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 AIRCRAFT SY

 AIRCRAFT SYSTEMS STEMS 11 - 111 - 1

P

PMMDDG G 774477--44000 0 AAOOMM DDO O NNOOT T DDUUPPLLIICCAATTEE RReevviissiioon n – – 2266JJUULL0055

AIRCRAFT SYSTEMS

AIRCRAFT SYSTEMS

TABLE OF CONTENTS

TABLE OF CONTENTS

S SUUBBJJEECCTT PPAAGGEE

INTENTIONA

INTENTIONALLY BLANKAIR CONDITIONING

LLY BLANKAIR CONDITIONING / PRESSURIZATION...6

/ PRESSURIZATION...6

AIR CONDITIONING

AIR CONDITIONING /

/ PRESSURIZ

PRESSURIZATION...

ATION...

...

...7

7

Overview Overview ... ... ... ... ... 77 Cabin Temperature...7

Cabin Temperature...7

 Air Conditioning  Air Conditioning Packs...Packs... ... ... ... 77 Pack Control...8

Pack Control...8

Pack Hi Flow Mode...8

Pack Hi Flow Mode...8

Recirculation Fans...8

Recirculation Fans...8

Trim Air...8

Trim Air...8

Equipment Equipment CoolingCooling ... ... ... ... ...9...9

Gasper Gasper OperationOperation ... ... ... ... ....9....9

Humidifie Humidifie ... ... ... ... ... 99 Secondary Secondary EICAS EICAS IndicationsIndications ... ... ... ...9...9

Master Master Target Target Temperature:Temperature: ... ... ... ... 99 Pressurization Pressurization OverviewOverview ... ... ... ... 1010 Cabin Cabin Altitude Altitude ControlControl... ... ... ... 1010 Landing Altitude...10

Landing Altitude...10

Outflow Valves...10

Outflow Valves...10

Cabin Cabin Altitude Altitude WarningWarning ... ... ... ... 1010  AIR CONDITION  AIR CONDITIONING/PRESSURING/PRESSURIZATION EICAS IZATION EICAS MESSAGES....MESSAGES.... ... ... 1111

ELECTRICA

ELECTRICAL SYSTEM

L SYSTEM ...

...

...

...12

...12

Overview Overview ... ... ... ... ... 1212  AC Power  AC Power ... ... ... ... ..1..122 IDG Drive Disconnects...12

IDG Drive Disconnects...12

 APU / Externa  APU / External Powerl Power ... ... ... ... 1313 Split Split System System BreakerBreaker ... ... ... ... 1313 Power Power Switching/PreferencSwitching/Preferencinging ... ... ... ... 1414  AC Bus Tie Sys  AC Bus Tie System...tem... ... ... ... ... 1414  Autoland Configuration  Autoland Configuration ... ... ... ... ..1..144 Batteries Batteries ... ... ... ... ... 1414 DC DC PowerPower ... ... ... ... ... 1414 DC Tie Bus...15 DC Tie Bus...15 Battery Battery BussesBusses ... ... ... ... ... 1515 Main Standby Power...15

Main Standby Power...15

 APU Standby Pow  APU Standby Powerer ... ... ... ... 1515 Transfer Busses...15

Transfer Busses...15

Ground Handling Bus...16

Ground Handling Bus...16

Ground Service Bus...16

Ground Service Bus...16

Utility Utility and and Galley Galley BussesBusses ... ... ... ... 1616 Load Load SheddingShedding ... ... ... ... ...1717 EICAS EICAS ELEC ELEC SynopticSynoptic ... ... ... ... 1717 ELECTRICAL CONTROL PANEL DIAGRAMS...18

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11

11 - - 2 2 AIRCRAFT AIRCRAFT SYSTEMSSYSTEMS

SECONDARY

SECONDARY EICAS EICAS DISPLAY DISPLAY - - ELECTRICAL ELECTRICAL SYSTEM SSYSTEM SYNOPTICYNOPTIC ... ... 1919

Bus Equipment Overview...20

Bus Equipment Overview...20

 APU Battery Bus  APU Battery Bus EquipmentEquipment ... ... ... ... 2020  APU Hot Battery  APU Hot Battery Bus Equipment...Bus Equipment... ... ... ... 2020 Main Main Battery Battery BusBus ... ... ... ... ... 2020 Main Hot Battery Bus...20

Main Hot Battery Bus...20

Main Standby Bus...20

Main Standby Bus...20

 APU Standby Bus...  APU Standby Bus... ... ... ... ... 2020  AC Bus 1  AC Bus 1 ... ... ... ... ... 2020  AC Bus 2  AC Bus 2 ... ... ... ... ... 2121  AC Bus 3  AC Bus 3 ... ... ... ... ... 2121  AC Bus 4  AC Bus 4 ... ... ... ... ... 2121 DC Bus 1...21 DC Bus 1...21 DC Bus 2...21 DC Bus 2...21 DC Bus 3...22 DC Bus 3...22 DC Bus 4...22 DC Bus 4...22 ELECTRICAL ELECTRICAL SYSTEM SYSTEM EICAS EICAS MESSAMESSAGESGES ... ... ... 2222

ENGINES AND ENGINE SYSTEMS

ENGINES AND ENGINE SYSTEMS ...

...

