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CIRRUS DESIGN 2220, Pilot Operating Handbook

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C

IRRUS

 D

ESIGN

S

ECTION

 7: A

IRPLANE

 

AND

 S

YSTEMS

SR20

F

UEL

 S

YSTEM

P/N 11934-005

7-39

Fuel System

A 56-gallon usable wet-wing fuel storage system provides fuel for engine 
operation. The system consists of a 29.3-gallon capacity (28 gallon usable) 
vented integral fuel tank and a fuel collector/sump in each wing, a three 
position selector valve, an electric fuel pump, and an engine-driven fuel 
pump. Fuel is gravity fed from each tank to the associated collector sumps 
where the engine-driven fuel pump draws fuel through a filter and selector 
valve to pressure feed the engine fuel injection system. The electric fuel 
pump is provided for engine priming and as an emergency backup for the 
engine-driven fuel pump.
Each integral wing fuel tank has a filler cap in the upper surface of each 
wing for fuel servicing. Access panels in the lower surface of each wing 
allow access to the associated wet compartment (tank) for inspection and 
maintenance. Float-type fuel quantity sensors in each wing tank supply fuel 
level information to the fuel quantity gauges. 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 flapper valve to the associ-
ated collector tank 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 tanks 
through a three-position (LEFT-RIGHT-OFF) selector valve. The selector 
valve allows tank selection. From the fuel pump, the fuel is metered to a 
flow divider, and delivered to the individual cylinders.
A dual-reading fuel quantity gauge is located in plain view of the pilot.
An analog electronic fuel quantity gauge is located on the Engine Strip 
along the left edge of the MFD and in the Fuel Qty block on the MFD’s 
Engine page.
Fuel shutoff and tank selection is positioned nearby for easy access.
Fuel system venting is essential to system operation. Blockage of the system 
will result in decreasing fuel flow and eventual engine fuel starvation and 
stoppage. Venting is accomplished independently from each tank by a vent 
line leading to a NACA-type vent mounted in an access panel underneath 
the wing near each wing tip.
The airplane may be serviced to a reduced capacity to permit heavier cabin 
loadings. This is accomplished by filling each tank to a tab visible below the 
fuel filler, giving a reduced fuel load of 13.0 gallons usable in each tank (26 
gallons total usable in all flight conditions).

Reissue A

Summary of Contents for 2220

Page 1: ...Approved in Normal Category based on 14 CFR 23 This document must be carried in the airplane at all times and be kept within the reach of the pilot during all flight operations THIS MANUAL INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY 14 CFR 23 AND ADDITIONAL INFORMATION PROVIDED BY CIRRUS AIRCRAFT AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL Model Serial Registration R...

Page 2: ...Cover Page ii P N 11934 005 Copyright 2019 All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth MN 55811 Reissue A ...

Page 3: ... Reissue A 2 17 Reissue A 2 18 Reissue A 2 19 Reissue A 2 20 Reissue A 2 21 Reissue A 2 22 Reissue A 2 23 Reissue A 2 24 Reissue A 2 25 Reissue A 2 26 Reissue A 2 27 Reissue A 2 28 Reissue A 2 29 Reissue A 2 30 Reissue A 3 1 Reissue A 3 2 Reissue A 3 3 Reissue A 3 4 Reissue A 3 5 Reissue A 3 6 Reissue A 3 7 Reissue A 3 8 Reissue A 3 9 Reissue A 3 10 Reissue A 3 11 Reissue A 3 12 Reissue A 3 13 Rei...

Page 4: ...eissue A 6 7 Reissue A 6 8 Reissue A 7 1 Reissue A 7 2 Reissue A 7 3 Reissue A 7 4 Reissue A 7 5 Reissue A 7 6 Reissue A 7 7 Reissue A 7 8 Reissue A 7 9 Reissue A 7 10 Reissue A 7 11 Reissue A 7 12 Reissue A 7 13 Reissue A 7 14 Reissue A 7 15 Reissue A 7 16 Reissue A 7 17 Reissue A 7 18 Reissue A 7 19 Reissue A 7 20 Reissue A 7 21 Reissue A 7 22 Reissue A 7 23 Reissue A 7 24 Reissue A 7 25 Reissue...

Page 5: ... Reissue A 8 10 Reissue A 8 11 Reissue A 8 12 Reissue A 8 13 Reissue A 8 14 Reissue A 8 15 Reissue A 8 16 Reissue A 8 17 Reissue A 8 18 Reissue A 8 19 Reissue A 8 20 Reissue A 8 21 Reissue A 8 22 Reissue A 8 23 Reissue A 8 24 Reissue A 8 25 Reissue A 8 26 Reissue A 8 27 Reissue A 8 28 Reissue A 8 29 Reissue A 8 30 Reissue A 8 31 Reissue A 8 32 Reissue A 9 1 Reissue A 9 2 Reissue A 10 1 Reissue A 1...

Page 6: ...LOEP 4 P N 11934 005 CIRRUS DESIGN AIRPLANE FLIGHT MANUAL SR20 LIST OF EFFECTIVE PAGES Reissue A Intentionally Left Blank ...

Page 7: ...ided by Cirrus and constitutes the FAA Approved Airplane Flight Manual for the aircraft The Pilot s Operating Handbook This POH has been prepared using GAMA Specification 1 for Pilot s Operating Handbook Revision 2 dated 18 October 1996 as the content model and format guide However some deviations from this specification were made for clarity The POH is presented in loose leaf form for ease in ins...

Page 8: ... 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 POH 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 POH has revision identification at the lower...

Page 9: ...ne for flight oper ations when the subject optional equipment is installed or the special oper ations are to be performed Retention of Data In the event a new title page is issued the weight and balance data changes the equipment list changes or the Log of Supplements is replaced the owner must ensure that all information applicable to the airplane is trans ferred to the new pages and the aircraft...

Page 10: ...FRONTMATTER CIRRUS DESIGN WARNINGS CAUTIONS AND NOTES SR20 Frontmatter 4 P N 11934 005 Reissue A Intentionally Left Blank ...

Page 11: ... General Table of Contents Introduction 3 The Airplane 7 Engine 7 Propeller 7 Hartzell 7 Fuel 7 Approved Fuel Grades 7 Oil 8 Maximum Certificated Weights 8 Cabin and Entry Dimensions 8 Baggage Spaces and Entry Dimensions 8 Specific Loadings 8 Terminology 9 Reissue A ...

Page 12: ...SECTION 1 GENERAL CIRRUS DESIGN SR20 1 2 P N 11934 005 Reissue A Intentionally Left Blank ...

Page 13: ...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 Hand book revisions supplements and procedures to be used to obtain publications see the Foreword section All liquid volumes referenced in this public...

Page 14: ...IGN INTRODUCTION SR20 1 4 P N 11934 005 Figure 1 1 Airplane Three View 74 inches 3 BLADE 188 cm 38 3 ft 11 67 m 9 1 ft 2 8 m 26 0 ft 7 92 m 8 9 ft 2 71 m NOTE Wing span includes position and strobe lights SR20_FM01_5314 Reissue A ...

Page 15: ...ons Location Length Width Height Volume Cabin 122 49 3 49 7 137 cu ft Baggage Compartment 36 39 8 38 5 32 cu ft 39 8 49 3 240 220 200 180 160 140 120 16 0 49 7 27 0 38 5 FS 10 5 33 4 39 0 20 0 33 3 32 0 SR20_FM01_5316 100 222 CABIN DOOR OPENING BAGGAGE DOOR OPENING 20 0 21 0 5 0 Station Fuselage Reissue A ...

Page 16: ...2 77 m 0 5 ft 0 15 m 24 3 ft 7 41 m 7 0 ft 2 16 m RADIUS FOR NOSE GEAR RADIUS FOR OUTSIDE GEAR RADIUS FOR INSIDE GEAR RADIUS FOR WING TIP TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER ACTUAL TURNING RADIUS MAY VARY AS MUCH AS THREE FEET GROUND TURNING CLEARANCE SR20_FM01_5398 Reissue A ...

Page 17: ... HP 2700 RPM Propeller Hartzell Propeller Type ConstantSpeed Three Blade Propeller Metal Standard Model Number HC E3YR 1RF F7392S 1 Diameter 74 0 73 0 Minimum Refer to Section 2 Powerplant Limitations for servicing limitations Three Blade Propeller Composite Optional Model Number 3C1 R919A1 76C03 2 Diameter 74 0 Minimum Fuel Total Capacity 58 5 U S Gallons 221 0 L Total Usable 56 0 U S Gallons 212...

Page 18: ...s for Takeoff 3150 lb 1429 kg Maximum Baggage Compartment Loading 130 lb 59 kg Cabin and Entry Dimensions Refer to the preceding figures for dimensions of the cabin interior and entry door openings Baggage Spaces and Entry Dimensions Refer to the preceding figures for dimensions of the baggage area and baggage door opening Specific Loadings Wing Loading 21 7 lb per square foot Power Loading 14 7 l...

Page 19: ...itude and temperature VG Best Glide Speed is the speed at which the greatest 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 Maxi...

Page 20: ...ed at which the airplane will obtain the maximum increase in altitude per unit of time The best rate of climb speed decreases slightly with altitude Meteorological Terminology Terminology Definition IMC Instrument Meteorological Conditions are meteorological conditions expressed in terms of visibility distance from cloud and ceiling less than the minima for visual flight defined in 14 CFR 91 155 I...

Page 21: ...o 29 92 in Hg 1013 21 mb corrected for position and instrument error In this Handbook altimeter instrument errors are assumed to be zero Standard Temperature Standard Temperature is the temperature that would be found at a given pressure altitude in the standard atmosphere It is 59 F 15 C at sea level pressure altitude and decreases approximately 4 F 2 C for each 1000 feet of altitude increase See...

Page 22: ...ertification testing Demonstrated crosswind is not considered to be limiting Service Ceiling Service Ceiling is the maximum altitude at which the aircraft at maximum weight has the capability of climbing at a rate of 100 feet per minute GPH Gallons Per Hour is the amount of fuel in gallons consumed by the aircraft per hour NMPG Nautical Miles Per Gallon is the distance in nautical miles which can ...

Page 23: ...of Gravity is the point at which an airplane would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane Arm Arm is the horizontal distance from the reference datum to the center of gravity CG of an item The airplane s arm is obtained by adding the airplane s individual moments and dividing the sum by the total weight M...

Page 24: ... Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff run Maximum Zero Fuel Weight Maximum Zero Fuel Weight is the maximum permissible weight of the airplane and its contents minus the total weight of the fuel onboard Useful Load Useful Load is the basic empty weight subtracted from the maximum ramp weight It is the maximum allowable combined weight of pilot passenger...

Page 25: ...imits 12 Flight Load Factor Limits 12 Minimum Flight Crew 12 Kinds of Operation 12 Kinds of Operation Equipment List 12 Icing 17 Runway Surface 17 Taxi Power 17 Fuel Limits 17 Altitude Limits 18 Environmental Conditions 18 Maximum Occupancy 18 Serials w 2 1 Rear Seat 18 Child Restraint System 18 Serials w Observer s Seat 19 Child Restraint System 19 Serials w o 2 1 Rear Seat or Observer s Seat 19 ...

Page 26: ...P N 11934 005 MD302 Standby Attitude Module Optional 24 Air Conditioning System Optional 24 Inflatable Restraint System 24 Flap Limitations 24 Paint 24 Cirrus Airframe Parachute System CAPS 24 Other Limitations 24 Smoking 24 Placards 25 Reissue A ...

Page 27: ...ation of the aircraft and its standard systems and equipment Note Compliance with the operating limitations in this section and in Section 9 is required by Federal Aviation Regulations Limitations associated with optional equipment are not described in this section Refer to Section 9 Log of Supplements of this handbook for amended operating limitations for airplanes equipped with optional equipmen...

Page 28: ...t any time VNO 164 166 Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution VO 3150 Lb 133 135 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 ...

Page 29: ...king Value KIAS Remarks White Arc 62 110 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 71 164 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 VNO Yellow Arc 164 20...

Page 30: ...Minimum Idling 25 psi Normal Operating Range 55 95 psi Maximum Starting Warm up Taxi Takeoff 115 psi Approved Oils Engine Break In For first 50 hours of operation or until oil consumption stabilizes use straight mineral oil conforming to SAE J1966 or MIL L 6082B SAE grades If engine oil must be added to the factory installed oil add only SAE J1966 or MIL L 6082B straight mineral oil After Engine B...

Page 31: ...n a higher viscosity oil can help to decrease the temperatures Fuel Fuel Grade Aviation Grade 100 LL Blue or 100 Green NOTE Refer to Fuel Limits in this Section regarding fuel and fuel storage 30 F 1 C to 90 F 32 C SAE 40 SAE 40 0 F 18 C to 70 F 21 C SAE 30 SAE 30 SAE 40 SAE 20W 40 Below 10 F 12 C SAE 20 SAE 20 SAE 30 SAE 20W 30 a For additional qualified oil grades and viscosities refer to the Ly...

Page 32: ...ions 6 0 and 22 0 on both face and camber sides Blades having damage to the shot peened areas exceeding 0 015 inch deep including material removal neces sary to blend out such damage must be removed from service and the reworked area shot peened before further flight NOTE For leading and trailing edge damage a 0 250 inch deep rework limit applies before shot peening is required Reference Hartzell ...

Page 33: ... F 500 F 240 435 435 465 465 Engine Speed 0 3000 RPM 500 2700 2700a Exhaust Gas Temperature 500 F 1750 F 1000 1600 Manifold Pressure 10 35 Inch Hg 15 29 5 Oil Pressure 0 115 PSI 0 25b 25 55b 55 95 95 115 115b Oil Temperature 75 F 250 F 100 235 235 Percent Power 0 100 0 100 a Engine Speed Warning when RPM between 2710 and 2730 for more than 10 seconds OR when RPM greater than 2730 for more than 5 s...

Page 34: ...lon 0 0 10 10 28 a Top of green arc dynamically changes based on altitude Instrument Range Units Red Arc Bar Yellow Arc Bar Green Arc Bar Yellow Arc Bar Red Arc Bar Minimum Minimum Caution Range Normal Range Maximum Caution Range Maximum Essential Bus Volts 0 36 Volts 0 24 4 24 5 32 32 Main Bus 1 Voltage 0 36 Volts 0 24 4 24 5 32 32 Main Bus 2 Voltage 0 36 Volts 0 24 4 24 5 32 32 Alternator 1 Curr...

Page 35: ...ward Refer to Figure 2 1 Aft Refer to Figure 2 1 Figure 2 1 Center of Gravity Envelope FS139 1 2700 lb FS141 1 3150 lb FS148 1 3150 lb FS148 1 2100 lb FS 137 8 2100 lb 2000 2050 2100 2150 2200 2250 2300 2350 2400 2450 2500 2550 2600 2650 2700 2750 2800 2850 2900 2950 3000 3050 3100 3150 3200 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 Reissue A ...

Page 36: ...r to Section 3 Inadver tent Spin Entry Flight Load Factor Limits Flaps UP 0 3150 lb 3 8g 1 9g Flaps 50 3150 lb 1 9g 0g Flaps 100 Down 3150 lb 1 9g 0g Minimum Flight Crew The minimum flight crew is one pilot Kinds of Operation The aircraft is equipped and approved for the following type operations VFR day and night IFR day and night Kinds of Operation Equipment List The following listing summarizes...

Page 37: ...OM 1 1 ELECTRICAL POWER Battery 1 1 1 1 1 Battery 2 1 1 Alternator 1 1 1 1 1 Alternator 2 1 1 Amp Meter Indication 1 1 1 1 Low Volts Annunciator 1 1 1 1 ALT 1 Annunciator 1 1 1 1 ALT 2 Annunciator 1 1 Circuit Breakers A R A R A R A R As required 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 Extingui...

Page 38: ...2 2 2 Fuel Selector Valve 1 1 1 1 ICE RAIN PROTECTION Alternate Engine Air Induction System 1 1 1 1 Alternate Static Air Source 1 1 1 1 Pitot Heater 1 1 LANDING GEAR Wheel Pants May be removed LIGHTS PFD Bezel Lighting 1 PFD Backlighting 1 1 1 Required if MFD Backlighting Fails Engine Indicators Must Be Shown in Backup Mode MFD Bezel Lighting 1 System Instrument and or Equipment Kinds of Operation...

