B767 200-300 BOOK 24 101 - Electrical Power

For training purposes onlyLEVEL 1 ATA 24 page 113 - 04 - 2012

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B767/24/101Electrical Power

Boeing 767-200/300

Training manual

Electrical Power

B767/24/101Electrical PowerTraining manual

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This publication was created by Sabena technics training de-partment, Brussels-Belgium, following ATA 104 specifications. The information in this publication is furnished for informational and training use only, and is subject to change without notice. Sabena technics training assumes no responsibility for any errors or inaccuracies that may appear in this publication. No part of this publication may be reproduced, stored in a re-trieval system, or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of Sabena technics training.

Contact address for

course registrationscourse schedule information

Sabena technics [email protected]


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1................................................ 13 - 04 - 20122................................................ 13 - 04 - 20123................................................ 13 - 04 - 20124................................................ 13 - 04 - 20125................................................ 13 - 04 - 20126................................................ 13 - 04 - 20127................................................ 13 - 04 - 20128................................................ 13 - 04 - 20129................................................ 13 - 04 - 201210.............................................. 13 - 04 - 201211.............................................. 13 - 04 - 201212.............................................. 13 - 04 - 201213.............................................. 13 - 04 - 201214.............................................. 13 - 04 - 201215.............................................. 13 - 04 - 201216.............................................. 13 - 04 - 201217.............................................. 13 - 04 - 201218.............................................. 13 - 04 - 201219.............................................. 13 - 04 - 201220.............................................. 13 - 04 - 201221.............................................. 13 - 04 - 201222.............................................. 13 - 04 - 201223.............................................. 13 - 04 - 201224.............................................. 13 - 04 - 201225.............................................. 13 - 04 - 201226.............................................. 13 - 04 - 201227.............................................. 13 - 04 - 201228.............................................. 13 - 04 - 201229.............................................. 13 - 04 - 201230.............................................. 13 - 04 - 201231.............................................. 13 - 04 - 201232.............................................. 13 - 04 - 201233.............................................. 13 - 04 - 201234.............................................. 13 - 04 - 2012

LIST OF EFFECTIVE PAGES


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AC POWER INDICATION ......................................................................................................... 34APU GENERATOR EXTERNAL DETAILS .................................................................................... 31AUXILIARY ELECTRICAL CONTROL PANEL .............................................................................. 25DC POWER INDICATION ......................................................................................................... 18ELECTRICAL SYSTEM ............................................................................................................. 21ELECTRICAL SYSTEM CONTROL PANEL .................................................................................. 23EXTERNAL POWER PANEL ...................................................................................................... 29GROUND SERVICE / MISC. TEST PANEL .................................................................................. 27HYDRAULIC MOTOR GENERATOR SYSTEM ............................................................................ 33IDG AIR / OIL COOLING .......................................................................................................... 15IDG FUEL / OIL EXCHANGER .................................................................................................. 13INTEGRATED DRIVE GENERATOR SYSTEM .............................................................................. 11MAIN AND APU BATTERY CHARGING SYSTEM ...................................................................... 19POWER DISTRIBUTION ............................................................................................................. 7POWER DISTRIBUTION - GENERAL ............................................................................................ 9TRANSFORMER RECTIFIER UNIT.............................................................................................. 19

1. ELECTRICAL SYSTEM SUMMARY. ..........................................................61.1. External Power. ......................................................................................61.2. Integrated Drive Generator System. ......................................................101.3. IDG Cooling and Control. ....................................................................12

1.3.1. GE CF6. .......................................................................................121.3.2. PW 4000. ....................................................................................14

1.4. IDG Temperature Monitoring. ..............................................................161.4.1. GE CF6. .......................................................................................161.4.2. PW4000. .....................................................................................16

1.5. DC Power System. ...............................................................................181.6. System Control and Indication. ............................................................181.7. AC Power System. ...............................................................................20

2. ELECTRICAL SYSTEM PANELS. .............................................................222.1. Electrical System Control Panel (P5). .....................................................222.2. Auxiliary Electrical System Control Panel. ..............................................242.3. Ground Service/Misc Test Panel. ...........................................................26

