Cirrus SR22 Pilot Operating Handbook

Cirrus SR22 Pilot Operating Handbook

Aircraft serials 22-3915 & subsequent 3600 pound takeoff weight
Table of Contents

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PILOT'S OPERATING HANDBOOK
AND EASA APPROVED
AIRPLANE FLIGHT MANUAL
for the
CIRRUS SR22
Airplanes Registered in Europe
A i r c r a f t S e r i a l s 2 2 - 3 9 1 5 & S u b s e q u e n t
3 6 0 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 flight
operations.
THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO
THE PILOT BY FAR PART 23 AND ADDITIONAL INFORMATION PROVIDED BY
CIRRUS DESIGN AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT
MANUAL.
The EASA approved Airplane Flight Manual consists of the FAA approved Airplane
Flight Manual, associated POH Supplements, and this Title Page.
______________
Model - Serial Num. SR22 _____________ Registration Num.
P/N 13772-004E
Original Issue: May 15, 2013

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Summary of Contents for Cirrus SR22

  • Page 1 THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY FAR PART 23 AND ADDITIONAL INFORMATION PROVIDED BY CIRRUS DESIGN AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL. The EASA approved Airplane Flight Manual consists of the FAA approved Airplane Flight Manual, associated POH Supplements, and this Title Page.
  • Page 2 Copyright © 2013 - All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811...
  • Page 3 Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages Use this page to determine the current effective date for each page in the POH. Supplements are issued individually and are controlled by the Log of Supplements Page in Section 9.
  • Page 4: Table Of Contents

    Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status Original Issue 5-29 Revision 1 7-42 Revision 1 Original Issue 5-30 Revision 1 7-43 Revision 1 Original Issue 5-31...
  • Page 5 Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 7-97 Revision 1 10-10 Original Issue 7-98 Revision 1 10-11 Original Issue 7-99 Revision 1 10-12 Revision 1 7-100...
  • Page 6: Original Issue

    Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status Intentionally Left Blank P/N 13772-004E Original Issue...
  • Page 7: Revision

    SR22 Foreword Foreword This Pilot’s Operating Handbook (POH) has been prepared by Cirrus Design Corporation to familiarize operators with the aircraft. Read this POH carefully. It provides operational procedures that will assure the operator obtains the performance published in the manual, data designed to allow the most efficient use of the airplane, and basic information for maintaining the airplane in a “like new”...
  • Page 8 Front Matter Cirrus Design Foreword SR22 The Pilot’s Operating Handbook This Pilot’s Operating Handbook has been prepared using GAMA Specification #1 for Pilot’s Operating Handbook, Revision 2, dated 18 October 1996 as the content model and format guide. However, some deviations from this specification were made for clarity.
  • Page 9: Original Issue

    Original issue pages will be identified by the words “Original Issue” at this location. In the event that the majority of pages in the POH are revised, Cirrus may determine that it is more effective to reissue the POH. Reissued pages will be identified by the word “Reissue”...
  • Page 10 Design Supplements produced for this airplane. The “Log of Supplements” page can be utilized as a “Table of Contents” for Section 9. If the airplane is modified at a non Cirrus Design facility through an STC or other approval method, it is the owner’s responsibility to ensure that the proper supplement, if applicable, is installed in the POH and that the supplement is properly recorded on the “Log of...
  • Page 11 Cirrus Design Front Matter SR22 Foreword In the event a new POH is purchased, the owner must ensure that all information applicable to the airplane is transferred to the new POH and the aircraft records are current. Warnings, Cautions, and Notes...
  • Page 12: Original Issue

    Front Matter Cirrus Design Foreword SR22 Intentionally Left Blank Front Matter-6 P/N 13772-004 Original Issue...
  • Page 13: Original Issue

    Cirrus Design Section 1 SR22 General Section 1: General Table of Contents Introduction ..................3 The Airplane..................7 Engine..................... 7 Propeller ..................7 Fuel....................8 Oil ....................8 Maximum Certificated Weights ............8 Cabin and Entry Dimensions ............8 Baggage Spaces and Entry Dimensions ........8 Specific Loadings................
  • Page 14: Original Issue

    Section 1 Cirrus Design General SR22 Intentionally Left Blank P/N 13772-004 Original Issue...
  • Page 15: Introduction

    Cirrus Design Section 1 SR22 General Introduction This section contains information of general interest to pilots and owners. You will find the information useful in acquainting yourself with the airplane, as well as in loading, fueling, sheltering, and handling the airplane during ground operations.
  • Page 16: Original Issue

    Section 1 Cirrus Design General SR22 26.0 ft 7.92 m 8.9 ft 2.71 m 9 inches (minimum) 23 cm (minimum) NOTE: • Wing span includes position and strobe lights. • Prop ground clearance - 9" inches (23 cm). • Wing Area = 144.9 sq. ft.
  • Page 17 Cirrus Design Section 1 SR22 General 49.3" 39.8" Fuselage Station 49.7" 38.5" 27.0" 16.0" 20.0" 10.5" 32.0" 39.0" 33.4" 20.0" 33.3" 5.0" 21.0" CABIN DOOR BAGGAGE DOOR OPENING OPENING SR22_FM01_1019A Location Length Width Height Volume 122” 49.3” 49.7 137 cu ft Cabin 36”...
  • Page 18 Section 1 Cirrus Design General SR22 GROUND TURNING CLEARANCE 24.3 ft. (7.41 m) RADIUS FOR WING TIP 7.0 ft. (2.16 m) RADIUS FOR NOSE GEAR 0.5 ft. (0.15 m) RADIUS FOR INSIDE GEAR 9.1 ft. (2.77 m) RADIUS FOR OUTSIDE GEAR TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER.
  • Page 19: The Airplane

    Cirrus Design Section 1 SR22 General The Airplane Engine Number of Engines................1 Number of Cylinders................6 Engine Manufacturer ..........Teledyne Continental Engine Model ................. IO-550-N Fuel Metering ..............Fuel Injected Engine Cooling ..............Air Cooled Engine Type ........Horizontally Opposed, Direct Drive Horsepower Rating..........
  • Page 20: Fuel

    Section 1 Cirrus Design General SR22 Fuel Total Capacity ..........94.5 U.S. Gallons (358.0 L) Total Usable..........92.0 U.S. Gallons (348.0 L) Approved Fuel Grades: 100 LL Grade Aviation Fuel (Blue) 100 (Formerly 100/130) Grade Aviation Fuel (Green) Oil Capacity (Sump) ..........8 U.S. Quarts (7.6 L) Oil Grades: All Temperatures ......
  • Page 21: Symbols, Abbreviations And Terminology

    Cirrus Design Section 1 SR22 General Symbols, Abbreviations and Terminology General Airspeed Terminology and Symbols KCAS Knots Calibrated Airspeed is the indicated airspeed corrected position instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level.
  • Page 22: Meteorological Terminology

    Section 1 Cirrus Design General SR22 Stalling Speed is minimum steady flight speed at which the aircraft is controllable with 50% flaps. Stalling Speed is the minimum steady flight speed at which the aircraft is controllable in the landing configuration (100% flaps) at the most unfavorable weight and balance.
  • Page 23: Engine Power Terminology

    Cirrus Design Section 1 SR22 General Outside Air Temperature is the free air static temperature obtained from inflight temperature indications or from ground meteorological sources. It is expressed in either degrees Celsius or degrees Fahrenheit. Pressure Pressure Altitude is the altitude read from the...
  • Page 24: Weight And Balance Terminology

    Section 1 Cirrus Design General SR22 Demonstrated Demonstrated Crosswind Velocity is the velocity of Crosswind the crosswind component for which adequate Velocity control of the airplane during taxi, takeoff, and landing actually demonstrated during certification testing. Demonstrated crosswind is not considered to be limiting.
  • Page 25 Cirrus Design Section 1 SR22 General Basic Empty Basic Empty Weight is the actual weight of the Weight airplane including all operating equipment that has a fixed location in the airplane. The basic empty weight includes the weight of unusable fuel and full oil.
  • Page 26 Section 1 Cirrus Design General SR22 Intentionally Left Blank 1-14 P/N 13772-004 Original Issue...
  • Page 27 Maximum Occupancy ..............18 Refer to Section 7, Seats for additional information......18 Systems and Equipment Limits............19 Cirrus Perspective Integrated Avionics System ......19 L-3 Skywatch Traffic Advisory System ......... 22 L-3 Stormscope Weather Information System ......22 Max Viz Enhanced Vision System (Optional) ....... 23 MD302 Standby Attitude Module (Optional) .........
  • Page 28 Section 2 Cirrus Design Limitations SR22 Cirrus Airframe Parachute System (CAPS) ........24 Other Limitations ................24 Smoking ..................24 Placards ................... 25 P/N 13772-004 Revision 1...
  • Page 29: Introduction

    Cirrus Design Section 2 SR22 Limitations Introduction The limitations included in this Section of the Pilot’s Operating Handbook (POH) approved Federal Aviation Administration. This section provides operating limitations, instrument markings and basic placards required by regulation and necessary for the safe operation of the aircraft and its standard systems and equipment.
  • Page 30: Airspeed Limitations

    Section 2 Cirrus Design Limitations SR22 Airspeed Limitations The indicated airspeeds in the following table are based on Section 5, Airspeed Calibration - Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
  • Page 31: Airspeed Indicator Markings

    Cirrus Design Section 2 SR22 Limitations Airspeed Indicator Markings The airspeed indicator markings are based on Section 5, Airspeed Calibration - Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
  • Page 32: Powerplant Limitations

    Section 2 Cirrus Design Limitations SR22 Powerplant Limitations Engine Teledyne Continental .............. IO-550-N Power Rating ............310 hp @ 2700 RPM Maximum RPM ..............2700 RPM Oil Temperature ........... 240 °F (116 °C) maximum Minimum Oil Temperature for Takeoff....... 75 °F (24 °C) Oil Pressure: Minimum ................
  • Page 33: Propeller

    Cirrus Design Section 2 SR22 Limitations Propeller Hartzell Propeller Type ........Constant Speed, Three Blade Model Number..........PHC-J3YF-1RF/F7694(B) Diameter.............78.0” (76.0” Minimum) Model Number......... PHC-J3YF-1RF/F7693DF(B) Diameter.............78.0" (76.0" Minimum) McCauley Propeller Type ........Constant Speed, Three Blade Model Number............ D3A34C443/78CYA-0 Diameter.............78.0" (76.0" Minimum) MT Propeller Propeller Type ........
  • Page 34: Engine Instrument Markings & Annunciations

    Section 2 Cirrus Design Limitations SR22 Engine Instrument Markings & Annunciations The following describes the engine instrument markings. Associated Warning and Caution Annunciations are shown in capitalized text. PowerPlant Yellow Green Arc/ Yellow Arc/ Arc/Bar Arc/Bar Arc/Bar Instrument (Range & Units)
  • Page 35: Fuel

    Cirrus Design Section 2 SR22 Limitations Fuel Yellow Green Yellow Arc/Bar Arc/Bar Arc/Bar Arc/Bar Arc/Bar Instrument Minimum Maximum (Range & Units) Caution Normal Caution Minimum Range Range Range Maximum –– –– –– –– Fuel Flow 0 – 25 (0 – 30 U.S. Gal/Hr) Fuel Totalizer N <...
  • Page 36: Center Of Gravity Limits

    Section 2 Cirrus Design Limitations SR22 Center of Gravity Limits Reference Datum ........100 inches forward of firewall Forward ..............Refer to Figure 2-1 Aft ................Refer to Figure 2-1 3600 21.1% MAC 31.5% MAC FS 143.2 FS 148.2 3600 lb 3600 lb...
  • Page 37: Maneuver Limits

    60°. • Note • Because the aircraft has not been certified for spin recovery, the Cirrus Airframe Parachute System (CAPS) must be deployed if the airplane departs controlled flight. Refer to Section 3, Inadvertent Spin Entry.
  • Page 38: Kinds Of Operation

    Section 2 Cirrus Design Limitations SR22 Kinds of Operation The aircraft is equipped and approved for the following type operations: • VFR day and night. • IFR day and night. Kinds of Operation Equipment List The following listing summarizes the equipment required under Federal Aviation Regulations (FAR) Part 23 for airworthiness under the listed kind of operation.
  • Page 39 Cirrus Design Section 2 SR22 Limitations Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions Low Volts Annunciator ALT 1 Annunciator ALT 2 Annunciator — — Circuit Breakers As required. Equipment & Furnishings Emergency Locator Trans-...
  • Page 40 Section 2 Cirrus Design Limitations SR22 Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions Ice & Rain Protection Alternate Engine Air Induc- tion System Alternate Static Air Source Pitot Heater — — Landing Gear Wheel Pants —...
  • Page 41 Cirrus Design Section 2 SR22 Limitations Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions Navigation & Pitot Static Airspeed Indicator Altimeter Magnetic Compass Pitot System Static System, Normal Attitude Indicator — — Clock — —...
  • Page 42: Icing

    Oil Pressure Indication Oil Quantity Indicator (Dip- stick) Oil Temperature Indication Engine Speed Special Equipment Cirrus Airframe Parachute (CAPS) Icing Flight into known icing conditions is prohibited. Runway Surface This airplane may be operated on any smooth runway surface. Taxi Power Maximum continuous engine speed for taxiing is 1000 RPM on flat, smooth, hard surfaces.
  • Page 43: Fuel Limits

    Environmental Conditions For operation of the airplane below an outside air temperature of -10°F (-23°C), use of cowl inlet covers approved by Cirrus Design and listed in the Winterization Kit AFM Supplement P/N 13772-118 is required. P/N 13772-004...
  • Page 44: Maximum Occupancy

    Section 2 Cirrus Design Limitations SR22 Maximum Occupancy Occupancy of this airplane is limited to “4+1” persons, the pilot and four passengers. If carrying three rear seat passengers, occupants must be wearing a seat belt and shoulder harness with their hips and back firmly against the seatback as show in the following illustration.
  • Page 45: Systems And Equipment Limits

    Systems and Equipment Limits Cirrus Perspective Integrated Avionics System 1. The appropriate revision of the Cirrus Perspective Cockpit Reference Guide (p/n 190-00821-XX, where X can be any digit from 0 to 9) must be immediately available to the pilot during flight.
  • Page 46: Original Issue

    The Perspective Integrated Avionics System is compliant with AC 90-100A. As such, the Cirrus Perspective system is eligible to fly RNAV 'Q' or 'T' routes, RNAV SID/STAR/ODPs and eligible to use RNAV substitution or RNAV alternate means of navigation (US Only).
  • Page 47: Revision 1

    Cirrus Design Section 2 SR22 Limitations n. Serials w/ system software load 0764-21 or later: Barometric vertical navigation (Baro-VNAV) operations may be conducted if SBAS is unavailable or disabled. The Perspective Integrated Avionics System will provide automatic, temperature- compensated glidepath vertical guidance and has been...
  • Page 48: L-3 Skywatch Traffic Advisory System

    Section 2 Cirrus Design Limitations SR22 11. The SYNTHETIC VISION SYSTEM (SVS) cannot be used for flight guidance, navigation, traffic avoidance, or terrain avoidance. Maneuvering the airplane in any phase of flight such as taxi, takeoff, approach, landing, or roll out shall not be predicated on SVS imagery.
  • Page 49: Max Viz Enhanced Vision System (Optional)

    Cirrus Design Section 2 SR22 Limitations Max Viz Enhanced Vision System (Optional) 1. The Enhanced Vision System (EVS) cannot be used for flight guidance, navigation, traffic avoidance, or terrain avoidance. Maneuvering the airplane in any phase of flight such as taxi, takeoff, approach, landing, or roll out shall not be predicated on EVS imagery.
  • Page 50: Cirrus Airframe Parachute System (Caps)

    Limitations SR22 in the Airplane Maintenance Manual. Refer to Airplane Maintenance Manual (AMM), Chapter 51, for specific paint requirements. Cirrus Airframe Parachute System (CAPS) VPD Maximum Demonstrated Deployment Speed....140 KIAS • Note • Refer to Section 10, Cirrus Airframe Parachute System (CAPS) for additional CAPS guidance.
  • Page 51: Placards

    Cirrus Design Section 2 SR22 Limitations Placards Engine compartment, inside oil filler access: ENGINE OIL GRADE ABOVE 40° F SAE 50 OR 20W50 OR 20W60 BELOW 40° F SAE 30 OR 10W30, 15W50, OR 20W50 REFER TO AFM FOR APPROVED OILS...
  • Page 52: Revision 1

    Section 2 Cirrus Design Limitations SR22 Elevator and Rudder, both sides: NO PUSH Left fuselage, on external power supply door: EXTERNAL POWER 28 V DC Doors, adjacent to latch: PUSH OPEN OPEN Serials 3915 thru 4299 Serials 4300 & subs...
  • Page 53: Revision 1

    Cirrus Design Section 2 SR22 Limitations Engine control panel: FLAPS KIAS 100% KIAS CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT ALTITUDE GPH 16000 ----- 17 12000 ----- 18 8000 ----- 21 4000 ----- 24...
  • Page 54: Revision 1

    Section 2 Cirrus Design Limitations SR22 Wing, flap aft edge and fuselage vortex generator: NO STEP Cabin Door Window, lower edge, centered, applied upside down: RESCUE: FRACTURE AND REMOVE WINDOW Bolster Switch Panel, left edge: THIS AIRCRAFT IS CERTIFIED FOR THE...
  • Page 55: Revision 1

    Cirrus Design Section 2 SR22 Limitations Instrument Panel, center: DISPLAY BACKUP Bolster Panel, both sides: GRAB HERE Baggage Compartment, aft edge: ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Instrument Panel: FASTEN SEATBELTS • NO SMOKING Cabin Window, above door latch:...
  • Page 56: Revision 1

