DASSAULT AVIATION Falcon 7 Series Manuel utilisateur
FALCON 7X 02-24-05
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DGT97831
ATA 24 – ELECTRICAL POWER
GENERAL ISSUE 2
DASSAULT AVIATION Proprietary Data
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
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GENERAL DGT97831
DASSAULT AVIATION Proprietary Data
RFSPDB 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
SPDB Secondary Power Distribution Box
SSPC Solid State Power Controller
TRU Transformer Rectifier Unit
VDC Volt Direct Courant
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INTRODUCTION
The Falcon 7X uses 28 Volts DC power for operation of the various systems installed in the
airplane.
The electrical system is supplied by:
- Three engine-driven generators,
- Two Batteries,
- A RAT in some emergency cases.
The Primary Flight Control System and Engine Electronic Controller are also powered by
dedicated Permanent Magnet Alternators.
On ground, the electrical system can also be supplied by:
- An Auxiliary Power Unit (APU) driven generator,
- An external 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 MAIN buses,
- Batt 1 and Batt 2 buses.
Electrical Power is distributed from the two Primary Power Distribution Boxes (PPDB) toward
four Secondary Power Distribution Boxes (SPPD) installed forward and aft of the airplane, on
the Right and Left Hand sides.
Protection of equipment, cables, and electrical buses is provided by different control boards,
by fuses and by mechanical and electronic Circuit Breakers (CB).
The Emergency lighting system is fitted with dedicated batteries.
¾Refer to ATA 33 for additional information.
There is no optional of equipment associated with the electrical system.
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GENERAL DGT97831
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FLIGHT DECK OVERVIEW
CONTROLS
Crew has control over the electrical system via:
- The " DC SUPPLY" Panel on the overhead panel,
- The CB sub page of the ELEC synoptic,
- Two switches on the Emergency Panel (aft end of the pedestal) for RAT inhibit and "RH
ESS ISOL",
- The RAT Manual Release Handle (right side of the pedestal),
- The Fire Control Panel in case of engine fire, to confirm 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
Boxes. The "CB page" of the ELEC synoptic allows modifying status of electronic CB on ground
only. In flight, the "CB page" provides the status of the mechanical and electronic CB.
INDICATIONS
Indications related to the Electrical System configuration and status are displayed in:
- 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.
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ATA 24 – ELECTRICAL POWER
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FIGURE 02-24-05-00 - FLIGHT DECK OVERVIEW
DASSAULT AVIATION Proprietary Data
FALCON 7X 02-24-10
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ATA 24 – ELECTRICAL POWER
DESCRIPTION ISSUE 2
DASSAULT AVIATION Proprietary Data
GENERAL
The Electrical Power system provides following functions:
- Electrical 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 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
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POWER GENERATION AND ENERGY STORAGE
GENERAL
In flight, the 28Vdc generation is provided by:
- 3 engine driven generators: 12kW (500 A),
- A RAT (Ram Air Turbine) which can provide a non time limited electrical power (9 kW)
to LH and RH Essential Buses.
On ground, the 28Vdc generation is provided by:
- An APU starter-generator: 12 kW (400 A),
- A 28Vdc GPU which can be connected to the airplane to energize the entire electrical
system.
Additionally,
- Two PMA (Engines 1 and 2) provide an independent source of electrical power for the
PFCS,
- Three PMA (Engines 1, 2 and 3) provide an independent source of electrical power to
Engine Electronic Controllers EEC.
Electrical energy is stored in two 24 V dc (25 Ah) lead-acid batteries.
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 case of a generator failure. They are regulated at 28.5 VDC by a Generator Control Unit
(GCU) associated to each engine.
Each GCU provides current and voltage control and protection for its associated generator.
APU GENERATOR
The Auxiliary Power Unit (APU) is equipped with a starter-generator. As a generator and for
ground use only, it provides DC power to airplane systems and batteries charging.
The APU is rated at 12 kW and regulated at 28.5 VDC by its associated GCU.
The APU Generator Control Unit (GCU):
- Provides current and voltage control and protection for its associated generator,
- Controls APU start sequence.
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.
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DESCRIPTION ISSUE 2
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NOTE
Very low-charged batteries cannot be connected to the buses,
as their contactors need at least 18 VDC to close.
As soon as one generator is connected, batteries are charging and flatten generator
electrical spikes.
The batteries are also used in case of main generators loss, during the RAT deployment and
additionally just before landing when low airspeed does not allow the RAT to provide
sufficient electrical power.
In flight, the batteries can provide electrical power for a load of 200 A for 7 minutes.
RAM AIR TURBINE
The Ram Air Turbine (RAT) system provides a non-time limited electrical power source 9kw
to the RH and LH Ess bus for continued safe flight and landing in case of:
- Loss of all three engines (automatic deployment),
- Loss of all three engine generators (automatic deployment),
- Loss of engine 2 generator and short on LH ESS bus (manual deployment),
- 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 RAT generator output voltage is
reduced, and batteries start providing power. In this manner both the RAT and batteries
power all the required airplane loads during this phase.
NOTE
A safety lock pin with a REMOVE PIN BEFORE FLIGHT flag is used
to preclude inadvertent deployment of the RAT on ground.
The RAT is fitted with a RAT generator heater that is powered during all phases of flight,
except when the RAT is deployed and in operation. The purpose of the heater is to prevent
moisture within the air gap of the generator from freezing.
When deployed, the RAT induces a moderate level of noise and vibration in the cockpit.
Once the RAT is deployed, it will have to be restowed on ground with a restow pump.
PMA
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).
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ATA 24 – ELECTRICAL POWER
DESCRIPTION DGT97831
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GPU
An approved 28 VDC Ground Power Unit (GPU) may be used for prolonged periods to
power the DC system in order to facilitate maintenance and 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 or engine-driven generators. 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.
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ATA 24 – ELECTRICAL POWER
DESCRIPTION ISSUE 2
DASSAULT AVIATION Proprietary Data
POWER DISTRIBUTION
GENERAL
The different electrical power sources provide power to six buses:
- BATT1 bus: powered by battery 1 or APU generator,
- LH MAIN bus: powered by Engines 1 and 3 generators,
- LH ESSential bus: powered by BATT1 bus,
- BATT2 bus: powered 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 Servicing Bus.
The six buses are gathered in two Primary Distribution Boxes:
- LH PPDB contains:
o LH MAIN and ESSential buses,
o BATT1 bus
- RH PPDB contains:
o RH MAIN and ESSential buses,
o BATT2 bus
Power is distributed:
- from the two Primary Power Distribution Boxes (PPDB),
- Toward:
o The four Secondary Power Distribution Boxes (SPDB),
o Galley and cabin loads,
o Hot loads,
o Some PFCS loads.
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