PILOT'S INFORMATION MANUAL

Chapter 5 ........................................................................................... Wing Flaps Chapter 6 ....................................................................................... Landing Gear Chapter 7 .......................................................................................................Seats Chapter 8 ...........................................................................Doors and Windows Chapter 9 ........................................................................................... Powerplant Chapter 10 ......................................................................................................Fuel Chapter 11 ............................................................................................. Electrical Chapter 12 ...............................................................................................Lighting Chapter 13 .................................................................... Environmental Control Chapter 14 .................................................................................Air Data System Chapter 15 ........................................................................................Automation Chapter 16 .............................................................................................. Avionics Chapter 17 ................................................................................... Cabin Features Chapter 18 ................................................................................Recovery System Chapter 19 ..........................................................Safe Return Autoland System Chapter 20 ...........................................................................Log of Supplements Revision 1 FRONT M ATTER CIRRUS FOREWORD SR20 Front Matter-2 P/N 44764-001 Revising the Manual Two types of revisions may be issued for this manual: Temporary and Numbered. Temporary revisions are printed on yellow paper, normally cover only one topic or procedure, and are issued to provide safety related information or other time-sensitive information where the rigor of providing a numbered revision is not possible in the time allowed. All the information needed to properly file a temporary revision is included on the revision itself. Typi- cally, a temporary revision is superseded and replaced by the next numbered revision. Numbered revisions are printed on white paper, normally cover several subjects, and are issued as general updates. Each numbered revision includes an “Instruction Sheet,” a “List of Effective Pages”, and a “Revision Highlights” page. The “Instruction Sheet” is intended to assist the manual holder in removing superseded pages and inserting new or superseding pages. The “List of Effective Pages” shows the issue or revision status of all pages in the manual. The “Revision Highlights” page gives a brief descrip- tion of changes made to each page in the current revision. • N OTE • The owner is responsible to ensure that the manual is current at all times. Therefore, it is very important that all revisions be properly incorporated as soon as they are available. Identifying Revised Material Each page has revision identification at the lower inside corner opposite the page number. Original Issue pages will be identified by the words “Original Issue” at this location. In the event that the majority of pages are revised, Cirrus Aircraft may determine that it is more effective to reissue the manual. Reissued pages will be identified by the word “Reissue” followed by a letter indicating the reissue level; for example, “Reissue A” Revised pages will be identified by the word “Revision” followed by the revision number at this location; for example, “Revision 2” (Original Issue, Revision 2) or “Revision B1” (Reissue B, Revision 1). Revised material on a page can be identified by a change bar located at the outside page margin. Obtaining Revisions Revisions, temporary revisions, and supplements can be downloaded from Cirrus Aircraft at www.cirrusaircraft.com. Paper copies of revisions and supplements can be purchased from Cirrus Aircraft at www.cirrusaircraft.com. Revision 1 CIRRUS FRONT MATTER SR20 SUPPLEMENTS P/N 44764-001 Front Matter-3 Supplements The Supplements chapter contains supplementary information relating to optional equipment not provided with the standard airplane or not included in the manual. Supplements are essentially “mini-handbooks” and may contain data corresponding to most chapters of the manual. Data in a supplement either adds to, supersedes, or replaces similar data in the basic manual. Retention of Data In the event a new manual is purchased, the owner must ensure that all information applicable to the airplane is transferred to the new manual. It is not a requirement that owners retain information, such as supple- ments, that is no longer applicable to their airplane. Warnings, Cautions, and Notes Warnings, Cautions, and Notes are