3. AC EXTERNAL POWER SYSTEM. ..........................................................283.1. System Description. ..............................................................................28

4. APU GENERATOR. .................................................................................304.1. Physical Description..............................................................................30

5. HYDRAULIC MOTOR GENERATOR SYSTEM. .......................................325.1. System Description. ..............................................................................325.2. AC Power Indications. ..........................................................................34

LIST OF ILLUSTRATIONSTABLE OF CONTENTS


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FLT FlightFMCS Flight Management Computer systemFWD ForwardGCB Generator Control BreakerGCR Generator Control RelayGCU Generator Control UnitGEN GeneratorGHB Ground Handling BusGHR Ground Handling RelayGND GroundGSB Ground Service BusGSSR Ground Service Select RelayGSTR Ground Service Transfer RelayHF High FrequencyHMG Hydraulic Motor generatorHYD Hydraulic(ally)IAS Indicated AirspeedIDG Integrated Drive GeneratorILS Instrument Landing SystemIND IndicatorINTLK InterlockINTPH InterphoneIRU Inertial Reference UnitISLN IsolationLAV LavatoryLct Line Current TransformerLRU Line Replaceable UnitLTS LightsMAN ManualMPU Magnetic Pick UpNct Neutral Current TransformerNVM Non-Volatile MemoryOF Over FrequencyOV Over VoltageOVHD OverheadPdp Power Distribution PanelPDT Pole Double ThrowPMG Permanent Magnet GeneratorPNL PanelPOR Point Of Regulation

ACMP Alternating Current Motor PumpADF Automatic Direction Finder AFT AfterwardsAgcu Apu Generator Control UnitAgb Accessory GearboxALT AltitudeAOA Angle Of AttackAPB APU BreakerAPU Auxiliary Power UnitBAT BatteryBITE Built In Test EquipmentBPCU Bus Power Control UnitBTB Bus Tie BreakerCB Circuit BreakerCHGR ChargerCMD CommandCOMM CommunicationCONT Control(ler)CSD Constant Speed DriveCT Current TransformerCTA Current Transformer AssemblyCTR CenterDCTCU DC Tie Control BusDME Distance Measurement EquipmentDPCT Differntial Protection Current TransformerEADI Electronic Attitude Direction IndicatorEAROM Electrically Alterable Read Only MemoryEEC Electronic Engine ControlEFIS Electronic Flight Instrument SystemEHSI Electronic Horizontal Situation IndicatorEICAS Engine Indicating and Crew Alerting SystemELCU Electrical Load Control UnitELEC Electric(ally)EMI Electromagnetic InterferenceEQUIP COOL Equipment CoolingEP External PowerEPC External Power ContactorEPREQ External Power RequestEXT ExternalFCC Flight Coltrol Computer

PST Pole Single ThrowPWR PowerQAD Quick Attach DetachRCCB Remote Control Circuit BreakerRDMI Radio Distance Magnetic IndicatorREF ReferenceSENS SensorSTBY StandbyTEMP TemperatureTR Transformer RectifierTRU Transformer Rectifier UnitUBR Utility Bus RelayUF Under FrequencyUTIL UtilityUV Under VoltageVHF Very High FrequencyVOR VHF Omnidirectional RangeVr Voltage RegulatorVSI Vertical Speed IndicatorXFER TransferXFMR Transformer

ABBREVIATIONS AND ACRONYMS


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1. ELECTRICAL SYSTEM SUMMARY.