Page 39: ...1 For hire operations Flash Light 1 1 NAVIGATION PITOT STATIC Airspeed Indicator 1 1 1 1 Altimeter 1 1 1 1 Magnetic Compass 1 1 1 1 Pitot System 1 1 1 1 Static System Normal 1 1 1 1 Attitude Indicator 1 1 Clock 1 1 Gyroscopic Directional Indication HSI 1 1 Magnetometer 1 1 Nav Radio 1 1 PFD Airspeed Indication 1 1 PFD Altitude Indication 1 1 System Instrument and or Equipment Kinds of Operation Re...

Page 40: ...quired per procedure Marker Beacon Receiver A R A R As required per procedure VHF Navigation Radio A R A R As required per procedure Vertical Speed Indicator ENGINE INDICATING Cylinder Head Temperature Indication Exhaust Gas Temperature Indication Fuel Flow Indication 1 1 1 1 Manifold Pressure Indication 1 1 1 1 Oil Pressure Indication 1 1 1 1 System Instrument and or Equipment Kinds of Operation ...

Page 41: ...ts Approved Fuel Aviation Grade 100 LL Blue or 100 Green Total Fuel Capacity 58 5 U S gallons 221 4 L Total Fuel Each Tank 29 3 U S gallons 110 9 L Total Usable Fuel all flight conditions 56 0 U S gallons 212 0 L Maximum Allowable Fuel Imbalance 7 5 U S gallons 28 4 L The fuel pump must be set to ON for takeoff climb maneuvering flight landing and for switching fuel tanks Oil Quantity Indicator Di...

Page 42: ...ed to 4 1 persons the pilot and four passengers If carrying three rear seat passengers occupants must be wearing a seat belt and shoulder harness with their hips and back firmly against the seat back as shown in the following illustration If three rear seat passengers cannot meet these requirements occupancy is limited to four persons Child Restraint System 1 Rear seat configuration for LATCH ISOF...

Page 43: ...traint System 1 Rear seat configuration for LATCH ISOFIX compliant child seat is limited to the Observer s Seat Figure 2 3 Observer s Seat Arrangement Serials w o 2 1 Rear Seat or Observer s Seat 1 Occupancy of this airplane is limited to two persons the pilot and one passenger 2 Installation of child seat is prohibited Refer to Section 7 Seats for additional information SR20_FM02_5320 Reissue A ...

Page 44: ... from the GPS equipment data base The GPS equipment database must incorporate the current update cycle a Receiver Autonomous Integrity Monitoring RAIM must be avail able at the Final Approach Fix for instrument approach procedures that do not use the integrity information from Satellite Based Augmentation Systems SBAS For flight planning purposes in areas where SBAS coverage is not available the p...

Page 45: ...Based Augmenta tion System complying with ICAO annex 10 for IFR enroute terminal and approach operations j The Perspective Integrated Avionics System complies with the standards set forth in AC 90 96A and JAA TGL 10 rev 1 for BRNAV and PRNAV operations k The navigation databases employed by the Perspective Integrated Avionics System meet the requirements set forth in AC 20 153 for database integri...

Page 46: ...rt surface to improve pilot situa tional awareness during ground operations 9 The TERRAIN PROXIMITY MAP is intended only to enhance situa tional awareness Use of the TERRAIN PROXIMITY information for primary terrain avoidance is prohibited 10 LTNG information on the NAVIGATION MAP or WEATHER MAP is approved only as an aid to hazardous weather avoidance Use of the WEATHER MAP for hazardous weather ...

Page 47: ...for tactical maneuvering L 3 Stormscope Weather Information System Optional 1 Use of the Weather Information System is not intended for hazardous weather penetration thunderstorm penetration Weather informa tion as displayed on the Perspective Integrated Avionics System is to be used only for weather avoidance not penetration 2 When option installed the appropriate revision of the L 3 Avionics Sys...

Page 48: ...ation Mode during flight is prohibited Inflatable Restraint System Use of a child safety seat with inflatable restraint system is prohibited Flap Limitations Approved Takeoff Settings 50 Approved Landing Settings 0 50 or 100 Paint To ensure that the temperature of the composite structure does not exceed 150 F 66 C the outer surface of the airplane must be painted in accor dance with the paint colo...

Page 49: ...Placards Figure 2 4 Placards 1 of 6 WARNING STAY CLEAR WHEN AIRPLANE IS OCCUPIED ROCKET FOR PARACHUTE DEPLOYMENT INSIDE Upper fuselage either side of CAPS rocket cover Wing adjacent to fuel filler caps SR20_FM02_5410 Engine compartment inside oil filler access Reissue A ...

Page 50: ...2 LIMITATIONS CIRRUS DESIGN PLACARDS SR20 2 26 P N 11934 005 Figure 2 4 Placards 2 of 6 Doors adjacent to latch OPEN EXTERNAL POWER 28 V DC Left fuselage on external power supply door SR20_FM02_5411A Reissue A ...

Page 51: ...G FLIGHT LANDING AND SWITCHING FUEL TANKS 13 15 16 18 20 OFF MAX IDLE F R I C T I O N ON OFF BOOST PUMP CUTOFF OFF LIFT BUTTON FOR OFF POSITION RICH CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT MAX POWER FUEL FLOWS P O W E R RIGHT 28 U S GALLONS USABLE LEFT 28 U S GALLONS USABLE Engine control panel SR20_FM02_5412 Reissue A ...

Page 52: ...E WINDOW OPERATE PER AIRPLANE FLIGHT MANUAL FLIGHT INTO KNOWN ICING IS PROHIBITED WITH REQUIRED EQUIPMENT DAY NIGHT VFR IFR FOLLOWING FLIGHT OPERATIONS THIS AIRCRAFT IS CERTIFIED FOR THE Instrument Panel left Bolster Switch Panel left edge Cabin Door Window lower edge centered applied upside down SR20_FM02_5413A Reissue A ...

Page 53: ...CE INFORMATION Baggage Compartment Door inside 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 FIRE EXTINGUISHER FORWARD LEFT OF PILOT SEAT FASTEN SEATBELTS NO SMOKING Instrument Panel ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Baggage Compartment aft edge Instrument Panel cen...

Page 54: ... PULL 2 ACTIVATION HANDLE PULL STRAIGHT DOWN 1 THIS COVER REMOVE 3 FUEL MIXTURE CUT OFF ACTIVATION PROCEDURE CIRRUS AIRFRAME PARACHUTE SYSTEM 133 KIAS MAXIMUM DEMONSTRATED DEPLOYMENT SPEED IN INJURY OR DEATH USE OF THIS DEVICE COULD RESULT MUST BE WORN AT ALL TIMES SEAT BELT AND SHOULDER HARNESS USE FOR EXTREME EMERGENCIES ONLY WARNING CAPS Deployment Handle Cover above pilot s right shoulder SR20...

Page 55: ...t Breakers 5 Memory Items 6 Procedure Division Symbols 6 Landing Guidance 6 Land as Soon as Practicable 6 Land as Soon as Possible 7 Airspeeds for Emergency Operations 8 Maneuvering Speed 8 Best Glide Gear and Flaps UP 8 Emergency Landing 8 Engine Failures 9 Engine Failure On Takeoff Low Altitude 9 Engine Failure In Flight 10 Airstart 11 Engine Airstart 11 Smoke and Fire 12 Cabin Fire In Flight 12...

Page 56: ...W RIGHT Warning 24 FUEL LOW TOTAL Warning 25 FUEL IMBALANCE Warning 25 Electrical System Emergencies 26 M BUS 1 Warning 26 M BUS 2 Warning 27 ESS BUS Warning 28 Environmental System Emergencies 29 CO LVL HIGH Warning 29 Integrated Avionics System Emergencies 30 Attitude Heading Reference System AHRS Failure 30 Air Data Computer ADC Failure 30 PFD Display Failure 31 Unusual Attitude Emergencies 31 ...

Page 57: ...ents for optional equipment Emergency Procedures Crew Alert System CAS Messaging Warnings Displayed in red against a black background Warning CAS messages arise during emergency situations that require immediate flight crew awareness and immediate flight crew response A flashing Warning CAS message with an accompanying aural alert requires immediate action A Warning CAS message with no accompanyin...

Page 58: ...o any oil leaks or fuel stains that could indicate engine problems NOTE Refer to Section 4 Normal Procedures Preflight Inspection for more information Methodology Aircraft emergencies are dynamic events Because of this it is impossible to enumerate every action a pilot should properly undertake in response to a particular situation However four basic actions can be applied to any emergency They ar...

Page 59: ...and responded to the emergency assess your next move Perform any non critical clean up items in the checklist and land as soon as practicable Even if the airplane appears to be in sound condi tion it may not be NOTE Refer to Landing Guidance in this section for factors that deter mine landing criticality Circuit Breakers Some procedures involve manipulating circuit breakers CBs The following crite...

Page 60: ...es the pilot through the remaining decisions Once the applicable condition s are identified the pilot follows the remaining steps until the indication Proce dure Complete is reached The procedure symbol levels are First Level Second Level Third Level Landing Guidance Land as Soon as Practicable Extended flight is not recommended and the pilot should proceed to land the plane but not necessarily at...

Page 61: ... at which a safe landing can be made Continued flight beyond an available airfield at which a safe landing can be made will result in increased risk and shall not be attempted The nearest suitable landing site shall be determined by the pilot with consideration given to weather surface dimensions and conditions and pilot experience Reissue A ...

Page 62: ...11934 005 Airspeeds for Emergency Operations Maneuvering Speed 3150 lb 1429 kg 133 KIAS 2700 lb 1225 kg 123 KIAS 2300 lb 1043 kg 114 KIAS Best Glide Gear and Flaps UP 3150 lb 1429 kg 100 KIAS 2600 lb 1179 kg 92 KIAS Emergency Landing Flaps UP 89 KIAS Flaps 50 83 KIAS Flaps 100 78 KIAS Reissue A ...

Page 63: ...xture Control to CUTOFF Fuel Selector to OFF and do not attempt a restart If a turn back to the runway is elected be very careful not to stall the airplane NOTE If the engine fails immediately after becoming airborne abort on the runway if possible If altitude precludes a runway stop but is not sufficient to restart the engine lower the nose to maintain airspeed and establish a glide attitude In m...

Page 64: ...edure Complete WARNING If engine failure is accompanied by fuel fumes in the cockpit or if in ternal engine damage is suspected move Mixture Control to CUTOFF Fuel Selector to OFF and do not attempt a restart If a turn back to the runway is elected be very careful not to stall the airplane NOTE If the engine fails at altitude pitch as necessary to establish best glide speed While gliding toward a ...

Page 65: ...Power Lever SLOWLY INCREASE 11 ALT 1 and ALT 2 Switches ON 12 CHTs and Oil Temperature WARM ENGINE AT PARTIAL POWER IF REQUIRED 13 If engine will not start perform Emergency Landing w o Power Check list Procedure Complete NOTE Switching tanks and turning the fuel pump on will enhance starting if fuel contamination was the cause of the failure Leaning the mixture and then slowly enriching mixture m...

Page 66: ... of fire or fumes and airplane is in night weather or IFR conditions a Airflow Selector OFF b BAT 1 BAT 2 ALT 1 and ALT 2 Switches ON c AVIONICS Switch ON d Required Systems ACTIVATE ONE AT A TIME e Temperature Selector COLD f Vent Selector FEET PANEL DEFROST POSITION g Airflow Selector SET AIRFLOW TO MAXIMUM h Panel Eyeball Outlets OPEN i Land as soon as possible Procedure Complete NOTE With mast...

Page 67: ...the fire extinguisher to extinguish flames and land as soon as possible Opening the vents or doors may feed the fire but to avoid incapac itating the crew from smoke inhalation it may be necessary to rid cabin of smoke or fire extinguishant If required to re activate systems pause several seconds between activating each system to isolate malfunctioning system Continue flight to earliest possible l...

Page 68: ... Procedure Complete CAUTION Putting the airplane into a dive may blow out the fire Do not exceed VNE during the dive 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 Procedure Complete NOTE A fire during engine start may be caused by fuel igniting in the ...

Page 69: ...ssible Procedure Complete NOTE If smoke and or fumes are detected in the cabin check the engine parameters for any sign of malfunction If a fuel leak has occurred actuation of electrical components may cause a fire If there is a strong smell of fuel in the cockpit divert to the nearest suitable landing field Perform Forced Landings Checklist and shut down the fuel supply to the engine once a safe ...

Page 70: ...179 kg 92 KIAS Figure 3 1 Maximum Glide Ratio 9 1 Conditions Example Power OFF Altitude 8 000 ft AGL Propeller Windmilling Airspeed Best Glide Flaps 0 UP Glide Distance 12 NM Wind Zero 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_FM09_2765 Reissue A ...

Page 71: ...l and a forced landing is imminent select a suitable field and prepare for the landing If flight conditions or terrain does not permit a safe landing CAPS deployment may be required Refer to Section 10 Cirrus Airframe Parachute System CAPS for CAPS deployment scenarios and landing considerations A suitable field should be chosen as early as possible so that maximum time will be available to plan a...

Page 72: ...o provide a ready escape path It may be necessary to allow some cabin flooding to equalize pres sure on the doors If the doors cannot be opened break out the windows with the egress hammer and crawl through the opening 1 Flaps 50 2 Trim 80 KIAS 3 Power AS REQUIRED FOR GLIDE ANGLE Procedure Complete NOTE The pitch trim spring cartridge is attached directly to the elevator and provides a backup shou...

Page 73: ...landing pattern and shut down the en gine fuel supply once a safe landing is assured NOTE Indications of a partial power loss include fluctuating RPM reduced or fluctuating manifold pressure low oil pressure high oil temperature and a rough sounding or rough running engine Mild engine roughness in flight may be caused by one or more spark plugs becoming fouled A sudden engine roughness or misfirin...

Page 74: ...uffi cient fuel pressure to supply the engine if the engine driven fuel pump completely fails Selecting the opposite fuel tank may resolve the problem if fuel starvation or contamination in one tank was the problem Cycling the ignition switch momentarily from BOTH to L and then to R may help identify the problem An obvious power loss in single ignition operation indicates magneto or spark plug tro...

Page 75: ... to produce erroneous warnings Carefully evaluate other engine parameters and smoothness of operation before taking action If oil pressure is low the engine has probably lost a significant amount of its oil and engine failure may be imminent If oil pressure is suddenly high a blockage or obstruction may have devel oped in the oil circulation system and engine failure may be imminent OIL TEMP Oil T...

Page 76: ...ver MINIMUM REQUIRED 2 Flight PROHIBITED Procedure Complete If in flight a Power Lever REDUCE b Airspeed INCREASE c Mixture ADJUST FUEL FLOW TO TOP OF GREEN ARC d Annunciations and Engine Temperatures MONITOR If Caution or Warning annunciation is still illuminated 1 Power Lever MINIMUM REQUIRED 2 Engine Instruments MONITOR If Caution annunciation only remains illuminated a Land as soon as practica...

Page 77: ...f engine speed high a Perform Propeller Governor Failure Checklist 2 Oil Pressure Gauge CHECK Procedure Complete 1 Oil Pressure CHECK 2 Land as soon as practicable Procedure Complete 1 Power Lever ADJUST TO KEEP RPM IN LIMITS 2 Airspeed REDUCE TO 90 KIAS 3 Land as soon as practicable Procedure Complete NOTE If the RPM does not respond to power lever movement or over speeds the most likely cause is...

Page 78: ...Fuel Quantity in Left Tank 1 Fuel Quantity Gauges CHECK 2 Fuel Pump BOOST 3 Fuel Selector RIGHT TANK Procedure Complete NOTE Left fuel tank sensed quantity less than 1 gallon FUEL LOW RIGHT Low Fuel Quantity in Right Tank 1 Fuel Quantity Gauges CHECK 2 Fuel Pump BOOST 3 Fuel Selector LEFT TANK Procedure Complete NOTE Right fuel tank sensed quantity is less than 1 gallon Reissue A ...

