SYSTEM LOAD CHARTS AND BUS SCHEMATICS

Transcription

1 SYSTEM LOAD CHARTS AND BUS SCHEMATICS 1. GENERAL The airplane is equipped with a two alternator system, with each alternator operating continuously. Serials thru , thru , thru , thru , & subs w/o Fan or Air Conditioning: The forward alternator () is rated at 8 amps. Serials , , , & subs w/ Fan or Air Conditioning: The forward alternator () is rated at 8.8 amps. The aft alternator (ALT 2) is rated at 20 amperes. The total system load of the airplane is supported by the two alternator configuration. The battery is charged in flight. The total continuous connected load is held to less than 80% of the total rated generator output capacity. During normal operation the system operates like two separate systems; provides power to battery 1 and the main distribution bus loads, and ALT 2 provides power to battery 2 and the essential distribution bus loads. Low RPM operation or a failure of ALT 2 will cause all system loads and both batteries to be powered by only. Because this operation is automatic, main distribution and essential distribution bus continuous loads are held to less than 80% of the capacity of (80% of 8 A = 46.4 A, 80% of 8.8 A = A). Individual circuit loads have been determined by measuring the circuit loads as installed in the aircraft using a calibrated ammeter. Loads stated for circuits with oscillating or varying power use are maximum operating loads. These load measurements present the most accurate data for power usage available. Serials thru , thru , thru : The airplane has seven power distribution busses with associated protection devices located within the MCU. Three busses are used as distribution feeders from the Main Distribution Bus. Two busses are used as distribution feeders from the Essential Distribution Bus. All distribution feeders are routed to the circuit breaker panel located near the pilot's right knee. One bus is used to power the landing light directly from the Main Distribution Bus through a 1 amp circuit breaker. One bus is the clock keep-alive bus, which is protected with a five amp fuse located in the side of the MCU. The clock bus is the only bus not controlled by the master switch arrangement. Serials , , thru , & subs w/o Perspective Avionics: The airplane has nine power distribution busses with associated protection devices located within the MCU. Three busses are used as distribution feeders from the Main Distribution Bus. Two busses are used as distribution feeders for Air Conditioning. Two busses are used as distribution feeders from the Essential Distribution Bus. All distribution feeders are routed to the circuit breaker panel located near the pilot's right knee. One bus is used to power the landing light directly from the Main Distribution Bus through a 1 amp circuit breaker. One bus is the clock keep-alive bus, which is protected with a five amp fuse located in the side of the MCU. The clock bus is the only bus not controlled by the master switch arrangement. Serials & subs w/ Perspective Avionics, 22T-0001 & subs: The airplane has 10 power distribution busses with associated protection devices located within the MCU. Three busses are used as distribution feeders from the Main Distribution Bus 1. Three busses are used as distribution feeders from the Main Distribution Bus 2 Two busses are used as distribution feeders from the Essential Distribution Bus. All distribution feeders are routed to the circuit breaker panel located near the pilot's right knee. One bus is used to power the landing light directly from the Main Distribution Bus 1 through a 7. amp fuse. One bus is the constant power bus, which is protected with a five amp fuse located in the side of the MCU. The constant power bus is the only bus not controlled by the master switch arrangement. The constant power bus is not used by the Perspective Avionics. All Page 1 01 FEB 2013

2 2. CIRCUIT LOAD CHARTS CIRCUIT IDENTIFICATION ELECTRICAL LOAD PROTECTOR VALUE (AMPS) DUTY CYCLE CURRENT DRAIN AT 28 VDC (AMPS) ESSENTIAL ESSENTIAL COIL COM 1 7. (RX) (TX) GPS NON-ESSENTIAL NON-ESSENTIAL COIL GPS COM 2 7. (RX) (TX) ENCODER TRANSPONDER MULTI-FUNCTION DISPLAY 2.2 AUDIO PANEL 0.36 STORMSCOPE WEATHER SKYWATCH 1.17 TAWS 0.28 MAIN BUS 1 HOBBS 0.10 PITCH TRIM YAW TRIM ROLL TRIM INSTRUMENT ICE PROTECTION PUMP 1.0 ENGINE INSTRUMENTS 0.36 MAIN BUS 2 TURN COORDINATOR # ATTITUDE # HSI #2 (SNDL) 3.4 PFD # FUEL PUMP FLOOD CABIN ALTERNATOR 1 FIELD 3. Figure 1 Circuit Load Chart - Serials thru , thru , thru (Sheet 1 of 2) Page 2 1 Dec 2014 Serials thru , thru , thru

