Global 5000 Flight Crew Operating Manual (Volume 2)

the event of malfunction. The third stage, is the main alternator, which incorporates current transformers that are used for feeder fault and overcurrent protection. All VFG output is routed through the AC power center (ACPC), which protects, controls and distributes primary AC power to the main airplane busses. VFG output is then routed through the CCBP to bus feeders 1, 2 and 3 and the AC ESS BUS for power distribution to the 4 transformer rectifier units (TRU) and forward AC loads. Aft AC loads are fed directly from the ACPC. Each generator normally powers its own bus, through a generator line contactor (GLC). Generator #4 also powers AC ESS BUS. In the event of a generator malfunction, the generator transfer contactors (GTC) will automatically switch to an alternate generator, to supply the affected bus. AC bus 2 and 3 are automatically shed during single generator operations. AC power can also be supplied by the auxiliary power unit (APU) generator. The APU constant frequency generator is rated at 115 volt, 40 KVA, 3 phase, 400 Hz output. The APU generator has a ground power rating of 45 KVA continuous. External AC power, 115 volt, 3 phase, can also be used to supply power to the AC system. External AC Power Receptacle EXT AC GROUND SERVICE EXT DC BATTERY MASTER LAMP TEST MIC HDPH APU SHUT−OFF AVAIL AVAIL IN USE IN USE ON ON External AC/DC Power Status Indicators Displays status of external AC or DC power. Battery Master Status Indicator Displays status of the battery master switch (EMS or ON position). Ground Service Mode Switch Enables maintenance personnel to power selected AC loads in the cabin, with AC external power connected. External Service Panel SERVICE LIGHTS OFF GF0710_003 ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−4 AC SYSTEM (CONT'D) Emergency AC power is supplied by the ram air turbine (RAT) in flight, rated at 115 volts, 9 kVA, 3 phase. With engines running, the RAT will depoy with a 14 second time delay following the loss of all AC power, if the slat/flap handle is at the in/0° position. It will deploy automatically if the slat/flap handle is not at the in/0° position. With a dual-engine failure, the RAT will deploy automatically, regardless of slat/flat handle position. The RAT can also be manually deployed by pulling RAT manual deploy handle, located on the center pedestal. Once deployed, the RAT will power the AC ESS BUS via the ram air turbine line contactor (RATLC). MANUAL DEPLOY HANDLE RAT GF0710_004 The RAT also incorporates a hydraulic pump, which powers hydraulic system #3. At approximately 147 KIAS and below, the RAT sheds its electrical output, giving priority to hydraulics. A ground safety pin is installed in the nose wheel well area to secure the RAT in position while on ground. ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−5 AC SYSTEM (CONT'D) GROUND SAFETY PIN GF0710_005 DEPLOYMENT ACTUATOR RETRACTION PUMP UPLOCK RAM AIR TURBINE GENERATOR HYDRAULIC PUMP DOWNLOCK RELEASE ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−6 AC SYSTEM DISTRIBUTION 9 GTC 7 GEN 2 GEN 1 AC BUS 1 LH Engine RH Engine AC BUS 3 AC BUS 4 AC ESS BUS APU GEN EXT AC ACPC AC BUS 2 GCU GCU GCU GCU GCU GTC 12 GTC 11 GTC 4 GTC 5 GLC 1 GLC 2 GLC 3 GLC 4 GTC 3 GTC 6 GTC 1 GTC 8 GTC GTC 2 GTC 10 RATLC APULC EPLC CCBP TRU 1 GEN RAT GCU AC BUS 1A AC BUS 2A AC BUS 3A TRU 2 ESS TRU 1 ESS TRU 2 GEN 3 GEN 4 GF0710_006 ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−7 ELECTRICAL PANEL The generators and external power can be controlled manually by selecting the appropriate switch on the electrical panel, located on the overhead panel. GEN 1, 2, 3, 4 and APU GEN switches are normally ON. RAT GEN Switch Used to reset a fault or to turn RAT generator off. generator is on line. RAT generator operation is inhibited. GEN 1, 2, 3, 4 Switches Used to reset or to turn applicable generator off. failed generating channel (GEN, GCU, GLC). FAIL light illuminates when fire discharge handle is pulled generator operation inhibited. APU GEN Switch Used to reset or to turn APU generator off. failed generating channel. generator operation inhibited. NOTE If RAT GEN is powering AC ESS BUS, and a main generator is available, stow the RAT deploy handle and select RAT GEN to OFF, to transfer AC ESS BUS to the main generator. The RAT GEN will remain armed to ensure RAT GEN priority in the event of loss all main generators. External AC Switch Displays status of AC external power: external AC power is connected and is the correct phase, voltage and frequency. is being used or can be used by the airplane power distribution system to maintain power to the AC busses. GF0710_007 FAIL Light − Indicates a OFF Light − Indicates ON Light − Indicates that RAT OFF Light − Indicates that FAIL Light − Indicates a OFF