CIRRUS DESIGN SR20 Pilot Operating Handbook Download Page 238 | Manualshive

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7-68

P/N 11934-003

Section 7

Cirrus Design

Airplane Description

SR20

222) below the parachute canister. BAT 2 is charged from the circuit
breaker panel Essential Bus.

The Master Control Unit (MCU) is located on the left firewall. The MCU
controls ALT 1, ALT 2, starter, landing light, external power, and
power generation functions. In addition to ALT 1 and ALT 2 voltage
regulation, the MCU also provides external power reverse polarity
protection, alternator overvoltage protection, as well as alternator fail
and overcurrent annunciations. Power is distributed to the airplane
circuit panel buses through Main and Essential Buses in the MCU.
During normal operation, the alternators feed their respective
Distribution Bus independently (ALT 1 feeds Main Distribution Bus and
ALT 2 feeds the Essential Distribution Bus). The distribution buses are
interconnected by two 50-amp fuses and a diode. The diode prevents
ALT 2 from feeding the Main Distribution Bus. Additionally, since ALT
2 / Essential Distribution Bus voltage is slightly higher than ALT 1 /
Main Distribution Bus voltage, ALT 1 will not feed the Essential
Distribution Bus unless ALT 2 fails.

Power Distribution

The power distribution system for the SR20 consists of the Main
Distribution Bus and the Essential Distribution Bus in the MCU and
associated buses in the Circuit Breaker panel. The circuit breaker
panel is located on the left side of the console next to the pilots right
knee.

For normal operation, the Essential Buses in the circuit breaker panel
are powered from the Essential Distribution Bus in the MCU through
25-amp circuit breakers. BAT 2 is connected directly to the Essential
Bus in the circuit breaker panel and will power the bus should the
voltage coming from the MCU distribution buses drop below the
battery voltage. Additionally, in the event of an ALT 2 failure, the circuit
breaker panel Essential Bus will be powered from ALT 1 through the
Main distribution and Essential distribution buses in the MCU. Main
Bus 1, Main Bus 2, and the equipment Non-Essential Bus in the circuit
breaker panel are powered from ALT 1 through the Main Distribution
Bus in the MCU. The Avionics Non-Essential Bus in the circuit breaker
panel is powered from Main Bus 1.

Revision A5

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Summary of Contents for SR20

Page 1: ...3 This document must be carried in the airplane at all times and be kept within the reach of the pilot during all flight operations THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY FAR PART 23 AND ADDITIONAL INFORMATION PROVIDED BY CIRRUS DESIGN AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL Model Serial Num SR20 _____________ Registration Num _________________...

Page 2: ...Copyright 2003 All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth MN 55811 ...

Page 3: ...nance servicing requirements and performance data contained in this Handbook are mandatory for compliance with FAA operating rules and for continued airworthiness of the airplane This Handbook includes the material required to be furnished to the pilot by the Federal Aviation Regulations FARs and additional information provided by Cirrus Design Corporation and constitutes the FAA Approved Airplane...

Page 4: ...t section The Handbook is divided into ten sections as follows Section 1 General Section 2 Limitations Section 3 Emergency Procedures Section 4 Normal Procedures Section 5 Performance Data Section 6 Weight Balance Equipment List Section 7 Airplane Systems Description Section 8 Handling Servicing Maintenance Section 9 Supplements Section 10 Safety Information The data presented in this Handbook is ...

Page 5: ...Highlights page The Instruction Sheet is intended to assist the manual holder in removing superseded pages and inserting new or superseding pages The List of Effective Pages shows the issue or revision status of all pages in the Handbook The Revision Highlights page gives a brief description of changes made to each page in the current revision Identifying Revised Material Each page in the Handbook...

Page 6: ... Section 9 of this Handbook contains FAA Approved Supplements necessary to safely and efficiently operate the SR20 when equipped with optional equipment not provided with the standard airplane or not included in the Handbook Supplements are essentially mini handbooks and may contain data corresponding to most sections of the Handbook Data in a supplement either adds to supersedes or replaces simil...

Page 7: ...in information such as supplements that is not applicable to their airplane Warnings Cautions and Notes Warnings Cautions and Notes are used throughout this Handbook to focus attention on special conditions or procedures as follows WARNING Warnings are used to call attention to operating procedures which if not strictly observed may result in personal injury or loss of life Caution Cautions are us...

Page 8: ...vi P N 11934 003 Pilot s Operating Handbook Cirrus Design Foreword SR20 Reissue A Intentionally Left Blank ...

Page 9: ...aximum Certificated Weights 1 7 Cabin and Entry Dimensions 1 7 Baggage Spaces and Entry Dimensions 1 7 Specific Loadings 1 7 Symbols Abbreviations and Terminology 1 8 General Airspeed Terminology and Symbols 1 8 Meteorological Terminology 1 9 Engine Power Terminology 1 10 Performance and Flight Planning Terminology 1 10 Weight and Balance Terminology 1 11 Revision A3 ...

Page 10: ...1 2 P N 11934 003 Section 1 Cirrus Design General SR20 Intentionally Left Blank Revision A3 ...

Page 11: ...ng fueling sheltering and handling the airplane during ground operations Additionally this section contains definitions or explanations of symbols abbreviations and terminology used throughout this handbook Note For specific information regarding the organization of this Handbook revisions supplements and procedures to be used to obtain revision service for this handbook refer to the Foreword imme...

Page 12: ...n General SR20 Figure 1 1 76 2 BLADE 74 3 BLADE 35 5 11 0 9 2 7 26 0 SR20_FM01_1004A NOTE Wing span includes position and strobe lights Prop ground clearance at 3000 lb 7 2 blade 8 3 blade Wing Area 135 2 sq ft Airplane Three View Revision A3 ...

Page 13: ...1002 GROUND TURNING CLEARANCE TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER ACTUAL TURNING RADIUS MAY VARY A S MUCH AS THREE FEET RADIUS FOR WING TIP RADIUS FOR INSIDE GEAR 6 RADIUS FOR OUTSIDE GEAR RADIUS FOR NOSE GEAR 2 12 Figure 1 2 Turning Radius Reissue A ...

Page 14: ...l Injected Engine Cooling Air Cooled Engine Type Horizontally Opposed Direct Drive Horsepower Rating 200 hp 2700 rpm Propeller Hartzell Propeller Type Constant Speed Two Blade Propeller Model Number BHC J2YF 1BF F7694 Diameter 76 0 74 5 Minimum Three Blade Propeller Model Number PHC J3YF 1MF F7392 1 Diameter 74 0 72 5 Minimum Model Number PHC J3YF 1RF F7392 1 Diameter 74 0 72 5 Minimum Revision A1...

Page 15: ...cated Weights Maximum Gross for Takeoff 3000 lb 1361 Kg Maximum Landing Weight 2900 lb 1315 Kg Maximum Baggage Compartment Loading 130 lb 59 Kg Standard Empty Weight 2050 lb 930 Kg Maximum Useful Load 950 lb 431 Kg Full Fuel Payload 622 lb 282 Kg Cabin and Entry Dimensions Dimensions of the cabin interior and entry door openings are illustrated in detail in Section 6 Baggage Spaces and Entry Dimen...

Page 16: ...reatest flight distance is attained per unit of altitude lost with power off VO Operating Maneuvering Speed is the maximum speed at which application of full control movement will not overstress the airplane VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position VNO Maximum Structural Cruising Speed is the speed that should not be exceede...

Page 17: ...C 3 the pressure at sea level is 29 92 in Hg 1013 2 millibars and 4 the temperature gradient from sea level to the altitude at which the temperature is 56 5 C is 0 00198 C per foot and zero above that altitude MSL 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 r...

Page 18: ...ed Static RPM is RPM attained during a full throttle engine runup when the airplane is on the ground and stationary g One g is a quantity of acceleration equal to that of earth s gravity Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during taxi takeoff and landing was actually demonstrated during certification testing Demonstr...

Page 19: ...has a fixed location in the airplane The basic empty weight includes the weight of unusable fuel and full oil MAC Mean Aerodynamic Chord is the chord drawn through the centroid of the wing plan area LEMAC Leading Edge of Mean Aerodynamic Chord is the forward edge of MAC given in inches aft of the reference datum fuselage station Maximum Gross Weight is the maximum permissible weight of the airplan...

Page 20: ...rtical plane from which all horizontal distances are measured for balance purposes Tare is the weight of all items used to hold or position the airplane on the scales for weighing Tare includes blocks shims and chocks Tare weight must be subtracted from the associated scale reading Reissue A ...

Page 21: ...oad Factor Limits 2 10 Minimum Flight Crew 2 10 Kinds of Operation 2 11 Kinds of Operation Equipment List 2 11 Icing 2 15 Runway Surface 2 15 Instrument Procedures 2 15 Taxi Power 2 16 Fuel Limits 2 16 Maximum Operating Altitude 2 16 Environmental Conditions 2 16 Maximum Occupancy 2 16 Systems and Equipment Limits 2 17 Cirrus Airframe Parachute System CAPS 2 17 Primary Flight Display 2 17 Multi Fu...

Page 22: ...2 2 P N 11934 003 Section 2 Cirrus Design Limitations SR20 Placards 2 21 Revision A6 ...

Page 23: ...ting limitations instrument markings and basic placards required by regulation and necessary for the safe operation of the SR20 and its standard systems and equipment Refer to Section 9 of this handbook for amended operating limitations for airplanes equipped with optional equipment Compliance with the operating limitations in this section and in Section 9 is required by Federal Aviation Regulatio...

Page 24: ...VNO 165 165 Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution VO 3000 Lb 131 131 Operating Maneuvering Speed is the maximum speed at which full control travel may be used Below this speed the airplane stalls before limit loads are reached Above this speed full control movements can damage the airplane VFE 50 Flaps 100 Flaps 1...

Page 25: ... Arc 56 100 Full Flap Operating Range Lower limit is the most adverse stall speed in the landing configuration Upper limit is the maximum speed permissible with flaps extended Green Arc 65 165 Normal Operating Range Lower limit is the maximum weight stall at most forward C G with flaps retracted Upper limit is the maximum structural cruising speed Yellow Arc 165 200 Caution Range Operations must b...

Page 26: ...082 If engine oil must be added to the factory installed oil add only MIL L 6082 straight mineral oil After Engine Break In Use only oils conforming to Teledyne Continental Specification MHS 24 Ashless Dispersant Lubrication Oil or MHS 25 Synthetic Lubrication Oil Refer to Section 8 Oil Servicing Oil viscosity range as follows All Temperatures 15W 50 or 20W 50 Below 40 F 4 C SAE 30 or 10W 30 Above...

Page 27: ...Type Constant Speed Two Blade Propeller Model Number BHC J2YF 1BF F7694 Diameter 76 0 74 5 Minimum Three Blade Propeller Model Number PHC J3YF 1MF F7392 1 Diameter 74 0 72 5 Minimum Model Number PHC J3YF 1RF F7392 1 Diameter 74 0 72 5 Minimum Weight Limits Maximum Takeoff Weight 3000 lb 1361 kg Note All weights in excess of 2900 pounds 1315 kg must consist of wing fuel Maximum Landing Weight 2900 ...

Page 28: ...der Head Temperature 200 F 500 F 240 420 F 420 460 F 460 F Exhaust Gas Temp 1250 1650 F Manifold Pressure 10 35 Inches Hg 15 29 5 in Hg 29 5 35 in Hg Fuel Flow 0 18 U S Gal Hr 7 13 GPH Oil Temperature 50 240 F 100 240 F 240 F Oil Pressure 0 100 PSI 10 psi Idle 30 60 psi 10 30 psi 60 100 psi 100 psi Cold Fuel Quantity 0 28 U S Gallon 0 gal 0 8 2 gal Miscellaneous Instrumentation Voltmeter 16 32 Vol...

Page 29: ...e 2 4 FORWARD LIMIT The forward limit is FS 138 7 12 0 MAC at 2110 lb with straight line taper to FS 141 0 16 7 MAC at 2694 lb and to FS 144 1 23 1 MAC at 3000 lb AFT LIMIT The aft limit is FS 144 6 24 1 MAC at 2110 lb with straight line taper to FS 147 4 30 0 MAC at 2570 lb to FS 148 1 31 5 MAC at 2900 lb and to FS 148 0 31 3 MAC at 3000 lb Figure 2 4 C G Envelope Revision A5 ...

Page 30: ...n 3 Emergency Procedures Inadvertent Spiral Spin Entry This airplane is certified in the normal category and is not designed for aerobatic operations Only those operations incidental to normal flight are approved These operations include normal stalls chandelles lazy eights and turns in which the angle of bank is limited to 60 Flight Load Factor Limits Flaps UP 0 3000 lb 3 8g 1 9g Flaps 50 3000 lb...

Page 31: ...for airworthiness under the listed kind of operation Those minimum items of equipment necessary under the operating rules are defined in FAR Part 91 and FAR Part 135 as applicable Note All references to types of flight operations on the operating limitations placards are based upon equipment installed at the time of Airworthiness Certificate issuance System Instrument and or Equipment Kinds of Ope...

Page 32: ...ired Equipment Furnishings Emergency Locator Transmitter 1 1 1 1 Restraint System A R A R A R A R One Seat Belt for each occupant Fire Protection Fire Extinguisher 1 1 1 1 Flight Controls Flap Position Lights 3 3 3 3 Flap System 1 1 1 1 Pitch Trim Indicator 1 1 1 1 Pitch Trim System 1 1 1 1 Roll Trim Indicator 1 1 1 1 Roll Trim System 1 1 1 1 Stall Warning System 1 1 1 1 Fuel System Instrument and...

Page 33: ...s Anticollision Lights 2 2 2 2 Instrument Lights Must be operative Navigation Lights 4 4 Landing Light 1 1 For hire operations Navigation Pitot Static PFD Attitude Indicator 1 1 Serials 1337 subs w PFD only Standby Attitude Indicator 1 1 Serials 1337 subs w PFD only PFD Airspeed Indicator 1 1 Serials 1337 subs w PFD only Standby Airspeed Indicator 1 1 1 1 Serials 1337 subs w PFD only System Instru...

Page 34: ...1 1 Vertical Speed Indicator Magnetic Compass 1 1 1 1 Attitude Gyro 1 1 HSI 1 1 Turn Coordinator Gyro 1 1 Clock 1 1 Nav Radio 1 1 Pitot System 1 1 1 1 Static System Normal 1 1 1 1 Multi Function Display Engine Indicating Cylinder Head Temperature Indication Exhaust Gas Temperature Indication Fuel Flow Indication 1 1 1 1 System Instrument and or Equipment Kinds of Operation Remarks Notes and or Exc...

Page 35: ... needle oscillation in aircraft configured with a 2 blade propeller while conducting instrument procedures that use a localizer or Simplified Directional Facility SDF navaid engine speed above 2600 rpm is prohibited Manifold Pressure Indication 1 1 1 1 Oil Pressure Indication 1 1 1 1 Oil Quantity Indicator Dipstick 1 1 1 1 Oil Temperature Indication 1 1 1 1 Engine Speed 1 1 1 1 Special Equipment C...

Page 36: ... 30 3 U S gallons 114 5 L Total Usable Fuel all flight conditions 56 0 U S gallons 212 0 L Maximum Operating Altitude Maximum Operating Altitude 17 500 ft MSL The operating rules FAR Part 91 and FAR Part 135 require the use of supplemental oxygen at specified altitudes below the maximum operating altitude Refer to Oxygen System Limitations in this Section Environmental Conditions For operation of ...

Page 37: ... Flight Rules IFR is not permitted with the PFD or any standby indicator attitude indicator or magnetic compass inoperative Refer to Kinds of Operation Equipment List Note The Avidyne PFD software version is displayed on the PFD during system startup 4 Serials 1337 and subsequent before installation of PFD software version 530 00123 XXX REV05 where X can be any digit from 0 to 9 Backcourse approac...

Page 38: ...and tracking the following limitations apply a The autopilot must be disengaged no later than 100 feet below the Minimum Descent Altitude b The autopilot must be disconnected during approach if course deviation exceeds 50 The approach should only be continued by hand flying the airplane c The autopilot must be disengaged at the Decision Height d 12 knot maximum crosswind component between the miss...

Page 39: ... limitations 3 Under no circumstances should the Map page terrain representations be used as a basis for terrain avoidance 4 The Avidyne electronic checklists display supplements the Pilot Operating Handbook checklists and is advisory only The electronic checklists must not be used as the primary set of on board airplane checklists 5 The MFD interfaces with separately approved sensor installations...

Page 40: ...bed in the AFM Supplement noted above Inflatable Restraint System Serials 1268 thru 1540 after SB 2X 25 14 and serials 1541 and subsequent Use of a child safety seat with the inflatable restraint system is prohibited Flap Limitations Approved Takeoff Settings UP 0 or 50 Approved Landing Settings Up 0 50 or 100 Paint To ensure that the temperature of the composite structure does not exceed 150 F 66...

Page 41: ...P N 11934 003 2 21 Cirrus Design Section 2 SR20 Limitations Placards Figure 2 5 Placards Sheet 1 of 7 Revision A5 ...

Page 42: ...2 22 P N 11934 003 Section 2 Cirrus Design Limitations SR20 Figure 2 5 Placards Sheet 2 of 7 Revision A5 ...

Page 43: ...P N 11934 003 2 23 Cirrus Design Section 2 SR20 Limitations Figure 2 5 Placards Sheet 3 of 7 Revision A5 ...

Page 44: ... CERTIFIED FOR THE Instrument Panel Upper left INCLUDING APPROVED NO NORMAL CATEGORY AIRPLANE SPINS ACROBATIC MANEUVERS SPEED Vo 131 KIAS MANEUVERING OPERATE PER AIRPLANE FLIGHT MANUAL FLIGHT INTO KNOWN ICING IS PROHIBITED WITH REQUIRED EQUIPMENT FOLLOWING FLIGHT OPERATIONS THIS AIRCRAFT IS CERTIFIED FOR THE NO STEP RESCUE FRACTURE AND REMOVE WINDOW Wing flap aft edge Cabin Door Window lower edge ...

Page 45: ...R FRACTURING Cabin Window above door latch OR Above MFD on one line FIRE EXTINGUISHER UNDER PILOT SEAT FRONT FASTEN SEATBELTS NO SMOKING Instrument Panel Upper Right UNDER PILOT SEAT FRONT FIRE EXTINGUISHER FASTEN SEATBELTS NO SMOKING EMERGENCY EXIT REMOVE EGRESS HAMMER FROM WITHIN CENTER ARMREST LID STRIKE CORNER OF WINDOW KICK OR PUSH OUT AFTER FRACTURING Cabin Window above door latch Serials 11...

Page 46: ...ge Compartment Door inside Baggage Compartment aft edge AND WEIGHT AND BALANCE INFORMATION SEE AIRPLANE FLIGHT MANUAL FOR BAGGAGE TIE DOWN BAGGAGE STRAP CAPACITY IS 35 LBS EACH MAXIMUM DISTRIBUTED FLOOR LIMIT 130 LBS REMOVE CARPET AND ACCESS PANEL ELT LOCATED BEHIND BULKHEAD Placards Sheet 6 of 7 Revision A5 ...

Page 47: ...AT ALL TIMES USE OF THIS DEVICE COULD RESULT IN INJURY OR DEATH MAXIMUM DEMONSTRATED DEPLOYMENT SPEED 135 KIAS CIRRUS AIRFRAME PARACHUTE SYSTEM ACTIVATION PROCEDURE 1 FUEL MIXTURE CUT OFF 2 THIS COVER REMOVE 3 ACTIVATION HANDLE PULL STRAIGHT DOWN BOTH HANDS MAXIMUM FORCE STEADY PULL DO NOT JERK HANDLE 4 FUEL SELECTOR HANDLE OFF 5 MASTER SWITCH OFF 6 RESTRAINT SYSTEM SECURE Figure 2 5 Placards Shee...

Page 48: ...2 28 P N 11934 003 Section 2 Cirrus Design Limitations SR20 Revision A5 Intentionally Left Blank ...

Page 49: ... Flight Emergencies 3 9 Engine Failure On Takeoff Low Altitude 3 9 Maximum Glide 3 10 Engine Failure In Flight 3 11 Engine Airstart 3 12 Engine Partial Power Loss 3 13 Low Oil Pressure 3 15 Propeller Governor Failure 3 15 Smoke and Fume Elimination 3 16 Engine Fire In Flight 3 16 Wing Fire In Flight 3 16 Cabin Fire In Flight 3 17 Emergency Descent 3 18 Inadvertent Spiral Dive During IMC Flight 3 1...

Page 50: ...3 2 P N 11934 003 Section 3 Cirrus Design Emergency Procedures SR20 Exit IMC 3 25 PFD Loss of Attitude Data 3 25 Exit IMC 3 25 Power Lever Linkage Failure 3 26 Revision A5 ...

Page 51: ... or engine malfunctions are extremely rare the guidelines described in this section should be considered and applied as necessary should an emergency arise Note Emergency procedures associated with optional systems can be found in Section 9 Serials 1337 and subsequent with SRV standard configuration The airplane is equipped with a single alternator dual battery electrical system References to Alte...

Page 52: ...rocedures SR20 Airspeeds for Emergency Operations Maneuvering Speed 3000 lb 131 KIAS 2600 lb 122 KIAS 2200 lb 111 KIAS Best Glide 3000 lb 96 KIAS 2500 lb 87 KIAS Emergency Landing Engine out Flaps Up 86 KIAS Flaps 50 81 KIAS Flaps 100 75 KIAS Revision A5 ...

Page 53: ...damage occurred during the previous flight or while the airplane was on the ground Pay special attention to any oil leaks or fuel stains that could indicate engine problems Methodology Aircraft emergencies are very dynamic events Because of this it is impossible to address every action a pilot might take to handle a situation However four basic actions can be applied to any emergency They are Main...

Page 54: ...ilot judgment Land as soon as Conditions Permit Once you have handled the emergency assess your next move Handle any non critical clean up items in the checklist and put the aircraft on the ground Remember even if the airplane appears to be in sound condition it may not be Memory Items Checklist steps emphasized by underlining such as this 1 Best Glide Speed ESTABLISH should be memorized for accom...

Page 55: ... fire back into the engine by continuing to crank the engine 1 Mixture CUTOFF 2 Fuel Pump OFF 3 Fuel Selector OFF 4 Power Lever FORWARD 5 Starter CRANK 6 If flames persist perform Emergency Engine Shutdown on Ground and Emergency Ground Egress checklists Emergency Engine Shutdown On Ground 1 Power Lever IDLE 2 Fuel Pump if used OFF 3 Mixture CUTOFF 4 Fuel Selector OFF 5 Ignition Switch OFF 6 Bat A...

Page 56: ...f other aircraft spinning propellers and other hazards 1 Engine SHUTDOWN Note If the engine is left running set the Parking Brake prior to evacuating the airplane 2 Seat belts RELEASE 3 Airplane EXIT Note If the doors cannot be opened break out the windows with egress hammer located in the console between the front seats and crawl through the opening Revision A5 ...

Page 57: ... a glide attitude In most cases the landing should be made straight ahead turning only to avoid obstructions After establishing a glide for landing perform as many of the checklist items as time permits WARNING If a turn back to the runway is elected be very careful not to stall the airplane 1 Best Glide or Landing Speed as appropriate ESTABLISH 2 Mixture CUTOFF 3 Fuel Selector OFF 4 Ignition Swit...

