DASSAULT AVIATION Falcon 7 Series User manual

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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
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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

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DESCRIPTION ISSUE 2
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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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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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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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DESCRIPTION DGT97831
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Control and protection of contactors and buses within the Primary Power 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 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).

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SECONDARY POWER DISTRIBUTION BOX (SPDB)
Each of the SPDB performs similar functions. The main difference is the location in the
airplane, and the variation in the number of connections to the airplane wiring. The four
SPDB:
- Receive electrical power inputs from LH and RH PPDB,
- Distribute electrical power to Equipments loads via feeder cables,
- Ensure protection of cables and monitor the status of supply to the different airplane
equipment.
Each SPDB contains:
- Power supply,
- Circuit breakers,
- Electronic CB (SSPC) for the rear SPDB.
BATTERY BUSES
The battery buses are powered as soon as the dedicated battery is installed and plugged in.
Regardless of battery switch position, the battery bus provides electrical power 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 Service Bus powers a limited number of RH ESS bus equipment without the
need to power up the entire electrical distribution.
The Ground Service Bus is accessible via the maintenance panel.
The Ground Service Bus operation is limited to 3 minutes by a circuit timer.
NOTE
With ambient temperatures below 0°c do not operate the Ground Service Bus (Battery Load).
POWER DISTRIBUTION CONTROL UNIT (PDCU)
Each Primary Power Distribution Box (PPDB) is controlled through a Primary Distribution
Control Unit (PDCU) that manages:
- Batteries, buses ties, load shed cabin, galley, GCU contactors,
- 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.
¾Refer to "System Protections" section for these load-shedding logics.

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DESCRIPTION - SUPPLEMENTARY INFORMATION ISSUE 2
DASSAULT AVIATION Proprietary Data
DESIGN PRINCIPLES
The electrical system was designed considering technology, architecture, safety and
maintenance design principles.
TECHNOLOGY:
Since a low level of loads is required by airplane equipment, the electrical system circuit is a
28Vdc design. This allows simplification for circuit control and a good level of reliability
without significant increase in weight.
Electronic CB (named SSPC) are used because their status can be modified by software,
without direct access to the electronic CB.
ARCHITECTURE:
If the engines are running, the engines controllers and PFCS remain powered by dedicated
power sources even if the airplane distribution system is not available.
Non time limited electrical power is available in case of all engines out or all generators
failed, by a RAT.
In case of normal generation failure, the 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 from the PPDB in order to facilitate load-
shedding logic.
Some PFCS loads are directly powered from the PPDB in order to be segragated from other
system loads and to allow load shedding of SPDB in case of loss of engine-driven
generators.
SAFETY:
The segregation of electrical energy to various points in the airplane is provided by two
PPDB (Primary Power Distribution Box) and four SPDB (Secondary Power Distribution Box).
During flight, the left buses are segregated from right buses. So, in case of over-voltage or
short-circuit inducing severe under voltage on one side, the other side is not affected.
In normal and abnormal conditions an automatic control of electrical system is
simultaneously performed by the two 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).

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DESCRIPTION - SUPPLEMENTARY INFORMATION DGT97831
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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

