Cirrus SR22T Pilot Operating Handbook

Cirrus SR22T Pilot Operating Handbook

Aircraft serials sr22t-0442 & subsequent with teledyne continental motors turbocharged engine 3600 pound takeoff weight
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PILOT’'S OPERATING HANDBOOK
AND FAA APPROVED
AIRPLANE FLIGHT MANUAL
for the
CIRRUS SR22T
A i r c r a f t S e r i a l s S R 2 2 T - 0 4 4 2 & S u b s e q u e n t w i t h
T e l e d y n e C o n t i n e n t a l M o t o r s T u r b o c h a r g e d E n g i n e
3 6 0 0 P o u n d T a k e o f f W e i g h t
FAA Approved in Normal Category based on FAR 23. This document must be carried in
the airplane at all times and be kept within the reach of the pilot during all flight
operations.
THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO
THE PILOT BY FAR PART 23 AND ADDITIONAL INFORMATION PROVIDED BY
CIRRUS DESIGN AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT
MANUAL.
Model - Serial Num.:
Registration Num.:
CoverPage-i
P/N 13772-005
Original Issue: February 01, 2013

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Summary of Contents for Cirrus SR22T

  • 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 © 2013 - All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811 CoverPage-ii P/N 13772-005 Original Issue: February 01, 2013...
  • Page 3 Cirrus Design Pilot’s Operating Handbook SR22T List of Effective Pages List of Effective Pages Use this page to determine the current effective date for each page in the POH. Supplements are issued individually and are controlled by the Log of Supplements Page in Section 9.
  • Page 4: Table Of Contents

    Cirrus Design Pilot’s Operating Handbook SR22T List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status Original Issue 5-30 Original Issue 7-37 Original Issue Original Issue 5-31 Original Issue 7-38 Original Issue Original Issue 5-32...
  • Page 5: Original Issue

    Cirrus Design Pilot’s Operating Handbook SR22T List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 7-92 Original Issue 7-93 Original Issue 7-94 Original Issue Original Issue Original Issue Original Issue Original Issue Original Issue...
  • Page 6: Original Issue

    Cirrus Design Pilot’s Operating Handbook SR22T List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status Intentionally Left Blank P/N 13772-005 Original Issue...
  • Page 7: Original Issue

    Foreword Foreword This Pilot’s Operating Handbook (POH or Handbook) has been prepared by Cirrus Design Corporation to familiarize operators with the aircraft. Read this Handbook carefully. It provides operational procedures that will assure the operator obtains the performance published in the manual, data designed to allow the most efficient use of the airplane, and basic information for maintaining the airplane in a “like new”...
  • Page 8: Original Issue

    Section Front Matter Cirrus Design Foreword SR22T The 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. The Handbook is presented in loose-leaf form for ease in inserting revisions and is sized for convenient storage.
  • Page 9: Original Issue

    Original issue pages will be identified by the words “Original Issue” at this location. In the event that the majority of pages in the Handbook are revised, Cirrus may determine that it is more effective to reissue the Handbook. Reissued pages will be identified by the word “Reissue”...
  • Page 10: Original Issue

    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 Handbook and that the supplement is properly recorded on the “Log of...
  • Page 11: Original Issue

    Cirrus Design Section Front Matter SR22T Foreword Retention of Data In the event a new title page is issued, the weight and balance data changes, equipment list changes, or the “Log of Supplements” is replaced, the owner must ensure that all information applicable to the airplane is transferred to the new pages and the aircraft records are current.
  • Page 12: Original Issue

    Section Front Matter Cirrus Design Foreword SR22T Intentionally Left Blank Front Matter-6 P/N 13772-005 Original Issue...
  • Page 13: Original Issue

    Cirrus Design Section 1 SR22T General Section 1: General Table of Contents Introduction ..................3 The Airplane..................7 Engine..................... 7 Propeller ..................7 Fuel....................8 Oil ....................8 Maximum Certificated Weights ............8 Cabin and Entry Dimensions ............8 Baggage Spaces and Entry Dimensions ........8 Specific Loadings................
  • Page 14: Original Issue

    Section 1 Cirrus Design General SR22T Intentionally Left Blank P/N 13772-005 Original Issue...
  • Page 15: Introduction

    Cirrus Design Section 1 SR22T General Introduction This section contains information of general interest to pilots and owners. You will find the information useful in acquainting yourself with the airplane, as well as in loading, fueling, sheltering, and handling the airplane during ground operations.
  • Page 16: Original Issue

    Section 1 Cirrus Design General SR22T 26.0 ft 7.92 m 8.9 ft 2.71 m 9 inches (minimum) 23 cm (minimum) NOTE: • Wing span includes position and strobe lights. • Prop ground clearance - 9" inches (23 cm). • Wing Area = 144.9 sq. ft.
  • Page 17: Original Issue

    Cirrus Design Section 1 SR22T General 49.3" 39.8" Fuselage Station 49.7" 38.5" 27.0" 16.0" 20.0" 10.5" 32.0" 39.0" 33.4" 20.0" 33.3" 5.0" 21.0" CABIN DOOR BAGGAGE DOOR OPENING OPENING SR22_FM01_1019A Location Length Width Height Volume 122” 49.3” 49.7 137 cu ft Cabin 36”...
  • Page 18: Original Issue

    Section 1 Cirrus Design General SR22T GROUND TURNING CLEARANCE 24.3 ft. (7.41 m) RADIUS FOR WING TIP 7.0 ft. (2.16 m) RADIUS FOR NOSE GEAR 0.5 ft. (0.15 m) RADIUS FOR INSIDE GEAR 9.1 ft. (2.77 m) RADIUS FOR OUTSIDE GEAR TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER.
  • Page 19: The Airplane

    Cirrus Design Section 1 SR22T General The Airplane Engine Number of Engines................1 Engine Manufacturer ..........Teledyne Continental Engine Model ..............TSIO-550-K Engine Type..Turbocharged, direct drive, fuel injected, air cooled, horizontally opposed 6 cylinder engine with 550 cubic inch displacement. Horsepower Rating..........315 bhp @ 2500 rpm...
  • Page 20: Fuel

    Section 1 Cirrus Design General SR22T Fuel Total Capacity ..........94.5 U.S. Gallons (358.0 L) Total Usable ..........92.0 U.S. Gallons (348.0 L) Approved Fuel Grades: 100 LL Grade Aviation Fuel (Blue) 100 (Formerly 100/130) Grade Aviation Fuel (Green) Oil Capacity (Sump) ..........8 U.S. Quarts (7.6 L) Oil Grades: All Temperatures ........
  • Page 21: Symbols, Abbreviations And Terminology

    Cirrus Design Section 1 SR22T General Symbols, Abbreviations and Terminology General Airspeed Terminology and Symbols KCAS Knots Calibrated Airspeed is the indicated airspeed corrected position instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level.
  • Page 22: Meteorological Terminology

    Section 1 Cirrus Design General SR22T Stalling Speed is minimum steady flight speed at which the aircraft is controllable with 50% flaps. Stalling Speed is the minimum steady flight speed at which the aircraft is controllable in the landing configuration (100% flaps) at the most unfavorable weight and balance.
  • Page 23: Engine Power Terminology

    Cirrus Design Section 1 SR22T 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 (PA) is the altitude read from the...
  • Page 24: Performance And Flight Planning Terminology

    Section 1 Cirrus Design General SR22T Performance and Flight Planning Terminology One “g” is a quantity of acceleration equal to that of earth’s gravity. Demonstrated Demonstrated Crosswind Velocity is the velocity of Crosswind the crosswind component for which adequate Velocity...
  • Page 25: Original Issue

    Cirrus Design Section 1 SR22T General Arm is the horizontal distance from the reference datum to the center of gravity (CG) of an item. The airplane’s arm is obtained by adding the airplane’s individual moments and dividing the sum by the total weight.
  • Page 26: Original Issue

    Section 1 Cirrus Design General SR22T Tare Tare is the weight of all items used to hold or position the airplane on the scales for weighing. Tare includes blocks, shims, and chocks. Tare weight must be subtracted from the associated scale reading.
  • Page 27: Original Issue

    Environmental Conditions ..............17 Maximum Occupancy ..............18 Systems and Equipment Limits............19 Cirrus Perspective Integrated Avionics System ......19 L-3 Skywatch Traffic Advisory System (Optional)......22 L-3 Stormscope Weather Information System (Optional) ..... 22 Max Viz Enhanced Vision System (Optional) ....... 22 Air Conditioning System (Optional)..........
  • Page 28: Original Issue

    Section 2 Cirrus Design Limitations SR22T Cirrus Airframe Parachute System (CAPS) ........23 Other Limitations ................23 Smoking ..................23 Placards ................... 24 P/N 13772-005 Original Issue...
  • Page 29: Introduction

    Cirrus Design Section 2 SR22T 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 30: Airspeed Limitations

    Section 2 Cirrus Design Limitations SR22T Airspeed Limitations The indicated airspeeds in the following table are based on Section 5, Airspeed Calibration: Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
  • Page 31: Airspeed Indicator Markings

    Cirrus Design Section 2 SR22T Limitations Airspeed Indicator Markings The airspeed indicator markings are based on Section 5, Airspeed Calibration: Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
  • Page 32: Powerplant Limitations

    Section 2 Cirrus Design Limitations SR22T Powerplant Limitations Engine Number of Engines................1 Engine Manufacturer ........... Teledyne Continental Engine Model..............TSIO-550-K Engine Type..Turbocharged, direct drive, fuel injected, air cooled, horizontally opposed 6 cylinder engine with 550 cubic inch displacement. Horsepower Rating..........315 bhp @ 2500 rpm Oil Temperature ..........
  • Page 33: Fuel Grade

    Cirrus Design Section 2 SR22T Limitations Fuel Grade: Aviation Grade 100 LL (Blue) or 100 (green) • Note • Refer to Fuel Limits in this Section for operational limitations regarding fuel and fuel storage. Propeller Hartzell Compact Series Lightweight Hub with Composite Blades Propeller Type ........Constant Speed, Three Blade...
  • Page 34: Engine Instrument Markings & Annunciations

    Section 2 Cirrus Design Limitations SR22T Engine Instrument Markings & Annunciations The following describes the engine instrument markings. Associated Warning and Caution Annunciations are shown in capitalized text. PowerPlant Instrument Yellow Green Yellow (Range & Units) Arc/Bar Arc/Bar Arc/Bar Arc/Bar...
  • Page 35: Fuel

    Cirrus Design Section 2 SR22T Limitations Fuel Instrument Yellow Arc/ Green Arc/ Yellow Arc/ (Range & Units) Arc/Bar Arc/Bar Minimum Minimum Normal Maximum Maximum Caution Range Caution Range Range Fuel Flow –– –– *See Note –– –– (0 – 45 U.S. Gal./Hr.) Fuel Totalizer N <...
  • Page 36: Center Of Gravity Limits

    Section 2 Cirrus Design Limitations SR22T 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 37: Maneuver Limits

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

    Section 2 Cirrus Design Limitations SR22T Kinds of Operation The aircraft is equipped and approved for the following type operations: • VFR day and night. • IFR day and night. Kinds of Operation Equipment List The following listing summarizes the equipment required under Federal Aviation Regulations (FAR) Part 23 for airworthiness under the listed kind of operation.
  • Page 39: Original Issue

    Cirrus Design Section 2 SR22T Limitations Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions Low Volts Annunciator ALT 1 Annunciator ALT 2 Annunciator — — Circuit Breakers As required. Equipment & Furnishings Emergency Locator Trans-...
  • Page 40: Original Issue

    Section 2 Cirrus Design Limitations SR22T Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions Ice & Rain Protection Alternate Engine Air Induc- tion System Alternate Static Air Source Pitot Heater — — Landing Gear Wheel Pants —...
  • Page 41 Cirrus Design Section 2 SR22T Limitations Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions Navigation & Pitot Static Airspeed Indicator Altimeter Magnetic Compass Pitot System Static System, Normal Attitude Indicator — — Clock — —...
  • Page 42: Icing

    Oil Quantity Indicator (Dip- stick) Oil Temperature Indication Turbine Inlet 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. 2-16...
  • Page 43: Taxi Power

    Cirrus Design Section 2 SR22T Limitations Taxi Power Maximum continuous engine speed for taxiing is 1000 RPM on flat, smooth, hard surfaces. Power settings slightly above 1000 RPM are permissible to start motion, for turf, soft surfaces, and on inclines. Use minimum power to maintain taxi speed.
  • Page 44: Maximum Occupancy

    Section 2 Cirrus Design Limitations SR22T Maximum Occupancy Occupancy of this airplane is limited to “4+1” persons, the pilot and four passengers. If carrying three rear seat passengers, occupants must be wearing a seat belt and shoulder harness with their hips and back firmly against the seatback as show in the following illustration.
  • Page 45: Systems And Equipment Limits

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

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

    Cirrus Design Section 2 SR22T Limitations 5. Navigation using the Perspective Integrated Avionics System is not authorized in the following geographic areas: a. north of 70°North latitude (northern polar region), b. south of 70°South latitude (southern polar region), c. north of the 65°North latitude between longitude 75°W and 120°W (Northern Canada),...
  • Page 48: Skywatch Traffic Advisory System (Optional)

    Section 2 Cirrus Design Limitations SR22T 12. Use of the TRAFFIC ADVISORY SYSTEM (TAS) to maneuver the airplane to avoid traffic is prohibited. The TAS is intended for advisory use only. TAS is intended only to help the pilot to visually located traffic.
  • Page 49: Air Conditioning System (Optional)

    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 50: Placards

    Section 2 Cirrus Design Limitations SR22T 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 51: Original Issue

    Cirrus Design Section 2 SR22T Limitations Elevator and Rudder, both sides: NO PUSH Left fuselage, on external power supply door: EXTERNAL POWER 28 V DC Doors, above and below latch: PUSH 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 52: Original Issue

    Section 2 Cirrus Design Limitations SR22T Engine control panel: FLAPS KIAS 100% KIAS CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT RICH TURN BOOST PUMP ON DURING TAKE OFF, CLIMB, LANDING AND SWITCHING FUEL TANKS.
  • Page 53: Original Issue

    Cirrus Design Section 2 SR22T Limitations 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 54: Original Issue

    Section 2 Cirrus Design Limitations SR22T 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 55: Original Issue

    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 56: Original Issue

    Section 2 Cirrus Design Limitations SR22T Intentionally Left Blank 2-30 P/N 13772-005 Original Issue...
  • Page 57: Original Issue

    Cirrus Design Section 3 SR22T Emergency Procedures Section 3: Emergency Procedures Table of Contents Introduction ..................3 Emergency Procedures Guidance ............. 4 CAPS Guidance................4 Preflight Planning................4 Preflight Inspections/Maintenance ..........4 Methodology ................... 4 Circuit Breakers ................5 Memory Items ................. 6 Airspeeds for Emergency Operations ..........
  • Page 58: Original Issue

    Section 3 Cirrus Design Emergency Procedures SR22T Turbine Inlet Temperature High ............ 27 EGT, TIT or CHT Temperature Sensor Failure......28 Propeller System Emergencies ............29 Engine Speed High ............... 29 Propeller Governor Failure............30 Fuel System Emergencies ............... 31 Low Fuel Quantity .................
  • Page 59: Section 3: Emergency Procedures

    Cirrus Design Section 3 SR22T Emergency Procedures Introduction This section provides procedures for handling emergencies and critical flight situations that may occur while operating the aircraft. Although emergencies caused by airplane, systems, or engine malfunctions are extremely rare, the guidelines described in this section should be considered and applied as necessary should an emergency arise.
  • Page 60: Emergency Procedures Guidance

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

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

    Section 3 Cirrus Design Emergency Procedures SR22T • Circuit breakers that “CYCLE” should be pulled, delayed for several seconds, and reset only once. Allow sufficient cooling time for circuit breakers that are reset through a “CYCLE” procedure. Memory Items Checklist steps emphasized by underlining such as the example below, should be memorized for accomplishment without reference to the procedure.
  • Page 63: Airspeeds For Emergency Operations

    Cirrus Design Section 3 SR22T Emergency Procedures Airspeeds for Emergency Operations Maneuvering Speed: 3600 lb ................140 KIAS Best Glide: All Weights ................. 92 KIAS Emergency Landing (Engine-out): Flaps Up ................90 KIAS Flaps 50% ................85 KIAS Flaps 100% ................ 80 KIAS...
  • Page 64: Engine Failures

