Cirrus SR20 Specifications Page 301
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P/N 11934-S36 5 of 8
Cirrus Design Section 9
SR20 Supplements
Section 7 - Systems Description
This airplane is equipped with a self-contained Artex ME406 406 MHz
ELT System. The transmitter unit is automatically activated upon
sensing a change of velocity along its longitudinal axis exceeding 4 to
5 feet per second. Once activated, the transmitter transmits VHF band
audio sweeps at 121.5 Mhz until battery power is gone. In addition, for
the first 24 hours of operation, a 406 MHz signal is transmitted at 50-
second intervals. This transmission lasts 440 ms and contains
identification data received by Cospas-Sarsat satellites. The
transmitted data is referenced in a database maintained by the
national authority responsible for ELT registration to identify the
beacon and owner.
The ELT transmitter is installed immediately behind the aft cabin
bulkhead, slightly to the right of the airplane 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”. The transmitter is in the armed position for
normal operations. A red LED annunciator flashes when the ELT is
transmitting. A battery pack consisting of two “D” cell lithium batteries
mounts to a cover assembly within the transmitter to provide power to
the transmitter. The expiration date of the batteries are indicated on
the outside of the ELT battery case and recorded in the aircraft logs.
A warning buzzer is mounted to the transmitter mounting tray. When
the ELT is activated, the buzzer “beeps” periodically. This buzzer
operates in tandem with the ELT panel indicator and serves as a
redundant annunciation. Power to the buzzer is supplied by the ELT
batteries.
Serials 1005 thru 2015; The ELT Remote Switch and Control Panel
Indicator (RCPI) is located below the circuit breakers on the circuit
breaker panel or Serials 2016 and subsequent, below the Alternate
Induction Air Control knob near the pilot’s right knee.
The RCPI provides test and monitoring functions for the transmitter.
The panel contains a switch labeled “ON” - “ARM”, and a red LED
annunciator. The red LED annunciator flashes when the ELT is
transmitting. Power to the LED is supplied by the clock bus on the
MCU.
Revision 01: 12-18-08
- CIRRUS DESIGN SR20 1
- Cirrus Design Corporation 2
- 4515 Taylor Circle 2
- Duluth, MN 55811 2
- List of Effective Pages 3
- B P/N 11934-004 4
- SR20 List of Effective Pages 4
- P/N 11934-004 C 5
- Foreword 7
- The Handbook 8
- Revising the Handbook 9
- Identifying Revised Material 9
- Revision Service 10
- Supplements 10
- Retention of Data 11
- Warnings, Cautions, and Notes 11
- Section 1 13
- Figure 1-1 16
- Airplane Three View 16
- Figure 1-2 17
- Airplane Interior Dimensions 17
- Figure 1-3 18
- Turning Radius 18
- The Airplane 19
- 1-8 P/N 11934-004 20
- Section 1 Cirrus Design 20
- General SR20 20
- Meteorological Terminology 22
- Engine Power Terminology 23
- 1-12 P/N 11934-004 24
- Cirrus Design Section 1 25
- SR20 General 25
- P/N 11934-004 1-13 25
- Section 2 27
- Limitations 27
- 2-2 P/N 11934-004 28
- Section 2 Cirrus Design 28
- Limitations SR20 28
- Certification Status 29
- Airspeed Limitations 30
- Airspeed Indicator Markings 31
- Powerplant Limitations 32
- Weight Limits 33
- PowerPlant 34
- Electrical 35
- Center of Gravity Limits 36
- Maneuver Limits 37
- Flight Load Factor Limits 37
- Minimum Flight Crew 37
- Kinds of Operation 38
- Runway Surface 42
- Fuel Limits 43
- Altitude Limits 43
- Environmental Conditions 43
- Maximum Occupancy 43
- Systems and Equipment Limits 44
- Cirrus Design Section 2 45
- SR20 Limitations 45
- P/N 11934-004 2-19 45
- Enhanced Vision System 46
- Other Limitations 47
- Placards 48
- EXTERNAL 49
- Figure 2-4 50
- (Sheet 3 of 6) 50
- DAY - NIGHT - VFR - IFR 51
- FOLLOWING FLIGHT OPERATIONS: 51