Page 58: ...imum Glide Ratio 10 9 1 Conditions Example Power OFF Altitude 7 000 ft AGL Propeller Windmilling Airspeed Best Glide Flaps 0 UP Wind Zero Glide Distance 12 5 NM 14000 12000 10000 8000 6000 2000 4000 0 6 8 10 12 14 16 18 4 2 20 0 GROUND DISTANCE NAUTICAL MILES HEIGHT ABOVE GROUND FEET SR20_FM03_1046 Figure 3 1 Maximum Glide Revision A5 ...

Page 59: ...CUTOFF and do not attempt a restart 1 Best Glide Speed ESTABLISH Note With a seized or failed engine the distance that the airplane will glide will be more than the distance it would glide with the engine at idle such as during training If the propeller is windmilling some additional glide range may be achieved by moving the Power Lever to idle and increasing airspeed by 5 to 10 knots 2 Mixture FU...

Page 60: ...xture may correct faulty mixture control Note Engine airstarts may be performed during 1g flight anywhere within the normal operating envelope of the airplane 1 Bat Master Switches ON 2 Power Lever OPEN 3 Mixture RICH AS REQ D 4 Fuel Selector SWITCH TANKS 5 Ignition Switch BOTH 6 Fuel Pump BOOST 7 Alternate Induction Air ON 8 Alt Master Switches OFF 9 Starter Propeller not Windmilling ENGAGE 10 Po...

Page 61: ... is suspected immediately shut down engine and perform Forced Landing checklist If a partial engine failure permits level flight land at a suitable airfield as soon as conditions permit If conditions do not permit safe level flight use partial power as necessary to set up a forced landing pattern over a suitable landing field Always be prepared for a complete engine failure If the power loss is du...

Page 62: ...light conditions 4 Power Lever SWEEP Sweep the Power Lever through range as required to obtain smooth operation and required power 5 Alternate Induction Air ON A gradual loss of manifold pressure and eventual engine roughness may result from the formation of intake ice Opening the alternate engine air will provide air for engine operation if the normal source is blocked or the air filter is iced o...

Page 63: ...ysis of the low oil pressure indication to confirm oil pressure has actually been lost If low oil pressure is accompanied by normal oil temperature it is possible that the oil pressure sensor gage or relief valve is malfunctioning In any case land as soon as practical and determine cause 1 Power Lever MINIMUM REQUIRED 2 Land as soon as possible Propeller Governor Failure If the RPM does not respon...

Page 64: ...ater OFF 2 Air Vents OPEN FULL COLD 3 Prepare to land as soon as possible If airflow is not sufficient to clear smoke or fumes from cabin 4 Cabin Doors UNLATCH Engine Fire In Flight If an engine fire occurs during flight do not attempt to restart the engine 1 Mixture CUTOFF 2 Fuel Pump OFF 3 Power Lever IDLE 4 Fuel Selector OFF 5 Ignition Switch OFF 6 Perform Forced Landing checklist Wing Fire In ...

Page 65: ...switches OFF Power from battery 2 will keep the Primary Flight Display operational for approximately 30 minutes 1 Bat Alt Master Switches OFF AS REQ D Note With Bat Alt Master Switches OFF engine will continue to run However no electrical power will be available 2 Heater OFF 3 Air Vents CLOSED 4 Fire Extinguisher ACTIVATE WARNING Halon gas used in the fire extinguisher can be toxic especially in a...

Page 66: ...vate only the minimum amount of equipment necessary to complete a safe landing Emergency Descent 1 Power Lever IDLE 2 Mixture AS REQUIRED Caution If significant turbulence is expected do not descend at indicated airspeeds greater than VNO 165 KIAS 3 Airspeed VNE 200 KIAS Inadvertent Spiral Dive During IMC Flight 1 Power Lever IDLE 2 Stop the spiral dive by using coordinated aileron and rudder cont...

Page 67: ...er abusing the flight controls with accelerated inputs when close to the stall see Stalls Section 4 If at the stall the controls are misapplied and abused accelerated inputs are made to the elevator rudder and or ailerons an abrupt wing drop may be felt and a spiral or spin may be entered In some cases it may be difficult to determine if the aircraft has entered a spiral or the beginning of a spin...

Page 68: ...tivated when any other means of handling the emergency would not protect the occupants from serious injury Caution Expected impact in a fully stabilized deployment is equivalent to a drop from approximately 10 feet Note Several possible scenarios in which the activation of the CAPS would be appropriate are discussed in Section 10 Safety Information of this Handbook These include Mid air collision ...

Page 69: ...r Clasp both hands around the handle and pull straight down in a strong steady and continuous motion Maintain maximum pull force until the rocket activates Pull forces up to or exceeding 45 pounds may be required Bending of the handle housing mount is to be expected WARNING Jerking or rapidly pulling the activation T handle will greatly increase the pull forces required to activate the rocket Use ...

Page 70: ...ody position is assumed by placing both hands on the lap clasping one wrist with the opposite hand and holding the upper torso erect and against the seat backs 14 After the airplane comes to a complete stop evacuate quickly and move upwind As occupants exit the airplane the reduced weight may allow winds to drag the airplane further As a result of landing impact the doors may jam If the doors cann...

Page 71: ...le If engine power is available before attempting an off airport landing fly over the landing area at a low but safe altitude to inspect the terrain for obstructions and surface conditions Note Use of full 100 flaps will reduce glide distance Full flaps should not be selected until landing is assured If ditching avoid a landing flare because of difficulty in judging height over water 1 Best Glide ...

Page 72: ... lose the primary elevator control system Set elevator trim for a 80 KIAS approach to landing Thereafter do not change the trim setting until in the landing flare During the flare the nose down moment resulting from a power reduction may cause the airplane to hit on the nosewheel At touchdown bring the power lever to idle 1 Flaps SET 50 2 Trim SET 80 KIAS 3 Power AS REQUIRED FOR GLIDE ANGLE Revisi...

Page 73: ...of Air Data In the event the PFD detects a loss of air data the affected indicator is removed from the display and replaced with a red X If loss of air data occurs refer to the mechanical standby instruments altitude airspeed and perform the following procedure 1 Land as soon as practical 2 Standby Instruments altitude airspeed MONITOR If failure occurs while flying in IMC Exit IMC PFD Loss of Att...

Page 74: ...inkage fails in flight the engine will not respond to power lever control movements Use power available and flaps as required to safely land the airplane If the power lever is stuck at or near the full power position proceed to a suitable airfield Fly a forced landing pattern With landing assured shut down engine by moving mixture control full aft to CUTOFF If power is needed again return mixture ...

Page 75: ...A 5 In Flight Procedures 3A 6 Inadvertent Icing Encounter 3A 6 Inadvertent IMC Encounter 3A 6 Door Open In Flight 3A 6 Landing Procedures 3A 7 Landing With Failed Brakes 3A 7 Landing With Flat Tire 3A 7 System Malfunctions 3A 9 Alternator Failure 3A 9 Engine Indicating System Failure 3A 11 LOW VOLTS Warning Light Illuminated 3A 11 Communications Failure 3A 12 Pitot Static Malfunction 3A 13 Electri...

Page 76: ...3A 2 P N 11934 003 Section 3A Cirrus Design Abnormal Procedures SR20 Revision A5 Intentionally Left Blank ...

Page 77: ...cedures 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 Revision A5 ...

Page 78: ...ugh study of the information in this handbook while on the ground will help you prepare for time critical situations in the air Sound judgement as well as thorough knowledge of the aircraft its characteristics and the flight manual procedures are essential in the handling of any abnormal system and or flight condition In addition to the outlined items in the Abnormal Procedures the following steps...

Page 79: ...ering INCREASE 2 Directional Control MAINTAIN WITH RUDDER 3 Brake Pedal s PUMP If directional control can not be maintained 4 Mixture CUTOFF Aborted Takeoff 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 the runway 1 Power Lever IDLE 2 Brakes AS REQUIRED Caution For maximum brake effectiveness retract flaps hold...

Page 80: ...ntering IMC a pilot who is not completely proficient in instrument flying should rely upon the autopilot to execute a 180 turn to exit the conditions Immediate action should be made to turn back as follows 1 Airplane Control Establish Straight and Level Flight 2 Autopilot Engage to hold Heading and Altitude 3 Heading Reset to initiate 180 turn Door Open In Flight The doors on the SR20 will remain ...

Page 81: ...Note Rudder effectiveness will decrease with decreasing airspeed 4 Perform Emergency Engine Shutdown on Ground checklist Landing With Flat Tire If a flat tire or tread separation occurs during takeoff and you cannot abort land as soon as conditions permit Main Gear 1 Land on the side of the runway corresponding to the good tire 2 Maintain directional control with the brakes and rudder 3 Do not tax...

Page 82: ...HTS FLAPS ESSENTIAL COM 2 ENCODER XPONDER WEATHER STORMSCOPE AUDIO PANEL MFD AVIONICS FUEL QTY HOBBS INST LIGHTS PITCH TRIM ICE PROTECTION BATT SR20_FM03_1453D SKYWATCH TAWS ROLL TRIM ALT 1 ALT 2 AMMETER BAT 2 BAT 1 ALT 2 ALT 1 MAIN DISTRIBUTION BUS ESSENTIAL DISTRIBUTION BUS NON ESSENTIAL ESSENTIAL MAIN BUS 1 ALT 1 CABIN LIGHTS HSI PFD 2 ATTITUDE 2 TURN COORD 2 MAIN BUS 2 FUEL PUMP NON ESSENTIAL ...

Page 83: ...ght indicates an excessive charging rate This could occur with a very low BAT 1 and heavy equipment loads Since the loads on ALT 2 are much lower it is unlikely that a flashing ALT 2 light could occur even with a very low BAT 2 Figure 3 2 shows the electrical system power distribution Individual loads on each circuit breaker panel bus are shown in the same order as they are on the panel Note that ...

Page 84: ...he most likely cause is a severely discharged battery along with heavy equipment loads In this event reduce loads on Main and Non Essential buses and monitor amperage until charging rate is within normal limits Then loads can be added as required 1 Ammeter Switch BATT 2 If charging rate is greater than 30 amps reduce load on Main Bus 1 Main Bus 2 and Non Essential buses 3 Monitor ammeter until bat...

Page 85: ...uts will display as three white dashes the CHT and EGT bar graphs will be removed and indicator needles displayed on the simulated gages will be removed In the event of DAU failure pull and reset the ANNUN ENGINE INST circuit breaker If the engine indicating system fails to resest land as soon as practical 1 ANNUN ENGINE INST Circuit Breaker Cycle 2 Land as soon as practical LOW VOLTS Warning Ligh...

Page 86: ...on is not restored proceed with FAR AIM lost communications procedures Note In the event of an audio panel power failure the audio panel connects COM 1 to the pilot s headset and speakers Setting the audio panel Off will also connect COM 1 to the pilot s headsets and speakers 1 Switches Controls CHECK 2 Frequency CHANGE 3 Circuit Breakers CHECK 4 Headset CHANGE 5 Hand Held Microphone CONNECT Revis...

Page 87: ...ugh the vertical speed indicator the vertical speed UP DOWN indications will be reversed i e the needle will indicate UP for descent and DOWN for climb With the alternate static source on adjust indicated airspeed slightly during climb or approach according to the Airspeed Calibration Alternate Static Source table in Section 5 as appropriate for vent heater configuration 1 Pitot Heat ON 2 Alternat...

Page 88: ... yoke If runaway trim is the problem de energize the circuit by pulling the circuit breaker PITCH TRIM ROLL TRIM or AUTOPILOT and land as soon as conditions permit 1 Airplane Control MAINTAIN MANUALLY 2 Autopilot if engaged Disengage If Problem Is Not Corrected 3 Circuit Breakers PULL AS Required PITCH TRIM ROLL TRIM AUTOPILOT 4 Power Lever AS REQUIRED 5 Control Yoke MANUALLY HOLD PRESSURE Revisio...

Page 89: ...4 10 Starting Engine 4 11 Before Taxiing 4 13 Taxiing 4 13 Before Takeoff 4 14 Takeoff 4 16 Normal Takeoff 4 17 Short Field Takeoff 4 17 Climb 4 18 Cruise 4 19 Cruise Leaning 4 20 Descent 4 21 Before Landing 4 21 Landing 4 21 Balked Landing Go Around 4 22 After Landing 4 23 Shutdown 4 23 Stalls 4 24 Environmental Considerations 4 25 Cold Weather Operation 4 25 Hot Weather Operation 4 27 Noise Char...

Page 90: ...4 2 P N 11934 003 Section 4 Cirrus Design Normal Procedures SR20 Intentionally Left Blank Revision A5 ...

Page 91: ... for normal operation Normal procedures associated with optional systems can be found in Section 9 Note Serials 1337 and subsequent with SRV standard configuration The airplane is equipped with a single alternator dual battery electrical system References to Alternator 2 in the following section do not apply Revision A5 ...

Page 92: ...d Flaps 50 65 KIAS Obstacle Clearance Flaps 50 75 KIAS Enroute Climb Flaps Up Normal SL 105 KIAS Normal 10 000 95 KIAS Best Rate of Climb SL 96 KIAS Best Rate of Climb 10 000 91 KIAS Best Angle of Climb SL 81 KIAS Best Angle of Climb 10 000 85 KIAS Landing Approach Normal Approach Flaps Up 85 KIAS Normal Approach Flaps 50 80 KIAS Normal Approach Flaps 100 75 KIAS Short Field Flaps 100 75 KIAS Go A...

Page 93: ...age condition and evidence of delamination check all control surfaces for proper movement and excessive free play check area around liquid reservoirs and lines for evidence of leaking In cold weather remove all frost ice or snow from fuselage wing stabilizers and control surfaces Ensure that control surfaces are free of internal ice or debris Check that wheel fairings are free of snow and ice accu...

Page 94: ... Test Note Test stall warning system by applying suction to the stall warning system inlet and noting the warning horn sounds k Fuel Quantity Check l Fuel Selector Select Fullest Tank m Flaps 100 Check Light ON n Oil Annunciator On o Bat 1 and 2 Master Switches OFF p Alternate Static Source NORMAL q Circuit Breakers IN r Fire Extinguisher Charged and Available s Emergency Egress Hammer Available t...

Page 95: ...c Button Check for Blockage b Wing Fuselage Fairings Check 5 Right Wing Trailing Edge a Flap and Rub Strips if installed Condition and Security b Aileron and Tab Condition and Movement c Hinges actuation arm bolts and cotter pins Secure 6 Right Wing Tip a Tip Attachment b Strobe Nav Light and Lens Condition and Security c Fuel Vent underside Unobstructed 7 Right Wing Forward and Main Gear a Leadin...

Page 96: ...ide a Cowling Attachments Secure b Exhaust Pipe Condition Security and Clearance c Transponder Antenna underside Condition and Attachment d Gascolator underside Drain for 3 seconds Sample 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 Note Serials 1337 and subsequent with SRV sta...

Page 97: ...ton housing If indicator center is black the brake assembly has been overheated The brake linings must be inspected and O rings replaced c Wheel and Brakes Fluid Leaks Evidence of Overheating General Condition and Security d Chocks and Tiedown Ropes Remove e Fuel Drains 2 underside Drain and Sample f Cabin Air Vent Unobstructed g Fuel Cap Check Quantity and Secure h Leading Edge and Stall Strips C...

Page 98: ...ED Note Ensure all the passengers have been fully briefed on smoking the use of the seat belts doors emergency exits egress hammer and CAPS Verify CAPS handle safety pin is removed 4 Seats Seat Belts and Harnesses ADJUST SECURE Caution Crew seats must be locked in position and control handles fully down before flight Ensure seat belt harnesses are not twisted Revision A5 ...

Page 99: ...e engine is under primed especially with a cold soaked engine it will not fire and additional priming will be necessary As soon as the cylinders begin to fire open the power lever slightly to keep it running Refer to Cold Weather Operation in this section or additional information regarding cold weather operations WARNING If airplane will be started using external power keep all personnel and powe...

Page 100: ...prove starting 8 Propeller Area CLEAR 9 Power Lever OPEN INCH 10 Ignition Switch START Release after engine starts Caution Limit cranking to intervals of 20 seconds with a 20 second cooling period between cranks This will improve battery and contactor life 11 Power Lever RETARD to maintain 1000 RPM 12 Oil Pressure CHECK 13 Alt Master Switches ON 14 Avionics Power Switch ON 15 Engine Parameters MON...

Page 101: ... will result in increased brake temperature Taxi over loose gravel at low engine speed to avoid damage to the propeller tips WARNING Maximum continuous engine speed for taxiing is 1000 RPM on flat smooth hard surfaces Power settings slightly above 1000 RPM are permissible to start motion for turf soft surfaces and on inclines Use minimum power to maintain taxi speed If the 1000 RPM taxi power limi...

Page 102: ...PS Handle Verify Pin Removed 3 Seat Belts and Shoulder Harness SECURE 4 Fuel Quantity CONFIRM 5 Fuel Selector FULLEST TANK 6 Fuel Pump ON 7 Flaps SET 50 CHECK 8 Transponder SET 9 Autopilot CHECK 10 Navigation Radios GPS SET for Takeoff 11 Cabin Heat Defrost AS REQUIRED 12 Brakes HOLD 13 Power Lever 1700 RPM 14 Alternator CHECK a Pitot Heat ON b Navigation Lights ON c Landing Light ON d Annunciator...

Page 103: ...OTH Note RPM drop must not exceed 150 RPM for either magneto RPM differential must not exceed 75 RPM between magnetos If there is a doubt concerning operation of the ignition system RPM checks at higher engine speeds will usually confirm whether a deficiency exists An absence of RPM drop may indicate faulty grounding of one side of the ignition system or magneto timing set in advance of the specif...

Page 104: ...s 50 Normal and short field takeoffs are accomplished with flaps set at 50 Takeoffs using 50 flaps require less ground roll and distance over an obstacle than do takeoffs with no flaps Takeoff flap settings greater than 50 are not approved Soft or rough field takeoffs are performed with 50 flaps by lifting the airplane off the ground as soon as practical in a tail low attitude If no obstacles are ...

Page 105: ... Brakes RELEASE Steer with Rudder Only 4 Elevator Control ROTATE Smoothly at 65 70 KIAS 5 At 85 KIAS Flaps UP Short Field Takeoff 1 Flaps 50 2 Brakes HOLD 3 Power Lever FULL FORWARD 4 Engine Instruments CHECK 5 Brakes RELEASE Steer with Rudder Only 6 Elevator Control ROTATE Smoothly at 65 KIAS 7 Airspeed at Obstacle 75 KIAS Revision A5 ...

Page 106: ...ates the use of a steep climb angle the best angle of climb speed should be used Climbs at speeds lower than the best rate of climb speed should be of short duration to avoid engine cooling problems Note The engine is equipped with an altitude compensating fuel pump that automatically provides the proper full rich mixture for climb The mixture for climb should be left full rich 1 Climb Power SET 2...

Page 107: ...ruise at a minimum of 75 power until the engine has been operated for at least 25 hours or until oil consumption has stabilized Operation at this higher power will ensure proper seating of the rings is applicable to new engines and engines in service following cylinder replacement or top overhaul of one or more cylinders 1 Fuel Pump OFF Note The Fuel Pump may be used for vapor suppression during c...

Page 108: ...the fuel system serviced Note Serials 1337 thru 1581 with SRV standard configuration The airplane is not equipped with an EGT CHT gage To lean the engine for cruise pull the mixture lever towards CUTOFF until engine runs rough and then push the mixture lever towards FULL RICH until engine operation smooths out Exhaust gas temperature EGT may be used as an aid for mixture leaning in cruise flight F...

Page 109: ...oy or to extend the aircraft s glide distance due to engine malfunction Landings with flaps at 50 or 0 power should be used to achieve a normal glidepath and low descent rate Flare should be minimized Normal Landing Normal landings are made with full flaps with power on or off Surface winds and air turbulence are usually the primary factors in determining the most comfortable approach speeds Actua...

Page 110: ...k and apply maximum brake pressure without skidding Crosswind Landing Normal crosswind landings are made with full flaps Avoid prolonged slips After touchdown hold a straight course with rudder and brakes as required The maximum allowable crosswind velocity is dependent upon pilot capability as well as aircraft limitations Operation in direct crosswinds of 21 knots has been demonstrated Balked Lan...

Page 111: ...mp if used OFF 2 Throttle IDLE 3 Ignition Switch CYCLE Caution Note that the engine hesitates as the switch cycles through the OFF position If the engine does not hesitate one or both magnetos are not grounded Prominently mark the propeller as being Hot and contact maintenance personnel immediately 4 Mixture CUTOFF 5 All Switches OFF 6 Magnetos OFF 7 ELT TRANSMIT LIGHT OUT Note After a hard landin...

Page 112: ...duced you will notice a slight airframe buffet and hear the stall speed warning horn sound between 5 and 10 knots before the stall Normally the stall is marked by a gentle nose drop and the wings can easily be held level or in the bank with coordinated use of the ailerons and rudder Upon stall warning in flight recovery is accomplished by immediately by reducing back pressure to maintain safe airs...

Page 113: ...hes in strength the spark plugs have probably frosted over Preheat must be used before another start is attempted WARNING If airplane will be started using external power keep all personnel and power unit cables well clear of the propeller rotation plane Caution Inadequate application of preheat to a cold soaked engine may warm the engine enough to permit starting but will not de congeal oil in th...

Page 114: ...uld cause the engine to fire 2 Propeller Hand TURN several rotations 3 External Power If applicable CONNECT 4 Brakes HOLD 5 Bat Master Switches ON check voltage 6 Mixture FULL RICH 7 Power lever FULL FORWARD 8 Fuel Pump PRIME then BOOST Note In temperatures down to 20 F hold Fuel Boost Pump switch to PRIME for 10 seconds prior to staring 9 Propeller Area CLEAR 10 Power Lever OPEN INCH 11 Ignition ...

Page 115: ...ameters MONITOR 17 External Power If applicable DISCONNECT 18 Amp Meter Indication CHECK 19 Strobe Lights ON Hot Weather Operation Avoid prolonged engine operation on the ground Note Fuel BOOST should be left ON during takeoff and for climb as required for vapor suppression with hot or warm fuel Revision A5 ...

Page 116: ...minimize the effect of airplane noise on the general public The following suggested procedures minimize environmental noise when operating the SR20 Note Do not follow these noise abatement procedures where they conflict with Air Traffic Control clearances or instructions weather considerations or wherever they would reduce safety 1 When operating VFR over noise sensitive areas such as outdoor even...

Page 117: ...P N 11934 003 4 29 Cirrus Design Section 4 SR20 Normal Procedures Fuel Conservation Minimum fuel use at cruise will be achieved using the best economy power setting described under cruise Revision A5 ...

Page 118: ...4 30 P N 11934 003 Section 4 Cirrus Design Normal Procedures SR20 Revision A5 Intentionally Left Blank ...

Page 119: ...ibration 5 11 Alternate Static Source 5 11 Altitude Correction 5 12 Normal Static Source 5 12 Altitude Correction 5 13 Alternate Static Source 5 13 Temperature Conversion 5 14 Outside Air Temperature for ISA Condition 5 15 Stall Speeds 5 16 Wind Components 5 17 Takeoff Distance 5 18 Takeoff Distance 5 19 Takeoff Distance 5 20 Takeoff Climb Gradient 5 21 Takeoff Rate of Climb 5 22 Enroute Climb Gra...

