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DASSAULT AVIATION Falcon 7 Series Manual

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FALCON 7X
CODDE 1
DGT97831
ACRONYMS
AC
Alternative Current
APU
Auxiliary Power Unit
BC
Battery Contactor
BIT
Built In Test
BTC
Bus Tie Contactor
CAS
Crew Alerting System
CB
Circuit Breaker
CLSC
Cabin Load Shed Contactor
CMC
Central Maintenance Computer
DC
Direct Current
ECU
Electronic Control Unit
EEC
Engine Electronic Controller
FADEC
Full Authority Digital Electronic Control
FBW
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 Secondary Power Distribution Box
LH
Left Hand
LPPDB
Left Primary Power Distribution Box
LRSPDB
Left Rear Secondary Power Distribution Box
LS
Load shed
MAU
Modular Avionic Unit
MDU
Multi function Display Unit
MMEL
Master Minimum Equipment List
O/C
OverCurrent
OP
Overhead Panel
OVHT
OVerHeaT
PDCU
Power Distribution Control Unit
PFCS
Primary Flight Control System
PMA
Permanent Magnet Alternator
PPDB
Primary Power Distribution Box
RAT
Ram Air Turbine
RATC
Ram Air Turbine Contactor
ATA 24 – ELECTRICAL POWER
GENERAL
DASSAULT AVIATION Proprietary Data
02-24-05
PAGE 1 / 6
ISSUE 2

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Summary of Contents for DASSAULT AVIATION Falcon 7 Series

  • Page 1 MMEL Master Minimum Equipment List OverCurrent Overhead Panel OVHT OVerHeaT PDCU Power Distribution Control Unit PFCS Primary Flight Control System Permanent Magnet Alternator PPDB Primary Power Distribution Box Ram Air Turbine RATC Ram Air Turbine Contactor DASSAULT AVIATION Proprietary Data...
  • Page 2 Right Hand RPPDB Right Primary Power Distribution Box RRSPDB Right Rear Secondary Power Distribution Box Starter Generator Shut Off Valve SPDB Secondary Power Distribution Box SSPC Solid State Power Controller Transformer Rectifier Unit Volt Direct Courant DASSAULT AVIATION Proprietary Data...
  • Page 3 Circuit Breakers (CB). The Emergency lighting system is fitted with dedicated batteries. Refer to ATA 33 for additional information. There is no optional of equipment associated with the electrical system. DASSAULT AVIATION Proprietary Data...
  • Page 4 The "DC SUPPLY" Panel ( on the overhead panel ), The ELECtrical System Synoptic and subpage "Circuit Breaker", The TEST synoptic page, The ENG-CAS window for CAS messages, The STATus synoptic / FAULT tab for fault messages. DASSAULT AVIATION Proprietary Data...
  • Page 5 FALCON 7X 02-24-05 ATA 24 – ELECTRICAL POWER CODDE 1 PAGE 5 / 6 GENERAL DGT97831 ISSUE 2 FIGURE 02-24-05-00 - FLIGHT DECK OVERVIEW DASSAULT AVIATION Proprietary Data...
  • Page 6 Following general diagram of the electrical system shows: The different sources of electrical power, The repartition of buses in the Primary Distribution Boxes, The distribution of electrical power toward the Secondary Distribution Boxes and other loads. FIGURE 02-24-10-00 - ELECTRICAL SYSTEM DIAGRAM DASSAULT AVIATION Proprietary Data...
  • Page 7 BATTERIES On ground, two 24 V dc (25 Ah) lead-acid batteries provide the primary source of DC power to the entire distribution system prior to APU starting. The BAT1 supplies electrical power for starting the APU. DASSAULT AVIATION Proprietary Data...
  • Page 8 Two PMA (Permanent Magnet Alternator) driven by engines 1 and 2 provide an independent source of power to the Primary Flight Control system. Three PMA driven by each engine provide an independent source of AC power for their respective EEC (Engine Electronic Controller). DASSAULT AVIATION Proprietary Data...
  • Page 9 Order of priority is the following: The APU generator will provide power to the distribution system only once the GPU is off line, The GPU is automatically disconnected from electrical buses when one engine-driven generator comes on line. DASSAULT AVIATION Proprietary Data...