1.1. External Power.

The external power system allows 115 volt ac ground power to be connectedfor powering the ground handling, ground service, and left and right main acbuses. An external power source is connected to the external powerreceptacle located in the P30 panel. Other external power components arelocated in the main equipment center P34, P33 panels and E2 rack. If the BusPower Control Unit (BPCU) senses good power quality the AC CONNECTEDand PWR NOT IN USE LIGHTS (P30) and AVAIL LIGHT (P5) are illuminated.The BPCU initiates opening and closing of the external power contactor,ground handling relay, and ground service select and transfer relays.It provides external power monitoring for fault isolation and contains BITE forthe complete electrical system. The ground handling bus is automaticallypowered for good external power quality, and external power is given priorityover APU generator power. The ground service bus receives powerautomatically when the right main AC bus is powered. When the right mainbus is not powered, pushing the GROUND SERVICE switch (P21 forwardattendants panel) allows the ground service bus to be powered either fromexternal power or APU generator. Pushing the EXT PWR switch (P5 overheadpanel) closes the external power contactor and the EXT PWR ON lightilluminates. External power has priority over the integrated drive generator(IDG) and APU generator when manually selected. After both generatorcircuit breakers close, the external power contactor is tripped open.The BPCU protection circuitry monitors external power current, voltage andfrequency for fault isolation tripping of the external power contactor, groundhandling relay and ground service select and transfer relays. External powercontactor fault protection trips are reset by pushing the EXT PWR switch.Ground handling and ground service system fault protection trips are reset bypushing the GROUND SERVICE switch.

Power Distribution.Each power feeder includes a length of high temperature copper wire and alength of light weight aluminium wire spliced together. Copalum splices areused to connect the copper and aluminium wires together. The IDG powerfeeder splices are located in the upper part of the nacelle strut. The APUgenerator power feeder splices are located between the APU firewall and therear pressure bulkhead. The all copper external power feeder is one piece.

The IDG power feeders can only be disconnected at the IDG terminal block.For the APU generator, power feeders are disconnected at either the firewallor the generator terminal block.

The tie bus feeders interconnect the main power panel distribution centersthrough the bus tie breakers. Connections are provided to the auxiliary powerbreaker and the external power contactor. Tie bus feeders between BTBs,APB and EPC are connected in a ring-bus configuration.

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POWER DISTRIBUTION - GENERAL


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1.2. Integrated Drive Generator System.

The generator outputs 115/200 volt, 3-phase, 400 Hz, ac power and is rated at 90 KVA.

Each integrated drive generator is QAD ring attached to the accessory gearbox. Constant generator speed is maintained by a mechanical speed governor. The disconnect reset ring allows reconnection of the IDG input spline mechanical connection after a disconnect. Two electrical connectors provide IDG to GCU interface for control, protection and monitoring. A terminal block is used for power feeder connections.

The IDG is cooled by an external oil cooling system composed of fuel/oil and air/oil heat exchanger assemblies connected in series. The fuel/oil heat exchangers use engine fuel to cool IDG oil. An air/oil heat exchanger receives fan air through a pneumatic and electrically controlled cooling air shutoff valve. A generator drive disconnect switch, when pushed, disconnects the IDG input shaft from the engine accessory gearbox if the associated engine fuel control switch is not in cutoff.


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INTEGRATED DRIVE GENERATOR SYSTEM


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1.3. IDG Cooling and Control.

1.3.1. GE CF6.

IDG Fuel/Oil Heat Exchanger.This unit provides primary cooling for the integrated drive generator oil during normal flight operations.

Location.The heat exchanger is attached to the accessory gearbox lower rightside.

IDG Air/Oil Heat Exchanger.The air/oil heat exchanger cools IDG oil when the fuel/oil heat exchanger hasinsufficient fuel flow. A cooling air shutoff valve controls fan air flow to theair/oil heat exchanger.

Location.The air oil heat exchanger and cooling air shutoff valve are on theengine compressor case at approximately 4 oclock.The air/oil heat exchanger is a tube and fin-type heat exchanger.Heated oil flows from the inlet port through tubes to the outlet port.An air supply duct on the engine fan case directs fan air through thecooling air shutoff valve. The fan air passes over the heat exchangerfins.


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IDG FUEL / OIL EXCHANGER


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1.3.2. PW 4000.

Purpose.The IDG Air/Oil Heat Exchanger cools the IDG oil when the Fuel/OilCooler has insufficient capability.Airflow through the heat exchanger is controlled by the IDG Air/OilHeat Exchanger Valve.

The HPC Secondary Flow Control/IDG Air Oil Heat Exchanger ValveOverride Solenoid controls Ps3 pneumatic pressure to the Override FuelPressure Switch.

