ELECTRICAL PILOT TRAINING GUIDE Table of Contents Introduction ......................................................................................................................... 7-1 Alternating Current (AC) System ........................................................................................ 7-3 Description ....................................................................................................................7-3 Components and Operation .......................................................................................... 7-4 Integrated Drive Generators (IDGs) ........................................................................ 7-4 APU Generator........................................................................................................ 7-6 External AC Electrical Power ........................................................................................ 7-8 Description ....................................................................................................................7-8 Operation ...................................................................................................................... 7-8 AC Electrical Power Distribution ....................................................................................... 7-10 Description .................................................................................................................. 7-10 Components and Operation ........................................................................................ 7-11 AC BUS 1 and AC BUS 2 ..................................................................................... 7-11 AC ESS (Essential) Bus ........................................................................................ 7-13 AC Utility Buses .................................................................................................... 7-14 Air-Driven Generator (ADG).............................................................................................. 7-15 Description .................................................................................................................. 7-15 Components and Operation ........................................................................................ 7-16 Air-Driven Generator ............................................................................................. 7-16 ADG Auto Deploy Control Unit.............................................................................. 7-17 ADG Manual Deploy Handle ................................................................................. 7-18 DC Electrical Power System ............................................................................................. 7-20 Description .................................................................................................................. 7-20 Components and Operation ........................................................................................ 7-22 Transformer-Rectifier Units (TRUs) ...................................................................... 7-22 TRU Power Distribution System............................................................................ 7-22 Battery Power Distribution System........................................................................ 7-24 External DC Electrical Power ................................................................................ 7-25 Circuit Breakers........................................................................................................... 7-27 Description ............................................................................................................ 7-27 Controls and Indicators ..................................................................................................... 7-30 AC Electrical Power .................................................................................................... 7-30 Air-Driven Generator (ADG)........................................................................................ 7-31 DC Electrical Power .................................................................................................... 7-32 Circuit Breaker Panels ................................................................................................ 7-33 EICAS Synoptic Pages ............................................................................................... 7-37 AC Synoptic Page ................................................................................................. 7-37 DC Synoptic Page................................................................................................. 7-44 EICAS Messages ........................................................................................................ 7-50 For Training Purposes Only May 03 7-i ELECTRICAL PILOT TRAINING GUIDE Page Intentionally Left Blank 7-ii For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE List of Figures Graphic Title Figure AC Electrical Power Sources .............................................................................................. 7-1 DC Electrical Power Sources .............................................................................................. 7-2 AC Electrical System .......................................................................................................... 7-3 GEN 1 and GEN 2 Power ................................................................................................... 7-4 APU Power ......................................................................................................................... 7-5 External AC Receptacle...................................................................................................... 7-6 External AC Electrical Power .............................................................................................. 7-7 EICAS AC Electrical Synoptic Page ................................................................................... 7-8 AC BUS Automatic Transfer ............................................................................................... 7-9 AC Essential Bus on Alternate Source ............................................................................. 7-10 AC Utility Bus Shedding.................................................................................................... 7-11 Air-Driven Generator (Wet ADG Shown) .......................................................................... 7-12 ADG Manual Deploy Handle and ADG Auto Deploy Control Panel.................................. 7-13 ADG Operation ................................................................................................................. 7-14 DC System Schematic ...................................................................................................... 7-15 EICAS DC Electrical Synoptic Page ................................................................................. 7-16 TRU 1 Failed and MAIN BUS TIE Closed......................................................................... 7-17 External DC Receptacle.................................................................................................... 7-18 External DC Power Connected ......................................................................................... 7-19 Circuit Breaker Panels (CBPs).......................................................................................... 7-20 Circuit Breaker Grid System ............................................................................................. 7-21 ELECTRICAL POWER Panel ........................................................................................... 7-22 Air-Driven Generator (ADG).............................................................................................. 7-23 ELECTRICAL POWER Panel ........................................................................................... 7-24 Circuit Breaker Panel 1 ..................................................................................................... 7-25 Circuit Breaker Panel 2 ..................................................................................................... 7-26 Circuit Breaker Panels 3 & 4............................................................................................. 7-27 Circuit Breaker Panel 5 ..................................................................................................... 