Airbus-AC-A340-200-300-Apr2013

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@AIRBUS

A340-200/-300

AIRCRAFT CHARACTERISTICSAIRPORT AND MAINTENANCE PLANNING

AC

The content of this document is the property of Airbus.It is supplied in confidence and commercial security on its contents must be maintained.It must not be used for any purpose other than that for which it is supplied, nor mayinformation contained in it be disclosed to unauthorized persons.It must not be reproduced in whole or in part without permission in writing from the owners of the copyright. Requests for reproduction of any data in this document and the media authorizedfor it must be addressed to Airbus.

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

AIRBUS S.A.S.

Customer Services

Technical Data Support and Services

31707 Blagnac Cedex

FRANCE

Issue: Jul 30/92 Rev: Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013


@A340-200/-300 AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

HIGHLIGHTS

Revision No. 20 - Apr 01/13

LOCATIONS CHGCODE

DESCRIPTIONS OF CHANGE

CHAPTER 1

Section 1-1

Subject 1-1-0

Purpose R PURPOSE CHANGED DUE TO MERGINGOF THE MFP AND AC MANUALS.

Section 1-2 R

Subject 1-2-1 N

Glossary NSubject 01-02-00 D

CHAPTER 2 R

Section 2-1 R

Subject 02-01-00 D

Subject 2-1-1 R

General Aircraft Characteristics Data R DESCRIPTION TITLE UPDATED

Section 2-2 R

Subject 2-2-0 RGeneral Aircraft Dimensions R DESCRIPTION TITLE UPDATED

FIGURE General Aircraft Dimensions R ILLUSTRATION REVISED

FIGURE General Aircraft Dimensions R ILLUSTRATION REVISED

Section 2-3

Subject 2-3-0

Ground Clearances R ADDED GROUND CLEARANCES FORFLIGHT CONTROLSUPDATED FIGURES LAYOUT.

FIGURE Ground Clearances R ILLUSTRATION REVISED

FIGURE Ground Clearances N ILLUSTRATION ADDED

FIGURE Ground Clearances - Ailerons Up R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

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LOCATIONS CHGCODE


FIGURE Ground Clearances - AileronsDown

R ILLUSTRATION REVISEDPART EFFECTIVITY

ADDED/REVISED/DELETED

FIGURE Ground Clearances - SpoilersExtended

R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Clearances - Slats FullyExtended

N ILLUSTRATION ADDED

FIGURE Ground Clearances - Flaps FullyExtended


FIGURE Ground Clearances - Flaps-

Tracks Fully Extended


Section 2-4 R

Subject 02-04-00 D

Subject 2-4-1 R

Interior Arrangements - Plan View R DESCRIPTION TITLE UPDATED

FIGURE Interior Arrangements - PlanView - Typical Configuration

R ILLUSTRATION REVISED





Section 2-5 R

Subject 2-5-0 R

Interior Arrangements - Cross Section R REVISED TITLE TO ”INTERIORARRANGEMENTS - CROSS SECTION”.DESCRIPTION TITLE UPDATED

FIGURE Interior Arrangements - CrossSection - Typical Configuration


Section 2-6 RSubject 02-06-00 D

Subject 2-6-1 R

Lower Deck Cargo Compartments R

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LOCATIONS CHGCODE


FIGURE Lower Deck CargoCompartments - Location and Dimensions

R

FIGURE Lower Deck CargoCompartments - Loading Combinations


FIGURE Lower Deck CargoCompartments - Loading Combinations


Section 2-7

Subject 2-7-0

Door Clearances N

FIGURE Door Identification and Location- Door Identification


FIGURE Door Identification and Location- Door Identification


Section 2-8 N

Subject 2-8-0 N

Escape Slides N

FIGURE Escape Slides - Location N ILLUSTRATION ADDED

FIGURE Escape Slides - Location N ILLUSTRATION ADDED

Section 2-9 N

Subject 2-9-0 N

Landing Gear Maintenance Pits N

FIGURE Landing Gear Maintenance Pits -Maintenance Pit Envelopes


FIGURE Landing Gear Maintenance Pits -Maintenance Pit Envelopes


Landing Gear N

FIGURE Main Landing Gear - General N ILLUSTRATION ADDED

FIGURE Centerline Landing Gear -

General


FIGURE Nose Landing Gear - General N ILLUSTRATION ADDED

Section 2-10 N

Subject 2-10-0 N

Exterior Lighting N

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LOCATIONS CHGCODE


FIGURE Exterior Lighting N ILLUSTRATION ADDED

FIGURE Exterior Lighting N ILLUSTRATION ADDEDSection 2-11 N

Subject 2-11-0 N

Antennas and Probes Location N

FIGURE Antennas and Probes - Location N ILLUSTRATION ADDED

FIGURE Antennas and Probes - Location N ILLUSTRATION ADDED

Section 2-12 N

Subject 2-12-0 N

Engine and Nacelle N

FIGURE Engine and Nacelle - EngineDimensions - CFM 56-5C


FIGURE Engine and Nacelle - NacelleDimensions - CFM 56-5C


FIGURE Engine and Nacelle - Fan Cowls -CFM 56-5C


FIGURE Engine and Nacelle - ThrustReverser Cowls - CFM 56-5C


Subject 2-12-1 N

Auxiliary Power Unit N

FIGURE Auxiliary Power Unit - AccessDoors


Section 2-13 N

Subject 2-13-0 N

Leveling, Symmetry and Alignment N

FIGURE Location of Leveling Points N ILLUSTRATION ADDED

FIGURE Location of Leveling Points N ILLUSTRATION ADDED

Section 2-14 N

Subject 2-14-0 NJacking for Maintenance N

FIGURE Jacking for Maintenance -Jacking Points Location


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LOCATIONS CHGCODE


FIGURE Jacking for Maintenance -Jacking Points Location


FIGURE Jacking for Maintenance -Forward Jacking Point


FIGURE Jacking for Maintenance - WingJacking Points


FIGURE Jacking for Maintenance -Auxiliary Jacking Point - Safety Stay


FIGURE Jacking for Maintenance -Jacking Dimensions


FIGURE Jacking for Maintenance -

Jacking Dimensions


FIGURE Jacking for Maintenance - Loadat the Aircraft Jacking Points


FIGURE Jacking for Maintenance - Loadat the Aircraft Jacking Points


Subject 2-14-1 N

Jacking for Wheel Change N

FIGURE Jacking for Wheel Change - MLGJacking Point Heights


FIGURE Jacking for Wheel Change -Jacking of the NLG


FIGURE Jacking for Wheel Change -Jacking of the CLG


FIGURE Jacking for Wheel Change - MLGJacking Point Loads


FIGURE Jacking for Wheel Change - MLGJacking Point Loads


FIGURE Jacking for Wheel Change - NLG

Jacking Point Loads


FIGURE Jacking for Wheel Change - NLGJacking Point Loads


FIGURE Jacking for Wheel Change - CLGJacking Point Loads


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LOCATIONS CHGCODE


FIGURE Jacking for Wheel Change - CLGJacking Point Loads


Subject 2-14-2 N

Support of Aircraft N

FIGURE Support of Aircraft - Location of Shoring Cradles


FIGURE Support of Aircraft - Location of Shoring Cradles


CHAPTER 3 R

Section 3-5 R

Subject 3-5-0

Final Approach Speed N

Subject 03-05-01 D

CHAPTER 4

Section 4-2

Subject 4-2-0

FIGURE Turning Radii - (Sheet 1) R

FIGURE Turning Radii - (Sheet 2) R ILLUSTRATION REVISED

FIGURE Turning Radii - (Sheet 2) R ILLUSTRATION REVISED

Section 4-3

Subject 4-3-0

FIGURE Minimum Turning Radii R

FIGURE Minimum Turning Radii R

Section 4-4

Subject 4-4-0

Visibility from Cockpit in Static Position R

FIGURE Visibility from Cockpit in StaticPosition

R

FIGURE Binocular Visibility ThroughWindows from Captain Eye Position


Section 4-5

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LOCATIONS CHGCODE


Subject 4-5-3

FIGURE 180˚ Turn on a Runway RFIGURE 180˚ Turn on a Runway R

FIGURE 180˚ Turn on a Runway R

FIGURE 180˚ Turn on a Runway R

Section 4-7 R

Subject 4-7-0 R

CHAPTER 5 R

Section 5-1 R

Subject 5-1-0 RSubject 5-1-1

Symbols Used on Servicing Diagrams R ADDED ”BULK TRAIN” AND DELETED”MAIN DECK CARGO LOADER”.

Subject 5-1-2 R

Typical Ramp Layout - Open Apron R ADDED ”STAND SAFETY LINE”DEFINITION.DESCRIPTION TITLE UPDATED

FIGURE Typical Ramp Layout - OpenApron


FIGURE Typical Ramp Layout - OpenApron


Subject 5-1-3 R

Typical Ramp Layout - Gate R ADDED ”STAND SAFETY LINE”DEFINITION.DESCRIPTION TITLE UPDATED

FIGURE Typical Ramp Layout - Gate R ILLUSTRATION REVISED

FIGURE Typical Ramp Layout - Gate R ILLUSTRATION REVISED

Section 5-2 R

Subject 5-2-0 R

Terminal Operations - Full Servicing TurnRound Time

N

FIGURE Full Servicing Turn Round TimeChart


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LOCATIONS CHGCODE


Terminal Operations - Full Servicing TurnRound Time

N

FIGURE Full Servicing Turn Round TimeChart


Subject 05-02-01 D

Section 5-3 R

Subject 5-3-0 R

Terminal Operations - Minimum ServicingTurn-Round Time

N

FIGURE Minimum Servicing Turn-RoundTime


Terminal Operations - Minimum ServicingTurn-Round Time

N

FIGURE Minimum Servicing Turn-RoundTime


Subject 05-03-01 D

Section 5-4 R

Subject 05-04-00 D

Subject 5-4-1

Ground Service Connections Layout R

FIGURE Ground Service ConnectionsLayout


Subject 5-4-3

Hydraulic System R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Service Connections -Green System Ground Service Panel


FIGURE Ground Service Connections -Blue System Ground Service Panel


FIGURE Ground Service Connections -Yellow System Ground Service Panel


Subject 5-4-4

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LOCATIONS CHGCODE


Electrical System R PART EFFECTIVITYADDED/REVISED/DELETED

NOTE AMENDEDFIGURE Ground Service Connections -Electrical Service Panel


Subject 5-4-5

Oxygen System R PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Ground Service Connections -Oxygen System


Subject 5-4-6Fuel System R

Subject 5-4-7

Pneumatic System R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Service Connections - LPand HP Ground Connectors


Subject 5-4-8

Potable Water System N

FIGURE Ground Service Connections -Potable-Water Ground Service Panels


Potable Water System N

FIGURE Ground Service Connections -Potable-Water Ground Service Panels


Subject 5-4-9

APU Oil System R ADDED ACCESS DOORS FOR ”APU OILSERVICING”.

FIGURE Ground Service Connections -

APU Oil Servicing

R

Subject 5-4-10

Vacuum Toilet System R PART EFFECTIVITYADDED/REVISED/DELETED

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LOCATIONS CHGCODE


FIGURE Ground Service Connections -Waste Water Ground Service Panel


Section 5-5 R

Subject 5-5-0

Engine Starting Pneumatic Requirements R ADDED PERFORMANCE REQUIREMENTSFOR PNEUMATIC ENGINE STARTING.CROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETED

FIGURE Example for Use of the Charts R ILLUSTRATION REVISED

FIGURE Engine Starting PneumaticRequirements - CFM56-5C2 Series


Subject 05-05-01 D

Subject 05-05-02 D

Subject 05-05-03 D

Section 5-6 R

Subject 5-6-0

Ground Pneumatic Power Requirements N ADDED PERFORMANCE REQUIREMENTSOF THE GROUND PNEUMATIC SERVICEEQUIPMENT FOR HEATING ANDCOOLING OF THE CABIN.

FIGURE Ground Pneumatic PowerRequirements - Heating


FIGURE Ground Pneumatic PowerRequirements - Cooling


Subject 05-06-01 D

Subject 05-06-02 D

Section 5-7

Subject 5-7-0

Preconditioned Airflow Requirements R UPDATED REQUIREMENTS FORPRECONDITIONED AIRFLOW AT THEGROUND CONNECTION.

FIGURE Preconditioned AirflowRequirements

R

Section 5-8

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LOCATIONS CHGCODE


Subject 5-8-0

Ground Towing Requirements R DELETED THE TEXT ”REVISION C” AND”ISSUE C” FOR THE SAE ARP 1915 ANDSAE AS 1614 STANDARDS. DELETED THETEXT ABOUT SHEAR PINARRANGEMENT. DELETED THEILLUSTRATIONS OF ”TYPICAL TOWBARCONFIGURATION” AND ”MAXIMUMEXTENSION OF THE NLG SHOCKABSORBER”.DELETED THE TEXT ”REVISION C” AND”ISSUE C” FOR THE SAE ARP 1915 AND

SAE AS 1614 STANDARDS. DELETED THETEXT ABOUT SHEAR PINARRANGEMENT.

Section 5-9 N

Subject 5-9-0 N

De-Icing and External Cleaning N

CHAPTER 7

Section 7-1

Subject 7-1-0

General Information N TEXT UPDATED

Section 7-2

Subject 7-2-0

Landing Gear Footprint R ILLUSTRATIONS UPDATED

FIGURE Landing Gear Footprint R ILLUSTRATION REVISED

FIGURE Landing Gear Footprint R

Section 7-3

Subject 7-3-0

Maximum Pavement Loads R ILLUSTRATIONS UPDATEDFIGURE Maximum Pavement Loads R ILLUSTRATION REVISED

FIGURE Maximum Pavement Loads R

Section 7-4 R

Subject 7-4-0

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LOCATIONS CHGCODE


Landing Gear Loading on Pavement R ILLUSTRATIONS AND EXAMPLEUPDATED.

FIGURE Landing Gear Loading onPavement - WV000, MRW 254 400 kg








Subject 07-04-01 D

Subject 07-04-02 D

Subject 07-04-03 D

Section 7-5 R

Subject 7-5-0

Flexible Pavement Requirements - USArmy Corps of Engineers Design MethodS-77-1

R ILLUSTRATIONS AND EXAMPLEUPDATED.DESCRIPTION TITLE UPDATED

FIGURE Flexible Pavement Requirements- WV000, MRW 254 400 kg, CG 37.7 %


FIGURE Flexible Pavement Requirements- WV000, MRW 254 400 kg, CG 38.18 %


Subject 07-05-01 D

Section 7-6 R

Subject 7-6-0

Flexible Pavement Requirements - LCNConversion

R TEXT, ILLUSTRATIONS AND EXAMPLEUPDATED.

FIGURE Flexible Pavement Requirements- LCN table


FIGURE Flexible Pavement Requirements- LCN - WV000, MRW 254 400 kg, CG37.7 %


FIGURE Flexible Pavement Requirements- LCN table


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LOCATIONS CHGCODE


FIGURE Flexible Pavement Requirements- LCN - WV000, MRW 254 400 kg, CG

38.18 %


Subject 07-06-01 D

Section 7-7 R

Subject 7-7-0

Rigid Pavement Requirements - PortlandCement Association Design Method

R TEXT, ILLUSTRATIONS AND EXAMPLEUPDATED.NOTE AMENDED

FIGURE Rigid Pavement Requirements -WV000, MRW 254 400 kg, CG 37.7 %


FIGURE Rigid Pavement Requirements -WV000, MRW 254 400 kg, CG 38.18 %


Subject 07-07-01 D

Section 7-8 R

Subject 7-8-0

Rigid Pavement Requirements - LCNConversion


FIGURE Rigid Pavement Requirements -LCN table


FIGURE Rigid Pavement Requirements -LCN table


FIGURE Radius of Relative Stiffness (L) N ILLUSTRATION ADDED

FIGURE Rigid Pavement Requirements -LCN - WV000, MRW 254 400 kg, CG37.7 %


FIGURE Rigid Pavement Requirements -LCN - WV021, MRW 275 900 kg, CG 37%


FIGURE Rigid Pavement Requirements -

LCN - WV000, MRW 254 400 kg, CG38.18 %


FIGURE Rigid Pavement Requirements -LCN - WV028, MRW 277 400 kg, CG 35%


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LOCATIONS CHGCODE


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


Subject 07-08-01 D

Subject 07-08-02 D

Subject 07-08-03 D

Subject 07-08-04 D

Section 7-9 R

Subject 7-9-0

Aircraft Classification Number - Flexibleand Rigid Pavements


DESCRIPTION TITLE UPDATEDFIGURE Aircraft Classification Number -ACN Table


FIGURE Aircraft Classification Number -Flexible Pavement - WV000, MRW 254400 kg, CG 37.7 %


FIGURE Aircraft Classification Number -Flexible Pavement - WV021, MRW 275900 kg, CG 37 %


FIGURE Aircraft Classification Number -

ACN Table


FIGURE Aircraft Classification Number -Flexible Pavement - WV000, MRW 254400 kg, CG 38.18 %


FIGURE Aircraft Classification Number -Flexible Pavement - WV028, MRW 277400 kg, CG 35 %


Subject 07-09-01 D

Subject 07-09-02 D

CHAPTER 8 R

Section 8-0 N

Subject 8-0-0 N

Scaled Drawings N

FIGURE Scaled Drawing N ILLUSTRATION ADDED

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LOCATIONS CHGCODE


FIGURE Scaled Drawing N ILLUSTRATION ADDED

Section 08-01 DCHAPTER 10 N

Section 10-0 N

Subject 10-0-0 N

Aircraft Rescue and Fire Fighting N

FIGURE Front Page N ILLUSTRATION ADDED

FIGURE Highly Flammable and HazardousMaterials and Components


FIGURE Crew Rest Compartments

Location


FIGURE Wheel/Brake Overheat - WheelSafety Area


FIGURE Composite Materials Location N ILLUSTRATION ADDED

FIGURE Ground Lock Safety Devices N ILLUSTRATION ADDED

FIGURE Emergency Evacuation Devices N ILLUSTRATION ADDED

FIGURE Pax/Crew Doors and EmergencyExits


FIGURE FWD and AFT Lower Deck

Cargo Doors


FIGURE Control Panels N ILLUSTRATION ADDED

FIGURE APU Compartment Access N ILLUSTRATION ADDED

FIGURE Ground Clearances N ILLUSTRATION ADDED

FIGURE Structural Break-in Points N ILLUSTRATION ADDED

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LIST OF EFFECTIVE CONTENT

Revision No. 20 - Apr 01/13

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 1

Subject 1-1-0

Purpose R Apr 01/13

Subject 1-2-1

Glossary N Apr 01/13

CHAPTER 2

Subject 2-1-1General Aircraft Characteristics Data R Apr 01/13

Subject 2-2-0

General Aircraft Dimensions R Apr 01/13

FIGURE General Aircraft Dimensions R Apr 01/13

FIGURE General Aircraft Dimensions R Apr 01/13

Subject 2-3-0

Ground Clearances R Apr 01/13

FIGURE Ground Clearances R Apr 01/13

FIGURE Ground Clearances N Apr 01/13

FIGURE Ground Clearances - Ailerons Up R Apr 01/13

FIGURE Ground Clearances - Ailerons Down R Apr 01/13

FIGURE Ground Clearances - Spoilers Extended R Apr 01/13

FIGURE Ground Clearances - Slats Fully Extended N Apr 01/13

FIGURE Ground Clearances - Flaps Fully Extended N Apr 01/13

FIGURE Ground Clearances - Flaps-Tracks Fully Extended N Apr 01/13

Subject 2-4-1

Interior Arrangements - Plan View R Apr 01/13

FIGURE Interior Arrangements - Plan View - Typical Configuration R Apr 01/13


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CONTENT CHGCODE

LAST REVISIONDATE


Subject 2-5-0Interior Arrangements - Cross Section R Apr 01/13

FIGURE Interior Arrangements - Cross Section - TypicalConfiguration

R Apr 01/13

Subject 2-6-1

Lower Deck Cargo Compartments R Apr 01/13

FIGURE Lower Deck Cargo Compartments - Location and Dimensions R Apr 01/13

FIGURE Lower Deck Cargo Compartments - Loading Combinations R Apr 01/13

FIGURE Lower Deck Cargo Compartments - Loading Combinations N Apr 01/13Subject 2-7-0

Door Clearances N Apr 01/13

FIGURE Door Identification and Location - Door Identification N Apr 01/13

FIGURE Door Identification and Location - Door Identification N Apr 01/13

Subject 2-7-1

Forward Passenger / Crew Door May 01/07

FIGURE Forward Passenger / Crew Doors May 01/07

Subject 2-7-2Mid Passenger / Crew Door May 01/07

FIGURE Mid Passenger / Crew Door May 01/07

Subject 2-7-3

Emergency Exits May 01/07

FIGURE Emergency Exits May 01/07

Subject 2-7-4

Aft Passenger / Crew Doors May 01/07

FIGURE Aft Passenger / Crew Doors May 01/07

Subject 2-7-5

Forward Cargo Compartment Doors May 01/07

FIGURE Forward Cargo Compartment Doors May 01/07

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CONTENT CHGCODE

LAST REVISIONDATE

Subject 2-7-6

Aft Cargo Compartment Doors May 01/07FIGURE Aft Cargo Compartment Doors May 01/07

Subject 2-7-7

Bulk Cargo Compartment Doors May 01/07

FIGURE Bulk Cargo Compartment Doors May 01/07

Subject 2-7-8

Main Landing Gear Doors May 01/07

FIGURE Main and Center Landing Gear Doors May 01/07

Subject 2-7-9Radome May 01/07

FIGURE Radome May 01/07

Subject 2-7-10

APU and Nose Landing Gear Doors May 01/07

FIGURE APU and Nose Landing Gear Doors May 01/07

FIGURE APU and Nose Landing Gear Doors May 01/07

Subject 2-8-0

Escape Slides N Apr 01/13

FIGURE Escape Slides - Location N Apr 01/13

FIGURE Escape Slides - Location N Apr 01/13

Subject 2-9-0

Landing Gear Maintenance Pits N Apr 01/13

FIGURE Landing Gear Maintenance Pits - Maintenance Pit Envelopes N Apr 01/13

FIGURE Landing Gear Maintenance Pits - Maintenance Pit Envelopes N Apr 01/13

Landing Gear N Apr 01/13

FIGURE Main Landing Gear - General N Apr 01/13

FIGURE Centerline Landing Gear - General N Apr 01/13

FIGURE Nose Landing Gear - General N Apr 01/13

Subject 2-10-0

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CONTENT CHGCODE

LAST REVISIONDATE

Exterior Lighting N Apr 01/13

FIGURE Exterior Lighting N Apr 01/13FIGURE Exterior Lighting N Apr 01/13

Subject 2-11-0

Antennas and Probes Location N Apr 01/13

FIGURE Antennas and Probes - Location N Apr 01/13

FIGURE Antennas and Probes - Location N Apr 01/13

Subject 2-12-0

Engine and Nacelle N Apr 01/13

FIGURE Engine and Nacelle - Engine Dimensions - CFM 56-5C N Apr 01/13

FIGURE Engine and Nacelle - Nacelle Dimensions - CFM 56-5C N Apr 01/13

FIGURE Engine and Nacelle - Fan Cowls - CFM 56-5C N Apr 01/13

FIGURE Engine and Nacelle - Thrust Reverser Cowls - CFM 56-5C N Apr 01/13

Subject 2-12-1

Auxiliary Power Unit N Apr 01/13

FIGURE Auxiliary Power Unit - Access Doors N Apr 01/13

Subject 2-13-0

Leveling, Symmetry and Alignment N Apr 01/13

FIGURE Location of Leveling Points N Apr 01/13

FIGURE Location of Leveling Points N Apr 01/13

Subject 2-14-0

Jacking for Maintenance N Apr 01/13

FIGURE Jacking for Maintenance - Jacking Points Location N Apr 01/13

FIGURE Jacking for Maintenance - Jacking Points Location N Apr 01/13

FIGURE Jacking for Maintenance - Forward Jacking Point N Apr 01/13

FIGURE Jacking for Maintenance - Wing Jacking Points N Apr 01/13

FIGURE Jacking for Maintenance - Auxiliary Jacking Point - SafetyStay

N Apr 01/13

FIGURE Jacking for Maintenance - Jacking Dimensions N Apr 01/13

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CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Jacking for Maintenance - Jacking Dimensions N Apr 01/13

FIGURE Jacking for Maintenance - Load at the Aircraft JackingPoints N Apr 01/13

FIGURE Jacking for Maintenance - Load at the Aircraft JackingPoints

N Apr 01/13

Subject 2-14-1

Jacking for Wheel Change N Apr 01/13

FIGURE Jacking for Wheel Change - MLG Jacking Point Heights N Apr 01/13

FIGURE Jacking for Wheel Change - Jacking of the NLG N Apr 01/13

FIGURE Jacking for Wheel Change - Jacking of the CLG N Apr 01/13

FIGURE Jacking for Wheel Change - MLG Jacking Point Loads N Apr 01/13

FIGURE Jacking for Wheel Change - MLG Jacking Point Loads N Apr 01/13

FIGURE Jacking for Wheel Change - NLG Jacking Point Loads N Apr 01/13

FIGURE Jacking for Wheel Change - NLG Jacking Point Loads N Apr 01/13

FIGURE Jacking for Wheel Change - CLG Jacking Point Loads N Apr 01/13

FIGURE Jacking for Wheel Change - CLG Jacking Point Loads N Apr 01/13

Subject 2-14-2

Support of Aircraft N Apr 01/13

FIGURE Support of Aircraft - Location of Shoring Cradles N Apr 01/13

FIGURE Support of Aircraft - Location of Shoring Cradles N Apr 01/13

CHAPTER 3

Subject 3-1-0

General Information May 01/07

Subject 3-2-0

Payload / Range May 01/07

Subject 3-2-1ISA Conditions May 01/07

FIGURE PAYLOAD / RANGE - CFM56-5C2 engine May 01/07


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CONTENT CHGCODE

LAST REVISIONDATE


FIGURE PAYLOAD / RANGE - CFM56-5C3 engine May 01/07FIGURE PAYLOAD / RANGE - CFM56-5C4 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 --CFM56-5C2 engine

May 01/07


May 01/07


May 01/07


May 01/07

FIGURE FAR / JAR Takeoff Weight Limitation - ISA Conditions --

CFM56-5C4 engine

May 01/07


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 -- CFM56-5C2 engine

May 01/07


May 01/07


May 01/07


May 01/07

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CONTENT CHGCODE

LAST REVISIONDATE


May 01/07


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 --CFM56-5C2 engine

May 01/07


May 01/07


May 01/07


May 01/07


May 01/07

FIGURE FAR / JAR Landing Field Length - ISA Conditions --

CFM56-5C4 engine

May 01/07

Subject 3-5-0

Final Approach Speed N Apr 01/13

CHAPTER 4

Subject 4-1-0

General Information May 01/07

Subject 4-2-0

Turning Radii Jan 01/11

FIGURE Turning Radii - (Sheet 1) R Apr 01/13



Subject 4-3-0

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LAST REVISIONDATE

Minimum Turning Radii May 01/07

FIGURE Minimum Turning Radii R Apr 01/13FIGURE Minimum Turning Radii R Apr 01/13

Subject 4-4-0

Visibility from Cockpit in Static Position R Apr 01/13

FIGURE Visibility from Cockpit in Static Position R Apr 01/13

FIGURE Binocular Visibility Through Windows from Captain EyePosition

N Apr 01/13

Subject 4-5-0

Runway and Taxiway Turn Paths May 01/07

Subject 4-5-1

135˚ Turn - Runway to Taxiway Jan 01/11

FIGURE 135˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

Jan 01/11

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

Jan 01/11

FIGURE 135˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

Jan 01/11


Jan 01/11

Subject 4-5-2

90˚ Turn - Runway to Taxiway Jan 01/11

FIGURE 90˚ Turn - Runway to Taxiway - Judgement OversteeringMethod

Jan 01/11


Jan 01/11

FIGURE 90˚ Turn - Runway to Taxiway - Judgement OversteeringMethod

Jan 01/11


Jan 01/11

Subject 4-5-3

180˚ Turn on a Runway May 01/07

FIGURE 180˚ Turn on a Runway R Apr 01/13

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FIGURE 180˚ Turn on a Runway R Apr 01/13

FIGURE 180˚ Turn on a Runway R Apr 01/13FIGURE 180˚ Turn on a Runway R Apr 01/13

Subject 4-5-4

135˚ Turn - Taxiway to Taxiway Jan 01/11

FIGURE 135˚ Turn - Taxiway to Taxiway - JudgementalOversteering Method

Jan 01/11

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

Jan 01/11

FIGURE 135˚ Turn - Taxiway to Taxiway - Judgemental

Oversteering Method

Jan 01/11


Jan 01/11

Subject 4-5-5

90˚ Turn - Taxiway to Taxiway Jan 01/11

FIGURE 90˚ Turn - Taxiway to Taxiway - Judgement OversteeringMethod

Jan 01/11


Jan 01/11

FIGURE 90˚ Turn - Taxiway to Taxiway - Judgement OversteeringMethod

Jan 01/11


Jan 01/11

Subject 4-6-0

Runway Holding Bay (Apron) May 01/07

FIGURE Runway Holding Bay (Apron) 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


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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 R Apr 01/13

Subject 5-1-2

Typical Ramp Layout - Open Apron R Apr 01/13

FIGURE Typical Ramp Layout - Open Apron R Apr 01/13

FIGURE Typical Ramp Layout - Open Apron R Apr 01/13

Subject 5-1-3

Typical Ramp Layout - Gate R Apr 01/13

FIGURE Typical Ramp Layout - Gate R Apr 01/13

FIGURE Typical Ramp Layout - Gate R Apr 01/13

Subject 5-2-0

Terminal Operations - Full Servicing Turn Round Time N Apr 01/13

FIGURE Full Servicing Turn Round Time Chart N Apr 01/13

Terminal Operations - Full Servicing Turn Round Time N Apr 01/13

FIGURE Full Servicing Turn Round Time Chart N Apr 01/13

Subject 5-3-0

Terminal Operations - Minimum Servicing Turn-Round Time N Apr 01/13

FIGURE Minimum Servicing Turn-Round Time N Apr 01/13Terminal Operations - Minimum Servicing Turn-Round Time N Apr 01/13

FIGURE Minimum Servicing Turn-Round Time N Apr 01/13

Subject 5-4-1

Ground Service Connections Layout R Apr 01/13

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FIGURE Ground Service Connections Layout R Apr 01/13

Subject 5-4-2Grounding Points May 01/07

FIGURE Ground Service Connections - Grounding Points May 01/07

FIGURE Ground Service Connections - Grounding Points May 01/07

Subject 5-4-3

Hydraulic System R Apr 01/13

FIGURE Ground Service Connections - Green System Ground ServicePanel

N Apr 01/13

FIGURE Ground Service Connections - Blue System Ground ServicePanel

N Apr 01/13

FIGURE Ground Service Connections - Yellow System Ground ServicePanel

N Apr 01/13

Subject 5-4-4

Electrical System R Apr 01/13

FIGURE Ground Service Connections - Electrical Service Panel N Apr 01/13

Subject 5-4-5

Oxygen System R Apr 01/13

FIGURE Ground Service Connections - Oxygen System N Apr 01/13Subject 5-4-6

Fuel System R Apr 01/13

FIGURE Overpressure Protector and NACA Flame Arrestor Jan 01/12

Subject 5-4-7

Pneumatic System R Apr 01/13

FIGURE Ground Service Connections - LP and HP GroundConnectors

N Apr 01/13

Subject 5-4-8Potable Water System N Apr 01/13

FIGURE Ground Service Connections - Potable-Water Ground ServicePanels

N Apr 01/13

Potable Water System N Apr 01/13

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FIGURE Ground Service Connections - Potable-Water Ground ServicePanels

N Apr 01/13

Subject 5-4-9

Oil System May 01/07

FIGURE Ground Service Connections - Engine Oil Tank - CFM56-5C2series engine

May 01/07

FIGURE Ground Service Connections - IDG Oil Tank - CFM56-5C2series engine

May 01/07

APU Oil System R Apr 01/13

FIGURE Ground Service Connections - APU Oil Servicing R Apr 01/13

Subject 5-4-10Vacuum Toilet System R Apr 01/13

FIGURE Ground Service Connections - Waste Water Ground ServicePanel

N Apr 01/13

Subject 5-5-0

Engine Starting Pneumatic Requirements R Apr 01/13

FIGURE Example for Use of the Charts R Apr 01/13

FIGURE Engine Starting Pneumatic Requirements - CFM56-5C2Series

N Apr 01/13

Subject 5-6-0

Ground Pneumatic Power Requirements N Apr 01/13

FIGURE Ground Pneumatic Power Requirements - Heating N Apr 01/13

FIGURE Ground Pneumatic Power Requirements - Cooling N Apr 01/13

Subject 5-7-0

Preconditioned Airflow Requirements R Apr 01/13

FIGURE Preconditioned Airflow Requirements R Apr 01/13

Subject 5-8-0Ground Towing Requirements R Apr 01/13

FIGURE Ground Towing Requirements Jan 01/10

Subject 5-9-0

De-Icing and External Cleaning N Apr 01/13

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CHAPTER 6

Subject 6-1-0Engine 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 - CFM56-5Cseries engine

May 01/07

Subject 6-1-2

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

FIGURE Engine Exhaust Temperatures - Ground Idle Power -CFM56-5C series engine

May 01/07

Subject 6-1-3

Engine Exhaust Velocities Contours - Breakaway Power May 01/07

FIGURE Engine Exhaust Velocities - Breakaway Power - CFM56-5Cseries engine

May 01/07

Subject 6-1-4

Engine Exhaust Temperatures Contours - Breakaway Power May 01/07

FIGURE Engine Exhaust Temperatures - Breakaway Power -CFM56-5C series engine

May 01/07

Subject 6-1-5

Engine Exhaust Velocities Contours - Takeoff Power May 01/07

FIGURE Engine Exhaust Velocities - Takeoff Power - CFM56-5Cseries engine

May 01/07

Subject 6-1-6

Engine Exhaust Temperatures Contours - Takeoff Power May 01/07

FIGURE Engine Exhaust Temperatures - Takeoff Power - CFM56-5C

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

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FIGURE Airport and Community Noise - CFM56-5C series engine May 01/07

Subject 6-3-0Danger Areas of Engines May 01/07

Subject 6-3-1

Ground Idle Power May 01/07

FIGURE Danger Areas of Engines - CFM56-5C series engine May 01/07

Subject 6-3-2

Breakaway Power May 01/07


Subject 6-3-3Takeoff 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 GTCP

331-350

May 01/07

CHAPTER 7

Subject 7-1-0

General Information N Apr 01/13

Subject 7-2-0

Landing Gear Footprint R Apr 01/13

FIGURE Landing Gear Footprint R Apr 01/13

FIGURE Landing Gear Footprint R Apr 01/13

Subject 7-3-0

Maximum Pavement Loads R Apr 01/13

FIGURE Maximum Pavement Loads R Apr 01/13

FIGURE Maximum Pavement Loads R Apr 01/13

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Subject 7-4-0

Landing Gear Loading on Pavement R Apr 01/13FIGURE Landing Gear Loading on Pavement - WV000, MRW 254400 kg

N Apr 01/13

FIGURE Landing Gear Loading on Pavement - WV021, MRW 275900 kg

N Apr 01/13


N Apr 01/13


N Apr 01/13

Subject 7-5-0Flexible Pavement Requirements - US Army Corps of EngineersDesign Method S-77-1

R Apr 01/13

FIGURE Flexible Pavement Requirements - WV000, MRW 254 400kg, CG 37.7 %

N Apr 01/13

FIGURE Flexible Pavement Requirements - WV000, MRW 254 400kg, CG 38.18 %

N Apr 01/13

Subject 7-6-0

Flexible Pavement Requirements - LCN Conversion R Apr 01/13

FIGURE Flexible Pavement Requirements - LCN table N Apr 01/13

FIGURE Flexible Pavement Requirements - LCN - WV000, MRW 254400 kg, CG 37.7 %

N Apr 01/13

FIGURE Flexible Pavement Requirements - LCN table N Apr 01/13

FIGURE Flexible Pavement Requirements - LCN - WV000, MRW 254400 kg, CG 38.18 %

N Apr 01/13

Subject 7-7-0

Rigid Pavement Requirements - Portland Cement Association DesignMethod

R Apr 01/13

FIGURE Rigid Pavement Requirements - WV000, MRW 254 400 kg,CG 37.7 %

N Apr 01/13

FIGURE Rigid Pavement Requirements - WV000, MRW 254 400 kg,CG 38.18 %

N Apr 01/13

Subject 7-8-0

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Rigid Pavement Requirements - LCN Conversion R Apr 01/13

FIGURE Rigid Pavement Requirements - LCN table N Apr 01/13FIGURE Rigid Pavement Requirements - LCN table N Apr 01/13

FIGURE Radius of Relative Stiffness (L) N Apr 01/13

FIGURE Rigid Pavement Requirements - LCN - WV000, MRW 254400 kg, CG 37.7 %

N Apr 01/13

FIGURE Rigid Pavement Requirements - LCN - WV021, MRW 275900 kg, CG 37 %

N Apr 01/13

FIGURE Rigid Pavement Requirements - LCN - WV000, MRW 254400 kg, CG 38.18 %

N Apr 01/13

FIGURE Rigid Pavement Requirements - LCN - WV028, MRW 277400 kg, CG 35 %

N Apr 01/13

FIGURE Radius of Relative Stiffness (Effect E and µ ON ”L” values) N Apr 01/13

Subject 7-9-0

Aircraft Classification Number - Flexible and Rigid Pavements R Apr 01/13

FIGURE Aircraft Classification Number - ACN Table N Apr 01/13

FIGURE Aircraft Classification Number - Flexible Pavement - WV000,MRW 254 400 kg, CG 37.7 %

N Apr 01/13

FIGURE Aircraft Classification Number - Flexible Pavement - WV021,MRW 275 900 kg, CG 37 %

N Apr 01/13

FIGURE Aircraft Classification Number - ACN Table N Apr 01/13

FIGURE Aircraft Classification Number - Flexible Pavement - WV000,MRW 254 400 kg, CG 38.18 %

N Apr 01/13

FIGURE Aircraft Classification Number - Flexible Pavement - WV028,MRW 277 400 kg, CG 35 %

N Apr 01/13

CHAPTER 8

Subject 8-0-0

Scaled Drawings N Apr 01/13

FIGURE Scaled Drawing N Apr 01/13

FIGURE Scaled Drawing N Apr 01/13

CHAPTER 10

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Subject 10-0-0

Aircraft Rescue and Fire Fighting N Apr 01/13FIGURE Front Page N Apr 01/13

FIGURE Highly Flammable and Hazardous Materials and Components N Apr 01/13

FIGURE Crew Rest Compartments Location N Apr 01/13

FIGURE Wheel/Brake Overheat - Wheel Safety Area N Apr 01/13

FIGURE Composite Materials Location N Apr 01/13

FIGURE Ground Lock Safety Devices N Apr 01/13

FIGURE Emergency Evacuation Devices N Apr 01/13

FIGURE Pax/Crew Doors and Emergency Exits N Apr 01/13

FIGURE FWD and AFT Lower Deck Cargo Doors N Apr 01/13

FIGURE Control Panels N Apr 01/13

FIGURE APU Compartment Access N Apr 01/13

FIGURE Ground Clearances N Apr 01/13

FIGURE Structural Break-in Points N Apr 01/13

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TABLE OF CONTENTS

1 SCOPE

1-1-0 Purpose

1-2-1 Glossary

2 AIRCRAFT DESCRIPTION

2-1-1 General Aircraft Characteristics Data

2-2-0 General Aircraft Dimensions

2-3-0 Ground Clearances

2-4-1 Interior Arrangements - Plan View

2-5-0 Interior Arrangements - Cross Section

2-6-1 Lower Deck Cargo Compartments2-7-0 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 Doors2-7-9 Radome

2-7-10 APU and Nose Landing Gear Doors

2-8-0 Escape Slides

2-9-0 Landing Gear

2-10-0 Exterior Lighting

2-11-0 Antennas and Probes Location

2-12-0 Engine and Nacelle

2-12-1 Auxiliary Power Unit

2-13-0 Levelling, symmetry and Alignment

2-14-0 Jacking for Maintenance

2-14-1 Jacking for Wheel Change

2-14-2 Support of Aircraft

3 AIRCRAFT PERFORMANCE

3-1-0 General Information

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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

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 Position4-5-0 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 Aircraft Parking

5 TERMINAL SERVICING

5-0-0 TERMINAL SERVICING

5-1-0 Aircraft Servicing Arrangements

5-1-1 Symbols Used on Servicing Diagrams

5-1-2 Typical Ramp Layout - Open Apron

5-1-3 Typical Ramp Layout - Gate

5-2-0 Terminal Operations - Full Servicing

5-3-0 Terminal Operations - Transit

5-4-1 Ground Service Connections Layout

5-4-2 Grounding Points5-4-3 Hydraulic System

5-4-4 Electrical System

5-4-5 Oxygen System

5-4-6 Fuel System

5-4-7 Pneumatic System

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5-4-8 Potable Water System

5-4-9 Oil System

5-4-10 Vacuum Toilet System

5-5-0 Engine Starting Pneumatic Requirements

5-6-0 Ground Pneumatic Power Requirements

5-7-0 Preconditioned Airflow Requirements

5-8-0 Ground Towing Requirements

5-9-0 De-Icing and External Cleaning

6 OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

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

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

6-1-3 Engine Exhaust Velocities Contours - Breakaway Power6-1-4 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

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

7-6-0 Flexible Pavement Requirements - LCN Conversion7-7-0 Rigid Pavement Requirements - Portland Cement Association Design Method

7-8-0 Rigid Pavement Requirements - LCN Conversion

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

8 SCALED DRAWINGS

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8-0-0 SCALED DRAWINGS

10 AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 AIRCRAFT RESCUE AND FIRE FIGHTING

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SCOPE

1-1-0 Purpose

**ON A/C A340-200 A340-300Purpose

1. GeneralThe A340-200/-300 AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCEPLANNING (AC) manual is issued for the A340-200 and A340-300 basic versions to providenecessary data to airport operators, airlines and Maintenance/Repair Organizations (MRO) for airporand maintenance facilities planning.