    Section 3 Cirrus Design Emergency Procedures SR22T Engine Failures Engine Failure On Takeoff (Low Altitude) 1. Best Glide or Landing Speed (as appropriate).... ESTABLISH 2. Mixture ................CUTOFF 3. Fuel Selector ................OFF 4. Ignition Switch ................OFF 5. Flaps ..............AS REQUIRED If time permits: 6.
  • Page 65: Engine Failure In Flight

    If altitude or terrain does not permit a safe landing, CAPS deployment may be required. Refer to Section 10, Cirrus Airframe Parachute System (CAPS) for CAPS deployment scenarios and landing considerations. Excessive engine cooling may be experienced during long descents resulting in low engine oil and cylinder head temperatures.
  • Page 66: Original Issue

    Section 3 Cirrus Design Emergency Procedures SR22T Possible Engine Failure Causes Improper Fuel Management: If the engine failure cause is determined to be improper fuel management, turn off Fuel Pump and resume fight. Engine Driven Fuel Pump Failure: If fuel management is correct, failure of the engine driven fuel pump or a clogged fuel filter is probable.
  • Page 67: Original Issue

    Cirrus Design Section 3 SR22T Emergency Procedures Above 18,000 Feet The manifold pressure should be maintained at or above 15 in.Hg (bottom of the green arc on the manifold pressure gage) when the aircraft is operating above 18,000 feet. If the manifold pressure is reduced below 15 in.Hg and the Power Lever positioned close to or at...
  • Page 68: Airstart

    Section 3 Cirrus Design Emergency Procedures SR22T Airstart Engine Airstart 1. Bat Master Switches ..............ON 2. Power Lever ............OPEN ½ INCH 3. Mixture ..............RICH, AS REQ’D 4. Fuel Selector ............SWITCH TANKS 5. Ignition Switch ............... BOTH 6.
  • Page 69: Smoke And Fire

    Cirrus Design Section 3 SR22T 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 4.
  • Page 70: Engine Fire In Flight

    Section 3 Cirrus Design Emergency Procedures SR22T 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 71: Wing Fire In Flight

    Cirrus Design Section 3 SR22T 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 72: Smoke And Fume Elimination

    Section 3 Cirrus Design Emergency Procedures SR22T Smoke and Fume Elimination 1. Oxygen Masks or Cannulas ............ DON 2. Oxygen System................. ON 3. Oxygen Flow Rate............MAXIMUM 4. Air Conditioner (if installed) ............OFF 5. Temperature Selector............COLD 6. Vent Selector......FEET/PANEL/DEFROST POSITION 7.
  • Page 73: Emergency Descent

    Cirrus Design Section 3 SR22T 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 74: Forced Landing

    Section 3 Cirrus Design Emergency Procedures SR22T Forced Landing 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 75: Ditching

    Cirrus Design Section 3 SR22T 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 76: Engine System Emergencies

    Section 3 Cirrus Design Emergency Procedures SR22T Engine System Emergencies Engine Partial Power Loss 1. Fuel Pump............ HIGH BOOST/PRIME 2. Fuel Selector ............SWITCH TANKS 3. Mixture ......CHECK appropriate for flight conditions 4. Power Lever ............... SWEEP 5. Ignition Switch ............BOTH, L, then R 6.
  • Page 77: Original Issue

    Cirrus Design Section 3 SR22T Emergency Procedures Selecting HIGH BOOST/PRIME may clear the problem if vapor in the injection lines is the problem or if the engine-driven fuel pump has partially failed. The electric fuel pump will not provide sufficient fuel pressure to supply the engine if the engine-driven fuel pump completely fails.
  • Page 78: Oil Pressure Out Of Range

    Section 3 Cirrus Design Emergency Procedures SR22T Oil Pressure Out of Range OIL PRESS Warning OIL PRESS 1. Oil Pressure Gage ............. CHECK If pressure low: a. Power....... REDUCE to minimum for sustained flight b. Land as soon as possible.
  • Page 79: High Cylinder Head Temperature

    Cirrus Design Section 3 SR22T 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 80: Turbocharger System Emergencies

    Section 3 Cirrus Design Emergency Procedures SR22T Turbocharger System Emergencies Unexpected Loss Of Manifold Pressure 1. Power ....ADJUST to minimum required for sustained flight 2. Mixture ....ADJUST for EGTs between 1300° to 1400ºF 3. Descend to MINIMUM SAFE ALTITUDE from which a landing may be safely accomplished.
  • Page 81: Original Issue

    Cirrus Design Section 3 SR22T Emergency Procedures 2. A significant leak in the exhaust system. a. An exhaust leak may present a possible fire hazard. Reducing power and adjusting the mixture as described reduces the possibility of an engine compartment fire.
  • Page 82: Manifold Pressure High

    Section 3 Cirrus Design Emergency Procedures SR22T Manifold Pressure High MAN PRESSURE Warning MAN PRESSURE 1. Power Lever ....... REDUCE MAP to less than 36.5 in.Hg 2. Flight ................CONTINUE If noticeable surging is present: 3. Perform Overboost / Pressure Relief Valve Checklist.
  • Page 83: Overboost / Pressure Relief Valve

    Cirrus Design Section 3 SR22T Emergency Procedures Overboost / Pressure Relief Valve 1. Power Lever ........REDUCE to 30.5 in.Hg or less 2. Mixture ........ADJUST fuel flow to top of green arc If continued surging is present: 3. Land as soon as practical.
  • Page 84: Egt, Tit Or Cht Temperature Sensor Failure

    Section 3 Cirrus Design Emergency Procedures SR22T EGT, TIT or CHT Temperature Sensor Failure 1. Similar gages ..............MONITOR 2. Flight ................CONTINUE using remaining gages as representative. Amplification Isolated red X presentation of an EGT, TIT or CHT indicates that sensor has failed.
  • Page 85: Propeller System Emergencies

    Cirrus Design Section 3 SR22T Emergency Procedures Propeller System Emergencies Engine Speed High RPM Warning: Engine Speed High 1. Power Lever ...... REDUCE by 2 in.Hg Manifold Pressure If governor is not in control (RPM reduces and remains lower after power adjustment): 2.
  • Page 86: Propeller Governor Failure

    Section 3 Cirrus Design Emergency Procedures SR22T Propeller Governor Failure 1. Power Lever ..Reduce to minimum necessary for sustained flight 2. Airspeed ............Reduce to 85-90 KIAS 3. Oil Pressure ..............MONITOR 4. Land as soon as possible. Amplification An in-flight governor failure will likely result in a large exceedance (3000 RPM or more), as propeller blade angle will be go to fine pitch.
  • Page 87: Fuel System Emergencies

    Cirrus Design Section 3 SR22T Emergency Procedures Fuel System Emergencies Low Fuel Quantity FUEL QTY Warning FUEL QTY 1. Fuel Quantity Gages ............CHECK If fuel quantity indicates less than or equal to 9 gallons: a. Land as soon as practical.
  • Page 88: Electrical System Emergencies

    Section 3 Cirrus Design Emergency Procedures SR22T 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.
  • Page 89: High Voltage On Main Bus 2

    Cirrus Design Section 3 SR22T Emergency Procedures 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 90: High Or Low Voltage On Essential Bus

    Section 3 Cirrus Design Emergency Procedures SR22T 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 91: Environmental System Emergencies

    Cirrus Design Section 3 SR22T Emergency Procedures Environmental System Emergencies Carbon Monoxide Level High CO LVL HIGH Warning CO LVL HIGH 1. Air Conditioner (if installed)...... NOT IN RECIRC MODE 2. Temperature Selector............COLD 3. Vent Selector......FEET/PANEL/DEFROST POSITION 4. Airflow Selector .......SET AIRFLOW TO MAXIMUM 5.
  • Page 92: Oxygen System Emergencies

    Section 3 Cirrus Design Emergency Procedures SR22T 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 93: Oxygen Quantity Low

    Cirrus Design Section 3 SR22T Emergency Procedures 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.
  • Page 94: Integrated Avionics System Emergencies

    Section 3 Cirrus Design Emergency Procedures SR22T 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 95: 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 96: 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. 3-40...
  • Page 97: Other Emergencies

    Cirrus Design Section 3 SR22T Emergency Procedures 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 98: Left/Right Brake Over-Temperature

    Section 3 Cirrus Design Emergency Procedures SR22T Left/Right Brake Over-Temperature 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...
  • Page 99: Emergency Ground Egress

    Cirrus Design Section 3 SR22T Emergency Procedures Amplification • WARNING • Use extreme 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 100: Caps Deployment

    Section 3 Cirrus Design Emergency Procedures SR22T CAPS Deployment • WARNING • The maximum demonstrated deployment speed is 140 KIAS. 1. Activation Handle Cover..........REMOVE 2. Activation Handle (Both Hands) ..... PULL STRAIGHT DOWN After Deployment as time permits: 3. Mixture ................CUTOFF 4.
  • Page 101 Section 3 SR22T Emergency Procedures 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 102 Section 3 Cirrus Design Emergency Procedures SR22T Intentionally Left Blank 3-46 P/N 13772-005 Original Issue...
  • Page 103 Cirrus Design Section 3A SR22T Abnormal Procedures Section 3A: Abnormal Procedures Table of Contents Introduction ..................3 Abnormal Procedures Guidance ............4 Circuit Breakers ................4 Flight Environment ................5 Inadvertent Icing Encounter ............5 Inadvertent IMC Encounter............. 5 Door Open In Flight ................ 5 Abnormal Landings ................
  • Page 104 Section 3A Cirrus Design Abnormal Procedures SR22T Electric Trim/Autopilot Failure ............19 Flap System Exceedance ............. 19 Landing Gear System ..............20 Brake Failure During Taxi ............. 20 Left/Right Brake Over-Temperature..........20 Oxygen System ................21 Oxygen Quantity Low..............21 Other Conditions ................
  • Page 105: Introduction

    Cirrus Design Section 3A SR22T 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 106: Abnormal Procedures Guidance

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 107: Flight Environment

    Cirrus Design Section 3A SR22T Abnormal Procedures Flight Environment Inadvertent Icing Encounter 1. Pitot Heat ...................ON 2. Exit icing conditions. Turn back or change altitude. 3. Cabin Heat ..............MAXIMUM 4. Windshield Defrost............FULL OPEN Amplification Flight into known icing conditions is prohibited.
  • Page 108: Abnormal Landings

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 109: Engine System

    Cirrus Design Section 3A SR22T Abnormal Procedures Engine System Low Idle Oil Pressure OIL PRESS Caution OIL PRESS 1. If In-Flight ........LAND AS SOON AS PRACTICAL Amplification Oil pressure between 10 psi and 30 psi at or above 1000 RPM This message will appear prior to engine start and should clear after engine start.
  • Page 110: Starter Engaged

    Section 3A Cirrus Design Abnormal Procedures SR22T Starter Engaged STARTER ENGAGED Caution START ENGAGE On-Ground 1. Ignition Switch ......DISENGAGE prior to 20 Seconds 2. Battery Switches ...Wait 20 seconds before next start attempt If starter does not disengage (relay or solenoid failure): 3.
  • Page 111: Alternate Air Door Open Annunciation

    Cirrus Design Section 3A SR22T Abnormal Procedures Alternate Air Door Open Annunciation ALT AIR OPEN Caution ALT AIR OPEN 1. Manifold Pressure .............. CHECK If environment suspect as cause (icing or visible debris): 2. Flight Conditions .............CHANGE/EXIT 3. Power ........Reduce to 30.5 in.Hg when practical 4.
  • Page 112: Fuel System

    Section 3A Cirrus Design Abnormal Procedures SR22T Fuel System Low Fuel Quantity FUEL QTY Caution FUEL QTY 1. Fuel Quantity Gages ............CHECK If left & right fuel quantities indicate less than or equal to 14 gallons per side: a. Land as soon as practical.
  • Page 113: Fuel Imbalance

    Cirrus Design Section 3A SR22T Abnormal Procedures Fuel Imbalance FUEL IMBALANCE Caution 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 114 Section 3A Cirrus Design Abnormal Procedures SR22T 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 115: Low Alternator 1 Output

    Cirrus Design Section 3A SR22T Abnormal Procedures Low Alternator 1 Output ALT 1 Caution (Failure) ALT 1 1. ALT 1 Circuit Breaker ..........CHECK & SET 2. ALT 1 Master Switch ............CYCLE If alternator does not reset (low A1 Current and M1 voltage): 3.
  • Page 116: Low Alternator 2 Output

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 117: Integrated Avionics System

    Cirrus Design Section 3A SR22T Abnormal Procedures Integrated Avionics System Avionics Switch Off AVIONICS OFF Caution AVIONICS OFF 1. AVIONICS Switch ........... ON, AS REQUIRED Amplification The AVIONICS master switch is off. PFD Cooling Fan Failure PFD FAN FAIL Advisory PFD FAN FAIL 1.
  • Page 118: Flight Displays Too Dim

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 119: Pitot Static System

    Cirrus Design Section 3A SR22T Abnormal Procedures Pitot Static System Pitot Static Malfunction Static Source Blocked 1. Pitot Heat ...................ON 2. Alternate Static Source ............OPEN Amplification If erroneous readings of the static source instruments (airspeed, altimeter and vertical speed) are suspected, the alternate static source valve, on side of console near pilot’s right ankle, should be opened to...
  • Page 120: Pitot Heat Current Sensor Annunciation

    Section 3A Cirrus Design Abnormal Procedures SR22T Pitot Heat Current Sensor Annunciation PITOT HEAT FAIL Caution PITOT HEAT FAIL 1. Pitot Heat Circuit Breaker............ CYCLE 2. Pitot Heat ............. CYCLE OFF, ON If inadvertent icing encountered, perform Inadvertent Icing Encounter Checklist and: a.
  • Page 121: Flight Control System

    Cirrus Design Section 3A SR22T Abnormal Procedures Flight Control System Electric Trim/Autopilot Failure 1. Airplane Control ..........MAINTAIN MANUALLY 2. Autopilot (if engaged)..........DISENGAGE If Problem Is Not Corrected: 3. Circuit Breakers ........... PULL AS REQUIRED • PITCH TRIM • ROLL TRIM •...
  • Page 122: Landing Gear System

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 123: Oxygen Quantity Low

    Cirrus Design Section 3A SR22T Abnormal Procedures Oxygen System Oxygen Quantity Low OXYGEN QTY Caution OXYGEN QTY 1. Oxygen Pressure and Flow Rate ........CHECK 2. Oxygen Duration ............CALCULATE a. See Oxygen AFMS; calculate duration based on remaining pressure, number of occupants and type of device (mask or cannula).
  • Page 124 Section 3A Cirrus Design Abnormal Procedures SR22T 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 Oxygen System AFMS.
  • Page 125: Other Conditions

    Cirrus Design Section 3A SR22T Abnormal Procedures Other Conditions Aborted Takeoff 1. Power Lever ................IDLE 2. Brakes..............AS REQUIRED Amplification Use as much of the remaining runway as needed to safely bring the airplane to a stop or to slow the airplane sufficiently to turn off runway.
  • Page 126: Parking Brake Engaged Annunciation

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 127 Cirrus Design Section 4 SR22T 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 128 Section 4 Cirrus Design Normal Procedures SR22T Intentionally Left Blank P/N 13772-005 Original Issue...
  • Page 129: Airspeeds For Normal Operation

    Cirrus Design Section 4 SR22T 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 130: Normal Procedures

    Section 4 Cirrus Design Normal Procedures SR22T Normal Procedures Preflight Inspection Before carrying out preflight inspections, ensure that all required maintenance has been accomplished. Review your flight plan and compute weight and balance. Throughout the walk-around: check all hinges, hinge pins, and bolts for security; check skin for damage, condition, and evidence of delamination;...
  • Page 131 Cirrus Design Section 4 SR22T 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 Oxygen Masks/Cannulas and Hoses .....Check Condition...
  • Page 132 Section 4 Cirrus Design Normal Procedures SR22T Baggage Door ........... Closed and Secure g. Static Button ..........Check for Blockage h. Parachute Cover ........Sealed and Secure 3. Empennage a. Tiedown Rope .............Remove b. Horizontal and Vertical Stabilizers ......Condition • Note •...
  • Page 133 Cirrus Design Section 4 SR22T Normal Procedures d. Wheel Fairings...... Security, Accumulation of Debris e. Tire ..........Condition, Inflation, and Wear • Caution • Clean and inspect temperature indicator installed to piston housing. If indicator center is black, the brake assembly has been overheated.
  • Page 134 Section 4 Cirrus Design Normal Procedures SR22T c. Cowling ............ Attachments Secure d. External Power .............Door Secure e. Vortex Generator ............Condition Exhaust Pipe(s) ....Condition, Security, and Clearance 11. Left Main Gear and Forward Wing a. Wheel fairings ....... Security, Accumulation of Debris b.
  • Page 135: Before Starting Engine

