AIRCRAFT CHARACTERISTICS AIRPORT AND MAINTENANCE PLANNING … AD Seminar-Worksho… · @A380 AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING LOCATIONS CHG CODE DESCRIPTIONS

@AIRBUSA380

AIRCRAFT CHARACTERISTICSAIRPORT AND MAINTENANCE PLANNING

AC

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© AIRBUS S.A.S. 2005. All rights reserved.

AIRBUS S.A.S.Customer Services

Technical Data Support and Services31707 Blagnac Cedex

FRANCE

Issue: Mar 30/05 Rev: Dec 01/16

@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

HIGHLIGHTS

Revision No. 15 - Dec 01/16

LOCATIONS CHGCODE

DESCRIPTIONS OF CHANGE

CHAPTER 2

Section 2-1

Subject 2-1-1

General Aircraft Characteristics Data R

Section 2-6

Subject 2-6-0

FIGURE Cargo Compartments - Locationand Dimensions

R

FIGURE Cargo Compartments - LoadingCombinations

R

Section 2-9

Subject 2-9-0

Landing Gear R

FIGURE Nose Landing Gear - General R REVISED THE ILLUSTRATION (SHEET 3)TO SHOW TOW TRUCK POWERCONNECTOR.

Section 2-14

Subject 2-14-0

Jacking for Maintenance R

Jacking of the Landing Gear R DESCRIPTION TITLE UPDATEDNOTE AMENDED

CHAPTER 5

Section 5-4

Subject 5-4-4

Electrical Servicing R

CHAPTER 7

Section 7-1

Subject 7-1-0

General Information R

HIGHLIGHTSPage 1

Dec 01/16


LOCATIONS CHGCODE


Section 7-2

Subject 7-2-0

Landing Gear Footprint R

FIGURE Landing Gear Footprint R ADDED WV010, WV011 AND WV012 INTHE TABLE. UPDATED TIRE PRESSURE(WING GEAR AND BODY GEAR) FORWV009.

Section 7-3

Subject 7-3-0

FIGURE Maximum Pavement Loads R ADDED MAXIMUM PAVEMENT LOADSFOR WV010, WV011 AND WV012.

Section 7-4

Subject 7-4-0

Landing Gear Loading on Pavement R

FIGURE Landing Gear Loading onPavement - WV010, MRW 482 000 kg,CG 43%

R REPLACED LANDING GEAR LOADING ONPAVEMENT GRAPHS OF WV007 WITHWV010 AND UPDATED THE TITLERESPECTIVELY.

FIGURE Landing Gear Loading onPavement - WV008, MRW 577 000 kg,CG 41%

R

Section 7-5

Subject 7-5-0

Flexible Pavement Requirements - USArmy Corps of Engineers Design Method

R

FIGURE Flexible Pavement Requirements- WV010, MRW 482 000 kg, CG 43% -Wing Landing Gear

R REPLACED FLEXIBLE PAVEMENTREQUIREMENTS GRAPHS OF WV007WITH WV010 AND UPDATED THE TITLERESPECTIVELY.

FIGURE Flexible Pavement Requirements- WV008, MRW 577 000 kg, CG 41% -Wing Landing Gear

R

Section 7-6

Subject 7-6-0

HIGHLIGHTSPage 2

Dec 01/16


LOCATIONS CHGCODE


Flexible Pavement Requirements - LCNConversion

R CROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETED

Section 7-7

Subject 7-7-0

Rigid Pavement Requirements - PortlandCement Association Design Method

R

FIGURE Rigid Pavement Requirements -WV010, MRW 482 000 kg, CG 43% -WLG

R REPLACED RIGID PAVEMENTREQUIREMENTS GRAPHS OF WV007WITH WV010 AND UPDATED THE TITLERESPECTIVELY.

FIGURE Rigid Pavement Requirements -WV008, MRW 577 000 kg, CG 41% -WLG

R

Section 7-8

Subject 7-8-0

Rigid Pavement Requirements - LCNConversion

R CROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETED

Section 7-9

Subject 7-9-0

ACN/PCN Reporting System - Flexibleand Rigid Pavements

R

FIGURE Aircraft Classification Number -ACN Table

R ADDED ACN DATA FOR WV010, WV011AND WV012. UPDATED VAULES FORWV009.ILLUSTRATION REVISED

FIGURE Aircraft Classification Number -Flexible Pavement - WV010, MRW 482000 kg, CG 43%

R REPLACED FLEXIBLE AND RIGIDPAVEMENT GRAPHS OF WV007 WITHWV010 AND UPDATED THE TITLERESPECTIVELY.

HIGHLIGHTSPage 3

Dec 01/16


LIST OF EFFECTIVE CONTENT

Revision No. 15 - Dec 01/16

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 1

Subject 1-1-0

Introduction Dec 01/14

Subject 1-2-1

Glossary Dec 01/15

CHAPTER 2

Subject 2-1-1

General Aircraft Characteristics Data R Dec 01/16

Subject 2-2-0

General Aircraft Dimensions Dec 01/13

FIGURE General Aircraft Dimensions Dec 01/13

Subject 2-3-0

Ground Clearances Dec 01/14

FIGURE Ground Clearances Dec 01/14

FIGURE Ground Clearances - Leading Edge Slats - Extended Dec 01/14

FIGURE Ground Clearances - Trailing Edge Flaps - Extended Dec 01/14

FIGURE Ground Clearances - Spoilers - Extended Dec 01/13

FIGURE Ground Clearances - Ailerons - Down Dec 01/14

FIGURE Ground Clearances - Ailerons - Up Dec 01/14

FIGURE Ground Clearances - Flap Tracks - Extended Dec 01/14

FIGURE Ground Clearances - Trimmable Horizontal Stabilizer andElevators - Down

Dec 01/14

Subject 2-4-0

Interior Arrangement - Plan View Dec 01/15

FIGURE Interior Arrangements - Plan View - Standard Configuration- Upper Deck

Dec 01/15

L.E.C.Page 1

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Interior Arrangements - Plan View - Standard Configuration- Main Deck

Dec 01/15

Subject 2-5-0

Interior Arrangements - Cross Section Dec 01/15

FIGURE Interior Arrangements - Cross Section - TypicalConfiguration - Upper Deck

Dec 01/15

FIGURE Interior Arrangements - Cross Section - TypicalConfiguration - Main Deck

Dec 01/15

Subject 2-6-0

Cargo Compartments Dec 01/15

FIGURE Cargo Compartments - Location and Dimensions R Dec 01/16

FIGURE Cargo Compartments - Loading Combinations R Dec 01/16

Subject 2-7-0

Door Clearances Dec 01/14

FIGURE Door Clearances - Door Location (Sheet 1) Dec 01/13

FIGURE Door Clearances - Door Location (Sheet 2) Dec 01/13

FIGURE Door Clearances - Forward Passenger Doors Dec 01/15

FIGURE Door Clearances - Main and Upper Deck Passenger Doors Dec 01/15

FIGURE Door Clearances - Aft Passenger Doors Dec 01/15

FIGURE Door Clearances - Forward Cargo Compartment Door Dec 01/15

FIGURE Door Clearances - Aft Cargo Compartment Doors Dec 01/15

FIGURE Door Clearances - Forward Nose Landing Gear Doors Dec 01/15

FIGURE Door Clearances - Wing Landing Gears - Main Doors Dec 01/14

FIGURE Door Clearances - Body Landing Gears - Outer Doors Dec 01/14

FIGURE Door Clearances - APU Doors Dec 01/14

Subject 2-8-0

Escape Slides Dec 01/15

FIGURE Escape Slides - Location Dec 01/15

FIGURE Escape Slides - Dimensions Dec 01/15

Subject 2-9-0

L.E.C.Page 2

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

Landing Gear R Dec 01/16

FIGURE Wing Landing Gear - General Dec 01/15

FIGURE Body Landing Gear - General Dec 01/15

FIGURE Nose Landing Gear - General R Dec 01/16

Landing Gear Maintenance Pits Dec 01/15

FIGURE Landing Gear Maintenance Pits - Maintenance Pit Envelopes Dec 01/13

FIGURE Landing Gear Maintenance Pits - Necessary Depths Dec 01/13

FIGURE Landing Gear Maintenance Pits - Maintenance Pit Envelopes- WLG Pit Dimensions

Dec 01/13

FIGURE Landing Gear Maintenance Pits - Maintenance Pit Envelopes- BLG Pit Dimensions

Dec 01/13

Subject 2-10-0

Exterior Lighting Dec 01/13

FIGURE Exterior Lighting Dec 01/13





Subject 2-11-0

Antennas and Probes Location Dec 01/13

FIGURE Antennas and Probes - Location Dec 01/13

Subject 2-12-0

Auxiliary Power Unit Dec 01/13

FIGURE Auxiliary Power Unit - Access Doors Dec 01/13

FIGURE Auxiliary Power Unit - General Layout Dec 01/13

Engine and Nacelle Dec 01/13

FIGURE Power Plant Handling - Engine Dimensions - GP 7200Engine

Dec 01/13

FIGURE Power Plant Handling - Nacelle Dimensions - GP 7200Engine

Dec 01/13

L.E.C.Page 3

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Power Plant Handling - Fan Cowls - GP 7200 Engine Dec 01/13

FIGURE Power Plant Handling - Thrust Reverser Cowls - GP 7200Engine

Dec 01/13

FIGURE Power Plant Handling - Fan Exhaust Cowls - GP 7200Engine

Dec 01/15

FIGURE Power Plant Handling - Engine Dimensions - TRENT 900Engine

Dec 01/13

FIGURE Power Plant Handling - Nacelle Dimensions - TRENT 900Engine

Dec 01/13

FIGURE Power Plant Handling - Fan Cowls - TRENT 900 Engine Dec 01/13

FIGURE Power Plant Handling - Thrust Reverser Cowls - TRENT900 Engine

Dec 01/13

FIGURE Power Plant Handling - Fan Exhaust Cowls - TRENT 900Engine

Dec 01/15

Subject 2-13-0

Leveling, Symmetry and Alignment Dec 01/13

FIGURE Location of Leveling Points Dec 01/13

Subject 2-14-0

Jacking for Maintenance R Dec 01/16

FIGURE Jacking for Maintenance - Jacking Points Location Dec 01/13

FIGURE Jacking for Maintenance - Jacking Dimensions Dec 01/13

FIGURE Jacking for Maintenance - Forward Jacking Point Dec 01/13

FIGURE Jacking for Maintenance - Wing Jacking Point Dec 01/13

FIGURE Jacking for Maintenance - Auxiliary Jacking Point - SafetyStay

Dec 01/13

Jacking of the Landing Gear R Dec 01/16

FIGURE Nose Landing Gear Jacking Point Heights Dec 01/13

FIGURE Wing Landing Gear Jacking Point Heights Dec 01/13

FIGURE Body Landing Gear Jacking Point Heights Dec 01/13

CHAPTER 3

Subject 3-1-0

L.E.C.Page 4

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

General Information Dec 01/13

Subject 3-2-1

Payload/Range - ISA Conditions Dec 01/14

FIGURE Payload/Range - ISA Conditions - TRENT 900 Engines Dec 01/13

FIGURE Payload/Range - ISA Conditions - GP 7200 Engines Dec 01/13

Subject 3-3-1

Take-Off Weight Limitation - ISA Conditions Dec 01/14

FIGURE Take-Off Weight Limitation - ISA Conditions - TRENT 900Engines

Dec 01/14

FIGURE Take-Off Weight Limitation - ISA Conditions - GP 7200Engines

Dec 01/14

Subject 3-3-2

Take-Off Weight Limitation - ISA + 15 ˚C (+59 ˚F) Conditions Dec 01/14

FIGURE Take-Off Weight Limitation - ISA + 15 ˚C (+59 ˚F)Conditions - TRENT 900 Engines

Dec 01/14

FIGURE Take-Off Weight Limitation - ISA + 15 ˚C (+59 ˚F)Conditions - GP 7200 Engines

Dec 01/14

Subject 3-4-1

Landing Field Length Dec 01/14

FIGURE Landing Field Length - Dry Runway Dec 01/14

Subject 3-5-0

Final Approach Speed Dec 01/13

CHAPTER 4

Subject 4-1-0

General Dec 01/13

Subject 4-2-0

Turning Radii Dec 01/14

FIGURE Turning Radii - (Sheet 1) Dec 01/14

FIGURE Turning Radii - (Sheet 2) Dec 01/14

Subject 4-3-0

L.E.C.Page 5

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

Minimum Turning Radii Dec 01/14

FIGURE Minimum Turning Radii Dec 01/14

Subject 4-4-0

Visibility from Cockpit in Static Position Dec 01/13

FIGURE Visibility from Cockpit in Static Position Dec 01/13

FIGURE Binocular Visibility Through Windows from Captain EyePosition

Dec 01/13

Subject 4-5-0

Runway and Taxiway Turn Paths Dec 01/13

Subject 4-5-1

135˚ Turn - Runway to Taxiway Dec 01/13

FIGURE 135˚ Turn -- Runway to Taxiway - Judgemental OversteerMethod

Dec 01/13

FIGURE 135˚ Turn -- Runway to Taxiway - Cockpit TracksCentreline Method

Dec 01/13

Subject 4-5-2

90˚ Turn - Runway to Taxiway Dec 01/13

FIGURE 90˚ Turn -- Runway to Taxiway - Judgemental OversteerMethod

Dec 01/13

FIGURE 90˚ Turn -- Runway to Taxiway - Cockpit Tracks CentrelineMethod

Dec 01/13

Subject 4-5-3

180˚ Turn on a Runway Dec 01/13

FIGURE 180˚ Turn on a Runway Dec 01/13

Subject 4-5-4

90˚ Turn - Taxiway to Taxiway Dec 01/13

FIGURE 90˚ Turn -- Taxiway to Taxiway - Judgemental OversteerMethod

Dec 01/13

FIGURE 90˚ Turn -- Taxiway to Taxiway - Cockpit Tracks CentrelineMethod

Dec 01/13

Subject 4-5-5

135˚ Turn - Taxiway to Taxiway Dec 01/13

L.E.C.Page 6

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 135˚ Turn -- Taxiway to Taxiway - Judgemental OversteerMethod

Dec 01/13

FIGURE 135˚ Turn -- Taxiway to Taxiway - Cockpit TracksCenterline Method

Dec 01/13

Subject 4-6-0

Runway Holding Bay (Apron) Dec 01/13

FIGURE Runway Holding Bay (Apron) Dec 01/13

Subject 4-7-0

Minimum Line-Up Distance Corrections Dec 01/13

FIGURE Minimum Line-Up Distance Corrections - 90˚ Turn onRunway Entry

Dec 01/13

FIGURE Minimum Line-Up Distance Corrections - 180˚ Turn onRunway Turn Pad

Dec 01/13

FIGURE Minimum Line-Up Distance Corrections - 180˚ Turn onRunway Width

Dec 01/13

Subject 4-8-0

Aircraft Mooring Dec 01/13

FIGURE Aircraft Mooring Dec 01/13

CHAPTER 5

Subject 5-1-0

Aircraft Servicing Arrangements Dec 01/14

Subject 5-1-1

Typical Ramp Layout (Open Apron) Dec 01/15

FIGURE Typical Ramp Layout - Open Apron Dec 01/13

Subject 5-1-2

Typical Ramp Layout (Gate) Dec 01/15

FIGURE Typical Ramp Layout - Gate Dec 01/13

Subject 5-2-1

Typical Turn-Round Time - Standard Servicing Via Main Deck andUpper Deck

Dec 01/14

L.E.C.Page 7

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Typical Turn-Round Time - Servicing Via Main and UpperDeck

Dec 01/14

Subject 5-2-2

Typical Turn-Round Time - Servicing Via Main Deck Dec 01/14

FIGURE Typical Turn-Round Time - Servicing Via Main Deck Dec 01/14

Subject 5-4-1

Ground Service Connections Layout Dec 01/13

FIGURE Ground Service Connections Layout Dec 01/13

Subject 5-4-2

Grounding (Earthing) Points Dec 01/14

FIGURE Grounding (Earthing) Point - NLG Dec 01/14

FIGURE Grounding (Earthing) Points - WLG Dec 01/14

FIGURE Grounding (Earthing) Points - BLG Dec 01/14

Subject 5-4-3

Hydraulic Servicing Dec 01/15

FIGURE Ground Service Connections - Hydraulic Reservoir ServicingPanel

Dec 01/14

FIGURE Ground Service Connections - Hydraulic Ground Connections Dec 01/13

Subject 5-4-4

Electrical Servicing R Dec 01/16

FIGURE Ground Service Connections - Electrical Service Panel Dec 01/13

FIGURE Ground Service Connections - Ram Air Turbine Retracted Dec 01/14

FIGURE Ground Service Connections - Ram Air Turbine Extended Dec 01/14

Subject 5-4-5

Oxygen System Dec 01/14

FIGURE Ground Service Connections - Oxygen System Dec 01/13

Subject 5-4-6

Fuel Servicing Dec 01/15

FIGURE Ground Service Connections - Refuel/Defuel Control Panel Dec 01/13

FIGURE Ground Service Connections - Pressure Refuel Connections Dec 01/13

L.E.C.Page 8

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Ground Service Connections - Overpressure Protector andNACA Flame Arrestor - Wing

Dec 01/14

FIGURE Ground Service Connections - Overpressure Protector andNACA Flame Arrestor - Trim Tank

Dec 01/14

Subject 5-4-7

Pneumatic Servicing Dec 01/15

FIGURE Ground Service Connections - Low Pressure PreconditionedAir

Dec 01/13

FIGURE Ground Service Connections - High Pressure PreconditionedAir

Dec 01/13

Subject 5-4-8

Oil Servicing Dec 01/15

FIGURE Ground Service Connections - Engine Oil Servicing - TRENT900 Engines

Dec 01/15

FIGURE Ground Service Connections - VFG Oil Servicing - TRENT900 Engines

Dec 01/15

FIGURE Ground Service Connections - Starter Oil Servicing - TRENT900 Engines

Dec 01/15

FIGURE Ground Service Connections - Engine Oil Servicing - GP7200Engines

Dec 01/15

FIGURE Ground Service Connections - VFG Oil Servicing - GP7200Engines

Dec 01/15

FIGURE Ground Service Connections - Starter Oil Servicing - GP7200Engines

Dec 01/15

FIGURE Ground Service Connections - APU Oil Servicing Dec 01/15

Subject 5-4-9

Potable Water Servicing Dec 01/15

FIGURE Ground Service Connections - Potable Water Ground ServicePanel

Dec 01/14

FIGURE Ground Service Connections - Potable Water Drain Panel Dec 01/14

FIGURE Ground Service Connections - Potable Water Tanks Location Dec 01/14

Subject 5-4-10

Waste Water System Dec 01/14

L.E.C.Page 9

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Ground Service Connections - Waste Water Ground ServicePanel

Dec 01/14

FIGURE Ground Service Connections - Waste Tanks Location Dec 01/13

Subject 5-4-11

Cargo Control Panels Dec 01/15

FIGURE Forward Cargo Control Panels Dec 01/14

FIGURE Aft Cargo Control Panels Dec 01/14

Subject 5-5-0

Engine Starting Pneumatic Requirements Dec 01/13

FIGURE Example for Use of the Charts Dec 01/13

FIGURE Engine Starting Pneumatic Requirements - Engine Alliance -GP 7200

Dec 01/13

FIGURE Engine Starting Pneumatic Requirements - Rolls Royce -Trent 900 Engine

Dec 01/13

Subject 5-6-0

Ground Pneumatic Power Requirements Dec 01/15

FIGURE Ground Pneumatic Power Requirements - Heating Dec 01/13

FIGURE Ground Pneumatic Power Requirements - Cooling Dec 01/13

Subject 5-7-0

Preconditioned Airflow Requirements Dec 01/15

FIGURE Preconditioned Airflow Requirements Dec 01/13

Subject 5-8-0

Ground Towing Requirements Dec 01/15

FIGURE Ground Towing Requirements Dec 01/13

FIGURE Ground Towing Requirements - Nose Gear Towing Fittings Dec 01/13

Subject 5-9-0

De-Icing and External Cleaning Dec 01/15

CHAPTER 6

Subject 6-1-0

Engine Exhaust Velocities and Temperatures Dec 01/14

L.E.C.Page 10

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

Subject 6-1-1

Engine Exhaust Velocities - Ground Idle Power Dec 01/13

FIGURE Engine Exhaust Velocities - Ground Idle Power - TRENT 900Engines

Dec 01/13

FIGURE Engine Exhaust Velocities - Ground Idle Power - GP 7200Engines

Dec 01/13

Subject 6-1-2

Engine Exhaust Temperatures - Ground Idle Power Dec 01/13

FIGURE Engine Exhaust Temperatures - Ground Idle Power - TRENT900 Engines

Dec 01/13

FIGURE Engine Exhaust Temperatures - Ground Idle Power - GP7200 Engines

Dec 01/13

Subject 6-1-3

Engine Exhaust Velocities - Breakaway Power Dec 01/13

FIGURE Engine Exhaust Velocities - Breakaway Power - TRENT 900Engines

Dec 01/13

FIGURE Engine Exhaust Velocities - Breakaway Power - GP 7200Engines

Dec 01/13

Subject 6-1-4

Engine Exhaust Temperatures - Breakaway Power Dec 01/13

FIGURE Engine Exhaust Temperatures - Breakaway Power - TRENT900 Engines

Dec 01/13

FIGURE Engine Exhaust Temperatures - Breakaway Power - GP 7200Engines

Dec 01/13

Subject 6-1-5

Engine Exhaust Velocities - Max Take-off Power Dec 01/13

FIGURE Engine Exhaust Velocities - Max. Take-Off Power - TRENT900 Engines

Dec 01/13

FIGURE Engine Exhaust Velocities - Max. Take-Off Power - GP 7200Engines

Dec 01/13

Subject 6-1-6

Engine Exhaust Temperatures - Max Take-off Power Dec 01/13

L.E.C.Page 11

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Engine Exhaust Temperatures - Max Take-Off Power -TRENT 900 Engines

Dec 01/13

FIGURE Engine Exhaust Temperatures - Max Take-Off Power - GP7200 Engines

Dec 01/13

Subject 6-3-0

Danger Areas of the Engines Dec 01/13

Subject 6-3-1

Danger Areas of the Engines - Ground Idle Power Dec 01/13

FIGURE Danger Areas of the Engines - Ground Idle Power - TRENT900 Engines

Dec 01/13

FIGURE Danger Areas of the Engines - Ground Idle Power - GP 7200Engines

Dec 01/13

Subject 6-3-2

Danger Areas of the Engines - Max. Take-Off Power Dec 01/13

FIGURE Danger Areas of the Engines - Max Take-Off Power -TRENT 900 Engines

Dec 01/13

FIGURE Danger Areas of the Engines - Max Take-Off Power - GP7200 Engines

Dec 01/13

Subject 6-3-3

Danger Areas of the Engines - Breakaway Power Dec 01/13

FIGURE Danger Areas of the Engines - Breakaway Power - TRENT900 Engines

Dec 01/13

FIGURE Danger Areas of the Engines - Breakaway Power - GP 7200Engines

Dec 01/13

Subject 6-4-1

APU Exhaust Velocities and Temperatures - ECS Conditions Dec 01/14

FIGURE APU Exhaust Velocities and Temperatures - Max. ECSConditions

Dec 01/13

Subject 6-4-2

APU Exhaust Velocities and Temperatures - MES Conditions Dec 01/13

FIGURE APU Exhaust Velocities and Temperatures - MES Conditions Dec 01/13

CHAPTER 7

L.E.C.Page 12

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

Subject 7-1-0

General Information R Dec 01/16

Subject 7-2-0

Landing Gear Footprint R Dec 01/16

FIGURE Landing Gear Footprint R Dec 01/16

Subject 7-3-0

Maximum Pavement Loads Dec 01/14

FIGURE Maximum Pavement Loads R Dec 01/16

Subject 7-4-0

Landing Gear Loading on Pavement R Dec 01/16

FIGURE Landing Gear Loading on Pavement - WV010, MRW 482000 kg, CG 43%

R Dec 01/16

FIGURE Landing Gear Loading on Pavement - WV008, MRW 577000 kg, CG 41%

R Dec 01/16

Subject 7-5-0

Flexible Pavement Requirements - US Army Corps of EngineersDesign Method

R Dec 01/16

FIGURE Flexible Pavement Requirements - WV010, MRW 482 000kg, CG 43% - Wing Landing Gear

R Dec 01/16

FIGURE Flexible Pavement Requirements - WV008, MRW 577 000kg, CG 41% - Wing Landing Gear

R Dec 01/16

Subject 7-6-0

Flexible Pavement Requirements - LCN Conversion R Dec 01/16

Subject 7-7-0

Rigid Pavement Requirements - Portland Cement Association DesignMethod

R Dec 01/16

FIGURE Rigid Pavement Requirements - WV010, MRW 482 000 kg,CG 43% - WLG

R Dec 01/16

FIGURE Rigid Pavement Requirements - WV008, MRW 577 000 kg,CG 41% - WLG

R Dec 01/16

Subject 7-8-0

Rigid Pavement Requirements - LCN Conversion R Dec 01/16

L.E.C.Page 13

Dec 01/16


CONTENT CHGCODE

LAST REVISIONDATE

Subject 7-9-0

ACN/PCN Reporting System - Flexible and Rigid Pavements R Dec 01/16

FIGURE Aircraft Classification Number - ACN Table R Dec 01/16

FIGURE Aircraft Classification Number - Flexible Pavement - WV010,MRW 482 000 kg, CG 43%

R Dec 01/16

FIGURE Aircraft Classification Number - Flexible Pavement - WV008,MRW 577 000 kg, CG 41%

Dec 01/14

CHAPTER 8

Subject 8-0-0

Scaled Drawings Dec 01/13

FIGURE Scaled Drawing Dec 01/13

CHAPTER 10

Subject 10-0-0

Aircraft Rescue and Fire Fighting Dec 01/15

FIGURE Front Page Dec 01/15

FIGURE Highly Flammable and Hazardous Materials and Components Dec 01/15

FIGURE Batteries Location and Access Dec 01/15

FIGURE Crew Rest Compartments Location Dec 01/13

FIGURE Wheel/Brake Overheat - Wheel Safety Area Dec 01/13

FIGURE Composite Materials Location Dec 01/13

FIGURE Landing Gear - Ground Lock Safety Devices Dec 01/13

FIGURE Emergency Evacuation Devices Dec 01/15

FIGURE Pax/Crew Doors and Emergency Exits Dec 01/13

FIGURE Cargo Doors - FWD and AFT Lower Deck Cargo Doors Dec 01/13

FIGURE Control Panels Dec 01/13

FIGURE APU Compartment Access Dec 01/13

FIGURE Aircraft Ground Clearances Dec 01/15

FIGURE Structural Break-in Points Dec 01/13

L.E.C.Page 14

Dec 01/16


TABLE OF CONTENTS

1 SCOPE

1-1-0 Introduction

1-2-1 Glossary

2 AIRCRAFT DESCRIPTION

2-1-1 General Aircraft Characteristics Data

2-2-0 General Aircraft Dimensions

2-3-0 Ground Clearances

2-4-0 Interior Arrangement - Plan View

2-5-0 Interior Arrangements - Cross Section

2-6-0 Cargo Compartments

2-7-0 Door Clearances

2-8-0 Escape Slides

2-9-0 Landing Gear

2-10-0 Exterior Lighting

2-11-0 Antennas and Probes Location

2-12-0 Power Plant

2-13-0 Leveling, Symmetry and Alignment

2-14-0 Jacking

3 AIRCRAFT PERFORMANCE

3-1-0 General Information

3-2-1 Payload/Range - ISA Conditions

3-3-1 Take Off Weight Limitation - ISA Conditions

3-3-2 Take Off Weight Limitation - ISA + 15 ˚C (59 ˚F) Conditions

3-4-1 Landing Field Length - ISA Conditions

3-5-0 Final Approach Speed

4 GROUND MANEUVERING


4-2-0 Turning Radii

4-3-0 Minimum Turning Radii

4-4-0 Visibility from Cockpit in Static Position

4-5-0 Runway and Taxiway Turn Paths

4-5-1 135˚ Turn - Runway to Taxiway

T.O.C.Page 1

Dec 01/16



4-5-3 180˚ Turn on a Runway

4-5-4 90˚ Turn - Taxiway to Taxiway


4-6-0 Runway Holding Bay (Apron)

4-7-0 Minimum Line-Up Distance Corrections

4-8-0 Aircraft Mooring

5 TERMINAL SERVICING

5-1-0 Aircraft Servicing Arrangements

5-1-1 Typical Ramp Layout (Open Apron)

5-1-2 Typical Ramp Layout (Gate)

5-2-1 Typical Turn-Round Time - Standard Servicing Via Main Deck and Upper Deck

5-2-2 Typical Turn-Round Time - Servicing Via Main Deck

5-4-1 Ground Service Connections Layout

5-4-2 Grounding (Earthing) Points

5-4-3 Hydraulic System

5-4-4 Electrical System

5-4-5 Oxygen System

5-4-6 Fuel System

5-4-7 Pneumatic System

5-4-8 Oil System

5-4-9 Potable Water System

5-4-10 Waste Water System

5-4-11 Cargo Control Panels

5-5-0 Engine Starting Pneumatic Requirements

5-6-0 Ground Pneumatic Power Requirements

5-7-0 Preconditioned Airflow Requirements

5-8-0 Ground Towing Requirements

5-9-0 De-Icing and External Cleaning

6 OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

6-1-1 Engine Exhaust Velocities - Ground Idle Power

6-1-2 Engine Exhaust Temperatures - Ground Idle Power

6-1-3 Engine Exhaust Velocities - Breakaway Power

6-1-4 Engine Exhaust Temperatures - Breakaway Power

6-1-5 Engine Exhaust Velocities - Max Take-off Power

T.O.C.Page 2

Dec 01/16


6-1-6 Engine Exhaust Temperatures - Max Take-off Power

6-3-0 Danger Areas of the Engines

6-3-1 Danger Areas of the Engines - Ground Idle Power

6-3-2 Danger Areas of the Engines - Max. Take-Off Power

6-3-3 Danger Areas of the Engines - Breakaway Power

6-4-1 APU Exhaust Velocities and Temperatures

6-4-2 APU Exhaust Velocities and Temperatures - MES Conditions

7 PAVEMENT DATA


7-2-0 Landing Gear Footprint

7-3-0 Maximum Pavement Loads

7-4-0 Landing Gear Loading on Pavement

7-5-0 Flexible Pavement Requirements - US Army Corps of Engineers Design Method

7-6-0 Flexible Pavement Requirements - LCN Conversion

7-7-0 Rigid Pavement Requirements - Portland Cement Association Design Method

7-8-0 Rigid Pavement Requirements - LCN Conversion

7-9-0 ACN/PCN Reporting System - Flexible and Rigid Pavements

8 SCALED DRAWINGS

8-0-0 SCALED DRAWINGS

10 AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 AIRCRAFT RESCUE AND FIRE FIGHTING

T.O.C.Page 3

Dec 01/16


SCOPE

1-1-0 Introduction

**ON A/C A380-800

Introduction

1. GeneralThe A380 AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING (AC)manual is issued for the A380 series aircraft to provide necessary data to airport operators, airlinesand Maintenance/Repair Organizations (MRO) for airport and maintenance facilities planning.

This document is not customized and must not be used for training purposes. No information withinmay constitute a contractual commitment.

The A380-800 is a subsonic, very long range and very high capacity civil transport aircraft. TheA380-800 offers several payload capabilities ranging from 400 passengers in a very comfortable multi-class configuration, up to 853 passengers in an all economy class configuration.

Designed in close collaboration with major airlines, airports and airworthiness authorities, the A380 isthe most advanced, spacious and productive aircraft in service setting a new standard in air traveland environmental efficiency.

The A380 Family starts from a baseline passenger aircraft - the A380-800. A higher capacity version,the A380-900 could be developed when required by the market.

Two engine types are currently offered, the Engine Alliance GP7200 series and the Rolls-Royce Trent900 series. Both engines use state of the art technology for better performance, maintainability, lowerfuel consumption and environmental impact.

The A380-800 was designed to be compatible with current airport infrastructure and equipment, asproven in service. Bigger, quieter and capable of achieving quick turn around times, the A380-800provides an efficient solution for airports and airlines to grow in a sustainable manner.

Correspondence concerning this publication should be directed to:

AIRBUS S.A.S.Customer ServicesTechnical Data Support and Services1, Rond Point Maurice BELLONTE31707 BLAGNAC CEDEXFRANCE

1-1-0Page 1

Dec 01/16


1-2-1 Glossary

**ON A/C A380-800

Glossary

1. List of Abbreviations

A/C Aircraft

ACN Aircraft Classification NumberAMM Aircraft Maintenance ManualAPU Auxiliary Power Unit

B/C Business Class

BLG Body Landing Gear

CBR California Bearing Ratio

CC Cargo Compartment

CG Center of Gravity

C/L Center Line

CLS Cargo Loading System

E Young’s Modulus

ECS Environmental Control System

ELEC Electric, Electrical, Electricity

ESWL Equivalent Single Wheel Load

FAA Federal Aviation AdministrationF/C First Class

FDL Fuselage Datum Line

FR FrameFSTE Full Size Trolley Equivalent

FWD ForwardGPU Ground Power UnitGSE Ground Support Equipment

HYD Hydraulic

ICAO International Civil Aviation Organisation

ISA International Standard Atmosphere

L Radius of Relative StiffnessLCN Load Classification NumberLD Load DeviceLD Lower DeckLH Left HandLPS Last Pax Seating

MAC Mean Aerodynamic Chord

1-2-1Page 1

Dec 01/16


MAX MaximumMD Main DeckMES Main Engine Start

MIN MinimumNLG Nose Landing Gear

OAT Outside Air Temperature

PAX Passenger

PBB Passenger Boarding Bridge

PB/D Passenger Boarding/Deplaning

PCA Portland Cement AssociationPCN Pavement Classification NumberPRM Passenger with Reduced Mobility

RH Right Hand

UD Upper Deck

ULD Unit Load DeviceUS United StatesVFG Variable Frequency Generator

WLG Wing Landing Gear

WV Weight Variant

Y/C Tourist Class

2. Design Weight Terminology- Maximum Design Ramp Weight (MRW):

Maximum weight for ground maneuver (including weight of taxi and run-up fuel) as limited byaircraft strength and airworthiness requirements. It is also called Maximum Design Taxi Weight(MTW).

- Maximum Design Landing Weight (MLW):Maximum weight for landing as limited by aircraft strength and airworthiness requirements.

- Maximum Design Take-Off Weight (MTOW):Maximum weight for take-off as limited by aircraft strength and airworthiness requirements. (Thisis the maximum weight at start of the take-off run).

- Maximum Design Zero Fuel Weight (MZFW):Maximum permissible weight of the aircraft without usable fuel.

- Maximum Seating Capacity:Maximum number of passengers specifically certified or anticipated for certification.

- Usable Volume:Usable volume available for cargo, pressurized fuselage, passenger compartment and cockpit.

- Water Volume:Maximum volume of cargo compartment.

- Usable Fuel:

1-2-1Page 2

Dec 01/16


Fuel available for aircraft propulsion.

