PILOT’S INFORMATION MANUAL for the CIRRUS SR22T with Cirrus Perspective Touch+ Avionics System

Chapter 2 .....................................................................................Flight Controls Chapter 3 .................................................................................Instrument Panel Chapter 4 ...............................................................................Flight Instruments 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 .....................................................................................Ice Protection Chapter 17 .............................................................................................. Avionics Chapter 18 ................................................................................... Cabin Features Chapter 19 ................................................................................Recovery System Chapter 20 ...........................................................................Log of Supplements Original Issue FRONT M ATTER CIRRUS FOREWORD SR22T Front Matter-2 P/N 44768-001 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, or from the Authorized Service Center website. Paper copies of revisions and supplements can be purchased from Cirrus Direct at www.buycirrusdirect.com. Original Issue CIRRUS FRONT MATTER SR22T SUPPLEMENTS P/N 44768-001 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 SR22T Front Matter-4 P/N 44768-001 Original Issue Intentionally Left Blank P/N 44768-001 1-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 1 SR22T 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 SR22T 1-2 P/N 44768-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 1 SR22T A IRFRAME P/N 44768-001 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 47.25-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 SR22T 1-4 P/N 44768-001 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. Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 1 SR22T A IRFRAME P/N 44768-001 1-5 Figure 1-1: Equipment Locations 5 27 19 21 20 6 4 SR22_PM01_1003 14 3 17 12 15 16 18 23 25 28 3 2 1 33 30 29 22 34 31 8 24 29 35 2 10 36 32 7 LEGEND 1. Fan 28 VDC 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. Fuel Tank Selector/AFSS 14. CAPS Activation Handle 15. Egress Hammer 16. Cabin Speaker 17. Roll Servo 18. Convenience System Controller 19. Pitch Trim Adapter 20. Pitch Servo 21. XM Radio Receiver 22. Gateway Module (if installed) 23. Transponder 24. XM Satellite Data Link Receiver (if installed) 25. ELT 26. Yaw Servo (if installed) 27. Battery 2 28. Iridium Global Satellite Datalink (if installed) 29. Tiedown Loops 30. CAPS Parachute 31. Stormscope WX-500 (if installed) 32. ADF 33. TAS Receiver (if installed) 34. DME (if installed) 35. Single USB-C PD Charging 36. GMC 707 Mode Controller 37. GTC 1 38. Bolster Switch Panel 39. PFD 13 37 11 2 1 38 39 9 26 Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 1 CIRRUS A IRFRAME SR22T 1-6 P/N 44768-001 Original Issue Intentionally Left Blank P/N 44768-001 2-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 2 SR22T 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 SR22T 2-2 P/N 44768-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 2 SR22T F LIGHT C ONTROLS P/N 44768-001 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 supplied through the 2-amp PITCH TRIM circuit breaker on Essential Bus 2. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 2 CIRRUS FLIGHT C ONTROLS SR22T 2-4 P/N 44768-001 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 SR22_PM02_1006 4 5 4 1 23 6 6 Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 2 SR22T F LIGHT C ONTROLS P/N 44768-001 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 supplied through the 2-amp ROLL TRIM circuit breaker on Essential Bus 2. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 2 CIRRUS FLIGHT C ONTROLS SR22T 2-6 P/N 44768-001 Figure 2-2: Aileron System SR22_PM02_1012 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 SR22T F LIGHT C ONTROLS P/N 44768-001 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 SR22T 2-8 P/N 44768-001 Figure 2-3: Rudder System LEGEND 1. Spring Cartridge 2. Pulley 3. Rudder SR22_PM02_1015 2 2 2 1 3 Original Issue P/N 44768-001 3-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 3 SR22T 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 Switch Panel Arrangement.................................................... 7 Overview ......................................................................................... 7 Operation......................................................................................... 7 Protection ........................................................................................ 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 Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 3 CIRRUS TABLE OF C ONTENTS SR22T 3-2 P/N 44768-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 3 SR22T I NSTRUMENT PANEL P/N 44768-001 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 revisionary 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. Operation For specific pilot panel operation details, refer to the applicable system. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 3 CIRRUS I NSTRUMENT PANEL SR22T 3-4 P/N 44768-001 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 friction knob for adjusting throttle and mixture control feel and position stability is located on the right side of the console. A center console storage compartment is located between the Center Console Switch Panel (CCSP) and autopilot controller. A storage compart- ment and emergency egress hammer are installed inside the console armrest. Operation For specific center console control operation details, refer to the applicable system. Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 3 SR22T I NSTRUMENT PANEL P/N 44768-001 3-5 Figure 3-1: Instrument Panel and Console (1 of 2) 4 7 8 9 10 11 12 11 13 15 16 7 17 5 14 19 SR22_PM03_1020 LEGEND 1. Magnetic Compass (if installed) 2. CAPS 3. Task Lights 4. MFD 5. GTC 1 6. RH Fresh Air Vent 7. Side Stick 8. GTC 2 9. Fire Extinguisher 10. Rudder Pedals 11. Side Storage Compartment 12. Center Storage Compartment 13. Left Side Console • ELT Remote • Starter Disable Switch • Alternate Static Source 14. USB Ports 15. Parking Brake 16. AFCS Mode Control Panel 17. LH Fresh Air Vent 18. Engine Start and Ignition Control 19. PFD 3 6 18 1 2 A Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 3 CIRRUS I NSTRUMENT PANEL SR22T 3-6 P/N 44768-001 Figure 3-1: Instrument Panel and Console (2 of 2) BOOST FUEL PUMP HIGH BOOST PRIME 22 LEGEND 21. Audio Jacks 22. Fuel Tank Selector 23. Fuel Pump Switch 24. Circuit Breaker Panel 25. ECS Controls 28 27 26 21 26. Flap Selector Switch 27. Power Lever 28. Mixture Lever 29. Friction Knob 30. Fuel Selector Cover (Open Position) SR22_PM03_1021 24 25 29 DETAIL A 30 23 Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 3 SR22T I NSTRUMENT PANEL P/N 44768-001 3-7 Bolster Switch 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), pitot tube and lift transducer heat (PROBE HEAT), oxygen (OXY), ice protection (ON/HIGH/MAX, BKUP, and W/S), instrument panel dimmer knob (INST LIGHTS), and checklist thumbwheel (CHECKLIST). Operation For specific bolster switch operation details, refer to the applicable system. Protection For specific bolster switch power source details, refer to the applicable system. Figure 3-2: Bolster Switch Panel Arrangement MAX CHECKLIST ON ON 4 BAT2 BAT1 ALT1 ELECTRICAL ALT2 STRB LAND ICE PROBE HEAT OXY OFF NORM BKUP W/S INST LIGHTS LIGHTS ON ON ON ON HIGH SR22_PM03_1024 LEGEND 1. Oxygen Switch (if installed) 2. Instrument Panel Dimmer Knob 3. Checklist Thumbwheel 4. Ice Protection Switches (if installed) 5. Alternator Switches 6. Battery Switches 7. Exterior Lights Switches 8. Probe Heat Switch 6 8 1 2 3 7 5 ICE PROTECT Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 3 CIRRUS I NSTRUMENT PANEL SR22T 3-8 P/N 44768-001 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. SR22_PM03_1027 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 SR22T I NSTRUMENT PANEL P/N 44768-001 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. SR22_PM03_1030 3 1 2 LEGEND 1. Enviromental System Controls 2. Flap Selector Switch 3. Fuel Pump Switch 100% 50% UP FLAPS BOOST FUEL PUMP HIGH BOOST/ PRIME Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 3 CIRRUS I NSTRUMENT PANEL SR22T 3-10 P/N 44768-001 Original Issue Intentionally Left Blank P/N 44768-001 4-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 4 SR22T 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 Protection ...................................................................................... 