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ELECTRICAL POWER DISTRIBUTION
Equipment load distribution is provided in following table:
LH MAIN BUS LH ESS BUS RH ESS BUS RH MAIN BUS
ADSP 1 CH A HEAT
ADSP 1 CH A
ADSP 2 CH A HEAT
ADSP 2 CH A
AMSAC (AMM1, AMM3)
ANTICOL LIGHT LH
AUDIO PANEL 3
AUTOTROTTLE
BAG VENT LH
CCD CH B
DATA LOADER
DISPLAY UNIT LH
DME 1
EMERG LIGHT LH
ENG 2 FADEC CH B
ENG 2 IGN CH B
FASTEN BELTS
FBW TEST E2
GALLEY
GEAR CH 2A
GND BAG VENT
GUIDANCE PANEL LH
HF 1
HF 1 R/E
HGS COMP FAN
HUD HGS
HUD OHU
HUMIDIFIER
HYDR PRESS #A
HYDR PRESS #C
ICE DETECTOR 1
LANDING LIGHT LH
LFSPDB MAIN
LGSCU CH 2
LIGHT CTRL LH
LOGO LIGHT LOWER
LRSPDB MAIN
MASTER WARNING &
CAUTION LH
MAINTENANCE EEC
MAU 1 CH A
MAU 2 CH B
NAV LIGHT LH
NO SMOKING
NOSE FAN
OVERHEAD PANEL 3A
OXYGENE MASK 3
ADF 1
ADSP 3 CH A HEAT
ADSP 3 CH A
ADSP 4 CH A
ADSP 4 CH A HEAT
AMSEC BALD
AMSEC EMM (LS)
AMSEC LH
APU SOV
AUDIO PANEL LH
ATC 1
BAG ISOL VALVE CH1
BAT 1 HEATER
BAT 1 MONITOR
BOOST PUMP 2
BSCU #1
CAB VENT VALVE RH
CAB. OXYGENE AUTO
CCD LH CH A
COMBINE RECORD. 1
DIPLAY UNIT LH
DISPLAY UNIT UPPER
EFCU (normal, first aid)
ENG 1 ANTI-ICE
ENG 1 FADEC CH A
ENG 1 IGN CH A
ENG 2 SOV
ENG 3 ANTI-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
HYDR 2B DEPRESS
HYDR 3A DEPRESS
HYDR PCB LH
HSECU
ADSP 3 CH B HEAT
ADSP 3 CH B
ADSP 4 CH B
ADSP 4 CH B HEAT
AHRS 2
AMSEC EMM (RS)
AMSEC RH
APU COMPUTER
APU IGNITION
AUDIO PANEL RH
B/U STAB
BAG COMP FAN
BAG COMP FAN CTRL
BAG COMP SMOKE
BAG ISOL VALVE CH2
BAT 2 HEATER
BAT 2 MONITOR
BSCU #2
CAB VENT VALVE LH
CCD RH CH A
COMBINE RECORD. 2
DISPLAY UNIT RH
EBHA
EFCU (override)
ELT
ENG 1 SOV
ENG 2 ANTI-ICE
ENG 2 FADEC CH A
ENG 2 IGN CH A
ENG 3 SOV
FBW B/U UNIT
FBW LF E4
FBW RF E4
FBW RR E4
FIRE EXT BAG COMP
FIRE EXT ENG 1
FIRE EXT ENG 3
FIRE EXT R. COMP
FIRE PANEL RH
FLCU RH
FQMC RH
FUEL PCB STBY
GCU 2 PWR
HYDR 3B DEPRESS
HYDR PCB RH
HYDR PRESS #B
HYDR ST-BY PUMP
ADF 2
ADSP 1 CH B
ADSP 1 CH B HEAT
ADSP 2 CH B
ADSP 2 CH B HEAT
AFT FLUSH
AMSAC AMM2
ANTICOL LIGHT RH
ATC 2
AUDIO PANEL RH
BAG VENT RH
BOOST PUMP 1
BOOST PUMP 3
BSCU #2
CCD CH B
COCKPIT PRINTER
DISPLAY UNIT LOWER
DME 2
EMERG LIGHT RH
ENG 1 FADEC CH B
ENG 1 IGN CH B
ENG 3 FADEC CH B
ENG 3 IGN CH B
ENG 1,2,3 VIBRATION
FBW TEST E1
GUIDANCE PANEL RH
GND VENT VALVE
HF 2
HF 2 R/E
ICE DETECTOR RH
LANDING LIGHT RH
LGSCU CH 2
LIGHT CTRL RH
LOGO LIGHT LOWER
LSS
MAU 1 CH B
MASTER WARNING &
CAUTION RH
MKB RH
MRC 2 NIM
NAV LIGHT (RH)
OVERHEAD PANEL 3B
POTABLE WATER
PRECOLLER ENG 2
QA RECORDER
RADIO ALT 2
READING LIGHT RH