7-28 AC Synoptic Page Color Coding - Integrated Drive Generators (1 of 2)........................... 7-29 AC Synoptic Page Color Coding - Integrated Drive Generators (2 of 2)........................... 7-30 AC Synoptic Page Color Coding - APU Generator (1 of 2)............................................... 7-31 AC Synoptic Page Color Coding - APU Generator (2 of 2)............................................... 7-32 AC Synoptic Page Color Coding - AC Electrical Power Distribution ................................. 7-33 AC Synoptic Page Color Coding - External AC Electrical Power...................................... 7-34 For Training Purposes Only May 03 7-iii ELECTRICAL PILOT TRAINING GUIDE AC Synoptic Page Color Coding - Air-Driven Generator .................................................. 7-35 DC Synoptic Page - TRU Power Distribution System (1 of 2) .......................................... 7-36 DC Synoptic Page - TRU Power Distribution System (2 of 2) .......................................... 7-37 DC Synoptic Page - Battery Power Distribution System (1 of 2) ...................................... 7-38 DC Synoptic Page - Battery Power Distribution System (2 of 2) ...................................... 7-39 DC Synoptic Page - DC Electrical Power Distribution (1 of 2) .......................................... 7-40 DC Synoptic Page - DC Electrical Power Distribution (2 of 2) .......................................... 7-41 7-iv For Training Purposes Only May 03 PILOT TRAINING GUIDE ELECTRICAL CHAPTER 7: ELECTRICAL Introduction The Challenger 604 primarily uses 115-volt AC power and also 28-volt DC electrical power. Engine-driven integrated drive generators (IDGs) supply the primary source of AC electrical power. A generator mounted on the Auxiliary Power Unit (APU) provides an alternate source of AC electrical power. In flight, if a total loss of AC power occurs, the air-driven generator (ADG) is deployed from the right side of the forward fuselage to provide an emergency source of AC electrical power. External AC electrical power is supplied through an electrical power receptacle located on the right side of the forward fuselage. Various aircraft systems and components require DC electrical power for operation. DC electrical power needs are primarily supplied by four Transformer Rectifier Units (TRU) mounted in the nose compartment. Two nickel-cadmium (NiCad) batteries, located in the aft equipment bay, store and provide a source of DC electrical power for normal and emergency operations. The aircraft is capable of accepting 28-volt DC external electrical power through a DC power receptacle installed on the rear fuselage below the right engine. Five circuit breaker panels provide power distribution. Four circuit breaker panels are located in the flight compartment and the fifth panel is in the aft equipment bay. Control and operation are accomplished through the ELECTRICAL POWER Panel located on the left side of the overhead panel. AC and DC electrical system information is provided on the EICAS. For Training Purposes Only May 03 7-1 ELECTRICAL PILOT TRAINING GUIDE APU Generator Generator 1 P604_07_001 Generator 2 External Power Air-Driven Generator (ADG) AC Electrical Power Sources Figure 7-1 APU Battery Charger External Power Main Battery Charger APU Battery Transformer Rectifier Units P604_07_004 Main Battery DC Electrical Power Sources Figure 7-2 7-2 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE Alternating Current (AC) System Description Three AC generators provide AC power for the aircraft electrical systems. Two engine-driven generators power all AC buses during normal operations. An APU generator provides a source of AC electrical power when the aircraft is on the ground with the engines off, and during flight if both engine-driven generators become inoperative. ADG GCU ADG GEN AC ESS BUS AC UTILITY BUS 1 ADG BUS UTILITY BUS CONTACTOR 1 AC ESS BUS TX CONTACTOR UTILITY BUS CONTACTOR 2 EMERG AC TX CONTACTOR AC BUS 1 AC BUS 2 EXT PWR MON EXT. AC ENG. 1 GEN 1 GTC2 APU GCU APU GEN APU GCU 1 GLC2 GCU 2 P604_07_002 GTC1 GLC1 AC UTILITY BUS 2 GEN 2 ENG. 2 NOTE: This schematic only displays AC power sources. Disregard the position of the GLCs and Generator Transfer Contactors (GTCs). AC Electrical System Figure 7-3 For Training Purposes Only May 03 7-3 ELECTRICAL PILOT TRAINING GUIDE Components and Operation Integrated Drive Generators (IDGs) Two engine-driven IDGs supply 115-volt AC, 400-Hz, three-phase electrical power to the AC buses. The IDG consists of two subcomponents, a constant speed drive and an electrical generator. The generators are identified on the EICAS AC Electrical Synoptic page by the symbols GEN 1 and GEN 2 (see Figure 7-4). The nominal rating of each generator is 30 kilovolt-amperes (kVA) to an altitude of 35,000 feet MSL, then 25 kVA to 41,000 feet MSL. In the event of a single generator failure, the remaining generator is capable of supplying sufficient power for operation of the main systems. The generators are controlled by two-position GEN 1 or GEN 2 switches located on the ELECTRICAL POWER Panel. Selecting GEN 1 or GEN 2 switch to ON connects the respective generator to the main AC buses provided they are operating normally. Selecting the switches to OFF/RESET will disconnect the respective generator from the main AC buses. The OFF/RESET position can also be used to reset the generator control circuit when a fault occurs. Generator Control Unit Each IDG is controlled and monitored by its respective generator control unit (GCU). The GCUs provide protection and bus priority logic during normal and non-normal operations. The engine generator is tripped off and removed from the AC buses if any of the following conditions occur: • • • 7-4 over- and undervoltage over- and underfrequency generator and bus overcurrent For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE ELECTRICAL POWER BATT MASTER EXT. POWER AVAIL OFF IN USE IN USE AC DC ON AC POWER GEN 1 APU GEN OFF/ RESET ON GEN 2 OFF/ RESET ON FAIL OFF/ RESET ON FAIL AUTOXFER OFF OFF DC POWER ESS. POWER ALTN CLOSED AC ESS XFER MAIN BUS TIE AC ELECTRICAL UTIL BUS 1 UTIL BUS 2 BUS 1 BUS 2 4 KVA 115 V 400 HZ GEN 1 0 KVA 0V 0 HZ GEN 4 KVA 115 V 400 HZ GEN 2 APU P604_07_028 ESS BUS GEN 1 and GEN 2 Power Figure 7-4 For Training Purposes Only May 03 7-5 ELECTRICAL PILOT TRAINING GUIDE APU Generator The APU generator supplies 115-volt AC, 400-Hz, three-phase electrical power to the AC buses during ground operations with the engines off. The APU generator may also be used in flight as a backup power source to the AC buses following a failure of both engine generators. The APU generator is mounted on the APU generator adapter and is driven at a constant speed, maintaining its frequency output at 400 Hz. The APU generator is identified on the AC Electrical Synoptic page by the symbol GEN above the APU icon (see Figure 7-5). The nominal rating of the APU generator is 30 kVA from sea level up to the APU’s maximum operating altitude of 20,000 feet MSL. The two-position APU GEN switch located on the ELECTRICAL POWER Panel controls the APU generator. Selecting the APU GEN switch to ON connects the APU generator to the main AC buses, providing it is operating normally. Selecting the switch to OFF/RESET disconnects the APU generator from the main AC buses. The OFF/RESET position can also be used to reset the generator control circuit when a fault occurs. NOTE Use of the APU generator in flight is not permitted unless both main generators have failed or are off-line. Generator Control Unit The APU generator is controlled and monitored by the APU generator control unit (GCU). The APU GCU in conjunction with the engine GCUs provide protection and bus priority logic during normal and non-normal operations. The APU GENERATOR is tripped off and removed from the AC buses if any of the following conditions occur: • • • 7-6 over- and undervoltage over- and underfrequency generator and bus overcurrent For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE ELECTRICAL POWER BATT MASTER EXT. POWER AVAIL OFF IN USE IN USE AC DC ON AC POWER GEN 1 APU GEN OFF/ RESET ON GEN 2 OFF/ RESET ON FAIL OFF/ RESET ON FAIL AUTOXFER OFF OFF DC POWER ESS. POWER ALTN CLOSED AC ESS XFER MAIN BUS TIE AC ELECTRICAL UTIL BUS 1 UTIL BUS 2 BUS 1 BUS 2 0 KVA 0V 0 HZ GEN 1 6 KVA 113 V 400 HZ GEN APU 0 KVA 0V 0 HZ GEN 2 P604_07_029 ESS BUS APU Power Figure 7-5 For Training Purposes Only May 03 7-7 ELECTRICAL PILOT TRAINING GUIDE External AC Electrical Power Description P604_07_055 The aircraft is capable of being powered by an external AC power source when both engines and APU are off. External AC electrical is connected at a receptacle located on the forward right side of the fuselage. External AC Receptacle Figure 7-6 Operation External AC ground power is controlled by the EXT POWER switch/light located on the ELECTRICAL POWER Panel. When connected, the external AC ground power is checked by an external power monitor for proper voltage, frequency, and phase. When the external power is within limits, the green AVAIL annunciator on the EXT POWER switch/light illuminates (see Figure 7-7). When the EXT POWER switch/light is pressed with the AVAIL annunciator illuminated, external AC electrical power is connected to the aircraft main AC buses via the auxiliary power/external power contactor (AP/EPC). External AC ground power is identified on the AC Electrical Synoptic page by the symbol EXT AC. This symbol appears only if external AC power is connected to the aircraft (see Figure 7-7). 