1-2-1Page 3

Dec 01/16


AIRCRAFT DESCRIPTION

2-1-1 General Aircraft Characteristics Data

**ON A/C A380-800

General Aircraft Characteristics Data

1. The following table provides characteristics of A380-800 Models, these data are specific to eachWeight Variant:

Aircraft CharacteristicsWV000 WV001 WV002 WV003 WV004

Maximum Ramp Weight(MRW)Maximum Taxi Weight(MTW)

562 000 kg(1 238 998 lb)

512 000 kg(1 128 766 lb)

571 000 kg(1 258 839 lb)

512 000 kg(1 128 766

lb)

562 000 kg(1 238 998 lb)

Maximum Take-OffWeight (MTOW)

560 000 kg(1 234 588 lb)

510 000 kg(1 124 357 lb)

569 000 kg(1 254 430 lb)

510 000 kg(1 124 357

lb)

560 000 kg(1 234 588 lb)

Maximum LandingWeight (MLW)

386 000 kg(850 984 lb)

394 000 kg(868 621 lb)

391 000 kg(862 007 lb)

395 000 kg(870 826 lb)

391 000 kg(862 007 lb)

Maximum Zero FuelWeight (MZFW)

361 000 kg(795 869 lb)

372 000 kg(820 119 lb)

366 000 kg(806 892 lb)

373 000 kg(822 324 lb)

366 000 kg(806 892 lb)

Aircraft CharacteristicsWV005 WV006 WV007 WV008 WV009

Maximum Ramp Weight(MRW)Maximum Taxi Weight(MTW)

562 000 kg(1 238 998 lb)

575 000 kg(1 267 658 lb)

492 000 kg(1 084 674 lb)

577 000 kg(1 272 067

lb)

512 000 kg(1 128 766 lb)

Maximum Take-OffWeight (MTOW)

560 000 kg(1 234 588 lb)

573 000 kg(1 263 248 lb)

490 000 kg(1 080 265 lb)

575 000 kg(1 267 658

lb)

510 000 kg(1 124 357 lb)

Maximum LandingWeight (MLW)

386 000 kg(850 984 lb)

393 000 kg(866 416 lb)

395 000 kg(870 826 lb)

394 000 kg(868 621 lb)

386 000 kg(850 984 lb)

Maximum Zero FuelWeight (MZFW)

366 000 kg(806 892 lb)

368 000 kg(811 301 lb)

373 000 kg(822 324 lb)

369 000 kg(813 506 lb)

361 000 kg(795 869 lb)

2-1-1Page 1

Dec 01/16


Aircraft CharacteristicsWV010 WV011 WV012

Maximum Ramp Weight (MRW)Maximum Taxi Weight (MTW)

482 000 kg(1 062 628 lb)

577 000 kg(1 272 067 lb)

571 000 kg(1 258 839 lb)

Maximum Take-Off Weight(MTOW)

480 000 kg(1 058 219 lb)

575 000 kg(1 267 658 lb)

569 000 kg(1 254 430 lb)

Maximum Landing Weight (MLW)386 000 kg(850 984 lb)

395 000 kg(870 826 lb)

395 000 kg(870 826 lb)

Maximum Zero Fuel Weight(MZFW)

361 000 kg(795 869 lb)

369 000 kg(813 506 lb)

366 000 kg(806 892 lb)

2. The following table provides characteristics of A380-800 Models, these data are common to eachWeight Variant:

Aircraft CharacteristicsStandard SeatingCapacity

555

323 546 l(85 472 US gal)Usable Fuel Capacity

(density = 0.785kg/l) 253 983 kg

(559 937 lb)

Pressurized FuselageVolume (A/C nonequipped, main andupper deck)

2 100 m3

(74 161 ft3)

PassengerCompartment Volume(main deck)

775 m3

(27 369 ft3)

PassengerCompartment Volume(upper deck)

530 m3

(18 717 ft3)

Cockpit Volume12 m3

(424 ft3)

Usable Volume, FWDCC(Based on LD3)

89.4 m3

(3 157 ft3)

Usable Volume, AFTCC(Based on LD3)

71.5 m3

(2 525 ft3)

2-1-1Page 2

Dec 01/16


Aircraft Characteristics

Usable Volume, BulkCC

14.3 m3

(505 ft3)

Water Volume, FWDCC

131 m3

(4 626 ft3)

Water Volume, AFTCC

107.8 m3

(3 807 ft3)

Water Volume, BulkCC

17.3 m3

(611 ft3)

2-1-1Page 3

Dec 01/16


2-2-0 General Aircraft Dimensions

**ON A/C A380-800

General Aircraft Dimensions

1. This section provides General Aircraft Dimensions.

2-2-0Page 1

Dec 01/16


**ON A/C A380-800

72.73 m

70.4 m

53.94 m 4.7 m(15.42 ft)

12.06 m(39.57 ft)

14.5

9 m

8.41 m

14.08 m(46.19 ft)

33.58 m − WLG

36.85 m − BLG

4.97 m(16.31 ft)

(27.59 ft)8.56 m

(28.08 ft)

(176.97 ft)

(230.97 ft)

(238.62 ft)

(47.

87 ft

)12.46 m(40.88 ft)

7.14 m(23.43 ft)

14.34 m

29.6 m

51.4 m

79.75 m

30.37 m(261.65 ft)

(99.64 ft)

5.26 m(17.26 ft)

(47.05 ft)

(97.11 ft)

(168.64 ft)

NOTE: RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.

(110.17 ft)

(120.9 ft)

L_AC_020200_1_0010101_01_02

General Aircraft Dimensions(Sheet 1 of 2)

FIGURE-2-2-0-991-001-A01

2-2-0Page 2

Dec 01/16


**ON A/C A380-800

11.57 m(37.96 ft)

3.72 m(12.2 ft)

17.67 m

72.57 m

68.85 m

46.97 m 3.98 m

29.94 m

22.23 m

(57.97 ft)

(98.23 ft)

(72.93 ft)

(154.1 ft)

52.07 m(170.83 ft)

(13.06 ft)

(225.89 ft)

(238.09 ft)

25.9

7 m

(85.

2 ft)

13.4

9 m

(44.

26 ft

)

17.6

5 m

(57.

91 ft

)21

.87

m(7

1.75

ft)

9.36 m(30.71 ft)

NOTE: RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.L_AC_020200_1_0010103_01_00

General Aircraft Dimensions(Sheet 2 of 2)

FIGURE-2-2-0-991-001-A01

2-2-0Page 3

Dec 01/16


2-3-0 Ground Clearances

**ON A/C A380-800

Ground Clearances

1. This section provides the heights of various points of the aircraft, above the ground, for differentaircraft configurations.Dimensions in the tables are approximate and will vary with tire type, weight and balance and otherspecial conditions.

The dimensions are given for:- A light weight, for an aircraft in maintenance configuration with a FWD CG and an AFT CG,- An aircraft at Maximum Ramp Weight with a FWD CG and an AFT CG,- Aircraft on jacks, FDL at 7.20 m (23.62 ft).

NOTE : Passenger and cargo door ground clearances are measured from the center of the door silland from floor level.

2-3-0Page 1

Dec 01/16


**ON A/C A380-800

2.27 2.22 2.411.66 1.66 1.82

2.38 4.271.82 3.68

4.74 4.82 4.76 5.02 6.84 22.416.515.615.815.67.13 7.17 7.16 7.42 9.22

7.55 7.49 8.27 8.22 10.125.27 5.21 5.97 5.94 7.849.20 9.15 9.30 9.20 11.147.65 7.60 7.75 7.65 9.59

14.012.1

30.2

33.225.736.531.5

7.86.0

24.3

27.019.530.225.1

7.96.0

23.5

27.119.630.525.4

7.35.4

23.5

24.617.130.024.9

7.45.4

23.4

24.817.330.225.1

FROM THE CENTER OF THE DOOR SILL AND FROM FLOOR LEVEL.− MAXIMUM JACKING WEIGHT = 333 700 kg (735 682 lb).

NOTE:− PASSENGER AND CARGO DOOR GROUND CLEARANCES ARE MEASURED

F2F3BF1BF2CP1RD1W1W2HTHT1VTN1N2

FUSELAGE

WINGS

TAILPLANE

ENGINE/NACELLE

24.171.051.90

24.12 24.27 24.17 26.11 85.779.379.679.179.31.08 1.30 1.30 3.14 10.34.34.33.53.41.90 2.27 2.27 4.13 13.57.47.46.26.2

(37.8%)FWD CG

(29%)FWD CG

A/C JACKEDFDL = 7.20 m

(23.6 ft)(44%)AFT CG

5.105.125.155.185.207.877.917.943.053.113.24

5.135.145.155.155.167.897.907.913.083.103.23

5.145.205.305.375.427.988.108.153.243.273.41

5.365.345.315.285.278.088.048.023.303.233.36

7.157.157.157.157.159.909.909.905.125.125.24

(41%)AFT CG

23.523.523.523.523.532.532.532.516.816.817.2

17.617.517.417.317.326.526.426.310.810.611.0

16.917.117.417.617.826.226.626.710.610.711.2

16.816.916.916.916.925.925.926.010.110.210.6

16.716.816.917.017.125.826.026.010.010.210.6

m ft m ft m ft m ft m ft

A/CCONFIGURATION

MRW 300 t

M1M2M3M4M5U1U2U3C1C2C3

DOORS

2.34 2.38 2.45 2.59 4.41 14.58.58.07.87.7F110.75 10.79 10.84 11.00 12.8210.83 10.78 10.97 10.93 12.82

42.142.1

36.135.9

35.636.0

35.435.4

35.335.5

M1F2

M2 U1 M3 U2 M4 U3F3

W2

M5 HT1 HT

C3 C2BF2 N2 BF1 N1 F1

C1 CP1RD1VT W1

L_AC_020300_1_0010101_01_04

Ground ClearancesFIGURE-2-3-0-991-001-A01

2-3-0Page 2

Dec 01/16


**ON A/C A380-800

m ft m ft m ft

MRWAFT CG

MRWFWD CG

300 tMID CGDESCRIPTION

3.95 13.0 3.98 13.1 4.10 13.5DN1* INBD END

DN1/DN2* 4.60 15.1 4.62 15.2 4.78 15.7

DN2* OUTBD END 5.12 16.8 5.13 16.8 5.32 17.5

SLAT 2 INBD END 5.12 16.8 5.13 16.8

5.34 17.5 5.35 17.6

5.35 17.6

SLAT 2/3

SLAT 3/4 5.53 18.1 5.53 18.1 5.85 19.2

SLAT 4 OUTBD END 5.65 18.5 5.65 18.5 6.04 19.8

SLAT 5 INBD END 5.78 19.0 5.77 18.9 6.21 20.4

SLAT 5/6

SLAT 6/7

SLAT 7 OUTBD END

5.89

5.98

6.05

19.3

19.6

19.8

5.87

5.96

6.02

19.3

19.6

19.8

6.40

6.58

6.75

21.0

21.6

22.1

A

B

C

D

E

F

G

H

J

K

L

LEADING EDGE SLATS EXTENDED

18.45.61

NOTE:* DN − DROOP NOSE

A B C D E F G H J K L

L_AC_020300_1_0040101_01_01

Ground ClearancesLeading Edge Slats - ExtendedFIGURE-2-3-0-991-004-A01

2-3-0Page 3

Dec 01/16


**ON A/C A380-800

m ft m ft m ft

MRWAFT CG

MRWFWD CG


A

B

1.54 5.1 1.53 5.0 1.71 5.6

3.43 11.3 3.42 11.2 3.66 12.0

C

D

4.56 15.0 4.54 14.9 4.92 16.1

5.11 16.8 5.08 16.7 5.61 18.4

INNER END

INNER/MID

MID OUTER

OUTER END

FLAPS EXTENDED

BCD

A

L_AC_020300_1_0050101_01_01

Ground ClearancesTrailing Edge Flaps - Extended

FIGURE-2-3-0-991-005-A01

2-3-0Page 4

Dec 01/16


**ON A/C A380-800

BFGJK CE DH A

m ft m ft m ft

MRWAFT CG

MRWFWD CG


A

B

C

D

E

F

G

HJ

K

SPOILER 1 INBDSPOILER 1/2

SPOILER 2 OUTBD END

SPOILER 3SPOILER 3/4

SPOILER 4/5

SPOILER 5/6

SPOILER 6/7

SPOILER 7/8

SPOILER 8 OUTBD END

4.98 16.3 4.97 16.3 5.17 17.0

5.62 18.4 5.61 18.4 5.81 19.1

6.09 20.0 6.08 19.9 6.31 20.7

6.32 20.7 6.31 20.7 6.55 21.5

6.56 21.5 6.55 21.5 6.80 22.3

6.79 22.3 6.78 22.2 7.07 23.2

6.94 22.8 6.93 22.7 7.25 23.8

7.02 23.0 7.00 23.0 7.36 24.1

7.02 23.0 7.00 23.0 7.42 24.3

7.00 23.0 6.98 22.9 7.45 24.4

SPOILERS EXTENDED

L_AC_020300_1_0060101_01_00

Ground ClearancesSpoilers - Extended

FIGURE-2-3-0-991-006-A01

2-3-0Page 5

Dec 01/16


**ON A/C A380-800

m ft m ft m ft

MRWAFT CG

MRWFWD CG


A

B

C

D

INNER ENDINNER/MID

MID OUTER

OUTER END

5.83 19.1 5.80 19.0

5.90 19.4 5.87 19.3

5.99 19.7 5.96 19.6

6.12 20.1 6.08 19.9

AILERONS DOWN

6.32 20.7

6.43 21.1

6.58 21.6

6.78 22.2

BC AD

L_AC_020300_1_0070101_01_01

Ground ClearancesAilerons - Down

FIGURE-2-3-0-991-007-A01

2-3-0Page 6

Dec 01/16


**ON A/C A380-800

m ft m ft m ft

MRWAFT CG

MRWFWD CG


A

B

C

D

INNER ENDINNER/MID

MID OUTER

OUTER END

6.38

6.41

6.45

6.50

20.9

21.0

21.221.3

6.35

6.38

6.41

6.46

20.8

20.9

21.0

21.2

6.87

6.94

7.04

7.17

22.5

22.8

23.1

23.5

AILERONS UP

ABCD

L_AC_020300_1_0080101_01_01

Ground ClearancesAilerons - Up

FIGURE-2-3-0-991-008-A01

2-3-0Page 7

Dec 01/16


**ON A/C A380-800

MRWAFT CG

MRWFWD CG


A

B

C

E

FLAP TRACKS EXTENDED

TRACK 2

TRACK 3

TRACK 4

TRACK 5

TRACK 6

2.172.87

3.08

3.48

3.86

7.19.4

10.1

11.4

12.7

2.15

2.85

3.06

3.45

3.82

7.19.4

10.0

11.3

12.5

2.37

3.12

3.42

3.89

4.35

7.8

10.2

11.212.8

14.3

D

m ft m ft m ft

A

BCDE

L_AC_020300_1_0090101_01_01

Ground ClearancesFlap Tracks - Extended

FIGURE-2-3-0-991-009-A01

2-3-0Page 8

Dec 01/16


**ON A/C A380-800

ARE IN FULLY DOWN POSITION.

NOTE:TRIMMABLE HORIZONTAL STABILIZER AND ELEVATORS

6.55 m(21.49 ft)

L_AC_020300_1_0100101_01_00

Ground ClearancesTrimmable Horizontal Stabilizer and Elevators - Down

FIGURE-2-3-0-991-010-A01

2-3-0Page 9

Dec 01/16


2-4-0 Interior Arrangement - Plan View

**ON A/C A380-800

Interior Arrangement - Plan View

1. This section provides the standard configuration.

2-4-0Page 1

Dec 01/16


**ON A/C A380-800

STOWAGES 4

PASSENGER SEATS UPPER DECK (199 TOTAL)

BUSINESS CLASS 96 SEATS

TOURIST CLASS 103 SEATS

ATTENDANT SEATS 7

COAT STOWAGE 1

GALLEYS 8

LIFT 2

UPPER DECK

LAVATORIES 7

STAIRS 2

CREW REST BUNKS 5

STAIRCREW REST BUNKS

CREW REST BUNKSSTOWAGE

STOWAGE

GALLEY

LIFT

ATTENDANT SEATATTENDANT SEATLAVATORY

LAVATORYLAVATORY

ATTENDANT SEATSCLASS SEATS

CLASS SEATS

LAVATORIES

GALLEYSLIFT

GALLEY

ATTENDANT SEATS

TOURIST

BUSINESS

CLASS SEATSBUSINESS

LAVATORY

LAVATORY

ATTENDANT SEAT

STOWAGE

STAIR

COAT STOWAGE

L_AC_020400_1_0010101_01_00

Interior Arrangements - Plan ViewStandard Configuration - Upper Deck

FIGURE-2-4-0-991-001-A01

2-4-0Page 2

Dec 01/16


**ON A/C A380-800

PASSENGER SEATS MAIN DECK (356 TOTAL)

FIRST CLASS 22 SEATS

TOURIST CLASS 334 SEATS

COAT STOWAGE 1

STOWAGE 1

GALLEYS 9

MAIN DECK

LAVATORIES 10

ATTENDANT SEATS 11

LIFT 2

STAIRS 3

STAIR

STOWAGELIFT

ATTENDANT SEAT

LAVATORY

LAVATORY

LAVATORIES

STAIRCOAT STOWAGE

ATTENDANT SEAT

CLASS SEATSTOURIST

CLASS SEATSTOURIST

CLASS SEATSTOURIST

ATTENDANT SEATS ATTENDANT SEAT

LAVATORY

STAIR

CLASS SEATSFIRST

ATTENDANT SEAT ATTENDANT SEAT

GALLEY

GALLEYSGALLEY


LAVATORY

LAVATORYLAVATORY


GALLEYS

GALLEYS

LIFT

L_AC_020400_1_0020101_01_00

Interior Arrangements - Plan ViewStandard Configuration - Main Deck

FIGURE-2-4-0-991-002-A01

2-4-0Page 3

Dec 01/16


2-5-0 Interior Arrangements - Cross Section

**ON A/C A380-800

Interior Arrangements - Cross Section

1. This section provides the typical configuration.

2-5-0Page 1

Dec 01/16


**ON A/C A380-800

UPPER DECKBUSINESS CLASS 6 ABREAST

UPPER DECKTOURIST CLASS 8 ABREAST

1.07 m 1.07 m

(42 in)

1.07 m

(42 in)

1.07 m

(42 in)

1.37 m

(54 in)

1.37 m

(54 in)

1.37 m

(54 in)

0.58 m(23 in)

0.51 m(20 in)

(42 in)

L_AC_020500_1_0010101_01_00

Interior Arrangements - Cross SectionTypical Configuration - Upper Deck

FIGURE-2-5-0-991-001-A01

2-5-0Page 2

Dec 01/16


**ON A/C A380-800

MAIN DECKTOURIST CLASS 10 ABREAST

MAIN DECKFIRST CLASS 6 ABREAST

(62 in)

1.07 m

(42 in)

0.51 m(20 in)

1.57 m 1.07 m

(42 in) (62 in)1.57 m

(38 in)0.97 m

1.45 m(57 in)

1.45 m(57 in)

1.45 m(57 in)

L_AC_020500_1_0020101_01_00

Interior Arrangements - Cross SectionTypical Configuration - Main Deck

FIGURE-2-5-0-991-002-A01

2-5-0Page 3

Dec 01/16


2-6-0 Cargo Compartments

**ON A/C A380-800

Cargo Compartments

1. This section provides cargo compartments:- Location and dimensions- Loading combinations.

2-6-0Page 1

Dec 01/16


**ON A/C A380-800

FORWARD AFT CARGO

COMPARTMENT)

LOWER DECK

COMPARTMENT(T−SHAPED

LOWER DECKREAR AFT CARGOCOMPARTMENT

LOWER DECKBULK CARGO

COMPARTMENT

2.8 m(110.2 in)

(110.2 in)9.7 m

(381.9 in)

1.1 m(43.3 in)

3.1 m(122.8 in)

FR17 FR44 FR57FR90

FR86

2.8 m17.4 m(685.04 in)

LOWER DECKFOWARD CARGOCOMPARTMENT

8.2 m(322.8 in)

L_AC_020600_1_0010101_01_01

Cargo CompartmentsLocation and Dimensions

FIGURE-2-6-0-991-001-A01

2-6-0Page 2

Dec 01/16


**ON A/C A380-800

STANDARD: 20 LD3 OR 7 PALLETS 88 in / 96 in X 125 inOPTION: 22 LD3 OR 7 PALLETS 88 in / 96 in X 125 in

STANDARD: 16 LD3 OR 6 LD3 3 PALLETS 88 in / 96 in X 125 inOPTION: 6 PALLETS 88 in / 96 in X 125 in

L_AC_020600_1_0020101_01_01

Cargo CompartmentsLoading Combinations

FIGURE-2-6-0-991-002-A01

2-6-0Page 3

Dec 01/16


2-7-0 Door Clearances

**ON A/C A380-800

Door Clearances

1. This section provides door clearances and location.

2-7-0Page 1

Dec 01/16


**ON A/C A380-800

FWDCARGO DOOR

AFTCARGO DOOR

BULKCARGO DOOR

DOORM2L

DOORM1L

DOORU1L

DOORU2L

DOORU3L

DOORM4L

DOORM5L

EMERGENCYEXIT DOOR

M3L

DOORU1R

DOORU2R

DOORU3R

DOORM5R DOOR

M4RDOORM2R

DOORM1R

EMERGENCYEXIT DOOR

M3R

L_AC_020700_1_0010101_01_01

Door ClearancesDoor Location (Sheet 1)

FIGURE-2-7-0-991-001-A01

2-7-0Page 2

Dec 01/16


**ON A/C A380-800

53.63 m(175.95 ft)

49.19 m(161.38 ft)

44.74 m(146.78 ft)

40.3 m(132.22 ft)

20.94 m(68.7 ft)

6.32 m(20.73 ft)

16.5 m(54.13 ft)

11.73 m(38.48 ft)

48.07 m(157.71 ft)

51.09 m(167.62 ft)

32.68 m(107.22 ft)

L_AC_020700_1_0020101_01_01

Door ClearancesDoor Location (Sheet 2)

FIGURE-2-7-0-991-002-A01

2-7-0Page 3

Dec 01/16


**ON A/C A380-800

0.04 m(0.13 ft)

1.26 m(4.13 ft)

0.04 m(0.13 ft)

2.51 m(8.23 ft)

1.07 m(3.51 ft)

0.72 m(2.36 ft)

01

0.86 m(2.82 ft)

01

FWD

0.05 m(0.16 ft)

2.13 m(6.99 ft)

1.90 m(6.23 ft)

FWD

MAIN DECK DOORSM1L, M1R

MEASURED FROM THE EXTERNAL POINT OF THE SCUFF PLATEAND THE MOST EXTERNAL POINT OF THE DOOR SKIN.

01NOTE:

SEECHAPTER

2−3

L_AC_020700_1_0050101_01_01

Door ClearancesForward Passenger Doors

FIGURE-2-7-0-991-005-A01

2-7-0Page 4

Dec 01/16


**ON A/C A380-800

1.92 m(6.30 ft)

1.90 m(6.23 ft)

SEECHAPTER

2−3

SEECHAPTER

2−3

2.13 m(6.99 ft)

0.05 m(0.16 ft)

FWD

0.08 m(0.26 ft)

2.11 m(6.92 ft)

0.89 m(2.92 ft)

ON M3L/M3R0.70 m(2.30 ft)

0.04 m(0.13 ft)

0.04 m(0.13 ft) 0.04 m

(0.13 ft)

1.02 m(3.35 ft)

ON M3L/M3R0.84 m(2.76 ft)

01

02

01

02

2.51 m(8.23 ft)

2.51 m(8.23 ft)

1.07 m(3.51 ft)

0.52 m(1.71 ft)

0.72 m(2.36 ft)

0.04 m(0.13 ft)

FWD

1.26 m(4.13 ft)

1.07 m(3.51 ft)

0101

UPPER DECK DOORSU1L, U2L, U3L, U1R, U2R, U3R

MAIN DECK DOORSM2L, M3L, M4L, M2R, M3R, M4R

MEASURED FROM THE EXTERNAL POINT OF THE SCUFF PLATEAND THE MOST EXTERNAL POINT OF THE DOOR SKIN.

01NOTE:

02 ON DOOR M3L/M3R MEASURED FROM THE EXTERNAL POINTOF THE CUTOUT IN THE BELLY FAIRING AND THE MOSTEXTERNAL POINT OF THE BELLY FAIRING FROM THE DOOR.

L_AC_020700_1_0060101_01_01

Door ClearancesMain and Upper Deck Passenger Doors

FIGURE-2-7-0-991-006-A01

2-7-0Page 5

Dec 01/16


**ON A/C A380-800

010.96 m(3.15 ft)

1.09 m(3.58 ft)

2.51 m(8.23 ft)

1.07 m(3.51 ft)

0.04 m(0.13 ft)

0.04 m(0.13 ft)

1.26 m(4.13 ft)

FWD

01

SEECHAPTER

2−3

2.13 m(6.99 ft)

0.05 m(0.16 ft)

1.90 m(6.23 ft)

FWD

MAIN DECK DOORSM5L, M5R

AND THE MOST EXTERNAL POINT OF THE DOOR SKIN.

NOTE:MEASURED FROM THE EXTERNAL POINT OF THE SCUFF PLATE01

L_AC_020700_1_0070101_01_01

Door ClearancesAft Passenger Doors

FIGURE-2-7-0-991-007-A01

2-7-0Page 6

Dec 01/16


**ON A/C A380-800

SEECHAPTER

2−3

1.75 m(5.74 ft)

6.34 m(20.80 ft)

2.12 m(6.96 ft)

3.11 m(10.20 ft)

GROUND LINE

2.09 m(6.86 ft)

A

A

A A

FWD

(9.81 ft)R 2.99 m

DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT.01NOTE:

01

L_AC_020700_1_0080101_01_01

Door ClearancesForward Cargo Compartment Door

FIGURE-2-7-0-991-008-A01

2-7-0Page 7

Dec 01/16


**ON A/C A380-800

SEECHAPTER

2−3

SEECHAPTER

2−3

1.75 m(5.74 ft)

2.09 m(6.86 ft)

0.99 m(3.25 ft)

2.79 m(9.15 ft)

GROUND LINE

2.01 m(6.59 ft)

FWD

1.13 m(3.71 ft)

6.42 m(21.06 ft)

B BA A

B

B

A

A

R 3.07 m (10.07 ft) AT R 2.95 m (9..68ft) AT

FR81AFR85

R 1.40 m(4.59 ft)


01

L_AC_020700_1_0090101_01_01

Door ClearancesAft Cargo Compartment Doors

FIGURE-2-7-0-991-009-A01

2-7-0Page 8

Dec 01/16


**ON A/C A380-800

AIR

CR

AF

T

GROUND LINE

A

62°

2.50 m(8.20 ft)

1.36 m(4.46 ft)

R 1.89 m(6.20 ft)

AB

(3.08 ft)0.94 m

FORWARD NOSELANDING GEARDOOR

LH SHOWNRH SYMMETRICAL


01

L_AC_020700_1_0100101_01_01

Door ClearancesForward Nose Landing Gear Doors (Sheet 1 of 2)

FIGURE-2-7-0-991-010-A01

2-7-0Page 9

Dec 01/16


**ON A/C A380-800

0.75 mA

IRC

RA

FT

C/L

69.2°

0.50 m

R 1.89 m

B

(1.64 ft)

(6.20 ft)

(2.46 ft)

AFT NOSE LANDINGGEAR DOOR


L_AC_020700_1_0100102_01_00

Door ClearancesAft Nose Landing Gear Doors (Sheet 2 of 2)

FIGURE-2-7-0-991-010-A01

2-7-0Page 10

Dec 01/16


**ON A/C A380-800

30.91 m(101.41 ft)


GROUND LINE(10.60 ft)3.23 m

MAX 79°

AIR

CR

AF

T

(5.61 ft)1.71 m

4.28 m(14.04 ft)

R 2.30 m(7.55 ft)

WING−LANDING−GEARMAIN DOOR

A

(12.96 ft)3.95 m

NOTE:DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT.01

01MAX. 0.25 m (0.82 ft)MIN. 0.10 m (0.33 ft)

A

L_AC_020700_1_0110101_01_00

Door ClearancesWing Landing Gears - Main Doors

FIGURE-2-7-0-991-011-A01

2-7-0Page 11

Dec 01/16


**ON A/C A380-800

(15.49 ft)4.72 m

AIR

CR

AF

TMAX. 0.35 m (1.15 ft)MIN. 0.25 m (0.82 ft)

MAX 99°

GROUND LINE

35.67 m(117.03 ft)

(16.96 ft)5.17 m

ALH SHOWN

RH SYMMETRICAL

NOTE:

(7.38 ft)2.25 m

(16.47 ft)5.02 m

BODY−LANDING−GEAROUTER DOOR

A B

DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT.01

01

R 2.90 m(9.51 ft)

L_AC_020700_1_0120101_01_00

Door ClearancesBody Landing Gears - Outer Doors (Sheet 1 of 2)

FIGURE-2-7-0-991-012-A01

2-7-0Page 12

Dec 01/16


**ON A/C A380-800

(4.04 ft)1.23 m

2.25 m(7.38 ft)

GROUND LINE


NOTE:

AIR

CR

AF

T

MAX. 0.95 m (3.12 ft)MIN. 0.70 m (2.30 ft)

(3.87 ft)1.18 m

MAX 94°

BODY−LANDING−GEARINNER DOOR

DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT.01

01

R 1.32 m(4.33 ft)

B

L_AC_020700_1_0120102_01_00

Door ClearancesBody Landing Gears - Inner Doors (Sheet 2 of 2)

FIGURE-2-7-0-991-012-A01

2-7-0Page 13

Dec 01/16


**ON A/C A380-800

GROUND LINE

FR117FR112

NOTE:DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT.01

01 MAX. 5.52 m (18.11 ft)MIN. 5.49 m (18.01 ft)

FUSELAGE DATUM LINE

01MAX. 6.66 m (21.85 ft)MIN. 6.63 m (21.75 ft)

APU DOOR

L_AC_020700_1_0130101_01_00

Door ClearancesAPU Doors

FIGURE-2-7-0-991-013-A01

2-7-0Page 14

Dec 01/16


2-8-0 Escape Slides

**ON A/C A380-800

Escape Slides

1. GeneralThis section provides the location of cabin escape facilities and related clearances.

2. Location

A. Escape facilities are provided at the following locations:

(1) Upper deck evacuation:- One slide-raft at each passenger/crew door (total six).

(2) Main deck evacuation:- One slide-raft at each passenger/crew door (total eight)- One ramp/slide for each emergency exit door (total two). The slides are housed in the

belly fairing for off-the-wing evacuation.

2-8-0Page 1

Dec 01/16


**ON A/C A380-800

MAIN DECK DUAL−LANE

COCKPIT ESCAPEROPE

SLIDE/RAFT

UPPER DECK DUAL−LANESLIDE/RAFT

OVERWING DUAL−LANERAMP/SLIDE


MAIN DECK DUAL−LANESLIDE/RAFT

MAIN DECK DUAL−LANESLIDE/RAFT


− THE RAMPS/SLIDES AT DOORS M3L AND M3R DO NOT HAVE RAFT CAPABILITY.

NOTE:− LH SHOWN, RH SYMMETRICAL.

L_AC_020800_1_0010101_01_02

Escape SlidesLocation

FIGURE-2-8-0-991-001-A01

2-8-0Page 2

Dec 01/16


**ON A/C A380-800

0

− 3

− 6

− 9

− 1

2

− 1

5

− 1

8

− 2

1

− 2

4

− 2

7

− 3

0

− 3

3

− 3

6

− 3

9

GR

ID E

QU

ALS

1 m

(3.

28 ft

) IN

RE

ALI

TY

− 4

2

NO

TE

:−

LH

SH

OW

N, R

H S

YM

ME

TR

ICA

L.

EM

ER

GE

NC

Y D

ES

CE

NT

TH

RO

UG

H T

HE

WIN

DO

W O

PE

NIN

G W

ITH

TH

E E

SC

AP

E R

OP

E

− D

IME

NS

ION

S A

RE

AP

PR

OX

IMA

TE

.

EM

ER

GE

NC

Y E

VA

CU

AT

ION

L_AC_020800_1_0020101_01_02

Escape SlidesDimensions

FIGURE-2-8-0-991-002-A01

2-8-0Page 3

Dec 01/16


2-9-0 Landing Gear

**ON A/C A380-800

Landing Gear

1. GeneralThe aircraft has:- Two Wing Landing Gears (WLG) with four wheel bogie assembly and related doors,- Two Body Landing Gears (BLG) with six wheel bogie assembly and related doors,- A Nose Landing Gear (NLG) with twin wheel assembly and related doors.

The wing landing gears are located under the wing and retract sideways towards the fuselagecenterline.The body landing gears are located on the belly and retract rearward into a bay in the fuselage.The nose landing gear retracts forward into a fuselage compartment below the cockpit.

The landing gear and landing gear doors operation are controlled electrically and are hydraulically andmechanically operated.In abnormal operation, the landing gear can be extended by gravity.

For landing gear footprint and tire size, refer to 07-02-00.

2. Wing Landing GearEach WLG has a leg assembly and a four-wheel bogie beam. The WLG leg includes a Bogie TrimActuator (BTA) and an oleo-pneumatic shock absorber.A two-piece sidestay assembly holds the WLG in the extended position. A lockstay keeps the sidestayassembly stable in the locked down position.

3. Body Landing GearThe two BLG have a six-wheel bogie beam and a leg assembly that includes an oleo-pneumatic shockabsorber. A two-piece dragstay assembly mechanically locks the leg in the extended position.

4. Nose Landing GearThe NLG includes a single-stage direct acting oleo-pneumatic shock absorber. A two-piece dragstayassembly with a lockstay, mechanically locks the leg in the extended position.

5. Tow Truck PowerElectric power to the navigation lights can be provided through the tow truck power connector on the24GC service panel, see FIGURE 2-9-0-991-007-A and for connector definition, see 05-04-04.

6. SteeringThe wheel steering control system has two parts:- Nose wheel Steering (NWS),- Body Wheel Steering (BWS).Steering is controlled by two hand wheels in the cockpit. For steering angle controlled by the handwheels, refer to AMM 32-51-00 (NWS) and AMM 32-54-00 (BWS).For steering angle limitation, refer to AMM 09-10-00.

2-9-0Page 1

Dec 01/16


A steering disconnection box installed on the nose landing gear to allow steering deactivation fortowing purpose.

7. Landing Gear Servicing Points

A. GeneralFilling of the landing gear shock absorbers is through MS28889 standard valves.Charging of the landing gear shock absorbers is accomplished with nitrogen through MS28889standard valves.

B. Charging PressureFor charging of the landing gear shock absorbers, refer to AMM 32-00-00.

8. Braking

A. GeneralCarbon brakes are installed on each wheel of the WLG and on the wheels of the front andcenter axles of the BLG.The braking system is electrically controlled and hydraulically operated.The braking system has four braking modes plus autobrake and anti-skid systems:- Normal braking with anti-skid capability,- Alternative braking with anti-skid capability,- Emergency Braking (with Ultimate Braking),- Emergency braking without anti-skid protection is also available as an alternative function of

the alternate braking system,- A park brake system that is manually set is available for the BLG only. This system can also

be used to supply emergency braking.

B. In-Flight Wheel BrakingBraking occurs automatically during the retraction of the landing gear. This stops the rotationof the BLG and WLG wheels (except the wheels on the aft axle of each BLG) before the landinggears go into their related bays.

9. Tire Pressure Indicating System (TPIS)The TPIS automatically monitors the tire pressures and shows these values on Built In TestEquipment (BITE) and also supplies other data and warnings on the WHEEL page of the SystemDisplay (SD).The TPIS includes Built In Test Equipment.

10. Built In Test Equipment (BITE)The BITE has these functions, it:- Continuously monitors its systems for failures,- Sends failure data (maintenance and warnings) to other systems in the aircraft,- Keeps a record of the failures,- Automatically does specified tests of the system, or part of the system, at specified times,- Lets specified tests to be done during the maintenance procedures.

2-9-0Page 2

Dec 01/16


The BITE for the following systems is described in these chapters:- The Brakes AMM 32-46-00,- The Steering AMM 32-52-00,- The TPIS AMM 32-49-00,- The Landing Gear AMM 32-69-00.