Page 120: ...ion 5 Cirrus Design Performance Data SR20 Range Endurance Profile 5 29 Range Endurance Profile 5 30 Balked Landing Climb Gradient 5 31 Balked Landing Rate of Climb 5 32 Landing Distance 5 33 Landing Distance 5 34 Revision A5 ...

Page 121: ... ambient conditions are for a standard day refer to Section 1 Flap position as well as power setting technique is similarly noted with each table The charts in this section provide data for ambient temperatures from 20 C 4 F to 40 C 104 F If ambient temperature is below the chart value use the lowest temperature shown to compute performance This will result in more conservative performance calcula...

Page 122: ... an extra margin of safety and to account for events that could occur during a flight Sample Problem The following sample flight problem uses information derived from the airplane performance charts and tables to determine the predicted performance for a typical flight The first step in flight planning is to determine the aircraft weight and center of gravity as well as information about the fligh...

Page 123: ...he conservative values results in the following Ground roll 1940 Feet Total distance to clear a 50 foot obstacle 2734 Feet Since the takeoff distance tables are based upon a zero wind conditions a correction for the effect of winds must be made Use the wind components chart Figure 5 8 to determine the crosswind and the headwind or tailwind component of the reported winds Using the 11 knot headwind...

Page 124: ...start of climb or next higher altitude values for end of climb Using conservative values for the sample data the following calculations are made Start of climb values SL to 1750 feet Time to climb 1 3 minutes Distance to climb 2 0 NM Fuel to climb 0 3 Gal End of climb values SL to 6500 feet Time to climb 10 3 minutes Distance to climb 17 0 NM Fuel to climb 2 4 Gal Climb values 1750 to 6500 feet Ti...

Page 125: ...re given for this sample problem Power selection for cruise should be based upon the cruise performance characteristics tabulated in Figure 5 15 and the range endurance profile presented in Figure 5 16 The relationship between power and range as well as endurance is shown in the range endurance profile chart Figure 5 16 Note that fuel economy and range are substantially improved at lower power set...

Page 126: ...ground speed for cruise is expected to be 121 knots Therefore the time required for the cruise portion of the trip is 543 0 NM 121 knots 4 5 hours The fuel required for cruise is 4 5 hours x 9 2 GPH 41 4 gallons From the 6000 ft Cruise Table Figure 5 15 a 45 minute IFR reserve at approximately 70 power requires 45 60 x 11 1 GPH 8 3 gallons The total estimated fuel required is as follows Engine sta...

Page 127: ... 1110 Feet Total distance to land over a 50 foot obstacle 2166 Feet A correction for the effect of wind may be made based on the headwind and tailwind corrections presented with the landing chart using the same procedure as outlined for takeoff Demonstrated Operating Temperature Satisfactory engine cooling has been demonstrated for this airplane with an outside air temperature 23 C above standard ...

Page 128: ...rspeed KCAS Knots Calibrated Airspeed Conditions Example Power for level flight or maximum continuous whichever is less Flaps 50 Indicated Airspeed 85 Knots Weight 3000 LB Calibrated Airspeed 86 Knots KIAS KCAS Flaps 0 Flaps 50 Flaps 100 50 49 60 60 60 70 72 71 71 80 81 81 81 90 91 91 91 100 101 101 101 110 111 111 120 120 120 130 130 140 140 150 150 160 160 170 170 180 180 190 190 200 200 Reissue...

Page 129: ...ibrated Airspeed Conditions Example Power for level flight or maximum continuous whichever is less Flaps 50 Indicated Airspeed 85 Knots Weight 3000 LB Heater Defroster Vents ON Calibrated Airspeed 84 Knots KIAS KCAS Flaps 0 Flaps 50 Flaps 100 50 45 60 59 56 70 70 69 67 80 80 79 78 90 90 89 88 100 100 99 98 110 110 109 120 120 118 130 130 140 140 150 150 160 161 170 171 180 182 190 192 200 203 Figu...

Page 130: ...nuous whichever is less Flaps 50 Indicated Airspeed 85 Knots Weight 3000 LB Desired Altitude 12 000 FT Altitude Correction 7 FT Altitude to Fly 11 993 FT Flaps Press Alt CORRECTION TO BE ADDED FEET Normal Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 12 11 10 9 8 5 3 3 5 10 5000 14 13 12 11 9 6 4 3 5 11 10000 16 15 14 12 11 7 4 4 6 13 15000 19 18 16 14 12 8 5 4 7 16 50 S L 2 4 5 6 5...

Page 131: ...peed 120 Knots Weight 3000 LB Desired Altitude 12 000 FT Heater Defroster Vents ON Altitude Correction 11 FT Altitude to Fly 11 989 FT Flaps Press Alt CORRECTION TO BE ADDED FEET Normal Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 9 10 10 11 10 7 1 11 27 51 5000 10 11 12 12 12 9 1 12 32 59 10000 12 13 14 14 14 10 1 14 37 69 15000 14 15 16 17 16 12 1 17 44 80 50 S L 11 15 18 21 22 1...

Page 132: ...7 2 36 17 62 144 49 56 69 16 4 39 18 64 147 48 54 65 14 6 43 19 66 151 47 52 62 13 8 46 20 68 154 46 50 58 12 10 50 21 70 158 44 48 54 11 12 54 22 72 162 43 46 51 10 14 57 23 74 165 42 44 47 9 16 61 24 76 169 41 42 44 8 18 64 26 78 172 40 40 40 7 20 68 27 80 176 39 38 36 6 22 72 28 82 180 38 36 33 4 24 75 29 84 183 37 34 29 3 26 79 30 86 187 36 32 26 2 28 82 31 88 190 34 30 22 1 30 86 32 90 194 33...

Page 133: ...95 1000 27 18 7 18 13 54 23 72 33 90 2000 29 20 9 16 11 52 21 70 31 88 3000 31 24 11 12 9 48 19 66 29 84 4000 33 27 13 9 7 45 17 63 27 81 5000 35 31 15 5 5 41 15 59 25 77 6000 37 34 17 2 3 38 13 56 23 74 7000 39 38 19 2 1 34 11 52 21 70 8000 41 42 21 6 1 30 10 48 20 66 9000 43 45 23 9 3 27 7 45 17 63 10000 45 49 25 13 5 23 5 41 15 59 11000 47 52 27 16 7 20 3 38 13 56 12000 49 56 29 20 9 16 1 34 11...

Page 134: ... G Noted Bank Angle 15 Power Idle Bank Angle Noted Stall Speed 66 KIAS 68 KCAS Weight LB Bank Angle Deg STALL SPEEDS Flaps 0 Full Up Flaps 50 Flaps 100 Full Down KIAS KCAS KIAS KCAS KIAS KCAS 3000 Most FWD C G 0 65 67 61 63 56 59 15 66 68 62 64 57 60 30 70 72 65 68 61 63 45 78 80 72 75 67 70 60 92 95 86 89 80 83 3000 Most AFT C G 0 64 66 59 62 54 57 15 65 67 60 63 55 58 30 69 71 64 66 58 61 45 76 ...

Page 135: ... 50 Wind Direction 60 Crosswind Component 12 Knots Wind Velocity 15 Knots Headwind Component 10 Knots 10 Headwind Tailwind 0 A N G L E B E T W E E N W I N D D I R E C T I O N A N D F L I G H T P A T H 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 V E L O C I T Y K N O T S W IND 40 40 30 20 10 WIND COMPONENTS KNOTS CROSSWIND COMPONENT KNOTS 20 10 0 10 20 40 30 SR20_FM05_1014 10 20 30 ...

Page 136: ...lope are required to be included herein These corrections should be used with caution since published runway slope data is usually the net slope from one end of the runway to the other Many runways will have portions of their length at greater or lesser slopes than the published slope lengthening or shortening takeoff ground roll estimated from the table If brakes are not held while applying power...

Page 137: ... 1526 1643 1766 1893 1564 50 ft 2022 2175 2333 2497 2666 2226 2000 Grnd Roll 1552 1676 1805 1940 2079 1692 50 ft 2214 2381 2555 2734 2920 2402 3000 Grnd Roll 1706 1842 1985 2132 2286 1831 50 ft 2426 2609 2799 2996 3200 2593 4000 Grnd Roll 1877 2027 2183 2346 1983 50 ft 2660 2861 3069 3285 2802 5000 Grnd Roll 2066 2231 2404 2583 2149 50 ft 2919 3139 3368 3605 3029 6000 Grnd Roll 2276 2458 2648 2845...

Page 138: ...d Roll 892 964 1038 1116 1196 986 50 ft 1326 1426 1529 1636 1747 1457 2000 Grnd Roll 980 1059 1141 1226 1314 1067 50 ft 1451 1561 1674 1791 1912 1572 3000 Grnd Roll 1078 1164 1254 1348 1445 1156 50 ft 1590 1709 1834 1962 2095 1697 4000 Grnd Roll 1185 1281 1380 1483 1253 50 ft 1743 1874 2010 2151 1835 5000 Grnd Roll 1305 1410 1519 1632 1358 50 ft 1912 2056 2205 2360 1985 6000 Grnd Roll 1438 1553 16...

Page 139: ... table provides use extreme caution Conditions Example Power Full Throttle Outside Air Temp 20 C Mixture Full Rich Weight 3000 LB Flaps 50 Pressure Altitude 1750 FT Airspeed Best Rate of Climb Climb Airspeed 85 Knots Gradient 491 FT NM Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile Temperature C 20 0 20 40 ISA 3000 SL 85 678 621 568 518 581 2000 85 587 532 481 433 50...

Page 140: ... table provides use extreme caution Conditions Example Power Full Throttle Outside Air Temp 20 C Mixture Full Rich Weight 3000 LB Flaps 50 Pressure Altitude 1750 FT Airspeed Best Rate of Climb Climb Airspeed 85 Knots Rate of Climb 725 FPM Weight LB Press Alt FT Climb Speed KIAS RATE OF CLIMB Feet per Minute Temperature C 20 0 20 40 ISA 3000 SL 85 905 862 817 771 828 2000 85 807 761 712 663 734 400...

Page 141: ...s weight does not exceed 2900 lb and the ambient temperature is 20 C or less Conditions Example Power Full Throttle Outside Air Temp 20 C Mixture Full Rich Weight 3000 LB Flaps 0 UP Pressure Altitude 4200 FT Airspeed Best Rate of Climb Climb Airspeed 94 Knots Gradient 359 FT NM Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile Temperature C 20 0 20 40 ISA 3000 SL 96 650...

Page 142: ... weight does not exceed 2900 lb and the ambient temperature is 20 C or less Conditions Example Power Full Throttle Outside Air Temp 10 C Mixture Full Rich Weight 3000 LB Flaps 0 UP Pressure Altitude 6500 FT Airspeed Best Rate of Climb Climb Airspeed 93 Knots Rate of Climb 513 FPM Weight LB Press Alt FT Climb Speed KIAS RATE OF CLIMB Feet per Minute Temperature C 20 0 20 40 ISA 3000 SL 96 979 923 8...

Page 143: ...Vs Density Altitude Conditions Power Full Throttle Mixture Full Rich Flaps 0 UP Airspeed Best Rate of Climb 1 000 2 000 3 000 4 000 5 000 6 000 7 000 8 000 9 000 10 000 11 000 12 000 13 000 14 000 15 000 1 0 0 2 0 0 3 0 0 4 0 0 5 0 0 6 0 0 7 0 0 8 0 0 9 0 0 1 0 0 0 1 1 0 0 1 2 0 0 2 5 0 0 L B 3 0 0 0 L B Rate of Climb Feet Per Minute ...

Page 144: ...L Airport Press 1000 FT Weight 3000 LB Pressure Altitude 12000 FT Winds Zero Climb Airspeed Noted Time to Climb 22 5 Minutes Fuel to Climb 4 7 Gallon Distance to Climb 39 NM Press Alt FT OAT ISA C Climb Speed KIAS Rate Of Climb FPM TIME FUEL DISTANCE From Sea Level Time Minutes Fuel U S Gal Distance NM SL 15 96 880 0 0 0 0 0 1000 13 96 828 1 3 0 3 2 2000 11 95 775 2 4 0 6 4 3000 9 94 723 3 8 1 0 6...

Page 145: ... 10 2 2500 22 0 65 136 10 5 62 136 10 2 59 133 9 9 2500 19 7 55 127 9 5 52 127 9 20 50 124 8 9 4000 Feet Pressure Altitude ISA 30 C 23 C ISA 7 C ISA 30 C 37 C RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH 2700 25 8 94 159 14 8 89 159 14 4 84 157 13 4 2500 25 8 84 153 13 3 79 153 12 7 75 150 11 7 2500 24 8 80 150 12 7 75 150 11 6 72 147 11 2 2500 23 6 75 146 11 5 70 146 11 1 67 143 10 8 2500 22 3 ...

Page 146: ... GPH 2700 20 6 76 155 11 7 72 155 11 2 68 152 10 9 2500 20 6 68 148 10 8 64 148 10 5 61 145 10 1 2500 19 6 64 144 10 4 60 144 10 0 57 141 9 7 2500 18 5 59 139 9 8 55 139 9 5 53 136 9 2 2500 17 3 54 134 9 3 50 134 9 0 48 131 8 7 12 000 Feet Pressure Altitude ISA 30 C 39 C ISA 9 C ISA 30 C 21 C RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH 2700 19 0 70 153 11 1 66 153 10 7 63 150 10 3 2500 19 0 63 ...

Page 147: ...d Day Takeoff Press Alt 2000 FT Winds Zero Cruise Press Alt 6000 FT Mixture See Tables Total Fuel 56 Gallons Fuel to Climb 1 4 Gal Cruise Fuel Flow 10 5 GPH Endurance 4 4 Hr Range 635 NM True Airspeed 143 Knots 75 POWER Mixture Best Power Press Alt FT Climb Fuel Gal Fuel Remaining For Cruise Gal Airspee d KTAS Fuel Flow GPH Endurance Hours Range NM Specific Range Nm Gal 0 0 0 46 3 143 11 6 4 0 576...

Page 148: ... 13 2 8000 2 9 43 4 145 10 5 4 4 645 13 3 10000 3 8 42 5 147 10 5 4 4 654 13 3 12000 5 0 41 3 150 10 5 4 4 666 13 4 14000 6 8 39 5 55 POWER Mixture Best Economy Press Alt FT Climb Fuel Gal Fuel Remaining For Cruise Gal Airspee d KTAS Fuel Flow GPH Endurance Hours Range NM Specific Range Nm Gal 0 0 0 46 3 127 8 4 5 5 708 15 2 2000 0 6 45 7 130 8 4 5 5 726 15 5 4000 1 3 45 0 131 8 4 5 5 731 15 4 600...

Page 149: ...eved by climbing at Best Rate of Climb speeds shown with flaps down or following the Go Around Balked Landing procedure in Section 4 Conditions Example Power Full Throttle Outside Air Temp 20 C Mixture Full Rich Weight 2500 LB Flaps 100 DN Pressure Altitude 2000 FT Airspeed Best Rate of Climb Climb Airspeed 74 Knots Rate of Climb 679 FT NM Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Fee...

Page 150: ...nce can be achieved by climbing at Best Rate of Climb speeds shown with flaps down or following the Go Around Balked Landing procedure in Section 4 Conditions Example Power Full Throttle Outside Air Temp 20 C Mixture Full Rich Weight 2500 LB Flaps 100 DN Pressure Altitude 4000 FT Climb Airspeed Noted Climb Airspeed 73 Knots Rate of Climb 733 FT NM Weight LB Press Alt FT Climb Speed KIAS RATE OF CL...

Page 151: ...herein These corrections should be used with caution since published runway slope data is usually the net slope from one end of the runway to the other Many runways will have portions of their length at greater or lesser slopes than the published slope lengthening or shortening landing ground roll estimated from the table Dry Grass Runway Add 40 to computed ground roll distance For operation in ou...

Page 152: ...oll 997 1034 1070 1067 1143 1045 50 ft 2018 2065 2113 2161 2210 2079 2000 Grnd Roll 1034 1072 1110 1148 1186 1076 50 ft 2066 2116 2166 2217 2268 2121 3000 Grnd Roll 1073 1112 1151 1191 1230 1108 50 ft 2117 2169 2222 2275 2329 2164 4000 Grnd Roll 1113 1154 1195 1236 1142 50 ft 2170 2225 2281 2337 2209 5000 Grnd Roll 1156 1198 1240 1283 1177 50 ft 2227 2285 2343 2402 2256 6000 Grnd Roll 1200 1244 12...

Page 153: ... Balance Table of Contents Introduction 6 3 Airplane Weighing Form 6 6 Airplane Weighing Procedures 6 7 Weight Balance Record 6 10 Loading Instructions 6 12 Center of Gravity Limits 6 14 Weight Balance Loading Form 6 15 Loading Data 6 16 Moment Limits 6 17 Equipment List 6 18 Revision A3 ...

Page 154: ...6 2 P N 11934 003 Section 6 Cirrus Design Weight and Balance SR20 Intentionally Left Blank Revision A3 ...

Page 155: ...for various operations are also provided A comprehensive list of all equipment available for this airplane is included at the back of this section It should be noted that specific information regarding the weight arm moment and installed equipment for this airplane as delivered from the factory can only be found in the plastic envelope carried in the back of this handbook It is the responsibility ...

Page 156: ...station 0 0 FS 38 3 WATER LINE WL 150 WL100 50 50 0 0 100 150 200 250 300 350 220 FS 157 5 FS 350 2 WL 165 5 FS FUSELAGE STATION FS 132 9 LEMAC RBL 210 9 RBL 77 3 BL 0 0 LBL 77 3 LBL 66 3 RBL 66 3 MAC 48 4 RBL 87 7 Typical LBL LBL 210 9 SR20_FM06_1031A 200 150 100 50 BL 0 0 50 100 150 200 BUTTOCK LINE BL Airplane Dimensional Data Reissue A ...

Page 157: ...tion 6 SR20 Weight Balance SR20_FM06_1021A Spirit Level LONGITUDINAL LEVELING LATERAL LEVELING Spirit Level Straight Edge Door Sill Door Sill Spacer Block Straight Edge Straight Edge Spacer Block Figure 6 2 Airplane Leveling Revision A2 ...

Page 158: ...ed CG CG Total Moment Total Weight Space below provided for additions or subtractions to as weighed condition Empty Weight CG Engine Oil if oil drained 15 lb at FS 78 4 moment 1176 Unusable Fuel 26 4 153 95 4064 Basic Empty Weight CG SR20_FM06_1441 x WL 100 0 y A B FS 100 0 FS 145 0 A x 100 B A y y ____________ Measured x ____________ Measured REF DATUM FS 0 0 Airplane Weighing Form Reissue A ...

Page 159: ...es b Service brake reservoir c Drain fuel system d Service engine oil e Move crew seats to the most forward position f Raise flaps to the fully retracted position g Place all control surfaces in neutral position h Verify equipment installation and location by comparison to equipment list 2 Leveling Figure 6 2 a Level longitudinally with a spirit level placed on the pilot door sill and laterally wi...

Page 160: ... nosewheel weighing point arm dimension B 5 Determine and record the moment for each of the main and nose gear weighing points using the following formula Moment Net Weight x Arm 6 Calculate and record the as weighed weight and moment by totaling the appropriate columns 7 Determine and record the as weighed C G in inches aft of datum using the following formula C G Total Moment Total Weight 8 Add ...

Page 161: ... the airplane Basic Empty Weight moment and center of gravity in inches aft of datum C G can also be expressed in terms of its location as a percentage of the airplane Mean Aerodynamic Cord MAC using the following formula C G MAC 100 x C G Inches LEMAC MAC Where LEMAC 132 9 MAC 48 4 Reissue A ...

Page 162: ...us history of changes and modifications to airplane structure or equipment affecting weight and balance Serial Num Reg Num Page of Date Item No Description of Article or Modification Weight Change Added or Removed Running Basic Empty Weight In Out WT LB ARM IN MOM 1000 WT LB MOM 1000 As Delivered Weight and Balance Record Reissue A ...

Page 163: ...in 122 49 3 49 7 137 cu ft Baggage Compartment 36 39 8 38 5 32 cu ft SR20 FM06 1019 32 0 33 3 20 0 39 0 33 4 10 5 FS 38 5 25 0 49 7 16 0 120 140 160 180 200 220 240 49 3 39 8 100 Fuselage Station 5 0 21 0 20 0 BAGGAGE DOOR OPENING CABIN DOOR OPENING 222 Figure 6 5 Airplane Interior Dimensions Reissue A ...

Page 164: ...e Loading Data Figure 6 8 3 Rear Seat Occupants Enter the total weight and moment 1000 for the rear seat occupants from the Loading Data Figure 6 8 4 Baggage Enter weight and moment for the baggage from the Loading Data Figure 6 8 If desired subtotal the weights and moment 1000 from steps 1 through 4 This is the Zero Fuel Condition It includes all useful load items excluding fuel 5 Fuel Loading En...

Page 165: ...Design Section 6 SR20 Weight Balance The total moment 1000 must not be above the maximum or below the minimum moment 1000 for the Takeoff Condition Weight as determined from the Moment Limits chart or table Figure 6 9 Reissue A ...

Page 166: ...inches aft of the reference datum and as a percentage of the Mean Aerodynamic Cord MAC The relationship between the two is detailed in the weighing instructions SR20_FM06_1941 138 140 142 144 146 148 150 2000 2200 2400 2600 2800 3000 C G Inches Aft of Datum Weight Pounds 10 15 20 25 30 35 2000 2200 2400 2600 2800 3000 C G MAC Weight Pounds Center of Gravity Limits Reissue A ...

Page 167: ...ment range at the Takeoff Condition Weight Refer to Figure 6 9 Moment Limits Item Description Weight LB Moment 1000 1 Basic Empty Weight Includes unusable fuel full oil 2 Front Seat Occupants Pilot Passenger total 3 Rear Seat Occupants 4 Baggage Area 130 lb maximum 5 Zero Fuel Condition Weight Sub total item 1 thru 4 6 Fuel Loading 56 Gallon 6 0 lb gal Maximum 7 Ramp Condition Weight Sub total ite...

Page 168: ...220 31 57 39 60 33 83 40 5 74 7 20 8 32 6 15 240 34 44 43 20 36 90 60 8 61 10 80 12 48 9 23 260 37 31 46 80 39 98 80 11 48 14 40 16 64 12 30 280 40 18 50 40 43 05 100 14 35 18 00 20 80 15 38 300 43 05 54 00 46 13 120 17 22 21 60 24 96 18 45 320 45 92 57 60 49 20 140 20 09 25 20 27 04 21 53 340 48 79 61 20 52 28 160 22 96 28 80 24 60 360 51 66 64 80 55 35 180 25 83 32 40 27 68 380 54 53 68 40 200 2...

Page 169: ...1000 Weight LB Moment 1000 Minimum Maximum Minimum Maximum 2110 293 305 2600 366 383 2150 299 311 2650 374 391 2200 306 320 2700 381 399 2250 314 328 2750 390 406 2300 321 336 2800 398 414 2350 329 344 2850 407 422 2400 336 352 2900 415 429 2450 344 360 2950 424 437 2500 351 368 3000 432 444 2550 359 376 SR20_FM06_1943 280 300 320 3000 Moment 1000 Weight Pounds 440 420 2800 2600 2400 2200 2000 400...

