Cirrus DESIGN SR22 Pilot Operating Handbook
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PILOT'S OPERATING HANDBOOK
AND FAA APPROVED
AIRPLANE FLIGHT MANUAL
for the
CIRRUS DESIGN SR22
A i r c r a f t S e r i a l s 2 9 7 9 , 2 9 9 2 , 3 0 0 2 , 3 0 2 6 & S u b s e q u e n t
w i t h t h e C i r r u s P e r s p e c t i v e A v i o n i c s S y s t e m
FAA Approved in Normal Category based on FAR 23. This document must be carried in
the airplane at all times and be kept within the reach of the pilot during all flight
operations.
THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO
THE PILOT BY FAR PART 23 AND ADDITIONAL INFORMATION PROVIDED BY
CIRRUS DESIGN AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT
MANUAL.
Model - Serial Num.:
Registration Num.:
P/N 13772-002
CoverPage-i
Reissue A: 01-14-2013
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Summary of Contents for Cirrus DESIGN SR22
- Page 1 THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY FAR PART 23 AND ADDITIONAL INFORMATION PROVIDED BY CIRRUS DESIGN AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL. Model - Serial Num.: Registration Num.:...
- Page 2 Copyright © 2013 - All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811 CoverPage-ii P/N 13772-002 Reissue A: 01-14-2013...
- Page 3 Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages Use this page to determine the current effective date for each page in the POH. Supplements are issued individually and are controlled by the Log of Supplements Page in Section 9.
-
Page 4: Table Of Contents
Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 4-23 Reissue A Reissue A 7-61 Reissue A 4-24 Reissue A Reissue A 7-62 Reissue A 4-25 Reissue A... -
Page 5: Reissue A
Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 8-22 Reissue A 8-23 Reissue A 8-24 Reissue A 8-25 Reissue A 8-26 Reissue A 8-27 Reissue A 8-28... -
Page 6: Reissue A
Cirrus Design Pilot’s Operating Handbook SR22 List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status Intentionally Left Blank P/N 13772-002 Reissue A... -
Page 7: Reissue A
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: Reissue A
Front Matter Cirrus Design Foreword SR22 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: Reissue A
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: Reissue A
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: Reissue A
Cirrus Design Front Matter SR22 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: Reissue A
Front Matter Cirrus Design Foreword SR22 Intentionally Left Blank Front Matter-6 P/N 13772-002 Reissue A... -
Page 13: Reissue A
Cirrus Design Section 1 SR22 General Section 1: General Table of Contents Introduction ..................3 The Airplane..................7 Engine..................... 7 Propeller ..................7 Fuel....................8 Oil ....................8 Maximum Certificated Weights ............8 Cabin and Entry Dimensions ............8 Baggage Spaces and Entry Dimensions ........8 Specific Loadings................ -
Page 14: Reissue A
Section 1 Cirrus Design General SR22 Intentionally Left Blank P/N 13772-002 Reissue A... -
Page 15: Introduction
Cirrus Design Section 1 SR22 General Introduction This section contains information of general interest to pilots and owners. You will find the information useful in acquainting yourself with the airplane, as well as in loading, fueling, sheltering, and handling the airplane during ground operations. -
Page 16: Reissue A
Section 1 Cirrus Design General SR22 26.0 ft 7.92 m 8.9 ft 2.71 m 9 inches (minimum) 23 cm (minimum) NOTE: • Wing span includes position and strobe lights. • Prop ground clearance at 3400 lb - 9" inches (23 cm). -
Page 17: Reissue A
Cirrus Design Section 1 SR22 General 49.3" 39.8" Fuselage Station 49.7" 38.5" 27.0" 16.0" 20.0" 32.0" 10.5" 39.0" 33.4" 20.0" 33.3" 5.0" 21.0" CABIN DOOR BAGGAGE DOOR OPENING OPENING SR22_FM01_1019A Location Length Width Height Volume 122” 49.3” 49.7 137 cu ft Cabin 36”... -
Page 18: Reissue A
Section 1 Cirrus Design General SR22 GROUND TURNING CLEARANCE 24.3 ft. (7.41 m) RADIUS FOR WING TIP 7.0 ft. (2.16 m) RADIUS FOR NOSE GEAR 0.5 ft. (0.15 m) RADIUS FOR INSIDE GEAR 9.1 ft. (2.77 m) RADIUS FOR OUTSIDE GEAR TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER. -
Page 19: The Airplane
Cirrus Design Section 1 SR22 General The Airplane Engine Number of Engines................1 Number of Cylinders................6 Engine Manufacturer ..........Teledyne Continental Engine Model ................. IO-550-N Fuel Metering ..............Fuel Injected Engine Cooling ..............Air Cooled Engine Type........Horizontally Opposed, Direct Drive Horsepower Rating.......... -
Page 20: Fuel
Section 1 Cirrus Design General SR22 Fuel Total Capacity ..........94.5 U.S. Gallons (358.0 L) Total Usable ..........92.0 U.S. Gallons (348.0 L) Approved Fuel Grades: 100 LL Grade Aviation Fuel (Blue) 100 (Formerly 100/130) Grade Aviation Fuel (Green) Oil Capacity (Sump) ..........8 U.S. Quarts (7.6 L) Oil Grades: All Temperatures ...... -
Page 21: Symbols, Abbreviations And Terminology
Cirrus Design Section 1 SR22 General Symbols, Abbreviations and Terminology General Airspeed Terminology and Symbols KCAS Knots Calibrated Airspeed is the indicated airspeed corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. -
Page 22: Meteorological Terminology
Section 1 Cirrus Design General SR22 Stalling Speed is the minimum steady flight speed at which aircraft controllable 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: Engine Power Terminology
Cirrus Design Section 1 SR22 General • Pressure Altitude is the altitude read from the altimeter when the 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: Weight And Balance Terminology
Section 1 Cirrus Design General SR22 NMPG Nautical Miles Per Gallon is the distance (in nautical miles) which can be expected per gallon of fuel consumed at a specific engine power setting and/or flight configuration. • Unusable Fuel is the quantity of fuel that cannot be safely used in flight. -
Page 25: Reissue A
Cirrus Design Section 1 SR22 General • Station is a location along the airplane fuselage measured in inches from the reference datum and expressed as a number. For example: A point 123 inches aft of the reference datum is Fuselage Station 123.0 (FS 123). -
Page 26: Reissue A
Section 1 Cirrus Design General SR22 Intentionally Left Blank 1-14 P/N 13772-002 Reissue A... -
Page 27: Reissue A
Environmental Conditions ..............17 Maximum Occupancy ..............18 Systems and Equipment Limits............19 Cirrus Perspective Integrated Avionics System ......19 L-3 Skywatch Traffic Advisory System ......... 22 L-3 Stormscope Weather Information System ......22 Max Viz Enhanced Vision System (Optional) ....... 22 Air Conditioning System (Optional).......... -
Page 28: Reissue A
Section 2 Cirrus Design Limitations SR22 Smoking ..................24 Placards ................... 25 P/N 13772-002 Reissue A... -
Page 29: Introduction
Cirrus Design Section 2 SR22 Limitations Introduction The limitations included in this Section of the Pilot’s Operating Handbook (POH) are approved by the Federal Aviation Administration. This section provides operating limitations, instrument markings and basic placards required by regulation and necessary for the safe operation of the aircraft and its standard systems and equipment. -
Page 30: Airspeed Limitations
Section 2 Cirrus Design Limitations SR22 Airspeed Limitations The indicated airspeeds in the following table are based on Section 5, Airspeed Calibration - Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources. -
Page 31: Airspeed Indicator Markings
Cirrus Design Section 2 SR22 Limitations Airspeed Indicator Markings The airspeed indicator markings are based on Section 5, Airspeed Calibration - Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources. -
Page 32: Powerplant Limitations
Section 2 Cirrus Design Limitations SR22 Powerplant Limitations Engine Teledyne Continental .............. IO-550-N Power Rating ............310 hp @ 2700 RPM Maximum RPM ..............2700 RPM Oil Temperature ..........240°F (115°C) maximum Minimum Oil Temperature for Takeoff .......75 F (24 C) Oil Pressure: Minimum................ -
Page 33: Propeller
Cirrus Design Section 2 SR22 Limitations Propeller Hartzell Propeller Type ........Constant Speed, Three Blade Model Number..........PHC-J3YF-1RF/F7694(B) Diameter.............78.0” (76.0” Minimum) Model Number......... PHC-J3YF-1RF/F7693DF(B) Diameter.............78.0" (76.0" Minimum) McCauley Propeller Type ........Constant Speed, Three Blade Model Number............ D3A34C443/78CYA-0 Diameter.............78.0" (76.0" Minimum) MT Propeller Propeller Type ........Constant Speed, Three Blade... -
Page 34: Engine Instrument Markings & Annunciations
Section 2 Cirrus Design Limitations SR22 Engine Instrument Markings & Annunciations The following describes the engine instrument markings. Associated Warning and Caution Annunciations are shown in capitalized text. PowerPlant Yellow Green Arc/ Yellow Arc/ Arc/Bar Arc/Bar Arc/Bar Instrument (Range & Units) -
Page 35: Fuel
Cirrus Design Section 2 SR22 Limitations Fuel Yellow Green Yellow Arc/Bar Arc/Bar Arc/Bar Arc/Bar Arc/Bar Instrument Minimum Maximum (Range & Units) Caution Normal Caution Minimum Range Range Range Maximum –– –– 0 – 30 –– –– Fuel Flow (0 – 30 U.S. Gal/Hr) Fuel Totalizer N <... -
Page 36: Center Of Gravity Limits
Section 2 Cirrus Design Limitations SR22 Center of Gravity Limits Reference Datum ........100 inches forward of firewall Forward..............Refer to Figure 2-1 Aft ................Refer to Figure 2-1 3600 31 .5% M A C 1 9.2% M A C FS 1 48.1 FS 1 42.3... -
Page 37: Maneuver Limits
60°. • Note • Because the aircraft has not been certified for spin recovery, the Cirrus Airframe Parachute System (CAPS) must be deployed if the airplane departs controlled flight. Refer to Section 3, Inadvertent Spin Entry. -
Page 38: Kinds Of Operation
Section 2 Cirrus Design Limitations SR22 Kinds of Operation The aircraft is equipped and approved for the following type operations: • VFR day and night. • IFR day and night. Kinds of Operation Equipment List The following listing summarizes the equipment required under Federal Aviation Regulations (FAR) Part 23 for airworthiness under the listed kind of operation. -
Page 39: Reissue A
Cirrus Design Section 2 SR22 Limitations Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions Low Volts Annunciator ALT 1 Annunciator ALT 2 Annunciator — — Circuit Breakers As required. Equipment & Furnishings Emergency Locator Trans-... -
Page 40: Reissue A
Section 2 Cirrus Design Limitations SR22 Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions Ice & Rain Protection Alternate Engine Air Induc- tion System Alternate Static Air Source Pitot Heater — — Landing Gear Wheel Pants —... -
Page 41: Reissue A
