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787 Flight Crew Operations Manual
Electrical -
System Description
6.20.6 Boeing Proprietary
The highest degree of redundancy is provided to the C1 and C2 power supplies.
This ensures the flight controls that may require center hydraulic power from a
RAT deployment also have electrical power.
Flight Control Power Schematic
Electrical Power Distribution and Conversion
Electrical Power Distribution
The airplane electrical system is largely a traditional 115 Vac and 28 Vdc system,
with relatively small portions optimized with 235 Vac, ±270 Vdc, and ±135 Vdc.
Electrical power is distributed to the various loads through the Primary Power
Distribution System (PPDS) or the Remote Power Distribution System (RPDS).
Flight Control
Power Supply
Power Source Priority
1 2 3
C1 PMG 1 Capt Flight Instrument Bus Hot Battery Bus
C2 PMG 3 F/O Flight Instrument Bus Hot Battery Bus
L PMG 2 L 28 Vdc Bus 10 Minute Battery
R PMG 4 R 28 Vdc Bus 10 Minute Battery
CAPT F/O
VFSG
L1
PMG
1
PMG
2
PMG
3
PMG
4
VFSG
L2
VFSG
R1
VFSG
R2
VFSG
C1 C2 L R
HBB
L 28 10 MIN R 28
BATT
10 MIN
BATT
F L I G H T C O N T R O L P O W E R S U P P L Y
Primary Power Source Backup Power Sources
PRELIMINARY
HBB - Hot Battery Bus
787 Flight Crew Operations Manual
Electrical -
System Description
Boeing Proprietary 6.20.7
Loads with high power requirements are distributed by the PPDS, while those
loads with lower power requirements can be distributed by the RPDS. There are
17 remote units located throughout the airplane, distributing either 28 Vdc or 115
Vac power to various airplane loads.
787 Flight Crew Operations Manual
Electrical -
System Description
6.20.8 Boeing Proprietary
787 Electrical System Schematic
.
HBB - Hot Battery Bus
Condition: VFSGs supplying all airplane power.
APU, Standby, or EP Power
Primary Power
EP - External Power
PRELIMINARY
L1 235 L2 235 R1 235 R2 235
L1
ATRU
L2
ATRU
L1 270 L2 270
R1
ATRU
R2
ATRU
R1 270 R2 270
RAT
AFT EP
BKUP
L
ATU
L
TRU
C1
TRU
C2
TRU
R
TRU
R
ATU
L 115 R 115
L 28 R 28
CAPT F/O
L1 L2 L R
ENG
GEN
APU GEN
R1 R2
ENG
GEN
FWD EP L FWD EP R
LTB
RTB
HBB
MAIN
BATT
APU HBB
APU
BAT
BAT
CHG
BAT
CHG
787 Flight Crew Operations Manual
Electrical -
System Description
Boeing Proprietary 6.20.9
Electrical Power Conversion
The Power Conversion System (PCS) consists of components that transform
airplane power from one type to another to supply power to various airplane buses.
The PCS includes the following units:
• Four (4) Autotransformer Rectifier Units (ATRU)
• Four (4) Transformer Rectifier Units (TRU)
• Two (2) Autotransformer Units (ATU)
• One (1) Main Battery and Charger
• One (1) APU Battery and Charger
• One (1) Start Power Unit (SPU)
• Four (4) Electric Brake Power Supply Units (E-BPSU)
Autotransformer Rectifier Unit (ATRU)
ATRUs receive at their input either:
• 235 Vac from the main AC buses, then output ±270 Vdc, or
• 115 Vac aft external ground power, then output ±270 Vdc
The ±270 Vdc output supplies the motor controllers (see ±270 Vdc Buses in this
section) with power.
Transformer Rectifier Unit (TRU)
TRUs receive at their input:
• 235 Vac from the main buses, and then output 28 Vdc
The 28 Vdc output supplies power to the four 28 Vdc power buses (left 28 Vdc,
right 28 Vdc, captains instrument, first officers instrument), and the E-BPSUs.
Autotransformer Unit (ATU)
ATUs receive at their input either:
• 235 Vac from the main AC buses, and then output 115 Vac, or
• 115 Vac forward external ground power at their input, and then output 235
Vac
The 115 Vac output supplies power to the two 115 Vac buses. The 235 Vac output
supplies power to the remainder of the 235 Vac system, and operates on the ground
when only 115 Vac forward external power is available to the airplane.
787 Flight Crew Operations Manual
Electrical -
System Description
6.20.10 Boeing Proprietary
Main Battery and Battery Charger
The main battery powers the hot battery bus, providing power to the airplane
　
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