Light − Indicates AVAIL Light − Comes on to indicate that ON Light − Indicates that external power ELECTRICAL ON BATT MASTER OFF EMS ON ON AVAIL AVAIL EXT AC EXT DC PUSH OFF/RESET OFF OFF FAIL FAIL GEN 3 GEN 4 OFF FAIL GEN 2 OFF FAIL GEN 1 OFF FAIL APU GEN PUSH OFF/RESET OFF ON RAT GEN ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−8 ELECTRICAL MANAGEMENT SYSTEM Load control consists of smart contactors, Solid State Power Controllers (SSPC) and control logic. Smart contactors and SSPC are functionally similar to a control switch in series with a circuit breaker. The status of all circuit breakers is monitored (trips are automatically displayed) and can be acknowledged and reseted via the Electrical Management System (EMS). EMS Control Display Units (CDU) are installed on the pilot’s and copilot’s side panel. Page Number Displays which page is selected and how many pages are available. Line Select Keys Used to select displayed items. Activation Keys Used to switch current status. STAT Key Displays the status of tripped, out and locked circuit breakers. System Key Displays circuit breaker status by aircraft system. BUS Key Displays circuit breaker status by electrical busses. PREV PAGE Key Scrolls list to previous page. NEXT PAGE Key Scrolls list to next page. CNTL Key Displays system’s control options. TEST Key Displays system’s test options. EMER CNTL Key Displays Bus isolation status Brightness Control If no action is taken within 2 minutes of page activation or selection, the display will automatically turn off and become dark. NOTE Page Title Displayed when a selection has been made using page select key. Page Select Keys GF0710_008 STAT SYS BUS PREV CNTL TEST PAGE NEXT PAGE EMER CNTL BUS CIRCUIT BREAKER − SYSTEM 1/2 SYSTEM CIRCUIT BREAKER AFCS AIR COND/PRESS APU BLEED CAIMS COMM DOORS ELEC ENGINE FIRE FLT CONTROLS FUEL BRT ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−9 ELECTRICAL MANAGEMENT SYSTEM (CONT'D) The circuit breaker STATUS page will automatically appear anytime a circuit breaker trips (CB TRIP message appears on EICAS). The STATUS page can be selected using STATUS page select key. The circuit breakers will be displayed in the following sequence: TRIP, OUT then LOCKED. CIRCUIT BREAKER − STATUS 1/1 LOCKED DISPLAY UNIT 1 DC ESS CCBP OUT H STAB TRIM 1 AC 1 OUT H STAB TRIM 2 AC ESS FUEL COMP B DC ESS OUT RAD ALT 1 DC 1 TRIP ACPC LOCKED − Circuit breaker has been locked by maintenance personnel. CCBP − Thermal circuit breaker located on Cockpit Circuit Breaker Panel. DC ESS − BUS location of affected circuit breaker. FUEL COMP B − Circuit breaker identification ACPC − Thermal circuit breaker located on the component within ACPC. OUT − Circuit breaker has been selected out. TRIP − Circuit breaker has tripped. GF0710_009 STAT SYS BUS PREV CNTL TEST PAGE NEXT PAGE EMER CNTL BUS CIRCUIT BREAKER − SYSTEM 1/2 SYSTEM CIRCUIT BREAKER RAD ALT 1 H STAB TRIM 1 H STAB TRIM 2 FUEL COMP B DISPLAY UNIT 1 TRIP OUT OUT OUT LOCKED DC 1 AC 1 AC ESS DC ESS DC ESS ACPC CCBP BRT ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−10 ELECTRICAL MANAGEMENT SYSTEM (CONT'D) The EMS CDUs are designed to be linked. When linked, a CDU (secondary) is operating exactly as the controlling CDU (primary). A primary CDU controls itself and, when linked, the other CDU. The following table identifies the possible relationships: Link State EMS CDU Pilot Copilot Initial Power Up Secondary Secondary Pilot CDU Linked Secondary Primary Copilot CDU Linked Primary Secondary Both unlinked Primary Primary A CDU is considered secondary in the following conditions: • At initial power up, • A CDU display is turned on by pressing a function control key on the other CDU (except PREV page key). A CDU is considered primary in the following conditions: • When any key of a secondary CDU is pressed, • When in the TEST page, a selection is made on the other CDU, • When the STAT page is selected. An “S“ character is displayed in the lower left corner of the screen of a secondary CDU and an “M” character in the lower left corner of the screen of a primary CDU. GF0710_012 M − Linked CDU indication STAT SYS BUS PREV CNTL TEST PAGE NEXT PAGE EMER CNTL BUS CIRCUIT BREAKER − SYSTEM 1/2 SYSTEM CIRCUIT BREAKER RAD ALT 1 H STAB TRIM 1 H STAB TRIM 2 FUEL COMP B DISPLAY UNIT 1 TRIP OUT OUT OUT LOCKED DC 1 AC 1 AC ESS DC ESS DC ESS ACPC CCBP M BRT ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−11 ELECTRICAL MANAGEMENT SYSTEM (CONT'D) Circuit breakers can be acknowledged or acknowledged and reset, using the line select keys. Most recent tripped circuit breaker will automatically highl ight. To select another circuit breaker, use the line select key, this acknowledges and high lights the displayed breaker. Once acknowleged or reset, the CB TRIP message goes out. Select activation key adjacent highlighted circuit breaker. 