DASSAULT AVIATION Falcon 7 Series, Manual

Page 1: ...BW Fly By Wire GCU Generator Control Unit GLC Generator Line Contactor GLSC Galley Load Shed Contactor GPC Ground Power Contactor GPU Ground Power Unit GSB Ground Service Bus LFSPDB Left Front Seconda...

Page 2: ...DB Right Front Secondary Power Distribution Box RH Right Hand RPPDB Right Primary Power Distribution Box RRSPDB Right Rear Secondary Power Distribution Box S G Starter Generator SOV Shut Off Valve SPD...

Page 3: ...xternal 28 DC GPU Ground Power Unit The different electrical power sources provide power to six buses installed in two Primary Distribution Boxes LH ESSential and LH MAIN buses RH ESSential and RH MAI...

Page 4: ...firm generator disconnection The Servicing sub page of TEST synoptic for ground servicing bus NOTE Circuit Breakers are not accessible in the cockpit CB are installed in the different Distribution Box...

Page 5: ...FALCON 7X 02 24 05 CODDE 1 PAGE 5 6 DGT97831 ATA 24 ELECTRICAL POWER GENERAL ISSUE 2 FIGURE 02 24 05 00 FLIGHT DECK OVERVIEW DASSAULT AVIATION Proprietary Data...

Page 6: ...power generation and energy storage Electrical power distribution Protection of electrical components Following general diagram of the electrical system shows The different sources of electrical powe...

Page 7: ...ries ENGINE DRIVEN GENERATORS Engine driven generators are driven by the accessory gearbox of each engine Engine driven generators are rated at 12 kW but they can provide 15 kW for a limited time in c...

Page 8: ...oyment Loss of engine 2 generator and BUS TIE contactor failed open manual deployment When operative the RAT will charge the airplane batteries When the airplane speed is low approach and landing the...

Page 9: ...d servicing The GPU may also be used For APU starting recommended power is 1 000 A To charge the batteries The GPU will not provide power to the distribution system simultaneously with APU generator o...

Page 10: ...by battery 2 RH ESSential bus powered by BATT2 bus and potentially by the RAT generator RH MAIN bus powered by Engine 2 generator An additional bus is considered for preflight use only Ground Servici...

Page 11: ...Distribution Boxes PPDB is performed by Primary Distribution Control Units PDCU FIGURE 02 24 10 01 POWER DISTRIBUTION PRIMARY POWER DISTRIBUTION BOX PPDB The LH and RH Primary Power Distribution Boxe...

Page 12: ...ower directly to The Ground Service Bus GSB The refueling system The engine FIRE extinguishers secondary discharge The fuel shut off valves The access door lighting GROUND SERVICE BUS The Ground Servi...

Page 13: ...RAT system was selected rather than using the APU generator in flight this way the electrical system architecture is not affected by fuel contamination The galley and cabin load are directly powered f...

Page 14: ...N SUPPLEMENTARY INFORMATION DGT97831 DASSAULT AVIATION Proprietary Data EQUIPMENT LOCATION Equipment locations correspond to a physical segregation of components power supplies wiring routing main and...

Page 15: ...TI ICE ENG 3 FADEC CH A ENG 3 IGN CH A FBW LF E3 FBW LR E3 FBW RF E3 FIRE EXT APU FIRE EXT ENG 2 FIRE PANEL LH FLCU LH FQMC LH FUEL PCB NORMAL GCU 1 PWR GCU 3 PWR GUIDANCE PANEL LH HYDR 1A DEPRESS HYD...

Page 16: ...1 RAIN REPELLANT LH RAT GCU TEST RAT HEATER REV PANEL LIGHT RH PDCU B U PWR RH WARNING LH SEAT PEDAL LH SFAU ST BY BOOST 1 ST BY BOOST 3 THIRD OXYGEN MASK TLA DISC LH UPPER ANTICOL VIDL G 1 VHF 1 WOW...

