CHAPTER ELECTRICAL

Transcription

1 Vol ELECTRICAL Table of Contents REV, May 0/05 CHAPTER ELECTRICAL Page TABLE OF CONTENTS Table of Contents INTRODUCTION Introduction AC ELECTRICAL SYSTEM AC Electrical System Integrated Drive Generator (IDG) APU Generator AC Distribution AC Loads Distribution Air Driven Generator (ADG) Systems Circuit Breakers DC ELECTRICAL SYSTEM DC Electrical System Transformer Rectifier Units (TRU) Batteries DC Distribution DC Loads Distribution Systems Circuit Breakers CIRCUIT BREAKER PANELS Circuit Breaker Panels ATA Numbering and Circuit Breaker Location LIST OF ILLUSTRATIONS INTRODUCTION Figure Electrical System -- Introduction AC ELECTRICAL SYSTEM Figure AC System Distribution Figure AC Electrical System Figure AC Electrical System Synoptic Page Figure AC Electrical System -- EICAS Indications (Generators) Figure AC Electrical System -- EICAS Indications (Busses) Figure Air Driven Generator (ADG)

2 Table of Contents Vol REV, May 0/05 DC ELECTRICAL SYSTEM Figure DC Electrical System -- Schematic Figure Electrical Power Overhead Panel Figure DC Electrical Page Tru Voltage Figure DC Electrical Page Service Configuration Figure EICAS Primary Display Auxiliary Power Unit/Main Battery Off Figure Transformer Rectifire Unit Fail -- Status Page CIRCUIT BREAKER PANELS Figure Panel Overview Figure Circuit Breaker Panel (Reference Only)

3 Vol Introduction Sep 09/0. INTRODUCTION The aircraft AC electrical power is provided by two engine-driven generation systems. Each system includes an integrated drive generator (IDG) and a generator control unit (GCU). An auxiliary power unit (APU) generator is also available as a back AC power source to replace either or both IDGs. In the event of total AC power loss, emergency AC power is available from an in-flight air-driven generator (ADG). The ADG assembly is stowed in a compartment on the right side of the nose section. DC power is supplied by four transformer rectifier units (TRU) which rectifies AC input power into DC output power. An AC power center (ACPC) and two DC power centers (DCPCs) are used for connecting AC and DC power to the appropriate buses, depending on system configuration and health. The following is a list of all the aircraft electrical system buses: AC BUSSES AC BUS AC BUS AC ESSENTIAL BUS AC SERVICE BUS ADG BUS DC BUSSES DC BUS DC BUS DC ESSENTIAL BUS DC SERVICE BUS DC BATTERY BUS DC EMERGENCY BUS DC UTILITY BUS MAIN BATTERY DIRECT BUS APU BATTERY DIRECT BUS A main battery and an APU battery, with battery chargers, are installed in the aircraft electrical power system. Power for starting the APU is provided by the APU battery. On the ground, the aircraft can receive external AC power through a receptacle located on the forward right side of the fuselage. The electrical power panel in the flight compartment, and the external service panel on the right forward fuselage, contain the AC system control switches. The switches are used for manual and automatic control of the electrical power generating system and external power operation. Electrical system warnings and cautions are displayed on the EICAS primary page. Status and advisory messages are displayed on the EICAS status page. General views of the electrical systems are displayed on the EICAS, AC and DC synoptic pages. Access to the AC and DC synoptic page is through the EICAS control panel (ECP). One push of the ELEC key on the ECP will display the AC synoptic page. Pushing the ELEC key a second time will display the DC synoptic page.

4 Introduction Vol REV, May 0/05 APU BATTERY IDG APU GENERATOR IDG ACPC CIRCUIT BREAKER PANELS DCPC MAIN BATTERY AC EXTERNAL POWER ADG Electrical System --- Introduction Figure

5 Vol ELECTRICAL Introduction REV, May 0/05 A B A Electrical Power Panel Overhead Panel B External Service Panel Right Forward Fuselage Electrical System --- Control Panels <05> Figure

6 Introduction Vol REV, May 0/05 THIS PAGE INTENTIONALLY LEFT BLANK

7 Vol ELECTRICAL AC Electrical System REV, May 0/05. AC ELECTRICAL SYSTEM AC power for the aircraft electrical systems is provided by two engine-driven, integrated drive generators (IDGs) which power all AC buses during normal operations. An APU generator provides a backup AC power source, in flight, if an IDG is inoperative or when the aircraft is on the ground with the engines off. If all AC power is lost in flight, emergency AC power is provided automatically by a deployable air-driven generator (ADG). The AC distribution system is controlled by the respective IDG and APU generator control units (GCUs). Each generator is monitored by the GCUs for voltage, frequency and kilovolt amps (kva) for display on the EICAS and for system fault protective shutdowns. A. Integrated Drive Generator (IDG) Each IDG consists of a constant speed drive (CSD) and a generator. The CSD hydro--mechanically, converts the variable input speed from the engine accessory gearbox to a constant output speed to the generator to produce a constant frequency. An oil cooler cools the oil used by the IDG. Each IDG has a disconnect switchlight (on the electrical panel) to manually decouple the IDG from the engine gearbox in the event of a CSD low oil pressure or high oil temperature. The IDG will automatically disconnect if a severe over temperature or overtorque condition occurs. Once disconnected, either manually or automatically, the IDG cannot be reconnected in flight. It can only be reset on the ground, with the engine shutdown. Voltage and frequency regulation and fault protection is incorporated into each generator control unit (GCU). The GCU also protects the electrical system from overcurrent and differential current faults. In the event of a malfunction, the GCU will automatically disconnect the faulty generator from the respective AC buses. The generator may be reset when the malfunction is corrected or no longer exists, by selecting the generator switch to the OFF/RESET position then back to ON. B. APU Generator The APU generator is driven, directly by the APU gearbox, at a constant speed to maintain a constant frequency output. A GCU, identical to the IDG GCU, provides the same regulation and protection functions as the IDG GCUs. C. AC Distribution AC power from IDG and IDG is distributed to the AC buses via GCU controlled switches in the AC power center (ACPC). There is a priority control of AC power distribution. During normal operations, IDG powers AC bus and IDG powers AC bus. Failure of an IDG generator, for any reason other than a fault on its associated bus, will automatically transfer the load from the failed IDG to the remaining operative IDG. The APU generator can then be used to replace the failed IDG to power the respective AC bus.

8 AC Electrical System Vol Sep 09/0 On the ground, if the aircraft is being powered with external AC power and either the APU or an IDG is brought on line, the external power will be automatically disconnected and the respective APU or IDG generator will power all the AC buses. When external power is not available, the APU generator provides electrical power to the AC buses and bleed air to start the aircraft engines. If an IDG is powering its respective AC bus and the APU generator is powering the other AC bus, when the remaining IDG is brought on line, the APU generator will be automatically taken off line. IDG APU GENERATOR IDG Failed Not available Both AC Bus and AC Bus Failed AC Bus AC Bus Both AC Bus and AC Bus Not available Failed AC Bus AC Bus Failed Failed Both AC Bus and AC Bus Failed

9 Vol ELECTRICAL AC Electrical System REV, May 0/05 LEFT ENGINE RIGHT ENGINE APU EXTERNAL AC GCU GEN GEN GCU APU GEN GCU GTCB GTCB GLC GTC GLC GTC AEPC EXTERNAL POWER MONITOR PITCH TRIM SLATS FLAPS STC ACPC AC BUS ADGPC ETC AC BUS ADG BUS AC SERVICE EMERG HYD ADG LC B ADG AC ESS BUS HYD PUMP GCU AC System Distribution Figure