7-8 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE AC ELECTRICAL ELECTRICAL POWER BATT MASTER EXT. POWER AVAIL OFF IN USE IN USE AC DC ON UTIL BUS 1 UTIL BUS 2 AC POWER APU GEN OFF/ RESET ON GEN 2 OFF/ RESET ON BUS 1 BUS 2 ESS BUS OFF/ RESET ON FAIL 116 V 400 HZ FAIL AUTOXFER OFF OFF EXT AC DC POWER ESS. POWER ALTN CLOSED AC ESS XFER MAIN BUS TIE 0 KVA 0V 0 HZ 0 KVA 0V 0 HZ 0 KVA 0V 0 HZ GEN 1 GEN GEN 2 APU P604_07_030 GEN 1 EXTERNAL AC POWER CONNECTED TO AIRCRAFT AC ELECTRICAL ELECTRICAL POWER BATT MASTER EXT. POWER AVAIL OFF ON IN USE IN USE AC DC UTIL BUS 1 UTIL BUS 2 AC POWER APU GEN OFF/ RESET ON GEN 2 OFF/ RESET ON FAIL BUS 1 OFF/ RESET ON BUS 2 ESS BUS 116 V 400 HZ FAIL AUTOXFER OFF ESS. POWER OFF EXT AC DC POWER ALTN CLOSED AC ESS XFER MAIN BUS TIE 0 KVA 0V 0 HZ 0 KVA 0V 0 HZ 0 KVA 0V 0 HZ GEN 1 GEN GEN 2 APU P604_07_031 GEN 1 EXTERNAL AC POWER SUPPLYING MAIN AC BUSES External AC Electrical Power Figure 7-7 For Training Purposes Only May 03 7-9 ELECTRICAL PILOT TRAINING GUIDE AC Electrical Power Distribution Description 115-volt AC electrical power from the aircraft generators and APU generator is distributed to five AC buses through circuit breaker panels. Monitoring of system status is done using the EICAS AC Electrical Synoptic page. The aircraft AC bus system consists of the following five buses: • • • • • AC BUS 1 (Main) AC BUS 2 (Main) AC ESS BUS (Essential) AC UTILITY BUS 1 AC UTILITY BUS 2 AC ELECTRICAL AC UTILITY BUS 1 AC UTILITY BUS 2 UTIL BUS 1 UTIL BUS 2 AC BUS 1 (Main) AC BUS 2 (Main) BUS 1 BUS 2 ESS BUS 4 KVA 115 V 400 HZ GEN 1 0 KVA 0V 0 HZ GEN 4 KVA 115 V 400 HZ GEN 2 APU P604_07_032 AC ESS BUS (Essential) EICAS AC Electrical Synoptic Page Figure 7-8 7-10 For Training Purposes Only May 03 PILOT TRAINING GUIDE ELECTRICAL Components and Operation AC BUS 1 and AC BUS 2 AC BUS 1 and AC BUS 2 are the main AC buses of the aircraft, and receive power from any of the three generators or from external AC power. AC BUS 1 normally supplies power to the AC ESS BUS and AC UTIL BUS 1. AC BUS 2 normally powers AC UTIL BUS 2. Bus Priority AC BUS 1 and AC BUS 2 are protected by a bus priority logic to ensure that the buses remain powered at all times. The generator control units (GCUs) determine the bus priority logic for AC BUS 1 and AC BUS 2 via the generator line contactors (GLCs) and generator transfer contactors (GTCs). The bus priority logic for AC BUS 1 and AC BUS 2 is as follows: • • • • on-side engine-driven generator (example: AC BUS 1 powered by GEN 1) APU generator cross-side engine-driven generator (example: AC BUS 1 powered by GEN 2) external AC Power According to the above priority logic, the GLCs and GTCs will automatically tie the main AC buses to any of the available AC power sources, to ensure the main AC buses remain powered at all times. AC BUS 1(2) Automatic Transfer (AUTOXFER) Switch/Lights The flight crew may manually inhibit the automatic bus transfer priority logic by pressing the appropriate AUTOXFER switch/light located on the ELECTRICAL POWER Panel. This prevents the corresponding AC BUS from being powered by any source except its on-side engine-driven generator. This may be used to isolate a main AC bus in the event of an electrical emergency (example: electrical smoke or fire). Selection of the AUTOXFER switch/light is indicated by illumination of the corresponding white OFF annunciator on the switch/light and the white AUTO XFER OFF icon on the AC Electrical Synoptic page (see Figure 7-9). Should a bus fault or generator overcurrent condition occur on a main AC bus, the automatic bus transfer priority logic will be inhibited, isolating the fault from the remaining AC electrical system. This condition is indicated by the AC 1(2) AUTOXFER caution EICAS message, illumination of the corresponding amber FAIL annunciator on the AUTOXFER switch/light, and the amber AUTO XFER FAIL icon on the AC Synoptic page (see Figure 7-9). For Training Purposes Only Jan 04 7-11 ELECTRICAL PILOT TRAINING GUIDE AC ELECTRICAL ELECTRICAL POWER BATT MASTER EXT. POWER AVAIL OFF IN USE IN USE AC DC ON UTIL BUS 1 UTIL BUS 2 AC POWER APU GEN OFF/ RESET ON BUS 1 GEN 2 OFF/ RESET ON BUS 2 ESS BUS OFF/ RESET ON FAIL AUTO XFER OFF FAIL AUTOXFER OFF OFF DC POWER ESS. POWER ALTN CLOSED AC ESS XFER MAIN BUS TIE 4 KVA 115 V 400 HZ 0 KVA 0V 0 HZ GEN 1 4 KVA 115 V 400 HZ GEN 2 GEN APU P604_07_033 GEN 1 AC BUS 2 AUTOXFER SWITCH/LIGHT SELECTED OFF AC ELECTRICAL ELECTRICAL POWER BATT MASTER EXT. POWER AVAIL OFF ON IN USE IN USE AC DC UTIL BUS 1 SHED UTIL BUS 2 AC POWER APU GEN OFF/ RESET ON FAIL BUS 1 GEN 2 OFF/ RESET ON BUS 2 ESS BUS OFF/ RESET ON AUTO XFER FAIL FAIL AUTOXFER OFF ESS. POWER OFF DC POWER ALTN CLOSED AC ESS XFER MAIN BUS TIE 4 KVA 115 V 400 HZ GEN 1 0 KVA 0V 0 HZ 0 KVA 0V 0 HZ GEN GEN 2 APU P604_07_034 GEN 1 AC BUS 2 AUTOMATIC TRANSFER FAILURE AC BUS Automatic Transfer Figure 7-9 7-12 For Training Purposes Only Jan 04 ELECTRICAL PILOT TRAINING GUIDE AC ESS (Essential) Bus The AC ESS BUS supplies power to the equipment essential for flight. It is normally powered by AC BUS 1, but may also be powered by AC BUS 2 or the ADG BUS. The AC ESS BUS supplies power to ESS TRU 1, which provides DC power to the DC ESS BUS and the BATT BUS. Refer to the ADG section in this chapter for information on the ADG BUS. AC ESS Bus Transfer If a loss of power on AC BUS 1 is sensed, the AC ESS BUS is automatically transferred to AC BUS 2. When an automatic transfer to AC BUS 2 occurs, the AC ESS XFER switch/light located on the ELECTRICAL POWER Panel illuminates and the AC ESS ALTN status EICAS message appears (see Figure 7-10). If the automatic transfer fails to occur, the AC ESS BUS can be manually transferred to AC BUS 2 by pressing the AC ESS XFER switch/light. AC ELECTRICAL ELECTRICAL POWER BATT MASTER EXT. POWER AVAIL OFF ON IN USE IN USE AC DC UTIL BUS 1 UTIL BUS 2 AC POWER APU GEN OFF/ RESET ON FAIL BUS 1 GEN 2 OFF/ RESET ON BUS 2 ESS BUS OFF/ RESET ON AUTO XFER FAIL FAIL AUTOXFER OFF ESS. POWER OFF DC POWER ALTN CLOSED AC ESS XFER MAIN BUS TIE 2 KVA 115 V 400 HZ GEN 1 0 KVA 0V 0 HZ GEN APU 4 KVA 115 V 400 HZ GEN 2 P604_07_035 GEN 1 AC Essential Bus on Alternate Source Figure 7-10 For Training Purposes Only May 03 7-13 ELECTRICAL PILOT TRAINING GUIDE AC Utility Buses AC UTILITY BUS 1 and 2 receive power from AC BUS 1 and 2 respectively. The AC utility buses supply AC power to nonessential cabin equipment. Utility Bus Shedding During single-generator operation in flight, AC UTILITY BUS 1 and 2 are automatically load shed to reduce the electrical load on the remaining generator. During ground operations, AC UTILITY BUS 1 and 2 are load shed when a single generator (or external AC power only) is supplying AC power and the flaps are not retracted. Load shedding of AC UTILITY BUS 1 and 2 is indicated by the appearance of AC UTIL 1(2) OFF status EICAS messages and the SHED icons on the AC Electrical Synoptic page (see Figure 7-11). AC ELECTRICAL UTIL BUS 1 SHED AC UTIL 2 OFF AC UTIL 1 OFF UTIL BUS 2 SHED BUS 1 EICAS SECONDARY DISPLAY BUS 2 ESS BUS 0 KVA 0V 0 HZ GEN 1 7 KVA 113 V 401 HZ GEN 0 KVA 0V 0 HZ GEN 2 APU P604_07_036 AUTO XFER FAIL AC Utility Bus Shedding Figure 7-11 7-14 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE Air-Driven Generator (ADG) Description The ADG provides 115-volt, 400-Hz, 15-kVA power to the AC ESS BUS and 3B hydraulic pump, in the event of a complete loss of AC power in flight. The ADG is located in the forward right fuselage beside the nose gear and is deployed automatically