Cirrus DESIGN SR22T Pilot Operating Handbook

Cirrus DESIGN SR22T Pilot Operating Handbook

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PILOT'S OPERATING HANDBOOK
AND FAA APPROVED
AIRPLANE FLIGHT MANUAL
for the
CIRRUS DESIGN SR22T
A i r c r a f t S e r i a l s S R 2 2 T - 0 0 0 1 & 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
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. SR22T ____________ Registration Num. __________________
P/N 13772-003
Original Issue: January 06, 2010

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  • 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. SR22T ____________ Registration Num. __________________...
  • Page 2 Copyright © 2010 - All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811...
  • 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 3A-20 Revision 1 5-19 Original Issue 7-26 Original Issue 3A-21 Revision 1 5-20 Revision 1 7-27 Original Issue 3A-22...
  • Page 5: Revision 1

    Cirrus Design Pilot’s Operating Handbook SR22T List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 7-81 Revision 1 10-6 Original Issue 7-82 Revision 1 10-7 Original Issue 7-83 Revision 1 10-8 Original Issue 7-84...
  • Page 6: Revision 1

    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 13772-003 Revision 1...
  • 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 13772-003 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 13772-003 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 at 3400 lb - 9" inches (23 cm).
  • Page 17: Original Issue

    Cirrus Design Section 1 SR22T General 49.3" 39.8" Fuselage Station 49.7" 38.5" 25.0" 16.0" 20.0" 32.0" 10.5" 39.0" 33.4" 20.0" 33.3" 5.0" 21.0" CABIN DOOR BAGGAGE DOOR OPENING OPENING SR22_FM06_1019 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: Original Issue

    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: Original Issue

    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: Original Issue

    Section 1 Cirrus Design General SR22T 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. Best Angle of Climb Speed is the speed at which the airplane will obtain the highest altitude in a given horizontal distance.
  • Page 23: Original Issue

    Cirrus Design Section 1 SR22T General Pressure Pressure Altitude (PA) is the altitude read from the Altitude altimeter when altimeter’s barometric adjustment has been set to 29.92 in.Hg (1013 mb) corrected for position and instrument error. In this Handbook, altimeter instrument errors are assumed to be zero.
  • Page 24: Original Issue

    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 Intentionally Left Blank 1-14 P/N 13772-003 Original Issue...
  • Page 27: Revision 1

    Environmental Conditions ..............17 Maximum Occupancy ..............17 Systems and Equipment Limits............18 Cirrus Perspective Integrated Avionics System ......18 L-3 Skywatch Traffic Advisory System (Optional)......21 L-3 Stormscope Weather Information System (Optional) ..... 21 Max Viz Enhanced Vision System (Optional) ....... 21 Air Conditioning System (Optional)..........
  • Page 28 Section 2 Cirrus Design Limitations SR22T Other Limitations ................22 Smoking ..................22 Placards ................... 23 P/N 13772-003 Revision 1...
  • 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 upon Section 5 Airspeed Calibrations using the normal static source. 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 upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
  • Page 32: Original Issue

    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: Weight Limits

    Cirrus Design Section 2 SR22T Limitations Propeller Hartzell Compact Series Lightweight Hub with Composite Blades Propeller Type ........Constant Speed, Three Blade Model Number..........PHC-J3Y1F-1N/N7605(B) Diameter..................78.0" Weight Limits Maximum Takeoff Weight ......... 3400 lb (1542 Kg) Maximum Weight in Baggage Compartment....130 lb (59 Kg)
  • Page 34: Original Issue

    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 Yellow Green Yellow Arc/Bar Arc/Bar Arc/Bar Arc/Bar Arc/Bar Instrument (Range & Units)
  • Page 35: Fuel

    Cirrus Design Section 2 SR22T Limitations Fuel Yellow Green Yellow Arc/Bar Arc/Bar Arc/Bar Arc/Bar Arc/Bar Instrument (Range & Units) Minimum Maximum Caution Normal Caution Minimum Range Range Range Maximum Fuel Flow –– –– 10 - 45 –– *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 31 .5% M A C 1 9.2% M A C FS 1 48.1 FS 1 42.3...
  • Page 37: Original Issue

    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 – Emergency Procedures, Spins.
  • 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 Cirrus Design Section 2 SR22T Limitations Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions ALT 1 Annunciator ALT 2 Annunciator — — Circuit Breakers As required. Equipment & Furnishings Emergency Locator Trans- mitter Restraint System One seat belt for each occupant.
  • 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: Original Issue

    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: Original Issue

    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: 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 45 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 46 Section 2 Cirrus Design Limitations SR22T 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 47: Skywatch Traffic Advisory System (Optional)

    Cirrus Design Section 2 SR22T Limitations 12. Use of use of portable electronic devices during takeoff and landing is prohibited. L-3 Skywatch Traffic Advisory System (Optional) 1. Traffic information shown on the Perspective Integrated Avionics System displays is provided as an aid in visually acquiring traffic.
  • Page 48: Inflatable Restraint System

    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....133 KIAS • Note •...
  • Page 49 Cirrus Design Section 2 SR22T Limitations Placards Engine compartment, inside oil filler access: ENGINE OIL GRADE ABOVE 40° F SAE 50 OR 20W50 OR 20W60 BELOW 40° F SAE 30 OR 10W30, 15W50, OR 20W50 REFER TO AFM FOR APPROVED OILS...
  • Page 50 Section 2 Cirrus Design Limitations SR22T 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: DE-ICING FLUID...
  • Page 51 Cirrus Design Section 2 SR22T Limitations Engine control panel: 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. BOOST FUEL PUMP...
  • Page 52 Section 2 Cirrus Design Limitations SR22T 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 53 Cirrus Design Section 2 SR22T Limitations Instrument Panel, center: DISPLAY BACKUP Bolster Panel, both sides: GRAB HERE Baggage Compartment, aft edge: ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Instrument Panel: FASTEN SEATBELTS • NO SMOKING Cabin Window, above door latch:...
  • Page 54 MUST BE WORN AT ALL TIMES USE OF THIS DEVICE COULD RESULT IN INJURY OR DEATH MAXIMUM DEMONSTRATED DEPLOYMENT SPEED 133 KIAS CIRRUS AIRFRAME PARACHUTE SYSTEM ACTIVATION PROCEDURE 1. FUEL MIXTURE........CUT-OFF 2. THIS COVER..........REMOVE 3. ACTIVATION HANDLE..PULL STRAIGHT DOWN BOTH HANDS, MAXIMUM FORCE, STEADY PULL DO NOT JERK HANDLE 4.
  • Page 55: Original Issue

    Cirrus Design Section 3 SR22T Emergency Procedures Section 3 Emergency Procedures Table of Contents Introduction ..................3 Emergency Procedures Guidance ............. 4 Preflight Planning................4 Preflight Inspections/Maintenance ..........4 Methodology ................... 4 Circuit Breakers ................5 Memory Items ................. 5 Airspeeds for Emergency Operations ..........
  • Page 56: Original Issue

    Section 3 Cirrus Design Emergency Procedures SR22T EGT, TIT or CHT Temperature Sensor Failure......26 Propeller System Emergencies ............27 Engine Speed High ............... 27 Propeller Governor Failure............28 Fuel System Emergencies ............... 29 Low Fuel Quantity ................. 29 Electrical System Emergencies............30 High Voltage on Main Bus 1 ............
  • Page 57: 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 58: Original Issue

    Section 3 Cirrus Design Emergency Procedures SR22T Emergency Procedures Guidance Although this section provides procedures for handling most emergencies and critical flight situations that could arise in the aircraft, it is not a substitute for thorough knowledge of the airplane and general aviation techniques.
  • Page 59: 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 life-threatening emergency where CAPS deployment is determined to be safer than continued flight and landing. Refer to Section 10, Safety Information, for CAPS deployment information and landing considerations.
  • Page 60: Airspeeds For Emergency Operations

    Section 3 Cirrus Design Emergency Procedures SR22T Airspeeds for Emergency Operations Maneuvering Speed: 3400 lb ................133 KIAS Best Glide: All Weights .................88 KIAS Emergency Landing (Engine-out): Flaps Up................90 KIAS Flaps 50% ................85 KIAS Flaps 100% ................80 KIAS P/N 13772-003 Original Issue...
  • Page 61: Engine Failures

    Cirrus Design Section 3 SR22T Emergency Procedures 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 62: Engine Failure In Flight

    Section 3 Cirrus Design Emergency Procedures SR22T Engine Failure In Flight 1. Best Glide Speed ............ESTABLISH 2. Fuel Selector ............SWITCH TANKS 3. Ignition Switch ............CHECK, BOTH 4. Fuel Pump................. BOOST 5. Power Lever ..............½ OPEN 6. Mixture ...IDLE CUTOFF then slowly ADVANCE until engine starts If engine does not start: 7.
  • Page 63 Cirrus Design Section 3 SR22T Emergency Procedures 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 64: 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 65: Revision 1

    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 66: Original Issue

    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 67: Original Issue

    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 68: 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 69: Original Issue

    Cirrus Design Section 3 SR22T Emergency Procedures Emergency Descent Emergency Descent 1. Power Lever ................IDLE 2. Mixture ..............AS REQUIRED 3. Airspeed..............V (200 KIAS) Amplification • Caution • If significant turbulence is expected do not descend at indicated airspeeds greater than V...
  • Page 70: Original Issue