10 AC Electrical System Vol REV, May 0/05 IDG and DISC (Guarded) Used to disconnect IDG from engine. DISC (white) light indicates selected disconnect is successful. FAULT (amber) light indicates a fault within IDG (low oil pressure or high oil temperature). IDG will automatically disconnect, when an overtemperature or overtorque condition occurs. Once disconnected, the IDG cannot be reset with the engines running. OFF ON DC SERVICE IDG FAULT DISC DISC GEN ELECTRICAL POWER BATTERY MASTER OFF ON OFF/ RESET FAIL OFF ALTN AC ESS XFER APU GEN OFF/ RESET AUTO XFER Electrical Power Panel Overhead Panel AUTO XFER Used to disable automatic transfer of associated IDG. OFF (white) light indicates autotransfer is selected off. FAIL (amber) light indicates a fault preventing autotransfer. AC ESS XFER Used to switch essential bus feed from AC bus to AC bus. ALTN (white) light indicates essential bus is fed from AC bus. Transfer is automatic during an AC bus failure. AC Used to select external AC power. AC AVAIL (green) light AVAIL indicates external IN USE power is connected and is ready to use. IN USE (white) light indicates that the FAULT external AC power unit DISC is supplying the electrical system. AC POWER IDG FAIL OFF DISC GEN OFF/ RESET GEN, and APU GEN AUTO -- Connects generator to associated bus. OFF/ RESET -- Disconnects generator from associated bus and/ or resets the generator control circuit. EXT AC PUSH Used to select external AC power. AVAIL (green) light indicates external power is connected and is ready to use. IN USE (white) light indicates that the external AC power unit is supplying the electrical system. External Service Panel Right Forward Fuselage AC Electrical System Figure

11 Vol AC Electrical System Sep 09/0 BRT AC ELECTRICAL Flow Lines Green -- Bus energized. Blank -- Bus not energized. SERV BUS BUS BUS ESS BUS Generator Load Displays the load on the generator. 8 KVA 5 V 400 HZ 0 KVA 0 V 0 HZ GEN GEN IDG APU 6 KVA 5 V 400 HZ GEN IDG Generator Voltage Displays the generator voltage level. Generator Frequency Displays the generator frequency level. AC Electrical Page EICAS DIGITAL READOUT XX KVA XXX V XXX HZ GREEN AMBER WHITE Generator loaded Voltage in range Frequency in range Generator overload Generator not loaded Voltage not in range Frequency not in range HALF INTENSITY MAGENTA Insufficient data Insufficient data Insufficient data AMBER DASHES Invalid data Invalid data Invalid data EICAS OUTLINE GREEN AMBER WHITE BUS Bus powered Bus not powered or voltage low _ HALF INTENSITY MAGENTA Invalid data HALF INTENSITY CYAN _ GEN IDG Generator on Generator off with engine / APU running Both generator and engine / APU are off Low oil pressure Constant Engine is off or IDG or high oil speed drive on has disconnected temperature Invalid data Invalid data APU Engine / APU off Invalid data Engine / APU running and ready to load AC Electrical System Synoptic Page Figure Sheet

12 AC Electrical System Vol REV, Jan /0 BRT AC ELECTRICAL ADG Features Displayed when ADG voltage is more than 0 volts and frequency is more than 00 Hz. 5 V 400 HZ ADG ADG BUS SERV BUS SHED BUS ESS BUS BUS AUTO XFER FAIL AUTO XFER OFF SHED (white) Indicates that service bus is not powered. 0 KVA 0 V 0 HZ GEN IDG DISC 0 KVA 0 V 0 HZ GEN APU 0 KVA 0 V 0 HZ GEN IDG DISC AUTO XFER OFF (white) Indicates that corresponding automatic transfer has been selected off. AUTO XFER FAIL (amber) Indicates that corresponding automatic transfer has failed. AC Electrical Page DISC (white) Indicates that IDG has been disconnected. EICAS DIGITAL READOUT XXX V XXX HZ GREEN Between 08 and 0 volts Between 60 and 440 Hz WHITE Less than 08 volts or more than 0 volts Less than 60 Hz or more than 440 Hz AMBER DASHES Invalid data Invalid data EICAS OUTLINE GREEN WHITE ADG BUS ADG outline green ADG outline white ADG Voltage and frequency digital readouts green Voltage or frequency digital readouts white AC Electrical System Synoptic Page Figure Sheet

13 Vol AC Electrical System Sep 09/0 BRT SERVICE CONFIGURATION AC ELECTRICAL SERVICE CONFIGURATION (green) Displayed when external AC power is available and the AVAIL switchlight on the external AC service panel has been selected. Only the AC service bus will be powered. SERV BUS BUS BUS ESS BUS 0 KVA 5 V 400 HZ EXT AC 8 KVA 5 V 400 HZ 0 KVA 0 V 0 HZ 6 KVA 5 V 400 HZ GEN GEN GEN IDG APU IDG DISC DISC External AC Power Features Displayed when external AC voltage is more than 0 volts and frequency is more than 50 Hz. AC Electrical Page EICAS DIGITAL READOUT GREEN AMBER WHITE HALF INTENSITY MAGENTA AMBER DASHES XX KVA Loaded Overload Not loaded Insufficient data Invalid data XXX V XXX HZ Between 06 and 4 volts Between 70 and 40 Hz Less than 06 volts or more than 4 volts Less than 70 Hz or more than 40 Hz Invalid data Invalid data EICAS OUTLINE GREEN WHITE HALF INTENSITY MAGENTA EXT AC External AC available or in use External AC not available and not in use Invalid data AC Electrical System Synoptic Page Figure Sheet

14 AC Electrical System Vol Sep 09/0 BRT N TO ITT 600 IDG IDG GEN OFF GEN OFF GEN OVLD GEN OVLD APU GEN OFF APU GEN OVLD IDG or caution (amber) Indicates that IDG has low oil pressure or high oil temperature. GEN or OFF caution (amber) Indicates that generator is off. GEN or OVLD caution (amber) Indicates that generator control unit has detected a load of greater than 40 kva N FF (KPH) OIL TEMP OIL PRESS 0.9 F A N VIB C ALT 0 DN RATE P GEAR DN DN SLATS / FLAPS 0 FUEL QTY (KG) TOTAL FUEL 5470 APU GEN OFF caution (amber) Indicates that APU generator is off and APU is ready to load. APU GEN OVLD caution (amber) Indicates that generator control unit has detected a load of greater than 40 kva. Primary Page BRT IDG DISC IDG DISC IDG or DISC status (white) Indicates that IDG has been disconnected, either automatically or manually. Status Page AC Electrical System --- EICAS Indications (Generators) <00> Figure

15 Vol AC Electrical System Sep 09/0 BRT EMER PWR ONLY warning (red) Indicates that the ADG has deployed N TO ITT 600 EMER PWR ONLY AC BUS AC BUS AC ESS BUS AC SERV BUS AC AUTOXFER AC AUTOXFER AC BUS or caution (amber) Indicates that the associated bus is not powered. AC ESS BUS caution (amber) Indicates that AC essential bus is less than 90 Volts FF (KPH) OIL TEMP OIL PRESS 0.9 N F A N VIB C ALT 0 DN RATE 0 GEAR DN DN SLATS / FLAPS 0 P 0.0 FUEL QTY (KG) TOTAL FUEL 5470 AC SERV BUS caution (amber) Indicates that AC bus is powered and AC service bus is less than 90 Volts. AC or AUTOXFER caution (amber) Indicates that the corresponding automatic bus transfer has failed. Primary Page BRT AC or AUTOXFER OFF status (white) Indicates that the corresponding automatic bus transfer has been selected off. AC ESS ALTN status (white) Indicates that AC essential bus is being fed from AC bus. AC AUTOXFER OFF AC AUTOXFER OFF AC ESS ALTN ADG FAIL ADG AUTO FAIL ADG FAIL Status (white) Indicates that generator control unit has failed. ADG AUTO FAIL status (white) Indicates a fault in the deploy control unit, unit is not powered or up--lock solenoid has failed. Status Page AC Electrical System --- EICAS Indications (Busses)<00> Figure