- GRAB HERE 52
- IN INJURY OR DEATH 53
- Section 3 55
- Emergency Procedures 55
- 3-2 P/N 11934-004 56
- Section 3 Cirrus Design 56
- Emergency Procedures SR20 56
- Emergency Procedures Guidance 58
- Circuit Breakers 59
- Memory Items 59
- 3-6 P/N 11934-004 60
- Engine Failures 61
- Engine Failure In Flight 62
- Airstart 63
- Smoke and Fire 64
- Cirrus Design Section 3 65
- SR20 Emergency Procedures 65
- P/N 11934-004 3-11 65
- Wing Fire In Flight 66
- Engine Fire During Start 66
- Smoke and Fume Elimination 67
- Emergency Descent 68
- Forced Landings 69
- Ditching 70
- Engine System Emergencies 71
- Oil Temperature High 72
- Engine Speed High 72
- P/N 11934-004 3-19 73
- Engine Partial Power Loss 74
- P/N 11934-004 3-21 75
- Propeller System Emergencies 76
- Fuel System Emergencies 77
- Electrical System Emergencies 78
- Low Voltage on Essential Bus 79
- Low Alternator 1 Output 80
- Low Alternator 2 Output 80
- PFD Display Failure 81
- Emergency Exit 82
- Unusual Attitude Emergencies 83
- 3-30 P/N 11934-004 84
- Other Emergencies 85
- Starter Engaged Annunciation 86
- CAPS Deployment 87
- 3-34 P/N 11934-004 88
- P/N 11934-004 3-35 89
- Section 3A 91
- Abnormal Procedures 91
- 3A-2 P/N 11934-004 92
- Section 3A Cirrus Design 92
- Abnormal Procedures SR20 92
- Abnormal Procedures Guidance 93
- Flight Environment 94
- Abnormal Landings 95
- Engine System 96
- Fuel System (Cont) 98
- Figure 3A-1 99
- Circuit Breaker Panel 99
- Integrated Avionics System 100
- MFD Cooling Fan Failure 101
- Pitot Static System 102
- Flight Control System 104
- Landing Gear System 105
- Other Conditions 106
- Communications Failure 107
- Intentionally Left Blank 108
- Section 4 109
- Normal Procedures 109
- Introduction 111
- SR22_FM04_1454 112
- Cirrus Design Section 4 113
- SR20 Normal Procedures 113
- P/N 11934-004 4-5 113
- Revision 1 113
- 4-6 P/N 11934-004 114
- Section 4 Cirrus Design 114
- Normal Procedures SR20 114
- Original Issue 114
- P/N 11934-004 4-7 115
- 4-8 P/N 11934-004 116
- Before Starting Engine 117
- Starting Engine 118
- P/N 11934-004 4-11 119
- Before Taxiing 120
- Before Takeoff 121
- 4-14 P/N 11934-004 122
- P/N 11934-004 4-15 123
- Normal Takeoff 124
- Short Field Takeoff 124
- P/N 11934-004 4-17 125
- 4-18 P/N 11934-004 126
- Cruise Leaning 127
- Before Landing 128
- P/N 11934-004 4-21 129
- Balked Landing/Go-Around 130
- After Landing 130
- Shutdown 131
- Environmental Considerations 132
- P/N 11934-004 4-25 133
- Fuel Conservation 134
- Section 5 135
- Performance Data 135
- Temperature Conversion 142
- Stall Speeds 144
- Wind Components 145
- Takeoff Distance 146
- Takeoff Distance - 3050 LB 147
- Takeoff Distance - 2500 LB 148
- Takeoff Climb Gradient 149
- Takeoff Rate of Climb 150
- Enroute Climb Gradient 151
- Enroute Rate of Climb 152
- Cruise Performance 155
- Range / Endurance Profile 157
- Balked Landing Climb Gradient 159
- Balked Landing Rate of Climb 160
- Landing Distance 161
- Section 6 163
- Weight and Balance Data 163
- Airplane Weighing Form 166
- Airplane Weighing Procedures 167
- 6-6 P/N 11934-004 168
- Section 6 Cirrus Design 168
- Weight and Balance Data SR20 168
- SR22_FM06_1440A 169
- Loading Instructions 170
- Loading Data 172
- Moment Limits 173
- Weight & Balance Record 174
- Equipment List 175
- Section 7 177
- 7-2 P/N 11934-004 178
- Section 7 Cirrus Design 178
- Airframe 180
- Empennage 181
- Flight Controls 182
- Figure 7-1 183
- Elevator System 183
- Aileron System 184
- Figure 7-2 185
- Rudder System 186
- Control Locks 186
- Figure 7-3 187
- Instrument Panel 188
- SR20_FM07_3010 189
- Flight Instruments 190
- SR20_FM07_3009 191
- Attitude Indicator 192
- Airspeed Indicator 193
- Altimeter 194
- Vertical Speed Indicator 195
- Magnetic Compass 195
- Wing Flaps 196
- Figure 7-6 197
- Landing Gear 198