used throughout this manual to focus attention on special conditions or procedures as follows: • WARNING • Warnings are used to call attention to operating procedures which, if not strictly observed, may result in personal injury or loss of life. • CAUTION • Cautions are used to call attention to operating procedures which, if not strictly observed, may result in damage to equipment. • N OTE • Notes are used to highlight specific operating conditions or steps of a procedure. Original Issue FRONT M ATTER CIRRUS WARNINGS, C AUTIONS, AND NOTES SR20 Front Matter-4 P/N 44764-001 Original Issue Intentionally Left Blank P/N 44764-001 1-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 1 SR20 TABLE OF C ONTENTS Chapter 1: Airframe Table of Contents Airframe............................................................................................... 3 Fuselage............................................................................................ 3 Overview ......................................................................................... 3 Wings ................................................................................................ 3 Overview ......................................................................................... 3 Empennage ....................................................................................... 4 Overview ......................................................................................... 4 Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 1 CIRRUS TABLE OF C ONTENTS SR20 1-2 P/N 44764-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 1 SR20 A IRFRAME P/N 44764-001 1-3 Airframe Fuselage Overview The airplane’s monocoque fuselage is constructed primarily of composite materials and is designed to be aerodynamically efficient. The cabin area is bounded on the forward side by the firewall at fuselage station 100, and on the rear by the aft baggage compartment bulkhead at fuselage station 222. Comfortable seating is provided for the pilot and up to four passengers. A composite roll cage within the fuselage structure provides roll protection for the cabin occupants. The cabin and baggage compartment floors are constructed of a 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 aft of bulkhead 222 and accessible through an access panel installed on the RH side of the aft fuselage. Wings Overview The wing structure is constructed of composite materials producing wing surfaces that are smooth and seamless. The wing cross section is a blend of several high performance airfoils. A high aspect ratio results in low drag. Each wing provides attach structure for the main landing gear and contains a 29.3-gallon fuel tank. The wing is constructed in a conventional spar, rib, and shear section arrangement. The upper and lower skins are bonded to the spar, ribs, and aft shear web forming a torsion box that carries all of the wing bending and torsion loads. The rear shear webs are similar in construction but do not carry through the fuselage. The main spar is laminated epoxy/carbon fiber in a C-section, and is continuous from wing tip to wing tip. The wing spar passes under the fuselage below the two front seats and is attached to the fuselage in two locations. Lift and landing loads are carried by the single carry-through spar, plus a pair of rear shear webs (one on each wing) attached to the fuselage. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 1 CIRRUS A IRFRAME SR20 1-4 P/N 44764-001 Empennage Overview The empennage consists of a horizontal stabilizer, a two-piece elevator, a vertical stabilizer, and a rudder. All of the empennage components are conventional spar (shear web), rib, and skin construction. The horizontal stabilizer is a single composite structure from tip to tip. The two-piece elevator, attached to the horizontal stabilizer, is aluminum. The vertical stabilizer is composite structure integral to the main fuselage shell for smooth transfer of flight loads. The single-piece rudder, attached to the vertical stabilizer, is aluminum. Revision 1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 1 SR20 A IRFRAME P/N 44764-001 1-5 Figure 1-1: Equipment Locations 5 30 21 23 22 6 4 15 18 12 16 17 20 26 28 31 3 1 37 33 32 25 38 34 27 32 39 2 40 35 LEGEND 1. Avionics Cooling Fan 2. ADAHRS 3. Integrated Avionics Unit 4. Stick Shaker Controller 5. Audio Panel 6. Engine Interface 7. Battery 1 8. Fire Extinguisher 9. MFD 10. GTC 2 11. Center Console Switch Panel 12. Single USB-C Charging 13. Throttle Servo (if installed) 14. Fuel Tank Selector/AFSS 15. CAPS Activation Handle 16. Egress Hammer 17. Cabin Speaker 18. Roll Servo 19. Radar Altimeter (if installed) 20. Convenience System Controller 21. Pitch Trim Adapter 22. Pitch Servo 23. XM Radio Receiver 24. LTE Datalink (if installed) 25. Gateway Module (if installed) 26. Transponder 27. XM Satellite Data Link Receiver (if installed) 28. ELT 29. EAL Yaw Servo (if installed) 30. Battery 2 31. Iridium Global Satellite Datalink (if installed) 32. Tiedown Loops 33. CAPS Parachute 34. Stormscope WX-500 (if installed) 35. Safe Return Activation Panel 36. Mixture Servo (if installed) 37. TAS Receiver (if installed) 38. DME (if installed) 39. Single USB-C PD Charging 40. AFCS Mode Controller 41. ADF (if installed) 42. GTC 1 / SFD 43. Bolster Switch Panel 44. PFD 14 42 2 3 8 10 7 11 SR20_PM01_1001A 2 13 19 36 24 1 1 NOTE Optional MD302 ADAHRS shown. 