16 AC Electrical System Vol REV, May 0/05 The AC essential bus is normally powered by AC bus. If a fault exists on AC bus, the GCU will automatically transfer the power supplied to the AC essential bus, from AC bus to AC bus. The crew can also manually transfer the AC essential bus supply power, from AC bus to AC bus, using the AC ESS XFER switchlight on the electrical panel. In flight, the AC service bus is normally powered from AC bus. On the ground, it is powered from the APU or external AC. D. AC Loads Distribution AC BUS AC BUS AC ESSENTIAL Flight Recorder Power TRU Main Battery Charger Recirculating Fan Display Cooling Fan Lavatory Exhaust Fan Baggage Compartment Heater Slats and Flaps Channel Pitch Trim Channel Hydraulic Pumps B and B Hydraulic System Fan Left Windshield Heater TAT Probe Heater Right AOA Heater Right Pitot Heater Enhanced Ground Proximity Warning System (EGPWS) Engine Vibration Monitor Avionics Cooling Fan ADG Heater Quick Access Recorder (QAR) <04> TRU Essential TRU Recirculating Fan Galley Exhaust Fan Galley Heater Slats and Flaps Channel Pitch Trim Channel Hydraulic Pumps A and B Right Windshield Heaters Right Window Heater Ice Detector Copilot Panel Integral Lights Inertial Reference Unit Fan <05> Essential TRU Display Cooling Fan Avionics Cooling Fan Crossflow Pump Left Pitot Heater Standby Pitot Heater Left AOA Heater Ice Detector Left Window Heater Cabin Ceiling Lighting CB Panel Integral Lights Pilot Panel Integral Lights Overhead Panel Integral Lights Center Panel Integral Lights Traffic Alert and Collision Avoidance System (TCAS) Engine Ignition A AC SERVICE BUS APU Charger Logo Lights <00> 0 Cabin Sidewall Lighting Cabin Ceiling Lighting g Toilet Water System E. Air Driven Generator (ADG) ADG Bus Hydraulic Pump B Pitch Trim # Slats and Flaps # Slats and Flaps # In the event of a complete AC power failure in flight, the ADG will automatically deploy and supply emergency AC power to the ADG bus and to the AC essential bus. If the automatic deploy function fails, the ADG can be deployed manually by pulling the ADG manual release handle on the ADG CONTROL control panel at the rear of the center console.

17 Vol ELECTRICAL AC Electrical System REV, May 0/05 The ADG is heated in flight by an internal heater. The heater protects against frost or ice formation which could prevent the ADG from deploying in an emergency. The heater is continuously powered in flight from AC Bus when the nose gear is up and locked. On landing, when the nose gear is extended, power is removed from the heater. The ADG bus will supply power to the B hydraulic pump, flaps and slats and pitch trim channel. If either main generator is restored, the crew can override the ADG by pressing the PWR TXFR OVERRIDE button on the ADG control panel. This will reconnect the restored IDG to power AC bus and. The ADG will continue to power the critical flight controls and the ADG bus. The flaps and slats will move at half speed when powered from the ADG bus. The ADG generator, voltage, frequency and ADG bus indications on the EICAS, AC ELECTRICAL synoptic page are only displayed when the ADG bus is powered. The ADG will continue to operate and supply power to the ADG bus until the airspeed decreases below 5 kts. At that point, if the APU generator or IDG has not been restore, the only power available will be from the batteries. The ADG cannot be restowed in flight. It is restowed manually, on the ground, by maintenance personnel. UNIT Used to test auto--deploy system. Test can only be accomplished with two generators selected ON and both main AC busses powered. PWR TXFR OVERRIDE Used to transfer AC essential bus power source from the ADG bus back to the main AC bus. ADG UNIT TEST PWR TXFR OVERRIDE ADG CONTROL ADG Manual Deploy Handle Used to manually deploy the ADG. ADG Manual Deploy Handle and Auto -Deploy Panel Center Pedestal Air Driven Generator (ADG) Figure TEST Light (green) Comes on after successful completion of auto--deploy system test.

18 AC Electrical System Vol REV, May 0/05 F. System Circuit Breakers SYSTEM SUB -SYSTEM CB NAME BUS BAR CB PANEL Generators IDG DISC IDG DISC CB P0 P GCU BATTERY BUS Q9 Generator GCU Q0 Control GCU Q AC Bus PWR SENS C4 ADG ADG HEATER AC BUS C AC Bus PWR SENS AC BUS C4 AC Essential AC ESS FEED AC S Bus PWR SENS ESSENTIAL S PWR SENS D0 AC Electrical l AC Service Power Bus AC SERVICE AC SERVICE E FEED ACPC CONT DC BUS D AC Power ACPC CONT DC BUS L9 Center ACPC CONT N ADG DEPLOY N6 AUTO BATTERY BUS ADG Deploy ADG DEPLOY N7 MAN APU BATT EXT AC PWR 5 A8 DIRECT BUS External AC Power MAIN EXT AC PWR BATTERY 6 A8 DIRECT BUS NOTES

19 Vol ELECTRICAL DC Electrical System REV, May 0/05. DC ELECTRICAL SYSTEM Four transformer rectifier units (TRU) and two batteries (Main and APU) provide the aircraft with DC electrical power. A. Transformer Rectifier Units (TRU) AC power from AC bus, AC bus and from the AC essential bus is converted by four transformer rectifier units to 8VDC and supplied to DC bus, DC bus, DC essential bus, battery bus, DC service bus and the DC utility bus. Normal distribution of the TRU outputs is shown in the following table: INPUT BUS TRU OUTPUT BUS AC Bus TRU DC Bus AC Bus TRU Essential TRU DC Bus / DC Utility Bus DC Battery Bus AC Essential Bus Essential TRU DC Essential Bus ESS TRU is normally supplied AC power from AC BUS. If AC BUS is not available, ESS TRU will be automatically supplied from the AC ESS BUS, via the ESS TRUXFRswitch. B. Batteries There are two nickel--cadmium batteries installed in the aircraft, an APU battery and a main battery. The APU battery is located in the aft equipment compartment and provides DC power to the APU battery direct bus. The APU batery has a nominal output voltage of 4 Vdc with a capacity of 4 ampere--hours. The main battery is located in the nose avionics compartment and provides DC power to the main battery direct bus. The main batery has a nominal output voltage of 4 Vdc with a capacity of 7 ampere--hours. Each battery is maintained at full charge by its related battery charger. The main battery charger is powered from AC bus and the APU battery charger is powered from the AC service bus. Battery charging is controlled automatically. Each charger monitors the battery voltage and temperature to control the charge rate and prevent overheating (thermal runaway). C. DC Distribution DC power is distributed through two DC power centers (DCPCs) located in the avionics compartment. DC bus and DC bus are powered from TRU and TRU respectively with connection controlled by the DCPC control logic. The DC essential, battery and DC emergency buses are normally powered from the essential TRUs. In the event that both essential TRUs fail, the DC essential, battery and emergency bus will be powered by TRU via the automatic CROSS TIE.

20 DC Electrical System Vol Sep 09/0 The Main battery direct bus, APU battery direct bus, and the emergency bus are all hot buses (they are continuously powered at all times from the batteries). When the BATTERY MASTER switch is selected ON, an input signal is supplied to the two power controllers (PC) to connect their respective batteries to the DCPCs for power distribution. Each battery direct bus can power the DC battery bus. Both the battery bus and the APU battery direct bus feed the DC emergency bus. The DC service bus is normally powered from DC bus. If the DC SERVICE switch on the electrical power panel is selected ON, the DC service bus is powered from the APU battery direct bus. If a complete loss of AC power occurs, the ESS TIE will close to connect the DC essential bus to the battery bus for emergency power. If TRU or TRU fails, the MAIN TIE will close to connect DC Bus and DC Bus to functioning TRU ( or ) When the MAIN TIE closes, the DC utility bus is shed to reduce load draw on the remaining TRUs. When both essential TRUs fail or when both TRU and TRU fail, the CROSS TIE closes. If AC bus fails, essential TRU will be powered from the AC essential bus.

