Airbus_AC_A340-500_600_Jan11

@AIRBUSA340-500/-600

AIRPLANE CHARACTERISTICSFOR AIRPORT PLANNING

AC

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

AIRBUS S.A.S.Customer Services

Technical Data Support and Services31707 Blagnac Cedex

FRANCE

Issue: Apr 01/01 Rev: Jan 01/11

@A340-500/-600AIRPLANE CHARACTERISTICS FOR AIRPORT PLANNING

HIGHLIGHTS

Revision No. 9 - Jan 01/11

LOCATIONS CHGCODE

DESCRIPTIONS OF CHANGE

CHAPTER 2

Section 2-1

Subject 2-1-1

General Airplane Characteristics Data R PART EFFECTIVITYADDED/REVISED/DELETED

Section 2-6 R

Subject 02-06-02 D

Subject 02-06-03 D

CHAPTER 4

Section 4-2

Subject 4-2-0

Turning Radii R PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Turning Radii - Turning Radii R ILLUSTRATION REVISEDILLUSTRATION REVISED

FIGURE Turning Radii - Turning Radii R ILLUSTRATION REVISEDILLUSTRATION REVISED

FIGURE Turning Radii - Steady StateTurning Radii

N NEW ILLUSTRATION ADDEDILLUSTRATION ADDED

FIGURE Turning Radii - Steady StateTurning Radii


Section 4-5

Subject 4-5-1

135˚ Turn - Runway to Taxiway R

FIGURE 135˚ Turn - Runway to Taxiway- Judgemental Oversteering Method

R ILLUSTRATION REVISED

FIGURE 135˚ Turn - Runway to Taxiway- Cockpit Over Centerline Method


HIGHLIGHTSPage 1

Jan 01/11


LOCATIONS CHGCODE


FIGURE 135˚ Turn - Runway to Taxiway- Judgemental Oversteering Method


FIGURE 135˚ Turn - Runway to Taxiway- Cockpit Over Centerline Method


Subject 4-5-2

90˚ Turn - Runway to Taxiway R

FIGURE 90˚ Turn - Runway to Taxiway -Judgement Oversteering Method


FIGURE 90˚ Turn - Runway to Taxiway -Cockpit Over Centerline Method


FIGURE 90˚ Turn - Runway to Taxiway -Judgement Oversteering Method

R

FIGURE 90˚ Turn - Runway to Taxiway -Cockpit Over Centerline Method


Subject 4-5-3

FIGURE 180˚ Turn on a Runway - 75˚Nose Wheel Steering

R

FIGURE 180˚ Turn on a Runway - 70˚Nose Wheel Steering

R

Subject 4-5-4

135˚ Turn - Taxiway to Taxiway R

FIGURE 135˚ Turn - Taxiway to Taxiway- Judgement Oversteering Method


FIGURE 135˚ Turn - Taxiway to Taxiway- Cockpit Over Centerline Method


FIGURE 135˚ Turn - Taxiway to Taxiway- Judgement Oversteering Method




Subject 4-5-5

90˚ Turn - Taxiway to Taxiway R

FIGURE 90˚ Turn - Taxiway to Taxiway- Judgemental Oversteering Method


HIGHLIGHTSPage 2

Jan 01/11


LOCATIONS CHGCODE




FIGURE 90˚ Turn - Taxiway to Taxiway- Judgemental Oversteering Method




Section 4-6

Subject 4-6-0

Runway Holding Bay (Apron) R

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

R ILLUSTRATION REVISEDILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

CHAPTER 5

Section 5-4

Subject 5-4-2

FIGURE Ground Service Connections -Grounding Points


Subject 5-4-6

Fuel System R

Section 5-8

Subject 5-8-0

Ground Towing Requirements R UPDATE OF THE TOWBAR CATEGORY

CHAPTER 7

Section 7-1

Subject 7-1-0

General Information R

Section 7-2

Subject 7-2-0

Landing Gear Footprint R PART EFFECTIVITYADDED/REVISED/DELETED

HIGHLIGHTSPage 3

Jan 01/11


LOCATIONS CHGCODE


FIGURE Landing Gear Footprint - MTOW365 000 kg


















Section 7-3

Subject 7-3-0

Maximum Pavement Loads R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Maximum Pavement Loads -Maximum Pavement Loads

R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED


R ILLUSTRATION REVISED ANDCOMPLETEDILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

HIGHLIGHTSPage 4

Jan 01/11


LOCATIONS CHGCODE








Section 7-4

Subject 7-4-0

Landing Gear Loading on Pavement R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 7-4-1

Landing Gear Loading on Pavement R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Landing Gear Loading onPavement - MTOW 365 000 kg










HIGHLIGHTSPage 5

Jan 01/11


LOCATIONS CHGCODE









R NEW ILLUSTRATION ADDEDILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED


N ILLUSTRATION REVISEDILLUSTRATION ADDED

Subject 7-4-2

Wing Gear and Center Landing GearLoading on Pavement

R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 7-4-3

Wing Gear and Center Landing GearLoading on Pavement


FIGURE Wing Gear and Center LandingGear Loading on Pavement - MTOW 365000 kg








HIGHLIGHTSPage 6

Jan 01/11


LOCATIONS CHGCODE












Section 7-5

Subject 7-5-0

Flexible Pavement Requirements - U.S.Army Corps of Engineers Design Method


Subject 7-5-1

Flexible Pavement Requirements - U.S.Army Corps of Engineers Design Method


FIGURE Flexible Pavement Requirements- MTOW 365 000 kg






HIGHLIGHTSPage 7

Jan 01/11


LOCATIONS CHGCODE














Section 7-6

Subject 7-6-0

Flexible Pavement Requirements - LCNConversion


Subject 7-6-1

Flexible Pavement Requirements - LCNConversion




HIGHLIGHTSPage 8

Jan 01/11


LOCATIONS CHGCODE


















Section 7-7

Subject 7-7-0

Rigid Pavement Requirements - PortlandCement Association Design Method


Subject 7-7-1

HIGHLIGHTSPage 9

Jan 01/11


LOCATIONS CHGCODE


Rigid Pavement Requirements - PortlandCement Association Design Method


FIGURE Rigid Pavement Requirements -MTOW 365 000 kg


















Section 7-8

Subject 7-8-0

Rigid Pavement Requirements - LCNConversion


Subject 7-8-2

Rigid Pavement Requirements - LCNConversion


HIGHLIGHTSPage 10

Jan 01/11


LOCATIONS CHGCODE


FIGURE Rigid Pavement RequirementsLCN - MTOW 365 000 kg

R ILLUSTRATION COMPLETEDILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

















Subject 7-8-3

Radius of Relative Stiffness (Other valuesof ”E” and ”L”)

R

Section 7-9

Subject 7-9-0

HIGHLIGHTSPage 11

Jan 01/11


LOCATIONS CHGCODE


ACN/PCN Reporting System - Flexibleand Rigid Pavements


Subject 7-9-1

Aircraft Classification Number - FlexiblePavement


FIGURE Aircraft Classification Number --Flexible Pavement - MTOW 365 000 kg


















HIGHLIGHTSPage 12

Jan 01/11


LOCATIONS CHGCODE


Subject 7-9-2

Aircraft Classification Number - RigidPavement


FIGURE Aircraft Classification Number --Rigid Pavement - MTOW 365 000 kg


















HIGHLIGHTSPage 13

Jan 01/11


LIST OF EFFECTIVE CONTENT

Revision No. 9 - Jan 01/11

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 1

Subject 1-1-0

Purpose May 01/07

Subject 1-2-0

Introduction May 01/07

CHAPTER 2

Subject 2-1-0

General Airplane Characteristics May 01/07

Subject 2-1-1

General Airplane Characteristics Data R Jan 01/11

Subject 2-2-0

General Airplane Dimensions May 01/07

FIGURE General Airplane Dimensions - General Airplane Dimensions May 01/07

FIGURE General Airplane Dimensions - General Airplane Dimensions May 01/07

Subject 2-3-0

Ground Clearances May 01/07

FIGURE Ground Clearances - Ground Clearances May 01/07

FIGURE Ground Clearances - Ground Clearances May 01/07

Subject 2-4-0

Interior Arrangements May 01/07

Subject 2-4-1

Typical Configuration May 01/07

FIGURE Typical Configuration - Typical Configuration May 01/07

FIGURE Typical Configuration - Typical Configuration May 01/07

Subject 2-5-0

Passenger Compartment Cross-section May 01/07

L.E.C.Page 1

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Passenger Compartment Cross-section - PassengerCompartment Cross-section

May 01/07


May 01/07


May 01/07

Subject 2-6-0

Cargo Compartment May 01/07

Subject 2-6-1

Lower Deck Cargo Compartments May 01/07

FIGURE Lower Deck Cargo Compartments - Lower Deck CargoCompartments

May 01/07

FIGURE Loading Combinations - Loading Combinations May 01/07

Subject 2-7-0

Doors Clearances May 01/07

Subject 2-7-1

Forward Passenger / Crew Door May 01/07

FIGURE Forward Passenger / Crew Doors - Forward Passenger /Crew Doors

May 01/07

Subject 2-7-2

Mid Passenger / Crew Door May 01/07

FIGURE Mid Passenger / Crew Door - Mid Passenger / Crew Door May 01/07

FIGURE Mid Passenger / Crew Door - Mid Passenger / Crew Door May 01/07

Subject 2-7-3

Emergency Exits May 01/07

FIGURE Emergency Exits - Emergency Exits May 01/07

FIGURE Emergency Exits - Emergency Exits May 01/07

Subject 2-7-4

Aft Passenger / Crew Doors May 01/07

FIGURE Aft Passenger / Crew Doors - Aft Passenger / Crew Doors May 01/07

Subject 2-7-5

L.E.C.Page 2

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE

Forward Cargo Compartment Doors May 01/07

FIGURE Forward Cargo Compartment Doors - Forward CargoCompartment Doors

May 01/07

Subject 2-7-6

Aft Cargo Compartment Doors May 01/07

FIGURE Aft Cargo Compartment Doors - Aft Cargo CompartmentDoors

May 01/07

Subject 2-7-7

Bulk Cargo Compartment Doors May 01/07

FIGURE Bulk Cargo Compartment Doors - Bulk Cargo CompartmentDoors

May 01/07

Subject 2-7-8

Main Landing Gear Doors May 01/07

FIGURE Main and Center Landing Gear Doors - Main and CenterLanding Gear Doors

May 01/07

Subject 2-7-9

Radome May 01/07

FIGURE Radome - Radome May 01/07

Subject 2-7-10

APU and Nose Landing Gear Doors May 01/07

FIGURE APU and Nose Landing Gear Doors - APU and Nose LandingGear Doors

May 01/07

FIGURE APU and Nose Landing Gear Doors - APU and Nose LandingGear Doors

May 01/07

CHAPTER 3

Subject 3-1-0

General Information May 01/07

Subject 3-2-0

Payload / Range May 01/07

Subject 3-2-1

ISA Conditions May 01/07

L.E.C.Page 3

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE PAYLOAD / RANGE - RB 211 TRENT 556 engine May 01/07

FIGURE PAYLOAD / RANGE - RB 211 TRENT 553 engine May 01/07

Subject 3-3-0

FAR / JAR Takeoff Weight Limitation May 01/07

Subject 3-3-1

FAR / JAR Takeoff Weight Limitation May 01/07

FIGURE FAR / JAR Takeoff Weight Limitation - ISA Conditions --RB 211 TRENT 556 engine

May 01/07

FIGURE FAR / JAR Takeoff Weight Limitation - ISA Conditions --RB 211 TRENT 553 engine

May 01/07

Subject 3-3-2

ISA +15˚C (ISA +27˚F) Conditions May 01/07

FIGURE FAR / JAR Takeoff Weight Limitation - ISA +15˚C (ISA+27˚F) Conditions -- RB 211 TRENT 556 engine

May 01/07

FIGURE FAR / JAR Takeoff Weight Limitation - ISA +15˚C (ISA+27˚F) Conditions -- RB 211 TRENT 553 engine

May 01/07

Subject 3-4-0

Landing Field Length May 01/07

Subject 3-4-1

ISA Conditions All series engine May 01/07

FIGURE FAR / JAR Landing Field Length - ISA Conditions -- RB 211TRENT 556 engine

May 01/07

FIGURE FAR / JAR Landing Field Length - ISA Conditions -- RB 211TRENT 553 engine

May 01/07

Subject 3-5-0

Final Approach Speed May 01/07

Subject 3-5-1

Final Approach Speed May 01/07

FIGURE Final Approach Speed - RB 211 TRENT 556 engine May 01/07

FIGURE Final Approach Speed - RB 211 TRENT 553 engine May 01/07

L.E.C.Page 4

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 4

Subject 4-1-0

General Information May 01/07

Subject 4-2-0

Turning Radii R Jan 01/11

FIGURE Turning Radii - Turning Radii R Jan 01/11

FIGURE Turning Radii - Turning Radii R Jan 01/11

FIGURE Turning Radii - Steady State Turning Radii N Jan 01/11

FIGURE Turning Radii - Steady State Turning Radii N Jan 01/11

Subject 4-3-0

Minimum Turning Radii May 01/07

FIGURE Minimum Turning Radii - Minimum Turning Radii May 01/07

FIGURE Minimum Turning Radii - Minimum Turning Radii May 01/07

Subject 4-4-0

Visibility from Cockpit in Static Position May 01/07

FIGURE Visibility from Cockpit in Static Position - Visibility fromCockpit in Static Position

May 01/07

Subject 4-5-0

Runway and Taxiway Turn Paths May 01/07

Subject 4-5-1

135˚ Turn - Runway to Taxiway R Jan 01/11

FIGURE 135˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

R Jan 01/11

FIGURE 135˚ Turn - Runway to Taxiway - Cockpit Over CenterlineMethod

N Jan 01/11

FIGURE 135˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

R Jan 01/11


N Jan 01/11

Subject 4-5-2

90˚ Turn - Runway to Taxiway R Jan 01/11

L.E.C.Page 5

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 90˚ Turn - Runway to Taxiway - Judgement OversteeringMethod

R Jan 01/11


N Jan 01/11

FIGURE 90˚ Turn - Runway to Taxiway - Judgement OversteeringMethod

R Jan 01/11


N Jan 01/11

Subject 4-5-3

180˚ Turn on a Runway May 01/07

FIGURE 180˚ Turn on a Runway - 75˚ Nose Wheel Steering R Jan 01/11

FIGURE 180˚ Turn on a Runway - 70˚ Nose Wheel Steering R Jan 01/11

Subject 4-5-4

135˚ Turn - Taxiway to Taxiway R Jan 01/11

FIGURE 135˚ Turn - Taxiway to Taxiway - Judgement OversteeringMethod

R Jan 01/11

FIGURE 135˚ Turn - Taxiway to Taxiway - Cockpit Over CenterlineMethod

N Jan 01/11

FIGURE 135˚ Turn - Taxiway to Taxiway - Judgement OversteeringMethod

R Jan 01/11


N Jan 01/11

Subject 4-5-5

90˚ Turn - Taxiway to Taxiway R Jan 01/11

FIGURE 90˚ Turn - Taxiway to Taxiway - Judgemental OversteeringMethod

R Jan 01/11


N Jan 01/11

FIGURE 90˚ Turn - Taxiway to Taxiway - Judgemental OversteeringMethod

R Jan 01/11


N Jan 01/11

Subject 4-6-0

Runway Holding Bay (Apron) R Jan 01/11

L.E.C.Page 6

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE

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

R Jan 01/11

Subject 4-7-0

Airplane Parking May 01/07

FIGURE Airplane Parking - Steering Geometry May 01/07


FIGURE Airplane Parking - Minimum Parking Space Requirements May 01/07



FIGURE Airplane Parking - Minimum Parking Space Requirements May 01/07

CHAPTER 5

Subject 5-0-0

TERMINAL SERVICING Jan 01/10

Subject 5-1-0

Airplane Servicing Arrangements Jan 01/10

Subject 5-1-1

Symbols Used on Servicing Diagrams Jan 01/10

Subject 5-1-2

Loading (Open Apron) Jan 01/10

FIGURE Airplane Servicing Arrangements - Typical Ramp Layout(Open Apron)

Jan 01/10

FIGURE Airplane Servicing Arrangements - Typical Ramp Layout(Open Apron)

Jan 01/10

Subject 5-1-3

Loading (Passenger Bridge) Jan 01/10

FIGURE Airplane Servicing Arrangements - Typical Ramp Layout(gate area)

Jan 01/10

FIGURE Airplane Servicing Arrangements - Typical Ramp Layout(gate area)

Jan 01/10

Subject 5-2-0

L.E.C.Page 7

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE

Terminal Operations - Full Servicing Turn Round Charts Jan 01/10

Subject 5-2-1

Full Servicing Turn Round Charts Jan 01/10

FIGURE Turn around charts - Turn Round Time 63 min. Jan 01/10

FIGURE Turn around charts - Turn Round Time 74 min. Jan 01/10

Subject 5-3-0

Terminal Operations - Transit Turn Round Charts Jan 01/10

Subject 5-3-1

Transit Turn Round Charts Jan 01/10

FIGURE Transit Turn Round Charts - Turn Round Time 40 min. Jan 01/10

FIGURE Transit Turn Round Charts - Turn Round Time 46 min. Jan 01/10

Subject 5-4-0

Ground Service Connections May 01/07

Subject 5-4-1

Ground Service Connections Layout May 01/07

FIGURE Ground Service Connections - Ground Service ConnectionsLayout

May 01/07

FIGURE Ground Service Connections - Ground Service ConnectionsLayout

May 01/07

Subject 5-4-2

Grounding Points May 01/07

FIGURE Ground Service Connections - Grounding Points R Jan 01/11

Subject 5-4-3

Hydraulic System May 01/07

Subject 5-4-4

Electrical System May 01/07

Subject 5-4-5

Oxygen System May 01/07

Subject 5-4-6

Fuel System R Jan 01/11

L.E.C.Page 8

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE

Subject 5-4-7

Pneumatic System May 01/07

Subject 5-4-8

Potable Water System May 01/07

Subject 5-4-9

Oil System May 01/07

FIGURE Ground Service Connections - Engine Oil Tank - RR TRENT500 series engine

May 01/07

FIGURE Ground Service Connections - IDG Oil Tank - RR TRENT500 series engine

May 01/07

FIGURE Ground Service Connections - Starter Oil Tank - RR TRENT500 series engine

May 01/07

APU Oil System Jan 01/10

FIGURE Ground Service Connections - APU Oil Tank Jan 01/10

Subject 5-4-10

Vacuum Toilet System May 01/07

Subject 5-5-0

Engine Starting Pneumatic Requirements May 01/07

Subject 5-5-1

Low Temperature -40˚C (-40˚F) May 01/07

FIGURE Engine Starting Pneumatic Requirements - Temperature-40˚C (-40˚F) -- RB 211 TRENT 500 series engine

May 01/07

Subject 5-5-2

Ambient Temperature +15˚C (+59˚F) May 01/07

FIGURE Engine Starting Pneumatic Requirements - Temperature+15˚C (+59˚F) -- RB 211 TRENT 500 series engine

May 01/07

Subject 5-5-3

High Temperature +50˚C (122˚F) May 01/07

FIGURE Engine Starting Pneumatic Requirements - Temperature+50˚C (+122˚F) -- RB 211 TRENT 500 series engine

May 01/07

Subject 5-6-0

L.E.C.Page 9

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE

Ground Pneumatic Power Requirements May 01/07

Subject 5-6-1

Heating May 01/07

FIGURE Ground Pneumatic Power Requirements - Heating May 01/07

Subject 5-6-2

Cooling May 01/07

FIGURE Ground Pneumatic Power Requirements - Cooling May 01/07

Subject 5-7-0

Preconditioned Airflow Requirements May 01/07

FIGURE Preconditioned Airflow Requirements - PreconditionedAirflow Requirements

May 01/07

Subject 5-8-0

Ground Towing Requirements R Jan 01/11

FIGURE Ground Towing Requirements - Ground TowingRequirements

Jan 01/10

FIGURE Ground Towing Requirements - Typical tow barconfiguration 1

Jan 01/10

FIGURE Ground Towing Requirements - Typical tow barconfiguration 2

Jan 01/10

FIGURE Ground Towing Requirements - Maximum Extension of theNLG Shock Absorber

Jan 01/10

CHAPTER 6

Subject 6-1-0

Engine Exhaust Velocities and Temperatures May 01/07

Subject 6-1-1

Engine Exhaust Velocities Contours - Ground Idle Power May 01/07

FIGURE Engine Exhaust Velocities - Ground Idle Power - RR TRENT500 series engine

May 01/07

Subject 6-1-2

Engine Exhaust Temperatures Contours - Ground Idle Power May 01/07

L.E.C.Page 10

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Engine Exhaust Temperatures - Ground Idle Power - RRTRENT 500 series engine

May 01/07

Subject 6-1-3

Engine Exhaust Velocities Contours - Breakaway Power May 01/07

FIGURE Engine Exhaust Velocities - Breakaway Power - RR TRENT500 series engine

May 01/07

Subject 6-1-4

Engine Exhaust Temperatures Contours - Breakaway Power May 01/07

FIGURE Engine Exhaust Temperatures - Breakaway Power - RRTRENT 500 series engine

May 01/07

Subject 6-1-5

Engine Exhaust Velocities Contours - Takeoff Power May 01/07

FIGURE Engine Exhaust Velocities - Takeoff Power - RR TRENT 500series engine

May 01/07

Subject 6-1-6

Engine Exhaust Temperatures Contours - Takeoff Power May 01/07

FIGURE Engine Exhaust Temperatures - Takeoff Power - RR TRENT500 series engine

May 01/07

Subject 6-2-0

Airport and Community Noise Data May 01/07

Subject 6-2-1

Noise Data May 01/07

FIGURE Airport and Community Noise - RR TRENT 500 seriesengine

May 01/07

Subject 6-3-0

Danger Areas of Engines May 01/07

Subject 6-3-1

Ground Idle Power May 01/07

FIGURE Danger Areas of Engines - RR TRENT 500 series engine May 01/07

Subject 6-3-2

Breakaway Power May 01/07

L.E.C.Page 11

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE


Subject 6-3-3

Takeoff Power May 01/07


Subject 6-4-0

APU Exhaust Velocities and Temperatures May 01/07

Subject 6-4-1

APU - GARRETT May 01/07

FIGURE Exhaust Velocities and Temperatures - GARRETT GTCP331-600 (A)

May 01/07

CHAPTER 7

Subject 7-1-0

General Information R Jan 01/11

Subject 7-2-0

Landing Gear Footprint R Jan 01/11

FIGURE Landing Gear Footprint - MTOW 365 000 kg R Jan 01/11

FIGURE Landing Gear Footprint - MTOW 368 000 kg R Jan 01/11

FIGURE Landing Gear Footprint - MTOW 365 000 kg N Jan 01/11







Subject 7-3-0

Maximum Pavement Loads R Jan 01/11

FIGURE Maximum Pavement Loads - Maximum Pavement Loads R Jan 01/11



L.E.C.Page 12

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE


FIGURE Maximum Pavement Loads - Maximum Pavement Loads N Jan 01/11

Subject 7-4-0

Landing Gear Loading on Pavement R Jan 01/11

Subject 7-4-1

Landing Gear Loading on Pavement R Jan 01/11

FIGURE Landing Gear Loading on Pavement - MTOW 365 000 kg R Jan 01/11


FIGURE Landing Gear Loading on Pavement - MTOW 365 000 kg N Jan 01/11








Subject 7-4-2

Wing Gear and Center Landing Gear Loading on Pavement R Jan 01/11

Subject 7-4-3

Wing Gear and Center Landing Gear Loading on Pavement R Jan 01/11

FIGURE Wing Gear and Center Landing Gear Loading on Pavement -MTOW 365 000 kg

R Jan 01/11


R Jan 01/11


N Jan 01/11


R Jan 01/11


R Jan 01/11

L.E.C.Page 13

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE


R Jan 01/11


N Jan 01/11


N Jan 01/11


R Jan 01/11

Subject 7-5-0

Flexible Pavement Requirements - U.S. Army Corps of EngineersDesign Method

R Jan 01/11

Subject 7-5-1

Flexible Pavement Requirements - U.S. Army Corps of EngineersDesign Method

R Jan 01/11

FIGURE Flexible Pavement Requirements - MTOW 365 000 kg R Jan 01/11


FIGURE Flexible Pavement Requirements - MTOW 365 000 kg N Jan 01/11







Subject 7-6-0

Flexible Pavement Requirements - LCN Conversion R Jan 01/11

Subject 7-6-1

Flexible Pavement Requirements - LCN Conversion R Jan 01/11





L.E.C.Page 14

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE






Subject 7-7-0

Rigid Pavement Requirements - Portland Cement Association DesignMethod

R Jan 01/11

Subject 7-7-1

Rigid Pavement Requirements - Portland Cement Association DesignMethod

R Jan 01/11

FIGURE Rigid Pavement Requirements - MTOW 365 000 kg R Jan 01/11


FIGURE Rigid Pavement Requirements - MTOW 365 000 kg N Jan 01/11







Subject 7-8-0

Rigid Pavement Requirements - LCN Conversion R Jan 01/11

Subject 7-8-1

Radius of Relative Stiffness May 01/07

FIGURE Radius of relative stiffness - (Reference : Portland CementAssociation)

May 01/07

Subject 7-8-2

Rigid Pavement Requirements - LCN Conversion R Jan 01/11

FIGURE Rigid Pavement Requirements LCN - MTOW 365 000 kg R Jan 01/11


L.E.C.Page 15

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Rigid Pavement Requirements LCN - MTOW 365 000 kg N Jan 01/11







Subject 7-8-3

Radius of Relative Stiffness (Other values of ”E” and ”L”) R Jan 01/11

Subject 7-8-4

Radius of Relative Stiffness May 01/07

FIGURE Radius of Relative Stiffness - (Effect of ”E” and ”µ” on ”L”values)

May 01/07

Subject 7-9-0

ACN/PCN Reporting System - Flexible and Rigid Pavements R Jan 01/11

Subject 7-9-1

Aircraft Classification Number - Flexible Pavement R Jan 01/11

FIGURE Aircraft Classification Number -- Flexible Pavement - MTOW365 000 kg

R Jan 01/11


R Jan 01/11


N Jan 01/11


R Jan 01/11


R Jan 01/11


R Jan 01/11


N Jan 01/11

L.E.C.Page 16

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE


N Jan 01/11


R Jan 01/11

Subject 7-9-2

Aircraft Classification Number - Rigid Pavement R Jan 01/11

FIGURE Aircraft Classification Number -- Rigid Pavement - MTOW365 000 kg

R Jan 01/11


R Jan 01/11


N Jan 01/11


R Jan 01/11


R Jan 01/11


R Jan 01/11


N Jan 01/11


N Jan 01/11


R Jan 01/11

CHAPTER 8

Subject 8-1-0

Possible Future Derivative Airplane May 01/07

CHAPTER 9

Subject 9-1-0

Scaled Drawing 1 in. = 50 ft. May 01/07

FIGURE Scaled Drawing - 1 in. = 50 ft. May 01/07


L.E.C.Page 17

Jan 01/11


CONTENT CHGCODE

LAST REVISIONDATE



Subject 9-2-0

Scaled Drawing 1 cm. = 500 cm. May 01/07

FIGURE Scaled Drawing - 1 cm. = 500 cm. May 01/07




L.E.C.Page 18

Jan 01/11


TABLE OF CONTENTS

1 SCOPE

1-1-0 Purpose

1-2-0 Introduction

2 AIRPLANE DESCRIPTION

2-1-0 General Airplane Characteristics

2-1-1 General Airplane Characteristics Data

2-2-0 General Airplane Dimensions

2-3-0 Ground Clearances

2-4-0 Interior Arrangements

2-4-1 Typical Configuration

2-5-0 Passenger Compartment Cross Section

2-6-0 Cargo Compartments

2-6-1 Lower Deck Cargo Compartments (Loading combinations)

2-7-0 Door Clearances

2-7-1 Forward Passenger / Crew Doors

2-7-2 Mid Passenger / Crew Doors

2-7-3 Emergency Exits

2-7-4 Aft Passenger / Crew Doors

2-7-5 Forward Cargo Compartment Doors

2-7-6 Aft Cargo Compartment Doors

2-7-7 Bulk Cargo Compartment Doors

2-7-8 Main and Center Landing Gear Doors

2-7-9 Radome

2-7-10 APU and Nose Landing Gear Doors

3 AIRPLANE PERFORMANCE

3-1-0 General Information

3-2-0 Payload / Range

3-2-1 ISA Conditions

3-3-0 FAR / JAR Takeoff Weight Limitation


3-3-2 ISA +15˚C (ISA +27˚F) Conditions

3-4-0 FAR / JAR Landing Field Length

3-4-1 ISA Conditions All series engines

T.O.C.Page 1

Jan 01/11


3-5-0 Final Approach Speed


4 GROUND MANEUVERING


4-2-0 Turning Radii

4-3-0 Minimum Turning Radii

4-4-0 Visibility from Cockpit in Static Position

4-5-0 Runway and Taxiway Turn Paths

4-5-1 135˚ Turn - Runway to Taxiway


4-5-3 180˚ Turn on a Runway

4-5-4 135˚ Turn - Taxiway to Taxiway


4-6-0 Runway Holding Bay (Apron)

4-7-0 Airplane Parking

5 TERMINAL SERVICING

5-0-0 TERMINAL SERVICING

5-1-0 Airplane Servicing Arrangements

5-1-1 Symbols Used on Servicing Diagrams

5-1-2 Loading (Open Apron)

5-1-3 Loading (Passenger Bridge)

5-2-0 Terminal Operations - Full Servicing Turn Round Charts

5-2-1 Full Servicing Turn Round Charts

5-3-0 Terminal Operations - Transit Turn Round Charts

5-3-1 Transit Turn Round Charts

5-4-0 Ground Service Connections

5-4-1 Ground Service Connections Layout

5-4-2 Grounding Points

5-4-3 Hydraulic System

5-4-4 Electrical System

5-4-5 Oxygen System

5-4-6 Fuel System

5-4-7 Pneumatic System

5-4-8 Potable Water System

5-4-9 Oil System

5-4-10 Vacuum Toilet System

T.O.C.Page 2

Jan 01/11


5-5-0 Engine Starting Pneumatic Requirements

5-5-1 Low Temperatures

5-5-2 Ambient Temperatures

5-5-3 High Temperatures

5-6-0 Ground Pneumatic Power Requirements

5-6-1 Heating

5-6-2 Cooling

5-7-0 Preconditioned Airflow Requirements

5-8-0 Ground Towing Requirements

6 OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

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

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

6-1-3 Engine Exhaust Velocities Contours - Breakaway Power

6-1-4 Engine Exhaust Temperatures Contours - Breakaway Power

6-1-5 Engine Exhaust Velocities Contours - Takeoff Power

6-1-6 Engine Exhaust Temperatures Contours - Takeoff Power

6-2-0 Airport and Community Noise

6-2-1 Noise Data

6-3-0 Danger Areas of Engines

6-3-1 Ground Idle Power

6-3-2 Breakaway Power

6-3-3 Takeoff Power

6-4-0 APU Exhaust Velocities and Temperatures

6-4-1 APU

7 PAVEMENT DATA


7-2-0 Landing Gear Footprint

7-3-0 Maximum Pavement Loads

7-4-0 Landing Gear Loading on Pavement


7-4-2 Wing Gear and Center Landing Gear Loading on Pavement


7-5-0 Flexible Pavement Requirements - U.S. Army Corps of Engineers Design Method

7-5-1 Flexible Pavement Requirements - U.S. Army Corps of Engineers Design Method S-77-1

7-6-0 Flexible Pavement Requirements - LCN Conversion

T.O.C.Page 3

Jan 01/11



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


7-8-0 Rigid Pavement Requirements - LCN Conversion

7-8-1 Radius of Relative Stiffness


7-8-3 Radius of Relative Stiffness (Other values of E and L)


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

7-9-1 Aircraft Classification Number - Flexible Pavement

7-9-2 Aircraft Classification Number - Rigid Pavement

8 DERIVATIVE AIRPLANES

8-1-0 Possible Future Derivative Airplane

9 SCALED DRAWINGS

9-1-0 Scaled Drawing 1 in. = 500 ft.

9-2-0 Scaled Drawing 1 cm. = 500 cm.

T.O.C.Page 4

Jan 01/11


SCOPE

1-1-0 Purpose

**ON A/C A340-500 A340-600

Purpose

1. GeneralThe A340-500/-600 AIRPLANE CHARACTERISTICS (AC) manual is issued for the A340-500,A340-600 basic versions to provide the necessary data needed by airport operators and airlines for theplanning of airport facilities.

This document conforms to NAS 3601.