10 Magnetic Compass (If Installed)...................................................... 10 Overview ....................................................................................... 10 Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 4 CIRRUS TABLE OF C ONTENTS SR22T 4-2 P/N 44768-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 4 SR22T F LIGHT I NSTRUMENTS P/N 44768-001 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 17: 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 SR22T 4-4 P/N 44768-001 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 SR22_PM04_1033 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. Minimum Descent Altitude/Decision Height 11. Barometric Altimeter Setting 12. Navigation Status Box 1 3 4 5 6 8 9 10 11 12 13 15 16 17 18 19 20 21 22 23 13. HSI 14. GPS AGL Altitude 15. Flight Timer 16. System Time 17. Ground Speed 18. Outside Air Temperature (F°) 19. Outside Air Temperature (C°) 20. True Airspeed 21. Angle of Attack 22. Wind Data 23. Indicated Airspeed 2 14 7 USING AHRS2 20 80 HDG AOA .60 1.0 2 Power COM1 N 136.97 150 30 00 30 00 2100 FT BARO MIN 65 % 0 35 25 OAT 9° C OAT 48° F TAS 157 KT GS 161 KT GAGL 1900 FT FLT 0:17:33 UTC 15:37:59 DIS NM D LOLCU laf 6.5 0207 ETE 29.92 IN 250° BARO MIN 30 15 6 N W S E 3 33 24 21 12 OBS 360° RNP 2.00 GPS Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 4 SR22T F LIGHT I NSTRUMENTS P/N 44768-001 4-5 Figure 4-1: Primary Flight Instruments (2 of 2) __:__ __._ 30 15 6 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 SR22_PM04_1128 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° RNP 2.00FMS HDG 360° DTK 360° Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 4 CIRRUS FLIGHT I NSTRUMENTS SR22T 4-6 P/N 44768-001 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 Attitude and Heading Reference System (AHRS). 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 module sensor. 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 MD302 standby attitude module sensor. 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 Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 4 SR22T F LIGHT I NSTRUMENTS P/N 44768-001 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 atti- tude module sensor available for display on the 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. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 4 CIRRUS FLIGHT I NSTRUMENTS SR22T 4-8 P/N 44768-001 Horizontal Situation Indicator Overview The Horizontal Situation Indicator (HSI) is displayed along the lower center of the PFD. Heading data is provided by an Attitude and Heading Reference System (AHRS) and the onboard magnetometers. The HSI displays a rotating compass card in a heading-up orientation. Letters indi- cate 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. Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 4 SR22T F LIGHT I NSTRUMENTS P/N 44768-001 4-9 Vertical speed must exceed 100 feet/min before digits will appear in the VSI pointer. If the rate of ascent/descent exceeds 2000 fpm, the pointer appears at the corresponding edge of the tape and the rate appears inside the pointer. Standby Flight Display Overview Attitude and airspeed indications are provided by the remote MD302 standby attitude module located on the bottom of the avionics shelf on the pilot’s side. Operation The remote MD302 standby attitude module is a combined standby airspeed indicator, standby altimeter, and standby attitude indicator. Standby Airspeed Indicator The standby airspeed indicator displays the current indicated airspeed (IAS). The digits of the display are enlarged for visibility and increment by one (1) unit. The units will scroll to assist in quick reference as to the increasing or decreasing nature of the aircraft’s airspeed. Airspeed units are always in knots (Kts). Standby Altimeter The standby altimeter displays the altitude and the barometric pressure. The altitude window displays the current, barometric corrected altitude. The display will scroll to assist in quick reference as to the increasing or decreasing nature of the aircraft’s altitude. Altitude is displayed in feet, but may also be shown in meters. Metric display is pilot-selectable via the touchscreen softkey bezel button. The barometer window shows the currently set barometric pressure located at the bottom of the altitude tape. Setting the current barometric pressure compensates the altitude for the appropriate environmental conditions. When the LH touchscreen controller is transitioned to the standby flight display, the current barometric setting from the PFD syncs to the standby flight display. The barometric setting for the standby display can then be further adjusted by simply turning the bottom knob on GTC 1. Barometric pressure units are displayed in inches of mercury (inHg), but may also be displayed in millibars (mb) via the pilot-selectable softkey bezel button on GTC 1. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 4 CIRRUS FLIGHT I NSTRUMENTS SR22T 4-10 P/N 44768-001 Standby Attitude Indicator The attitude indicator gives backup indication of flight attitude. Bank atti- tude is indicated by a pointer at the top of the indicator relative to the roll scale with index marks at 0°, 10°, 20°, 30°, 45°, and 60° either side of the center mark. A fixed symbolic airplane superimposed over a movable mask containing a representative white horizon line, which divides the mask into two sections, indicates pitch and roll attitudes. The upper blue “sky” section and the lower brown “ground” sections have pitch reference lines useful for pitch attitude control. The slip indicator portion of the display will always appear at the top of the attitude display, below the roll pointer. Indicator behavior is the same as that found on the PFD. Display of data from the sensor is available on GTC 1 by pressing the DISPLAY BACKUP push button located on the center instrument panel between the PFD and MFD. Standby flight display can also be presented automatically for certain sensed situations, if the system decides it is warranted. Protection 28 VDC for remote MD302 standby attitude module operation is supplied through the 5-amp STNDBY ATT A circuit breaker on Essential Bus 1 and through the 5-amp STNDBY ATT B circuit breaker on Main Bus 2. Magnetic Compass (If Installed) Overview A conventional, internally lighted, liquid filled, magnetic compass is installed on the windshield. A compass correction card is installed with the compass. Original Issue P/N 44768-001 5-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 5 SR22T TABLE OF C ONTENTS Chapter 5: Wing Flaps Table of Contents Wing Flaps .......................................................................................... 