21 Vol ELECTRICAL DC Electrical System REV, May 0/05 AC BUS AC ESS BUS AC BUS ESS TRU XFR CONTACTOR TRU ESS TRU ESS TRU TRU TRU CONT ESS TRU CONT LDCPC RDCPC ESS TRU CONT TRU CONT CONTROL LOGIC MAIN TIE CROSS TIE CONTROL LOGIC ESS TIE DC BUS DC ESS BUS DC UTIL BATT BUS DC BUS MAIN BATT CHRG PWR CONTACTOR PWR CONTACTOR AC SERVICE SERV BUS MAIN BATT MAIN BATT DIRECT BUS BATTERY MASTER SWITCH EMER BUS APU BATT DIRECT BUS APU BATT CHRG APU BATT DC Electrical System --- Schematic Figure

22 DC Electrical System Vol Sep 09/0 DC SERVICE Used to connect the DC service bus to the APU battery direct bus. OFF ON DC SERVICE IDG FAULT DISC ELECTRICAL POWER BATTERY MASTER OFF ON ALTN AC AVAIL IN USE AC POWER IDG FAULT DISC AC ESS XFER DISC GEN APU GEN DISC GEN OFF/ RESET OFF/ RESET OFF/ RESET AUTO AUTO AUTO FAIL FAIL OFF AUTO XFER OFF BATTERY MASTER Used to connect the APU and main battery direct busses to the battery bus. NOTE Battery master should always be in the ON position in flight. Electrical Power Panel Overhead Panel Electrical Power Overhead Panel Figure

23 Vol DC Electrical System Sep 09/0 BRT TRU Voltage Displays the TRU voltage level. TRU Load Displays the load on the TRU. AC BUS TRU 8 V 8 A BUS BUS SERV BUS UTIL BUS DC ELECTRICAL AC BUS TRU 8 V 8 A CROSS TIE AC BUS AC ESS BUS ESS ESS TRU TRU 8 V 8 V 0 A 0 A ESS BUS ESS TIE BATT BUS Battery Voltage Displays the battery voltage level. MAIN TIE APU BATT MAIN BATT 4 V 0 A 4 V 0 A APU BATT DIR BUS MAIN BATT DIR BUS Flow Lines Green -- Energized. Blank -- Not energized. DC ELEC Page EICAS Secondary Display Center Instrument Panel Battery Load Displays the load on the battery. EICAS DIGITAL READOUT GREEN WHITE AMBER DASHES xx V (TRU) Between and 9 volts Less than volts or more than 9 volts Invalid data xx V (BATT) Between 8 and volts Less than 8 volts or more than volts Invalid data xx A (TRU) Between.7 and 0.7 amps Less than.7 amps or more than 0.7 amps Invalid data xx A (BATT) Not less than.7 amps or not less than volts Less than.7 amps and less than volts Invalid data EICAS OUTLINE GREEN AMBER WHITE HALF INTENSITY MAGENTA BUS Bus powered Bus not powered _ Invalid data DIR BUS Not less than 8 volts Less than 8 volts _ Invalid data TRU Not less than.7 amps and not less than 8 volts _ Less than.7 amps and less than 8 volts Invalid data BATT Not less than 8 volts Less than 8 volts _ Invalid data DC Electrical Page Tru Voltage Figure

24 DC Electrical System Vol Sep 09/0 BRT AC BUS DC ELECTRICAL AC BUS AC BUS AC ESS BUS TRU 0 V 0 A TRU 0 V 0 A ESS ESS TRU TRU 0 V 0 V 0 A 0 A BUS BUS SERV BUS UTIL BUS CROSS TIE ESS BUS ESS TIE BATT BUS SERVICE CONFIGURATION (amber) Indicates that the DC SERVICE has been selected on. MAIN TIE SERVICE CONFIGURATION APU BATT MAIN BATT 4 V 0 A 4 V 0 A APU BATT DIR BUS MAIN BATT DIR BUS DC Electrical Page Alternate AC Essential Flow Lines Displayed only when AC bus is not available. BRT AC BUS DC ELECTRICAL AC BUS AC ESS BUS TRU 8 V 8 A TRU 0 V 0 A ESS ESS TRU TRU 8 V 8 V 0 A 0 A CHARGER (white) Indicates that the corresponding charger is not charging. BATT OFF (amber) Indicates that the corresponding battery is not available. APU BATT MAIN BATT BUS BUS SERV BUS UTIL BUS MAIN TIE CROSS TIE CHARGER 0 V BATT OFF 0 A CHARGER 0 V BATT OFF 0 A ESS BUS APU BATT DIR BUS MAIN BATT DIR BUS DC Electrical Page ESS TIE BATT BUS EMER BUS DC Electrical Page Service Configuration Figure DC Emergency Bus and Flow Lines Displayed only when the emergency bus is not powered by both the battery bus and the APU battery direct bus.

25 Vol DC Electrical System Sep 09/0 APU or MAIN BATT OFF caution (amber) Indicates that APU or main battery is not available. BRT N TO ITT N FF (KPH) OIL TEMP OIL PRESS 0.9 F A N VIB APU BATT OFF MAIN BATT OFF DC BUS DC BUS DC EMER BUS DC ESS BUS DC SERV BUS BATTERY BUS C ALT 0 RATE 0 GEAR FUEL QTY (KG) TOTAL FUEL 5470 P 0.0 DN DN DN SLATS / FLAPS 0 DC BUS or caution (amber) Indicates that the corresponding DC bus is not powered with either AC bus or on line. DC EMER BUS caution (amber) Indicates that emergency bus is not powered. DC ESS BUS caution (amber) Indicates that essential bus is not powered in flight or essential bus is not powered on the ground with either AC essential bus or APU generator on line. DC SERV BUS caution (amber) Indicates that service bus is not powered with either DC bus powered or DC SERVICE selected on and APU voltage >8 volts. BATTERY BUS caution (amber) Indicates that battery bus is not powered. Primary Page BRT DC CROSS, MAIN or ESS TIE CLSD status (white) Indicates that the corresponding bus tie is closed. ESS TRU XFER status (white) Indicates that essential TRU is powered by AC essential bus. APU or MAIN BATT CHGR status (white) Indicates that the corresponding battery is overheating or not charging. DC CROSS TIE CLSD DC MAIN TIE CLSD DC ESS TIE CLSD ESS TRU XFER APU BATT CHGR MAIN BATT CHGR 00 APU DOOR OPEN 40 FLT. NO. CRJ - TRIM - AIL STAB NU LWD RWD ND RPM EGT BRAKE TEMP 0. RUDDER NL NR OXY 500 CTEMP CALT 0 RATE 0 P 0.0 LDG ELEV Status Page EICAS Primary Display Auxiliary Power Unit / Main Battery off <00> Figure

26 DC Electrical System Vol Sep 09/0 TRU FAIL status (white) Indicates that TRU voltage is < 8 volts with AC bus on line or main tie is closed with TRU load <.7 amps. TRU FAIL status (white) Indicates that TRU voltage is < 8 volts with AC bus on line or main tie is closed with TRU load <.7 amps. BRT ESS TRU FAIL status (white) Indicates that essential TRU voltage is < 8 volts with AC essential bus on line or essential tie is closed with essential TRU load <.7 amps. TRU FAIL TRU FAIL ESS TRU FAIL ESS TRU FAIL TRU FAN FAIL FLT. NO. CRJ - TRIM - AIL STAB NU 0. ND LWD RWD RUDDER NL NR ESS TRU FAIL status (white) Indicates that essential TRU voltage is < 8 volts with AC bus on line or essential TRU is powered by AC essential bus or essential tie is closed with essential TRU load <.7 amps. OXY 500 APU CTEMP CALT RATE 0 P 0.0 LDG ELEV 00 RPM EGT BRAKE TEMP DOOR OPEN TRU FAN FAIL status (white) Indicates that any of 4 TRU fans have failed. Status Page Transformer Rectifire Unit Fail --- Status Page Figure