Location.The IDG Air/Oil Heat Exchanger and Valve are mounted in the aft sideof the intermediate case at the 4 oclock position.

The HPC Secondary Flow Control/IDG Air/Oil Heat Exchanger ValveOverride Solenoid and the Override Fuel Pressure Switch are mountedon the aft side of the intermediate case at the 1 oclock position.


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IDG AIR / OIL COOLING


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1.4. IDG Temperature Monitoring.

1.4.1. GE CF6.

IDG temperature is monitored by two temperature sensors locatedinside the IDG. After processing the GCU sends IDG rise and oil outtemperature to EICAS for display on the ELEC/HYD page.

Operation.EICAS supplies a dc reference voltage to the GCUs trough resistorR10111. The voltage and current of this ref circuit vary with IDGtemperature (1 mA = 180 C). This changing voltage represents theIDG temp and is monitored by the EICAS computers.The K1 timer module located in the P61 panel signals the GCU totransmit either oil out or rise temp. The same signal is used to informEICAS which temperature is being transmitted by the GCU.If the K1 timer should fail in the ground (rise temp) or open position(outlet temp) for longer than 5 seconds EICAS will blank the failedtemperature indication for both IDGs.

Indication.IDG oil out and rise temp are displayed on the ELEC/HYD page.The GCU alternately transmits oil out and oil rise temperature sensor inone of the following ways :

- Both temp sensors failed. Transmit 180 C for oil out and risetemp.- Oil in or oil out temp sensor failed. Set rise temp to 8 C ifengine is running or 0 C if engine is not running.- Oil out temp sensor failed. Oil out indication will be oil in + 8 Cwith engine running and oil in temp with engine not running.- Oil in temp sense failed. The GCU uses oil out - 8 C for oil in.

1.4.2. PW4000.

Operation.The generator control unit monitors the IDG inlet and outlet oiltemperature sensors located in the IDG.The sensors are temperature bulbs whose resistance varies with oiltemperature.Each sensor is read by the microprocessor through an analog-to-digitalconverter. The signals are converted to temperature units in C.

The generator control unit provides IDG oil temperature signals to bothEICAS computers for display on the EICAS ELEC/HYD maintenance page.

A dc reference voltage is supplied by each EICAS computer.The generator control unit controls the current flow based on IDGoutlet and rise temperature.Current flow varies up to a maximum of 1 ma.A voltage divider is used to send a voltage to each EICAS computer.This voltage is compared with the dc reference voltage to computeeither IDG OUT or IDG RISE temperature.The data is displayed from 0 to 180 C.

The K1 TIMER module located in the P61 panel changes theinformation requested every 0.5 second (from open - to closed thenback to open) .The closed circuit discrete represents a request for IDG RISEtemperature and the open condition a request for IDG OUTtemperature.Real time updating occurs 200 msec after the IDG OUT temperaturediscrete is sensed.Each outlet temperature pulse normally resets and starts a 5 secondcounter. If the discrete ceases for greater than 5 seconds, the, oppositevalue of IDG OUT temperature or IDG RISE temperature for both IDGsgoes blank. The remaining displayed value is continuously updated.


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1.5. DC Power System.

The dc power system supplies loads requiring dc power. Both transformerrectifier units (TRU) are located in the main equipment center.The main battery, battery charger and static inverter are located in the mainequipment center. An APU battery and battery charger are located in the aftequipment center.

The main battery/battery charger system provides dc power for the standbyand autoland systems. A separate APU battery/battery charger systemsupplies power for APU starting. Both batteries are 40 amp-hour, 20 cellnickel-cadmium, rated at 24 volt dc. In the charge mode, battery charging isconstant current and temperature compensated. A thermistor and thermalswitch, both integral to the battery, provide temperature sensing andovertemperature protection signals for charger control and shut-down.In the transformer rectifier unit mode, the battery charger supplies constantvoltage. The standby system static inverter supplies single phase AC powerfor the ac standby bus. The BAT switch controls back-up dc input inverterpower and the STBY POWER rotary switch controls auto/manual standbymodes. Each TRU normally supplies its own dc load buses. An automaticoperating dc tie control unit allows a single TRU to supply both main dcbuses. A remote control circuit breaker (RCCB)automatically closes during standby power system operation tying the mainand APU battery buses together.