3 Flap Control System.......................................................................... 3 Overview ......................................................................................... 3 Operation......................................................................................... 5 Controls ........................................................................................... 5 Indications ....................................................................................... 7 Protection ........................................................................................ 8 Alerts ............................................................................................... 8 Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 5 CIRRUS TABLE OF C ONTENTS SR22T 5-2 P/N 44768-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 5 SR22T WING F LAPS P/N 44768-001 5-3 Wing Flaps Flap Control System Overview The electrically controlled, single-slotted flaps provide low-speed lift enhancement. Each flap is manufactured of aluminum and connected to the wing structure at three hinge points. Rub strips are installed on the top leading edge of each flap as an intentional wear item between the flap and wing flap cove. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 5 CIRRUS W ING F LAPS SR22T 5-4 P/N 44768-001 Figure 5-1: Wing Flaps SR22_PM05_1036 2 1 4 3 LEGEND 1. RH Flap 2. Torque Tube 3. Flap Actuator 4. LH Flap Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 5 SR22T WING F LAPS P/N 44768-001 5-5 Operation The flaps are selectively set to three positions: UP, 50%, and 100% by oper- ating the flaps selector switch. The flaps selector switch positions the flaps through a motorized linear actuator mechanically connected to both flaps by a torque tube. Proximity switches on the actuator limit flap travel to the selected position and provide position indication. The Garmin avionics monitors the flap actuator position sensors and the flaps selector switch to control flap positions. The wing flap inhibit system monitors sensed flap position and commanded flap position. This feature prevents the flaps from extending or retracting according to the aircraft’s airspeed. If the flap overspeed or underspeed limits are exceeded while a new flap position is selected or while the flaps are in motion and prior to reaching the selected flap position, the flap inhibit system will prevent flap motion until the FLAPS AIRSPEED INHIBIT Caution CAS message is cleared. Controls An airfoil-shaped flaps selector switch is located on the CCSP. The selector switch is marked and has detents at three positions: UP, 50%, and 100%. Setting the switch to the desired position will cause the flaps to extend or retract to the appropriate setting. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 5 CIRRUS W ING F LAPS SR22T 5-6 P/N 44768-001 Figure 5-2: Flaps Selector Switch SR22_PM05_1039 1 LEGEND 1. Flaps Selector Switch FLAPS UP 50% 100% Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 5 SR22T WING F LAPS P/N 44768-001 5-7 Indications • N OTE • Flap position is indicated in the left side of the MFD on the Engine Indication System (EIS) section displayed as UP, 50%, and 100%. Figure 5-3: Flaps Indication A FLAPS AIRSPEED INHIBIT Caution CAS message will be displayed, and flaps will not actuate, under the following conditions: • Airspeed is less than 74 KIAS, and flaps are then selected to 0%. • Airspeed is less than 70 KIAS or greater than 150 KIAS, and flaps are then selected to 50%. • Airspeed is greater than 110 KIAS, and flaps are then selected to 100%. Selected flap position is highlighted in a cyan box. When the flaps reach a given position the text is highlighted green and the flap symbol is colored cyan. The flap symbol turns white when the flaps are in an intermediate position. The flap symbol will turn amber under certain failure conditions. The maximum flap extended speed (V FE ) for the adjacent flap setting will be displayed directly below the flap widget. SR22_PM05_1042 1 2 LEGEND 1. Flaps Position 2. Maximum Flap Extended Speed Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 5 CIRRUS W ING F LAPS SR22T 5-8 P/N 44768-001 Protection The wing flaps actuator and flap control switch are powered by 28 VDC through the 10-amp FLAPS circuit breaker on Non-Essential Bus. Alerts • N OTE • For specific pilot actions in response to System Annunciations, refer to Section 3: Emergency Procedures and Section 3A: Abnormal Procedures in the AFM. Original Issue P/N 44768-001 6-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 6 SR22T TABLE OF C ONTENTS Chapter 6: Landing Gear Table of Contents Landing Gear....................................................................................... 3 Main Gear.......................................................................................... 3 Overview ......................................................................................... 3 Nose Gear ......................................................................................... 3 Overview ......................................................................................... 3 Brake System .................................................................................... 3 Overview ......................................................................................... 3 Operation......................................................................................... 3 Indications ....................................................................................... 4 Alerts ............................................................................................... 4 Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 6 CIRRUS TABLE OF C ONTENTS SR22T 6-2 P/N 44768-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 6 SR22T L ANDING G EAR P/N 44768-001 6-3 Landing Gear Main Gear Overview The main landing gear are bolted to composite wing structure between the wing spar and shear web. The landing gear struts are constructed of composite material for fatigue resistance. The main wheels and wheel pants are bolted to the struts. Each main gear wheel has a 15 x 6.0 x 6 tubeless tire installed. Standard wheel pants are removable to provide access to tires and brakes. Access doors in the wheel pants allow tire inflation and pressure checking. Each main gear wheel is equipped with an independent, hydrau- lically operated single cylinder, dual piston, disc brake. Nose Gear Overview The nose gear strut is of tubular steel construction and is attached to the steel engine mount structure. Nose gear shock absorption is provided by an oleo strut. The nose wheel is free castering and can turn through an arc of approximately 170 degrees (85 degrees either side of center). Steering is accomplished by differential application of individual main gear brakes. The nosewheel has a 5.0 x 5 tubeless tire installed. Brake System Overview 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 for each rudder pedal, a hydraulic fluid reservoir, a parking brake valve, a single disc brake assembly on each main landing gear wheel, and associated hydraulic plumbing and wiring. The main wheel brakes are set for parking by using the parking brake handle near the pilot’s knees. Brake lines from the toe brakes to the main wheel brake calipers are plumbed through a parking brake valve. Operation Braking pressure is initiated by depressing the top half of a rudder pedal (toe brake). The brakes are plumbed so that depressing either the pilot’s or copilot’s left or right toe brake will apply the respective (left or right) main wheel brake. The reservoir is serviced with MIL-PRF-87257 hydraulic fluid. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 6 CIRRUS L ANDING GEAR SR22T 6-4 P/N 44768-001 Brake system malfunction or impending brake failure may be indicated by a gradual decrease in braking action after brake application, noisy or drag- ging brakes, soft or spongy pedals, excessive travel, and/or weak braking action. Should any of these symptoms occur, immediate maintenance is required. If, during taxi or landing roll, braking action decreases, let up on the toe brakes and then reapply the brakes with heavy pressure. If the brakes are spongy or pedal travel increases, pumping the pedals may build braking pressure. • CAUTION • Do not set the parking brake in flight. If a landing is made with the parking brake valve set, tire damage may occur. To apply the parking brake, set desired brake pressure with the rudder-pedal toe brakes, and then pull the parking brake handle aft. To release the parking brake, push the handle in. Indications The parking brake position status is displayed on the Status & Info Synoptic Page. When the parking brake is applied, the SET status is shown in black text with an amber background below the “Parking Brake” gray label. Alerts An alert indicates in the CAS window on the PFD when the parking brake is set. Original Issue P/N 44768-001 7-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 7 SR22T TABLE OF C ONTENTS Chapter 7: Seats Table of Contents Seats ................................................................................................... 3 Crew Seats........................................................................................ 3 Overview ......................................................................................... 3 Operation......................................................................................... 3 Controls ........................................................................................... 3 Passenger Seats ............................................................................... 5 Overview ......................................................................................... 5 Operation......................................................................................... 5 Controls ........................................................................................... 5 Seat Belt and Shoulder Harness ....................................................... 7 Overview ......................................................................................... 7 Operation......................................................................................... 7 Inflatable Restraints........................................................................... 8 Overview ......................................................................................... 8 Operation......................................................................................... 8 Child Restraint System...................................................................... 8 Overview ......................................................................................... 8 Operation......................................................................................... 9 Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 7 CIRRUS TABLE OF C ONTENTS SR22T 7-2 P/N 44768-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 7 SR22T S EATS P/N 44768-001 7-3 Seats Crew Seats Overview This airplane has two individual front crew seats. The front seats are adjust- able fore and aft and the seat backs can be reclined for passenger comfort or folded forward for rear seat access. Integral headrests are provided. Operation • CAUTION • Do not kneel or stand on the seats or damage to the energy absorp- tion materials in the seat bottoms may occur. The fore and aft travel path is adjusted through the seat position control located below the forward edge of the seat cushion. The seat track is angled upward for forward travel so the seat will be positioned slightly higher as the seat moves forward. The seatbacks can be reclined for pilot comfort or folded forward for rear seat access. Integral headrests are provided. Recline position is controlled through levers located on the side of the seatbacks. Controls Recline position is controlled through levers located on each side of the seat backs. To position front seat fore and aft 1. Grab the hand hold below the bolsters. 2. Lift the position control handle. 3. Slide the seat into position. 4. Release the handle and check that the seat is locked in place. Shifting the seat forward/backward can help verify the seat is locked in place. To adjust recline position 1. Actuate and hold the seat back control lever. 2. Position the seat back to the desired angle. 3. Release the control lever. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 7 CIRRUS S EATS SR22T 7-4 P/N 44768-001 Figure 7-1: Crew Seats SR22_PM07_1045 1 3 4 3 2 A A DETAIL LEGEND 1. Co-pilot Seat 2. Pilot Seat 3. Seat Back Control Lever 4. Position Control Handle Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 7 SR22T S EATS P/N 44768-001 7-5 Passenger Seats Overview The rear seats employ a one-piece bench seat and two seat backs configured in 60/40 split. This “2+1” seating configuration provides for a center seat/restraint area for a third passenger on the wider left hand seat. Operation • CAUTION • Do not kneel or stand on the seats or damage to the energy absorp- tion materials in the seat bottoms may occur. Each seat back reclines independently of each other and can be folded forward to provide a semi-flat surface for cargo extending forward from the baggage compartment. Controls Recline position is controlled through a lever located on either side of the seat. To fold seat back forward 1. With no pressure on the seat back, rotate the lever to the recline posi- tion and fold the seat back forward. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 7 CIRRUS S EATS SR22T 7-6 P/N 44768-001 Figure 7-2: Rear Seats Location SR22_PM07_1048 1 2 LEGEND 1. Passenger Seats 2. Recline Lock Mechanism 3 3. Seat Back Control Lever Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 7 SR22T S EATS P/N 44768-001 7-7 Seat Belt and Shoulder Harness Overview Integrated seat belt and shoulder harness assemblies with inertia reels are provided for the pilot and each passenger. Seats belts must be worn and tightened snug and low on the waist. The seats belts are designed to accommodate an approximately 5th percentile female and 95th percentile male. Those outside this range need to ensure the lap belt is securely tightened and there is sufficient room to maneuver around with the shoulder harness secured. The front seats use a 4-point inflatable restraint system. Forward seat belts are attached to the seat frame. The shoulder harnesses are attached to inertia reels mounted in the seat back. The rear seats use a 3-point safety harness consisting of one shoulder harness and a lap belt. The rear seat belts are attached to fittings on the cabin floor. The shoulder harnesses are attached to inertia reels mounted to the baggage compartment rear bulkhead. The inertia reels allow complete freedom of movement of the occupant’s upper torso. In the event of a sudden deceleration, the reels lock automati- cally to protect the occupants. It is recommended that the seat belts be stowed in the latched position when not in use. • WARNING • Ensure that no twists exist anywhere on the belt and that no slack exists between the occupant’s shoulder and the shoulder harness. Failure to do so could prevent the occupant from being properly restrained, which could cause injury. Operation To use forward restraints 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 harnesses should fit snug against the shoulder. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 7 CIRRUS S EATS SR22T 7-8 P/N 44768-001 To use aft restraints 1. Slip arm into the harness so that the harness extends over the occu- pant’s respective shoulder. 2. Hold the buckle and firmly insert the link. 3. Tighten lap belt by pulling excess shoulder belt through the tongue. 4. Ensure lap belt is snug. To release forward restraints 1. Grasp the top of the buckle opposite the link and pull outward. The link will slip free of buckle. 2. Slip arms from behind the harness. To release aft restraints 1. Press button on buckle. The tongue will slip free of the buckle. 2. Slip arm from behind the harness. Inflatable Restraints Overview An inflatable shoulder harness is integral to each front seat harness. The electronic module assembly, mounted below the cabin floor, contains a crash sensor, battery, and related circuitry to monitor the deceleration rate of the airplane. Operation In the event of a crash, the sensor evaluates the crash pulse and sends a signal to an inflator assembly mounted to the aft seat frame. This signal releases the gas in the inflator and rapidly inflates the airbag within the shoulder harness cover. After airbag deployment, the airbag deflates to enable the pilot/co-pilot to egress the airplane without obstruction. The crash sensor’s predetermined deployment threshold does not allow inadvertent deployment during normal operations, such as hard landings, strikes on the seat, or random vibration. Child Restraint System Overview The aircraft is equipped with provisions for installing two LATCH compliant child seats in the outboard rear seat positions, OR one non-LATCH compliant seat in the center rear seat position. Lower anchors for the LATCH compliant seats are located in the outboard seat positions. The non-LATCH compliant seat must be installed using the center seat belt. Three top tether anchors for the child seats are located on the rear bulkhead. Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 7 SR22T S EATS P/N 44768-001 7-9 Operation To install child seat 1. Fasten lower seat attachments to bench seat: a LATCH Compliant Outboard Seat: Fasten lower seat attachment to the outboard anchors in the bench seat. b Non-LATCH Compliant Center Seat: Using the center seat belt, fasten lower seat attachments to the bench seat as described by the manufacturer's instructions. 2. Locate top tether pass-through - a narrow slit in the seat back uphol- stery - near the top, outboard section of the seat back. • WARNING • Do not route child seat top tether over or around seat back. The top tether must be routed through the seat back pass-through for the child seat to function properly. 3. Route child seat’s top tether through the seat back pass-through. 4. Fasten top tether to rear bulkhead anchor. 5. Firmly tension the child seat straps according to the manufacturer’s instructions. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 7 CIRRUS S EATS SR22T 7-10 P/N 44768-001 Original Issue Intentionally Left Blank P/N 44768-001 8-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 8 SR22T TABLE OF C ONTENTS Chapter 8: Doors and Windows Table of Contents Doors and Windows ............................................................................ 3 Cabin Doors ...................................................................................... 3 Overview ......................................................................................... 3 Operation......................................................................................... 3 Control ............................................................................................. 3 Indications ....................................................................................... 3 Baggage Compartment Door ............................................................ 3 Overview ......................................................................................... 3 Operation......................................................................................... 4 Control ............................................................................................. 4 Indications ....................................................................................... 4 Baggage Tie-Downs/Cargo Net ........................................................ 4 Overview ......................................................................................... 4 Emergency Egress Hammer ............................................................. 5 Overview ......................................................................................... 5 Operation......................................................................................... 5 Remote Keyless Entry (If Installed) ................................................... 5 Overview ......................................................................................... 5 Operation......................................................................................... 5 Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 8 CIRRUS TABLE OF C ONTENTS SR22T 8-2 P/N 44768-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 8 SR22T D OORS AND W INDOWS P/N 44768-001 8-3 Doors and Windows Cabin Doors Overview Two large forward hinged doors allow crew and passengers to enter and exit the cabin. The door handles use two over center latches that engage a striker pin on the fuselage door opening. Gas charged struts provide assis- tance in opening the doors. Front seat armrests are integrated with the doors. Unique keys are provided for the fuel caps, baggage door, and engine starter disable switch. The door windows serve as an emergency exit. Operation To open doors from outside 1. Rotate handle up until unlatched. 2. Pull door open. To close door from outside 1. Pull down on the door to close it. 2. Rotate door handle down. The handle will spring back into the pocket. To open door from inside 1. Rotate door handle up. 2. Push door outside to open. To close door from inside 1. Pull down on door to close it. 2. Rotate door handle down. Control The cabin doors are unlocked or locked from the outside with a key lock or a key fob (if installed). Refer to Chapter 8: Doors and Windows, "Remote Keyless Entry (If Installed)" for more details. Indications The cabin door status is displayed on the Status & Info Synoptic Page. The OPEN or CLOSED status is shown in white letters below the “Cabin Door” gray label. Baggage Compartment Door Overview The baggage compartment door, located on the left side of the fuselage aft of the wing, allows entry to the baggage compartment. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 8 CIRRUS DOORS AND W INDOWS SR22T 8-4 P/N 44768-001 The baggage compartment extends from behind the rear passenger seat to the aft cabin bulkhead. The rear seats can be folded forward to provide additional baggage area for long or bulky items. Operation To open baggage door 1. Press button at baggage door. 2. Pull baggage door open. To close baggage door 1. Close and latch baggage door. Control The baggage door is unlocked or locked from the outside with a key lock or a key fob (if installed). Refer to Chapter 8: Doors and Windows, "Remote Keyless Entry (If Installed)" for more details. Indications The baggage door status is displayed on the Status & Info Synoptic Page. The OPEN or CLOSED status is shown in white letters below the “Baggage Door” gray label. Baggage Tie-Downs/Cargo Net Overview • CAUTION • If not adequately restrained, baggage compartment items may pose a projectile hazard to cabin occupants in the event of rapid deceleration. Secure all baggage items with tie-down straps or cargo net. Four baggage tie-down straps are provided with the aircraft to secure items in the baggage compartment. Each strap assembly has a hook at each end and a cam-lock buckle in the middle. The hook ends clip over loop fittings installed in the baggage floor and in the rear bulkhead. The tie-down straps should be stowed attached and tightened to the fittings. The aircraft is equipped with a retractable cargo net to secure items in the baggage compartment. Integral inertia reels attached to the rear bulkhead allow the cargo net to be extended forward, placed over baggage, and secured to the seat back via four latch assemblies. The cargo net should be stowed attached to the seat back fittings. The cargo net is not functional when rear seats are folded forward. Use conventional tie-down straps in this configuration. Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 8 SR22T D OORS AND W INDOWS P/N 44768-001 8-5 Emergency Egress Hammer Overview A hammer is located in the center armrest. Operation In the event where the cabin doors are jammed or inoperable, the hammer may be used to break through the acrylic windows to provide an escape path. Remote Keyless Entry (If Installed) Overview Remote operation of the cabin and baggage door locks is provided by a battery-powered key fob. An electronic key lock is performed with the Convenience System Controller (CSC) which receives signals from a key fob to control door locks using solenoids as their electro-mechanical device to engage locking mechanisms. Operation When BAT 1 switch is turned on, the cabin doors will automatically unlock via the door solenoid lockout device. This device will also prevent any further key fob commands to the cabin doors while the BAT 1 switch is ON. When BAT 1 switch is turned on, the baggage door will automatically lock after a 5-minute delay as long as all doors are closed. If any door is open at the end of 5 minutes, the timer will restart. When BAT 1 switch is turned OFF, all doors will automatically unlock. The key fob complies with part 15 of the FCC Rules. Operation is subject to the following two conditions: 1. This device may not cause harmful interference. 2. This device must accept any interference received, including interfer- ence that may cause undesired operation. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 8 CIRRUS DOORS AND W INDOWS SR22T 8-6 P/N 44768-001 Original Issue Intentionally Left Blank P/N 44768-001 9-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 9 SR22T TABLE OF C ONTENTS Chapter 9: Powerplant Table of Contents Powerplant .......................................................................................... 3 Engine ............................................................................................... 3 Overview ......................................................................................... 3 Operation......................................................................................... 3 Controls ........................................................................................... 5 Indications ....................................................................................... 6 Propeller .......................................................................................... 10 Overview ....................................................................................... 10 Operation....................................................................................... 10 Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 9 CIRRUS TABLE OF C ONTENTS SR22T 9-2 P/N 44768-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 9 SR22T POWERPLANT P/N 44768-001 9-3 Powerplant Engine Overview The airplane is powered by a Continental Motors TSIO-550-K, twin turbo- charged, direct drive, fuel injected, air cooled, horizontally opposed 6 cylinder engine. The engine has a 550 cubic inch displacement and is rated to 315 bhp at 2500 RPM. The engine utilizes a top air induction system, engine mounted throttle body, bottom exhaust system, and a full flow spin-on disposable oil filter. Engine front accessories include a hydrauli- cally operated propeller governor, a gear-driven primary alternator and a belt-driven secondary alternator. Rear engine accessories include a starter, gear driven oil pump, gear driven fuel pump, and dual gear driven magnetos. The engine is attached to the firewall by a six-point steel engine mount. The firewall attach points are structurally reinforced with gusset-type attach- ments that transfer thrust and bending loads into the fuselage shell. Operation 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 an eight-quart capacity sump through an oil suction strainer screen and directed through the oil filter to the engine-mounted oil cooler by a positive displacement oil pump. The oil pump is equipped with a pressure relief valve at the pump output end to bypass oil back to the pump inlet should the pump exceed limits. The oil cooler is equipped with a temperature control valve set to bypass oil if the temperature is below approximately 180 °F (82 °C). Bypass or cooled oil is then directed through oil galleries to the engine rotating parts and piston inner domes. Oil is also directed to the propeller governor to regulate propeller pitch. The complete oil system is contained in the engine. An oil filler cap and dipstick are located inboard, at the left rear of the engine. The filler cap and dipstick are accessed through a door on the top left side of the engine cowling. Ignition and Starter System Two engine-driven magnetos and two spark plugs in each cylinder provide engine fuel ignition. The right magneto fires the lower right and upper left spark plugs, and the left magneto fires the lower left and upper right spark plugs. Normal operation is conducted with both magnetos, as more complete burning of the fuel-air mixture occurs with dual ignition. A rotary-type engine knob and push button start switch, located on the instrument panel, and keyed STARTER DISABLE switch, located on the left side of the center console, controls ignition and starter operation. The Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 9 CIRRUS POWERPLANT SR22T 9-4 P/N 44768-001 engine knob is labeled OFF - RIGHT - LEFT - BOTH. In the OFF position, the starter is electrically isolated, the magnetos are grounded and will not operate. Normally, the engine is operated on both magnetos (switch in BOTH position) except for magneto checks and emergency operations. The RIGHT and LEFT positions are used for individual magneto checks and for single magneto operation when required. When the BAT1 switch is ON and starter disable switch is enabled, rotating the engine knob to the BOTH position and pressing the start button energizes the starter and acti- vates both magnetos. When the BAT1 switch is OFF and the engine knob is not in the OFF position, an intermittent aural warning tone will sound to alert the pilot that the magnetos are not grounded. 