    MUST BE WORN AT ALL TIMES USE OF THIS DEVICE COULD RESULT IN INJURY OR DEATH MAXIMUM DEMONSTRATED DEPLOYMENT SPEED 140 KIAS CIRRUS AIRFRAME PARACHUTE SYSTEM ACTIVATION PROCEDURE 1. THIS COVER..........REMOVE 2. ACTIVATION HANDLE..PULL STRAIGHT DOWN BOTH HANDS, MAXIMUM FORCE, STEADY PULL DO NOT JERK HANDLE 3.
  • Page 57 Cirrus Design Section 3 SR22 Emergency Procedures Section 3: Emergency Procedures Table of Contents Introduction ..................3 Emergency Procedures Guidance ............. 4 CAPS Guidance................4 Preflight Planning................4 Preflight Inspections/Maintenance ..........4 Methodology ................... 4 Circuit Breakers ................5 Memory Items ................. 6 Airspeeds for Emergency Operations ..........
  • Page 58 Section 3 Cirrus Design Emergency Procedures SR22 High Fuel Flow ................23 Low Fuel Quantity ................. 23 Fuel Imbalance ................24 Electrical System Emergencies............25 High Voltage on Main Bus 1 ............25 High Voltage on Main Bus 2 ............26 High or Low Voltage on Essential Bus..........
  • Page 59: Section 3: Emergency Procedures

    Cirrus Design Section 3 SR22 Emergency Procedures Introduction This section provides procedures for handling emergencies and critical flight situations that may occur while operating 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 should an emergency arise.
  • Page 60: Emergency Procedures Guidance

    CAPS Guidance All Cirrus aircraft are equipped with a pilot or passenger activated ballistic airframe parachute system. The system is capable of lowering the aircraft and occupants safely to the ground for life threatening emergencies.
  • Page 61: Circuit Breakers

    121.500 MHz. If the display is available, it will also show it in the “Active” frequency window. The Cirrus Airframe Parachute System (CAPS) should be activated in the event of a spin. It should also be used in other life-threatening emergencies where CAPS deployment is determined to be safer than continued flight and landing.
  • Page 62: Memory Items

    Section 3 Cirrus Design Emergency Procedures SR22 • Circuit breakers that “CYCLE” should be pulled, delayed for 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 example below, should be memorized for accomplishment without reference to the procedure.
  • Page 63: Airspeeds For Emergency Operations

    Cirrus Design Section 3 SR22 Emergency Procedures 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% ................85 KIAS Flaps 100% ................ 80 KIAS...
  • Page 64: Engine Failures

    Section 3 Cirrus Design Emergency Procedures SR22 Engine Failures Engine Failure On Takeoff (Low Altitude) 1. Best Glide or Landing Speed (as appropriate) ... ESTABLISH 2. Mixture ................CUTOFF 3. Fuel Selector ................OFF 4. Ignition Switch ................OFF 5. Flaps ..............AS REQUIRED If time permits: 6.
  • Page 65: Engine Failure In Flight

    If altitude or terrain does not permit a safe landing, CAPS deployment may be required. Refer to Section 10, Cirrus Airframe Parachute System (CAPS) for CAPS deployment scenarios and landing considerations. P/N 13772-004...
  • Page 66: Airstart

    Section 3 Cirrus Design Emergency Procedures SR22 Airstart Engine Airstart 1. Bat Master Switches ..............ON 2. Power Lever ..............½” OPEN 3. Mixture ..............RICH, AS REQ’D 4. Fuel Selector ............SWITCH TANKS 5. Ignition Switch ...............BOTH 6. Fuel Pump................BOOST 7.
  • Page 67: Smoke And Fire

    Cirrus Design Section 3 SR22 Emergency Procedures Smoke and Fire Cabin Fire In Flight 1. Bat-Alt Master Switches........OFF, AS REQ’D 2. Fire Extinguisher ............ACTIVATE If airflow is not sufficient to clear smoke or fumes from cabin: 3. Cabin Doors ............PARTIALLY OPEN Airspeed may need to be reduced to partially open door in flight.
  • Page 68: Engine Fire In Flight

    Section 3 Cirrus Design Emergency Procedures SR22 If the cause of the fire is readily apparent and accessible, use the fire extinguisher to extinguish flames and land as soon as possible. Opening the vents or doors may feed the fire, but to avoid incapacitating the crew from smoke inhalation, it may be necessary to rid cabin of smoke or fire extinguishant.
  • Page 69: Wing Fire In Flight

    Cirrus Design Section 3 SR22 Emergency Procedures Wing Fire In Flight 1. Pitot Heat Switch ..............OFF 2. Navigation Light Switch ............OFF 3. Landing Light ................OFF 4. Strobe Light Switch ..............OFF 5. If possible, side slip to keep flames away from fuel tank and cabin.
  • Page 70: Smoke And Fume Elimination

    Section 3 Cirrus Design Emergency Procedures SR22 Smoke and Fume Elimination 1. Air Conditioner (if installed) ............OFF 2. Temperature Selector............COLD 3. Vent Selector......FEET/PANEL/DEFROST POSITION 4. Airflow Selector ......SET AIRFLOW TO MAXIMUM If source of smoke and fume is firewall forward: a.
  • Page 71: Emergency Descent

    Cirrus Design Section 3 SR22 Emergency Procedures Emergency Descent Emergency Descent 1. Power Lever................IDLE 2. Mixture ..............AS REQUIRED 3. Airspeed..............V (205 KIAS) Amplification • Caution • If significant turbulence is expected do not descend at indicated airspeeds greater than V...
  • Page 72: Forced Landings

    Section 3 Cirrus Design Emergency Procedures SR22 Forced Landings Emergency Landing Without Engine Power 1. Best Glide Speed ............ESTABLISH 2. Radio..........Transmit (121.5 MHz) MAYDAY giving location and intentions 3. Transponder............SQUAWK 7700 4. If off airport, ELT ............ACTIVATE 5. Power Lever ................IDLE 6.
  • Page 73: Ditching

    Cirrus Design Section 3 SR22 Emergency Procedures Ditching 1. Radio ..........Transmit (121.5 MHz) MAYDAY giving location and intentions 2. Transponder............SQUAWK 7700 3. CAPS ................ACTIVATE 4. Airplane................ EVACUATE 5. Flotation Devices ....INFLATE WHEN CLEAR OF AIRPLANE Amplification If available, life preservers should be donned and life raft should be prepared for immediate evacuation upon touchdown.
  • Page 74: Engine System Emergencies

    Section 3 Cirrus Design Emergency Procedures SR22 Engine System Emergencies Engine Partial Power Loss 1. Air Conditioner (if installed) ............OFF 2. Fuel Pump................BOOST 3. Fuel Selector ............SWITCH TANKS 4. Mixture ......CHECK appropriate for flight conditions 5. Power Lever ............... SWEEP 6.
  • Page 75: Revision 1

    Cirrus Design Section 3 SR22 Emergency Procedures which may prevent a fire at altitude. However, as the Power Lever is reduced during descent and approach to landing the cooling air may not be sufficient to prevent an engine fire. Selecting BOOST on may clear the problem if vapor in the injection lines is the problem or if the engine-driven fuel pump has partially failed.
  • Page 76: Oil Pressure Out Of Range

    Section 3 Cirrus Design Emergency Procedures SR22 Oil Pressure Out of Range OIL PRESS Warning OIL PRESS 1. Oil Pressure Gage ............. CHECK If pressure low: a. Power ...... REDUCE to minimum for sustained flight b. Land as soon as possible.
  • Page 77: High Cylinder Head Temperature

    Cirrus Design Section 3 SR22 Emergency Procedures High Cylinder Head Temperature CHT Caution and Warning On-Ground 1. Power Lever..............REDUCE 2. Annunciations and Engine Temperatures ...... MONITOR If Caution or Warning annunciation is still illuminated: 3. Power Lever..........MINIMUM REQUIRED 4.
  • Page 78: Propeller System Emergencies

    Section 3 Cirrus Design Emergency Procedures SR22 Propeller System Emergencies Engine Speed High RPM Warning: Engine SpeedHigh 1. Tachometer ................ CHECK If engine speed normal: a. If On-Ground......CORRECT PRIOR TO FLIGHT b. If In-Flight..........CONTINUE, MONITOR If engine speed high: a.
  • Page 79: Fuel System Emergencies

    Cirrus Design Section 3 SR22 Emergency Procedures Fuel System Emergencies High Fuel Flow FUEL FLOW Warning FUEL FLOW Fuel flow greater than 30 GPH. On-Ground 1. Correct prior to flight. In-Flight 1. Mixture ................ADJUST Adjust engine operation to correct condition. Check engine instruments to verify HIGH FLOW Warning is not erroneous, i.e.
  • Page 80: Fuel Imbalance

    Section 3 Cirrus Design Emergency Procedures SR22 Fuel Imbalance FUEL IMBALANCE Warning FUEL IMBALANCE 1. Fuel Quantity Gages ............CHECK 2. Fuel Pump................BOOST If HIGH BOOST already in use for vapor suppression, pump should be left in this position for tank switch.
  • Page 81: Electrical System Emergencies

    Cirrus Design Section 3 SR22 Emergency Procedures Electrical System Emergencies High Voltage on Main Bus 1 M BUS 1 Warning M BUS 1 1. ALT 1 Master Switch ............CYCLE 2. M Bus 1 Voltage (M1) ............CHECK If M Bus 1 Voltage is greater than 32 volts 3.
  • Page 82: Original Issue

    Section 3 Cirrus Design Emergency Procedures SR22 High Voltage on Main Bus 2 M BUS 2 Warning M BUS 2 1. Main Bus 1 Voltage (M1)............ CHECK If M Bus 1 Voltage is greater than 32 volts 2. Perform M BUS 1 Warning Checklist 3.
  • Page 83: High Or Low Voltage On Essential Bus

    Cirrus Design Section 3 SR22 Emergency Procedures High or Low Voltage on Essential Bus ESS BUS Warning ESS BUS 1. Essential Bus Voltage (ESS)..........CHECK If Essential Bus Voltage is greater than 32 volts: 2. Main Bus 1 and Main Bus 2 Voltages (M1 and M2)... CHECK 3.
  • Page 84: Environmental System Emergencies

    Section 3 Cirrus Design Emergency Procedures SR22 Environmental System Emergencies Carbon Monoxide Level High CO LVL HIGH Warning CO LVL HIGH 1. Air Conditioner (if installed) ...... NOT IN RECIRC MODE 2. Temperature Selector............COLD 3. Vent Selector......FEET/PANEL/DEFROST POSITION 4. Airflow Selector ......SET AIRFLOW TO MAXIMUM 5.
  • Page 85: Integrated Avionics System Emergencies

    Cirrus Design Section 3 SR22 Emergency Procedures Integrated Avionics System Emergencies A “Red X” through any electronic display field, such as COM frequencies, NAV frequencies, or engine data, indicates that display field is not receiving valid data. Attitude & Heading Reference System (AHRS) Failure 1.
  • Page 86: Unusual Attitude Emergencies

    CAPS deployment be attempted. The aircraft is not approved for spins, and has not been certified for traditional spin recovery characteristics. The only approved and demonstrated method of spin recovery is activation of the Cirrus Airframe Parachute System (See CAPS Deployment Checklist, this section).
  • Page 87: Inadvertent Spiral Dive During Imc Flight

    7. Exit IMC conditions as soon as possible. Amplification In all cases, if the aircraft enters an unusual attitude from which recovery is not assured, immediately deploy CAPS. Refer to Section Cirrus Airframe Parachute System (CAPS) for CAPS deployment information. P/N 13772-004...
  • Page 88: Other Emergencies

    Section 3 Cirrus Design Emergency Procedures SR22 Other Emergencies Power Lever Linkage Failure 1. Power Lever Movement ............. VERIFY 2. Power ................SET if able 3. Flaps ................ SET if needed 4. Mixture ........AS REQUIRED (full rich to cut-off) 5.
  • Page 89: Left/Right Brake Over-Temperature Annunciation

    Cirrus Design Section 3 SR22 Emergency Procedures Left/Right Brake Over-Temperature Annunciation BRAKE TEMP Warning BRAKE TEMP 1. Stop aircraft and allow the brakes to cool. Amplification Annunciation indicates brake temperature is greater than 293°F. Refer to Section 10, Taxiing, Steering, and Braking Practices for additional information.
  • Page 90: Emergency Ground Egress

    Section 3 Cirrus Design Emergency Procedures SR22 Amplification • WARNING • Use caution after shutdown if STARTER circuit breaker required pull (failed relay or solenoid). If breaker is unknowingly or unintentionally reset, starter will instantly engage if Battery 1 power is supplied; creating a hazard for ground personnel.
  • Page 91: Revision 1

    – a “chin-up” type pull ensures successful activation. The Cirrus Airframe Parachute System (CAPS) should be activated immediately in the event of a spin. It should also be used in other life- threatening emergencies where CAPS deployment is determined to be safer than continued flight and landing.
  • Page 92: Revision 1

    Section 3 Cirrus Design Emergency Procedures SR22 Expected impact in a fully stabilized deployment is equivalent to a drop from approximately 13 feet. • Caution • CAPS deployment will likely result in damage or loss to the airframe. Several possible scenarios in which the activation of the CAPS would...
  • Page 93: Original Issue

    Cirrus Design Section 3A SR22 Abnormal Procedures Section 3A: Abnormal Procedures Table of Contents Introduction ..................3 Abnormal Procedures Guidance ............4 Circuit Breakers ................4 Flight Environment ................5 Inadvertent Icing Encounter ............5 Inadvertent IMC Encounter............. 5 Door Open In Flight ................ 5 Abnormal Landings ................
  • Page 94 Section 3A Cirrus Design Abnormal Procedures SR22 Landing Gear System ..............20 Brake Failure During Taxi ............. 20 Left/Right Brake Over-Temperature..........20 Other Conditions ................21 Aborted Takeoff ................21 Parking Brake Engaged Annunciation .......... 22 Communications Failure ............... 22...
  • Page 95: Introduction

    Cirrus Design Section 3A SR22 Abnormal Procedures Introduction This section provides procedures for handling abnormal system and/or flight conditions which, if followed, will maintain an acceptable level of airworthiness or reduce operational risk. The guidelines described in this section are to be used when an abnormal condition exists and should be considered and applied as necessary.
  • Page 96: Abnormal Procedures Guidance

    Section 3A Cirrus Design Abnormal Procedures SR22 Abnormal Procedures Guidance Although this section provides procedures for handling most abnormal system and/or flight conditions that could arise in the aircraft, it is not a substitute for thorough knowledge of the airplane and general aviation techniques.
  • Page 97: Flight Environment

    Cirrus Design Section 3A SR22 Abnormal Procedures Flight Environment Inadvertent Icing Encounter 1. Pitot Heat ...................ON 2. Exit icing conditions. Turn back or change altitude. 3. Cabin Heat ..............MAXIMUM 4. Windshield Defrost............FULL OPEN 5. Alternate Induction Air ...............ON Amplification Flight into known icing conditions is prohibited.
  • Page 98: Abnormal Landings

    Section 3A Cirrus Design Abnormal Procedures SR22 Abnormal Landings Landing With Failed Brakes One brake inoperative 1. Land on the side of runway corresponding to the inoperative brake. 2. Maintain directional control using rudder and working brake. Both brakes inoperative 1.
  • Page 99: Engine System

    Cirrus Design Section 3A SR22 Abnormal Procedures Engine System Low Idle Oil Pressure OIL PRESS Caution OIL PRESS 1. If In-Flight ..........LAND as soon as practical Amplification Oil pressure between 10 psi and 30 psi at or above 1000 RPM This message will appear prior to engine start and should clear after engine start.
  • Page 100: Starter Engaged Annunciation

    Section 3A Cirrus Design Abnormal Procedures SR22 Starter Engaged Annunciation STARTER ENGAGED Caution START ENGAGE On-Ground 1. Ignition Switch ......DISENGAGE prior to 10 Seconds 2. Battery Switches ..Wait 20 seconds before next start attempt If starter does not disengage (relay or solenoid failure): 3.
  • Page 101: Fuel System

    Cirrus Design Section 3A SR22 Abnormal Procedures Fuel System Low Fuel Quantity FUEL QTY Caution FUEL QTY 1. Fuel Quantity Gages ............CHECK If left & right fuel quantities indicate less than or equal to 14 gallons per side: a. Land as soon as practical.
  • Page 102: Right Fuel Tank Quantity

    Section 3A Cirrus Design Abnormal Procedures SR22 Right Fuel Tank Quantity R FUEL QTY Advisory R FUEL QTY 1. Right Fuel Quantity Gage ..........CHECK If right fuel quantity indicates less than or equal to 14 gallons: a. If On-Ground.......REFUEL PRIOR TO FLIGHT b.
  • Page 103: Original Issue

    Cirrus Design Section 3A SR22 Abnormal Procedures 1. Fuel Quantity Gages ............CHECK 2. Fuel Pump ................. BOOST If HIGH BOOST already in use for vapor suppression, pump should be left in this position for tank switch. 3. Fuel Selector.......... SELECT FULLEST TANK 4.
  • Page 104: Low Voltage On Main Bus 1

    Section 3A Cirrus Design Abnormal Procedures SR22 Electrical System Low Voltage on Main Bus 1 M BUS 1 Caution M BUS 1 1. Perform ALT 1 Caution (Failure) Checklist. Amplification Main Bus 1 Voltage is low, indicates Alt 1 failure; will typically be associated with low M1 voltage Alt 1 current indications, Battery 1 discharge and ALT 1 Caution message.
  • Page 105: Low Alternator 1 Output

    Cirrus Design Section 3A SR22 Abnormal Procedures Low Alternator 1 Output ALT 1 Caution (Failure) ALT 1 1. ALT 1 Circuit Breaker..........CHECK & SET 2. ALT 1 Master Switch ............CYCLE If alternator does not reset (low A1 Current and M1 voltage): 3.
  • Page 106: Low Alternator 2 Output

    Section 3A Cirrus Design Abnormal Procedures SR22 Low Alternator 2 Output ALT 2 Caution (Failure) ALT 2 1. ALT 2 Circuit Breaker ..........CHECK & SET 2. ALT 2 Master Switch ............CYCLE If alternator does not reset (low A2 Current and M2 voltage less than M1 voltage): 3.
  • Page 107: Integrated Avionics System

    Cirrus Design Section 3A SR22 Abnormal Procedures Integrated Avionics System Avionics Switch Off AVIONICS OFF Caution AVIONICS OFF 1. AVIONICS Switch ........... ON, AS REQUIRED Amplification The AVIONICS master switch is off. PFD Cooling Fan Failure PFD FAN FAIL Advisory PFD FAN FAIL 1.
  • Page 108: Flight Displays Too Dim

