Maintenance Facility Planning

@AIRBUSA380

MAINTENANCE FACILITY PLANNING

MFP

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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: Nov 01/08 Rev: Oct 01/09

@A380MAINTENANCE FACILITY PLANNING

HIGHLIGHTS

Revision No. 8 - Oct 01/09

LOCATIONS CHGCODE

DESCRIPTIONS OF CHANGE

CHAPTER 1

Section 1-3

General Airplane Characteristics Data R ADDED WEIGHT VARIANT WV000 TOWV003DESCRIPTION TITLE UPDATED

Section 1-10

FIGURE Door Clearances - Aft CargoCompartment Doors - A380-800 Models

R

FIGURE Door Clearances - Lower DeckAft Cargo Doors - A380-800F Models

R

FIGURE Door Clearances - Upper DeckCargo Door - A380-800F Models

R

FIGURE Door Clearances - Lower DeckForward Cargo Door - A380-800F Models

R

CHAPTER 2

Section 2-3

Engine Oil Servicing R

FIGURE Ground Service Connections -Engine Oil Servicing - GP 7200 Engines

R

VFG Oil Servicing R

FIGURE Ground Service Connections -VFG Oil Servicing - TRENT 900 Engines

R

FIGURE Ground Service Connections -VFG Oil Servicing - GP 7200 Engines

R

Starter Oil Servicing R

FIGURE Ground Service Connections -Starter Oil Servicing - GP 7200 Engines

R

Section 2-8

Towing R NOTE AMENDED

HIGHLIGHTSPage 1

Oct 01/09


LOCATIONS CHGCODE


FIGURE Ground Towing Requirements -Ground Towing Requirements A380-800Models

R ILLUSTRATION REVISED

FIGURE Ground Towing Requirements -Typical Tow Bar configuration 1


FIGURE Ground Towing Requirements -Typical Tow Bar configuration 2


FIGURE Ground Towing Requirements -Nose Gear Towing Fittings

R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Towing Requirements -Maximum Extension of the NLG ShockAbsorber

N ILLUSTRATION ADDED

Section 2-9

Ground Maneuvering R

FIGURE Turning Radii - Turning Radii(Sheet 1)

R

FIGURE Turning Radii - Turning Radii(Sheet 2)

R

FIGURE 135˚ Turn - Runway to Taxiway- 135˚ Turn - Runway to Taxiway (Sheet1)


FIGURE 135˚ Turn - Runway to Taxiway- 135˚ Turn - Runway to Taxiway (Sheet2)


FIGURE 90˚ Turn - Runway to Taxiway -90˚ Turn - Runway to Taxiway (Sheet 1)


FIGURE 90˚ Turn - Runway to Taxiway -90˚ Turn - Runway to Taxiway (Sheet 2)


FIGURE 180˚ Turn on a Runway - 180˚Turn on a Runway


FIGURE 90˚ Turn - Taxiway to Taxiway- 90˚ Turn - Taxiway to Taxiway (Sheet1)


HIGHLIGHTSPage 2

Oct 01/09


LOCATIONS CHGCODE








Section 2-11

Operating Conditions R

CHAPTER 3

Section 3-1

Airplane Maintenance Jacking R

FIGURE Jacking Points Location -Jacking Points Location


Section 3-14

Power Plant R

FIGURE Fan Cowls - TRENT 900 Engines R

FIGURE Fan Cowls - Engine 1-2-3-4 - GP7200 Engines


FIGURE Fan Exhaust Cowls - Engine 1-4- GP 7200 Engines


FIGURE Thrust Reverser - Engine 2-3 -GP 7200 Engines


HIGHLIGHTSPage 3

Oct 01/09


LIST OF EFFECTIVE CONTENT

Revision No. 8 - Oct 01/09

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 0

Section 0-1

Introduction Jun 01/07

Section 0-2

Alphabetical Index Nov 01/08

Section 0-3

Section Index Nov 01/08

Section 0-4

Glossary Nov 01/08

CHAPTER 1

Section 1-1

Airplane Overall Dimensions and Outline Basic Reference Drawing Jun 01/07

FIGURE Airplane Overall Dimensions and Outline Basic ReferenceDrawing - A380-800 Models

Jun 01/07

FIGURE Airplane Overall Dimensions and Outline Basic ReferenceDrawing - A380-800F Models

Jun 01/07

Section 1-2

Airplane Dimensions Jun 01/07

FIGURE Airplane Dimensions - Airplane Dimensions (Sheet 1) Nov 01/08

FIGURE Airplane Dimensions - Airplane Dimensions (Sheet 2) Jun 01/07

Section 1-3

General Airplane Characteristics Data R Oct 01/09

Section 1-4

Zoning and Access Jun 01/07

FIGURE Aircraft Zoning - Major Zones Jun 01/07

FIGURE Aircraft Zoning - Major Sub-Zones - Zone 100 (Sheet 1) Jun 01/07

FIGURE Aircraft Zoning - Major Sub-Zones - Zone 100 (Sheet 2) Jun 01/07

FIGURE Aircraft Zoning - Major Sub-Zones - Zone 200 Jun 01/07

L.E.C.Page 1

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FIGURE Aircraft Zoning - Major Sub-Zones - Zone 400 - TRENT 900Engines

Jan 31/08

FIGURE Aircraft Zoning - Major Sub-Zones - Zone 400 -- GP 7200Engines

Jan 31/08

FIGURE Aircraft Zoning - Major Sub-Zones - Zone 500/600 Jun 01/07



Section 1-5

Fuselage Frames / Stations Jun 01/07

FIGURE Fuselage Frames/Stations - Sections Identification -A380-800 Models

Jun 01/07

FIGURE Fuselage Frames/Stations - Sections Identification -A380-800F Models

Jun 01/07

FIGURE Fuselage Frames/Stations - Section 11/12 - A380-800Models

Jun 01/07

FIGURE Fuselage Frames/Stations - Section 11/12 - A380-800FModels

Jun 01/07

FIGURE Fuselage Frames/Stations - Section 13 - A380-800 Models Jun 01/07

FIGURE Fuselage Frames/Stations - Section 13 - A380-800F Models Jun 01/07

FIGURE Fuselage Frames/Stations - Section 15/21 - A380-800Models

Jun 01/07

FIGURE Fuselage Frames/Stations - Section 15/21 - A380-800FModels

Jun 01/07

FIGURE Fuselage Frames/Stations - Section 18 - A380-800 Models Jun 01/07

FIGURE Fuselage Frames/Stations - Section 18 - A380-800F Models Jun 01/07

FIGURE Fuselage Frames/Stations - Section 19 Jun 01/07

Section 1-6

Wing Ribs / Stations Jun 01/07

FIGURE Wing Ribs/Stations - Wing Ribs/Stations (Sheet 1) Jun 01/07



L.E.C.Page 2

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Wing Ribs/Stations - Flap Track Positions Jan 31/08

Section 1-7

Center of Gravity Limits Nov 01/08

FIGURE Center of Gravity Limits - MTOW 510000 kg- A380-800Models

Nov 01/08

FIGURE Center of Gravity Limits - MTOW 560000 kg - A380-800Models

Nov 01/08

FIGURE Center of Gravity Limits - MTOW 569000 kg - A380-800Models

Nov 01/08

FIGURE Center of Gravity Limits - MTOW 590000 kg - A380-800FModels

Nov 01/08

FIGURE Center of Gravity Limits - MTOW 600000 kg - A380-800FModels

Nov 01/08

Section 1-8

Airplane Attitude Nov 01/08

FIGURE NLG Shock-Absorber Deflection - NLG Shock-AbsorberDeflection - A380-800 Models

Nov 01/08

FIGURE NLG Shock-Absorber Deflection - NLG Shock-AbsorberDeflection - A380-800F Models

Nov 01/08

FIGURE NLG Tire Deflection 50 % Load - NLG Tire Deflection 50 %Load - A380-800 Models

Nov 01/08

FIGURE NLG Tire Deflection 100 % Load - NLG Tire Deflection 100% Load - A380-800 Models

Nov 01/08

FIGURE NLG Tire Deflection 50 % Load - NLG Tire Deflection 50 %Load - A380-800F Models

Nov 01/08

FIGURE NLG Tire Deflection 100 % Load - NLG Tire Deflection 100% Load - A380-800F Models

Nov 01/08

FIGURE WLG Shock-Absorber Deflection - WLG Shock-AbsorberDeflection - A380-800 Models

Nov 01/08

FIGURE WLG Shock-Absorber Deflection - WLG Shock-AbsorberDeflection - A380-800F Models

Nov 01/08

FIGURE WLG Tire Deflection 25 % Load - WLG Tire Deflection 25% Load - A380-800 Models

Nov 01/08

FIGURE WLG Tire Deflection 50 % Load - WLG Tire Deflection 50% Load - A380-800 Models

Nov 01/08

L.E.C.Page 3

Oct 01/09


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FIGURE WLG Tire Deflection 25 % Load - WLG Tire Deflection 25% Load - A380-800F Models

Nov 01/08

FIGURE WLG Tire Deflection 50 % Load - WLG Tire Deflection 50% Load - A380-800F Models

Nov 01/08

FIGURE BLG Shock-Absorber Deflection - BLG Shock-AbsorberDeflection - A380-800 Models

Nov 01/08

FIGURE BLG Shock-Absorber Deflection - BLG Shock-AbsorberDeflection - A380-800F Models

Nov 01/08

FIGURE BLG Tire Deflection 16.7 % Load - BLG Tire Deflection 16.7% Load - A380-800 Models

Nov 01/08

FIGURE BLG Tire Deflection 25 % Load - BLG Tire Deflection 25 %Load - A380-800 Models

Nov 01/08

FIGURE BLG Tire Deflection 33.3 % Load - BLG Tire Deflection 33.3% Load - A380-800 Models

Nov 01/08

FIGURE BLG Tire Deflection 50 % Load - BLG Tire Deflection 50 %Load - A380-800 Models

Nov 01/08

FIGURE BLG Tire Deflection 16.7 % Load - BLG Tire Deflection 16.7% Load - A380-800F Models

Nov 01/08

FIGURE BLG Tire Deflection 25 % Load - BLG Tire Deflection 25 %Load - A380-800F Models

Nov 01/08

FIGURE BLG Tire Deflection 33.3 % Load - BLG Tire Deflection 33.3% Load - A380-800F Models

Nov 01/08

FIGURE BLG Tire Deflection 50 % Load - BLG Tire Deflection 50 %Load - A380-800F Models

Nov 01/08

FIGURE WLG Tire Deflection Notes - WLG Tire Deflection Jun 01/07

FIGURE BLG Tire Deflection Notes - BLG Tire Deflection Jun 01/07

FIGURE BLG Tire Deflection Notes - BLG Tire Deflection Notes Jun 01/07

Section 1-9

Ground Clearances Jun 01/07

FIGURE Ground Clearances - A380-800 Models Jun 01/07

FIGURE Ground Clearances - A380-800F Models Jun 01/07

FIGURE Ground Clearances - Leading Edge Slats - Extended -A380-800 Models

Jun 01/07

L.E.C.Page 4

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Ground Clearances - Leading Edge Slats - Extended -A380-800F Models

Jun 01/07

FIGURE Ground Clearances - Trailing Edge Flaps - Extended Jun 01/07

FIGURE Ground Clearances - Spoilers - Extended - A380-800 Models Jun 01/07

FIGURE Ground Clearances - Spoilers - Extended - A380-800F Models Jun 01/07

FIGURE Ground Clearances - Ailerons - Down Jun 01/07

FIGURE Ground Clearances - Ailerons - Up Jun 01/07

FIGURE Ground Clearances - Flap Tracks - Extended Jun 01/07

FIGURE Ground Clearances - Forward Nose Landing Gear Doors Jun 01/07

FIGURE Ground Clearances - Aft Nose Landing Gear Doors Jun 01/07

FIGURE Ground Clearances - Wing Landing Gear Doors Jun 01/07

FIGURE Ground Clearances - Body Landing Gear Doors - Sheet 1/2 Jun 01/07

FIGURE Ground Clearances - Body Landing Gear Doors - Sheet 2/2 Jun 01/07

FIGURE Ground Clearances - APU Doors Jun 01/07

Section 1-10

Door Clearances Jun 01/07

FIGURE Door Clearances - Door Location (Sheet 1) - A380-800Models

Jun 01/07

FIGURE Door Clearances - Door Location (Sheet 2) - A380-800Models

Jun 01/07

FIGURE Door Clearances - Door Location (Sheet 1) - A380-800FModels

Jun 01/07

FIGURE Door Clearances - Door Location (Sheet 2) - A380-800FModels

Jun 01/07

FIGURE Door Clearances - Forward Doors Jun 01/07

FIGURE Door Clearances - Main and Upper Deck Doors - A380-800Models

Jun 01/07

FIGURE Door Clearances - Upper Deck Doors - A380-800F Models Jun 01/07

FIGURE Door Clearances - Aft Doors - A380-800 Models Jun 01/07

FIGURE Door Clearances - Aft Doors - A380-800F Models Jun 01/07

FIGURE Door Clearances - Aft Cargo Compartment Doors -A380-800 Models

R Oct 01/09

L.E.C.Page 5

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Door Clearances - Main Deck Cargo Door - A380-800FModels

Jun 01/07

FIGURE Door Clearances - Lower Deck Aft Cargo Doors - A380-800FModels

R Oct 01/09

FIGURE Door Clearances - Forward Cargo Compartment Doors -A380-800 Models

Jun 01/07

FIGURE Door Clearances - Upper Deck Cargo Door - A380-800FModels

R Oct 01/09

FIGURE Door Clearances - Lower Deck Forward Cargo Door -A380-800F Models

R Oct 01/09

Section 1-11

Fuselage Cross-sections Jun 01/07

FIGURE Fuselage Cross-Section - Section 11/12 - FR0 to FR7 Jun 01/07



FIGURE Fuselage Cross-Section - Section 11/12 - FR15A to FR17C Jun 01/07

FIGURE Fuselage Cross-Section - Section 11/12 - FR18A to FR19B Jun 01/07


FIGURE Fuselage Cross-Section - Section 13 - FR23 to FR26 -A380-800 Models

Jun 01/07

FIGURE Fuselage Cross-Section - Section 13 - FR23 to FR26 -A380-800F Models

Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07

L.E.C.Page 6

Oct 01/09


CONTENT CHGCODE

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Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07

FIGURE Fuselage Cross-Section - Section 15/21 - FR39 to FR40 -A380-800 Models

Jun 01/07

FIGURE Fuselage Cross-Section - Section 15/21 - FR39 to FR40 -A380-800F Models

Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07

L.E.C.Page 7

Oct 01/09


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Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


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Jun 01/07

L.E.C.Page 8

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07


Jun 01/07

FIGURE Fuselage Cross-Section - Section 19 - FR96 to FR98 Jun 01/07





FIGURE Fuselage Cross-Section - Section 19.1 - FR115 to FR119 Jun 01/07

Section 1-12

Nose Contours Jun 01/07

FIGURE Nose Contours - Level Positions - A380-800 Models Jun 01/07

FIGURE Nose Contours - Level Positions - A380-800F Models Jan 31/08

FIGURE Nose Contours - Contour Points at Frame Positions -A380-800 Models

Nov 01/08

FIGURE Nose Contours - Contour Points at Frame Positions -A380-800F Models

Nov 01/08

FIGURE Nose Contours - Upper and Lower Contours - A380-800Models

Jun 01/07

L.E.C.Page 9

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Nose Contours - Upper and Lower Contours - A380-800FModels

Jun 01/07

Section 1-13

Vertical Stabilizer Contours Jun 01/07

FIGURE Vertical Stabilizer Contours - Level Positions Jun 01/07

FIGURE Vertical Stabilizer Contours - Vertical Stabilizer Contours Jun 01/07

Section 1-14

Horizontal Stabilizer Contours Jun 01/07

FIGURE Horizontal Stabilizer Contours - Horizontal StabilizerContours (Sheet 1)

Jun 01/07

FIGURE Horizontal Stabilizer Contours - Horizontal StabilizerContours (Sheet 2)

Jun 01/07

FIGURE Horizontal Stabilizer Contours - Level Positions Jun 01/07

Section 1-15

Tail Contours Jun 01/07

FIGURE Tail Contours - Tail Contours Jun 01/07

FIGURE Tail Contours - Level Positions Jan 31/08

Section 1-16

General Nov 01/08

FIGURE Wing Profile - Rib Locations Jun 01/07

FIGURE Wing Profile - Rib Positions Jun 01/07

FIGURE Wing Profile - Wing Profile Jun 01/07

Section 1-17

Nacelle Contours Nov 01/08

FIGURE Nacelle Contours - Nacelle Contours - TRENT 900 Engines Jan 31/08

FIGURE Nacelle Contours - Nacelle Contours - GP 7200 Engines Jan 31/08

CHAPTER 2

Section 2-1

Airplane Servicing Arrangement Jun 01/07

FIGURE Typical Ramp Layout -- Two Bridges - Servicing Via Mainand Upper Decks

Jun 01/07

L.E.C.Page 10

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Typical Ramp Layout -- Two Bridges - Servicing Via MainDeck

Jun 01/07

FIGURE Opportunities of Direct Upper Deck Access - for Airport andAirlines

Jun 01/07

FIGURE Typical Ramp Layout - Typical Ramp Layout Jun 01/07

Section 2-2

Turnaround Stations Jun 01/07

FIGURE Baseline Turn-Round Time -- Two Bridges - Servicing ViaMain and Upper Decks

Jun 01/07

FIGURE Typical Turn-Round Time -- Two Bridges - Servicing ViaMain Deck

Jun 01/07

Section 2-3

Ground Service Connections and Locations Jun 01/07

FIGURE Ground Service Connections Layout - A380-800 Models Jun 01/07

FIGURE Ground Service Connections Layout - A380-800F Models Jun 01/07

Hydraulic System Nov 01/08

FIGURE Ground Service Connections - Hydraulic Reservoir ServicingPanel

Jun 01/07

FIGURE Ground Service Connections - Hydraulic Ground Connections Jun 01/07

Electrical System Nov 01/08

FIGURE Ground Service Connections - Electrical Service Panel -A380-800 Models

Jun 01/07

FIGURE Ground Service Connections - Electrical Service Panel -A380-800F Models

Jun 01/07

Fuel System Nov 01/08

FIGURE Ground Service Connections - Refuel/Defuel Control Panel Jun 01/07

FIGURE Ground Service Connections - Pressure Refuel Connectors Jun 01/07

Pneumatic System Nov 01/08

FIGURE Ground Service Connections - Low Pressure PreconditionedAir

Jun 01/07

FIGURE Ground Service Connections - High Pressure PreconditionedAir

Jun 01/07

Potable Water System Nov 01/08

L.E.C.Page 11

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Ground Service Connections - Potable Water Ground ServicePanel - A380-800 Models

Jun 01/07

FIGURE Ground Service Connections - Potable Water Ground ServicePanel - A380-800F Models

Jun 01/07

FIGURE Ground Service Connections - Potable Water Drain Panel Jun 01/07

Engine Oil Servicing R Oct 01/09

FIGURE Ground Service Connections - Engine Oil Servicing - TRENT900 Engines

Jan 31/08

FIGURE Ground Service Connections - Engine Oil Servicing - GP7200 Engines

R Oct 01/09

VFG Oil Servicing R Oct 01/09

FIGURE Ground Service Connections - VFG Oil Servicing - TRENT900 Engines

R Oct 01/09

FIGURE Ground Service Connections - VFG Oil Servicing - GP 7200Engines

R Oct 01/09

Starter Oil Servicing R Oct 01/09

FIGURE Ground Service Connections - Starter Oil Servicing - TRENT900 Engines

Jan 31/08

FIGURE Ground Service Connections - Starter Oil Servicing - GP7200 Engines

R Oct 01/09

APU Oil Servicing Nov 01/08

FIGURE Ground Service Connections - APU Oil Servicing Jun 01/07

Vacuum Toilet System Nov 01/08

FIGURE Ground Service Connections - Vacuum Toilet System -A380-800 Models

Jun 01/07

FIGURE Ground Service Connections - Vacuum Toilet System -A380-800F Models

Jun 01/07

Oxygen System Nov 01/08

FIGURE Ground Service Connections - Oxygen System Jun 01/07

Section 2-4

Interior Arrangements Jun 01/07

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

Jun 01/07

L.E.C.Page 12

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

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

Jun 01/07

FIGURE Interior Arrangements - Plan View - Standard Configuration- Cargo Compartments

Jun 01/07

FIGURE Interior Arrangements - Cross-section - Typical Configuration- Upper Deck

Jun 01/07

FIGURE Interior Arrangements - Cross-section - Typical Configuration- Main Deck

Jun 01/07

FIGURE Interior Arrangements - Cross-section - Typical Configuration Jun 01/07

Section 2-5

Escape Slides Nov 01/08

FIGURE Escape Slides/Rafts - Location Jan 31/08

FIGURE Escape Slides/Rafts - Dimensions Jun 01/07

Section 2-6

Galley Jun 01/07

FIGURE General Location of Transversal Galleys - General Location ofTransversal Galleys

Jun 01/07

FIGURE General Layout - Transversal Galley (Sheet 1) Jun 01/07

FIGURE General Layout - Transversal Galley (Sheet 2) Jun 01/07

FIGURE General Location - Longitudinal Galleys Jun 01/07

FIGURE General Layout - Longitudinal Galleys (Sheet 1) Jun 01/07

FIGURE General Layout - Longitudinal Galleys (Sheet 2) Jun 01/07

Section 2-7

Cargo Jun 01/07

FIGURE Cargo Compartments - Location and Dimensions - A380-800Models

Jun 01/07

FIGURE Cargo Compartments - Location and Dimensions -A380-800F Models (Sheet 1)

Jun 01/07

FIGURE Cargo Compartments - Location and Dimensions -A380-800F Models (Sheet 2)

Jun 01/07

FIGURE Cargo Compartments - Loading Combinations - A380-800Models

Jun 01/07

L.E.C.Page 13

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Cargo Compartments - Loading Combinations - A380-800FModels (Sheet 1)

Jun 01/07

FIGURE Cargo Compartments - Loading Combinations - A380-800FModels (Sheet 2)

Jun 01/07

Section 2-8

Towing R Oct 01/09

FIGURE Ground Towing Requirements - Ground TowingRequirements A380-800 Models

R Oct 01/09

FIGURE Ground Towing Requirements - Typical Tow Barconfiguration 1

R Oct 01/09

FIGURE Ground Towing Requirements - Typical Tow Barconfiguration 2

R Oct 01/09

FIGURE Ground Towing Requirements - Nose Gear Towing Fittings R Oct 01/09

FIGURE Ground Towing Requirements - Maximum Extension of theNLG Shock Absorber

N Oct 01/09

Section 2-9

Ground Maneuvering R Oct 01/09

FIGURE Turning Radii - Turning Radii (Sheet 1) R Oct 01/09

FIGURE Turning Radii - Turning Radii (Sheet 2) R Oct 01/09

FIGURE Minimum Turning Radii - (Sheet 1) Nov 01/08

FIGURE Minimum Turning Radii - (Sheet 2) Jun 01/07

FIGURE 135˚ Turn - Runway to Taxiway - 135˚ Turn - Runway toTaxiway (Sheet 1)

R Oct 01/09


R Oct 01/09


R Oct 01/09


R Oct 01/09

FIGURE 180˚ Turn on a Runway - 180˚ Turn on a Runway R Oct 01/09

FIGURE 90˚ Turn - Taxiway to Taxiway - 90˚ Turn - Taxiway toTaxiway (Sheet 1)

R Oct 01/09

L.E.C.Page 14

Oct 01/09


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LAST REVISIONDATE


R Oct 01/09


R Oct 01/09


R Oct 01/09

FIGURE Runway Holding Bay (Apron) - Runway Holding Bay(Apron)

Jun 01/07

Section 2-10

Airplane Parking Jun 01/07

FIGURE Airplane Parking - Steering Geometry Jun 01/07

FIGURE Airplane Parking - Steering Geometry - Minimum ParkingSpace Requirements

Jun 01/07

Section 2-11

Operating Conditions R Oct 01/09

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

Jan 31/08

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

Jan 31/08

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

Jan 31/08

FIGURE Engine Exhaust Temperatures - Ground Idle Power -- GP7200 Engines

Jan 31/08

FIGURE Engine Exhaust Velocities - Breakaway Power -- TRENT 900Engines

Jan 31/08

FIGURE Engine Exhaust Velocities - Breakaway Power -- GP 7200Engines

Jan 31/08

FIGURE Engine Exhaust Temperatures - Breakaway Power -- TRENT900 Engines

Jan 31/08

FIGURE Engine Exhaust Temperature - Breakaway Power -- GP 7200Engines

Jan 31/08

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

Jan 31/08

L.E.C.Page 15

Oct 01/09


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

Jan 31/08

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

Jan 31/08

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

Jan 31/08

FIGURE APU Exhaust Velocities and Temperatures - Max. ECSConditions

Jun 01/07

FIGURE APU Exhaust Velocities and Temperatures - MES Conditions Jun 01/07

FIGURE Airport and Community Noise Data - TRENT 900 Engines Nov 01/08

FIGURE Airport and Community Noise Data - GP 7200 Engines Nov 01/08

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

Jan 31/08

FIGURE Danger Areas of the Engines - Ground Idle Power - GP7200Engines

Jan 31/08

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

Jan 31/08

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

Jan 31/08

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

Jan 31/08

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

Jan 31/08

Section 2-12

Airplane Mooring Jun 01/07

FIGURE Airplane Mooring - Airplane Mooring Jun 01/07

CHAPTER 3

Section 3-1

Airplane Maintenance Jacking R Oct 01/09

FIGURE Jacking Points Location - Jacking Points Location R Oct 01/09

FIGURE Jacking Dimensions - Jacking Dimensions Jun 01/07

L.E.C.Page 16

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Jacks and Safety Stay Adapter - Jacks and Safety StayAdapter

Jun 01/07

Section 3-2

Landing Gear Jacking for Wheel Change Jun 01/07

FIGURE Nose Landing Gear Jacking Point Heights - A380-800Models

Jan 31/08

FIGURE Wing Landing Gear Jacking Point Heights - A380-800Models

Jan 31/08

FIGURE Body Landing Gear Jacking Point Heights - A380-800Models

Jan 31/08

FIGURE Nose Landing Gear Jacking Point Loads - A380-800 Models Nov 01/08

FIGURE Nose Landing Gear Jacking Point Loads - A380-800F Models Nov 01/08

FIGURE Wing Landing Gear Jacking Point Loads - A380-800 Models Nov 01/08

FIGURE Wing Landing Gear Jacking Point Loads - A380-800FModels

Nov 01/08

FIGURE Body Landing Gear Jacking Point Loads - A380-800 Models Nov 01/08

FIGURE Body Landing Gear Jacking Point Loads - A380-800F Models Nov 01/08

Section 3-3

Leveling, Symmetry and Alignment Jun 01/07

FIGURE Location of Leveling Points - Location of Leveling Points Jun 01/07

Section 3-4

De-icing and Washing Nov 01/08

Section 3-5

Air Conditioning Nov 01/08

FIGURE Air Conditioning - General Layout Jun 01/07

FIGURE Air Conditioning - Air Generation Unit (AGU) Jun 01/07

Section 3-6

Communications Jun 01/07

FIGURE Communications - Location of Antennas Jan 31/08

Section 3-7

Electrical Power Nov 01/08

FIGURE Electrical Power - General Schematic Jun 01/07

L.E.C.Page 17

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Electrical Power - AC and DC Distribution Jun 01/07

FIGURE Electrical Power - Component Location Jun 01/07

Section 3-8

Flight Controls Nov 01/08

FIGURE Control Surface Travel - Rudder (Sheet 1) Jun 01/07

FIGURE Control Surface Travel - Rudder (Sheet 2) Jun 01/07

FIGURE Control Surface Travel - Trimmable Horizontal Stabilizer andElevator (Sheet 1)

Jun 01/07

FIGURE Control Surface Travel - Trimmable Horizontal Stabilizer andElevator (Sheet 2)

Jun 01/07

Section 3-9

Hydraulic Power Jun 01/07

FIGURE Hydraulic Power System - Symbols Jun 01/07

FIGURE Main Hydraulic Power System - Architecture Jun 01/07

FIGURE Green Hydraulic System - General Jun 01/07

FIGURE Yellow Hydraulic System - General Jun 01/07

FIGURE Hydraulic Power - Distribution Jun 01/07

Section 3-10

Landing Gear Jun 01/07

FIGURE Landing Gear - Nose Gear and Doors Jun 01/07

FIGURE Landing Gear - Nose Gear Servicing Points Jun 01/07

FIGURE Landing Gear - Wing Gear and Doors Jun 01/07

FIGURE Landing Gear - Wing Gear Servicing Points Jun 01/07

FIGURE Landing Gear - Body Gear and Doors Jun 01/07

FIGURE Landing Gear - Body Gear Servicing Points Jun 01/07

FIGURE Landing Gear - Landing Gear Footprint - A380-800 Models Jun 01/07

FIGURE Landing Gear - Landing Gear Footprint - A380-800F Models Jun 01/07

Section 3-11

Exterior Lighting Jun 01/07

L.E.C.Page 18

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Exterior Lighting - Exterior Lighting Available in Flight(Sheet 1)

Jun 01/07

FIGURE Exterior Lighting - Exterior Lighting Available in Flight(Sheet 2)

Jun 01/07

FIGURE Exterior Lighting - Exterior Lighting for Ground Use -A380-800 Models

Jun 01/07

FIGURE Exterior Lighting - Exterior Lighting for Ground Use -A380-800F Models

Jun 01/07

Section 3-12

Navigation Jun 01/07

FIGURE Navigation - Location of Antennas Jun 01/07

Section 3-13

Auxiliary Power Unit Jun 01/07

FIGURE Auxiliary Power Unit - APU Access Doors Jun 01/07

FIGURE Auxiliary Power Unit - General Layout Jun 01/07

Section 3-14

Power Plant R Oct 01/09

FIGURE Engine Dimensions - GP 7200 Engines Jan 31/08

FIGURE Engine Dimensions - TRENT 900 Engines Jan 31/08

FIGURE Fan Cowls - TRENT 900 Engines R Oct 01/09

FIGURE Fan Cowls - Engine 1-2-3-4 - GP 7200 Engines N Oct 01/09

FIGURE Fan Exhaust Cowls - Engine 1-4 - GP 7200 Engines N Oct 01/09

FIGURE Thrust Reverser - Engine 2-3 - GP 7200 Engines N Oct 01/09

Section 3-15

Component Sizes and Weights Nov 01/08

Section 3-16

Component Handling Nov 01/08

FIGURE Droop Nose 1 - CG Location Jun 01/07

FIGURE Droop Nose 2 - CG Location Jun 01/07

FIGURE Slat 2 - CG Location Jun 01/07


L.E.C.Page 19

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE





FIGURE Inboard Aileron - CG Location Nov 01/08

FIGURE Mid Aileron - CG Location Nov 01/08

FIGURE Outboard Aileron - CG Location Nov 01/08

FIGURE Spoiler 1 - CG Location Nov 01/08








FIGURE Horizontal Stabilizer - CG Location Jun 01/07

FIGURE Vertical Stabilizer and Rudder - CG Location (Sheet 1) Jun 01/07

FIGURE Vertical Stabilizer and Rudder - CG Location (Sheet 2) Jun 01/07

FIGURE Tail cone - CG Location Jun 01/07

Section 3-17

Suggested Hangar Arrangement Jun 01/07

FIGURE Suggested Hangar Arrangement - Nose--in Position (Sheet 1) Jun 01/07

FIGURE Suggested Hangar Arrangement - Nose--in Position (Sheet 2) Jun 01/07

FIGURE Suggested Hangar Arrangement - Tail--in Position (Sheet 1) Jun 01/07

FIGURE Suggested Hangar Arrangement - Tail--in Position (Sheet 2) Jun 01/07

Section 3-18

Landing Gear Maintenance Pits Jun 01/07

FIGURE Maintenance Pits - Maintenance Pit Envelopes Jun 01/07

FIGURE Maintenance Pits - Necessary Depths Jun 01/07

L.E.C.Page 20

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Maintenance Pits - Maintenance Pit Envelopes - WLG PitDimensions

Jun 01/07

FIGURE Maintenance Pits - Maintenance Pit Envelopes - BLG PitDimensions

Jun 01/07

Section 3-19

Suggested Workstands Nov 01/08

FIGURE General Arrangement - (Sheet 1) Jun 01/07

FIGURE General Arrangement - (Sheet 2) Jun 01/07

FIGURE Cargo Compartment Platform - (Sheet 1) Jun 01/07

FIGURE Cargo Compartment Platform - (Sheet 2) Jun 01/07

FIGURE Engine Platform - Engine Platform Jun 01/07

FIGURE WLG/BLG Compartment Platform - WLG/BLGCompartment Platform

Jun 01/07

FIGURE Rear Fuselage Platform - Rear Fuselage Platform Jun 01/07

FIGURE Hydraulic Platform -- Giraffe - Hydraulic Platform -- Giraffe Jun 01/07

FIGURE Pax Door Platform -- Main and Upper Decks - Pax DoorPlatform -- Main and Upper Decks

Jun 01/07

FIGURE Fuselage Platform - Fuselage Platform Jun 01/07

FIGURE Inner Wing Platform - Inner Wing Platform Jun 01/07

FIGURE Outer Wing Platform - Outer Wing Platform Jun 01/07

CHAPTER 4

Section 4-1

Batteries Shop Jun 01/07

Section 4-2

VFG Generator Shop Jun 01/07

Section 4-3

Composite Repair Shop Jun 01/07

Section 4-4

Electrical Accessories Shop Jun 01/07

Section 4-5

Electrical Wire Marking Shop Jun 01/07

L.E.C.Page 21

Oct 01/09


CONTENT CHGCODE

LAST REVISIONDATE

Section 4-6

Engine and APU Shop Jun 01/07

Section 4-7

Fuel Component Shop Jun 01/07

Section 4-8

Hydraulic Component Shop Jun 01/07

Section 4-9

I.E.R.A. Shop Jun 01/07

Section 4-10

Interior Equipment Shop Jun 01/07

Section 4-11

Laboratory Test of Fluids Jun 01/07

Section 4-12

Metal Shop Jun 01/07

Section 4-13

Painting Shop Jun 01/07

Section 4-14

Pneumatic Component Shop Jun 01/07

Section 4-15

Life Jacket, Escape Slide / Raft Shop Jun 01/07

Section 4-16

Surface Heat Treatment Shop Jun 01/07

Section 4-17

Tube Repair Shop Jun 01/07

Section 4-18

Tire/Wheel and Brake Shop Jun 01/07

CHAPTER 5

Section 5-1

General Jun 01/07

L.E.C.Page 22

Oct 01/09


TABLE OF CONTENTS

0 INTRODUCTION

0-1 Introduction

0-2 Alphabetical Index

0-3 Section Index

0-4 Glossary

1 GENERAL INFORMATION

1-1 Airplane Overall Dimensions and Outline Basic Reference

1-2 Airplane Dimensions

1-3 General Airplane Characteristics

1-4 Zoning and Access

1-5 Fuselage Frames / Stations

1-6 Wing Ribs / Stations

1-7 Center of Gravity Limits

1-8 Airplane Attitude

1-9 Ground Clearances

1-10 Door Clearances

1-11 Fuselage Cross-sections

1-12 Nose Contours

1-13 Vertical Stabilizer Contours

1-14 Horizontal Stabilizer Contours

1-15 Tail Contours

1-16 Wing Profile

1-17 Nacelle Contours

2 TERMINAL AND RAMP

2-1 Airplane Servicing Arrangement

2-2 Turnaround Stations

2-3 Ground Service Connections and Locations

2-4 Interior Arrangements

2-5 Escape Slides

2-6 Galley

2-7 Cargo

2-8 Towing

2-9 Ground Maneuvering

T.O.C.Page 1

Oct 01/09


2-10 Airplane Parking

2-11 Operating Conditions

2-12 Airplane Mooring

3 LINE MAINTENANCE AND HANGAR

3-1 Airplane Maintenance Jacking

3-2 Landing Gear Jacking for Wheel Change

3-3 Leveling, Symmetry and Alignment

3-4 De-icing and Washing

3-5 Air Conditioning

3-6 Communications

3-7 Electrical Power

3-8 Flight Controls

3-9 Hydraulic Power

3-10 Landing Gear

3-11 Exterior Lighting

3-12 Navigation

3-13 Auxiliary Power Unit

3-14 Power Plant

3-15 Component Sizes and Weights

3-16 Component Handling

3-17 Suggested Hangar Arrangement

3-18 Landing Gear Maintenance Pits

3-19 Suggested Workstands

4 COMPONENT REPAIR/OVERHAUL AND FUNCTIONAL TEST

4-1 Batteries Shop

4-2 VFG Generator Shop

4-3 Composite Repair Shop

4-4 Electrical Accessories Shop

4-5 Electrical Wire Marking Shop

4-6 Engine and APU Shop

4-7 Fuel Component Shop

4-8 Hydraulic Component Shop

4-9 I.E.R.A. Shop

4-10 Interior Equipment Shop

4-11 Laboratory Test of Fluids

4-12 Metal Shop

T.O.C.Page 2

Oct 01/09


4-13 Painting Shop

4-14 Pneumatic Component Shop

4-15 Life Jacket, Escape Slide / Raft Shop

4-16 Surface Heat Treatment Shop

4-17 Tube Repair Shop

4-18 Tire/Wheel and Brake Shop

5 VENDORS LIST

5-1 Vendors Information

T.O.C.Page 3

Oct 01/09


INTRODUCTION

0-1 Introduction

**ON A/C A380-800 Models A380-800F Models

Introduction

1. PURPOSE

This A380 MAINTENANCE FACILITY PLANNING (MFP) manual is issued for the A380-800 andA380-800F series aircraft to provide necessary data to airlines for maintenance facilities planning.

The A380-800 is a subsonic, very long range, very high capacity, civil transport aircraft.There are two models in the A380-800 series :- A380-841 model equipped with Rolls-Royce Trent 970 engine,- A380-861 model equipped with Engine Alliance GP 7270 engine.

The A380-800F is a subsonic, very long range, civil freighter aircraft.

There are two models in the A380-800F series :- A380-843F model equipped with Rolls-Royce Trent 977 engine,- A380-863F model equipped with Engine Alliance GP 7277 engine.

In this manual, effectivity is managed as follows :- by default, the data is effective for all A380-800 and A380-800F models,- ″A380-800/800F models″ indicates that the related data or page is effective for all A380-800 and

A380-800F models,- ″A380-800 models″ restricts the effectivity of the related data or page to the A380-841 and

A380-861 models,- ″A380-800F models″ restricts the effectivity of the related data or page to the A380-843F and

A380-863F models,- the mention of a specific model (e.g. A380-841 model, A380-863F model, etc.) restricts the

effectivity of the related data or page to that specific model.

2. CORRESPONDENCE

Correspondence concerning this publication should be directed to :AIRBUS S.A.S.Technical Data Support and Services1 Rond Point Maurice BELLONTE31707 BLAGNAC CEDEXFRANCE

3. CONTENTS

0-1Page 1

Oct 01/09


This manual comprises 5 sections :

Section 0 : INTRODUCTION

Section 1 : GENERAL INFORMATION

This section contains general dimensional and other basic data.It covers :- aircraft dimensions,- zoning, fuselage frame and wing stations,- cross-sections and profile for fuselage, wings and tail,- ground clearances and travel limits of movable parts,- aircraft center of gravity limits and aircraft attitude.

Section 2 : TERMINAL AND RAMP

This section contains the ground equipment required for the aircraft servicing at turn-round stations.It covers :- suggested servicing arrangement around the aircraft,- estimated servicing times for turn-round,- ground service connections and locations with their characteristics,- cargo compartment loading and unloading,- ground maneuvering capabilities and characteristics.

Section 3 : LINE MAINTENANCE AND HANGAR

This section outlines the technical data and requirements related to maintenance functions, regardlessof whether these would be performed inside or outside the hangar or on the ramp.It includes :- description of the main aircraft systems,- the aircraft jacking, leveling and the landing gear lifting,- the main removable components weight and handling,- the suggested hangar arrangement with the corresponding workstands.

Section 4 : COMPONENT REPAIR/OVERHAUL AND FUNCTIONAL TEST

This section contains the data and requirements relative to aircraft components repair/overhaul andfunctional testing.

