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CIRRUS DESIGN SR20 Pilot Operating Handbook

CIRRUS DESIGN SR20 Pilot Operating Handbook

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PILOT'S OPERATING HANDBOOK

AND FAA APPROVED

AIRPLANE FLIGHT MANUAL

for the CIRRUS DESIGN SR20

Aircraft Serials 2220, 2339 and Subsequent with

Cirrus Perspective+ Avionics System

FAA Approved in Normal Category based on 14 CFR 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 MANUAL INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO

THE PILOT BY 14 CFR 23 AND ADDITIONAL INFORMATION PROVIDED BY

CIRRUS AIRCRAFT AND CONSTITUTES THE FAA APPROVED AIRPLANE

FLIGHT MANUAL.

Model - Serial #:

Registration #:

P/N 11934-005

Cover Page-i

Reissue A

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Summary of Contents for CIRRUS DESIGN SR20

Page 1 PILOT’S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL for the CIRRUS DESIGN SR20 Aircraft Serials 2220, 2339 and Subsequent with Cirrus Perspective+ Avionics System FAA Approved in Normal Category based on 14 CFR 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.
Page 2 Copyright © 2019 - All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811 Cover Page-ii P/N 11934-005 Reissue A...
Page 3 IRRUS ESIGN IRPLANE LIGHT ANUAL SR20 FFECTIVE AGES List of Effective Pages Use this page to determine the current effective date for each page in the AFM. Supplements are issued individually and are controlled by the Log of Supplements Page in Section 9.
Page 4 IRRUS ESIGN IRPLANE LIGHT ANUAL SR20 FFECTIVE AGES List of Effective Pages (Cont.) Page Status Page Status Page Status Reissue A 5-30 Reissue A 7-37 Reissue A Reissue A 5-31 Reissue A 7-38 Reissue A Reissue A 5-32 Reissue A...
Page 5 IRRUS ESIGN IRPLANE LIGHT ANUAL SR20 FFECTIVE AGES List of Effective Pages (Cont.) Page Status Page Status Page Status 7-92 Reissue A 7-93 Reissue A 7-94 Reissue A 7-95 Reissue A 7-96 Reissue A Reissue A Reissue A Reissue A...
Page 6 IRRUS ESIGN IRPLANE LIGHT ANUAL SR20 FFECTIVE AGES Intentionally Left Blank LOEP-4 P/N 11934-005 Reissue A...
Page 7 IRRUS ESIGN RONTMATTER SR20 OREWORD Foreword This Pilot’s Operating Handbook (POH) has been prepared by Cirrus to familiarize operators with the aircraft. Read this POH carefully. It provides operational procedures that will ensure the operator obtains the perfor- mance published in the manual, data designed to allow the most efficient and safe use of the airplane, and basic information to assist in maintaining the airplane in airworthy condition.
Page 8 RONTMATTER IRRUS ESIGN SR20 OREWORD The data presented in this POH is the result of extensive flight tests and is approved by the Federal Aviation Administration. However, as new proce- dures or performance data are developed, the POH will be revised.
Page 9 IRRUS ESIGN RONTMATTER SR20 UPPLEMENTS Supplements The Supplements section (Section 9) of this POH contains FAA Approved Supplements necessary to safely and efficiently operate the airplane when equipped with optional equipment not provided with the standard airplane or not included in the POH. Supplements are essentially “mini-handbooks”...
Page 10 RONTMATTER IRRUS ESIGN SR20 ARNINGS AUTIONS OTES Intentionally Left Blank Frontmatter-4 P/N 11934-005 Reissue A...
Page 11: Table Of Contents
1: G IRRUS ESIGN ECTION ENERAL SR20 Section 1: General Table of Contents Introduction..................3 The Airplane ..................7 Engine ....................7 Propeller .................... 7 Hartzell .................... 7 Fuel ....................7 Approved Fuel Grades ..............7 Oil ...................... 8 Maximum Certificated Weights............8 Cabin and Entry Dimensions.............
Page 12 1: G ECTION ENERAL IRRUS ESIGN SR20 Intentionally Left Blank P/N 11934-005 Reissue A...
Page 13: Introduction
1: G IRRUS ESIGN ECTION ENERAL SR20 NTRODUCTION 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 14 1: G ECTION ENERAL IRRUS ESIGN SR20 NTRODUCTION Figure 1-1: Airplane Three View 26.0 ft 7.92 m 8.9 ft 2.71 m NOTE: • Wing span includes position and strobe lights. 38.3 ft 11.67 m 74 inches 3-BLADE 188 cm 9.1 ft SR20_FM01_5314 2.8 m...
Page 15 1: G IRRUS ESIGN ECTION ENERAL SR20 NTRODUCTION Figure 1-2: Airplane Interior Dimensions 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 SR20_FM01_5316 Location Length Width...
Page 16 1: G ECTION ENERAL IRRUS ESIGN SR20 NTRODUCTION Figure 1-3: Turning Radius 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.
Page 17: The Airplane
1: G IRRUS ESIGN ECTION ENERAL SR20 IRPLANE The Airplane Engine Number of Engines .................... 1 Number of Cylinders ..................4 Engine Manufacturer ............Lycoming Engines Engine Model .................IO-390-C3B6 Engine Metering ................Fuel Injected Engine Cooling .................. Air Cooled Engine Type..........Horizontally Opposed, Direct Drive Horsepower Rating............
Page 18: Oil
1: G ECTION ENERAL IRRUS ESIGN SR20 IRPLANE Oil Capacity (Sump)............7 U.S. Quarts (6.6 L) Refer to Section 2, Powerplant Limitations, for approved oil grades. Maximum Certificated Weights Maximum Gross for Takeoff..........3150 lb (1429 kg) Maximum Baggage Compartment Loading......130 lb (59 kg)
Page 19: Terminology
1: G IRRUS ESIGN ECTION ENERAL SR20 IRPLANE Terminology Table 1: General Airspeed Terminology General Airspeed Terminology Terminology Definition 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 20 1: G ECTION ENERAL IRRUS ESIGN SR20 IRPLANE General Airspeed Terminology (Continued) Terminology Definition Stalling Speed is minimum steady flight speed at which S 50% the aircraft is controllable with 50% flaps. Stalling Speed is the minimum steady flight speed at...
Page 21 1: G IRRUS ESIGN ECTION ENERAL SR20 IRPLANE Meteorological Terminology (Continued) Terminology Definition Mean Sea Level is the average height of the surface of the sea for all stages of tide. In this Handbook, altitude given as MSL is the altitude above the mean sea level. It is the altitude read from the altimeter when the altimeter’s barometric adjustment has been set to the...
Page 22 1: G ECTION ENERAL IRRUS ESIGN SR20 IRPLANE Table 4: Performance and Flight Planning Terminology Performance and Flight Planning Terminology Terminology Definition One “g” is a quantity of acceleration equal to that of earth’s gravity. Demonstrated Demonstrated Crosswind Velocity is the velocity of...
Page 23 1: G IRRUS ESIGN ECTION ENERAL SR20 IRPLANE Table 5: Weight and Balance Terminology Weight and Balance Terminology Terminology Definition Reference Datum Reference Datum is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. Tare Tare is the weight of all items used to hold or position the airplane on the scales for weighing.
Page 24 1: G ECTION ENERAL IRRUS ESIGN SR20 IRPLANE Weight and Balance Terminology (Continued) Terminology Definition Maximum Ramp Maximum Ramp Weight is the maximum weight Weight approved for ground maneuver and includes the weight of the fuel used for startup and taxi.
Page 25 2: L IRRUS ESIGN ECTION IMITATIONS SR20 Section 2: Limitations Table of Contents Introduction..................3 Certification Status ................3 Airspeed Limitations ................4 Airspeed Indicator Markings..............5 Powerplant Limitations ................ 6 Engine ....................6 Fuel ....................7 Propeller .................... 8 Hartzell ....................
Page 26 2: L ECTION IMITATIONS IRRUS ESIGN SR20 MD302 Standby Attitude Module (Optional) ........24 Air Conditioning System (Optional) ..........24 Inflatable Restraint System.............. 24 Flap Limitations ................24 Paint ....................24 Cirrus Airframe Parachute System (CAPS) ........24 Other Limitations ................24 Smoking...................
Page 27: Introduction
2: L IRRUS ESIGN ECTION IMITATIONS SR20 NTRODUCTION 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 28: Airspeed Limitations
2: L ECTION IMITATIONS IRRUS ESIGN SR20 IRSPEED IMITATIONS Airspeed Limitations The indicated airspeeds in the following table are based on Section 5, Airspeed Calibration - Normal Static Source Table. When using the alter- nate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
Page 29: Airspeed Indicator Markings
2: L IRRUS ESIGN ECTION IMITATIONS SR20 IRSPEED NDICATOR ARKINGS Airspeed Indicator Markings The airspeed indicator markings are based on Section 5, Airspeed Calibra- tion - Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alter- nate static sources.
Page 30: Powerplant Limitations
2: L ECTION IMITATIONS IRRUS ESIGN SR20 OWERPLANT IMITATIONS Powerplant Limitations Engine Lycoming Engines................. IO-390-C3B6 Power Rating ..............215 HP @ 2700 RPM Maximum RPM ..................2700 RPM • N • Due to the mechanical design of the propeller governor, it is normal for the engine to temporarily exceed 2700 RPM during some phases of flight.
Page 31: Fuel
2: L IRRUS ESIGN ECTION IMITATIONS SR20 OWERPLANT IMITATIONS Recommended Oil Grades (Continued) Engine Break-In After Engine Break-In Ambient Air Single Multi- Single Multi- Temperature (SL) Viscosity Viscosity Viscosity Viscosity 30 °F (-1 °C) to SAE 40 SAE 40 90 °F (32 °C) 0 °F (-18 °C) to...
Page 32: Propeller
2: L ECTION IMITATIONS IRRUS ESIGN SR20 OWERPLANT IMITATIONS Propeller Hartzell Propeller Type ................Constant Speed Three-Blade Propeller, Metal (Standard): Model Number............HC-E3YR-1RF/F7392S-1 Diameter................74.0” (73.0” Minimum) • WARNING • Failure to comply with the shot peening requirement described below may cause damaging loads on the propeller hub, blades and/or pitch change system that can lead to propeller failure.
Page 33: Engine Instrument Markings & Annunciations
2: L IRRUS ESIGN ECTION IMITATIONS SR20 OWERPLANT IMITATIONS Engine Instrument Markings & Annunciations The following describes the engine instrument markings. Powerplant Yellow Green Yellow Arc/Bar Arc/Bar Arc/Bar Arc/Bar Arc/Bar Instrument Lower Min. Max. Upper (Range & Units) Normal Warning...
Page 34: Fuel
2: L ECTION IMITATIONS IRRUS ESIGN SR20 OWERPLANT IMITATIONS Fuel Yellow Green Yellow Arc/Bar Arc/Bar Arc/Bar Arc/Bar Arc/Bar Instrument Minimum Maximum (Range & Units) Normal Minimum Caution Caution Maximum Range Range Range Fuel Flow –– –– –– –– 0 – 21 (0 –...
Page 35: Center Of Gravity Limits
2: L IRRUS ESIGN ECTION IMITATIONS SR20 ENTER OF RAVITY IMITS Center of Gravity Limits Reference Datum ..........100 inches forward of firewall Forward................. Refer to Figure 2-1 Aft ..................Refer to Figure 2-1 Figure 2-1: Center of Gravity Envelope 3200 FS 141.1...
Page 36: Maneuver Limits
2: L ECTION IMITATIONS IRRUS ESIGN SR20 ANEUVER IMITS Maneuver Limits Acrobatic maneuvers are strictly prohibited. Spins are prohibited. This airplane is certified in the normal category and is not designed for acrobatic operations. Only those operations incidental to normal flight are approved.
Page 37 2: L IRRUS ESIGN ECTION IMITATIONS SR20 INDS OF PERATION Kinds of Operation System, Instrument Remarks, Notes, and/or Equipment and/or Exceptions Night Night PLACARDS AND MARKINGS Airplane Flight Manual (Included w/ POH) COMMUNICATIONS VHF COM ELECTRICAL POWER Battery 1 Battery 2...
Page 38 2: L ECTION IMITATIONS IRRUS ESIGN SR20 INDS OF PERATION Kinds of Operation System, Instrument Remarks, Notes, and/or Equipment and/or Exceptions Night Night Pitch Trim Indicator Pitch Trim System Roll Trim Indicator Roll Trim System Stall Warning System FUEL Emergency Boost...
Page 39 2: L IRRUS ESIGN ECTION IMITATIONS SR20 INDS OF PERATION Kinds of Operation System, Instrument Remarks, Notes, and/or Equipment and/or Exceptions Night Night MFD Backlighting *Required if PFD Backlighting Fails. Engine Indicators Must Be Shown in Backup Mode. Anticollision Lights...
Page 40 2: L ECTION IMITATIONS IRRUS ESIGN SR20 INDS OF PERATION Kinds of Operation System, Instrument Remarks, Notes, and/or Equipment and/or Exceptions Night Night PFD Attitude Indication PFD Heading Indication PFD Slip/Skid Indication Turn Coordinator Altitude Encoder As required per procedure.
Page 41: Icing
2: L IRRUS ESIGN ECTION IMITATIONS SR20 IMITS Kinds of Operation System, Instrument Remarks, Notes, and/or Equipment and/or Exceptions Night Night Oil Quantity Indicator (Dipstick) Oil Temperature Indication Engine Speed SPECIAL EQUIPMENT Cirrus Airframe Parachute (CAPS) Icing Flight into known icing conditions is prohibited.
Page 42: Altitude Limits