Page 17: ...ERATION DETAILED DESCRIPTION Following figure shows the detailed description of contactors within the PPDB BC 1 2 Bus Contactor 1 2 BTC 1 2 3 Bus Tie Contactor 1 2 3 CLSC 1 2 Cabin Load Shed Contactor...

Page 18: ...al condition APU GENERATOR The APU Generator Control Unit GCU provides current and voltage control and protection for its associated generator Control the GCU regulates the voltage at 28 5 VDC and mon...

Page 19: ...The deployment actuator The re stow pump ground operation only The up lock The manual release handle Deployment Actuator Turbine RAT Bay Door Door Link Aircraft fuselage Generator FIGURE 02 24 15 03...

Page 20: ...CRIPTION SUPPLEMENTARY INFORMATION DGT97831 DASSAULT AVIATION Proprietary Data DISTRIBUTION DETAILED DESCRIPTION Following figure shows the detailed description of distribution from the PPDB to the SP...

Page 21: ...RY INFORMATION ISSUE 2 DASSAULT AVIATION Proprietary Data DISTRIBUTION DURING AIRPLANE POWER UP The following diagrams show the position of the contactors during the various normal ground operations I...

Page 22: ...RICAL POWER DESCRIPTION SUPPLEMENTARY INFORMATION DGT97831 DASSAULT AVIATION Proprietary Data BATTERY MASTERS SELECTED FIGURE 02 24 15 06 DISTRIBUTION BATTERY MASTERS SELECTED EXTERNAL POWER CONNECTED...

Page 23: ...DESCRIPTION SUPPLEMENTARY INFORMATION ISSUE 2 APU START WITHOUT EXTERNAL POWER FIGURE 02 24 15 08 DISTRIBUTION APU START WITHOUT EXTERNAL POWER APU START WITH EXTERNAL POWER FIGURE 02 24 15 09 DISTRIB...

Page 24: ...MATION DGT97831 DASSAULT AVIATION Proprietary Data APU RUNNING WITH GROUND POWER UNIT ON LINE GPU has priority over APU FIGURE 02 24 15 10 DISTRIBUTION APU ON LINE WITH GROUND POWER UNIT APU GENERATOR...

Page 25: ...RH ESS The RAT Manual Release Handle right side of the pedestal TEST synoptic page for the RAT test The Fire Control Panel in case of engine fire to confirm generator disconnection The Maintenance pa...

Page 26: ...tomatically control the corresponding generator Generator is not connected conformaly to normal operation Engine is stopped Generator is disconnected Commanded by the crewmembers GEN 1 connects genera...

Page 27: ...magnetic switch Two position trip magnetic switch BAT 1 connects battery 1 bus to the LH ESS bus and contactor is controlled by PDCU NOTE Battery 1 supplies the battery bus whatever battery switch po...

Page 28: ...PTIC On airplane powered by external power Push On System feedback Abnormal operation airplane powered by external power and fault conditions or current 400 A Flash Abnormal operation extenal power is...

Page 29: ...ON TO DEACTIVATE SYNOPTIC Buses normally untied Push unlighted auto Buses abnormally tied Buses tied as commanded Ties up LH ESS and RH ESS buses Push TIED Buses abnormally untied Buses normally tied...

Page 30: ...s acceptable OFF contactor is disconnected and also GALLEY one SHED allows to recover some pre determined loads after automatic shed OFF No specific indication on the ELEC synoptic Auto SHED Sheds gal...

Page 31: ...ed No specific indication on the ELEC synoptic Push on connected Supplies power to RH MAIN bus equipment Push OFF not connected No specific indication on the ELEC synoptic Push on connected Supplies p...

Page 32: ...INDICATIONS DGT97831 DASSAULT AVIATION Proprietary Data TO ACTIVATE CONTROL FUNCTION TO DEACTIVATE SYNOPTIC momentary pushbutton Resets RAT GEN in case of disconnection due to over current No indicati...

Page 33: ...ptic Normal off RAT AUTO pushbutton on Emergency Panel prohibites the automatic deployment of RAT Push INHIBIT No specific indication on the ELEC synoptic Advisory CAS message is displayed ELEC RAT AU...