Section 5 : VENDORS LIST

0-1Page 2

Oct 01/09


0-2 Alphabetical Index


Alphabetical Index

1. Alphabetical index

Subject Section

Air Conditioning 3-5

Airplane Attitude 1-8

Airplane Dimensions 1-2

Airplane Maintenance Jacking 3-1

Airplane Overall Dimensions and Outline BasicReference Drawing

1-1

Airplane Parking 2-10

Airplane Servicing Arrangement 2-1

Auxiliary Power Unit 3-13

Batteries Shop 4-1

Cargo Compartments - Loading and Unloading 2-7

Center of Gravity Limits 1-7

Communications 3-6Component Handling 3-16

Component Sizes and Weights 3-15

Composite Repair Shop 4-3

De-icing and Washing 3-4

Door Clearances 1-10Electrical Accessories Shop 4-4

Electrical Power 3-7Electrical Wire Marking Shop 4-5

Engine and APU Shop 4-6

Escape Slides/Rafts 2-5

Exterior Lighting 3-11

Flight Controls 3-8

Fuel Component Shop 4-7

Fuselage Cross-sections 1-11

Fuselage Frames/Stations 1-5

Galleys 2-6

General Airplane Characteristics 1-3

Generator Shop 4-2

0-2Page 1

Oct 01/09


Ground Clearances 1-9Ground Maneuvering 2-9

Ground Service Connections and Locations 2-3Horizontal Stabilizer Contours 1-14Hydraulic Component Shop 4-8

Hydraulic Power 3-9

I E R A Shop 4-9

Interior Arrangements 2-4

Interior Equipment Shop 4-10

Laboratory Test of Fluids 4-11

Landing Gear 3-10

Landing Gear Jacking for Wheel Change 3-2

Landing Gear Maintenance Pits 3-18

Leveling, Symmetry and Alignment 3-3

Life Jacket, Escape Slide/raft Shop 4-15

Machine Shop 4-12

Nacelle Contours 1-17Navigation 3-12

Nose Contours 1-12Operating Conditions 2-11

Painting Shop 4-13

Pneumatic Component Shop 4-14

Power Plant 3-14Suggested Hangar Arrangement 3-17

Suggested Workstands 3-19

Surface Heat Treatment Shop 4-16

Tail Contours 1-15Terminal Operation 2-2

Tire/Wheel and Brake Shop 4-18

Towing 2-8

Tube Repair Shop 4-17

Vendors Information 5-1Vertical Stabilizer Contours 1-13Wing Profile 1-16

Wing Ribs/Stations 1-6

Zoning 1-4

0-2Page 2

Oct 01/09


0-3 Section Index


Section Index

1. Section index

SECTION 0: INTRODUCTION0-0 Table Of Contents0-1 Introduction0-2 Alphabetical Index

0-3 Section Index0-4 Glossary

SECTION 1: LINE MAINTENANCE AND HANGAR1-0 Table Of Contents1-1 Airplane Overall Dimensions and Outline Basic Reference drawing



1-4 Zoning

1-5 Fuselage Frames/Stations

1-6 Wing Ribs/Stations



1-9 Ground Clearances1-10 Door Clearances1-11 Fuselage Cross-sections

1-12 Nose Contours1-13 Vertical Stabilizer Contours1-14 Horizontal Stabilizer Contours1-15 Tail Contours1-16 Wing Profile


SECTION 2: TERMINAL AND RAMP2-0 Table Of Contents2-1 Airplane Servicing Arrangement

2-2 Terminal Operation

2-3 Ground Service Connections and Locations2-4 Interior Arrangements

0-3Page 1

Oct 01/09


2-5 Escape Slides/Rafts

2-6 Galleys

2-7 Cargo Compartments - Loading and Unloading

2-8 Towing




SECTION 3: LINE MAINTENANCE AND HANGAR3-0 Table Of Contents3-1 Airplane Maintenance Jacking





3-6 Communications3-7 Electrical Power3-8 Flight Controls

3-9 Hydraulic Power

3-10 Landing Gear


3-12 Navigation


3-14 Power Plant3-15 Component Sizes and Weights





SECTION 4: COMPONENT REPAIR/OVERHAUL AND FUNCTIONAL TEST

4-0 Table Of Contents4-1 Batteries Shop

4-2 Generator Shop




0-3Page 2

Oct 01/09





4-9 I E R A Shop



4-12 Machine Shop

4-13 Painting Shop


0-3Page 3

Oct 01/09


0-4 Glossary


Glossary

1. List of Abbreviations

A/C Aircraft

ADIRS Air Data Inertial Reference System

AGU Air Generation UnitAPU Auxiliary Power Unit

ATA Air Transport Association of America

BLG Body Landing Gear

CAS Calibrated Air Speed

CG Center of Gravity

C/L Center Line

FAA Federal Aviation AdministrationFDL Fuselage Datum Line

FR FrameFSTE Full Size Trolley Equivalent

FWD ForwardGPU Ground Power UnitGSE Ground Support Equipment

IERA Instrument, Electric, Radio and navigation, Avionic

ILS Instrument Landing System

ISA International Standard Atmosphere

L LeftLPS Last Pax Seating

MAC Mean Aerodynamic Chord

MAX MaximumMIN MinimumMLW Maximum Design Landing Weight

MRW Maximum Design Ramp Weight

MTOW Maximum Design Take-Off Weight

MTW Maximum Design Taxi Weight

MZFW Maximum Design Zero Fuel Weight

NDT Non-Destructive TestNLG Nose Landing Gear

OAT Outside Air Temperature

OWE Operating Weight Empty

0-4Page 1

Oct 01/09


PAX Passenger

PB/D Passenger Boarding/Deboarding

R Right

RC Reference ChordSLS Sea Level Static conditionSTA StationTBD To Be DeterminedTBIL To Be Issued LaterULD Unit Load Device US United StatesVF Variable Frequency

VFG Variable Frequency Generator

VHF Very High Frequency

VOR VHF Omnidirectional Range

Vref Landing reference speed

WLG Wing Landing Gear

2. Units of Measurement

˚ degree (angle)

% percent

˚C degree Celsius

˚F degree Fahrenheit

bar barcm centimeterdeg degree (angle)

ft footft/s foot per second

ft/s2 foot per second squared

ft2 square foot

ft3 cubic footin inchkg kilogram

kg/l kilogram per liter

km/h kilometer per hour

kt knotkVA kiloVolt Ampere

l literl/m2 liter per square meter

lb/in2 pound per square inch

0-4Page 2

Oct 01/09


lb pound

lm/m2 lumen per square meterm meterm/s meter per second

m2 square meter

m3 cubic meter

m3/h cubic meter per hour

min minutemm millimeternm nautical milepsi pound-force per square incht tonneUS gal United States gallon

3. Design Weight TerminologyMaximum Design Ramp Weight (MRW) :Maximum weight for ground maneuver (including weight of taxi and runup fuel) as limited by aircraftstrength 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 Takeoff Weight (MTOW) :Maximum weight for take-off as limited by aircraft strength and airworthiness requirements. (This isthe maximum weight at start of the take-off run).Maximum Design Zero Fuel Weight (MZFW) :Maximum permissible weight of the aircraft less usable fuel.Operational Empty Weight (OEW) :Weight of structure, powerplant, furnishings, systems, and other items of equipment that are anintegral part of a particular aircraft configuration plus the operator’s items.The operator’s items are the flight and cabin crew and their baggage, unusable fuel, engine oil,emergency equipment, toilet chemical and fluids, galley structure, catering equipment, seats,documents, etc.Maximum Payload :Maximum Design Zero Fuel Weight (MZFW) minus Operating Weight Empty (OWE).Maximum Seating Capacity :Maximum number of passengers specifically certified or anticipated for certification.Maximum Cargo Volume :Maximum usable volume available for cargo.

Usable Fuel :

0-4Page 3

Oct 01/09


Fuel available for aircraft propulsion.

0-4Page 4

Oct 01/09


GENERAL INFORMATION

1-1 Airplane Overall Dimensions and Outline Basic Reference


Airplane Overall Dimensions and Outline Basic Reference Drawing

1. This section gives the airplane overall dimensions and outline basic reference drawing.

1-1Page 1

Oct 01/09


**ON A/C A380-800 Models

DB1A

0 4 8 12 16METERS

0 10 20 30 40 50FEET

L_MF_010100_1_0050101_01_00

Airplane Overall Dimensions and Outline Basic Reference DrawingA380-800 Models

1-1Page 2

Oct 01/09


**ON A/C A380-800F Models

DB1A

0 4 8 12 16METERS

0 10 20 30 40 50FEET

L_MF_010100_1_0060101_01_00

Airplane Overall Dimensions and Outline Basic Reference DrawingA380-800F Models

1-1Page 3

Oct 01/09




Airplane Dimensions

1. This section gives airplane dimensions.

1-2Page 1

Oct 01/09



11.568 m(37.95 ft)

3.717 m(12.19 ft)

17.668 m (57.96 ft)

72.571 m (238.09 ft)

68.854 m (225.90 ft)

46.972 m (154.11 ft) 3.983 m (13.07 ft)

FOR DOOR DIMENSIONS ANDLOCATION, SEE SECTION 1−10.

NOTE:

29.943 m (98.23 ft)

22.228 m (72.92 ft)

L_MF_010200_1_0040101_01_01

52.065 m (170.82 ft)

Airplane DimensionsAirplane Dimensions (Sheet 1)

1-2Page 2

Oct 01/09



72.727 m (238.61 ft)

70.400 m (230.97 ft)

53.943 m (176.98 ft) 4.700 m(15.41 ft)

12.056 m(33.55 ft)

14.5

92 m

(47

.87

ft)12.456 m(40.87 ft)

5.264 m(17.27 ft)

79.750 m (261.65 ft)

7.142 m(23.43 ft)

30.372 m (99.65 ft)

14.336 m (47.03 ft)

29.598 m (97.11 ft)

51.400 m (168.64 ft)

8.410 m (27.60 ft)

8.557 m (28.07 ft)

14.084 m(46.20 ft)

33.578 m (110.16 ft) − WLG

36.854 m (120.91 ft) − BLG

4.972 m (16.31 ft)

L_MF_010200_1_0030101_01_00

Airplane DimensionsAirplane Dimensions (Sheet 2)

1-2Page 3

Oct 01/09




General Airplane Characteristics Data

1. This part gives general airplane characteristics data for A380-800 models.

Airplane Characteristics

WV000 WV001 WV002 WV003Kilograms 562 000 512 000 571 000 571 000Maximum Ramp

Weight (MRW) Pounds 1 238 998 1 128 766 1 258 839 1 258 839Kilograms 560 000 510 000 569 000 510 000Maximum Takeoff

Weight (MTOW) Pounds 1 234 588 1 124 357 1 254 430 1 124 357Kilograms 386 000 394 000 391 000 395 000Maximum Landing

Weight (MLW) Pounds 850 984 868 621 862 007 870 826Kilograms 361 000 372 000 366 000 373 000Maximum Zero Fuel

Weight (MZFW) Pounds 795 869 820 119 806 892 822 324Trent 970Engines

270 364 kg (596 050 lb)Estimated OperatingEmpty Weight (OEW) GP 7270

Engines270 630 kg (596 637 lb)

Kilograms 90 636 101 636 95 636 102 636Estimated MaximumPayload Trent 970 Pounds 199 818 224 069 210 841 226 274

Kilograms 90 370 101 370 95 370 102 370Estimated MaximumPayload GP 7270 Pounds 199 232 223 483 210 255 225 687Standard SeatingCapacity <1>

Three-Class 555

Liters 323 546US gallons 85 472

Kilograms(density =0.785 kg/l)

253 983Usable Fuel Capacity

Pounds 559 937Cubic meters 2100Pressurized Fuselage

Volume (A/C nonequipped, main andupper deck)

Cubic feet 74 161

Cubic meters 775PassengerCompartment Volume(main deck) Cubic feet 27 369

1-3Page 1

Oct 01/09



Cubic meters 530PassengerCompartment Volume(upper deck) Cubic feet 18 717

Cubic meters 12Cockpit Volume

Cubic feet 424Cubic meters 256Usable Cargo

Compartment Volume<2>

Cubic feet 9040

<1> 555 pax :- Main deck : First Class 22 and Tourist Class 334.- Upper deck : Business Class 96 and Tourist Class 103.<2> Volume of cargo compartments :- Lower deck forward cargo compartment (Water volume) : 131 m3 (4626 ft3)- Lower deck aft cargo compartment (Water volume) : 107.8 m3 (3807 ft3)- Lower bulk cargo compartment (Water volume) : 17.2 m3 (607 ft3)

2. This part gives the general airplane characteristics data for A380-800F models.


Airplane Model A380-843F A380-863F

Engines TRENT 977 GP 7277

kilograms 592 000 592 000Maximum Design RampWeight (MRW) pounds 1 305 136 1 305 136

kilograms 590 000 590 000Maximum Design Take OfWeight (MTOW) pounds 1 300 727 1 300 727

kilograms 427 000 427 000Maximum Design LandingWeight (MLW) pounds 941 374 941 374

kilograms 402 000 402 000Maximum Design ZeroFuel Weight (MZFW) pounds 886 258 886 258

kilograms 250 560 250 826Operating Empty Weight(OEW) Typical pounds 552 390 552 976

kilograms 151 440 151 174Maximum Payload

pounds 333 868 333 281

liters 310 000 <2> 310 000 <2>US gallons 81 893 81 893

kilograms (density= 0.785 kg/l)

243 350 243 350

Usable Fuel Capacity

pounds 536 494 536 494

1-3Page 2

Oct 01/09



cubic meters 938.4 938.4Volume of cargo compartments<1> cubic feet 33 139 33 139

cubic meters 12.6 12.6Volume of Cockpitcubic feet 444.96 444.96

<1> Volume of cargo compartments- lower deck forward cargo compartment (usable containerized volume) : 90 m3 (3 157 ft3)- lower deck aft cargo compartment (usable containerized volume) : 72 m3 (2 525 ft3)- lower bulk cargo compartment (usable volume) : 18.4 m3 (650 ft3)- main deck cargo compartment (usable palletized volume) : 508 m3 (18 222 ft33)- upper deck cargo compartment (usable palletized volume) : 250 m3 (9 075 ft3)<2> Usable fuel capacity with center tank : 355 850 l (94 005 US gal)

1-3Page 3

Oct 01/09


1-4 Zoning and Access


Zoning and Access

1. General

This section provides the zone division/delimitation.

2. Aircraft Zoning

NOTE : If no side differentiation is needed (eg. : pylon, bilge area), the old numbering for ″centerzones″ is used.

A. Identification Method

(1) Zones identification is based on ATA 100 Specification.

(2) The aircraft is broken down into Zones identified, each, by a three-digit number where thefirst digit (hundreds) corresponds to the Major Zones, the second digit (tens) correspondsto the Major Sub-Zones and the third digit (units) corresponds to the Zones.

B. Identification of Major Zones, Major Sub-Zones and ZonesLocations and boundaries of the Major Zones and Major Sub-Zones are illustrated on thefollowing pages.

NOTE : Locations and boundaries of the zones are not given in this manual.

(1) Major Zones (hundreds)

(a) Major Zones boundaries are identified by :- Frame/Stations/Stringers for fuselage.- Ribs for wings and vertical/horizontal tail.- Stations for nacelle and pylon.

(b) The Major Zones are :- 100 Lower part of fuselage (below main deck floor lower datum), including

radome to forward face of aft pressure bulkead.- 200 Upper part of fuselage (above main deck floor lower datum) to forward face

of aft pressure bulkead.- 300 Stabilizer and fuselage rear section from rear of aft pressure bulkead

(including rudder and elevators).- 400 Powerplants, nacelles and pylons.- 500 Left wing.- 600 Right wing.- 700 Landing gear and landing gear doors.- 800 Passenger/crew doors, cargo compartment doors, emergency exits and

pressurized maintenance doors.

1-4Page 1

Oct 01/09


(2) Major Sub-Zones (tens)

(a) These are divisions of the Major Zones, eg : 100 divided into 110, 120, 130, 140, etc.

(b) The sequence of Major Sub-Zones numbering for fuselage runs from the front to therear.

(3) Zones (units)

(a) These are divisions of Major Sub-Zones, eg : 120 divided into 121, 122, 123, etc.

(b) The sequence of Zones for fuselage runs from inboard to outboard, front to rear inthe wing, forward to aft and away from the floor line in the fuselage and from root totip in the vertical tail.

(c) Whenever feasible odd numbers are allocated to the zones left of fuselage or nacellecenterlines and even numbers to zones to the right.

1-4Page 2

Oct 01/09



Z100Z800Z300 Z400Z700 Z600

Z500

Z200

L_MF_010400_1_0010102_01_00

Aircraft ZoningMajor Zones

1-4Page 3

Oct 01/09



Z110 Z130 Z150 Z170

Z120

FR0 FR17 FR46 FR56 FR72 FR86 FR91 FR95

COCKPIT FLOORLOWER DATUM

MAIN DECK FLOORLOWER DATUM

Z160Z140

L_MF_010400_1_0020102_01_00

Aircraft ZoningMajor Sub-Zones - Zone 100 (Sheet 1)

1-4Page 4

Oct 01/09



Z190

Z190

L_MF_010400_1_0030102_01_00

Aircraft ZoningMajor Sub-Zones - Zone 100 (Sheet 2)

1-4Page 5

Oct 01/09



Z220 Z230 Z240 Z250

FR36 FR61 FR80

FR95

Z290Z280Z270

FR73FR43FR21

Z210

FR5

Z260

FR16

FR14

COCKPIT FLOORLOWER DATUM LOWER DATUM

MAIN DECK FLOORLOWER DATUM

UPPER DECK FLOOR

L_MF_010400_1_0040102_01_00

Aircraft ZoningMajor Sub-Zones - Zone 200

1-4Page 6

Oct 01/09



FR95

Z320

Z310

Z310

Z340

Z330

L_MF_010400_1_0050102_01_00


1-4Page 7

Oct 01/09



OUTBOARD

INBOARD

Z450

Z410

Z480

Z440

LEFT WING(ENGINE 1)

RIGHT WING(ENGINE 4)

Z460

Z420

LEFT WING(ENGINE 2)

Z470

Z430


L_MF_010400_1_0060102_01_00

Aircraft ZoningMajor Sub-Zones - Zone 400 - TRENT 900 Engines

1-4Page 8

Oct 01/09



OUTBOARD

INBOARD

Z450

Z410

Z480

Z440

LEFT WING(ENGINE 1)


Z460

Z420

LEFT WING(ENGINE 2)

Z470

Z430


L_MF_010400_1_0070102_01_00

Aircraft ZoningMajor Sub-Zones - Zone 400 -- GP 7200 Engines

1-4Page 9

Oct 01/09



Z630

Z630

Z630

Z630

Z690

Z630

Z660

Z680

Z670

Z610

Z610

Z610

Z640

Z650Z630

Z630

Z630

Z630

Z690

Z630

Z660

Z680

Z670

Z610

Z610

Z610

Z640

Z650

Z620Z620

Z510

Z510

Z510

Z540

Z550

Z520 Z560

Z530

Z530

Z530

Z530

Z530

Z580

Z590

Z570

L_MF_010400_1_0080102_01_00

Aircraft ZoningMajor Sub-Zones - Zone 500/600

1-4Page 10

Oct 01/09



Z710 Z730Z750Z760

Z740

L_MF_010400_1_0090102_01_00


1-4Page 11

Oct 01/09



Z820Z820

Z850 Z850 Z850

Z830 Z830 Z830

Z840

Z860 Z860 Z860

Z840Z840 Z840Z840

Z830Z830

Z810

L_MF_010400_1_0100102_01_00


1-4Page 12

Oct 01/09


1-5 Fuselage Frames / Stations


Fuselage Frames / Stations

1. General

This section gives fuselage frame stations measured along X datum at 7330 mm from the nose.The stations (STA) are given in millimeters without conversion.

1-5Page 1

Oct 01/09



FR95FR74FR38

SECTION11/12

FR22FR5

SECTION 13 SECTION 15/21 SECTION 18 SECTION 19

L_MF_010500_1_0010102_01_00

Fuselage Frames/StationsSections Identification - A380-800 Models

1-5Page 2

Oct 01/09



FR95FR74FR38

SECTION11/12

FR22FR5

SECTION 13 SECTION 15/21 SECTION 18 SECTION 19

L_MF_010500_1_0020102_01_00

Fuselage Frames/StationsSections Identification - A380-800F Models

1-5Page 3

Oct 01/09



3°

FR10A

X = 0

SECTION 12SECTION 11

10°

X = 7330

FR10 DATUM−STA 10406

FR9/STA10083

FR8/STA9763FR7/STA9437


FR0/STA8170FR18A/STA13824

FR17C/STA13429

FR16/STA12657

FR14/STA11778

FR15A/STA12355

FR15/STA12053

FR13/STA11453FR12/STA11128

FR11A/STA10805

FR17B/STA13073

FR19B/STA14351

FR5 FR15 FR22

FR11/STA10767

FR10B

FR10 DATUM/STA10406

RADOME ANDNOSE LOWER UNIT

FR22/STA16205FR21/STA15570

FR20/STA14935FR19/STA14300

FR18/STA13646FR17/STA12991

L_MF_010500_1_0030102_01_00

Fuselage Frames/StationsSection 11/12 - A380-800 Models

1-5Page 4

Oct 01/09



3°

FR10A

X = 0

SECTION 12SECTION 11

10°

X = 7330

FR10 DATUM−STA 10406

FR9/STA10083



FR0/STA8170FR18A/STA13824

FR17C/STA13429

FR16/STA12657

FR14/STA11778

FR15A/STA12355

FR15/STA12053

FR13/STA11453FR12/STA11128

FR11A/STA10805

FR17B/STA13073

FR19B/STA14351

FR5 FR15 FR22

FR11/STA10767

FR10B

FR10 DATUM/STA10406

RADOME ANDNOSE LOWER UNIT

FR22/STA16205FR21/STA15570

FR20/STA14935FR19/STA14300

FR18/STA13646FR17/STA12991

L_MF_010500_1_0040102_01_00

Fuselage Frames/StationsSection 11/12 - A380-800F Models

1-5Page 5

Oct 01/09



FR22/STA16205FR23/STA16840

FR24/STA17475FR25/STA18110

FR26/STA18745FR27/STA19380

FR28/STA20015FR29/STA20650

FR30/STA21285FR31/STA21920

FR32/STA22555FR33/STA23190

FR34/STA23825

FR36/STA25095FR37/STA25730

FR38/STA26365

FR35/STA24460

L_MF_010500_1_0050102_01_00

Fuselage Frames/StationsSection 13 - A380-800 Models

1-5Page 6

Oct 01/09



FR22/STA16205FR23/STA16840

FR24/STA17475FR25/STA18110

FR26/STA18745FR27/STA19380

FR28/STA20015FR29/STA20650

FR30/STA21285FR31/STA21920

FR32/STA22555FR33/STA23190

FR34/STA23825

FR36/STA25095FR37/STA25730

FR38/STA26365

FR35/STA24460

L_MF_010500_1_0060102_01_00

Fuselage Frames/StationsSection 13 - A380-800F Models

1-5Page 7

Oct 01/09



FR74/STA49530FR73/STA48895

FR72/STA48260FR71/STA47625

FR70/STA46990FR69/STA46355

FR68/STA45720FR67/STA45085

FR66/STA44450

FR61/STA41275FR60/STA40640

FR59/STA40005FR58/STA39370

FR57/STA38735FR56/STA38100

FR55/STA37439FR54/STA36779

FR53/STA36119FR52/STA35458

FR51/STA34798FR50/STA34137

FR49/STA33477FR48/STA32817

FR65/STA43815FR64/STA43180

FR63/STA42545FR62/STA41910

FR47/STA32156FR46/STA31496

FR45/STA30835FR44/STA30175

FR43/STA29540FR42/STA28905

FR41/STA28270FR40/STA27635

FR39/STA27000FR38/STA26365

L_MF_010500_1_0070102_01_00

Fuselage Frames/StationsSection 15/21 - A380-800 Models

1-5Page 8

Oct 01/09



FR74/STA49530FR73/STA48895

FR72/STA48260FR71/STA47625

FR70/STA46990FR69/STA46355

FR68/STA45720FR67/STA45085

FR66/STA44450

FR61/STA41275FR60/STA40640

FR59/STA40005FR58/STA39370

FR57/STA38735FR56/STA38100

FR55/STA37439FR54/STA36779

FR53/STA36119FR52/STA35458

FR51/STA34798FR50/STA34137

FR49/STA33477FR48/STA32817

FR65/STA43815FR64/STA43180

FR63/STA42545FR62/STA41910

FR47/STA32156FR46/STA31496

FR45/STA30835FR44/STA30175

FR43/STA29540FR42/STA28905

FR41/STA28270FR40/STA27635

FR39/STA27000FR38/STA26365

L_MF_010500_1_0080102_01_00

Fuselage Frames/StationsSection 15/21 - A380-800F Models

1-5Page 9

Oct 01/09



FR84/STA55880

FR74/STA49530

FR75/STA50165

FR76/STA50800

FR77/STA51435

FR78/STA52070

FR79/STA52705

FR80/STA53340

FR82/STA54610

FR83/STA55245

FR81/STA53975

FR85/STA56515

FR86/STA57150

FR87/STA57785

FR88/STA58420

FR89/STA59055

FR90/STA59690

FR91/STA60325

FR92/STA60960

FR93/STA61595

FR94/STA62230

FR95/STA62865

L_MF_010500_1_0090102_01_00

Fuselage Frames/StationsSection 18 - A380-800 Models

1-5Page 10

Oct 01/09



FR84/STA55880

FR74/STA49530

FR75/STA50165

FR76/STA50800

FR77/STA51435

FR78/STA52070

FR79/STA52705

FR80/STA53340

FR82/STA54610

FR83/STA55245

FR81/STA53975

FR85/STA56515

FR86/STA57150

FR87/STA57785

FR88/STA58420

FR89/STA59055

FR90/STA59690

FR91/STA60325

FR92/STA60960

FR93/STA61595

FR94/STA62230

FR95/STA62865

L_MF_010500_1_0100102_01_00

Fuselage Frames/StationsSection 18 - A380-800F Models

1-5Page 11

Oct 01/09



X = 77730

FR103/STA67945

FR104/STA68580

FR105/STA69260

FR106/STA69940

FR107/STA70620

FR108/STA71300

FR109/STA71810

FR110/STA72320

FR95/STA62865

FR96/STA63500

FR97/STA64135

FR98/STA64770

FR99/STA65405

FR100/STA66040

FR101/STA66675

FR102/STA67310

FR95

SECTION 19 SECTION 19 − 1

FR110

L_MF_010500_1_0110102_01_00

Fuselage Frames/StationsSection 19

1-5Page 12

Oct 01/09


1-6 Wing Ribs / Stations


Wing Ribs / Stations

1. General

This section shows wing ribs/stations and dimensions.

1-6Page 1

Oct 01/09



STA0RIB1

RIB7

RIB10

RIB37

RIB34

RIB31

RIB28

RIB25

RIB22

RIB19

RIB16

RIB13

RIB4

RIB40

RIB43

RIB46

RIB49

A B C

LH WING SHOWNRH WING SYMMETRICAL

STA2516

STA4813

STA7066

STA9180

STA11409

STA13456

STA15654

STA17796

STA19903

STA22011

STA24038

STA26098

STA28325

STA30535

STA32712

STA34889

NOTE:

FRONT SPAR

THE STATION NUMBER IS THE DISTANCEIN MILLIMETERS BETWEEN RIB1 (STA0) ANDEACH RIB2 THRU 49. THE DISTANCE IS MEASURED (AT 90 DEGREES TO RIB1)BETWEEN RIB1 AND THE INTERSECTION OFEACH RIB DATUM WITH THE FRONT SPARDATUM

A

L_MF_010600_1_0010101_01_00

Wing Ribs/StationsWing Ribs/Stations (Sheet 1)

1-6Page 2

Oct 01/09



L_MF_010600_0_AAM0_02_00

RIB3

RIB6

RIB9

RIB12

RIB15

RIB18

RIB21

RIB24

RIB27

RIB30

RIB33

RIB36

RIB39

RIB42

RIB45

RIB48


STA1856

STA4049

STA6349

STA8451

STA10674

STA12723

STA14921

STA17187

STA19186

STA21337

STA23366

STA25381

STA27583

STA29809

STA31986

STA34163NOTE:THE STATION NUMBER IS THE DISTANCEIN MILLIMETERS BETWEEN RIB1 (STA0) ANDEACH RIB2 THRU 49. THE DISTANCE IS MEASURED (AT 90 DEGREES TO RIB1)BETWEEN RIB1 AND THE INTERSECTION OFEACH RIB DATUM WITH THE FRONT SPARDATUM

FRONT SPAR

B

L_MF_010600_1_0020101_01_00


1-6Page 3

Oct 01/09



RIB2

RIB5

RIB47

RIB44

RIB41

RIB38

RIB35

RIB32

RIB29

RIB26

RIB23

RIB20

RIB17

RIB14

RIB11

RIB8


STA1074

STA3289

STA5581

STA7785

STA9946

STA11998

STA14189

STA16390

STA18469

STA20620

STA22704

STA24709

STA26841

STA29067

STA31260

STA33437NOTE:THE STATION NUMBER IS THE DISTANCEIN MILLIMETERS BETWEEN RIB1 (STA0) ANDEACH RIB2 THRU 49. THE DISTANCE IS MEASURED (AT 90 DEGREES TO RIB1)BETWEEN RIB1 AND THE INTERSECTION OFEACH RIB DATUM WITH THE FRONT SPARDATUM

FRONT SPAR

C

L_MF_010600_1_0030101_01_00


1-6Page 4

Oct 01/09



A380−700

9235.2 mm(363.59 in)

A380−800/800F

7330.2 mm(288.59 in)

A380−900

4155.2 mm(163.59 in)

AIRPLANE DATUM

4669

9 m

m (

1838

.54

in)

4809

4 m

m (

1893

.47

in)

5109

7 m

m (

2011

.69

in)

5258

8 m

m (

2070

.39

in)

5407

1 m

m (

2128

.79

in)

25973 mm (1022.56 in)

17649 mm (694.84 in)

21868 mm (860.95 in)

(368.66 in)9364 mm

(531.22 in)13493 mm

L_MF_010600_1_0040101_01_00

Wing Ribs/StationsFlap Track Positions

1-6Page 5

Oct 01/09




Center of Gravity Limits

1. General

This section gives center of gravity limits.

1-7Page 1

Oct 01/09



L_MF_010700_1_0040101_01_00

2728

2930

3132

3334

3536

3738

3940

4142

4344

4546

47

2725

2931

3335

3739

4143

4547

49%

MA

C26

0

280

300

320

340

360

380

400

420

440

460

480

500

520

540

560

580

260

280

300

320

340

360

380

400

420

440

460

480

500

520

540

560

580

Aircraft Weight (kg x 1000)

Max

. Tak

e−of

f Wei

ght =

510

000

kg

Max

. Lan

ding

Wei

ght =

394

000

kg

Max

. Zer

o F

uel W

eigh

t = 3

72 0

00 k

g

Take−off /

Landing

Take−off /Landing

Flight

Flight

Center of Gravity LimitsMTOW 510000 kg- A380-800 Models

1-7Page 2

Oct 01/09



260

280

300

320

340

360

380

400

420

440

460

480

500

520

540

560

580

260

280

300

320

340

360

380

400

420

440

460

480

500

520

540

560

580

3527

2829

3031

3233

3436

3738

3940

4142

4344

4546

47

3533

3129

2725

3739

4143

4547

49%

MA

C

AIRCRAFT WEIGHT (kg x 1000)

TAKE−OFF

MA

X. Z

ER

O F

UE

L W

EIG

HT

= 3

61 0

00kg

MA

X. L

AN

DIN

G W

EIG

HT

= 3

86 0

00kg LANDING

TAKE−OFF/LANDING

TAKE−OFF/LANDING

FLIGHT

MA

X. T

AK

E−

OF

F W

EIG

HT

= 5

60 0

00kg FLIGHT

L_MF_010700_1_0010101_01_00

Center of Gravity LimitsMTOW 560000 kg - A380-800 Models

1-7Page 3

Oct 01/09



260

280

300

320

340

360

380

400

420

440

460

480

500

520

540

560

580

260

280

300

320

340

360

380

400

420

440

460

480

500

520

540

560

580

3527

2829

3031

3233

3436

3738

3940

4142

4344

4546

47

3533

3129

2725

3739

4143

4547

49%

MA

C


L_MF_010700_1_0050101_01_00

TAKE−OFF

MA

X. L

AN

DIN

G W

EIG

HT

= 3

91 0

00kg

MA

X. Z

ER

O F

UE

L W

EIG

HT

= 3

66 0

00kg

MA

X. T

AK

E−

OF

F W

EIG

HT

= 5

69 0

00kg

FLIGHT TAKE−OFF/LANDIN

G

LANDING

TAKE−OFF/LANDING

FLIGHT

Center of Gravity LimitsMTOW 569000 kg - A380-800 Models

1-7Page 4

Oct 01/09



260

280

300

320

340

360

380

400

420

440

460

480

500

520

540

560

580

260

280

300

320

340

360

380

400

420

440

460

480

500

520

540

560

580

3527

2829

3031

3233

3436

3738

3940

4142

4344

4546

47

3533

3129

2725

3739

4143

4547

49%

MA

C


MA

X. L

AN

DIN

G W

EIG

HT

= 4

27 0

00kg

FLIGHT

TAKE−OFF/LANDING

TAKE−OFF

MA

X. T

AK

E−

OF

F W

EIG

HT

= 5

90 0

00kg

MA

X. Z

ER

O F

UE

L W

EIG

HT

= 4

02 0

00kg LANDING

FLIGHT

TAKE−OFF/LANDING

L_MF_010700_1_0030101_01_00

Center of Gravity LimitsMTOW 590000 kg - A380-800F Models

1-7Page 5

Oct 01/09



260

280

300

320

340

360

380

400

420

440

460

480

500

520

540

560

580

260

280

300

320

340

360

380

400

420

440

460

480

500

520

540

560

580

3527

2829

3031

3233

3436

3738

3940

4142

4344

4546

47

3533

3129

2725

3739

4143

4547

49%

MA

C


L_MF_010700_1_0060101_01_00

MA

X. L

AN

DIN

G W

EIG

HT

= 4

27 0

00kg

MA

X. Z

ER

O F

UE

L W

EIG

HT

= 3

79 0

00kg

FLIGHT TAKE−OFF/LANDIN

G

TAKE−OFF

MA

X. T

AK

E−

OF

F W

EIG

HT

= 6

00 0

00kg

LANDING

FLIGHT

TAKE−OFF/LANDING

Center of Gravity LimitsMTOW 600000 kg - A380-800F Models

1-7Page 6

Oct 01/09




Airplane Attitude

1. GeneralThis section contains the graphs that show the approximate deflections of:- the tires- the Nose Landing Gear shock absorbers- the Wing Landing Gear shock absorbers- the Body Landing Gear shock absorbers.When different combinations of deflated tires are considered, the figures are approximate.

NOTE : These aircraft have radial or bias ply tires installed. They are required to have the samestatic loaded radius. There are many manufacturers of radial and bias ply tires, each makeof tire could give different deflections. The graphs that follow are for Michelin radial plytires:

Tires DimensionsA380-800 A380-800F

NLG 1270 x 455R22 32PR 50 x 20R22 34PRWLG 1400 x 530R23 40PR 1400 x 530R23 42PRBLG 1400 x 530R23 40PR 1400 x 530R23 42PR

1-8Page 1

Oct 01/09



L_MF_010800_1_0010101_01_01

300

320

340

360

380

400

420

440

460

480

500

520

540

560

260 300 340 380 420 460 500 540 580

AIRCRAFT GROSS WEIGHT

SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

mm

)

11.8

12.8

13.8

14.8

15.8

16.8

17.8

18.8

19.8

20.8

21.8

120011001000900800700600

(x1000 kg)

(x1000 lb)

SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

in )

CG POSITION29 % mac37.5 % mac41 % mac43 % mac

NLG Shock-Absorber DeflectionNLG Shock-Absorber Deflection - A380-800 Models

1-8Page 2

Oct 01/09



L_MF_010800_1_0020101_01_01

300

320

340

360

380

400

420

440

460

480

500

520

540

560

260 300 340 380 420 460 500 540 580 620


SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

mm

)

11.8

12.8

13.8

14.8

15.8

16.8

17.8

18.8

19.8

20.8

21.8

1300120011001000900800700600

(x1000 kg)

(x1000 lb)

SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

in )

CG POSITION29 % mac36 % mac40 % mac43 % mac

NLG Shock-Absorber DeflectionNLG Shock-Absorber Deflection - A380-800F Models

1-8Page 3

Oct 01/09



L_MF_010800_1_0030101_01_01

CG POSITION29 % mac33 % mac37.5 % mac41 % mac43 % mac

1270 x 455R22 32PR TIRESTIRE PRESSURE CONSTANT AT 14.1 bar (205 psi)

30

40

50

60

70

80

90

100

110

120

130

260 300 340 380 420 460 500 540 580


TIR

E D

EF

LEC

TIO

NS

( m

m )

1.2

1.5

1.8

2.1

2.4

2.7

3.0

3.3

3.6

3.9

4.2

4.5

4.8

5.1

120011001000900800700600

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)ALL TIRES INFLATED

50 % SHOCK−ABSORBERLOAD ON TIRE

NLG Tire Deflection 50 % LoadNLG Tire Deflection 50 % Load - A380-800 Models

1-8Page 4

Oct 01/09



L_MF_010800_1_0040101_01_01


60

80

100

120

140

160

180

200

220

240

260 300 340 380 420 460 500 540 580


TIR

E D

EF

LEC

TIO

NS

( m

m )

2.4

2.9

3.4

3.9

4.4

4.9

5.4

5.9

6.4

6.9

7.4

7.9

8.4

8.9

9.4

120011001000900800700600

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)

CG POSITION 29 % mac 33 % mac 37.5 % mac 41 % mac 43 % mac

ONE TIRE DEFLATED100 % SHOCK−ABSORBER

LOAD ON TIRE

NLG Tire Deflection 100 % LoadNLG Tire Deflection 100 % Load - A380-800 Models

1-8Page 5

Oct 01/09



L_MF_010800_1_0050101_01_01


30

40

50

60

70

80

90

100

110

120

130

260 290 320 350 380 410 440 470 500 530 560 590 620


TIR

E D

EF

LEC

TIO

NS

( m

m )

1.2

1.5

1.8

2.1

2.4

2.7

3.0

3.3

3.6

3.9

4.2

4.5

4.8

5.1

600 700 800 900 1000 1100 1200 1300

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)

CG POSITION29 % mac33 % mac36 % mac40 % mac43 % mac

ALL TIRES INFLATED 50 % SHOCK−ABSORBER

LOAD ON TIRE

NLG Tire Deflection 50 % LoadNLG Tire Deflection 50 % Load - A380-800F Models

1-8Page 6

Oct 01/09



L_MF_010800_1_0060101_01_01

60

80

100

120

140

160

180

200

220

240

260 290 320 350 380 410 440 470 500 530 560 590 620


TIR

E D

EF

LEC

TIO

NS

( m

m )

2.4

2.9

3.4

3.9

4.4

4.9

5.4

5.9

6.4

6.9

7.4

7.9

8.4

8.9

9.4

600 700 800 900 1000 1100 1200 1300

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)


29 % mac33 % mac36 % mac40 % mac43 % mac

CG POSITION

ONE TIRE DEFLATED 100 % SHOCK−ABSORBER

LOAD ON TIRE

NLG Tire Deflection 100 % LoadNLG Tire Deflection 100 % Load - A380-800F Models

1-8Page 7

Oct 01/09



L_MF_010800_1_0070101_01_01

345

360

375

390

405

420

435

450

465

480

495

510

260 300 340 380 420 460 500 540 580


SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

mm

)

13.6

14.6

15.6

16.6

17.6

18.6

19.6

120011001000900800700600

(x1000 kg)

(x1000 lb)

SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

in )

CG POSITION29 % mac37.5 % mac43 % mac

WLG Shock-Absorber DeflectionWLG Shock-Absorber Deflection - A380-800 Models

1-8Page 8

Oct 01/09



L_MF_010800_1_0080101_01_01

290

310

330

350

370

390

410

430

450

470

490

260 300 340 380 420 460 500 540 580 620


SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

mm

)

11.4

12.4

13.4

14.4

15.4

16.4

17.4

18.4

1300120011001000900800700600

(x1000 kg)

(x1000 lb)

SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

in )

CG POSITION29 % mac36 % mac43 % mac

WLG Shock-Absorber DeflectionWLG Shock-Absorber Deflection - A380-800F Models

1-8Page 9

Oct 01/09



L_MF_010800_1_0090101_01_01

50

55

60

65

70

75

80

85

90

95

100

105

260 300 340 380 420 460 500 540 580


TIR

E D

EF

LEC

TIO

NS

( m

m )

2.0

2.2

2.4

2.6

2.8

3.0

3.2

3.4

3.6

3.8

4.0

120011001000900800700600

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)

1400 x 530R23 40PRTIRE PRESSURE CONSTANT AT 15 bar (218 psi)

CG POSITION 29 % mac 33 % mac 37.5 % mac 43 % mac

ALL TIRES INFLATED25 % SHOCK−ABSORBER

LOAD ON TIRE

WLG Tire Deflection 25 % LoadWLG Tire Deflection 25 % Load - A380-800 Models

1-8Page 10

Oct 01/09



L_MF_010800_1_0100101_01_01

90

100

110

120

130

140

150

160

170

180

190

260 300 340 380 420 460 500 540 580


TIR

E D

EF

LEC

TIO

NS

( m

m )

3.5

3.8

4.1

4.4

4.7

5.0

5.3

5.6

5.9

6.2

6.5

6.8

7.1

7.4

120011001000900800700600

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)



ONE TIRE DEFLATED50 % SHOCK−ABSORBER

LOAD ON TIRE

WLG Tire Deflection 50 % LoadWLG Tire Deflection 50 % Load - A380-800 Models

1-8Page 11

Oct 01/09



L_MF_010800_1_0110101_01_01

45

50

55

60

65

70

75

80

85

90

95

100

105

260 290 320 350 380 410 440 470 500 530 560 590 620


TIR

E D

EF

LEC

TIO

NS

( m

m )

1.8

2.0

2.2

2.4

2.6

2.8

3.0

3.2

3.4

3.6

3.8

4.0

600 700 800 900 1000 1100 1200 1300

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)

1400 x 530R23 42 PRTIRE PRESSURE CONSTANT AT 16.1 bar (234 psi)

ALL TIRES INFLATED 25 % SHOCK−ABSORBER

LOAD ON TIRE

CG POSITION 29 % mac 33 % mac 36 % mac 40 % mac 43 % mac

WLG Tire Deflection 25 % LoadWLG Tire Deflection 25 % Load - A380-800F Models

1-8Page 12

Oct 01/09



L_MF_010800_1_0120101_01_01

85

95

105

115

125

135

145

155

165

175

185

260 290 320 350 380 410 440 470 500 530 560 590 620


TIR

E D

EF

LEC

TIO

NS

( m

m )

3.3

3.6

3.9

4.2

4.5

4.8

5.1

5.4

5.7

6.0

6.3

6.6

6.9

7.2

600 700 800 900 1000 1100 1200 1300

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)



ONE TIRE DEFLATED 50 % SHOCK−ABSORBER

LOAD ON TIRE

WLG Tire Deflection 50 % LoadWLG Tire Deflection 50 % Load - A380-800F Models

1-8Page 13

Oct 01/09



L_MF_010800_1_0130101_01_01

350

370

390

410

430

450

470

490

510

260 300 340 380 420 460 500 540 580


SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

mm

)

13.8

14.8

15.8

16.8

17.8

18.8

19.8

120011001000900800700600

(x1000 kg)

(x1000 lb)

SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

in )

CG POSITION29 % mac37.5 % mac43 % mac

BLG Shock-Absorber DeflectionBLG Shock-Absorber Deflection - A380-800 Models

1-8Page 14

Oct 01/09



L_MF_010800_1_0140101_01_01

320

340

360

380

400

420

440

460

480

500

260 300 340 380 420 460 500 540 580 620


SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

mm

)

12.6

13.6

14.6

15.6

16.6

17.6

18.6

19.6

1300120011001000900800700600

(x1000 kg)

(x1000 lb)

SH

OC

K−

AB

SO

RB

ER

DE

FLE

CT

ION

S (

in )

CG POSITION29 % mac36 % mac43 % mac

BLG Shock-Absorber DeflectionBLG Shock-Absorber Deflection - A380-800F Models

1-8Page 15

Oct 01/09



50

55

60

65

70

75

80

85

90

95

100

105

260 300 340 380 420 460 500 540 580


TIR

E D

EF

LEC

TIO

NS

( m

m )

2.0

2.2

2.4

2.6

2.8

3.0

3.2

3.4

3.6

3.8

4.0

120011001000900800700600

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)

1400 x 530R23 40 PRTIRE PRESSURE CONSTANT AT 15 bar (218 psi)


ALL TIRES INFLATED16.7 % SHOCK−ABSORBER

LOAD ON TIRE

L_MF_010800_1_0150101_01_01

BLG Tire Deflection 16.7 % LoadBLG Tire Deflection 16.7 % Load - A380-800 Models

1-8Page 16

Oct 01/09



L_MF_010800_1_0160101_01_01

70

80

90

100

110

120

130

140

150

260 300 340 380 420 460 500 540 580


TIR

E D

EF

LEC

TIO

NS

( m

m )

2.8

3.1

3.4

3.7

4.0

4.3

4.6

4.9

5.2

5.5

5.8

120011001000900800700600

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)


TWO TIRES DEFLATED25 % SHOCK−ABSORBER

LOAD ON TIRE

CG POSITION29 % mac33 % mac37.5 % mac43 % mac

BLG Tire Deflection 25 % LoadBLG Tire Deflection 25 % Load - A380-800 Models

1-8Page 17

Oct 01/09



L_MF_010800_1_0170101_01_01

90

100

110

120

130

140

150

160

170

180

190

260 300 340 380 420 460 500 540 580


TIR

E D

EF

LEC

TIO

NS

( m

m )

3.5

3.8

4.1

4.4

4.7

5.0

5.3

5.6

5.9

6.2

6.5

6.8

7.1

7.4

120011001000900800700600

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)


ONE TIRE DEFLATED33.3 % SHOCK−ABSORBER

LOAD ON TIRE

CG POSITION29 % mac33 % mac37.5 % mac43 % mac

BLG Tire Deflection 33.3 % LoadBLG Tire Deflection 33.3 % Load - A380-800 Models

1-8Page 18

Oct 01/09



L_MF_010800_1_0180101_01_01

120

140

160

180

200

220

240

260

260 300 340 380 420 460 500 540 580


TIR

E D

EF

LEC

TIO

NS

( m

m )

4.7

5.2

5.7

6.2

6.7

7.2

7.7

8.2

8.7

9.2

9.7

10.2

120011001000900800700600

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)



FOUR TIRES DEFLATED50 % SHOCK−ABSORBER

LOAD ON TIRE

BLG Tire Deflection 50 % LoadBLG Tire Deflection 50 % Load - A380-800 Models

1-8Page 19

Oct 01/09



L_MF_010800_1_0190101_01_01

45

50

55

60

65

70

75

80

85

90

95

100

105

260 290 320 350 380 410 440 470 500 530 560 590 620


TIR

E D

EF

LEC

TIO

NS

( m

m )

1.8

2.0

2.2

2.4

2.6

2.8

3.0

3.2

3.4

3.6

3.8

4.0

600 700 800 900 1000 1100 1200 1300

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)



ALL TIRES INFLATED 16.7 % SHOCK−ABSORBER

LOAD ON TIRE

BLG Tire Deflection 16.7 % LoadBLG Tire Deflection 16.7 % Load - A380-800F Models

1-8Page 20

Oct 01/09



L_MF_010800_1_0200101_01_01

65

75

85

95

105

115

125

135

145

260 290 320 350 380 410 440 470 500 530 560 590 620


TIR

E D

EF

LEC

TIO

NS

( m

m )

2.6

2.9

3.2

3.5

3.8

4.1

4.4

4.7

5.0

5.3

5.6

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)


600 700 800 900 1000 1100 1200 1300


TWO TIRES DEFLATED 25 % SHOCK−ABSORBER

LOAD ON TIRE

BLG Tire Deflection 25 % LoadBLG Tire Deflection 25 % Load - A380-800F Models

1-8Page 21

Oct 01/09



L_MF_010800_1_0210101_01_01

85

95

105

115

125

135

145

155

165

175

185

260 290 320 350 380 410 440 470 500 530 560 590 620


TIR

E D

EF

LEC

TIO

NS

( m

m )

3.3

3.6

3.9

4.2

4.5

4.8

5.1

5.4

5.7

6.0

6.3

6.6

6.9

7.2

600 700 800 900 1000 1100 1200 1300

(x1000 kg)

(x1000 lb)

TIR

E D

EF

LEC

TIO

NS

( in

)


ONE TIRE DEFLATED 33.3 % SHOCK−ABSORBER

LOAD ON TIRE


BLG Tire Deflection 33.3 % LoadBLG Tire Deflection 33.3 % Load - A380-800F Models

1-8Page 22

Oct 01/09



L_MF_010800_1_0220101_01_01

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

260 290 320 350 380 410 440 470 500 530 560 590 620


TIR

E D

EF

LEC

TIO

NS

( m

m )

4.7

5.2

5.7

6.2

6.7

7.2

7.7

8.2

8.7

9.2

9.7

10.2

600 700 800 900 1000 1100 1200 1300

(x1000 kg)

TIR

E D

EF

LEC

TIO

NS

( in

)


(x1000 lb)


FOUR TIRES DEFLATED 50 % SHOCK−ABSORBER

LOAD ON TIRE

BLG Tire Deflection 50 % LoadBLG Tire Deflection 50 % Load - A380-800F Models

1-8Page 23

Oct 01/09



CONDITION AXLE ALL TIRES INFLATED, 25% OF GEAR LOAD ON EACH TIRE.HEIGHT OF AXLE A ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (25% LOAD).HEIGHT OF AXLE B ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (25% LOAD).

