Cirrus SR22 Pilot's Operating Handbook And Flight Manual
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Cirrus SR22 Pilot's Operating Handbook And Flight Manual

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PILOT'S OPERATING HANDBOOK
AND FAA APPROVED
AIRPLANE FLIGHT MANUAL
for the
CIRRUS SR22
A i r c r a f t S e r i a l s S R 2 2 - 4 4 3 3 & S u b s e q u e n t w i t h
+
C i r r u s P e r s p e c t i v e
A v i o n i c s S y s t e m
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.
Model - Serial Num.:
Registration Num.:
P/N 13772-006
CoverPage-i
Original Issue: December 28, 2016

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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. Model - Serial Num.: Registration Num.:...
  • Page 2 Copyright © 2016 - All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811 CoverPage-ii P/N 13772-006 Original Issue: December 28, 2016...
  • 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 Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status Original Issue 5-27 Original Issue 7-40 Original Issue Original Issue 5-28 Original Issue 7-41 Original Issue Original Issue 5-29...
  • Page 5 Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 7-95 Original Issue 10-6 Original Issue 7-96 Original Issue 10-7 Original Issue 7-97 Original Issue 10-8 Original Issue 7-98...
  • Page 6 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 13772-006 Original Issue...
  • Page 7 Cirrus Design TPOH SR22 AFM Temporary Change SR22 Airplane Flight Manual (AFM) Temporary Change Information in this Temporary Change adds to, supersedes, or deletes information in the basic Pilot’s Operating Handbook. Affected SR22 Basic Airplane Flight Manuals: Publications: • PN 13772-006 Original / 13772-004 Rev 1 /...
  • Page 8 TPOH Cirrus Design AFM Temporary Change SR22 Intentionally Left Blank 2 of 8 TPOH 15-15R1 14 May 2018...
  • Page 9 Cirrus Design TPOH SR22 AFM Temporary Change SR22 Airplane Flight Manual (AFM) Temporary Change Information in this Temporary Change adds to, supersedes, or deletes information in the basic Pilot’s Operating Handbook. Affected SR22 Basic Airplane Flight Manuals: Publications: • PN 13772-006 Original Issue (FAA Approved) •...
  • Page 10 TPOH Cirrus Design AFM Temporary Change SR22 Intentionally Left Blank 2 of 2 TPOH 17-02 27 Jul 2018...
  • Page 11 Cirrus Design TPOH SR22 AFM Temporary Change SR22 Airplane Flight Manual (AFM) Temporary Change Information in this Temporary Change adds to, supersedes, or deletes information in the basic Pilot’s Operating Handbook. Affected SR22 Basic Airplane Flight Manuals: Publications: • PN 13772-006 Original Issue (FAA Approved) •...
  • Page 12 TPOH Cirrus Design AFM Temporary Change SR22 Intentionally Left Blank 2 of 2 TPOH 17-04 11 May 2018...
  • Page 13 Cirrus Design TPOH SR22 AFM Temporary Change SR22 Airplane Flight Manual (AFM) Temporary Change Information in this Temporary Change adds to, supersedes, or deletes information in the basic Pilot’s Operating Handbook. Affected SR22 Basic Airplane Flight Manual: Publications: • PN 13772-006 Original Issue (FAA Approved) •...
  • Page 14 TPOH Cirrus Design AFM Temporary Change SR22 Intentionally Left Blank 2 of 2 TPOH 17-08 27 Jul 2018...
  • Page 15 Cirrus Design TPOH SR22 POH Temporary Change SR22 Pilot’s Operating Handbook (POH) Temporary Change Information in this Temporary Change adds to, supersedes, or deletes information in the basic Pilot’s Operating Handbook. Affected SR22 Pilot’s Operating Handbook: Publications: • PN 13772-006 Original Issue (FAA Approved) •...
  • Page 16 TPOH Cirrus Design POH Temporary Change SR22 Intentionally Left Blank 2 of 2 TPOH 17-10 Dec 22, 2017...
  • Page 17 Cirrus Design TPOH SR22 POH Temporary Change SR22 Pilot’s Operating Handbook (POH) Temporary Change Information in this Temporary Change adds to, supersedes, or deletes information in the basic Pilot’s Operating Handbook. Affected SR22 Pilot’s Operating Handbook: Publications: • PN 13772-006 Original (FAA Approved) •...
  • Page 18 TPOH Cirrus Design POH Temporary Change SR22 Intentionally Left Blank 2 of 2 TPOH 18-06 11 May 2018...
  • Page 19 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 20 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 21 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 22 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 23 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 24 Front Matter Cirrus Design Foreword SR22 Intentionally Left Blank Front Matter-6 P/N 13772-006 Original Issue...

  • Page 25: Table Of Contents

    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 26 Section 1 Cirrus Design General SR22 Intentionally Left Blank P/N 13772-006 Original Issue...