  • Page 10: Power Distribution

    RH PPDB contains: RH MAIN and ESSential buses, BATT2 bus Power is distributed: from the two Primary Power Distribution Boxes (PPDB), Toward: The four Secondary Power Distribution Boxes (SPDB), Galley and cabin loads, Hot loads, Some PFCS loads. DASSAULT AVIATION Proprietary Data...
  • Page 11 The LH and RH Primary Power Distribution Boxes contain: Essential, Main and Battery buses, Powers Distribution Control Unit ( PDCU ), Engines and APU Generators GCU Cards, Lines contactors , Bus Tie Contactors (BTC), Thermal fuses and Circuit Breakers (CB). DASSAULT AVIATION Proprietary Data...
  • Page 12 In accordance with load shedding and fault isolation logic. The load shedding is controlled by the two PDCU by opening contactors when electrical power sources can not supply all airplane loads. Refer to "System Protections" section for these load-shedding logics. DASSAULT AVIATION Proprietary Data...

  • Page 13: Maintenance

    PDCU and all Generator GCU. The Pilot has priority over PDCU automation, except in case of short circuit or overload protection. MAINTENANCE: Failures and fault detected by the system are sent in the form of ARINC message to the Central Maintenance Computer (CMC). DASSAULT AVIATION Proprietary Data...
  • Page 14 CODDE 1 DESCRIPTION - SUPPLEMENTARY INFORMATION ISSUE 2 DGT97831 EQUIPMENT LOCATION Equipment locations correspond to a physical segregation of components, power supplies, wiring routing, main and essential controls. FIGURE 02-24-15-00 - ELECTRICAL SYSTEM - LOCATION OF EQUIPMENT DASSAULT AVIATION Proprietary Data...

  • Page 15: Electrical Power Distribution

    HYDR 3B DEPRESS PRECOLLER ENG 2 NOSE FAN HYDR 3A DEPRESS HYDR PCB RH QA RECORDER OVERHEAD PANEL 3A HYDR PCB LH HYDR PRESS #B RADIO ALT 2 OXYGENE MASK 3 HSECU HYDR ST-BY PUMP READING LIGHT RH DASSAULT AVIATION Proprietary Data...
  • Page 16 ST-BY BOOST 3 ST-BY BOOST 2 THIRD OXYGEN MASK TLA DISC RH TLA DISC LH TOILET SMOKE AFT UPPER ANTICOL TOILET SMOKE FWD VIDL-G 1 WSHIELD BACKUP VHF 1 WSHIELD RH WOW LH WOW RH WSHIELD LH DASSAULT AVIATION Proprietary Data...
  • Page 17 BC 1/2: Bus Contactor 1/2 BTC 1/2/3: Bus Tie Contactor 1/2/3 CLSC 1/2:Cabin Load Shed Contactor 1/2 GLC 1/2/3: Generator Line Contactor for Generator 1/2/3 GLSC: Galley Load Shed Contactor LS 1/2:Load Shed 1/2 FIGURE 02-24-15-01 - PPDB DETAILED CONTENT DASSAULT AVIATION Proprietary Data...

  • Page 18: Engine-Driven Generator

    The RAT is fully operative (400A rating) until airplane speed is above 140 kt. Aircraft Speed - KEAS Assuming a 15% Dynamic Pressure Loss at the RAT FIGURE 02-24-15-02 - RAT ELECTRICAL OUTPUT DEPENDING ON AIRPLANE SPEED DASSAULT AVIATION Proprietary Data...
  • Page 19 The RAT deployment actuator is a spring loaded shock absorber actuator that mechanically deploys the RAT. The deployment is activated by the manual release handle positioned in the floor on the left side of the copilot's seat rail. DASSAULT AVIATION Proprietary Data...
  • Page 20 PAGE 8 / 12 CODDE 1 DESCRIPTION - SUPPLEMENTARY INFORMATION ISSUE 2 DGT97831 DISTRIBUTION DETAILED DESCRIPTION Following figure shows the detailed description of distribution from the PPDB to the SPDB and other loads. FIGURE 02-24-15-04 - DISTRIBUTION DETAILED DESCRIPTION DASSAULT AVIATION Proprietary Data...