...23

...23

Overview Overview ... ... ... ... ... 2323 Electronic Engine Controls...23

Electronic Engine Controls...23

EEC EEC NORMAL NORMAL ModeMode ... ... ... ... 2424 EEC ALTERNATE Mode...24

EEC ALTERNATE Mode...24

Engine Engine IndicationIndication ... ... ... ... ... 2525 Engine Engine VibrometersVibrometers ... ... ... ... ... 2525 Engine Fuel System...25

Engine Fuel System...25

Engine Engine Starter/Ignition Starter/Ignition SystemsSystems ... ... ... ... 2525 Oil Oil SystemSystem ... ... ... ... ... 2626 Reverse Reverse Thrust Thrust CapabilitiesCapabilities ... ... ... ... 2626 ENGINE START/CONTROL SWITCHES...28

ENGINE START/CONTROL SWITCHES...28

PRIMARY PRIMARY / SECONDAR/ SECONDARY EICAS Y EICAS ENGINE DIENGINE DISPLAYSSPLAYS ... ... ...2929 ENGINE ENGINE THRUST THRUST REVERSREVERSER ER ACTIVATION ACTIVATION DIAGRAMDIAGRAM ... ... .3.311

FIRE DETECTION / SUPPRESSI

FIRE DETECTION / SUPPRESSION SYSTEMS

ON SYSTEMS ...

...32

...32

Fire/Overheat Indications...32

Fire/Overheat Indications...32

Cargo Compartment Fire Detection/Suppression...32

Cargo Compartment Fire Detection/Suppression...32

Lower Lower Cargo Cargo Fire Fire SwitchesSwitches ... ... ... ... 3333  APU Fire Detect  APU Fire Detection/Suppression...ion/Suppression... ... ... ... 3333  APU Fire/Shuto  APU Fire/Shutoff Handle...ff Handle... ... ... ... ... 3333  APU BTL DISCH  APU BTL DISCH LightLight ... ... ... ... 3333 Using Using Fire Fire HandlesHandles ... ... ... ... 3333 Engine Engine Fire Fire Detection/SuppDetection/Suppressionression ... ... ... ...3333 Engine Engine Fire/Shutoff Fire/Shutoff HandlesHandles ... ... ... ... 3434 Lavatory Fire Detection/Suppression...34

Lavatory Fire Detection/Suppression...34

Wheel Well Fire Detection...34

Wheel Well Fire Detection...34

FIRE/Overheat FIRE/Overheat TestingTesting ... ... ... ... 3434 Importance of Procedures...34

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 AIRCRAFT SY

 AIRCRAFT SYSTEMS STEMS 11 - 311 - 3

FLIGHT

FLIGHT CONTROLS...

CONTROLS...

...

...37

...37

Overview: Overview: ... ... ... ... ... 3737 Elevators Elevators ... ... ... ... ... 3737 Elevator Position Indication...37

Elevator Position Indication...37

Horizontal Stabilizer...37

Horizontal Stabilizer...37

Important Note on Trimming...37

Important Note on Trimming...37

 Ailerons  Ailerons ... ... ... ... ... 3737 Spoilers Spoilers ... ... ... ... ... 3838 Spoiler Position Indication...38

Spoiler Position Indication...38

Speedbrake Handle Function...38

Speedbrake Handle Function...38

Rudder Rudder ... ... ... ... ... 3939 FLIGHT FLIGHT CONTROL CONTROL CONFIGURACONFIGURATIONTION ... ... ... 4040 Leading and Trailing Edge Flaps...41

Leading and Trailing Edge Flaps...41

Trailing Edge Flaps...41

Trailing Edge Flaps...41

Leading Edge Slats...41

Leading Edge Slats...41

Flap Position Indicators...42

Flap Position Indicators...42

FLIGHT FLIGHT CONTROLS CONTROLS EICAS EICAS MESSAGES:MESSAGES: ... ... ... 4343

FUEL

FUEL SYSTEM...

SYSTEM...

...

...

...44

...44

Overview Overview ... ... ... ... ... 4444 Fuel Pump Systems...44

Fuel Pump Systems...44

Fueling Fueling ... ... ... ... ... 4444 Fuel Management...45

Fuel Management...45

Main Tank Fuel Pumps...45

Main Tank Fuel Pumps...45

Main Tank 2 and 3 Override/Jettison Pumps...45

Main Tank 2 and 3 Override/Jettison Pumps...45

Center Center Wing Wing Tank Tank Fuel Fuel PumpsPumps ... ... ... ... 4545 Crossfeed Manifold and Valves...45

Crossfeed Manifold and Valves...45

Reserve Tank Transfer Valves...46

Reserve Tank Transfer Valves...46

Main Tank 1 and 4 Transfer Valves...46

Main Tank 1 and 4 Transfer Valves...46

Operating With Center Wing Tank Fuel...46

Operating With Center Wing Tank Fuel...46

Operating With Center Wing Tank Empty...47

Operating With Center Wing Tank Empty...47

Fuel Fuel Quantity Quantity Indicating Indicating System System (FQIS)(FQIS) ... ... ... 4747 Fuel Jettison System...47

Fuel Jettison System...47

Fuel Fuel TransferTransfer ... ... ... ... ... 4848 Secondary Secondary EICAS EICAS Fuel Fuel System System SynopticSynoptic ... ... ... 4848 FUEL SYSTEM AND FUEL SYSTEM AND EICAS FUEICAS FUEL SYSTEM DEEL SYSTEM DEPICTIPICTIONON ... ... ..4949 FUEL SY FUEL SYSTEM STEM CONTROL CONTROL PANEL PANEL DIAGRAMDIAGRAM ... ... ... 4949 FUEL SY FUEL SYSTEM STEM CONTROL CONTROL PANEL PANEL DIAGRAMDIAGRAM ... ... ... 5050 FUEL CON FUEL CONTROL PANETROL PANEL / L / FUEL PUFUEL PUMP SCHMP SCHEMATICEMATIC ... ... ... 5151 FUEL SYSTEM EICAS MESSAGES...52

FUEL SYSTEM EICAS MESSAGES...52

HYDRAULI

HYDRAULIC

C SYSTEM

SYSTEM...

...

...