A

B

1

HEIGHT OF AXLE A ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (50% LOAD).HEIGHT OF AXLE B ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (25% LOAD).

A

B

2

= TIRE RADIUS − TIRE DEFLECTION (50% LOAD).HEIGHT OF AXLE B ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (50% LOAD).

A

B

3

HEIGHT OF AXLE A ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (25% LOAD).HEIGHT OF AXLE B ABOVE GROUND= RIM OUTER FLANGE RADIUS.

A

B

4

HEIGHT OF AXLE A ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (50% LOAD).HEIGHT OF AXLE B ABOVE GROUND= RIM OUTER FLANGE RADIUS.

A

B

5

25% 25%

25% 25%

50% 0%

25% 25%

50% 0%

50% 0%

25% 25%

25% 25%

50% 0%

25% 25%

ONE TIRE DEFLATED ON ONE AXLE, 50% OF GEAR LOADON INFLATED TIRE, 0% ON THE DEFLATED TIRE.

ONE TIRE DEFLATED ON BOTH AXLES, 50% OF GEAR LOADON BOTH INFLATED TIRES, 0% ON THE DEFLATED TIRES.

TWO TIRES DEFLATED ON ONE AXLE, 25% OF GEAR LOAD ON EACHINFLATED TIRE, 25% ON THE RIMS OF EACH DEFLATED TIRE.

THE RIMS OF EACH DEFLATED TIRE ON AXLE B.

THREE TIRES DEFLATED, 50% OF GEAR LOAD ON THE INFLATEDTIRE, 0% ON THE DEFLATED TIRE ON THE SAME AXLE, 25% ON

TIRE SIZE 1400 X 530 R23 40PR

NOTE:

MAXIMUM GROWN TIRE (UNLOADED) RADIUS = 722 mm (28.4 in).RIM OUTER FLANGE RADIUS = 356 mm (14 in).

TWO EXAMPLES OF HOW TO USE THE TIRE INFLATED/DEFLATED GRAPHS AS SHOWN.ASSUME AN AIRCRAFT WEIGHT OF 510 000 kg (1 124 360 lb) WITH THE CG AT 37.4% MAC.

EXAMPLE 2

FROM THE GRAPHS,

EXAMPLE 1FOR CONDITION 2,HEIGHT OF AXLE A ABOVE GROUND = 722 −165 = 557 mm (21.9 in).HEIGHT OF AXLE B ABOVE GROUND = 722 −92 = 630 mm (24.8 in).

FOR CONDITION 5,HEIGHT OF AXLE A ABOVE GROUND = 722 −165 = 557 mm (21.9 in).HEIGHT OF AXLE B ABOVE GROUND = 356 mm (14 in) (RIM OUTER FLANGE RADIUS).

A TIRE THAT CARRIES 25% OF THE WLG LOADS DEFLECTS 92 mm (3.6 in).A TIRE THAT CARRIES 50% OF THE WLG LOADS DEFLECTS 165 mm (6.5 in).

HEIGHT OF AXLE A ABOVE GROUND

CONDITIONS 1 TO 5 SHOW POSSIBLE DAMAGE SITUATIONS FOR TIRES ON WLG BOGIE.

L_MF_010800_1_0230101_01_00

WLG Tire Deflection NotesWLG Tire Deflection

1-8Page 24

Oct 01/09



CONDITION AXLE ALL TIRES INFLATED, 16.7% OF GEAR LOAD ON EACH TIRE.HEIGHT OF AXLES A, B, C ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (16.7% LOAD).

A

B1

C

16.7%

16.7%

16.7%

16.7%

16.7%

16.7%

A

B2

C

33.3%

16.7%

16.7%

0%

16.7%

16.7%

A

B3

C

33.3%

33.3%

16.7%

0%

0%

16.7%

A

B4

C

33.3%

33.3%

33.3%

0%

0%

0%

THEN FOR CONDITION 2,HEIGHT OF AXLE A ABOVE GROUND = 722 −165 = 557 mm (21.9 in).HEIGHT OF AXLE C ABOVE GROUND = 722 −92 = 630 mm (24.8 in).

FROM THE GRAPHS, A TIRE THAT CARRIES 16.7% OF THE BLG LOADS DEFLECTS 92 mm (3.6 in).A TIRE THAT CARRIES 25% OF THE BLG LOADS DEFLECTS 129 mm (5.1 in).A TIRE THAT CARRIES 33.3% OF THE BLG LOADS DEFLECTS 165 mm (6.5 in).

EXAMPLE OF HOW TO USE THE TIRE INFLATED/DEFLATED GRAPHS AS SHOWN.ASSUME AN AIRCRAFT WEIGHT IS 510 000 kg (1 124 360 lb) WITH THE CG AT 37.4% MAC.

CONDITIONS 1 TO 4 SHOW POSSIBLE DAMAGE SITUATIONS FOR TIRES ON BLG BOGIE.NOTE:TIRE SIZE 1400 X 530 R23 40PRMAXIMUM GROWN TIRE (UNLOADED) RADIUS = 722 mm (28.4 in).RIM OUTER FLANGE RADIUS = 356 mm (14 in).

HEIGHT OF AXLE A ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (33.3% LOAD).

HEIGHT OF AXLE C ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (16.7% LOAD).

ONE TIRE DEFLATED ON ONE AXLE, 33.3% OF GEAR LOAD ONINFLATED TIRE, 0% ON THE DEFLATED TIRE.


HEIGHT OF AXLE C ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (33.3% LOAD).

ONE TIRE DEFLATED ON THREE AXLES, 33.3% OF GEAR LOAD ONEACH INFLATED TIRE, 0% ON THE DEFLATED TIRES.


HEIGHT OF AXLE C ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (33.3% LOAD)

ONE TIRE DEFLATED ON TWO AXLES, 33.3% OF GEAR LOAD ONEACH INFLATED TIRE, 0% ON THE DEFLATED TIRE.

L_MF_010800_1_0240101_01_00

BLG Tire Deflection NotesBLG Tire Deflection

1-8Page 25

Oct 01/09



CONDITION AXLE FOUR TIRES DEFLATED, 50% OF GEAR LOAD ON EACHINFLATED TIRE, 0% ON THE DEFLATED TIRES.A

B5

C

50%

50%

0%

0%

0%

0%

A

B6

C

50%

0%

25%

0%

0%

25%

A

B7

C

25%

0%

25%

25%

0%

25%

A

B8

C

25%

0%

25%

25%

0%

25%

THEN FOR CONDITION 8,HEIGHT OF AXLE A ABOVE GROUND = 722 −129 = 593 mm (23.3 in).HEIGHT OF AXLE C ABOVE GROUND = 356 mm (14 in) (RIM OUTER FLANGE RADIUS).

FROM THE GRAPHS, A TIRE THAT CARRIES 16.7% OF THE BLG LOADS DEFLECTS 92 mm (3.6 in).A TIRE THAT CARRIES 25% OF THE BLG LOADS DEFLECTS 129 mm (5.1 in).A TIRE THAT CARRIES 33.3% OF THE BLG LOADS DEFLECTS 165 mm (6.5 in).

EXAMPLE OF HOW TO USE THE TIRE INFLATED/DEFLATED GRAPHS AS SHOWN.ASSUME AN AIRCRAFT WEIGHT IS 510 000 kg (1 124 360 lb) WITH THE CG AT 37.4% MAC.

CONDITIONS 5 TO 8 SHOW POSSIBLE DAMAGE SITUATIONS FOR TIRES ON BLG BOGIE.NOTE:TIRE SIZE 1400 X 530 R23 40PRMAXIMUM GROWN TIRE (UNLOADED) RADIUS = 722 mm (28.4 in).RIM OUTER FLANGE RADIUS = 356 mm (14 in).

AXLE C. HEIGHT OF AXLE A ABOVE GROUND

HEIGHT OF AXLE C ABOVE GROUND= RIM OUTER FLANGE RADIUS.

FIVE TIRES DEFLATED, 50% OF GEAR LOAD ON INFLATED TIRE,0% ON THE DEFLATED TIRE ON THE SAME AXLE.

HEIGHT OF AXLE C ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (50% LOAD).

HEIGHT OF AXLE A ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (50% LOAD).

25% OF GEAR LOAD ON THE RIMS OF THE DEFLATED TIRES ON

HEIGHT OF AXLE A ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (25% LOAD).

HEIGHT OF AXLE C ABOVE GROUND= TIRE RADIUS − TIRE DEFLECTION (25% LOAD).

TWO TIRES DEFLATED ON CENTER AXLE, 25% OF GEAR LOAD ONEACH INFLATED TIRE.

AXLE C.HEIGHT OF AXLE A ABOVE GROUND

HEIGHT OF AXLE C ABOVE GROUND= RIM OUTER FLANGE RADIUS.

FOUR TIRES DEFLATED, 25% OF GEAR LOAD ONEACH INFLATED TIRE.25% OF GEAR LOAD ON THE RIMS OF THE DEFLATED TIRES ON

= TIRE RADIUS − TIRE DEFLECTION (50% LOAD).

= TIRE RADIUS − TIRE DEFLECTION (25% LOAD).

L_MF_010800_1_0250101_01_00

BLG Tire Deflection Notes

1-8Page 26

Oct 01/09


1-9 Ground Clearances


Ground Clearances

1. General

This section gives the heights of various points of the aircraft, above the ground, for different aircraftconfigurations. Dimensions in the tables are approximate and will vary with tire type and conditions.

1-9Page 1

Oct 01/09



D

C1F1

E1

F3F2C2

E2

H G

K2 K1

L2

L3 L4 L5 L6 J2 J1

M1M2M3M5 M4 U1U2U3

NOTE: MAXIMUM JACKING WEIGHT = 333 700 kg

C3

L_MF_010900_1_0010102_01_01

m ft m ft m ft m ft

MRWAFT CG

290tMID CG

A/C JACKEDFDL = 7.2 m

(23.6 ft)

ft

MRW (562t)FWD CG

10.010.3

23.435.335.67.77.55.4

30.279.324.817.33.56.210.113.4

3.113.10

7.2110.8110.802.402.241.669.11

24.087.505.221.081.903.074.08

3.113.10

7.2110.8110.802.402.241.669.11

24.087.505.221.081.903.074.08

10.210.2

23.735.535.47.97.45.5

29.979.024.617.13.56.210.113.4

3.303.23

7.42

2.592.381.829.2024.178.225.941.302.273.264.31

4.2

10.810.6

24.336.135.98.57.86.0

30.279.3

19.5

7.410.714.1 4.34

1.25

3.193.32

7.2510.9011.032.492.461.829.43

24.408.336.05

2.273.27

4.1

10.510.9

23.835.836.28.28.16.0

30.980.127.319.8

7.510.714.2

5.125.12

9.2212.8212.824.414.273.6811.1426.1110.12

3.147.84

4.135.126.18

16.816.8

30.242.142.114.514.012.136.685.733.225.710.313.516.820.3

300tAFT CG

11.0010.93

27.0

10.7 3.22 10.6 3.36 11.0 3.43 11.3 5.24 17.2

16.716.816.917.025.825.926.0

5.145.135.135.127.897.887.88

5.145.135.135.127.897.887.88

16.916.816.816.825.925.925.8

5.325.295.265.258.068.038.01

17.517.317.317.226.526.326.3

5.235.295.345.378.008.078.11

17.217.417.517.626.326.526.6

7.157.157.15

9.909.909.90

23.523.523.523.532.532.532.5

7.15

15.316.417.116.6

4.654.995.185.14

4.654.995.185.14

15.316.417.016.9

4.935.345.615.34

16.217.518.417.5

4.985.405.675.19

16.417.718.617.0

6.817.227.507.15

22.423.724.623.5

CONFIGURATIONA/C

mC1C2

DE1E2F1F2F3GHJ1J2K1K2L2L3

1.05

3.053.14

7.1310.7610.842.352.271.669.21

24.187.555.27

1.903.084.10

C3 3.27

M2M3M4M5U1U2U3

5.095.135.165.187.857.907.92

L4L5L6M1

4.675.015.215.07

Ground ClearancesA380-800 Models

1-9Page 2

Oct 01/09



K2 K1

L2L3 L4 L5 L6 J2 J1

F3

D A1 C3

C1F1

E1 E2

G H

F2C2

C4

A5A6

A/CCONFIGURATION

MRWFWD CG

MRWAFT CG

260tMID CG

m ft m ft m ft m ftA1

C1C2C3C4DE1E2F1F2F3GHJ1J2K1K2L2L3L4L5L6

m ft

10.2

5.4 5.4

A5A6

300tAFT CG

A/C JACKEDFDL = 7.3 m

(24.0 ft)

5.035.167.803.023.127.935.157.0910.7310.832.322.261.639.21

24.187.545.261.031.883.054.084.654.995.19

16.516.925.69.9

26.016.923.335.235.57.67.4

30.279.324.7

3.46.210.013.415.316.417.0

5.125.107.873.093.077.995.107.19

10.7910.782.382.221.649.08

24.057.485.201.051.883.054.064.634.965.16

16.816.725.810.110.126.216.723.635.435.47.87.3

29.878.924.517.13.56.210.013.315.216.316.9

5.345.248.083.303.228.195.257.4111.0010.922.592.371.819.19

24.168.215.931.292.263.254.304.935.335.60

17.517.226.510.810.626.917.224.336.135.88.57.85.930.179.326.919.44.27.410.714.116.217.518.4

5.215.417.993.213.368.125.387.2710.9211.072.512.491.859.48

24.458.376.081.282.303.304.375.025.435.71

17.117.726.210.511.026.617.723.835.836.38.28.26.131.180.227.520.04.27.510.814.316.517.818.7

7.257.2510.005.225.2210.127.259.3212.9212.924.514.373.7811.2426.2110.227.94

4.235.226.286.917.327.60

23.823.832.817.117.133.223.830.642.442.414.814.312.436.986.033.526.010.613.917.120.622.724.024.9

17.23.24

L_MF_010900_1_0020102_01_00

Ground ClearancesA380-800F Models

1-9Page 3

Oct 01/09



A B CD E F GH J K L

m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

3.95 12.9 3.98 13.0 4.15 13.6 4.10 13.4DN1 INBDEND

DN1/DN2 4.60 15.1 4.62 15.2 4.82 15.8 4.78 15.7DN2 OUTBD

END5.12 16.8 5.13 16.8 5.35 17.5 5.32 17.5

SLAT 2 INBDEND

5.12 16.8 5.13 16.8

5.34 17.5 5.35 17.6 5.62 18.4

17.6 5.35 17.5

SLAT 2/3SLAT 3/4 5.53 18.1 5.53 18.1 5.84 19.2 5.85 19.2

SLAT 4 OUTBDEND

5.65 18.5 5.65 18.5 6.02 19.8 6.04 19.8

SLAT 5 INBDEND

5.78 19.0 5.77 18.9 6.18 20.3 6.21 20.4

SLAT 5/6SLAT 6/7

SLAT 7 OUTBDEND

5.895.986.05

19.319.619.8

5.875.966.02

19.319.619.7

6.356.526.67

20.821.421.9

6.406.586.75

21.021.622.1

A

BC

D

EFG

H

JKL

A380−800 LEADING EDGE SLATS EXTENDED

18.45.61

3.36

L_MF_010900_1_0030103_01_00

Ground ClearancesLeading Edge Slats - Extended - A380-800 Models

1-9Page 4

Oct 01/09



m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

12.9 13.0 13.6DN1 INBDEND

DN1/DN2DN2 OUTBD

END16.8 17.5

SLAT 2 INBDEND

16.8

17.5

17.6

SLAT 2/3SLAT 3/4 18.1 5.84 19.2

SLAT 4 OUTBDEND

18.5 18.5

SLAT 5 INBDEND

18.9

SLAT 5/6SLAT 6/7

SLAT 7 OUTBDEND

19.319.619.8 19.7

20.821.421.9

A

BC

D

EFG

H

JKL

3.92 3.95 4.14 4.12 13.5

4.57 15.0 4.60 15.1 4.81 15.8 4.80 15.85.09 16.7 5.11 5.34 5.35 17.6

5.09 16.7 5.11 5.36 5.37 17.6

5.32 5.33 17.5 5.61 18.4 5.64 18.55.50 18.1 5.50 5.88 19.35.63 5.62 6.01 19.7 6.07 19.9

5.76 18.9 5.75 6.17 20.2 6.24 20.5

5.87 5.85 19.2 6.35 6.43 21.15.97 5.94 19.5 6.51 6.61 21.76.03 5.99 6.66 6.78 22.2

A380−800F LEADING EDGE SLATS EXTENDED

A B CD E F GH J K L

L_MF_010900_1_0040102_01_00

Ground ClearancesLeading Edge Slats - Extended - A380-800F Models

1-9Page 5

Oct 01/09



m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

AB

1.54 5.0 1.53 5.0 1.68 5.5 1.71 5.63.43 11.3 3.42 11.2 3.62 11.9 3.66 12.0

CD

4.56 15.0 4.54 14.9 4.86 16.0 4.92 16.25.11 16.8 5.08 16.7 5.53 18.1 5.61 18.4

INNER ENDINNER/MIDMID OUTEROUTER END

m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

AB

5.0 5.511.9

CD 18.1


1.52 1.50 4.9 1.67 1.74 5.73.41 11.2 3.39 11.1 3.61 3.70 12.14.54 14.9 4.52 14.8 4.86 15.9 4.96 16.35.10 16.7 5.06 16.6 5.52 5.64 18.5

ABCD

A380−800 FLAPS EXTENDED

A380−800F FLAPS EXTENDED

L_MF_010900_1_0050102_01_00

Ground ClearancesTrailing Edge Flaps - Extended

1-9Page 6

Oct 01/09



m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

ABC

DEFGHJK

SPOILER 1 INBDSPOILER 1/2SPOILER 2

OUTBD ENDSPOILER 3

SPOILER 3/4SPOILER 4/5SPOILER 5/6SPOILER 6/7SPOILER 7/8SPOILER 8

OUTBD END

4.98 16.3 4.97 16.3 5.12 16.8 5.17 17.05.62 18.4 5.61 18.4 5.76 18.9 5.81 19.16.09 20.0 6.08 19.9 6.23 20.4 6.31 20.7

6.32 20.7 6.31 20.7 6.46 21.2 6.55 21.56.56 21.5 6.55 21.5 6.70 22.0 6.80 22.36.79 22.3 6.78 22.2 6.93 22.7 7.07 23.26.94 22.8 6.93 22.7 7.08 23.2 7.25 23.87.02 23.0 7.00 23.0 7.14 23.4 7.36 24.17.02 23.0 7.00 23.0 7.14 23.4 7.42 24.37.00 23.0 6.98 22.9 7.12 23.4 7.45 24.5

ABCDEFGHJK

A380−800 SPOILERS EXTENDED

L_MF_010900_1_0060102_01_00

Ground ClearancesSpoilers - Extended - A380-800 Models

1-9Page 7

Oct 01/09



ABCDEFGHJK

m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

ABC

DEFGHJK

SPOILER 1 INBDSPOILER 1/2SPOILER 2

OUTBD ENDSPOILER 3

SPOILER 3/4SPOILER 4/5SPOILER 5/6SPOILER 6/7SPOILER 7/8SPOILER 8

OUTBD END

16.318.4

20.721.5

22.2

23.023.0

4.96 4.95 16.2 5.14 16.9 5.20 17.15.60 5.59 18.3 5.78 19.0 5.84 19.26.07 19.9 6.05 19.9 6.27 20.6 6.34 20.8

6.30 6.29 20.6 6.51 21.4 6.58 21.66.54 6.53 21.4 6.76 22.26.77 22.2 6.76 7.02 23.0 7.10 23.36.93 22.7 6.91 7.20 23.6 7.28 23.97.00 6.97 22.9

22.7

22.97.31 24.0 7.39 24.3

24.424.6

7.01 6.98 7.35 24.1 7.456.98 22.9 6.95 22.8 7.38 24.2 7.49

A380−800F SPOILERS EXTENDED

22.46.83

L_MF_010900_1_0070102_01_00

Ground ClearancesSpoilers - Extended - A380-800F Models

1-9Page 8

Oct 01/09



D C B A

m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

ABCD


5.83 19.1 5.80 19.0 6.24 20.5 6.32 20.75.90 19.4 5.87 19.2 6.35 20.8 6.43 21.15.99 19.7 5.96 19.5 6.49 21.3 6.58 21.66.12 20.1 6.08 19.9 6.69 21.9 6.78 22.3

m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

ABCD


5.815.885.986.10

19.119.319.620.0

5.775.845.936.05

18.919.219.519.9

6.236.356.496.68

20.520.821.321.9

6.356.476.616.82

20.821.221.722.4

A380−800 AILERONS DOWN

A380−800F AILERONS DOWN

L_MF_010900_1_0080102_01_00

Ground ClearancesAilerons - Down

1-9Page 9

Oct 01/09



D C B A

m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

ABCD


m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

ABCD


6.386.416.456.50

20.921.021.221.3

6.356.386.416.46

20.820.921.021.2

6.806.876.957.07

22.322.522.823.2

6.876.947.047.17

22.522.823.123.5

6.366.756.846.97

20.922.122.422.9

6.646.716.806.92

21.822.022.322.7

6.796.866.957.06 23.2

22.522.8

6.906.987.077.20

22.722.923.223.6

22.3

A380−800F AILERONS UP

A380−800 AILERONS UP

L_MF_010900_1_0090102_01_00

Ground ClearancesAilerons - Up

1-9Page 10

Oct 01/09



DE C

m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

ABCD

TRACK 2TRACK 3TRACK 4TRACK 5TRACK 6 E

2.172.873.083.483.86

7.19.410.111.412.7

2.152.853.063.453.82

7.19.310.011.312.5

2.333.083.353.824.27

7.710.111.012.514.0

2.373.123.423.894.35

7.810.211.212.814.3

m ft m ft m ft m ft

MRWAFT CG

MRWFWD CG

300TAFT CG

OWEMID

DESCRIPTION

ABCDE

2.152.853.073.463.84

7.09.310.111.412.6

2.132.823.033.433.80

7.09.310.011.212.5

2.333.073.343.814.26

7.610.1

14.012.511.0

2.413.153.453.934.38

7.910.411.312.914.4

TRACK 2TRACK 3TRACK 4TRACK 5TRACK 6

B

A

A380−800F FLAP TRACKS EXTENDED

A380−800 FLAP TRACKS EXTENDED

L_MF_010900_1_0100102_01_00

Ground ClearancesFlap Tracks - Extended

1-9Page 11

Oct 01/09



AIR

CR

AF

T C

/L

GROUND LINE

A

62°

2.50 m(8.20 ft)

1.36 m(4.46 ft)A

(3.08 ft)

0.94 m

1.89 m(6.20 ft)

L_MF_010900_1_0110102_01_00

Ground ClearancesForward Nose Landing Gear Doors

1-9Page 12

Oct 01/09



0.75 m (2.46 ft)

A

A

AIR

CR

AF

T C

/L

69.2°

0.50 m (1.64 ft)

1.89 m (6.20 ft)

L_MF_010900_1_0120102_01_00

Ground ClearancesAft Nose Landing Gear Doors

1-9Page 13

Oct 01/09



GROUND LINE

AIR

CR

AF

T C

/L

* DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT

38.23 m(123.48 ft)

4.28 m

(5.61 ft)1.71 m

*(10.59 ft)

(15.04 ft)3.95 m

MAX 0.25 m (0.82 ft)MIN 0.10 m (0.32 ft)

A

A

3.23 m

(14.03 ft)

2.30 m(7.54 ft)

MAX 79°

L_MF_010900_1_0130102_01_00

Ground ClearancesWing Landing Gear Doors

1-9Page 14

Oct 01/09



GROUND LINE

AIR

CR

AF

T C

/L


5.02 m(16.46 ft)

4.72 m(15.48 ft)

* MAX 0.35 m (1.41 ft)MIN 0.25 m (0.82 ft)

43.00 m(141.04 ft)

5.17 m(16.95 ft)

A

A

2.25 m(7.38 ft)

MAX 99° 2.90 m(9.51 ft)

L_MF_010900_1_0140102_01_00

Ground ClearancesBody Landing Gear Doors - Sheet 1/2

1-9Page 15

Oct 01/09



GROUND LINE

AIR

CR

AF

T C

/L


*

2.25 m

1.18 m(3.87 ft)

1.23 m(4.03 ft)

MAX 0.95 m (3.11 ft)MIN 0.70 m (2.29 ft)

43.00 m(141.04 ft)

5.17 m(16.95 ft)

A

A

(7.38 ft)

MAX 94°

1.32 m(4.32 ft)

L_MF_010900_1_0150102_01_00

Ground ClearancesBody Landing Gear Doors - Sheet 2/2

1-9Page 16

Oct 01/09



FR117FR112


GROUND LINE

MAX 5.52 (18.10 ft)MIN 5.49 (18.00 ft)

MAX 6.66 m (21.84 ft)MIN 6.63 m (21.74 ft)

FUSELAGE DATUM LINE

**

L_MF_010900_1_0160102_01_00

Ground ClearancesAPU Doors

1-9Page 17

Oct 01/09


1-10 Door Clearances


Door Clearances

1. General

This section gives the identification/location, dimensions and clearances of :- passenger/crew doors (passenger A/C)- courier/crew doors (freighter A/C)- cargo compartment doors- emergency exit doors.

NOTE : For ground clearances of door stills, refer to Section 1-9.

1-10Page 1

Oct 01/09



FORWARDCARGO DOOR

AFTCARGO DOOR

BULKDOOR

DOORM2L

DOORM1L

DOORU1L

DOORU2L

DOORU3L

DOORM4L

DOORM5L

EMERGENCYEXIT DOOR

M3L

DOORU1R

DOORU2R

DOORU3R

DOORM5R

DOORM4R

DOORM2R

DOORM1R

EMERGENCYEXIT DOOR

M3R

L_MF_011000_1_0010101_01_00

Door ClearancesDoor Location (Sheet 1) - A380-800 Models

1-10Page 2

Oct 01/09



11.74 m(462.20 in)

48.08 m(1892.91 in)

51.10 m(2011.80 in)

53.64 m(2111.81 in)

48.22 m(1898.42 in)

44.77 m(1762.59 in)

40.33 m(1587.79 in)

32.71 m(1287.79 in)

20.97 m(825.59 in)

16.32 m(642.52 in)

6.33 m(249.21 in)

L_MF_011000_1_0020101_01_00

Door ClearancesDoor Location (Sheet 2) - A380-800 Models

1-10Page 3

Oct 01/09



LOWER DECK AFTCARGO DOOR

MAIN DECKCARGO DOOR

UPPER DECKCARGO DOOR

LOWER DECK FORWARDCARGO DOOR

BULK DOOR

DOOR M1L DOOR M2L

HATCH U1R

HATCH U1L

DOOR M1R

L_MF_011000_1_0030101_01_00

Door ClearancesDoor Location (Sheet 1) - A380-800F Models

1-10Page 4

Oct 01/09



6.33 m(249.21 in)

51.01 m(2008.26 in)

16.02 m(630.71 in)

48.24 m(1899.21 in)

53.64 m(2111.81 in)

11.74 m(462.20 in)

48.08 m(1892.91 in)

11.10 m(437.01 in)

6.33 m(249.21 in)

11.10 m(437.01 in)

L_MF_011000_1_0040101_01_00

Door ClearancesDoor Location (Sheet 2) - A380-800F Models

1-10Page 5

Oct 01/09



SEECHAPTER

1−9

1067 mm(42 in)

(96.5 in)

859 mm(33.8 in)

2451 mm

MAIN DECK DOORM1L, M1R

1891 mm(74.45 in)

45 mm(1.77 in)

MEASURED FROM THE EXTERNAL POINT OFTHE SCUFF PLATE AND THE MOSTEXTERNAL POINT OF THE DOOR SKIN

2137 mm(84.1 in)

2128 mm(83.8 in)

1262 mm(49.7 in)

FREE AISLE

720 mm(28.3 in)

01NOTE:

FREE AISLE

01

01

L_MF_011000_1_0050101_01_00

Door ClearancesForward Doors

1-10Page 6

Oct 01/09



UPPER DECK DOORU1L, U2L, U3L, U1R, U2R, U3R

MAIN DECK DOORM2L, M3L, M4L, M2R, M3R, M4R

FWD

45 mm(1.77 in)

SEECHAPTER

1−9MEASURED 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

2134 mm(84 in)

SEECHAPTER

1−9

1883 mm(74.1in)FREEAISLE

2124 mm(83.6 in)

1916 mm(75.4 in)

FREEAISLE 2087 mm

(82.2 in)2088 mm(82.2 in)

84 mm(3.31 in)

2453 mm(96.6 in)

1067 mm(42 in)

FREE AISLE

891 mm(35.1 in)ON M3L/M3R702 mm(27.6 in)

2434 mm(95.8 in)

1067 mm(42 in)

FREE AISLE

719 mm(28.3 in)

518 mm(20.4 in)

01

01

1022 mm(40.2 in)ON M3L/M3R840 mm(33.1 in)

01

02

01

02

L_MF_011000_1_0060101_01_00

Door ClearancesMain and Upper Deck Doors - A380-800 Models

1-10Page 7

Oct 01/09



A−A

SEECHAPTER

1−9

UPPER DECK DOORU1R

FWD

A

A

545 mm(214.57 in)

1080 mm(425.20 in)

L_MF_011000_1_0070101_01_00

Door ClearancesUpper Deck Doors - A380-800F Models

1-10Page 8

Oct 01/09



SEECHAPTER

1−9

1067 mm

2453 mm

1091 mm

(96.6 in)

(42 in)

(43 in)

FWD

45 mm(1.77 in)


01NOTE:

MAIN DECK DOORM5L, M5R

FREE AISLE

955 mm(37.6 in)

01

01

1262 mm(49.7 in)

2138 mm(84.2 in)

1883 mm(74.1 in)

FREE AISLE

2124 mm(83.6 in)

L_MF_011000_1_0080101_01_00

Door ClearancesAft Doors - A380-800 Models

1-10Page 9

Oct 01/09



SEECHAPTER

1−9

45 mm(1.77 in)


01NOTE:

2138 mm(84.2 in)

1883 mm(74.1 in)

FREE AISLE

2124 mm(83.6 in)

1067 mm

2453 mm

1091 mm

(96.6 in)

(42 in)

(43 in)

FWD

MAIN DECK DOORM5L

FREE AISLE 01

955 mm(37.6 in)

01

1262 mm(49.7 in)

L_MF_011000_1_0090101_01_00

Door ClearancesAft Doors - A380-800F Models

1-10Page 10

Oct 01/09



SEECHAPTER

1−9

SEECHAPTER

1−9

1752 mm(68.98 in)

2090 mm(82.28 in)

6420 mm(252.76 in) 991 mm

(39.02 in)

1402 mm(55 in)

3071 mm (121 in) AT FR81A2945 mm (116 in) AT FR85

FWD

1130 mm(44.49 in)

2794 mm(110 in)

GROUND LINE

2008 mm(79.05 in)

B

B

A AB BL_MF_011000_1_0100101_01_02

A

A

Door ClearancesAft Cargo Compartment Doors - A380-800 Models

1-10Page 11

Oct 01/09



SEECHAPTER

1−9

A

A−A

3086 mm

6385 mm(251.38 in)

(121.50 in)

3038 mm(120 in)

A

4318 mm(170 in)

2540 mm(100 in)

FWD

L_MF_011000_1_0110101_01_00

Door ClearancesMain Deck Cargo Door - A380-800F Models

1-10Page 12

Oct 01/09



SEECHAPTER

1−9

SEECHAPTER

1−9

1752 mm(68.98 in)

2090 mm(82.28 in)

6420 mm(252.76 in) 991 mm

(39.02 in)

1402 mm(55 in)

FWD

1130 mm(44.49 in)

2794 mm(110 in)

GROUND LINE

2008 mm(79.05 in)

A

A

B

B

A AB BL_MF_011000_1_0120101_01_02

3071 mm (121 in) AT FR81A2945 mm (116 in) AT FR85

Door ClearancesLower Deck Aft Cargo Doors - A380-800F Models

1-10Page 13

Oct 01/09



SEECHAPTER

1−9

1752 mm(68.98 in)

6335 mm

(249.41 in)

2118 mm(83.39 in)

(118 in)2986 mm

3111 mm(122.48 in)

FWD

GROUND LINE

2091 mm(82.32 in)

A

A

A AL_MF_011000_1_0130101_01_01

Door ClearancesForward Cargo Compartment Doors - A380-800 Models

1-10Page 14

Oct 01/09



A−A

SEECHAPTER

1−9

3237 mm(127 in)

2478 mm(97.6 in)

2184 mm(85.98 in)

4748 mm(186.93 in)

3796 mm(149 in)

FWDA

A

L_MF_011000_1_0140101_01_02

Door ClearancesUpper Deck Cargo Door - A380-800F Models

1-10Page 15

Oct 01/09



SEECHAPTER

1−9

1752 mm(68.98 in)

6335 mm

(249.41 in)

2118 mm(83.39 in)

(118 in)2986 mm

3111 mm(122.48 in)

FWD

GROUND LINE

2091 mm(82.32 in)

A

A

A AL_MF_011000_1_0150101_01_02

Door ClearancesLower Deck Forward Cargo Door - A380-800F Models

1-10Page 16

Oct 01/09


1-11 Fuselage Cross-sections


Fuselage Cross-sections

1. General

This section gives fuselage cross-sections.