2: L ECTION IMITATIONS IRRUS ESIGN SR20 LTITUDE IMITS Altitude Limits Maximum Takeoff Altitude............10,000 ft MSL Maximum Operating Altitude ............17,500 ft MSL The operating rules (CFR Part 91 and CFR Part 135) require the use of supplemental oxygen at specified altitudes below the maximum operating altitude.
Page 43: Serials W/ Observer's Seat
2: L IRRUS ESIGN ECTION IMITATIONS SR20 AXIMUM CCUPANCY Serials w/ Observer’s Seat Occupancy of this airplane is limited to three persons, the pilot and two passengers. Child Restraint System 1. Rear seat configuration for LATCH / ISOFIX compliant child seat is limited to the Observer’s Seat.
Page 44: Systems And Equipment Limits
2: L ECTION IMITATIONS IRRUS ESIGN SR20 YSTEMS AND QUIPMENT IMITS Systems and Equipment Limits Cirrus Perspective+ Integrated Avionics System 1. The appropriate revision of the Cirrus Perspective+ Cockpit Reference Guide (p/n 190-02184-XX, where X can be any digit from 0 to 9) must be immediately available to the pilot during flight.
Page 45 2: L IRRUS ESIGN ECTION IMITATIONS SR20 YSTEMS AND QUIPMENT IMITS airports in other airspace are not approved unless authorized by the appropriate governing authority. f) RNAV approaches must be conducted utilizing the GPS sensor. g) The Perspective+ Integrated Avionics System is compliant with AC 90-100A.
Page 46 2: L ECTION IMITATIONS IRRUS ESIGN SR20 YSTEMS AND QUIPMENT IMITS 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 65°...
Page 47: Stormscope Weather Information System (Optional)
2: L IRRUS ESIGN ECTION IMITATIONS SR20 YSTEMS AND QUIPMENT IMITS 13.The installed ADS-B OUT system, including GTX 335 Mode S Tran- sponder and GTX 345 Mode S UAT in Transponder (optional), has been shown to meet the equipment requirements of 14 CFR 91.227.
Page 48: Md302 Standby Attitude Module (Optional)
2: L ECTION IMITATIONS IRRUS ESIGN SR20 THER IMITATIONS MD302 Standby Attitude Module (Optional) 1. Selection of the option menu of the MD302 is limited to ground or visual meteorological conditions. 2. The display has an operational lower temperature limit of -22 °F (-30 °C).
Page 49: Placards
2: L IRRUS ESIGN ECTION IMITATIONS SR20 LACARDS Placards Figure 2-4: Placards (1 of 6) Engine compartment, inside oil filler access: Wing, adjacent to fuel filler caps: Upper fuselage, either side of CAPS rocket cover: WARNING! ROCKET FOR PARACHUTE DEPLOYMENT INSIDE...
Page 50 2: L ECTION IMITATIONS IRRUS ESIGN SR20 LACARDS Figure 2-4: Placards (2 of 6) Left fuselage, on external power supply door: EXTERNAL POWER 28 V DC Doors, adjacent to latch: OPEN SR20_FM02_5411A 2-26 P/N 11934-005 Reissue A...
Page 51 2: L IRRUS ESIGN ECTION IMITATIONS SR20 LACARDS Figure 2-4: Placards (3 of 6) Engine control panel: CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT MAX POWER FUEL FLOWS RICH TURN BOOST PUMP ON DURING TAKE OFF,...
Page 52 2: L ECTION IMITATIONS IRRUS ESIGN SR20 LACARDS Figure 2-4: Placards (4 of 6) 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 FOLLOWING FLIGHT OPERATIONS:...
Page 53 2: L IRRUS ESIGN ECTION IMITATIONS SR20 LACARDS Figure 2-4: Placards (5 of 6) Instrument Panel, center: DISPLAY BACKUP Baggage Compartment, aft edge: ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Instrument Panel: FASTEN SEATBELTS • NO SMOKING Cabin Window, above door latch:...
Page 54 2: L ECTION IMITATIONS IRRUS ESIGN SR20 LACARDS Figure 2-4: Placards (6 of 6) CAPS Deployment Handle Cover, above pilot's right shoulder: WARNING USE FOR EXTREME EMERGENCIES ONLY SEAT BELT AND SHOULDER HARNESS MUST BE WORN AT ALL TIMES USE OF THIS DEVICE COULD RESULT...
Page 55 3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 Section 3: Emergency Procedures Table of Contents Introduction..................3 Crew Alert System (CAS) Messaging ..........3 Warnings ..................3 CAPS Guidance ................3 Preflight Planning ................4 Preflight Inspections/Maintenance ............ 4 Methodology..................4 Maintain Aircraft Control ..............
Page 56 3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 Emergency Landing w/o Power............17 Ditching.................... 18 Landing Without Elevator Control............ 18 Engine System Emergencies ............19 Engine Partial Power Loss .............. 19 OIL PRESS Warning ............... 21 OIL TEMP Warning ................. 21 CHT Caution and Warning ..............
Page 57: Introduction
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 NTRODUCTION 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 rare, the guidelines described in this section should be considered and applied as necessary should an emergency arise.
Page 58: Preflight Planning
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 NTRODUCTION option for occupants as compared to continued flight or traditional countermeasures. Pilots flying Cirrus aircraft must be properly trained and familiar with CAPS guidance, limitations, and operating procedures. Refer to Section 10,...
Page 59: Take Appropriate Action
IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 NTRODUCTION Take Appropriate Action In many situations, the procedures listed in this section will either correct or mitigate the aircraft problem or allow safe recovery of the aircraft. Follow them and use good pilot judgment.
Page 60: Memory Items
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 NTRODUCTION Memory Items Checklist steps emphasized by a rectangular enclosure, such as the example below, should be memorized for accomplishment without reference to the procedure, due to the nature of their urgency.
Page 61: Land As Soon As Possible
IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 NTRODUCTION Land as Soon as Possible Land without delay at the first site at which a safe landing can be made. Continued flight beyond an available airfield at which a safe landing can be made will result in increased risk and shall not be attempted.
Page 62: Airspeeds For Emergency Operations
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 IRSPEEDS FOR MERGENCY PERATIONS Airspeeds for Emergency Operations Maneuvering Speed 3150 lb (1429 kg).................. 133 KIAS 2700 lb (1225 kg).................. 123 KIAS 2300 lb (1043 kg).................. 114 KIAS Best Glide (Gear and Flaps: UP) 3150 lb (1429 kg)..................
Page 63: Engine Failures
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 NGINE AILURES Engine Failures Engine Failure On Takeoff - Low Altitude 1. Best Glide or Landing Speed ............ESTABLISH 2. Mixture..................... CUTOFF 3. Fuel Selector....................OFF 4. Ignition Switch ..................OFF 5. Flaps ..................AS REQUIRED ◆...
Page 64: Engine Failure In Flight
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 NGINE AILURES Engine Failure In Flight 1. Best Glide Speed ................ ESTABLISH 2. Mixture ..................AS REQUIRED 3. Fuel Selector ..............SWITCH TANKS 4. Fuel Pump ....................ON 5. Alternate Induction Air................ON 6. Ignition Switch ..............CHECK, BOTH ◆...
Page 65: Airstart
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 IRSTART Airstart Engine Airstart 1. BAT 1 and BAT 2 Switches ..............ON 2. Power Lever ................OPEN ½ INCH 3. Mixture................RICH, AS REQ’D 4. Fuel Selector..............SWITCH TANKS 5. Ignition Switch ..................BOTH 6.
Page 66: Smoke And Fire
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 MOKE AND Smoke and Fire Cabin Fire In Flight 1. BAT 1, ALT 1, and ALT 2 Switches......OFF, AS REQUIRED 2. Fire Extinguisher ................ ACTIVATE 3. AVIONICS Switch ...................OFF 4. All other switches ..................OFF 5.
Page 67: Engine Fire In Flight
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 MOKE AND (Continued) • N • If the airplane is in IMC conditions, turn ALT 1, ALT 2, and BAT 1 switches OFF. Power from battery 2 will keep the Primary Flight Display operational for approximately 30 minutes.
Page 68: Wing Fire In Flight
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 MOKE AND 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
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 MERGENCY ESCENT 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: Glide
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 LIDE Glide Conditions Example Power Altitude 8,000 ft. AGL Propeller Windmilling Airspeed Best Glide Flaps 0% (UP) Glide Distance 12 NM Wind Zero Best Glide Speed 3150 lb (1429 kg).................. 100 KIAS 2600 lb (1179 kg)..................
Page 71: Forced Landings
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 ORCED ANDINGS Forced Landings Emergency Landing w/o Power 1. Best Glide Speed.................ESTABLISH 2. Radio..TRANSMIT (121.5 MHz) MAYDAY GIVING LOCATION AND INTENTIONS 3. Transponder .................SQUAWK 7700 4. Power Lever .................... IDLE 5. Mixture..................... CUTOFF 6.
Page 72: Ditching
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 ORCED ANDINGS 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 Procedure Complete •...
Page 73: Engine System Emergencies
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 NGINE YSTEM MERGENCIES Engine System Emergencies Engine Partial Power Loss 1. Air Conditioner (if installed) ..............OFF 2. Fuel Pump....................ON 3. Fuel Selector..............SWITCH TANKS 4. Mixture....CHECK APPROPRIATE FOR FLIGHT CONDITIONS 5. Power Lever ..................SWEEP 6.
Page 74 3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 NGINE YSTEM MERGENCIES (Continued) • N • Low oil pressure may be indicative of an imminent engine failure. OIL PRESS Warning Checklist in this Section for special procedures with low oil pressure.
Page 75: Oil Press Warning
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 NGINE YSTEM MERGENCIES OIL PRESS Warning OIL PRESS Oil Pressure Out of Range 1. Oil Pressure Gauge ................CHECK ◆ If pressure low / high: a. Power..REDUCE TO MINIMUM FOR SUSTAINED FLIGHT b.
Page 76: Cht Caution And Warning
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 NGINE YSTEM MERGENCIES CHT Caution and Warning High Cylinder Head Temperature ◆ If on ground: a. Power Lever ................REDUCE b. Annunciations and Engine Temperatures .......MONITOR ❍ If Caution or Warning annunciation is still illuminated: (1)Power Lever..........MINIMUM REQUIRED...
Page 77: Propeller System Emergencies
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 ROPELLER YSTEM MERGENCIES Propeller System Emergencies RPM Warning Engine Speed High 1. Tachometer..................CHECK ◆ If engine speed normal: a. If on ground........CORRECT PRIOR TO FLIGHT b. If in flight ............CONTINUE, MONITOR Procedure Complete ◆...
Page 78: Fuel System Emergencies
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 YSTEM MERGENCIES Fuel System Emergencies FUEL LOW LEFT Warning FUEL LOW LEFT Low Fuel Quantity in Left Tank 1. Fuel Quantity Gauges ...............CHECK 2. Fuel Pump ...................BOOST 3. Fuel Selector ................RIGHT TANK Procedure Complete •...
Page 79: Fuel Low Total Warning
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 YSTEM MERGENCIES FUEL LOW TOTAL Warning FUEL LOW TOTAL Low Fuel Quantity 1. Fuel Quantity Gauges............... CHECK 2. Totalized Fuel Quantity ..............CHECK ◆ If totalized fuel quantity differs significantly from sensed quantity: a.
Page 80: Electrical System Emergencies
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 LECTRICAL YSTEM MERGENCIES Electrical System Emergencies M BUS 1 Warning M BUS 1 High Voltage on Main Bus 1 1. ALT 1 Switch..................CYCLE 2. M Bus 1 Voltage (M1) ..............CHECK ◆...
Page 81: M Bus 2 Warning
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 LECTRICAL YSTEM MERGENCIES M BUS 2 Warning M BUS 2 High Voltage on Main Bus 2 1. Main Bus 1 Voltage (M1)..............CHECK ◆ If M Bus 1 Voltage is greater than 32 volts: a.
Page 82: Ess Bus Warning
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 LECTRICAL YSTEM MERGENCIES ESS BUS Warning ESS BUS High or Low Voltage on Essential Bus 1. Essential Bus Voltage (ESS) .............CHECK ◆ If Essential Bus Voltage is greater than 32 Volts: a. Main Bus 1 and Main Bus 2 Voltages (M1 and M2)....CHECK b.
Page 83: Environmental System Emergencies
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 NVIRONMENTAL YSTEM MERGENCIES Environmental System Emergencies CO LVL HIGH Warning CO LVL HIGH Carbon Monoxide Level High 1. Air Conditioner (if installed) ......NOT IN RECIRC MODE 2. Temperature Selector ................COLD 3. Vent Selector........FEET/PANEL/DEFROST POSITION 4.
Page 84: Integrated Avionics System Emergencies