...53

...53

Overview Overview ... ... ... ... ... 5353 Hydraulic Reservoirs...53

Hydraulic Reservoirs...53 Engine

Engine Driven Driven PumpsPumps ... ... ... ... 5353  Auxiliary Demand Pu

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11

11 - - 4 4 AIRCRAFT AIRCRAFT SYSTEMSSYSTEMS

EICAS

EICAS STAT STAT Screen Screen Hydraulic Hydraulic IndicatorsIndicators ... ... ... 5454

Hydraulic Quantity Warning...54

Hydraulic Quantity Warning...54

SECONDARY EICA SECONDARY EICAS DISPLAY - HYDRAULIC SYSTEM SYNS DISPLAY - HYDRAULIC SYSTEM SYNOPTIC...OPTIC... ... 5555 Secondary Secondary EICAS EICAS HYD HYD DisplayDisplay ... ... ... ... 5555 HYD Display Examples...55

HYD Display Examples...55

Hydraulic Hydraulic Reservoir Reservoir Quantity Quantity IndicatorIndicator ... ... ... 5555 HYDRAULIC HYDRAULIC SYSTEM SYSTEM CONTROL CONTROL PANELPANEL ... ... ... 5656 SYS SYS FAULT FAULT LightLight ... ... ... ... ... 5656 DEM PUMP PRESS Light...56

DEM PUMP PRESS Light...56

Demand Pump Selector...56

Demand Pump Selector...56

ENG ENG PUMP PUMP SwitchSwitch... ... ... ... ...5656 ENG ENG PUMP PUMP PRESS PRESS lightlight ... ... ... ... 5656 HYDRAULIC SYSTEM EICAS MESSAGES...57

HYDRAULIC SYSTEM EICAS MESSAGES...57

ICE AND R

ICE AND RAIN PROTECTION

AIN PROTECTION...

...

...

...58

58

Overview Overview ... ... ... ... ... 5858 Probe Probe HeatHeat ... ... ... ... ... 5858 Nacelle Nacelle Anti-IceAnti-Ice ... ... ... ... ... 5858

LANDING GEAR

LANDING GEAR ...

...

...

...60

...60

Overview Overview ... ... ... ... ... 6060 Landing Gear...60 Landing Gear...60 Landing Landing Gear Gear Position Position IndicatorsIndicators ... ... ... ... 6060 Expanded Expanded Gear Gear Disagree Disagree IndicatorIndicator ... ... ... ...6060 Landing Landing Gear Gear Brake Brake SystemSystem ... ... ... ... 6060  Antiskid...  Antiskid... ... ... ... ... 6161  Autobrakes  Autobrakes ... ... ... ... ... 6161 Ground Ground SteeringSteering ... ... ... ... ... 6161 Landing Landing Gear Gear Configuration Configuration WarningWarning ... ... ... ...6262 Secondary EICAS Secondary EICAS Display - Display - Landing Landing Gear SynopticGear Synoptic... ... ... 6262

LIGHTING

LIGHTING SYSTEM

SYSTEMS...

S...

...

...63

...63

Overview Overview ... ... ... ... ... 6363 Storm Storm LightsLights ... ... ... ... ... 6363 Circuit Breaker/Overhead Panel Dimmer...63

Circuit Breaker/Overhead Panel Dimmer...63

Glare shield/Panel Flood Dimmer...63

Glare shield/Panel Flood Dimmer...63

Dome Dome LightLight ... ... ... ... ... 6363  Aisle Stand Panel  Aisle Stand Panel Flood Dimmer...Flood Dimmer... ... ... 6363 Landing Landing LightsLights ... ... ... ... ... 6363 Runway Turnoff Lights...63

Runway Turnoff Lights...63

Runway Turnoff Lights...63

Runway Turnoff Lights...63

Taxi Lights...63 Taxi Lights...63 Beacon Lights...63 Beacon Lights...63 Navigation Lights...63 Navigation Lights...63 Strobe

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 AIRCRAFT SY

 AIRCRAFT SYSTEMS STEMS 11 - 511 - 5

PNEUMATIC SYS

PNEUMATIC SYSTEMS

TEMS ...

...

...

...65

...65

Overview Overview ... ... ... ... ... 6565 External Air...65

External Air...65

 APU Bleed A  APU Bleed Air...ir... ... ... ... ... 6565 Engine Bleed Air...65

Engine Bleed Air...65

Engine Engine Bleed Bleed Air Air ValveValve ... ... ... ... 6565 Engine Bleed Switch...65

Engine Bleed Switch...65

Nacelle Nacelle Anti-IceAnti-Ice ... ... ... ... ... 6666 Distribution Distribution ... ... ... ... ... 6666 Pneumatic Pneumatic System System IndicationsIndications ... ... ... ... 6666 SECONDARY SECONDARY EICAS DISPLEICAS DISPLAY - PNEUMAAY - PNEUMATIC SYSTEM SYNTIC SYSTEM SYNOPTICOPTIC ... ... 6767 Secondary EICAS Pneumatic Indications...67

Secondary EICAS Pneumatic Indications...67

Pneumatic System Control Panel...67

Pneumatic System Control Panel...67

Isolation Valve Switch...67

Isolation Valve Switch...67

SYS FAULT Lights...67

SYS FAULT Lights...67

 APU Bleed A  APU Bleed Air Switchir Switch ... ... ... ... 6767 Engine Engine Bleed Bleed Air Air SwitchesSwitches ... ... ... ... 6767

GLOBAL NAVIGATION SYSTEMS

GLOBAL NAVIGATION SYSTEMS ...

...

...68

...68

Overview Overview ... ... ... ... ... 6868 Inertial Reference Units...68

Inertial Reference Units...68

CENTER

CENTER PEDES

PEDESTAL

TAL SYSTEM

SYSTEMS

S ...

...

...

