INTEGRATED ENGINE INSTRUMENT SYSTEMS

Transcription

1 All INTEGRATED ENGINE INSTRUMENT SYSTEMS. DESCRIPTION This section describes that portion of the engine indicating system which is used to analyze engine performance, temperature, and condition. Serials -000 thru -66 w/ EMax Engine Monitoring: Engine instrumentation is displayed on the Multi-Function Display (MFD). The Sensor Interface Unit (SIU), mounted above the RH kick plate, converts analog signals from the engine and fuel sensors to digital format, which is then transmitted to the MFD. The MFD displays fuel flow, nautical miles per gallon, fuel remaining, fuel-to-waypoint, fuel-to-destination, cylinder head temperatures (CHT), exhaust gas temperatures (EGT), engine crankshaft speed, manifold pressure, percent power, oil temperature, oil pressure, outside air temperature (OAT), and electrical bus voltages. EGT and CHT sensors are mounted to all six exhaust pipes and cylinder heads respectively. MFD functionality is enhanced by displaying six channels of EGT and CHT data. 8 VDC for system operation is suppled through the -amp ENGINE INST circuit breaker located on Main Bus. Serials -66 & subs w/o Perspective Avionics: Engine instrumentation is displayed on the Primary Flight Display (PFD) and Multi-Function Display (MFD). The Data Acquisition Unit (DAU), mounted above the RH kick plate, converts analog signals from the engine and fuel sensors to digital format, which is then transmitted to the MFD and PFD. The PFD displays percent power, engine crankshaft speed, manifold pressure, fuel flow, and oil pressure. The MFD displays fuel flow, nautical miles per gallon, fuel remaining, fuel-to-waypoint, fuel-to-destination, cylinder head temperatures (CHT), exhaust gas temperatures (EGT), engine crankshaft speed, manifold pressure, percent power, oil temperature, oil pressure, outside air temperature (OAT), and electrical bus voltages. The DAU replaces all of the signal conditioning, sensor excitation and warning light outputs that had been a function of the engine gages. 8 VDC for the digital instrument operation is supplied through the -amp ANNUN / ENGINE INST circuit breaker on the Essential Bus. Serials -66 & subs w/ EMax Engine Monitoring and w/o Perspective Avionics: EGT and CHT sensors are installed to each exhaust pipe and cylinder head respectively. MFD functionality is enhanced by displaying six channels of EGT and CHT data. Serials w/ Perspective Avionics: Engine instrumentation is displayed on the Primary Flight Display (PFD) and Multi-Function Display (MFD). The GEA 7 engine airframe unit, mounted behind the MFD, converts analog signals from the engine and fuel sensors to digital format, which is then transmitted to the MFD and PFD. The PFD displays percent power, engine crankshaft speed, manifold pressure, fuel flow, and oil pressure. The MFD displays fuel flow, nautical miles per gallon, fuel remaining, fuel-to-waypoint, fuel-to-destination, cylinder head temperatures (CHT), exhaust gas temperatures (EGT), engine crankshaft speed, manifold pressure, percent power, oil temperature, oil pressure, outside air temperature (OAT), and electrical bus voltages. 8 VDC for the digital instrument operation is supplied through the -amp ENGINE INSTR circuit breaker on Essential Bus. Serials T-000 & subs: The LH and RH turbine inlet temperatures are displayed on the MFD. Manifold air temperature data is used to calculate percent power but is not depicted on either display. The GEA 7 engine airframe unit is integral to the Perspective Integrated Avionics system. For an overview of the Perspective Avionics system, refer to Chapter 4, Integrated Modular Avionics. (Refer to 4-00) For maintenance practices pertinent to the engine crankshaft speed and manifold pressure sensors, see the Power section of Engine Indicating. (Refer to 77-0) For maintenance practices pertinent to the CHT, EGT, TIT, and MAT sensors, see the Temperature section of Engine Indicating. (Refer to 77-0) For maintenance practices pertinent to the oil temperature and oil pressure sensors, see the Indicating section of Oil. (Refer to 79-0) For maintenance practices pertinent to the OAT sensor, see the Flight Environment Pitot-Static Systems section of Navigation and Pitot-Static Systems. (Refer to 4-0) Page Jun 00

2 . TROUBLESHOOTING Serials w/ Perspective Avionics: Trouble Probable Cause Remedy Engine airframe sensors not receiving valid data. Software or configuration error. GEA 7 is offline. Check PFD Alert Window for GIA, GIA, or GEA configuration, software or failed data path error messages. Correct any errors before proceeding. On PFD in Configuration Mode, turn to GEA STATUS page and verify that GEA internal power supply, configuration, and calibration status boxes are green.. If internal power supply box is red, check for shorted engine airframe sensors that receive V, 0V or V power from GEA (tach sensor, MAP sensor, fuel flow sensor, oil pressure sensor, and pitot heat sensor).. The configuration and calibration boxes should be green. If calibration status boxes are red, replace GEA 7. Verify internal, external, and reference voltages listed in the Main Analog and I/O A Analog boxes are not dashed out (does not include Aircraft Power and ). If any voltages are dashed out, replace GEA 7. On MFD AUX SYSTEM STATUS page, verify GEA is online (green checkmark is present). If GEA is not online (Red-X is present), verify the unit is receiving power at GEA rack connector. Faulty GEA 7. Replace GEA 7. Faulty wiring and connectors. Check GIA and GEA interconnect wiring and unit connector pins for faults. Page Jun 00 All