  • Page 21: Initial Conditions

    DGT97831 ISSUE 2 DISTRIBUTION DURING AIRPLANE POWER UP The following diagrams show the position of the contactors during the various normal ground operations. INITIAL CONDITIONS All contactors are open. FIGURE 02-24-15-05 - DISTRIBUTION - INITIAL CONDITIONS DASSAULT AVIATION Proprietary Data...
  • Page 22 ATA 24 – ELECTRICAL POWER PAGE 10 / 12 CODDE 1 DESCRIPTION - SUPPLEMENTARY INFORMATION ISSUE 2 DGT97831 BATTERY MASTERS SELECTED FIGURE 02-24-15-06 - DISTRIBUTION - BATTERY MASTERS SELECTED EXTERNAL POWER CONNECTED FIGURE 02-24-15-07 - DISTRIBUTION - EXTERNAL POWER CONNECTED DASSAULT AVIATION Proprietary Data...
  • Page 23 DESCRIPTION - SUPPLEMENTARY INFORMATION DGT97831 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 - DISTRIBUTION - APU START WITH EXTERNAL POWER DASSAULT AVIATION Proprietary Data...
  • Page 24 GPU has priority over APU. FIGURE 02-24-15-10 - DISTRIBUTION - APU ON LINE WITH GROUND POWER UNIT APU GENERATOR ON LINE / GROUND POWER UNIT OFF FIGURE 02-24-15-11 - DISTRIBUTION - APU ON LINE WITHOUT GROUND POWER UNIT DASSAULT AVIATION Proprietary Data...

  • Page 25: Controls And Indications

    The C/B STATUS sub-page page of the ELECtrical synoptic page, on ground, for changing electronic CB status. DC SUPPLY CONTROL PANEL Pilots can manually control the Electrical System via the switches in the DC SUPPLY overhead panel. FIGURE 02-24-20-00 - DC SUPPLY SECTION OF THE OVERHEAD PANEL DASSAULT AVIATION Proprietary Data...
  • Page 26 Generator is GEN 3 disconnected: connects Commanded generator 3 to by the the LH MAIN crewmembers. OFF: allow to manually disconnect the Generator is not corresponding connected due to a generator malfunction, while engine is running. DASSAULT AVIATION Proprietary Data...
  • Page 27 Two-position system detects an disconnected trip magnetic anomaly (high reverse switch current) BAT 1 and 2 act as reset switches when Abnormal the fault is cleared situation: BAT1 BAT1 is connected Disconnected while it should disconnected DASSAULT AVIATION Proprietary Data...
  • Page 28 On ground only: allows external power to supply LH ESS bus light Abnormal pushbutton operation: extenal power is connected and at least one engine generator is Flash connected. Off: airplane not powered by external power. Push Off DASSAULT AVIATION Proprietary Data...
  • Page 29 Buses abnormally Push TIED untied Buses normally tied Buses abnormally Isolates Push unlighted isolated LH / RH MAIN buses from auto respective LH / RH ESS buses Buses isolated as commanded Buses abnormally tied Push ISOL DASSAULT AVIATION Proprietary Data...
  • Page 30 PDCU, ELEC synoptic closed if condition is acceptable. OFF: contactor is disconnected SHED: allows to recover some pre determined loads after automatic shed. For further information on "Long push pushbuttons", refer to CODDE 1 chapter 1 DASSAULT AVIATION Proprietary Data...
  • Page 31 No specific indication LH ESS bus equipment on the ELEC synoptic Push OFF (not connected) Push on (connected) Supplies power to No specific indication RH ESS bus equipment on the ELEC synoptic Push OFF (not connected) DASSAULT AVIATION Proprietary Data...
  • Page 32 CONTROLS AND INDICATIONS ISSUE 2 DGT97831 TO ACTIVATE CONTROL FUNCTION SYNOPTIC TO DEACTIVATE Resets RAT GEN in case of disconnection No indication due to over-current momentary pushbutton EMERGENCY CONTROL PANEL FIGURE 02-24-20-01 - EMERGENCY CONTROL PANEL, ON PEDESTAL DASSAULT AVIATION Proprietary Data...
  • Page 33 The release handle used to manually deploy the RAT is located on the cockpit floor to the left side of the copilot's seat. The release handle is protected from inadvertent release by a cover. FIGURE 02-24-20-02 - MANUAL RELEASE COVER AND MANUAL RELEASE HANDLE DASSAULT AVIATION Proprietary Data...
  • Page 34 FIRE CONTROL PANEL The generators will be confirmed as disconnected when the corresponding engine FIRE guarded pushbuttons on the Fire Control Panel is depressed. FIGURE 02-24-20-04 – GENERATOR DISCONNECTION ON FIRE CONTROL PANEL INDICATIONS DASSAULT AVIATION Proprietary Data...
  • Page 35 The STATus synoptic / FAULT tab for fault messages. "DC SUPPLY" PANEL NOTE The DC supply panel provides system feedback indications for EXTernal POWER connection, bus tied or isolated, and Generator contactor "OFF". ELEC SYNOPTIC PAGE FIGURE 02-24-20-05 - ELEC SYNOPTIC PAGE DASSAULT AVIATION Proprietary Data...
  • Page 36 For each battery, temperature indication is given by a pointer position on a temperature tape and by a digital readout. The scale is colored in white below 56°C, in amber above 56°C. BAT1 FIGURE 02-24-20-07 - BATTERY TEMPERATURE DASSAULT AVIATION Proprietary Data...
  • Page 37 LH and RH buses. When a generator supplies the bus, the digital readout is colored in amber below 25 V and above 30 V. This range is different in case of RAT operation. DASSAULT AVIATION Proprietary Data...
  • Page 38 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 buses voltages, Generators and batteries amperage. FIGURE 02-24-20-10 - STATUS/ FAULT SYNOPTIC PAGE DASSAULT AVIATION Proprietary Data...
  • Page 39 The CHANGE SSPC STATE soft keys are not usable in flight (greyed out). The description of the controls is described in sub-section 02-24-40. FIGURE 02-24-20-11 – AIR CONDITIONING BREAKERS STATUS PAGE ON GROUND ONLY DASSAULT AVIATION Proprietary Data...
  • Page 40 FALCON 7X ATA 24 – ELECTRICAL POWER PAGE 16 / 16 CODDE 1 CONTROLS AND INDICATIONS ISSUE 2 DGT97831 FIGURE 02-24-20-12 – SELECTED SYSTEM PULL DOWN MENU FIGURE 02-24-20-13 – RH AVION MASTER BREAKERS STATUS PAGE DASSAULT AVIATION Proprietary Data...
  • Page 41 The avionics equipments are connected to the MAIN and ESS buses through the master pushbuttons. Power supply of each avionics equipment is provided in following table. FIGURE 02-24-25-00 - DC SUPPLY SECTION OF THE OVERHEAD PANEL DASSAULT AVIATION Proprietary Data...
  • Page 42 SATAFIS MRC NIM 2 TCAS RH MKB VHF3 RH GP VHF 2 VIDL-G 2 NOTE In case LH ESS bus power is lost, avionics equipment connected through LH INIT pushbutton is fed by LH MAIN bus. DASSAULT AVIATION Proprietary Data...