...69

69

Overview Overview ... ... ... ... ... 6969 Communications Communications RadiosRadios ... ... ... ... 6969 Navigation Radio Signal Monitoring...69

Navigation Radio Signal Monitoring...69

 Autobrakes:  Autobrakes: ... ... ... ... ... 6969 Flight Control Trimming:...69

Flight Control Trimming:...69 Transponder

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11

11 - - 6 6 AIRCRAFT AIRCRAFT SYSTEMSSYSTEMS

INTENTIONALLY BLANK

INTENTIONALLY BLANK

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 AIRCRAFT SY

 AIRCRAFT SYSTEMS STEMS 11 - 711 - 7

AIR CONDITIONING / PRESSURIZATION

AIR CONDITIONING / PRESSURIZATION

Overview:

Overview: To provide cabin air To provide cabin air  conditioning, air from the pn

conditioning, air from the pn eumaticeumatic manifold is directed to three

manifold is directed to three air conditioningair conditioning packs.

packs. Ozone is Ozone is removed by cremoved by catalyticatalytic

converters, and after passing through one of  converters, and after passing through one of  the three packs, the conditioned air enters a the three packs, the conditioned air enters a common air conditioning manifold for 

common air conditioning manifold for  distribution to the cabin.

distribution to the cabin.

Conditioned air is then circulated to the Conditioned air is then circulated to the cockpit, the upper deck area,

cockpit, the upper deck area, and one of fiveand one of five main deck cabin condition control zones. main deck cabin condition control zones. Output temperature of the air conditioning Output temperature of the air conditioning packs is determined by the single zone packs is determined by the single zone which requires

which requires the coolest air the coolest air output. output. TheThe air destined for other zones is warmed air destined for other zones is warmed above this temperature level by the addition above this temperature level by the addition of hot air from the pneumatic system (trim of hot air from the pneumatic system (trim air.)

air.)

ECS Overhead Panel  ECS Overhead Panel 

The air conditioning packs can operate The air conditioning packs can operate using pressurized bleed air from the using pressurized bleed air from the engines, APU or an external pneumatic engines, APU or an external pneumatic ground source.

ground source.

Temperature control is managed by Temperature control is managed by adjusting the temperature of the air  adjusting the temperature of the air  conditioned output from the packs to the conditioned output from the packs to the coolest zone

coolest zone requirement. requirement. Other zones Other zones areare then heated using a modulated

then heated using a modulated amount of amount of  trim air to meet commanded temperature trim air to meet commanded temperature requirements in those zones. Unless requirements in those zones. Unless manually set, the temperature

manually set, the temperature controlcontrol selectors will target an average cabin selectors will target an average cabin temperature of 24ºC.

temperature of 24ºC.

The forward cargo compartment is heated The forward cargo compartment is heated by the equipment cooling air exhaust from by the equipment cooling air exhaust from the flight compartment and the equipment the flight compartment and the equipment center.

center. The aft caThe aft cargo compartment rgo compartment takestakes hot bleed air directly from the center bleed hot bleed air directly from the center bleed air duct.

air duct. Temperature is Temperature is regulated by regulated by aa temperature sensing probe and a regulator  temperature sensing probe and a regulator  valve. Control of aft cargo heat can

valve. Control of aft cargo heat can bebe effected through use of the Aft Cargo effected through use of the Aft Cargo HeatHeat switch on the overhead ECS panel.

switch on the overhead ECS panel. The air conditioning system synoptic The air conditioning system synoptic provides an overview of the aircraft provides an overview of the aircraft

temperature control zones in the upper left temperature control zones in the upper left corner.

corner. This overview This overview includes the includes the master master  temperature setting, target and average temperature setting, target and average temperature for each zone, plus the current temperature for each zone, plus the current temperature of the forward and aft cargo temperature of the forward and aft cargo compartments.

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11

11 - - 8 8 AIRCRAFT AIRCRAFT SYSTEMSSYSTEMS

compressed, cooled air then passes through compressed, cooled air then passes through the turbine section of the pack where it the turbine section of the pack where it expands rapidly

expands rapidly causing further causing further cooling. cooling. AA condenser/separator eliminates excess condenser/separator eliminates excess moisture which is produced during the moisture which is produced during the expansion process.

expansion process.

To prevent ice forming in the To prevent ice forming in the

condenser/separator, the temperature of air  condenser/separator, the temperature of air  flowing through the mechanism is con

flowing through the mechanism is con trolledtrolled by mixing hot air from the compression by mixing hot air from the compression stage of the pack.

stage of the pack.

The air conditioning packs and heat The air conditioning packs and heat

exchangers produce significant amounts of  exchangers produce significant amounts of  heat during no

heat during normal operatrmal operation. ion. AdditionallAdditionallyy they consume bleed air resources from the they consume bleed air resources from the engines thus increasing EGT values and engines thus increasing EGT values and reducing engine

reducing engine efficiency. efficiency. It It isis

recommended that two packs be turned off  recommended that two packs be turned off  during takeoff.

during takeoff.

The packs themselves are cooled by The packs themselves are cooled by inducing air flow over the heat exchanger  inducing air flow over the heat exchanger  during ground operation, and by ram during ground operation, and by ram air air  during in-flight operation.

during in-flight operation. Pack Control:

Pack Control: Pack control is handled byPack control is handled by two pack cont

two pack controllers, A and rollers, A and B. B. Each packEach pack controller has three control channels, one for  controller has three control channels, one for  each pack.

each pack. If either pack If either pack controller controller fails,fails, control will automatically switch to the other  control will automatically switch to the other  controller.

controller.

Pack controllers can be selected Pack controllers can be selected

automatically, or manually by positioning the automatically, or manually by positioning the pack control selector to NORM, A or B. pack control selector to NORM, A or B. Provided bleed air is

Provided bleed air is available, this willavailable, this will cause the selected controller to command cause the selected controller to command

EICAS screen for the

EICAS screen for the Environmental ControlEnvironmental Control System (ECS

System (ECS screen.) screen.) The pack controThe pack controll mode is denoted by the letter A or B mode is denoted by the letter A or B associated with each pack.

associated with each pack.