1.6. System Control and Indication.

Manual or automatic source selection is provided during ground and inflightoperations from the electrical system and auxiliary electrical system controlpanels located in the flight compartment. Electrical system monitoring isdisplayed on EICAS.

DC POWER INDICATION


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TRANSFORMER RECTIFIER UNIT MAIN AND APU BATTERY CHARGING SYSTEM


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1.7. AC Power System.

During normal operations, the ac system uses the electrical output of the twoIDGs, with each IDG powering its associated channel. For ground operations,external power or the APU generator can power either or both channels.The APU generator can also be used in flight as a back-up source, should anIDG fail. The APU generator, mounted to the APU gearbox, is cooled andlubricated using APU oil. The electrical output of the APU generator is thesame as that of an IDG.Each GCU (El and E2 racks) automatically controls and protects an individualgenerating channel by monitoring source output from IDG or APU generator,serial data link to and from the BPCU and control switch positions.Main power breakers (P31, P32 and P34) control ac power flow and are all(except EPC) interchangeable.

Current transformer assemblies monitor current flow for open phase,differential protection, load monitoring and overload protection.

Electrical load control units and utility bus relays (P31 and P32) connect nonessential galley and utility bus loads to main ac buses.

A GEN CONT switch controls the associated field relay (GCR) and main powerbreaker (GCB or APB). Latching the switch (ON) closes the GCR. Unlatchingthe switch (OFF) opens the GCR. If the GEN CONT switch is unlatched, thenthe GCR is opened and closed using GEN FIELD switch. With the GEN CONTswitch latched the main power breaker is automatically opened and closed bythe associated GCU. The BTB is automatically controlled by the associatedGCU if the corresponding BUS TIE switch is latched (AUTO). The GCU andBPCU protective functions monitor system current, voltage, frequency andinput speed for open phase, overvoltage, undervoltage, shorted permanentmagnet generator, underfrequency, overfrequency, shorted rotating diode,underspeed, differential current and load shedding faults.

The hydraulic motor generator (HMG) system provides a back-up source ofelectrical power after loss of all generators. An air-driven hydraulic pumppressurizes the center hydraulic system to power the HMG. The HMG andshutoff valve are located in the left wheel well. A generator control unit (P65)performs control and protection functions. A momentary test switch (P61) isused to perform system check-out. Ac bus transfer relays connect thecaptains, left and right ac transfer buses to the hydraulic motor generatorAC output. A DC contactor connects the hydraulic motor generator dcoutput to the hot battery bus.


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ELECTRICAL SYSTEM


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2. ELECTRICAL SYSTEM PANELS.

Normal operation of the electrical power system is performed at the electricalsystem control panel and the auxiliary electrical system control panel.Both momentary and alternate action pushbutton switches are used on theelectrical panels. The alternate action switches are normally in the latched(ON) position. This allows automatic operation of the electrical systembreakers and relays under the control of the systems computers.Switch indicator lights are powered by the master dim and test system.

2.1. Electrical System Control Panel (P5).

The momentary external power switch controls the position of the externalpower contactor. A white AVAIL light indicates power is of proper quality.The white ON light illuminates when the external power contactor is closed.

The generator control switches provide a control signal which closes thegenerator control relay (GCR), and, when proper power is available, enablesautomatic closing of the generator circuit breaker (GCB). The flow bar andON legend indicate switch position. An amber OFF light illuminates when theassociated generator circuit breaker is open.

The ac bus tie switches allow manual or automatic control of the bus tiebreaker (BTB). When a switch is unlatched, the associated BTB is locked open,isolating the associated main ac bus from the ac tie bus. In this case, theAUTO indication is not visible and the amber ISLN light is illuminated.Latching an ac bus tie switch (ON) enables automatic operation of theassociated bus tie breaker. In this case, the AUTO light normally illuminatesand the ISLN light is off. If the ISLN light illuminates when the bus tie switch islatched, then a fault has tripped and locked the BTB open.