    Section 3A Cirrus Design Abnormal Procedures SR22 Flight Displays Too Dim 1. INSTRUMENT dimmer knob....OFF (full counter-clockwise) If flight displays do not provide sufficient brightness: 2. Revert to standby instruments. Amplification The instrument dimmer knob provides manual dimming control of the display screens, key and text backlighting, flap and Environmental Control System (ECS) status indicators, and standby instruments.
  • Page 109: Pitot Static System

    Cirrus Design Section 3A SR22 Abnormal Procedures Pitot Static System Pitot Static Malfunction Static Source Blocked 1. Pitot Heat ...................ON 2. Alternate Static Source ............OPEN Amplification If erroneous readings of the static source instruments (airspeed, altimeter and vertical speed) are suspected, the alternate static source valve, on side of console near pilot’s right ankle, should be opened to...
  • Page 110: Pitot Heat Current Sensor Annunciation

    Section 3A Cirrus Design Abnormal Procedures SR22 Pitot Heat Current Sensor Annunciation PITOT HEAT FAIL Caution PITOT HEAT FAIL 1. Pitot Heat Circuit Breaker ........... CYCLE 2. Pitot Heat .............CYCLE OFF, ON If inadvertent icing encountered, perform Inadvertent Icing Encounter Checklist and: a.
  • Page 111: Flight Control System

    Cirrus Design Section 3A SR22 Abnormal Procedures Flight Control System Electric Trim/Autopilot Failure 1. Airplane Control ......... MAINTAIN MANUALLY 2. Autopilot (if engaged)..........DISENGAGE If Problem Is Not Corrected: 3. Circuit Breakers ........... PULL AS REQUIRED • PITCH TRIM • ROLL TRIM •...
  • Page 112: Landing Gear System

    Section 3A Cirrus Design Abnormal Procedures SR22 Landing Gear System Brake Failure During Taxi 1. Engine Power............AS REQUIRED • To stop airplane - REDUCE • If necessary for steering - INCREASE 2. Directional Control ......MAINTAIN WITH RUDDER 3. Brake Pedal(s) ..............PUMP If directional control can not be maintained: 4.
  • Page 113: Other Conditions

    Cirrus Design Section 3A SR22 Abnormal Procedures Other Conditions Aborted Takeoff 1. Power Lever................IDLE 2. Brakes..............AS REQUIRED Amplification Use as much of the remaining runway as needed to safely bring the airplane to a stop or to slow the airplane sufficiently to turn off runway.
  • Page 114: Parking Brake Engaged Annunciation

    Section 3A Cirrus Design Abnormal Procedures SR22 Parking Brake Engaged Annunciation PARK BRAKE Caution PARK BRAKE 1. Parking Brake ..............RELEASE 2. Monitor CAS for BRAKE TEMP Caution. Stop aircraft and allow the brakes to cool if necessary. Amplification Parking brake is set.
  • Page 115: Revision 1

    Cirrus Design Section 4 SR22 Normal Procedures Section 4: Normal Procedures Table of Contents Introduction ..................3 Airspeeds for Normal Operation ............3 Normal Procedures ................4 Preflight Inspection ................. 4 Before Starting Engine..............9 Starting Engine ................10 Before Taxiing................12 Taxiing ..................
  • Page 116 Section 4 Cirrus Design Normal Procedures SR22 Intentionally Left Blank P/N 13772-004 Original Issue...
  • Page 117: Airspeeds For Normal Operation

    Cirrus Design Section 4 SR22 Normal Procedures Introduction This section provides amplified procedures for normal operation. Normal procedures associated with optional systems can be found in Section 9: Log of Supplements. Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3600 lb.
  • Page 118: Normal Procedures

    Section 4 Cirrus Design Normal Procedures SR22 Normal Procedures Preflight Inspection Before carrying out preflight inspections, ensure that all required maintenance has been accomplished. Review your flight plan and compute weight and balance. Throughout the walk-around: check all hinges, hinge pins, and bolts for security; check skin for damage, condition, and evidence of delamination;...
  • Page 119 Cirrus Design Section 4 SR22 Normal Procedures c. Bat 2 Master Switch ............ON d. PFD ................Verify On e. Essential Bus Voltage..........23-25 Volts Flap Position Light ............OUT g. Bat 1 Master Switch ............ON h. Avionics Cooling Fan............ Audible Lights .............
  • Page 120 Section 4 Cirrus Design Normal Procedures SR22 3. Empennage a. Tiedown Rope............. Remove b. Horizontal and Vertical Stabilizers ......Condition • Note • Verify tape covering the forward and aft inspection holes located on outboard ends of horizontal stabilizer is installed and securely attached.
  • Page 121: Revision 1

    Cirrus Design Section 4 SR22 Normal Procedures • Caution • Serials 3915 thru 4030, 4032, 4045 before SB2X-32-21: Clean and inspect temperature indicator installed to piston housing. If indicator center is black, the brake assembly has been overheated. The brake linings must be inspected and O- rings replaced.
  • Page 122: Revision 1

    Section 4 Cirrus Design Normal Procedures SR22 d. External Power .............Door Secure e. Vortex Generator ............Condition Exhaust Pipe(s) ....Condition, Security, and Clearance 11. Left Main Gear and Forward Wing a. Wheel fairings....... Security, Accumulation of Debris b. Tire..........Condition, Inflation, and Wear •...
  • Page 123: Before Starting Engine

    Cirrus Design Section 4 SR22 Normal Procedures Before Starting Engine 1. Preflight Inspection ...........COMPLETED 2. Weight and Balance..........Verify within limits 3. Emergency Equipment ..........ON BOARD 4. Passengers ..............BRIEFED 5. Seats, Seat Belts, and Harnesses ....ADJUST & SECURE Amplification •...
  • Page 124: Starting Engine

    Section 4 Cirrus Design Normal Procedures SR22 Starting Engine If the engine is warm, no priming is required. For the first start of the day and in cold conditions, prime will be necessary. Weak intermittent firing followed by puffs of black smoke from the exhaust stack indicates over-priming or flooding.
  • Page 125 Cirrus Design Section 4 SR22 Normal Procedures 6. Power Lever............FULL FORWARD 7. Fuel Pump ............ PRIME, then BOOST • Note • On first start of the day, especially under cool ambient conditions, holding Fuel Pump switch to PRIME for 2 seconds will improve starting.
  • Page 126: Taxiing

    Section 4 Cirrus Design Normal Procedures SR22 Before Taxiing 1. Flaps ................. UP (0%) 2. Radios/Avionics............AS REQUIRED 3. Cabin Heat/Defrost ..........AS REQUIRED 4. Fuel Selector ............SWITCH TANK Taxiing When taxiing, directional control is accomplished with rudder deflection and intermittent braking (toe taps) as necessary. Use only as much power as is necessary to achieve forward movement.
  • Page 127 Cirrus Design Section 4 SR22 Normal Procedures Before Takeoff During cold weather operations, the engine should be properly warmed up before takeoff. In most cases this is accomplished when the oil temperature has reached at least 100°F (38°C). In warm or hot weather, precautions should be taken to avoid overheating during prolonged ground engine operation.
  • Page 128 Section 4 Cirrus Design Normal Procedures SR22 16. Alternator ................CHECK a. Pitot Heat................ON b. Navigation Lights ..............ON c. Landing Light ..............ON d. Annunciator Lights............CHECK - Verify both ALT 1 and ALT 2 caution lights out and positive amps indication for each alternator.
  • Page 129: Maximum Power Fuel Flow

    Cirrus Design Section 4 SR22 Normal Procedures Maximum Power Fuel Flow Target fuel flow is indicated by the top of a dynamically calculated green arc displayed on the fuel gage. Target fuel flow should be maintained at the top of this arc by use of the mixture lever.
  • Page 130: Takeoff

    Section 4 Cirrus Design Normal Procedures SR22 Takeoff Power Check: Check full-throttle engine operation early in takeoff run. The engine should run smoothly and turn approximately 2700 RPM. All engine parameters are not in caution or warning ranges. Discontinue takeoff at any sign of rough operation or sluggish acceleration.
  • Page 131: Short Field Takeoff

    Cirrus Design Section 4 SR22 Normal Procedures Short Field Takeoff 1. Flaps ..................50% 2. Brakes .................. HOLD 3. Power Lever............FULL FORWARD 4. Mixture ..................SET 5. Engine Parameters ............CHECK 6. Brakes........RELEASE (Steer with Rudder Only) 7. Elevator Control ......ROTATE Smoothly at 73 KIAS 8.
  • Page 132: Cruise

    Section 4 Cirrus Design Normal Procedures SR22 Cruise Normal cruising is performed between 55% and 85% power. The engine power setting and corresponding fuel consumption for various altitudes and temperatures can be determined by using the cruise data in Section 5.
  • Page 133: Descent

    Cirrus Design Section 4 SR22 Normal Procedures Cruise Leaning Exhaust gas temperature (EGT) may be used as an aid for mixture leaning in cruise flight. For “Best Power” use 75% power or less. For “Best Economy” use 65% power or less. To adjust the mixture, lean...
  • Page 134: Normal Landing

    Section 4 Cirrus Design Normal Procedures SR22 Normal Landing 1. Flaps ..................100% 2. Airspeed ............... 80-85 KIAS 3. Power Lever ............AS REQUIRED After touchdown: 4. Brakes ..............AS REQUIRED Amplification • Caution • Landings should be made with full flaps. Landings with less than full flaps are recommended only if the flaps fail to deploy or to extend the aircraft’s glide distance due to engine...
  • Page 135: Short Field Landing

    Cirrus Design Section 4 SR22 Normal Procedures Short Field Landing 1. Flaps ..................100% 2. Airspeed................79 KIAS 3. Power Lever............AS REQUIRED After clear of obstacles: 4. Power Lever............REDUCE TO IDLE After touchdown: 5. Brakes................MAXIMUM Amplification For a short field landing in smooth air conditions, make an approach at...
  • Page 136: Revision 1

    Section 4 Cirrus Design Normal Procedures SR22 Balked Landing/Go-Around 1. Autopilot ..............DISENGAGE 2. Power Lever ............FULL FORWARD 3. Flaps ..................50% 4. Airspeed ............... 80-85 KIAS After clear of obstacles: 5. Flaps ..................UP Amplification In a balked landing (go around) climb, disengage autopilot, apply full power, then reduce the flap setting to 50%.
  • Page 137: Shutdown

    Cirrus Design Section 4 SR22 Normal Procedures Shutdown 1. Fuel Pump (if used) ..............OFF 2. Throttle..................IDLE • Caution • Note that the engine hesitates as the switch cycles through the “OFF” position. If the engine does not hesitate, one or both magnetos are not grounded.
  • Page 138: Stalls

    Section 4 Cirrus Design Normal Procedures SR22 Stalls Aircraft stall characteristics are conventional. Power-off stalls may be accompanied by a slight nose bobbing if full aft stick is held. Power-on stalls are marked by a high sink rate at full aft stick. Power-off stall...
  • Page 139: Environmental Considerations

    Cirrus Design Section 4 SR22 Normal Procedures Environmental Considerations Cold Weather Operation • Caution • An engine that has been superficially warmed, may start and appear to run satisfactorily, but can be damaged from lack of lubrication due to the congealed oil blocking proper oil flow through the engine.
  • Page 140: Revision 1

    Section 4 Cirrus Design Normal Procedures SR22 1. Ignition Switch ................OFF • WARNING • Use caution when pulling the propeller through by hand. Make sure ignition switch is OFF, keys are out of ignition, and then act as if the engine will start.
  • Page 141: Hot Weather Operation

    Cirrus Design Section 4 SR22 Normal Procedures Hot Weather Operation Avoid prolonged engine operation on the ground. Fuel BOOST must be ON for engine start and takeoff, and should be ON during climb for vapor suppression which could occur under hot ambient conditions or after extended idle.
  • Page 142 Section 4 Cirrus Design Normal Procedures SR22 Lead Reduction Before Shut Down Complete the following procedure before shutdown to reduce potential for lead build-up in the combustion chamber, spark plugs, and engine oil. • Caution • The airplane must be stationary before the following procedure is completed.
  • Page 143: Noise Characteristics/Abatement

    Cirrus Design Section 4 SR22 Normal Procedures Noise Characteristics/Abatement The certificated noise levels for the aircraft established in accordance with FAR 36 Appendix G are: Configuration Actual Maximum Allowable Hartzell 3-blade Propeller 84.7 dB(A) 88.0 dB(A) PHC-J3YF-1RF/F7693DF Hartzell 3-blade Propeller 84.7 dB(A)
  • Page 144 Section 4 Cirrus Design Normal Procedures SR22 Intentionally Left Blank 4-30 P/N 13772-004 Revision 1...
  • Page 145 Cirrus Design Section 5 SR22 Performance Data Section 5: Performance Data Table of Contents Introduction ..................3 Associated Conditions Affecting Performance........ 3 Demonstrated Operating Temperature ........... 3 Airspeed Calibration - Normal Static Source........4 Airspeed Calibration - Alternate Static Source........5 Altitude Correction Normal Static Source: Primary Flight Display ........
  • Page 146 Section 5 Cirrus Design Performance Data SR22 Intentionally Left Blank P/N 13772-004 Original Issue...
  • Page 147: Introduction

    Cirrus Design Section 5 SR22 Performance Data Introduction Performance data in this section are presented for operational planning so that you will know what performance to expect from the airplane under various ambient and field conditions. Performance data are presented for takeoff, climb, and cruise (including range &...
  • Page 148: Airspeed Calibration - Normal Static Source

    Section 5 Cirrus Design Performance Data SR22 Airspeed Calibration - Normal Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Note • Indicated airspeed values assume zero instrument error. KCAS KIAS Flaps Flaps Flaps...
  • Page 149: Airspeed Calibration - Alternate Static Source

    Cirrus Design Section 5 SR22 Performance Data Airspeed Calibration - Alternate Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster & Vents .................. ON • Note • Indicated airspeed values assume zero instrument error.
  • Page 150: Altitude Correction Normal Static Source: Primary Flight Display

    Section 5 Cirrus Design Performance Data SR22 Altitude Correction Normal Static Source: Primary Flight Display Conditions: • Power for level flight or maximum continuous, whichever is less. • 3600 LB • Note • Add correction to desired altitude to obtain indicated altitude to fly.
  • Page 151: Altitude Correction Normal Static Source: Standby Altimeter

    Cirrus Design Section 5 SR22 Performance Data Altitude Correction Normal Static Source: Standby Altimeter Conditions: • Power for level flight or maximum continuous, whichever is less. • 3600 LB • Note • Add correction to desired altitude to obtain indicated altitude to fly.
  • Page 152: Altitude Correction Alternate Static Source: Primary Flight Display

    Section 5 Cirrus Design Performance Data SR22 Altitude Correction Alternate Static Source: Primary Flight Display Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster, & Vents .................. ON • Note • Add correction to desired altitude to obtain indicated altitude to fly.
  • Page 153: Altitude Correction Alternate Static Source: Standby Altimeter

    Cirrus Design Section 5 SR22 Performance Data Altitude Correction Alternate Static Source: Standby Altimeter Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster, & Vents.................. ON • Note • Add correction to desired altitude to obtain indicated altitude to fly.
  • Page 154: Temperature Conversion

    Section 5 Cirrus Design Performance Data SR22 Temperature Conversion To convert from Celsius (°C) to Fahrenheit (°F) find in the shaded columns the number representing the temperature value (°C) to be converted. The equivalent Fahrenheit temperature is read to the right.
  • Page 155: Outside Air Temperature For Isa Condition

    Cirrus Design Section 5 SR22 Performance Data Outside Air Temperature for ISA Condition Press ISA-30°C ISA-15°C ISA+15°C ISA+30°C Feet °C °F °C °F °C °F °C °F °C °F 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000...
  • Page 156: Stall Speeds

    Section 5 Cirrus Design Performance Data SR22 Stall Speeds Conditions: • Weight ......................3600 LB • CG ........................Noted • Power ........................ Idle • Bank Angle .....................Noted • Note • Altitude loss during wings level stall may be 250 feet or more.
  • Page 157 Cirrus Design Section 5 SR22 Performance Data Wind Components Example: • Runway Heading....................10° • Wind Direction....................60° • Wind Velocity .....................15 Knots • Note • The max demonstrated crosswind is 21 knots. Value not considered limiting. 0° 10° 20°...
  • Page 158: Takeoff Distance

    Section 5 Cirrus Design Performance Data SR22 Takeoff Distance Conditions: • Winds........................ Zero • Runway..................Dry, Level, Paved • Flaps......................... 50% • Air Conditioner....................OFF • Power: •Throttle....................Full Open •Mixture ..................Set per Placard Set prior to brake release for short field takeoff.
  • Page 159: Takeoff Distance - 3600 Lb

    Cirrus Design Section 5 SR22 Performance Data Takeoff Distance - 3600 LB Weight: 3600 LB Headwind: Subtract 10% for each 12 knots Speed at Liftoff: 76 KIAS headwind. Speed over 50 Ft. Obstacle: 84 KIAS Tailwind: Add 10% for each 2 knots tailwind up Flaps: 50% to 10 knots.
  • Page 160 Section 5 Cirrus Design Performance Data SR22 Takeoff Distance - 2900 LB Weight: 2900 LB Headwind: Subtract 10% for each 12 knots Speed at Liftoff: 70 KIAS headwind. Speed over 50 Ft. Obstacle: 74 KIAS Tailwind: Add 10% for each 2 knots tailwind up Flaps: 50% to 10 knots.
  • Page 161: Takeoff Climb Gradient

    Cirrus Design Section 5 SR22 Performance Data Takeoff Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps .........................50% • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
  • Page 162: Takeoff Rate Of Climb

    Section 5 Cirrus Design Performance Data SR22 Takeoff Rate of Climb Conditions: • Power ....................Full Throttle • Mixture....................... Full Rich • Flaps......................... 50% • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude for unit time expended expressed in Feet per Minute.
  • Page 163: Enroute Climb Gradient

    Cirrus Design Section 5 SR22 Performance Data Enroute Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .......................Full Rich • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
  • Page 164: Enroute Rate Of Climb

    Section 5 Cirrus Design Performance Data SR22 Enroute Rate of Climb Conditions: • Power ....................Full Throttle • Mixture....................As Required • Flaps......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude in feet per unit time expressed in Feet per Minute.
  • Page 165: Enroute Rate Of Climb Vs Density Altitude

    Cirrus Design Section 5 SR22 Performance Data Enroute Rate of Climb Vs Density Altitude Conditions: • Power ....................Full Throttle • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb 17000 16000 15000 14000 13000 12000 11000 10000 9000 8000...
  • Page 166: Time, Fuel And Distance To Climb

