Display Systems. 1. General. A. Multi-Function Display (MFD) B. Primary Flight Display (PFD)

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1 CIRRUS AIRPLANE MAINTENANCE MANUAL Display Systems CHAPTER 31-60: DISPLAY SYSTEMS GENERAL 31-60: DISPLAY SYSTEMS 1. General This section covers those systems and components which give visual display of conditions in unrelated systems. This includes the multi-function display, primary flight display, and Flight Stream 510. (See Figure ) (See Figure ) A. Multi-Function Display (MFD) Airplanes are equipped with either a Garmin GDU inch or Garmin GDU inch multi-function display. The MFD, located above the center console, depicts navigation, terrain, lightning, traffic data, NAV/COM frequencies, and annunciation information. All engine data is displayed on a dedicated ENGINE page. When the ENGINE page is not shown, all essential engine information is shown on an engine strip at the edge of the display. Redundant power sources provide 28 VDC for MFD operation. Power is supplied through the 5-amp MFD A circuit breaker on Main Bus 3 and the 5-amp MFD B circuit breaker on Main Bus 1. Either circuit is capable of powering the MFD. System start-up is automatic once power is applied. Power-on default brightness is determined by ambient lighting and is user adjustable. For additional information on the MFD, refer to the Cirrus Perspective+ Integrated Avionics System Pilot s Guide. (Refer to 5-00) B. Primary Flight Display (PFD) Airplanes are equipped with either a Garmin GDU inch or Garmin GDU inch primary flight display. The PFD, located directly in front of the pilot, is intended to be the primary display of flight parameter information (attitude, airspeed, heading, and altitude) during normal operations. The PFD accepts data from a variety of sources, including the MFD and the Integrated Avionics Units through a high-speed data bus connection. In conjunction with Flight Management System Keyboard, the PFD also controls and displays all communication and navigation frequencies as well as displaying warning/status annunciations on aircraft systems. During engine start, reversionary operation (MFD failure), or when the reversionary switch is selected, engine system information is displayed on the PFD. Redundant power sources provide 28 VDC for PFD operation. Power is supplied through the 5-amp PFD A circuit breaker on the Essential Bus 1 and the 5-amp PFD B circuit breaker on Main Bus 2. Either circuit is capable of powering the PFD. System start-up is automatic once power is applied. 1

2 CHAPTER 31-60: DISPLAY SYSTEMS GENERAL CIRRUS AIRPLANE MAINTENANCE MANUAL Power-on default brightness is determined by ambient lighting and is user adjustable. Typical alignment time is 60 seconds from battery turn on. In the event of a detected display failure, the Perspective+ Avionics System automatically switches to reversionary mode. In reversionary mode, all essential flight information from the PFD is presented on the remaining display in the same format as in normal operating mode with the addition of the engine indicating system. The reversionary switch, located on the center instrument panel between the PFD and MFD, may be used to manually activate the reversionary mode. For additional information on the PFD, refer to the Cirrus Perspective+ Integrated Avionics System Pilot s Guide. (Refer to 5-00) C. Flight Stream 510 The optionally installed Flight Stream 510 Wireless Gateway provides connectivity between the integrated avionics system and compatible mobile devices. Data output from the Flight Stream 510 can be used to provide additional situational awareness for the pilot and passengers. The Flight Stream 510 provides remote display of position, velocity, time, altitude, attitude, and heading. In addition, flight plans can be transferred between compatible mobile devices and the integrated avionics system using supported mobile applications. Up to four Bluetooth devices can be paired to the Flight Stream 510. The Flight Stream 510 is installed in the bottom slot of the MFD. If the optional GDL 69 SXM transceiver is installed, the Flight Stream 510 also serves as a wireless GDL 69 controller through which the aircraft crew or passengers can select Sirius/XM audio channels, control volume, and view SXM weather on compatible mobile devices. If the optional GTX 345 transponder is installed, the Flight Stream 510 also provides remote display of ADS-B IN, TIS-B, and FIS-B data. For additional information on the Flight Stream 510, see Cirrus Perspective+ Integrated Avionics Pilot s Guide. (Refer to 5-00) For an overview of the Perspective+ Integrated Avionics system, see Chapter 42, Integrated Modular Avionics. (Refer to 42-00) 2