  • Page 43: System Monitoring

    ISSUE 2 SYSTEM MONITORING Monitoring of the following parameters is provided by the system: Generator load and voltage, Battery voltage, recharge current and temperature, Bus voltage. Refer to CODDE 2 for a complete list of CAS messages. DASSAULT AVIATION Proprietary Data...
  • Page 44 Their status can be modified by software from the cockpit or by connecting to the SPDB. DASSAULT AVIATION Proprietary Data...
  • Page 45 The PDCU automatically disconnects ground power to the aircraft distribution system if voltage or current are outside the limits range by opening GPC 1 (see figure 02-24-15-07) and by tripping the ON-OFF toggle switch in the ground power. DASSAULT AVIATION Proprietary Data...

  • Page 46: Ground Operation

    28 volt DC plug into the power receptacle, select the ground power ON/OFF toggle action switch to ON, enter the flight deck and select EXT POWER pushbutton on the OP. Refer to Ground Servicing manual. DASSAULT AVIATION Proprietary Data...
  • Page 47 To active the GSB the batteries must be set to the down position (off) and the GND SERVICING switch located on the maintenance panel must be set to the upper position. FIGURE 02-24-40-01 - MAINTENANCE PANEL - GND SERVICING SWITCH Refer to Ground Servicing manual. DASSAULT AVIATION Proprietary Data...
  • Page 48 Red vertical line U1, Green vertical line U1, Green vertical line U2, Green vertical line U3. If only red line is lighted then the tested battery is not usable. FIGURE 02-24-40-02 - MAINTENANCE PANEL - BATT SWITCH AND INDICATOR DASSAULT AVIATION Proprietary Data...
  • Page 49 OUT soft key is selectable, and the LOCK soft key is not selectable (since it is already in this state). It can go from LOCK to OUT, but not from LOCK to IN. DASSAULT AVIATION Proprietary Data...
  • Page 50 ATA 24 – ELECTRICAL POWER CODDE 1 PAGE 5 / 6 GROUND OPERATION DGT 97831 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 Proprietary Data...