3 CIRCUIT IDENTIFICATION ELECTRICAL LOAD PROTECTOR VALUE (AMPS) DUTY CYCLE CURRENT DRAIN AT 28 VDC (AMPS) NON-ESSENTIAL BUS COOLING FAN PITOT HEAT FLAPS RIGHT STROBE LIGHT P.S. LEFT STROBE LIGHT P.S. RIGHT NAV LIGHT LEFT NAV LIGHT CONVENIENCE OUTLET ESSENTIAL BUS TURN COORDINATOR # ATTITUDE # HSI #1 (SNDL) 3.4 PFD # STALL WARNING ANNUNCIATOR ALTERNATOR 2 FIELD 3. ESSENTIAL 2 BUS AUTOPILOT 1.0 CLOCK BUS CLOCK 0.11 LANDING LIGHT BUS LANDING LIGHT COIL 0.08 LANDING LIGHT AIR CONDITIONING BUS 1 CONDENSER AIR CONDITIONING BUS 2 FAN COMPRESSOR/ CONTROL PANEL Figure 1 Circuit Load Chart - Serials thru , thru , thru (Sheet 2 of 2) All Page 3

4 CIRCUIT IDENTIFICATION ELECTRICAL LOAD PROTECTOR VALUE (AMPS) DUTY CYCLE CURRENT DRAIN AT 28 VDC (AMPS) ESSENTIAL ESSENTIAL COIL COM 1 7. (RX) (TX) GPS NON-ESSENTIAL NON-ESSENTIAL COIL GPS COM 2 7. (RX) (TX) ENCODER TRANSPONDER MULTI-FUNCTION DISPLAY 2.2 AUDIO PANEL 0.36 STORMSCOPE WEATHER SKYWATCH 1.17 TAWS 0.28 MAIN BUS 1 DAU 0.18 HOBBS 0.10 PITCH TRIM YAW TRIM ROLL TRIM INSTRUMENT ICE PROTECTION PUMP 1.0 MAIN BUS 2 TURN COORDINATOR # ATTITUDE # HSI #2 (SNDL) 3.4 PFD # FUEL PUMP FLOOD CABIN ALTERNATOR 1 FIELD 3. Figure 2 Circuit Load Chart - Serials , , thru , & subs w/o Perspective Avionics (Sheet 1 of 2) Page 4 1 Dec 2014 Serials , , thru , & subs w/o Perspective Avionics

5 CIRCUIT IDENTIFICATION ELECTRICAL LOAD PROTECTOR VALUE (AMPS) DUTY CYCLE CURRENT DRAIN AT 28 VDC (AMPS) NON-ESSENTIAL BUS COOLING FAN PITOT HEAT FLAPS RIGHT STROBE LIGHT P.S. LEFT STROBE LIGHT P.S. RIGHT NAV LIGHT LEFT NAV LIGHT CONVENIENCE OUTLET ESSENTIAL BUS TURN COORDINATOR # ATTITUDE # HSI #1 (SNDL) 3.4 PFD # STALL WARNING ANNUNCIATOR ALTERNATOR 2 FIELD 3. ENGINE INSTRUMENTS ESSENTIAL 2 BUS AUTOPILOT 1.0 CLOCK BUS CLOCK 0.11 LANDING LIGHT BUS LANDING LIGHT COIL 0.08 LANDING LIGHT AIR CONDITIONING BUS 1 CONDENSER AIR CONDITIONING BUS 2 FAN COMPRESSOR/ CONTROL PANEL Figure 2 Circuit Load Chart - Serials , , thru , & subs w/o Perspective Avionics (Sheet 2 of 2) All Page