Cirrus Design Section 2 SR22 Limitations Kinds of Operation (Continued) Remarks, Notes, System, Instrument, and/ and/or or Equipment Exceptions Navigation & Pitot Static Airspeed Indicator Altimeter Magnetic Compass Pitot System Static System, Normal Attitude Indicator — — Clock — —... -
Page 42: Icing
Oil Pressure Indication Oil Quantity Indicator (Dip- stick) Oil Temperature Indication Engine Speed Special Equipment Cirrus Airframe Parachute (CAPS) Icing Flight into known icing conditions is prohibited. Runway Surface This airplane may be operated on any smooth runway surface. Taxi Power Maximum continuous engine speed for taxiing is 1000 RPM on flat, smooth, hard surfaces. -
Page 43: Fuel Limits
Environmental Conditions For operation of the airplane below an outside air temperature of -10°F (-23°C), use of cowl inlet covers approved by Cirrus Design and listed in the Winterization Kit AFM Supplement P/N 13772-118 is required. P/N 13772-002... -
Page 44: Maximum Occupancy
Section 2 Cirrus Design Limitations SR22 Maximum Occupancy Serials w/o 2+1 Rear Seat Occupancy of this airplane is limited to four persons, the pilot and three passengers. Serials w/ 2+1 Rear Seat Occupancy of this airplane is limited to “4+1” persons, the pilot and four passengers. -
Page 45: Systems And Equipment Limits
Systems and Equipment Limits Cirrus Perspective Integrated Avionics System 1. The appropriate revision of the Cirrus Perspective Cockpit Reference Guide (p/n 190-00821-XX, where X can be any digit from 0 to 9) must be immediately available to the pilot during flight. -
Page 46: Reissue A
The Perspective Integrated Avionics System is compliant with AC 90-100A. As such, the Cirrus Perspective system is eligible to fly RNAV 'Q' or 'T' routes, RNAV SID/STAR/ODPs and eligible to use RNAV substitution or RNAV alternate means of navigation (US Only). -
Page 47: Reissue A
Cirrus Design Section 2 SR22 Limitations 5. Navigation using the Perspective Integrated Avionics System is not authorized in the following geographic areas: a. north of 70°North latitude (northern polar region), b. south of 70°South latitude (southern polar region), c. north of the 65°North latitude between longitude 75°W and 120°W (Northern Canada),... -
Page 48: L-3 Skywatch Traffic Advisory System
Section 2 Cirrus Design Limitations SR22 12. Use of the TRAFFIC ADVISORY SYSTEM (TAS) to maneuver the airplane to avoid traffic is prohibited. The TAS is intended for advisory use only. TAS is intended only to help the pilot to visually located traffic. -
Page 49: Reissue A
Cirrus Design Section 2 SR22 Limitations 2. The Max Viz Enhanced Vision System Information Manual, P/N 309100024 Revision 01 or later must be available to the pilot during flight. P/N 13772-002 P/N 13772-002 2-23 2-23 Reissue A... -
Page 50: Air Conditioning System (Optional)
Airplane Maintenance Manual. Refer to Airplane Maintenance Manual (AMM), Chapter 51, for specific paint requirements. Cirrus Airframe Parachute System (CAPS) VPD Maximum Demonstrated Deployment Speed....133 KIAS • Note •... -
Page 51: Reissue A
Cirrus Design Section 2 SR22 Limitations Placards Engine compartment, inside oil filler access: ENGINE OIL GRADE ABOVE 40° F SAE 50 OR 20W50 OR 20W60 BELOW 40° F SAE 30 OR 10W30, 15W50, OR 20W50 REFER TO AFM FOR APPROVED OILS... -
Page 52: Reissue A
Section 2 Cirrus Design Limitations SR22 Elevator and Rudder, both sides: NO PUSH Left fuselage, on external power supply door: EXTERNAL POWER 28 V DC Doors, above and below latch: PUSH OPEN Wing, adjacent to fluid filler cap: DE-ICING FLUID... -
Page 53: Reissue A
Cirrus Design Section 2 SR22 Limitations Engine control panel: CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT ALTITUDE GPH 16000 ----- 17 12000 ----- 18 8000 ----- 21 4000 ----- 24 SL ----- 27... -
Page 54: Reissue A
Section 2 Cirrus Design Limitations SR22 Wing, flap aft edge and fuselage vortex generator: NO STEP Cabin Door Window, lower edge, centered, applied upside down: RESCUE: FRACTURE AND REMOVE WINDOW Bolster Switch Panel, left edge: THIS AIRCRAFT IS CERTIFIED FOR THE... -
Page 55: Reissue A
Cirrus Design Section 2 SR22 Limitations Instrument Panel, center: DISPLAY BACKUP Bolster Panel, both sides: GRAB HERE Baggage Compartment, aft edge: ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Instrument Panel: FASTEN SEATBELTS • NO SMOKING Cabin Window, above door latch:... -
Page 56: Reissue A
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 57: Reissue A
Cirrus Design Section 3 SR22 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 58: Reissue A
Section 3 Cirrus Design Emergency Procedures SR22 Low Fuel Quantity ................. 22 Electrical System Emergencies............23 High Voltage on Main Bus 1 ............23 High Voltage on Main Bus 2 ............24 High or Low Voltage on Essential Bus.......... 25 Environmental System Emergencies .......... -
Page 59: Introduction
Cirrus Design Section 3 SR22 Emergency Procedures Introduction This section provides procedures for handling emergencies and critical flight situations that may occur while operating the aircraft. Although emergencies caused by airplane, systems, or engine malfunctions are extremely rare, the guidelines described in this section should be considered and applied as necessary should an emergency arise. -
Page 60: Emergency Procedures Guidance
Section 3 Cirrus Design Emergency Procedures SR22 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 61: Circuit Breakers
121.500 MHz. If the display is available, it will also show it in the “Active” frequency window. The Cirrus Airframe Parachute System (CAPS) should be activated in the event of a life-threatening emergency where CAPS deployment is determined to be safer than continued flight and landing. Refer to... -
Page 62: Airspeeds For Emergency Operations
Section 3 Cirrus Design Emergency Procedures SR22 Airspeeds for Emergency Operations Maneuvering Speed: 3400 lb ................133 KIAS Best Glide: 3400 lb ................88 KIAS 2900 lb ................87 KIAS Emergency Landing (Engine-out): Flaps Up................90 KIAS Flaps 50% ................85 KIAS Flaps 100% ................80 KIAS... -
Page 63: Engine Failures
Cirrus Design Section 3 SR22 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 64: Engine Failure In Flight
If altitude or terrain does not permit a safe landing, CAPS deployment may be required. Refer to Section 10, Cirrus Airframe Parachute System (CAPS) for CAPS deployment scenarios and landing considerations. P/N 13772-002... -
Page 65: Airstart
Cirrus Design Section 3 SR22 Emergency Procedures Airstart Engine Airstart 1. Bat Master Switches ..............ON 2. Power Lever ..............½” OPEN 3. Mixture ..............RICH, AS REQ’D 4. Fuel Selector............SWITCH TANKS 5. Ignition Switch............... BOTH 6. Fuel Pump ................. BOOST 7. -
Page 66: Smoke And Fire
Section 3 Cirrus Design Emergency Procedures SR22 Smoke and Fire Cabin Fire In Flight 1. Bat-Alt Master Switches ........OFF, AS REQ’D 2. Fire Extinguisher ............ACTIVATE If airflow is not sufficient to clear smoke or fumes from cabin: 3. Cabin Doors ............PARTIALLY OPEN Airspeed may need to be reduced to partially open door in flight. -
Page 67: Engine Fire In Flight
Cirrus Design Section 3 SR22 Emergency Procedures 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 68: Wing Fire In Flight
Section 3 Cirrus Design Emergency Procedures SR22 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 69: Smoke And Fume Elimination
Cirrus Design Section 3 SR22 Emergency Procedures Smoke and Fume Elimination 1. Air Conditioner (if installed)............OFF 2. Temperature Selector............COLD 3. Vent Selector......FEET/PANEL/DEFROST POSITION 4. Airflow Selector .......SET AIRFLOW TO MAXIMUM If source of smoke and fume is firewall forward: a. -
Page 70: Emergency Descent
Section 3 Cirrus Design Emergency Procedures SR22 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... -
Page 71: Forced Landings
If flight conditions or terrain does not permit a safe landing, CAPS deployment may be required. Refer to Section 10, Cirrus Airframe Parachute System (CAPS) for CAPS deployment scenarios and landing considerations. -
Page 72: Ditching
Section 3 Cirrus Design Emergency Procedures SR22 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 73: Engine System Emergencies
Cirrus Design Section 3 SR22 Emergency Procedures Engine System Emergencies Engine Partial Power Loss 1. Fuel Pump ................. BOOST 2. Fuel Selector............SWITCH TANKS 3. Mixture ......CHECK appropriate for flight conditions 4. Power Lever ............... SWEEP 5. Alternate Induction Air ...............ON 6. -
Page 74: Reissue A
Section 3 Cirrus Design Emergency Procedures SR22 during descent and approach to landing the cooling air may not be sufficient to prevent an engine fire. Selecting BOOST on may clear the problem if vapor in the injection lines is the problem or if the engine-driven fuel pump has partially failed. -
Page 75: Oil Pressure Out Of Range
Cirrus Design Section 3 SR22 Emergency Procedures 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 76: High Cylinder Head Temperature
Section 3 Cirrus Design Emergency Procedures SR22 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 77: Propeller System Emergencies
Cirrus Design Section 3 SR22 Emergency Procedures Propeller System Emergencies Engine Speed High RPM Warning: Engine SpeedHigh 1. Tachometer ................ CHECK If engine speed normal: a. If On-Ground ......CORRECT PRIOR TO FLIGHT b. If In-Flight ........... CONTINUE, MONITOR If engine speed high: a. -
Page 78: Fuel System Emergencies
Section 3 Cirrus Design Emergency Procedures SR22 Fuel System Emergencies High Fuel Flow FUEL FLOW Warning FUEL FLOW Fuel flow greater than 30 GPH. On-Ground 1. Correct prior to flight. In-Flight 1. Mixture ................ADJUST Adjust engine operation to correct condition. Check engine instruments to verify HIGH FLOW Warning is not erroneous, i.e. -
Page 79: Reissue A
Cirrus Design Section 3 SR22 Emergency Procedures Electrical System Emergencies High Voltage on Main Bus 1 M BUS 1 Warning M BUS 1 1. ALT 1 Master Switch ............CYCLE 2. M Bus 1 Voltage (M1) ............CHECK If M Bus 1 Voltage is greater than 32 volts 3. -
Page 80: Reissue A
Section 3 Cirrus Design Emergency Procedures SR22 High Voltage on Main Bus 2 M BUS 2 Warning M BUS 2 1. Main Bus 1 Voltage (M1)............ CHECK If M Bus 1 Voltage is greater than 32 volts 2. Perform M BUS 1 Warning Checklist 3. -
Page 81: High Or Low Voltage On Essential Bus
Cirrus Design Section 3 SR22 Emergency Procedures High or Low Voltage on Essential Bus ESS BUS Warning ESS BUS 1. Essential Bus Voltage (ESS)..........CHECK If Essential Bus Voltage is greater than 32 volts: 2. Main Bus 1 and Main Bus 2 Voltages (M1 and M2)... CHECK 3. -
Page 82: Environmental System Emergencies