    Cirrus Design Section 4 SR22T 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 136: Starting Engine

    Section 4 Cirrus Design Normal Procedures SR22T Starting Engine 1. External Power (If applicable) ........CONNECT 2. Brakes ................... HOLD 3. Bat Master Switches ........... ON (Check Volts) 4. Strobe Lights ................ON 5. Mixture ................. FULL RICH 6. Power Lever ............FULL FORWARD 7.
  • Page 137 Cirrus Design Section 4 SR22T Normal Procedures Amplification • WARNING • If airplane will be started using external power, keep all personnel and power unit cables well clear of the propeller rotation plane. • Caution • Alternators should be left OFF during engine starting to avoid high electrical loads.
  • Page 138: Taxiing

    Section 4 Cirrus Design Normal Procedures SR22T Before Taxiing 1. Flaps ................. UP (0%) 2. Radios/Avionics............AS REQUIRED 3. Cabin Heat/Defrost ..........AS REQUIRED 4. Fuel Selector ............SWITCH TANK Taxiing 1. Parking Brake.............DISENGAGE 2. Brakes ................CHECK 3. HSI Orientation ..............CHECK 4.
  • Page 139 Cirrus Design Section 4 SR22T Normal Procedures Before Takeoff 1. Doors ................LATCHED 2. CAPS Handle...........Verify Pin Removed 3. Seat Belts and Shoulder Harness........SECURE 4. Air Conditioner ............AS DESIRED • Caution • Use of RECIRC mode prohibited in flight.
  • Page 140 Section 4 Cirrus Design Normal Procedures SR22T 19. Navigation Lights............ AS REQUIRED 20. Landing Light ............AS REQUIRED 21. Magnetos ............ CHECK Left and Right RPM drop must not exceed 150 RPM for either magneto. RPM differential must not exceed 75 RPM between magnetos a.
  • Page 141: Maximum Power Fuel Flow

    Cirrus Design Section 4 SR22T Normal Procedures indicate faulty grounding of one side of the ignition system or magneto timing set in advance of the specified setting. Maximum Power Fuel Flow For maximum power operations (Power Lever full forward - 2500 RPM, 36.0 in.Hg manifold pressure) fuel flow should be in the green arc.
  • Page 142: Normal Takeoff

    Section 4 Cirrus Design Normal Procedures SR22T Normal Takeoff 1. Brakes ........RELEASE (Steer with Rudder Only) 2. Power Lever ............FULL FORWARD 3. Engine Parameters ............CHECK 4. Elevator Control ......ROTATE Smoothly at 80-83 KIAS 5. At 90 KIAS, Flaps............... UP Short Field Takeoff 1.
  • Page 143 Cirrus Design Section 4 SR22T Normal Procedures Amplification The fuel pump should be in the BOOST position during takeoff and for climb as required for vapor suppression with hot or warm fuel. Takeoff Power Check Check full-throttle engine operation early in takeoff run. The engine should run smoothly and turn approximately 2500 RPM.
  • Page 144: Full Power Climb: Rich Of Peak Technique

    Section 4 Cirrus Design Normal Procedures SR22T Full Power Climb: Rich of Peak Technique 1. Oxygen..............AS REQUIRED 2. Power Lever ............FULL FORWARD 3. Mixture ........Maintain Fuel Flow in GREEN ARC 4. Flaps ................Verify UP 5. Airspeed ................120 KIAS 6.
  • Page 145 Cirrus Design Section 4 SR22T Normal Procedures HIGH BOOST /PRIME position and reset the mixture as required to maintain adequate stable fuel flow. Vapor lock is most often indicated by any or a combination of the following: • Fluctuations in normal fuel flow possibly coupled with abnormal engine operation;...
  • Page 146 Section 4 Cirrus Design Normal Procedures SR22T Cruise Climb: Lean of Peak Technique 1. Power Lever ..........REDUCE to 30.5 in.Hg 2. Mixture ..........LEAN to cyan target or less 3. Minimum Airspeed ............120 KIAS 4. Fuel Pump................BOOST 5. Oxygen..............AS REQUIRED a.
  • Page 147: Cruise

    Cirrus Design Section 4 SR22T Normal Procedures Cruise 1. Oxygen ..............AS REQUIRED 2. Cruise Altitude ............ESTABLISHED 3. Power Lever ........REDUCE to 30.5 in.Hg or less 4. Fuel Pump ............. AS REQUIRED 5. Mixture ................ADJUST 6. Engine Parameters ............MONITOR 7.
  • Page 148: Descent

    Section 4 Cirrus Design Normal Procedures SR22T Descent 1. Oxygen..............AS REQUIRED 2. Altimeter ................... SET 3. Cabin Heat/Defrost ..........AS REQUIRED 4. Landing Light ................ON 5. Fuel System ............... CHECK 6. Power Lever ............AS REQUIRED For Rapid Descent: a.
  • Page 149: Normal Landing

    Cirrus Design Section 4 SR22T Normal Procedures 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 150: Short Field Landing

    Section 4 Cirrus Design Normal Procedures SR22T 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 151: After Landing

    Cirrus Design Section 4 SR22T Normal Procedures 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 152: Shutdown

    Section 4 Cirrus Design Normal Procedures SR22T Shutdown 1. Fuel Pump (if used)..............OFF 2. Throttle ..................IDLE 3. Ignition Switch ..............CYCLE 4. Mixture ................CUTOFF 5. All Switches................OFF 6. Magnetos .................OFF 7. ELT ............TRANSMIT LIGHT OUT 8. Chocks, Tie-downs, Pitot Covers ......AS REQUIRED Amplification •...
  • Page 153: Stalls

    Cirrus Design Section 4 SR22T Normal Procedures 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 154: Environmental Considerations

    Section 4 Cirrus Design Normal Procedures SR22T 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 155 Cirrus Design Section 4 SR22T Normal Procedures 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 156: Hot Weather Operation

    Section 4 Cirrus Design Normal Procedures SR22T 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 157: Noise Characteristics/Abatement

    Cirrus Design Section 4 SR22T 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 81.5 dB(A) 88.0 dB(A) PHC-J3Y1F-1N/N7605 Hartzell 3-blade Propeller 81.5 dB(A)
  • Page 158 Section 4 Cirrus Design Normal Procedures SR22T Intentionally Left Blank 4-32 P/N 13772-005 Original Issue...
  • Page 159 Cirrus Design Section 5 SR22T Performance Data Section 5: Performance Data Table of Contents Introduction ..................3 Associated Conditions Affecting Performance........ 3 Demonstrated Operating Temperature ........... 3 Airspeed Calibration: Normal Static Source........4 Airspeed Calibration: Alternate Static Source ........5 Altitude Correction Normal Static Source: Primary Flight Display ........
  • Page 160 Section 5 Cirrus Design Performance Data SR22T Intentionally Left Blank P/N 13772-005 Original Issue...
  • Page 161: Introduction

    Cirrus Design Section 5 SR22T 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 162: Airspeed Calibration: Normal Static Source

    Section 5 Cirrus Design Performance Data SR22T 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 100%...
  • Page 163: Airspeed Calibration: Alternate Static Source

    Cirrus Design Section 5 SR22T 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 164: Altitude Correction Normal Static Source: Primary Flight Display

    Section 5 Cirrus Design Performance Data SR22T 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 165: Altitude Correction Normal Static Source: Standby Altimeter

    Cirrus Design Section 5 SR22T 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 166: Altitude Correction Alternate Static Source: Primary Flight Display

    Section 5 Cirrus Design Performance Data SR22T 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 167: Altitude Correction Alternate Static Source: Standby Altimeter

    Cirrus Design Section 5 SR22T 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 168: Temperature Conversion

    Section 5 Cirrus Design Performance Data SR22T 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 169: Outside Air Temperature For Isa Condition

    Cirrus Design Section 5 SR22T 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 170: Stall Speeds

    Section 5 Cirrus Design Performance Data SR22T 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 171: Wind Components

    Cirrus Design Section 5 SR22T 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 172: Takeoff Distance

    Section 5 Cirrus Design Performance Data SR22T 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 173 Cirrus Design Section 5 SR22T Performance Data Takeoff Distance: 3600 LB Weight: 3600 LB Headwind: Subtract 10% for each 12 knots headwind. Approx. Speed at Liftoff: 80 KIAS Tailwind: Add 10% for each 2 knots tailwind up Speed over 50 Ft. Obstacle: 85 KIAS to 10 knots.
  • Page 174 Section 5 Cirrus Design Performance Data SR22T Takeoff Distance: 2900 LB Weight: 2900 LB Headwind: Subtract 10% for each 12 knots headwind. Approx. Speed at Liftoff: 67 KIAS Tailwind: Add 10% for each 2 knots tailwind up Speed over 50 Ft. Obstacle: 72 KIAS to 10 knots.
  • Page 175: Takeoff Climb Gradient

    Cirrus Design Section 5 SR22T Performance Data Takeoff Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .......................Full Rich • Flaps .........................50% • Airspeed ..................Best Rate of Climb • Note • Climb Gradient values shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
  • Page 176: Takeoff Rate Of Climb

    Section 5 Cirrus Design Performance Data SR22T 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 in ft per unit time...
  • Page 177: Enroute Climb Gradient

    Cirrus Design Section 5 SR22T Performance Data Enroute Climb Gradient Conditions: • Power ....................Full Throttle • Mixture ............Maintain Fuel Flow in GREEN ARC • Flaps ......................0% (UP) • Airspeed ....................120 KIAS • Note • Climb Gradient values shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
  • Page 178: Enroute Rate Of Climb

    Section 5 Cirrus Design Performance Data SR22T Enroute Rate of Climb Conditions: • Power....................Full Throttle • Mixture............. Maintain Fuel Flow in GREEN ARC • Flaps......................0% (UP) • Airspeed ....................120 KIAS • Note • Rate-of-Climb values shown are change in altitude in ft per unit time expressed in Feet per Minute.
  • Page 179: Time, Fuel & Distance To Climb: Full Power Climb

    Cirrus Design Section 5 SR22T Performance Data Time, Fuel & Distance to Climb: Full Power Climb Conditions: • Power ....................Full Throttle • Mixture ............Maintain Fuel Flow in GREEN ARC • Weight ......................3600 LB • Winds ....................... Zero • Climb Airspeed..................120 KIAS •...
  • Page 180: Time, Fuel & Distance To Climb: Cruise Climb

    Section 5 Cirrus Design Performance Data SR22T Time, Fuel & Distance to Climb: Cruise Climb Conditions: • Power...................... 30.5” MAP • Mixture................Target Fuel flow or less • Weight ......................3600 LB • Winds........................ Zero • Climb Airspeed ..................120 KIAS •...
  • Page 181: Cruise Performance

    Cirrus Design Section 5 SR22T Performance Data Cruise Performance Conditions: • Weight ......................3400 LB • Winds ....................... Zero • Note • Subtract 10 KTAS if nose wheel pant and fairing removed. Lower KTAS by 10% if nose and main wheel pants & fairings are removed.
  • Page 182 Section 5 Cirrus Design Performance Data SR22T CRUISE PERFORMANCE ISA -30°C ISA +30°C Altitude Power Econ Econ Econ (ft MSL) (% of 315) (GPH) (KTAS) (nm/gal) (KTAS) (nm/gal) (KTAS) (nm/gal) 14000 18.3 10.0 10.4 10.8 16.4 10.6 11.0 11.4 14.6 11.3...
  • Page 183: Range / Endurance: Full Power Climb

    Cirrus Design Section 5 SR22T Performance Data Range / Endurance: Full Power Climb Conditions: • Mixture ............ Best Economy - Target Fuel Flow or less • Weight ..........3600 LB for Climb, Avg 3400 LB for Cruise • Winds ....................... Zero •...
  • Page 184 Section 5 Cirrus Design Performance Data SR22T Range / Endurance: 75% Power Cruise - Full Power Climb Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 2000 78.5 16.4 4000 77.5 16.4 10.1...
  • Page 185 Cirrus Design Section 5 SR22T Performance Data Range / Endurance: 55% Power Cruise - Full Power Climb Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 2000 78.5 12.7 11.2 4000 77.5 12.7...
  • Page 186: Range / Endurance: Cruise Climb

    Section 5 Cirrus Design Performance Data SR22T Range / Endurance: Cruise Climb Conditions: • Mixture.............Best Economy - Target Fuel Flow or less • Weight ..........3600 LB for Climb, Avg 3400 LB for Cruise • Winds........................ Zero • Total Fuel ....................92 Gallons •...
  • Page 187 Cirrus Design Section 5 SR22T Performance Data Range / Endurance: 75% Power Cruise - Cruise Climb Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 2000 78.9 16.4 4000 78.2 16.4 10.1 6000 77.5...
  • Page 188 Section 5 Cirrus Design Performance Data SR22T Range / Endurance: 55% Power Cruise - Cruise Climb Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 2000 78.9 12.7 11.2 4000 78.2 12.7 11.4...
  • Page 189: Balked Landing Climb Gradient

    Cirrus Design Section 5 SR22T Performance Data Balked Landing Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .......................Full Rich • Flaps ...................... 100% (DN) • Climb Airspeed....................V • Note • Climb Gradient values shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
  • Page 190: Balked Landing Rate Of Climb

    Section 5 Cirrus Design Performance Data SR22T Balked Landing Rate of Climb Conditions: • Power....................Full Throttle • Mixture....................... Full Rich • Flaps...................... 100% (DN) • Climb Airspeed ....................V • Note • Rate-of-Climb values shown are change in altitude in ft per unit time...
  • Page 191: Landing Distance

    Cirrus Design Section 5 SR22T Performance Data Landing Distance Conditions: • Winds ....................... Zero • Runway ..................Dry, Level, Paved • Flaps.......................100% • 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 192 Section 5 Cirrus Design Performance Data SR22T Landing Distance 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 193 Cirrus Design Section 6 SR22T Weight and Balance Data Section 6: Weight and Balance Data Table of Contents Introduction ..................3 Airplane Weighing Form ..............4 Airplane Weighing Procedures ............5 Loading Instructions ................8 Weight and Balance Loading Form............ 9 Loading Data..................
  • Page 194 Section 6 Cirrus Design Weight and Balance Data SR22T Intentionally Left Blank P/N 13772-005 Original Issue...
  • Page 195: Introduction

    Cirrus Design Section 6 SR22T Weight and Balance Data Introduction This section describes the procedure for establishing the basic empty weight and moment of the airplane. Sample forms are provided for reference. Procedures for calculating the weight and moment for various operations are also provided.
  • Page 196: Airplane Weighing Form

    Section 6 Cirrus Design Weight and Balance Data SR22T Airplane Weighing Form REF DATUM FS 0.0 FS 100.0 FS 142.5 WL 100.0 A = x + 100 B = A - y y = ____________ Measured x = ____________ Measured...
  • Page 197: Airplane Weighing Procedures

    Cirrus Design Section 6 SR22T Weight and Balance Data Airplane Weighing Procedures A basic empty weight and center of gravity were established for this airplane when the airplane was weighed just prior to initial delivery. However, major modifications, loss of records, addition or relocation of...
  • Page 198 Section 6 Cirrus Design Weight and Balance Data SR22T main wheel centers to a plumb bob dropped from the forward side of the firewall (FS 100). Add 100 to this measurement to obtain left and right weighing point arm (dimension ‘‘A’’).
  • Page 199 Cirrus Design Section 6 SR22T Weight and Balance Data Airplane Leveling Spirit Level LONGITUDINAL LEVELING Spirit Level Straight Edge Straight Edge Straight Edge Spacer Spacer Block Block Door Sill Door Sill LATERAL LEVELING SR22_FM06_1440A Figure 6-2 P/N 13772-005 P/N 13772-005...
  • Page 200: Loading Instructions

