panel located on the left side of the instrument panel A voltage sensor in the MCU monitors voltage on the Essential Bus and illuminates the warning light when the voltage is less than approximately 24 5 volts Note The LOW VOLTS warning light may come on during extended low RPM operation with heavy electrical loads Under these conditions the light will go out at higher ...

Page 240: ...ter switch panel Main Buses The circuit breaker panel Main Bus 1 and Main Bus 2 are powered by ALT 1 and BAT 1 from the MCU Main Distribution Bus through 25 amp circuit breakers on the Distribution Bus ALT 2 and BAT 2 are prevented from powering the Main Buses by the isolation diode interconnecting the MCU distribution buses Loads on circuit breaker panel Main Buses are shed by pulling the individ...

Page 241: ...ed to 28 VDC The external power control contactor is wired through the BAT 1 MASTER switch so that the BAT 1 switch must be on to apply external power Refer to Section 8 Ground Handling Servicing and Maintenance for use of external power and special precautions to be followed Convenience Outlet A 12 volt convenience outlet is installed in the center console The receptacle accepts a standard cigare...

Page 242: ...nt panel bolster 28 VDC for strobe light and control circuits is supplied through the 5 amp STROBE LIGHTS circuit breaker on Non Essential Bus Landing Light A High Intensity Discharge HID landing light is mounted in the lower engine cowl The landing light is controlled through the LAND light switch on the instrument panel bolster Setting the LAND light switch ON energizes the landing light control...

Page 243: ...erate on 28 VDC supplied through the 3 amp CABIN LIGHTS circuit breaker on Main Bus 2 Reading Lights Individual eyeball type reading lights are installed in the headliner above each passenger position Each light is aimed by positioning the lens in the socket and is controlled by a push button switch located next to the light The pilot and copilot reading lights are also dimmable through the PANEL ...

Page 244: ... air is provided by ducting fresh air from air inlets located in each wing leading edge to eyeball outlets for each occupant Each occupant can direct the fresh air flow by positioning the nozzle or control flow rate from off to maximum by rotating the nozzle Heating is accomplished by mixing ventilation air from the fresh air inlets with heated air from the heat exchanger and then distributing the...

Page 245: ...DIFFUSER AIR GASPER FRESH AIR CONDITIONED AIR MECHANICAL CONNECTION OFF HEAT COLD WINDSHIELD DEFROST DIFFUSER HVAC PLENUM TEMP CONTROL HEAT EXCHANGER SR22_FM07_1012B FRESH AIR INTAKE FRESH AIR INTAKE CABIN HEAT DEFROST SELECT Figure 7 14 Cabin Heating and Cooling Serials 0002 thru 1862 March 2010 ...

Page 246: ...t floor level Cabin Heat Control The amount of heated air allowed into the air mixing plenum is controlled by rotating the Cabin Heat Control located inboard of the Cabin Air Selector The control is mechanically linked to a door in a heater box between the heater muff and the mixing plenum Rotating the control full counterclockwise HEAT OFF bypasses heated air from the heater muff into the engine ...

Page 247: ...bution manifold If option installed the blower fan is turned on when the selector dial exceeds the full open position Vent Selection Conditioned air from the distribution manifold can be proportioned and directed to passengers and or the windshield by manipulating the cabin vent selector The selector is mechanically linked to butterfly valves at the entrances to the windshield diffuser and the cab...

Page 248: ...LD FRESH AIR VALVE FAN ASSEMBLY HOT AIR VALVE HEAT EXCHANGER SR22_FM07_2324 VENTS TEMPERATURE AIRFLOW AIR INLET NOTE Illustration depicts maximum cabin cooling airflows and selector settings PANEL AIRFLOW FRESH AIR INTAKE FLOOR AIRFLOW WINDSHIELD DIFFUSER AIR MIXING PLENUM AIR GASPER Cabin Heating and Cooling Serials 1863 subsequent March 2010 ...

Page 249: ...o the windshield diffuser Temperature Selection The temperature selector is mechanically linked to the hot air valve and fresh air intake valve Rotating the selector simultaneously opens and closes the two valves permitting hot and cold air to mix and enter the distribution system Rotating the selector clockwise permits warmer air to enter the system counterclockwise cooler air March 2010 ...

Page 250: ...em consists of a heating element in the pitot tube a rocker switch labeled PITOT HEAT and associated wiring The switch and circuit breaker are located on the left side of the switch and control panel When the pitot heat switch is turned on the element in the Pitot tube is heated electrically to maintain proper operation in possible icing conditions Pitot heat should be used only when required The ...

Page 251: ...435 subs w PFD PRIMARY FLIGHT DISPLAY SR22_FM07_1013D PITOT MAST STATIC BUTTONS PITOT STATIC WATER TRAPS ALTERNATE STATIC AIR SOURCE VERTICAL SPEED INDICATOR ALTIMETER ALTITUDE TRANSDUCER OPTIONAL ALTITUDE ENCODER ANNUNCIATOR PITOT HEAT LOGIC CURRENT SENSOR HEATER 7 5A PITOT HEAT CB PITOT HEAT SW Figure 7 16 Pitot Static System Schematic March 2010 ...

Page 252: ...e of the right wing a pressure switch and associated plumbing and a piezo ceramic horn behind the instrument panel As the airplane approaches a stall the low pressure on the upper surface of the wings moves forward around the leading edge of the wings As the low pressure area passes over the stall warning sense inlet a slight negative pressure is sensed by the pressure switch The pressure switch c...

Page 253: ...ing configurations Avionics Configuration A Serials 0002 through 1601 1603 through 1643 and 1645 through 1662 without PFD Moving Map Display Avidyne MFD Two Axis Autopilot S Tec System 30 Integrated Audio System with Intercom Garmin GMA 340 Marker Beacon Receiver Garmin GMA 340 Two IFR Approach Certified GPS Garmin GNS 430 and Garmin GNS 420 Two VHF Communications Transceivers Garmin GNS 430 and G...

Page 254: ...e Encoder Garmin GTX 327 Multi Function Display This airplane is equipped with an Avidyne FlightMax EX5000C 700 00004 XXX Multi Function Flight Display MFD The MFD is a 10 4 inch landscape oriented display mounted in the instrument panel The MFD provides supplemental display of situational and navigation information to the pilot This is accomplished by showing an icon representing the airplane aga...

Page 255: ...ain features such as airports and special use airspace and select color enhanced terrain Select and view trip data from GPS Power for the MCU is 28 VDC supplied through the 5 amp MFD circuit breaker on the Avionics Non Essential Bus Note Serials 0002 through 1103 before MFD software version 530 00162 000 Revision 02 Do not use the Garmin 420 or 430 Navigators to display Stormscope lightning data w...

Page 256: ...eparate pitch computer provides the ALT hold function The S Tec System Thirty Autopilot features Roll Stabilization Turn Command NAV LOC GPS tracking HI and LO sensitivity Altitude Hold GPS Steering GPSS for smoother turns onto a course or during course tracking A separate GPSS converter provides GPS roll steering to the autopilot A GPSS HDG button allows the operator to switch between HDG and Rol...

Page 257: ... and Command NAV LOC GPS GS tracking high and low sensitivity and automatic 45 course intercept GPS Steering GPSS Altitude Pre select Hold and Command Altitude display and baro correction Altitude and Decision Height DH alert and Vertical Speed Hold and Command 28 VDC for autopilot and altitude selector alerter is supplied through the 5 amp AUTOPILOT circuit breaker on the Essential Bus Refer to S...

Page 258: ...and flying status In flight director equipped aircraft when a vertical mode of the autopilot is being used a set of flight director command bars will indicate the required steering of the aircraft to achieve the commanded tracking from the autopilot In autopilot mode AP will be in the autopilot annunciation field the command bars will be visible and magenta and the aircraft should track the bars I...

Page 259: ... Safe Altitudes Controlled Airspace Advisories and Frequencies North American and International databases are available Database information is provided on a card that can be inserted into the card slot on the GPS unit Subscription information is provided in a subscription packet provided with each system Serials with Avionics Configuration A 0002 through 1601 1603 through 1643 and 1645 through 16...

Page 260: ...PS navigators Dual Garmin GNS 430s are designated GPS 1 and GPS 2 Both Garmin GPS navigators are IFR certified The primary unit designated GPS 1 is coupled to the airplane s HSI or PFD Autopilot and MFD The secondary unit designated GPS 2 is coupled to the airplane s HSI or PFD and MFD The GPS navigators are capable of providing IFR enroute terminal and approach navigation with position accuracies...

Page 261: ...sceiver active and standby frequency indication frequency memory storage and knob operated frequency selection The COM 1 transceiver provides either 720 channel 25 kHz spacing or 2280 channel 8 33 kHz spacing operation in a frequency range from 118 000 to 136 975 MHz The COM 1 antenna is located above the cabin on the airplane centerline 28 VDC for COM 1 transceiver operation is controlled through...

Page 262: ...op of the vertical tail provides VOR LOC input for both Nav receivers 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 Avionics Configuration B and PFD The airplane is equipped with two NAV rece...

Page 263: ...itized altitude information provided by the altitude encoder is plumbed into the airplane static system The transponder and integrated controls are mounted in the center console The transponder control provides active code display code selection IDENT button and test functions A FUNC function key allows for selection of pressure altitude flight time count up timer and countdown timer modes The dis...

Page 264: ...e rear passenger ANR power jacks These jacks can be used to plug in personal entertainment devices such as portable radios cassette players or CD players Audio volume through these jacks is controlled by connected individual entertainment device Emergency Locator Transmitter The airplane is equipped with a self contained emergency locator transmitter ELT The transmitter and antenna are installed i...

Page 265: ...ntenance manual procedures The RESET button can be used to cancel an inadvertent transmission A 6 volt Lithium battery mounted in the panel powers the LED The battery must be replaced at regular intervals refer to Airplane Maintenance Manual In the event of an accident 1 Verify ELT operation by noting that the ELT indicator light on the remote panel is flashing 2 If possible access the unit as des...

Page 266: ...63 through 1862 28 VDC for hour meter operation is supplied through the 5 amp FUEL QTY HOBBS circuit breaker on Main Bus 1 Serials 1821 1840 1863 and subsequent The airplane is equipped with two hour meters located inside the armrest storage compartment between the pilot and copilot seats The 1 hour meter labeled HOBBS begins recording when the BAT 1 switch is ON and either the ALT 1 or ALT 2 swit...

Page 267: ...installed to provide up to three years battery back up SEL and CTL Buttons All time keeping and set functions are addressable using the Select and Control buttons below the time display Upon power up the clock will display Universal Time UT Pressing the Select button 3 times will display Local Time LT and Elapsed Time ET sequentially Pressing the button again will return the display to UT Set UT o...

Page 268: ...l deactivates the alarm Test Mode To enter the self test mode hold the Select button for 3 seconds The display will indicate 88 88 and all four UT LT FT ET annunciators will come on OAT VOLTS Button Note OAT indication is subject to small errors It is possible for ice to accrete on the aircraft at indicated temperatures higher than 32 F 0 C Serials 0002 through 0434 The red OAT VOLTS button is use...

Page 269: ...ystem Description The CAPS consists of a parachute a solid propellant rocket to deploy the parachute a rocket activation handle and a harness imbedded within the fuselage structure A composite box containing the parachute and solid propellant rocket is mounted to the airplane structure immediately aft of the baggage compartment bulkhead The box is covered and protected from the elements by a thin ...

Page 270: ...r held in place with hook and loop fasteners covers the T handle and prevents tampering with the control The cover is be removed by pulling the black tab at the forward edge of the cover Pulling the activation T handle will activate the rocket and initiate the CAPS deployment sequence To activate the rocket two separate events must occur 1 Pull the activation T handle from its receptacle Pulling t...

Page 271: ...ed to the pin WARNING After maintenance has been performed or any other time the system has been safetied operators must verify that the pin has been removed before further flight Deployment Characteristics When the rocket launches the parachute assembly is extracted outward due to rocket thrust and rearward due to relative wind In approximately two seconds the parachute will begin to inflate When...