CORRESPONDENCECorrespondence concerning this publication should be directed to :

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

1-1-0Page 1

Jan 01/11


1-2-0 Introduction

**ON A/C A340-500 A340-600

Introduction

1. General

This manual comprises 9 chapters with a List of Effective Pages (LEP) and a Table Of Content(TOC) at the beginning of the manual.

Chapter 1 : SCOPE

Chapter 2 : AIRPLANE DESCRIPTION

This chapter contains general dimensional and other basic aircraft data.

It covers :- aircraft dimensions and ground clearances,- passenger and cargo compartments arrangement.

Chapter 3 : AIRPLANE PERFORMANCE

This chapter indicates the aircraft performance.

It covers :- payload range,- takeoff and landing runway requirements,- landing approach speed.

Chapter 4 : GROUND MANEUVERING

This chapter provides the aircraft turning capability and maneuvering characteristics on the ground.

It includes :- turning radii and visibility from the cockpit,- runway and taxiway turn path.

Chapter 5 : TERMINAL SERVICING

This chapter provides information for the arrangement of ground handling and servicing equipment.

It covers :- location and connections of ground servicing equipment,

1-2-0Page 1

Jan 01/11


- engines starting pneumatic and preconditioned airflow requirements.

Chapter 6 : OPERATING CONDITIONS

This chapter contains data and safety/environmental precautions related to engine and APUoperation on the ground.

It covers :- contour size and shape of the jet engine exhaust velocities and temperatures,- noise data.

Chapter 7 : PAVEMENT DATA

This chapter contains the pavement data helpful for airport planning.

It gives :- landing gear foot print and static load,- charts for flexible pavements with Load Classification Number (LCN),- charts for rigid pavements with LCN,- Aircraft Classification Number (ACN), Pavement Classification Number (PCN), reporting system

for flexible and rigid pavements.

Chapter 8 : DERIVATIVE AIRPLANES

This chapter gives relevant data of possible new version with the associated size change.

Chapter 9 : SCALED DRAWINGS

This chapter contains different airplane scaled drawings.

1-2-0Page 2

Jan 01/11


AIRPLANE DESCRIPTION

2-1-0 General Airplane Characteristics

**ON A/C A340-500 A340-600

General Airplane Characteristics

1. General Airplane CharacteristicsThe weight terms used throughout this manual are given below together with their respectivedefinitions.

Maximum Taxi Weight (MTW) :Maximum weight for ground maneuver as limited by aircraft strength and airworthiness requirements.(It includes weight of run-up and taxi fuel). It is also called Maximum Ramp Weight (MRW).

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

Maximum Takeoff Weight (MTOW) :Maximum weight for takeoff as limited by aircraft strength and airworthiness requirements. (This isthe maximum weight at start of the takeoff run).

Maximum Zero Fuel Weight (MZFW) :Maximum operational weight of the aircraft without 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 arethe flight and cabin crew and their baggage, unusable fuel, engine oil, emergency equipment, toiletchemical and fluids, galley structure, catering equipment, passenger seats and life vests, documents,etc.

Maximum Payload :Maximum Zero Fuel Weight (MZFW) minus Operational Empty Weight (OEW).

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

Maximum Cargo Volume :Maximum usable volume available for cargo.

Usable Fuel :Fuel available for aircraft propulsion.

2-1-0Page 1

Jan 01/11


2-1-1 General Airplane Characteristics Data

**ON A/C A340-500WV0xx A340-500WV1xx A340-600WV0xx A340-600WV1xx

General Airplane Characteristics Data

**ON A/C A340-600WV0xx

1. The following table provides characteristics of A340-600 Models, these data are specific to eachWeight Variant:

Aircraft CharacteristicsWV000 WV001

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

366 200 kg(807 333 lb)

369 200 kg(813 946 lb)

Maximum Takeoff Weight (MTOW)365 000 kg(804 687 lb)

368 000 kg(811 301 lb)

Maximum Landing Weight (MLW)256 000 kg(564 383 lb)

259 000 kg(570 997 lb)

Maximum Zero Fuel Weight (MZFW)242 000 kg(533 519 lb)

245 000 kg(540 132 lb)

Estimated Operational Empty Weight (OEW) With Trent 500 Engines : 176 364 kg (388 816 lb)

Estimated Maximum Payload RR Trent 50065 636 kg

(144 703 lb)68 636 kg

(151 316 lb)

195 010 l(51 516 US gal)Usable Fuel Capacity

(density = 0.785 kg/l) 153 082 kg(337 488 lb)



Aircraft CharacteristicsWV101 WV102 WV103

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

381 200 kg(840 402 lb)

369 200 kg(813 946 lb)

366 200 kg(807 333 lb)

Maximum Takeoff Weight (MTOW)380 000 kg(837 756 lb)

368 000 kg(811 301 lb)

365 000 kg(804 687 lb)

Maximum Landing Weight (MLW)265 000 kg(584 225 lb)

259 000 kg(570 997 lb)

265 000 kg(584 225 lb)

2-1-1Page 1

Jan 01/11



Maximum Zero Fuel Weight(MZFW)

251 000 kg(553 360 lb)

245 000 kg(540 132 lb)

251 000 kg(553 360 lb)

Estimated Operational EmptyWeight (OEW)

With Trent 500 Engines :176 364 kg (388 816 lb)

Estimated Maximum Payload RRTrent 500

74 636 kg(164 544 lb)

68 636 kg(151 316 lb)

74 636 kg(164 544 lb)

198 139 l (1) - 208 939 l (2)(52 343 US gal (1) - 55 196 US gal (2))Usable Fuel Capacity

(density = 0.785 kg/l) 155 539 kg (1) - 164 017 kg (2)(342 905 lb (1) - 361 595 lb (2))

(1) Without forward ACT(2) With forward ACT

**ON A/C A340-600WV0xx A340-600WV1xx

3. The following table provides characteristics of A340-600 Models, these data are common to eachWeight Variant:

Aircraft CharacteristicsStandard SeatingCapacity

384

Pressurized FuselageVolume (A/C nonequipped)

1 305 m3

(46 086 ft3)

Passenger CompartmentVolume

557 m3

(19 670 ft3)

Cockpit Volume12 m3

(424 ft3)

Usable Volume, FWD CC(Based on LD3)

107.3 m3

(3 792 ft3)

Usable Volume, AFT CC(Based on LD3)

80.5 m3

(2 844 ft3)

Usable Volume, Bulk CC19.7 m3

(695 ft3)

Water Volume, FWD CC143 m3

(5 050,6 ft3)

Water Volume, AFT CC102.3 m3

3 612,ft3)

2-1-1Page 2

Jan 01/11


Aircraft Characteristics

Water Volume, Bulk CC22.7 m3

(802 ft3)



Aircraft CharacteristicsWV000 WV001 WV002 WV003 WV004

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

369 200 kg(813 946 lb)

373 200 kg(822 765 lb)

373 200 kg(822 765 lb)

375 200 kg(827 174 lb)

375 200 kg(827 174 lb)

Maximum Takeoff Weight(MTOW)

368 000 kg(811 301 lb)

372 000 kg(820 119 lb)

372 000 kg(820 119 lb)

374 000 kg(824 529 lb)

374 000 kg(824 529 lb)

Maximum Landing Weight(MLW)

240 000 kg(529 109 lb)

243 000 kg(535 723 lb)

243 000 kg(535 723 lb)

231 000 kg(509 268 lb)

243 000 kg(535 723 lb)


225 000 kg(496 040 lb)

230 000 kg(507 063 lb)

229 000 kg(504 858 lb)

218 000 kg(480 608 lb)

218 000 kg(480 608 lb)



Estimated Maximum PayloadRR Trent 500

54 430 kg(119 998 lb)

59 430 kg(131 021 lb)

58 430 kg(128 816 lb)

47 430 kg(104 565 lb)

214 808 l(56 746 US

gal)

215 108 l * - 223 078 l **(56 826 US gal * - 58 931

US gal **)

214 066 l * - 222 036 l **(56 550 US gal * - 58 656

US gal **)Usable Fuel Capacity(density = 0.785 kg/l) 214 808 l

(56 746 USgal)

168 859 kg * - 175 116 kg**

(372 270 lb * - 386 065 lb**)

168 041 kg * - 174 298 kg**

(370 467 lb * - 384 261 lb** )

2-1-1Page 3

Jan 01/11





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

381 200 kg(840 402 lb)

373 200 kg(822 765 lb)

373 200 kg(822 765 lb)

Maximum Takeoff Weight(MTOW)

380 000 kg(837 756 lb)

372 000 kg(820 119 lb)

372 000 kg(820 119 lb)

Maximum Landing Weight(MLW)

246 000 kg(542 337 lb)

243 000 kg(535 723 lb)

246 000 kg(542 337 lb)


232 000 kg(511 472 lb)

230 000 kg(507 063 lb)

232 000 kg(511 472 lb)



Estimated Maximum PayloadRR Trent 500

61 430 kg(132 429 lb)

59 430 kg(131 020 lb)

61 430 kg(135 429 lb)

214 066 l * - 222 036 l**

(56 550 US gal * - 58656 US gal **)

216 622 l * - 223 210 l **(57 225 US gal * - 58 966 US gal **)

Usable Fuel Capacity(density = 0.785 kg/l) 168 041 kg * - 174 298

kg **(370 467 lb * - 384 261

lb **)

170 048 kg * - 175 219 kg **(374 892 lb * - 386 292 lb **)

* (Production model) RCT = 5 frames** (Optional model) RCT = 7 frames

**ON A/C A340-500WV0xx A340-500WV1xx

6. The following table provides characteristics of A340-500 Models, these data are common to eachWeight Variant:

Aircraft CharacteristicsStandard Seating Capacity 313

Pressurized Fuselage Volume(A/C non equipped)

1 120 m3

(39 552 ft3)

2-1-1Page 4

Jan 01/11


Aircraft Characteristics

Passenger CompartmentVolume

490 m3

(17 304 ft3)

Cockpit Volume12 m3

(424 ft3)

Usable Volume, FWD CC(Based on LD3)

80.5 m3

(2 844 ft3)

Usable Volume, AFT CC(Based on LD3)

53.6 m3

(1 896 ft3)

Usable Volume, Bulk CC19.7 m3

(695 ft3)

Water Volume, FWD CC107.1 m3

(3 782 ft3)


(2 610 ft3)


(802 ft3)

2-1-1Page 5

Jan 01/11


2-2-0 General Airplane Dimensions

**ON A/C A340-500 A340-600

General Airplane Dimensions

1. This section provides General Airplane Dimensions.

2-2-0Page 1

Jan 01/11


**ON A/C A340-600

74.765 m (245.29 ft)

75.362 m (247.25 ft)

10.684 m (35.05 ft)

50.367 m (165.24 ft)

73.461 m (241.01 ft)

22.592 m (74.12 ft)

SE

E C

HA

PT

ER

2−

3−0

0 20 40

27.323 m (89.64 ft)

SCALE FEET

28.587 m (93.79 ft)

0 6 12 SCALE METER

5.64 m (18.50 ft)

AND LOCATIONS,NOTE: FOR DOOR DIMENSIONS

SEE CHAPTER 2−7.

33.953 m (111.41 ft)

40.213 m (131.93 ft) CLG

F_AC_020200_1_0090101_01_00

6.576 m (21.57 ft)

39.459 m (129.46 ft) MLG

63.449 m (208.16 ft)

38.540 m (126.44 ft)

18.740 m (61.48 ft)

General Airplane DimensionsFIGURE 1

2-2-0Page 2

Jan 01/11

chandru

Sticky Note

airplane 3 view


**ON A/C A340-500

0

0 20

6 12

4028.658 m (94.00 ft)

66.028 m (216.63 ft)

67.929 m (228.86 ft)

63.449 m (208.16 ft)

22.592 m (74.12 ft)

5.64 m (18.50 ft)

18.740 m (61.48 ft)

10.684 m (35.05 ft)

F_AC_020200_1_0100101_01_00

45.067 m (147.86 ft)

22.023 m (72.25 ft)

23.287 m (76.40 ft)

67.332 m (220.90 ft)

6.576 m (21.57 ft)

38.540 m (126.44 ft)

SE

E C

HA

PT

ER

2−

3−0

SCALE METER

SCALE FEET

FOR DOOR DIMENSIONSNOTE:

34.913 m (114.54 ft) CLG

34.159 m (112.07 ft) MLG

F_AC_020200_1_0100101_01_00

AND LOCATIONS,SEE CHAPTER 2−7.

General Airplane DimensionsFIGURE 2

2-2-0Page 3

Jan 01/11


2-3-0 Ground Clearances

**ON A/C A340-500 A340-600

Ground Clearances

1. This section gives the height 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.

2-3-0Page 1

Jan 01/11


**ON A/C A340-600

X L C2Y K E3H E2

D C1B E1

AM

P N V U T S R O Q

ZJ

A/CCONFIGURATION

FR 37.9FR 74

FR 23FR 37.9FR 56.4

FR 40.4

m ft4.782.887.998.475.002.172.352.66

1.855.313.505.69

6.158.607.761.750.713.844.314.364.777.253.595.90

15.679.4626.2227.7716.417.127.718.72

6.0717.4211.4918.68

20.1828.2125.455.752.32

12.6014.1614.3015.6523.7811.7919.35

m ft m ft m ft m ft4.532.657.798.354.801.942.152.51

1.675.163.375.58

6.008.517.611.580.523.684.154.194.617.153.475.65

14.888.69

25.5527.3815.756.367.058.24

5.4716.9411.0518.29

19.6927.9224.975.171.70

12.0613.6113.7515.1323.4711.3718.54

4.602.707.818.274.821.992.172.47

1.665.123.315.50

5.968.397.561.560.523.654.124.174.587.043.405.72

15.088.8625.6127.1215.816.537.118.09

5.4616.7910.8418.03

19.5527.5424.815.121.71

11.9713.53

23.1111.1418.77

3.255.42

5.938.267.531.580.563.654.134.174.566.923.335.87

4.732.827.878.194.882.112.232.44

1.705.09

15.539.2725.8326.8616.036.937.337.99

5.5716.6910.6617.77

19.4627.1024.705.181.8511.9713.54

14.9722.7110.9219.27

7.035.09

10.0210.027.034.384.384.38

3.787.035.147.25

7.889.989.463.622.665.656.146.186.548.665.198.20

23.0716.7132.8732.8723.0714.3714.3714.37

12.4023.0716.8623.78

25.8732.7431.0411.898.73

18.5420.1520.2921.4428.4117.0326.90

FR 99

17.93 58.84 17.84 58.54 17.73 58.17 17.60 57.74 19.32 63.39

15.0113.67 13.69

OWEMID CG

354.6tCG: 16%

MTWFWD CG

350tCG: 38%

F

4.64 15.23 4.46 4.45 14.61 4.48 14.70 6.54 21.4714.65

AIRCRAFTON JACKS *

* NOTE:F_AC_020300_1_0120101_01_00

THESE FIGURES WILL GIVE AN AIRCRAFT FUSELAGE DATUM (FD) AT 7200 MM.

ABC1C2DE1E2E3

H

YZ

JKLMNOPQRSTUVX

F

F_AC_020300_1_0120101_01_00

Ground ClearancesFIGURE 1

2-3-0Page 2

Jan 01/11


**ON A/C A340-500

X L C2 Y K E3 H E2D C1

B E1A

M

P N V U T S R O Q

ZJ

m ft m ft m ft m ft m ft4.762.887.958.524.962.162.312.29

1.845.273.535.7517.536.198.687.81

1.750.693.864.334.374.807.343.635.87

15.619.4426.0827.9516.287.107.587.51

6.0317.2811.5918.8657.5120.3128.4725.615.752.2512.6614.2014.3515.7424.0811.9219.25

4.522.657.748.394.751.932.102.12

1.655.103.395.6217.446.048.597.661.570.493.694.164.204.647.243.505.62

14.828.68

25.3927.5415.596.346.896.97

5.4116.7411.1318.4557.2019.8128.1725.125.161.6112.1113.6413.7915.2223.7611.4918.44

4.532.657.748.354.751.942.102.10

1.635.083.365.5817.386.018.537.621.560.483.674.134.184.617.183.465.63

14.858.70

25.3827.4015.586.36

6.89

5.3616.6611.0118.3157.0119.7027.9725.015.101.5812.0313.5713.7115.1323.5711.3518.48

3.295.4917.235.968.387.571.550.513.654.124.164.587.053.385.75

4.632.747.798.264.802.032.152.07

1.655.05

15.18

25.5427.0915.746.647.046.79

5.4216.5710.7918.0056.5319.5627.4824.835.101.6611.9613.5213.6615.0123.1211.0918.86

7.035.09

10.0210.027.034.384.38

3.787.035.147.25

18.827.889.969.463.622.665.656.146.186.548.665.198.20

23.0716.7132.8732.8723.0714.3714.37

12.4023.0716.8623.7861.7525.8732.6831.0411.898.73

18.5420.1520.2921.4428.4117.0326.90

8.98

4.05 13.306.88

OWEMID CG

349.2tCG: 22%

MTWFWD CG

MTWAFT CG

F

4.64 15.22 4.45 14.61 4.44 14.56 4.45 14.59 6.54 21.47

AIRCRAFTON JACKS *

* NOTE: THESE FIGURES WILL GIVE AN AIRCRAFT FUSELAGE DATUM (FD) AT 7200 MM.

A/CCONFIGURATION

FR 37.9FR 74

FR 23FR 37.9FR 53.6

FR 40.4

FR 99

ABC1C2DE1E2E3

H

YZ

JKLMNOPQRSTUVX

F

F_AC_020300_1_0130101_01_00

Ground ClearancesFIGURE 2

2-3-0Page 3

Jan 01/11


2-4-0 Interior Arrangements

**ON A/C A340-500 A340-600

Interior Arrangements

1. This section gives the standard interior arrangements configuration.

2-4-0Page 1

Jan 01/11


2-4-1 Typical Configuration

**ON A/C A340-500 A340-600

Typical Configuration

1. This section gives the typical configuration for A340-500 and A340-600.

2-4-1Page 1

Jan 01/11


**ON A/C A340-600

PA

SS

EN

GE

R S

EA

TS

(38

0 T

OT

AL)

12 F

IRS

T C

LAS

S

54 B

US

INE

SS

CLA

SS

314

TO

UR

IST

CLA

SS

ITE

M

DE

SIG

NA

TIO

N

AT

TE

ND

AN

T S

EA

T

GA

LLE

Y

LAV

AT

OR

Y

ST

OW

AG

E

CO

AT

ST

OW

AG

E

VC

C V

IDE

O

(12)

(3)

(10)

(11)

(3)

(1)

A C G L S

VC

C

A

A AA

G

A

G

A

A

A

A AA AG G

S

SGG

GC

GG

G

S

CCL

L LL

L L

LLL

L LV

CC

F_AC_020401_1_0060101_01_00

Typical ConfigurationFIGURE 1

2-4-1Page 2

Jan 01/11


**ON A/C A340-500

PA

SS

EN

GE

R S

EA

TS

(31

3 T

OT

AL)

12 F

IRS

T C

LAS

S

36 B

US

INE

SS

CLA

SS

ITE

M

DE

SIG

NA

TIO

N

AT

TE

ND

AN

TS

SE

AT

GA

LLE

Y

LAV

AT

OR

Y

ST

OW

AG

E

265

TO

UR

IST

CLA

SS

CO

AT

ST

OW

AG

E

VC

C V

IDE

O

(12)

(2)

(11)

(10)

(3)

(1)

A C G L S

VC

C

F_AC_020401_1_0070101_01_00

A AV

CC

A

A

AA A

GA A A

G

S

S

G G

GL L

L L

L L

G G

GG

C

LL L

GG

C

S

A AL

Typical ConfigurationFIGURE 2

2-4-1Page 3

Jan 01/11


2-5-0 Passenger Compartment Cross Section

**ON A/C A340-500 A340-600

Passenger Compartment Cross-section

1. This section gives the typical passenger compartment cross-section configuration of A340-500/-600models.

2-5-0Page 1

Jan 01/11


**ON A/C A340-500 A340-600

1006 mm(39.61 in)

450 mm(17.72 in)

2462 mm(96.93 in)

5287 mm(208.15 in)

1827

mm

(71.

92 in

)

1650

mm

(64.

96 in

)

1006 mm(39.61 in)

128.8 mm(5.07 in)

2402 mm(94.56 in)

2222 mm(87.48 in)

1371.6 mm(54.00 in)

533.4 mm(21.00 in)

1371.6 mm(54.00 in)

F_AC_020500_1_0030101_01_00

Passenger Compartment Cross-sectionFIGURE 1

2-5-0Page 2

Jan 01/11


**ON A/C A340-500 A340-600

1783 mm(70.20 in)

2401 mm(94.52 in)1006 mm

(39.61 in)450 mm

(17.72 in)

2462 mm(96.93 in)

5287 mm(208.15 in)

1827

mm

(71.

92 in

)

1650

mm

(64.

96 in

)

1006 mm(39.61 in)

128.8 mm(5.07 in)

1371.6 mm(54.00 in)

533.4 mm(21.00 in)

1371.6 mm(54.00 in)

F_AC_020500_1_0040101_01_00


2-5-0Page 3

Jan 01/11


**ON A/C A340-500 A340-600

482.6 mm(19.00 in)

1006 mm(39.61 in)

450 mm(17.72 in)

2462 mm(96.93 in)

5287 mm(208.15 in)

1783 mm(70.20 in)

2401 mm(94.52 in)

1827

mm

(71.

92 in

)

1650

mm

(64.

96 in

)

1054.1 mm(41.50 in)

503 mm(19.80 in)

503 mm(19.80 in)

135.2 mm(5.32 in)

(41.50 in)1054.1 mm

F_AC_020500_1_0050101_01_00


2-5-0Page 4

Jan 01/11


2-6-0 Cargo Compartments

**ON A/C A340-500 A340-600

Cargo Compartment

1. This section gives the cargo compartments location and dimensions.

2-6-0Page 1

Jan 01/11


2-6-1 Lower Deck Cargo Compartments (Loading combinations)

**ON A/C A340-500 A340-600

Lower Deck Cargo Compartments

**ON A/C A340-600

1. This table gives cargo compartments loading combinations.

Cargo Compartment Palletized volume - 600 Containerized volume - 600

Forward Door size (h × w) 3256 ft3 (92.200 m3) 3792 ft3 (107.377 m3)

66.89 in (1.699 m) x 106.34 in(2.701 m)

based on 96 in × 125 in palletsloaded to height of 64 in (1.626

m)

based on LD3 (IATA E NAS3610-2K2C) container volume

Aft Door size (h × w) 2442 ft3 (69.150 m3) 2844 ft3 (80.533 m3)

66.3 in (1.684 m) x 107.1 in(2.720 m)


m)


Bulk Door size (h × w)

37.4 in (0.950 m) x 37.4 in (0.950m)

695 ft3 (19.680 m3)

**ON A/C A340-500

2. This table gives cargo compartments loading combinations.

Cargo Compartment Palletized volume - 500 Containerized volume - 500

Forward Door size (h × w) 2442 ft3 (69.150 m3) 2844 ft3 (80.533 m3)

66.89 in (1.699 m) x 106.34 in(2.701 m)


m)


Aft Door size (h × w) 1628 ft3 (46.100 m3) 1896 ft3 (53.689 m3)

66.3 in (1.684 m) x 107.1 in(2.720 m)


m)


Bulk Door size (h × w)

37.4 in (0.950 m) x 37.4 in (0.950m)

695 ft3 (19.680 m3)

2-6-1Page 1

Jan 01/11


**ON A/C A340-500 A340-600

(125.0 in)

(163.4 in)

(37.4 in)

(222.0 in)

(106.3 in)

(159.1 in)

AFT CARGOCOMPARTMENT

BULK CARGOCOMPARTMENT

FWD CARGOCOMPTARTMENT

TYPICAL SECTIONSFR20 TO FR39.2

AND FR53.2 TO FR65TOP OF CARGO COMPT

CARGO COMPT FLOOR

(159.1 in)

(66.6 ft) (50.1 ft)−600:

−500:

3.18 m

4.15 m

5.640 m

2.72 m

(107.1 in)2.70 m

0.95 m

FWD : 1.75 m (68.9 in)AFT : 1.71 m (67.3 in)

4.04 m20.297 m 15.274 m

4.04 m10.370 m14.997 m(34.0 ft)(49.2 ft)

F_AC_020601_1_0070101_01_00

Lower Deck Cargo CompartmentsFIGURE 1

2-6-1Page 2

Jan 01/11


**ON A/C A340-500 A340-600

−HALF−SIZE CONTAINERS NAS 3610−2K2C AS PER IATA CONTOUR E

−HALF−SIZE CONTAINERS NAS 3610−2K2C AS PER IATA CONTOUR C

−FULL−SIZE CONTAINERS NAS 3610−2L2C AS PER IATA CONTOUR F

CARGO FLEXIBILITY−LOADING COMBINATIONS

AFT FWD AFTFWDTYPICAL LOADING COMBINATIONS−STANDARD AIRCRAFT

FWD CARGO COMPT

AFT CARGO COMPT

LIMITED TO MAX GROSS WEIGHT 3500 lb (1587kg) EACH OR 60.4 in X 61.5 in PALLETS NAS 3610−2K3P

LIMITED TO MAX GROSS WEIGHT 3500 lb (1587kg) EACH

OR 60.4 in X 61.5 in PALLETS NAS 3610−2K3P,2L4PLIMITED TO MAX GROSS WIGHT 3500 lb (3174kg) EACH

−96 in X 125 in PALLETS NAS 3610−2MIP,2P,3PLIMITED TO MAX GROSS WEIGHT 10200 lb (4626kg) EACH(WITH POTENTIAL FOR EXTENSION TO 11250 lb (5103 kg)

A340−500 A340−600

18 12 24 18

9 6 12 9

9 6 12 9

6 4 8 6

F_AC_020601_1_0080101_01_00

Loading CombinationsFIGURE 2

2-6-1Page 3

Jan 01/11


2-7-0 Door Clearances

**ON A/C A340-500 A340-600

Doors Clearances

1. This section gives doors clearances.

2-7-0Page 1

Jan 01/11


2-7-1 Forward Passenger / Crew Doors

**ON A/C A340-500 A340-600

Forward Passenger / Crew Door

1. This section gives forward passenger / crew doors clearances.

2-7-1Page 1

Jan 01/11


**ON A/C A340-500 A340-600

CRITICALCLEARANCELIMIT

SEECHAPTER

2−3

CL

CL

CL

1.07 m(3 ft 6 in)

2.43 m(7 ft 11 in)

0.64 m(2 ft 1 in)

5.85 m(19 ft 2 in)

3.30 m(10 ft 9 in)

0.75 m(2 ft 5 in)

3.00 m(9 ft 10 in)

1.93 m(6 ft 3 in)

0.045 m(1.77 in)

F_AC_020701_1_0040101_01_01

Forward Passenger / Crew DoorsFIGURE 1

2-7-1Page 2

Jan 01/11


2-7-2 Mid Passenger / Crew Doors

**ON A/C A340-500 A340-600

Mid Passenger / Crew Door

1. This section gives mid passenger / crew doors clearances.

2-7-2Page 1

Jan 01/11


**ON A/C A340-600

CL

3.41 m(11 ft 2 in)

1.93 m(6 ft 3 in)

0.64 m(2 ft 1 in)

A A

2.43 m

(7 ft 11 in)

1.07 m(3 ft 6 in)

3.40 m(11 ft 1 in)

4.85 m(15 ft 10 in)

0.75 m(2 ft 5 in)

A

A

CL

CL

0.045 m(1.77 in)

(FROM NOSE)23.91m

(78 ft 10 in)

4.85 m(15 ft 10 in)

3.40 m(11 ft 1 in)

SEECHAPTER

2−3

(FROM NOSE)47.46 m

(155 ft 8 in)

A

A

2.43 m

(7 ft 11 in)

1.07 m(3 ft 6 in)

0.75 m(2 ft 5 in)

F_AC_020702_1_0030101_01_02

(TOP OF FLOOR)

Mid Passenger / Crew DoorFIGURE 1

2-7-2Page 2

Jan 01/11


**ON A/C A340-500 A340-600

CL

3.41 m(11 ft 2 in)

1.93 m(6 ft 3 in)

(TOP OF FLOOR)0.64 m

(2 ft 1 in)

A A

0.045 m(1.77 in)

1.07 m(3 ft 6 in)

2.43 m(7 ft 11 in)

3.40 m(11 ft 1 in)

(FROM NOSE): 18.61 m (61 ft 7 in)

SEECHAPTER

2−3

3.40 m(11 ft 1 in)

A

A

0.75 m(2 ft 5 in)

CL

CL

F_AC_020702_1_0040101_01_02

Mid Passenger / Crew DoorFIGURE 2

2-7-2Page 3

Jan 01/11


2-7-3 Emergency Exits

**ON A/C A340-500 A340-600

Emergency Exits

1. This section gives emergency exits doors clearances.

2-7-3Page 1

Jan 01/11


**ON A/C A340-600

CL

CL

CL

A

A

A A

(FROM NOSE)

DOORLINING

DOOR

34.087 m(111 ft 10 in)

3.2 m(10 ft 6 in)

0.38 m(1 ft 2 in)

1.46 m(4 ft 9 in)

1.66 m(5 ft 5 in)

SEECHAPTER

2−3

LINING0.53 m

(1 ft 8 in)

0.5 m

(1 ft 7 in)

0.61 m(2 ft)

1.47 m

(4 ft 9 in)

0.1 m(3.93 in)

F_AC_020703_1_0030101_01_00

Emergency ExitsFIGURE 1

2-7-3Page 2

Jan 01/11


**ON A/C A340-500

SEECHAPTER

2−3

CL

CL

CL

(FROM NOSE)

0.52 m(1 ft 8 in)

0.61 m(2 ft)

37.669 m(123 ft 6 in)

3.24 m(10 ft 7 in)

1.66 m(5 ft 5 in)

0.42 m(1 ft 4 in)

DOOR

DOOR

A

A

A A

0.032 m(1.25 in)

1.46 m(4 ft 9 in)

F_AC_020703_1_0040101_01_00

Emergency ExitsFIGURE 2

2-7-3Page 3

Jan 01/11


2-7-4 Aft Passenger / Crew Doors

**ON A/C A340-500 A340-600

Aft Passenger / Crew Doors

1. This section gives Aft passenger / crew doors clearances.

2-7-4Page 1

Jan 01/11


**ON A/C A340-500 A340-600

CRITICALCLEARANCE

LIMIT

SEECHAPTER

2−3

CLCL

CL

(FROM NOSE)

2.43 m(8 ft)

1.07 m(3 ft 6 in)

0.75 m(2 ft 5 in)

A340−600: 61.576 m (200 ft 0.2 in)

A340−500: 54.143 m (177 ft 7 in)3.00 m

(9 ft 10 in)

1.99 m(6 ft 6 in)

0.64 m(2 ft 1 in)

A

A

CL

A A

0.045 m(1.8 in)

F_AC_020704_1_0030101_01_00

Aft Passenger / Crew DoorsFIGURE 1

2-7-4Page 2

Jan 01/11


2-7-5 Forward Cargo Compartment Doors

**ON A/C A340-500 A340-600

Forward Cargo Compartment Doors

1. This section gives forward cargo compartment doors clearances.

2-7-5Page 1

Jan 01/11


**ON A/C A340-500 A340-600

(FROM NOSE)

CL

CL

CL

SEECHAPTER

2−3

2.7 m(8 ft 10 in)

2.04 m(6 ft 8 in) 1.70 m

(5 ft 6 in)

5.27 m(17 ft 3 in)

9.530 m(31 ft 3 in)

CL

A

A

A AF_AC_020705_1_0050101_01_00

Forward Cargo Compartment DoorsFIGURE 1

2-7-5Page 2

Jan 01/11


2-7-6 Aft Cargo Compartment Doors

**ON A/C A340-500 A340-600

Aft Cargo Compartment Doors

1. This section gives Aft cargo compartment doors clearances.

2-7-6Page 1

Jan 01/11


**ON A/C A340-500 A340-600

CL

CL

CL

SEECHAPTER

2−3

CL

(FROM NOSE)A340−600: 54.98 m(180 ft 4 in)

A340−500: 47.546 m(155 ft 11 in)

1.68 m(5 ft 6 in)

5.19 m(17 ft)

1.92 m(6 ft 3 in)

2.72m(8 ft 11 in)

A

A

BULK CARGOCOMPARTMENT DOOR

A A

AFT PASSENGER/CREW DOOR

COMPARTMENT DOORAFT CARGO

F_AC_020706_1_0050101_01_00

Aft Cargo Compartment DoorsFIGURE 1

2-7-6Page 2

Jan 01/11


2-7-7 Bulk Cargo Compartment Doors

**ON A/C A340-500 A340-600

Bulk Cargo Compartment Doors

1. This section gives the bulk cargo compartment doors clearances.

2-7-7Page 1

Jan 01/11


**ON A/C A340-500 A340-600

A

A

CL

CL

CL

SEECHAPTER

2−3

CL

(FROM NOSE)A340−600: 57.962 m (190 ft 1 in)A340−500: 50.529 m (165 ft 9 in)

1.41 m(4 ft 7 in)

1.07 m(3 ft 6 in)

0.95 m(3 ft 1 in)

1.1 m(3 ft 7 in)

F_AC_020707_1_0040101_01_00

AFT PASSENGER/CREW DOOR (REF)

A A

BULK CARGOCOMPARTMENT DOOR

F_AC_020707_1_0040101_01_00

COMPARTMENT DOORAFT CARGO

Bulk Cargo Compartment DoorsFIGURE 1

2-7-7Page 2

Jan 01/11


2-7-8 Main and Center Landing Gear Doors

**ON A/C A340-500 A340-600

Main Landing Gear Doors

1. This section gives the main landing gear doors clearances.

2-7-8Page 1

Jan 01/11


**ON A/C A340-500 A340-600

F_AC_020708_1_0040101_01_00

A340−600: 36.713 m (120 ft 5 in)A340−500: 31.313 m (102 ft 8 in)

3.96 m(13 ft)

A

GROUND LINE

* DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT

2.58 m(8 ft 5 in)

MAX. 0.37 m (1 ft 2 in)MIN. 0.17 m (6 in)*

90°

3.157 m(10 ft 4 in)

0.045 m(1 in)

1.1 m(3 ft 7 in)

(3 ft 4 in)1.02 m

A/C

C L

81

2.30m(7 ft 6 in)

A

Main and Center Landing Gear DoorsFIGURE 1

2-7-8Page 2

Jan 01/11


2-7-9 Radome

**ON A/C A340-500 A340-600

Radome

1. This section gives the radome clearances.

2-7-9Page 1

Jan 01/11


**ON A/C A340-500 A340-600

67°

CL

STA 7662.5FR1

1.32

5 m

(4 ft

4 in

)1.