41 1 43 44 29 9 Revision 1 P ILOT ’S I NFORMATION M ANUAL : CHAPTER 1 CIRRUS A IRFRAME SR20 1-6 P/N 44764-001 Original Issue Intentionally Left Blank P/N 44764-001 2-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 2 SR20 TABLE OF C ONTENTS Chapter 2: Flight Controls Table of Contents Flight Controls ..................................................................................... 3 Elevator System ................................................................................ 3 Overview ......................................................................................... 3 Operation......................................................................................... 3 Aileron System .................................................................................. 5 Overview ......................................................................................... 5 Operation......................................................................................... 5 Rudder System.................................................................................. 7 Overview ......................................................................................... 7 Operation......................................................................................... 7 Control Locks .................................................................................... 7 Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 2 CIRRUS TABLE OF C ONTENTS SR20 2-2 P/N 44764-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 2 SR20 F LIGHT C ONTROLS P/N 44764-001 2-3 Flight Controls Conventional flight controls for ailerons, elevator, and rudder are used. The ailerons and elevator are controlled through either of two side sticks. The rudder is controlled through either of two sets of rudder pedals. The control system uses a combination of push rods, cables, and bell cranks for control of the surfaces. Elevator System Overview The two-piece elevator provides airplane pitch control. The elevator is of conventional design with skin, spar and ribs manufactured from aluminum. Each elevator half is attached to the horizontal stabilizer at two hinge points and to the fuselage tailcone at the elevator control sector. Operation Elevator motion is generated through the side sticks by sliding the side stick tubes forward or aft in a bearing carriage. A push-pull linkage is connected to a cable sector mounted on a torque tube. A single cable system runs from the forward elevator sector under the cabin floor to the aft elevator sector pulley. A push-pull tube connected to the aft elevator sector pulley trans- mits motion to the elevator bellcrank attached to the elevators. Pitch Trim System The pitch trim system employs a ground adjustable trim tab and a spring cartridge activated by an electric motor. The spring cartridge, directly connected to the elevator bellcrank and the electric trim motor, provides a centering force regardless of the direction of control surface deflection. Pitch trim is provided by adjusting the neutral position of the compression spring cartridge in the elevator control system by means of an electric motor. An electric motor changes the neutral position of the spring cartridge attached to the elevator control horn. A conical trim switch located on top of each side stick controls the motor. Moving the switch forward will initiate nose-down trim and moving the switch aft will initiate nose-up trim. Neutral (takeoff) trim is indicated by the alignment of a reference mark on the side stick 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. A ground adjustable trim tab is installed on the elevator to provide small adjustments in neutral trim. This tab is factory set and does not normally require adjustment. Pitch trim operates on 28 VDC provided through the 2-amp PITCH TRIM circuit breaker on Essential Bus 2. Revision 1 P ILOT ’S I NFORMATION M ANUAL : CHAPTER 2 CIRRUS FLIGHT C ONTROLS SR20 2-4 P/N 44764-001 Figure 2-1: Elevator System 7 LEGEND 1. RH Elevator 2. LH Elevator 3. Spring Cartridge 4. Pulley 5. Cable 6. Side Stick 7. Ground Adjustable Trim Tab SR20_PM02_1004 4 5 4 1 23 6 6 Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 2 SR20 F LIGHT C ONTROLS P/N 44764-001 2-5 Aileron System Overview The ailerons provide airplane roll control. The ailerons are of conventional design with skin, spar and ribs manufactured of aluminum. Each aileron is attached to the wing shear web at two hinge points. Operation Aileron control motion is generated through the side sticks