    Section 3 Cirrus Design Emergency Procedures SR22T Forced Landings Emergency Landing Without Engine Power 1. Best Glide Speed ............ESTABLISH 2. Radio..........Transmit (121.5 MHz) MAYDAY giving location and intentions 3. Transponder ............SQUAWK 7700 4. If off airport, ELT ............ACTIVATE 5.
  • Page 71: 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 72: Engine System Emergencies

    Section 3 Cirrus Design Emergency Procedures SR22T Engine System Emergencies Engine Partial Power Loss 1. Air Conditioner (if installed) ............OFF 2. Fuel Pump............ HIGH BOOST/PRIME 3. Fuel Selector ............SWITCH TANKS 4. Mixture ......CHECK appropriate for flight conditions 5. Power Lever ............... SWEEP 6.
  • Page 73: 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 74: 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 75: Original Issue

    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 76: Original Issue

    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 77: 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 78: 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. Complete Overboost / Pressure Relief Valve checklist...
  • Page 79: Original Issue

    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 80: Original Issue

    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 81: 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 82: Original Issue

    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 able 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 83: Original Issue

    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 84: Original Issue

    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 3.
  • Page 85: 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 86: 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 87: 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)............OFF 2. Temperature Selector............COLD 3. Vent Selector......FEET/PANEL/DEFROST POSITION 4. Airflow Selector .......SET AIRFLOW TO MAXIMUM 5.
  • Page 88: 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 89: 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 90: 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 91: Unusual Attitude Emergencies

    The aircraft is not approved for spins, and has not been tested or certified for spin recovery characteristics. The only approved and demonstrated method of spin recovery is activation of the Cirrus Airframe Parachute System (See CAPS Deployment, this section).
  • Page 92: Inadvertent Spiral Dive During Imc Flight

    Section 3 Cirrus Design Emergency Procedures SR22T Inadvertent Spiral Dive During IMC Flight 1. Power Lever ................IDLE 2. Stop the spiral dive by using coordinated aileron and rudder control while referring to the attitude indicator and turn coordinator to level the wings.
  • Page 93: 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 94: 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 - Safety Information: Taxiing, Steering, and Braking...
  • Page 95: 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 96: Caps Deployment

    Section 3 Cirrus Design Emergency Procedures SR22T CAPS Deployment 1. Airspeed ............MINIMUM POSSIBLE The maximum demonstrated deployment speed is 133 KIAS. 2. Mixture (If time and altitude permit) ......... CUTOFF 3. Activation Handle Cover..........REMOVE 4. Activation Handle (Both Hands) ..... PULL STRAIGHT DOWN After Deployment: 5.
  • Page 97 Section 3 SR22T Emergency Procedures The Cirrus Airframe Parachute System (CAPS) should be activated in the event of a life-threatening emergency where CAPS deployment is determined to be safer than continued flight and landing. Expected impact in a fully stabilized deployment is equivalent to a drop from approximately 13 feet.
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  • Page 99: Revision 1

    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 100 Section 3A Cirrus Design Abnormal Procedures SR22T Flap System Exceedance ............. 18 Landing Gear System ..............19 Brake Failure During Taxi ............. 19 Left/Right Brake Over-Temperature..........19 Oxygen System ................20 Oxygen Quantity Low..............20 Other Conditions ................22 Aborted Takeoff ................22 Parking Brake Engaged Annunciation ..........
  • Page 101: 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 102: 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 103: 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 104: 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 105: 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 106: 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 107: 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 108: 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 fuel quantity indicates less than or equal to 14 gallons: a. Land as soon as practical.
  • Page 109: Electrical System

    Cirrus Design Section 3A SR22T Abnormal Procedures Electrical System Low Voltage on Main Bus 1 M BUS 1 Caution M BUS 1 1. Perform Alt 1 Caution (Failure) Checklist. Amplification Main Bus 1 Voltage is low, indicates Alt 1 failure; will typically be associated with low M1 voltage Alt 1 current indications, Battery 1 discharge and ALT 1 Caution message.
  • Page 110: Low Alternator 1 Output

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 111: Low Alternator 2 Output

    Cirrus Design Section 3A SR22T Abnormal Procedures Low Alternator 2 Output ALT 2 Caution (Failure) ALT 2 1. ALT 2 Circuit Breaker ..........CHECK & SET 2. ALT 2 Master Switch ............CYCLE If alternator does not reset (low A2 Current and M2 voltage less than M1 voltage): 3.
  • Page 112: Integrated Avionics System

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 1 FAN FAIL Advisory PFD 1 FAN FAIL 1.
  • Page 113: Flight Displays Too Dim

    Cirrus Design Section 3A SR22T Abnormal Procedures Flight Displays Too Dim 1. INSTRUMENT dimmer knob....OFF (full counter-clockwise) If flight displays do not provide sufficient brightness: 2. Revert to standby instruments. Amplification The instrument dimmer knob provides manual dimming control of the display screens, key and text backlighting, flap and Environmental Control System (ECS) status indicators, and standby instruments.
  • Page 114: Pitot Static System

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 115: Pitot Heat Current Sensor Annunciation

    Cirrus Design Section 3A SR22T Abnormal Procedures Pitot Heat Current Sensor Annunciation PITOT HEAT FAIL Caution PITOT HEAT FAIL 1. Pitot Heat Circuit Breaker ........... CYCLE 2. Pitot Heat ............. CYCLE OFF, ON If inadvertent icing encountered, perform Inadvertent Icing Encounter Emergency Checklist and: a.
  • Page 116: Flight Control System

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 117: Landing Gear System

    Cirrus Design Section 3A SR22T Abnormal Procedures Landing Gear System Brake Failure During Taxi 1. Engine Power............AS REQUIRED • To stop airplane - REDUCE • If necessary for steering - INCREASE 2. Directional Control ....... MAINTAIN WITH RUDDER 3. Brake Pedal(s) ..............PUMP If directional control can not be maintained: 4.
  • Page 118: Oxygen System

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 119 Cirrus Design Section 3A SR22T Abnormal Procedures OXYGEN QTY Advisory OXYGEN QTY On-Ground 1. Oxygen Supply ..REPLENISH if use of oxygen is anticipated In-Flight 1. If use of oxygen is anticipated, verify adequate oxygen supply for flight duration. Refer to Duration chart in Oxygen System AFMS.
  • Page 120: Other Conditions

    Section 3A Cirrus Design Abnormal Procedures SR22T 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 121: Parking Brake Engaged Annunciation

    Cirrus Design Section 3A SR22T Abnormal Procedures Parking Brake Engaged Annunciation PARK BRAKE Caution PARK BRAKE 1. Parking Brake ..............RELEASE 2. Monitor CAS for BRAKE TEMP Caution. Stop aircraft and allow the brakes to cool if necessary. Amplification Parking brake is set.
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  • Page 123 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 ..................
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  • Page 125: 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. Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3400 lb.
  • Page 126: 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 127 Cirrus Design Section 4 SR22T Normal Procedures 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 Oxygen System ..............ON...
  • Page 128 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 129 Cirrus Design Section 4 SR22T Normal Procedures 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. The brake linings must be inspected and O- rings replaced.
  • Page 130 Section 4 Cirrus Design Normal Procedures SR22T d. External Power .............Door Secure e. Vortex Generator ............Condition Exhaust Pipe(s) ....Condition, Security, and Clearance 11. Left Main Gear and Forward Wing a. Wheel fairings ....... Security, Accumulation of Debris b. Tire ..........Condition, Inflation, and Wear •...
  • Page 131: 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 132: 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 133 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 134: 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 135: Before Takeoff

    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 • Note • If Air Conditioner is ON for takeoff roll, see Section 5, Performance for takeoff distance change.
  • Page 136 Section 4 Cirrus Design Normal Procedures SR22T 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. Ignition Switch ......... R, note RPM, then BOTH b.
  • Page 137: Maximum Power Fuel Flow

    Cirrus Design Section 4 SR22T Normal Procedures Maximum Power Fuel Flow For maximum power operations (Power Lever full forward - 2500 RPM, 36.0 in.Hg manifold pressure) fuel flow should be in the green arc. For any power setting greater than 30.5 in.Hg (cruise power) fuel flow is indicated by a dynamically calculated green arc displayed on the fuel gage.
  • Page 138: 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 70-73 KIAS 5. At 80 KIAS, Flaps............... UP Short Field Takeoff 1.
  • Page 139 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 140: 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 141 Cirrus Design Section 4 SR22T Normal Procedures 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; • Rising EGTs and TIT coupled with falling fuel flow •...
  • Page 142: Cruise Climb: Lean Of Peak Technique

    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 143: 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 144: 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 145: 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 146: Short Field Landing

    Section 4 Cirrus Design Normal Procedures SR22T Short Field Landing 1. Flaps ..................100% 2. Airspeed ................77 KIAS 3. Power Lever ............AS REQUIRED After clear of obstacles: 4. Power Lever ............REDUCE TO IDLE After touchdown: 5. Brakes ................MAXIMUM Amplification...
  • Page 147: Balked Landing/Go-Around