Page 272: ...nd impact Caution Ground impact is expected to be equivalent to touchdown from a height of approximately 13 feet While the airframe seats and landing gear are designed to accommodate this stress occupants must prepare for it in accordance with the CAPS Deployment procedure in Section 3 Emergency Procedures Note The CAPS is designed to work in a variety of aircraft attitudes including spins However...

Page 273: ...ction 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 8 12 Parking 8 13 Tiedown 8 14 Leveling 8 14 Jacking 8 15 Servicing 8 16 Landing Gear Servicing 8 16 Brake Servicing 8 16 Tire Inflation 8 18 Propeller Servicing 8 18 Oil Servicing 8 19 Fuel System Servicing 8 22 Fuel Co...

Page 274: ...8 2 Information Manual Section 8 Cirrus Design Handling Servicing Maintenance SR22 March 2010 ...

Page 275: ... covering inspection servicing maintenance troubleshooting and repair of the airplane structure systems and wiring Revision Service for this manual is also available A current copy of the AMM is provided at delivery Engine Operators and Maintenance Manual Cirrus Design provides a Teledyne Continental Engine Operator s and Maintenance Manual at the time of delivery Engine and engine accessory overh...

Page 276: ...ata or corrections not requiring a Service Bulletin Give careful attention to the Service Advisory Notice information Ordering Publications SR22 publications revision service and 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 ...

Page 277: ...s Required Documents Note A Airworthiness Certificate FAA Form 8100 2 Must be displayed at all times R Registration Certificate FAA Form 8050 3 Must be in the aircraft for all operations R Radio Station License FCC Form 556 Required only for flight operations outside the United States O Operating Instructions FAA Approved Flight Manual and Pilot s Operating Handbook fulfills this requirement W Wei...

Page 278: ...approximately 35 KIAS and should be used to track maintenance time intervals as it more accurately records time in service than the 1 Hour Meter which begins recording when the BAT 1 switch is ON and either the ALT 1 or ALT 2 switch is ON The inspection items specified in the Annual 100 Inspection have been determined by the average aircraft use rate of the typical owner Non commercially operated ...

Page 279: ...hanic The 100 hour interval may be exceeded by not more than 10 flight hours in order to reach a place where the inspection can be accomplished Any flight hours used to reach an inspection station must be deducted from the next 100 Hour Inspection interval The inspection is listed in detail in Chapter 5 of the Aircraft Maintenance Manual Cirrus Design Progressive Inspection Program In lieu of the ...

Page 280: ...erating system or interfere with an operating system or affect the primary structure Remove install and repair tires Clean grease or replace wheel bearings Replace defective safety wire or cotter pins Lubrication not requiring disassembly other than removal of non structural items such as access covers cowlings or fairings Caution Do not use unapproved lubricants Unapproved lubricants may damage c...

Page 281: ...id level and specific gravity Logbook Entry After any of the above work is accomplished appropriate logbook entries must be made Logbook entries should contain The date the work was accomplished Description of the work Number of hours on the aircraft The certificate number of pilot performing the work Signature of the individual doing the work Logbooks should be complete and up to date Good record...

Page 282: ... from the airplane and battery maintenance performed in accordance with the appropriate Airplane Maintenance Manual procedures 1 Ensure that external power source is regulated to 28 VDC 2 Check BAT and AVIONICS power switches are off 3 Plug external power source into the receptacle 4 Set BAT 1 switch to ON 28 VDC from the external power unit will energize the main distribution and essential distri...

Page 283: ... push or pull on control surfaces or propeller to maneuver the airplane Do not tow the airplane when the main gear is obstructed with mud or snow If the airplane is to be towed by vehicle do not turn the nose wheel more than 90 degrees either side of center or structural damage to the nose gear could result 1 Refer to Airplane Three View Section 1 Figure 1 1 and Turning Radius Section 1 Figure 1 2...

Page 284: ...des Taxi with minimum power needed for forward movement Excessive braking may result in overheated or damaged brakes 1 Remove chocks 2 Start engine in accordance with Starting Engine procedure Section 4 3 Release parking brake 4 Advance throttle to initiate taxi Immediately after initiating taxi apply the brakes to determine their effectiveness During taxiing use differential braking to make sligh...

Page 285: ...vernight chock and tie down the airplane 1 For parking head airplane into the wind if possible 2 Retract flaps 3 Set parking brake by first applying brake pressure using the toe brakes and then pulling the PARK BRAKE knob aft Caution Care should be taken when setting overheated brakes or during cold weather when accumulated moisture may freeze a brake 4 Chock both main gear wheels 5 Tie down airpl...

Page 286: ...tail ring at approximately 45 degree angles to the ground When using rope or non synthetic material leave sufficient slack to avoid damage to the airplane should the ropes contract Caution Anchor points for wing tiedowns should not be more than 18 feet apart to prevent eyebolt damage in heavy winds Use bowline knots square knots or locked slipknots Do not use plain slipknots Leveling The airplane ...

Page 287: ...nd 300 lb minimum attached to the tail tiedown 1 Position airplane on a hard flat level surface 2 Remove tiedown rings from wings Stow tie down rings in baggage compartment 3 Attach a weighted tailstand to the tail tiedown ring 4 Position jacks and jack points pads for jacking Insert jack point pad into wing tiedown receptacle Holding the jack point pad in place position the jack under the point a...

Page 288: ... at the annual 100 hour inspection replenishing the system when necessary The brake reservoir is located on the right side of the battery support frame If the entire system must be refilled refer to the Airplane Maintenance Manual To replenish brake fluid 1 Chock tires and release parking brake 2 Remove top engine cowling to gain access to hydraulic fluid reservoir 3 Clean reservoir cap and area a...

Page 289: ...at may obstruct inspection 3 Check brake linings for deterioration and maximum permissible wear Replace lining when worn to 0 100 inch 2 54 mm 4 Inspect temperature indicator s Serials 0002 thru 3450 before SB 2X 05 01 a Clean and inspect temperature indicator installed to piston housing If indicator center is black the brake assembly has been overheated The brake linings must be inspected and the...

Page 290: ...ttons All wheels and tires are balanced before original installation and the relationship of tire tube and wheel should be maintained upon reinstallation In the installation of new components it may be necessary to rebalance the wheels with the tires mounted Unbalanced wheels can cause extreme vibration in the landing gear Propeller Servicing The spinner and backing plate should be cleaned and ins...

Page 291: ...left side of the engine cowling The engine should not be operated with less than six quarts of oil Seven quarts dipstick indication is recommended for extended flights To check and add oil 1 Open access door on upper left hand side of cowl Pull dipstick and verify oil level 2 If oil level is below 6 quarts 5 7 liters remove filler cap and add oil through filler as required to reach 6 8 quarts 5 7 ...

Page 292: ...lled oil add only MIL L 6082 straight mineral oil 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 use only aviation lubricating oils conforming to Teledyne Continental Motors TCM Specification MHS...

Page 293: ...ro AD Oil Castrol Ltd Australia Chevron Aero Oil Chevron U S A Inc Conoco Aero S Continental Oil Delta Avoil Delta Petroleum Co Exxon Aviation Oil EE Exxon Company U S A Mobil Aero Oil Mobil Oil Company Pennzoil Aircraft Engine Oil Pennzoil Company Quaker State AD Aviation Engine Oil Quaker State Oil Refining Co Red Ram Aviation Oil 20W 50 Red Ram Ltd Canada Sinclair Avoil Sinclair Oil Company Tex...

Page 294: ...tor is not visible If tab is visible the fuel filter element must be replaced and the pop up tab manually reset Refer to the Airplane Maintenance Manual for Fuel Screen Element servicing information Fuel Requirements Aviation grade 100 LL blue or 100 green fuel is the minimum octane approved for use in this airplane Caution Use of lower grades can cause serious engine damage in a short period The ...

Page 295: ...suitable earth ground 3 Place rubber protective cover over wing around fuel filler Note Do not permit fuel nozzle to come in contact with bottom of fuel tanks Keep fuel tanks at least half full at all times to minimize condensation and moisture accumulation in tanks In extremely humid areas the fuel supply should be checked frequently and drained of condensation to prevent possible distribution pr...

Page 296: ...l slightly to move contaminates to the drain points for sampling If after repeated samplings three or more evidence of significant contamination remains do not fly the airplane until a mechanic is consulted the fuel system is drained and purged and the source of contamination is determined and corrected Airplane serials 2710 thru 3420 before SB 2X 28 08 R1 The gascolator incorporates a filter bypa...

Page 297: ...ought above the baffle plates Until experience indicates a longer interval is justified the battery should be checked every 30 days or 25 flight hours to determine that the fluid level is proper and the connections are tight and free of corrosion Do not fill the battery with acid use distilled water only If the battery is not properly charged recharge it starting with a rate of four amperes and fi...

Page 298: ...uld cause corrosion of metal Cover static ports and other areas where cleaning solution could cause damage Be sure to remove the static port covers before flight To wash the airplane use the following procedure 1 Flush away loose dirt with water 2 Apply cleaning solution with a soft cloth a sponge or a soft bristle brush 3 To remove exhaust stains allow the solution to remain on the surface longer...

Page 299: ... System Fuselage Exterior Wings and Wheels AeroShell Flight Jacket Plexicoat Fuselage Exterior ShellStore Online XL 100 Heavy Duty Cleaner Degreaser Fuselage Exterior and Landing Gear Buckeye International Stoddard Solvent PD 680 Type ll Engine Compartment Any Source Kerosene Exterior Windscreen and Windows Any Source Klear To Land Exterior Windscreen and Windows D W Davies Co Prist Exterior Winds...

Page 300: ...ly a nonabrasive cotton cloth or genuine chamois to clean acrylic windows Paper towel or newspaper are highly abrasive and will cause hairline scratches 1 Remove grease or oil using a soft cloth saturated with kerosene then rinse with clean fresh water Note Wiping with a circular motion can cause glare rings Use an up and down wiping motion to prevent this To prevent scratching from dirt that has ...

Page 301: ...th additional solvent and allow it to dry Do not operate the engine until excess solvent has evaporated or otherwise been removed 5 Remove the protective tape from the magnetos 6 Open induction system air inlet and install filter 7 Lubricate the controls bearing surfaces etc in accordance with the Lubrication Chart Landing Gear Before cleaning the landing gear place a plastic cover or similar mate...

Page 302: ...lvent free none abrasive antistatic acrylic cleaner Do not use gasoline alcohol benzene carbon tetrachloride thinner acetone or glass window cleaning sprays Use only a nonabrasive cotton cloth or genuine chamois to clean acrylic windows Paper towel or newspaper are highly abrasive and will cause hairline scratches Note Wiping with a circular motion can cause glare rings Use an up and down wiping m...

Page 303: ...Care Kit 50689 001 Leather Upholstery Cirrus Design Leather Cleaner 50684 001 Leather Upholstery Cirrus Design Ink Remover 50685 001 Leather Upholstery Cirrus Design Leather Conditioner 50686 001 Leather Upholstery Cirrus Design Spot and Stain Remover 50687 001 Leather Upholstery Cirrus Design Vinyl Finish Cleaner 50688 001 Vinyl Panels Cirrus Design Vinyl Leather Cleaner 51479 001 Vinyl and Leath...

Page 304: ...splay screen with power OFF 1 Gently wipe the display with a clean dry cotton cloth 2 Moisten clean cotton cloth with cleaning solution 3 Wipe the soft cotton cloth across the display in one direction moving from the top of the display to the bottom Do not rub harshly 4 Gently wipe the display with a clean dry cotton cloth Headliner and Trim Panels The airplane interior can be cleaned with a mild ...

Page 305: ...not use soaps as they contain alkaline which will alter the leather s pH balance and cause the leather to age prematurely Cover areas where cleaning solution could cause damage Use the following procedure Solvent cleaners and alcohol should not be used on leather upholstery 1 Clean leather upholstery with a soft bristle brush and vacuum where necessary 2 Wipe leather upholstery with a soft damp cl...