2-9-0Page 3

Dec 01/16


**ON A/C A380-800

MAIN DOOR(HYDRAULICALLY OPERATED)

AUXILIARY

HINGED DOOR

FAIRING DOOR

A

TIRE INFLATION ADAPTER(EXAMPLE)

E

A

B

WLG LEGASSEMBLY

TORQUELINKS

AFT AXLE

BRAKE RODASSEMBLY

FWDAXLE

BOGIE BEAMASSEMBLY

BOGIE TRIMACTUATOR

SLAVELINKS

SHOCKABSORBER

F

G

DOOR

D

L_AC_020900_1_0050101_01_00

Wing Landing GearGeneral (Sheet 1 of 3)

FIGURE-2-9-0-991-005-A01

2-9-0Page 4

Dec 01/16


**ON A/C A380-800

WLG DOORACTUATOR

WARNING FLAG

SAFETY COLLAR

GROUND LOCK PIN

SIDE STAYASSEMBLY

UNLOCKACTUATOR

LOCK LINK

DOWNLOCKSPRINGS

QUICK RELEASE PIN

C

C

D

B

L_AC_020900_1_0050102_01_00

Wing Landing GearSafety Devices (Sheet 2 of 3)FIGURE-2-9-0-991-005-A01

2-9-0Page 5

Dec 01/16


**ON A/C A380-800

GROUNDING (EARTHING) POINT

E CHARGE VALVE(NITROGEN)

CHECK/FILLVALVE (OIL)

SEAL CHANGEOVERVALVE (COV)

G

F

L_AC_020900_1_0050103_01_01

Wing Landing GearServicing (Sheet 3 of 3)

FIGURE-2-9-0-991-005-A01

2-9-0Page 6

Dec 01/16


**ON A/C A380-800

INNER DOOR

OUTER DOOR

BLG LEGASSEMBLY

CENTER DOORACTUATOR

DRAG BRACE ASSEMBLY

OUTER DOOR ACTUATOR

CENTER DOOR

A

B

A

(EXAMPLE)

BOGIE TRIMACTUATOR

STEERING

BRAKE ROD

BOGIE/AXLEASSEMBLY

SLAVELINKS

SHOCKABSORBER

OUTERCYLINDER

PINTLE

ACTUATOR

TORQUELINKS

TIRE INFLATIONADAPTOR

FRAME

D

J

H

G

F

G

L_AC_020900_1_0060101_01_00

Body Landing GearGeneral (Sheet 1 of 4)

FIGURE-2-9-0-991-006-A01

2-9-0Page 7

Dec 01/16


**ON A/C A380-800

C

INNER DOORACTUATOR

B

WARNINGFLAG

SAFETY COLLAR

QUICKRELEASE

PIN

C

L_AC_020900_1_0060102_01_01

Body Landing GearDoor Safety Devices (Sheet 2 of 4)

FIGURE-2-9-0-991-006-A01

2-9-0Page 8

Dec 01/16


**ON A/C A380-800

WARNINGFLAG

SAFETY STRUT

SAFETY COLLAR

E

QUICKRELEASE

PIN

QUICKRELEASE

PIN

QUICKRELEASE

PIN

LOCKINGPIN

SOLIDPIN

ATTACHMENT PIN

ATTACHMENT PIN

LOCKINGPIN

BLG OUTERDOOR ACTUATOR

CENTER DOORFITTING

E

D

L_AC_020900_1_0060103_01_00

Body Landing GearDoor Safety Devices (Sheet 3 of 4)

FIGURE-2-9-0-991-006-A01

2-9-0Page 9

Dec 01/16


**ON A/C A380-800

CHARGING VALVE(NITROGEN)

DRAINVALVE


TYPICAL

F

LOCK SPRINGS

LOCK LINKS

H J

GGROUNDING(EARTHING)

POINT

GROUNDLOCK PIN

WARNINGFLAG

L_AC_020900_1_0060104_01_01

Body Landing GearServicing and Safety Device (Sheet 4 of 4)

FIGURE-2-9-0-991-006-A01

2-9-0Page 10

Dec 01/16


**ON A/C A380-800

B

TOWINGADAPTER

NWSACTUATOR

DOORACTUATOR

FORWARDDOOR

REARDOOR

STEERINGMECHANISM

JACKINGPOINT

MAINTENANCESERVICE PANEL

STEERINGDISCONNECT

PANEL

TIRE INFLATIONADAPTER

A

SHOCKABSORBER

AXLE

TORQUELINKS

MAIN FITTING

C

A

J

E

RETRACTIONACTUATOR

DRAG STAY ASSEMBLY

L

H

L_AC_020900_1_0070101_01_00

Nose Landing GearGeneral (Sheet 1 of 4)

FIGURE-2-9-0-991-007-A01

2-9-0Page 11

Dec 01/16


**ON A/C A380-800

D NLG DOORACTUATOR

B

C

LOCK STAY

SAFETY COLLAR

QUICKRELEASE PIN

D

UNLOCKACTUATOR

GROUNDLOCK PIN

WARNINGFLAG

WARNINGFLAG

L_AC_020900_1_0070102_01_01

Nose Landing GearSafety Devices (Sheet 2 of 4)FIGURE-2-9-0-991-007-A01

2-9-0Page 12

Dec 01/16


**ON A/C A380-800

FG

GROUND TOWING SWITCH

SAFETY PIN

F G

STEERING DISCONNECT PANEL24GC

E

TOW TRUCK POWER CONNECTORFOR PIN ALLOCATIONSEE 05−04−04

L_AC_020900_1_0070103_01_01

Nose Landing GearSteering Disconnect Panel (Sheet 3 of 4)

FIGURE-2-9-0-991-007-A01

2-9-0Page 13

Dec 01/16


**ON A/C A380-800

CHARGE VALVE(NITROGEN)


DRAIN VALVE

GROUNDING(EARTHING) POINT

J

L

H

K

K

L_AC_020900_1_0070104_01_01

Nose Landing GearServicing (Sheet 4 of 4)

FIGURE-2-9-0-991-007-A01

2-9-0Page 14

Dec 01/16


**ON A/C A380-800

Landing Gear Maintenance Pits

1. General

The minimum maintenance pit envelopes for the landing gear shock absorber maintenance are shownin FIGURE 2-9-0-991-001-A, FIGURE 2-9-0-991-002-A, FIGURE 2-9-0-991-003-A and FIGURE2-9-0-991-004-A.The three envelopes show the minimum dimensions for these maintenance operations:- Extension and retraction- Gear removal- Piston removal.

All dimensions shown are minimum dimensions with zero clearances. The dimensions for the pits havebeen determined as follows:- The length and width of the pits allow the gear to rotate as the weight is taken off the landing

gear- The landing gear is in the maximum grown condition- The WLG and BLG bogie beams are removed before the piston is removed- The NLG wheels are removed before the piston is removed- All pistons are removed vertically.

Dimensions for elevators and associated mechanisms must be added to those in FIGURE2-9-0-991-001-A, FIGURE 2-9-0-991-002-A, FIGURE 2-9-0-991-003-A and FIGURE 2-9-0-991-004-A.

A. ElevatorsThese can be either mechanical or hydraulic. They are used to:- Permit easy movement of persons and equipment around the landing gears- Lift and remove landing gear assemblies out of the pits.

B. JackingThe aircraft must be in position over the pits to put the gear on the elevators. Jacks must beinstalled and engaged with all the jacking points, Ref. 02-14-00 for aircraft maintenance jacking.Jacks must support the total aircraft weight, i.e. when the landing gears do not touch theelevators on retraction/extension tests.When tripod support jacks are used the tripod-base circle radius must be limited because thelocations required for positioning the columns are close to the sides of the pits.

2-9-0Page 15

Dec 01/16


**ON A/C A380-800

2 59

8

(102

.3)

5 62

5.5

(221

.5)

1 66

3(6

5.5)

FRONT OF NOSE RADOME

1 52

6(6

0.1) 76

3(3

0)

NLG

EX

TE

NS

ION

/RE

TR

AC

TIO

N P

IT O

UT

LIN

E

FW

D J

AC

KIN

G P

OIN

T

AIR

CR

AF

T C

EN

TE

R L

INE

WLG

RE

MO

VA

L P

IT O

UT

LIN

E

WLG

PIS

TO

N R

EM

OV

AL

PIT

OU

TLI

NE

WIN

G J

AC

KIN

G P

OIN

T

BLG

RE

MO

VA

L P

IT O

UT

LIN

E

BLG

EX

TE

NS

ION

/RE

TR

AC

TIO

N

BLG

PIS

TO

N R

EM

OV

AL

PIT

OU

TLI

NE

DIM

EN

SIO

NS

IN m

m(I

NC

HE

S IN

BR

AC

KE

TS

)M

INIM

UM

DIM

EN

SIO

NS

, ZE

RO

CLE

AR

AN

CE

S S

HO

WN

33 6

59(1

325

.2)

LH S

HO

WN

RH

SY

MM

ET

RIC

AL

4 50

6(1

77.4

)

PIT

OU

TLI

NE

WLG

EX

TE

NS

ION

/RE

TR

AC

TIO

NP

IT O

UT

LIN

E

L_AC_020900_1_0010101_01_00

Landing Gear Maintenance PitsMaintenance Pit EnvelopesFIGURE-2-9-0-991-001-A01

2-9-0Page 16

Dec 01/16


**ON A/C A380-800

NLG EXTENSION/RETRACTION

NLG REMOVAL/INSTALLATION

NLG PISTON REMOVAL/INSTALLATION

WLG EXTENSION/RETRACTION

WLG PISTON REMOVAL/INSTALLATION

WLG REMOVAL/INSTALLATION

BLG REMOVAL/INSTALLATION

BLG PISTON REMOVAL/INSTALLATION

BLG EXTENSION/RETRACTION

DIMENSIONS IN mm(INCHES IN BRACKETS)

MINIMUM DIMENSIONS, ZERO CLEARANCES SHOWN

576(22.7)

709(27.9)

1 725(67.9)

802(31.6)

1 243(48.9) 1 989

(78.3)

804(31.7) 1 127

(44.4)1 977(77.8)

L_AC_020900_1_0020101_01_00

Landing Gear Maintenance PitsNecessary Depths

FIGURE-2-9-0-991-002-A01

2-9-0Page 17

Dec 01/16


**ON A/C A380-800

972

(38.

3)3

158

(124

.3)

3 71

1(1

46.1

)

7 13

4(2

80.9

)

4 12

6(1

62.4

)1

929

(75.

9)

WLG

EX

TE

NS

ION

/RE

TR

AC

TIO

NP

IT O

UT

LIN

E

WLG

RE

MO

VA

LP

IT O

UT

LIN

E

BLG

RE

MO

VA

L P

IT O

UT

LIN

E

AIR

CR

AF

T C

EN

TE

R L

INE

DIM

EN

SIO

NS

IN m

m(I

NC

HE

S IN

BR

AC

KE

TS

)M

INIM

UM

DIM

EN

SIO

NS

, ZE

RO

CLE

AR

AN

CE

S S

HO

WN

WLG

PIS

TO

N R

EM

OV

AL

PIT

OU

TLI

NE

(101

.8)

2 58

5

3 56

0(1

40.2

)

6 22

8(2

45.2

)

1 06

7(4

2)

(37.

5)95

2

(93.

2)2

368

1 49

0(5

8.7)

(109

.9)

2 79

1

(20.

2)51

3

L_AC_020900_1_0030101_01_00

Landing Gear Maintenance PitsMaintenance Pit Envelopes - WLG Pit Dimensions

FIGURE-2-9-0-991-003-A01

2-9-0Page 18

Dec 01/16


**ON A/C A380-800

AIR

CR

AF

T C

EN

TE

R L

INE

1 68

0(6

6.1)

DIM

EN

SIO

NS

IN m

m(I

NC

HE

S IN

BR

AC

KE

TS

)M

INIM

UM

DIM

EN

SIO

NS

, ZE

RO

CLE

AR

AN

CE

S S

HO

WN

133

(5.2

)

3 18

8(1

25.5

)

7 13

4(2

80.9

)

BLG

PIS

TO

N R

EM

OV

AL

BLG

RE

MO

VA

LP

IT O

UT

LIN

E

WLG

RE

MO

VA

L P

IT O

UT

LIN

E

PIT

OU

TLI

NE

4 85

6(1

91.2

)

BLG

EX

TE

NS

ION

/RE

TR

AC

TIO

NP

IT O

UT

LIN

E

2 63

2(1

03.6

)

1 16

8(4

6)

1 05

2(4

1.4)

2 10

5(8

2.9)

1 49

0(5

8.7)

WLG

EX

TE

NS

ION

/RE

TR

AC

TIO

N P

IT O

UT

LIN

E

L_AC_020900_1_0040101_01_00

Landing Gear Maintenance PitsMaintenance Pit Envelopes - BLG Pit Dimensions

FIGURE-2-9-0-991-004-A01

2-9-0Page 19

Dec 01/16


2-10-0 Exterior Lighting

**ON A/C A380-800

Exterior Lighting

1. GeneralThis section gives the location of the aircraft exterior lighting.

EXTERIOR LIGHTINGITEM DESCRIPTION

1 RIGHT NAVIGATION LIGHT (GREEN)

2 LEFT NAVIGATION LIGHT (RED)

3 TAIL NAVIGATION LIGHT (WHITE)

4 OBSTRUCTION LIGHT

5UPPER ANTI-COLLISION LIGHTS/BEACONS(RED)

6LOWER ANTI-COLLISION LIGHT/BEACON(RED)

7 LOGO LIGHTS8 ENGINE SCAN LIGHTS9 WING SCAN LIGHTS

10WING STROBE LIGHT (HIGH INTENSITY,WHITE)

11TAIL STROBE LIGHT (HIGH INTENSITY,WHITE)

12 TAXI CAMERA LIGHTS (NLG)

13 TAXI CAMERA LIGHTS (MLG)

14 LANDING LIGHTS15 RUNWAY TURN-OFF LIGHTS16 TAXI LIGHTS17 TAKE-OFF LIGHTS18 CARGO COMPARTMENT FLOOD LIGHTS

19 LANDING GEAR BAY/WELL LIGHTS (DOME)

2-10-0Page 1

Dec 01/16


**ON A/C A380-800

RH

LH

11

3

2

1

10 4

7

5

8 9

13

12

6

L_AC_021000_1_0070101_01_00

Exterior LightingFIGURE-2-10-0-991-007-A01

2-10-0Page 2

Dec 01/16


**ON A/C A380-800

17 15

14

16

L_AC_021000_1_0080101_01_00


2-10-0Page 3

Dec 01/16


**ON A/C A380-800

2

15 15

3

1

17

88

L_AC_021000_1_0090101_01_00


2-10-0Page 4

Dec 01/16


**ON A/C A380-800

11

1010

16

14

5 5 6

16

9 9

14

L_AC_021000_1_0100101_01_00


2-10-0Page 5

Dec 01/16


**ON A/C A380-800

19 191818

EXAMPLE FOR LIGHT N° 18

CEILING LIGHT

SPOT LIGHT

GROUND

7

7

L_AC_021000_1_0110101_01_00


2-10-0Page 6

Dec 01/16


2-11-0 Antennas and Probes Location

**ON A/C A380-800

Antennas and Probes Location

1. This section gives the location of antennas and probes.

2-11-0Page 1

Dec 01/16


**ON A/C A380-800

VHF(1)ELTVHF(3)

ADF(2)

ADF(1)

SATCOM(1)

TCAS TOP(2)

TCAS TOP(1)

GPS(1)

GPS(2)

MFP(1)

ISP(1−1)

ISP(3−1)

ISP(2−1) RADIO ALTIMETRE(1)

RADIO ALTIMETRE(2)

RADIO ALTIMETRE(3)

HF

VHF(2)MARKER

VOR

MFP(3)

ISP(2−2)

ISP(1−2)

MFP(2)

STBY STATIC PROBE(2)

TCAS BOTTOM(2)

DME(1) BOTTOM

TCAS BOTTOM(1)

DME(2) BOTTOM

ISP(3−2)

WEATHER RADAR

ICE DETECTOR PROBE RH

SSA(2/3)

SSA(1)

GLIDE TRACK

STBY STATIC PROBE(1)STBY PITOT

LOCGLIDE CAPTURE

ICE DETECTOR PROBE LH

L_AC_021100_1_0010101_01_00

Antennas and ProbesLocation

FIGURE-2-11-0-991-001-A01

2-11-0Page 2

Dec 01/16


2-12-0 Power Plant

**ON A/C A380-800

Auxiliary Power Unit

1. General- The APU is installed in the tail cone, at the rear part of the fuselage (Section 19.1), inside a

fireproof compartment (between frames 112 and 117).- The Air Intake System is located on top of the APU and crosses the space between the APU

plenum chamber and the aircraft outside (upper right side position). The Air Intake Housing islocated between frames 111 and 113 and the Air Intake Duct is located in the space betweenframes 113 and 115.

- The Exhaust Muffler is located at the end of the tail cone, aligned with the APU and crossesthree different zones, from frame 116 to the rear fairing.

- The Electronic Control Box (ECB) is installed in an electronic cooled rack, closed to frame 95,within the pressurized fuselage.

2. Controls and IndicationPrimary APU controls and indications are installed in the cockpit, mainly in the overhead panel,center pedestal panel and forward center panel. Additionally, two external emergency shutoff controlsare installed on the Nose Landing Gear panel and on the Refuel/Defuel panel.

2-12-0Page 1

Dec 01/16


**ON A/C A380-800

THE DISTANCE FROM FR94, FR98, FR100 BOTTOMCENTERLINE TO FUSELAGE DATUM (FD) AS FOLLOWS:

NOTE:

FR117/

FR112/

FR110/

A

STA72320

STA72922

STA75622

317AB

315AL

313AB

313AZ

FR112 TO FD = 974.9 mm (38.38 in)FR117 TO FD = 1 772.4 mm (69.78 in)FR120 TO FD = 2 239.8 mm (88.18 in).

A B

315BL

315AR

Z310

L_AC_021200_1_0010101_01_00

Auxiliary Power UnitAccess Doors

FIGURE-2-12-0-991-001-A01

2-12-0Page 2

Dec 01/16


**ON A/C A380-800

EXHAUSTMUFFLER

FIREWALL

FIRE EXTINGUISHERBOTTLE

FIREWALL

AIR INTAKEDUCT ASSEMBLY

COOLING AIR DUCT

BLEEDLINE

FR112/

FR117/

FR110/

STA72922

STA72320

STA75622

B

L_AC_021200_1_0020101_01_00

Auxiliary Power UnitGeneral Layout

FIGURE-2-12-0-991-002-A01

2-12-0Page 3

Dec 01/16


**ON A/C A380-800

Engine and Nacelle

1. Engine and Nacelle - GP 7200 Engine

A. EngineThe engine is a high by-pass ratio, two-rotor, axial flow turbofan engine with a highcompression ratio. The Engine has Four Major Sections as Follows:- compressor section- combustion section- turbine sectionaccessory drive section.The compressor section supplies High Pressure (HP) compressed air to the diffuser/burner forcore engine thrust, aircraft service bleed systems, and by-pass air for thrust. A five-stage LowPressure (LP) compressor rotor assembly is located to the rear of the fan rotor. An acousticsplitter fairing directs the primary airstream into the nine-stage HP compressor rotor assembly.The HP compressor has three stages of variable Inlet Guide Vanes (IGVs) and external bleedsfrom stages four, seven, and nine, with an internal bleed from stage six.The combustion section receives compressed heated air from the HP compressor and fuel fromthe fuel nozzles. The mixture of hot air and fuel is ignited and burned in the single-annularcombustion chamber to generate a HP stream of hot gas to turn the HP turbine and LPturbine.The turbine section consists of HP turbine and LP turbine. The two-stage HP turbine rotorassembly receives the hot gas from the diffuser/burner. The HP turbine supplies the power toturn the HP compressor. The six-stage LP turbine has an active clearance control system formore efficient engine operation. The LP turbine provides the power to turn the LP compressorand fan rotor. The Turbine Exhaust Case (TEC) assembly supplies the structural support for therear of the engine. The TEC straightens the exhaust gas flow as it exits the engine.The accessory drive section consists of Main Gearbox (MGB) and Angle Gearbox (AGB). TheMGB supplies the power to turn the attached engine and aircraft accessories. The AGBtransmits the power from the engine rotor to the MGB. During engine start, the AGB transmitsthe power from the MGB to turn the engine rotor.The LP rotor system is independent of the HP rotor system. The LP rotor system consists ofthe LP compressor and the LP turbine. The HP rotor system consists of the HP compressor andthe HP turbine.

B. NacelleThe Nacelle gives an aerodynamic shape to the engine and supports the thrust reverser system.Each engine is housed in a nacelle suspended from a pylon attached below the wing.The nacelle consists of the following major components:

(1) Air Intake Cowl AssemblyThe air intake cowl is an interchangeable aerodynamic cowl installed on the forward faceof the engine fan case with bolts. It is designed to provide contour for airflow entering theengine and attenuates the fan noise.

2-12-0Page 4

Dec 01/16


(2) Fan Cowl AssemblyThe fan-cowl doors are an assembly of aerodynamic cowls attached to the aircraft pylonstructure through its hinges. It is installed between the air intake cowl and the fan exhaustcowl/thrust reverser, around the engine fan case. It is composed of two semicircularpanels, the left and the right fan cowl door.

(3) Thrust ReverserThe thrust reverser assembly is installed at the aft part of the nacelle. The thrust reversercowls are installed on the aircraft inboard engines. It is attached to the wing pylon byhinges. The thrust reverser assembly is a standard fixed cascade, translating cowl andblocker door type thrust reverser. It is only installed on the aircraft inboard positionnacelles. It is made of two halves that make a duct around the engine. Each half consistsof a fixed structure, which gives support for the cascades and actuation system and atranslating cowl.The thrust reverser assembly encloses the engine core with an aerodynamic flow path anduses the outer translating cowl to give a fan exhaust duct and nozzle exit.In stow mode, the thrust reverser is an aerodynamic structure that adds to the enginethrust generation.In reverse mode, it is used to turn and direct the fan exhaust air in the forward directionusing blocker door through the cascades. The thrust reverser increases the aircraft brakingfunction in order to reduce the landing or aborted take-off distance, especially on acontaminated runway.

(4) Fan Exhaust Cowl AssemblyThe fan exhaust cowls is a component of the aircraft propulsion system nacelle. It isinstalled at the aft part of the nacelle. The fan exhaust cowls are installed on the aircraftoutboard engines.The fan exhaust cowls are attached to the wing pylon by hinges. The two halves of the fanexhaust cowl close the engine core with an aerodynamic flow path.The fan exhaust structure has two half-cowls hinged at the top to the wing pylon andlatched together at the bottom centerline. Its forward end is secured on the aft of the fancase and aft of the intermediate engine case.

(5) Exhaust SystemThe primary air flow is the part of the air absorbed by the engine that enters into theengine combustor and that is exhausted to atmosphere through the turbine exhaustsystem.The turbine exhaust flow path is formed by the inner wall of the exhaust nozzle and theouter wall of the exhaust plug.The secondary air flow is the part of the air absorbed by the fan that bypasses the coreengine and flows through the thrust reverser and fan exhaust cowl directly to theatmosphere.

2-12-0Page 5

Dec 01/16


2. Engine and Nacelle -TRENT 900 Engine

A. EngineThe RB211-TRENT 900 engine is a high by-pass ratio, triple spool turbo-fan.The principal modules of the engine are:- Low Pressure Compressor (LPC) rotor- Intermediate Pressure (IP) compressor- Intermediate case- HP system (this includes the High Pressure Compressor (HPC), the combustion system and

the High Pressure Turbine (HPT))- IP turbine- external gearbox- LPC case- Low Pressure Turbine (LPT)The Intermediate Pressure (IP) and Low Pressure Compressor (LPC)/Low Pressure Turbine(LPT) assemblies turn in a counter clockwise direction and the High Pressure Compressor(HPC)/ High Pressure Turbine (HPT) assembly turns in a clockwise direction (when seen fromthe rear of the engine) during engine operation.The compressors increase the pressure of the air, which flows through the engine. The necessarypower to turn the compressors is supplied by turbines.The LP system has a one-stage compressor installed at the front of the engine. A shaft connectsthe single-stage LPC to a five-stage axial flow turbine at the rear of the gas generator. The gasgenerator also includes an eight-stage IP compressor, a six-stage HPC and a combustion system.Each of the compressors in the gas generator is connected to, and turned by, a different turbine.Between the HPC and the HPT is the annular combustion system which burns a mixture of fueland air to supply energy as heat. Behind the LPT there is a collector nozzle assembly throughwhich the hot gas exhaust flows.

B. NacelleA nacelle gives the engine an aerodynamic shape and supports the thrust reverser system. Eachengine is housed in a nacelle suspended from a pylon attached below the wing.The nacelle consists of the following major components:

(1) Air Intake Cowl AssemblyThe air intake cowl is an interchangeable aerodynamic cowl installed at the front of theengine. It ducts the airflow to the fan and the engine core. The cowl has panels for easyaccess to the components. Acoustic materials are used in the manufacture of the cowl tohelp decrease the engine noise.

(2) Fan Cowl AssemblyThe fan cowl assembly has two semicircular panels, the left fan cowl door and the rightfan cowl door. The installation of the fan cowl doors is around the engine fan casebetween the air intake cowl and the thrust reverser cowl.

2-12-0Page 6

Dec 01/16


The fan Cowl Opening System (COS) have two electrical actuators which open or closethe fan cowls. Personnel operate the actuators from the ground only during enginemaintenance operations. The personnel use a switch box located on the air intake cowl.

(3) Thrust ReverserThe thrust reverser assembly is installed at the aft part of the nacelle. The thrust reversersare installed on the aircraft inboard engines. It is attached to the wing pylon by hinges.The thrust reverser assembly is a standard fixed cascade, translating cowl and blocker doortype thrust-reverser. It is only installed on the aircraft inboard engine nacelles. It is madeof two halves that make a duct around the engine. Each half has a fixed structure thatholds the cascades, the actuation system and a translating cowl.The thrust reverser assembly closes the engine core with an aerodynamic flow path anduses the outer translating cowl to make a fan exhaust duct and nozzle exit.In stow mode, the thrust reverser is an aerodynamic structure that makes the enginethrust.In reverse mode, it changes the direction of the fan exhaust air in the forward direction byuse of the blocker doors through the cascades. The thrust reverser increases the aircraftbraking and speed braking function in order to decrease the landing or aborted take-offdistance, especially on a dirty runway.

(4) Fan Exhaust Cowl AssemblyThe fan exhaust cowl is a component of the aircraft engine nacelle. It is installed at the aftpart of the nacelle. The fan exhaust structures are installed on the aircraft outboardengines. They are attached to the wing pylon by hinges. The left and right fan exhauststructures closed the engine core with an aerodynamic flow path. The structure gives a fireprotection and a support for the aerodynamic, inertial and engine loads.The fan exhaust structure has left and right cowls hinged at the top to the wing pylon andlatched together at the bottom centerline. Its forward end is attached at the aft of the fancase.

(5) Exhaust SystemPrimary air is the part of the air absorbed by the fan that enters the engine near the fanblade platform, continues through the Low Pressure (LP) and High Pressure (HP)compressors, the combustor, and the HP and LP turbines, and is accelerated andexhausted to the atmosphere through the turbine exhaust system.The turbine exhaust flow path is formed by the inner surface of the exhaust nozzle and theouter surface of the exhaust plug.Secondary air is the part of the air absorbed by the fan that is directly discharged from theouter portion of the fan, by-passes the core engine and flows through the fan exhaust tothe atmosphere.

2-12-0Page 7

Dec 01/16


**ON A/C A380-800

3.15 m(10.33 ft)

LPTURBINE

HP COMPRESSOR

COMBUSTORSECTION

2.77 m(9.09 ft)

4.72 m(15.49 ft)

4.93 m(16.17 ft)

TURBINEEXHAUST

CASE

ANGLEGEARBOX

MAINGEARBOX

DRIVE SECTIONACCESSORY

TURBINECENTER FRAME

HPTURBINE

A

A

LP COMPRESSOR

1.93 m(6.33 ft)

L_AC_021200_1_0030101_01_00

Power Plant HandlingEngine Dimensions - GP 7200 Engine

FIGURE-2-12-0-991-003-A01

2-12-0Page 8

Dec 01/16


**ON A/C A380-800

NOSECOWL

INBOARD POSITION

OUTBOARD POSITION

3.8 m(12.47 ft)

A

1.5 m(4.92 ft)

PLUG

PRIMARY NOZZLE

THRUST REVERSERFAN COWL

2.18 m(7.15 ft)

2.52 m(8.27 ft)

1.17 m(3.84 ft)

2.33 m(7.64 ft)

1.31 m(4.3 ft)

A

3.9 m(12.8 ft)

2.11 m(6.92 ft)

L_AC_021200_1_0040101_01_00

Power Plant HandlingNacelle Dimensions - GP 7200 Engine

FIGURE-2-12-0-991-004-A01

2-12-0Page 9

Dec 01/16


**ON A/C A380-800

45° C

B

ALL ENGINES

6.8 m(22.31 ft)45°

A

MIN. MAX.

A

ENGINE 1−4

2.64 m(8.66 ft)

B

3.14 m(10.3 ft)

MIN. MAX.

ENGINE 2−3

1.86 m(6.1 ft)

2.16 m(7.09 ft)

C

SEE AC SECTION2−3−0

NOTE:

: FAN COWL

1 1

B AND C DEPENDING ON AIRCRAFT CONFIGURATION.

1

A

A

AA

A

POSITIONOPEN

L_AC_021200_1_0050101_01_00

Power Plant HandlingFan Cowls - GP 7200 EngineFIGURE-2-12-0-991-005-A01

2-12-0Page 10

Dec 01/16


**ON A/C A380-800

6.32 m(20.73 ft)45°

AMIN. MAX.

1.86 m(6.1 ft)

B

2.16 m(7.09 ft)


NOTE:

5.8 m(19.03 ft)35°

1.52 m(4.99 ft)

1.82 m(5.97 ft)

C

: THRUST REVERSER1


45°35°C

BC

B

A A11

1 1

A

A

A

POSITIONOPEN

L_AC_021200_1_0060101_01_00

Power Plant HandlingThrust Reverser Cowls - GP 7200 Engine

FIGURE-2-12-0-991-006-A01

2-12-0Page 11

Dec 01/16


**ON A/C A380-800

NOTE: B AND C DEPENDING ON AIRCRAFT CONFIGURATION.

6.32 m(20.73 ft)

AMIN. MAX.

2.64 m(8.66 ft)

3.14 m(10.3 ft)


5.8 m(19.03 ft)

2.3 m(7.55 ft)

2.8 m(9.19 ft)

CB

: FAN EXHAUST COWL

45°35°C

BC

B

A A

A

A

A

1 11 1

1

45°

35°

POSITIONOPEN

L_AC_021200_1_0070101_01_01

Power Plant HandlingFan Exhaust Cowls - GP 7200 Engine

FIGURE-2-12-0-991-007-A01

2-12-0Page 12

Dec 01/16


**ON A/C A380-800

1.88 m(6.17 ft)

5.14 m(16.86 ft)

1.5 m(4.92 ft)

(2.59 ft)

8.07 m(26.48 ft)

IP COMPRESSOR

SECTIONCOMBUSTOR

IP TURBINE

HP TURBINE

HP COMPRESSOR

ACCESSORY DRIVE SECTION

1.66 m(5.45 ft)

PLUG

3.11 m(10.2 ft)

LP COMPRESSOR

0.79 m

LP TURBINE

NOZZLETURBINE EXHAUST

1.84 m(6.04 ft)

A

A

L_AC_021200_1_0080101_01_00

Power Plant HandlingEngine Dimensions - TRENT 900 Engine

FIGURE-2-12-0-991-008-A01

2-12-0Page 13

Dec 01/16


**ON A/C A380-800

INBOARD

OUTBOARD

INSTALLATION

INSTALLATION

PLUG

PRIMARY NOZZLE

THRUST REVERSER

FAN COWL

NOSE COWL

2.38 m(7.81 ft)

3.9 m(12.8 ft)

1.18 m(3.87 ft)

3.88 m(12.73 ft)

1.3 m(4.27 ft)

1.63 m(5.35 ft)

2.18 m(7.15 ft)

2.39 m(7.84 ft)

A

A

FWD

2.19 m(7.19 ft)

L_AC_021200_1_0090101_01_00

Power Plant HandlingNacelle Dimensions - TRENT 900 Engine

FIGURE-2-12-0-991-009-A01

2-12-0Page 14

Dec 01/16


**ON A/C A380-800

OPEN POSITIONS:INITIAL: 40°FULL: 50°

40°50°

INBOARD ENG. OUTBOARD ENG. INBOARD ENG. OUTBOARD ENG.

B C

1.3 m(4.27 ft)1.3 m

(4.27 ft)

2.27 m(7.45 ft)2.27 m(7.45 ft)

2 m(6.56 ft)2.4 m

(7.87 ft)

3 m(9.84 ft)

3.4 m(11.15 ft)

OPENPOSITION

40°

50°

A

C

B

A

A

AA

A

ALL ENG.

A

6.95 m(22.8 ft)7.3 m

(23.95 ft)

1 1

: FAN COWL1

L_AC_021200_1_0100101_01_00

Power Plant HandlingFan Cowls - TRENT 900 Engine

FIGURE-2-12-0-991-010-A01

2-12-0Page 15

Dec 01/16


**ON A/C A380-800

NOTE: B AND C DEPENDING ON AIRCRAFT CONFIGURATION.

6.32 m(20.73 ft)

AMIN. MAX.

1.86 m(6.1 ft)

B

2.16 m(7.09 ft)


5.8 m(19.03 ft)

1.52 m(4.99 ft)

1.82 m(5.97 ft)

C

: THRUST REVERSER1

45°35°C

BC

B

A A11

1 1

A

A

A

45°

35°

POSITIONOPEN

L_AC_021200_1_0110101_01_00

Power Plant HandlingThrust Reverser Cowls - TRENT 900 Engine

FIGURE-2-12-0-991-011-A01

2-12-0Page 16

Dec 01/16


**ON A/C A380-800

NOTE:

1


6.32 m(20.73 ft)

AMIN. MAX.

2.64 m(8.66 ft)

3.14 m(10.3 ft)


5.8 m(19.03 ft)

2.3 m(7.55 ft)

2.8 m(9.19 ft)

C

: FAN EXHAUST COWL

B

45°35°C

BC

B

A A11

1 1

A

A

A

45°

35°

POSITIONOPEN

L_AC_021200_1_0120101_01_01

Power Plant HandlingFan Exhaust Cowls - TRENT 900 Engine

FIGURE-2-12-0-991-012-A01

2-12-0Page 17

Dec 01/16


2-13-0 Leveling, Symmetry and Alignment

**ON A/C A380-800

Leveling, Symmetry and Alignment

1. Quick LevelingThere are three alternative procedures to level the aircraft:- Quick leveling procedure with Air Data/Inertial Reference System (ADIRS).- Quick leveling procedure with a spirit level in the upper or main deck passenger compartment.- Quick leveling procedure with a spirit level in the FWD cargo compartment.

2. Precise LevelingFor precise leveling, it is necessary to install sighting rods in the receptacles located under thefuselage (points 11 and 16 for longitudinal leveling) and under the wings (points 1L and 1R for lateralleveling) and use a sighting tube. With the aircraft on jacks, adjust the jacks until the referencemarks on the sighting rods are aligned in the sighting plane (aircraft level).

3. Symmetry and Alignment CheckPossible deformation of the aircraft is measured by photogrammetry.

2-13-0Page 1

Dec 01/16


**ON A/C A380-800

FR35FR36

FR88

FR89

RIB6

RIB61L

11

1R

16

L_AC_021300_1_0010101_01_00

Location of Leveling PointsFIGURE-2-13-0-991-001-A01

2-13-0Page 2

Dec 01/16


2-14-0 Jacking

**ON A/C A380-800

Jacking for Maintenance

1. Aircraft Jacking Points for Maintenance

A. General

(1) The A380-800 can be jacked:- At not more than 333 700 kg (735 682 lb),- Within the limits of the permissible wind speed when the aircraft is jacked outside a

closed environment.

