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7-24

P/N 13772-005

Section 7

Cirrus Design

Systems Description

SR22T

Landing Gear

Main Gear

The main landing gear are bolted to composite wing structure between
the wing spar and shear web. The landing gear struts are constructed
of composite material for fatigue resistance. The composite
construction is both rugged and maintenance free. The main wheels
and wheel pants are bolted to the struts. Each main gear wheel has a
15 x 6.00 x 6 tire with inner-tube installed. Standard wheel pants are
easily removable to provide access to tires and brakes. Access plugs
in the wheel pants can be removed to allow tire inflation and pressure
checking. Each main gear wheel is equipped with an independent,
hydraulically operated single cylinder, dual piston, disc brake.

Nose Gear

The nose gear strut is of tubular steel construction and is attached to
the  steel  engine  mount  structure.  Shock  absorption  is  accomplished
by an oleo shock absorber. The nosewheel is free castering and can
turn  through  an  arc  of  approximately  170  degrees  (85  degrees
degrees either side of center). Steering is accomplished by differential
application of  individual main  gear  brakes.  The tube-type nosewheel
tire measures 5.00 x 5.

Brake System

The main wheels have hydraulically operated, single-disc type brakes,
individually activated by floor mounted toe pedals at both pilot stations.
A parking brake mechanism holds induced hydraulic pressure on the
disc  brakes  for  parking.  The  brake  system  consists  of  a  master
cylinder  for  each  rudder  pedal,  a  hydraulic  fluid  reservoir,  a  parking
brake valve, a single disc brake assembly on each main landing gear
wheel,  temperature  sensors,  and  associated  hydraulic  plumbing  and
wring.
Braking  pressure  is  initiated  by  depressing  the  top  half  of  a  rudder
pedal (toe brake). The 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  travel,  and/or

Original Issue

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Summary of Contents for SR22T

Page 1: ...0 P o u n d T a k e o f f W e i g h t FAA Approved in Normal Category based on FAR 23 This document must be carried in the airplane at all times and be kept within the reach of the pilot during all f...

Page 2: ...CoverPage ii P N 13772 005 Original Issue February 01 2013 Copyright 2013 All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth MN 55811...

Page 3: ...Original Issue 3 1 Original Issue 3 2 Original Issue 3 3 Original Issue 3 4 Original Issue 3 5 Original Issue 3 6 Original Issue 3 7 Original Issue 3 8 Original Issue 3 9 Original Issue 3 10 Original...

Page 4: ...ginal Issue 7 2 Original Issue 7 3 Original Issue 7 4 Original Issue 7 5 Original Issue 7 6 Original Issue 7 7 Original Issue 7 8 Original Issue 7 9 Original Issue 7 10 Original Issue 7 11 Original Is...

Page 5: ...riginal Issue 8 16 Original Issue 8 17 Original Issue 8 18 Original Issue 8 19 Original Issue 8 20 Original Issue 8 21 Original Issue 8 22 Original Issue 8 23 Original Issue 8 24 Original Issue 8 25 O...

Page 6: ...D P N 13772 005 Cirrus Design Pilot s Operating Handbook SR22T List of Effective Pages List of Effective Pages Cont Page Status Page Status Page Status Original Issue Intentionally Left Blank...

Page 7: ...d to allow the most efficient use of the airplane and basic information for maintaining the airplane in a like new condition Note All limitations procedures maintenance servicing requirements and perf...

Page 8: ...andbook is divided into ten sections as follows Section 1 General Section 2 Limitations Section 3 Emergency Procedures Section 3A Abnormal Procedures Section 4 Normal Procedures Section 5 Performance...

Page 9: ...and a Revision Highlights page The Instruction Sheet is intended to assist the manual holder in removing superseded pages and inserting new or superseding pages The List of Effective Pages shows the i...

Page 10: ...ly operate the airplane when equipped with optional equipment not provided with the standard airplane or not included in the Handbook Supplements are essentially mini handbooks and may contain data co...

Page 11: ...hat owners retain information such as supplements that is not applicable to their airplane Warnings Cautions and Notes Warnings Cautions and Notes are used throughout this Handbook to focus attention...

Page 12: ...Front Matter 6 P N 13772 005 Section Front Matter Cirrus Design Foreword SR22T Original Issue Intentionally Left Blank...

Page 13: ...n and Entry Dimensions 8 Baggage Spaces and Entry Dimensions 8 Specific Loadings 8 Symbols Abbreviations and Terminology 9 General Airspeed Terminology and Symbols 9 Meteorological Terminology 10 Engi...

Page 14: ...1 2 P N 13772 005 Section 1 Cirrus Design General SR22T Original Issue Intentionally Left Blank...

Page 15: ...ing ground operations Additionally this section contains definitions or explanations of symbols abbreviations and terminology used throughout this handbook Note For specific information regarding the...

Page 16: ...plane Three View 78 inches 3 BLADE 198 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 8 9 ft 2 71 m NOTE Wing span includes position and strobe lights Prop ground cleara...

Page 17: ...abin 122 49 3 49 7 137 cu ft Baggage Compartment 36 39 8 38 5 32 cu ft Figure 1 2 Airplane Interior Dimensions 39 8 49 3 240 220 200 180 160 140 120 16 0 49 7 27 0 38 5 FS 10 5 33 4 39 0 20 0 33 3 32...

Page 18: ...ft 0 15 m 24 3 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 TU...

Page 19: ...ype Turbocharged direct drive fuel injected air cooled horizontally opposed 6 cylinder engine with 550 cubic inch displacement Horsepower Rating 315 bhp 2500 rpm Propeller Hartzell Compact Series Ligh...

Page 20: ...r 20W60 Below 40 F 4 C SAE 30 10W30 15W50 or 20W50 Maximum Certificated Weights Maximum Gross for Takeoff 3600 lb 1633 Kg Maximum Zero Fuel Weight 3400 lb 1542 Kg Maximum Baggage Compartment Loading 1...

Page 21: ...eed is the speed at which the 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 mov...

Page 22: ...slightly with altitude IMC Instrument Meteorological Conditions are meteorological conditions expressed in terms of visibility distance from cloud and ceiling less than the minima for visual flight d...

Page 23: ...rd Temperature is the temperature that would be found at a given pressure altitude in the standard atmosphere It is 15 C 59 F at sea level pressure altitude and decreases approximately 2 C 3 6 F for e...

Page 24: ...by the aircraft per hour NMPG Nautical Miles Per Gallon is the distance in nautical miles which can be expected per gallon of fuel consumed at a specific engine power setting and or flight configurati...

Page 25: ...unusable fuel and full oil Maximum Ramp Weight Maximum Ramp Weight is the maximum weight approved for ground maneuver and includes the weight of the fuel used for startup taxi and run up Maximum Gross...

Page 26: ...sign General SR22T Tare 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 a...

Page 27: ...imits 11 Minimum Flight Crew 11 Kinds of Operation 12 Kinds of Operation Equipment List 12 Icing 16 Runway Surface 16 Taxi Power 17 Fuel Limits 17 Altitude Limits 17 Environmental Conditions 17 Maximu...

Page 28: ...2 2 P N 13772 005 Section 2 Cirrus Design Limitations SR22T Cirrus Airframe Parachute System CAPS 23 Other Limitations 23 Smoking 23 Placards 24 Original Issue...

Page 29: ...d equipment Refer to Section 9 Log of Supplements of this handbook for amended operating limitations for airplanes equipped with optional equipment Compliance with the operating limitations in this se...

Page 30: ...to 17 500 feet MSL 176 179 Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution VNO at 25 000 feet MSL 150 153 VNO is reduced line...

Page 31: ...flaps above 17 500 feet MSL Green Arc up to 17 500 feet MSL 25 000 feet MSL 74 176 74 150 Normal Operating Range Lower limit is the maximum weight stall at most forward C G with flaps retracted Upper...

Page 32: ...ure Minimum 10 psi Maximum 100 psi Operating Limits Do not reduce manifold pressure below 15 inches when above 18 000 ft MSL Approved Oils Engine Break In For first 25 hours of operation or until oil...

Page 33: ...garding fuel and fuel storage Propeller Hartzell Compact Series Lightweight Hub with Composite Blades Propeller Type Constant Speed Three Blade Model Number PHC J3Y1F 1N N7605 B Diameter 78 0 Model Nu...

Page 34: ...r Warning Range Minimum Caution Range Normal Range Maximum Caution Range Upper Warning Range Cylinder Head Temperature 100 F 500 F 240 420 420 460 CHT 460 CHT Engine Speed 0 3000 RPM 500 2550 2550 RPM...

Page 35: ...9 18 18 Fuel Quantity Gage 0 46 U S Gallon 0 10 14 14 46 Instrument Range Units Red Arc Bar Yellow Arc Bar Green Arc Bar Yellow Arc Bar Red Arc Bar Minimum Minimum Caution Range Normal Range Maximum...

Page 36: ...t of Datum Weight Pounds 12 5 MAC FS 139 1 2700 lb 9 8 MAC FS 137 8 2100 lb 31 5 MAC FS 148 2 2100 lb 21 1 MAC FS 143 2 3600 lb 31 5 MAC FS 148 2 3600 lb Max Zero Fuel 138 136 140 142 144 146 148 150...

Page 37: ...ed These operations include normal stalls chandelles lazy eights and turns in which the angle of bank is limited to 60 Note Because the aircraft has not been certified for spin recovery the Cirrus Air...

Page 38: ...necessary 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 eq...

Page 39: ...belt for each occupant Fire Protection Fire Extinguisher 1 1 1 1 Flight Controls Flap Position Indicator 1 1 1 1 Flap System 1 1 1 1 Pitch Trim Indicator 1 1 1 1 Pitch Trim System 1 1 1 1 Roll Trim I...

Page 40: ...quired if MFD Backlighting Fails Engine Indicators Must Be Shown in Backup Mode MFD Bezel Lighting 1 MFD Backlighting 1 1 1 Required if PFD Backlighting Fails Engine Indicators Must Be Shown in Backup...

Page 41: ...1 PFD Airspeed Indication 1 1 PFD Altitude Indication 1 1 PFD Attitude Indication 1 1 PFD Heading Indication 1 1 PFD Slip Skid Indication 1 1 Turn Coordinator 1 1 Altitude Encoder A R A R 1 1 As requi...

Page 42: ...haust Gas Temperature Indication Fuel Flow Indication 1 1 1 1 Manifold Pressure Indica tion 1 1 1 1 Oil Pressure Indication 1 1 1 1 Oil Quantity Indicator Dip stick 1 1 1 1 Oil Temperature Indication...

Page 43: ...n 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 37 9 L The fuel pump must be se...

Page 44: ...wing illustration If three rear seat passengers cannot meet these requirements occupancy is limited to four persons Child Restraint System 1 Rear seat configuration for LATCH ISOFIX compliant child se...

Page 45: ...proved instrument approach procedures that are retrieved from the GPS equipment database The GPS equipment database must incorporate the current update cycle a Receiver Autonomous Integrity Monitoring...

Page 46: ...quirements and limitations i The Perspective Integrated Avionics System includes navigation sensors that meet the standards set forth in TSO C145a ETSO C145 Sensors and TSO C146a ETSO C146 Display Uni...

Page 47: ...be used as an Airport Moving Map Display AMMD SAFETAXI and CHARTVIEW are to be used by the flight crew to orient themselves on the airport surface to improve pilot situational awareness during ground...

Page 48: ...he L 3 Avionics Systems SkyWatch Traffic Advisory System Model SKY497 Pilot s Guide p n 009 10801 001 must be available to the pilot during flight L 3 Stormscope Weather Information System Optional 1...

Page 49: ...0 or 50 Approved Landing Settings 0 50 or 100 Do not use flaps above 17 500 feet MSL Paint To ensure that the temperature of the composite structure does not exceed 150 F 66 C the outer surface of the...

Page 50: ...APS rocket cover WARNING STAY CLEAR WHEN AIRPLANE IS OCCUPIED ROCKET FOR PARACHUTE DEPLOYMENT INSIDE Wing adjacent to fuel filler caps SR22_FM02_2680 Engine compartment inside oil filler access ENGINE...

Page 51: ...adjacent to fluid filler cap OPEN TO PUSH USE ONLY AL 5 DTD 406B FLUID 4 0 US GALLONS 15 1 LITERS TOTAL USABLE CAPACITY TKS ICE PROTECTION FLUID EXTERNAL POWER 28 V DC Left fuselage on external power...

Page 52: ...FORE FLIGHT RICH OFF LIFT BUTTON FOR OFF POSITION P O W E R OFF RIGHT 46 U S GALLONS USABLE LEFT 46 U S GALLONS USABLE CUTOFF F R I C T I O N IDLE M I X T U R E MAX TURN BOOST PUMP ON DURING TAKE OFF...

Page 53: ...PINS APPROVED REDUCE LINEARLY WITH ALTITUDE VNE VNO 17 500 205 176 KIAS 25 000 175 150 KIAS OPERATE PER AIRPLANE FLIGHT MANUAL FLIGHT INTO KNOWN ICING IS PROHIBITED WITH REQUIRED EQUIPMENT DAY NIGHT V...

Page 54: ...GUISHER FORWARD LEFT OF PILOT SEAT FASTEN SEATBELTS NO SMOKING Instrument Panel EMERGENCY EXIT REMOVE EGRESS HAMMER FROM WITHIN CENTER ARMREST LID STRIKE CORNER OF WINDOW KICK OR PUSH OUT AFTER FRACTU...