  • Page 27: 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 28 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 29 Cirrus Design Section 1 SR22 General 49.3" 39.8" Fuselage Station 49.7" 38.5" 27.0" 16.0" 20.0" 32.0" 10.5" 39.0" 33.4" 20.0" 33.3" 5.0" 21.0" CABIN DOOR BAGGAGE DOOR OPENING OPENING SR22_FM01_5315 Location Length Width Height Volume 122” 49.3” 49.7 137 cu ft Cabin 36”...
  • Page 30 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 31: 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 32: 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 33: 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 34: 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 35: 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 36: 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 37 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 38 Section 1 Cirrus Design General SR22 Intentionally Left Blank 1-14 P/N 13772-006 Original Issue...
  • Page 39 Max Viz Enhanced Vision System (Optional) ....... 23 MD302 Standby Attitude Module (Optional) ......... 23 Air Conditioning System (Optional)..........23 Inflatable Restraint System............23 Flap Limitations................23 Paint....................24 Cirrus Airframe Parachute System (CAPS) ........24 P/N 13772-006 Original Issue...

  • Page 40: Section 2: Limitations

    Section 2 Cirrus Design Limitations SR22 Other Limitations ................24 Smoking ..................24 Placards ................... 25 P/N 13772-006 Original Issue...

  • Page 41: Introduction

    Cirrus Design Section 2 SR22 Limitations Introduction The limitations included in this Section of the Pilot’s Operating Handbook (POH) are approved by the 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 42: 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 43: 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 44: 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 45: 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 ........Constant Speed, Three Blade...

  • Page 46: 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 47: 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 48: 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 3400...

  • Page 49: 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 50: 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 51 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 52 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 53 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 54: 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 55: 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 13772-006...

  • Page 56: 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 shown in the following illustration.

  • Page 57: 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 190-02184-XX, where X can be any digit from 0 to 9) must be immediately available to the pilot during flight.
  • Page 58 RNAV approaches must be conducted utilizing the GPS sensor. g. 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 59 Cirrus Design Section 2 SR22 Limitations Perspective Integrated Avionics System will provide automatic, temperature-compensated glidepath vertical guidance and has been shown to meet the accuracy requirements of VFR/IFR enroute, terminal, and approach Baro-VNAV operations within the conterminous US and Alaska in accordance with the criteria in AC 20-138D.

  • Page 60: Stormscope Weather Information System (Optional)

    Section 2 Cirrus Design Limitations SR22 SVS imagery. The synthetic vision system is not intended to be used independently of traditional attitude instrumentation. Consequently, disabled when traditional attitude instrumentation is not available. Otherwise, the traditional attitude instrumentation will always be visible in the foreground with SVS features in the background.

  • Page 61: Max Viz Enhanced Vision System (Optional)

    Cirrus Design Section 2 SR22 Limitations 2. When option installed, the appropriate revision of the L-3 Avionics Systems WX500 Stormscope Series II Weather Mapping Sensor User’s Guide, (p/n 009-11501-001) must be available to the pilot during flight. Max Viz Enhanced Vision System (Optional) 1.

  • Page 62: Paint

    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 •...
  • Page 63 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 64 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: OPEN Wing, adjacent to fluid filler cap: TKS ICE PROTECTION FLUID USE ONLY AL-5 (DTD-406B) FLUID 4.0 US GALLONS (15.1 LITERS)
  • Page 65 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 66 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 67 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 68 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 69 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 Landing Guidance................
  • Page 70 Section 3 Cirrus Design Emergency Procedures SR22 Fuel System Emergencies ............... 23 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 71: Introduction

    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 72: Cirrus Airframe Parachute System (Caps)

    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 73: 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 74: 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 75: 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 76: 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 77: 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 13772-006...

  • Page 78: 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 79: 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 80: 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 81: 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 82: 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 83: 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 84: 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.

  • Page 85: 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 86: 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 87 Cirrus Design Section 3 SR22 Emergency Procedures 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 88: 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. (1) Prepare for potential engine failure.

  • Page 89: 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 90: 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 91: 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 92: 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 93: 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 94: High Voltage On Main Bus 2

    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 95: 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 96: 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.

  • Page 97: Oxygen System Emergencies

    Cirrus Design Section 3 SR22 Emergency Procedures Oxygen System Emergencies Oxygen System Fault - Above 10,000 Ft OXYGEN FAULT Warning OXYGEN FAULT 1. Oxygen Flow Rate ............. CHECK If no flow: 2. Initiate Emergency Descent to below 10,000 ft: a. Power Lever..............IDLE b.

  • Page 98: Oxygen Quantity Low

    Section 3 Cirrus Design Emergency Procedures SR22 Oxygen Quantity Low OXYGEN QTY Warning OXYGEN QTY 1. Oxygen Pressure and Flow Rate ........CHECK 2. Initiate Normal Descent (non-emergency) below 10,000 ft. 3. Oxygen Flow Rate............MONITOR Below 10,000 ft: 4. Flight ................CONTINUE Remain below altitudes requiring supplemental oxygen.

  • Page 99: 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 100: 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 101: 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 13772-006...

  • Page 102: 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. Land as soon as possible.

  • Page 103: 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 104: 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 105 – 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 106 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 107 Cirrus Design Section 3A SR22 Abnormal Procedures Section 3A: Abnormal Procedures Table of Contents Introduction ..................3 Abnormal Procedures Guidance ............4 Circuit Breakers ................4 Landing Guidance................4 Flight Environment ................6 Inadvertent Icing Encounter ............6 Inadvertent IMC Encounter............. 6 Door Open In Flight ................
  • Page 108 Section 3A Cirrus Design Abnormal Procedures SR22 Flap System Exceedance ............. 20 Landing Gear System ..............21 Brake Failure During Taxi ............. 21 Left/Right Brake Over-Temperature..........21 Oxygen System ................21.1 Oxygen Quantity Low..............21.1 Other Conditions ................22 Aborted Takeoff ................22 Parking Brake Engaged Annunciation ..........

