INDICATING/RECORDING SYSTEMS 1. DESCRIPTION This section describes the Indicating/Recording Systems which consists of an Annunciator Panel and related sensors and switches. A. Annunciator Panel - Serials 1005 thru 015, 016 & subs w/o Perspective Avionics The annunciator assembly is mounted on the flight instrument panel and contains six annunciators. Each annunciator has two individual LEDs as light sources. The annunciator panel has bright, dim, and test modes, which are activated by a toggle switch mounted next to the annunciator panel. In test mode all annunciators illuminate in the bright mode, allowing the pilot to verify that all LEDs are functional. The entire annunciator assembly is mounted on a printed circuit board, which decodes information from the individual sensors and illuminates the necessary annunciator. 8 VDC for annunciator operation is supplied through the -amp ANNUNCIATOR POWER circuit breaker on the Essential Bus. The OIL annunciator will illuminate if the oil temperature is greater than 40 F or if the oil pressure is less than 10 PSI. The oil pressure/oil temperature gage provides a logic low signal if either the oil pressure or oil temperature meets the above temperature or pressure criteria. The OIL annunciator illuminates red. The FUEL annunciator will illuminate if the fuel quantity is less than 8.5 ± 0.5 gallons in both tanks. The fuel quantity gage provides a logic low signal when each tank is below 8.5 ± 0.5 gallons. The annunciator decodes these two signals and illuminates when both signals are low. The FUEL annunciator illuminates amber. The LOW VOLTS annunciator will illuminate under low RPM conditions or if the system voltage falls below 5.0 ± 0.35 volts. The MCU provides a logic low signal when the voltage is low. The LOW VOLTS annunciator illuminates red. Serials 1005 thru 167: The VACUUM annunciator will illuminate if the system vacuum is below 3.0 ± 0.5 in Hg. A vacuum sensor, mounted on the main vacuum side of the vacuum manifold, provides a logic low signal when the vacuum falls to unacceptable levels. The VACUUM annunciator illuminates red. Serials 1005 thru 167: The AUX VAC annunciator will illuminate if the standby vacuum pump operates. The vacuum switch on the standby side of the vacuum manifold provides a ground when the pump is activated and working correctly. The AUX VAC annunciator illuminates amber. Serials 168 & subs: The ALT 1 annunciator provides two indications. During an overload condition, when alternator 1 is generating more than maximum rated alternator amperage, the light will flash approximately 40 times per minute. When the alternator is generating less than.0 ±.0 amps, the ALT 1 annunciator will illuminate steady, notifying the pilot that the alternator is not generating power. The ALT 1 annunciator illuminates amber. Serials 168 & subs w/o single alternator SRV: The ALT annunciator also provides two indications. During an overload condition, where alternator is generating more than maximum rated alternator amperage, the light will flash approximately 40 times per minute. When the alternator is generating less than.0 ±.0 amps, the ALT annunciator will illuminate steady, notifying the pilot that the alternator is not generating power. The ALT annunciator illuminates amber. The PITOT HEAT annunciator will illuminate if the pitot heat is inoperative. If the Pitot Heat switch is ON and there is no current in the line, indicating a circuit malfunction, the PITOT HEAT annunciator will illuminate. A current sensor provides a logic low signal to the annunciator when current is absent in the pitot heat circuit and the pitot heat switch is ON. The PITOT HEAT annunciator illuminates amber. Serials 1441 thru 015 w/ TAWS, 016 & subs w/ TAWS and w/o Perspective Avionics: TAWS terrain annunciations and control functions are incorporated into the Annunciator Panel. The panel consists of a momentary push button switch (SELF TEST), an illuminated push button switch (TERR INHIBIT), Page 1