Page 55: ...T 140 KIAS BOTH HANDS MAXIMUM FORCE STEADY PULL MAXIMUM DEMONSTRATED DEPLOYMENT SPEED MUST BE WORN AT ALL TIMES SEAT BELT AND SHOULDER HARNESS USE FOR EXTREME EMERGENCIES ONLY WARNING 3 FUEL MIXTURE C...

Page 56: ...2 30 P N 13772 005 Section 2 Cirrus Design Limitations SR22T Original Issue Intentionally Left Blank...

Page 57: ...ight 13 Engine Fire In Flight 14 Wing Fire In Flight 15 Engine Fire During Start 15 Smoke and Fume Elimination 16 Emergency Descent 17 Emergency Descent 17 Maximum Glide 17 Forced Landing 18 Emergency...

Page 58: ...Bus 34 Environmental System Emergencies 35 Carbon Monoxide Level High 35 Oxygen System Emergencies 36 Oxygen System Fault Above 10 000 Ft 36 Oxygen Quantity Low 37 Integrated Avionics System Emergenci...

Page 59: ...ating the aircraft Although emergencies caused by airplane systems or engine malfunctions are extremely rare the guidelines described in this section should be considered and applied as necessary shou...

Page 60: ...inued flight or traditional countermeasures Pilots flying Cirrus aircraft must be properly trained and familiar with CAPS guidance limitations and operating procedures Refer to Section 10 Cirrus Airfr...

Page 61: ...ency pressing and holding the COM transfer button for 2 seconds will tune the emergency frequency of 121 500 MHz If the display is available it will also show it in the Active frequency window The Cir...

Page 62: ...several seconds and reset only once Allow sufficient cooling time for circuit breakers that are reset through a CYCLE procedure Memory Items Checklist steps emphasized by underlining such as the examp...

Page 63: ...ocedures P N 13772 005 3 7 P N 13772 005 3 7 Airspeeds for Emergency Operations Maneuvering Speed 3600 lb 140 KIAS Best Glide All Weights 92 KIAS Emergency Landing Engine out Flaps Up 90 KIAS Flaps 50...

Page 64: ...cockpit or if internal engine damage is suspected move Mixture Control to CUTOFF and do not attempt a restart If the engine fails immediately after becoming airborne abort on the runway if possible In...

Page 65: ...Mixture Control to CUTOFF Fuel Selector to OFF and do not attempt a restart If the engine fails at altitude pitch as necessary to establish best glide speed While gliding toward a suitable landing ar...

Page 66: ...scent or landing Improper Mixture Setting If fuel management is correct and the engine driven fuel pump is functioning properly it is possible the mixture is either too lean or too rich Possible over...

Page 67: ...d pressure is reduced below 15 in Hg and the Power Lever positioned close to or at idle the engine may cease combustion Upon advancing the Power Lever if the wind milling engine does not immediately r...

Page 68: ...SE 10 Alt Master Switches ON 11 CHTs and Oil Temperature VERIFY within GREEN range warm engine at partial power if required 12 If engine will not start perform Forced Landing checklist Amplification S...

Page 69: ...ystems ACTIVATE one at a time 11 Temperature Selector COLD 12 Vent Selector FEET PANEL DEFROST POSITION 13 Airflow Selector SET AIRFLOW TO MAXIMUM 14 Panel Eyeball Outlets OPEN 15 Land as soon as poss...

Page 70: ...required to re activate systems Pause several seconds between activating each system to isolate malfunctioning system Continue flight to earliest possible landing with malfunctioning system off Activa...

Page 71: ...ion Putting the airplane into a dive may blow out the fire Do not exceed VNE during the dive Engine Fire During Start 1 Mixture CUTOFF 2 Fuel Pump OFF 3 Fuel Selector OFF 4 Power Lever ADVANCE 5 Start...

Page 72: ...ible Amplification WARNING Use Oxygen System only if flames and heat are not present In addition to the procedures described above pilot and passengers should don masks and use the oxygen system at th...

Page 73: ...expected do not descend at indicated airspeeds greater than VNO 176 KIAS Maximum Glide Best Glide Speed 92 KIAS at 3600 lb Maximum Glide Ratio 8 6 1 Conditions Example Power OFF Altitude 10 000 ft AGL...

Page 74: ...d a forced landing is imminent select a suitable field and prepare for the landing As forced landings on unprepared surfaces are not recommended CAPS activation may be the safest option Refer to Secti...

Page 75: ...be necessary to allow some cabin flooding to equalize pressure on the doors If the doors cannot be opened break out the windows with the egress hammer and crawl through the opening Landing Without Ele...

Page 76: ...ed by one or more spark plugs becoming fouled A sudden engine roughness or misfiring is usually evidence of a magneto malfunction If for any reason the aircraft experiences an unexpected loss of norma...

Page 77: ...loss in single ignition operation indicates magneto or spark plug trouble Lean the mixture to the recommended cruise setting If engine does not smooth out in several minutes try a richer mixture sett...

Page 78: ...le 1 Prepare for potential engine failure Amplification If oil pressure is low the engine has probably lost a significant amount of its oil and engine failure may be imminent If oil pressure is sudden...

Page 79: ...3 Power Lever MINIMUM REQUIRED 4 Flight PROHIBITED In Flight 1 Power Lever REDUCE 2 Mixture ADJUST fuel flow to top of green arc 3 Airspeed INCREASE 4 Annunciations and Engine Temperatures MONITOR If...

Page 80: ...ion similar to a normally aspirated aircraft at approximately the same altitude However continued flight should only be conducted to the nearest suitable landing place in order to investigate the caus...

Page 81: ...ssure at altitude may be an early indication of an oil leak and impending further loss of oil pressure c Monitor for reduction in oil pressure if observed continue for diversion airfield but prepare f...

Page 82: ...l pressure on the wastegate controller Maintain power at or below 36 5 in Hg by power lever management If High Manifold Pressure persists when oil temperatures are greater than 150 F MAP controller re...

Page 83: ...ure relief valve but turbo overspeed may result in turbo failure if pressure relief valve remains OPEN Reducing manifold pressure via power lever will decrease the airflow through the engine thereby r...

Page 84: ...remaining gages as representative Amplification Isolated red X presentation of an EGT TIT or CHT indicates that sensor has failed Continued flight is permitted using the remaining gages as representat...

Page 85: ...ecklist If governed engine speed is 2600 RPM or less 5 Flight CONTINUE Amplification Propeller governor is set in a fixed position governed RPM is not directly influenced by cabin controls If propelle...

Page 86: ...le Amplification An in flight governor failure will likely result in a large exceedance 3000 RPM or more as propeller blade angle will be go to fine pitch Failure may evidence of engine oil pressure o...

Page 87: ...ion Annunciation indicates fuel totalizer quantity is less than or equal to 9 gallons Fuel Imbalance FUEL IMBALANCE Warning 1 Fuel Quantity Gages CHECK 2 Fuel Pump BOOST If HIGH BOOST already in use f...

Page 88: ...1 Voltage is greater than 32 volts 3 ALT 1 Master Switch OFF 4 Perform ALT 1 Caution Failure Checklist do not reset alternator Amplification Main Bus 1 Voltage is excessive indicates an alternator 1...

Page 89: ...greater than 32 Volts 4 ALT 2 Master Switch CYCLE 5 Main Bus 2 Voltage M2 CHECK If M Bus 2 Voltage remains greater than 32 Volts 6 ALT 2 Master Switch OFF 7 Perform ALT 2 Caution Failure Checklist do...

Page 90: ...a If flight conditions permit consider shedding Air Conditioning Landing Light Pitot Heat Cabin Fan Nav Lights Strobe Lights Audio Panel COM 2 Yaw Damper 6 Land as soon as practical Battery reserve on...

Page 91: ...rflow Selector SET AIRFLOW TO MAXIMUM 5 Panel Eyeball Outlets OPEN If CO LVL HIGH does not extinguish 6 Supplemental Oxygen if available a Oxygen Masks or Cannulas DON b Oxygen System ON c Oxygen Flow...

Page 92: ...ow is normal 3 Oxygen Flow Rate MONITOR 4 Initiate Normal Descent as soon as practical Below 10 000 ft 5 Oxygen System OFF 6 Flight CONTINUE Remain below altitudes requiring supplemental oxygen Amplif...

Page 93: ...Flow Rate CHECK 2 Initiate Normal Descent non emergency below 10 000 ft 3 Oxygen Flow Rate MONITOR Below 10 000 ft 4 Flight CONTINUE Remain below altitudes requiring supplemental oxygen Amplification...

Page 94: ...ding Reference System AHRS is indicated by removal of the sky ground presentation and a Red X and a yellow ATTITUDE FAIL shown on the PFD The digital heading presentation will be replaced with a yello...

Page 95: ...method of spin recovery is activation of the Cirrus Airframe Parachute System see CAPS Deployment Checklist this section Because of this if the aircraft enters a spin CAPS must be deployed immediatel...

Page 96: ...evator 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 maintain a constant heading through the coordina...

Page 97: ...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 98: ...r additional information Starter Engaged STARTER ENGAGED Warning On Ground 1 Ignition Switch DISENGAGE 2 Battery Switches Wait 1 minute before next start attempt If starter does not disengage relay or...

Page 99: ...it is 20 seconds if not manually engaged such as during difficult start this annunciation may indicate a failure of the starter solenoid or a stuck keyswitch Emergency Ground Egress 1 Engine SHUTDOWN...

Page 100: ...any necessary radio communications 7 Ignition Switch OFF 8 ELT ON 9 Seat Belts and Harnesses TIGHTEN 10 Loose Items SECURE 11 Assume emergency landing body position 12 After the airplane comes to a co...

Page 101: ...CAPS would be appropriate are discussed in Section 10 Safety Information of this Handbook These include Mid air collision Structural failure Loss of control Landing on an unprepared surface Pilot inca...

Page 102: ...3 46 P N 13772 005 Section 3 Cirrus Design Emergency Procedures SR22T Original Issue Intentionally Left Blank...

Page 103: ...on 9 Fuel System 10 Low Fuel Quantity 10 Left Fuel Tank Quantity 10 Right Fuel Tank Quantity 10 Fuel Imbalance 11 Electrical System 12 Low Voltage on Main Bus 1 12 Low Voltage on Main Bus 2 12 Battery...

Page 104: ...ilot Failure 19 Flap System Exceedance 19 Landing Gear System 20 Brake Failure During Taxi 20 Left Right Brake Over Temperature 20 Oxygen System 21 Oxygen Quantity Low 21 Other Conditions 23 Aborted T...

Page 105: ...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...

Page 106: ...rmal system and or flight condition In addition to the outlined items in the Abnormal Procedures the following steps are considered part of all abnormal situations Maintain Aircraft Control Analyze th...

Page 107: ...Autopilot ENGAGE to hold heading and altitude 3 Heading RESET to initiate 180 turn Amplification Upon entering IMC a pilot who is not completely proficient in instrument flying should rely upon the au...

Page 108: ...gency Engine Shutdown On Ground Checklist Amplification Rudder effectiveness will decrease with decreasing airspeed Landing With Flat Tire Main Gear 1 Land on the side of the runway corresponding to t...

Page 109: ...list Amplification Manifold Pressure has exceeded caution limits High Manifold Pressure may be a result of cold oil and the affect of high associated oil pressure on the wastegate controller Maintain...

Page 110: ...TER Circuit breaker PULL 3 Flight CONTINUE Engine start will not be available at destination Amplification WARNING Use extreme caution after shutdown if STARTER circuit breaker required pull failed re...

Page 111: ...air won t pose an operating hazard for the engine but conditions significant enough to ice obstruct filters are not suitable conditions for long duration flight of light aircraft If flying through con...

Page 112: ...n Annunciation indicates measured sensed fuel quantity for both tanks is less than or equal to 14 gallons per side Left Fuel Tank Quantity L FUEL QTY Advisory 1 Left Fuel Quantity Gage CHECK If left f...

Page 113: ...ntil sensed imbalance is less than 10 gallons Amplification Fuel level imbalance between left and right is greater than 10 gallons FUEL IMBALANCE Advisory 1 Fuel Quantity Gages CHECK 2 Fuel Pump BOOST...

Page 114: ...ALT 2 Caution Failure Checklists Amplification Main Bus 2 Voltage is low indicative of dual Alt 1 and 2 failures will typically be associated with low M1 and M2 voltages Alt 1 and Alt 2 current indica...

Page 115: ...t consider shedding the following to preserve Battery 1 1 Air Conditioning 2 Landing Light 3 Yaw Servo 4 Convenience Power aux items plugged into armrest jack 5 Continue Flight avoiding IMC or night f...

Page 116: ...t reset low A2 Current and M2 voltage less than M1 voltage 3 ALT 2 Master Switch OFF 4 Continue Flight avoiding IMC or night flight as able reduced power redundancy Amplification Alternator 2 output i...

Page 117: ...CYCLE If annunciation does not extinguish a Hot cabin temperatures LAND AS SOON AS PRACTICAL b Cool cabin temperatures CONTINUE MONITOR Amplification The cooling fan for the PFD is inoperative MFD Coo...

Page 118: ...me lighting knob OFF full counterclockwise Standby instruments all Avionics system keypads and the bolster switch panel are unlit MFD and PFD screen illumination is controlled by automatic photocell p...

Page 119: ...to these instruments With the alternate static source on adjust indicated airspeed slightly during climb or approach in accordance with Section 5 Airspeed Calibration Alternate Static Source as appro...