1/1 removed from STATUS page list, after successful reset and a new status list is selected. CB TRIP message goes out. NOTE Will appear if an attempt to reset is carried out on a thermal circuit breaker. A thermal breaker cannot be reset using EMS CDU. The affected circuit breaker can only be manually reset at its location. THERM CB CAN’T BE CHANGED FROM CDU. 2 1 GF0710_013 STAT SYS BUS PREV CNTL TEST PAGE NEXT PAGE EMER CNTL BUS CIRCUIT BREAKER − SYSTEM 1/1 SYSTEM CIRCUIT BREAKER H STAB TRIM 1 H STAB TRIM 2 FUEL COMP B DISPLAY UNIT 1 OUT OUT OUT LOCKED AC 1 AC ESS DC ESS DC ESS ACPC CCBP M CIRCUIT BREAKER − STATUS 1/1 CIRCUIT BREAKER − STATUS 1/1 IN LOCKED TRIP FUEL COMP B DISPLAY UNIT 1 RAD ALT 1 LOCK H STAB TRIM 1 OUT H STAB TRIM 2 DC ESS DC ESS DC ESS AC1 AC ESS ACPC CCBP THERM CB CANT BE CHANGED FROM CDU OUT LOCKED FUEL COMP B DISPLAY UNIT 1 H STAB TRIM 1 OUT H STAB TRIM 2 DC ESS DC ESS AC1 AC ESS ACPC CCBP OUT IN LOCKED reduced when reset. The reset circuit breaker will automatically be FUEL COMP B DC ESS DISPLAY UNIT 1 DC ESS Affected circuit OUT IN breaker font size is NOTE OUT H STAB TRIM 1 AC1 ACPC CIRCUIT BREAKER − STATUS 1/1 OUT H STAB TRIM 2 CCBP AC ESS BRT RAD ALT 1 TRIP DC 1 ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−12 AC SYSTEM EICAS MESSAGES CB TRIP AC FEED Indicates that a circuit breaker for an AC feeder/AC cabin feeder has tripped. RAT GEN FAIL (on ground only) Indicates that a fault has been detected in the RAT generator system during built in test (BIT). AC ESS BUS FAIL Indicates that AC ESS BUS is not powered or has a fault. EMER PWR ONLY Indicates that RAT is powering the AC ESS BUS or the battery is powering the BATT BUS. AC BUS 1 (2)(3)(4) FAIL Indicates that affected bus is not powered or has a fault. APU GEN OVLD Indicates an overload on the APU generator. GEN 1 (2)(3)(4) OVLD Indicates an overload on affected generator channel. CB TRIP DC FEED Indicates that a circuit breaker for a DC feeder/DC cabin feeder has tripped. APU GEN OVERHEAT Indicates that the APU generator oil has overheated. GF0710_016b EMER PWR ONLY AC BUS 1 FAIL AC BUS 2 FAIL AC BUS 3 FAIL AC BUS 4 FAIL AC ESS BUS FAIL APU GEN OVERHEAT APU GEN OVLD CB TRIP AC FEED CB TRIP DC FEED GEN 1 OVLD GEN 2 OVLD GEN 3 OVLD GEN 4 OVLD RAT GEN FAIL ELEC SYS FAIL (on ground only) Indicates that a major fault has been detected in the electrical system. ELEC SYS FAIL ELECTRICAL Rev 11, Apr 17, 2006 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−13 AC SYSTEM EICAS MESSAGES (CONT'D) CB TRIP Indicates that a circuit breaker has tripped. AC BUS 1 (2)(3)(4) MAN OFF Indicates that the affected bus has been manually isolated. All 4 busses cannot be manually isolated concurrently. GEN 1 (2)(3)(4) OFF Indicates that affected generator is selected off. EXT AC PWR ON Indicates that external AC power has been selected on. ELEC SYS FAULT Indicates that a minor fault has been detected in the EMS. APU GEN FAIL Indicates that APU GEN has failed. EXT AC PWR AVAIL Indicates that external power is available. GEN 1 (2)(3)(4) FAIL Indicates a GCU fault in the applicable generator APU GEN OFF Indicates that APU GEN is selected off. RAT GEN ON Indicates that the RAT generator is powering the AC ESS BUS and is RAT GEN OFF Indicate that the RAT is deployed and the RAT generator is not powering the AC ESS BUS. GF0710_015a APU GEN FAIL ELEC SYS FAULT EXT AC PWR AVAIL CB TRIP GEN 1 FAIL GEN 2 FAIL GEN 3 FAIL GEN 4 FAIL RAT GEN ON AC BUS 1 MAN OFF AC BUS 2 MAN OFF AC BUS 3 MAN OFF AC BUS 4 MAN OFF APU GEN OFF EXT AC PWR ON GEN 1 OFF GEN 2 OFF GEN 3 OFF GEN 4 OFF RAT GEN OFF the only online generator. ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−14 AC SYSTEM SYNOPTIC Electrical system warnings, cautions, advisories and status messages are presented on the EICAS primary display. General views of airplane electrical systems (either AC or DC) are presented through synoptic diagrams on the EICAS secondary display (after selecting the appropriate key on the EICAS control panel). Generator Output Flow Line (Lower) Green − Generator is on. Blank − Generator is off. Generator Output Flow Line (Upper) · Green − Generator line contactor at generator position. · Blank − Generator line contactor at tie position. Generator Voltage Readout Displays, in VAC, the generator voltage level. · Green − 100−125 VAC · Amber − GCU fault · White − GEN off · Magenta − Invalid data. Generator Load Readout Displays in KVA, the load on the generator. APU Generator Frequency Readout Displays, in Hz, the generator frequency level. EICAS Control Panel GF0710_018 AC BUS 1 V KVA 115 12 GEN 1 GEN 2 AC BUS 2 V KVA 115 12 GEN 3 AC BUS 3 V KVA 115 12 V KVA 115 15 GEN 4 AC BUS 4 AC ESS BUS V KVA 0 0 HZ 0 APU AC ELECTRICAL GEN The AC electrical page contains digital readouts of