1-11Page 1

Oct 01/09



0SCALE (mm)

1000 2000

Z=1063.9

Z=−1561.1

FRAME 0STA8170.2

Z=1533.3

Z=−1868.2

FRAME 5STA8789.2

FRAME 6STA9114.2

Z=1694.4

FRAME 7STA9437.2

Z=1998.7

Z

YY

Z

Y

Z

Y 00

0

Z

0

Z=−1985 Z=−2080

L_MF_011100_1_0010101_01_00

Fuselage Cross-SectionSection 11/12 - FR0 to FR7

1-11Page 2

Oct 01/09



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FRAME 8STA9760.2

Z=2320.6

Z=−2158.8

Z=2621.9

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FRAME 9STA10083.2

FRAME 10STA10406.2

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FRAME 11STA10805.2

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Z=2339.3

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Z

Y

Z

Y

Y

Z

Y

00

00

Z=2897.2

L_MF_011100_1_0020101_01_00


1-11Page 3

Oct 01/09



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Z

Y

Z

Y

00

0

Z

Y0

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L_MF_011100_1_0030101_01_00


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Oct 01/09



0SCALE (mm)

1000 2000

Z=−70.4

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Z=4404.7

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Z=4110.1

Z=−2529.0

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Z

Y

Z

Y

00

0

Z

Y0

Z=4528.5

Z=−2612.0

L_MF_011100_1_0040101_01_00

Fuselage Cross-SectionSection 11/12 - FR15A to FR17C

1-11Page 5

Oct 01/09



0SCALE (mm)

1000 2000

Z=−70.4

MAIN DECKDOOR 1

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Z=4651.4

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Z=−2636.2

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Z

Y

Z

Y

L_MF_011100_1_0050101_01_00

Fuselage Cross-SectionSection 11/12 - FR18A to FR19B

1-11Page 6

Oct 01/09



0SCALE (mm)

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Z=5064

Z=−2713.4

Z=−5176.5

Z=−2732.2

Z=4934.1

Z=−2690.1

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FRAME 22STA16205.2

FRAME 20STA14935.2

Z

Y

Z

Y

Z

Y

L_MF_011100_1_0060101_01_00


1-11Page 7

Oct 01/09



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FRAME 24STA17475.2

FRAME 25STA18110.2

FRAME 26STA18745.2

Z=5274.3

Z=−2747.2

Z=5358.9

Z=−2759

Z=5431.1

FRAME 23STA16840.2

Z

Y

Z

Y

ZZ

Y

a: FORWARD CARGO COMPARTMENT DOOR

a a

Z=−2429.6

Z=−2768.1

Z=−2432.2

Z=−660

0 0

Y0

Z=5491.5

Z=−2775

Z=−66

L_MF_011100_1_0070101_01_00

Fuselage Cross-SectionSection 13 - FR23 to FR26 - A380-800 Models

1-11Page 8

Oct 01/09



FRAME 23STA16840.2

Z

Y

Z

Y

0SCALE (mm)

1000 2000 a: FORWARD CARGO COMPARTMENT DOOR

DOORM1L

Z=−2747.2

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0

Z=−2759

0

Z Z

Y Y

FRAME 25STA18110.2

FRAME 26STA18745.2

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Z=2688.5

Z=4788.5

aa

0 0

FRAME 24STA17475.2

Z=5358.9

Z=−2432.2

L_MF_011100_1_0080101_01_00

Fuselage Cross-SectionSection 13 - FR23 to FR26 - A380-800F Models

1-11Page 9

Oct 01/09



0SCALE (mm)

1000 2000

Z

Y

Z

Z=−2780

Z=5540.3

FORWARDCARGO

COMPARTMENTDOOR

FORWARDCARGO

COMPARTMENTDOOR

FRAME 28STA20015.2

FRAME 27STA19380.2

Z=−2434.1

Z=−66

Z=−2435.4

Z=−66

0

0

Y

Z=5577.7

Z=−2783

L_MF_011100_1_0090101_01_00


1-11Page 10

Oct 01/09



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Y

Y

Z

Z

FRAME 28STA20015.2

Z=5540.3

Z=−2780

Z=5577.7

Z=−2783Z=−2435.4

Z=−66

Z=−2434.1

Z=−66

FORWARD CARGOCOMPARTMENT DOOR

FORWARD CARGOCOMPARTMENT DOOR

0

0

0SCALE (mm)

1000 2000

L_MF_011100_1_0100101_01_00


1-11Page 11

Oct 01/09



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Y

Z

Y

FRAME 29STA20650.2

FRAME 30STA21285.2

Z=5604.2

Z=5619.8

0

0

Z=−2785.3

Z=−2784.8

L_MF_011100_1_0110101_01_00


1-11Page 12

Oct 01/09



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Z=−2784.8

Z=5619.8

Z=−2785.3

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FRAME 30STA21285.2

Y

Z

Y

Z

0

0

L_MF_011100_1_0120101_01_00


1-11Page 13

Oct 01/09



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1000 2000

Z

Y0

FRAME 31STA21920.2

Z=5624.7

Z=−2785.3

Z

Y0

Z=5624.7

Z=−2785.3

FRAME 32STA22555.2

L_MF_011100_1_0130101_01_00


1-11Page 14

Oct 01/09



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FRAME 32STA22555.2

Z=5624.7

0SCALE (mm)

1000 2000

Z=5233.1

Z=2556.3

Z=−2785.3

Z=5624.7

Z=−2785.3

Z=5233.1

Z=2556.3



0

Y

Z

Y

Z

0

L_MF_011100_1_0140101_01_00


1-11Page 15

Oct 01/09



0SCALE (mm)

1000 2000

Z

Y

Z

Y

Z=−2785.3

0

FRAME 33STA23190.2

Z=−2785.3

0

FRAME 34STA23825.2

MAIN DECKDOOR 2

Z=2054

Z=−70.4

Z=5624.7

Z=5624.7

L_MF_011100_1_0150101_01_00


1-11Page 16

Oct 01/09



FRAME 33STA23190.2

Z=5233.1

Z=2556.3

Z

Y


Z=−2785.3

Z=5624.7

FRAME 34STA23825.2

Z

Y

Z=5233.1

Z=2556.3

Z=−2785.3

Z=5624.7


0SCALE (mm)

1000 2000

0

0

L_MF_011100_1_0160101_01_00


1-11Page 17

Oct 01/09



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1000 2000

Z

Y

Z

Y

FRAME 36STA25095.2

FRAME 35STA24460.2

Z=5624.7

Z=−2785.3

0

0

Z=5624.7

Z=−2785.3

L_MF_011100_1_0170101_01_00


1-11Page 18

Oct 01/09



0

Z=5233.1

Y

Z


Z=2556.3

Z=−2785.3

Y

Z

Z=−2785.3

FRAME 35STA24480.2

FRAME 36STA25095.2

0SCALE (mm)

1000 2000

0

L_MF_011100_1_0180101_01_00


1-11Page 19

Oct 01/09



0SCALE (mm)

1000 2000

Z

Y

Z=5624.7

Z=−2785.3

FRAME 37STA25730.2

FRAME 38STA26365.2

0

Z

Y

Z=5624.7

Z=−2785.3

0

L_MF_011100_1_0190101_01_00


1-11Page 20

Oct 01/09



FRAME 37STA25790.2

FRAME 38STA26365.2

Z=5624.7

0

0

Y

Z

Y

Z

0SCALE (mm)

1000 2000

Z=−2785.3

Z=5624.7

Z=−2833.2

L_MF_011100_1_0200101_01_00


1-11Page 21

Oct 01/09



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1000 2000

Z

Y

FRAME 39STA27000.2

FRAME 40STA27635.2

0

Z=−2985.3

Z=5624.7

Z=−2911.8

Z=5624.7Z

Y0

L_MF_011100_1_0210101_01_00

Fuselage Cross-SectionSection 15/21 - FR39 to FR40 - A380-800 Models

1-11Page 22

Oct 01/09



FRAME 39STA27000.2

Z

Z=5624.7

Z=−2911.8

0

FRAME 40STA27685.2

Z

Z=5624.7

Z=−2985.3

Y

0SCALE (mm)

1000 2000

0

Y

L_MF_011100_1_0220101_01_00

Fuselage Cross-SectionSection 15/21 - FR39 to FR40 - A380-800F Models

1-11Page 23

Oct 01/09



0SCALE (mm)

1000 2000

Z

Y

Z

Y

Z=5624.7

0

0

UPPER DECKDOOR 7

FRAME 41STA28270.2

FRAME 42STA28905.2

Z=4775.5

Z=1753.4

Z=−3053.1

Z=−3115.5

Z=−3053.1

Z=5624.7Z=5624.7

L_MF_011100_1_0230101_01_00


1-11Page 24

Oct 01/09



FRAME 41STA28270.2

Z

FRAME 42STA28905.2

Z

Z=5624.7

Z=−3053.1

Z=5624.7

Z=−3115.5

0SCALE (mm)

1000 2000

Y

Y

0

0

L_MF_011100_1_0240101_01_00


1-11Page 25

Oct 01/09



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1000 2000

FRAME 43STA29540.2

FRAME 44STA30175.2

Z

Y

Z

Y

0

0

Z=5624.7

Z=5624.7

Z=−3224.3

Z=−3172.5

L_MF_011100_1_0250101_01_00


1-11Page 26

Oct 01/09



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1000 2000

Z

Y

Z=5624.7

Z=−3172.5

FRAME 43STA29540.2

Z=5624.7

FRAME 44STA30175.2

Z=−3224.3

Z

Y0

0

L_MF_011100_1_0260101_01_00


1-11Page 27

Oct 01/09



0SCALE (mm)

1000 2000

Z

Y

Z=5624.7

Z

Y

Z=5624.7

Z

Y

Z=5624.7

Z

Y

Z=5624.7

Z=−3272.5

0

Z=−3315.5

FRAME 45STA30835.6

FRAME 46STA31496

FRAME 47STA32156.4

FRAME 48STA32816.8

Z=−3353.7

0

00

Z=−3387.2

L_MF_011100_1_0270101_01_00


1-11Page 28

Oct 01/09



FRAME 45STA30835.6

FRAME 47STA32156.4

FRAME 48X=32816.8

FRAME 46STA31496

0SCALE (mm)

1000 2000

0 0

0 0

Z Z

Z Z

Y

YY

Z=5624.7

Z=−3272.5

Z=5624.7

Z=−3353.7

Z=5624.7

Z=−3315.5

Z=5624.7

Z=−3387.2

Y

L_MF_011100_1_0280101_01_00


1-11Page 29

Oct 01/09



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Z

Y

Z=5624.7

Z

Y

Z=5624.7

0

FRAME 49STA33477.2

Z=−3416.5

Z=−3441.8

FRAME 50STA34137.6

0

L_MF_011100_1_0290101_01_00


1-11Page 30

Oct 01/09



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FRAME 50STA34137.6

Z=5624.7

Z=5624.7

Z=−3416.5

Z=−3441.8

0

0

0SCALE (mm)

1000 2000

Z

Y

Z

Y

L_MF_011100_1_0300101_01_00


1-11Page 31

Oct 01/09



FRAME 51STA34798

FRAME 53STA36118.8

Z Z

ZZ

Y Y

YY

0 0

0 0

0SCALE (mm)

1000 2000

FRAME 52STA35458.4

FRAME 54STA36779.2

Z=−3463.2

Z=5624.7

Z=−3495.8 Z=−3507.4

Z=−3481.2

Z=5624.7

Z=5624.7Z=5624.7

L_MF_011100_1_0310101_01_00


1-11Page 32

Oct 01/09



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FRAME 53STA36118.8

Z Z

ZZ

Y Y

YY

0 0

0 0

0SCALE (mm)

1000 2000

FRAME 52STA35458.4

FRAME 54STA36779.2

Z=−3463.2

Z=5624.7

Z=−3495.8 Z=−3507.4

Z=−3481.2

Z=5624.7

Z=5624.7Z=5624.7

L_MF_011100_1_0320101_01_00


1-11Page 33

Oct 01/09



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1000 2000

Z

Y

Z=5624.7

Z

Y

Z=5624.7

Z

Y

Z=5624.7

Y

Z=5624.7Z

Z=−3515.9

FRAME 55STA37439.6

0 0

Z=−3521.7

FRAME 56STA38100

0

Z=−3524.7

FRAME 57STA38735

FRAME 58STA39370

Z=−3525.5

0

L_MF_011100_1_0330101_01_00


1-11Page 34

Oct 01/09



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Z

Y0

Z=5624.7

Z=−3515.9

Z=5624.7

Z=−3521.7

FRAME 56STA38100

Z

Y0

FRAME 57STA38735

Z

FRAME 58STA39370

Z

Z=5624.7

Z=−3524.7

Z=5624.7

Z=−3525.5

0SCALE (mm)

1000 2000

0 0Y Y

L_MF_011100_1_0340101_01_00


1-11Page 35

Oct 01/09



0SCALE (mm)

1000 2000

Z

Y

Z=5624.7

Z

Y

Z=5624.7

0

0

MAIN DECKDOOR 3

Z=−3520.7

Z=−3524.2

FRAME 60STA40640

FRAME 59STA40005

Z=2054

Z=−65

L_MF_011100_1_0350101_01_00


1-11Page 36

Oct 01/09



FRAME 59

0

0

Z=5624.7

Z=−3524.2

Z=5624.7

Z=−3520.7

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FRAME 60STA40640

0SCALE (mm)

1000 2000

Z

Y

Z

Y

L_MF_011100_1_0360101_01_00


1-11Page 37

Oct 01/09



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Z

Y

Z=5624.7

Z

Y

Z

Y

Z=5624.7

Z=5624.7

0 0

Z=−3506

FRAME 61STA41275

FRAME 62STA41910

0

FRAME 63STA42545

Z=−3479.5

FRAME 64STA43180

Z=−3494.3

Z=5624.7

Z=−3514.7

Z

Y0

L_MF_011100_1_0370101_01_00


1-11Page 38

Oct 01/09



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Y

Z=5624.7 Z=5624

Z=5624.7

Z=−3506Z=−3514.7

FRAME 62STA41910

Y0

Y

FRAME 63STA42545

FRAME 64STA43180

Y

Z=5624.7

Z=−3494.3 Z=−3479.5

0

0SCALE (mm)

1000 2000

0

0

Z Z

Z Z

L_MF_011100_1_0380101_01_00


1-11Page 39

Oct 01/09



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Y

Z

Y

Y

Z

0 0

FRAME 65STA43815

FRAME 66STA44450

FRAME 67STA45085

0

FRAME 68STA45720

Z=5624.7

Z=5624.7

Z=5624.7

Z=5624.7

Z=−3461.6

Z=−3388.3Z=−3416

Z=−3440.4

Z

Y0

L_MF_011100_1_0390101_01_00


1-11Page 40

Oct 01/09



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FRAME 66STA44450

FRAME 68STA45720

FRAME 67STA45085

0SCALE (mm)

1000 2000

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Z=−3461.6 Z=−3440.4

Z=5624.7 Z=5624.7

Z=−3416 Z=−3388.3

Z Z

ZZ

Y

YY

Y0 0

0 0

L_MF_011100_1_0400101_01_00


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Y

Z=5624.7

Z

Y

Z=5624.7

0

Z=−3322.9

FRAME 70STA46990

0

FRAME 69STA46255

Z=−3357.4

L_MF_011100_1_0410101_01_00


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Oct 01/09



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FRAME 66STA44450

FRAME 68STA45720

FRAME 67STA45085

0SCALE (mm)

1000 2000

Z=5624.7 Z=5624.7

Z=−3461.6 Z=−3440.4

Z=5624.7 Z=5624.7

Z=−3416 Z=−3388.3

Z Z

ZZ

Y

YY

Y0 0

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L_MF_011100_1_0420101_01_00


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Y

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Z

Y

Z=5624.7

0

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UPPER DECKDOOR 8

0

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FRAME 71STA48260

Z=4775.5

Z=1753.4

L_MF_011100_1_0430101_01_00


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Z=5624.7

Z=−3242

0

0

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Z

FRAME 72STA48260

Z

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Y

L_MF_011100_1_0440101_01_00


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Y

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Y

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0

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FRAME 74STA49530

FRAME 73STA48895

Z=−3194.9

0

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FRAME 74STA49530

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Z

Y

Z

Y

0

0

L_MF_011100_1_0460101_01_00


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FRAME 75STA50165

1000 2000

FRAME 77STA51435

FRAME 76STA50800

FRAME 78STA52070

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Z=5624.7

Z=5624.7

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DOOR 4

Z=5624.7

Z=2054

Z=−70.4

Z

Y

Z

Y

Z

Y

Z

Y

0

0

0

0

L_MF_011100_1_0470101_01_00


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Oct 01/09



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Z Z

Y Y

Y Y

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0 0

FRAME 75

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1000 2000

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FRAME 76FRAME 75STA50800

FRAME 77STA51435

FRAME 78STA52070

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L_MF_011100_1_0480101_01_00


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FRAME 79STA52705

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Z=−2932.7 Z=−2912.3

FRAME 81STA53975

Z

Y

Z

Y

Z

Y

00

0

Z=5624.7

Z=−2850.9

FRAME 80STA53340

L_MF_011100_1_0490101_01_00


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Z=5624.7

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FRAME 82STA54610

FRAME 83STA55245

Z=−2771

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AFTCARGODOOR

Z

Y

Z

Y

0

0Z=−68

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AFTCARGODOOR

Z=−2497.9

L_MF_011100_1_0510101_01_00


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FRAME 83STA55245

Z=5624.7

Z=−2771

Z=5624.7

Z=−2683.4

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Z=2597.8

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Z=−2497.9

Z=−68

Z=−68

Z=−2532.5

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MAIN DECKCARGO DOOR

MAIN DECKCARGO DOOR

LOWER DECKAFT CARGO

DOOR

0

0

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FRAME 85STA56515

Z=5624.7

Z=−2589.8

Z=−2492.1

UPPERDECK

DOOR 9

Z=4775.5

Z=1753.4

Z

Y

Z

Y

0

0Z=−68

AFTCARGODOOR

Z=−68

AFTCARGODOOR

Z=−2382.5

Z=−2448.3

L_MF_011100_1_0530101_01_00


1-11Page 53

Oct 01/09



0SCALE (mm)

1000 2000

Z=−2448.3

Z=−68

LOWER DECKAFT CARGO

FRAME 84STA55880

Z

0

Z=5624.7

Y

MAIN DECKCARGO DOOR

Z=2597.8

Z=−452.2

FRAME 85STA58515

Z

Z=5624.7

Z=−2589.8

Z=−68

Z=−2382.5

DOOR

LOWER DECKAFT CARGO

DOOR

MAIN DECKCARGO DOOR

Z=2597.8

Z=−452.2

Z=−2492.1

Y0

L_MF_011100_1_0540101_01_00


1-11Page 54

Oct 01/09



0SCALE (mm)1000 2000

Z

Y

Y Y

Z

Y

0

0

0

0

Z=5624.7 Z=5622.4

FRAME 86STA57150

FRAME 87STA57785

Z=−2286.1Z=−2390.7

FRAME 88STA58420

Z=5615.1

Z

FRAME 89STA59055

Z=5802.7

Z

Z=−2178.7 Z=−2068.4

BULKCARGODOOR

Z=−1956.9

Z=−1330.9

L_MF_011100_1_0550101_01_00


1-11Page 55

Oct 01/09



Z=5624.7

Z=−2390.7

Z=5615.1

Z=−2178.7

Z=−2286.1

Z=5622.4

Z=−452.2

Z=2597.8

a

b

Z=−1330.9

Z=−1956.9

FRAME 86STA57150

0SCALE (mm)

1000 2000

FRAME 88STA58420

FRAME 89STA59055

FRAME 87STA57785

a: MAIN DECK CARGO DOOR

b: BULK DOOR

0 0

0 0

Z

Y

Z

Y

Z

Y

Z

Y

Z=5602.7

Z=−2068.4

L_MF_011100_1_0560101_01_00


1-11Page 56

Oct 01/09



0SCALE (mm)

1000 2000

FRAME 90STA59690

Z=5585.3

Z=−1955.3

FRAME 91STA60325

Z=5562.9

Z=−1839.3

FRAME 92STA60960

Z=−1720.2

Z=2054

Z=5535.3Z=5535.3Z=5535.3

MAIN DECKDOOR 5

Z=−70.4

Z

Y

Z

Z

Y

Y

00

0

L_MF_011100_1_0570101_01_00


1-11Page 57

Oct 01/09



FRAME 90STA59690

Z=5585.3

Z=−1955.3

Z=5562.9

Z=−1839.3

Z=5535.3

Z=−1720.2

Z=−117.8

Z=2042.2

DOOR M5L

Z

0

Z

Y

Z

FRAME 91STA60325

FRAME 92STA60960

0 0

0SCALE (mm)

1000 2000

Y Y

L_MF_011100_1_0580101_01_00


1-11Page 58

Oct 01/09



0SCALE (mm)

1000 2000

Y0

Z

Y0

Z

Y0

FRAME 95STA62865

Z

FRAME 93STA61595

FRAME 94STA62230

Z=5502.8

Z=−1597.7

Z=5465.2

Z=−1471

Z=5422.4

Z=−1339.2

L_MF_011100_1_0590101_01_00


1-11Page 59

Oct 01/09



FRAME 93STA61595

Z=5502.8

Z=−1597.7

Z=5465.2

Z=−1471

Z=5422.4

Z=−1339.2

FRAME 94STA62230

FRAME 95STA62865

0SCALE (mm)

1000 2000

Y

Z

Y

Z

Y

Z

0 0

0

L_MF_011100_1_0600101_01_00


1-11Page 60

Oct 01/09



0SCALE (mm)

1000 2000

Z

Y0

Z

Y0

Z

Y0

FRAME 98STA64770

Z=5263.8

Z=−932.3

FRAME 96STA63500

FRAME 97STA64135

Z=5374.7 Z=5321.8

Z=−1204.1 Z=−1068.4

L_MF_011100_1_0610101_01_00

Fuselage Cross-SectionSection 19 - FR96 to FR98

1-11Page 61

Oct 01/09



0SCALE (mm)

1000 2000

FRAME 99STA65405

FRAME 100STA66040

FRAME 101STA66675

FRAME 102STA67310

Z=5200.8 Z=5132.6

Z=−795.5 Z=−658

Z=5059.2 Z=4980.8

Z=−519.6 Z=−380.1

Z

Y

Z

Y

Z

Y

Z

Y

0

0

0

0

L_MF_011100_1_0620101_01_00


1-11Page 62

Oct 01/09



0SCALE (mm)

1000 2000

FRAME 103STA67945

FRAME 104STA68580

FRAME 105STA69260

FRAME 106STA69640

Z=4897.2 Z=4814.6

Z=−239.4 Z=−97

Z=4731.9 Z=4655

Z=57.6 Z=215.2

Z

Y

Z

Y

Z

Y

Z

Y

0

0

0

0

L_MF_011100_1_0630101_01_00


1-11Page 63

Oct 01/09



0SCALE (mm)

1000 2000

FRAME 107STA70620

FRAME 108STA71300

FRAME 109STA71810

FRAME 110STA72320

Z=4584.1

Z=542.7

Z=4519

Z=4473.5 Z=4424.8

Z=671.5 Z=804.6

Z=376.5

Z

Y

Z

Y

Z

Y

Z

Y

0

0

0

0

L_MF_011100_1_0640101_01_00


1-11Page 64

Oct 01/09



0SCALE (mm)

1000 2000

FRAME 111STA72354

FRAME 112STA72922

FRAME 113STA73462

FRAME 114STA74002

Z=4421.4 Z=4359.5

Z=4297.8 Z=4236.1

Z=813.4 Z=974.9

Z=1134.4 Z=1293.9

Z

Y

Z

Y

Z

Y

Z

Y

0

0

0

0

L_MF_011100_1_0650101_01_00


1-11Page 65

Oct 01/09



0SCALE (mm)

1000 2000

FRAME 115STA74542

FRAME 116STA75082

Z=4112.6Z=4174.4

Z=1453.4 Z=1612.9

FRAME 117STA75622

Z=4050.9

FRAME 118STA75983

Z=4009.7

Z=1879

FRAME 119STA76149.5

Z=3990.6

Z=1928.2

Z

Y

Z

Y

Z

Y0

0

0

Y0

Z

Y0

Z

Z=1772.4

L_MF_011100_1_0660101_01_00

Fuselage Cross-SectionSection 19.1 - FR115 to FR119

1-11Page 66

Oct 01/09


1-12 Nose Contours


Nose Contours

1. GeneralThis section gives the Nose Contours.

1-12Page 1

Oct 01/09



X=1

490

FR0

X=2

757

FR

7

X=4

773

FR13

X=7

144

FR18

A

X=2

0650

FR

29

X=1

7475

FR

24

EV

OLU

TIV

E S

HA

PE

LIM

IT X

=145

75

A

B

C

D

E

F

Z=4150

Z=2703.5

Z=778

Z=−50

Z=−1000

Z=−2128

UPPER DECKFLOOR LEVEL

COCKPITFLOOR LEVELMAIN DECKFLOOR LEVEL

CARGOFLOOR LEVEL

A

B

C

D

E

F

L_MF_011200_1_0010102_01_00

Nose ContoursLevel Positions - A380-800 Models

1-12Page 2

Oct 01/09



X=8

170.

2 FR

0

X=9

437.

2 F

R7

X=1

1453

.2 F

R13

X=1

3824

.2 F

R18

A

X=2

0650

FR

29

X=1

7475

.2 F

R24

EV

OLU

TIV

E S

HA

PE

LIM

IT X

=145

75

A

B

C

D

E

F

Z=4150

Z=2770.6

Z=778

Z=−97.4

Z=−1000

Z=−2128

UPPER DECKFLOOR LEVEL

COCKPITFLOOR LEVELMAIN DECKFLOOR LEVEL

CARGOFLOOR LEVEL

A

B

C

D

E

FX

=187

45.2

FR

26

L_MF_011200_1_0020102_01_00

Nose ContoursLevel Positions - A380-800F Models

1-12Page 3

Oct 01/09



NOSE CONTOUR POINTS A380−800

POINTS X (mm) Y (mm) Z (mm)

8170.2FR0

P1 633.7 7788170.2P2 1136 −508170.2P3 1038.9 −10009427.2P4 1507.4 7789427.2P5 1843.1 −509427.2P6 1751.5 −1000

11453.2P7 1430.6 2703.511453.2P8 2393.7

−5011453.2P9 2520.2778

11453.2P10 2381.7 −100011453.2P11 1471.6 −212813824.2P12 1317.2 415013824.2P13 2422.5 2703.513824.2P14 2978.1 77813824.2P15 2979.9 −5013824.2P16 2783.5 −100013824.2P17 1911.9 −212817475.2P18 2372.3 415017475.2P19 3135.4 2703.517475.2P20 3420.6 77817475.2P21 3314.6 −5017475.2P22 2993.6 −100017475.2P23 2013.7 −212820650.2P24 2717.9 415020650.2P25 3537.8 2703.520650.2P26 3377.8 77820650.2P27 3381.1 −5020650.2P28 3015.7 −100020650.2P29 2019 −2128

FR7

FR13

FR18A

FR24

FR29

FR

0

FR

7

FR

13

FR

18A

FR

24

FR

29

P1

P2

P3

P4

P5

P6 P10

P9

P8

P11 P17

P16

P7 P13

P12 P18

P19

P20

P21

P25

P24

P29

P28

P27

P26P14

P22

P23

L_MF_011200_1_0030102_01_02

P15

Nose ContoursContour Points at Frame Positions - A380-800 Models

1-12Page 4

Oct 01/09



NOSE CONTOUR POINTS A380−800F

POINTS X (mm) Y (mm) Z (mm)

8170.2FR0

P1 633.7 7788170.2P2 1150.1 −97.48170.2P3 1038.9 −10009427.2P4 1507.4 7789427.2P5 1852.2 −97.49427.2P6 1751.5 −1000

11453.2P7 1376.2 2770.611453.2P8 2393.7

−97.411453.2P9 2520778

11453.2P10 2381.7 −100011453.2P11 1471.6 −212813824.2P12 1317.2 415013824.2P13 2389.9 2770.613824.2P14 2978.1 77813824.2P15 2976.1 −97.413824.2P16 2783.5 −100013824.2P17 1911.9 −212817475.2P18 2372.3 415017475.2P19 3110.3 2770.617475.2P20 3420.6 77817475.2P21 3304.3 −97.417475.2P22 2993.6 −100017475.2P23 2013.7 −212820650.2P24 2717.9 415020650.2P25 3358.2 2770.620650.2P26 3537.8 77820650.2P27 3367.8 −97.420650.2P28 3015.7 −100020650.2P29 2019 −2128

FR7

FR13

FR18A

FR24

FR29

FR

0

FR

7

FR

13

FR

18A

FR

24

FR

29

P1

P2

P3

P4

P5

P6 P10

P9

P8

P11 P17

P16

P7 P13

P12 P18

P19

P20

P21

P25

P24

P29

P28

P27

P26P14

P22

P23

L_MF_011200_1_0040102_01_01

P15

Nose ContoursContour Points at Frame Positions - A380-800F Models

1-12Page 5

Oct 01/09



ABC

X=

1747

5

X=

2065

0

D

E

F

X=

1490

X=

2757

X=

4773

X=

7144

UPPER NOSE CONTOUR

LOWER NOSE CONTOUR

L_MF_011200_1_0050102_01_00

Nose ContoursUpper and Lower Contours - A380-800 Models

1-12Page 6

Oct 01/09



ABC

X=

1747

5.2

X=

2065

0.2

D

E

F

X=

8170

.2

X=

9437

.2

X=

1145

3.2

X=

1382

4.2

X=

1874

5.2

UPPER NOSE CONTOUR

LOWER NOSE CONTOUR

L_MF_011200_1_0060102_01_00

Nose ContoursUpper and Lower Contours - A380-800F Models

1-12Page 7

Oct 01/09


1-13 Vertical Stabilizer Contours


Vertical Stabilizer Contours

1. GeneralThis section gives Vertical Stabilizer contours.Vertical stabilizer contours shown in this section have been selected to assist in designing stands orequipment. These levels provide access to important maintenance areas such as servo controls, rudderhinges, leading edge, trailing edge, HF and VOR antennas.The contours given are on the surface of body skin ; clearance space allowances will have to be madeas required.Ground clearances will depend on whether the airplane is on jacks or on wheels and in this case whatthe CG and weight conditions are.

1-13Page 1

Oct 01/09



Z

4320 mm

A

Z=0

1000 mm (39.37 in)

2000 mm (78.74 in)

3000 mm (118.11 in)

4000 mm (157.48 in)

6000 mm (236.22 in)

7000 mm (275.59 in)

9000 mm (354.33 in)

10000 mm (393.70 in)

11000 mm (433.07 in)

12000 mm (472.44 in)

13000 mm (511.81 in)

14000 mm (551.18 in)

(170.08 in)

B

8000 mm (314.96 in)

5000 mm (196.85 in)

L_MF_011300_1_0010101_01_00

Vertical Stabilizer ContoursLevel Positions

1-13Page 2

Oct 01/09



AZ

BB

BB

BB

BB

BB

BB

BB

BB

BB

BB

BB

B

L_MF_011300_1_0020101_01_01

Vertical Stabilizer Contours

1-13Page 3

Oct 01/09


1-14 Horizontal Stabilizer Contours


Horizontal Stabilizer Contours

1. GeneralThis section gives Horizontal Stabilizer contours.Horizontal stabilizer contours shown in this subject have been selected to assist in designing stands orequipment. These levels provide access to important maintenance areas such as servo controls,elevator hinges, trimmable horizontal stabilizer hinges, leading edge, trailing edge.The contours given are on the surface of body skin ; clearance space allowances will have to be madeas required.Ground clearance will depend on whether the airplane is on jacks or on wheels and in this case whatthe CG and weight conditions are.

1-14Page 1

Oct 01/09



X

(Z=0)

Z1

Z2

mm

mm

mm

mm

mm

mm

mm

mm

mm

mm

mm

mm

mm

Y X

250098.433500

137.804500177.175500

216.546500

255.917500

295.288500

334.659500

374.0210500413.3911500

452.7612500492.1313500531.50

00

Z1 Z2 Z1 Z2 Z1 Z2 Z1 Z22671

105.142782

109.552894113.923003118.223108

122.373213

126.513319

130.653424

134.803529

138.943634

143.083739

147.223825

150.60

2671105.142782

109.552894113.923003118.223108

122.373213

126.513319

130.653424

134.803529

138.943634

143.083739

147.223825

150.60

75029.53

2957116.403030119.303107

122.333187

125.473281

129.163376

132.933472

136.693567

140.423661

144.143755

147.833848151.503923

154.45

222187.46229090.15250398.532635

103.752755

108.452872113.072989117.693107

122.323225

126.95

131.593460

136.233567

140.42

225088.58

2983117.433051120.113123

122.953199

125.963289

129.493380

133.083471

136.653561

140.183649

143.673737147.123823150.513891

153.20

211483.23223788.08240894.812546

100.252670105.112791

109.872912

114.643033119.423155

124.213277

129.003399133.813514

138.35

2970 2060116.923036119.533107

122.343184

125.343270

128.743357132.153442

135.523526

138.843609

142.083689

145.243767

148.293825

150.57

81.10220486.78236292.98250398.552630

103.552755

108.452879113.363005118.303131

123.263257

128.243385

133.263511

138.23

in

in

in

in

in

in

in

in

in

in

in

in

150059.06

3342

L_MF_011400_1_0010101_01_00

Horizontal Stabilizer ContoursHorizontal Stabilizer Contours (Sheet 1)

1-14Page 2

Oct 01/09



mm

mm

mm

mm

mm

mm

mm

mm

mm

mm

mm

mm

mm

Y X

250098.433500

137.804500177.175500

216.546500

255.917500

295.288500

334.659500

374.0210500413.3911500

452.7612500492.1313500531.50

3000 3750 4500 5250118.11 147.64 177.17 206.69

Z1 Z2 Z1 Z2 Z1 Z2 Z1 Z22931115.412998118.033071

120.903148

123.953230127.183312

130.383391

133.493468

136.523542

139.443613

142.263684

145.043743

147.35

203980.29219586.43234692.37249098.052621

103.202750

108.272880113.383010

118.523142

123.713275

128.933408134.193544

139.52

2875113.182943115.863016

118.763093121.793170

124.813245

127.743318

130.613390

133.473464

136.403539

139.343614

142.283676

144.74

204680.55221387.14235792.80250498.592640

103.922774

109.202909114.523045119.873181

125.233317

130.593452

135.893588141.28

2807110.512876113.212948116.063022118.983097121.913172

124.893249

127.903326

130.933402

133.953477136.913550

139.76− − −− − − − − − − − − − − −

− − − − − − − − −− − −− − −− − −− − −− − −

− − −− − −− − −

207781.79226489.12239294.172541

100.062681

105.552819

110.982957116.423095121.843231

127.213366

132.523499

137.74

2735107.682805110.432880113.372957116.423035119.503114

122.603192

125.683269

128.703343131.63

213083.84236493.07244596.262595102.152735

107.702874113.163012

118.593149

123.973284

129.29

X

(Z=0)

Z1

Z2

in

in

in

in

in

in

in

in

in

in

in

in

in

L_MF_011400_1_0020101_01_00

Horizontal Stabilizer ContoursHorizontal Stabilizer Contours (Sheet 2)

1-14Page 3

Oct 01/09



L_MF_011400_0_AAM0_01_00

Y10500

Y11500

Y12500

Y13500

Y0

Y2500

Y3500

Y4500

Y5500

Y6500

Y7500

Y8500

Y9500

L_MF_011400_1_0030101_01_00

Horizontal Stabilizer ContoursLevel Positions

1-14Page 4

Oct 01/09


1-15 Tail Contours


Tail Contours

1. General

This section gives Tail contours.Tail contours shown in this section have been selected to assist in designing stands or equipment.The levels provide access to maintenance areas such as APU, aft passenger/crew doors.The contours given are on the surface of body skin ; clearance allowances will have to be made asrequired.Ground clearances will depend on whether the airplane is on jacks or on wheels in this last case whatthe C.G and weight conditions are.

1-15Page 1

Oct 01/09



FR95/STA62865

FR96/STA63500

FR97/STA64135

FR98/STA64770

FR99/STA65405

FR100/STA66040

FR101/STA66675

FR102/STA67310

FR103/STA67945

FR104/STA68580

FR105/STA69260

FR106/STA69940

FR107/STA70620

FR108/STA71300

FR109/STA71810

FR110/STA72320FR111/STA72354FR112/STA72922

FR114/STA74002

FR117/STA75622

FR120/STA77204.5

FR119/STA76677

FR118/STA76149.5

FR116/STA75132

FR115/STA74592

FR113/STA73462

L_MF_011500_1_0010101_01_00

Tail Contours

1-15Page 2

Oct 01/09



Y=

0.0

1155.4 mm

2233.2 mm

2899.2 mm

3423.9 mm

3873 mm

4268.5 mm

4614.6 mm

4923.7 mm

5203.7 mm

5459.3 mm

STA72320/FR110

STA71810/FR109

STA71300/FR108

(114.141 in)

(134.799 in)

(152.480 in)

(168.051 in)

(181.677 in)

(193.846 in)

(204.870 in)

(214.933 in)

(45.488 in)

(87.921 in)

STA70620/FR107

STA69640/FR106

STA69260/FR105

STA68580/FR104

STA67945/FR103

STA67310/FR102

STA66675/FR101

STA66040/FR100

STA65450/FR99

STA64770/FR98

STA64135/FR97

STA63500/FR96

STA62865/FR95

3164.3 mm

3371.2 mm

3521.1 mm

3557.9 mm

3625.8 mm

3732.1 mm

3877.5 mm

4048.4 mm

4252.6 mm

4489.7 mm

4758.7 mm

5057.2 mm

5375.4 mm

5687.9 mm

5974.2 mm

6170.8 mm

(124.578 in)

(132.724 in)

(138.625 in)

(140.074 in)

(142.748 in)

(146.933 in)

(152.657 in)

(159.385 in)

(167.425 in)

(176.759 in)

(187.350 in)

(199.102 in)

(211.629 in)

(223.933 in)

(235.204 in)

(242.944 in)

L_MF_011500_1_0020101_01_00

Tail ContoursLevel Positions

1-15Page 3

Oct 01/09


1-16 Wing Profile


General

1. This section gives the Wing Profile.Positions and dimensions of the wing ribs, from the centerline of the aircraft are given in Figures 1and 2.Figure 2 also shows a typical aerofoil cross-section with dimensions for Y and Z.The selection of these rib positions along the wing is to give the aircraft operator the necessaryheights to make aircraft servicing stands, supports or trestles.The dimensions for the wing profiles (dimensions Y and Z) at each of the rib positions are given inpara. 2. to 9. All the dimensions for the profiles are taken from the local datum position (at the wingleading edge, with the slats retracted) and from the horizontal datum VZO.These dimensions (when plotted from datum VZO) give the shape of the aerofoil cross-section andfull slope of the wing from wingtip to wingroot.All the dimensions for the profiles are taken from the local datum position (at the wing leading edge,with the slats retracted) and from the horizontal datum VZO.

2. RIB 7Intersection of Front Spar and rib 7.Source of Local datum for rib 7.

SKIN PROFILE POINTS TO LOCAL DATUMX X Y Y Z

mm in mm in2746.23 108.12 -- 228.28 -- 8.99 03056.71 120.34 -- 295.96 -- 11.65 03367.68 132.59 -- 361.41 -- 14.23 03679.15 144.85 -- 424.45 -- 16.71 03991.12 157.13 -- 484.90 --19.09 04303.61 169.43 -- 542.68 -- 21.37 04616.57 181.75 -- 597.79 -- 23.54 04929.98 194.09 -- 650.33 -- 25.60 05243.77 206.45 -- 700.49 -- 27.58 05557.90 218.81 -- 748.55 -- 29.47 05872.30 231.19 -- 794.74 -- 31.29 06186.95 243.58 -- 839.27 -- 33.04 06501.81 255.98 -- 882.23 -- 34.73 06816.89 268.38 -- 923.59 -- 36.36 07132.19 280.79 -- 963.20 -- 37.92 07447.74 293.22 -- 1000.79 -- 39.40 07763.55 305.65 -- 1036.09 -- 40.79 08079.64 318.10 -- 1068.81 -- 42.08 08396.00 330.55 -- 1098.80 -- 43.26 0

1-16Page 1

Oct 01/09



mm in mm in8712.61 343.02 -- 1126.08 - 44.33 0



mm in mm in1357.81 53.46 974.01 38.35 01672.93 65.86 917.43 36.12 01988.25 78.28 861.91 33.93 02303.97 90.71 808.69 31.84 02620.15 103.16 758.35 29.86 02936.75 115.62 710.65 27.98 03253.66 128.1 665.07 26.18 03570.82 140.58 621.31 24.46 03888.24 153.08 579.46 22.81 04205.98 165.59 540.05 21.26 04524.09 178.11 503.88 19.84 04842.65 190.66 471.76 18.57 05161.63 203.21 444.34 17.49 05481.01 215.79 421.92 16.61 05800.70 228.37 404.52 15.93 06120.61 240.97 391.71 15.42 06440.66 253.57 382.90 15.07 06760.78 266.17 377.46 14.86 07080.94 278.78 374.54 14.75 07401.10 291.38 373.01 14.69 0



mm in mm in1208.34 47.57 1430.76 56.33 01490.67 58.69 1384.62 54.51 01773.38 69.82 1340.85 52.79 02056.60 80.97 1300.54 51.2 0

1-16Page 2

Oct 01/09



mm in mm in2340.38 92.14 1264.43 49.78 02624.70 103.33 1232.80 48.54 02909.48 114.55 1205.61 47.46 03194.63 125.77 1182.68 46.56 03480.08 137.01 1163.72 45.82 03765.74 148.26 1148.42 45.21 04051.57 159.51 1136.49 44.74 04337.51 170.77 1127.69 44.4 04623.53 182.03 1121.98 44.17 04909.59 193.29 1119.41 44.07 05195.66 204.55 1120.16 44.1 05481.71 215.82 1124.09 44.26 05767.72 227.08 1130.67 44.51 06053.68 238.33 1138.95 44.84 06339.62 249.59 1147.76 45.19 06625.58 260.85 1155.96 45.51 0



mm in mm in1078.37 42.46 1926.80 75.86 01342.52 52.86 1888.34 74.34 01607.23 63.28 1853.93 72.99 01872.47 73.72 1823.99 71.81 02138.20 84.18 1798.63 70.81 02404.32 94.66 1777.83 69.99 02670.76 105.15 1761.59 69.35 02937.44 115.65 1750.03 68.9 03204.29 126.15 1743.34 68.64 03471.22 136.66 1741.76 68.57 03738.13 147.17 1745.42 68.72 04004.91 157.67 1754.31 69.07 04803.74 189.12 1768.29 69.62 04271.48 168.17 1787.01 70.35 04537.75 178.65 1809.53 71.24 05069.53 199.59 1834.22 72.21 0

1-16Page 3

Oct 01/09



mm in mm in5335.34 210.05 1858.72 73.18 05601.37 220.53 1880.68 74.04 0



mm in mm in1023.63 40.3 2111.24 83.12 01317.16 51.86 2069.15 81.46 01611.41 63.44 2032.40 80.02 01906.44 75.06 2002.66 78.84 02202.15 86.7 1980.57 77.98 02498.30 98.36 1965.59 77.39 02794.70 110.03 1956.84 77.04 03091.22 121.7 1953.66 76.92 03387.74 133.38 1955.80 77.00 03684.18 145.05 1963.33 77.3 03980.43 156.71 1976.28 77.81 04276.40 168.36 1994.49 78.52 04572.05 180.00 2017.36 79.42 04867.48 191.63 2043.06 80.44 05162.95 203.27 2068.22 81.43 0



mm in mm in905.61 35.65 2510.61 98.84 01139.12 44.85 2479.20 97.61 01372.92 54.05 2450.08 96.46 01607.16 63.27 2424.69 95.46 01841.91 72.52 2404.70 94.67 02077.11 81.78 2390.91 94.13 02312.59 91.05 2383.03 93.82 02548.18 100.32 2380.19 93.71 0

1-16Page 4

Oct 01/09



mm in mm in2783.78 109.6 2381.50 93.76 03019.34 118.87 2386.46 93.96 03254.81 128.14 2394.74 94.28 03490.16 137.41 2405.81 94.72 03725.40 146.67 2418.94 95.23 03960.57 155.93 2433.33 95.8 04195.75 165.19 2447.71 96.37 0



mm in mm in799.38 31.47 2862.47 112.7 01076.17 42.37 2831.00 111.46 01353.12 53.27 2801.03 110.28 01630.57 64.2 2776.08 109.29 01908.64 75.14 2759.57 108.64 02187.13 86.11 2753.27 108.40 02465.66 97.07 2756.86 108.54 02743.96 108.03 2769.03 109.02 03021.90 118.97 2787.73 109.75 03299.67 129.91 2808.93 110.59 0



mm in mm in698.44 27.5 3158.68 124.36 0889.44 35.02 3139.88 123.62 01080.60 42.54 3122.74 122.94 01272.02 50.08 3109.03 122.4 01463.74 57.63 3100.28 122.06 01655.63 65.18 3097.23 121.94 01847.53 72.74 3099.73 122.04 02039.29 80.29 3107.32 122.34 0

1-16Page 5

Oct 01/09



mm in mm in2230.84 87.83 3119.28 122.81 02422.17 95.36 3134.28 123.4 0

1-16Page 6

Oct 01/09



RIB7

RIB14

RIB19

RIB26

RIB29

RIB36

RIB42

RIB48

A

AL_MF_011600_1_0010101_01_00

Wing ProfileRib Locations

1-16Page 7

Oct 01/09



RIB

7R

IB14

RIB

19R

IB26

RIB

29R

IB36

RIB

42R

IB48

AIR

CR

AF

TC

EN

TE

R−

LIN

E

5582

.7(2

19.8

)10

631.

6(4

18.6

)14

424.

2(5

67)

1982

3.3

(780

.4)

2214

7.1

(872

)

2729

2.5

(107

4.5)

3207

6.2

(126

2.8)

3677

7.8

(144

7.9)

8203

.4(3

23)

1333

6(5

25)

1684

5.7

(663

.2)

2185

9.2

(860

.6)

2401

0.3

(945

.3)

2877

1.2

(113

2.7)

3319

9.5

(130

7)37

553.

2(1

478.