or manually. Once deployed, the ADG can only be restowed when the aircraft is on the ground (see Figure 7-12). Ejection Jack Assembly Manual Retraction Pump Assembly ADG Ground Safety Lockpin Air-Driven Generator Assembly AIR - DRIVEN WET GENERATOR (Aircraft 5301 to 5407) Ejection Jack Assembly Manual Restowable Pump Assembly Auto Release (Wet ADG - Squib Cartridge / Dry ADG - Solenoid) P604_07_003 Manual Release Air-Driven Generator Assembly AIR - DRIVEN DRY GENERATOR (Aircraft 5408 and subsequent) UPLOCK ASSEMBLY Air-Driven Generator (Wet ADG Shown) Figure 7-12 For Training Purposes Only Jan 04 7-15 ELECTRICAL PILOT TRAINING GUIDE Components and Operation Air-Driven Generator The ADG consists of an AC generator mounted on a pivoted support leg and a variable-pitch two-bladed propeller that turns in the airstream. There are two versions of the ADG. Airplanes 5301 to 5407 On airplanes 5301 to 5407, constant speed of the generator is achieved by hydraulically controlling the propeller pitch angle. This ADG is commonly referred to as the “wet ADG”. Wet ADG operation is airspeed-limited (refer to the Airplane Flight Manual Limitations). NOTE On landing with the wet ADG deployed, use gentle deceleration to prevent the ADG from swinging forward and contacting the fuselage. Airplane 5408 and Subsequent On airplanes 5408 and subsequent, the constant speed of the ADG is achieved by using a counterweight system to control the propeller pitch angle. This ADG is commonly referred to as the “dry ADG”. ADG Generator Control Unit The ADG generator is controlled and monitored by the ADG generator control unit (GCU). The ADG GCU provides the following functions: • • • 7-16 monitors and controls ADG voltage output protects against overvoltage, overfrequency and underfrequency to the ADG BUS provides a signal to the ADG Auto Deploy Control Unit to energize the HYD PUMP 3B Transfer Contactor, Emergency AC Transfer Contactor, and Emergency DC Transfer Contactor when the ADG voltage and frequency are within limits For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE ADG AUTO DEPLOY CONTROL Unit Located on the lower center pedestal, the ADG AUTO DEPLOY CONTROL Unit controls the automatic deployment of the ADG. Automatic deployment of the ADG occurs when: • • both AC BUS 1 and AC BUS 2 become unpowered the aircraft is in flight Another ADG deployment prerequisite is that one of the three main generators must be on line prior to both AC main buses going off (this prevents the ADG from deploying during ground maintenance tests with external power being connected and disconnected with the aircraft on jacks. The red EMER PWR ONLY warning EICAS message appears to indicate loss of all normal electrical power and ADG deployment. When the ADG unit is fully extended, the two-blade propeller is unlocked and rotates in the airstream. Once the ADG voltage and frequency are within normal limits, the AUTO DEPLOY CONTROL Unit energizes the appropriate transfer contactors, and allows the ADG to provide power to the AC ESS BUS and to hydraulic pump 3B via the ADG BUS. Airplanes 5301 to 5407 On airplanes 5301 to 5407, the ADG AUTO DEPLOY CONTROL Unit deploys the ADG by sending an electrical signal to fire the squib cartridge in the ADG uplock mechanism. Airplane 5408 and Subsequent On airplanes 5408 and subsequent, the ADG AUTO DEPLOY CONTROL Unit sends a signal to release the solenoid of the ADG uplock mechanism. LAMP TEST PWR TXFR OVERRIDE ADG AUTO DEPLOY CONTROL P604_07_041 ADG UNIT ADG Manual Deploy Handle and ADG AUTO DEPLOY CONTROL Panel Figure 7-13 For Training Purposes Only May 03 7-17 ELECTRICAL PILOT TRAINING GUIDE PWR TXFR OVERRIDE With the ADG deployed, it may be possible to restore normal AC electrical power by resetting an engine-driven generator or by using the APU generator. If AC electrical power is restored, the PWR TXFR OVERRIDE switch (see Figure 7-13) should be selected to reset the three transfer contactors and regain normal AC distribution. This returns the AC ESS BUS to AC BUS 1 and the 3B hydraulic pump to normal operation. NOTE The ADG Manual Deploy Handle must be stowed to allow the transfer contactors to reset. ADG LAMP / UNIT Switch The ADG Auto Deploy Control Unit may be tested using the two-position ADG LAMP / UNIT switch located on the ADG AUTO DEPLOY CONTROL Panel. Selecting the switch to the UNIT position tests the continuity of the uplock circuit, the three transfer contactors, and the ADG AUTO DEPLOY CONTROL Unit internal logic circuitry. Both engine generators must be operating and AC BUS 1 and AC BUS 2 must be powered to ensure a proper test. Selecting the switch to the LAMP position checks the serviceability of the green TEST lamp only. ADG Manual Deploy Handle In the event of an auto-deploy failure, the ADG can be manually deployed using the ADG Manual Deploy Handle located on the lower center pedestal. Pulling the handle manually releases the uplock that allows the ADG to deploy. In addition, the Emergency AC Transfer Contactor and Emergency DC Transfer Contactor are energized immediately. In the event the ADG fails, operating the ADG Manual Deploy Handle enables the DC ESS BUS to be supplied by the BATT BUS through the Emergency DC Transfer Contactor. NOTE If the ADG is not operating properly and the airplane is on battery power only, then all electrical power may be lost after 30 minutes. Hydraulic pump 3B will be inoperative when on battery power. 7-18 For Training Purposes Only Jan 04 ELECTRICAL PILOT TRAINING GUIDE Manual deployment of the ADG handle is also required for landing when the ADG is the only source of AC electrical power. This ensures that the DC ESS BUS remains powered by the BATT BUS throughout the landing rollout, when the ADG is no longer capable of generating AC power. AC ELECTRICAL AC ELECTRICAL UTIL BUS 1 UTIL BUS 2 BUS 1 UTIL BUS 1 BUS 2 4 KVA 115 V 400 HZ GEN 2 GEN 0 KVA 0V 0 HZ 0 KVA 0V 0 HZ GEN 1 GEN GEN 2 APU 1. NORMAL OPERATION 2. EMER PWR ONLY – ADG DEPLOYED AC ELECTRICAL AC ELECTRICAL ADG BUS 1 UTIL BUS 2 SHED UTIL BUS 1 SHED BUS 2 115 V 400 HZ BUS 1 ESS BUS ADG UTIL BUS 2 SHED BUS 2 ESS BUS AUTO XFER FAIL 0 KVA 0V 0 HZ 9 KVA 113 V 400 HZ GEN 1 GEN AUTO XFER FAIL 0 KVA 0V 0 HZ 0 KVA 0V 0 HZ GEN 2 GEN 1 10 KVA 113 V 400 HZ GEN APU APU 3. APU GEN SELECTED ON 0 KVA 0V 0 HZ GEN 2 P604_07_037 115 V 400 HZ BUS 2 0 KVA 0V 0 HZ APU UTIL BUS 1 SHED UTIL BUS 2 ESS BUS 0 KVA 0V 0 HZ GEN 1 ADG BUS 1 ESS BUS 4 KVA 115 V 400 HZ 115 V 400 HZ 4. PWR TXFR OVERRIDE PRESSED ADG Operation Figure 7-14 For Training Purposes Only May 03 7-19 ELECTRICAL PILOT TRAINING GUIDE DC Electrical Power System Description Four transformer-rectifier units (TRUs), two NiCad batteries and an external DC power receptacle supply direct current (DC) power to the DC buses. The TRUs carry the majority of the DC electrical loads and the batteries provide emergency power inflight and allow the APU to be started on the ground. DC power is distributed to the DC buses directly from the TRUs or batteries, and from various contactors which provide alternate sources of power. Electrical power is supplied to the buses through the circuit breaker panels. AC ESS BUS AC BUS 2 AC BUS 1 TRU 2 TRU 1 ESS TRU 2 ESS TRU 1 DC ESS BUS DC BUS 1 DC BUS 2 DC ESS SOLID-STATE CONTACTOR DC UTILITY BUS 1 DC TIE RELAY 1 EMERGENCY DC TX CONTACTOR FROM ADG BATT BUS DC UTILITY BUS 2 APU BATT SOLID-STATE CONTACTOR DC TIE RELAY 2 APU BATT DIR BUS EXTERNAL DC CONTACTOR MAIN BATT SOLID STATE CONTACTOR MAIN BATT DIR BUS EMERGENCY BUS APU BATT MAIN BATT APU BATT CHGR MAIN BATT CHGR P604_07_005 EXT DC NOTE: This schematic only displays DC power sources. Disregard the positions of all contactors and ties. DC System Schematic Figure 7-15 7-20 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE Monitoring of system status is done using the EICAS DC Electrical Synoptic page. The aircraft DC bus system consists of the following nine buses: • • • • • • • • • DC BUS 1 DC BUS 2 DC ESS (Essential) BUS DC EMER (Emergency) BUS BATT (Battery) BUS DC UTIL (Utility) BUS 1 DC UTIL (Utility) BUS 2 MAIN BATTERY DIRECT BUS APU BATTERY DIRECT BUS DC ELECTRICAL AC BUS 1 DC BUS 1 DC BUS 2 AC BUS 2 TRU 1 TRU 2 28 V 8 A 28 V 13 A AC ESS BUS ESS TRU 2 28 V 24 A ESS TRU 1 28 V 24 A DC ESS (Essential) BUS BUS 1 ESS BUS BATT (Battery) BUS BUS 2 BATT BUS APU BATTERY DIRECT BUS TIE APU BATT DIR BUS DC UTIL (Utility) BUS 1 DC UTIL (Utility) BUS 2 EMER BUS MAIN BATTERY DIRECT BUS MAIN BATT DIR BUS UTIL BUS 2 EXT DC 28 V 19 A APU BATT 27 V 0 A MAIN BATT 26 V 0 A