If left in NORM, the airplane will If left in NORM, the airplane will automatically alternate betwe

automatically alternate between A and B en A and B onon subsequent flights, or the control mode may subsequent flights, or the control mode may be selected manually by the crew in the be selected manually by the crew in the event a particular control mode fails. event a particular control mode fails. Pack Hi Flow Mode:

Pack Hi Flow Mode: Packs normallyPacks normally operate in HI FLOW mode at all times operate in HI FLOW mode at all times except cruise f

except cruise flight. light. During cruiDuring cruise, these, the packs will operate in low flow in order to packs will operate in low flow in order to increase efficiency and reduce pneumatic increase efficiency and reduce pneumatic demands on

demands on the engines. the engines. This may beThis may be overridden by selecting HI FLOW on the overridden by selecting HI FLOW on the pack control switch if

pack control switch if desired or necessary.desired or necessary.  An EICAS

 An EICAS memo indicating the Hmemo indicating the HI FLOWI FLOW setting will be displayed in order to remind setting will be displayed in order to remind the crew that the Hi Flow switch is ON and the crew that the Hi Flow switch is ON and the pack flow setting is not being m

the pack flow setting is not being m anagedanaged automatically.

automatically.

Recirculation Fans:

Recirculation Fans: In order to In order to recirculaterecirculate passenger cabin air through the manifold passenger cabin air through the manifold system, four recirculation fans are i

system, four recirculation fans are i nstalled,nstalled, two o

two overhead and two verhead and two under floor. under floor. TheThe recirculation fans operate in conjunction with recirculation fans operate in conjunction with the air conditioning packs, and are

the air conditioning packs, and are controlled by t

controlled by the pack controller. he pack controller. UnlessUnless manually overridden, the lower recirculation manually overridden, the lower recirculation

(22)

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 AIRCRAFT SY

 AIRCRAFT SYSTEMS STEMS 11 - 911 - 9

the bleed ducts is used to m

the bleed ducts is used to m odulate air odulate air  temperature

temperature in different in different zones. zones. This airfThis airflowlow is called Trim Air, and the control for this is called Trim Air, and the control for this function is located on the ECS Overhead function is located on the ECS Overhead Panel.

Panel.

Equipment Cooling:

Equipment Cooling: The equipmentThe equipment cooling system provides cooling air for the cooling system provides cooling air for the flight deck electrical equipment and the flight deck electrical equipment and the electronics and equipment center racks. electronics and equipment center racks. This system directs cooler air from the lower  This system directs cooler air from the lower  fuselage into the equipment racks and

fuselage into the equipment racks and exhausts warmer air to

exhausts warmer air to the forward cargothe forward cargo compartment.

compartment.

The Equipment Cooling system operates in The Equipment Cooling system operates in three modes; NORM, STBY and OVRD. three modes; NORM, STBY and OVRD. The modes are selected using the The modes are selected using the equipment cooling selector on the ECS equipment cooling selector on the ECS portion of the overhead panel.

portion of the overhead panel.

On the ground without engine power, the On the ground without engine power, the NORM setting will automatically cause NORM setting will automatically cause warmer exhaust air to be ducted to warmer exhaust air to be ducted to thethe forward cargo compartment or out the forward cargo compartment or out the ground exhaust valve if the

ground exhaust valve if the ambientambient temperature is greater than 45º F. temperature is greater than 45º F. With the selector on

With the selector on STBY, the systemSTBY, the system functions the sa

functions the same as in Nme as in NORM mode. ORM mode. TheThe system will not exhaust warmer air out the system will not exhaust warmer air out the ground exhaust valve, regardless of ambient ground exhaust valve, regardless of ambient temperature, however.

temperature, however.

With the selector in OVRD, the

With the selector in OVRD, the equipmentequipment cooling system is deactivated and an cooling system is deactivated and an outboard vent is opened, creating airflow outboard vent is opened, creating airflow across the equipment, through the supply across the equipment, through the supply duct and overboard through the use of duct and overboard through the use of cabincabin

routing it through the evaporator. routing it through the evaporator.

Humidification levels will vary depending on Humidification levels will vary depending on the number of packs in

the number of packs in operation.operation. Secondary EICAS Indications:

Secondary EICAS Indications: A synopticA synoptic of the air conditioning system is provided on of the air conditioning system is provided on the Environmental Control Systems (ECS) the Environmental Control Systems (ECS) page, which is selected using the ECS page, which is selected using the ECS switch on the secondary EICAS control switch on the secondary EICAS control panel.

panel.

Main Deck Temperature by Zone: Main Deck Temperature by Zone: Flight Deck/Upper Deck Temp: Flight Deck/Upper Deck Temp: Master Target Temperature: Master Target Temperature:

FWD and AFT Cargo Zone Temp: FWD and AFT Cargo Zone Temp:

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11

11 - - 10 10 AIRCRAFT AIRCRAFT SYSTEMSSYSTEMS

Pressurization Overview:

Pressurization Overview: The cabin isThe cabin is pressurized with conditioned air from the pressurized with conditioned air from the air air  conditioning packs

conditioning packs. . Cabin altiCabin altitude istude is controlled by regulating the discharge of  controlled by regulating the discharge of  conditioned air through two outflow valves at conditioned air through two outflow valves at the rear of

the rear of the cabin. the cabin. The system The system isis normally fully automatic but the

normally fully automatic but the outflowoutflow valves may be positioned manually if  valves may be positioned manually if  required due to a

required due to a system failure or as asystem failure or as a result of some contingency with the normal result of some contingency with the normal system or requirement in the event of an system or requirement in the event of an onboard s

onboard smoke source. moke source. There are There are twotwo cabin altitude controllers designated A and cabin altitude controllers designated A and B.