An ac BUS OFF indicator light illuminates when the associated main ac bus isde-energized.

The alternate action utility bus switches provide manual control of the powerrelays connecting utility and galley buses to the main ac buses.The ON legend is seen when the switch is latched (ON). The amber OFF lightilluminates when the associated utility bus relay (UBR) is open.

Pushing the momentary generator drive disconnect switches causes amechanical disconnection between the integrated drive generator and theengine when the associated engine fuel control switch is not off. An amberDRIVE light on the switch illuminates for a mechanical failure of the IDG orwhen the engine is not running.

The alternate action battery switch controls connection of the battery bus tothe left dc bus or the hot battery bus. The ON legend is seen when the switchis latched (ON). An amber OFF light illuminates when the battery switch isunlatched during normal ground and flight operations.For the main and APU batteries, a dedicated battery discharge lightilluminates if the battery is discharging.

The standby power mode of operation is controlled by the standby powerselector switch. To turn the switch off, push the switch in, when going fromthe AUTO to the OFF position. An amber standby power bus OFF lightilluminates when the ac or dc standby bus is unpowered.


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ELECTRICAL SYSTEM CONTROL PANEL


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2.2. Auxiliary Electrical System Control Panel.

The momentary generator field manual reset switch is pushed to open andclose the generator field control relay when the generator control switch isunlatched. A white FIELD OFF light illuminates when the generator controlrelay (GCR) is open.


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AUXILIARY ELECTRICAL CONTROL PANEL


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2.3. Ground Service/Misc Test Panel.

Ground Service Switch.A single momentary switch allows the ground service bus to be powereddirectly from the APU generator or external power. Pushing the groundservice switch connects or disconnects the APU generator or external power ifthe right main ac bus is de-energized.

A light inside the switch illuminates to indicate that the ground service bus ispowered directly from external or APU generator power.

Hydraulic Motor Generator Test Switch.A momentary toggle switch (EQUIP COOL/HYD GEN) on the right side P61panel is provided for hydraulic motor generator system testing. When toggledto the HYD GEN position, the test switch simulates loss of both main acbuses, and provides a start-up signal to the hydraulic motor generatorsystem. Release of the test switch causes system shut-down and transfer of loads back to normal bus sources.


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GROUND SERVICE / MISC. TEST PANEL


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3. AC EXTERNAL POWER SYSTEM.

3.1. System Description.

A ground power source can be connected at the airplane external powerreceptacle to supply power to the 767 ac electrical power system. Power issupplied to main load buses when the external power contactor (EPC) andcorresponding bus tie breakers (BTBs) close. The external power source alsosupplies power to the ground service and ground handling buses, using theground service select, ground service transfer, and ground handling relays.

Component Locations.An external power receptacle (P30 panel) is located on the lower fuselage,just aft of the nose gear. All other external power system components arelocated in the main equipment center. There are two control switches.An EXT PWR switch is located on the P5 overhead panel, and a groundservice switch is located on the P21 forward attendants panel.

Operation.The Bus Power Control Unit (BPCU) controls the EPC. The EPC controls theflow of external power to the ac tie bus. When external power of acceptablequality (as determined by the BPCU) is first connected, the AC CONNECTEDand PWR NOT IN USE lights on the P30 panel come on. Also, the AVAIL lighton the EXT PWR switch comes on. Pressing the momentary EXT PWR switchcloses the EPC. When the EPC closes, the ON light on the EXT PWR switchcomes on.

External power always has priority over the IDGs and APU generator whenmanually selected. If both engines are started and the IDGs are ready tosupply electrical power, then, automatically, the EPC and BTBs are trippedopen and the GCBs close. If both engines are operating, and external poweris supplying power to the main buses, cycling the generator control switches(unlatch-latch) also causes the EPC and BTBs to trip open and the GCBs toclose.