5)

DIM

EN

SIO

N F

RO

M A

IRC

RA

FT

CE

NT

ER

−LI

NE

TO

TH

E R

IB/R

EA

R S

PA

R IN

TE

RS

EC

TIO

ND

IME

NS

ION

S IN

mm

(in

IN B

RA

CK

ET

S)

DIM

EN

SIO

N F

RO

M A

IRC

RA

FT

CE

NT

ER

−LI

NE

TO

TH

E R

IB/F

RO

NT

SP

AR

INT

ER

SE

CT

ION

DIM

EN

SIO

NS

IN m

m (

in IN

BR

AC

KE

TS

)

L_MF_011600_1_0020101_01_00

Wing ProfileRib Positions

1-16Page 8

Oct 01/09



FRONTSPAR

REARSPAR

VZO

VIEW ON LOCAL DATUMRIB 7

y

z zz

LOCAL DATUMSOURCE

Z

VIEW ON LOCAL DATUMRIBS 14, 19, 29, 36, 42 AND 48

LOCAL DATUMSOURCE

Z

FRONTSPAR REAR

SPAR

VZO

y

z z z

L_MF_011600_1_0030101_01_00

Wing Profile

1-16Page 9

Oct 01/09




Nacelle Contours

1. General

Nacelle contours shown in this section have been selected to assist in designing stands or equipment.These levels provide access to important maintenance areas.The contours given are on the surface of body skin ; clearance space allowances will have to be madeas required.Ground clearances will depend on whether the airplane is on jacks or on wheels and in this case whatthe CG and weight conditions are.

1-17Page 1

Oct 01/09



Z=1906,53

Z=−1989,67

Y=−1936,62Y=1936,62

X=−165 X=3640,5 (TOP)

DISTANCE FROM THE NOSE

INBOARDENGINE

22.228 m(72.92 ft)

DISTANCE FROMTHE NOSE

Y=0

Z=0

29.943 m(98.23 ft)

FWD

OUTBOARDENGINE

A

X=167,95 X=1466,67 X=3642 (BOTT) X=6501,83X=8221,27

X=6028,9

X=6873,20

X=6769,73

PLUG

PRIMARY NUZZLE

THRUST REVERSER

FAN COWL

NOSE COWL

AL_MF_011700_1_0010102_01_00

Nacelle ContoursNacelle Contours - TRENT 900 Engines

1-17Page 2

Oct 01/09



X=175.62X=1341.77 X=3519.98 X=6036.19

X=6364.77X=6960.47

X=8134.4

PLUG

PRIMARY NOZZLE

THRUST REVERSERFAN COWL

NOSE COWL

X=−157.69

X=0

IVGOVG

X=3443.44 X=3595.64

A

X=6996.85

Z=0

Y=0

Y=1938.18

Z=1889.531

Z=1989.64

Y=1938.18

AL_MF_011700_1_0020101_01_00

Nacelle ContoursNacelle Contours - GP 7200 Engines

1-17Page 3

Oct 01/09


TERMINAL AND RAMP

2-1 Airplane Servicing Arrangement


Airplane Servicing Arrangement

1. General

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 the positioning and operation on the ramp.For each ramp layout, the associated typical turn-round time is given in a Chart in the section 2-2.

2-1Page 1

Oct 01/09



0 5 10METERS

0 16 32FEET

2 2

RL28/B1A/800/STD

GATE DIMENSIONS (A380 + 7.50 m (24.60 ft)):

− STORAGE AREA: 2 x 931 m (2 x 10021 ft )

AC: AIR COND UNIT GPU: GROUND POWER UNITAIR: AIR START UNIT LV: LAVATORY VEHICLECAT: CATERING VEHICLECLEAN: CLEANING VEHICLE TOW: TOWING TRACTOR

WV: POTABLE WATER VEHICLECONVEYOR: CONVEYOR BELTFUEL: FUEL HYDRANT DISPENSER

PL: PALLET/CONTAINER LOADER

− WIDTH: 87.50 m (287 ft)− LENGTH: 80.20 m (263 ft)

FUEL

FUEL

G.P

.U

G.P

.U

TOW

CLE

AN

CA

T

PL

PL

CO

NV

EY

OR

WV

CLE

AN

CA

T

AIR

AC

LV

CA

T

UD

CA

T

UDCAT: UPPER DECK CATERING VEHICLE

L_MF_020100_1_0010102_01_00

Typical Ramp Layout -- Two BridgesServicing Via Main and Upper Decks

2-1Page 2

Oct 01/09



RL01/B1A/800/STD

FUEL

FUEL

G.P

.U

G.P

.U

TOW

CLE

AN

CA

T

PL

PL

CO

NV

EY

OR

WV

CLE

AN

CA

T

AIR

AC

0 5 10METERS

0 16 32FEET

CA

T

LV

2 2



AC: AIR COND UNIT GPU: GROUND POWER UNITAIR: AIR START UNIT LV: LAVATORY VEHICLECAT: CATERING VEHICLECLEAN: CLEANING VEHICLE TOW: TOWING TRACTOR

WV: POTABLE WATER VEHICLECONVEYOR: CONVEYOR BELTFUEL: FUEL HYDRANT DISPENSER



CA

T

L_MF_020100_1_0020102_01_00

Typical Ramp Layout -- Two BridgesServicing Via Main Deck

2-1Page 3

Oct 01/09



L_AC_050103_0_AAM0_01_04

BA

SE

LIN

E

HIG

H

VE

RY

HIG

H

BA

SE

LIN

E

SC

EN

AR

IOS

PR

OD

UC

T &

SE

RV

ICE

DIF

FE

RE

NT

IAT

ION

TU

RN

−R

OU

ND

TIM

E(T

RT

)

OP

PO

RT

UN

ITIE

S O

F D

IRE

CT

UP

PE

R D

EC

K (

UD

) A

CC

ES

SF

OR

AIR

PO

RT

S &

AIR

LIN

ES

M2

U1

U1

M1

M2

BE

NE

FIT

S R

EA

LIS

ED

DE

PE

ND

LA

RG

ELY

ON

CA

BIN

LA

YO

UT

& B

OA

RD

ING

PR

OC

ED

UR

ES

SIM

ILA

R T

O B

AS

ELI

NE

MD

AC

CE

SS

M1

M2

SIM

ILA

R T

O B

AS

ELI

NE

MD

AC

CE

SS

L_MF_020100_1_0030102_01_00

Opportunities of Direct Upper Deck Accessfor Airport and Airlines

2-1Page 4

Oct 01/09



FUEL

FUEL

G.P

.UG

.P.U

TOW

PL

PL

CO

NV

EY

OR

WV

0 5 10METERS

0 16 32FEET

LV

RL04/B1/800F/STD

PL PL

2 2



AC: AIR COND UNIT

GPU: GROUND POWER UNIT

AIR: AIR START UNITLV: LAVATORY VEHICLE

TOW: TOWING TRACTORWV: POTABLE WATER VEHICLE

CONVEYOR: CONVEYOR BELTFUEL: FUEL HYDRANT DISPENSER

PS: PASSENGER STAIRS

AIR



PS P

S

L_MF_020100_1_0040102_01_00

Typical Ramp Layout

2-1Page 5

Oct 01/09


2-2 Turnaround Stations


Turnaround Stations

1. General

This section provides typical turn-round time charts showing the typical times for ramp activitiesduring aircraft turn-round.Actual times may vary due to each operator’s specific practice and operating conditions.For each turn-round time chart, the associated typical ramp layout is given in section 2-1.

2. Assumed Turn-Round Time Parameters For A380-800

A. PASSENGER BOARDING/DEBOARDING (PB/D) → 100% (555 pax) passenger exchange :- Doors (type A - 42″ wide) used : M1L and M2L (main deck) and U1R (upper deck).- PB/D rate : boarding = 15 pax/min / deboarding = 25 pax/min- Last Pax Seating Allowance (LPS) = + 4 min- 60″ stair flow rate : up-flow = 14 pax/min / down-flow = 18 pax/min

B. CARGO → Full LD-3 exchange (22 + 16) LD-3 and bulk exchange of 2 000 kg (4 409 lb) :- LD-3 off-loading/loading times :

off-loading = 1.4 min/LD-3 / loading = 1.7 min/LD-3- Pallet loading times :

off-loading = 2.5 min/pallet / loading = 2.9 min/pallet- bulk off-loading/loading times :

off-loading = 9.2 min/t / loading = 10.5 min/t

C. REFUELLING → Block fuel for Nominal Range through 4 nozzles :- 261 200 liters (67 364 US gallons) at 40 psi (48 min)- dispenser positioning or removal = 3 min (fuel truck change) / if any = 5 min

D. CLEANING → Full cleaning :- Crew adapted to match catering time

E. CATERING → Full catering :- average truck capacity = 30 Full Size Trolley Equivalent (FSTE)- simultaneous catering and PB/D = not represented- inbound/outbound FSTE = mixed in the same truck- FSTE exchange time :- dedicated door-galley = 1.5 min/FSTE- cart circulation (1 seat zone) = + 0.5 min/FSTE- cart circulation (> 1 seat zone) = + 1.0 min/FSTE- via lift :dedicated door to single lift = 2.0 min/FSTE

F. GROUND HANDLING/SERVICING- start of operations :

2-2Page 1

Oct 01/09


- bridges = t0 = 0others = t0 + 1 min

- vehicle positioning/removal = 2 min (fuel truck excluded)- upper deck vehicle positioning/removal = 3 min- clearance between GSE = 0.5 m (20 in)- Ground Power Unit (GPU) = up to 4 × 90 kVA- air conditioning = two carts- potable water (standard/option) = 1 700/2 500 liters (495/660 US gal) at 60 l/min (23 US

gal/min).- waste water = discharge and rinsing- dollies per tractor = 4 to 6

3. The A380-800F can achieve turn-round times of 120 ± 20 minutes depending on ULD layouts on thethree decks.

NOTE : These values are similar to other wide-body freighter aircraft in similar operating conditions.

2-2Page 2

Oct 01/09



BRIDGES

DEBOARDING/BOARDING&LPS

LD−3 CARGO FWD

LD−3 CARGO AFT

FREIGHT

BULK

CLEANING

POTABLE WATER

WASTE WATER

REFUELLING

DB1A

CATERING AT M2R

CATERING AT M4R

CATERING AT M1R

CATERING AT M5R

CATERING AT U1R

CATERING AT U3L

0 10 20 30 40 50 60 70 80 90

TURN−ROUND TIME IN MINUTES

2

14 422

3731

22

0 0

18 21

30

21

20

48

CRITICAL PATH

90’

2

27

36

EQUIPMENTPOSITIONING / REMOVAL

0 10 20 30 40 50 60 70 80 90

32

36

20

L_MF_020200_1_0010102_01_00

Baseline Turn-Round Time -- Two BridgesServicing Via Main and Upper Decks

2-2Page 3

Oct 01/09



BRIDGES

TURNAROUND TIME IN MINUTES

LD−3 CARGO FWD

LD−3 CARGO AFT

FREIGHT

BULK

CLEANING

POTABLE WATER

WASTE WATER

REFUELLING

126’

CATERING @M2R

CATERING @M4R

CATERING @M5L

CATERING @U1R

CATERING @U3R

0 10 20 30 40 50 60 70 80 90 100 120110

DEPLANING/

0 10 20 30 40 50 60 70 80 90 100 120110

CABIN

STANDARD 555 PAX PAX 555 TWO BRIDGES(M1,M2) MD CATERING

BOARDING&LPS

2 2

37

0

13

17 20

22 4

21

84

36

20

0

0

0

48

28

20

30

31

18

EQUIPMENTPOSITIONING / REMOVAL

L_MF_020200_1_0020102_01_00

Typical Turn-Round Time -- Two BridgesServicing Via Main Deck

2-2Page 4

Oct 01/09


2-3 Ground Service Connections and Locations


Ground Service Connections and Locations

1. General

This section gives the ground service connections and locations.

2-3Page 1

Oct 01/09



1 − PRESSURE REFUEL CONNECTORS2 − HYDRAULIC RESERVOIR SERVICING PANEL

(RESERVOIR FILLING AND RESERVOIR PRESSURISATION)3 − ENGINE OIL FILLING4 − VF GENERATOR OIL FILLING5 − TOILET AND WASTE SERVICE PANEL6 − GROUND ELECTRICAL POWER7 − LOW PRESSURE PRECONDITIONED AIR

DB1A

8 − YELLOW HYDRAULIC GROUND CONNECTOR9 − GREEN HYDRAULIC GROUND CONNECTOR10 − POTABLE WATER SERVICE PANEL11 − APU OIL FILLING12 − HIGH PRESSURE AIR ENGINE START13 − REFUEL/DEFUEL CONTROL PANEL14 − OXYGEN SYSTEM

4 3 4 3 11

7 115

3

4

8

3

4

6

14

12 10

13

2

94

3

4

3

1

5

1

15

15

15 − POTABLE WATER DRAIN PANEL

L_MF_020300_1_0010102_01_00

Ground Service Connections LayoutA380-800 Models

2-3Page 2

Oct 01/09



1 − PRESSURE REFUEL CONNECTORS2 − HYDRAULIC RESERVOIR SERVICING PANEL

(RESERVOIR FILLING AND RESERVOIR PRESSURISATION)3 − ENGINE OIL FILLING4 − VF GENERATOR OIL FILLING5 − TOILET AND WASTE SERVICE PANEL6 − GROUND ELECTRICAL POWER7 − LOW PRESSURE PRECONDITIONED AIR

8 − YELLOW HYDRAULIC GROUND CONNECTOR9 − GREEN HYDRAULIC GROUND CONNECTOR10 − POTABLE WATER SERVICE PANEL11 − APU OIL FILLING12 − HIGH PRESSURE AIR ENGINE START13 − REFUEL/DEFUEL CONTROL PANEL14 − OXYGEN SYSTEM

DB1A

5 4 3 4 3 11

7 11

8

6

12

13

2

94

3

4

3

1

14

10

1

3

4

3

4

L_MF_020300_1_0020102_01_00

Ground Service Connections LayoutA380-800F Models

2-3Page 3

Oct 01/09



Hydraulic System

1. Doors Location

DISTANCE : Meters (ft)

FROM AIRPLANECENTERLINE

AFT OF NOSER SIDE L SIDE

MEANHEIGHTFROM

GROUNDGreen hydraulic groundconnectors :(Access door 469FL)

34.67 (113.7) 14.90 (48.88) 5.08(16.67)

Yellow hydraulic groundconnector :(Access door 479FL)

34.67 (113.7) 14.90 (48.88) 5.08 (16.67)

Hydraulic Reservoir ServicingPanel :(Access door 197CB)

31.89 (104.63) 2.34 (7.68) 1.71 (5.61)

A. Reservoir pressurization- one connector ETRTO V0.09.6, 1/4 in.

B. Reservoir filling- One connector AE96993E, 1/4 in.

2-3Page 4

Oct 01/09



A

B

RESERVOIRPRESSURIZATION

CONNECTOR

RESERVOIR FILLINGCONNECTOR

Z190

A

B

L_MF_020300_1_0270101_01_00

Ground Service ConnectionsHydraulic Reservoir Servicing Panel

2-3Page 5

Oct 01/09



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_MF_020300_1_0300101_01_00

Ground Service ConnectionsHydraulic Ground Connections

2-3Page 6

Oct 01/09



Electrical System

1. Electrical System for A380-800 Models.




MEANHEIGHTFROM

GROUNDRight side access door :134AR

5.99 (19.65) 0.45 (1.48) 2.59 (8.49)

Left side access door : 133AL 5.99 (19.65) 0.45 (1.48) 2.59 (8.49)

A. External Power Receptacles :- Four standard ISO R461 receptacles - 90 KVA each.

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

C. Electrical connectors for servicing :- AC outlets : HUBBEL 5258- DC outlets : HUBBEL 7472- Vacuum cleaner outlets : HUBBEL 5258

2. Electrical System for A380-800F Models.




MEANHEIGHTFROM

GROUNDAccess door : TBD 5.99 (19.65) 0.45 (1.48) 2.59 (8.49)

A. External Power Receptacles :- Two standard ISO R461 receptacles - 90 KVA each.

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

C. Electrical connectors for servicing :- AC outlets : HUBBEL 5258- DC outlets : HUBBEL 7472

2-3Page 7

Oct 01/09



A

B

A

B

EXTERNAL POWER RECEPTABLES


L_MF_020300_1_0280101_01_00

Ground Service ConnectionsElectrical Service Panel - A380-800 Models

2-3Page 8

Oct 01/09



A


A

L_MF_020300_1_0290101_01_00

Ground Service ConnectionsElectrical Service Panel - A380-800F Models

2-3Page 9

Oct 01/09



Fuel System

1. Ground Service Panel




MEANHEIGHTFROM

GROUND

Refuel/Defuel control panel: (Access door 199KB)

41.55 (136.31) 0.68 (2.23) 1.98 (6.50)

2. Refuel/Defuel connectors

Refuel/defuel coupling, left(Access door 522GB)

31.89 (104.63) 17.97 (58.96)MAX 5.94(19.49)

Refuel/defuel coupling,right (Access door 622GB)

31.89 (104.63) 17.97 (58.96)MAX 5.94(19.49)

A. Refuel/Defuel couplings :- Standard ISO R45, 2.5 in., two per wing

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

2-3Page 10

Oct 01/09



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_MF_020300_1_0310101_01_00

Ground Service ConnectionsRefuel/Defuel Control Panel

2-3Page 11

Oct 01/09



REFUEL PRESSURE

REFUEL / DEFUEL COUPLINGS

Z500

Z600 ALH SIDE SHOWN

RH SIDE SYMETRICAL

B

B

A

A

L_MF_020300_1_0320101_01_00

Ground Service ConnectionsPressure Refuel Connectors

2-3Page 12

Oct 01/09



Pneumatic System

1. Low Pressure Air Connectors for Preconditioned Air :


FROM AIRPLANECENTERLINEAFT OF NOSER SIDE L SIDE

MEAN HEIGHTFROM GROUND

Access doors 191GB, 21.85 (71.69) 1.24 (4.07) 2.08 (6.82)

Access doors 191JB 22.36 (73.36) 1.76 (5.77) 2.08 (6.82)

Access doors 192HB 21.85 (71.69) 1.24 (4.07) 2.08 (6.82)

Access doors 192KB 22.36 (73.36) 1.76 (5.77) 2.08 (6.82)

A. Connectors :- Four standard MS33562 (ISO1034), 8 in.

2. High Pressure Air Connectors for Cabin Heating, Cooling and Engine Starting :


FROM AIRPLANECENTERLINEAFT OF NOSE

R SIDE L SIDE


Access doors 193BB 25.37 (83.23) 0.2 (0.66) 1.78 (5.84)

A. Connectors :- three standard MS33740 (ISO2026), 3 in.

2-3Page 13

Oct 01/09



LOW PRESSURE AIR CONNECTOR

Z190

BB

B

BA

A

B

L_MF_020300_1_0330101_01_00

Ground Service ConnectionsLow Pressure Preconditioned Air

2-3Page 14

Oct 01/09



HIGH PRESSURE AIR CONNECTORS

Z190

BA

A

B

L_MF_020300_1_0340101_01_00

Ground Service ConnectionsHigh Pressure Preconditioned Air

2-3Page 15

Oct 01/09



Potable Water System

1. Potable Water Ground Service Panel for A380-800 Models:




MEANHEIGHTFROMGROUND

Potable water groundservice panel (access door199NB)

43.67 (143.27) 0.37 (1.21) 2.18 (7.15)

Potable water drain panel(access door 133BL)

9.83 (32.25) 0.3 (0.98) 2.74 (8.99)

A. Connectors :- Fill/Drain Nipple, 3/4 in.

B. Capacity :- Standard configuration - six tanks : 1700 l (449 USgal)- Optional : 2266 l (598 USgal)

C. Filling pressure :- Max Filling Pressure: 8.6 bar (125 psi)

2. Potable Water Ground Service Panel for A380-800F Models :





Access door TBD 5.99 (19.65) 0.45 (1.48) 2.59 (8.49)

A. Connectors :- Fill/Drain Nipple, 3/4 in.

B. Capacity :- Standard configuration - one tank : 80 l (21 USgal)- Option available for reservoir of 160 l (42 USgal)

C. Filling pressure :- Max Filling Pressure: 8.6 bar (125 psi)

2-3Page 16

Oct 01/09



80LWL PRE

1000

0/

PRESS UP OR DOWN TO PRESET

0

50

DOWN PRESET WATER UP

MENUSELECT

DRAIN FILL

NORMAL

FILL/DRAIN NIPPLE

Z190

BA

A

BL_MF_020300_1_0350101_01_00

Ground Service ConnectionsPotable Water Ground Service Panel - A380-800 Models

2-3Page 17

Oct 01/09



SWITCH FOR PANEL CLOSING FILL/DRAIN NIPPLE TANK FULL INDICATOR

OVERFLOW NIPPLEHANDLE

C

O

A

A

L_MF_020300_1_0360101_01_00

Ground Service ConnectionsPotable Water Ground Service Panel - A380-800F Models

2-3Page 18

Oct 01/09



ACCESS DOOR

DRAIN NIPPLE

FWD CARGOFWD CARGOCOMPARTMENTDOOR

DRAIN VALVECONTROL HANDLE

Z130A

B

B

A

FR23

FR24

FR23

FR24

L_MF_020300_1_0370101_01_00

Ground Service ConnectionsPotable Water Drain Panel

2-3Page 19

Oct 01/09



Engine Oil Servicing

1. Engine Oil Servicing (TRENT 900 Engines)





Engine 1 (access door416BR)

32.65 (107.12) 23.58 (77.36) 4.24 (13.91)


24.98 (81.96) 12.74 (41.79) 3.83 (12.56)


24.98 (81.96) 16.61 (54.49) 3.83 (12.56)


32.65 (107.12) 27.45 (90.05) 4.24 (13.91)

2. Engine Oil Servicing (GP 7200 Engines)





Engine 1 (access door415CL)

33.03 (108.37) 27.42 (89.96) 4.4 (14.44)


25.35 (83.17) 16.62 (54.53) 3.13 (10.27)


25.35 (83.17) 12.78 (41.93) 3.13 (10.27)


33.03 (108.37) 23.62 (77.49) 4.4 (14.44)

2-3Page 20

Oct 01/09



A

OIL TANK

OIL FILLER CAP

OIL LEVELSIGHT GLASS

A

L_MF_020300_1_0380101_01_00

Ground Service ConnectionsEngine Oil Servicing - TRENT 900 Engines

2-3Page 21

Oct 01/09



PW

VE

−002

36 (1

007)

"T" HANDLE

OIL TANKFILLER CAP

OIL TANKSIGHT GAGE

PINENGAGEMENT

A

B

BFWD

A

L_MF_020300_1_0390101_01_01

Ground Service ConnectionsEngine Oil Servicing - GP 7200 Engines

2-3Page 22

Oct 01/09



VFG Oil Servicing

1. VFG oil servicing (TRENT 900 Engines)


FROM AIRPLANE CENTERLINE




33.17 (108.83) 26.14 (85.76) 2.56 (8.39)


25.57 (83.89) 15.31 (50.22) 1.33 (4.36)


25.57 (83.89) 13.93 (45.70) 1.33 (4.36)


33.17 (108.83) 24.90 (81.69) 2.56 (8.39)

2. VFG oil servicing (GP 7200 Engines)





Engine 1 34.49 (113.16) 25.43 (83.43) 2.63 (8.63)

Engine 2 26.81 (87.96) 14.63 (48.00) 1.36 (4.46)

Engine 3 26.81 (87.96) 14.63 (48.00) 1.36 (4.46)

Engine 4 34.49 (113.16) 25.43 (83.43) 2.63 (8.63)

For VFG (GP 7200 Engines), open:- Fan Exhaust Cowl (engine 1 - 4)- Thrust Reverser Cowl (engine 2 -3)

2-3Page 23

Oct 01/09



A

1

B

8

7

DISCONNECT WHEN ONLY DROPS 4

2

65

3

COME OUT SLOWLY

OIL LEVEL

A

B

L_MF_020300_1_0400101_01_01

Ground Service ConnectionsVFG Oil Servicing - TRENT 900 Engines

2-3Page 24

Oct 01/09



A

OIL LEVEL

DISCONNECT WHEN ONLY DROPSCOME OUT SLOWLY

2

3

4

7

8

6

C

1

C

CASE DRAINPLUG

A

5

B

B

L_MF_020300_1_0420101_01_01

Ground Service ConnectionsVFG Oil Servicing - GP 7200 Engines

2-3Page 25

Oct 01/09



Starter Oil Servicing

1. Starter Oil Servicing (TRENT 900 Engines)





Engine 1 39.78 (130.51) 25.78 (84.57) 2.59 (8.49)

Engine 2 32.15 (105.49) 14.94 (49.01) 1.39 (4.56)

Engine 3 32.15 (105.49) 14.42 (47.30) 1.39 (4.56)

Engine 4 39.78 (130.51) 25.25 (82.84) 2.59 (8.49)

2. Starter Oil Servicing (GP 7200 Engines)





Engine 1 40.42 (132.61) 27.34 (89.70) 3.35 (10.99)

Engine 2 32.74 (107.41) 16.55 (54.30) 2.47 (8.10)

Engine 3 32.74 (107.41) 12.71 (41.70) 2.47 (8.10)

Engine 4 40.42 (132.61) 23.53 (77.20) 3.35 (10.99)

For access to Starter Oil Servicing, open Fan Cowl

2-3Page 26

Oct 01/09



A

OIL FILL PLUG

OILSIGHTGLASS

A

L_MF_020300_1_0430101_01_00

Ground Service ConnectionsStarter Oil Servicing - TRENT 900 Engines

2-3Page 27

Oct 01/09



PW

VE

−005

49 (

0308

)

PNEUMATIC STARTER

MAGNETICCHIP

DETECTOR

STARTER CONTROL VALVE

V−BANDCLAMP

AND QADADAPTER

FILLPORT

5000ES 4005KS

A

A

L_MF_020300_1_0440101_01_01

Ground Service ConnectionsStarter Oil Servicing - GP 7200 Engines

2-3Page 28

Oct 01/09



APU Oil Servicing

1. APU Oil





Access door 315BL 67.55 (217.36) 0.44 (1.44) 6.83 (22.40)

A. Capacity:- 18.13L (4.85 US gal)

2-3Page 29

Oct 01/09



Z310

FULL MARK

VISUAL SIGHT−GLASS

FILL CAP

B

A

FWD

FR117

FR112C

B

A

C

L_MF_020300_1_0450101_01_00

Ground Service ConnectionsAPU Oil Servicing

2-3Page 30

Oct 01/09



Vacuum Toilet System

1. Vacuum Toilet System For A380-800 Models





Access door 171AL 53.31 (174.90) 0.26 (0.85) 3.40 (11.15)

A. Connectors :- Flushing and filling : 1 in.- Draining : 4 in.

B. Capacity : 2100 l

C. Operating pressure for the waste tank rinsing process: 50 psi (max 125 psi)

D. Flow rate : 40 l/min

2. Vacuum Toilet System For A380-800F Models


FROM AIRPLANECENTERLINEAFT OF NOSER SIDE L SIDE


Access door TBD 11.11 (36.45) 2.48 (8.14) 3.51 (11.52)

A. Connectors :- Flushing and filling : 1 in.- Draining : 4 in.

B. Capacity : 80l

C. Operating pressure for the waste tank rinsing process: 50 psi (max 125 psi)

D. Flow rate : 40 l/min

2-3Page 31

Oct 01/09



WASTE TANK DRAIN VALVEOPEN

UPPERDECK

MAINDECK

RH LH RH LH

CLOSE

CONTROLLEVER

CONNECTIONWASTE DRAIN

FILL AND RINSECONNECTION

FWDB

Z160

FR86FR91A

A

B

L_MF_020300_1_0460101_01_00

Ground Service ConnectionsVacuum Toilet System - A380-800 Models

2-3Page 32

Oct 01/09



Z130 A

FR22

FR38

CONTROL LEVERWASTE DRAIN

FILL AND RINSE

CONNECTION

CONNECTION

B

B

A

FWD

L_MF_020300_1_0470101_01_00

Ground Service ConnectionsVacuum Toilet System - A380-800F Models

2-3Page 33

Oct 01/09



Oxygen System

1. Door Location





Access door: 272AFZ 7.45 (24.44) 2.23 (7.32) 3.25 (10.66)

Zero, one or two service connections (external charging in the avionics compartment) MS22066 Std

2-3Page 34

Oct 01/09



A

AL_MF_020300_1_0480101_01_00

Ground Service ConnectionsOxygen System

2-3Page 35

Oct 01/09


2-4 Interior Arrangements


Interior Arrangements

1. General

This section gives standard interior arrangements.

2-4Page 1

Oct 01/09



STOWAGES 1

PASSENGER SEATS UPPER DECK (199 TOTAL)

BUSINESS CLASS 96 SEATS

TOURIST CLASS 103 SEATS

ATTENDANT SEATS 8

COAT STOWAGE 6

GALLEYS 8

LIFT 2

UPPER DECK

LAVATORIES 7

STAIRS 2

CREW REST BUNKS 5

L_MF_020400_1_0010102_01_00

Interior Arrangements - Plan ViewStandard Configuration - Upper Deck

2-4Page 2

Oct 01/09



PASSENGER SEATS MAIN DECK (356 TOTAL)

FIRST CLASS 22 SEATS

TOURIST CLASS 334 SEATS

COAT STOWAGE 1

STOWAGES 1

GALLEYS 9

MAIN DECK

LAVATORIES 10

ATTENDANT SEATS 12

LIFT 2

STAIRS 2

L_MF_020400_1_0020102_01_00

Interior Arrangements - Plan ViewStandard Configuration - Main Deck

2-4Page 3

Oct 01/09



MAIN DECK SERVICE AREA

UPPER DECK COURIER AREA

UPPER DECKCARGOCOMPARTMENT

STAIR

COURIER AREA

BARRIER

BARRIERSTAIR

12 SEATS B/C

MAIN DECKCARGOCOMPARTMENT

STOWAGES 1

ATTENDANT SEATS 2

GALLEYS 1

LAVATORIES 1

L_MF_020400_1_0030102_01_00

Interior Arrangements - Plan ViewStandard Configuration - Cargo Compartments

2-4Page 4

Oct 01/09



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_MF_020400_1_0040102_01_00

Interior Arrangements - Cross-sectionTypical Configuration - Upper Deck

2-4Page 5

Oct 01/09



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_MF_020400_1_0050102_01_00

Interior Arrangements - Cross-sectionTypical Configuration - Main Deck

2-4Page 6

Oct 01/09



UPPER DECKCARGO COMPARTMENT

MAIN DECKCARGO COMPARTMENT

LOWER DECKCARGO COMPARTMENT

UPPER DECKCOURIER AREA

L_MF_020400_1_0060102_01_00

Interior Arrangements - Cross-sectionTypical Configuration

2-4Page 7

Oct 01/09


2-5 Escape Slides


Escape Slides

1. General

This section gives location of cabin escape facilities and related clearances.

2. Location

A. A380-800 ModelsEscape 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 slide for each emergency exit door (total two). The slides are housed in the belly

fairing for off-the-wing evacuation.

2-5Page 1

Oct 01/09



OFFWING SLIDE

MAIN DECK SLIDE

UPPER DECK SLIDE

MAIN DECK SLIDE

UPPER DECK SLIDEMAIN DECK SLIDE

MAIN DECK SLIDE

UPPER DECKSLIDE

L_MF_020500_1_0010101_01_00

Escape Slides/RaftsLocation

2-5Page 2

Oct 01/09



0

3

EMERGENCY EVACUATION

GRID EQUALS 1m IN REALITY

6

9

12

15

18

21

24

27

30

33

36

39

L_MF_020500_1_0020101_01_00

Escape Slides/RaftsDimensions

2-5Page 3

Oct 01/09


2-6 Galley


Galley

1. General

This section gives information on Galleys Location and General Layout.

2-6Page 1

Oct 01/09



MA

IN D

EC

K

UP

PE

R D

EC

K

FLEXIBLE INSTALLATION ZONES FOR TRANSVERSAL GALLEYS

MA

XF

LEX

AR

EA

LAT

ER

AL

MA

XF

LEX

AR

EA

LAT

ER

AL

MA

XF

LEX

AR

EA

CE

NT

ER

MA

XF

LEX

AR

EA

CE

NT

ER

L_MF_020600_1_0010101_01_00

General Location of Transversal Galleys

2-6Page 2

Oct 01/09



TRANSVERSAL GALLEY MODULE

L_MF_020600_1_0020101_01_00

General LayoutTransversal Galley (Sheet 1)

2-6Page 3

Oct 01/09



TRANSVERSAL GALLEY MODULE

L_MF_020600_1_0030101_01_00

General LayoutTransversal Galley (Sheet 2)

2-6Page 4

Oct 01/09



MA

IN D

EC

K

UP

PE

R D

EC

K

FLEXIBLE INSTALLATION ZONES FOR LONGITUDINAL GALLEYS

MA

XFL

EX

AR

EA

LAT

ER

AL

MA

XFL

EX

AR

EA

LAT

ER

AL

MA

XFL

EX

AR

EA

CE

NT

ER

MA

XFL

EX

AR

EA

CE

NT

ER

L_MF_020600_1_0040101_01_00

General LocationLongitudinal Galleys

2-6Page 5

Oct 01/09



LONGITUDINAL GALLEY MODULE

L_MF_020600_1_0050101_01_00

General LayoutLongitudinal Galleys (Sheet 1)

2-6Page 6

Oct 01/09



LONGITUDINAL GALLEY MODULE

L_MF_020600_1_0060101_01_00

General LayoutLongitudinal Galleys (Sheet 2)

2-6Page 7

Oct 01/09


2-7 Cargo


Cargo

1. General

This section gives information related to cargo compartment location/dimensions and loading.

NOTE : For cargo door clearances, refer to Section 1-10.

A. Arrangements

(1) A380-800 ModelsThere are three cargo compartments (forward, aft and bulk), all located on the lower deck.

(2) A380-800F ModelsThere are five cargo compartments as follows :- three lower deck cargo compartments (forward, aft and bulk),- one main deck cargo compartment,- one upper deck cargo compartment.

B. Loading/UnloadingAll the cargo compartments can be used independently within the overall weight andperformance limitations of the aircraft.All the cargo compartments (except the lower deck bulk cargo compartment) are equipped forsemi-automatic power assisted cargo handling.

(1) Lower deck forward and aft cargo compartments (A380-800/800F Models)These compartments can accommodate the following Unit Load Devices (ULDs) :- Half-size containers,- Full-size containers,- 60.4 in x 61.5 in pallets,- 60.4 in x 125 in pallets,- 88 in x 125 in pallets,- 96 in x 125 in pallets.

(2) Lower deck bulk cargo compartment (A380-800/800F Models)This compartment can accommodate bulk cargo and/or be used for the transportation oflive animals (as limited by the compartment’s characteristics and conditions).The usable volume is approximately 18.4 m3 (650 ft3) for the A380-800F model, and 14.3m3 (505 ft3) for the A380-800 model.

(3) Main and upper deck cargo compartments (A380-800F Models)These compartments can accommodate the following Unit Load Devices (ULDs) :- 96 in x 125 in containers,- 96 in x 125 in pallets.

2-7Page 1

Oct 01/09



FO

RW

AR

D A

FT

CA

RG

O

CO

MP

AR

TM

EN

T)

LOW

ER

DE

CK

FO

RW

AR

D C

AR

GO

CO

MP

AR

TM

EN

T

LOW

ER

DE

CK

FO

RW

AR

D A

FT

CA

RG

OC

OM

PA

RT

ME

NT

(T−

SH

AP

ED

LOW

ER

DE

CK

RE

AR

AF

T C

AR

GO

CO

MP

AR

TM

EN

T

LOW

ER

DE

CK

BU

LK C

AR

GO

CO

MP

AR

TM

EN

T

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)

8.2 m(322.8 in)

FR

17F

R44

FR

57F

R90

FR

86F

R17

FR

44F

R57

FR

90F

R86

2.8 m

17.4 m(685.04 in)

L_MF_020700_1_0010101_01_00

Cargo CompartmentsLocation and Dimensions - A380-800 Models

2-7Page 2

Oct 01/09



LOW

ER

DE

CK

FO

RW

AR

D C

AR

GO

CO

MP

AR

TM

EN

T

LOW

ER

DE

CK

FO

RW

AR

D A

FT

CA

RG

OC

OM

PA

RT

ME

NT

(T−

SH

AP

ED

CO

MP

AR

TM

EN

T)

RE

AR

AF

T C

AR

GO

CO

MP

AR

TM

EN

T

LOW

ER

DE

CK

BU

LK C

AR

GO

CO

MP

AR

TM

EN

T

UP

PE

R D

EC

KC

AR

GO

CO

MP

AR

TM

EN

TM

AIN

DE

CK

CA

RG

O C

OM

PA

RT

ME

NT LO

WE

R D

EC

KA

FT

CA

RG

OC

OM

PA

RT

ME

NT

LOW

ER

DE

CK

FO

RW

AR

D C

AR

GO

CO

MP

AR

TM

EN

T

LOW

ER

DE

CK

FO

RW

AR

D A

FT

CA

RG

OC

OM

PA

RT

ME

NT

(T−

SH

AP

ED

CO

MP

AR

TM

EN

T)

LOW

ER

DE

CK

RE

AR

AF

T C

AR

GO

CO

MP

AR

TM

EN

T

LOW

ER

DE

CK

BU

LK C

AR

GO

CO

MP

AR

TM

EN

T

UP

PE

R D

EC

KC

AR

GO

CO

MP

AR

TM

EN

TM

AIN

DE

CK

CA

RG

O C

OM

PA

RT

ME

NT LO

WE

R D

EC

KA

FT

CA

RG

OC

OM

PA

RT

ME

NT

FR

95

FR

27F

R21

FR

17

FR

90

L_MF_020700_1_0020101_01_00

Cargo CompartmentsLocation and Dimensions - A380-800F Models (Sheet 1)

2-7Page 3

Oct 01/09



FR

17F

R44

/45

FR

72

UP

PE

R D

EC

K

LOW

ER

DE

CK

MA

IN D

EC

K

FR

95

FR

90F

R86

FR

27F

R95

FR

57

UP

PE

R D

EC

K

LOW

ER

DE

CK

FR

21F

R95

FR

94

2.7 m(108 in)

43.2 m(1700.79 in)

4.3 m(170 in)

47.2 m(1858.27 in)

3.1 m(122.8 in) 17.4 m

(685.04 in)

2.8 m(110.2 in)

8.2 m(322.8 in)

9.7 m(381.9 in)

1.1 m(43.3 in)

2.8 m(110.2 in)

L_MF_020700_1_0030101_01_00

Cargo CompartmentsLocation and Dimensions - A380-800F Models (Sheet 2)

2-7Page 4

Oct 01/09



ST

AN

DA

RD

: 20

LD−

3 O

R 7

PA

LLA

TS

88

in /

96 in

X 1

25 in

OP

TIO

N: 2

2 LD

−3

OR

7 P

ALL

ET

S 8

8 in

/ 96

in X

125

inS

TA

ND

AR

D: 1

6 LD

−3

OR

6 L

D−

3 3

PA

LLA

TS

88

in /

96 in

X 1

25 in

OP

TIO

N: 6

PA

LLE

TS

88

in /

96 in

X 1

25 in

ST

AN

DA

RD

: 20

LD−

3 O

R 7

PA

LLA

TS

88

in /

96 in

X 1

25 in

OP

TIO

N: 2

2 LD

−3

OR

7 P

ALL

ET

S 8

8 in

/ 96

in X

125

inS

TA

ND

AR

D: 1

6 LD

−3

OR

6 L

D−

3 3

PA

LLA

TS

88

in /

96 in

X 1

25 in

OP

TIO

N: 6

PA

LLE

TS

88

in /

96 in

X 1

25 in

L_MF_020700_1_0040101_01_00

Cargo CompartmentsLoading Combinations - A380-800 Models

2-7Page 5

Oct 01/09



MA

IN D

EC

K L

OA

DIN

G 2

9 U

LD’S

LOW

ER

DE

CK

LO

AD

ING

36

LD−

3 O

R 6

LD

−3

+ 1

0 P

ALL

ET

S 8

8 in

OR

96

in X

125

in

UP

PE

R D

EC

K L

OA

DIN

G 2

5 U

DL’

S (

CO

NT

OU

RE

D P

ALL

ET

S)

L_MF_020700_1_0050101_01_00

Cargo CompartmentsLoading Combinations - A380-800F Models (Sheet 1)

2-7Page 6

Oct 01/09



UP

PE

R D

EC

K L

OA

DIN

G 5

3 A

YY

MA

IN D

EC

K L

OA

DIN

G 3

3 A

MJ

UP

PE

R D

EC

K L

OA

DIN

G 5

3 A

YY

MA

IN D

EC

K L

OA

DIN

G 3

3 A

MJ

L_MF_020700_1_0060101_01_00

Cargo CompartmentsLoading Combinations - A380-800F Models (Sheet 2)

2-7Page 7

Oct 01/09


2-8 Towing


Towing

1. This section provides information on aircraft Towing.

The A380-800/800F is designed with means for conventional towing or towbarless towing.Information on towbarless towing can be found in SIL 09-002 and chapter 9 of the AircraftMaintenance Manual.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 nose gear leg. The towbar fitting is installed at the front ofthe 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 to chapter 7 of theAircraft Recovery Manual).

NOTE : Information on aircraft towing procedures and corresponding aircraft limitations are given inchapter 9 of the Aircraft Maintenance Manual.

A. Figure 1: Ground Towing Requirements A380-800 Models shows the chart to determine thetowbar pull and tow tractor mass requirements as function of the following physicalcharacteristics:- Aircraft weight,- Slope,- Number of engines at idle.The chart is based on the A380-800 engine type with the biggest idle thrust. The chart istherefore valid for all A380-800 models.

B. Figure : Typical Tow Bar configuration 1 and Figure : Typical Tow Bar configuration 2 givesguidelines for the towbar.

2. Towbar design guidelines

The aircraft towbar shall respect the following norms:- SAE AS 1614, ”Main Line Aircraft TowBar Attach Fitting Interface”,- SAE ARP1915 Revision C, ”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 standard type towbar should be equipped with a damping system to protect the nose gear againstjerks and with towing shear pins:- A traction shear pin calibrated at 62000 daN (139381.53 lbf),- A torsion pin calibrated at 4800 m.daN (424778.76 lbf.in).

2-8Page 1

Oct 01/09


The towing head is designed according to SAE/AS 1614 (issue C) cat. V.

3. Maximum Extension of the NLG Shock Absorber.

- Measure the dimension H between the two red marks on the left side of the NLG.- Make sure that the dimension H of the NLG is never more than 295 mm (11.6 in.) when you tow

the aircraft (the compression of the shock absorber is 340 mm (13.4 in.)).