B. Although botAlthough both controllers h controllers simultaneouslysimultaneously receive identical information, only one

receive identical information, only one controller is active at a time.

controller is active at a time.

Pressurization Control Panel  Pressurization Control Panel 

Cabin Altitude Control:

Cabin Altitude Control: The active cabinThe active cabin altitude controller uses origin airport altitude controller uses origin airport elevation, cruise altitude and landing

elevation, cruise altitude and landing altitudealtitude information from the FMS and

information from the FMS and automaticallyautomatically positions the outflow valves to conform to positions the outflow valves to conform to cabin altitude climb and

cabin altitude climb and descent rate limits,descent rate limits, differential pressure limits and to achieve the differential pressure limits and to achieve the correct landing cabi

correct landing cabin altitude. n altitude. The initialThe initial pressurization, slightly above ambient pressurization, slightly above ambient pressure, begins when the airplane reaches pressure, begins when the airplane reaches 65 knots

65 knots ground sground speed. peed. The cabin The cabin altitudealtitude controller automatically sets cabin altitude controller automatically sets cabin altitude

from the FMC

from the FMC The message iThe message is inhibited is inhibited if f  both cabin altitude controllers A and B fail. both cabin altitude controllers A and B fail. Outflow Valves:

Outflow Valves: The outflow valves areThe outflow valves are located on the bottom of the

located on the bottom of the aircraft aft of aircraft aft of  the lower aft cargo compartment. They are the lower aft cargo compartment. They are bifold type valves

bifold type valves that operate independentlythat operate independently of each other. Each

of each other. Each outflow valve has an ACoutflow valve has an AC motor and a

motor and a DC motor. The AC motor isDC motor. The AC motor is used to position the

used to position the outflow valve whoutflow valve whenen operating in

operating in the automatthe automatic ic mode of mode of  operation. An

operation. An EICAS adEICAS advisory messavisory messagege OUTFLOW VLV L (R) is displayed if  OUTFLOW VLV L (R) is displayed if  automatic control is inoperative or the automatic control is inoperative or the manual mode is selected for the respective manual mode is selected for the respective valve. An EICAS caution message CABIN valve. An EICAS caution message CABIN  ALT AUTO is d

 ALT AUTO is displayed if both cabin aisplayed if both cabin altitudeltitude controllers are inoperative or both outflow controllers are inoperative or both outflow valves are in the manual mode.

valves are in the manual mode.

If either Outflow Valve Manual switch is If either Outflow Valve Manual switch is ON,ON, the Outflow Valves Manual control may be the Outflow Valves Manual control may be used to open or close the

used to open or close the respective outflowrespective outflow valve using the slower operating DC motor. valve using the slower operating DC motor. The outflow valve not selected for manual The outflow valve not selected for manual operation remains under the control of the operation remains under the control of the cabin altitude controller. When an Outflow cabin altitude controller. When an Outflow Valve Manual switch is ON, the cabin Valve Manual switch is ON, the cabin altitude controller and the cabin

altitude controller and the cabin altitudealtitude limiter are bypassed for the respective limiter are bypassed for the respective outflow valve. If both Outflow Valve

outflow valve. If both Outflow Valve ManualManual switches are ON, all

switches are ON, all automatic cabin altitudeautomatic cabin altitude control functions are bypassed. Outflow control functions are bypassed. Outflow valve position indicators are located on the valve position indicators are located on the cabin altitude panel and the ECS synoptic. cabin altitude panel and the ECS synoptic.

(26)

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 AIRCRAFT SY

 AIRCRAFT SYSTEMS STEMS 11 - 1111 - 11

AIR CONDITIONING/PRESSURIZATION EICAS MESSAGES: AIR CONDITIONING/PRESSURIZATION EICAS MESSAGES: C

CAABBIIN N AALLTTIITTUUDDEE CCaabbiin n aallttiittuudde e eexxcceeeedds s 1100,,00000 0 ffeeeett.. C

CAABBIIN N AALLT T AAUUTTOO FFaaiilulurre e oof f bbootth h ccaabbin in aallttiitutudde e ccoonnttrorolllelerrs s oor r bbootth h oouuttfflolow w vavallveve MANUAL switches ON.

MANUAL switches ON. E

EQQUUIIP P CCOOOOLLIINNGG WiWitth h EEqquuiippmmeennt t CCoooolliinng g sseelleecctotor r iin n NNOORRM M oor r SSTTBBYY, , aaiirrfflloow w iiss inadequate, or overheat or smoke detected. With selector in inadequate, or overheat or smoke detected. With selector in OVRD, differential press

OVRD, differential pressure for ure for reverse flow cooling isreverse flow cooling is inadequate, or ground exhaust valve not in

inadequate, or ground exhaust valve not in commanded position.commanded position. >

>EE//E E CCLLNNG G CCAARRDD MMeessssaagge e iinnhhiibbiitteed d iin n fflliigghhtt.. On Ground: Control card failure. On Ground: Control card failure. L

LAANNDDIINNG G AALLTT DDiissaaggrreeeemmeennt t bbeettwweeeen n FFMMC C llaannddiinng g aallttiittuudde e aannd d ccaabbiin n pprreessssuurree controller landing altitude.

controller landing altitude. O

OUTUTFLFLOOW VW VLV LV L(L(R)R) AAututo co coontntrorol ol of L f L or or R R ououttfflolow w VValalve ve ininopopereraatitiveve, o, or r MAMANNUUAAL L wwasas selected for the respective valve.

selected for the respective valve. P

PAACCK K 11, , 22, , 33 PPaacck k CCoonnttrroolllleer r FFaauulltt Pack Operation Fault Pack Operation Fault