Page 79: ...ists a Land as soon as practicable Procedure Complete NOTE Fuel Totalizer or sensed quantity is less than 7 gallons FUEL IMBALANCE Fuel Imbalance 1 Fuel Quantity Gauges CHECK 2 Fuel Pump ON a If the Boost Pump is already in use for vapor suppression pump should be left in this position for tank switch 3 Fuel Selector SELECT FULLER TANK 4 Fuel Pump AS REQUIRED a After switching tanks message will r...

Page 80: ...M1 CHECK If M Bus 1 Voltage is greater than 32 volts a ALT 1 Switch OFF b Perform ALT 1 Caution Failure Checklist do not reset alternator Procedure Complete NOTE Main Bus 1 Voltage is excessive indicates an alternator 1 voltage regulator failure will typically be associated with abnormally high voltage indications on M1 M2 and ESS buses may also be associ ated with M BUS 2 Warning or ESS BUS Warni...

Page 81: ...s 2 Voltage is greater than 32 volts a ALT 2 Switch CYCLE b Main Bus 2 Voltage M2 CHECK If M Bus 2 Voltage remains greater than 32 volts 1 ALT 2 Switch OFF 2 Perform ALT 2 Caution Failure Checklist do not reset alter nator Procedure Complete NOTE Main Bus 2 Voltage is excessive Indicates an alternator voltage regulator failure will typically be associated with abnormally high bus voltage indicatio...

Page 82: ...light conditions permit consider shedding 1 Air Conditioning 2 Landing Light 3 Pitot Heat 4 Cabin Fan 5 Nav Lights 6 Strobe Lights 7 Audio Panel 8 COM 2 2 Land as soon as practicable Battery reserve only Procedure Complete CAUTION Dependent on battery state flaps and landing light may be unavail able on landing NOTE Essential Bus voltage is high or low High voltage indicates alter nator voltage re...

Page 83: ...OST POSITION 4 Airflow Selector SET AIRFLOW TO MAXIMUM 5 Panel Eyeball Outlets OPEN If CO LVL HIGH does not extinguish a Supplemental Oxygen if available 1 Oxygen Masks or Cannulas DON 2 Oxygen System ON 3 Oxygen Flow Rate MAXIMUM b Land as soon as possible Procedure Complete NOTE Annunciation indicates carbon monoxide level is greater than 50 PPM Ensure that air condition is not in recirculate mo...

Page 84: ... Instruments Attitude Heading Procedure Complete NOTE Failure of the Attitude and Heading Reference System AHRS is indicated by removal of the sky ground presentation and a Red X and a yellow ATTITUDE FAIL shown on the PFD The digital heading presentation will be replaced with a yellow HDG and the compass rose digits will be removed The course pointer will indicate straight up and course may be se...

Page 85: ... recovery characteristics The only approved and demonstrated method of spin recovery is activation of the Cirrus Airframe Parachute System see CAPS Deployment Checklist this section Because of this if the aircraft enters a spin CAPS must be deployed immediately While the stall characteristics of the aircraft make inadvertent entry into a spin extremely unlikely it is possible Spin entry can be avo...

Page 86: ...ethod of spin recovery is activation of the Cirrus Airframe Parachute System see CAPS Deployment Checklist this section Because of this if the aircraft enters a spin CAPS must be deployed immediately While the stall characteristics of the aircraft make inadvertent entry into a spin extremely unlikely it is possible Spin entry can be avoided by using good airmanship coordinated use of controls in t...

Page 87: ...sly apply elevator back pressure to bring airplane to level flight attitude 4 Trim for level flight 5 Set power as required 6 Use autopilot if functional otherwise maintain a constant heading through the coordinated aileron and rudder inputs 7 Exit IMC conditions as soon as possible Procedure Complete NOTE In all cases if the aircraft enters an unusual attitude from which recovery is not assured i...

Page 88: ...able 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 control to full RICH and regain safe pattern parameters or go around If airspeed cannot be controlled shut engine down and perform the Forced Landings Checklist After landing bring the airplane to a stop and complete the Emergency Eng...

Page 89: ...n indicates brake temperature is greater than 293 F Refer to Section 10 Taxiing Steering and Braking Practices for additional information START ENGAGED Starter Engaged Annunciation If on ground a Ignition Switch DISENGAGE b Wait 1 minute before next start attempt If starter does not disengage relay or solenoid failure 1 BAT 1 Switch OFF 2 Engine SHUTDOWN 3 STARTER Circuit Breaker PULL Procedure Co...

Page 90: ...er required pull failed relay or solenoid If breaker is unknowingly or unintentionally reset starter will instantly engage if Battery 1 power is supplied creat ing a hazard for ground personnel NOTE Starter has been engaged for more than 30 seconds starter limit is 10 seconds if not manually engaged such as during difficult start this annunciation may indicate a failure of the starter solenoid or ...

Page 91: ...Complete WARNING While exiting the airplane make sure evacuation path is clear of other aircraft spinning propellers and other hazards If the engine is left running set the Parking Brake prior to evacuating the airplane If the doors cannot be opened break out the windows with egress ham mer located in the console between the front seats and crawl through the opening Reissue A ...

Page 92: ...ECURE 11 Assume emergency landing body position 12 After the airplane comes to a complete stop evacuate quickly and move upwind Procedure Complete WARNING Jerking or rapidly pulling the activation T handle will greatly increase the pull forces required to activate the rocket Use a firm and steady pulling motion a chin up type pull ensures successful activation NOTE The Cirrus Airframe Parachute Sy...

Page 93: ...os in which the activation of the CAPS would be appropriate are discussed in Section 10 Safety Informa tion of this Handbook These include Mid air collision Structural failure Loss of control Landing in inhospitable terrain Pilot incapacitation All pilots should carefully review the information on CAPS activa tion and deployment in Section 10 before operating the airplane Continued Reissue A ...

Page 94: ...SECTION 3 EMERGENCY PROCEDURES CIRRUS DESIGN OTHER EMERGENCIES SR20 3 40 P N 11934 005 Reissue A Intentionally Left Blank ...

Page 95: ...cing Encounter 5 Inadvertent IMC Encounter 6 Door Open In Flight 6 Abnormal Landings 7 Landing With Failed Brakes 7 Landing With Flat Tire 7 Engine System 8 OIL PRESS Caution 8 OIL TEMP Caution 8 START ENGAGED Caution 9 Fuel System 10 FUEL LOW TOTAL Caution 10 FUEL IMBALANCE Caution 10 FUEL IMBALANCE Advisory 11 Electrical System 11 M BUS 1 Caution 11 M BUS 2 Caution 12 BATT 1 Caution 12 ALT 1 Cau...

Page 96: ... FAIL Caution 18 PITOT HEAT REQD Caution 18 Flight Control System 19 Electric Trim Autopilot Failure 19 FLAPS OVERSPEED Caution 19 TAKEOFF FLAPS Caution 20 FLAPS CLIMB Advisory 20 Landing Gear System 21 Brake Failure During Taxi 21 BRAKE TEMP Caution 21 Other Conditions 22 Aborted Takeoff 22 PARK BRAKE Caution 22 Communications Failure 23 Reissue A ...

Page 97: ...w response A flashing Caution CAS message with no accompanying aural alert requires flight crew response dependent on workload A non flashing Caution CAS message with no accompanying aural alert requires attention dependent on workload It may also require performing maintenance or taking corrective action prior to next flight NOTE Crew Alerting System messages and related procedures described here...

Page 98: ...rcuit breaker is not SET it may be reset only once If the circuit breaker opens again do not reset When instructed to PULL the appropriate circuit breaker should only be pulled and not reset When instructed to CYCLE the appropriate circuit breaker should be pulled delayed for several seconds and reset only once Allow suffi cient cooling time for circuit breakers that are reset through a CYCLE proc...

Page 99: ...n to weather runway dimensions surface conditions and services available However in no case shall a suitable landing airfield be discounted in the name of convenience Land as Soon as Possible Land without delay at the first site at which a safe landing can be made Continued flight beyond an available airfield at which a safe landing can be made will result in increased risk and shall not be attemp...

Page 100: ...o 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 described above 1 Airplane Control MAINTAIN Procedure Complete NOTE The doors on the airplane will remain 1 3 inches open in flight if not latched If this is discovered on takeoff roll abort takeoff if practical If already a...

Page 101: ...acle avoidance d Perform Emergency Engine Shutdown On Ground Checklist Procedure Complete NOTE Rudder effectiveness will decrease with decreasing airspeed Main Gear a Land on the side of the runway corresponding to the good tire b Maintain directional control with the brakes and rudder c Do not taxi Stop airplane and perform a normal Engine Shutdown Procedure Complete Nose Gear a Land in the cente...

Page 102: ...flight a Land as soon as practicable Procedure Complete NOTE Oil pressure between 25 psi and 55 psi at or above 1000 RPM This message will appear prior to engine start and should clear after engine start OIL TEMP High Oil Temperature 1 Power REDUCE as much as practical 2 Airspeed INCREASE 3 Mixture AS REQUIRED 4 Oil Temperature Gauge MONITOR Procedure Complete Reissue A ...

Page 103: ...NSURE NOT STUCK IN START b STARTER Circuit Breaker PULL c Flight CONTINUE Engine start will not be available at destination Procedure Complete WARNING Use caution after shutdown if STARTER circuit breaker required pull failed relay or solenoid If breaker is unknowingly or unintentionally reset starter will instantly engage if Battery 1 power is supplied creat ing a hazard for ground personnel NOTE...

Page 104: ... Land as soon as practicable Procedure Complete NOTE Fuel totalizer or sensed fuel quantity is less than or equal to 10 gallons FUEL IMBALANCE Fuel Imbalance 1 Fuel Quantity Gauges CHECK 2 Fuel Pump ON If Fuel Pump is already ON for vapor suppression pump should be left in this position for tank switch 3 Fuel Selector SELECT FULLER TANK 4 Fuel Pump AS REQUIRED After switching tanks message will re...

Page 105: ...Selector SELECT FULLER TANK 4 Fuel Pump AS REQUIRED After switching tanks message will remain until sensed imbalance is less than 5 5 gallons Procedure Complete NOTE Fuel level imbalance between left and right is greater than 5 5 gallons M BUS 1 Low Voltage on Main Bus 1 1 Perform ALT 1 Caution Failure Checklist Procedure Complete NOTE Main Bus 1 Voltage is low indicates Alt 1 failure and will typ...

Page 106: ...ll typically be associated with low M1 and M2 voltages Alt 1 and Alt 2 current indications Battery 1 discharge ALT 1 2 and M BUS 1 Caution M BUS 2 Caution messages and ESS BUS Warning message BATT 1 Unexpected discharge on battery 1 1 Main Bus 1 2 and Non Essential Bus Loads REDUCE 2 Main Bus 1 2 and Essential Bus Voltages MONITOR 3 Land as soon as practicable Procedure Complete NOTE Battery 1 dis...

Page 107: ...lowing to preserve Battery 1 1 Air Conditioning 2 Landing Light 3 Convenience Power aux items plugged into armrest jack 4 EVS Camera if installed c Continue Flight avoiding IMC or night flight as able reduced power redundancy Procedure Complete CAUTION Dependent on Battery 1 state indicated by M1 voltage landing light may be weak or inoperative for landing NOTE Alternator 1 output is low indicativ...

Page 108: ...or does not reset a ALT 2 Switch OFF b Continue Flight avoiding IMC or night flight as able reduced power redundancy Procedure Complete NOTE Alternator 2 output is low indicative of alternator failure Isolated Alt 2 failure will not typically be associated with any other unusual indications cautions or warnings Alt 1 will pick up all loads AVIONICS OFF Avionics Switch Off 1 AVIONICS Switch ON AS R...

Page 109: ...es not extinguish a High cabin temps LAND AS SOON AS PRACTICABLE b Low cabin temps CONTINUE MONITOR Procedure Complete NOTE The cooling fan for the PFD is inoperative MFD FAN FAIL MFD Cooling Fan Failure 1 AVIONICS FAN 1 Circuit Breaker CYCLE If annunciation does not extinguish a High cabin temps LAND AS SOON AS PRACTICABLE b Low cabin temps CONTINUE MONITOR Procedure Complete NOTE The cooling fan...

Page 110: ...aker In daytime lighting knob OFF full counterclockwise or with CABIN LIGHTS circuit breaker pulled Electro mechanical standby instruments all avionics system keypads and the bolster switch panel are unlit MFD PFD and MD302 Standby Attitude Module optional screen illumination is controlled by automatic photocell providing full brightness in high light conditions only slightly reduced by darkness E...

Page 111: ...sure from the cabin to these instru ments With the alternate static source on adjust indicated airspeed slightly during climb or approach in accordance with Section 5 Alternate Static Source as appropriate for vent heater configuration 1 Pitot Heat ON Procedure Complete NOTE If only the airspeed indicator is providing erroneous information and in icing conditions the most probable cause is Pitot i...

Page 112: ...ered perform Inadvertent Icing Encounter Checklist and a Airspeed EXPECT NO RELIABLE INDICATION b Exit icing conditions using attitude altitude and power instru ments Procedure Complete NOTE Pitot heat failure Displayed when Pitot heat switch is ON and Pitot heat current is not detected PITOT HEAT REQD Pitot Heat Required 1 Pitot Heat ON Procedure Complete NOTE Displayed 15 seconds after system de...

Page 113: ...ESSURE d Land as soon as practicable Procedure Complete NOTE Any failure or malfunction of the electric trim or autopilot can be overridden by use of the control yoke If runaway trim is the problem deenergize the circuit by pulling the appropriate circuit breakers and land as soon as conditions permit FLAPS OVERSPEED Flap System Exceedance 1 Airspeed REDUCE OR 1 Flaps RETRACT Procedure Complete NO...

Page 114: ...S CLIMB Advisory TAKEOFF FLAPS Flaps Not In Takeoff Configuration 1 Takeoff ABORT 2 Aircraft Control MAINTAIN 3 Aircraft Configuration CHECK Procedure Complete NOTE Flaps are not set to 50 during takeoff FLAPS CLIMB Flaps Not Set For Climb 1 Flaps UP Procedure Complete NOTE Flaps are not set for enroute climb Reissue A ...

Page 115: ...Ignition Switch OFF Procedure Complete NOTE Ground steering is accomplished by differential braking However increasing power may allow some rudder control due to increased ground speed and airflow over the rudder BRAKE TEMP Left Right Brake Over Temperature 1 Stop aircraft and allow the brakes to cool Procedure Complete WARNING Do not set parking brake unless required for safety NOTE Brake tempera...

Page 116: ... takeoff brake temperatures will be elevated Subsequent aborted takeoffs or other high energy use of the brakes may cause brake overheat failure and possibly even fire A 25 minute cooling time is recommended following high energy use of the brake system before attempting to conduct operations that may require further high energy braking Brake temperature indicator should be inspected prior to flig...

Page 117: ...eed with CFR AIM lost communications proce dures 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 SET 4 Headset CHANGE 5 Handheld Microphone CONNECT Procedure Complete Reissue A ...

Page 118: ...SECTION 3A ABNORMAL PROCEDURES CIRRUS DESIGN OTHER CONDITIONS SR20 3A 24 P N 11934 005 Reissue A Intentionally Left Blank ...

Page 119: ...Normal Takeoff 16 Short Field Takeoff 16 Climb 17 Cruise 18 Cruise Leaning 20 Descent 21 Before Landing 21 Landing 21 Normal Landing 21 Short Field Landing 21 Crosswind Landing 22 Balked Landing Go Around 22 After Landing 22 Shutdown 23 Stalls 23 Environmental Conditions 24 Cold Weather Operation 24 Starting 24 Hot Weather Operation 26 Ground Operation of Air Conditioning System Optional 26 Extend...

Page 120: ...SECTION 4 NORMAL PROCEDURES CIRRUS DESIGN SR20 4 2 P N 11934 005 Reissue A Intentionally Left Blank ...