This revision is now a merging of the Maintenance Facility Planning (MFP) document and theAirplane Characteristics for Airport Planning (AC). This document has been renamed Aircraft

Characteristics - Airport and Maintenance Planning (AC) to reflect this change.Additionally, a chapter 10 ”Aircraft Rescue and Fire Fighting” has been added to the AC. Thischapter contains the illustrations of the Aircraft Rescue and Fire fighting Charts poster and replacesthe PDF document that was available for download.

This document is not customized and must not be used for training purposes.

The A340 is part of an integrated family sharing the same modern technology as the A330 andmaintaining the commonality that is integrated into the Airbus Fly-by-Wire Family. It has undergonea program of continuous improvement and still delivers the value that airline customers expect, as theA340 has over 50 customers and operators with more than 350 A340s flying to over 150 airports

every week.

The different models of the A340 Family can carry from 250 to 440 passengers and are operating onsome of the world’s longest routes.

A stand-out benefit of the four-engine A340 is that it does not require any ETOPS certification. Thisallows quick start-up of long-haul operations. It also has good ’hot and high’ capability at airportsthat would be off-limits to other aircraft.

The A340 has one of the quietest and most comfortable cabins in the sky, with state-of-the-art LED(Light Emitting Diode) lighting, mood styles of lighting and AVOD IFE systems.

The A340 combines good capability, economics and passenger product in one package.

Correspondence concerning this publication should be directed to:

AIRBUS S.A.S.

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Customer ServicesTechnical Data Support and Services1, Rond Point Maurice BELLONTE31707 BLAGNAC CEDEX

FRANCE

1-1-0

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1-2-1 Glossary

**ON A/C A340-200 A340-300

Glossary

1. List of Abbreviations

A/C Aircraft

ACN Aircraft Classification NumberAMM Aircraft Maintenance ManualAPU Auxiliary Power Unit

B/C Business Class

C/L Center Line

CBR California Bearing Ratio

CC Cargo Compartment

CG Center of GravityCKPT Cockpit

CLG Centerline Landing Gear

E Young’s Modulus

ELEC Electric, Electrical, Electricity

ESWL Equivalent Single Wheel Load

F/C First Class

FAA Federal Aviation AdministrationFDL Fuselage Datum Line

FR FrameFSTE Full Size Trolley Equivalent

FWD ForwardGPU Ground Power UnitGSE Ground Support Equipment

HYD Hydraulic

ICAO International Civil Aviation Organisation

IDG Integrated Drive Generator

ISA International Standard Atmosphere

L Radius of relative stiffnessLCN Load Classification NumberLD Load DeviceLD Lower DeckL/G Landing Gear

LH Left HandLPS Last Pax Seating

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MAC Mean Aerodynamic Chord

MAX MaximumMD Main DeckMIN Minimum

MLG Main Landing GearMLW Maximum Design Landing Weight

MRW Maximum Design Ramp Weight

MTOW Maximum Design Take-Off Weight

MTW Maximum Design Taxi Weight

MZFW Maximum Design Zero Fuel Weight

NLG Nose Landing Gear

OAT Outside Air Temperature

PAX Passenger

PB/D Passenger Boarding/DeboardingPBB Passenger Boarding Bridge

PCA Portland Cement AssociationPCN Pavement Classification NumberPRM Passenger with Reduced Mobility

RH Right Hand

ULD Unit Load DeviceUS United StatesWV Weight Variant

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

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

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

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

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

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

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

- Water Volume:

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Maximum volume of cargo compartment.- Usable Fuel:

Fuel available for aircraft propulsion.

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2-1-1 General Aircraft Characteristics Data

**ON A/C A340-200 A340-300

General Aircraft Characteristics Data

**ON A/C A340-300

1. The following table provides characteristics of A340-300 Models, these data are specific to eachWeight Variant:

Aircraft CharacteristicsWV000 WV001 WV002 WV003 WV004

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

254 400 kg(560 856 lb)

257 900 kg(568 572 lb)

260 900 kg(575 186 lb)

257 900 kg(568 572 lb)

260 900 kg(575 186 lb)

Maximum Take-Off Weight(MTOW)

253 500 kg(558 872 lb)

257 000 kg(566 588 lb)

260 000 kg(573 202 lb)

257 000 kg(566 588 lb)

260 000 kg(573 202 lb)

Maximum Landing Weight(MLW)

186 000 kg(410 060 lb)

186 000 kg(410 060 lb)

186 000 kg(410 060 lb)

188 000 kg(414 469 lb)

188 000 kg(414 469 lb)

Maximum Zero Fuel Weight(MZFW)

174 000 kg(383 604 lb)

174 000 kg(383 604 lb)

174 000 kg(383 604 lb)

178 000 kg(392 423 lb)

178 000 kg(392 423 lb)



271 900 kg(599 437 lb)

275 900 kg(608 255 lb)

262 900 kg(579 595 lb)

275 900 kg(608 255 lb)

260 900 kg(575 186 lb)


271 000 kg(597 453 lb)

275 000 kg(606 271 lb)

262 000 kg(577 611 lb)

275 000 kg(606 271 lb)

260 000 kg(573 202 lb)


190 000 kg(418 878 lb)

190 000 kg(418 878 lb)

190 000 kg(418 878 lb)

192 000 kg(423 287 lb)

190 000 kg(418 878 lb)


178 000 kg(392 423 lb)

178 000 kg(392 423 lb)

178 000 kg(392 423 lb)

180 000 kg(396 832 lb)

178 000 kg(392 423 lb)

Aircraft CharacteristicsWV026 WV027 WV028 WV029


275 900 kg(608 255 lb)

271 900 kg(599 437 lb)

277 400 kg(611 562 lb)

260 900 kg(575 186 lb)

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275 000 kg(606 271 lb)

271 000 kg(597 453 lb)

276 500 kg(609 578 lb)

260 000 kg(573 202 lb)


192 000 kg(423 287 lb)

192 000 kg(423 287 lb)

190 000 kg(418 878 lb)

188 000 kg(414 469 lb)


181 000 kg(399 037 lb)

178 000 kg(392 423 lb)

178 000 kg(392 423 lb)

178 000 kg(392 423 lb)



275 900 kg(608 255 lb)

275 900 kg(608 255 lb)

277 400 kg(611 562 lb)

277 400 kg(611 562 lb)

275 900 kg(608 255 lb)


275 000 kg(606 271 lb)

275 000 kg(606 271 lb)

276 500 kg(609 578 lb)

276 500 kg(609 578 lb)

275 000 kg(606 271 lb)


192 000 kg(423 287 lb)

192 000 kg(423 287 lb)

192 000 kg(423 287 lb)

192 000 kg(423 287 lb)

192 000 kg(423 287 lb)


180 000 kg(396 832 lb)

181 000 kg(399 037 lb)

181 000 kg(399 037 lb)

183 000 kg(403 446 lb)

183 000 kg(403 446 lb)

2. The following table provides characteristics of A340-300 Models, these data are common to each

Weight Variant:Aircraft Characteristics

Standard Seating Capacity 335

140 640 l(37 153 US gal)Usable Fuel Capacity

(density = 0.785 kg/l) 110 402 kg(243 395 lb)

Pressurized Fuselage Volume(A/C non equipped)

1 056 m3

(37 292 ft3)

Passenger CompartmentVolume

372 m3

(13 137 ft3)

Cockpit Volume12 m3

(424 ft3)

Usable Volume, FWD CC(Based on LD3)

78 m3

(2 754 ft3)

2-1-1

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



Aircraft CharacteristicsUsable Volume, AFT CC(Based on LD3)

60.7 m3

(2 142 ft3)

Usable Volume, Bulk CC19.7 m3

(695 ft3)

Water Volume, FWD CC107 m3

(3 789 ft3)

Water Volume, AFT CC85.7 m3

(3 026 ft3)

Water Volume, Bulk CC22.7 m3

(802 ft3)

**ON A/C A340-200

3. The following table provides characteristics of A340-200 Models, these data are specific to eachWeight Variant:



254 400 kg(560 856 lb)

257 900 kg(568 572 lb)

260 900 kg(575 186 lb)

275 900 kg(608 255 lb)

Maximum Take-Off Weight

(MTOW)

253 500 kg

(558 872 lb)

257 000 kg

(566 588 lb)

260 000 kg

(573 202 lb)

275 000 kg

(606 271 lb)Maximum Landing Weight(MLW)

181 000 kg(399 037 lb)

181 000 kg(399 037 lb)

181 000 kg(399 037 lb)

185 000 kg(407 855 lb)


169 000 kg(372 581 lb)

169 000 kg(372 581 lb)

169 000 kg(372 581 lb)

173 000 kg(381 400 lb)

4. The following table provides characteristics of A340-200 Models, these data are common to eachWeight Variant:

Aircraft CharacteristicsStandard Seating Capacity 303

140 640 l(37 153 US gal)Usable Fuel Capacity

(density = 0.785 kg/l) 110 402 kg(243 395 lb)

Pressurized Fuselage Volume(A/C non equipped)

946 m3

(33 408 ft3)

2-1-1

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



Aircraft Characteristics

Passenger CompartmentVolume

345 m3

(12 184 ft3)

Cockpit Volume12 m3

(424 ft3)

Usable Volume, FWD CC(Based on LD3)

60.7 m3

(2 142 ft3)

Usable Volume, AFT CC(Based on LD3)

52 m3

(1 836 ft3)

Usable Volume, Bulk CC19.7 m3

(695 ft3)

Water Volume, FWD CC84.6 m3

(2 988 ft3)

Water Volume, AFT CC 71.1 m3

(2 511 ft3)

Water Volume, Bulk CC22.7 m3

(802 ft3)

2-1-1

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-2-0 General Aircraft Dimensions

**ON A/C A340-200 A340-300

General Aircraft Dimensions

1. This section provides General Aircraft Dimensions.

2-2-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

(126.44 ft)

38.54 m

(3.18 ft)

0.97 m

(35.04 ft)

10.68 m

(41.37 ft)

12.61 m

(61.48 ft)

18.74 m

(2.33 ft)

0.71 m

(197.83 ft)

60.3 m

(63.65 ft)

19.4 m

(26.71 ft)

8.14 m

(25.52 ft)7.78 m

(171.98 ft)

52.42 m

(206.17 ft)

62.84 m

(208.86 ft)

63.66 m

(21.88 ft)

6.67 m

(105.15 ft)

32.05 m − MLG

(108.4 ft)

33.04 m − CLG

(18.5 ft)

5.64 m

(27.23 ft)

8.3 m

(10.17 ft)3.1 m

NOTE:

RELATED TO AIRCRAFT ATTITUDE AND WEIGHT. F_AC_020200_1_0070101_01_02

General Aircraft Dimensions(Sheet 1 of 2)

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

2-2-0

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

(73.46 ft)22.39 m

(95.01 ft)28.96 m

(138.52 ft)42.22 m

(128.28 ft)39.1 m

(202.33 ft)61.67 m

(208.96 ft)63.69 m

(34.45 ft)10.5 m

(8.2 ft)2.5 m

(6.63 ft)2.02 m

(21.1 ft)6.43 m

(35.7 ft)10.88 m

7.46 m

( 4 6 . 6 2 f t )

1 4 . 2

1 m

( 5 7 . 9 1

f t )

1 7 . 6 5 m

(24.48 ft)

NOTE:RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.

F_AC_020200_1_0070102_01_00


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

2-2-0

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

(3.18 ft)

0.97 m

(35.04 ft)

10.68 m

(41.37 ft)

12.61 m

(61.48 ft)

18.74 m

(128.61 ft)

39.2 m

(2.33 ft)

0.71 m

(197.83 ft)

60.3 m

(63.65 ft)

19.4 m

(26.7 ft)

8.14 m

(25.59 ft)7.8 m

(157.97 ft)

48.15 m(192.16 ft)

58.57 m

(194.85 ft)

59.39 m

(21.88 ft)

6.67 m

(98.13 ft)

29.91 m − MLG

(101.41 ft)

30.91 m − CLG

(27.23 ft)8.3 m

NOTE:

RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.

(10.17 ft)3.1 m

(18.5 ft)

5.64 m

F_AC_020200_1_0080101_01_02


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

2-2-0

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

NOTE:RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.

(66.44 ft)20.25 m

(88.02 ft)26.83 m

(132.22 ft)40.3 m

(121.29 ft)36.97 m

(188.32 ft)57.4 m

(194.95 ft)59.42 m

(34.45 ft)10.5 m

(8.43 ft)2.57 m

(6.63 ft)2.02 m

(21.1 ft)6.43 m

(35.7 ft)10.88 m

7.46 m(24.48 ft)

( 5 7 . 9 1 f t )

1 7 . 6 5 m

( 4 6 . 6

2 f t )

1 4 . 2

1 m

F_AC_020200_1_0080102_01_00


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

2-2-0

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-3-0 Ground Clearances

**ON A/C A340-200 A340-300

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, W&B an others specialconditions.

The dimensions are given for:- A light weight for an A/C in maintenance configuration with a mid CG,- The MRW for the lightest weight variant with a FWD CG and a AFT CG,- The MRW for the heaviest weight variant with a FWD CG and a AFT CG,- Aircraft on jacks, FDL at 6.5 m (21.33 ft).

NOTE : Passenger and cargo door clearances are measured from the center of the door sill and fromfloor level.

2-3-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

X

L C 2 Y

K

E 3

H

E 2

D

C 1

B E 1

A

M

P

N

V

U

T

S

R

O

Q

Z

J

N O T E : P A S S E N G E R A N D C A R G O D O O R C L E A R A N C E S A R E M

E A S U R E D F R O M T H E C E N T E R

O F T H E D O O R S I L L A N D F R O M F L O O R L E V E L .

F_AC_020300_1_0050101_01_02

Ground Clearances(Sheet 1 of 2)

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

2-3-0

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

A

m

f t

m

m

B C 1 C 2 D P O N M L K J H E

3 E 2

E 1

6 6 . 9 5

6 . 5 9

f t

f t

Q R S T U V X Y

4 . 5 9

2 . 7 3

7 . 7 6

8 . 4 2

4 . 8 4

2 . 1 3

2 . 2 7

2 . 3 7

2 . 0 2

5 . 3 1

3 . 4 4

5 . 7 0

1 6 . 9 9

6 . 3 5

8 . 1 4

7 . 9 1

2 . 5 9

1 . 4 2

3 . 8 5

4 . 3 1

4 . 5 9

4 . 9 0

7 . 3 0

3 . 5 8

1 5 . 0 5

8 . 9 5

2 5 . 4 5

2 7 . 6 2

1 5 . 8 7

6 . 9 8

7 . 4 4

7 . 7 7

6 . 6 2

1 7 . 4 2

1 1 . 2 8

1 8 . 6 9

5 5 . 7 2

2 0 . 8 3

2 6 . 7 0

2 5 . 9 4

8 . 4 9

4 . 6 5

1 2 . 6 3

1 4 . 1 4

1 5 . 0 5

1 6 . 0 7

2 3 . 9 4

1 1 . 7 4

2 . 5 4

7 . 5 8

8 . 2 5

4 . 6 5

1 . 9 4

2 . 0 9

2 . 4 9

1 . 8 4

5 . 1 2

3 . 2 6

5 . 5 2

1 6 . 8 2

6 . 0 1

7 . 9 6

7 . 5 7

2 . 3 5

1 . 2 3

3 . 6 7

4 . 1 2

4 . 3 8

4 . 6 6

7 . 1 2

1 4 . 5 9

8 . 3 3

2 4 . 8 6

2 7 . 0 6

1 5 . 2 5

6 . 3 6

6 . 8 5

8 . 1 7

6 . 0 3

1 6 . 8 0

1 0 . 6 9

1 8 . 1 0

5 5 . 1 7

1 9 . 7 1

2 6 . 1 1

2 4 . 8 3

7 . 7 1

4 . 0 3

1 2 . 0 4

1 3 . 5 1

1 4 . 3 7

1 5 . 2 8

2 3 . 3 5

1 1 . 1 2

4 . 5 2

2 . 5 8

7 . 6 0

8 . 2 0

4 . 6 7

1 . 9 6

2 . 1 0

2 . 4 6

1 . 8 3

5 . 1 0

3 . 2 3

5 . 4 7

1 6 . 7 3

5 . 9 8

7 . 8 8

7 . 5 3

2 . 3 4

1 . 2 4

3 . 6 5

4 . 1 0

4 . 3 6

4 . 6 4

7 . 0 5

3 . 3 5

8 . 6 2

2 5 . 0 9

2 6 . 7 3

1 5 . 4 1

7 . 9 7

1 6 . 7 3

1 0 . 4 9

1 7 . 7 4

5 4 . 6 1

1 9 . 5 5

2 5 . 5 8

2 4 . 6 0

7 . 6 7

4 . 1 0

1 1 . 9 4

1 3 . 4 5

1 4 . 2 3

1 5 . 1 5

2 2 . 8 3

1 0 . 8 6

3 . 3 9

4 . 4 5

1 4 . 8

f t

m

m

f t

m 3 . 6 8

3 . 6 8

2 9 . 4

3 0 . 2

2 4 . 7

2 1 . 4

1 0 . 7

1 2

1 2

1 2

2 0 . 7

3 0 . 5

2 0 . 7

6 f t

8 . 9 6

9 . 2 3

7 . 5 5

6 . 5 3

4 . 2 4

3 . 2 6

3 . 6 8

9 . 3 2

9 . 3 2

4 . 1 4

1 3 . 5

3 0 . 5

1 3 . 9

2 . 3 5

4 . 1 2

4 . 6 6

1 3 . 5 1

1 5 . 2 8

5 . 1 0

4 . 1 0

1 6 . 7 3

1 3 . 4 5

6 . 3 2

6 . 3 2

6 . 3 2

1 7 . 6 2

3 . 9 8

2 . 7 9

5 . 2 5

5 . 7 0 6 6 . 3 0

8 . 1 0

4 . 3 9

1 3 9 . 1 1 7 . 2

1 8 . 7

1 9 . 6

2 0 . 6

2 6 . 5

1 4 . 4

2 0 . 7 3

5 7 . 8

1 5 . 0 9

8 . 8 8

2 5 . 1 2

2 6 . 8 3

6 . 4 9

6 . 9 8

7 . 8 3

1 0 . 4 3

1 7 . 5 8

5 4 . 6 8

1 9 . 4 8

2 5 . 6 8

2 4 . 5 4

7 . 7 0

4 . 2 0

1 1 . 9 4

1 4 . 2 0

1 5 . 1 2

2 2 . 8 9

1 0 . 8 9

1 7 . 7 4

4 . 6 0

2 . 7 1

7 . 6 6

8 . 1 8

1 . 9 8

2 . 1 3

2 . 3 9

1 . 8 3

3 . 1 8

5 . 3 6

1 6 . 6 7

5 . 9 4

7 . 8 3

7 . 4 8

2 . 3 5

1 . 2 8

3 . 6 4

4 . 3 3

4 . 6 1

6 . 9 8

3 . 3 2

5 . 4 1

1 4 . 5 9

8 . 4 6

2 4 . 7 3

2 7 . 2 3

6 . 0 3

6 . 7 5

8 . 0 3

5 . 9 7

1 6 . 8 6

1 0 . 7 3

1 8 . 0 1

5 5 . 3 6

1 9 . 6

2 6 . 3 7

2 4 . 7 6

7 . 7 0

4 . 1 0

1 2 . 0 1

1 4 . 3 3

2 3 . 5 8

1 1 . 1 5

1 7 . 1 5

4 . 4 5

2 . 5 8

7 . 5 4

8 . 3 0

1 . 8 4

2 . 0 6

2 . 4 5

1 . 8 2

5 . 1 4

3 . 2 7

5 . 4 9

1 6 . 8 8 6 8 . 0 4

7 . 5 5

1 . 2 5

3 . 6 6

4 . 3 7

7 . 1 9

3 . 4 3

5 . 2 3

1 5 . 7 1

4 . 7 9

1 5 . 5

4 . 7 2

7 . 1 0

2 3 . 3

Z

1 2 5 0 0 0 k g

C G 3 1 . 9 %

M R W

2 5 4 4 0 0 k g

C G 2 0 . 7 %

M R W

2 5 4 4 0 0 k g

C G 3 8 . 2 %

M R W 2 7 1

9 0 0 k g

C G 2 0

. 7 %

M R W

2 7 1 9 0 0 k g

C G 3 8 . 2 %

A I R C

R A F T

O N J A C K S

N O

T E : P A S S E N G E R A N D C A R G O D O O R C

L E A R A N C E S A R E M E A S U R E D F R O M T H E C E N T E R


F_AC_020300_1_0050102_01_00


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

2-3-0

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

X

L C

2 Y

K

E 3

H

E 2

D

C 1

B E 1

A

M

P

N

V

U

T

S

O

Q

J

N O T E : P A S S E N G E R A N D C A R G O D O O R C L E A R A N C E S A R E M E A S

U R E D F R O M T H E C E N T E R

O F T H E D O O R S I L L

A N D F R O M F L O O R L E V E L .

R

F_AC_020300_1_0050201_01_00


FIGURE-2-3-0-991-005-B01

2-3-0

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

A

m

f t

m

m

B C 1 C 2 D P O N M L K J H E

3 E 2

E 1

6 f t

f t

M R W

2 5 4 4

0 0 k g

C G 2 0 . 7

%

M R W

2 5 4 4 0 0 k g

C G 3 8 . 2 %

Q R S T U V X Y

2 . 7 3

2 . 0 2

5 . 7 0

8 . 9 5

6 . 6 2

1 8 . 6 9

2 . 3 5

3 . 6 7

4 . 1 2

4 . 3 8

8 . 3 3

6 . 0 3

1 2 . 0 4

1 3 . 5 1

1 4 . 3 7

1 1 . 1 2

2 . 1 0

1 . 8 3

5 . 9 8

7 . 8 8

7 . 5 3

2 . 3 4

1 . 2 4

3 . 6 5

4 . 1 0

8 . 6 2

1 7 . 7 4

7 . 6 7

1 3 . 4 5

1 0 . 8 6

4 . 5 8

7 . 7 8

8 . 4 3

4 . 8 6

2 . 1 4

2 . 2 6

2 . 6 6

5 . 3 2

3 . 4 5

1 7 . 0 3

6 . 3 7

8 . 1 8

7 . 9 5

2 . 6 0

1 . 4 1

3 . 8 6

4 . 3 3

4 . 6 0

4 . 9 3

7 . 3 3

3 . 5 8

1 5 . 0 2

2 5 . 5 2

2 7 . 6 5

1 5 . 9 4

7 . 0 2

7 . 4 1

8 . 7 2

1 7 . 4 5

1 1 . 3 1

5 5 . 8 6

2 0 . 8 9

2 6 . 8 3

2 6 . 0 8

8 . 5 3

4 . 6 2

1 2 . 6 6

1 4 . 2 0

1 5 . 0 9

1 6 . 1 7

2 4 . 0 4

1 1 . 7 4

4 . 4 0

2 . 5 4

7 . 5 6

8 . 2 4

4 . 6 7

1 . 9 3

2 . 0 7

2 . 4 7

1 . 8 4

5 . 1 3

3 . 2 5

5 . 5 1

1 6 . 8 4

6 . 0 3

7 . 9 9

7 . 5 9

1 . 2 2

4 . 6 8

7 . 1 4

3 . 3 9

1 4 . 4 3

2 4 . 8 0

2 7 . 0 2

1 5 . 3 1

6 . 3 3

6 . 7 8

8 . 1 0

1 6 . 8 3

1 0 . 6 6

1 8 . 0 7

5 5 . 2 3

1 9 . 7 8

2 6 . 2 1

2 4 . 8 9

7 . 7 0 4

1 5 . 3 5

2 3 . 4 2

4 . 5 0

2 . 6 3

7 . 6 3

8 . 1 6

4 . 7 1

1 . 9 9

2 . 4 2

5 . 0 9

3 . 1 9

5 . 4 1

1 6 . 6 8

4 . 3 5

4 . 6 3

6 . 9 8

3 . 3 1

1 4 . 7 6

2 5 . 0 3

2 6 . 7 6

1 5 . 4 5

6 . 5 3

6 . 8 9

7 . 9 4

1 6 . 7 0

1 0 . 4 6

5 4 . 7 1

1 9 . 6 1

2 5 . 8 5

2 4 . 7 0

4 . 0 6

1 1 . 9 7

1 4 . 2 7

1 5 . 1 9

2 2 . 8 9

f t

m

m

f t

m 3 . 6 8

3 . 6 8

2 9 . 4

3 0 . 2

2 4 . 7

2 1 . 4

1 0 . 7

1 2

1 2

1 2

2 0 . 7

3 0 . 5

2 0 . 7

f t

8 . 9 6

9 . 2 3

7 . 5 5

6 . 5 3

4 . 2 4

3 . 2 6

3 . 6 8

9 . 3 2

9 . 3 2

4 . 1 4

1 3 . 5

3 0 . 5

1 3 . 9

M R W

2 7 5

9 0 0 k g

C G 2 0 . 7 %

M R W

2 7 5 9 0 0 k g

C G 3 8 . 2 %

4 . 6 6

1 5 . 2 8

5 . 1 0

4 . 1 0

1 6 . 7 3

1 3 . 4 5

6 . 3 2

6 . 3 2

6 . 3 2

1 7 . 6 2

3 . 9 8

2 . 7 9

5 . 2 5

5 . 7 0 6 6 . 3 0

8 . 1 0

4 . 3 9

1 3 9 . 1 1 7 . 2

1 8 . 7

1 9 . 6

2 0 . 6

2 6 . 5

1 4 . 4

2 0 . 7 3

5 7 . 8

6 . 9 8

1 0 . 4 3

1 1 . 9 4

3 . 1 8

3 . 6 4

8 . 4 6

2 4 . 7 3

1 8 . 0 1

1 2 . 0 1

1 4 . 3 3

2 . 5 8

7 . 5 4

5 . 4 9

4 . 3 7

4 . 4 4

1 4 . 5 6

8 . 2 9

2 7 . 1 9

1 . 8 3

6

2 . 0 8

6 . 8 2

2 . 4 6

8 . 0 6

1 . 8 6

6 . 1 0

5 . 1 3

1 6 . 8 3

3 . 4 1

1 1 . 1 8

1 6 . 9 0

5 5 . 4 3

6 . 0 1

1 9 . 7 1

8 . 0 5

2 6 . 4 1

7 . 5 7

2 4 . 8 3

2 . 3 4

7 . 6 7

1 . 2 2

4

3 . 6 6

4 . 1 1

1 3 . 4 8

7 . 2 0

2 3 . 6 1

3 . 4 1

1 1 . 1 8

5 . 2 1

1 7 . 0 9

4 . 5 6

1 4 . 9 5

2 . 6 8

8 . 7 9

7 . 6 4

2 5 . 0 6

8 . 1 9

2 6 . 8 6

1 . 9 5

6 . 4 0

2 . 1 3

2 . 4 1

7 . 9 0

1 . 8 5

6 . 0 7

5 . 3 8

1 7 . 6 4

1 6 . 7 2

5 4 . 8 5

5 . 9 6

1 9 . 5 5

7 . 8 8

2 5 . 8 4

7 . 5 0

2 4 . 6 0

2 . 3 4

7 . 6 7

1 . 2 6

4 . 1 3

4 . 3 4

1 4 . 2 3

4 . 6 2

1 5 . 1 5

7 . 0 2

2 3 . 0 2

3 . 3 3

1 0 . 9 2

5 . 3 6

1 7 . 5 8

7 . 1 0

2 3 . 3

1 5 . 4 5

4 . 7 7

1 5 . 6 5

4 . 7 1

A I R C R A F T

O N J A

C K S

Z

N O

T E : P A S S E N G E R A N D C A R G O D O O R C

L E A R A N C E S A R E M E A S U R E D F R O M T H E C E N T E R


1 2 4 0 0 0 k g

C G 3 1 . 9 %

F_AC_020300_1_0050202_01_00


FIGURE-2-3-0-991-005-B01

2-3-0

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

m ft m ft m ft

A

B

C

D

MAXIMUM RAMPWEIGHT CG 23.1%


6.70

6.46

6.46

6.28

21.97

21.20

21.20

6.36

6.15

6.15

5.99

20.86

20.18

20.18

19.65

6.30

6.10

6.10

5.95

20.68

20.03

20.02

19.5220.61

A B C D

A/C IN MAINTENANCECONFIGURATION

MID CG 31.9%

F_AC_020300_1_0080101_01_02

Ground ClearancesAilerons Up

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

2-3-0

Page 6Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

A B C D

A

B

C

D



6.15

5.71

5.71

5.37 17.61

18.73

20.16 5.80

5.40

5.40

5.08

19.04

17.70

17.70

16.65

5.75

5.35

5.35

5.04 16.52

17.55

17.55

18.86

18.72

m ft m ft m ft


MID CG 31.9%

F_AC_020300_1_0100101_01_02

Ground ClearancesAilerons Down

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

2-3-0

Page 7Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

m ft m ft m ft

A

B

CD

E

F

G

H

J

K

L

M



6.50

6.37

6.376.23

6.23

6.08

6.08

5.90

5.90

5.70

5.30

4.75

21.34

20.89

20.8820.45

20.45

19.95

19.95

19.37

19.36

18.70

17.38

15.60

5.09

4.56

6.10

6.10

6.22

5.98

5.98

5.85

5.85

5.68

5.68

5.49

20.42

20.02

20.02

18.65

19.19

19.19

19.64

16.69

14.97

18.64

18.01

5.96

5.966.07

6.07

6.19

5.82

5.82

5.66

5.66

4.55

5.07

5.47

20.32

19.92

19.9219.55

19.55

19.11

18.58

18.58

19.11

14.91

16.63

17.95

19.64


MID CG 31.9%

A B C D E F G H J K L M

F_AC_020300_1_0110101_01_02

Ground ClearancesSpoilers Extended

FIGURE-2-3-0-991-011-A01

2-3-0

Page 8Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

A B D


m ft m ft m ft

A

B

C


D

E

F

G

H

J

K

L

E F G H J K L

M

N

P 6.06 19.88 5.73 18.80 5.68 18.64

18.01

18.01

5.49

5.49

18.14

18.14

5.53

5.53

19.13

19.13

5.83

5.83

5.58

5.57 18.27

18.31 5.30

5.30 17.39

17.39 5.27

5.27 17.29

17.29

16.505.0316.605.0617.395.30

5.24 17.19 5.00 16.40 4.98 16.34

15.49

15.494.72

4.7215.52

15.524.73

4.7316.24

16.244.95

4.95

4.63

4.63 15.19

15.19 4.43

4.43 14.53

14.53 4.43

4.43 14.53

14.53

3.45

4.26

4.27 14.01

13.98

11.32 3.26

4.05

4.08 13.39

13.29

10.70 3.28

4.06

4.09 13.42

13.32

10.76

M N PC


MID CG 32.3%

F_AC_020300_1_0210101_01_00

Ground ClearancesSlats Fully Extended

FIGURE-2-3-0-991-021-A01

2-3-0

Page 9Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

A B C D

A

B

C

D



3.98

3.66

2.92

3.44

13.07

12.01

11.29

9.58 2.73

3.25

3.47

3.79 12.44

11.38

10.66

8.95

3.75

3.43

3.22

2.70 8.86

10.55

11.26

12.30

m ft m ft m ft


MID CG 31.9%

F_AC_020300_1_0220101_01_00

Ground ClearancesFlaps Fully Extended

FIGURE-2-3-0-991-022-A01

2-3-0

Page 10Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

A B C D

A

B

C

D



3.98

3.66

2.92

3.44

13.07

12.01

11.29

9.58 2.73

3.25

3.47

3.79 12.44

11.38

10.66

8.95

3.75

3.43

3.22

2.70 8.86

10.55

11.26

12.30

m ft m ft m ft


MID CG 31.9%

F_AC_020300_1_0230101_01_00

Ground ClearancesFlaps-Tracks Fully ExtendedFIGURE-2-3-0-991-023-A01

2-3-0

Page 11Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-4-1 Interior Arrangements - Plan View

**ON A/C A340-200 A340-300

Interior Arrangements - Plan View

1. This section gives the typical configuration for A340-200 and A340-300.

2-4-1

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

E M E R G E N C Y E X I T


F O R W A R D P A S S E N G E R / C R E W D

O O R


O O R

A F T P A S S E N G E R / C R E W D

O O R


O O R

F O R D O O R S I Z E S

S E E C H A P T E R 2 .

7

P A S S E N G E R S E A T S

3 0 F I R S T C L A S S

3 0 5 T O U R I S T C L A S S

F_AC_020401_1_0030101_01_00

N O T E :

I T E M

D E S I G N A T I O N

A G L S

A T T E N D A N T S S E A T

G A L L E Y

L A V A T O R Y

S T O W A G E

( 9 )

( 6 )

( 8 )

( 3 )

F_AC_020401_1_0030101_01_00

A A A

A A

A A

A A

L L

L L L

G G

S

S S

G

G

G

G

L

L L

Interior Arrangements - Plan ViewTypical Configuration

FIGURE-2-4-1-991-003-A01

2-4-1

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

E M E

R G E N C Y E X I T

E M E

R G E N C Y E X I T

F O R W A R D P A S S E N G E R / C R E W

D O O R

F O R W A R D P A S S E N G E R / C R E W

D O O R


O O R


O O R

I T E M


A G L S


G A L L E Y

L A V A T O R Y

S T O W A G E




F O R D O O R S

I Z E S

S E E C H A P T E

R 2 . 7

F_AC_020401_1_0040101_01_00

L

N O T E :

L

( 9 )

( 5 )

( 7 )

( 3 )

F_AC_020401_1_0040101_01_00

A A A

A A

A A

A A

S

G G S S

L L

L L

L

G

G

G


FIGURE-2-4-1-991-004-A01

2-4-1

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200




O O R


O O R

A F T P A S S E N G E R / C R E

W D

O O R

A F T P A S S E N G E R / C R E

W D

O O R




4 8 B U S I N E S S C L A S S

N

O T E :

S E E C H A P T E R 2 . 7

F O R D O O R S I Z E S

I T E M


A G L S


G A L L E Y

L A V A T O R Y

S T O W A G E

( 1 4 )

( 1 0 )

( 8 )

( 4 )

S

A

A

A

A

A

A A

A A

A A

G G

G

G G G

A A

S S

G

A

S

G G

L L L

L

L L

L L

G

F_AC_020401_1_0050101_01_00


FIGURE-2-4-1-991-005-A01

2-4-1

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-5-0 Interior Arrangements - Cross Section

**ON A/C A340-200 A340-300

Interior Arrangements - Cross Section

1. This section gives the typical configuration of A340-200/-300 models.

2-5-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

C D C

F N M

H

K K

222 in5.640 m

208 in5.290 m

FIRST CLASS, 6 ABREAST BUSINESS CLASS, 7 ABREAST

TOURIST CLASS, 8 ABREAST CHARTER CLASS, 9 ABREAST

A − 54.0 in (1371.6 mm)B − 21.0 in (533 mm)C − 39.6 in (1006 mm)

D − 17.7 in (450 mm)E − 72.0 in (1829 mm)F − 19.0 in (483 mm)

G − 48.0 in (1219 mm)H − 19.8 in (503 mm)K − 41.5 in (1054.1 mm)M − 57.1 in (1450 mm)N − 16.5 in (419 mm)

C

ABA

D

F G

C D

DCH

C C

E

M

91.7 in2.330 mA

F_AC_020500_1_0020101_01_00

Interior Arrangements - Cross SectionTypical Configuration

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

2-5-0

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-6-1 Lower Deck Cargo Compartments

**ON A/C A340-200 A340-300

Lower Deck Cargo Compartments

1. This section gives the following data about lower deck cargo compartments:- Location and dimensions- Loading combinations.