Page 170: ...6 18 P N 11934 003 Section 6 Cirrus Design Weight Balance SR20 Equipment List This list will be determined after the final equipment has been installed in the aircraft Reissue A ...

Page 171: ...ntrol System 7 14 Yaw Trim System 7 15 Flight Deck Arrangement 7 16 Instrument Panel 7 16 Center Console 7 17 Flight Instruments 7 21 Primary Flight Display Serials 1337 and Subsequent 7 21 Attitude Indicator 7 26 Airspeed Indicator 7 27 Vertical Speed Indicator 7 27 Altimeter 7 28 Turn Coordinator 7 28 Directional Gyro 7 29 Course Deviation Indicator 7 30 Horizontal Situation Indicator 7 31 Magne...

Page 172: ...6 Propeller 7 55 Fuel System 7 56 Fuel Selector Valve 7 58 Fuel Quantity Indicator 7 59 Fuel Flow Indication 7 62 Fuel Caution Light 7 62 Boost Pump Switch 7 63 Brake System 7 64 Electrical System 7 67 Power Generation 7 67 Power Distribution 7 68 BAT ALT Master Switches 7 70 Avionics Power Switch 7 71 Volts and Ampere Meter Indication 7 71 Ammeter Select Switch 7 72 Low Volts Warning Light 7 72 A...

Page 173: ...tatic Source 7 81 Stall Warning System 7 82 Standard Avionics 7 83 Multi Function Display 7 85 Autopilot 7 86 GPS Navigation 7 89 Communication COM Transceivers 7 91 Navigation Nav Receiver 7 92 Transponder 7 94 Audio System 7 94 Emergency Locator Transmitter 7 95 Hour Meter 7 96 Digital Clock 7 97 Cirrus Airplane Parachute System 7 99 System Description 7 99 Activation Handle 7 100 Deployment Cha...

Page 174: ...7 4 P N 11934 003 Section 7 Cirrus Design Airplane Description SR20 Revision A5 Intentionally Left Blank ...

Page 175: ...ration of the standard airplane and its systems Optional equipment described within this section is identified as optional Note Some optional equipment primarily avionics may not be described in this section For description and operation of optional equipment not described in this section refer to Section 9 Supplements Revision A5 ...

Page 176: ...nt The lower firewall employes a 20 bevel to improve crashworthiness In addition an avionics bay is located aft of bulkhead 222 and accessible through an access panel installed on the RH side of the aft fuselage Note Refer to Airplane Cabin description in this section for a complete description of doors windows baggage compartment seats and safety equipment Wings The wing structure is constructed ...

Page 177: ...l stabilizer a two piece elevator a vertical fin and a rudder All of the empennage components are conventional spar shear web rib and skin construction The horizontal stabilizer is a single composite structure from tip to tip The two piece elevator attached to the horizontal stabilizer is aluminum The vertical stabilizer is composite structure integral to the main fuselage shell for smooth transfe...

Page 178: ...rol yoke Elevator System The two piece elevator provides airplane pitch control The elevator is of conventional design with skin spar and ribs manufactured of aluminum Each elevator half is attached to the horizontal stabilizer at two hinge points and to the fuselage tailcone at the elevator control sector Elevator motion is generated through the pilot s control yokes by sliding the yoke tubes for...

Page 179: ...P N 11934 003 7 9 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1461 Figure 7 1 Elevator Control System Revision A5 ...

Page 180: ...at two hinge points Aileron control motion is generated through the pilot s control yokes by rotating the yokes in pivoting bearing carriages Push rods link the pivoting carriages to a centrally located pulley sector A single cable system runs from the sector to beneath the cabin floor and aft of the rear spar From there the cables are routed in each wing to a vertical sector crank arm that rotate...

Page 181: ...P N 11934 003 7 11 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1462 Figure 7 2 Aileron Control System Revision A5 ...

Page 182: ... in the aft fuselage A push pull tube from the sector to the rudder bell crank translates cable motion to the rudder Springs and a ground adjustable spring cartridge connected to the rudder pedal assembly tension the cables and provide centering force A rudder aileron interconnect is installed to provide a maximum of 8 down aileron with full rudder deflection Right rudder input will cause right ro...

Page 183: ...P N 11934 003 7 13 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1463 Figure 7 3 Rudder Control System Revision A5 ...

Page 184: ... indicated by the alignment of a reference mark on the yoke tube with a tab attached to the instrument panel bolster The elevator trim also provides a secondary means of aircraft pitch control in the event of a failure in the primary pitch control system not involving a jammed elevator Elevator pitch trim operates on 28 VDC supplied through the 2 amp PITCH circuit breaker on Main Bus 1 Roll Trim C...

Page 185: ...n Yaw Trim System Yaw trim is provided by spring cartridge attached to the rudder pedal torque tube and console structure The spring cartridge provides a centering force regardless of the direction of rudder deflection The yaw trim is ground adjustable only Revision A5 ...

Page 186: ...ents and annunciators are located on the left side of the panel and engine instruments are located on the right side of the instrument panel A large color multifunction display is located between the flight instruments and the engine instruments Temperature controls are located on the right side below the engine instruments The SR20 uses standard flight instruments arranged in the basic six patter...

Page 187: ...the left side of the panel and a large color multifunction display is located adjacent to the primary flight display Temperature controls are located on the right side below the glove compartment A switch panel located in the dash board bolster below the flight instruments contains the master switch avionics power switch pitot heat switch and lighting switches Center Console A center console conta...

Page 188: ...ilation Controls 9 Control Yoke 10 Fresh Air Eyeball Outlet 16 0 60 30 30 20 24 28 60 32 P M A T L O V 9 8 7 5 4 1 0 ALTIMETER 3 6 2 SPEED VERTICAL 0 5 5 15 15 10 20 10 S E W N SR20_FM07_1059E G I T F E R L L L FUEL W R H L A G G H N I O L F L E U F 0 6 9 12 18 N A M S S E R P 20 10 30 N O I T C U S 6 4 5 X 100 RPM 0 5 10 35 30 25 20 15 P E T M OIL E S S R P 0 75 50 25 75 100 150 200 100 240 P U S...

Page 189: ...cators 15 Passenger Audio Jacks 16 Armrest 17 Engine Fuel System Controls Legend 1 Start Ignition Key Switch 2 Annunciator Panel 3 Primary Flight Display 4 Overhead Light Switch 5 Magnetic Compass 6 Cirrus Airframe Parachute System CAPS Activation T Handle Cover 7 Multifunction Display 8 Engine Instruments SR20_FM07_2027 18 Left Side Console Circuit Breaker Panel Alternate Engine Air Parking Brake...

Page 190: ...Legend 1 Start Ignition Key Switch 2 Annunciator Panel 3 Primary Flight Display 4 Overhead Light Switch 5 Magnetic Compass 6 Cirrus Airframe Parachute System CAPS Activation T Handle Cover 7 Multifunction Display 8 Glove Box SR20_FM07_2215 18 Left Side Console Circuit Breaker Panel Alternate Engine Air Parking Brake Alternate Static Source 19 Avionics Panel 20 Bolster Switch Panel 21 Control Yoke ...

Page 191: ...rtical and directional gyros ADAHRS also provides roll pitch heading data and continually updates the winds aloft and true airspeed TAS indications on the PFD The magnetometer assembly mounted in the wing also provides outside air temperature OAT data The airplane s Pitot Static system is connected to the PFD to provide airspeed altitude and vertical speed Standby instruments for airspeed attitude...

Page 192: ...yne PFD SR20_FM07_1607B PFD 1 10 PFD 2 10 PITOT STATIC Avidyne MFD STEC System 55x Autopilot Data Aquisition Unit OAT Sensor Magnetometer ESSENTIAL BUS MAIN BUS 2 2 GNS 430 GPS 1 GNS 430 GPS AP ON Flight Director System Optional AP OFF FD ON PFD System Simplified Schematic Revision A5 ...

Page 193: ...VSI is 2000 FPM and for rates above 2000 FPM the needle will peg just outside the scale and a digital readout of actual VSI up to 4000 FPM is then displayed An additional data block is provided for display of outside air temperature OAT true airspeed TAS and groundspeed GS Controls for selecting bug and barometric correction values are along the right side of the PFD A wind indicator is also provi...

Page 194: ...n Avionics Configuration Button s 2 Percent Power 3 Bus Voltages 4 Airspeed Window 5 Airspeed Tape 6 Autopilot Annunciations 7 Aircraft Reference Symbol 8 Bank Angle Indicator 9 Skid Slip Indicator 10 Pitch Ladder 11 Flight Director Steering Command Bars 12 Vertical Deviation Indicator VDI 13 Altitude Tape 14 Altitude Window 15 Vertical Speed Indicator VSI 16 Brightness Control BRT DIM 17 Mode and...

Page 195: ... the left side of the PFD The active flight plan contained in the GPS Nav Com unit selected as the primary navigation source Nav can be optionally selected for display on the HSI as well as the desired range of the optionally selectable moving map display If a localizer or ILS frequency is tuned and captured in the GPS Nav Com selected as the Nav source a vertical deviation indicator VDI and horiz...

Page 196: ...ll attitudes The upper blue sky section and the lower earth sections have pitch reference lines useful for pitch attitude control The indicator can follow maneuvers through 360 in roll and 360 in pitch A knob at the bottom of the instrument allows adjustment of the miniature airplane to the horizon bar for a more accurate flight attitude indication A PULL TO CAGE knob on the indicator is used for ...

Page 197: ... is set in the correction window A knob in the lower left corner of the instrument is used to rotate the pressure altitude scale in the correction window to align the current pressure altitude with the outside air temperature Vertical Speed Indicator Note Serials 1337 and subsequent The Vertical Speed Indicator is integrated into the PFD Airplane rate of climb or descent in feet per minute is disp...

Page 198: ...00 feet Barometric windows on the instrument s face allow barometric calibrations in either inches of mercury in Hg or millibars mb The barometric altimeter settings are input through the barometric adjustment knob at the lower left of the instrument Turn Coordinator Note Serials 1337 and subsequent Turn Coordinator function and roll data display is integrated into the PFD Avionics Configuration 2...

Page 199: ... left instrument panel displays airplane heading by rotating a compass dial in relation to a fixed simulated airplane image and lubber line The compass dial rotates counter clockwise for right turns The compass dial should be set in agreement with the magnetic compass just prior to takeoff As the gyro will precess slightly over a period of time the directional gyro compass dial should be readjuste...

Page 200: ...eaker on Main Bus 1 Avionics Configuration 2 2 The Course Deviation Indicator CDI displays navigation information from GPS 2 Garmin GNS 430 Navigation source selection is made using the CDI button on the GPS 2 control The CDI displays course deviation from a VOR or Localizer LOC and Glideslope when VLOC is the selected navigation source and displays GPS track deviation when GPS is the selected nav...

Page 201: ...ne s magnetic compass using the PUSH SET CARD knob in the lower right corner of the instrument The course is set using the Course Arrow knob in the lower left corner of the instrument The HSI course and heading outputs provided to the autopilot to allow NAV LOC GPS course tracking or to track a preset heading The HSI incorporates conventional warning flags The HDG Heading flag will be out of view ...

Page 202: ...e pointer course deviation bar TO FROM indicator glideslope indicator and flags Heading bug and course pointer settings include digital readouts that make it easy to set precise headings and courses One button operation allows primary navigation to be selected from up to four different sources two VOR ILS receivers and two GPS receivers Either GPS1 or NAV1 may be selected as primary navigation sou...

Page 203: ...ing conditions Redundant circuits paralleled through diodes at the indicator supply DC electrical power for gyro operation 28 VDC for the redundant power circuits is supplied through the 5 amp HSI PFD 1 circuit breaker on the Essential Bus and 5 amp HSI PFD 2 circuit breaker on Main Bus 2 Magnetic Compass A conventional internally lighted liquid filled magnetic compass is installed on the cabin he...

Page 204: ...roximity switches in the actuator limit flap travel to the selected position and provide position indication The wing flaps and control circuits are powered by 28 VDC through the 15 amp FLAPS circuit breaker on the Non Essential Bus Flap Control Switch An airfoil shaped FLAPS control switch is located at the bottom of the vertical section of the center console The control switch is marked and has ...

Page 205: ...P N 11934 003 7 35 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1460 Figure 7 7 Wing Flaps Revision A5 ...

Page 206: ...ount structure The nosewheel is free castering and can turn through an arc of approximately 216 degrees 108 degrees either side of center Steering is accomplished by differential application of individual main gear brakes The tube type nosewheel tire is 5 00 x 5 Airplane Cabin Cabin Doors Caution Serials 1423 and subsequent The seat back must be in the fully upright or the fully reclined position ...

Page 207: ...MER IN ARMREST CABIN SPEAKER TIEDOWN LOOPS 4 PLACES BAGGAGE FLOOR TIEDOWN LOOPS 6 PLACES AFT BULKHEAD UNDER PILOT S SEAT PASSENGER FRESH AIR OUTLET OVERHEAD LIGHT AND SWITCH DOOR HANDLE DEFROST AIR OUTLETS STALL WARNING HORN A DETAIL A CAPS ACTIVATION T HANDLE OVERHEAD SR20_FM07_1064 Figure 7 8 Cabin Arrangement Revision A5 ...

Page 208: ...lkhead The tie down straps should be stowed attached and tightened to the fittings If not adequately restrained baggage compartment items may pose a projectile hazard to cabin occupants in the event of rapid deceleration Secure all baggage items with tie down straps To install tie down strap 1 Position straps over baggage Thread straps through luggage handles if possible 2 Clip hook ends of straps...

Page 209: ...position control handle 2 Slide the seat into position 3 Release the handle and check that the seat is locked in place To adjust recline position 1 Actuate and hold the seat back control lever 2 Position the seat back to the desired angle 3 Release the control lever Each rear seat consists of a fixed seat bottom a folding seat back and a headrest The seat backs can be unlatched from inside the bag...

Page 210: ...ugh 1540 after SB 2X 25 14 and serials 1541 and subsequent An inflatable shoulder harness is integral to each crew 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 In the event of a crash the sensor evaluates the crash pulse and sends a signal to an inflator assembly moun...

Page 211: ...escape path for the cabin occupants Fire Extinguisher A liquefied gas type fire extinguisher containing Halon 1211 1301 extinguishing agent is mounted on the forward inboard side of the pilot s seat base The extinguisher is approved for use on class B liquid grease and class C electrical equipment fires The Halon 1211 1301 blend provides the best fire extinguishing capability with low toxicity A p...

Page 212: ...ust be visually inspected before each flight to assure that it is available charged and operable The preflight inspection consists of ensuring that the nozzle is unobstructed the pin has not been pulled and the canister has not been damaged Additionally the unit should weigh approximately 1 5 lb 0 7 kg For preflight charge can be determined by hefting the unit Revision A5 ...

Page 213: ...is below 170 F or the pressure drop is greater than 18 psi Bypass or cooled oil is then directed through the one quart full flow oil filter a pressure relief valve and then through oil galleries to the engine rotating parts and piston inner domes Oil is also directed to the propeller governor to regulate propeller pitch The complete oil system is contained in the engine An oil filler cap and dipst...

Page 214: ...ual injector nozzles The system meters fuel flow in proportion to engine RPM throttle angle and ambient altitude pressure Manual mixture control and idle cut off are provided An electric fuel pump provides fuel boost for vapor suppression and for priming Engine Air Induction System Induction air enters the engine compartment through the two inlets in the forward cowling The air passes through a dr...

Page 215: ...e control labeled MAX POWER IDLE on the console adjusts the engine throttle setting in addition to automatically adjusting propeller speed The lever is mechanically linked by cables to the air throttle body fuel metering valve and to the propeller governor Moving the lever towards MAX opens the air throttle butterfly and meters more fuel to the fuel manifold A separate cable to the propeller gover...

Page 216: ...ter and activates both magnetos The switch automatically returns to the BOTH position when released Alternate Air Control An Alternate Induction Air Control knob labeled ALT AIR PULL is installed on the left console near the pilot s right ankle To operate the control depress the center lock button pull the knob to the open position and then release the lock button Pulling the knob opens the altern...

Page 217: ...ssure are continuously displayed in the engine data block located in the lower right corner of the PFD System health caution and warning messages are displayed in color coded advisory boxes in the lower right corner of the MFD In addition the text of the engine parameters displayed on the PFD change to the corresponding color of advisory box during an annunciation event The oil temperature pressur...

Page 218: ...E R L FUEL Controls LEGEND 1 Power Lever 2 Mixture Control 3 Friction Control 4 Tachometer 5 EGT Alternate Air Control Start Ignition Switch 3 2 1 SR20_FM07_1603A Serials 1005 thru 1336 Switch is located on the left bolster panel 6 CHT 7 Oil Temperature 8 Oil Pressure 9 Manifold Pressure Engine Controls and Indicating Sheet 1 of 2 Revision A5 ...

Page 219: ...EGT shown with EMax 6 CHT shown with EMax 7 Oil Temperature 8 Oil Pressure 9 Manifold Pressure 10 Percent Power 11 Oil Warning Light 5 4 11 7 8 Engine Instruments 9 6 Multifunction Display Primary Flight Display 4 9 8 10 Annunciator Panel SR20_FM07_2217 Serials 1582 subs Figure 7 9 Engine Controls and Indicating Sheet 2 of 2 Revision A5 ...

Page 220: ...he lower right corner of the PFD In the event engine speed exceeds 2710 RPM for five seconds the MFD will display Check RPM in a red advisory box in the lower right corner of the MFD 28 VDC for the digital instrument operation is supplied through the 2 amp ANNUN ENGINE INST circuit breaker on the Essential Bus Exhaust Gas Temp Cylinder Head Temp Gage Bar Graphs Serials 0002 through 1601 1603 throu...

Page 221: ...nts The CHT of the cylinder is displayed above the bar in text and an up or down trend arrow appears below the temperature to indicate whether EGT is rising or falling In the event CHT exceeds 420 F the MFD will display Check CHT in a yellow advisory box in the lower right corner of the MFD In the event CHT exceeds 460 F the MFD will display Check CHT in a red advisory box in the lower right corne...

Page 222: ...box in the lower right corner of the MFD Oil pressure is shown in the upper right most corner of the MFD as both a simulated pressure gage and as text The simulated gage receives a pressure signal from a sensor mounted below the oil cooler via the DAU and sweeps a scale marked from 0 psi to 100 psi in 5 psi increments Oil pressure is also continuously displayed in the engine data block located in ...

Page 223: ...gage and as text The simulated gage receives a pressure signal from a pressure sensor mounted in the induction air manifold near the throttle body via the DAU and sweeps a scale marked from 10 to 30 inches Hg in one inch Hg increments Manifold pressure is also continuously displayed in the engine data block located in the lower right corner of the PFD 28 VDC for the digital instrument operation is...

Page 224: ...il temperature or low oil pressure The light is illuminated by a switch in the oil temperature gage DAU if the oil temperature reaches 240 F or if the oil pressure drops to 10 psi or less If the OIL warning light comes on in flight refer to the oil temperature and pressure gages to determine the cause Typically low oil pressure will be accompanied by a high oil temperature indication The light is ...

Page 225: ...le control lever in the cockpit The propeller governor boosts oil pressure in order to regulate propeller pitch position Moving the throttle lever forward causes the governor to meter less high pressure oil to the propeller hub allowing centrifugal force acting on the blades to lower the propeller pitch for higher RPM operation Reducing the power throttle lever position causes the governor to mete...

Page 226: ... indicators Positive pressure in the tank is maintained through a vent line from each wing tank Fuel from each wing tank gravity feeds through strainers and a check valve to the associated collector tank sump in each wing Each collector tank sump incorporates a flush mounted fuel drain and a vent to the associated fuel tank The engine driven fuel pump pulls filtered fuel from the two collector tan...

Page 227: ...IRCUIT DAU GASCOLATOR ELECTRIC AUXILIARY PUMP R WING COLLECTOR VENT FILLER R WING TANK FILLER OFF FEED RETURN LEFT RIGHT FEED RETURN SELECTOR VALVE OPERATION FUEL FLOW INDICATOR ANNUNCIATOR FUEL FUEL QUANTITY INDICATOR FUEL PUMP PRIME BOOST DRAIN 5 PLACES INJECTOR MANIFOLD FIREWALL VENT L WING TANK L WING COLLECTOR FUEL RELAY ENGINE DRIVEN FUEL PUMP MIXTURE CNTL FLAPPER VALVE FLAPPER VALVE SELECTO...

Page 228: ...ter factory installation or after Service Bulletin SB 22 77 01 The following fuel system component descriptions are the same as those listed for airplane serials 1582 and subsequent except MFD functionality is enhanced by displaying fuel used fuel remaining time remaining fuel economy and the addition of Initial Usable Fuel page Refer to Avidyne FlightMax EX5000C Pilot s Guide P N 600 00108 000 Re...

Page 229: ...illuminate the FUEL caution light when the fuel quantity goes below approximately 8 9 gallons in each tank The indicator is internally lighted Serials 1268 through 1581 28 VDC for fuel quantity system operation is supplied through the 5 amp ENGINE INST circuit breaker on Main Bus 1 Serials 1582 and subsequent 28 VDC for fuel quantity system operation is supplied through the 5 amp FUEL QTY HOBBS ci...

Page 230: ...us Design Airplane Description SR20 Figure 7 11 4 Serials 1005 thru 1581 LEGEND 1 Fuel Pump Switch 2 Fuel Quantity Gage 3 Fuel Selector Valve 4 Fuel Flow 3 2 1 SR20_FM07_2225 Fuel System Controls and Indicating Sheet 1 of 2 Revision A5 ...

Page 231: ...END 4 Fuel Flow 5 Fuel Used EMax only 6 Fuel Remaining EMax only 7 Time Remaining EMax only 8 Fuel Economy EMax only 9 Fuel Caution Light Multifunction Display Primary Flight Display 4 Annunciator Panel 4 5 6 7 8 SR20_FM07_2227 Serials 1582 subs Figure 7 11 Fuel System Controls and Indicating Sheet 2 of 2 Revision A5 ...

Page 232: ... MFD will display Check Fuel Flow in a red advisory box in the lower right corner of the MFD 28 VDC for the digital instrument operation is supplied through the 2 amp ANNUN ENGINE INST circuit breaker on the Essential Bus Fuel Caution Light The amber FUEL caution light in the annunciator panel comes on to indicate a low fuel condition The light is illuminated by switches in the fuel quantity indic...

Page 233: ...on The oil pressure oil temperature sensor provides a signal to the starting circuit DAU to generate a ground for the oil annunciator and the fuel system This system allows the fuel pump to run at high speed PRIME when the engine oil pressure is less than 10 PSI Whenever the engine oil pressure exceeds 10 PSI pressing PRIME will have no effect Selecting BOOST energizes the boost pump in low speed ...

Page 234: ...brakes are plumbed so that depressing either the pilot s or copilot s left or right toe brake will apply the respective left or right main wheel brake The reservoir is serviced with Mil H 5606 hydraulic fluid Brake system malfunction or impending brake failure may be indicated by a gradual decrease in braking action after brake application noisy or dragging brakes soft or spongy pedals excessive t...

Page 235: ...t side of the console near the pilot s right ankle Brake lines from the toe brakes to the main wheel brake calipers are plumbed through a parking brake valve For normal operation the knob is pushed in With the knob pushed in poppets in the valve are mechanically held open allowing normal brake operation When the handle is pulled out the parking brake valve holds applied brake pressure locking the ...