3 . MAINTENANCE PRACTICES A. Sensor Interface Unit (SIU) - Serials -000 thru -66 w/ Emax Engine Monitoring (See Figure ) () Removal - Sensor Interface Unit (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull ENGINE INST circuit breaker. (c) Remove RH kick plate. (Refer to -0) (d) Disconnect electrical connectors from SIU. (e) Remove screws, washers, and nuts securing SIU to kick plate. Remove SIU from airplane. () Installation - Sensor Interface Unit (a) Perform Adjustment/Test - Sensor Interface Unit. (Refer to ) (b) Position SIU to kick plate and secure with screws, washers, and nuts. (c) Connect electrical connectors to SIU. (d) Install RH kick plate. (Refer to -0) (e) Reset ENGINE INST circuit breaker. () Adjustment/Test - Sensor Interface Unit CAUTION: DIP switches must be set to the proper configuration or the Sensor interface unit could send inaccurate data to the MFD. Exercise caution when setting DIP switches. Sensor interface units installed in accordance with Service Bulletin SB use different DIP switch settings than sensor interface units installed during airplane production. The sensor interface unit is considered non-adjustable, once the unit has the switches set to the proper configuration, no further adjustment is required. (a) Remove screws securing DIP switch cover to SIU. (b) Reset DIP switches in accordance with supporting figure. (See Figure ) (c) Position DIP switch cover to SIU and secure with screws. Serials -000 thru -66 w/ Emax Engine Monitoring Page 9 Sep 07

4 DIP SWITCH SETTINGS - SERVICE BULLETIN AIRPLANE SW SW SW SW4 SW SW6 SW7 SW8 SW9 SW0 SR AIRPLANE SR DIP SWITCH SETTINGS - PRODUCTION SW SW SW SW4 SW SW6 SW7 SW SW9 SW0 0 ON () ON () OFF (0) OFF (0) KICK PLATE (REF) Serials -000 thru -60, -60 thru -64, -64 thru -66 w/ EMax Engine Monitoring. LEGEND. Sensor Interface Unit. Screw. Washer 4. Nut. Nylon Washer 6. DIP Switch Cover 7. Connector SR_MM77_76 Figure Sensor Interface Unit Installation - Serials -000 thru -66 w/ EMax Engine Monitoring Page 4 Jun 00 Serials -000 thru -66 w/ EMax Engine Monitoring

5 B. Data Acquisition Unit - Serials -66 & subs w/o Perspective Avionics (See Figure ) () Removal - Data Acquisition Unit (DAU) (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull ANNUN / ENGINE INST circuit breaker. (c) Remove RH kick plate. (Refer to -0) (d) Disconnect electrical connectors from DAU. (e) Remove screws, washers, and nuts securing DAU to kick plate. Remove DAU from airplane. () Installation - Data Acquisition Unit (DAU) (a) Position DAU to kick plate and secure with screws, washers, and nuts. (b) Connect electrical connectors to DAU. (c) Install RH kick plate. (Refer to -0) (d) Reset ANNUN / ENGINE INST circuit breaker. Serials -66 & subs w/o Perspective Avionics Page Jun 00

6 4 KICK PLATE (REF) LEGEND. Data Acquisition Unit. Screw. Washer 4. Connector. Model Identification Jumper SR_MM77_ Page 6 Jun 00 Figure Date Acquisition Unit Installation - Serials -66 & subs w/o Perspective Avionics Serials -66 & subs w/o Perspective Avionics

7 C. GEA 7 Engine Airframe Unit - Serials w/ Perspective Avionics (See Figure ) () Removal - GEA 7 Engine Airframe Unit (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull ENGINE INSTR circuit breaker. (c) Remove MFD. (Refer to -60) (d) Loosen screw securing handle-lock mechanism to engine airframe unit. (e) Lift handle-lock mechanism to disengage engine airframe unit from connectors. (f) Remove engine airframe unit from mounting rack. () Installation - GEA 7 Engine Airframe Unit (a) Position engine airframe unit to mounting rack, ensuring handle-lock mechanism engages slot on side of rack. (b) Using handle-lock mechanism, gently push engine airframe unit into mounting rack to engage connectors. (c) Tighten screw securing handle-lock mechanism to engine airframe unit. (d) Install MFD. (Refer to -60) (e) Reset ENGINE INSTR circuit breaker. (f) If GEA 7 has been replaced with a new or different unit, or original unit has been repaired, perform Adjustment/Test - Component Software and Configuration Loading. (Refer to 4-00) Serials w/ Perspective Avionics Page 7 9 Sep 07

8 4 CONSOLE (REF) LEGEND. GEA 7 Engine Airframe Unit. Rack. Screw 4. Washer. Nut SR_MM77_70A Page 8 9 Sep 07 Figure GEA 7 Engine Airframe Unit Installation - Serials w/ Perspective Avionics Serials w/ Perspective Avionics

9 D. Engine Monitoring Recording System - Serials -000 & subs w/ EMax Engine Monitoring and w/o Perspective Avionics The engine monitoring recording system records and stores engine data on the MFD. For maintenance practices pertinent to the engine maintenance recording system, see Unscheduled Maintenance Checks. (Refer to 0-0) Serials -000 & subs w/ EMax Engine Monitoring and w/o Perspective Avionics Page 9 9 Sep 07

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