    Section 5 Cirrus Design Performance Data SR22 Time, Fuel and Distance to Climb Conditions: • Power ....................Full Throttle • Mixture................Per Schedule, Section 4 • Fuel Density...................6.0 LB/GAL • Weight ......................3600 LB • Winds........................ Zero • Climb Airspeed ....................Noted •...
  • Page 167: Cruise Performance

    Cirrus Design Section 5 SR22 Performance Data Cruise Performance Conditions: • Cruise Weight..................... 3400 LB • Winds ....................... Zero • Shaded Cells: Cruise Pwr above 85% not recommended. • Note • Subtract 10 KTAS if nose wheel pant and fairing removed. Lower KTAS by 10% if nose and main wheel pants and fairings are removed.
  • Page 168 Section 5 Cirrus Design Performance Data SR22 ISA - 30°C ISA + 30°C Press RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH 8000 2700 21.7 19.7 18.6 17.7 2600 21.7 18.8 17.8 17.0 2500 21.7 17.7 16.8 16.0...
  • Page 169: Range / Endurance Profile

    Cirrus Design Section 5 SR22 Performance Data Range / Endurance Profile Conditions: • Weight ..........3600 LB for Climb, Avg 3400 LB for Cruise • Temperature ..................Standard Day • Winds ....................... Zero • Mixture ....................Best Economy • Total Fuel....................92 Gallons •...
  • Page 170 Section 5 Cirrus Design Performance Data SR22 Range / Endurance Profile (Continued) 65% POWER Mixture: Best Power Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 81.2 15.4 10.3 2000 79.3 15.4 10.5...
  • Page 171: Balked Landing Climb Gradient

    Cirrus Design Section 5 SR22 Performance Data Balked Landing Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps ...................... 100% (DN) • Climb Airspeed....................V REF • Note • Balked Landing Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
  • Page 172: Balked Landing Rate Of Climb

    Section 5 Cirrus Design Performance Data SR22 Balked Landing Rate of Climb Conditions: • Power ....................Full Throttle • Mixture.................... Set per Placard • Flaps...................... 100% (DN) • Climb Airspeed ....................V REF • Note • Balked Landing Rate of Climb values shown are the full flaps change in altitude for unit time expended expressed in Feet per Minute.
  • Page 173: Landing Distance

    Cirrus Design Section 5 SR22 Performance Data Landing Distance Conditions: • Winds ....................... Zero • Runway ..................Dry, Level, Paved • Flaps..................100%, 50%, or 0% • Power ..................3° Power Approach to 50 FT obstacle, then reduce power passing the estimated 50 foot point and smoothly continue power reduction to reach idle just prior to touchdown.
  • Page 174: Landing Distance - Flaps 100

    Section 5 Cirrus Design Performance Data SR22 Landing Distance - Flaps 100% WEIGHT: 3600 LB Headwind: Subtract 10% for each 13 Speed over 50 Ft Obstacle: 79 KIAS knots headwind. Flaps: 100% Tailwind: Add 10% for each 2 knots Power: Idle tailwind up to 10 knots.
  • Page 175: Landing Distance - Flaps 0

    Cirrus Design Section 5 SR22 Performance Data Landing Distance - Flaps 50% WEIGHT: 3600 LB Headwind: Subtract 10% for each 13 Speed over 50 Ft Obstacle: 87 KIAS knots headwind. Flaps: 50% Tailwind: Add 10% for each 2 knots Power: Idle tailwind up to 10 knots.
  • Page 176 Section 5 Cirrus Design Performance Data SR22 Landing Distance - Flaps 0% WEIGHT: 3600 LB Headwind: Subtract 10% for each 13 Speed over 50 Ft Obstacle: 94 KIAS knots headwind. Flaps: 0% Tailwind: Add 10% for each 2 knots Power: Idle tailwind up to 10 knots.
  • Page 177 Cirrus Design Section 6 SR22 Weight and Balance Data Section 6: Weight and Balance Data Table of Contents Introduction ..................3 Loading Instructions ................4 Weight and Balance Loading Form............ 5 Loading Data..................6 Moment Limits..................7 Weight & Balance Record ..............8 Equipment List ...................
  • Page 178 Section 6 Cirrus Design Weight and Balance Data SR22 Intentionally Left Blank P/N 13772-004 Original Issue...
  • Page 179 Cirrus Design Section 6 SR22 Weight and Balance Data Introduction This section describes the procedure for calculating the weight and moment for various operations. A comprehensive list of all equipment available for this airplane is included at the back of this section.
  • Page 180: Loading Instructions

    Section 6 Cirrus Design Weight and Balance Data SR22 Loading Instructions It is the responsibility of the pilot to ensure that the airplane is properly loaded and operated within the prescribed weight and center of gravity limits. The following information enables the pilot to calculate the total weight and moment for the loading.
  • Page 181: Weight And Balance Loading Form

    Cirrus Design Section 6 SR22 Weight and Balance Data Weight and Balance Loading Form • Note • The Takeoff Condition Weight must not exceed 3600 lb. The Takeoff Condition Moment must be within the Minimum Moment to Maximum Moment range at the Takeoff Condition Weight.
  • Page 182: Loading Data

    Section 6 Cirrus Design Weight and Balance Data SR22 Loading Data Use the following chart or table to determine the moment/1000 for fuel and payload items to complete the Loading Form. Fuel Aft Pass Fwd Pass Loading Chart Baggage 20.0 40.0...
  • Page 183: Moment Limits

    Cirrus Design Section 6 SR22 Weight and Balance Data Moment Limits Use the following chart or table to determine if the weight and moment from the completed Weight and Balance Loading Form (Figure 6-1) are within limits. 3600 Airplane 3400...
  • Page 184 Section 6 Cirrus Design Weight and Balance Data SR22 Weight & Balance Record Use this form to maintain a continuous history of changes and modifications to airplane structure or equipment affecting weight and balance: Serial Num: Reg. Num: Page Weight Change Running Basic Item No.
  • Page 185: Equipment List

    Cirrus Design Section 6 SR22 Weight and Balance Data Equipment List This list will be determined after the final equipment has been installed in the aircraft. P/N 13772-004 P/N 13772-004 Revision 1...
  • Page 186 Section 6 Cirrus Design Weight and Balance Data SR22 Intentionally Left Blank 6-10 P/N 13772-004 Revision 1...
  • Page 187 Cirrus Design Section 7 SR22 Systems Description Section 7: Systems Description Table of Contents Introduction ..................5 Airframe ..................... 6 Fuselage ..................6 Wings....................6 Empennage ..................7 Flight Controls ..................8 Elevator System................8 Aileron System................10 Rudder System ................12 Control Locks................
  • Page 188 Section 7 Cirrus Design Systems Description SR22 Engine ....................35 Engine Controls ................35 Engine Indicating ................36 Engine Lubrication System ............40 Ignition and Starter System............40 Air Induction System ..............40 Engine Exhaust................41 Engine Fuel Injection ..............41 Engine Cooling................
  • Page 189 Emergency Locator Transmitter ..........101 Fire Extinguisher................. 102 Hour Meters ................103 Emergency Egress Hammer............103 Convenience Outlet(s) ..............103 Cirrus Airframe Parachute System ..........105 System Description ..............105 Activation Handle ................ 106 Deployment Characteristics ............107 P/N 13772-004...
  • Page 190 Section 7 Cirrus Design Systems Description SR22 Intentionally Left Blank P/N 13772-004 Original Issue...
  • Page 191: Introduction

    Cirrus Design Section 7 SR22 Systems Description Introduction This section provides a basic description and operation of the standard airplane and its systems. Optional equipment described within this section is identified as optional. • Note • Some optional equipment may not be described in this section.
  • Page 192: Airframe

    Section 7 Cirrus Design Systems Description SR22 Airframe Fuselage The airplane’s monocoque fuselage is constructed primarily of composite materials and is designed to be aerodynamically efficient. The cabin area is bounded on the forward side by the firewall at fuselage station 100, and on the rear by the aft baggage compartment bulkhead at fuselage station 222.
  • Page 193: Empennage

    Cirrus Design Section 7 SR22 Systems Description Empennage The empennage consists of a horizontal stabilizer, a two-piece elevator, a vertical fin and a rudder. All of the empennage components are conventional spar (shear web), rib, and skin construction. The horizontal stabilizer is a single composite structure from tip to tip.
  • Page 194: Flight Controls

    Section 7 Cirrus Design Systems Description SR22 Flight Controls The airplane uses conventional flight controls for ailerons, elevator and rudder. The control surfaces are pilot controlled through either of two single-handed side control yokes mounted beneath the instrument panel. The location and design of the control yokes allow easy, natural use by the pilot.
  • Page 195 Cirrus Design Section 7 SR22 Systems Description SR22_FM07_1461 Figure 7-1 Elevator System P/N 13772-004 P/N 13772-004 Original Issue...
  • Page 196: Aileron System

    Section 7 Cirrus Design Systems Description SR22 Aileron System The ailerons provide airplane roll control. The ailerons are of conventional design with skin, spar and ribs manufactured of aluminum. Each aileron is attached to the wing shear web at two hinge points.
  • Page 197 Cirrus Design Section 7 SR22 Systems Description SR22_FM07_1462 Figure 7-2 Aileron System P/N 13772-004 P/N 13772-004 7-11 7-11 Original Issue...
  • Page 198: Rudder System

    Section 7 Cirrus Design Systems Description SR22 Rudder System The rudder provides airplane directional (yaw) control. The rudder is of conventional design with skin, spar and ribs manufactured of aluminum. The rudder is attached to the aft vertical stabilizer shear web at three hinge points and to the fuselage tailcone at the rudder control bell crank.
  • Page 199 Cirrus Design Section 7 SR22 Systems Description SR22_FM07_1463 Figure 7-3 Rudder System P/N 13772-004 P/N 13772-004 7-13 7-13 Original Issue...
  • Page 200: Instrument Panel

    Section 7 Cirrus Design Systems Description SR22 Instrument Panel The instrument panel is of all metal construction and is installed in sections so equipment can be easily removed for maintenance. The surrounding glareshield is made of composite material and projects over the instrument panel to reduce reflections on the windshield from lighted equipment and to shield the panel equipment from glare.
  • Page 201 Cirrus Design Section 7 SR22 Systems Description Legend 1. Cirrus Airframe Parachute System 13. Left Side Console (CAPS) Activation T-Handle Cover · Circuit Breaker Panel 2. Magnetic Compass · Alternate Engine Air 3. Multifunction Display · ELT Remote Switch 4. Fresh Air “Eyeball” Outlet ·...
  • Page 202 Section 7 Cirrus Design Systems Description SR22 Legend 1. Cirrus Airframe Parachute System 13. Left Side Console (CAPS) Activation T-Handle Cover · Circuit Breaker Panel 2. Magnetic Compass · Alternate Engine Air 3. Multifunction Display · ELT Remote Switch 4. Fresh Air “Eyeball” Outlet ·...
  • Page 203: Flight Instruments

    Cirrus Design Section 7 SR22 Systems Description Flight Instruments Flight instruments and annunciations are displayed on the Primary Flight Display (PFD) located directed in front of the pilot. The PFD presents the primary flight instruments arranged in the conventional basic “T” configuration. Standby instruments for airspeed, attitude, and altitude are mounted on the LH bolster panel and are powered independently of the PFD.
  • Page 204 Section 7 Cirrus Design Systems Description SR22 125° LEGEND 1. True Airspeed TERM 2. Airspeed Indicator 3. Horizontal Situation Indicator (HSI) 4. Attitude Indicator 5. Slip/Skid Indicator 1.01NM 6. Vertical Deviation Indicator (VDI) 7. Selected Altitude Bug 8. Current Altitude 9.
  • Page 205: Attitude Indicator

    Cirrus Design Section 7 SR22 Systems Description Attitude Indicator The primary attitude indicator is show on the upper center of the PFD and displays pitch, roll, and slip/skid information provided by the Attitude and Heading Reference System (AHRS). Above and below the horizon line, major pitch marks and labels are shown for every 10°, up to 80°.
  • Page 206: Airspeed Indicator

    Section 7 Cirrus Design Systems Description SR22 Serials 4164 & subs w/ MD302 Standby Attitude Module: The MD302 Standby Attitude Module is mounted on the LH bolster panel and gives backup indication of flight attitude. Bank attitude is indicated by a pointer at the top of the indicator relative to the bank scale with index marks at 0°...
  • Page 207 Cirrus Design Section 7 SR22 Systems Description precision airspeed indicator installed in the pilot's instrument panel. The instrument senses difference in static and Pitot pressures and displays the result in knots on an airspeed scale. A single pointer sweeps an indicated airspeed scale calibrated from 40 to 220 knots.
  • Page 208 Section 7 Cirrus Design Systems Description SR22 Standby Altimeter Serials w/o MD302 Standby Attitude Module: Airplane altitude is depicted 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 displays the result on the instrument in feet.
  • Page 209: Horizontal Situation Indicator

    Cirrus Design Section 7 SR22 Systems Description Horizontal Situation Indicator The horizontal situation indicator is displayed along the lower center of the PFD. Heading data is provided by the Attitude and Heading Reference System (AHRS) and the onboard magnetometers. The HSI displays a rotating compass card in a heading-up orientation.
  • Page 210: Magnetic Compass

    Section 7 Cirrus Design Systems Description SR22 Vertical speed must exceed 100 feet/min before digits will appear in the VSI pointer. If the rate of ascent/descent exceeds 2000 fpm, the pointer appears at the corresponding edge of the tape and the rate appears inside the pointer.
  • Page 211: Wing Flaps

    Cirrus Design Section 7 SR22 Systems Description Wing Flaps The electrically controlled, single-slotted flaps provide low-speed lift enhancement. Each flap is manufactured of aluminium and connected to the wing structure at three hinge points. Rub strips are installed on the top leading edge of each flap to prevent contact between the flap and wing flap cove.
  • Page 212 Section 7 Cirrus Design Systems Description SR22 SR22_FM07_2935A Figure 7-6 Wing Flaps 7-26 P/N 13772-004 Revision 1...
  • Page 213: Landing Gear

    Cirrus Design Section 7 SR22 Systems Description Landing Gear Main Gear The main landing gear are bolted to composite wing structure between the wing spar and shear web. The landing gear struts are constructed of composite material for fatigue resistance. The composite construction is both rugged and maintenance free.
  • Page 214 Section 7 Cirrus Design Systems Description SR22 Braking pressure is initiated by depressing the top half of a rudder pedal (toe brake). The brakes are plumbed so that depressing either the pilot’s or copilot’s left or right toe brake will apply the respective (left or right) main wheel brake.
  • Page 215: Baggage Compartment

    Cirrus Design Section 7 SR22 Systems Description Baggage Compartment The baggage compartment door, located on the left side of the fuselage aft of the wing, allows entry to the baggage compartment. The baggage door is hinged on the forward edge and latched on the rear edge.
  • Page 216: Seats

    Section 7 Cirrus Design Systems Description SR22 Seats The seating arrangement consists of two individually adjustable seats for the pilot and front seat passenger and a “2+1” configuration with a one-piece bench seat and fold-down seat backs for the rear seat passengers.
  • Page 217: Seat Belt And Shoulder Harness

    Cirrus Design Section 7 SR22 Systems Description forward from the baggage compartment. Recline position is controlled through a lever located on either side of the seat. To fold seat back forward: 1. With no pressure on the seat back, rotate the lever to the recline position and fold the seat back forward.
  • Page 218 Section 7 Cirrus Design Systems Description SR22 Front Seat Inflatable Restraints An inflatable shoulder harness is integral to each front seat harness. The electronic module assembly, mounted below the cabin floor, contains a crash sensor, battery, and related circuitry to monitor the deceleration rate of the airplane.
  • Page 219 Cirrus Design Section 7 SR22 Systems Description installed using the center seat belt. Three top tether anchors for the child seats are located on the rear bulkhead. To install a child seat: 1. Fasten lower seat attachments to bench seat: a.
  • Page 220: Cabin Doors

    Section 7 Cirrus Design Systems Description SR22 Cabin Doors Two large forward hinged doors allow crew and passengers to enter and exit the cabin. The door handles engage striker pins in the door frame receptacles at the upper aft and lower aft door perimeter. Gas charged struts provide assistance in opening the doors and hold the doors open against gusts.
  • Page 221: Engine

    Cirrus Design Section 7 SR22 Systems Description Engine The airplane is powered by a Teledyne Continental IO-550-N, six- cylinder, normally aspirated, fuel-injected engine rated to 310 hp at 2700 RPM. The engine has a 2000-hour Time Between Overhaul (TBO). Dual, conventional magnetos provide ignition.
  • Page 222: Engine Indicating

    Section 7 Cirrus Design Systems Description SR22 control, depress the center lock button, pull the knob to the open position, and then release the lock button. Pulling the knob opens the alternate air induction door on the engine induction air manifold, bypasses the air filter, and allows warm unfiltered air to enter the engine.
  • Page 223 Cirrus Design Section 7 SR22 Systems Description Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Engine Instruments LEGEND 1. Percent Power 2. CHT 3. Tachometer 4. EGT 5. Manifold Pressure 6. Oil Temperature and Pressure 7. Alternate Air Control 8.
  • Page 224 Section 7 Cirrus Design Systems Description SR22 Tachometer Engine speed (RPM) is shown in the upper mid-left corner of the ENGINE page as both a simulated tachometer and as a digital value. The tachometer pointer sweeps a scale range from 0 to 3000 RPM in 100 RPM increments.
  • Page 225 Cirrus Design Section 7 SR22 Systems Description Oil Temperature Oil temperature is shown in the upper right corner of the ENGINE page, opposite the oil pressure scale, as both a simulated temperature gage and as a digital value. The gage pointer sweeps a scale range from 75°F to 250°F in 50°F increments.
  • Page 226: Engine Lubrication System

    Section 7 Cirrus Design Systems Description SR22 Engine Lubrication System The engine is provided with a wet-sump, high-pressure oil system for engine lubrication and cooling. Oil for engine lubrication is drawn from an eight-quart capacity sump through an oil suction strainer screen and directed through the oil filter to the engine-mounted oil cooler by a positive displacement oil pump.
  • Page 227: Engine Exhaust