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 NTEGRATED VIONICS YSTEM MERGENCIES 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.
Page 85: Pfd Display Failure
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 NUSUAL TTITUDE MERGENCIES PFD Display Failure 1. Display Backup................ACTIVATE 2. Land as soon as practicable. Procedure Complete Unusual Attitude Emergencies Inadvertent Spin Entry 1. CAPS..................... ACTIVATE Procedure Complete • WARNING •...
Page 86: Spin Spin Spin Warning
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 NUSUAL TTITUDE MERGENCIES SPIN SPIN SPIN Warning 1. CAPS ..................... ACTIVATE Procedure Complete • WARNING • In all cases, if the aircraft enters an unusual attitude following or in connection with a stall, a spin condition should be assumed and, imme- diate deployment of the CAPS is required.
Page 87: Inadvertent Spiral Dive During Imc Flight
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 NUSUAL TTITUDE MERGENCIES Inadvertent Spiral Dive During IMC Flight 1. Power Lever .................... IDLE 2. Stop the spiral dive by using coordinated aileron and rudder control while referring to the attitude indicator and turn coordinator to level the wings.
Page 88: Other Emergencies
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 THER MERGENCIES 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 CUTOFF) 5.
Page 89: Brake Temp Warning
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 THER MERGENCIES BRAKE TEMP Warning BRAKE TEMP Left/Right Brake Over-Temperature Annunciation 1. Stop aircraft and allow the brakes to cool. Procedure Complete • WARNING • Do not set parking brake unless required for safety.
Page 90 3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 THER MERGENCIES (Continued) c. Flight..................CONTINUE (1)Engine start will not be available at destination. Procedure Complete • WARNING • Use caution after shutdown if STARTER circuit breaker required pull (failed relay or solenoid). If breaker is unknowingly or unintentionally reset, starter will instantly engage if Battery 1 power is supplied;...
Page 91: Emergency Ground Egress
3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 THER MERGENCIES Emergency Ground Egress 1. Engine..................SHUTDOWN 2. Seat Belts ..................RELEASE 3. Airplane....................EXIT Procedure Complete • WARNING • While exiting the airplane, make sure evacuation path is clear of other aircraft, spinning propellers, and other hazards.
Page 92: Caps Deployment
3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 THER MERGENCIES CAPS Deployment • WARNING • The maximum demonstrated deployment speed is 133 KIAS. 1. Activation Handle Cover ..............REMOVE 2. Activation Handle (Both Hands)....PULL STRAIGHT DOWN After deployment, as time permits: 3.
Page 93 3: E IRRUS ESIGN ECTION MERGENCY ROCEDURES SR20 THER MERGENCIES (Continued) • CAUTION • CAPS deployment will likely result in damage or loss to the airframe. • N • Several possible scenarios in which the activation of the CAPS would be appropriate are discussed in...
Page 94 3: E ECTION MERGENCY ROCEDURES IRRUS ESIGN SR20 THER MERGENCIES Intentionally Left Blank 3-40 P/N 11934-005 Reissue A...
Page 95 3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 Section 3A: Abnormal Procedures Table of Contents Introduction..................3 Crew Alert System (CAS) Messaging ..........3 Cautions ..................3 Advisories ..................3 Abnormal Procedures Guidance ............3 Circuit Breakers................. 4 Procedure Division Symbols ............. 4 Landing Guidance ................
Page 96 3A: A ECTION BNORMAL ROCEDURES IRRUS ESIGN SR20 Pitot Static System ................17 Static Source Blocked ..............17 Pitot Tube Blocked ................17 PITOT HEAT FAIL Caution ............. 18 PITOT HEAT REQD Caution............18 Flight Control System ................ 19 Electric Trim/Autopilot Failure............19 FLAPS OVERSPEED Caution ............
Page 97: Introduction
3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 NTRODUCTION 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 98: Circuit Breakers
BNORMAL ROCEDURES IRRUS ESIGN SR20 NTRODUCTION Sound judgment as well as thorough knowledge of the aircraft, its charac- teristics, and the flight manual procedures are essential in the handling of any abnormal system and/or flight condition. In addition to the outlined...
Page 99: Landing Guidance
3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 LIGHT NVIRONMENT Landing Guidance Land as Soon as Practicable Extended flight is not recommended and the pilot should proceed to land the plane, but not necessarily at the first or closest landing location. The landing location and duration of flight remains at the discretion of the pilot in command, after considering all factors related to the safety of the flight.
Page 100: Inadvertent Imc Encounter
3A: A ECTION BNORMAL ROCEDURES IRRUS ESIGN SR20 LIGHT NVIRONMENT Inadvertent IMC Encounter 1. Airplane Control ..ESTABLISH STRAIGHT AND LEVEL FLIGHT 2. Autopilot ....ENGAGE TO HOLD HEADING AND ALTITUDE 3. Heading ..........RESET TO INITIATE 180° TURN Procedure Complete •...
Page 101: Abnormal Landings
3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 BNORMAL ANDINGS Abnormal Landings Landing With Failed Brakes ◆ One brake inoperative: a. Land on the side of runway corresponding to the inoperative brake. b. Maintain directional control using rudder and working brake.
Page 102: Engine System
3A: A ECTION BNORMAL ROCEDURES IRRUS ESIGN SR20 NGINE YSTEM Engine System OIL PRESS Caution OIL PRESS Low Idle Oil Pressure ◆ If in flight: a. Land as soon as practicable. Procedure Complete • N • Oil pressure between 25 psi and 55 psi at or above 1000 RPM.
Page 103: Start Engaged Caution
3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 NGINE YSTEM START ENGAGED Caution START ENGAGED Starter Engaged Annunciation ◆ If on ground: a. Ignition Switch....DISENGAGE PRIOR TO 10 SECONDS b. Wait 30 seconds before next start attempt. ❍ If starter does not disengage (relay or solenoid failure): (1)BAT 1 Switch ................OFF...
Page 104: Fuel System
3A: A ECTION BNORMAL ROCEDURES IRRUS ESIGN SR20 YSTEM Fuel System FUEL LOW TOTAL Caution FUEL LOW TOTAL Low Fuel Quantity 1. Fuel Quantity Gauges ...............CHECK 2. Totalized Fuel Quantity ..............CHECK ◆ If totalized value differs significantly from sensed quantity: a.
Page 105: Fuel Imbalance Advisory
3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 LECTRICAL YSTEM FUEL IMBALANCE Advisory FUEL IMBALANCE Fuel Imbalance 1. Fuel Quantity Gauges............... CHECK 2. Fuel Pump....................ON If Fuel Pump is already ON for vapor suppression, pump should be left in this position for tank switch.
Page 106: M Bus 2 Caution
3A: A ECTION BNORMAL ROCEDURES IRRUS ESIGN SR20 LECTRICAL YSTEM M BUS 2 Caution M BUS 2 Low Voltage on Main Bus 2 1. Perform ALT 1 Caution (Failure) ALT 2 Caution (Failure) Check- lists. Procedure Complete • N •...
Page 107: Alt 1 Caution (Failure)
3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 LECTRICAL YSTEM ALT 1 Caution (Failure) ALT 1 Low Alternator 1 Output 1. ALT 1 Circuit Breaker ........... CHECK AND SET 2. ALT 1 Switch ..................CYCLE ◆ If alternator does not reset: a.
Page 108: Alt 2 Caution (Failure)
3A: A ECTION BNORMAL ROCEDURES IRRUS ESIGN SR20 NTEGRATED VIONICS YSTEM ALT 2 Caution (Failure) ALT 2 Low Alternator 2 Output 1. ALT 2 Circuit Breaker ........... CHECK AND SET 2. ALT 2 Switch..................CYCLE ◆ If alternator does not reset: a.
Page 109: Pfd Fan Fail Advisory
3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 NTEGRATED VIONICS YSTEM PFD FAN FAIL Advisory PFD FAN FAIL PFD Cooling Fan Failure 1. AVIONICS FAN 2 Circuit Breaker..........CYCLE ◆ If annunciation does not extinguish: a. High cabin temps....LAND AS SOON AS PRACTICABLE b.
Page 110: Flight Displays Too Dim
3A: A ECTION BNORMAL ROCEDURES IRRUS ESIGN SR20 NTEGRATED VIONICS YSTEM Flight Displays Too Dim 1. INSTRUMENT dimmer knob ...............OFF (FULL COUNTER-CLOCKWISE) ◆ If flight displays do not provide sufficient brightness: a. Revert to standby instruments. Procedure Complete • N •...
Page 111: Pitot Static System
3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 ITOT TATIC YSTEM Pitot Static System Static Source Blocked 1. Pitot Heat ....................ON 2. Alternate Static Source ................ OPEN Procedure Complete • N • 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...
Page 112: Pitot Heat Fail Caution
3A: A ECTION BNORMAL ROCEDURES IRRUS ESIGN SR20 ITOT TATIC YSTEM PITOT HEAT FAIL Caution PITOT HEAT FAIL Pitot Heat Current Sensor 1. Pitot Heat Circuit Breaker ..............CYCLE 2. Pitot Heat................CYCLE OFF, ON ◆ If inadvertent icing encountered, perform...
Page 113: Flight Control System
3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 LIGHT ONTROL YSTEM Flight Control System Electric Trim/Autopilot Failure 1. Airplane Control ..........MAINTAIN MANUALLY 2. Autopilot (if engaged) .............DISENGAGE ◆ If Problem Is Not Corrected: a. Circuit Breakers ..........PULL AS REQUIRED •...
Page 114: Takeoff Flaps Caution
3A: A ECTION BNORMAL ROCEDURES IRRUS ESIGN SR20 LIGHT ONTROL YSTEM TAKEOFF FLAPS Caution TAKEOFF FLAPS Flaps Not In Takeoff Configuration 1. Takeoff ....................ABORT 2. Aircraft Control ................. MAINTAIN 3. Aircraft Configuration..............CHECK Procedure Complete • N • Flaps are not set to 50% during takeoff.
Page 115: Landing Gear System
3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 ANDING YSTEM 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.
Page 116: Other Conditions
3A: A ECTION BNORMAL ROCEDURES IRRUS ESIGN SR20 THER ONDITIONS Other Conditions Aborted Takeoff 1. Power Lever..................... IDLE 2. Brakes..................AS REQUIRED Procedure Complete • N • 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 117: Communications Failure
3A: A IRRUS ESIGN ECTION BNORMAL ROCEDURES SR20 THER ONDITIONS Communications Failure 1. Switches, Controls ................CHECK 2. Frequency..................CHANGE 3. Circuit Breakers..................SET 4. Headset ....................CHANGE 5. Handheld Microphone............... CONNECT Procedure Complete • N • If, after following the checklist procedure, communication is not restored, proceed with CFR/AIM lost communications proce- dures.
Page 118 3A: A ECTION BNORMAL ROCEDURES IRRUS ESIGN SR20 THER ONDITIONS Intentionally Left Blank 3A-24 P/N 11934-005 Reissue A...
Page 119 4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 Section 4: Normal Procedures Table of Contents Introduction..................3 Airspeeds for Normal Operation............3 Normal Procedures ................4 Preflight Inspection................4 Before Engine Start ................9 Engine Start..................10 Before Taxiing ................. 11 Taxiing.....................
Page 120 4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 Intentionally Left Blank P/N 11934-005 Reissue A...
Page 121: Introduction
ESIGN ECTION ORMAL ROCEDURES SR20 NTRODUCTION Introduction This section provides amplified procedures for normal operation of the Cirrus Design SR20 aircraft. • N • Refer to Section 9: Log of Supplements for optional equipment Normal Procedures. Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3150 lb.
Page 122: Normal Procedures
4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 ORMAL ROCEDURES Normal Procedures Preflight Inspection • WARNING • Before carrying out preflight inspections, ensure that all required main- tenance has been accomplished. Review your flight plan and compute weight and balance and performance requirements. Throughout the walk-around: check all hinges, hinge pins, and bolts for security;...
Page 123 4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 ORMAL ROCEDURES (Continued) 1. Cabin a. Required Documents ............ON BOARD b. AVIONICS Switch ................OFF c. BAT 2 Switch..................ON d. PFD..................VERIFY ON e. Essential Bus Voltage ............23-25 VOLTS f. Flap Position Light ................OUT g.
Page 124 4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 ORMAL ROCEDURES (Continued) 2. Left Fuselage a. Door Lock .................UNLOCK b. COM 1 Antenna (top).... CONDITION AND ATTACHMENT c. Transponder Antenna (underside) ..... CONDITION AND ATTACHMENT d. COM 2 Antenna (underside) CONDITION AND ATTACHMENT e.
Page 125 4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 ORMAL ROCEDURES (Continued) • N • Verify bolt located under the inboard edge of aileron is secured with safety wire. d. Hinges, actuation arm, bolts, and cotter pins......SECURE 6. Right Wing Tip a.
