ELECTRICAL SYS

Question 1

WHICH SYSTEM POWERS THE ELECTRICAL SYS OF THE B787?

Answer 1

ENGINE START

PRESSURIZATION

WING ANTI-ICE

STABILIZER TRIM

WHEEL BRAKE SYSTEM

Question 2

WHICH TYPE OF FREQUENCIES IS THE ELECTRICAL SYSTEM USING?

Answer 2

PRIMARLY 115VAC ,28 DCV AND SOME LIMITED NUMBER OF SYSTEMS USING 235 Vac

Question 3

WHAT ARE THE ELECTRICAL POWER SOURCE IN ELECTRICAL SYS?

Answer 3

4 VFSG (VARIABLE FREQUENCY STARTER/GENERATOR)

2 VFSG APU

3 EXT POWER RECEPTACLE

1 RAT

MAIN BATTERY

APU BATTER

3 FLIGHT CONTROL PMG (PERMANENT MAGNET GENERATOR)

2 EEC PMA

Question 4

HOW MANY VFSG HAS EACH ENGINE?

Answer 4

2 EACH OF 235 VAC

Question 5

WHICH SOURCE CAN PROVIDE ELECTRICAL POWER TO START THE ENGINE?

Answer 5

APU,EXT POWER OR OTHER ENGINE RUNNING

Question 6

HOW CAN BE DISCONNECTED EACH VFSG IN THE ENGINE?

Answer 6

AUTOMATICALLY OR MANUALLY, ONCE DISCONNECTED ONLY ENGINEER CAN CONNECT IT AGAIN

Question 7

WHAT THE APU GENERATORS CAN PROVIDE?

Answer 7

ELEC POWER ON GROUND AND IN FLIGHT

Question 8

HOW MANY VFSG HAS AN APU?

Answer 8

2

Question 9

WHO CAN POWER THE START OF THE APU?

Answer 9

EXT POWER, APU BATTERY OR ENGINE GENERATED POWER.

Question 10

WHICH GENERATOR IS USED TO START THE APU WHEN USING APU BATTERY?

Answer 10

THE RIGHT GENERATOR ONLY

Question 11

How many EXT power receptacles are installed on B787

Answer 11

Total of 3, two FWD and 1 in the AFT

Question 12

When GROUND HANDLING mode is energized ?

Answer 12

Only one connection required to power this mode

Question 13

TO POWER THE ENGINE START HOW MANY kVA ARE REQUIRED?

Answer 13

90 Kva

Question 14

HOW TO START THE ENGINE USING EXT POWER?

Answer 14

EITHER USING THE FWD 2 ONLY AND IN THIS CONFIGURATION ANY ENGINE CAN BE STARTED FIRST OR USING 3 CONNECTIONS BUT IN THAT CASE THE RIGHT ENGINE MUSTBE STARTED FIRST.

Question 15

HOW MANY STARTED GENERATORS ARE USED TO START THE ENGINE IN EXT PWR?

Answer 15

1 VFSG IS USED

Question 16

WHEN THE RAT DEPLOY AUTOMATICALLY IN FLIGHT?

Answer 16

LOSS OF BOTH ENGINE

LOSS OF ALL THREE HYDRAULICS

LOSS OF ELECTRIC POWER OF CPT AND FO INSTRUMENTS

LOSS OF ALL 4 EMP AND A FAULTS OCCURS ON THE FLIGHT CONTROLS SYS ON APPROACH

LOSS OF ALL 4 EMP AND ENGINE FAILS IN TAKE OFF OR LANDING

Question 17

THE MAIN BATTERY SUPPLY POWER TO?

Answer 17

AIRPLANE POWER UP

APU START (ASSIST APU BATTERY)

REFUELING OPERATIONS

TOWING OPERATIONS

ELECTRIC BRAKING (AS BACKUP)

CPT FLIGHT INSTRUMENTS (UNTIL RAT DEPLOYMENT)

Question 18

APU BATTERY ON GROUND PROVIDES POWER TO?

Answer 18

APU START

NAVIGATIONS LIGHTS

Question 19

WHICH PROTECTION SYSTEMS IS PROVIDED FOR THE BATTERIES?

Answer 19

AN OVERCHARGING OF FAULT MONITORING SYSTEM IS PROVIDED TO STOP CHARGING OR ISOLATING THE BATTERY IF NECESSARY.

Question 20

IF EITHER BATTERY EXPERIENCES A SEVERE FAILURE WHAT WILL HAPPEN?

Answer 20

HEAT AND GASSES WILL BE DISCHARGED OVERBOARD

Question 21

HOW MANY PMG (PERMANENT MAGNET GENERATOR) ARE INSTALLED IN B787

Answer 21

TOTAL OF 3

Question 22

WHICH SYS THE PMG ARE POWERING?

Answer 22

FLIGHT CONTROLS ELECTRONICS

Question 23

WHICH IS A SECONDARY POWER SOURCE FOR THE FLIGHT CONTROLS SYSTEM?

Answer 23

28 VDC BUS DISTRIBUTION SYSTEM AND MAIN BATTERY

Question 24

HOW MANY PMA (PERMANENT MAGNETIC ALTERNATORS) ARE AVAILABLE ON B787?

Answer 24

2 ENGINE DRIVE PMA

Question 25

WHAT THE PMA ARE POWERING?

Answer 25

EEC

Question 26

WHICH IS A SECONDARY POWER SOURCE FOR THE EEC?

Answer 26

THE 115 VAC BUS DISTRIBUTION SYSTEM

Question 27

HOW MANY RPDU WE HAVE ON BOARD?

Answer 27

17

Question 28

HOW MANY 235 VAC BUSES WE HAVE ON BOARD?

Answer 28

4 MAIN BUSSES L1 L2 R1 R2

Question 29

ON GRD FROM WHICH SOURCE THE BUSSES ARE ENERGIZED?

Answer 29

IF ONLY EXT POWER IS CONNECTED , FROM THE 115 VAC BUS SYSTEM, IF APU IS ON FROM THE APU 235 VAC

Question 30

WITH APU AND ENGINE RUNNING HOW THE 235 VAC BUSSES ARE POWERED

Answer 30

2 EACH

Question 31

How does it work the power distribution system?

Answer 31

High load are distribute by bus while the low load are using RPDU