    Cirrus Design Section 7 SR22 Systems Description through the throttle butterfly, into the six-tube engine manifold, and finally through the cylinder intake ports into the combustion chambers. Should the dry induction filter become clogged, a pilot controlled alternate induction air door can be opened, allowing engine operation to continue as described below.
  • Page 228: Propeller

    Section 7 Cirrus Design Systems Description SR22 Propeller The airplane is equipped with a constant-speed, aluminum-alloy propeller with a three-blade (78" diameter) propeller and governor. The propeller governor automatically adjusts propeller pitch to regulate propeller and engine RPM. The propeller governor senses...
  • Page 229: Fuel System

    Cirrus Design Section 7 SR22 Systems Description Fuel System An 92-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 47.25-gallon capacity (46- gallon usable) vented integral fuel tank and a fuel collector/sump in each wing, a three position selector valve, an electric fuel pump, and an engine-driven fuel pump.
  • Page 230: Fuel Selector Valve

    Section 7 Cirrus Design Systems Description SR22 Drain valves at the system low points allow draining the system for maintenance and for examination of fuel in the system for contamination and grade. The fuel must be sampled prior to each flight.
  • Page 231 Cirrus Design Section 7 SR22 Systems Description ANNUNCIATOR FUEL FUEL QUANTITY VENT VENT FILLER FILLER INDICATOR L. WING TANK R. WING TANK R. WING L. WING COLLECTOR COLLECTOR CHECK CHECK VALVE VALVE SELECTOR VALVE FLAPPER FLAPPER VALVE VALVE DRAIN (5 PLACES)
  • Page 232: Fuel Indicating

    Section 7 Cirrus Design Systems Description SR22 Fuel Indicating Fuel quantity is measured by float-type quantity sensors installed in each fuel tank and displayed on the Engine Strip along the left edge of the MFD and in the Fuel Qty block on the MFD’s Engine page.
  • Page 233 Cirrus Design Section 7 SR22 Systems Description block. The fuel flow signal is sent to the Engine Airframe Unit, processed, and transmitted to the Engine Indicating System for display. Fuel Totalizer and Calculated Information Fuel totalizer calculations are located in the lower right section of the ENGINE page and are separate and independent of the fuel quantity gage and float sensor system.
  • Page 234 Section 7 Cirrus Design Systems Description SR22 Fuel System Annunciations Fuel 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 Altimeter and Vertical Speed Indicator. In combination...
  • Page 235 Cirrus Design Section 7 SR22 Systems Description Fuel System Indication 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 (Totalizer) 3. Fuel Quantity Gage (Float Sensor) 4.
  • Page 236: Mixture Management

    Section 7 Cirrus Design Systems Description SR22 Mixture Management The mixture control needs to be carefully monitored and managed during all phases of flight to avoid damage to the engine or a possible loss of power. After engine start, and during taxiing operations, lean the mixture until maximum engine RPM is attained to prevent possible spark plug fouling and ensure smooth engine operation.
  • Page 237: Electrical System

    Cirrus Design Section 7 SR22 Systems Description Electrical System The airplane is equipped with a two-alternator, two-battery, 28-volt direct current (VDC) electrical system designed to reduce the risk of electrical system faults. The system provides uninterrupted power for avionics, flight instrumentation, lighting, and other electrically operated and controlled systems during normal operation.
  • Page 238 Section 7 Cirrus Design Systems Description SR22 LANDING 100A ALT 1 LIGHT ALT 1 7.5A VOLT REG RELAY LANDING LIGHT SWITCH EXTERNAL ALT 1 POWER RELAY SWITCH EXTERNAL POWER 125A BAT 1 BAT 1 BAT 1 SWITCH RELAY STARTER STARTER...
  • Page 239 Cirrus Design Section 7 SR22 Systems Description LANDING 100A ALT 1 LIGHT ALT 1 7.5A VOLT REG RELAY LANDING LIGHT EXTERNAL SWITCH POWER RELAY ALT 1 EXTERNAL SWITCH POWER 125A BAT 1 BAT 1 BAT 1 SWITCH RELAY STARTER STARTER...
  • Page 240: Power Distribution

    Section 7 Cirrus Design Systems Description SR22 Power Distribution Power is supplied to the airplane circuits through three distribution buses contained in the MCU: Main Distribution Bus 1, Main Distribution Bus 2, and the Essential Distribution Bus. The three distribution buses power the associated buses on the circuit breaker panel.
  • Page 241: Electrical System Protection

    Cirrus Design Section 7 SR22 Systems Description Main Distribution Bus 2 The output from ALT 2 is connected to the Main Distribution Bus 2 in the MCU through an 80-amp fuse. Main Distribution Bus 2 powers three circuit breaker buses through 30-amp fuses located in the MCU: •...
  • Page 242 Section 7 Cirrus Design Systems Description SR22 through 30-amp fuses inside the MCU and also by BAT 2 through the 20-amp BAT 2 circuit breaker. In the event of ALT 1 or ALT 2 failure, the Essential Buses in the circuit breaker panel will be powered by the remaining alternator through the Main Distribution Bus 1 or Main Distribution Bus 2 in the MCU.
  • Page 243 Cirrus Design Section 7 SR22 Systems Description AVIONICS A/C COND PROTECTION STDBY ALT1 ALT2 ATTD #2 ENGINE MFD #2 SERVO INSTR STALL CABIN LIGHTS CAMERA WARNING / OXYGEN 12V DC ROLL FUEL QTY OUTLET TRIM PITCH A/C COMPR MFD #1...
  • Page 244 Section 7 Cirrus Design Systems Description SR22 AVIONICS PROTECT B PROTECT A RECOG STDBY ALT2 LIGHTS ATTD #2 CONV ENGINE MFD #2 LIGHTS SERVO INSTR STALL CABIN LIGHTS A/C COND CAMERA WARNING / OXYGEN 12V DC ROLL ALT 1 FUEL QTY...
  • Page 245: Electrical System Control

    Cirrus Design Section 7 SR22 Systems Description Electrical System Control The rocker type electrical system MASTER switches are ‘on’ in the up position and ‘off’ in the down position. The switches, labeled BAT 2, BAT 1, ALT 1, ALT 2 are located in the bolster switch panel immediately below the instrument panel.
  • Page 246: Ground Service Receptacle

    Section 7 Cirrus Design Systems Description SR22 Avionics Power Switch A rocker switch, labeled AVIONICS, controls electrical power from the circuit breaker panel (MAIN BUS 1) to the Avionics Bus. The switch is located next to the ALT and BAT Master switches. Typically, the switch is used to energize or de-energize all non-essential avionics on the AVIONICS bus simultaneously.
  • Page 247: Electrical Indicating

    Cirrus Design Section 7 SR22 Systems Description Electrical Indicating Electrical system information is displayed as bar graphs and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), Battery 1 ampere output and Essential Bus voltage output are displayed along the LH edge of the display.
  • Page 248 Section 7 Cirrus Design Systems Description SR22 Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Electrical System Indication 8 9 10 Electrical and Lighting Controls LEGEND 7. Avionics 1. Essential & Main Bus Voltage 2. Alternator & Battery Current 8.
  • Page 249: Lighting Systems

    Cirrus Design Section 7 SR22 Systems Description Lighting Systems Exterior Lighting The airplane is equipped with wing tip navigation lights with integral anti-collision strobe lights and recognition Lights. The landing light is located in the lower cowl. Navigation Lights The airplane is equipped with standard wing tip navigation lights. The lights are controlled through the NAV light switch on the instrument panel bolster.
  • Page 250: Interior Lighting

    Section 7 Cirrus Design Systems Description SR22 Interior Lighting Interior lighting for the airplane consists of overhead lights for general cabin lighting, individual lights for the pilots and passengers, and dimmable panel floodlights. The flight instrumentation and avionics equipment lights are dimmable.
  • Page 251 Cirrus Design Section 7 SR22 Systems Description Panel Flood Lights A string of red LEDs mounted under the instrument panel glareshield provide flood lighting for the instrument panel. The lights are controlled through the PANEL dimmer control on the instrument panel bolster.
  • Page 252: Convenience Lighting

    Section 7 Cirrus Design Systems Description SR22 Convenience Lighting Serials 4300 & subs w/ Convenience Lighting: The convenience lighting option consists of the overhead dome light, overhead baggage compartment lights, interior footwell lights, exterior entry step lights, and a key fob.
  • Page 253 Cirrus Design Section 7 SR22 Systems Description Convenience Lighting Operation When the cabin light switch is in the ON position: • Dome light and footwell lights will turn on. • Entry step lights will turn on when either cabin door is opened or...
  • Page 254: Environmental System

    Section 7 Cirrus Design Systems Description SR22 Environmental System • Note • To facilitate faster cabin cooling, prior to engine start leave the cabin doors open for a short time to allow hot air to escape. Standard cabin heating and ventilation is accomplished by supplying conditioned air from the heat exchanger for heating and windshield defrost and fresh outside air for ventilation.
  • Page 255: Distribution

    Cirrus Design Section 7 SR22 Systems Description Distribution Ventilation and cooling is provided by ducting fresh air from a NACA inlet on the RH lower cowl to the mixing chamber located on the lower RH portion of the firewall. Depending on operating mode and...
  • Page 256: Cooling

    Section 7 Cirrus Design Systems Description SR22 Cooling Standard cabin cooling is provided by ram air admitted through the NACA inlet on the RH cowl to the fresh air valve, mounted to the forward side of the firewall. When the fresh air valve is open, the air flows into the cabin mixing chamber.
  • Page 257 Cirrus Design Section 7 SR22 Systems Description RAM AIR RAM AIR HOT AIR VALVE MIXING CHAMBER HEAT EXCHANGER FRESH AIR VALVE AIR FLOW VALVE CONTROL PANEL SERVO MOTOR FLOOR AIRFLOW WINDSHIELD DIFFUSER PANEL AIRFLOW DISTRIBUTION MANIFOLD AIR GASPER ASSEMBLY FOOT-WARMER...
  • Page 258 Section 7 Cirrus Design Systems Description SR22 RAM AIR RAM AIR HOT AIR VALVE MIXING CHAMBER HEAT EXCHANGER COMPRESSOR FRESH AIR VALVE WINDSHIELD AIR FLOW VALVE DIFFUSER SERVO MOTOR FLOOR AIRFLOW CONTROL PANEL PANEL AIRFLOW DISTRIBUTION MANIFOLD GASPER EVAPORATOR ASSEMBLY...
  • Page 259: Airflow Selection

    Cirrus Design Section 7 SR22 Systems Description Airflow Selection The airflow selector on the system control panel regulates the volume of airflow allowed into the cabin distribution system. When the airflow selector is moved past the OFF position an electro-mechanical linkage actuates a valve in the mixing chamber on the forward firewall to the full open position.
  • Page 260: Temperature Selection

    Section 7 Cirrus Design Systems Description SR22 Temperature Selection The temperature selector is electrically linked to the hot and cold air valves. Rotating the selector simultaneously opens and closes the two valves, permitting hot and cold air to mix and enter the distribution system.
  • Page 261 Cirrus Design Section 7 SR22 Systems Description Rotating the selector controls the volume of airflow allowed into the cabin distribution system through use of an electro-mechanical linkage to a butterfly (hot air) valve in the mixing chamber on the forward firewall.
  • Page 262: Stall Warning System

    Section 7 Cirrus Design Systems Description SR22 Stall Warning System The airplane is equipped with an electro-pneumatic stall warning system to provide audible warning of an approach to aerodynamic stall. The system consists of an inlet in the leading edge of the right wing, a pressure switch and associated plumbing, and the avionics system aural warning system.
  • Page 263: Pitot-Static System

    Cirrus Design Section 7 SR22 Systems Description Pitot-Static System The Pitot-Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage. The Pitot heat is pilot controlled through a panel-mounted switch. An internally mounted alternate static pressure source provides backup static pressure should that the primary static source becomes blocked.
  • Page 264 Section 7 Cirrus Design Systems Description SR22 AIR DATA COMPUTER 2 (optional) AIR DATA COMPUTER PFD Air Data AIRSPEED INDICATOR ALTIMETER ALTERNATE PITOT-STATIC STATIC WATER TRAPS AIR SOURCE PITOT MAST STATIC HEATER BUTTONS Annunciation PITOT HEAT CURRENT SENSOR LOGIC PITOT 7.5A...
  • Page 265 Cirrus Design Section 7 SR22 Systems Description AIR DATA COMPUTER 2 (optional) AIR DATA COMPUTER PFD Air Data MD302 STANDBY ATTITUDE MODULE ALTERNATE PITOT-STATIC STATIC WATER TRAPS AIR SOURCE PITOT MAST STATIC HEATER BUTTONS Annunciation PITOT HEAT CURRENT SENSOR LOGIC PITOT 7.5A...
  • Page 266: Avionics

    Section 7 Cirrus Design Systems Description SR22 Avionics Perspective Integrated Avionics System The Perspective Integrated Avionics System provides advanced cockpit functionality and improved situational awareness through the use of fully integrated flight, engine, communication, navigation and monitoring equipment. The system consists of the following components: •...
  • Page 267 Cirrus Design Section 7 SR22 Systems Description XM RADIO RECEIVER (optional) XM SATELLITE DATA LINK RECEIVER (optional) FMS KEYBOARD MAG 1 MAG 2 AHRS 1 AHRS 2 AUTOPILOT (optional) MODE CONTROLLER IRIDIUM GLOBAL SATELLITE DATALINK AIR DATA (optional) COMPUTER 2...
  • Page 268 Section 7 Cirrus Design Systems Description SR22 GDU Primary Flight Display The Primary Flight Display, located directly in front of the pilot, is intended to be the primary display of flight parameter information (attitude, airspeed, heading, and altitude) during normal operations.
  • Page 269 Cirrus Design Section 7 SR22 Systems Description 3 and the 5-amp MFD 2 circuit breaker on MAIN BUS 1. Either circuit is capable of powering the MFD. System start-up is automatic once power is applied. Power-on default brightness is determined by ambient lighting and is user adjustable.
  • Page 270 Section 7 Cirrus Design Systems Description SR22 3 4 5 6 7 8 9 13 14 15 19 20 21 Legend 1. Soft Keys 11. NAV Transceiver Selection & Tune 2. PFD 12. MFD 3. PFD Range/Pan Joystick 13. PFD Direct-to-Course 4.
  • Page 271 Cirrus Design Section 7 SR22 Systems Description 22 23 25 26 27 28 29 30 31 GARMIN IDENT FMS/XPDR RANGE MENU XPDR COM/NAV PROC DFLT MAP PUSH SYNC PUSH PUSH EMERG CRSR/1-2 PUSH CTR ALT SEL BKSP PUSH SYNC Flight Management System Keyboard Legend 22.
  • Page 272 Section 7 Cirrus Design Systems Description SR22 GIA 63W Integrated Avionics Units The Integrated Avionics Units, located behind the MFD and instrument panel, function as the main communication hub, linking all Integrated Avionics System components with the PFD. Each Integrated Avionics...
  • Page 273 Cirrus Design Section 7 SR22 Systems Description GMA 350 Audio Panel with Marker Beacon Receiver The 350 Audio Panel, installed on the center console below the Flight Management System Keyboard, integrates NAV/COM digital audio, intercom and marker beacon controls. The VHF communications...
  • Page 274 Section 7 Cirrus Design Systems Description SR22 GFC 700 3-Axis Autopilot and GMC 705 Autopilot Controller Refer to latest revision of AFM Supplement 13772-135 GFC 700 Automatic Flight Control System for operating information. 7-88 P/N 13772-004 Revision 1...
  • Page 275: Optional Avionics

    Cirrus Design Section 7 SR22 Systems Description Optional Avionics GTX 33 Mode S and GTX 33 ES Mode S Transponders The GTX 33 Mode S and GTX 33 ES Mode S solid-state transponders communicate with the primary Integrated Avionics Unit and provide Modes A, C, and S interrogation/reply capabilities.
  • Page 276 Section 7 Cirrus Design Systems Description SR22 GDL 69/69A XM Satellite Weather and Radio The Data Link Satellite Receiver, mounted in the empennage avionics compartment, receives and transmits real-time weather information to the MFD and PFD. If GDL 69A option is installed, this unit also...
  • Page 277 Cirrus Design Section 7 SR22 Systems Description Stormscope WX-500 Weather Mapping Sensor The Stormscope WX-500 System detects electrical discharges associated with thunderstorms and displays the activity on the MFD. The system consists of an antenna located on top of the fuselage and a processor unit mounted under the aft baggage floor.
  • Page 278 Section 7 Cirrus Design Systems Description SR22 DME/ADF circuit breaker on AVIONICS BUS. Refer to the Perspective Integrated Avionics System Pilot’s Guide for a general description of the system and its operating modes. Refer to the Bendix/King DME System Pilot’s Guide for a detailed discussion of the system.
  • Page 279 Cirrus Design Section 7 SR22 Systems Description Max Viz Enhanced Vision System The Enhanced Vision System is an electro-optical system that uses a Long-Wave Infrared (IR) camera. Infrared is particularly effective at night, smoke, haze, and smog in addition to a broad spectrum of rain, snow, and radiation-type fog.
  • Page 280 Section 7 Cirrus Design Systems Description SR22 Approach Baro-VNAV While executing an LNAV/VNAV approach with SBAS unavailable, Baro-VNAV is used for vertical approach guidance. This occurs due to any of the following conditions: • SBAS fails or becomes unavailable prior to final approach fix (FAF) •...
  • Page 281 Cirrus Design Section 7 SR22 Systems Description message will be displayed on the PFDs and the vertical deviation indicator (VDI) will be flagged. If SBAS is required for the approach, the approach mode (e.g. LPV) will be shown in amber but the GPS/ SBAS VDI will be displayed until 60 seconds prior to the FAF.
  • Page 282 Section 7 Cirrus Design Systems Description SR22 29.92 LEGEND NOTE 1.Excessive Deviation While Baro-VNAV is being utilized, Indicator the Glidepath Indicator appears as 2.Glidepath Indicator a magenta pentagon. SR22_FM02_3686 Figure 7-19 Baro-VNAV Vertical Deviation Indicator 7-96 P/N 13772-004 Revision 1...
  • Page 283 Cirrus Design Section 7 SR22 Systems Description LEGEND 1. AHRS 1 2. Integrated Avionics Unit 1 3. AHRS 2 4. Avionics Cooling Fan 5. Integrated Avionics Unit 2 6. Engine Airframe Unit 7. Air Data Computer 2 (opt) 8. Air Data Computer 1 9.
  • Page 284: Avionics Support Equipment