by rotating the side sticks in pivoting bearing carriages. Push rods link the pivoting carriages to a centrally located pulley sector. A single cable system runs from the sector to beneath the cabin floor and aft of the rear spar. From there, the cables are routed in each wing to a vertical sector/crank arm that rotates the aileron through a right angle conical drive arm. Roll Trim System Ground adjustable trim tabs are installed on both ailerons to provide small adjustments in neutral trim. These tabs are factory set and do not normally require adjustment. Roll trim is provided by adjusting the neutral position of a compression spring cartridge in the aileron control system by means of an electric motor. An electric motor changes the neutral position of a spring cartridge attached to the left actuation pulley in the wing. A conical trim switch located on top of each side stick controls the motor. Moving the switch left will initiate left-wing-down trim and moving the switch right will initiate right-wing-down trim. Neutral trim is indicated by the alignment of the upward facing corner of the square side stick tube with the centering indi- cation marked on the roll trim placard. The roll trim also provides a secondary means of airplane roll control in the event of a failure in the primary roll control system not involving jammed ailerons. Roll trim operates on 28 VDC provided through the 2-amp ROLL TRIM circuit breaker on Essential Bus 2. Revision 1 P ILOT ’S I NFORMATION M ANUAL : CHAPTER 2 CIRRUS FLIGHT C ONTROLS SR20 2-6 P/N 44764-001 Figure 2-2: Aileron System SR20_PM02_1010 LEGEND 1. RH Aileron 2. Pulley 3. LH Aileron 4. Spring Cartridge 5. Cable 6. Side Stick 1 2 2 3 2 5 2 4 6 6 Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 2 SR20 F LIGHT C ONTROLS P/N 44764-001 2-7 Rudder System Overview The rudder provides directional (yaw) control. The rudder is of conven- tional design with skin, spar and ribs manufactured of aluminum. The rudder is attached to the aft vertical stabilizer shear web at three hinge points and to the fuselage tailcone at the rudder control bell crank. Operation Rudder motion is transferred from the rudder pedals to the rudder by a single cable system under the cabin floor to a sector next to the elevator sector pulley in the aft fuselage. A push-pull tube from the sector to the rudder bell crank translates cable motion to the rudder. Springs and a ground adjustable spring cartridge connected to the rudder pedal assembly tension the cables and provide centering force. Yaw Trim System Centering springs are attached to the rudder pedal torque tube and console structure and provide a centering force regardless of the direction of rudder deflection. Yaw trim is provided by a ground adjustable trim tab installed on the rudder to provide small adjustments in neutral trim. This tab is factory set and does not normally require adjustment. Control Locks The airplane’s control system is not equipped with gust locks. The centering springs have sufficient power to act as a gust damper without rigidly locking the position. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 2 CIRRUS FLIGHT C ONTROLS SR20 2-8 P/N 44764-001 Figure 2-3: Rudder System SR20_PM02_1013 LEGEND 1. Spring Cartridge 2. Pulley 3. Rudder 2 2 2 1 3 Original Issue P/N 44764-001 3-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 3 SR20 TABLE OF C ONTENTS Chapter 3: Instrument Panel Table of Contents Instrument Panel ................................................................................. 3 Overview ........................................................................................... 3 Pilot Instrument Panel Arrangement ................................................. 3 Overview ......................................................................................... 3 Operation......................................................................................... 3 Center Console Arrangement............................................................ 4 Overview ......................................................................................... 4 Operation......................................................................................... 4 Bolster Panel Arrangement ............................................................... 7 Overview ......................................................................................... 7 Operation......................................................................................... 7 Power Source .................................................................................. 7 Engine Start and Ignition Control Arrangement................................. 8 Overview ......................................................................................... 8 Operation......................................................................................... 8 Center Console Switch Panel............................................................ 