Page 306: ...8 34 Information Manual Section 8 Cirrus Design Handling Servicing Maintenance SR22 March 2010 Intentionally Left Blank ...

Page 307: ...o most sections of the handbook Data in a supplement adds to supersedes or replaces similar data in the basic handbook A Log of Supplements page immediately follows this page and precedes all 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 t...

Page 308: ...9 2 Information Manual Section 9 Cirrus Design Supplements SR22 Intentionally Left Blank March 2010 ...

Page 309: ...ce Protection System 05 13 08 ___ 13772 118 R1 Winterization Kit 12 07 04 ___ 13772 119 SR22 Airplanes Registered in Israel 12 03 03 ___ 13772 120 Garmin GTX 330 Mode S Transponder 07 03 04 ___ 13772 121 R1 Honeywell KGP 560 Terrain Awareness Warning System12 15 07 ___ 13772 122 SR22 Airplanes Registered in the European Union 04 12 06 ___ 13772 123 R1 Avidyne Flight Director 12 15 07 ___ 13772 124...

Page 310: ...ubject optional equipment is installed or the special operations are to be performed This Log of Supplements shows all Cirrus Design Supplements available for the aircraft at the 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 March 2010 ...

Page 311: ...R22 this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR22 Pilot s Operating Handbook Handbook Information in this supplement either adds to supersedes or deletes information in the basic Handbook Note This POH Supplement Revision dated Revision 02 07 18 05 supersedes and replaces the original issue of this supplement dated 07 03 04 This r...

Page 312: ... Button LED 3 Marker Sensitivity Select Button a HI Sensitivity LED b LO Sensitivity LED 4 Pilot Intercom Squelch outer knob 5 Power Intercom Volume inner knob 6 Transceiver Audio Select Buttons LEDs 7 Photocell 8 Receiver Audio Select Buttons LEDs 9 Transceiver Audio Transmit Select Buttons LEDs 10 Split COM Button LED 11 Cabin Audio Select Buttons LEDs a SPKR Cabin Speaker b PA Public Address 12...

Page 313: ...operation of the Audio Control Panel Section 5 Performance No change from basic Handbook Section 6 Weight Balance Garmin GMA 340 Audio System No change from basic Handbook Installation of the optional XM Radio System adds the following optional Sym O equipment at the weight and arm shown in the following table Section 7 System Description Power On and Fail safe Operation The Audio Control Panel is...

Page 314: ...vigation receiver audio source is selected by depressing NAV1 NAV2 if installed MKR DME if installed or ADF if installed will select that radio or device as the audio source Audio level of navigation receivers is controlled through the selected radio volume control Transceiver audio is selected by depressing COM1 COM2 or COM3 if installed When the audio source is selected using the COM1 COM2 and C...

Page 315: ...ap mode is not available in this installation Speaker Output Pressing the SPKR button will cause the selected airplane radios to be heard over the cabin speaker Speaker output is muted when a COM microphone is keyed Speaker level is adjustable through an access hole in the top of the unit refer to Garmin installation manual or AMM Public Address PA Function Pressing the PA button on the audio cont...

Page 316: ...y and pilot or copilot ICS activity will mute Music1 Music2 is not muted When both the PILOT and CREW ICS Isolation mode are not selected Music1 is available to crew and passengers Radio activity and MKR activity will mute Music1 Intercom Intercom controls are located towards the left side of the Audio Control Panel The controls consist of a Volume control for the pilot and copilot a Squelch contr...

Page 317: ... can adjust the trip level of the VOX squelch to fit the individual voice and microphone this helps eliminate the frustration of clipping the first syllables There is a slight delay after a person stops talking before the channel closes This prevents closure between words and eliminates choppy communications To adjust squelch 1 With the engine running set the VOX trip level by slowly rotating the ...

Page 318: ...ot and copilot are connected on one intercom channel and have exclusive access to the aircraft radios They may also listen to Music1 Passengers can continue to communicate with themselves without interrupting the Crew and also may listen to Music2 ALL All parties will hear the aircraft radio intercom and Music1 The music volume increases gradually back to the original level after communications ha...

Page 319: ...nd audio keying for ILS approach are summarized below Marker Beacon Sensitivity The SENS push button on the left side of the panel is used to set the marker beacon receiver sensitivity The selected sensitivity level is indicated by illumination of the HIGH or LOW LED When HIGH sensitivity is selected the outer marker beacon tone will sound farther out Selecting LOW sensitivity at this point allows...

Page 320: ... from two geosynchronous XM broadcast satellites The audio signal is then sent by wire to the Audio Control Panel s Music1 and Music2 AUDIO INPUT jacks System operation is provided by a hand held wireless controller When initially powered the XM radio volume is set to mute and will remain muted until the XM radio establishes communication with the wireless controller System volume for both AUDIO I...

Page 321: ...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 This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Original 12 12 00 ...

Page 322: ...rovides complete operating instructions for the GTX 327 and does not require any additional data be carried in the airplane SR22_FM09_1501 1 2 3 4 5 6 7 8 9 10 1 Identification Key 2 Mode Selector Keys a OFF b STBY Standby c ON d ALT 3 Display Window 4 FUNC Function Key 5 CRSR Cursor 6 CLR Clear Key 7 START STOP Key 8 Photocell 9 VFR Key 10 Selector Keys a 0 7 Code Selection b 8 9 Display Brightne...

Page 323: ...ondary surveillance radar Before Takeoff 1 Transponder Mode Selector Keys ALT If the transponder is in the STBY mode it will automatically switch to ALT during takeoff when the groundspeed increases through approximately 35 knots The transponder will respond to ATC Mode C altitude and identification interrogations Note Selecting ON puts the transponder in Mode A identification only The transponder...

Page 324: ... transmits to the interrogating Air Traffic Control Center Digitized altitude information is provided by the altitude digitizer encoder plumbed into the airplane static system The transponder and integrated controls are mounted in the center console The transponder control provides active code display code selection IDENT button and test functions The display is daylight readable and is automatica...

Page 325: ...gations from an ATC secondary ground surveillance radar system This is the normal position for ground operations in the SR22 Note STBY mode is automatically entered from ALT mode during landing ground roll as the groundspeed decreases through 35 knots ON Powers on the GTX 327 in Mode A identification mode The last active identification code will be selected In addition to the airplane s identifica...

Page 326: ... current code 2 Use 0 7 keys to input the new code The new code will not be activated until the last fourth digit is entered Pressing the CLR key will move the cursor back to the previous digit Pressing the CRSR key during code entry will remove the cursor and cancel the entry Note When making routine code changes avoid inadvertent selection of code 7500 and all codes within the 7600 series 7600 7...

Page 327: ...ansponder to the pre programmed VFR code selected in the configuration mode factory set to 1200 Pressing the VFR key a second time will restore the previous identification code FUNC Key Pressing the FUNC key changes the data shown on the right side of the display Pressing the FUNC key a second time will cycle the display to the next data Displayed data includes Pressure Altitude Flight Time Count ...

Page 328: ...tial time Pressing the CLR key resets the timer to the initial value CONTRAST Allows adjustment of display contrast When CONTRAST is selected pressing the 8 key reduces contrast and pressing 9 increases contrast DISPLAY The display function is not available in this installation Display brightness is automatically controlled through a photocell in the front panel Original 12 12 00 ...

Page 329: ...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 Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Note This POH Supplement Revision dated Revision 05 08 1...

Page 330: ...d and Command Altitude display and baro correction Altitude and Decision Height DH alert and Vertical Speed Hold and Command Refer to S Tec System Fifty Five X Autopilot Pilot s Operating Handbook POH Serials 0002 thru 0434 P N 87109 dated 8 November 2000 or later OR Serials 0435 and subsequent P N 87247 original release or later for full operational procedures and description of implemented modes...

Page 331: ...utopilot must be disengaged for missed approach go around and balked landing 4 Flaps must be set to 50 for autopilot operation in Altitude Hold at airspeeds below 95 KIAS 5 Flap deflection is limited to 50 during autopilot operations 6 The autopilot must be disconnected in moderate or severe turbulence 7 Minimum engage height for the autopilot is 400 ft AGL WARNING Autopilot may not be able to mai...

Page 332: ...le shall be no greater than a 45 degree intercept h The ILS is flown at normal approach speeds and within any STC or TC speed constraints and as defined in this flight manual i The flaps should be extended in the approach configuration prior to the Outer Marker No further changes in the flap configuration should be made throughout the autopilot coupled approach j The glideslope is approached in su...

Page 333: ...P N 13772 108 5 of 24 Cirrus Design Section 9 SR22 Supplements SR22_FM09_1502A Figure 1 System 55X Altitude Selector Alerter Autopilot Computer Revision 05 08 15 07 ...

Page 334: ...lfunction has been identified and corrected The autopilot may be disconnected by 1 Pressing the A P DISC Trim switch on the control yoke handle 2 Pulling the AUTOPILOT circuit breaker on Essential Bus Altitude lost during a roll or pitch axis autopilot malfunction and recovery Flight Phase Bank Angle Altitude Loss Climb 40 200 ft Cruise 45 300 ft Descent 40 350 ft Maneuvering 10 60 ft Approach 10 ...

Page 335: ...heck power to turn coordinator Flashing NAV REV or APR Off navigation course by 50 needle deviation or more Use HDG mode until problem is identified Crosscheck raw NAV data compass heading and radio operation Flashing NAV REV or APR with steady FAIL Invalid radio navigation signal Check Nav radio for proper reception Use HDG mode until problem is corrected Flashing VS Excessive vertical speed erro...

Page 336: ...ssing the autopilot VS button WARNING The pilot must properly monitor and control the engine power to avoid stalling the airplane in autopilot altitude hold or vertical speed modes Note Any coupled Altitude Selector Alerter mode can be disabled by disconnecting the autopilot Autopilot and Altitude Selector Pre Flight Tests 1 Battery Master Switch ON 2 Transponder ON 3 Avionics Power Switch ON Note...

Page 337: ...n the ALT SEL setting on the altitude selector is within 100 feet of indicated altitude on altimeter Autopilot ALT mode should remain illuminated indicating autopilot altitude hold is engaged If ALT engagement does not occur within 100 feet of indicated altitude readjust BARO setting on altitude selector 5 Autopilot Tests a Heading Mode TEST 1 Center the HDG bug under the lubber line on the HSI 2 ...

Page 338: ...deviation needle moves left or right Note that control yokes follow direction of needle movement f Autopilot Disconnect Tests 1 Press Pilot A P DISC Trim Switch control yoke Note that the autopilot disengages Move control yoke to confirm that pitch and roll control is free with no control restriction or binding 2 Repeat step using Copilot A P DISC Trim Switch In Flight Procedures 1 Autopilot RDY L...

Page 339: ...the present altitude Note Manually flying the airplane off the selected altitude will not disengage altitude hold and the autopilot will command a pitch change to recapture the altitude when the control input is released 4 Altitude can be synchronized to another altitude by rotating the VS knob on the programmer computer Clockwise rotation will increase and counterclockwise rotation will decrease ...

Page 340: ...tween actual vertical speed and the selected vertical speed usually in climb The pilot should adjust power or reduce the commanded vertical speed as appropriate to remove the error Altitude Pre Select The altitude selector may be used to set up an altitude and vertical speed for intercept and capture The altitude can be above or below the current altitude and the vertical speed chosen should be ap...

Page 341: ... Positive vertical speed indicates climb and negative vertical speeds indicates descent Any vertical speed from 1 100 FPM to 16 1600 FPM is selectable Note If an altitude is selected that requires an opposite vertical speed from that selected the system will automatically select the correct sign for climb for descent and a vertical speed of 500 FPM 6 After takeoff press the VS button and then pres...

Page 342: ...the selector knob CW to increase setting or CCW to decrease setting Only three digits are displayed for millibars for a BARO setting of 952 8 mb the display will indicate 952 and for a BARO setting of 1003 8 mb the display will read 003 For inches Hg the 1 100 decimal position will not be selectable or displayed for example a 29 92 inch Hg setting is input and displayed as 29 9 4 Press DTA again t...