    Section 7 Cirrus Design Systems Description SR22 Avionics Support Equipment Antennas Two rod-type COM antennas are mounted to the airplane’s exterior; COM 1 is mounted directly above the passenger compartment, COM 2 is mounted directly below the baggage compartment. These antennas are connected to the two VHF communication transceivers contained in the Integrated Avionics Units.
  • Page 285 Cirrus Design Section 7 SR22 Systems Description Headset and Microphone Installation The airplane is equipped with provisions for five Active Noise Reduction (ANR) and three conventional (MIC/HEADPHONES) headsets. Headset jacks for the pilot, front, and rear seat passenger are located in the map case.
  • Page 286 Section 7 Cirrus Design Systems Description SR22 Cell Phone Input Jack One 2.5 mm cell phone jack is located on the front of the audio panel and is distributed by selecting the Entertainment button (shown as a phone and music-note symbol) on the audio panel. Volume is...
  • Page 287: Cabin Features

    Cirrus Design Section 7 SR22 Systems Description Cabin Features Emergency Locator Transmitter The airplane is equipped with a self-contained emergency locator transmitter (ELT). The transmitter and antenna are installed immediately behind the aft cabin bulkhead, slightly to the right of the airplane centerline.
  • Page 288 Section 7 Cirrus Design Systems Description SR22 b. Disconnect fixed antenna lead from front of unit. c. Disconnect lead from remote switch and indicator unit. d. Loosen attach straps and remove transmitter unit and portable antenna. e. Attach portable antenna to antenna jack on front of unit.
  • Page 289: Hour Meters

    Cirrus Design Section 7 SR22 Systems Description of ensuring that the nozzle is unobstructed, the pin has not been pulled, and the canister has not been damaged. Serials w/o gaged fire extinguisher: The unit should weigh approximately 1.5 lb (0.7 kg). For preflight, charge can be determined by ‘hefting’...
  • Page 290 Section 7 Cirrus Design Systems Description SR22 center console for use by the rear passengers. The ports comply with USB Battery Charging 1.2 Compliance Plan, and are intended for USB-compatible devices only. There is no data or audio access at the ports.
  • Page 291: System Description

    Systems Description Cirrus Airframe Parachute System The airplane is equipped with a Cirrus Airframe Parachute System (CAPS) designed to bring the airplane and its occupants to the ground in the event of a life-threatening emergency. The system is intended to...
  • Page 292: Activation Handle

    Section 7 Cirrus Design Systems Description SR22 A three-point harness connects the airplane fuselage structure to the parachute. The aft harness strap is stowed in the parachute canister and attached to the structure at the aft baggage compartment bulkhead. The forward harness straps are routed from the canister to firewall attach points just under the surface of the fuselage skin.
  • Page 293: Deployment Characteristics

    Cirrus Design Section 7 SR22 Systems Description A maintenance safety pin is provided to ensure that the activation handle is not pulled during maintenance. However, there may be some circumstances where an operator may wish to safety the CAPS system; for example, the presence of unattended children in the airplane, the presence of people who are not familiar with the CAPS activation system in the airplane, or during display of the airplane.
  • Page 294 Section 7 Cirrus Design Systems Description SR22 stress, occupants must prepare for it in accordance with Section 3 - CAPS Deployment Checklist. • 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 other than those described above.
  • Page 295 Airworthiness Directives..............6 Airplane Inspection Periods ............... 6 Annual Inspection ................6 100-Hour Inspection ............... 7 Cirrus Design Progressive Inspection Program ......7 Pilot Performed Preventative Maintenance ........8 Ground Handling ................10 Application of External Power ............10 Towing ..................11 Taxiing ..................
  • Page 296 Section 8 Cirrus Design Handling and Servicing SR22 Intentionally Left Blank P/N 13772-004 Original Issue...
  • Page 297: Introduction

    This section provides general guidelines for handling, servicing and maintaining your aircraft. In order to ensure continued safe and efficient operation of your airplane, keep in contact with your Authorized Cirrus Service Center to obtain the latest information pertaining to your aircraft. Operator’s Publications The FAA Approved Airplane Flight Manual and Pilot’s Operating...
  • Page 298: Obtaining Publications

    Service Bulletin. Give careful attention to the Service Advisory information. Obtaining Publications Pilot’s Operating Handbooks and aircraft service publications can be obtained from Cirrus Design at www.cirrusaircraft.com, or the Cirrus Connection at www.cirrusconnection.com. P/N 13772-004 Revision 1...
  • Page 299: Airplane Records And Certificates

    Cirrus Design Section 8 SR22 Handling and Servicing Airplane Records and Certificates The Federal Aviation Administration (FAA) requires that certain data, certificates, and licenses be displayed or carried aboard the airplane at all times. Additionally, other documents must be made available upon request.
  • Page 300: Airworthiness Directives

    AD’s are mandatory changes and must be complied with within a time limit set forth in the AD. Operators should periodically check with Cirrus Service Centers or A&P mechanic to verify receipt of the latest issued AD for their airplane.
  • Page 301: 100-Hour Inspection

    In lieu of the above requirements, an airplane may be inspected using a Progressive Inspection Program in accordance with the Federal Aviation Regulation Part 91.409. The Cirrus Design Progressive Inspection Program provides for the complete inspection of the airplane utilizing a five-phase cyclic inspection program.
  • Page 302: Pilot Performed Preventative Maintenance

    Section 8 Cirrus Design Handling and Servicing SR22 Pilot Performed Preventative Maintenance The holder of a Pilot Certificate issued under FAR Part 61 may perform certain preventive maintenance described in FAR Part 43, Appendix A. This maintenance may be performed only on an aircraft that the pilot owns or operates and which is not used in air carrier service.
  • Page 303 Cirrus Design Section 8 SR22 Handling and Servicing • Replace any hose connection, except hydraulic connections, with replacement hoses. • Clean or replace fuel and oil strainers, as well as replace or clean filter elements. • Replace prefabricated fuel lines.
  • Page 304: Ground Handling

    Section 8 Cirrus Design Handling and Servicing SR22 Ground Handling Application of External Power A ground service receptacle, located just aft of the cowl on the left side of the airplane, permits the use of an external power source for cold weather starting and maintenance procedures.
  • Page 305: Towing

    Cirrus Design Section 8 SR22 Handling and Servicing Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed in the rear baggage compartment or by power equipment that will not damage or excessively strain the nose gear assembly.
  • Page 306: Taxiing

    Section 8 Cirrus Design Handling and Servicing SR22 Taxiing Before attempting to taxi the airplane, ground personnel should be instructed and authorized by the owner to taxi the airplane. Instruction should include engine starting and shutdown procedures in addition to taxi and steering techniques.
  • Page 307: Parking

    Cirrus Design Section 8 SR22 Handling and Servicing Parking The airplane should be parked to protect the airplane from weather and to prevent it from becoming a hazard to other aircraft. The parking brake may release or exert excessive pressure because of heat buildup after heavy braking or during wide temperature swings.
  • Page 308: Tiedown

    Section 8 Cirrus Design Handling and Servicing SR22 Tiedown The airplane should be moored for immovability, security and protection. FAA Advisory Circular AC 20-35C, Tiedown Sense, contains additional information regarding preparation for severe weather, tiedown, and related information. The following procedures should be used for the proper mooring of the airplane: 1.
  • Page 309 Cirrus Design Section 8 SR22 Handling and Servicing Raise Airplane • Caution • Do not jack the aircraft outside or in open hangar with winds in excess of 10 mph. The empty CG is forward of the wing jacking points. To...
  • Page 310: Servicing

    Section 8 Cirrus Design Handling and Servicing SR22 Servicing Landing Gear Servicing Serials 3915 thru 4030, 4032, 4045 before SB2X-32-21: The main landing gear wheel assemblies use 15 x 6.00 x 6 tires and tubes. The nose wheel assembly uses a 5.00 x 5 tire and tube.
  • Page 311: Tire Inflation

    Cirrus Design Section 8 SR22 Handling and Servicing Tire Inflation For maximum service from the tires, keep them inflated to the proper pressure. When checking tire pressure, examine the tires for wear, cuts, nicks, bruises and excessive wear. To inflate tires: 1.
  • Page 312: Oil Servicing

    Section 8 Cirrus Design Handling and Servicing SR22 Oil Servicing The oil capacity of the Teledyne Continental IO-550-N engine is 8 quarts. It is recommended that the oil be changed every 50 hours and sooner under unfavorable operating conditions. The following grades...
  • Page 313 Cirrus Design Section 8 SR22 Handling and Servicing Product Supplier Aeroshell (R) W Shell Australia Aeroshell Oil W Shell Canada Ltd. Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50 Aeroshell Oil W Shell Oil Company Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50...
  • Page 314: Fuel System Servicing

    Section 8 Cirrus Design Handling and Servicing SR22 Fuel System Servicing Fuel Filtration Screen/Element After the first 25 hours of operation, then every 50-hours or as conditions dictate, the fuel filtration screen in the gascolator must be cleaned. After cleaning, a small amount of grease applied to the gascolator bowl gasket will facilitate reassembly.
  • Page 315: Fuel Contamination And Sampling

    Cirrus Design Section 8 SR22 Handling and Servicing To refuel airplane: 1. Place fire extinguisher near fuel tank being filled. 2. Connect ground wire from refuel nozzle to airplane exhaust, from airplane exhaust to fuel truck or cart, and from fuel truck or cart to a suitable earth ground.
  • Page 316: Draining Fuel System

    Section 8 Cirrus Design Handling and Servicing SR22 If sampling reveals contamination, the gascolator and tank drains must be sampled again repeatedly until all contamination is removed. It is helpful to gently rock the wings and lower the tail slightly to move contaminates to the drain points for sampling.
  • Page 317: Oxygen System Servicing

    Service the oxygen system per the appropriate revision of the Precise Flight Instructions for Continued Airworthiness for the Cirrus SR22/ SR22T Built-In Oxygen System, STC number SA01708SE, document number 102NPMAN0003.
  • Page 318: Cleaning And Care

    Section 8 Cirrus Design Handling and Servicing SR22 Cleaning and Care Cleaning Exterior Surfaces • Caution • Airplane serials with Ice Protection System: Do not wax leading edge porous panels. Refer to Section 9: Log of Supplements of this handbook for instructions and limitations for airplanes equipped with the Ice Protection System.
  • Page 319 Cirrus Design Section 8 SR22 Handling and Servicing Cleaning Product Cleaning Application Supplier Pure Carnauba Wax Fuselage Exterior Any Source Mothers California Gold Fuselage Exterior Wal-Mart Stores Pure Carnauba Wax RejeX Fuselage Exterior Corrosion Technologies WX/Block System Fuselage Exterior Wings and Wheels...
  • Page 320: Care Of Graphics

    Section 8 Cirrus Design Handling and Servicing SR22 Care of Graphics Graphics require care similar to any fine paint finish. Use high quality products designed specifically for use on automobile finishes. Use products in accordance with the manufacturer’s instructions. Exposure to Environmental Conditions Graphics, like paint, are degraded by prolonged exposure to sun and atmospheric pollutants.
  • Page 321 Cirrus Design Section 8 SR22 Handling and Servicing • Caution • Holding the nozzle of a pressure washer at an angle less than 90 degrees to the graphic may lift the edges of the graphic. 4. Keep the spray nozzle perpendicular to the graphic, and at a distance of at least 1 foot (30 cm).
  • Page 322 Section 8 Cirrus Design Handling and Servicing SR22 Cleaning Fuel Spills • Caution • Immediately clean fuel spills to avoid degrading the vinyl and adhesive used in the graphic. 1. Wipe off spilled fuel. 2. Clean graphic with a wet, non-abrasive detergent such as 3M™...
  • Page 323 Cirrus Design Section 8 SR22 Handling and Servicing Graphic Restoration If typical cleaning methods fail to produce satisfactory results, refer to the recommended restoration products and mixtures below to help preserve the condition of the graphics on your aircraft. • Caution •...
  • Page 324 Section 8 Cirrus Design Handling and Servicing SR22 Windscreen and Windows Before cleaning an acrylic window, rinse away all dirt particles before applying cloth or chamois. Never rub dry acrylic. Dull or scratched window coverings may be polished using a special acrylic polishing paste.
  • Page 325 Cirrus Design Section 8 SR22 Handling and Servicing Do not use abrasive cleansers or cleaning pads on the germanium window. Abrasive cleaning can damage the sensor window coating. Do not use any cleansers containing ammonia. Ammonia will remove the sensor window coating.
  • Page 326: Cleaning Interior Surfaces