2-8Page 2

Oct 01/09



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

L_MF_020800_1_0010102_01_01

Ground Towing RequirementsGround Towing Requirements A380-800 Models

2-8Page 3

Oct 01/09



D1

MF

M

LONGHOLE BLOCKINGLATERAL MOVEMENTS

HOLES FOR SPARE SHEAR PINS

MF

LOCKING/UNLOCKING HANDLE

SHEAR PIND1

L

F F

Fshear

F

Mshear

Fshear

Lshear

M = Fshear

x L

Mshear

= Fshear

x Lshear

Mshear

= F x D1 (Mshear

< M)

D1 = (M/L) x Lshear

/ F

Fshear

= M / L

Mshear

= (M/L) x Lshear

D1 = (M x Lshear

/ (F x L)

A

AL_MF_020800_1_0020102_01_01

Ground Towing RequirementsTypical Tow Bar configuration 1

2-8Page 4

Oct 01/09



MF

D2

OVERSIZED HOLEWRT RETENTION BOLT

M

L

F

F/2

F/2

D2

D2 = (2 x Mshear

) / F D2 = (2 x M x Lshear

) / (F x L)

F M D1 D2

62000 4800 69.7 148.6

[daN] [m.daN] [mm] [mm]

RESULTS FOR A TOWBAR LENGTH OF Lshear

/L = 0.90

Fshear

Fshear

Lshear

Mshear

M = Fshear

x L

Mshear

= Fshear

x Lshear

Mshear

= F/2 x D2 (Mshear

< M)

Fshear

= M / L

Mshear

= (M / L) x Lshear

L_MF_020800_1_0030102_01_01

Ground Towing RequirementsTypical Tow Bar configuration 2

2-8Page 5

Oct 01/09



A

0.200 m(7.9 in)

A

0.555 m(21.85 in)

L_MF_020800_1_0040101_01_02

Ground Towing RequirementsNose Gear Towing Fittings

2-8Page 6

Oct 01/09



TOP OF TORQUELINK STOP

SHOULDER OF MAINFITTING LOWERBEARING

DETAIL A

DETAIL B

A

H

A

B

A

L_MF_020800_1_0050101_01_00

Ground Towing RequirementsMaximum Extension of the NLG Shock Absorber

2-8Page 7

Oct 01/09




Ground Maneuvering

1. General

This section provides information on airplane 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 guidelines for the method of determination of such parameters and for themaneuvering characteristics of this aircraft type.In the 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 throughout the world. Variations from standard aircraft operatingpatterns may be necessary to satisfy physical constraints within the maneuvering area, such asadverse grades, limited area or high risk of jet blast damage. For these reasons, ground maneuveringrequirements should be coordinated with the using airlines prior to layout planning.

2-9Page 1

Oct 01/09



R4

R3

R5

R6

55°

60°

65°

SEE PAGE 3 FOR DIMENSIONS

29.83 m (97.9 ft)

70°

NOTE:

L_MF_020900_1_0010101_01_00

Turning RadiiTurning Radii (Sheet 1)

2-9Page 2

Oct 01/09



NOTE:

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

TYPE 2 TURNS USE :SYMMETRIC THRUST AND NO BRAKING.

2 100.16328.6

TYPEOF

TURN

20

STEERINGANGLE

17.9

EFFECTIVESTEERING

ANGLE

mft

135.45444.4

101.01331.4

115.87380.1

2 78.86258.7

25 22.7 mft

113.14371.2

80.12262.9

94.90311.4

2 65.69215.5

30 27.5 mft

98.90324.5

67.33220.9

81.91268.7

2 56.84186.5

35 32.1 mft

88.97291.9

58.83193.0

73.13239.9

2 50.59166.0

40 36.6 mft

81.61267.8

52.89173.5

66.84219.3

2 46.02151.0

45 41.0 mft

75.94249.1

48.61159.5

62.16203.9

2 42.61139.8

50 45.1 mft

71.43234.4

45.45149.1

58.57192.2

1 40.13131.6

55 51.2 mft

67.02219.9

43.22141.8

55.43181.9

1 37.64123.5

60 57.3 mft

62.60205.4

40.98134.5

52.29171.5

1 35.15115.3

65 63.4 mft

58.18190.9

38.75127.1

49.15161.2

1 32.66107.2

70 69.5 mft

53.76176.4

36.52119.8

46.01150.9

R3 R4 R5 R6

A380−800/800F TURNING RADII

THE TURN.

L_MF_020900_1_0020101_01_00

Turning RadiiTurning Radii (Sheet 2)

2-9Page 3

Oct 01/09



A

R4

R3

R5

Y

R6

(TU

RN

ING

WID

TH

)

NOTE: SEE PAGE 5 FOR DIMENSIONS

65°

29.83 m (97.9 ft)

L_MF_020900_1_0030101_01_01

CL

Minimum Turning Radii(Sheet 1)

2-9Page 4

Oct 01/09



A

R4

R3

R5

Y

R6

(TU

RN

ING

WID

TH

)

55°

60°

65°

29.83 m ( 97.9 ft )

70°

TURN PERFORMED WITH ASYMMETRIC THRUST AND DIFFERENTIAL BRAKINGNOTE:

EffectiveSteering

AngleY

m

ft70° 69.5°

A380−800/800F Minimum Turning Radius

SteeringAngle

Typeof

Turn

11.08

36.3

A

50.91

167.0

R3

32.66

107.2

R4

53.76

176.4

R5

36.52

119.8

R6

46.01

150.91

L_MF_020900_1_0040101_01_00

Minimum Turning Radii(Sheet 2)

2-9Page 5

Oct 01/09



NOTE:

NLG PATH

COCKPIT TRACKPARALLEL TOGUIDE LINE

NOMINAL OFFSET

TAXIWAY GUIDELINEWLG PATH

FAA GROUP V JUDGEMENTAL OVERSTEER METHOD

45.7 m(150 ft)

R 45.7 m (150 ft)

4.99 m (16.4 ft)

R 25.9 m (85 ft)

6.62 m (21.7 ft)

7 m (23 ft)

22.9 m (75 ft)

L_MF_020900_1_0050101_01_00

135˚ Turn - Runway to Taxiway135˚ Turn - Runway to Taxiway (Sheet 1)

2-9Page 6

Oct 01/09



NOTE:

TAXIWAY GUIDELINE

WLG PATH

60 m

(196.9 ft) R 25.5 m (83.7 ft)

5.81 m(19.1 ft)

(98.4 ft)

FAA GROUP VI COCKPIT TRACKS CENTRELINE METHOD

30 m

R 51 m (167.3 ft)

L_MF_020900_1_0110101_01_00


2-9Page 7

Oct 01/09



NOTE:

NLG PATH

COCKPIT TRACKPARALLEL TOGUIDELINE

TAXIWAYGUIDELINE

WLG PATH


45.7 m(150 ft)

4.94 m (16.2 ft)

R 45.7 m (150 ft)

R 25.9 m (85 ft)

9.21 m(30.2 ft)

22.9 m (75 ft)

7 m (23 ft)

L_MF_020900_1_0060101_01_00


2-9Page 8

Oct 01/09



NOTE:

TAXIWAYGUIDELINE

WLG PATH


60 m(196.9 ft)

R 25.5 m (83.7 ft)

R 51 m (167.3 ft)

10.24 m

(33.6 ft)

30 m

(98.4 ft)

L_MF_020900_1_0130101_01_00


2-9Page 9

Oct 01/09



NOTE:

4.5 m(14.8 ft)

4.5 m(14.8 ft)

60.0 m (196.9 ft)

51.0 m (167.3 ft)

R36.6 m (119.9 ft)

0.7 m(2.2 ft)

16.8 m(55.0 ft)

31.2 m(102.4 ft)

23.2 m(76.2 ft)

R46.0 m

(150.9 ft)

R54.0 m (177.1 ft)

70° NOSE GEAR STEERING ASYMMETRIC THRUST AND BRAKINGON A 60.0 m (196.9 ft) WIDE RUNWAY.

L_MF_020900_1_0070101_01_00

180˚ Turn on a Runway

2-9Page 10

Oct 01/09



NOTE:


NLG PATH

TAXIWAYGUIDELINE

NOMINAL OFFSET

WLG PATH


22.9 m

(75 ft)

4.94 m

(16.2 ft)

8.85 m

(29 ft)

22.9 m

(75 ft)

R 25.9 m (85 ft)

R 45.7 m (150 ft)

7 m (23 ft)

L_MF_020900_1_0080101_01_00

90˚ Turn - Taxiway to Taxiway90˚ Turn - Taxiway to Taxiway (Sheet 1)

2-9Page 11

Oct 01/09



NOTE:

TAXIWAYGUIDELINE

WLG PATH


30 m

(98.4 ft)

R 25.5 m (83.7 ft)

30 m(98.4 ft)

R 51 m (167.3 ft)

8.67 m(28.5 ft)

75 m (246.1 ft)

L_MF_020900_1_0140101_01_00


2-9Page 12

Oct 01/09



NOTE:

NLG PATH


TAXIWAYGUIDELINE

WLG PATH


22.9 m

(75 ft)

R 45.7 m (150 ft)

R 25.9 m (85 ft)8.47 m(27.8 ft)

(23 ft)

4.99 m (16.4 ft)

22.9 m(75 ft)

7 m

L_MF_020900_1_0090101_01_00


2-9Page 13

Oct 01/09



NOTE:

TAXIWAY GUIDELINE

WLG PATH


R 25.5 m (83.7 ft)7.37 m

(24.2 ft)

(98.4 ft)

30 m

(98.4 ft)

R 51 m (167.3 ft)

30 m

L_MF_020900_1_0120101_01_00


2-9Page 14

Oct 01/09



NOTE:

(360 ft)

109.7 m

6.1 m

(20 ft)

12.2 m

(40 ft)

6.1 m

(20 ft)

COORDINATE WITH USING AIRLINE FOR SPECIFIC PLANNED OPERATING PROCEDURE

L_MF_020900_1_0100101_01_00

Runway Holding Bay (Apron)

2-9Page 15

Oct 01/09




Airplane Parking

1. General

This section gives information on Aircraft Parking.The following figures and charts show the rectangular space required for parking against the terminalbuilding :- Steering Geometry- Minimum Parking Space Requirements

2-10Page 1

Oct 01/09



PARKINGSTRAIGHT ENTRY PUSH BACK

PARKING45° ENTRY PUSH OUT

70.3

1 m

(23

0.7

ft)77

.07

m (

252.

9 ft)

80.81 m (265.1 ft)

94.64 m (310.5 ft)

L_MF_021000_1_0010101_01_00

Airplane ParkingSteering Geometry

2-10Page 2

Oct 01/09



0 10 20 30 40 50 60 70 80 90 100 110 120

20

30

40

50

60

70

80

90

100

0

20

40

60

80

100

120

140

160

180

200

220

240

260

280

300

0 20 40 60 80 100 120 140 160 180 200 220 240 260 280 300 320 340 360

DISTANCEOUT

FROM TERMINAL

DISTANCE ALONG TERMINAL (m)

DISTANCE ALONG TERMINAL (ft)

(m)(ft)

45° ENTRY PUSH OUT

STRAIGHT ENTRY PUSH BACK

10

L_MF_021000_1_0020101_01_00

Airplane ParkingSteering Geometry - Minimum Parking Space Requirements

2-10Page 3

Oct 01/09




Operating Conditions

1. Jet Engine Exhaust Velocities and Temperatures

This section shows the estimated engine exhaust efflux velocity and temperature contours forMaximum Take-off, Breakaway and Idle conditions for the A380 engine models.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 enginemodels, including the A380-800F Freighter version. Therefore, contours hereafter include contours ofthe A380-800 Passenger version.The Breakaway data are presented at a rating corresponding to the minimum thrust level required toinitiate movement of an A380-800F model at its maximum ramp weight from static position and onuphill ground.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 centreline.

A. Data from Rolls-Royce’s Trent 900The estimated efflux data are presented at ISA+15 ˚C (30 ˚C), Sea Level Static and negligiblewind 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 GP7200The estimated efflux data are presented at ISA+15 ˚C (30 ˚C), Sea Level Static with 20-knotheadwind. It also assumed ground plane and proximity effects.Velocity contours are presented at 35 MPH (15 m/s), 65 MPH (30 m/s) and 105 MPH (46m/s), while temperature contours are presented at 122 ˚F (50 ˚C), 212 ˚F (100 ˚C) and 392˚F (200 ˚C).Engine Alliance strongly recommends that jet blast studies using their contours include theeffect of a 20-knot headwind.

2. 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.

2-11Page 1

Oct 01/09


Regarding the risk of ingesting typical loose objects, which can be found on ground at the edge ofrunways/taxiways paved areas (loose gravels for example), it was demonstrated that the A380 outerengines are high enough above ground so that the risk og ingestion is remote in the followingconditions:- 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.

2-11Page 2

Oct 01/09



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_MF_021100_1_0010102_01_00

Engine Exhaust VelocitiesGround Idle Power - TRENT 900 Engines

2-11Page 3

Oct 01/09



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)

NOTE:

L_MF_021100_1_0020102_01_01

Engine Exhaust VelocitiesGround Idle Power - GP 7200 Engines

2-11Page 4

Oct 01/09



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_MF_021100_1_0030102_01_01

GROUND IDLE POWER

Engine Exhaust TemperaturesGround Idle Power -- TRENT 900 Engines

2-11Page 5

Oct 01/09



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_MF_021100_1_0040102_01_01

Engine Exhaust TemperaturesGround Idle Power -- GP 7200 Engines

2-11Page 6

Oct 01/09



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_MF_021100_1_0050102_01_00

Engine Exhaust VelocitiesBreakaway Power -- TRENT 900 Engines

2-11Page 7

Oct 01/09





PW

VE

−02

200

(020

7)


NOTE:

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)

L_MF_021100_1_0060102_01_01

Engine Exhaust VelocitiesBreakaway Power -- GP 7200 Engines

2-11Page 8

Oct 01/09



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_MF_021100_1_0070102_01_01

BREAKAWAY POWER(11% MAX TAKE−OFF THRUST)

Engine Exhaust TemperaturesBreakaway Power -- TRENT 900 Engines

2-11Page 9

Oct 01/09



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_MF_021100_1_0080102_01_00

Engine Exhaust TemperatureBreakaway Power -- GP 7200 Engines

2-11Page 10

Oct 01/09



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_MF_021100_1_0090102_01_00

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

2-11Page 11

Oct 01/09





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)




L_MF_021100_1_0100102_01_01

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

2-11Page 12

Oct 01/09



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_MF_021100_1_0110102_01_01

MAX TAKE−OFF POWER

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

2-11Page 13

Oct 01/09



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_MF_021100_1_0120102_01_00

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

2-11Page 14

Oct 01/09



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_MF_021100_1_0130102_01_00

APU Exhaust Velocities and TemperaturesMax. ECS Conditions

2-11Page 15

Oct 01/09



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_MF_021100_1_0140102_01_00

APU Exhaust Velocities and TemperaturesMES Conditions

2-11Page 16

Oct 01/09



0°10°20°

30°

40°

50°

60°

70°

80°

90°

100°

110°

120°

130°

140°

150°160°

170° 180° 190°200°

210°

220°

230°

240°

250°

260°

270°

280°

290°

300°

310°

320°

330°340°350°

DB (A)

75

80

85

90

95

100

105

110

DESCRIPTION OF TEST CONDITIONS

THE ARC OF CIRCLE ( RADIUS = 60 m (196.85 ft)), WITH MICROPHONES 1.2 m (3.94 ft) HIGH,IS CENTERED ON THE POSITION OF THE NOISE REFERENCE POINT.A.P.U.: OFF ; E.C.S.: PACKS OFF.

− TEMPERATURE: 32° C (89.6° F)− RELATIVE HUMIDITY: 31 %− ATMOSPHERIC PRESSURE (QFE): 996 hPa (144.45 PSI)− WIND SPEED: NEGLIGIBLE− NO RAIN

L_MF_021100_1_0300101_01_01

MAX THRUST POSSIBLEON BRAKES

4 ENGINES RUNNING

GROUND IDLE4 ENGINES RUNNING

Airport and Community Noise DataTRENT 900 Engines

2-11Page 17

Oct 01/09



0°10°20°

30°

40°

50°

60°

70°

80°

90°

100°

110°

120°

130°

140°

150°160°

170° 180° 190°200°

210°

220°

230°

240°

250°

260°

270°

280°

290°

300°

310°

320°

330°340°350°

DB (A)

75

80

85

90

95

100

105

110

MAX THRUST POSSIBLEON BRAKES

4 ENGINES RUNNING

GROUND IDLE4 ENGINES RUNNING

L_MF_021100_1_0150102_01_01

DESCRIPTION OF TEST CONDITIONS

THE ARC OF CIRCLE (RADIUS = 60 m (196.85 ft)), WITH MICROPHONES 1.2 m (3.94 ft) HIGH,IS CENTERED ON THE POSITION OF THE NOISE REFERENCE POINT.A.P.U.: OFF ; E.C.S.: PACKS OFF.

− TEMPERATURE: 12° C (53.6° F)− RELATIVE HUMIDITY: 90 %− ATHMOSPHERIC PRESSURE (QFE): 1015 hPa (147.21 PSI)− WIND SPEED: NEGLIGIBLE− NO RAIN

Airport and Community Noise DataGP 7200 Engines

2-11Page 18

Oct 01/09



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)

L_MF_021100_1_0160102_01_00

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

Danger Areas of the EnginesGround Idle Power - TRENT 900 Engines

2-11Page 19

Oct 01/09



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_MF_021100_1_0170102_01_01

Danger Areas of the EnginesGround Idle Power - GP7200 Engines

2-11Page 20

Oct 01/09



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_MF_021100_1_0180102_01_00

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

2-11Page 21

Oct 01/09




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_MF_021100_1_0190102_01_01

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

2-11Page 22

Oct 01/09



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_MF_021100_1_0200102_01_00

Danger Areas of the EnginesBreakaway Power - TRENT 900 Engines

2-11Page 23

Oct 01/09



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_MF_021100_1_0210102_01_02

Danger Areas of the EnginesBreakaway Power - GP 7200 Engines

2-11Page 24

Oct 01/09


2-12 Airplane Mooring


Airplane Mooring

1. General

This section provides information on airplane mooring.

2-12Page 1

Oct 01/09



A

FWD

SLING

TOWING FITTING

MOVABLE PIN

LOCKING SCREW

HOOK

HOOK PIN

MOORING POINT

A

L_MF_021200_1_0010101_01_00

Airplane Mooring

2-12Page 2

Oct 01/09


LINE MAINTENANCE AND HANGAR

3-1 Airplane Maintenance Jacking


Airplane Maintenance Jacking

1. Aircraft Jacking Points for Maintenance

A. General

(1) The A380 aircraft can be jacked :- at not more than the maximum permitted aircraft weight for jacking,- within the limits of the permissible wind speed when the aircraft is jacked outside a

closed environment.

B. Primary jacking Points

(1) The aircraft are 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 jack pad adapters at the wings (one at each wing).

C. Auxiliary stabilizing Point (Safety point)

(1) When the aircraft is on jacks, a safety stay is installed under the aft fuselage (Ref. Fig.Jacking point location) to prevent tail tipping caused by accidental displacement of theaircraft 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 intermediary part betweenthe aircraft safety point and the stay.

2. Jacks and Safety Stay

A. Jacks Specifications

The Maximum Eligible Static Load (Ref. Fig. Jacking Point Location) given in graph are themaximum loads applicable on jack fittings.

(1) In fully retracted position (jack stroke at minimum), the height of the jacks is such thatthey may be placed beneath the airplane under the most adverse conditions, namely, tiresdeflated and chock absorbers depressurized and, in addition, with a sufficient clearancebetween the aircraft jacking point and the jack upper end.

3-1Page 1

Oct 01/09


(2) The jacks stroke enables the aircraft to be jacked up so that the Fuselage Datum Line(FDL) may be positioned up to 7300 mm (23.95 ft) from the ground to allow all requiredmaintenance procedure and in particular, the Landing Gear shock absorbersremoval/installation.

B. Safety stay

(1) The stay stroke enables the aircraft tail to be supported up to the Fuselage Datum Line(FDL) positioned at 7300 mm (23.95 ft) from the ground.

3-1Page 2

Oct 01/09



JACKINGPOINT

JACKINGPOINT

SAFETYSTAY

Y

JACKINGPOINT

X

7.33 m(24.04 ft)

X =

0

L_MF_030100_1_0010102_01_02

A

B

B’

C

NOTE: SAFETY STAY IS NOT USE FOR JACKING

SAFETY STAY

WING JACKINGPOINT

C

B’

B

FORWARD FUSELAGEJACKING POINT A

7.28 23.91 0

12.22

−12.22

0

0

40.10

−40.10

0

MAXIMUMLOAD ELIGIBLE

m ft daN

YX

m ft

35.23

35.23

59.34

115.58

115.58

194.70

34 011

157 480

157 480

4 500

Jacking Points Location

3-1Page 3

Oct 01/09



LN

AIRCRAFT ON WHEELS WITH STANDARD TIRES, MAX.JACKWEIGHT 333700kg (735683lb)

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 6350 mm (250 in) FOR LANDINGGEARS EXTENSION/RETRACTION

2472 mm97.32 in

2259 mm88.94 in

2296 mm90.39 in

2474 mm97.4 in

2391mm94.13 in

3673 mm144.61 in

5112 mm201.26 in

4788 mm188.5 in

5117 mm201.46 in

4523 mm178.07 in

4803 mm189.09 in

6158 mm242.44 in

4707 mm185.31 in

4462 mm175.67 in

5044 mm198.59 in

4257 mm167.6 in

4291 mm168.94 in

5830 mm229.53 in

(M left)

AIRCRAFT ON JACKS, FUSELAGE DATUM LINEPARALLEL TO GROUND AT 7200 mm (283.46 in) FOR LANDINGGEARS REMOVAL/INSTALLATION

L M N

4523 mm178.07 in

7008 mm275.9 in

6680 mm262.99 in

FUSELAGE DATUM LINE

M

L_MF_030100_1_0020102_01_01

Jacking Dimensions

3-1Page 4

Oct 01/09



FR20 RIB16 1

B

2

3

4

C

FR101

5

A

BA

B

CRIB16

L_MF_030100_1_0030102_01_00

Jacks and Safety Stay Adapter

3-1Page 5

Oct 01/09




Landing Gear Jacking for Wheel Change

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.

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 Fig. 001.The reaction loads at the jacking positions for the A380-800 are shown in Figs. 004 to 009.

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

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 forward 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 :

(1) Replace the wheel assemblies on the aft axle.

(2) Replace the wheel assemblies on the forward axle.Important dimensions of the WLG when lifted are shown in Fig. 002.The reaction loads at the jacking position for the A380-800 are shown in Figs. 004 to 009.


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 forward 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 :

(1) Replace the wheel assemblies on the aft axle.

(2) Replace the wheel assemblies on the center axle.

3-2Page 1

Oct 01/09


(3) Replace the wheel assemblies on the forward axle.Important dimensions of the WLG when lifted are shown in FIG. 003.The reaction loads at the jacking position for the A380-800 are shown in Figs. 004 to 009.


3-2Page 2

Oct 01/09



DATA FOR 1270X455R22 TIRES

MRW = 562 000 kg (1 238 989 lb)MLW = 386 000 kg (850 984 lb)

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

2 DEFLATED TIRES +50%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 (5.34)

166 (6.54) 519 (20.43)

519 (20.43)

519 (20.43)


MLW−PAX

MLW−PAX

MLW−PAX

NOTE: DIMENSIONS IN MILIMETERS (INCHES IN BRACKETS)

44

20 DEFLATED TIRES+50%RIM DAMAGE


N/A

L_MF_030200_1_0010101_01_00

Nose Landing Gear Jacking Point HeightsA380-800 Models

3-2Page 3

Oct 01/09



NOTE: DIMENSIONS IN MILIMETERS (INCHES IN BRACKETS)MRW = 562 000 kg (1 238 989 lb)MLW = 386 000 kg (850 984 lb)

A A

B

CONFIGURATION WEIGHT CG% DIM. A

FWD

DIM. A

AFT

DIM. B DIM. C

ALL 4 TIRES SERVICEABLE

MRW 43 347 (13.7) 347 (13.7) 750 (25.9) 364 (14.3)

1 FWD TIRE DEFLATED

MRW 43 264 (10.4) 353 (13.9) 718 (28.3) 364 (14.3)

1 AFT TIRE DEFLATED

MRW 43 353 (13.9 ) 264 (10.4) 718 (28.3) 364 (14.3)

2 DEFLATED FWD TIRES +50% RIM DAMAGE

MLW

− PAX

44 93 (3.7) 406 (16) 686 (27) 364 (14.3)

2 DEFLATED AFT TIRES +50% RIM DAMAGE

MLW

− PAX

44 406 (16) 93 (3.7) 686 (27) 364 (14.3)

+50% RIM DAMAGE

MLW

− PAX

44 93 (3.7) 93 (3.7) 686 (27) 364 (14.3)

FWD TIRE CHANGE MAX. GROWN TIRE

MRW 43 513 (20.2) 331 (13) 795 (31.3) 364 (14.3)

AFT TIRE CHANGE MAX. GROWN TIRE

MRW 43 331 (13) 513 (20.2) 795 (31.3) 364 (14.3)

20 FLAT TIRES+50% RIM DAMAGE

N/A N/A 83 (3.3) 83 (3.3) 686 (27) 364 (14.3)


C

4 TIRES DEFLATED

L_MF_030200_1_0020101_01_00

Wing Landing Gear Jacking Point HeightsA380-800 Models

3-2Page 4

Oct 01/09



MLW = 386 000 kg (850 984 lb)

C

B

A A

NOTE: DIMENSIONS IN MILIMETERS (INCHES IN BRACKETS)MRW = 562 000 kg (1 238 989 lb)

CONFIGURATION WEIGHT CG%

MRW 43

MRW 43

DIM. A


N/A N/A

DIM. A DIM. B DIM. C DIM. CFWD AFT FWD AFT

ALL 6 TIRESSERVICABLE

347 (13.7) 312 (12.3) 930 (36.6) 460 (18.1) 432 (17)

1 FWD TIREUNSERVICEABLE 295 (11.6) 328 (12.9) 898 (35.4) 460 (18.1) 432 (17)

MRW 43 898 (35.4) 460 (18.1) 432 (17)

460 (18.1) 432 (17)

MRW 43 460 (18.1) 432 (17)

MRW 43 460 (18.1) 432 (17)

43 898 (35.4) 460 (18.1) 432 (17)

MLW−PAX

460 (18.1) 432 (17)

MLW−PAX

460 (18.1) 432 (17)

MLW−PAX

460 (18.1) 432 (17)

43 460 (18.1) 432 (17)

1 CENTER TIREUNSERVICEABLE

MRW 334 (13.1) 299 (11.8)

1 AFT TIREUNSERVICEABLE

363 (14.3) 260 (10.2)

2 FWD TIRESDEFLATED +50%RIM DAMAGE

44 74 (2.9) 505 (19.9) 866 (34.1)

2 CENTER TIRESDEFLATED

44 358 (14.1) 323 (12.7) 866 (34.1)MLW−PAX

2 AFT TIRESDEFLATED +50%RIM DAMAGE

44 540 (21.1) 40 (1.6) 866 (34.1)

6 TIRES DEFLATED+50% RIMDAMAGE

44 74 (2.9) 39 (1.5) 866 (34.1)

FWD TIRE CHANGEMAX. GROWN TIRE

496 (19.5) 264 (10.4) 975 (38.4)

CTR TIRE CHANGEPOSITIONMAX. GROWN TIRE

MRW 496 (19.5) 461 (18.2) 975 (38.4)

AFT TIRE CHANGEMAX. GROWN TIRE

299 (11.8) 461 (18.2) 975 (38.4)

20 DEFLATEDTIRES +50% RIMDAMAGE

102 (4) 67 (2.6) 866 (34.1) 460 (18.1) 432 (17)

L_MF_030200_1_0030101_01_00

Body Landing Gear Jacking Point HeightsA380-800 Models

3-2Page 5

Oct 01/09



L_MF_030200_1_0040101_01_01

10

15

20

25

30

35

40

45

50

55

60

260 300 340 380 420 460 500 540 580

LOA

D A

T J

AC

KIN

G P

OIN

T [

x 10

00 k

g ]

22

32

42

52

62

72

82

92

102

112

122

132

(x1000 kg)

LOA

D A

T J

AC

KIN

G P

OIN

T [

x 10

00 lb

]


120011001000900800700600

(x1000 lb)


Nose Landing Gear Jacking Point LoadsA380-800 Models

3-2Page 6

Oct 01/09



L_MF_030200_1_0050101_01_01

10

15

20

25

30

35

40

45

50

55

60

65

260 290 320 350 380 410 440 470 500 530 560 590 620


LOA

D A

T J

AC

KIN

G P

OIN

T [

x 10

00 k

g ]

22

32

42

52

62

72

82

92

102

112

122

132

142

1300120011001000900800700600

(x1000 kg)

(x1000 lb)

LOA

D A

T J

AC

KIN

G P

OIN

T [

x 10

00 lb

]

CG POSITION29 % mac33 % mac36 % mac40 % mac43 % mac

Nose Landing Gear Jacking Point LoadsA380-800F Models

3-2Page 7

Oct 01/09



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Wing Landing Gear Jacking Point LoadsA380-800 Models

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L_MF_030200_1_0070101_01_01

Wing Landing Gear Jacking Point LoadsA380-800F Models

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Oct 01/09



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Body Landing Gear Jacking Point LoadsA380-800 Models

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Oct 01/09



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Body Landing Gear Jacking Point LoadsA380-800F Models

3-2Page 11

Oct 01/09




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 1R and 1L 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 photogrametry.

3-3Page 1

Oct 01/09



FR35

FR36

FR88

FR89

RIB6

RIB6

16

11

1L

1R

L_MF_030300_1_0010102_01_00

Location of Leveling Points

3-3Page 2

Oct 01/09




De-icing and Washing

1. De-Icing and Washing on GroundThe mobile equipment for aircraft de-icing and washing must be capable of reaching heights up toapproximately 25 meters (82 ft). For use on the ramp, it must have a de-icing liquid storage tankwith means for heating the liquid to the required temperature. Inside the hangar, the same mobileunit or fixed equipment may be used. Impingement pressure of the de-icing or washing liquid is about5 psi (0.35 bar) except for wing root fillet and various other fairings where it will be 1.5 psi (0.10bar).At major airports, a substantial saving in manpower and aircraft time can be achieved if a de-icing/washing hangar, especially one with a mechanized and automated facility, is provided for use byall airlines.

2. Wetted Area for the Complete Aircraft

A380m2 ft2

Fuselage 1490 16038

Belly fairing 384 4133

Wing (3) 1454 15651

Vertical Stabilizer 232 2497Horizontal Stabilizer 346 3724Nacelles and Pylons 390 4198

TOTAL 4296 46241

3. Liquid- Anti/De-Icing fluid type I - AMS 1424 (Material 10-001)- Anti/De-icing fluid type II - AMS 1428 (Material 10-003)- Anti/De-Icing fluid type IV - AMS 1428C (Material 10-004)

3-4Page 1

Oct 01/09




Air Conditioning

1. Air conditioningThe air conditioning system controls the airflow in the cockpit, the two cabin decks and the lowerdeck cargo compartments. The air conditioning system keeps the air in the pressurized fuselagecompartments at the correct pressure, temperature and freshness.The bleed air system supplies compressed air to the air conditioning system from:- the main engine compressor,- the APU compressor,- three high pressure ground connectionsThe air conditioning system cools and conditions the hot compressed air. Then it sends the air to thefuselage compartments. From there, the hot air flows through ducts and goes overboard through avalve.Four low-pressure ground connections can also supply the conditioned air to the distribution system.In a double failure case during flight operations, two emergency ram air inlets open automatically andsupply the distribution system with air from outside.The conditioned air is supplied to the cabin and the cockpit. The cockpit and the cabin zones havean independent temperature control. The temperature of the cabin zones and the cockpit arenormally controlled to between 18˚C and 30˚C (65˚ and 86˚F). An automatic control keeps the airtemperature at the selected value in each cabin zone and in the cockpit.

2. PressurizationThe Cabin Pressure Control System (CPCS) controls the pressure in the fuselage during flight andground operations.The CPCS controls the rate of change of the cabin pressure and the cabin differential pressure.It gives the best possible comfort and safety for the passengers and the crew.The operation of the CPCS is fully automatic under all operating conditions.

3. Ventilation

A. Unpressurized Compartment Ventilation SystemThe function of the unpressurized compartments ventilation system is to supply air to theunpressurized compartments ventilation in the belly fairing.The unpressurized compartments have two main zones:- Zone A is in the forward belly fairing and includes the Air Generation Units (AGU) 1 and 2

and the hot air ducts.

3-5Page 1

Oct 01/09


- Zone B is under the wing center box, in the belly fairing. The unpressurized compartmentsventilation system supplies a correct quantity of ventilation air on each zone (A and B), toremove heat from the AGUs and fuel vapors. It also keeps, on the ground or in flight, amean temperature of 80˚C in the unpressurized compartment with an external temperatureof 55˚C. This temperature is compatible with the structure constraints in the unpressurizedcompartments. The unpressurized compartments ventilation-system operates without aircraftelectrical power.

B. Avionics Equipment Ventilation SystemThe avionics equipment ventilation system supplies cooling to the components with airflowthrough the racks in the compartment. The supplemental cooling system supplies cooled air tothe compartment. An extraction fan moves the hot air to the under floor area and lateroverboard through the outflow valve.

4. AGU Dimensions

Length 1645.9 mm (64.8 in.)

Width 1818.6 mm (71.6 in.)

Height 1535.3 mm (60.5 in.)

Weight 403.3 kg (889.0 lb)

3-5Page 2

Oct 01/09



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L_MF_030500_1_0010102_01_00

Air ConditioningGeneral Layout

3-5Page 3

Oct 01/09



RH FANINLET PLENUM

LH PLENUM HEADER

CONDENSER

LH ACM

LH TURBINEBYPASS VALVE

RH TURBINE BYPASS VALVE

RH ACM

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LH TEMPCONTROL VALVE

LH TEMPCONTROL VALVE

RH DUALHEAT EXCHANGER

AL_MF_030500_1_0020102_01_00

Air ConditioningAir Generation Unit (AGU)

3-5Page 4

Oct 01/09


3-6 Communications


Communications

1. GeneralThe communications system has these functions:- Speech communication inside and outside the aircraft by the crew members- Data transmission with the ground stations- Radio and audio management- Audio and video monitoring and intercommunication.

For the protection of the communications system, static dischargers are installed on the aircraft.The A380-800 basic aircraft is equipped with:

A. Speech Communication

(1) High Frequency (HF) systemThe HF system is used for all long-distance voice and data

(2) Very High Frequency (VHF) systemThe VHF system is used for short-range voice and data communications.

B. Interphone

(1) Cockpit-to-ground crew call systemThe cockpit to ground crew call system enables cockpit crew-to-ground mechanic calls orground mechanic-to-cockpit crew calls.

(2) Service interphoneThis system provides a means of telephone communication on the ground between theflight crew and the ground service personnel.

C. Radio and Audio Management

(1) Audio IntegratingThe audio integrating system integrates and manages all audio signals supplied by and sentto the radio communication and radio navigation systems. Also, it has SELCAL and flightinterphone functions.

(2) Radio Frequencies and Satellite Channels TuningThrough this function, the frequencies of all radio communication equipment are controlledby the Radio and Audio Management Panel (RMP). The RMP also controls thefrequencies of radio navigation equipment as a back-up solution.

D. Static DischargingStatic dischargers protect the communications system from interference caused by staticelectricity.

3-6Page 1

Oct 01/09


E. Audio and Video Monitoring and Intercommunication

(1) Cockpit Voice Recorder (CVR)The CVR records in-flight and on-ground conversations and communications in solid-statememories.

(2) External Video System (ETACS)The External and Taxiing Aid Camera System (ETACS) is an aid to the crew duringtaxiing of the aircraft.

3-6Page 2

Oct 01/09



SATCOM2−TOP

HF ANTENNA

HPA1−TOP TWLU

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LANDINGGEAR

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6RJ5RJ

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22RJ

24RJ

L_MF_030600_1_0010102_01_02

CommunicationsLocation of Antennas

3-6Page 3

Oct 01/09


3-7 Electrical Power


Electrical Power

1. General

The electrical system generates and distributes electrical power to all the aircraft systems throughthese networks.A 115VAC normal network with variable frequency. Power is supplied to this network from :- Four Variable Frequency Generators (VFG) or,- Two auxiliary generators (APU generators) with constant frequency or,- Four external power units (through four external-power receptacles).A 28VDC normal network with the No Break Power Transfer (NBPT) function. Power is supplied tothis network from :- Two Transformer Rectifier Units (TRU)- One Transformer Rectifier (TR) 2- Two batteries (1 and 2).A 115VAC and 28VDC emergency network which is segregated from the normal network.Power is supplied to the AC emergency network from :- The normal AC network (if available) or,- An electrical Ram Air Turbine (RAT) with variable frequency or,- Battery 1 and the essential battery through the static inverter. Power is supplied to the DC

emergency network from :- The AC emergency network through the essential TRU or,- Battery 1 and the essential battery (during extension of the RAT and after landing in emergency

electrical configuration).An APU network, supplied by busbar 200XP4. This network has a TR, a battery and the relatedcontactors and protection devices. The APU network is used to start the APU.

2. AC Generation (Ref. Fig. 001)

A. Variable Frequency Generator (VFG)Each of the four engines drives its related VFG through the accessory gearbox.The VFG is an oil-cooled generator with a nominal 115V, 150KVA, three-phase, 370-770 Hzoutput.Each VFG has two pushbutton switches on ICP 1225VM (overhead panel), one for mechanicaldisconnection of the VFG, the other for electrical connection and disconnection of the VFG.The Generator and Ground Power Control Unit (CCPCU) 1(2,3,4) control and monitor the VFG1(2,3,4).

3-7Page 1

Oct 01/09


B. APU GeneratorThe APU drives two APU generators at a constant frequency. The APU generator is an oil-cooled generator with a nominal output of 115V, 120KVA, three-phase, 400Hz. Each APUgenerator has a pushbutton switch on the overhead panel for electrical connection anddisconnection.

C. External powerThe external power supply is the AC power source used on the ground when the VFGs and theAPU generators are not available. Four external power receptacles are used to supply power tothe aircraft network.Each external power receptacle supplies 90KVA with a constant frequency of 400Hz.The GGPCU 1(2,3,4) controls and monitors the external power unit 1(2,3,4) that is connectedto the receptacles.

D. Electrical RATThe electrical RAT supplies electrical power if the main power source is unserviceable. It drivesan AC emergency generator at a variable frequency. The generator is an air-cooled generatorwith a nominal 115V, 70KVA, three-phase, 360-800 Hz output.The generator is mechanically connected to the RAT. A Generator Control Unit (GCU) controlsand monitors the RAT. The RAT extends automatically but it is possible to control the RATmanually by means of a pushbutton switch on the overhead panel.

E. Transfer circuitThe transfer circuit reconfigures the electrical network to keep the busbars supplied according tothe availability of the power sources. The primary main distribution reconfigures the network ifthere is connection and disconnection of the AC main power source.The transfer contactors close to obey the priority and segregation rules. If two VFGs of a sameside are not available (without external power supply or APU supply) :- The outer serviceable VFG supplies the busbar of the outer unserviceable VFG.- The inner serviceable generator supplies the busbar of the inner unserviceable VFG.

3. DC Generation (Ref. Fig. 001)

A. TRUsEach TRU has these functions :- It controls the charge of the batteries- It monitors the batteries to DC network.

B. TR 2TR 2 is used if TRU 2 is unserviceable. It has these functions :- It changes 115VAC into 28VDC.- It controls the charge of the batteries.- It monitors the batteries.

3-7Page 2

Oct 01/09


C. APU TRThe APU TR is supplied by the APU DC busbar and is used to start the APU with or withoutthe battery.The APU TR :- Controls the charge of the batteries.- Monitors the batteries and the DC network.

D. BatteriesThe primary functions of the batteries are the NBPT function and the supply of the DCnetwork in some conditions.

4. AC and DC Distribution (Ref. Fig. 002)The electrical distribution system :- Connects and disconnects the power source.- Reconfigures the electrical network.- Gives maximum availability of the busbar.- Gives electrical protection to prevent paralleling and protection faults.- Prevents short circuits.

The distribution system has three sub-systems segregated on two electrical sides.- The primary main distribution- The secondary main distribution- The emergency distribution.

A. Primary main distributionThe components for the primary main distribution are in the PEPDC. The PEPDC supplies115VAC variable-frequency and 28VDC to all the electrical users of the aircraft. It alsoconfigures the electrical network architecture.

B. Secondary main distributionThe secondary main distribution is installed in the SEPDCs and in the SPDRs. It supplies115VAC variable frequency and 28VDC electrical power. The secondary main distributionincludes the AC and DC secondary technical -- system and commercial-system busbars andrelated protection devices. The SEPDCs and the SPDBs use the SSPC technology for AC andDC rating. The secondary main distribution has these items :- Two SEPDCs which include all the circuit breakers (SSPCs) that supply all the AC and DC

low-power loads.- Eight SPDBs which include all the circuit breakers (SSPCs) that supply the cabin and cargo

electrical system.

C. Emergency distributionThe emergency distribution is installed in the emergency power center. The emergency powercenter is segregated from the PEPDC. In normal electrical configuration, the AC emergencybusbar is supplied by busbar 100XP1 or 200XP4 (see primary main distribution). The DCessential busbars are supplied by the essential TRU. If the essential TRU is unserviceable, TRU1 supplies busbar 400PP.

3-7Page 3

Oct 01/09


In emergency electrical configuration (power supplied from the RAT), the electrical RATgenerator supplies the emergency busbars 400XP and 491XP. Busbar 247XP (EHA busbar) issupplied if the hydraulic system is unserviceable (TEFO configuration). Essential TRU suppliesthe DC essential busbars. In emergency electrical configuration (power supplied from thebatteries), the batteries supply busbar 400PP and the static inverter supplies busbar 491XP.

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Oct 01/09



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L_MF_030700_1_0010102_01_01

Electrical PowerGeneral Schematic

3-7Page 5

Oct 01/09



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L_MF_030700_1_0020102_01_00

Electrical PowerAC and DC Distribution

3-7Page 6

Oct 01/09



VFG4

VFG3

SPDB2

SPDB4

SPDB6 APU

SPDB5SPDB1SEPDC1

SEPDC2

RAT

VFG2

VFG1

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EXTERNAL POWERRECEPTACLE

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EQUIPMENT LOCATION

SPDB8

EMER PWR CTR

L_MF_030700_1_0030102_01_00

Electrical PowerComponent Location

3-7Page 7

Oct 01/09


3-8 Flight Controls


Flight Controls

1. There are two types of flight controls :- the Primary controls- the Secondary controls.

A. Primary Controls

(1) The roll control is achieved on each wing by the inner and outer aileron complementedwith six spoilers.