3 CIRRUS AIRPLANE MAINTENANCE MANUAL 2. Troubleshooting CHAPTER 31-60: DISPLAY SYSTEMS TROUBLESHOOTING Trouble - PFD Probable Cause Remedy PFD display does not power up. PFD failure. Ensure power is present at display backshell connector. Replace PFD. (Refer to 31-60) GIA1 and/or GIA2 to LRU data path not working. GIA1 and/or GIA2 configuration failure. Ensure GIA1 and GIA2 are configured correctly. Check wiring, connectors & pins as needed. 3

4 CHAPTER 31-60: DISPLAY SYSTEMS TROUBLESHOOTING CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : Flight Display System Schematic PFD PWR A 5 ESS BUS 1 MAIN BUS 3 PFD PWR B 5 MAIN BUS 2 MAIN BUS 1 MFD PWR A 5 MFD PWR B 5 PFD Satellite Data Link Receiver (optional) MFD FMS Keyboard Magnetometer 1 Magnetometer 2 Autopilot Mode Controller (optional) ADAHRS 1 ADAHRS 2 (optional) Integrated Avionics Unit 1 Integrated Avionics Unit 2 SR22_MM31_5053 4

5 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 31-60: DISPLAY SYSTEMS TROUBLESHOOTING Figure : Display Controls VOLUME KNOB FREQUENCY CONTROL NAV KNOB Multi-Function Display (MFD). VOLUME KNOB FREQUENCY CONTROL COM KNOB BARO KNOB RANGE / PAN KNOB KEYPAD FMS KNOB Primary Flight Display (PFD). FMS KNOB KEYPAD MODE KEYS COM / NAV / CRS / XPDR KNOB RANGE KNOB FREQUENCY CONTROL HDG KNOB ALT SEL KNOB NOTE Soft keys. Alphanumeric keys. Flight Management System Keyboard SR22_MM31_5055 5

6 CHAPTER 31-60: DISPLAY SYSTEMS 3. Maintenance Practices CIRRUS AIRPLANE MAINTENANCE MANUAL A. Multi-Function Display (MFD) (See Figure ) (1) Removal - MFD (a) (b) (c) (d) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Pull MFD A and MFD B circuit breakers. Remove captive screws securing MFD to instrument panel. CAUTION When removing MFD, do not strain wire harness by pulling cable too far from instrument panel. Partially slide MFD out of instrument panel, then disconnect electrical connector. Remove MFD from airplane. (2) Installation - MFD (a) (b) (c) (d) Partially slide MFD into instrument panel, then connect electrical connector to corresponding fitting. Install screws securing MFD to instrument panel. Reset MFD A and MFD B circuit breakers. If MFD has been repaired or is a new or different unit from originally installed unit, perform Adjustment/Test - Component Software and Configuration Loading. (Refer to 42-00) (e) Perform Operational Test - MFD. (Refer to 31-60) (3) Operational Test - MFD (a) (b) (c) Pull STARTER and FUEL PUMP circuit breakers. Set BAT 1, BAT 2, and AVIONICS switches to ON positions. Allow PFD and MFD to initialize for approximately one minute. 6