6 CIRCUIT IDENTIFICATION ELECTRICAL LOAD PROTECTOR VALUE (AMPS) DUTY CYCLE CURRENT DRAIN AT 28 VDC (AMPS) BUS AUDIO PANEL 0.3 LIGHTNING DETECTION XM DATA LINK (RX) (TX) TRAFFIC 1.29 TRANSPONDER ADF DME MAIN BUS 1 NON-ESSENTIAL COIL FUEL QUANTITY HOBBS CABIN FLOOD INSTRUMENT ICE PROTECTION PUMP 1.0 AUTOPILOT KEY PAD PITCH SERVO ROLL SERVO MAIN BUS 2 GIA 63W #2 COM 2 7. (RX) (TX) GIA 63W #2 GPS FUEL PUMP 1.00 AHRS # PFD COOLING FAN GIA COOLING FAN CO DETECTOR ADC #2 0.2 Figure 3 Circuit Load Chart & subs w/ Perspective Avionics, 22T-0001 & subs (Sheet 1 of 3) Page 6 1 Dec 2014 All

7 CIRCUIT IDENTIFICATION ELECTRICAL LOAD PROTECTOR VALUE (AMPS) DUTY CYCLE CURRENT DRAIN AT 28 VDC (AMPS) MAIN BUS 3 MFD # CONVENIENCE OUTLET (PWR) CONVENIENCE OUTLET (GND) YAW SERVO NON-ESSENTIAL BUS RIGHT STROBE LIGHT P.S. LEFT STROBE LIGHT P.S RIGHT NAV LIGHT LEFT NAV LIGHT RIGHT REC LIGHT LEFT REC LIGHT FLAPS MFD COOLING FAN XPDR COOLING FAN PITOT HEAT ESSENTIAL BUS 1 STANDBY ATTITUDE # PFD # GIA 63W #1 COM 1 7. (RX) (TX) GIA 63W #1 GPS AHRS # ADC #1 0.1 ESSENTIAL BUS 2 STALL WARNING PITCH TRIM ROLL TRIM GEA ALTERNATOR 2 FIELD 3.0 Figure 3 Circuit Load Chart & subs w/ Perspective Avionics, 22T-0001 & subs (Sheet 2 of 3) All Page 7

8 CIRCUIT IDENTIFICATION ELECTRICAL LOAD PROTECTOR VALUE (AMPS) DUTY CYCLE CURRENT DRAIN AT 28 VDC (AMPS) AIR CONDITIONING BUS 1 LANDING LIGHT COIL 0.08 LANDING LIGHT CONDENSER ALTERNATOR 1 FIELD 3.0 AIR CONDITIONING BUS 2 FAN COMPRESSOR A/C CONTROL PANEL Figure 3 Circuit Load Chart & subs w/ Perspective Avionics, 22T-0001 & subs (Sheet 3 of 3) Page 8 All