- Cirrus Design Section 7 199
- P/N 11934-004 7-25 199
- Baggage Compartment 200
- P/N 11934-004 7-27 201
- 7-28 P/N 11934-004 202
- Cabin Doors 203
- Engine Controls 204
- P/N 11934-004 7-31 205
- Engine Indicating 206
- Density Alt 8000 Ft 207
- 7-34 P/N 11934-004 208
- P/N 11934-004 7-35 209
- Engine Lubrication System 210
- Ignition and Starter System 210
- Air Induction System 210
- Engine Exhaust 211
- Engine Fuel Injection 211
- Engine Cooling 211
- Propeller 212
- Fuel System 213
- Fuel Selector Valve 214
- Fuel Pump Operation 214
- Figure 7-8 215
- Fuel System Schematic 215
- Fuel Indicating 216
- 7-44 P/N 11934-004 218
- P/N 11934-004 7-45 219
- Electrical System 220
- Figure 7-10 221
- Electrical System Schematic 221
- Power Distribution 222
- Electrical System Protection 223
- 7-50 P/N 11934-004 224
- Electrical System Control 225
- Ground Service Receptacle 226
- Electrical Indicating 227
- Lighting Systems 229
- Interior Lighting 230
- Environmental System 231
- Figure 7-12 232
- Distribution 233
- 7-60 P/N 11934-004 234
- Stall Warning System 235
- Pitot-Static System 236
- Figure 7-13 237
- Avionics 238
- Figure 7-14 239
- 7-66 P/N 11934-004 240
- P/N 11934-004 7-67 241
- SR20_FM07_2807 242
- SR20_FM07_2820 243
- 7-70 P/N 11934-004 244
- P/N 11934-004 7-71 245
- Optional Avionics 246
- P/N 11934-004 7-73 247
- 7-74 P/N 11934-004 248
- P/N 11934-004 7-75 249
- SR20_FM07_3011 250
- Avionics Support Equipment 251
- 7-78 P/N 11934-004 252
- Cabin Features 253
- Fire Extinguisher 254
- Hour Meters 255
- Emergency Egress Hammer 255
- Convenience Outlet 255
- System Description 256
- Activation Handle 257
- 7-84 P/N 11934-004 258
- Deployment Characteristics 259
- Section 8 261
- Operator’s Publications 263
- Ordering Publications 264
- Airworthiness Directives 266
- Airplane Inspection Periods 266
- 100-Hour Inspection 267
- 8-8 P/N 11934-004 268
- Section 8 Cirrus Design 268
- Cirrus Design Section 8 269
- P/N 11934-004 8-9 269
- Ground Handling 270
- P/N 11934-004 8-11 271
- 8-12 P/N 11934-004 272
- P/N 11934-004 8-13 273
- Leveling 274
- P/N 11934-004 8-15 275
- Servicing 276
- P/N 11934-004 8-17 277
- Tire Inflation 278
- Propeller Servicing 278
- Oil Servicing 278
- Figure 8-1 280
- Approved Oils 280
- Fuel System Servicing 281
- 8-22 P/N 11934-004 282
- Draining Fuel System 283
- Battery Service 284
- Cleaning and Care 285
- Figure 8-2 286
- P/N 11934-004 8-27 287
- 8-28 P/N 11934-004 288
- Cleaning Interior Surfaces 289
- Figure 8-3 290
- P/N 11934-004 8-31 291
- 8-32 P/N 11934-004 292
- Section 9 293
- Log of Supplements 295
- P/N 11934-S36 1 of 8 297
- Cirrus Design Section 9 297
- SR20 Supplements 297
- Revision 01: 12-18-08 297
- Section 1 - General 298
- Section 2 - Limitations 299
- Section 4 - Normal Procedures 300
- Section 5 - Performance 300
- P/N 11934-S36 5 of 8 301
- Inspection / Test 302
- P/N 11934-S36 7 of 8 303
- Control System 305
- Autopilot Malfunction 307
- Autopilot Miscompare 308
- P/N 11934-S41 7 of 16 311
- Revision 01: 08-26-09 311
- Figure - 1 312
- GFC 705 AFCS Mode Controller 313
- Altitude Hold (ALT) 10 Feet 314
- P/N 11934-S41 11 of 16 315
- SR20_FM09_2920 316
- Roll and Pitch Servo 317
- Integrated Avionics Units 317
- Autopilot Disconnect Switch 318
- Take Off / Go Around Button 318
- Pitch Trim Adapter 318
- Annunciation System 319
- No Change 320
- P/N 11934-S42 1 of 6 321
- Original Issue: 12-18-08 321
- Response To TAWS Warnings 323
- Response To TAWS Cautions 323
- System Constraints 325
- Section 10 327
- Safety Information 327
- Deployment Scenarios 330
- Cirrus Design Section 10 331
- SR20 Safety Information 331
- P/N 11934-004 10-5 331
- Landing Considerations 333
- P/N 11934-004 10-9 335
- Operating Practices 336
- Brake Maintenance 337
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