25 m

(4 ft

1 in

)

1.65 m(5 ft 4 in)

F_AC_020709_1_0010101_01_00

RadomeFIGURE 1

2-7-9Page 2

Jan 01/11


2-7-10 APU and Nose Landing Gear Doors

**ON A/C A340-500 A340-600

APU and Nose Landing Gear Doors

1. This section gives APU and Nose Landing Gear doors clearances.

2-7-10Page 1

Jan 01/11


**ON A/C A340-600

FUSELAGE DATUM LINE

**

FR94

FR98


MAX. 6.82 m (22 ft 4 in)

MIN. 6.50 m (21 ft 3 in)

MAX. 6.03 m (19 ft 9 in)

MIN. 5.71 m (18 ft 8 in)

MAX. 2.2 m (7 ft 2 in)

MIN. 1.96 m (6 ft 5 in)

MAX. 1.67 m (5 ft 5 in)

MIN. 1.43 m (4 ft 5 in)

**

F_AC_020710_1_0050101_01_00

APU and Nose Landing Gear DoorsFIGURE 1

2-7-10Page 2

Jan 01/11


**ON A/C A340-500

FUSELAGE DATUM LINE

**

**

FR94

FR98


MAX. 6.11 m (2 ft 0.4 in)

MIN. 5.82 m (19 ft 1 in)

MAX. 6.91 m (22 ft 8 in)

MIN. 6.62 m (21 ft 8 in)

MAX. 2.18 m (7 ft 1 in)

MIN. 1.93 m (6 ft 3 in)

MAX. 1.65 m (5 ft 4 in)

MIN. 1.41 m (4 ft 7 in)

F_AC_020710_1_0060101_01_00

APU and Nose Landing Gear DoorsFIGURE 2

2-7-10Page 3

Jan 01/11


AIRPLANE PERFORMANCE


**ON A/C A340-500 A340-600

General Information

1. This section gives standard day temperatures.

Section 3-2 indicates payload range information at specific altitudes recommended for long rangecruise with a given fuel reserve condition.

Section 3-3 represents FAR takeoff runway length requirements at ISA and ISA +15˚C (+27˚F) forRB 211 TRENT 500 series engine conditions for FAA certification.

Section 3-4 represents FAR landing runway length requirements for FAA certification.

Section 3-5 indicates final approach speeds.

Standard day temperatures for the altitude shown are tabulated below:

Standard day temperatures for the altitude

Altitude Standard Day Temperature

FEET METERS ˚F ˚C0 0 59.0 15.02000 610 51.9 11.14000 1219 44.7 7.16000 1829 37.6 3.18000 2438 30.5 -0.8

3-1-0Page 1

Jan 01/11


3-2-0 Payload / Range

**ON A/C A340-500 A340-600

Payload / Range

1. Payload / Range

3-2-0Page 1

Jan 01/11



**ON A/C A340-500 A340-600

ISA Conditions

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

3-2-1Page 1

Jan 01/11


**ON A/C A340-600

NOTE:

0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000

0

5

10

15

20

25

30

35

40

45

50

55

1000

185

190

195

200

205

210

215

220

225

60

65

230

235

240

ZFW(1000 kg)

PAYLOAD(1000 kg)

RANGE(nm)

RANGE(km)

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

180

175

70250

3000 5000 7000 9000 11000 13000 15000 17000 19000

CRUISE CONDITIONSISA 39000 ft M = 0.82

MAX PASSENGER PAYLOAD

MAX STRUCTURAL PAYLOAD

F_AC_030201_1_0180101_01_00

PAYLOAD / RANGERB 211 TRENT 556 engine

FIGURE 1

3-2-1Page 2

Jan 01/11


**ON A/C A340-500

NOTE:

0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000

0

5

10

15

20

25

30

35

40

45

50

55225

11000

RANGE(km)

RANGE(nm)


PAYLOAD(1000 kg)

ZFW(1000 kg)

165

170

175

180

185

190

195

200

205

210

215

220

1000 3000 5000 7000 9000 11000 13000 15000 17000 19000 21000

F_AC_030201_1_0190101_01_00

CRUISE CONDITIONSISA 39000 ft M = 0.82

MAX PASSENGER PAYLOAD

MAX STRUCTURAL PAYLOAD

PAYLOAD / RANGERB 211 TRENT 553 engine

FIGURE 2

3-2-1Page 3

Jan 01/11


3-3-0 FAR / JAR Takeoff Weight Limitation

**ON A/C A340-500 A340-600

FAR / JAR Takeoff Weight Limitation

1. FAR / JAR Takeoff Weight Limitation

3-3-0Page 1

Jan 01/11



**ON A/C A340-500 A340-600

FAR / JAR Takeoff Weight Limitation

1. This section gives the takeoff weight limitation at ISA conditions.

3-3-1Page 1

Jan 01/11


**ON A/C A340-600

0

TAKE−OFF WEIGHT

NOTE:

2

4

6

8

1000 kg1000 lb

1.5 2 2.5 3 3.5180

200

220

240

260

280

300

320

340

360

380

400

420

440

4 4.5 5

4 6 8 10 12 14 16 18

350

400

450

500

550

600

650

700

750

800

850

900

950

1000


AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 ft

)

RUNWAY LENGTH(1000 m)

RUNWAY LENGTH(1000 ft)

F_AC_030301_1_0100101_01_00

BRAKE ENERGY LIMITATIONV.M.C

FAR / JAR Takeoff Weight LimitationISA Conditions -- RB 211 TRENT 556 engine

FIGURE 1

3-3-1Page 2

Jan 01/11


**ON A/C A340-500

0

TAKE−OFF WEIGHT

NOTE:

2

4

6

8

1000 kg1000 lb

1.5 2 2.5 3 3.5180

200

220

240

260

280

300

320

340

360

380

400

420

440

4 4.5 5

4 6 8 10 12 14 16 18

350

400

450

500

550

600

650

700

750

800

850

900

950

1000


AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 ft

)

RUNWAY LENGTH(1000 m)


F_AC_030301_1_0110101_01_00

V.M.C

BRAKE ENERGY LIMITATION

FAR / JAR Takeoff Weight LimitationISA Conditions -- RB 211 TRENT 553 engine

FIGURE 2

3-3-1Page 3

Jan 01/11


3-3-2 ISA +15˚C (ISA +27˚F) Conditions

**ON A/C A340-500 A340-600

ISA +15˚C (ISA +27˚F) Conditions

1. This section gives the takeoff weight limitation at ISA +15˚C (ISA +27˚F) conditions.

3-3-2Page 1

Jan 01/11


**ON A/C A340-600

0

TAKE−OFF WEIGHT

NOTE:

2

4

6

8

1000 kg1000 lb

1.5 2 2.5 3 3.5180

200

220

240

260

280

300

320

340

360

380

400

420

440

4 4.5 5

4 6 8 10 12 14 16 18

350

400

450

500

550

600

650

700

750

800

850

900

950

1000


AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 ft

)

(1000 m)


RUNWAY LENGTH

V.M.CBRAKE ENERGY LIMITATION

F_AC_030302_1_0100101_01_00

FAR / JAR Takeoff Weight LimitationISA +15˚C (ISA +27˚F) Conditions -- RB 211 TRENT 556 engine

FIGURE 1

3-3-2Page 2

Jan 01/11


**ON A/C A340-500

0

TAKE−OFF WEIGHT

NOTE:

2

4

6

8

1000 kg1000 lb

1.5 2 2.5 3 3.5180

200

220

240

260

280

300

320

340

360

380

400

420

440

4 4.5 5

4 6 8 10 12 14 16 18

350

400

450

500

550

600

650

700

750

800

850

900

950

1000


AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 ft

)

(1000 m)


BRAKE ENERGY LIMITATIONV.M.C

RUNWAY LENGTH

F_AC_030302_1_0110101_01_00

FAR / JAR Takeoff Weight LimitationISA +15˚C (ISA +27˚F) Conditions -- RB 211 TRENT 553 engine

FIGURE 2

3-3-2Page 3

Jan 01/11


3-4-0 FAR / JAR Landing Field Length

**ON A/C A340-500 A340-600

Landing Field Length

1. Landing Field Length

3-4-0Page 1

Jan 01/11


3-4-1 ISA Conditions All series engines

**ON A/C A340-500 A340-600

ISA Conditions All series engine

1. This section gives the landing field length.

3-4-1Page 1

Jan 01/11


**ON A/C A340-600

NOTE:

2

4

6

8

GROSS WEIGHT(1000 lb)

GROSS WEIGHT(1000 kg)

(1000 m)(1000 ft)

1.5

2.0

2.5

3.0

3.5

180 200 220 240 260 280 300

0

AIRFIELD ELEVATION(1000 ft)

400 450350 500 550 600 650 700

4

6

8

10

12

THESE CURVES ARE GIVEN FOR INFORMATION ONLY.THE APPROVED VALUES ARE STATED IN THE "OPERATINGMANUALS" SPECIFIC TO THE AIRLINE OPERATINGTHE AIRCRAFT.

LANDING FIELD LENGTH

F_AC_030401_1_0100101_01_00

VALID FOR ALL TEMPERATURES

FAR / JAR Landing Field LengthISA Conditions -- RB 211 TRENT 556 engine

FIGURE 1

3-4-1Page 2

Jan 01/11


**ON A/C A340-500

180 200 220 240 300260

NOTE:

2

4

6

8



(1000 m)(1000 ft)

1.5

2.0

2.5

3.0

3.5

0

AIRFIELD ELEVATION(1000 ft)

400 450350 500 550 600 650 700

4

6

8

10

12

THESE CURVES ARE GIVEN FOR INFORMATION ONLY.THE APPROVED VALUES ARE STATED IN THE "OPERATINGMANUALS" SPECIFIC TO THE AIRLINE OPERATINGTHE AIRCRAFT.

LANDING FIELD LENGTH

280

VALID FOR ALL TEMPERATURES

F_AC_030401_1_0110101_01_00

FAR / JAR Landing Field LengthISA Conditions -- RB 211 TRENT 553 engine

FIGURE 2

3-4-1Page 3

Jan 01/11



**ON A/C A340-500 A340-600

Final Approach Speed

1. Final Approach Speed

3-5-0Page 1

Jan 01/11



**ON A/C A340-500 A340-600

Final Approach Speed

1. This section gives the final approach speed.

3-5-1Page 1

Jan 01/11


**ON A/C A340-600

C.A.S (Kts)

120

130

140

150

160

180 220 260 300 340 380

170

180

190

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



350 430 510 590 670 750 830 910

F_AC_030501_1_0040101_01_00

LANDING GEAR DOWNFULL POSITION

Final Approach SpeedRB 211 TRENT 556 engine

FIGURE 1

3-5-1Page 2

Jan 01/11


**ON A/C A340-500

120

130

140

150

160

180 220 260 300 340 380

170

180

190

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



350 430 510 590 670 750 830 910

C.A.S (Kts)

F_AC_030501_1_0050101_01_00

FULL POSITIONLANDING GEAR DOWN

Final Approach SpeedRB 211 TRENT 553 engine

FIGURE 2

3-5-1Page 3

Jan 01/11


GROUND MANEUVERING


**ON A/C A340-500 A340-600

General Information

1. This section provides 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 in the level of performance, over a wide range of operatingcircumstances throughout the world. Variations from standard aircraft operating patterns may benecessary to satisfy physical constraints within the maneuvering area, such as adverse grades, limitedarea or high risk of jet blast damage. For these reasons, ground maneuvering requirements should becoordinated with the using airlines prior to layout planning.

4-1-0Page 1

Jan 01/11


4-2-0 Turning Radii

**ON A/C A340-500 A340-600

Turning Radii

1. This section gives the turning radii.

4-2-0Page 1

Jan 01/11


**ON A/C A340-600

55°

60°

65°

70°75°

R5

R3

R4

R6

F_AC_040200_1_0080101_01_01

Turning RadiiFIGURE 1

4-2-0Page 2

Jan 01/11


**ON A/C A340-500

55°

60°

65°

70°

R5

R3

R4

R6

F_AC_040200_1_0090101_01_01

Turning RadiiFIGURE 2

4-2-0Page 3

Jan 01/11


**ON A/C A340-600

98.9325

mft

124.8409

98.2322

R6

109.9361

TAILR3 R4 R5

NLG WING NOSE

24.6°25°80.2263

104.7344

82.8272

91.1299

29.5°30°67.9223

91299

70.9233

78.6258

34.4°35°59.3195

80.9265

62.8206

69.7229

39.2°40°53

17473.2240

56.9187

63.1207

44°45°48.3159

66.9220

52.6173

58190

48.8°50°44.7147

61.7202

49.3162

53.9177

53.4°55°41.9138

57.4188

46.8154

50.7166

57.9°60°39.8131

53.6176

44.9147

48158

62°65°38.2125

50.5166

43.5143

45.9151

65.6°70°37.1122

48158

42.5139

44.4146

mftmftmftmftmftmftmftmftmftmft

A340−600 TURNING RADII

67.4°75°36.6120

46.8153

42.1138

43.6143

mft

19.7°

STEERING ANGLESTEERING EFFECTIVE

ANGLE

20°

TURNING RADII TABLE

NOTE: SYMMETRIC THRUST− NO BRAKING

F_AC_040200_1_0120101_01_00

Turning RadiiSteady State Turning Radii

FIGURE 3

4-2-0Page 4

Jan 01/11


**ON A/C A340-500

83.4274

mft

110.3362

85.7281

R6

95.3313

TAILR3 R4 R5

NLG WING NOSE

24.6°25°67.6222

93.3306

70.3231

79.6261

29.5°30°57.3188

81.8268

60.4198

69.2227

34.3°35°50.1164

73.4241

53.6176

61.9203

39.1°40°44.8147

66.9220

48.7160

56.4185

43.9°45°40.8134

61.6202

45.1148

52.2171

48.6°50°37.8124

57.3188

42.4139

48.9160

53.2°55°35.4116

53.7176

40.3132

46.3152

57.6°60°33.6110

50.5166

38.7127

44.1145

61.7°65°32.3106

47.9157

37.6123

42.4139

65.2°70°31.4103

45.9151

36.8121

41.1135

mftmftmftmftmftmftmftmftmftmft

A340−500 TURNING RADII

19.7°

STEERING ANGLESTEERING EFFECTIVE

ANGLE

20°

TURNING RADII TABLE

NOTE: SYMMETRIC THRUST− NO BRAKING

F_AC_040200_1_0130101_01_00

Turning RadiiSteady State Turning Radii

FIGURE 4

4-2-0Page 5

Jan 01/11


4-3-0 Minimum Turning Radii

**ON A/C A340-500 A340-600

Minimum Turning Radii

1. This section gives the minimum turning radii.

4-3-0Page 1

Jan 01/11


**ON A/C A340-600

NOTE:

TYPEOF TURN

EFFECTIVETURN ANGLE Y A R3 R4 R6R5

TYPE OF TURN: 2−SYMMETRIC THRUST − NO BRAKING

2

R5

R3

A

(MINIMUM TURNING WIDTH)

R4

R6

Y

33.2(109.0)

67.4°13.745.1

56.7185.9

36.6120.0

46.8153.4

42.1138.2

43.6143.1

mft

F_AC_040300_1_0050101_01_00

Minimum Turning RadiiFIGURE 1

4-3-0Page 2

Jan 01/11


**ON A/C A340-500

A

Y

R5

R4

R6

(MINIMUM TURNING WIDTH)

27.952(91.7)

R3

NOTE:

TYPEOF TURN

EFFECTIVETURN ANGLE Y A R3 R4 R6R5

TYPE OF TURN: 2−SYMMETRIC THRUST − NO BRAKING

2 65.2°12.842.1

50.5165.8 102.9

31.4 45.9150.4 120.8

36.8 41.4134.9

mft

F_AC_040300_1_0060101_01_00

Minimum Turning RadiiFIGURE 2

4-3-0Page 3

Jan 01/11


4-4-0 Visibility from Cockpit in Static Position

**ON A/C A340-500 A340-600

Visibility from Cockpit in Static Position

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

4-4-0Page 1

Jan 01/11


**ON A/C A340-500 A340-600

NOTEPILOT’S EYEPOSITION

6.576 m(21.57 ft)

2.40 m(7.87 ft)14.00 m(45.93 ft)

0.53 m(1.73 ft)

42°

62°

36°

25°

19° 20’

135°

135°

PILOT EYE’S POSITION

42°

30°36°

30°

115°

111°

62°

F_AC_040400_1_0050101_01_00

Visibility from Cockpit in Static PositionFIGURE 1

4-4-0Page 2

Jan 01/11


4-5-0 Runway and Taxiway Turn Paths

**ON A/C A340-500 A340-600

Runway and Taxiway Turn Paths

1. Runway and Taxiway Turn Paths.

4-5-0Page 1

Jan 01/11



**ON A/C A340-500 A340-600

135˚ Turn - Runway to Taxiway

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

4-5-1Page 1

Jan 01/11


**ON A/C A340-600

(150 ft)

FILLET R = 25.5 m(85 ft)

APPROX 6.5 m

APPROX 4.6 mFAA LEAD−IN FILLET

(22 ft)

(15 ft)L = 75 m (250 ft)

(150 ft)

23 m(75 ft)

NLG PATH

MLG PATH

45 m

TURN R = 45 m

F_AC_040501_1_0040101_01_01

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

135˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

FIGURE 1

4-5-1Page 2

Jan 01/11


**ON A/C A340-600

45 m(150 ft)

TURN R = 45 m(150 ft)


APPROX 3.2 m(11 ft)

FAA LEAD−IN FILLET

L = 75 m (250 ft)

23 m(75 ft)

NLG PATH

MLG PATH

ADDITIONAL FILLET TO MEET4.5 m (15 ft) EDGE CLEARANCE

F_AC_040501_1_0110101_01_00

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

135˚ Turn - Runway to TaxiwayCockpit Over Centerline Method

FIGURE 2

4-5-1Page 3

Jan 01/11


**ON A/C A340-500


L = 75 m (250 ft)

TURN R = 45 m(150 ft)


(33 ft)

APPROX 4.6 m(15 ft)

45 m(150 ft)

23 m(75 ft)

NLG PATH

MLG PATH

APPROX 9.8 m

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

F_AC_040501_1_0050101_01_01

135˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

FIGURE 3

4-5-1Page 4

Jan 01/11


**ON A/C A340-500


L = 75 m (250 ft)

45 m(150 ft)

TURN R = 45 m(150 ft)


APPROX 1.5 m(5 ft)

23 m(75 ft)

NLG PATH

MLG PATH


RUNWAYCENTERLINE

TAXIWAYCENTERLINE

F_AC_040501_1_0120101_01_00


FIGURE 4

4-5-1Page 5

Jan 01/11



**ON A/C A340-500 A340-600

90˚ Turn - Runway to Taxiway

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

4-5-2Page 1

Jan 01/11


**ON A/C A340-600

45 m(150 ft)

(44 ft)APPROX 13.1 m


TURN R = 45 m(150 ft)

(25 ft)APPROX 7.6 m

FAA LEAD−IN FILLETL = 75 m (250 ft)

23 m(75 ft)

NLG PATH

MLG PATH

F_AC_040502_1_0040101_01_01

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

90˚ Turn - Runway to TaxiwayJudgement Oversteering Method

FIGURE 1

4-5-2Page 2

Jan 01/11


**ON A/C A340-600

APPROX 1.4 m(5 ft)


TURN R = 45 m(150 ft)

23 m(75 ft)


45 m(150 ft)

NLG PATH

MLG PATH

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

F_AC_040502_1_0130101_01_00

4.5 m (15 ft) EDGE CLEARANCEADDITIONAL FILLET TO MEET


FIGURE 2

4-5-2Page 3

Jan 01/11


**ON A/C A340-500

APPROX 13.5 m(45 ft)


TURN R = 45 m(150 ft)

23 m(75 ft)


45 m(150 ft)


NLG PATH

MLG PATH

F_AC_040502_1_0050101_01_01

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

90˚ Turn - Runway to TaxiwayJudgement Oversteering Method

FIGURE 3

4-5-2Page 4

Jan 01/11


**ON A/C A340-500

45 m(150 ft)


APPROX 4.3 m(14 ft)



TURN R = 45 m(150 ft)

23 m(75 ft)

NLG PATH

MLG PATH

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

F_AC_040502_1_0140101_01_00


FIGURE 4

4-5-2Page 5

Jan 01/11


4-5-3 180˚ Turn on a Runway

**ON A/C A340-500 A340-600

180˚ Turn on a Runway

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

4-5-3Page 1

Jan 01/11


**ON A/C A340-600

4.6 m

R = 42.1 mR = 46.8 m

R = 43.6 m

65.8 m

56.7 m

19 m

4.6 m

22.1 m 5.6 m

0.9 m

(18.3 ft)

(3.1 ft)

(138.2 ft)

(216 ft)

(185.9 ft)

(153.4 ft)

(143.1 ft)

(62.2 ft)

(15 ft)

(72.6 ft)

(15 ft)

RUNWAY CENTERLINE

NLG PATH

MLG PATH

F_AC_040503_1_0090101_01_01

180˚ Turn on a Runway75˚ Nose Wheel Steering

FIGURE 1

4-5-3Page 2

Jan 01/11


**ON A/C A340-500

4.6 m4.6 m

59.5 m

50.5 m

R = 36.8 mR = 45.8 m

R = 41.1 m

17.5 m

22.2 m 10 m

1 m

(120.9 ft)

(165.6 ft)

(195.1 ft)

(150.4 ft)

(134.8 ft)

(57.4 ft)

(72.9 ft)

(15 ft) (15 ft)

(32.7 ft)

(3.3 ft)

NLG PATH

MLG PATH

RUNWAY CENTERLINE

F_AC_040503_1_0100101_01_01

180˚ Turn on a Runway70˚ Nose Wheel Steering

FIGURE 2

4-5-3Page 3

Jan 01/11



**ON A/C A340-500 A340-600

135˚ Turn - Taxiway to Taxiway

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

4-5-4Page 1

Jan 01/11


**ON A/C A340-600

TAXIWAY CENTERLINE

23 m(75 ft)


L = 75 m (250 ft)

APPROX 7.7 m(26 ft)


TURN R = 45 m(150 ft)

APPROX 4.6 m(15 ft)

TAXIWAY CENTERLINE

NLG PATH

MLG PATH

23 m(75 ft)

F_AC_040504_1_0050101_01_01

135˚ Turn - Taxiway to TaxiwayJudgement Oversteering Method

FIGURE 1

4-5-4Page 2

Jan 01/11


**ON A/C A340-600

23 m(75 ft)


L = 75 m (250 ft)

(8 ft)APPROX 2.4 m


TURN R = 45 m(150 ft)

TAXIWAY CENTERLINE


TAXIWAY CENTERLINE

NLG PATH

MLG PATH

23 m(75 ft)

F_AC_040504_1_0130101_01_00

135˚ Turn - Taxiway to TaxiwayCockpit Over Centerline Method

FIGURE 2

4-5-4Page 3

Jan 01/11


**ON A/C A340-500


L = 75 m (250 ft)


TURN R = 45 m(150 ft)


TAXIWAY CENTERLINE

23 m(75 ft)

APPROX 4.6 m(15 ft)

TAXIWAY CENTERLINE

NLG PATH

MLG PATH

23 m(75 ft)

F_AC_040504_1_0060101_01_01

135˚ Turn - Taxiway to TaxiwayJudgement Oversteering Method

FIGURE 3

4-5-4Page 4

Jan 01/11


**ON A/C A340-500


L = 75 m (250 ft)

APPROX 1.5 m(5 ft)


TURN R = 45 m(150 ft)


TAXIWAY CENTERLINE

23 m(75 ft)

TAXIWAY CENTERLINE

NLG PATH

MLG PATH

23 m(75 ft)

F_AC_040504_1_0140101_01_00


FIGURE 4

4-5-4Page 5

Jan 01/11



**ON A/C A340-500 A340-600

90˚ Turn - Taxiway to Taxiway

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

4-5-5Page 1

Jan 01/11


**ON A/C A340-600



TURN R = 45 m(150 ft)

(24 ft)APPROX 7.3 m

TAXIWAY CENTERLINE


23 m(75 ft)

TAXIWAY CENTERLINE

23 m(75 ft)

NLG PATH

MLG PATH

F_AC_040505_1_0080101_01_01

90˚ Turn - Taxiway to TaxiwayJudgemental Oversteering Method

FIGURE 1

4-5-5Page 2

Jan 01/11


**ON A/C A340-600

APPROX 0.3 m(1 ft)


TURN R = 45 m(150 ft)



23 m(75 ft)

TAXIWAY CENTERLINE

TAXIWAY CENTERLINE

23 m(75 ft)

NLG PATH

MLG PATH

F_AC_040505_1_0150101_01_00


FIGURE 2

4-5-5Page 3

Jan 01/11


**ON A/C A340-500



TAXIWAY CENTERLINE



TURN R = 45 m(150 ft)

TAXIWAY CENTERLINE

23 m(75 ft)

23 m(75 ft)

NLG PATH

MLG PATH

F_AC_040505_1_0090101_01_01

90˚ Turn - Taxiway to TaxiwayJudgemental Oversteering Method

FIGURE 3

4-5-5Page 4

Jan 01/11


**ON A/C A340-500

APPROX 3 m(10 ft) ADDITIONAL FILLET TO MEET

4.5 m (15 ft) EDGE CLEARANCE



TURN R = 45 m(150 ft)

23 m(75 ft)

TAXIWAY CENTERLINE

TAXIWAY CENTERLINE

23 m(75 ft)

NLG PATH

MLG PATH

F_AC_040505_1_0160101_01_00


FIGURE 4

4-5-5Page 5

Jan 01/11


4-6-0 Runway Holding Bay (Apron)

**ON A/C A340-500 A340-600

Runway Holding Bay (Apron)

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

4-6-0Page 1

Jan 01/11


**ON A/C A340-500 A340-600

NOTE : 20° NOSE WHEEL STEERING ANGLE.COORDINATE WITH USING AIRPLANE FOR SPECIFIC

6.1 m(20 ft)

6.1 m(20 ft)

45 m(150 ft)

12.2 m(40 ft)

HOLDINGPOINT

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

F_AC_040600_1_0040101_01_01PLANNED OPERATING PROCEDURES.

190 m(625 ft)

100.54 m(329 ft)

90 m(300 ft)

23 m(75 ft)

Runway Holding Bay (Apron)FIGURE 1

4-6-0Page 2

Jan 01/11


4-7-0 Airplane Parking

**ON A/C A340-500 A340-600

Airplane Parking

1. The following figures and charts show the rectangular space required for parking against the terminalbuilding.

The rectangle includes allowance for swinging the airplane on arrival and departure.- Steering Geometry- Minimum Parking Space Requirements

4-7-0Page 1

Jan 01/11


**ON A/C A340-600

PARKINGSTRAIGHT ENTRY PUSH BACK

PARKING45° ENTRY PUSH OUT

PARKING90° ENTRY PUSH OUTNOTE: DIMENSIONS IN METERS

(FEET IN BRACKETS).

116.07 (380.8)

79.8

666.0

3

76.53 (251.0)

88.6

3

(216

.6)

(262

.0)

78.61 (258.0)

(290

.8)

F_AC_040700_1_0130101_01_00

Airplane ParkingSteering Geometry

FIGURE 1

4-7-0Page 2

Jan 01/11


**ON A/C A340-600

PARKING45° ENTRY POWER OUT

PARKINGPARALLEL IN POWER OUT

100.56 (330.0)

119.97 (393.6)

NOTE: DIMENSIONS IN METERS(FEET IN BRACKETS)

77.8

1

(255

.3)

F_AC_040700_1_0140101_01_00

78.6

1

(258

.0)


FIGURE 2

4-7-0Page 3

Jan 01/11


**ON A/C A340-600

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

10

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)

1. STRAIGHT ENTRY PUSH BACK2. 45° ENTRY POWER OUT3. PARALLEL IN POWER OUT

45° ENTRY PUSH OUT

90° ENTRY PUSH OUT

1 2

3

F_AC_040700_1_0150101_01_00

Airplane ParkingMinimum Parking Space Requirements

FIGURE 3

4-7-0Page 4

Jan 01/11


**ON A/C A340-500

PARKINGSTRAIGHT ENTRY PUSH BACK

PARKING45° ENTRY PUSH OUT

PARKING90° ENTRY PUSH BACK

72.3

0

71.05 (233.1)

60.5

5

NOTE: DIMENSIONS IN METERS(FEET IN BRACKETS).

78.61 (258.0)

85.3

9

106.58 (349.7)

(198

.7)

(280

.2)

(237

.2)

F_AC_040700_1_0160101_01_00


FIGURE 4

4-7-0Page 5

Jan 01/11


**ON A/C A340-500

PARKING45° ENTRY POWER OUT

PARKINGPARALLEL IN POWER OUT

78.6

1

100.56 (329.9)

NOTE: DIMENSIONS IN METERS(FEET IN BRACKETS).

75.8

111.04 (364.0)

(257

.9)

(248

.7)

F_AC_040700_1_0170101_01_00


FIGURE 5

4-7-0Page 6

Jan 01/11


**ON A/C A340-500

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

10

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

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

90° ENTRY PUSH BACK

PARALLEL IN POWER OUT

45° ENTRY POWER OUT

STRAIGHT ENTRY PUSH BACK

F_AC_040700_1_0180101_01_00

Airplane ParkingMinimum Parking Space Requirements

FIGURE 6

4-7-0Page 7

Jan 01/11


TERMINAL SERVICING

5-0-0 TERMINAL SERVICING

**ON A/C A340-500 A340-600

TERMINAL SERVICING

1. Terminal servicing

This chapter provides typical ramp layouts, corresponding minimum turnaround time estimations,locations of ground service points and service requirements.The information given in this chapter reflects ideal conditions. Actual ramp layouts and servicerequirements may vary according to local regulations, airline procedures and the airplane condition.

Section 5.1 shows typical ramp layouts for passenger aircraft at the gate or on an Open Apron andfreighter aircraft on an Open Apron.

Section 5.2 shows the minimum turnaround schedules for full servicing arrangements (turnroundstations).

Section 5.3 shows the minimum turnaround schedule for reduced servicing arrangements (en routestations).

Section 5.4 gives the locations of ground service connections, the standard of connections used andtypical capacities and requirements.

Section 5.5 provides the engine starting pneumatic requirements for different engine types anddifferent ambient temperatures.

Section 5.6 provides the air conditioning requirements for heating and cooling (pull-down and pull-up)using ground conditioned air for different ambient temperatures.

Section 5.7 provides the air conditioning requirements for heating and cooling to maintain a constantcabin air temperature using low pressure conditioned air.