Page 343: ...sh again as the airplane approaches within 300 feet of the selected altitude If the airplane s altitude deviates 300 feet from the selected altitude the chime will sound and the ALR annunciator will flash to indicate the condition 2 To disable ALR press the altitude selector ALR button again The ALR annunciator will go out GPS Tracking and GPS Approach 1 Begin with a reliable GPS signal selected o...

Page 344: ... the APR button on the autopilot programmer computer The NAV GPSS and APR annunciators will be illuminated Use HDG to accomplish a procedure turn Engage GPSS again to complete the approach VOR Tracking and VOR LOC Approach 1 Begin with a reliable VOR or VOR LOC signal selected on the NAV receiver 2 Select desired course on HSI and establish a desired intercept heading 3 Press the NAV button on the...

Page 345: ...ode can be manually armed by pressing the ALT button once Once capture is achieved GS annunciator will come on and ALT annunciator will go out Section 5 Performance There is no change to the airplane performance when the S Tec System 55X autopilot is installed Section 6 Weight Balance There is no change to the airplane weight balance when the S Tec System 55X autopilot is installed Section 7 Syste...

Page 346: ...ector will signal the autopilot to hold the selected altitude The altitude selector alerter receives uncorrected altitude data from the same altitude encoder used by the transponder In addition to the preselect functions the altitude selector provides altitude alert decision height and altitude readout 28 VDC for autopilot and altitude selector alerter is supplied through the 5 amp AUTOPILOT circu...

Page 347: ...n Indicator GPSS converts this information and sends this heading error directly to the autopilot In the GPSS mode the converter receives ground speed and bank angle digital signals that are calculated and converted to a commanded turn rate The turn rate is then scaled and converted to a DC heading error signal that is compatible with the autopilot The end result is an autopilot that can be direct...

Page 348: ...ll not engage if an autopilot roll mode is not engaged Altitude correction for enroute barometric pressure changes may be made by rotation of the VS knob on the autopilot programmer computer Clockwise rotation will increase and counterclockwise rotation will decrease altitude 20 feet for each click The maximum adjustment is 360 feet Adjustments greater than 360 feet can be made by selecting VS mod...

Page 349: ...ncoder are operating and then both the autopilot ALT and VS modes are selected The altitude selector also provides a vertical speed signal to the autopilot pitch computer that is proportional to the amplitude and direction of the selected or computed vertical speed This signal is not used by the autopilot until the autopilot VS mode is engaged When VS is engaged the autopilot compares the selected...

Page 350: ... this mode the autopilot will hold the last vertical speed selected Note It is not necessary to enter the DTA mode to change the vertical speed if vertical speed is coupled to the autopilot If this is the case vertical speed changes can be made by rotating the input knob as required to obtain the new vertical speed While in this mode pressing DTA a second time will toggle the system to operate mod...

Page 351: ...or will command the autopilot to engage altitude hold Readout When the ALT button is pressed in the operate mode the SEL annunciator will go out and the display will show the baro corrected encoder altitude Repeated pushes of the ALT button will alternately display baro corrected encoder altitude and pre selected altitude ALR Alert Mode The ALR button enables the altitude alert system in conjuncti...

Page 352: ...go out Repeated activation of the DH button alternately activates and deactivates the DH mode VS Vertical Speed At initial start up after self test pressing the Altitude Selector Alerter VS button enables vertical speed selector mode The initial vertical speed will be set at 2 indicating a climb at 200 feet per minute Rotating the selector input knob will change the selected vertical speed in 100 ...

Page 353: ...t s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Note Noted effectivity Serials with G3 Wing indicates Serials 2334 2420 2438 and subsequent Noted effectivity Serials before G3 Wing indicates Serials 0334 thru 2333 2335 thru 2419 2421 thru 2437 unle...

Page 354: ...er and propeller blades Section 2 Limitations 1 Flight into known icing is prohibited 2 De icing fluids meeting DTD 406B AVL DTD 406B Aviation Laboratories AL 5 DTD 406B Canyon Industries Dimax 80 TKS 80 Canyon Industries TKS Fluid DTD 406B D W Davies Co Note The Ice Protection System is certified only as No Hazard to normal operations therefore no determination has been made as to the capability ...

Page 355: ...eft wing above de icing fluid filler cap DE ICING FLUID REFER TO AFM FOR APPROVED DE ICING FLUIDS L E U F ON L E U F O N L E U F O N Serials 22 0334 thru 22 2333 22 2335 thru 22 2419 22 2421 thru 22 2437 LH Fuselage above de icing fluid filler cap SR22_FM09_2592A Figure 1 Required Placards Revision 07 05 13 08 ...

Page 356: ...lected when icing conditions are encountered and prior to ice accretion The maximum system operating time while in NORMAL mode is approximately Serials before G3 Wing 60 minutes Serials with G3 Wing 80 minutes MAXIMUM mode is selected if ice has accreted to flight surfaces The maximum system operating time while in MAXIMUM mode is approximately Serials before G3 Wing 30 minutes Serials with G3 Win...

Page 357: ...TY Warning The Ice Protection System is operating in NORMAL or MAX mode and de icing fluid quantity is less than 0 5 gallon 1 9 L Amber ANTI ICE QTY Caution The Ice Protection System is operating in NORMAL or MAX mode and de icing fluid quantity is between 0 5 1 0 gallon 1 9 3 8 L White ANTI ICE QTY Advisory The Ice Protection System is off and de icing fluid is less than or equal to 1 0 gallon 3 ...

Page 358: ... lower by approximately three knots and range is reduced by a maximum of 2 Note Experience with your airplane s power settings may result in more accurate performance numbers than those given above 1 Reduce KTAS shown on the Cruise Performance tables and the Range Endurance Profile tables by 3 knots 2 Reduce range shown on the Range Endurance Profiles by 2 During certain flight conditions such as ...

Page 359: ... Fluid Reservoir Serials before G3 Wing Weight LB Moment 1000 Fluid Reservoir FS 181 0 Weight LB Moment 1000 Fluid Reservoir FS 181 0 0 5 0 09 15 0 2 72 1 0 0 18 16 0 2 90 2 0 0 36 17 0 3 08 3 0 0 54 18 0 3 26 4 0 0 72 19 0 3 44 5 0 0 91 20 0 3 62 6 0 1 09 21 0 3 80 7 0 1 27 22 0 3 98 8 0 1 45 23 0 4 16 9 0 1 63 24 0 4 34 10 0 1 81 25 0 4 53 11 0 1 99 26 0 4 71 12 0 2 17 27 0 4 89 13 0 2 35 28 0a ...

Page 360: ... 1000 Fluid Reservoir FS 148 0 0 5 0 07 18 0 2 66 1 0 0 15 19 0 2 81 2 0 0 30 20 0 2 96 3 0 0 44 21 0 3 11 4 0 0 59 22 0 3 26 5 0 0 74 23 0 3 40 6 0 0 89 24 0 3 55 7 0 1 04 25 0 3 70 8 0 1 18 26 0 3 85 9 0 1 33 27 0 4 00 10 0 1 48 28 0 4 14 11 0 1 63 29 0 4 29 12 0 1 78 30 0 4 44 13 0 1 92 31 0 4 59 14 0 2 07 32 0a a 3 5 gallon 13 2 L Capacity 4 74 15 0 2 22 16 0 2 37 17 0 2 52 Revision 07 05 13 0...

Page 361: ...linger ring proportioning units metering pump filter strainer fluid tank activation switch filler cap system plumbing and attaching hardware The system operates on 28 VDC supplied through the 5 amp ICE PROTECTION circuit breaker on Main Bus 1 De icing Fluid Tank Serials before G3 Wing The de icing fluid tank is serviced through a filler located on the LH side of the fuselage just forward of the ba...

Page 362: ...alue is displayed in white numerals below the gage When the ENGINE page is not active or in the case of an electronic display failure backup mode fluid quantity is displayed along the LH edge of the PFD Fluid quantity is measured by a float type quantity sensor installed in the de icing fluid tank The fuel flow signal is sent to the Engine Airframe Unit processed and transmitted to the Engine Indi...

Page 363: ...mp and then carried to the proportioning units located in the wing Serials before G3 Wing only empennage and cabin floor forward through plastic tubing Proportioning units regulate flow to the porous panels attached to the leading edges of the wing and horizontal stabilizer and to the propeller slinger ring De icing fluid is carried from the proportioning units to the porous panels where the fluid...

Page 364: ...R22_FM09_1527 FINGER STRAINER FLUID TANK VENT DRAIN POROUS PANEL POROUS PANELS PROPORTIONING UNIT PROPORTIONING UNIT PROPORTIONING UNIT POROUS PANEL POROUS PANELS PROPORTIONING UNIT VENT FITTING METERING PUMP FILTER SLINGER RING System Schematic Serials before G3 Wing Revision 07 05 13 08 ...

Page 365: ...NER TUBE FILLER NECK FILTER TEST PORT SLINGER RING FLUID TANK OUTLET STRAINER VENT POROUS PANELS PROPORTIONING UNIT POROUS PANELS POROUS PANELS CHECK VALVE DRAIN VALVE METERING PUMP PRIMING PUMP SR22_FM09_2591 Figure 2 Sheet 1 of 2 System Schematic Serials with G3 Wing Revision 07 05 13 08 ...

Page 366: ...Tank Caution Use only approved de icing fluid See Section 2 Limitations The de icing fluid tank is serviced through a filler located on the LH side of the fuselage just forward of the baggage door or Serials with G3 Wing on the upper LH wing To prevent de icing fluid contamination maintain a clean dedicated measuring container and ensure mouth of fluid container is clean before dispensing Secure t...

Page 367: ... Sample de icing fluid until fluid streams shows no evidence of air bubbles for at least three seconds 3 Perform Pre Flight Inspection verifying evidence of de icing fluid from porous panels and slinger ring 4 If necessary repeat steps 2 and 3 5 If after the above procedure no de icing fluid is evident the ice protection system must be purged in accordance with the Airplane Maintenance Manual by a...

Page 368: ...ision should be based on weather briefings recent pilot reports ATC observations and may include course changes or altitude changes During simulated icing encounters stall speed increases of approximately 12 knots in the clean configuration and 3 knots in the landing configuration were observed In addition cruise speed was reduced by at least 20 KCAS and the airplanes rate of climb diminished by a...

Page 369: ...n 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 Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Note This POH Supplement Revision dated Revision 01 12 15 07 supersedes and...

Page 370: ...s of the 560 GA EGPWS Processor mounted on the underside of the pilot side kickplate a Terrain Obstacle Database integral to the processor the Configuration Module integral to the system s wire harness and the TAWS annunciator panel mounted on the lower LH portion of the instrument panel The KGP 560 receives data from the GPS sensor Transponder Primary Flight Display and the Multifunction Display ...

Page 371: ...nly vertical maneuvers are recommended responses to warnings and alerts unless operating in VMC or the pilot determines using all available information and instruments that a turn in addition to the vertical escape maneuver is the safest course of action During certain operations warning thresholds may be exceeded due to specific terrain or operating procedures During day VFR flight these warnings...

Page 372: ...RESS 7 MFD Soft Keys SET to TAWS Response To Ground Proximity Warnings Aural PULL UP Warning Red TERR WARN Annunciation 1 Level the wings simultaneously adding full power 2 Increase pitch attitude to 15 degrees nose up 3 Adjust pitch attitude to ensure terrain clearance while respecting stall warning If flaps are extended retract flaps to the UP position 4 Continue climb at best angle of climb spe...

Page 373: ...ncrease pitch attitude to 15 degrees nose up 3 Adjust pitch attitude to ensure terrain clearance while respecting stall warning If flaps are extended retract flaps to the UP position 4 Continue climb at best angle of climb speed Vx until terrain clearance is assured Deactivate TAWS 1 SKYWATCH TAWS Circuit Breaker PULL or 2 Avionics Power Switch OFF Section 5 Performance No Change Section 6 Weight ...