    Section 6 Cirrus Design Weight and Balance Data SR22T 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 201: Weight And Balance Loading Form

    Cirrus Design Section 6 SR22T 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 202: Loading Data

    Section 6 Cirrus Design Weight and Balance Data SR22T 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 Loading Chart Fwd Pass Baggage 20.0 40.0...
  • Page 203 Cirrus Design Section 6 SR22T 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 6-3) are within limits. 3600 Airplane 3400...
  • Page 204: Weight & Balance Record

    Section 6 Cirrus Design Weight and Balance Data SR22T 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 205: Equipment List

    Cirrus Design Section 6 SR22T Weight and Balance Data Equipment List This list will be determined after the final equipment has been installed in the aircraft. P/N 13772-005 P/N 13772-005 6-13 6-13 Original Issue...
  • Page 206 Section 6 Cirrus Design Weight and Balance Data SR22T Intentionally Left Blank 6-14 P/N 13772-005 Original Issue...
  • Page 207 Cirrus Design Section 7 SR22T 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 208 Section 7 Cirrus Design Systems Description SR22T Engine Controls ................31 Engine Indicating ................33 Engine Lubrication System ............36 Ignition and Starter System............36 Air Induction System ..............37 Engine Exhaust System..............37 Engine Fuel Injection ..............37 Engine Cooling................38 Propeller ...................
  • Page 209 Cirrus Design Section 7 SR22T Systems Description Emergency Egress Hammer............90 Convenience Outlet ..............90 Cirrus Airplane Parachute System ........... 91 System Description ............... 91 Activation Handle ................92 Deployment Characteristics ............93 P/N 13772-005 P/N 13772-005 Original Issue...
  • Page 210 Section 7 Cirrus Design Systems Description SR22T Intentionally Left Blank P/N 13772-005 Original Issue...
  • Page 211: Introduction

    Cirrus Design Section 7 SR22T 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 212: Airframe

    Section 7 Cirrus Design Systems Description SR22T 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 213: Empennage

    Cirrus Design Section 7 SR22T 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 214: Flight Controls

    Section 7 Cirrus Design Systems Description SR22T 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 215 Cirrus Design Section 7 SR22T Systems Description SR22_FM07_1461 Figure 7-1 Elevator System P/N 13772-005 P/N 13772-005 Original Issue...
  • Page 216: Aileron System

    Section 7 Cirrus Design Systems Description SR22T 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 217 Cirrus Design Section 7 SR22T Systems Description SR22_FM07_1462 Figure 7-2 Aileron System P/N 13772-005 P/N 13772-005 7-11 7-11 Original Issue...
  • Page 218: Rudder System

    Section 7 Cirrus Design Systems Description SR22T 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 219 Cirrus Design Section 7 SR22T Systems Description SR22_FM07_1463 Figure 7-3 Rudder System P/N 13772-005 P/N 13772-005 7-13 7-13 Original Issue...
  • Page 220: Instrument Panel

    Section 7 Cirrus Design Systems Description SR22T 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 221 Cirrus Design Section 7 SR22T Systems Description Legend 1. Cirrus Airframe Parachute System 12. Engine & Fuel System Controls (CAPS) Activation T-Handle Cover 13. Left Side Console 2. Magnetic Compass · Circuit Breaker Panel 3. Multifunction Display · ELT Remote Switch 4.
  • Page 222: Flight Instruments

    Section 7 Cirrus Design Systems Description SR22T 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 on separate power sources than the PFD.
  • Page 223 Cirrus Design Section 7 SR22T Systems Description 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 224: Attitude Indicator

    Section 7 Cirrus Design Systems Description SR22T 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 225: Airspeed Indicator

    Cirrus Design Section 7 SR22T Systems Description Airspeed Indicator Primary airspeed data is provided by the Air Data Computer and is shown as a vertical tape along the upper left side of the PFD. The airspeed scale is graduated with major tick marks at intervals of 10 knots and minor tick marks at intervals of 5 knots.
  • Page 226: Altimeter

    Section 7 Cirrus Design Systems Description SR22T Altimeter Primary altitude data is provided by the Air Data Computer and is shown as a vertical tape along the upper right side of the PFD. The altimeter scale is graduated with major tick marks at intervals of 100 feet and minor tick marks at intervals of 20 feet.
  • Page 227: Horizontal Situation Indicator

    Cirrus Design Section 7 SR22T 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 228: Magnetic Compass

    Section 7 Cirrus Design Systems Description SR22T 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 229 Cirrus Design Section 7 SR22T Systems Description SR22_FM07_2935A Figure 7-6 Wing Flaps P/N 13772-005 P/N 13772-005 7-23 7-23 Original Issue...
  • Page 230: Landing Gear

    Section 7 Cirrus Design Systems Description SR22T Landing Gear Main Gear The main landing gear are bolted to composite wing structure between the wing spar and shear web. The landing gear struts are constructed of composite material for fatigue resistance. The composite construction is both rugged and maintenance free.
  • Page 231 Cirrus Design Section 7 SR22T Systems Description weak braking action. A temperature sensitive resistor is mounted to each brake assembly which transmit signals via the Engine Airframe Unit to the Engine Indicating System for brake temperature caution/ warning annunciation. Should any of these symptoms occur, immediate maintenance is required.
  • Page 232: Baggage Compartment

    Section 7 Cirrus Design Systems Description SR22T Baggage Compartment The baggage compartment, 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. The door is locked from the outside with a key lock.
  • Page 233: Seats

    Cirrus Design Section 7 SR22T Systems Description 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 234: Seat Belt And Shoulder Harness

    Section 7 Cirrus Design Systems Description SR22T 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 235 Cirrus Design Section 7 SR22T Systems Description Front Seat Inflatable Restraints An inflatable shoulder harness is integral to each front seat harness. The electronic module assembly, mounted below the cabin floor, contains a crash sensor, battery, and related circuitry to monitor the deceleration rate of the airplane.
  • Page 236: Cabin Doors

    Section 7 Cirrus Design Systems Description SR22T installed using the center seat belt. Three top tether anchors for the child seats are located on the rear bulkhead. To install a child seat: 1. Fasten lower seat attachments to bench seat: a.
  • Page 237: Engine

    Cirrus Design Section 7 SR22T Systems Description Engine The airplane is powered by a Teledyne Continental TSIO-550-K, twin turbocharged, direct drive, fuel injected, air cooled, horizontally opposed 6 cylinder engine that uses a high pressure, wet sump style oil system for lubrication. The engine has a 550 cubic inch displacement and is rated to 315 bhp at 2500 RPM with a 2000-hour Time Between Overhaul (TBO) schedule.
  • Page 238 Section 7 Cirrus Design Systems Description SR22T 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. Turbine Inlet Temperature 8.
  • Page 239: Engine Indicating

    Cirrus Design Section 7 SR22T Systems Description Engine Indicating Engine information is displayed as analog-style gages, bar graphs, and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), all essential engine information is displayed along the LH edge of the display.
  • Page 240 Section 7 Cirrus Design Systems Description SR22T 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 241 Cirrus Design Section 7 SR22T Systems Description Oil Temperature Oil temperature is shown in the upper right corner of the ENGINE page, opposite the oil pressure scale, as both a simulated temperature gage and as a digital value. The gage pointer sweeps a scale range from 75°F to 250°F in 50°F increments.
  • Page 242: Engine Lubrication System

    Section 7 Cirrus Design Systems Description SR22T Engine Lubrication System The engine is provided with a wet-sump, high-pressure oil system for engine lubrication and cooling. Oil for engine lubrication is drawn from an eight-quart capacity sump through an oil suction strainer screen and directed through the oil filter to the engine-mounted oil cooler by a positive displacement oil pump.
  • Page 243: Air Induction System

    Cirrus Design Section 7 SR22T Systems Description Air Induction System Induction air enters the engine compartment through two NACA ducts located in the lower engine cowls. The air continues to the air boxes where it is filtered and ducted into the compressor housing where the...
  • Page 244: Engine Cooling

    Section 7 Cirrus Design Systems Description SR22T the pilot controlled Power Lever position. From the metering valve, fuel is directed to the fuel manifold valve (spider) and then to the individual injector nozzles. The system meters fuel flow in proportion to engine RPM, mixture setting, and throttle angle.
  • Page 245: Propeller

    Cirrus Design Section 7 SR22T Systems Description Propeller The airplane is equipped with a composite, three-blade, constant speed, governor-regulated propeller. The propeller governor automatically adjusts propeller pitch to regulate propeller and engine RPM by controlling the flow of engine oil - boosted to high pressure by the governing pump - to or from a piston in the propeller hub.
  • Page 246: Fuel System

    Section 7 Cirrus Design Systems Description SR22T 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 247: Fuel Selector Valve

    Cirrus Design Section 7 SR22T Systems Description 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 248 Section 7 Cirrus Design Systems Description SR22T ANNUNCIATOR FUEL FUEL QUANTITY VENT VENT FILLER FILLER INDICATOR L. WING TANK R. WING TANK R. WING L. WING COLLECTOR COLLECTOR SELECTOR VALVE FLAPPER FLAPPER VALVE VALVE DRAIN (5 PLACES) FIREWALL SELECTOR VALVE...
  • Page 249: Fuel Indicating

    Cirrus Design Section 7 SR22T Systems Description Fuel Indicating Fuel quantity is measured by float-type quantity sensors installed in each fuel tank and displayed on the Fuel Quantity Gage. • Caution • When the fuel tanks are 1/4 full or less, prolonged uncoordinated flight such as slips or skids can uncover the fuel tank outlets.
  • Page 250 Section 7 Cirrus Design Systems Description SR22T fuel flow signal is sent to the Engine Airframe Unit, processed, and transmitted to the Engine Indicating System for display. The gage displays a green normal arc, which is dynamically updated to display the range of normal values appropriate to engine power settings.
  • Page 251 Cirrus Design Section 7 SR22T Systems Description ENGINE page changes to the corresponding color of CAS alert and the annunciation system issues an audio alert. FUEL QTY: Fuel quantity. • A white Advisory message is generated when either fuel tank goes below 14 gallons.
  • Page 252 Section 7 Cirrus Design Systems Description SR22T Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) 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)
  • Page 253: Electrical System

    Cirrus Design Section 7 SR22T 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 254 Section 7 Cirrus Design Systems Description SR22T LANDING 100A ALT 1 LIGHT ALT 1 7.5A VOLT REG RELAY LANDING LIGHT SWITCH EXTERNAL ALT 1 POWER RELAY SWITCH EXTERNAL POWER 125A BAT 1 BAT 1 BAT 1 RELAY SWITCH STARTER STARTER...
  • Page 255: Power Distribution

    Cirrus Design Section 7 SR22T 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 256: Electrical System Protection

    Section 7 Cirrus Design Systems Description SR22T 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 257 Cirrus Design Section 7 SR22T Systems Description Main Distribution Bus 1 or Main Distribution Bus 2 in the MCU. In the case of both alternators failing, BAT 1 is connected directly to the Essential Distribution Bus in the MCU and will power ESS BUS 1 and ESS BUS 2.
  • Page 258 Section 7 Cirrus Design Systems Description SR22T AVIONICS A/C COND PROTECTION STDBY ALT1 ALT2 ATTD #2 ENGINE MFD #2 SERVO INSTR STALL CABIN LIGHTS CAMERA WARNING / OXYGEN 12V DC ROLL FUEL QTY OUTLET TRIM PITCH A/C COMPR MFD #1...
  • Page 259: Electrical System Control

    Cirrus Design Section 7 SR22T 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 260: Ground Service Receptacle

    Section 7 Cirrus Design Systems Description SR22T 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 261: Electrical Indicating

    Cirrus Design Section 7 SR22T Systems Description Electrical Indicating Electrical system information is displayed as bar graphs and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), Battery 1 ampere output and Essential Bus voltage output are displayed along the LH edge of the display.
  • Page 262 Section 7 Cirrus Design Systems Description SR22T Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Electrical System Indication 8 9 10 Electrical and Lighting Controls LEGEND 7. Avionics 1. Essential & Main Bus Voltage 8. Navigation 2. Alternator & Battery Current 9.
  • Page 263: Lighting Systems

    Cirrus Design Section 7 SR22T 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 264: Interior Lighting

    Section 7 Cirrus Design Systems Description SR22T Interior Lighting Interior lighting for the airplane consists of separately controlled incandescent 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 265 Cirrus Design Section 7 SR22T 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 266: Environmental System

    Section 7 Cirrus Design Systems Description SR22T 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 267: Heating

    Cirrus Design Section 7 SR22T Systems Description selection, the air in the mixing chamber is ducted directly into the distribution system or, if in optional air conditioning mode, is further cooled as it passes through the evaporator assembly located under the front passenger seat.
  • Page 268: Cooling

    Section 7 Cirrus Design Systems Description SR22T cycled to ensure supply temperature is maintained below duct temperature limits. Conditioned air can be directed to passengers and/or the windshield diffuser by manipulating the cabin vent selector mounted on the RH instrument panel. The conditioned air enters the cabin through adjustable air vents located in each kick plate and through non- adjustable, floor level vents located in the rear cabin trim side panels.
  • Page 269 Cirrus Design Section 7 SR22T Systems Description RAM AIR RAM AIR RAM AIR CROSSOVER TUBE HOT AIR VALVE MIXING CHAMBER AIR FLOW VALVE CONTROL PANEL SERVO MOTOR FRESH AIR VALVE CONTROLLER TEMPERATURE SENSOR FLOOR AIRFLOW WINDSHIELD DIFFUSER PANEL AIRFLOW DISTRIBUTION...
  • Page 270 Section 7 Cirrus Design Systems Description SR22T RAM AIR RAM AIR RAM AIR CROSSOVER TUBE MIXING CHAMBER FRESH AIR VALVE HOT AIR VALVE COMPRESSOR CONTROLLER TEMPERATURE SENSOR WINDSHIELD AIR FLOW VALVE DIFFUSER SERVO MOTOR FLOOR AIRFLOW CONTROL PANEL PANEL AIRFLOW...
  • Page 271: Airflow Selection

    Cirrus Design Section 7 SR22T Systems Description Airflow Selection The airflow selector on the system control panel regulates the volume of airflow allowed into the cabin distribution system. When the airflow selector is moved past the OFF position an electro-mechanical linkage actuates a valve in the mixing chamber on the forward firewall to the full open position.
  • Page 272: Temperature Selection

    Section 7 Cirrus Design Systems Description SR22T Temperature Selection The temperature selector is electrically linked to the hot and cold air valves. Rotating the selector simultaneously opens and closes the two valves, permitting hot and cold air to mix and enter the distribution system.
  • Page 273 Cirrus Design Section 7 SR22T Systems Description Rotating the selector controls the volume of airflow allowed into the cabin distribution system through use of an electro-mechanical linkage to a butterfly (hot air) valve in the mixing chamber on the forward firewall.
  • Page 274 Section 7 Cirrus Design Systems Description SR22T 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 275: Pitot Heat Switch

    Cirrus Design Section 7 SR22T Systems Description Pitot-Static System The Pitot-Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage. The Pitot heat is pilot controlled through a panel-mounted switch. An internally mounted alternate static pressure source provides backup static pressure should that the primary static source becomes blocked.
  • Page 276 Section 7 Cirrus Design Systems Description SR22T AIR DATA COMPUTER PFD Air Data AIRSPEED INDICATOR ALTIMETER ALTERNATE PITOT-STATIC STATIC WATER TRAPS AIR SOURCE PITOT MAST STATIC HEATER BUTTONS Annunciation PITOT HEAT CURRENT SENSOR LOGIC PITOT 7.5A HEAT PITOT HEAT SW...
  • Page 277: Avionics