27 Vol DC Electrical System Sep 09/0 D. DC Loads Distribution Flight Recorder Control EICAS Primary Display EICAS Secondary Display Left Lamp Driver Unit EICAS Dimming Data Loader Left IAPS Boarding Music Passenger Door Actuator ACPC Control Baggage Compartment Control Fan Monitor Cabin Pressure Control Cockpit Temperature Sensors Aft Cabin Temperature Sensors Right IAPS Right AFCS Right IAPS Fan Observer Audio VHF Communication RTU Service Bus Feed ACPC Control Left ACS Pressure Sensors Cabin Pressure Control Galley Heater Control Fwd Cabin Temperature Sensors ACS Control Channel B Right ACS Manual DC BUS ACS Control Channel A Lavatory Smoke Detector SSCU Channel A Pitch Feel Radio Altimeter Hydraulic Pump and B Control Hydraulic System Fan Control Hydraulic System Indication Anti-Ice Control Channel A Left T Heater Pilot Windshield Wiper Left Windshield Heater Control ADS Heater Control Right Static Heaters DC BUS SSCU Channel B Aileron and Rudder Trim Clock Radio Altimeter <045> Air Data Computer Primary Flight Director Multifunctional Display EFIS Control Panel Attitude Heading Right Fuel Pump and Control Hydraulic System Indication Hydraulic Pump and A Control Right T Heater Copilot Windshield Wiper Right Windshield Heater Control Right EFIS CRT Dimming Brake Pressure Application PSEU Channel A Nose Wheel Steering Anti-Skid Left Cabin Reading Lights Cockpit Dome Light Taxi Lights Nose Landing Lights Cockpit Floor Lights Rear Anti-Collision Lights Wing Inspection Lights Maintenance Lights GPS DME Weather Radar Right Window Heater Control PSEU Channel B Nose Wheel Steering Brake Pressure Indication Anti-Skid Chart Holder Lights Copilot Map Light Wing Anti-Collision Lights ADF Transponder VHF Navigation DME AHRS Fan GPS <07> EMERGENCY BUS SERVICE BUS UTILITY BUS APU Battery Direct Bus Feed FIREX Engine and APU Fuel SOVs Hydraulic SOVs Service Lights Boarding Lights Navigation Lights Toilet Lights Galley Area Lights Beacon Lights Water System Right Cabin Reading Lights

28 DC Electrical System Vol REV, May 0/05 EICAS DCU RTU Pilot Audio Cockpit Voice Recorder Door Indication and ACS Control Channel B Left ACS Manual Display Fan Control Right ACS Pressure Sensors Flap and Slat Control Channel SSCU Pitch Feel Rudder Travel Limit ESSENTIAL BUS Stall Protection Right Channel Left EFIS CRT Dimming EFIS Control Panel Air Data Computer Primary Flight Director Multifunctional Display Crossflow Pump Control Fuel System Control Left Static Heater ADS Heater Control ADS Standby Heater Control Left Window Heater Control Anti-Ice Control Channel B Instrument Flood Lights Emergency Lights ADF Transponder VHF Navigation Attitude Heading AHRS Fan Bleed Air SOVs Thrust Reversers Right Engine Oil Pressure Left T Heater EICAS DCU and EICAS Primary Display EICAS Secondary Display EICAS Control Panel Right Lamp Driver Unit EICAS Dimming Left AFCS MDC Left IAPS Fan APU Control APU ECU Primary VHF Communication Emergency Tuning Pilot, Copilot and Observer Audio Cabin Interphone Passenger Address Emergency Bus Feed IDG Disconnect Generator Control Units BATTERY BUS ACPC Control ADG Deployment ACS Control Channel A Ram Air SOV Manual Cabin Pressure Control Passenger Oxygen Deployment Crew Oxygen Monitor Cargo Smoke Detection Fire Detection MLG Bay Overheat Detection Flap and Slat Control Channel Aileron and Rudder Trim Indication Stall Protection Stick Pusher Stall Protection Left Channel Standby Instrument Clock Left Fuel Pump and Control Fuel System Control Right T Heater Gravity Fuel Crossflow Fuel Transfer SOVs APU Fuel Pump Hydraulic System Indication Cowl Anti-Ice Valves Wing Anti-ice Isolation Valve PSEU Channel A and B Weight-On-Wheels Passenger Signs Wing Landing Lights Map Lights Cabin Utility Lights Overhead Panel Lights EICAS and RTU Dimming Left Engine Oil Pressure Engine Starting FADEC Engine Ignition B MAIN BATTERY DIRECT BUS Main Battery Power Sensors Main Battery Control External AC Power DCPC Main Battery Charger Output Clocks Cockpit Dome Lights APU ECU Secondary APU Door Actuator APU Battery Power Sensors APU Battery Control DCPC External AC Power APU BATTERY DIRECT BUS Service Bus Feed Emergency Bus Feed Refuel/Defuel Control Emergency Refuel Engine Oil Indication Engine Oil Replenishment <>

29 E. System Circuit Breakers ELECTRICAL Vol DC Electrical System Sep 09/0 SYSTEM SUB -SYSTEM CB NAME BUS BAR CB PANEL DC Electrical Power Transformer Rectifier Units DC Bus DC Bus DC Essential Bus DC Emergency Bus DC Service Bus DC Utility Bus Battery Bus DC Power Center CB TRU AC BUS B5 ESS TRU AC T ESS TRU B ESSENTIAL T5 TRU B5 AC BUS ESS TRU A C5 DC FEED D6 DC BUS PWR SENS D4 RCCB DC D DC FEED L8 DC BUS PWR SENS L0 RCCB DC D4 DC ESS FEED DC R6 PWR SENS ESSENTIAL R RCCB DC ESS D5 EMER BUS FEED EMER BUS FEED PWR SENS SERV BUS FEED SERV BUS FEED APU BATT DIRECT BUS BATTERY BUS DC EMERGENCY APU BATT DIRECT BUS DC BUS 5 A0 L0 R 5 A9 F5 PWR SENS DC SERVICE M PWR SENS L DC UTILITY DC UTILITY L7 FEED BATT BUS FEED BATTERY N BUS PWR SENS L DCPC APU BATT DIRECT BUS 5 A4 MAIN DCPC BATTERY 6 B DIRECT BUS NOTES

30 DC Electrical System Vol Sep 09/0 SYSTEM SUB -SYSTEM CB NAME BUS BAR CB PANEL CB NOTES DC Electrical Power APU Battery Main Battery Battery Charging g APU BATT DIR FEED APU BATT CONT APU BATT PWR SENS APU BATT PWR SENS REF RCCB APU BATT MAIN BATT CONT MAIN BATT PWR SENS MAIN BATT PWR SENS REF RCCB MAIN BATT APU CHARGER MAIN BATTERY CHARGER MAIN BATT CHARGER OUTPUT DC EMERGENCY APU BATT DIRECT BUS R 5 MAIN BATTERY 6 DIRECT BUS A A A D A A A D AC SERVICE E5 AC BUS C5 MAIN BATTERY DIRECT BUS 6 B6

31 . CIRCUIT BREAKER PANELS Vol ELECTRICAL Circuit Breaker Panels REV, May 0/05 There are eight circuit breaker panels (CBP s) located in the aircraft (Refer to figure ). There are two circuit breaker panels, identified as CBPs and, located in the flight compartment. A circuit breaker panel, identified as CBP--5, is located in the aft equipment compartment. Another circuit breaker panel, identified as CBP--6, is located in the forward equipment compartment. Circuit breakers are also installed on the AC power center, the left and right DC power centers and on the galley control panel (not shown). Circuit breaker panels, and the galley circuit breakers are crew accessable during flight. Circuit breaker panels 5, 6, and the circuit breakers on the AC and DC power centers are only accessable on the ground. The circuit breakers are clearly identified. For circuit breaker referencing, each circuit breaker panel is laid out in an alphanumeric grid with letters running down the side of the panel and numbers running across each row (Refer to figure ). For example, the location of a circuit breaker on circuit breaker panel, in the 4th row, column, would be identified as CBP--D. In this instance, D is the circuit breaker for the APU BATT.