  • Page 109: 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 110: 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 111 Cirrus Design Section 3A SR22 Abnormal Procedures conditions, and services available. However, in no case shall a suitable landing airfield be discounted in the name of convenience. Land as soon as possible Land without delay at the first site at which a safe landing can be made.

  • Page 112: Flight Environment

    Section 3A Cirrus Design Abnormal Procedures SR22 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 113: Abnormal Landings

    Cirrus Design Section 3A SR22 Abnormal Procedures 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 114: Engine System

    Section 3A Cirrus Design Abnormal Procedures SR22 Engine System Low Idle Oil Pressure OIL PRESS Caution OIL PRESS 1. If In-Flight ......LAND AS SOON AS PRACTICABLE 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 115: Starter Engaged Annunciation

    Cirrus Design Section 3A SR22 Abnormal Procedures 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 116: Fuel System

    Section 3A Cirrus Design Abnormal Procedures SR22 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 practicable.

  • Page 117: Right Fuel Tank Quantity

    Cirrus Design Section 3A SR22 Abnormal Procedures 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 118 Section 3A Cirrus Design Abnormal Procedures SR22 FUEL IMBALANCE Advisory 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 119: Low Voltage On Main Bus 1

    Cirrus Design Section 3A SR22 Abnormal Procedures 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 120: Low Alternator 1 Output

    Section 3A Cirrus Design Abnormal Procedures SR22 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 121: Low Alternator 2 Output

    Cirrus Design Section 3A SR22 Abnormal Procedures 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 122: Integrated Avionics System

    Section 3A Cirrus Design Abnormal Procedures SR22 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 123: Flight Displays Too Dim

    Cirrus Design Section 3A SR22 Abnormal Procedures 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 124: Pitot Static System

    Section 3A Cirrus Design Abnormal Procedures SR22 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 125: Pitot Heat Current Sensor Annunciation

    Cirrus Design Section 3A SR22 Abnormal Procedures 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...

  • Page 126: Flight Control System

    Section 3A Cirrus Design Abnormal Procedures SR22 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 127 Cirrus Design Section 3A SR22 Abnormal Procedures 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 128 Section 3A Cirrus Design Abnormal Procedures SR22 Oxygen System Oxygen Quantity Low OXYGEN QTY Caution OXYGEN QTY 1. Oxygen Pressure and Flow Rate ........CHECK 2. Oxygen Duration ............CALCULATE a. See Precise Flight Fixed Oxygen System AFMS; calculate duration based on remaining pressure, number of occupants and type of device (mask or cannula).
  • Page 129 Cirrus Design Section 3A SR22 Abnormal Procedures OXYGEN QTY Advisory OXYGEN QTY On-Ground 1. Oxygen Supply ....REPLENISH IF USE OF OXYGEN IS ANTICIPATED In-Flight 1. If use of oxygen is anticipated, verify adequate oxygen supply for flight duration. Refer to Duration chart in Precise Flight Fixed Oxygen System AFMS.
  • Page 130 Section 3A Cirrus Design Abnormal Procedures SR22 Intentionally Left Blank 3A-21.3 TPOH 17-04...

  • Page 131: Landing Gear System

    Cirrus Design Section 3A SR22 Abnormal Procedures 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 132: Other Conditions

    Section 3A Cirrus Design Abnormal Procedures SR22 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 133: Parking Brake Engaged Annunciation

    Cirrus Design Section 3A SR22 Abnormal Procedures 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 134 Section 3A Cirrus Design Abnormal Procedures SR22 Intentionally Left Blank 3A-24 P/N 13772-006 Original Issue...
  • Page 135 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 136 Section 4 Cirrus Design Normal Procedures SR22 Intentionally Left Blank P/N 13772-006 Original Issue...

  • Page 137: Introduction

    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 138: Normal Procedures

    Section 4 Cirrus Design Normal Procedures SR22 Normal Procedures Preflight Inspection (All Serials) 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;...
  • Page 139 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 Avionics Master Switch............ON...
  • Page 140 Section 4 Cirrus Design Normal Procedures SR22 b. COM 1 Antenna (top) ..CONDITION AND ATTACHMENT c. Transponder Antenna (underside) ....CONDITION AND ATTACHMENT d. COM 2 Antenna (underside)......CONDITION AND ATTACHMENT e. Wing/Fuselage Fairing..........CHECK Baggage Door ........CLOSED AND SECURE g.
  • Page 141 Cirrus Design Section 4 SR22 Normal Procedures 6. Right Wing Tip a. Tip ..............ATTACHMENT b. Strobe, Nav Light and Lens ..CONDITION AND SECURITY c. Fuel Vent (underside) ......... UNOBSTRUCTED 7. Right Wing Forward and Main Gear a. Leading Edge and Stall Strips ......CONDITION b.
  • Page 142 Section 4 Cirrus Design Normal Procedures SR22 10. Nose, Left Side a. Landing Light ............CONDITION b. Engine Oil ..CHECK 6-8 QUARTS, LEAKS, CAP & DOOR SECURE c. Cowling .......... ATTACHMENTS SECURE d. External Power ..........DOOR SECURE e. Vortex Generator ..........CONDITION Exhaust Pipe(s) ......
  • Page 143 Cirrus Design Section 4 SR22 Normal Procedures Supplemental Preflight Inspection (Serials w/ FIKI) 14. Cabin a. Circuit Breakers ..............SET b. Battery 1 Master Switch ............ON c. Flaps................100% d. Avionics Master Switch............ON e. Cabin Speaker..............ON Cabin Door ..............CLOSE g.
  • Page 144 Section 4 Cirrus Design Normal Procedures SR22 15. Empennage a. Stabilizers Porous Panels ..CONDITION AND SECURITY (1) Verify evidence of deicing fluid along length of panels and elevator horns. b. Vertical Porous Panels....CONDITION AND SECURITY (1) Verify evidence of deicing fluid along length of panels.
  • Page 145 Cirrus Design Section 4 SR22 Normal Procedures 21. Cabin a. Fluid Quantity ......VERIFY 5 GALLONS MINIMUM b. ICE PROTECT System Switch .......... OFF c. Flaps..................0% d. Cabin Speaker..............OFF e. Avionics Master Switch............OFF Battery 1 Master Switch ............ OFF...
  • Page 146 Section 4 Cirrus Design Normal Procedures SR22 Intentionally Left Blank 4-8.4 TPOH 17-02 27 Jul 2018...