Page 236: ...ign Airplane Description SR20 Figure 7 12 CALIPER ASSEMBLY CALIPER ASSEMBLY RUDDER PEDAL 4 SR20_FM07_1015 PARKING BRAKE VALVE PARKING BRAKE KNOB MASTER CYLINDER 4 RESERVOIR MIL H 5606 FLUID ONLY ROTOR DISK ROTOR DISK Brake System Revision A5 ...

Page 237: ...es for starting and electrical power storage Alternator 1 ALT 1 is a belt driven internally rectified 75 amp alternator mounted on the right front of the engine Alternator 2 ALT 2 is a gear driven internally rectified 20 amp alternator mounted on the accessory drive at the rear of the engine ALT 1 is regulated to 28 volts and ALT 2 is regulated to 28 75 volts The output from ALT 1 is connected to ...

Page 238: ...htly higher than ALT 1 Main Distribution Bus voltage ALT 1 will not feed the Essential Distribution Bus unless ALT 2 fails Power Distribution The power distribution system for the SR20 consists of the Main Distribution Bus and the Essential Distribution Bus in the MCU and associated buses in the Circuit Breaker panel The circuit breaker panel is located on the left side of the console next to the ...

Page 239: ...WITCH BAT 1 RELAY FUEL OIL ALT 1 ALT 2 PITOT HEAT ESSENTIAL DIST MAIN DIST 25A 25A 25A 25A 25A VOLT REG ALT 2 F B ALT 1 F B 100A 40A VOLT REG GPS 2 ANNUN ENGINE INST MASTER CONTROL UNIT CIRCUIT BREAKER PANEL TURN COORD 1 AVIONICS ESSENTIAL BAT 2 ALT 1 SWITCH LOW VOLTS ATTITUDE 1 HSI PFD 1 STALL WARNING BATTERY 2 ALT 2 ESSENTIAL POWER ESSENTIAL AUTOPILOT AVIONICS COM 1 GPS 1 FUEL PUMP TURN COORD 2 ...

Page 240: ... BAT 2 switch on will energize those systems connected to the circuit breaker panel Essential Bus If any system on the other buses is energized a failure of the Distribution Bus interconnect isolation diode is indicated When the BAT 1 switch is set to on the remaining systems will be energized To check or use avionics equipment or radios while on the ground the AVIONICS power switch must also be t...

Page 241: ...dicator is internally lighted 28 VDC for instrument lighting is supplied through the 2 amp INST LIGHTS circuit breaker on Main Bus 1 The VOLT pointer sweeps a scale from 16 to 32 volts Refer to Section 2 Limitations in basic POH for instrument limit markings The voltage indication is measured off the Essential Bus The AMP pointer sweeps a scale from 100 to 100 amps with zero at the 9 o clock posit...

Page 242: ...for 20 seconds or more the MFD will display Check ALT 1 or Check ALT 2 respectively in a yellow advisory box in the lower right corner of the MFD 28 VDC for the digital instrument operation is supplied through the 2 amp ANNUN ENGINE INST circuit breaker on the Essential Bus Ammeter Select Switch Serials 1268 through 1581 The AMMETER SELECT switch on the instrument panel is used to select the desir...

Page 243: ...s connected to the Main Essential and Non Essential Buses in the airplane are protected by re settable circuit breakers mounted in the circuit breaker panel on the left side of the center console Essential Buses The circuit breaker panel Essential Bus is powered by ALT 2 from the MCU Essential Distribution Bus through the 20 amp ESSENTIAL POWER circuit breaker and from BAT 2 through the 20 amp BAT...

Page 244: ...us by the isolation diode interconnecting the MCU distribution buses Loads on the Non Essential Equipment Bus are shed by pulling the individual circuit breakers Ground Service Receptacle A ground service receptacle is located just aft of the cowl on the left side of the airplane This receptacle is installed to permit the use of an external power source for cold weather starting and maintenance pr...

Page 245: ...e strobe power supplies are controlled through the STROBE light switch on the instrument panel bolster 28 VDC for strobe light and control circuits is supplied through the 5 amp STROBE LIGHTS circuit breaker on Non Essential Bus Landing Light Serials 1337 and subsequent with SRV standard configuration The airplane is equipped with a Halogen landing light A High Intensity Discharge HID landing ligh...

Page 246: ...hts A string of red LEDs mounted under the instrument panel glareshield provide flood lighting for the instrument panel The lights are controlled through the PANEL lights control on the instrument panel bolster Rotating the knob clockwise energizes the lights and increases brightness The panel lights operate on 28 VDC supplied through the 3 amp CABIN LIGHTS circuit breaker on Main Bus 2 Reading Li...

Page 247: ...ing edge to eyeball outlets for each occupant Each occupant can direct the fresh air flow by positioning the nozzle or control flow rate from off to maximum by rotating the nozzle Heating is accomplished by mixing ventilation air from the fresh air inlets with heated air from the heat exchanger and then distributing the conditioned air to the occupants and or the windshield diffuser Air for heatin...

Page 248: ...TION OFF HEAT COLD FRESH AIR OUTLET E N G I N E E X H A U S T CREW OUTLETS CREW OUTLETS WINDSHIELD DEFROST DIFFUSER HVAC PLENUM TEMP CONTROL AIR INLET HEAT MUFF PASSENGER OUTLET SR20_FM07_1012A FRESH AIR OUTLET FRESH AIR INTAKE PASSENGER OUTLET FRESH AIR INTAKE CABIN HEAT DEFROST SELECT Cabin Heating and Cooling Revision A5 ...

Page 249: ...sh air inlet in the right wing root Rotating the control clockwise opens the butterfly allowing fresh cooling air to enter the mixing plenum Rotating the knob to the full clockwise COLD position provides maximum cooling airflow to the mixing plenum Cabin Air Selector Conditioned air from the mixing plenum can be proportioned and directed to the windshield or passengers by manipulating the Cabin Ai...

Page 250: ...1337 thru 1422 w o PFD Serials 1337 subs w PFD SR20_FM07_1013D PITOT MAST STATIC BUTTONS PITOT STATIC WATER TRAPS ALTERNATE STATIC AIR SOURCE VERTICAL SPEED INDICATOR ALTIMETER ALTITUDE TRANSDUCER OPTIONAL ALTITUDE ENCODER ANNUNCIATOR PITOT HEAT LOGIC CURRENT SENSOR HEATER 7 5A PITOT HEAT CB PITOT HEAT SW Pitot Static System Schematic Revision A5 ...

Page 251: ...tot tube is heated electrically to maintain proper operation in possible icing conditions Pitot heat should be used only when required The Pitot heat system operates on 28 VDC supplied through the 7 5 amp PITOT HEAT COOLING FAN circuit breaker on the Non Essential Bus Pitot Heat Light Illumination of the amber PITOT HEAT caution light indicates that the Pitot Heat switch is in the on position and ...

Page 252: ... low pressure area passes over the stall warning sense inlet a slight negative pressure is sensed by the pressure switch The pressure switch completes a ground circuit causing the warning horn to sound The warning horn provides a 94dB continuous 2800 Hz tone The warning sounds at approximately 5 knots above stall with full flaps and power off in wings level flight and at slightly greater margins i...

Page 253: ...vailable in the following configurations Avionics Configuration 2 0 Serials 1268 through 1336 Single Axis Autopilot S Tec System 20 Integrated Audio System with Intercom Garmin GMA 340 Marker Beacon Receiver Garmin GMA 340 One IFR Approach Certified GPS Garmin GNS 430 and One VFR GPS Garmin GNC 250XL Two VHF Communications Garmin GNS 430 and Garmin GNC 250XL Single Navigation VOR LOC GS Receiver G...

Page 254: ...Receiver GNS 430 Mode C Transponder with Altitude Encoder Garmin GTX 327 Electronic Navigation Display Sandel SN3308 Course Deviation Indicator Avionics Configuration PFD Serials 1337 and subsequent Moving Map Display Avidyne MFD Primary Flight Display Avidyne PFD Two Axis Autopilot S Tec System 55SR Integrated Audio System with Intercom Garmin GMA 340 Marker Beacon Receiver Garmin GMA 340 One IFR...

Page 255: ...sors the WX 500 Stormscope and the SkyWatch Traffic Advisory System The unit is organized around logical grouping of information presented on Pages The Avidyne FlightMax EX Series MFD is 10 4 inch diagonal color Active Matrix Liquid Crystal Display AMLCD integrated into a Control Display Unit CDU which displays the airplane current position and track against a moving map The EX Series MFD can perf...

Page 256: ...r later for a more complete description of the MFD its operating modes and additional detailed operating procedures Autopilot Avionics Configuration 2 0 The standard SR20 is equipped with an S TEC System Twenty Autopilot This single axis autopilot system is a rate based system deriving roll axis control inputs from its electric turn coordinator The programmer computer annunciators and servo amplif...

Page 257: ...provides the ALT hold function Roll axis steering is accomplished by autopilot steering commands to the aileron trim motor and spring cartridge Pitch axis command for altitude hold is accomplished by pitch computer commands to the elevator servo The autopilot operates on 28 VDC supplied through the 5 amp AUTOPILOT circuit breaker on the Essential Bus The S Tec System Thirty Autopilot features Roll...

Page 258: ...des and rates of climb or descent to be used by the autopilot A button on each control yoke handle may be used to disengage the autopilot The autopilot makes roll changes through the aileron trim motor and spring cartridge and makes pitch changes for altitude preselect and hold through the elevator trim motor The autopilot operates on 28 VDC supplied through the 5 amp AUTOPILOT circuit breaker on ...

Page 259: ...amp AUTOPILOT circuit breaker on the Essential Bus The S Tec System 55SR Autopilot features Heading Hold and Command NAV LOC GPS tracking Altitude Hold and Command GPS Steering GPSS for smoother turns onto a course or during course tracking GPS Navigation The Jeppesen Navigation Database provides access to data on Airports Approaches Standard Instrument Departures SIDs Standard Terminal Arrivals S...

Page 260: ...rplane s position latitude longitude and altitude and the altitude encoder to enhance the altitude calculation The GPS1 antenna is located above the headliner along the airplane centerline The GPS2 antenna is located below the glareshield and behind the MFD All GPS navigator controls and functions are accessible through the GPS receiver units front control panels located in the center console The ...

Page 261: ...e upper Garmin GNS 430 is designated COM 1 The Garmin GNS 430 control panel provides COM 1 transceiver active and standby frequency indication frequency memory storage and knob operated frequency selection The COM 1 transceiver provides either 720 channel 25 kHz spacing or 2280 channel 8 33 kHz spacing operation in a frequency range from 118 000 to 136 975 MHz The COM 1 antenna is located above th...

Page 262: ...1 The Garmin GNS 420 control panel provides COM 1 transceiver active and standby frequency indication frequency memory storage and knob operated frequency selection The transceiver provides either 720 channel 25 kHz spacing or 2280 channel 8 33 kHz spacing operation in a frequency range from 118 000 to 136 975 MHz The COM 1 antenna is located above the cabin on the airplane centerline 28 VDC for C...

Page 263: ...to the Garmin GNS control mounted in the center console Each unit has VHF Omnirange Localizer VOR LOC capability The VOR LOC receiver receives VOR LOC on a frequency range from 108 000 Mhz to 117 950 Mhz with 50 kHz spacing The GNS 430 has glideslope capability Glideslope is received from 329 150 to 335 000 in 150 kHz steps The receiver control provides active and standby frequency indication freq...

Page 264: ...on the underside of the fuselage just aft of the firewall 28 VDC for transponder operation is controlled through the Avionics Master Switch on the bolster switch panel 28 VDC for receiver transmitter and altitude encoder operation is supplied through the 2 amp ENCODER XPONDER circuit breaker on the Avionics Non Essential Bus Audio System The airplane is equipped with a Garmin GMA 340 Audio Panel R...

Page 265: ...perations A remote switch and indicator panel is installed immediately below the circuit breaker panel The transmitter unit is mounted longitudinally in the airplane in order to detect deceleration greater than 3 5 ft sec If rapid deceleration is detected the transmitter will repeatedly transmit VHF band audio sweeps at 121 5 MHz and 243 0 MHz approximately 0 5 seconds apart The transmitter and po...

Page 266: ... lead from front of unit c Disconnect lead from remote switch and indicator unit d Loosen attach straps and remove transmitter unit and portable antenna e Attach portable antenna to antenna jack on front of unit f Set main control switch to ON g Hold antenna upright as much as possible Hour Meter The airplane is equipped with an hour meter to record engine operating time The hour meter is located ...

Page 267: ...talled to provide up to three years battery back up SEL and CTL Buttons All time keeping and set functions are addressable using the Select and Control buttons below the time display Upon power up the clock will display Universal Time UT Pressing the Select button 3 times will display Local Time LT and Elapsed Time ET sequentially Pressing the button again will return the display to UT Set UT or L...

Page 268: ... the display flashes Pressing either Select or Control deactivates the alarm Test Mode To enter the self test mode hold the Select button for 3 seconds The display will indicate 88 88 and all four UT LT FT ET annunciators will come on OAT VOLTS Button Serials 1268 through 1337 The red OAT VOLTS button is used to display Outside Air Temperature and airplane Main Bus voltage When the airplane is pow...

Page 269: ... System Description The CAPS consists of a parachute a solid propellant rocket to deploy the parachute a rocket activation handle and a harness imbedded within the fuselage structure A composite box containing the parachute and solid propellant rocket is mounted to the airplane structure immediately aft of the baggage compartment bulkhead The box is covered and protected from the elements by a thi...

Page 270: ...ndle and prevents tampering with the control The cover is be removed by pulling the black tab at the forward edge of the cover Pulling the activation T handle will activate the rocket and initiate the CAPS deployment sequence To activate the rocket two separate events must occur 1 Pull the activation T handle from its receptacle Pulling the T handle removes it from the o ring seal that holds it in...

Page 271: ...pin has been removed before further flight Deployment Characteristics When the rocket launches the parachute assembly is extracted outward due to rocket thrust and rearward due to relative wind In approximately two seconds the parachute will begin to inflate When air begins to fill the canopy forward motion of the airplane will dramatically be slowed This deceleration increases with airspeed but i...

Page 272: ...from a height of approximately 10 feet While the airframe seats and landing gear are designed to accommodate this stress occupants must prepare for it in accordance with the CAPS Deployment procedure in Section 3 Emergency Procedures Note The CAPS is designed to work in a variety of aircraft attitudes including spins However deployment in an attitude other than level flight may yield deployment ch...

Page 273: ... 8 8 Ground Handling 8 10 Application of External Power 8 10 Towing 8 11 Taxiing 8 12 Parking 8 13 Tiedown 8 14 Leveling 8 14 Jacking 8 15 Servicing 8 16 Landing Gear Servicing 8 16 Brake Servicing 8 16 Tire Inflation 8 17 Propeller Servicing 8 18 Oil Servicing 8 18 Fuel System Servicing 8 21 Fuel Contamination and Sampling 8 23 Draining Fuel System 8 23 Battery Service 8 24 Cleaning and Care 8 25...

Page 274: ...1934 003 Section 8 Cirrus Design Handling Servicing Maintenance SR20 Instrument Panel and Electronic Display Screens 8 31 Headliner and Trim Panels 8 31 Leather Upholstery and Seats 8 32 Carpets 8 32 Revision A6 ...

Page 275: ...overing inspection servicing maintenance troubleshooting and repair of the airplane structure systems and wiring Revision Service for this manual is also available A current copy of the AMM is provided at delivery Engine Operators and Maintenance Manual Cirrus Design provides a Teledyne Continental Engine Operator s and Maintenance Manual at the time of delivery Engine and engine accessory overhau...

Page 276: ...a or corrections not requiring a Service Bulletin Give careful attention to the Service Advisory Notice information Ordering Publications SR20 publications revision service and service publication subscription service may be obtained by contacting Customer Service at Cirrus Design as follows Cirrus Design Corporation Customer Service 4515 Taylor Circle Duluth MN 55811 Phone 218 727 2737 FAX 218 72...

Page 277: ...Required Documents Note A Airworthiness Certificate FAA Form 8100 2 Must be displayed at all times R Registration Certificate FAA Form 8050 3 Must be in the aircraft for all operations R Radio Station License FCC Form 556 Required only for flight operations outside the United States O Operating Instructions FAA Approved Flight Manual and Pilot s Operating Handbook fulfills this requirement W Weigh...

Page 278: ...shes Airworthiness Directives AD s that apply to specific aircraft and aircraft appliances or accessories AD s are mandatory changes and must be complied with within a time limit set forth in the AD Operators should periodically check with Cirrus Service Centers or A P mechanic to verify receipt of the latest issued AD for their airplane Reissue A ...

Page 279: ...rframe and Powerplant A P mechanic holding an Inspection Authorization IA All Cirrus Authorized Service Centers can perform annual inspections The inspection is listed in detail in Chapter 5 of the Cirrus Design SR20 Maintenance Manual If the airplane is used commercially in addition to the annual inspection requirement the regulation requires that the airplane undergo a 100 hour inspection each 1...

Page 280: ...ting system or interfere with an operating system or affect the primary structure Remove install and repair tires Clean grease or replace wheel bearings Replace defective safety wire or cotter pins Lubrication not requiring disassembly other than removal of nonstructural items such as access covers cowlings or fairings Caution Do not use unapproved lubricants Unapproved lubricants may damage contr...

Page 281: ...level and specific gravity 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 Number of hours on the aircraft The certificate number of pilot performing the work Signature of the individual doing the work Logbooks should be complete and up to date Good records r...

Page 282: ... the airplane and battery maintenance performed in accordance with the appropriate Airplane Maintenance Manual procedures 1 Ensure that external power source is regulated to 28 VDC 2 Check BAT and AVIONICS power switches are off 3 Plug external power source into the receptacle 4 Set BAT 1 switch to ON 28 VDC from the external power unit will energize the main distribution and essential distributio...

Page 283: ...or pull on control surfaces or propeller to maneuver the airplane Do not tow the airplane when the main gear is obstructed with mud or snow If the airplane is to be towed by vehicle do not turn the nose wheel more than 90 degrees either side of center or structural damage to the nose gear could result 1 Refer to Airplane Three View Section 1 Figure 1 1 and Turning Radius Section 1 Figure 1 2 or cl...

Page 284: ... Taxi with minimum power needed for forward movement Excessive braking may result in overheated or damaged brakes 1 Remove chocks 2 Start engine in accordance with Starting Engine procedure Section 4 3 Release parking brake 4 Advance throttle to initiate taxi Immediately after initiating taxi apply the brakes to determine their effectiveness During taxiing use differential braking to make slight t...

Page 285: ...rnight chock and tie down the airplane 1 For parking head airplane into the wind if possible 2 Retract flaps 3 Set parking brake by first applying brake pressure using the toe brakes and then pulling the PARK BRAKE knob aft Caution Care should be taken when setting overheated brakes or during cold weather when accumulated moisture may freeze a brake 4 Chock both main gear wheels 5 Tie down airplan...

Page 286: ...il ring at approximately 45 degree angles to the ground When using rope or non synthetic material leave sufficient slack to avoid damage to the airplane should the ropes contract Caution Anchor points for wing tiedowns should not be more than 18 feet apart to prevent eyebolt damage in heavy winds Use bowline knots square knots or locked slipknots Do not use plain slipknots Leveling The airplane is...

Page 287: ...300 lb minimum attached to the tail tiedown 1 Position airplane on a hard flat level surface 2 Remove tiedown rings from wings Stow tie down rings in baggage compartment 3 Attach a weighted tailstand to the tail tiedown ring 4 Position jacks and jack points pads for jacking Insert jack point pad into wing tiedown receptacle Holding the jack point pad in place position the jack under the point and ...

Page 288: ...l change and at the annual 100 hour inspection replenishing the system when necessary The brake reservoir is located on the right side of the battery support frame If the entire system must be refilled refer to the Airplane Maintenance Manual AMM To replenish brake fluid 1 Chock tires and release parking brake 2 Remove top engine cowling to gain access to hydraulic fluid reservoir 3 Clean reservoi...

Page 289: ...ible wear Replace lining when worn to 0 100 inch 2 54 mm Caution Serials 1005 through 1592 after Service Bulletin SB 2X 32 14 and airplane serials 1593 and subsequent Clean and inspect temperature indicator installed to piston housing If indicator center is black the brake assembly has been overheated The brake linings must be inspected and the O rings replaced 3 Check brake assemblies for evidenc...

Page 290: ...ks scratches and corrosion If found they should be repaired as soon as possible by a rated mechanic since a nick or scratch causes an area of increased stress which can lead to serious cracks or the loss of a propeller tip The back face of the blades should be painted when necessary with flat black paint to retard glare To prevent corrosion the surface should be cleaned and waxed periodically Oil ...

Page 291: ...te and insert dipstick 4 Close and secure access panel Approved Oils For the first 25 hours of operation on a new or rebuilt engine or until oil consumption stabilizes use only straight mineral oil conforming to Mil L 6082 If engine oil must be added to the factory installed oil add only MIL L 6082 straight mineral oil Caution MIL C 6529 Type II straight mineral oil with corrosion preventive can c...

Page 292: ...astrolaero AD Oil Castrol Ltd Australia Chevron Aero Oil Chevron U S A Inc Conoco Aero S Continental Oil Delta Avoil Delta Petroleum Co Exxon Aviation Oil EE Exxon Company U S A Mobil Aero Oil Mobil Oil Company Pennzoil Aircraft Engine Oil Pennzoil Company Quaker State AD Aviation Engine Oil Quaker State Oil Refining Co Red Ram Aviation Oil 20W 50 Red Ram Ltd Canada Sinclair Avoil Sinclair Oil Com...

Page 293: ...nks Observe all safety precautions required when handling gasoline Fuel fillers are located on the forward slope of the wing Each wing holds a maximum of 30 3 U S gallons When using less than the standard 60 5 gallon capacity fuel should be distributed equally between each side WARNING Have a fire extinguisher available Ground fuel nozzle and fuel truck to airplane exhaust pipe and ground fuel tru...

Page 294: ... all times to minimize condensation and moisture accumulation in tanks In extremely humid areas the fuel supply should be checked frequently and drained of condensation to prevent possible distribution problems 4 Remove fuel filler cap and fuel airplane to desired level Note If fuel is going to be added to only one tank the tank being serviced should be filled to the same level as the opposite tan...

Page 295: ...ck the wings and lower the tail slightly to move contaminates to the drain points for sampling If after repeated samplings three or more evidence of significant contamination remains do not fly the airplane until a mechanic is consulted the fuel system is drained and purged and the source of contamination is determined and corrected If sampling reveals the airplane has been serviced with an improp...

Page 296: ...cid use distilled water only If the battery is not properly charged recharge it starting with a rate of four amperes and finishing with a rate of two amperes in accordance with Airplane Maintenance Manual AMM procedures The battery should be removed from the airplane for charging and quick charges are not recommended Battery 2 is a maintenance free rechargeable sealed lead acid batter Mounted in t...

Page 297: ... Be sure to remove the static port covers before flight To wash the airplane use the following procedure 1 Flush away loose dirt with water 2 Apply cleaning solution with a soft cloth a sponge or a soft bristle brush 3 To remove exhaust stains allow the solution to remain on the surface longer 4 To remove stubborn oil and grease use a cloth dampened with naphtha 5 Rinse all surfaces thoroughly Any...