Pack overheat or Pack 2 shutdown with either cabin pressure Pack overheat or Pack 2 shutdown with either cabin pressure relief valve open.

relief valve open. P

PAACCK K CCOONNTTRROOLL AAuuttoomamattiic cc coonnttrrool l oof f oouuttlleet t tteemmppeerraattuurre e oof af alll pl paacckks s hhaas s fafaiilleedd.. P

PRREESSS S RREELLIIEEFF EEiitthheer r pprreessssuurre e rreelliieef f vvaallvve e aaccttuuaattees s aannd d ppaacck k 2 2 ffaaiills s tto o sshhuutt down.

down. TE

TEMP MP CCARARGO GO HHEEAATT CCarargo go cocompmparartmtmenent ot oveverrheheat at anand d tthe he ttemempeperaratturure ce cononttrrol ol vavallveve failed to

failed to close. close. (Inhibited o(Inhibited on ground)n ground) T

TEEMMP P ZZOONNEE ZZoonne e dduucct t oovveerrhheeaat t sseennsseed d oor r mmaasstteer r ttrriim m aaiir r vvaallvve e ffaaiilleed d cclloosseedd or zone temp controller failed.

or zone temp controller failed.

Cabin temperature control is in backup mode. Cabin temperature control is in backup mode. >

(28)

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11

11 - - 12 12 AIRCRAFT AIRCRAFT SYSTEMSSYSTEMS

ELECTRICAL SYSTEM

ELECTRICAL SYSTEM

Overview:

Overview: The electrical system on theThe electrical system on the 747-400 is highly automated, and was 747-400 is highly automated, and was designed from the beginning to

designed from the beginning to both reduceboth reduce pilot workload and provide a higher level of  pilot workload and provide a higher level of  dependability.

dependability. The electThe electrical sysrical systemtem provides for automatic system fault provides for automatic system fault

detection, automatic system fault isolation detection, automatic system fault isolation and reconfiguration, load management, and reconfiguration, load management, on-line power, no-break power switching, AC line power, no-break power switching, AC and DC system status monitoring and and DC system status monitoring and master frequenc

master frequency referencing. y referencing. The electricalThe electrical system is also designed to automatically system is also designed to automatically configure itself to provide the

configure itself to provide the tripletriple

redundant power required by the autopilot redundant power required by the autopilot system for full autoland

system for full autoland capability.capability.

Electrical Control Panel  Electrical Control Panel 

IDG Drive Disconnects:

IDG Drive Disconnects: The constantThe constant speed drive that operates the IDG in speed drive that operates the IDG in eacheach engine can be separated f

engine can be separated from the accessoryrom the accessory section in the event of a

section in the event of a fault or failure. fault or failure. TheThe IDG Drive Disconnect switches located on IDG Drive Disconnect switches located on the Electrical Panel on the overhead provide the Electrical Panel on the overhead provide access to this disconnect function.

access to this disconnect function.

Disconnecting an IDG drive should only be Disconnecting an IDG drive should only be conducted at the request of maintenance, or  conducted at the request of maintenance, or  in the conduct of

in the conduct of an Abnormal Checklist, asan Abnormal Checklist, as the disconnect action will cause the loss of  the disconnect action will cause the loss of  that generator for the remainder of the flight. that generator for the remainder of the flight. When starting or shutting down an engine, it When starting or shutting down an engine, it

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 AIRCRAFT SY

 AIRCRAFT SYSTEMS STEMS 11 - 1311 - 13

APU / External Power:

APU / External Power: While on theWhile on the

ground, it is possible to provide AC power to ground, it is possible to provide AC power to the 747-400 via an

the 747-400 via an external power source or external power source or  the

the Auxiliary Auxiliary Power Power Unit Unit generatogenerator. r. TheThe electrical system is designed so that both electrical system is designed so that both methods of providing electrical power can be methods of providing electrical power can be used simultaneously on different portions of  used simultaneously on different portions of  the electrical system.

the electrical system.

Two non-paralleled 90KVA generators are Two non-paralleled 90KVA generators are driven by the APU and are

driven by the APU and are capable of capable of  providing 115 Volt, 400 hertz AC power to providing 115 Volt, 400 hertz AC power to each AC system while the aircraft is on the each AC system while the aircraft is on the ground.

ground.

To simulate differences in various airport  To simulate differences in various airport  facilities around the world, PMDG has  facilities around the world, PMDG has  included a logic parameter that will provide  included a logic parameter that will provide  External Ground Power for EXT1 when  External Ground Power for EXT1 when  selected from the 

selected from the 

PMDG/OPTIONS/VARIOUS menu. (See  PMDG/OPTIONS/VARIOUS menu. (See  Chapter 00 Introduction for more 

Chapter 00 Introduction for more  information.)

information.) Occasionally, the Occasionally, the ground ground  power will also be made available on EXT2. power will also be made available on EXT2.

Split System Breaker:

Split System Breaker: The electricalThe electrical

IDGs are powering both sides of the IDGs are powering both sides of the airplane, the SSB will be

airplane, the SSB will be closed.closed. It is possible to power the left and

It is possible to power the left and right sidesright sides of the

of the airplane using dissimilar power airplane using dissimilar power  sources.

sources. If the right If the right side of tside of the airplane ishe airplane is powered by an APU generator, while the left powered by an APU generator, while the left side is powered by Ground Power, then the side is powered by Ground Power, then the SSB will open to allow both sides to receive SSB will open to allow both sides to receive power from the selected source while power from the selected source while preventing them from being

preventing them from being paralleled.paralleled. When first beginning to power the aircraft, When first beginning to power the aircraft, the behavior of the SSB will depend upon the behavior of the SSB will depend upon what power sources are AVAILABLE. what power sources are AVAILABLE. (AVAILABLE means that the source is (AVAILABLE means that the source is available for use, but has not

available for use, but has not been selectedbeen selected as an ACTIVE pow

as an ACTIVE power source.) er source.) If only EXIf only EXT1T1 is showing as AVAIL on the

is showing as AVAIL on the electrical panel,electrical panel, then the SSB will remain open when EXT1 then the SSB will remain open when EXT1 is selected.

is selected.