8 Overview ......................................................................................... 8 Operation......................................................................................... 8 System Circuit Breaker Panel Arrangement...................................... 9 Overview ......................................................................................... 9 Operation......................................................................................... 9 Safe Return Autoland Panel Arrangement (If Installed) .................. 10 Overview ....................................................................................... 10 Operation....................................................................................... 10 Revision 1 P ILOT ’S I NFORMATION M ANUAL : CHAPTER 3 CIRRUS TABLE OF C ONTENTS SR20 3-2 P/N 44764-001 Revision 1 Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 3 SR20 I NSTRUMENT PANEL P/N 44764-001 3-3 Instrument Panel Overview The instrument panel is installed in sections so equipment can be easily removed for maintenance. The surrounding glareshield projects over the instrument panel to reduce reflections on the windshield from lighted equipment and to shield the panel equipment from glare. Pilot Instrument Panel Arrangement Overview The pilot instrument panel consists of two flight displays (GDUs) – the Primary Flight Display (PFD) and Multi Function Display (MFD) – and two Garmin Touch Screen Controllers (GTCs). The PFD, installed directly in front of the pilot, is intended to be the primary display of flight param- eter information (attitude, airspeed, heading, and altitude). The MFD, installed to the right of the PFD, provides supplemental situational and navigation information to the pilot. The center instrument panel, installed between the PFD and MFD, includes the DISPLAY BACKUP push button and baro knob. The GTCs are pilot selectable to be either the Primary Flight Window (PFW) controller, Multi Function Window (MFW) controller (for GTC 1 only), or NAV/COM controller. GTC 1 reverts to the standby flight display when in display reversionary or backup mode. The engine knob and starter button are located on the left side of the PFD. Instrument panel air vents are located on the outboard sections of the panel. The interior lighting mode switch is located on the pilot side panel. Instru- ment lights and micro spot lights are controlled by the dimmer knob on the bolster switch panel. Convenience and accent lights are controlled by the lighting controller, and crew task lights are controlled by an adjacent knob at the light assembly. A fire extinguisher is mounted at the RH lower valence panel, in front of the co-pilot seat. Serials w/ Safe Return Autoland: A button to reset the brakes after a Safe Return Autoland landing is located on pilot side lower valence panel. Operation For specific operation details, refer to the applicable system. Revision 1 P ILOT ’S I NFORMATION M ANUAL : CHAPTER 3 CIRRUS I NSTRUMENT PANEL SR20 3-4 P/N 44764-001 Center Console Arrangement Overview A center console contains the autopilot controls, flap system control, fuel pump switch, fuel selector valve, Automatic Fuel Selector System (AFSS), environmental system controls, power and mixture levers, headset jacks, and USB power. The system circuit breakers, alternate static source valve, ELT panel switch, and starter disable switch are located on the left side of the center console. A storage compartment and emergency egress hammer are installed inside the console armrest. Serials 9750 thru 10614: A friction knob for adjusting throttle and mixture control feel and position stability is located on the right side of the console. Operation For specific center console control operation details, refer to the applicable system. Revision 1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 3 SR20 I NSTRUMENT PANEL P/N 44764-001 3-5 Figure 3-1: Instrument Panel and Console (1 of 2) 3 5 8 9 10 11 12 13 12 14 16 18 8 19 6 15 21 SR20_PM03_1016A LEGEND 1. Magnetic Compass (if installed) 2. CAPS 3. Safe Return Autoland Panel (if installed) 4. Task Lights 5. MFD 6. GTC 1 / SFD 7. RH Fresh Air Vent 8. Side Stick 9. GTC 2 10. Fire Extinguisher 11. Rudder Pedals 12. Side Storage Compartment 13. Center Storage Compartment 14. Left Side Console • ELT Remote • Starter Disable Switch • Alternate Static Source 15. USB Ports 16. Parking Brake 17. Brake Reset (if installed) 18. AFCS Mode Control Panel 19. LH Fresh Air Vent 20. Engine Start and Ignition Control 21. PFD 4 7 20 1 2 17 A Revision 1 P ILOT ’S I NFORMATION M ANUAL : CHAPTER 3 CIRRUS I NSTRUMENT PANEL SR20 3-6 P/N 44764-001 Figure 3-1: Instrument Panel and Console (2 of 2) 24 23 LEGEND 22. Audio Jacks 23. Fuel Tank Selector 24. Fuel Pump Switch 25. Circuit Breaker Panel 26. ECS Controls 29 28 27 22 27. Flap Selector Switch 28. Throttle 29. Mixture Lever 30. Friction Knob (if installed) 31. Fuel Selector Cover (Open Position) SR20_PM03_1017A 25 26 30 DETAIL