B. Primary Jacking Points

(1) The aircraft is provided with three primary jacking points:- One located under the forward fuselage,- Two located under the wings (one under each wing).

(2) Three jack adapters (ground equipment) are used as intermediary parts between theaircraft jacking points and the jacks:- One male spherical jack adapter at the forward fuselage,- Two female spherical jack pad adapters at the wings (one at each wing).

C. Auxiliary Jacking Point (Safety Stay)

(1) When the aircraft is on jacks, a safety stay is installed under the AFT fuselage (Ref.FIGURE 2-14-0-991-001-A) to prevent tail tipping caused by accidental displacement ofthe aircraft center of gravity.

(2) The safety point must not be used for lifting the aircraft.

(3) One male spherical stay adapter (ground equipment) is used as an intermediary partbetween the aircraft safety point and the stay.

2. Jacks and Safety Stay

A. Jack Design

(1) The maximum eligible loads given in the table (Ref. FIGURE 2-14-0-991-001-A) are themaximum loads applicable on jack fittings.

(2) In fully retracted position (jack stroke at minimum), the height of the jacks is such thatthe jack may be placed beneath the aircraft under the most adverse conditions, namely,tires deflated and shock absorbers depressurized, with sufficient clearance between theaircraft jacking point and the jack upper end.

(3) The jacks stroke enables the aircraft to be jacked up so that the Fuselage Datum Line(FDL) may be positioned up to 7 200 mm (283.46 in) from the ground to allow allrequired maintenance procedures and in particular, the removal/installation of the landing-gear shock absorbers.

2-14-0Page 1

Dec 01/16


B. Safety Stay

(1) The stay stroke enables the aircraft tail to be supported up to the Fuselage Datum Line(FDL) positioned 7 200 mm (283.46 in) from the ground.

2-14-0Page 2

Dec 01/16


**ON A/C A380-800

FWD JACKINGPOINT

WING JACKINGPOINT

SAFETYSTAY

Y

X

A C

B’

B

NOTE: SAFETY STAY IS NOT USED FOR JACKING.

SAFETY STAY

WING JACKINGPOINT

C

B’

B

FORWARD FUSELAGEJACKING POINT A

7.29 23.92 0

12.22

−12.22

0

0

40.09

−40.09

0

MAXIMUMLOAD ELIGIBLE

m ft daN

YX

m ft

35.23

35.23

59.34

115.58

115.58

194.68

34 011

157 480

157 480

7 874

WING JACKINGPOINT

L_AC_021400_1_0010101_01_00

Jacking for MaintenanceJacking Points Location

FIGURE-2-14-0-991-001-A01

2-14-0Page 3

Dec 01/16


**ON A/C A380-800

AIRCRAFT ON WHEELS WITH STANDARD TIRES, MAX. JACKWEIGHT 333 700 kg (735 682 lb)AIRCRAFT ON WHEELS, SHOCK ABSORBERS DEFLATED ANDTIRES FLAT

AIRCRAFT ON WHEELS, NOSE LANDING GEAR SHOCKABSORBERS DEFLATED AND TIRES FLAT

AIRCRAFT ON WHEELS, LEFT WING AND BODY LANDINGGEARS SHOCK ABORBERS DEFLATED AND TIRES FLAT (SAMEDATA FOR RIGHT SIDE CONDITIONS)AIRCRAFT ON WHEELS, WING AND BODY LANDING GEARSSHOCK ABSORBERS DEFLATED AND TIRES FLAT

AIRCRAFT ON JACKS, FUSELAGE DATUM LINEPARALLEL TO GROUND AT 6 350 mm (250 in) FOR LANDINGGEARS EXTENSION/RETRACTION

2 472 mm(97.32 in)

2 259 mm(88.94 in)

2 296 mm(90.39 in)

2 474 mm(97.4 in)

2 391mm(94.13 in)

3 673 mm(144.61 in)

5 112 mm(201.26 in)

4 788 mm(188.5 in)

5 117 mm(201.46 in)

4 523 mm(178.07 in)

4 803 mm(189.09 in)

6 158 mm(242.44 in)

4 707 mm(185.31 in)

4 462 mm(175.67 in)

5 044 mm(198.58 in)

4 257 mm(167.6 in)

4 291 mm(168.94 in)

5 830 mm(229.53 in)

AIRCRAFT ON JACKS, FUSELAGE DATUM LINEPARALLEL TO GROUND AT 7 200 mm (283.46 in) FOR LANDINGGEARS REMOVAL/INSTALLATION

L M N

4 523 mm(178.07 in)

7 008 mm(275.91 in)

6 680 mm(262.99 in)

LN

FUSELAGE DATUM LINE

M

AIRCRAFT JACKED AT FORWARD JACKING POINT,WING AND BODY LANDING GEARS WHEELS ON THE GROUND,FOR NOSE LANDING GEAR EXTENSION/RETRACTION TEST

4 523 mm(178.07 in) N/A 2 910 mm

(114.57 in)

L_AC_021400_1_0020101_01_01

Jacking for MaintenanceJacking Dimensions

FIGURE-2-14-0-991-002-A01

2-14-0Page 4

Dec 01/16


**ON A/C A380-800

FR20

A

B

A

ADAPTOR−JACK NOSE

Z−2676.63

B

L_AC_021400_1_0030101_01_00

Jacking for MaintenanceForward Jacking Point

FIGURE-2-14-0-991-003-A01

2-14-0Page 5

Dec 01/16


**ON A/C A380-800

RIB16

OUTER SKIN

JACKING PAD SET− WING

B

AEXAMPLE

Z−147

B

A

ARIB16RIB16

LOWER SURFACE

L_AC_021400_1_0100101_01_00

Jacking for MaintenanceWing Jacking Point

FIGURE-2-14-0-991-010-A01

2-14-0Page 6

Dec 01/16


**ON A/C A380-800

FR101

A

ADAPT−SUPP, AFT JACK

FR101

A

Z−519.589

FWD

L_AC_021400_1_0110101_01_00

Jacking for MaintenanceAuxiliary Jacking Point - Safety Stay

FIGURE-2-14-0-991-011-A01

2-14-0Page 7

Dec 01/16


**ON A/C A380-800

Jacking of the Landing Gear

1. To replace a wheel or wheel brake assembly on any of the landing gears it is necessary to lift thelanding gear with a jack. The landing gear can be lifted by a pillar jack or with a cantilever jack.

NOTE : You can lift the aircraft at Maximum Ramp Weight (MRW).

NOTE : The load at each jacking position is the load required to give a 25.5 mm (1 in) clearancebetween the ground and the tire.

A. Nose Landing Gear (NLG)The nose gear can be lifted with a pillar jack or a cantilever jack. The NLG has a dome shapedjacking adaptor at the base of the shock absorber strut. The adapter is 31.75 mm (1.25 in) indiameter.Important dimensions of the NLG when lifted are shown in FIGURE 2-14-0-991-004-A.

NOTE : The maximum load at NLG jacking point is 42 000 daN (94 420 lbf).

B. Wing Landing Gear (WLG)An adapter at the front and rear of each bogie is fitted to make sure that the jack is locatedcorrectly. The adapter is 31.75 mm (1.25 in) in diameter. The wheels and brake units can bereplaced on the end of the bogie beam that is lifted.The FWD and AFT ends of the bogie can be lifted at the same time. When lifting both ends atthe same time the bogie beam must always be kept level to prevent damage.If a WLG has all four tires deflated or shredded, replace the wheel assemblies in this sequence:- Replace the wheel assemblies on the AFT axle,- Replace the wheel assemblies on the FWD axle.

Important dimensions of the WLG when lifted are shown in FIGURE 2-14-0-991-005-A.

NOTE : The maximum load at each WLG jacking point is 80 000 daN (179 847 lbf).

C. Body Landing Gear (BLG)An adapter at the front and at the rear of each bogie is fitted to make sure that the jack islocated correctly. The adapter is 31.75 mm (1.25 in) in diameter. Both wheels and brake unitscan be replaced on the end of the bogie beam that is lifted.For a center wheel change only, the FWD and AFT ends of the bogie can be lifted at the sametime. When lifting both ends at the same time the bogie beam must always be kept level toprevent damage.If a BLG has all six tires deflated or shredded, replace the wheel assemblies in this sequence:- Replace the wheel assemblies on the AFT axle,- Replace the wheel assemblies on the center axle,- Replace the wheel assemblies on the FWD axle.

Important dimensions of the BLG when lifted are shown in FIGURE 2-14-0-991-006-A.

2-14-0Page 8

Dec 01/16


NOTE : The maximum load at BLG jacking point is 136 000 daN (305 740 lbf).

2-14-0Page 9

Dec 01/16


**ON A/C A380-800

DATA FOR 1 270 x 455 R22 TIRES

MRW = 562 000 kg (1 238 998 lb)MLW = 386 000 kg (850 984 lb)

NOTE: DIMENSIONS IN MILLIMETERS (INCHES IN BRACKETS)

VIEW LOOKING INBOARD LHS(LH WHEEL NOT SHOWN) A

B

CONFIGURATION WEIGHT CG%

MRW 43

MRW 43

MLW−PAX

44

DIM. B

2 INFLATED TIRES 400 (15.75)

DIM. A

541 (21.3)

1 INFLATED TIRE 353 (13.9) 530 (20.87)

2 DEFLATED TIRES +50%RIM DAMAGE

29 134 (5.28) 519 (20.43)

2 DEFLATED TIRESNO RIM DAMAGE


136 (5.35) 519 (20.43)

519 (20.43)29 164 (6.46)

N/A N/A

N/A N/A

MAXIMUM JACKINGHEIGHT TO CHANGEWHEELS

N/A 506 (19.92) N/A

168 (6.61)

137 (5.39)

166 (6.54) 519 (20.43)

519 (20.43)

519 (20.43)


44



N/A

MLW−PAX

MLW−PAX

MLW−PAX

L_AC_021400_1_0040101_01_00

Nose Landing Gear Jacking Point HeightsFIGURE-2-14-0-991-004-A01

2-14-0Page 10

Dec 01/16


**ON A/C A380-800

A

B

CONFIGURATION WEIGHT CG%DIM. A FWD

DIM. A AFT

DIM. B DIM. C

ALL 4 TIRES SERVICEABLE MRW 43 347 (13.66) 347 (13.66) 750 (29.53)

1 FWD TIRE DEFLATED MRW 43 264 (10.39) 353 (13.9) 718 (28.27)

1 AFT TIRE DEFLATED MRW 43 353 (13.9) 264 (10.39) 718 (28.27)

2 DEFLATED FWD TIRES +50% RIM DAMAGE

44 93 (3.66) 406 (15.98) 686 (27.01)

2 DEFLATED AFT TIRES +50% RIM DAMAGE

44

+50% RIM DAMAGE4 TIRES DEFLATED 44

FWD TIRE CHANGE MAX. GROWN TIRE MRW 43 513 (20.2) 331 (13.03) 795 (31.3)

AFT TIRE CHANGE MAX. GROWN TIRE MRW 43 513 (20.2) 795 (31.3)

20 FLAT TIRES+50% RIM DAMAGE

N/A N/A 83 (3.27) 686 (27.01)


C

MLW−PAX

MLW−PAX

MLW−PAX

MRW = 562 000 kg (1 238 998 lb)MLW = 386 000 kg (850 984 lb)

NOTE: DIMENSIONS IN MILLIMETERS (INCHES IN BRACKETS)

364 (14.33)

686 (27.01)

686 (27.01)

93 (3.66)406 (15.98)

93 (3.66) 93 (3.66)

331 (13.03)

83 (3.27)

A

364 (14.33)

364 (14.33)

364 (14.33)

364 (14.33)

364 (14.33)

364 (14.33)

364 (14.33)

364 (14.33)

L_AC_021400_1_0050101_01_00

Wing Landing Gear Jacking Point HeightsFIGURE-2-14-0-991-005-A01

2-14-0Page 11

Dec 01/16


**ON A/C A380-800

MLW = 386 000 kg (850 984 lb)

NOTE: DIMENSIONS IN MILLIMETERS (INCHES IN BRACKETS)MRW = 562 000 kg (1 238 998 lb)

C

B

A

CONFIGURATION WEIGHT CG%

MRW 43

MRW 43

DIM. AFWD


N/A N/A

DIM. AAFT

DIM. B DIM. CFWD

DIM. CAFT

ALL 6 TIRESSERVICEABLE

347 (13.66) 312 (12.28) 930 (36.61) 460 (18.11) 432 (17.01)

1 FWD TIREUNSERVICEABLE

295 (11.61) 328 (12.91) 898 (35.35)

MRW 43

MRW 43

MRW 43

43

MLW−PAX

43

1 CENTER TIREUNSERVICEABLE MRW 334 (13.15) 299 (11.77)

1 AFT TIREUNSERVICEABLE

363 (14.29) 260 (10.24)

2 FWD TIRESDEFLATED +50%RIM DAMAGE

44 74 (2.91) 505 (19.88) 866 (34.09)

2 CENTER TIRESDEFLATED

44 358 (14.09) 323 (12.72)

2 AFT TIRESDEFLATED +50%RIM DAMAGE

44 540 (21.26) 40 (1.57)

6 TIRES DEFLATED+50% RIMDAMAGE

44 74 (2.91) 39 (1.54)

FWD TIRE CHANGEMAX. GROWN TIRE

496 (19.53) 264 (10.39) 975 (38.39)

CTR TIRE CHANGEPOSITIONMAX. GROWN TIRE

MRW 461 (18.15) 975 (38.39)

AFT TIRE CHANGEMAX. GROWN TIRE

299 (11.77) 461 (18.15) 975 (38.39)

20 DEFLATEDTIRES +50% RIMDAMAGE

102 (4.02) 67 (2.64) 866 (34.09)

460 (18.11) 432 (17.01)

460 (18.11) 432 (17.01)

460 (18.11) 432 (17.01)

460 (18.11) 432 (17.01)

460 (18.11) 432 (17.01)

460 (18.11) 432 (17.01)

460 (18.11) 432 (17.01)

460 (18.11) 432 (17.01)

460 (18.11) 432 (17.01)

460 (18.11) 432 (17.01)

460 (18.11) 432 (17.01)

898 (35.35)

898 (35.35)

866 (34.09)

866 (34.09)

866 (34.09)

496 (19.53)

MLW−PAX

MLW−PAX

MLW−PAX

A

L_AC_021400_1_0060101_01_00

Body Landing Gear Jacking Point HeightsFIGURE-2-14-0-991-006-A01

2-14-0Page 12

Dec 01/16


AIRCRAFT PERFORMANCE


**ON A/C A380-800

General Information

1. Standard day temperatures for the altitudes shown are tabulated below :

Standard day temperatures for the altitudes

Altitude Standard Day Temperature

FEET METERS ˚F ˚C0 0 59.0 15.0

2000 610 51.9 11.64000 1220 44.7 7.16000 1830 37.6 3.18000 2440 30.5 -0.8

3-1-0Page 1

Dec 01/16


3-2-1 Payload/Range - ISA Conditions

**ON A/C A380-800

Payload/Range - ISA Conditions

1. This section provides the payload/range at ISA conditions.

3-2-1Page 1

Dec 01/16


**ON A/C A380-800

0

10

20

30

40

50

60

70

80

90

4000 4500 5000 5500 6000 6500 7000 7500 8000 8500 9000 9500 100000

20

40

60

80

140

160

180

2007400 8400 9400 10400 11400 12400 13400 14400 15400 16400 17400 18400

MAXIMUM PASSENGER PAYLOAD

MAXIMUM STRUCTURAL PAYLOAD

RANGE (km)

PA

YLO

AD

(t)

RANGE (nm)

ISA / NO WINDTYPICAL INTERNATIONAL FLIGHT PROFILE

NOTE: THESE CURVES ARE GIVEN FOR INFORMATION ONLY.THE APPROVED VALUES ARE STATED IN THE "OPERATING MANUALS"SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.

100

120

PA

YLO

AD

(x

1000

lb)

200 nm DIVERSION5% TRIP FUEL ALLOWANCE, 30 min HOLDING

L_AC_030201_1_0010101_01_00

Payload/RangeISA Conditions - TRENT 900 Engines

FIGURE-3-2-1-991-001-A01

3-2-1Page 2

Dec 01/16


**ON A/C A380-800

0

10

20

30

40

50

60

70

80

90

4000 4500 5000 5500 6000 6500 7000 7500 8000 8500 9000 9500 100000

20

40

60

80

100

120

140

160

180

2007400 8400 9400 10400 11400 12400 13400 14400 15400 16400 17400 18400

MAXIMUM PASSENGER PAYLOAD

MAXIMUM STRUCTURAL PAYLOAD

RANGE (km)

PA

YLO

AD

(t)

RANGE (nm)

ISA / NO WINDTYPICAL INTERNATIONAL FLIGHT PROFILE


PA

YLO

AD

(x

1000

lb)

200 nm DIVERSION5% TRIP FUEL ALLOWANCE, 30 min HOLDING

L_AC_030201_1_0080101_01_00

Payload/RangeISA Conditions - GP 7200 Engines

FIGURE-3-2-1-991-008-A01

3-2-1Page 3

Dec 01/16


3-3-1 Take Off Weight Limitation - ISA Conditions

**ON A/C A380-800

Take-Off Weight Limitation - ISA Conditions

1. This section provides the take-off weight limitation at ISA conditions.

3-3-1Page 1

Dec 01/16


**ON A/C A380-800


RUNWAY LENGTH (ft)

RUNWAY LENGTH (m)

TA

KE

−O

FF

WE

IGH

T (

t)

300

350

400

450

500

550

600

650

1500 2000 2500 3000 3500 4000 4500 5000 5500660

760

860

960

1060

1160

1260

1360

5000 6000 7000 8000 9000 10000 11000 12000 13000 14000 15000 16000 17000 18000

0

2000

6000

4000

8000

TA

KE

−O

FF

WE

IGH

T (

x 10

00 lb

)

AIRFIELD PRESSURE ALTITUDE (ft)

L_AC_030301_1_0010101_01_00

Take-Off Weight LimitationISA Conditions - TRENT 900 Engines

FIGURE-3-3-1-991-001-A01

3-3-1Page 2

Dec 01/16


**ON A/C A380-800


RUNWAY LENGTH (ft)

RUNWAY LENGTH (m)

TAK

E−O

FF W

EIG

HT

(t)

300

350

400

450

500

550

600

650

1500 2000 2500 3000 3500 4000 4500 5000 5500660

760

860

960

1060

1160

1260

1360

5000 6000 7000 8000 9000 10000 11000 12000 13000 14000 15000 16000 17000 18000

0

2000

6000

4000

8000

TA

KE

−OF

F W

EIG

HT

(x

1000

lb)AIRFIELD PRESSURE ALTITUDE (ft)

L_AC_030301_1_0080101_01_00

Take-Off Weight LimitationISA Conditions - GP 7200 Engines

FIGURE-3-3-1-991-008-A01

3-3-1Page 3

Dec 01/16


3-3-2 Take Off Weight Limitation - ISA + 15 ˚C (59 ˚F) Conditions

**ON A/C A380-800

Take-Off Weight Limitation - ISA + 15 ˚C (+59 ˚F) Conditions

1. This section provides the take-off weight limitation at ISA + 15˚C (+59˚F) conditions.

3-3-2Page 1

Dec 01/16


**ON A/C A380-800


RUNWAY LENGTH (ft)

RUNWAY LENGTH (m)

TA

KE

−O

FF

WE

IGH

T (

t)

300

350

400

450

500

550

600

650

1500 2000 2500 3000 3500 4000 4500 5000 5500660

760

860

960

1060

1160

1260

1360

5000 6000 7000 8000 9000 10000 11000 12000 13000 14000 15000 16000 17000 18000

0

2000

6000

4000

8000

TA

KE

−O

FF

WE

IGH

T (

x 10

00 lb

)AIRFIELD PRESSURE ALTITUDE (ft)

L_AC_030302_1_0010101_01_00

Take-Off Weight LimitationISA + 15 ˚C (+59 ˚F) Conditions - TRENT 900 Engines

FIGURE-3-3-2-991-001-A01

3-3-2Page 2

Dec 01/16


**ON A/C A380-800


RUNWAY LENGTH (ft)

RUNWAY LENGTH (m)

TA

KE

−O

FF

WE

IGH

T (

t)

350

400

450

500

550

600

650

1500 2000 2500 3000 3500 4000 4500 5000 5500660

760

860

960

1060

1160

1260

1360

5000 6000 7000 8000 9000 10000 11000 12000 13000 14000 15000 16000 17000 18000

0

2000

6000

4000

8000

TA

KE

−O

FF

WE

IGH

T (

x 10

00 lb

)300

AIRFIELD PRESSURE ALTITUDE (ft)

L_AC_030302_1_0080101_01_00

Take-Off Weight LimitationISA + 15 ˚C (+59 ˚F) Conditions - GP 7200 Engines

FIGURE-3-3-2-991-008-A01

3-3-2Page 3

Dec 01/16


3-4-1 Landing Field Length - ISA Conditions

**ON A/C A380-800

Landing Field Length

1. This section provides the landing field length on a dry runway.

3-4-1Page 1

Dec 01/16


**ON A/C A380-800


1400

1500

1600

1700

1800

1900

2000

2100

2200

2300

2400

2500

2600

2700

2800

280 300 320 340 360 380 400 420 440 4604600

5000

5400

5800

6200

6600

7000

7400

7800

8200

8600

9000

620 670 720 770 820 870 920 970

GROSS WEIGHT (t)

VALID FOR ALL TEMPERATURES

AIRFIELD ELEVATION (ft)

0

2000

6000

4000

8000

LAN

DIN

G F

IELD

LE

NG

TH

(ft)

LAN

DIN

G F

IELD

LE

NG

TH

(m

)

GROSS WEIGHT (x 1000 lb)

L_AC_030401_1_0010101_01_01

Landing Field LengthDry Runway

FIGURE-3-4-1-991-001-A01

3-4-1Page 2

Dec 01/16


3-5-0 Final Approach Speed

**ON A/C A380-800

Final Approach Speed

1. This section gives the final approach speed which is the indicated airspeed at threshold in the landingconfiguration at the certificated maximum flap setting and maximum landing weight at standardatmospheric conditions. The approach speed is used to classify the aircraft into Aircraft ApproachCategory, a grouping of aircraft based on the indicated airspeed at threshold.

2. The final approach speed is 138 kt at a Maximum Landing Weight (MLW) of 395 000 kg (870 826lb) and classifies the aircraft into the Aircraft Approach Category C.

NOTE : This value is given for information only.

3-5-0Page 1

Dec 01/16


GROUND MANEUVERING


**ON A/C A380-800

General

1. This section provides aircraft turning capability and maneuvering characteristics.

For ease of presentation, this data has been determined from the theoretical limits imposed by thegeometry of the aircraft, and where noted, provides for a normal allowance for tire slippage. As such,it reflects the turning capability of the aircraft in favorable operating circumstances. This data shouldonly be used as a guidelines for the method of determination of such parameters and for themaneuvering characteristics of this aircraft type.

In ground operating mode, varying airline practices may demand that more conservative turningprocedures be adopted to avoid excessive tire wear and reduce possible maintenance problems. Airlineoperating techniques will vary in the level of performance, over a wide range of operatingcircumstances throughout the world. Variations from standard aircraft operating patterns may benecessary to satisfy physical constraints within the maneuvering area, such as adverse grades, limitedarea or a high risk of jet blast damage. For these reasons, ground maneuvering requirements shouldbe coordinated with the airlines in question prior to layout planning.

4-1-0Page 1

Dec 01/16


4-2-0 Turning Radii

**ON A/C A380-800

Turning Radii

1. This section provides the turning radii.

4-2-0Page 1

Dec 01/16


**ON A/C A380-800

NOTE:

R4

R3

R6

FOR TURNING RADII VALUES, REFER TO SHEET 2.

55°

60°

65°

29.83 m

70°

R5

(97.9 ft)

L_AC_040200_1_0010101_01_01

Turning Radii(Sheet 1)

FIGURE-4-2-0-991-001-A01

4-2-0Page 2

Dec 01/16


**ON A/C A380-800

2100.16328.6

TYPEOF

TURN

20°

STEERINGANGLE

17.9°

EFFECTIVESTEERING

ANGLE

mft

135.45444.4

101.01331.4

115.87380.1

278.86258.7

25° 22.7°mft

113.14371.2

80.12262.9

94.90311.4

265.69215.5

30° 27.5°mft

98.90324.5

67.33220.9

81.91268.7

256.84186.5

35° 32.1°mft

88.97291.9

58.83193.0

73.13239.9

250.59166.0

40° 36.6°mft

81.61267.8

52.89173.5

66.84219.3

246.02151.0

45° 41.0°mft

75.94249.1

48.61159.5

62.16203.9

242.61139.8

50° 45.1°mft

71.43234.4

45.45149.1

58.57192.2

140.13131.6

55° 51.2°mft

67.02219.9

43.22141.8

55.43181.9

137.64123.5

60° 57.3°mft

62.60205.4

40.98134.5

52.29171.5

135.15115.3

65° 63.4°mft

58.18190.9

38.75127.1

49.15161.2

132.66107.2

70° 69.5°mft

53.76176.4

36.52119.8

46.01150.9

R3 R4 R5 R6NLG WING NOSE THS

A380−800 TURNING RADII

NOTE:TYPE 1 TURNS USE :ASYMMETRIC THRUST − BOTH ENGINES ON THE INSIDE OF THE TURN TO BE AT IDLE THRUST.DIFFERENTIAL BRAKING − BRAKING APPLIED TO THE WING GEAR WHEELS ON THE INSIDE OF

TYPE 2 TURNS USE :SYMMETRIC THRUST AND NO BRAKING.

THE TURN.

L_AC_040200_1_0020101_01_01

Turning Radii(Sheet 2)

FIGURE-4-2-0-991-002-A01

4-2-0Page 3

Dec 01/16


4-3-0 Minimum Turning Radii

**ON A/C A380-800

Minimum Turning Radii

1. This section provides the minimum turning radii.

4-3-0Page 1

Dec 01/16


**ON A/C A380-800

(MINIMUMTURNING WIDTH)

A

R4

R3

R5Y

R6

55°

60°

65°

70°

TURN PERFORMED WITH ASYMMETRIC THRUST AND DIFFERENTIAL BRAKING.

NOTE:

EFFECTIVESTEERING

ANGLE

STEERINGANGLE

TYPEOF

TURNY

m

ft70° 69.5°

A380−800 MINIMUM TURNING RADIUS

11.08

36.3

A

50.91

167.0

R3 R4 R5 R6NLG WING NOSE THS

32.66

107.2

53.76

176.4

36.52

119.8

46.01

150.91

29.83 m (97.9 ft)

OUTSIDE FACEOF TIRE

L_AC_040300_1_0010101_01_02

Minimum Turning RadiiFIGURE-4-3-0-991-001-A01

4-3-0Page 2

Dec 01/16


4-4-0 Visibility from Cockpit in Static Position

**ON A/C A380-800

Visibility from Cockpit in Static Position

1. This section gives the visibility from cockpit in static position.

4-4-0Page 1

Dec 01/16


**ON A/C A380-800

PERPENDICULAR TOLONGITUDINAL AXIS.

VISUAL ANGLES IN VERTICALPLANE THROUGH PILOTEYE POSITION.

DIMENSIONS ARE APPROXIMATE

107°

CAPTAIN FIELD OF VIEW

121°

107°

MAX AFT VISION WITH HEAD TURNEDAROUND SPINAL COLUMN.WING TIP CAN BE SEEN WHEN HEAD IS MOVEDTO THE SIDE.

VISUAL ANGLES IN HORIZONTALPLANE THROUGH PILOTEYE POSITION.

FIRST OFFICERFIELD OF VIEW

30°

24°

VISUAL ANGLES IN PLANE

30°

121°

NOT TO BE USED FORLANDING APPROACH VISIBILITY

NOTE:PILOT EYE POSITION WHEN PILOT’S EYES ARE IN LINE WITH THE RED AND WHITE BALLS.

ZONE THAT CANNOT BE SEEN

17.36 m(56.96 ft)

4.97 m(16.31 ft)

2.92 m(9.58 ft)7.17 m

(23.52 ft)

31°

19.5°

24°

L_AC_040400_1_0010101_01_01

Visibility from Cockpit in Static PositionFIGURE-4-4-0-991-001-A01

4-4-0Page 2

Dec 01/16


**ON A/C A380-800

CA

PT

AIN

FIE

LD O

F V

IEW

SH

OW

N.

FIR

ST

OF

FIC

ER

FIE

LD O

F V

IEW

SY

MM

ET

RIC

AL.

EX

AM

PLE

: WH

EN

CA

PT

AIN

TU

RN

S H

IS H

EA

D B

Y 9

0° L

EF

T, V

ISIB

ILIT

YW

ILL

BE

30°

UP

AN

D 2

4° D

OW

N T

HR

OU

GH

TH

E S

LID

ING

WIN

DO

W F

RA

ME

.

CA

PT

AIN

FIX

ED

WIN

DO

W

130°

120°

110°

100°

90°

80°

70°

60°

50°

40°

30°

20°

10°

0°10

°20

°30

°40

°50

°60

°70

°80

°90

°100

°110

°120

°130

°140

°

30°

20°

10°

0°10°

20°

30°

40°

50°

CA

PT

AIN

SLI

DIN

GW

IND

OW

CA

PT

AIN

WIN

DS

HIE

LD

FIR

ST

OF

FIC

ER

WIN

DS

HIE

LDF

IRS

T O

FF

ICE

RF

IXE

D W

IND

OW

FIR

ST

OF

FIC

ER

SLI

DIN

G W

IND

OW

PIL

OT

EY

E P

OS

ITIO

N(C

AP

TA

IN P

OS

ITIO

N)

A38

0

AR

P 4

101−

2

24°

150°

L_AC_040400_1_0020101_01_00

Binocular Visibility Through Windows from Captain Eye PositionFIGURE-4-4-0-991-002-A01

4-4-0Page 3

Dec 01/16


4-5-0 Runway and Taxiway Turn Paths

**ON A/C A380-800

Runway and Taxiway Turn Paths

1. Runway and Taxiway Turn Paths

4-5-0Page 1

Dec 01/16



**ON A/C A380-800

135˚ Turn - Runway to Taxiway

1. This section gives the 135˚ turn -- runway to taxiway.

4-5-1Page 1

Dec 01/16


**ON A/C A380-800

APPROX 6.6 m(22 ft)

FILLET R = 25.5 m(85 ft)

TURN R = 45 m(150 ft)

APPROX 4.9 m(16 ft)

OFFSET 7 m(23 ft)

NOMINAL

45 m(150 ft)

23 m(75 ft)

RUNWAYCENTERLINE TAXIWAY CENTERLINE

FAA LEAD−IN FILLET

L = 75 m (250 ft)

NOTE: FAA GROUP V FACILITIES.

NLG PATH

WLG PATH

COCKPIT PATH

L_AC_040501_1_0010101_01_01

135˚ Turn -- Runway to TaxiwayJudgemental Oversteer Method

FIGURE-4-5-1-991-001-A01

4-5-1Page 2

Dec 01/16


**ON A/C A380-800

NLG PATH

WLG PATH

NOTE: FAA GROUP VI FACILITIES.


APPROX 5.8 m(19 ft)

TURN R = 51 m(167 ft)

60 m(200 ft)

30 m(100 ft)

RUNWAY CENTERLINE

TAXIWAY CENTERLINE


L = 75 m (250 ft)

L_AC_040501_1_0020101_01_01

135˚ Turn -- Runway to TaxiwayCockpit Tracks Centreline Method

FIGURE-4-5-1-991-002-A01

4-5-1Page 3

Dec 01/16



**ON A/C A380-800

90˚ Turn - Runway to Taxiway

1. This section gives the 90˚ turn -- runway to taxiway.

4-5-2Page 1

Dec 01/16


**ON A/C A380-800

23 m(75 ft)

45 m(150 ft)

RUNWAY CENTERLINE

APPROX 9.2 m(30 ft)


TURN R = 45 m(150 ft)

APPROX 10 m(33 ft)

APPROX 7 m(23 ft)

TAXIWAYCENTERLINE

FAA LEAD−IN FILLETL = 75 m (250 ft)


NLG PATH

WLG PATH

COCKPIT PATH

L_AC_040502_1_0010101_01_01

90˚ Turn -- Runway to TaxiwayJudgemental Oversteer Method

FIGURE-4-5-2-991-001-A01

4-5-2Page 2

Dec 01/16


**ON A/C A380-800

TURN R = 51 m(167 ft)

30 m

(100

ft)

60 m(200 ft)

RUNWAY CENTERLINE


APPROX 10.2 m(33 ft)

TAXIWAYCENTERLINE


NOTE: FAA GROUP VI FACILITIES.

NLG PATH

WLG PATH

L_AC_040502_1_0020101_01_01

90˚ Turn -- Runway to TaxiwayCockpit Tracks Centreline Method

FIGURE-4-5-2-991-002-A01

4-5-2Page 3

Dec 01/16


4-5-3 180˚ Turn on a Runway

**ON A/C A380-800

180˚ Turn on a Runway

1. This section gives the 180˚ turn on a runway.

4-5-3Page 1

Dec 01/16


**ON A/C A380-800

NOTE:

4.5 m(15 ft)

4.5 m(15 ft)

0.7 m(2 ft)

16.8 m(55 ft)

31.2 m(102 ft)

23.2 m(76 ft)

R4 = 54 m(177 ft)

R5 = 36.6 m(120 ft)

R6 = 46 m(151 ft)

51 m(167 ft)

60 m(200 ft)

RUNWAYCENTERLINE

NLG PATH

WLG PATH

NOSE TIP PATH

WING TIP PATH

TAIL TIP PATH

R3 = 32.7 m(107 ft)

NLG WHEELOUTER−FACE PATH70° NOSE GEAR STEERING − ASYMMETRIC THRUST AND BRAKING

ON A 60 m (200 ft) WIDE RUNWAY.L_AC_040503_1_0010101_01_01

180˚ Turn on a RunwayFIGURE-4-5-3-991-001-A01

4-5-3Page 2

Dec 01/16



**ON A/C A380-800

90˚ Turn - Taxiway to Taxiway

1. This section gives the 90˚ turn - taxiway to taxiway.

4-5-4Page 1

Dec 01/16


**ON A/C A380-800

TAXIWAY CENTERLINE

23 m(75 ft)

23 m(75 ft)

NOMINAL OFFSET 7 m(23 ft)

APPROX 8.9 m(29 ft)


TURN R = 45 m(150 ft)

APPROX 10 m(33 ft)


TAXIWAYCENTERLINE


NLG PATH

WLG PATH

COCKPIT PATH

L_AC_040504_1_0010101_01_01

90˚ Turn -- Taxiway to TaxiwayJudgemental Oversteer Method

FIGURE-4-5-4-991-001-A01

4-5-4Page 2

Dec 01/16


**ON A/C A380-800

APPROX 8.7 m(29 ft)

TAXIWAY CENTERLINE

30 m

(100

ft)


TURN R = 51 m(167 ft)

TAXIWAYCENTERLINE


30 m(100 ft) NLG PATH

WLG PATH

NOTE: FAA GROUP VI FACILITIES.L_AC_040504_1_0020101_01_01

90˚ Turn -- Taxiway to TaxiwayCockpit Tracks Centreline Method

FIGURE-4-5-4-991-002-A01

4-5-4Page 3

Dec 01/16



**ON A/C A380-800

135˚ Turn - Taxiway to Taxiway

1. This section gives the 135˚ turn - taxiway to taxiway.

4-5-5Page 1

Dec 01/16


**ON A/C A380-800

23 m(75 ft)

TAXIWAY CENTERLINE


APPROX 8.5 m(28 ft)

TAXIWAY CENTERLINE

23 m(75 ft)

TURN R = 45 m(150 ft)

APPROX 7 m(23 ft)

APPROX 4.9 m(16 ft)


L = 75 m (250 ft)

NLG PATH

WLG PATH

COCKPIT PATH

NOTE: FAA GROUP V FACILITIES.L_AC_040505_1_0010101_01_01

135˚ Turn -- Taxiway to TaxiwayJudgemental Oversteer Method

FIGURE-4-5-5-991-001-A01

4-5-5Page 2

Dec 01/16


**ON A/C A380-800


APPROX 7.4 m(24 ft)

30 m(100 ft)

TURN R = 51 m(167 ft)

TAXIWAY CENTERLINE

TAXIWAY CENTERLINE


L = 75 m (250 ft)

NLG PATH

WLG PATH

30 m(100 ft)

NOTE: FAA GROUP VI FACILITIES.L_AC_040505_1_0020101_01_01

135˚ Turn -- Taxiway to TaxiwayCockpit Tracks Centerline Method

FIGURE-4-5-5-991-002-A01

4-5-5Page 3

Dec 01/16


4-6-0 Runway Holding Bay (Apron)

**ON A/C A380-800

Runway Holding Bay (Apron)

1. This section gives the runway holding bay (Apron).

4-6-0Page 1

Dec 01/16


**ON A/C A380-800

6.1 m(20 ft)

RUNWAY CENTERLINETAXIWAY

CENTERLINE

6.1 m(20 ft)

190 m(625 ft)

30 m(100 ft)

60 m(200 ft)

HOLDING POINT

12.2 m(40 ft)

90 m(300 ft)110 m

(360 ft)

NOTE: COORDINATE WITH USING AIRLINE FOR SPECIFIC PLANNED OPERATING PROCEDURE.