Page 120: ...cklist and a Airspeed EXPECT NO RELIABLE INDICATION b Exit icing conditions using attitude altitude and power instruments Amplification Pitot heat failure Displayed when Pitot heat switch is ON and Pi...

Page 121: ...URE 6 Land as soon as practical Amplification Any failure or malfunction of the electric trim or autopilot can be over ridden by use of the control yoke If runaway trim is the problem de energize the...

Page 122: ...ntained 4 Ignition Switch OFF Amplification Ground steering is accomplished by differential braking However increasing power may allow some rudder control due to increased groundspeed and airflow over...

Page 123: ...ts and type of device mask or cannula 3 Perform Normal Descent as necessary dependant on duration calculation Amplification 1 Annunciation indicated tank pressure is between 800 and 400 PSI see Oxygen...

Page 124: ...Oxygen System AFMS Amplification Annunciation indicates oxygen tank pressure is below 800 PSI at pressure altitudes below 10 000 ft OXYGEN SYSTEM LEFT ON Advisory 1 Oxygen System OFF Amplification Ann...

Page 125: ...e airplane to a stop by smooth even application of the brakes After a high speed aborted takeoff brake temperatures will be elevated subsequent aborted takeoffs or other high energy use of the brakes...

Page 126: ...ailure 1 Switches Controls CHECK 2 Frequency CHANGE 3 Circuit Breakers SET 4 Headset CHANGE 5 Hand Held Microphone CONNECT Amplification If after following the checklist procedure communication is not...

Page 127: ...15 Normal Takeoff 16 Short Field Takeoff 16 Full Power Climb Rich of Peak Technique 18 Cruise Climb Lean of Peak Technique 20 Cruise 21 Descent 22 Before Landing 22 Normal Landing 23 Short Field Landi...

Page 128: ...4 2 P N 13772 005 Section 4 Cirrus Design Normal Procedures SR22T Original Issue Intentionally Left Blank...

Page 129: ...ce the speed appropriate to the particular weight must be used Takeoff Rotation Normal Flaps 50 80 KIAS Obstacle Clearance Flaps 50 85 KIAS Enroute Climb Flaps Up Best Rate of Climb SL 103 KIAS Best R...

Page 130: ...on 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 fusela...

Page 131: ...n l Stall Warning Test Note Test stall warning system by applying suction to the stall warning system inlet and noting the warning horn sounds m Fuel Quantity Check n Fuel Selector Select Fullest Tank...

Page 132: ...tion 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 Fl...

Page 133: ...cted 8 Nose Right Side a Vortex Generator Condition b Cowling Attachments Secure c Exhaust Pipe Condition Security and Clearance d Gascolator underside Drain for 3 seconds Sample 9 Nose gear Propeller...

Page 134: ...st be inspected and O rings replaced c Wheel and Brakes Fluid Leaks Evidence of Overheating General Condition and Security d Chocks and Tiedown Ropes Remove e Fuel Drains 2 underside Drain and Sample...

Page 135: ...fication WARNING Ensure that the airplane is properly loaded and within the AFM s weight and balance limitations prior to takeoff Caution Crew seats must be locked in position and control handles full...

Page 136: ...ST 8 Propeller Area CLEAR 9 Power Lever OPEN INCH 10 Ignition Switch START Release after engine starts 11 Mixture LEAN until RPM rises to a maximum value Leave the mixture in this position during taxi...

Page 137: ...r flooding Excess fuel can be cleared from the combustion chambers by the following procedure Turn fuel pump off Allow fuel to drain from intake tubes Set the mixture control full lean and the power l...

Page 138: ...issible to start motion for turf soft surfaces and on inclines Use minimum power to maintain taxi speed If the 1000 RPM taxi power limit and proper braking procedures are not observed the brake system...

Page 139: ...s necessary if system remains OFF for takeoff roll 5 Fuel Quantity CONFIRM 6 Fuel Selector FULLEST TANK 7 Fuel Pump BOOST 8 Mixture FULL RICH 9 Flaps SET 50 CHECK 10 Transponder SET 11 Autopilot CHECK...

Page 140: ...36 0 in Hg manifold pressure for all takeoffs the mixture should be full rich for takeoff even at high elevation airports Leaning for takeoff and during maximum performance climb may cause excessive c...

Page 141: ...setting Maximum Power Fuel Flow For maximum power operations Power Lever full forward 2500 RPM 36 0 in Hg manifold pressure fuel flow should be in the green arc For any power setting greater than 30 5...

Page 142: ...LL FORWARD 3 Engine Parameters CHECK 4 Elevator Control ROTATE Smoothly at 80 83 KIAS 5 At 90 KIAS Flaps UP Short Field Takeoff 1 Flaps 50 2 Brakes HOLD 3 Power Lever FULL FORWARD 4 Engine Parameters...

Page 143: ...o maintain no more than 37 0 in Hg For takeoff over a gravel surface advance Power Lever slowly This allows the airplane to start rolling before high RPM is developed and gravel will be blown behind t...

Page 144: ...flow drops below the green range this will usually be corrected by use of BOOST below 18 000 feet or HIGH BOOST PRIME above 18 000 feet If cylinder head temperatures consistently exceed 420 F use high...

Page 145: ...ck is most often indicated by any or a combination of the following Fluctuations in normal fuel flow possibly coupled with abnormal engine operation Rising EGTs and TIT coupled with falling fuel flow...

Page 146: ...under 420 F This climb procedure may not be possible in hot weather but in moderate temperature conditions LOP cruise climbs provide extended range and better fuel economy Depending on aircraft weight...

Page 147: ...Temperature and Manifold Air Pressure and indicates a fuel flow that will give the approximate air to fuel ratio for best economy operation Alternatively the mixture can be set by finding a fuel flow...

Page 148: ...RED For Rapid Descent a Power Lever Smoothly REDUCE MAP 18 to 20 in Hg 7 Mixture AS REQUIRED For Rapid Descent a Mixture Maintain CHTs above 240 F 8 Brake Pressure CHECK Amplification Avoid prolonged...

Page 149: ...l flaps with power on or off Surface winds and air turbulence are usually the primary factors in determining the most comfortable approach speeds Actual touchdown should be made with power off and on...

Page 150: ...ontrol the glide path slightly higher approach speeds should be used under turbulent air conditions After all approach obstacles are cleared progressively reduce power to reach idle just before touchd...

Page 151: ...hen reduce the flap setting to 50 If obstacles must be cleared during the go around climb at 80 85 KIAS with 50 flaps After clearing any obstacles retract the flaps and accelerate to the normal flaps...

Page 152: ...T OUT 8 Chocks Tie downs Pitot Covers AS REQUIRED Amplification Caution Note that the engine hesitates as the switch cycles through the OFF position If the engine does not hesitate one or both magneto...

Page 153: ...ight airframe buffet hear the stall speed warning horn sound between 5 and 10 knots before the stall and see the Crew Alerting System display a STALL Warning annunciation Normally the stall is marked...

Page 154: ...hasten the preheat process Starting If the engine has been cold soaked it is recommended that the propeller be pulled through by hand several times to break loose or limber the oil This procedure will...

Page 155: ...wer lever FULL FORWARD 8 Fuel Pump HIGH BOOST PRIME then BOOST Note In temperatures down to 20 F hold Fuel Pump switch to HIGH BOOST PRIME for 15 seconds prior to starting 9 Propeller Area CLEAR 10 Po...

Page 156: ...itions or after extended idle Ground Operation of Air Conditioning If Installed Note To facilitate faster cabin cooling prior to engine start leave the cabin doors open for a short time to allow hot a...

Page 157: ...ggested procedures minimize environmental noise when operating the aircraft Note Do not follow these noise abatement procedures where they conflict with Air Traffic Control clearances or instructions...

Page 158: ...4 32 P N 13772 005 Section 4 Cirrus Design Normal Procedures SR22T Original Issue Intentionally Left Blank...

Page 159: ...ternate Static Source Standby Altimeter 9 Temperature Conversion 10 Outside Air Temperature for ISA Condition 11 Stall Speeds 12 Wind Components 13 Takeoff Distance 14 Takeoff Distance 3600 LB 15 Take...

Page 160: ...5 2 P N 13772 005 Section 5 Cirrus Design Performance Data SR22T Original Issue Intentionally Left Blank...

Page 161: ...the Conditions notes presented with each table ambient conditions are for a standard day refer to Section 1 Meteorological Terminology Flap position as well as power setting technique is similarly not...

Page 162: ...ues assume zero instrument error Conditions Power for level flight or maximum continuous whichever is less KIAS KCAS Flaps 0 Flaps 50 Flaps 100 60 57 50 56 70 68 66 69 80 79 80 80 90 89 92 91 100 100...

Page 163: ...es assume zero instrument error Conditions Power for level flight or maximum continuous whichever is less Heater Defroster Vents ON KIAS KCAS Flaps 0 Flaps 50 Flaps 100 60 57 60 60 70 67 70 70 80 78 7...

Page 164: ...ditions Power for level flight or maximum continuous whichever is less 3600 LB Flaps Density Alt CORRECTION TO BE ADDED FEET Normal Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 0 0 0 0...

Page 165: ...for level flight or maximum continuous whichever is less 3600 LB Flaps Density 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 24 38 50...

Page 166: ...mum continuous whichever is less Heater Defroster Vents ON Flaps Density Alt CORRECTION TO BE ADDED FEET Alternate Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 4 8 14 21 40 64 94 127 1...

Page 167: ...or maximum continuous whichever is less Heater Defroster Vents ON Flaps Density Alt CORRECTION TO BE ADDED FEET Alternate Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 16 17 19 22 29 4...

Page 168: ...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 4...

Page 169: ...14 7 1 34 16 61 31 88 8000 31 24 16 3 1 30 14 57 29 84 9000 33 27 18 0 3 27 12 54 27 81 10000 35 31 20 4 5 23 10 50 25 77 11000 37 35 22 8 7 19 8 46 23 73 12000 39 38 24 11 9 16 6 43 21 70 13000 41 42...

Page 170: ...LB CG Noted Power Idle Bank Angle Noted Weight LB Bank Angle Deg STALL SPEEDS Flaps 0 Full Up Flaps 50 Flaps 100 Full Down KIAS KCAS KIAS KCAS KIAS KCAS 3600 Most FWD CG 0 74 73 70 67 64 61 15 76 74 7...

Page 171: ...ample Runway Heading 10 Wind Direction 60 Wind Velocity 15 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...

Page 172: ...e 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...

Page 173: ...ll 1443 1559 1680 1805 1936 2071 1595 Total 1980 2131 2288 2450 2618 2792 2178 2000 Grnd Roll 1540 1664 1793 1927 2066 2210 1677 Total 2104 2264 2431 2603 2782 2967 2281 3000 Grnd Roll 1645 1777 1914...

Page 174: ...3 852 1000 Grnd Roll 517 559 602 647 694 742 571 Total 812 872 935 1000 1068 1138 891 2000 Grnd Roll 552 596 642 690 740 792 601 Total 861 925 992 1061 1133 1207 932 3000 Grnd Roll 589 637 686 737 791...

Page 175: ...s Power Full Throttle Mixture Full Rich Flaps 50 Airspeed Best Rate of Climb Weight LB Press Altitude FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile Temperature C 20 0 20 40 50 ISA 3600 SL...

Page 176: ...climb performance the air conditioner should be off Conditions Power Full Throttle Mixture Full Rich Flaps 50 Airspeed Best Rate of Climb Weight LB Press Altitude FT Climb Speed KIAS RATE OF CLIMB Fee...

Page 177: ...685 577 480 390 349 542 6000 120 746 632 530 438 353 313 516 8000 120 690 583 486 398 317 279 490 10000 120 638 536 444 360 284 248 466 12000 120 588 491 404 325 252 218 442 14000 120 541 449 367 292...

Page 178: ...43 1079 917 836 1153 4000 120 1524 1355 1189 1025 863 783 1131 6000 120 1469 1301 1135 971 810 730 1110 8000 120 1414 1246 1081 918 757 677 1089 10000 120 1359 1191 1027 864 703 624 1067 12000 120 130...

Page 179: ...NCE From Sea Level Time Minutes Fuel U S Gal Distance NM S L 15 120 0 0 0 0 0 0 1000 13 120 0 9 0 5 1 7 2000 11 120 1 7 1 0 3 5 3000 9 120 2 6 1 6 5 4 4000 7 120 3 5 2 1 7 2 5000 5 120 4 4 2 6 9 2 600...

Page 180: ...OAT ISA C Climb Speed KIAS TIME FUEL DISTANCE From Sea Level Time Minutes Fuel U S Gal Distance NM S L 15 120 0 0 0 0 0 0 1000 13 120 1 1 0 3 2 2 2000 11 120 2 2 07 4 4 3000 9 120 3 3 1 0 6 7 4000 7 1...

Page 181: ...9 0 170 9 3 176 9 6 75 16 4 157 9 6 162 9 9 167 10 2 65 14 6 148 10 2 154 10 5 158 10 8 55 12 7 138 10 9 143 11 2 147 11 5 4000 85 18 3 168 9 1 174 9 5 179 9 8 75 16 4 160 9 7 165 10 1 170 10 4 65 14...

Page 182: ...11 2 192 11 7 198 12 0 65 14 6 174 11 9 180 12 3 185 12 7 55 12 7 160 12 6 165 13 0 169 13 3 22000 85 18 3 199 10 8 206 11 3 213 11 6 80 17 4 194 11 1 201 11 6 208 12 0 75 16 4 188 11 5 195 11 9 202...