  • Page 147: 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 148: 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 149 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 150: Before 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 151: Before Takeoff

    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 152 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 153: 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 154: 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 155: 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 156: 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 157: Cruise Leaning

    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 to...

  • Page 158: 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 159: 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...

  • Page 160: Balked Landing/Go-Around

    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 161: 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 162: 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 163: 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 164 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 165: 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 166: Lead Reduction Before Shut Down

    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 167: 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 168 Section 4 Cirrus Design Normal Procedures SR22 Intentionally Left Blank 4-30 P/N 13772-006 Original Issue...
  • Page 169 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 ........
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  • Page 171: 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 172: 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 173: 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 174: 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 175: 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 176: 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 177: 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 178: 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 179: 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 180: 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 181 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 182: 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 183: 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 184 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 185: 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 186: 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 187: 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 188: 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 189: 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 190: 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 191: 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 192 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 193: 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 194 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 195: 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 196: 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 197: 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 198: 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 199: Landing Distance - Flaps 50

    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 200: Landing Distance - Flaps 0

    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 201 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 202 Section 6 Cirrus Design Weight and Balance Data SR22 Intentionally Left Blank P/N 13772-006 Original Issue...

  • Page 203: P/N 13772-006

    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 204 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 205 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 206 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 207 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 208 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 209 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 13772-006 P/N 13772-006 Original Issue...
  • Page 210 Section 6 Cirrus Design Weight and Balance Data SR22 Intentionally Left Blank 6-10 P/N 13772-006 Original Issue...
  • Page 211 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 212 Section 7 Cirrus Design Systems Description SR22 Engine ....................35 Engine Controls ................35 Engine Indicating ................36 Engine Lubrication System ............39 Ignition and Starter System............40 Air Induction System ..............40 Engine Exhaust................40 Engine Fuel Injection ..............41 Engine Cooling................
  • Page 213 Emergency Locator Transmitter (ELT) ......... 96 Fire Extinguisher................98 Hour Meters .................. 99 Emergency Egress Hammer............99 Convenience Outlet(s) ..............99 Cirrus Airframe Parachute System ..........100 System Description ..............100 Activation Handle ................ 101 Deployment Characteristics ............102 P/N 13772-006...
  • Page 214 Section 7 Cirrus Design Systems Description SR22 Intentionally Left Blank P/N 13772-006 Original Issue...
  • Page 215 Cirrus Design TPOH SR22 AFM Temporary Change Section 7 - Systems Description Landing Gear Main Gear Serials after SB2X-32-21: Each main gear wheel has a 15 x 6.00 x 6 tubeless tire installed. Nose Gear Serials after SB2X-32-21: The tubeless nosewheel tire measures 5.00 x 5.
  • Page 216 TPOH Cirrus Design AFM Temporary Change SR22 Intentionally Left Blank 4 of 8 TPOH 15-15R1...

  • Page 217: 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 218: 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 219: 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 220: 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 221 Cirrus Design Section 7 SR22 Systems Description SR22_FM07_5342 Figure 7-1 Elevator System P/N 13772-006 P/N 13772-006 Original Issue...

  • Page 222: 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 223 Cirrus Design Section 7 SR22 Systems Description SR22_FM07_5344 Figure 7-2 Aileron System P/N 13772-006 P/N 13772-006 7-11 7-11 Original Issue...

  • Page 224: 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 225 Cirrus Design Section 7 SR22 Systems Description SR22_FM07_5345 Figure 7-3 Rudder System P/N 13772-006 P/N 13772-006 7-13 7-13 Original Issue...

  • Page 226: 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 227 USB POWER 5 VDC, 2.1 AMPS AUDIO MAX PER PORT INPUT Legend 1. Cirrus Airframe Parachute System 13. Engine & Fuel System Controls (CAPS) Activation T-Handle Cover 14. Left Side Console 2. Magnetic Compass · Circuit Breaker Panel 3. Multifunction Display ·...
  • Page 228 USB POWER 5 VDC, 2.1 AMPS AUDIO MAX PER PORT INPUT Legend 1. Cirrus Airframe Parachute System 13. Engine & Fuel System Controls (CAPS) Activation T-Handle Cover 14. Left Side Console 2. Magnetic Compass · Circuit Breaker Panel 3. Multifunction Display ·...