2-6-1

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

0.95 m

(3.12 ft)2.75 m

(9.02 ft)

2.78 m

(9.12 ft)

15.02 m

(49.28 ft)A340−300

12.88 m

(42.26 ft)A340−200

12.32 m

(40.42 ft)

10.19 m

(33.43 ft)

4.04 m

(13.25 ft)

4.04 m

(13.25 ft)

LOWER DECKFWD CARGO

COMPARTMENT

LOWER DECKAFT CARGO

COMPARTMENT

LOWER DECKBULK CARGO

COMPARTMENT

FR39.1 FR53.2 FR65 FR73FR20

NOTE:

APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATION.

F_AC_020601_1_0050101_01_02

Lower Deck Cargo CompartmentsLocation and Dimensions

FIGURE-2-6-1-991-005-A01

2-6-1

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

14 LD3 60.4 in X 61.5 in

7 LD3 60.4 in X 61.5 in

5 PALLETS 96 in X 125 in


7 PALLETS 60.4 in X 125 in

12 LD3 60.4 in X 61.5 in

6 LD3 60.4 in X 61.5 in




F_AC_020601_1_0060101_01_02

Lower Deck Cargo CompartmentsLoading Combinations

FIGURE-2-6-1-991-006-A01

2-6-1

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

18 LD3 60.4 in X 61.5 in

9 LD3 60.4 in X 61.5 in




14 LD3 60.4 in X 61.5 in

7 LD3 60.4 in X 61.5 in




F_AC_020601_1_0060201_01_00

Lower Deck Cargo CompartmentsLoading Combinations

FIGURE-2-6-1-991-006-B01

2-6-1

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-7-0 Door Clearances

**ON A/C A340-200 A340-300

Door Clearances

1. This section gives door identification and location.

2-7-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

FWDPASSENGER/CREW

DOOR (1L)

MIDPASSENGER/CREW

DOOR (2L)

EMERGENCY EXITDOOR (3L)

AFTPASSENGER/CREW

DOOR (4L)

BULK CARGOCOMPARTMENT

DOORAFT CARGO

COMPARTMENTDOOR

AFTPASSENGER/CREW

DOOR (4R)

EMERGENCY EXITDOOR (3R)

FWDPASSENGER/CREW

DOOR (1R)MID

PASSENGER/CREWDOOR (2R)

FWD CARGOCOMPARTMENT

DOOR

F_AC_020700_1_0080101_01_00

Door Identification and LocationDoor Identification (Sheet 1 of 2)

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

2-7-0

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

46.69 m(153.18 ft)

33.83 m

(110.99 ft)17.74 m

(58.2 ft)5.85 m

(19.19 ft)

43.07 m

(141.31 ft)

9.53 m

(31.27 ft)40.09 m

(131.53 ft)

F_AC_020700_1_0080102_01_00

Door Identification and LocationDoor Location (Sheet 2 of 2)FIGURE-2-7-0-991-008-A01

2-7-0

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

FWDPASSENGER/CREW

DOOR (1L)

MIDPASSENGER/CREW

DOOR (2L)

EMERGENCY EXITDOOR (3L)

AFTPASSENGER/CREW

DOOR (4L)

BULK CARGOCOMPARTMENT

DOORAFT CARGO

COMPARTMENTDOOR

AFTPASSENGER/CREW

DOOR (4R)

EMERGENCY EXITDOOR (3R)

FWDPASSENGER/CREW

DOOR (1R)MID

PASSENGER/CREWDOOR (2R)

FWD CARGOCOMPARTMENT

DOOR

F_AC_020700_1_0080201_01_00

Door Identification and LocationDoor Identification (Sheet 1 of 2)

FIGURE-2-7-0-991-008-B01

2-7-0

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

50.96 m(167.19 ft)

35.96 m

(117.98 ft)17.74 m

(58.2 ft)5.85 m

(19.19 ft)

47.35 m

(155.35 ft)

9.53 m

(31.27 ft)44.36 m

(145.54 ft)

F_AC_020700_1_0080202_01_00

Door Identification and LocationDoor Location (Sheet 2 of 2)FIGURE-2-7-0-991-008-B01

2-7-0

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-7-1 Forward Passenger / Crew Doors

**ON A/C A340-200 A340-300

Forward Passenger / Crew Door

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

2-7-1

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

CRITICALCLEARANCELIMIT

2.43 m

(7 ft 11 in)

1.07 m

(3 ft 6 in)

0.64 m(2 ft 1 in)

0.75 m(2 ft 5 in)

3.00 m(9 ft 10 in)

5.85 m(19 ft 2 in)

SEECHAPTER

2−3

1.93 m(6 ft 3 in)

3.3 m

(10 ft 9 in)

0.045 m(1.77 in)

CL

CL

CL

F_AC_020701_1_0030101_01_01

Forward Passenger / Crew DoorsFIGURE-2-7-1-991-003-A01

2-7-1

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-7-2 Mid Passenger / Crew Doors

**ON A/C A340-200 A340-300

Mid Passenger / Crew Door

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

2-7-2

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

(TOP OF FLOOR)

0.75 m(2 ft 5 in)

1.07 m(3 ft 6 in)

2.43 m

(7 ft 11 in)

0.64 m(2 ft 1 in)

3.41 m(11 ft 2 in)

A340−200: 17.741 m (58 ft 2 in)

A340−300: 17.741 m (58 ft 2 in)(FROM NOSE)

1.93 m(6 ft 3 in)

SEECHAPTER

2−3

CL

CL

CL

0.045 m(1.77 in)

A

A

A AF_AC_020702_1_0020101_01_00

Mid Passenger / Crew DoorFIGURE-2-7-2-991-002-A01

2-7-2

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-7-3 Emergency Exits

**ON A/C A340-200 A340-300

Emergency Exits

1. This section gives emergency exits doors clearances.

2-7-3

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

(TOP OF FLOOR)

0.77 m(2 ft 6 in)

1.07 m

(3 ft 6 in)

(11 ft 2 in)

0.59 m(1 ft 11 in)

A340−200: 33.66 m (110 ft 5 in)

A340−300: 35.793 m (117 ft 5 in)(FROM NOSE)

1.93 m

SEECHAPTER

2−3

0.036 m(1.4 in)

A

A

3.41 m

CL

CL

CL

2.36 m(7 ft 8 in)

(6 ft 3 in)

A AF_AC_020703_1_0020101_01_01

Emergency ExitsFIGURE-2-7-3-991-002-A01

2-7-3

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-7-4 Aft Passenger / Crew Doors

**ON A/C A340-200 A340-300

Aft Passenger / Crew Doors

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

2-7-4

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

CRITICALCLEARANCE

LIMIT

CLSEE

CHAPTER2−3

CL CL

CL

1.07 m

(3 ft 6 in)

2.43 m(8 ft)

0.75 m(2 ft 5 in)

3 m

(9 ft 10 in)

1.99 m(6 ft 6 in)

0.64 m(2 ft 1 in)

A340−300: 50.956 m (167 ft 2 in)

A340−200: 46.689 m (153 ft 2 in)

(FROMNOSE)

A

A

A A

0.045 m

(1.8 in)

F_AC_020704_1_0020101_01_00

Aft Passenger / Crew DoorsFIGURE-2-7-4-991-002-A01

2-7-4

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-7-5 Forward Cargo Compartment Doors

**ON A/C A340-200 A340-300

Forward Cargo Compartment Doors

1. This section gives forward cargo compartment doors clearances.

2-7-5

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

A

A

(FROM NOSE)

COMPARTMENT DOOR

CL

CL

CL

SEECHAPTER

2−3

MID PASSENGER/CREW DOOR

CL

9.53 m(31 ft 3 in)

0.64 m(2 ft 1 in)

2.7 m(8 ft 10 in)

6.37 m(20 ft 10 in)

1.70 m(5 ft 6 in)

5.27 m(17 ft 3 in)

2.04 m(6 ft 8 in)

FORWARD PASSENGER/ CREW DOOR

FORWARD CARGO

A AF_AC_020705_1_0040101_01_00

Forward Cargo Compartment DoorsFIGURE-2-7-5-991-004-A01

2-7-5

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-7-6 Aft Cargo Compartment Doors

**ON A/C A340-200 A340-300

Aft Cargo Compartment Doors

1. This section gives Aft cargo compartment doors clearances.

2-7-6

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

A

AAFT PASSENGER/CREW DOOR

CL

CL

CL

SEECHAPTER

2−3

CL

BULK CARGOCOMPARTMENT DOOR

1.68 m(5 ft 6 in)

5.19 m

(17 ft)

2.03 m(6 ft 7 in)

F_AC_020706_1_0040101_01_00

A A

(FROM NOSE)A340−200: 40.092 m (131 ft 6 in)

A340−300: 44.36 m (145 ft 6 in)

2.78 m

(9 ft 1 in)

AFT CARGOCOMPARTMENT DOOR

F_AC_020706_1_0040101_01_00

Aft Cargo Compartment DoorsFIGURE-2-7-6-991-004-A01

2-7-6

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-7-7 Bulk Cargo Compartment Doors

**ON A/C A340-200 A340-300

Bulk Cargo Compartment Doors

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

2-7-7

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

A

A CL

CL

CL

SEECHAPTER

2−3

CL

AFT PASSENGER/CREW DOOR(REF)

(FROM NOSE)A340−200: 43.075 m (141 ft 3 in)

A340−300: 47.342 m (155 ft 3 in)

1.1 m(3 ft 7 in)

0.95 m(3 ft 1 in)

BULK CARGOCOMPARTMENT DOOR

1.07 m(3 ft 6 in)

1.41 m(4 ft 7 in)

A A

AFT CARGOCOMPARTMENT DOOR

F_AC_020707_1_0030101_01_00

Bulk Cargo Compartment DoorsFIGURE-2-7-7-991-003-A01

2-7-7

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-7-8 Main and Center Landing Gear Doors

**ON A/C A340-200 A340-300

Main Landing Gear Doors

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

2-7-8

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

GROUND LINE

A / C

8 1 °

0.06 m

0. 9 7 m

( 3 f t 2

i n )

0.85 m

(2 ft 9 in)

(2.4 in)

1.1m

(3 ft 7 in )

2.7 m

(8 ft 10 in)

3.96 m

(13 ft)

A340−200: 27.31 m (89 ft 7 in)

A340−300: 29.45 m (96 ft 7in)

0.23 m(9 in)

C L

2 .3 4 m ( 7 f t 8 i n )

3.03 m

(9 ft 11 in)

1.56 m

(5 ft 1 in) Z−2 m (6 ft 6 in)

A

A

F_AC_020708_1_0030101_01_01

Main and Center Landing Gear DoorsFIGURE-2-7-8-991-003-A01

2-7-8

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-7-9 Radome

**ON A/C A340-200 A340-300

Radome

1. This section gives the radome clearances.

2-7-9

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

6 7 °

CL

STA 7662.5FR1

1 . 3 2 5 m

( 4 f t 4 i n )

1 . 2

5 m

( 4 f t 1 i n )

1.65 m(5 ft 4 in)

F_AC_020709_1_0010101_01_00

RadomeFIGURE-2-7-9-991-001-A01

2-7-9

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-7-10 APU and Nose Landing Gear Doors

**ON A/C A340-200 A340-300

APU and Nose Landing Gear Doors

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

2-7-10

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

FUSELAGE DATUM LINE

FR95

FR101

* DEPENDING OF THE CG POSITION AND AIRCRAFT LOAD

MAX = 6.53 m (21 ft 5 in)

MIN = 5.79 m (18 ft 11 in)

MAX = 6.88 m (22 ft 6 in)

MIN = 6.14 m (20 ft 1 in)

MAX = 2.01 m (6 ft 7 in)

MIN = 1.83 m (6 ft)

MAX = 1.58 m (5 ft 2 in)

MIN = 1.4 m (4 ft 7 in)*

*

**

F_AC_020710_1_0030101_01_00

APU and Nose Landing Gear DoorsFIGURE-2-7-10-991-003-A01

2-7-10

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

FUSELAGE DATUM LINE

FR95

FR101

* DEPENDING OF THE CG POSITION AND AIRCRAFT LOAD

MAX = 6.51 m (21 ft 4 in)

MIN = 5.77 m (18 ft 11 in)

MAX = 6.85 m (22 ft 5 in)

MIN = 6.11 m (20 ft)

MIN = 1.39 m (4 ft 6 in)

MAX = 1.57 m (5 ft 1 in)MAX = 2.00 m (6 ft 6 in)

MIN = 1.82 m (5 ft 11 in)

**

**

F_AC_020710_1_0040101_01_00

APU and Nose Landing Gear DoorsFIGURE-2-7-10-991-004-A01

2-7-10

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



2-8-0 Escape Slides

**ON A/C A340-200 A340-300

Escape Slides

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

2. LocationEscape facilities are provided at the following locations:

A. Door Escape Facility- One dual lane escape slide-raft at each passenger/crew door (total six)- One single lane escape slide-raft at each emergency exit door (total two).The slides are installed in a container in the lower part of the door.

2-8-0

Page 1Apr 01/13

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**ON A/C A340-200

FWD CABIN ESCAPE SLIDE

MID CABIN ESCAPE SLIDE

AFT CABINESCAPE SLIDE

EMERGENCY EXITESCAPE SLIDE

F_AC_020800_1_0030101_01_00

Escape SlidesLocation (Sheet 1 of 2)

FIGURE-2-8-0-991-003-A01

2-8-0

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**ON A/C A340-200

G R I D E Q U A L S 1 m ( 3 . 2 8 f t ) I N R E A L I T Y

E M E R G E N C Y D E S C E N T D E V I C E

T H R O U G H W I N D O W O P E N I N G

0 − 3

− 6

− 9

− 1 2

− 1 5

− 2 1

− 1 8

− 2 4

− 2 7

− 3 0

− 3 3

F_AC_020800_1_0030102_01_00

Escape SlidesDimensions (Sheet 2 of 2)

FIGURE-2-8-0-991-003-A01

2-8-0

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**ON A/C A340-300

FWD CABIN ESCAPE SLIDE

EMERGENCY EXITESCAPE SLIDE

MID CABIN ESCAPE SLIDE

AFT CABINESCAPE SLIDE

F_AC_020800_1_0030201_01_00

Escape SlidesLocation (Sheet 1 of 2)

FIGURE-2-8-0-991-003-B01

2-8-0

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**ON A/C A340-300

G R I D E Q U A L S 1 m ( 3 . 2 8 f t ) I N R E A L I T Y

E M E R G E N C Y D E S C E N T D E V I C E

T H R O U G H W I N D O W O P E N I N G

0 − 3

− 6

− 9

− 1 2

− 1 5

− 2 1

− 1 8

− 2 4

− 2 7

− 3 0

− 3 3

F_AC_020800_1_0030202_01_00

Escape SlidesDimensions (Sheet 2 of 2)

FIGURE-2-8-0-991-003-B01

2-8-0

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2-9-0 Landing Gear

**ON A/C A340-200 A340-300

Landing Gear Maintenance Pits

1. General

The minimum maintenance pit envelopes for the main landing gear shock absorber removal are shownin Figures 1 and 2.

All dimensions shown are minimum dimensions with zero clearances.

The dimensions for the pits have been determined for these design factors:- The length and width of the pits allow the gear to rotate as the weight is taken off the landing

gear

- The depth of the pits allow the shock absorber to be removed when all the weight is taken off thlanding gear.

Dimensions for elevators and associated mechanisms must be added to those in Figures 1 and 2.

A. Elevators

These can be either mechanical or hydraulic. Elevators are used to:- permit easy movement of persons and equipment around the main landing gears- to lift and remove landing gear assemblies out of the pits.

B. Jacking

The aircraft must be in position over the pits to put the gear on the elevators. Jacks must beinstalled and engaged with all the jacking points (Ref. Section 2-14 for Jacking).Jacks must support the total aircraft weight, i.e. when the landing gears do not touch theelevators on retraction/extension tests.When tripod support jacks are used, the tripod-base circle radius must be limited because thelocations required for positioning the jacks are close to the sides of the pits.

2-9-0

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**ON A/C A340-300

F R O N T O F N O S E R A D O M E

F O R W A R D J A C K I N G P O I N T

W I N G J A C K

I N G P O I N T

A I R C R A F T C E N T E R L I N E

W I N G J A C K I N G P O I N T

3 1 . 5 5 m

( 1 0 3 . 5 1 f t )

3 . 5 8 m

( 1 1 . 7 5 f t )

8 . 5 1 m

( 2 7 . 9 2 f t )

3 . 8 9 m

( 1 2 . 7 6 f t )

6 . 3 1 m

( 2 0 . 7 f t )

5 . 3 4 m

( 1 7 . 5 2 f t )

3 4 . 3 1 m

( 1 1 2 . 5 7 f t ) 2

5 . 3 8 m

( 8 3 . 2 7 f t )

3 . 6 5 m

( 1 1 . 9 8 f t )

N O T E :

E N

V E L O P E S S H O W N W I T H Z E R O C L E A R A N C E T O O U T S I D E E D G E O F T I R E S .

F_AC_020900_1_0030101_01_00

Landing Gear Maintenance PitsMaintenance Pit Envelopes (Sheet 1 of 2)

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

2-9-0

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**ON A/C A340-300

D I M E N S I O N S

m

m

f t

f t

M A I N L A

N D I N G G E A R

6 . 5 3 m

( 2

1 . 4 2 f t )

F U S E L A G E H O R I Z O N T A L D A T U M

( 1 0 3 . 0 2 f t )

3 1 . 4 m

3 3 . 1 3 m

( 1 0 8 . 6 9 f t )

F R O N T O F N O S E R A D O M E A

B

C

6 . 6 7 m

( 2 1 . 8 8 f t )

D

1 . 5 3

5 . 0 2

0 . 2

0 . 6 6

0 . 8 1

2 . 6 6

m

f t

B

C

D

m

f t

A

1 . 5 6

5 . 1 2

3 .

’ C ’ R E P R E S E N T S P O S I T I O N O F H Y D R A U L I C O R

M E C H A N I C A L E L E V A T O R W I T H T H E M L G

S H O C K A B S O R B E R I N T H E D E F L A T E D

A N D

C O M P R E S S E D C O N D I T I O N F O R S H O C

K

A B S O R B E R R E M O V A L .

4 .

’ D ’ R E P R E S E N T S P O S I T I O N O F H Y D R A U L I C O R


S H O C K A B S O R B E R I N T H E E X T E N D E D

C O N D I T I O N

F O R S H O C K A B S O R B E R R E M O V A L .

1 .

’ A ’ R E P R E S E N T S P O S I T I O N O F N L G W H

E E L

A B O V E S T A T I C G R O U N D L I N E W I T H A I R C R A F T

L E V E L L E D A N D J A C K E D .

A P I T I S N O T R E Q U I R E D F O R T H E N L G

.

2 .

’ B ’ R E P R E S E N T S P O S I T I O N O F L O W E S

T M L G

M A I N W H E E L A B O V E S T A T I C G R O U N D

L I N E

W I T H A I R C R A F T J A C K E D I N T O P O S I T I O N

A B O V E H Y D R A U L I C O R M E C H A N I C A L E L E V A T O R ,

F O R R E T R A C T I O N / E X T E N S I O N T E S T S .

N O T E :

F_AC_020900_1_0030102_01_00


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

2-9-0

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**ON A/C A340-200

3 . 5 8 m

( 1 1 . 7 5 f t )

8 . 5 1 m

( 2 7 . 9 2 f t )

3 . 8 9 m

( 1 2 . 7 6 f t )

6 . 3 1 m

( 2 0 . 7 f t )

5 . 3 4 m

( 1 7 . 5 2 f t )

3 2 . 1 8 m

( 1 0 5 . 5 8 f t )

2 9 . 4 1 m

( 9 6 . 4 9 f t )

2 3 . 2 4 m

( 7 6 . 2 5 f t )

3 . 6 5 m

( 1 1 . 9 8 f t )

F R O N T O F N O S E R A D O M E

F O R W A R D J A C K I N G P O I N T

W I N G J A C K

I N G P O I N T

A I R C R A F T C E N T E R L I N E

W I N G J A C K I N G P O I N T

N O T E :

E N

V E L O P E S S H O W N W I T H Z E R O C L E A R A N C E T O O U T S I D E E D G E O F T I R E S .

F_AC_020900_1_0030201_01_00


FIGURE-2-9-0-991-003-B01

2-9-0

Page 4Apr 01/13

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**ON A/C A340-200

D I M E N S I O N S

m

m

f t

f t

M A I N L A

N D I N G G E A R

6 . 5 3 m

( 2

1 . 4 2 f t )

F U S E L A G E H O R I Z O N T A L D A T U M

F R O N T O F N O S E R A D O M E A

B

C

6 . 6 7 m

( 2 1 . 8 8 f t )

D

1 . 5 3

5 . 0 2

0 . 2

0 . 6 6

0 . 8 1

2 . 6 6

m

f t

B

C

D

m

f t

A

1 . 5 6

5 . 1 2

( 9 5 . 8 3 f t )

2 9 . 2 1 m

3 0 . 4 m

( 9 9 . 7 4 f t )

3 .

’ C ’ R E P R E S E N T S P O S I T I O N O F H Y D R A U L I C O R


S H O C K A B S O R B E R I N T H E D E F L A T E D

A N D

C O M P R E S S E D C O N D I T I O N F O R S H O C

K

A B S O R B E R R E M O V A L .

4 .

’ D ’ R E P R E S E N T S P O S I T I O N O F H Y D R A U L I C O R


S H O C K A B S O R B E R I N T H E E X T E N D E D

C O N D I T I O N

F O R S H O C K A B S O R B E R R E M O V A L .

1 .

’ A ’ R E P R E S E N T S P O S I T I O N O F N L G W H

E E L

A B O V E S T A T I C G R O U N D L I N E W I T H A I R C R A F T

L E V E L L E D A N D J A C K E D .

A P I T I S N O T R E Q U I R E D F O R T H E N L G

.

2 .

’ B ’ R E P R E S E N T S P O S I T I O N O F L O W E S

T M L G

M A I N W H E E L A B O V E S T A T I C G R O U N D

L I N E

W I T H A I R C R A F T J A C K E D I N T O P O S I T I O N

A B O V E H Y D R A U L I C O R M E C H A N I C A L E L E V A T O R ,

F O R R E T R A C T I O N / E X T E N S I O N T E S T S .

N O T E :

F_AC_020900_1_0030202_01_00


FIGURE-2-9-0-991-003-B01

2-9-0

Page 5Apr 01/13

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**ON A/C A340-200 A340-300

Landing Gear

1. General

The aircraft has:- Two Main Landing Gears (MLG) with four wheel bogie assembly and related doors- A Centerline Landing Gear (CLG) with twin wheel assembly and related doors- A Nose Landing Gear retracts forward into a fuselage compartment below the cockpit.

The Main Landing Gears are located under each wing and retract sideways towards the fuselagecenterline.The Centerline Landing Gear is located on the belly and retract forward into a bay in the fuselage.The Nose Landing Gear retracts forward into a fuselage compartment below the cockpit.The retraction and extension of the landing gears and landing gear doors are operated hydraulically

and mechanically. The control, sequence and indication are electrical.In abnormal operation, the landing gears can be extended by gravity.

For the dimensions of the landing gear footprint and tire size, refer to 7-2-0

2. Main Landing Gear and Doors

Each Main Landing Gear has a leg assembly and a four-wheel bogie beam. The MLG leg includes ashortening mechanism, a bogie pitch trimmer and an oleo-pneumatic shock absorber. In flight, withthe MLG extended, the bogie is held in a trailing condition (rear wheels low) by an articulationlinkage and a pitch trimmer. The folding sidestay is locked mechanically by a lockstay (which is

operated by the downlock actuator) when the MLG is fully extended.

Each MLG bay has the following doors:- A hydraulically-operated main door- A mechanically-operated hinged door- A fairing door on the MLG leg.

All the doors close when the MLG retracts. When the MLG is extended the main door closes and thehinged door stays open. A manually operated mechanism (for maintenance personnel) lets the maindoors be opened for access to the MLG bay when the aircraft is on the ground.

3. Centerline Landing Gear and Doors

The CLG includes a twin-wheel axle assembly and a leg assembly that includes an oleo pneumaticshock absorber. The CLG is supported longitudinally by a two-piece folding dragstay. The dragstay islocked mechanically by the lock links when the CLG is fully extended.

Each CLG bay has the following doors:

2-9-0

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- Two hydraulically-operated FWD doors- Two mechanically-operated AFT doors- A fixed fairing door on the CLG leg.

All the doors close when the CLG retracts. When the CLG is extended the FWD doors close and theAFT doors stay open. A door opening mechanism lets the FWD doors be opened on the ground foraccess to the CLG bay.

4. Nose Landing Gear and Doors

The NLG includes a twin-wheel axle assembly and an oleo-pneumatic shock absorber. The NLG issupported longitudinally by a two-piece dragstay. The dragstay is locked mechanically by the locklinks when the NLG is fully extended.

Each NLG bay has the following doors:- Two hydraulically-operated FWD doors- Two mechanically-operated AFT doors- A fixed fairing door on the NLG leg.

All the doors close when the NLG retracts. When the NLG is extended the FWD doors close and theAFT doors stay open. A door opening mechanism lets the FWD doors be opened on the ground foraccess to the NLG bay.

5. Nose Wheel Steering

Nose wheel steering system is a computer controlled electro-hydraulic system. The system uses theGreen main hydraulic power system to operate the hydraulic components.

The steering is controlled by two hand wheel transmitters in the cockpit, which supply the primarysteering inputs to the BSCU (Brake and Steering Control Unit ).A steering disconnection box is installed on the NLG to disconnect the steering for towing.

For the operation and control of nose wheel steering, refer to AMM 32-51-00.For the steering angle limits, refer to AMM 09-10-00.

6. Landing Gear Servicing Points

A. GeneralFluid filling and gas charging of the MLG,CLG and NLG shock absorbers are accomplishedthrough MS28889 standard valves.

B. Charging PressuresFor charging of the landing gear shock absorbers, refer to AMM 12-14-32.

7. Landing Gear Control

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The landing gear and door operation is controlled electrically by one of the two Landing Gear Controand Interface Units (LGCIU). Control changes from one LGCIU to the other after each extensioncycle.In normal operation, the landing gears and doors are operated by the Green hydraulic system.

In abnormal operation, the landing gears can be extended by the operation of electro-mechanical free-fall system. The related electrical switches in the cockpit disengages the doors and the landing gearuplocks. The landing gears then extend by free-fall and the downlock links of each landing gear (L/G)are locked in position by springs.

8. Braking

A. GeneralCarbon multi-disc brakes are installed on each wheel of the MLG. Each brake assembly has twowear indicators installed.

The braking system has four braking modes and also autobrake and anti-skid systems:

- Normal braking with anti-skid- Alternate braking with anti-skid- Alternate braking without anti-skid- Parking brake with full brake pressure.

B. In-Flight Wheel BrakingBraking occurs automatically during the retraction of the landing gears. This stops the rotationof the MLG wheels before the landing gears go into their related bays.The wheels of the NLG are braked by spring loaded pads.

9. Tire Pressure Indicating System (TPIS)

The TPIS automatically monitors the tire pressures and shows these values on Test Equipment(BITE) and also supplies other data and warnings on the WHEEL page of the System Display (SD).

10. Built In Test Equipment (BITE)

The BITE has hardware and software for these functions:- to automatically do a self test at power-up- to continuously monitor the related systems for failures- to continuously monitor the interface with other specified systems in the aircraft- to keep a record of each failure and defect and send this data to other systems in the aircraft- to automatically do a functional test of some related systems before a landing

- to do specified system tests during ground maintenance.

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

2-9-0

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**ON A/C A340-200 A340-300

MAIN DOOR

HINGED DOOR

FIXED FAIRING DOOR

A

B

C

D

F

E

DOWNLOCKACTUATOR

SHORTENINGMECHANISM

SIDE STAYASSEMBLY MLG LEG

ASSEMBLY

TORQUE LINKS

BOGIE PITCHTRIMMER

BOGIE BEAMASSEMBLY

SHOCK ABSORBER

ARTICULATING LINKS

RADIAL OR BIASPLY TIRES

A

(HYDRAULICALLYOPERATED)

FWD AXLE

AFT AXLE

BRAKE RODASSEMBLY

F_AC_020900_1_0090101_01_00

Main Landing GearGeneral (Sheet 1 of 3)

FIGURE-2-9-0-991-009-A01

2-9-0

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**ON A/C A340-200 A340-300

C

WARNING FLAG

GROUND LOCK PIN

LOCK STAY

B

LH SHOWNRH SYMMETRICAL

QUICK RELEASE PIN

SAFETYCOLLAR

WARNING FLAG

WARNING FLAG

QUICK RELEASE PIN

DOOR ACTUATOR

F_AC_020900_1_0090102_01_00

Main Landing GearSafety Devices (Sheet 2 of 3)FIGURE-2-9-0-991-009-A01

2-9-0

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**ON A/C A340-200 A340-300

SEAL CHANGEOVERVALVE

BLEED/INFLATIONVALVE

D

E

F

FWD

FILL VALVE

GROUND POINT

F_AC_020900_1_0090103_01_00

Main Landing GearServicing (Sheet 3 of 3)

FIGURE-2-9-0-991-009-A01

2-9-0

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**ON A/C A340-200 A340-300

E

F

RETRACTIONACTUATOR

SIDE MEMBER

MAIN FITTING

BARREL

UPLOCK PIN

WEIGHT AND BALANCE SENSORATTACHMENT POINTS

SHOCKABSORBER

AXLE

TORQUE LINKS

SERVICING PLATE

HINGED DOORDRIVE MECHANISM

ATTACHEMENT POINT

A

AFT DOOROPERATING ROD

AFT DOOR

FIXED FAIRING

FWD DOOR

A

D

(MECHANICALLYOPERATED)

(HYDRAULICALLYOPERATED)

C

B

B


F_AC_020900_1_0100101_01_00

Centerline Landing GearGeneral (Sheet 1 of 3)

FIGURE-2-9-0-991-010-A01

2-9-0

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**ON A/C A340-200 A340-300

B

RH SHOWNLH SYMMETRICAL

GROUNDLOCK PIN

DRAG STAY

DOWNLOCK SPRINGS

C

ASSEMBLY

SAFETYCOLLAR

QUICK RELEASE PIN

WARNING FLAG

WARNING FLAG

QUICK RELEASE PIN

WARNINGFLAG

DOOR ACTUATOR

F_AC_020900_1_0100102_01_00

Centerline Landing GearSafety Devices (Sheet 2 of 3)FIGURE-2-9-0-991-010-A01

2-9-0

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**ON A/C A340-200 A340-300

D

G

OIL FILLERVALVE

INFLATION VALVE(FIRST STAGE)

E

INFLATION VALVE(SECOND STAGE)

F

FWD


G

FWD

F_AC_020900_1_0100103_01_00

Centerline Landing GearServicing (Sheet 3 of 3)

FIGURE-2-9-0-991-010-A01

2-9-0

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**ON A/C A340-200 A340-300

RETRACTION ACTUATOR

DOWNLOCKACTUATOR

MAIN FITTING

DOWNLOCK SPRINGS

TORQUE LINKS


TOWING BRACKET

SHOCK ABSORBER

AXLE

NWS ACTUATORS

LOWER DRAGSTAY(FOLDING STRUT)

UPPER DRAGSTAY(FOLDING STRUT)

EH

D

AFT DOOR(MECHANICALLY OPERATED)

FWD DOORS

A

(HYDRAULICALLY

AFT DOOR(MECHANICALLY OPERATED)

FIXED FAIRING

A

C

F

G

OPERATED)

B

B

F_AC_020900_1_0110101_01_00

Nose Landing GearGeneral (Sheet 1 of 4)

FIGURE-2-9-0-991-011-A01

2-9-0

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**ON A/C A340-200 A340-300

B

DRAG STAYATTACHMENT

GROUNDLOCK PIN

LOCK SPRINGATTACHMENT

LOWER

LOCK−LINK

UPPERLOCK−LINK

DOWN LOCKACTUATOR

ATTACHMENT

WARNING FLAG

C

RH SHOWNLH SYMMETRICAL

SAFETYCOLLAR

QUICK RELEASE PIN

WARNING FLAG

WARNING FLAG

QUICK RELEASE PIN

DOOR ACTUATOR

F_AC_020900_1_0110102_01_00

Nose Landing GearSafety Devices (Sheet 2 of 4)FIGURE-2-9-0-991-011-A01

2-9-0

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**ON A/C A340-200 A340-300


CHARGE VALVE

BLEED VALVE

E

D

INFLATION VALVE(FIRST STAGE)

FWD

F_AC_020900_1_0110103_01_00

Nose Landing GearServicing (Sheet 3 of 4)

FIGURE-2-9-0-991-011-A01

2-9-0

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**ON A/C A340-200 A340-300

INFLATION VALVE(SECOND STAGE)

LANDING GEAR

GROUND POINT

FWD

F

TOWING LEVER

SAFETY PIN(TOWING POSITION)

WARNING FLAG

NORMAL POSITION(NOSE WHEEL STEERING

OPERATIONAL)

TOWING POSITION(NOSE WHEEL STEERING

DEACTIVATED)

G

H

F_AC_020900_1_0110104_01_00

Nose Landing GearServicing and Steering Disconnection Box (Sheet 4 of 4)

FIGURE-2-9-0-991-011-A01

2-9-0

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2-10-0 Exterior Lighting

**ON A/C A340-200 A340-300

Exterior Lighting

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

EXTERIOR LIGHTINGITEM DESCRIPTION

1 RIGHT NAVIGATION LIGHT (GREEN)

2 LEFT NAVIGATION LIGHT (RED)

3 TAIL NAVIGATION LIGHT (WHITE)

4 UPPER ANTI-COLLISION LIGHT/BEACON(RED)

5 LOWER ANTI-COLLISION LIGHT/BEACON(RED)

6 LOGO LIGHTS7 ENGINE SCAN LIGHTS8 WING SCAN LIGHTS9 WING STROBE LIGHT (HIGH INTENSITY,

WHITE)

10 TAIL STROBE LIGHT (HIGH INTENSITY,WHITE)

11 LANDING LIGHTS

12 RUNWAY TURN-OFF LIGHTS13 TAXI LIGHTS14 TAKE-OFF LIGHTS15 CARGO COMPARTMENT FLOOD LIGHTS16 LANDING GEAR BAY/WELL LIGHTS (DOME)

2-10-0

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**ON A/C A340-200

1 RH

2 LH

87 9

5

10

3

64

F_AC_021000_1_0040101_01_00

Exterior Lighting(Sheet 1 of 5)

FIGURE-2-10-0-991-004-A01

2-10-0

Page 2Apr 01/13

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**ON A/C A340-200

13 12 11

14

NOTE:

LIGHTS 13 AND 14 ARE THE SAME, BUT THEY OPERATE WITH DIFFERENT POWER SETTINGS.

F_AC_021000_1_0040102_01_00


FIGURE-2-10-0-991-004-A01

2-10-0

Page 3Apr 01/13

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**ON A/C A340-200

7

21

3

7

12 12

13

14

F_AC_021000_1_0040103_01_00


FIGURE-2-10-0-991-004-A01

2-10-0

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**ON A/C A340-200

99

4 5

8

10

8

1111

F_AC_021000_1_0040104_01_00


FIGURE-2-10-0-991-004-A01

2-10-0

Page 5Apr 01/13

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**ON A/C A340-200

EXAMPLE FOR LIGHT N° 15

CEILING LIGHT

SPOT LIGHT

GROUND

6

6

15 16 15 16

F_AC_021000_1_0040105_01_00


FIGURE-2-10-0-991-004-A01

2-10-0

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**ON A/C A340-300

1 RH

LH

4

78

6

2

9

3

10

5

F_AC_021000_1_0050101_01_00


FIGURE-2-10-0-991-005-A01

2-10-0

Page 7Apr 01/13

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**ON A/C A340-300

12

14

1113

NOTE:

LIGHTS 13 AND 14 ARE THE SAME, BUT THEY OPERATE WITH DIFFERENT POWER SETTINGS.