L_AC_040600_1_0010101_01_01

Runway Holding Bay (Apron)FIGURE-4-6-0-991-001-A01

4-6-0Page 2

Dec 01/16


4-7-0 Minimum Line-Up Distance Corrections

**ON A/C A380-800

Minimum Line-Up Distance Corrections

1. The ground manoeuvres were performed using asymmetric thrust and differential only braking toinitiate the turn.TODA: Take-Off Available DistanceASDA: Acceleration-Stop Distance Available

2. 90˚ Turn on Runway EntryThis section gives the minimum line-up distance correction for a 90˚ turn on runway entry.This manoeuvre consists in a 90˚ turn at minimum turn radius starting with the edge of the WLG ata distance of 4.5 m (15 ft) from taxiway edge, and finishing with the aircraft aligned on thecenterline of the runway, see FIGURE 4-7-0-991-003-A.During the turn, all the clearances must meet the minimum value of 4.5 m (15 ft) for this category ofaircraft as recommended in ICAO Annex 14.

3. 180˚ Turn on Runway Turn PadThis section gives the minimum line-up distance correction for a 180˚ turn on runway turn pad.This manoeuvre consists in a 180˚ turn at minimum turn radius on a standard ICAO runway turnpad geometry, .It starts with the edge of the WLG at 4.5 m (15 ft) from pavement edge, and it finishes with theaircraft aligned on the centerline of the runway, see FIGURE 4-7-0-991-004-A.During the turn, all the clearances must meet the minimum value of 4.5 m (15 ft) for this category ofaircraft as recommended in ICAO Annex 14.

4. 180˚ Turn on Runway WidthThis section gives the minimum line-up distance correction for a 180˚ turn on runway width.For this manoeuvre, the pavement width is considered to be the runway width, which is a frozenparameter (45 m (150 ft) and 60 m (200 ft)).As per the ”180˚ turn on runway” standard operating procedures described in the Flight CrewOperating Manual, the aircraft is initially angled with respect to runway centerline when starting the180˚ turn, see FIGURE 4-7-0-991-005-A.During the turn, all the clearances must meet the minimum value of 4.5 m (15 ft) for this category ofaircraft as recommended in ICAO Annex 14.

4-7-0Page 1

Dec 01/16


**ON A/C A380-800

> 4.5 m(15 ft)

90° TURN ON RUNWAY ENTRY

AIRCRAFTTYPE

MAXSTEERING

ANGLE

(STANDARD WIDTH)

MINIMUM LINE−UPDISTANCE CORRECTION

ON TODA ON ASDA ON TODA ON ASDA


70°A380−800 94 ft28.6 m 192 ft58.5 m 75 ft22.8 m 173 ft52.7 m

TAXIWAYCENTERLINE

ASDA

4.5 m(15 ft)

TODA

RUNWAY CENTERLINE

45 m (150 ft) WIDE RUNWAY60 m (200 ft) WIDE RUNWAY

NOTE:

ASDA: ACCELERATION−STOP DISTANCE AVAILABLETODA: TAKE−OFF DISTANCE AVAILABLE

L_AC_040700_1_0030101_01_00

Minimum Line-Up Distance Corrections90˚ Turn on Runway EntryFIGURE-4-7-0-991-003-A01

4-7-0Page 2

Dec 01/16


**ON A/C A380-800

180° TURN ON RUNWAY TURNPAD

AIRCRAFTTYPE

STEERINGANGLE

MAX(STANDARD WIDTH)

DISTANCECORRECTION

MINIMUM LINE−UP

70°A380−800224 ft68.1 m

TODA

ASDA

MINIMUM PAVEMENT WIDTH

ON TODA130 ft39.5 m

ON ASDA227 ft69.3 m

PAVEMENTWIDTH

MINIMUMREQUIRED

DISTANCECORRECTION

MINIMUM LINE−UP

209.9 ft64 mON TODA

122 ft37.1 mON ASDA

219 ft66.9 m

PAVEMENTWIDTH

MINIMUMREQUIRED

RUNWAY CENTERLINE

NOTE:


45 m (150 ft) WIDE RUNWAY 60 m (200 ft) WIDE RUNWAY

4.5 m(15 ft)

4.5 m(15 ft)> 4.5 m

(15 ft)

L_AC_040700_1_0040101_01_00

Minimum Line-Up Distance Corrections180˚ Turn on Runway Turn Pad

FIGURE-4-7-0-991-004-A01

4-7-0Page 3

Dec 01/16


**ON A/C A380-800

180° TURN ON RUNWAY WIDTH

AIRCRAFTTYPE

MAXSTEERING

ANGLE

(STANDARD WIDTH)


ON TODA ON ASDA ON TODA ON ASDA


70°A380−800 NOT POSSIBLE NOT POSSIBLE

ASDA

>4.5 m(15 ft)

4.5 m(15 ft)

TODA

NOTE:

IN THE A380 FCOM, THERE IS AN OPERATIONAL PROCEDURE THAT DESCRIBES HOW TO PERFORM A 180°TURN ON A 60 m (200 ft) RUNWAY WIDTH, BUT THE RECOMMENDED 4.5 m (15 ft) MARGINS CANNOT BE MET.

4.5 m(15 ft)

RUNWAY CENTERLINE

45 m (150 ft) WIDE RUNWAY60 m (200 ft) WIDE RUNWAY


15°

L_AC_040700_1_0050101_01_00

Minimum Line-Up Distance Corrections180˚ Turn on Runway WidthFIGURE-4-7-0-991-005-A01

4-7-0Page 4

Dec 01/16


4-8-0 Aircraft Mooring

**ON A/C A380-800

Aircraft Mooring

1. This section provides information on aircraft mooring.

4-8-0Page 1

Dec 01/16


**ON A/C A380-800

A

FWD

SLING

TOWING FITTING

MOVABLE PIN

LOCKING SCREW

HOOK

HOOK PIN

MOORING POINT

A

L_AC_040800_1_0010101_01_00

Aircraft MooringFIGURE-4-8-0-991-001-A01

4-8-0Page 2

Dec 01/16


TERMINAL SERVICING

5-1-0 Aircraft Servicing Arrangements

**ON A/C A380-800

Aircraft Servicing Arrangements

1. This section provides typical ramp layouts, showing the various GSE items in position during typicalturn-round scenarios.

These ramp layouts show typical arrangements only. Each operator will have its own specificrequirements/regulations for positioning and operation on the ramp.

This table gives the symbols used on servicing diagrams.

GROUND SUPPORT EQUIPMENT

AC AIR CONDITIONING UNITAS AIR START UNITBULK BULK TRAINCAT CATERING TRUCKCB CONVEYOR BELTCLEAN CLEANING TRUCKFUEL FUEL HYDRANT DISPENSER or TANKERGPU GROUND POWER UNITLDCL LOWER DECK CARGO LOADERLV LAVATORY VEHICLEPBB PASSENGER BOARDING BRIDGEPS PASSENGER STAIRSTOW TOW TRACTORUDCAT UPPER DECK CATERING TRUCKULD ULD TRAINWV POTABLE WATER VEHICLE

5-1-0Page 1

Dec 01/16


5-1-1 Typical Ramp Layout (Open Apron)

**ON A/C A380-800

Typical Ramp Layout (Open Apron)

1. This section provides the typical ramp layout (Open Apron).The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m (24.61 ft) fromthe aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears) and the beacon lights are off.

5-1-1Page 1

Dec 01/16


**ON A/C A380-800

CAT

LD CL

GPU

GPU

ULD

BULK

TOW

METERS

FEET16 320

0 5 10 15

48

LD CL

CLEAN

STAND SAFETY LINE

CB

FUEL

AS

CAT

AC

PS

PS

PS

CATLV

UDCAT

WV

ULD

L_AC_050101_1_0010101_01_02

Typical Ramp LayoutOpen Apron

FIGURE-5-1-1-991-001-A01

5-1-1Page 2

Dec 01/16


5-1-2 Typical Ramp Layout (Gate)

**ON A/C A380-800

Typical Ramp Layout (Gate)

1. This section provides the baseline ramp layout (Gate).The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m (24.61 ft) fromthe aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears) and the beacon lights are off.

5-1-2Page 1

Dec 01/16


**ON A/C A380-800

GPU

GPU

LD CL

ULD

BULK

LD CL

CLEAN

CB

AS

CAT

CAT

AC

FUELFUEL

PBB

PBB

CAT LV

UDCAT

WV

ULD

STAND SAFETY LINE

METERS

FEET16 320

0 5 10 15

48 TOW

L_AC_050102_1_0010101_01_02

Typical Ramp LayoutGate

FIGURE-5-1-2-991-001-A01

5-1-2Page 2

Dec 01/16


5-2-1 Typical Turn-Round Time - Standard Servicing Via Main Deck and Upper Deck

**ON A/C A380-800

Typical Turn-Round Time - Standard Servicing Via Main Deck and Upper Deck

1. This section provides a typical turn-round time chart showing the typical time for ramp activitiesduring aircraft turn-round.Actual times may vary due to each operator’s specific practices, resources, equipment and operatingconditions.

2. Assumptions used for standard servicing via main and upper deck during typical turn-round time

A. PASSENGER HANDLING555 pax (22 F/C + 96 B/C + 437 Y/C).All passengers deplane and board the aircraft.2 Passenger Boarding Bridges (PBB) used at doors M2L and U1L.Equipment positioning main deck + opening door = +3 min.Closing door + equipment removal main deck = +3 min.Equipment positioning upper deck + opening door = +4 min.Closing door + equipment removal upper deck = +4 min.No Passenger with Reduced Mobility (PRM) on board.

Deplaning:- 356 pax at door M2L (22 F/C + 334 Y/C)- 199 pax at door U1L (96 B/C + 103 Y/C)- Deplaning rate = 25 pax/min per door- Priority deplaning for premium passengers.

Boarding:- 356 pax at door M2L (22 F/C + 334 Y/C)- 199 pax at door U1L (96 B/C + 103 Y/C)- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min.

B. CARGO2 cargo loaders + 1 belt loader.Opening door + equipment positioning = +2.5 min.Equipment removal + closing door = +2.5 min.

100% cargo exchange:- FWD cargo compartment: 20 containers- AFT cargo compartment: 16 containers- Bulk cargo compartment: 1 000 kg (2 205 lb).

Container unloading/loading times:

5-2-1Page 1

Dec 01/16


- Unloading = 1.2 min/container- Loading = 1.4 min/container.

Bulk unloading/loading times:- Unloading = 110 kg/min (243 lb/min)- Loading = 95 kg/min (209 lb/min).

C. REFUELING242 700 l (64 115 US gal) at 40 psig.Dispenser positioning + connection = +8 min.Disconnection + dispenser removal = +8 min.

D. CLEANINGCleaning is performed in available time.

E. CATERING3 main deck catering trucks + 1 upper deck catering truck.Main deck equipment positioning + door opening = +5 min.Main deck closing door + equipment removal = 3 min.Upper deck equipment positioning + door opening = +9 min.Upper deck closing door + equipment removal = 4 min.

Full Size Trolley Equivalent (FSTE) to unload and load: 78 FSTE- 28 FSTE at door M2R- 16 FSTE at door M4R- 23 FSTE at door U1R- 11 FSTE at door M5L.Time for trolley exchange = 1.5 min per FSTE.Time for trolley exchange via lift = 2 min per FSTE.

F. GROUND HANDLING/SERVICINGStart of operations:- Bridges/stairs: t0 = 0- Other equipment: t = t0 + 1 min.

Ground Power Unit (GPU): up to 4 x 90 kVA.Air conditioning: up to 4 hoses.Potable water servicing: 100% uplift, 1 700 l (449 US gal).Waste water servicing: draining + rinsing.

5-2-1Page 2

Dec 01/16


**ON A/C A380-800

GSE POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH

AT M2LDEPLANING/BOARDING

HEADCOUNTING & LPS

CATERING AT M4R

CLEANING AT M1R

CARGO FWD CC

BULK

REFUELING

POTABLE WATER SERVICING

WASTE WATER SERVICING

DEPLANING/BOARDINGAT U1L

CATERING AT U1R

CATERING AT M5L

CARGO AFT CC

CATERING AT M2R

100 20 30 40 50 60 70 80 90

TRT: 90 min

AVAILABLE TIME

L_AC_050201_1_0020101_01_03

Typical Turn-Round TimeServicing Via Main and Upper Deck

FIGURE-5-2-1-991-002-A01

5-2-1Page 3

Dec 01/16


5-2-2 Typical Turn-Round Time - Servicing Via Main Deck

**ON A/C A380-800

Typical Turn-Round Time - Servicing Via Main Deck

1. This section provides a typical turn-round time chart showing the typical time for ramp activitiesduring aircraft turn-round.Actual times may vary due to each operator’s specific practices, resources, equipment and operatingconditions.

2. Assumptions used for standard servicing via main deck only during typical turn-round time

A. PASSENGER HANDLING555 pax (22 F/C + 96 B/C + 437 Y/C).All passengers deplane and board the aircraft.2 Passenger Boarding Bridges (PBB) used at doors M1L and M2L.Equipment positioning main deck + opening door = +3 min.Closing door + equipment removal main deck = +3 min.No Passenger with Reduced Mobility (PRM) on board.

Deplaning:- 221 pax at door M1L (22 F/C + 96 B/C + 103 Y/C)- 334 pax at door M2L (334 Y/C)- Deplaning rate = 25 pax/min per door- Priority deplaning for premium passengers.

Boarding:- 221 pax at door M1L (22 F/C + 96 B/C + 103 Y/C)- 334 pax at door M2L (334 Y/C)- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min.

B. CARGO2 cargo loaders + 1 belt loader.Opening door + equipment positioning = +2.5 min.Equipment removal + closing door = +2.5 min.

100% cargo exchange:- FWD cargo compartment: 20 containers- AFT cargo compartment: 16 containers- Bulk compartment: 1 000 kg (2 205 lb).

Container unloading/loading times:- Unloading = 1.2 min/container- Loading = 1.4 min/container.

5-2-2Page 1

Dec 01/16


Bulk unloading/loading times:- Unloading = 110 kg/min (243 lb/min)- Loading = 95 kg/min (209 lb/min).

C. REFUELING242 700 l (64 115 US gal) at 40 psig.Dispenser positioning + connection = +8 min.Disconnection + dispenser removal = +8 min.

D. CLEANINGCleaning is performed in available time.

E. CATERING3 main deck catering trucks.Main deck equipment positioning + door opening = +5 min.Main deck closing door + equipment removal = +3 min.Full Size Trolley Equivalent (FSTE) to unload and load: 78 FSTE.- 28 FSTE at door M2R- 16 FSTE at door M4R- 23 FSTE at door U1R- 11 FSTE at door M5L.Time for trolley exchange = 1.5 min per FSTE.Time for trolley exchange via lift = 2 min per FSTE.

F. GROUND HANDLING/SERVICINGStart of operations:- Bridges/stairs: t0 = 0- Other equipment: t = t0 + 1 min.

Ground Power Unit (GPU): up to 4 x 90 kVA.Air conditioning: up to 4 hoses.Potable water servicing: 100% uplift, 1 700 l (449 US gal).Waste water servicing: draining + rinsing.

5-2-2Page 2

Dec 01/16


**ON A/C A380-800

AT M1LDEPLANING/BOARDING

HEADCOUNTING & LPS

CATERING AT M4R

CLEANING AT M1R

CARGO FWD CC

BULK

REFUELING

POTABLE WATER SERVICING

WASTE WATER SERVICING

DEPLANING/BOARDINGAT M2L

CATERING AT M5L

CARGO AFT CC

CATERING AT M2R

20

GSE POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH

0 40 60 80 100 120 140

TRT: 140 min

AVAILABLE TIME

L_AC_050202_1_0010101_01_03

Typical Turn-Round TimeServicing Via Main Deck

FIGURE-5-2-2-991-001-A01

5-2-2Page 3

Dec 01/16


5-4-1 Ground Service Connections Layout

**ON A/C A380-800

Ground Service Connections Layout

1. This section gives the ground service connections layout.

5-4-1Page 1

Dec 01/16


**ON A/C A380-800

1 − GROUNDING POINT NLG2 − GROUND ELECTRICAL POWER CONNECTORS3 − POTABLE WATER DRAIN PANEL4 − OXYGEN SYSTEM

6 − HIGH PRESSURE AIR ENGINE START7 − VFG AND STARTER OIL FILLING8 − ENGINE OIL FILLING*9 − HYDRAULIC RESERVOIR SERVICING PANEL10 − YELLOW HYDRAULIC GROUND CONNECTOR

5 − LOW PRESSURE PRECONDITIONED AIR

13 − GROUNDING POINT WLG14 − GROUNDING POINT BLG

16 − OVERPRESSURE PROTECTOR17 − REFUEL/DEFUEL CONTROL PANEL18 − POTABLE WATER SERVICE PANEL

15 − NACA FLAME ARRESTOR

11 − GREEN HYDRAULIC GROUND CONNECTOR12 − PRESSURE REFUEL CONNECTORS

19 − TOILET AND WASTE SERVICE PANEL20 − APU OIL FILLING

1

34

15

12

1119

20

8 712

10

15

6

5

1718

2

13

14

9

8 7

8

7

87

16

16

15

16

NOTE:

*FOR THE GP 7200 ENGINE, THE ENGINE OIL SERVICING POINTS (8) ARE LOCATED SYMMETRICALLYON THE LH SIDE OF EACH ENGINE.

THE ENGINE OIL SERVICING POINTS (8) ARE SHOWN FOR THE RR TRENT 900 ENGINE.

L_AC_050401_1_0010101_01_03

Ground Service Connections LayoutFIGURE-5-4-1-991-001-A01

5-4-1Page 2

Dec 01/16


5-4-2 Grounding (Earthing) Points

**ON A/C A380-800

Grounding (Earthing) Points

1. Grounding (Earthing) Points

DISTANCEFROM AIRCRAFT CENTERLINEACCESS

AFT OF NOSELH SIDE RH SIDE

MEAN HEIGHTFROM GROUND

On Nose LandingGear leg

5.71 m(18.73 ft)

0.18 m(0.59 ft)

1.39 m(4.56 ft)

On Wing Gear leg(Inboard)

34.21 m(112.24 ft)

5.95 m(19.52 ft)

5.95 m(19.52 ft)

1.24 m(4.07 ft)

On Body Gear leg(Outboard)

37.16 m(121.92 ft)

2.85 m(9.35 ft)

2.85 m(9.35 ft)

1.38 m(4.53 ft)

On Body Gear leg(Inboard)

37.16 m(121.92 ft)

2.41 m(7.91 ft)

2.41 m(7.91 ft)

1.38 m(4.53 ft)

A. The grounding (earthing) stud on each landing gear is designed for use with a clip-on connector,such as an Appleton TGR.

B. The grounding (earthing) studs are used to connect the aircraft to approved ground (earth)connection on the ramp or in the hangar for:- Refuel/defuel operations- Maintenance operations- Bad weather conditions.

5-4-2Page 1

Dec 01/16


**ON A/C A380-800

GROUNDING (EARTHING)POINT

A

A

L_AC_050402_1_0010101_01_01

Grounding (Earthing) Point - NLGFIGURE-5-4-2-991-001-A01

5-4-2Page 2

Dec 01/16


**ON A/C A380-800


A

A

L_AC_050402_1_0020101_01_01

Grounding (Earthing) Points - WLGFIGURE-5-4-2-991-002-A01

5-4-2Page 3

Dec 01/16


**ON A/C A380-800


A

A

(RIGHT ONE SHOWN LEFT ONE SIMILAR)

L_AC_050402_1_0030101_01_01

Grounding (Earthing) Points - BLGFIGURE-5-4-2-991-003-A01

5-4-2Page 4

Dec 01/16


5-4-3 Hydraulic System

**ON A/C A380-800

Hydraulic Servicing

1. Ground Service Panel

DISTANCEFROM AIRCRAFT

CENTERLINEACCESSAFT OF NOSE

LH SIDE RH SIDE

MEANHEIGHTFROM

GROUND

Hydraulic Reservoir Servicing Panel:Access Door 197CB

31.89 m(104.63 ft)

2.34 m(7.68 ft)

1.71 m(5.61 ft)

A. Connectors

(1) Reservoir Filling:- One 3022079-312

(2) Reservoir Pressurization/Depressurization:- One 3022079-324 (pressurization)- One pressure-switch (green hydraulic reservoir depressurization)- One pressure-switch (yellow hydraulic reservoir depressurization).

2. Ground Test



LH SIDE RH SIDE

MEANHEIGHTFROM

GROUNDGreen Hydraulic Ground Connectors:Behind Engine 2Access Door 469FL

34.67 m(113.75 ft)

14.90 m(48.88 ft)

5.08 m(16.67 ft)

Yellow Hydraulic GroundConnectors:Behind Engine 3Access Door 479FL

34.67 m(113.75 ft)

14.90 m(48.88 ft)

5.08 m(16.67 ft)

A. Connectors- One D24331000 (Suction)- One D24330000 (Delivery).

5-4-3Page 1

Dec 01/16


**ON A/C A380-800

A

RESERVOIRPRESSURIZATION

CONNECTOR

RESERVOIR FILLINGCONNECTOR

GREEN HYD RESERVOIRDEPRESSURIZATION

SWITCH

YELLOW HYD RESERVOIRDEPRESSURIZATION

SWITCH

B

Z190

A

B

FWD

L_AC_050403_1_0010101_01_01

Ground Service ConnectionsHydraulic Reservoir Servicing Panel

FIGURE-5-4-3-991-001-A01

5-4-3Page 2

Dec 01/16


**ON A/C A380-800

Z460

Z470 B C

A

SELF SEALINGGND CONNECTOR

GREEN HP


GREEN SUCTION


YELLOW HP


YELLOW SUCTION

B C

A

FOR LH PYLON FOR RH PYLON

A

L_AC_050403_1_0020101_01_00

Ground Service ConnectionsHydraulic Ground ConnectionsFIGURE-5-4-3-991-002-A01

5-4-3Page 3

Dec 01/16


5-4-4 Electrical System

**ON A/C A380-800

Electrical Servicing

1. AC External Power

DISTANCEFROM AIRCRAFT CENTERLINE

ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUND

Right Side Access Door:134AR

5.99 m(19.65 ft)

0.45 m(1.48 ft)

2.59 m(8.50 ft)

Left Side Access Door:133AL

5.99 m(19.65 ft)

0.45 m(1.48 ft)

2.59 m(8.50 ft)

2. Technical Specifications

A. External Power Receptacles:- Four receptacles according to MS 90362-3 (without shield MS 17845-1) - 90 kVA.

NOTE : Make sure that for connectors featuring micro switches, the connectors are chamferedto properly engage in the receptacles.

B. Power Supply:- Three-phase, 115V, 400 Hz.

C. Electrical Connectors:- AC outlets: HUBBELL 5258- DC outlets: HUBBELL 7472.

3. Tow Truck Power


ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUND

NLG Service Panel: 24GC4.97 m

(16.31 ft)0.25 m(0.82 ft)

1.39 m(4.56 ft)


A. Power Supply:- Two-Phase, 115 V, 400 Hz- 28V DC.

B. Electrical Connector for Servicing:- Bernier, 22--11--10--13 Connector.

5-4-4Page 1

Dec 01/16


C. Pin Allocation:

Pin IdentificationA 28V DCB 0V DCD 115V ACE 0V ACGH

PWR SPLYINT LOCK

NOTE : The power cable should be extendable in order to guarantee fit and non-interferencewith nose gear nor tow vehicle during the pick-up and the towing process. Theconnector shall be secured against pull-out by means of straps against the nose gear.

5. AC Emergency Generation


ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUNDRAT Safety-PinInstallationAccess Panel: 531DL

31.00 m(101.71 ft)

9.50 m(31.17 ft)

3.20 m(10.5 ft)

5-4-4Page 2

Dec 01/16


**ON A/C A380-800

RECEPTACLES

A

B

FWD

FWD

FR17FR18

FR17 FR18

FR17 FR18EXTERNAL POWER

RECEPTACLESEXTERNAL POWER

133AL134AR

A

B

L_AC_050404_1_0010101_01_01

Ground Service ConnectionsElectrical Service Panel

FIGURE-5-4-4-991-001-A01

5-4-4Page 3

Dec 01/16


**ON A/C A380-800

Z531

A

531DL

B

A

B

C

C

NOTE:ALWAYS KEEP THE WARNING FLAGOUT OF THE RAT FAIRING HAND HOLE.

RAM AIR TURBINE (RAT)

RAT UPLOCK SAFETY−PIN

L_AC_050404_1_0050101_01_00

Ground Service ConnectionsRam Air Turbine RetractedFIGURE-5-4-4-991-005-A01

5-4-4Page 4

Dec 01/16


**ON A/C A380-800

RAM AIR TURBINE (RAT)

A

531KR

531KL

(5.41 ft)1.65 m

B

GROUND

B

FWD

Z531

A

L_AC_050404_1_0060101_01_00

Ground Service ConnectionsRam Air Turbine ExtendedFIGURE-5-4-4-991-006-A01

5-4-4Page 5

Dec 01/16


5-4-5 Oxygen System

**ON A/C A380-800

Oxygen System

1. Oxygen System


ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUNDAccess Panels: 132AJW

132EJW

13.32 m(43.70 ft)

2.23 m(7.32 ft)

3.25 m(10.66 ft)

A. Access:Get access to the forward lower-deck cargo-compartment.The access panel to the crew oxygen servicing point is located on the rear triangular area of theFWD cargo door.

B. Technical Specifications:- MIL-DTL-7891 standard service connection- Zero, one or two service connections (external charging in the FWD cargo compartment).

5-4-5Page 1

Dec 01/16


**ON A/C A380-800

FR29

A

B

FR34

FR17

FR29

Z130

PASSENGEROXYGENFILLING POINT

CREW OXYGENFILLING POINT

L_AC_050405_1_0020101_01_00

A

B

Ground Service ConnectionsOxygen System

FIGURE-5-4-5-991-002-A01

5-4-5Page 2

Dec 01/16


5-4-6 Fuel System

**ON A/C A380-800

Fuel Servicing

1. Refuel/Defuel Control Panel




Refuel/Defuel ControlPanel:Access Door 199KB

48 m(157.48 ft)

0.68 m(2.23 ft)

1.98 m(6.50 ft)

2. Refuel/Defuel Connectors




Refuel/Defuel Coupling,Left:Access Door 522GB

31.89 m(104.63 ft)

17.97 m(58.96 ft)

5.94 m(19.49 ft)

Refuel/Defuel Coupling,Right:Access Door 622GB

31.89 m(104.63 ft)

17.97 m(58.96 ft)

5.94 m(19.49 ft)

A. Refuel/Defuel couplings:- Four standard 2.5 in. ISO 45 connections.

B. Refuel pressure:- Maximum pressure: 50 psi (3.45 bar).

3. Overpressure Protector and NACA Flame Arrestor




Overpressure Protector(Wing):Access Panel 550CB(650CB)

46.65 m(153.05 ft)

36.75 m(120.57 ft)

36.75 m(120.57 ft)

7.51 m(24.64 ft)

NACA Flame Arrestor(Wing):Access Panel 550BB(650BB)

46.33 m(152.00 ft)

35.98 m(118.04 ft)

35.98 m(118.04 ft)

7.44 m(24.41 ft)

5-4-6Page 1

Dec 01/16





Overpressure Protector(Trim Tank):Access Panel 344AB

62.75 m(205.87 ft)

5.19 m(17.03 ft)

7.68 m(25.20 ft)

NACA Flame Arrestor(Trim Tank):Access Panel 344AB

63.97 m(209.88 ft)

4.64 m(15.22 ft)

7.55 m(24.77 ft)

5-4-6Page 2

Dec 01/16


**ON A/C A380-800

Z190

HI LVL

HI LVL

APU EMERGENCY

INCREASE

DECREASE

PRESELECT

PRESELECT (PFQ)

OVERFLOWFAULT

SHUTOFFTEST

NORMAL

BATTERY

POWER SUPPLY

ACTUAL (FOB)

STATUS

MANREFUEL

XFR

DEFUEL

AUTOREFUEL

OFF

MODE SELECT

FEED 1

FEED 1

L OUTR

L OUTR

R MID

OPEN

SHUT

R MID

R INR

R INR

TRIM

TRIM

L INR

L INR

L MID

L MID

R OUTROPEN

SHUT

R OUTR

FEED 4

FEED 4

FEED 3

FEED 3

FEED 2

FEED 2

SHUTDOWN

REFUEL/DEFUEL VALVES

kg

B

42QU

BA

A

L_AC_050406_1_0010101_01_00

Ground Service ConnectionsRefuel/Defuel Control PanelFIGURE-5-4-6-991-001-A01

5-4-6Page 3

Dec 01/16


**ON A/C A380-800

REFUEL PRESSURE

REFUEL / DEFUEL COUPLINGS

Z500

Z600 ALH SIDE SHOWN

RH SIDE SYMETRICAL

B

B

A

A

L_AC_050406_1_0020101_01_00

Ground Service ConnectionsPressure Refuel ConnectionsFIGURE-5-4-6-991-002-A01

5-4-6Page 4

Dec 01/16


**ON A/C A380-800

L_AC_050406_1_0030101_01_01

550CB(650CB)

COVERPRESSURE PROTECTOR

A

NACA FLAME ARRESTOR

B

550BB(650BB)

A

B

C

A FWD

LH SIDE SHOWNRH SIDE SYMMETRICAL

Ground Service ConnectionsOverpressure Protector and NACA Flame Arrestor - Wing

FIGURE-5-4-6-991-003-A01

5-4-6Page 5

Dec 01/16


**ON A/C A380-800

Z344

NACA INTAKE

B

BOTTOM SKIN

B

RIB9

RIB8

344AB

OVERPRESSUREPROTECTOR

AFWD

A

L_AC_050406_1_0040101_01_00

Ground Service ConnectionsOverpressure Protector and NACA Flame Arrestor - Trim Tank

FIGURE-5-4-6-991-004-A01

5-4-6Page 6

Dec 01/16


5-4-7 Pneumatic System

**ON A/C A380-800

Pneumatic Servicing

1. Low Pressure Connectors




Access Door 191GB21.85 m(71.69 ft)

1.24 m(4.07 ft)

2.08 m(6.82 ft)

Access Door 191JB22.36 m(73.36 ft)

1.76 m(5.77 ft)

2.08 m(6.82 ft)

Access Door 191HB21.85 m(71.69 ft)

1.24 m(4.07 ft)

2.08 m(6.82 ft)

Access Door 191KB22.36 m(73.36 ft)

1.76 m(5.77 ft)

2.08 m(6.82 ft)

A. Connectors:

(1) Four standard 8 in. SAE AS4262 type B connections.

2. High Pressure Connectors




Access Door 193BB25.37 m(83.23 ft)

0.2 m(0.66 ft)

1.78 m(5.84 ft)

A. Connectors:

(1) Three standard 3 in. ISO 2026 connections.

5-4-7Page 1

Dec 01/16


**ON A/C A380-800

LOW PRESSURE AIR CONNECTOR

Z190

BB

B

BA

A

B

L_AC_050407_1_0010101_01_00

Ground Service ConnectionsLow Pressure Preconditioned Air

FIGURE-5-4-7-991-001-A01

5-4-7Page 2

Dec 01/16


**ON A/C A380-800

HIGH PRESSURE AIR CONNECTORS

Z190

BA

A

B

L_AC_050407_1_0020101_01_00

Ground Service ConnectionsHigh Pressure Preconditioned Air

FIGURE-5-4-7-991-002-A01

5-4-7Page 3

Dec 01/16


5-4-8 Oil System

**ON A/C A380-800

Oil Servicing

1. RR TRENT 900 Engines

A. Engine Oil Servicing



LH SIDE RH SIDE

MEANHEIGHTFROM

GROUND

Engine 1:Access Door 416BR

32.65 m(107.12 ft)

23.58 m(77.36 ft)

4.24 m(13.91 ft)


24.98 m(81.96 ft)

12.74 m(41.80 ft)

3.08 m(10.10 ft)


24.98 m(81.96 ft)

16.61 m(54.49 ft)

3.08 m(10.10 ft)


32.65 m(107.12 ft)

27.45 m(90.06 ft)

4.24 m(13.91 ft)

B. VFG Oil Servicing


ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUND

Engine 1:Access Door 415AL

33.17 m(108.83 ft)

26.14 m(85.76 ft)

2.56 m(8.40 ft)


25.57 m(83.89 ft)

15.31 m(50.23 ft)

1.33 m(4.36 ft)


25.57 m(83.89 ft)

13.93 m(45.70 ft)

1.33 m(4.36 ft)


33.17 m(108.83 ft)

24.90 m(81.69 ft)

2.56 m(8.40 ft)

(1) For VFG oil servicing, open:- Left Fan Exhaust Cowl.

5-4-8Page 1

Dec 01/16


C. Starter Oil Servicing



LH SIDE RH SIDE

MEANHEIGHTFROM

GROUND

Engine 1:Access Door 415AL and 416AR

39.78 m(130.51 ft)

25.78 m(84.58 ft)

2.59 m(8.49 ft)


32.15 m(105.49 ft)

14.94 m(49.02 ft)

1.39 m(4.56 ft)


32.15 m(105.48 ft)

14.42 m(47.31 ft)

1.39 m(4.56 ft)


39.78 m(130.51 ft)

25.25 m(82.84 ft)

2.59 m(8.49 ft)

(1) For access to Starter Oil Servicing, open Fan Cowl.

2. GP7200 Engines

A. Engine Oil Servicing



LH SIDE RH SIDE

MEANHEIGHTFROM

GROUND

Engine 1:Access Door 415CL

33.03 m(108.37 ft)

27.42 m(89.96 ft)

4.40 m(14.44 ft)


25.35 m(83.17 ft)

16.62 m(54.53 ft)

3.13 m(10.27 ft)


25.35 m(83.17 ft)

12.78 m(41.93 ft)

3.13 m(10.27 ft)


33.03 m(108.37 ft)

23.62 m(77.49 ft)

4.40 m(14.44 ft)

5-4-8Page 2

Dec 01/16


B. VFG Oil Servicing


ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUND

Engine 1:Access Door 415AL and 417AL

34.49 m(113.16 ft)

25.43 m(83.43 ft)

2.63 m(8.63 ft)


26.81 m(87.96 ft)

14.63 m(48.00 ft)

1.36 m(4.46 ft)


26.81 m(87.96 ft)

14.63 m(48.00 ft)

1.36 m(4.46 ft)


34.49 m(113.16 ft)

25.43 m(83.43 ft)

2.63 m(8.63 ft)

(1) For VFG oil servicing, open:- Left Fan Exhaust Cowl- Left Thrust Reverser Cowl.