Page 298: ...only a nonabrasive cotton cloth or genuine chamois to clean acrylic windows Paper towel or newspaper are highly abrasive and will cause hairline scratches 1 Remove grease or oil using a soft cloth saturated with kerosene then rinse with clean fresh water Note Wiping with a circular motion can cause glare rings Use an up and down wiping motion to prevent this To prevent scratching from dirt that ha...

Page 299: ...d degreaser In order to remove especially heavy dirt and grease deposits it may be necessary to brush areas that were sprayed Caution Do not spray solvent into the alternator vacuum pump starter or induction air intakes 4 Allow the solvent to remain on the engine from 5 to 10 minutes Then rinse engine clean with additional solvent and allow it to dry Caution Do not operate the engine until excess ...

Page 300: ...the gear area with solvent or a mixture of solvent and degreaser as desired Where heavy grease and dirt deposits have collected it may be necessary to brush areas that were sprayed in order to clean them 3 Allow the solvent to remain on the gear from five to ten minutes Then rinse the gear with additional solvent and allow to dry 4 Remove the cover from the wheel and remove the catch pan 5 Lubrica...

Page 301: ...stem Fuselage Exterior Wings and Wheels AeroShell Flight Jacket Plexicoat Fuselage Exterior ShellStore Online XL 100 Heavy Duty Cleaner Degreaser Fuselage Exterior and Landing Gear Buckeye International Stoddard Solvent PD 680 Type ll Engine Compartment Any Source Kerosene Exterior Windscreen and Windows Any Source Klear To Land Exterior Windscreen and Windows D W Davies Co Prist Exterior Windscre...

Page 302: ...solvent free none abrasive antistatic acrylic cleaner Do not use gasoline alcohol benzene carbon tetrachloride thinner acetone or glass window cleaning sprays Use only a nonabrasive cotton cloth or genuine chamois to clean acrylic windows Paper towel or newspaper are highly abrasive and will cause hairline scratches Note Wiping with a circular motion can cause glare rings Use an up and down wiping...

Page 303: ...ay screen with power OFF 1 Gently wipe the display with a clean dry cotton cloth 2 Moisten clean cotton cloth with cleaning solution 3 Wipe the soft cotton cloth across the display in one direction moving from the top of the display to the bottom Do not rub harshly 4 Gently wipe the display with a clean dry cotton cloth Headliner and Trim Panels The airplane interior can be cleaned with a mild det...

Page 304: ...e soaps as they contain alkaline which will alter the leather s pH balance and cause the leather to age prematurely Cover areas where cleaning solution could cause damage Use the following procedure Caution Solvent cleaners and alcohol should not be used on leather upholstry 1 Clean leather upholstery with a soft bristle brush and vacuum where necessary 2 Wipe leather upholstery with a soft damp c...

Page 305: ...e Kit 50689 001 Leather Upholstery Cirrus Design Leather Cleaner 50684 001 Leather Upholstery Cirrus Design Ink Remover 50685 001 Leather Upholstery Cirrus Design Leather Conditioner 50686 001 Leather Upholstery Cirrus Design Spot and Stain Remover 50687 001 Leather Upholstery Cirrus Design Vinyl Finish Cleaner 50688 001 Vinyl Panels Cirrus Design Vinyl Leather Cleaner 51479 001 Vinyl and Leather ...

Page 306: ...8 34 P N 11934 003 Section 8 Cirrus Design Handling Servicing Maintenance SR20 Revision A3 Intentionally Left Blank ...

Page 307: ...most sections of the handbook Data in a supplement adds to supersedes or replaces similar data in the basic handbook A Log of Supplements page immediately follows this page and precedes all Cirrus Design Supplements produced for this airplane The Log of Supplements page can be utilized as a Table of Contents for this section In the event the airplane is modified at a non Cirrus Design facility thr...

Page 308: ...9 2 P N 11934 003 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank Reissue A ...

Page 309: ...n GNC 420 GPS Navigator 05 25 05 ___ 11934 S24 Sandel Avionics SN3308 Navigation Display 01 07 03 ___ 11934 S25 R1 Winterization Kit 12 07 04 ___ 11934 S27 R2 S Tec System 55SR Autopilot 07 18 05 ___ 11934 S28 Garmin GTX 330 Mode S Transponder 07 03 04 ___ 11934 S29 SR20 Airplanes Registered in the European Union 05 27 04 ___ 11934 S30 Honeywell KGP 560 Terrain Awareness Warning System07 03 04 ___...

Page 310: ...9 4 P N 11934 003 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank Revision A5 ...

Page 311: ...20 this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook Handbook Information in this supplement either adds to supersedes or deletes information in the basic Handbook Note This POH Supplement Revision dated Revision 1 07 18 05 supersedes and replaces the original issue of this supplement dated 07 03 04 This rev...

Page 312: ...elect Button LED 3 Marker Sensitivity Select Button a HI Sensitivity LED b LO Sensitivity LED 4 Pilot Intercom Squelch outer knob 5 Power Intercom Volume inner knob 6 Transceiver Audio Select Buttons LEDs 7 Photocell 8 Receiver Audio Select Buttons LEDs 9 Transceiver Audio Transmit Select Buttons LEDs 10 Split COM Button LED 11 Cabin Audio Select Buttons LEDs a SPKR Cabin Speaker b PA Public Addre...

Page 313: ...eration of the Audio Control Panel Section 5 Performance No change from basic Handbook Section 6 Weight Balance Garmin GMA 340 Audio System No change from basic Handbook Installation of the optional XM Radio System adds the following optional Sym O equipment at the weight and arm shown in the following table Section 7 System Description Power On and Fail safe Operation The Audio Control Panel is p...

Page 314: ...gation receiver audio source is selected by depressing NAV1 NAV2 if installed MKR DME if installed or ADF if installed will select that radio or device as the audio source Audio level of navigation receivers is controlled through the selected radio volume control Transceiver audio is selected by depressing COM1 COM2 or COM3 if installed When the audio source is selected using the COM1 COM2 and COM...

Page 315: ...is not available in this installation Speaker Output Pressing the SPKR button will cause the selected airplane radios to be heard over the cabin speaker Speaker output is muted when a COM microphone is keyed Speaker level is adjustable through an access hole in the top of the unit refer to Garmin installation manual or AMM Public Address PA Function Pressing the PA button on the audio control pane...

Page 316: ...and pilot or copilot ICS activity will mute Music1 Music2 is not muted When both the PILOT and CREW ICS Isolation mode are not selected Music1 is available to crew and passengers Radio activity and MKR activity will mute Music1 Intercom Intercom controls are located towards the left side of the Audio Control Panel The controls consist of a Volume control for the pilot and copilot a Squelch control...

Page 317: ...an adjust the trip level of the VOX squelch to fit the individual voice and microphone this helps eliminate the frustration of clipping the first syllables There is a slight delay after a person stops talking before the channel closes This prevents closure between words and eliminates choppy communications To adjust squelch 1 With the engine running set the VOX trip level by slowly rotating the SQ...

Page 318: ...io receptions or pilot transmissions CREW Pilot and copilot are connected on one intercom channel and have exclusive access to the aircraft radios They may also listen to Music1 Passengers can continue to communicate with themselves without interrupting the Crew and also may listen to Music2 ALL All parties will hear the aircraft radio intercom and Music1 The music volume increases gradually back ...

Page 319: ...below Marker Beacon Sensitivity The SENS push button on the left side of the panel is used to set the marker beacon receiver sensitivity The selected sensitivity level is indicated by illumination of the HIGH or LOW LED When HIGH sensitivity is selected the outer marker beacon tone will sound farther out Selecting LOW sensitivity at this point allows more accurate location of the Outer Marker Typi...

Page 320: ...rom two geosynchronous XM broadcast satellites The audio signal is then sent by wire to the Audio Control Panel s Music1 and Music2 AUDIO INPUT jacks System operation is provided by a hand held wireless controller When initially powered the XM radio volume is set to mute and will remain muted until the XM radio establishes communication with the wireless controller System volume for both AUDIO INP...

Page 321: ...PS Navigator with VHF COM is installed in the Cirrus Design SR20 this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement either adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Original 3...

Page 322: ...gitizer to enhance the altitude calculation The VHF COM transceiver facilitates communication with Air Traffic Control Provided the GPS Navigator is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy specifications of AC 20 138 for VFR flight Navigation is accomplished using the WGS 84 NAD 83 coordinate reference datum Navigation data is b...

Page 323: ...r is invalid utilize remaining operational navigation equipment as required 2 If the RAIM POSITION WARNING message is displayed immediately revert to an alternate means of navigation appropriate to the route and phase of flight 3 If the RAIM NOT AVAILABLE message is displayed continue to navigate using the GPS equipment or revert to an alternate means of navigation appropriate to the route and pha...

Page 324: ...eted the Navigator asks for NavData database confirmation displays the satellite status page while it acquires position and then displays the acquired position on the Navigator s display Deactivate GPS 1 Navigator COM Power Switch Rotate CCW OFF Section 5 Performance No Change Section 6 Weight Balance No Change Section 7 Systems Description Note This supplement provides a general description of th...

Page 325: ... GPS satellite network to derive the airplane s position latitude longitude and altitude and the altitude digitizer to enhance the altitude calculation The GPS antenna is located on the underside of the glareshield behind the MFD All GPS navigator controls and functions are accessible through the GNC 250XL front control panel located in the center console The panel includes function keys power swi...

Page 326: ...0XL front panel Frequency tuning is accomplished by rotating the large and small concentric knobs to select a standby frequency and then transferring the frequency to the active window The active frequency is always displayed at the upper left corner of the GNC 250XL display The standby frequency is displayed below the active frequency in the map mode and to the right of the active frequency in al...

Page 327: ...ment is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement either adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Note This POH Supplement Revision dated 12 07 04 supersedes and replaces the original ...

Page 328: ...Pilot inputs to the autopilot are made through the multi function control knob at the upper left corner of the turn coordinator The control knob provides mode selection disengage and turn command functions The autopilot drives the aileron trim motor and spring cartridge to control airplane roll The S Tec System Twenty Autopilot features Roll Stabilization Turn Command NAV LOC GPS tracking HI and L...

Page 329: ...iguration Section 3 Emergency Procedures Autopilot Malfunction Refer to Electric Trim Autopilot Failure procedure in the basic Handbook Do not reengage the autopilot until the malfunction has been identified and corrected The autopilot may be disconnected by 1 Pressing and holding the Mode Selector Knob on the Turn Coordinator for approximately 2 seconds 2 Pressing the Trim Switch on the control y...

Page 330: ...n right Note that control yokes follow movement of knob 4 Heading Mode TEST a Center the HDG bug under the lubber line on the HSI or DG b Momentarily depress Autopilot Mode Selector and note that HD Heading light illuminates c Then rotate HDG knob on the DG or HSI to the left then right Note that control yokes follow movement of knob Then return HDG bug to lubber line 5 Overpower Test a Grasp cont...

Page 331: ...sengages Move control yoke to confirm that roll control is free with no control restriction or binding d Repeat steps b and c using Copilot Trim Switch Inflight Procedures 1 RDY Light CHECK ON 2 Trim airplane for existing flight conditions 3 Center Autopilot Mode Selector Knob and then depress once to enter ST Stabilizer mode 4 Rotate Autopilot Mode Selector Knob as desired to setup level or turni...

Page 332: ...nd VOR LOC Approach 1 Begin with a reliable VOR or VOR LOC signal and CDI course needle centered with airplane on the suggested heading to the waypoint Note The airplane must be within 5 of the desired course when TRK is selected If airplane is more than 5 off the selected course the autopilot will turn the airplane towards the course but may not capture and track it 2 Use Autopilot Mode Selector ...

Page 333: ...d mode discussed in the following paragraphs and shown in Figure 1 is not available with the System Twenty Autopilot This feature is available on the System Thirty Autopilot Altitude hold is shown in this supplement only because both the System Twenty and Thirty Autopilots use the same Turn Coordinator Altitude hold is not selectable and the associated annunciators will not illuminate All Autopilo...

Page 334: ... the autopilot will turn the airplane to the heading and then follow the heading Subsequent heading changes can be made using the HDG knob on the DG or HSI TRK Track Mode When TRK LO is selected the autopilot will provide low system gain for comfortable cross country tracking of GPS or VOR courses When TRK HI is selected the autopilot will provide a higher level of system gain for more active trac...

Page 335: ...es FAR Part 91 or FAR Part 135 this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook Handbook Information in this supplement either adds to supersedes or deletes information in the basic Handbook Note This POH Supplement Revision dated 01 07 03 supersedes and replaces the original issue of this supplement dated ...

Page 336: ...vailable to each user The instructions must contain the following information A warning against smoking while oxygen is in use An illustration showing the correct method of donning and A visible warning against use of the cannula with nasal obstructions or head colds with resultant nasal congestion The oxygen bottle must be secured in the right front seat so that the pilot can view the oxygen pres...

Page 337: ...Oxygen Bottle right front seat Check Properly Secured 2 Oxygen Masks or Cannulas Connected to Regulator 3 Oxygen Pressure Gage Green Arc 4 Oxygen Shutoff Valve OFF Before Starting Engine 1 Passengers Brief on Oxygen System Operation Note Briefing to include oxygen mask cannula donning flowmeter adjustment and connection to oxygen bottle regulator Climb As airplane approaches altitude requiring oxy...

Page 338: ... Refer to approved system manufacturer s data for a description of the equipment cleaning instructions and specific operational instructions Mounting Instructions The oxygen bottle must be properly mounted in the right front passenger seat using the cylinder harness supplied with the system When properly mounted and secured the pilot will be able to view the oxygen pressure gage and operate the sh...

Page 339: ...ps on forward side of bottle as shown in Detail B through the male buckle half and through the cinch as shown in Detail C Insert male buckle half into female buckle half and tighten strap at cinch LOOP FEMALE BUCKLE CINCH MALE BUCKLE SR20_FM09_1081 OXYGEN BOTTLE TUFF PACK BAG Same as step 2 LOOP CLIP Clip strap to triangular loop as shown in Detail A Route strap over headrest down the back of the ...

Page 340: ...ersons Using O2 Altitude Feet 10 000 15 000 18 000 XCP 180 134 1 2 23 1 49 1 24 2 1 12 0 75 0 62 3 0 74 0 50 0 41 XCP 415 371 1 6 18 4 12 3 43 2 3 09 2 06 1 71 3 2 06 1 37 1 14 XCP 682 609 1 10 15 6 77 5 64 2 5 08 3 39 2 82 3 3 38 2 26 1 88 Durations assume typical flow rate of 1 0 liter minute at 10 000 feet pressure altitude Oxygen Duration Revised 01 07 03 ...

Page 341: ... this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Note This POH Supplement Revision dated Revision 1 07 18 05 supersedes and replac...

Page 342: ...is FOR REFERENCE ONLY and must not be used for navigation Section 3 Emergency Procedures There is no change to the basic POH Emergency Procedures when the WX500 stormscope is installed Section 4 Normal Procedures Refer to the Multi Function Display Pilot s Guide installed with the airplane for detailed operating procedures and specific display information Stormscope Status Box When the Stormscope ...

Page 343: ...Guide installed with the airplane for detailed operating procedures and specific display information The L 3 Avionics Systems WX 500 Weather Mapping Sensor Stormscope detects electrical discharges associated with thunderstorms and displays the activity on the Multi Function Display The system consists of an antenna located on top of the fuselage just forward of the rear window and a processor unit...

Page 344: ...4 P N 11934 002 Section 9 Cirrus Design Supplements SR20 Revision 1 07 18 05 Intentionally Left Blank ...

Page 345: ...sponder is installed in the Cirrus Design SR20 this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook 26 Dec 2000 Original 12 26 00 ...

Page 346: ...ides complete operating instructions for the GTX 327 and does not require any additional data be carried in the airplane SR20_FM09_1501 1 2 3 4 5 6 7 8 9 10 1 Identification Key 2 Mode Selector Keys a OFF b STBY Standby c ON d ALT 3 Display Window 4 FUNC Function Key 5 CRSR Cursor 6 CLR Clear Key 7 START STOP Key 8 Photocell 9 VFR Key 10 Selector Keys a 0 7 Code Selection b 8 9 Display Brightness ...

Page 347: ...dary surveillance radar Before Takeoff 1 Transponder Mode Selector Keys ALT If the transponder is in the STBY mode it will automatically switch to ALT during takeoff when the groundspeed increases through approximately 35 knots The transponder will respond to ATC Mode C altitude and identification interrogations Note Selecting ON puts the transponder in Mode A identification only The transponder w...

Page 348: ...ransmits to the interrogating Air Traffic Control Center Digitized altitude information is provided by the altitude digitizer encoder plumbed into the airplane static system The transponder and integrated controls are mounted in the center console The transponder control provides active code display code selection IDENT button and test functions The display is daylight readable and is automaticall...

Page 349: ...ions from an ATC secondary ground surveillance radar system This is the normal position for ground operations in the SR20 Note STBY mode is automatically entered from ALT mode during landing ground roll as the groundspeed decreases through 35 knots ON Powers on the GTX 327 in Mode A identification mode The last active identification code will be selected In addition to the airplane s identificatio...

Page 350: ...rrent code 2 Use 0 7 keys to input the new code The new code will not be activated until the last fourth digit is entered Pressing the CLR key will move the cursor back to the previous digit Pressing the CRSR key during code entry will remove the cursor and cancel the entry Note When making routine code changes avoid inadvertent selection of code 7500 and all codes within the 7600 series 7600 7677...

Page 351: ...sponder to the pre programmed VFR code selected in the configuration mode factory set to 1200 Pressing the VFR key a second time will restore the previous identification code FUNC Key Pressing the FUNC key changes the data shown on the right side of the display Pressing the FUNC key a second time will cycle the display to the next data Displayed data includes Pressure Altitude Flight Time Count Up...

Page 352: ...al time Pressing the CLR key resets the timer to the initial value CONTRAST Allows adjustment of display contrast When CONTRAST is selected pressing the 8 key reduces contrast and pressing 9 increases contrast DISPLAY The display function is not available in this installation Display brightness is automatically controlled through a photocell in the front panel Original 12 26 00 ...

Page 353: ...20 this POH Supplement is applicable and must be inserted in the Supplements Section Section 9 of the appropriate Cirrus Design Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic Pilot s Operating Handbook Note This POH Supplement Revision dated 10 12 05 supersedes and replaces ...

Page 354: ...ormation shown on the GARMIN 430 displays is provided as an aid in visually acquiring traffic Pilots must maneuver the aircraft based only upon ATC guidance or positive visual acquisition of conflicting traffic 2 If the pilot is advised by ATC to disable transponder altitude reporting the SkyWatch must be turned OFF 3 The L 3 Avionics Systems SkyWatch Traffic Advisory System Model SKY497 Pilot s G...

Page 355: ... reduced and aural warnings will be inhibited when flaps are set to 50 and 100 3 Refer to the GARMIN 400 Series Pilot s Guide Addendum for Display Interface for Traffic and Weather Data P N 190 001140 10 Rev B for additional SkyWatch operational data not included in this supplement Operator Initiated Control of SkyWatch Self Test In addition to the power up self test an automatic self test is perf...

Page 356: ...he cursor on and highlight OPER 2 Use the small PUSH CRSR knob to select STBY 3 Press the ENT key to place SkyWatch in the STBY standby mode Change Altitude Display 1 From the Traffic Screen turn the cursor on highlight the current mode and use the small PUSH CRSR knob to cycle through the options 2 With each turn the display changes to display the traffic in the selected display range ABV look up...

Page 357: ...threat exists SkyWatch calculates the range altitude bearing and closure rate of all transponder equipped aircraft with the 6 nautical mile range When SkyWatch detects an intruder aircraft within 0 55 nautical mile horizontal distance and a 800 ft relative altitude or detects an intruder aircraft is on a course that will intercept the SkyWatch airplane s course within 20 seconds non altitude repor...

Page 358: ...led on the airplane exterior above the cabin The system also utilizes inputs from the altitude encoder the aircraft heading system gyro slaving amplifier and a speed switch plumbed into the pitot system Electrical power for system operation is 28 vdc supplied through the 5 amp SKYWATCH Circuit Breaker on the Avionics Non Essential bus Note Refer to the L 3 Avionics Systems SkyWatch Pilot s Guide P...

Page 359: ...ements The information contained herein supplements or supersedes that in the basic manual and approved supplements only in those areas indicated 3 Compliance with the limitations contained in the basic manual and approved supplements is mandatory 4 Foreign operating rules and any references to such rules in the basic manual and approved supplements are not applicable in Canada The aircraft must b...

Page 360: ...167 6 169 8 172 0 174 1 80 176 4 178 6 180 8 183 0 185 2 187 4 189 6 191 8 194 0 196 2 90 198 4 200 6 202 8 205 0 207 2 209 4 211 6 213 9 216 0 218 3 100 220 5 222 7 224 9 227 1 229 3 231 5 233 7 235 9 238 1 240 3 lb 0 1 2 3 4 5 6 7 8 9 kg kg kg kg kg kg kg kg kg kg 0 0 0 0 5 0 9 1 4 1 8 2 3 2 7 3 2 3 6 4 1 10 4 5 5 0 5 4 5 9 6 4 6 8 7 3 7 7 8 2 8 6 20 9 1 9 5 10 0 10 4 10 9 11 3 11 8 12 2 12 7 13...

Page 361: ...Kilograms x 2 205 Pounds Pounds x 0 454 Kilograms SR20_FM09_1510 KILOGRAMS POUNDS Units x 10 100 etc 220 210 200 190 180 170 160 150 140 130 120 110 100 90 80 70 60 50 40 30 20 10 0 100 95 90 85 80 75 70 65 60 55 50 45 40 35 30 25 20 15 10 5 0 Figure 1 Sheet 2 of 2 Original 10 10 01 ...

Page 362: ...8 246 1 249 3 252 6 255 9 259 2 80 262 5 265 8 269 0 272 3 275 6 278 9 282 2 285 4 288 7 292 0 90 295 3 298 6 301 8 305 1 308 4 311 7 315 0 318 2 321 5 324 8 100 328 1 331 4 334 6 337 9 341 2 344 5 347 8 351 0 354 3 357 6 Ft 0 1 2 3 4 5 6 7 8 9 m m m m m m m m m m 0 0 0 0 3 0 6 0 9 1 2 1 5 1 8 2 1 2 4 2 7 10 3 0 3 4 3 6 4 0 4 3 4 6 4 9 5 2 5 5 5 8 20 6 1 6 4 6 7 7 0 7 3 7 6 7 9 8 2 8 5 8 8 30 9 1 ...

Page 363: ...ength Conversion Metres x 3 281 Feet Feet x 0 305 Metres FEET SR20_FM09_1511 Units x 10 100 etc 0 0 20 40 60 80 100 120 140 160 180 200 220 240 260 280 300 320 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 METRES Figure 2 Sheet 2 of 4 Original 10 10 01 ...

Page 364: ...1 10 80 31 50 31 89 32 28 32 68 33 07 33 47 33 86 34 25 34 65 35 04 90 35 43 35 83 36 22 36 61 37 01 37 40 37 80 38 19 38 58 38 98 100 39 37 39 76 40 15 40 55 40 95 41 34 41 73 42 13 42 52 42 91 in 0 1 2 3 4 5 6 7 8 9 cm cm cm cm cm cm cm cm cm cm 0 0 0 2 5 5 1 7 6 10 2 12 7 15 2 17 8 20 3 22 9 10 25 4 27 9 30 5 33 0 35 6 38 1 40 6 43 2 45 7 48 3 20 50 8 53 3 55 9 58 4 61 0 63 5 66 0 68 6 71 1 73 ...