The only way to close the

The only way to close the SSB, thusSSB, thus

providing power to the entire airplane, is for  providing power to the entire airplane, is for  a power source to be AVAILABLE for the a power source to be AVAILABLE for the right side of the airplane, whether it is in use right side of the airplane, whether it is in use or not.

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11

11 - - 14 14 AIRCRAFT AIRCRAFT SYSTEMSSYSTEMS

the two power sources fails, the SSB will the two power sources fails, the SSB will close automatically, and power will continue close automatically, and power will continue to be provided to both the

to be provided to both the Left and RightLeft and Right systems without interruption.

systems without interruption. Power Switching/Preferencing:

Power Switching/Preferencing: WhenWhen both systems are being powered by engine both systems are being powered by engine driven IDGs, selection of either an APU or  driven IDGs, selection of either an APU or  EXT power source will

EXT power source will automatiautomatically takecally take both IDGs on that side of the

both IDGs on that side of the electricalelectrical system offline, and will instead

system offline, and will instead provideprovide power from the newly selected

power from the newly selected source.source.

If APU or EXT power is selected on the If APU or EXT power is selected on the other side of the electrical system, then the other side of the electrical system, then the entire electrical system will be powered from entire electrical system will be powered from non IDG

non IDG sources. sources. (And the SSB (And the SSB will remainwill remain open!)

open!)

If the entire system is being powered by non If the entire system is being powered by non IDG sources, the SS

IDG sources, the SSB is open. B is open. If an IDG iIf an IDG iss then brought online on the

then brought online on the right side of theright side of the

Each of the AC buses is connected to

Each of the AC buses is connected to the tiethe tie bus by a B

bus by a Bus Tie Breaker us Tie Breaker (BTB). (BTB). PlacingPlacing the BUS TIE switch in

the BUS TIE switch in AUTO will commandAUTO will command the BTB to open and cl

the BTB to open and close automatically inose automatically in order to maintain the integrity of the system order to maintain the integrity of the system in the event of a sys

in the event of a system fault. tem fault. If the BUSIf the BUS TIE switch is placed in ISLN, the BTB and TIE switch is placed in ISLN, the BTB and the DC ISLN relay

the DC ISLN relay will open, separating thatwill open, separating that  AC bus from the r

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 AIRCRAFT SY

 AIRCRAFT SYSTEMS STEMS 11 - 1511 - 15

buses 1-4, res

buses 1-4, respectively. pectively. The DC buses The DC buses cancan be paralleled or isolated.

be paralleled or isolated. DC Tie Bus:

DC Tie Bus: With the BUS TIE switch inWith the BUS TIE switch in  AUTO, each DC

 AUTO, each DC isolation relay operatesisolation relay operates automatically, and will remain closed if no automatically, and will remain closed if no DC faults

DC faults are detected. are detected. With the BUWith the BUS TIES TIE switch set to ISLN, the

switch set to ISLN, the respective system isrespective system is opened, which isolates the DC bus from the opened, which isolates the DC bus from the tie bus and leaves it

tie bus and leaves it powered only by thepowered only by the respective AC bus and TR.

respective AC bus and TR. Battery Busses:

Battery Busses: There are four batteryThere are four battery busses:

busses:

Main Battery Bus Main Battery Bus Main Hot Battery Bus Main Hot Battery Bus APU Battery Bus APU Battery Bus APU Hot Battery Bus APU Hot Battery Bus

The hot busses are always connected to The hot busses are always connected to their respective batteries and are normally their respective batteries and are normally powered by the ground service bus through powered by the ground service bus through the battery chargers if the ground service the battery chargers if the ground service bus is po

bus is powered.wered.

The main and APU battery busses are The main and APU battery busses are normally powered by DC bus 3.

normally powered by DC bus 3.

 AUTO position, the

 AUTO position, the Main Standby bus wMain Standby bus will beill be powered from the main standby inverter. powered from the main standby inverter. The standby inverter

The standby inverter will draw it’s power will draw it’s power  from AC bus 1 (via the

from AC bus 1 (via the ground service bus,ground service bus, the main battery charger and the m

the main battery charger and the m ain hotain hot battery bus).

battery bus). The BATTERY sThe BATTERY switch must bewitch must be on for this backup to function properly.

on for this backup to function properly. If both AC bus 1

If both AC bus 1 and AC bus 3 areand AC bus 3 are unpowered, the standby bus is

unpowered, the standby bus is poweredpowered from the main battery through the main hot from the main battery through the main hot battery bus and the standby inverter. battery bus and the standby inverter.

Battery power can be expected to power the Battery power can be expected to power the main standby bus for at least

main standby bus for at least 30 minutes.30 minutes. The battery switch must be ON and the The battery switch must be ON and the standby power selector must be in the standby power selector must be in the  AUTO position

 AUTO position for this transfer tfor this transfer to take place.o take place. If the

If the STANDBY POSTANDBY POWER selector is rotatedWER selector is rotated to the BAT position and the

to the BAT position and the battery switcbattery switch ish is ON, the standby bus is powered by the m ON, the standby bus is powered by the m ainain battery via the main hot batter

battery via the main hot batter bus and thebus and the standby inverter.

standby inverter. The APU batThe APU battery bus istery bus is powered by the APU battery through the powered by the APU battery through the  APU hot battery bus

 APU hot battery bus. . (In this conf(In this configurationiguration the APU battery chargers are

the APU battery chargers are disabled.)disabled.) The standby bus can be powered in this The standby bus can be powered in this configuration for

References

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