C. Starter Oil Servicing



LH SIDE RH SIDE

MEANHEIGHTFROM

GROUND


40.42 m(132.61 ft)

27.34 m(89.70 ft)

3.35 m(10.99 ft)


32.74 m(107.41 ft)

16.55 m(54.30 ft)

2.47 m(8.10 ft)


32.74 m(107.41 ft)

12.71 m(41.70 ft)

2.47 m(8.10 ft)


40.42 m(132.61 ft)

23.53 m(77.20 ft)

3.35 m(10.99 ft)

(1) For access to Starter Oil Servicing, open Fan Cowl.

3. APU Oil Servicing

5-4-8Page 3

Dec 01/16




LH SIDE RH SIDE

MEANHEIGHTFROM

GROUND

Access Doors: 315AL and 315AR67.55 m

(221.62 ft)0.44 m(1.44 ft)

6.83 m(22.41 ft)

A. Capacity:- 18.13 l (4.79 US gal).

5-4-8Page 4

Dec 01/16


**ON A/C A380-800

A

OIL TANK

OIL FILLERCAP

B

SIGHTGLASS

FWD

446BR (ENGINE 4)436BR (ENGINE 3)426BR (ENGINE 2)416BR (ENGINE 1)

B

A

L_AC_050408_1_0060101_01_01

Ground Service ConnectionsEngine Oil Servicing - TRENT 900 Engines

FIGURE-5-4-8-991-006-A01

5-4-8Page 5

Dec 01/16


**ON A/C A380-800

A B

VFG

OVERFLOWDRAIN VALVE

PRESSURE FILLVALVE

CASE DRAINPLUG

B

A

446AR (ENGINE 4)436AR (ENGINE 3)426AR (ENGINE 2)416AR (ENGINE 1)

445AL (ENGINE 4)435AL (ENGINE 3)425AL (ENGINE 2)415AL (ENGINE 1)

SIGHTGLASS

FWD

L_AC_050408_1_0070101_01_01

Ground Service ConnectionsVFG Oil Servicing - TRENT 900 Engines

FIGURE-5-4-8-991-007-A01

5-4-8Page 6

Dec 01/16


**ON A/C A380-800

A

OIL FILL PLUG




446AR(ENGINE 4)436AR(ENGINE 3)426AR(ENGINE 2)416AR(ENGINE 1)

A

SIGHTGLASS

OIL LEVELOVERFLOW PLUG

PNEUMATICSTARTER

DRAIN PLUG MAGNETIC CHIPDETECTOR

L_AC_050408_1_0130101_01_00

Ground Service ConnectionsStarter Oil Servicing - TRENT 900 Engines

FIGURE-5-4-8-991-013-A01

5-4-8Page 7

Dec 01/16


**ON A/C A380-800

PINENGAGEMENT

A

B

BFWD

A

445CL (ENGINE 4)435CL (ENGINE 3)425CL (ENGINE 2)415CL (ENGINE 1)

SIGHTGLASS

"T" HANDLE

OIL TANKFILLER CAP

L_AC_050408_1_0140101_01_00

Ground Service ConnectionsEngine Oil Servicing - GP7200 Engines

FIGURE-5-4-8-991-014-A01

5-4-8Page 8

Dec 01/16


**ON A/C A380-800

C

CASE DRAINPLUG

A

B

VFG

PRESSUREFILL VALVE

OVERFLOWDRAIN VALVE





A

SIGHTGLASS

B

C

FWD

L_AC_050408_1_0150101_01_00

Ground Service ConnectionsVFG Oil Servicing - GP7200 Engines

FIGURE-5-4-8-991-015-A01

5-4-8Page 9

Dec 01/16


**ON A/C A380-800

PNEUMATIC STARTER

MAGNETIC CHIPDETECTOR

STARTER CONTROL VALVE

V−BANDCLAMP

AND QADADAPTER

FILLPORT

A





A

L_AC_050408_1_0160101_01_00

Ground Service ConnectionsStarter Oil Servicing - GP7200 Engines

FIGURE-5-4-8-991-016-A01

5-4-8Page 10

Dec 01/16


**ON A/C A380-800

C

FILL CAP

FR112

FR117

315AL315AR

A

B

SIGHTGLASS

FR117

Z310

FR112

FR95

A

BCFWD

FULL

1 LT

FULL

1 LT

ADD

APURUN

APUOFF

L_AC_050408_1_0170101_01_00

Ground Service ConnectionsAPU Oil Servicing

FIGURE-5-4-8-991-017-A01

5-4-8Page 11

Dec 01/16


5-4-9 Potable Water System

**ON A/C A380-800

Potable Water Servicing

1. Potable Water ServicingThis section provides data related to the location of the ground service connections.


CENTERLINEACCESS AFT OFNOSE

LH SIDE RH SIDE

MEANHEIGHTFROM

GROUND

Potable Water Ground Service Panel:Access Door 199NB

43.67 m(143.27 ft)

0.37 m(1.21 ft)

2.13 m(6.99 ft)

Potable Water Drain Panel:Access Door 133BL

9.83 m(32.25 ft)

0.30 m(0.98 ft)

2.74 m(8.99 ft)

NOTE : Distances are approximate.

A. Connections

Fill and drain port - ISO 17775, 3/4 in.

B. Capacity:

(1) Total Capacity- Standard configuration (six tanks): 1 700 l (449 US gal)- Optional configuration (seven tanks): 1 998 l (528 US gal)- Optional configuration (eight tanks): 2 267 l (599 US gal).

C. Filling Pressure:

(1) Max Filling Pressure: 8.6 bar (125 psi).

5-4-9Page 1

Dec 01/16


**ON A/C A380-800

80LWL PRE

1000

0/

PRESS UP OR DOWN TO PRESET

0

50

DOWN PRESET WATER UP

MENUSELECT

DRAIN FILL

NORMAL

FILL/DRAIN PORT

Z190

A

B

FR76

199NB

B

A

FWD

L_AC_050409_1_0160101_01_00

Ground Service ConnectionsPotable Water Ground Service Panel

FIGURE-5-4-9-991-016-A01

5-4-9Page 2

Dec 01/16


**ON A/C A380-800

ACCESS DOOR

DRAIN PORT

DRAIN VALVECONTROL HANDLE

B

A

FR24

Z130

FR23

B

133BL

A

L_AC_050409_1_0170101_01_00

Ground Service ConnectionsPotable Water Drain PanelFIGURE-5-4-9-991-017-A01

5-4-9Page 3

Dec 01/16


**ON A/C A380-800

FR59

FR57

FR55

A

OPTIONAL

OPTIONAL

Z140

POTABLE WATER TANKS(STANDARD: 6 TANKS,OPTION: 7 OR 8 TANKS)

A

L_AC_050409_1_0180101_01_00

Ground Service ConnectionsPotable Water Tanks LocationFIGURE-5-4-9-991-018-A01

5-4-9Page 4

Dec 01/16


5-4-10 Waste Water System

**ON A/C A380-800

Waste Water System

1. Waste Water SystemThis section provides data related to the location of the ground service connections.

DISTANCESFROM AIRCRAFT CENTERLINEACCESS



Waste Water GroundService Panel:Access door 171AL

53.31 m(174.90 ft)

0.26 m(0.85 ft)

3.40 m(11.15 ft)

NOTE : Distances are approximate.


A. Connectors

(1) Waste water drain-connection - ISO 17775, 4 in.

(2) Waste water rinse/fill port - ISO 17775, 1 in.

B. CapacityThere are four waste tanks, two upper deck tanks and two main deck tanks, see FIGURE5-4-10-991-003-A.

(1) Upper Deck Waste Tanks- Two tanks (373 l (99 US gal) each).Each tank is precharged with 35 l (9 US gal) of chemical fluid.

(2) Main Deck Waste Tanks- Two tanks (675 l (178 US gal) each).Each tank is precharged with 35 l (9 US gal) of chemical fluid.

(3) Total Waste Tank Capacity- 2096 l (554 US gal).

C. PressureMaximum pressure for rinsing and precharge to the rinse/fill port is 3.45 bar (50 psi).

5-4-10Page 1

Dec 01/16


**ON A/C A380-800

WASTE TANK DRAIN VALVEOPEN

UPPERDECK

MAINDECK

RH LH RH LH

CLOSE

CONTROLLEVER

CONNECTIONWASTE DRAIN

FILL AND RINSECONNECTION

FWDB

Z160

FR86FR91A

A

B

L_AC_050410_1_0010101_01_00

Ground Service ConnectionsWaste Water Ground Service Panel

FIGURE-5-4-10-991-001-A01

5-4-10Page 2

Dec 01/16


**ON A/C A380-800

Z170

A

FR91

FR92

FR93

FR94

FR95

A

WASTE TANK(STANDARD: 4 TANKS)

L_AC_050410_1_0030101_01_01

Ground Service ConnectionsWaste Tanks Location

FIGURE-5-4-10-991-003-A01

5-4-10Page 3

Dec 01/16


5-4-11 Cargo Control Panels

**ON A/C A380-800

Cargo Control Panels

1. Cargo Control Panels




FWD CLS* Panel:Access Door 132AR

9.83 m(32.25 ft)

3.08 m(10.10 ft)

4.40 m(14.44 ft)

FWD Cargo DoorPanel:Access Door 132BR

9.85 m(32.32 ft)

2.42 m(7.94 ft)

3.40 m(11.15 ft)

AFT CLS* Panel:Access Door 152AR

46.32 m(151.97 ft)

3.11 m(10.20 ft)

4.38 m(14.37 ft)

AFT Cargo DoorPanel:Access Door 199DR

45.67 m(149.84 ft)

2.45 m(8.04 ft)

3.08 m(10.10 ft)

NOTE : * CLS - CARGO LOADING SYSTEMS

5-4-11Page 1

Dec 01/16


**ON A/C A380-800

JOYSTICK

SYST ON LAMP

PWR ON/OFF SWITCH

INDICATOR LIGHT"CARGO DOOR FULLYOPEN AND ARRESTED"

MANUALOPERATING DEVICE

TOGGLE SWITCHOPEN OR CLOSE

CARGO DOOR

PROTECTIONCOVER

132BR

132AR

B

C

Z130

A

OUTSIDE CARGO LOADINGSYSTEM CONTROL PANEL

CARGO DOOR CONTROL PANEL

FWD CARGO DOOR

C

A

FR23FR24

B

L_AC_050411_1_0010101_01_00

Forward Cargo Control PanelsFIGURE-5-4-11-991-001-A01

5-4-11Page 2

Dec 01/16


**ON A/C A380-800

MANUAL OPERATINGDEVICE

INDICATOR LIGHT"CARGO DOOR FULLYOPEN AND ARRESTED"

PROTECTIONCOVER

TOGGLE SWITCHOPEN OR CLOSE

CARGO DOOR

199DR

JOYSTICK

SYST ON LAMP

PWR ON/OFF SWITCH

152AR

B

C

Z150

Z190

A

OUTSIDE CARGO LOADINGSYSTEM CONTROL PANEL

CARGO DOOR CONTROL PANEL

A

FR79

FR80

FR81

C

B

AFT CARGO DOOR

L_AC_050411_1_0020101_01_00

Aft Cargo Control PanelsFIGURE-5-4-11-991-002-A01

5-4-11Page 3

Dec 01/16


5-5-0 Engine Starting Pneumatic Requirements

**ON A/C A380-800

Engine Starting Pneumatic Requirements

1. The purpose of this section is to provide the air data at the aircraft connection, needed to start theengine within no more than 90 seconds, at sea level (0 ft), for a set of Outside Air Temperatures(OAT).

ABBREVIATION DEFINITION

A/C Aircraft

ASU Air Start UnitHPGC High Pressure Ground Connection

OAT Outside Air Temperature

A. Air data (discharge temperature, absolute discharge pressure) are given at the HPGC.

B. For the requirements below, the configuration with two HPGC is used. Using more than twoconnectors (for a given mass flow rate and discharge pressure from the ASU) will lower thepressure loss in the ducts of the bleed system and therefore increase the performances at theengine starter.

C. For a given OAT the following charts are used to determine an acceptable combination for airdata: discharge temperature, absolute discharge pressure and mass flow rate at the HPGC.

D. This section addresses requirements for the ASU only, and is not representative of the startperformance of the aircraft using the APU or engine cross bleed procedure.

E. To protect the A/C, the charts feature, if necessary:- The maximum discharge pressure at the HPGC- The maximum discharge temperature at the HPGC.

5-5-0Page 1

Dec 01/16


**ON A/C A380-800

EXAMPLE:FOR AN OAT OF 15° C (59° F) AND AN ASU PROVIDING A DISCHARGE TEMPERATURE OF 135° C (275° F)

− THE REQUIRED PRESSURE AT HPGC IS 42.8 psia− THE REQUIRED AIRFLOW AT A/C CONNECTION IS 96 kg/min.

AT HPGC:

IN CASE THE ACTUAL DISCHARGE TEMPERATURE OF THE ASU DIFFERS SUBSTANTIALLY FROM THEONES GIVEN IN THE CHARTS, A SIMPLE INTERPOLATION (LINEAR) IS SUFFICIENT TO DETERMINE THE

FOR AN OAT OF 15° C (59° F) AND AN ASU PROVIDING A DISCHARGE TEMPERATURE OF 195° C (383° F)AT HPGC, INTERPOLATING BETWEEN THE LINES 135° C (275° F) AND 265° C (509° F) RESULTS IN:− A REQUIRED PRESSURE AT HPGC OF 41.8 psia− A REQUIRED AIRFLOW AT A/C CONNECTION OF 88 kg/min.

REQUIRED AIR DATA.

EXAMPLE:

NOTE:

ENGINE ALLIANCE GP 7200/SEA LEVELSTARTING TIME: LESS THAN 90 s

AIR DATA AT AIRCRAFT CONNECTION (TWO CONNECTORS)140

130

120

110

100

90

80

70

60

58

56

54

52

50

48

46

44

42

40

0 20 40 60 80 100 120OUTSIDE AIR TEMPERATURE OAT (° F)

150

170

190

210

230

250

270

5 15 25 35 45 55OUTSIDE AIR TEMPERATURE OAT (° C)

40 45 50 55ABSOLUTE PRESSURE (psia)

AIR

FLO

W (

kg/m

in)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

AIR

FLO

W (

lb/m

in)

265° C (509° F) MAX.135° C (275° F)60° C (140° F)

ASU DISCHARGE TEMPERATURE:

−40 −20

−45 −35 −25 −15 −5

L_AC_050500_1_0030101_01_02

Example for Use of the ChartsFIGURE-5-5-0-991-003-A01

5-5-0Page 2

Dec 01/16


**ON A/C A380-800

ENGINE ALLIANCE GP 7200/SEA LEVELSTARTING TIME: LESS THAN 90 s

AIR DATA AT AIRCRAFT CONNECTION (TWO CONNECTORS)140

130

120

110

100

90

80

70150

170

190

210

230

250

270


0 20 40 60 80 100 120

OUTSIDE AIR TEMPERATURE OAT (° F)


60

58

56

54

52

50

48

46

44

42

40

AIR

FLO

W (

kg/m

in)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

AIR

FLO

W (

lb/m

in)

265° C (509° F) MAX.135° C (275° F)60° C (140° F)


L_AC_050500_1_0040101_01_01

Engine Starting Pneumatic RequirementsEngine Alliance - GP 7200FIGURE-5-5-0-991-004-A01

5-5-0Page 3

Dec 01/16


**ON A/C A380-800

ROLLS ROYCE TRENT 900/SEA LEVELSTARTING TIME: LESS THAN 90 s

AIR DATA AT AIRCRAFT CONNECTION (TWO CONNECTORS)

140

130

120

110

100

90

80170

190

210

230

250

270

160

150

280

290

60

55

50

45

40

65

0 20 40 60 80 100 120

OUTSIDE AIR TEMPERATURE OAT (° F)



50 55

255° C (491° F) MAX.130° C (266° F)55° C (131° F)


AIR

FLO

W (

lb/m

in)

AIR

FLO

W (

kg/m

in)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

L_AC_050500_1_0050101_01_01

Engine Starting Pneumatic RequirementsRolls Royce - Trent 900 Engine

FIGURE-5-5-0-991-005-A01

5-5-0Page 4

Dec 01/16


5-6-0 Ground Pneumatic Power Requirements

**ON A/C A380-800

Ground Pneumatic Power Requirements

1. GeneralThis section describes the required performance for the ground equipment to maintain the cabintemperature at 27 ˚C (80.6 ˚F) for the cooling or 21 ˚C (69.8 ˚F) for the heating cases afterboarding (Section 5.7 - steady state), and provides the time needed to cool down or heat up theaircraft cabin to the required temperature (Section 5.6 - dynamic cases with aircraft empty).

ABBREVIATION DEFINITION

A/C Aircraft

AHM Aircraft Handling Manual

AMM Aircraft Maintenance ManualGC Ground ConnectionGSE Ground Service Equipment

IFE In-Flight Entertainment

LPGC Low Pressure Ground ConnectionOAT Outside Air Temperature

PCA Pre-Conditioned Air

A. The air flow rates and temperature requirements for the GSE, provided in Sections 5.6 and 5.7,are given at A/C ground connection.

NOTE : The cooling capacity of the equipment (kW) is only indicative and is not sufficient byitself to ensure the performance (outlet temperature and flow rate combinations arethe requirements needed for ground power).An example of cooling capacity calculation is given in Section 5.7.

B. The air flow rates and temperature requirements for the GSE are given for the A/C in theconfiguration ”4 LP ducts connected”.

NOTE : The maximum air flow is driven by pressure limitation at LPGC.

C. For temperatures at ground connection below +2 ˚C (+35.6 ˚F) (Subfreezing), the groundequipment shall be compliant with the Airbus document ”Subfreezing PCA Carts - ComplianceDocument for Suppliers” (contact Airbus to obtain this document) defining all the requirementswith which Subfreezing Pre-Conditioning Air equipment must comply to allow its use on Airbusaircraft. These requirements are in addition to the functional specifications included in the IATAAHM997.

2. Ground Pneumatic Power RequirementsThis section provides the ground pneumatic power requirements for:

5-6-0Page 1

Dec 01/16


- Heating (pull up) the cabin, initially at OAT, up to 21 ˚C (69.8 ˚F) (see FIGURE5-6-0-991-001-A)

- Cooling (pull down) the cabin, initially at OAT, down to 27 ˚C (80.6 ˚F) (see FIGURE5-6-0-991-002-A).

5-6-0Page 2

Dec 01/16


**ON A/C A380-800

OAT ISA −38° C (−36.4° F); GC OUTLET +70° C (+158° F); EMPTY CABIN; IFE OFF;NO SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON

20 40 60 80 100 120

3.5

4

4.5

5

5.5

6

6.5

03

MAXIMUM AIR FLOW

PULL UP PERFORMANCE

7

8

9

10

11

12

13

14

AIR

FLO

W A

T G

C (

kg/s

)

AIR

FLO

W A

T G

C (

lb/s

)

TIME TO HEAT CABIN TO +21° C (+69.8° F) ON GROUND (min)

715

L_AC_050600_1_0010101_01_00

Ground Pneumatic Power RequirementsHeating

FIGURE-5-6-0-991-001-A01

5-6-0Page 3

Dec 01/16


**ON A/C A380-800

OAT ISA +23° C (+73.4° F); GC OUTLET −10° C (+14° F); EMPTY CABIN; IFE OFF;SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON

AIR

FLO

W A

T G

C (

kg/s

)

0 20 40 60 80 100 120

AIR

FLO

W A

T G

C (

lb/s

)

0

1

2

3

4

5

6

7PULL DOWN PERFORMANCE

TIME TO COOL CABIN TO +27° C (+80.6° F) ON GROUND (min)

MAXIMUM AIR FLOW

0

2

4

6

8

10

12

14

OAT ISA +23° C (+73.4° F); GC OUTLET +2° C (+35.6° F); EMPTY CABIN; IFE OFF;SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON

L_AC_050600_1_0020101_01_00

Ground Pneumatic Power RequirementsCooling

FIGURE-5-6-0-991-002-A01

5-6-0Page 4

Dec 01/16


5-7-0 Preconditioned Airflow Requirements

**ON A/C A380-800

Preconditioned Airflow Requirements

1. This section provides the preconditioned airflow rate and temperature needed to maintain the cabintemperature at 27 ˚C (80.6 ˚F) for the cooling or 21 ˚C (69.8 ˚F) for the heating cases.

These settings are not intended to be used for operation (they are not a substitute for the settingsgiven in the AMM). They are based on theoretical simulations and give the picture of a real steadystate.For the air conditioning (cooling) operation, the AMM details the procedure and the preconditionedairflow settings to maintain the cabin temperature below 27 ˚C (80.6 ˚F) during boarding (thereforeit is not a steady state).

5-7-0Page 1

Dec 01/16


**ON A/C A380-800

05

1015

2025

30−

5−

10−

15−

203.

5

4.0

4.5

5.0

5.5

6.5

6.0

8.0

9.0

10.0

11.0

12.0

13.0

AIRFLOW AT GC (kg/s)

14.0

C2

C3

C1

MA

XIM

UM

AIR

FLO

W

H

6.3

TO

BE

US

ED

FO

R O

PE

RA

TIO

N

010

2030

4050

6070

80

CO

OLI

NG

/HE

AT

ING

PE

RF

OR

MA

NC

E

INLE

T T

EM

PE

RA

TU

RE

AT

GC

(°

C)

INLE

T T

EM

PE

RA

TU

RE

AT

GC

(°

F)

OA

T IS

A +

30 °

C (

86 °

F);

723

PA

SS

EN

GE

RS

AN

D C

RE

W; I

FE

ON

; LIG

HT

S O

N; S

OLA

R L

OA

D; R

EC

IRC

ULA

TIO

N F

AN

S O

N

EX

AM

PL

E:

FO

R T

HE

CO

ND

ITIO

NS

C3,

TH

E C

OO

LIN

G C

AP

AC

ITY

OF

4 k

g/s

x 1

kJ/(

kg. °

C)

x [2

7 −

(−

13)]

= 1

52 k

W(O

R 4

5 T

ON

S C

OO

LIN

G C

AP

AC

ITY

) IS

NE

ED

ED

TO

MA

INT

AIN

TH

E C

AB

IN T

EM

PE

RA

TU

RE

AT

27

° C

(80

.6 °

F)

OA

T IS

A +

23 °

C (

73.4

° F

); 7

23 P

AS

SE

NG

ER

S A

ND

CR

EW

; IF

E O

N; L

IGH

TS

ON

; SO

LAR

LO

AD

; RE

CIR

CU

LAT

ION

FA

NS

ON

OA

T IS

A; 7

23 P

AS

SE

NG

ER

S A

ND

CR

EW

; IF

E O

N; L

IGH

TS

ON

; SO

LAR

LO

AD

; RE

CIR

CU

LAT

ION

FA

NS

ON

OA

T IS

A −

38 °

C (

−36

.4 °

F);

EM

PT

Y C

AB

IN; I

FE

OF

F; L

IGH

TS

ON

; NO

SO

LAR

LO

AD

; RE

CIR

CU

LAT

ION

FA

NS

ON

CO

OLI

NG

CA

PA

CIT

Y C

ALC

ULA

TIO

N:

AIRFLOW AT GC (lb/s)

[4 k

g/s

AT

−13

° C

(8.

6 °

F)

FO

R A

IR A

T G

C IN

LET

].SE

TT

ING

S N

OT

INT

EN

DE

D

L_AC_050700_1_0010101_01_05

Preconditioned Airflow RequirementsFIGURE-5-7-0-991-001-A01

5-7-0Page 2

Dec 01/16


5-8-0 Ground Towing Requirements

**ON A/C A380-800

Ground Towing Requirements

1. This section provides information on aircraft towing.

The A380-800 is designed with means for conventional or towbarless towing. Information/procedurescan be found for both in AMM 09.Status on towbarless towing equipment qualification can be found in ISI 09.11.00001.It is possible to tow or push the aircraft, at maximum ramp weight with engines at zero or up to idlethrust, using a towbar attached to the NLG. The towbar fitting is installed at the front of the leg(optional towing fitting for towing from the rear of the NLG available).The body gears have attachment points for towing or debogging (for details, refer ARM 07).

This section shows the chart to determine the drawbar pull and tow tractor mass requirements as afunction of the following physical characteristics, see FIGURE 5-8-0-991-001-A:- Aircraft weight,- Number of engines at idle,- Slope.The chart is based on the A380-800 engine type with the highest idle thrust. The chart is thereforevalid for all A380-800 models.

2. Towbar design guidelines

The aircraft towbar shall comply with the following standards:- SAE AS 1614, ”Main Line Aircraft Towbar Attach Fitting Interface”,- SAE ARP1915, ”Aircraft Towbar”,- ISO 8267-1, ”Aircraft - Towbar Attachment Fitting - Interface Requirements - Part 1: Main Line

Aircraft”,- ISO 9667, ”Aircraft Ground Support Equipment - Towbars”,- IATA Airport Handling Manual AHM 958, ”Functional Specification for an Aircraft Towbar”.

A conventional type towbar should be equipped with a damping system (to protect the NLG againstjerks) and with towing shear pins:- A traction shear pin calibrated at 62 000 daN (139 382 lbf),- A torsion pin calibrated at 4 800 m.daN (424 779 lbf.in).The towing head is designed according to ISO 8267-1, cat. V.

5-8-0Page 1

Dec 01/16


**ON A/C A380-800

L_AC_050800_1_0010101_01_02

EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A380 AT 560 t, AT 1.5% SLOPE,2 ENGINES AT IDLE AND FOR WET TARMAC CONDITIONS:

−ON THE RIGHT HAND SIDE OF THE GRAPH, CHOOSE THE RELEVANT AIRCRAFT WEIGHT (560 t),−FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUIRED SLOPE PERCENTAGE (1.5%),−FROM THE POINT OBTAINED DRAW A STRAIGHT HORIZONTAL LINE UNTIL No. OF ENGINES AT IDLE = 4,−FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUESTED NUMBER OF ENGINES (2),−FROM THIS POINT DRAW A STRAIGHT HORIZONTAL LINE TO THE DRAWBAR PULL AXIS,−THE Y−COORDINATE OBTAINED IS THE NECESSARY DRAWBAR PULL FOR THE TRACTOR (34.4 t),−SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE.

THE OBTAINED X−COORDINATE IS THE RECOMMENDED MINIMUM TRACTOR WEIGHT (60.4 t).

00

5

10

15

20

25

30

35

40

45

50

10 20 30 40 50 60 70 80 0 1 2 3 4 0 0.5 1.0 1.5 2.0

BREAKAWAY RESISTANCE 4%# OF ENGINES ON FOR PB:2ENGINE THRUST 1779.3 daN 600

550500

450

400

350

300

TRACTOR WEIGHT [ t ] NO OF ENGINES AT IDLE SLOPE [ % ]

2 ENGINES ON1.5% SLOPE

A/C WEIGHT [ t ]DRAWBAR PULL [ t ]

WET C

ONCRETE =

0.5

7

HARD SNOW = 0.2

ICE = 0.05

DR

Y C

ON

CR

ETE

=

0.8

34.4

60.4

560

Ground Towing RequirementsFIGURE-5-8-0-991-001-A01

5-8-0Page 2

Dec 01/16


**ON A/C A380-800

A

0.200 m(7.9 in)

A

0.555 m(21.85 in)

L_AC_050800_1_0040101_01_00

Ground Towing RequirementsNose Gear Towing FittingsFIGURE-5-8-0-991-004-A01

5-8-0Page 3

Dec 01/16


5-9-0 De-Icing and External Cleaning

**ON A/C A380-800

De-Icing and External Cleaning

1. De-Icing and External Cleaning on GroundThe mobile equipment for aircraft de-icing and external cleaning must be capable of reaching heightsup to approximately 24 m (79 ft).

2. De-Icing

AIRCRAFTTYPE

Wing Top Surface(Both Sides)

Wingtip Devices(Both Inside andOutside Surfaces)

(Both Sides)

HTP Top Surface(Both Sides)

VTP(Both Sides)

A380 - 800723 m2

(7 782 ft2)10 m2

(108 ft2)186 m2

(2 002 ft2)230 m2

(2 476 ft2)

AIRCRAFT TYPEFuselage Top Surface

(Top Third - 120˚ Arc)

Nacelle and Pylon(Top Third - 120˚ Arc)

(All Engines)Total De-Iced Area

A380 - 800497 m2

(5 350 ft2)112 m2

(1 206 ft2)1 757 m2

(18 912 ft2)

NOTE : Dimensions are approximate.

3. External Cleaning

AIRCRAFTTYPE

Wing TopSurface

(Both Sides)

Wing LowerSurface

(Including FlapTrack Fairing)(Both Sides)

Wingtip Devices(Both Insideand OutsideSurfaces)

(Both Sides)

HTP TopSurface

(Both Sides)

HTP LowerSurface

(Both Sides)

A380 - 800723 m2

(7 782 ft2)794 m2

(8 547 ft2)10 m2

(108 ft2)186 m2

(2 002 ft2)186 m2

(2 002 ft2)

AIRCRAFT TYPEVTP

(Both Sides)Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned Area

A380 - 800230 m2

(2 476 ft2)1 531 m2

(16 480 ft2)373 m2

(4 015 ft2)4 034 m2

(43 422 ft2)

NOTE : Dimensions are approximate.

5-9-0Page 1

Dec 01/16


OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

**ON A/C A380-800

Engine Exhaust Velocities and Temperatures

1. General

This section provides the estimated engine exhaust efflux velocity and temperature contours forMaximum Take-off, Breakaway and Idle conditions for the A380 engine.

Contours are available for both Rolls-Royce’s Trent 900 engine and the Engine Alliance’s GP7200engine.

The Maximum Take-off data are presented at the maximum thrust rating for all the A380 engine.

The Breakaway data are presented at a rating corresponding to the minimum thrust level required toinitiate movement of an A380-800 at its maximum ramp weight from static position and on uphillground.

The Idle data are directly provided by the engine manufacturers.

In the charts, longitudinal distances are measured from the inboard engine core nozzle exit station,while lateral distances are measured from the aircraft fuselage centerline.

A. Data from Rolls-Royce’s Trent 900:

The estimated efflux data are presented at ISA +15˚C (+59˚F), Sea Level Static andnegligible wind conditions.The analysis assumes that the core and bypass streams are fully mixed and calculates the jetbehaviour in free, still air and therefore does not take into account effects such as on-winginstallation, ground entrainment and ambient wind conditions.Velocity contours are presented at 50 ft/s (15 m/s), 100 ft/s (30 m/s) and 150 ft/s (46 m/s),while temperature contours are presented at 104 ˚F (40˚C), 122˚F (50˚C) and 140˚F(60˚C).

B. Data from Engine Alliance’s GP7200:

6-1-0Page 1

Dec 01/16


The estimated efflux data are presented at ISA +15˚C (+59˚F), Sea Level Static with 20 ktheadwind. It also assumed ground plane and proximity effects. Velocity contours are presentedat 35 mph (16 m/s), 65 mph (29 m/s) and 105 mph (47 m/s), while temperature contours arepresented at 122˚F (50˚C), 212˚F (100˚C) and 392˚F (200˚C). Engine Alliance stronglyrecommends that jet blast studies using their contours include the effect of a 20 kt headwind.

6-1-0Page 2

Dec 01/16


6-1-1 Engine Exhaust Velocities - Ground Idle Power

**ON A/C A380-800

Engine Exhaust Velocities - Ground Idle Power

1. This section gives engine exhaust velocities at ground idle power.

6-1-1Page 1

Dec 01/16


**ON A/C A380-800

deh0

0023

17

10

20

0

0 40 60

20

80

30

100 120

40 50

140 160

60

180 200

METERS

FEET

ELEVATION

PLAN

0

5

10

15

20

40

60m ft

50 ft/sec(15 m/sec)

100 ft/sec(30 m/sec)




50 ft/sec(15 m/sec)

0

5

10

15

20

40

60

m ft

60

60

60

15

15

15

15

220

L_AC_060101_1_0010101_01_00

Engine Exhaust VelocitiesGround Idle Power - TRENT 900 Engines

FIGURE-6-1-1-991-001-A01

6-1-1Page 2

Dec 01/16


**ON A/C A380-800

ALL VELOCITY VALUES ARE IN STATUE MILES PER HOUR.

FEET(METERS)

GROUND PLANE

CONVERSION FACTOR1 MPH = 1.6 km/h

300

(91)

140(43)

ELEVATION

FEET

(METERS)

0

0

PLAN

150

(46)

0

70(21)

PW

VE

−00

224

(020

7)

AIRPLANECL

105 MPH

65 MPH

35 MPH

DANGER (KEEP OUT) ZONES 35 MPH

(169 km/h)

(105 km/h)

(56 km/h)

105 MPH65 MPH

35 MPH

(169 km/h)(105 km/h)

(56 km/h)

FEET(METERS)

140

0

70(21)

L_AC_060101_1_0020101_01_01

NOTE:

Engine Exhaust VelocitiesGround Idle Power - GP 7200 Engines

FIGURE-6-1-1-991-002-A01

6-1-1Page 3

Dec 01/16


6-1-2 Engine Exhaust Temperatures - Ground Idle Power

**ON A/C A380-800

Engine Exhaust Temperatures - Ground Idle Power

1. This section gives engine exhaust temperatures at ground idle power.

6-1-2Page 1

Dec 01/16


**ON A/C A380-800

10

20 40 60

20 30

80 100 120

40

140 160

500

0

METERS

FEET

20

40

60

15

0

10

5

m ft

ELEVATION

PLAN

deh0

0023

16

20

40

60

15

0

10

5

m ft

140°F(60°C)

122°F(50°C)

104°F(40°C)

140°F(60°C)

122°F(50°C)

104°F(40°C)

80

100

120

20

25

30

35

L_AC_060102_1_0010101_01_01

GROUND IDLE POWER

Engine Exhaust TemperaturesGround Idle Power - TRENT 900 Engines

FIGURE-6-1-2-991-001-A01

6-1-2Page 2

Dec 01/16


**ON A/C A380-800

FEET(METERS)

GROUND PLANEELEVATIONFEET

(METERS)

0

0

PLAN AIRPLANECL

0

70(21)

0

70(21)

105(32)

ALL TEMPERATURES ARE IN FAHRENHEIT (CELSIUS).

392°F (200°C)

212°F (100°C)

122°F (50°C)

150

(46)

75

(23)

225

(69)

105(32)

35(11)

35(11)

PW

VE

−00

226

(020

7)

392°F (200°C)

122°F (50°C)

212°F (100°C)

NOTE:

L_AC_060102_1_0020101_01_01

Engine Exhaust TemperaturesGround Idle Power - GP 7200 Engines

FIGURE-6-1-2-991-002-A01

6-1-2Page 3

Dec 01/16


6-1-3 Engine Exhaust Velocities - Breakaway Power

**ON A/C A380-800

Engine Exhaust Velocities - Breakaway Power

1. This section gives engine exhaust velocities at breakaway power.

6-1-3Page 1

Dec 01/16


**ON A/C A380-800

deh0

0023

19

100METERS 0

0FEET 40 80

20 40 60 80

120 160 200 240 280 320 360

5

10

1540

60ftm

20

50 ft/sec(15 m/sec)



ELEVATION

PLAN

50 ft/sec(15 m/sec)



5

10

1540

0

60

ftm

20

0

80

100

120

20

25

30

35

L_AC_060103_1_0010101_01_00

Engine Exhaust VelocitiesBreakaway Power - TRENT 900 Engines

FIGURE-6-1-3-991-001-A01

6-1-3Page 2

Dec 01/16


**ON A/C A380-800



PW

VE

−02

200

(020

7)


NOTE:

L_AC_060103_1_0020101_01_01

FEET(METERS)

GROUND PLANE

140(43)

ELEVATION0

70(21)

PLAN AIRPLANECL

FEET

(METERS)

0

0

150

(46)

300

(91)

450

(137)

105 MPH65 MPH

35 MPH(169 km/h)(105 km/h)

(56 km/h)

105 MPH(169 km/h) 65 MPH

(105 km/h) 35 MPH(56 km/h)

FEET

140(43)

0

70(21)

Engine Exhaust VelocitiesBreakaway Power - GP 7200 Engines

FIGURE-6-1-3-991-002-A01

6-1-3Page 3

Dec 01/16


6-1-4 Engine Exhaust Temperatures - Breakaway Power

**ON A/C A380-800

Engine Exhaust Temperatures - Breakaway Power

1. This section gives engine exhaust temperatures at breakaway power.

6-1-4Page 1

Dec 01/16


**ON A/C A380-800

ELEVATION

20 40 60 80 100 120 140 160

40302010METERS 0

0FEET

520

10

40

60

15

m ft

0

deh0

0023

18

520

10

40

60

15

m ft

PLAN

140°F(60°C)

122°F(50°C)

104°F(40°C)

140°F(60°C)

122°F(50°C)

104°F(40°C)

0

80

100

120

20

25

30

35

180

50

L_AC_060104_1_0010101_01_01

BREAKAWAY POWER(11% MAX TAKE−OFF THRUST)

Engine Exhaust TemperaturesBreakaway Power - TRENT 900 Engines

FIGURE-6-1-4-991-001-A01

6-1-4Page 2

Dec 01/16


**ON A/C A380-800

AIRPLANECL

NOTE : ALL TEMPERATURES ARE IN FAHRENHEIT (CELSIUS).