Page 365: ...ion Centimetres x 0 394 Inches Inches x 2 54 Centimeters SR20_FM09_1989 Units x 10 100 etc 0 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 INCHES CENTIMETERS Figure 2 Sheet 4 of 4 Original 10 10 01 ...

Page 366: ...Miles Nautical Miles x 1 852 Kilometers Kilometers x 0 54 Nautical Miles SR20_FM09_1990 Units x 10 100 etc 0 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 105 110 115 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 STATUTE MILES NAUTICAL MILES 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 0 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 K...

Page 367: ...4 49 56 69 16 4 39 18 64 147 48 54 65 14 6 43 19 66 151 47 52 62 13 8 46 20 68 154 46 50 58 12 10 50 21 70 158 44 48 54 11 12 54 22 72 162 43 46 51 10 14 57 23 74 165 42 44 47 9 16 61 24 76 169 41 42 44 8 18 64 26 78 172 40 40 40 7 20 68 27 80 176 39 38 36 6 22 72 28 82 180 38 36 33 4 24 75 29 84 183 37 34 29 3 26 79 30 86 187 36 32 26 2 28 82 31 88 190 34 30 22 1 30 86 32 90 194 33 28 18 0 32 90 ...

Page 368: ...48 18 70 18 92 19 14 19 36 19 58 90 19 80 20 02 20 24 20 46 20 68 20 90 21 12 21 34 21 56 21 78 100 22 00 22 22 22 44 22 66 22 88 23 10 23 32 23 54 23 76 23 98 Gal 0 1 2 3 4 5 6 7 8 9 litres litres litres litres litres litres litres litres litres litres 0 0 0 4 6 9 1 13 6 18 2 22 7 27 3 31 8 36 4 40 9 10 45 5 50 0 54 55 59 1 63 6 68 2 72 7 77 3 81 8 86 4 20 90 9 95 5 100 0 104 6 109 1 113 6 118 2 ...

Page 369: ... 200 220 240 260 280 300 320 340 360 380 400 420 440 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 IMPERIAL GALLONS LITRES 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 105 110 115 120 0 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 20 40 60 80 100 120 140 160 180 200 220 240 260 280 300 320...

Page 370: ... x 1 58 Pounds Pounds x 0 633 Litres SR20_FM09_1513 0 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 POUNDS LITRES 0 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 105 110 115 120 125 130 135 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 LITRES KILOGRAMS Units x 10 100 etc Original 10 10 01 ...

Page 371: ...ollow arrow and multiply backtrack the arrow and divide Bear in mind that the figures are approximations for quick reference but with enough accuracy to eliminate gross errors and dead stick landings to abandoned airfields SR20_FM09_1514 1 58 6 0 7 2 0 72 2 72 3 27 2 2 1 2 3 8 4 5 IMPERIAL GALLONS KILOGRAMS U S GALLONS POUNDS AV GAS LITRES SPECIFIC GRAVITY 0 72 Figure 7 Original 10 10 01 ...

Page 372: ...14 of 14 P N 11934 S17 Section 9 Cirrus Design Supplements SR20 Original 10 10 01 Intentionally Left Blank ...

Page 373: ...1268 and subsequent this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Note This POH Supplement Revision dated 12 07 04 supersedes an...

Page 374: ...pplements SR20 Figure 1 SR20_FM09_1515 L R ST HD TRK ALT RDY DN TRIM UP 2 MIN TURN COORDINATOR HI LO C S I D P A D L O H H S U P N O I T A M R O F N I H C T I P O N L R B A GPSS HDG TURN COORDINATOR GPSS SWITCH System 30 Autopilot Revision 1 12 07 04 ...

Page 375: ... Turn Command NAV LOC GPS tracking HI and LO sensitivity Altitude Hold A separate GPSS converter provides GPS roll steering to the autopilot A GPSS HDG button allows the operator to switch between HDG and Roll Steering modes In the HDG mode the autopilot responds to the HDG bug on the HSI In the GPSS mode the autopilot responds to roll steering inputs from the GPS navigator Refer to S TEC System T...

Page 376: ...ng 4 Flaps must be set to 50 for autopilot operation in Altitude Hold at airspeeds below 95 KIAS 5 Flap deflection is limited to 50 during autopilot operations 6 The autopilot must be disconnected in moderate or severe turbulence 7 The autopilot must be disengaged no later than 100 feet below the Minimum Descent Altitude 8 Minimum engage height for the autopilot is 400 ft AGL 9 Minimum speed with ...

Page 377: ...he pitch ALT mode Exercise caution when examining these functions after a malfunction The autopilot may be disconnected by 1 Pressing and holding the Mode Selector Knob on the Turn Coordinator for approximately 2 seconds 2 Pressing the A P DISC Trim switch on either control yoke handle 3 Pulling the AUTOPILOT circuit breaker on the Essential Bus Altitude lost during a roll axis autopilot malfuncti...

Page 378: ... Selector and note that ST Stabilizer light illuminates b Then rotate Mode Selector Knob left then right Note that control yokes follow movement of knob 4 Heading Mode TEST a Center the HDG bug under the lubber line on the HSI b Momentarily depress Autopilot Mode Selector Note that HD Heading light illuminates c Then rotate HDG knob on the HSI to the left then right Note that control yokes follow ...

Page 379: ...ut 7 Radio Check a Turn on NAV1 radio with a valid NAV signal and select VLOC for display on the HSI b Use Autopilot Mode Selector to engage TRK LO mode and move OBS so that VOR deviation needle moves left or right Note that control yokes follow direction of needle movement c Use Autopilot Mode Selector to engage TRK HI mode and move OBS so that VOR deviation needle moves left or right Note that c...

Page 380: ...ed to setup level or turning flight Heading Mode 1 Begin by selecting a heading on the HSI within 10 of the current airplane heading 2 Use Autopilot Mode Selector to select HD Heading mode The HD light will come on and the airplane will turn toward the selected heading 3 Use the HSI HDG knob to make heading changes as desired Altitude Hold Mode 1 Manually fly the airplane to the desired altitude a...

Page 381: ...must be within 5 of the desired course when TRK is selected If airplane is more than 5 off the selected course the autopilot will turn the airplane towards the course but may not capture and track it 2 Use Autopilot Mode Selector to select TRK HI mode for GPS approach and cross country tracking GPS Tracking and GPS Approach With GPSS Note GPSS can be used for enroute navigation or GPS approaches G...

Page 382: ...e and ground speed signals are not being received or is not valid If GPSS begins to flash the airplane will go wings level in 0 5 to 2 0 seconds At this time the pilot can either enter a valid GPS waypoint or press and release the GPSS HDG switch to return the autopilot to the HD Heading mode GPS Approach Procedures With GPSS 1 Use Autopilot Mode Selector to select HD mode The HD light will come o...

Page 383: ...th airplane on the suggested heading to the waypoint Note The airplane must be within 5 of the desired course when TRK is selected If airplane is more than 5 off the selected course the autopilot will turn the airplane towards the course but may not capture and track it 2 Use Autopilot Mode Selector to select TRK HI mode for approach or TRK HI or LO for cross country tracking Section 5 Performance...

Page 384: ...urn Coordinator instrument dimming is controlled through the INST light dimmer on the bolster switch panel The system also incorporates a GPSS GPS Steering converter and switch to apply roll steering commands from GPS1 to the autopilot The GPSS function consists of a GPSS HDG switch a GPSS converter box and associated wiring During normal flight operations the system can be switched from heading t...

Page 385: ...ob on the HSI if the GPSS HDG switch is in the HDG mode When HDG mode is selected the autopilot will turn the airplane to the selected heading and then follow the selected heading Subsequent heading changes can be made using the HDG knob on the HSI For smoothest transition to HDG it is recommended that the airplane be aligned to within 10 of the selected heading before engaging HDG TRK Track Mode ...

Page 386: ... the GPSS HDG switch located next to the system annunciators on the instrument panel Refer to Figure 1 for an illustration of the switch HDG When HDG is selected on the GPSS HDG switch the green light below the HDG label will illuminate In this mode the autopilot is coupled to the HSI heading error outputs and the autopilot will respond to inputs made on the HSI heading HDG or course OBS controls ...

Page 387: ... Design SR20 serials 1268 and subsequent this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Note This POH Supplement Revision dated R...

Page 388: ...intercept GPS Steering GPSS Altitude Pre select Hold and Command Altitude display and baro correction Altitude and Decision Height DH alert and Vertical Speed Hold and Command Refer to S Tec System Fifty Five X Autopilot Pilot s Operating Handbook POH P N 87109 dated 8 November 2000 or later revision for full operational procedures and description of implemented modes The System 55X POH also conta...

Page 389: ...3 The autopilot must be disengaged for missed approach go around and balked landing 4 Flaps must be set to 50 for autopilot operation in Altitude Hold at airspeeds below 95 KIAS 5 Flap deflection is limited to 50 during autopilot operations 6 The autopilot must be disconnected in moderate or severe turbulence 7 Minimum engage height for the autopilot is 400 ft AGL WARNING Autopilot may not be able...

Page 390: ...tside of the outer marker g The intercept angle shall be no greater than a 45 degree intercept h The ILS is flown at normal approach speeds and within any STC or TC speed constraints and as defined in this flight manual i The flaps should be extended in the approach configuration prior to the Outer Marker No further changes in the flap configuration should be made throughout the autopilot coupled ...

Page 391: ...P N 11934 S20 5 of 24 Cirrus Design Section 9 SR20 Supplements SR20_FM09_1502A Figure 1 System 55X Altitude Selector Alerter Autopilot Computer Revision 3 07 18 05 ...

Page 392: ...ilot may be disconnected by 1 Pressing the A P DISC Trim switch on the control yoke handle 2 Pulling the AUTOPILOT circuit breaker on Essential Bus Altitude lost during a roll axis autopilot malfunction and recovery Altitude lost during a pitch axis autopilot malfunction and recovery Flight Phase Bank Angle Altitude Loss Climb 30 None Cruise 55 100 ft Descent 55 120 ft Maneuvering 10 None Approach...

Page 393: ...Check power to turn coordinator Flashing NAV REV or APR Off navigation course by 50 needle deviation or more Use HDG mode until problem is identified Crosscheck raw NAV data compass heading and radio operation Flashing NAV REV or APR with steady FAIL Invalid radio navigation signal Check Nav radio for proper reception Use HDG mode until problem is corrected Flashing VS Excessive vertical speed err...

Page 394: ...essing the autopilot VS button WARNING The pilot must properly monitor and control the engine power to avoid stalling the airplane in autopilot altitude hold or vertical speed modes Note Any coupled Altitude Selector Alerter mode can be disabled by disconnecting the autopilot Autopilot and Altitude Selector Pre Flight Tests 1 Battery Master Switch ON 2 Transponder ON 3 Avionics Power Switch ON Not...

Page 395: ...en the ALT SEL setting on the altitude selector is within 100 feet of indicated altitude on altimeter Autopilot ALT mode should remain illuminated indicating autopilot altitude hold is engaged If ALT engagement does not occur within 100 feet of indicated altitude readjust BARO setting on altitude selector 5 Autopilot Tests a Heading Mode TEST 1 Center the HDG bug under the lubber line on the HSI 2...

Page 396: ...deviation needle moves left or right Note that control yokes follow direction of needle movement f Autopilot Disconnect Tests 1 Press Pilot A P DISC Trim Switch control yoke Note that the autopilot disengages Move control yoke to confirm that pitch and roll control is free with no control restriction or binding 2 Repeat step using Copilot A P DISC Trim Switch In Flight Procedures 1 Autopilot RDY L...

Page 397: ...the present altitude Note Manually flying the airplane off the selected altitude will not disengage altitude hold and the autopilot will command a pitch change to recapture the altitude when the control input is released 4 Altitude can be synchronized to another altitude by rotating the VS knob on the programmer computer Clockwise rotation will increase and counterclockwise rotation will decrease ...

Page 398: ...etween actual vertical speed and the selected vertical speed usually in climb The pilot should adjust power or reduce the commanded vertical speed as appropriate to remove the error Altitude Pre Select The altitude selector may be used to set up an altitude and vertical speed for intercept and capture The altitude can be above or below the current altitude and the vertical speed chosen should be a...

Page 399: ... Positive vertical speed indicates climb and negative vertical speeds indicates descent Any vertical speed from 1 100 FPM to 16 1600 FPM is selectable Note If an altitude is selected that requires an opposite vertical speed from that selected the system will automatically select the correct sign for climb for descent and a vertical speed of 500 FPM 6 After takeoff press and hold the VS button and ...

Page 400: ...ate the selector knob CW to increase setting or CCW to decrease setting Only three digits are displayed for millibars for a BARO setting of 952 8 mb the display will indicate 952 and for a BARO setting of 1003 8 mb the display will read 003 For inches Hg the 1 100 decimal position will not be selectable or displayed for example a 29 92 inch Hg setting is input and displayed as 29 9 4 Press DTA aga...

Page 401: ...and the ALR annunciator will flash again as the airplane approaches within 300 feet of the selected altitude If the airplane s altitude deviates 300 feet from the selected altitude the chime will sound and the ALR annunciator will flash to indicate the condition 2 To disable ALR press the altitude selector ALR button again The ALR annunciator will go out GPS Tracking and GPS Approach 1 Begin with ...

Page 402: ...e is reduced to 15 standard rate 4 For increased sensitivity during GPS approach or if desired for enroute tracking press the APR button on the autopilot programmer computer The NAV GPSS and APR annunciators will be illuminated Use HDG to accomplish a procedure turn Engage GPSS again to complete the approach VOR Tracking and VOR LOC Approach 1 Begin with a reliable VOR or VOR LOC signal selected o...

Page 403: ... annunciator will go out and the system will track the glideslope Note If approach vectoring locates the airplane too near the glideslope at the intercept point usually the outer marker the GS mode can be manually armed by pressing the ALT button once Once capture is achieved GS annunciator will come on and ALT annunciator will go out Section 5 Performance There is no change to the airplane perfor...

Page 404: ...then follow the selected vertical speed until the selected altitude is reached Then the altitude selector will signal the autopilot to hold the selected altitude The altitude selector alerter receives uncorrected altitude data from the same altitude encoder used by the transponder In addition to the preselect functions the altitude selector provides altitude alert decision height and altitude read...

Page 405: ...n Indicator GPSS converts this information and sends this heading error directly to the autopilot In the GPSS mode the converter receives ground speed and bank angle digital signals that are calculated and converted to a commanded turn rate The turn rate is then scaled and converted to a DC heading error signal that is compatible with the autopilot The end result is an autopilot that can be direct...

Page 406: ...ill not engage if an autopilot roll mode is not engaged Altitude correction for enroute barometric pressure changes may be made by rotation of the VS knob on the autopilot programmer computer Clockwise rotation will increase and counterclockwise rotation will decrease altitude 20 feet for each click The maximum adjustment is 360 feet Adjustments greater than 360 feet can be made by selecting VS mo...

Page 407: ...ncoder are operating and then both the autopilot ALT and VS modes are selected The altitude selector also provides a vertical speed signal to the autopilot pitch computer that is proportional to the amplitude and direction of the selected or computed vertical speed This signal is not used by the autopilot until the autopilot VS mode is engaged When VS is engaged the autopilot compares the selected...

Page 408: ...n this mode the autopilot will hold the last vertical speed selected Note It is not necessary to enter the DTA mode to change the vertical speed if vertical speed is coupled to the autopilot If this is the case vertical speed changes can be made by rotating the input knob as required to obtain the new vertical speed While in this mode pressing DTA a second time will toggle the system to operate mo...

Page 409: ...tor will command the autopilot to engage altitude hold Readout When the ALT button is pressed in the operate mode the SEL annunciator will go out and the display will show the baro corrected encoder altitude Repeated pushes of the ALT button will alternately display baro corrected encoder altitude and pre selected altitude ALR Alert Mode The ALR button enables the altitude alert system in conjunct...

Page 410: ... go out Repeated activation of the DH button alternately activates and deactivates the DH mode VS Vertical Speed At initial start up after self test pressing the Altitude Selector Alerter VS button enables vertical speed selector mode The initial vertical speed will be set at 2 indicating a climb at 200 feet per minute Rotating the selector input knob will change the selected vertical speed in 100...

Page 411: ...quent this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement either adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Note This POH Supplement Revision dated Revision 1 05 25 05 supersede...

Page 412: ...GNS 430 GPS Navigator may be installed in single or dual installations If one GNS 430 is installed it will be designated GPS 1 and a GARMIN GNC 420 GPS Navigator will be installed as GPS 2 Refer to applicable supplements for descriptions of these units If two GARMIN GNS 430 Navigators are installed the upper unit will be designated GPS 1 and the lower unit will be designated GPS 2 In these install...

Page 413: ...n the use of the GPS Navigator The software status stated in the pilot s guide must match that displayed on the equipment 3 The Navigator must utilize software version 2 XX where X is a digit 0 9 4 IFR enroute and terminal navigation is prohibited unless the pilot verifies the currency of the database or verifies each selected waypoint for accuracy by reference to current approved data 5 GPS instr...

Page 414: ... use GPS navigation position must be verified every 15 minutes using another IFR approved navigation system Section 4 Normal Procedures The GARMIN GNS 430 Navigator is available in single or dual installations Operating procedures for each unit of a dual installation are identical Refer to the GNS 430 Integration paragraphs in this supplement for integration differences when single and dual units ...

Page 415: ...lay on the CDI each time the button is pressed The CDI source is indicated by illumination of the GPS or VLOC annunciation in the lower left corner of the GNS 430 display Note The CDI displays course deviation from a VOR Localizer LOC or Glideslope G S when VLOC is selected for display and displays GPS track deviation when GPS is the selected navigation source b GPS 2 in this configuration is a GA...

Page 416: ...he lower GNS 430 unit a GPS 1 in this configuration is a GARMIN GNS 430 GPS Navigator with VHF Com interfaced with the HSI and MFD Pressing the alternate action CDI push button on GPS 1 alternately selects GPS or NAV for display in the HSI and MFD each time the button is depressed The HSI source is indicated by illumination of the GPS or VLOC annunciation in the lower left corner of the GNS 430 di...

Page 417: ...tructions refer to the Garmin GNS 430 Pilot s Guide and Reference P N 190 00140 00 Revision F dated July 2000 or later appropriate revision The following paragraphs describe a single GARMIN GNS 430 unit and its functions In the event a second GNS 430 is installed the second unit will function as described below except that the GPS navigator is designated GPS 2 the NAV receiver is designated NAV 2 ...

Page 418: ...S Navigator provides backup and is approved for VFR use only If the second GPS is also a Garmin 430 it will be coupled to the CDI and is also approved for IFR use The Garmin GPS 430 is capable of providing IFR enroute terminal and approach navigation with position accuracies better than 15 meters The system utilizes the Global Positioning System GPS satellite network to derive the airplane s posit...

Page 419: ...er Switch on the bolster switch panel and supplied through the 5 amp GPS 1 circuit breaker on the Avionics Essential Bus The airplane is equipped with a Garmin GNS 430 integrated GPS Navigator Navigation NAV receiver with VHF Omnirange Localizer VOR LOC and Glideslope receiver Communication COM Transceiver The GNS 430 includes a digitally tuned integrated VHF communications COM transceiver The tra...

Page 420: ... 11934 S22 Section 9 Cirrus Design Supplements SR20 operating is controlled through the Avionics Master Switch and supplied through the 7 5 amp COM1 circuit breaker on the Avionics Essential Bus Revision 1 05 25 05 ...

Page 421: ...ent this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement either adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Note This POH Supplement Revision dated Revision 1 05 25 05 supersedes ...

Page 422: ...ce the altitude calculation Provided the GPS Navigator is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy specifications of VFR IFR enroute terminal and instrument approach GPS operations that is enroute terminal and instrument approach within the U S National Airspace System North Atlantic Minimum Navigation Performance Specification M...

Page 423: ... approach procedures that are retrieved from the Navigator s NavData database The database must incorporate the current update cycle a Instrument approaches must be conducted in the approach mode and RAIM must be available at the Final Approach Fix b Accomplishment of ILS LOC LOC BC LDA SDF and MLS approaches are not authorized in GPS mode c When an alternate airport is required by the applicable ...

Page 424: ...in the GARMIN GNC 420 Pilot s Guide and Reference P N 190 00140 20 Revision B dated August 2002 or later appropriate revision Activate GPS 1 Battery Master Switch ON 2 Avionics Power Switch ON 3 Navigator Com Power Switch Rotate ON The Navigator will display a welcome page while the self test is in progress When the self test is successfully completed the Navigator asks for NavData database confir...

Page 425: ...the GARMIN GNC 420 Pilot s Guide and Reference P N 190 00140 20 Revision B dated August 2002 or later appropriate revision GNC 420 Integrated GPS COM System This airplane is equipped with a GNC 420 integrated GPS navigator and COM transceiver The GPS navigator consists of a GPS receiver a navigation computer and a Jeppeson NavData database all contained in the GNC 420 control unit mounted in the c...

Page 426: ...onics Non Essential Bus The Jeppesen Navigation Database provides access to data on Airports Approaches Standard Instrument Departures SIDs Standard Terminal Arrivals STARs VORs NDBs Intersections Minimum Safe Altitudes Controlled Airspace Advisories and Frequencies North American and International databases are available Database information is provided on a card that can be inserted into the car...

Page 427: ... display Auto tuning can be accomplished by entering a frequency from a menu The COM 2 antenna is located below the cabin on the airplane centerline 28 VDC for transceiver operating is controlled through the Avionics Master Switch and supplied through the 7 5 amp COM2 circuit breaker on the Avionics Non Essential Bus Revision 1 05 25 05 ...

Page 428: ...8 of 8 P N 11934 S23 Section 9 Cirrus Design Supplements SR20 Revision 1 05 25 05 Intentionally Left Blank ...

Page 429: ...vigation Display is installed in the Cirrus Design SR20 serials 1268 and subsequent this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handboo...

Page 430: ...308 navigation display This SN3308 is a three inch instrument installed in the pilot s instrument panel which performs the functions of a standard HSI combined with a two pointer RMI The instrument also displays a moving map marker beacon WX500 stormscope data and GPS data SR20_FM09_1504 SN3308 Navigation Display Original 01 07 03 ...

Page 431: ...rative the compass rose color will change from white to amber and the flux gate will provide the heading The heading display will respond much more slowly than normal 3 If the fluxgate fails the SN3308 Navigation Display compass rose color will change from white to amber and the heading numbers will disappear The display can be used to determine relative heading for turns however the magnetic comp...

Page 432: ...ation Display 1 Avionics Power Switch OFF Section 5 Performance No change Section 6 Weight Balance No change Section 7 Systems Description Sandel SN3308 Navigation Display Note For a full description of the Sandel SN3308 Navigation Display refer to the Sandel Avionics SN3308 Navigation Display Pilot s Guide SPN 90106 PG C or later revision This airplane is equipped with a Sandel SN3308 Navigation ...

Page 433: ...Redundant power sources provide 28 VDC for system operation Power is supplied through the 5 amp HSI PFD 1 circuit breaker on the Essential Bus and the 5 amp HSI PFD 2 circuit breaker on Main Bus 2 Either circuit is capable of powering the Navigation Display Original 01 07 03 ...