F_AC_021000_1_0050102_01_00


FIGURE-2-10-0-991-005-A01

2-10-0

Page 8Apr 01/13

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**ON A/C A340-300

21

7

12

13

14

12

7

3

F_AC_021000_1_0050103_01_00


FIGURE-2-10-0-991-005-A01

2-10-0

Page 9Apr 01/13

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**ON A/C A340-300

99

10

8

54

8

1111

F_AC_021000_1_0050104_01_00


FIGURE-2-10-0-991-005-A01

2-10-0

Page 10Apr 01/13

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**ON A/C A340-300

EXAMPLE FOR LIGHT N° 15

CEILING LIGHT

SPOT LIGHT

GROUND

6

6

15 16 15 16

F_AC_021000_1_0050105_01_00


FIGURE-2-10-0-991-005-A01

2-10-0

Page 11Apr 01/13

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2-11-0 Antennas and Probes Location

**ON A/C A340-200 A340-300

Antennas and Probes Location

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

2-11-0

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**ON A/C A340-200

L O C

G P S ( 1 )

G P S ( 2 )

T C A S T O P

V H F ( 1 )

G P S ( 2 )

V H F ( 3 )

E

L T

M A R K E R

G P S ( 1 )

S T A

T I C P R O B E ( 1 )

E M E R

G E N C Y S T A T I C P R O B E ( 3 )

S T

A T I C P R O B E ( 2 )

R A D I O A L T I M E T E R ( 2 )

R A

D I O A L T I M E T E R ( 1 )

A T C ( 4 )

W E A T H E R R A D A R

V H F ( 4 )

H F

T C A S B O T T

O M

D M

E ( 2 )

P

I T O T P R O B E ( 3 )

G L I D E

A O A S E N S O R ( 1 )

T A T P R O B E

I C E

D E T E C T O R P R O B E

P I T O T P R O B E ( 1 )

D M E ( 1 )

A T C ( 1 )

N O T E :

D E P E N D I N G O N A I R C R A F T C O N F I G U R A T

I O N

F_AC_021100_1_0040101_01_00

Antennas and ProbesLocation (Sheet 1 of 2)

FIGURE-2-11-0-991-004-A01

2-11-0

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**ON A/C A340-200

A D F ( 2 )

A D F ( 1 )

V O R

E M E R G E N C Y S T A T I C

P R O B E ( 3 )

A T C ( 3 )


I C E D E T E C T O R P R O B E

T A T P R O B E

S A T C O M

V H F ( 2 )

S T A T I C P R

O B E ( 1 )

S T A T I C P R O B E ( 2 )

A T C ( 2 ) A

O A S E N S O R ( 2 )

A O A S E N S O R ( 3 ) S T B Y

N O T E :


I O N

F_AC_021100_1_0040102_01_00


FIGURE-2-11-0-991-004-A01

2-11-0

Page 3Apr 01/13

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**ON A/C A340-300

G P S ( 1 )

G P S ( 2 )

T C A S T O P

V H F ( 1 )

A T C ( 4 )

G P S ( 2 )

V H F ( 3 )

E L T

G P S ( 1 )

W E A T H E R R A D A R

H F


E M E R G

E N C Y S T A T I C P R O B E ( 3 )


T C A S B O T T O M

A O A S E N S O R ( 1 )

I C E D E T E C T O R P R O B

E


L O C

M

A R K E R

D M E ( 2

)

D M E ( 1 )

A T C ( 1 ) V H

F ( 4 )

P I T

O T P R O B E ( 3 )

G L I D E

T A T P R O B E



N O T E :


I O N

F_AC_021100_1_0050101_01_00


FIGURE-2-11-0-991-005-A01

2-11-0

Page 4Apr 01/13

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**ON A/C A340-300

A D F ( 2 )

A D F ( 1 )

V O R

A O A S E N S O R ( 3 ) S T B Y

A O A S E N S O R ( 2 )

A T C ( 2 )

S T A T

I C P R O B E ( 2 )

E M E R G E N C Y S T A T I C

P R O B E ( 3 )

S T A T I C P

R O B E ( 1 )

V H F ( 2 )

A T C ( 3 )

T A T P R O B

E


I C E D E T E C T O R P R O B E

S A T C O M

N O T E :


I O N

F_AC_021100_1_0050102_01_00


FIGURE-2-11-0-991-005-A01

2-11-0

Page 5Apr 01/13

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2-12-0 Engine and Nacelle

**ON A/C A340-200 A340-300

Engine and Nacelle

1. Engine and Nacelle - CFM 56-5C Engine

A. EngineThe engine is an axial flow, dual spool, high bypass ratio, turbofan engine.The principal modules of the engine are:- The fan and booster- The high pressure compressor- The combustion chamber- The High Pressure Turbine (HPT)- The Low Pressure Turbine (LPT)- The accessory drive gearbox.

The fan and booster assembly consists of a single-stage fan rotor and a four-stage axial booster,cantilever-mounted at the rear of the fan disk. The compressor is a nine-stage axial flowassembly. Air, taken in through the fan and booster sections, passes through successive stagesof rotor blades and stator vanes, being compressed as it passes from stage to stage. Afterpassing through the 9 high pressure compressor stages, the air is fully compressed. The InletGuide Vanes (IGV) and the first 3 stages of the compressor are variable. The combustionchamber is a short, annular structure. The combustion of fuel takes place in the combustorinstalled in the combustion casing. The HPT module consists of a single-stage nozzle and rotor.The HPT is an air-cooled single-stage high-energy turbine. Rotor blades are individuallyreplaceable without the need for rotor disassembly or re-balancing. The LPT consists of 5 stagesof blades and vanes. The LPT drives the fan rotor through the inner concentric shaft and isaerodynamically coupled to the high pressure system. The engine and aircraft accessories aremounted on the accessory gearbox which is located on the lower portion of the fan casing and isdriven by a shaft from the transfer gearbox. Power for the engine and the aircraft accessories isextracted from the high pressure compressor rotor shaft through an inlet gearbox through theradial drive shaft to the transfer gearbox.

B. NacelleThe nacelle provides protection for the engine and the engine accessories, and aerodynamicairflow around the engine during operation. Each engine is housed in a nacelle suspended from apylon attached below the wing. The nacelle consists of the following major components:

(1) Air Intake Cowl AssemblyThe engine air intake cowl structure is an interchangeable aerodynamically-faired assemblyIt is installed on the forward face of the engine fan case.

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(2) Fan Cowl AssemblyThe fan cowls are interchangeable units. They enclose the engine fan case between the airintake cowl and the thrust reverser. Three hinges at the pylon support each fan cowl. Thefan cowls are latched at the bottom with three adjustable tension hook latches.

(3) Fan Thrust ReverserThe thrust reverser comprises two cowls. Each cowl is hinged at the top to the pylon andlatched to the other cowl along the bottom centerline; the forward end is secured onto theaft outer flange of the fan case and the aft end onto the forward outer barrel of theexhaust nozzle. The fan thrust reverser assembly forms the passage for fan airstream flowbetween the fan case aft frame and the exhaust nozzle/mixer inlet. When in reverse thrustmode, four pivoting doors turn the engine fan air flow forward and provide a braking effectto reduce the aircraft stopping distance. The thrust reverser is designed for groundoperation only. A hydraulically-actuated cowl-opening system allows each thrust reversercowl to be opened independently.

(4) Exhaust NozzleThe exhaust nozzle attaches to the thrust reverser when the reverser cowls are closed.When they are open the exhaust nozzle is maintained on the mixer by two support pinslocated on the upper forward part of the mixer and by a strut. The nozzle can be removedalone or together with the engine.

2-12-0

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**ON A/C A340-200 A340-300

HP COMPRESSORFAN AND BOOSTER

1.01 m

(3.31 ft)

2.62 m

(8.6 ft)

2.99 m

(9.81 ft)

COMBUSTION

SECTION

1.07 m(3.51 ft)

HP TURBINE

LP TURBINE

TURBINE

REAR FRAME

ACCESSORY DRIVE

SECTION

A

1.98 m(6.5 ft)

1.05 m

(3.44 ft)

2.09 m

(6.86 ft)

1.28 m(4.2 ft)

2.25 m(7.38 ft)

A

B

B

NOTE:

APPROXIMATE DIMENSIONS

FWD

F_AC_021200_1_0160101_01_00

Engine and NacelleEngine Dimensions - CFM 56-5C

FIGURE-2-12-0-991-016-A01

2-12-0

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**ON A/C A340-200 A340-300

(4.63 ft)

1.41 m

E E

(6.66 ft)

2.03 m

(6.43 ft)

1.96 m

D D

(7.22 ft)2.2 m BLOCKERDOOR

EXTENDED

3.17 m(10.4 ft)

C C

(7.32 ft)

2.23 m

(7.91 ft)

2.41 m

NOTE:APPROXIMATE DIMENSIONS

A A B B

NAC STA

(27.99 ft)8.53 m

NAC STA

(22.28 ft)6.79 m

NAC STA

(19.13 ft)5.83 m

NAC STA

(12.43 ft)3.79 m

NAC STA

(9.35 ft)2.85 m

NAC STA

(17.03 ft)5.19 m

(18.67 ft)5.69 m

FAN

COWL

EXHAUST

NOZZLE

THRUST

REVERSERDISTANCE FROM

THE NOSE

A

A

B

B

C

C

E

E

D

D

AIR INTAKE

COWL

DISTANCE FROMTHE NOSE

A340−300 A340−200

(73.46 ft)22.39 m

(66.44 ft)20.25 m

(95.01 ft)28.96 m

(88.02 ft)26.83 m

INBOARDENGINE

OUTBOARDENGINE

(7.97 ft)2.43 m

F_AC_021200_1_0170101_01_00

Engine and NacelleNacelle Dimensions - CFM 56-5C

FIGURE-2-12-0-991-017-A01

2-12-0

Page 4Apr 01/13

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**ON A/C A340-200 A340-300

4.43 m

(14.53 ft)2.01 m

(6.59 ft)

1.99 m

(6.53 ft)

55°

0.8 m(2.62 ft)

0.76 m2.49 ft

CONDITIONS: MTOW, MID C.G., STATIC, CFM ENGINES.

INBOARDENGINE

OUTBOARDENGINE

(REFER TOCHAPTER 2−3)

A

NOTE:APPROXIMATE DIMENSIONS

1.24 m (4.07 ft)

2.53 m (8.3 ft)

A

F_AC_021200_1_0180101_01_00

Engine and NacelleFan Cowls - CFM 56-5C

FIGURE-2-12-0-991-018-A01

2-12-0

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**ON A/C A340-200 A340-300

ABSORBERS AND TIRES ARE AT NOMINAL PRESSURE.HEIGHT DATA GIVEN IS CORRECT WHEN LANDING GEAR SHOCK STRUT

1.69 m(5.54 ft)

NOTE:

APPROXIMATE DIMENSIONS

DISTANCE FROMTHE GROUND

INBOARDENGINE

OUTBOARDENGINE

1.21 m(3.97 ft)

2.99 m(9.81 ft)

2.52 m(8.27 ft)

A B

4.05 m(13.29 ft)

* *

45°

A

*

GROUND LINE

*

* * FWD: 1.72 m (5.64 ft)AFT: 1.61 m (5.28 ft)

FWD: 1.2 m (3.94 ft)AFT: 1.33 m (4.36 ft)

B

F_AC_021200_1_0190101_01_00

Engine and NacelleThrust Reverser Cowls - CFM 56-5C

FIGURE-2-12-0-991-019-A01

2-12-0

Page 6Apr 01/13

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2-12-1 Auxiliary Power Unit

**ON A/C A340-200 A340-300

Auxiliary Power Unit

1. GeneralThe Auxiliary Power Unit (APU) and its related mechanical components are installed at the rear partof the fuselage in the tailcone section. The APU compartment is a fireproof area (identified as theFire Zone).The APU is a pneumatic and shaft-power gas-turbine engine and is used for the ground and in-flightpower supply of the aircraft.

The APU supplies:- mechanical shaft-power to operate a generator- bleed-air to the Main Engine Start (MES) and the Environmental Control System (ECS).

A part of the automatic system, with the pneumatic and the electromechanical controls, operates thestart and the acceleration functions of the APU.An air intake system with a flap-type door is installed in front of the APU compartment. The exhaustgases pass overboard at the end of the fuselage cone.

2. PowerplantThe APU is the Garrett Gas-Turbine Compressor Power-unit (GTCP) 331-350C with a single shaftengine.

The engine is the primary component of the APU, which is of the modular design. The modules of the engine are:- The power section- The load compressor- The accessory drive gearbox with LRU(s).

The power section has a two-stage centrifugal compressor, a reverse-flow annular combustionchamber and a three-stage axial turbine. The power section directly operates the one-stagecentrifugal load-compressor which supplies the bleed-air to the pneumatic system. The inlet guidevanes as part of the load compressor, control the airflow.The power section also operates the gearbox which is attached to the load compressor. The followingLRU’s are mounted on the gearbox :

- the APU generator,- the starter motor,- the oil pump,- the Fuel Control Unit (FCU),- the cooling air fan.The APU has a gearbox-driven oil-cooled AC generator.

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The cooling air and ventilation system of the APU supplies the air for cooling of the APU and theequipment on the APU. It also supplies the air for ventilation of the APU compartment.

3. Control circuitThe Electronic Control Box (ECB), which controls the Fuel Control Unit (FCU) and the Inlet Guide

Vanes (IGV), keeps the APU at a constant speed. The control circuit is used to start the APU, toshut it down, to control it and to prevent internal failure.

4. Controls and IndicationThe primary APU controls and indications are installed in the overhead panel, on the center pedestalpanel and on the forward center panel. External APU panels are also installed on the nose landinggear and on the refuel/defuel panel, to initiate an APU emergency shut-down.

2-12-1

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**ON A/C A340-200 A340-300

FR106A

FR103

FR101

FR95

FR94

FR92

FR91 317AL

315AL

313AL

Z310

A B

A

316AR

F_AC_021201_1_0020101_01_00

Auxiliary Power UnitAccess Doors (Sheet 1 of 2)FIGURE-2-12-1-991-002-A01

2-12-1

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**ON A/C A340-200 A340-300

FIRE EXTINGUISHERBOTTLE

AIR INTAKE DUCT

APU

FIRE WALL

BLEED AIR LINE

OIL COOLER OUTLET

EXHAUST MUFFLER

FIXED DIVERTER

GUTTER

FR90

FR92

FR95

FR106A

FIRE WALL

FR101

B

AIR INTAKE

FORWARD

REAR

F_AC_021201_1_0020102_01_00

Auxiliary Power UnitGeneral Layout (Sheet 2 of 2)FIGURE-2-12-1-991-002-A01

2-12-1

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2-13-0 Levelling, symmetry and Alignment

**ON A/C A340-200 A340-300

Leveling, Symmetry and Alignment

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

2. Precision LevelingFor precise leveling, it is necessary to install sighting rods in the receptacles located under thefuselage (points 12 and 13 for longitudinal leveling) and under the wings (points 2LH and 2RH forlateral leveling) and use a sighting tube. With the aircraft on jacks, adjust the jacks until thereference marks on the sighting rods are aligned in the sighting plane (aircraft level).

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

2-13-0

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**ON A/C A340-200

FR57 FR58RIB12

RIB12

FR38 FR39

13

2 RH

2 LH

12

F_AC_021300_1_0040101_01_00

Location of Leveling PointsFIGURE-2-13-0-991-004-A01

2-13-0

Page 2Apr 01/13

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**ON A/C A340-300

FR38 FR39

RIB12

FR58FR57.4RIB12

132 LH

2 RH

12

F_AC_021300_1_0050101_01_00

Location of Leveling PointsFIGURE-2-13-0-991-005-A01

2-13-0

Page 3Apr 01/13

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2-14-0 Jacking for Maintenance

**ON A/C A340-200 A340-300

Jacking for Maintenance

1. Aircraft Jacking Points for Maintenance

A. General

(1) The A340-200/-300 can be jacked:- At not more than 152 000 kg (335 103 lb)- Within the limits of the permissible wind speed when the aircraft is jacked outside a

closed environment.

B. Primary Jacking Points

(1) The aircraft are provided with three primary jacking points:- One located under the forward fuselage (after FR10A)

- Two located under the wings (one under each wing), at the intersection of RIB10 andthe rear of the spar-datum.

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

C. Auxiliary Jacking Point (Safety Stay)

(1) When the aircraft is on jacks, a safety stay is placed under the fuselage at FR85 to preventtail tipping caused by accidental displacement of the aircraft center of gravity.

(2) The safety point must not be used for lifting the aircraft.(3) One male spherical stay adapter (ground equipment) is used as an intermediary part

between the aircraft safety point and the stay.

2. Jacks and Safety Stay

A. Jack Design

(1) The maximum eligible loads given in the table (Ref. Fig. Jacking Point Location) are themaximum loads applicable on jack fittings.

(2) In fully retracted position (jack stroke at minimum), the height of the jack is such that the jack may be placed beneath the aircraft under the most adverse conditions, namely, tires

deflated and shock absorbers depressurized, with sufficient clearance between the aircraft jacking point and the jack upper end.

(3) The lifting jack stroke enables the aircraft to be jacked up so that the Fuselage Datum line(FDL) may be positioned up to 7.2 m (23.62 ft) from the ground to allow all requiredmaintenance procedures and in particular, the removal/installation of the landing-gearshock absorbers.

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B. Safety StayThe stay stroke enables the aircraft tail to be supported up to the Fuselage Datum Line (FDL)positioned 7.2 m (23.62 ft) from the ground.

2-14-0

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**ON A/C A340-200

SAFETY STAY

WING JACKINGPOINT

C

B’

B

FORWARD FUSELAGEJACKING POINT A

3.58 11.75 0

8.51

−8.51

0

0

27.92

−27.92

0

MAXIMUMLOAD ELIGIBLE

m ft daN

YX

m ft

29.41

29.41

51.54

96.49

96.49

169.09

12 300

80 982

80 982

4 500

FWD JACKINGPOINT

SAFETYSTAY

Y

B’

B

WING JACKINGPOINT

X

NOTE:

SAFETY STAY IS NOT USED FOR JACKING.

CA

WING JACKINGPOINT

F_AC_021400_1_0080101_01_00

Jacking for MaintenanceJacking Points Location

FIGURE-2-14-0-991-008-A01

2-14-0

Page 3Apr 01/13

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**ON A/C A340-300

SAFETY STAY

WING JACKINGPOINT

C

B’

B

FORWARD FUSELAGEJACKING POINT A

3.58

31.55

31.55

55.81

11.75

103.51

103.51

183.1

0

8.51

−8.51

0

0

27.92

−27.92

0

MAXIMUMLOAD ELIGIBLE

m ft

12 300

daN

YX

81 084

81 084

4 500

m ft

FWD JACKINGPOINT B’

B

NOTE:

SAFETY STAY IS NOT USED FOR JACKING.

Y

X

A C

SAFETYSTAY

WING JACKINGPOINT

WING JACKINGPOINT

F_AC_021400_1_0080201_01_00

Jacking for MaintenanceJacking Points Location

FIGURE-2-14-0-991-008-B01

2-14-0

Page 4Apr 01/13

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**ON A/C A340-200 A340-300

Z−2157.8

Z−2136

SPHERICALRADIUS 19 mm (0.75 in)

A

FR10A

FR10AA

FWD

B

ADAPTOR −JACK NOSE

B

F_AC_021400_1_0090101_01_00

Jacking for MaintenanceForward Jacking Point

FIGURE-2-14-0-991-009-A01

2-14-0

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**ON A/C A340-200 A340-300

LOWER SURFACE

EXAMPLE

Z −790.3

Z −700.6


JACKING PADSET−WING

OUTER SKIN

RIB10OUTER SKIN

B

B

A

DATUM INTERSECTIONAT MID REAR SPAR DATUM

RIB10

RIB10

A

A

F_AC_021400_1_0100101_01_00

Jacking for MaintenanceWing Jacking Points

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

2-14-0

Page 6Apr 01/13

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**ON A/C A340-200 A340-300

ADAPT−SUPP, AFT JACK


Z −474.0

Z −440.7

A

FR85

B

B

FWD

FR85

A

F_AC_021400_1_0110101_01_00

Jacking for MaintenanceAuxiliary Jacking Point - Safety Stay

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

2-14-0

Page 7Apr 01/13

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**ON A/C A340-200

L

AIRCRAFT ON WHEELS WITH STANDARD TIRES, MAX. JACKWEIGHT 152 000 kg (335 103 lb)

2.61 m(8.56 ft)

4.46 m(14.63 ft)

5.36 m(17.59 ft)

AIRCRAFT ON WHEELS, SHOCK ABSORBERS DEFLATED ANDFLAT TIRES

2.2 m(7.22 ft)

4.11 m(13.48 ft)

4.77 m(15.65 ft)

AIRCRAFT ON JACKS, FUSELAGE DATUM LINEPARALLEL TO GROUND AT 6.5 m (21.33 ft) FOR LANDINGGEARS EXTENSION/RETRACTION

4.37 m(14.34 ft)

5.8 m(19.03 ft)

6.06 m(19.88 ft)

AIRCRAFT ON JACKS, FUSELAGE DATUM LINEPARALLEL TO GROUND AT 7.2 m (23.62 ft) FOR LANDINGGEARS REMOVAL/INSTALLATION

5.07 m(16.63 ft)

6.5 m(21.33 ft)

6.76 m(22.18 ft)

L M N

AIRCRAFT ON WHEELS WITH STANDARD TIRES,OEW 127 000 kg (279 987 lb)

2.62 m(8.6 ft)

4.51 m(14.8 ft)

5.43 m(17.81 ft)

FUSELAGE

N

DATUM LINE

M

F_AC_021400_1_0120101_01_00

Jacking for MaintenanceJacking Dimensions

FIGURE-2-14-0-991-012-A01

2-14-0

Page 8Apr 01/13

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**ON A/C A340-300

L

AIRCRAFT ON WHEELS WITH STANDARD TIRES, MAX. JACKWEIGHT 152 000 kg (335 103 lb)

2.52 m(8.27 ft)

4.46 m(14.63 ft)

5.38 m(17.65 ft)

AIRCRAFT ON WHEELS, SHOCK ABSORBERS DEFLATED ANDFLAT TIRES

2.2 m(7.22 ft)

4.1 m(13.45 ft)

4.77 m(15.65 ft)

AIRCRAFT ON JACKS, FUSELAGE DATUM LINEPARALLEL TO GROUND AT 6.5 m (21.33 ft) FOR LANDINGGEARS EXTENSION/RETRACTION

4.37 m(14.34 ft)

5.8 m(19.03 ft)

6.06 m(19.88 ft)

AIRCRAFT ON JACKS, FUSELAGE DATUM LINEPARALLEL TO GROUND AT 7.2 m (23.62 ft) FOR LANDINGGEARS REMOVAL/INSTALLATION

5.07 m(16.63 ft)

6.5 m(21.33 ft)

6.76 m(22.18 ft)

L M N

AIRCRAFT ON WHEELS WITH STANDARD TIRES,OEW 131 215 kg (279 279 lb)

2.58 m(8.47 ft)

4.51 m(14.8 ft)

5.39 m(17.68 ft)

FUSELAGE

N

DATUM LINE

M

F_AC_021400_1_0120201_01_00

Jacking for MaintenanceJacking Dimensions

FIGURE-2-14-0-991-012-B01

2-14-0

Page 9Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

80

90

100

110

120

130

140

150

0 6 8 10 12 14 16 18 20

80

90

100

110

120

130

140

150

160

170 40

2520

1510

4520 30 40 50 60 70

5

2 4

160

170

LOAD ON FORWARD FUSELAGE JACKING POINT (kg x 1 000)

L O A D O N W I N G J A C K I N G P O I N T S ( k g x 1 0 0 0 )

A I R C R A F T G R O S S W E I G H T

( k g x 1 0 0 0 )

PERMISSIBLE WIND SPEED (km/h)

AIRCRAFT CG (%RC)

EXAMPLE:

AT 22.8% RC . THE REACTION AT THE WING JACKING POINTS IS 137 000 kg

(68 500 kg PER SIDE) AND THE REACTION AT THE FORWARD FUSELAGE JACKING POINT

IS 8 000 kg . IF THE AIRCRAFT MUST BE LIFTED OUTSIDE, THE WIND SPEED MUST NOT

ASSUME AIRCRAFT WITH A GROSS WEIGHT OF 145 000 kg AND CENTER OF GRAVITYA

B

C

DBE IN EXCESS OF 50 km/h.

A

D

C

TIP UPSECURITYMARGIN

B

3035

F_AC_021400_1_0130101_01_00

Jacking for MaintenanceLoad at the Aircraft Jacking Points

FIGURE-2-14-0-991-013-A01

2-14-0

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**ON A/C A340-300

0 6 8 10 12 14 16 18 20

80

90

100

110

120

130

140

150

160

170 4035

2520

1510

45 20 30 40 50 60 70

50

2 4

80

90

100

110

120

130

140

150

160

170

EXAMPLE:

AT 22.8% RC . THE REACTION AT THE WING JACKING POINTS IS 136 000 kg

(68 000 kg PER SIDE) AND THE REACTION AT THE FORWARD FUSELAGE JACKING POINT

IS 9 000 kg . IF THE AIRCRAFT MUST BE LIFTED OUTSIDE, THE WIND SPEED MUST NOT

ASSUME AIRCRAFT WITH A GROSS WEIGHT OF 145 000 kg AND CENTER OF GRAVITYA

B

C

DBE IN EXCESS OF 60 km/h.

TIP UPSECURITYMARGIN

LOAD ON FORWARD FUSELAGE JACKING POINT (kg x 1 000)

L O A D O N W I N G J A C K I N G P O I N T S ( k g x 1 0 0 0 )


( k g x 1 0 0 0 )

PERMISSIBLE WIND SPEED (km/h)

30

A

B

D

C

AIRCRAFT CG (%RC)

F_AC_021400_1_0130201_01_00

Jacking for MaintenanceLoad at the Aircraft Jacking Points

FIGURE-2-14-0-991-013-B01

2-14-0

Page 11Apr 01/13

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2-14-1 Jacking for Wheel Change

**ON A/C A340-200 A340-300

Jacking for Wheel Change

1. GeneralTo replace either the wheel or brake unit assemblies on any of the landing gears, it is necessary to liftthe landing gear with a jack.The landing gear can be lifted by a pillar jack or with a cantilever jack.The possible damage conditions than can be found on the landing-gear wheel units are shown inFigures ”MLG Jacking Point Heights”, ”NLG Jacking Point Heights” and ”CLG Jacking PointHeights”.

NOTE : You can lift the aircraft at the Maximum Take-Off Weight (MTOW).

2. Main Landing Gear (MLG)

To lift the MLG bogie with jacks, a dome shaped pad (PN MS33559 TYPE IV) is installed below theFWD and AFT ends of each bogie beam. Each pair of wheels and brake units can be replaced on theend of the bogie that is lifted.Both FWD and AFT ends of the bogie beam can be lifted together, but the bogie beam must be keptlevel during the lift to prevent damage.

The MLG has a pitch trimmer installed. If an MLG has all four tires deflated or shredded, replace thewheel assemblies in this sequence:- Replace the wheel assemblies on the AFT axle,- Replace the wheel assemblies on the FWD axle.

If the FWD axle is lifted first the pitch trimmer contacts the outstop. Further jacking will cause thewhole bogie to be lifted.Important dimensions on heights of the MLG when lifted are shown in Figure ”MLG Jacking PointHeights”.The maximum height of the bogie beam when lifted must not exceed 650 mm (25.6 in).The reaction loads at each jack position are shown in Figure ”MLG Jacking Point Loads”.

NOTE : The load at each jacking position is the load required to give 25.4 mm (1 in) clearancebetween the ground and the tire.

3. Nose Landing Gear (NLG)

To lift the NLG axle with a jack, a dome shaped pad (PN MS33559 Type II) is installed between thewheels.Important dimensions on heights of the NLG when lifted are shown in Figure ”NLG Jacking PointHeights”.The reaction loads at the jack position are shown in Figure ”NLG Jacking Point Loads”.


2-14-1

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4. Center Landing Gear (CLG)To lift the CLG with a jack, a dome shaped pad (PN MS33559 TYPE IV) is installed between thewheels.Important dimensions on heights of the CLG when lifted are shown in Figure ”CLG Jacking Point

Heights”.The reaction loads at the jack position are shown in Figure ”CLG Jacking Point Loads”.


2-14-1

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**ON A/C A340-200 A340-300

AFT WHEELS JACKED UPFWD WHEELS INSTALLED AND INFLATED

FWD WHEELS JACKED UPAFT WHEELS INSTALLED AND INFLATED

JACKING POINT570 mm

(22.44 in)

MAX DIAMETER1 443.7 mm(56.84 in)

25.4 mm(1 in)

NORMAL ATTITUDE

JACKING POINT376 mm(14.8 in)

25.4 mm

(1 in)

FWD

FWD

FWD


JACKING POINT570 mm

(22.44 in)

F_AC_021401_1_0050102_01_00

Jacking for Wheel ChangeMLG Jacking Point Heights (Sheet 1 of 3)

FIGURE-2-14-1-991-005-A01

2-14-1

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**ON A/C A340-200 A340-300

FWD AXLE

BOTH TIRES SHREDDED OR DEFLATED

AFT AXLE

BOTH TIRES SHREDDED OR DEFLATED

FWD AND AFT AXLEBOTH TIRES SHREDDED OR DEFLATED

JACKING POINT376 mm(14.8 in)JACKING POINT

145.9 mm(5.74 in)

JACKING POINT376 mm(14.8 in) JACKING POINT

145.5 mm(5.73 in)



FWD

FWD

FWD

F_AC_021401_1_0050103_01_00


FIGURE-2-14-1-991-005-A01

2-14-1

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

AFT AXLEBOTH TIRES SHREDDED OR DEFLATED AND WHEEL RIMS WORN

JACKING POINT376 mm(14.8 in) JACKING POINT

118.8 mm(4.68 in)

FWD

FWD AND AFT AXLESTIRES SHREDDED OR DEFLATED AND WHEEL RIMS WORN



FWD

JACKING POINT376 mm(14.8 in)JACKING POINT

118.8 mm(4.68 in)

FWD

FWD AXLEBOTH TIRES SHREDDED OR DEFLATED AND WHEEL RIMS WORN

F_AC_021401_1_0050104_01_00


FIGURE-2-14-1-991-005-A01

2-14-1

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

1 FLAT TIRE110 mm

(4.33 in)180 mm MAX

(7.09 in)

(1 in)25.4 mm

400 mm

(15.75 in)

170 mm(6.69 in) FWD

F_AC_021401_1_0060101_01_00

Jacking for Wheel ChangeJacking of the NLG (Sheet 1 of 2)

FIGURE-2-14-1-991-006-A01

2-14-1

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**ON A/C A340-200 A340-300

1 083 mm(42.64 in)

270 mm

(10.63 in)

NORMAL ATTITUDE

TWO TIRES DEFLATED OR SHREDDED

HEIGHT OF JACKING POINT TO GROUNDTO CHANGE/REPLACE THE WHEEL ASSEMBLY

297.5 mm(11.71 in)

JACKING POINT290 mm

(11.42 in)

JACKING POINT148.5 mm(5.85 in)

JACKING POINT400 mm

(15.75 in)

25.4 mm(1 in)

FWD

FWD

FWD

F_AC_021401_1_0060102_01_00

Jacking for Wheel ChangeNLG Jacking Point Heights (Sheet 2 of 2)

FIGURE-2-14-1-991-006-A01

2-14-1

Page 7Apr 01/13

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**ON A/C A340-200 A340-300

640 mm(25.19 in)

235 mm(9.25 in) FWD

300 mm

(11.81 in)

94° 15’

F_AC_021401_1_0070101_01_00

Jacking for Wheel ChangeJacking of the CLG (Sheet 1 of 2)

FIGURE-2-14-1-991-007-A01

2-14-1

Page 8Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

TWO TIRES DEFLATED OR SHREDDED

HEIGHT OF JACKING POINT TO GROUNDTO CHANGE/REPLACE THE WHEEL ASSEMBLY

NORMAL ATTITUDE

343 mm(13.5 in)


363 mm

(14.29 in)

FWD

JACKING POINT236.4 mm(9.31 in)FWD

FWD

1 443.7 mm

(56.84 in)


25.4 mm(1 in)

F_AC_021401_1_0070102_01_00

Jacking for Wheel ChangeCLG Jacking Point Heights (Sheet 2 of 2)

FIGURE-2-14-1-991-007-A01

2-14-1

Page 9Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

AIRCRAFT GROSS WEIGHT

280 320 360 400 440 480 520

120 140 160 180 200 220 24020

50

70

90

120

260

560

(x 1 000 kg)

(x 1 000 lb)

L O A D A T J A C K I N G P O I N T

( x 1 0 0 0 k g )


( x 1 0 0 0 l b )

280

600

30

40

60

80

100

110

260

250

240

230

220

210

200

190

180

170

160

150

140

130

120

110

100

90

80

70

60

50

100

240

35% MAC25% MAC18% MAC

42% MACCG POSITION

F_AC_021401_1_0080101_01_00

Jacking for Wheel ChangeMLG Jacking Point Loads

FIGURE-2-14-1-991-008-A01

2-14-1

Page 10Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200


41% MACCG POSITION


280 320 360 400 440 480 520

120 140 160 180 200 220 24040

50

60

70

80

90

100

110

120

260

560

(x 1 000 kg)

(x 1 000 lb)


( x 1 0 0 0 k g )


( x 1 0 0 0 l b )

110

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

280

600

100

90

F_AC_021401_1_0080201_01_00

Jacking for Wheel ChangeMLG Jacking Point Loads

FIGURE-2-14-1-991-008-B01

2-14-1

Page 11Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

120 140 160 180 200 220 240 260


280 320 360 400 440 480 520

2

22

30

560

(x 1 000 kg)

(x 1 000 lb)


( x 1 0 0 0 k g )


( x 1 0 0 0 l b )

280

600

6

26

100

240

55

45

35

25

15

65

4

8

20

24

18

16

14

12

10

28

10

5

20

30

40

50

60


18% MACCG POSITION

F_AC_021401_1_0090101_01_00

Jacking for Wheel ChangeNLG Jacking Point Loads

FIGURE-2-14-1-991-009-A01

2-14-1

Page 12Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200


280 320 360 400 440 480 520

120 140 160 180 200 220 2400

5

10

15

20

25

30

35

40

260

560

(x 1 000 kg)

(x 1 000 lb)


( x 1 0 0 0 k g )


( x 1 0 0 0 l b )

10

20

30

40

50

60

70

80

280

600

0


20% MACCG POSITION

F_AC_021401_1_0090201_01_00

Jacking for Wheel ChangeNLG Jacking Point Loads

FIGURE-2-14-1-991-009-B01

2-14-1

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7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

280 320 360 400 440 480 520 560 600240


120 140 160 180 200 220 2400

6

10

14

260

(x 1 000 kg)

(x 1 000 lb)


( x 1 0 0 0 k g )


( x 1 0 0 0 l b )

280

2

4

8

12

1000

25

20

15

10

5

30


42% MACCG POSITION

F_AC_021401_1_0100101_01_00

Jacking for Wheel ChangeCLG Jacking Point Loads

FIGURE-2-14-1-991-010-A01

2-14-1

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**ON A/C A340-200


120 140 160 180 200 220 2400

5

15

20

25

30

260

(x 1 000 kg)

(x 1 000 lb)


( x 1 0 0 0 k g )


( x 1 0 0 0 l b )

280

10

35

40

45

10

20

30

40

50

60

70

80

90

0


41% MACCG POSITION

280 320 360 400 440 480 520 560 600

F_AC_021401_1_0100201_01_00

Jacking for Wheel ChangeCLG Jacking Point Loads

FIGURE-2-14-1-991-010-B01

2-14-1

Page 15Apr 01/13

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2-14-2 Support of Aircraft

**ON A/C A340-200 A340-300

Support of Aircraft

1. Support of AircraftWhen it is necessary to support the aircraft in order to relieve the loads on the structure for theaccomplishment of modifications or major work, it is advisable to provide adapters under the wingsand the fuselage for an alternative means of lifting.

The aircraft must not be lifted or supported by the wings or fuselage alone. It is important to supportthe aircraft fuselage and wings at the same time to prevent structural damage.

A. Shoring CradlesShoring cradles are used when it is necessary to stress-jack the aircraft to carry out maintenanceand repair work. These are used to oppose the deflections of the wings and reduce the stresses

to an acceptable level at the area of maintenance and repair.

The shoring cradles, each with two adjustable pads, 152.4 mm (6 in) square, are positioned atfour locations under each wing.

The adjustable pads are faced with thin rubber and are in contact with the wing profile at thedatum intersections of the ribs and the front and rear spars (F/S and R/S).

2-14-2

Page 1Apr 01/13

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**ON A/C A340-200

(SAFETY STAY)FR85

FR80

FR72

FR26

FR17

FR11

RIB6 RIB6

NOTE:THE SHORING CRADLE MUST BE INSTALLED AT THE EXACT LOCATION OF THE FRAME.

FR58

RIB16

RIB21

RIB31

FR53.2

RIB31

RIB21

RIB16

F_AC_021402_1_0020101_01_00

Support of AircraftLocation of Shoring Cradles (Sheet 1 of 2)

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

2-14-2

Page 2Apr 01/13

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**ON A/C A340-200

FR7

FR17

FR20

FR26.1

FR32

FR39.1 FR53.8 FR59 FR76

A

LH SHOWN

(9.02 ft)

2.75 m

(15.09 ft)

4.6 m

(6.89 ft)

2.1 m

EXAMPLE

A

B

RH SYMMETRICAL

B B

F_AC_021402_1_0020102_01_00

Support of AircraftLocation of Auxiliary Jacking Points (Sheet 2 of 2)

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

2-14-2

Page 3Apr 01/13

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**ON A/C A340-300

FR80

FR72

FR26

FR17

FR11

(SAFETY STAY)FR85

NOTE:THE SHORING CRADLE MUST BE INSTALLED AT THE EXACT LOCATION OF THE FRAME.