392°F (200°C)

212°F (100°C)

122°F (50°C)

392°F (200°C)

212°F (100°C)

122°F (50°C)

FEET(METERS)

GROUND PLANEELEVATIONFEET

(METERS)

0

0

PLAN

0

70(21)

0

70(21)

105(32)

150

(46)

75

(23)

225

(69)

105(32)

35(11)

35(11)

PW VE−02201 (0805)

L_AC_060104_1_0020101_01_00

Engine Exhaust TemperaturesBreakaway Power - GP 7200 Engines

FIGURE-6-1-4-991-002-A01

6-1-4Page 3

Dec 01/16


6-1-5 Engine Exhaust Velocities - Max Take-off Power

**ON A/C A380-800

Engine Exhaust Velocities - Max Take-off Power

1. This section gives engine exhaust velocities at max take-off power.

6-1-5Page 1

Dec 01/16


**ON A/C A380-800

deh0

0023

15

20

100 200 300 400 500 600 700 800

40 60 80 100 120 140 160 180 200 220 240METERS 0

FEET

0

20

10 40

80m ft

TO1800 ft(540 m)

TO1800 ft(540 m)

PLAN

ELEVATION

50 ft/sec(15 m/sec)



0

20

10 40

80

m ft

120

160

30

40

60

50 ft/sec(15 m/sec)



L_AC_060105_1_0010101_01_00

Engine Exhaust VelocitiesMax. Take-Off Power - TRENT 900 Engines

FIGURE-6-1-5-991-001-A01

6-1-5Page 2

Dec 01/16


**ON A/C A380-800

L_AC_060105_1_0020101_01_01



PW

VE

−00

225

(020

7)


NOTE:

FEET(METERS)

GROUND PLANE

300 450 600

140(43)

ELEVATIONFEET

0 150

0

70(21)

(91) (137) (183)0 (46)

(METERS)

PLAN AIRPLANECL

65 MPHOUT TO1090 ft(332 m)



FEET(METERS)

140(43)

0

70(21)




Engine Exhaust VelocitiesMax. Take-Off Power - GP 7200 Engines

FIGURE-6-1-5-991-002-A01

6-1-5Page 3

Dec 01/16


6-1-6 Engine Exhaust Temperatures - Max Take-off Power

**ON A/C A380-800

Engine Exhaust Temperatures - Max Take-off Power

1. This section gives engine exhaust temperatures at max take-off power.

6-1-6Page 1

Dec 01/16


**ON A/C A380-800

deh0

0023

14

20METERS 0

FEET 0 40 80 120

40 60

160

80

200 240 280 320

100

360

120

400

20

40

60

10

5

15

0

ftm

ELEVATION

PLAN

20

40

60

10

5

15

0

ftm

80

100

120

15

20

25

30

35

140°F(60 C)

122°F(50 C)

104°F(40 C) TO

540 ft(162 m)

140°F(60 C)

122°F(50 C)

104°F(40 C)

TO540 ft

(162 m)

L_AC_060106_1_0010101_01_01

MAX TAKE−OFF POWER

Engine Exhaust TemperaturesMax Take-Off Power - TRENT 900 Engines

FIGURE-6-1-6-991-001-A01

6-1-6Page 2

Dec 01/16


**ON A/C A380-800

70(21)

35(11)

105(32)

E−00227 (0704)PW V

FEET(METERS)

0ELEVATION

0 PLAN

0

0

FEET

(METERS)

75

(23)

150

(46)

225

(69)

AIRPLANE

GROUND PLANE

392°F (200°C)

212°F (100°C)

122°F (50°C)

392°F (200°C)212°F (100°C)

122°F (50°C)

NOTE : ALL TEMPERATURES ARE IN FAHRENHEIT (CELSIUS).

CL

70(21)

35(11)

105(32)

L_AC_060106_1_0020101_01_00

Engine Exhaust TemperaturesMax Take-Off Power - GP 7200 Engines

FIGURE-6-1-6-991-002-A01

6-1-6Page 3

Dec 01/16


6-3-0 Danger Areas of the Engines

**ON A/C A380-800

Danger Areas of the Engines

1. Danger Areas of the Engines

The intake suction danger areas, which are plotted in this chapter, correspond to very low suctionvelocities in order to prevent very low density objects (hat, handkerchief) from ingestion by engines.The primary aim of those danger areas is to protect the people working around the engines.

The A380 outer engines are high enough above ground to prevent the ingestion of typical looseobjects, which can be found on ground at the edge of runways/taxiways paved areas (loose gravelsfor example), in the following conditions:- at usual taxiway thrust (i.e. up to the breakaway power setting), even if the loose objects are

below the A380 outer engines.- at usual take-off thrust (i.e. up to the maximum take-off power setting), if the loose objects are

beyond 3 meters from the A380 outer engines centreline.

6-3-0Page 1

Dec 01/16


6-3-1 Danger Areas of the Engines - Ground Idle Power

**ON A/C A380-800

Danger Areas of the Engines - Ground Idle Power

1. This section gives danger areas of the engines at ground idle power conditions.

6-3-1Page 1

Dec 01/16


**ON A/C A380-800

deh0

0015

13

INTAKE SUCTION DANGER AREA MINIMUM IDLE POWER

EXHAUST DANGER AREA

ENTRY CORRIDOR

4.5 m(15 ft)

1.3 m(4 ft 3 in)

30TO 70 m (230 ft) AFT OF EXHAUST NOZZLES

L_AC_060301_1_0010101_01_00

Danger Areas of the EnginesGround Idle Power - TRENT 900 Engines

FIGURE-6-3-1-991-001-A01

6-3-1Page 2

Dec 01/16


**ON A/C A380-800

A

B

15 ft(4.6 m)

5 ft(1.5 m)

A

A

A

B

AREA A − INTAKE SUCTION DANGER AREA

AREA B − ENTRY CORRIDOR

AREA C − EXHAUST DANGER AREA (AFT OF EXHAUST NOZZLE)277 ft (84 m) − GROUND IDLE (20 kt HEADWIND)

33°

PW

VE

−021

97 (0

207)

C

C C

C

L_AC_060301_1_0020101_01_01

Danger Areas of the EnginesGround Idle Power - GP 7200 Engines

FIGURE-6-3-1-991-002-A01

6-3-1Page 3

Dec 01/16


6-3-2 Danger Areas of the Engines - Max. Take-Off Power

**ON A/C A380-800

Danger Areas of the Engines - Max. Take-Off Power

1. This section gives danger areas of the engines at max take-off power conditions.

6-3-2Page 1

Dec 01/16


**ON A/C A380-800

deh0

0015

15

INTAKE SUCTION DANGER AREA MAX TAKE−OFF POWER

EXHAUST DANGER AREA

8.9 m(29 ft)

30TO 548.6 m (1800 ft) AFT OF EXHAUST NOZZLES

L_AC_060302_1_0010101_01_00

Danger Areas of the EnginesMax Take-Off Power - TRENT 900 Engines

FIGURE-6-3-2-991-001-A01

6-3-2Page 2

Dec 01/16


**ON A/C A380-800


AREA C − EXHAUST DANGER AREA (AFT OF EXHAUST NOZZLE)1553 ft (473 m) − MAXIMUM TAKEOFF (20 kt HEADWIND)

B


A

C

A

B

C

41°

32 ft(9.8 m)

11 ft(3.4 m)

E−

0219

9 (0

207)

PW

V

L_AC_060302_1_0020101_01_01

Danger Areas of the EnginesMax Take-Off Power - GP 7200 Engines

FIGURE-6-3-2-991-002-A01

6-3-2Page 3

Dec 01/16


6-3-3 Danger Areas of the Engines - Breakaway Power

**ON A/C A380-800

Danger Areas of the Engines - Breakaway Power

1. This section gives danger areas of the engines at breakaway power.

6-3-3Page 1

Dec 01/16


**ON A/C A380-800

deh0

0015

14

INTAKE SUCTION DANGER AREA BREAKAWAY POWER

EXHAUST DANGER AREA

6.0 m(20 ft)4 ENGINE BREAKAWAY

30TO 123.4 m (405 ft) AFT OF EXHAUST NOZZLES

L_AC_060303_1_0010101_01_00

Danger Areas of the EnginesBreakaway Power - TRENT 900 Engines

FIGURE-6-3-3-991-001-A01

6-3-3Page 2

Dec 01/16


**ON A/C A380-800

A

B

C



AREA C − EXHAUST DANGER AREA (AFT OF EXHAUST NOZZLE)415 ft (126 m) − BREAKAWAY (20 kt HEADWIND)

B

A A

A

C

38°

PW

VE

−02

198

(020

7)

20 ft(6.10 m)

6.5 ft(1.98 m)

L_AC_060303_1_0020101_01_01

Danger Areas of the EnginesBreakaway Power - GP 7200 Engines

FIGURE-6-3-3-991-002-A01

6-3-3Page 3

Dec 01/16


6-4-1 APU Exhaust Velocities and Temperatures

**ON A/C A380-800

APU Exhaust Velocities and Temperatures - ECS Conditions

1. This section provides APU exhaust velocities and temperatures in max. ECS conditions.

6-4-1Page 1

Dec 01/16


**ON A/C A380-800

DIS

TA

NC

E F

RO

M A

IRC

RA

FT

CE

NT

ER

LIN

E

0 10 20 30 40 50 60 70 80 90 100

30

6

10

20

0

−10

−20

FEET

DIS

TA

NC

E F

RO

M A

IRC

RA

FT

CE

NT

ER

LIN

E

DISTANCE DOWNSTREAM FROM NOZZLEMETERS

10

20

0

−10

−20

FEET

NOTE: THE DATA GIVEN IS BASED ON THE FOLLOWING ASSUMPTIONS:−SEA LEVEL STATIC CONDITIONS−ISA + 23 °C (73 °F)−NO WIND

100

30


0 3 6 9 12 15 18 21 24 27

3

0

−3

−6

0 80 90

0 3 6 9 12 15 18 21 24 27

3

6

0

−3

−6

574 °C (1065 °F)

260 °C (500 °F)

149 °C (300 °F)

316 °C (600 °F)

204 °C (400 °F)93 °C (200 °F)

10 20 30 40 50 60 70

46 m/s (150 ft/s)

27 m/s (90 ft/s)

68 m/s (223 ft/s)

37 m/s (120 ft/s)

18 m/s (60 ft/s)

9 m/s (30 ft/s)

L_AC_060401_1_0010101_01_00

APU Exhaust Velocities and TemperaturesMax. ECS Conditions

FIGURE-6-4-1-991-001-A01

6-4-1Page 2

Dec 01/16


6-4-2 APU Exhaust Velocities and Temperatures - MES Conditions

**ON A/C A380-800

APU Exhaust Velocities and Temperatures - MES Conditions

1. This section gives the APU exhaust velocities and temperatures in MES conditions.

6-4-2Page 1

Dec 01/16


**ON A/C A380-800

L_AC_060402_0_AAM0_01_00

NOTE: THE DATA GIVEN IS BASED ON THE FOLLOWING ASSUMPTIONS:−SEA LEVEL STATIC CONDITIONS−ISA + 23 °C (73 °F)−NO WIND

0 10 20 30 40 50 60 70 80 90 100

30

10

20

0

−10

−20

FEET


10

20

0

−10

−20

FEET100

0 3 6 9 12 15 18 21 24 27 30−6

DIS

TA

NC

E F

RO

M A

IRC

RA

FT

CE

NT

ER

LIN

E


0 3 6 9 12 15 18 21 24 27

3

6

0

−3

−6

DIS

TA

NC

E F

RO

M A

IRC

RA

FT

CE

NT

ER

LIN

E

0 10 20 30 40 50 60 70 80 90

3

6

0

−3

458 °C (857 °F)

260 °C (500 °F)

149 °C (300 °F)

316 °C (600 °F)

204 °C (400 °F)

46 m/s (150 ft/s)

27 m/s (90 ft/s)

80 m/s (263 ft/s)

37 m/s (120 ft/s)

18 m/s (60 ft/s)

9 m/s (30 ft/s)

93 °C (200 °F)

L_AC_060402_1_0010101_01_00

APU Exhaust Velocities and TemperaturesMES Conditions

FIGURE-6-4-2-991-001-A01

6-4-2Page 2

Dec 01/16


PAVEMENT DATA


**ON A/C A380-800

General Information

1. A brief description of the pavement charts that follow will help in airport planning.

To aid in the interpolation between the discrete values shown, each aircraft configuration is shownwith a minimum range of five loads on the Main Landing Gear (MLG).

All curves on the charts represent data at a constant specified tire pressure with:- The aircraft loaded to the Maximum Ramp Weight (MRW),- The CG at its maximum permissible aft position.

Pavement requirements for commercial aircraft are derived from the static analysis of loads imposedon the MLG struts.

Landing Gear Footprint:Section 07-02-00 presents basic data on the landing gear footprint configuration, MRW and tire sizesand pressures.

Maximum Pavement Loads:Section 07-03-00 shows maximum vertical and horizontal pavement loads for certain criticalconditions at the tire-ground interfaces.

Landing Gear Loading on Pavement:Section 07-04-00 contains charts to find these loads throughout the stability limits of the aircraft atrest on the pavement.These MLG loads are used as the point of entry to the pavement design charts which follow,interpolating load values where necessary.

Flexible Pavement Requirements - US Army Corps of Engineers Design Method:Section 07-05-00 uses procedures in Instruction Report No. S-77-1 ”Procedures for Development ofCBR Design Curves”, dated June 1977 and as modified according to the methods described in ICAOAerodrome Design Manual, Part 3. Pavements, 2nd Edition, 1983, Section 1.1 (The ACN-PCNMethod), and utilizing the alpha factors approved by ICAO in October 2007.The report was prepared by the ”U.S. Army Corps Engineers Waterways Experiment Station, Soilsand Pavement Laboratory, Vicksburg, Mississippi”.The line showing 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).

Flexible Pavement Requirements - LCN Conversion Method:

7-1-0Page 1

Dec 01/16


The Load Classification Number (LCN) curves are no longer provided in section 07-06-00 since theLCN system for reporting pavement strength is obsolete, having been replaced by the ICAOrecommended ACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

Rigid Pavement Requirements - PCA (Portland Cement Association) Design Method:Section 07-07-00 provides the rigid pavement design curves that have been prepared with the use ofthe Westergaard Equation.This is in general accordance with the procedures outlined in the Portland Cement Associationpublications, ”Design of Concrete Airport Pavement”, 1973 and ”Computer Program for AirportPavement Design” (Program PDILB), 1967 both by Robert G. Packard.

Rigid Pavement Requirements - LCN Conversion:The Load Classification Number (LCN) curves are no longer provided in section 07-08-00 since theLCN system for reporting pavement strength is obsolete, having been replaced by the ICAOrecommended ACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

ACN/PCN Reporting System:Section 07-09-00 provides ACN data prepared according to the ACN/PCN system as referenced inICAO Annex 14, ”Aerodromes”, Volume 1 ”Aerodrome Design and Operations” Fourth Edition, July2004, incorporating Amendments 1 to 6.The ACN/PCN system provides a standardized international aircraft/pavement rating systemreplacing the various S, T, TT, LCN, AUW, ISWL, etc., rating systems used throughout the world.ACN is the Aircraft Classification Number and PCN is the corresponding Pavement ClassificationNumber.An aircraft having an ACN less than or equal to the PCN can operate without restriction on thepavement.Numerically the ACN is two times the derived single wheel load expressed in thousands of kilograms.The derived single wheel load is defined as the load on a single tire inflated to 1.25 MPa (181 psi)that would have the same pavement requirements as the aircraft.Computationally the ACN/PCN system uses PCA program PDILB for rigid pavements and S-77-1 forflexible pavements to calculate ACN values.

The Airport Authority must decide on the method of pavement analysis and the results of theirevaluation shown as follows:

PCNPAVEMENT TYPE SUBGRADE

CATEGORYTIRE PRESSURE

CATEGORYEVALUATION

METHODR - Rigid A - High W - No pressure limit T - Technical

F - Flexible B - MediumX - High pressure limitedto 1.75 MPa (254 psi)

U - Using Aircraft

7-1-0Page 2

Dec 01/16


PCNPAVEMENT TYPE SUBGRADE

CATEGORYTIRE PRESSURE

CATEGORYEVALUATION

METHOD

C - Low

Y - Medium pressurelimited to 1.25 MPa (181psi)

D - Ultra LowZ - Low pressure limitedto 0.5 MPa (73 psi)

For flexible pavements, the four subgrade categories (CBR) are:

- A. High Strength CBR 15

- B. Medium Strength CBR 10

- C. Low Strength CBR 6

- D. Ultra Low Strength CBR 3

For rigid pavements, the four subgrade categories (k) are:

- A. High Strength k = 150 MN/m3 (550 pci)

- B. Medium Strength k = 80 MN/m3 (300 pci)

- C. Low Strength k = 40 MN/m3 (150 pci)

- D. Ultra Low Strength k = 20 MN/m3 (75 pci)

7-1-0Page 3

Dec 01/16


7-2-0 Landing Gear Footprint

**ON A/C A380-800

Landing Gear Footprint

1. This section provides data about the landing gear footprint in relation with the aircraft MaximumRamp Weight (MRW) and tire sizes and pressures.The landing-gear footprint information is given for all the operational weight variants of the aircraft.

7-2-0Page 1

Dec 01/16


**ON A/C A380-800

1.05

0 m

(3.4

45 ft

)

1.53

0 m

(5.0

20 ft

)

NO

SE

LA

ND

ING

GE

AR

12.4

56 m

(40.

866

ft)

WIN

G L

AN

DIN

GG

EA

R

BO

DY

LA

ND

ING

GE

AR

(5.0

85 ft

)1.

550

m

5.26

4 m

(17.

270

ft)

(5.0

20 ft

)1.

530

m

(5.5

77 ft

)1.

700

m(5

.577

ft)

1.70

0 m

1.35

0 m

(4.4

29 ft

)

(5.5

77 ft

)1.

700

m

(93.

848

ft)28

.605

m

(104

.596

ft)

31.8

81 m

L_AC_070200_1_0030101_01_01

Landing Gear Footprint(Sheet 1 of 2)

FIGURE-7-2-0-991-003-A01

7-2-0Page 2

Dec 01/16


**ON A/C A380-800

WE

IGH

TV

AR

IAN

TM

AX

IMU

MR

AM

PW

EIG

HT

WV

005

562

000

kg(1

239

000

lb)

95.1

%14

.1 b

ar(2

05 p

si)

15 b

ar(2

18 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

15 b

ar(2

18 p

si)

1 40

0x53

0 R

23 4

0PR

WV

006

575

000

kg(1

267

650

lb)

94.3

%14

.1 b

ar(2

05 p

si)

15 b

ar(2

18 p

si)

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

15 b

ar(2

18 p

si)

1 40

0x53

0 R

23 4

0PR

WV

007

492

000

kg(1

084

675

lb)

95.1

%14

.1 b

ar(2

05 p

si)

14 b

ar(2

03 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

14 b

ar(2

03 p

si)

1 40

0x53

0 R

23 4

0PR

WV

008

577

000

kg(1

272

075

lb)

94.3

%14

.1 b

ar(2

05 p

si)

15 b

ar(2

18 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

1 40

0x53

0 R

23 4

0PR

15 b

ar(2

18 p

si)

WV

009

512

000

kg(1

128

775

lb)

95.1

%14

.1 b

ar(2

05 p

si)

15 b

ar(2

18 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

15 b

ar(2

18 p

si)

1 40

0x53

0 R

23 4

0PR

WV

004

562

000

kg(1

239

000

lb)

95.1

%14

.1 b

ar(2

05 p

si)

15 b

ar(2

18 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

15 b

ar(2

18 p

si)

1 40

0x53

0 R

23 4

0PR

WV

000

562

000

kg(1

239

000

lb)

95.1

%14

.1 b

ar(2

05 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

15 b

ar(2

18 p

si)

1 40

0x53

0 R

23 4

0PR

15 b

ar(2

18 p

si)

1 40

0x53

0 R

23 4

0PR

WV

001

512

000

kg(1

128

775

lb)

95.1

%14

.1 b

ar(2

05 p

si)

14 b

ar(2

03 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

14 b

ar(2

03 p

si)

1 40

0x53

0 R

23 4

0PR

WV

002

571

000

kg(1

258

850

lb)

94.3

%14

.1 b

ar(2

05 p

si)

15 b

ar(2

18 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

15 b

ar(2

18 p

si)

1 40

0x53

0 R

23 4

0PR

WV

003

512

000

kg(1

128

775

lb)

95.1

%14

.1 b

ar(2

05 p

si)

14 b

ar(2

03 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

14 b

ar(2

03 p

si)

1 40

0x53

0 R

23 4

0PR

PE

RC

EN

TA

GE

OF

WE

IGH

TO

N M

AIN

GE

AR

GR

OU

P

NO

SE

GE

AR

TIR

EP

RE

SS

UR

EN

OS

E G

EA

RT

IRE

SIZ

EW

ING

GE

AR

TIR

E S

IZE

BO

DY

GE

AR

TIR

E S

IZE

WIN

GG

EA

R T

IRE

PR

ES

SU

RE

BO

DY

GE

AR

TIR

EP

RE

SS

UR

E

WV

010

482

000

kg(1

062

625

lb)

95.1

%14

.1 b

ar(2

05 p

si)

15 b

ar(2

18 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

1 40

0x53

0 R

23 4

0PR

15 b

ar(2

18 p

si)

WV

011

577

000

kg(1

272

075

lb)

94.3

%14

.1 b

ar(2

05 p

si)

15 b

ar(2

18 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

1 40

0x53

0 R

23 4

0PR

15 b

ar(2

18 p

si)

WV

012

571

000

kg(1

258

850

lb)

94.3

%14

.1 b

ar(2

05 p

si)

15 b

ar(2

18 p

si)

1 27

0x45

5 R

22 3

2PR

OR

50x

20 R

22 3

4PR

1 40

0x53

0 R

23 4

0PR

1 40

0x53

0 R

23 4

0PR

15 b

ar(2

18 p

si)

1 27

0x45

5 R

22 3

2PR

L_AC_070200_1_0030102_01_02

Landing Gear Footprint(Sheet 2 of 2)

FIGURE-7-2-0-991-003-A01

7-2-0Page 3

Dec 01/16


7-3-0 Maximum Pavement Loads

**ON A/C A380-800

Maximum Pavement Loads

1. This section provides maximum vertical and horizontal pavement loads for some critical conditions atthe tire-ground interfaces.The maximum pavement loads are given for all the operational weight variants of the aircraft.

7-3-0Page 1

Dec 01/16


**ON A/C A380-800

H

V(W

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

WD

CG

V(N

G)

MA

XIM

UM

VE

RT

ICA

L W

ING

GE

AR

GR

OU

ND

LO

AD

AT

MA

X A

FT

CG

HM

AX

IMU

M V

ER

TIC

AL

BO

DY

GE

AR

GR

OU

ND

LO

AD

AT

MA

X A

FT

CG

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

GV

(BG

)

V(B

G)

12

34

56

(PE

R S

TR

UT

)

V(W

G)

H (

PE

R S

TR

UT

)

WV

000

WE

IGH

TV

AR

IAN

T

MA

XIM

UM

RA

MP

WE

IGH

TA

TS

TA

TIC

LO

AD

MO

ST

FW

D C

GA

T 1

0 ft/

s²D

EC

ELE

RA

TIO

N

AT

ST

AT

IC L

OA

D

MA

X A

FT

CG

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

562

000

kg(1

239

000

lb)

BR

AK

ING

INS

TA

NT

AN

EO

US

106

920

kg(2

35 7

25 lb

)16

0 38

0 kg

(353

575

lb)

97 4

10 k

g(2

14 7

50 lb

)14

6 11

0 kg

(322

125

lb)

107

720

kg(2

37 4

75 lb

)16

1 57

0 kg

(356

200

lb)

97 4

10 k

g(2

14 7

50 lb

)14

6 11

0 kg

(322

125

lb)

37.5

%M

AC

(a)

43 %

MA

C(a

)

35.8

1 %

MA

C(a

)

37.8

%M

AC

(a)

35.8

1 %

MA

C(a

)

43 %

MA

C(a

)

41 %

MA

C(a

)

43 %

MA

C(a

)

V(N

G)

WV

001

WV

002

WV

003

512

000

kg(1

128

775

lb)

571

000

kg(1

258

850

lb)

512

000

kg(1

128

775

lb)

39 8

30 k

g(8

7 80

0 lb

)

39 7

60 k

g(8

7 67

5 lb

)

39 7

80 k

g(8

7 70

0 lb

)

39 7

60 k

g(8

7 67

5 lb

)

69 4

30 k

g(1

53 0

75 lb

)

66 7

30 k

g(1

47 1

25 lb

)

69 8

50 k

g(1

54 0

00 lb

)

66 7

30 k

g(1

47 1

25 lb

)

43 %

MA

C(a

)

(PE

R S

TR

UT

)

V(B

G)

43 %

MA

C(a

)

41 %

MA

C(a

)

43 %

MA

C(a

)

ST

AT

IC

AT

ST

AT

IC L

OA

D

MA

X A

FT

CG

AT

10

ft/s²

DE

CE

LER

AT

ION

BR

AK

ING

ST

EA

DY

7

34 9

30 k

g(7

7 02

5 lb

)52

400

kg

(115

525

lb)

85 5

40 k

g(1

88 5

75 lb

)12

8 31

0 kg

(282

875

lb)

31 8

30 k

g(7

0 17

5 lb

)47

740

kg

(105

250

lb)

77 9

30 k

g(1

71 8

00 lb

)11

6 89

0 kg

(257

700

lb)

35 4

90 k

g(7

8 25

0 lb

)53

240

kg

(117

375

lb)

86 1

70 k

g(1

89 9

75 lb

)12

9 26

0 kg

(284

975

lb)

31 8

30 k

g(7

0 17

5 lb

)47

740

kg

(105

250

lb)

77 9

30 k

g(1

71 8

00 lb

)11

6 89

0 kg

(257

700

lb)

(c)

(b)

(c)

(b)

(c)

(b)

(c)

(b)

(c)

(b)

(c)

(b)

(c)

(b)

(c)

(b)

AT

NO

TE

:

V(W

G)

V(N

G)

(a)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T M

RW

(b)

BR

AK

ED

WIN

G G

EA

R(c

) B

RA

KE

D B

OD

Y G

EA

R

L_AC_070300_1_0060101_01_00

Maximum Pavement Loads(Sheet 1 of 2)

FIGURE-7-3-0-991-006-A01

7-3-0Page 2

Dec 01/16


**ON A/C A380-800

NO

TE

:

12

34

56

(PE

R S

TR

UT

)

V(W

G)

H (

PE

R S

TR

UT

)V

(NG

)(P

ER

ST

RU

T)

V(B

G)

WV

004

WE

IGH

TV

AR

IAN

T

MA

XIM

UM

RA

MP

WE

IGH

TA

TS

TA

TIC

LO

AD

MO

ST

FW

D C

GA

T 1

0 ft/

s²D

EC

ELE

RA

TIO

N

BR

AK

ING

ST

AT

IC

AT

ST

AT

IC L

OA

D

MA

X A

FT

CG

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

INS

TA

NT

AN

EO

US

AT

AT

ST

AT

IC L

OA

D

MA

X A

FT

CG

AT

10

ft/s²

DE

CE

LER

AT

ION

BR

AK

ING

ST

EA

DY

562

000

kg(1

239

000

lb)

106

920

kg(2

35 7

25 lb

)16

0 38

0 kg

(353

575

lb)

37.5

%M

AC

(a)

43 %

MA

C(a

)

39 8

30 k

g(8

7 80

0 lb

)69

430

kg

(153

075

lb)

43 %

MA

C(a

)

34 9

30 k

g(7

7 02

5 lb

)52

400

kg

(115

525

lb)

(c)

(b)

108

470

kg(2

39 1

25 lb

)16

2 70

0 kg

(358

700

lb)

93 6

00 k

g(2

06 3

50 lb

)14

0 41

0 kg

(309

550

lb)

37.8

%M

AC

(a)

35.0

6 %

MA

C(a

)

41 %

MA

C(a

)

43 %

MA

C(a

)

WV

005

WV

006

WV

007

575

000

kg(1

267

650

lb)

492

000

kg(1

084

675

lb)

40 0

50 k

g(8

8 30

0 lb

)

39 7

00 k

g(8

7 52

5 lb

)

70 3

40 k

g(1

55 0

75 lb

)

65 6

10 k

g(1

44 6

50 lb

)

41 %

MA

C(a

)

43 %

MA

C(a

)

35 7

40 k

g(7

8 80

0 lb

)53

610

kg

(118

200

lb)

(c)

(b)

30 5

80 k

g(6

7 42

5 lb

)45

880

kg(1

01 1

50 lb

)(c

)

(b)

35 8

70 k

g(7

9 07

5 lb

)53

800

kg

(118

600

lb)

(c)

(b)

31 8

30 k

g(7

0 17

5 lb

)47

740

kg

(105

250

lb)

(c)

(b)

34 9

30 k

g(7

7 02

5 lb

)52

400

kg

(115

525

lb)

(c)

(b)

29 9

60 k

g(6

6 05

0 lb

)44

940

kg(9

9 07

5 lb

)(c

)

(b)

35 8

70 k

g(7

9 07

5 lb

)53

800

kg

(118

600

lb)

(c)

(b)

35 4

90 k

g(7

8 25

0 lb

)53

240

kg

(117

375

lb)

(c)

(b)

7

85 5

40 k

g(1

88 5

75 lb

)12

8 31

0 kg

(282

875

lb)

(c)

(b)

86 7

80 k

g(1

91 3

00 lb

)13

0 16

0 kg

(286

950

lb)

(c)

(b)

74 8

80 k

g(1

65 1

00 lb

)11

2 32

0 kg

(247

625

lb)

(c)

(b)

87 0

80 k

g(1

91 9

75 lb

)13

0 62

0 kg

(287

950

lb)

(c)

(b)

77 9

30 k

g(1

71 8

00 lb

)11

6 89

0 kg

(257

700

lb)

(c)

(b)

85 5

40 k

g(1

88 5

75 lb

)12

8 31

0 kg

(282

875

lb)

(c)

(b)

73 3

60 k

g(1

61 7

25 lb

)11

0 04

0 kg

(242

600

lb)

(c)

(b)

87 0

80 k

g(1

91 9

75 lb

)13

0 62

0 kg

(287

950

lb)

(c)

(b)

86 1

70 k

g(1

89 9

75 lb

)12

9 26

0 kg

(284

975

lb)

(c)

(b)

108

850

kg(2

39 9

75 lb

)16

3 27

0 kg

(359

950

lb)

97 4

10 k

g(2

14 7

50 lb

)14

6 11

0 kg

(322

125

lb)

37.8

%M

AC

(a)

35.8

3 %

MA

C(a

)

41 %

MA

C(a

)

43 %

MA

C(a

)

WV

008

WV

009

577

000

kg(1

272

075

lb)

512

000

kg(1

128

775

lb)

40 1

90 k

g(8

8 60

0 lb

)

39 7

20 k

g(8

7 57

5 lb

)

70 5

90 k

g(1

55 6

25 lb

)

66 6

90 k

g(1

47 0

25 lb

)

41 %

MA

C(a

)

43 %

MA

C(a

)

562

000

kg(1

239

000

lb)

106

920

kg(2

35 7

25 lb

)16

0 38

0 kg

(353

575

lb)

37.5

%M

AC

(a)

43 %

MA

C(a

)

39 8

30 k

g(8

7 80

0 lb

)69

430

kg

(153

075

lb)

43 %

MA

C(a

)

91 7

00 k

g(2

02 1

75 lb

)13

7 55

0 kg

(303

250

lb)

34.6

5 %

MA

C(a

)

43 %

MA

C(a

)W

V01

048

2 00

0 kg

(1 0

62 6

25 lb

)39

680

kg

(87

500

lb)

65 0

70 k

g(1

43 4

50 lb

)

43 %

MA

C(a

)

108

850

kg(2

39 9

75 lb

)16

3 27

0 kg

(359

950

lb)

107

720

kg(2

37 4

75 lb

)16

1 57

0 kg

(356

200

lb)

37.8

%M

AC

(a)

37.8

%M

AC

(a)

41 %

MA

C(a

)

41 %

MA

C(a

)

WV

011

WV

012

577

000

kg(1

272

075

lb)

571

000

kg(1

258

850

lb)

40 1

90 k

g(8

8 60

0 lb

)

39 7

80 k

g(8

7 70

0 lb

)

70 5

90 k

g(1

55 6

25 lb

)

69 8

50 k

g(1

54 0

00 lb

)

41 %

MA

C(a

)

41 %

MA

C(a

)

(a)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T M

RW

(b)

BR

AK

ED

WIN

G G

EA

R(c

) B

RA

KE

D B

OD

Y G

EA

R

L_AC_070300_1_0060102_01_02

Maximum Pavement Loads(Sheet 2 of 2)

FIGURE-7-3-0-991-006-A01

7-3-0Page 3

Dec 01/16


7-4-0 Landing Gear Loading on Pavement

**ON A/C A380-800

Landing Gear Loading on Pavement

1. This section provides data about the landing gear loading on pavement.The MLG loading on pavement graphs are given for the weight variants that produce (at the MRWand maximum aft CG) the lowest MLG load and the highest MLG load for each type of aircraft.

2. MLG Loading on PavementExample, see FIGURE 7-4-0-991-001-A (Sheet 1), calculation of the total weight on the MLG for:- An aircraft with a MRW of 482 000 kg (1 062 625 lb),- The aircraft gross weight is 420 000 kg (925 950 lb),- A percentage of weight on the MLG of 95.1% (percentage of weight on the MLG at MRW and

maximum aft CG).The total weight on the MLG group is 399 530 kg (880 800 lb).

3. Wing Gear and Body Gear Loading on PavementThe MLG group consists of two wing gears (4-wheel bogies) plus two body gears (6-wheel bogies).

Example, see FIGURE 7-4-0-991-001-A (Sheet 2), calculation of the total weight on the MLG for:- An aircraft with a MRW of 482 000 kg (1 062 625 lb),- The aircraft gross weight is 420 000 kg (925 950 lb).The load on the two wing gears is 159 810 kg (352 325 lb) and the load on the two body gears is239 720 kg (528 475 lb).The total weight on the MLG group is 399 530 kg (880 800 lb).

NOTE : The CG in the figure title is the CG used for ACN/LCN calculation.