    Cirrus Design Section 4 SR22T Normal Procedures Balked Landing/Go-Around 1. Autopilot ..............DISENGAGE 2. Power Lever ............FULL FORWARD 3. Flaps ..................50% 4. Airspeed................75-80 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 148: 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 149: 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 speeds at maximum weight for both forward and aft CG positions are presented in Section 5 - Performance Data.
  • Page 150: 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 151: Hot Weather Operation

    Cirrus Design Section 4 SR22T Normal Procedures 2. Propeller .......... Hand TURN several rotations 3. External Power (If applicable) ........CONNECT 4. Brakes .................. HOLD 5. Bat Master Switches ........ON (check voltage) 6. Mixture ................. FULL RICH 7. Power lever ............FULL FORWARD 8.
  • Page 152: Noise Characteristics/Abatement

    Section 4 Cirrus Design Normal Procedures SR22T Ground Operation of Air Conditioning (If Installed) • Note • To facilitate faster cabin cooling, prior to engine start leave the cabin doors open for a short time to allow hot air to escape cabin.
  • Page 153: Fuel Conservation

    Cirrus Design Section 4 SR22T Normal Procedures above the surface even though flight at a lower level may be allowed. 2. For departure from or approach to an airport, avoid prolonged flight at low altitude near noise-sensitive areas. Fuel Conservation Minimum fuel use at cruise will be achieved using Lean-of-Peak Cruise Climb.
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  • Page 155 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 Normal Static Source: Primary Flight Display ........
  • Page 156 Section 5 Cirrus Design Performance Data SR22T Intentionally Left Blank P/N 13772-003 Original Issue...
  • Page 157: 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 158: 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 159: 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 160: 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. • 3400 LB • Note • Add correction to desired altitude to obtain indicated altitude to fly.
  • Page 161: 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. • 3400 LB • Note • Add correction to desired altitude to obtain indicated altitude to fly.
  • Page 162 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 163 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 164: 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 165: 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 166: Stall Speeds

    Section 5 Cirrus Design Performance Data SR22T Stall Speeds Conditions: • Weight ......................3400 LB • CG ........................Noted • Power......................... Idle • Bank Angle .....................Noted • Note • Altitude loss during wings level stall may be 250 feet or more.
  • Page 167: 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 20 knots. Value not considered limiting. 0° 10° 20°...
  • Page 168: 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 169 Cirrus Design Section 5 SR22T Performance Data Takeoff Distance: 3400 LB Weight: 3400 LB Headwind: Subtract 10% for each 12 knots headwind. Approx. Speed at Liftoff: 72 KIAS Tailwind: Add 10% for each 2 knots Speed over 50 Ft. Obstacle: 78 KIAS tailwind up to 10 knots.
  • Page 170 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 Speed over 50 Ft. Obstacle: 72 KIAS tailwind up to 10 knots.
  • Page 171: 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 172: 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 173: 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 174: 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 175: 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 ......................3400 LB • Winds ....................... Zero • Climb Airspeed..................120 KIAS •...
  • Page 176: 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 ......................3400 LB • Winds........................ Zero • Climb Airspeed ..................120 KIAS •...
  • Page 177: Cruise Performance

    Cirrus Design Section 5 SR22T Performance Data Cruise Performance Conditions: • Weight ......................3200 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 178 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 10.1 10.5 10.8 16.4 10.7 11.1 11.5 14.6 11.4...
  • Page 179: 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 ..........3400 LB for Climb, Avg 3200 LB for Cruise • Winds ....................... Zero •...
  • Page 180 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 78.6 16.4 4000 77.6 16.4 10.1...
  • Page 181 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 4000 77.6 12.7 11.5 6000 76.6 12.7...
  • Page 182: 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 ..........3400 LB for Climb, Avg 3200 LB for Cruise • Winds........................ Zero • Total Fuel ....................92 Gallons •...
  • Page 183 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 78.3 16.4 10.1 6000 77.7...
  • Page 184 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 11.3 4000 78.3 12.7 11.5...
  • Page 185: 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................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 186: 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 ................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude in ft per unit time...
  • Page 187: 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 188 Section 5 Cirrus Design Performance Data SR22T Landing Distance WEIGHT: 3400 LB Headwind: Subtract 10% for each 13 Speed over 50 Ft Obstacle: 77 KIAS knots headwind. Flaps: 100% Tailwind: Add 10% for each 2 knots Power: Idle tailwind up to 10 knots.
  • Page 189 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 190 Section 6 Cirrus Design Weight and Balance Data SR22T Intentionally Left Blank P/N 13772-003 Original Issue...
  • Page 191: 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 192: 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 193: 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 194 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 195 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 13772-003 Original Issue...
  • Page 196: 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 197: 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 3400 lb. The Takeoff Condition Moment must be within the Minimum Moment to Maximum Moment range at the Takeoff Condition Weight.
  • Page 198: 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 Fwd Pass Aft Pass Loading Chart Baggage 20.0 40.0...
  • Page 199: Moment Limits

    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. 3400 3200 3000...
  • Page 200: 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 201: 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 13772-003 6-13 Original Issue...
  • Page 202 Section 6 Cirrus Design Weight and Balance Data SR22T Intentionally Left Blank 6-14 P/N 13772-003 Original Issue...
  • Page 203 Cirrus Design Section 7 SR22T Airplane and Systems Description Section 7 Airplane and 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 ................
  • Page 204 Section 7 Cirrus Design Airplane and Systems Description SR22T Ignition and Starter System............35 Air Induction System ..............36 Engine Exhaust System..............36 Engine Fuel Injection ..............36 Engine Cooling................37 Propeller ................... 38 Fuel System ..................39 Fuel Selector Valve............... 40 Fuel Pump Operation..............
  • Page 205 Cirrus Design Section 7 SR22T Airplane and Systems Description Cirrus Airplane Parachute System ........... 88 System Description ............... 88 Activation Handle ................89 Deployment Characteristics ............91 P/N 13772-003 Revision 1...
  • Page 206 Section 7 Cirrus Design Airplane and Systems Description SR22T Intentionally Left Blank P/N 13772-003 Revision 1...
  • Page 207: Introduction

    Cirrus Design Section 7 SR22T Airplane and 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 208: Airframe

    Section 7 Cirrus Design Airplane and 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 209: Empennage

    Cirrus Design Section 7 SR22T Airplane and 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.
  • Page 210: Flight Controls

    Section 7 Cirrus Design Airplane and 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.
  • Page 211 Cirrus Design Section 7 SR22T Airplane and Systems Description SR22_FM07_1461 Figure 7-1 Elevator System P/N 13772-003 Original Issue...
  • Page 212: Aileron System

    Section 7 Cirrus Design Airplane and 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 213 Cirrus Design Section 7 SR22T Airplane and Systems Description SR22_FM07_1462 Figure 7-2 Aileron System P/N 13772-003 7-11 Original Issue...
  • Page 214: Rudder System

    Section 7 Cirrus Design Airplane and 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 215 Cirrus Design Section 7 SR22T Airplane and Systems Description SR22_FM07_1463 Figure 7-3 Rudder System P/N 13772-003 7-13 Original Issue...
  • Page 216: Instrument Panel

    Section 7 Cirrus Design Airplane and 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 217: Cirrus Airframe Parachute System (Caps)

    Cirrus Design Section 7 SR22T Airplane and 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 218: Flight Instruments

    Section 7 Cirrus Design Airplane and 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”...
  • Page 219 Cirrus Design Section 7 SR22T Airplane and 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 220: Attitude Indicator

    Section 7 Cirrus Design Airplane and 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).
  • Page 221: Airspeed Indicator

    Cirrus Design Section 7 SR22T Airplane and 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 222: Altimeter

    Section 7 Cirrus Design Airplane and 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 223: Horizontal Situation Indicator

    Cirrus Design Section 7 SR22T Airplane and 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 224: Magnetic Compass

    Section 7 Cirrus Design Airplane and 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 225 Cirrus Design Section 7 SR22T Airplane and Systems Description SR22_FM07_2935A Figure 7-6 Wing Flaps P/N 13772-003 7-23 Original Issue...
  • Page 226: Landing Gear

    Section 7 Cirrus Design Airplane and 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 227 Cirrus Design Section 7 SR22T Airplane and 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.
  • Page 228: Baggage Compartment

    Section 7 Cirrus Design Airplane and Systems Description SR22T Baggage Compartment The baggage compartment door, located on the left side of the fuselage aft of the wing, allows entry to the baggage compartment. The baggage door is hinged on the forward edge and latched on the rear edge.
  • Page 229: Seats

    Cirrus Design Section 7 SR22T Airplane and Systems Description Seats The seating arrangement consists of two individually adjustable seats for the pilot and front seat passenger and two individual seats with fold down seat backs for the rear seat passengers.The front seats are adjustable fore and aft and the seat backs can be reclined for passenger comfort or folded forward for rear seat access.
  • Page 230: Seat Belt And Shoulder Harness

    Section 7 Cirrus Design Airplane and Systems Description SR22T Seat Belt and Shoulder Harness Integrated seat belt and shoulder harness assemblies with inertia reels are provided for the pilot and each passenger. The rear seat belts are attached to fittings on the floorboard and the forward seat belts are attached to the seat frame.
  • Page 231: Cabin Doors

    Cirrus Design Section 7 SR22T Airplane and Systems Description 4. Restraint harnesses should fit snug against the shoulder with the lap buckle centered and tightened around the hips. To release the restraints: 1. Grasp the top of the buckle opposite the link and pull outward. The link will slip free of buckle.
  • Page 232: Engine