    Cirrus Design Section 7 SR22T 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. The system consists of the following components: •...
  • Page 278 Section 7 Cirrus Design Systems Description SR22T XM RADIO RECEIVER (optional) XM SATELLITE DATA LINK RECEIVER (optional) FMS KEYBOARD MAG 1 MAG 2 AHRS 1 AHRS 2 AUTOPILOT (optional) MODE CONTROLLER IRIDIUM GLOBAL SATELLITE DATALINK AIR DATA (optional) COMPUTER 2...
  • Page 279 Cirrus Design Section 7 SR22T Systems Description GDU Primary Flight Display The Primary Flight Display, located directly in front of the pilot, is intended to be the primary display of flight parameter information (attitude, airspeed, heading, and altitude) during normal operations.
  • Page 280 Section 7 Cirrus Design Systems Description SR22T 3 and the 5-amp MFD 2 circuit breaker on MAIN BUS 1. Either circuit is capable of powering the MFD. System start-up is automatic once power is applied. Power-on default brightness is determined by ambient lighting and is user adjustable.
  • Page 281 Cirrus Design Section 7 SR22T Systems Description 3 4 5 6 7 8 9 13 14 15 19 20 21 Legend 1. Soft Keys 11. NAV Transceiver Selection & Tune 2. PFD 12. MFD 3. PFD Range/Pan Joystick 13. PFD Direct-to-Course 4.
  • Page 282 Section 7 Cirrus Design Systems Description SR22T 22 23 25 26 27 28 29 30 31 GARMIN IDENT FMS/XPDR RANGE MENU XPDR COM/NAV PROC DFLT MAP PUSH SYNC PUSH PUSH EMERG CRSR/1-2 PUSH CTR ALT SEL BKSP PUSH SYNC Flight Management System Keyboard Legend 22.
  • Page 283 Cirrus Design Section 7 SR22T Systems Description GIA 63W Integrated Avionics Units The Integrated Avionics Units, located behind the MFD and instrument panel, function as the main communication hub, linking all Integrated Avionics System components with the PFD. Each Integrated Avionics...
  • Page 284 Section 7 Cirrus Design Systems Description SR22T GMA 350 Audio Panel with Marker Beacon Receiver The 350 Audio Panel, installed on the center console below the Flight Management System Keyboard, integrates NAV/COM digital audio, intercom and marker beacon controls. The VHF communications...
  • Page 285: Optional Avionics

    Cirrus Design Section 7 SR22T Systems Description Optional Avionics GTX 33 Mode S Transponder The GTX 33 Mode S solid-state transponder communicates with the primary Integrated Avionics Unit and provides Modes A, C, and S interrogation/reply capabilities. The transponder is controlled via the PFD or Flight Management System Keyboard and is located in the empennage avionics compartment.
  • Page 286 Section 7 Cirrus Design Systems Description SR22T GDL 69/69A XM Satellite Weather and Radio The Data Link Satellite Receiver, mounted in the empennage avionics compartment, receives and transmits real-time weather information to the MFD and PFD. If GDL 69A option is installed, this unit also...
  • Page 287 Cirrus Design Section 7 SR22T Systems Description Stormscope WX-500 Weather Mapping Sensor The Stormscope WX-500 System detects electrical discharges associated with thunderstorms and displays the activity on the MFD. The system consists of an antenna located on top of the fuselage and a processor unit mounted under the aft baggage floor.
  • Page 288 Section 7 Cirrus Design Systems Description SR22T DME/ADF circuit breaker on AVIONICS BUS. Refer to the Perspective Integrated Avionics System Pilot’s Guide for a general description of the system and its operating modes. Refer to the Bendix/King DME System Pilot’s Guide for a detailed discussion of the system.
  • Page 289 Cirrus Design Section 7 SR22T Systems Description Max Viz Enhanced Vision System The Enhanced Vision System is an electro-optical system that uses a Long-Wave Infrared (IR) camera. Infrared is particularly effective at night, smoke, haze, and smog in addition to a broad spectrum of rain, snow, and radiation-type fog.
  • Page 290 Section 7 Cirrus Design Systems Description SR22T LEGEND 1. AHRS 1 2. Integrated Avionics Unit 1 3. AHRS 2 4. Avionics Cooling Fan 5. Integrated Avionics Unit 2 6. Engine Airframe Unit 7. Air Data Computer 2 (opt) 8. Air Data Computer 1 9.
  • Page 291: Avionics Support Equipment

    Cirrus Design Section 7 SR22T Systems Description 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 292 Section 7 Cirrus Design Systems Description SR22T Headset and Microphone Installation The airplane is equipped with provisions for five Active Noise Reduction (ANR) and three conventional (MIC/HEADPHONES) headsets. Headset jacks for the pilot, front, and rear seat passenger are located in the map case.
  • Page 293 Cirrus Design Section 7 SR22T Systems Description for PFD and Integrated Avionics Unit Fan operation is supplied through the 5-amp AVIONICS FAN 2 circuit breaker on MAIN BUS 2. P/N 13772-005 P/N 13772-005 7-87 7-87 Original Issue...
  • Page 294: Cabin Features

    Section 7 Cirrus Design Systems Description SR22T Cabin Features Emergency Locator Transmitter The airplane is equipped with a self-contained emergency locator transmitter (ELT). The transmitter and antenna are installed immediately behind the aft cabin bulkhead, slightly to the right of the airplane centerline.
  • Page 295 Cirrus Design Section 7 SR22T Systems Description b. Disconnect fixed antenna lead from front of unit. c. Disconnect lead from remote switch and indicator unit. d. Loosen attach straps and remove transmitter unit and portable antenna. e. Attach portable antenna to antenna jack on front of unit.
  • Page 296: Hour Meters

    Section 7 Cirrus Design Systems Description SR22T Hour Meters The airplane is equipped with two hour meters located inside the armrest storage compartment between the pilot and copilot seats. The #1 hour meter, labeled HOBBS begins recording when the BAT 1 switch is ON and either the ALT 1 or ALT 2 switch is ON.
  • Page 297: Cirrus Airplane Parachute System

    Systems Description Cirrus Airplane Parachute System The airplane is equipped with a Cirrus Airplane 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 298: Activation Handle

    Section 7 Cirrus Design Systems Description SR22T 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 299: Deployment Characteristics

    Cirrus Design Section 7 SR22T Systems Description 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 300 Section 7 Cirrus Design Systems Description SR22T • Note • The CAPS is designed to work in a variety of airplane attitudes, including spins. However, deployment in an attitude other than level flight may yield deployment characteristics other than those described above.
  • Page 301 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 302 Section 8 Cirrus Design Handling and Servicing SR22T Intentionally Left Blank P/N 13772-005 Original Issue...
  • Page 303: Introduction

    Operator’s Publications The FAA Approved Airplane Flight Manual and Pilot’s Operating Handbook (POH) is provided at delivery. Additional or replacement copies may be obtained from Cirrus Design by contacting the Customer Service Department. Service Publications The following service publications are available for purchase from Cirrus Design: •...
  • Page 304: Ordering Publications

    Service Bulletin. Give careful attention to the Service Advisory Notice information. Ordering Publications Aircraft publications subscription service may be obtained by contacting Customer Service at Cirrus Design as follows: Cirrus Design Corporation Customer Service 4515 Taylor Circle Duluth, MN 55811...
  • Page 305: Airplane Records And Certificates

    Cirrus Design Section 8 SR22T 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 306: 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 307: 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 308: Pilot Performed Preventative Maintenance

    Section 8 Cirrus Design Handling and Servicing SR22T 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 309 Cirrus Design Section 8 SR22T 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 310: Ground Handling

    Section 8 Cirrus Design Handling and Servicing SR22T 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 311: Towing

    Cirrus Design Section 8 SR22T 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 312: Taxiing

    Section 8 Cirrus Design Handling and Servicing SR22T Taxiing Before attempting to taxi the airplane, ground personnel should be instructed and authorized by the owner to taxi the airplane. Instruction should include engine starting and shutdown procedures in addition to taxi and steering techniques.
  • Page 313: Parking

    Cirrus Design Section 8 SR22T Handling and Servicing Parking The airplane should be parked to protect the airplane from weather and to prevent it from becoming a hazard to other aircraft. The parking brake may release or exert excessive pressure because of heat buildup after heavy braking or during wide temperature swings.
  • Page 314: Tiedown

    Section 8 Cirrus Design Handling and Servicing SR22T Tiedown The airplane should be moored for immovability, security and protection. FAA Advisory Circular AC 20-35C, Tiedown Sense, contains additional information regarding preparation for severe weather, tiedown, and related information. The following procedures should be used for the proper mooring of the airplane: 1.
  • Page 315 Cirrus Design Section 8 SR22T Handling and Servicing Raise Airplane • Caution • Do not jack the aircraft outside or in open hangar with winds in excess of 10 mph. The empty CG is forward of the wing jacking points. To prevent...
  • Page 316: Servicing

    Section 8 Cirrus Design Handling and Servicing SR22T Servicing Landing Gear Servicing The main landing gear wheel assemblies use 15 x 6.00 x 6, six-ply rating tires and tubes. The nose wheel assembly uses a 5.00 x 5 six- ply rating, type III tire and tube. Always keep tires inflated to the rated pressure to obtain optimum performance and maximum service.
  • Page 317 Cirrus Design Section 8 SR22T Handling and Servicing Brake Inspection The brake assemblies and linings should be checked at every oil change (50 hours) for general condition, evidence of overheating, and deterioration. The aircraft should not be operated with overheated, damaged, or leaking brakes.
  • Page 318: Tire Inflation

    Section 8 Cirrus Design Handling and Servicing SR22T Tire Inflation For maximum service from the tires, keep them inflated to the proper pressure. When checking tire pressure, examine the tires for wear, cuts, nicks, bruises and excessive wear. To inflate tires: 1.
  • Page 319 Cirrus Design Section 8 SR22T Handling and Servicing sooner under unfavorable operating conditions. The following grades are recommended for the specified temperatures at sea level (SL): Ambient Air Temperature (SL) Single Viscosity Multi-Viscosity All Temperatures -— 20W-60 20W-50 15W-50 Below 40°F...
  • Page 320 Section 8 Cirrus Design Handling and Servicing SR22T 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 321: Fuel System Servicing

    Cirrus Design Section 8 SR22T Handling and Servicing 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 322 Section 8 Cirrus Design Handling and Servicing SR22T To refuel airplane: 1. Place fire extinguisher near fuel tank being filled. 2. Connect ground wire from refuel nozzle to airplane exhaust, from airplane exhaust to fuel truck or cart, and from fuel truck or cart to a suitable earth ground.
  • Page 323: Battery Service

    Cirrus Design Section 8 SR22T Handling and Servicing If sampling reveals contamination, the gascolator and tank drains must be sampled again repeatedly until all contamination is removed. It is helpful to gently rock the wings and lower the tail slightly to move contaminates to the drain points for sampling.
  • Page 324: Oxygen System Servicing

    Service the oxygen system per the appropriate revision of the Precise Flight Instructions for Continued Airworthiness for the Cirrus SR20/ SR22 Built-In Oxygen System, STC number SA01708SE, document number 102NPMAN0003.
  • Page 325: Cleaning And Care

    Cirrus Design Section 8 SR22T Handling and Servicing 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 326 Section 8 Cirrus Design Handling and Servicing SR22T 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 327 Cirrus Design Section 8 SR22T Handling and Servicing 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 328 Section 8 Cirrus Design Handling and Servicing SR22T 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 329 Cirrus Design Section 8 SR22T Handling and Servicing Landing Gear Before cleaning the landing gear, place a plastic cover or similar material over the wheel and brake assembly. 1. Place a pan under the gear to catch waste. 2. Spray or brush the gear area with solvent or a mixture of solvent and degreaser, as desired.
  • Page 330: Cleaning Interior Surfaces