9 3. ELECTRICAL SYSTEM SCHEMATICS EXTERNAL POWER VOLT REG 100A 1A F B LANDING LIGHT 12A MAIN DIST 2A 2A LANDING LIGHT 2A 2A 2A F ALT 2 B FUEL OIL ALT 2 LOW VOLTS PITOT HEAT 0A 0A ESSENTIAL DIST VOLT REG 2A 2A 40A MASTER CONTROL UNIT CIRCUIT BREAKER PANEL NON-ESSENTIAL MAIN BUS 1 TRAFF/TAWS GPS 2 COM 2 XPNDER XM/WX MFD AUDIO PANEL FUEL QUANTITY REC/INST LTS PITCH TRIM ROLL TRIM ICE PROTECT MAIN BUS 2 NON-ESSENTIAL FUEL PUMP TRN CRD #2 ATTITUDE #2 PFD #2 CABIN LTS 2A START PITOT/FAN 12V/ANR STROBE LTS NAV LTS FLAPS ESSENTIAL ESSENTIAL ANN/ENG IND TRN CRD #1 ATTITUDE #1 2A PFD #1 STALL WARN BATTERY 2 ALT 2 ESS POWER AUTOPILOT COM 1 GPS 1 2A ESSENTIAL ATT GYRO ALT 2 A/C 2 FAN COMPR/CTRL A/C 1 CONDENSER NON-ESSENTIAL Serials , , , & subs. SR22_MM24_1426F Figure 4 Electrical System Schematic - Serials thru , & subs w/o Perspective Avionics Serials thru , & subs w/o Perspective Avionics NOTE Serials thru , thru and thru : 80A fuse. Serials thru , thru and thru : 100A fuse. Page 9

10 F B 100A LANDING LIGHT EXTERNAL POWER VOLT REG EXTERNAL POWER MAIN DIST BUS 1 7.A LANDING LIGHT F ALT 2 B 12A 60A 80A MAIN DIST BUS 2 0A 0A 0A ESSENTIAL DIST BUS VOLT REG MASTER CONTROL UNIT ALT 2 20A A/C BUS 2 NON-ESSENTIAL BUS A/C COMPR/ CONTROL CABIN FAN FAN 1 RECOG NAV STROBE PITOT HEAT FLAPS STALL VANE HEAT 8A 8A A/C BUS 1 MAIN BUS 3 MAIN BUS 2 A/C COND YAW SERVO EVS CAMERA 12V DC OUTLET MFD #1 FAN 2 GPS NAV GIA 2 COM 2 AHRS 2/ (ADC 2) FUEL PUMP PFD #2 ESSENTIAL BUS 2 ESSENTIAL BUS 1 ICE PROTECT B ALT 2 ENGINE INSTR STALL WARNING ROLL TRIM PITCH TRIM ESSENTIAL POWER GPS NAV GIA 1 COM 1 ADC 1 AHRS 1 STDBY ATTD #1 PFD #1 20A MAIN BUS 1 BUS ICE PROTECT A STDBY ATTD #2 MFD #2 CABIN / OXYGEN FUEL QTY AP SERVOS KEYPADS / AP CTRL DME / ADF AUDIO PANEL WEATHER XPONDER TRAFFIC CIRCUIT BREAKER PANEL NOTE Serials w/ FIKI. Serials thru w/ Perspective Avionics. NON-ESSENTIAL SR22_MM24_2901D Page 10 Figure Electrical System Schematic - Serials thru w/ Perspective Avionics Serials thru w/ Perspective Avionics

11 F B EXTERNAL POWER VOLT REG EXTERNAL POWER 100A MAIN DIST BUS 1 7.A LANDING LIGHT LANDING LIGHT F ALT 2 B 12A 80A 80A MAIN DIST BUS 2 0A 0A 0A ESSENTIAL DIST BUS VOLT REG MASTER CONTROL UNIT ALT 2 20A A/C BUS 2 NON-ESSENTIAL BUS A/C COMPR CABIN FAN FAN 1 RECOG NAV STROBE PITOT HEAT FLAPS STALL VANE HEAT 8A 8A A/C BUS 1 MAIN BUS 3 MAIN BUS 2 A/C COND YAW SERVO EVS CAMERA 12V DC OUTLET MFD #1 FAN 2 GPS NAV GIA 2 COM 2 AHRS 2/ (ADC 2) FUEL PUMP PFD #2 ESSENTIAL BUS 2 ESSENTIAL BUS 1 ICE PROTECT B ALT 2 ENGINE INSTR STALL WARNING ROLL TRIM PITCH TRIM ESSENTIAL POWER GPS NAV GIA 1 COM 1 ADC 1 AHRS 1 STDBY ATTD #1 PFD #1 20A MAIN BUS 1 BUS ICE PROTECT A STDBY ATTD #2 MFD #2 CABIN / OXYGEN FUEL QTY AP SERVOS KEYPADS / AP CTRL CABIN AIR CONTROL DME / ADF AUDIO PANEL WEATHER /DATA LINK XPONDER TRAFFIC CIRCUIT BREAKER PANEL NOTE Serials w/ FIKI. Serials thru w/ Perspective Avionics, 22T-0001 thru 22T NON-ESSENTIAL SR22_MM24_3246B Figure 6 Electrical System Schematic - Serials thru w/ Perspective Avionics, 22T-0001 thru 22T-0689 Serials thru w/ Perspective Avionics, 22T-0001 thru 22T-0689 Page 11 1 Dec 2014