generator output voltage, frequency (APU only), load in KVA, input/output flow on the buses, general status indications via color logic and the following messages: • SHED message − Corresponding AC bus has been shed. GF0710_019 AC BUS 3 AC BUS 2 SHED SHED ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−15 AC SYSTEM SYNOPTIC (CONT'D) • AC BUS 1, 2, 3, 4 MAN OFF icon − Corresponding AC bus is isolated. • AC BUS 1, 2, 3, 4 MAN OFF status message displayed on EICAS. NOTE A maximum of 3 buses only can be manually isolated concurrently. GF0710_020 AC BUS 1 MAN OFF AC BUS 1 MAN OFF AC BUS 2 MAN OFF AC BUS 3 MAN OFF AC BUS 4 MAN OFF AC BUS FEED SYSTEM Each AC bus is normally powered by its own generator through generator line contactors. In the event of a generator malfunction, the priority system will automatically provide an alternate generator (feed), to power that bus (APU must be started to be available to the feed system), through generator transfer contactors. The AC busses are normally powered by their own generator, but can be powered by alternate generators in the following descending order: • AC BUS 1 − GEN 1, GEN 4, GEN 3, GEN 2, APU GEN. • AC BUS 2 − GEN 2, GEN 3, GEN 4, APU GEN. • AC BUS 3 − GEN 3, GEN 2, GEN 1, APU GEN. • AC BUS 4 − GEN 4, GEN 1, GEN 2, GEN 3, APU GEN. • AC ESS BUS − RAT GEN (if deployed), GEN 4, GEN 1, GEN 2, GEN 3, APU GEN. Normal power for AC ESS BUS is generator 4. When the RAT is deployed and RAT GEN is ON the AC ESS Bus is fed directly from the RAT GEN. AC busses 2 and 3 are automatically load shed when a single generator is powering the buses. External AC power will power all AC buses when selected ON. The AC bus feed is displayed on the AC ELECTRICAL synoptic page as follows: ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−16 AC BUS FEED SYSTEM (CONT'D) AC BUS 1 − Normally powered by GEN 1, alternately powered by the following, in descending priority: GEN 2 APU GEN GEN 4 GEN 3 GEN 1 GF0710_022 GEN 1 GEN 4 GEN 3 GEN APU GEN 2 P R I O R I T Y AC BUS 1 V KVA 115 12 GEN 1 GEN 2 AC BUS 2 V KVA 115 12 GEN 3 AC BUS 3 V KVA 115 12 V KVA 115 15 GEN 4 AC BUS 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL GEN 1 GEN 2 AC BUS 2 V KVA 115 12 GEN 3 AC BUS 3 V KVA 115 12 V KVA 115 15 GEN 4 AC BUS 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL AC BUS 1 AC BUS 1 GEN 1 GEN 2 GEN 3 GEN 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL GEN 1 GEN 2 GEN 3 GEN 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL V KVA V KVA 115 12 V KVA V KVA AC BUS 1 AC BUS 4 V KVA 0 0 GEN 2 GEN 3 GEN 4 GEN APU AC ELECTRICAL AC BUS 1 AC BUS 2 AC BUS 3 AC BUS 4 AC ESS BUS 0 0 0 0 0 0 GEN 1 V KVA 0 0 V KVA 0 0 V KVA 0 0 V KVA V KVA 0 0 0 0 V KVA 115 24 V KVA 115 28 HZ 400 V KVA 115 24 V KVA 115 24 AC BUS 4 AC BUS 2 AC BUS 3 SHED SHED AC BUS 2 AC BUS 3 ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−17 AC BUS FEED SYSTEM (CONT'D) AC BUS 2 − Normally powered by GEN 2, alternately powered by the following, in descending priority: GEN 2 GEN 4 GF0710_024 GEN 3 APU GEN GEN 2 GEN 3 GEN 4 GEN APU P R I O R I T Y AC BUS 1 V KVA 115 12 GEN 1 GEN 2 AC BUS 2 V KVA 115 12 GEN 3 AC BUS 3 V KVA 115 12 V KVA 115 15 GEN 4 AC BUS 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL AC BUS 1 V KVA 115 12 GEN 1 GEN 2 GEN 3 V KVA 115 24 GEN 4 AC BUS 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL V KVA 115 12 V KVA GEN 2 GEN 3 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL AC BUS 1 AC BUS 2 AC BUS 3 AC BUS 4 V KVA 0 0 V KVA 0 0 GEN 1 GEN 2 GEN 4 AC ESS BUS GEN APU AC ELECTRICAL V KVA 0 0 V KVA V KVA 115 28 HZ 400 V KVA AC BUS 2 0 0 0 0 AC BUS 3 GEN 1 115 12 V KVA 115 24 GEN 4 115 12 V KVA 115 24 0 0 AC BUS 2 AC BUS 3 AC BUS 4 AC BUS 1 GEN 3 V KVA 0 0 ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−18 AC BUS FEED SYSTEM (CONT'D) AC BUS 3 − Normally powered by GEN 3, alternately powered by the following, in descending priority: GEN 3 GEN 1 GF0710_026 GEN 2 APU GEN GEN 3 GEN 2 GEN 1 GEN APU P R I O R I T Y AC BUS 1 V KVA 115 12 GEN 1 GEN 2 AC BUS 2 V KVA 115 12 GEN 3 AC BUS 3 V KVA 115 12 V KVA 115 15 GEN 4 AC BUS 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL AC BUS 1 V KVA 115 12 GEN 1 GEN 2 GEN 3 V KVA 115 24 GEN 4 AC BUS 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL GEN 2 GEN 3 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL AC BUS 1 AC BUS 2 AC BUS 3 AC BUS 4 V KVA 0 0 V KVA 0 0 GEN 1 GEN 2 GEN 3 V KVA 115 24 GEN 4 AC BUS 4 AC ESS BUS GEN APU AC ELECTRICAL AC BUS 1 V KVA 0 0 V KVA V KVA 115 28 HZ 400 V KVA AC BUS 2 0 0 0 0 AC BUS 3 AC BUS 2 AC BUS 3 V KVA 115 12 V KVA 0 0 GEN 1 GEN 4 115 12 V KVA 115 12 V KVA 115 24 115 24 ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−19 AC BUS FEED SYSTEM (CONT'D) AC BUS 4 − Normally powered by GEN 4, alternately powered by the following, in descending