Page 121: ...n 5 for takeoff and landing distance the speed appropriate to the particular weight must be used Takeoff Normal Flaps 50 71 75 KIAS Short Field Flaps 50 71 KIAS Obstacle Clearance Flaps 50 81 KIAS Enroute Climb Flaps Up Normal SL 96 KIAS Normal 10 000 92 KIAS Best Rate of Climb SL 96 KIAS Best Rate of Climb 10 000 92 KIAS Landing Approach Normal Approach Flaps Up 89 KIAS Normal Approach Flaps 50 8...

Page 122: ...all con trol 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 polished or not ice snow or slush from fuselage wing stabilizers and control surfaces Ensure that con trol surfaces are free of internal ice or debris Check that wheel fairings are free of snow and ice accumulation Check that Pitot...

Page 123: ...s 100 CHECK LIGHT ON m Lights CHECK OPERATION n Stall Warning System Inlet UNOBSTRUCTED o Stall Warning TEST NOTE Test stall warning system by applying suction to the stall warning system inlet and noting the warning horn sounds p Pitot Heat ON WARNING Pitot Heat Probe may be hot 1 Verify probe is hot q Pitot Heat OFF r AVIONICS Switch OFF s BAT 1 and BAT 2 Switches OFF t Alternate Static Source N...

Page 124: ...ontal and Vertical Stabilizers CONDITION NOTE Verify tape covering the forward and aft inspection holes located on outboard ends of horizontal stabilizer is installed and securely attached c Elevator and Tab CONDITION AND MOVEMENT d Rudder FREEDOM OF MOVEMENT e Rudder Trim Tab CONDITION AND SECURITY f Attachment hinges bolts and cotter pins SECURE 4 Right Fuselage a Static Button CHECK FOR BLOCKAG...

Page 125: ...l Drains 2 underside DRAIN AND SAMPLE d Wheel Fairings SECURITY ACCUMULATION OF DEBRIS e Tire CONDITION INFLATION AND WEAR f Wheel and Brakes FLUID LEAKS EVIDENCE OF OVERHEATING GENERAL CONDITION AND SECURITY g Chocks and Tiedown Ropes REMOVE 8 Nose Right Side CAUTION The engine must not be operated with less than six quarts of oil in the sump dipstick indication Seven quarts is recommended for ex...

Page 126: ...ht CONDITION AND SECURITY b Cowling ATTACHMENTS SECURE c External Power DOOR SECURE d Gascolator underside DRAIN FOR 3 SECONDS SAMPLE 11 Left Main Gear and Forward Wing a Wheel Fairings SECURITY ACCUMULATION OF DEBRIS b Tire CONDITION INFLATION AND WEAR c Wheel and Brakes FLUID LEAKS EVIDENCE OF OVERHEATING GENERAL CONDITION AND SECURITY d Chocks and Tiedown Ropes REMOVE e Fuel Drains 2 underside ...

Page 127: ...Inspection COMPLETED WARNING Ensure that the airplane is properly loaded and within the AFM s weight and balance limitations prior to takeoff 2 Weight and Balance VERIFY WITHIN LIMITS 3 Emergency Equipment ON BOARD 4 Passengers BRIEFED 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 p...

Page 128: ... advance the mixture control to RICH and promptly retard the power lever If the 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 WARNIN...

Page 129: ...OFF 11 Ignition Switch START RELEASE AFTER ENGINE STARTS CAUTION Limit cranking to intervals of 10 seconds with a 30 second cooling period between cranks This will improve battery and contactor life 12 Mixture SMOOTHLY ADVANCE TO RICH AFTER ENGINE STARTS 13 Oil Pressure CHECK 14 Power Lever RETARD MAINTAIN 1000 RPM 15 Fuel Pump OFF 16 ALT 1 and ALT 2 Switches ON 17 AVIONICS Switch ON 18 Engine Par...

Page 130: ...RNING 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 limit and proper braking procedures are not observed the brake system may overheat and result in brake dam age or brake fire CAUTIO...

Page 131: ...er contamination on the fu selage wing stabilizers and control surfaces 1 Doors LATCHED 2 CAPS Handle VERIFY PIN REMOVED 3 Seat Belts and Shoulder Harness SECURE 4 Cabin Heat Defrost AS REQUIRED 5 Air Conditioner RECIRC DISABLED CAUTION Use of RECIRC mode prohibited in flight NOTE If Air Conditioner is ON for takeoff roll see Section 5 Takeoff Distance for takeoff distance change No takeoff distan...

Page 132: ...RPM THEN BOTH NOTE RPM drop must not exceed 175 RPM for either magneto RPM differential must not exceed 50 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 ...

Page 133: ... Settings Normal and short field takeoffs are accomplished with flaps set at 50 Takeoffs with 100 flaps 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 ahead the airplane should be leveled off immediately to accel erate to a higher climb speed Takeoffs into strong crossw...

Page 134: ...le before best power is attained Idle to maximum power throttle movements should be made slowly approximately 3 seconds for full range motion 3 Engine Parameters CHECK 4 Elevator Control ROTATE SMOOTHLY AT 71 75 KIAS 5 At 85 KIAS Flaps UP 1 Flaps 50 2 Brakes HOLD 3 Power Lever FULL FORWARD 4 Engine Parameters CHECK 5 Brakes RELEASE STEER WITH RUDDER ONLY 6 Elevator Control ROTATE SMOOTHLY AT 71 KI...

Page 135: ...ate of climb speeds shown in the rate of climb chart in Section 5 If an obstruction dictates 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 1 Climb Power SET 2 Flaps VERIFY UP 3 Mixture LEAN AS REQUIRED FOR ALTITUDE 4 Engine Parameters CHECK 5 Fuel Pump...

Page 136: ...r slightly richer for the first 50 hours of engine operation or until oil consumption stabilizes During break in make sure the engine is operated at 65 or higher cruise power as much as practical to ensure correct piston ring seating Cruise power of 75 for the first hour of flight and alternating power settings between 65 and 75 power for the second hour of flight is recommended for proper engine ...

Page 137: ... during maneuvering flight flight training maneuvers chandelles stalls etc 2 Cruise Power SET 3 Mixture LEAN AS REQUIRED 4 Engine Parameters MONITOR NOTE Fuel Pump must be used for switching from one tank to another Failures to activate the Fuel Pump before transfer could result in delayed restart if the engine should quit due to fuel starvation 5 Fuel Flow and Balance MONITOR Continued Reissue A ...

Page 138: ...ement based on the following table Alternatively leaning can be done by adjusting the mixture to the cyan Target Fuel Flow caret displayed on the fuel flow gauge Target Fuel Flow is determined using a calculated engine air flow based on engine speed manifold air temperature and manifold air pressure Target Fuel Flow is advisory only and does not guarantee sufficient cylinder cooling If any CHT s a...

Page 139: ... power off and on the main wheels first to reduce the landing speed and subsequent need for braking Gently lower the nose wheel to the runway after airplane speed has diminished This is especially important for rough or soft field landings Short Field Landing For a short field landing in smooth air conditions make an approach at 78 KIAS with full flaps using enough power to control the glide path ...

Page 140: ...t upon pilot capa bility as well as aircraft limitations Operation in direct crosswinds of 20 knots has been demonstrated Balked Landing Go Around After Landing In a balked landing go around climb disengage autopilot apply full power then reduce the flap setting to 50 If obstacles must be cleared during the go around climb at the best angle of climb with 50 flaps After clearing any obstacles retra...

Page 141: ...n the bank with coordinated use of the ailerons and rudder Upon stall warning in flight recovery is accomplished by immediately reducing back pressure to reduce the angle of attack and to maintain safe airspeed adding power if necessary and rolling wings level with coordinated use of the controls WARNING Extreme care must be taken to avoid uncoordinated accelerated or abused control inputs when cl...

Page 142: ...posite parts seals hoses and drive belts do not attempt to hasten the preheat process Starting When the engine has been exposed to temperatures below 10 F 12 C for a period of two hours or more the use of an external pre heater and external power is recommended Failure to properly preheat a cold soaked engine may result in oil congealing within the engine oil hoses and oil cooler with subsequent l...

Page 143: ... CUTOFF 10 Mixture CUTOFF 11 Ignition Switch START RELEASE AFTER ENGINE STARTS CAUTION Limit cranking to intervals of 10 seconds with a 30 second cooling period between cranks This will improve battery and contactor life 12 Mixture SMOOTHLY ADVANCE TO RICH AFTER ENGINE STARTS 13 Oil Pressure CHECK 14 Power Lever RETARD MAINTAIN 1000 RPM 15 Fuel Pump OFF 16 ALT 1 and ALT 2 Switches ON 17 AVIONICS S...

Page 144: ... procedure is recommended to reduce potential for spark plug lead fouling and lead build up on engine valve guides 1 Set throttle to 1200 RPM 2 Lean the mixture for maximum RPM 3 Reduce throttle to RPM for continued ground operations 800 1000 RPM is recommended WARNING Except as required for high elevation airports the mixture lever must be returned to the full forward rich position before take of...

Page 145: ... for lead build up in the combustion chamber spark plugs and engine oil CAUTION The airplane must be stationary before the following procedure is completed 1 Maintain throttle between 1000 and 1200 RPM until operating tempera ture has stabilized 2 Increase throttle to 1800 RPM for 15 20 seconds 3 Reduce throttle back to between 1000 and 1200 RPM and shut down immediately using mixture control Reis...

Page 146: ...s minimize environmental noise when oper ating the aircraft 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 events parks and recreational areas fly not less than 2000 feet above the surface even thoug...

Page 147: ...d Calibration 11 Normal Static Source 11 Alternate Static Source 12 Altitude Correction 13 Normal Static Source Primary Flight Display 13 Normal Static Source Standby Altimeter 14 Alternate Static Source Primary Flight Display 15 Alternate Static Source Standby Altimeter 16 Stall Speeds 17 Wind Components 18 Takeoff Distance 19 Takeoff Distance 3150 lb 1429 kg 20 Takeoff Distance 2600 lb 1179 kg 2...

Page 148: ...SECTION 5 PERFORMANCE DATA CIRRUS DESIGN SR20 5 2 P N 11934 005 Landing Distance 37 Landing Distance Table Flaps 100 38 Landing Distance Table Flaps 50 39 Landing Distance Table Flaps 0 40 Reissue A ...

Page 149: ... day Flap position as well as thrust setting technique is similarly noted with each table The charts in this section provide data over temperature ranges as specified on the chart If ambient temperature is below the chart value use the lowest temperature shown to compute performance This will result in more conservative performance calculations If ambient temperature is above the chart value use c...

Page 150: ...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 33 92 198 32 26 15 1 34 93 34 94 201 31 24 11 2 36 97 36 96 205 30 22 8 3 38 100 37 98 208 29 20 4 4 40 104 38 100 212 28 18 0 6 42 108 39 102 216 27 16 3 7 44 111 40 104 219 26 14 7 8 46 115 41 106 223 ...

Page 151: ...75 39 102 4000 23 9 8 18 7 45 22 72 37 99 5000 25 13 10 14 5 41 20 68 35 95 6000 27 17 12 10 3 37 18 64 33 91 7000 29 20 14 7 1 34 16 61 31 88 8000 31 24 16 3 1 30 14 57 29 84 9000 33 27 18 0 3 27 12 54 27 81 10 000 35 31 20 4 5 23 10 50 25 77 11 000 37 35 22 8 7 19 8 46 23 73 12 000 39 38 24 11 9 16 6 43 21 70 13 000 41 42 26 15 11 12 4 39 19 66 14 000 43 45 28 18 13 9 2 36 17 63 15 000 45 49 30 ...

Page 152: ...cury Millibars Inches Of Mercury Millibars 28 0 948 29 6 1002 28 1 951 29 7 1006 28 2 955 29 8 1009 28 3 958 29 9 1012 28 4 962 30 0 1016 28 5 965 30 1 1019 28 6 968 30 2 1023 28 7 972 30 3 1026 28 8 975 30 4 1029 28 9 979 30 5 1033 29 0 982 30 6 1036 29 1 985 30 7 1040 29 2 989 30 8 1043 29 3 992 30 9 1046 29 4 995 31 0 1050 29 5 999 Reissue A ...

Page 153: ... provided for reference assuming nominal 6 0 lb gallon at 59 F 15 C U S Gallons Liters Lb Kg U S Gallons Liters Lb Kg 10 37 9 60 27 2 35 132 5 210 95 3 15 56 8 90 40 8 40 151 4 240 108 9 20 75 7 120 54 4 45 170 3 270 122 5 25 94 6 150 68 0 50 189 3 300 136 1 28 106 0 168 76 2 55 208 2 330 150 0 30 113 6 180 81 6 56 212 0 336 152 4 Reissue A ...

Page 154: ... SR20 5 8 P N 11934 005 Weight Conversion Pounds to Kilograms Pounds Kilograms Pounds Kilograms 2000 907 2 2700 1224 7 2100 952 5 2800 1270 1 2200 998 0 2900 1315 4 2300 1043 3 3000 1360 1 2400 1088 6 3100 1406 1 2500 1134 0 3150 1428 8 2600 1179 3 Reissue A ...

Page 155: ...tance Conversion Feet to Meters Feet Meters Feet Meters 10 3 600 183 20 6 700 213 30 9 800 244 40 12 900 274 50 15 1000 305 60 18 2000 610 70 21 3000 914 80 24 4000 1219 90 27 5000 1524 100 30 6000 1829 200 61 7000 2134 300 91 8000 2438 400 122 9000 2743 500 152 10 000 3048 Reissue A ...

Page 156: ...Length Conversion Inches to Centimeters Inches Centimeters Inches Centimeters 1 2 54 20 50 8 2 5 08 30 76 2 3 7 62 40 101 6 4 10 16 50 127 5 12 70 60 142 4 6 15 24 70 177 8 7 17 78 80 203 2 8 20 32 90 228 6 9 22 86 100 254 10 25 40 150 381 11 27 94 200 508 12 30 48 250 635 Reissue A ...

Page 157: ...Power for level flight or maximum continuous whichever is less NOTE Indicated airspeed values assume zero instrument error KIAS KCAS Flaps 0 Flaps 50 Flaps 100 60 57 56 57 70 68 68 70 80 79 80 80 90 89 91 89 100 100 101 99 110 111 111 111 120 121 121 130 132 131 140 142 140 150 152 149 160 163 170 173 180 183 190 193 200 203 Reissue A ...

Page 158: ...imum continuous whichever is less Heater Defroster Vents ON NOTE Indicated airspeed values assume zero instrument error KIAS KCAS Flaps 0 Flaps 50 Flaps 100 60 61 58 54 70 68 66 63 80 77 74 72 90 85 83 82 100 94 92 92 110 103 102 101 120 112 112 110 130 121 122 140 131 132 150 141 144 160 150 155 170 160 180 170 190 179 200 189 210 198 Reissue A ...

Page 159: ... obtain indicated altitude to fly Indicated airspeed values assume zero instrument error KIAS Knots Indicated Airspeed Flaps Density Alt CORRECTION TO BE ADDED ft Normal Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 0 0 0 0 0 0 0 0 0 5000 0 0 0 0 0 0 0 0 0 10000 0 0 0 0 0 0 0 0 0 15000 0 0 0 0 0 0 0 0 0 50 S L 1 6 10 11 3 26 81 5000 2 7 12 13 4 30 94 10000 2 8 13 15 4 35 110 100 S L...

Page 160: ...tude to fly Indicated airspeed values assume zero instrument error KIAS Knots Indicated Airspeed Flaps Density Alt CORRECTION TO BE ADDED ft Normal Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 12 9 5 0 11 24 38 50 61 5000 14 10 6 0 13 28 44 58 71 10000 16 12 7 0 16 33 51 68 82 15000 19 14 8 0 18 39 60 80 97 50 S L 11 3 5 11 15 1 43 5000 12 3 6 13 17 1 50 10000 15 4 7 15 20 1 59 100...

Page 161: ...cated airspeed values assume zero instrument error KIAS Knots Indicated Airspeed Flaps Density Alt CORRECTION TO BE ADDED ft Alternate Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 2 15 33 52 92 131 170 209 253 5000 3 17 39 61 107 152 197 243 294 10000 3 20 45 71 125 178 230 283 343 15000 4 23 53 83 146 209 270 332 403 50 S L 12 29 47 65 96 114 109 5000 14 34 55 75 112 133 127 10000...