Page 183: ...ecreased by Conditions Mixture Best Economy Target Fuel Flow or less Weight 3600 LB for Climb Avg 3400 LB for Cruise Winds Zero Total Fuel 92 Gallons Range Endurance 85 Power Cruise Full Power Climb P...

Page 184: ...2 841 11 7 22000 12 6 66 9 195 16 4 4 1 847 11 9 24000 14 2 65 4 199 16 4 4 0 852 12 1 25000 15 1 64 4 201 16 4 3 9 853 12 2 Range Endurance 65 Power Cruise Full Power Climb Press Alt FT Climb Fuel Ga...

Page 185: ...43 12 7 6 2 884 11 2 4000 2 1 77 5 145 12 7 6 1 890 11 4 6000 3 2 76 4 147 12 7 6 0 896 11 6 8000 4 3 75 3 150 12 7 5 9 902 11 8 10000 5 4 74 2 152 12 7 5 8 908 12 0 12000 6 5 73 0 155 12 7 5 7 913 12...

Page 186: ...ased by 1 if system in operation Aircraft with optional Enhanced Vision System range is decreased by Conditions Mixture Best Economy Target Fuel Flow or less Weight 3600 LB for Climb Avg 3400 LB for C...

Page 187: ...2 192 16 4 4 4 899 11 7 22000 8 1 71 4 195 16 4 4 3 913 11 9 24000 9 1 70 5 199 16 4 4 3 927 12 1 25000 9 6 69 9 201 16 4 4 3 934 12 2 Range Endurance 65 Power Cruise Cruise Climb Press Alt FT Climb F...

Page 188: ...2 889 11 2 4000 1 3 78 2 145 12 7 6 1 900 11 4 6000 2 0 77 5 147 12 7 6 1 912 11 6 8000 2 7 76 8 150 12 7 6 0 924 11 8 10000 3 5 76 1 152 12 7 6 0 936 12 0 12000 4 2 75 3 155 12 7 5 9 948 12 2 14000 5...

Page 189: ...onditions Power Full Throttle Mixture Full Rich Flaps 100 DN Climb Airspeed VREF Weight LB Press Alt FT Climb Speed VREF KIAS CLIMB GRADIENT Feet Nautical Mile Temperature C 20 0 20 40 50 ISA 3600 SL...

Page 190: ...ure Full Rich Flaps 100 DN Climb Airspeed VREF Weight LB Press Alt FT Climb Speed VREF KIAS RATE OF CLIMB Feet per Minute Temperature C 20 0 20 40 50 ISA 3600 SL 79 1344 1163 986 811 725 1030 2000 79...

Page 191: ...e The above 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...

Page 192: ...Roll 1201 1245 1289 1333 1377 1421 1250 Total 2568 2633 2699 2765 2832 2900 2636 3000 Grnd Roll 1246 1292 1337 1383 1428 1474 1287 Total 2635 2702 2771 2841 2911 2983 2691 4000 Grnd Roll 1293 1340 138...

Page 193: ...Introduction 3 Airplane Weighing Form 4 Airplane Weighing Procedures 5 Loading Instructions 8 Weight and Balance Loading Form 9 Loading Data 10 Moment Limits 11 Weight Balance Record 12 Equipment Lis...

Page 194: ...6 2 P N 13772 005 Section 6 Cirrus Design Weight and Balance Data SR22T Original Issue Intentionally Left Blank...

Page 195: ...and moment for various operations are also provided A comprehensive list of all equipment available for this airplane is included at the back of this section It should be noted that specific informati...

Page 196: ...l As Weighed 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...

Page 197: ...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 against equipm...

Page 198: ...weight and moment by totaling the appropriate columns 7 Determine and record the as weighed CG in inches aft of datum using the following formula CG Total Moment Total Weight 8 Add or subtract any it...

Page 199: ...ta P N 13772 005 6 7 P N 13772 005 6 7 Airplane Leveling Figure 6 2 SR22_FM06_1440A Spirit Level LONGITUDINAL LEVELING LATERAL LEVELING Spirit Level Straight Edge Door Sill Door Sill Spacer Block Stra...

Page 200: ...the rear seat occupants from the Loading Data Figure 6 4 4 Baggage Enter weight and moment for the baggage from the Loading Data Figure 6 4 If desired subtotal the weights and moment 1000 from steps 1...

Page 201: ...eg Num Initials 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 max...

Page 202: ...10 8 12 5 9 3 340 48 8 61 2 52 7 80 11 5 14 4 16 6 12 4 360 51 7 64 8 55 8 100 14 4 18 0 20 8 15 5 380 54 5 68 4 58 9 120 17 2 21 6 25 0 18 6 400 57 4 72 0 62 0 140 20 1 25 2 27 04 21 7 420 60 3 75 6...

Page 203: ...0 414 437 2250 311 333 3000 422 444 2300 318 341 3050 430 452 2350 325 348 3100 438 459 2400 332 356 3150 445 467 2450 340 363 3200 453 474 2500 347 370 3250 461 481 2550 354 378 3300 469 489 2600 361...

Page 204: ...inuous 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...

Page 205: ...Design Section 6 SR22T Weight and Balance Data P N 13772 005 6 13 P N 13772 005 6 13 Equipment List This list will be determined after the final equipment has been installed in the aircraft Original...

Page 206: ...6 14 P N 13772 005 Section 6 Cirrus Design Weight and Balance Data SR22T Original Issue Intentionally Left Blank...

Page 207: ...angement 14 Flight Instruments 16 Attitude Indicator 18 Airspeed Indicator 19 Altimeter 20 Horizontal Situation Indicator 21 Vertical Speed Indicator 21 Magnetic Compass 22 Wing Flaps 22 Flap Control...

Page 208: ...49 Electrical System Protection 50 Electrical System Control 53 Ground Service Receptacle 54 Electrical Indicating 55 Lighting Systems 57 Exterior Lighting 57 Interior Lighting 58 Environmental System...

Page 209: ...Systems Description P N 13772 005 7 3 P N 13772 005 7 3 Emergency Egress Hammer 90 Convenience Outlet 90 Cirrus Airplane Parachute System 91 System Description 91 Activation Handle 92 Deployment Char...

Page 210: ...7 4 P N 13772 005 Section 7 Cirrus Design Systems Description SR22T Original Issue Intentionally Left Blank...

Page 211: ...tion and operation of the standard airplane and its systems Optional equipment described within this section is identified as optional Note Some optional equipment may not be described in this section...

Page 212: ...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 Wings The wing structure is constructed of composite materia...

Page 213: ...ventional 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 Th...

Page 214: ...ley A push pull tube connected to the aft elevator sector pulley transmits motion to the elevator bellcrank attached to the elevators Pitch Trim System Pitch trim is provided by adjusting the neutral...

Page 215: ...Cirrus Design Section 7 SR22T Systems Description P N 13772 005 7 9 P N 13772 005 7 9 Figure 7 1 Elevator System SR22_FM07_1461 Original Issue...

Page 216: ...The electric roll trim is also used by the autopilot to position the ailerons It is possible to easily override full trim or autopilot inputs by using normal control inputs A ground adjustable trim t...

Page 217: ...Cirrus Design Section 7 SR22T Systems Description P N 13772 005 7 11 P N 13772 005 7 11 Figure 7 2 Aileron System SR22_FM07_1462 Original Issue...

Page 218: ...crank translates cable motion to the rudder Springs and a ground adjustable spring cartridge connected to the rudder pedal assembly tension the cables and provide centering force Yaw Trim System Yaw t...

Page 219: ...Cirrus Design Section 7 SR22T Systems Description P N 13772 005 7 13 P N 13772 005 7 13 Figure 7 3 Rudder System SR22_FM07_1463 Original Issue...

Page 220: ...f the instrument panel The cabin environmental control switches are located on the right side of the instrument panel Instrument panel air vents are located on the outboard sections of the panel Cente...

Page 221: ...Avionics Panel 15 Parking Brake 16 Flight Instrument Panel 17 Bolster Switch Panel 18 Start Ignition Key Switch 19 Primary Flight Display 20 Overhead Light Switch Legend 1 Cirrus Airframe Parachute S...

Page 222: ...irspeed attitude and altitude are mounted on the LH bolster panel and are on separate power sources than the PFD Knobs knob sets and membrane type push button switches are located along the inboard ed...

Page 223: ...Selected Altitude 11 Vertical Speed Indicator VSI 12 Current Heading 13 Lubber Line 14 Selected Heading Bug 15 Flight Phase 16 Navigation Source 17 Aircraft Symbol 18 Course Deviation Scale 19 Rotati...

Page 224: ...a traditional slip skid indicator Standby Attitude Indicator The standby attitude indicator is mounted on the LH bolster panel and gives backup indication of flight attitude Bank attitude is indicate...

Page 225: ...d white barber pole coloration Calculated true airspeed is displayed in window at the bottom edge of the airspeed tape Airspeed trend is also displayed as a bar along side of the airspeed tape Standby...

Page 226: ...picted on a conventional three pointer internally lit barometric altimeter installed on the LH bolster panel The instrument senses the local barometric pressure adjusted for altimeter setting and disp...

Page 227: ...ection of the set course The To From arrow rotates with the course pointer and is displayed when the active NAVAID is received The HSI heading reference bug is set using the heading selection knob on...

Page 228: ...o three positions 0 50 16 and 100 35 5 by operating the FLAP control switch The FLAP control switch positions the flaps through a motorized linear actuator mechanically connected to both flaps by a to...

Page 229: ...Cirrus Design Section 7 SR22T Systems Description P N 13772 005 7 23 P N 13772 005 7 23 Figure 7 6 Wing Flaps SR22_FM07_2935A Original Issue...

Page 230: ...imately 170 degrees 85 degrees degrees either side of center Steering is accomplished by differential application of individual main gear brakes The tube type nosewheel tire measures 5 00 x 5 Brake Sy...

Page 231: ...ng Practices for Brake System operational considerations Parking Brake Caution Do not set the PARK BRAKE in flight If a landing is made with the parking brake valve set the brakes will maintain any pr...

Page 232: ...leration Secure all baggage items with tie down straps or cargo net Four baggage tie down straps are provided to secure items in the baggage compartment Each strap assembly has a hook at each end and...

Page 233: ...for forward travel so that shorter people will be positioned slightly higher as they adjust the seat forward Recline position is controlled through levers located on each side of the seat backs Depres...

Page 234: ...ard seat belts are attached to the seat frame The shoulder harnesses are attached to inertia reels mounted in the seat back The rear seats use a 3 point safety harness consisting of one shoulder harne...

Page 235: ...vibration Caution No slack may exist between the occupant s shoulder and restraint harness shoulder strap Stow the seat belts in the latched position when not in use To use the restraints 1 Slip arms...

Page 236: ...hild seat to function properly 3 Route child seat s top tether through the seat back pass through 4 Fasten top tether to rear bulkhead anchor Firmly tension the child seat straps according to the manu...

Page 237: ...to the fuselage shell Engine Controls Engine controls are easily accessible to the pilot on a center console They consist of a single lever power throttle control and a mixture control lever A frictio...

Page 238: ...g Density Alt 8000 Ft Oat 31 F 1 C ISA 0 C 8 Engine Instruments Engine Controls 9 10 1 3 4 5 6 LEGEND 1 Percent Power 2 CHT 3 Tachometer 4 EGT 5 Manifold Pressure 6 Oil Temperature and Pressure 7 Turb...

Page 239: ...inoperative Engine System Annunciations Engine system health caution and warning messages are displayed in color coded text in the Crew Alerting System CAS window located to the right of the Altimete...

Page 240: ...me Unit which processes and transmits the data to the Engine Indicating System Cylinder Head Temperature CHT Cylinder head temperatures for all six cylinders are displayed in the Engine Temperature bl...

Page 241: ...signal to the Engine Airframe Unit that is processed and transmitted to the Engine Indicating System for display Manifold Pressure Gage Manifold pressure is shown in the upper center portion of the E...

Page 242: ...ough a door on the top left side of the engine cowling Ignition and Starter System Two engine driven magnetos and two spark plugs in each cylinder provide engine fuel ignition The right magneto fires...

Page 243: ...uction system should become blocked suction created by the engine will open the door and draw unfiltered air from inside the cowl When the door opens a switch opens which causes an annunciation on the...

Page 244: ...where the heat transfer takes place The heated air exits the engine compartment through louvered vents in the bottom of the cowlings No movable cowl flaps are used Turbochargers The TSIO 550 K has twi...

Page 245: ...ted to high pressure by the governing pump to or from a piston in the propeller hub Oil pressure acting on the piston twists the blades toward high pitch low RPM When oil pressure to the piston in the...

Page 246: ...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 fu...

Page 247: ...feed off a particular tank the valve should be pointed to the fuel indicator for that tank To select RIGHT or LEFT rotate the selector to the desired position To select Off first raise the fuel select...

Page 248: ...e engine starting when engine speed is less than 500 RPM MAP SENSOR HIGH in Hg ENGINE AIRFRAME UNIT FUEL FLOW SENSOR ELECTRIC AUXILIARY PUMP R WING COLLECTOR VENT FILLER R WING TANK FILLER OFF FEED RE...

Page 249: ...sential fuel information is displayed on the Engine Strip along the left edge of the PFD The LEFT pointer indicates left tank fuel quantity and sweeps a vertical bar scale marked from 0 to 46 U S gall...