7-4-0Page 1

Dec 01/16


**ON A/C A380-800

100989694929088260270280290300310320330340350360370380390400410420430440450460470480490500510520530540550560570580590600

260270280290300310320330340350360370380390400410420430440450460470480490500510520530540550560570580590600

30 35 40 45 50 55

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1 00

0 kg

)

(x 1

000

kg)

PERCENTAGE OF WEIGHT ON MAIN GEAR

PERCENTAGE MAC

600

650

700

750

800

850

900

950

1 000

1 050

1 100

1 150

1 200

1 250

1 300

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

CG FOR ACN/LCNCALCULATION

43% MAC

MZFW

TAKE OFF

MLW

MTOW − 480 000 kg

LANDING

34.65% MAC

L_AC_070400_1_0010101_01_01

Landing Gear Loading on PavementWV010, MRW 482 000 kg, CG 43% (Sheet 1 of 2)

FIGURE-7-4-0-991-001-A01

7-4-0Page 2

Dec 01/16


**ON A/C A380-800

100

120

140

160

180

200

220

240

260

280

300

320

340 26

028

030

032

034

036

038

040

042

044

046

048

050

052

054

056

058

060

0

LOAD ON CENTER GEARS OR LOAD ON WING GEARS (x 1 000 kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T (

x 1

000

kg)

600

700

800

900

1 00

01

100

1 20

01

300

(x 1

000

lb)

300

400

500

600

700

(x 1 000 lb)

WIN

G G

EA

RS

BO

DY

GE

AR

S

L_AC_070400_1_0010102_01_01


FIGURE-7-4-0-991-001-A01

7-4-0Page 3

Dec 01/16


**ON A/C A380-800

100989694929088260270280290300310320330340350360370380390400410420430440450460470480490500510520530540550560570580590600

260270280290300310320330340350360370380390400410420430440450460470480490500510520530540550560570580590600

30 35 40 45 50 55

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1 00

0 kg

)

(x 1

000

kg)

PERCENTAGE OF WEIGHT ON MAIN GEAR

PERCENTAGE MAC

600

650

700

750

800

850

900

950

1 000

1 050

1 100

1 150

1 200

1 250

1 300

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

37.8% MAC

MTOW − 575 000 kgCG FOR ACN/LCN

CALCULATION41% MAC

MLW

MZFW

TAKE OFF

LANDING

L_AC_070400_1_0020101_01_00


FIGURE-7-4-0-991-002-A01

7-4-0Page 4

Dec 01/16


**ON A/C A380-800

100

120

140

160

180

200

220

240

260

280

300

320

340 26

028

030

032

034

036

038

040

042

044

046

048

050

052

054

056

058

060

0

LOAD ON CENTER GEARS OR LOAD ON WING GEARS (x 1 000 kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T (

x 1

000

kg)

600

700

800

900

1 00

01

100

1 20

01

300

(x 1

000

lb)

300

400

500

600

700

(x 1 000 lb)

BO

DY

GE

AR

S

WIN

G G

EA

RS

L_AC_070400_1_0020102_01_00


FIGURE-7-4-0-991-002-A01

7-4-0Page 5

Dec 01/16


7-5-0 Flexible Pavement Requirements - US Army Corps of Engineers Design Method

**ON A/C A380-800

Flexible Pavement Requirements - US Army Corps of Engineers Design Method

1. This section provides data about the flexible pavement requirements.The flexible pavement requirements graphs are given at standard tire pressure for the weight variantsthat produce (at the MRW and maximum aft CG) the lowest MLG and the highest MLG load of eachtype of aircraft.They are calculated with the US Army Corps of Engineers Design Method.To find a flexible pavement thickness, you must know the Subgrade Strength (CBR), the annualdeparture level and the weight on one MLG.The line that shows 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).The procedure that follows is used to develop flexible pavement design curves:- With the scale for pavement thickness at the bottom and the scale for CBR at the top, a random

line is made to show 10 000 coverages,- A plot is then made of the incremental values of the weight on the MLG,- Annual departure lines are made based on the load lines of the weight on the MLG that is shown

on the graph.

Example, see FIGURE 7-5-0-991-001-A (Sheet 1), calculation of the thickness of the flexiblepavement for Wing Landing Gear:- An aircraft with a MRW of 482 000 kg (1 062 625 lb),- A ”CBR” value of 10,- An annual departure level of 3 000,- The load on one WLG of 75 000 kg (165 350 lb).The required flexible pavement thickness is 58.7 cm (23 in).

Example, see FIGURE 7-5-0-991-001-A (Sheet 2), calculation of the thickness of the flexiblepavement for Body Landing Gear:- An aircraft with a MRW of 482 000 kg (1 062 625 lb),- A ”CBR” value of 10,- An annual departure level of 3 000,- The load on one BLG of 115 000 kg (253 525 lb).The required flexible pavement thickness is 57.8 cm (23 in).

NOTE : The CG in the figure title is the CG used for ACN calculation.

7-5-0Page 1

Dec 01/16


**ON A/C A380-800

10 000 COVERAGES USED

SUBGRADE STRENGTH − CBR

8060403020151063

8060403020151063

FLEXIBLE PAVEMENT THICKNESS

1 400 x 530 R23 40PR TIRES

TIRE PRESSURE CONSTANT AT 15 bar (218 psi)

10 15 20 30 40 60 80 100 120 150 180

FOR ACN CALCULATIONS

(cm)

(in)

WEIGHT ON ONE WING LANDING GEAR91 700 kg (202 175 lb)

60 000 kg (132 275 lb)45 000 kg (99 200 lb)30 000 kg (66 150 lb)

75 000 kg (165 350 lb)

ALPHA FACTOR = 0.8

1 2003 0006 00015 000

ANNUAL DEPARTURES*

*20 YEAR PAVEMENT LIFE25 000

MAXIMUM POSSIBLE WINGLANDING GEAR LOAD ATMAXIMUM RAMP WEIGHTAND AFT CG

L_AC_070500_1_0010101_01_01

Flexible Pavement RequirementsWV010, MRW 482 000 kg, CG 43% - Wing Landing Gear (Sheet 1 of 2)

FIGURE-7-5-0-991-001-A01

7-5-0Page 2

Dec 01/16


**ON A/C A380-800


MAXIMUM POSSIBLE BODYLANDING GEAR LOAD ATMAXIMUM RAMP WEIGHT


8060403020151063

8060403020151063


1 400 x 530 R23 40PR TIRES


10 15 20 30 40 60 80 100 120 150 180

FOR ACN CALCULATIONS

AND AFT CG

(cm)

(in)

1 2003 0006 00015 000

ANNUAL DEPARTURES*


WEIGHT ON ONE BODY LANDING GEAR137 550 kg (303 250 lb)

100 000 kg (220 450 lb)85 000 kg (187 400 lb)70 000 kg (154 325 lb)

115 000 kg (253 525 lb)

ALPHA FACTOR = 0.72

L_AC_070500_1_0010102_01_01

Flexible Pavement RequirementsWV010, MRW 482 000 kg, CG 43% - Body Landing Gear (Sheet 2 of 2)

FIGURE-7-5-0-991-001-A01

7-5-0Page 3

Dec 01/16


**ON A/C A380-800


MAXIMUM POSSIBLE WINGLANDING GEAR LOAD ATMAXIMUM RAMP WEIGHT


8060403020151063

8060403020151063


1 400 x 530 R23 40PR TIRES


10 15 20 30 40 60 80 100 120 150 180

FOR ACN CALCULATIONSALPHA FACTOR = 0.8

AND AFT CG

1 2003 0006 00015 000

ANNUAL DEPARTURES*


WEIGHT ON ONE WING LANDING GEAR108 850 kg (239 975 lb)

70 000 kg (154 325 lb)55 000 kg (121 250 lb)40 000 kg (88 175 lb)

85 000 kg (187 400 lb)

(cm)

(in)

L_AC_070500_1_0020101_01_00

Flexible Pavement RequirementsWV008, MRW 577 000 kg, CG 41% - Wing Landing Gear (Sheet 1 of 2)

FIGURE-7-5-0-991-002-A01

7-5-0Page 4

Dec 01/16


**ON A/C A380-800



8060403020151063

8060403020151063

(cm)


1 400 x 530 R23 40PR TIRES


10 15 20 30 40 60 80 100 120 150 180

(in)

FOR ACN CALCULATIONSALPHA FACTOR = 0.72

1 2003 0006 00015 000

ANNUAL DEPARTURES*


MAXIMUM POSSIBLE BODYLANDING GEAR LOAD ATMAXIMUM RAMP WEIGHTAND AFT CG

WEIGHT ON ONE BODY LANDING GEAR163 270 kg (359 950 lb)

130 000 kg (286 600 lb)115 000 kg (253 525 lb)100 000 kg (220 450 lb)

145 000 kg (319 675 lb)

L_AC_070500_1_0020102_01_00

Flexible Pavement RequirementsWV008, MRW 577 000 kg, CG 41% - Body Landing Gear (Sheet 2 of 2)

FIGURE-7-5-0-991-002-A01

7-5-0Page 5

Dec 01/16


7-6-0 Flexible Pavement Requirements - LCN Conversion

**ON A/C A380-800

Flexible Pavement Requirements - LCN Conversion

1. The Load Classification Number (LCN) curves are no longer provided in section 07-06-00 since theLCN system for reporting pavement strength is obsolete, having been replaced by the ICAOrecommended ACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

7-6-0Page 1

Dec 01/16


7-7-0 Rigid Pavement Requirements - Portland Cement Association Design Method

**ON A/C A380-800

Rigid Pavement Requirements - Portland Cement Association Design Method

1. This section provides data about the rigid pavement requirements for the PCA (Portland CementAssociation) design method.The rigid pavement requirement graphs are given at standard tire pressure for the weight variantsproducing (at the MRW and maximum aft CG) the lowest MLG load and the highest MLG load foreach type of aircraft.They are calculated with the PCA design method.To find a rigid pavement thickness, you must know the Subgrade Modulus (k), the permitted workingstress and the weight on one MLG.The procedure that follows is used to develop rigid pavement design curves:- With the scale for pavement thickness on the left and the scale for permitted working stress on

the right, a random load line is made. This represents the MLG maximum weight to be shown,- A plot is then made of all values of the subgrade modulus (k values),- More load lines for the incremental values of the weight on the MLG are made based on the

curve for k = 80 MN/m3, which is already shown on the graph.

Example, see FIGURE 7-7-0-991-001-A (Sheet 1), calculation of the thickness of the rigid pavementfor the WLG:- An aircraft with a MRW of 482 000 kg (1 062 625 lb),- A k value of 80 MN/m3 (300 lbf/in3),- A permitted working stress of 38.67 kg/cm2 (550 lb/in2),- The load on one MLG is 75 000 kg (165 350 lb).The required rigid pavement thickness is 227 mm (9 in).

Example, see FIGURE 7-7-0-991-001-A (Sheet 2), calculation of the thickness of the rigid pavementfor the BLG:- An aircraft with a MRW of 482 000 kg (1 062 625 lb),- A k value of 80 MN/m3 (300 lbf/in3),- A permitted working stress of 38.67 kg/cm2 (550 lb/in2),- The load on one MLG is 115 000 kg (253 525 lb).The required rigid pavement thickness is 231 mm (9 in).


7-7-0Page 1

Dec 01/16


**ON A/C A380-800

1 400 x 530 R23 40PR TIRESTIRE PRESSURE CONSTANT AT 15 bar (218 psi)

100

200

300

400

500

600

700

800

90015

14

13

12

11

10

9

7

8

FOR LOADS LESS THAN MAXIMUM,EXACT.LINE AND ANY VALUES FOR k ARETHE MAXIMUM LOAD REFERENCETHE VALUES OBTAINED BY USINGNOTE:

THE CURVES ARE EXACT FOR k =80 MN/m³ BUT DEVIATE SLIGHTLYFOR ANY OTHER VALUES OF k.

PDILB" PORTLAND CEMENTPAVEMENT DESIGN − PROGRAMPROGRAM FOR AIRPORTPAVEMENTS" AND "COMPUTER"DESIGN OF CONCRETE AIRPORTREFERENCE:

ASSOCIATION.

k = 150 MN/m³k = 80 MN/m³k = 40 MN/m³k = 20 MN/m³

45 000 kg60 000 kg75 000 kg91 700 kg

LANDING GEARWEIGHT ON ONE WING

30 000 kg

(165 350 lb)(132 275 lb)

(99 200 lb)(66 150 lb)

GEAR LOAD AT MAXIMUMMAXIMUM POSSIBLE WING

RAMP WEIGHT AND AFT CG

(202 175 lb)

60

50

40

30

20

10

38

36

34

32

30

28

26

24

22

20

18(k

g/cm

²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

(lb/in

²)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S(c

m)

(in)

L_AC_070700_1_0010101_01_01

Rigid Pavement RequirementsWV010, MRW 482 000 kg, CG 43% - WLG (Sheet 1 of 2)

FIGURE-7-7-0-991-001-A01

7-7-0Page 2

Dec 01/16


**ON A/C A380-800


100

200

300

400

500

600

700

800

90015

14

13

12

11

10

9

7

8




ASSOCIATION.


85 000 kg100 000 kg115 000 kg137 550 kgLANDING GEARWEIGHT ON ONE BODY

70 000 kg

(253 525 lb)(220 450 lb)(187 400 lb)(154 325 lb)

(303 250 lb)

60

50

40

30

20

10

38

36

34

32

30

28

26

24

22

20

18(k

g/cm

²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

(lb/in

²)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S(c

m)

(in)

GEAR LOAD AT MAXIMUMMAXIMUM POSSIBLE BODY


L_AC_070700_1_0010102_01_01

Rigid Pavement RequirementsWV010, MRW 482 000 kg, CG 43% - BLG (Sheet 2 of 2)

FIGURE-7-7-0-991-001-A01

7-7-0Page 3

Dec 01/16


**ON A/C A380-800


60

50

40

30

20

10

100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8

(kg/

cm²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

(lb/in

²)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S(c

m)

(in)




ASSOCIATION.

55 000 kg70 000 kg85 000 kg

108 850 kg (239 975 lb)LANDING GEARWEIGHT ON ONE WING

40 000 kg


GEAR LOAD AT MAXIMUMMAXIMUM POSSIBLE WING


(187 400 lb)(154 325 lb)(121 250 lb)

(88 175 lb)

L_AC_070700_1_0020101_01_00

Rigid Pavement RequirementsWV008, MRW 577 000 kg, CG 41% - WLG (Sheet 1 of 2)

FIGURE-7-7-0-991-002-A01

7-7-0Page 4

Dec 01/16


**ON A/C A380-800


60

50

40

30

20

10

100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8

(kg/

cm²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

(lb/in

²)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S(c

m)

(in)




ASSOCIATION.


115 000 kg (253 525 lb)130 000 kg (286 600 lb)145 000 kg (319 675 lb)163 270 kg (359 950 lb)LANDING GEARWEIGHT ON ONE BODY

100 000 kg (220 450 lb)

GEAR LOAD AT MAXIMUMMAXIMUM POSSIBLE BODY


L_AC_070700_1_0020102_01_00

Rigid Pavement RequirementsWV008, MRW 577 000 kg, CG 41% - BLG (Sheet 2 of 2)

FIGURE-7-7-0-991-002-A01

7-7-0Page 5

Dec 01/16


7-8-0 Rigid Pavement Requirements - LCN Conversion

**ON A/C A380-800

Rigid Pavement Requirements - LCN Conversion

1. The Load Classification Number (LCN) curves are no longer provided in section 07-08-00 since theLCN system for reporting pavement strength is obsolete, having been replaced by the ICAOrecommended ACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

7-8-0Page 1

Dec 01/16


7-9-0 ACN/PCN Reporting System - Flexible and Rigid Pavements

**ON A/C A380-800

ACN/PCN Reporting System - Flexible and Rigid Pavements

1. This section provides data about the Aircraft Classification Number (ACN) for an aircraft grossweight in relation to a subgrade strength value for flexible and rigid pavement.The flexible and rigid pavement requirements graphs are given at standard tire pressure for theweight variants producing (at the MRW and maximum aft CG) the lowest MLG load and the highestMLG load for each type of aircraft.To find the ACN of an aircraft on flexible and rigid pavement, you must know the aircraft grossweight and the subgrade strength.

NOTE : An aircraft with an ACN equal to or less than the reported PCN can operate on thatpavement, subject to any limitation on the tire pressure.(Ref: ICAO Aerodrome Design Manual, Part 3, Chapter 1, Second Edition 1983).

Example, see FIGURE 7-9-0-991-002-A (Sheet 1), calculation of the ACN for flexible pavement for:- An aircraft with a MRW of 482 000 kg (1 062 625 lb),- An aircraft gross weight of 420 000 kg (925 950 lb),- A medium subgrade strength (code B).The ACN for flexible pavement is 44.

Example, see FIGURE 7-9-0-991-002-A (Sheet 2), calculation of the ACN for rigid pavement for:- An aircraft with a MRW of 482 000 kg (1 062 625 lb),- An aircraft gross weight of 420 000 kg (925 950 lb),- A medium subgrade strength (code B).The ACN for rigid pavement is 45.

2. Aircraft Classification Number - ACN tableThe table in FIGURE 7-9-0-991-001-A provide ACN data in tabular format similar to the one used byICAO in the ”Aerodrome Design Manual Part 3, Pavements - Edition 1983” for all the operationalweight variants of the aircraft.As an approximation, use a linear interpolation in order to get the ACN at the required operatingweight using the following equation:- ACN = ACN min + (ACN max - ACN min) x (Operating weight - 300 000 kg)/(MRW - 300 000

kg)As an approximation, also use a linear interpolation in order to get the aircraft weight at thepavement PCN using the following equation:- Operating weight = 300 000 kg + (MRW - 300 000 kg) x (PCN - ACN min)/(ACN max - ACN

min)With ACN max = ACN calculated at the MRW in the table and with ACN min = ACN calculated at300 000 kg.

7-9-0Page 1

Dec 01/16



7-9-0Page 2

Dec 01/16


**ON A/C A380-800

WV000

ALL UPMASS

(kg)

LOAD ONONE MAINGEAR LEG

(%)

TIREPRESSURE

(MPa)

562 00019 (WLG)

28.5 (BLG)

300 00019 (WLG)

28.5 (BLG)

1.50

5655

ACN FORRIGID PAVEMENT

SUBGRADES−MN/m³

ACN FORFLEXIBLE PAVEMENT

SUBGRADES−CBR

HIGH150

MEDIUM80

LOW40

ULTRA−LOW20 15

HIGH10

MEDIUM6

LOW3

ULTRA−LOW

6668

7888

91110

5956

6462

7575

102106

27 2929

3434

3942

2725

2927

31 4029 30 40

512 00019 (WLG)

28.5 (BLG)

300 00019 (WLG)

28.5 (BLG)

1.40

4948

5757

6875

7994

5149

5654

6665

9092

26 2928

3333

3842

2725

2827

31 4028 30 40

571 00018.9 (WLG)28.3 (BLG)

300 00018.9 (WLG)28.3 (BLG)

1.50

5756

6769

7989

91111

5957

6463

7676

104107

27 2929

3334

3842

2725

2826

31 4028 30 39

512 00019 (WLG)

28.5 (BLG)

300 00019 (WLG)

28.5 (BLG)

1.40

4948

5757

6875

7994

5149

5654

6665

9092

26 2928

3333

3842

2725

2827

31 4028 30 40

562 00019 (WLG)

28.5 (BLG)

300 00019 (WLG)

28.5 (BLG)

1.50

5655

6668

7888

91110

5956

6462

7575

102106

27 2929

3434

3942

2725

2927

31 4029 30 40

562 00019 (WLG)

28.5 (BLG)

300 00019 (WLG)

28.5 (BLG)

1.50

5655

6668

7888

91110

5956

6462

7575

102106

27 2929

3434

3942

2725

2927

31 4029 30 40

575 00018.9 (WLG)28.3 (BLG)18.9 (WLG)28.3 (BLG)

1.50

5856

6769

8090

92113

6057

6563

7777

105108

27 2929

3334

3842

2725

2826

31 4028 30 39

19 (WLG)28.5 (BLG)19 (WLG)

28.5 (BLG)

1.40

4646

5454

6470

7589

4947

5351

6261

8587

26 2928

3333

3842

2725

2827

31 4028 30 40

18.9 (WLG)28.3 (BLG)18.9 (WLG)28.3 (BLG)

1.50

5856

6870

8091

93113

6058

6564

7777

105108

27 2929

3334

3842

2725

2826

31 4028 30 39

19 (WLG)28.5 (BLG)19 (WLG)

28.5 (BLG)

1.50

5050

5859

6976

8096

5249

5654

6665

9092

27 2929

3434

3942

2725

2927

31 4029 30 40

WEIGHTVARIANT

WV001

WV002

WV003

WV004

WV005

WV006

WV007

WV008

WV009300 000

512 000

300 000

577 000

300 000

300 000

492 000

L_AC_070900_1_0010101_01_02

Aircraft Classification NumberACN Table (Sheet 1 of 2)

FIGURE-7-9-0-991-001-A01

7-9-0Page 3

Dec 01/16


**ON A/C A380-800

WV010

ALL UPMASS

(kg)

LOAD ONONE MAINGEAR LEG

(%)

TIREPRESSURE

(MPa)

482 00019 (WLG)

28.5 (BLG)

300 00019 (WLG)

28.5 (BLG)

1.50

4746

ACN FORRIGID PAVEMENT

SUBGRADES−MN/m³

ACN FORFLEXIBLE PAVEMENT

SUBGRADES−CBR

HIGH150

MEDIUM80

LOW40

ULTRA−LOW20 15

HIGH10

MEDIUM6

LOW3

ULTRA−LOW

5454

6369

7487

4845

5250

6059

8384

27 2929

3434

3942

2725

2927

31 4029 30 40

WEIGHTVARIANT

WV011577 000

18.9 (WLG)28.3 (BLG)

300 00018.9 (WLG)28.3 (BLG)

1.50

5856

6870

8091

93113

6058

6564

7777

105108

27 2929

3334

3842

2725

2826

31 4028 30 39

WV012571 000

18.9 (WLG)28.3 (BLG)

300 00018.9 (WLG)28.3 (BLG)

1.50

5756

6769

7989

91111

5957

6463

7676

104107

27 2929

3334

3842

2725

2826

31 4028 30 39

L_AC_070900_1_0010102_01_00

Aircraft Classification NumberACN Table (Sheet 2 of 2)

FIGURE-7-9-0-991-001-A01

7-9-0Page 4

Dec 01/16


**ON A/C A380-800

2030405060708090100

110

120

600

700

800

900

1 00

01

100

1 20

01

300

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

5 ba

r (2

18 p

si)

1 40

0 x

530

R23

40P

R T

IRE

SS

EE

SE

CT

ION

7−

4−0.

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

D −

CB

R

3 (

ULT

RA

LO

W)

SU

BG

RA

DE

ST

RE

NG

TH

C −

CB

R

6 (

LOW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

ALP

HA

FA

CT

OR

= 0

.72

FO

R B

LGA

LPH

A F

AC

TO

R =

0.8

FO

R W

LG

250

300

350

400

450

500

550

600

(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

AIRCRAFT CLASSIFICATION NUMBER (ACN)

L_AC_070900_1_0020101_01_01

Aircraft Classification NumberFlexible Pavement - WV010, MRW 482 000 kg, CG 43% (Sheet 1 of 2)

FIGURE-7-9-0-991-002-A01

7-9-0Page 5

Dec 01/16


**ON A/C A380-800

250

2030405060708090100

110

120

600

700

800

900

1 00

01

100

1 20

0

300

350

400

1 30

0

450

500

550

600

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

5 ba

r (2

18 p

si)

1 40

0 x

530

R23

40P

R T

IRE

SS

EE

SE

CT

ION

7−

4−0.

(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

D −

k =

20

MN

/m³

(ULT

RA

LO

W)

SU

BG

RA

DE

ST

RE

NG

TH

C −

k =

40

MN

/m³

(LO

W)

B −

k =

80

MN

/m³

(ME

DIU

M)

A −

k =

150

MN

/m³

(HIG

H)


L_AC_070900_1_0020102_01_01

Aircraft Classification NumberRigid Pavement - WV010, MRW 482 000 kg, CG 43% (Sheet 2 of 2)

FIGURE-7-9-0-991-002-A01

7-9-0Page 6

Dec 01/16


**ON A/C A380-800

2030405060708090100

110

120

600

700

800

900

1 00

01

100

1 20

01

300

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

5 ba

r (2

18 p

si)

1 40

0 x

530

R23

40P

R T

IRE

SS

EE

SE

CT

ION

7−

4−0.

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

D −

CB

R

3 (

ULT

RA

LO

W)

SU

BG

RA

DE

ST

RE

NG

TH

C −

CB

R

6 (

LOW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

ALP

HA

FA

CT

OR

= 0

.72

FO

R B

LGA

LPH

A F

AC

TO

R =

0.8

FO

R W

LG

250

300

350

400

450

500

550

600

(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T


L_AC_070900_1_0030101_01_00

Aircraft Classification NumberFlexible Pavement - WV008, MRW 577 000 kg, CG 41% (Sheet 1 of 2)

FIGURE-7-9-0-991-003-A01

7-9-0Page 7

Dec 01/16


**ON A/C A380-800

250

2030405060708090100

110

120

600

700

800

900

1 00

01

100

1 20

0

300

350

400

1 30

0

450

500

550

600

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

5 ba

r (2

18 p

si)

1 40

0 x

530

R23

40P

R T

IRE

SS

EE

SE

CT

ION

7−

4−0.

(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

D −

k =

20

MN

/m³

(ULT

RA

LO

W)

SU

BG

RA

DE

ST

RE

NG

TH

C −

k =

40

MN

/m³

(LO

W)

B −

k =

80

MN

/m³

(ME

DIU

M)

A −

k =

150

MN

/m³

(HIG

H)


L_AC_070900_1_0030102_01_00

Aircraft Classification NumberRigid Pavement - WV008, MRW 577 000 kg, CG 41% (Sheet 2 of 2)

FIGURE-7-9-0-991-003-A01

7-9-0Page 8

Dec 01/16


SCALED DRAWINGS

8-0-0 SCALED DRAWINGS

**ON A/C A380-800

Scaled Drawings

1. This section provides the scaled drawings.

NOTE : When printing this drawing, make sure to adjust for proper scaling.

8-0-0Page 1

Dec 01/16


**ON A/C A380-800

DB1A

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS

NOTE: WHEN PRINTING THIS DRAWING, MAKE SURE TO ADJUST FOR PROPER SCALING.

L_AC_080000_1_0010101_01_01

Scaled DrawingFIGURE-8-0-0-991-001-A01

8-0-0Page 2

Dec 01/16


AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 AIRCRAFT RESCUE AND FIRE FIGHTING

**ON A/C A380-800

Aircraft Rescue and Fire Fighting

1. Aircraft Rescue and Fire Fighting ChartsThis section provides data related to aircraft rescue and fire fighting.The figures contained in this section are the figures that are in the Aircraft Rescue and Fire FightingCharts poster available on AIRBUSWorld and the Airbus website.

10-0-0Page 1

Dec 01/16


**ON A/C A380-800

DE

CE

MB

ER

201

5

L_AC_100000_1_0010101_01_02

Front PageFIGURE-10-0-0-991-001-A01

10-0-0Page 2

Dec 01/16


**ON A/C A380-800

L_AC_100000_1_0020101_01_03

Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-0-0-991-002-A01

10-0-0Page 3

Dec 01/16


**ON A/C A380-800

AC

CE

SS

VIA

AC

CE

SS

DO

OR

131

CF

Z

AC

CE

SS

DO

OR

811

VIA

FW

D C

AR

GO

DO

OR

AC

CE

SS

DO

OR

132

CF

ZV

IA F

WD

CA

RG

O D

OO

RB

AT

−2

AA

CC

ES

S D

OO

R 2

72A

FX

VIA

UP

PE

R D

EC

K

BA

T−

1

BA

T−

ES

S

BA

T−

AP

UA

CC

ES

S V

IA B

ULK

CA

RG

O D

OO

R 8

23

DIV

IDE

R N

ET

AC

CE

SS

VIA

AF

T C

AR

GO

DO

OR

B

ELT

FR

93F

R92

FR

17F

R86

FR

91

FR

5

FR

93

FR

90 A

C

DE

BC

E

FR

91

FR

92

FR

90

FR

93

D

ELT

AN

TE

NN

A

Z12

0

Z16

0F

R21

Z26

0

L_AC_100000_1_0170101_01_01

Batteries Location and AccessFIGURE-10-0-0-991-017-A01

10-0-0Page 4

Dec 01/16


**ON A/C A380-800

L_AC_100000_1_0160101_01_00

Crew Rest Compartments LocationFIGURE-10-0-0-991-016-A01

10-0-0Page 5

Dec 01/16


**ON A/C A380-800

L_AC_100000_1_0140101_01_00

Wheel/Brake OverheatWheel Safety Area (Sheet 1 of 2)

FIGURE-10-0-0-991-014-A01

10-0-0Page 6

Dec 01/16


**ON A/C A380-800

L_AC_100000_1_0140102_01_00

Wheel/Brake OverheatRecommendations (Sheet 2 of 2)

FIGURE-10-0-0-991-014-A01

10-0-0Page 7

Dec 01/16


**ON A/C A380-800

L_AC_100000_1_0030101_01_01

Composite Materials LocationFIGURE-10-0-0-991-003-A01

10-0-0Page 8

Dec 01/16


**ON A/C A380-800

A

AB

C

B

C

L_AC_100000_1_0040101_01_01

Landing GearGround Lock Safety DevicesFIGURE-10-0-0-991-004-A01

10-0-0Page 9

Dec 01/16


**ON A/C A380-800

− 3

− 6

− 9

− 1

2

− 1

5

− 1

8G

RID

EQ

UA

LS 1

m (

3.28

ft)

IN R

EA

LIT

Y

MA

IN D

EC

K D

UA

L−LA

NE

CO

CK

PIT

ES

CA

PE

RO

PE

SLI

DE

/RA

FT

UP

PE

R D

EC

K D

UA

L−LA

NE

SLI

DE

/RA

FT

OV

ER

WIN

G D

UA

L−LA

NE

RA

MP

/SLI

DE

UP

PE

R D

EC

K D

UA

L−LA

NE

SLI

DE

/RA

FT

MA

IN D

EC

K D

UA

L−LA

NE

SLI

DE

/RA

FT

MA

IN D

EC

K D

UA

L−LA

NE

SLI

DE

/RA

FT

UP

PE

R D

EC

K D

UA

L−LA

NE

SLI

DE

/RA

FT

NO

TE

:−

LH

SH

OW

N, R

H S

YM

ME

TR

ICA

L.−

DIM

EN

SIO

NS

AR

E A

PP

RO

XIM

AT

E.

− T

HE

RA

MP

S/S

LID

ES

AT

DO

OR

S M

3L A

ND

M3R

DO

NO

T H

AV

E R

AF

T C

AP

AB

ILIT

Y.

EM

ER

GE

NC

YD

ES

CE

NT

TH

RO

UG

HT

HE

WIN

DO

W O

PE

NIN

GW

ITH

TH

E E

SC

AP

E R

OP

E

L_AC_100000_1_0050101_01_04

Emergency Evacuation DevicesFIGURE-10-0-0-991-005-A01

10-0-0Page 10

Dec 01/16


**ON A/C A380-800

L_AC_100000_1_0060101_01_02

Pax/Crew Doors and Emergency ExitsFIGURE-10-0-0-991-006-A01

10-0-0Page 11

Dec 01/16


**ON A/C A380-800

132B

R19

9DR

/

5070

JE1

6336

MJ

197C

B

L_AC_100000_1_0070101_01_02

Cargo DoorsFWD and AFT Lower Deck Cargo Doors

FIGURE-10-0-0-991-007-A01

10-0-0Page 12

Dec 01/16


**ON A/C A380-800

D

TO

GA

FLX CL 0M C T T H RA

TO

GA

FLX C

L 0M C T T H RA

43

21

1125

VU

OF

F

ON

OF

F

ON

EN

GM

AS

TE

R

OF

F

ON

OF

F

ON

1F

AU

LT

FIR

E

2F

AU

LT

FIR

E

3F

AU

LT

FIR

E

4F

AU

LT

FIR

E

AP

U

CO

CK

PIT

AV

NC

S V

EN

TE

LT

HO

RN

RE

SE

TLI

GH

T T

ES

T

FLT

INT

SV

CE

INT

FIR

E

CA

LLA

PU

SH

UT

OF

F

CA

BIN

PR

ES

S12

15V

M

CA

BIN

ALT

CA

BIN

V/S

A U T O

INC

DE

CA U T O

DN

UP D

ITC

HIN

G

MA

NM

AN

INT

LT

AN

N L

T TE

ST

DIMBR

T

ST

OR

MO

N

OF

F

ST

BY

CO

MP

AS

S

ICE

IND

OF

F

SIG

NS

EM

ER

EX

IT L

T

OF

F

AR

M

ON

OF

F

NO

SM

OK

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ON

OF

F

AU

TO

SE

AT

BE

LTS

OF

F

AU

TO

ON

EN

G

12

34

AN

TI I

CE

ON

FA

ULT

ON

FA

ULT

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FA

ULT

ON

FA

ULT

ON

FA

ULT

ON

FA

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EX

T L

T

NO

SE

T.O

OF

F

TA

XI

LAN

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OF

F

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Y T

UR

N O

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& C

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OF

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GO

N

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N

OF

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L V

ALV

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FA

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OF

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ER

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OF

F

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MP

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L15

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T

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L V

ALV

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OF

F

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ULT

FW

D

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L V

ALV

ES

525

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MP

RE

GU

L15

OF

F

FA

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OF

F

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NT

AV

NC

SA

VN

CS

EX

TR

AC

T

A U T O

CA

B F

AN

SC

OO

LG

SM

OK

E

OF

F

FA

ULT

OF

FO

VR

D

FA

ULT

A U T O

EN

GM

AN

ST

AR

T

1

23

4

ON

ON

ON

ON

WIP

ER

SLO

W

FA

ST

OF

FR

AIN

RP

LNT

B E

C

BC

DE

HI L

VL

HI L

VL

AP

U E

ME

RG

EN

CY

INC

RE

AS

E

DE

CR

EA

SE

PR

ES

ELE

CT

PR

ES

ELE

CT

(P

FQ

)

OV

ER

FLO

WF

AU

LT

SH

UT

OF

FT

ES

T

NO

RM

AL

BA

TT

ER

Y

PO

WE

R S

UP

PLY

AC

TU

AL

(FO

B)

ST

AT

US

MA

NR

EF

UE

L

XF

R

DE

FU

EL

AU

TO

RE

FU

EL

OF

F

MO

DE

SE

LEC

T

FE

ED

1

FE

ED

1

L O

UT

R

L O

UT

R

R M

ID

OP

EN

SH

UT

R M

ID

R IN

R

R IN

R

TR

IM

TR

IM

L IN

R

L IN

R

L M

ID

L M

ID

R O

UT

RO

PE

N

SH

UT

R O

UT

R

FE

ED

4

FE

ED

4

FE

ED

3

FE

ED

3

FE

ED

2

FE

ED

2

SH

UT

DO

WN

RE

FU

EL/

DE

FU

EL

VA

LVE

S

kg

L_AC_100000_1_0100101_01_01

Control PanelsFIGURE-10-0-0-991-010-A01

10-0-0Page 13

Dec 01/16


**ON A/C A380-800

A

A

FR

112

FR

117

315A

L

315A

R

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**ON A/C A380-800

F1

BF

2B

F1

C1

CP

1R

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U2

U3

5.36

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5.28

5.27

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8.04

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8

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0

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HT

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F1

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5.97

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EN

GIN

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719

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300

000

kg(6

61 3

87 lb

)A

FT

CG

(44

%)

300

000

kg(6

61 3

87 lb

)A

FT

CG

(44

%)

300

000

kg(6

61 3

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FT

CG

(44

%)

C1

C2

C3

8.02

3.30

3.23

26.3

110

.83

10.6

03.

3611

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M5

FT

55.

6118

.41

C2

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