Section 5.8 shows the ground towing requirements taking into account different ground surface andaircraft conditions.

5-0-0Page 1

Jan 01/11


5-1-0 Airplane Servicing Arrangements

**ON A/C A340-500 A340-600

Airplane Servicing Arrangements

1. This section provides typical ramp layouts, showing the various GSE items in position during typicalturnaround scenarios for the passenger aircraft.

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

The associated turnaround station is given in the section 5-2-1 for Full Servicing Turn Round Charts.The associated minimum turnaround time for Transit Turn Round Charts is given in a section 5-3-1.

5-1-0Page 1

Jan 01/11


5-1-1 Symbols Used on Servicing Diagrams

**ON A/C A340-500 A340-600

Symbols Used on Servicing Diagrams

1. This table gives the symbols used on servicing diagrams.

Ground Support Equipment

AC AIR CONDITIONING UNITAS AIR START UNIT

CAT CATERING TRUCKCB CONVEYOR BELT

CLEAN CLEANING TRUCKFUEL FUEL HYDRANT DISPENSER or TANKERGPU GROUND POWER UNIT

LD CL LOWER DECK CARGO LOADERLV LAVATORY VEHICLE

MD CL MAIN DECK CARGO LOADERPBB PASSENGER BOARDING BRIDGE

PS PASSENGER STAIRSTOW TOW TRACTORULD ULD TRAINWV POTABLE WATER VEHICLE

5-1-1Page 1

Jan 01/11


5-1-2 Loading (Open Apron)

**ON A/C A340-500 A340-600

Loading (Open Apron)

1. This section gives the typical ramp layout for the passenger aircraft on an Open Apron.

5-1-2Page 1

Jan 01/11


**ON A/C A340-600

PS

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

TOW

AS

GP

U

LD CL

CAT

CATPS

AC

LD CL

CATPS

CAT

F_AC_050102_1_0080101_01_00

ULD

FUELFUEL

WV

LV

ULD

BULKCB

Airplane Servicing ArrangementsTypical Ramp Layout (Open Apron)

FIGURE 1

5-1-2Page 2

Jan 01/11


**ON A/C A340-500

PS CAT

CATPS

PS CAT

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

TOW

AS

GP

U

LD CL

AC

LD CL

F_AC_050102_1_0090101_01_00

ULD

FUELFUEL

WV CB BULK

ULD

LV

Airplane Servicing ArrangementsTypical Ramp Layout (Open Apron)

FIGURE 2

5-1-2Page 3

Jan 01/11


5-1-3 Loading (Passenger Bridge)

**ON A/C A340-500 A340-600

Loading (Passenger Bridge)

1. This section gives the typical ramp layout for the passenger aircraft at a gate with 2 passengerboarding bridges.

5-1-3Page 1

Jan 01/11


**ON A/C A340-600

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

TOW

AS

GP

U

LD CL

CAT

CAT

AC

LD CL

CAT

CLEAN

ULD

FUELFUEL

WV

LV

ULD

BULKCB

F_AC_050103_1_0040101_01_02

PBB

PBB

Airplane Servicing ArrangementsTypical Ramp Layout (gate area)

FIGURE 1

5-1-3Page 2

Jan 01/11


**ON A/C A340-500

CLEAN CAT

CAT

CAT

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

TOW

AS

GP

U

LD CL

AC

LD CL

ULD

FUELFUEL

CB BULK

ULD

LV

F_AC_050103_1_0050101_01_02

PBB

PBB

WV

Airplane Servicing ArrangementsTypical Ramp Layout (gate area)

FIGURE 2

5-1-3Page 3

Jan 01/11


5-2-0 Terminal Operations - Full Servicing Turn Round Charts

**ON A/C A340-500 A340-600

Terminal Operations - Full Servicing Turn Round Charts

1. This section provides a series of charts showing typical activities during turnaround at destinationairports.

This data is provided to show the general scope and type of activities involved in ramp operationsduring the turnaround of an aircraft.

Varying Airline practices and operating circumstances may result in different sequences and differenttime intervals to do the activities shown.

5-2-0Page 1

Jan 01/11


5-2-1 Full Servicing Turn Round Charts

**ON A/C A340-500 A340-600

Full Servicing Turn Round Charts

**ON A/C A340-500

1. Assumptions for full servicing turn round chart.

A. PASSENGER BOARDING/DEBOARDING (PB/D)

Deboarding : 246 passengers (8 first + 42 business + 196 tourists)- For full servicing, all passengers deboard and board- Doors used: L1 + L2- Deboarding:

- 120 pax at L1 (8 first + 42 business + 70 tourists) and 126 pax at L2- Deboarding rate = 25 pax/min- Priority deboarding for premium passengers

- Boarding:- 52 pax at L1 and 196 pax at L2- Boarding rate = 15 pax/min

- Last Pax Seating Allowance (LPS) + headcounting = + 4 min

B. CARGO- 6 LD3 + 2 pallets for AFT CC- 12 LD3 + 2 pallets for FWD CC- 1 000 kg (2 205 lb) in Bulk CC- LD-3 off-loading/loading times:

- off-loading = 1.2 min/LD-3- loading = 1.4 min/LD-3

- Pallet loading times:- off-loading = 2.4 min/pallet- loading = 2.8 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- 191 000 l (50 457 US gal) at 50 psi- Dispenser positioning or removal = 3 min (fuel truck change) / if any = 5 min

D. CLEANING- Cleaning is performed in available time

5-2-1Page 1

Jan 01/11


E. CATERING- 3 catering vehicles- 39 Full size trolley: 8 FSTE at R1, 9 FSTE at R2 and 22 FST at R4- FST exchange time = 1.5 min/FST

F. GROUND HANDLING/SERVICING- Start of operations :

(1) Bridges = t0 = 0(2) Others = t0 + 1 min

- Vehicle positioning/removal = 2 min (fuel truck excluded)- Ground Power Unit (GPU) = up to 2 × 90 kVA- Air conditioning = two carts- Potable water servicing: replenish 700 l (185 US gal); flow rate: 60 l/min (15.85 US

gal/min)- Waste water servicing (draining + rinsing): discharge 1 140 l (301 US gal)- Dollies per tractor = 4

**ON A/C A340-600

2. Assumptions for full servicing turn round chart.


Deboarding : 319 passengers (12 first + 42 business + 265 tourists)- For full servicing, all passengers deboard and board- Doors used: L1 + L2- Deboarding:




B. CARGO- 12 LD3 + 2 pallets for AFT CC- 12 LD3 + 2 pallets for FWD CC- 1 000 kg (2 205 lb) in Bulk CC- LD-3 off-loading/loading times:


- Pallet loading times:- off-loading = 2.4 min/pallet- loading = 2.8 min/pallet

5-2-1Page 2

Jan 01/11


- 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- 178 000 l (47 023 US gal) at 50 psi- Dispenser positioning or removal = 3 min (fuel truck change) / if any = 5 min


E. CATERING- 3 catering vehicles- 45 Full size trolley: 9 FSTE at R1, 9 FSTE at R2 and 27 FST at R4- FST exchange time = 1.5 min/FST



- Vehicle positioning/removal = 2 min (fuel truck excluded)- Ground Power Unit (GPU) = up to 2 × 90 kVA- Air conditioning = two carts- Potable water servicing: replenish 1 070 l (283 US gal); flow rate: 60 l/min (15.85 US

gal/min)- Waste water servicing (draining + rinsing): discharge 1 140 l (301 US gal)- Dollies per tractor = 4

5-2-1Page 3

Jan 01/11


**ON A/C A340-500

0 10 20 30 40 50 60 70

DEBOARDING/BOARDING AT L1

HEADCOUNTING

CATERING AT R1

CLEANING

CARGO FWD CC

BULK

REFUELLING

POTABLE WATER SERVICING

TOILET SERVICING


CATERING AT R2

CATERING AT R4

CARGO AFT CC

TRT : 63 min

POSITIONING/REMOVAL

ACTIVITY

AVAILABLE TIME

F_AC_050201_1_0100101_01_01

Turn around chartsTurn Round Time 63 min.

FIGURE 1

5-2-1Page 4

Jan 01/11


**ON A/C A340-600

0 10 20 30 40 50 60 70


HEADCOUNTING

CATERING AT R1

CLEANING

CARGO FWD CC

BULK

REFUELLING


TOILET SERVICING


CATERING AT R2

CATERING AT R4

CARGO AFT CC

TRT : 74 min

POSITIONING/REMOVAL

ACTIVITY

AVAILABLE TIME

80

F_AC_050201_1_0110101_01_01

Turn around chartsTurn Round Time 74 min.

FIGURE 2

5-2-1Page 5

Jan 01/11


5-3-0 Terminal Operations - Transit Turn Round Charts

**ON A/C A340-500 A340-600

Terminal Operations - Transit Turn Round Charts

1. This section provides a series of charts showing typical activities during turnaround at transit airports.

This data is provided to show the general scope and type of activities involved in ramp operationsduring the turnaround of an aircraft.

Varying Airline practices and operating circumstances may result in different sequences and differenttime intervals to do the activities shown.

5-3-0Page 1

Jan 01/11


5-3-1 Transit Turn Round Charts

**ON A/C A340-500 A340-600

Transit Turn Round Charts

**ON A/C A340-500

1. Assumptions for transit turn round chart.


Deboarding : 246 passengers (8 first + 42 business + 196 tourists)- 50% pax in transit, all passengers deboard and board- Doors used: L1 + L2- Deboarding:

- 120 pax at L1 (8 first + 42 business and 70 tourists) and 126 pax at L2- Deboarding rate = 25 pax/min- Priority deboarding for premium passengers



B. CARGO

For transit, 50% of luggages are exchanged in one cargo compartment only- 1 container loader for AFT CC- 4 LD3 for AFT CC- LD-3 off-loading/loading times:


C. REFUELLING- Refueling through 2 nozzles- For transit, fuel uplift is 30% of maximum fuel uplift. (Max = 214 808 l (56 746 US gal))

Note: local rules and regulations to be respected.- Passengers boarding can start before refuel is finished- Dispenser positioning or removal = 3 min (fuel truck change) / if any = 5 min


E. CATERING- Time needed just for additional meals- Assumptions: 10 min

5-3-1Page 1

Jan 01/11




- Vehicle positioning/removal = 2 min (fuel truck excluded)- Ground Power Unit (GPU) = up to 2 × 90 kVA- Air conditioning = two carts- No potable water servicing- No waste water servicing- Dollies per tractor = 4

**ON A/C A340-600

2. Assumptions for transit turn round chart.


Deboarding : 319 passengers (12 first + 42 business + 265 tourists)- 50% pax in transit, all passengers deboard and board- Doors used: L1 + L2- Deboarding:




B. CARGO

For transit, 50% of luggages are exchanged in one cargo compartment only- 1 container loader for AFT CC- 6 LD3 for AFT CC- LD-3 off-loading/loading times:


C. REFUELLING- Refueling through 2 nozzles- For transit, fuel uplift is 30% of maximum fuel uplift. (Max = 195 521 l (51 651 US gal))

Note: local rules and regulations to be respected.- Passengers boarding can start before refuel is finished- Dispenser positioning or removal = 3 min (fuel truck change) / if any = 5 min

5-3-1Page 2

Jan 01/11



E. CATERING- Time needed just for additional meals- Assumptions: 10 min



- Vehicle positioning/removal = 2 min (fuel truck excluded)- Ground Power Unit (GPU) = up to 2 × 90 kVA- Air conditioning = two carts- No potable water servicing- No waste water servicing- Dollies per tractor = 4

5-3-1Page 3

Jan 01/11


**ON A/C A340-500

0 5 15 20 25 30 35 40


HEADCOUNTING

CATERING AT R1

CLEANING

CARGO FWD CC

BULK

REFUELLING


TOILET SERVICING


CATERING AT R2

CATERING AT R4

CARGO AFT CC

TRT : 40 min

POSITIONING/REMOVAL

ACTIVITY

10 45

AVAILABLE TIME

F_AC_050301_1_0060101_01_01

Transit Turn Round ChartsTurn Round Time 40 min.

FIGURE 1

5-3-1Page 4

Jan 01/11


**ON A/C A340-600

0 5 15 20 25 30 35 40


HEADCOUNTING

CATERING AT R1

CLEANING

CARGO FWD CC

BULK

REFUELLING


TOILET SERVICING


CATERING AT R2

CATERING AT R4

CARGO AFT CC

TRT : 46 min

POSITIONING/REMOVAL

ACTIVITY

10 45 50

AVAILABLE TIME

F_AC_050301_1_0070101_01_01

Transit Turn Round ChartsTurn Round Time 46 min.

FIGURE 2

5-3-1Page 5

Jan 01/11


5-4-0 Ground Service Connections

**ON A/C A340-500 A340-600

Ground Service Connections

1. Ground Service Connections.

5-4-0Page 1

Jan 01/11


5-4-1 Ground Service Connections Layout

**ON A/C A340-500 A340-600

Ground Service Connections Layout

1. This section gives the ground service connections layout.

Ground Service Connections Layout

1 -- POTABLE WATER SERVICE PANEL2 -- REMOTE WATER DRAIN

3 -- HYDRAULIC GROUND POWER (YELLOW)

4 -- IDG OIL FILLING4.1 -- ENGINE OIL FILLING5 -- WASTE SERVICE PANEL6 -- ELECTRICAL GROUND POWER RECEPTABLES7 -- LOW PRESSURE AIR8 -- FUEL GRAVITY FILLING9 -- AIR CHARCHING FOR HYDRAULIC ACCUMULATORS

10 -- HYDRAULIC RESERVOIR FILLING AND GROUND POWER (GREEN)

11 -- HYDRAULIC RESERVOIR AIR CHARGING AND GROUND POWER (BLUE)

12 -- REFUEL/DEFUEL COUPLINGS

13 -- HIGH PRESSURE AIR14 -- APU OIL FILLING

15 -- REFUEL/DEFUEL PANEL

5-4-1Page 1

Jan 01/11


**ON A/C A340-600

6 4 4.1 1 5 14

12

8

6 2

4

4.1

9 1

14

12

11

4

4.1

5

15

10

8

3

2

7 13

F_AC_050401_1_0040101_01_01

Ground Service ConnectionsGround Service Connections Layout

FIGURE 1

5-4-1Page 2

Jan 01/11


**ON A/C A340-500

6 4 4.1 1 5 14

12

8

4

4.1

9

14

12

4

4.1

5

7

15

10

13

8

3

2

6 21

11

F_AC_050401_1_0050101_01_01

Ground Service ConnectionsGround Service Connections Layout

FIGURE 2

5-4-1Page 3

Jan 01/11


5-4-2 Grounding Points

**ON A/C A340-500 A340-600

Grounding Points

**ON A/C A340-600

1. Grounding Points.

DISTANCE: Meters (ft)

FROM AIRPLANE CENTERLINE

AFT OF NOSER SIDE L SIDE

MEANHEIGHTFROM

GROUND

On Nose Landing Gear leg:6.57 m(21.56 ft) on centerline

1.40 m(4.59 ft)

On left Main Landing Gearleg:

39.45 m(129.43 ft)

5.34 m(17.52 ft)

1.50 m(4.92 ft)

On right Main LandingGear leg:

39.45 m(129.43 ft)

5.34 m(17.52 ft)

1.50 m(4.92 ft)

A. The grounding stud on each landing gear leg is designed for use with a clip-on connector (suchas Appleton TGR).

B. The grounding studs are used to connect the aircraft to an approved ground connection on theramp or in the hangar for:- refuel/defuel operations.- maintenance operations.- bad weather conditions.

NOTE : In all other conditions, the electrostatic discharge through the tyre is sufficient.

**ON A/C A340-500

2. Grounding Points.

5-4-2Page 1

Jan 01/11





MEANHEIGHTFROM

GROUND

On Nose Landing Gear leg:6.57 m(21.56 ft) on centerline

1.40 m(4.59 ft)

On left Main Landing Gearleg:

34.15 m(112.04 ft)

5.34 m(17.52 ft)

1.50 m(4.92 ft)

On right Main LandingGear leg:

34.15 m(112.04 ft)

5.34 m(17.52 ft)

1.50 m(4.92 ft)

A. The grounding stud on each landing gear leg is designed for use with a clip-on connector (suchas Appleton TGR).

B. The grounding studs are used to connect the aircraft to an approved ground connection on theramp or in the hangar for:- refuel/defuel operations.- maintenance operations.- bad weather conditions.

NOTE : In all other conditions, the electrostatic discharge through the tyre is sufficient.

5-4-2Page 2

Jan 01/11


**ON A/C A340-500 A340-600

(1)(2)

LANDINGGEAR

GROUND CABLE(OPTIONAL)

A

GROUNDINGPOINT

MAIN GEAR

A

NOSE GEAR

GROUNDINGPOINT

A

F_AC_050402_1_0050101_01_01

Ground Service ConnectionsGrounding Points

FIGURE 1

5-4-2Page 3

Jan 01/11


5-4-3 Hydraulic System

**ON A/C A340-500 A340-600

Hydraulic System

**ON A/C A340-600

1. Ground service panels.




MEANHEIGHTFROM

GROUNDGreen System:(Access door 197 FB)

42.00 m(137.80 ft)

1.50 m(4.92 ft)

2.10 m(6.89 ft)

Yellow System:(Access door 196 PB)

36.70 m(120.41 ft)

1.70 m(5.58 ft)

1.80 m(5.91 ft)

Blue System:(Access door 195 MB)

34.20 m(112.20 ft)

1.50 m(4.92 ft)

1.75 m(5.74 ft)

A. Reservoir pressurization.

On Blue ground service panel:- one self-sealing connector - Green reservoir pressurization.- one self-sealing connector - Blue and Yellow reservoir pressurization.

B. Reservoir filling.

On Green ground service panel:- one self-sealing connector - reservoir filling.- one self-sealing connector - reservoir filling (hand pump).

C. Ground test.

On each ground service panel:- one self-sealing connector - suction.- one self-sealing connector - delivery.

D. Accumulator charging.

On each ground service panel:- one nitrogen charging connector - Power accumulator.On Blue ground service panel:

5-4-3Page 1

Jan 01/11


- two nitrogen charging connectors - Parking/ultimate emergency brake accumulators.

NOTE : The nitrogen charging connectors for normal and alternate braking systems areinstalled on the accumulators located on the main and center landing gear legs.

**ON A/C A340-500

2. Ground service panels.




MEANHEIGHTFROM

GROUNDGreen System:(Access door 197 FB)

36.70 m(120.41 ft)

1.50 m(4.92 ft)

2.10 m(6.89 ft)

Yellow System:(Access door 196 PB)

31.40 m(103.02 ft)

1.70 m(5.58 ft)

1.80 m(5.91 ft)

Blue System:(Access door 195 MB)

28.85 m(94.65 ft)

1.50 m(4.92 ft)

1.75 m(5.74 ft)

A. Reservoir pressurization.

On Blue ground service panel:- one self-sealing connector - Green reservoir pressurization.- one self-sealing connector - Blue and Yellow reservoir pressurization.

B. Reservoir filling.

On Green ground service panel:- one self-sealing connector - reservoir filling.- one self-sealing connector - reservoir filling (hand pump).

C. Ground test.

On each ground service panel:- one self-sealing connector - suction.- one self-sealing connector - delivery.

D. Accumulator charging.

On each ground service panel:- one nitrogen charging connector - Power accumulator.On Blue ground service panel:

5-4-3Page 2

Jan 01/11


- two nitrogen charging connectors - Parking/ultimate emergency brake accumulators.

NOTE : The nitrogen charging connectors for normal and alternate braking systems areinstalled on the accumulators located on the main and center landing gear legs.

5-4-3Page 3

Jan 01/11


5-4-4 Electrical System

**ON A/C A340-500 A340-600

Electrical System

1. Electrical System.


FROM AIRPLANE CENTERLINEAFT OF NOSE

R SIDE L SIDE

MEAN HEIGHTFROM

GROUND

A/C External Power:(Access door 121 EL)

7.00 m(22.97 ft) on centerline

2.00 m(6.56 ft)

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

B. Power supply:- three phase, 400 Hz, 115/200V.

5-4-4Page 1

Jan 01/11


5-4-5 Oxygen System

**ON A/C A340-500 A340-600

Oxygen System

1. Replenishment of high pressure oxygen source.

A. For the A340-500/600 aircraft (basic version), the oxygen source is replenished by replacing theoxygen cylinder installed in the avionics compartment.

5-4-5Page 1

Jan 01/11


5-4-6 Fuel System

**ON A/C A340-500 A340-600

Fuel System

**ON A/C A340-600

1. Refuel/defuel couplings



R SIDE L SIDE

MEAN HEIGHTFROM

GROUND

Refuel/defuel coupling,left:(Access door 522 HB)

37.10 m(121.71 ft)

12.60 m(41.33 ft)

5.00 m(16.40 ft)

Refuel/defuel coupling,right:(Access door 622 HB)

37.10 m(121.72 ft)

12.60 m(41.34 ft)

5.00 m(16.40 ft)

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

B. Refuel/Defuel pressure/suction:- max. pressure: 3.45 bar (50.00 psi).- max. suction: 0.75 bar (11.00 psi).

C. Flow rate:- 2 couplings (total/minute): 1576 l (416.34 US gal).- 4 couplings (total/minute): 1438 l (379.88 US gal).

2. Refuel/defuel control panel.



R SIDE L SIDE

MEAN HEIGHTFROM

GROUND

Refuel/defuel controlpanel:(Access door 198 FB)

42.50 m(139.44 ft)

1.40 m(4.59 ft)

2.00 m(6.56 ft)

5-4-6Page 1

Jan 01/11


**ON A/C A340-500

3. Refuel/defuel couplings



R SIDE L SIDE

MEAN HEIGHTFROM

GROUND

Refuel/defuel coupling,left:(Access door 522 HB)

31.40 m(103.02 ft)

12.60 m(41.33 ft)

5.00 m(16.40 ft)

Refuel/defuel coupling,right:(Access door 622 HB)

31.40 m(103.02 ft)

12.60 m(41.33 ft)

5.00 m(16.40 ft)

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

B. Refuel/Defuel pressure/suction:- max. pressure: 3.45 bar (50.00 psi).- max. suction: 0.75 bar (11.00 psi).

C. Flow rate:- 2 couplings (total/minute): 1576 l (416.34 US gal).- 4 couplings (total/minute): 1438 l (379.88 US gal).

4. Refuel/defuel control panel.



R SIDE L SIDE

MEAN HEIGHTFROM

GROUND

Refuel/defuel controlpanel:(Access door 198 FB)

37.20 m(122.05 ft)

1.40 m(4.59 ft)

2.00 m(6.56 ft)

5-4-6Page 2

Jan 01/11


5-4-7 Pneumatic System

**ON A/C A340-500 A340-600

Pneumatic System

**ON A/C A340-600

1. High Pressure Connectors.




MEANHEIGHTFROM

GROUND

Access door 193 DB:29.71 m(97.47 ft)

0.35 m(1.15 ft)

1.75 m(5.74 ft)

A. Connectors:- two standard MS33740, 3 in.

2. Low Pressure Connectors.




MEANHEIGHTFROM

GROUND

Access door 193 BB:28.75 m(94.32 ft) on centerline

1.80 m(5.91 ft)

Access door 193 GB:28.75 m(94.32 ft)

0.63 m(2.07 ft)

1.80 m(5.91 ft)

A. Connectors:- two standard SAE AS4262 type ″B″, 8 in.

**ON A/C A340-500

3. High Pressure Connectors.

5-4-7Page 1

Jan 01/11





MEANHEIGHTFROM

GROUND

Access door 193 DB:23.41 m(76.80 ft)

0.35 m(1.15 ft)

1.75 m(5.74 ft)

A. Connectors:- two standard MS33740, 3 in.

4. Low Pressure Connectors.




MEANHEIGHTFROM

GROUND

Access door 193 BB:23.45 m(76.94 ft) on centerline

1.80 m(5.91 ft)

Access door 193 GB:23.45 m(76.94 ft)

0.63 m(2.07 ft)

1.80 m(5.91 ft)

A. Connectors:- two standard SAE AS4262 type ″B″, 8 in.

5-4-7Page 2

Jan 01/11


5-4-8 Potable Water System

**ON A/C A340-500 A340-600

Potable Water System

**ON A/C A340-600

1. Potable Water Ground Service Panel.




MEANHEIGHTFROM

GROUND

Access door 164 AR:58.75 m(192.75 ft)

0.50 m(1.64 ft)

3.50 m(11.48 ft)

A. Connectors:- Roylin, 3/4 in.

B. Capacity (three tanks - standard configuration):- 1070 l (283 US gal).

C. Filling pressure:- 1.72 bar (24.95 psi)/2.07 bar (30.02 psi).

D. Flow rate:- 87.5 l/min (23.1 US gal/min).

**ON A/C A340-500

2. Potable Water Ground Service Panel.




MEANHEIGHTFROM

GROUND

Access door 164 AR:51.32 m(168.37 ft)

0.50 m(1.64 ft)

3.50 m(11.48 ft)

5-4-8Page 1

Jan 01/11


A. Connectors:- Roylin, 3/4 in.

B. Capacity (two tanks - standard configuration):- 700 l (185 US gal).

C. Filling pressure:- 1.72 bar (24.95 psi)/2.07 bar (30.02 psi).


5-4-8Page 2

Jan 01/11


5-4-9 Oil System

**ON A/C A340-500 A340-600

Oil System

**ON A/C A340-600

1. Engine Oil Replenishment:

One gravity filling cap and one pressure filling connection per engine.



R SIDE L SIDE

MEANHEIGHT FROM

GROUND

Engine 1 (access door 416BR):

36.30 m(119.09 ft)

17.85 m(58.56 ft)

3.15 m(10.33 ft)


29.70 m(97.44 ft)

7.95 m(26.08 ft)

1.60 m(5.25 ft)


29.70 m(97.44 ft)

10.80 m(35.43 ft)

1.60 m(5.25 ft)


36.30 m(119.09 ft)

20.70 m(67.91 ft)

3.15 m(10.33 ft)

A. Engine oil replenishment:- one gravity filling cap.

B. Approximate tank capacity:- full level: 23.20 l (6.13 US gal).- usable: 15.90 l (4.20 US gal).

**ON A/C A340-500

2. Engine Oil Replenishment:

One gravity filling cap and one pressure filling connection per engine.

5-4-9Page 1

Jan 01/11




R SIDE L SIDE

MEANHEIGHT FROM

GROUND


31.00 m(101.71 ft)

17.85 m(58.56 ft)

3.15 m(10.33 ft)


24.42 m(80.12 ft)

7.95 m(26.08 ft)

1.60 m(5.25 ft)


24.42 m(80.12 ft)

10.80 m(35.43 ft)

1.60 m(5.25 ft)


31.00 m(101.71 ft)

20.70 m(67.91 ft)

3.15 m(10.33 ft)

A. Engine oil replenishment:- one gravity filling cap.

B. Approximate tank capacity:- full level: 23.20 l (6.13 US gal).- usable: 15.90 l (4.20 US gal).

**ON A/C A340-600

3. IDG Oil Replenishment:

One pressure filling connection per engine.



R SIDE L SIDE

MEANHEIGHT FROM

GROUND

Engine 1 (access door 415CL):

36.97 m(121.29 ft)

19.66 m(64.50 ft)

1.85 m(6.07 ft)


30.36 m(99.61 ft)

9.76 m(32.02 ft)

0.80 m(2.62 ft)


30.36 m(99.61 ft)

8.98 m(29.46 ft)

0.80 m(2.62 ft)


36.97 m(121.29 ft)

18.87 m(61.91 ft)

1.85 m(6.07 ft)

5-4-9Page 2

Jan 01/11


A. IDG oil replenishment:- one ozone self-sealing pressure fill and overfill connector.

B. Max. delivery pressure:- 2.41 bar (34.95 psi).

C. Approximate max. oil capacity of the IDG:- 7.00 l (1.85 US gal).

**ON A/C A340-500

4. IDG Oil Replenishment:

One pressure filling connection per engine.



R SIDE L SIDE

MEANHEIGHT FROM

GROUND


31.66 m(103.87 ft)

19.66 m(64.50 ft)

1.85 m(6.07 ft)


25.05 m(82.19 ft)

9.76 m(32.02 ft)

0.80 m(2.62 ft)


25.05 m(82.19 ft)

8.98 m(29.46 ft)

0.80 m(2.62 ft)


31.66 m(103.87 ft)

18.87 m(61.91 ft)

1.85 m(6.07 ft)

A. IDG oil replenishment:- one ozone self-sealing pressure fill and overfill connector.

B. Max. delivery pressure:- 2.41 bar (34.95 psi).

C. Approximate max. oil capacity of the IDG:- 7.00 l (1.85 US gal).

**ON A/C A340-600

5. Starter Oil Replenishment:

One filling connection per engine.

5-4-9Page 3

Jan 01/11




R SIDE L SIDE

MEANHEIGHT FROM

GROUND

Engine 1:36.30 m(119.09 ft)

19.72 m(64.70 ft)

1.80 m(5.91 ft)

Engine 2:29.70 m(97.44 ft)

9.82 m(32.22 ft)

0.77 m(2.53 ft)

Engine 3:29.70 m(97.44 ft)

8.92 m(29.27 ft)

0.77 m(2.53 ft)

Engine 4:36.30 m(119.09 ft)

18.82 m(61.75 ft)

1.80 m(5.91 ft)

A. Pneumatic starter, oil replenishment:- one gravity filling plug.

B. Approximate max. oil capacity of the starter:- 355 cc (12 fl.oz).

**ON A/C A340-500

6. Starter Oil Replenishment:

One filling connection per engine.



R SIDE L SIDE

MEANHEIGHT FROM

GROUND

Engine 1:31.00 m(101.71 ft)

19.72 m(64.70 ft)

1.80 m(5.91 ft)

Engine 2:24.42 m(80.12 ft)

9.82 m(32.22 ft)

0.77 m(2.53 ft)

Engine 3:24.42 m(80.12 ft)

8.92 m(29.27 ft)

0.77 m(2.53 ft)

Engine 4:31.00 m(101.71 ft)

18.82 m(61.75 ft)

1.80 m(5.91 ft)

5-4-9Page 4

Jan 01/11


A. Pneumatic starter, oil replenishment:- one gravity filling plug.

B. Approximate max. oil capacity of the starter:- 355 cc (12 fl.oz).

5-4-9Page 5

Jan 01/11


**ON A/C A340-500 A340-600

F_AC_050409_1_0110101_01_00

B

OILFILLER

CAP

OIL LEVELSIGHT GLASS

OILTANK

B

A

FULL FULL

LIT

RE

S R

EQ

UIR

ED

US

QU

AR

TS

RE

QU

IRE

D

5

4

3

2

1

5

4

3

2

1

A

Ground Service ConnectionsEngine Oil Tank - RR TRENT 500 series engine

FIGURE 1

5-4-9Page 6

Jan 01/11


**ON A/C A340-500 A340-600

OIL LEVELSIGHT GLASS

OVERFILLDRAIN

CONNECTOR

IDG

RED

YELLOW

GREEN

RED

A

B

A340

OVER FULL

ADDOIL

ADDOIL

PRESSUREFILL

CONNECTOR

F_AC_050409_1_0120101_01_00

A

B

Ground Service ConnectionsIDG Oil Tank - RR TRENT 500 series engine

FIGURE 2

5-4-9Page 7

Jan 01/11


**ON A/C A340-500 A340-600

PNEUMATIC STARTER

OIL FILLPLUG

EXTERNALGEARBOXMODULE

OIL LEVELOVERFLOW

PLUG

MAGNETIC CHIPDETECTOR

DRAINPLUG

A

AF_AC_050409_1_0130101_01_00

Ground Service ConnectionsStarter Oil Tank - RR TRENT 500 series engine

FIGURE 3

5-4-9Page 8

Jan 01/11


**ON A/C A340-500 A340-600

APU Oil System

**ON A/C A340-600

1. APU Oil System.

APU oil gravity filling cap.


AFT OF NOSE

FROM AIRPLANECENTERLINE(LEFT HAND)

MEAN HEIGHT FROMGROUND

APU Oil Replenishment:71.00 m(232.94 ft)

0.40 m(1.31 ft)

8.00 m(26.25 ft)

A. Tank capacity (usable):- APU Type: 331-350: 7.30 l (1.93 US gal).- APU Type: 331-600: 11.00 l (2.91 US gal).

**ON A/C A340-500

2. APU Oil System.

APU oil gravity filling cap.