  • Page 229: 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 230 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 231: 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 232: Airspeed Indicator

    Section 7 Cirrus Design Systems Description SR22 Serials 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 233: Altimeter

    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 234 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 235: 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 236: 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 237: 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 238 Section 7 Cirrus Design Systems Description SR22 SR22_FM07_5349 Figure 7-6 Wing Flaps 7-26 P/N 13772-006 Original Issue...

  • Page 239: 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 240 Section 7 Cirrus Design Systems Description SR22 Brake system malfunction or impending brake failure may be indicated by a gradual decrease in braking action after brake application, noisy or dragging brakes, soft or spongy pedals, excessive travel, and/or weak braking action. A temperature sensor is mounted to each brake assembly and provides measured brake temperatures to the avionics system for caution and warning annunciation.

  • Page 241: 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 242: 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 243: 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 244 Section 7 Cirrus Design Systems Description SR22 • Caution • No slack may exist between the occupant’s shoulder and restraint harness shoulder strap. Stow the seat belts in the latched position when not in use. To use the restraints: 1. Slip arms behind the harness so that the harness extends over shoulders.
  • Page 245 Cirrus Design Section 7 SR22 Systems Description • Caution • Do not route child seat top tether over or around seat back. The top tether must be routed through the seat back pass- through for the child seat to function properly.

  • Page 246: 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 247: 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 248: 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 249 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 250 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 251: Engine Lubrication System

    Cirrus Design Section 7 SR22 Systems Description Oil Pressure Oil Pressure is shown in the upper right corner of the ENGINE page, opposite the oil temperature scale, as both a simulated pressure gage and as a digital value. The gage pointer sweeps a scale range from 0 to 90 PSI in 10 PSI increments.

  • Page 252: Ignition And Starter System

    Section 7 Cirrus Design Systems Description SR22 propeller pitch. The complete oil system is contained in the engine. An oil filler cap and dipstick are located at the left rear of the engine. The filler cap and dipstick are accessed through a door on the top left side of the engine cowling.

  • Page 253: Engine Fuel Injection

    Cirrus Design Section 7 SR22 Systems Description lower cowling. A muff type heat exchanger, located around the right muffler, provides cabin heat. Engine Fuel Injection The multi-nozzle, continuous-flow fuel injection system supplies fuel for engine operation. An engine driven fuel pump draws fuel from the selected wing tank and passes it to the mixture control valve integral to the pump.

  • Page 254: 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 255: 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 256: 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 257 Cirrus Design Section 7 SR22 Systems Description ANNUNCIATOR FUEL INDICATION VENT VENT FILLER FILLER L. WING TANK R. WING TANK R. WING L. WING COLLECTOR COLLECTOR CHECK CHECK VALVE VALVE SELECTOR FLAPPER FLAPPER VALVE VALVE VALVE DRAIN FIREWALL (5 PLACES)

  • Page 258: 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 259 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 260 Section 7 Cirrus Design Systems Description SR22 • Note • For specific pilot actions in response to Fuel System Annunciations, refer to Section 3 - Emergency Procedures, Fuel System Emergencies, and Section 3A - Abnormal Procedures, Fuel System. For additional information on Engine Instrument Markings and...
  • Page 261 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 262: 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 263: 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 264 Section 7 Cirrus Design Systems Description SR22 100A LANDING LIGHT ALT 1 7.5A ALT 1 VOLT REG RELAY LANDING LIGHT SWITCH EXTERNAL POWER RELAY ALT 1 EXTERNAL SWITCH POWER 125A BAT 1 BAT 1 BAT 1 SWITCH RELAY STARTER STARTER...

  • Page 265: Power Distribution

    Cirrus Design Section 7 SR22 Systems Description 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 266 Section 7 Cirrus Design Systems Description SR22 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 267 Cirrus Design Section 7 SR22 Systems Description 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 268 Section 7 Cirrus Design Systems Description SR22 AVIONICS PROTECT 2 PROTECT 1 LANDING STDBY ALT2 LIGHTS ATTD B CONV ENGINE MFD B LIGHTS SERVO INSTR STALL CABIN LIGHTS A/C COND CAMERA WARNING / OXYGEN 12V & USB ROLL FUEL QTY...
  • Page 269 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 270: Electrical Indicating

    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 271 Cirrus Design Section 7 SR22 Systems Description window located to the right of the Altimeter and Vertical Speed Indicator. In combination with a CAS alert, the affected electrical parameter displayed on the ENGINE page changes to the corresponding color of CAS alert and the annunciation system issues an audio alert.
  • Page 272 Section 7 Cirrus Design Systems Description SR22 Anti Ice - TKS (H+MM) Time 0+00 0+00 High Density Alt 8000 Ft 0+00 Norm Oat 31°F -1°C (ISA +0°C) Range Electrical System Indication 8 9 10 Electrical and Lighting Controls LEGEND 7. Avionics 1.