A 31 Revision 1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 3 SR20 I NSTRUMENT PANEL P/N 44764-001 3-7 Bolster Panel Arrangement Overview A switch panel located in the bolster below the instrument panel contains switches and controls for the batteries (BAT 1 and BAT 2), alternators (ALT 1 and ALT 2), exterior lighting (STRB, LAND, and ICE), instrument panel dimmer knob (INST LIGHTS), and checklist thumbwheel (CHECKLIST). Serials 9750 thru 10614: A switch is present for pitot tube heat (PROBE HEAT). Serials 10615 and subs: Pitot tube heat is automatically controlled via avionics. Operation For specific bolster switch operation details, refer to the applicable system. Power Source For specific bolster switch power source details, refer to the applicable system. Figure 3-2: Bolster Switch Panel Arrangement ON CHECKLIST BAT2 BAT1 ALT1 ELECTRICAL ALT2 STRB LAND ICE PROBE HEAT INST LIGHTS LIGHTS ON ON LEGEND 1. Instrument Panel Dimmer Knob 2. Checklist Thumbwheel 3. Alternator Switches 4. Battery Switches 5. Exterior Lights Switches 6. Probe Heat Switch ( Serials 9750 thru 10614 ) 4 6 1 3 2 5 Revision 1 P ILOT ’S I NFORMATION M ANUAL : CHAPTER 3 CIRRUS I NSTRUMENT PANEL SR20 3-8 P/N 44764-001 Engine Start and Ignition Control Arrangement Overview The engine start controls are located on the left side of the instrument panel and contains the following: • Engine PUSH TO START button • Engine knob (OFF/RIGHT/LEFT/BOTH) Operation For specific center console control operation details, refer to Chapter 9: Powerplant, "Ignition and Starter System". Figure 3-3: Engine Start Control Arrangement Center Console Switch Panel Overview The CCSP is located below the center instrument panel and contains the following: • Environmental System Controls • Fuel Pump Switch • Flaps Selector Switch Operation For specific CCSP operation details, refer to the applicable system. SR20_PM03_1025 1 2 LEGEND 1. Engine Knob 2. Engine Start Button BOTH LEFT RIGHT OFF PUSH TO START ENGINE Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 3 SR20 I NSTRUMENT PANEL P/N 44764-001 3-9 Figure 3-4: Center Console Switch Panel System Circuit Breaker Panel Arrangement Overview System circuit breakers are located on the left side of the center console. For specific information about system circuit breaker locations, refer to “Figure 11-2: Circuit Breaker Panel”. Operation For specific pilot actions in response to System Annunciations, refer to Section 3: Emergency Procedures and Section 3A: Abnormal Procedures in the AFM. SR20_PM03_1028 3 1 2 LEGEND 1. Enviromental System Controls 2. Flap Selector Switch 3. Fuel Pump Switch 100% 50% UP FLAPS ON FUEL PUMP OFF Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 3 CIRRUS I NSTRUMENT PANEL SR20 3-10 P/N 44764-001 Safe Return Autoland Panel Arrangement (If Installed) Overview Safe Return Autoland panel is located aft of CAPS panel. Refer to “Figure 19-1: Safe Return Autoland”. Operation For specific Safe Return Autoland operation details, Refer to Chapter 19: Safe Return Autoland (Optional), "Safe Return Autoland (If Installed)" Revision 1 P/N 44764-001 4-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 4 SR20 TABLE OF C ONTENTS Chapter 4: Flight Instruments Table of Contents Flight Instruments................................................................................ 3 Attitude Indicator ............................................................................... 6 Overview ......................................................................................... 6 Operation......................................................................................... 6 Airspeed Indicator ............................................................................. 6 Overview ......................................................................................... 6 Operation......................................................................................... 6 Altimeter ............................................................................................ 7 Overview ......................................................................................... 7 Operation......................................................................................... 7 Horizontal Situation Indicator ............................................................ 8 Overview ......................................................................................... 8 Operation......................................................................................... 8 Vertical Speed Indicator .................................................................... 8 Overview ......................................................................................... 8 Operation......................................................................................... 8 Standby Flight Display....................................................................... 9 Overview ......................................................................................... 