Page 250: ...culated to provide a fuel flow closely corresponding with the best economy fuel to air ratio Note Target Fuel Flow is removed from gage when resulting engine power would be less than 55 intended for c...

Page 251: ...een Left and Right Tanks A white Advisory message is generated when the imbalance between tanks is greater than 8 gallons An amber Caution message is generated when the imbalance between tanks is grea...

Page 252: ...ication LEGEND 1 Fuel Flow Gage 2 Fuel Calculations Fuel At Destination Totalizer Fuel Used Totalizer Fuel Remaining Totalizer Time Remaining Totalizer Fuel Range Totalizer Nautical Miles Per Gallon T...

Page 253: ...a gear driven internally rectified 100 amp alternator mounted on the right front of the engine Alternator 2 ALT 2 is a belt driven internally rectified 70 amp alternator mounted on the front left of...

Page 254: ...E ADF AVIONICS BUS AUDIO PANEL WEATHER DATA LINK TRAFFIC XPONDER STDBY ATTD 2 MFD 2 MAIN BUS 1 CABIN LIGHTS OXYGEN FUEL QTY KEYPADS AP CTRL AP SERVOS AVIONICS ICE PROTECTION ESSENTIAL BUS 2 ENGINE INS...

Page 255: ...Avionics System Power is distributed to the airplane circuit panel buses through Main and Essential buses in the MCU The Main distribution buses are interconnected by an 80 amp fuse and a diode The d...

Page 256: ...ng strikes enormous energy spikes can be induced within the airplane electrical system In the absence of any transient protection this unwanted energy would typically be dissipated in the form of high...

Page 257: ...MAIN BUS 3 is powered by ALT 1 and BAT 1 from the MCU Main Distribution Bus 1 through a 30 amp fuse inside the MCU In the event of ALT 1 failure BAT 1 will power MAIN BUS 3 ALT 2 is prevented from po...

Page 258: ...LAPS AVIONICS FAN 2 GPS NAV GIA 2 COM 2 AHRS 2 ADC 2 FUEL PUMP PFD 2 MFD 1 12V DC OUTLET YAW SERVO ALT1 A C COND A C COMPR SR22_FM07_3519 BAT 2 GPS NAV GIA 1 COM 1 ADC 1 STDBY ATTD 1 PFD 1 PITCH TRIM...

Page 259: ...cted to the circuit breaker panel s ESS BUS 1 and ESS BUS 2 If any system on the other buses is energized a failure of the Distribution Bus interconnect isolation diode is indicated When the BAT 1 swi...

Page 260: ...tches For normal operations the AVIONICS switch should be placed in the OFF position prior to activating the MASTER switches starting the engine or applying an external power source Ground Service Rec...

Page 261: ...noperative Electrical System Annunciations Electrical system health caution and warning messages are displayed in color coded text in the Crew Alerting System CAS window located to the right of the Al...

Page 262: ...in Bus Voltage 2 Alternator Battery Current 3 Battery 2 4 Battery 1 5 Alternator 1 6 Alternator 2 Density Alt 8000 Ft Oat 31 F 1 C ISA 0 C 1 3 4 7 6 Electrical System Indication 2 7 Avionics 8 Navigat...

Page 263: ...panel bolster 28 VDC for strobe light and control circuits is supplied through the 5 amp STROBE LIGHTS circuit breaker on the NON ESS BUS Landing Light A High Intensity Discharge HID landing light is...

Page 264: ...his position not full DIM In daytime lighting knob OFF full counterclockwise Standby instruments all Avionics system keypads and the bolster switch panel are unlit MFD and PFD screen illumination is c...

Page 265: ...rument panel bolster The reading lights are powered by 28 VDC supplied through the 5 amp CABIN LIGHTS circuit breaker on MAIN BUS 1 Overhead Dome Light General cabin lighting is provided by a dome lig...

Page 266: ...ABIN AIR CONTROL breaker on MAIN BUS 1 The optional Blower Fan is powered by 28 VDC supplied through a 15 amp CABIN FAN breaker on A C BUS 2 Serials with Optional Air Condition System The optionally i...

Page 267: ...ger floor air vents are mounted to the bottom portion of the LH and RH cabin wall trim panels The windshield diffuser located in the glareshield assembly directs conditioned air to the base of the win...

Page 268: ...en vapor reaches a point much hotter than the outside air The compressor then pumps the vapor to the condenser where it cools changes to a liquid and passes to the receiver drier The receiver drier s...

Page 269: ...OOR AIRFLOW AIR FLOW VALVE HOT AIR VALVE SR22_FM07_3261 RAM AIR RAM AIR FRESH AIR VALVE CROSSOVER TUBE FOOT WARMER DIFFUSER DISTRIBUTION MANIFOLD FAN ASSEMBLY NOTE Illustration depicts maximum cabin c...

Page 270: ...ROL PANEL AIR GASPER AIR FLOW VALVE RAM AIR FRESH AIR VALVE HOT AIR VALVE S P S P EVAPORATOR ASSEMBLY COMPRESSOR RECIRCULATION CHECK VALVE CONDENSER ASSEMBLY NOTE llustration depicts maximum cabin coo...

Page 271: ...uttons which electrically actuate butterfly valves at the entrances to the windshield diffuser and the cabin floor ducting When the Temperature Selector is in the blue cool zone there is continuous ra...

Page 272: ...d when the air conditioning button snowflake is pushed the valve on the firewall completely closes and the air conditioner is activated When recirculation button is pushed the fresh air valve complete...

Page 273: ...l linkage actuates the hot air valve to the full open position and the 3 speed blower fan is turned on Shared airflow to the defroster cabin floor and panel outlets Maximum airflow to the rear seat fo...

Page 274: ...f the wings moves forward around the leading edge of the wings As the low pressure area passes over the stall warning inlet a slight negative pressure is sensed by the pressure switch The pressure swi...

Page 275: ...ectrically to maintain proper operation in possible icing conditions The Pitot heat system operates on 28 VDC supplied through the 7 5 amp PITOT HEAT circuit breaker on the NON ESSENTIAL BUS Pitot Hea...

Page 276: ...tatic System STATIC BUTTONS PITOT HEAT PFD Air Data SR22_FM07_2794A AIRSPEED INDICATOR PITOT MAST Annunciation PITOT STATIC WATER TRAPS ALTERNATE STATIC AIR SOURCE ALTIMETER ENGINE AIRFRAME UNIT LOGIC...

Page 277: ...d Avionics Units GEA 71 Engine Airframe Unit GTX 32 Mode A C Transponder GMA 350 Audio Panel with Marker Beacon Receiver GFC 700 3 Axis Autopilot and GMC 705 Controller GTX 33 Mode S Transponder Optio...

Page 278: ...DER ENGINE AIRFRAME UNIT AIR DATA COMPUTER 1 AHRS 1 XM RADIO RECEIVER optional XM SATELLITE DATA LINK RECEIVER optional FMS KEYBOARD AUTOPILOT MODE CONTROLLER MAG 1 MAG 2 INTEGRATED AVIONICS UNIT 1 IN...

Page 279: ...applied Power on default brightness is determined by ambient lighting and is user adjustable Typical alignment time is 60 seconds from battery turn on Display Backup Mode In the event of a detected di...

Page 280: ...uding accelerometers and rate sensors and interfaces with the primary Magnetometer to obtain magnetic field information the Air Data Computer to obtain air data and both Integrated Avionics Units to o...

Page 281: ...Frequency Transfer 121 5 Emer Tune 7 COM Volume and Squelch 8 Display Backup Selection 9 NAV and ID Audio Volume 10 NAV Frequency Transfer 2 13 14 15 3 4 5 6 7 8 9 10 12 19 20 21 1 17 18 16 SR22_FM07...

Page 282: ...PL CLR MENU PROC ENT FMS XPDR COM NAV Legend 22 MFD Clear Cancel Information Default Map 23 MFD Flight Plan Page 24 MFD Direct to Course 25 MFD Menu 26 MFD Procedures 27 MFD Enter Key 28 COM Tuning Mo...

Page 283: ...2 and 5 amp GPS NAV GIA 2 circuit breakers on the MAIN BUS 2 GEA 71 Engine Airframe Unit The Engine Airframe Unit mounted behind the MFD receives and processes analog signals from the fuel gaging syst...

Page 284: ...nd VSI Aircraft annunciations are grouped by criticality and sorted by order of appearance with the most recent message on top The color of the message text is based on its urgency and required action...

Page 285: ...er The Iridium Satellite Network Transceiver mounted in the empennage avionics compartment communicates with the primary Integrated Avionics Unit and Audio Panel to provide near real time weather voic...

Page 286: ...of the system its operating modes and additional detailed operating procedures Traffic Advisory System The Traffic Advisory System TAS advises the pilot of transponder equipped airplane that may pose...

Page 287: ...endix King KR 87 Automatic Direction Finder ADF The KR 87 ADF System is used as a means of identifying positions receiving low and medium frequency voice communications homing tracking and for navigat...

Page 288: ...elevation model with a 9 arc sec approx 885 ft 270m horizontal resolution The synthetic vision system is not intended to be used independently of traditional attitude instrumentation Consequently SVS...

Page 289: ...ays Other traffic during takeoff approach and landing Runway and taxi lights Runway and terrain features during climb descent and low altitude maneuvering The EVS sensor located on the underside of th...

Page 290: ...ling 12 Hour Meters 13 Egress Hammer 14 Telephone and Audio Jacks 15 Cabin Speaker 16 Roll Servo 17 Pitch Trim Adapter opt 18 Pitch Servo 19 XM Radio Transceiver Opt 20 Transponder 21 Satellite Data L...

Page 291: ...this antenna is located below the baggage floor inside of the airplane The transponder antenna is located on the bottom side of the airplane just aft of the baggage compartment bulkhead on the RH sid...

Page 292: ...tion of a device connected to the forward jack is through the MUS 1 selection on the audio panel Distribution of the rear jack is by the MUS 2 selection on the audio panel A third jack on the audio pa...

Page 293: ...Section 7 SR22T Systems Description P N 13772 005 7 87 P N 13772 005 7 87 for PFD and Integrated Avionics Unit Fan operation is supplied through the 5 amp AVIONICS FAN 2 circuit breaker on MAIN BUS 2...

Page 294: ...ane after an accident Eight dated D cell alkaline batteries contained within the transmitter unit power the ELT transmitter The batteries must be replaced at specified intervals based upon the date ap...

Page 295: ...d provides the best fire extinguishing capability with low toxicity A pin is installed through the discharge mechanism to prevent inadvertent discharge of extinguishing agent The fire extinguisher mus...

Page 296: ...it breaker on MAIN BUS 1 Emergency Egress Hammer An eight ounce ball peen type hammer is located in the center armrest accessible to either front seat occupant In the event of a mishap where the cabin...

Page 297: ...ploy 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 struc...

Page 298: ...he rocket two separate events must occur 1 Pull the activation T handle from its receptacle Pulling the T handle removes it from the o ring seal that holds it in place and takes out the slack in the c...

Page 299: ...is deceleration increases with airspeed but in all cases within the parachute envelope should be less than 3 g s During this deceleration a slight nose up may be experienced particularly at high speed...

Page 300: ...ms Description SR22T Note The CAPS is designed to work in a variety of airplane attitudes including spins However deployment in an attitude other than level flight may yield deployment characteristics...

Page 301: ...e Inspection Program 7 Pilot Performed Preventative Maintenance 8 Ground Handling 10 Application of External Power 10 Towing 11 Taxiing 12 Parking 13 Tiedown 14 Leveling 14 Jacking 14 Servicing 16 Lan...

Page 302: ...8 2 P N 13772 005 Section 8 Cirrus Design Handling and Servicing SR22T Original Issue Intentionally Left Blank...

Page 303: ...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...

Page 304: ...Bulletin Give careful attention to the Service Advisory Notice information Ordering Publications Aircraft publications subscription service may be obtained by contacting Customer Service at Cirrus Des...

Page 305: ...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 Stati...

Page 306: ...me in service than the 1 Hour Meter 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 air...

Page 307: ...m 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 above requirement...

Page 308: ...operating 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 p...

Page 309: ...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 Descr...

Page 310: ...ved from the airplane and battery maintenance performed in accordance with the appropriate AMM procedures 1 Ensure that external power source is regulated to 28 VDC 2 Check BAT and AVIONICS power swit...

Page 311: ...push points Do not 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 ve...

Page 312: ...ades 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 3 Rele...

Page 313: ...overnight 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 pulli...

Page 314: ...t apart to prevent eyebolt damage in heavy winds Use bowline knots square knots or locked slipknots Do not use plain slipknots Leveling The airplane is leveled longitudinally by means of a spirit leve...

Page 315: ...fairings Refer to AMM 32 10 3 Remove and stow tie down rings from wings 4 Attach a weighted tailstand to tail tiedown ring 5 Position jacks and jack points for jacking Insert jack point into wing tied...

Page 316: ...em is filled with MIL H 5606 hydraulic brake fluid The fluid level should be checked at every oil change and at the annual 100 hour inspection replenishing the system when necessary The brake reservoi...

Page 317: ...ion or warping of the disk rotor Excessive heat can cause the caliper components to discolor or cause yellowing of the part identification label To inspect the brake assemblies 1 Remove main gear fair...

Page 318: ...ls 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 inspected for cracks frequently Befo...

Page 319: ...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 q...

Page 320: ...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 Pennzo...

Page 321: ...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 le...

Page 322: ...to the same level as the opposite tank This will aid in keeping fuel loads balanced 5 Remove nozzle install filler cap and remove protective cover 6 Repeat refuel procedure for opposite wing 7 Remove...