Page 126 4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 ORMAL ROCEDURES (Continued) 9. Nose Gear, Propeller, and Spinner • WARNING • Keep clear of propeller rotation plane. Do not allow others to approach propeller. a. Tow Bar .............REMOVE AND STOW b. Strut..................CONDITION c.
Page 127: Before Engine Start
4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 ORMAL ROCEDURES (Continued) 13.Left Wing Trailing Edge • N • Verify bolt located under the inboard edge of aileron is secured with safety wire. a. Hinges, actuation arm, bolts, and cotter pins......SECURE b.
Page 128: Engine Start
4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 ORMAL ROCEDURES Engine Start 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 129: Before Taxiing
4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 ORMAL ROCEDURES (Continued) 1. External Power (If applicable)........... CONNECT 2. Brakes ....................HOLD 3. BAT 1 and BAT 2 Switches ........ON (CHECK VOLTS) 4. Strobe Lights ....................ON 5. Power Lever ................OPEN ¼ INCH 6.
Page 130: Taxiing
4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 ORMAL ROCEDURES 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. Deceleration or taxi speed control using brakes but without a reduction in power will result in increased brake temperature.
Page 131: Before Takeoff
4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 ORMAL ROCEDURES 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 132 4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 ORMAL ROCEDURES (Continued) 15.Alternator ...................CHECK a. Pitot Heat ..................... ON b. Navigation Lights................ON c. Landing Light ..................ON 16.Voltage....................CHECK 17.Pitot Heat................AS REQUIRED • N • Pitot Heat should be turned ON for flight into IMC, flight into visible moisture, or whenever ambient temperatures are 41 °F (5...
Page 133: Best Power Fuel Flow
4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 ORMAL ROCEDURES Best Power Fuel Flow The fuel flow values in the table below were demonstrated to obtain the takeoff and climb performance presented in Section 5. Pressure Altitude Target Fuel Flow GPH...
Page 134: Normal Takeoff
4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 ORMAL ROCEDURES Normal Takeoff 1. Brakes........RELEASE (STEER WITH RUDDER ONLY) 2. Power Lever..............FULL FORWARD • N • Abrupt full range throttle movement may result in a slight engine hesitation or stumble before best power is attained. Idle to maximum power throttle movements should be made slowly (approximately 3 seconds for full range motion).
Page 135: Climb
4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 ORMAL ROCEDURES Climb Normal climbs are performed flaps UP (0%) and full power at speeds 5 to 10 knots higher than best rate-of-climb speeds. These higher speeds give the best combination of performance, visibility and engine cooling.
Page 136: Cruise
4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 ORMAL ROCEDURES 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 137 4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 ORMAL ROCEDURES (Continued) 1. Fuel Pump....................OFF • N • The Fuel Pump may be used for vapor suppression during cruise. The Fuel Pump must be set to ON during maneuvering flight (flight training maneuvers, chandelles, stalls, etc.).
Page 138: Cruise Leaning
4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 ORMAL ROCEDURES Cruise Leaning • CAUTION • If moving the mixture control from the full rich position only decreases the EGT from the full rich value, place the mixture control back in the full forward position and have the fuel system serviced.
Page 139: Descent
4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 ORMAL ROCEDURES Descent 1. Altimeter ....................SET 2. Cabin Heat/Defrost ............. AS REQUIRED 3. Landing Light .................... ON 4. Fuel System ..................CHECK 5. Mixture.................. AS REQUIRED 6. Brake Pressure ................... CHECK Before Landing 1.
Page 140: Crosswind Landing
ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 ORMAL ROCEDURES lowering the nose of the airplane. Touchdown should be made power-off and on the main wheels first. Immediately after touchdown, lower the nose wheel and apply braking as required. For maximum brake effectiveness, retract the flaps, hold the control yoke full back, and apply maximum brake pressure without skidding.
Page 141: Shutdown
4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 TALLS Shutdown 1. Fuel Pump....................OFF 2. Throttle....................IDLE • CAUTION • If the engine hesitates as the switch cycles through the “OFF” posi- tion. If the engine does not hesitate, one or both magnetos are not grounded.
Page 142: Environmental Conditions
4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 NVIRONMENTAL ONDITIONS Environmental Conditions 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 143 4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 NVIRONMENTAL ONDITIONS (Continued) 5. Power Lever ................OPEN ¼ INCH 6. Mixture..................... CUTOFF 7. Propeller Area..................CLEAR 8. Fuel Pump....................ON 9. Mixture..............ADVANCE TO RICH UNTIL STABLE FUEL FLOW IS INDICATED (3-5 SECONDS) •...
Page 144: Hot Weather Operation
4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 NVIRONMENTAL ONDITIONS Hot Weather Operation Avoid prolonged engine operation on the ground. Fuel Pump 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 145: Lead Reduction Before Shut Down
4: N IRRUS ESIGN ECTION ORMAL ROCEDURES SR20 NVIRONMENTAL ONDITIONS Lead Reduction Before Shut Down If required, complete the following procedure before shutdown to reduce potential for lead build-up in the combustion chamber, spark plugs, and engine oil. • CAUTION •...
Page 146: Noise Characteristics/Abatement
4: N ECTION ORMAL ROCEDURES IRRUS ESIGN SR20 OISE HARACTERISTICS BATEMENT Noise Characteristics/Abatement The certificated noise levels for the aircraft established in accordance with CFR 36 Appendix G are: Configuration Actual Maximum Allowable Hartzell 3-blade Propeller, 82.9 dB(A) 88.0 dB(A)
Page 147 5: P IRRUS ESIGN ECTION ERFORMANCE SR20 Section 5: Performance Data Table of Contents Introduction..................3 Standard Charts .................. 3 Associated Conditions Affecting Performance ........3 Demonstrated Operating Temperature ..........3 Temperature Conversion..............4 OAT for International Standard Atmosphere (ISA) Condition.... 5 Pressure Conversion - Inches of Mercury to Millibars .......
Page 148 5: P ECTION ERFORMANCE IRRUS ESIGN SR20 Landing Distance................37 Landing Distance Table - Flaps 100%..........38 Landing Distance Table - Flaps 50%..........39 Landing Distance Table - Flaps 0%..........40 P/N 11934-005 Reissue A...
Page 149: Introduction
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 NTRODUCTION 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 150: Temperature Conversion
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 TANDARD HARTS Temperature Conversion Temp to Convert Temp to Convert Temp to Convert °C or °F °C or °F °C or °F °C < > °F °C < > °F °C < >...
Page 151: Oat For International Standard Atmosphere (Isa) Condition
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 TANDARD HARTS OAT for International Standard Atmosphere (ISA) Condition Press -30 °C -15 °C +15 °C +30 °C °C °F °C °F °C °F °C °F °C °F 1000 2000 3000 4000 5000...
Page 152: Pressure Conversion - Inches Of Mercury To Millibars
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 TANDARD HARTS Pressure Conversion - Inches of Mercury to Millibars Inches Of Inches Of Millibars Millibars Mercury Mercury 28.0 29.6 1002 28.1 29.7 1006 28.2 29.8 1009 28.3 29.9 1012 28.4 30.0 1016 28.5...
Page 153: Fuel Quantity Conversion - U.s. Gallons To Liters
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 TANDARD HARTS Fuel Quantity Conversion - U.S. Gallons to Liters • N • Fuel mass provided for reference assuming nominal 6.0 lb/gallon at 59 °F (15 °C). U.S. U.S. Gallons Lb (Kg) Gallons...
Page 154: Weight Conversion - Pounds To Kilograms
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 TANDARD HARTS Weight Conversion - Pounds to Kilograms Pounds Kilograms Pounds Kilograms 2000 907.2 2700 1224.7 2100 952.5 2800 1270.1 2200 998.0 2900 1315.4 2300 1043.3 3000 1360.1 2400 1088.6 3100 1406.1 2500 1134.0...
Page 155: Distance Conversion: Feet To Meters
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 TANDARD HARTS Distance Conversion: Feet to Meters Feet Meters Feet Meters 1000 2000 3000 4000 1219 5000 1524 6000 1829 7000 2134 8000 2438 9000 2743 10,000 3048 P/N 11934-005 Reissue A...
Page 156: Length Conversion: Inches To Centimeters
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 TANDARD HARTS Length Conversion: Inches to Centimeters Inches Centimeters Inches Centimeters 2.54 50.8 5.08 76.2 7.62 101.6 10.16 12.70 142.4 15.24 177.8 17.78 203.2 20.32 228.6 22.86 25.40 27.94 30.48 5-10 P/N 11934-005...
Page 157: Airspeed Calibration
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 TANDARD HARTS Airspeed Calibration Normal Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • N • Indicated airspeed values assume zero instrument error. KCAS KIAS Flaps 0%...
Page 158: Alternate Static Source
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 TANDARD HARTS Alternate Static Source Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster & Vents ..............ON • N • Indicated airspeed values assume zero instrument error.
Page 159: Altitude Correction
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 TANDARD HARTS Altitude Correction Normal Static Source: Primary Flight Display Conditions: • Power for level flight or maximum continuous, whichever is less. • 3150 LB • N • Add correction to desired altitude to obtain indicated altitude to fly.
Page 160: Normal Static Source: Standby Altimeter
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 TANDARD HARTS Normal Static Source: Standby Altimeter Conditions: • Power for level flight or maximum continuous, whichever is less. • 3150 LB • N • Add correction to desired altitude to obtain indicated altitude to fly.
Page 161: Alternate Static Source: Primary Flight Display
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 TANDARD HARTS Alternate Static Source: Primary Flight Display Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster & Vents..............ON • N • Add correction to desired altitude to obtain indicated altitude to fly.
Page 162: Alternate Static Source: Standby Altimeter
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 TANDARD HARTS Alternate Static Source: Standby Altimeter Conditions: • Power for level flight or maximum continuous, whichever is less. • Heater, Defroster & Vents ..............ON • N • Add correction to desired altitude to obtain indicated altitude to fly.
Page 163 5: P IRRUS ESIGN ECTION ERFORMANCE SR20 TANDARD HARTS Stall Speeds Conditions: • Weight....................3150 LB • CG......................Noted • Power......................Idle • Bank Angle ..................Noted • N • Altitude loss during wings level stall may be 250 ft or more.
Page 164: Wind Components
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 TANDARD HARTS Wind Components Example: Runway Heading..................... 10° Wind Direction ....................60° Wind Velocity ..................15 Knots • N • The maximum demonstrated crosswind is 20 knots. Value not considered limiting. Figure 5-1: Wind Components 0°...
Page 165: Takeoff Distance
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 AKEOFF ISTANCE Takeoff Distance Conditions: • Winds ..................... Zero • Runway................Dry, Level, Paved • Flaps......................50% • Air Conditioner ..................OFF • Power..................Full Throttle • Mixture................. Set per Placard Set prior to brake release for short field takeoff.
Page 166: Takeoff Distance: 3150 Lb (1429 Kg)
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 AKEOFF ISTANCE Takeoff Distance: 3150 lb (1429 kg) Weight: 3150 lb (1429 kg) Headwind: Subtract 10% per each 12 Approximate Speed at Liftoff: knots headwind. 75 KIAS Tailwind: Add 10% per each 2 knots Speed over 50 ft Obstacle: 81 KIAS tailwind up to 10 knots.
Page 167: Takeoff Distance: 2600 Lb (1179 Kg)