Page 162: ...ted airspeed values assume zero instrument error KIAS Knots Indicated Airspeed Flaps Density Alt CORRECTION TO BE ADDED ft Alternate Static Source KIAS 60 70 80 90 100 120 140 160 180 200 0 S L 10 24 38 53 81 107 132 159 192 5000 11 28 44 61 94 124 153 184 223 10000 13 32 52 71 109 145 179 215 261 15000 15 38 61 84 128 170 210 252 306 50 S L 24 38 52 65 85 90 71 5000 28 44 60 75 98 104 83 10000 33...

Page 163: ...ft or more KIAS values may not be accurate at stall Bank Angle Deg STALL SPEEDS Flaps 0 Full Up Flaps 50 Flaps 100 Full Down KIAS KCAS KIAS KCAS KIAS KCAS 3150 lb Most FWD C G 0 71 69 67 64 62 60 15 72 70 68 66 63 61 30 76 74 71 69 65 64 45 83 82 77 77 71 71 60 98 98 90 91 85 85 3150 lb Most AFT C G 0 71 69 64 61 60 57 15 72 70 65 62 61 58 30 76 74 68 66 63 61 45 83 82 74 73 68 68 60 98 98 86 86 8...

Page 164: ...ted crosswind is 20 knots Value not considered limiting Figure 5 1 Wind Components 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 WIND 40 40 30 20 10 WIND COMPONENTS KNOTS CROSSWIND COMPONENT KNOTS 20 10 0 10 20 40 30 SR20_FM05_5335 10 20 30 50 Reissue A ...

Page 165: ...ound roll distance at Sea Level 10 of the ground roll distance at 5000 ft and 14 of the ground roll distance at 10 000 ft per each 1 of downslope CAUTION The above corrections for runway slope 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 port...

Page 166: ...43 2618 2799 2986 3179 2530 1000 Gnd Roll 1653 1784 1921 2063 2210 2363 1825 Total 2491 2675 2867 3065 3270 3482 2732 2000 Gnd Roll 1818 1962 2113 2269 2431 2599 1978 Total 2730 2932 3142 3359 3584 3817 2953 3000 Gnd Roll 2002 2161 2326 2498 2676 2862 2145 Total 2995 3217 3447 3686 3932 4187 3195 4000 Gnd Roll 2206 2381 2563 2753 2950 3154 2329 Total 3288 3532 3785 4048 4319 4599 3460 5000 Gnd Rol...

Page 167: ...3 1621 1732 1848 1967 1566 1000 Gnd Roll 1004 1083 1166 1252 1342 1435 1108 Total 1542 1656 1775 1897 2024 2154 1692 2000 Gnd Roll 1104 1192 1283 1378 1476 1578 1201 Total 1690 1815 1945 2079 2218 2361 1828 3000 Gnd Roll 1215 1312 1412 1517 1625 1738 1303 Total 1854 1991 2133 2281 2433 2590 1978 4000 Gnd Roll 1339 1446 1556 1671 1791 1915 1414 Total 2036 2186 2342 2504 2672 2844 2141 5000 Gnd Roll...

Page 168: ...ise climbs or short duration climbs are permissible at best power as long as altitudes and temperatures remain within those specified in the table For operation in air colder than this table provides use coldest data shown For operation in air warmer than this table provides use caution Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile TEMPERATURE C 20 0 20 40 50 ISA 31...

Page 169: ...75 712 653 626 727 2000 87 731 668 609 554 529 635 4000 86 624 565 511 460 436 546 6000 86 523 468 418 371 348 460 8000 85 426 376 329 285 264 378 10000 84 334 288 244 204 185 299 Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile TEMPERATURE C 20 0 20 40 50 ISA Reissue A ...

Page 170: ... remain within those specified in the table For operation in air colder than this table provides use coldest data shown For operation in air warmer than this table provides use caution Aircraft with optional Air Conditioning System Maximum rate of climb performance is reduced by approximately 75 feet per minute For maximum climb performance the Air Conditioner should be OFF Weight LB Press Alt FT ...

Page 171: ... 1109 1056 1003 976 1069 2000 87 1033 981 928 874 847 952 4000 86 906 854 800 745 718 835 6000 86 780 726 671 616 589 718 8000 85 654 599 543 487 459 602 10000 84 527 471 415 358 329 486 Weight LB Press Alt FT Climb Speed KIAS RATE OF CLIMB Feet per Minute TEMPERATURE C 20 0 20 40 50 ISA Reissue A ...

Page 172: ...duration climbs are permissible at best power as long as altitudes and temperatures remain within those specified in the table For operation in air colder than this table provides use coldest data shown For operation in air warmer than this table provides use caution Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile TEMPERATURE C 20 0 20 40 50 ISA 3150 SL 97 646 583 526...

Page 173: ... For operation in air colder than this table provides use coldest data shown For operation in air warmer than this table provides use caution Aircraft with optional Air Conditioning System Maximum rate of climb performance is reduced by approximately 75 feet per minute if system is ON For maximum climb performance the Air Conditioner should be OFF 2600 SL 93 857 780 710 645 615 727 2000 92 737 666...

Page 174: ...719 657 596 535 505 636 6000 94 594 532 469 407 376 522 8000 94 469 405 341 278 247 408 10000 93 344 278 212 148 116 294 12000 92 218 150 83 17 15 180 14000 91 91 21 48 115 148 66 2600 SL 97 1279 1211 1143 1075 1041 1160 2000 96 1133 1065 995 927 893 1026 4000 95 988 918 848 778 744 893 6000 94 842 771 699 629 594 760 8000 94 697 624 551 479 444 627 10000 93 551 476 402 329 293 494 12000 92 405 32...

Page 175: ...Placard Flaps 0 UP Airspeed Best Rate of Climb Figure 5 2 Enroute Rate of Climb Vs Density Altitude 1 0 0 2 6 0 0 L B 3 1 5 0 L B 15 000 14 000 13 000 12 000 11 000 10 000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 1 2 0 0 1 1 0 0 1 0 0 0 9 0 0 8 0 0 7 0 0 6 0 0 5 0 0 4 0 0 3 0 0 2 0 0 0 Rate of Climb Feet Per Minute Density Altitude Feet SR20_FM05_5418 Reissue A ...

Page 176: ...r short duration climbs are permissible at best power as long as altitudes and temperatures remain within those specified in the table 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 97 864 0 0 0 0 0 1000 13 96 807 1 2 0 4 2 2000 11 96 750 2 6 0 8 4 3000 9 95 693 4 0 1 3 7 4000 7 95 636 5 6 1 7 9 5000 5 95 579 ...

Page 177: ... ISA 30 C PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH 2000 2700 27 1 94 151 16 5 90 156 15 8 85 158 15 2 2500 27 1 86 148 14 9 82 151 14 2 78 153 13 7 2500 26 0 81 145 14 2 77 148 13 6 73 150 11 5 2500 24 9 77 142 13 5 73 144 12 3 69 146 10 9 2500 23 8 72 139 13 3 68 140 11 6 65 142 10 3 2500 22 7 67 135 12 5 64 136 10 9 61 138 9 7 2500 21 6 62 130 11 7 59 132 10 3 56 132 9 1 2500 20 5 58 126 11 0 55 1...

Page 178: ...8 50 131 7 8 2500 17 2 50 124 9 3 48 124 8 1 45 124 7 2 2500 16 1 45 117 8 6 43 117 7 5 41 116 6 7 10000 2700 20 0 71 148 12 7 67 150 11 0 64 151 9 7 2500 20 0 65 142 11 5 61 144 10 0 58 145 8 8 2500 18 9 60 138 10 7 56 139 9 3 54 139 8 2 2500 17 8 55 132 9 9 52 133 8 6 49 133 7 6 2500 16 7 50 126 9 1 47 126 8 0 45 126 7 1 2500 15 6 45 119 8 4 43 118 7 3 41 117 6 5 12000 2700 18 5 66 146 11 7 62 1...

Page 179: ...e is decreased by 5 if nose wheel pant and fairings removed Range is decreased by 15 if nose and main wheel pants and fair ings removed Aircraft with optional Air Conditioning System Range is decreased by 1 if system in operation For maximum range the Air Conditioner should be OFF 75 POWER Mixture Target Fuel Flow Press Alt FT Climb Fuel GAL Fuel Remaining For Cruise GAL Airspeed KTAS Fuel Flow GP...

Page 180: ...3 4 6000 2 8 45 5 143 10 3 4 4 643 13 8 8000 4 1 44 3 145 10 2 4 3 655 14 4 10000 5 7 42 7 12000 8 2 40 4 14000 13 6 35 0 55 POWER Mixture Target Fuel Flow Press Alt FT Climb Fuel GAL Fuel Remaining For Cruise GAL Airspeed KTAS Fuel Flow GPH Endurance HOURS Range NM Specific Range NM GAL 0 0 0 47 9 125 9 5 5 1 630 13 2 2000 0 8 47 2 127 9 3 5 1 651 13 7 4000 1 7 46 4 130 9 1 5 1 670 14 2 6000 2 8 ...

Page 181: ... required data for certification However significantly better performance can be achieved by climbing at Best Rate of Climb speeds shown with flaps down or following the Balked Landing Go Around procedure in Section 4 Weight LB Press Alt FT Climb Speed KIAS CLIMB GRADIENT Feet per Nautical Mile TEMPERATURE C 20 0 20 40 50 ISA 3150 SL 78 695 606 526 454 421 546 2000 78 559 479 407 341 310 438 4000 ...

Page 182: ...ble provides use caution This chart is required data for certification However significantly better performance can be achieved by climbing at Best Rate of Climb speeds shown with flaps down or following the Balked Landing Go Around procedure in Section 4 Weight LB Press Alt FT Climb Speed KIAS RATE OF CLIMB Feet per Minute TEMPERATURE C 20 0 20 40 50 ISA 3150 SL 78 840 763 687 613 577 706 2000 78...

Page 183: ...ce Grass Runway Wet Add 60 to ground roll distance Sloped Runway Increase table distances by 27 of the ground roll distance per each 1 of downslope Decrease table distances by 9 of the ground roll distance per each 1 of upslope CAUTION The above corrections for runway slope are required to be included herein These corrections should be used with caution since published runway slope data is usually...

Page 184: ... 2779 2838 2898 2682 2000 Gnd Roll 870 901 933 965 997 1029 905 Total 2666 2725 2785 2846 2907 2970 2731 3000 Gnd Roll 902 935 968 1001 1034 1067 932 Total 2726 2788 2852 2916 2981 3048 2782 4000 Gnd Roll 936 971 1005 1039 1073 1108 960 Total 2790 2856 2923 2991 3060 3130 2837 5000 Gnd Roll 972 1007 1043 1079 1114 1150 990 Total 2858 2928 2999 3070 3143 3217 2894 6000 Gnd Roll 1009 1046 1083 1120 ...

Page 185: ...2974 3044 3115 2856 2000 Gnd Roll 1106 1147 1187 1228 1268 1309 1151 Total 2837 2908 2980 3053 3127 3202 2915 3000 Gnd Roll 1148 1190 1232 1274 1316 1358 1186 Total 2909 2984 3060 3137 3216 3295 2977 4000 Gnd Roll 1191 1234 1278 1322 1365 1409 1222 Total 2987 3066 3146 3227 3309 3392 3042 5000 Gnd Roll 1236 1281 1327 1372 1417 1462 1259 Total 3069 3152 3236 3322 3408 3496 3111 6000 Gnd Roll 1283 1...

Page 186: ...252 3325 3399 3130 2000 Gnd Roll 1274 1321 1368 1414 1461 1508 1326 Total 3109 3183 3258 3335 3412 3490 3191 3000 Gnd Roll 1322 1371 1419 1467 1516 1564 1366 Total 3185 3263 3342 3422 3504 3586 3256 4000 Gnd Roll 1372 1422 1472 1523 1573 1623 1408 Total 3265 3348 3431 3515 3601 3688 3323 5000 Gnd Roll 1424 1476 1528 1581 1633 1685 1451 Total 3351 3437 3525 3614 3704 3795 3395 6000 Gnd Roll 1479 15...

Page 187: ...E SR20 Section 6 Weight and Balance Table of Contents Introduction 3 Weight and Balance Record 3 Weight and Balance Data 3 Loading Instructions 4 Weight and Balance Loading Form 5 Loading Data 6 Moment Limits 7 Weight Balance Record 8 Equipment List 8 Reissue A ...

Page 188: ...SECTION 6 WEIGHT AND BALANCE CIRRUS DESIGN SR20 6 2 P N 11934 005 Reissue A Intentionally Left Blank ...

Page 189: ...e that the airplane is loaded prop erly and that all changes to the basic empty weight and center of gravity are recorded Figure 6 1 Airplane Weighing Basic empty weight moment and center of gravity are provided in inches aft of datum where 0 inches datum is 100 0 inches forward of the cabin fire wall CG can also be expressed in terms of its location as a percentage of the airplane Mean Aerodynami...

Page 190: ...0 for the rear seat occupants from the Loading Data Figure 6 3 4 Baggage Enter weight and moment for the baggage from the Loading Data Figure 6 3 NOTE 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 Enter the weight and moment of usable fuel loaded on the airplane from the Loading...

Page 191: ...ope refer to Section 2 Limitations Serial Num Date Reg Num Initials Figure 6 2 Weight Balance Loading Form 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 ...

Page 192: ...t Pass FS 180 0 Baggage FS 208 0 Fuel FS 153 8 Weight LB Fwd Pass FS 143 5 Aft Pass FS 180 0 Fuel FS 153 8 20 2 87 3 60 4 16 3 10 220 31 57 39 60 34 08 40 5 74 7 20 8 32 6 20 240 34 44 43 20 37 18 60 8 61 10 80 12 48 9 29 260 37 31 46 80 40 27 80 11 48 14 40 16 64 12 39 280 40 18 50 40 43 37 100 14 35 18 00 20 80 15 49 300 43 05 54 00 46 47 120 17 22 21 60 24 96 18 59 320 45 92 57 60 49 57 140 20 ...

Page 193: ...s Chart 480 460 Moment 1000 SR20_FM06_5341 Weight Pounds 2000 2200 2400 2600 2800 3000 3200 300 320 340 360 380 400 420 440 Weight LB Moment 1000 Weight LB Moment 1000 Minimum Maximum Minimum Maximum 2200 304 326 2700 375 398 2250 311 333 2750 383 406 2300 318 341 2800 390 414 2350 326 348 2850 398 421 2400 333 354 2900 406 429 2450 340 362 2950 414 437 2500 347 369 3000 421 444 2550 354 375 3050 ...

Page 194: ...ructure or equipment affecting weight and balance Figure 6 5 Weight Balance Record Form Equipment List This list will be determined after the final equipment has been installed in the aircraft 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 Reissue...

Page 195: ...nsole Arrangement 13 Bolster Panel Arrangement 13 Flight Instruments 16 Attitude Indicator 18 Airspeed Indicator 19 Altimeter 20 Horizontal Situation Indicator 21 Vertical Speed Indicator 22 Magnetic Compass 22 Wing Flaps 22 Flap Control Switch 23 Landing Gear 25 Main Gear 25 Nose Gear 25 Brake System 25 Baggage Compartment 26 Baggage Tie Downs Cargo Net 26 Seats 27 Front Seats 27 Rear Seats 28 Se...

Page 196: ...ixture Management 45 Electrical System 46 Power Generation 46 Power Distribution 48 Electrical System Protection 49 Electrical System Control 52 Ground Service Receptacle 53 Electrical Indicating 53 Lighting Systems 56 Exterior Lighting 56 Interior Lighting 56 Convenience Lighting 57 Environmental System 59 Distribution 62 Heating 62 Cooling 62 Airflow Selection 63 Vent Selection 63 Temperature Se...