Section 3 Cirrus Design Emergency Procedures SR22 Environmental System Emergencies Carbon Monoxide Level High CO LVL HIGH Warning CO LVL HIGH 1. Air Conditioner (if installed) ...... NOT IN RECIRC MODE 2. Temperature Selector............COLD 3. Vent Selector......FEET/PANEL/DEFROST POSITION 4. -
Page 83: Integrated Avionics System Emergencies
Cirrus Design Section 3 SR22 Emergency Procedures Integrated Avionics System Emergencies A “Red X” through any electronic display field, such as COM frequencies, NAV frequencies, or engine data, indicates that display field is not receiving valid data. Attitude & Heading Reference System (AHRS) Failure 1. -
Page 84: Unusual Attitude Emergencies
CAPS. 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 Checklist, this section). -
Page 85: Inadvertent Spiral Dive During Imc Flight
7. Exit IMC conditions as soon as possible. Amplification In all cases, if the aircraft enters an unusual attitude from which recovery is not assured, immediately deploy CAPS. Refer to Section Cirrus Airframe Parachute System (CAPS) for CAPS deployment information. P/N 13772-002... -
Page 86: Other Emergencies
Section 3 Cirrus Design Emergency Procedures SR22 Other Emergencies Power Lever Linkage Failure 1. Power Lever Movement............VERIFY 2. Power ................SET if able 3. Flaps ................ SET if needed 4. Mixture ........AS REQUIRED (full rich to cut-off) 5. Land as soon as possible. -
Page 87: Left/Right Brake Over-Temperature Annunciation
Cirrus Design Section 3 SR22 Emergency Procedures Left/Right Brake Over-Temperature Annunciation BRAKE TEMP Warning BRAKE TEMP 1. Stop aircraft and allow the brakes to cool. Amplification Annunciation indicates brake temperature is greater than 293°F. Refer to Section 10, Taxiing, Steering, and Braking Practices for additional information. -
Page 88: Emergency Ground Egress
Section 3 Cirrus Design Emergency Procedures SR22 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 89: Reissue A
Cirrus Design Section 3 SR22 Emergency Procedures 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 90: Reissue A
Cirrus Design Emergency Procedures SR22 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. -
Page 91: Reissue A
Cirrus Design Section 3A SR22 Abnormal Procedures Section 3A: Abnormal Procedures Table of Contents Introduction ..................3 Abnormal Procedures Guidance ............3 Circuit Breakers ................3 Flight Environment ................4 Inadvertent Icing Encounter ............4 Inadvertent IMC Encounter............. 4 Door Open In Flight ................ 4 Abnormal Landings ................ -
Page 92: Reissue A
Section 3A Cirrus Design Abnormal Procedures SR22 Landing Gear System ..............18 Brake Failure During Taxi ............. 18 Left/Right Brake Over-Temperature..........18 Other Conditions ................19 Aborted Takeoff ................19 Parking Brake Engaged Annunciation .......... 20 Communications Failure ............... 20... -
Page 93: Introduction
Cirrus Design Section 3A SR22 Abnormal Procedures Introduction This section provides procedures for handling abnormal system and/or flight conditions which, if followed, will maintain an acceptable level of airworthiness or reduce operational risk. The guidelines described in this section are to be used when an abnormal condition exists and should be considered and applied as necessary. -
Page 94: Flight Environment
Section 3A Cirrus Design Abnormal Procedures SR22 Flight Environment Inadvertent Icing Encounter 1. Pitot Heat .................. ON 2. Exit icing conditions. Turn back or change altitude. 3. Cabin Heat ..............MAXIMUM 4. Windshield Defrost ............FULL OPEN 5. Alternate Induction Air............... ON Amplification Flight into known icing conditions is prohibited. -
Page 95: Abnormal Landings
Cirrus Design Section 3A SR22 Abnormal Procedures Abnormal Landings Landing With Failed Brakes One brake inoperative 1. Land on the side of runway corresponding to the inoperative brake. 2. Maintain directional control using rudder and working brake. Both brakes inoperative 1. -
Page 96: Engine System
Section 3A Cirrus Design Abnormal Procedures SR22 Engine System Low Idle Oil Pressure OIL PRESS Caution OIL PRESS 1. If In-Flight ..........LAND as soon as 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 97: Starter Engaged Annunciation
Cirrus Design Section 3A SR22 Abnormal Procedures Starter Engaged Annunciation STARTER ENGAGED Caution START ENGAGE On-Ground 1. Ignition Switch......DISENGAGE prior to 20 Seconds 2. Battery Switches ...Wait 20 seconds before next start attempt If starter does not disengage (relay or solenoid failure): 3. -
Page 98: Fuel System
Section 3A Cirrus Design Abnormal Procedures SR22 Fuel System Low Fuel Quantity FUEL QTY Caution FUEL QTY 1. Fuel Quantity Gages ............CHECK If left & right fuel quantities indicate less than or equal to 14 gallons per side: a. Land as soon as practical. -
Page 99: Right Fuel Tank Quantity
Cirrus Design Section 3A SR22 Abnormal Procedures Right Fuel Tank Quantity R FUEL QTY Advisory R FUEL QTY 1. Right Fuel Quantity Gage ..........CHECK If right fuel quantity indicates less than or equal to 14 gallons: a. If On-Ground ......REFUEL PRIOR TO FLIGHT b. -
Page 100: Low Voltage On Main Bus 1
Section 3A Cirrus Design Abnormal Procedures SR22 Electrical System Low Voltage on Main Bus 1 M BUS 1 Caution M BUS 1 1. Perform ALT 1 Caution (Failure) Checklist. Amplification Main Bus 1 Voltage is low, indicates Alt 1 failure; will typically be associated with low M1 voltage Alt 1 current indications, Battery 1 discharge and ALT 1 Caution message. -
Page 101: Low Alternator 1 Output
Cirrus Design Section 3A SR22 Abnormal Procedures Low Alternator 1 Output ALT 1 Caution (Failure) ALT 1 1. ALT 1 Circuit Breaker ..........CHECK & SET 2. ALT 1 Master Switch ............CYCLE If alternator does not reset (low A1 Current and M1 voltage): 3. -
Page 102: Low Alternator 2 Output
Section 3A Cirrus Design Abnormal Procedures SR22 Low Alternator 2 Output ALT 2 Caution (Failure) ALT 2 1. ALT 2 Circuit Breaker ..........CHECK & SET 2. ALT 2 Master Switch ............CYCLE If alternator does not reset (low A2 Current and M2 voltage less than M1 voltage): 3. -
Page 103: Integrated Avionics System
Cirrus Design Section 3A SR22 Abnormal Procedures Integrated Avionics System Avionics Switch Off AVIONICS OFF Caution AVIONICS OFF 1. AVIONICS Switch ........... ON, AS REQUIRED Amplification The AVIONICS master switch is off. PFD Cooling Fan Failure PFD FAN FAIL Advisory PFD FAN FAIL 1. -
Page 104: Flight Displays Too Dim
Section 3A Cirrus Design Abnormal Procedures SR22 Flight Displays Too Dim 1. INSTRUMENT dimmer knob ....OFF (full counter-clockwise) If flight displays do not provide sufficient brightness: 2. Revert to standby instruments. Amplification The instrument dimmer knob provides manual dimming control of the display screens, key and text backlighting, flap and Environmental Control System (ECS) status indicators, and standby instruments. -
Page 105: Pitot Static System
Cirrus Design Section 3A SR22 Abnormal Procedures Pitot Static System Pitot Static Malfunction Static Source Blocked 1. Pitot Heat ...................ON 2. Alternate Static Source ............OPEN Amplification If erroneous readings of the static source instruments (airspeed, altimeter and vertical speed) are suspected, the alternate static source valve, on side of console near pilot’s right ankle, should be opened to... -
Page 106: Pitot Heat Current Sensor Annunciation
Section 3A Cirrus Design Abnormal Procedures SR22 Pitot Heat Current Sensor Annunciation PITOT HEAT FAIL Caution PITOT HEAT FAIL 1. Pitot Heat Circuit Breaker............ CYCLE 2. Pitot Heat ............. CYCLE OFF, ON If inadvertent icing encountered, perform Inadvertent Icing Encounter Checklist and: a. -
Page 107: Flight Control System
Cirrus Design Section 3A SR22 Abnormal Procedures Flight Control System Electric Trim/Autopilot Failure 1. Airplane Control ..........MAINTAIN MANUALLY 2. Autopilot (if engaged)..........DISENGAGE If Problem Is Not Corrected: 3. Circuit Breakers ........... PULL AS REQUIRED • PITCH TRIM • ROLL TRIM •... -
Page 108: Landing Gear System
Section 3A Cirrus Design Abnormal Procedures SR22 Landing Gear System Brake Failure During Taxi 1. Engine Power ............AS REQUIRED • To stop airplane - REDUCE • If necessary for steering - INCREASE 2. Directional Control .......MAINTAIN WITH RUDDER 3. Brake Pedal(s)..............PUMP If directional control can not be maintained: 4. -
Page 109: Other Conditions
Cirrus Design Section 3A SR22 Abnormal Procedures Other Conditions Aborted Takeoff 1. Power Lever ................IDLE 2. Brakes..............AS REQUIRED Amplification Use as much of the remaining runway as needed to safely bring the airplane to a stop or to slow the airplane sufficiently to turn off runway. -
Page 110: Parking Brake Engaged Annunciation
Section 3A Cirrus Design Abnormal Procedures SR22 Parking Brake Engaged Annunciation PARK BRAKE Caution PARK BRAKE 1. Parking Brake..............RELEASE 2. Monitor CAS for BRAKE TEMP Caution. Stop aircraft and allow the brakes to cool if necessary. Amplification Parking brake is set. - Page 111 Cirrus Design Section 4 SR22 Normal Procedures Section 4: Normal Procedures Table of Contents Introduction ..................3 Airspeeds for Normal Operation ............3 Normal Procedures ................4 Preflight Inspection ................. 4 Preflight Walk-Around ..............4 Before Starting Engine..............9 Starting Engine ................10 Before Taxiing................
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Page 112: Normal Procedures
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Page 113: Airspeeds For Normal Operation
Cirrus Design Section 4 SR22 Normal Procedures Introduction This section provides amplified procedures for normal operation. Normal procedures associated with optional systems can be found in Section 9: Log of Supplements. Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3400 lb. -
Page 114: Preflight Inspection
Section 4 Cirrus Design Normal Procedures SR22 Normal Procedures Preflight Inspection Before carrying out preflight inspections, ensure that all required maintenance has been accomplished. Review your flight plan and compute weight and balance. • Note • Throughout the walk-around: check all hinges, hinge pins, and bolts for security;... - Page 115 Cirrus Design Section 4 SR22 Normal Procedures 1. Cabin a. Required Documents..........On Board b. Avionics Power Switch............OFF c. Bat 2 Master Switch ............ON d. PFD ................Verify On e. Essential Bus Voltage..........23-25 Volts Flap Position Light ............OUT g.
- Page 116 Section 4 Cirrus Design Normal Procedures SR22 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 • Verify tape covering the forward and aft inspection holes located on outboard ends of horizontal stabilizer is installed and securely attached.