32 Circuit Breaker Panels Vol REV, May 0/05 Circuit Breaker Panel Circuit Breaker Sub--Panel Right DC Power Center AC Power Center Circuit Breaker Panel Circuit Breaker Sub--Panel Left DC Power Center Circuit Breaker Panel 5 Circuit Breaker Panel 6 Panel Overview Figure

33 Vol ELECTRICAL Circuit Breaker Panels REV, May 0/05 CIRCUIT BREAKER PANEL (Behind Pilot s Seat) POWER MUST BE OFF BEFORE OPENING PANEL CBP-- A AVIONICS FAN 5 RECIRC FAN AC BUS 7 HYD SYST FAN L WSHLD 0 HEATERS TAT AOA R B AVIONICS DISPLAY COOLING FAN 7 4 TRU AC BUS LAV EXHAUST FAN C BAGG COMPT HEATER 5 4 MAIN BATTERY CHARGER AC BUS ENG VIB MON 7 8 FLIGHT REC PWR 9 0 D MAIN BATT APU BATT RCCB DC DC 4 DC ESS 5 DC FEED 80 6 A/ICE CONT CH A 7 BAGG COMPT CONT 8 LAV SMOKE DET 9 DC BUS ACPC CONT 0 0 E PASS DOOR ACT 5 L CABIN READING FWD 0 LIGHTS AFT 0 CKPT DOME LIGHT 4 DC BUS BRAKE PRESS APPL F SSCU CH A 7 PFEEL 4 TAXI LTS 7 5 FAN MONIT 6 DC BUS CABIN PRESS CONT 0 AC PUMP CONT B HYD SYST FAN CONT IND G PSEU CH A 7 NOSE STEER BOARD MUSIC ANTI SKID 4 WIPER PILOT 5 5 LDG NOSE 5 6 DC BUS CKPT FLOOR 7 LIGHTS REAR A/COLL 5 8 WING INSP 5 9 MAINT 7 0 CONT HEATERS ADS LWSHLD CONT H IAPS L PRIM DISPL 0 SEC DISPL 0 4 EICAS LDU L 5 BRT / DIM PWR SUP DC BUS 7 DATA LOAD PITOT R 7 4 GND PROX WARN 4 PWR SENS 4 PWR SENS 4 FLIGHT REC CONT 4 AC PUMP CONT 4 STATIC R 4 DME 4 AFT CABIN TEMP SENS DC BUS RAD ALT 4 J R/T WEATHER RADAR CONT DC BUS ACS CONT CH A CKPT TEMP SENS ACS CONT CH A PWR SENS BATTERY BUS FLAPS CONT CH SLATS CONT CH AIL / RUD TRIM IND LENG OIL PRESS ENG START R L BATTERY BUS L FUEL PUMP LFUEL PUMP CONT BATTERY BUS A FIRE DET B APU CONT LDG WINGS PLT MAP LIGHTS C / PLT OBS MAP CAB UTIL O/H PNL BATTERY BUS EICAS / RTU DIMMING STALL PROT STICK L PUSHER CH VHF COM EMER TUNING BATTERY BUS PILOT AUDIO C/PLT K HYD SYST IND 8 9 CARGO SMOKE DET A B 8 9 FUEL GRAVITY XFLOW LXFER FUEL SOV PASS OXYGEN MANUAL DEPLOY R L OBS EMER BUS FEED 0 0 PASS SIGNS 5 0 APU FUEL PUMP 7 0 IDG DISC 5 0 GCU 0 L FUEL SYST CONT APU ECU PRIM 5 IDG DISC 5 M N P Q Circuit Breaker Panel (For Reference Only) Figure

34 Circuit Breaker Panels Vol REV, May 0/05. ATA NUMBERING AND CIRCUIT BREAKER The aircraft circuit breakers are listed in this chapter by ATA as follows: SUBJECT ATA FCOM CHAPT AIR CONDITIONING 8 AUTO FLIGHT COMMUNICATIONS 5 ELECTRICAL 4 7 EQUIPMENT 5 9&0 FIRE PROTECTION 6 0 FLIGHT CONTROLS 7 FUEL 8 HYDRAULICS 9 4 ICE&RAIN 0 5 INDICATING & RECORDING LANDING GEAR 6 LIGHTING 7 NAVIGATION 4 & 8 OXYGEN 5 9 PNEUMATICS 6 9 WATER & WASTE 8 MDC (DIAGNOSTICS) 45 APU 49 4 DOORS 5 6 POWERPLANT 7 TO 80 0 The circuit breakers for each ATA are listed by sub--section and alphabetically as follows:. ATA - AIR CONDITIONING A. AVIONICS COOLING AVIONICS DISPLAY COOLING FAN AVIONICS DISPLAY COOLING FAN CBP--U CBP--B (--PHASE)

35 Vol ELECTRICAL Circuit Breaker Panels REV, May 0/05 AVIONICS COOLING FAN AVIONICS COOLING FAN DISPLAY FAN CONT FAN MONIT CBP--V CBP--A CBP--T0 CBP--F6 B. BAGGAGE COMPARTMENT BAGG COMPT CONT BAGG COMPT HEATER <0> CBP--D8 CBP--C (--PHASE) C. GALLEY AND LAVATORY SYSTEM GALLEY EXHAUST FAN CBP--B8 (--PHASE) GALLEY HEATER CBP--B (--PHASE) GALLEY HEATER CONT CBP--F LAV EXHAUST FAN CBP--B8 (--PHASE) D. PRESSURIZATION CABIN PRESS CONT CABIN PRESS CONT CABIN PRESS MAN CONT CBP--F0 CBP--F0 CBP--P5 E. RAM AIR AND RECIRC SYSTEM RAM AIR SOV RECIRC FAN RECIRC FAN CBP--P4 CBP--A5 CBP--A5

36 Circuit Breaker Panels Vol REV, May 0/05 F. TEMPERATURE CONTROL ACS CONT CH A ACS CONT CH B ACS CONT CH A ACS CONT CH B ACS L MAN ACS R MAN ACS L PRESS SENS ACS R PRESS SENS AFT CABIN TEMP SENS CKPT TEMP SENS FWD CABIN TEMP SENS CBP--L CBP--J4 CBP--K6 CBP--K7 CBP--T8 CBP--K6 CBP--F6 CBP--T CBP--J CBP--K7 CBP--J 4. ATA - AUTO FLIGHT IAPS L or (IAPS L FMS) IAPS L AFCS/MDC IAPS L FAN IAPS R IAPS R AFCS IAPS R FAN CBP--H CBP--P6 CBP--P7 CBP--H CBP--H CBP--H 5. ATA - COMMUNICATIONS A. AUDIO INTEGRATING SYSTEM AUDIO -- C/PLT AUDIO -- PILOT AUDIO PILOT AUDIO -- OBS CABIN INPH PASS ADDR CBP--Q7 CBP--Q6 CBP--V CBP--Q8 and CBP--H4 CBP--Q CBP--Q4

