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Cirrus Design

Section 7

SR22T

Systems Description

P/N 13772-005

7-51

P/N 13772-005

7-51

Main Distribution Bus 1 or Main Distribution Bus 2 in the MCU. In the
case of both alternators failing, BAT 1 is connected directly to the
Essential Distribution Bus in the MCU and will power ESS BUS 1 and
ESS BUS 2. In the event of both alternators and BAT 1 failing, BAT 2 is
connected directly to ESS BUS 1.

Main Buses

The circuit breaker panel MAIN BUS 1 and MAIN BUS 2 are powered
by ALT 2 from the MCU Main Distribution Bus 2 and - in the event of
ALT 2 failure - by ALT 1 and BAT 1 from the Main Distribution Bus 2 via
the diode interconnecting the MCU distribution buses through 30-amp
fuses inside the MCU.
The 10-amp AVIONICS circuit breaker on MAIN BUS 1, controlled
through the AVIONICS master switch on the bolster switch panel,
powers all loads on the AVIONICS BUS.
The circuit breaker panel 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 powering MAIN BUS 3 by the isolation diode
interconnecting the MCU distribution buses 1 and 2.

Non-Essential Buses

The circuit breaker panel NON ESS BUS is powered by ALT 2 from the
MCU Main Distribution Bus 2 and - in the event of ALT 2 failure - by
ALT  1  and  BAT  1  from  the  Main  Distribution  Bus  2  via  the  diode
interconnecting  the  MCU  distribution  buses  through  30-amp  fuses
inside the MCU. The Avionics Non-Essential Bus is powered through
the  10-amp  AVIONICS  circuit  breaker  on  MAIN  BUS  1  and  is
discussed above.
The circuit breaker panel A/C BUS 1 and A/C BUS 2, 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 A/C BUS 1 and A/C BUS 2. ALT 2 is prevented from powering
A/C BUS 1 and A/C BUS 2 by the isolation diode interconnecting the
MCU distribution buses 1 and 2.

Original Issue

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Содержание SR22T

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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 __...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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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