7 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 31-60: DISPLAY SYSTEMS (d) (e) (f) (g) (h) (i) NOTE In normal operating mode, a large red X through a data field indicates the data field is invalid. Valid data fields will not display a red X. At top corners of PFD and MFD, verify all NAV and COM fields are valid. On PFD, verify altitude, airspeed, vertical speed, TAS, and OAT fields are valid. Verify engine instrument fields are valid and read as follows: 1 Percent Power should read zero. 2 RPM should read zero. 3 Manifold Pressure should read the current barometric pressure ±0.5 inhg. 4 Fuel Used should read zero. 5 Fuel Flow should read zero. 6 Oil Temperature should read ambient. 7 Oil Pressure should read 0±2 PSI. 8 BAT 1 Current should read between 0 and 10 amps. NOTE Turn on large electrical loads (landing light, navigation lights, pitot heat, etc.) to ensure more amps are drawn when larger electrical loads are introduced. 9 Essential Bus Voltage should read 26±2 VDC. 10 Main Bus 1 Voltage should read 26±2 VDC. 11 Main Bus 2 Voltage should read 26±2 VDC. 12 CHT should read bottom of scale (All six CHTs). 13 EGT should read bottom of scale (All six EGTs). 14 ALT 1 should read 0 amps. 15 ALT 2 should read 0 amps. Press reversionary switch and verify both the PFD and MFD enter reversion mode. Both displays should have valid altitude, airspeed, vertical speed, and engine instrument fields. Press reversionary switch again and verify both the PFD and MFD are in normal display mode. Verify that no MANIFEST or CONFIGURATION alert messages appear in the lower right corner of the PFD (press the flashing ALERTS softkey to view alert messages). If any MANIFEST errors appear, the correct software to the related LRU must be loaded before proceeding. (Refer to 42-00) 7

8 CHAPTER 31-60: DISPLAY SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL (j) (k) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Reset STARTER and FUEL PUMP circuit breakers. 8

9 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 31-60: DISPLAY SYSTEMS Figure : MFD Installation - Serials w/ 12-Inch Display (1 of 2) INSTRUMENT PANEL (REF) INSTRUMENT PANEL (REF) LEGEND 1. MFD 2. Captive Screw 3. Connector SR22_MM31_5061 9

10 CHAPTER 31-60: DISPLAY SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : MFD Installation - Serials w/ 10-Inch Display (2 of 2) INSTRUMENT PANEL (REF) LEGEND 1. MFD 2. Captive Screw 3. Connector SR22_MM31_

11 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 31-60: DISPLAY SYSTEMS B. Primary Flight Display (PFD) (See Figure ) (1) Removal - PFD (a) (b) (c) (d) (e) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Pull PFD A and PFD B circuit breakers. Remove captive screws securing PFD to instrument panel. CAUTION When removing PFD, do not strain wire harness by pulling cable too far from instrument panel. Partially slide PFD out of instrument panel, then disconnect electrical connector. Remove PFD from airplane. (2) Installation - PFD NOTE If replacing the PFD with a new, repaired, or exchanged PFD, the new PFD must be temporarily installed in the MFD location while loading software and configuration files. Failure to do so may cause the system ID residing in the config module to be deleted. After system files have been installed, the PFD may be installed in the correct location. (a) If installing a new, repaired, or exchanged PFD, perform the following: 1 Remove MFD. (Refer to 31-60) 2 Partially slide PFD into MFD location of instrument panel, then connect electrical connector to corresponding fitting. 3 Install captive screws securing PFD to instrument panel. 4 Perform Adjustment/Test - Component Software and Configuration Loading. (Refer to 42-00) 5 Remove PFD from MFD location. 6 Partially slide PFD into PFD location of instrument panel, then connect electrical connector to corresponding fitting. 7 Install captive screws securing PFD to instrument panel. 8 Install MFD. (Refer to 31-60) 9 Perform Operational Test - PFD. (Refer to 31-60) 11

12 CHAPTER 31-60: DISPLAY SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL (b) If installing existing PFD, perform the following: 1 Partially slide PFD into instrument panel, then connect electrical connector to corresponding fitting. 2 Install captive screws securing PFD to instrument panel. 3 Reset PFD A and PFD B circuit breakers. 4 Perform Operational Test - PFD. (Refer to 31-60) (3) Operational Test - PFD (a) (b) (c) (d) (e) (f) (g) (h) (i) (j) Pull STARTER and FUEL PUMP circuit breakers. Set BAT 1, BAT 2, and AVIONICS switches to ON positions. Allow PFD and MFD to initialize for approximately one minute. NOTE In normal operating mode, a large red X through a data field indicates the data field is invalid. Valid data fields will not display a red X. At top corners of PFD and MFD, verify all NAV and COM fields are valid. On PFD, verify altitude, airspeed, vertical speed, TAS, and OAT fields are valid. Press reversionary switch and verify both the PFD and MFD enter reversion mode. Both displays should have valid altitude, airspeed, vertical speed, and engine instrument fields. Press reversionary switch again and verify both the PFD and MFD switch back to normal display mode. Verify that no MANIFEST or CONFIGURATION alert messages appear in the lower right corner of the PFD (press the flashing ALERTS softkey to view alert messages). If any MANIFEST errors appear, the correct software to the related LRU must be loaded before proceeding. (Refer to 42-00) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Reset STARTER and FUEL PUMP circuit breakers. 12