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DESCRIPTION - SUPPLEMENTARY INFORMATION DGT97831
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LH MAIN BUS LH ESS BUS RH ESS BUS RH MAIN BUS
PRECOLLER ENG 1
PDCU MAIN LH
PRECOLLER ENG 3
RADIO ALT 1
READING LIGHT LH
REAR STROBE
SATCOM HPA
SATCOM SDU
TAT 1 HEAT
TCAS
TEMP PROBE FAN
TRUST REVERSER
VHF 3
WEATHER RADAR
WING LIGHT LH
WOW RH
WSHIELD B/U LH
WSHIELD CTRL LH
IRS 1
LFSPDB ESS
LGSCU CH 1
LIGHTING MINIM. LH
LRSPDB ESS
MASTER WARNING &
CAUTION RH
MAU 1 CH A
MKB LH
MRC 1 NIM
OVERHEAD PANEL 1A
OVERHEAD PANEL 2B
OXYGENE MASK LH
PDCU
PRECOLLER ENG 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 LH
WSHIELD LH
IRS 2
IRS 3
LGSCU CH 2
LH PDCU B/U PWR
LH WARNING RH
LIGHTING MINIM. RH
MAGNETOMETER
MASTER WARNING &
CAUTION LH
MAU 2 CH A
OXYGENE MASK RH
OVERHEAD PANEL 2A
OVERHEAD PANEL 1B
PRECOLLER ENG 3
RAIN REPELLANT RH
RAT DEPLOY
RFSPDB ESS
RRSPDB ESS
SEAT/PEDAL RH
SFAU BACKUP
SFD
SIDESTICK LH
SIDESTICK RH
SLAT EMERG CTRL
ST-BY BOOST 2
TLA DISC RH
TOILET SMOKE AFT
TOILET SMOKE FWD
WSHIELD BACKUP
WSHIELD RH
WOW RH
REAR TOILET SMOKE
RECIRC VALVE
RFSPDB MAIN
RRSPDB MAIN
TAT 2 HEAT
TAXI LIGHT
TPMU
TOILETS SMOKE
VHF 2
VIDL-G 2
WATER COMPRESSOR
WATER REHEAT HOSE
WSCU
WSHIELD B/U RH
WING LIGHT RH
WOW LH

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DESCRIPTION - SUPPLEMENTARY INFORMATION ISSUE 2
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GENERATION 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 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

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ENGINE-DRIVEN GENERATOR
Three Generator Control Units (GCU) provide current and voltage control and protection for
their associated generator:
- Control: the GCU regulates the voltage at 28.5 VDC. It monitors the output current in
order to comply with peak power protection (above 500 A continuous rating). It also
provides generator output control in order to balance the voltage between several
generators, when connected in parallel,
- Protection: the GCU provides the PDCU with an overcurrent detection signal in order to
start the fault isolation sequence,
The GCU automatically disconnects its associated generator when the electric load limit is
reached or in case of an over-voltage or abnormal 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 monitors the output current to
400 A, with a maximum of 600 A for 2 minutes. It also provides generator output control
in order to balance the voltage between several generators, when connected in parallel,
- Protection: the GCU automatically disconnects the generator when the electric load limit
is reached or in case of an over-voltage.
RAM AIR TURBINE
When the airplane speed is low, the 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.
The RAT is fully operative (400A rating) until airplane speed is above 140 kt.
0
2
4
6
8
10
12
90 100 110 120 130 140 150 160 170
Aircraft Speed - KEAS
Assuming a 15% Dynamic Pressure Loss at the RAT
Power at TRU Output - kW
FIGURE 02-24-15-02 - RAT ELECTRICAL OUTPUT DEPENDING ON AIRPLANE SPEED

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DESCRIPTION - SUPPLEMENTARY INFORMATION ISSUE 2
The RAT system includes seven separate components:
- The Ram Air Turbine, which houses the generator and its heater,
- The Generator Control Unit (GCU),
- The Transformer Rectifier Unit (TRU),
- 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 - RAT IN THE DEPLOYED POSITION
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

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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