Page 197: ...upport Equipment 87 Cabin Features 89 Emergency Locator Transmitter ELT 89 Fire Extinguisher 91 Hour Meters 92 Emergency Egress Hammer 92 Convenience Outlet s 92 Cirrus Airframe Parachute System 93 System Description 93 Activation Handle 94 Deployment Characteristics 95 Reissue A ...

Page 198: ...SECTION 7 AIRPLANE AND SYSTEMS CIRRUS DESIGN SR20 7 4 P N 11934 005 Reissue A Intentionally Left Blank ...

Page 199: ...foam core composite with access to under floor compo nents All flight and static loads are transferred to the fuselage structure from the wings and control surfaces through four wing attach points in two locations under the front seats and two locations on the sidewall just aft of the rear seats The lower firewall employs a 20 bevel to improve crashworthiness In addition an avionics bay is located...

Page 200: ...ot The control system uses a combination of push rods cables and bell cranks for control of the surfaces 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 sec...

Page 201: ...ff trim is 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 airplane 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 TRIM circuit breaker on ESS BUS...

Page 202: ...SECTION 7 AIRPLANE AND SYSTEMS CIRRUS DESIGN FLIGHT CONTROLS SR20 7 8 P N 11934 005 Figure 7 1 Elevator System SR20_FM07_5343 Reissue A ...

Page 203: ...ctric motor The electric roll trim is also used by the autopilot to position the ailerons It is possible to easily override full trim or autopilot inputs by using normal control inputs A ground adjustable trim tab is installed on the right aileron to provide small adjustments in neutral trim This tab is factory set and does not normally require adjustment An electric motor changes the neutral posi...

Page 204: ...SECTION 7 AIRPLANE AND SYSTEMS CIRRUS DESIGN FLIGHT CONTROLS SR20 7 10 P N 11934 005 Figure 7 2 Aileron System SR20_FM07_5345 Reissue A ...

Page 205: ...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 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 def...

Page 206: ...SECTION 7 AIRPLANE AND SYSTEMS CIRRUS DESIGN FLIGHT CONTROLS SR20 7 12 P N 11934 005 Figure 7 3 Rudder System SR20_FM07_5346 Reissue A ...

Page 207: ... on the left side of the instrument panel The cabin environmental control switches are located on the right side of the instrument panel Instrument panel air vents are located on the outboard sections of the panel Center Console Arrangement A center console contains the Flight Management System Keyboard auto pilot and audio controls flap system control and indication fuel selector valve and the po...

Page 208: ...ake 17 Flight Instrument Panel 18 Bolster Switch Panel 19 Start Ignition Key Switch 20 Primary Flight Display 21 Overhead Light Switch LEGEND 1 Cirrus Airframe Parachute System CAPS Activation T Handle Cover 2 Magnetic Compass 3 Multifunction Display 4 Fresh Air Eyeball Outlet 5 Temperature Ventilation Controls 6 Control Yoke 7 ADF opt 8 Conditioned Air Outlet 9 Rudder Pedals 10 Flap Control Posit...

Page 209: ...ke 17 Flight Instrument Panel 18 Bolster Switch Panel 19 Start Ignition Key Switch 20 Primary Flight Display 21 Overhead Light Switch LEGEND 1 Cirrus Airframe Parachute System CAPS Activation T Handle Cover 2 Magnetic Compass 3 Multifunction Display 4 Fresh Air Eyeball Outlet 5 Temperature Ventilation Controls 6 Control Yoke 7 ADF opt 8 Conditioned Air Outlet 9 Rudder Pedals 10 Flap Control Positi...

Page 210: ...struments for airspeed attitude and altitude are mounted on the LH bolster panel and are powered independently of the PFD Knobs knob sets and membrane type push button switches are located along the inboard edge of the PFD and MFD and provide control for communication COM navigation NAV heading HDG barometric pressure set BARO and various Flight Management functions For elec trical requirements an...

Page 211: ...lected Altitude 11 Vertical Speed Indicator VSI 12 Current Heading 13 Lubber Line 14 Selected Heading Bug 15 Flight Phase 16 Navigation Source 17 Aircraft Symbol 18 Course Deviation Scale 19 Rotating Compass Rose 20 Course Pointer 21 To From Indicator 22 Course Deviation Indicator 23 Current Track Indicator 24 Turn Rate Heading Trend Vector 25 Turn Rate Indicator Typical View N W S E 6 3 3 3 3 0 2...

Page 212: ...ication of flight attitude Bank attitude is indicated by a pointer at the top of the indicator relative to the bank scale with index marks at 10 20 30 60 and 90 either side of the center mark A fixed miniature airplane superimposed over a movable mask containing a white symbolic horizon bar which divides the mask into two sections indicates pitch and roll attitudes The upper blue sky section and t...

Page 213: ... Speeds above the never exceed speed appear in the high speed warning range represented on the airspeed tape by red white barber pole coloration Calculated true airspeed is displayed in window at the bottom edge of the airspeed tape Airspeed trend is also displayed as a bar along side of the airspeed tape Standby Airspeed Indicator Serials w o MD302 Standby Attitude Module The standby airspeed ind...

Page 214: ...tude is corrected for static source position error normal static source 0 flaps the altitude calibration errors for the PFD are zero with flaps up and normal source typical cruise flight Calibration corrections are only necessary when flaps are extended or the alternate static source is selected Standby Altimeter Serials w o MD302 Standby Attitude Module Airplane altitude is depicted on a conventi...

Page 215: ... altitudes and high airspeeds where the position error corrections are the highest Horizontal Situation Indicator The horizontal situation indicator is displayed along the lower center of the PFD Heading data is provided by the Attitude and Heading Reference System AHRS and the onboard magnetometers The HSI displays a rotating compass card in a heading up orientation Letters indicate the cardinal ...

Page 216: ...appears at the corresponding edge of the tape and the rate appears inside the pointer Serials w MD302 Standby Attitude Module The Altitude Trend Bar is located along the right margin of the Altitude Display This feature is optional and can be turned on or off by the user Magnetic Compass A conventional internally lighted liquid filled magnetic compass is installed on the cabin headliner immediatel...

Page 217: ...e bottom of the vertical section of the center console The control switch is marked and has detents at three positions UP 0 50 and 100 The appropriate VFE speed is marked at the Flap 50 and 100 switch positions Setting the switch to the desired position will cause the flaps to extend or retract to the appropriate setting An indicator light at each control switch position illu minates when the flap...

Page 218: ...SECTION 7 AIRPLANE AND SYSTEMS CIRRUS DESIGN WING FLAPS SR20 7 24 P N 11934 005 Figure 7 6 Wing Flaps SR20_FM07_5350 Reissue A ...

Page 219: ...erential application of individual main gear brakes Each nosewheel has a 5 00 x 5 tubeless tire installed Brake System The main wheels have hydraulically operated single disc type brakes indi vidually activated by floor mounted toe pedals at both pilot stations A parking brake mechanism holds induced hydraulic pressure on the disc brakes for parking The brake system consists of a master cylinder f...

Page 220: ...e parking brake valve holds applied brake pressure locking the brakes To apply the parking brake set the brakes with the rudder pedal toe brakes and then pull the PARK BRAKE handle aft Baggage Compartment The baggage compartment door located on the left side of the fuselage aft of the wing allows entry to the baggage compartment The baggage door is hinged on the forward edge and latched on the rea...

Page 221: ...ssengers CAUTION Do not kneel or stand on the seats The seat bottoms have an inte gral aluminum honeycomb core designed to crush under impact to absorb downward loads Front Seats The front seats are adjustable fore and aft and the seat backs can be reclined for passenger comfort or folded forward for rear seat access Integral head rests are provided The fore and aft travel path is adjusted through...

Page 222: ...controlled through a lever located on either side of the seat 1 With no pressure on the seat back rotate the lever to the recline posi tion and fold the seat back forward Seat Belt and Shoulder Harness Integrated seat belt and shoulder harness assemblies with inertia reels are provided for the pilot and each passenger The front seats use a 4 point inflatable restraint system Forward seat belts are...

Page 223: ... occupant s shoulder and restraint harness shoulder strap Stow the seat belts in the latched position when not in use 1 Slip arms behind the harness so that the harness extends over shoul ders 2 Hold the buckle and firmly insert the link 3 Grasp the seat belt tabs outboard of the link and buckle and pull to tighten Buckle should be centered over hips for maximum comfort and safety 4 Restraint harn...

Page 224: ... bulkhead anchor 5 Firmly tension the child seat straps according to the manufacturer s instructions To Install Child Seat Serials w Observer s Seat The aircraft is equipped with provisions for installing a single LATCH compliant child seat in the Observer s seat Lower anchors for the LATCH compliant seat is located in the outboard seat position A top tether anchor for the child seat is located on...

Page 225: ... device must accept any interference received including interfer ence that may cause undesired operation NOTE Key fob will not actuate door locks when BAT 1 switch is ON Windshield and Windows The windshield and side windows are manufactured of acrylic Use only clean soft cloths and mild detergent to clean acrylic surfaces Refer to Section 8 Exterior Windshield and Windows for detailed cleaning in...

Page 226: ... the console allows the pilot to manually lean the mixture for a specific power setting or fuel consumption The mixture control lever is mechanically linked to a sliding valve inside the fuel servo The pressure regulator within the servo functions to maintain a differential pressure across the fuel metering jet in proportion to the volume of airflow The mixture control allows the pilot to effectiv...

Page 227: ...gine System Annunciations Engine system health caution and warning messages are displayed in color coded text in the Crew Alerting System CAS window located to the right of the Altimeter and Vertical Speed Indicator In combination with a CAS alert the affected engine parameter displayed on the ENGINE page changes to the corresponding color of CAS alert and the annunciation system issues an audio a...

Page 228: ...3 4 5 6 2 8 Engine Instruments Engine Controls 9 10 7 LEGEND 1 Percent Power 2 CHT 3 Tachometer 4 EGT 5 Manifold Pressure 6 Oil Temperature and Pressure 7 Alternate Air Control 8 Power Lever 9 Friction Control 10 Mixture Control SR20_FM07_5394 ON BOOST PUMP OFF TURN BOOST PUMP ON DURING TAKEOFF CLIMB MANEUVERING FLIGHT LANDING AND SWITCHING FUEL TANKS Reissue A ...

Page 229: ...peratures for all four cylinders are displayed in the Engine Temperature block of the ENGINE page as vertical bars The CHT graph is marked from 100 F to 500 F in 100 F increments The digital CHT value of the cylinder is displayed above the bar in white numerals A sensor in each cylinder head measures cylinder head temperature and provides a voltage signal to the Engine Airframe Unit which processe...

Page 230: ...r temperature pressure altitude engine speed and fuel flow Engine Lubrication System The engine is provided with a wet sump high pressure oil system for engine lubrication and cooling Oil for engine lubrication is drawn from a seven quart capacity sump through an oil suction strainer screen through the remotely mounted oil cooler and then directed to a full flow oil filter The oil cooler is equipp...

Page 231: ...ombustion chambers Should the dry induction filter become clogged a pilot controlled alternate induc tion air door can be opened allowing engine operation to continue For additional information on the Alternate Air Control refer to Engine Controls Alternate Air Control description in this section Engine Exhaust Engine exhaust gases are routed through an exhaust system After leaving the cylinders e...

Page 232: ...al composite three blade 74 diameter propeller The propeller governor automatically adjusts propeller pitch to regulate propeller and engine RPM The propeller governor senses engine speed by means of flyweights and senses throttle setting through a cable connected to the power throttle control lever in the cockpit The propeller governor boosts oil pressure in order to regulate propeller pitch posi...

Page 233: ...through strainers and a flapper valve to the associ ated collector tank 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 tanks through a three position LEFT RIGHT OFF selector valve The selector valve allows tank selection From the fuel pump the fuel is metered...

Page 234: ...om the left tank RIGHT Allows fuel to flow from the right tank OFF Cuts off fuel flow from both tanks The valve is arranged so that to feed off a particular tank the valve should be pointed to the fuel indicator for that tank To select RIGHT or LEFT rotate the selector to the desired position To select Off first raise the fuel selector knob release and then rotate the knob to OFF Fuel Pump Operati...

Page 235: ...AUXILIARY PUMP R WING COLLECTOR VENT FILLER R WING TANK SELECTOR VALVE FILLER FEED RETURN LEFT RIGHT FEED RETURN SELECTOR VALVE OPERATIO N FUEL ANNUNCIATOR MFD INDICATION FUEL PUMP DRAIN 5 PLACES FIREWALL VENT L WING TANK L WING COLLECTOR MIXTURE CONTROL FLAPPER VALVE FLAPPER VALVE OFF FUEL FLOW INDICATOR FUEL SERVO INJECTOR MANIFOLD INJECTOR MANIFOLD SR20_FM07_5373 Reissue A ...

Page 236: ...f the PFD The LEFT pointer indicates left tank fuel quantity and sweeps a vertical bar scale marked from 0 to 28 U S gallons in 5 gallon increments The RIGHT pointer sweeps an identical scale for the right tank Each scale is marked with a yellow band from 0 to 8 2 U S gallons and a green band from 8 2 to 28 U S gallons The indicators are calibrated to read 0 gallons when no usable fuel remains Fue...

Page 237: ... to Full or to Tabs buttons is also available Fuel System Annunciations Fuel system health caution and warning messages are displayed in color coded text in the Crew Alerting System CAS window located to the right of the Altimeter and Vertical Speed Indicator In combination with a CAS alert the affected fuel parameter displayed on the ENGINE page changes to the corresponding color of CAS alert and...

Page 238: ... Fuel Flow Gauge 2 Fuel Calculations Fuel At Destination Totalizer Fuel Used Totalizer Fuel Remaining Totalizer Time Remaining Totalizer Fuel Range Totalizer Nautical Miles Per Gallon Totalizer 3 Fuel Quantity Gauge Float Sensor 4 Fuel Pump Switch 5 Fuel Selector Valve 5 Engine Controls SR20_FM07_5395 TURN BOOST PUMP ON DURING TAKEOFF CLIMB MANEUVERING FLIGHT LANDING AND SWITCHING FUEL TANKS BOOST...

Page 239: ... Follow the placarded MAX power fuel flow leaning schedule and informa tion published in this POH Refer to Section 4 Normal Procedures The top of the green arc on the display may be used as a reference EGT s should generally be at least 1300 F at full power If CHTs or oil temps become higher than desired using a slightly richer than placarded fuel flow will aid in engine cooling During cruise flig...

Page 240: ...lectrical power storage Alternator 1 ALT 1 is a belt driven internally rectified 100 amp alter nator mounted on the right front of the engine Alternator 2 ALT 2 is a belt driven internally rectified 70 amp alternator mounted on the front left of the engine ALT 1 is regulated to 27 7 volts and ALT 2 is regulated to 28 7 volts Both alternators require battery voltage for field excitation in order to...

Page 241: ...CH DME ADF AVIONICS BUS AUDIO PANEL DATA LINK WEATHER TRAFFIC XPONDER STDBY ATTD B MFD B MAIN BUS 1 CABIN LIGHTS FUEL QTY KEYPADS AP CTRL AP SERVOS AVIONICS ICE LIGHTS ESSENTIAL BUS 2 ENGINE INSTR STALL WARNING PITCH TRIM ROLL TRIM GPS NAV GIA 1 COM 1 ESSENTIAL BUS 1 ADAHRS 1 PFD A STDBY ATTD A ESSENTIAL POWER BAT 2 A C BUS 1 A C COND ALT 1 GPS NAV GIA 2 COM 2 MAIN BUS 2 ADAHRS 2 PFD B FUEL PUMP A...

Page 242: ...n distribution buses are interconnected by an 80 amp fuse and a diode The diode prevents ALT 2 from feeding the Main Distribution Bus 1 Addi tionally since ALT 2 Bus voltage is slightly higher than ALT 1 voltage bus separation is further assured Essential Distribution Bus The Essential Distribution Bus is fed by both Main Distribution Bus 1 and Main Distribution Bus 2 in the MCU through two 50 amp...

Page 243: ...oltage discharge across the avionics and electrical systems of the airplane By adding a high power TVS at key power entry points on the electrical buses unwanted energy from electrical transients is allowed to dissipate through a semi conducting pathway to ground CAUTION If smoke and or fumes are detected in the cabin and it is suspected that this event was caused by a TVS failure the operator sho...