12 F B 100A LANDING LIGHT EXTERNAL POWER VOLT REG EXTERNAL POWER MAIN DIST BUS 1 7.A LANDING LIGHT 12A F ALT 2 B A 60A 60A MAIN DIST BUS 2 0A 0A 0A ESSENTIAL DIST BUS ALT 2 VOLT REG MASTER CONTROL UNIT 20A NON-ESSENTIAL BUS A/C BUS 2 A/C BUS 1 CONS CONV 1 AFT BUS 2 A/C COND 1 AFT BUS 3 A/C COMPR CABIN FAN FAN 1 NAV STROBE PITOT HEAT FLAPS STALL VANE HEAT 8A 8A MAIN BUS 3 MAIN BUS 2 1 AFT BUS 1 UAT RECOG YAW SERVO EVS CAMERA 12V DC OUTLET MFD #1 FAN 2 GPS NAV GIA 2 COM 2 AHRS 2/ ADC 2 FUEL PUMP PFD #2 ESSENTIAL BUS 2 ESSENTIAL BUS 1 ICE PROTECT B ALT 2 ENGINE INSTR STALL WARNING ROLL TRIM PITCH TRIM ESSENTIAL POWER GPS NAV GIA 1 COM 1 ADC 1 AHRS 1 STDBY ATTD #1 PFD #1 20A MAIN BUS 1 BUS ICE PROTECT A STDBY ATTD #2 MFD #2 CABIN / OXYGEN FUEL QTY AP SERVOS KEYPADS / AP CTRL CABIN AIR CONTROL DME / ADF AUDIO PANEL DATA LINK/ WEATHER XPONDER TRAFFIC MAIN CIRCUIT BREAKER PANEL AFT CIRCUIT BREAKER PANEL 1 2 AFT BUS 1 AFT BUS 2 AFT BUS 3 AFT CB AFT CB NON-ESSENTIAL 1 NOTE Serials w/ Perception. 2 For each aft circuit breaker bus, connection is made at discretion of Perception system integrator. Figure 7 Electrical System Schematic - Serials & subs w/ Perspective Avionics, 22T-0690 & subs Page Jan 2016 Serials & subs w/ Perspective Avionics, 22T-0690 & subs. SR22_MM24_3637E Serials & subs w/ Perspective Avionics, 22T & subs

13 4. POWER DISTRIBUTION SCHEMATICS 0 A Main Distribution Bus Essential Distribution Bus 2 A 2 A 2 A 2 A 2 A 0 A 2 A 2 A Main Bus A 1 A 8.00 A.16 A A 11.3 A A A 8.46 A 3.2 A Main Bus 2 Non-Essential Bus Air Conditioning Bus 1 Air Conditioning Bus 2 Essential Bus 1 Essential Bus 2.16 A A 11.3 A A 8.46 A 1.08 A 1 A 2.17 A Avionics Non- Essential Bus Avionics Essential Bus 8.00 A 2.17 A This figure depicts the system loading during normal system operation with alternator 1 and alternator 2 generating at nominal values. Note the diode between the Main Distribution Bus and the Essential Distribution Bus is reverse biased and therefore is not conducting current between buses. The circuit breaker rating is greater than the total load value so all circuit breakers and fuses are of adequate capacity. Figure 8 Power Distribution - Normal Operation - Serials thru , & subs w/o Perspective Avionics Serials thru , & subs w/o Perspective Avionics WM13828_01 Page 13