Page 374: ...tion of the instrument panel The 560 GA EGPWS Processor is powered by 28 VDC through the 5 amp SKYWATCH TAWS circuit breaker on the Avionics Nonessential Bus For a additional system information refer to the KGP 560 860 EGPWS Pilot s Guide P N 006 18254 001 Revision 04 or later System Constraints If there is no terrain data in the database for a particular area then TAWS alerting is not available f...

Page 375: ...ments GNS 430 GPS Avidyne PFD Transponder TAWS 5 AVIONICS NON ESSENTIAL BUS Configuration Module GMA 340 Audio Panel SR20_FM09_2031 Avidyne MFD KGP 560 Processor TAWS Annunciator Panel Figure 1 Honeywell KGP 560 TAWS Simplified Schematic Revision 01 12 15 07 ...

Page 376: ...s Display will remain functional with the message Warnings Inhibited displayed on the MFD When activated the switch will illuminate amber TERR INOP Indicates the TAWS inoperative When activated the LED will illuminate amber TERR CAUT Indicates a possible terrain or obstacle conflict within 40 60 seconds When activated the LED will illuminate amber TERR WARN Indicates a possible terrain or obstacle...

Page 377: ...ER All TAWS alerting functions inhibited TERR INOP AMBER Indicates TAWS inoperative TERR CAUT AMBER Possible terrain or obstacle conflict within 40 60 seconds TERR WARN RED Possible terrain or obstacle conflict within 30 seconds TAWS SELF TEST TERR INHIBIT TERR INOP TERR CAUT TERR WARN SR22_FM09_2032 Figure 2 TAWS Annunciator Panel Revision 01 12 15 07 ...

Page 378: ...ature of the alert is presented in the MFD message bar Warning Alert Possible terrain or obstacle conflict within 30 seconds When triggered the terrain or obstacle that caused the alert is displayed in bright red In addition a message describing the nature of the alert is presented in the message bar When a caution or warning alert is active the display image surrounding the target is enlarged som...

Page 379: ...ence for color coding for the Terrain Awareness Display Page and as an input to the TAWS Look Ahead algorithm Because it is derived from GPS Geometric Altitude may differ from corrected barometric altitude Therefore Geometric Altitude may be in error by as much as 100 ft and should not be used for navigation MSL G is presented solely to provide the pilot additional situational awareness regarding ...

Page 380: ...minated b The amber TERR INOP light should extinguish c The red TERR WARN light should be illuminated d An aural EGPWS SYSTEM OK is enunciated over cockpit speaker e The red TERR WARN light should extinguish f The amber TERR CAUT light should be illuminated g The amber TERR CAUT light should extinguish h A terrain self test pattern should appear on the MFD i The terrain self test should disappear ...

Page 381: ...plicable 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 Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Note This POH Supplement Revision dated Revision 01 12 15 07 supersedes and replaces the original relea...

Page 382: ...nces situational awareness by reducing cockpit workload through providing a visual cue for the pilot to follow as indicated by the PFD s Flight Director Steering Command Bar Through turning or pitching the airplane as directed by the Steering Command Bar the pilot will follow the necessary course to arrive at a programmed destination Figure 1 Revision 01 12 15 07 ...

Page 383: ...r system replaces the flying W aircraft reference symbol on the PFD with the Flight Director Steering Command Bars and Wedge The system consists of two lighted push buttons installed on the upper LH side of the instrument panel and associated relays and wiring between the PFD and autopilot The remaining portion of the Flight Director system is entirely software dependant When a vertical mode of th...

Page 384: ...mplete description of the Flight Director its operating modes and additional detailed operating procedures No Annunciation Autopilot off or Autopilot not active in either roll or pitch control Green AP ON Annunciation Autopilot active in roll and or pitch control If Autopilot active in roll and pitch control AP annunciation appears on top edge of PFD and Flight Director Steering Command Bars MAGEN...

Page 385: ...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 Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Note This POH Supplement Revision dated Revision 01 12 15 07 supersedes and replaces th...

Page 386: ... 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 Avidyne EMax Engine Instrumentation Revision 01 12 15 07 ...

Page 387: ...ane gauges and provide data to the MFD for display Airplanes equipped with EMax Engine Instrumentation display all engine settings and parameters on a dedicated MFD engine monitor page The MFD also displays engine and fuel data in data blocks on the full screen moving map display In the event of an exceedence each out of limit parameter is highlighted on the screen for immediate attention The engi...

Page 388: ...arameters 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 Revision 01 12 15 07 ...

Page 389: ...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 Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Note This POH Supplement Revision dated Revision 01 12 15 07 supersedes and replace...

Page 390: ...ocedure chart data on the EX5000C MFD If the chart is geo referenced an ownship symbol and flight plan legs can be overlaid on the chart to further enhance the pilot s situational awareness Most approach charts and airport diagrams are geo referenced most arrival departure and miscellaneous charts are not Avidyne CMax Electronic Approach Charts Revision 01 12 15 07 ...

Page 391: ...are and data If no back up data is available contact Air Traffic Control for approach information Section 4 Normal Procedures Note Back up approach charts for CMax are not required However back up approach data for departure destination and alternate field is recommended Reference CMax Description in this supplement Section 7 System Description The CMax installation is entirely software dependant ...

Page 392: ...ion 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 Revision 01 12 15 07 ...

Page 393: ...nt 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 Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Note This POH Supplement Revision dated Revision 01 12 15 07 supersedes and replaces the origin...

Page 394: ...2 Figure 1 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 XM Satellite Weather Overlay Revision 01 12 15 07 ...

Page 395: ...n in the following table Section 7 System Description The XM Satellite Weather System enhances situational awareness by providing the pilot with real time graphical weather information The XM antenna integrated with the COM1 antenna receives weather information from dual redundancy satellites This signal is sent to the XM receiver installed in the co pilot side of the instrument console which inte...

Page 396: ...ellite 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 Revision 01 12 15 07 ...

Page 397: ...Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Note Noted effectivity Serials with G3 Wing indicates Serials 2334 2420 2438 and subsequent Noted effectivity Serials before G3 Wing indicates Serials 1602 1821 1840 1863 thru 2333 2335 thru 2419 and 2421...

Page 398: ...uff type heat exchanger surrounding the right engine exhaust muffler The conditioned air is then forced by ram air pressure or by blower fan into a distribution manifold which regulates airflow and vent selection Serials with G3 Wing Ventilation and cooling is provided by ducting fresh air from a NACA vent on the RH lower cowl to the mixing chamber located on the lower RH portion of the firewall D...

Page 399: ...PRESSOR HEAT EXCHANGER RECIRCULATION CHECK VALVE SR22_FM09_2081C VENTS TEMPERATURE AIRFLOW AIR INLET CONDENSER ASSEMBLY NOTE Illustration depicts maximum cabin cooling airflows and selector settings PANEL AIRFLOW FRESH AIR INTAKE FLOOR AIRFLOW WINDSHIELD DIFFUSER AIR MIXING CHAMBER AIR GASPER Figure 1 Sheet 1 of 2 Air Conditioning System Schematic Serials before G3 Wing Revision 01 03 27 07 ...

Page 400: ...OT WARMER DIFFUSER DISTRIBUTION MANIFOLD EVAPORATOR ASSEMBLY COMPRESSOR RECIRCULATION CHECK VALVE VENTS TEMPERATURE AIRFLOW CONDENSER ASSEMBLY NOTE Illustration depicts maximum cabin cooling airflows and selector settings PANEL AIRFLOW FLOOR AIRFLOW WINDSHIELD DIFFUSER AIR GASPER SR22_FM09_2593A MIXING CHAMBER SERVO MOTOR Air Conditioning System Schematic Serials G3 and Subs Revision 01 03 27 07 ...

Page 401: ...oner OFF Low Oil Pressure 1 Air conditioner OFF Smoke and Fume Elimination See Figure 2 1 Air conditioner OFF 2 Temperature Selector COLD 3 Vent Selector FEET PANEL DEFROST POSITION 4 Airflow Selector SET FAN SPEED TO 3 POSITION If source of smoke and fume is firewall foward a Airflow Selector OFF 5 Panel Eyeball Outlets OPEN 6 Prepare to land as soon as possible If airflow is not sufficient to cl...

Page 402: ...ts SR22 Cabin Fire In Flight 1 Air conditioner OFF Section 3A Abnormal Procedures Alternator Failure 1 Air conditioner OFF Engine Indicating System Failure 1 Air conditioner OFF LOW VOLTS Warning Light Illuminated 1 Air conditioner OFF Revision 01 03 27 07 ...

Page 403: ...m cabin cooling set Airflow Selector to fan speed 3 Vent Selector to feet panel defrost position and Temperature Selector to recirculation mode Additionally ensure the instrument panel and armrest eyeball outlets are open See Figure 1 1 Control Panel SELECT Desired Mode and Temperature 2 Voltage MONITOR Note Decrease electrical load if battery discharge is noted 3 Annunciator Lights CHECK a Verify...

Page 404: ... performance the air conditioner should be off 4 Cruise performance is reduced by 2 knots If maximum performance is desired the air conditioner should be off 5 Range is decreased by 1 for maximum range the air conditioner should be off Section 6 Weight Balance Installation of the Air Conditioning System adds the following optional Sym O equipment at the weight and arm shown in the following table ...

Page 405: ... input Heating Ram air from the upper right cowl inlet flows through the upper cowl and is ducted to the heat exchanger The heated air is then routed to the butterfly valve mounted to the forward side of the firewall which controls entry of hot air into the cabin distribution system When the butterfly valve is open the air flows into the cabin mixing chamber When the butterfly valve is closed the ...

Page 406: ...nd further cooled as the air passes through the evaporator coils and ducted forward to the distribution manifold Conditioned air is circulated through the system by ram air or by the blower fan mounted adjacent to the evaporator Airflow Selection Serials before G3 Wing The airflow selector on the system control panel regulates the volume of airflow allowed into the cabin distribution system throug...

Page 407: ... quarter turn clockwise opens the windshield diffuser butterfly valve which permits shared airflow to the defrosting mechanism and cabin floor outlets When the selector is in the far right position the cabin floor butterfly valve is closed providing maximum airflow to the windshield diffuser When the full max defrost position is selected the air conditioner is activated to provide conditioned dry ...

Page 408: ...tion the 3 speed blower fan is turned on Shared airflow to the defroster cabin floor and panel outlets Maximum airflow to the rear seat foot warmer diffusers and the front seat kickplate outlets Maximum airflow to the panel and armrest air gaspers Maximum airflow to defroster Rotating the selector simultaneously opens and closes the hot and fresh air butterfly valves permitting conditioned mixed a...

Page 409: ...d blower fan is turned on Shared airflow to the defroster cabin floor and panel outlets Maximum airflow to the rear seat foot warmer diffusers and the front seat kickplate outlets Maximum airflow to the panel and armrest air gaspers Maximum airflow to defroster Rotating the selector simultaneously opens and closes the hot and fresh air butterfly valves permitting conditioned mixed air to enter dis...

Page 410: ...14 of 14 P N 13772 127 Section 9 Cirrus Design Supplements SR22 Revision 01 03 27 07 Intentionally Left Blank ...

Page 411: ...s 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 Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Note This POH Supplement Change dated Revision 02 08 26 09 super...

Page 412: ...ions Hartzell Compact Series Propeller with Composite Blades Propeller Type Constant Speed Three Blade Model Number PHC J3YF 1N N7605 B Diameter 78 0 Hartzell Compact Series Lightweight Hub Propeller with Composite Blades Propeller Type Constant Speed Three Blade Model Number PHC J3Y1F 1N N7605 B Diameter 78 0 Section 3 Emergency Procedures Glide performance on aircraft with the subject propeller ...