37 Vol ELECTRICAL Circuit Breaker Panels REV, May 0/05 B. ANNOUNCEMENT AND BOARDING MUSIC SYSTEM BOARD MUSIC CBP--G C. VHF EMER TUNING RTU RTU VHF COM VHF COM CBP--Q4 CBP--U9 CBP--K7 CBP--Q CBP--H0 6. ATA 4 - ELECTRICAL A. AC SYSTEM AC ESS FEED AC ESS FEED AC ESS FEED ACPC CONT ACPC CONT ACPC CONT AC SERVICE FEED APU GEN POR CABIN FEED BATT BUS FEED CABIN FEED CTRL PWR CTRL PWR CBP--S AC PWR CTR AC PWR CTR CBP--D CBP--L9 CBP--N CBP--E AC PWR CTR AC PWR CTR CBP--N AC PWR CTR AC PWR CTR AC PWR CTR

38 Circuit Breaker Panels Vol REV, May 0/05 CTRL PWR EXT AC POR EXT AC PWR EXT AC PWR EXT AC V/F SENSE GCU -- GCU -- GCU -- GEN POR GEN POR IDG DISC IDG DISC PWR SENS PWR SENS SERVICE BUS FEED TRU EMP IN TRU EMP OUT AC PWR CTR AC PWR CTR CBP6--A8 CBP5--A8 AC PWR CTR CBP--Q9 CBP--Q0 CBP--Q AC PWR CTR AC PWR CTR CBP--P0 CBP--P CBP--S and C4 CBP--D0 and C4 AC PWR CTR AC PWR CTR AC PWR CTR B. ADG AC ESS FEED ADG DEPLOY -- AUTO ADG DEPLOY -- MAN ADG HEATER ADG LOADS ADG LOADS ADG V/F SENSE ADG PWR CTR CBP--N6 CBP--N7 CBP--C ADG PWR CTR ADG PWR CTR ADG PWR CTR C. DC SYSTEM APU BATT CONT APU BATT DIR FEED CBP5--A CBP--R

39 Vol ELECTRICAL Circuit Breaker Panels REV, May 0/05 APU BATT PWR SENS APU BATT PWR SENS REF APU CHARGER BATT/ESS XFEED DC FEED DC/ XFEED DC FEED DC ESS FEED DC UTILITY FEED DCPC DCPC EMER BUS FEED EMER BUS FEED ESS TRU ESS TRU -- LOGIC PWR ESS TRU -- SENSE HI ESS TRU -- SENSE LO ESS TRU A ESS TRU B ESS TRU -- LOGIC PWR ESS TRU -- SENSE HI ESS TRU -- SENSE LO FEED -- BATT BUS FEED -- DC FEED -- DC UTIL MAIN BATT CHARGER OUTPUT MAIN BATT CONT MAIN BATT PWR SENS MAIN BATT PWR SENS REF MAIN BATTERY CHARGER PWR SENS PWR SENS RCCB -- APU BATT RCCB -- DC RCCB -- DC RCCB -- DC ESS CBP5--A CBP5--A CBP--E5 RDCPWRCTR CBP--D6 RDCPWRCTR CBP--L8 CBP--R6 and DC PWR CTR CBP--L7 CBP5--A4 CBP6--B CBP--L0 CBP5--A0 CBP--T LDCPWRCTR LDCPWRCTR LDCPWRCTR CBP--C5 CBP--T5 RDCPWRCTR RDCPWRCTR RDCPWRCTR RDCPWRCTR RDCPWRCTR RDCPWRCTR CBP6--B6 CBP6--A CBP6--A CBP6--A CBP--C5 CBP--D4, L, R CBP--L, L0, M, R CBP--D CBP--D CBP--D4 CBP--D5

40 Circuit Breaker Panels Vol REV, May 0/05 RCCB -- MAIN BATT SERV BUS FEED TRU TRU -- LOGIC POWER TRU -- SENSE HI TRU -- SENSE LO TRU TRU -- LOGIC POWER TRU -- SENSE HI TRU -- SENSE LO XFEED -- BATT/ESS XFEED -- DC / CBP--D CBP--F5 and CBP5--A9 CBP--B5 LDCPWRCTR LDCPWRCTR LDCPWRCTR CBP--B5 RDCPWRCTR RDCPWRCTR RDCPWRCTR LDCPWRCTR LDCPWRCTR 7. ATA 5 - EQUIPMENT AND FURNISHINGS COFFEE MAKER COFFEE MAKER OUTLET OVEN OVEN GALLEY CONTROL PANEL GALLEY CONTROL PANEL GALLEY CONTROL PANEL GALLEY CONTROL PANEL GALLEY CONTROL PANEL 8. ATA 6 - FIRE PROTECTION A. DETECTION CARGO -- SMOKE DET A CARGO -- SMOKE DET B FIRE DET -- A FIRE DET -- B LAV SMOKE DET MLG BAY OVHT DET CBP-- M8 CBP--M9 CBP--N CBP--N CBP--D9 CBP--N9

41 Vol ELECTRICAL Circuit Breaker Panels REV, May 0/05 B. EXTINGUISHING FIREX -- A FIREX -- B CBP--R CBP--R 9. ATA 7 - FLIGHT CONTROLS A. AILERONS AIL TRIM AIL/RUD TRIM IND CBP-- F CBP--L7 B. ELEVATORS PFEELRTL PFEELRTL CBP--F CBP--R5 C. FLAPS FLAPS FLAPS FLAPS CONT CH FLAPS CONT CH AC PWR CTR AC PWR CTR CBP--R CBP--L5 D. HORIZONTAL STABILIZER PFEELRTL PFEELRTL PITCH TRIM PITCH TRIM CBP--F CBP--R5 AC PWR CTR AC PWR CTR

42 Circuit Breaker Panels Vol REV, May 0/05 SSCU CH A SSCU CH B SSCU CH A SSCU CH B CBP--F CBP--F CBP--R CBP--R4 E. RUDDER AIL/RUD TRIM IND RUDDER TRIM CBP--L7 CBP--F F. SLATS SLATS CONT CH SLATS CONT CH SLATS SLATS CBP--R CBP--L6 AC PWR CTR AC PWR CTR G. SPOILERS SSCU CH A SSCU CH B SSCU CH A SSCU CH B CBP--F CBP--F CBP--R CBP--R4 H. STALL PROTECTION STALL PROT -- L CH STALL PROT -- R CH STALL PROT -- STICK PUSHER CBP--Q CBP--U5 CBP--Q

43 Vol ELECTRICAL Circuit Breaker Panels REV, May 0/05 0. ATA 8 - FUEL A. DISTRIBUTION APU FUEL PUMP FUEL SOV -- L ENG FUEL SOV -- R ENG FUEL SOV -- APU LFUELPUMP LFUELPUMPCONT R FUEL PUMP R FUEL PUMP CONT CBP--N0 CBP--R8 CBP--R7 CBP--R9 CBP--M6 CBP--M7 CBP--G9 CBP--G0 B. MANAGEMENT CROSSFLOW PUMP CROSSFLOW PUMP CONT FUEL GRAVITY XFLOW LXFERFUELSOV RXFERFUELSOV CBP--S5 CBP--R7 CBP--N8 CBP--N9 CBP--P8 C. REFUELING/DEFUELING EMER REFL FUEL DEFL CBP5--B5 CBP5--B4 D. INDICATION FUEL SYST CONT FUEL SYS CONT CBP--M CBP--U