RIB6 RIB6

RIB31

RIB21

RIB16

FR58

FR53.2

RIB16

RIB21

RIB31

F_AC_021402_1_0020201_01_00

Support of AircraftLocation of Shoring Cradles (Sheet 1 of 2)

FIGURE-2-14-2-991-002-B01

2-14-2

Page 4Apr 01/13

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**ON A/C A340-300

FR7

FR17 FR20

FR26.1

FR59 FR76FR39.1FR36 FR53.8

A

LH SHOWN

(9.02 ft)

2.75 m

(15.09 ft)

4.6 m

(6.89 ft)

2.1 m

EXAMPLE

A

B

RH SYMMETRICAL

B B

F_AC_021402_1_0020202_01_00

Support of AircraftLocation of Auxiliary Jacking Points (Sheet 2 of 2)

FIGURE-2-14-2-991-002-B01

2-14-2

Page 5Apr 01/13

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AIRCRAFT PERFORMANCE


**ON A/C A340-200 A340-300General 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) forCFM56-5C 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 11.1

4000 1219 44.7 7.16000 1829 37.6 3.18000 2438 30.5 -0.8

3-1-0

Page 1Apr 01/13

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3-2-0 Payload / Range

**ON A/C A340-200 A340-300

Payload / Range

1. Payload / Range

3-2-0

Page 1Apr 01/13

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**ON A/C A340-200 A340-300

ISA Conditions

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

3-2-1

Page 1Apr 01/13

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**ON A/C A340-300

0

10

20

30

40

50

60

70

80

90

100

110

120

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 90008500

160007000 8000 9000 10000 11000 12000 13000 14000 15000

270

280

290

300

310

320

330

340

350

360

370

380

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

NOTE: MAX TAKE−OFF WEIGHT

ZFW(1000 lb)

PAYLOAD(1000 lb)

RANGE(Nm)

RANGE(Km)

MAX STRUCTURAL PAYLOAD

MAX PASSENGER PAYLOAD

CRUISE CONDITIONSISA 39000 ft M = 0.82

F_AC_030201_1_0110101_01_00

PAYLOAD / RANGECFM56-5C2 engine

FIGURE-3-2-1-991-011-A01

3-2-1

Page 2Apr 01/13

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**ON A/C A340-200

0

10

20

30

40

50

60

70

80

90

100

110

120

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 90008500

160007000 8000 9000 10000 11000 12000 13000 14000 15000

270

280

290

300

310

320

330

340

350

360

370

380



ZFW(1000 lb)

PAYLOAD(1000 lb)

RANGE(Nm)

RANGE(Km)



F_AC_030201_1_0120101_01_00



FIGURE-3-2-1-991-012-A01

3-2-1

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

0

10

20

30

40

50

60

70

80

90

100

110

120

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 90008500

160007000 8000 9000 10000 11000 12000 13000 14000 15000

270

280

290

300

310

320

330

340

350

360

370

380



ZFW(1000 lb)

PAYLOAD(1000 lb)

RANGE(Nm)

RANGE(Km)



F_AC_030201_1_0130101_01_00



FIGURE-3-2-1-991-013-A01

3-2-1

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

0

10

20

30

40

50

60

70

80

90

100

110

120

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 90008500

160007000 8000 9000 10000 11000 12000 13000 14000 15000

270

280

290

300

310

320

330

340

350

360

370

380



ZFW(1000 lb)

PAYLOAD(1000 lb)

RANGE(Nm)

RANGE(Km)



F_AC_030201_1_0140101_01_00



FIGURE-3-2-1-991-014-A01

3-2-1

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

0

10

20

30

40

50

60

70

80

90

100

110

120

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 90008500

160007000 8000 9000 10000 11000 12000 13000 14000 15000

270

280

290

300

310

320

330

340

350

360

370

380

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


ZFW(1000 lb)

PAYLOAD(1000 lb)

RANGE(Nm)

RANGE(Km)

BASIC AIRCRAFT257t MTOW

NOMINAL PERFORMANCE LEVEL



F_AC_030201_1_0150101_01_00



FIGURE-3-2-1-991-015-A01

3-2-1

Page 6Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

0

10

20

30

40

50

60

70

80

90

100

110

120

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 90008500

160007000 8000 9000 10000 11000 12000 13000 14000 15000

270

280

290

300

310

320

330

340

350

360

370

380



ZFW(1000 lb)

PAYLOAD(1000 lb)

RANGE(Nm)

RANGE(Km)



F_AC_030201_1_0160101_01_00



FIGURE-3-2-1-991-016-A01

3-2-1

Page 7Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

0

10

20

30

40

50

60

70

80

90

100

110

120

4000 4500 5000 5500 6000 6500 7000 7500 8000 90008500

160007000 8000 9000 10000 11000 12000 13000 14000 15000

270

280

290

300

310

320

330

340

350

360

370

380

NOTE: THESE CURVES ARE GIVEN FOR INFORMATION ONLY

THE APPROVED VALUES ARE STATED IN THE "OPERATINGMANUALS" SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.


ZFW(1000 lb)

PAYLOAD(1000 lb)

RANGE(Nm)

RANGE(Km)

BASIC AIRCRAFT271t AND 275t MTOW

NOMINAL PERFORMANCE LEVEL

275t

271t

F_AC_030201_1_0170101_01_00





FIGURE-3-2-1-991-017-A01

3-2-1

Page 8Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



3-3-0 FAR / JAR Takeoff Weight Limitation

**ON A/C A340-200 A340-300

FAR / JAR Takeoff Weight Limitation

1. FAR / JAR Takeoff Weight Limitation

3-3-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013




**ON A/C A340-200 A340-300

FAR / JAR Takeoff Weight Limitation

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

3-3-1

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

TAKE−OFF WEIGHT1000 lb1000 kg

RUNWAY LENGHT(1000 ft)

RUNWAY LENGHT(1000 m)

NOTE:

320

340

360

380

400

420

440

460

480

500

520

540

560

THES CURVES ARE GIVEN FOR INFORMATION

ONLY THE APPROVED VALUES ARE STATEDIN THE "OPERATING MANUALS" SPECIFIC TOTHE AIRLINE OPERATING THE AIRCRAFT

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

FLAPS 2

580

600

620

640

145

165

185

205

225

245

265

285

FLAPS 3 FLAPS 1

0

F_AC_030301_1_0040101_01_00

A I R P O R T P R E S S U

R E A L T I T U D E ( 1 0 0 0 f t )

2

4

6

8

BRAKE ENERGY

V.M.C

LIMITATION

FAR / JAR Takeoff Weight LimitationISA Conditions -- CFM56-5C2 engine

FIGURE-3-3-1-991-004-A01

3-3-1

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

TAKE−OFF WEIGHT1000 lb1000 kg

320

340

360

380

400

420

440

460

480

500

520

540

560

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

0

FLAPS 2

580

600

620

640

145

165

185

205

225

245

265

285

FLAPS 3 FLAPS 1

NOTE: THESE CURVES ARE GIVEN FOR INFORMATIONONLY THE APPROVED VALUES ARE STATEDIN THE "OPERATING MANUALS" SPECIFIC TOTHE AIRLINE OPERATING THE AIRCRAFT

RUNWAY LENGTH(1000 ft)

RUNWAY LENGTH(1000 m)

2

F_AC_030301_1_0050101_01_00

A I R P O R T P R E S S U R E A L T I T U D E ( 1 0 0 0 f t )

4

6

8

BRAKE ENERGY

V.M.C

LIMITATION


FIGURE-3-3-1-991-005-A01

3-3-1

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

TAKE−OFF WEIGHT

1000 lb1000 kg

NOTE:

320

340

360

380

400

420

440

460

480

500

520

540

560

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

FLAPS 2

580

600

620

145

165

185

205

225

245

265

FLAPS 3 FLAPS 1

640

660

285

680305



THESE CURVES ARE GIVEN FOR INFORMATIONONLY THE APPROVED VALUES ARE STATEDIN THE "OPERATING MANUALS" SPECIFIC TOTHE AIRLINE OPERATING THE AIRCRAFT

8

0

4

A I R P O R T

P R E S S U R E A L T I T U D E ( 1 0 0 0 f t )

6

2

BRAKE ENERGY

V.M.C

LIMITATION

F_AC_030301_1_0060101_01_00


FIGURE-3-3-1-991-006-A01

3-3-1

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

1000 lb1000 kg

NOTE:

320

340

360

380

400

420

440

460

480

500

520

540

560

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

FLAPS 2

580

600

620

145

165

185

205

225

245

265

FLAPS 3 FLAPS 1

640

660

285

680305




F_AC_030301_1_0070101_01_00

TAKE−OFF WEIGHT

0

2

4

6

8 A I R P O R T


BRAKE ENERGY

V.M.C

LIMITATION


FIGURE-3-3-1-991-007-A01

3-3-1

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

1000 lb1000 kg

NOTE:

320

340

360

380

400

420

440

460

480

500

520

540

560

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

FLAPS 2

580

600

620

145

165

185

205

225

245

265

FLAPS 3 FLAPS 1

640

660

285

680305




F_AC_030301_1_0080101_01_00

TAKE−OFF WEIGHT

A I R P O R T P R E S S U R E A L T I T U D E ( 1 0 0 0 f t )0

2

4

6

8

BRAKE ENERGY

V.M.C

LIMITATION


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

3-3-1

Page 6Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

1000 lb1000 kg

NOTE:

320

340

360

380

400

420

440

460

480

500

520

540

560

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

FLAPS 2

580

600

620

145

165

185

205

225

245

265

FLAPS 3 FLAPS 1

640

660

285

680305




F_AC_030301_1_0090101_01_00

TAKE−OFF WEIGHT

8

6

4

2

0

A I R P O R T


BRAKE ENERGY

V.M.C

LIMITATION


FIGURE-3-3-1-991-009-A01

3-3-1

Page 7Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



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

**ON A/C A340-200 A340-300

ISA +15˚C (ISA +27˚F) Conditions

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

3-3-2

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

1000 lb1000 kg

RUNWAY LENGHT(1000 ft)

RUNWAY LENGHT(1000 m)

NOTE:

320

340

360

380

400

420

440

460

480

500

520

540

560

THES CURVES ARE GIVEN FOR INFORMATIONONLY THE APPROVED VALUES ARE STATEDIN THE "OPERATING MANUALS" SPECIFIC TOTHE AIRLINE OPERATING THE AIRCRAFT

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

FLAPS 2

580

600

620

640

145

165

185

205

225

245

265

285

FLAPS 3 FLAPS 1

F_AC_030302_1_0040101_01_00

TAKE−OFF WEIGHT

A I R P O R T P R

E S S U R E A L T I T U D E ( 1 0 0 0 f t )0

2

4

6

8

BRAKE ENERGY

V.M.C

LIMITATION

FAR / JAR Takeoff Weight LimitationISA +15˚C (ISA +27˚F) Conditions -- CFM56-5C2 engine

FIGURE-3-3-2-991-004-A01

3-3-2

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

1000 lb1000 kg

NOTE:

320

340

360

380

400

420

440

460

480

500

520

540

560

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

FLAPS 2

580

600

620

640

145

165

185

205

225

245

265

285

FLAPS 3 FLAPS 1




F_AC_030302_1_0050101_01_00

TAKE−OFF WEIGHT

0

2

4

6

8

A I R P O R T P R

E S S U R E A L T I T U D E ( 1 0 0 0 f t )

BRAKE ENERGY

V.M.C

LIMITATION


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

3-3-2

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

1000 lb1000 kg

NOTE:

320

340

360

380

400

420

440

460

480

500

520

540

560

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

FLAPS 2

580

600

620

145

165

185

205

225

245

265

FLAPS 3 FLAPS 1

640

660

285

680305




F_AC_030302_1_0060101_01_00

TAKE−OFF WEIGHT

0

2

4

6

8 A I R P O R T


BRAKE ENERGY

V.M.C

LIMITATION


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

3-3-2

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

NOTE:

320

340

360

380

400

420

440

460

480

500

520

540

560

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

FLAPS 2

580

600

620

145

165

185

205

225

245

265

FLAPS 3 FLAPS 1

640

660

285

680305




F_AC_030302_1_0070101_01_00

1000 lb1000 kg

TAKE−OFF WEIGHT

A I R P O R T


0

2

4

6

8

BRAKE ENERGY

V.M.C

LIMITATION


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

3-3-2

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

NOTE:

320

340

360

380

400

420

440

460

480

500

520

540

560

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

FLAPS 2

580

600

620

145

165

185

205

225

245

265

FLAPS 3 FLAPS 1

640

660

285

680305




F_AC_030302_1_0080101_01_00

1000 lb1000 kg

TAKE−OFF WEIGHT

0

2

4

6

8

A I R P O R T


BRAKE ENERGY

V.M.C

LIMITATION


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

3-3-2

Page 6Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

NOTE:

320

340

360

380

400

420

440

460

480

500

520

540

560

4 6 8 10 12 14 16

1 1.5 2 2.5 3 3.5 4 4.5 5

FLAPS 2

580

600

620

145

165

185

205

225

245

265

FLAPS 3 FLAPS 1

640

660

285

680305




F_AC_030302_1_0090101_01_00

1000 lb1000 kg

TAKE−OFF WEIGHT

A I R P O R T

P R E S S U R E A L T I T U D E ( 1 0 0 0 f t )0

2

4

6

8

BRAKE ENERGY

V.M.C

LIMITATION


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

3-3-2

Page 7Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



3-4-0 FAR / JAR Landing Field Length

**ON A/C A340-200 A340-300

Landing Field Length

1. Landing Field Length

3-4-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



3-4-1 ISA Conditions All series engines

**ON A/C A340-200 A340-300

ISA Conditions All series engine

1. This section gives the landing field length.

3-4-1

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

3 4 5 6 7 8

1 1 . 5 2

2 . 5

N O T E : T H E S

E C U R V E S A R E G I V E N F O R I N F O R M A T

I O N O N L Y

T H E A P P R O V E D V A L U E S A R E S T A T E D I N T H

E " O P E R A T I N G

M A N U A L S " S P E C I F I C T O T H E A I R L I N E O P E R

A T I N G

T H E A I R C R A F T .

G R O S S W E I G H T

( 1 0

0 0 k g )


( 1 0 0 0 l b )

( 1 0 0 0

m )

( 1 0 0 0 f t )

2

4

6

8

1 0

S E A L E V E L

1 5 0

2 0 0

2 5 0

3 0 0

3 5 0

4 0 0

4 5 0

5 0 0

7 5

1 0 0

1 2 5

1 5 0

1 7 5

2 0 0

2 5 0

5 0

2 2 5

I S A C O N D I T I O N S

A I R F I E L D E L E V A T I O N

( 1 0 0 0 f t )

F . A . R L A N D I N G L E N G H T

F_AC_030401_1_0040101_01_00

FAR / JAR Landing Field LengthISA Conditions -- CFM56-5C2 engine

FIGURE-3-4-1-991-004-A01

3-4-1

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

3 4 5 6 7 8

1 1 . 5 2 2 . 5

N O T E :

T H E S E

C U R V E S A R E G I V E N F O R I N F O R M A T I O N O N L Y

T H E A

P P R O V E D V A L U E S A R E S T A T E D I N T H E

" O P E R A T I N G

M A N U

A L S " S P E C I F I C T O T H E A I R L I N E O P E R A

T I N G

T H E A

I R C R A F T .

G R O S

S W E I G H T

( 1 0 0 0 k g )

G R O S

S W E I G H T

( 1 0

0 0 l b )

2

4

6

8

1 0

S E A L E V E L

1 5 0

2 0 0

2 5 0

3 0 0

3 5 0

4 0 0

4 5 0

5 0 0

7 5

1 0 0

1 2 5

1 5 0

1 7 5

2 0 0

2 5 0

5 0

2 2 5

A I R F I E L D E L E V A T

I O N

( 1 0 0 0 f t )

F . A . R

L A N D I N G L E N G H T

F_AC_030401_1_0050101_01_00 ( 1 0 0 0

m )

( 1 0 0 0 f t )



FIGURE-3-4-1-991-005-A01

3-4-1

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

3 4 5 6 7 8

1 1 . 5 2 2 . 5

N O T E : T H E S


I O N O N L Y




A T I N G


G R O S

S W E I G H T

( 1 0 0 0 k g )

G R O S

S W E I G H T

( 1 0

0 0 l b )

2

4

6

8

1 0

S E A L E

V E L

1 5 0

2 0 0

2 5 0

3 0 0

3 5 0

4 0 0

4 5 0

5 0 0

7 5

1 0 0

1 2 5

1 5 0

1 7 5

2 0 0

2 5 0

5 0

2 2 5

A I R F I E L D E L

E V A T I O N

( 1 0 0 0

f t )


F_AC_030401_1_0060101_01_00


( 1 0 0 0

m )

( 1 0 0 0 f t )


FIGURE-3-4-1-991-006-A01

3-4-1

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

3 4 5 6 7 8

1 1 . 5 2 2 . 5

N O T E : T H E S

E C U R V E S A R E G I V E N F O R I N F O R M A T I O N O N L Y

T H E A

P P R O V E D V A L U E S A R E S T A T E D I N T H E " O P E R A T I N G

M A N U

A L S " S P E C I F I C T O T H E A I R L I N E O P E R A

T I N G

T H E A

I R C R A F T .

G R O S S

W E I G H T

( 1 0 0

0 k g )


( 1 0 0 0 l b )

2

4

6

8

1 0

S E A L E

V E L

1 5 0

2 0 0

2 5 0

3 0 0

3 5 0

4 0 0

4 5 0

5 0 0

7 5

1 0 0

1 2 5

1 5 0

1 7 5

2 0 0

2 5 0

5 0

2 2 5


( 1 0 0 0

f t )

F . A . R

L A N D I N G L E N G H T

F_AC_030401_1_0070101_01_00 ( 1 0 0 0 m )

( 1 0 0 0 f t )



FIGURE-3-4-1-991-007-A01

3-4-1

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

3 4 5 6 7 8

1 1 . 5 2 2 . 5

N O T E : T H E S


I O N O N L Y




A T I N G


G R O S

S W E I G H T

( 1 0 0 0 k g )

G R O S

S W E I G H T

( 1 0 0 0 l b )

2

4

6

8

1 0

S E A L E V E L

1 5 0

2 0 0

2 5 0

3 0 0

3 5 0

4 0 0

4 5 0

5 0 0

7 5

1 0 0

1 2 5

1 5 0

1 7 5

2 0 0

2 5 0

5 0

2 2 5


( 1 0 0 0 f t )


F_AC_030401_1_0080101_01_00


( 1 0 0 0

m )

( 1 0 0 0 f t )


FIGURE-3-4-1-991-008-A01

3-4-1

Page 6Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

3 4 5 6 7 8

1

1 . 5 2

2 . 5

N O T E : T H E

S E C U R V E S A R E G I V E N F O R I N F O R M A T I O N O N L Y

T H E

A P P R O V E D V A L U E S A R E S T A T E D I N T H E " O P E R A T I N G

M A N

U A L S " S P E C I F I C T O T H E A I R L I N E O P E R

A T I N G

T H E

A I R C R A F T .


( 1 0 0 0 k g )

G R O S

S W E I G H T

( 1 0

0 0 l b )

2

4

6

8

1 0

S E A L E V E L

1 5 0

2 0 0

2 5 0

3 0 0

3 5 0

4 0 0

4 5 0

5 0 0

7 5

1 0 0

1 2 5

1 5 0

1 7 5

2 0 0

2 5 0

5 0

2 2 5

A I R F I E L D E L

E V A T I O N

( 1 0 0 0

f t )


F_AC_030401_1_0090101_01_00 ( 1 0 0 0 m )

( 1 0 0 0 f t )



FIGURE-3-4-1-991-009-A01

3-4-1

Page 7Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



3-5-0 Final Approach Speed

**ON A/C A340-200 A340-300

Final Approach Speed

**ON A/C A340-200

1. Final Approach Speed

A. This section gives the final approach speed. This is the indicated airspeed at threshold in thelanding configuration, at the certificated maximum flap setting and maximum landing weight, instandard atmospheric conditions. The approach speed is used to classify the aircraft into anAircraft Approach Category, a grouping of aircraft based on the indicated airspeed at threshold.

B. The final approach speed is 136 kt at a Maximum Landing Weight (MLW) of 185 000 kg (407855 lb) and classifies the aircraft into the Aircraft Approach Category C.

NOTE : This value is given for information only.

**ON A/C A340-300

2. Final Approach Speed

A. This section gives the final approach speed. This is the indicated airspeed at threshold in thelanding configuration, at the certificated maximum flap setting and maximum landing weight, instandard atmospheric conditions. The approach speed is used to classify the aircraft into anAircraft Approach Category, a grouping of aircraft based on the indicated airspeed at threshold.

B. The final approach speed is 138 kt at a Maximum Landing Weight (MLW) of 192 000 kg (423287 lb) and classifies the aircraft into the Aircraft Approach Category C.

NOTE : This value is given for information only.

3-5-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



GROUND MANEUVERING



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.

4-1-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



4-2-0 Turning Radii

**ON A/C A340-200 A340-300

Turning Radii

1. This section gives the turning radii.

4-2-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

62°60°

55°

R6

R4

R5

R3

NOTE:

FOR TURNING RADII VALUES, REFER TO SHEET 2.

R2

R1

F_AC_040200_1_0050101_01_02

Turning Radii(Sheet 1)

FIGURE-4-2-0-991-005-A01

4-2-0

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

19.320

TYPE OFTURN

2 67.9223

A340−300 TURNING RADII

mft

78.6258

77.2253

R4WING

102.9338

R5NOSE

79.1260

R6TAIL

87.9288

R1RMLG

R2LMLG

R3NLG

24.125252.3

172

62.9

206

62.6

205

87.3

286

65.1

214

73.5

241

28.930241.5

136

52.2

171

52.9

174

76.7

252

56.0

184

64.0

210

33.735233.7

111

44.4

146

46.2

152

68.9

226

49.8

163

57.3

188

38.440227.7

91

38.3

126

41.3

135

62.9

206

45.3

149

52.4

172

43.045222.8

75

33.5

110

37.6

123

58.1

191

42.0

138

48.6

159

47.550218.8

62

29.5

97

34.8

114

54.2

178

39.6

130

45.7

150

51.9552 15.551

26.286

32.6107

51.0167

37.7124

43.3142

56.060212.8

42

23.4

77

30.9

101

48.2

158

36.3

119

41.5

136

59.665210.5

34

21.2

70

29.7

97

46.0

151

35.3

116

40.1

132

62.47028.9

29

19.5

64

28.9

95

44.4

146

34.7

114

39.1

128

51.750115.7

52

26.4

87

32.7

107

51.1

168

37.8

124

43.4

142

56.555112.4

41

23.1

76

30.7

101

47.9

157

36.2

119

41.3

135

61.26019.531

20.266

29.296

45.1148

34.9115

39.5

130

65.96517.0

23

17.7

58

28.0

92

42.6

140

34.0

112

38.0

125

70.47014.7

15

15.3

50

27.1

89

40.3

132

33.3

109

36.8

121

m

ft

m

ft

m

ft

m

ft

m

ft

m

ft

mft

m

ft

m

ft

m

ft

m

ft

m

ft

m

ft

m

ft

m

ft

STEERING ANGLE (deg)EFFECTIVESTEERING

ANGLE (deg)

NOTE:

ABOVE 50°, AIRLINES MAY USE TYPE 1 OR TYPE 2 TURNS DEPENDING ON THE SITUATION.TYPE 1 TURNS USE:ASYMMETRIC THRUST DURING THE WHOLE TURN; ANDDIFFERENTIAL BRAKING TO INITIATE THE TURN ONLY.TYPE 2 TURNS USE:

SYMMETRIC THRUST DURING THE WHOLE TURN; AND NO DIFFERENTIAL BRAKING AT ALL.IT IS POSSIBLE TO GET LOWER VALUES THAN THOSE FROM TYPE 1 BY APPLYINGDIFFERENTIAL BRAKING DURING THE WHOLE TURN.

63.27228.4

28

19.1

63

28.7

94

44.0

144

34.5

113

38.8

127

m

ft

72.27213.8

12

14.5

48

26.8

88

39.5

130

33.1

109

36.3

119

m

ft

F_AC_040200_1_0100101_01_01


FIGURE-4-2-0-991-010-A01

4-2-0

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

19.120

TYPE OFTURN

2 62.6205

A340−200 TURNING RADII

mft

73.3240

71.4234

R4WING

97.6320

R5NOSE

73.4241

R6TAIL

82.2270

R1RMLG

R2LMLG

R3NLG

23.925248.1

158

58.8

193

57.9

190

83.2

273

60.4

198

68.8

226

28.630238.2

125

48.9

160

49.0

161

73.4

241

52.1

171

60.1

197

33.335231.0

102

41.7

137

42.8

140

66.3

218

46.4

152

53.9

177

37.940225.5

84

36.2

119

38.3

126

60.8

199

42.3

139

49.4

162

42.445221.1

69

31.7

104

34.9

115

56.4

185

39.3

129

45.9

151

46.850217.5

57

28.1

92

32.3

106

52.9

174

37.0

121

43.2

142

50.9552 14.548

25.283

30.399

49.9164

35.4116

41.1135

54.860212.0

39

22.7

75

28.8

94

47.5

156

34.1

112

39.4

129

58.065210.1

33

20.8

68

27.7

91

45.7

150

33.2

109

38.2

125

60.37028.9

29

19.6

64

27.0

89

44.4

146

32.7

107

37.4

123

51.350114.2

47

24.9

82

30.1

99

49.7

163

35.2

115

40.9

134

56.155111.3

37

22.0

72

28.3

93

46.8

154

33.8

111

38.9

128

60.76018.729

19.363

26.988

44.2145

32.6107

37.3

122

65.36516.3

21

17.0

56

25.8

85

42.0

138

31.8

104

35.9

118

69.77014.2

14

14.9

49

25.0

82

39.9

131

31.1

102

34.7

114

m

ft

m

ft

m

ft

m

ft

m

ft

m

ft

mft

m

ft

m

ft

m

ft

m

ft

m

ft

m

ft

m

ft

m

ft


ANGLE (deg)

NOTE:

ABOVE 50°, AIRLINES MAY USE TYPE 1 OR TYPE 2 TURNS DEPENDING ON THE SITUATION.TYPE 1 TURNS USE:ASYMMETRIC THRUST DURING THE WHOLE TURN; ANDDIFFERENTIAL BRAKING TO INITIATE THE TURN ONLY.TYPE 2 TURNS USE:

SYMMETRIC THRUST DURING THE WHOLE TURN; AND NO DIFFERENTIAL BRAKING AT ALL.IT IS POSSIBLE TO GET LOWER VALUES THAN THOSE FROM TYPE 1 BY APPLYINGDIFFERENTIAL BRAKING DURING THE WHOLE TURN.

60.87228.6

28

19.3

63

26.9

88

44.2

145

32.6

107

37.2

122

m

ft

71.67213.4

11

14.1

46

24.7

81

39.1

128

30.9

101

34.3

113

m

ft

F_AC_040200_1_0110101_01_01


FIGURE-4-2-0-991-011-A01

4-2-0

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



4-3-0 Minimum Turning Radii

**ON A/C A340-200 A340-300

Minimum Turning Radii

1. This section gives the minimum turning radii.

4-3-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

NOTE:

TYPE 1 TURNS USE:ASYMMETRIC THRUST DURING THE WHOLETURN; AND DIFFERENTIAL BRAKING TOINITIATE THE TURN ONLY.TYPE 2 TURNS USE:SYMMETRIC THRUST DURING THE WHOLETURN; AND NO DIFFERENTIAL BRAKING AT ALL.

A(MINIMUM TURNING WIDTH)

65.965 (MAX)

TYPE OFTURN

111.4

37

A340−300 MINIMUM TURNING RADII

m

ft

46.0

151

28.0

92

R4WING

42.6

140

R5NOSE

34.0

112

R6TAIL

38.0

125

R3NLG

59.665 (MAX)214.9

49

51.2

168

29.7

97

46.0

151

35.3

116

40.1

132

m

ft


ANGLE (deg)

NOTE:

IT IS POSSIBLE TO GET LOWER VALUES THAN THOSE FROM TYPE 1BY APPLYING DIFFERENTIAL BRAKING DURING THE WHOLE TURN.

25.4

83

25.4

83

AX Y

Y

R6

R4

OUTSIDE FACEOF TIRE

72 (MAX)

72 (MAX)

2

1

63.2

72.2m

ft

m

ft

8.2

27

41.7

137

26.8

88

39.5

130

33.1

109

36.3

119

12.8

42

48.1

158

28.7

94

44.0

144

34.5

113

38.8

127

25.4

83

25.4

83

R5

R3

X

F_AC_040300_1_0030101_01_02

Minimum Turning RadiiFIGURE-4-3-0-991-003-A01

4-3-0

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

NOTE:

TYPE 1 TURNS USE:ASYMMETRIC THRUST DURING THE WHOLETURN; AND DIFFERENTIAL BRAKING TOINITIATE THE TURN ONLY.TYPE 2 TURNS USE:SYMMETRIC THRUST DURING THE WHOLETURN; AND NO DIFFERENTIAL BRAKING AT ALL.

A(MINIMUM TURNING WIDTH)

65.365 (MAX)

TYPE OFTURN

110.7

35

A340−200 MINIMUM TURNING RADII

m

ft

43.2

142

25.8

85

R4WING

42.0

138

R5NOSE

31.8

104

R6TAIL

35.9

118

R3NLG

58.065 (MAX)214.5

48

48.8

160

27.7

91

45.7

150

33.2

109

38.2

125

m

ft


ANGLE (deg)

NOTE:


23.2

76

23.2

76

AX Y

72 (MAX)

72 (MAX)

2

1

60.8

71.6m

ft

m

ft

7.7

25

39.1

128

24.7

81

39.1

128

30.9

101

34.3

113

13.0

43

46.5

153

26.9

88

44.2

145

32.6

107

37.2

122

23.2

76

23.2

76

R6

R4

R5

R3

Y

OUTSIDE FACEOF TIRE

X

F_AC_040300_1_0040101_01_02

Minimum Turning RadiiFIGURE-4-3-0-991-004-A01

4-3-0

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



4-4-0 Visibility from Cockpit in Static Position

**ON A/C A340-200 A340-300

Visibility from Cockpit in Static Position

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

4-4-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

NOT TO BE USED FORLANDING APPROACH VISIBILITY

115°

CAPTAIN FIELD OF VIEW

135°

115°

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

TO THE SIDE.

VISUAL ANGLES IN HORIZONTALPLANE THROUGH PILOTEYE POSITION.

FIRST OFFICERFIELD OF VIEW

0.53 m(1.74 ft)

62°

42°

30°36°

30°

VISUAL ANGLES IN PLANEPERPENDICULAR TOLONGITUDINAL AXIS.

62°

42°

WITH HEAD MOVED125 mm (5 in) OUTBOARD

NOTE:

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

ZONE THAT CANNOT BE SEEN

135°

36°

25°

20°

13.75 m

(45.11 ft)

6.67 m

(21.88 ft)

VISUAL ANGLES IN VERTICALPLANE THROUGH PILOTEYE POSITION.

DIMENSIONS ARE APPROXIMATE

2.4 m(7.87 ft)

F_AC_040400_1_0040101_01_01

Visibility from Cockpit in Static PositionFIGURE-4-4-0-991-004-A01

4-4-0

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

C A P

T A I N

W I N D S H I E L D

C A

P T A I N S L I D I N G

W I N D O W

C A P T A I N

F I X E D W I N D O W

W I N G T I P

V I S I B L E

C A P T A I N ’ S F I E L D O F V I E W S H O W N , T H R O U G H C A P T A I N W I N D O W S

O N L Y .

F I R S T O F F I C E R F I E L D O F V I E

W

S Y M M E T R I C A L .

E X A M P L E : W H E N C A P T A I N T U R N S H I S H E A D B Y 8 5 ° L E F T , V I S I B I L I T

Y

W I L L B E 4 3 ° U P A N D 3 0 ° D O W N T H R O U G H T H E S L I D I N G

W I N D O W

F R A M E .

A 3 3 0 / A 3 4 0

5 0 °

4 0 °

3 0 °

2 0 °

1 0 °

0 °

1 0 °

2 0 °

3 0 °

4 0 °

5 0 °

6 0 °

7 0 °

8 0 °

9 0 °

1 0 0 °

1 1 0 °

1 2 0 °

1 3 0 °

1 4 0 °

3 0 °

2 0 °

1 0 °

0 °

1 0 °

2 0 °

3 0 °

4 0 °

4 3 °

P I L O T E Y E P O S I T I O N

( C A P T A I N P O S I T I O N )

F_AC_040400_1_0080101_01_00

Binocular Visibility Through Windows from Captain Eye PositionFIGURE-4-4-0-991-008-A01

4-4-0

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



4-5-0 Runway and Taxiway Turn Paths

**ON A/C A340-200 A340-300

Runway and Taxiway Turn Paths

1. Runway and Taxiway Turn Paths.

4-5-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013




**ON A/C A340-200 A340-300

135˚ Turn - Runway to Taxiway

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

4-5-1

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

F A A L E A D − I N F I L L E T

L = 7 5 m ( 2 5 0 f t )

(15 ft)

APPROX 4.5 m

APPROX 11.7 m

(39 ft)

FILLET R = 25.5 m(85 ft)

TURN R = 45 m(150 ft)

45 m

(150 ft)

23 m

(75 ft)

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

NLG PATH

MLG PATH

F_AC_040501_1_0030101_01_01

135˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

FIGURE-4-5-1-991-003-A01

4-5-1

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

APPROX 2 m

(7 ft)

ADDITIONAL FILLET TO MEET

4.5 m (15 ft) EDGE CLEARANCE


TURN R = 45 m(150 ft)

45 m

(150 ft)


L = 7 5 m ( 2 5 0 f t )

23 m(75 ft)

F_AC_040501_1_0080101_01_00

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

NLG PATH

MLG PATH

135˚ Turn - Runway to TaxiwayCockpit Over Centerline Method

FIGURE-4-5-1-991-008-A01

4-5-1

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

45 m

(150 ft)

APPROX 10.8 m

(35 ft)

FILLET R = 25.5 m

(85 ft)

TURN R = 45 m

(150 ft)

APPROX 6.4 m

(21 ft)

23 m(75 ft)

F A A L E A D − I N

F I L L E T

L = 7 5 m ( 2 5 0 f t )

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

NLG PATH

MLG PATH

F_AC_040501_1_0090101_01_00

135˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

FIGURE-4-5-1-991-009-A01

4-5-1

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

APPROX 3.4 m

(11 ft)



FILLET R = 25.5 m

(85 ft)

TURN R = 45 m

(150 ft)


L = 7 5 m ( 2 5 0 f t )

45 m150 ft

23 m

(75 ft)

F_AC_040501_1_0100101_01_00

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

NLG PATH

MLG PATH


FIGURE-4-5-1-991-010-A01

4-5-1

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013




**ON A/C A340-200 A340-300

90˚ Turn - Runway to Taxiway

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

4-5-2

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

FAA LEAD−IN FILLETL = 75 m (250 ft)

(41 ft)

APPROX 12.3 m

(44 ft)

APPROX 13.2 m


TURN R = 45 m

(150 ft)

45 m

(150 ft)F_AC_040502_1_0030101_01_01

23 m(75 ft)

NLG PATH

MLG PATH

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

F_AC_040502_1_0030101_01_01

90˚ Turn - Runway to TaxiwayJudgement Oversteering Method

FIGURE-4-5-2-991-003-A01

4-5-2

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

(18 ft)

APPROX 5.4 m


FAA LEAD−IN FILLET

L = 75 m (250 ft)

45 m(150 ft)

TURN R = 45 m

(150 ft)

23 m(75 ft)

NLG PATH

MLG PATH

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

F_AC_040502_1_0100101_01_00


FIGURE-4-5-2-991-010-A01

4-5-2

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

45 m

(150 ft)


(44 ft)

APPROX 13.3 m

FAA LEAD−

IN FILLETL = 75 m (250 ft)

(42 ft)

APPROX 12.7 m

TURN R = 45 m

(150 ft)

23 m

(75 ft)

NLG PATH

MLG PATH

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

F_AC_040502_1_0110101_01_00

90˚ Turn - Runway to TaxiwayJudgement Oversteering Method

FIGURE-4-5-2-991-011-A01

4-5-2

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200


(27 ft)

APPROX 8 m


45 m(150 ft)

TURN R = 45 m(150 ft)

23 m

(75 ft)

NLG PATH

MLG PATH

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

F_AC_040502_1_0120101_01_00


FIGURE-4-5-2-991-012-A01

4-5-2

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



4-5-3 180˚ Turn on a Runway

**ON A/C A340-200 A340-300

180˚ Turn on a Runway

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

4-5-3

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

NLG PATH

MLG PATH

NOSE TIP PATH

WING TIP PATH

TAIL TIP PATH

NOTE:

TYPE 1 VALUES FOR MAX STEERING ANGLE = 72°.