P604_07_038 UTIL BUS 1 DC EMER (Emergency) BUS EICAS DC Electrical Synoptic Page Figure 7-16 For Training Purposes Only May 03 7-21 ELECTRICAL PILOT TRAINING GUIDE Components and Operation Transformer-Rectifier Units (TRUs) The normal sources of 28-volt DC electrical power for the DC system are the four TRUs. Each TRU converts 115-volt AC to 28-volt DC and supplies it to its respective DC buses. Each TRU is rated at 100 amps. The four TRUs are identified as: • • • • TRU 1 TRU 2 ESS (Essential) TRU 1 ESS (Essential) TRU 2 The TRUs supply the following buses: • • • • TRU 1 normally supplies DC BUS 1 and DC UTIL BUS 1 TRU 2 normally supplies DC BUS 2 and DC UTIL BUS 2 ESS TRU 1 normally supplies DC ESS BUS and DC BATT BUS ESS TRU 2 normally supplies DC ESS BUS and DC BATT BUS TRU Power Distribution System The TRU Power Distribution System supplies the following buses: DC BUS 1 and DC BUS 2 DC BUS 1 is supplied by TRU 1 and DC BUS 2 is supplied by TRU 2. If either TRU fails, both buses can be supplied by either TRU by selecting the MAIN BUS TIE switch/light on the ELECTRICAL POWER Panel (see Figure 7-17). DC ESS BUS The DC ESS BUS powers equipment essential for safe flight, and therefore, may be supplied by numerous DC sources to ensure redundancy of its power supply. Normally, ESS TRU 1 and ESS TRU 2 power the DC ESS BUS. In the event of a single ESS TRU failure, either ESS TRU is capable of sustaining the DC ESS BUS load. Should both ESS TRUs fail with the aircraft in flight, the APU BATT DIR BUS through the DC ESS solid-state contactor will power the DC ESS BUS. During ADG operation, the AC ESS BUS powers ESS TRU 1 which in turn powers the DC ESS BUS. The DC ESS BUS can also be powered by the APU and Main batteries through the Emergency DC Transfer Contactor. Refer to the ADG section of this chapter for additional information. 7-22 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE DC ELECTRICAL ELECTRICAL POWER BATT MASTER AC BUS 1 EXT. POWER AVAIL OFF ON IN USE TRU 1 TRU 2 IN USE AC DC –– V 0 A 28 V 20 A AC POWER APU GEN OFF/ RESET ON OFF/ RESET ON FAIL AUTOXFER OFF ESS. POWER ESS TRU 2 28 V 24 A ESS TRU 1 28 V 24 A GEN 2 OFF/ RESET ON FAIL AC ESS BUS BUS 1 ESS BUS BUS 2 BATT BUS TIE OFF APU BATT DIR BUS DC POWER UTIL BUS 1 ALTN CLOSED AC ESS XFER MAIN BUS TIE EMER BUS MAIN BATT DIR BUS UTIL BUS 2 EXT DC 28 V 19 A APU BATT 27 V 0 A MAIN BATT 26 V 0 A P604_07_039 GEN 1 AC BUS 2 TRU 1 Failed and MAIN BUS TIE Closed Figure 7-17 BATT BUS The BATT BUS powers equipment essential for safe flight, and may be supplied by several DC sources to ensure redundancy. Normally, ESS TRU 1 and ESS TRU 2 power the BATT BUS when the main AC buses are powered. If the ESS TRUs are not operating (no AC power or ESS TRU failures), the BATT BUS will be powered by the APU BATT DIR BUS and MAIN BATT DIR BUS provided the BATT MASTER Switch is selected ON. The BATT MASTER Switch located on the ELECTRICAL POWER Panel controls the APU BATT and MAIN BATT contactors to supply the BATT BUS, as described above. The BATT BUS also supplies the DC EMER BUS. For Training Purposes Only May 03 7-23 ELECTRICAL PILOT TRAINING GUIDE DC UTIL BUS 1 and DC UTIL BUS 2 The DC UTIL buses supply power to nonessential cabin equipment. TRU 1 and TRU 2 power DC UTILITY BUS 1 and 2 respectively. Whenever the MAIN BUS TIE switch/light is selected following a TRU 1 or 2 failure, the DC UTIL buses are load shed to reduce the DC electrical load. Battery Power Distribution System The Battery Power Distribution System represents a small portion of the aircraft’s total DC load. The batteries primarily provide the energy needed to start the APU, which can then be used to supply AC power to the aircraft. The batteries also supply emergency DC power in-flight should all AC power be lost and the ADG become inoperative. Two rechargeable nickel-cadmium (NiCad) batteries are installed in the aft equipment bay. The main battery is a 24-volt, 17-amp/hour battery. The APU battery is a 24-volt, 43-amp/hour battery. The batteries supply DC electrical power to the following buses: • • • • MAIN BATT DIR BUS APU BATT DIR BUS DC EMER BUS BATT BUS Battery Charging The main battery charger and APU battery charger are in a charging configuration at all times when the applicable main AC buses are powered: • • AC BUS 1 for Main Battery Charger AC BUS 2 for APU Battery Charger The battery chargers operate automatically in various modes based on battery temperatures. Should a battery or battery charger fault be detected, the respective battery charger will shut down. A MAIN (APU) BATT CHGR FAIL status EICAS message will appear and the CHGR OFF icon will be displayed on the DC Electrical Synoptic page to indicate a failure. 7-24 For Training Purposes Only Jan 04 ELECTRICAL PILOT TRAINING GUIDE MAIN and APU BATT DIR BUSES These DC buses are continuously powered from the associated battery, regardless of the BATT MASTER switch position. The main battery is connected to the MAIN BATT DIR BUS and the APU battery is connected to the APU BATT DIR BUS. These buses provide power to the aircraft systems which primarily relate to ground service operation (refueling, service lights, etc.). The APU BATT DIR BUS also supplies the DC EMER BUS. DC Emergency Bus The DC EMER BUS provides power to the engine and APU fire extinguishers and the fuel and hydraulic shutoff valves. The bus is connected to the APU BATT DIR BUS and the BATT BUS and is continuously powered. BATT BUS Refer to the TRU distribution section of this chapter. External DC Electrical Power P604_07_056 External DC ground power may be used to start the APU if the APU battery charge is low. The External DC receptacle is located at the rear of the aircraft near the right engine pylon (see Figure 7-18). External DC Receptacle Figure 7-18 For Training Purposes Only May 03 7-25 ELECTRICAL PILOT TRAINING GUIDE When connected, external DC ground power automatically supplies the APU BATT DIR BUS through the External DC contactor, and the BATT BUS when the BATT MASTER switch is selected ON. The DC EXTERNAL POWER white IN USE light on the ELECTRICAL POWER panel illuminates whenever DC external power is connected. External DC ground power is identified on the DC Electrical Synoptic page by the symbol EXT DC. This symbol appears only if DC external power is connected to the aircraft. DC ELECTRICAL ELECTRICAL POWER BATT MASTER AC BUS 1 EXT. POWER AVAIL OFF ON IN USE IN USE AC DC AC POWER APU GEN OFF/ RESET ON TRU 2 0 V 0 A 0 V 0 A OFF/ RESET ON FAIL AUTOXFER OFF ESS. POWER ESS TRU 2 0 V 0 A ESS TRU 1 0 V 0 A GEN 2 OFF/ RESET ON FAIL TRU 1 AC ESS BUS BUS 1 ESS BUS BUS 2 BATT BUS TIE OFF APU BATT DIR BUS DC POWER UTIL BUS 1 ALTN CLOSED AC ESS XFER MAIN BUS TIE EMER BUS MAIN BATT DIR BUS UTIL BUS 2 EXT DC 28 V 19 A APU BATT 27 V 0 A MAIN BATT 24 V 18 A P604_07_040 GEN 1 AC BUS 2 External DC Power Connected Figure 7-19 7-26 For Training Purposes Only Jan 04 ELECTRICAL PILOT TRAINING GUIDE Circuit Breakers Description Electrical power distribution is accomplished through five circuit breaker panels. Four circuit breaker panels are installed in the flight deck and the fifth panel is in the aft equipment bay. They are identified as follows (see Figure 7-20): • • • • • Circuit Breaker Panel 1 (CBP-1) Circuit Breaker Panel 2 (CBP-2) Circuit Breaker Panel 3 (CBP-3) Circuit Breaker Panel 4 (CBP-4) Circuit Breaker Panel 5 (CBP-5) Electrical equipment protection is provided by conventional thermal circuit breakers. When a circuit breaker is tripped, a white collar is exposed. Depending on airplane completion specification, circuit breakers may also be located in other parts of the airplane. Should a circuit breaker trip while the airplane is in flight, the circuit breaker should be allowed to cool for as long as possible before resetting. NOTE Do not attempt more than one reset of a circuit breaker. For Training Purposes Only May 03 7-27 ELECTRICAL PILOT TRAINING GUIDE AC ESS BUS DC ESS BUS CBP-3 CBP-4 AC BUS 2 DC BUS 2 BATT BUS CBP-2 CBP-1 AC BUS 1 DC BUS 1 BATT BUS CBP-1 (LOWER) CBP-5 P604_07_011 MAIN BATT DIR BUS APU BATT DIR BUS EMERGENCY Circuit Breaker Panels (CBPS) Figure 7-20 7-28 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE Circuit Breaker Grid System A circuit breaker can be located, when called for in a procedure, by using the grid reference on the circuit breaker panel. For example, the “VOLTS & FREQ IND” circuit breaker location is identified as (3A13), and therefore found on panel CBP-3, row A, column 13 (see Figure 7-21). Circuit