AFT OF NOSE

FROM AIRPLANECENTERLINE(LEFT HAND)

MEAN HEIGHT FROMGROUND

APU Oil Replenishment:63.50 m(208.33 ft)

0.40 m(1.31 ft)

8.00 m(26.25 ft)

A. Tank capacity (usable):- APU Type: 331-350: 7.30 l (1.93 US gal).- APU Type: 331-600: 11.00 l (2.91 US gal).

5-4-9Page 9

Jan 01/11


**ON A/C A340-500 A340-600

FR95

316AR

315AL

FR101

A

PRESSURE FILLOVERFLOW PORT

OIL SCUPPER

GRAVITY FILLPORT

LUBRIFICATION OIL FILTER

GENERATOR SCAVENGE OIL FILTER

OIL PUMPMODULE5100KT9

A

B

OIL FILLERCAP

OVERFLOW PORT

PRESSUREFILL PORT

OIL SIGHTGLASS

OIL SCUPPER

GRAVITY FILL PORT

B

DO NOT REMOVE OILFILLER CAP WHEN OILLEVEL IS ABOVE FULLMARK ON SIGHT GLASS

FWD

F_AC_050409_1_0140101_01_01

Ground Service ConnectionsAPU Oil Tank

FIGURE 4

5-4-9Page 10

Jan 01/11


5-4-10 Vacuum Toilet System

**ON A/C A340-500 A340-600

Vacuum Toilet System

**ON A/C A340-600

1. Vacuum Toilet System.



R SIDE L SIDE

MEAN HEIGHTFROM

GROUNDWaste Service panel:(Access door 171 AL)

67.30 m(220.80 ft)

0.10 m(0.33 ft)

4.00 m(13.12 ft)

A. Connectors:- flushing and filling: Roylin, 1 in.- draining: Roylin, 4 in.

B. Capacity (three tanks - standard configuration):- 1050 l (277.38 US gal).

C. Operating pressure:- 0.07 bar (1.02 psi)/0.70 bar (10.15 psi).


**ON A/C A340-500

2. Vacuum Toilet System.



R SIDE L SIDE

MEAN HEIGHTFROM

GROUNDWaste Service panel:(Access door 171 AL)

59.86 m(196.39 ft)

0.10 m(0.33 ft)

4.00 m(13.12 ft)

A. Connectors:- flushing and filling: Roylin, 1 in.

5-4-10Page 1

Jan 01/11


- draining: Roylin, 4 in.

B. Capacity (three tanks - standard configuration):- 1050 l (277.38 US gal).

C. Operating pressure:- 0.07 bar (1.02 psi)/0.70 bar (10.15 psi).


5-4-10Page 2

Jan 01/11


5-5-0 Engine Starting Pneumatic Requirements

**ON A/C A340-500 A340-600

Engine Starting Pneumatic Requirements

1. Engine Starting Pneumatic Requirements.

5-5-0Page 1

Jan 01/11


5-5-1 Low Temperatures

**ON A/C A340-500 A340-600

Low Temperature -40˚C (-40˚F)

1. This section provides the engine starting pneumatic requirements for a temperature of -40˚C(-40˚F).

5-5-1Page 1

Jan 01/11


**ON A/C A340-500 A340-600

0.52.5

1 2 2.5 3 3.5

5

4.5

4

3.5

3

40

50

60

70

PSI

GROUND CART FLOW(Kg/s)

BARSGROUND CART PRESSURE

F_AC_050501_1_0050101_01_00

1.5

STARTING TIME = 90 Sec




AIR TEMPERATUREGROUND CART OUTLET

0°C 85°C 100°C

220°C180°C150°C

Engine Starting Pneumatic RequirementsTemperature -40˚C (-40˚F) -- RB 211 TRENT 500 series engine

FIGURE 1

5-5-1Page 2

Jan 01/11


5-5-2 Ambient Temperatures

**ON A/C A340-500 A340-600

Ambient Temperature +15˚C (+59˚F)

1. This section provides the engine starting pneumatic requirements for a temperature of +15˚C(+59˚F).

5-5-2Page 1

Jan 01/11


**ON A/C A340-500 A340-600

20.5

2.5

1 1.5 2 2.5 3 3.5

5

4.5

4

3.5

3

30

40

50

60

70

PSI



F_AC_050502_1_0050101_01_00





0°C 85°C

180°C150°C

100°C

220°C


Engine Starting Pneumatic RequirementsTemperature +15˚C (+59˚F) -- RB 211 TRENT 500 series engine

FIGURE 1

5-5-2Page 2

Jan 01/11


5-5-3 High Temperatures

**ON A/C A340-500 A340-600

High Temperature +50˚C (122˚F)

1. This section provides the engine starting pneumatic requirements for a temperature upper +50˚C(+122˚F).

5-5-3Page 1

Jan 01/11


**ON A/C A340-500 A340-600

20.5

2.5

1 1.5 2 2.5 3 3.5

5

4.5

4

3.5

3

30

40

50

60

70

PSI



F_AC_050503_1_0050101_01_00






85°C 100°C 150°C

180°C 220°C

Engine Starting Pneumatic RequirementsTemperature +50˚C (+122˚F) -- RB 211 TRENT 500 series engine

FIGURE 1

5-5-3Page 2

Jan 01/11


5-6-0 Ground Pneumatic Power Requirements

**ON A/C A340-500 A340-600

Ground Pneumatic Power Requirements

1. Ground Pneumatic Power Requirements.

5-6-0Page 1

Jan 01/11


5-6-1 Heating

**ON A/C A340-500 A340-600

Heating

1. This section provides the ground pneumatic power requirements heating.

5-6-1Page 1

Jan 01/11


**ON A/C A340-500 A340-600

20 25 30 35 40 45 50 55 60 65 70 75 803.40

3.82

4.24

4.67

5.09

5.52

5.94

6.37

6.79

7.21

7.64

8.06

8.49

8.91

3.53

3.97

4.41

4.85

5.29

5.73

6.17

6.61

7.05

7.50

7.94

8.38

8.82

9.26

1.6

1.8

2.0

2.2

2.4

2.6

2.8

3.0

3.2

3.4

3.6

3.8

4.0

4.2

1.54

1.73

1.93

2.12

2.31

2.50

2.70

2.89

3.08

3.27

3.47

3.66

3.85

4.04

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

THIS CHART ASSUMES:− INITIAL CABIN TEMPERATURE: −23°C (−9.4°F)− TEMPERATURE AT GROUND CONNECTION: 70°C (158°F)− EMPTY CABIN− ELECTRICAL LOAD:

. A340−500: 4600 W

. A340−600: 5200 W− RECIRCULATION: ON

NOTE:

CABIN FRESHAIRFLOW

(kg/s)

TOTAL FRESHAIRFLOW

(kg/s)

TOTAL FRESHAIRFLOW

(lb/s)

CABIN FRESHAIRFLOW

(lb/s)

TOTAL FLOW INTO CONNECTORS MUST NEVER EXCEED 4.0 kg/s (8.82 lb/s)AND/OR 65 mbar (0.94 psi) AT AIRCRAFT CONNECTION.

F_AC_050601_1_0030101_01_00

A340−500

A340−600

MAXIMUM ALLOWED TOTAL AIRFLOW

Ground Pneumatic Power RequirementsHeating

FIGURE 1

5-6-1Page 2

Jan 01/11


5-6-2 Cooling

**ON A/C A340-500 A340-600

Cooling

1. This section provides the ground pneumatic power requirements cooling.

5-6-2Page 1

Jan 01/11


**ON A/C A340-500 A340-600

20 25 30 35 40 45 50 55 60 653.40

3.82

4.24

4.67

5.09

5.52

5.94

6.37

6.79

7.21

7.64

8.06

8.49

8.91

3.53

3.97

4.41

4.85

5.29

5.73

6.17

6.61

7.05

7.50

7.94

8.38

8.82

9.26

1.6

1.8

2.0

2.2

2.4

2.6

2.8

3.0

3.2

3.4

3.6

3.8

4.0

4.2

1.54

1.73

1.93

2.12

2.31

2.50

2.70

2.89

3.08

3.27

3.47

3.66

3.85

4.04

THIS CHART ASSUMES:

. A340−500: 4600 W

. A340−600: 5200 W− RECIRCULATION: ON

NOTE:

15

− INITIAL CABIN TEMPERATURE: 38°C (100.4°F)− TEMPERATURE AT GROUND CONNECTION: 1.5°C (34.7°F)− EMPTY CABIN− ELECTRICAL LOAD:

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

CABIN FRESHAIRFLOW

(kg/s)

TOTAL FRESHAIRFLOW

(kg/s)

TOTAL FRESHAIRFLOW

(lb/s)

CABIN FRESHAIRFLOW

(lb/s)


F_AC_050602_1_0030101_01_00


A340−500

A340−600

Ground Pneumatic Power RequirementsCooling

FIGURE 1

5-6-2Page 2

Jan 01/11


5-7-0 Preconditioned Airflow Requirements

**ON A/C A340-500 A340-600

Preconditioned Airflow Requirements

1. This section gives the preconditioned airflow requirements for cabin air conditioning.

The total airflow must be not more than 4 kg.s. If the total airflow is more than this value, it will bemore than the capacity of the outflow valve in the fully open position and a cabin overpressure ofmore than 65 mbar will occur.

Other Filling capacities and characteristics (hydraulic, electrical, oxygen, fuel, oil, water, toilet) areshown in chapter 5-4.

5-7-0Page 1

Jan 01/11


**ON A/C A340-500 A340-600

3.82

4.24

4.67

5.09

5.52

5.94

6.37

6.79

7.21

7.64

8.06

8.49

8.91

3.97

4.41

4.85

5.29

5.73

6.17

6.61

7.05

7.50

7.94

8.38

8.82

9.26

1.8

2.0

2.2

2.4

2.6

2.8

3.0

3.2

3.4

3.6

3.8

4.0

4.2

1.73

1.93

2.12

2.31

2.50

2.70

2.89

3.08

3.27

3.47

3.66

3.85

4.04

NOTE:

−40 −30 −20 −10 0 10 20 30 40 50 60

OA

T: 3

8°C

(100

.4°F

)

OA

T: 3

8°C

(100

.4°F

)

OA

T: 40°C (−40°F)

OA

T: −30°C (−22°F)

(−9.4°F)O

AT: −23°C

INLET TEMPERATURE (C°)

−40 −20 0 20 40 60 80 100 120 140INLET TEMPERATURE (F°)

C1 CURVE ASSUMES:

C2 CURVE ASSOMES:

C3 CURVE ASSUMES:

C4, C5 AND C6 CURVES ASSUME:

NOTE:

− SAME CONDITIONS AS C1 BUT WITH IFE OFF

− SAME CONDITIONS AS C1 BUT WITHOUT PASSENGERS

CABIN FRESHAIRFLOW

(kg/s)

TOTAL FRESHAIRFLOW

(kg/s)

TOTAL FRESHAIRFLOW

(lb/s)

CABIN FRESHAIRFLOW

(lb/s)

IFE = IN−FLIGHT ENTERTAINMENT SYSTEM.OAT = OUTSIDE AIR TEMPERATURE.

− CABIN TEMPERATURE: 27°C (80.6°F)− MAX. PASSENGER LOAD, 10 ATTENDANTS, 3 CREW MEMBERS− RECIRCULATION: ON− ELECTRICAL LOAD: 6200 W− SOLAR RADIATION: 7990 W− IFE: ON

− CABIN TEMPERATURE: 21°C (69.8°F)− NO PASSENGERS OR ATTENDANTS− RECIRCULATION: ON− ELECTRICAL LOAD: 5200 W


F_AC_050700_1_0040101_01_00

60 mbar

55 mbar

50 mbar

45 mbar

40 mbar

AT CONNECTION

AT CONNECTION

C1 C6C5C4C3C2

OA

T: 3

8°C

(10

0.4°

F)


F_AC_050700_1_0040101_01_00

Preconditioned Airflow RequirementsFIGURE 1

5-7-0Page 2

Jan 01/11


5-8-0 Ground Towing Requirements

**ON A/C A340-500 A340-600

Ground Towing Requirements

1. This section provides information on aircraft towing.

The A340 is designed with means for conventional or towbarless towing.Information/procedures can be found for both in chapter 9 of the Aircraft Maintenance Manual.Status on towbarless towing equipment qualification can be found in SIL 09-002.It is possible to tow or push the aircraft, at maximum ramp weight with engines at zero or up to idlethrust, using a tow bar attached to the nose gear leg (refer to AMM chapter 9 for conditions andlimitations). One tow bar fitting is installed at the front of the leg (optional towing fitting for towingfrom the rear of the NLG available).The Main Landing Gears have attachment points for towing or debogging (for details refer to chapter7 of the Aircraft Recovery Manual).

- The first part of this section shows the chart to determine the draw bar pull and tow tractormass requirements as function of the following physical characteristics:- aircraft weight- slope- number of engines at idle

The following chart is applicable to both A340-500 and -600 aircraft.

- The second part of this section supplies guidelines for the tow bar.

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

2. Towbar design guidelines

The aircraft towbar shall respect the following norms:- SAE AS 1614, ”Main Line Aircraft Tow Bar Attach Fitting Interface”- SAE ARP1915 Revision C, ”Aircraft Tow Bar”- ISO 8267-1, ”Aircraft - Tow bar attachment fitting - Interface requirements - Part 1: Main line

aircraft”- ISO 9667, ”Aircraft ground support equipment - Tow bars”- IATA Airport Handling Manual AHM 958, ”Functional Specification for an Aircraft Towbar”

A conventional type tow bar is required which should be equipped with a damping system to protectthe nose gear against jerks and with towing shear pins :- A traction shear pin calibrated at 40 400 daN (90 822 lbf)- A torsion pin calibrated at 4 800 m.daN (424 836 lbf.in)

5-8-0Page 1

Jan 01/11


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

There is a variety of shear pin arrangements and the values of the shear pins depend on them. Wehereafter show two arrangements classically used on towbars.

5-8-0Page 2

Jan 01/11


**ON A/C A340-500 A340-600

EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A340−500 OR −600 AT 380 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 (380 t),− FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUIRED SLOPE PERCENTAGE (1.5%),− FROM THIS 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 (1),− 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 (30.3 t),− SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE. THE OBTAINED X−COORDINATE IS THE RECOMMENDED MINIMUM TRACTOR WEIGHT (53.1 t).

F_AC_050800_1_0100101_01_00

40

25

20

15

10

5

00 10 20 30 40 50 60 70 80 0 1 2 3 4 0 0.5 1.0 1.5 2.0

390

350

310

270

230

190

150

TOTAL TRACTION WHEEL LOAD [ t ] NO OF ENGINES AT IDLE SLOPE [ % ]

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

30.3

53.1

1.5% SLOPE

HARD SNOW = 0.2

ICE = 0.05

WET C

ONCRETE

= 0.

57

DR

Y C

ON

CR

ETE

=

0.8

BREAKWAY RESISTANCE 6%# OF ENGINES ON FOR PB: 2ENGINE THRUST 876.3 daN

380 tons

2 ENGINES ON

35

30

Ground Towing RequirementsFIGURE 1

5-8-0Page 3

Jan 01/11


**ON A/C A340-500 A340-600

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

AF_AC_050800_1_0110101_01_00

Ground Towing RequirementsTypical tow bar configuration 1

FIGURE 2

5-8-0Page 4

Jan 01/11


**ON A/C A340-500 A340-600

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

40400 4800 106.9 228.1

[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

A

AF_AC_050800_1_0120101_01_00

Ground Towing RequirementsTypical tow bar configuration 2

FIGURE 3

5-8-0Page 5

Jan 01/11


**ON A/C A340-500 A340-600

H

MAKE SURE THAT THE DIMENSION "H" OF THE NLG IS NEVER GREATER THAN 310 mm (12.2047 in.) WHEN YOU TOW THE AIRCRAFT.

F_AC_050800_1_0130101_01_00

Ground Towing RequirementsMaximum Extension of the NLG Shock Absorber

FIGURE 4

5-8-0Page 6

Jan 01/11


OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

**ON A/C A340-500 A340-600

Engine Exhaust Velocities and Temperatures

1. GeneralThis section shows the estimated engine exhaust efflux velocities and temperatures contours forGround Idle, Breakaway, Maximum Takeoff conditions.

6-1-0Page 1

Jan 01/11


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

**ON A/C A340-500 A340-600

Engine Exhaust Velocities Contours - Ground Idle Power

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

6-1-1Page 1

Jan 01/11


**ON A/C A340-500 A340-600

150 fps 100 fps 50 fps

FEET

METERS

50 100 150

15 30 450

0



m ft

10

5

40

30

20

10

m ft

10

5

40

30

10

20

0

0

PLAN

ELEVATION

LOW IDLE POWER (100 fps = 68 mph = 109 kmph)

F_AC_060101_1_0050101_01_00

Engine Exhaust VelocitiesGround Idle Power - RR TRENT 500 series engine

FIGURE 1

6-1-1Page 2

Jan 01/11


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

**ON A/C A340-500 A340-600

Engine Exhaust Temperatures Contours - Ground Idle Power

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

6-1-2Page 1

Jan 01/11


**ON A/C A340-500 A340-600

LOW IDLE POWER

50°C(122°F)

40°C(104°F)

30°C(86°F)

FEET

METERS

50 100 150

15 30 450

0

ft

m ft

10

5

40

30

10

20

0

PLAN

ELEVATION

40°C

30°C(86°F)

40°C(104°F)

30°C(86°F)

50°C(122°F)

F_AC_060102_1_0050101_01_00

50°C(122°F)

(104°F)

40

30

20

10

0

10

5

m

Engine Exhaust TemperaturesGround Idle Power - RR TRENT 500 series engine

FIGURE 1

6-1-2Page 2

Jan 01/11


6-1-3 Engine Exhaust Velocities Contours - Breakaway Power

**ON A/C A340-500 A340-600

Engine Exhaust Velocities Contours - Breakaway Power

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

6-1-3Page 1

Jan 01/11


**ON A/C A340-500 A340-600

50 fps100 fps

ELEVATION

20

80m ft

20

60

15

10

5

m ft40

10

5

0

METERS

FEET

0 15 30 45

15010050

60 75 90

200 250 300

BREAKAWAY POWER (100 fps = 60 mph = 109 Kmph)

PLAN

F_AC_060103_1_0050101_01_00

150 fps 50 fps100 fps

150 fps

40

20

0

0

Engine Exhaust VelocitiesBreakaway Power - RR TRENT 500 series engine

FIGURE 1

6-1-3Page 2

Jan 01/11


6-1-4 Engine Exhaust Temperatures Contours - Breakaway Power

**ON A/C A340-500 A340-600

Engine Exhaust Temperatures Contours - Breakaway Power

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

6-1-4Page 1

Jan 01/11


**ON A/C A340-500 A340-600

40°C(104°F)

30°C(86°F)

50°C(122°F)

0

METERS

FEET

0 15 30

10050

ELEVATION

BREAKAWAY POWER

PLAN

50°C(122°F)

40°C(104°F) (86°F)

F_AC_060104_1_0050101_01_00

m ft40

10

5

m

15

10

5

0

20

0

30°C

20

60

40

ft

Engine Exhaust TemperaturesBreakaway Power - RR TRENT 500 series engine

FIGURE 1

6-1-4Page 2

Jan 01/11


6-1-5 Engine Exhaust Velocities Contours - Takeoff Power

**ON A/C A340-500 A340-600

Engine Exhaust Velocities Contours - Takeoff Power

1. This section gives engine exhaust velocities contours at takeoff power.

6-1-5Page 1

Jan 01/11


**ON A/C A340-500 A340-600

MA

X T

AK

E−

OF

F P

OW

ER

(10

0 fp

s =

68

mph

= 1

09 k

mph

)

105

350

90 300

75 250

60 200

45 150

30 100

15 50

0 0

ME

TE

RS

FE

ET

mft 80 60 40 20

5101520

(162

0 ft)

494

mT

O

(600

ft)

183

mT

O

50 fp

s10

0 fp

s15

0 fp

s

PLA

N

F_AC_060105_1_0050101_01_00

0

Engine Exhaust VelocitiesTakeoff Power - RR TRENT 500 series engine

FIGURE 1

6-1-5Page 2

Jan 01/11


6-1-6 Engine Exhaust Temperatures Contours - Takeoff Power

**ON A/C A340-500 A340-600

Engine Exhaust Temperatures Contours - Takeoff Power

1. This section gives engine exhaust temperatures contours at takeoff power.

6-1-6Page 1

Jan 01/11


**ON A/C A340-500 A340-600

m ft

20

40

60

15

10

5

0

METERS

FEET

0 15 30 45

15010050

60 75 90

200 250 300

(122°F)

PLAN

50°C(104°F)40°C

(86°F)30°C

MAX TAKE−OFF POWER

0

F_AC_060106_1_0050101_01_00

Engine Exhaust TemperaturesTakeoff Power - RR TRENT 500 series engine

FIGURE 1

6-1-6Page 2

Jan 01/11


6-2-0 Airport and Community Noise

**ON A/C A340-500 A340-600

Airport and Community Noise Data

1. Airport and Community Noise Data

This section gives data concerning engine maintenance run-up noise to permit evaluation of possibleattenuation requirements.

6-2-0Page 1

Jan 01/11


6-2-1 Noise Data

**ON A/C A340-500 A340-600

Noise Data

1. Noise Data for RR TRENT 500 series engine

A. Description of test conditions:

The arc of circle (radius = 60 m (196.85 ft)), with microphones 1.2 m (3.94 ft) high, iscentered on the position of the noise reference point.A.P.U.: off; E.C.S.: Packs off.

B. Engine parameters:- 4 engines running: ground idle- 2 engines running: max thrust possible on brakes

C. Meteorological data:

The meteorological parameters measured 1.6 m (5.25 ft) from the ground on the day of testwere as follows:- Temperature: 20˚C (68˚F)- Relative humidity: 78%- Atmospheric pressure: 1013 hPa- Wind speed: Negligible- No rain

6-2-1Page 1

Jan 01/11


**ON A/C A340-500 A340-600

7880

8284

8688

9294

96

0°10°

20°

30°

40°

50°

60°

70°

80°

90°

100°

110°

120°

130°

140°

150°

98100

102104

106108

110

350°340°

330°

320°

310°

300°

290°

280°

270°

250°

240°

230°

220°

210°

NOISE REFERENCEPOINT

N1

CURVE

GROUND IDLE4 ENGINES RUNNING

E.P.R. 1.33

18% 82%

MAX THRUST POSSIBLEON BRAKES

2 ENGINES RUNNING

112114

116118

260°

1.004

90

F_AC_060201_1_0050101_01_00

Airport and Community NoiseRR TRENT 500 series engine

FIGURE 1

6-2-1Page 2

Jan 01/11


6-3-0 Danger Areas of Engines

**ON A/C A340-500 A340-600

Danger Areas of Engines

1. Danger Areas of the Engines.

6-3-0Page 1

Jan 01/11


6-3-1 Ground Idle Power

**ON A/C A340-500 A340-600

Ground Idle Power

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

6-3-1Page 1

Jan 01/11


**ON A/C A340-500 A340-600

(25 ft)7,6 m

(3 ft 8 in)1,1 m

30°TO 48,8 m (160 ft) AFT OF EXHAUST NOZZLES

INTAKE SUCTION DANGER AREA MINIMUM IDLE POWER

EXHAUST DANGER AREA

ENTRY CORRIDOR

DEF0004201A

F_AC_060301_1_0050101_01_00

Danger Areas of EnginesRR TRENT 500 series engine

FIGURE 1

6-3-1Page 2

Jan 01/11


6-3-2 Breakaway Power

**ON A/C A340-500 A340-600

Breakaway Power

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

6-3-2Page 1

Jan 01/11


**ON A/C A340-500 A340-600

(25 ft)7,6 m

30°TO 82.3 m (270 ft) AFT OF EXHAUST NOZZLES

INTAKE SUCTION DANGER AREA BREAKWAY POWER

EXHAUST DANGER AREA

F_AC_060302_1_0050101_01_00


FIGURE 1

6-3-2Page 2

Jan 01/11


6-3-3 Takeoff Power

**ON A/C A340-500 A340-600

Takeoff Power

1. This section gives danger areas of the engines at max takeoff conditions.

6-3-3Page 1

Jan 01/11


**ON A/C A340-500 A340-600

(25 ft)7,6 m

30°TO 490,7 m (1610 ft) AFT OF EXHAUST NOZZLES

INTAKE SUCTION DANGER AREA MAX TAKE−OFF

EXHAUST DANGER AREA

F_AC_060303_1_0050101_01_00


FIGURE 1

6-3-3Page 2

Jan 01/11


6-4-0 APU Exhaust Velocities and Temperatures

**ON A/C A340-500 A340-600

APU Exhaust Velocities and Temperatures

1. APU Exhaust Velocities and Temperatures.

6-4-0Page 1

Jan 01/11


6-4-1 APU

**ON A/C A340-500 A340-600

APU - GARRETT

1. This section gives APU exhaust velocities and temperatures.

6-4-1Page 1

Jan 01/11


**ON A/C A340-500 A340-600

20

METERS

0

5 10 15FEET

0

10 20 30 40 50

0

60

0

20

METERS

0

5 10 15FEET

0

10 20 30 40 50

0

60

0

10

5

10

20

30

40

METERS FEET50

15 m/s(50 ft/s)18 m/s

(60 ft/s)24 m/s(80 ft/s)

30.5 m/s(100 ft/s)

46 m/s(150 ft/s)

61 m/s(200 ft/s)

10

5

10

20

30

40

METERS FEET50

93°C(200°F)121°C

(250°F)

149°C(300°F)

177°C(350°F)

204°C(400°F)

260°C(500°F)

315.5°C(600°F)

427°C(800°F)

15

15

F_AC_060401_1_0030101_01_00

Exhaust Velocities and TemperaturesGARRETT GTCP 331-600 (A)

FIGURE 1

6-4-1Page 2

Jan 01/11


PAVEMENT DATA


**ON A/C A340-500 A340-600

General Information

1. General Information

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

To help in the interpolation between the discrete values shown, each airplane configuration is shownwith a minimum range of five loads on the main landing gear.

All curves on the charts represent data at a constant specified tire pressure with:- the airplane loaded to the maximum ramp weight- the CG at its maximum permissible aft position.Pavement requirements for commercial airplanes are derived from the static analysis of loads imposedon the main landing gear struts.

Section 7-2-0, presents basic data on the landing gear footprint configuration, maximum rampweights and tire sizes and pressures.

Section 7-3-0, shows maximum vertical and horizontal pavement loads for certain critical conditionsat the tire-ground interfaces.

Section 7-4, contains charts to find these loads throughout the stability limits of the airplane at reston the pavement.

These main landing gear loads are used as the point of entry to the pavement design charts whichfollow, interpolating load values where necessary.

Section 7-5-1 uses procedures in Instruction Report No S-77-1 ”Procedures for Development of CBRDesign Curves”, dated June 1977 and as modified according to the methods described in ICAOAerodrome Design Manual, Part 3.

Pavements, 2nd Edition, 1983, Section 1.1 (The ACN-PCN Method), and utilizing the alpha factorsapproved by ICAO in October 2007.

The report was prepared by the U. S. Army Corps Engineers Waterways Experiment Station, Soilsand Pavement Laboratory, Vicksburg, Mississipi.The line showing 10 000 coverages is used to calculate Aircraft Classification Number (ACN)

7-1-0Page 1

Jan 01/11


The flexible pavement charts in Section 7-6-1 show LCN against equivalent single wheel load, andequivalent single wheel load against pavement thickness.

The rigid pavement charts in Section 7-8-2 shown LCN against equivalent single wheel load, andequivalent single wheel load against radius of relative stiffness.

Section 7-9-0 provides ACN data prepared according to the ACN/PCN system as referenced in ICAOAnnex 14, ”Aerodromes”, Volume 1 ”Aerodrome Design and Operations” Fourth Edition July 2004,incorporating Amendments 1 to 6.

The ACN/PCN system provides a standardized international airplane/pavement rating systemreplacing the various S, T, TT, LCN, AUW, ISWL, etc... rating systems used throughout the world.

ACN is the Aircraft Classification Number and PCN is the corresponding Pavement ClassificationNumber.

An aircraft having an ACN equal to or less than the PCN can operate without restriction on thepavement.

Numerically the ACN is two times the derived single wheel load expressed in thousands of kilograms.

The derived single wheel load is defined as the load on a single tire inflated to 1.25 Mpa (181 psi)that would have the same pavement requirements as the aircraft.

Computationally the ACN/PCN system uses PCA program PDILB for rigid pavements and S-77-1 forflexible pavements to calculate ACN values. The Airport Authority must decide on the method ofpavement analysis and the results of their evaluation shown as follows:

PCNPAVEMENT

TYPESUBGRADECATEGORY

TIRE PRESSURE CATEGORY EVALUATION METHOD

R -- Rigid A -- High W -- No Limit T -- Technical

F -- Flexible B -- Medium X -- To 1.5 Mpa (217 psi) U -- Using Aircraft

C -- Low Y -- To 1.0 Mpa (145 psi)

D -- Ultra Low Z -- To 0.5 Mpa (73 psi)

Section 7-9-1 shows the aircraft ACN values for flexible pavements.

The four subgrade categories are:- A. High Strength CBR 15- B. Medium Strength CBR 10

7-1-0Page 2

Jan 01/11


- C. Low Strength CBR 6- D. Ultra Low Strength CBR 3

Section 7-9-2 shows the aircraft ACN for rigid pavements.

The four subgrade categories are:- A. High Strength Subgrade k = 150 MN/m3 (550 pci)- B. Medium Strength Subgrade k = 80 MN/m3 (300 pci)- C. Low Strength Subgrade k = 40 MN/m3 (150 pci)- D. Ultra Low Strength Subgrade k = 20 MN/m3 (75 pci)

A. Flexible Pavement

The procedure that follows is used to develop flexible pavement design curves such as thoseshown in Section 7-5-1.- With the scale for pavement thickness at the bottom and the scale for CBR at the top, an

arbitrary line is drawn representing 10 000 coverages.- Incremental values of the weight on the main landing gear are then plotted.- Annual departure lines are drawn based on the load lines of the weight on the main landing

gear that is shown on the graph.Sextion 7-7-1 gives the rigid pavement design curves that have been prepared with the use ofthe Westergaard Equation. This is in general accordance with the procedures outlined in thePortland Cement Association Publications, ”Design of Concrete Airport Pavement”, 1973 and”Computer Program for Airport Pavement Design”, (Program PDILB), 1967 both by Robert G.Packard.

B. Rigid pavement

The procedure that follows is used to develop rigid pavement design curves such as those shownin Section 7-7-1.- With the scale for pavement thickness on the left and the scale for allowable working stress

on the right, an arbitrary line load line is drawn. This represents the main landing gearmaximum weight to be shown.

- All values of the subgrade modulus (k values) are then plotted.- Additional load lines for the incremental values of weight on the main landing gear are

drawn on the basis of the curve for k = 80 MN/m3 already established.All Load Classification Number (LCN) curves shown in Section 7-6-1 and Section 7-8-2 havebeen developed from a computer program based on data provided in International Civil AviationOrganisation (ICAO) document 7920-AN/865/2, Aerodrome Manual, Part 2, ”AerodromePhysical Characteristics”, Second Edition, 1965.