Page 323: ...ll as operational conditions permit to reduce condensation on the inside of fuel tanks Draining Fuel System The bulk of the fuel may be drained from the wing fuel tanks by the use of a siphon hose pla...

Page 324: ...external power receptacle is located on the left side of the fuselage just aft of the firewall Refer to the AMM for battery servicing procedures Oxygen System Servicing Caution To preclude the possib...

Page 325: ...surfaces or could 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...

Page 326: ...ll 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 Compa...

Page 327: ...r 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 accumulated on the cloth fold cloth to expose a cle...

Page 328: ...uction system inlet 3 With the engine cowling removed spray or brush the engine with solvent or a mixture of solvent and degreaser In order to remove especially heavy dirt and grease deposits it may b...

Page 329: ...sh the gear area with solvent or a mixture of solvent and degreaser as desired Where heavy grease and dirt deposits have collected it may be necessary to brush areas that were sprayed in order to clea...

Page 330: ...ee 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 cham...

Page 331: ...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 Leat...

Page 332: ...lean 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...

Page 333: ...e the leather to age prematurely Cover areas where cleaning solution could cause damage Use the following procedure Caution Solvent cleaners and alcohol should not be used on leather upholstery 1 Clea...

Page 334: ...8 34 P N 13772 005 Section 8 Cirrus Design Handling and Servicing SR22T Original Issue Intentionally Left Blank...

Page 335: ...72 135 R3 GFC 700 Automatic Flight Control System 12 14 10 ___ 13772 136 R1 Garmin Terrain Awareness Warning System 01 06 10 ___ 13772 143 R2 Part 135 Electrical Loading Shedding Procedure 01 06 10 __...

Page 336: ...ct optional equipment is installed or the special operations are to be performed This Log of Supplements shows all Cirrus Design Supplements available for the aircraft at the corresponding date of the...

Page 337: ...R Part 135 this Supplement is applicable and must be inserted in the Supplements Section of the Pilot s Operating Handbook This document must be carried in the airplane at all times Information in thi...

Page 338: ...ffixed to the tubing on each cannula and available to each user The instructions must contain the following information A warning against smoking while oxygen is in use An illustration showing the cor...

Page 339: ...1 Oxygen Bottle right front seat Check Properly Secured 2 Oxygen Masks or Cannulas Connected to Regulator 3 Oxygen Pressure Gage Green Arc 4 Oxygen Shutoff Valve OFF Before Starting Engine 1 Passenge...

Page 340: ...ion Refer to approved system manufacturer s data for a description of the equipment cleaning instructions and specific operational instructions Mounting Instructions The oxygen bottle must be properly...

Page 341: ...oops on forward side of bottle as shown in Detail B through the male buckle half and through the cinch as shown in Detail C Insert male buckle half into female buckle half and tighten strap at cinch L...

Page 342: ...e Feet 10 000 15 000 18 000 25 000 XCP 180 134 1 2 23 1 49 1 24 0 89 2 1 12 0 75 0 62 0 45 3 0 74 0 50 0 41 0 30 XCP 415 371 1 6 18 4 12 3 43 2 47 2 3 09 2 06 1 71 1 24 3 2 06 1 37 1 14 0 82 XCP 682 6...

Page 343: ...ly in those areas indicated 3 Compliance with the limitations contained in the basic manual and approved supplements is mandatory 4 Foreign operating rules and any references to such rules in the basi...

Page 344: ...6 169 8 172 0 174 1 80 176 4 178 6 180 8 183 0 185 2 187 4 189 6 191 8 194 0 196 2 90 198 4 200 6 202 8 205 0 207 2 209 4 211 6 213 9 216 0 218 3 100 220 5 222 7 224 9 227 1 229 3 231 5 233 7 235 9 23...

Page 345: ...Kilograms x 2 205 Pounds Pounds x 0 454 Kilograms SR22_FM09_1510 KILOGRAMS POUNDS Units x 10 100 etc 220 210 200 190 180 170 160 150 140 130 120 110 100 90 80 70 60 50 40 30 20 10 0 100 95 90 85 80 75...

Page 346: ...8 246 1 249 3 252 6 255 9 259 2 80 262 5 265 8 269 0 272 3 275 6 278 9 282 2 285 4 288 7 292 0 90 295 3 298 6 301 8 305 1 308 4 311 7 315 0 318 2 321 5 324 8 100 328 1 331 4 334 6 337 9 341 2 344 5 3...

Page 347: ...ength Conversion Metres x 3 281 Feet Feet x 0 305 Metres FEET SR22_FM09_1511 Units x 10 100 etc 0 0 20 40 60 80 100 120 140 160 180 200 220 240 260 280 300 320 5 10 15 20 25 30 35 40 45 50 55 60 65 70...

Page 348: ...1 10 80 31 50 31 89 32 28 32 68 33 07 33 47 33 86 34 25 34 65 35 04 90 35 43 35 83 36 22 36 61 37 01 37 40 37 80 38 19 38 58 38 98 100 39 37 39 76 40 15 40 55 40 95 41 34 41 73 42 13 42 52 42 91 in 0...

Page 349: ...ion Centimeters x 0 394 Inches Inches x 2 54 Centimeters SR22_FM09_1989 Units x 10 100 etc 0 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 5 10 15 20 25 30 35 40 45 50 55 60 65 7...

Page 350: ...Miles Nautical Miles x 1 852 Kilometers Kilometers x 0 54 Nautical Miles SR22_FM09_1990 Units x 10 100 etc 0 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 105 110 115 5 10 15 20 25 30...

Page 351: ...6 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 1...

Page 352: ...48 18 70 18 92 19 14 19 36 19 58 90 19 80 20 02 20 24 20 46 20 68 20 90 21 12 21 34 21 56 21 78 100 22 00 22 22 22 44 22 66 22 88 23 10 23 32 23 54 23 76 23 98 Gal 0 1 2 3 4 5 6 7 8 9 litres litres l...

Page 353: ...200 220 240 260 280 300 320 340 360 380 400 420 440 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 IMPERIAL GALLONS LITRES 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 0...

Page 354: ...x 1 58 Pounds Pounds x 0 633 Litres SR22_FM09_1513 0 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 POUNDS LITRES 0 0 5 10 15 20 25 3...

Page 355: ...Follow arrow and multiply backtrack the arrow and divide Bear in mind that the figures are approximations for quick reference but with enough accuracy to eliminate gross errors and dead stick landings...

Page 356: ...14 of 14 P N 13772 114 Section 9 Cirrus Design Supplements SR22 SR22T Figure 7 Revision 01 07 07 10 Intentionally Left Blank...

Page 357: ...th the basic AFM and supplements The information contained herein supplements or supersedes that in the basic manual and approved supplements only in those areas indicated 3 Compliance with the limita...

Page 358: ...certificated noise levels for the aircraft established in accordance with ICAO Annex 16 Volume I are Section 5 Performance No Change Section 6 Weight Balance No Change Section 7 Systems Description No...

Page 359: ...his POH Supplement is applicable and must be inserted in the Supplements Section of the Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supple...

Page 360: ...MHz if rapid deceleration is detected In addition for the first 24 hours of operation a 406 MHz signal containing aircraft specific information is transmitted at 50 seconds for 440 milliseconds 8 CIRC...

Page 361: ...al switching 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...

Page 362: ...onnect 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...

Page 363: ...ion 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 prov...

Page 364: ...a series 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 a...

Page 365: ...conditions 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 conditio...

Page 366: ...8 of 8 P N 13772 131 Section 9 Cirrus Design Supplements SR22 SR22T Revision 02 01 06 10 Intentionally Left Blank...

Page 367: ...utomatic Descent functions When the GFC 700 Automatic Flight Control System is installed on the aircraft this POH Supplement is applicable and must be inserted in the Supplements Section of the basic...

Page 368: ...the aircraft is equipped with ESP software load 0764 09 or later it is identified and displayed on the second MFD splash screen presented after power up This page will state This aircraft is equipped...

Page 369: ...selected mode 7 The Autopilot and Flight Director will not command pitch or roll beyond the Command Limits 8 Use of VNAV is not supported during an approach with a teardrop course reversal VNAV will b...

Page 370: ...lot until the malfunction has been identified and corrected The Autopilot may be disconnected by 1 Pressing the A P DISC on the control yoke or 2 Pulling the AP SERVOS circuit breaker on MAIN BUS 1 Al...

Page 371: ...DC SELECT more reliable a Press SENSOR softkey then select the ADC that provided the most reliable altitude indication Airspeed Miscompare IAS MISCOMP Caution For dual ADC installations airspeed diffe...

Page 372: ...IT MISCOMP Caution For dual AHRS installations pitch difference is greater than 5 between AHRS 1 and AHRS 2 Flight Director Autopilot and ESP if installed will not be available when pitch miscompare e...

Page 373: ...Attitude Indicator 4 AHRS SELECT more reliable a Press SENSOR softkey then select the AHRS that provided the most reliable roll indication 5 UNRELIABLE AHRS CIRCUIT BREAKER PULL Pulling circuit breake...

Page 374: ...le NO ADC MODES Caution Autopilot air data modes are not available 1 Autopilot may only be engaged in pitch PIT mode No Autopilot Vertical Modes Available NO VERT MODES Caution Autopilot vertical mode...

Page 375: ...ading CORRECT AS REQUIRED Autopilot Hypoxia Detection System Optional ARE YOU ALERT Advisory No pilot activity has been detected over a prescribed interval of time interval decreases as altitude incre...

Page 376: ...will interrupt this process 1 If within 60 seconds of AUTO DESCENT Warning prior to descent a Actuate Integrated Avionics System softkey or knob to reset 2 If greater than 60 seconds of AUTO DESCENT W...

Page 377: ...lot engaged and airspeed has fallen below minimum threshold Recovery may be initiated in one of three ways 1 Power Lever INCREASE as required to correct underspeed condition or 1 Autopilot AP DISC Swi...

Page 378: ...TEST Press the AP DISC button down and hold while commanding trim Trim should not operate either nose up or nose down 2 Autopilot ENGAGE press AP button 3 Autopilot Override TEST Move flight controls...

Page 379: ...f the AP Disconnect button ESP will be restored 1 AP Disconnect PRESS and HOLD until maneuver complete Section 5 Performance WARNING The Autopilot may not be able to maintain all selectable vertical s...

Page 380: ...With the Flight Director activated the pilot can hand fly the aircraft to follow the path shown by the command bars Flight Director operation takes place within the 1 Integrated Avionics Unit and prov...

Page 381: ...0 Automatic Flight Control System Schematic GFC 705 MODE CONTROLLER PITCH TRIM CARTRIDGE INTEGRATED AVIONICS UNIT 2 INTEGRATED AVIONICS UNIT 1 MFD PFD PITCH TRIM ADAPTER YAW SERVO optional ROLL SERVO...

Page 382: ...or localizer or back course approaches and glideslope coupling for GPS approaches This button is also used to couple to the GPS APR Approach Button The APR button selects the Approach mode This provid...

Page 383: ...value is displayed next to the active mode annunciation on the PFD Go Around and Glidescope modes are not controlled by the nose Pitch Wheel however use of the Pitch Wheel during Go Around mode will c...

Page 384: ...ontrols the selected heading bug on the HSI portion of the PFD It provides the reference for heading select mode Pushing the HDG knob synchronizes the selected heading to the current heading CRS Cours...

Page 385: ...M N O P Q R W S X T Y U Z V SPC BKSP 1 2 3 4 5 6 7 8 9 0 EMERG CRSR 1 2 PUSH FMS XPDR COM NAV IDENT DFLT MAP PUSH SYNC PUSH CTR PUSH SYNC D FPL CLR MENU PROC ENT FMS XPDR COM NAV Legend 1 Heading Sele...

Page 386: ...h Integrated Avionics Unit contains a GPS WAAS receiver VHF COM NAV GS receivers and system integration microprocessors The AFCS function within the Integrated Avionics Units control the active and ar...

Page 387: ...d if initially not engaged autopilot will remain not engaged After TO GA engagement other roll modes may be selected and Autopilot engagement is allowed However an attempt to modify the pitch attitude...

Page 388: ...rom the same page or is automatically re enabled at the next system power up Pitch and Roll Modes When the aircraft reaches the pitch and or roll engagement limit the system commands the servos to app...

Page 389: ...agement Limit 17 5 Maximum Stick Force attained at 22 5 Disengagement Threshold Zero Stick Force 12 5 Always Protected Only Protected after cross ing turn on threshold Bank Angle 0 30 45 60 75 90 15 W...

Page 390: ...nd roll modes but is instead triggered by airspeed and controlled by pitch attitude When the aircraft reaches the ESP engagement limit the system commands the pitch servo to apply a supplemental stick...

Page 391: ...A Engagement Limit Mach 0 419 Maximum Stick Force attained at Mach 0 430 Disengagement Threshold Zero Stick Force Mach 0 399 205 Indicated Airspeed KIAS 180 190 195 200 210 185 Nose Up Supplemental St...

Page 392: ...probable and minimized altitude loss is critical and Non Altitude Critical which generally correspond with activities that can afford exchange of altitude for airspeed without introducing terrain haz...

Page 393: ...nfluence only airspeed affects the AP FD in non altitude critical events The originally selected lateral mode remains active Upon reaching minimum airspeed the AFCS will abandon its Flight Director an...