    Section 8 Cirrus Design Handling and Servicing SR22 3. Allow the solvent to remain on the gear from five to ten minutes. Then rinse the gear with additional solvent and allow to dry. 4. Remove the cover from the wheel and remove the catch pan.
  • Page 327 Cirrus Design Section 8 SR22 Handling and Servicing Cleaning Product Cleaning Application Supplier Prist Interior Windscreen and Prist Aerospace Windows Optimax Display Screens PhotoDon Mild Dishwasher Soap Cabin Interior Any Source (abrasive free) Leather Care Kit Leather Upholstery Cirrus Design...
  • Page 328 Section 8 Cirrus Design Handling and Servicing SR22 Instrument Panel and Electronic Display Screens The instrument panel, control knobs, and plastic trim need only to be wiped clean with a soft damp cloth. The multifunction display, primary flight display, and other electronic display screens should be cleaned with Optimax - LCD Screen Cleaning Solution as follows: •...
  • Page 329 For deeper cleaning, start with mix of mild detergent and water then, if necessary, work your way up to the products available from Cirrus for more stubborn marks and stains. Do not use soaps as they contain alkaline which will alter the leather’s pH balance and cause the leather to age prematurely.
  • Page 330 Section 8 Cirrus Design Handling and Servicing SR22 Intentionally Left Blank 8-36 P/N 13772-004 Revision 1...
  • Page 331 09-24-13 ___ 13772-119 SR22 Airplanes Registered in Israel 12-03-03 ___ 13772-122 R1 SR22 / SR22T Airplanes Registered in European Union 07-07-10 ___ 13772-131 R2 Artex ME406 406 MHz ELT System 01-06-10 ___ 13772-135 R4 GFC 700 Automatic Flight Control System...
  • Page 332 This Log of Supplements shows all Cirrus Design Supplements available for the aircraft at the corresponding date of the revision level shown in the lower left corner. A check mark in the Part Number column indicates that the supplement is applicable to the POH.
  • Page 333 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement Approved Oxygen Systems When supplemental oxygen is required by the applicable operating rules (FAR Part 91 or FAR Part 135), this Supplement is applicable and must be inserted in the Supplements Section of the Pilot’s...
  • Page 334 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General This supplement lists the approved portable oxygen systems that may be used in the aircraft when supplemental oxygen is required by the applicable operating rules, as well as provides mounting instructions and general operating procedures for all approved systems.
  • Page 335 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3 - Emergency Procedures Smoke and Fume Elimination In addition to the procedures outlined in the basic Handbook, pilot and passengers should don cannulas or masks and use oxygen at the maximum flow rate until smoke and fumes have cleared.
  • Page 336 Section 9 Cirrus Design Supplements SR22 / SR22T Descent After airplane descends through altitude requiring oxygen: 1. Oxygen Shutoff Valve...............OFF 2. Pilot and passengers....... Stow Masks or Cannulas Section 5 - Performance No change from basic Handbook. Section 6 - Weight & Balance The weight, arm, and moment for fully charged systems (1800 –...
  • Page 337 Cirrus Design Section 9 SR22 / SR22T Supplements INITIAL INSTALLATION Clip strap to triangular loop as shown in Detail A. Route strap over headrest, down TUFF PACK BAG the back of the seat, and forward between the cushion and seat back. Clip strap to lower triangular loop.
  • Page 338 Section 9 Cirrus Design Supplements SR22 / SR22T OXYGEN DURATION - HOURS Fully Charged System (1800 psig at 70° F) Number of Altitude ~ Feet System Persons Typical Using O 10,000 15,000 18,000 25,000 (Liters) 2.23 1.49 1.24 0.89 XCP-180 1.12...
  • Page 339 Supplement SR22 / SR22T Airplanes Registered in the European Union 1. This supplement is required for operation of Cirrus Design SR22 serial numbers 0002 and subsequent and SR22T serial numbers 0001 and subsequent when registered in the European Union. This supplement must be attached to the applicable SR22 and SR22T EASA/FAA-approved Airplane Flight Manuals.
  • Page 340 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General No Change. Section 2 - Limitations No Change. Section 3 - Emergency Procedures No Change. Section 4 - Normal Procedures Noise Characteristics/Abatement Serials 22T-0001 and subsequent: The certificated noise levels for the...
  • Page 341 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement Artex ME406 406 MHz ELT System When Artex ME406 406 MHz ELT System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements Section of the Pilot’s Operating Handbook.
  • Page 342 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General The 406 MHz emergency locator transmitter (ELT) is a radio- frequency transmitter that generates a signal to assist in search and rescue for missing aircraft. The ELT automatically transmits the standard sweep tone on 121.5 MHz if rapid deceleration is detected.
  • Page 343 Cirrus Design Section 9 SR22 / SR22T Supplements containing aircraft specific information is transmitted at 50 seconds for 440 milliseconds. CIRCUIT BREAKER PANEL ALT AIR BRACKET (REF) MOUNTING TRAY (REF) LEGEND 1. LED Annunciator 2. Remote Switch 3. Antenna 4 Remote Cable 5.
  • Page 344 Section 9 Cirrus Design Supplements SR22 / SR22T Section 2 - Limitations No Change. Section 3 - Emergency Procedures Forced Landing Before performing a forced landing activate the ELT transmitter manually by turning the ELT remote switch to the 'ON'-position.
  • Page 345 Cirrus Design Section 9 SR22 / SR22T Supplements Portable Use of ELT The ELT transmitter can be removed from the airplane and used as a personal locating device if it is necessary to leave the airplane after an accident. Access the unit as described below and set the ELT transmitter control switch to the 'ON'-position.
  • Page 346 Section 9 Cirrus Design Supplements SR22 / SR22T Section 7 - Systems Description This airplane is equipped with a self-contained Artex ME406 406 MHz ELT System. The transmitter unit is automatically activated upon sensing a change of velocity along its longitudinal axis exceeding 4 to 5 feet per second.
  • Page 347 Cirrus Design Section 9 SR22 / SR22T Supplements Section 8 - Handling, Servicing & Maintenance ELT and RCPI batteries must be inspected in accordance with the Airplane Maintenances Manual, 5-20 - Scheduled Maintenance Checks. The ELT and RCPI batteries must be replaced upon reaching the date...
  • Page 348 Section 9 Cirrus Design Supplements SR22 / SR22T does not check the integrity of the ELT system or provide the same level of confidence as does an AM radio. 1. Tune aircraft receiver to 121.5 MHz. 2. Turn the ELT aircraft panel switch "ON" for about 1 second, then back to the "ARM"...
  • Page 349 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the GFC 700 Automatic Flight Control System (Aircraft Serials w/ Perspective Avionics Only) Including optionally installed Electronic Stability and Protection (ESP), Underspeed Protection (USP), and Hypoxia Detection and Automatic Descent functions.
  • Page 350 Control System (AFCS) which is fully integrated within the Cirrus Perspective Integrated Avionics System architecture. Refer to Section 7 - System Description and the Cirrus Perspective Pilot’s Guide for additional description of the AFCS and operating procedures.. Determining status of Autopilot Underspeed Protection (USP)
  • Page 351 Cirrus Design Section 9 SR22 / SR22T Supplements 6. The Autopilot may not be engaged beyond the Engagement Limits. If the Autopilot is engaged beyond the command limits (up to engagement limits), it will be rolled or pitched to within the command limits and an altitude loss of 1000 feet or more can be expected while attitude is established in the selected mode.
  • Page 352 Section 9 Cirrus Design Supplements SR22 / SR22T Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure abnormal procedure in the basic POH. Do not reengage the Autopilot until the malfunction has been identified and corrected. The Autopilot may be disconnected by: 1.
  • Page 353 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3A - Abnormal Procedures Altitude Miscompare ALT MISCOMP Caution ALT MISCOMP For dual ADC installations, altitude difference is greater than 200 feet between ADC1 and ADC2. 1. Altitude ..... CROSS-CHECK ADC1 against Standby Altimeter 2.
  • Page 354 Section 9 Cirrus Design Supplements SR22 / SR22T Heading Miscompare HDG MISCOMP Caution HDG MISCOMP For dual AHRS installations, heading difference is greater than 6° between AHRS 1 and AHRS 2. 1. Heading..CROSS-CHECK AHRS1 against Magnetic Compass 2. AHRS2 ................SELECT a.
  • Page 355 Cirrus Design Section 9 SR22 / SR22T Supplements advisory since backup source is not available for comparison. Flight Director, Autopilot and ESP will become available when unreliable AHRS CB is pulled. Roll Miscompare ROLL MISCOMP Caution ROLL MISCOMP For dual AHRS installations, roll (bank) difference is greater than 6°...
  • Page 356 Section 9 Cirrus Design Supplements SR22 / SR22T Autopilot and PFD Using Different AHRSs AP/PFD AHRS Caution AP/PFD AHRS The Autopilot and PFD are using different Attitude and Heading Reference Systems. 1. Continue flight without Autopilot. Monitor Standby Instruments. Pilot may manually select other AHRS if installed.
  • Page 357 Cirrus Design Section 9 SR22 / SR22T Supplements Course Selection Track Error COURSE SEL Advisory COURSE SEL The pilot has selected an Autopilot mode (ROL) and engaged a NAV mode (VLOC or GPS) and the current aircraft track will not intercept the selected course.
  • Page 358 Section 9 Cirrus Design Supplements SR22 / SR22T AUTO DESCENT Warning AUTO DESCENT No pilot response to the HYPOXIA ALERT annunciation detected after one minute. Warning remains until pilot responds. Automatic descent begins after one minute of unanswered Warning. Once it begins, automatic descent will commence to 14,000 feet for 4 minutes, then to 12,500 feet thereafter.
  • Page 359 Cirrus Design Section 9 SR22 / SR22T Supplements Underspeed Protection Recovery (Optional) UNDERSPEED PROTECT ACTIVE Warning UNDERSPEED PROTECT ACTIVE Autopilot 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.
  • Page 360 Section 4 - Normal Procedures • Note • Normal operating procedures for the GFC 700 Automatic Flight Control System are described in the Cirrus Perspective Pilot’s Guide. PreFlight Inspection 1. A self test is performed upon power application to the AFCS. A...
  • Page 361 Cirrus Design Section 9 SR22 / SR22T Supplements Temporary Interrupt of ESP (Optional) Although ESP is only provided when AFCS Autopilot is disengaged, the AFCS and its servos are the source of ESP guidance. When the AP Disconnect button is pressed and held, the servos will provide no ESP control force feedback.
  • Page 362 Section 9 Cirrus Design Supplements SR22 / SR22T Section 7 - System Description This airplane is equipped with a GFC 700 - a two axis (three axis optional), fully digital, dual channel, fail passive Automatic Flight Control System (AFCS). The system consists of the GFC 705 AFCS...
  • Page 363 Cirrus Design Section 9 SR22 / SR22T Supplements GFC 705 MODE CONTROLLER INTEGRATED GO-AROUND INTEGRATED AVIONICS UNIT 2 SWITCH AVIONICS UNIT 1 A/P DISC PITCH TRIM ADAPTER 4-WAY TRIM PITCH TRIM CARTRIDGE ROLL SERVO PITCH SERVO YAW SERVO (optional) SR22_FM09_2919...
  • Page 364 Section 9 Cirrus Design Supplements SR22 / SR22T GFC 705 AFCS Mode Controller The GFC 705 AFCS Mode Controller, located in the upper section of the center console, provides primary control of Autopilot modes and, if installed, yaw damper engagement. A pitch wheel is included for adjustment of pitch mode reference.
  • Page 365 Cirrus Design Section 9 SR22 / SR22T Supplements YD - Yaw Damper Button (Optional) The YD button engages/disengages the yaw damper. • Note • The yaw damper is automatically engaged when the Autopilot is engaged with the AP button. UP/DN - Pitch Wheel The Pitch UP/DN Wheel on the controller is used to change the Flight Director pitch mode reference value.
  • Page 366 Section 9 Cirrus Design Supplements SR22 / SR22T Flight Management System Keyboard The Flight Management System Keyboard, found in the center console below the AFCS mode controller, is the primary means for data entry for the MFD and is used to control NAV/COM Radios, transponder, and flight management system entry.
  • Page 367 Cirrus Design Section 9 SR22 / SR22T Supplements GARMIN IDENT FMS/XPDR RANGE MENU XPDR COM/NAV PROC DFLT MAP PUSH SYNC PUSH PUSH EMERG CRSR/1-2 PUSH CTR ALT SEL BKSP PUSH SYNC Flight Management System Keyboard GFC 705 Mode Controller Legend 1.
  • Page 368 Section 9 Cirrus Design Supplements SR22 / SR22T Roll, Pitch and Optional Yaw Servo The Roll Servo, located below the passenger seat, the Pitch Servo, located below the baggage compartment, and the optional Yaw Servo, located in the empennage avionics bay, position the aircraft flight controls in response to commands generated by the Integrated Avionics Units Autopilot calculations.
  • Page 369 Cirrus Design Section 9 SR22 / SR22T Supplements control forces if intentional maneuvers are necessary beyond ESP's engagement threshold (i.e., isolated training maneuvers). Take Off / Go Around Button The remote TO/GA switch, located on the left side of the power lever, selects the Takeoff or Go Around mode on the Flight Director.
  • Page 370 Section 9 Cirrus Design Supplements SR22 / SR22T Electronic Stability and Protection (Optional) When installed, Electronic Stability and Protection (ESP) assists the pilot in maintaining the airplane in a safe flight condition. Through the use of the GFC 700 AFCS sensors, processors, and servos, ESP provides control force feedback, i.e.
  • Page 371 Cirrus Design Section 9 SR22 / SR22T Supplements Roll Protection Limits: Always Protected Only Protected after cross- ing turn-on threshold 0° 15° 30° 45° 60° 75° 90° Bank Angle Engagement Limit: ..............45° Maximum Stick Force attained at..........50° Disengagement Threshold (Zero Stick Force) ......30°...
  • Page 372 Section 9 Cirrus Design Supplements SR22 / SR22T Low Pitch Protection Limits Always Protected Only Protected after cross- ing turn-on threshold -0° -5° -10° -15° -20° -25° Nose Down Pitch Angle Engagement Limit: ..............-15.5° Maximum Stick Force attained at: ......... -20.5°...
  • Page 373 Cirrus Design Section 9 SR22 / SR22T Supplements High Airspeed Protection Limits - Below 17,500 ft PA Always Protected Only Protected after cross- ing turn-on threshold Indicated Airspeed (KIAS) Engagement Limit: ............200 KIAS Maximum Stick Force attained at:........205 KIAS Disengagement Threshold (Zero Stick Force): ....
  • Page 374 Section 9 Cirrus Design Supplements SR22 / SR22T Serials w/ Discrete-Triggered Low Speed Mode (Optional) To protect against an impending stall, the Discrete-Triggered Low Speed Mode uses stick forces, similar to those used for the pitch and roll modes, to control the pitch attitude. These stick forces are triggered by the stall warning system.
  • Page 375 Cirrus Design Section 9 SR22 / SR22T Supplements As described in the following table, when the aircraft reaches predetermined airspeeds a yellow MINSPD annunciation will appear above the airspeed indicator and a single aural “AIRSPEED” will sound to alert the pilot to an impending underspeed condition.
  • Page 376 Section 9 Cirrus Design Supplements SR22 / SR22T Non-Altitude Critical Mode (VS, PIT, VNAV, LVL, IAS) For all non-altitude critical modes the Autopilot will maintain its original reference (VS, PIT, etc...) until airspeed decays to a minimum airspeed (MINSPD). Crew alert and annunciation during a non-altitude critical underspeed event are similar to an altitude-critical event, except that;...
  • Page 377 Cirrus Design Section 9 SR22 / SR22T Supplements Hypoxia Detection and Automatic Descent (Optional) When installed, the AFCS Hypoxia Detection and Automatic Descent function monitors pilot inputs to the Integrated Avionics System to identify if a pilot has become incapacitated due to hypoxia, and upon determination, automatically descends to a lower altitude where pilot recovery is more probable.
  • Page 378 Supplements SR22 / SR22T Annunciation System • Note • Refer to the Cirrus Perspective Pilot’s Guide for a detailed description of the annunciator system and all warnings, cautions and advisories. Crew Alerting System AFCS alerts are displayed in the Crew Alerting System (CAS) window located to the right of the altimeter and VSI.
  • Page 379 Cirrus Design Section 9 SR22 / SR22T Supplements Section 8 – Handling, Service, & Maintenance No Change. Section 10 – Safety Information No Change. P/N 13772-135 31 of 32 Revision 04: 09-08-14...
  • Page 380 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 32 of 32 P/N 13772-135 Revision 04: 09-08-14...
  • Page 381 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the Garmin Terrain Awareness/Warning System (Aircraft Serials w/ Perspective Avionics Only) When the Garmin Terrain Awareness/Warning System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements Section of the Pilot’s Operating Handbook.
  • Page 382 System that performs the functions of a Class C Terrain Awareness and Warning System (TAWS) in accordance with TSO C151b. Refer to the Cirrus Perspective Integrated Flight Deck Pilot’s Guide for a additional information on the system and its operating modes.
  • Page 383 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3 - Emergency Procedures To prevent unwanted aural alerting during ditching or other off-airport landings, inhibit the Terrain Awareness System functions by selecting the INHIBIT Softkey on the TAWS Page. Response To TAWS Warnings...
  • Page 384 PFD. Refer to the Cirrus Perspective Integrated Flight Deck Pilot’s Guide for a additional information on the system and its operating modes. 4 of 6...
  • Page 385 Cirrus Design Section 9 SR22 / SR22T Supplements System Constraints System test at startup: Aural tone lasting approximately one second indicates successful completion of internal system test. Red TAWS FAIL Warning TAWS FAIL Aural “TAWS SYSTEM FAILURE” Warning 1. TAWS power-up self-test has failed or TAWS has detected problems with database validity, hardware status, and/or GPS status.
  • Page 386 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 6 of 6 P/N 13772-136 Revision 01: 01-06-10...
  • Page 387 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement 14 Code of Federal Regulations (CFR) Part 135 Commercial Operation of Small Aircraft Electrical Loading Shedding Procedure This supplement provides the necessary guidance for load shed in the event of a primary electrical generating source failure in accordance with 14 CFR Section 135.163(f).
  • Page 388 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General No Change. Section 2 - Limitations 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: Kinds of Operation...
  • Page 389 13.6 amp-hour battery (available from Cirrus Design Spare Parts Sales) in good condition for equipment required for emergency operation under 14 CFR 135.163(f) and meets the requirements of that paragraph.
  • Page 390 Section 9 Cirrus Design Supplements SR22 / SR22T 8. Reduce loads as required for flight conditions: a. Air Conditioning and Fan ..........OFF b. Convenience Outlet ........Disconnect appliance c. Audio Panel ...............OFF COM 1 will be supplied to pilot’s headset. Communication with passengers through audio panel will not be available.
  • Page 391 Cirrus Design Section 9 SR22 / SR22T Supplements Aircraft Serials with Perspective PFD/MFD Avionics ALT 1 Failure (Alt 1 Light Steady) Steady illumination indicates failure of alternator 1. Attempt to restore alternator. If alternator cannot be restored, Alternator 2, and Bat 2 will...
  • Page 392 Section 9 Cirrus Design Supplements SR22 / SR22T Section 3A - Abnormal Procedures 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.
  • Page 393 Cirrus Design Section 9 SR22 Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the TKS Anti-Ice System • Approved for Flight Into Known Icing (FIKI) • 8.0 gallon usable capacity. • 4.0 gallon tank in each wing.
  • Page 394 Section 9 Cirrus Design Supplements SR22 Section 1 - General This system, when compliant with the Kinds of Operation Equipment List and Minimum Dispatch Fluid Quantity, allows flight in icing conditions as defined by Title 14 of the Code of Federal Regulations (CFR) Part 25, Appendix C - Envelopes for Continuous Maximum and Intermittent Maximum Icing.
  • Page 395 Cirrus Design Section 9 SR22 Supplements • Accumulation of ice on the upper surface or lower surface of the wing aft of the protected area. • Accumulation of ice on the propeller spinner farther back than normally observed. If the airplane encounters conditions that are determined to contain...
  • Page 396 Code of Federal Regulations (CFR) Part 25, Appendix C - Envelopes for Continuous Maximum and Intermittent Maximum Icing. This airplane is approved for flight into known icing conditions only if the following Cirrus and FAA approved equipment is installed and fully functional. Kinds of Operation...
  • Page 397 Cirrus Design Section 9 SR22 Supplements Minimum Dispatch Fluid Quantity Dispatch into known icing conditions with less than 5 gallons (19 liters) of deicing fluid is prohibited. The pilot must ensure adequate fluid quantity before each flight. If dispatching without the minimum 5 gallons and icing conditions are encountered, exit icing conditions as soon as possible.
  • Page 398: Pilot Qualification And Training