  • Page 273: 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 274: 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 275: Convenience Lighting

    Cirrus Design Section 7 SR22 Systems Description The panel lights operate on 28 VDC supplied through the 5-amp CABIN LIGHTS circuit breaker on MAIN BUS 1. Reading Lights Individual eyeball-type reading lights are installed in the headliner above each passenger position. Each light is aimed by positioning the lens in the socket and is controlled by a push-button switch located next to the light.
  • Page 276 Section 7 Cirrus Design Systems Description SR22 Entry Step Lights Illumination of the entry steps is provided by lights located above each step. Convenience lighting is controlled by the cabin light switch located on the ceiling of the airplane. 28 VDC for convenience lighting is supplied through the 3-amp CONV LIGHTS circuit breaker on the CONS BUS.

  • Page 277: Environmental System

    Cirrus Design Section 7 SR22 Systems Description 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 278: Heating

    Section 7 Cirrus Design Systems Description SR22 Heating is accomplished by mixing ventilation air from the fresh air inlet with heated air provided by the heat exchanger in the mixing chamber on the firewall. From the mixing chamber - which also...
  • Page 279 Cirrus Design Section 7 SR22 Systems Description compressor then pumps the vapor to the condenser where it cools, changes to a liquid, and passes to the receiver-drier. The receiver- drier’s function is to filter, remove moisture, and ensure a steady flow...
  • Page 280 Section 7 Cirrus Design Systems Description SR22 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 281 Cirrus Design Section 7 SR22 Systems Description 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 282: Airflow Selection

    Section 7 Cirrus Design Systems Description SR22 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 283 Cirrus Design Section 7 SR22 Systems Description firewall completely closes and the air-conditioner is activated. When recirculation button is pushed, the fresh air valve completely closes and cabin air is recirculated to provide for maximum air conditioning operation. When the air conditioning system is on and the temperature selector is rotated to the full cool position, recirculating mode can be activated to provide maximum cabin cooling.
  • Page 284 Section 7 Cirrus Design Systems Description SR22 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 285 Cirrus Design Section 7 SR22 Systems Description 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 286 Section 7 Cirrus Design Systems Description SR22 Pitot-Static System The Pitot-Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage. The Pitot heat is pilot controlled through a panel-mounted switch. An internally mounted alternate static pressure source provides backup static pressure should that the primary static source becomes blocked.
  • Page 287 Cirrus Design Section 7 SR22 Systems Description ADAHRS 1 ADAHRS 2 (optional) PFD Air Data AIRSPEED ALTIMETER INDICATOR ALTERNATE PITOT-STATIC STATIC WATER TRAPS AIR SOURCE PITOT MAST STATIC HEATER Annunciation BUTTONS PITOT HEAT CURRENT SENSOR LOGIC PITOT 7.5A HEAT ENGINE AIRFRAME UNIT...
  • Page 288 Section 7 Cirrus Design Systems Description SR22 ADAHRS 1 ADAHRS 2 (optional) 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 HEAT...