Page 244: ... will power MAIN BUS 3 ALT 2 is prevented from powering MAIN BUS 3 by the isolation diode intercon necting the MCU distribution buses 1 and 2 Non Essential Buses The circuit breaker panel NON ESS BUS is powered by ALT 2 from the MCU Main Distribution Bus 2 and in the event of ALT 2 failure by ALT 1 and BAT 1 from the Main Distribution Bus 2 via the diode intercon necting the MCU distribution buses...

Page 245: ... FAN 1 NAV LIGHTS STROBE LIGHTS PITOT HEAT FLAPS AVIONICS FAN 2 GPS NAV GIA 2 COM 2 ADAHRS 2 FUEL PUMP PFD B MFD A LANDING LIGHTS A C COMPR SR20_FM07_5370 BAT 2 GPS NAV GIA 1 COM 1 ADAHRS 1 STDBY ATTD A PFD A PITCH TRIM ROLL TRIM ENGINE INSTR ALT2 STALL WARNING ESSENTIAL POWER DME ADF AUDIO PANEL DATA LINK WEATHER TRAFFIC AP SERVOS FUEL QTY MFD B STDBY ATTD B CABIN LIGHTS KEYPADS AP CTRL XPONDER I...

Page 246: ...on the remaining systems will be energized To check or use non essential avionics equipment or radios while on the ground the AVIONICS master switch must also be turned on Alternator Switches The ALT 1 and ALT 2 switches control field power to the respective alter nator For ALT 1 to start the BAT 1 switch must be on Setting the ALT 1 switch on energizes a relay allowing 28 VDC from the 5 amp ALT 1...

Page 247: ...Indicating Electrical system information is displayed as bar graphs and text on the MFD s ENGINE page When the ENGINE page is not active or in the case of an electronic display failure backup mode Battery 1 ampere output and Essential Bus voltage output are displayed along the LH edge of the display Electrical data is acquired by the Engine Airframe Unit which transmits the data to the Engine Indi...

Page 248: ... Section 3A Abnormal Procedures Electrical System For additional information on Engine Instrument Markings and Annunciations refer to Section 2 Limitations For additional information on the System Annunciations And Alerts refer to the Perspective Integrated Avionics System description in this section Reissue A ...

Page 249: ... Essential Main Bus Voltage 2 Alternator Battery Current 3 Battery 2 4 Battery 1 5 Alternator 1 6 Alternator 2 Density Alt 8000 Ft Oat 31 F 1 C ISA 0 C 1 3 4 7 6 Electrical System Indication 2 7 Avionics 8 Navigation 9 Strobe 10 Landing Light 11 Panel Dimmer 12 Instrument Dimmer SR20_FM07_5385 Electrical and Lighting Controls 5 8 9 10 12 11 Reissue A ...

Page 250: ...lly counterclockwise all systems revert to daytime lighting in this position not full DIM In daytime lighting knob OFF full counterclockwise Standby instruments all Avionics system keypads and the bolster switch panel are unlit MFD and PFD screen illumination is controlled by automatic photo cell providing full brightness in high light conditions only slightly reduced by darkness ECS and control p...

Page 251: ... cabin light switch located next to the light assembly on the ceiling of the airplane The dome light is powered by 28 VDC supplied through the 5 amp CABIN LIGHTS circuit breaker on MAIN BUS 1 Convenience Lighting Serials w Convenience Lighting The convenience lighting option consists of the overhead dome light over head baggage compartment lights interior footwell lights exterior entry step lights...

Page 252: ...rtment lights will turn on when baggage door is opened and will turn off when baggage door is closed When the cabin light switch is in the OFF position Dome light baggage compartment lights footwell lights and entry step lights will turn off When the cabin light switch is in the AUTO position Dome light footwell lights and entry step lights will turn on when either cabin door is opened or the door...

Page 253: ...ature control An optional 3 speed blower fan is available to supplement airflow when ram air may be inadequate such as during ground operation 28 VDC for Environmental System Control Panel operation is supplied through the 2 amp CABIN AIR CONTROL circuit breaker on MAIN BUS 1 The optional Blower Fan is powered by 28 VDC supplied through a 15 amp CABIN FAN circuit breaker on A C BUS 2 Serials w Opt...

Page 254: ...R FLOW VALVE HOT AIR VALVE SR20_FM07_5353 RAM AIR RAM AIR FRESH AIR VALVE HEAT EXCHANGER FOOT WARMER DIFFUSER DISTRIBUTION MANIFOLD FAN ASSEMBLY NOTE Illustration depicts maximum cabin cooling airflows and selector settings with optional Fan installation PANEL AIRFLOW CONTROL PANEL WINDSHIELD DIFFUSER AIR GASPER MIXING CHAMBER SERVO MOTOR Reissue A ...

Page 255: ...NTROL PANEL AIR GASPER AIR FLOW VALVE RAM AIR RAM AIR FRESH AIR VALVE HOT AIR VALVE HEAT EXCHANGER S P S P EVAPORATOR ASSEMBLY COMPRESSOR RECIRCULATION CHECK VALVE CONDENSER ASSEMBLY NOTE llustration depicts maximum cabin cooling airflows and selector settings while on ground or warm outside air temperatures FLOOR AIRFLOW WINDSHIELD DIFFUSER SR20_FM07_5356 MIXING CHAMBER SERVO MOTOR Reissue A ...

Page 256: ...k plate The passenger panel air vents are chest high outlets mounted in the armrests integral to the LH and RH cabin wall trim panels The passenger floor air vents are mounted to the bottom portion of the LH and RH cabin wall trim panels The windshield diffuser located in the glareshield assembly directs conditioned air to the base of the windshield Heating Ram air from the NACA inlet flows throug...

Page 257: ...ontrol panel regulates the volume of airflow allowed into the cabin distribution system When the airflow selector is moved past the OFF position an electro mechanical linkage actuates a valve in the mixing chamber on the forward firewall to the full open position The air is then distributed by either ram air or blower fan to the distribution manifold mounted to the center aft side of the firewall ...

Page 258: ...rclockwise cooler air On airplane with the optional Air Conditioning System installed when the air conditioning button snowflake is pushed the valve on the firewall completely closes and the air conditioner is activated When recirculation button is pushed the fresh air valve completely closes and cabin air is recir culated to provide for maximum air conditioning operation When the air conditioning...

Page 259: ...nical linkage actuates the hot air valve to the full open position and the 3 speed blower fan is turned on Shared airflow to the defroster cabin floor and panel outlets Maximum airflow to the rear seat foot warmer diffusers and the front seat kickplate outlets Maximum airflow to the panel and armrest air gaspers Maximum airflow to defroster Rotating the selector simultaneously opens and closes the...

Page 260: ...ll be annunciated and the aural stall warning is muted until the fault clears The system operates on 28 VDC supplied though the 2 amp STALL WARNING circuit breaker on ESS BUS 2 Pitot Static System The Pitot Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage The Pitot heat is pilot controlled through a panel mounted switch An ...

Page 261: ... Alternate Static Source An alternate static pressure source valve is installed on the switch and control panel to the right of the pilot s leg This valve supplies static pres sure from inside the cabin instead of the external static port If erroneous instrument readings are suspected due to water or ice in the pressure line going to the standard external static pressure source the alternate stati...

Page 262: ...ic System Serials w o MD302 1 of 2 PITOT HEAT Annunciation ENGINE AIRFRAME UNIT STATIC BUTTONS ADAHRS 1 ADAHRS 2 optional AIRSPEED INDICATOR PITOT MAST PITOT STATIC WATER TRAPS ALTERNATE STATIC AIR SOURCE ALTIMETER LOGIC CURRENT SENSOR HEATER 7 5A PITOT HEAT CB PITOT HEAT SW PFD Air Data SR20_FM07_5383 Reissue A ...

Page 263: ...ic System Serials w MD302 2 of 2 STATIC BUTTONS MD302 STANDBY ATTITUDE MODULE PITOT MAST PITOT STATIC WATER TRAPS ALTERNATE STATIC AIR SOURCE LOGIC CURRENT SENSOR HEATER 7 5A PITOT HEAT CB PITOT HEAT SW ADAHRS 1 PFD Air Data ADAHRS 2 optional PITOT HEAT Annunciation ENGINE AIRFRAME UNIT SR20_FM07_5384 Reissue A ...

Page 264: ...nits GEA 71 71B Engine Airframe Unit GTX 335 Mode S or GTX 345 Mode S UAT in optional Transponder GMA 350 or 350c optional Audio Panel w Marker Beacon Receiver GFC 700 Autopilot and GMC 707 Mode Controller GSR 56 Iridium Global Satellite Datalink optional GDL 69A XM Satellite Weather Radio Receiver optional Flight Stream 510 Wireless Avionics Interface optional GTS 800 Traffic Advisory System opti...

Page 265: ...ICS UNIT 1 AUDIO PANEL GATEWAY MODULE optional ENGINE AIRFRAME UNIT PITCH TRIM ADAPTER ROLL SERVO PITCH SERVO IRIDIUM GLOBAL SATELLITE DATALINK optional ADAHRS 1 AUTOPILOT MODE CONTROLLER optional MAG 1 MAG 2 INTEGRATED AVIONICS UNIT 2 PFD MFD ADAHRS 2 optional FMS KEYBOARD XM SATELLITE DATA LINK RECEIVER optional 1 1 NOTE Serials w GTX 345 SR20_FM07_5362A Reissue A ...

Page 266: ...0 seconds from battery turn on Display Backup Mode In the event of a detected display failure the Integrated Avionics System automatically switches to Display Backup Mode In Display Backup Mode all essential flight information from the PFD is presented on the remaining display in the same format as in normal operating mode with the addition of the Engine Indicating System The change to backup is c...

Page 267: ...rplane attitude and heading information to both the PFD and the primary ADC The AHRS contains advanced sensors including accelerometers and rate sensors and interfaces with the primary Magnetometer to obtain magnetic field information the ADC to obtain air data and both Integrated Avionics Units to obtain GPS informa tion The ADC processes data from the Pitot Static system and outside air temperat...

Page 268: ...quency Transfer 121 5 Emer Tune 7 COM Volume and Squelch 8 Display Backup Selection 9 NAV and ID Audio Volume 10 NAV Frequency Transfer 11 NAV Transceiver Selection Tune 2 13 14 15 3 4 5 6 7 8 9 10 12 19 20 21 1 17 18 16 SR20_FM07_5388 12 MFD 13 PFD Direct to Course 14 PFD Flight Plan Page 15 PFD Clear Cancel Information 16 PFD Flight Management System 17 GMC 707 Mode Controller 18 Audio Panel 19 ...

Page 269: ...MFD Direct to Course 25 MFD Menu 26 MFD Procedures 27 MFD Enter Key 28 COM Tuning Mode 29 FMS Mode 30 Transponder Mode Ident 31 NAV Tuning Mode 32 MFD Range Pan Joystick 33 Frequency Transfer 121 5 Tune 34 MFD CRS XPDR NAV COM Control 35 Alphanumeric Keys 36 Backspace Key 37 Space Key 38 Multi function knob 39 Course Selection HSI 40 Ident 41 Home Key SR20_FM07_5389 35 37 35 28 33 32 31 30 29 27 2...

Page 270: ...3 amp ENGINE INSTR circuit breaker on ESS BUS 2 GTX 335 Mode S Transponder The GTX 335 solid state transponder communicates with the primary Integrated Avionics Unit and provides Modes A and C interrogation reply capabilities The transponder is controlled via the PFD or Flight Manage ment System Keyboard and is located in the empennage avionics compart ment 28 VDC for Transponder operation is supp...

Page 271: ...m Annunciations refer to Section 3 Emergency Procedures and Section 3A Abnormal Procedures For additional information on Engine Instrument Markings and Annunciations refer to Section 2 Limitations GFC 700 3 Axis Autopilot and GMC 707 Autopilot Controller Refer to latest revision of AFM Supplement 11934 S57 GFC 700 Auto matic Flight Control System for operating information Approach Baro VNAV While ...

Page 272: ... to 60 seconds before the FAF the system will determine whether or not the approach mode can be supported using Baro VNAV If Baro VNAV can be supported the APR ADVISORY SBAS VNAV not available Using Baro VNAV message will be displayed on the PFDs and the vertical deviation indicator VDI will be flagged If SBAS is required for the approach the approach mode e g LPV will be shown in amber but the GP...

Page 273: ... to or after the FAF Sensor Comparison Annunciation Serials w dual Air Data Computer ADC installations The temperature compensated altitudes from ADC1 and ADC2 are contin uously compared If a miscompare of greater than 50 feet is detected the text VDI MISCOMP is displayed in the sensor comparison annunciation area on the PFD in black text with an amber background When a temperature compensated alt...

Page 274: ...7 19 Baro VNAV Vertical Deviation Indicator SR20_FM07_5361 1900 1700 1600 1500 1400 29 92IN 3500 1800 V 16 60 40 LEGEND 1 Excessive Deviation Indicator 2 Glidepath Indicator 1 2 1 1 NOTE While Baro VNAV is being utilized the Glidepath Indicator appears as a magenta pentagon 1 Reissue A ...

Page 275: ...l detailed operating procedures GSR 56 Iridium Satellite Network Transceiver The Iridium Satellite Network Transceiver mounted in the empennage avionics compartment communicates with the primary Integrated Avionics Unit and Audio Panel to provide near real time weather voice and data services to the cabin audio system and integrated displays The GSR 56 receives near real time satellite weather inf...

Page 276: ...stem detects electrical discharges associated with thunderstorms and displays the activity on the MFD The system consists of an antenna located on top of the fuselage and a processor unit mounted under the aft baggage floor The antenna detects the electrical and magnetic fields generated by intra cloud inter cloud or cloud to ground electrical discharges occurring within 200 nm of the airplane and...

Page 277: ...th SVS features in the background The PFD with SVS installed includes Perspective depiction of surrounding terrain Zero pitch line Perspective depiction of runways Perspective depiction of large bodies of water Perspective depiction of obstacles Flight path marker Terrain warning system and Field of view depiction on the MFD Navigation Page Refer to the Perspective Integrated Avionics System Pilot...

Page 278: ...ective Integrated Flight Deck Pilot s Guide for a detailed discussion of the SurfaceWatch feature Flight Stream 510 Wireless Avionics Interface The Flight Stream 510 Wireless Avionics Interface allows the connection of a compatible mobile electronic device to the avionics The Flight Stream 510 utilizes a Bluetooth connection for pairing up to 4 devices as well as a Wi Fi connection for wireless da...

Page 279: ... connection while on the ground for automatic transmis sion of aircraft data This data can then be accessed by the pilot via a mobile application provided by Cirrus The Gateway Module also provides access to the current status of aircraft consumables when the aircraft is unat tended by remotely powering select systems on the aircraft when requested via the mobile application Reissue A ...

Page 280: ... 10 Hour Meters 11 Egress Hammer 12 Passenger Audio USB Jacks 13 Cabin Speaker 14 Roll Servo 15 Convenience System Controller 16 Pitch Trim Adapter opt 17 Pitch Servo 18 Gateway Module opt 19 Transponder 20 XM Satellite Data Link Receiver opt 21 ELT 22 Battery 2 23 Iridium Global Satellite Datalink opt 24 Tiedown Loops 25 CAPS Parachute 26 Stormscope WX 500 opt 27 Microphone 28 TAS Receiver opt 29...

Page 281: ...tional XM system is installed a combination GPS 1 XM antenna is installed in this location A combination GPS 2 Iridium antenna is mounted just forward of the baggage compartment window These antennas are connected to the two GPS receivers contained in the Inte grated Avionics Units The optional Traffic System antenna is mounted just above the pilot copilot compartment If the GTS 800 Traffic Adviso...

Page 282: ...itional 3 5 mm jack on the front of the audio panel will also accept a mobile device input A device connected to this jack is distributed by selecting the Entertainment button shown as a phone and music note symbol on the audio panel Audio volume can be controlled by the device itself and can be further refined by the audio panel distribution volume control Avionics Cooling Fans Three electric fan...