13 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 31-60: DISPLAY SYSTEMS Figure : PFD Installation - Serials w/ 12-Inch Display (1 of 2) INSTRUMENT PANEL (REF) 3 INSTRUMENT PANEL (REF) 1 2 LEGEND 1. PFD 2. Captive Screw 3. Connector SR22_MM31_

14 CHAPTER 31-60: DISPLAY SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : PFD Installation - Serials w/ 10-Inch Display (2 of 2) 3 INSTRUMENT PANEL (REF) 2 1 LEGEND 1. PFD 2. Captive Screw 3. Connector SR22_MM31_

15 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 31-60: DISPLAY SYSTEMS C. Reversionary Switch - Serials w/ 12-Inch Displays (See Figure ) (1) Removal - Reversionary Switch (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Remove glareshield. (Refer to 25-10) (c) Disconnect switch wiring from wire harness. (d) Remove cable tie securing switch wiring to instrument panel support. (e) Remove switch from instrument panel. (2) Installation - Reversionary Switch (a) Install switch to instrument panel. (b) Connect switch wiring to wire harness. (c) Position switch wiring to instrument panel support and secure with cable tie. (d) Install glareshield. (Refer to 25-10) 15

16 CHAPTER 31-60: DISPLAY SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL D. Reversionary Switch - Serials w/ 10-Inch Displays (See Figure ) (1) Removal - Reversionary Switch (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Remove glareshield. (Refer to 25-10) (c) Disconnect wiring from switch terminals. (d) Remove nut, washer, and gasket securing switch to instrument panel. Remove switch from airplane. (2) Installation - Reversionary Switch (a) Position switch to instrument panel and secure with gasket, washer, and nut. (b) Connect wiring to switch terminals. (c) Install glareshield. (Refer to 25-10) 16

17 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 31-60: DISPLAY SYSTEMS Figure : Reversionary Switch Installation - Serials w/ 12-Inch Displays (1 of 2) INSTRUMENT PANEL (REF) LEGEND 1. Reversionary Switch 2. Cable Tie Anchor 3. Cable Tie 4. Connector 5. Flexible Grommet 6. Screw SR22_MM31_

18 CHAPTER 31-60: DISPLAY SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : Reversionary Switch Installation - Serials w/ 10-Inch Displays (2 of 2) INSTRUMENT PANEL (REF) LEGEND 1. Reversionary Switch 2. Cable Tie Anchor 3. Cable Tie 4. Connector 5. Flexible Grommet 6. Screw 7. Gasket 8. Washer 9. Nut SR22_MM31_

19 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 31-60: DISPLAY SYSTEMS E. Flight Stream 510 (1) Removal - Flight Stream 510 (a) (b) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Remove Garmin Flight Stream 510 from bottom card slot of MFD. (2) Installation - Flight Stream 510 (a) (b) Insert Garmin Flight Stream 510 from bottom card slot of MFD. If unit is different from originally installed unit, perform Adjustment/Test - Flight Stream 510 Setup. (Refer to 31-60) (3) Adjustment/Test - Flight Stream 510 Setup For maintenance practices regarding Flight Stream 510 setup, see Cirrus Perspective+ Integrated Avionics Pilot s Guide. (Refer to 5-00) Dec 2017

20 CHAPTER 31-60: DISPLAY SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL Intentionally Left Blank 20

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