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 AKEOFF ISTANCE Takeoff Distance: 2600 lb (1179 kg) Weight: 2600 lb (1179 kg) Headwind: Subtract 10% per each 12 Approximate Speed at Liftoff: knots headwind. 69 KIAS Tailwind: Add 10% per each 2 knots Speed over 50 ft Obstacle: 75 KIAS tailwind up to 10 knots.
Page 168: Takeoff Climb Gradient
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 AKEOFF ISTANCE Takeoff Climb Gradient Conditions: • Power ..................Full Throttle • Mixture.................Set per Placard • Flaps ......................50% • Airspeed ................ Best Rate of Climb • N • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
Page 169 5: P IRRUS ESIGN ECTION ERFORMANCE SR20 AKEOFF ISTANCE CLIMB GRADIENT - Feet per Nautical Mile Weight Press Alt Climb Speed TEMPERATURE ~°C KIAS 2600 2000 4000 6000 8000 10000 P/N 11934-005 5-23 Reissue A...
Page 170: Takeoff Rate Of Climb
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 AKEOFF ISTANCE Takeoff Rate of Climb Conditions: • Power ..................Full Throttle • Mixture.................Set per Placard • Flaps ......................50% • Airspeed ................ Best Rate of Climb • N • Rate-of-Climb values shown are change in altitude for unit time expended expressed in Feet per Minute.
Page 171 5: P IRRUS ESIGN ECTION ERFORMANCE SR20 AKEOFF ISTANCE RATE OF CLIMB - Feet per Minute Weight Press Alt Climb Speed TEMPERATURE ~°C KIAS 2600 1159 1109 1056 1003 1069 2000 1033 4000 6000 8000 10000 P/N 11934-005 5-25 Reissue A...
Page 172: Enroute Climb
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 NROUTE LIMB Enroute Climb Enroute Climb Gradient Conditions: • Power ..................Full Throttle • Mixture.................Set per Placard • Flaps ....................0% (UP) • Airspeed ................ Best Rate of Climb • N • Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
Page 173: Enroute Rate Of Climb
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 NROUTE LIMB Weight Press Alt Climb CLIMB GRADIENT - Feet per Nautical Mile Speed TEMPERATURE ~°C KIAS 2600 2000 4000 6000 8000 10000 12000 14000 Enroute Rate Of Climb Conditions: • Power..................Full Throttle •...
Page 174 5: P ECTION ERFORMANCE IRRUS ESIGN SR20 NROUTE LIMB RATE OF CLIMB - Feet per Minute Weight Press Alt Climb Speed TEMPERATURE ~°C KIAS 3150 2000 4000 6000 8000 10000 12000 14000 -115 -148 2600 1279 1211 1143 1075 1041...
Page 175: Enroute Rate Of Climb Vs Density Altitude
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 NROUTE LIMB Enroute Rate of Climb Vs Density Altitude Conditions: • Power..................Full Throttle • Mixture................. Set per Placard • Flaps....................0% (UP) • Airspeed .................Best Rate of Climb Figure 5-2: Enroute Rate of Climb Vs Density Altitude...
Page 176: Time, Fuel, & Distance To Climb
5: P ECTION ERFORMANCE IRRUS ESIGN , & D SR20 ISTANCE TO LIMB Time, Fuel, & Distance to Climb Conditions: • Power ..................Full Throttle • Mixture.................Set per Placard • Fuel Density ................6.0 LB/GAL • Weight ....................3150 LB • Winds .....................Zero •...
Page 177: Cruise Performance
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 RUISE ERFORMANCE Cruise Performance Conditions: • Mixture................Target Fuel Flow* • Weight....................2600 LB • Winds ..................... Zero • Shaded Cells: Cruise Pwr above 85% not recommended. *For power settings greater than 75% power, Best Power.
Page 178 5: P ECTION ERFORMANCE IRRUS ESIGN SR20 RUISE ERFORMANCE ISA -30 °C ISA +30 °C Press Alt RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH 6000 2700 23.4 82% 151 14.7 78% 154 14.1 74% 156 11.4 2500 23.4 75% 146 13.5 71% 148 11.7 68% 150 10.4...
Page 179: Range / Endurance Profile
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 ANGE NDURANCE ROFILE Range / Endurance Profile Conditions: • Weight....................3000 LB • Temperature................Standard Day • Winds ..................... Zero • Mixture..................See Tables • Total Fuel ..................56 Gallons • N • Fuel Remaining For Cruise accounts for 10.1 gallons for 45 minutes IFR reserve fuel at 75% power and fuel burn for descent.
Page 180 5: P ECTION ERFORMANCE IRRUS ESIGN SR20 ANGE NDURANCE ROFILE 65% POWER Mixture = Target Fuel Flow Press Climb Fuel Airspeed Fuel Endurance Range Specific Range Fuel Remaining Flow For Cruise KTAS HOURS NM/GAL 47.9 10.9 12.4 2000 47.2 10.7 12.9...
Page 181: Balked Landing
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 ALKED ANDING Balked Landing Balked Landing Climb Gradient Conditions: • Power..................Full Throttle • Mixture................. Set per Placard • Flaps.................... 100% (DN) • Airspeed .................Best Rate of Climb • N • Balked Landing Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile.
Page 182: Balked Landing Rate Of Climb
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 ALKED ANDING Balked Landing Rate of Climb Conditions: • Power ..................Full Throttle • Mixture.................Set per Placard • Flaps .................... 100% (DN) • Airspeed ....................Noted • N • Balked Landing Rate of Climb values shown are the full flaps change in altitude for unit time expended expressed in Feet per Minute.
Page 183: Landing Distance
5: P IRRUS ESIGN ECTION ERFORMANCE SR20 ANDING ISTANCE Landing Distance Conditions: • Winds ..................... Zero • Runway................Dry, Level, Paved • Flaps................. 100%, 50%, or 0% • Power..........3° Power Approach to 50 ft obstacle, then reduce power passing the estimated 50 ft point and smoothly continue power reduction to reach idle just prior to touchdown.
Page 184: Landing Distance Table - Flaps 100
5: P ECTION ERFORMANCE IRRUS ESIGN SR20 ANDING ISTANCE Landing Distance Table - Flaps 100% Weight: 3150 lb (1429 kg) Headwind: Subtract 10% per each 13 Speed over 50 ft Obstacle: 78 KIAS knots headwind. Flaps: 100% Tailwind: Add 10% per each 2 knots Power: Idle tailwind up to 10 knots.
Page 185 5: P IRRUS ESIGN ECTION ERFORMANCE SR20 ANDING ISTANCE Landing Distance Table - Flaps 50% Weight: 3150 lb (1429 kg) Headwind: Subtract 10% per each 13 Speed over 50 ft Obstacle: 82 KIAS knots headwind. Flaps: 50% Tailwind: Add 10% per each 2 knots Power: Idle tailwind up to 10 knots.
Page 186 5: P ECTION ERFORMANCE IRRUS ESIGN SR20 ANDING ISTANCE Landing Distance Table - Flaps 0% Weight: 3150 lb (1429 kg) Headwind: Subtract 10% per each 13 Speed over 50 ft Obstacle: 87 KIAS knots headwind. Flaps: 0% Tailwind: Add 10% per each 2 knots Power: Idle tailwind up to 10 knots.
Page 187 6: W IRRUS ESIGN ECTION EIGHT AND ALANCE SR20 Section 6: Weight and Balance Table of Contents Introduction..................3 Weight and Balance Record..............3 Weight and Balance Data..............3 Loading Instructions ................4 Weight and Balance Loading Form ............. 5 Loading Data ..................
Page 188 6: W ECTION EIGHT AND ALANCE IRRUS ESIGN SR20 Intentionally Left Blank P/N 11934-005 Reissue A...
Page 189: Introduction
IRRUS ESIGN ECTION EIGHT AND ALANCE SR20 NTRODUCTION Introduction This section describes the procedure for calculating the weight and moment for various operations. A comprehensive list of all equipment available for this airplane is included at the back of this section.
Page 190: Loading Instructions
6: W ECTION EIGHT AND ALANCE IRRUS ESIGN SR20 EIGHT AND ALANCE ECORD 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.
Page 191: Weight And Balance Loading Form
6: W IRRUS ESIGN ECTION EIGHT AND ALANCE SR20 EIGHT AND ALANCE OADING Weight and Balance Loading Form • N • The Takeoff Condition Weight must not exceed 3150 lb. The Takeoff Condition Moment must be within the Minimum Moment to Maximum Moment range at the Takeoff Condition Weight.
Page 192 6: W ECTION EIGHT AND ALANCE IRRUS ESIGN SR20 OADING Loading Data Use the following chart or table to determine the moment/1000 for fuel and payload items to complete the Loading Form. Figure 6-3: Loading Chart Fuel Fwd Pass Loading Chart...
Page 193: Moment Limits
6: W IRRUS ESIGN ECTION EIGHT AND ALANCE SR20 OMENT IMITS Moment Limits Use the following chart or table to determine if the weight and moment from the completed Weight and Balance Loading Form (Figure 6-2) are within limits. Figure 6-4: Moment Limits Chart...
Page 194: Weight & Balance Record
6: W ECTION EIGHT AND ALANCE IRRUS ESIGN & B SR20 EIGHT ALANCE ECORD Weight & Balance Record Use this form to maintain a continuous history of changes and modifica- tions to airplane structure or equipment affecting weight and balance: Figure 6-5: Weight &...
Page 195 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 Section 7: Airplane and Systems Table of Contents Introduction..................5 Airframe....................5 Fuselage.................... 5 Wings ....................5 Empennage ..................6 Flight Controls ..................6 Elevator System ................6 Aileron System .................. 9 Rudder System................
Page 196 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 Key Fob ................... 31 Windshield and Windows ..............31 Engine ....................31 Engine Controls ................32 Engine Indicating ................33 Engine Lubrication System.............. 36 Ignition and Starter System ............. 36 Air Induction System................ 37 Engine Exhaust ................
Page 197 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 Avionics Support Equipment ............87 Cabin Features.................. 89 Emergency Locator Transmitter (ELT) ..........89 Fire Extinguisher ................91 Hour Meters..................92 Emergency Egress Hammer ............92 Convenience Outlet(s)..............92 Cirrus Airframe Parachute System............ 93 System Description .................
Page 198 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 Intentionally Left Blank P/N 11934-005 Reissue A...
Page 199: Introduction
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 NTRODUCTION 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. • N • Some optional equipment may not be described in this section.
Page 200: Empennage
ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LIGHT ONTROLS in a C-section, and is continuous from wing tip to wing tip. The wing spar passes under the fuselage below the two front seats and is attached to the fuselage in two locations. Lift and landing loads are carried by the single carry-through spar, plus a pair of rear shear webs (one on each wing) attached to the fuselage.
Page 201 IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LIGHT ONTROLS motor. Moving the switch forward will initiate nose-down trim and moving the switch aft will initiate nose-up trim. Neutral (takeoff) trim is indicated by the alignment of a reference mark on the yoke tube with a tab attached to the instrument panel bolster.
Page 202 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LIGHT ONTROLS Figure 7-1: Elevator System SR20_FM07_5343 P/N 11934-005 Reissue A...
Page 203: Aileron System
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LIGHT ONTROLS 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 204 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LIGHT ONTROLS Figure 7-2: Aileron System SR20_FM07_5345 7-10 P/N 11934-005 Reissue A...
Page 205: Rudder System
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LIGHT ONTROLS 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 206 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LIGHT ONTROLS Figure 7-3: Rudder System SR20_FM07_5346 7-12 P/N 11934-005 Reissue A...
Page 207: Instrument Panel
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 NSTRUMENT ANEL 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 208 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 NSTRUMENT ANEL Figure 7-4: Instrument Panel & Console - Serials w/o MD302 (1 of 2) USB POWER 5 VDC, 2.1 AMPS AUDIO MAX PER PORT INPUT LEGEND 1. Cirrus Airframe Parachute System 13.
Page 209 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 NSTRUMENT ANEL Figure 7-4: Instrument Panel & Console - Serials w/ MD302 (2 of 2) USB POWER AUDIO 5 VDC, 2.1 AMPS MAX PER PORT INPUT LEGEND 1. Cirrus Airframe Parachute System 13.
Page 210: Flight Instruments
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LIGHT NSTRUMENTS Flight Instruments Flight instruments and annunciations are displayed on the Primary Flight Display (PFD) located directly in front of the pilot. The PFD presents the primary flight instruments arranged in the conventional basic “T” config- uration.