Page 434: ...6 of 6 P N 11934 S24 Section 9 Cirrus Design Supplements SR20 Original 01 07 03 Intentionally Left Blank ...

Page 435: ...esign drawing 70102 this POH Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Note This POH Supplement Revision dated 12 07 04 supersede...

Page 436: ...ization Kit cowl inlet covers airflow restrictors are installed Placards On forward side of each Cowl Inlet Cover On aft side of each Cowl Inlet Cover Serials 1005 through 1147 before Service Bulletin SB 20 71 03 Serials 1148 through 1422 and Serials 1005 through 1147 after Service Bulletin SB 20 71 03 Section 3 Emergency Procedures No Change REMOVE WHEN OUTSIDE TEMP IS ABOVE 32 F FOR USE ON A C W...

Page 437: ...trictor See Figure 1 1 Loosen screw securing latch plate to inlet cover and slide latch plate inboard 2 Position inlet cover in inlet 3 Slide latch plate outward behind edge of cowl and tighten screw 4 Install inboard screw securing inlet cover to cowl 5 Repeat procedure for opposite cowl inlet cover Revision 1 12 07 04 ...

Page 438: ...9 Cirrus Design Supplements SR20 3 2 1 3 Serials 1423 and subsequent Serials 1005 through 1422 1 2 3 3 4 LEGEND 1 Cowl Inlet Cover 2 Latch Plate 3 Screw 4 Wellnut SR20_FM09_1516B Figure 1 Cowl Inlet Installation Revision 1 12 07 04 ...

Page 439: ... CHT and Oil Temperatures above the red line The Winterization Kit consists of two cowl inlet covers that can be easily installed in the inlets to restrict airflow into the engine compartment When the ambient temperature is below 32 F 0 C installing the inlet covers allows the engine to reach and maintain CHT Cylinder Head Temperatures and Oil Temperatures well into the green arc The covers are ea...

Page 440: ...6 of 6 P N 11934 S25 Section 9 Cirrus Design Supplements SR20 Revision 1 12 07 04 Intentionally Left Blank ...

Page 441: ...d subsequent this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Note This POH Supplement Revision dated Revision 2 07 18 05 supersede...

Page 442: ...ivity Altitude Hold and Command Vertical Speed Hold and Command GPS Steering GPSS for smoother turns onto a course or during course tracking Refer to S Tec System Fifty Five SR Autopilot Pilot s Operating Handbook POH P N 87127 dated 01 September 2003 or later revision for full operational procedures and description of implemented modes Note The SR20 implementation of the System 55SR Autopilot doe...

Page 443: ...ept capture and tracking the following limitations apply a The autopilot must be disengaged no later than 100 feet below the Minimum Descent Altitude b The autopilot must be disconnect during approach if course deviation exceeds 50 The approach should only be continued by hand flying the airplane c The autopilot must be disengaged at the decision height d 12 knot maximum crosswind component betwee...

Page 444: ...or to the Outer Marker No further changes in the flap configuration should be made throughout the autopilot coupled approach 10 The S Tec System 55SR Autopilot Pilot s Operating Handbook POH P N 87127 dated 01 September 2003 or later must be carried in the airplane and available to the pilot while in flight Revision 2 07 18 05 ...

Page 445: ...sign Section 9 SR20 Supplements SR20_FM09_1996 NAV HDG REV APR ALT VS S TEC FIFTY FIVE SR HDG NAV APR REV TRIM ALT GS VS R D Y C W S F L A I G S P S VS x 100 I N C R D E C R Figure 1 System Fifty Five SR Autopilot Revision 2 07 18 05 ...

Page 446: ...autopilot may be disconnected by 1 Pressing the A P DISC Trim switch on the control yoke handle 2 Pulling the AUTOPILOT circuit breaker on Essential Bus Altitude lost during a roll axis autopilot malfunction and recovery Altitude lost during a pitch axis autopilot malfunction and recovery Flight Phase Bank Angle Altitude Loss Climb 30 None Cruise 55 100 ft Descent 55 120 ft Maneuvering 10 None App...

Page 447: ...t disconnect All annunciations except RDY are cleared None Flashing RDY with audible tone then goes out Turn coordinator gyro speed low Autopilot disengages and cannot be re engaged Check power to turn coordinator Flashing NAV REV or APR Off navigation course by 50 needle deviation or more Use HDG mode until problem is identified Crosscheck raw NAV data compass heading and radio operation Flashing...

Page 448: ...inator gyro has reached operational RPM the RDY annunciator will come on 4 Autopilot Tests a Heading Mode TEST 1 Momentarily press HDG button on autopilot Mode Selector Note that HDG light illuminates 2 Select and rotate the HDG bug knob on the PFD to the left then right Note that control yokes follow movement of knob b Activate a GPS flight plan or waypoint on the GPS navigator GPS 1 c Press and ...

Page 449: ...at VOR deviation needle moves left or right Note that control yokes follow direction of needle movement h Autopilot Disconnect Tests 1 Press Pilot A P DISC Trim Switch control yoke Note that the autopilot disengages Move control yoke to confirm that pitch and roll control is free with no control restriction or binding 2 Repeat step using Copilot A P DISC Trim Switch In Flight Procedures 1 Autopilo...

Page 450: ...rogrammer computer The ALT annunciator will illuminate indicating that the mode is engaged and the autopilot will hold the present altitude Note Manually flying the airplane off the selected altitude will not disengage altitude hold and the autopilot will command a pitch change to recapture the altitude when the control input is released 4 Altitude can be synchronized to another altitude by rotati...

Page 451: ...s value indicates climb and a negative or minus value indicates descent 4 Vertical speed can be adjusted by rotating the VS knob on the programmer computer Clockwise rotation increases and counterclockwise rotation decreases rate of climb or descent 100 FPM for each click The maximum adjustment is 1600 FPM Note A flashing VS mode annunciator indicates excessive error between actual vertical speed ...

Page 452: ...eviation needle centered the course tracking program is activated The system will remain at maximum sensitivity for approximately 15 seconds while the wind correction angle is established The maximum turn rate is then reduced to 45 standard rate Approximately 60 seconds later the maximum turn rate is reduced to 25 standard rate 4 For increased sensitivity during GPS approach or if desired for enro...

Page 453: ...d with an S Tec System 55SR two axis Automatic Flight Control System Autopilot The autopilot programmer computer is installed in the center console radio stack The autopilot roll axis uses an inclined gyro in the turn coordinator case as the primary turn and roll rate sensor In addition to the turn coordinator instrument the roll axis computer receives signals from the PFD and the NAV GPS radio Th...

Page 454: ...on with the NAV mode to set up a pilot selected intercept angle to a course GPSS GPS Steering Pressing NAV twice will cause the autopilot to go to GPSS for smoother tracking and transitions When GPSS is selected the autopilot can be switched between heading and GPSS modes of operation In the heading mode the converter receives a heading error signal from the heading bug on the Horizontal Situation...

Page 455: ...t for each click The maximum adjustment is 360 feet Adjustments greater than 360 feet can be made by selecting VS mode and flying the airplane to the new altitude and then re engaging ALT mode VS Vertical Speed Mode When VS is selected the autopilot will synchronize to and hold the vertical speed at the time the mode was selected Altitude hold will not engage if an autopilot roll mode is not engag...

Page 456: ...16 of 16 P N 11934 S27 Section 9 Cirrus Design Supplements SR20 Revision 2 07 18 05 Intentionally Left Blank ...

Page 457: ...GTX 330 Transponder is installed in the Cirrus Design SR20 this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Original 07 03 04 ...

Page 458: ...RSR ALT 1 2 3 4 5 6 7 8 9 10 1 Identification Key 2 Mode Selector Keys a OFF b STBY Standby c ON d ALT 3 Display Window 4 FUNC Function Key 5 CRSR Cursor 6 CLR Clear Key 7 START STOP Key 8 Photocell 9 VFR Key 10 Selector Keys a 0 7 Code Selection b 8 9 Display Brightness Contrast ALT 1200 FLIGHT TIME 01 23 20 Garmin GTX 330 Transponder Original 07 03 04 ...

Page 459: ... may result in reduced range Range can be improved by climbing to a higher altitude After Engine Start 1 Avionics Power Switch ON The transponder will turn on in the same mode of operation selected at the last power down and will display the last entered identification code Before Takeoff 1 Transponder Mode Selector Keys ALT If the transponder is in STBY or GND mode it will automatically switch to...

Page 460: ...cription of the unit For a detailed description of the GTX 330 refer to GARMIN GTX 330 Mode S Transponder Pilots Guide p n 190 00207 00 Revision A Sept 2002 or later revision The Garmin GTX 330 transponder system consists of an integrated receiver transmitter control unit an antenna and an altitude digitizer In addition to displaying the code reply symbol and mode of operation the GTX 330 displays...

Page 461: ...unted on the underside of the fuselage just aft of the firewall 28 VDC for transponder operation is controlled through the Avionics Master Switch on the bolster switch panel 28 VDC for receiver transmitter and altitude encoder operation is supplied through the 2 amp ENCODER XPONDER circuit breaker on the Avionics Non Essential Reply Light The reply light is the small reverse video R immediately be...

Page 462: ...l be selected The transponder will respond to interrogations with the unique aircraft address and standard pressure altitude 29 92 inches Hg Note ALT mode is automatically entered from STBY mode during takeoff ground roll as the groundspeed increases through 35 knots Code Selector Keys Code selection is accomplished by depressing the eight selector keys numbered 0 7 located immediately below the d...

Page 463: ...enterable Function Keys IDENT Key Pressing the IDENT button activates the Special Position Identification SPI pulse for approximately 18 seconds allowing ATC to identify your transponder return from other returns on the controller s scope The Reply annunciator in the display will illuminate during the SPI pulse Momentarily press the IDENT key when the controller requests SQUAWK IDENT VFR Key Press...

Page 464: ...at the airplane is climbing or descending FLIGHT TIME Displays the flight time The timer receives groundspeed from GPS1 Flight time starts when the groundspeed reaches 35 knots on takeoff and pauses when the groundspeed descends below 35 knots on landing ALT MONITOR Controlled by START STOP key Activates a voice alarm when altitude limit is exceeded COUNT UP TIMER The count up timer is controlled ...

Page 465: ...this supplement is to be used in conjunction with the basic AFM and supplements The information contained herein supplements or supersedes that in the basic manual and approved supplements only in those areas indicated 3 Compliance with the limitations contained in the basic manual and approved supplements is mandatory 4 Foreign operating rules and any references to such rules in the basic manual ...

Page 466: ...erating Handbook Amend Propeller limitation to read as follows Hartzell Propeller Type Constant Speed Three Blade Propeller Model Number PHC J3YF 1MF F7392 1 Diameter 74 0 72 5 Minimum Model Number PHC J3YF 1RF F7392 1 Diameter 74 0 72 5 Minimum Section 3 Emergency Procedures No Change Section 4 Normal Procedures No Change Section 5 Performance No Change Section 6 Weight Balance No Change Section ...

Page 467: ...P N 11934 S29 3 of 4 Cirrus Design Section 9 SR20 Supplements Section 8 Handling Servicing Maintenance No Change Section 9 Supplements No Change Section 10 Safety Information No Change Original 05 27 04 ...

Page 468: ...4 of 4 P N 11934 S29 Section 9 Cirrus Design Supplements SR20 Original 05 27 04 Intentionally Left Blank ...

Page 469: ...560 Terrain Awareness and Warning System is installed in the Cirrus Design SR20 this Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Or...

Page 470: ...kplate a Terrain Obstacle Database integral to the processor the Configuration Module integral to the system s wire harness and the TAWS annunciator panel mounted on the lower LH portion of the instrument panel The KGP 560 receives data from the GPS sensor Transponder Primary Flight Display and the Multifunction Display MFD Aural alerts are communicated to the pilot via the GMA 340 Audio Panel To ...

Page 471: ...ly vertical maneuvers are recommended responses to warnings and alerts unless operating in VMC or the pilot determines using all available information and instruments that a turn in addition to the vertical escape maneuver is the safest course of action During certain operations warning thresholds may be exceeded due to specific terrain or operating procedures During day VFR flight these warnings ...

Page 472: ...ESS 7 MFD Soft Keys SET to TAWS Response To Ground Proximity Warnings Aural PULL UP Warning Red TERR WARN Annunciation 1 Level the wings simultaneously adding full power 2 Increase pitch attitude to 15 degrees nose up 3 Adjust pitch attitude to ensure terrain clearance while respecting stall warning If flaps are extended retract flaps to the UP position 4 Continue climb at best angle of climb spee...

Page 473: ...crease pitch attitude to 15 degrees nose up 3 Adjust pitch attitude to ensure terrain clearance while respecting stall warning If flaps are extended retract flaps to the UP position 4 Continue climb at best angle of climb speed Vx until terrain clearance is assured Deactivate TAWS 1 SKYWATCH TAWS Circuit Breaker PULL or 2 Avionics Power Switch OFF Section 5 Performance No Change Section 6 Weight B...

Page 474: ...tion of the instrument panel The 560 GA EGPWS Processor is powered by 28 VDC through the 5 amp SKYWATCH TAWS circuit breaker on the Avionics Nonessential Bus For a additional system information refer to the KGP 560 860 EGPWS Pilot s Guide P N 006 18254 001 Revision 4 or later System Constraints If there is no terrain data in the database for a particular area then TAWS alerting is not available fo...

Page 475: ...ents GNS 430 GPS Avidyne PFD Transponder TAWS 5 AVIONICS NON ESSENTIAL BUS Configuration Module GMA 340 Audio Panel SR20_FM09_2031 Avidyne MFD KGP 560 Processor TAWS Annunciator Panel Figure 1 Honeywell KGP 560 TAWS Simplified Schematic Original 07 03 04 ...

Page 476: ... Display will remain functional with the message Warnings Inhibited displayed on the MFD When activated the switch will illuminate amber TERR INOP Indicates the TAWS inoperative When activated the LED will illuminate amber TERR CAUT Indicates a possible terrain or obstacle conflict within 40 60 seconds When activated the LED will illuminate amber TERR WARN Indicates a possible terrain or obstacle ...

Page 477: ...R All TAWS alerting functions inhibited TERR INOP AMBER Indicates TAWS inoperative TERR CAUT AMBER Possible terrain or obstacle conflict within 40 60 seconds TERR WARN RED Possible terrain or obstacle conflict within 30 seconds SELF TEST SR20_FM09_2033 TERR INHIBIT TERR INOP TERR CAUT TERR WARN TAWS Figure 2 TAWS Annunciator Panel Original 07 03 04 ...

Page 478: ...ure of the alert is presented in the MFD message bar Warning Alert Possible terrain or obstacle conflict within 30 seconds When triggered the terrain or obstacle that caused the alert is displayed in bright red In addition a message describing the nature of the alert is presented in the message bar When a caution or warning alert is active the display image surrounding the target is enlarged somew...

Page 479: ...nce for color coding for the Terrain Awareness Display Page and as an input to the TAWS Look Ahead algorithm Because it is derived from GPS Geometric Altitude may differ from corrected barometric altitude Therefore Geometric Altitude may be in error by as much as 100 ft and should not be used for navigation MSL G is presented solely to provide the pilot additional situational awareness regarding t...

Page 480: ...nated b The amber TERR INOP light should extinguish c The red TERR WARN light should be illuminated d An aural EGPWS SYSTEM OK is enunciated over cockpit speaker e The red TERR WARN light should extinguish f The amber TERR CAUT light should be illuminated g The amber TERR CAUT light should extinguish h A terrain self test pattern should appear on the MFD i The terrain self test should disappear af...

Page 481: ...e Instrumentation system is installed in the Cirrus Design SR20 this POH Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Original 10 12...

Page 482: ...Section 1 General EMax Engine Instrumentation provides the pilot with engine parameters depicted on simulated gauges and electrical system parameters located in a dedicated region within in the EX5000C MFD display Avidyne EMax Engine Instrumentation Original 10 12 05 ...

Page 483: ...ne gauges and provide data to the MFD for display Airplanes equipped with EMax Engine Instrumentation display all engine settings and parameters on a dedicated MFD engine monitor page The MFD also displays engine and fuel data in data blocks on the full screen moving map display In the event of an exceedence each out of limit parameter is highlighted on the screen for immediate attention The engin...

Page 484: ...Instruments system is powered by 28 VDC supplied through the 5 amp Engine Instruments breaker on the Main Bus 1 Refer to Avidyne FlightMax EX5000C Pilot s Guide P N 600 00108 000 Revision 03 or later for a more complete description of EMax Engine Instruments its operating modes and additional detailed operating procedures Original 10 12 05 ...

Page 485: ...ronic Approach Charts system is installed in the Cirrus Design SR20 this POH Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Original 1...

Page 486: ...cedure chart data on the EX5000C MFD If the chart is geo referenced an ownship symbol and flight plan legs can be overlaid on the chart to further enhance the pilot s situational awareness Most approach charts and airport diagrams are geo referenced most arrival departure and miscellaneous charts are not Avidyne CMax Electronic Approach Charts Original 10 12 05 ...

Page 487: ...re and data If no back up data is available contact Air Traffic Control for approach information Section 4 Normal Procedures Note Back up approach charts for CMax are not required However back up approach data for departure destination and alternate field is recommended Reference CMax Description in this supplement Section 7 System Description The CMax installation is entirely software dependant N...

Page 488: ...upplements SR20 Refer to Avidyne FlightMax EX5000C Pilot s Guide P N 600 00108 000 Revision 03 or later for a more complete description of CMax Approach Charts its operating modes and additional detailed operating procedures Original 10 12 05 ...

Page 489: ...er System system is installed in the Cirrus Design SR20 this POH Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Original 10 12 05 ...

Page 490: ... Figure 1 Section 1 General The XM Satellite Weather System enhances situational awareness by providing the pilot with real time graphical weather information depicted on the MAP page of the EX5000C MFD display XM Satellite Weather Overlay Original 10 12 05 ...

Page 491: ... in the following table Section 7 System Description The XM Satellite Weather System enhances situational awareness by providing the pilot with real time graphical weather information The XM antenna integrated with the COM1 antenna receives weather information from dual redundancy satellites This signal is sent to the XM receiver installed in the co pilot side of the instrument console which inter...

Page 492: ...m is powered by 28 VDC supplied through the 3 amp Weather Stormscope breaker on the Non Essential Bus Refer to Avidyne FlightMax EX5000C Pilot s Guide P N 600 00108 000 Revision 03 or later for a more complete description of XM Satellite Weather System its operating modes and additional detailed operating procedures Original 10 12 05 ...

Page 493: ...he Avidyne Flight Director is installed in the Cirrus Design SR20 this POH Supplement is applicable and must be inserted in the Supplements Section Section 9 of the Cirrus Design SR20 Pilot s Operating Handbook This document must be carried in the airplane at all times Information in this supplement adds to supersedes or deletes information in the basic SR20 Pilot s Operating Handbook Original 1 1...

Page 494: ...through providing a visual cue for the pilot to follow as indicated by the PFD s Flight Director Steering Command Bar Through turning or pitching the airplane as directed by the Steering Command Bar the pilot will follow the necessary course to arrive at a programmed destination The Avidyne system software version for this installation is 530 00159 XXX where X can be any digit from 0 to 9 Figure 1...

Page 495: ...r system replaces the flying W aircraft reference symbol on the PFD with the Flight Director Steering Command Bars and Wedge The system consists of two lighted push buttons installed on the upper LH side of the instrument panel and associated relays and wiring between the PFD and autopilot The remaining portion of the Flight Director system is entirely software dependant When a vertical mode of th...

Page 496: ...ter for a more complete description of the Flight Director its operating modes and additional detailed operating procedures No Annunciation Autopilot off or Autopilot not active in either roll or pitch control Green AP ON Annunciation Autopilot active in roll and or pitch control If Autopilot active in roll and pitch control AP annunciation appears on top edge of PFD and Flight Director Steering C...

Page 497: ...f Control 10 5 Landing Required in Terrain not Permitting a Safe Landing 10 5 Pilot Incapacitation 10 5 General Deployment Information 10 5 Deployment Speed 10 5 Deployment Altitude 10 6 Deployment Attitude 10 6 Landing Considerations 10 7 Emergency Landing Body Position 10 7 Door Position 10 7 Water Landings 10 8 Post Impact Fire 10 9 Ground Gusts 10 9 Taxiing Steering and Braking Practices 10 10...

Page 498: ...10 2 P N 11934 003 Section 10 Cirrus Design Safety Information SR20 Reissue A Intentionally Left Blank ...

Page 499: ... guides and data provided by manufacturers of equipment installed in this airplane You must operate the airplane in accordance with the applicable FAA operating rules and within the Limitations specified in Section 2 of this Handbook The Normal Procedures section of this handbook was designed to provide guidance for day to day operation of this airplane The procedures given are the result of fligh...

Page 500: ... when and how the CAPS will be used Deployment Scenarios This section describes possible scenarios in which the activation of the CAPS might be appropriate This list is not intended to be exclusive but merely illustrative of the type of circumstances when CAPS deployment could be the only means of saving the occupants of the aircraft Mid air Collision A mid air collision may render the airplane in...

Page 501: ...r no risk to the aircraft occupants However if the condition occurs over terrain thought not to permit such a landing such as over extremely rough or mountainous terrain over water out of gliding distance to land over widespread ground fog or at night CAPS activation should be considered Pilot Incapacitation Pilot incapacitation may be the result of anything from a pilot s medical condition to a b...

Page 502: ...ision altitude Above 2 000 feet there would normally be time to systematically assess and address the aircraft emergency Below 2 000 feet the decision to activate the CAPS has to come almost immediately in order to maximize the possibility of successful deployment At any altitude once the CAPS is determined to be the only alternative available for saving the aircraft occupants deploy the system wi...

Page 503: ...maintain the emergency landing body position until the airplane comes to a complete stop The emergency landing body position is assumed with tightened seat belt and shoulder harness by placing both hands on the lap clasping one wrist with the opposite hand and holding the upper torso erect and against the seat backs The seat cushions contain an aluminum honeycomb core designed to crush under impac...

Page 504: ... it is possible for an object such as a tree limb or flying debris to come through the opening and strike an occupant WARNING If it is decided to unlatch a door unlatch one door only Opening only one door will provide for emergency egress as well as reduce risks associated with ground contact Typically this would be the copilot s door as this allows the other occupants to exit first after the airp...

Page 505: ...s Ground Gusts If it is known or suspected that ground gusts of approximately 30 knots or more 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 In order to assure that the occupants can escape the airplane in the timeliest manner after the airplane comes to rest the pilot may el...

Page 506: ...r taxi speed control using brakes but without a reduction in power will result in increased brake temperature On flat smooth hard surfaces do not exceed 1000 RPM maximum continuous engine speed for taxi Power settings slightly above 1000 RPM are permissible to start motion for turf soft surfaces and on inclines Use minimum power to maintain constant taxi speed Riding the brakes while taxiing is si...

Page 507: ...kes have a large energy absorbing capacity therefore cooling time should be considered Energy absorbed during a few seconds of deceleration can take up to an hour to dissipate Always allow adequate cooling time after brake use Brake Maintenance The brake assemblies and linings should be checked at every oil change 50 hours for general condition evidence of overheating and deterioration In addition...

Page 508: ...10 12 P N 11934 003 Section 10 Cirrus Design Safety Information SR20 Revision A6 Intentionally Left Blank ...

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