priority: GEN 3 APU GEN GEN 1 GEN 2 GEN 4 GF0710_028 GEN 4 GEN 1 GEN 2 GEN APU GEN 3 AC BUS 1 V KVA 115 12 GEN 1 GEN 2 AC BUS 2 V KVA 115 12 GEN 3 AC BUS 3 V KVA 115 12 V KVA 115 15 GEN 4 AC BUS 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL GEN 1 GEN 2 AC BUS 2 V KVA 115 12 GEN 3 AC BUS 3 V KVA 115 12 GEN 4 AC ESS BUS V KVA 0 0 HZ 0 APU AC ELECTRICAL AC BUS 4 AC BUS 1 V KVA 0 0 V KVA 115 12 AC BUS 1 GEN 1 GEN 2 GEN 3 GEN 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL V KVA 0 0 V KVA 0 0 V KVA 115 24 V KVA 115 24 AC BUS 4 AC BUS 2 AC BUS 3 GEN 1 GEN 2 GEN 3 GEN 4 AC ESS BUS GEN APU AC ELECTRICAL V KVA 0 0 HZ 0 V KVA V KVA 115 32 V KVA V KVA 0 0 0 0 0 0 AC BUS 4 AC BUS 1 115 32 GEN 1 GEN 2 GEN 3 GEN 4 AC ESS BUS GEN APU AC ELECTRICAL V KVA V KVA 0 0 AC BUS 1 AC BUS 4 V KVA 115 32 HZ 400 0 0 V KVA 0 0 V KVA 0 0 SHED SHED AC BUS 2 AC BUS 3 SHED SHED AC BUS 2 AC BUS 3 GEN ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−20 AC BUS FEED SYSTEM (CONT'D) AC ESS BUS − Normally powered by GEN 4, alternately powered by the following, in descending priority: GEN 2 APU GEN GEN 4 GEN 1 RAT GEN GF0710_030 GEN 3 NOTE The RAT GEN has priority, . GEN 4 GEN 1 GEN 2 GEN APU GEN 3 GEN RAT P R I O R I T Y ON . only if it has been deployed and RAT GEN AC BUS 1 V KVA GEN 1 GEN 2 AC BUS 2 V KVA 0 GEN 3 AC BUS 3 V KVA V KVA GEN 4 AC BUS 4 GEN V KVA 0 0 HZ 0 APU GEN RAT 115 400 V HZ AC ELECTRICAL AC ESS BUS 0 0 0 0 0 0 0 AC BUS 1 V KVA 115 12 GEN 1 GEN 2 AC BUS 2 V KVA 115 12 GEN 3 AC BUS 3 V KVA 115 12 V KVA 115 15 GEN 4 AC BUS 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL GEN 1 GEN 2 AC BUS 2 V KVA 115 12 GEN 3 AC BUS 3 V KVA 115 12 GEN 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL AC BUS 4 AC BUS 1 V KVA 0 0 V KVA 115 12 AC BUS 1 GEN 1 GEN 2 GEN 3 GEN 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL V KVA 0 0 V KVA 0 0 V KVA 115 24 V KVA 115 24 AC BUS 4 AC BUS 2 AC BUS 3 GEN 1 GEN 2 GEN 3 GEN 4 AC ESS BUS GEN APU AC ELECTRICAL V KVA 0 0 HZ 0 V KVA V KVA V KVA V KVA 0 0 0 0 0 0 AC BUS 4 AC BUS 1 115 32 GEN 1 GEN 2 GEN 3 GEN 4 AC ESS BUS GEN APU AC ELECTRICAL V KVA V KVA 0 0 AC BUS 1 AC BUS 4 V KVA 115 32 HZ 400 0 0 V KVA 0 0 V KVA 0 0 SHED SHED AC BUS 2 AC BUS 3 SHED SHED AC BUS 2 AC BUS 3 OFF ON RAT GEN ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−21 AC BUS FEED SYSTEM (CONT'D) EXT AC Power external AC power is available and is the correct phase, voltage and frequency. ON Light − Indicates that external power is being used or can be used by the airplane power distribution system to maintain power to the AC busses. NOTE The ON light will remain illuminated, even when other source(s) is powering AC busses, to indicate that the priority system can call upon EXT AC if needed. AVAIL Light − Comes on to indicate that GF0710_031 GEN 1 GEN 3 GEN 4 AC ELECTRICAL V KVA 0 0 GEN 2 GEN V KVA HZ APU V KVA 0 0 AC BUS 1 AC BUS 2 AC BUS 3 AC BUS 4 AC ESS BUS V KVA 115 HZ 400 GEN 1 GEN 3 GEN 4 AC ELECTRICAL GEN 2 AC ESS BUS EXT AC 28 0 0 0 V KVA 0 0 V KVA 0 0 EXT AC AC BUS 1 AC BUS 4 AC BUS 2 AC BUS 3 V KVA 0 0 V KVA 0 0 V KVA HZ 115 23 400 V KVA 0 0 V KVA 0 0 GEN APU V KVA 115 0 HZ 400 EXT AC V KVA 115 0 HZ 400 EXT AC EXT AC V KVA 115 0 HZ 400 V KVA 115 HZ 400 28 ON AVAIL EXT AC ON EXT AC ON EXT AC ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−22 DC SYSTEM There are six primary DC power sources: four identical transformer rectifier units (TRU), an Avionics battery and an APU battery. All sources are routed through the DC power center (DCPC). The six primary sources are monitored, switched, distributed and controlled by the DCPC. The DCPC reconfigures the busses automatically in the event of a TRU failure. Four main DC buses provide DC power to the secondary airplane loads. Each TRU normally powers a bus, through a TRU line contactor (TLC). In the event of a TRU malfunction, the TRU transfer contactors (TTC), will automatically switch to an alternate TRU, to supply the affected bus. DC busses 1 and 2 are automatically shed during single TRU operations. The avionics battery direct bus and DC emergency bus power is distributed to their secondary loads through circuit breakers. Two nickel cadmium batteries are installed in the airplane. Both batteries are used together in an emergency to provide DC power for a minimum of 15 minutes. Each battery has a separate dedicated battery charger, to maintain that battery in a fully charged condition. The battery charger provides protection against battery overtemperature, defective or unbalanced cell, open/short battery temperature sense thermistor, open/short battery voltage sense lines and charger overtemperature. The charger will shut itself off, if required and annunciate when it senses a battery fault or charger fault. External DC power is supplied to the airplane via the DC external power