Page 413: ...o 8 5 1 Conditions Example Power OFF Altitude 10 000 ft AGL Propeller Windmilling Airspeed Best Glide Flaps 0 UP Wind Zero Glide Distance 13 9 NM SR22_FM09_2438 GROUND DISTANCE NAUTICAL MILES HEIGHT ABOVE GROUND FEET 0 2 4 6 8 10 12 14 16 18 20 0 2000 4000 6000 8000 10000 12000 14000 Figure 1 Maximum Glide Revision 02 08 26 09 ...

Page 414: ...ated noise levels for the Cirrus Design SR22 established in accordance with FAR 36 Appendix G are Section 5 Performance Installation of the subject propeller changes the climb airspeeds required to meet engine cooling requirements on hot days Refer to the basic AFM for all performance information except for the following tables Configuration Actual Maximum Allowable Hartzel 3 blade Propeller PHC J...

Page 415: ... of Climb Climb Airspeed 109 Knots Gradient 529 FT NM Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile Temperature C 20 0 20 40 ISA 3400 SL 112 769 731 694 657 703 2000 110 682 645 610 574 689 4000 109 598 563 529 495 607 6000 108 518 484 451 419 528 8000 107 440 408 376 346 452 10000 105 366 335 305 276 379 12000 104 295 266 237 209 308 14000 103 228 199 171 145 240 1...

Page 416: ... Knots Rate of Climb 913 FPM Weight LB Press Alt FT Climb Speed KIAS RATE OF CLIMB Feet per Minute Temperature C 20 0 20 40 ISA 3400 SL 112 1328 1314 1292 1266 1298 2000 110 1211 1192 1167 1138 1179 4000 109 1093 1070 1041 1008 1060 6000 108 974 946 913 877 941 8000 107 853 821 784 745 822 10000 105 730 694 654 612 703 12000 104 606 566 523 477 584 14000 103 481 437 390 341 465 16000 102 354 306 2...

Page 417: ...h contains the pitch changing mechanism consisting of a piston cylinder piston rod and blade actuating components Refer to the basic POH for additional information on the propeller system ATA Item Description Sym Part Number Unit Wt Arm 61 01 Propeller Installation without Ice Protection O 13599 007 67 2 48 0 61 02 Propeller Installation with Ice Protection O 15319 00x 68 0 48 0 61 03 Lightweight ...

Page 418: ...cratch causes an area of increased stress which can lead to serious cracks or the loss of a propeller tip Propeller blades are painted with a durable specialized coating that is resistant to abrasion If this coating becomes eroded it is necessary to repaint the blades to provide proper erosion protection Painting should be performed by an authorized propeller repair station It is permissible to pe...

Page 419: ...s 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 Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Note This POH Supplement Change dated Revision 02 08 26 09 supersedes and replace...

Page 420: ...2 of 58 13772 130 Section 9 Cirrus Design Supplements SR22 Revision 02 08 26 09 Intentionally Left Blank ...

Page 421: ...ttached to the fuselage G3 Wing geometry is slightly changed with an 1 increase in dihedral which allows for the elimination of the aileron rudder interconnect system The CG Envelope Center of Gravity Envelope is expanded to allow for slightly more forward loading at higher gross weights The main landing gear is moved slightly inboard and the strut angle increased to achieve an increase in airplan...

Page 422: ...ft 7 41 m 7 0 ft 2 16 m RADIUS FOR NOSE GEAR RADIUS FOR OUTSIDE GEAR RADIUS FOR INSIDE GEAR RADIUS FOR WING TIP TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER ACTUAL TURNING RADIUS MAY VARY AS MUCH AS THREE FEET GROUND TURNING CLEARANCE SR22_FM01_2412 Turning Radius Revision 02 08 26 09 ...

Page 423: ...98 cm 38 3 ft 11 67 m 9 1 ft 2 8 m 9 inches minimum 23 cm minimum 26 0 ft 7 92 m SR22_FM01_2414 8 9 ft 2 71 m NOTE Wing span includes position and strobe lights Prop ground clearance at 3400 lb 9 inches 23 cm Wing Area 144 9 sq ft Figure 2 Airplane Three View Revision 02 08 26 09 ...

Page 424: ...6 of 58 13772 130 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 Revision 02 08 26 09 ...

Page 425: ...any time VNO 177 180 Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution VO 3400 Lb 133 135 Operating Maneuvering Speed is the maximum speed at which full control travel may be used Below this speed the airplane stalls before limit loads are reached Above this speed full control movements can damage the airplane VFE 50 Flaps 10...

Page 426: ...52 Diameter 78 0 Weight Limits Maximum Takeoff Weight 3400 lb 1542 Kg no change Marking Value KIAS Remarks White Arc 62 104 Full Flap Operating Range Lower limit is the most adverse stall speed in the landing configuration Upper limit is the maximum speed permissible with flaps extended Green Arc 73 177 Normal Operating Range Lower limit is the maximum weight stall at most forward C G with flaps r...

Page 427: ...ine taper to FS 139 1 12 5 MAC at 2700 lb to FS 142 3 19 2 MAC at 3400 lb AFT LIMIT The aft limit is FS 148 1 31 5 MAC at all weights from 2100 lb to 3400 lb 2000 2200 2400 2600 2800 3000 3200 3400 3600 136 138 140 142 144 146 148 150 C G Inches Aft of Datum Weight Pounds 1 2 5 M AC FS 1 39 1 2700 lb 9 8 M AC FS 1 37 8 21 00 lb 1 9 2 M AC FS 1 42 3 3400 lb 31 5 M AC FS 1 48 1 3400 lb 31 5 M AC FS ...

Page 428: ...en Total Fuel Capacity 94 5 U S Gallon 358 0 L Total Fuel Each Tank 47 25 U S Gallon 179 0 L Total Usable Fuel all flight conditions 92 0 U S Gallon 348 0 L Maximum Allowable Fuel Imbalance 10 0 U S Gallon tank The fuel system BOOST pump must be on for takeoff climb landing and for switching fuel tanks Revision 02 08 26 09 ...

Page 429: ...HT 46 U S GALLONS USABLE LEFT 46 U S GALLONS USABLE 13614 001 FUEL PUMP PRIME BOOST P O W E R CUTOFF IDLE RICH MAX FLAPS Engine control panel CONTROL HANDLES FULLY DOWN BEFORE FLIGHT CREW SEATS MUST BE LOCKED IN POSITION AND Airplanes Registered in Brazil and Operating Under the Agência Nacional de Aviação Civil Requirements Wing adjacent to fuel filler caps SR22_FM09_2584B Figure 4 Placards Revis...

Page 430: ...12 of 58 13772 130 Section 9 Cirrus Design Supplements SR22 Revision 02 08 26 09 Intentionally Left Blank ...

Page 431: ...mponents may cause a fire If there is a strong smell of fuel in the cockpit divert to the nearest suitable landing field Perform a Forced Landing pattern and shut down the fuel supply to the engine once a safe landing is assured 1 Temperature Selector COLD 2 Vent Selector FEET PANEL DEFROST POSITION 3 Airflow Selector SET FAN SPEED TO FULL ON 3 POSITION If source of smoke and fume is firewall fowa...

Page 432: ... extinguish flames and land as soon as possible Opening the vents or doors may feed the fire but to avoid incapacitating the crew from smoke inhalation it may be necessary to rid cabin of smoke or fire extinguishant If the cause of fire is not readily apparent is electrical or is not readily accessible proceed as follows WARNING If the airplane is in IMC conditions turn ALT 1 ALT 2 and BAT 1 switc...

Page 433: ...RNING If airplane is in day VFR conditions and turning off the master switches eliminated the fire situation leave the master switches OFF Do not attempt to isolate the source of the fire by checking each individual electrical component 7 Airflow Selector OFF 8 Bat Alt Master Switches ON 9 Avionics Power Switch ON 10 Activate required systems one at a time Pause several seconds between activating ...

Page 434: ...16 of 58 13772 130 Section 9 Cirrus Design Supplements SR22 Revision 02 08 26 09 Intentionally Left Blank ...

Page 435: ...tion Normal Flaps 50 70 KIAS Obstacle Clearance Flaps 50 78 KIAS Enroute Climb Flaps Up Normal 110 120 KIAS Best Rate of Climb SL 101 KIAS Best Rate of Climb 10 000 96 KIAS Best Angle of Climb SL 79 KIAS Best Angle of Climb 10 000 83 KIAS Landing Approach Normal Approach Flaps Up 90 95 KIAS Normal Approach Flaps 50 85 90 KIAS Normal Approach Flaps 100 80 85 KIAS Short Field Flaps 100 VREF 77 KIAS ...

Page 436: ...18 of 58 13772 130 Section 9 Cirrus Design Supplements SR22 Revision 02 08 26 09 Intentionally Left Blank ...

Page 437: ...rument error Conditions Example Power for level flight or maximum continuous whichever is less Flaps 50 Indicated Airspeed 90 Knots Calibrated Airspeed 91 Knots KIAS KCAS Flaps 0 Flaps 50 Flaps 100 60 57 56 57 70 68 68 70 80 79 80 80 90 89 91 89 100 100 101 99 110 111 111 111 120 121 121 130 132 140 142 150 152 160 163 170 173 180 183 190 193 200 204 Revision 02 08 26 09 ...

Page 438: ...ple Power for level flight or maximum continuous whichever is less Flaps 50 Indicated Airspeed 90 Knots Heater Defroster Vents ON Calibrated Airspeed 83 Knots KIAS KCAS Flaps 0 Flaps 50 Flaps 100 60 61 58 54 70 68 66 63 80 77 74 72 90 85 83 82 100 94 92 92 110 103 102 101 120 112 112 130 121 122 140 131 150 141 160 150 170 160 180 170 190 179 200 189 210 198 Revision 02 08 26 09 ...

Page 439: ...d Airspeed Conditions Power for level flight or maximum continuous whichever is less 3400 LB Flaps Press Alt CORRECTION TO BE ADDED FEET Normal Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 12 9 5 0 11 23 36 49 59 5000 13 10 5 0 13 27 42 56 69 10000 16 12 6 0 15 32 49 66 80 15000 18 14 7 0 17 37 58 77 94 50 S L 9 2 4 10 16 5000 11 3 5 12 18 10000 12 3 6 14 22 100 S L 10 1 1 2 6 5000...

Page 440: ...level flight or maximum continuous whichever is less Heater Defroster Vents ON Flaps Press Alt CORRECTION TO BE ADDED FEET Normal Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 12 28 43 57 82 104 126 148 172 5000 16 35 54 71 104 136 168 203 242 10000 20 43 66 87 128 169 211 258 311 15000 23 51 78 103 152 200 251 308 373 50 S L 43 65 87 108 148 5000 21 32 39 42 26 10000 36 54 70 82 88...

Page 441: ... 15 Power Idle C G Forward Bank Angle Noted Stall Speed 74 KIAS 71 KCAS Weight LB Bank Angle Deg STALL SPEEDS Flaps 0 Full Up Flaps 50 Flaps 100 Full Down KIAS KCAS KIAS KCAS KIAS KCAS 3400 Most FWD C G 0 73 70 66 64 62 60 15 74 71 67 65 64 61 30 76 75 71 69 66 64 45 83 83 77 76 72 71 60 99 99 90 90 84 84 3400 Most AFT C G 0 72 69 65 63 60 58 15 73 70 66 64 61 59 30 76 74 69 67 63 62 45 82 82 76 7...

Page 442: ...ions for runway slope are required to be included herein These corrections should be used with caution since published runway slope data is usually the net slope from one end of the runway to the other Many runways will have portions of their length at greater or lesser slopes than the published slope lengthening or shortening takeoff ground roll estimated from the table If brakes are not held whi...

Page 443: ...1691 1813 1939 2069 1728 2000 Grnd Roll 1116 1206 1299 1395 1496 1215 50 ft 1732 1861 1995 2133 2276 1874 3000 Grnd Roll 1234 1332 1435 1542 1653 1323 50 ft 1907 2049 2196 2349 2507 2035 4000 Grnd Roll 1365 1474 1588 1706 1829 1441 50 ft 2102 2259 2422 2590 2764 2212 5000 Grnd Roll 1512 1633 1758 1889 2025 1572 50 ft 2320 2493 2673 2858 3051 2407 6000 Grnd Roll 1676 1810 1950 2095 2245 1717 50 ft ...