44 Circuit Breaker Panels Vol REV, May 0/05. ATA 9 - HYDRAULICS A. SYSTEMS AND HYD SOV -- L ENG HYDSOV--RENG HYD SYST -- AC PUMP CONT HYD SYST -- AC PUMP CONT HYD SYST FAN HYD SYST -- FAN CONT HYD SYST -- IND HYD SYST -- IND CBP--R6 CBP--R5 CBP--F CBP--F4 CBP--A8 CBP--F CBP--F CBP--F B. SYSTEM HYD SYST -- AC PUMP CONT A HYD SYST -- AC PUMP CONT B HYD SYST IND CBP--F4 CBP--F CBP--L8. ATA 0 - ICE & RAIN A. AIR DATA ANTI -ICE HEATERS -- ADS CONT HEATERS -- ADS CONT HEATERS -- ADS CONT STBY HEATERS -- AOA L HEATERS -- AOA R HEATERS -- PITOT L HEATERS -- PITOT R HEATERS -- PITOT STBY HEATERS -- STATIC L HEATERS -- STATIC R HEATERS -- TAT CBP--S CBP--G CBP--S CBP--T8 CBP--A CBP--T7 CBP--A4 CBP--T9 CBP--S CBP--G4 CBP--A

45 Vol ELECTRICAL Circuit Breaker Panels REV, May 0/05 B. COWL ANTI -ICE A/ICE -- VALVE L ENG A/ICE -- VALVE R ENG CBP--N CBP--N4 C. ICE DETECTION ICE DET ICE DET CBP--T CBP--A4 D. WING ANTI -ICE A/ICE CONT CH A A/ICE CONT CH B WING A/ICE ISOL CBP--D7 CBP--T CBP--N5 E. WINDSHIELD ANTI -ICE HEATERS -- CONT L WIND HEATERS -- CONT L WSHLD HEATERS -- CONT R WIND HEATERS -- CONT R WSHLD HEATER -- L WIND HEATERS -- L WSHLD HEATERS -- L WSHLD HEATER -- R WIND HEATERS -- R WSHLD HEATERS -- R WSHLD CBP-- S4 CBP--G CBP--G4 CBP--G CBP--U0 CBP--A0 CBP--A CBP--C7 CBP--A0 CBP--A

46 Circuit Breaker Panels Vol REV, May 0/05 F. WINDSHIELD WIPERS WIPER C/PILOT WIPER PILOT CBP--G5 CBP--G5. ATA - INDICATING & RECORDING A. CLOCKS CLOCK CLOCK CBP--N and CBP6--B7 CBP--H5 and CBP6--B8 B. EICAS EICAS -- CONT PNL EICAS -- DCU EICAS -- DCU EICAS -- LDU L EICAS -- LDU R EICAS -- PRIM DISPL EICAS -- SEC DISPL CBP--Q7 CBP--Q, U8 CBP--H, Q CBP--H5 CBP--Q8 CBP--H and CBP--Q5 CBP--H4 and CBP--Q6 C. RECORDERS CKPT VOICE REC CBP--V7 CREW FORCE SYST <> CBP--E DATA LOAD <08> CBP--H0 FLIGHT REC CONT CBP--E4

47 Vol ELECTRICAL Circuit Breaker Panels REV, May 0/05 FLIGHT REC PWR CBP--C9 QAR <04> CBP--C 4. ATA - LANDING GEAR A. BRAKES ANTI--SKID BRAKE PRESS APPL BRAKE PRESS IND CBP--G4 and CBP--G4 CBP--E CBP--G B. NOSE WHEEL STEERING NOSE STEER CBP--G and CBP--G C. PROXIMITY SENSING PSEU CH A PSEU CH B WOW RELAY CBP--G and CBP--P CBP--G and CBP--P CBP--P 5. ATA - LIGHTING A. EMERGENCY LIGHTING EMER LTS CBP-- U B. EXTERNAL LIGHTING BEACON LIGHTS CBP--M8

48 Circuit Breaker Panels Vol REV, May 0/05 LIGHTS -- LDG NOSE CBP--G6 LIGHTS -- LDG WINGS CBP--P LIGHTS -- NAV CBP--M4 LIGHTS -- REAR A/COLL CBP--G8 LIGHTS -- WING A/COLL CBP--G8 LIGHTS -- WING INSP CBP--G9 LOGO LIGHTS <00> CBP--D TAXI LTS CBP--F5 C. FLIGHT COMPARTMENT LIGHTING CKPT DOME LIGHTS L EFIS CRT DIMMING EICAS -- BRT / DIM PWR SUP EICAS -- BRT / DIM PWR SUP INST FLOOD LTS INTEG LTS -- C/PLT PNLS INTEG LTS -- CB PNLS INTEG LTS -- CTR PNLS INTEG LTS -- O/H PNLS INTEG LTS -- PLT PNLS LIGHTS -- CHART HOLDER LIGHTS -- CKPT FLOOR LIGHTS -- C/PLT MAP LIGHTS -- C/PLT OBS MAP LIGHTS -- EICAS/RTU DIMMING LIGHTS -- O/H PNL LIGHTS -- PLT MAP R EFIS CRT DIMMING CBP--E4 and CBP6--B5 CBP--U4 CBP--H6 and CBP--Q0 CBP--H7 and CBP--Q CBP--U CBP--B4 CBP--V4 CBP--V6 CBP--V7 CBP--V5 CBP--G6 CBP--G7 CBP--G7 CBP--P CBP--P6 CBP--P5 CBP--P CBP--J D. PASSENGER COMPARTMENT LIGHTING CABIN LIGHTING CEILING CBP--T0

49 Vol ELECTRICAL Circuit Breaker Panels REV, May 0/05 CABIN LIGHTING CEILING L CABIN LIGHTING CEILING R CABIN LIGHTING SIDEWALL L CABIN LIGHTING SIDEWALL R L CABIN -- READING LIGHTS -- AFT L CABIN -- READING LIGHTS -- FWD L CABIN -- READING LIGHTS -- MID LIGHTS -- BOARD LIGHTS -- CABIN UTIL LIGHTS -- GALLEY AREA LIGHTS -- TOILET PASS SIGNS R CABIN -- READING LIGHTS AFT R CABIN -- READING LIGHTS FWD CBP--D4 CBP--D CBP--E4 CBP--D CBP--E8 CBP--E6 CBP--E7 CBP--M CBP--P4 CBP--M6 CBP--M5 CBP--M0 CBP--L4 CBP--L E. SERVICE AND MAINTENANCE LIGHTING LIGHTS -- AFT SERV LIGHTS -- FWD SERV LIGHTS -- MAINT LIGHTS -- SERV AREA CBP--M CBP--M CBP--G0 CBP--M7 6. ATA 4 - NAVIGATION A. AIR DATA SYSTEM ADC ADC CBP--V CBP--H6

50 Circuit Breaker Panels Vol REV, May 0/05 B. AUTOMATIC DIRECTION FINDER (ADF) ADF ADF CBP--V4 CBP--H7 C. AIR TRAFFIC CONTROL TRANSPONDER SYSTEM (ATC) XPDR XPDR CBP--V5 CBP--H8 D. INERTIAL REFERENCE SYSTEM (IRS) <05> AHRS FAN CBP--V9 AHRS FAN CBP--K5 ATT HDG CBP--V8 ATT HDG CBP--K4 IRU FAN <05> CBP--C E. DISTANCE MEASURING EQUIPMENT (DME) DME DME CBP--H4 CBP--H4 F. ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) EFIS CONT PNL EFIS CONT PNL EFIS CRT DIMMING MFD CBP--U7 CBP--K CBP--U4 CBP--V

51 Vol ELECTRICAL Circuit Breaker Panels REV, May 0/05 MFD PFD PFD CBP--K CBP--V0 CBP--K G. FLIGHT MANAGEMENT SYSTEM (FMS) CDU < 4> CBP--H9 CDU < 4> CBP--H9 FMS <4> CBP--H FMS <4> CBP--H H. GLOBAL POSITIONING SYSTEM (GPS) GPS CBP--G GPS <07> CBP--G I. GROUND PROXIMITY WARNING SYSTEM (GPWS) GND PROX WARN CBP--B4 J. RADIO ALTIMETER RAD ALT CBP--J4 RAD ALT <045> CBP--J K. STANDBY INSTRUMENTS INT STBY INST CBP--N0