Page 394: ...esponse to the Caution is detected the system annunciates an AUTO DESCENT Warning and continuous aural warning tone Lack of response after one minute of Warning annunciation is considered evidence of...

Page 395: ...sequent action may be required In combination with the CAS Window the system issues an audio alert when specific system conditions are meet and an expanded description of the condition is displayed in...

Page 396: ...30 of 30 P N 13772 135 Section 9 Cirrus Design Supplements SR22 SR22T Section 8 Handling Service Maintenance No Change Section 10 Safety Information No Change Revision 03 12 14 10...

Page 397: ...tem is installed on the aircraft this POH Supplement is applicable and must be inserted in the Supplements Section of the Pilot s Operating Handbook This document must be carried in the airplane at al...

Page 398: ...elity on which to solely base terrain or obstacle avoidance maneuvering decisions 2 To avoid getting unwanted alerts TAWS must be inhibited when landing at an airport that is not included in the airpo...

Page 399: ...ees 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 u...

Page 400: ...em Description The Terrain Awareness Warning System receives data from the GPS receiver to determine horizontal position and altitude and compares this information to the onboard terrain and obstacle...

Page 401: ...tion TAWS N A is generated in the annunciation window and on the TAWS Page The aural message TAWS NOT AVAILABLE is generated When the GPS signal is re established and the aircraft is within the databa...

Page 402: ...6 of 6 P N 13772 136 Section 9 Cirrus Design Supplements SR22 SR22T Revision 01 01 06 10 Intentionally Left Blank...

Page 403: ...event of a primary electrical generating source failure in accordance with 14 CFR Section 135 163 f When the aircraft is being operated under the provisions 14 CFR 135 this Supplement is applicable an...

Page 404: ...ations Kinds of Operation Equipment List Aircraft Serial Numbers 22 0002 thru 22 3416 before SB2X 33 03 Rev 1 or later LED Position Strobe Assembly Installation System Instrument and or Equipment Kind...

Page 405: ...required For 14 CFR 135 Operations the load shedding and equipment management in the following procedure will provide at least one hour operating time on aircraft with a fully charged 13 6 amp hour b...

Page 406: ...Light OFF WARNING Do not shed loads from Avionics Essential Essential or Essential 2 Bus row h Skywatch TAWS Circuit Breaker PULL i Weather Stmscpe Circuit Breaker PULL j MFD Circuit Breaker PULL 9 A...

Page 407: ...rical power to supply all requirements for emergency operation of equipment indefinitely as is required by 14 CFR 135 163 f 1 ALT 1 Master Switch OFF 2 Alternator 1 Circuit Breaker Check and Reset 3 A...

Page 408: ...Section 4 Normal Procedures No Change Section 5 Performance Data No Change Section 6 Weight and Balance No Change Section 7 Airplane and Systems Description No Change Section 8 Handling Service Mainte...

Page 409: ...1 This supplement is required for operation of Cirrus Design SR22T airplanes registered in South Africa and operating under the South African Civil Aviation Authority SACAA Requirements 2 The supplem...

Page 410: ...Placards Instrument Panel left ABOVE 17 500 VNE AND VNO MANEUVERING SPEED Vo 133 KIAS NORMAL CATEGORY AIRPLANE NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED REDUCE LINEARLY WITH ALTITUDE VNE VNO 17...

Page 411: ...dures No Change Section 4 Normal Procedures No Change Section 5 Performance Data No Change Section 6 Weight and Balance No Change Section 7 Airplane and Systems Description No Change Section 8 Handlin...

Page 412: ...4 of 4 P N 13772 146 Section 9 Cirrus Design Supplements SR22T Original Issue 11 16 2010 Intentionally Left Blank...

Page 413: ...plement is required for operation of Cirrus Design SR22 SR22T airplanes SR22 SR22T Airplanes Registered in Colombia and Operating Under the Republica De Colombia Aeronautica Civil Requirements 2 The s...

Page 414: ...FM and approved supplements are not applicable in Colombia 3 The aircraft must be equipped and operated in accordance with the applicable Colombia operating requirements 4 The use of GPS is not author...

Page 415: ...RIRSE AL POH PARA LOS LUBRICANTES APROBADOS ABOVE 40 F SAE 50 20W50 OR 20W60 BELOW 40 F SAE 30 10W30 15W50 OR 20W50 TIPO DEL ACEITE DE MOTOR POR DEBAJO DE 4 C 40 F SAE 30 10W30 15W50 O 20W50 POR ARRIB...

Page 416: ...CAIDAS ADENTRO ADVERTENCIA MANTENGA DISTANCIA CUANDO EL AVION ESTE OCUPADO STAY CLEAR WHEN AIRPLANE IS OCCUPIED ROCKET FOR PARACHUTE DEPLOYMENT INSIDE WARNING NO PUSH NO PRESIONAR RESCUE FRACTURE AND...

Page 417: ...CING FLUIDS LIQUIDO DESCONGELANTE REFERIRSE AL POH PARA LIQUIDOS DESCONGELANTES APROBADOS EXTERNAL POWER 28 V DC 28 V DC EXTERNA POTENCIA CO_SR22_FM09_3417 PRESIONAR PARA ABRIR PUSH TO OPEN OPEN ABRIR...

Page 418: ...2 AMMETER SELECT BATT EM_SR22_FM02_3184 EMERG ENCY EXIT REMOVE EGRESS HAMMER FROM ARMREST LID STRIKE CORN ER OF WINDOW KICK OR PUSH OUT AFTER FRACTURING 4 FU EL SELE CTOR H AN DLE OFF 6 R ES TR A IN T...

Page 419: ...UCTURAL CIRRUS PROCEDIMIENTO DE ACTIVACION CON AMBAS MANOS Y MAXIMA FUERZA 2 ESTA CUBIERTA REMOVER 3 PALANCA DE ACTIVACION TIRE HACIA ABAJO EN FORMA PAREJA 4 SELECTORA DE TANQUE OFF 5 MASTER SWITCH OF...

Page 420: ...CAPACIDAD MAXIMA DE CADA CORREA DE EQUIPAJE 15 KG 35 LBS VER POH PARA AMARRE E INFORMACION DE PESO Y BALANCE EMERGENCY EXIT WINDOW KICK OR PUSH OUT AFTER FRACTURING REMOVE EGRESS HAMMER FROM WITHIN CE...

Page 421: ...hange Section 5 Performance Data No Change Section 6 Weight and Balance No Change Section 7 Airplane and Systems Description No Change Section 8 Handling Service Maintenance No Change Section 9 Supple...

Page 422: ...10 of 10 P N 13772 147 Section 9 Cirrus Design Supplements SR22 SR22T Original Issue Dec 07 2010 Intentionally Left Blank...

Page 423: ...1 This supplement is required for operation of Cirrus Design SR22 SR22T Airplanes Registered in Chile and Operating Under the Direcci n General de Aeron utica Civil de Chile DGAC Requirements 2 The s...

Page 424: ...basic AFM and approved supplements are not applicable in Chile 3 The aircraft must be equipped and operated in accordance with the applicable Chilean operating requirements 4 The use of GPS is not aut...

Page 425: ...REFERIRSE AL POH PARA LOS LUBRICANTES APROBADOS ABOVE 40 F SAE 50 20W50 OR 20W60 BELOW 40 F SAE 30 10W30 15W50 OR 20W50 TIPO DEL ACEITE DE MOTOR INFERIOR DE 4 C 40 F SAE 30 10W30 15W50 O 20W50 SUPERIO...

Page 426: ...CAIDAS ADENTRO ADVERTENCIA MANTENGASE ALEJADO CUANDO EL AVION ESTE OCUPADO STAY CLEAR WHEN AIRPLANE IS OCCUPIED ROCKET FOR PARACHUTE DEPLOYMENT INSIDE WARNING NO PUSH NO PRESIONAR RESCUE FRACTURE AND...

Page 427: ...CING FLUIDS LIQUIDO DESCONGELANTE REFERIRSE AL POH PARA LIQUIDOS DESCONGELANTES APROBADOS EXTERNAL POWER 28 V DC 28 V DC EXTERNA POTENCIA CL_SR22_FM09_3539 PRESIONAR PARA ABRIR PUSH TO OPEN OPEN ABRIR...

Page 428: ...2 AMMETER SELECT BATT CL_SR22_FM09_3542 EMERG ENCY EXIT REMOVE EGRESS HAMMER FROM ARMREST LID STRIKE CORN ER OF WINDOW KICK OR PUSH OUT AFTER FRACTURING 4 FU EL SELE CTOR H AN DLE OFF 6 R ES TR A IN T...

Page 429: ...CTURAL CIRRUS PROCEDIMIENTO DE ACTIVACION CON AMBAS MANOS Y MAXIMA FUERZA 2 ESTA CUBIERTA REMOVER 3 PALANCA DE ACTIVACION TIRE HACIA ABAJO EN FORMA PAREJA 4 SELECTORA DE ESTANQUE OFF 5 MASTER SWITCH O...

Page 430: ...S CAPACIDAD MAXIMA DE CADA CORREA DE EQUIPAJE 15 KG 35 LBS VER POH PARA AMARRE E INFORMACION DE PESO Y BALANCE EMERGENCY EXIT WINDOW KICK OR PUSH OUT AFTER FRACTURING REMOVE EGRESS HAMMER FROM WITHIN...

Page 431: ...AO Annex 16 Volume I are Section 5 Performance Data No Change Section 6 Weight and Balance No Change Section 7 Airplane and Systems Description No Change Section 8 Handling Service Maintenance No Chan...

Page 432: ...10 of 10 P N 13772 148 Section 9 Cirrus Design Supplements SR22 SR22T Original Issue Oct 04 2012 Intentionally Left Blank...

Page 433: ...This supplement is required for operation of Cirrus Design SR22 SR22T airplanes Registered in Mexico and Operating Under the Direccion General de Aeronautica Civil DGAC Requirements 2 The supplement...

Page 434: ...in the basic AFM and approved supplements are not applicable in Mexico 3 The aircraft must be equipped and operated in accordance with the applicable Mexico operating requirements 4 The use of GPS is...

Page 435: ...40 F SAE 50 OR 20W50 BELOW 40 F SAE 30 10W30 15W50 OR 20W50 CALIDADES DE ACEITE PARA MOTOR DEBAJO 40 F 4 C SAE 30 10W30 15W50 O 20W50 SOBRE 40 F 4 C SAE 50 O 20W50 REFER TO AFM FOR APPROVED OILS ENGIN...

Page 436: ...ON ESTE OCUPADO STAY CLEAR WHEN AIRPLANE IS OCCUPIED ROCKET FOR PARACHUTE DEPLOYMENT INSIDE WARNING RESCUE FRACTURE AND REMOVE WINDOW RESCATE FRACTURAR Y REMOVER VENTANA NO PUSH NO EMPUJE CLOSE CERRAR...

Page 437: ...O 4 0 GALONES US 1 5 LITROS CAPACIDAD TOTAL UTILIZABLE USAR SOLAMENTE FLUIDO AL 5 DTD 406B DE ICING FLUID REFER TO AFM FOR APPROVED DE ICING FLUIDS LIQUIDO DESCONGELANTE REFIERASE AL MVA PARA LIQUIDOS...

Page 438: ...Cirrus Design Supplements SR22 SR22T Figure 1 GRABHERE EM_SR22_FM09_3547 EMERGENCY EXIT REMOVE EGRESS HAMMER FROM ARMREST LID STRIKE CORNER OF WINDOW KICK OR PUSH OUT AFTER FRACTURING Interior Placard...

Page 439: ...rrus Design Section 9 SR22 SR22T Supplements EM_SR22_FM09_3548 EXTINTOR BAJO EL FRENTE DEL ASIENTO DE PILOTO AGARRAR AQU PROHIBIDO FUMAR AJUSTE CINTURON DE SEGURIDAD Figure 1 Interior Placards Origina...

Page 440: ...ERA CENTRAL GOLPEE LA VENTANA EN LA ESQUINA PATEE O EMPUJE FUERA DESPUES DE FRACTURAR LIMITE DE PESO DISTRIBUIDO EN PISO 130 LBS 60 KG CAPACIDAD DE CORREA DEL EQUIPAJE 35 LBS 15 KG MAX CADA UNA VEA MA...

Page 441: ...e Section 5 Performance Data No Change Section 6 Weight and Balance No Change Section 7 Airplane and Systems Description No Change Section 8 Handling Service Maintenance No Change Section 9 Supplement...

Page 442: ...10 of 10 P N 13772 149 Section 9 Cirrus Design Supplements SR22 SR22T Original Issue January 14 2013 Intentionally Left Blank...

Page 443: ...lon usable capacity 4 0 gallon tank in each wing When the TKS Anti Ice System is installed on the aircraft this POH Supplement is applicable and must be inserted in the Supplements Section of the Pilo...

Page 444: ...nown icing conditions are defined by FAR Part 25 Appendix C These conditions do not include nor were tests conducted in all icing conditions that may be encountered such as freezing rain freezing driz...

Page 445: ...lity to evaluate and understand weather along the intended route and identify any potential weather hazards thru evaluation of but not limited to Current Observations Pilot Reports Area Forecasts AIRM...

Page 446: ...al System Instrument and or Equipment Kinds of Operation IFR Day IFR Nt Placards and Markings Airplane Flight Manual Supplement 1 1 Ice and Rain Protection Windshield Spray Nozzles 1 1 Wing LH and RH...