- Page 117 Cirrus Design Section 4 SR22 Normal Procedures • 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 118 Section 4 Cirrus Design Normal Procedures SR22 d. External Power .............Door Secure e. Vortex Generator ............Condition Exhaust Pipe(s) ....Condition, Security, and Clearance 11. Left Main Gear and Forward Wing a. Wheel fairings ....... Security, Accumulation of Debris b. Tire ..........Condition, Inflation, and Wear •...
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Page 119: Before Starting Engine
Cirrus Design Section 4 SR22 Normal Procedures Before Starting Engine 1. Preflight Inspection ...........COMPLETED • WARNING • Ensure that the airplane is properly loaded and within the AFM’s weight and balance limitations prior to takeoff. 2. Weight and Balance..........Verify within limits 3. -
Page 120: Starting Engine
Section 4 Cirrus Design Normal Procedures SR22 Starting Engine If the engine is warm, no priming is required. For the first start of the day and in cold conditions, prime will be necessary. Weak intermittent firing followed by puffs of black smoke from the exhaust stack indicates over-priming or flooding. - Page 121 Cirrus Design Section 4 SR22 Normal Procedures 6. Power Lever ............FULL FORWARD 7. Fuel Pump ............ PRIME, then BOOST • Note • On first start of the day, especially under cool ambient conditions, holding Fuel Pump switch to PRIME for 2 seconds will improve starting.
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Page 122: Taxiing
Section 4 Cirrus Design Normal Procedures SR22 Before Taxiing 1. Flaps ................. UP (0%) 2. Radios/Avionics............AS REQUIRED 3. Cabin Heat/Defrost ..........AS REQUIRED 4. Fuel Selector ............SWITCH TANK Taxiing When taxiing, directional control is accomplished with rudder deflection and intermittent braking (toe taps) as necessary. Use only as much power as is necessary to achieve forward movement. -
Page 123: Before Takeoff
Cirrus Design Section 4 SR22 Normal Procedures Before Takeoff During cold weather operations, the engine should be properly warmed up before takeoff. In most cases this is accomplished when the oil temperature has reached at least 100°F (38°C). In warm or hot weather, precautions should be taken to avoid overheating during prolonged ground engine operation. - Page 124 Section 4 Cirrus Design Normal Procedures SR22 16. Alternator ................CHECK a. Pitot Heat................ON b. Navigation Lights ..............ON c. Landing Light ..............ON d. Annunciator Lights............CHECK - Verify both ALT 1 and ALT 2 caution lights out and positive amps indication for each alternator.
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Page 125: Maximum Power Fuel Flow
Cirrus Design Section 4 SR22 Normal Procedures Maximum Power Fuel Flow Serials w/ Perspective System software load 0764-01: Leaning for Takeoff and Maximum Climb is accomplished at full throttle by leaning the mixture from full rich to the target fuel flow for the given pressure altitude per the table below. -
Page 126: Takeoff
Section 4 Cirrus Design Normal Procedures SR22 Takeoff Power Check: Check full-throttle engine operation early in takeoff run. The engine should run smoothly and turn approximately 2700 RPM. All engine parameters are not in caution or warning ranges. Discontinue takeoff at any sign of rough operation or sluggish acceleration. -
Page 127: Short Field Takeoff
Cirrus Design Section 4 SR22 Normal Procedures Short Field Takeoff 1. Flaps ..................50% 2. Brakes .................. HOLD 3. Power Lever ............FULL FORWARD 4. Mixture ..................SET 5. Engine Parameters ............CHECK 6. Brakes........RELEASE (Steer with Rudder Only) 7. -
Page 128: Cruise
Section 4 Cirrus Design Normal Procedures SR22 Cruise Normal cruising is performed between 55% and 85% power. The engine power setting and corresponding fuel consumption for various altitudes and temperatures can be determined by using the cruise data in Section 5. -
Page 129: Descent
Cirrus Design Section 4 SR22 Normal Procedures Cruise Leaning Exhaust gas temperature (EGT) may be used as an aid for mixture leaning in cruise flight. For “Best Power” use 75% power or less. For “Best Economy” use 65% power or less. To adjust the mixture, lean to... -
Page 130: Landing
Section 4 Cirrus Design Normal Procedures SR22 Landing • 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 malfunction. -
Page 131: After Landing
Cirrus Design Section 4 SR22 Normal Procedures Balked Landing/Go-Around In a balked landing (go around) climb, disengage autopilot, apply full power, then reduce the flap setting to 50%. If obstacles must be cleared during the go around, climb at 75-80 KIAS with 50% flaps. -
Page 132: Shutdown
Section 4 Cirrus Design Normal Procedures SR22 Shutdown 1. Fuel Pump (if used) ..............OFF 2. Throttle ..................IDLE • Caution • Note that the engine hesitates as the switch cycles through the “OFF” position. If the engine does not hesitate, one or both magnetos are not grounded. -
Page 133: Stalls
Cirrus Design Section 4 SR22 Normal Procedures Stalls Aircraft stall characteristics are conventional. Power-off stalls may be accompanied by a slight nose bobbing if full aft stick is held. Power-on stalls are marked by a high sink rate at full aft stick. Power-off stall... -
Page 134: Environmental Considerations
Section 4 Cirrus Design Normal Procedures SR22 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 135 Cirrus Design Section 4 SR22 Normal Procedures 1. Ignition Switch................OFF • WARNING • Use caution when pulling the propeller through by hand. Make sure ignition switch is OFF, keys are out of ignition, and then act as if the engine will start.
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Page 136: Hot Weather Operation
Section 4 Cirrus Design Normal Procedures SR22 Hot Weather Operation Avoid prolonged engine operation on the ground. Fuel BOOST must be ON for engine start and takeoff, and should be ON during climb for vapor suppression which could occur under hot ambient conditions or after extended idle. -
Page 137: Noise Characteristics/Abatement
Cirrus Design Section 4 SR22 Normal Procedures Noise Characteristics/Abatement The certificated noise levels for the aircraft established in accordance with FAR 36 Appendix G are: Configuration Actual Maximum Allowable Hartzel 3-blade Propeller 83.65 dB(A) 88.00 dB(A) PHC-J3YF-1RF/F7694 Hartzel 3-blade Propeller 84.81 dB(A) - Page 138 Section 4 Cirrus Design Normal Procedures SR22 Intentionally Left Blank 4-28 P/N 13772-002 Reissue A...
- Page 139 Cirrus Design Section 5 SR22 Performance Data Section 5: Performance Data Table of Contents Introduction ..................3 Associated Conditions Affecting Performance........ 3 Demonstrated Operating Temperature ........... 3 Airspeed Calibration - Normal Static Source........4 Airspeed Calibration - Alternate Static Source........5 Normal Static Source: Primary Flight Display ........
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Page 141: Introduction
Cirrus Design Section 5 SR22 Performance Data Introduction Performance data in this section are presented for operational planning so that you will know what performance to expect from the airplane under various ambient and field conditions. Performance data are presented for takeoff, climb, and cruise (including range &... -
Page 142: Airspeed Calibration - Normal Static Source
Section 5 Cirrus Design Performance Data SR22 Airspeed Calibration - Normal Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Note • Indicated airspeed values assume zero instrument error. KCAS KIAS Flaps Flaps Flaps... -
Page 143: Airspeed Calibration - Alternate Static Source
Cirrus Design Section 5 SR22 Performance Data Airspeed Calibration - Alternate Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster & Vents .................. ON • Note • Indicated airspeed values assume zero instrument error. -
Page 144: Normal Static Source: Primary Flight Display
Section 5 Cirrus Design Performance Data SR22 Altitude Correction Normal Static Source: Primary Flight Display Conditions: • Power for level flight or maximum continuous, whichever is less. • 3400 LB • Note • Add correction to desired altitude to obtain indicated altitude to fly. - Page 145 Cirrus Design Section 5 SR22 Performance Data Altitude Correction Normal Static Source: Standby Altimeter Conditions: • Power for level flight or maximum continuous, whichever is less. • 3400 LB • Note • Add correction to desired altitude to obtain indicated altitude to fly.
- Page 146 Section 5 Cirrus Design Performance Data SR22 Altitude Correction Alternate Static Source: Primary Flight Display Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster, & Vents .................. ON • Note • Add correction to desired altitude to obtain indicated altitude to fly.
- Page 147 Cirrus Design Section 5 SR22 Performance Data Altitude Correction Alternate Static Source: Standby Altimeter Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster, & Vents.................. ON • Note • Add correction to desired altitude to obtain indicated altitude to fly.
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Page 148: Temperature Conversion
Section 5 Cirrus Design Performance Data SR22 Temperature Conversion To convert from Celsius (°C) to Fahrenheit (°F), find, in the shaded columns, the number representing the temperature value (°C) to be converted. The equivalent Fahrenheit temperature is read to the right. -
Page 149: Outside Air Temperature For Isa Condition
Cirrus Design Section 5 SR22 Performance Data Outside Air Temperature for ISA Condition Press ISA-40°C ISA-20°C ISA+10°C ISA+20°C Feet °C °F °C °F °C °F °C °F °C °F 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000... -
Page 150: Stall Speeds
Section 5 Cirrus Design Performance Data SR22 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 151: Wind Components
Cirrus Design Section 5 SR22 Performance Data Wind Components Example: • Runway Heading ....................10° • Wind Direction....................60° • Wind Velocity....................15 Knots • Note • The max demonstrated crosswind is 20 knots. Value not considered limiting. 0° 10° 20°... -
Page 152: Takeoff Distance
Section 5 Cirrus Design Performance Data SR22 Takeoff Distance Conditions: • Winds........................ Zero • Runway..................Dry, Level, Paved • Flaps......................... 50% • Air Conditioner....................OFF • Power: •Throttle....................Full Open •Mixture ..................Set per Placard Set prior to brake release for short field takeoff. -
Page 153: Takeoff Distance - 3400 Lb
Cirrus Design Section 5 SR22 Performance Data Takeoff Distance - 3400 LB Weight: 3400 LB Headwind: Subtract 10% for each 12 knots Speed at Liftoff: 73 KIAS headwind. Speed over 50 Ft. Obstacle: 78 KIAS Tailwind: Add 10% for each 2 knots tailwind up Flaps: 50% to 10 knots. - Page 154 Section 5 Cirrus Design Performance Data SR22 Takeoff Distance - 2900 LB Weight: 2900 LB Headwind: Subtract 10% for each 12 knots Speed at Liftoff: 70 KIAS headwind. Speed over 50 Ft. Obstacle: 74 KIAS Tailwind: Add 10% for each 2 knots tailwind up Flaps: 50% to 10 knots.