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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.
  • Page 233 Cirrus Design Section 7 SR22T Airplane and Systems Description 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. Power Lever 9. Friction Control 10. Mixture Control...
  • Page 234: Engine Indicating

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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 235 Cirrus Design Section 7 SR22T Airplane and Systems Description 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 236 Section 7 Cirrus Design Airplane and Systems Description SR22T 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 237: Engine Lubrication System

    Cirrus Design Section 7 SR22T Airplane and Systems Description 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 238: Air Induction System

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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 239: Engine Cooling

    Cirrus Design Section 7 SR22T Airplane and Systems Description 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 240: Propeller

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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 241: Fuel System

    Cirrus Design Section 7 SR22T Airplane and Systems Description Fuel System An 92-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 47.25-gallon capacity (46- gallon usable) vented integral fuel tank and a fuel collector/sump in each wing, a three position selector valve, an electric fuel pump, and an engine-driven fuel pump.
  • Page 242: Fuel Selector Valve

    Section 7 Cirrus Design Airplane and Systems Description SR22T contamination and grade. The fuel must be sampled prior to each flight. A sampler cup is provided to drain a small amount of fuel from the wing tank drains, the collector tank drains, and the gascolator drain.
  • Page 243 Cirrus Design Section 7 SR22T Airplane and Systems Description ANNUNCIATOR FUEL FUEL QUANTITY VENT VENT FILLER FILLER INDICATOR L. WING TANK R. WING TANK L. WING R. WING COLLECTOR COLLECTOR SELECTOR VALVE FLAPPER FLAPPER VALVE VALVE DRAIN (5 PLACES) FIREWALL...
  • Page 244: Fuel Indicating

    Section 7 Cirrus Design Airplane and Systems Description SR22T Fuel Indicating Fuel system information is displayed as analog-style gages 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), fuel flow is displayed along the LH edge of the display.
  • Page 245 Cirrus Design Section 7 SR22T Airplane and Systems Description 4 5 6 7 Fuel System Indication LEGEND 1. Fuel Flow 2. Fuel At Destination (Totalizer) 3. Fuel Used (Totalizer) 4. Fuel Remaining (Totalizer) 5. Time Remaining (Totalizer) 6. Fuel Range (Totalizer) 7.
  • Page 246 Section 7 Cirrus Design Airplane and Systems Description SR22T Fuel Quantity Gage A dual reading 2¼” fuel quantity gage is installed on the console immediately forward of the fuel selector valve. The LEFT pointer indicates left tank fuel quantity and sweeps a scale marked from 0 to 46 U.S.
  • Page 247 Cirrus Design Section 7 SR22T Airplane and Systems Description The gage displays a green normal arc, which is dynamically updated to display the range of normal values appropriate to engine power settings. • When manifold pressures is above 30.6 in.Hg, the green arc covers a narrow range depicting the full rich fuel flow appropriate for that power setting.
  • Page 248: Electrical System

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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 249 Cirrus Design Section 7 SR22T Airplane and Systems Description 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...
  • Page 250: Power Distribution

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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 251: Electrical System Protection

    Cirrus Design Section 7 SR22T Airplane and Systems Description Main Distribution Bus 2 The output from ALT 2 is connected to the Main Distribution Bus 2 in the MCU through an 80-amp fuse. Main Distribution Bus 2 powers three circuit breaker buses through 30-amp fuses located in the MCU;...
  • Page 252 Section 7 Cirrus Design Airplane and Systems Description SR22T 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 253 Cirrus Design Section 7 SR22T Airplane and Systems Description AVIONICS A/C COND PROTECTION STDBY ALT1 ALT2 ATTD #2 ENGINE MFD #2 SERVO INSTR STALL CABIN LIGHTS CAMERA WARNING / OXYGEN 12V DC ROLL FUEL QTY OUTLET TRIM PITCH A/C COMPR...
  • Page 254: Electrical System Control

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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 255: Ground Service Receptacle

    Cirrus Design Section 7 SR22T Airplane and Systems Description 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 256: Electrical Indicating

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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 257 Cirrus Design Section 7 SR22T Airplane and Systems Description Electrical System Indication 8 9 10 Electrical and Lighting Controls LEGEND 1. Essential & Main Bus Voltage 7. Avionics 8. Navigation 2. Alternator & Battery Current 9. Strobe 3. Battery 2 10.
  • Page 258: Lighting Systems

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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.
  • Page 259: Interior Lighting

    Cirrus Design Section 7 SR22T Airplane and Systems Description 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 260 Section 7 Cirrus Design Airplane and Systems Description SR22T 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 261: Environmental System

    Cirrus Design Section 7 SR22T Airplane and Systems Description Environmental System • Note • To facilitate faster cabin cooling, prior to engine start leave the cabin doors open for a short time to allow hot air to escape. Standard cabin heating and ventilation is accomplished by supplying conditioned air from the heat exchanger for heating and windshield defrost and fresh outside air for ventilation.
  • Page 262: Heating

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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 263: Cooling

    Cirrus Design Section 7 SR22T Airplane and Systems Description 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.
  • Page 264 Section 7 Cirrus Design Airplane and Systems Description SR22T 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...
  • Page 265 Cirrus Design Section 7 SR22T Airplane and Systems Description 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...
  • Page 266: Airflow Selection

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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 267: Temperature Selection

    Cirrus Design Section 7 SR22T Airplane and Systems Description 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 268 Section 7 Cirrus Design Airplane and Systems Description SR22T 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 269: Stall Warning System

    Cirrus Design Section 7 SR22T Airplane and Systems Description Stall Warning System The airplane is equipped with an electro-pneumatic stall warning system to provide audible warning of an approach to aerodynamic stall. The system consists of an inlet in the leading edge of the right wing, a pressure switch and associated plumbing, and the avionics system aural warning system.
  • Page 270: Pitot-Static System

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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 271 Cirrus Design Section 7 SR22T Airplane and Systems Description 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 272: Avionics

    Section 7 Cirrus Design Airplane and Systems Description SR22T 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 273 Cirrus Design Section 7 SR22T Airplane and Systems Description XM RADIO RECEIVER (optional) SATELLITE DATA LINK RECEIVER (optional) FMS KEYBOARD MAG 2 MAG 1 AHRS 1 AUTOPILOT MODE CONTROLLER (optional) AHRS 2 (optional) AIR DATA COMPUTER AIR DATA COMPUTER 2...
  • Page 274 Section 7 Cirrus Design Airplane and Systems Description SR22T 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 275 Cirrus Design Section 7 SR22T Airplane and Systems Description 3 and the 5-amp MFD 2 circuit breaker on MAIN BUS 1. Either circuit is capable of powering the MFD. System start-up is automatic once power is applied. Power-on default brightness is determined by ambient lighting and is user adjustable.
  • Page 276 Section 7 Cirrus Design Airplane and Systems Description SR22T 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.
  • Page 277 Cirrus Design Section 7 SR22T Airplane and Systems Description 22 23 25 26 27 28 29 30 31 GARMIN IDENT FMS/XPDR RANGE MENU XPDR COM/NAV PROC DFLT MAP PUSH SYNC PUSH PUSH EMERG CRSR/1-2 PUSH CTR ALT SEL BKSP PUSH SYNC...
  • Page 278 Section 7 Cirrus Design Airplane and Systems Description SR22T 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 279 Cirrus Design Section 7 SR22T Airplane and Systems Description GMA 347 Audio Panel with Integrated Marker Beacon Receiver The 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 280: Optional Avionics

    Section 7 Cirrus Design Airplane and Systems Description SR22T Optional Avionics GFC 700 3-Axis Autopilot and GMC 705 Autopilot Controller Refer to Section 9, Supplements for GFC 700 3-Axis Autopilot operating information. 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.
  • Page 281 Cirrus Design Section 7 SR22T Airplane and Systems Description Traffic Advisory System The Traffic Advisory System (TAS) advises the pilot of transponder- equipped airplane that may pose a collision threat. TAS information is displayed on the MFD and indicates the relative range, bearing, and altitude of intruder airplane.
  • Page 282 Section 7 Cirrus Design Airplane and Systems Description SR22T 28 VDC for ADF System operation is supplied through the 3-amp 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.
  • Page 283 Cirrus Design Section 7 SR22T Airplane and Systems Description • Terrain warning system, • Field of view depiction on the MFD Navigation Page. Refer to the Perspective Integrated Avionics System Pilot’s Guide for a complete description of the system, its operating modes, and additional detailed operating procedures.
  • Page 284 Section 7 Cirrus Design Airplane and 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.
  • Page 285: Avionics Support Equipment

    Cirrus Design Section 7 SR22T Airplane and 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 286 Section 7 Cirrus Design Airplane and Systems Description SR22T Headset and Microphone Installation The airplane is equipped with provisions for four noise-canceling headsets with integrated microphones. forward microphone-headsets use remote Push-To-Talk (PTT) switches located on the top of the associated control yoke grip. The rear headsets do not have COM transmit capabilities and do not require PTT switches.
  • Page 287: Cabin Features

    Cirrus Design Section 7 SR22T Airplane and Systems Description Cabin Features Emergency Locator Transmitter The airplane is equipped with a self-contained emergency locator transmitter (ELT). The transmitter and antenna are installed immediately behind the aft cabin bulkhead, slightly to the right of the airplane centerline.
  • Page 288: Fire Extinguisher