58.5 m

(192 ft)

49.5 m

(162 ft)

4.6 m(15 ft)

20.3 m

(67 ft)

14.7 m

(48 ft)

0.9 m

(3 ft)

4.6 m

(15 ft)

R4 = 39.5 m(130 ft)

R6 = 36.3 m(119 ft)

RUNWAY CENTERLINE

R3 = 26.8 m

(88 ft)

R5 = 33.1 m(109 ft)

F_AC_040503_1_0050101_01_02

180˚ Turn on a RunwayFIGURE-4-5-3-991-005-A01

4-5-3

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

NLG PATH

MLG PATH

NOSE TIP PATH

WING TIP PATH

TAIL TIP PATH

NOTE:



58.6 m

(192 ft)

49.6 m

(162 ft)

4.6 m

20.2 m

(66 ft)

14.6 m

(48 ft)

0.9 m

(3 ft)

4.6 m

(15 ft)

R4 = 39.5 m(130 ft)

R6 = 36.3 m(119 ft) R3 = 26.8 m

(88 ft)

R5 = 33.1 m(109 ft)

RUNWAY CENTERLINE

(15 ft)

F_AC_040503_1_0060101_01_02


4-5-3

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

NLG PATH

MLG PATH

NOSE TIP PATH

WING TIP PATH

TAIL TIP PATH

NLG PATH

MLG PATH

NOSE TIP PATH

WING TIP PATH

TAIL TIP PATH

NOTE:



R5 = 30.9 m(101 ft)

4.6 m(15 ft)

20.4 m

(67 ft)

13.4 m(44 ft)

0.9 m

(3 ft)

4.6 m

(15 ft)

R3 = 24.7 m(81 ft)

R6 = 34.3 m(113 ft)

R4 = 39.1 m(128 ft)

55 m

(180 ft)

45.8 m

(150 ft)

RUNWAY CENTERLINE

F_AC_040503_1_0070101_01_02


4-5-3

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

NLG PATH

MLG PATH

NOSE TIP PATH

WING TIP PATH

TAIL TIP PATH

NLG PATH

MLG PATH

NOSE TIP PATH

WING TIP PATH

TAIL TIP PATH

NOTE:



R5 = 30.9 m(101 ft)

4.6 m(15 ft)

20.3 m

(67 ft)

13.4 m(44 ft)

0.9 m

(3 ft)

4.6 m

(15 ft)

R4 = 39.1 m(128 ft)

55 m

(180 ft)

45.8 m

(150 ft)

RUNWAY CENTERLINE

R3 = 24.7 m(81 ft)

R6 = 34.3 m(113 ft)

F_AC_040503_1_0080101_01_02


4-5-3

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013




**ON A/C A340-200 A340-300

135˚ Turn - Taxiway to Taxiway

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

4-5-4

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

TURN R = 45 m(150 ft)


APPROX 12.9 m

(43 ft)

APPROX 4.5 m(15 ft)


L = 7 5 m ( 2 5 0 f t )

TAXIWAY CENTERLINE

TAXIWAY CENTERLINE

NLG PATH

MLG PATH

(75 ft)23 m

23 m(75 ft)

F_AC_040504_1_0090101_01_00

135˚ Turn - Taxiway to TaxiwayJudgemental Oversteering Method

FIGURE-4-5-4-991-009-A01

4-5-4

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300



L = 7 5 m ( 2 5 0 f t )

APPROX 3.5 m(12 ft)

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

TAXIWAY CENTERLINE

TAXIWAY CENTERLINE

23 m

(75 ft)

(75 ft)

23 m

TURN R = 45 m

(150 ft)

NLG PATH

MLG PATH

F_AC_040504_1_0100101_01_00

135˚ Turn - Taxiway to TaxiwayCockpit Over Centerline Method

FIGURE-4-5-4-991-010-A01

4-5-4

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**ON A/C A340-200

APPROX 13 m

(43 ft)


TURN R = 45 m

(150 ft)

TAXIWAY CENTERLINE

APPROX 5.1 m(17 ft)


L = 7 5 m ( 2 5 0 f t )

(75 ft)23 m

TAXIWAY CENTERLINE

NLG PATH

MLG PATH

23 m

(75 ft)

F_AC_040504_1_0110101_01_00

135˚ Turn - Taxiway to TaxiwayJudgemental Oversteering Method

FIGURE-4-5-4-991-011-A01

4-5-4

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**ON A/C A340-200

FILLET R = 25.5 m

(85 ft)

APPROX 5.2 m

(17 ft)

TAXIWAY CENTERLINE


L = 7 5 m ( 2 5 0 f t )

23 m

(75 ft)

TAXIWAY CENTERLINE

(75 ft)

23 mNLG PATH

MLG PATH

TURN R = 45 m(150 ft)

F_AC_040504_1_0120101_01_00


FIGURE-4-5-4-991-012-A01

4-5-4

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**ON A/C A340-200 A340-300

90˚ Turn - Taxiway to Taxiway

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

4-5-5

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**ON A/C A340-300

(40 ft)APPROX 12 m


TAXIWAY CENTERLINE(43 ft)

APPROX 12.9 m

FILLET R = 25.5 m

(85 ft)

TURN R = 45 m

(150 ft)

TAXIWAY CENTERLINE

23 m

(75 ft)

(75 ft)23 m NLG PATH

MLG PATH

F_AC_040505_1_0050101_01_01

90˚ Turn - Taxiway to TaxiwayJudgement Oversteering Method

FIGURE-4-5-5-991-005-A01

4-5-5

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**ON A/C A340-300


(14 ft)APPROX 4.1 m


TURN R = 45 m

(150 ft)



TAXIWAY CENTERLINE

23 m(75 ft)

TAXIWAY CENTERLINE

(75 ft)23 m

NLG PATH

MLG PATH

F_AC_040505_1_0130101_01_00


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

4-5-5

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**ON A/C A340-200

(44 ft)

APPROX 13.1 m

FILLET R = 25.5 m

(85 ft)

TURN R = 45 m(150 ft)

(41 ft)APPROX 12.4 m


TAXIWAY CENTERLINE

(75 ft)

23 m NLG PATH

MLG PATH

23 m

(75 ft)

TAXIWAY CENTERLINE

F_AC_040505_1_0060101_01_02

90˚ Turn - Taxiway to TaxiwayJudgement Oversteering Method

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

4-5-5

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**ON A/C A340-200


(24 ft)APPROX 7.1 m

FILLET R = 25.5 m

(85 ft)

TURN R = 45 m(150 ft)

TAXIWAY CENTERLINE

(75 ft)23 m

NLG PATH

MLG PATH

TAXIWAY CENTERLINE

23 m

(75 ft)

F_AC_040505_1_0140101_01_00


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

4-5-5

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4-6-0 Runway Holding Bay (Apron)

**ON A/C A340-200 A340-300

Runway Holding Bay (Apron)

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

4-6-0

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**ON A/C A340-200 A340-300

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

RUNWAY

CENTERLINE

TAXIWAY

CENTERLINE

PLANNED OPERATING PROCEDURES.

190 m

(625 ft)

97.3 m(319 ft)

90 m

(300 ft)

23 m

(75 ft)

F_AC_040600_1_0030101_01_02

Runway Holding Bay (Apron)FIGURE-4-6-0-991-003-A01

4-6-0

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4-7-0 Aircraft Parking

**ON A/C A340-200 A340-300

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

4-7-0

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**ON A/C A340-300

73.85

PARKING45° ENTRY PUSH OUT

PARKINGSTRAIGHT ENTRY PUSH BACK


67.23

5 6 . 5 3

6 8 . 2 6

8 2 . 5 7

96.76

F_AC_040700_1_0070101_01_01

Airplane ParkingSteering Geometry

FIGURE-4-7-0-991-007-A01

4-7-0

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**ON A/C A340-300

PARKINGPARALLEL IN POWER OUT

PARKING45° ENTRY POWER OUT

7 3 . 8 5

95.89

7 2 . 0 2

100.77

F_AC_040700_1_0080101_01_01


FIGURE-4-7-0-991-008-A01

4-7-0

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**ON A/C A340-300

0

20

40

60

80

100

120

140

160

180

200

220

240

260

280

300

10

20

30

40

50

60

70

80

90

100

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

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

DISTANCE ALONG TERMINAL (m)

DISTANCE ALONG TERMINAL (ft)

(m)

DISTANCE OUTFROM TERMINAL

STRAIGHT ENTRY PUSH BACK

45° ENTRY PUSH OUT

PARALLEL IN POWER OUT

90° ENTRY PUSH OUT

45° ENTRY POWER OUT

(ft)

F_AC_040700_1_0090101_01_00

Airplane ParkingMinimum Parking Space Requirements

FIGURE-4-7-0-991-009-A01

4-7-0

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**ON A/C A340-200

65.72 73.85

6 6 . 1 3

5 5 . 0 2


PARKINGSTRAIGHT ENTRY PUSH BACK

93.76

8 0 . 4 3

PARKING

90° ENTRY PUSH OUT

F_AC_040700_1_0100101_01_01


FIGURE-4-7-0-991-010-A01

4-7-0

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**ON A/C A340-200

PARKINGPARALLEL IN POWER OUT

PARKING45° ENTRY POWER OUT

7 3 . 8 5

7 0 . 8 7

95.89

96.86

F_AC_040700_1_0110101_01_01


FIGURE-4-7-0-991-011-A01

4-7-0

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**ON A/C A340-200

0

20

40

60

80

100

120

140

160

180

200

220

240

260

280

300

10

20

30

40

50

60

70

80

90

100

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

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

DISTANCE ALONG TERMINAL (m)

DISTANCE ALONG TERMINAL (ft)

(m)

DISTANCE OUTFROM TERMINAL

0

45° ENTRY PUSH OUT

STRAIGHT ENTRY PUSH BACK

PARALLEL IN POWER OUT

90° ENTRY PUSH OUT

45° ENTRY POWER OUT

F_AC_040700_1_0120101_01_00

(ft)

Airplane ParkingMinimum Parking Space Requirements

FIGURE-4-7-0-991-012-A01

4-7-0

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TERMINAL SERVICING

5-0-0 TERMINAL SERVICING

**ON A/C A340-200 A340-300TERMINAL 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 and

freighter 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-upusing 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.

5-0-0

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5-1-0 Aircraft Servicing Arrangements

**ON A/C A340-200 A340-300

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.

5-1-0

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5-1-1 Symbols Used on Servicing Diagrams

**ON A/C A340-200 A340-300

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

BULK BULK TRAINCAT CATERING TRUCK

CB CONVEYOR BELTCLEAN CLEANING TRUCK

FUEL FUEL HYDRANT DISPENSER or TANKERGPU GROUND POWER UNIT

LD CL LOWER DECK CARGO LOADERLV LAVATORY VEHICLE

PBB PASSENGER BOARDING BRIDGEPS PASSENGER STAIRS

TOW TOW TRACTORULD ULD TRAINWV POTABLE WATER VEHICLE

5-1-1

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5-1-2 Typical Ramp Layout - Open Apron

**ON A/C A340-200 A340-300

Typical Ramp Layout - Open Apron

1. This section gives the typical servicing arrangements on the open apron, for the passenger version of the aircraft.The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m (24.61 ft) fromthe aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).

5-1-2

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**ON A/C A340-300

P S CAT

PS

P S CA T

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

AS

G P U

LD CL

LD CL

AC

ULD

FUELFUEL

LV

CB

ULD

BULKWV

TOW

STAND SAFETY LINE

CAT

F_AC_050102_1_0030101_01_02

Typical Ramp LayoutOpen Apron

FIGURE-5-1-2-991-003-A01

5-1-2

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**ON A/C A340-200

P S

PS

CA T

CAT

P S CAT

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

TOW

AS

G P U

LD CL

LD CL

AC

ULD

ULD

BULKCBWV

LV

FUELFUEL

STAND SAFETY LINE

F_AC_050102_1_0040101_01_02

Typical Ramp LayoutOpen Apron

FIGURE-5-1-2-991-004-A01

5-1-2

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5-1-3 Typical Ramp Layout - Gate

**ON A/C A340-200 A340-300

Typical Ramp Layout - Gate

1. This section gives the typical servicing arrangements in the gate area for the passenger version of theaircraft, with two Passenger Boarding Bridges.The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m (24.61 ft) fromthe aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).

5-1-3

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**ON A/C A340-300

C LEA N

CA T

CAT

CAT

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

TOW

AS

G P U

LD CL

LD CL

AC

ULD

ULD

BULKCB

LV

FUELFUEL

PBB

PBB

WV

STAND SAFETY LINE

F_AC_050103_1_0020101_01_02

Typical Ramp LayoutGate

FIGURE-5-1-3-991-002-A01

5-1-3

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**ON A/C A340-200

C LEA N

WV

CAT

CAT

CA T

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

AS

G P U

LD CL

LD CL

AC

ULD

FUELFUEL

LV

CB

ULD

BULK

TOW

PBB

PBB

STAND SAFETY LINE

F_AC_050103_1_0030101_01_02

Typical Ramp LayoutGate

FIGURE-5-1-3-991-003-A01

5-1-3

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5-2-0 Terminal Operations - Full Servicing

**ON A/C A340-300

Terminal Operations - Full Servicing Turn Round Time

1. This section provides typical turn-round time charts showing the typical times for ramp activitiesduring aircraft turn-round.Actual times may vary due to each operator’s specific practice and operating conditions.

2. Assumptions for full servicing turn-round time chart

A. PASSENGER HANDLING270 pax (10 F/C + 28 B/C + 232 Y/C)All passengers deboard and board the aircraft2 Passenger Boarding Bridges (PBB) used at doors L1 and L2Equipment positioning/removal + opening/closing door = 3 minNo Passenger with Reduced Mobility (PRM) on board

Deboarding:- 135 pax at door L1 (10 F/C + 28 B/C + 97 Y/C)- 135 pax at door L2 (135 Y/C)- Deboarding rate = 25 pax/min per door- Priority deboarding for premium passengers

Boarding:- 135 pax at door L1 (10 F/C + 28 B/C + 97 Y/C)- 135 pax at door L2 (135 Y/C)

- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min

B. CARGO2 cargo loaders + 1 belt loaderEquipment positioning/removal + opening/closing door = 2.5 min

Cargo exchange:- 8 LD3 + 2 pallets in AFT cargo compartment- 12 LD3 + 2 pallets in FWD cargo compartment- 1 000 kg (2 205 lb) in bulk cargo compartment

LD3 off-loading/loading times:- Off-loading = 1.2 min/LD3- Loading = 1.4 min/LD3

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

5-2-0

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- Loading = 2.8 min/pallet

Bulk off-loading/loading times:- Off-loading = 9.2 min/t

- Loading = 10.5 min/tC. REFUELLING

Block-fuel quantity for nominal range through 2 nozzles127 000 l (33 550 US gal) at 50 psi (3.45 bar)Dispenser positioning/removal = 3 min

D. CLEANINGPerformed in available time

E. CATERING3 catering trucks for servicing galleys at doors R1, R2 and R4Equipment positioning + door opening = 5 min

Equipment removal + door closing = 3 minFull Size Trolley Equivalent (FSTE) to unload and load: 48 FSTE- 10 FSTE at door R1- 13 FSTE at door R2- 25 FSTE at door R4Time for trolley exchange = 1.5 min per FSTE

F. GROUND HANDLING/SERVICINGStart of operations:- Bridges: t0 = 0- Others: t0 + 1 min

Vehicle positioning/removal = 2 min (except for fuel and catering trucks)Ground Power Unit (GPU): up to 2 × 90 kVAAir conditioning: two hosesPotable water servicing: 100% uplift, 700 l (185 US gal) at 60 l/min (15.85 US gal/min)Toilet servicing: draining + rinsing

5-2-0

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**ON A/C A340-300

GSE POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH

TRT: 62 min

100 20 30 40 50 60 70

AT L1DEBOARDING/BOARDING

HEADCOUNTING

CATERING AT R2

CLEANING

CARGO FWD CC

BULK

REFUELLING

POTABLE WATER SERVICING

TOILET SERVICING

DEBOARDING/BOARDINGAT L2

CATERING AT R4

CARGO AFT CC

CATERING AT R1

AVAILABLE TIME

F_AC_050200_1_0040101_01_00

Full Servicing Turn Round Time ChartFIGURE-5-2-0-991-004-A01

5-2-0

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**ON A/C A340-200

Terminal Operations - Full Servicing Turn Round Time

1. This section provides typical turn-round time charts showing the typical times for ramp activities

during aircraft turn-round.Actual times may vary due to each operator’s specific practice and operating conditions.

2. Assumptions for full servicing turn-round time chart

A. PASSENGER HANDLING231 pax (10 F/C + 42 B/C + 179 Y/C)All passengers deboard and board the aircraft2 Passenger Boarding Bridges (PBB) used at doors L1 and L2Equipment positioning/removal + opening/closing door = 3 minNo Passenger with Reduced Mobility (PRM) on board

Deboarding:- 116 pax at door L1 (10 F/C + 42 B/C + 64 Y/C)- 115 pax at door L2 (115 Y/C)- Deboarding rate = 25 pax/min per door- Priority deboarding for premium passengers

Boarding:- 116 pax at door L1 (10 F/C + 42 B/C + 64 Y/C)- 115 pax at door L2 (115 Y/C)- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min

B. CARGO2 cargo loaders + 1 belt loaderEquipment positioning/removal + opening/closing door = 2.5 min

Cargo exchange:- 6 LD3 + 2 pallets in AFT cargo compartment- 8 LD3 + 2 pallets in FWD cargo compartment- 1 000 kg (2 205 lb) in bulk cargo compartment

LD3 off-loading/loading times:

- Off-loading = 1.2 min/LD3- Loading = 1.4 min/LD3

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

5-2-0

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Bulk off-loading/loading times:- Off-loading = 9.2 min/t- Loading = 10.5 min/t

C. REFUELLING

Block-fuel quantity for nominal range through 4 nozzles127 000 l (33 550 US gal) at 50 psi (3.45 bar)Dispenser positioning/removal = 3 min


E. CATERING3 catering trucks for servicing galleys at doors R1, R2 and R4Equipment positioning + door opening = 5 minEquipment removal + door closing = 3 minFull Size Trolley Equivalent (FSTE) to unload and load: 36 FSTE

- 7 FSTE at door R1- 9 FSTE at door R2- 20 FSTE at door R4Time for trolley exchange = 1.5 min per FSTE


Vehicle positioning/removal = 2 min (except for fuel and catering trucks)

Ground Power Unit (GPU): up to 2 × 90 kVAAir conditioning: two hosesPotable water servicing: 100% uplift, 700 l (185 US gal) at 60 l/min (15.85 US gal/min)Toilet servicing: draining + rinsing

5-2-0

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**ON A/C A340-200


ACTIVITY

CRITICAL PATH

TRT: 52 min

100 20 30 40 50 60 70


HEADCOUNTING

CATERING AT R2

CLEANING

CARGO FWD CC

BULK

REFUELLING


TOILET SERVICING

DEBOARDING/BOARDINGAT L2

CATERING AT R4

CARGO AFT CC

CATERING AT R1

AVAILABLE TIME

F_AC_050200_1_0050101_01_00

Full Servicing Turn Round Time ChartFIGURE-5-2-0-991-005-A01

5-2-0

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5-3-0 Terminal Operations - Transit

**ON A/C A340-300

Terminal Operations - Minimum Servicing Turn-Round Time

1. This section provides typical turn-round time chart showing the typical times for ramp activitiesduring aircraft turn-round.Actual times may vary due to each operator’s specific practice and operating conditions.

2. Assumptions for minimum servicing turn-round time chart

A. PASSENGER HANDLING270 pax (10 F/C + 38 B/C + 222 Y/C)50% of passengers deboard and board the aircraft1 Passenger Boarding Bridge (PBB) used at door L1Equipment positioning/removal + opening/closing door = 3 minNo Passenger with Reduced Mobility (PRM) on board

Deboarding:- 135 pax at door L1- Deboarding rate = 25 pax/min per door

Boarding:- 135 pax at door L1- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min

B. CARGO

1 cargo loader + 1 belt loaderEquipment positioning/removal + opening/closing door = 2.5 min

Cargo exchange:- 4 LD3 in AFT cargo compartment- 500 kg (1 102 lb) in bulk cargo compartment


Bulk off-loading/loading times:- Off-loading = 9.2 min/t- Loading = 10.5 min/t

C. REFUELLINGRefuelling through 2 nozzles30% of max capacity at 50 psi (3.45 bar)

5-3-0

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Dispenser positioning/removal = 3 min


E. CATERING1 catering truck for servicing galleys as requiredEquipment positioning + door opening = 5 minEquipment removal + door closing = 3 minPerformed in available timeTime for trolley exchange = 1.5 min per FSTE


Vehicle positioning/removal = 2 min (except for fuel and catering trucks)Ground Power Unit (GPU): up to 2 × 90 kVAAir conditioning: two hosesNo potable water servicingNo toilet servicing

5-3-0

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**ON A/C A340-300

TRT: 33 min

50 10 15 20 25 30 35


HEADCOUNTING

CLEANING

CARGO FWD CC

BULK

REFUELLING


TOILET SERVICING

CATERING

CARGO AFT CC

40

AVAILABLE TIME


ACTIVITY

CRITICAL PATH

F_AC_050300_1_0050101_01_00

Minimum Servicing Turn-Round TimeFIGURE-5-3-0-991-005-A01

5-3-0

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**ON A/C A340-200

Terminal Operations - Minimum Servicing Turn-Round Time

1. This section provides typical turn-round time chart showing the typical times for ramp activities

during aircraft turn-round.Actual times may vary due to each operator’s specific practice and operating conditions.

2. Assumptions for minimum servicing turn-round time chart

A. PASSENGER HANDLING231 pax (10 F/C + 42 B/C + 179 Y/C)50% of passengers deboard and board the aircraft1 Passenger Boarding Bridge (PBB) used at door L1Equipment positioning/removal + opening/closing door = 3 minNo Passenger with Reduced Mobility (PRM) on board

Deboarding:- 116 pax at door L1- Deboarding rate = 25 pax/min per door

Boarding:- 116 pax at door L1- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min

B. CARGO1 cargo loader + 1 belt loaderEquipment positioning/removal + opening/closing door = 2.5 min

Cargo exchange:- 4 LD3 in AFT cargo compartment- 500 kg (1 102 lb) in bulk cargo compartment


Bulk off-loading/loading times:

- Off-loading = 9.2 min/t- Loading = 10.5 min/t

C. REFUELLINGRefuelling through 2 nozzles30% of max capacity at 50 psi (3.45 bar)Dispenser positioning/removal = 3 min

5-3-0

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E. CATERING1 catering truck for servicing galleys as required

Equipment positioning + door opening = 5 minEquipment removal + door closing = 3 minPerformed in available timeTime for trolley exchange = 1.5 min per FSTE


Vehicle positioning/removal = 2 min (except for fuel and catering trucks)

Ground Power Unit (GPU): up to 2 × 90 kVAAir conditioning: two hosesNo potable water servicingNo toilet servicing

5-3-0

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**ON A/C A340-200

TRT: 31 min

50 10 15 20 25 30 35


HEADCOUNTING

CLEANING

CARGO FWD CC

BULK

REFUELLING


TOILET SERVICING

CATERING

CARGO AFT CC

40

AVAILABLE TIME


ACTIVITY

CRITICAL PATH

F_AC_050300_1_0060101_01_00

Minimum Servicing Turn-Round TimeFIGURE-5-3-0-991-006-A01

5-3-0

Page 6Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



5-4-1 Ground Service Connections Layout

**ON A/C A340-200 A340-300

Ground Service Connections Layout

1. This section gives the ground service connections layout.

5-4-1

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

1 17 2 3 7 6 7 6 11 3 15 1614

1

317

2

4 5

17

17 12 1115

16

67

8

76

179

917

67

8

67

10 3 1413

1 − OXYGEN SYSTEM2 − GROUND ELECTRICAL POWER CONNECTORS3 − POTABLE WATER DRAIN4 − LOW PRESSURE AIR PRE−CONDITIONING

AND ENGINE STARTING6 − ENGINE OIL FILLING7 − IDG OIL FILLING

8 − PRESSURE REFUEL/DEFUEL COUPLINGS9 − OVERWING REFUEL

5 − HIGH PRESSURE AIR PRE−CONDITIONING12 − HYD RESERVOIR AIR PRESSURIZATION AND

GROUND POWER SUPPLY (BLUE)

14 − POTABLE WATER SERVICE PANEL15 − TOILET AND WASTE SERVICE PANEL

16 − APU OIL FILLING17 − GROUNDING POINTS

13 − REFUEL/DEFUEL PANEL

11 − HYD RESERVOIR FILLING AND GROUND POWERSUPPLY (GREEN)

10 − HYDRAULIC GROUND POWER SUPPLY (YELLOW)

F_AC_050401_1_0030101_01_01

Ground Service Connections LayoutFIGURE-5-4-1-991-003-A01

5-4-1

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



5-4-2 Grounding Points

**ON A/C A340-200 A340-300

Grounding Points

**ON A/C A340-300

1. Grounding Points.

DISTANCE: Meters (ft)

FROM AIRPLANE CENTERLINE

AFT OF NOSER SIDE L SIDE

MEANHEIGHT

FROMGROUND

On Nose Landing Gear leg:

6.57 m

(21.56 ft) on centerline

1.40 m

(4.59 ft)

On left Main Landing Gearleg:

31.58 m(103.61 ft)

5.34 m(17.52 ft)

1.50 m(4.92 ft)

On right Main LandingGear leg:

31.58 m(103.61 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 A340-200

2. Grounding Points.

5-4-2

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013





AFT OF NOSER SIDE L SIDE

MEANHEIGHT

FROM

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:

29.40 m(96.46 ft)

5.34 m(17.52 ft)

1.50 m(4.92 ft)

On right Main LandingGear leg:

29.40 m(96.46 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.

5-4-2

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

(1)(2)

LANDINGGEAR

GROUND CABLE(OPTIONAL)

GROUNDINGPOINT

GROUNDINGPOINT

NOSE GEAR MAIN GEAR

AA

A

F_AC_050402_1_0030101_01_00

Ground Service ConnectionsGrounding Points

FIGURE-5-4-2-991-003-A01

5-4-2

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

RIB22

RIB23

NOTE

A

A

B

: R SIDE SYMETRICALB

F

W

D

F_AC_050402_1_0040101_01_00

A

Ground Service ConnectionsGrounding Points

FIGURE-5-4-2-991-004-A01

5-4-2

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



5-4-3 Hydraulic System

**ON A/C A340-200 A340-300

Hydraulic System

**ON A/C A340-300

1. Ground Service Panels

DISTANCEFROM AIRCRAFT CENTERLINE

ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHT

FROMGROUND

Green System:(Access Door 197CB)

41.3 m(135.5 ft)

-1.34 m(4.4 ft)

2.23 m(7.32 ft)

Yellow System:(Access Door 196BB)

35.4 m(116.14 ft)

1.3 m(4.27 ft)

- 1.95 m(6.4 ft)

Blue System:(Access Door 195BB)

34.41 m(112.89 ft)

-1.28 m(4.2 ft)

1.94 m(6.36 ft)

**ON A/C A340-200

2. Ground Service Panels


ACCESS AFT OF NOSERH SIDE LH SIDE

MEAN

HEIGHTFROM

GROUNDGreen System:(Access Door 197CB)

39.17 m(128.51 ft)

-1.34 m(4.4 ft)

2.23 m(7.32 ft)

Yellow System:(Access Door 196BB)

33.27 m(109.15 ft)

1.3 m(4.27 ft)

-1.95 m(6.4 ft)

Blue System:(Access Door 195BB)

32.28 m(105.91 ft)

-1.28 m(4.2 ft)

1.94 m(6.36 ft)

5-4-3

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

3. Reservoir Pressurization


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHT

FROMGROUND

One 1/4 in. self-sealingconnection common to the3 reservoirs.(Blue System GroundService Panel):(Access Door 195BB)

34.47 m(113.09 ft)

-1.41 m(4.63 ft)

1.89 m(6.2 ft)

**ON A/C A340-200

4. Reservoir Pressurization


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHT

FROMGROUND

One 1/4 in. self-sealingconnection common to the

3 reservoirs.(Blue System GroundService Panel):(Access Door 195BB)

32.34 m(106.1 ft) - 1.41 m(4.63 ft) 1.89 m(6.2 ft)

**ON A/C A340-300

5. Accumulator Charging

Five connections (one for each accumulator):

5-4-3

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013




ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHT

FROM

GROUNDYellow SystemAccumulator:(Access Door 196BB)

35.55 m(116.63 ft)

1.43 m(4.69 ft)

-1.91 m(6.27 ft)

Green SystemAccumulator:(Access Door 197CB)

41.52 m(136.22 ft)

-1.33 m(4.36 ft)

2.19 m(7.19 ft)

Blue SystemAaccumulator:(Access Door 195BB)

34.54 m(113.32 ft)

-1.38 m(4.53 ft)

1.9 m(6.23 ft)

Blue System BrakeAccumulator:(Access Door 195BB)

34.54 m(113.32 ft)

-1.24 m(4.07 ft)

1.9 m(6.23 ft)

**ON A/C A340-200

6. Accumulator Charging

Five connections (one for each accumulator):

DISTANCE

FROM AIRCRAFT CENTERLINEACCESS

AFT OF NOSERH SIDE LH SIDE

MEANHEIGHT

FROMGROUND

Yellow SystemAccumulator:(Access Door 196BB)

33.42 m(109.65 ft)

1.43 m(4.69 ft)

-1.91 m(6.27 ft)

Green SystemAccumulator:(Access Door 197CB)

39.39 m(129.23 ft)

-1.33 m(4.36 ft)

2.19 m(7.19 ft)

Blue System Accumulator:(Access Door 195BB)

32.41 m(106.33 ft)

- 1.38 m(4.53 ft)

1.9 m(6.23 ft)

Blue System BrakeAccumulator:(Access Door 195BB)

32.41 m(106.33 ft)

- 1.18 m3.87 ft

1.9 m(6.23 ft)

5-4-3

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

7. Reservoir Filling

Two connections (one self-sealing connection for pressurized supply on the Green system ground

service panel).


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHT

FROMGROUND

One handpump fillingconnection(Access Door 197CB)

41.31 m(135.53 ft)

-1.3 m(4.27 ft)

2.11 m(6.92 ft)

**ON A/C A340-200

8. Reservoir Filling

Two connections (one self-sealing connection for pressurized supply on the Green system groundservice panel).


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHT

FROM

GROUNDOne handpump fillingconnection(Access Door 197CB)

39.18 m(128.54 ft)

-1.3 m(4.27 ft)

2.11 m(6.92 ft)

**ON A/C A340-300

9. Reservoir Drain

One 3/8 in. self-sealing connection on the reservoir for:

5-4-3

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013




ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHT

FROM

GROUND

Yellow System29.03 m(95.24 ft)

2.12 m(6.96 ft)

- 2.4 m(7.87 ft)

Green System33.17 m(108.83 ft)

-0.7 m(2.3 ft)

3.8 m(12.47 ft)

Blue System29.03 m(95.24 ft)

- 2.12 m(6.96 ft)

2.4 m(7.87 ft)

**ON A/C A340-200

10. Reservoir Drain

One 3/8 in. self-sealing connection on the reservoir for:


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHT

FROMGROUND

Yellow System26.9 m(88.25 ft)

2.12 m(6.96 ft)

-2.4 m(7.87 ft)

Green System 31.04 m(101.84 ft)

- 0.7 m(2.3 ft)

3.8 m(12.47 ft)

Blue System26.9 m(88.25 ft)

-2.12 m(6.96 ft)

2.4 m(7.87 ft)

**ON A/C A340-300

11. Ground Test

Three 1 in. self-sealing connections and three 1-1/2 in. self-sealing connections (one pair per system).

5-4-3

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013




ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUND

Green System GroundService Panel:(Access Door 197CB)

34.92 m(114.57 ft)

-1.35 m(4.43 ft)

2.2 m(7.22 ft)

Yellow System GroundService Panel:(Access Door 196BB)

29.03 m(95.24 ft)

1.3 m(4.27 ft)

-2 m(6.56 ft)

Blue System GroundService Panel:(Access Door 195BB)

28.03 m(91.96 ft)

-1.28 m(4.2 ft)

2 m(6.56 ft)

**ON A/C A340-200

12. Ground Test

Three 1 in. self-sealing connections and three 1-1/2 in. self-sealing connections (one pair per system).


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUNDGreen System Ground

Service Panel:(Access Door 197CB)

32.79 m(107.58 ft) -

1.35 m(4.43 ft)

2.2 m(7.22 ft)

Yellow System GroundService Panel:(Access Door 196BB)

26.9 m(88.25 ft)

1.3 m(4.27 ft)

-2 m(6.56 ft)

Blue System GroundService Panel:(Access Door 195BB)

25.9 m(84.97 ft)

-1.28 m(4.2 ft)

2 m(6.56 ft)

5-4-3

Page 6Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

MAN SELECTORVALVE−RSVR

FILLING

LEVER HANDPUMP

GND CNCTR−SELFSEALING RSVR

FILLING

HAND PUMPRSVR FILLING

FILTER−RSVRFILLING

RSVRFILLING VALVE

GND CNCTR−SELFSEALING, G SUCTION

GND CNCTR−SELFSEALING, G DELIVERY

VALVE−MANDEPRESS, G−RSVR

HYDRSVR FILLINGADJUSTMENT

INDICATOR

PRESS GAGEG POWER ACCU

GND CNCTRNITROGEN CHARGING

G POWER ACCU

F

W

D

A

FR53.4 FR53.5197CB

A

F_AC_050403_1_0040101_01_00

Ground Service ConnectionsGreen System Ground Service Panel

FIGURE-5-4-3-991-004-A01

5-4-3

Page 7Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

PRESS GAGE

B POWER ACCU

GND CNCTRNITROGENCHARGING

B POWER ACCU

GND CNCTRSELF−SEALING,

B SUCTION

VALVE−MANDEPRESS, B RSVR

GND CNCTR−SELFSEALING,

B DELIVERY

GND CNCTRSELF−SEALING,

B/Y RSVR PRESS

GND CNCTRSELF−SEALING,G RSVR PRESS

PRESS GAGESPARK BRK ACCU

PARK BRK ACCU

F

W

D

A

FR44 FR45

A

195BB

F_AC_050403_1_0050101_01_00

Ground Service ConnectionsBlue System Ground Service Panel

FIGURE-5-4-3-991-005-A01

5-4-3

Page 8Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

SIGHTGLASSCARGO DOOR

SELECTOR MANIFOLD

HAND PUMPCARGO DOORS, Y RAT STOW PANEL

GND CNCTR−SELFSEALING, Y SUCTION

VALVE−MANDEPRESS, Y RSVR

GND CNCTR−SELFSEALING, Y DELIVERY

PRESS GAGEY POWER ACCU

GND CNCTRNITROGEN CHARGING

Y POWER ACCU

FWD

A

FR46FR47

A

196BB

F_AC_050403_1_0060101_01_00

Ground Service ConnectionsYellow System Ground Service Panel

FIGURE-5-4-3-991-006-A01

5-4-3

Page 9Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



5-4-4 Electrical System

**ON A/C A340-200 A340-300

Electrical System

1. Electrical System


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUND

A/C External Power:Access Door 121EL

7.01 m(23 ft) On centerline

1.98 m(6.5 ft)

NOTE : Distances are approximate.

2. Technical Specifications

A. External Power Receptacle:- Two standard ISO 461 receptacles - 90 kVA each.

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

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

D. Electrical Loads in Ground Configuration

In ground configuration, in addition to the power necessary for maintenance, all the circuits,except those which are directly connected to the engines, are supplied as in flight. In theseconditions, the maximum power on the ground is approximately 105 kVA; this value does nottake into account the supply of the galleys, which according to the aircraft interior layout, mayreach 90 kVA.

E. Electrical Power necessary for Maintenance at Line Stop and Workshops:- Hydraulic electric-pumps: 20 × 3 kVA- Air Conditioning/ventilation: 50.1 kVA- Fuel pumps: 12.6 kVA- Lighting (commercial): 12.3 kVA

- Lighting (technical): 6.1 kVA- Ice and rain protection: 3 kVA- Cargo loading: 13 kVA- AFS, flight controls, ADS, recorders: 3.5 kVA- Communications: 1 kVA- Radio navigation: 2 kVA.

5-4-4

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

B

F

W

D

FR19FR18

B

A

A121EL

GROUND CONNECTOR925VU

F_AC_050404_1_0020101_01_00

Ground Service ConnectionsElectrical Service Panel

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

5-4-4

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



5-4-5 Oxygen System

**ON A/C A340-200 A340-300

Oxygen System

1. Oxygen System


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUNDOxygen Replenishment(Option 1):Access Door 811

2.5 m(8.2 ft)

0.53 m(1.74 ft)

-3.2 m(10.5 ft)

Oxygen Replenishment(Option 2):

Access Door 811

2.5 m(8.2 ft)

0.68 m(2.23 ft)

- 3.2 m(10.5 ft)

- 0 -- Basic: External charging in the avionic compartment- 1 -- Option- 2 -- Option.Zero, one or two service connections (external charging in the avionics compartment) MS22066 Std.

NOTE : Internal charging connection provided.

5-4-5

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

BA

B

OXYGENFILLING PORT

TESTPORT

FR7

FR10

Z120

A

811

F

W

D

FR4

FR7

NOTE:

THE NUMBER OF OXYGEN CYLINDERS DEPENDS ON THE SYSTEM CONFIGURATION.