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Page 155: Takeoff Climb Gradient
Cirrus Design Section 5 SR22 Performance Data Takeoff Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps .........................50% • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile. -
Page 156: Takeoff Rate Of Climb
Section 5 Cirrus Design Performance Data SR22 Takeoff Rate of Climb Conditions: • Power....................Full Throttle • Mixture....................... Full Rich • Flaps......................... 50% • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude for unit time expended expressed in Feet per Minute. -
Page 157: Enroute Climb Gradient
Cirrus Design Section 5 SR22 Performance Data Enroute Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .......................Full Rich • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile. -
Page 158: Enroute Rate Of Climb
Section 5 Cirrus Design Performance Data SR22 Enroute Rate of Climb Conditions: • Power....................Full Throttle • Mixture....................As Required • Flaps......................0% (UP) • Airspeed ..................Best Rate of Climb • Note • Rate-of-Climb values shown are change in altitude in feet per unit time expressed in Feet per Minute. -
Page 159: Enroute Rate Of Climb Vs Density Altitude
Cirrus Design Section 5 SR22 Performance Data Enroute Rate of Climb Vs Density Altitude Conditions: • Power ....................Full Throttle • Flaps ......................0% (UP) • Airspeed ..................Best Rate of Climb 17,000 16,000 15,000 14,000 13,000 12,000 11,000 10,000 9,000 8,000... -
Page 160: Time, Fuel And Distance To Climb
Section 5 Cirrus Design Performance Data SR22 Time, Fuel and Distance to Climb Conditions: • Power....................Full Throttle • Mixture................Per Schedule, Section 4 • Fuel Density...................6.0 LB/GAL • Weight ......................3400 LB • Winds........................ Zero • Climb Airspeed ....................Noted •... -
Page 161: Cruise Performance
Cirrus Design Section 5 SR22 Performance Data Cruise Performance Conditions: • Cruise Weight..................... 2900 LB • Winds ....................... Zero • Shaded Cells: Cruise Pwr above 85% not recommended. • Note • Subtract 10 KTAS if nose wheel pant and fairing removed. Lower KTAS by 10% if nose and main wheel pants &... - Page 162 Section 5 Cirrus Design Performance Data SR22 ISA - 30°C ISA + 30°C Press RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH 8000 2700 21.7 19.7 18.6 17.7 2600 21.7 18.8 17.8 17.0 2500 21.7 17.7 16.8 16.0...
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Page 163: Range / Endurance Profile
Cirrus Design Section 5 SR22 Performance Data Range / Endurance Profile Conditions: • Weight ......................3400 LB • Temperature ..................Standard Day • Winds ....................... Zero • Mixture ....................Best Economy • Total Fuel....................81 Gallons • Note • Fuel Remaining For Cruise is equal to 81.0 gallons usable, less climb fuel, less 9.8 gallons for 45 minutes IFR reserve fuel at 47% power (ISA @ 10,000... - Page 164 Section 5 Cirrus Design Performance Data SR22 Range / Endurance Profile (Continued) 65% POWER Mixture: Best Power Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 70.8 15.4 10.3 2000 69.0 15.4 10.5...
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Page 165: Balked Landing Climb Gradient
Cirrus Design Section 5 SR22 Performance Data Balked Landing Climb Gradient Conditions: • Power ....................Full Throttle • Mixture .................... Set per Placard • Flaps ...................... 100% (DN) • Climb Airspeed....................V REF • Note • Balked Landing Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile. -
Page 166: Balked Landing Rate Of Climb
Section 5 Cirrus Design Performance Data SR22 Balked Landing Rate of Climb Conditions: • Power....................Full Throttle • Mixture.................... Set per Placard • Flaps...................... 100% (DN) • Climb Airspeed ....................V REF • Note • Balked Landing Rate of Climb values shown are the full flaps change in altitude for unit time expended expressed in Feet per Minute. -
Page 167: Landing Distance
Cirrus Design Section 5 SR22 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 168 Section 5 Cirrus Design Performance Data SR22 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 169 Cirrus Design Section 6 SR22 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..................
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Page 171: P/N 13772-002
Cirrus Design Section 6 SR22 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 172: Airplane Weighing Form
Section 6 Cirrus Design Weight and Balance Data SR22 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 173: Airplane Weighing Procedures
Cirrus Design Section 6 SR22 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 174 Section 6 Cirrus Design Weight and Balance Data SR22 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 175 Cirrus Design Section 6 SR22 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 13772-002 P/N 13772-002...
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Page 176: Loading Instructions
Section 6 Cirrus Design Weight and Balance Data SR22 Loading Instructions It is the responsibility of the pilot to ensure that the airplane is properly loaded and operated within the prescribed weight and center of gravity limits. The following information enables the pilot to calculate the total weight and moment for the loading. -
Page 177: Weight And Balance Loading Form
Cirrus Design Section 6 SR22 Weight and Balance Data Weight and Balance Loading Form • Note • The Takeoff Condition Weight must not exceed 3400 lb. The Takeoff Condition Moment must be within the Minimum Moment to Maximum Moment range at the Takeoff Condition Weight. -
Page 178: Loading Data
Section 6 Cirrus Design Weight and Balance Data SR22 Loading Data Use the following chart or table to determine the moment/1000 for fuel and payload items to complete the Loading Form. Fuel Fwd Pass Aft Pass Loading Chart Baggage 20.0 40.0... -
Page 179: Moment Limits
Cirrus Design Section 6 SR22 Weight and Balance Data Moment Limits Use the following chart or table to determine if the weight and moment from the completed Weight and Balance Loading Form (Figure 6-3) are within limits. 3400 3200 3000... -
Page 180: Weight & Balance Record
Section 6 Cirrus Design Weight and Balance Data SR22 Weight & Balance Record Use this form to maintain a continuous history of changes and modifications to airplane structure or equipment affecting weight and balance: Serial Num: Reg. Num: Page Weight Change Running Basic Item No. -
Page 181: Equipment List
Cirrus Design Section 6 SR22 Weight and Balance Data Equipment List This list will be determined after the final equipment has been installed in the aircraft. P/N 13772-002 P/N 13772-002 6-13 6-13 Reissue A... - Page 182 Section 6 Cirrus Design Weight and Balance Data SR22 Intentionally Left Blank 6-14 P/N 13772-002 Reissue A...
- Page 183 Cirrus Design Section 7 SR22 Systems Description Section 7: Systems Description Table of Contents Introduction ..................5 Airframe ..................... 6 Fuselage ..................6 Wings....................6 Empennage ..................7 Flight Controls ..................8 Elevator System................8 Aileron System................10 Rudder System ................12 Control Locks................
- Page 184 Section 7 Cirrus Design Systems Description SR22 Engine Controls ................31 Engine Indicating ................32 Engine Lubrication System ............36 Ignition and Starter System............36 Air Induction System ..............36 Engine Exhaust................37 Engine Fuel Injection ..............37 Engine Cooling................37 Propeller ...................
- Page 185 SR22 Systems Description Fire Extinguisher................89 Hour Meters .................. 90 Emergency Egress Hammer............90 Convenience Outlet ..............90 Cirrus Airplane Parachute System ........... 91 System Description ............... 91 Activation Handle ................92 Deployment Characteristics ............93 P/N 13772-002 P/N 13772-002...
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Page 187: Introduction
Cirrus Design Section 7 SR22 Systems Description Introduction This section provides a basic description and operation of the standard airplane and its systems. Optional equipment described within this section is identified as optional. • Note • Some optional equipment may not be described in this section. -
Page 188: Airframe
Section 7 Cirrus Design Systems Description SR22 Airframe Fuselage The airplane’s monocoque fuselage is constructed primarily of composite materials and is designed to be aerodynamically efficient. The cabin area is bounded on the forward side by the firewall at fuselage station 100, and on the rear by the aft baggage compartment bulkhead at fuselage station 222. -
Page 189: Empennage
Cirrus Design Section 7 SR22 Systems Description Empennage The empennage consists of a horizontal stabilizer, a two-piece elevator, a vertical fin and a rudder. All of the empennage components are conventional spar (shear web), rib, and skin construction. The horizontal stabilizer is a single composite structure from tip to tip. -
Page 190: Flight Controls
Section 7 Cirrus Design Systems Description SR22 Flight Controls The airplane uses conventional flight controls for ailerons, elevator and rudder. The control surfaces are pilot controlled through either of two single-handed side control yokes mounted beneath the instrument panel. The location and design of the control yokes allow easy, natural use by the pilot. - Page 191 Cirrus Design Section 7 SR22 Systems Description SR22_FM07_1461 Figure 7-1 Elevator System P/N 13772-002 P/N 13772-002 Reissue A...
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Page 192: Aileron System
Section 7 Cirrus Design Systems Description SR22 Aileron System The ailerons provide airplane roll control. The ailerons are of conventional design with skin, spar and ribs manufactured of aluminum. Each aileron is attached to the wing shear web at two hinge points. - Page 193 Cirrus Design Section 7 SR22 Systems Description SR22_FM07_1462 Figure 7-2 Aileron System P/N 13772-002 P/N 13772-002 7-11 7-11 Reissue A...
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Page 194: Rudder System
Section 7 Cirrus Design Systems Description SR22 Rudder System The rudder provides airplane directional (yaw) control. The rudder is of conventional design with skin, spar and ribs manufactured of aluminum. The rudder is attached to the aft vertical stabilizer shear web at three hinge points and to the fuselage tailcone at the rudder control bell crank. - Page 195 Cirrus Design Section 7 SR22 Systems Description SR22_FM07_1463 Figure 7-3 Rudder System P/N 13772-002 P/N 13772-002 7-13 7-13 Reissue A...
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Page 196: Instrument Panel
Section 7 Cirrus Design Systems Description SR22 Instrument Panel The instrument panel is of all metal construction and is installed in sections so equipment can be easily removed for maintenance. The surrounding glareshield is made of composite material and projects over the instrument panel to reduce reflections on the windshield from lighted equipment and to shield the panel equipment from glare. - Page 197 Cirrus Design Section 7 SR22 Systems Description Legend 1. Cirrus Airframe Parachute System 13. Left Side Console (CAPS) Activation T-Handle Cover · Circuit Breaker Panel 2. Magnetic Compass · Alternate Engine Air 3. Multifunction Display · ELT Remote Switch 4. Fresh Air “Eyeball” Outlet ·...
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Page 198: Flight Instruments
Section 7 Cirrus Design Systems Description SR22 Flight Instruments Flight instruments and annunciations are displayed on the Primary Flight Display (PFD) located directed in front of the pilot. The PFD presents the primary flight instruments arranged in the conventional basic “T” configuration. Standby instruments for airspeed, attitude and altitude are mounted on the LH bolster panel and are on separate power sources than the PFD. - Page 199 Cirrus Design Section 7 SR22 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.
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Page 200: Attitude Indicator
Section 7 Cirrus Design Systems Description SR22 Attitude Indicator The primary attitude indicator is show on the upper center of the PFD and displays pitch, roll, and slip/skid information provided by the Attitude and Heading Reference System (AHRS). Above and below the horizon line, major pitch marks and labels are shown for every 10°, up to 80°. -
Page 201: Airspeed Indicator
Cirrus Design Section 7 SR22 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 202: Altimeter
Section 7 Cirrus Design Systems Description SR22 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 203: Horizontal Situation Indicator
Cirrus Design Section 7 SR22 Systems Description Horizontal Situation Indicator The horizontal situation indicator is displayed along the lower center of the PFD. Heading data is provided by the Attitude and Heading Reference System (AHRS) and the onboard magnetometers. The HSI displays a rotating compass card in a heading-up orientation. -
Page 204: Magnetic Compass
Section 7 Cirrus Design Systems Description SR22 Vertical speed must exceed 100 feet/min before digits will appear in the VSI pointer. If the rate of ascent/descent exceeds 2000 fpm, the pointer appears at the corresponding edge of the tape and the rate appears inside the pointer. - Page 205 Cirrus Design Section 7 SR22 Systems Description SR22_FM07_2935A Figure 7-6 Wing Flaps P/N 13772-002 P/N 13772-002 7-23 7-23 Reissue A...