    The Pilot Qualification and Training Limitation does not apply to airplanes registered in the European Union. The pilot-in-command must successfully complete the Cirrus Icing Awareness Course or a Cirrus Design approved equivalent training course, within the preceding 24 months prior to Flight Into Forecast or Known Icing Conditions.
  • Page 399 Cirrus Design Section 9 SR22 Supplements Placards Lower wing, above anti-ice fluid drain: Upper wing, above anti-ice fluid filler cap: Bolster Switch Panel, left edge: THIS AIRCRAFT IS CERTIFIED FOR THE FOLLOWING FLIGHT OPERATIONS DAY - NIGHT - VFR - IFR...
  • Page 400 Section 9 Cirrus Design Supplements SR22 Section 3 - Emergency Procedures A failure of the Anti-Ice System is any condition, observed or suspected, in which the system fails to remove ice from protected surfaces including the propeller, in addition to any Anti-Ice System CAS failure annunciations.
  • Page 401 Cirrus Design Section 9 SR22 Supplements Anti-Ice System Failure / Excessive Ice Accumulation 1. ICE PROTECT A and B Circuit Breakers ........ SET 2. Fluid Quantity........SWITCH TO FULLEST TANK 3. WIND SHLD Push-Button ........... PRESS a. Repeat operation of windshield pump to verify metering pumps are primed properly as evidenced by deicing fluid exiting windshield nozzles.
  • Page 402 Section 9 Cirrus Design Supplements SR22 Maximum Glide with Ice Accumulation Conditions Example: Power Altitude 10,000 ft. AGL Propeller Windmilling Airspeed 92 KIAS Flaps 0% (UP) Glide Distance 10.5 NM Wind Zero Best Glide Speed 92 KIAS at 3600 lb Maximum Glide Ratio ~ 6.4: 1...
  • Page 403 Cirrus Design Section 9 SR22 Supplements Section 3A - Abnormal Procedures Windshield De-Ice System Malfunction 1. ICE PROTECT A Circuit Breaker........CYCLE 2. Fluid Quantity........SWITCH TO FULLEST TANK 3. WIND SHLD Push-Button ......PRESS AS REQUIRED If the forward field of view is overly restricted during landing approach and taxiing: a.
  • Page 404 Section 9 Cirrus Design Supplements SR22 Static System Malfunction If erroneous readings on the pilot’s flight instruments are suspected the static button(s) on side of fuselage may be obstructed. Refer to Section 3A - Abnormal Procedures, Static Source Blocked in the basic handbook.
  • Page 405 Cirrus Design Section 9 SR22 Supplements 4. ICE PROTECT Mode Switch ..........HIGH If warning annunciation extinguishes: a. Anti-Ice System ............MONITOR If warning annunciation does not extinguishes or intermittent: a. PUMP BKUP Switch............ON b. Icing Conditions..........AVOID / EXIT...
  • Page 406 Section 9 Cirrus Design Supplements SR22 Unreliable Fluid Quantity Warning ANTI ICE QTY PFD Alerts Window: “Left and right fluid quantities unknown (TKS)” Both fluid quantities are unknown and both tanks are closed. 1. ICE PROTECT System Switch ..........OFF 2. Icing Conditions ............AVOID / EXIT Low Pressure Caution.
  • Page 407 Cirrus Design Section 9 SR22 Supplements High Pressure Caution ANTI ICE PSI PFD Alerts Window: “Pressure is high (TKS)” Typically indicates clogged filter. 1. Evidence of Anti-Ice Flow ......MONITOR / VERIFY 2. Icing Conditions ............AVOID / EXIT Airspeed Caution ANTI ICE SPD PFD Alerts Window: “Airspeed is too low/high for ice protection (TKS)”...
  • Page 408 Section 9 Cirrus Design Supplements SR22 Fluid Quantity Imbalance Caution ANTI ICE QTY PFD Alerts Window: “Fluid quantity imbalance has been detected” Imbalance between left and right sensed fluid quantity is greater than 1.0 gallon. 1. Revert to AUTO control of the fluid source to control the fluid quantity.
  • Page 409 Cirrus Design Section 9 SR22 Supplements Left/Right Fluid Quantity Caution ANTI ICE LVL PFD Alerts Window: “Right/Left tank fluid quantity is unreliable (TKS)” L / R fluid quantities on Anti Ice - TKS block of ENGINE page is “greyed out” and/or fluid quantity is marked with a “Red X”. The deicing fluid sensing system has detected conflicting system information regarding the fluid quantity in the tanks.
  • Page 410 Section 9 Cirrus Design Supplements SR22 Section 4 - Normal Procedures • WARNING • Holding in icing conditions for longer than 45 minutes may reduce margins and could result in inadequate handling and control characteristics. Flight into known icing conditions is prohibited if porous panels do not fully "wet-out"...
  • Page 411 Cirrus Design Section 9 SR22 Supplements which may not be adequate to wet-out the entire panel if the Pre-Flight Inspection is performed at warmer temperatures. Increasing the system flow rate (MAX vs. HIGH or HIGH w/ PUMP BKUP vs. HIGH) will increase the arterial pressure of the system which promotes the complete wet-out of the porous panels.
  • Page 412 Section 9 Cirrus Design Supplements SR22 n. PITOT HEAT Switch ....... ON 45 seconds, then OFF 2. Empennage a. Stabilizers Porous Panels....CONDITION / SECURITY (1) Verify Evidence of Deicing Fluid Along Length of Panels and Elevator Horns. 3. Right Wing Forward and Main Gear a.
  • Page 413 Cirrus Design Section 9 SR22 Supplements 8. Left Wing Tip • WARNING • Pitot Probe may be HOT. a. Pitot Probe (underside) ......UNOBSTRUCTED b. Pitot Probe..............VERY HOT 9. Cabin a. Fluid Quantity ......VERIFY 5 GALLON MINIMUM b. ICE PROTECT System Switch.......... OFF c.
  • Page 414 Section 9 Cirrus Design Supplements SR22 Before Takeoff If icing conditions are anticipated immediately after take-off: 1. ICE PROTECT System Switch ..........ON 2. ICE PROTECT Mode Switch ........NORM / HIGH 3. PITOT HEAT Switch..............ON 4. Cabin Heat ................HOT 5.
  • Page 415 Cirrus Design Section 9 SR22 Supplements While in Icing Conditions: 1. FLAPS ..................UP 2. Ice-Inspection Lights ..........AS REQUIRED 3. Cabin Heat ................HOT 4. Windshield Defrost..............ON 5. Fluid Quantity and Endurance ........MONITOR a. Ensure adequate quantity to complete flight.
  • Page 416: Approach And Landing

    Section 9 Cirrus Design Supplements SR22 Cruise During icing encounters in cruise, increase engine power to maintain cruise speed as ice accumulates on the unprotected areas and causes the aircraft to slow down. The autopilot may be used in icing conditions. However, every 30 minutes the autopilot should be disconnected to detect any out-of-trim conditions caused by ice buildup.
  • Page 417 Cirrus Design Section 9 SR22 Supplements After Landing and Shutdown 1. PITOT HEAT Switch ..............OFF 2. ICE PROTECT System Switch ..........OFF 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 fluid.
  • Page 418: Stall Speeds With Ice Accumulation

    Section 9 Cirrus Design Supplements SR22 Section 5 - Performance Airplane performance and stall speeds without ice accumulation are essentially unchanged with the installation of the Ice Protection System. Significant climb and cruise performance degradation, range reduction, as well as buffet and stall speed increase can be expected if ice accumulates on the airframe.
  • Page 419 Cirrus Design Section 9 SR22 Supplements Enroute Climb Gradient with Ice Accumulation Conditions: • Power ....................Full Throttle • Mixture ....................Set Per Placard • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
  • Page 420: Enroute Rate Of Climb With Ice Accumulation

    Section 9 Cirrus Design Supplements SR22 Enroute Rate of Climb with Ice Accumulation Conditions: • Power ....................Full Throttle • Mixture....................As Required • Flaps......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude in feet per unit time expressed in Feet per Minute.
  • Page 421 Cirrus Design Section 9 SR22 Supplements Time, Fuel & Distance to Climb: Full Power Climb with Ice Accumulation Conditions: • Power ....................Full Throttle • Mixture ............Maintain Fuel Flow in GREEN ARC • Weight ......................3600 LB • Winds ....................... Zero •...
  • Page 422 Section 9 Cirrus Design Supplements SR22 Cruise Performance with Ice Accumulation Conditions: • Cruise Weight ..................... 3400 LB • Winds........................ Zero • Note • Aircraft with optional Air Conditioning System - Cruise performance is reduced by 2 knots. For maximum performance, the air-conditioner should be off.
  • Page 423 Cirrus Design Section 9 SR22 Supplements Cruise Performance (Continued) 6000 Feet Pressure Altitude ISA -30°C (-27°C) ISA (3°C) ISA + 30°C (33°C) KTAS KTAS KTAS 2700 23.5 21.2 20.1 2600 23.5 20.3 19.2 2500 23.5 19.1 18.1 2500 22.5 18.1 17.1...
  • Page 424 Section 9 Cirrus Design Supplements SR22 Range / Endurance: Full Power Climb with Ice Accumulation Conditions: • Mixture.............Best Economy - Target Fuel Flow or less • Weight ..........3600 LB for Climb, Avg 3400 LB for Cruise • Winds........................ Zero •...
  • Page 425 Cirrus Design Section 9 SR22 Supplements Range / Endurance: Full Power Climb with Ice Accumulation (Continued) Range / Endurance: 65% Power Cruise - Full Power Climb Airspee Press Climb Fuel Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise...
  • Page 426 Section 9 Cirrus Design Supplements SR22 Range / Endurance: Full Power Climb with Ice Accumulation (Continued) Range / Endurance: 55% Best Economy Cruise - Full Power Climb Airspee Press Climb Fuel Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise...
  • Page 427 Cirrus Design Section 9 SR22 Supplements Balked Landing Climb Gradient with Ice Accumulation Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps ......................50% (DN) • Climb Airspeed....................V REF • Note • Balked Landing Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
  • Page 428 Section 9 Cirrus Design Supplements SR22 Balked Landing Rate of Climb with Ice Accumulation Conditions: • Power ....................Full Throttle • Mixture.................... Set per Placard • Flaps......................... 50% • Climb Airspeed ....................V REF • Note • Balked Landing Rate of Climb values shown are the full flaps change in altitude for unit time expended expressed in Feet per Minute.
  • Page 429 Cirrus Design Section 9 SR22 Supplements Landing Distance with Ice Accumulation Conditions: • Winds ....................... Zero • Runway ..................Dry, Level, Paved • Note • The following factors are to be applied to the computed landing distance for the noted condition: •...
  • Page 430 Section 9 Cirrus Design Supplements SR22 Landing Distance - Flaps 50% Associated balked landing climb gradient less than 3.3% shown in heavier table borders WEIGHT: 3600 LB Headwind: Subtract 10% for each 13 Speed over 50 Ft Obstacle: 88 KIAS knots headwind.
  • Page 431 Cirrus Design Section 9 SR22 Supplements Section 6 - Weight & Balance Weight and Balance Refer to Section 6 - of the basic POH for current weight and balance data. Use the following table to determine the Moment/1000 for deicing fluid to complete the Loading Form in the Weight and Balance Section of the basic POH.
  • Page 432 Section 9 Cirrus Design Supplements SR22 Section 7 - System Description The TKS Anti-Ice System can prevent and remove ice accumulation on the flight surfaces by distributing a thin film of ice protection fluid on the wing, horizontal stabilizer, vertical stabilizer, elevator tips, and propeller.
  • Page 433: Porous Panels

    Cirrus Design Section 9 SR22 Supplements If the system is ON and PUMP BKUP is selected, #1 pump will operate (if not failed) based on the mode setting (NORM or HIGH) while #2 pump operates continuously (PUMP BKUP), causing the range and endurance to decrease from the published values, e.g.
  • Page 434 Section 9 Cirrus Design Supplements SR22 smaller than the openings of the outer surface. The leading edge of the panel serves as a reservoir as fluid entering the panel fills the cavity behind the porous membrane then overcomes this resistance to be distributed by the openings in the external surface.
  • Page 435 Cirrus Design Section 9 SR22 Supplements 8 9 10 LEGEND 1. LH Outbd Panel 14. Stall Transducer 27. RH Elevator Tip Panel 2. LH Vent 15. RH Vent 28. V Stab Panel 3. LH Inbd Panel 16. RH Outbd Panel 29.
  • Page 436 Section 9 Cirrus Design Supplements SR22 System Control System operation is controlled by five bolster panel switches and three MFD softkeys: • Bolster Panel Switches: Metering pump operation and mode control (flow rate) are controlled by the NORM, HIGH, and MAX switches.
  • Page 437 Cirrus Design Section 9 SR22 Supplements • LEFT: Ice protection fluid is drawn from the left tank regardless of sensed quantity. • RIGHT: Ice protection fluid is drawn from the right tank regardless of sensed quantity. System Indicating System Indicating is displayed as bar graphs and text in the lower left corner of the MFD ENGINE page.
  • Page 438 Section 9 Cirrus Design Supplements SR22 Anti Ice - TKS Time Rem (H:MM) 0:31 High 1:03 Norm 2:06 Range 79 NM ENGINE ANTI-ICE DCLTR ASSIST FUEL NOTE Illustration depicts system during Auto Tank Mode with LH and RH tanks ON while operating in MAX mode.
  • Page 439 Cirrus Design Section 9 SR22 Supplements Stall Warning System Stall warning is provided by the lift transducer, mounted on the leading edge of the right wing and the stall warning computer located under the cabin floor. The lift transducer senses the force of the airstream on the vane, producing an electrical output to the stall warning computer.
  • Page 440 Section 9 Cirrus Design Supplements SR22 inspection lights illuminate the leading edge of the wing and 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.
  • Page 441 Cirrus Design Section 9 SR22 Supplements Section 8 – Handling, Service, & Maintenance • Caution • During long periods of non-use, the porous panel membranes may dry out which could cause uneven fluid flow during subsequent operation. Perform the Pre-Flight Inspection every 30 days to keep porous panel membranes wetted.
  • Page 442 Section 9 Cirrus Design Supplements SR22 Metering Pump Priming If air entered the system due to the fluid tank(s) running dry during system operation, 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...
  • Page 443 When Hartzell Propeller Model Number PHC-J3YF-1N/N7605(B), PHC-J3Y1F-1N/N7605(B), or PHC-J3Y1F-1N/N7605C(B) is installed in the Cirrus Design SR22, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR22 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
  • Page 444 Section 9 Cirrus Design Supplements SR22 Section 1 - General For additional information on Hartzell Compact Series Propeller with Composite Blades refer to Hartzell Propeller Owner’s Manual, p/n 145, revision 1 or later. Section 2 - Limitations Power Plant Limitations Hartzell Compact Series Propeller with Composite Blades Propeller Type ........Constant Speed, Three Blade...
  • Page 445 Cirrus Design Section 9 SR22 Supplements Maximum Glide Conditions Example: Power Altitude 10,000 ft. AGL Propeller Windmilling Airspeed Best Glide Flaps 0% (UP) Wind Zero Glide Distance 13.4 NM Best Glide Speed 3600 lb 92 KIAS Maximum Glide Ratio ~ 8.1 : 1...
  • Page 446 For climb, follow basic AFM procedure but use performance data in Section 5 of this supplement. Noise Characteristics/Abatement The certificated noise levels for the Cirrus Design SR22 established in accordance with FAR 36 Appendix G are: Configuration...
  • Page 447 Cirrus Design Section 9 SR22 Supplements Enroute Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp ......20°C • Mixture ...... Set Per Placard Weight ........3600 LB • Flaps ........0% (UP) Pressure Altitude ....4000 FT • Airspeed ......Climb Speed Climb Airspeed ....108 Knots...
  • Page 448 Section 9 Cirrus Design Supplements SR22 Enroute Rate of Climb Conditions: Example: • Power ......Full Throttle Outside Air Temp ....... 20°C • Mixture...... Set Per Placard Weight........3600 LB • Flaps........0% (UP) Pressure Altitude....6000 FT • Airspeed ......Climb Speed Climb Airspeed....
  • Page 449 Cirrus Design Section 9 SR22 Supplements Section 6 - Weight & Balance Installation of the subject propeller adds the following optional (Sym = O) equipment at the weight and arm shown in the following table. ATA / Unit Description Part Number...
  • Page 450 Section 9 Cirrus Design Supplements SR22 Section 8 - Handling, Servicing & Maintenance Propeller Servicing The spinner and backing plate should be cleaned and inspected for cracks frequently. Before each flight the propeller should be inspected for nicks, scratches, and gouges. If found, they should be repaired as...
  • Page 451 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement Artex ELT 1000 406 MHz ELT System When Artex ELT 1000 406 MHz ELT System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements section (Section 9) of the Pilot’s Operating Handbook.
  • Page 452 The ELT automatically transmits the standard sweep tone on 121.5 MHz if rapid deceleration is detected or the Cirrus Airframe Parachute System (CAPS) is deployed. CENTER CONSOLE...
  • Page 453 Cirrus Design Section 9 SR22 / SR22T Supplements Section 2 - Limitations No Change. Section 3 - Emergency Procedures Portable use of ELT The ELT transmitter can be removed from the airplane and used as a personal locating device if it is necessary to leave the airplane after an accident.
  • Page 454 4 to 5 feet per second, or upon sensing deployment of the Cirrus Airframe Parachute System (CAPS). Once activated, the ELT transmits VHF band audio sweeps at 121.5 MHz until battery power is gone.
  • Page 455 Cirrus Design Section 9 SR22 / SR22T Supplements “ARM/OFF” - “TEST”, and a red LED annunciator. The red LED annunciator flashes when the ELT is transmitting. Section 8 - Handling, Servicing & Maintenance The ELT batteries must be inspected in accordance with the Airplane Maintenance Manual, 5-20 - Scheduled Maintenance Checks.
  • Page 456 Section 9 Cirrus Design Supplements SR22 / SR22T even if the radiating ELT’s antenna is disconnected. Therefore, it does not check the integrity of the ELT system or provide the same level of confidence as does an AM radio. 1. Tune aircraft receiver to 121.5 MHz.
  • Page 457 SR22 Safety Information Section 10: Safety Information Table of Contents Introduction ..................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 Maintenance ...............
  • Page 458 Section 10 Cirrus Design Safety Information SR22 Intentionally Left Blank 10-2 P/N 13772-004 Original Issue...
  • Page 459: Introduction

    Cirrus strongly recommends that all pilots seek regular recurrent training and that they operate in accordance with the Cirrus Flight Operations Manual and Envelope of Safety. As the pilot you must be thoroughly familiar with the contents of this...
  • Page 460: Cirrus Airframe Parachute System (Caps)

    Instead, possible CAPS activation scenarios should be well thought out and mentally practiced by every Cirrus pilot. Pilots who regularly conduct CAPS training and think about using CAPS will often have a higher probability of deploying CAPS when necessary.
  • Page 461 CAPS activation is strongly recommended. Numerous fatalities that have occurred in Cirrus aircraft accidents likely could have been avoided if pilots had made the timely decision to deploy CAPS.
  • Page 462 Section 10 Cirrus Design Safety Information SR22 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 they could effectively deploy CAPS if required.
  • Page 463: General Deployment Information

    Cirrus Design Section 10 SR22 Safety Information General Deployment Information Deployment Speed The maximum speed at which deployment has been demonstrated is 140 KIAS. Deployment at higher speeds could subject the parachute and aircraft to excessive loads that could result in structural failure. Once a decision has been made to deploy the CAPS, make all reasonable efforts to slow to the minimum possible airspeed.
  • Page 464: Landing Considerations

    Section 10 Cirrus Design Safety Information SR22 Landing Considerations After a CAPS deployment, the airplane will descend at less than 1700 feet per minute with a lateral speed equal to the velocity of the surface wind. The CAPS landing touchdown is equivalent to ground impact from a height of approximately 13 feet.
  • Page 465 Cirrus Design Section 10 SR22 Safety Information • If a door is open prior to touchdown in a CAPS landing, the door will most likely break away from the airplane at impact. • If the door is open and the airplane contacts the ground in a rolled condition, an occupant could be thrown forward and strike their head on the exposed door pillar.
  • Page 466 Section 10 Cirrus Design Safety Information SR22 Post Impact Fire If there is no fire prior to touchdown and the pilot is able to shut down the engine, fuel, and electrical systems, there is less chance of a post impact fire. If the pilot suspects a fire could result from impact, unlatching a door immediately prior to assuming the emergency landing body position should be considered to assure rapid egress.
  • Page 467: Taxiing, Steering, And Braking Practices

    SR22 Safety Information Taxiing, Steering, and Braking Practices Cirrus aircraft use a castering nose wheel and rely on aerodynamic forces and differential braking for directional control while taxiing. Proper braking practices are therefore critical to avoid potential damage to the brakes.
  • Page 468: Brake Maintenance

    Section 10 Cirrus Design Safety Information SR22 • Use only as much power (throttle) as is necessary to achieve forward movement. Keep in mind, any additional power added with the throttle will be absorbed in the brakes to maintain constant speed.
  • Page 469 Cirrus Design Section 10 SR22 Safety Information • Overheated components, indicated by discoloration or warping of the disk rotor. Excessive heat can cause the caliper components to discolor or cause yellowing of the part identification label. Refer to Section 8,...
  • Page 470 Section 10 Cirrus Design Safety Information SR22 Intentionally Left Blank 10-14 P/N 13772-004 Revision 1...

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