Breaker Panel Number Row Column CBP-3 115VAC ESS BUS ESS TRU 1 A 115VAC ADG BUS 10 1 2 25 7.5 3 4 L HTR WIND L PITOT 5 ESS HYD PUMP SUPPLY AC ESS FEED STAB CH 2 HSTA 6 7 8 VOLTS & FREQ IND 25 9 10 11 1 12 13 115VAC ESS BUS B/LEAK L R DET DET B HEATERS L PITOT AOA STBY O/H PNLS L STATIC 3 3 10 5 3 5 3 1 2 3 4 5 6 7 IRU 1 IRU FAN 1 FDR PWR 3 3 3 1 2 3 8 INTEG LTS CB PLT PNLS PNLS CTR PNLS 3 5 3 5 9 10 11 12 13 9 10 11 12 13 11 12 13 115VAC ESS BUS 5 4 5 ICE DET 1 3 6 7 8 26VAC ESS BUS D 1 2 3 115VAC ESS BUS SURF POS IND L 26 VAC ESS XFMR 2 2 4 5 6 7 8 9 10 P604_07_006 C ENG IGN A TCAS Circuit Breaker Grid System Figure 7-21 For Training Purposes Only May 03 7-29 ELECTRICAL PILOT TRAINING GUIDE Controls and Indicators The overhead ELECTRICAL POWER Panel and the Air-Driven Generator (ADG) panel provide the system controls. The EICAS (AC Electrical and DC Electrical) Synoptic pages provide a pictorial representation of system status. The EICAS Primary and Secondary pages provide system caution and advisory messages respectively. Circuit Breaker Panel (CBP) diagrams are also located in this section. AC Electrical Power External AC Power Switch/Light (alternate-action) Push – Connects external AC power to appropriate main AC BUS(s) when the AVAIL light is illuminated. AVAIL Light Illuminated – Indicates that external AC power is connected and operating within limits. IN USE Light Illuminated – Indicates external AC power is connected and supplying the appropriate main AC BUS(s). GEN 1 (2) Switch ON – Connects applicable generator to appropriate main AC BUS(s) provided it is operating normally. OFF/RESET ! Disconnects applicable generator from main AC BUS(s). ! Resets generator control circuit. ELECTRICAL POWER BATT MASTER EXT. POWER AVAIL OFF IN USE IN USE AC DC ON AC POWER GEN 1 APU GEN OFF/ RESET ON GEN 2 OFF/ RESET ON FAIL OFF/ RESET ON FAIL AUTOXFER OFF OFF ESS. POWER DC POWER ALTN CLOSED AC ESS XFER MAIN BUS TIE AC ESS XFER Switch/Light (alternate-action) Push – Manually transfers source of power for AC ESS BUS from AC BUS 1 to AC BUS 2. ALTN Light Illuminated – Indicates AC ESS BUS is being supplied from AC BUS 2. P604_07_025 APU GEN Switch ON – Connects APU generator to appropriate main AC BUS(s) provided it is operating normally. OFF/RESET ! Disconnects APU generator from main AC BUS(s). ! Resets generator control circuit. NOTE: The APU GEN generator may not be selected ON in flight, unless both GEN 1 and GEN 2 are off-line or failed. AC AUTOXFER Switch/Lights (alternate-action) Push – Disables automatic bus tie operation for corresponding main AC BUS (left AC BUS 1, right AC BUS 2). OFF Light Illuminated – Indicates automatic bus tie operation has been manually disabled. FAIL Light Illuminated – Indicates automatic bus tie operation has been automatically disabled due to a bus fault or generator overcurrent condition. ELECTRICAL POWER Panel Figure 7-22 7-30 For Training Purposes Only Jan 04 ELECTRICAL PILOT TRAINING GUIDE Air-Driven Generator (ADG) ADG TEST LAMP During LAMP Test ! Illuminates steady. During UNIT Test ! On the ground, illuminates after 2 seconds for 2 seconds. ! In-flight, illuminates after 5 seconds for 2 seconds. LAMP TEST ADG UNIT PWR TXFR OVERRIDE ADG AUTO DEPLOY CONTROL PWR TXFR OVERRIDE Switch Push – De-energizes the Emergency AC Transfer Contactor, Emergency DC Transfer Contactor and Hydraulic Pump 3B Transfer Contactor if power is restored to the main AC buses. NOTE: ADG Manual Deploy Handle must be stowed for all transfer contactors to de-energize. P604_07_027 ADG Manual Deploy Handle Pull aft until latched: ! Manually releases ADG uplock mechanism to deploy the ADG. ! Immediately energizes the Emergency AC Transfer Contactor, Emergency DC Transfer Contactor and the Hydraulic Pump 3B Transfer Contactor. ADG LAMP-UNIT Test Switch LAMP – Tests the ADG TEST LAMP. UNIT: !Tests continuity of the ADG uplock release circuit and of the Emergency AC, DC and, Hydraulic Pump 3B Transfer Contactors. !Tests the auto-deploy control unit logic circuits. Air-Driven Generator (ADG) Figure 7-23 For Training Purposes Only May 03 7-31 ELECTRICAL PILOT TRAINING GUIDE DC Electrical Power BATT MASTER Switch ON – Connects the batteries (MAIN BATT DIR BUS and the APU BATT DIR BUS) to the BATT BUS. OFF – Disconnects the batteries from the BATT BUS. ELECTRICAL POWER BATT MASTER External DC Power Light Illuminated – Indicates external DC power is connected to the aircraft and is supplying the APU BATT DIR BUS. EXT. POWER AVAIL OFF ON IN USE IN USE AC DC AC POWER GEN 1 APU GEN OFF/ RESET ON GEN 2 OFF/ RESET ON FAIL OFF/ RESET ON FAIL AUTOXFER ESS. POWER OFF DC POWER ALTN CLOSED AC ESS XFER MAIN BUS TIE P604_07_026 OFF MAIN BUS TIE Switch/Light (alternate-action) Push – Ties DC BUS 1 and DC BUS 2 together. CLOSED Light Illuminated – Indicates that both DC BUS 1 and DC BUS 2 have been tied together. NOTE: Both DC utility buses are load shed whenever the switch/light indicates CLOSED. ELECTRICAL POWER Panel Figure 7-24 7-32 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE Circuit Breaker Panels POWER MUST BE OFF BEFORE OPENING PANEL CBP-1 115 VAC BUS 1 HEATERS L WSHLD TAT HYD PUMP A 3B 2B CKPT HTR 25 25 7.5 20 20 3 5 10 11 12 13 14 15 GPWS IRU 3 IRU 3 FAN TRU 1 FLAP MOTOR 1 9 8 7 115 VAC BUS 1 115VAC ESS FEED B 10 5 25 4 3 2 1 4 3 2 1 5 5 6 6 MAIN BATT CHGR C 7.5 3 2 1 5 4 115 VAC BUS 1 FUEL PUMP PRIM XFER DISP FAN 3 3 D 2 1 5 4 3 28 VDC UTILITY BUS 1 E 2 3 FEED 50 50 DISP WOW/ FLAP FAN GEAR/ CONT 1 CONT SPLR 1 GND SPLR RUD TRIM NOSE STEER 3 7.5 7.5 3 3 3 1 2 3 4 5 6 3 2 3 4 L LDU PRIM DISPL 3 10 10 7.5 7.5 7.5 3 4 5 6 7 8 SELCAL 3 2 6 7 8 28 VDC BUS 1 3 3 3 13 14 15 NAV LTS 3 10 5 LDG/TAXI LTS L L NOSE WING J 1 2 3 4 28 VDC BUS 1 L IAPS WEATHER RDR AFCS 2 R/T CONT 1 CONT 2 FMS 1 5 5 7.5 3 3 14 15 1 2 3 ECU APU FAULT START ANN CONT 7.5 7.5 3 7.5 15 14 13 28 VDC BUS 1 UTIL CKPT TEMP CONT BUS PWR TIE & TRU 1 UTIL SENSE CONT SENSE AUTO 1 2 3 50 3 5 12 13 12 11 115 VAC UTILITY BUS 1 GAL/LAV SUPPLY PWR LIGHT LINE HTRS SENSE LOGO 9 3 11 3 9 10 EICAS BRT/DIM PWR SUPP SEC DISPL 2 3 1 9 10 12 3 3 11 12 14 ST B/AIR SOV L 3 7 8 9 10 28 VDC BUS 1 FUEL FSCU DEFUEL PRIM FUEL SOV POS XFER CONT 3 11 3 7 8 9 10 28 VDC UTILITY BUS 1 A/ICE CKPT AUTO HTR ANTI 1 SKID CONT 3 5 3 10 9 8 DC BUS 1 CONTROL FEED 6 1 8 PWR SENSE HYD SYST AC PUMP IND CONT 2 2 H 7 7 5 1 3 6 4 G 3 3 3 1 F 6 10 9 8 7 115 VAC BUS 1 ADG PASS ENG WARN CKPT DEPLOY VIB MON SIGNS FAN SENSE AUX AOA 11 CHRT HLDR 13 14 14 ST B/AIR HTR ISOL CONT SOV L WSHLD 3 3 3 12 13 14 10 CPL 10 K 3 4 5 6 7 28 VDC BATTERY BUS 1 ENG IGN L OIL PRESS TRANS A B R L 3 7.5 7.5 6 7 8 28 VDC BATTERY BUS 9 10 3 4 5 ENG START 3 3 20 5 3 1 2 3 WOW/ GEAR/ SPLR 1 7.5 1 2 3 L FUEL L PUMP FSCU GRAV CONT L PUMP CH 1 XFLOW EMERG FMS 1 FMS BUS BACKUP CDU 1 FEED PWR 15 LIGHTS WING CKPT REAR INSP FLOOR A/COLL 7.5 HF COMM 1 TX/RX 4 5 6 7 8 28 VDC BATTERY BUS ENG JET FLAP STALL PROT PIPE OVHT TRIM STICK LH IND PUSH CH L R 7.5 3 4 5 3 3 3 20 3 3 9 10 11 12 FIRE DETECTORS L ENG APU TEST R ENG 3 3 3 3 3 6 7 8 28 VDC BATTERY BUS 9 10 11 12 DOME 1 GCU 2 3 ADC 2 STBY PA O/H PNLS STBY INSTR LIGHTS C/PLT MAP PLT MAP 3 5 3 3 3 3 3 10 11 12 3 5 3 5 7.5 7.5 7.5 11 12 13 14 1 2 3 GPS 1 DME 1 AFIS RAD ALT 1 4 M 5 6 7 8 9 28 VDC BATTERY BUS ESS AC VHF L IAPS AUDIO XFER COMM FDR AFCS 1 L IAPS IRU IRU CONT 1 CONT MDC C/PLT BATT 1 BATT 3 FAN PLT N P EICAS STBY RTU/CDU HORIZ DIMMING RTU 1 3 3 3 3 3 7.5 3 7.5 3 5 5 5 5 3 3 3 11 12 13 14 1 2 3 4 5 6 7 8 9 10 11 12 Q CIRCUIT BREAKER PANEL CBP - 1 POWER MUST BE OFF BEFORE OPENING PANEL CBP-1 28 VDC EMERGENCY BUS FIRE FIRE APU EXT 1 EXT 2 FIRE R ENG L ENG R ENG L ENG EXT 7.5 1 7.5 7.5 7.5 5 4 3 28 VDC EMERGENCY BUS FUEL SOV HYD SOV 2 R ENG L ENG APU PWR SENSE 7.5 3 6 R ENG L ENG R 7 FEED 20 3 3 3 3 3 1 2 3 4 5 6 7 1 2 3 4 5 6 7 S T TEST MFD 1 NORM MFD 2 MAINT ADSHC P604_07_013 OFF CIRCUIT BREAKER PANEL CBP - 1 (LOWER) Circuit Breaker Panel 1 Figure 7-25 For Training Purposes Only May 03 7-33 ELECTRICAL PILOT TRAINING GUIDE POWER MUST BE OFF BEFORE OPENING PANEL CBP-2 1 K 1 7.5 3 2 3 28 VDC BUS 2 4 5 3 2 3 CLOCK 1 3 3 7.5 6 7 4 4 CH B FUEL PUMP PRIM XFER 3 3 3 2 9 10 3 4 0.5 0.5 50 5 6 7 28 VDC BATTERY BUS WOW/ MLG BAY CABIN ADG DEPLOY CONT GEAR/ DOOR OVHT PRESS SPLR 2 WARN DET CONT AUTO MAN 5 3 3 3 2 3 4 5 HYD SYST PUMP IND CONT 3B 3 7.5 3 FEED 2 DC BATT ESS BUS 50 50 50 8 9 10 A/ICE VALVE L ENG R ENG 3 3 A/ICE MAN 2 ESS TRU 1 SHUNT FUSES F5PA F6PA 11 12 3 20 3 2 3 4 5 CONT PNL R LDU PRIM DISPL 3 3 10 10 7.5 7.5 7.5 3 3 3 3 2 3 4 5 6 7 8 9 10 11 12 3 1 2 3 WOW/ FLAP