receptacle. The APU start contactor assembly (ASCA) checks the power being delivered from the power unit before connecting it to the airplane busses. EXTERNAL DC POWER RECEPTACLE GF0710_032 ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−23 DC SYSTEM DISTRIBUTION EXT DC AC ESS BUS AC BUS 1A AC BUS 3A AC BUS 2A CCBP CCBP A2 CCBP G6 CCBP E11 CCBP E8 CCBP C2 ESS TRU 2 ESS TRU 1 TRU 1 TRU 2 BATT BUS DC ESS BUS DC BUS 2 DC BUS 1 TLC 1 TLC 2 TTC 1 TTC 2 ETC DCPC TLC 3 TLC 4 TTC 3 TTC 4 AVIONICS BATT DIRECT BUS START APU BATT DIRECT BUS CCBP C4 CCBP C6 ASCA EPC APUSC APU BATTERY AVIONICS BATTERY APU EBBC ETTC SSPC 1 SSPC 2 SSPC 3 SSPC 4 SSPC 5 DC EMERGENCY BUS GF0710_033 ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−24 ELECTRICAL PANEL External DC power is controlled manually. Battery master must be selected ON for all phases of flight. External DC Switch Displays status of DC external power: AVAIL Light − Comes on to indicate that external DC power is connected and is operating within limits. ON Light − Indicates external DC power is powering the APU battery direct bus. BATT MASTER Switch Used to control battery power. OFF − Isolates the battery bus from the batteries. EMS − Electrical Management System is in maintenance mode. ON − Battery bus is powered by battery (only if no AC power on the airplane). GF0710_034a ELECTRICAL ON BATT MASTER OFF EMS ON ON AVAIL AVAIL EXT AC EXT DC PUSH OFF/RESET OFF OFF FAIL FAIL GEN 3 GEN 4 OFF FAIL GEN 2 OFF FAIL GEN 1 OFF FAIL APU GEN PUSH OFF/RESET OFF ON RAT GEN ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−25 DC SYSTEM EICAS MESSAGES BATT BUS FAIL Indicates that battery bus is not powered due to a fault. BATT MASTER OFF Indicates that the battery switch is not on. DC EMER BUS FAIL Indicates that DC EMER BUS is not powered due to a fault. APU (AV) BATT FAIL Indicates that APU (AV) battery has failed, voltage or temperature is out of range. DC BUS 1 (2) FAIL Indicates that affected DC bus is not powered due to a fault or is shed. DC ESS BUS FAIL Indicates that DC ESS BUS is not powered due to a fault. ELEC SYS FAIL (on ground only) Indicates that a major fault has been detected in the electrical system. GF0710_035a APU BATT FAIL AV BATT FAIL BATT MASTER OFF BATT BUS FAIL DC BUS 1 FAIL DC BUS 2 FAIL DC ESS BUS FAIL DC EMER BUS FAIL ELEC SYS FAIL CAIMS LEVEL A fault. Prevents aircraft dispatch until fixed. ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−26 DC SYSTEM EICAS MESSAGES (CONT'D) EXT DC PWR AVAIL Indicates that external DC power is available. APU (AV) BATT CHGR FAIL Indicates that affected battery charger has detected a fault and has shut down. TRU 1−2 FAIL ESS TRU 1−2 FAIL Indicates that affected TRU has failed. EXT DC PWR ON Indicates that external DC power has been selected on. BATT BUS MAN OFF DC BUS 1 (2) MAN OFF DC ESS BUS MAN OFF Indicates that affected DC bus has been manually isolated. DC essential cannot be manually isolated if battery has been isolated and vice versa. BATT EMER PWR ON Indicates that the batteries are feeding the DC ESS BUS and BATT busses in an emergency condition. ELEC SYS FAULT (on ground only) Indicates that a minor fault has been detected in the electrical system. CB TRIP Indicates that a circuit breaker has tripped. GF0710_036a APU BATT CHGR FAIL AV BATT CHGR FAIL BATT EMER PWR ON CB TRIP ELEC SYS FAULT EXT DC PWR AVAIL ESS TRU 1 FAIL ESS TRU 2 FAIL TRU 1 FAIL TRU 2 FAIL BATT BUS MAN OFF DC BUS 1 MAN OFF DC BUS 2 MAN OFF DC ESS BUS MAN OFF EXT DC PWR ON CAIMS Level C fault. Fault must be fixed within 10 days. ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−27 DC SYSTEM SYNOPTIC EICAS Control Panel GF0710_039 AC BUS 2 FEEDER DC BUS 1 V A 28 35 TRU 1 AC BUS 3 FEEDER DC BUS 2 V A 28 35 TRU 2 AC BUS 1 FEEDER AC ESS BUS DC ESS V A 28 35 ESS TRU 1 V A 28 35 ESS TRU 1 BUS DC EMER BATT BUS BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL EICAS SCROLL SYSTEM SELECT The DC electrical page contains digital readouts of TRU and battery output (voltage and ampere output), input/output flow on the bus bars, general status information via color logic and the following messages: • CHARGER message (adjacent to APU BATT symbol) − APU battery is not charging. Corresponds to APU BATT CHGR FAIL advisory message . • CHARGER message (adjacent to AV BATT symbol) − Main airplane battery is not charging. AV BATT CHGR FAIL advisory message displayed on EICAS. • SHED message − Corresponding DC bus has been shed. • MAN OFF message − Corresponding DC bus is isolated. DC BUS 1, 2, MAN OFF, DC ESS MAN OFF and/or BATT BUS MAN OFF status message displayed on EICAS. DC BUS 1 MAN OFF DC BUS 2 SHED −10 AV BATT APU BATT 20 C C CHARGER CHARGER GF0710_041 APU BATT CHGR FAIL AV BATT CHGR FAIL DC BUS 1 MAN OFF DC BUS 2 MAN OFF DC ESS MAN OFF BATT BUS MAN OFF ELECTRICAL Rev 11, Apr 17, 