  • Page 289: Avionics

    Cirrus Design Section 7 SR22 Systems Description 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. System components include: •...
  • Page 290 Section 7 Cirrus Design Systems Description SR22 XM SATELLITE DATA LINK RECEIVER (optional) KEYBOARD MAG 1 MAG 2 AUTOPILOT MODE CONTROLLER (optional) ADAHRS 1 ADAHRS 2 (optional) IRIDIUM GLOBAL SATELLITE DATALINK (optional) INTEGRATED INTEGRATED AVIONICS AVIONICS UNIT 2 UNIT 1...
  • Page 291 Cirrus Design Section 7 SR22 Systems Description GDU 1050A Primary Flight Display (PFD), 10-inch, or GDU 1250A, 12-inch (optional) 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 292 Section 7 Cirrus Design Systems Description SR22 Redundant power sources provide 28 VDC for MFD operation. Power is supplied through the 5-amp MFD A circuit breaker on MAIN BUS 3 and the 5-amp MFD B circuit breaker on MAIN BUS 1. Either circuit is capable of powering the MFD.
  • Page 293 Cirrus Design Section 7 SR22 Systems Description 3 4 5 6 7 8 9 13 14 15 19 20 21 Legend 1. Soft Keys 12. MFD 2. PFD 13. PFD Direct-to-Course 3. PFD Range/Pan Joystick 14. PFD Flight Plan Page 4.
  • Page 294 Section 7 Cirrus Design Systems Description SR22 Flight Management System Keyboard LEGEND 22. MFD Clear/Cancel Information 32. MFD Range/Pan Joystick 23. MFD Flight Plan Page 33. Frequency Transfer (121.5 Tune) 24. MFD Direct-to-Course 34. MFD CRS/XPDR/NAV/COM Control 25. MFD Menu 35.
  • Page 295 Cirrus Design Section 7 SR22 Systems Description GIA 63W/64W 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 296 Section 7 Cirrus Design Systems Description SR22 28 VDC for Audio Panel operation is supplied through the 5-amp AUDIO PANEL circuit breaker on the AVIONICS bus. For a detailed operating instructions, refer to the GMA 350 or 350c Audio Panel Pilot’s Guide.
  • Page 297 Cirrus Design Section 7 SR22 Systems Description 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 298 Section 7 Cirrus Design Systems Description SR22 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 299 Cirrus Design Section 7 SR22 Systems Description 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_FM07_5360 Figure 7-19 Baro-VNAV Vertical Deviation Indicator P/N 13772-006 P/N 13772-006 7-87...
  • Page 300 Section 7 Cirrus Design Systems Description SR22 Optional Avionics GTX 345 Mode S Transponder w/ UAT in The GTX 345 solid state transponder communicates with the primary Integrated Avionics Unit and performs the following functions: • UAT Reception: The GTX 345 receives ADS-B, ADS-R, and TIS-B data transmitted on the 978 MHz frequency from other aircraft, vehicles, and ground stations for traffic awareness.
  • Page 301 Cirrus Design Section 7 SR22 Systems Description 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 provides digital XM audio entertainment to the cabin audio system via the audio panel.
  • Page 302 Section 7 Cirrus Design Systems Description SR22 28 VDC for Weather System operation is supplied through the 5-amp DATA LINK/WEATHER 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. If applicable, refer to the L-3 Stormscope WX-500 Weather Mapping Sensor Pilot’s Guide...
  • Page 303 Cirrus Design Section 7 SR22 Systems Description • Flight path marker, • Terrain warning system, • Field of view depiction on the MFD Navigation Page. Refer to the Perspective Integrated Avionics System Pilot’s Guide for a complete description of the system, its operating modes, and additional detailed operating procedures.
  • Page 304 PFD to improve pilot situational awareness during ground operations and air operations in the airport environment. Refer to the Cirrus Perspective Integrated Flight Deck Pilot’s Guide for a detailed discussion of the SurfaceWatch feature. Flight Stream 510 Wireless Avionics Interface The Flight Stream 510 Wireless Avionics Interface allows the connection of a compatible mobile electronic device to the avionics.
  • Page 305 Cirrus Design TPOH SR22 AFM Temporary Change LEGEND 1. GSU 75 ADAHRS 1 2. Integrated Avionics Unit 1 3. GSU 75 ADAHRS 2 4. Avionics Cooling Fan 5. Integrated Avionics Unit 2 6. Engine Airframe Unit 7. ADF (opt) 8. GMC 707 Mode Controller 9.
  • Page 306 TPOH Cirrus Design AFM Temporary Change 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 307 Cirrus Design Section 7 SR22 Systems Description headsets. Headset jacks for the pilot, front, and rear seat passenger are located in the map case. The forward headset mics use the remote Push-To-Talk (PTT) switches located on the top of the associated control yoke grip. The rear headsets do not have COM transmit capabilities and do not require PTT switches.
  • Page 308 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 309 Cirrus Design Section 7 SR22 Systems Description “ARM/OFF” - “TEST”, and a red LED annunciator. The red LED annunciator flashes when the ELT is transmitting. CENTER CONSOLE (REF) ELT SHELF (REF) LEGEND 1. LED Annunciator 2. Remote Switch 3. Antenna 4 Remote Cable 5.
  • Page 310 Section 7 Cirrus Design Systems Description SR22 accident. Access the unit as described below and set the ELT transmitter control switch to the ON position. 1. Remove avionics bay access panel along aft portion of RH fuselage or lower aft center access panel of baggage compartment.
  • Page 311 Cirrus Design Section 7 SR22 Systems Description pulled, and the canister has not been damaged. The unit should weigh approximately 2.5 lb (1.1 kg). For preflight, charge can be determined by verifying the gage pressure is in the operable (green) range, or by ‘hefting’...
  • Page 312 Systems Description SR22 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 313 Cirrus Design Section 7 SR22 Systems Description 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 314 Section 7 Cirrus Design Systems Description SR22 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 315 Cirrus Design Section 7 SR22 Systems Description • Caution • Ground impact is expected to be equivalent to touchdown from a height of approximately 13 feet. While the airframe, seats and landing gear are designed to accommodate this stress, occupants must prepare for it in accordance with...
  • Page 316 Section 7 Cirrus Design Systems Description SR22 Intentionally Left Blank 7-104 P/N 13772-006 Original Issue...
  • Page 317 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 318 Section 8 Cirrus Design Handling and Servicing SR22 Intentionally Left Blank P/N 13772-006 Original Issue...
  • Page 319 Cirrus Design TPOH SR22 AFM Temporary Change Section 8 - Handling, Servicing, and Maintenance Servicing Landing Gear Servicing Serials after SB2X-32-21: The main landing gear wheel assemblies use 15 x 6.00 x 6 tubeless tires. The nose wheel assembly uses a 5.00 x 5 tubeless tire.
  • Page 320 TPOH Cirrus Design AFM Temporary Change SR22 Tire Inflation Serials after SB2X-32-21: To inflate tires: 1. Remove inspection buttons on wheel pants to gain access to valve stems. It may be necessary to move airplane to get valve stem aligned with the access hole.

  • Page 321: 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 322: 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 13772-006 Original Issue...

  • Page 323: 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 324: 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 325: 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 326: 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 327 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 328: 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 329: 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 330: Parking

    Section 8 Cirrus Design Handling and Servicing SR22 • Caution • Verify that taxi and propeller wash areas are clear before beginning taxi. Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones, gravel, or any loose material that may cause damage to the propeller blades.

  • Page 331: Tiedown

    Cirrus Design Section 8 SR22 Handling and Servicing • Caution • Care should be taken when setting overheated brakes or during cold weather when accumulated moisture may freeze a brake. 4. Chock both main gear wheels. 5. Tie down airplane in accordance with tiedown procedure in this section.