28 VDC for starter operation is supplied through the 2-amp STARTER circuit breaker on Non-Essential Bus. Air Induction System Induction air enters the engine compartment through two NACA ducts located in the lower engine cowls. The air continues to the air boxes where it is filtered and ducted into the compressor housing where the compressor wheel, spinning at a high RPM, increases the air pressure which provides a greater mass of air available to the engine for the combustion cycle. From the compressor housing, the air is ducted through the intercoolers where the air temperature is lowered which further increases the density of the induction air. Downstream of the intercoolers the airflow joins at the “Y” junction of intake tubes, then passes through the throttle body and into the intake manifold where it is divided by the intake pipes flowing to each cylinder. In the case of filter blockage or induction ice, alternate air can enter the engine via the alternate air assembly located in the lower front of the engine and connected to the LH and RH air boxes. Under normal conditions, the alternate air assembly door is held closed by magnetic force. If the air induction system should become blocked, suction created by the engine will open the door and draw unfiltered air from inside the cowl. When the door opens, a switch opens which causes an annunciation on the Primary Flight Display to alert the pilot. Use of alternate air will result in a reduction of engine power due to lower inlet air pressure and higher air temperature. Additionally, a reduction in manifold pressure will occur when operating above the critical altitude and low RPM where the turbocharger wastegate is closed. Engine Exhaust After leaving the cylinders, exhaust gases flow through the exhaust collector to the turbocharger turbine housing inlet. The exhaust gas flow provides turbine wheel rotation then exits through the turbine housing discharge port and overboard through tailpipes exiting through the lower cowling. Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 9 SR22T POWERPLANT P/N 44768-001 9-5 Engine Fuel Injection The multi-nozzle, continuous-flow fuel injection system supplies fuel for engine operation. An engine driven fuel pump draws fuel from the selected wing tank and passes it to the mixture control valve integral to the pump. The mixture control valve proportions fuel in response to the pilot oper- ated mixture control lever position. From the mixture control, fuel is routed to the fuel-metering valve on the air-induction system throttle body. The fuel-metering valve adjusts fuel flow in response to the pilot controlled power lever position. From the metering valve, fuel is directed to the fuel manifold valve (spider) and then to the individual injector nozzles. The system meters fuel flow in proportion to engine RPM, mixture setting, and throttle angle. Manual mixture control and idle cut-off are provided. An electric fuel pump provides fuel boost for vapor suppression and for priming. Engine Cooling Engine cooling is accomplished by discharging heat to the oil and then to the air passing through the oil cooler, and by discharging heat directly to the air flowing past the engine. Cooling air enters the engine compartment through the two inlets in the cowling. Aluminum baffles direct the incoming air to the engine and over the engine cylinder cooling fins where the heat transfer takes place. The heated air exits the engine compartment through louvered vents in the bottom of the cowlings. No movable cowl flaps are used. Turbochargers The TSIO-550-K has twin turbochargers which use exhaust gas flow to boost induction air pressure for increased power. There is one turbo- charger on each side of the engine. The turbochargers compress and raise the temperature of the incoming air before going to the intercoolers. The dual turbochargers are lubricated from external oil supply lines from a source at the bottom of the oil cooler. There is one oil pressure actuated wastegate on the left side of the engine controlling the amount of exhaust gas used by the turbochargers. Control is accomplished by a diaphragm actuated valve sensing differential pressure across the throttle plate and controlling the oil return flow rate from the wastegate. An overboost valve in the induction system provides protection from too much pressure by actuating at overly high manifold pressures. Controls Engine controls are easily accessible to the pilot on a center console. They consist of a single-lever power (throttle) control and a mixture control lever. A friction control wheel, labeled FRICTION, on the right side of the console is used to adjust control lever resistance to rotation for feel and control setting stability. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 9 CIRRUS POWERPLANT SR22T 9-6 P/N 44768-001 Engine Start Controls The engine start controls are located on the pilot’s side of the instrument panel to the left of the PFD. For additional information on the engine start controls, refer to Chapter 3: Instrument Panel, "Engine Start and Ignition Control Arrangement". Power (Throttle) Lever The single-lever throttle control, labeled MAX-POWER-IDLE, on the console adjusts the engine throttle setting. The lever is mechanically linked by cable to the air throttle body/fuel-metering valve. Moving the lever towards MAX opens the air throttle butterfly and meters more fuel to the fuel manifold. No propeller control is required. The governor is set to 2500 maximum RPM in climb and cruise. Mixture Control The mixture control lever, labeled RICH-MIXTURE-CUTOFF, on the console adjusts the proportion of fuel to air for combustion. The Mixture Control Lever is mechanically linked to the mixture control valve in the engine-driven fuel pump. Moving the lever forward (towards RICH) repo- sitions the valve allowing greater proportions of fuel and moving the lever aft (towards CUTOFF) reduces (leans) the proportion of fuel. The full aft position (CUTOFF) closes the control valve. Indications Engine information is displayed using gauges and numeric displays on the MFD’s EIS display. Engine data is acquired by the engine airframe unit which transmits the data to the EIS for display as described in the following pages. • N OTE • An amber “X” through any electronic display field indicates the field is not receiving valid data and is considered inoperative. Engine System Annunciations Engine system health, caution, and warning messages are displayed in the Crew Alerting System (CAS) window on the PFD. In combination with a CAS alert, the affected engine parameter displayed on the EIS changes to the corresponding color of CAS alert and the annunciation system issues an audio alert. Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 9 SR22T POWERPLANT P/N 44768-001 9-7 • N OTE • For specific pilot actions in response to System Annunciations, refer to Section 3: Emergency Procedures and Section 3A: Abnormal Procedures in the AFM. For additional information on Engine Instrument Markings and Annunciations, refer to Section 2. Limitations in the AFM. For additional information on the System Annunciations and Alerts, refer to Cirrus Perspective Touch+ Avionics System Pilot’s Guide. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 9 CIRRUS POWERPLANT SR22T 9-8 P/N 44768-001 Figure 9-1: Engine Controls and Indicating 1500 SR22_PM09_1051 11 7 6 4 9 8 1 2 3 % Power 19.0 FFlow GPH 28.0 MAP inHg 2500 RPM 400 390 212 CHT °F Oil °F LEGEND 1. Power Lever 2. Mixture Lever 3. Friction Knob 4. Engine Manifold Pressure 5. Tachometer 6. Oil Pressure 7. Oil Temperature 8. Turbine Inlet Temperature 9. Cylinder Head Temperature 10. Fuel Flow 11. Percent Power 5 82 45 Oil PSI 1490 TIT °F 10 Original Issue CIRRUS P ILOT ’S I NFORMATION M ANUAL : C HAPTER 9 SR22T POWERPLANT P/N 44768-001 9-9 Tachometer Engine speed (RPM) is displayed on the EIS as a vertical bar and numeric display. Engine speed is displayed in revolutions per minute. During normal operating conditions, gauge pointer and display text appear in white. The tachometer receives a speed signal from a magnetic pickup sensor on the right hand magneto via the engine airframe unit. Exhaust Gas Temperature (EGT) Exhaust gas temperatures for all six cylinders are displayed on the Engine & Fuel Synoptic Page as vertical bar and numeric display. The numeric EGT value of the cylinder is displayed below the bar in white numerals. A sensor in the exhaust pipe of each cylinder measures exhaust gas temperature and provides a voltage signal to the engine airframe unit which processes and transmits the data to the Engine & Fuel Synoptic Page. Cylinder Head Temperature (CHT) Cylinder head temperatures for all six cylinders are displayed on the Engine & Fuel Synoptic Page as vertical bar and numeric display. The digital CHT value of the cylinder is displayed below the bar in white numerals. On the EIS, only the cylinder head temperatures of the hottest and coldest cylin- ders are displayed. The digital CHT value of the hottest and coldest cylin- ders are displayed below 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 processes and transmits the data to the EIS. Turbine Inlet Temperature (TIT) Turbine inlet temperature for the LH and RH turbochargers is displayed on the EIS as vertical bar and numeric display. The TIT left and right are displayed in degrees Fahrenheit. The digital TIT value of the turbine inlet is displayed below the bar in white numerals. A sensor in each turbocharger measures turbine inlet temperature and provides a voltage signal to the engine airframe unit which processes and transmits the data to the EIS. The TIT gauge is used as the primary source to lean fuel mixture. Oil Temperature Oil temperature is displayed on the EIS as a vertical bar and numeric display. The oil temperature is displayed in degrees Fahrenheit. The digital temperature value is displayed in white numerals below the vertical bar. The oil temperature sensor is mounted below the oil cooler and provides a signal to the engine airframe unit that is processed and transmitted to the EIS for display. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 9 CIRRUS POWERPLANT SR22T 9-10 P/N 44768-001 Oil Pressure Oil pressure is displayed on the EIS as a vertical bar and numeric display. The oil pressure is displayed in a digital bar in psi. The digital pressure value is displayed in white numerals below the vertical bar. The oil pressure sensor is mounted below the oil cooler and provides a signal to the engine airframe unit that is processed and transmitted to the EIS for display. Manifold Pressure Gauge Manifold pressure is displayed on the EIS as a vertical bar and numeric display. The pressure is displayed in inches of mercury to indicate engine power. The digital value is displayed in white numerals below the vertical bar. The manifold pressure sensor is mounted in the induction air manifold near the throttle body and provides a signal to the engine airframe unit that is processed and transmitted to the EIS for display. Percent Power Gauge Percent power is displayed on the EIS as an analog gauge and numeric display. The gauge will display 0 to 100% power while the numeric display will display 0 to 140%. The digital percent power value is displayed in white numerals below the gauge. The display units calculate the percentage of maximum engine power produced by the engine based on manifold pres- sure, manifold air temperature, engine speed, and fuel flow. Propeller Overview The airplane is equipped with a 78-inch diameter, composite, three-blade, constant speed, governor-regulated propeller. Operation The propeller governor automatically adjusts propeller pitch to regulate propeller and engine RPM by controlling the flow of engine oil – boosted to high pressure by the governing pump – to or from a piston in the propeller hub. Oil pressure acting on the piston twists the blades toward high pitch (low RPM). When oil pressure to the piston in the propeller hub is relieved, centrifugal force, assisted by an internal spring, twists the blades toward low pitch (high RPM). Any change in airspeed or load on the propeller results in a change in propeller pitch. The governor automatically adjusts propeller pitch to maintain 2500 RPM. Original Issue P/N 44768-001 10-1 CIRRUS P ILOT ’S I NFORMATION M ANUAL : CHAPTER 10 SR22T TABLE OF C ONTENTS Chapter 10: Fuel Table of Contents Fuel ..................................................................................................... 3 Fuel Storage System......................................................................... 3 Overview ......................................................................................... 3 Operation......................................................................................... 3 Controls ........................................................................................... 6 Indications ....................................................................................... 6 Alerts ............................................................................................... 8 Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 10 CIRRUS TABLE OF C ONTENTS SR22T 10-2 P/N 44768-001 Original Issue Intentionally Left Blank CIRRUS P ILOT ’S I NFORMATION M ANUAL : CHAPTER 10 SR22T F UEL P/N 44768-001 10-3 Fuel Fuel Storage System Overview A 92-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 47.25-gallon capacity (46-gallon usable) vented integral fuel tank and a fuel collector tank in each wing, an Auto- matic Fuel Selection System (AFSS) with manual override, an electric fuel pump, and an engine-driven fuel pump. Operation Fuel System Fuel is gravity fed from each tank to the associated collector tanks 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 vapor suppression. 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 engine airframe unit for fuel quantity display on the EIS. Fuel from each wing tank gravity feeds through strainers and a flapper valve to the associated collector tank in each wing. Each collector tank incorporates a flush mounted fuel drain and a vent to the associated fuel tank. Fuel system venting is essential to system operation. Blockage of the system will result in decreasing fuel flow and eventual engine fuel star- vation 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 engine-driven fuel pump pulls filtered fuel from the two collector tanks through the fuel tank selector valve. Fuel shutoff and tank selection is posi- tioned near the pilot for easy access. The AFSS uses a motorized mecha- nism to automatically move the fuel tank selector valve to the LEFT or RIGHT tank valve positions. In manual mode, the crew can select LEFT, RIGHT, or OFF valve positions. From the fuel pump, the fuel is metered to a flow divider, and delivered to the individual cylinders. Excess fuel is returned to the selected tank. A fuel quantity gauge is located on the EIS along the left edge of the MFD and in the fuel tank quantities on the Engine & Fuel Synoptic Page. Original Issue P ILOT ’S I NFORMATION M ANUAL : CHAPTER 10 CIRRUS FUEL SR22T 10-4 P/N 44768-001 Drain valves at the system low points allow draining the system for main- tenance and for examination of fuel in the system for contamination and grade. The fuel must be sampled prior to each flight. A sampler cup is provided to drain a small amount of fuel from the wing tank drains, the collector tank drains, and the gascolator drain. If takeoff weight limitations for the next flight pe