9 Operation......................................................................................... 9 Power Source ................................................................................ 10 Magnetic Compass (If Installed)...................................................... 10 Overview ....................................................................................... 10 Revision 1 P ILOT ’S I NFORMATION M ANUAL : CHAPTER 4 CIRRUS TABLE OF C ONTENTS SR20 4-2 P/N 44764-001 Revision 1 Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 4 SR20 F LIGHT I NSTRUMENTS P/N 44764-001 4-3 Flight Instruments Flight instruments and annunciations are displayed on the Primary Flight Display (PFD) located directly in front of the pilot in normal mode, and on the Multi Function Display (MFD) in reversionary mode. The primary flight instruments are arranged in the conventional basic “T” configura- tion. Standby instruments for airspeed, attitude, and altitude are displayed on GTC 1 (mounted on the LH bolster panel) by selecting the DISPLAY BACKUP push button on the center instrument panel. The primary and standby flight instruments utilize separate power sources. There are softkeys on the bottom of the PFD and the MFD. On the PFD, these can be used at any time. On the MFD, these can be used only when in reversionary mode. Refer to Chapter 16: Avionics, "Cirrus Perspective Touch+ Avionics System" for more details. For additional information on PFD and MFD operation, refer to Cirrus Perspective Touch+ Integrated Avionics System Pilot’s Guide. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 4 CIRRUS FLIGHT I NSTRUMENTS SR20 4-4 P/N 44764-001 Figure 4-1: Primary Flight Instruments (1 of 2) 180 120 250° 160 170 140 130 -450 3000 1 32 00 10 10 10 10 31 00 29 00 30 00 2 1 2 FEET 7 SR20_PM04_1031B 1 3 4 5 6 8 9 11 12 13 14 16 17 18 19 20 21 22 23 LEGEND 1. Percent Power 2. Reversionary Sensor Annunciation 3. Attitude Indicator 4. Slip Skid Indicator 5. Selected Altitude Bug 6. Altimeter 7. Flight ID 8. Selected Altitude 9. Vertical Speed Indicator (VSI) 10. Radar Altimeter 11. Minimum Descent Altitude/Decision Height 12. Barometric Altimeter Setting 13. Navigation Status Box 14. HSI 15. GPS AGL Altitude 16. Flight Timer 17. System Time 18. Ground Speed 19. Outside Air Temperature (F°) 20. Outside Air Temperature (C°) 21. True Airspeed 22. Wind Data 23. Indicated Airspeed 10 2 USING AHRS2 20 80 Power COM1 N 136.97 150 30 00 30 00 2100 FT BARO MIN 65 % 35 25 OAT 9° C OAT 48° F TAS 157 KT GS 161 KT GAGL FLT 0:17:33 UTC 15:37:59 DIS D LOLCU laf 6.5 0207 ETE NM 29.92 IN 1900 FT 15 30 15 6 N W S E 3 33 24 21 12 OBS 360° RNP 2.00 GPS 250 RA Revision 1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 4 SR20 F LIGHT I NSTRUMENTS P/N 44764-001 4-5 Figure 4-1: Primary Flight Instruments (2 of 2) 30 15 6 SR20_PM04_1126 LEGEND 1. Lubber Line 2. Current Heading 3. Turn Rate and Heading Trend Vector 4. Selected Course 5. Flight Phase 6. Course Deviation Indicator (CDI) 7. Aircraft Symbol 8. Rotating Compass Card 9. OBS Mode Active 10. To/From Indicator 11. Course Pointer 12. Selected Heading Bug 13. Lateral Deviation Scale 14. Navigation Source 15. Current Track Indicator 16. Selected Heading 17. Turn Rate Indicator N W S E 3 33 24 21 12 OBS HSI DETAIL ETE DIS NM 360° __:__ __._ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 RNP 2.00FMS HDG 360° DTK 360° Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 4 CIRRUS FLIGHT I NSTRUMENTS SR20 4-6 P/N 44764-001 Attitude Indicator Overview The primary attitude indicator is shown on the upper center of the PFD and displays pitch, roll, and slip/skid information provided by the Air Data, Attitude, and Heading Reference System (ADAHRS). Operation Above and below the horizon line, major pitch marks and labels are shown for every 5°, up to 80°. Between 25° below and 45° above the horizon line, the pitch index scale is graduated in 5° increments with every 10° of pitch labeled. Between 20° below and 20° above the horizon line, minor pitch marks occur every 2.5°. If pitch limits are exceeded in either the nose-up or nose-down attitude, red warning chevrons will appear and point the way back to level flight. The roll index scale is graduated with major tick marks at 30° and 60° and minor tick marks at 10°, 20°, and 45°. The roll pointer is slaved to the airplane symbol. The slip-skid indicator is the bar beneath the roll pointer. The indicator moves with the roll pointer and moves laterally away from the pointer to indicate lateral acceleration. Slip/skid is indicated by the location of the bar relative to the pointer. One bar displacement is equal to one-half ball displacement on a traditional slip/skid indicator. Additionally, a standby attitude indicator is provided by the standby atti- tude source. In certain scenarios, the standby attitude indicator is displayed automatically. It can be viewed at anytime by selecting the DISPLAY BACKUP push button