F_AC_050405_1_0030101_01_00

Ground Service ConnectionsOxygen System

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

5-4-5

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



5-4-6 Fuel System

**ON A/C A340-200 A340-300

Fuel System

**ON A/C A340-200

1. Refuel/Defuel Access



MEAN HEIGHTFROM

GROUND

Refuel/Defuel Coupling,Left:Access Door 522HB

27.8 m(91.21 ft)

-12.6 m(41.34 ft)

5 m(16.4 ft)

Refuel/Defuel Coupling,Right:Access Door 622HB

27.8 m(91.21 ft)

12.6 m(41.34 ft)

-5 m(16.4 ft)

Overwing GravityRefuel Cap

31.2 m(102.36 ft)

17.2 m(56.43 ft)

17.2 m(56.43 ft)

5.8 m(19.03 ft)

A. Four standard 2.5 in. ISO 45 connections.

B. Two service connections (gravity refuel).

2. Refuel/Defuel Control Panel



MEAN HEIGHTFROM

GROUND

Refuel/Defuel ControlPanel:Access Door 198DB

32.2 m(105.64 ft)

0.8 m(2.62 ft)

-1.9 m(6.23 ft)

A. Flow rate: 1250 l/min (330 US gal/min) per connection.

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

5-4-6

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



3. Overpressure Protector and NACA Flame Arrestor


AFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUND

Overpressure Protector37.36 m(122.57 ft)

27.17 m(89.14 ft)

27.17 m(89.14 ft)

5.75 m(18.86 ft)

NACA Flame Arrestor37 m(121.39 ft)

26.53 m(87.04 ft)

26.53 m(87.04 ft)

5.7 m(18.7 ft)

**ON A/C A340-300

4. Refuel/Defuel Access



MEAN HEIGHTFROM

GROUND

Refuel/Defuel Coupling,Left:Access Door 522HB

30 m(98.43 ft)

-12.6 m(41.34 ft)

5 m(16.4 ft)

Refuel/Defuel Coupling,Right:Access Door 622HB

30 m(98.43 ft)

12.6 m(41.34 ft)

-5 m(16.4 ft)

Overwing Gravity

Refuel Cap

34.5 m

(113.19 ft)

17.2 m

(56.43 ft)

17.2 m

(56.43 ft)

5.8 m

(19.03 ft)

A. Four standard 2.5 in. ISO 45 connections.

B. Two service connections (gravity refuel).

5. Refuel/Defuel Control Panel



MEAN HEIGHTFROM

GROUND

Refuel/Defuel ControlPanel:Access Door 198DB

34.3 m(112.53 ft)

0.8 m(2.62 ft)

- 1.9 m(6.23 ft)

A. Flow rate: 1250 l/min (330 US gal/min) per connection.

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

5-4-6

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



6. Overpressure Protector and NACA Flame Arrestor


AFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUND

Overpressure Protector39.48 m(129.53 ft)

27.17 m(89.14 ft)

27.17 m(89.14 ft)

5.75 m(18.86 ft)

NACA Flame Arrestor39.12 m(128.35 ft)

26.53 m(87.04 ft)

26.53 m(87.04 ft)

5.7 m(18.7 ft)

5-4-6

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

C

OVERPRESSURE PROTECTOR

A

NACA FLAME ARRESTOR

B

A

A

FWD

LH SIDE SHOWN

RH SIDE SYMMETRICAL

B

C

RIB36

RIB37

RIB38

550EB(650EB)

550DB(650DB)

F_AC_050406_1_0030101_01_00

Overpressure Protector and NACA Flame ArrestorFIGURE-5-4-6-991-003-A01

5-4-6

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



5-4-7 Pneumatic System

**ON A/C A340-200 A340-300

Pneumatic System

**ON A/C A340-300

1. High Pressure Air Connection



MEANHEIGHT

FROMGROUND

23.9 m(78.41 ft)

-0.84 m(2.76 ft)

1.79 m(5.87 ft)HP Connectors:

Access door 193CB 24.25 m(79.56 ft)

- 0.84 m(2.76 ft)

1.79 m(5.87 ft)

A. Connectors:- Two standard 3 in. ISO 2026 connections.

2. Low Pressure Connection



MEANHEIGHT

FROMGROUND

22.48 m(73.75 ft)

-0.31 m(1.02 ft)

1.86 m(6.1 ft)LP Connectors:

Access door 191EB 22.48 m(73.75 ft)

- 0.76 m(2.49 ft)

1.89 m(6.2 ft)

A. Connectors:- Two standard 8 in. SAE AS4262 connections.

5-4-7

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

3. High Pressure Air Connection

DISTANCE

FROM AIRCRAFT CENTERLINEAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHT

FROMGROUND

21.77 m(71.42 ft)

- 0.84 m(2.76 ft)

1.79 m(5.87 ft)HP Connectors:

Access door 193CB 22.12 m(72.57 ft)

-0.84 m(2.76 ft)

1.79 m(5.87 ft)

A. Connectors:

- Two standard 3 in. ISO 2026 connections.4. Low Pressure Air Connection



MEANHEIGHT

FROMGROUND

20.35 m(66.77 ft)

-0.31 m(1.02 ft)

1.86 m(6.1 ft)LP Connectors:

Access door 191EB 20.35 m

(66.77 ft)

-0.76 m

(2.49 ft)

1.89 m

(6.2 ft)

A. Connectors:- Two standard 8 in. SAE AS4262 connections.

5-4-7

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

193CB

191EB

B

A

FR40

HP CONNECTOR

B

LP CONNECTOR

A

F_AC_050407_1_0020101_01_00

Ground Service ConnectionsLP and HP Ground Connectors

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

5-4-7

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



5-4-8 Potable Water System

**ON A/C A340-300

Potable Water System

1. Potable Water System


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHT

FROMGROUND

Potable-Water Service Panel:Access Door 164AR

48.15 m(157.97 ft)

0.51 m(1.67 ft)

-3.15 m(10.33 ft)

FWD Drain Panel:Access Door 133BL

14.7 m(48.23 ft)

-0.6 m(1.97 ft)

1.9 m(6.23 ft)

AFT Drain Panel:Access Door 154AR

40.18 m(131.82 ft)

0.72 m(2.36 ft)

-2.46 m(8.07 ft)



A. Connections

(1) On the potable-water service panel (Access Door 164AR):- One heated 3/4 in. quick release filling connection

- One heated 3/4 in. overflow and discharge connection- One ground pressurization connection.

(2) On the FWD drain panel (Access Door 133BL):- One standard 3/4 in. drain connection with back-up mechanical control.

(3) On the AFT drain panel (Access Door 154AR):- One standard 3/4 in. drain connection with back-up mechanical control- One standard 3/4 in. overflow and discharge connection with back-up mechanical

control.

B. Capacity- 700 l (184.92 US gal) standard

- 1050 l (277.38 US gal) standard option.

C. Filling Pressure and Flow Rate

FWD tank:- Filling pressure: 50/125 psi (3.45/8.62 bar)- Flow rate: 45/73 l/min (11.89/19.28 US gal/min).

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AFT tank:- Filling pressure: 50/125 psi (3.45/8.62 bar)- Flow rate: 56/85 l/min (14.79/22.45 US gal/min).

5-4-8

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**ON A/C A340-300

A

B

C

164AR154AR

133BL

DRAIN VALVECONTROL HANDLE

DRAIN NIPPLE

OVERFLOWNIPPLE

(FILL/DRAIN VALVE)OVERFLOW CONTROL HANDLE

(FILLING LINE DRAIN VALVE)DRAIN CONTROL HANDLE

DRAIN NIPPLE

FWD POTABLE−WATER DRAIN PANEL

AFT POTABLE−WATER DRAIN PANELC

B

FR29

FR28

FR57.2

FR57.1

OVERFLOW NIPPLE

CAP

NIPPLE

CONTROL HANDLEFILL/DRAIN MAINTENANCE DOOR

LIMIT−SWITCH

FILL/DRAIN

A

POTABLE−WATER SERVICE PANEL

ASSEMBLY

GROUND AIRCONNECTION

FR70

FR69

F_AC_050408_1_0080101_01_00

Ground Service ConnectionsPotable-Water Ground Service Panels

FIGURE-5-4-8-991-008-A01

5-4-8

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**ON A/C A340-200

Potable Water System

1. Potable Water System


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHT

FROMGROUND

Potable-Water Service Panel:Access Door 164AR

43.88 m(143.96 ft)

0.51 m(1.67 ft)

-3.13 m(10.27 ft)

FWD Drain Panel:Access Door 133BL

14.7 m(48.23 ft)

- 0.6 m(1.97 ft)

1.92 m(6.3 ft)

AFT Drain Panel:

Access Door 154AR

36.51 m

(119.78 ft)

0.72 m

(2.36 ft)

-2.44 m

(8.01 ft)



A. Connections

(1) On the potable-water service panel (Access Door 164AR):- One heated 3/4 in. quick release filling connection- One heated 3/4 in. overflow and discharge connection- One ground pressurization connection.

(2) On the FWD drain panel (Access Door 133BL):- One standard 3/4 in. drain connection with back-up mechanical control.

(3) On the AFT drain panel (Access Door 154AR):- One standard 3/4 in. drain connection with back-up mechanical control- One standard 3/4 in. overflow and discharge connection with back-up mechanical

control.

B. Capacity- 700 l (184.92 US gal) standard- 1050 l (277.38 US gal) standard option.

C. Filling Pressure and Flow Rate

FWD tank:- Filling pressure: 50/125 psi (3.45/8.62 bar)- Flow rate: 45/73 l/min (11.89/19.28 US gal/min).

AFT tank:

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- Filling pressure: 50/125 psi (3.45/8.62 bar)- Flow rate: 56/85 l/min (14.79/22.45 US gal/min).

5-4-8

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**ON A/C A340-200

DRAIN VALVECONTROL HANDLE

DRAIN NIPPLE

OVERFLOWNIPPLE

(FILL/DRAIN VALVE)OVERFLOW CONTROL HANDLE

(FILLING LINE DRAIN VALVE)DRAIN CONTROL HANDLE

DRAIN NIPPLE

FWD POTABLE−WATER DRAIN PANEL

AFT POTABLE−WATER DRAIN PANELC

B

FR29

FR28

FR57

FR56

133BL

154AR

164AR

C

B

A

OVERFLOW NIPPLE

CAP

NIPPLE

CONTROL HANDLEFILL/DRAIN MAINTENANCE DOOR

LIMIT−SWITCH

FILL/DRAIN

A

POTABLE−WATER SERVICE PANEL

ASSEMBLY

GROUND AIRCONNECTION

FR70

FR69

F_AC_050408_1_0090101_01_00

Ground Service ConnectionsPotable-Water Ground Service Panels

FIGURE-5-4-8-991-009-A01

5-4-8

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5-4-9 Oil System

**ON A/C A340-200 A340-300

Oil System

**ON A/C A340-300

1. Engine Oil Tank and IDG for CFM56-5C2 series engine.

A. Engine Oil Replenishment:

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



AFT OF NOSE LH SIDE RH SIDE

MEAN

HEIGHT FROMGROUND

Engine Oil Gravity FillingCap:

Engine 1-431.03 m(101.80 ft)Engine 2-324.46 m(80.25 ft)

Engine 120.56 m(67.45 ft)Engine 210.33 m(33.89 ft)



Engine Oil Pressure Filling

Port:

Engine 1-430.90 m(101.38 ft)

Engine 2-324.32 m(79.79 ft)

Engine 120.64 m(67.72 ft)

Engine 210.41 m(34.15 ft)

Engine 38.32 m(27.30 ft)

Engine 418.56 m(60.89 ft)

Engine 1-43.47 m(11.38 ft)

Engine 2-32.20 m(7.22 ft)

- Max delivery pressure required: 25 psi (1.72 bar).- Max delivery flow required: 66.00 US gal/hour (249.84 l/hour).

(1) Tank capacity:- Full level: 20.70 Qts (22.79 l).- Minimum Usable: 9.70 Qts (10.68 l).

B. IDG Oil Replenishment:

One pressure filling connection per engine.

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FROM AIRPLANE CENTERLINEAFT OF NOSE

LH SIDE RH SIDE

MEANHEIGHT FROM

GROUND

IDG Oil Pressure FillingPort:





- Max delivery pressure required: 40 psi (2.76 bar).- Max OIL capacity of IDG: 1.10 US gal (4.16 l).

**ON A/C A340-200

2. Engine Oil Tank and IDG for CFM56-5C2 series engine.

A. Engine Oil Replenishment:

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



LH SIDE RH SIDE

MEANHEIGHT FROM

GROUND

Engine Oil Gravity FillingCap:





Engine Oil Pressure Filling

Port:

Engine 1-428.77 m(94.39 ft)

Engine 2-322.19 m(72.80 ft)

Engine 120.64 m(67.72 ft)

Engine 210.41 m(34.15 ft)

Engine 38.32 m(27.30 ft)

Engine 418.56 m(60.89 ft)

Engine 1-43.47 m(11.38 ft)

Engine 2-32.20 m(7.22 ft)

- Max delivery pressure required: 25 psi (1.72 bar).- Max delivery flow required: 66.00 US gal/hour (249.84 l/hour).

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(1) Tank capacity:- Full level: 20.70 Qts (22.79 l).- Minimum Usable: 9.70 Qts (10.68 l).

B. IDG Oil Replenishment:

One pressure filling connection per engine.



LH SIDE RH SIDE

MEANHEIGHT FROM

GROUND

IDG Oil Pressure FillingPort:

Engine 1-427.99 m(91.83 ft)

Engine 2-321.41 m(70.24 ft)

Engine 119.40 m(63.65 ft)

Engine 29.17 m(30.09 ft)

Engine 39.57 m(31.40 ft)

Engine 419.80 m(64.96 ft)

Engine 1-42.55 m(8.37 ft)

Engine 2-31.35 m(4.43 ft)

- Max delivery pressure required: 40 psi (2.76 bar).- Max OIL capacity of IDG: 1.10 US gal (4.16 l).

5-4-9

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**ON A/C A340-200 A340-300

A

AIR PRESSURESWITCH NIPPLE

OIL CAP

PRESSURE NIPPLE

SIGHT WINDOW

ANTI−

SIPHONDEVICE

VENT

OIL OUT

OIL/FUEL HEATEXCHANGER SERVO FUEL

HEATER

SELF−SEALING MAGNETICDRAIN PLUG

OIL INOIL LEVELTRANSMITTER(OPTIONAL)

AF_AC_050409_1_0080101_01_00

Ground Service ConnectionsEngine Oil Tank - CFM56-5C2 series engine

FIGURE-5-4-9-991-008-A01

5-4-9

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**ON A/C A340-200 A340-300

A

RED

YELLOW

GREEN

RED

A

B

C

OIL LEVELINDICATOR

(SIGHT GLASS)

CASEDRAINPLUG

DUSTCAP

PRESSUREFILL

VALVE

OVERFILLDRAINVALVE

NOTE :

OIL SERVICING IS REQUIRED.B IF THE OIL LEVEL IS WITHIN THE GREEN AND YELLOW BANDS,

OIL SERVICING IS NOT REQUIRED.

C IF THE OIL LEVEL IS BELOW THE GREEN BAND,OIL SERVICING IS REQUIRED.

A

B

A IF THE OIL LEVEL IS ABOVE THE YELLOW BAND,

F_AC_050409_1_0090101_01_00

B

A340

OVER

ADD

OIL

CFM56−5C2

FULL

ADD

OIL

Ground Service ConnectionsIDG Oil Tank - CFM56-5C2 series engine

FIGURE-5-4-9-991-009-A01

5-4-9

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**ON A/C A340-200 A340-300

APU Oil System

**ON A/C A340-300

1. APU Oil SystemAPU oil gravity filling cap.



MEAN HEIGHTFROM GROUND

APU OilReplenishment:Access Doors316AR, 315AL

60.3 m(197.83 ft)

-0.4 m(1.31 ft)

8 m(26.25 ft)

A. Tank capacity (usable):- APU Type: 331-350: 7.3 l (1.93 US gal)- APU Type: 331-600: 11 l (2.91 US gal).

**ON A/C A340-200

2. APU Oil SystemAPU oil gravity filling cap.



MEAN HEIGHTFROM GROUND

APU OilReplenishment:Access Doors316AR, 315AL

56 m(183.73 ft)

- 0.4 m(1.31 ft)

8 m(26.25 ft)

A. Tank capacity (usable):- APU Type: 331-350: 7.3 l (1.93 US gal)- APU Type: 331-600: 11 l (2.91 US gal).

5-4-9

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**ON A/C A340-200 A340-300

FR95

316AR

315AL

FR101

A

PRESSURE FILLOVERFLOW PORT

OIL SCUPPER

GRAVITY FILLPORT

LUBRIFICATIONOIL FILTER

GENERATORSCAVENGEOIL FILTER

OIL PUMPMODULE5100KT9

A

B

OIL FILLERCAP

OVERFLOWPORT

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_0100101_01_01

Ground Service ConnectionsAPU Oil Servicing

FIGURE-5-4-9-991-010-A01

5-4-9

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5-4-10 Vacuum Toilet System

**ON A/C A340-200 A340-300

Vacuum Toilet System

**ON A/C A340-300

1. Vacuum Toilet System

DISTANCEFROM AIRPLANE CENTERLINE


MEAN HEIGHTFROM

GROUNDWaste Water GroundService Panel:Access Door 171AL

50 m(164.04 ft)

-0.09 m(0.3 ft)

3.6 m(11.81 ft)

A. Waste water ground service panel comprising:- Standard: One standard 4 in. drain connection and two 1 in. flushing connections- Standard option: One standard 4 in. drain connection and three 1 in. flushing connections.

B. Capacity waste tanks:- Standard: 700 l (184.92 US gal)- Standard option: 1050 l (277.38 US gal).

C. Chemical fluid:- Standard: 36 l (9.51 US gal)- Standard option: 54 l (14.27 US gal).

**ON A/C A340-200

2. Vacuum Toilet System

DISTANCEFROM AIRPLANE CENTERLINE


MEAN HEIGHTFROM

GROUNDWaste Water GroundService Panel:Access Door 171AL

45.72 m(150.00 ft)

-0.09 m(0.3 ft)

3.6 m(11.81 ft)

A. Waste water ground service panel comprising:- Standard: One standard 4 in. drain connection and two 1 in. flushing connections- Standard option: One standard 4 in. drain connection and three 1 in. flushing connections.

B. Capacity waste tanks:- Standard: 700 l (184.92 US gal)

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- Standard option: 1050 l (277.38 US gal).

C. Chemical fluid:- Standard: 36 l (9.51 US gal)- Standard option: 54 l (14.27 US gal).

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**ON A/C A340-200 A340-300

LIMIT SWITCHWASTE−PANEL

RINSE CONNECTIONTANK 2 FILL AND

TANK 1 FILL ANDRINSE CONNECTION

WASTEDRAIN−LINE VALVE

DRAIN−VALVECONTROL LEVERS

FR75

FR59

FR74 FR73

A

171AL

OPEN

CLOSE

LH RH

A

FWD

F_AC_050410_1_0020101_01_00

Ground Service ConnectionsWaste Water Ground Service Panel

FIGURE-5-4-10-991-002-A01

5-4-10

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5-5-0 Engine Starting Pneumatic Requirements

**ON A/C A340-200 A340-300

Engine Starting Pneumatic Requirements

1. The purpose of this section is to provide the minimum air data requirements at the aircraftconnection, needed to start the engine within no more than 70 seconds, at sea level (0 feet), for a setof Outside Air Temperatures (OAT).

ABBREVIATION DEFINITION

A/C Aircraft

ASU Air Start UnitHPGC High Pressure Ground Connection


A. Air data (discharge temperature, absolute discharge pressure) are given at the HPGC.B. For the requirements below, the configuration with two HPGC is used. Using one connector only

(for a given mass flow rate and discharge pressure from the ASU) will increase the pressure lossin the ducts of the bleed system and therefore lower the performances at the engine starter.

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

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

E. To protect the A/C, the charts feature, if necessary:

- The maximum discharge pressure at the HPGC- The maximum discharge temperature at the HPGC.

5-5-0

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**ON A/C A340-200 A340-300

A I R F L O W

( k g / m i n )

A I R F L O W

( l b / m i n )

A B S O L U T E P R E S S U R E ( p s i a )

CFM56−5C2 SERIES/SEA LEVEL

STARTING TIME: LESS THAN 70 s

AIR DATA AT AIRCRAFT CONNECTION (TWO CONNECTORS)

OUTSIDE AIR TEMPERATURE OAT (° C)

OUTSIDE AIR TEMPERATURE OAT (° F)

0 20 40 60 80 100 120 140−20−40

EXAMPLE:

NOTE:

35

40

45

50

0 10 20 30 40 50 60−

10−

20−

30−

40−

50

30 35 40 45 5040

45

50

55

60

65

70

75

80

90

100

110

120

130

140

150

160

170

FOR AN OAT OF 20° C (68° F) AND AN ASU PROVIDING A DISCHARGE TEMPERATURE OF 150° C (302° F)AT HPGC:− THE REQUIRED PRESSURE AT HPGC IS 39 psia− THE REQUIRED AIRFLOW AT HPGC IS 50.5 kg/min.

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

ABSOLUTE PRESSURE (psia)

OAT = 100° C (212° F)

OAT = 150° C (302° F)

OAT = 220° C (428° F) MAX.

F_AC_050500_1_0020101_01_01

Example for Use of the ChartsFIGURE-5-5-0-991-002-A01

5-5-0

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**ON A/C A340-200 A340-300

OAT = 100° C (212° F)

OAT = 150° C (302° F)

OAT = 220° C (428° F) MAX.

A I R F L O W ( k g / m i n )

A I R F L O W

( l b / m i n )

A B S O L U

T E P R E S S U R E ( p s i a )

STARTING TIME: LESS THAN 70 s

AIR DATA AT AIRCRAFT CONNECTION (TWO CONNECTORS)

OUTSIDE AIR TEMPERATURE OAT (° C)

OUTSIDE AIR TEMPERATURE OAT (° F)0 20 40 60 80 100 120 140−20−40

30 35 40 45 5040

45

50

55

60

65

70

75

80

90

100

110

120

130

140

150

160

170

35

40

45

50

0 10 20 30 40 50 60−10−20−30−40−50

ABSOLUTE PRESSURE (psia)

CFM56−5C2 SERIES/SEA LEVEL

F_AC_050500_1_0080101_01_00

Engine Starting Pneumatic RequirementsCFM56-5C2 Series

FIGURE-5-5-0-991-008-A01

5-5-0

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5-6-0 Ground Pneumatic Power Requirements

**ON A/C A340-200 A340-300

Ground Pneumatic Power Requirements

1. This section describes the required performance for the ground equipment to maintain the cabintemperature at 27˚C (80.6˚F) after boarding (Section 5.7 - steady state), and provides the timeneeded to cool down or heat up the aircraft cabin to the required temperature (Section 5.6 - dynamiccases with aircraft empty).

ABBREVIATION DEFINITION

A/C Aircraft

AHM Aircraft Handling Manual

GC Ground ConnectionGSE Ground Service Equipment

IFE In-Flight EntertainmentLP Low Pressure


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

NOTE : The maximum air flow is driven by pressure limitation at the ground connection.

B. The air flow rates and temperature requirements for the GSE are given for the A/C in theconfiguration ”2 LP ducts connected”.

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

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

2. Ground Pneumatic Power RequirementsThis section provides the ground pneumatic power requirements for:- Heating (pull up) the cabin, initially at OAT, up to 21˚C (69.8˚F) FIGURE 5---0-99--002-A- Cooling (pull down) the cabin, initially at OAT, down to 27˚C (80.6˚F) FIGURE 5---0-99--004-

A.

5-6-0

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**ON A/C A340-200 A340-300

30 60 90 120 1500.8

1.2

1.4

1.6

1.8

2.2

2.4

2.0

2.5

3.0

3.5

4.0

4.5

5.0

A I R F L O W

A T G C ( k g / s )

A I R F L O W A T G C ( l b / s )

PULL UP PERFORMANCE

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

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

LOAD; LIGHTS ON; GALLEYS OFF; RECIRCULATION FANS ON

40 50 70 80 100 110 130 140

MAXIMUM AIR FLOW

1.0

2.0

F_AC_050600_1_0020101_01_00

Ground Pneumatic Power RequirementsHeating

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

5-6-0

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**ON A/C A340-200 A340-300

30 60 90 120 1500.8

1.2

1.4

1.6

1.8

2.2

2.4

2.0

2.5

3.0

3.5

4.0

4.5

5.0

A I R F L O W

A T G C

( k g / s )

A I R F L O W A T G C

( l b / s )

PULL DOWN PERFORMANCE

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

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

LOAD; LIGHTS ON; GALLEYS OFF; RECIRCULATION FANS ON

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

40 50 70 80 100 110 130 140

MAXIMUM AIR FLOW

2.0

1.0

F_AC_050600_1_0040101_01_00

Ground Pneumatic Power RequirementsCooling

FIGURE-5-6-0-991-004-A01

5-6-0

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5-7-0 Preconditioned Airflow Requirements

**ON A/C A340-200 A340-300

Preconditioned Airflow Requirements

1. This section provides the preconditioned airflow rate and temperature needed to maintain the cabintemperature at 27 ˚C (80.6 ˚F).

These settings are not intended to be used for operation (they are not a substitute for the settingsgiven in the AMM). They are based on theoretical simulations and give the picture of a real steadystate. The purpose of the air conditioning operation (described in the AMM) is to maintain the cabintemperature below 27 ˚C (80.6 ˚F) during boarding (therefore it is not a steady state).

5-7-0

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**ON A/C A340-200 A340-300

A I R F L O

W

A T G C ( k g / s )

−150.8

A I R F L O

W A T G C ( l b / s )

1.0

1.2

1.4

1.6

1.8

2.0

2.2

2.4

−10 −5 0 5 10 15 20 25 30 35 40 45 50 55 60

2.0

2.5

3.0

3.5

4.0

4.5

5.0

0 10 20 30 40 50 60 70 80

INLET TEMPERATURE AT GC (° C)

INLET TEMPERATURE AT GC (° F)

MAXIMUM AIRFLOW

COOLING/HEATING PERFORMANCE

SETTINGS NOTINTENDED TO BE USED

FOR OPERATION

OAT ISA; EMPTY CABIN; IFE ON; LIGHTS ON; SOLAR LOAD; RECIRCULATION FANS ON; GALLEYS ON

OAT ISA −38° C (−36.4° F); EMPTY CABIN; IFE OFF; LIGHTS ON; NO SOLAR LOAD; RECIRCULATION

FANS ON; GALLEYS OFF

C H

EXAMPLE:

COOLING CAPACITY CALCULATION:FOR THE CONDITIONS "C", THE COOLING CAPACITY OF 1.9 kg/s x 1 kJ/(kg.° C) x (27− 5) = 41.8 kW(OR 12.5 TONS COOLING CAPACITY) IS NEEDED TO MAINTAIN THE CABIN TEMPERATURE AT 27° C (80.6° F)(1.9 kg/s AT 5° C (41° F) FOR AIR AT GC INLET).

90 100 110 120 130 140

F_AC_050700_1_0030101_01_01

Preconditioned Airflow RequirementsFIGURE-5-7-0-991-003-A01

5-7-0

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5-8-0 Ground Towing Requirements

**ON A/C A340-200 A340-300

Ground Towing Requirements

1. This section provides information on aircraft towing.

The A340-200/-300 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 towbar attached to the nose gear leg (refer to AMM chapter 9 for conditions andlimitations). One towbar 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

chapter 7 of the Aircraft Recovery Manual).

This section shows the chart to determine the draw bar pull and tow tractor mass requirements as afunction of the following physical characteristics:- Aircraft weight,- Number of engines at idle,- Slope.

The following chart is applicable to both A340-200 and -300 aircraft.

2. Towbar design guidelines

The aircraft towbar shall comply with the following standards:- SAE AS 1614, ”Main Line Aircraft TowBar Attach Fitting Interface”,- SAE ARP 1915, ”Aircraft TowBar”,- ISO 8267-1, ”Aircraft - Towbar attachment fitting - Interface requirements - Part 1: Main line

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

A conventional type towbar 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 28 620 daN (64 340 lbf),- A torsion pin calibrated at 3 130 m.daN (276 991 lbf.in).The towing head is designed according to SAE AS 1614, cat. III.

5-8-0

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**ON A/C A340-200 A340-300

F_AC_050800_1_0060101_01_00

EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A340−200 OR −300 AT 270 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 (270 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 (21.3 t),− SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE.

THE OBTAINED X−COORDINATE IS THE RECOMMENDED MINIMUM TRACTOR WEIGHT (37.3 t).

30

25

20

15

10

5

0

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

280

255

230

205

180

155

130

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

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

BREAKWAY RESISTANCE 6%# OF ENGINES ON FOR PB: 2ENGINE THRUST 500 daN

21.3

37.3

2 ENGINES ON1.5% SLOPE

270 tons

ICE = 0.05

H A R D

S N O W

= 0

. 2

W E T

C O N C R E T

E = 0 . 5 7

D R Y

C O

N C R E T E

= 0 . 8

Ground Towing RequirementsFIGURE-5-8-0-991-006-A01

5-8-0

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5-9-0 De-Icing and External Cleaning

**ON A/C A340-200 A340-300

De-Icing and External Cleaning

1. De-Icing and External Cleaning on GroundThe mobile equipment for aircraft de-icing and external cleaning must be capable of reaching heightsup to approximately 17 m (56 ft).

**ON A/C A340-200

2. De-Icing

Wing Top Surface(Both Sides)

Wingtip Devices(Both Inside and

Outside Surfaces)(Both Sides)

HTP Top Surface(Both Sides)

VTP(Both Sides)AIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2 m2 ft2

A340-200 306 3 294 11 118 65 700 91 980

Fuselage Top Surface(Top Third - 120˚ Arc)

Nacelle and Pylon(Top Third - 120˚ Arc)

(All Engines)Total De-Iced AreaAIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2

A340-200 294 3 165 55 592 821 8 837

NOTE : Dimensions are approximate.

**ON A/C A340-300

3. De-Icing





VTP(Both Sides)AIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2 m2 ft2

A340-300 306 3 294 11 118 65 700 91 980

5-9-0

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Fuselage Top Surface(Top Third - 120˚ Arc)

Nacelle and Pylon(Top Third - 120˚ Arc)

(All Engines)Total De-Iced AreaAIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2

A340-300 319 3 434 55 592 847 9 117


**ON A/C A340-200

4. External Cleaning


Wing LowerSurface

(Including Flap

Track Fairing)(Both Sides)


Outside Surfaces)

(Both Sides)


HTP LowerSurface

(Both Sides)

AIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2 m2 ft2 m2 ft2

A340-200 306 3 294 340 3 660 11 118 65 700 65 700

VTP(Both Sides)

Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned AreaAIRCRAFT

TYPEm2 ft2 m2 ft2 m2 ft2 m2 ft2

A340-200 91 980 896 9 644 200 2 153 1 982 21 334


**ON A/C A340-300

5. External Cleaning


Wing LowerSurface

(Including FlapTrack Fairing)(Both Sides)




HTP LowerSurface

(Both Sides)AIRCRAFT

TYPE

m2

ft2

m2

ft2

m2

ft2

m2

ft2

m2

ft2

A340-300 306 3 294 340 3 660 11 118 65 700 65 700

5-9-0

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VTP(Both Sides)

Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned AreaAIRCRAFT

TYPEm2 ft2 m2 ft2 m2 ft2 m2 ft2

A340-300 91 980 971 10 452 200 2 153 2 057 22 141


5-9-0

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OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

**ON A/C A340-200 A340-300Engine Exhaust Velocities and Temperatures

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

6-1-0

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

**ON A/C A340-200 A340-300

Engine Exhaust Velocities Contours - Ground Idle Power

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

6-1-1

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**ON A/C A340-200 A340-300

F_AC_060101_1_0040101_01_00

F E E T

M E T E R S

5 0

G R O U N D P L A

N E

A I R P L A N E

E L E V A T I O

N 1 0 0

1 5 0

2 0 0

2 5 0

3 0 0

3 5 0

4 0 0

1 5

3 0

4 5

6 0

7 5

9 0

1 0 5

1 2 0

C L

f t

m 0

0

V =

4 0 m / s

V = 2 0

m / s

V = 1 2 m / s

V =

4 0 m / s

V = 2 0 m / s

V = 1 2 m / s

3 0

1 2

1 8 2

4 6

1 0 0 4

0 6 0

8 0

2 0

0 3 0

1 2

1 8 2

4 6

G R O U N D I D L E

I N C L U D E S : ( W O R S T C A S E )

G R O U N D P L A N E

P R O X I M I T Y

H E A D W I N D ( 2 0 K N T S )

P L A N

f t

m

0 1 0 0 4

0 6 0

8 0

2 0

0 0

Engine Exhaust VelocitiesGround Idle Power - CFM56-5C series engine

FIGURE-6-1-1-991-004-A01

6-1-1

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

**ON A/C A340-200 A340-300

Engine Exhaust Temperatures Contours - Ground Idle Power

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

6-1-2

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**ON A/C A340-200 A340-300

FEET

METERS

50

GROUND PLANE

AIRPLANE

100

15 30

CL

ftm

0

12

18

6

60

ftm

0

30

12

18

24

6

100

45

150

60

200

GROUND IDLE

INCLUDES: (WORST CASE)GROUND PLANEPROXIMITYHEADWIND (20 KNTS)

306°F152°C

207°F97°C

108°F42°C

306°F 207°F 108°F152°C 97°C 42°C

PLAN0

40

60

80

20

ELEVATION0

40

20

0

0

F_AC_060102_1_0040101_01_00

Engine Exhaust TemperaturesGround Idle Power - CFM56-5C series engine

FIGURE-6-1-2-991-004-A01

6-1-2

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

**ON A/C A340-200 A340-300

Engine Exhaust Velocities Contours - Breakaway Power

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

6-1-3

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**ON A/C A340-200 A340-300

F_AC_060103_1_0040101_01_00

F E E T

M E T E R S

5 0

G R

O U N D P L A N E

A I R P L A N E

E L E V A T I O N 1

0 0

1 5 0

2 0 0

2 5 0

3 0 0

3 5 0

4 0 0

1 5

3 0

4 5

6 0

7 5

9 0

1 0 5

1 2 0

C L

1 3 5

1 5 0

1 6 5

1 8 0

1 9 5

f t

m

4 5 0

5 0 0

5 5 0

6 5 0

6 0 0

0

0

V = 4 0 m / s

V = 2 0 m / s

V = 1 2 m / s

4 − E N G I N E B R E A K A W A Y



P R O X I M I T Y

H E A D W I N D ( 2 0 K N T S )

V = 4 0 m / s

V = 2 0 m / s

V = 1 2 m

/ s

3 0 1 2 1 8 2 4 6

1 0 0

4 0

6 0

8 0

2 0

f t

m 0 3 0 1 2 1 8 2 4 6

P L A N

0 1 0 0

4 0

6 0

8 0

2 0

0 0

Engine Exhaust VelocitiesBreakaway Power - CFM56-5C series engine

FIGURE-6-1-3-991-004-A01

6-1-3

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

**ON A/C A340-200 A340-300

Engine Exhaust Temperatures Contours - Breakaway Power

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

6-1-4

Page 1Apr 01/13

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**ON A/C A340-200 A340-300

F_AC_060104_1_0040101_01_00

GROUND PLANE

AIRPLANE

ELEVATION

PLAN CL

ftm

0 0

12

18

6

40

60

20

ftm

0 0

30

12

18

24

6

100

40

60

80

20

240°F116°C

140°F60°C

100°F38°C

240°F116°C

140°F60°C

100°F38°C

FEET

METERS

50 100

15 30 45

150

60

2000

0

Engine Exhaust TemperaturesBreakaway Power - CFM56-5C series engine

FIGURE-6-1-4-991-004-A01

6-1-4

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

**ON A/C A340-200 A340-300

Engine Exhaust Velocities Contours - Takeoff Power

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

6-1-5

Page 1Apr 01/13

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**ON A/C A340-200 A340-300

F_AC_060105_1_0040101_01_00

F E E T

M E T

E R S

G R O U N D P L A

N E

A I R P L A N E

E L E V A T I O N

P L A N

1 0 0

2 0 0

3 0 0

C L

f t

m 0

0

3 0

1 2 1 8 2 4

6

1 0 0

4 0

6 0

8 0

2 0

3 0

6 0

9 0

1 2 0

1 5 0

1 8 0

2 1 0

2 4

0

2 7 0

3 0 0

3 3 0

3 6 0

3 9 0

4 0 0

5 0 0

7 0 0

8 0 0

6 0 0

9 0 0

1 0 0 0

1 1 0 0

1 2 0 0

1 3 0 0

f t

m 0

0

3 0

1 2 1 8 2 4

6

1 0 0

4 0

6 0

8 0

2 0

V = 4 0 m / s

V = 2 0 m / s

V = 1 2 m / s

V = 4 0 m / s

V = 2 0 m / s

V = 1 2 m / s

T A K E O F F P O W E R



P R O X I M I T Y

H E A D W I N D ( 2 0 K N T S )

0 0

Engine Exhaust VelocitiesTakeoff Power - CFM56-5C series engine

FIGURE-6-1-5-991-004-A01

6-1-5

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

**ON A/C A340-200 A340-300

Engine Exhaust Temperatures Contours - Takeoff Power

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

6-1-6

Page 1Apr 01/13

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**ON A/C A340-200 A340-300

F_AC_060106_1_0040101_01_00

FEET

METERS

50

GROUND PLANE

AIRPLANE

ELEVATION

PLAN

100

15 30

CL

ftm

0 0

30

12

18

24

6

100

40

60

80

20

45

150

306°F152°C

207°F97°C

108°F42°C

60

200 250

75 90

300

0 0

30

12

18

24

6

100

40

60

80

108°F42°C

306°F152°C

207°F97°C

TAKEOFF POWER

INCLUDES: (WORST CASE)GROUND PLANEPROXIMITYHEADWIND (20KNTS)

ftm

20

0

0

Engine Exhaust TemperaturesTakeoff Power - CFM56-5C series engine

FIGURE-6-1-6-991-004-A01

6-1-6

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6-2-0 Airport and Community Noise

**ON A/C A340-200 A340-300

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.

6-2-0

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6-2-1 Noise Data

**ON A/C A340-200 A340-300

Noise Data

1. Noise Data for CFM56-5C 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: 2 engines running

C. Meteorological data:

The meteorological parameters measured 1.6 m (5.25 ft) from the ground on the day of testwere as follows:- Temperature: 19˚C (66˚F)- Relative humidity: 68%- Atmospheric pressure: 1004 hPa- Wind speed: Negligible- No rain

6-2-1

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**ON A/C A340-200 A340-300

8082

84

868890

9294

96

0°10°20°

30°

40°

50°

60°

70°

80°

90°

100°

110°

120°

130°

140°

150°

98100

102104

106108

110112

350°340°

330°

320°

310°

300°

290°

280°

270°

250°

240°

230°

220°

210°

NOISE REFERENCEPOINT

GROUND IDLE

N1

CURVE

MAX THRUST POSSIBLEON BRAKES

21%

260°78

F_AC_060201_1_0040101_01_00

92.7%

Airport and Community NoiseCFM56-5C series engine

FIGURE-6-2-1-991-004-A01

6-2-1

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6-3-0 Danger Areas of Engines

**ON A/C A340-200 A340-300

Danger Areas of Engines

1. Danger Areas of the Engines.

6-3-0

Page 1Apr 01/13

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6-3-1 Ground Idle Power

**ON A/C A340-200 A340-300

Ground Idle Power

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

6-3-1

Page 1Apr 01/13

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**ON A/C A340-200 A340-300

F_AC_060301_1_0040101_01_00F_AC_060301_1_0040101_01_00

NOT TO SCALE

RADIUS = 9.7 ft

4.7 ft45°

CLOSE ENTRYCORRIDOR FOR

WIND DIRECTION>90 DEGREES

AB

CNO ENTRY 105 ft (32 m)AFT OF NOZZLE EXIT

GMM−1137912−00−B

AREA

A 210−145(338−233)

B 145−105(233−169)

C

D65−20

(105−32)

105−65(169−105)

E < 20 (32) BEYOND DANGER AREA.

INLET SUCTIONDANGER AREA

ENTRYCORRIDOR

EXHAUST WAKE DANGERAREA, 65 mph (105 km/h)OR LESS

APPROX. WINDVELOCITYmph (km/h)

LIGHT TO MODERATE DAMAGE TO TRANSPORT − TYPE AIRCRAFT.

POSSIBLE EFFECTS WITHIN DANGER ZONE BASED ON"RADIOLOGICAL DEFENSE", VOL. II, ARMED FORCES SPECIALWEAPONS PROJECT, NOV 1951.

D

EXHAUST WAKE DANGERAREA, 65 mph (105 km/h)OR GREATER

A MAN STANDING WILL BE PICKED UP AND THROWN; AIRCRAFT WILL BECOMPLETELY DESTROYED OR DAMAGED BEYOND ECONOMICAL REPAIR;COMPLETE DESTRUCTION OF FRAME OR BRICK HOMES.

A MAN STANDING FACE − ON WILL BE PICKED UP AND THROWN; DAMAGENEARING TOTAL DESTRUCTION TO LIGHT INDUSTRIAL BUILDINGS OR RIGIDSTEEL FRAMING; CORRUGATED STEEL STRUCTURES LESS SEVERELY.