    Section 7 Cirrus Design Airplane and Systems Description SR22T b. Disconnect fixed antenna lead from front of unit. c. Disconnect lead from remote switch and indicator unit. d. Loosen attach straps and remove transmitter unit and portable antenna. e. Attach portable antenna to antenna jack on front of unit.
  • Page 289: Hour Meters

    Cirrus Design Section 7 SR22T Airplane and Systems Description 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 290: Cirrus Airplane Parachute System

    Airplane and Systems Description SR22T 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 291: Activation Handle

    Cirrus Design Section 7 SR22T Airplane and Systems Description rate at which the parachute inflates. As the slider moves down the suspension lines the canopy inflates. 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.
  • Page 292 Section 7 Cirrus Design Airplane and Systems Description SR22T Pulling the activation T-handle straight down generates the greatest force. A maintenance safety pin is provided to ensure that the activation handle is not pulled during maintenance. However, there may be some circumstances where an operator may wish to safety the CAPS system;...
  • Page 293: Deployment Characteristics

    Cirrus Design Section 7 SR22T Airplane and Systems Description Deployment Characteristics When the rocket launches, the parachute assembly is extracted outward due to rocket thrust and rearward due to relative wind. In approximately two seconds the parachute will begin to inflate.
  • Page 294 Section 7 Cirrus Design Airplane and Systems Description SR22T Intentionally Left Blank 7-92 P/N 13772-003 Revision 1...
  • Page 295 Airworthiness Directives..............6 Airplane Inspection Periods ............... 6 Annual Inspection ................6 100-Hour Inspection ............... 7 Cirrus Design Progressive Inspection Program ......7 Pilot Performed Preventative Maintenance ........8 Ground Handling ................10 Application of External Power ............10 Towing ..................11 Taxiing ..................
  • Page 296 Section 8 Cirrus Design Handling, Servicing, & Maintenance SR22T Intentionally Left Blank P/N 13772-003 Original Issue...
  • Page 297: 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 298: 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 299: Airplane Records And Certificates

    Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance Airplane Records and Certificates The Federal Aviation Administration (FAA) requires that certain data, certificates, and licenses be displayed or carried aboard the airplane at all times. Additionally, other documents must be made available upon request.
  • Page 300: Airworthiness Directives

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

    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. A total of eight inspections are accomplished over the course of 400 flight hours, with an inspection occurring every 50 flight hours.
  • Page 302: Pilot Performed Preventative Maintenance

    Section 8 Cirrus Design Handling, Servicing, and Maintenance 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 303 Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance • Replace any hose connection, except hydraulic connections, with replacement hoses. • Clean or replace fuel and oil strainers, as well as replace or clean filter elements. • Replace prefabricated fuel lines.
  • Page 304: Ground Handling

    Section 8 Cirrus Design Handling, Servicing, and Maintenance 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 305: Towing

    Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed in the rear baggage compartment or by power equipment that will not damage or excessively strain the nose gear assembly.
  • Page 306: Taxiing

    Section 8 Cirrus Design Handling, Servicing, and Maintenance 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 307: Parking

    Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance Parking The airplane should be parked to protect the airplane from weather and to prevent it from becoming a hazard to other aircraft. The parking brake may release or exert excessive pressure because of heat buildup after heavy braking or during wide temperature swings.
  • Page 308: Tiedown

    Section 8 Cirrus Design Handling, Servicing, and Maintenance 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 309 Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance 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 310: Servicing

    Section 8 Cirrus Design Handling, Servicing, and Maintenance 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 four- ply rating, type III tire and tube.
  • Page 311 Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance 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 312: Tire Inflation

    Section 8 Cirrus Design Handling, Servicing, and Maintenance 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 313 Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance 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 314 Section 8 Cirrus Design Handling, Servicing, and Maintenance 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...
  • Page 315: Fuel System Servicing

    Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance 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 316 Section 8 Cirrus Design Handling, Servicing, and Maintenance 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 317: Battery Service

    Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance 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 318: 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 319: Cleaning And Care

    Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance Cleaning and Care Cleaning Exterior Surfaces • Caution • Airplane serials with Ice Protection System; Do not wax leading edge porous panels. Refer to Section 9, Supplements for specific servicing information on the Ice Protection System.
  • Page 320 Section 8 Cirrus Design Handling, Servicing, and Maintenance 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...
  • Page 321 Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance 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 322 Section 8 Cirrus Design Handling, Servicing, and Maintenance 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 323 Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance 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 324: Cleaning Interior Surfaces

    Section 8 Cirrus Design Handling, Servicing, and Maintenance 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 325 Cirrus Design Section 8 SR22T Handling, Servicing, and Maintenance 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 326 Section 8 Cirrus Design Handling, Servicing, and Maintenance 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 327 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 328 Section 8 Cirrus Design Handling, Servicing, and Maintenance SR22T Intentionally Left Blank 8-34 P/N 13772-003 Original Issue...
  • Page 329 Cirrus Design Supplements produced for this airplane. The Log of Supplements page can be utilized as a “Table of Contents” for this section. In the event the airplane is modified at a non Cirrus Design facility through an STC or other approval method, it is the...
  • Page 330 Section 9 Cirrus Design Supplements SR22T Intentionally Left Blank P/N 13772-003 Original Issue...
  • Page 331 Cirrus Design Section Section 9 SR22T Log of Supplements Section Section 9 Log of Supplements Part Number Title Date ___ 13772-109 R2 Approved Oxygen Systems 01-06-10 ___ 13772-114 R1 SR22 / SR22T Airplanes Registered in Canada 07-07-10 ___ 13772-115 R9 Basic Ice Protection System...
  • Page 332 This Log of Supplements shows all Cirrus Design Supplements available for the aircraft at the corresponding date of the revision level shown in the lower left corner. A mark (x) in the Part Number column indicates that the supplement is installed in the POH.
  • Page 333 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement Approved Oxygen Systems When supplemental oxygen is required by the applicable operating rules (FAR Part 91 or FAR Part 135), this Supplement is applicable and must be inserted in the Supplements Section of the Pilot’s...
  • Page 334 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General This supplement lists the approved portable oxygen systems that may be used in the aircraft when supplemental oxygen is required by the applicable operating rules, as well as provides mounting instructions and general operating procedures for all approved systems.
  • Page 335 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3 - Emergency Procedures Smoke and Fume Elimination In addition to the procedures outlined in the basic Handbook, pilot and passengers should don cannulas or masks and use oxygen at the maximum flow rate until smoke and fumes have cleared.
  • Page 336 Section 9 Cirrus Design Supplements SR22 / SR22T Descent After airplane descends through altitude requiring oxygen: 1. Oxygen Shutoff Valve...............OFF 2. Pilot and passengers ......Stow Masks or Cannulas Section 5 - Performance No change from basic Handbook. Section 6 - Weight & Balance The weight, arm, and moment for fully charged systems (1800 –...
  • Page 337 Cirrus Design Section 9 SR22 / SR22T Supplements INITIAL INSTALLATION Clip strap to triangular loop as shown in Detail A. Route strap over headrest, down TUFF PACK BAG the back of the seat, and forward between the cushion and seat back. Clip strap to lower triangular loop.
  • Page 338 Section 9 Cirrus Design Supplements SR22 / SR22T OXYGEN DURATION - HOURS Fully Charged System (1800 psig at 70° F) Number of Altitude ~ Feet System Persons Typical Using O 10,000 15,000 18,000 25,000 (Liters) 2.23 1.49 1.24 0.89 XCP-180 1.12...
  • Page 339 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the Basic Ice Protection System When the Basic Ice Protection 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 340 Section 9 Cirrus Design Supplements SR22 / SR22T Section 1 - General The airplane is equipped with an Ice Protection System. This system allows a pilot who inadvertently enters icing conditions, to initiate de- icing fluid flow along the wing, horizontal stabilizer, and propeller blades.
  • Page 341 Cirrus Design Section 9 SR22 / SR22T Supplements Placards Serials 22-0334 thru 22-2333, 22-2335 thru 22-2419, 22-2421 thru 22-2437; LH Fuselage, above de-icing fluid filler cap: Serials 22-2334, 22-2420, 22-2438 & subs, 22T-0001 & subs; Left wing, above de-icing fluid filler cap:...
  • Page 342 Section 9 Cirrus Design Supplements SR22 / SR22T Section 3 - Emergency Procedures Inadvertent Icing Encounter • WARNING • The Ice Protection System may not remove significant accumulations of ice if accretions are permitted to form with the system off. Ensure system start time and system mode is noted while exiting icing conditions to aid in estimating ice protection fluid quantity.
  • Page 343 SR22 / SR22T Supplements Section 3A - Abnormal Procedures The following Crew Alerting System (CAS) annuciations are available only on aircraft equipped with the Cirrus Perspective Integrated Avionics System. Ice Protection System CAS Annunciation Low Fluid Quantity Warning, Caution, and Advisory ANTI ICE QTY PFD Alerts Window: “Fluid quantity is low (TKS)”...
  • Page 344 Section 9 Cirrus Design Supplements SR22 / SR22T Section 4 - Normal Procedures • Caution • Prolonged operation of the system in clear air, at very high altitudes, and very cold temperatures can result in “flash” evaporation of water and alcohol from the de-icing fluid. This evaporation results in a glycol rich fluid that could become “gel”...
  • Page 345 Cirrus Design Section 9 SR22 / SR22T Supplements a. Slinger Ring......EVIDENCE OF DEICING FLUID 5. Left Wing Forward and Main Gear a. Serials with G3 Wing; (1) Fluid Tank......VERIFY DESIRED QUANTITY (a) Filler Cap ......CONDITION / SECURITY (b)Vent (underside of wing)UNOBSTRUCTED b.
  • Page 346 Section 9 Cirrus Design Supplements SR22 / SR22T Section 5 - Performance Cruise speed is lower by approximately three knots and range is reduced by a maximum of 2%. Experience with your airplane’s power settings may result in more accurate performance numbers than those given above.
  • Page 347 Cirrus Design Section 9 SR22 / SR22T Supplements Section 6 - Weight & Balance Refer to Section 6 - Weight and Balance 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 348 Section 9 Cirrus Design Supplements SR22 / SR22T Loading Data - Serials with G3 Wing Mom/ Mom/ Weight 1000@ Weight 1000@ Gallons Gallons Fluid Tank Fluid Tank (FS148.0) (FS148.0) 0.14 27.6 4.08 0.27 28.5 4.22 0.41 29.4 4.36 0.54 30.4 4.49...
  • Page 349 Cirrus Design Section 9 SR22 / SR22T Supplements Section 7 - System Description The Ice Protection System can prevent, and in certain conditions, remove ice accumulation on the flight surfaces by distributing a thin film of glycol-based fluid on the wing, horizontal stabilizer, and propeller.
  • Page 350 Section 9 Cirrus Design Supplements SR22 / SR22T SLINGER RING POROUS PANELS POROUS PANELS PROPORTIONING PROPORTIONING PROPORTIONING UNIT UNIT UNIT VENT FILTER FITTING FINGER STRAINER FLUID TANK METERING PUMP PROPORTIONING UNIT POROUS PANEL VENT DRAIN POROUS PANEL SR22_FM09_1527 Figure - 2...
  • Page 351: Porous Panels