(2) The yaw control is achieved by a rudder attached to the vertical stabilizer with a hinge.

(3) The pitch control is achieved by two elevators attached to the Trimmable HorizontalStabilizer (THS) (trim function) with hinges.

B. Secondary ControlsThe lift augmenting is achieved by the surfaces on each wing as follows :- two trailing edge flaps- seven leading edge slats- two ailerons which droop when the flaps are extended.

2. Operation

A. Roll ControlHydraulic servo controls, which receive electrical signals and are independently supplied, operatethe spoilers and ailerons.Two servo controls are on each aileron and one on each spoiler. Signals by the side stickcontrollers are analyzed by the electrical control computers which give the calculated controlsurface position.

B. Yaw ControlsThe rudder is operated by three independently supplied hydraulic servo-controls. The servo-controls receive signals through interconnected pedals by a single cable. The single cable runs upto a spring-loaded artificial feed unit. Yaw trim is signalled from a switch located on the centerpedestal and analyzed by the flight augmentation computers which control the rudder trimactuator.

C. Pitch ControlThe two elevators are operated by independent hydraulic servo controls. The servo controls areoperated hydraulically and controlled electrically with hydraulic pressure. Two servo controls areinstalled on each elevator.Pitch trim is provided by adjustment of the Trimmable Horizontal Stabilizer (THS). Control ofthe THS position can be achieved automatically in the normal (electrical) operating mode, viathe elevator and the Aileron computer, or mechanically by operation of the interconnectedhandwheels located on the center pedestal.

3-8Page 1

Oct 01/09


D. Lift AugmentationEach trailing edge flap moves by means of the carriages. The flaps are actuated by a powercontrol unit which has two hydraulic motors that drive the rotary actuator by means of atransmission shaft.Each leading edge slat moves by means of the tracks. The slats are actuated by a power controlunit which has two hydraulic motors. The two hydraulic motors drive the rotary actuator bymeans of a transmission shaft.

3-8Page 2

Oct 01/09



30

30

A

A A−−B B

Z= 0

(574.49 in)

4320 mm(170.08 in)

(25.73 in)

660.27 mm(25.99 in)

1691.1 mm(66.58 in)

1684.27 mm(66.31 in)

12056.5 mm(474.67 in)

4700 mm(104.61 in)

1314.1 mm(51.74 in) 3366.71 mm

(132.55 in)

30

30

32.1

24.75

ARUDDER HINGELINE 67%

653.57 mm

14592 mm

B

B

L_MF_030800_1_0010101_01_00

Control Surface TravelRudder (Sheet 1)

3-8Page 3

Oct 01/09



30

30

30

DIM mm in

DIMENSION CODESAND CONVERSIONS

XC

XD

XE

806.97

1162.86

1518.76

31.77

45.78

59.79

Z:

Z:

Z:

−−

−

C

D

E E

C

E E

D

17000 mm(669.29 in)

12000 mm(472.44 in)

7000 mm(275.59 in)

XC

XE

XD

Z= 0

DC

C

D

L_MF_030800_1_0020101_01_00

Control Surface TravelRudder (Sheet 2)

3-8Page 4

Oct 01/09



6

19.92 25.62

ELEVATORHINGE AXIS 70%

1527.19 mm(60.13 in)

A

A

B

B

C

C

L_MF_030800_1_0030101_01_00

Control Surface TravelTrimmable Horizontal Stabilizer and Elevator (Sheet 1)

3-8Page 5

Oct 01/09



ELEVATOR HINGE AXIS

THS CHORD PLANE

THS REAR SPAR

THS CHORD PLANE

THS HINGE AXIS

ELEVATOR HINGE AXIS

THS HINGE AXIS

THS CHORD PLANE

10

2

30

10

20

20

2

10

1425.53 mm(56.12 in)

1800.70 mm(70.89 in)

375.17 mm(14.75 in)

2832.09 mm(111.50 in)

1786.84 mm(70.35 in)

191.33 mm(7.53 in) 1045.25 mm

(41.15 in)

1906.44 mm(75.06 in)

1338.82 mm(52.71 in)

358.57 mm(14.12 in)

750.78 mm(29.56 in)

A A−

−B B

−C C

THS HINGE AXIS

580.39 mm(22.85 in)

2657.22mm104.61(in)

30

2

ELEVATORFRONT SPAR

L_MF_030800_1_0040101_01_00

Control Surface TravelTrimmable Horizontal Stabilizer and Elevator (Sheet 2)

3-8Page 6

Oct 01/09


3-9 Hydraulic Power


Hydraulic Power

1. General

The hydraulic power system supplies the applicable hydraulic flow and pressure to the consumers.It supplies hydraulic fluid to the consumers in normal operation and for ground maintenance whenthe engines are not in operation. The indicating system monitors the system continuously. It giveswarning and cautions, and shows messages as applicable.Two hydraulic power systems operate independently :- The Green system- The Yellow system.

NOTE : There is no Blue system.The primary flight controls of the aircraft are supplied through :- The hydraulic system that operates the servo-controls,- The electrical system that supplies the Electro-Hydrostatic Actuators (EHA) and the Electrical

Back-up Hydraulic Actuators (EBHA).

2. GenerationIn normal operation, the engine hydraulic pumps get the hydraulic fluid from the applicable reservoirby suction. Then, the hydraulic pumps supply the fluid to the consumers at a nominal pressure of 345bar (5000 psi). The consumers receive the fluid flow and pressure that is necessary for theiroperation.The fluid is depressurized through the consumers and goes back to the applicable reservoir at apressure of 70 bar (1015 psi). The electrical motor pumps supply the hydraulic power for groundmaintenance operations only.The main consumers are :- The flight control system- The landing gear system- The cargo door system- The retraction system of the Ram Air Turbine (RAT)

3. Distribution

A. Green Main Hydraulic PowerThe Green main hydraulic system is one of the two systems that supply the aircraft withhydraulic power.The Green system is mechanically and hydraulically isolated from the Yellow system. In normaloperation, four engine hydraulic pumps pressurize the High-Pressure (HP) system at a nominalpressure of 345 bar (5004 psi).For the ground maintenance, it is also possible to pressurize the system with a HP hydraulicground-cart.

3-9Page 1

Oct 01/09


The Green hydraulic system supplies :

(1) The flight control system- The primary and secondary flight controls with one slat and one flap motor- The flap wing-tip brakes (WTB)- An actuator of the Trimmable Horizontal Stabilizer (THS).The primary flight controls of the aircraft are supplied through :- The hydraulic system that operates the servo-controls.- The electrical system that supplies the Electro-Hydrostatic Actuators (EHA) and the

Electrical Back-up Hydraulic Actuators (EBHA).

(2) The landing gear system and specially :- The nose landing-gear system (extension/retraction)- The wing landing-gear system (extension/retraction)- The nose-wheel steering system- The normal braking system

(3) The retraction system of the Ram Air Turbine (RAT)

B. Yellow Main Hydraulic PowerThe Yellow main hydraulic system is one of the two systems that supply the aircraft withhydraulic power.The Yellow system is mechanically and hydraulically isolated from the Green system. In normaloperation, four engine hydraulic pumps pressurize the High-Pressure (HP) system at a nominalpressure of 345 bar (5004 psi).For the ground maintenance, it is also possible to pressurize the system with a HP hydraulicground-cart. The Yellow hydraulic system supplies :

(1) Flight control system specially :- Primary and secondary flight controls (one flap motor)- Flap Wing-tip brakes (WTB)- An actuator of the Trimmable Horizontal Stabilizer (THS).The primary flight controls of the aircraft are supplied through :- The hydraulic system that operates the servo-controls- The electrical system that supplies the Electro-Hydrostatic Actuators (EHA) and the

Electrical Back-up Hydraulic Actuators (EBHA).

(2) Landing gear system and specially :- Body landing-gear system (extension/retraction)- Body wheel-steering system (extension/retraction)- Normal braking system

3-9Page 2

Oct 01/09


4. Particulars

A. Engine Driven Pump :- Eight Engine Driven Pumps to provide main hydaulic power. Two EDP are fixed to the

accessory gearbox on the bottom of each gearbox. Each EDP supplies fluid to the system ata nominal pressure of 345 bars (5004 psi) with 0 flow, and a flow of 160 l/mn at a pressureof 330 bars.

- The nominal EDP speed for RR engine at take-off is 3775 rpm (max = 3841 rpm). Duringthe flight, descent, approach, the minimum speed can reach 2204 rpm.

- The Maximum EDP speed for EA engine at take-off is 4070 rpm. During the flight, descent,approach, the minimum speed can reach 2205 rpm.

- A clutch which is integrated into the EDP may disconnect in flight the EDP from theengine. This function is controlled by the crew, or may be used on ground by maintenancecrew for dispatch purpose (MMEL).

B. Electric Motor Pump :- Four Electric Motor Pumps (EMP) to supply auxiliary hydraulic power only on ground. The

electrical motor is a three phase AC induction motor (dual winding stator) using the A/C115 volts, 400 Hz electrical power supply. The electrical motor turns at 7580 rpm. Ahydraulic pump is fixed to the electrical motor through a shaft. This hydraulic pump is avariable displacement pump with 9 pistons and supplies fluid to the system at a nominalpressure of 345 bars (5004 psi) with 0 flow, a flow of 22.5 l/mn at 330 bars, and a flow of37.5 l/mn at 200 bars. Two EMPs are dedicated to each system and are located within eachinner pylon.

3-9Page 3

Oct 01/09



PMV

S

M

F

S

HP

M

P

Pr

H

ELECTRIC PUMP

ENGINE PUMP

RAM AIR TURBINE (RAT)

HAND PUMP

ELECTRICALLY OPERATED

GROUND CONNECTOR

SELF SEALING COUPLING

PRESSURE RELIEF VALVE

CHECK VALVE

FILTER

PRESSURE TRANSMITTER

PRESSURE SWITCH

SOLENOID VALVE

HYDRAULIC ACTUATOR

HYDRAULIC MOTOR

PRIORITY VALVE

TEMPERATURE SENSOR

PRESSURE ACCUMULATOR

SHUT OFF VALVE

HYDRAULIC SAFETY VALVE(FUSE)

PRESSURE MAINTAININGVALVE

HYDRAULIC OPERATEDSELECTOR VALVE

HIGHT PRESSUREREMANIFOLD

L_MF_030900_1_0010102_01_00

Hydraulic Power SystemSymbols

3-9Page 4

Oct 01/09



P P

P P

P P

P

SS

SS

SS

SS

CA

RG

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− P

ITC

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1

ELE

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LH

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TB

D &

LH

INB

D

RU

DD

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S U

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& L

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SP

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S 2

, 4, 6

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LH &

RH

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AIL

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S L

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115

VA

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L_MF_030900_1_0020102_01_00

Main Hydraulic Power SystemArchitecture

3-9Page 5

Oct 01/09



SS

SS

M

RE

LIE

FV

ALV

E

HP

FIL

TE

RH

PF

ILT

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GIN

EP

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P 1

.1E

NG

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PU

MP

1.2

GR

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NR

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VO

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N L

P M

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LD(1

300

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600

JG)

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EP

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P 2

.1E

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GR

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(17

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G)

FLT

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LLH

WIN

G

−R

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S−

ELE

VA

TO

RS

−F

LAP

S

−W

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S L

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RA

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LT/C

TL

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WIN

G−

BP

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)

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Pr

L_MF_030900_1_0030102_01_00

Green Hydraulic SystemGeneral

3-9Page 6

Oct 01/09



SS

SS

M

RE

LIE

FV

ALV

E

YE

LLO

W H

PM

AN

IFO

LD F

ILT

ER

(17

00 J

Y)

HP

FILT

ER

HP

FILT

ER

GN

D C

NC

TR

DE

LIV

ER

Y

EN

GIN

EP

UM

P 3

.1E

NG

INE

PU

MP

3.2

FS

OV

HY

DFI

LTE

RH

YD

FILT

ER

YE

LLO

W C

DM

AN

IFO

LD(1

600

JY)

AIR

/HY

DC

OO

LER

AIR

/HY

D H

XH

YD

FA

N

TE

MP

ER

AT

UR

E T

RA

NS

MIT

TE

R

TO

FE

ED

TA

NK

FR

OM

FE

ED

TA

NK

FU

EL/

HY

D H

X

FU

EL

SH

UT

OF

VA

LVE

FR

OM

US

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S

TE

MP

ER

AT

UR

ET

RA

NS

MIT

TE

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LOW

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LT

RA

NS

MIT

TE

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WR

ES

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VO

IRQ

UA

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TR

AN

SM

ITT

ER

FLT

/CT

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WIN

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BO

DY

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SY

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PR

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TR

AN

SM

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AC

CU

MU

LAT

OR

AIR

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D H

XH

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NF

LT/C

TL

RH

WIN

G SA

MP

LIN

GV

ALV

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BR

AK

ES

SY

STE

M

−FLA

PS

−RU

DD

ER

−ELE

VA

TOR

S−T

HS

YE

LLO

W L

P M

AN

IFO

LD(1

300

JY)

YE

LLO

W H

PM

AN

IFO

LD F

ILT

ER

(14

00 J

Y)

RE

LIE

FV

ALV

E

HP

FILT

ER

HP

FILT

ER

EN

GIN

EP

UM

P 4

.1E

NG

INE

PU

MP

4.2

FS

OV

HY

DFI

LTE

RH

YD

FILT

ER

AIR

/HY

D H

XH

YD

FA

NA

IR/H

YD

CO

OLE

R

MM

Pr

L_MF_030900_1_0040102_01_00

Yellow Hydraulic SystemGeneral

3-9Page 7

Oct 01/09



SP

EE

D B

RA

KE

S, G

RO

UN

D S

PO

ILE

RS

RO

LL S

UR

FA

CE

S

SP

EE

D B

RA

KE

S, G

RO

UN

D S

PO

ILE

RS

RO

LL S

UR

FA

CE

S

O/B

ME

D

AIL

ER

ON

S8

76

54

32

1

SP

OIL

ER

S

SLA

TS

FLA

PS

12

34

56

78

SP

OIL

ER

S

ME

DO

/B

AIL

ER

ON

S

TH

S A

TH

S

O/B

I/BI/B

O/B

ELE

VA

TO

RS

ELE

VA

TO

RS

UP

PE

RR

UD

DE

R

LOW

ER

RU

DD

ER

VE

RT

ICA

LS

TA

BIL

IZE

R

GY

YG

GY

GY

GY

GY

G

GY

GY

GG

YY

GG

GG

YY

YY

GG

YY

Y G YG

CO

NV

EN

TIO

NA

L H

YD

RA

ULI

C S

ER

VO

CO

NT

RO

L

G Y

GR

EE

N H

YD

RA

ULI

C S

YS

TE

M

YE

LLO

W H

YD

RA

ULI

C S

YS

TE

M

I/BI/B

L_MF_030900_1_0050102_01_00

Hydraulic PowerDistribution

3-9Page 8

Oct 01/09


3-10 Landing Gear


Landing Gear

1. The aircraft has:- two Wing Landing Gears (WLG) and related doors- two Body Landing Gears (BLG) and related doors- a Nose Landing Gear (NLG) and related doors.The Landing Gear (L/G) System includes:- a number of control devices in the cockpit- a number of computers in the avionics compartment- a number of L/Gs and their related doors- an extension and retraction system for the gears and doors- a system of brakes and related systems- a tire pressure indicating system- an oleo pressure monitoring system- a steering system.The control devices in the cockpit let the flight crew make the necessary inputs to the computers.These inputs tell the computers how to control the L/G functions that follow :- extension and retraction- braking- steering.The landing gears support the aircraft on the ground and include oleo-pneumatic shock absorbersthat absorb taxi, take-off and landing loads. During flight the L/Gs are retracted into bays.Mechanically and hydraulically operated doors close to make the aerodynamic contours of thefuselage when the L/G retracts. The hydraulically operated doors also close after the L/G is extended.The extension and retraction system extends and retracts the L/G. A normal extension and retractionsystem is usually used for this function. If the normal extension and retraction system is not available,an emergency (free fall) extension system lets each L/G extend.

2. Nose Gear and Doors (Fig. 001 and 002)The nose landing gear (NLG) includes a single-stage direct acting oleo-pneumatic shock absorber andretracts forward into a bay in the fuselage. A two-piece drag-stay assembly with a lock-stay,mechanically locks the leg in the extended position. The leg includes a hydraulically operated steeringmechanism.Four doors close the NLG bay. These are:- two hydraulically operated forward doors- two mechanically operated rear doors.An electrically operated ground door opening mechanism (for maintenance personnel) lets the forwarddoors be opened for access to the NLG bay when the aircraft is on the ground.

3. Wing Gear and Doors (Fig. 003 and 004)Each wing landing gear has a leg assembly and a four-wheel bogie beam. The WLG leg includes abogie trim actuator (BTA) and an oleo-pneumatic shock absorber.

3-10Page 1

Oct 01/09


The shock absorber is a single piece main cylinder with a sliding piston (slider) inside. Torque linksare attached on the rear of the leg between the shock absorber cylinder and the slider. The lower endof the slider is in the shape of a fork to which the bogie beam is attached with a pivot-pin.The BTA is mounted between the forward side of the slider and the bogie beam. The BTA keeps thebogie beam in the correct position in relation to the slider when the weight is off the landing gearduring:- take-off- retraction- and landing.A two-piece side-stay assembly holds the WLG in the extended position. A lock-stay keeps the side-stay assembly stable in the locked down position.Four doors close each WLG bay. These are:- a hydraulically-operated main door- two mechanically-operated hinged doors- a fixed fairing door attached to the WLG leg.

4. Body Landing Gear and Doors (Fig. 005 and 006)The two body landing gears have a six-wheel bogie beam and a leg assembly that includes an oleo-pneumatic shock absorber. The landing gear retracts aft into a bay in the fuselage. A two-piece drag-stay assembly mechanically locks the leg in the extended position. A bogie-trim-actuator (BTA) keepsthe bogie beam in the correct position in relation to the slider when the weight is off the landing gearduring:- take-off- retraction- and landing.The aft axle of the bogie beam can be steered.Four doors close the BLG bay. These are:- three hydraulically-operated doors- a driven fairing door attached to the inner door.An electrically operated ground door opening mechanism open the door for maintenance access to theBLG bay when the aircraft is on the ground.

5. Landing Gear Extension and Retraction SystemsTwo independent systems can be used to extend the landing gear.The Normal system is hydraulically operated and computer controlled. The hydraulic piping andelectrical harness runs are contained in a combination of rigid and flexible hoses/conduits. Theconduit routing gives protection from damage that runway debris and birdstrikes can cause. Theconduit routing also gives the maximum separation of the two systems.The Emergency Extension System (Free Fall) This system will extend the wing, body and nose gears.The system includes switches and electric actuators. When selected, the actuators operate to openthe gear and door up-locks and hydraulic valves. This lets gravity extend the gears.The L/G control lever mechanism has a baulk device. This device is a solenoid-controlled valve thatprevents selection to the UP position until:- the NLG, WLG and BLG shock absorbers are fully extended

3-10Page 2

Oct 01/09


- the nose wheel steering is centered.

6. SteeringThe Steering System is a computer controlled electro-hydraulic system used to change the directionof the aircraft when it moves on the ground with engine power. The system uses nose wheel steering(NWS) and body wheel steering (BWS).Pressure for the hydraulic components in the system is supplied from the:- Green Hydraulic Power system for the NWS- Yellow Hydraulic System for the BWS.The hydraulic components operate a steering mechanism which changes the direction of the NLGwheels.The core processing input/output module (CPIOM) is the computer that controls and monitors theoperation of the system. Two hand-wheel transmitters in the cockpit supply the primary steeringinputs to the CPIOM. The rudder pedals and the autopilot supply secondary steering inputs to theCPIOM through the Flight Control Primary Computers (FCPC)The system operation can be:- cancelled to let the nose wheels castor during aircraft movement on the ground- isolated from the rudder pedal inputs during the pre-flight check.

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

8. Built In Test Equipment (BITE)The BITE has these functions, it:- continuously monitors its system 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 be done during maintenance procedures.The BITE for the following systems is described in these chapters:- the Brakes and Steering,- the TPIS,- the Landing Gear.

3-10Page 3

Oct 01/09



TOWINGADAPTER

NWSACTUATOR

NWSACTUATOR

LOCK STAY

DOORACTUATOR

FORWARDDOOR RETRACTION

ACTUATOR

DRAG STAYASSEMBLY

DOWNLOCKACTUATOR

REARDOOR

STEERINGMECHANISM

L_MF_031000_1_0010101_01_00

Landing GearNose Gear and Doors

3-10Page 4

Oct 01/09



JACKINGPOINT

GROUNDINGPOINT

OIL DRAINVALVE

MAINTENANCE SERVICEPANEL

NITROGEN AND OILCHARGING VALVE

SEAL CHANGEOVERVALVE (COV)

STEERINGDISCONNECT

PANEL

TIRE INFLATIONADAPTER

L_MF_031000_1_0020101_01_00

Landing GearNose Gear Servicing Points

3-10Page 5

Oct 01/09



MAIN DOOR(HYDRAULICALLY

OPERATED)

AUXILIARY DOOR

DOOR ACTUATOR

HINGED DOORFAIRING DOOR

L_MF_031000_1_0030101_01_00

Landing GearWing Gear and Doors

3-10Page 6

Oct 01/09



CHECK/FILLVALVE (OIL)


GROUND POINT

CHARGE VALVE(NITROGEN)

A

B

C

C

B

A

TIRE INFLATION ADAPTER(TYPICAL)

L_MF_031000_1_0040101_01_00

Landing GearWing Gear Servicing Points

3-10Page 7

Oct 01/09



INNER DOOR

AUXILIARY DOOR

INNER DOOR OUTER DOOR

INNER DOORACTUATOR

BLG LEGASSEMBLY

RETRACTION ACTUATOR CENTER DOORACTUATOR

DRAG BRACE ASSEMBLY

OUTER DOOR ACTUATOR

CENTER DOOR

A

A

L_MF_031000_1_0050101_01_00

Landing GearBody Gear and Doors

3-10Page 8

Oct 01/09



CHARGING VALVE(NITROGEN)

DRAINVALVE


GROUNDINGPOINTS

(RIGHT ONE SHOWN LEFT ONE SIMILAR)

C

A

B

C

TIRE INFLATION ADAPTOR(TYPICAL)

A

B

L_MF_031000_1_0060101_01_00

Landing GearBody Gear Servicing Points

3-10Page 9

Oct 01/09



MAXIMUM RAMP WEIGHT

WING GEAR TIRE SIZE

WING GEAR TIRE PRESSURE

BODY GEAR TIRE SIZE

BODY GEAR TIRE PRESSURE

562 000 kg (1 239 000 lb)

NOSE GEAR TIRE SIZE

NOSE GEAR TIRE PRESSURE

1270 x 455R22 32PR

14.1 bar (205 psi)

15 bar (218 psi)

1400 x 530R23 40PR

1400 x 530R23 40PR

15 bar (218 psi)

1 050 mm(41.3 in)

1 550 mm(61.0 in)

1 530 mm(60.2 in)

NOSE LANDINGGEAR

BODY LANDINGGEAR

1 350 mm(53.1 in)

1 700 mm

(66.9 in)

(60.2 in)1 530 mm

12 456 mm(40.87 ft)

28 606 mm (93.85 ft)

31 882 mm (104.6 ft)

5 264 mm(17.27 ft)

WING LANDINGGEAR

1 700 mm(66.9 in)

1 700 mm(66.9 in)

14 336 mm(47.03 ft)

7 344 mm(24.1 ft)

L_MF_031000_1_0070101_01_00

Landing GearLanding Gear Footprint - A380-800 Models

3-10Page 10

Oct 01/09



1 050 mm(41.3 in)

1 550 mm(61.0 in)

1 530 mm(60.2 in)

NOSE LANDINGGEAR

BODY LANDINGGEAR

1 350 mm(53.1 in)

1 800 mm

(70.9 in)

(60.2 in)1 530 mm

12 456 mm(40.87 ft)

28 606 mm (93.85 ft)

31 882 mm (104.6 ft)

5 264 mm(17.27 ft)

WING LANDINGGEAR

MAXIMUM RAMP WEIGHT

WING GEAR TIRE SIZE

WING GEAR TIRE PRESSURE

BODY GEAR TIRE SIZE

BODY GEAR TIRE PRESSURE

14.7 bar (213 psi)

15 bar (218 psi)

15 bar (218 psi)

592 000 kg (1 305 125 lb)

NOSE GEAR TIRE SIZE

NOSE GEAR TIRE PRESSURE

50 x 20R22 34PR

1400 x 530R23 42PR

1400 x 530R23 42PR

1 700 mm(66.9 in)

1 700 mm(66.9 in)

14 336 mm(47.03 ft)

7 344 mm(24.1 ft)

L_MF_031000_1_0080101_01_00

Landing GearLanding Gear Footprint - A380-800F Models

3-10Page 11

Oct 01/09




Exterior Lighting

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

3-11Page 1

Oct 01/09



BEACON LIGHT

BEACON LIGHTS

OBSTRUCTION LIGHT

WING STROBE LIGHT

WING TIP NAVIGATION LIGHT

OBSTRUCTION LIGHT

WING STROBE LIGHT

WING TIP NAVIGATION LIGHT

REAR STROBE LIGHT

REAR NAVIGATION LIGHT

TAXI CAMERA LIGHTS

TAXI CAMERA LIGHTS

A

LOGO LIGHTS

WING / ENGINESCAN LIGHTS (LH/RH)

L_MF_031100_1_0010101_01_00

Exterior LightingExterior Lighting Available in Flight (Sheet 1)

3-11Page 2

Oct 01/09



TAXI LIGHTS (WING LEADING EDGE)

TAKE OFF LIGHTS

RUNWAY TURN OFF LIGHTS(NOSE LANDING GEAR)

TAKE OFF LANDING LIGHTS

(SYMMETRICAL ON RH WING)

(SYMMETRICAL ON RH WING)

L_MF_031100_1_0020101_01_00

Exterior LightingExterior Lighting Available in Flight (Sheet 2)

3-11Page 3

Oct 01/09



FORWARD LANDINGWHEEL WELL LIGHT

FORWARD CARGO COMPARTMENTLOADING AREA LIGHT

RIGHT AND LEFTLANDING WHEEL

WELL LIGHTS

AFT CARGO COMPARTMENTLOADING AREA LIGHT

L_MF_031100_1_0030101_01_00

Exterior LightingExterior Lighting for Ground Use - A380-800 Models

3-11Page 4

Oct 01/09



FORWARD LANDINGWHEEL WELL LIGHT

UPPER DECK CARGO COMPARTMENTLOADING AREA LIGHT

MAIN DECK CARGO COMPARTMENTLOADING AREA LIGHT

AFT CARGO COMPARTMENTLOADING AREA LIGHT

FORWARD LANDING WHEELWELL LIGHT

FORWARD CARGO COMPARTMENTLOADING AREA LIGHT

RIGHT LANDING WHEELWELL LIGHT

LEFT LANDING WHEELWELL LIGHT

L_MF_031100_1_0040101_01_00

Exterior LightingExterior Lighting for Ground Use - A380-800F Models

3-11Page 5

Oct 01/09


3-12 Navigation


Navigation

1. Air Data/Inertial Reference System (ADIRS)

A. A triplicated ADIRS shall be installed to provide main air data, inertial reference informationGPS position and GPIRS position and integrity, to cockpit instruments and other systems. Thesystem shall consist of three sets of air data probes and three Air. Data and Inertial ReferenceUnits (ADIRU), which combine air data and inertial reference systems.Each air data probe set shall consist of a pair of static probes, a sideslip probe and a multifunction probe which groups pitot, total temperature and angle of attack sensors.All probes shall be de-iced.

B. Standby navigation systemThe following standby indications shall be displayed on two Integrated.Standby Instrument Systems (ISIS) :- Altimeter scales in feet or if selected in feet and meters- Baro setting in hPa or in Hg- Airspeed- Attitude- Landing System deviations upon crew selection.

A standby magnetic compass shall be installed in a position visible to both pilots.

2. Landing and Taxiing aids

A. Two Multi-Mode Receivers (MMR)The primary function of the MMR is to process signals received from the Localizer, the GLIDEand the Global Positioning System antennas. The MMR includes two main functions :- ILS function

The ILS provides the crew and airborne system users with the aircraft position during thelanding phase with respect to a predetermined descent path.

- GPS functionThe GPS is a radio aid to worldwide navigation, which provides the crew and the airbornesystem user (FMGEC) with a readout of accurate navigation information.

- FLS functionThe FLS function enables the pilot to fly the current published non precision approaches(RNAV, VOR, VOR/DME, NDB, NDB/DME, GPS) in a way similar to precisionapproaches.

3. Independent Position Determining

A. Aircraft Environment Surveillance System (AESS)Three distinct systems of the AESS :

3-12Page 1

Oct 01/09


- Two weather radar system. This system enables detection and localization of theatmospheric disturbances in the area defined by the antenna scanning and displays them onthe Navigation-Display (ND) with different colors according to the level of disturbance.

- One Traffic Collision Avoidance System (TCAS). This system enables detection and displayof aircraft in the immediate vicinity and gives corrective vertical deviation in case of collisionthreat.

- GPWS system One Enhanced Ground Proximity Warning System (Enhanced GPWS). Thissystem provides the flight crew with visual and aural alerts when potentially hazardousconditions are met with the terrain.

B. Two radio altimetersThis system provides, below 2500 feet, the crew and the airborne system users with the radioheight data, which is the main landing gear wheels height above the ground. Radio altimeterinformation is displayed on the PFDs.

4. Dependent Position Determining

A. Two Distance Measuring Equipment (DME) systemsThis system provides the crew and the airborne user systems with a digital readout of the slantrange distance of the aircraft from a selected ground station with audio and possible digitalidentification of the selected ground station.

B. Two Air Traffic Control (ATC) systemsThis system gives aircraft identification to the ground and other aircraft and enables effectiveground surveillance of the air traffic.

C. One Automatic Direction Finder (ADF) systemThis system provides an indication of the relative bearing of the aircraft to a selected groundstation with aural identification of the ground station and decoding of the Morse identification.

D. Two VOR/MARKER systemsThis system comprises two independent systems :

(1) VOR system for the radio navigation.This system provides the crew with aircraft position with respect to the ground station andaircraft angular deviation from the selected course.

(2) MARKER (MKR) system for the landing approach phase.This system determines the distance between the aircraft and the runway and providesaural and visual indications of the passage of the aircraft over the marker transmitterlocated on the runway.

3-12Page 2

Oct 01/09



VO

R A

NT

EN

NA

AD

F 1

AD

F 2

TC

AS

TO

P 2

TC

AS

TO

P 1

GP

S2

GPS

1

WE

AT

HE

RR

AD

AR

GLI

DE

CA

PTU

RE G

LID

ET

RA

CK

TC

AS

BO

TT

OM

2 DM

E 1

TC

AS

BO

TT

OM

1

DM

E 2MA

RK

ER

L_MF_031200_1_0010102_01_01

NavigationLocation of Antennas

3-12Page 3

Oct 01/09




Auxiliary Power Unit

1. DescriptionThe Auxiliary Power Unit (APU) PW980 is a twin-spool gas turbine engine used to provide auxiliaryelectrical and pneumatic power to the aircraft. The APU supplies bleed air power to the aircraft forthe Environmental Control System (ECS) and for Main Engine Starting (MES), and it also supplieselectrical power for the Electrical System through two A/C generators. The APU is a self-containedunit which makes the aircraft independent of external pneumatic or electrical power supply, mainlyfor on ground use. Anyway, during the take-off the APU supplies bleed air to the ECS (thus avoidinga reduction in engine thrust) and in flight it backs up both electrical and air conditioning systems.The APU obtains power for self-starting from the aircraft batteries, or in combination with theexternal power, ground service, or normal aircraft supply. lThe APU system has four different subsystems:- the APU engine system,- the APU fuel system,- the APU oil system,- the APU air system.The APU Engine architecture splits in five sections:- the load gearbox section,- the load compressor section,- the accessory gearbox section,- the engine section,- the exhaust section.

2. Installation- 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.

3-13Page 1

Oct 01/09


3. APU PW980The APU PW980 is a double-shaft gas generator. Air from outside the aircraft enters through the airintake to the APU inlet, where it is delivered to both the engine and load compressor. The enginecompressor (High Pressure Compressor) compresses the air and delivers it to the reverse-flowcombustor chamber where fuel is added and burned. The high pressure/high temperature gas expandsthrough the engine turbine (High Pressure Turbine) providing the energy to drive the enginecompressor and the Accessory Gearbox (AGB). The gas further expands through the power turbine,which provides the energy to drive the load compressor and the electrical generators through theLoad Gearbox (LGB). The low energy gas expands through the exhaust diffuser from where it isdelivered to the aircraft mounted exhaust muffler. The power spool and the gas generator spoolrotate about a common axis.

4. Control CircuitThe Elecronic Control Box (ECB) initiates and automatically executes an APU start sequence uponreceipt of a start command from the aircraft flight deck. The ECB continually monitors APUoperation in order to maintain optimal performance. It also provides automatic fault shutdowns.

5. 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.

3-13Page 2

Oct 01/09



L_MF_031300_0_AAM0_01_00

THE DISTANCE FROM FR94, FR98, FR100 BOTTOMCENTERLINE TO FUSELAGE DATUM (FD) AS FOLLOWSFR112 TO FD= 974.9 mm (38.38 in)FR117 TO FD= 1772.4 mm (69.78 in)FR120 TO FD= 2239.8 mm (88.18 in)

NOTE:

A

STA73713 FR117/

STA72922 FR112/

STA72310 FR110/

315BL

315AL315AR

313AB

317AB

313AZ

A

L_MF_031300_1_0010101_01_00

Auxiliary Power UnitAPU Access Doors

3-13Page 3

Oct 01/09



EXHAUSTMUFFLER

FIREWALL

FIRE EXTINGUISHERBOTTLE

FIREWALL

AIR INTAKEDUCT ASSEMBLY

COOLING AIR DUCT

BLEEDLINE

Z317

Z313Z315

FR112

FR110

FR117

L_MF_031300_1_0020101_01_00

Auxiliary Power UnitGeneral Layout

3-13Page 4

Oct 01/09


3-14 Power Plant


Power Plant

1. DimensionsThis section contains data necessary for determining the platforms and associated facilities requiredfor power plant handling.

3-14Page 1

Oct 01/09



AT

W−

MM

−05

16−

A

INBOARD POSITION

OUTBOARD POSITION

8495 mm(334.45 in)

6194 mm(243.86 in)

10565 mm(415.94 in)

3808 mm(149.92 in)

1311 mm(51.81 in) 2333 mm

(91.85 in)

L_MF_031400_1_0010102_01_01

3899 mm(153.5 in)

Engine DimensionsGP 7200 Engines

3-14Page 2

Oct 01/09



INBOARD

OUTBOARD

7194 mm(283.2 in)

6178 mm(243.2 in)

8360 mm(329 in)

3873 mm(152.5 in)

INSTALLATION

INSTALLATION

2376 mm(93.5 in)

1178 mm(46.3 in)

3896 mm(153.4 in)

L_MF_031400_1_0020102_01_00

Engine DimensionsTRENT 900 Engines

3-14Page 3

Oct 01/09



OPEN POSITIONS:INITIAL: 40°FULL: 50°

40°50°

OPENPOSITION INBOARD ENG. OUTBOARD ENG. INBOARD ENG. OUTBOARD ENG. ALL ENG.

DIM. B DIM. C DIM. A

40°

50°

6.95 m1.30 m(4.2 ft)1.30 m

2.27 m(7.4 ft)2.27 m(7.4 ft)

A

C

B

2.0 m(6.6 ft)2.4 m(7.8 ft)

3.0 m(9.7 ft)

3.4 m(11.2 ft)

7.3 m(23.9 ft)(4.2 ft)

(22.8 ft)

L_MF_031400_1_0040101_01_01

A

A

Fan CowlsTRENT 900 Engines

3-14Page 4

Oct 01/09



45°

C

B

ALL ENGINES

6.80

22.3045°

m

ft

A

MIN MAX

A

ENGINE 1−4

2.64

8.6645°

m

ft

B

3.14

10.30

MIN MAX

ENGINE 2−3

1.86

6.10

2.16

7.08

C

SEE MFP SECTION1−9

NOTE:

AA

A

A

: FAN COWL

1 1

B AND C DEPENDING ON AIRCRAFT CONFIGURATION.

1 A

L_MF_031400_1_0060101_01_01

Fan Cowls - Engine 1-2-3-4GP 7200 Engines

3-14Page 5

Oct 01/09



6.30

20.6645°

m

ft

AMIN MAX

2.64

8.6645°

m

ft

3.14

10.30


NOTE:

A

A

5.70

18.7035°

m

ft

2.30

7.5435°

m

ft

2.80

9.18

C

45°35°C B C

B

A A11

1 1

: FAN EXHAUST COWL1


A

B

L_MF_031400_1_0070101_01_01

Fan Exhaust Cowls - Engine 1-4GP 7200 Engines

3-14Page 6

Oct 01/09



A

A

6.30

20.6645°

m

ft

AMIN MAX

1.86

6.1045°

m

ft

B

2.16

7.08


NOTE:

5.80

19.0235°

m

ft

1.52

4.9835°

m

ft

1.82

5.97

C

: TRUST REVERSER1


A

L_MF_031400_1_0080101_01_00

45°35°C B C

B

A A11

1 1

Thrust Reverser - Engine 2-3GP 7200 Engines

3-14Page 7

Oct 01/09


3-15 Component Sizes and Weights


Component Sizes and Weights

1. General

This topic details the weights of the primary removable components on the A380 aircraft for models-800 and -800F. Weights in para. A are for components fitted to each wingAll weights are approximate values and are given in kg (lb.).

A. Wing

SLATS

Model -800/ Model -800F

Droop Nose 1 219 kg (482 lb.) /221 kg (487 lb.)

Droop Nose 2 200 kg (441 lb.) /202 kg (445 lb.)

Slat 2 148 kg (326 lb.) /149 kg (328 lb.)

Slat 3 145 kg (319 lb.) /146 kg (322 lb.)

Slat 4 150 kg (330 lb.) /152 kg (335 lb.)

Slat 5 131 kg (288 lb.) /132 kg (291 lb.)

Slat 6 115 kg (253 lb.) /116 kg (255 lb.)

Slat 7 108 kg (238 lb.) /109 kg (240 lb.)

FLAPS


Inner 656 kg (1446 lb.) /687 kg (1514 lb.)

Midboard 681 kg (1501 lb.) /709 kg (1563 lb.)

Outer 395 kg ( 870 lb.) /410 kg ( 904 lb.)

FLAP TRACKS


Equipped Track 1 212 kg ( 467 lb.) /229 kg ( 505 lb)

Equipped Track 2 455 kg (1003 lb.) /478 kg (1053 lb)





3-15Page 1

Oct 01/09


FLAP TRACKS


Flap Track Fairing 2 (LH wing) <1> 209 kg (460 lb.)

Flap Track Fairing 2 (RH wing) 179 kg (394 lb.)

Flap Track Fairing 3 139 kg (306 lb.)




<1> RAT installed.

AILERONS


Inner 215 kg (474 lb.)

Midboard 235 kg (518 lb.)

Outer 256 kg (564 lb.)

SPOILERS


Spoiler 1 96 kg (211 lb.)








B. Landing gear

BODY LANDING GEAR (BLG)


BLG 5847 kg (12890 lb.)

BLG Dragbrace assembly 462 kg (1018 lb.)

BLG Shock absorber assembly 2111 kg (4654 lb.)

BLG Actuator retraction assembly 91 kg (201 lb.)

BLG Actuator bogie trim assembly 71 kg (157 lb.)

3-15Page 2

Oct 01/09


BODY LANDING GEAR (BLG)


BLG wheels 873 kg (1925 lb.)

BLG Brakes 443 kg (977 lb.)

BLG Tires 701 kg (1545 lb.)

BLG Door actuator centre 18 kg (40 lb.)

BLG Door actuator inner 20 kg (44 lb.)

BLG Door actuator outer 38 kg (84 lb.)

WING LANDING GEAR (WLG)


WLG 4014 kg (8849 lb)

WLG Sidestay assembly 238 kg (525 lb)

WLG Shock absorber assembly 1598 kg (3523 lb)

WLG Actuator retraction assembly 117 kg (258 lb)

WLG Actuator bogie trim assembly 9 kg (20 lb)

WLG Wheels 606 kg (1336 lb)

WLG Brakes 443 kg (977 lb)

WLG Tires 467 kg (1030 lb)

Wing gear door actuator 30 kg (66 lb)

NOSE LANDING GEAR


NLG 1909 kg (4209 lb.)

NLG Leg 1215 kg (2679 lb.)

NLG Upper panel equiped 226 kg (498 lb.)

NLG Retraction actuator equiped 69 kg (152 lb.)

NLG Wheels 176 kg (388 lb.)

NLG Tires 182 kg (401 lb.)

Nose gear door actuator 27 kg (60 lb.)

3-15Page 3

Oct 01/09


C. Fuselage

NOSE FUSELAGE


Radome 60 kg (132 lb.)

Windshield panel 36 kg ( 79 lb.)

Lateral Sliding Window panel 21 kg ( 46 lb.)

(including mechanism) 46 kg (101 lb.)

Lateral Fixed Window panel 21 kg ( 46 lb.)

PASSENGER DOORS AND ASSOCIATED SLIDES (MAIN DECK)

Model -800Door n˚ M2 + Slide 125 kg (275 lb.) + 102 kg (225 lb.)

Door n˚ M3 + Slide 122 kg (269 lb.) + 96 kg (216 lb.)




PASSENGER DOORS AND ASSOCIATED SLIDES (UPPER DECK)

Model -800Door n˚ U1 + Slide 125 kg (275 lb.) + 136 kg (299 lb.)

Door n˚ U2 + Slide 125 kg (275 lb.) + 134 kg (295 lb.)

Door n˚ U3 + Slide 125 kg (275 lb.) + 134 kg (295 lb.)

CARGO DOORSModel -800

Forward Cargo Door 300 kg ( 661 lb.)

Aft Cargo Door 270 kg ( 595 lb.)

Bulk Cargo Door 40 kg ( 88 lb.)

Upper Deck Cargo Door 410 kg ( 904 lb.)

Main Deck Cargo Door 470 kg (1036 lb.)

REAR FUSELAGE SECTION 19.1


Structure 433 kg (955 lb)

3-15Page 4

Oct 01/09


REAR FUSELAGE SECTION 19.1


Systems 236 kg (520 lb.)