and three LEDS for Terrain Warning (TERR WARN), Terrain Caution (TERR CAUT), and Terrain Inoperative (TERR INOP). The annunciators are dimmed via the instrument panel lighting bus. The TAWS annunciator panel is powered by 8 VDC through the -amp ANNUN circuit breaker on the Essential Bus. B. Crew Alerting System - Serials 016 & subs w/ Perspective Avionics Aircraft annunciations and alerts are displayed in the Crew Alerting System (CAS) window located to the right of the altimeter and VSI. Aircraft annunciations are grouped by criticality and sorted by order of appearance with the most recent message on top. The color of the message text is based on its urgency and required action: Warning (red) Immediate crew awareness and action required. Caution (yellow) Immediate crew awareness and future corrective action required. Advisory (white) Crew awareness required and subsequent action may be required. In combination with the CAS window, the system issues an audio alert when specific system conditions are met and an expanded description of the condition is displayed in the Alerts Window located in the lower RH corner of the PFD. For additional Crew Alerting System information for the Perspective Integrated Avionics System refer to the latest revision of Cirrus Perspective Line Maintenance Manual, Garmin publication number 190-0090-00. Refer to the following Figures for detailed descriptions of CAS messages. (See Figure 1),(See Figure ),(See Figure 3),(See Figure 4),(See Figure 5), (See Figure 6) Page
. CIRRUS PERSPECTIVE ANNUNCIATIONS AND ALERTS CAS Warning Text Alerts Window Text Definition AUTO DESCENT Aircraft descent to 14,000 feet in 60 seconds. Emergency descent warning. AUTO DESCENT Aircraft descent to 14,000 feet. Emergency descent in progress (initial descent) AUTO DESCENT Aircraft descent to 1,500 feet. Emergency descent in progress (secondary descent) BRAKE TEMP Brake temperature is high. Brake temperature > 93 F. CHT Cylinder head temperature is high. Temperature of one or more cylinder heads > 460 F. CO LVL HIGH Carbon monoxide level is too high. Carbon monoxide level is too high. ESS BUS Check essential power bus voltage. Voltage output for Alternator 1 or Alternator < 4.5v for more than 0 seconds or > 3.0v. This is usually associated with an Alternator 1 or Alternator failure and will be displayed in combination with a M BUS 1 or M BUS voltage annunciation for the corresponding Alternator. FUEL FLOW Check fuel flow. Fuel flow > 30 GPH. FUEL QTY Check fuel tank levels. Fuel Totalizer quantity < 9 gallons. M BUS 1 Check main power bus 1 voltage. Alternator voltage output > 3.0v. This is usually associated with an alternator failure M BUS Check main power bus voltage. Alternator voltage output > 3.0v. This is usually associated with an alternator failure OIL PRESSURE Oil pressure is out of range. Oil pressure < 10 psi or > 100 psi. If low oil pressure is low, the engine has probably lost a significant amount of its oil and engine failure may be imminent. If low oil pressure is accompanied by normal oil temperature, it is possible that the oil pressure sensor, gage, or relief valve is malfunctioning. OIL TEMP Oil temperature is high. Oil temperature > 40 F. OXYGEN FAULT OXYGEN QTY Serials w/ Oxygen: Oxygen system fault. Serials w/ Oxygen: Oxygen quantity is low. Tank solenoid has failed (open or closed) or flow rate is low. If flow is checked and confirmed present, solenoid has failed open. Altitude > 10,000 ft and tank pressure < 400 psi. RPM Check engine RPM. Engine speed is between 710 RPM and 730 RPM for 10 seconds or more, OR engine speed > 730 RPM for 5 seconds or more. Figure 1 CAS Warning Messages Page 3
CAS Warning Text Alerts Window Text Definition STALL Stall warning. Impending stall. START ENGAGED Starter is engaged. Starter stuck engaged. MCU detects 4 VDC to Starter 30 seconds after initial engagement. UNDERSPEED PROTECT ACTIVE None Figure 1 CAS Warning Messages (Continued) Underspeed Protection (USP) is active. Page 4
CAS Caution Text Alerts Window Text Definition ALT 1 Check alternator 1 current. Illumination of ALT 1 indicates that the ampere output < amps for 0 seconds or more. ALT Check alternator current. Illumination of ALT indicates that the ampere output < amps for 0 seconds or more. ALT AIR OPEN Alternate air door is open. Alternate air door is open. AP MISCOMPARE AP/PFD DIF ADC AP/PFD DIF AHRS Autopilot miscompare, autopilot is not available. Autopilot and PFD are using different ADCs. Autopilot and PFD are using different AHRSs. Autopilot miscompare, autopilot is not available. Autopilot and PFD are using different ADCs. Autopilot and PFD are using different AHRSs. AVIONICS OFF Avionics master switch is off. Avionics master switch is off. BATT 1 Check battery 1 