Page 447: ...Dispatch Fluid Quantity NORM 90 Minutes HIGH 45 Minutes MAX 22 5 Minutes Deicing Fluid Limits Usable Tank Capacity 8 gal 30L Tank Capacity 8 5 gal 32L Maximum Operating Time Continuous operation of t...

Page 448: ...g Flaps are limited to a maximum deflection of 50 when the aircraft has encountered icing conditions and or has accumulated ice on the airframe When holding in icing conditions the flaps must be UP 0...

Page 449: ...Upper wing above anti ice fluid filler cap SR22_FM09_2964 THIS AIRCRAFT IS CERTIFIED FOR THE FOLLOWING FLIGHT OPERATIONS DAY NIGHT VFR IFR FLIGHT INTO KNOWN ICING WITH REQUIRED EQUIPMENT OPERATE PER...

Page 450: ...frame vibrations Note Significant loss in cruise or climb performance may be an indication of propeller ice accretions that are not visible to the naked eye Operation of the engine at 2500 RPM will he...

Page 451: ...95 KIAS or higher to stay above pre stall buffet If unable to maintain this airspeed allow altitude to decrease in order to maintain 95 KIAS 8 Minimum Approach Speed w Residual Ice Flaps 50 88KIAS In...

Page 452: ...AS at 3600 lb Maximum Glide Ratio 6 4 1 Conditions Example Power OFF Altitude 10 000 ft AGL Propeller Windmilling Airspeed 92 KIAS Flaps 0 UP Glide Distance 10 5 NM Wind Zero GROUND DISTANCE NAUTICAL...

Page 453: ...t Transducer Malfunction Airframe buffet before the stall is a good indication of an impending stall The stall warning horn typically activates prematurely if there is ice accumulated on the lift tran...

Page 454: ...ow Fluid Quantity Caution and Warning PFD Alerts Window Fluid quantity is low TKS ANTI ICE QTY Warning Fluid quantity is less than 0 5 gallon 1 9 L ANTI ICE QTY Caution Fluid quantity is less than 1 0...

Page 455: ...itot Heat on hot days may annunciate the AOA OVERHEAT Warning when flying at slow speeds When air temperatures are greater than 41 F 5 C operation of Pitot Heat is at discretion of the pilot If overhe...

Page 456: ...eased caution because the tail section s smaller leading edge radius will typically collect ice more quickly and ice accretion is more difficult to monitor 1 ICE PROTECT A and B Circuit Breakers SET 2...

Page 457: ...95 KIAS ANTI ICE SPD High Airspeed is greater than 177 KIAS or 204 KTAS 1 Airspeed MAINTAIN 95 177 KIAS or less than 204 KTAS Lift Transducer Heater Failure Caution PFD Alerts Window Stall warning AoA...

Page 458: ...level quantity 1 Fluid Quantity SWITCH TO FULLEST TANK b WIND SHLD Push Button PRESS 1 Repeat operation of windshield pump to verify metering pumps are primed properly as evidenced by deicing fluid e...

Page 459: ...l the fluid level quantity If ANTI ICE FLO or ANTI ICE PSI annunciates a Fluid Quantity SWITCH TO OPPOSITE TANK b WIND SHLD Push Button PRESS 1 Repeat operation of windshield pump to verify metering p...

Page 460: ...ITOT HEAT to 45 seconds Operation of Lift Transducer Heat in excess of 45 seconds while on the ground may cause excessive temperature on the lift transducer faceplate and surrounding wing skin Note Th...

Page 461: ...itch ON e Cabin Speaker ON f Cabin Doors CLOSE g WIND SHLD Push Button PRESS 1 Verify evidence of deicing fluid from spray nozzles h PUMP BKUP Switch ON 1 Metering Pump Duty Cycle Verify Continuously...

Page 462: ...r Faceplate and Vane may be HOT c Lift Transducer Faceplate PERCEPTIBLY HOT d Lift Transducer Vane VERY HOT 1 Verify Stall Warning audio alert after lifting stall vane with wooden tooth pick or tongue...

Page 463: ...ce Formation Determination Typically a leading edge with a small radius will collect ice more quickly than a leading edges with a large radius To help monitor possible ice accumulation a thin metal ta...

Page 464: ...advertent Icing Encounter OR Icing Conditions Exist 1 PITOT HEAT Switch Verify ON 2 ICE PROTECT System Switch ON 3 ICE PROTECT Mode Switch NORM 4 WIND SHLD Push Button PRESS AS REQUIRED 5 Monitor ice...

Page 465: ...indshield Defrost ON 5 Fluid Quantity and Endurance MONITOR a Ensure adequate quantity to complete flight After Leaving Icing Conditions 1 Anti Ice System OFF 2 Airspeed as flight CONDITIONS DICTATE 3...

Page 466: ...autopilot with ice accretions on the airplane the pilot should be alert for out of trim forces Approach and Landing If Icing Conditions Exist 1 ICE PROTECT System Switch ON 2 ICE PROTECT Mode Switch...

Page 467: ...F 3 PUMP BKUP Switch OFF 4 Ice Inspection Lights OFF Note When the Anti Ice System has been used avoid touching the airframe structure or windshield as they will be partially covered with deicing flui...

Page 468: ...on the unprotected areas of the airplane can cause noticeable performance losses and stall speed increases even with the Anti Ice System operating Stall Speeds with Ice Accumulation Note Altitude loss...

Page 469: ...use coldest data shown Conditions Power Full Throttle Mixture Full Rich Green Arc Flaps 0 UP Airspeed Best Rate of Climb Negative climb data shown in heavier table borders Weight LB Press Altitude FT...

Page 470: ...978 889 805 765 585 2000 103 895 811 732 694 487 4000 103 817 738 663 626 393 6000 102 743 668 597 563 302 8000 102 674 603 536 503 777 10000 102 609 542 478 447 743 12000 102 548 484 424 395 710 1400...

Page 471: ...a shown Conditions Power Full Throttle Mixture Full Rich Green Arc Flaps 0 UP Airspeed Best Rate of Climb Negative climb data shown in heavier table borders Weight LB Press Altitude FT Climb Speed KIA...

Page 472: ...86 2000 103 1477 1368 1260 1206 837 4000 103 1399 1290 1182 1129 688 6000 102 1321 1213 1105 1052 540 8000 102 1244 1136 1029 976 1484 10000 102 1167 1059 953 900 1462 12000 102 1090 983 877 825 1440...

Page 473: ...OAT ISA C Climb Speed KIAS TIME FUEL DISTANCE From Sea Level Time Minutes Fuel U S Gal Distance NM S L 15 103 0 0 0 0 0 0 1000 13 103 1 2 0 7 2 1 2000 11 103 2 4 1 4 4 2 3000 9 103 3 6 2 2 6 4 4000 7...

Page 474: ...ot Cruise data not shown for power settings resulting in airspeeds with inadequate stall margins Conditions Weight 3400 LB Winds Zero CRUISE PERFORMANCE ISA 30 C ISA ISA 30 C Altitude ft MSL Power of...

Page 475: ...5 16 4 150 9 1 151 9 2 65 14 6 131 9 0 131 9 0 18000 85 18 3 167 9 1 169 9 2 75 16 4 151 9 2 151 9 2 65 14 6 131 9 0 20000 85 18 3 168 9 2 170 9 3 80 17 4 160 9 2 161 9 3 75 16 4 151 9 2 151 9 2 65 14...

Page 476: ...n Aircraft with optional Enhanced Vision System range is decreased by Conditions Mixture Best Economy Target Fuel Flow or less Weight 3600 LB for Climb Avg 3400 LB for Cruise Winds Zero Total Fuel 92...

Page 477: ...66 1 142 16 4 4 0 617 8 7 18000 15 5 64 1 142 16 4 3 9 605 8 6 20000 17 6 61 9 142 16 4 3 8 593 8 6 22000 20 0 59 5 141 16 4 3 6 579 8 6 Range Endurance 65 Power Cruise Full Power Climb Press Alt FT C...

Page 478: ...Conditions Power Full Throttle Mixture Set per Placard Flaps 50 DN Climb Airspeed VREF Weight LB Press Alt FT Climb Speed VREF KIAS CLIMB GRADIENT Feet Nautical Mile Temperature C 20 10 0 5 ISA 3600...

Page 479: ...wer Full Throttle Mixture Set per Placard Flaps 50 Climb Airspeed VREF Weight LB Press Alt FT Climb Speed VREF KIAS RATE OF CLIMB Feet per Minute Temperature C 20 10 0 5 ISA 3600 SL 88 1104 1028 953 9...

Page 480: ...for runway slope are required to be included herein for certification They should be used with caution since published runway slope data is usually the net slope from one end of the runway to the othe...

Page 481: ...1409 1463 1489 Total 2833 2908 2984 3022 1000 Grnd Roll 1406 1461 1517 1544 Total 2903 2981 3061 3101 2000 Grnd Roll 1458 1516 1573 1602 Total 2977 3059 3143 3185 3000 Grnd Roll 1513 1572 1632 1662 To...

Page 482: ...9 35 9 5 31 7 1 65 3 9 67 0 8 7 4 1 09 4 0 36 8 5 45 7 2 66 2 9 80 0 9 8 3 1 23 4 1 37 7 5 58 7 3 67 2 9 94 1 0 9 2 1 36 4 2 38 6 5 72 7 4 68 1 10 08 1 1 10 1 1 50 4 3 39 6 5 85 7 5 69 0 10 21 1 2 11...

Page 483: ...and 5 amp ICE PROTECT B circuit breaker on Essential Bus 2 Storage and Distribution Two separate and symmetrical 4 25 gallon 16 1L deicing fluid tanks are serviced through filler caps located on the...

Page 484: ...umps From the metering pumps deicing fluid is pushed through a filter assembly mounted adjacent to the pumps and then carried through nylon tubing to the proportioning units located in the cabin floor...

Page 485: ...passenger seat supplies fluid to the windshield nozzles The pump also acts as a priming pump for the main metering pumps In the event the metering pumps cannot prime themselves the windshield pump may...

Page 486: ...RH Drain Valve 18 RH Tank Strainer 19 In Line Strainer 20 Flow Transducer 21 Pump Control Unit 22 Metering Pump 1 23 Metering Pump 2 24 High Pressure Switch 25 Low Pressure Switches 26 RH H Stab Panel...

Page 487: ...econds on 90 seconds off HIGH controls 1 pump to operate continuously to provide 200 flow rate i e two times the normal flow rate MAX controls both pumps to operate continuously for 2 minutes to provi...

Page 488: ...ins the tank selection mode that was current when reversionary mode was activated Manual tank selection mode is selected by pressing the ANTI ICE softkey to access control of the LEFT and RIGHT tanks...

Page 489: ...6 3 8 5 7 8 1 5 NORM HIGH Mode Switch 6 MAX Mode Push Button 7 Pump Backup Switch 8 Wind Shield Push Button SR22_FM09_2983 Bolster Panel 2 3 4 6 ENGINE ANTI ICE DCLTR ASSIST FUEL Anti Ice TKS Time Re...

Page 490: ...uring ground operations a signal from the avionics is used to operate the heaters at 25 power during ground operation or 100 power while in the air The lift transducer heat is powered by 28 VDC suppli...

Page 491: ...d horizontal stabilizer Components of the system include the LED light assemblies and a two position toggle switch labeled ICE on the Exterior Lights section of the bolster switch panel The ice inspec...

Page 492: ...e Use only soap and water isopropyl alcohol or ethyl alcohol to clean panels Do not wax leading edge porous panels Storage To prepare the Anti Ice System for flyable storage fill the deicing fluid tan...

Page 493: ...it may require several cycles of the windshield priming pump to prime the metering pumps In the event that the metering pumps cannot prime themselves the windshield priming pump may be cycled 3s ON 3s...

Page 494: ...52 of 52 P N 13772 151 Section 9 Cirrus Design Supplements SR22T Original Issue 02 01 13 Intentionally Left Blank...

Page 495: ...tion 3 Cirrus Airframe Parachute System CAPS 4 Deployment Scenarios 4 General Deployment Information 7 Landing Considerations 8 Taxiing Steering and Braking Practices 11 Operating Practices 11 Brake M...

Page 496: ...10 2 P N 13772 005 Section 10 Cirrus Design Safety Information SR22T Original Issue Intentionally Left Blank...

Page 497: ...Handbook the Handbook Supplements Flight Checklist and operational guides and data provided by manufacturers of equipment installed in this airplane You must operate the airplane in accordance with t...

Page 498: ...owing discussion is intended to be informative not directive It is the responsibility of you the pilot to determine when and how the CAPS will be used It is important to understand however that numero...

Page 499: ...ould the pilot attempt recovery from a spin other than by CAPS activation Landing Required in Terrain not Permitting a Safe Landing If a forced landing on an unprepared surface is required CAPS activa...

Page 500: ...ion SR22T activation by the passengers is highly recommended This scenario should be discussed with passengers prior to flight and all appropriate passengers should be briefed on CAPS operation so the...

Page 501: ...a data point altitude loss from level flight deployments has been demonstrated at less than 400 feet Deployment at such a low altitude leaves little or no time for the aircraft to stabilize under the...

Page 502: ...nding 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 th...

Page 503: ...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 t...

Page 504: ...re 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 occ...

Page 505: ...ion occurs the pilot should stop the aircraft and allow the brakes to cool to avoid damaging the brake system Operating Practices When taxiing directional control is accomplished with rudder deflectio...

Page 506: ...iing may result in excessive demands on the brakes increased brake wear and the possibility of brake failure or fire Brakes have a large energy absorbing capacity therefore cooling time should be cons...

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