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Page 206: Landing Gear
Section 7 Cirrus Design Systems Description SR22 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 207 Cirrus Design Section 7 SR22 Systems Description wheel, temperature sensors, and associated hydraulic plumbing and wring. Braking pressure is initiated by depressing the top half of a rudder pedal (toe brake). The brakes are plumbed so that depressing either the pilot’s or copilot’s left or right toe brake will apply the respective (left or right) main wheel brake.
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Page 208: Baggage Compartment
Section 7 Cirrus Design Systems Description SR22 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 209: Seats
Cirrus Design Section 7 SR22 Systems Description Seats The seating arrangement consists of two individually adjustable seats for the pilot and front seat passenger and, Serials w/o 2+1 Rear Seat: two individual rear seats with fold-down seat backs or, Serials w/ 2+1 Rear Seat: a “2+1”... -
Page 210: Seat Belt And Shoulder Harness
Section 7 Cirrus Design Systems Description SR22 bulky cargo extending forward from the baggage compartment. The detent pins are located at the base of the backrest. To fold seat back forward: 1. From the baggage access, lift the carpet panel at lower aft edge of seat to reveal the seat back locking pins (attached to lanyards). - Page 211 Cirrus Design Section 7 SR22 Systems Description Front Seat Inflatable Restraints An inflatable shoulder harness is integral to each front seat harness. The electronic module assembly, mounted below the cabin floor, contains a crash sensor, battery, and related circuitry to monitor the deceleration rate of the airplane.
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Page 212: Cabin Doors
Section 7 Cirrus Design Systems Description SR22 installed using the center seat belt. Three top tether anchors for the child seats are located on the rear bulkhead. To install a child seat: 1. Fasten lower seat attachments to bench seat: a. -
Page 213: Engine
Cirrus Design Section 7 SR22 Systems Description Engine The airplane is powered by a Teledyne Continental IO-550-N, six- cylinder, normally aspirated, fuel-injected engine rated to 310 hp at 2700 RPM. The engine has a 2000-hour Time Between Overhaul (TBO). Dual, conventional magnetos provide ignition. -
Page 214: Engine Indicating
Section 7 Cirrus Design Systems Description SR22 control, depress the center lock button, pull the knob to the open position, and then release the lock button. Pulling the knob opens the alternate air induction door on the engine induction air manifold, bypasses the air filter, and allows warm unfiltered air to enter the engine. - Page 215 Cirrus Design Section 7 SR22 Systems Description Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Engine Instruments LEGEND 1. Percent Power 2. CHT 3. Tachometer 4. EGT 5. Manifold Pressure 6. Oil Temperature and Pressure 7. Alternate Air Control 8.
- Page 216 Section 7 Cirrus Design Systems Description SR22 Tachometer Engine speed (RPM) is shown in the upper mid-left corner of the ENGINE page as both a simulated tachometer and as a digital value. The tachometer pointer sweeps a scale range from 0 to 3000 RPM in 100 RPM increments.
- Page 217 Cirrus Design Section 7 SR22 Systems Description Oil Temperature Oil temperature is shown in the upper right corner of the ENGINE page, opposite the oil pressure scale, as both a simulated temperature gage and as a digital value. The gage pointer sweeps a scale range from 75°F to 250°F in 50°F increments.
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Page 218: Engine Lubrication System
Section 7 Cirrus Design Systems Description SR22 Engine Lubrication System The engine is provided with a wet-sump, high-pressure oil system for engine lubrication and cooling. Oil for engine lubrication is drawn from an eight-quart capacity sump through an oil suction strainer screen and directed through the oil filter to the engine-mounted oil cooler by a positive displacement oil pump. -
Page 219: Engine Exhaust
Cirrus Design Section 7 SR22 Systems Description through the throttle butterfly, into the six-tube engine manifold, and finally through the cylinder intake ports into the combustion chambers. Should the dry induction filter become clogged, a pilot controlled alternate induction air door can be opened, allowing engine operation to continue as described below. -
Page 220: Propeller
Section 7 Cirrus Design Systems Description SR22 Propeller The airplane is equipped with a constant-speed, aluminum-alloy propeller with a three-blade (78" diameter) propeller and governor. The propeller governor automatically adjusts propeller pitch to regulate propeller and engine RPM. The propeller governor senses... -
Page 221: Fuel System
Cirrus Design Section 7 SR22 Systems Description Fuel System An 92-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 47.25-gallon capacity (46- gallon usable) vented integral fuel tank and a fuel collector/sump in each wing, a three position selector valve, an electric fuel pump, and an engine-driven fuel pump. -
Page 222: Fuel Selector Valve
Section 7 Cirrus Design Systems Description SR22 The airplane may be serviced to a reduced capacity to permit heavier cabin loadings. This is accomplished by filling each tank to a tab visible below the fuel filler, giving a reduced fuel load of 30.0 gallons usable in each tank (60 gallons total usable in all flight conditions). - Page 223 Cirrus Design Section 7 SR22 Systems Description ANNUNCIATOR FUEL FUEL QUANTITY VENT VENT FILLER FILLER INDICATOR L. WING TANK R. WING TANK L. WING R. WING COLLECTOR COLLECTOR CHECK CHECK VALVE VALVE SELECTOR VALVE FLAPPER FLAPPER VALVE VALVE DRAIN (5 PLACES)
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Page 224: Fuel Indicating
Section 7 Cirrus Design Systems Description SR22 Fuel Indicating Fuel quantity is measured by float-type quantity sensors installed in each fuel tank and displayed on the Fuel Quantity Gage. • Caution • When the fuel tanks are 1/4 full or less, prolonged uncoordinated flight such as slips or skids can uncover the fuel tank outlets. - Page 225 Cirrus Design Section 7 SR22 Systems Description Serials 3849 and subs: A dual reading fuel quantity gage is displayed on the Engine Strip along the left edge of the MFD and in the Fuel Qty block of the ENGINE page. In the case of an electronic display failure (backup mode), all essential fuel information is displayed on the Engine Strip along the left edge of the PFD.
- Page 226 Section 7 Cirrus Design Systems Description SR22 Fuel System Annunciations Fuel system health, caution, and warning messages are displayed in color-coded text in the Crew Alerting System (CAS) window located to the right of the Altimeter and Vertical Speed Indicator. In combination...
- Page 227 Cirrus Design Section 7 SR22 Systems Description Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) 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.
- Page 228 Section 7 Cirrus Design Systems Description SR22 Fuel System Indication LEGEND 1. Fuel Flow Gage 2. Fuel Calculations: ·Fuel At Destination (Totalizer) ·Fuel Used (Totalizer) ·Fuel Remaining (Totalizer) ·Time Remaining (Totalizer) ·Fuel Range (Totalizer) ·Nautical Miles Per Gallon (Totalizer) 3. Fuel Quantity Gage (Float Sensor) 4.
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Page 229: Electrical System
Cirrus Design Section 7 SR22 Systems Description Electrical System The airplane is equipped with a two-alternator, two-battery, 28-volt direct current (VDC) electrical system designed to reduce the risk of electrical system faults. The system provides uninterrupted power for avionics, flight instrumentation, lighting, and other electrically operated and controlled systems during normal operation. - Page 230 Section 7 Cirrus Design Systems Description SR22 LANDING 100A ALT 1 LIGHT ALT 1 7.5A VOLT REG RELAY LANDING LIGHT SWITCH EXTERNAL ALT 1 POWER RELAY SWITCH EXTERNAL POWER 125A BAT 1 BAT 1 BAT 1 RELAY SWITCH STARTER STARTER...
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Page 231: Power Distribution
Cirrus Design Section 7 SR22 Systems Description Power Distribution Power is supplied to the airplane circuits through three distribution buses contained in the MCU: Main Distribution Bus 1, Main Distribution Bus 2, and the Essential Distribution Bus. The three distribution buses power the associated buses on the circuit breaker panel. -
Page 232: Electrical System Protection
Section 7 Cirrus Design Systems Description SR22 Main Distribution Bus 2 The output from ALT 2 is connected to the Main Distribution Bus 2 in the MCU through an 80-amp fuse. Main Distribution Bus 2 powers three circuit breaker buses through 30-amp fuses located in the MCU: •... - Page 233 Cirrus Design Section 7 SR22 Systems Description Main Distribution Bus 1 or Main Distribution Bus 2 in the MCU. In the case of both alternators failing, BAT 1 is connected directly to the Essential Distribution Bus in the MCU and will power ESS BUS 1 and ESS BUS 2.
- Page 234 Section 7 Cirrus Design Systems Description SR22 AVIONICS A/C COND PROTECTION STDBY ALT1 ALT2 ATTD #2 ENGINE MFD #2 SERVO INSTR STALL CABIN LIGHTS CAMERA WARNING / OXYGEN 12V DC ROLL FUEL QTY OUTLET TRIM PITCH A/C COMPR MFD #1...
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Page 235: Electrical System Control
Cirrus Design Section 7 SR22 Systems Description Electrical System Control The rocker type electrical system MASTER switches are ‘on’ in the up position and ‘off’ in the down position. The switches, labeled BAT 2, BAT 1, ALT 1, ALT 2 are located in the bolster switch panel immediately below the instrument panel. -
Page 236: Ground Service Receptacle
Section 7 Cirrus Design Systems Description SR22 Avionics Power Switch A rocker switch, labeled AVIONICS, controls electrical power from the circuit breaker panel (MAIN BUS 1) to the Avionics Bus. The switch is located next to the ALT and BAT Master switches. Typically, the switch is used to energize or de-energize all non-essential avionics on the AVIONICS bus simultaneously. -
Page 237: Electrical Indicating
Cirrus Design Section 7 SR22 Systems Description Electrical Indicating Electrical system information is displayed as bar graphs and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), Battery 1 ampere output and Essential Bus voltage output are displayed along the LH edge of the display. - Page 238 Section 7 Cirrus Design Systems Description SR22 Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Electrical System Indication 8 9 10 Electrical and Lighting Controls LEGEND 1. Essential & Main Bus Voltage 7. Avionics 8. Navigation 2. Alternator & Battery Current 9.
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Page 239: Lighting Systems
Cirrus Design Section 7 SR22 Systems Description Lighting Systems Exterior Lighting The airplane is equipped with wing tip navigation lights with integral anti-collision strobe lights and recognition Lights. The landing light is located in the lower cowl. Navigation Lights The airplane is equipped with standard wing tip navigation lights. The lights are controlled through the NAV light switch on the instrument panel bolster. -
Page 240: Interior Lighting
Section 7 Cirrus Design Systems Description SR22 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 241 Cirrus Design Section 7 SR22 Systems Description Panel Flood Lights A string of red LEDs mounted under the instrument panel glareshield provide flood lighting for the instrument panel. The lights are controlled through the PANEL dimmer control on the instrument panel bolster.