    Cirrus Design Section 9 SR22 / SR22T Supplements • A cabin floor-forward proportioning unit distributes fluid to the propeller slinger ring assembly. In addition to distributing fluid to the porous panels and propeller slinger ring, the proportioning units provide an additional, distinct pressure drop to the supply lines such that a specific flow rate is provided to each protected surface.
  • Page 352 Section 9 Cirrus Design Supplements SR22 / SR22T Ice Protection System - Serials with G3 Wing The system consists of six porous panels, propeller slinger ring, two proportioning units, metering pump, priming pump, filter, in-line strainer, fluid tank, filler cap and neck, test port assembly, electrical switching, system plumbing, and (Serials w/ Perspective Avionics) deicing fluid level sensor.
  • Page 353 Cirrus Design Section 9 SR22 / SR22T Supplements POROUS POROUS SLINGER FILLER FLUID PANELS PANELS RING NECK TANK VENT OUTLET STRAINER DRAIN VALVE PROPORTIONING TEST UNIT PORT STRAINER TUBE CHECK VALVE PRIMING PROPORTIONING PUMP UNIT FILTER METERING PUMP POROUS PANELS...
  • Page 354 Section 9 Cirrus Design Supplements SR22 / SR22T • The empennage proportioning unit distributes fluid to the LH and RH horizontal panels. In addition to distributing fluid to the porous panels and propeller slinger ring, the proportioning units provide an additional, distinct pressure drop to the supply lines such that a specific flow rate is provided to each protected surface.
  • Page 355 Cirrus Design Section 9 SR22 / SR22T Supplements Fluid Quantity Sensing Serials w/ Perspective Avionics: Fluid quantity is measured by a float type quantity sensor installed in the deicing fluid tank. System Indicating Serials w/ Perspective Avionics: System Indicating is displayed as a dial gauge and text in the lower left corner of the MFD ENGINE page.
  • Page 356 Section 9 Cirrus Design Supplements SR22 / 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 357 Cirrus Design Section 9 SR22 / SR22T Supplements Metering Pump Priming - Serials before G3 Wing If air enters the system due to the fluid tank running dry during system operation, the metering pump may not be capable of priming itself. To...
  • Page 358 Section 9 Cirrus Design Supplements SR22 / SR22T Section 10 – Safety Information The Ice Protection System is not intended to remove ice from the aircraft on the ground. Do not attempt to take off with frost, ice, or snow on flying surfaces.
  • 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 TKS Anti-Ice System • Approved for Flight Into Known Icing (FIKI) • 8.0 gallon usable capacity. • 4.0 gallon tank in each wing.
  • Page 368 Section 9 Cirrus Design Supplements SR22 / 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 369 Cirrus Design Section 9 SR22 / 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.
  • Page 370 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 371 Cirrus Design Section 9 SR22 / 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 372: 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 373 Cirrus Design Section 9 SR22 / 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 374 Section 9 Cirrus Design Supplements SR22 / 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 375 Cirrus Design Section 9 SR22 / 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 376 Section 9 Cirrus Design Supplements SR22 / SR22T Maximum Glide with Ice Accumulation Conditions Example: Power Altitude 10,000 ft. AGL Propeller Windmilling Airspeed 88 KIAS Flaps 0% (UP) Glide Distance 12.7 NM Wind Zero Best Glide Speed 88 KIAS at 3400 lb Maximum Glide Ratio ~ 7.7: 1...
  • Page 377 Cirrus Design Section 9 SR22 / 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 378 Section 9 Cirrus Design Supplements SR22 / 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 379 Cirrus Design Section 9 SR22 / 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 380 Section 9 Cirrus Design Supplements SR22 / 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.
  • Page 381 Cirrus Design Section 9 SR22 / 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...
  • Page 382 Section 9 Cirrus Design Supplements SR22 / 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 383 Cirrus Design Section 9 SR22 / 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”...
  • Page 384 Section 9 Cirrus Design Supplements SR22 / 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 385 Cirrus Design Section 9 SR22 / 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 386 Section 9 Cirrus Design Supplements SR22 / 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 387 Cirrus Design Section 9 SR22 / 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.
  • Page 388 Section 9 Cirrus Design Supplements SR22 / 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 389 Cirrus Design Section 9 SR22 / 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 390: Approach And Landing