7-1-0Page 3

Jan 01/11


7-2-0 Landing Gear Footprint


Landing Gear Footprint

1. This section gives Landing Gear Footprint and Aircraft Identification.

7-2-0Page 1

Jan 01/11



32 889 mm (107 ft 10.8 in)

33 637 mm (110 ft 4.3 in)

10 684 mm(35 ft 0.6 in)

1 981 mm(78 in)

1 397 mm(55 in)

1 981 mm(78 in)

NOTE: DIMENSIONS IN MILLIMETERS(FEET AND INCHES IN BRACKETS)

1 176 mm(46 in)

814 mm(32 in)

WING GEAR TIRE SIZE 1 400x530R23 40PR

WING GEAR TIRE PRESSURE 16.1 bar (234 psi)

NOSE TIRE SIZE 45x18R17 36PR

NOSE TIRE PRESSURE 13.7 bar (199 psi)

PERCENTAGE OF WEIGHT ON MAIN GEAR GROUP

MAXIMUM RAMP WEIGHT 366 200 kg (807 330 lb)

CENTER GEAR TIRE SIZE

CENTER GEAR TIRE PRESSURE

1 400x530R23 40PR

15 bar (218 psi)

F_AC_070200_1_0320101_01_01

See Section 7−4−1 Figure: Landing Gear Loading onPavement − MTOW 365 000 kg − A340−600 WV0xx

Landing Gear FootprintMTOW 365 000 kg

FIGURE 1

7-2-0Page 2

Jan 01/11



32 889 mm (107 ft 10.8 in)

33 637 mm (110 ft 4.3 in)

10 684 mm(35 ft 0.6 in)

1 981 mm

(78 in)

1 397 mm(55 in)

1 981 mm

(78 in)NOTE: DIMENSIONS IN MILLIMETERS(FEET AND INCHES IN BRACKETS)

1 176 mm(46 in)

814 mm(32 in)

WING GEAR TIRE SIZE 1 400x530R23 40PR

WING GEAR TIRE PRESSURE 16.1 bar (234 psi)

NOSE TIRE SIZE 45x18R17 36PR

NOSE TIRE PRESSURE 13.7 bar (199 psi)


MAXIMUM RAMP WEIGHT 369 200 kg (813 950 lb)



1 400x530R23 40PR

15 bar (218 psi)

F_AC_070200_1_0330101_01_01



FIGURE 2

7-2-0Page 3

Jan 01/11



MAXIMUM RAMP WEIGHT

PERCENTAGE OF WEIGHTON MAIN GEAR GROUP

NOSE TIRE SIZE

NOSE TIRE PRESSURE

WING GEAR TIRE SIZE

WING GEAR TIRE PRESSURE



366 200 kg (807 330 lb)

45x18R17 36PR

13.9 bar (201 psi)

1 400x530R23 40PR

16.1 bar (234 psi)

1 400x530R23 40PR

16.1 bar (234 psi)

32 889 mm (107 ft 10.8 in)

33 637 mm (110 ft 4.3 in)

10 684 mm(35 ft 0.6 in)

1 981 mm

(78 in)

1 397 mm(55 in)

1 981 mm

(78 in)


814 mm(32 in)

1 176 mm(46 in)

F_AC_070200_1_0420101_01_00



FIGURE 3

7-2-0Page 4

Jan 01/11



32 889 mm (107 ft 10.8 in)

33 637 mm (110 ft 4.3 in)

10 684 mm(35 ft 0.6 in)

1 981 mm

(78 in)

1 397 mm(55 in)

1 981 mm

(78 in)

MAXIMUM RAMP WEIGHT


NOSE TIRE SIZE

NOSE TIRE PRESSURE

WING GEAR TIRE SIZE




381 200 kg (840 400 lb)

45x18R17 36PR

13.9 bar (201 psi)

1 400x530R23 40PR

16.1 bar (234 psi)

1 400x530R23 40PR

16.1 bar (234 psi)


1 176 mm(46 in)

814 mm(32 in)

F_AC_070200_1_0430101_01_00



FIGURE 4

7-2-0Page 5

Jan 01/11



MAXIMUM RAMP WEIGHT


NOSE GEAR TIRE SIZE

NOSE GEAR TIRE PRESSURE

WING GEAR TIRE SIZE




369 200 kg (813 950 lb)

45x18R17 36PR

14.1 bar (205 psi)

1 400x530R23 40PR

16.1 bar (234 psi)

1 400x530R23 40PR

15 bar (218 psi)

27 589 mm (90 ft 6.2 in)

28 337 mm (92 ft 11.6 in)

10 684 mm(35 ft 0.6 in)

1 981 mm

(78 in)

1 397 mm(55 in)

1 981 mm

(78 in)


(32 in)1 176 mm

(46 in)814 mm

F_AC_070200_1_0440101_01_00



FIGURE 5

7-2-0Page 6

Jan 01/11



MAXIMUM RAMP WEIGHT


NOSE GEAR TIRE SIZE


WING GEAR TIRE SIZE




373 200 kg (822 775 lb)

45x18R17 36PR

14.1 bar (205 psi)

1 400x530R23 40PR

16.1 bar (234 psi)

1 400x530R23 40PR

15 bar (218 psi)

27 589 mm (90 ft 6.2 in)

28 337 mm (92 ft 11.6 in)

10 684 mm(35 ft 0.6 in)

1 981 mm

(78 in)

1 397 mm(55 in)

1 981 mm

(78 in)


1 176 mm(46 in)

814 mm(32 in)

F_AC_070200_1_0450101_01_00



FIGURE 6

7-2-0Page 7

Jan 01/11



MAXIMUM RAMP WEIGHT


NOSE GEAR TIRE SIZE


WING GEAR TIRE SIZE




375 200 kg (827 175 lb)

45x18R17 36PR

14.1 bar (205 psi)

1 400x530R23 40PR

16.1 bar (234 psi)

1 400x530R23 40PR

15 bar (218 psi)

27 589 mm (90 ft 6.2 in)

28 337 mm (92 ft 11.6 in)

10 684 mm(35 ft 0.6 in)

1 981 mm

(78 in)

1 397 mm(55 in)

1 981 mm

(78 in)


1 176 mm(46 in)

814 mm(32 in)

F_AC_070200_1_0460101_01_00



FIGURE 7

7-2-0Page 8

Jan 01/11



27 589 mm (90 ft 6.2 in)

28 337 mm (92 ft 11.6 in)

10 684 mm(35 ft 0.6 in)

1 981 mm

(78 in)

1 397 mm(55 in)

1 981 mm

(78 in)


MAXIMUM RAMP WEIGHT


NOSE GEAR TIRE SIZE


WING GEAR TIRE SIZE




373 200 kg (822 775 lb)

45x18R17 36PR

14.1 bar (205 psi)

1 400x530R23 40PR

16.1 bar (234 psi)

1 400x530R23 40PR

16.1 bar (234 psi)

1 176 mm(46 in)

814 mm(32 in)

F_AC_070200_1_0470101_01_00



FIGURE 8

7-2-0Page 9

Jan 01/11



MAXIMUM RAMP WEIGHT


NOSE GEAR TIRE SIZE


WING GEAR TIRE SIZE




381 200 kg (840 400 lb)

45x18R17 36PR

14.1 bar (205 psi)

1 400x530R23 40PR

16.1 bar (234 psi)

1 400x530R23 40PR

16.1 bar (234 psi)

27 589 mm (90 ft 6.2 in)

28 337 mm (92 ft 11.6 in)

10 684 mm(35 ft 0.6 in)

1 981 mm

(78 in)

1 397 mm(55 in)

1 981 mm

(78 in)


1 176 mm(46 in)

814 mm(32 in)

F_AC_070200_1_0480101_01_00



FIGURE 9

7-2-0Page 10

Jan 01/11


7-3-0 Maximum Pavement Loads


Maximum Pavement Loads

1. This section gives Maximum Pavement Loads.

7-3-0Page 1

Jan 01/11



(NG

)V

H

(MG

)(C

G)

VV

NO

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:A

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OA

DS

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LCU

LAT

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PLA

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MA

XIM

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V (N

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(1)

(2)

(3)

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V V

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L N

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366

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369

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F_AC_070300_1_0110101_01_00

−60

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807

325

366

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813

950

369

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88 9

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88 9

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40 3

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40 3

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121

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106

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78 4

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39 2

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35 4

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208

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187

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209

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185

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94 3

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85 2

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39 5

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45

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MA

XIM

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MP

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TM

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67

kgkg

kgkg

lblb

lblb

(1)

lb

(2)

VM

G (

PE

R S

TR

UT

)V

CG

H (

PE

R S

TR

UT

)

kgkg

lb

ST

AT

IC L

OA

D A

T

lb

MA

X A

FT

CG

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GD

EC

ELE

RA

TIO

N

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

kg

@ 1

0 ft/

s ²

@ 1

0 ft/

s ²

Maximum Pavement LoadsFIGURE 1

7-3-0Page 2

Jan 01/11



(NG

)V

H

(MG

)(C

G)

VV

(3)

BR

AK

ED

MA

IN G

EA

R

BR

AK

ED

CE

NT

ER

GE

AR

(4)

(1)

(2)

MR

W =

381

200

kg

FW

D C

G =

16

% M

AC

AT

A/C

WE

IGH

T =

354

600

kg

MR

W =

366

200

kg

FW

D C

G =

16

% M

AC

AT

A/C

WE

IGH

T =

354

600

kg

MR

W =

381

200

kg

AF

T C

G =

30.

2 %

MA

C A

T A

/C W

EIG

HT

= 3

81 2

00 k

gM

RW

= 3

66 2

00 k

g A

FT

CG

= 3

5 %

MA

C A

T A

/C W

EIG

HT

= 3

66 2

00 k

g

VN

G3

45

12

MA

XIM

UM

RA

MP

WE

IGH

TM

OD

EL

67

kgkg

kgkg

lblb

lblb

(1)

lb

(2)

VM

G (

PE

R S

TR

UT

)V

CG

H (

PE

R S

TR

UT

)

kgkg

lb

ST

AT

IC L

OA

D A

TS

TA

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AK

ING

ST

EA

DY

BR

AK

ING

AT

INS

TA

NT

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US

BR

AK

ING

CO

EF

FIC

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T =

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DE

CE

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AT

ION

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X A

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AT

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OA

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AF

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GD

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ELE

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ST

AT

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OA

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79 0

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38 9

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)

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206

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190

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4)

93 8

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86 2

80(4

)−

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MA

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AT

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TA

L G

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MA

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NE

MA

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RA

MP

WE

IGH

T

F_AC_070300_1_0120101_01_01


7-3-0Page 3

Jan 01/11



H

(1)

(2)

(3)

(4)

BR

AK

ED

MA

IN G

EA

RB

RA

KE

D C

EN

TE

R G

EA

R

FW

D C

G =

22

% M

AC

AT

349

200

kg

AF

T C

G =

36.

5 %

MA

C A

T 3

69 2

00 k

g A

ND

36.

4 %

MA

C A

T 3

73 2

00 k

g

V (N

G)

V (M

G)

V (C

G)

−50

0

813

950

369

200

373

200

41 1

60

41 1

60

128

950

128

950

58 4

90

58 4

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90 7

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90 7

50

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106

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87 2

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78 5

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)

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187

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188

275(

4)

94 3

90(3

)

84 9

90(4

)

95 6

30(3

)

85 4

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)

kgkg

kgkg

kglb

lblb

lblb

kgkg

lblb

VN

G

34

51

2

MA

XIM

UM

RA

MP

WE

IGH

TM

OD

EL

67

(1)

(2)

VM

G (

PE

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TR

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CG

H (

PE

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)

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AT

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DE

CE

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AT

ION

AT

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TA

NT

AN

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US

BR

AK

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CO

EF

FIC

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T =

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@ 1

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s ²

ST

EA

DY

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X A

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ST

AT

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TA

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RA

KIN

G

V(N

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V(M

G)

H

MA

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UM

VE

RT

ICA

L C

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TE

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R G

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UN

D L

OA

D A

T M

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T A

FT

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NO

TE

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LL L

OA

DS

CA

LCU

LAT

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US

ING

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PLA

NE

MA

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MP

WE

IGH

T

F_AC_070300_1_0130101_01_01


7-3-0Page 4

Jan 01/11



NO

TE

:

H

ALL

LO

AD

S C

ALC

ULA

TE

D U

SIN

G A

IRP

LAN

E M

AX

IMU

M R

AM

P W

EIG

HT

(1)

(3)

MR

W =

375

200

kg

FW

D C

G =

22

% M

AC

AT

A/C

WE

IGH

T =

349

200

kg

MR

W =

375

200

kg

AF

T C

G =

35.

01 %

MA

C A

T A

/C W

EIG

HT

= 3

75 2

00 k

g

BR

AK

ED

MA

IN G

EA

R

BR

AK

ED

CE

NT

ER

GE

AR

(2)

(4)

V (N

G)

V (M

G)

V (C

G)

−50

082

7 17

537

5 20

090

750

41 1

6058

480

263

850

119

680

235

300

106

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88 8

75(3

)

79 2

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)

40 1

30(3

)

35 9

50(4

)

211

075(

3)

188

250(

4)

95 7

40(3

)

85 3

80(4

)12

8 92

5

VN

G3

45

12

MA

XIM

UM

RA

MP

WE

IGH

TM

OD

EL

67

kgkg

kgkg

kglb

lblb

lb

(1)

lb

(2)

VM

G (

PE

R S

TR

UT

)V

CG

H (

PE

R S

TR

UT

)

kgkg

lb

ST

AT

IC L

OA

D A

TS

TA

TIC

BR

AK

ING

DE

CE

LER

AT

ION

AT

INS

TA

NT

AN

EO

US

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

lb

ST

EA

DY

BR

AK

ING

MA

X A

FT

CG

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GD

EC

ELE

RA

TIO

N

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

@ 1

0 ft/

s ²

@ 1

0 ft/

s ²

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

G

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

V(N

G)

V(M

G)

H

MA

XIM

UM

VE

RT

ICA

L C

EN

TE

R G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T A

FT

CG

V(C

G)

F_AC_070300_1_0140101_01_01


7-3-0Page 5

Jan 01/11



(3)

BR

AK

ED

MA

IN G

EA

R

BR

AK

ED

CE

NT

ER

GE

AR

(4)

(1)

(2)

MR

W =

381

200

kg

FW

D C

G =

22

% M

AC

AT

A/C

WE

IGH

T =

349

200

kg

MR

W =

373

200

kg

FW

D C

G =

22

% M

AC

AT

A/C

WE

IGH

T =

349

200

kg

MR

W =

381

200

kg

AF

T C

G =

34.

7 %

MA

C A

T A

/C W

EIG

HT

= 3

81 2

00 k

gM

RW

= 3

73 2

00 k

g A

FT

CG

= 3

6.4

% M

AC

AT

A/C

WE

IGH

T =

373

200

kg

VN

G3

45

12

MA

XIM

UM

RA

MP

WE

IGH

TM

OD

EL

67

kgkg

kgkg

lblb

lblb

(1)

lb

(2)

VM

G (

PE

R S

TR

UT

)V

CG

H (

PE

R S

TR

UT

)

kgkg

lb

ST

AT

IC L

OA

D A

TS

TA

TIC

BR

AK

ING

ST

EA

DY

BR

AK

ING

AT

INS

TA

NT

AN

EO

US

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

lb

DE

CE

LER

AT

ION

MA

X A

FT

CG

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GD

EC

ELE

RA

TIO

N

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

kg

@ 1

0 ft/

s ²

@ 1

0 ft/

s ²

840

400

381

200

90 7

2541

150

128

800

58 4

2026

5 85

012

0 59

024

2 47

510

9 98

089

700

(3)

81 8

00(4

)

40 6

90(3

)

37 1

10(4

)

212

675(

3)

193

975(

4)

96 4

70(3

)

87 9

90(4

)−

500

822

775

373

200

90 7

2541

150

128

800

58 4

2026

1 12

511

8 44

023

9 95

010

8 84

087

575

(3)

80 4

75(4

)

39 7

20(3

)

36 5

10(4

)

208

900(

3)

191

975(

4)

94 7

50(3

)

87 0

70(4

)−

500

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

G

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

V(N

G)

V(M

G)

H

MA

XIM

UM

VE

RT

ICA

L C

EN

TE

R G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T A

FT

CG

V(C

G)

NO

TE

:A

LL L

OA

DS

CA

LCU

LAT

ED

US

ING

AIR

PLA

NE

MA

XIM

UM

RA

MP

WE

IGH

T

H

V (N

G)

V (M

G)

V (C

G)

F_AC_070300_1_0150101_01_00


7-3-0Page 6

Jan 01/11




Landing Gear Loading on Pavement


1. GeneralIn the example shown in Section 7-4-1, Figure: Landing Gear Loading on Pavement - MTOW 365000 kg - A340-600WV0xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) and the percentage of weight on the MainLanding Gear is 93,5 %.For these conditions, the total weight on the Main Landing Gear Group is 266 520 kg (587 575 lb).In the example shown in Section 7-4-1, Figure: Landing Gear Loading on Pavement - MTOW 368000 kg - A340-600WV0xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) and the percentage of weight on the MainLanding Gear is 93,4 %.For these conditions, the total weight on the Main Landing Gear Group is 266 111 kg (586 675 lb).


2. GeneralIn the example shown in Section 7-4-1, Figure: Landing Gear Loading on Pavement - MTOW 365000 kg - A340-600WV1xxThe Gross Aircraft Weight is 275 000 kg (606 275 lb) and the percentage of weight on the MainLanding Gear is 93,5 %.For these conditions, the total weight on the Main Landing Gear Group is 257 115 kg (566 850 lb).In the example shown in Section 7-4-1, Figure: Landing Gear Loading on Pavement - MTOW 380000 kg - A340-600WV1xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) and the percentage of weight on the MainLanding Gear is 92,3 %.For these conditions, the total weight on the Main Landing Gear Group is 262 978 kg (579 775 lb).


3. GeneralIn the example shown in Section 7-4-1, Figure: Landing Gear Loading on Pavement - MTOW 368000 kg - A340-500WV0xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) and the percentage of weight on the MainLanding Gear is 92,7 %.For these conditions, the total weight on the Main Landing Gear Group is 264 160 kg (582 375 lb).In the example shown in Section 7-4-1, Figure: Landing Gear Loading on Pavement - MTOW 372000 kg - A340-500WV0xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) and the percentage of weight on the MainLanding Gear is 92.7 %.

7-4-0Page 1

Jan 01/11


For these conditions, the total weight on the Main Landing Gear Group is 264 009 kg (582 050 lb).In the example shown in Section 7-4-1, Figure: Landing Gear Loading on Pavement - MTOW 374000 kg - A340-500WV0xxThe Gross Aircraft Weight is 275 000 kg (606 275 lb) and the percentage of weight on the MainLanding Gear is 92.2 %.For these conditions, the total weight on the Main Landing Gear Group is 253 650 kg (579 775 lb).


4. GeneralIn the example shown in Section 7-4-1, Figure: Landing Gear Loading on Pavement - MTOW 372000 kg - A340-500WV1xxThe Gross Aircraft Weight is 275 000 kg (606 275 lb) and the percentage of weight on the MainLanding Gear is 92.6 %.For these conditions, the total weight on the Main Landing Gear Group is 254 750 kg (561 625 lb).In the example shown in Section 7-4-1, Figure: Landing Gear Loading on Pavement - MTOW 380000 kg - A340-500WV1xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) and the percentage of weight on the MainLanding Gear is 92.1 %.For these conditions, the total weight on the Main Landing Gear Group is 262 540 kg (578 800 lb).

7-4-0Page 2

Jan 01/11




Landing Gear Loading on Pavement

1. This section gives Landing Gear Loading on Pavement.

7-4-1Page 1

Jan 01/11



605040302010

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

360

370

86 88 90 92 94 96 98 100


WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

GR

OU

P −

x 1

000

kg

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

360

370

PERCENTAGE MAC

AIR

CR

AF

T G

RO

SS

WE

IGH

T−

x 1

000

kg

MTOW = 365 000 kg

TAKE OFF &LANDING

LANDING

CG FOR ACNCALCULATIONS

TAKE OFF

MLW = 256 000 kg

MZFW = 242 000 kg

F_AC_070401_1_0290101_01_01

Landing Gear Loading on PavementMTOW 365 000 kg

FIGURE 1

7-4-1Page 2

Jan 01/11



605040302010

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

360

370

86 88 90 92 94 96 98 100


WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

GR

OU

P −

x 1

000

kg

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

360

370

PERCENTAGE MAC

AIR

CR

AF

T G

RO

SS

WE

IGH

T−

x 1

000

kg


TAKE OFF &LANDING LANDING

MTOW = 368 000 kg

MZFW = 245 000 kg

TAKE OFF

MLW = 259 000 kg

F_AC_070401_1_0300101_01_01


FIGURE 2

7-4-1Page 3

Jan 01/11



605040302010

160

180

200

220

240

260

280

300

320

340

360

380

86 88 90 92 94 96 98 100

PERCENTAGE OF WEIGHT ON MAIN GEAR

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− x

1 0

00 k

g

160

180

200

220

240

260

280

300

320

340

360

380

PERCENTAGE MAC

AIR

CR

AF

T G

RO

SS

WE

IGH

T−

x 1

000

kg

MTOW = 365 000 kg


MZFW = 251 000 kg

MLW = 265 000 kg

LANDING

TAKE OFF

F_AC_070401_1_0350101_01_00


FIGURE 3

7-4-1Page 4

Jan 01/11



605040302010

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

360

370

380

86 88 90 92 94 96 98 100


WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

GR

OU

P −

x 1

000

kg

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

360

370

380

PERCENTAGE MAC

AIR

CR

AF

T G

RO

SS

WE

IGH

T−

x 1

000

kg

MTOW = 380 000 kg

TAKE OFF LANDINGTAKE OFF &LANDING


MLW = 265 000 kg

MZFW = 251 000 kg

F_AC_070401_1_0310101_01_01


FIGURE 4

7-4-1Page 5

Jan 01/11



6050403020

310

320

330

340

350

360

370

86 88 90 92 94 96 98 100


160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

360

370

PERCENTAGE MAC

AIR

CR

AF

T G

RO

SS

WE

IGH

T−

x 1

000

kg

LANDING

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

GR

OU

P −

x 1

000

kg

LANDINGTAKE OFF &

MTOW = 368 000 kg


MLW = 240 000 kg

MZFW = 225 000 kg

TAKE OFF

F_AC_070401_1_0320101_01_01


FIGURE 5

7-4-1Page 6

Jan 01/11



50403020

160

170

180

190

200

210

220

230

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250

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270

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290

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350

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370

86 88 90 92 94 96 98 100


WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

GR

OU

P −

x 1

000

kg

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

360

370

PERCENTAGE MAC

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

x 1

000

kgCG FOR ACN

CALCULATIONS

MTOW = 372 000 kg

TAKE OFF &LANDING

LANDING

60

MLW = 243 000 kg

MZFW = 230 000 kg

TAKE OFF

F_AC_070401_1_0330101_01_01


FIGURE 6

7-4-1Page 7

Jan 01/11



6050403020

160

180

200

240

260

280

300

320

340

360

380

86 88 90 92 94 96 98 100


WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− x

1 0

00 k

g

160

180

200

240

260

280

300

320

340

360

380

PERCENTAGE MAC

AIR

CR

AF

T G

RO

SS

WE

IGH

T−

x 1

000

kg

MTOW = 374 000 kg


F_AC_070401_1_0370101_01_00

MLW = 231 000 kg

MZFW = 218 000 kg

TAKE OFF

LANDING

220 220


FIGURE 7

7-4-1Page 8

Jan 01/11



6050403020

160

180

200

220

240

260

280

300

320

340

360

380

86 88 90 92 94 96 98 100


WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− x

1 0

00 k

g

160

180

200

220

240

260

280

300

320

340

360

380

PERCENTAGE MAC

AIR

CR

AF

T G

RO

SS

WE

IGH

T−

x 1

000

kg

MTOW = 374 000 kg


F_AC_070401_1_0380101_01_00

MLW = 243 000 kg

MZFW = 218 000 kg

TAKE OFF

LANDING


FIGURE 8

7-4-1Page 9

Jan 01/11



6050403020

160

180

200

220

240

260

280

300

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340

360

380

86 88 90 92 94 96 98 100


WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− x

1 0

00 k

g

160

180

200

220

240

260

280

300

320

340

360

380

PERCENTAGE MAC

AIR

CR

AF

T G

RO

SS

WE

IGH

T−

x 1

000

kg

MTOW = 372 000 kg


MLW = 246 000 kg

MZFW = 232 000 kg

LANDING

TAKE OFF

F_AC_070401_1_0340101_01_01


FIGURE 9

7-4-1Page 10

Jan 01/11



605040302010

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

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350

360

370

380

86 88 90 92 94 96 98 100


WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

GR

OU

P −

x 1

000

kg

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

360

370

380

PERCENTAGE MAC

AIR

CR

AF

T G

RO

SS

WE

IGH

T−

x 1

000

kg


MTOW = 380 000 kg

LANDING

TAKE OFF &LANDING

MLW = 246 000 kg

MZFW = 232 000 kg

TAKE OFF

F_AC_070401_1_0390101_01_00


FIGURE 10

7-4-1Page 11

Jan 01/11




Wing Gear and Center Landing Gear Loading on Pavement

1. The Main Landing Gear Group has two Wing Gears plus one Center Gear.


2. For an airplane with 365 000 kg (804 690 lb) MTOW.In the example shown in Section 7-4-3, Figure: Wing Gear and Center Landing Gear Loading onPavement - MTOW 365 000 kg - A340-600WV0xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) at AFT CG for ACN calculations.For these conditions, the load on the two Wing Gears is 180 845 kg (398 695 lb) and the load on theCenter Gear is 85 545 kg (188 595 lb).The total weight on the Main Landing Gear Group is 266 390 kg (587 290 lb).For an airplane with 368 000 kg (811 300 lb) MTOW.In the example shown in Section 7-4-3, Figure: Wing Gear and Center Landing Gear Loading onPavement - MTOW 368 000 kg - A340-600WV0xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) at AFT CG for ACN calculations.For these conditions, the load on the two Wing Gears is 180 690 kg (398 355 lb) and the load on theCenter Gear is 85 270 kg (187 985 lb).The total weight on the Main Landing Gear Group is 265 960 kg (586 340 lb).


3. For an airplane with 365 000 kg (804 690 lb) MTOW.In the example shown in Section 7-4-3, Figure: Wing Gear and Center Landing Gear Loading onPavement - MTOW 365 000 kg - A340-600WV1xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) at AFT CG for ACN calculations.The total weight on the Main Landing Gear Group is 266 320 kg (587 135 lb).For an airplane with 380 000 kg (837 760 lb) MTOW.In the example shown in Section 7-4-3, Figure: Wing Gear and Center Landing Gear Loading onPavement - MTOW 380 000 kg - A340-600WV1xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) at AFT CG for ACN calculations.For these conditions, the load on the two Wing Gears is 177 195 kg (390 650 lb) and the load on theCenter Gear is 85 645 kg (188 815 lb).The total weight on the Main Landing Gear Group is 262 840 kg (579 465 lb).


4. For an airplane with 368 000 kg (811 300 lb) MTOW.In the example shown in Section 7-4-3, Figure: Wing Gear and Center Landing Gear Loading onPavement - MTOW 368 000 kg - A340-500WV0xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) at AFT CG for ACN calculations.

7-4-2Page 1

Jan 01/11


For these conditions, the load on the two Wing Gears is 180 500 kg (397 934 lb) and the load on theCenter Gear is 83 560 kg (184 215 lb).The total weight on the Main Landing Gear Group is 264 060 kg (582 150 lb).For an airplane with 372 000 kg (820 120 lb) MTOW.In the example shown in Section 7-4-3, Figure: Wing Gear and Center Landing Gear Loading onPavement - MTOW 372 000 kg - A340-500WV0xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) at AFT CG for ACN calculations.For these conditions, the load on the two Wing Gears is 180 465 kg (397 855 lb) and the load on theCenter Gear is 83 505 kg (184 100 lb).The total weight on the Main Landing Gear Group is 263 970 kg (581 955 lb).For an airplane with 374 000 kg (824 530 lb) MTOW.In the example shown in Section 7-4-3, Figure: Wing Gear and Center Landing Gear Loading onPavement - MTOW 374 000 kg - A340-500WV0xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) at AFT CG for ACN calculations.For these conditions, the load on the two Wing Gears is 180 035 kg (396 910 lb) and the load on theCenter Gear is 82 745 kg (182 420 lb).The total weight on the Main Landing Gear Group is 262 780 kg (579 330 lb).


5. For an airplane with 372 000 kg (820 120 lb) MTOW.In the example shown in Section 7-4-3, Figure: Wing Gear and Center Landing Gear Loading onPavement - MTOW 372 000 kg - A340-500WV1xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) at AFT CG for ACN calculations.For these conditions, the load on the two Wing Gears is 177 240 kg (390 750 lb) and the load on theCenter Gear is 86 615 kg (190 950 lb).The total weight on the Main Landing Gear Group is 263 855 kg (581 700 lb).For an airplane with 380 000 kg (837 760 lb) MTOW.In the example shown in Section 7-4-3, Figure: Wing Gear and Center Landing Gear Loading onPavement - MTOW 380 000 kg - A340-500WV1xxThe Gross Aircraft Weight is 285 000 kg (628 325 lb) at AFT CG for ACN calculations.For these conditions, the load on the two Wing Gears is 176 690 kg (389 535 lb) and the load on theCenter Gear is 85 695 kg (188 925 lb).The total weight on the Main Landing Gear Group is 262 385 kg (578 460 lb).

7-4-2Page 2

Jan 01/11




Wing Gear and Center Landing Gear Loading on Pavement

1. This section gives Wing Gear and Center Landing Gear Loading on Pavement.

7-4-3Page 1

Jan 01/11



02040608010

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12

0

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LOAD ON CENTER GEAR OR LOAD ON TWO WING GEARS 1

400x

530R

23 4

0PR

TY

RE

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IGU

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: LA

ND

ING

GE

AR

LO

AD

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ON

400

450

500

550

600

650

700

750

800

[x1

00

0 k

g]

[x1 0

00 lb

]

CE

NT

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GE

AR

TW

O W

ING

GE

AR

S

TY

RE

PR

ES

SU

RE

: 16.

1 ba

r (2

34 p

si)

WIN

G G

EA

R15

bar

(21

8 ps

i) C

EN

TE

R G

EA

R[x1 000 kg]

F_AC_070403_1_0120101_01_01

PA

VE

ME

NT

− M

TO

W 3

65 0

00 k

g −

A34

0−60

0WV

0xx

Wing Gear and Center Landing Gear Loading on PavementMTOW 365 000 kg

FIGURE 1

7-4-3Page 2

Jan 01/11



020406080100

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020

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AIR

CR

AF

T G

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SS

WE

IGH

T

LOAD ON CENTRE GEAR OR LOAD ON TWO WING GEARS

1 40

0x53

0R23

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R T

YR

ES

TY

RE

PR

ES

SU

RE

: 16.

1 ba

r (2

34 p

si)

WIN

G G

EA

RS

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

4.4

% M

AC

.S

EE

SE

CT

ION

7−

4−1,

FIG

UR

E: L

AN

DIN

G G

EA

R L

OA

DIN

G O

N

400

450

500

550

600

650

700

750

800

[x1

000

kg]

[x1

000

lb]

TW

O W

ING

GE

AR

S

CE

NT

ER

GE

AR

15 b

ar (

218

psi)

CE

NT

ER

GE

AR

[x1 000 kg]

PA

VE

ME

NT

− M

TO

W 3

68 0

00 k

g −

A34

0−60

0WV

0xx

F_AC_070403_1_0130101_01_01


FIGURE 2

7-4-3Page 3

Jan 01/11



TW

O W

ING

GE

AR

S

CE

NT

ER

GE

AR

240

220

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140

120

100 80 60 40 20 0 16

018

020

022

024

026

028

030

032

034

036

038

0

[x1

000

kg]

[x1

000

lb]

AIR

CR

AF

T G

RO

SS

WE

IGH

T

LOAD ON CENTER GEAR OR LOAD ON TWO WING GEARS[x 1 000 kg]

1 40

0x53

0R23

40P

R T

IRE

ST

IRE

PR

ES

SU

RE

16.

1 ba

r (2

34 p

si)

WIN

G G

EA

RS

16.1

bar

(23

4 ps

i) C

EN

TE

R G

EA

RS

EE

SE

CT

ION

7−

4−1,

FIG

UR

E: L

AN

DIN

G G

EA

R L

OA

DIN

G O

NC

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 35

% M

AC

.

400

450

500

550

600

650

700

750

800

PA

VE

ME

NT

− M

TO

W 3

65 0

00 k

g −

A34

0−60

0WV

1xx

F_AC_070403_1_0180101_01_00


FIGURE 3

7-4-3Page 4

Jan 01/11



020406080100

120

140

160

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240 16

018

020

022

024

026

028

030

032

034

036

038

0

AIR

CR

AF

T G

RO

SS

WE

IGH

T

LOAD ON CENTER GEAR OR LOAD ON TWO WING GEARS

1 40

0x53

0R23

40P

R T

YR

ES

TY

RE

PR

ES

SU

RE

: 16.

1 ba

r (2

34 p

si)

WIN

G G

EA

RS

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

0.2

% M

AC

.S

EE

SE

CT

ION

7−

4−1,

FIG

UR

E: L

AN

DIN

G G

EA

R L

OA

DIN

G O

N

400

450

500

550

600

650

700

750

800

[x1

000

kg]

[x1

000

lb]

16.1

bar

(23

4 ps

i) C

EN

TE

R G

EA

R

CE

NT

ER

GE

AR

TW

O W

ING

GE

AR

S[x1 000 kg]

PA

VE

ME

NT

− M

TO

W 3

80 0

00 k

g −

A34

0−60

0WV

1xx

F_AC_070403_1_0140101_01_01


FIGURE 4

7-4-3Page 5

Jan 01/11



020406080100

120

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018

020

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024

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AIR

CR

AF

T G

RO

SS

WE

IGH

T


1 40

0x53

0R23

40P

R T

IRE

ST

YR

E P

RE

SS

UR

E:

16.1

bar

(23

4 ps

i) W

ING

GE

AR

SC

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 36.