Page 283: ...lane centerline The transmitter and antenna are accessible through the avionics bay access panel along the aft portion of the RH fuselage or the lower aft center access panel of baggage compartment The main transmitter control switch is labeled ON ARM OFF TEST The transmitter is in the armed position for normal operations A red LED annunciator flashes when the ELT is transmitting A battery pack co...

Page 284: ...34 005 Figure 7 21 Artex ELT 1000 System 4 5 8 CENTER CONSOLE REF ELT SHELF REF SR20_FM07_3680 LEGEND 1 LED Annunciator 2 Remote Switch 3 Antenna 4 Remote Cable 5 Main Control Switch 6 Antenna Jack 7 Attach Straps 8 Artex ELT 1000 1 2 3 7 6 1 W A R NI N G FO R W A R D Reissue A ...

Page 285: ...proved for use on class B liquid grease and class C electrical equip ment fires A pin is installed through the discharge mechanism to prevent inadvertent discharge of extinguishing agent The fire extinguisher must be recharged or replaced after each use To Operate Extinguisher 1 Loosen retaining clamp and remove the extinguisher from its mounting bracket 2 Hold the extinguisher upright and pull th...

Page 286: ...d to break through the acrylic windows to provide an escape path for the cabin occu pants Convenience Outlet s A 12 volt convenience outlet is installed in the center console The recep tacle accepts a standard cigarette lighter plug The outlet may be used to power portable entertainment equipment Amperage draw through the outlet must not exceed 3 5 amps Four Universal Serial Bus USB high power ded...

Page 287: ...eploy 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 compart ment bulkhead The box is covered and protected from the elements by a thin composite cover The parachute is enclosed within a deployment bag that stages th...

Page 288: ...e removes it from the o ring seal that holds it in place and takes out the slack in the cable approximately two inches 5 cm of cable will be exposed Once the slack is removed the T handle motion will stop and greater force will be required to activate the rocket 2 Clasp both hands around activation T handle and pull straight down ward with a strong steady and continuous force until the rocket acti...

Page 289: ...s intentionally snubbed short to preclude excessive nose up pitch Following any nose up pitching the nose will gradually drop until the airplane is hanging nose low beneath the canopy Eight seconds after deployment the rear riser snub line will be cut and the airplane tail will drop down into its final approximately level attitude Once stabilized in this attitude the airplane may yaw slowly back a...

Page 290: ...SECTION 7 AIRPLANE AND SYSTEMS CIRRUS DESIGN CIRRUS AIRFRAME PARACHUTE SYSTEM SR20 7 96 P N 11934 005 Reissue A Intentionally Left Blank ...

Page 291: ...rformed Preventative Maintenance 7 Ground Handling 8 Application of External Power 8 Towing 9 Taxiing 10 Parking 11 Tie Down 12 Leveling 12 Jacking 12 Servicing 13 Landing Gear Servicing 13 Brake Servicing 13 Tire Inflation 13 Propeller Servicing 14 Engine Oil Servicing 14 Fuel System Servicing 15 Battery Service 18 Key Fob Battery Replacement 18 Artex ELT 1000 Servicing 19 Cleaning Exterior Surfa...

Page 292: ...IGN SR20 8 2 P N 11934 005 Care of Graphics 25 Cleaning Interior Surfaces 29 Interior Windshield and Windows 29 Instrument Panel and Electronic Display Screens 30 Headliner and Trim Panels 30 Leather Upholstery and Seats 31 Carpets 31 Reissue A ...

Page 293: ...ne electrical wiring Illustrated Parts Catalog IPC Catalog prepared to aid operators and mechanics to identify and procure replacement airplane parts CAPS Component Maintenance Manual CMM Maintenance Manual with Illustrated Parts List prepared to enable an authorized Cirrus CAPS technician to restore the system to a functional condi tion Engine Operators and Maintenance Manual Cirrus provides a Ly...

Page 294: ...ym ARROW is often used to help remember the required documents RELATED TABLE FIGURE Refer to Table 1 Required Documents NOTE Owners of aircraft not registeredin the United States should check with the registering authority for additional requirements Table 1 Required Documents Required Documents Note A Airworthiness Certificate FAA Form 8100 2 Must be displayed at all times R Registration Certific...

Page 295: ... records time in service than the 1 Hour Meter The inspection items specified in the Annual 100 Inspection have been determined by the average aircraft use rate of the typical owner Non commercially operated aircraft that are flown signifi cantly more than 100 hours per year should consider additional inspections commensurate with the hours flown 100 Hour Inspection or enrollment in a Progressive ...

Page 296: ...where the inspection can be accomplished Any flight hours used to reach an inspection station must be deducted from the next 100 Hour Inspection interval The inspection is listed in detail in Chapter 5 of the Airplane Maintenance Manual Cirrus Design Progressive Inspection Program In lieu of the above requirements an airplane may be inspected using a Progressive Inspection Program in accordance wi...

Page 297: ...tires Clean grease or replace wheel bearings Replace defective safety wire or cotter pins Lubrication not requiring disassembly other than removal of non structural items such as access covers cowlings or fairings CAUTION Do not use unapproved lubricants Unapproved lubricants may damage control system components including but not limited to engine and flight controls Refer to the AMM for approved ...

Page 298: ...rt engine keep yourself others and power unit cables well clear of the propeller rotation plane To Apply External Power to Airplane CAUTION In accordance with the manufacturer s recommendation external power should not be used to start the airplane with a dead battery or to charge a dead or weak battery in the airplane The battery must be removed from the airplane and battery maintenance performed...

Page 299: ... vertical or horizontal control surfaces or stabilizers to move the airplane If a tow bar is not available use the wing roots as push points Do not push 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 ce...

Page 300: ...cause damage to the propeller blades Taxi with minimum power needed for forward movement Exces sive braking may result in overheated or damaged brakes Refer to Section 10 Safety Information Taxiing Steering and Braking Practices To Taxi Airplane 1 Remove chocks 2 Start engine in accordance with Engine Start procedure 3 Release parking brake 4 Advance throttle to initiate taxi Immediately after ini...

Page 301: ...venience lighting electronic door locks and Gateway Module will be disabled when CONV LIGHTS circuit breaker is pulled To Park Airplane 1 Position airplane on level surface and headed into the wind 2 Retract flaps CAUTION Use care if setting parking brake during cold weather when accu mulated moisture may freeze brakes or when brakes are over heated 3 Set parking brake by first applying brake pres...

Page 302: ...ure tie down ropes to the wing tie down rings and to the tail 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 the midsh...

Page 303: ...vel should be checked at every oil 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 NOTE If the entire system must be refilled refer to AMM Chapter 12 Servicing Brake Fluid Replenishing 1 Install chocks 2 Release parking brake 3 Remove top engine cowling to gain access to hydraulic flui...

Page 304: ... 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 Refer to the shot peening requirement described in Section 2 Limitations Propeller Engine Oil Servicing The total oi...

Page 305: ... and install dipstick and filler cap 4 Close and secure access panel Fuel System Servicing 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 29 3 U S gallons When using less than the standard 58 5 gallon capacity fuel should be distributed equally between each side WARNING During fueling have a fire...

Page 306: ... checked frequently and drained of condensation to prevent possible distribution prob lems 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 tank This will aid in keeping fuel loads balanced Refer to Section 2 Limitations Fuel for maximum fuel imbal ance informati...

Page 307: ...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 improper fuel grade do not fly the airplane until the fuel system is drained and refueled with an app...

Page 308: ...st aft of bulkhead 222 there is no need to check the specific gravity of the electrolyte or add water to these batteries during their service life Refer to AMM Chapter 5 Time Limits And Main tenance Checks Overhaul and Replacement Schedule The external power receptacle is located on the left side of the fuselage just aft of the firewall Refer to AMM Chapter 24 Electrical Power External Power for s...

Page 309: ... and must not last for more than 3 audio sweeps 1 5 seconds If you are at a location where there is an FAA control tower or other monitoring facility notify the facility before beginning the tests Never activate the ELT while airborne for any reason Operators may wish to use a low quality AM broadcast receiver to determine if energy is being transmitted from the antenna When the antenna of the rad...

Page 310: ...Flashes Not used If displayed correct condition before further flight d 4 Flashes Indicates low output power If displayed correct condi tion before further flight e 5 Flashes Indicates no position data present If displayed correct condition before further flight NOTE BAT1 must be powered on to provide position data to the ELT f 6 Flashes Indicates G switch loop is not present If displayed correct ...

Page 311: ...urfaces will reduce the abrasion problems in these areas To Clean Painted Surfaces 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 Exterior Windshield and W...

Page 312: ...ensor Windows Optional The Enhanced Vision System Sensor is located on the underside of the LH wing The three sensor windows are made of Germanium In contrast to visible light energy infrared energy typically passes through dirt on the window As such the Sensor windows require only occasional cleaning CAUTION If an EVS Sensor Window breaks use gloves and masks when handling broken germanium window...

Page 313: ...ot operate the engine until excess solvent has evaporated or otherwise been removed 5 Remove the protective tape from the magnetos 6 Open induction system air inlet and install filter 7 Lubricate in accordance with AMM Chapter 12 Servicing Landing Gear Before cleaning the landing gear place a plastic cover or similar material over the wheel and brake assembly To Clean Landing Gear 1 Place a pan un...

Page 314: ...others Polish RejeX High Gloss Protective Finish Corrosion Technologies WX Block System Wings and Wheels AeroShell Flight Jacket Plexicoat Aeroshell Painted Exterior and Landing Gear XL 100 Heavy Duty Cleaner Degreaser Buckeye International Engine Compartment Stoddard Solvent PD 680 Type ll Any Source Exterior Windshield and Windows Kerosene Any Source Klear To Land D W Davies Co Plastic and Glass...

Page 315: ...more difficult to remove 1 Rinse off as much dirt and grit as possible with a spray of water 2 Clean graphic with a wet non abrasive detergent such as 3M Car Wash Soap 39000 Meguiar s NXT Generation Car Wash or Deep Crystal Car Wash and a soft clean cloth or sponge 3 Rinse thoroughly with clean water 4 To reduce water spotting immediately use a silicone squeegee to remove water 5 Dry with a clean ...

Page 316: ... further cleaning is needed one of the following products may be used Meguiar s Gold Class Bug and Tar Remover 3M Citrus Base Cleaner a mixture of two parts isopropyl alcohol to one part water mix ratio 2 1 or denatured alcohol 6 Immediately rinse off all residue with clean water 7 To reduce water spotting immediately use a silicone squeegee to remove water 8 Dry with a clean microfiber cloth To C...

Page 317: ...on products and mixtures below to help preserve the condition of the graphics on your aircraft CAUTION Do not use abrasive polishes or cutting compounds Do not use polish or wax on graphics with a matte or texture finish Initially test restoration products and mixtures on an inconspic uous area of the graphic to verify they will not cause damage NOTE Use an all purpose cleaner to remove wax or wax...

Page 318: ...0 Depending on the type and degree of contamination to be removed use one or more of the following solutions in the order shown 1 Hot soapy water solution 2 Mixture of two parts isopropyl alcohol to one part water mix ratio 2 1 3 Simple Green All Purpose Cleaner 4 Household chlorine bleach followed by a mixture of two parts isopropyl alcohol to one part water mix ratio 2 1 5 Mineral spirits follow...

Page 319: ... acrylic cleaner Do not use gasoline alcohol benzene carbon tetrachloride thinner acetone or glass window cleaning sprays Use only a non abrasive 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 motion on the windshield in the dir...

Page 320: ... with a dry clean 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 dry clean cotton cloth Headliner and Trim Panels The airplane interior can be cleaned with a mild detergent or soap and water Harsh abrasives or alkali...

Page 321: ...cause the leather to age prematurely Cover areas where cleaning solution could cause damage CAUTION Solvent cleaners and alcohol should not be used on leather uphol stery To Clean Leather Upholstery and Seats 1 Clean leather upholstery with a soft bristle brush and vacuum where necessary 2 Wipe leather upholstery with a soft damp cloth 3 Soiled upholstery may be cleaned with the approved products ...

Page 322: ...rist Aerospace Display Screens Optimax PhotoDon Cabin Interior Mild Dishwasher Soap abrasive free Any Source Leather Upholstery Leather Care Kit 50689 001 Hemisphere International Leather Cleaner 50684 001 Cirrus Ink Remover 50685 001 Cirrus Leather Conditioner 50686 001 Cirrus Spot and Stain Remover 50687 001 Cirrus Vinyl Panels Vinyl Finish Cleaner 50688 001 Cirrus Vinyl and Leather Upholstery V...

Page 323: ...P N 11934 005 9 1 CIRRUS DESIGN SECTION 9 LOG OF SUPPLEMENTS SR20 Section 9 Log of Supplements Table of Contents As Required Reissue A ...

Page 324: ...or the special operations are to be performed This Log of Supplements shows all Cirrus Supplements available for the aircraft at the corresponding date of the revision level shown in the lower left corner A check mark in the Part Number column indicates that the supplement is applicable to the POH Any installed supplements not applicable to the POH are provided for reference only Reissue A ...

Page 325: ...rame Parachute System CAPS 5 Deployment Scenarios 5 Mid Air Collision 6 Structural Failure 6 Loss of Control 6 Landing Required in Terrain not Permitting a Safe Landing 6 Pilot Incapacitation 7 General Deployment Information 7 Deployment Speed 7 Deployment Altitude 7 Deployment Attitude 8 Landing Considerations 8 Emergency Landing Body Position 8 Door Position 8 Water Landings 9 Post Impact Fire 9...

Page 326: ...SECTION 10 SAFETY INFORMATION CIRRUS DESIGN SR20 10 2 P N 11934 005 Reissue A Intentionally Left Blank ...

Page 327: ... airplane The procedures given are the result of flight testing FAA certification requirements and input from pilots with a variety of operational experience Become fully familiar with the procedures perform all the required checks and operate the airplane within the limitations and as outlined in the procedures Taxiing Steering and Braking Practices Cirrus aircraft use a castering nose wheel and ...

Page 328: ...in mind any additional power added with the throttle will be absorbed in the brakes to maintain constant speed Use rudder deflection and the minimum necessary inputs of differen tial braking to achieve directional control Do not ride the brakes Pilots should consciously remove pressure from the brakes while taxiing Failure to do so results in excessive heat buildup premature brake wear and increas...

Page 329: ...igher probability of deploying CAPS when necessary The following discussion is meant to guide your thinking about CAPS acti vation Cirrus also recommends that pilots discuss CAPS deployment scenarios with instructors as well as fellow pilots through forums such as the Cirrus Owners and Pilots Association In the event of a spin or loss of aircraft control immediate CAPS activation is required See S...

Page 330: ... or jammed controls severe wake turbulence severe turbulence causing upset severe airframe icing or pilot disorientation caused by vertigo or panic If loss of control occurs the CAPS should be activated immediately WARNING In the event of a spin immediate CAPS activation is mandatory Under no circumstances should the pilot attempt recovery from a spin other than by CAPS activation Landing Required...

Page 331: ...e airplane s airspeed altitude and attitude at deployment as well as other environmental factors In all cases however the chances of a successful deployment increase with altitude In the event of a spin immediate CAPS activation is mandatory regardless of altitude In other situations the pilot in command may elect to troubleshoot a mechanical problem or attempt to descend out of icing conditions i...

Page 332: ...ings is to prepare the occupants for the touchdown in order to protect them from injury as much as possible Emergency Landing Body Position The most important consideration for a touchdown with CAPS deployed is to protect the occupants from injury especially back injury Contacting the ground with the back offset attempting to open a door or secure items increases the likelihood of back injury All ...

Page 333: ...y transient aircraft attitude With a door open 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 as sociated with ground contact Typically this would be the copilot s door as this allows t...

Page 334: ...out obstacles In order to ensure that the occupants can escape the airplane in the timeliest manner after the airplane comes to rest the pilot may elect to unlatch the copilot s door for the CAPS landing Occupants must be in the Emergency Landing Body Position for touchdown Occupants must not loosen seat belts until the airplane comes to rest When the airplane comes to rest the occupants should ex...

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