    Section 8 Cirrus Design Handling and Servicing SR22T Cleaning Interior Surfaces Seats, carpet, upholstery panels, and headliners should be vacuumed at regular intervals to remove surface dirt and dust. While vacuuming, use a fine bristle nylon brush to help loosen particles.
  • Page 331 Cirrus Design Section 8 SR22T 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 332 Section 8 Cirrus Design Handling and Servicing SR22T 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 333 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 334 Section 8 Cirrus Design Handling and Servicing SR22T Intentionally Left Blank 8-34 P/N 13772-005 Original Issue...
  • Page 335 01-06-10 ___ 13772-114 R1 SR22 / SR22T Airplanes Registered in Canada 07-07-10 ___ 13772-122 R1 SR22 / SR22T Airplanes Registered in European Union 07-07-10 ___ 13772-131 R2 Artex ME406 406 MHz ELT System 01-06-10 ___ 13772-135 R3 GFC 700 Automatic Flight Control System...
  • Page 336 This Log of Supplements shows all Cirrus Design Supplements available for the aircraft at the corresponding date of the revision level shown in the lower left corner. A check mark in the Part Number column indicates that the supplement is applicable to the POH.
  • Page 337 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement Approved Oxygen Systems When supplemental oxygen is required by the applicable operating rules (FAR Part 91 or FAR Part 135), this Supplement is applicable and must be inserted in the Supplements Section of the Pilot’s...
  • Page 338 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General This supplement lists the approved portable oxygen systems that may be used in the aircraft when supplemental oxygen is required by the applicable operating rules, as well as provides mounting instructions and general operating procedures for all approved systems.
  • Page 339 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3 - Emergency Procedures Smoke and Fume Elimination In addition to the procedures outlined in the basic Handbook, pilot and passengers should don cannulas or masks and use oxygen at the maximum flow rate until smoke and fumes have cleared.
  • Page 340 Section 9 Cirrus Design Supplements SR22 / SR22T Descent After airplane descends through altitude requiring oxygen: 1. Oxygen Shutoff Valve...............OFF 2. Pilot and passengers ......Stow Masks or Cannulas Section 5 - Performance No change from basic Handbook. Section 6 - Weight & Balance The weight, arm, and moment for fully charged systems (1800 –...
  • Page 341 Cirrus Design Section 9 SR22 / SR22T Supplements INITIAL INSTALLATION Clip strap to triangular loop as shown in Detail A. Route strap over headrest, down TUFF PACK BAG the back of the seat, and forward between the cushion and seat back. Clip strap to lower triangular loop.
  • Page 342 Section 9 Cirrus Design Supplements SR22 / SR22T OXYGEN DURATION - HOURS Fully Charged System (1800 psig at 70° F) Number of Altitude ~ Feet System Persons Typical Using O 10,000 15,000 18,000 25,000 (Liters) 2.23 1.49 1.24 0.89 XCP-180 1.12...
  • Page 343 FAA Approved Airplane Flight Manual Supplement SR22 / SR22T Airplanes Registered in Canada 1. This supplement is required for operation of Cirrus Design SR22 airplanes when registered in Canada. This supplement must be attached to the applicable SR22 FAA-approved Airplane Flight Manual (P/N 13772-001/002/003 FAA-approved Flight Manual revision).
  • Page 344 Section 9 Cirrus Design Supplements SR22 / SR22T Weight Conversion Kilograms Into Pounds Kilograms En Livres 11.0 13.2 15.4 17.6 19.8 22.0 24.3 26.5 28.7 30.9 33.1 35.3 37.5 39.6 41.9 44.1 46.3 48.5 50.7 52.9 55.1 57.3 59.5 61.7 63.9...
  • Page 345 Cirrus Design Section 9 SR22 / SR22T Supplements Weight Conversion Kilograms x 2.205 = Pounds Pounds x 0.454 = Kilograms POUNDS KILOGRAMS SR22_FM09_1510 Units x 10, 100, etc Figure -1 Sheet 2 of 2 P/N 13772-114 3 of 14 Revision 01: 07-07-10...
  • Page 346 Section 9 Cirrus Design Supplements SR22 / SR22T Length Conversion Metres Into Feet Metres En Pieds 13.1 16.4 19.7 23.0 26.3 29.5 32.8 36.1 39.4 42.7 45.9 49.2 52.5 55.8 59.1 62.3 65.6 68.9 72.2 75.5 78.7 82.0 85.3 88.6 91.9...
  • Page 347 Cirrus Design Section 9 SR22 / SR22T Supplements Length Conversion Metres x 3.281 = Feet Feet x 0.305 = Metres FEET METRES Units x 10, 100, etc SR22_FM09_1511 Figure -2 Sheet 2 of 4 P/N 13772-114 5 of 14 Revision 01: 07-07-10...
  • Page 348 Section 9 Cirrus Design Supplements SR22 / SR22T Length Conversion Centimeters Into Inches Centimeters En Pouces inch inch inch inch inch inch inch inch inch inch 0.39 0.79 1.18 1.58 1.97 2.36 2.76 3.15 3.54 3.94 4.33 4.72 5.12 5.51 5.91...
  • Page 349 Cirrus Design Section 9 SR22 / SR22T Supplements Length Conversion Centimeters x 0.394 = Inches Inches x 2.54 = Centimeters INCHES CENTIMETERS Units x 10, 100, etc SR22_FM09_1989 Figure - 2 Sheet 4 of 4 P/N 13772-114 7 of 14...
  • Page 350 Section 9 Cirrus Design Supplements SR22 / SR22T Distance Conversion Statute Miles x 1.609 = Kilometers Kilometers x 0.622 = Statute Miles Statute Miles x 0.869 = Nautical Miles Nautical Miles x 1.15 = Statute Miles Nautical Miles x 1.852 = Kilometers Kilometers x 0.54 = Nautical Miles...
  • Page 351 Cirrus Design Section 9 SR22 / SR22T Supplements Temperature Conversion • Note • 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 352 Section 9 Cirrus Design Supplements SR22 / SR22T Volume Conversion Litres Into Imperial Gallons Litres En Gallons Impérial Gal. Gal. Gal. Gal. Gal. Gal. Gal. Gal. Gal. Gal. 0.22 0.44 0.66 0.88 1.10 1.32 1.54 1.76 1.98 2.20 2.42 2.64 2.86...
  • Page 353 Cirrus Design Section 9 SR22 / SR22T Supplements Volume Conversion Imperial Gallons x 4.546 = Litres Litres x 0.22 = Imperial Gallons Imperial Gallons x 1.2 = U.S. Gal. U.S. Gal. x 0.833= Imperial Gallons U.S. Gallons x 3.785 = Litres Litres x 0.264 = U.S.
  • Page 354 Section 9 Cirrus Design Supplements SR22 / SR22T Volume to Weight Conversion AVGAS (Specific Gravity = 0.72) Litres x 0.72 = Kilograms Kilograms x 1.389 = Litres Litres x 1.58 = Pounds Pounds x 0.633 = Litres LITRES POUNDS LITRES...
  • Page 355 Cirrus Design Section 9 SR22 / SR22T Supplements Quick Conversions In a world of U.S., Imperial, and metric measures, below is a quick way to convert from one system to another. Follow arrow and multiply; backtrack the arrow and divide. Bear in mind that the figures are...
  • Page 356 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank Figure -7 14 of 14 P/N 13772-114 Revision 01: 07-07-10...
  • Page 357 Supplement SR22 / SR22T Airplanes Registered in European Union 1. This supplement is required for operation of Cirrus Design SR22 serial numbers 0002 and subsequent and SR22T serial numbers 0001 and subsequent when registered in the European Union. This supplement must be attached to the applicable SR22 and SR22T EASA/FAA-approved Airplane Flight Manuals.
  • Page 358 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General No Change. Section 2 - Limitations No Change. Section 3 - Emergency Procedures No Change. Section 4 - Normal Procedures Noise Characteristics/Abatement Serials 22T-0001 and subsequent: The certificated noise levels for the...
  • Page 359 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement Artex ME406 406 MHz ELT System When Artex ME406 406 MHz ELT System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements Section of the Pilot’s Operating Handbook.
  • Page 360 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General The 406 MHz emergency locator transmitter (ELT) is a radio-frequency transmitter that generates a signal to assist in search and rescue for missing aircraft. The ELT automatically transmits the standard sweep tone on 121.5 MHz if rapid deceleration is detected.
  • Page 361 Cirrus Design Section 9 SR22 / SR22T Supplements Section 2 - Limitations No Change. Section 3 - Emergency Procedures Forced Landing Before performing a forced landing activate the ELT transmitter manually by turning the ELT remote switch to the 'ON'-position.
  • Page 362 Section 9 Cirrus Design Supplements SR22 / SR22T Portable Use of ELT The ELT transmitter can be removed from the airplane and used as a personal locating device if it is necessary to leave the airplane after an accident. Access the unit as described below and set the ELT transmitter control switch to the 'ON'-position.
  • Page 363 Cirrus Design Section 9 SR22 / SR22T Supplements Section 7 - Systems Description This airplane is equipped with a self-contained Artex ME406 406 MHz ELT System. The transmitter unit is automatically activated upon sensing a change of velocity along its longitudinal axis exceeding 4 to 5 feet per second.
  • Page 364 Section 9 Cirrus Design Supplements SR22 / SR22T Section 8 - Handling, Servicing & Maintenance ELT and RCPI batteries must be inspected in accordance with the Airplane Maintenances Manual, 5-20 - Scheduled Maintenance Checks. The ELT and RCPI batteries must be replaced upon reaching the date...
  • Page 365 Cirrus Design Section 9 SR22 / SR22T Supplements system or provide the same level of confidence as does an AM radio. 1. Tune aircraft receiver to 121.5 MHz. 2. Turn the ELT aircraft panel switch "ON" for about 1 second, then back to the "ARM"...
  • Page 366 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 8 of 8 P/N 13772-131 Revision 02: 01-06-10...
  • Page 367 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the GFC 700 Automatic Flight Control System (Aircraft Serials w/ Perspective Avionics Only) Including optionally installed Electronic Stability and Protection (ESP), Underspeed Protection (USP), and Hypoxia Detection and Automatic Descent functions.
  • Page 368 Control System (AFCS) which is fully integrated within the Cirrus Perspective Integrated Avionics System architecture. Refer to Section 7 - System Description and the Cirrus Perspective Pilot’s Guide for additional description of the AFCS and operating procedures.. Determining status of Autopilot Underspeed Protection (USP)
  • Page 369 Cirrus Design Section 9 SR22 / SR22T Supplements 6. The Autopilot may not be engaged beyond the Engagement Limits. If the Autopilot is engaged beyond the command limits (up to engagement limits) it will be rolled or pitched to within the command limits and an altitude loss of 1000 feet or more can be expected while attitude is established in the selected mode.
  • Page 370 Section 9 Cirrus Design Supplements SR22 / SR22T Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure abnormal procedure in the basic POH. Do not reengage the Autopilot until the malfunction has been identified and corrected. The Autopilot may be disconnected by: 1.
  • Page 371 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3A - Abnormal Procedures Altitude Miscompare ALT MISCOMP Caution ALT MISCOMP For dual ADC installations, altitude difference is greater than 200 feet between ADC1 and ADC2. 1. Altitude ..... CROSS-CHECK ADC1 against Standby Altimeter 2.
  • Page 372 Section 9 Cirrus Design Supplements SR22 / SR22T Heading Miscompare HDG MISCOMP Caution HDG MISCOMP For dual AHRS installations, heading difference is greater than 6° between AHRS 1 and AHRS 2. 1. Heading..CROSS-CHECK AHRS1 against Magnetic Compass 2. AHRS2 ................SELECT a.
  • Page 373 Cirrus Design Section 9 SR22 / SR22T Supplements advisory since backup source is not available for comparison. Flight Director, Autopilot and ESP will become available when unreliable AHRS CB is pulled. Roll Miscompare ROLL MISCOMP Caution ROLL MISCOMP For dual AHRS installations, roll (bank) difference is greater than 6°...
  • Page 374 Section 9 Cirrus Design Supplements SR22 / SR22T Autopilot and PFD Using Different AHRSs AP/PFD AHRS Caution AP/PFD AHRS The Autopilot and PFD are using different Attitude and Heading Reference Systems. 1. Continue flight without Autopilot. Monitor Standby Instruments. Pilot may manually select other AHRS if installed.
  • Page 375 Cirrus Design Section 9 SR22 / SR22T Supplements Course Selection Track Error COURSE SEL Advisory COURSE SEL The pilot has selected an Autopilot mode (ROL) and engaged a NAV mode (VLOC or GPS) and the current aircraft track will not intercept the selected course.
  • Page 376 Section 9 Cirrus Design Supplements SR22 / SR22T AUTO DESCENT Warning AUTO DESCENT No pilot response to the HYPOXIA ALERT annunciation detected after one minute. Warning remains until pilot responds. Automatic descent begins after one minute of unanswered Warning. Once it begins automatic descent will commence to 14,000 for 4 minutes, then to 12,500' thereafter.
  • Page 377 Cirrus Design Section 9 SR22 / SR22T Supplements Underspeed Protection Recovery (Optional) UNDERSPEED PROTECT ACTIVE Warning UNDERSPEED PROTECT ACTIVE Autopilot engaged and airspeed has fallen below minimum threshold. Recovery may be initiated in one of three ways: 1. Power Lever ..............INCREASE as required to correct underspeed condition.
  • Page 378 Section 4 - Normal Procedures • Note • Normal operating procedures for the GFC 700 Automatic Flight Control System are described in the Cirrus Perspective Pilot’s Guide. PreFlight Inspection 1. A self test is performed upon power application to the AFCS. A...
  • Page 379 Cirrus Design Section 9 SR22 / SR22T Supplements Temporary Interrupt of ESP (Optional) Although ESP is only provided when AFCS Autopilot is disengaged, the AFCS and its servos are the source of ESP guidance. When the AP Disconnect button is pressed and held, the servos will provide no ESP control force feedback.
  • Page 380 Section 9 Cirrus Design Supplements SR22 / SR22T Section 7 - System Description This airplane is equipped with a GFC 700 - a two axis (three axis optional), fully digital, dual channel, fail passive Automatic Flight Control System (AFCS). The system consists of the GFC 705 AFCS...
  • Page 381 Cirrus Design Section 9 SR22 / SR22T Supplements GFC 705 MODE CONTROLLER INTEGRATED GO-AROUND INTEGRATED AVIONICS UNIT 2 SWITCH AVIONICS UNIT 1 A/P DISC PITCH TRIM ADAPTER 4-WAY TRIM PITCH TRIM CARTRIDGE ROLL SERVO PITCH SERVO YAW SERVO (optional) SR22_FM09_2919...
  • Page 382 Section 9 Cirrus Design Supplements SR22 / SR22T GFC 705 AFCS Mode Controller The GFC 705 AFCS Mode Controller, located in the upper section of the center console, provides primary control of Autopilot modes and, if installed, yaw damper engagement. A pitch wheel is included for adjustment of pitch mode reference.
  • Page 383 Cirrus Design Section 9 SR22 / SR22T Supplements YD - Yaw Damper Button (Optional) The YD button engages/disengages the yaw damper. • Note • The yaw damper is automatically engaged when the Autopilot is engaged with the AP button. UP/DN - Pitch Wheel The Pitch UP/DN Wheel on the controller is used to change the Flight Director pitch mode reference value.
  • Page 384 Section 9 Cirrus Design Supplements SR22 / SR22T Flight Management System Keyboard The Flight Management System Keyboard, found in the center console below the AFCS mode controller, is the primary means for data entry for the MFD and is used to control NAV/COM Radios, transponder, and flight management system entry.
  • Page 385 Cirrus Design Section 9 SR22 / SR22T Supplements GARMIN IDENT FMS/XPDR RANGE MENU XPDR COM/NAV PROC DFLT MAP PUSH SYNC PUSH PUSH EMERG CRSR/1-2 PUSH CTR ALT SEL BKSP PUSH SYNC Flight Management System Keyboard GFC 705 Mode Controller Legend 1.
  • Page 386 Section 9 Cirrus Design Supplements SR22 / SR22T Roll, Pitch and Optional Yaw Servo The Roll Servo, located below the passenger seat, the Pitch Servo, located below the baggage compartment, and the optional Yaw Servo, located in the empennage avionics bay, position the aircraft flight controls in response to commands generated by the Integrated Avionics Units Autopilot calculations.
  • Page 387 Cirrus Design Section 9 SR22 / SR22T Supplements control forces if intentional maneuvers are necessary beyond ESP's engagement threshold (i.e., isolated training maneuvers). Take Off / Go Around Button The remote TO/GA switch, located on the left side of the power lever, selects the Takeoff or Go Around mode on the Flight Director.
  • Page 388 Section 9 Cirrus Design Supplements SR22 / SR22T Electronic Stability and Protection (Optional) When installed, Electronic Stability and Protection (ESP) assists the pilot in maintaining the airplane in a safe flight condition. Through the use of the GFC 700 AFCS sensors, processors, and servos, ESP provides control force feedback, i.e.
  • Page 389 Cirrus Design Section 9 SR22 / SR22T Supplements Roll Protection Limits: Always Protected Only Protected after cross- ing turn-on threshold 0° 15° 30° 45° 60° 75° 90° Bank Angle Engagement Limit: ..............45° Maximum Stick Force attained at..........50° Disengagement Threshold (Zero Stick Force) ......30°...
  • Page 390 Section 9 Cirrus Design Supplements SR22 / SR22T Low Pitch Protection Limits Always Protected Only Protected after cross- ing turn-on threshold -0° -5° -10° -15° -20° -25° Nose Down Pitch Angle Engagement Limit: ..............-15.5° Maximum Stick Force attained at: ......... -20.5°...
  • Page 391 Cirrus Design Section 9 SR22 / SR22T Supplements High Airspeed Protection Limits - Below 17,500 ft PA Always Protected Only Protected after cross- ing turn-on threshold Indicated Airspeed (KIAS) Engagement Limit: ............200 KIAS Maximum Stick Force attained at:........205 KIAS Disengagement Threshold (Zero Stick Force) ....
  • Page 392 Section 9 Cirrus Design Supplements SR22 / SR22T Underspeed Protection Mode (Optional) When installed, to discourage aircraft operation below minimum established airspeeds the AFCS will automatically enter Underspeed Protection Mode when the Autopilot is engaged and airspeed falls below the minimum threshold. If aircraft stall warning system is not...
  • Page 393 Cirrus Design Section 9 SR22 / SR22T Supplements to a nose-up pitch to aggressively return to original altitude or glidepath/slope. 2. Disengage Autopilot via AP DISC and manually fly. 3. Change Autopilot modes to one in which the AFCS can maintain (such as VS with a negative rate).
  • Page 394 Section 9 Cirrus Design Supplements SR22 / SR22T Hypoxia Detection and Automatic Descent (Optional) When installed, the AFCS Hypoxia Detection and Automatic Descent function monitors pilot inputs to the Integrated Avionics System to identify if a pilot has become incapacitated due to hypoxia, and upon determination, automatically descends to a lower altitude where pilot recovery is more probable.
  • Page 395 SR22 / SR22T Supplements Annunciation System • Note • Refer to the Cirrus Perspective Pilot’s Guide for a detailed description of the annunciator system and all warnings, cautions and advisories. Crew Alerting System AFCS alerts are displayed in the Crew Alerting System (CAS) window located to the right of the altimeter and VSI.
  • Page 396 Section 9 Cirrus Design Supplements SR22 / SR22T Section 8 – Handling, Service, & Maintenance No Change. Section 10 – Safety Information No Change. 30 of 30 P/N 13772-135 Revision 03: 12-14-10...
  • Page 397 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the Garmin Terrain Awareness/Warning System (Aircraft Serials w/ Perspective Avionics Only) When the Garmin Terrain Awareness/Warning System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements Section of the Pilot’s Operating Handbook.
  • Page 398 System that performs the functions of a Class C Terrain Awareness and Warning System (TAWS) in accordance with TSO C151b. Refer to the Cirrus Perspective Integrated Flight Deck Pilot’s Guide for a additional information on the system and its operating modes.
  • Page 399 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3 - Emergency Procedures To prevent unwanted aural alerting during ditching or other off-airport landings, inhibit the Terrain Awareness System functions by selecting the INHIBIT Softkey on the TAWS Page. Response To TAWS Warnings...
  • Page 400 PFD. Refer to the Cirrus Perspective Integrated Flight Deck Pilot’s Guide for a additional information on the system and its operating modes. 4 of 6...
  • Page 401 Cirrus Design Section 9 SR22 / SR22T Supplements System Constraints System test at startup: Aural tone lasting approximately one second indicates successful completion of internal system test. Red TAWS FAIL Warning TAWS FAIL Aural “TAWS SYSTEM FAILURE” Warning 1. TAWS power-up self-test has failed or TAWS has detected problems with database validity, hardware status, and/or GPS status.
  • Page 402 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 6 of 6 P/N 13772-136 Revision 01: 01-06-10...
  • Page 403 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement 14 Code of Federal Regulations (CFR) Part 135 Commercial Operation of Small Aircraft Electrical Loading Shedding Procedure This supplement provides the necessary guidance for load shed in the event of a primary electrical generating source failure in accordance with 14 CFR Section 135.163(f).
  • Page 404 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General No Change. Section 2 - Limitations Kinds of Operation Equipment List Aircraft Serial Numbers 22-0002 thru 22-3416 before SB2X-33-03 Rev 1 or later, LED Position/Strobe Assembly Installation: Kinds of Operation...
  • Page 405 13.6 amp-hour battery (available from Cirrus Design Spare Parts Sales) in good condition for equipment required for emergency operation under 14 CFR 135.163(f) and meets the requirements of that paragraph.
  • Page 406 Section 9 Cirrus Design Supplements SR22 / SR22T 8. Reduce loads as required for flight conditions: a. Air Conditioning and Fan ..........OFF b. Convenience Outlet ........Disconnect appliance c. Audio Panel ...............OFF COM 1 will be supplied to pilot’s headset. Communication with passengers through audio panel will not be available.
  • Page 407 Cirrus Design Section 9 SR22 / SR22T Supplements Aircraft Serials with Perspective PFD/MFD Avionics ALT 1 Failure (Alt 1 Light Steady) Steady illumination indicates failure of alternator 1. Attempt to restore alternator. If alternator cannot be restored, Alternator 2, and Bat 2 will...
  • Page 408 Section 9 Cirrus Design Supplements SR22 / SR22T Section 3A - Abnormal Procedures No Change. Section 4 - Normal Procedures No Change. Section 5 - Performance Data No Change. Section 6 – Weight and Balance No Change. Section 7 – Airplane and Systems Description No Change.
  • Page 409 SR22T Airplanes Registered in South Africa and Operating Under the South African Civil Aviation Authority (SACAA) Requirements 1. This supplement is required for operation of Cirrus Design SR22T airplanes registered in South Africa and operating under the South African Civil Aviation Authority (SACAA) Requirements.
  • Page 410 Section 9 Cirrus Design Supplements SR22T Section 1 - General No Change. Section 2 - Limitations Placards Instrument Panel, left : NORMAL CATEGORY AIRPLANE NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED ABOVE 17,500 V NE AND V NO REDUCE LINEARLY WITH ALTITUDE:...
  • Page 411 Cirrus Design Section 9 SR22T Supplements Section 3 - Emergency Procedures No Change. Section 3A - Abnormal Procedures No Change. Section 4 - Normal Procedures No Change. Section 5 - Performance Data No Change. Section 6 – Weight and Balance No Change.
  • Page 412 Section 9 Cirrus Design Supplements SR22T Intentionally Left Blank 4 of 4 P/N 13772-146 Original Issue: 11-16-2010...
  • Page 413 SR22 / SR22T Airplanes Registered in Colombia and Operating Under the Republica De Colombia Aeronautica Civil Requirements 1. This supplement is required for operation of Cirrus Design SR22 / SR22T airplanes SR22 / SR22T Airplanes Registered in Colombia and Operating Under the Republica De Colombia Aeronautica Civil Requirements.
  • Page 414 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General No Change. Section 2 - Limitations 1. Compliance with the limitations contained in the basic AFM and approved supplements is mandatory. 2. Foreign operating rules and any references to such rules in the basic AFM and approved supplements are not applicable in Colombia.
  • Page 415 Cirrus Design Section 9 SR22 / SR22T Supplements Placards 4 PLC'S 2 PLC'S 2 PLC'S 2 PLC'S 3 PLC'S ENGINE OIL GRADE ABOVE 40°F SAE 50, 20W50 OR 20W60 BELOW 40°F SAE 30, 10W30, 15W50 OR 20W50 REFER TO AFM FOR APPROVED OILS TIPO DEL ACEITE DE MOTOR POR ARRIBA DE LOS 4°C (40°F) SAE 50, 20W50 O 20W60...
  • Page 416 Section 9 Cirrus Design Supplements SR22 / SR22T WARNING! ROCKET FOR PARACHUTE DEPLOYMENT INSIDE STAY CLEAR WHEN AIRPLANE IS OCCUPIED ¡ADVERTENCIA! COHETE PARA DESPLIEGUE DEL PARACAIDAS ADENTRO MANTENGA DISTANCIA CUANDO EL AVION ESTE OCUPADO NO PUSH NO PRESIONAR RESCUE: FRACTURE AND REMOVE WINDOW...
  • Page 417 Cirrus Design Section 9 SR22 / SR22T Supplements CLOSE PUSH PRESIONAR CERRAR PARA OPEN ABRIR OPEN ABRIR Serials 0002 thru 0521. Serials 0522 thru 0819. Serials 0820 & subs. NO STEP NO PISAR EXTERNAL DE-ICING FLUID REFER TO AFM FOR APPROVED...
  • Page 418 Section 9 Cirrus Design Supplements SR22 / SR22T AMMETER SELECT ALT 1 ALT 2 BATT GRAB HERE GRAB HERE ALT AIR PULL ON ALT STATIC SOURCE NORMAL PARK BRAKE PULL ON EM_SR22_FM02_3184 Figure - 1 Interior Placards 6 of 10...
  • Page 419 UTILIZADO EN TODO MOMENTO EL USO DE ESTE DISPOSITIVO PUEDE RESULTAR EN LESION O MUERTE MAXIMA VELOCIDAD DEMOSTRADA DE DESPLIEGUE 133 KIAS SISTEMA DE PARACAIDAS ESTRUCTURAL CIRRUS PROCEDIMIENTO DE ACTIVACION 1. CONTROL DE MEZCLA………………….CUTOFF 2. ESTA CUBIERTA........REMOVER 3. PALANCA DE ACTIVACION…..TIRE HACIA ABAJO...
  • Page 420 Section 9 Cirrus Design Supplements SR22 / SR22T ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL ELT LOCALIZADO DETRÁS DEL MAMPARO REMUEVA ALFOMBRA Y TABLERO DE ACCESO LIMITE DE PESO DISTRIBUIDO EN EL PISO 60 KG (130 LBS) CAPACIDAD MAXIMA DE CADA CORREA DE EQUIPAJE 15 KG ( 35 LBS)
  • Page 421 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3 - Emergency Procedures No Change. Section 3A - Abnormal Procedures No Change. Section 4 - Normal Procedures No Change. Section 5 - Performance Data No Change. Section 6 – Weight and Balance No Change.
  • Page 422 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 10 of 10 P/N 13772-147 Original Issue: Dec 07, 2010...
  • Page 423 Operating Under the Dirección General de Aeronáutica Civil de Chile (DGAC) Requirements 1. This supplement is required for operation of Cirrus Design SR22 / SR22T Airplanes Registered in Chile and Operating Under the Dirección General de Aeronáutica Civil de Chile (DGAC) Requirements.
  • Page 424 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General No Change. Section 2 - Limitations 1. Compliance with the limitations contained in the basic AFM and approved supplements is mandatory. 2. Foreign operating rules and any references to such rules in the basic AFM and approved supplements are not applicable in Chile.
  • Page 425 Cirrus Design Section 9 SR22 / SR22T Supplements Placards 4 PLC'S 2 PLC'S 2 PLC'S 2 PLC'S 3 PLC'S ENGINE OIL GRADE ABOVE 40°F SAE 50, 20W50 OR 20W60 BELOW 40°F SAE 30, 10W30, 15W50 OR 20W50 REFER TO AFM FOR APPROVED OILS TIPO DEL ACEITE DE MOTOR SUPERIOR DE 4°C (40°F) SAE 50, 20W50 O 20W60...
  • Page 426 Section 9 Cirrus Design Supplements SR22 / SR22T WARNING! ROCKET FOR PARACHUTE DEPLOYMENT INSIDE STAY CLEAR WHEN AIRPLANE IS OCCUPIED ¡ADVERTENCIA! COHETE PARA DESPLIEGUE DEL PARACAIDAS ADENTRO MANTENGASE ALEJADO CUANDO EL AVION ESTE OCUPADO NO PUSH NO PRESIONAR RESCUE: FRACTURE AND REMOVE WINDOW...
  • Page 427 Cirrus Design Section 9 SR22 / SR22T Supplements CLOSE PUSH PRESIONAR CERRAR PARA OPEN ABRIR OPEN ABRIR Serials 0002 thru 0521. Serials 0522 thru 0819. Serials 0820 & subs. NO STEP NO PISAR EXTERNAL DE-ICING FLUID REFER TO AFM FOR APPROVED...
  • Page 428 Section 9 Cirrus Design Supplements SR22 / SR22T AMMETER SELECT ALT 1 ALT 2 BATT GRAB HERE GRAB HERE ALT AIR PULL ON ALT STATIC SOURCE NORMAL PARK BRAKE PULL ON CL_SR22_FM09_3542 Figure - 1 Interior Placards 6 of 10...
  • Page 429 UTILIZADO EN TODO MOMENTO EL USO DE ESTE DISPOSITIVO PUEDE RESULTAR EN LESION O MUERTE MAXIMA VELOCIDAD DEMOSTRADA DE DESPLIEGUE 133 KIAS SISTEMA DE PARACAIDAS ESTRUCTURAL CIRRUS PROCEDIMIENTO DE ACTIVACION 1. CONTROL DE MEZCLA………………….CUTOFF 2. ESTA CUBIERTA........REMOVER 3. PALANCA DE ACTIVACION…..TIRE HACIA ABAJO...
  • Page 430 Section 9 Cirrus Design Supplements SR22 / SR22T ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL ELT LOCALIZADO DETRÁS DEL MAMPARO REMUEVA ALFOMBRA Y TABLERO DE ACCESO LIMITE DE PESO DISTRIBUIDO EN EL PISO 60 KG (130 LBS) CAPACIDAD MAXIMA DE CADA CORREA DE EQUIPAJE 15 KG ( 35 LBS)
  • Page 431 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3 - Emergency Procedures No Change. Section 3A - Abnormal Procedures No Change. Section 4 - Normal Procedures Noise Characteristics/Abatement Serials 22T-0001 and subsequent: The certificated noise levels for the aircraft established in accordance with ICAO Annex 16, Volume I are:...
  • Page 432 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 10 of 10 P/N 13772-148 Original Issue: Oct 04, 2012...
  • Page 433 SR22 / SR22T Airplanes Registered in Mexico and Operating Under the Direccion General de Aeronautica Civil (DGAC) Requirements 1. This supplement is required for operation of Cirrus Design SR22 / SR22T airplanes Registered in Mexico and Operating Under the Direccion General de Aeronautica Civil (DGAC) Requirements.
  • Page 434 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General No Change. Section 2 - Limitations 1. Compliance with the limitations contained in the basic AFM and approved supplements is mandatory. 2. Foreign operating rules and any references to such rules in the basic AFM and approved supplements are not applicable in Mexico.
  • Page 435 Cirrus Design Section 9 SR22 / SR22T Supplements Placards 4 PLC'S 2 PLC'S 2 PLC'S 2 PLC'S 2 PLC'S 3 PLC'S ENGINE OIL GRADE ABOVE 40°F SAE 50 OR 20W50 BELOW 40°F SAE 30, 10W30, 15W50 OR 20W50 REFER TO AFM FOR APPROVED OILS CALIDADES DE ACEITE PARA MOTOR SOBRE 40°F (4°C) SAE 50 O 20W50...
  • Page 436 Section 9 Cirrus Design Supplements SR22 / SR22T WARNING! ROCKET FOR PARACHUTE DEPLOYMENT INSIDE STAY CLEAR WHEN AIRPLANE IS OCCUPIED ¡ADVERTENCIA! COHETE PARA DESPLIEGUE DEL PARACAIDAS DENTRO MANTENGA DISTANCIA CUANDO EL AVION ESTE OCUPADO NO PUSH NO EMPUJE RESCUE: FRACTURE AND REMOVE WINDOW...
  • Page 437 Cirrus Design Section 9 SR22 / SR22T Supplements NO STEP NO PISAR EXTERNAL DE-ICING FLUID REFER TO AFM FOR APPROVED POWER DE-ICING FLUIDS 28 V DC LIQUIDO DESCONGELANTE POTENCIA REFIERASE AL MVA PARA LIQUIDOS EXTERNA DESCONGELANTES APROBADOS 28 V DC Serials w/ Ice Protection.
  • Page 438 Section 9 Cirrus Design Supplements SR22 / SR22T GRAB HERE EM_SR22_FM09_3547 Figure - 1 Interior Placards 6 of 10 P/N 13772-149 Original Issue: January 14, 2013...
  • Page 439 Cirrus Design Section 9 SR22 / SR22T Supplements PROHIBIDO FUMAR AJUSTE CINTURON DE SEGURIDAD EXTINTOR BAJO EL FRENTE DEL ASIENTO DE PILOTO AGARRAR AQUÍ EM_SR22_FM09_3548 Figure - 1 Interior Placards P/N 13772-149 7 of 10 Original Issue: January 14, 2013...
  • Page 440 Section 9 Cirrus Design Supplements SR22 / SR22T ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL ELT LOCALIZADO DETRÁS DE LA MAMPARA QUITE ALFOMBRA Y TABLERO DE ACCESO LIMITE DE PESO DISTRIBUIDO EN PISO 130 LBS (60 KG) CAPACIDAD DE CORREA DEL EQUIPAJE 35 LBS (15 KG) MAX CADA UNA...
  • Page 441 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3 - Emergency Procedures No Change. Section 3A - Abnormal Procedures No Change. Section 4 - Normal Procedures No Change. Section 5 - Performance Data No Change. Section 6 – Weight and Balance No Change.
  • Page 442 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 10 of 10 P/N 13772-149 Original Issue: January 14, 2013...
  • Page 443 Cirrus Design Section 9 SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the TKS Anti-Ice System • Approved for Flight Into Known Icing (FIKI) • 8.0 gallon usable capacity. • 4.0 gallon tank in each wing.
  • Page 444 Section 9 Cirrus Design Supplements SR22T Section 1 - General This system, when compliant with the Kinds of Operation Equipment List and Minimum Dispatch Fluid Quantity, allows flight in icing conditions as defined by Title 14 of the Code of Federal Regulations (CFR) Part 25, Appendix C - Envelopes for Continuous Maximum and Intermittent Maximum Icing.
  • Page 445 Cirrus Design Section 9 SR22T Supplements • Accumulation of ice on the upper surface or lower surface of the wing aft of the protected area. • Accumulation of ice on the propeller spinner farther back than normally observed. If the airplane encounters conditions that are determined to contain...
  • Page 446 Code of Federal Regulations (CFR) Part 25, Appendix C - Envelopes for Continuous Maximum and Intermittent Maximum Icing. This airplane is approved for flight into known icing conditions only if the following Cirrus and FAA approved equipment is installed and fully functional. Kinds of Operation...
  • Page 447 Cirrus Design Section 9 SR22T Supplements Minimum Dispatch Fluid Quantity Dispatch into known icing conditions with less than 5 gallons (19 liters) of deicing fluid is prohibited. The pilot must ensure adequate fluid quantity before each flight. If dispatching without the minimum 5 gallons and icing conditions are encountered, exit icing conditions as soon as possible.
  • Page 448: Pilot Qualification And Training