current. Battery 1 current is discharging at a rate > 4 amps for 30 seconds or more. BRAKE TEMP Brake temperature is high. Brake temperature is between 70 F and 93 F for more than 5 seconds. CHT Cylinder head temperature is high. Temperature of one or more cylinder heads has exceeded 40 F. FLAP OVERSPEED Flaps are extended beyond airspeed limitations. Flaps at 100%, airspeed > 109 KIAS for 5 seconds or more, OR Flaps at 50%, airspeed > 14 KIAS for 5 seconds or more. FUEL FILTER Fuel filter in bypass The fuel filter is in bypass mode. The fuel filter element must be replaced. FUEL QTY Check fuel tank levels. Check fuel tank levels. M BUS 1 Check main power bus 1. Illumination of M BUS 1 indicates that the alternator voltage output < 4.5v. This is usually associated with an alternator failure. M BUS Check main power bus. Illumination of M BUS indicates that the alternator voltage output < 4.5v. This is usually associated with an alternator failure. NO ADC MODES NO VERT MODES Autopilot air data modes are not available. Autopilot vertical modes are not available. Autopilot air data modes are not available. Autopilot vertical modes are not available. OIL PRESSURE Oil pressure is out of range. Oil pressure between 10 psi and 30 psi at or above 1000 RPM. This message will appear prior to engine start and should clear after engine start. Figure CAS Caution Messages Page 5
CAS Caution Text Alerts Window Text Definition OIL TEMP Oil temperature is high. Oil temperature > 35 F. OXYGEN QTY OXYGEN RQD Serials w/ Oxygen: Oxygen quantity is low. Serials w/ Oxygen: Oxygen is required. Altitude > 10,000 ft and tank pressure < 800 psi. Oxygen is required. PARK BRAKE Parking break is set. Parking break is set. PITOT HEAT FAIL Pitot heat failure. Pitot heat failure. Displayed when Pitot heat switch is ON and Pitot heat current is not detected. PITOT HEAT REQD Pitot heat is required. Displayed 0 seconds after system detects OAT < 41 F (5 C) and Pitot Heat Switch is OFF. START ENGAGED Starter is engaged. Starter stuck engaged. MCU detects 4 VDC to Starter 15 seconds after initial engagement. Figure CAS Caution Messages (Continued) CAS Advisory Text Alerts Window Text Definition ALTITUDE SEL Climbing away from selected altitude. Climbing away from selected altitude for more than 5 seconds. ALTITUDE SEL Descending away from selected altitude. Descending away from selected altitude for more than 5 seconds. ARE YOU ALERT? Are you alert? No pilot interaction within a reasonable time period. COURSE SEL HIGH MP FF Current track will not intercept selected course. Avoid fuel flow 18 to 30 GPH and MP above 6. Current track will not intercept selected course. Avoid fuel flow 18 to 30 GPH and MP above 6. L FUEL QTY Check left fuel tank level. Left fuel quantity < 18 gallons. OXYGEN LEFT ON OXYGEN QTY Serials w/ Oxygen: Oxygen system is left on after shutdown. Serials w/ Oxygen: Oxygen quantity is low. Oxygen system is left on after shutdown. Altitude < 10,000 ft and tank pressure < 800 psi. R FUEL QTY Check right fuel tank level. Right fuel quantity < 18 gallons. Figure 3 CAS Advisory Messages Page 6
Comparator Window Text ALT MISCOMP IAS MISCOMP HDG MISCOMP PIT MISCOMP ROL MISCOMP ALT NO COMP IAS NO COMP HDG NO COMP PIT NO COMP ROL NO COMP Condition Difference in altitude sensors > 00 ft. If both airspeed sensors detect < 35 knots, this is inhibited. If either airspeed sensor detects > 35 knots, and the difference in sensors > 10 kts. If either airspeed sensor detects > 80 knots, and the difference in sensors > 7 knots. Difference in heading sensors > 6 degrees. Difference in pitch sensors > 5 degrees. Difference in roll sensors > 6 degrees. No data from one or both altitude sensors. No data from one or both airspeed sensors. No data from one or both heading sensors. No data from one or both pitch sensors. No data from one or both roll sensors. Figure 4 CAS Comparator Window Messages Reversionary Sensor Window Text USING ADC USING AHRS Condition The PFD is displaying data from the # Air Data Computer. The PFD is displaying data from the # AHRS. Figure 5 CAS Reversionary Sensor Messages Alerts Window Message CO DET FAIL The carbon monoxide detector is inoperative. CO DET SRVC The carbon monoxide detector needs service. ESP CONFIG ESP config error. Config service required. ESP FAIL ESP is inoperative. ESP OFF ESP selected off. Carbon monoxide detector fault. Carbon monoxide detector fault. Condition ENABLE / unlock mis-match for ESP. Software for ESP option was not installed as specified in Service Bulletin X--07. GFC 700 is unavailable. Pilot DISABLED ESP. ESP DEGRADE ESP IAS mode is inoperative. ADC failure, limited GFC availability. FAILED PATH An autopilot servo data path has failed. Servo or servo wiring fault. Figure 6 CAS Alerts Messages Page 7