MISCELLANEAOUS


Nose Landing gear doors:-- forward (each)-- rear (each)

167 kg (368 lb.)58 kg (128 lb.)25.5 kg ( 56 lb.)

Body Landing gear doors:-- Outer door-- Centre door-- Inner door-- Auxiliary door

388.2 kg (856 lb)103.3 kg (228 lb)167.8 kg (370 lb)10.1 kg (22 lb)

Wing Landing gear doors-- Main door-- Auxiliary door

369.4 kg (814 lb)31.6 kg (70 lb)

Control Units:-- Flaps-- Slats

55 kg (121 lb.)34 kg (75 lb.)

Air Conditioning Pack (one side) 397 kg (875 lb.)

APU access door:-- right-- left

25 kg (55 lb.)27 kg (60 lb.)

APU exhaust 96 kg (211 lb.)

APU electrical system 49 kg (108 lb.)

D. Stabilizers

VERTICAL TAIL


Box (equipped without rudder) 2491 kg (5491 lb)

Rudder 693 kg (1527 lb)

Leading edge 171 kg ( 377 lb)

Dorsal fin 25 kg ( 55 lb)

Tip 30 kg ( 66 lb)

Fuselage fairing 62 kg ( 136 lb)

3-15Page 5

Oct 01/09


HORIZONTAL TAIL


Box 3982 kg (8778 lb.)

Outer elevator 388 kg ( 855 lb.)

Inner elevator 508 kg (1119 lb.)

Leading edge 467 kg (1029 lb.)

Trailing edge 688 kg (1516 lb.)

Tip 100 kg ( 220 lb.)

Miscellaneous 114 kg ( 251 lb.)

Systems 241 kg ( 531 lb.)

E. Miscellaneous

MISCELLANEAOUS


Ram air turbine assembly 185.2 kg ( 408 lb.)

Battery 41.9 kg ( 92 lb.)

Engine fire extinguisher bottle 21.8 kg ( 48 lb.)

F. Engine and nacelle

ENGINE AND NACELLE TRENT 900


Engine (Excluding mounting and BFE) 6469 kg (14262 lb)

Fan Cowl 198 kg (437 lb.) / nacelle

Thrust Reverser 650 kg (1433 lb.) / nacelle

Fan Exhaust Cowl 900 kg (1984 lb.) / nacelle

BFE 139 kg (306 lb.)

Air Inlet 351 kg (774 lb.) / nacelle

Pylon (structure + systems) 1230 kg (2712 lb)

ENGINE AND NACELLE GP 7200


Engine 6123 kg (13499 lb)

Fan Cowl 240 kg (529 lb) / nacelle

Thrust Reverser Unit 1381 kg (3045 lb) / nacelle

Fan Exhaust Cowl 918 kg (2024 lb) / nacelle

3-15Page 6

Oct 01/09


ENGINE AND NACELLE GP 7200


BFE-EBU 710 kg (1565 lb)

Air Inlet 358 kg (789 lb)

Pylon (structure + systems) 1240 kg (2734 lb)

3-15Page 7

Oct 01/09




Component Handling

1. General

Section 3-16 gives the information on dimensions and on the Center of Gravity (C.G.) locations of thevarious control surfaces. All the dimensions are in millimeters and inches.

3-16Page 1

Oct 01/09



DROOP NOSE 1

NOTE: DIMENSIONS IN MILLIMETRES (INCHES IN BRACKETS)

CG

HOISTINGPOINT

742 (29.2)2127 (83.7)

3511 (138.2)

4325 (170.3)

323(12.7)

328(12.9)

363(14.3)

FWD

OTBD

L_MF_031600_1_0010101_01_00

Droop Nose 1CG Location

3-16Page 2

Oct 01/09



DROOP NOSE 2


CG

HOISTINGPOINT

4383 (172.5)

3843 (151.3)2240 (88.1)

720 (28.3)

320(12.6)

338(13.3)

372(14.6)

FWD

OTBD

L_MF_031600_1_0020101_01_00

Droop Nose 2CG Location

3-16Page 3

Oct 01/09



CG

HOISTINGPOINT

SLAT 2


3724 (146.6)

2575 (101.4)

1802 (70.9)

883 (34.7)

315(12.4)

352(13.9)

438(17.3)

FWD

OTBD

L_MF_031600_1_0030101_01_00

Slat 2CG Location

3-16Page 4

Oct 01/09



CG

HOISTINGPOINT

SLAT 3


3854 (151.7)

2919 (114.9)

1937 (76.3)

999 (39.3)

361(14.2)

375(14.8)

395(15.5)

FWD

OTBD

L_MF_031600_1_0040101_01_00

Slat 3CG Location

3-16Page 5

Oct 01/09



CG

HOISTINGPOINT

SLAT 4


3871 (152.4)

2892 (113.9)

1892 (74.5)

1056 (41.6)

344(13.5)

327(12.9)

348(13.7)

FWD

OTBD

L_MF_031600_1_0050101_01_00

Slat 4CG Location

3-16Page 6

Oct 01/09



CG

HOISTINGPOINT

SLAT 5


4786 (188.4)

3424 (134.8)4786 (188.4)

2398 (94.4)

231(9.1)

278(11)

300(11.8)

FWD

OTBD

L_MF_031600_1_0060101_01_00

Slat 5CG Location

3-16Page 7

Oct 01/09



CG

HOISTINGPOINT

SLAT 6


4534 (178.5)3423 (134.8)

2317 (91.2)1143 (45)

215(8.5)

270(10.6)

317(12.5)

FWD

OTBD

L_MF_031600_1_0070101_01_00

Slat 6CG Location

3-16Page 8

Oct 01/09



CG

HOISTINGPOINT

SLAT 7


5234 (206)

4338 (170.8)2688 (105.8)

920 (36.2)

212(8.4)

218(8.6)

236(9.3)

FWD

OTBD

L_MF_031600_1_0080101_01_00

Slat 7CG Location

3-16Page 9

Oct 01/09



L_MF_031600_1_0130101_01_00

FWD

OUTBOARD

HINGELINE

2252 (88.7)

2074 (81.6)

1196 (47.1)

956 (37.6)

379(14.9)

277(10.9)

292(11.5)

256(10.1)

885(34.8)

CG

HOISTING POINT

INBOARD AILERON

Inboard AileronCG Location

3-16Page 10

Oct 01/09



CG

HOISTING POINT

MID AILERON

FWD

OUTBOARD

HINGELINE

2923 (115.1)

2455 (96.6)

1377 (54.2)

1201 (47.3)

417(16.4)

261(10.3)

299(11.8)

823(32.4) 258

(10.1)

L_MF_031600_1_0140101_01_00

Mid AileronCG Location

3-16Page 11

Oct 01/09



CG

HOISTING POINT

OUTBOARD AILERON

FWD

OUTBOARD

HINGELINE

4090 (161.0)

4026 (158.5)

2232 (87.9)

1911 (75.2)

652(25.7)

250(9.8)

226809

780(30.7)

271(10.7)

L_MF_031600_1_0150101_01_00

Outboard AileronCG Location

3-16Page 12

Oct 01/09



CG

HOISTING POINT

SPOILER 1

L_MF_031600_1_0160101_01_00

FWD

OUTBOARD

2517 (99.1)

2186 (86.1)

1273 (50.1)

596(23.5)

252(9.9)

50(1.9)

50(1.9)

Spoiler 1CG Location

3-16Page 13

Oct 01/09



CG

HOISTING POINT

SPOILER 2

L_MF_031600_1_0170101_01_00

FWD

OUTBOARD

2236 (88.0)

2021 (79.6)

1108 (43.6)

431(17.0)

235(9.2)

50(1.9)

50(1.9)


3-16Page 14

Oct 01/09



CG

HOISTING POINT

SPOILER 3

L_MF_031600_1_0180101_01_00

FWD

OUTBOARD

2311 (91.0)

2039 (80.3)

1037 (40.8)

299(11.8)

239(9.4)

50(1.9)

50(1.9)


3-16Page 15

Oct 01/09



CG

HOISTING POINT

SPOILER 4

L_MF_031600_1_0190101_01_00

FWD

OUTBOARD

2206 (86.8)

1966 (77.4)

1103 (43.4)

226(8.9)

248(9.8)

50(1.9)

50(1.9)


3-16Page 16

Oct 01/09



CG

HOISTING POINT

SPOILER 5

L_MF_031600_1_0200101_01_00

FWD

OUTBOARD

2089 (82.2)

1898 (74.7)

1047 (41.2)

308(12.1)

234(9.2)

50(1.9)

50(1.9)


3-16Page 17

Oct 01/09



CG

HOISTING POINT

SPOILER 6

L_MF_031600_1_0210101_01_00

FWD

OUTBOARD

2610 (102.7)

1942 (76.5)

1318 (51.9)

352(13.9)

196(7.7)

50(1.9)

50(1.9)


3-16Page 18

Oct 01/09



CG

HOISTING POINT

SPOILER 7

L_MF_031600_1_0220101_01_00

FWD

OUTBOARD

2716 (106.9)

2287 (90.0)

1370 (53.9)

697(27.4)

190(7.5)

50(1.9)

50(1.9)


3-16Page 19

Oct 01/09



CG

HOISTING POINT

SPOILER 8

FWD

OUTBOARD

2872 (113.1)

2183 (85.9)

1427 (56.2)

593(23.3)

154(6.1)

50(1.9)

50(1.9)

L_MF_031600_1_0230101_01_00


3-16Page 20

Oct 01/09



15 mm(0.6 in)

11896 mm(468.3 in)

1. CG POSITION OF HORIZONTAL STABILIZER WITHOUT THE ELEVATORS2. CG POSITION OF THE INNER ELEVATOR3. CG POSITION OF THE OUTER ELEVATOR

2 CG

3 CG

3293 mm(129.6 in)

9030 mm(355.5 in)

9356 mm(368.3 in)

1 CG

6864 mm(270.2 in) 3293 mm

(129.6 in)

L_MF_031600_1_0090101_01_00

Horizontal StabilizerCG Location

3-16Page 21

Oct 01/09



CG POSITION OF THE VERTICAL STABILIZER WITH THE RUDDER AND WITH THE DORSAL FIN

5912 mm(232.8 in)

9950 mm(391.7 in)

VTX0

VTZ0

CG

L_MF_031600_1_0100101_01_00

Vertical Stabilizer and RudderCG Location (Sheet 1)

3-16Page 22

Oct 01/09



2777 mm(109.3 in)

VTZ0

VTX0

1 CG

2 CG

3 CG

9027 mm(355.4 in)

5894 mm(232.0 in)

9320 mm(366.9 in)

14660 mm(577.2 in)

11021 mm(433.9 in)

1. CG POSITION OF THE VERTICAL STABILIZER WITHOUT THE RUDDER AND DORSAL FIN2. CG POSITION OF THE UPPER RUDER3. CG POSITION OF THE LOWER RUDDER

L_MF_031600_1_0110101_01_00

Vertical Stabilizer and RudderCG Location (Sheet 2)

3-16Page 23

Oct 01/09



Y

X

STA77204.5/FR120

STA72320/FR110

CG

WITHAPU GENERATOR

WITHOUTAPU GENERATOR

mm mm

XYZ

206622

2420 95.280.87

81.34 214635

2609 102.721.38

84.49

in in

Z

CL

STA74592/FR115

STA74002/FR114

L_MF_031600_1_0120101_01_00

Tail coneCG Location

3-16Page 24

Oct 01/09




Suggested Hangar Arrangement

1. General

The purpose of a maintenance hangar is to provide a weather-safe space for aircraft servicing,maintenance and repair activities. It may also include space for aircraft component workshops,support equipment and administrative facilities.Maintenance hangar planning should take the following factors into consideration :- level of maintenance to be performed,- capacity including storage space,

NOTE : The number of hangar bays depends on :- fleet size,- aircraft utilization,- maintenance check intervals,- number of aircraft requiring maintenance action at the same time,- maintenance check elapsed time,- working hours available.- local labor regulations,- clearances : external (e.g. hangar doors) and internal (e.g. for aircraft jacking),- tractor drive-through capability,- special features (see paragraph A.),- ground support equipment (see paragraph B.),- environmental control (lighting/heating/air conditioning) : temperature (hot or cold climate),

dust or humidity, prevailing winds,

NOTE : Hangar lighting levels should be 75 footcandles (800 lm/m2).- structural materials/design (the roof is the most expensive part of the hangar),- security,- safety equipment and fire protection (see paragraph C.),- local building codes,- site location with respect to aprons, taxiways, runways and electromagnetic constraints.- geotechnical investigation,- extension capability.

2. Special Features :- Cranes,- landing gear maintenance pits,- mezzanine,- fixed work stands,- aircraft cleaning, stripping and painting capabilities,- drainage,

3-17Page 1

Oct 01/09


- ventilation (work in fuel tank),- pneumatic, electrical and hydraulic connections,- computer system (aircraft maintenance and planning).

3. Ground Support Equipment :- Air conditioning unit,- nitrogen cart,- oxygen cart,- hydraulic rig,- air starter unit,- air compressor,- electrical ground power unit,- fuel tank ventilation unit,- lavatory service unit, -- tractor,- tow bars,- engine cradles and trolleys (engine Removal/Installation),- mobile maintenance docks/platforms,- jacks,- elevating platforms,- stairways,- access steps,- mobile scissor platform,- weighing devices,- storage racks.

4. Safety Equipment and Fire Equipment :- safety harnesses with damping device,- explosive atmosphere detection devices,- sprinkler network using a mixture of water and emulsifying agent,

NOTE : Quantity required is 10 l/m2 per minute minimum. Water storage tanks should haveenough capacity for one hour’s use.

- foam spray gun(s) using same mixture as the sprinkler system,

NOTE : Minimum flow rage : 200 m3/h.- portable fire-fighting devices using dry chemical (powder), water or CO2.

3-17Page 2

Oct 01/09



16 m(50.50 ft)

29.5 m(96.78 ft)5 m (16.40 ft)

5 m(16.40 ft)

29.5 m(96.78 ft)

L_MF_031700_1_0010102_01_00

Suggested Hangar ArrangementNose--in Position (Sheet 1)

3-17Page 3

Oct 01/09



15 m *(49.21 ft)*

10 m(32.80 ft)

10 m(32.80 ft)

10 m(32.80 ft)

98 m (321.52 ft)

100

m (

328.

08 ft

)

* : MINIMUM NECESSARY DISTANCE TO MOVE AWAY A TRACTOR WITH A TOW BAR

L_MF_031700_1_0020102_01_00

Suggested Hangar ArrangementNose--in Position (Sheet 2)

3-17Page 4

Oct 01/09



5 m(16.40 ft)

29.5 m(96.78 ft)

L_MF_031700_1_0030102_01_00

Suggested Hangar ArrangementTail--in Position (Sheet 1)

3-17Page 5

Oct 01/09



10 m(32.80 ft)

10 m(32.80 ft)

10 m(32.80 ft)

100

m(3

28.0

8 ft)

10 m(32.80 ft)

93 m (305.11 ft)

L_MF_031700_1_0040102_01_00

Suggested Hangar ArrangementTail--in Position (Sheet 2)

3-17Page 6

Oct 01/09




Landing Gear Maintenance Pits

1. General

The maintenance pit envelopes for the landing gear shock absorber maintenance are shown in Figs.001 thru 004. 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 max. 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 Figs 001 thru 003.

A. ElevatorsThese can be either mechanical or hydraulic. They are used to :

(1) Permit easy movement of persons and equipment around the landing gears.

(2) To lift remove landing gear assemblies out of the pits.

B. JackingThe airplane 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. Section 3-1 for airplane maintenancejacking. Jacks must support the total airplane weight, i.e. when the landing gears do not touchthe elevators 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.

3-18Page 1

Oct 01/09



2 59

8

(102

.3)

5 62

5.5

(221

.5)

1 66

3

(65.

5)

FRONT OF NOSE RADOME

1 52

6

(60.

1) 763

(30)

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 33 6

59(1

325

.1)

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

WLG

EX

TE

NS

ION

RE

TR

AC

T P

IT O

UT

LIN

E

WIN

G J

AC

KIN

G P

OIN

T

LH W

ING

SH

OW

N R

H S

IMIL

AR

BLG

EX

TE

NS

ION

RE

TR

AC

T P

IT O

UT

LIN

E

BLG

RE

MO

VA

L P

IT O

UT

LIN

E

BLG

PIS

TO

N R

EM

OV

AL

PIT

OU

TLI

NE

4 506

(177.4)

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

L_MF_031800_1_0010101_01_00

Maintenance PitsMaintenance Pit Envelopes

3-18Page 2

Oct 01/09



576

(22.

7)

709

(29.

9)

1 72

5(6

7.9)

804

(31.

7)1

127

(44.

4)

1 97

7

(77.

8)

802

(31.

6)

1 24

3(4

8.9)

1 98

9

(78.

3)

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

L_MF_031800_1_0020101_01_00

Maintenance PitsNecessary Depths

3-18Page 3

Oct 01/09



3 560(140.2)

513(20.2)

2 79

1(1

09.9

)

WLG

PIS

TO

N R

EM

OV

AL

PIT

OU

TLI

NE

972

(38.

3)

3 15

8(1

24.3

)

3 71

1(1

46.1

)

7 13

4(2

80.9

)

4 12

6(1

62.4

)

1 92

9(7

5.9)

1 490(58.7)

2 58

5(1

01.8

)

952(37.5)

2 368(93.2)

1 067(42)

6 228(245.2)

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

EX

TE

NS

ION

/RE

TR

AC

TIO

NP

IT O

UT

LIN

E

AIR

CR

AF

T C

EN

TE

R L

INE


MINIMUM DIMENSIONS, ZERO CLEARANCES SHOWN L_MF_031800_1_0030101_01_00

Maintenance PitsMaintenance Pit Envelopes - WLG Pit Dimensions

3-18Page 4

Oct 01/09



AIR

CR

AF

T C

EN

TE

R L

INE

1 68

0(6

6.1)


1 025(40.4)

2 105(82.9)

1 490(58.6)

133

(5.2

)

4 85

6(1

91.2

)3

188

(125

.5)

7 13

4(2

80.9

)

1 168(46)

2 632(103.6)

BLG

PIS

TO

N R

EM

OV

AL

BLG

RE

MO

VA

LP

IT O

UT

LIN

E

WLG

RE

MO

VA

L A

ND

EX

TE

NS

ION

/RE

TR

AC

TIO

NP

IT O

UT

LIN

E

BLG

EX

TE

NS

ION

/RE

TR

AC

TIO

NP

IT O

UT

LIN

E

PIT

OU

TLI

NE

MINIMUM DIMENSIONS, ZERO CLEARANCES SHOWN L_MF_031800_1_0040101_01_01

Maintenance PitsMaintenance Pit Envelopes - BLG Pit Dimensions

3-18Page 5

Oct 01/09




Suggested Workstands

1. GeneralThe essential aspects that affect a decision to build a fixed dock or a movable dock are :- the fleet size of one type of aircraft,- the different types of aircraft in operation which demand the same hangar facilities,- the hangar facilities must comply for both light maintenance or major maintenance.It would appear logical to build a fixed dock facility where the fleet size of one type of aircraftprovides for an adequate workload. This therefore implies that the fixed dock is in use most of thetime.When the fleet size is small or adaptability is required, movable workstands are more economic andproficient. Movable workstands are a facility that can be used for different types of aircraft.Illustrations which show the movable workstands have been incorporated to help develop basefacilities.

Summary of Recommended Movable Workstands Aircraft on Wheels A380-800 Models

Item No. of Description Access to

1 4Cargo CompartmentPlatform

Cargo Compartments

2 4 Engine Platform Engine/Pylon/Radome Nose LandingGear

3 1WLG/BLG CompartmentPlatform

Wing and Body Landing GearCompartments

4 1 Rear Fuselage Platform Rear Fuselage

5 1 Hydraulic Platform-GiraffeVertical/Horizontal Stabilizer/APUCompartment/Fuselage

6 6Pax Door Platform -- Mainand Upper Decks

Passenger Doors/Cabin/Flight Deck

7 1 Fuselage Platform Fuselage

8 2 Inner Wing Platform Wing Root and Flap/Slat System

9/10 4 Outer Wing Platform Flap/Slat and Spoiler System

Summary of Recommended Movable Workstands Aircraft on Wheels A380-800F Models


1 4 Cargo Compartment Platform Cargo Compartments

2 4 Engine Platform Engine/Pylon/Radome Nose LandingGear

3-19Page 1

Oct 01/09


Summary of Recommended Movable Workstands Aircraft on Wheels A380-800F Models


3 1WLG/BLG CompartmentPlatform

Wing and Body Landing GearCompartments

4 1 Rear Fuselage Platform Rear Fuselage

5 1 Hydraulic Platform-GiraffeVertical/Horizontal Stabilizer/APUCompartment/Fuselage

6 6Pax Door Platform -- Mainand Upper Decks

Passenger Doors/Cabin/Flight Deck

7 1 Fuselage Platform Fuselage

8 2 Inner Wing Platform Wing Root and Flap/Slat System

9/10 4 Outer Wing Platform Flap/Slat and Spoiler System

3-19Page 2

Oct 01/09



6 14 66 1

66

6 6

6 5

5 6

66 7

6 65

32910 8 9 9

L_MF_031900_1_0010101_01_01

General Arrangement(Sheet 1)

3-19Page 3

Oct 01/09



1

1

5

5

4 17

61 56

1

1 6

32910 8 9 9

L_MF_031900_1_0020101_01_01

General Arrangement(Sheet 2)

3-19Page 4

Oct 01/09



A

ASEE

CHAPTER1−9

L_MF_031900_1_0030101_01_00

Cargo Compartment Platform(Sheet 1)

3-19Page 5

Oct 01/09



A

A

EXAMPLE

FWD AND AFT CARGO DOORS

CARGO COMPARTMENT PLATFORM

EXAMPLE FOR MAIN DECK ANDUPPER DECK CARGO DOORS

A

SEECHAPTER

1−9

FWD FWD

L_MF_031900_1_0040101_01_00

Cargo Compartment Platform(Sheet 2)

3-19Page 6

Oct 01/09



ACCESS TO PYLONS AND ENGINES

A

A

EXAMPLEENGINE PLATFORM

SEE CHAPTER 1−9SEE CHAPTER 1−9

L_MF_031900_1_0050101_01_00

Engine Platform

3-19Page 7

Oct 01/09



A

A

BLG/WLG COMPARTMENT PLATFORM

SEECHAPTER

1−9

L_MF_031900_1_0060101_01_00

WLG/BLG Compartment Platform

3-19Page 8

Oct 01/09



ADJUSTABLE STAIRS

A

A

REAR FUSELAGE PLATFORM

SEECHAPTER

1−9

L_MF_031900_1_0070101_01_00

Rear Fuselage Platform

3-19Page 9

Oct 01/09



(137.8 in)3500 mm

SEECHAPTER

1−9

L_MF_031900_1_0080101_01_00

Hydraulic Platform -- Giraffe

3-19Page 10

Oct 01/09



A B

BB

MAIN DECK UPPER DECK

EXAMPLE

A

2400 mm

900 mm(35.4 in)

1200 mm(47.2 in)(94.5 in)

SEECHAPTER

1−9

SEECHAPTER

1−9

A

L_MF_031900_1_0090101_01_00

Pax Door Platform -- Main and Upper Decks

3-19Page 11

Oct 01/09



(197 in)5 m 8 m

(315 in)

A

A

FUSELAGE PLATFORM

L_MF_031900_1_0100101_01_00

Fuselage Platform

3-19Page 12

Oct 01/09



INNER WING PLATFORM

A

9.17 m(361.02 in)

L_MF_031900_1_0110101_01_01

SEE CHAPTER1−9

A

Inner Wing Platform

3-19Page 13

Oct 01/09



OUTER WING PLATFORM

TYPICAL

SEECHAPTER

1−9

SEECHAPTER

1−9

SEECHAPTER

1−9

6.95 m(273.62 in)

12.23 m(481.59 in)

A

B

A

BL_MF_031900_1_0120101_01_00

Outer Wing Platform

3-19Page 14

Oct 01/09


COMPONENT REPAIR/OVERHAUL AND FUNCTIONAL TEST

4-1 Batteries Shop


Batteries Shop

1. GeneralThe workshops should be located as close as possible to the maintenance hangar. Certain supportshops are closely associated with on-aircraft maintenance.They should be designed to allow future extension of the Airline fleet and to accept test and repair ofcomponents coming from other Airlines. The capability and consequently the size of the shops willdepend on the level of on and off-aircraft maintenance that they support.They should be located in the same area and arrangement should consider the following:- Rapid transit between hangar floor, workshops and stores.- Minimal movement and minimal administrative tracking.- Bring aircraft maintenance activities and workshops services ″to the aircraft″.They could be divided/regrouped in three main activities:

A. Aircraft Maintenance- Interior equipment shop.- Life jacket, slide/raft equipment shop.- Metal shop.- Machine shop.- Composite repair shop.- Tube repair shop.- Electrical wire marking shop.

B. Aircraft Components and Engines

(1) Avionic- Battery shop.- VFG Generator shop.- Electrical accessories shop.- I.E.R.A. (Instrument, Electric, Radio and navigation, Avionic) shop.

(2) Hydro/mechanic- Engine and APU shop.- Fuel components shop.- Hydraulic components shop.- Pneumatic components shop.- Tire/wheel and brake shop.

C. Aircraft Support- Laboratory test of fluids/metallurgical.- Painting shop.- Surface and heat treatment shop.

4-1Page 1

Oct 01/09


They should be at different floor level e.g.: wheel and brake, machine tool, surface protection...at ground level, cabin interior, safety equipment... at first floor.Stores and offices should be air conditioned. Shop lighting should be 50 foot-candles (800lumens/m2) with a 100 foot-candle local task lighting for inspection or detailed work. Nondestructive test, composite repair, avionic shops and safety equipment shop should be equippedwith air moisture and temperature control device.

4-1Page 2

Oct 01/09


4-2 VFG Generator Shop


VFG Generator Shop

1. GeneralThe shop is dedicated to overhaul, test and repair all components of electrical generation system.- VFG generator test stand- VFG governor test stand- Flushing cart VFG cooling system- Standard and specific adapters- Standard tools

4-2Page 1

Oct 01/09




Composite Repair Shop

1. GeneralThe shop is dedicated to composite and fibreglass repair according to SRM procedures.- The room or surrounding temperature has to remain between 18˚C and 30˚C (64-86˚F) during

the repair.- The preparation area has to be dust cleaned (air filtration = 10 micron m) and dry.- The relative humidity has not to be greater than 75 %.- Condensation on the repair area has to be avoided.- Environmental data: temperature and humidity, have to be recorded.

2. Paint Removal/cleaning

A. Scraper

B. Cutter

C. Abrasive rotating disk

D. Abrasive paper

E. ″Scotch brite″ brown

F. Ethyl acetate

G. Demineralized water

H. Tweezers

3. Machining/specific Tooling

A. Polymerized material

(1) Fibreglass/carbon- Drills has or carbide- Diamante shark cutters: spot face cutter, rose countersink, cone countersink, circular

saw cutter...- Countersink micro stop 100˚ adjustable drive- Pneumatic drilling machine- Pneumatic router equipped with vacuum system- Specific adaptors.

(2) Kevlar- Specific twist cutter or alternate teeth carbide cutter- Cutter- Abrasive disk/paper.

(3) Honeycomb- Diamante shark cutter- Cutter

4-3Page 1

Oct 01/09


- Metal saw- Abrasive disk/paper- Adhesive tape double face

B. Prepreg/dry fabric

(1) Fibreglass/carbon- Scissors standard- Cutter- Templates

(2) Kevlar- Specific ceramic scissors

(3) GLARE

4. Standard Tools

A. Spatula

B. High precision weighing device

C. Squeegee

D. Containers (for resin)

E. Glass rods

F. Plastic film

G. Bottles

H. Spring pin type clamps

J. Clamp

K. Adhesive tape

L. Syringe with hypodermic needle

M. Gloves (rubber and cotton)

N. Mask

P. Pair of glasses

Q. Sanding block

R. White ink ″rotring″S. Riveting machine for blind rivets

5. Heating and Pressure Equipment

A. Hot bonding and vacuum control unit

B. Heating blankets

C. Anti humidity heat blankets or radiant panels

4-3Page 2

Oct 01/09


D. Nylon vacuum bag films (3 grades)

E. Breather fabrics

F. Peel/bleed fabric

G. Shrink tapes

H. Perforated plastic film I. Mosite J. Sealant tape

J. Oven L. Autoclave (1 m dia x 2.5 m)*

6. Test Equipment

A. Ultra sonic test equipment

B. Tool for tap test

C. Compression/traction and peeling testers**

D. Lamp

E. Inspection mirror

4-3Page 3

Oct 01/09




Electrical Accessories Shop

1. GeneralThe shop is dedicated to the overhaul, test and repair of all aircraft electrical accessories.

A. General test stand ac/dc power requirements

B. Amplifier control test

C. Test stand for lights

D. Test stand coffee makers and refrigerators

E. Functional test stand for linear actuators and control dampers

F. Functional test stand for rotary actuators

G. Test set static inverters

4-4Page 1

Oct 01/09




Electrical Wire Marking Shop

1. GeneralDedicated to mark the electrical wires used for electrical harnesses repair.The wires authorized for use on Airbus aircraft are those listed in AWM/AWL Chapter 20-41. Ingeneral Airbus have nickel plated cores and American spec. wires have tin plated cores. We do notuse extruded x- linked Tefzel insulation (e.g. Raychem 55) for Airbus general airframe wires (exceptin specific areas like the U/C).- U.V. laser machine

or- Co2 laser machine

NOTE : ink-jet system is not generally used for Airbus aircraft.Airbus wire are marked with either UV laser or CO2 laser technology depending on the origin of theharness but CO2 may be phased out in the future with all wires being marked with UV laser. It wouldappear that UV laser technology is being accepted as the industry standard internationally.CO2 markable wire cannot be UV laser marked and vice versa.

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Oct 01/09




Engine and APU Shop

1. GeneralThe shop is dedicated to disassembly/assembly (modules exchange) and repair engines and APU.

A. Overhead cranes

B. Press

C. Standard hand tools

D. Balancing machine: static and dynamic balance

E. Grinding machine

F. Plasma spray and welding machines

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Oct 01/09




Fuel Component Shop

1. GeneralThe shop is dedicated to overhaul, test and repair all fuel system components.

A. Universal main engine fuel control/accessories test stand

B. Test stand

(1) Fuel boost

(2) Fuel pump

C. Standard adapters and tools

D. Low flow fuel accessory test stand

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Oct 01/09




Hydraulic Component Shop

1. GeneralThe shop is dedicated to test bench capabilities for hydraulic fluids-Working and static tests-Overhaul, inspection and component replacement of most hydraulic actuators and accumulators.

A. Hydraulic generation and accessory test bench

B. Pump hydraulic test stand

C. Servo valves and actuators test stand

D. Standard adapters and tools

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Oct 01/09


4-9 I.E.R.A. Shop


I.E.R.A. Shop

1. GeneralThe I.E.R.A. shop is dedicated to the overhaul and repair of all Instruments, Electric components,Radio and Avionic equipments.

A. Test bench radio

B. Test bench VOR/ILS

C. Test bench dme

D. Test bench adf

E. Test bench SATCOM

F. Test bench Weather Radar

G. Automatic Test Equipment

H. Dedicated test equipment

J. Personal computers

K. Oscilloscopes

L. Arinc reader/generators

M. Magnetic tapes/disc/cassettes eraser (TBC)

N. Data loaders

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Oct 01/09




Interior Equipment Shop

1. GeneralThe shop is dedicated to carpet, seats and cabin panels and partitions repair and fabrication.

A. Cabin Interior

(1) Drilling machine

(2) Painting booth

(3) Washing booth

(4) Vaccum cleaner

(5) Binding machine

(6) Engraving machine

(7) Sewing machine

(8) Press, heat/vacuum pressure equipment

(9) Polishing windows machine

(10) Shear bench

(11) Oven

(12) Freezer

(13) Hand grinder

(14) Circular saw

(15) Sander belt

(16) Kevlar driller

(17) Cutting tools

(18) Work bench

(19) Standard hand tools.

B. Seats

(1) Sewing machine

(2) Drilling machine

(3) Bending machine

(4) Grinding wheel

(5) Belt grinder

(6) Circular saw

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Oct 01/09


(7) Riveting gun

(8) Riveting block

(9) Work bench

(10) Standard hand tools.No special tools or specific equipment are required for maintenance or overhaul work to becarried out on the passenger seats. Standard tools are sufficient for these operations.In addition to standard tools, only few specific tools or equipment are required formaintenance and overhaul work to be carried out on the pilot seats. (Refer to relevantCMM)

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Oct 01/09




Laboratory Test of Fluids

1. GeneralThe laboratory is dedicated to analyse all fluids used on aircraft.

A. Hydraulic fluid - fire resistant - phosphoric ester basedReference documents

(1) NSA307110

(2) AMM A380

(3) CHAPTER 12.32.28

(4) SAE ARP 598

(5) SAE ARP 785

(6) NF T 60-100

(7) NF T 60-101

(8) NF T 60-112 (ASTM D974)

(9) NF T 20-052 (ASTM D1744)

(10) NAS 1638

B. The values below represent the max. Allowable limits of the fluid in service. These limits are alsospecified in the aircraft maintenance manual.

(1) Viscosity

(2) Water content

(3) Density . Acidity

(4) Chlorine content

(5) Conductivity

(6) Particles fluid contamination

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Oct 01/09


4-12 Metal Shop


Metal Shop

1. GeneralFabrication of all metallic parts involving milling boring and turning. All welding processes for allaircraft metals and alloys.

A. Universal lathe 1.5 x 2 x 2

B. Milling machine 1.6 x 0.4

C. Boring machine 0.75 x 0.75 x 0.6

D. Centerless grinding machine

E. Cylindrical grinding machine

F. Universal drilling machine

G. Radial drilling machine

H. Grinders

J. Circular saws

K. Hydraulic press (3 t)

L. Drilling machines set

M. Standard hand tools set

N. Benches

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Oct 01/09


4-13 Painting Shop


Painting Shop

1. GeneralThe shop is dedicated for painting aircraft parts and components.

A. Surface treatment rooms- Sand blasting- Washing- Decreasing- Phosphating cleaning- Drying

B. PaintingClosed spray booth with downdraft ventilation- With multiple wording zones in line- With ventilation zones- With drying device + oven- Open booth with dry filter- Open ″waterscreen″ spray booth- Painting guns- Air compressed sources- Special room for product storage- Special room for paint preparation- Safety equipment: masks, gloves, gas detectors, fire extinguishers.

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Oct 01/09




Pneumatic Component Shop

1. GeneralThe shop is dedicate to overhaul, test and repair all pneumatic components.Workshop test conditions:Atmospheric ambient pressure : TBDAmbient temperature : TBDRelative ambient humidity : TBDDust : normal protection (conventional dust cleaning at regular intervals)Air source :Capable of supplying clean, dry : CONTACT RELATED VENDORS FOR SPECIFICATIONS

NOTE : Hot air source: TBD.

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Oct 01/09


4-15 Life Jacket, Escape Slide / Raft Shop


Life Jacket, Escape Slide / Raft Shop

1. GeneralThe shop is dedicated to the periodic tests and repair of the on-board safety devices.THE SHOP AREA MUST BE CLEAN AND COVERED WITH A TARPAULIN, CARPETING OROTHER PROTECTIVE COVERING. DO NOT WALK ON THE EQUIPMENT. USE SPECIFICSHOES.

A. Cleaning

(1) Moderate duty : simple liquid detergent

(2) Heavy duty : toluene (C6H5CH3) and isopropyl alcohol (according to vendor equipmentspec.)

(3) Dry cleaning solvent for metal parts

(4) Stiff bristle brush

(5) Soft bristle brush

(6) Brush paint

(7) Gloves - Rubber

B. Testing

(1) Compressed air source (oil and moisture free, 20 micron filter) with pressure regulator.

(2) Leak test solution, Ivory clear, Mild liquid detergent.

(3) Soft bristle brush.

(4) Barometer, Scale increments not more than 0.10 inches.

(5) Thermometer, Scale increments not more than 1˚.

(6) Push/pull gage 0-50 lbs O.5 Lbs graduations.

(7) Stopwatch, plain timer, 1/10 Seconds graduations.

(8) Manometer (water). 0-0.5 psi.

(9) Manometer (meriam fluid). 0-6.4 psig. (0.01 graduation).

(10) Manometer (digital pressure). 0-20 psi.

(11) Test set slide raft batteries.

(12) Tester inertia reels.

(13) Weighing devices for bottles and cylinders.

C. Disassembly/assembly/repair

(1) Neoprene strap

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Oct 01/09


(2) Cotton clothes

(3) Scour cloth

(4) Talc or powdered soapstone

(5) Sealer heat poly bags

(6) Wrench open end set

(7) Crowfoot wrench set

(8) Hex key set

(9) Torque wrench. 0-80 in.Lb

(10) Strap wrench

(11) Crescent pliers

(12) Scissors

(13) 5 inch blunt nose, plated

(14) Spatula (pusher)

(15) Hand roller

(16) Vacuum cleaner. Household type

(17) Chain vise

(18) High pressure cap (AN929-4)

(19) Cap filler valve (MS20813-1)

(20) Valve core extraction/insertion tools (Specific. Vendor equipment items)

(21) O-ring installation tools (specific. Vendor equipment items)

(22) Heat gun

(23) Fixture check maximum envelope

(24) Sewing machine

D. Ingredients

(1) Refer to vendor equipment recommendation.

E. Reconditioning

(1) Refer to reconditioning method described in relevant CMM.

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Oct 01/09


4-16 Surface Heat Treatment Shop


Surface Heat Treatment Shop

1. GeneralThis shop is dedicated to surface and heat treatment.

A. Surface TreatmentChemical cleaning baths

(1) Acid

(2) Alkaline descaler

(3) Alkaline permanganate

(4) Caustic cleaner

(5) Corrosion inhibitor

(6) EmulsionHot water rinse bathCold water rinse bathChemical plating bath

(7) Cadmium

(8) Nickel

(9) Chromium

(10) Salt nitriding

(11) Alodine

(12) Chromate

(13) Phosphating

(14) Passivation

(15) Sulphuric/chromic acid anodisinShot peening equipmentSand blasting

B. Heat TreatmentOvenBathsFreezerStandard toolsLiquid effluent decontamination systemExtracted effluvium washing system.

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Oct 01/09


4-17 Tube Repair Shop


Tube Repair Shop

1. Rigid tubes

A. Bending machineBending machines with internal mandrels shall be used. For each nominal diameter there mustbe several mandrels. For titanium pipes it is recommended to use plastic mandrels.

B. Tube end forming device

C. Cutting, facing and deburingStandard hacksaw, band saw, circular saw and conical milling cutter can be used.

D. Cleaning and degreasingStandard equipment: compressed air, perchloroethylene vapour bath....

E. Test equipment

(1) Pressure testStandard pressure test bench with capacity of TBD min. (Pressure test with gas and withliquid).

(2) Dimensions and shape checkStandard equipment + master, template....

F. Tube repair equipmentRefer to AMM chapter 20-23-11 for permaswage repair kit and harrison/sierracin fittingsinstallation.

2. Flexible hosesDue to very specific equipment necessary to manufacture or repair flexible hoses it is suggested tocontact directly the vendors mentioned hereafter.

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Oct 01/09


4-18 Tire/Wheel and Brake Shop


Tire/Wheel and Brake Shop

1. 1. Tire Shop

A. Nitrogen bottles

B. Pressure gauge

C. Inflating gauge

D. Inflating/deflating adapters

E. Safety cage for tire pressure tests

F. Storage racks

2. Wheel Shop″Dirty″ work on wheel overhaul consists of disassembly of the wheel and rim-cleaning. Cleaning canbe done manually: hot water high pressure washing device, combined with semi-automatic devices:solvent baths including treatment bath + rinsing bath + drying bath or with a ″tunnel″ typemachine. Cleaning of small parts like bearings or bolts can be done using an ultrasonic washingmodule or a vertical agitation and total turbulence machine.″Clean″ procedures for wheels start NDT for crack detection. Eddy Current and ultrasonic testingdevices can be used for this purpose.

NOTE : Complete process of wheel cleaning may include paint stripping which can be done usingmedia plastic blasting equipment or solvent baths.

A. Standard equipment

(1) Tire bead breaker universal

(2) High pressure washing device and

(3) Ultrasonic bath or vertical agitation machine for wheel bearing cleaning

(4) Hydraulic press

(5) Hand tool set

(6) Torque wrench

(7) Wheel support

(8) Trolley crane

B. Specific toolsAccording to the relevant CMM.

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Oct 01/09


3. Brake shop″Dirty″ work on brake overhaul includes disassembly and cleaning of the brake. An intensive cleaningis necessary to avoid damages of the piston bearing, as the remaining dirt can create a leak when thepistons are repressed.″Clean″ procedures follow after the brakes has been visually inspected. Cleaning can be done usingultrasonic bath or vertical agitation and total turbulence machine.The brake pistons are returned to their original position. When it has been accomplished, test for leakare performed.

A. Standard equipment

(1) Bath solvent cleaning

(2) Trolley crane

(3) Hydraulic test bench (315 bars)

(4) Dummy body for functioning test

(5) Tester brake unit spring tension

(6) Press for resetting the brake piston to the zero, position

(7) Hardness test machine.Carbon brake disk repairSubcontracted to specialized repair centre

B. Specific toolsAccording to the relevant CMM.

4. StorageAircraft tire storage conditions are determined by the tire manufacturers. There is no Airbusdocument dealing with this subject.Tires should be stored in a cool, dry environment and protected from direct sunlight. Particular careshould be taken to store tires away from fluorescent lights, electrical motor, battery chargers, electricwelding equipment, electric generator since they all create ozone which cause a rapid ageing ofrubber.The store room temperature should be comprised between 0 and 40˚C. Tires should be storevertically in a suitable rack, away from oil, grease, hydraulic fluid or other contaminants.

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Oct 01/09


VENDORS LIST

5-1 Vendors Information


General

1. VENDORS INFORMATIONThe vendors information is contained in the Vendors Information Manual (VIM) and in the VendorsInformation Manual/Ground Support Equipment (VIM/GSE).The Vendor Information Manual (VIM) gives contact names and addresses of AIRBUS equipmentvendors and their product support organizations. This manual covers all aircraft types.In addition the VIM/GSE gives contact names and addresses of Ground Support Equipment Vendorswhich fabricate market facilities or maintenance equipment to test or to overhaul the aircraft. Itcontains also the Vendors product support organizations. This manual covers all aircraft types.

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Oct 01/09

Documents

Maintenance Facility Planning