Page 444: ... 1146 1228 1313 1401 1170 2000 Grnd Roll 743 802 864 929 995 809 50 ft 1173 1260 1351 1444 1541 1269 3000 Grnd Roll 821 887 955 1026 1100 880 50 ft 1292 1388 1487 1590 1697 1378 4000 Grnd Roll 908 981 1057 1135 1217 959 50 ft 1424 1530 1639 1753 1871 1498 5000 Grnd Roll 1006 1086 1170 1257 1348 1046 50 ft 1571 1688 1809 1935 2065 1630 6000 Grnd Roll 1116 1205 1298 1394 1494 1143 50 ft 1736 1865 19...

Page 445: ...mer than this table provides use extreme caution Conditions Example Power Full Throttle Outside Air Temp 20 C Mixture Set per Placard Weight 3400 LB Flaps 50 Pressure Altitude 4000 FT Airspeed Best Rate of Climb Climb Airspeed 89 Knots Gradient 654 FT NM Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile Temperature C 20 0 20 40 ISA 3400 SL 91 939 896 853 811 864 2000 90...

Page 446: ...ides use extreme caution Conditions Example Power Full Throttle Outside Air Temp 10 C Mixture Set per Placard Weight 3400 LB Flaps 50 Pressure Altitude 6000 FT Airspeed Best Rate of Climb Climb Airspeed 88 Knots Rate of Climb 948 FPM Weight LB Press Alt FT Climb Speed KIAS RATE OF CLIMB Feet per Minute Temperature C 20 0 20 40 ISA 3400 SL 91 1326 1317 1300 1277 1304 2000 90 1214 1200 1179 1153 118...

Page 447: ...e Outside Air Temp 20 C Mixture Full Rich Weight 3400 LB Flaps 0 UP Pressure Altitude 4000 FT Airspeed Best Rate of Climb Climb Airspeed 98 Knots Gradient 639 FT NM Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile Temperature C 20 0 20 40 ISA 3400 SL 101 911 867 823 781 834 2000 100 813 771 729 689 748 4000 99 720 679 639 600 665 6000 98 630 590 552 515 584 8000 97 544...

Page 448: ... As Required Weight 3400 LB Flaps 0 UP Pressure Altitude 6000 FT Airspeed Best Rate of Climb Climb Airspeed 97 Knots Rate of Climb 1030 FPM Weight LB Press Alt FT Climb Speed KIAS RATE OF CLIMB Feet per Minute Temperature C 20 0 20 40 ISA 3400 SL 101 1428 1414 1392 1366 1398 2000 100 1311 1292 1267 1238 1279 4000 99 1193 1170 1141 1108 1160 6000 98 1074 1046 1013 977 1041 8000 97 953 921 884 845 9...

Page 449: ...essure Altitude 12000 FT Winds Zero Climb Airspeed Noted Time to Climb 11 3 Minutes Fuel to Climb 5 6 Gallon Distance to Climb 20 5 NM Press Alt FT OAT ISA C Climb Speed KIAS Rate Of Climb FPM TIME FUEL DISTANCE From Sea Level Time Minutes Fuel U S Gal Distance NM SL 15 101 1398 0 0 0 0 0 0 1000 13 100 1339 0 7 0 3 1 0 2000 11 100 1279 1 5 0 7 2 5 3000 9 99 1220 2 5 1 0 4 0 4000 7 99 1160 3 0 1 3 ...

Page 450: ... nose and main wheel pants and fairings removed Conditions Example Weight 3400 LB Power Setting 55 Temperature Standard Day Takeoff Press Alt 2000 FT Winds Zero Cruise Press Alt 6000 FT Mixture Best Economy Total Fuel 92 Gallons Fuel to Climb 1 3 Gal Cruise Fuel Flow 13 1 GPH Endurance 6 1 Hr Range 968 NM True Airspeed 157 Knots 75 POWERMixture Best Power Press Alt FT Climb Fuel Gal Fuel Remaining...

Page 451: ... 0 8000 2 7 79 0 171 15 4 5 1 887 11 2 10000 3 5 78 2 174 15 4 5 1 899 11 5 12000 4 4 77 1 178 15 4 5 0 912 11 8 55 POWERMixture Best Power Press Alt FT Climb Fuel Gal Fuel Remaining For Cruise Gal Airspeed KTAS Fuel Flow GPH Endurance Hours Range NM Specific Range Nm Gal SL 0 0 81 8 149 13 1 6 3 931 11 4 2000 0 7 81 1 152 13 1 6 2 943 11 6 4000 1 3 80 4 154 13 1 6 2 955 11 9 6000 2 0 79 7 157 13 ...

Page 452: ...TAS Fuel Flow GPH Endurance Hours Range NM Specific Range Nm Gal SL 0 0 81 8 149 11 3 7 2 1074 13 1 2000 0 7 81 1 152 11 3 7 2 1088 13 4 4000 1 3 80 4 154 11 3 7 1 1108 13 7 6000 2 0 79 7 157 11 3 7 0 1115 14 0 8000 2 7 79 0 160 11 3 7 0 1129 14 3 10000 3 5 78 3 163 11 3 6 9 1143 14 6 12000 4 4 77 4 166 11 3 6 8 1156 15 0 14000 5 3 76 5 169 11 3 6 7 1170 15 4 Revision 02 08 26 09 ...

Page 453: ... Around Balked Landing procedure in Section 4 Conditions Example Power Full Throttle Outside Air Temp 20 C Mixture Set per Placard Weight 3400 LB Flaps 100 DN Pressure Altitude 4000 FT Climb Airspeed VREF Climb Airspeed 77 Knots Rate of Climb 633 FT NM Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet Nautical Mile Best Rate of Climb KIAS Temperature C 20 0 20 40 ISA 3400 SL 77 834 835 8...

Page 454: ...Balked Landing procedure in Section 4 Conditions Example Power Full Throttle Outside Air Temp 20 C Mixture Set per Placard Weight 3400 LB Flaps 100 DN Pressure Altitude 4000 FT Climb Airspeed VREF Climb Airspeed 77 Knots Rate of Climb 878 FT NM Weight LB Press Alt FT Climb Speed KIAS RATE OF CLIMB Feet per Minute Best Rate of Climb KIAS Temperature C 20 0 20 40 ISA 3400 SL 77 996 1035 1057 1067 10...

Page 455: ...uld be used with caution since published runway slope data is usually the net slope from one end of the runway to the other Many runways will have portions of their length at greater or lesser slopes than the published slope lengthening or shortening landing ground roll estimated from the table For operation in outside air temperatures colder than this table provides use coldest data shown For ope...

Page 456: ...33 2492 2551 2391 2000 Grnd Roll 1163 1206 1248 1291 1334 1210 Total 2375 2436 2497 2559 2621 2441 3000 Grnd Roll 1207 1251 1295 1339 1384 1247 Total 2437 2501 2565 2630 2696 2493 4000 Grnd Roll 1252 1298 1344 1390 1436 1285 Total 2503 2569 2637 2705 2774 2548 5000 Grnd Roll 1300 1348 1395 1443 1490 1324 Total 2572 2642 2713 2785 2857 2605 6000 Grnd Roll 1350 1399 1449 1498 1547 1365 Total 2645 27...

Page 457: ...STATION FUSELAGE NOTE Reference datum located at fuselage station 0 0 MAC 47 7 50 0 100 0 150 0 200 0 50 0 100 0 150 0 230 0 LEMAC FS 133 1 RBL 87 7 Typical LBL RBL 54 8 LBL 54 8 RBL 77 3 BL 0 0 LBL 77 3 RBL 229 5 LBL 229 5 200 0 50 0 150 0 WL 100 0 100 0 50 0 0 0 150 0 200 0 250 0 300 0 350 0 BUTTOCK LINE BL BL 0 0 WATER LINE WL SR22_FM09_2607 Revision 02 08 26 09 ...

Page 458: ...ed CG CG Total Moment Total Weight Space below provided for additions or subtractions to as weighed condition Empty Weight CG Engine Oil if oil drained 15 lb at FS 78 4 moment 1176 Unusable Fuel 15 0 154 9 2324 Basic Empty Weight CG SR22_FM06_1441 x WL 100 0 y A B FS 100 0 FS 145 0 A x 100 B A y y ____________ Measured x ____________ Measured REF DATUM FS 0 0 Revision 02 08 26 09 ...

Page 459: ...s 1 Preparation a Inflate tires to recommended operating pressures b Service brake reservoir c Drain fuel system d Drain ice protection system e Service engine oil f Move crew seats to the most forward position g Raise flaps to the fully retracted position h Place all control surfaces in neutral position i Verify equipment installation and location by comparison to equipment list 2 Leveling a Leve...

Page 460: ...epeat on right side and average the measurements Subtract this measurement from dimension A to obtain the nosewheel weighing point arm dimension B 5 Determine and record the moment for each of the main and nose gear weighing points using the following formula Moment Net Weight x Arm 6 Calculate and record the as weighed weight and moment by totaling the appropriate columns 7 Determine and record t...

Page 461: ...The above procedure determines the airplane Basic Empty Weight moment and center of gravity in inches aft of datum C G can also be expressed in terms of its location as a percentage of the airplane Mean Aerodynamic Cord MAC using the following formula C G MAC 100 x C G Inches LEMAC MAC Where LEMAC 133 1 MAC 47 7 Revision 02 08 26 09 ...

Page 462: ...as a percentage of the Mean Aerodynamic Cord MAC The relationship between the two is detailed in the weighing instructions 2000 2200 2400 2600 2800 3000 3200 3400 3600 136 138 140 142 144 146 148 150 C G Inches Aft of Datum Weight Pounds 1 2 5 M AC FS 1 39 1 2700 lb 9 8 M AC FS 1 37 8 21 00 lb 1 9 2 M AC FS 1 42 3 3400 lb 31 5 M AC FS 1 48 1 3400 lb 31 5 M AC FS 1 48 1 21 00 lb Revision 02 08 26 0...

Page 463: ...t range at the Takeoff Condition Weight Refer to Moment Limits Item Description Weight LB Moment 1000 1 Basic Empty Weight Includes unusable fuel full oil 2 Front Seat Occupants Pilot Passenger total 3 Rear Seat Occupants 4 Baggage Area 130 lb maximum 5 Zero Fuel Condition Weight Sub total item 1 thru 4 6 Fuel Loading 92 Gallon 6 0 lb gal Maximum 7 Ramp Condition Weight Sub total item 5 and 6 8 Fu...

Page 464: ... 5 74 7 2 8 32 6 196 320 45 92 57 6 49 568 60 8 61 10 8 12 48 9 294 340 48 79 61 2 52 666 80 11 48 14 4 16 64 12 392 360 51 66 64 8 55 764 100 14 35 18 20 8 15 49 380 54 53 68 4 58 862 120 17 22 21 6 24 96 18 588 400 57 4 72 61 96 140 20 09 25 2 27 04 21 686 420 60 27 75 6 65 058 160 22 96 28 8 24 784 440 63 14 79 2 68 156 180 25 83 32 4 27 882 460 71 254 200 28 7 36 30 98 480 74 352 220 31 57 39 ...

Page 465: ...0 Minimum Maximum Minimum Maximum 2200 304 326 2850 398 422 2250 311 333 2900 406 430 2300 318 341 2950 414 437 2350 326 348 3000 421 444 2400 333 355 3050 429 452 2450 340 363 3100 437 459 2500 347 370 3150 444 467 2550 354 378 3200 452 474 2600 362 385 3250 460 481 2650 369 392 3300 467 489 2700 375 400 3350 475 496 2750 383 407 3400 483 504 2800 390 415 2000 2200 2400 2600 2800 3000 3200 3400 3...

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Page 467: ...nded to the spar ribs and aft shear web forming a torsion box that carries all of the wing bending and torsion loads The rear shear webs are similar in construction but do not carry through the fuselage The main spar is laminated epoxy carbon fiber in a C section and is continuous from wing tip to wing tip The wing spar passes under the fuselage below the two front seats and is attached to the fus...