5 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1, F

IGU

RE

: LA

ND

ING

GE

AR

LO

AD

ING

ON

400

450

500

550

600

650

700

750

800

[x1

000

kg]

[x1

000

lb]

CE

NT

ER

GE

AR

15 b

ar (

218

psi)

CE

NT

ER

GE

AR

TW

O W

ING

GE

AR

S

[x1 000 kg]

F_AC_070403_1_0150101_01_01

PA

VE

ME

NT

− M

TO

W 3

68 0

00 k

g −

A34

0−50

0WV

0xx


FIGURE 5

7-4-3Page 6

Jan 01/11



020406080100

120

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018

020

022

024

026

028

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AIR

CR

AF

T G

RO

SS

WE

IGH

T

LOAD ON CENTER GEAR OR LOAD ON TWO WING GEARS 1

400x

530R

23 4

0PR

TY

RE

ST

YR

E P

RE

SS

UR

E: 1

6.1

bar

(234

psi

) W

ING

GE

AR

S15

bar

(21

8 ps

i) C

EN

TE

R G

EA

R

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

6.4

% M

AC

.S

EE

SE

CT

ION

7−

4−1,

FIG

UR

E: L

AN

DIN

G G

EA

R L

OA

DIN

G O

N

400

450

500

550

600

650

700

750

800

[x1

000

kg]

[x1

000

lb]

TW

O W

ING

GE

AR

S

CE

NT

ER

GE

AR

[x1 000 kg]P

AV

EM

EN

T −

MT

OW

372

000

kg

− A

340−

500W

V0x

x

F_AC_070403_1_0160101_01_01


FIGURE 6

7-4-3Page 7

Jan 01/11



240

220

200

180

160

140

120

100 80 60 40 20


160

180

200

220

240

260

280

300

320

340

360

380

[x1

000

kg]

[x1

000

lb]

AIR

CR

AF

T G

RO

SS

WE

IGH

T

400

450

500

550

600

650

700

750

800

TW

O W

ING

GE

AR

S

CE

NT

ER

GE

AR

1 40

0x53

0R23

40P

R T

IRE

ST

IRE

PR

ES

SU

RE

16.

1 ba

r (2

34 p

si)

WIN

G G

EA

RS

15 b

ar (

218

psi)

CE

NT

ER

GE

AR

SE

E S

EC

TIO

N 7

−4−

1, F

IGU

RE

: LA

ND

ING

GE

AR

LO

AD

ING

ON

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

5.01

% M

AC

.

F_AC_070403_1_0200101_01_00

PA

VE

ME

NT

− M

TO

W 3

74 0

00 k

g −

A34

0−50

0WV

0xx


FIGURE 7

7-4-3Page 8

Jan 01/11



240

220

200

180

160

140

120

100 80 60 40 20 0


160

180

200

220

240

260

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300

320

340

360

380

[x1

000

kg]

[x1

000

lb]

AIR

CR

AF

T G

RO

SS

WE

IGH

T

400

450

500

550

600

650

700

750

800

1 40

0x53

0R23

40P

R T

IRE

ST

IRE

PR

ES

SU

RE

16.

1 ba

r (2

34 p

si)

WIN

G G

EA

RS

16.1

bar

(23

4 ps

i) C

EN

TE

R G

EA

RS

EE

SE

CT

ION

7−

4−1,

FIG

UR

E: L

AN

DIN

G G

EA

R L

OA

DIN

G O

NC

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 36.

4 %

MA

C.

TW

O W

ING

GE

AR

S

CE

NT

ER

GE

AR

PA

VE

ME

NT

− M

TO

W 3

72 0

00 k

g −

A34

0−50

0WV

1xx

F_AC_070403_1_0190101_01_00


FIGURE 8

7-4-3Page 9

Jan 01/11



020406080100

120

140

160

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240 16

018

020

022

024

026

028

030

032

034

036

038

0

AIR

CR

AF

T G

RO

SS

WE

IGH

T


1 40

0x53

0R23

40P

R T

YR

ES

TY

RE

PR

ES

SU

RE

: 16.

1 ba

r (2

34 p

si)

WIN

G G

EA

RS

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

4.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1,

FIG

UR

E: L

AN

DIN

G G

EA

R L

OA

DIN

G O

N

400

450

500

550

600

650

700

750

800

[x1

000

kg]

[x1

000

lb]

16.1

bar

(23

4 ps

i) C

EN

TE

R G

EA

R

TW

O W

ING

GE

AR

S

CE

NT

RE

GE

AR

[x1 000 kg]

PA

VE

ME

NT

− M

TO

W 3

80 0

00 k

g −

A34

0−50

0WV

1xx

F_AC_070403_1_0170101_01_01


FIGURE 9

7-4-3Page 10

Jan 01/11


7-5-0 Flexible Pavement Requirements - U.S. Army Corps of Engineers Design Method


Flexible Pavement Requirements - U.S. Army Corps of Engineers Design Method


1. General

To find a Flexible Pavement Thickness, the Subgrade Strength (CBR), the Annual Departure Leveland the weight on one Main Landing Gear must be known.

In the example shown in Section 7-5-1, Figure: Flexible Pavement Requirements - MTOW 365 000 kg- A340-600WV0xx- A ”CBR” value of 10- An Annual Departure Level of 3 000- And the load on one Wing Landing Gear of 90 000 kg (198 425 lb)- The required Flexible Pavement Thickness is 53.8 cm (21.2 inches).

The line showing 10 000 Coverages is used to calculate Aircraft Classification Number (ACN).


2. General





3. General


7-5-0Page 1

Jan 01/11





4. General




7-5-0Page 2

Jan 01/11


7-5-1 Flexible Pavement Requirements - U.S. Army Corps of Engineers Design Method S-77-1


Flexible Pavement Requirements - U.S. Army Corps of Engineers Design Method

1. This section gives Flexible Pavement Requirements.

7-5-1Page 1

Jan 01/11



3 6 10 15 20 30

3020156 103

[INCHES]

SUBGRADE STRENGTH − CBR

10 15 20 30 40 60 80 100 120 150 180

[CENTIMETERS]

FLEXIBLE PAVEMENT THICKNESS

1 400x530R23 40PR TIRES

60 80

60 80

40

40 50

50

TIRE PRESSURE CONSTANT AT 16.1 bar (234 psi)

F_AC_070501_1_0130101_01_01

10 000 COVERAGES USED FOR ACN CALCULATIONS

MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT ANDAFT CG

117 950 kg (260 025 lb)WEIGHT ON ONE MAIN LANDING GEAR

100 000 kg (220 460 lb)110 000 kg (242 500 lb)

90 000 kg (198 410 lb) 80 000 kg (176 000 lb)

ANNUAL DEPARTURES*

*20 YEAR PAVEMENT LIFE

1 200 3 000 6 000

15 000 25 000

ALPHA FACTOR = 0.8

F_AC_070501_1_0130101_01_01

Flexible Pavement RequirementsMTOW 365 000 kg

FIGURE 1

7-5-1Page 2

Jan 01/11



3 6 10 15 20 30

3020156 103

[INCHES]


10 15 20 30 40 60 80 100 120 150 180

[CENTIMETERS]


1 400x530R23 40PR TIRES

60 80

60 80

40

40 50

50


25 000*20 YEAR PAVEMENT LIFE

1 200ANNUAL DEPARTURES*

3 000 6 000

15 000



WEIGHT ON ONE MAIN LANDING GEAR118 920 kg (262 175 lb)110 000 kg (242 500 lb)100 000 kg (220 460 lb) 90 000 kg (198 410 lb) 80 000 kg (176 000 lb)

ALPHA FACTOR = 0.8

F_AC_070501_1_0140101_01_01


FIGURE 2

7-5-1Page 3

Jan 01/11



10 15 20 30 40 60 80 100 120 150 180

3 6 10 15 20 30 40 60 80

3 6 10 15 20 30 40 60 80

[INCHES]

[CENTIMETERS]


1 400x530R23 40PR TIRES



117 270 kg (258 525 lb)110 000 kg (242 500 lb)100 000 kg (220 450 lb)90 000 kg (198 425 lb)80 000 kg (176 375 lb)

WEIGHT ON ONE MAIN LANDING GEAR

10 000 COVERAGES USEDFOR ACN CALCULATIONS


ANNUAL DEPARTURES*1 2003 0006 000

15 00025 000*20 YEAR PAVEMENT LIFE

ALPHA FACTOR = 0.8

F_AC_070501_1_0190101_01_00


FIGURE 3

7-5-1Page 4

Jan 01/11



3 6 10 15 20 30[INCHES]


10 15 20 30 40 60 80 100 120 150 180

[CENTIMETERS]


1 400x530R23 40PR TIRESTIRE PRESSURE CONSTANT AT 16.1 bar (234 psi)

60 8040 50

3020156 103 60 8040 50

MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT ANDAFT CG10 000 COVERAGES USED

FOR ACN CALCULATIONS



3 0006 000

15 000

ANNUAL DEPARTURES*1 200

*20 YEAR PAVEMENT LIFE25 000

ALPHA FACTOR = 0.8

F_AC_070501_1_0150101_01_01


FIGURE 4

7-5-1Page 5

Jan 01/11



[INCHES]


10 15 20 30 40 60 80 100 120 150 180

[CENTIMETERS]



3 6 10 15 20 30 40 50 60 80

3020156 103 60 8040 50



117 990 kg (260 125 lb)110 000 kg (242 500 lb)100 000 kg (220 460 lb)

90 000 kg (198 410 lb)80 000 kg (176 000 lb)


3 0006 000

15 000



ALPHA FACTOR = 0.8

F_AC_070501_1_0160101_01_01


FIGURE 5

7-5-1Page 6

Jan 01/11



[INCHES]


10 15 20 30 40 60 80 100 120 150 180

[CENTIMETERS]



3 6 10 15 20 30 60 8040 50

3020156 103 60 8040 50



90 000 kg (198 410 lb)80 000 kg (176 000 lb)

119 540 kg (263 525 lb)110 000 kg (242 500 lb)100 000 kg (220 460 lb)


3 0006 000

15 000



ALPHA FACTOR = 0.8

F_AC_070501_1_0170101_01_01


FIGURE 6

7-5-1Page 7

Jan 01/11



119 680 kg (263 850 lb)110 000 kg (242 500 lb)100 000 kg (220 450 lb)

90 000 kg (198 425 lb)80 000 kg (176 375 lb)






10 15 20 30 40 60 80 100 120 150 180

3 6 10 15 20 30 40 60 80[INCHES]

[CENTIMETERS]


1 400x530R23 40PR TIRES



ALPHA FACTOR = 0.8

3 6 10 15 20 30 40 60 80

F_AC_070501_1_0200101_01_00


FIGURE 7

7-5-1Page 8

Jan 01/11



118 440 kg (261 125 lb)110 000 kg (242 500 lb)100 000 kg (220 450 lb)

90 000 kg (198 425 lb)80 000 kg (176 375 lb)



10 000 COVERAGES USEDFOR ACN CALCULATIONS



ALPHA FACTOR = 0.8

[INCHES]

[CENTIMETERS]


1 400x530R23 40PR TIRES


10 15 20 30 40 60 80 100 120 150 180

3 6 10 15 20 30 40 60 80

3 6 10 15 20 30 40 60 80


F_AC_070501_1_0210101_01_00


FIGURE 8

7-5-1Page 9

Jan 01/11



3 6 10 15 20 30

3020156 103

[INCHES]


10 15 20 30 40 60 80 100 120 150 180

[CENTIMETERS]



60 80

60 80

40

40 50

50



WEIGHT ON ONE MAIN LANDING GEAR120 590 kg (265 850 lb)110 000 kg (242 500 lb)100 000 kg (220 460 lb)90 000 kg (198 410 lb)80 000 kg (176 000 lb)

3 0006 000

15 000



ALPHA FACTOR = 0.8

F_AC_070501_1_0180101_01_01


FIGURE 9

7-5-1Page 10

Jan 01/11




Flexible Pavement Requirements - LCN Conversion


1. General

To find the airplane weight that a Flexible Pavement can support, the LCN of the pavement and thethickness (h) must be known.

In the example shown in Section 7-6-1, Figure: Flexible Pavement Requirements - MTOW 365 000 kg- A340-600WV0xxThe thickness (h) is shown at 635 mm (25 inches) with an LCN of 115.

For these conditions, the weight on one Main Landing Gear is 110 000 kg (242 500 lb).


2. General


In the example shown in Section 7-6-1, Figure: Flexible Pavement Requirements - MTOW 365 000 kg- A340-600WV1xxThe thickness (h) is shown at 635 mm (25 inches) with an LCN of 115.



3. General


In the example shown in Section 7-6-1, Figure: Flexible Pavement Requirements - MTOW 368 000 kg- A340-500WV0xxThe thickness (h) is shown at 635 mm (25 in.) with an LCN of 115.

For these conditions the weight on one Main Landing Gear is 110 000 kg (242 500 lb).

7-6-0Page 1

Jan 01/11



4. General


In the example shown in Section 7-6-1, Figure: Flexible Pavement Requirements - MTOW 372 000 kg- A340-500WV1xxThe thickness (h) is shown at 635 mm (25 in.) with an LCN of 115.

For these conditions the weight on one Main Landing Gear is 110 000 kg (242 500 lb).

7-6-0Page 2

Jan 01/11




Flexible Pavement Requirements - LCN Conversion

1. This section gives Flexible Pavement Requirements - LCN Conversion.

7-6-1Page 1

Jan 01/11



101520253035404550

102030405060708090100

110

120

1020

3040

5060

7080

6070

8090

100

120

150

1805

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)F

LEX

IBLE

PA

VE

ME

NT

TH

ICK

NE

SS

[IN

CH

ES

]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965

EQUIVALENT SINGLE WHEEL LOAD [ x1 000 kg]

117 9

50

110 0

00

10

0 0

00

90 0

00

80

00

0

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

EQUIVALENT SINGLE WHEEL LOAD [ x1 000 lb]1

400x

530R

23 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

1 ba

r (2

33 p

si)

(26

0 0

25

lb)

(24

2 5

00

lb)

(220 4

60 lb

)(1

98 4

10 lb

)(1

76

00

0 lb

)

kg kg kg kg kg

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

M

RA

MP

WE

IGH

T A

ND

AF

T C

G

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

254

762

1 01

61

524

2 03

250

8

F_AC_070601_1_0130101_01_01


FIGURE 1

7-6-1Page 2

Jan 01/11



102030405060708090100

110

120

118 9

20

110 0

00

10

0 0

00

90 0

00

80

00

0

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

1020

3040

5060

7080

6070

8090

100

120

150

180

4050 45 35 30 25 20 15 510

NO

TE

: EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

1 40

0x53

0R23

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(233

psi

)

kg kg kg kg kg

(26

2 1

75

lb)

(24

2 5

00

lb)

(220 4

60 lb

)(1

98 4

10 lb

)(1

76

00

0 lb

)

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

M

RA

MP

WE

IGH

T A

ND

AF

T C

G

EQUIVALENT SINGLE WHEEL LOAD [ x1 000 lb]


FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)25

476

21

016

1 52

42

032

508

F_AC_070601_1_0140101_01_01


FIGURE 2

7-6-1Page 3

Jan 01/11



101520253035404550

102030405060708090100

110

120

1020

3040

5060

7080

6070

8090

100

120

140

160

5

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)F

LEX

IBLE

PA

VE

ME

NT

TH

ICK

NE

SS

[IN

CH

ES

]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965



400x

530R

23 4

0PR

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)F

LEX

IBLE

PA

VE

ME

NT

TH

ICK

NE

SS

(m

m)

254

762

1 01

61

524

508

180

117 2

70

110 0

00

10

0 0

00

90 0

00

80

00

0

(25

8 5

25

lb)

(24

2 5

00

lb)

(220 4

50 lb

)(1

98 4

25 lb

)(1

76

37

5 lb

)

kg kg kg kg kg

2 03

2

MA

XIM

UM

PO

SS

IBLE

BO

DY

GE

AR

LO

AD

AT

MA

XIM

UM

R

AM

P W

EIG

HT

AN

D A

FT

CG

WE

IGH

T O

N O

NE

WIN

G L

AN

DIN

G G

EA

R

F_AC_070601_1_0190101_01_00


FIGURE 3

7-6-1Page 4

Jan 01/11



6070

8050

4030

2010

102030405060708090100

110

120

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

100

9080

7060

150

120

180

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

510152025303540455012

1 02

011

0 00

010

0 00

090

000

80 0

00

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

NO

TE

: EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65

1 40

0x53

0R23

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

kg kg kg kg

(266

800

lb)

(242

500

lb)

(220

460

lb)

(198

410

lb)

(176

000

lb)

kg

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

M

RA

MP

WE

IGH

T A

ND

AF

T C

G



FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

254

762

1 01

61

524

2 03

250

8

F_AC_070601_1_0150101_01_01


FIGURE 4

7-6-1Page 5

Jan 01/11



6070

8050

4030

2010

102030405060708090100

110

120

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

100

9080

7060

110

150

120

180

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

5101520253035404550

NO

TE

: EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65

1 40

0x53

0R23

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(233

psi

)



FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

254

762

1 01

61

524

2 03

250

8

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

M

RA

MP

WE

IGH

T A

ND

AF

T C

G

117

990

110

000

100

000

90 0

0080

000

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

Rkg kg kg kg kg

(260

125

lb)

(242

500

lb)

(220

460

lb)

(198

410

lb)

(176

000

lb)

F_AC_070601_1_0160101_01_01


FIGURE 5

7-6-1Page 6

Jan 01/11



100

9080

7060

150

120

180

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

5101520253035404550

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65

6070

8050

4030

2010

102030405060708090100

110

120

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

1 40

0x53

0R23

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(233

psi

)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R11

9 54

0 kg

(26

3 52

5 lb

)11

0 00

0 kg

(24

2 50

0 lb

)10

0 00

0 kg

(22

0 46

0 lb

)90

000

kg

(198

410

lb)

80 0

00 k

g (1

76 0

00 lb

)

NO

TE

:

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

M

RA

MP

WE

IGH

T A

ND

AF

T C

G



FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

254

762

1 01

61

524

2 03

250

8

F_AC_070601_1_0170101_01_01


FIGURE 6

7-6-1Page 7

Jan 01/11



101520253035404550

102030405060708090100

110

120

1020

3040

5060

7080

6070

8090

100

120

140

160

5

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)F

LEX

IBLE

PA

VE

ME

NT

TH

ICK

NE

SS

[IN

CH

ES

]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965



400x

530R

23 4

0PR

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)F

LEX

IBLE

PA

VE

ME

NT

TH

ICK

NE

SS

(m

m)

254

762

1 01

61

524

508

180

119 6

80

110 0

00

10

0 0

00

90 0

00

80

00

0

(26

3 8

50

lb)

(24

2 5

00

lb)

(220 4

50 lb

)(1

98 4

25 lb

)(1

76

37

5 lb

)

kg kg kg kg kg

2 03

2

MA

XIM

UM

PO

SS

IBLE

BO

DY

GE

AR

LO

AD

AT

MA

XIM

UM

R

AM

P W

EIG

HT

AN

D A

FT

CG

WE

IGH

T O

N O

NE

WIN

G L

AN

DIN

G G

EA

R

F_AC_070601_1_0200101_01_00


FIGURE 7

7-6-1Page 8

Jan 01/11



101520253035404550

10203040506070120

1020

3040

5060

7080

6070

8090

100

120

140

160

5

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)F

LEX

IBLE

PA

VE

ME

NT

TH

ICK

NE

SS

[IN

CH

ES

]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965



400x

530R

23 4

0PR

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)F

LEX

IBLE

PA

VE

ME

NT

TH

ICK

NE

SS

(m

m)

254

762

1 01

61

524

508

180

2 03

2

118 4

40

110 0

00

10

0 0

00

90 0

00

80

00

0

(26

1 1

25

lb)

(24

2 5

00

lb)

(220 4

50 lb

)(1

98 4

25 lb

)(1

76

37

5 lb

)

kg kg kg kg kg

WE

IGH

T O

N O

NE

WIN

G L

AN

DIN

G G

EA

R

8090100

110

MA

XIM

UM

PO

SS

IBLE

BO

DY

GE

AR

LO

AD

AT

MA

XIM

UM

R

AM

P W

EIG

HT

AN

D A

FT

CG

F_AC_070601_1_0210101_01_00


FIGURE 8

7-6-1Page 9

Jan 01/11



6070

8050

4030

2010

102030405060708090100

110

120

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

100

9080

7060

150

120

180

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

5101520253035404550

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65

1 40

0x53

0R23

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

NO

TE

:

120

590

kg (

265

850

lb)

110

000

kg (

242

500

lb)

100

000

kg (

220

460

lb)

90 0

00 k

g (1

98 4

10 lb

)

80 0

00 k

g (1

76 0

00 lb

)

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

M

RA

MP

WE

IGH

T A

ND

AF

T C

G



WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

254

762

1 01

61

524

2 03

250

8

F_AC_070601_1_0180101_01_01


FIGURE 9

7-6-1Page 10

Jan 01/11




Rigid Pavement Requirements - Portland Cement Association Design Method


1. General

To determine a Rigid Pavement Thickness, the Subgrade Modulus (K), the allowable working stressand the weight on one Main Landing Gear must be known.

In the example shown in Section 7-7-1, Figure: Rigid Pavement Requirements - MTOW 365 000 kg -A340-600WV0xx- a ”k” value of 150 MN/m3 (550 lb/in3)- an allowable working stress of 35.2 kg/cm2 (500 lb/in2)- the load on one Main Landing Gear of 100 000 kg (220 450 lb) the required Rigid Pavement

Thickness is 25.7 cm (10.1 inches).


2. General





3. General


In the example shown in Section 7-7-1, Figure: Rigid Pavement Requirements - MTOW 368 000 kg -A340-500WV0xx- a ”k” value of 150 MN/m3 (550 lb/in3)- an allowable working stress of 35.2 kg/cm2 (500 lb/in2)

7-7-0Page 1

Jan 01/11


- the load on one Main Landing Gear of 100 000 kg (220 450 lb) the required Rigid PavementThickness is 25.7 cm (10.1 inches).


4. General




7-7-0Page 2

Jan 01/11




Rigid Pavement Requirements - Portland Cement Association Design Method

1. This section gives Rigid Pavement Requirements.

7-7-1Page 1

Jan 01/11



8

9

10

11

12

13

14

15

16

[INC

HE

S]

200

300

400

500

600

700

800

900

1000

[lb/in

²]

15

20

25

30

35

40

45

50

55

60

65

70

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

1400 x 530R23 TIRES

NOTES:THE VALUES OBTAINED BY USING THE MAXIMUM LOAD REFERENCE LINE AND ANY VALUES FOR K ARE EXACT. FOR LOADS LESS THAN MAXIMUM, THE CURVES ARE EXACT FORK = 80 MN/m³ BUT DEVIATE SLIGHTLY FOR ANY OTHER VALUES OF K

22

24

26

28

30

32

34

36

38

40

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

REFERENCE:"DESIGN OF CONCRETE AIRPORT PAVEMENTS" AND "COMPUTER PROGRAM FOR AIRPORT PAVEMENT DESIGN − PROGRAM PDILB" PORTLAND CEMENT ASSOCIATION

TIRE PRESSURE CONSTANT = 16.1 BAR (233 psi)

MAXIMUM POSSIBLE MAIN GEAR LOAD AT MAXIMUM RAMP WEIGHT AND AFT CG



80 MN/m³150 MN/m³

K =K =K =K =

F_AC_070701_1_0130101_01_00

40 MN/m³20 MN/m³

Rigid Pavement RequirementsMTOW 365 000 kg

FIGURE 1

7-7-1Page 2

Jan 01/11



8

9

10

11

12

13

14

15

16

[INC

HE

S]

200

300

400

500

600

700

800

900

1000

[lb/in

²]

15

20

25

30

35

40

45

50

55

60

65

70

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

1400 x 530R23 TIRES


22

24

26

28

30

32

34

36

38

40

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]




118 920 kg (262 175 lb)

100 000 kg (220 460 lb)90 000 kg (198 410 lb)80 000 kg (176 000 lb)


110 000 kg (242 500 lb)

F_AC_070701_1_0140101_01_00

80 MN/m³150 MN/m³

K =K =K =K =

20 MN/m³40 MN/m³


FIGURE 2

7-7-1Page 3

Jan 01/11



WEIGHT ON ONE MAINLANDING GEAR117 270 kg (258 525 lb)110 000 kg (242 500 lb)100 000 kg (220 450 lb)

90 000 kg (198 425 lb)

MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUM


RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S

[CE

NT

IME

TE

RS

]

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

68

62

56

50

44

38

32

26

20

38

36

34

32

30

28

26

24

22

16

15

14

13

12

11

10

9

8

1000

900

800

700

600

500

400

300

200

NOTE:THE VALUES OBTAINED BY USINGTHE MAXIMUM LOAD REFERENCELINE AND ANY VALUES FOR K ARE

FOR LOADS LESS THAN MAXIMUM,THE CURVES ARE EXACT FOR K =80 MN/mFOR ANY OTHER VALUES OF K

REFERENCE:"DESIGN OF CONCRETE AIRPORTPAVEMENTS" AND "COMPUTERPROGRAM FOR AIRPORTPAVEMENT DESIGN − PROGRAMPDILB" PORTLAND CEMENTASSOCIATION

RAMP WEIGHT AND AFT CG

EXACT.

BUT DEVIATE SLIGHTLY

K = 20 MN/mK = 40 MN/mK = 80 MN/mK = 150 MN/m

80 000 kg (176 375 lb)

F_AC_070701_1_0190101_01_00


FIGURE 3

7-7-1Page 4

Jan 01/11



8

9

10

11

12

13

14

15

16

[INC

HE

S]

200

300

400

500

600

700

800

900

1000

[lb/in

²]

15

20

25

30

35

40

45

50

55

60

65

70

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

1400 x 530R23 TIRESTIRE PRESSURE CONSTANT = 16.1 BAR (234 PSI)

NOTES:THE VALUES OBTAINED BY USING THE MAXIMUM LOAD REFERENCE LINE AND ANY VALUES FOR K ARE EXACT. FOR LOADS LESS THAN MAXIMUM,

= 80 MN/m³ BUT DEVIATE SLIGHTLY FOR ANY OTHER VALUES OF K

22

24

26

28

30

32

34

36

38

40

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

REFERENCE:"DESIGN OF CONCRETE AIRPORT PAVEMENTS" AND "COMPUTER PROGRAM FOR AIRPORT PAVEMENT DESIGN − PROGRAM PDILB" PORTLAND CEMENT ASSOCIATION THE CURVES ARE EXACT FOR

K



121 020 kg (266 800 lb)110 000 kg (242 500 lb)100 000 kg (220 460 lb)

90 000 kg (198 410 lb)80 000 kg (176 000 lb)

K =K =K =K =

80 MN/m³150 MN/m³

20 MN/m³40 MN/m³

F_AC_070701_1_0150101_01_00


FIGURE 4

7-7-1Page 5

Jan 01/11



8

9

10

11

12

13

14

15

16

[INC

HE

S]

200

300

400

500

600

700

800

900

1000

[lb/in

²]

15

20

25

30

35

40

45

50

55

60

65

70

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

1400 x 530R23 TIRES


22

24

26

28

30

32

34

36

38

40

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]






F_AC_070701_1_0160101_01_00

150 MN/m³

K =K =K =K =

80 MN/m³

20 MN/m³40 MN/m³


FIGURE 5

7-7-1Page 6

Jan 01/11



8

9

10

11

12

13

14

15

16

[INC

HE

S]

200

300

400

500

600

700

800

900

1000

[lb/in

²]

15

20

25

30

35

40

45

50

55

60

65

70

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

1400 x 530R23 TIRES


22

24

26

28

30

32

34

36

38

40

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]






F_AC_070701_1_0170101_01_00

K =K =K =K =150 MN/m³

80 MN/m³

20 MN/m³40 MN/m³


FIGURE 6

7-7-1Page 7

Jan 01/11



WEIGHT ON ONE MAINLANDING GEAR

MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT AND AFT CG




EXACT.


[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

68

62

56

50

44

38

32

26

20

1000

900

800

700

600

500

400

300

200

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S

[CE

NT

IME

TE

RS

]

[INC

HE

S]

38

36

34

32

30

28

26

24

22

16

15

14

13

12

11

10

9

8




F_AC_070701_1_0200101_01_00


FIGURE 7

7-7-1Page 8

Jan 01/11



[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

68

62

56

50

44

38

32

26

20

1000

900

800

700

600

500

400

300

200

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S

[INC

HE

S]

38

36

34

32

30

28

26

24

22

16

15

14

13

12

11

10

9

8




EXACT.



WEIGHT ON ONE MAINLANDING GEAR

MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT AND AFT CG

[CE

NT

IME

TE

RS

]

118 440 kg (261 125 lb)110 000 kg (242 500 lb)100 000 kg (220 450 lb)90 000 kg (198 425 lb)


80 000 kg (176 375 lb)

F_AC_070701_1_0210101_01_00


FIGURE 8

7-7-1Page 9

Jan 01/11



8

9

10

11

12

13

14

15

16

[INC

HE

S]

200

300

400

500

600

700

800

900

1000

[lb/in

²]

15

20

25

30

35

40

45

50

55

60

65

70

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

1400 x 530R23 TIRES


22

24

26

28

30

32

34

36

38

40

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]





120 590 kg (265 850 lb)110 000 kg (242 500 lb)100 000 kg (220 460 lb)

90 000 kg (198 410 lb)80 000 kg (176 000 lb)

F_AC_070701_1_0180101_01_00

K =K =K =K =150 MN/m³

80 MN/m³

20 MN/m³40 MN/m³


FIGURE 9

7-7-1Page 10

Jan 01/11




Rigid Pavement Requirements - LCN Conversion


1. General

To determine the airplane weight that a Rigid Pavement can support, the LCN of the pavement andthe Radius of Relative Stiffness (L) must be known.

In the example shown in Section 7-8-2, Figure: Rigid Pavement Requirements - MTOW 365 000 kg -a340-600WV0xx

The Radius of Relative Stiffness is shown at 762 mm (30 inches) with an LCN of 98.7.



2. General


In the example shown in Section 7-8-2, Figure: Rigid Pavement Requirements - MTOW 365 000 kg -A340-600WV1xx

The Radius of Relative Stiffness is shown at 762 mm (30 inches) with an LCN of 98.7.



3. General



7-8-0Page 1

Jan 01/11


The Radius of Relative Stiffness is shown at 762 mm (30 in.) with an LCN of 98.7.



4. General



The Radius of Relative Stiffness is shown at 762 mm (30 in.) with an LCN of 98.7.