14 3.6 A Main Distribution Bus Essential Distribution Bus 2 A 2 A 2 A 2 A 2 A 0 A 2 A 2 A Main Bus A 1 A 8.00 A 9.72 A A 11.3 A A A 0.4 A 3.2 A Main Bus 2 Non-Essential Bus Air Conditioning Bus 1 Air Conditioning Bus 2 Essential Bus 1 Essential Bus A A 13 A A 0.4 A 1.08 A 1 A 2.17 A Avionics Non- Essential Bus Avionics Essential Bus 8.00 A 2.17 A This figure depicts the system loading during operation with only alternator 1 generating at nominal values, as may occur during low RPM operation, or a failure of alternator 2. Note the diode between the Main Distribution Bus and the Essential Distribution Bus is forward biased and therefore is conducting current between buses. The circuit breaker rating is greater than the total load value so all circuit breakers and fuses are of adequate capacity. Figure 9 Power Distribution - Alternator 1 Only - Serials thru , & subs w/o Perspective Avionics Page 14 WM13828_02 Serials thru , & subs w/o Perspective Avionics

15 0 A Main Distribution Bus 1 80 A Main Distribution Bus 2 7. A 0 A 0 A (23 A) 0 A 9.8 A 3.6 A 7.9 A (22 A) 13.7 A (2 A) (2 A) Essential Distribution Bus 9.7 A A.79 A (26 A) 23.4 A () 3.79 A (20 A) 6.01 A (22 A) Main Bus 3 Air Conditioning Bus 1 Air Conditioning Bus 2 Essential Bus 1 Essential Bus 2 Main Bus 1 Main Bus 2 Non-Essential Bus 7.9 A 13.7 A 9.7 A 3.79 A 6.01 A A.79 A 23.4 A 10 A 6.23 A (10 A) Landing Lights Avionics Bus 3.6 A 6.23 A This figure depicts the system loading during normal system operation with alternator 1 and alternator 2 generating at nominal values. Note the diode between the Main Distribution Bus and the Essential Distribution Bus is reverse biased and therefore is not conducting current between buses. The circuit breaker rating is greater than the total load value so all circuit breakers and fuses are of adequate capacity. Figure 10 Power Distribution - Normal Operation - Serials & subs w/ Perspective Avionics, 22T-0001 & subs Serials & subs w/ Perspective Avionics, 22T & subs WM18721_01A Page 1

16 41.3 A Main Distribution Bus 1 80 A Main Distribution Bus 2 7. A 0 A 0 A (23 A) 7.39 A 0 A 3.6 A 8.7 A (22 A) 13.7 A (2 A) (2 A) Essential Distribution Bus 9.7 A A.3 A (26 A) 23.4 A () 4.88 A (20 A) 2.1 A (22 A) Main Bus 3 Air Conditioning Bus 1 Air Conditioning Bus 2 Essential Bus 1 Essential Bus 2 Main Bus 1 Main Bus 2 Non-Essential Bus 8.7 A 13.7 A 9.7 A 4.88 A 2.1 A A.3 A 23.4 A 10 A 6.23 A (10 A) Landing Lights Avionics Bus 3.6 A 6.23 A This figure depicts the system loading during operation with only alternator 1 generating at nominal values, as may occur during low RPM operation, or a failure of alternator 2. Note the diode between the Main Distribution Bus and the Essential Distribution Bus is forward biased and therefore is conducting current between buses. The circuit breaker rating is greater than the total load value so all circuit breakers and fuses are of adequate capacity. WM18721_02A Figure 11 Power Distribution - Alternator 1 Only - Serials & subs w/ Perspective Avionics, 22T-0001 & subs Page 16 Serials & subs w/ Perspective Avionics, 22T & subs