  • Page 332: Jacking

    Section 8 Cirrus Design Handling and Servicing SR22 Jacking Three jacking points, located at each wing tiedown and tail tiedown, are provided to perform maintenance operations. Tie-down rings must be removed and replaced with jack points prior to lifting. Jack points are stowed in the baggage compartment.
  • Page 333 Cirrus Design Section 8 SR22 Handling and Servicing Lower Airplane 1. Release pressure on all jacks simultaneously to keep airplane as level as possible. 2. Remove jacks, jack points, and tailstand. Stow points in baggage compartment. 3. Install tiedown rings.

  • Page 334: Servicing

    Section 8 Cirrus Design Handling and Servicing SR22 Servicing Landing Gear Servicing The main landing gear wheel assemblies use 15 x 6.00 x 6 tubeless tires. The nose wheel assembly uses a 5.00 x 5 tubeless tire. Always keep tires inflated to the rated pressure to obtain optimum performance and maximum service.

  • Page 335: Propeller Servicing

    Cirrus Design Section 8 SR22 Handling and Servicing 2. Remove valve stem cap and verify tire pressure with a dial-type tire pressure gage. • Caution • The LH and RH main wheel tire pressures must be within 20 psi of each other to ensure the load is evenly distributed between the main wheels.

  • Page 336: 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 337 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 338: 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 339: Fuel Contamination And Sampling

    Cirrus Design Section 8 SR22 Handling and Servicing Do not permit fuel nozzle to come in contact with bottom of fuel tanks. Keep fuel tanks at least half full at all times to minimize condensation and moisture accumulation in tanks. In...

  • Page 340: Draining Fuel System

    Section 8 Cirrus Design Handling and Servicing SR22 If sampling reveals the airplane has been serviced with an improper fuel grade, do not fly the airplane until the fuel system is drained and refueled with an approved fuel grade. To help reduce the occurrence of contaminated fuel coming from the...

  • Page 341: 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 342: Artex Elt 1000 Servicing

    Section 8 Cirrus Design Handling and Servicing SR22 Artex ELT 1000 Servicing The ELT batteries must be inspected in accordance with the Airplane Maintenance Manual, 5-20 - Scheduled Maintenance Checks. The ELT batteries must be replaced upon reaching the date stamped on the batteries, after an inadvertent activation of unknown duration, or whenever the batteries have been in use for one cumulative hour.
  • Page 343 Cirrus Design Section 8 SR22 Handling and Servicing 1. Tune aircraft receiver to 121.5 MHz. 2. Push switch lever to TEST position for approximately 1 second, then release. 3. Results of the test are displayed by a series of indications (flash codes), where the local LED, remote switch LED and buzzer(s) activate for ½...

  • Page 344: 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 345 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 346: 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 347 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 348 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 349 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 350 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 351 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 352: 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 353 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 354 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 355 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 356 Section 8 Cirrus Design Handling and Servicing SR22 Intentionally Left Blank 8-38 P/N 13772-006 Original Issue...
  • Page 357 Cirrus Design Section 9 SR22 Log of Supplements Section 9: Log of Supplements As Required P/N 13772-006, 13772-006AR, 13772-006E, 21400-006 Original Issue...
  • Page 358 This Log of Supplements shows all Cirrus 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 359 SR22 Safety Information Section 10: Safety Information Table of Contents Introduction ..................3 Cirrus Airframe Parachute System (CAPS) ........4 Deployment Scenarios..............4 General Deployment Information ............ 6 Landing Considerations ..............7 Taxiing, Steering, and Braking Practices ......... 10 Operating Practices ..............10 Brake Maintenance ...............
  • Page 360 Section 10 Cirrus Design Safety Information SR22 Intentionally Left Blank 10-2 P/N 13772-006 Original Issue...
  • Page 361 Cirrus Design TPOH SR22 AFM Temporary Change Section 10 - Safety Information Taxiing, Steering, and Braking Practices Operating Practices Serials after SB2X-32-21: Observe the following operating practices: • Verify that the parking brake is completely disengaged before taxi. • The rudder is effective for steering on the ground and should be used.
  • Page 362 TPOH Cirrus Design AFM Temporary Change SR22 Intentionally Left Blank 8 of 8 TPOH 15-15R1...

  • Page 363: 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 364: 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 365 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 366: General Deployment Information

    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 367 Cirrus Design Section 10 SR22 Safety Information Deployment Attitude The CAPS has been tested in all flap configurations at speeds ranging from Vso to Va. Most CAPS testing was accomplished from a level attitude. Deployment from a spin was also tested. From these tests it was found that...
  • Page 368 Section 10 Cirrus Design Safety Information SR22 There is the possibility that one or both doors could jam at impact. If this occurs, to exit the airplane, the occupants will have to force open a partially jammed door or break through a door window using the Emergency Exit Hammer located in the lid of the center armrest.
  • Page 369 Cirrus Design Section 10 SR22 Safety Information unlatching a door immediately prior to assuming the emergency landing body position should be considered to assure rapid egress. Ground Gusts If it is known or suspected that ground gusts are present in the landing zone, there is a possibility that the parachute could drag the airplane after touchdown, especially if the terrain is flat and without obstacles.

  • Page 370: Taxiing, Steering, And Braking Practices

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

  • Page 371: Brake Maintenance

    Cirrus Design Section 10 SR22 Safety Information • 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 372 Section 10 Cirrus Design Safety Information SR22 Intentionally Left Blank 10-12 P/N 13772-006 Original Issue...

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