Boeing 777 System (How does each system work together)_1 - created from Mind Map

Page 1

To make the big machine fly in the air we need a lot of Thrust

1. The Engine burns the the Fuel (mix with Air) to get the Thrust.

2. In the Process we get the bleed air from the exhausted air and Electric power and Hydraulic power(which produce from both engine and the pressure from bleed air as well)

3. We use the bleed air to pressurize the cabin,pumps, warm thel and also the source for anti-Ice, The electrical power to drive the pump and feed the aircraft for need of AC and DC power. and Hydraulic power to make the movement of giant Flight control system possible Under the Command of Autopilot the throttle system.

Engines and APU

The EEC (electronic engine control )the the full authority

The EEC has normal and alternate mode

Under Alternate mode we have Soft and Hard mode

The EEC command Approach idle in flight if Engine anti-ice is operating, Flaps in landing position (25 or 30), One hydraulic air-driven demand pump is INOP, and the flaps are out of the UP position

The Opposite engine bleed air valve is closed

Start is aborted for restart on GND for

and no Restart for

Engine Ignition

Auto Relight Fuction

Engine Fuel System

Engine Oil System

Thrust Reverser

Engine Failure Alert

Instrument Navigation & Communication

Auto Pilot and FMC

Gear and Break

Warming Systems

Hydraulic

Three Independent system

Left Center Right

Left and Right System each has

Primary Engine driven PUMP

Electrical Demand PUMP

Hydraulic L & R Demand pumps position at auto, and pumps run when ?

Takeoff and landing (flaps extended)

System or primary pump pressure drops

On GND right pump operates continously

Center hydraulic system has how many pumps

2 Electrical powered pumps

Designated C1 and C2 pumps

Electrial

Electrical Load Management system

Main AC power

(L&R) IDG

Primary and secondary external power

APU generator

External power ( Primary and Secondary)

Standby Power

2 Back up Generator (BUG)

SPD not regulated(constant SPD)

out put is regulated to 400 Hz by a converter

Come on line and stay on one slightly below idle PRM

There is Converter receives input from both backup generator at all time but can select and process inputs from only one BUG or the other, not both Simultaneously

Permanent Magnet Generators (PMG)

two contained in each BUG

Supply AC power to fight control Power Supply Assemblies(PSA)

PSAs convert power from AC to DC for flight control computerese

Output is dedicated to flight controls cannot be diverted to elsewhere

DC Electrical system

Main DC Electrical system

PFDs NDs GPS ADIRU

Flight Control DC Electrical system

Transformaer Rectifier Units ( TRUs)

L main DC

R main DC

C1 TRU to CA flight instrument bus

C2 TRU to FO flight instrument Bus

Standby Electrical System

Supplies AC and DC to selected key items

Main Battery Standby Inverter

RAT

C1 and C2

AIR

Bleed Air

Engine bleed air valves close automatically when

Loss of Bleed source Bleed air over temperatureBleed air overtemperature

Bleed air overpressure

Bleed air duct lick

ENG fire handle is pulled

Ground air cart supplying air

APU bleed air Primary for

Engine start

Ground air conditioning

Pressurezation for no ENG bleed Take off

APU TO PACK selection for take off accomplished through FMC

We have 2 Identical controler on Each Pachs

Standby Cooling mode

Duck Leak and Overheat Detection

Fuel

One center tank

L and R wing tank

2 AC pumps in each tank

Any single pumps has enough output to supply fuel to operate one engine under all conditions

Left Main Tank DC pump

Nitrogen Generation Sysem

Fire Protection

Flight Controls

Primary

Secondary

Direct

Mechanical back up

Flight Envelope Protection

Stall Protection

Overspeed Protection

Roll Evelope Bank Protection

Thrust Asymmetry Compensation

Wheel-Rudder Crosstie

Yaw Damping

Rudder and Aileron Trim Panel

Stabilizer Trim

Flaps and Slats

Primary

Secondary

Alternate

Anti Ice & Rain