Page 468: ...rough strainers and a flapper valve to the associated collector tank in each wing Each collector tank sump incorporates a flush mounted fuel drain and a vent to the associated fuel tank The engine driven fuel pump pulls filtered fuel from the two collector tanks through a three position LEFT RIGHT OFF selector valve The selector valve allows tank selection From the fuel pump the fuel is metered to...

Page 469: ... increments The RIGHT pointer sweeps an identical scale for the right tank Each scale is marked with a yellow arc from 0 to 14 U S gallons The indicators are calibrated to read 0 when no usable fuel remains Each indicator also provides an output signal to illuminate the FUEL caution light when the fuel quantity goes below approximately 14 gallons in each tank The fuel quantity indications are deri...

Page 470: ...ximately 14 gallons 28 gallons total with tanks balanced in level flight Since both tanks must be below 14 gallons to illuminate the light the light could illuminate with as little as 14 gallons in one tank during level flight if the other tank is allowed to run dry If the FUEL caution light comes on in flight refer to the Fuel Quantity gages to determine fuel quantity The light is powered by 28 V...

Page 471: ...nition Lights The landing light is located in the lower cowl Recognition Lights The airplane is equipped with recognition lights on the leading edge of the wing tips The lights are controlled through the landing light switch on the instrument panel bolster 28 VDC for recognition light operation is supplied through the 5 amp REC INST LTS circuit breaker on Main Bus 1 Revision 02 08 26 09 ...

Page 472: ...ower fan to the distribution manifold mounted to the center aft side of the firewall The distribution manifold uses butterfly valves to control airflow to the floor and defrost vents Airflow is ducted directly to all panel air vents The crew panel air vents are chest high outlets mounted in the RH and LH bolster panels The crew floor air vents are mounted to the bottom of each kick plate The passe...

Page 473: ...RFLOW SR22_FM09_2588A RAM AIR RAM AIR FRESH AIR VALVE HEAT EXCHANGER COLD HOT FOOT WARMER DIFFUSER DISTRIBUTION MANIFOLD FAN ASSEMBLY VENTS TEMPERATURE NOTE Illustration depicts maximum cabin cooling airflows and selector settings PANEL AIRFLOW FLOOR AIRFLOW WINDSHIELD DIFFUSER AIR GASPER MIXING CHAMBER SERVO MOTOR Revision 02 08 26 09 ...

Page 474: ...cupant can control the flow rate from off to maximum by rotating the nozzle When the selector is in the far left position both butterfly valves are closed providing maximum airflow to the panel and armrest eyeball outlets Rotating the selector a quarter turn clockwise opens the cabin floor butterfly valve allowing airflow to the rear seat foot warmer diffusers and the front seat outlets mounted to...

Page 475: ...d 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 Each wing holds a maximum of 46 0 U S gallons When using less than the standard 92 0 U S gallon capacity fuel should be distributed equally between each side Environmental System Revision 02 08 26 09 ...

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Page 477: ...ent 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 Information in this supplement adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook This POH Supplement Change dated Revision 01 05 13 08 supersedes and replaces the Original rel...

Page 478: ...if rapid deceleration is detected In addition for the first 24 hours of operation a 406 MHz signal containing aircraft specific information is transmitted at 50 seconds for 440 milliseconds 8 CIRCUIT BREAKER PANEL OR ALT AIR BRACKET REF 4 MOUNTING TRAY REF SR22_FM09_2677A LEGEND 1 LED Annunciator 2 Remote Switch 3 Antenna 4 Remote Cable 5 Main Control Switch 6 Antenna Jack 7 Attach Straps 8 Artex ...

Page 479: ...witching of the main control switch located on the ELT unit 1 ELT Remote Switch Verify ON Switch the ELT Remote Switch ON even if the red LED annunciator is flashing If airplane radio operable and can be safety used no threat of fire or explosion turn radio ON and select 121 5 MHz If the ELT can be heard transmitting it is working properly 2 Battery Power Conserve Do not use radio transceiver unti...

Page 480: ...ct fixed antenna lead from front of unit 3 Disconnect lead from remote switch and indicator unit 4 Disconnect antenna from mounting tray 5 Loosen attach straps and remove transmitter unit 6 Attach antenna to antenna jack on front of unit 7 Set main control switch to ON 8 Hold antenna upright as much as possible Section 4 Normal Procedures No Change Section 5 Performance No Change Section 6 Weight ...

Page 481: ... The transmitter is in the armed position for normal operations A red LED annunciator flashes when the ELT is transmitting A battery pack consisting of two D cell lithium batteries mounts to a cover assembly within the transmitter to provide power to the transmitter The expiration date of the batteries are indicated on the outside of the ELT battery case and recorded in the aircraft logs A warning...

Page 482: ...ries of pulses on the transmitter LED remote control panel indicator LED and alert buzzer Note FAA regulations require that transmitter tests only be done during the first 5 minutes of each hour and must not last for more than 3 audio sweeps 1 5 seconds If you are at a location where there is an FAA control tower or other monitoring facility notify the facility before beginning the tests Never act...

Page 483: ...itions were found b 2 Flashes Not used If displayed correct condition before further flight c 3 Flashes Open or short circuit condition on the antenna output or cable If displayed correct condition before further flight d 4 Flashes Low power detected If displayed correct condition before further flight e 5 Flashes Indicates that the ELT has not been programmed Does not indicate erroneous or corrup...

Page 484: ...8 of 8 13772 131 Section 9 Cirrus Design Supplements SR22 Revision 01 05 13 08 Intentionally Left Blank ...

Page 485: ... 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 Information in this supplement either adds to supersedes or deletes information in the basic SR22 Pilot s Operating Handbook Note This POH Supplement Change dated Revision 01 11 11 07 supersedes and replaces the ori...

Page 486: ...y satellites WAAS also provides the capability of quickly determining when signals from a given satellite are wrong and removing that satellite from the navigation solution using Receiver Autonomous Integrity Monitoring RAIM a technology developed to assess the integrity of GPS signals Note WAAS satellite coverage is only available in North America User in other parts of the world can receive WAAS...

Page 487: ...P N 13772 132 3 of 10 Cirrus Design Section 9 SR22 Supplements SR22_FM09_1109 SR22_FM09_1285 Figure 1 GNC 420W and GNS 430W 400W Series Navigators Revision 01 11 11 07 ...

Page 488: ...d it is receiving usable navigation information from the GPS receiver 4 Do not use the TERRAIN Interface for navigation of the aircraft The Terrain Display does not provide TAWS capability and is intended to serve as a situational awareness tool only and does not provide the accuracy fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions Section 3 Emergency Procedures...

Page 489: ...the self test is in progress When the self test is successfully completed the Navigator asks for NavData database confirmation acquires position and then displays the acquired position on the Navigators display and on the MFD Note The Navigator is not coupled to an air and fuel data computer Manual fuel on board and fuel flow entries must be made in order to use the fuel planning function of the A...

Page 490: ...d in the GNC 420W control unit mounted in the center console Additionally a VHF communications receiver designated COM 2 is also integrated into the unit GPS Navigator The GNC 420W navigator is coupled to the airplane s CDI The GPS 2 antenna is located on top of the fuselage slightly aft of the rear window along the airplane centerline The navigator is powered by 28 VDC through the 5 amp GPS2 and ...

Page 491: ...nctions GPS Navigator The GNS 430W Navigator is coupled to the airplanes HSI and MFD Typically the second GPS Navigator provides backup and is approved for VFR use only If the second GPS is also a GNS 430W it will be coupled to the CDI and is also approved for IFR use The GPS 1 antenna is located on top of the fuselage slightly aft of the rear window along the airplane centerline and the GPS 2 ant...

Page 492: ...OC 1 it can be alternately set between GPS or VLOC by the CDI button on the navigator The active source is identified on the PFD GPS 2 in this configuration is a GNS 420W Navigator with VHF COM interfaced with the PFD and MFD as GPS 2 Select NAV Source to GPS 2 through the PFD s NAV select button The active source is identified on the PFD 2 Dual GNS 430W units are installed GPS 1 in this configura...

Page 493: ...reness and aid in reducing controlled flight into terrain The TERRAIN function displays altitudes of terrain and obstructions relative to the aircraft s altitude and are advisory in nature only Individual obstructions may be shown if available in the database however not all obstructions may be available in the database and data may be inaccurate TERRAIN information should be used as an aid to vis...

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Page 495: ...s of Control 10 5 Landing Required in Terrain not Permitting a Safe Landing 10 5 Pilot Incapacitation 10 5 General Deployment Information 10 5 Deployment Speed 10 5 Deployment Altitude 10 6 Deployment Attitude 10 6 Landing Considerations 10 7 Emergency Landing Body Position 10 7 Door Position 10 7 Water Landings 10 8 Post Impact Fire 10 9 Ground Gusts 10 9 Taxiing Steering and Braking Practices 10...

Page 496: ...10 2 Information Manual Section 10 Cirrus Design Safety Information SR22 March 2010 Intentionally Left Blank ...

Page 497: ...nal guides and data provided by manufacturers of equipment installed in this airplane You must operate the airplane in accordance with the applicable FAA operating rules and within the Limitations specified in Section 2 of this Handbook The Normal Procedures section of this handbook was designed to provide guidance for day to day operation of this airplane The procedures given are the result of fl...

Page 498: ...ine when and how the CAPS will be used Deployment Scenarios This section describes possible scenarios in which the activation of the CAPS might be appropriate This list is not intended to be exclusive but merely illustrative of the type of circumstances when CAPS deployment could be the only means of saving the occupants of the aircraft Mid Air Collision A mid air collision may render the airplane...

Page 499: ... no risk to the aircraft occupants However if the condition occurs over terrain thought not to permit such a landing such as over extremely rough or mountainous terrain over water out of gliding distance to land over widespread ground fog or at night CAPS activation should be considered Pilot Incapacitation Pilot incapacitation may be the result of anything from a pilot s medical condition to a bi...

Page 500: ...sion altitude Above 2 000 feet there would normally be time to systematically assess and address the aircraft emergency Below 2 000 feet the decision to activate the CAPS has to come almost immediately in order to maximize the possibility of successful deployment At any altitude once the CAPS is determined to be the only alternative available for saving the aircraft occupants deploy the system wit...

Page 501: ...ld maintain the emergency landing body position until the airplane comes to a complete stop The emergency landing body position is assumed with tightened seat belt and shoulder harness by placing both hands on the lap clasping one wrist with the opposite hand and holding the upper torso erect and against the seat backs The seat cushions contain an aluminum honeycomb core designed to crush under im...

Page 502: ...pen it is possible for an object such as a tree limb or flying debris to come through the opening and strike an occupant WARNING If it is decided to unlatch a door unlatch one door only Opening only one door will provide for emergency egress as well as reduce risks associated with ground contact Typically this would be the copilot s door as this allows the other occupants to exit first after the a...

Page 503: ...o assure rapid egress Ground Gusts If it is known or suspected that ground gusts are present in the landing zone there is a possibility that the parachute could drag the airplane after touchdown especially if the terrain is flat and without obstacles In order to assure that the occupants can escape the airplane in the timeliest manner after the airplane comes to rest the pilot may elect to unlatch...

Page 504: ...n or taxi speed control using brakes but without a reduction in power will result in increased brake temperature On flat smooth hard surfaces do not exceed 1000 RPM maximum continuous engine speed for taxi Power settings slightly above 1000 RPM are permissible to start motion for turf soft surfaces and on inclines Use minimum power to maintain constant taxi speed Riding the brakes while taxiing is...

Page 505: ...s of deceleration can take up to an hour to dissipate Always allow adequate cooling time after brake use Allow a cooling period following a high energy braking event High energy braking can include an aborted takeoff or the equivalent energy required for a Maximum Gross Weight full stop from 70 knots in less than 1000 feet Brake Maintenance The brake assemblies and linings should be checked at eve...

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