Page 211 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LIGHT NSTRUMENTS Figure 7-5: Flight Instruments 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.
Page 212: Attitude Indicator
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LIGHT NSTRUMENTS Attitude Indicator The primary attitude indicator is shown on the upper center of the PFD and displays pitch, roll, and slip/skid information provided by the Attitude and Heading Reference System (AHRS).
Page 213: Airspeed Indicator
IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LIGHT NSTRUMENTS “earth”. The pitch scale on the attitude display is graduated in 5° incre- ments. Chevrons appear on the pitch scale at extreme pitch attitudes. The MD302 Standby Attitude Module is electrically driven. A red X indicates the attitude display is absent due to exceedance of internal rate sensors, loss of airspeed, or other reasons.
Page 214: Altimeter
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LIGHT NSTRUMENTS airspeed tape and denotes the current airspeed. Color coded bars are provided to indicate flap operating range, normal operating range, caution range, and never-exceed speed. 28 VDC for the MD302 Standby Attitude Module is supplied through the 5-amp STDBY ATTD A circuit breaker on ESS BUS 1 and the 5-amp STDBY ATTD B circuit breaker on MAIN BUS 1.
Page 215: Horizontal Situation Indicator
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LIGHT NSTRUMENTS Serials w/ MD302 Standby Attitude Module: The MD302 Standby Attitude Module is mounted on the LH bolster panel and displays the current barometric corrected altitude. The instrument senses the local barometric pressure adjusted for altimeter setting and displays the result in the Altitude Window.
Page 216: Vertical Speed Indicator
IRPLANE AND YSTEMS IRRUS ESIGN SR20 LAPS The Course Deviation Indicator (CDI) navigation source shown on the HSI is set using the CDI softkey to select GPS, NAV1, or NAV2 inputs. The course pointer is set on the GCU 479 FMS Keyboard by selecting the CRS button and then selecting the desired course by turning the multi-function knob.
Page 217: Flap Control Switch
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LAPS The wing flaps actuator, flap control switch and indicator lights are powered by 28 VDC through the 10-amp FLAPS circuit breaker on NON ESS BUS. Flap Control Switch An airfoil-shaped FLAPS control switch is located at the bottom of the vertical section of the center console.
Page 218 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LAPS Figure 7-6: Wing Flaps SR20_FM07_5350 7-24 P/N 11934-005 Reissue A...
Page 219: Landing Gear
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 ANDING 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 220: Baggage Compartment
ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 AGGAGE OMPARTMENT Should any of these symptoms occur, immediate maintenance is required. If, during taxi or landing roll, braking action decreases, let up on the toe brakes and then reapply the brakes with heavy pressure. If the brakes are spongy or pedal travel increases, pumping the pedals may build braking pressure.
Page 221: Seats
IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 EATS Serials w/ 2+1 Rear Seat: The aircraft is equipped with a retractable cargo net to secure items in the baggage compartment. Integral inertia reels attached to the rear bulkhead allow the cargo net to be extended forward, placed over baggage, and secured to the seat back via four latch assemblies.
Page 222: Rear Seats
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 ELT AND HOULDER ARNESS Rear Seats To Fold Seat Back Forward (Serials w/ Observer’s Seat) The Observer’s seat back reclines, and can be folded forward to provide a semi-flat surface for cargo extending forward from the baggage compart- ment.
Page 223: Front Seat Inflatable Restraints
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 ELT AND HOULDER ARNESS Front Seat Inflatable Restraints An inflatable shoulder harness is integral to each front seat harness. The electronic module assembly, mounted below the cabin floor, contains a crash sensor, battery, and related circuitry to monitor the deceleration rate of the airplane.
Page 224 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 ELT AND HOULDER ARNESS Fasten lower seat attachments to bench seat: LATCH Compliant Outboard Seat: Fasten lower seat attachment to the outboard anchors in the bench seat. Non-LATCH Compliant Center Seat: Using the center seat belt, fasten lower seat attachments to the bench seat as described by the manufacturer's instructions.
Page 225: Cabin Doors
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 ABIN OORS Cabin Doors Two large forward hinged doors allow crew and passengers to enter and exit the cabin. The door handles engage latching pins in the door frame receptacles at the upper aft and lower aft door perimeter. Gas charged struts provide assistance in opening the doors and hold the doors open against gusts.
Page 226: Engine Controls
ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 NGINE Engine Controls Engine controls are easily accessible to the pilot on a center console. They consist of a single-lever power (throttle) control and a mixture control lever. A friction control wheel, labeled FRICTION, on the right side of the console is used to adjust control lever resistance to rotation for feel and control setting stability.
Page 227: Engine Indicating
IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 NGINE Engine Indicating Engine information is displayed as analog-style gauges, bar graphs, and text on the MFD’s ENGINE page. When the ENGINE page is not active or in the case of an electronic display failure (backup mode), all essential engine information is displayed along the LH edge of the display.
Page 228 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 NGINE Figure 7-7: Engine Controls and Indicating Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Engine Instruments TURN BOOST PUMP ON DURING TAKEOFF, CLIMB, MANEUVERING FLIGHT, LANDING AND SWITCHING FUEL TANKS.
Page 229 IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 NGINE 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 230: Engine Lubrication System
ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 NGINE The oil pressure sensor is mounted on the rear engine case and provides a signal to the Engine Airframe Unit that is processed and transmitted to the Engine Indicating System for display.
Page 231: Air Induction System
ESIGN ECTION IRPLANE AND YSTEMS SR20 NGINE key switch, located on the instrument panel, controls ignition and starter operation. The switch is labeled OFF-R-LBOTH-START. In the OFF posi- tion, the starter is electrically isolated, the magnetos are grounded and will not operate.
Page 232: Engine Cooling
ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 ROPELLER Engine Cooling Engine cooling is accomplished by discharging heat to the oil and then to the air passing through the oil cooler, and by discharging heat directly to the air flowing past the engine. Cooling air enters the engine compartment through the two inlets in the cowling.
Page 233: Fuel System
IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 YSTEM Fuel System A 56-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 29.3-gallon capacity (28 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 234: Fuel Selector Valve
IRPLANE AND YSTEMS IRRUS ESIGN SR20 YSTEM Drain valves at the system low points allow draining the system for main- tenance and for examination of fuel in the system for contamination and grade. The fuel must be sampled prior to each flight. A sampler cup is provided to drain a small amount of fuel from the wing tank drains, the collector tank drains, and the gascolator drain.
Page 235 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 YSTEM Figure 7-8: Fuel System Schematic ANNUNCIATOR FUEL INDICATION VENT VENT FILLER FILLER L. WING TANK R. WING TANK R. WING L. WING COLLECTOR COLLECTOR SELECTOR FLAPPER FLAPPER VALVE VALVE VALVE...
Page 236: Fuel Indicating
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 YSTEM Fuel Indicating Fuel quantity is measured by float-type quantity sensors installed in each fuel tank and displayed on the Fuel Quantity Gauge. • 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 237 ESIGN ECTION IRPLANE AND YSTEMS SR20 YSTEM Target Fuel Flow is a cyan pointer placed on the fuel gauge to aid in cruise power leaning. The cyan pointer becomes available on the fuel flow gauge at engine power settings below 75%.
Page 238 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 YSTEM Figure 7-9: Fuel System Controls and Indicating Density Alt 8000 Ft Oat 31°F -1°C (ISA +0°C) Fuel System Indication TURN BOOST PUMP ON DURING TAKEOFF, LEGEND CLIMB, MANEUVERING FLIGHT, LANDING AND SWITCHING FUEL TANKS.
Page 239: Mixture Management
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 IXTURE ANAGEMENT Mixture Management The mixture control needs to be carefully monitored and managed during all phases of flight to avoid damage to the engine or a possible loss of power.
Page 240: Electrical System
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LECTRICAL YSTEM 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 241 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LECTRICAL YSTEM Figure 7-10: Electrical System Schematic 100A ALT 1 ALT 1 VOLT REG RELAY EXTERNAL POWER RELAY ALT 1 EXTERNAL SWITCH POWER 125A BAT 1 BAT 1 BAT 1 SWITCH...
Page 242: Power Distribution
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LECTRICAL YSTEM 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 243: Electrical System Protection
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LECTRICAL YSTEM Constant Power Bus (CONV) The Constant Power Bus (CONV) is fed by BAT 1 in the MCU through one 5-amp fuse located on top of the MCU. Electrical System Protection...
Page 244 ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LECTRICAL YSTEM Main Buses The circuit breaker panel MAIN BUS 1 and MAIN BUS 2 are powered by ALT 2 from the MCU Main Distribution Bus 2 and - in the event of ALT 2...
Page 245 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LECTRICAL YSTEM Figure 7-11: Circuit Breaker Panel AVIONICS LIGHTS LANDING STDBY ALT2 LIGHTS ATTD B CONV ENGINE MFD B SERVO LIGHTS INSTR STALL CABIN A/C COND CAMERA WARNING LIGHTS 12V & USB...
Page 246: Electrical System Control
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LECTRICAL YSTEM Electrical System Control The rocker type electrical system MASTER switches are ‘on’ in the up posi- tion 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 247: Ground Service Receptacle
IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LECTRICAL YSTEM regardless of the position of the MASTER switch or the individual equip- ment switches. For normal operations, the AVIONICS switch should be placed in the OFF position prior to activating the MASTER switches, starting the engine, or applying an external power source.
Page 248 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 LECTRICAL YSTEM System Emergencies, and Section 3A - Abnormal Procedures, Electrical System. For additional information on Engine Instrument Markings and Annunciations, refer to Section 2: Limitations. For additional information on the System Annunciations And...
Page 249 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 LECTRICAL YSTEM Figure 7-12: Electrical / Lighting Controls and Indicating 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.
Page 250: Lighting Systems
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 IGHTING YSTEMS Lighting Systems Exterior Lighting Refer to POH Supplement for Spectra Wing Tip Lights (p/n 11934-S56) for description of Exterior Lighting. Interior Lighting Interior lighting for the airplane consists of overhead lights for general cabin lighting, individual lights for the pilots and passengers, and dimmable panel floodlights.
Page 251: Convenience Lighting
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 IGHTING YSTEMS The panel lights operate on 28 VDC supplied through the 5-amp CABIN LIGHTS circuit breaker on MAIN BUS 1. Reading Lights Individual eyeball-type reading lights are installed in the headliner above each passenger position.
Page 252 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 IGHTING YSTEMS Key Fob Remote operation of the door locks is provided by a battery-powered key fob. Refer to Cabin Doors description in this section. Convenience Lighting Operation When the cabin light switch is in the ON position: •...
Page 253: Environmental System