7-8-0Page 2

Jan 01/11



**ON A/C A340-500 A340-600

Radius of Relative Stiffness

1. This section gives Radius of Relative Stiffness.

7-8-1Page 1

Jan 01/11


**ON A/C A340-500 A340-600

d6.06.57.07.5

K=75 K=100 K=150 K=200 K=250 K=300 K=350 K=400 K=550

8.08.59.09.5

10.010.511.011.512.012.513.013.514.014.515.015.516.016.517.017.518.019.020.021.022.023.024.025.0

31.4833.4335.3437.2239.0640.8842.6744.4346.1847.9049.6051.2852.9454.5956.2257.8359.4361.0262.5964.1565.6967.2368.7570.2671.7674.7377.6680.5583.4186.2489.0491.81

29.3031.1132.8934.6336.3538.0439.7141.3542.9744.5746.1647.7249.2750.8052.3253.8255.3156.7858.2559.7061.1362.5663.9865.3866.7869.5472.2774.9677.6380.2682.8685.44

26.4728.1129.7231.2932.8534.3735.8837.3638.8340.2841.7143.1244.5245.9047.2748.6349.9851.3152.6353.9455.2456.5357.8159.0860.3462.8465.3067.7470.1472.5274.8777.20

24.6326.1627.6529.1230.5731.9933.3934.7736.1437.4838.8140.1341.4342.7243.9945.2646.5147.7548.9850.2051.4152.6153.8054.9856.1558.4860.7763.0465.2867.4969.6871.84

23.3024.7426.1527.5428.9130.2531.5832.8934.1735.4536.7137.9539.1840.4041.6142.8043.9845.1646.3247.4748.6249.7550.8852.0053.1155.3157.4759.6261.7363.8365.9067.95

22.2623.6424.9926.3227.6228.9130.1731.4232.6533.8735.0736.2637.4438.6039.7540.8942.0243.1544.2645.3646.4547.5448.6149.6850.7452.8454.9156.9658.9860.9862.9664.92

21.4222.7424.0425.3226.5827.8129.0330.2331.4232.5933.7534.8936.0237.1438.2539.3540.4441.5142.5843.6444.7045.7446.7747.8048.8250.8452.8454.8156.7558.6860.5862.46

20.7222.0023.2524.4925.7026.9028.0829.2430.3931.5232.6433.7434.8435.9236.9938.0639.1140.1541.1942.2143.2344.2445.2446.2347.2249.1751.1053.0154.8956.7558.5960.41

19.1320.3121.4722.6123.7424.8425.9327.0028.0629.1130.1431.1632.1733.1734.1635.1436.1237.0838.0338.9839.9240.8541.7842.7043.6145.4147.1948.9550.6952.4154.1155.79

RADIUS OF RELATIVE STIFFNESS (L)VALUES IN INCHES

L =

E = Young’s Modulus = 4 x 10 psi

k = Subgrade Modulus, lb/in

d = Rigid Pavement Thickness, inches

= Poisson’s Ratio = 0.15

Ed12 (1 − ) k = 24.1652

dk

WHERE

F_AC_070801_1_0030101_01_00

3

6

3

3

2

4 4

Radius of relative stiffness(Reference : Portland Cement Association)

FIGURE 1

7-8-1Page 2

Jan 01/11




Rigid Pavement Requirements - LCN Conversion

1. This section gives Rigid Pavement Requirements - LCN Conversion.

7-8-2Page 1

Jan 01/11



6070

8090

100

5040

3020

102030405060708090100

110

120

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

EQUIVALENT SINGLE WHEEL LOAD [x 1 000 lb]

120

150

6070

8090

100

50LO

AD

CLA

SS

IFIC

AT

ION

NU

MB

ER

(LC

N)

5101520253035404550

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65

1 40

0x53

0R23

TIR

ES

EQUIVALENT SINGLE WHEEL LOAD [x 1 000 kg]

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(233

psi

)

117

950

kg (

260

025

lb)

110

000

kg (

242

500

lb)

100

000

kg (

220

460

lb)

90 0

00 k

g (1

98 4

10 lb

)80

000

kg

(176

000

lb)

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

M

RA

MP

WE

IGH

T A

ND

AF

T C

G

NO

TE

:

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

1 01

61

270

1 52

42

032

762

2 54

0

F_AC_070802_1_0130101_01_01

Rigid Pavement Requirements LCNMTOW 365 000 kg

FIGURE 1

7-8-2Page 2

Jan 01/11



6070

8090

100

5040

3020

102030405060708090100

110

120

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


120

150

6070

8090

100

50LO

AD

CLA

SS

IFIC

AT

ION

NU

MB

ER

(LC

N)

5101520253035404550

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65

1 40

0x53

0R23

TIR

ES


TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(233

psi

)

118

920

kg (

262

175

lb)

110

000

kg (

242

500

lb)

100

000

kg (

220

460

lb)

90 0

00 k

g (1

98 4

10 lb

)80

000

kg

(176

000

lb)

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

M

RA

MP

WE

IGH

T A

ND

AF

T C

G

NO

TE

:

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

1 01

61

270

1 52

42

032

762

2 54

0

F_AC_070802_1_0140101_01_01


FIGURE 2

7-8-2Page 3

Jan 01/11



6070

8090

100

5040

3020

102030405060708090100

110

120

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


120

150

6070

8090

100

50

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

5101520253035404550

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65

1 40

0x53

0R23

40P

R


TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

NO

TE

:

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

1 01

61

270

1 52

42

032

762

2 54

0

117

270

kg (

258

525

lb)

110

000

kg (

242

500

lb)

100

000

kg (

220

450

lb)

90 0

00 k

g (1

98 4

25 lb

)80

000

kg

(176

375

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

RM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

MA

XIM

UM

R

AM

P W

EIG

HT

AN

D A

FT

CG

F_AC_070802_1_0190101_01_00


FIGURE 3

7-8-2Page 4

Jan 01/11



6070

8090

100

5040

3020

102030405060708090100

110

120

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


120

150

6070

8090

100

50LO

AD

CLA

SS

IFIC

AT

ION

NU

MB

ER

(LC

N)

5101520253035404550

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

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n 19

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ES


TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

121

020

kg (

266

800

lb)

110

000

kg (

242

500

lb)

100

000

kg (

220

460

lb)

90 0

00 k

g (1

98 4

10 lb

)80

000

kg

(176

000

lb)

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

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M

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T A

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:

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TIF

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mm

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1 01

61

270

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F_AC_070802_1_0150101_01_01


FIGURE 4

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5040

3020

102030405060708090100

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(233

psi

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MA

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EA

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OA

D A

T M

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IMU

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7 95

0 kg

(26

0 02

5 lb

)11

0 00

0 kg

(24

2 50

0 lb

)10

0 00

0 kg

(22

0 46

0 lb

)90

000

kg

(198

410

lb)

80 0

00 k

g (1

76 0

00 lb

)

WE

IGH

T O

N O

NE

MA

IN L

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mm

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F_AC_070802_1_0160101_01_01


FIGURE 5

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8090

100

5040

3020

102030405060708090100

110

120

RA

DIU

S O

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ELA

TIV

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TIF

FN

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S [I

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S]


120

150

6070

8090

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LCN

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5101520253035404550

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TIR

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(233

psi

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MA

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IBLE

MA

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EA

R L

OA

D A

T M

AX

IMU

M

RA

MP

WE

IGH

T A

ND

AF

T C

G

NO

TE

:

119

540

kg (

263

525

lb)

110

000

kg (

242

500

lb)

100

000

kg (

220

460

lb)

90 0

00 k

g (1

98 4

10 lb

)80

000

kg

(176

000

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

RA

DIU

S O

F R

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TIV

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TIF

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S (

mm

)

508

1 01

61

270

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F_AC_070802_1_0170101_01_01


FIGURE 6

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8090

100

5040

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102030405060708090100

110

120

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DIU

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S [I

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HE

S]


120

150

6070

8090

100

50

LOA

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LCN

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EE

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n 19

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R


TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

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6.1

bar

(234

psi

)

NO

TE

:

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

1 01

61

270

1 52

42

032

762

2 54

0

119

680

kg (

263

850

lb)

110

000

kg (

242

500

lb)

100

000

kg (

220

450

lb)

90 0

00 k

g (1

98 4

25 lb

)80

000

kg

(176

375

lb)

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

M

RA

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T A

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AF

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G

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N O

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IN L

AN

DIN

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130

F_AC_070802_1_0200101_01_00


FIGURE 7

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100

5040

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120

150

6070

8090

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LCN

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TIR

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psi

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NO

TE

:

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F R

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TIV

E S

TIF

FN

ES

S (

mm

)50

81

016

1 27

01

524

2 03

276

22

540

118

440

kg (

261

125

lb)

110

000

kg (

242

500

lb)

100

000

kg (

220

450

lb)

90 0

00 k

g (1

98 4

25 lb

)80

000

kg

(176

375

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

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EA

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AX

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F_AC_070802_1_0210101_01_00


FIGURE 8

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6070

8090

100

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(LC

N)

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E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

120

590

kg (

265

850

lb)

110

000

kg (

242

500

lb)

100

000

kg (

220

460

lb)

90 0

00 k

g (1

98 4

10 lb

)80

000

kg

(176

000

lb)

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

M

NO

TE

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WE

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T A

ND

AF

T C

G

WE

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NE

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AN

DIN

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F R

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FIGURE 9

7-8-2Page 10

Jan 01/11


7-8-3 Radius of Relative Stiffness (Other values of E and L)

**ON A/C A340-500 A340-600

Radius of Relative Stiffness (Other values of ”E” and ”L”)

1. General

The table of Chapter 7-8-1, Figure: Radius of Relative Stiffness, presents ”L” values based onYoung’s Modulus (E) of 4 000 000 psi and Poisson’s Ratio (µ) of 0.15.

To find ”L” values based on other values of ”E” and ”µ”.See Section 7-8-4, Figure: Radius of Relative Stiffness (Other values of ”E” and ”µ”).

For example, to find an ”L” value based on an ”E” of 3 000 000 psi, the ”E” factor of 0.931 ismultiplied by the ”L” value found in the table of Section 7-8-1, Figure: Radius of Relative Stiffness.

The effect of variations of ”µ” on the ”L” value is treated in a similar manner.

7-8-3Page 1

Jan 01/11



**ON A/C A340-500 A340-600

Radius of Relative Stiffness

1. This section gives Radius of Relative Stiffness.

7-8-4Page 1

Jan 01/11


**ON A/C A340-500 A340-600

1.10

1.05

1.00

0.95

0.90

0.85

0.800 1 2 3 4 5

0.00 0.05 0.10 0.15 0.20 0.25

NOTE:

1.015

1.010

1.005

0.995

1.000

BOTH CURVES ON THIS PAGE ARE USED TO ADJUST THE VALUES OF TABLE 7.8.1

F_AC_070804_1_0030101_01_00

VALUESEFFECT OF "E" ON " "

"E", Young’s Modulus (10 , psi)

EFFECT OF " "" " ON VALUES

, Poisson’s Ratio" "

"E"

Fac

tor

Fac

tor

""

" "

Radius of Relative Stiffness(Effect of ”E” and ”µ” on ”L” values)

FIGURE 1

7-8-4Page 2

Jan 01/11


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


ACN/PCN Reporting System - Flexible and Rigid Pavements


1. General

To find the ACN of an aircraft on flexible or rigid pavement, both the aircraft gross weight and thesubgrade strength must be known.

In the example shown in Section 7-9-1, Figure: Aircraft Classification Number - Flexible Pavement -MTOW 365 000 kg - A340-600WV0xx- For an Aircraft Gross Weight of 270 000 kg (595 250 lb) and low subgrade strength (code B),

the ACN for the flexible pavement is 46.6.In the example shown in Section 7-9-2, Figure: Aircraft Classification Number - Rigid Pavement -MTOW 365 000 kg - A340-600WV0xx- For an Aircraft Gross Weight of 350 000 kg (771 620 lb) and low subgrade strength (code B),

the ACN for the rigid pavement is 65.5.In the example shown in Section 7-9-1, Figure: Aircraft Classification Number - Flexible Pavement -MTOW 368 000 kg - A340-600WV0xx- For an Aircraft Gross Weight of 270 000 kg (595 250 lb) and low subgrade strength (code B),

the ACN for the flexible pavement is 46.5.In the example shown in Section 7-9-2, Figure: Aircraft Classification Number - Rigid Pavement -MTOW 368 000 kg - A340-600WV0xx.- For an Aircraft Gross Weight of 350 000 kg (771 620 lb) and low subgrade strength (code B) the

ACN for the rigid pavement is 65.

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


2. General

To find the ACN of an aircraft on flexible or rigid pavement, both the aircraft gross weight and thesubgrade strength must be known.In the example shown in Section 7-9-1, Figure: Aircraft Classification Number - Flexible Pavement -MTOW 365 000 kg - A340-600WV1xx- For an Aircraft Gross Weight of 270 000 kg (595 250 lb) and low subgrade strength (code B),

the ACN for the flexible pavement is 45.7.

7-9-0Page 1

Jan 01/11


In the example shown in Section 7-9-2, Figure: Aircraft Classification Number - Rigid Pavement -MTOW 365 000 kg - A340-600WV1xx- For an Aircraft Gross Weight of 280 000 kg (617 300 lb) and low subgrade strength (code B) the

ACN for the rigid pavement is 48.In the example shown in Section 7-9-1, Figure: Aircraft Classification Number - Flexible Pavement -MTOW 380 000 kg - A340-600WV1xx- For an Aircraft Gross Weight of 280 000 kg (617 300 lb) and low subgrade strength (code B),

the ACN for the flexible pavement is 46.8.In the example shown in Section 7-9-2, Figure: Aircraft Classification Number - Rigid Pavement -MTOW 380 000 kg - A340-600WV1xx- For an Aircraft Gross Weight of 280 000 kg (617 300 lb) and low subgrade strength (code B) the

ACN for the rigid pavement is 64.



3. General



the ACN for the flexible pavement is 46.5.

In the example shown in Section 7-9-2, Figure: Aircraft Classification Number - Rigid Pavement -MTOW 368 000 kg - A340-500WV0xx- For an Aircraft Gross Weight of 350 000 kg (771 620 lb) and low subgrade strength (code B),

the ACN for the flexible pavement is 65.




7-9-0Page 2

Jan 01/11







4. General









7-9-0Page 3

Jan 01/11


7-9-1 Aircraft Classification Number - Flexible Pavement


Aircraft Classification Number - Flexible Pavement

1. This section gives the Aircraft Classification Number - Flexible Pavement.

7-9-1Page 1

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1 40

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40P

R T

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S

AC

N W

AS

DE

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AN

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G G

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PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

1 ba

r (2

34 p

si) (x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

160

180

200

220

240

260

280

300

320

340

360

380

125

115

105 95 85 75 65 55 45 35 25

400

440

480

520

560

600

640

680

720

760

800

SU

BG

RA

DE

ST

RE

NG

TH

D C B A

3 (U

LTR

A L

OW

)6

(LO

W)

10 (

ME

DIU

M)

15 (

HIG

H)

−C

BR

−C

BR

−C

BR

−C

BR

360

ALP

HA

FA

CT

OR

= 0

.8

(x 1

000

kg)

AIRCRAFT CLASSIFICATION NUMBER (ACN)P

AV

EM

EN

T −

MT

OW

365

000

kg

− A

340−

600W

V0x

x

F_AC_070901_1_0280101_01_01

Aircraft Classification Number -- Flexible PavementMTOW 365 000 kg

FIGURE 1

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Jan 01/11



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N W

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198

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: 34.

43 %

MA

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N 7

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: LA

ND

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AR

LO

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ON

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E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

160

180

200

220

240

260

280

300

320

340

360

380

125

115

105 95 85 75 65 55 45 35 25

400

440

480

520

560

600

640

680

720

760

800

360

(x 1

000

kg)

SU

BG

RA

DE

ST

RE

NG

TH

D C B A

3 (U

LTR

A L

OW

)6

(LO

W)

10 (

ME

DIU

M)

15 (

HIG

H)

−C

BR

−C

BR

−C

BR

−C

BR

ALP

HA

FA

CT

OR

= 0

.8


AV

EM

EN

T −

MT

OW

368

000

kg

− A

340−

600W

V0x

x

F_AC_070901_1_0290101_01_01


FIGURE 2

7-9-1Page 3

Jan 01/11



1 40

0x53

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40P

R T

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S

AC

N W

AS

DE

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: 35

% M

AC

. S

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SE

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ION

7−

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FIG

UR

E: L

AN

DIN

G G

EA

R L

OA

DIN

G O

NT

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

1 ba

r (2

34 p

si)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

160

180

200

220

240

260

280

300

320

340

360

380

125

115

105 95 85 75 65 55 45 35 25

400

440

480

520

560

600

640

680

720

760

800

SU

BG

RA

DE

ST

RE

NG

TH

D C B A

3 (U

LTR

A L

OW

)6

(LO

W)

10 (

ME

DIU

M)

15 (

HIG

H)

−C

BR

−C

BR

−C

BR

−C

BR

360

ALP

HA

FA

CT

OR

= 0

.8

(x 1

000

kg)

AIRCRAFT CLASSIFICATION NUMBER (ACN)

PA

VE

ME

NT

− M

TO

W 3

65 0

00 k

g −

A34

0−60

0WV

1xx

F_AC_070901_1_0340101_01_00


FIGURE 3

7-9-1Page 4

Jan 01/11



1 40

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R T

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AC

N W

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: 30.

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N 7

−4−

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GE

AR

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ON

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RE

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ON

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T A

T 1

6.1

bar

(234

psi

)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

160

180

200

220

240

260

280

300

320

340

360

380

125

115

105 95 85 75 65 55 45 35 25

400

440

480

520

560

600

640

680

720

760

800

360

(x 1

000

kg)

SU

BG

RA

DE

ST

RE

NG

TH

D C B A

3 (U

LTR

A L

OW

)6

(LO

W)

10 (

ME

DIU

M)

15 (

HIG

H)

−C

BR

−C

BR

−C

BR

−C

BR

ALP

HA

FA

CT

OR

= 0

.8


PA

VE

ME

NT

− M

TO

W 3

80 0

00 k

g −

A34

0−60

0WV

1xx

F_AC_070901_1_0300101_01_01


FIGURE 4

7-9-1Page 5

Jan 01/11



1 40

0x53

0R23

40P

R T

IRE

S

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1. S

EC

ON

D E

DIT

ION

198

3.C

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 36.

5 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1, F

IGU

RE

: LA

ND

ING

GE

AR

LO

AD

ING

ON

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

160

180

200

220

240

260

280

300

320

340

360

380

125

115

105 95 85 75 65 55 45 35 25

400

440

480

520

560

600

640

680

720

760

800

360

(x 1

000

kg)

SU

BG

RA

DE

ST

RE

NG

TH

D C B A

3 (U

LTR

A L

OW

)6

(LO

W)

10 (

ME

DIU

M)

15 (

HIG

H)

−C

BR

−C

BR

−C

BR

−C

BR

ALP

HA

FA

CT

OR

= 0

.8


AV

EM

EN

T −

MT

OW

368

000

kg

− A

340−

500W

V0x

x

F_AC_070901_1_0310101_01_01


FIGURE 5

7-9-1Page 6

Jan 01/11



1 40

0x53

0R23

40P

R T

IRE

S

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1. S

EC

ON

D E

DIT

ION

198

3.C

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 36.

4 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1, F

IGU

RE

: LA

ND

ING

GE

AR

LO

AD

ING

ON

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

160

180

200

220

240

260

280

300

320

340

360

380

125

115

105 95 85 75 65 55 45 35 25

400

440

480

520

560

600

640

680

720

760

800

SU

BG

RA

DE

ST

RE

NG

TH

D C B A

3 (U

LTR

A L

OW

)6

(LO

W)

10 (

ME

DIU

M)

15 (

HIG

H)

−C

BR

−C

BR

−C

BR

−C

BR

360

ALP

HA

FA

CT

OR

= 0

.8

(x 1

000

kg)


PA

VE

ME

NT

− M

TO

W 3

72 0

00 k

g −

A34

0−50

0WV

0xx

F_AC_070901_1_0320101_01_01


FIGURE 6

7-9-1Page 7

Jan 01/11



1 40

0x53

0R23

40P

R T

IRE

S

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1. S

EC

ON

D E

DIT

ION

198

3.C

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 35.

01 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1, F

IGU

RE

: LA

ND

ING

GE

AR

LO

AD

ING

ON

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

160

180

200

220

240

260

280

300

320

340

360

380

125

115

105 95 85 75 65 55 45 35 25

400

440

480

520

560

600

640

680

720

760

800

360

(x 1

000

kg)

SU

BG

RA

DE

ST

RE

NG

TH

D C B A

3 (U

LTR

A L

OW

)6

(LO

W)

10 (

ME

DIU

M)

15 (

HIG

H)

−C

BR

−C

BR

−C

BR

−C

BR

ALP

HA

FA

CT

OR

= 0

.8


AV

EM

EN

T −

MT

OW

374

000

kg

− A

340−

500W

V0x

x

F_AC_070901_1_0350101_01_00


FIGURE 7

7-9-1Page 8

Jan 01/11



1 40

0x53

0R23

40P

R T

IRE

S

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1. S

EC

ON

D E

DIT

ION

198

3.C

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 36.

4 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1, F

IGU

RE

: LA

ND

ING

GE

AR

LO

AD

ING

ON

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

160

180

200

220

240

260

280

300

320

340

360

380

125

115

105 95 85 75 65 55 45 35 25

400

440

480

520

560

600

640

680

720

760

800

360

(x 1

000

kg)

SU

BG

RA

DE

ST

RE

NG

TH

D C B A

3 (U

LTR

A L

OW

)6

(LO

W)

10 (

ME

DIU

M)

15 (

HIG

H)

−C

BR

−C

BR

−C

BR

−C

BR

ALP

HA

FA

CT

OR

= 0

.8


AV

EM

EN

T −

MT

OW

372

000

kg

− A

340−

500W

V1x

x

F_AC_070901_1_0360101_01_00


FIGURE 8

7-9-1Page 9

Jan 01/11



1 40

0x53

0R23

40P

R T

IRE

S

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1. S

EC

ON

D E

DIT

ION

198

3.C

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 34.

7 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1, F

IGU

RE

: LA

ND

ING

GE

AR

LO

AD

ING

ON

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

160

180

200

220

240

260

280

300

320

340

360

380

125

115

105 95 85 75 65 55 45 35 25

400

440

480

520

560

600

640

680

720

760

800

360

(x 1

000

kg)

SU

BG

RA

DE

ST

RE

NG

TH

D C B A

3 (U

LTR

A L

OW

)6

(LO

W)

10 (

ME

DIU

M)

15 (

HIG

H)

−C

BR

−C

BR

−C

BR

−C

BR

ALP

HA

FA

CT

OR

= 0

.8


PA

VE

ME

NT

− M

TO

W 3

80 0

00 k

g −

A34

0−50

0WV

1xx

F_AC_070901_1_0330101_01_01


FIGURE 9

7-9-1Page 10

Jan 01/11


7-9-2 Aircraft Classification Number - Rigid Pavement


Aircraft Classification Number - Rigid Pavement

1. This section gives the Aircraft Classification Number - Rigid Pavement.

7-9-2Page 1

Jan 01/11



1 40

0x53

0R23

40P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

1 ba

r (2

34 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1.

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

5 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1, P

AG

E 2

SU

BG

RA

DE

ST

RE

NG

TH

D−

K =

C−

K =

B−

K =

A−

K =

125

115

105 95 85 75 65 55 45 35 2516

018

020

022

024

026

028

030

032

034

036

038

0

(x 1

000

kg)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T


20 N

M/m

(U

LTR

A L

OW

)40

NM

/m

(LO

W)

80 N

M/m

(M

ED

IUM

)15

0 N

M/m

(H

IGH

)

353

396

482

525

568

612

655

698

741

784

827

870

F_AC_070902_1_0280101_01_01

Aircraft Classification Number -- Rigid PavementMTOW 365 000 kg

FIGURE 1

7-9-2Page 2

Jan 01/11



1 40

0x53

0R23

40P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

1 ba

r (2

34 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1.

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

4.43

% M

AC

. S

EE

SE

CT

ION

7−

4−1,

PA

GE

3AIRCRAFT CLASSIFICATION NUMBER (ACN)

125

115

105 95 85 75 65 55 45 35 2516

018

020

022

024

026

028

030

032

034

036

038

0

(x 1

000

kg)

SU

BG

RA

DE

ST

RE

NG

TH

D−

K =

C−

K =

B−

K =

A−

K =

20 N

M/m

(U

LTR

A L

OW

)40

NM

/m

(LO

W)

80 N

M/m

(M

ED

IUM

)15

0 N

M/m

(H

IGH

)

(x 1

000

lb)

353

396

482

525

568

612

655

698

741

784

827

870

AIR

CR

AF

T G

RO

SS

WE

IGH

T

F_AC_070902_1_0290101_01_01


FIGURE 2

7-9-2Page 3

Jan 01/11



125

115

105 95 85 75 65 55 45 35 2516

018

020

022

024

026

028

030

032

034

036

038

0

(x 1

000

kg)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T


353

396

482

525

568

612

655

698

741

784

827

870

SU

BG

RA

DE

ST

RE

NG

TH

D−

K =

C−

K =

B−

K =

A−

K =

20 M

N/m

(U

LTR

A L

OW

)40

MN

/m

(LO

W)

80 M

N/m

(M

ED

IUM

)15

0 M

N/m

(H

IGH

)

1 40

0x53

0R23

40P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

1 ba

r (2

34 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1.

SE

CO

ND

ED

ITIO

N 1

983.

SE

E S

EC

TIO

N 7

−4−1

, PA

GE

4C

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 35

% M

AC

F_AC_070902_1_0340101_01_00


FIGURE 3

7-9-2Page 4

Jan 01/11



2535455565758595105

115

125 16

018

020

022

024

026

028

030

032

034

036

038

0

AIR

CR

AF

T G

RO

SS

WE

IGH

T


1 40

0x53

0R23

40P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

1 ba

r (2

34 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1.

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

0.2

% M

AC

. S

EE

SE

CT

ION

7−

4−1,

PA

GE

5

(x 1

000

kg)

SU

BG

RA

DE

ST

RE

NG

TH

D−

K =

C−

K =

B−

K =

A−

K =

20 N

M/m

(U

LTR

A L

OW

)40

NM

/m

(LO

W)

80 N

M/m

(M

ED

IUM

)15

0 N

M/m

(H

IGH

)

F_AC_070902_1_0300101_01_01

(x 1

000

lb)

353

396

482

525

568

612

655

698

741

784

827

870


FIGURE 4

7-9-2Page 5

Jan 01/11



1 40

0x53

0R23

40P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

1 ba

r (2

34 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1.

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

6.5

% M

AC

. S

EE

SE

CT

ION

7−

4−1,

PA

GE

6AIRCRAFT CLASSIFICATION NUMBER (ACN)

2535455565758595105

115

125 16

018

020

022

024

026

028

030

032

034

036

038

0

(x 1

000

kg)

SU

BG

RA

DE

ST

RE

NG

TH

D−

K =

C−

K =

B−

K =

A−

K =

20 N

M/m

(U

LTR

A L

OW

)40

NM

/m

(LO

W)

80 N

M/m

(M

ED

IUM

)15

0 N

M/m

(H

IGH

)

F_AC_070902_1_0310101_01_01

(x 1

000

lb)

353

396

482

525

568

612

655

698

741

784

827

870


FIGURE 5

7-9-2Page 6

Jan 01/11



1 40

0x53

0R23

40P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

1 ba

r (2

34 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1.

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

6.4

% M

AC

. S

EE

SE

CT

ION

7−

4−1,

PA

GE

S 7

AN

D 8

125

115

105 95 85 75 65 55 45 35 25


160

180

200

220

240

260

280

300

320

340

360

380

(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

SU

BG

RA

DE

ST

RE

NG

TH

D−

K =

C−

K =

B−

K =

A−

K =

20 N

M/m

(U

LTR

A L

OW

)40

NM

/m

(LO

W)

80 N

M/m

(M

ED

IUM

)15

0 N

M/m

(H

IGH

)

F_AC_070902_1_0320101_01_01

(x 1

000

lb)

353

396

482

525

568

612

655

698

741

784

827

870


FIGURE 6

7-9-2Page 7

Jan 01/11



F_AC_070902_1_0350101_01_00

1 40

0x53

0R23

40P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

1 ba

r (2

34 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1.

SE

CO

ND

ED

ITIO

N 1

983.

SE

E S

EC

TIO

N 7

−4−1

, PA

GE

S 9

AN

D 1

0C

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 35.

01 %

MA

C.

125

115

105 95 85 75 65 55 45 35 2516

018

020

022

024

026

028

030

032

034

036

038

0

(x 1

000

kg)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T


353

396

439

482

525

568

612

655

698

741

784

827

SU

BG

RA

DE

ST

RE

NG

TH

D−

K =

C−

K =

B−

K =

A−

K =

20 M

N/m

(U

LTR

A L

OW

)40

MN

/m

(LO

W)

80 M

N/m

(M

ED

IUM

)15

0 M

N/m

(H

IGH

)


FIGURE 7

7-9-2Page 8

Jan 01/11



1 40

0x53

0R23

40P

R T

IRE

S

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1. S

EC

ON

D E

DIT

ION

198

3.C

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 36.

4 %

MA

CS

EE

SE

CT

ION

7−

4−1,

FIG

UR

E: L

AN

DIN

G G

EA

R L

OA

DIN

G O

NT

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

1 ba

r (2

34 p

si)

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

160

180

200

220

240

260

280

300

320

340

360

380

125

115

105 95 85 75 65 55 45 35 25

396

482

525

568

612

655

698

784

827

870

913

353

(x 1

000

kg)


SU

BG

RA

DE

ST

RE

NG

TH

D C B A

(ULT

RA

LO

W)

(LO

W)

(ME

DIU

M)

(HIG

H)

− − −−

K =

20

MN

/mK

= 4

0 M

N/m

K =

80

MN

/mK

= 1

50 M

N/m

F_AC_070902_1_0360101_01_01

PA

VE

ME

NT

− M

TO

W 3

72 0

00 k

g −

A34

0−50

0WV

1xx


FIGURE 8

7-9-2Page 9

Jan 01/11



2535455565758595105

115

125 16

018

020

022

024

026

028

030

032

034

036

038

0

AIR

CR

AF

T G

RO

SS

WE

IGH

T

AIRCRAFT CLASSIFICATION NUMBER (ACN)14

00x5

30R

23 4

0PR

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.1

bar

(234

psi

)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1.

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

4.7

% M

AC

. S

EE

SE

CT

ION

7−

4−1.

( x1

000

kg )

( x1

000

lb )

400

450

500

550

600

650

700

750

800

F_AC_070902_1_0330101_01_00

SU

BG

RA

DE

ST

RE

NG

TH

D−

K =

C−

K =

B−

K =

A−

K =

20 N

M/m

(U

LTR

A L

OW

)40

NM

/m

(LO

W)

80 N

M/m

(M

ED

IUM

)15

0 N

M/m

(H

IGH

)


FIGURE 9

7-9-2Page 10

Jan 01/11


DERIVATIVE AIRPLANES

8-1-0 Possible Future Derivative Airplane

**ON A/C A340-500 A340-600

Possible Future Derivative Airplane

1. General

Other versions of the A340 airplane are being studied to satisfy customer requests.

In the future, this program could have new versions:- Additional passenger capacity,- Additional cargo modularity,- New design version,- Different range or payload.

If these new aircraft definitions are developed, the design and weight will be considered in accordancewith airport facilities.

8-1-0Page 1

Jan 01/11


SCALED DRAWINGS

9-1-0 Scaled Drawing 1 in. = 500 ft.

**ON A/C A340-500 A340-600

Scaled Drawing 1 in. = 50 ft.

1. This section provides the Scaled Drawing - 1 in. = 50 ft.

9-1-0Page 1

Jan 01/11


**ON A/C A340-600

F_AC_090100_1_0090101_01_01

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS

AIR CONDITIONINGA

BULK CARGO COMPT DOORB

CARGO COMPT DOORC

ELECTRICAL

LAVATORY

MAIN LANDING GEARMLG

NOSE GEARNG

CENTER LINE GEARCLG

PASSENGER/CREW DOORX

E

L

FUEL

POTABLE WATER

F

H²O

LEGEND:

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

PNEUMATICP

NG

E

X X

XX

CLG

XX

X

H²OC

B

AP

X

L

F F

C

MLGMLG

Scaled Drawing1 in. = 50 ft.FIGURE 1

9-1-0Page 2

Jan 01/11


**ON A/C A340-500

F_AC_090100_1_0110101_01_01

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS

AIR CONDITIONINGA


CARGO COMPT DOORC

ELECTRICAL

LAVATORY


NOSE GEARNG

CENTER LINE GEARCLG


E

L

FUEL

POTABLE WATER

F

H²O

LEGEND:


PNEUMATICP

NG

E

X X

C

XX

FF AP

CLG MLGMLG

X

H²OC

B

X

L


9-1-0Page 3

Jan 01/11


**ON A/C A340-600

F_AC_090100_1_0100101_01_01

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS



9-1-0Page 4

Jan 01/11


**ON A/C A340-500

F_AC_090100_1_0120101_01_01

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS



9-1-0Page 5

Jan 01/11


9-2-0 Scaled Drawing 1 cm. = 500 cm.

**ON A/C A340-500 A340-600

Scaled Drawing 1 cm. = 500 cm.

1. This section provides the Scaled Drawing - 1 cm. = 500 cm.

9-2-0Page 1

Jan 01/11


**ON A/C A340-600

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS

AIR CONDITIONINGA


CARGO COMPT DOORC

ELECTRICAL

LAVATORY


NOSE GEARNG

CENTER LINE GEARCLG


E

L

FUEL

POTABLE WATER

F

H²O

LEGEND:


PNEUMATICP

NG

E

X X

XX

CLG

XX

X

H²OC

B

AP

X

L

F F

C

MLGMLG

F_AC_090200_1_0090101_01_01

Scaled Drawing1 cm. = 500 cm.

FIGURE 1

9-2-0Page 2

Jan 01/11


**ON A/C A340-500

F_AC_090200_1_0120101_01_01

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS

AIR CONDITIONINGA


CARGO COMPT DOORC

ELECTRICAL

LAVATORY


NOSE GEARNG

CENTER LINE GEARCLG


E

L

FUEL

POTABLE WATER

F

H²O

LEGEND:


PNEUMATICP

NG

E

X X

C

XX

FF AP

CLG MLGMLG

X

H²OC

B

X

L


FIGURE 2

9-2-0Page 3

Jan 01/11


**ON A/C A340-600

F_AC_090200_1_0130101_01_01

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS



FIGURE 3

9-2-0Page 4

Jan 01/11


**ON A/C A340-500

F_AC_090200_1_0100101_01_01

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS



FIGURE 4

9-2-0Page 5

Jan 01/11

Airbus_AC_A340-500_600_Jan11

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