GEAR/ CONT 2 SPLR 2 3 5 3 3 9 10 11 12 DCU 1 CH A CH B 1 1 3 POWER SENSE 3 5 12 13 14 15 28 VDC BUS 2 CABIN TEMP CONT UTIL PWR LO TIE & TRU 2 BUS UTIL SENSE CONT SENSE LIM MAN AUTO 3 3 3 3 3 11 12 13 14 15 A/ICE AUTO 2 10 ST B/AIR SOVR 14 ST B/AIR SOVR STAB R AIR CH 1 COND HSTCU CONT 3 7 LIGHTING SENSOR 20 3 7 3 8 9 28 VDC BUS 2 FMS CDU 2 3 6 3 8 9 10 28 VDC BUS 2 R SEC FUEL R FUEL PUMP FUEL XFER CONT PUMP CONT 6 8 C D 7.5 3 3 B 11 10 7 5 5 15 9 3 4 5 50 6 3 3 8 5 A LDG/TAXI LTS R R NOSE WING 50 4 3 3 15 7 3 2 3 14 6 2 XPDR 2 13 50 ANTI SKID 5 12 INTEG LTS C/PLT PNLS 11 12 13 14 115 VAC UTILITY BUS 2 LINE HTRS DRAIN SUPPLY GAL/LAV TANK 5 8 9 10 DC BUS 2 CONTROL FEED 11 3 3 7.5 1 7 NOSE STEER VHF COMM 2 DCU 2 CH A CH B IRU 2 IRU FAN 2 10 3 4 15 9 AIL TRIM 3 14 3 3 3 13 5 GND SPLR 3 12 8 7.5 2 3 11 2 5 3 5 10 8 9 10 115 VAC BUS 2 ADG ICE 26VAC DET CABIN DEPLOY XFMR 2 FAN SENSE PWR SENSE FEED 4 3 6 7 26 VAC BUS 2 HYD SYST AC PUMP IND AC PUMP CONT 1 2 CONT 3A RAM AIR SOV 3 5 3 10 7 6 R R PITOT STATIC 20 5 3 4 5 28 VDC UTILITY BUS 1 10 8 9 115 VAC BUS 2 115VAC ESS FEED HEATERS R R WIND AOA 20 7.5 HF COMM2 TX/RX CPL 3 12 2 10 ESS TRU 2 SHUNT FUSES F11PA F12PA 6 7 8 9 10 11 28 VDC BATTERY BUS T/T T/T DUMP FUEL APU SOV FUEL X FEED DUMP CREW/PASS IRU STBY SOV CONT PUMP CONT OXYGEN BATT 2 ALTM 6 7 8 28 VDC BATTERY BUS EICAS SEC BRT/DIM PWR SUPP DISPL 1 2 3 1 6 STAB CH 1 HSTA 2 3 115 VAC BUS 2 7 R WSHLD 25 5 CH A 2 1 5 3 1 Q 10 CONT PNL 8 6 TRU 2 10 0.5 1 5 MFD 7 3 FLAP MOTOR 2 ADC 2 1 4 10 3 P 1 3 PFD 3 1 25 SURF POS IND R 3 N 25 EICAS 1 2 3 4 5 6 DC ESS & BATT BUS CONTROL CONTACTOR BATT FEED 1 LOGIC RCCB CONT ESS TRUS BUS PWR MAIN APU DC DC BATT SENSE BATT BATT ESS ESS BUS 1 2 M 1B APU BATT CHGR EFIS 2 L 4 3A 2 J 1 2 28 VDC BUS 2 R IAPS BAG AFCS 2 BAY FMS 2 SMOKE 115 VAC BUS 2 ESS TRU 2 HYD PUMP 3 3 11 12 E HTR CONT R R WSHLD WIND 13 3 3 14 15 F LIGHTS ADS BRAKE HTR R PRESS LIGHTS WING CONT IND BEACON A/COLL G 3 3 5 5 10 11 12 13 14 15 RTU 2 GPS 2 DME 2 ADF 2 RAD ALT 2 VHF NAV 2 5 3 3 3 3 3 5 9 10 11 12 13 14 15 H P604_07_014 1A SPARE Circuit Breaker Panel 2 Figure 7-26 7-34 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE CBP-3 115VAC ESS BUS ESS TRU 1 A 115VAC ADG BUS 10 1 25 7.5 2 3 4 5 L HTR WIND L PITOT ESS HYD PUMP SUPPLY AC ESS FEED STAB CH 2 HSTA 6 7 VOLTS & FREQ IND 25 8 9 10 1 11 12 13 115VAC ESS BUS B/LEAK L R DET DET B HEATERS L PITOT AOA STBY O/H PNLS L STATIC 3 3 10 5 3 5 3 1 2 3 4 5 6 7 IRU 1 IRU FAN 1 FDR PWR 3 3 3 1 2 3 8 INTEG LTS CB PLT PNLS PNLS CTR PNLS 3 5 3 5 9 10 11 12 13 9 10 11 12 13 11 12 13 115VAC ESS BUS C TCAS 5 4 5 6 ENG IGN A ICE DET 1 5 5 7 8 26VAC ESS BUS D 1 2 3 115VAC ESS BUS SURF POS IND L 26 VAC ESS XFMR 2 2 4 5 6 7 8 9 10 CIRCUIT BREAKER PANEL CBP-3 CBP-4 DC ESS BUS ESS TRU'S SENSE 1 2 A PWR SENSE THRUST REV AUTO STOW 1 2 1 2 SOV T/T XFER SOV CONT FSCU CH 2 ADS HTR L CONT LIGHTS EMERG FLOOD 3 3 3 5 5 7.5 7.5 5 3 3 25 1 2 3 4 5 6 7 8 9 10 11 12 13 FMS DATA LOAD STAB CH 2 HSTCU L AIR COND CONT A/ICE MAN 1 10 ST B/AIR ISOL B/LEAK TEST HTR CONT L WIND 1 DC ESS BUS CPAM/ R OIL EMER PRESS CONT DEPRESS TRANS DOOR WARN B 1 2 3 10 3 3 3 3 5 3 3 3 3 3 4 5 6 7 8 9 10 11 12 13 DC ESS BUS EFIS 1 C EFIS STALL CONT CRT PROT PNL DIMMING R CH ADC 1 CLOCK 2 VHF CKPT TEMP CONT CONT B/AIR COMM LO LIMIT MAN SOV L 3 EICAS DCU 1 DCU 1 CH A CH B PFD MFD 10 10 3 3 3 3 3 7.5 3 3 3 3 5 1 2 3 4 5 6 7 8 9 10 11 12 13 CVR R IAPS FAN R IAPS AFCS 1 XPDR 1 AUDIO PLT C/PLT FMS CDU 3 ADF 1 VHF NAV 1 5 3 7.5 3 5 3 3 5 1 2 3 4 D 5 6 7 8 9 10 11 12 13 P604_07_015 DC ESS BUS CIRCUIT BREAKER PANEL CBP-4 Circuit Breaker Panels 3 & 4 Figure 7-27 For Training Purposes Only May 03 7-35 ELECTRICAL PILOT TRAINING GUIDE CBP-5 B 1 2 2 3 1 5 50 BATT BUS 5 3 4 3 5 5 5 4 5 10 3 FUEL DEFUEL 7 7 3 3 8 8 9 L/R AUX SOVS T/T SOVS PANEL ADG AUTO 10 11 11 12 50 12 50 7.5 AC ESS PWR CONT MAIN BATT CHGR OP 3 SERV 3 LTS 5 10 3 9 3 BOARD FSCU 13 13 MAN EXT AC PWR CONT APU BATT CHGR OP P604_07_016 EXT SERV ENG OIL POWER 6 5 6 WATER SYST. OIL BYPASS IND 5 28VDC MAIN BATT DIRECT BUS DCU 2/3 ESS/ EMERG BUS FEED APU BATT CONT 28VDC APU BATT DIRECT BUS ENG IGN B MAIN BATT CONT APR 20 A Circuit Breaker Panel 5 Figure 7-28 7-36 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE EICAS Synoptic Pages AC Synoptic Page AC ELECTRICAL Generator 1 Output Flow Line (Upper) UTIL BUS 1 UTIL BUS 2 BUS 1 BUS 2 ESS BUS Generator 1 Load Readout Generator 2 Load Readout Generator 1 Voltage Readout Generator 1 Frequency Readout Generator 1 Output Flow Line (Lower) Generator 2 Output Flow Line (Upper) Generator 2 Voltage Readout 4 KVA 115 V 400 HZ 0 KVA 0V 0 HZ GEN 1 GEN 4 KVA 115 V 400 HZ Generator 2 Frequency Readout Generator 2 Output Flow Line (Lower) GEN 2 APU Description Symbol Condition Engine off Engine Outline Engine running and ready to load Invalid data GEN 1 GEN 2 Generator on-line GEN 1 GEN 2 Generator off with engine running GEN 1 GEN 2 Both respective generator and engine are off GEN 1 GEN 2 Invalid data Generator 1, 2 Output Flow Lines (Lower) Generator is on Generator is off P604_07_042 Generator 1, 2 Outline AC Synoptic Page Color Coding - Integrated Drive Generators (1 of 2) Figure 7-29 For Training Purposes Only May 03 7-37 ELECTRICAL Symbol 4 KVA Generator 1, 2 Load Readout Generator is overloaded 0 KVA Generator is not on-line 115 V Generator 1, 2 Frequency Readout Generator 1, 2 Output Flow Lines (Upper) Generator is loaded 36 KVA - - KVA Generator 1, 2 Voltage Readout Condition 94 V Invalid data Voltage between 100 and 125 VAC Voltage less than 100 VAC or more than 125 VAC ---V Invalid data 400 HZ Frequency between 375 and 425 Hz 429 HZ Frequency less than 375 Hz or more than 425 Hz - - - HZ Invalid data Generator line contactor at generator position Generator line contactor at tie position P604_07_043 Description PILOT TRAINING GUIDE AC Synoptic Page Color Coding - Integrated Drive Generators (2 of 2) Figure 7-30 7-38 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE AC ELECTRICAL UTIL BUS 1 UTIL BUS 2 BUS 1 APU Generator Output Flow Lines (Upper) BUS 2 ESS BUS APU Generator Load Readout APU Generator Voltage Readout APU Generator Frequency Readout 0 KVA 0V 0 HZ GEN 1 6 KVA 113 V 400 HZ GEN 0 KVA 0V 0 HZ GEN 2 APU APU Generator Output Flow Line (Lower) Description APU Outline Symbol Condition APU APU off APU APU running and ready to load APU Invalid data GEN Generator on-line GEN Generator off with APU running GEN Both respective generator and APU are off GEN Invalid data APU Generator Output Flow Line (Lower) Generator is on Generator is off P604_07_044 APU Generator Outline AC Synoptic Page Color Coding - APU Generator (1 of 2) Figure 7-31 For Training Purposes Only May 03 7-39 ELECTRICAL Symbol 6 KVA APU Generator Load Readout Generator is overloaded 0 KVA Generator is not on-line 113 V APU Generator Frequency Readout APU Generator Output Flow Lines (Upper) Generator is loaded 36 KVA - - KVA APU Generator Voltage Readout Condition 94 V Invalid data Voltage between 100 and 125 VAC Voltage less than 100 VAC or more than 125 VAC ---V Invalid data 400 HZ Frequency between 375 and 425 Hz 429 HZ Frequency less than 375 Hz or more than 425 Hz - - - HZ Invalid data Generator line contactor at generator position Generator line contactor at tie position P604_07_045 Description PILOT TRAINING GUIDE AC Synoptic Page Color Coding - APU Generator (2 of 2) Figure 7-32 7-40 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE AC ELECTRICAL UTIL BUS 1 UTIL BUS 2 BUS 1 BUS 2 UTIL BUS 2 BUS 2 UTIL BUS 2 SHED BUS 2 ESS BUS AUTO XFER OFF 4 KVA 115 V 400 HZ GEN 1 0 KVA 0V 0 HZ GEN AUTO XFER OFF 4 KVA 115 V 400 HZ 4 KVA 115 V 400 HZ GEN 2 GEN 2 AUTO XFER FAIL 0 KVA 0V 0 HZ GEN 2 APU Description AC BUS 1, 2 Bus Bar Outline Symbol Condition BUS 1 BUS 2 Bus powered BUS 1 BUS 2 Bus not powered BUS 1 BUS 2 Invalid data ESS BUS Bus powered ESS BUS Bus inoperative ESS BUS Invalid data ESS BUS Bus Bar Outline UTIL BUS 1, 2 Bus Bar Outline UTIL BUS 1 UTIL BUS 2 Bus powered UTIL BUS 1 UTIL BUS 2 Bus not powered (shed) UTIL BUS 1 UTIL BUS 2 Invalid data AUTO XFER OFF Displayed when AUTO XFER switch/light is manually selected AUTO XFER FAIL Icon AUTO XFER FAIL Indicates that the corresponding automatic bus transfer has failed SHED Icon SHED Displayed when AC UTIL BUS 1 and 2 are load shed P604_07_047 AUTO XFER OFF Icon AC Synoptic Page Color Coding - AC Electrical Power Distribution Figure 7-33 For Training Purposes Only Jan 04 7-41 ELECTRICAL PILOT TRAINING GUIDE AC ELECTRICAL UTIL BUS 1 External AC Voltage Readout UTIL BUS 2 BUS 1 116 V 400 