    The Pilot Qualification and Training Limitation does not apply to airplanes registered in the European Union. The pilot-in-command must successfully complete the Cirrus Icing Awareness Course or a Cirrus Design approved equivalent training course, within the preceding 24 months prior to Flight Into Forecast or Known Icing Conditions.
  • Page 449 Cirrus Design Section 9 SR22T Supplements Placards Lower wing, above anti-ice fluid drain: Upper wing, above anti-ice fluid filler cap: Bolster Switch Panel, left edge: THIS AIRCRAFT IS CERTIFIED FOR THE FOLLOWING FLIGHT OPERATIONS DAY - NIGHT - VFR - IFR...
  • Page 450 Section 9 Cirrus Design Supplements SR22T Section 3 - Emergency Procedures A failure of the Anti-Ice System is any condition, observed or suspected, in which the system fails to remove ice from protected surfaces including the propeller, in addition to any Anti-Ice System CAS failure annunciations.
  • Page 451 Cirrus Design Section 9 SR22T Supplements Anti-Ice System Failure / Excessive Ice Accumulation 1. ICE PROTECT A and B Circuit Breakers......... SET 2. Fluid Quantity........SWITCH TO FULLEST TANK 3. WIND SHLD Push-Button ........... PRESS a. Repeat operation of windshield pump to verify metering pumps are primed properly as evidenced by deicing fluid exiting windshield nozzles.
  • Page 452 Section 9 Cirrus Design Supplements SR22T Maximum Glide with Ice Accumulation Conditions Example: Power Altitude 10,000 ft. AGL Propeller Windmilling Airspeed 92 KIAS Flaps 0% (UP) Glide Distance 10.5 NM Wind Zero Best Glide Speed 92 KIAS at 3600 lb Maximum Glide Ratio ~ 6.4: 1...
  • Page 453 Cirrus Design Section 9 SR22T Supplements Section 3A - Abnormal Procedures Windshield De-Ice System Malfunction 1. ICE PROTECT A Circuit Breaker........CYCLE 2. Fluid Quantity........SWITCH TO FULLEST TANK 3. WIND SHLD Push-Button ......PRESS AS REQUIRED If the forward field of view is overly restricted during landing approach and taxiing: a.
  • Page 454 Section 9 Cirrus Design Supplements SR22T Static System Malfunction If erroneous readings on the pilot’s flight instruments are suspected the static button(s) on side of fuselage may be obstructed. Refer to Section 3A - Abnormal Procedures, Static Source Blocked in the basic handbook.
  • Page 455 Cirrus Design Section 9 SR22T Supplements 4. ICE PROTECT Mode Switch ..........HIGH If warning annunciation extinguishes: a. Anti-Ice System ............MONITOR If warning annunciation does not extinguishes or intermittent: a. PUMP BKUP Switch............ON b. Icing Conditions..........AVOID / EXIT...
  • Page 456 Section 9 Cirrus Design Supplements SR22T Unreliable Fluid Quantity Warning ANTI ICE QTY PFD Alerts Window: “Left and right fluid quantities unknown (TKS)” Both fluid quantities are unknown and both tanks are closed. 1. ICE PROTECT System Switch..........OFF 2. Icing Conditions ............AVOID / EXIT Low Pressure Caution.
  • Page 457 Cirrus Design Section 9 SR22T Supplements High Pressure Caution ANTI ICE PSI PFD Alerts Window: “Pressure is high (TKS)” Typically indicates clogged filter. 1. Evidence of Anti-Ice Flow ......MONITOR / VERIFY 2. Icing Conditions ............AVOID / EXIT Airspeed Caution ANTI ICE SPD PFD Alerts Window: “Airspeed is too low/high for ice protection (TKS)”...
  • Page 458 Section 9 Cirrus Design Supplements SR22T Fluid Quantity Imbalance Caution ANTI ICE QTY PFD Alerts Window: “Fluid quantity imbalance has been detected” Imbalance between left and right sensed fluid quantity is greater than 1.0 gallon. 1. Revert to AUTO control of the fluid source to control the fluid quantity.
  • Page 459 Cirrus Design Section 9 SR22T Supplements Left/Right Fluid Quantity Caution ANTI ICE LVL PFD Alerts Window: “Right/Left tank fluid quantity is unreliable (TKS)” L / R fluid quantities on Anti Ice - TKS block of ENGINE page is “greyed out” and/or fluid quantity is marked with a “Red X”. The deicing fluid sensing system has detected conflicting system information regarding the fluid quantity in the tanks.
  • Page 460 Section 9 Cirrus Design Supplements SR22T Section 4 - Normal Procedures • WARNING • Holding in icing conditions for longer than 45 minutes may reduce margins and could result in inadequate handling and control characteristics. Flight into known icing conditions is prohibited if porous panels do not fully "wet-out"...
  • Page 461 Cirrus Design Section 9 SR22T Supplements which may not be adequate to wet-out the entire panel if the Pre-Flight Inspection is performed at warmer temperatures. Increasing the system flow rate (MAX vs. HIGH or HIGH w/ PUMP BKUP vs. HIGH) will increase the arterial pressure of the system which promotes the complete wet-out of the porous panels.
  • Page 462 Section 9 Cirrus Design Supplements SR22T n. PITOT HEAT Switch......ON 45 seconds, then OFF 2. Empennage a. Stabilizers Porous Panels ....CONDITION / SECURITY (1) Verify Evidence of Deicing Fluid Along Length of Panels and Elevator Horns. 3. Right Wing Forward and Main Gear a.
  • Page 463 Cirrus Design Section 9 SR22T Supplements 8. Left Wing Tip • WARNING • Pitot Probe may be HOT. a. Pitot Probe (underside) ......UNOBSTRUCTED b. Pitot Probe.............. VERY HOT 9. Cabin a. Fluid Quantity ......VERIFY 5 GALLON MINIMUM b. ICE PROTECT System Switch .......... OFF c.
  • Page 464 Section 9 Cirrus Design Supplements SR22T Before Takeoff If icing conditions are anticipated immediately after take-off: 1. ICE PROTECT System Switch..........ON 2. ICE PROTECT Mode Switch........NORM / HIGH 3. PITOT HEAT Switch ..............ON 4. Cabin Heat ................HOT 5.
  • Page 465 Cirrus Design Section 9 SR22T Supplements While in Icing Conditions: 1. FLAPS ..................UP 2. Ice-Inspection Lights ..........AS REQUIRED 3. Cabin Heat ................HOT 4. Windshield Defrost..............ON 5. Fluid Quantity and Endurance ........MONITOR a. Ensure adequate quantity to complete flight.
  • Page 466: Approach And Landing