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 NVIRONMENTAL YSTEM Environmental System • N • To facilitate faster cabin cooling, prior to engine start leave the cabin doors open for a short time to allow hot air to escape.
Page 254 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 NVIRONMENTAL YSTEM Figure 7-13: Standard Environmental System RAM AIR RAM AIR HOT AIR VALVE MIXING CHAMBER HEAT EXCHANGER FRESH AIR VALVE AIR FLOW VALVE CONTROL PANEL SERVO MOTOR FLOOR AIRFLOW WINDSHIELD...
Page 255 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 NVIRONMENTAL YSTEM Figure 7-14: Optional Air Conditioning System RAM AIR RAM AIR HOT AIR VALVE MIXING CHAMBER HEAT EXCHANGER COMPRESSOR FRESH AIR VALVE WINDSHIELD AIR FLOW VALVE DIFFUSER SERVO MOTOR FLOOR...
Page 256: Distribution
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 NVIRONMENTAL YSTEM Distribution Ventilation and cooling is provided by ducting fresh air from a NACA inlet on the RH cowl to the mixing chamber located on the lower RH portion of the firewall.
Page 257: Airflow Selection
IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 NVIRONMENTAL YSTEM In Air Conditioning mode (optional), R134A refrigerant enters the engine mounted compressor as a vapor and is pressurized until the heat-laden vapor reaches a point much hotter than the outside air. The compressor then pumps the vapor to the condenser where it cools, changes to a liquid, and passes to the receiver-drier.
Page 258: Temperature Selection
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 NVIRONMENTAL YSTEM When the Windshield selector button is pushed, the cabin floor butterfly valve is closed providing maximum airflow to the windshield diffuser. Temperature Selection The temperature selector is electrically linked to the hot and cold air valves.
Page 259 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 NVIRONMENTAL YSTEM Figure 7-15: Environmental System Operation Rotating the selector controls the volume of airflow allowed into the cabin distribution system through use of an electro-mechanical linkage to a butterfly (hot air) valve in the mixing chamber on the forward firewall.
Page 260: Stall Warning System
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 TALL ARNING YSTEM Stall Warning System The airplane is equipped with an electro-pneumatic stall warning system to provide audible warning of an approach to aerodynamic stall. The system consists of an inlet in the leading edge of the right wing, a pressure switch and associated plumbing.
Page 261: Pitot Heat Annunciation
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 ITOT TATIC YSTEM Pitot Heat Annunciation Illumination of the PITOT HEAT FAIL Caution indicates that the Pitot Heat switch is ON and the Pitot heater is not receiving electrical current. Illumination of PITOT HEAT REQD Caution indicates the system detects OAT is less than 41 °F (5 °C) and Pitot Heat Switch is OFF.
Page 262 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 ITOT TATIC YSTEM Figure 7-16: Pitot-Static System - Serials w/o MD302 (1 of 2) ADAHRS 1 ADAHRS 2 (optional) PFD Air Data AIRSPEED ALTIMETER INDICATOR ALTERNATE PITOT-STATIC STATIC WATER TRAPS AIR SOURCE...
Page 263 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 ITOT TATIC YSTEM Figure 7-16: Pitot-Static System - Serials w/ MD302 (2 of 2) ADAHRS 1 ADAHRS 2 (optional) PFD Air Data MD302 STANDBY ATTITUDE MODULE ALTERNATE PITOT-STATIC STATIC WATER TRAPS...
Page 264: Avionics
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 VIONICS 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, and consists of the following components: •...
Page 265 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 VIONICS Figure 7-17: Perspective+ Integrated Avionics System Schematic XM SATELLITE DATA LINK RECEIVER (optional) KEYBOARD MAG 2 MAG 1 AUTOPILOT MODE CONTROLLER (optional) ADAHRS 1 ADAHRS 2 IRIDIUM (optional) GLOBAL SATELLITE...
Page 266 ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 VIONICS GDU 1050A Primary Flight Display (PFD), 10-inch, or GDU 1250A, 12-inch (Optional) The Primary Flight Display, located directly in front of the pilot, is intended to be the primary display of flight parameter information (attitude, airspeed, heading, and altitude) during normal operations.
Page 267 IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 VIONICS GCU 479 Flight Management System Keyboard The Flight Management System Keyboard is found on the upper section of the center console and is the primary interface for avionics system data entry, PFD/MFD operation, NAV/COM tuning, and course selection.
Page 268 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 VIONICS Figure 7-18: Perspective+ Integrated Avionics System (1 of 2) 3 4 5 6 7 8 9 13 14 15 19 20 21 Legend 1. Soft Keys 12. MFD 2. PFD 13.
Page 269 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 VIONICS Figure 7-18: Perspective+ Integrated Avionics System (2 of 2) Flight Management System Keyboard LEGEND 22. MFD Clear/Cancel Information 32. MFD Range/Pan Joystick 23. MFD Flight Plan Page 33. Frequency Transfer (121.5 Tune) 24.
Page 270 ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 VIONICS GIA 63W/64W Integrated Avionics Units The Integrated Avionics Units, located behind the MFD and instrument panel, function as the main communication hub, linking all Integrated Avionics System components with the PFD. Each Integrated Avionics Unit...
Page 271 IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 VIONICS Annunciation and Alert System Aircraft annunciations and alerts are displayed in the Crew Alerting System (CAS) window located to the right of the altimeter and VSI. Aircraft annunciations are grouped by criticality and sorted by order of appearance with the most recent message on top.
Page 272 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 VIONICS While executing an LNAV/VNAV approach, between FAF and missed approach point (MAP), excessive deviation indicators appear as vertical yellow lines to indicate an area where the vertical deviation exceeds ±75 feet.
Page 273 ESIGN ECTION IRPLANE AND YSTEMS SR20 VIONICS Serials w/ dual Air Data Computer (ADC) installations: The Outside Air Temperature (OAT) from the selected-side ADC will be used. If the OAT becomes invalid, the VDI on that side will be flagged as invalid. The pilot must select the off-side ADC sensor and VDI will return regardless of if prior to or after the FAF.
Page 274 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 VIONICS Figure 7-19: Baro-VNAV Vertical Deviation Indicator 29.92 NOTE LEGEND While Baro-VNAV is being utilized, 1.Excessive Deviation the Glidepath Indicator appears as Indicator a magenta pentagon. 2.Glidepath Indicator SR20_FM07_5361 7-80 P/N 11934-005...
Page 275 7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 VIONICS Optional Avionics GTX 345 Mode S Transponder w/ UAT in The GTX 345 solid state transponder communicates with the primary Inte- grated Avionics Unit, provides Modes A and C interrogation/reply capabil- ities, and performs the following functions: •...
Page 276 ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 VIONICS 28 VDC for Satellite Datalink Receiver operation is supplied through the 5-amp WEATHER/DATA LINK circuit breaker on AVIONICS. Refer to the Perspective+ Integrated Avionics System Pilot’s Guide for a complete description of the system, its operating modes, and additional detailed operating procedures.
Page 277 IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 VIONICS tion is supplied through the 3-amp DME/ADF circuit breaker on AVIONICS. 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 discus- sion of the system.
Page 278 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 VIONICS • Runway and terrain features during climb, descent, and low altitude maneuvering. The EVS sensor, located on the underside of the LH wing, contains a long-wave infrared camera that produces an infrared image and a lowlight CMOS camera that produces a visible image.
Page 279 IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 VIONICS Gateway Module The Gateway Module collects aircraft data from the aircraft avionics and provides a cellular connection while on the ground for automatic transmis- sion of aircraft data. This data can then be accessed by the pilot via a mobile application provided by Cirrus.
Page 280 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 VIONICS Figure 7-20: Equipment Locations LEGEND 1. GSU 75 ADAHRS 1 2. Integrated Avionics Unit 1 3. GSU 75 ADAHRS 2 (opt) 4. Avionics Cooling Fan 5. Integrated Avionics Unit 2 6.
Page 281: Avionics Support Equipment
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 VIONICS 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 282 IRPLANE AND YSTEMS IRRUS ESIGN SR20 VIONICS The forward headset mics use the remote Push-To-Talk (PTT) switches located on the top of the associated control yoke grip. The rear headsets do not have COM transmit capabilities and do not require PTT switches.
Page 283: Cabin Features
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 ABIN EATURES Cabin Features Emergency Locator Transmitter (ELT) The airplane is equipped with a self-contained Artex ELT 1000 406 MHz emergency locator transmitter that generates a signal to assist in search and rescue for missing aircraft.
Page 284 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 ABIN EATURES Figure 7-21: Artex ELT 1000 System CENTER CONSOLE (REF) ELT SHELF (REF) LEGEND 1. LED Annunciator 2. Remote Switch 3. Antenna 4 Remote Cable 5. Main Control Switch 6. Antenna Jack 7.
Page 285: Fire Extinguisher
IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 ABIN EATURES To Use ELT portably 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 acci- dent.
Page 286: Hour Meters
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 ABIN EATURES 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 287: Cirrus Airframe Parachute System
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 IRRUS IRFRAME ARACHUTE YSTEM Cirrus Airframe Parachute System The airplane is equipped with a Cirrus Airframe Parachute System (CAPS) designed to bring the airplane and its occupants to the ground in the event of a life-threatening emergency.
Page 288: Activation Handle
7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 IRRUS IRFRAME ARACHUTE YSTEM A three-point harness connects the airplane fuselage structure to the para- chute. The aft harness strap is stowed in the parachute canister and attached to the structure at the aft baggage compartment bulkhead. The forward harness straps are routed from the canister to firewall attach points just under the surface of the fuselage skin.
Page 289: Deployment Characteristics
7: A IRRUS ESIGN ECTION IRPLANE AND YSTEMS SR20 IRRUS IRFRAME ARACHUTE YSTEM The pin is inserted through the handle retainer and barrel locking the handle in the “safe” position. A “Remove Before Flight” streamer is attached to the pin.
Page 290 7: A ECTION IRPLANE AND YSTEMS IRRUS ESIGN SR20 IRRUS IRFRAME ARACHUTE YSTEM Intentionally Left Blank 7-96 P/N 11934-005 Reissue A...
Page 291 Airworthiness Directives ..............5 Airplane Inspection Periods..............5 Annual Inspection................5 100-Hour Inspection ................6 Cirrus Design Progressive Inspection Program ........ 6 Pilot Performed Preventative Maintenance ........7 Ground Handling ................. 8 Application of External Power ............8 Towing....................9 Taxiing.....................
Page 292 8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 Care of Graphics ................25 Cleaning Interior Surfaces ..............29 Interior Windshield and Windows ............ 29 Instrument Panel and Electronic Display Screens......30 Headliner and Trim Panels .............. 30 Leather Upholstery and Seats ............31 Carpets ....................
Page 293: Introduction
IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 NTRODUCTION Introduction This section provides general guidelines for handling, servicing, and main- taining your aircraft. In order to ensure continued safe and efficient opera- tion of your airplane, keep in contact with your Authorized Cirrus Service Center to obtain the latest information pertaining to your aircraft.
Page 294: Obtaining Publications
8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 IRPLANE ECORDS AND ERTIFICATES requiring a Service Bulletin. Pay careful attention to the Service Advi- sory information. Obtaining Publications Pilot’s Operating Handbooks and aircraft service publications can be obtained from Cirrus at www.cirrusaircraft.com, or the Cirrus Connection at www.cirrusconnection.com.