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Page 242: Environmental System
Section 7 Cirrus Design Systems Description SR22 Environmental System • Note • To facilitate faster cabin cooling, prior to engine start leave the cabin doors open for a short time to allow hot air to escape. Standard cabin heating and ventilation is accomplished by supplying conditioned air from the heat exchanger for heating and windshield defrost and fresh outside air for ventilation. -
Page 243: Distribution
Cirrus Design Section 7 SR22 Systems Description Distribution Ventilation and cooling is provided by ducting fresh air from a NACA inlet on the RH lower cowl to the mixing chamber located on the lower RH portion of the firewall. Depending on operating mode and... -
Page 244: Cooling
Section 7 Cirrus Design Systems Description SR22 Cooling Standard cabin cooling is provided by ram air admitted through the NACA inlet on the RH cowl to the fresh air valve, mounted to the forward side of the firewall. When the fresh air valve is open, the air flows into the cabin mixing chamber. - Page 245 Cirrus Design Section 7 SR22 Systems Description RAM AIR RAM AIR HOT AIR VALVE MIXING CHAMBER HEAT EXCHANGER FRESH AIR VALVE AIR FLOW VALVE CONTROL PANEL SERVO MOTOR FLOOR AIRFLOW WINDSHIELD DIFFUSER PANEL AIRFLOW DISTRIBUTION MANIFOLD AIR GASPER ASSEMBLY FOOT-WARMER...
- Page 246 Section 7 Cirrus Design Systems Description SR22 RAM AIR RAM AIR HOT AIR VALVE MIXING CHAMBER HEAT EXCHANGER COMPRESSOR FRESH AIR VALVE WINDSHIELD AIR FLOW VALVE DIFFUSER SERVO MOTOR FLOOR AIRFLOW CONTROL PANEL PANEL AIRFLOW DISTRIBUTION MANIFOLD GASPER EVAPORATOR ASSEMBLY...
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Page 247: Airflow Selection
Cirrus Design Section 7 SR22 Systems Description Airflow Selection The airflow selector on the system control panel regulates the volume of airflow allowed into the cabin distribution system. When the airflow selector is moved past the OFF position an electro-mechanical linkage actuates a valve in the mixing chamber on the forward firewall to the full open position. -
Page 248: Temperature Selection
Section 7 Cirrus Design Systems Description SR22 Temperature Selection The temperature selector is electrically linked to the hot and cold air valves. Rotating the selector simultaneously opens and closes the two valves, permitting hot and cold air to mix and enter the distribution system. - Page 249 Cirrus Design Section 7 SR22 Systems Description Rotating the selector controls the volume of airflow allowed into the cabin distribution system through use of an electro-mechanical linkage to a butterfly (hot air) valve in the mixing chamber on the forward firewall.
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Page 250: Stall Warning System
Section 7 Cirrus Design Systems Description SR22 Stall Warning System The airplane is equipped with an electro-pneumatic stall warning system to provide audible warning of an approach to aerodynamic stall. The system consists of an inlet in the leading edge of the right... -
Page 251: Pitot Heat Switch
Cirrus Design Section 7 SR22 Systems Description Pitot-Static System The Pitot-Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage. The Pitot heat is pilot controlled through a panel-mounted switch. An internally mounted alternate static pressure source provides backup static pressure should that the primary static source becomes blocked. - Page 252 Section 7 Cirrus Design Systems Description SR22 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...
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Page 253: Avionics
Cirrus Design Section 7 SR22 Systems Description Avionics Perspective Integrated Avionics System The Perspective Integrated Avionics System provides advanced cockpit functionality and improved situational awareness through the use of fully integrated flight, engine, communication, navigation and monitoring equipment. The system consists of the following components: •... - Page 254 Section 7 Cirrus Design Systems Description SR22 XM RADIO RECEIVER (optional) XM SATELLITE DATA LINK RECEIVER (optional) FMS KEYBOARD MAG 1 MAG 2 AHRS 1 AHRS 2 AUTOPILOT (optional) MODE CONTROLLER (optional) IRIDIUM GLOBAL SATELLITE DATALINK AIR DATA (optional) COMPUTER 2...
- Page 255 Cirrus Design Section 7 SR22 Systems Description GDU Primary Flight Display The Primary Flight Display, located directly in front of the pilot, is intended to be the primary display of flight parameter information (attitude, airspeed, heading, and altitude) during normal operations.
- Page 256 Section 7 Cirrus Design Systems Description SR22 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 257 Cirrus Design Section 7 SR22 Systems Description 3 4 5 6 7 8 9 13 14 15 19 20 21 Legend 1. Soft Keys 11. NAV Transceiver Selection & Tune 2. PFD 12. MFD 3. PFD Range/Pan Joystick 13. PFD Direct-to-Course 4.
- Page 258 Section 7 Cirrus Design Systems Description SR22 22 23 25 26 27 28 29 30 31 GARMIN IDENT FMS/XPDR RANGE MENU XPDR COM/NAV PROC DFLT MAP PUSH SYNC PUSH PUSH EMERG CRSR/1-2 PUSH CTR ALT SEL BKSP PUSH SYNC Flight Management System Keyboard Legend 22.
- Page 259 Cirrus Design Section 7 SR22 Systems Description GIA 63W Integrated Avionics Units The Integrated Avionics Units, located behind the MFD and instrument panel, function as the main communication hub, linking all Integrated Avionics System components with the PFD. Each Integrated Avionics...
- Page 260 Section 7 Cirrus Design Systems Description SR22 GMA 347 or 350 Audio Panel with Marker Beacon Receiver The 347 or 350 Audio Panel, installed on the center console below the Flight Management System Keyboard, integrates NAV/COM digital audio, intercom marker beacon controls.
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Page 261: Optional Avionics
Cirrus Design Section 7 SR22 Systems Description Optional Avionics GFC 700 3-Axis Autopilot and GMC 705 Autopilot Controller Refer to latest revision of AFM Supplement 13772-135 GFC 700 Automatic Flight Control System for operating information. GTX 33 Mode S Transponder... - Page 262 Section 7 Cirrus Design Systems Description SR22 GDL 69/69A XM Satellite Weather and Radio The Data Link Satellite Receiver, mounted in the empennage avionics compartment, receives and transmits real-time weather information to the MFD and PFD. If GDL 69A option is installed, this unit also...
- Page 263 Cirrus Design Section 7 SR22 Systems Description Stormscope WX-500 Weather Mapping Sensor The Stormscope WX-500 System detects electrical discharges associated with thunderstorms and displays the activity on the MFD. The system consists of an antenna located on top of the fuselage and a processor unit mounted under the aft baggage floor.
- Page 264 Section 7 Cirrus Design Systems Description SR22 DME/ADF circuit breaker on AVIONICS BUS. Refer to the Perspective Integrated Avionics System Pilot’s Guide for a general description of the system and its operating modes. Refer to the Bendix/King DME System Pilot’s Guide for a detailed discussion of the system.
- Page 265 Cirrus Design Section 7 SR22 Systems Description Max Viz Enhanced Vision System The Enhanced Vision System is an electro-optical system that uses a Long-Wave Infrared (IR) camera. Infrared is particularly effective at night, smoke, haze, and smog in addition to a broad spectrum of rain, snow, and radiation-type fog.
- Page 266 Section 7 Cirrus Design Systems Description SR22 LEGEND 1. AHRS 1 2. Integrated Avionics Unit 1 3. AHRS 2 4. Avionics Cooling Fan 5. Integrated Avionics Unit 2 6. Engine Airframe Unit 7. Air Data Computer 2 (opt) 8. Air Data Computer 1 9.
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Page 267: Avionics Support Equipment
Cirrus Design Section 7 SR22 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 268 Section 7 Cirrus Design Systems Description SR22 Headset and Microphone Installation Serials 3026 thru 3827: The airplane is equipped with provisions for four Active Noise Reduction (ANR) and four conventional (MIC/ HEADPHONES) headsets. Headset jacks for the pilot and front seat passenger are located in the map case and on the aft portion of the center console for the rear passengers.
- Page 269 Cirrus Design Section 7 SR22 Systems Description Cell Phone Input Jack Serials w/ GMA 347: One 2.5 mm cell phone jack (CELL PHONE INPUT) is provided on the aft portion of the center console near the convenience outlet and is distributed by the TEL selection on the audio panel.
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Page 270: Cabin Features
Section 7 Cirrus Design Systems Description SR22 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 271 Cirrus Design Section 7 SR22 Systems Description b. Disconnect fixed antenna lead from front of unit. c. Disconnect lead from remote switch and indicator unit. d. Loosen attach straps and remove transmitter unit and portable antenna. e. Attach portable antenna to antenna jack on front of unit.
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Page 272: Hour Meters
Section 7 Cirrus Design Systems Description SR22 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 273: Cirrus Airplane Parachute System
Systems Description Cirrus Airplane Parachute System The airplane is equipped with a Cirrus Airplane Parachute System (CAPS) designed to bring the airplane and its occupants to the ground in the event of a life-threatening emergency. The system is intended to... -
Page 274: Activation Handle
Section 7 Cirrus Design Systems Description SR22 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 275: Deployment Characteristics
Cirrus Design Section 7 SR22 Systems Description 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 276 Section 7 Cirrus Design Systems Description SR22 seats and landing gear are designed to accommodate this stress, occupants must prepare for it in accordance with Section 3 - CAPS Deployment Checklist. • Note • The CAPS is designed to work in a variety of airplane attitudes, including spins.
- Page 277 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 278 Section 8 Cirrus Design Handling and Servicing SR22 Intentionally Left Blank P/N 13772-002 Reissue A...
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Page 279: 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 280: 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 281: Airplane Records And Certificates
Cirrus Design Section 8 SR22 Handling and Servicing Airplane Records and Certificates The Federal Aviation Administration (FAA) requires that certain data, certificates, and licenses be displayed or carried aboard the airplane at all times. Additionally, other documents must be made available upon request. -
Page 282: 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 283: 100-Hour Inspection
In lieu of the above requirements, an airplane may be inspected using a Progressive Inspection Program in accordance with the Federal Aviation Regulation Part 91.409. The Cirrus Design Progressive Inspection Program provides for the complete inspection of the airplane utilizing a five-phase cyclic inspection program. -
Page 284: Pilot Performed Preventative Maintenance
Section 8 Cirrus Design Handling and Servicing SR22 Pilot Performed Preventative Maintenance The holder of a Pilot Certificate issued under FAR Part 61 may perform certain preventive maintenance described in FAR Part 43, Appendix A. This maintenance may be performed only on an aircraft that the pilot owns or operates and which is not used in air carrier service. - Page 285 Cirrus Design Section 8 SR22 Handling and Servicing • Replace any hose connection, except hydraulic connections, with replacement hoses. • Clean or replace fuel and oil strainers, as well as replace or clean filter elements. • Replace prefabricated fuel lines.