    Section 9 Cirrus Design Supplements SR22 / 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 391 Cirrus Design Section 9 SR22 / 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 392 Section 9 Cirrus Design Supplements SR22 / SR22T Section 5 - Performance Airplane performance and stall speeds without ice accumulation are essentially unchanged with the installation of the Ice Protection System. Serials SR22T-0001 and subsequent: Performance of the airplane with the Teledyne Continental TSIO-550-K turbocharged engine installed is equal to or better than the performance described in the following section.
  • Page 393 Cirrus Design Section 9 SR22 / SR22T Supplements Enroute Climb Gradient with Ice Accumulation Conditions: • Power ....................Full Throttle • Mixture ....................Set Per Placard • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
  • Page 394 Section 9 Cirrus Design Supplements SR22 / SR22T Enroute Rate of Climb with Ice Accumulation Conditions: • Power....................Full Throttle • Mixture....................As Required • Flaps......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude in feet per unit time expressed in Feet per Minute.
  • Page 395 Cirrus Design Section 9 SR22 / SR22T Supplements Cruise Performance with Ice Accumulation Conditions: • Cruise Weight..................... 2900 LB • Winds ....................... Zero • Note • Aircraft with optional Air Conditioning System - Cruise performance is reduced by 2 knots. For maximum performance, the air-conditioner should be off.
  • Page 396 Section 9 Cirrus Design Supplements SR22 / SR22T Cruise Performance (Continued) 6000 Feet Pressure Altitude ISA -30°C (-27°C) ISA (3°C) ISA + 30°C (33°C) KTAS PWR KTAS PWR KTAS 2700 23.5 21.2 20.1 2600 23.5 20.3 19.2 2500 23.5 19.1 18.1...
  • Page 397 Cirrus Design Section 9 SR22 / SR22T Supplements Range / Endurance Profile with Ice Accumulation Conditions: • Weight ......................3400 LB • Temperature ..................Standard Day • Winds ....................... Zero • Mixture ....................Best Economy • Total Fuel....................92 Gallons • Note •...
  • Page 398 Section 9 Cirrus Design Supplements SR22 / SR22T Range / Endurance Profile (Continued) 65% POWER Mixture: Best Power Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 81.8 15.4 2000 81.1 15.4 4000 80.4...
  • Page 399 Cirrus Design Section 9 SR22 / SR22T Supplements Balked Landing Climb Gradient with Ice Accumulation Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps ......................50% (DN) • Climb Airspeed....................V REF • Note • Balked Landing Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
  • Page 400 Section 9 Cirrus Design Supplements SR22 / SR22T Balked Landing Rate of Climb with Ice Accumulation Conditions: • Power....................Full Throttle • Mixture.................... Set per Placard • Flaps......................... 50% • Climb Airspeed ....................V REF • Note • Balked Landing Rate of Climb values shown are the full flaps change in altitude for unit time expended expressed in Feet per Minute.
  • Page 401 Cirrus Design Section 9 SR22 / SR22T Supplements Landing Distance with Ice Accumulation Conditions: • Winds ....................... Zero • Runway ..................Dry, Level, Paved • Note • The following factors are to be applied to the computed landing distance for the noted condition: •...
  • Page 402 Section 9 Cirrus Design Supplements SR22 / SR22T Landing Distance - Flaps 50% WEIGHT: 3400 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 tailwind up to 10 knots.
  • Page 403 Cirrus Design Section 9 SR22 / SR22T Supplements Section 6 - Weight & Balance Refer to Section 6 - Weight and Balance 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 404 Section 9 Cirrus Design Supplements SR22 / SR22T 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 405 Cirrus Design Section 9 SR22 / SR22T Supplements If the system is ON and PUMP BKUP is selected, #1 pump will operate (if not failed) based on the mode setting (NORM or HIGH) while #2 pump operates continuously (PUMP BKUP), causing the range and endurance to decrease from the published values, e.g.
  • Page 406 Section 9 Cirrus Design Supplements SR22 / SR22T 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 407 Cirrus Design Section 9 SR22 / SR22T Supplements 8 9 10 LEGEND 1. LH Outbd Panel 14. Stall Transducer 27. RH Elevator Tip Panel 2. LH Vent 15. RH Vent 28. V Stab Panel 3. LH Inbd Panel 16. RH Outbd Panel 29.
  • Page 408 Section 9 Cirrus Design Supplements SR22 / SR22T 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 409 Cirrus Design Section 9 SR22 / SR22T Supplements • 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 410 Section 9 Cirrus Design Supplements SR22 / SR22T 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 411 Cirrus Design Section 9 SR22 / SR22T Supplements Stall Warning System Stall warning is provided by the lift transducer, mounted on the leading edge of the right wing and the stall warning computer located under the cabin floor. The lift transducer senses the force of the airstream on the vane, producing an electrical output to the stall warning computer.
  • Page 412 Section 9 Cirrus Design Supplements SR22 / SR22T aircraft beyond the required 5 KIAS to account for ice contamination on unprotected surfaces. Although this ensures the required margin is maintained during/after an icing encounter, it may be excessive when the aircraft is not contaminated by ice shapes.
  • Page 413 Cirrus Design Section 9 SR22 / SR22T Supplements Section 8 – Handling, Service, & Maintenance • Caution • During long periods of non-use, the porous panel membranes may dry out which could cause uneven fluid flow during subsequent operation. Perform the Pre-Flight Inspection every 30 days to keep porous panel membranes wetted.
  • Page 414 Section 9 Cirrus Design Supplements SR22 / SR22T 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.
  • Page 415 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 416 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 417 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 418 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 419 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 420 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 421 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 422 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 423 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 424 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 425 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 426 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 427 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 428 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 429 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 430 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 431 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 432 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 433 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 434 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 435 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 436 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 437 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 438 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 439 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 440 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 441 Cirrus Design Section 9 SR22 / SR22T Supplements AFCS recognizes it via acceleration and the AP/FD will transition 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 442 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 443 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 444 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 445 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 446 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 447 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 448 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 449 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 450 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 6 of 6 P/N 13772-136 Revision 01: 01-06-10...
  • Page 451 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement S-Tec Fifty Five X Autopilot w/ Optional Flight Director (Aircraft Serials w/ Perspective Avionics Only) When the System Fifty Five X Autopilot with Optional Flight Director System is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements Section of the basic Pilot’s...
  • Page 452 Section 2 - Limitations 1. The appropriate revision of the S-Tec System Fifty Five X, Pilot’s Operating Handbook for Perspective Equipped Cirrus Aircraft, (p/n 87277) must be immediately available to the pilot during flight. 2. Autopilot operation is prohibited above 185 KIAS.
  • Page 453 Cirrus Design Section 9 SR22 / SR22T Supplements d. 12 knot maximum crosswind component between the missed approach point and outer marker. e. The intercept of the localizer shall occur at least 5 miles outside of the outer marker. If the crosswind component is greater than 12 knots and less than 17 knots, the intercept shall occur at least 10 miles outside of the outer marker.
  • Page 454 Section 9 Cirrus Design Supplements SR22 / SR22T Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the basic Pilot’s Operating Handbook. Do not reengage the autopilot until the malfunction has been identified and corrected. The autopilot may be disconnected by: 1.
  • Page 455 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3A - Abnormal Procedures Autopilot Display Flashing Caution Annunciations If any of the following failure annunciations occur at low altitude or during an actual instrument approach, disengage the autopilot, execute a go-around or missed approach as appropriate. Inform ATC of problem.
  • Page 456 Section 9 Cirrus Design Supplements SR22 / SR22T Flashing NAV, REV, or APR Off navigation course by 50% needle deviation or more. 1. Use HDG mode until problem is identified. Crosscheck raw NAV data, compass heading, and radio operation. Flashing NAV, REV, or APR with steady FAIL FAIL Invalid radio navigation signal.
  • Page 457 Cirrus Design Section 9 SR22 / SR22T Supplements Flashing GS Off glideslope centerline by 50% needle deviation or more. 1. Check attitude and power. Adjust power as appropriate. Flashing GS with steady FAIL. FAIL Invalid glideslope radio navigation signal. 1. Disconnect autopilot and initiate go-around or missed approach procedure.
  • Page 458 Section 9 Cirrus Design Supplements SR22 / SR22T Section 4 - Normal Procedures • Note • Additional normal operating procedures for the System Fifty Five X are described in the S-Tec System Fifty Five X Pilot’s Operating Handbook. PreFlight Inspection 1.
  • Page 459 Cirrus Design Section 9 SR22 / SR22T Supplements Mode Selection Heading Mode 1. Set the PFD Heading Bug to the desired heading on the compass card. 2. Press HDG on Programmer/Computer. The HDG annunciation will illuminate and the airplane will turn to the selected heading.
  • Page 460 Section 9 Cirrus Design Supplements SR22 / SR22T Global Positioning System Steering (GPSS) Mode 1. Select a reliable GPS signal on the NAV receiver. 2. Engage GPSS mode: a. If NAV mode is already engaged, press NAV on Programmer/ Computer once.
  • Page 461 Cirrus Design Section 9 SR22 / SR22T Supplements Altitude Hold Mode 1. Manually fly the airplane to the desired altitude and level off. 2. Press HDG, NAV, GPSS, APR, or REV to engage a roll mode. The associated annunciations will illuminate.
  • Page 462 Section 9 Cirrus Design Supplements SR22 / SR22T Altitude Pre-Select Function The altitude selector may be used to set up an altitude and vertical speed for intercept and capture. The altitude can be above or below the current altitude and the vertical speed chosen should be appropriate (climb or descent) for the altitude.
  • Page 463 Cirrus Design Section 9 SR22 / SR22T Supplements Flight Director Operation - AP MODE (Optional) In AP MODE, the Flight Director provides a visual indication of how accurately the Autopilot is tracking the roll and pitch commands. 1. At Flight Director Remote Switches, press AP ON.
  • Page 464 Section 9 Cirrus Design Supplements SR22 / SR22T Section 7 - System Description The airplane is equipped with an S-Tec System Fifty Five X two-axis autopilot and, if installed, an integrated Flight Director System. The system consists of the Programmer / Computer, Flight Management...
  • Page 465 Cirrus Design Section 9 SR22 / SR22T Supplements INTEGRATED AVIONICS UNIT 2 FLIGHT DIRECTOR ALTITUDE TRANSDUCER SWITCHES STEC SYSTEM 55X AUTOPILOT A/P DISC SWITCH PITCH TRIM SERVO TURN COORDINATOR ROLL TRIM CARTRIDGE SR22_FM09_3014 PITCH TRIM CARTRIDGE Figure - 1 System Schematic...
  • Page 466 Section 9 Cirrus Design Supplements SR22 / SR22T Programmer / Computer The Programmer / Computer, located in the upper section of the center console, provides primary control of autopilot modes. 28 VDC for Programmer / Computer operation is supplied through the 5-amp KEYPADS / AP CTRL circuit breaker on MAIN BUS 1.
  • Page 467 Cirrus Design Section 9 SR22 / SR22T Supplements GPSS converts this information and sends this heading error directly to the autopilot. In the GPSS mode the autopilot can be directly coupled to the roll Commands produced by the GPS Navigator, eliminating the need for the pilot to make any further adjustments to the HSI course arrow.
  • Page 468 Section 9 Cirrus Design Supplements SR22 / SR22T When the above conditions have existed for 10 seconds, the GS annunciation will illuminate indicating GS arming has occurred (ALT annunciation will remain on). When the glideslope is intercepted and captured, the ALT annunciation will go out.
  • Page 469: Turn Coordinator