Alerts Window Message Condition MFD FAN FAIL The cooling fan for the MFD is inoperative. PFD FAN FAIL The cooling fan for PFD is inoperative. Figure 6 CAS Alerts Messages (Continued) Page 8
3. MAINTENANCE PRACTICES A. Annunciator Panel - Serials 1005 thru 015, 016 & subs w/o Perspective Avionics (See Figure 7) (1) Removal - Annunciator Panel (a) Set BAT 1, BAT, and AVIONICS switches to OFF positions. (b) Pull ANNUNCIATOR PANEL circuit breaker. (c) Remove glareshield. (Refer to 5-10) (d) Remove dress nut and washers securing annunciator toggle switch to instrument panel. (e) Disconnect electrical connector from annunciator. (f) Serials 1441 thru 015 w/ TAWS, 016 & subs w/ TAWS and w/o Perspective Avionics: Disconnect LED wire harness. Note: Label all wires and pins before disconnecting to facilitate re-installation. 1 Disconnect J703 connector from wire harness. At S500 connector, depin LED wires at pin locations 1 and 3. (g) Remove screws, washers, and nuts securing annunciator to instrument panel. Remove annunciator from airplane. () Installation - Annunciator Panel (a) Position annunciator to instrument panel and secure with screws, washers, and nuts. (b) Serials 1441 thru 015 w/ TAWS, 016 & subs w/ TAWS and w/o Perspective Avionics: Connect LED wire harness. 1 At S500 connector, pin LED wires at pin locations 1 and 3. Connect J703 connector to wire harness. (c) Connect electrical connector to annunciator. (d) Install washer on toggle switch and position on instrument panel so keyway on switch faces down. Install washer and dress nut. (e) Install glareshield. (Refer to 5-10) (f) Reset ANNUNCIATOR PANEL circuit breaker. (g) Perform Functional Test - Annunciator Panel. (Refer to ) (3) Functional Test - Annunciator Panel (a) Ensure that all flight controls are clear. (b) Connect 8 ±1 VDC external power to external power receptacle. (c) Pull Starter Relay and Fuel Pump Relay circuit breaker. (d) Set BAT 1, BAT, and AVIONICS switches to ON positions. (e) Set annunciator switch to center BRIGHT position. (f) If each tank has less than 8.5 gallons, ensure FUEL annunciator light is on. (g) Ensure OIL annunciator light is on. (h) Check functionality of LOW VOLTS annunciator. 1 Turn off external power supply. Note: If system voltage is less than 4.5 ±.0 VDC, the LOW VOLTS annunciator light is on. (i) (j) Turn on large electrical loads (landing light, nav lights, pitot heat, etc.) until the LOW VOLTS annunciator light is on. 3 Turn off loads and turn on external power supply. Ensure ALT 1 annunciator light is on. Ensure ALT annunciator light is on. Serials 1005 thru 015, 016 & subs w/o Perspective Avionics Page 9
(k) (l) (m) (n) Ensure PITOT HEAT annunciator light is off. Set annunciator switch to DIM position. Annunciator lights will dim. Set annunciator switch to TEST position. Annunciator lights will brighten. Ensure annunciator legends and colors are correct. OIL LOW VOLTS FUEL PITOT HEAT ALT 1 ALT Red Red Amber Amber Amber Amber (o) Disconnect 8 ±1 VDC external power from external power receptacle. Page 10 Serials 1005 thru 015, 016 & subs w/o Perspective Avionics
5 4 6 7 1 3 INSTRUMENT PANEL (REF) NOTE Keyway on toggle switch faces down. LEGEND 1. Dress Nut. Washer 3. Screw 4. Toggle Switch 5. Nut 6. Electrical Connector 7. Annunciator Serials 1005 thru 1336, 1337 thru 14 w/o PFD. SR0_MM31_118C Figure 7 Annunciator Panel Installation - Serials 1005 thru 1336, 1337 thru 14 w/o PFD (Sheet 1 of ) Serials 1005 thru 1336, 1337 thru 14 w/o PFD Page 11
5 J703 (REF) P703 (REF) 6 7 3 4 1 4 INSTRUMENT PANEL (REF) NOTE Keyway on toggle switch faces down. At S500 connector, depin wires at pin locations 1 and 3. LEGEND 1. Dress Nut. Washer 3. Screw 4. Toggle Switch, (S500) 5. Nut 6. Electrical Connector 7. Annunciator 8. Push Button Switch Figure 7 Annunciator Panel - Serials 1337-14 w/ PFD, 143-015, 016 & subs w/o Perspective Avionics (Sheet of ) Page 1 SR0_MM31_173C Serials 1337-14 w/ PFD, 143-015, 016 & subs w/ o Perspective Avionics