2006 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−28 DC BUS FEED SYSTEM Each DC bus is normally powered by its respective TRU. Each TRU is normally powered by its own AC BUS FEEDER (ESS TRU 2 is powered by AC ESS BUS). In the event of a TRU malfunction, the priority system will automatically provide an alternate TRU feed to power the respective DC bus. As soon as one TRU fails, the emergency tie contactor (ETC) closes to allow power distribution. ESS TRU 2 will be powered (through the AC ESS BUS) when the RAT is deployed and RAT GEN is selected ON. The DC buses are powered by the TRUs in the following descending order: • DC BUS 1 − TRU 1, ESS TRU 1. • DC ESS BUS − ESS TRU 1, ESS TRU 2, TRU 2, TRU 1. • BATT BUS − ESS TRU 2, ESS TRU 1, TRU 2, TRU 1. • DC BUS 2 − TRU 2, ESS TRU 2. DC BUS 1 and DC BUS 2 are automatically load shed when a single generator is powering the buses. External DC power will power the APU BATT DIR BUS and consequently, the BATT BUS and the DC EMER BUS. External DC power is normally used by maintenance personnel or to start the APU in the event of a low APU BATT voltage. The DC bus feed is displayed on the DC ELECTRICAL synoptic page as follows: ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−29 DC BUS FEED SYSTEM (CONT'D) DC BUS 1 − Normally powered by TRU 1, alternately powered by the following, in descending order: TRU 1 ESS TRU 1 GF0710_043 AC BUS 2 FEEDER DC BUS 1 V A 28 35 TRU 1 AC BUS 3 FEEDER DC BUS 2 V A 28 35 TRU 2 AC BUS 1 FEEDER AC ESS BUS DC ESS V A 28 35 ESS TRU 1 V A 28 35 ESS TRU 2 BUS DC EMER BATT BUS BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL AC BUS 2 FEEDER AC BUS 3 FEEDER DC BUS 2 V A 28 35 TRU 2 AC BUS 1 FEEDER AC ESS BUS V A 28 35 ESS TRU 2 DC EMER BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL V A 28 35 TRU 1 V A 28 35 ESS TRU 1 V A 0 0 TRU 1 V A 28 42 ESS TRU 1 DC ESS BUS DC BUS 1 BATT BUS ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−30 DC BUS FEED SYSTEM (CONT'D) DC ESS BUS − Normally powered by ESS TRU 1, alternately powered by the following, in descending order: ESS TRU 1 ESS TRU 2 TRU 2 TRU 1 GF0710_045 AC BUS 2 FEEDER DC BUS 1 V A 28 35 TRU 1 AC BUS 3 FEEDER DC BUS 2 V A 28 35 TRU 2 AC BUS 1 FEEDER AC ESS BUS DC ESS V A 28 35 ESS TRU 1 V A 28 35 ESS TRU 2 BUS DC EMER BATT BUS BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL AC BUS 2 FEEDER DC BUS 1 V A 28 35 TRU 1 AC BUS 3 FEEDER DC BUS 2 V A 28 35 TRU 2 AC BUS 1 FEEDER AC ESS BUS V A 28 42 ESS TRU 2 DC EMER BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL AC BUS 2 FEEDER DC BUS 1 V A 28 35 TRU 1 AC BUS 3 FEEDER AC BUS 1 FEEDER AC ESS BUS DC EMER BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL AC BUS 2 FEEDER AC BUS 3 FEEDER AC BUS 1 FEEDER AC ESS BUS DC EMER BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL SHED V A 28 35 TRU 1 V A 28 35 ESS TRU 2 V A 28 35 ESS TRU 1 V A 28 35 TRU 2 BATT BUS V A 28 54 TRU 2 V A 0 0 ESS TRU 2 SHED DC BUS 2 BATT BUS DC BUS 1 V A 28 75 TRU 1 DC ESS BUS V A 0 0 ESS TRU 1 V A 0 0 ESS TRU 1 DC ESS BUS DC BUS 2 TRU 2 V A 0 0 ESS TRU 2 V A 0 0 SHED BATT BUS V A 0 0 ESS TRU 1 DC ESS BUS ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−31 DC BUS FEED SYSTEM (CONT'D) BATT BUS − Normally powered by ESS TRU 2, alternately powered by the following, in descending order: GF0710_047 V A 28 35 TRU 1 V A 28 35 TRU 2 V A 28 35 ESS TRU 2 V A 28 35 ESS TRU 1 °C 20 XXX BATT ESS TRU 2 AC BUS 2 FEEDER DC BUS 1 V A 28 35 TRU 1 AC BUS 3 FEEDER DC BUS 2 V A 28 35 TRU 2 AC BUS 1 FEEDER AC ESS BUS DC ESS V A 28 35 ESS TRU 1 V A 28 35 ESS TRU 2 BUS DC EMER BATT BUS BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL ESS TRU 1 AC BUS 2 FEEDER DC BUS 1 V A 28 35 TRU 1 AC BUS 3 FEEDER DC BUS 2 V A 28 35 TRU 2 AC BUS 1 FEEDER AC ESS BUS V A 28 42 ESS TRU 1 V A 0 0 ESS TRU 2 DC EMER BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL DC ESS BUS BATT BUS TRU 2 AC BUS 2 FEEDER DC BUS 1 V A 28 35 TRU 1 AC BUS 3 FEEDER AC BUS 1 FEEDER AC ESS BUS V A 0 0 ESS TRU 2 AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC EMER BUS V A 28 54 TRU 2 BATT BUS V A 0 0 ESS TRU 1 TRU 1 AC BUS 2 FEEDER DC BUS 1 AC BUS 3 FEEDER DC BUS 2 TRU 2 AC BUS 1 FEEDER AC ESS BUS DC EMER BUS V A 26 0 °C −10 AV BATT V A 24 0 °C 20 APU BATT DC ELECTRICAL V A 0 0 ESS TRU 2 V A 0 0 SHED SHED BATT BUS APU BATT DIR BUS AV BATT DIR BUS DC ESS BUS V A 0 0 ESS TRU 1 V A 28 75 TRU 1 Batteries AC BUS 2 FEEDER DC BUS 1 AC BUS 3 FEEDER DC BUS 2 TRU 2 AC BUS 1 FEEDER AC ESS BUS V A 0 0 ESS TRU 1 DC EMER BUS V A 26 0 °C −10 AV BATT V A 24 0 °C 20 APU BATT DC ELECTRICAL V A 0 0 ESS TRU 2 V A 0 0 SHED SHED TRU 1 V A 0 0 BATT BUS APU BATT DIR BUS AV BATT DIR BUS DC ESS BUS DC ELECTRICAL DC BUS 2 SHED DC ESS BUS ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−32 DC BUS FEED SYSTEM (CONT'D) DC BUS 2 − Normally