    Cirrus Design Section 9 SR22 / SR22T Supplements Flight Management System Keyboard The Flight Management System Keyboard, found in the center console above the programmer / computer, 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 470 Section 9 Cirrus Design Supplements SR22 / SR22T 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 System 55X Autopilot Legend 1. Heading Selection 2.
  • Page 471 Cirrus Design Section 9 SR22 / SR22T Supplements Altitude Transducer The altitude transducer, installed behind the bolster panel and plumbing directly into the Pitot Static system provides altitude information to the Programmer/Computer. #2 Integrated Avionics Units The #2 Integrated Avionics Unit located behind the MFD and...
  • Page 472 Section 9 Cirrus Design Supplements SR22 / SR22T The yoke mounted Autopilot Disconnect Switch disengages the autopilot and may also be used to mute the aural alert associated with an AP disconnect. Flight Director System (Optional) The Flight Director system enhances situational awareness by reducing cockpit workload through providing a visual cue for the pilot to follow as indicated by the PFD’s Flight Director Command Bars.
  • Page 473 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. Autopilot Status Box and Mode Annunciation In addition to the Failure and Caution Annunciations displayed on the Programmer / Computer, Autopilot selection and status annunciations are displayed on the PFD above the Airspeed and Attitude indicators.
  • Page 474 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 24 of 24 P/N 13772-140 Revision 01: 01-06-10...
  • Page 475 Cirrus Design Section 9 SR22 / SR22T Supplements Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement S-Tec Fifty Five SR Autopilot (Aircraft Serials w/ Perspective Avionics Only) When the System Fifty Five SR Autopilot is installed on the aircraft, this POH Supplement is applicable and must be inserted in the Supplements Section of the basic Pilot’s Operating Handbook.
  • Page 476 Section 2 - Limitations 1. The appropriate revision of the S-Tec System Fifty Five X, Pilot’s Operating Handbook for Perspective Equipped Cirrus Aircraft, (p/n 87277) must be immediately available to the pilot during flight. 2. Autopilot operation is prohibited above 185 KIAS.
  • Page 477 Cirrus Design Section 9 SR22 / SR22T Supplements d. 12 knot maximum crosswind component between the missed approach point and outer marker. e. The intercept of the localizer shall occur at least 5 miles outside of the outer marker. If the crosswind component is greater than 12 knots and less than 17 knots, the intercept shall occur at least 10 miles outside of the outer marker.
  • Page 478 Section 9 Cirrus Design Supplements SR22 / SR22T Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the basic Pilot’s Operating Handbook. Do not reengage the autopilot until the malfunction has been identified and corrected. The autopilot may be disconnected by: 1.
  • Page 479 Cirrus Design Section 9 SR22 / SR22T Supplements Section 3A - Abnormal Procedures Autopilot Display Flashing Caution Annunciations If any of the following failure annunciations occur at low altitude or during an actual instrument approach, disengage the autopilot, execute a go-around or missed approach as appropriate. Inform ATC of problem.
  • Page 480 Section 9 Cirrus Design Supplements SR22 / SR22T Flashing NAV, REV, or APR with steady FAIL FAIL Invalid radio navigation signal. 1. Check Nav radio for proper reception. Use HDG mode until problem is corrected. Flashing VS Excessive vertical speed error over selected vertical speed. Usually occurs in climb.
  • Page 481 Cirrus Design Section 9 SR22 / SR22T Supplements Section 4 - Normal Procedures • Note • Additional normal operating procedures for the System Fifty Five SR are described in the S-Tec System Fifty Five SR Pilot’s Operating Handbook. PreFlight Inspection 1.
  • Page 482 Section 9 Cirrus Design Supplements SR22 / SR22T Mode Selection Heading Mode 1. Set the PFD Heading Bug to the desired heading on the compass card. 2. Press HDG on Programmer/Computer. The HDG annunciation will illuminate and the airplane will turn to the selected heading.
  • Page 483 Cirrus Design Section 9 SR22 / SR22T Supplements Global Positioning System Steering (GPSS) Mode 1. Select a reliable GPS signal on the NAV receiver. 2. Engage GPSS mode: a. If NAV mode is already engaged, press NAV on Programmer/ Computer once.
  • Page 484 Section 9 Cirrus Design Supplements SR22 / SR22T Altitude Hold Mode 1. Manually fly the airplane to the desired altitude and level off. 2. Press HDG, NAV, GPSS, APR, or REV to engage a roll mode. The associated annunciations will illuminate.
  • Page 485 Cirrus Design Section 9 SR22 / SR22T Supplements Section 5 - Performance • WARNING • The autopilot may not be able to maintain all selectable vertical speeds. Selecting a vertical speed that exceeds the aircraft’s available performance may cause the aircraft to stall.
  • Page 486 Section 9 Cirrus Design Supplements SR22 / SR22T Section 7 - System Description The airplane is equipped with an S-Tec System Fifty Five SR two-axis autopilot. The system consists of the Programmer / Computer, Flight Management System Keyboard, Turn Coordinator,...
  • Page 487 Cirrus Design Section 9 SR22 / SR22T Supplements INTEGRATED AVIONICS UNIT 2 ALTITUDE TRANSDUCER STEC SYSTEM 55SR AUTOPILOT FIFTY FIVE SR S-TEC REV TRIM VS + VS x 100 A/P DISC SWITCH PITCH TRIM SERVO TURN COORDINATOR ROLL TRIM CARTRIDGE...
  • Page 488 Section 9 Cirrus Design Supplements SR22 / SR22T Programmer / Computer The Programmer / Computer, located in the upper section of the center console, provides primary control of autopilot modes. 28 VDC for Programmer / Computer operation is supplied through the 5-amp KEYPADS / AP CTRL circuit breaker on MAIN BUS 1.
  • Page 489 Cirrus Design Section 9 SR22 / SR22T Supplements GPSS converts this information and sends this heading error directly to the autopilot. In the GPSS mode the autopilot can be directly coupled to the roll Commands produced by the GPS Navigator, eliminating the need for the pilot to make any further adjustments to the HSI course arrow.
  • Page 490 Section 9 Cirrus Design Supplements SR22 / SR22T the aircraft. If the autopilot is still in the process of automatically trimming the aircraft after four more seconds, the annunciation will flash. When the aircraft has been sufficiently trimmed, the annunciation will extinguish.
  • Page 491 Cirrus Design Section 9 SR22 / SR22T Supplements ALT SEL - Altitude Select Knob The ALT knob controls the Selected Altitude, which is used as the reference for the altitude alerter and the altitude capture function. Pushing the ALT SEL knob synchronizes the selected altitude to the displayed altitude to the nearest 10 ft.
  • Page 492 Section 9 Cirrus Design Supplements SR22 / SR22T 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 S-TEC FIFTY FIVE SR REV TRIM...
  • Page 493 Cirrus Design Section 9 SR22 / SR22T Supplements Pitch Servo The Pitch Servo, located below the baggage compartment position the aircraft flight controls in response to commands generated by the Programmer/Computer autopilot calculations. 28 VDC for Pitch Servo operation is supplied through the 5-amp KEYPADS/AP CTRL circuit breaker on MAIN BUS 1.
  • Page 494 Supplements SR22 / SR22T Annunciation System • Note • Refer to the Cirrus Perspective Pilot’s Guide for a detailed description of the annunciator system and all warnings, cautions and advisories. Autopilot Status Box and Mode Annunciation In addition to the Failure and Caution Annunciations displayed on the Programmer / Computer, Autopilot selection and status annunciations are displayed on the PFD above the Airspeed and Attitude indicators.
  • Page 495 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 496 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 497 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 498 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 499 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 500 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 501 Safety Information Section 10 Safety Information Table of Contents Introduction ..................3 Cirrus Airframe Parachute System (CAPS) ........4 Deployment Scenarios..............4 General Deployment Information ............ 6 Landing Considerations ..............7 Taxiing, Steering, and Braking Practices ......... 10 Operating Practices ..............10 Brake Maintenance ...............
  • Page 502 Section 10 Cirrus Design Safety Information SR22T Intentionally Left Blank 10-2 P/N 13772-003 Original Issue...
  • Page 503: Introduction

    Cirrus Design Section 10 SR22T Safety Information Introduction This aircraft is designed to operate safely and efficiently in a flight environment. However, like any other aircraft, pilots must maintain proficiency to achieve maximum safety, utility, and economy. As the pilot you must be thoroughly familiar with the contents of this...
  • Page 504: Cirrus Airframe Parachute System (Caps)

    Safety Information SR22T Cirrus Airframe Parachute System (CAPS) The Cirrus Airframe Parachute System (CAPS) is designed to lower the aircraft and its passengers to the ground in the event of a life- threatening emergency. However, because CAPS deployment is expected to result in damage to the airframe and, depending upon...
  • Page 505 Cirrus Design Section 10 SR22T Safety Information Loss of Control Loss of control may result from many situations, such as: a control system failure (disconnected or jammed controls); severe wake turbulence, severe turbulence causing upset, severe airframe icing, or sustained pilot disorientation caused by vertigo or panic; or a spiral/ spin.
  • Page 506: General Deployment Information

    Section 10 Cirrus Design Safety Information SR22T General Deployment Information Deployment Speed The maximum speed at which deployment has been demonstrated is 133 KIAS. Deployment at higher speeds could subject the parachute and aircraft to excessive loads that could result in structural failure.
  • Page 507: Landing Considerations

    Cirrus Design Section 10 SR22T Safety Information 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 508 Section 10 Cirrus Design Safety Information SR22T • 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 509 Cirrus Design Section 10 SR22T Safety Information 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 510: Taxiing, Steering, And Braking Practices

    Safety Information SR22T 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 511: Brake Maintenance

    Cirrus Design Section 10 SR22T Safety Information • Use only as much power (throttle) as is necessary to achieve forward movement. Keep in mind, any additional power added with the throttle will be absorbed in the brakes to maintain constant speed.
  • Page 512 Section 10 Cirrus Design Safety Information SR22T Intentionally Left Blank 10-12 P/N 13772-003 Original Issue...

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