    Section 9 Cirrus Design Supplements SR22T Cruise During icing encounters in cruise, increase engine power to maintain cruise speed as ice accumulates on the unprotected areas and causes the aircraft to slow down. The autopilot may be used in icing conditions. However, every 30 minutes the autopilot should be disconnected to detect any out-of-trim conditions caused by ice buildup.
  • Page 467 Cirrus Design Section 9 SR22T Supplements After Landing and Shutdown 1. PITOT HEAT Switch..............OFF 2. ICE PROTECT System Switch ..........OFF 3. PUMP BKUP Switch ..............OFF 4. Ice-Inspection Lights ..............OFF • Note • When the Anti-Ice System has been used, avoid touching the airframe structure or windshield as they will be partially covered with deicing fluid.
  • Page 468: Stall Speeds With Ice Accumulation

    Section 9 Cirrus Design Supplements SR22T Section 5 - Performance Airplane performance and stall speeds without ice accumulation are essentially unchanged with the installation of the Ice Protection System. Significant climb and cruise performance degradation, range reduction, as well as buffet and stall speed increase can be expected if ice accumulates on the airframe.
  • Page 469 Cirrus Design Section 9 SR22T Supplements Enroute Climb Gradient with Ice Accumulation Conditions: • Power ....................Full Throttle • Mixture ................... Full Rich (Green Arc) • 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 470 Section 9 Cirrus Design Supplements SR22T Enroute Climb Gradient (Continued) Weight Press Climb CLIMB GRADIENT - Feet / Nautical Mile Altitude Speed Temperature ~°C KIAS 2000 4000 6000 8000 10000 12000 2900 14000 16000 18000 20000 22000 24000 25000 28 of 52...
  • Page 471: Enroute Rate Of Climb With Ice Accumulation

    Cirrus Design Section 9 SR22T Supplements Enroute Rate of Climb with Ice Accumulation Conditions: • Power ....................Full Throttle • Mixture ................... Full Rich (Green Arc) • 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 472 Section 9 Cirrus Design Supplements SR22T Enroute Rate of Climb (Continued) Weight Press Climb RATE OF CLIMB ~ Feet per Minute Altitude Speed Temperature ~°C KIAS 1556 1446 1337 1283 2000 1477 1368 1260 1206 4000 1399 1290 1182 1129...
  • Page 473 Cirrus Design Section 9 SR22T Supplements Time, Fuel & Distance to Climb: Full Power Climb with Ice Accumulation Conditions: • Power ....................Full Throttle • Mixture ............Maintain Fuel Flow in GREEN ARC • Weight ......................3600 LB • Winds ....................... Zero •...
  • Page 474 Section 9 Cirrus Design Supplements SR22T Cruise Performance with Ice Accumulation Conditions: • Weight ......................3400 LB • Winds........................ Zero • Note • Subtract 10 KTAS if nose wheel pant and fairing removed. Lower KTAS by 10% if nose and main wheel pants & fairings are removed.
  • Page 475 Cirrus Design Section 9 SR22T Supplements CRUISE PERFORMANCE ISA -30°C ISA +30°C Altitude Power Econ Econ Econ (ft MSL) (% of 315) (GPH) (KTAS) (nm/gal) (KTAS) (nm/gal) (KTAS) (nm/gal) 12000 18.3 16.4 14.6 14000 18.3 16.4 14.6 16000 18.3 16.4 14.6...
  • Page 476 Section 9 Cirrus Design Supplements SR22T Range / Endurance: Full Power Climb with Ice Accumulation Conditions: • Mixture.............Best Economy - Target Fuel Flow or less • Weight ..........3600 LB for Climb, Avg 3400 LB for Cruise • Winds........................ Zero • Total Fuel ....................92 Gallons •...
  • Page 477 Cirrus Design Section 9 SR22T Supplements Range / Endurance: Full Power Climb with Ice Accumulation (Continued) Range / Endurance: 75% Power Cruise - Full Power Climb Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise...
  • Page 478 Section 9 Cirrus Design Supplements SR22T Balked Landing Climb Gradient with Ice Accumulation Conditions: • Power....................Full Throttle • Mixture.................... Set per Placard • Flaps......................50% (DN) • Climb Airspeed ....................V REF • Note • Balked Landing Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
  • Page 479 Cirrus Design Section 9 SR22T Supplements Balked Landing Rate of Climb with Ice Accumulation Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps .........................50% • Climb Airspeed....................V REF • Note • Balked Landing Rate of Climb values shown are the 50% flaps change in altitude for unit time expended expressed in Feet per Minute.
  • Page 480 Section 9 Cirrus Design Supplements SR22T Landing Distance with Ice Accumulation Conditions: • Winds........................ Zero • Runway..................Dry, Level, Paved • Note • The following factors are to be applied to the computed landing distance for the noted condition: • Normal landings will be completed with the flaps set to 50%.
  • Page 481 Cirrus Design Section 9 SR22T Supplements Landing Distance - Flaps 50% WEIGHT: 3600 LB Headwind: Subtract 10% for each 13 Speed over 50 Ft Obstacle: 88 KIAS knots headwind. Flaps: 50% Tailwind: Add 10% for each 2 knots Power: Smooth power reduction from obstacle to tailwind up to 10 knots.
  • Page 482 Section 9 Cirrus Design Supplements SR22T Section 6 - Weight & Balance Weight and Balance Refer to Section 6 - of the basic POH for current weight and balance data. Use the following table to determine the Moment/1000 for deicing fluid to complete the Loading Form in the Weight and Balance Section of the basic POH.
  • Page 483 Cirrus Design Section 9 SR22T Supplements Section 7 - System Description The TKS Anti-Ice System can prevent and remove ice accumulation on the flight surfaces by distributing a thin film of ice protection fluid on the wing, horizontal stabilizer, vertical stabilizer, elevator tips, and propeller.
  • Page 484: Porous Panels

    Section 9 Cirrus Design Supplements SR22T If the system is ON and PUMP BKUP is selected, #1 pump will operate (if not failed) based on the mode setting (NORM or HIGH) while #2 pump operates continuously (PUMP BKUP), causing the range and endurance to decrease from the published values, e.g.
  • Page 485 Cirrus Design Section 9 SR22T Supplements smaller than the openings of the outer surface. The leading edge of the panel serves as a reservoir as fluid entering the panel fills the cavity behind the porous membrane then overcomes this resistance to be distributed by the openings in the external surface.
  • Page 486 Section 9 Cirrus Design Supplements SR22T 8 9 10 LEGEND 1. LH Outbd Panel 14. Stall Transducer 27. RH Elevator Tip Panel 2. LH Vent 15. RH Vent 28. V Stab Panel 3. LH Inbd Panel 16. RH Outbd Panel 29.
  • Page 487 Cirrus Design Section 9 SR22T Supplements System Control System operation is controlled by five bolster panel switches and three MFD softkeys: • Bolster Panel Switches: Metering pump operation and mode control (flow rate) are controlled by the NORM, HIGH, and MAX switches.
  • Page 488 Section 9 Cirrus Design Supplements SR22T • RIGHT: Ice protection fluid is drawn from the right tank regardless of sensed quantity. System Indicating System Indicating is displayed as bar graphs and text in the lower left corner of the MFD ENGINE page. The bar graphs, marked from 0 to 4 U.S.
  • Page 489 Cirrus Design Section 9 SR22T Supplements Anti Ice - TKS Time Rem (H:MM) 0:31 High 1:03 Norm 2:06 Range 79 NM ENGINE ANTI-ICE DCLTR ASSIST FUEL NOTE Illustration depicts system during Auto Tank Mode with LH and RH tanks ON while operating in MAX mode.
  • Page 490 Section 9 Cirrus Design Supplements SR22T Stall Warning System Stall warning is provided by the lift transducer, mounted on the leading edge of the right wing and the stall warning computer located under the cabin floor. The lift transducer senses the force of the airstream on the vane, producing an electrical output to the stall warning computer.
  • Page 491 Cirrus Design Section 9 SR22T Supplements inspection lights illuminate the leading edge of the wing and horizontal stabilizer. Components of the system include the LED light assemblies and a two-position toggle switch labeled ICE on the Exterior Lights section of the bolster switch panel.
  • Page 492 Section 9 Cirrus Design Supplements SR22T Section 8 – Handling, Service, & Maintenance • Caution • During long periods of non-use, the porous panel membranes may dry out which could cause uneven fluid flow during subsequent operation. Perform the Pre-Flight Inspection every 30 days to keep porous panel membranes wetted.
  • Page 493 Cirrus Design Section 9 SR22T Supplements Metering Pump Priming If air entered the system due to the fluid tank(s) running dry during system operation, it may require several cycles of the windshield/ priming pump to prime the metering pumps. In the event that the metering pumps cannot prime themselves, the...
  • Page 494 Section 9 Cirrus Design Supplements SR22T Intentionally Left Blank 52 of 52 P/N 13772-151 Original Issue: 02-01-13...
  • Page 495 SR22T Safety Information Section 10: Safety Information Table of Contents Introduction ..................3 Cirrus Airframe Parachute System (CAPS) ........4 Deployment Scenarios..............4 General Deployment Information ............ 7 Landing Considerations ..............8 Taxiing, Steering, and Braking Practices ......... 11 Operating Practices ..............11 Brake Maintenance ...............
  • Page 496 Section 10 Cirrus Design Safety Information SR22T Intentionally Left Blank 10-2 P/N 13772-005 Original Issue...
  • Page 497: 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 498: 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 499 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 500 Section 10 Cirrus Design Safety Information SR22T activation by the passengers is highly recommended. This scenario should be discussed with passengers prior to flight and all appropriate passengers should be briefed on CAPS operation so they could effectively deploy CAPS if required.
  • Page 501: General Deployment Information

    Cirrus Design Section 10 SR22T Safety Information General Deployment Information Deployment Speed The maximum speed at which deployment has been demonstrated is 140 KIAS. Deployment at higher speeds could subject the parachute and aircraft to excessive loads that could result in structural failure. Once a decision has been made to deploy the CAPS, make all reasonable efforts to slow to the minimum possible airspeed.
  • Page 502: Landing Considerations

    Section 10 Cirrus Design Safety Information SR22T Landing Considerations After a CAPS deployment, the airplane will descend at less than 1700 feet per minute with a lateral speed equal to the velocity of the surface wind. The CAPS landing touchdown is equivalent to ground impact from a height of approximately 13 feet.
  • Page 503 Cirrus Design Section 10 SR22T Safety Information • If a door is open prior to touchdown in a CAPS landing, the door will most likely break away from the airplane at impact. • If the door is open and the airplane contacts the ground in a rolled condition, an occupant could be thrown forward and strike their head on the exposed door pillar.
  • Page 504 Section 10 Cirrus Design Safety Information SR22T Post Impact Fire If there is no fire prior to touchdown and the pilot is able to shut down the engine, fuel, and electrical systems, there is less chance of a post impact fire. If the pilot suspects a fire could result from impact, unlatching a door immediately prior to assuming the emergency landing body position should be considered to assure rapid egress.
  • Page 505: Taxiing, Steering, And Braking Practices

    SR22T Safety Information Taxiing, Steering, and Braking Practices Cirrus aircraft use a castering nose wheel and rely on aerodynamic forces and differential braking for directional control while taxiing. Proper braking practices are therefore critical to avoid potential damage to the brakes.
  • Page 506: Brake Maintenance

    Section 10 Cirrus Design Safety Information SR22T • 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.

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