powered by TRU 2, alternately powered by the following, in descending order: TRU 2 ESS TRU 2 GF0710_049a AC BUS 2 FEEDER DC BUS 1 V A 28 35 TRU 1 AC BUS 3 FEEDER DC BUS 2 V A 28 35 TRU 2 AC BUS 1 FEEDER AC ESS BUS DC ESS V A 28 35 ESS TRU 1 V A 28 35 ESS TRU 2 BUS DC EMER BATT BUS BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL AC BUS 2 FEEDER DC BUS 1 V A 28 35 TRU 1 AC BUS 3 FEEDER AC BUS 1 FEEDER AC ESS BUS DC EMER BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL DC ESS BUS V A 0 0 TRU 2 BATT BUS V A 28 42 V A 28 35 V A 28 35 TRU 2 V A 28 35 ESS TRU 2 ESS TRU 2 ESS TRU 1 DC BUS 2 ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−33 DC BUS FEED SYSTEM (CONT'D) External DC Power AVAIL Light Indicates that external DC power is connected (not on−line) and is within limits. ON Light Indicates external DC power is powering APU BATT DIR BUS. GF0710_050a AC BUS 2 FEEDER DC BUS 1 AC BUS 3 FEEDER DC BUS 2 TRU 2 AC BUS 1 FEEDER AC ESS BUS V A 0 0 ESS TRU 1 DC EMER BUS V A 26 0 °C −10 AV BATT °C 20 APU BATT DC ELECTRICAL V A 0 0 ESS TRU 2 V A 0 0 TRU 1 V A 0 0 BATT BUS APU BATT DIR BUS AV BATT DIR BUS DC ESS BUS EXT DC V A 24 10 °C 20 APU BATT EXT DC V A 28 10 °C 20 APU BATT EXT DC V A 24 10 ON EXT DC EXT DC AVAIL CHARGER CHARGER ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−34 RAT GEN FEED Emergency AC power is supplied by the ram air turbine (RAT) in flight, rated at 115volts, 9 kVA, 3−phase. With a dual−engine failure, the RAT will deploy automatically, regardless of slat/flap handle position. The RAT can also be manually deployed by pulling RAT manual deploy handle, located on the center pedestal. With engines running, the RAT will deploy with a 14−second time delay following the loss of all AC power, if the slat/flap handle is at the in/zero position. And if the flaps/slats are deployed, with a loss of all AC power, the RAT will deploy immediately and will supply power to AC ESS within 6 seconds of deployment. The RAT will supply power to AC ESS within 6 seconds of deployment. This delay is implemented to allow the pilot to regain GEN 1−2−3 or 4 or APU GEN power. In the event that an operating generator is restored, select the RAT GEN switch to OFF with the RAT manual deploy handle in the stowed position. The RAT GEN will remain in a standby mode. ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−35 RAT GEN FEED (CONT'D) GEN RAT GF0710_051a AC BUS 2 FEEDER DC BUS 1 AC BUS 3 FEEDER DC BUS 2 AC BUS 1 FEEDER AC ESS BUS V A 0 0 ESS TRU 1 V A 28 75 ESS TRU 2 DC EMER BUS AV BATT DIR BUS V A 26 0 °C −10 AV BATT V A 24 0 APU BATT DIR BUS °C 20 APU BATT DC ELECTRICAL BATT BUS DC ESS BUS V A 0 0 TRU 1 V A 0 0 TRU 2 AC BUS 1 V KVA GEN 1 GEN 2 AC BUS 2 V KVA 0 GEN 3 AC BUS 3 V KVA V KVA GEN 4 AC BUS 4 GEN V KVA 0 0 HZ 0 APU GEN RAT 115 400 V HZ AC ELECTRICAL AC ESS BUS 0 0 0 0 0 0 0 ON RAT GEN CHARGER CHARGER ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−36 RAT PILOT ACTIVATED TEST The pilot activated test is initiated by the pilot during pre-flight after AC power has been applied to the airplane. It takes approximately 5 seconds to complete the test. The test is activated through the EMS CDU on the ground only. RAT TEST: Press the RAT TEST activation button to initiate test. Test duration is approximately 5 seconds. GF0710_052 TEST CONTROL 2/2 OFF RAT TEST The pilot activated test checks the following: • The RAT line contactor, • the 147 KIAS discrete signal from the MADCs • the RAT GCU, • the RAT deploy handle status signal, • AC bus 4 status signal, • the RAT GEN push button annunciator status, • the RAT generator heater. A failed test results in a RAT GEN FAIL caution message being posted on the EICAS status page. ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−37 EMERGENCY DC POWER In the event of loss of all AC power , or the airplane speed is 147 knots or less with the RAT deployed, a “BATTERY EMER PWR ON” EICAS message will be displayed. This message will be displayed when the airplane is operating on emergency battery power only. If the RAT is deployed and speed is less than 147 knots, it will automatically shed its electrical output giving priority to hydraulics. NOTE Battery emergency power is available for a minimum of 15 minutes. GF0710_053 AC BUS 1 V KVA GEN 1 GEN 2 AC BUS 2 V KVA GEN 3 AC BUS 3 V KVA V KVA GEN 4 AC BUS 4 AC ESS BUS GEN V KVA 0 0 HZ 0 APU AC ELECTRICAL 0 0 0 0 0 0 0 0 0 0 V HZ BATTERY EMER PWR ON AC BUS 2 FEEDER DC BUS 1 AC BUS 3 FEEDER DC BUS 2 TRU 2 AC BUS 1 FEEDER AC ESS BUS V A 0 0 ESS TRU 1 DC EMER BUS V A 26 24 °C −10 AV BATT V A 24 24 °C 20 APU BATT DC ELECTRICAL V A 0 0 ESS TRU 2 V A 0 0 TRU 1 V A 0 0 BATT BUS APU BATT DIR BUS AV BATT DIR BUS DC ESS BUS 180 170 160 150 140 130 120 110 147 8 6 GEN RAT ELECTRICAL Rev 3, Apr 25, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 07−10−38