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Page 286: Ground Handling
Section 8 Cirrus Design Handling and Servicing SR22 Ground Handling Application of External Power A ground service receptacle, located just aft of the cowl on the left side of the airplane, permits the use of an external power source for cold weather starting and maintenance procedures. -
Page 287: Towing
Cirrus Design Section 8 SR22 Handling and Servicing Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed in the rear baggage compartment or by power equipment that will not damage or excessively strain the nose gear assembly. -
Page 288: Taxiing
Section 8 Cirrus Design Handling and Servicing SR22 Taxiing Before attempting to taxi the airplane, ground personnel should be instructed and authorized by the owner to taxi the airplane. Instruction should include engine starting and shutdown procedures in addition to taxi and steering techniques. -
Page 289: Parking
Cirrus Design Section 8 SR22 Handling and Servicing Parking The airplane should be parked to protect the airplane from weather and to prevent it from becoming a hazard to other aircraft. The parking brake may release or exert excessive pressure because of heat buildup after heavy braking or during wide temperature swings. -
Page 290: Tiedown
Section 8 Cirrus Design Handling and Servicing SR22 Tiedown The airplane should be moored for immovability, security and protection. FAA Advisory Circular AC 20-35C, Tiedown Sense, contains additional information regarding preparation for severe weather, tiedown, and related information. The following procedures should be used for the proper mooring of the airplane: 1. - Page 291 Cirrus Design Section 8 SR22 Handling and Servicing Raise Airplane • Caution • Do not jack the aircraft outside or in open hangar with winds in excess of 10 mph. The empty CG is forward of the wing jacking points. To prevent...
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Page 292: Servicing
Section 8 Cirrus Design Handling and Servicing SR22 Servicing Landing Gear Servicing The main landing gear wheel assemblies use 15 x 6.00 x 6, six-ply rating tires and tubes. The nose wheel assembly uses a 5.00 x 5 six- ply rating, type III tire and tube. Always keep tires inflated to the rated pressure to obtain optimum performance and maximum service. - Page 293 Cirrus Design Section 8 SR22 Handling and Servicing Brake Inspection The brake assemblies and linings should be checked at every oil change (50 hours) for general condition, evidence of overheating, and deterioration. Serials 0002 thru 3450 before SB 2X-05-01: At every annual/100-hour inspection the brakes should be disassembled, the brake linings should be checked and the O-rings replaced.
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Page 294: Tire Inflation
Section 8 Cirrus Design Handling and Servicing SR22 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 295 Cirrus Design Section 8 SR22 Handling and Servicing sooner under unfavorable operating conditions. The following grades are recommended for the specified temperatures at sea level (SL): Ambient Air Temperature (SL) Single Viscosity Multi-Viscosity All Temperatures -— 20W-60 20W-50 15W-50 Below 40°F...
- Page 296 Section 8 Cirrus Design Handling and Servicing SR22 Product Supplier Aeroshell (R) W Shell Australia Aeroshell Oil W Shell Canada Ltd. Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50 Aeroshell Oil W Shell Oil Company Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50...
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Page 297: Fuel System Servicing
Cirrus Design Section 8 SR22 Handling and Servicing Fuel System Servicing Fuel Filtration Screen/Element Airplane Serials 3026 thru 3420 before SB 2X-28-08 R1: After the first 25 hours of operation, then every 100-hours or as conditions dictate, the fuel filter element in the gascolator must be replaced. At every oil change, Verify red pop-up tab on gascolator is not visible. -
Page 298: Fuel Contamination And Sampling
Section 8 Cirrus Design Handling and Servicing SR22 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 299: Draining Fuel System
Cirrus Design Section 8 SR22 Handling and Servicing If sampling reveals contamination, the gascolator and tank drains must be sampled again repeatedly until all contamination is removed. It is helpful to gently rock the wings and lower the tail slightly to move contaminates to the drain points for sampling. -
Page 300: Battery Service
Section 8 Cirrus Design Handling and Servicing SR22 Battery Service The aircraft is delivered with a maintenance free, rechargeable, sealed, lead acid primary battery. Battery #1 is mounted to the forward right side of the firewall and access is gained by removing the upper cowl. -
Page 301: Cleaning And Care
Cirrus Design Section 8 SR22 Handling and Servicing Cleaning and Care Cleaning Exterior Surfaces • Caution • Airplane serials with Ice Protection System: Do not wax leading edge porous panels. Refer to Section 9: Log of Supplements of this handbook for instructions and limitations for airplanes equipped with the Ice Protection System. - Page 302 Section 8 Cirrus Design Handling and Servicing SR22 Cleaning Product Cleaning Application Supplier Pure Carnauba Wax Fuselage Exterior Any Source Mothers California Gold Fuselage Exterior Wal-Mart Stores Pure Carnauba Wax RejeX Fuselage Exterior Corrosion Technologies WX/Block System Fuselage Exterior Wings and Wheels...
- Page 303 Cirrus Design Section 8 SR22 Handling and Servicing Windscreen and Windows Before cleaning an acrylic window, rinse away all dirt particles before applying cloth or chamois. Never rub dry acrylic. Dull or scratched window coverings may be polished using a special acrylic polishing paste.
- Page 304 Section 8 Cirrus Design Handling and Servicing SR22 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.
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Page 305: Cleaning Interior Surfaces
Cirrus Design Section 8 SR22 Handling and Servicing 3. Allow the solvent to remain on the gear from five to ten minutes. Then rinse the gear with additional solvent and allow to dry. 4. Remove the cover from the wheel and remove the catch pan. - Page 306 Section 8 Cirrus Design Handling and Servicing SR22 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 307 Cirrus Design Section 8 SR22 Handling and Servicing 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 308 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 309 Cirrus Design Section 9 SR22 Log of Supplements Section 9: Log of Supplements Inst Part Number Title Rev Date ___ 13772-109 R2 Approved Oxygen Systems 01-06-10 ___ 13772-114 R1 SR22 / SR22T Airplanes Registered in Canada 07-07-10 ___ 13772-115 R10Basic Ice Protection System...
- Page 310 This Log of Supplements shows all Cirrus Design Supplements available for the aircraft at the corresponding date of the revision level shown in the lower left corner. A check mark in the Part Number column indicates that the supplement is applicable to the POH.
- Page 311 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 312 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 313 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: DE-ICING FLUID REFER TO AFM FOR APPROVED DE-ICING FLUIDS Serials 22-2334, 22-2420, 22-2438 & subs, 22T-0001 & subs;...
- Page 314 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 315 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 316 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 317 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 318 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 319 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 320 Section 9 Cirrus Design Supplements SR22 / SR22T Loading Data - Serials with G3 Wing Mom/ Mom/ 1000@ 1000@ Weight Weight Gallons Fluid Gallons Fluid Tank 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 321 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 322 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...
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Page 323: 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 324 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 325 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 326 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 327 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 328 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 329 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 330 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 331 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 332 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 333 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 334 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 335 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 336 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 337 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 338 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 8 of 8 P/N 13772-131 Revision 02: 01-06-10...
- Page 339 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 340 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 341 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 342 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 343 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.
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Page 344: 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 345 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 346 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 347 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 348 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 349 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 350 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 351 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 352 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 353 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 354 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 355 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 356 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 357 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 358 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 359 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 360 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 361 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.
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Page 362: 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 363 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 364 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 365 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 366 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 367 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 368 Section 9 Cirrus Design Supplements SR22 / SR22T 6000 Feet Pressure Altitude ISA -30°C (-27°C) ISA (3°C) ISA + 30°C (33°C) KTAS KTAS KTAS 2500 22.5 18.1 17.1 2500 21.5 17.0 16.1 2500 20.5 15.9 15.1 2500 19.5 14.9 14.1 8000 Feet Pressure Altitude ISA -30°C (-31°C)
- Page 369 Cirrus Design Section 9 SR22 / SR22T Supplements Range is reduced by a maximum of 2% as a result of the Anti-Ice System installation. Residual ice on unprotected airplane surfaces can cause a loss in rate of climb of approximately 50%.
- Page 370 Section 9 Cirrus Design Supplements SR22 / SR22T 55% POWERMixture: Best Power Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 81.8 13.1 2000 81.1 13.1 4000 80.4 13.1 6000 79.7 13.1 8000 79.0...
- Page 371 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 372 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 373 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 374 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 obstacle to tailwind up to 10 knots.
- Page 375 Cirrus Design Section 9 SR22 / SR22T Supplements Section 6 - Weight & Balance Weight and Balance Refer to Section 6 - of the basic POH for current weight and balance data. Use the following table to determine the Moment/1000 for deicing fluid to complete the Loading Form in the Weight and Balance Section of the basic POH.
- Page 376 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 377 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 378 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 379 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 380 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 381 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 382 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 383 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 384 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 385 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 386 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 387 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 388 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 389 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 390 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 391 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 392 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 393 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 394 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 395 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 396 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 397 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 398 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 399 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 400 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 401 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 402 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 403 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 404 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 405 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 406 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 407 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 408 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 409 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 410 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 411 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 412 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 413 Cirrus Design Section 9 SR22 / SR22T Supplements to a nose-up pitch to aggressively return to original altitude or glidepath/slope. 2. Disengage Autopilot via AP DISC and manually fly. 3. Change Autopilot modes to one in which the AFCS can maintain (such as VS with a negative rate).
- Page 414 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 415 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 416 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 417 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 418 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 419 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 420 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 421 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 422 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 6 of 6 P/N 13772-136 Revision 01: 01-06-10...
- Page 423 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 424 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 425 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 426 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 427 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 428 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 429 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 430 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 431 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 432 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 433 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 434 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 435 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 436 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 437 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 438 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 439 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 440 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.
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Page 441: 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 442 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 443 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 444 Section 9 Cirrus Design Supplements SR22 / SR22T Autopilot Disconnect Switch 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 445 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 446 Section 9 Cirrus Design Supplements SR22 / SR22T Intentionally Left Blank 24 of 24 P/N 13772-140 Revision 02: 09-20-12...
- Page 447 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 448 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 449 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 450 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 451 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 452 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 453 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 454 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 455 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 456 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 457 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 458 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 459 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 460 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 461 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 462 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 463 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 464 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 465 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 466 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 467 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 468 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 469 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 470 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 471 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 472 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 473 SR22 Safety Information Section 10: Safety Information Table of Contents Introduction ..................3 Cirrus Airframe Parachute System (CAPS) ........4 Deployment Scenarios..............4 General Deployment Information ............ 6 Landing Considerations ..............7 Taxiing, Steering, and Braking Practices ......... 10 Operating Practices ..............10 Brake Maintenance ...............
- Page 474 Section 10 Cirrus Design Safety Information SR22 Intentionally Left Blank 10-2 P/N 13772-002 Reissue A...
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Page 475: Introduction
Cirrus Design Section 10 SR22 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 476: Cirrus Airframe Parachute System (Caps)
Safety Information SR22 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 477 Cirrus Design Section 10 SR22 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.
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Page 478: General Deployment Information
Section 10 Cirrus Design Safety Information SR22 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 479: Landing Considerations
Cirrus Design Section 10 SR22 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 480 Section 10 Cirrus Design Safety Information SR22 • 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 481 Cirrus Design Section 10 SR22 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.
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Page 482: Taxiing, Steering, And Braking Practices
Safety Information SR22 Taxiing, Steering, and Braking Practices Cirrus aircraft use a castering nose wheel and rely on aerodynamic forces and differential braking for directional control while taxiing. Proper braking practices are therefore critical to avoid potential damage to the brakes. -
Page 483: Brake Maintenance
Cirrus Design Section 10 SR22 Safety Information • Use only as much power (throttle) as is necessary to achieve forward movement. Keep in mind, any additional power added with the throttle will be absorbed in the brakes to maintain constant speed. - Page 484 Section 10 Cirrus Design Safety Information SR22 Intentionally Left Blank 10-12 P/N 13772-002 Reissue A...
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