Page 34: ...ing contactor Placing the CCD cursor on the respective soft key and keeping the ENTER button pressed triggers the respective test An advisory ELEC RAT TEST IN PROGRESS CAS message is displayed when th...

Page 35: ...he overhead panel The ELECtrical System Synoptic and subpage Circuit Breaker The ENG CAS window for CAS messages The STATus synoptic FAULT tab for fault messages DC SUPPLY PANEL NOTE The DC supply pan...

Page 36: ...n by a digital readout and colored in amber above 330A NOTE A negative current designates a charging current FIGURE 02 24 20 06 BATTERY AMMETER Battery Temperature Indication For each battery temperat...

Page 37: ...bove 400 A NOTE For any generator or battery 0 A is displayed on synoptic ammeters when actual current is between 10 A and 10 A FIGURE 02 24 20 08 DC GENERATOR AMMETER Buses Voltmeter LH ESS RH ESS LH...

Page 38: ...GT97831 DASSAULT AVIATION Proprietary Data FIGURE 02 24 20 09 BUSES VOLTMETER STATUS SYNOPTIC PAGE At the top of the STATus page following information on the electrical system are summarized LH and RH...

Page 39: ...button The pull down menu button turn green to indicate selected for display An amber background behind the ATA number indicates at least one circuit breaker or SSPC is in the OUT position In the case...

Page 40: ...E 16 16 CODDE 1 ISSUE 2 ATA 24 ELECTRICAL POWER CONTROLS AND INDICATIONS DGT97831 DASSAULT AVIATION Proprietary Data FIGURE 02 24 20 12 SELECTED SYSTEM PULL DOWN MENU FIGURE 02 24 20 13 RH AVION MASTE...

Page 41: ...LEMENTARY INFORMATION ISSUE 2 DASSAULT AVIATION Proprietary Data CONTROLS The avionics equipments are connected to the MAIN and ESS buses through the master pushbuttons Power supply of each avionics e...

Page 42: ...RH ESS BUS RH MAIN BUS ADF 1 ATC 1 VIDL G 1 Audio Panel 3 Data Loader DME 1 HUD MAU 2B Radio Alt 1 MRC NIM 1 RH CCD Chan A SATAFIS TCAS VHF3 LH CCD Chan A LH GP MAU 1A MAU 2A RH CCD Chan B ADF 2 ATC 2...

Page 43: ...ROTECTIONS ISSUE 2 DASSAULT AVIATION Proprietary Data SYSTEM MONITORING Monitoring of the following parameters is provided by the system Generator load and voltage Battery voltage recharge current and...

Page 44: ...of lightning attachments Static dischargers are installed on the trailing edge of each wing and horizontal stabilizer LOAD SHEDDING LOGIC In flight main load shedding logics are PFCS loads never load...

Page 45: ...verheated by a trip magnetic switch which opens and disconnects the battery In that case the BAT 1 and or BAT 2 magnetic switches trip off and a CAS message is displayed Battery reverse current overch...

Page 46: ...is controlled from the Overhead Panel A switched circuit breaker located inside the ground power panel adjacent to the ground power receptacle provides protection and will automatically trip if power...

Page 47: ...e airplane systems in purpose to check or test them The checks or tests are done through the servicing page accessible through the TEST synoptic page To active the GSB the batteries must be set to the...

Page 48: ...with avionics power off The BATT switch has 3 positions One steady middle no test 2 momentary o Upper position allows to check BATT 2 o Lower position allows to check BATT 1 The test feedback is disp...

Page 49: ...is on an electrical load where the state is IN then the IN soft key is non actionable since it is already in this state the OUT soft key is selectable and the LOCK soft key is non selectable It can g...

Page 50: ...40 CODDE 1 PAGE 5 6 DGT 97831 ATA 24 ELECTRICAL POWER GROUND OPERATION ISSUE 2 NOTE It is necessary to click the soft key for at least 1 5 seconds to change the status of an SSPC DASSAULT AVIATION Pr...