on the center instrument panel. Airspeed Indicator Overview Primary airspeed data is provided by an Air Data Computer (ADC) and is shown as a vertical tape along the upper left side of the PFD. Additionally, a standby airspeed indicator is provided by the standby air data source. In certain scenarios, the standby airspeed indicator is displayed automatically. It can be viewed at anytime by selecting the DISPLAY BACKUP push button on the center instrument panel. Operation The airspeed scale is graduated with major tick marks at intervals of 10 knots and minor tick marks at intervals of 5 knots. Speed indication starts at 20 knots, with 60 knots of airspeed viewable at any time. The actual airspeed is displayed inside the black pointer. The pointer remains black until reaching the never-exceed speed (V NE), at which point it turns red. Color coded bars are provided to indicate flap operating range, normal operating range, caution range, and never-exceed speed. Speeds above the Revision 1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 4 SR20 F LIGHT I NSTRUMENTS P/N 44764-001 4-7 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 a window on the bottom LH side of the PFD. Airspeed trend is also displayed as a magenta bar along side of the airspeed tape. Altimeter Overview Primary altitude data is provided by an ADC and is shown as a vertical tape along the upper right side of the PFD. The altimeter scale is graduated with major tick marks at intervals of 100 feet and minor tick marks at intervals of 20 feet. Six hundred (600) feet of barometric altitude is viewable at any time. • N OTE • To change altimeter barometric pressure setting units and/or to display selected attitude in meters, refer to Cirrus Perspective Touch+ Avionics System Pilot Cockpit Reference Guide. Additionally, a standby altimeter indicator is provided by the standby air data source for display on GTC 1 by selecting the DISPLAY BACKUP push button on the center instrument panel. Operation The local barometric pressure is set using the barometric adjustment knob on the center instrument panel. The selectable altitude reference bug is displayed on the altimeter tape and is set using the altitude selection knob on the GMC 707. Barometric minimum descent altitude (MDA, or Deci- sion Height, DH), can be preset. Altimeter trend is also displayed as a magenta bar along side of the altimeter tape. The PFD Altitude is corrected for static source position error (normal static source/flaps UP), 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. Revision 1 P ILOT ’S I NFORMATION M ANUAL : CHAPTER 4 CIRRUS FLIGHT I NSTRUMENTS SR20 4-8 P/N 44764-001 Horizontal Situation Indicator Overview The Horizontal Situation Indicator (HSI) is displayed along the lower center of the PFD. Heading data is provided by ADAHRS and the onboard magnetometers. The HSI displays a rotating compass card in a heading-up orientation. Letters indicate the cardinal points and numeric labels occur every 30°. Major tick marks are at 10° intervals and minor tick marks at 5° intervals. Reference index marks are provided at 45° intervals around the compass card. A circular segment scale directly above the rotating compass card shows half and standard rates of turn based on the length of the turn rate trend vector. Operation The HSI presents heading, turn rate, course deviation, bearing, and naviga- tion source information in a 360° compass-rose format. The HSI contains a Course Deviation Indicator (CDI) with a course pointer arrow, a To/From arrow, a sliding deviation bar, and scale. The course pointer is a single line arrow (GPS, VOR1, and LOC1) or a double line arrow (VOR2 and LOC2) which points in the direction of the set course. The To/From arrow rotates with the course pointer and is displayed when the active NAVAID is received. The HSI heading reference bug is set using the HDG select knob on the GMC 707. The selected heading is displayed in a window above the upper LH 45° index mark and will disappear approximately 3 seconds after the HDG select knob stops turning. The Course Deviation Indicator (CDI) navigation source shown on the HSI is set using a touchscreen controller to select GPS, NAV1, or NAV2 inputs via PFW Home. The course pointer is set using the dual concentric knob (DCK) on a touchscreen controller. The selected course is displayed in a window above the upper RH 45° index mark and will disappear approxi- mately 3 seconds after the CRS select knob stops turning. Vertical Speed Indicator Overview Vertical speed data is provided by an ADC and is shown as a vertical tape along the right side of the altimeter on the PFD. The VSI scale is graduated with major tick marks at 1000 and 2000 fpm in each direction and minor tick marks at intervals of 500 fpm. Operation The vertical speed pointer moves up and down the fixed VSI scale and shows the rate of climb or descent in digits inside the pointer. A reference notch at the RH edge of the scale indicates 0 feet/min. Revision 1