Page 295: Airworthiness Directives
8: H IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 IRWORTHINESS IRECTIVES Other Documents Note Airplane Logbook Must be made available upon request. Engine Logbook Must be made available upon request. Pilot’s Checklist Available in cockpit at all times. Airworthiness Directives...
Page 296: 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(d). The Cirrus Design Progressive Inspection Program provides for the complete inspection of the airplane utilizing a five-phase cyclic inspection program.
Page 297: Pilot Performed Preventative Maintenance
8: H IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 IRPLANE NSPECTION ERIODS Pilot Performed Preventative Maintenance The holder of a Pilot Certificate issued under CFR Part 61 may perform certain preventive maintenance described in CFR 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 298: Ground Handling
8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 ROUND ANDLING Logbook Entry After any of the above work is accomplished, appropriate logbook entries must be made. Logbook entries should contain: • The date the work was accomplished. • Description of the work.
Page 299: Towing
8: H IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 ROUND ANDLING To Remove External Power from Airplane If battery power is no longer required, set BAT 1 switch ‘off.’ Pull external power unit plug. Towing The airplane may be moved on the ground by the use of the nose wheel...
Page 300: Taxiing
ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 ROUND ANDLING To obtain a minimum radius turn during ground handling, the airplane may be rotated around either main landing gear by pressing down on the fuselage just forward of the horizontal stabilizer to raise the nose wheel off the ground.
Page 301: Parking
8: H IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 ROUND ANDLING 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 302: Tie Down
8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 ROUND ANDLING Tie Down The airplane should be moored for immovability, security, and protection. FAA Advisory Circular AC 20-35C, Tie-down Sense, contains additional information regarding preparation for severe weather, tie down, and related information.
Page 303: Servicing
8: H IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 ERVICING Servicing Landing Gear Servicing The main landing gear wheel assemblies use 15 x 6.00 x 6 tubeless tires. The nose wheel assembly uses a 5.00 x 5 tubeless tire. Always keep tires inflated to the rated pressure to obtain optimum perfor- mance and maximum service.
Page 304: Propeller Servicing
8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 ERVICING To Inflate Tires Open access doors on wheel pants to gain access to valve stems. It may be necessary to move airplane to get valve stem aligned with the access hole.
Page 305: Fuel System Servicing
IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 ERVICING An oil filler cap and dipstick are located at the right rear of the engine and are accessible through an access door on the top right side of the engine cowling. • CAUTION •...
Page 306 8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 ERVICING To Refuel Airplane • CAUTION • Aviation grade 100 LL (blue) or 100 (green) fuel is the minimum octane approved for use in this airplane. Place fire extinguisher near fuel tank being filled.
Page 307 IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 ERVICING Fuel Contamination and Sampling Typically, fuel contamination results from foreign material such as water, dirt, rust, and fungal or bacterial growth. Additionally, chemicals and addi- tives that are incompatible with fuel or fuel system components are also a source of fuel contamination.
Page 308: Battery Service
ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 ERVICING 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. The battery vent is connected to an acid resistant plastic tube that vents gases and electrolyte overflow overboard.
Page 309: Artex Elt 1000 Servicing
IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 ERVICING Artex ELT 1000 Servicing The ELT batteries must be inspected in accordance with the Airplane Maintenance Manual, 5-20 - Scheduled Maintenance Checks. The ELT batteries must be replaced upon reaching the date stamped on the batteries, after an inadvertent activation of unknown duration, or when- ever the batteries have been in use for one cumulative hour.
Page 310 ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 ERVICING multiple flashes separated by 1-second periods, will begin to display after approximately 1 second. Flash Codes displayed with the associated conditions are as follows: 1-Flash: Indicates that the system is operational and that no error conditions were found.
Page 311: Cleaning Exterior Surfaces
8: H IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 LEANING XTERIOR URFACES Cleaning Exterior Surfaces • CAUTION • Prior to cleaning, place the airplane in a shaded area to allow the surfaces to cool. The airplane should be washed with a mild soap and water. Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause corrosion of metal.
Page 312: Enhanced Vision System Sensor Windows (Optional)
8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 LEANING XTERIOR URFACES To Clean Exterior Windshield and Windows Remove grease or oil using a soft cloth saturated with kerosene then rinse with clean, fresh water. • N • Wiping with a circular motion can cause glare rings. Use an up and down wiping motion on the windshield in the direction of the airflow to prevent this.
Page 313: Landing Gear
8: H IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 LEANING XTERIOR URFACES To Clean Engine Compartment Place a large pan under the engine to catch waste. Remove induction air filter and seal off induction system inlet. With the engine cowling removed, spray or brush the engine with solvent or a mixture of solvent and degreaser.
Page 314: Recommended Exterior Cleaning Products
8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 LEANING XTERIOR URFACES Recommended Exterior Cleaning Products Cleaning Application Cleaning Product Supplier Painted Exterior Pure Carnauba Wax Any Source Mothers California Gold Mothers Polish Pure Carnauba Wax RejeX High Gloss Corrosion...
Page 315: Care Of Graphics
8: H IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 LEANING XTERIOR URFACES Care of Graphics Graphics require care similar to any fine paint finish. Use high quality products designed specifically for use on automobile finishes. Use products in accordance with the manufacturer’s instructions.
Page 316 8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 LEANING XTERIOR URFACES To Spot Clean Difficult Contaminants Difficult contaminants such as bugs, bird droppings, or tree sap may require spot cleaning. • CAUTION • To prevent scratching the graphic, refrain from rough scrubbing and the use of abrasive tools.
Page 317 8: H IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 LEANING XTERIOR URFACES Graphic Restoration If typical cleaning methods fail to produce satisfactory results, refer to the recommended restoration products and mixtures below to help preserve the condition of the graphics on your aircraft.
Page 318 8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 LEANING XTERIOR URFACES Recommended Graphic Restoration Products and Mixtures Film or Finish Type Cleaning Product or Mixture Supplier Smooth Gloss 3M™ Perfect-it™ Show Car Paste 3M Company Wax 39526 Meguiar's Gold Class™ Carnuaba...
Page 319: Cleaning Interior Surfaces
8: H IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 LEANING NTERIOR URFACES Cleaning Interior Surfaces Seats, carpet, upholstery panels, and headliners should be vacuumed at regular intervals to remove surface dirt and dust. While vacuuming, use a fine bristle nylon brush to help loosen particles.
Page 320: Instrument Panel And Electronic Display Screens
8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 LEANING NTERIOR URFACES 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...
Page 321: Leather Upholstery And Seats
8: H IRRUS ESIGN ECTION ANDLING AND ERVICING SR20 LEANING NTERIOR URFACES Leather Upholstery and Seats For routine maintenance, occasionally wipe leather upholstery with a soft, damp cloth. For deeper cleaning, start with mix of mild detergent and water and, if necessary, work your way up to the products available from Cirrus for more stubborn marks and stains.
Page 322 8: H ECTION ANDLING AND ERVICING IRRUS ESIGN SR20 LEANING NTERIOR URFACES Recommended Interior Cleaning Products Cleaning Application Cleaning Product Supplier Interior Windshield Plastic and Glass Prist Aerospace and Windows Cleaner Display Screens Optimax PhotoDon Cabin Interior Mild Dishwasher Any Source...
Page 323 9: L IRRUS ESIGN ECTION OG OF UPPLEMENTS SR20 Section 9: Log of Supplements Table of Contents As Required P/N 11934-005 Reissue A...
Page 324 OG OF UPPLEMENTS IRRUS ESIGN SR20 FAA Approved POH Supplements must be in the airplane for flight operations when the subject optional equipment is installed or the special operations are to be performed. This Log of Supplements shows all Cirrus Supplements available for the aircraft at the corresponding date of the revision level shown in the lower left corner.
Page 325 10: S IRRUS ESIGN ECTION AFETY NFORMATION SR20 Section 10: Safety Information Table of Contents Introduction..................3 Taxiing, Steering, and Braking Practices ..........3 Operating Practices................4 Brake Maintenance ................4 Cirrus Airframe Parachute System (CAPS)......... 5 Deployment Scenarios ..............5 Mid-Air Collision ................
Page 326 10: S ECTION AFETY NFORMATION IRRUS ESIGN SR20 Intentionally Left Blank 10-2 P/N 11934-005 Reissue A...
Page 327: Introduction
IRRUS ESIGN ECTION AFETY NFORMATION SR20 NTRODUCTION Introduction This aircraft is designed to operate safely and efficiently in a flight environ- ment. However, like any other aircraft, pilots must maintain proficiency to achieve maximum safety, utility, and economy. Cirrus strongly recom-...
Page 328: Operating Practices
10: S ECTION AFETY NFORMATION IRRUS ESIGN SR20 AXIING TEERING RAKING RACTICES Operating Practices 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. Deceleration or taxi speed control using brakes but without a reduction in power will result in increased brake temperature.
Page 329: Cirrus Airframe Parachute System (Caps)
10: S IRRUS ESIGN ECTION AFETY NFORMATION SR20 (CAPS) IRRUS IRFRAME ARACHUTE YSTEM • Leaking brake fluid at the caliper. This can be observed by checking for evidence of fluid on the ground or deposited on the underside of the wheel fairing.
Page 330: Mid-Air Collision
10: S ECTION AFETY NFORMATION IRRUS ESIGN (CAPS) SR20 IRRUS IRFRAME ARACHUTE YSTEM Mid-Air Collision A mid-air collision likely will render the airplane unflyable by damaging the control system or primary structure. If a mid-air collision occurs, immediately evaluate if the airplane is controllable and structurally capable of continued safe flight and landing.
Page 331: Pilot Incapacitation
10: S IRRUS ESIGN ECTION AFETY NFORMATION SR20 (CAPS) IRRUS IRFRAME ARACHUTE YSTEM Pilot Incapacitation Pilot incapacitation may be the result of anything from a pilot's medical condition to a bird strike that injures the pilot. If incapacitation occurs and the passengers are not trained to land the aircraft, CAPS activation by the passengers is highly recommended.
Page 332: Deployment Attitude
10: S ECTION AFETY NFORMATION IRRUS ESIGN (CAPS) SR20 IRRUS IRFRAME ARACHUTE YSTEM Deployment Attitude The CAPS has been tested in all flap configurations at speeds ranging from to V . Most CAPS testing was accomplished from a level attitude.
Page 333: Water Landings
10: S IRRUS ESIGN ECTION AFETY NFORMATION SR20 (CAPS) IRRUS IRFRAME ARACHUTE YSTEM There is the possibility that one or both doors could jam at impact. If this occurs, to exit the airplane, the occupants will have to force open a partially jammed door or break through a door window using the Emergency Exit Hammer located in the lid of the center armrest.
Page 334: Ground Gusts
10: S ECTION AFETY NFORMATION IRRUS ESIGN (CAPS) SR20 IRRUS IRFRAME ARACHUTE YSTEM Ground Gusts If it is known or suspected that ground gusts are present in the landing zone, there is a possibility that the parachute could drag the airplane after touchdown, especially if the terrain is flat and without obstacles.

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