HZ External AC Frequency Readout External AC Input Outline BUS 2 ESS BUS EXT AC 0 KVA 0V 0 HZ 0 KVA 0V 0 HZ 0 KVA 0V 0 HZ GEN 1 GEN GEN 2 APU Symbol External AC Outline EXT AC Displayed when external AC power is connected (voltage greater than 10 VAC and frequency greater than 50 Hz) EXT AC External AC power is available (displayed only when external AC is between 106 to 124 VAC) EXT AC External AC power is in use External AC Input Outline External AC Voltage Readout External AC Frequency Readout Condition 116 V Voltage between 106 and 124 VAC 102 V Voltage less than 106 VAC or more than 124 VAC 400 HZ Frequency between 370 and 430 Hz 365 HZ Frequency less than 370 Hz or more than 430 Hz - - - HZ Invalid data P604_07_046 Description AC Synoptic Page Color Coding - External AC Electrical Power Figure 7-34 7-42 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE ADG Voltage Readout AC ELECTRICAL UTIL BUS 1 ADG Frequency Readout 115 V 400 HZ ADG Input Outline ADG BUS 1 UTIL BUS 2 BUS 2 ESS BUS 0 KVA 0V 0 HZ 0 KVA 0V 0 HZ 0 KVA 0V 0 HZ GEN 1 GEN GEN 2 APU Description Symbol Condition ADG Outline ADG Displayed when external AC power is connected (voltage greater than 10 VAC and frequency greater than 50 Hz) ADG ADG power is available (displayed only when external AC is between 106 to 124 VAC) ADG ADG power is in use ADG Voltage Readout ADG Frequency Readout 115 V Voltage between 106 and 124 VAC 100 V Voltage less than 106 VAC or more than 124 VAC 400 HZ Frequency between 370 and 430 Hz 435 HZ Frequency less than 370 Hz or more than 430 Hz - - - HZ Invalid data P604_07_048 ADG Input Outline AC Synoptic Page Color Coding - Air-Driven Generator Figure 7-35 For Training Purposes Only May 03 7-43 ELECTRICAL PILOT TRAINING GUIDE DC Synoptic Page AC BUS to TRU Flow Lines TRU Voltage Readouts DC ELECTRICAL AC BUS 1 AC BUS 2 TRU 1 TRU 2 28 V 8 A 28 V 13 A TRU Load Readouts AC ESS BUS ESS TRU 2 28 V 24 A ESS TRU 1 28 V 24 A BUS 1 ESS BUS BUS 2 BATT BUS TIE APU BATT DIR BUS UTIL BUS 1 EMER BUS MAIN BATT DIR BUS UTIL BUS 2 EXT DC 28 V 19 A Description APU BATT 27 V 0 A Symbol MAIN BATT 26 V 0 A Condition Respective AC BUS is powering TRU AC BUS to TRU Flow Lines Essential TRU 1 and TRU 2 Outline TRU 1 TRU 2 28 V 8A 28 V 13 A TRU 1 TRU 2 0V 0A 0V 0A TRU 1 TRU 2 -- V -- A -- V -- A ESS TRU 1 28 V 24 A ESS TRU 2 28 V 24 A TRU voltage is 18 VDC or greater and load is greater than 3 amps ESS TRU 1 0V 0A ESS TRU 2 0V 0A TRU voltage is less than 18 VDC or load is less than 3 amps ESS TRU 1 -- V -- A ESS TRU 2 -- V -- A Invalid data TRU voltage is 18 VDC or greater TRU voltage is less than 18 VDC Invalid data P604_07_049 TRU 1 and TRU 2 Outline No AC power to TRU DC Synoptic Page - TRU Power Distribution System (1 of 2) Figure 7-36 7-44 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE TRU Voltage Readouts TRU Load Readouts Symbol Condition 28 V Voltage is between 22 and 29 VDC 18 V Voltage is less than 22 VDC or more than 29 VDC --V Invalid data 8A Load is between 3 and 99 amps 0A Load is less than 3 amps or more than 99 amps --A Invalid data P604_07_050 Description DC Synoptic Page - TRU Power Distribution System (2 of 2) Figure 7-37 For Training Purposes Only May 03 7-45 ELECTRICAL PILOT TRAINING GUIDE DC ELECTRICAL AC BUS 1 AC BUS 2 TRU 1 TRU 2 28 V 8 A 28 V 13 A AC ESS BUS ESS TRU 2 28 V 24 A ESS TRU 1 28 V 24 A BUS 1 ESS BUS BUS 2 BATT BUS APU BATT 17 V 9 A MAIN BATT 15 V 7 A BATT OFF BATT OFF APU BATT 24 V 0 A MAIN BATT 24 V 0 A CHGR FAIL CHGR FAIL TIE APU BATT DIR BUS UTIL BUS 1 EMER BUS APU BATT DIR BUS EMER BUS MAIN BATT DIR BUS MAIN BATT DIR BUS UTIL BUS 2 APU Battery Voltage Readout Description MAIN Battery Outline APU Battery Outline APU BATT 27 V 4 A MAIN BATT 26 V 4 A Main Battery Voltage Readout Main Battery Load Readout EXT DC 28 V 19 A APU BATT 27 V 0 A MAIN BATT 26 V 0 A EXT DC IN USE APU Battery Load Readout Symbol Condition MAIN BATT 26 V 0A Battery voltage is equal to or greater than 18 VDC MAIN BATT 15 V 7A Battery voltage is less than 18 VDC MAIN BATT -- V -- A Invalid data BATT OFF Main battery is less than 18 VDC CHGR FAIL Main battery is not charging or Main charger has failed APU BATT 27 V 0A Battery voltage is equal to or greater than 18 VDC and EXT DC is not in use APU BATT 17 V 9A Battery voltage is less than 18 VDC and EXT DC is not in use APU BATT APU BATT -- V -- A EXT DC is in use Note: APU BATT voltage and amperage go blank Invalid data BATT OFF APU battery is less than 18 VDC CHGR FAIL APU battery is not charging or APU charger has failed P604_07_051 EXT DC 28 V 19 A DC Synoptic Page - Battery Power Distribution System (1 of 2) Figure 7-38 7-46 For Training Purposes Only Jan 04 ELECTRICAL PILOT TRAINING GUIDE Symbol EXT DC 28 V 19 A EXT DC Outline EXT DC 16 V 5A MAIN and APU Battery Voltage Readouts MAIN and APU Battery Load Readouts Condition EXT DC voltage is equal or greater than 18 VDC EXT DC voltage is less than 18 VDC 26 V Voltage is between 18 and 32 VDC 10 V Voltage is less than 18 VDC or greater than 32 VDC --V Invalid data 8A Battery is equal or greater than 12 VDC or load is greater than 0 amps 0A Battery is less than 12 VDC and load is 0 amps --A Invalid data P604_07_052 Description DC Synoptic Page - Battery Power Distribution System (2 of 2) Figure 7-39 For Training Purposes Only May 03 7-47 ELECTRICAL PILOT TRAINING GUIDE DC ELECTRICAL AC BUS 1 AC BUS 2 TRU 1 TRU 2 28 V 8 A 28 V 13 A Bus Input Flow Lines AC ESS BUS ESS TRU 2 28 V 24 A ESS TRU 1 28 V 24 A BUS 1 BUS 1 ESS BUS BUS 2 BUS 2 BATT BUS TIE TIE UTIL BUS 1 UTIL BUS 1 UTIL BUS 2 UTIL BUS 2 APU BATT DIR BUS EMER BUS EXT DC 28 V 19 A MAIN BATT DIR BUS APU BATT 27 V 0 A MAIN BATT 26 V 0 A MAIN BUS TIE CLOSED Symbol Respective TRU/battery is on-line and output is 18 VDC or greater Bus Input Flow Lines Respective TRU/battery is on-line and output is less than 18 VDC or no supply is being provided to respective bus BUS 1 BUS 2 DC BUS 1, 2 Bus Bar Outline BUS 1 BUS 2 BUS 1 BUS 2 UTIL BUS 1 UTIL BUS 2 UTIL BUS 1, 2 Bus Bar Outline Condition UTIL BUS 1 UTIL BUS 2 UTIL BUS 1 UTIL BUS 2 Bus powered Bus not powered Invalid data Bus powered Bus not powered P604_07_053 Description Invalid data DC Synoptic Page - DC Electrical Power Distribution (1 of 2) Figure 7-40 7-48 For Training Purposes Only May 03 ELECTRICAL PILOT TRAINING GUIDE Symbol ESS BUS BATT BUS ESS BUS and BATT BUS Bus Bar Outline ESS BUS BATT BUS ESS BUS BATT BUS APU BATT DIR BUS Bus Bar Outline MAIN BATT DIR BUS Bus Bar Outline Condition Bus powered Bus not powered Invalid data APU BATT DIR BUS Battery voltage is greater than 18 VDC, BATT MASTER switch ON, and EXT DC not in use APU BATT DIR BUS Battery voltage is less than 18 VDC, BATT MASTER switch ON, and EXT DC not in use APU BATT DIR BUS Invalid data MAIN BATT DIR BUS Battery voltage is greater than 18 VDC and BATT MASTER switch ON MAIN BATT DIR BUS Battery voltage is less than 18 VDC and BATT MASTER switch ON MAIN BATT DIR BUS Invalid data P604_07_054 Description DC Synoptic Page - DC Electrical Power Distribution (2 of 2) Figure 7-41 For Training Purposes Only May 03 7-49 ELECTRICAL PILOT TRAINING GUIDE EICAS Messages MESSAGE EMER POWER ONLY AC 1 AUTOXFER AC 2 AUTOXFER AURAL WARNING (IF ANY) MEANING ADG is supplying the AC essential bus, and no power is available from AC BUS 1 or 2. TRIPLE ATTENSON Respective automatic AC bus tie function has been inhibited because of an overcurrent condition on the respective AC bus. AC BUS 1 Respective AC bus is unpowered. AC BUS 2 AC ESS BUS AC essential bus is unpowered. APU BATTERY OFF APU battery is less than 18 VDC. APU GEN OFF APU generator is off-line with the APU running. APU GEN OVLD Load on the APU generator exceeds 34.5 kVA. BATTERY BUS Battery bus is unpowered. DC BUS 1 Respective DC bus is unpowered. DC BUS 2 DC EMER BUS DC emergency bus is unpowered. DC ESS BUS DC essential bus is unpowered. GEN 1 OFF Respective generator is OFF. GEN 2 OFF GEN 1 OVLD Load on respective generator exceeds 34.5 kVA. GEN 2 OVLD MAIN BATTERY OFF Main battery is less than 18 VDC. AC ESS ALTN AC essential bus is powered by AC BUS 2. AC UTIL 1 OFF Respective AC utility bus is unpowered. AC UTIL 2 OFF APU BATT CHGR FAIL APU battery is not charging or APU charger has failed. ESS TRU 1 FAIL Respective essential transformer-rectifier unit output is less than 18 VDC. ESS TRU 2 FAIL MAIN BATT CHGR FAIL Main battery is not charging or main battery charger has failed. EICAS Messages Table 7-1 7-50 For Training Purposes Only May 03
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