The 115 volt ac ground handling bus is automatically powered on the groundif external power is of acceptable quality. The BPCU controls the threeposition ground handling relay and automatically gives external powerpriority over the APU generator.Ground service bus power is supplied to equipment which must be poweredin both air and ground modes. This bus receives power automatically fromthe right main ac bus if that bus is powered. If the right main bus is notpowered, pressing the ground service switch allows supply of either externalpower or APU generator power (whichever is first available) to the groundservice bus. If both external and APU generator power are available when theground service switch is pressed, external power is used.If a fault exists in the external power circuit, BPCU trips the EPC to protect thepower source and loads.


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4. APU GENERATOR.

4.1. Physical Description.

The electromagnetic components of the auxiliary generator are the same asthose used in the IDG and are interchangeable except that the APU generatoris contained in its own magnesium cast housing and has a different inputspline and mounting flange. The generator weighs 61.9 pounds (27.63 kg)dry weight.

Keyhole slots allow mounting of the generator to the auxiliary power unitaccessory gearbox. An aluminium seal plate is installed between thegenerator mounting flange and gearbox drive pad. The mounting flangeincorporates three locating pins to position the generator on the APU flange.Elastomer compound inserts are installed in the seal plate OIL-IN and OILOUT ports. The input shaft incorporates a shear section that shears at 4700 300 in-lbs.

The APU generator is spray oil cooled and lubricated using APU engine oil.Pressurization, scavenging and filtering of the oil is provided by the auxiliarypower unit. Generator case pressure, 5 psig above ambient, is introducedfrom the APU gearbox through a rotating screw passageway in the inputshaft. APU generator oil is filtered by a 20/40 micron filter. The delta pressure(popout) indicator activates at 20 psid. A mechanical lockout preventsactivation when oil temperature is below 115 F (46 C). When the filter deltapressure reaches 35 psid and oil temperature above 115 F (46 C) an APUshut-down is initiated by the DP switch.

A terminal block with four stainless steel studs provides the feederconnections. A single electrical connector provides all other electricalconnections.


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5. HYDRAULIC MOTOR GENERATOR SYSTEM.

The hydraulic motor generator system provides a non-time limited back-upsource after loss of all generator electrical power.

5.1. System Description.

The hydraulic motor generator (HMG) is located in the left wheel well.The generator is driven by a hydraulic motor supplied from the centerhydraulic system. An air-driven hydraulic pump (ADP), supplied by left or rightengine bleed air, can pressurize the center hydraulic system. A motor drivenhydraulic shutoff valve provides on/off control for the HMG. Automaticactivation of the hydraulic motor generator system occurs with loss of powerto both main ac buses. A flow limiter regulates hydraulic flow to the trailingedge flaps and leading edge slats during HMG operation. Control andprotection functions are performed by the generator control unit located inthe P65 panel.A momentary test switch (P61 panel) is provided for system check-out.The HMG system operational status and electrical parameters are monitoredby EICAS.


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5.2. AC Power Indications.

Generator Load.Each GCU provides a dc voltage output to both EICAS computersproportional to the associated ac generator channel load. The GCU sensesgenerator load current from the generator current transformers.Generator load is displayed on the EICAS ELEC/HYD maintenance page forvalues between 0/0.05 to 1.50 (1.OO = 90KVA).External Power Load.The BPCU provides a dc voltage output to both EICAS computersproportional to the external power load. The BPCU senses external load fromthe ground power current transformer. The ac load for main ac, groundservice and ground handling buses is displayed for values between 0/0.1 to1.50 (1.00 = 90KVA) on the EICAS ELEC/HYD maintenance page.AC Voltage and Frequency.For each main power source (IDG, APU generator, EXT PWR, and HYDMOTOR GEN) the voltage and frequency are sensed from phase B. The singlephaseoutput of the static inverter is sensed to display voltage and frequency.All signals are supplied to both EICAS computers except the APU GENERATOR(L computer only) and HYD MOTOR GEN (R computer only). Indications aredisplayed on the EICAS ELEC/HYD maintenance page. AC voltage andfrequency are displayed between 0/100 to 130 volts ac and 0/380 to 420 Hz.

AC POWER INDICATION

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B767 200-300 BOOK 24 101 - Electrical Power

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