MODERATE DAMAGE TO LIGHT INDUSTRIAL BUILDINGS AIR TRANSPORT− TYPE AIRCRAFT.

171 ft (52 m)WIDTH

TO 417 ft (127 m)E

(3.0 m)

(1.4 m)

INLET DANGER AREASINCLUDE:(WORST CASE)

GROUND PLANE PROXIMITYHEADWIND/CROSSWIND (20 kts)

EXHAUST DANGER AREAS

INCLUDE (WORST CASE):GROUND PLANE PROXIMITY

HEADWIND (20 kts)

INLET HAZARD DIMENSIONSBASED ON 40 ft/SEC

CRITICAL VELOCITY WITH A3 ft CONTINGENCY ADDED

Danger Areas of EnginesCFM56-5C series engine

FIGURE-6-3-1-991-004-A01

6-3-1

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6-3-2 Breakaway Power

**ON A/C A340-200 A340-300

Breakaway Power

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

6-3-2

Page 1Apr 01/13

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**ON A/C A340-200 A340-300

AREA

A 210−145(338−233)

B145−105

(233−169)

C

D 65−20(105−32)

105−65(169−105)









ENTRYCORRIDOR

EXHAUST WAKE DANGERAREA 65 Mph (105 km/h)OR GREATER

EXHAUST WAKE DANGERAREA 65 Mph (105 km/h)OR LESS

RADIUS = 13.9 ft(4.2 m)

NOT TO SCALE

NO ENTRY 198 ft (60 m)AFT OF NOZZLE EXIT

TO 750 ft (229 m)

A

B

C

D

E



EXHAUST DANGER AREASINCLUDE (WORST CASE):

GROUND PLANE PROXIMITYHEADWIND (20 kts)



214 ft (65 m)

WIDTH

6.3 ft(1.9 m)

F_AC_060302_1_0040101_01_02


FIGURE-6-3-2-991-004-A01

6-3-2

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6-3-3 Takeoff Power

**ON A/C A340-200 A340-300

Takeoff Power

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

6-3-3

Page 1Apr 01/13

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**ON A/C A340-200 A340-300

RADIUS = 34 ft

NOT TO SCALE

13.4 ft

AREA

A 210−145(338−233)

B 145−105(233−169)

C

D65−20

(105−32)

105−65(169−105)



ENTRYCORRIDOR

EXHAUST WAKE DANGERAREA, 65 mph (105 km/h)OR LESS




EXHAUST WAKE DANGERAREA, 65 mph (105 km/h)OR GREATER




GMM−1137913−00−B

A

B

C

D

295 ft (90 m)

TO 1460 ft (445 m)

WIDTH

E

(10.4 m)

(4.1 m)

NO ENTRY 830 ft (253 m)AFT OF NOZZLE EXIT



EXHAUST DANGER AREASINCLUDE (WORST CASE):

GROUND PLANE PROXIMITYHEADWIND (20 kts)



F_AC_060303_1_0040101_01_01


FIGURE-6-3-3-991-004-A01

6-3-3

Page 2Apr 01/13

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6-4-0 APU Exhaust Velocities and Temperatures

**ON A/C A340-200 A340-300

APU Exhaust Velocities and Temperatures

1. APU Exhaust Velocities and Temperatures.

6-4-0

Page 1Apr 01/13

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6-4-1 APU

**ON A/C A340-200 A340-300

APU - GARRETT

1. This section gives APU exhaust velocities and temperatures.

6-4-1

Page 1Apr 01/13

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**ON A/C A340-200 A340-300

F_AC_060401_1_0020101_01_00

20METERS

0

5 10 15

FEET

0

10 20 30 40 50

0

60

0

10

5

10

20

30

40

METERS FEET

20

METERS

FD

0

5 10 15

FEET

0

10 20 30 40 50

0

60

0

10

5

10

20

30

40

METERS FEET

121°C

93°C

204°C260°C

315.5°C

427°C

15 m/s

18 m/s

24 m/s

FD

149°C

177°C

61 m/s46 m/s

30.5 m/s

Exhaust Velocities and TemperaturesGARRETT GTCP 331-350

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

6-4-1

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PAVEMENT DATA



1. General Information

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

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

All curves on the charts represent data at a constant specified tire pressure with :

- The aircraft loaded to the Maximum Ramp Weight (MRW),- The CG at its maximum permissible aft position.

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

Landing Gear FootprintSection 7-2-0 presents basic data on the landing gear footprint configuration, MRW and tire sizes andpressures.

Maximum Pavement Loads

Section 7-3-0 shows the maximum vertical and horizontal pavement loads for certain criticalconditions at the tire-ground interfaces.

Landing Gear Loading on PavementSection 7-4-0 contains charts to find these loads throughout the stability limits of the aircraft at reston the pavement.These MLG loads are used as the point of entry to the pavement design charts, which follow,interpolating load values where necessary.

Flexible Pavement Requirements - US Army Corps of Engineers Design MethodSection 7-5-0 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-PCNMethod), and utilizing the alpha factors approved by ICAO in October 2007.The report was prepared by the U.S. Army Corps Engineers Waterways Experiment Station, Soils andPavement Laboratory, Vicksburg, Mississippi”. The line showing 10 000 coverages is used to calculateAircraft Classification Number (ACN).

7-1-0

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Flexible Pavement Requirements - LCN Conversion MethodThe flexible pavement charts in Section 7-6-0 show Load Classification Number (LCN) againstequivalent single wheel load (ESWL), and ESWL against pavement thickness.

All LCN curves shown in ’Flexible Pavement Requirements’ were developed from a computer programbased on data in International Civil Aviation Organization (ICAO) document 7920-AN/865/2,Aerodrome manual, Part 2, ”Aerodrome Physical Characteristics”, Second Edition, 1965.

Rigid Pavement Requirements - PCA (Portland Cement Association) Design MethodSection 7-7-0 gives the rigid pavement design curves that have been prepared with the use of theWestergaard Equation.This is in general accordance with the procedures outlined in the Portland Cement Associationpublications, ”Design of Concrete Airport Pavement”, 1973 and ”Computer Program for AirportPavement Design”, (Program PDILB), 1967 both by Robert G. Packard.

Rigid Pavement Requirements - LCN ConversionSection 7-8-0 gives data about the rigid pavement requirements for the LCN Conversion.- For the radius of relative stiffness,- For the radius of relative stiffness (other values of E and µ).All LCN curves shown in Rigid Pavement Requirements - LCN conversion - were developed from acomputer program based on data in International Civil Aviation Organization (ICAO) document 7920AN/865/2, Aerodrome manual, Part 2, ”Aerodrome Physical Characteristics”, Second Edition, 1965.Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness.The rigid pavement charts show LCN against ESWL, and ESWL against radius of relative stiffness.Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness (other values of E and

µ)The rigid pavement charts show LCN against ESWL and ESWL against radius of relative stiffnessaffected by the other values of E and µ.ACN/PCN Reporting SystemSection 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 aircraft/pavement rating systemreplacing the various S, T, TT, LCN, AUW, ISWL, etc... rating systems used throughout the world.ACN is the Aircraft Classification Number and PCN is the corresponding Pavement ClassificationNumber.

An aircraft having an ACN 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 the system uses PCA program PDILB for rigid pavements and S-77-1for flexible pavements to calculate ACN values.

7-1-0

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

PCN

PAVEMENTTYPE

SUBGRADECATEGORY

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 7-9-0 shows the aircraft ACN values.For flexible pavements, the four subgrade categories are :

- A. High Strength CBR 15

- B. Medium Strength CBR 10

- C. Low Strength CBR 6

- D. Ultra Low Strength CBR 3

For rigid pavements, the four subgrade categories are :

- A. High StrengthSubgrade k

= 150 MN/m3 (550 pci

- B. Medium StrengthSubgrade k

= 80 MN/m3 (300 pci)

- C. Low StrengthSubgrade k

= 40 MN/m3 (150 pci)

- D. Ultra Low StrengthSubgrade k

= 20 MN/m3 (75 pci)

7-1-0

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7-2-0 Landing Gear Footprint

**ON A/C A340-200 A340-300

Landing Gear Footprint

1. This section gives data about the landing gear footprint in relation with the aircraft MRW and tiresizes and pressures.The landing gear footprint information is given for all the aircraft operational weight variants.

7-2-0

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**ON A/C A340-300

0 . 7 1 0 m

( 2 . 3 2 9 f t )

2 5 . 3 7 5 m

( 8 3 . 2 5 1 f t )

2 6 . 3 7 2 m

( 8 6 . 5 2 2 f t )

1 0 . 6 8 4 m

( 3 5 . 0 5 2 f t )

0 . 9 6 5 m

( 3 . 1 6 6 f t )

1 . 3 9 7 m

( 4 . 5 8 3 f t )

1 . 9 8 1 m

( 6

. 4 9 9 f t )

C E N T R A L G E A R

T I R E S I Z E

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 0 . 9 b a r

( 1 5 8 p s i )

C E N T R A L

G E A R

T I R E

P

R E S S U R E

W

E I G H T

M A X I M U M

P E R C E N T A G E

N O S E

M A I N G E A R T

I R E

M A I N G E A R

R A M P

W E I G H T

O F W E I G H T

O N M A I N

G E A R G R O U P

G E A R T I R E

P R E S S U R E

S I Z E

T I R E

P R E S S U R E

V A R I A N T

A 3 4 0 − 3 0 0

W V 0 0 1

2 5 7 9 0 0 k g

( 5 6 8 5 7 5 l b )

9 4 . 7 %

1 1 . 6 b a r

( 1 6 8 p s i )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

A 3 4 0 − 3 0 0

W V 0 0 2

A 3 4 0 − 3 0 0

W V 0 0 3

A 3 4 0 − 3 0 0

W V 0 0 4

1 3 . 2 b a r

( 1 9 1 p s i )

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

N

O S E G E A R

T I R E S I Z E

1

0 5 0 x 3 9 5 R 1 6

A 3 4 0 − 3 0 0

W V 0 2 0

1

0 5 0 x 3 9 5 R 1 6

2 6 0 9 0 0 k g

( 5 7 5 1 7 5 l b )

9 3 . 8 %

1 1 . 6 b a r

( 1 6 8 p s i )

1 3 . 2 b a r

( 1 9 1 p s i )

2 5 7 9 0 0 k g

( 5 6 8 5 7 5 l b )

9 4 . 7 %

1 1 . 6 b a r

( 1 6 8 p s i )

1 3 . 2 b a r

( 1 9 1 p s i )

2 6 0 9 0 0 k g

( 5 7 5 1 7 5 l b )

9 3 . 8 %

1 1 . 6 b a r

( 1 6 8 p s i )

1 3 . 2 b a r

( 1 9 1 p s i )

2 7 1 9 0 0 k g

( 5 9 9 4 2 5 l b )

9 4 . 6 %

1 2 . 1 b a r

( 1 7 5 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

F_AC_070200_1_0290101_01_03

Landing Gear Footprint(Sheet 1 of 2)

FIGURE-7-2-0-991-029-A01

7-2-0

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**ON A/C A340-300


T I R E S I Z E

C E N T R A L

G E A R

T I R E

P

R E S S U R E

W

E I G H T

M A X I M U M

P E R C E N T A G E

N O S E

M A I N G E A R T

I R E

M A I N G E A R

R A M P

W E I G H T

O F W E I G H T

O N M A I N

G E A R G R O U P

G E A R T I R E

P R E S S U R E

S I Z E

T I R E

P R E S S U R E

V A R I A N T

N

O S E G E A R

T I R E S I Z E

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

A 3 4 0 − 3 0 0

W V 0 2 6

A 3 4 0 − 3 0 0

W V 0 2 7

A 3 4 0 − 3 0 0

W V 0 2 8

A 3 4 0 − 3 0 0

W V 0 2 9

A 3 4 0 − 3 0 0

W V 0 5 0

2 7 5 9 0 0 k g

( 6 0 8 2 5 0 l b )

9 4 . 6 %

1 2 . 1 b a r

( 1 7 5 p s i )

A 3 4 0 − 3 0 0

W V 0 5 1

2 7 1 9 0 0 k g

( 5 9 9 4 2 5 l b )

9 4 . 6 %

1 2 . 1 b a r

( 1 7 5 p s i )

A 3 4 0 − 3 0 0

W V 0 5 2

2 7 7 4 0 0 k g

( 6 1 1 5 5 0 l b )

9 3 . 8 %

1 2 . 1 b a r

( 1 7 5 p s i )

A 3 4 0 − 3 0 0

W V 0 5 3

2 6 0 9 0 0 k g

( 5 7 5 1 7 5 l b )

9 4 . 7 %

1 2 . 1 b a r

( 1 7 5 p s i )

A 3 4 0 − 3 0 0

W V 0 5 4

2 7 5 9 0 0 k g

( 6 0 8 2 5 0 l b )

9 4 . 6 %

1 2 . 1 b a r

( 1 7 5 p s i )

2 7 5 9 0 0 k g

( 6 0 8 2 5 0 l b )

9 4 . 6 %

2 7 7 4 0 0 k g

( 6 1 1 5 5 0 l b )

9 3 . 8 %

2 7 7 4 0 0 k g

( 6 1 1 5 5 0 l b )

9 3 . 8 %

2 7 5 9 0 0 k g

( 6 0 8 2 5 0 l b )

9 4 . 6 %

1 2 . 1 b a r

( 1 7 5 p s i )

1 2 . 1 b a r

( 1 7 5 p s i )

1 2 . 1 b a r

( 1 7 5 p s i )

1 2 . 1 b a r

( 1 7 5 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1

0 5 0 x 3 9 5 R 1 6

A 3 4 0 − 3 0 0

W V 0 2 5

2 6 0 9 0 0 k g

( 5 7 5 1 7 5 l b )

9 4 . 7 %

1 2 . 1 b a r

( 1 7 5 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

A 3 4 0 − 3 0 0

W V 0 2 1

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

1

0 5 0 x 3 9 5 R 1 6

A 3 4 0 − 3 0 0

W V 0 2 3

A 3 4 0 − 3 0 0

W V 0 2 4

A 3 4 0 − 3 0 0

W V 0 2 5

2 7 5 9 0 0 k g

( 6 0 8 2 5 0 l b )

9 4 . 6 %

1 2 . 1 b a r

( 1 7 5 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

2 6 2 9 0 0 k g

( 5 7 9 6 0 0 l b )

9 4 . 7 %

1 2 . 1 b a r

( 1 7 5 p s i )

2 7 5 9 0 0 k g

( 6 0 8 2 5 0 l b )

9 4 . 6 %

1 2 . 1 b a r

( 1 7 5 p s i )

2 6 0 9 0 0 k g

( 5 7 5 1 7 5 l b )

9 4 . 7 %

1 2 . 1 b a r

( 1 7 5 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

( C G

3 8 . 0 2 % )

( C

G 3 8 % )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

F_AC_070200_1_0300101_01_03F_AC_070200_1_0290102_01_00

Landing Gear Footprint(Sheet 2 of 2)

FIGURE-7-2-0-991-029-A01

7-2-0

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**ON A/C A340-200

0 . 7 1 0 m

( 2 . 3 2 9 f t )

2 3 . 2 4 1 m

( 7 6 . 2 4 9 f t )

2 4 . 2 3 5 m

( 7 9 . 5 1 0 f t )

1 0 . 6 8 4 m

( 3 5 . 0 5 2 f t )

0 . 9 6 5 m

( 3 . 1 6 6 f t )

1 . 3 9 7 m

( 4 . 5 8 3 f t )

1 . 9 8 1 m

( 6

. 4 9 9 f t )


T I R E S I Z E

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 0 . 3 b a r

( 1 4 9 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

1 0 . 9 b a r

( 1 5 8 p s i )

C

E N T R A L

G E A R

T I R E

P R E S S U R E

1 0 . 9 b a r

( 1 5 8 p s i )

W E I G H T

M A X I M U M

P E R C E N T A G E

N O S E G E A R

M A I N G E A R T I R E

M A I N G E A R

R A M P

W E I G H T

O F W E I G H T

O N M A I N

G E A R G R O U P

T I R E

P R E S S U R E

S I Z E

T I R E

P R E S S U R E

V A

R I A N T

A 3 4 0 − 2 0 0

W

V 0 0 0

2 5 4 4 0 0 k g

( 5 6 0 8 5 0 l b )

9 3 . 8 %

1 1 . 4 b a r

( 1 6 5 p s i )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b

i a s )

A 3 4 0 − 2 0 0

W

V 0 0 1

2 5 7 9 0 0 k g

( 5 6 8 5 7 5 l b )

9 3 . 7 %

1 1 . 6 b a r

( 1 6 8 p s i )

A 3 4 0 − 2 0 0

W

V 0 0 2

2 6 0 9 0 0 k g

( 5 7 5 1 7 5 l b )

9 3 . 7 %

1 1 . 6 b a r

( 1 6 8 p s i )

A 3 4 0 − 2 0 0

W

V 0 2 1

2 7 5 9 0 0 k g

( 6 0 8 2 5 0 l b )

9 3 . 6 %

1 3 . 1 b a r

( 1 9 0 p s i )

1 3 b a r

( 1 8 9 p s i )

1 3 . 2 b a r

( 1 9 1 p s i )

1 3 . 2 b a r

( 1 9 1 p s i )

1 4 . 2 b a r

( 2 0 6 p s i )

1 0

5 0 x 3 9 5 R 1 6

1 0

5 0 x 3 9 5 R 1 6

1 0

5 0 x 3 9 5 R 1 6

N

O S E G E A R

T I R E S I Z E

1 0

5 0 x 3 9 5 R 1 6

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b

i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b

i a s )

1 4 0 0 x 5 3 0 R 2 3 O R

5 4 x 2 1 − 2 3 ( b i a s )

1 4 0 0 x 5 3 0 R 2 3

O R

5 4 x 2 1 − 2 3 ( b

i a s )

F_AC_070200_1_0380101_01_02

Landing Gear FootprintFIGURE-7-2-0-991-038-A01

7-2-0

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7-3-0 Maximum Pavement Loads

**ON A/C A340-200 A340-300

Maximum Pavement Loads

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

7-3-0

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**ON A/C A340-300

V ( M G )

M A X I M U M V E R T I C A L N O S E G E A R G R O U N D L O

A D A T M O S T F O R W A R D C G

V ( N G ) M A X I M U M V E R T I C A L M A I N G E A R G R O U N D L O A D A T M O S T A F T C G

V ( N G )

H

M A X I M U M H O R I Z O N T A L G R O U N D L O A D F R O M

B R A K I N G

V ( C G ) M A X I M U M V E R T I C A L C E N T E R G E A R G R O U N D

L O A D A T M O S T A F T C G

V ( M G )

H

V ( C G )

1

2

3

4

5

7

V N G

V M G ( P E R S T R U T )

H ( P E R S T R U T )

M O D E L

M A X I M U M

R A M P

S T A T I C L O A D A T

M O S T F W D C . G .

B R A K I N G

@ 1

0 f t / s

D E C E L E R A T I O N


M A X A F T C . G .

B R A K I N G

@ 1

0 f t / s


I N S T A N T A N E O U S

B R A

K I N G

C O E F F I C

I E N T = 0 . 8

W E I G H T

6

V C G (

P E R S T R U T )

S T A T

I C L O A D A T

M A X

A F T C . G .

A

T

S T A T I C

S T E A D Y

A 3 4 0 − 3 0 0

W

V 0 0 0

( 5 6 0 8 5 0 l b ) ( 5 6 3 7 5 l b )

( 8 3 9 2 5 l b )

( 2 2 0 9 7 5 l b )

( 8 7 1 5 0 l b )

M A C

M A C

( 8 9 3 0

0 l b )

( 1 7 6 7 7 5 l b )

2 5 4 4 0 0 k g

2 5 5 7 0 k g

3 8 0 7 0 k g

1 0 0 2 3 0 k g

3 9 5 3 0 k g

1 8 %

3 8 . 1 8 %

4 0 5 1

0 k g

8 0 1

8 0 k g

M A C

3 8 . 1 8 %

( a )

A 3 4 0 − 3 0 0

A 3 4 0 − 3 0 0

A 3 4 0 − 3 0 0

A 3 4 0 − 3 0 0

A 3 4 0 − 3 0 0

A 3 4 0 − 3 0 0

W

V 0 0 1

( 5 6 8 5 7 5 l b ) ( 5 6 3 7 5 l b )

( 8 3 8 7 5 l b )

( 2 2 4 1 0 0 l b )

( 8 8 3 5 0 l b )

M A C

( 9 0 2 0

0 l b )

( 1 7 9 2 7 5 l b )

2 5 7 9 0 0 k g

2 5 5 7 0 k g

3 8 0 5 0 k g

1 0 1 6 4 0 k g

4 0 0 8 0 k g

3 8 . 0 5 %

4 0 9 1

0 k g

8 1 3

2 0 k g

W

V 0 0 2

( 5 7 5 1 7 5 l b ) ( 5 6 3 7 5 l b )

( 8 3 7 2 5 l b )

( 2 2 4 8 2 5 l b )

( 8 9 3 7 5 l b )

M A C

( 9 0 0 5

0 l b )

( 1 7 9 8 7 5 l b )

2 6 0 9 0 0 k g

2 5 5 7 0 k g

3 7 9 8 0 k g

1 0 1 9 8 0 k g

4 0 5 5 0 k g

3 5 %

4 0 8 5

0 k g

8 1 5

9 0 k g

W

V 0 0 3

( 5 6 8 5 7 5 l b ) ( 5 6 3 7 5 l b )

( 8 3 8 7 5 l b )

( 2 2 4 1 0 0 l b )

( 8 8 3 5 0 l b )

M A C

( 9 0 2 0

0 l b )

( 1 7 9 2 7 5 l b )

2 5 7 9 0 0 k g

2 5 5 7 0 k g

3 8 0 5 0 k g

1 0 1 6 4 0 k g

4 0 0 8 0 k g

3 8 . 0 5 %

4 0 9 1

0 k g

8 1 3

2 0 k g

W

V 0 0 4

( 5 7 5 1 7 5 l b ) ( 5 6 3 7 5 l b )

( 8 4 0 2 5 l b )

( 2 2 4 8 2 5 l b )

( 8 9 3 7 5 l b )

M A C

( 9 0 0 5

0 l b )

( 1 7 9 8 7 5 l b )

2 6 0 9 0 0 k g

2 5 5 7 0 k g

3 8 1 1 0 k g

1 0 1 9 8 0 k g

4 0 5 5 0 k g

3 5 %

4 0 8 5

0 k g

8 1 5

9 0 k g

W

V 0 2 0

( 5 9 9 4 2 5 l b ) ( 6 0 5 7 5 l b )

( 9 3 0 7 5 l b )

( 2 3 7 4 5 0 l b )

( 9 3 1 5 0 l b )

M A C

( 9 2 1 5

0 l b )

( 1 8 9 9 5 0 l b )

2 7 1 9 0 0 k g

2 7 4 8 0 k g

4 2 2 2 0 k g

1 0 7 7 0 0 k g

4 2 2 5 0 k g

3 7 . 6 3 %

4 1 8 0

0 k g

8 6 1

6 0 k g

W

V 0 2 1

( 6 0 8 2 5 0 l b ) ( 6 0 7 5 0 l b )

( 9 3 6 7 5 l b )

( 2 4 1 3 0 0 l b )

( 9 4 5 2 5 l b )

M A C

( 9 2 5 7

5 l b )

( 1 9 3 0 5 0 l b )

2 7 5 9 0 0 k g

2 7 5 5 0 k g

4 2 4 9 0 k g

1 0 9 4 6 0 k g

4 2 8 8 0 k g

3 7 . 5 %

4 1 9 9

0 k g

8 7 5

7 0 k g

M A C

3 8 . 0 5 %

( a )

M A C

3 5 %

( a )

M A C

3 8 . 0 5 %

( a )

M A C

3 5 %

( a )

M A C

3 7 . 6 3 %

( a )

M A C

3 7 . 5 %

( a )

( b )

M A C

1 8 %

( b )

M A C

1 8 %

( b )

M A C

1 8 %

( b )

M A C

1 8 %

( b )

M A C

2 1 . 5 %

( a )

M A C

2 1 . 9 %

( a )

N O

T E :

( a ) L O A D S C A L C U L A T E D U S I N G A I R C R A F T A T M R W

( b ) L O A D S C A L C U L A T E D U S I N G A I R C R A F T A T 2 3 1 0 0 0 k g ( 5 0 9 2 6 7 l b )

F_AC_070300_1_0070101_01_04

Maximum Pavement Loads(Sheet 1 of 2)

FIGURE-7-3-0-991-007-A01

7-3-0

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7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

V ( M G )

M A X I M U M V E R T I C A L N O S E G E A R G R O U N D L O

A D A T M O S T F O R W A R D C G

V ( N G ) M A X I M U M V E R T I C A L M A I N G E A R G R O U N D L O A D A T M O S T A F T C G

V ( N G )

V ( M G )

H

1

2

3

4

5

7

V N G

V M G ( P E R S T R U T )

H ( P E R S T R U T )

M O D E L

M A X I M U M

R A M P


M O S T F W D C . G .

B R A K I N G

@ 1

0 f t / s



M A X A F T C . G .

B R A K I N G

@ 1

0 f t / s


I N S T A N T A N E O U S

B R A

K I N G

C O E F F I C

I E N T = 0 . 8

W E I G H T

6

V C G (

P E R S T R U T )

S T A T

I C L O A D A T

M A X

A F T C . G .

A

T

H

M A X I M U M H O R I Z O N T A L G R O U N D L O A D F R O M

B R A K I N G

V ( C G ) M A X I M U M V E R T I C A L C E N T E R G E A R G R O U N D

L O A D A T M O S T A F T C G

S T A T I C

S T E A D Y

A 3 4 0 − 2 0 0

W

V 0 0 0

2 5 4 4 0 0 k g

( 5 6 0 8 5 0 l b )

2 7 3 3 0 k g

( 6 0 2 5 0 l b )

4 0 7 3 0 k g

( 8 9 8 0 0 l b )

9 9 4 1 0 k g

( 2 1 9 1 5 0 l b )

3 9 7 0

0 k g

( 8 7 5 2

5 l b )

3 9 5 3 0 k g

( 8 7 1 5 0 l b )

2 0 %

M A C

3 7 . 7 %

M A C

A 3 4 0 − 2 0 0

W

V 0 0 1

2 5 7 9 0 0 k g

( 5 6 8 5 7 5 l b )

2 7 3 3 0 k g

( 6 0 2 5 0 l b )

4 0 7 2 0 k g

( 8 9 7 7 5 l b )

1 0 0 7 3 0 k g

( 2 2 2 0 7 5 l b )

4 0 2 4

0 k g

( 8 8 7 2

5 l b )

4 0 0 8 0 k g

( 8 8 3 5 0 l b )

2 0 %

M A C

3 7 . 6

M A C

A 3 4 0 − 2 0 0

W

V 0 0 2

2 6 0 9 0 0 k g

( 5 7 5 1 7 5 l b )

2 7 3 3 0 k g

( 6 0 2 5 0 l b )

4 0 7 0 0 k g

( 8 9 7 2 5 l b )

1 0 1 9 5 0 k g

( 2 2 4 7 7 5 l b )

4 0 5 5

0 k g

( 8 9 4 0

0 l b )

4 0 5 5 0 k g

( 8 9 3 7 5 l b )

2 0 %

M A C

3 7 . 5 %

M A C

A 3 4 0 − 2 0 0

W

V 0 2 1

2 7 5 9 0 0 k g

( 6 0 8 2 5 0 l b )

3 0 0 3 0 k g

( 6 6 2 0 0 l b )

4 6 2 1 0 k g

( 1 0 1 8 7 5 l b )

1 0 8 2 2 0 k g

( 2 3 8 5 7 5 l b )

4 1 6 9

0 k g

( 9 1 9 0

0 l b )

4 2 8 8 0 k g

( 9 4 5 2 5 l b )

2 3 . 7 %

M A C

3 7 %

M A C

7 9 5

3 0 k g

( 1 7 5

3 2 5 l b )

8 0 5

9 0 k g

( 1 7 7

6 7 5 l b )

8 1 5

6 0 k g

( 1 7 9

8 0 0 l b )

8 6 5

8 0 k g

( 1 9 0

8 7 5 l b )

3 7 . 7 %

M A C

3 7 . 6 %

M A C

3 7 . 5 %

M A C

3 7 %

M A C

V ( C G )

( a )

( a )

( a )

( a )

( a )

( b )

( b )

( b )

N O T E :

( a )

L O A D S C A L C U L A T E D U S I N G A I R C R A F T

A T M R W

( b )

L O A D S C A L C U L A T E D U S I N G A I R C R A F T

A T 2 2 7 0 0 0 k g ( 5 0 0 4 4 8 l b )

F_AC_070300_1_0090101_01_03

Maximum Pavement LoadsFIGURE-7-3-0-991-009-A01

7-3-0

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7-4-0 Landing Gear Loading on Pavement

**ON A/C A340-200 A340-300

Landing Gear Loading on Pavement

1. This section gives data about the landing gear loading on pavement.The MLG loading on pavement graphs are given for the lowest and the highest MRW of each type ofaircraft.

2. MLG Loading on PavementExample, see FIGURE 7---0-99--005-A (sheet 1), calculation of the total weight on the MLG for:- An aircraft with a MRW of 254 400 kg (560 850 lb),- The aircraft gross weight is 200 000 kg (440 925 lb).- A percentage of weight on MLG of 93,8% (percentage of weight on MLG at MRW and CG max

aft).The total weight on the MLG group is 187 510 kg (413 400 lb).

3. Main Gear and Center Gear Loading on PavementThe MLG Group consists of two main gears (4 wheel bogies) plus one center gear (2 wheels).

Example, see FIGURE 7---0-99--005-A (sheet 2), calculation of the total weight on the MLG for:- An aircraft with a MRW of 254 400 kg (560 850 lb),- The aircraft gross weight is 200 000 kg (440 925 lb).The load on the two main gears is 162 875 kg (359 100 lb) and the load on the center gear is 25 050kg (55 200 lb).The total weight on the MLG group is 187 510 kg (413 400 lb).

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

7-4-0

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**ON A/C A340-200

110

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

84 86 88 90 92 94 96 98 100

( x 1 0 0 0 K g )

W E I G H T O N M A I N L A N D I N G G E A R ( x 1 0 0 0 K g )

PERCENTAGE OF WEIGHT ON MAIN GEAR

250

300

350

400

450

500

550

600

( x 1 0 0 0 l b )

110

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280


CG FOR ACNCALCULATION

37.7% MAC

MTOW − 253 500 kg

24.2% MAC

MLW

MZFW

LANDING

TAKE OFF

F_AC_070400_1_0050101_01_00

Landing Gear Loading on PavementWV000, MRW 254 400 kg (Sheet 1 of 2)

FIGURE-7-4-0-991-005-A01

7-4-0

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7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

1 0 0

2 0 0

3 0 0

4 0 0

5 0 0

3 0 0

2 8 0

2 6 0

2 4 0

2 2 0

2 0 0

1 8 0

1 6 0

1 4 0

1 2 0

1 0 0

0 2 0

4 0

6 0

8 0

1 0 0

1 2 0

1 4 0

1 6 0

1 8 0

2 0 0

2 2 0

2 4 0

3 0 0

4 0 0

5 0 0

6 0 0

L O A D O N C E N T E R G E A R O R L O A D O N M A I N G E A R S ( x 1 0 0 0 K g )

A I R C R A F T G R O S S W E I G H T ( x 1 0 0 0 K

g )

( x 1 0 0 0 l b )

M A I N G E A R S

C E N T E R L I N E G E A R

(x 1000 lb)

F_AC_070400_1_0050102_01_00

Landing Gear Loading on PavementWV000, MRW 254 400 kg, CG 37.7 % (Sheet 2 of 2)

FIGURE-7-4-0-991-005-A01

7-4-0

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**ON A/C A340-200

110

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

84 86 88 90 92 94 96 98 100

( x 1 0 0 0 K g )



250

300

350

400

450

500

550

600

( x 1 0 0 0 l b )

110

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280


MTOW − 275 000 kg

TAKE OFF

MZFW


37% MAC

23.7% MAC

MLW

LANDING

F_AC_070400_1_0060101_01_00


FIGURE-7-4-0-991-006-A01

7-4-0

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7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

1 0 0

2 0 0

3 0 0

4 0 0

5 0 0

3 0 0

2 8 0

2 6 0

2 4 0

2 2 0

2 0 0

1 8 0

1 6 0

1 4 0

1 2 0

1 0 0

0 2 0

4 0

6 0

8 0

1 0 0

1 2 0

1 4 0

1 6 0

1 8 0

2 0 0

2 2 0

2 4 0

3 0 0

4 0 0

5 0 0

6 0 0



g )

( x 1 0 0 0 l b )

M A I N G E A R S


(x 1000 lb)

F_AC_070400_1_0060102_01_00

Landing Gear Loading on PavementWV021, MRW 275 900 kg, CG 37 % (Sheet 2 of 2)

FIGURE-7-4-0-991-006-A01

7-4-0

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7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

110

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

84 86 88 90 92 94 96 98 100

( x 1 0 0 0 K g )



250

300

350

400

450

500

550

600

( x 1 0 0 0 l b )

110

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280


CG FOR ACNCALCULATION38.18% MAC

MTOW − 253 500 kg

22% MAC

MLW

MZFW

TAKE OFF

LANDING

F_AC_070400_1_0070101_01_00


FIGURE-7-4-0-991-007-A01

7-4-0

Page 6Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

1 0 0

2 0 0

3 0 0

4 0 0

5 0 0

3 0 0

2 8 0

2 6 0

2 4 0

2 2 0

2 0 0

1 8 0

1 6 0

1 4 0

1 2 0

1 0 0

0 2 0

4 0

6 0

8 0

1 0 0

1 2 0

1 4 0

1 6 0

1 8 0

2 0 0

2 2 0

2 4 0

3 0 0

4 0 0

5 0 0

6 0 0



g )

( x 1 0 0 0 l b )

M A I N G E A R S


(x 1000 lb)

F_AC_070400_1_0070102_01_00

Landing Gear Loading on PavementWV000, MRW 254 400 kg, CG 38.18 % (Sheet 2 of 2)

FIGURE-7-4-0-991-007-A01

7-4-0

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7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

110

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

84 86 88 90 92 94 96 98 100

( x 1 0 0 0 K g )



250

300

350

400

450

500

550

600

( x 1 0 0 0 l b )

110

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280



35% MACMTOW − 276 500 kg

24% MAC

MLW

MZFW

TAKE OFF

LANDING

F_AC_070400_1_0080101_01_00


FIGURE-7-4-0-991-008-A01

7-4-0

Page 8Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

1 0 0

2 0 0

3 0 0

4 0 0

5 0 0

3 0 0

2 8 0

2 6 0

2 4 0

2 2 0

2 0 0

1 8 0

1 6 0

1 4 0

1 2 0

1 0 0

0 2 0

4 0

6 0

8 0

1 0 0

1 2 0

1 4 0

1 6 0

1 8 0

2 0 0

2 2 0

2 4 0

3 0 0

4 0 0

5 0 0

6 0 0



g )

( x 1 0 0 0 l b )

M A I N G

E A R S


(x 1000 lb)

F_AC_070400_1_0080102_01_00

Landing Gear Loading on PavementWV028, MRW 277 400 kg, CG 35 % (Sheet 2 of 2)

FIGURE-7-4-0-991-008-A01

7-4-0

Page 9Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



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

**ON A/C A340-200 A340-300

Flexible Pavement Requirements - US Army Corps of Engineers Design Method S-77-1

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

line is made to show 10 000 coverages,

- A plot is then made of the incremental values of the weight on the MLG,- Annual departure lines are made based on the load lines of the weight on the MLG that is shownon the graph.

Example, see FIGURE 7---0-99--005-A, calculation of the thickness of the flexible pavement for:- An aircraft with a MRW of 254 400 kg (560 850 lb),- A ”CBR” value of 10,- An annual departure level of 3 000,- The load on one MLG of 80 000 kg (176 375 lb).The required flexible pavement thickness is 48.5 cm (19 in).


7-5-0

Page 1Apr 01/13

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**ON A/C A340-200

SUBGRADE STRENGTH − CBR

3 10 15 20 30 40 60 80

FLEXIBLE PAVEMENT THICKNESS

1400x530R23 OR 54x21−23 (bias) TIRES

TIRE PRESSURE CONSTANT AT 13 bar (189 psi)

(cm)

(in)

MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT ANDAFT CG

10 000 COVERAGESUSED FOR ACNCALCULATIONS

6

3 10 15 20 30 40 60 806

10 15 20 30 40 60 80 100 120 150180

50 000 kg (110 225 lb)60 000 kg (132 275 lb)70 000 kg (154 325 lb)80 000 kg (176 375 lb)99 410 kg (219 150 lb)WEIGHT ON ONE MAIN LANDING GEAR

ALPHA FACTOR = 0.8*20 YEAR PAVEMENT LIFE25.00015.0006.000

3.0001.200ANNUAL DEPARTURES*

F_AC_070500_1_0050101_01_00

Flexible Pavement RequirementsWV000, MRW 254 400 kg, CG 37.7 % (Sheet 1 of 2)

FIGURE-7-5-0-991-005-A01

7-5-0

Page 2Apr 01/13

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**ON A/C A340-200


3 10 15 20 30 40 60 80


1400x530R23 OR 54x21−23 (bias) TIRES

TIRE PRESSURE CONSTANT AT 14.2 bar (206 psi)

(cm)

(in)

6

3 10 15 20 30 40 60 806

10 15 20 30 40 60 80 100 120 150180






F_AC_070500_1_0050201_01_00F_AC_070500_1_0050102_01_00

Flexible Pavement RequirementsWV021, MRW 275 900 kg, CG 37 % (Sheet 2 of 2)

FIGURE-7-5-0-991-005-A01

7-5-0

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300


3 10 15 20 30 40 60 80


1400x530R23 OR 54x21−23 (bias) TIRES


(cm)

(in)

6

3 10 15 20 30 40 60 806

10 15 20 30 40 60 80 100 120 150180






F_AC_070500_1_0060101_01_00

Flexible Pavement RequirementsWV000, MRW 254 400 kg, CG 38.18 % (Sheet 1 of 2)

FIGURE-7-5-0-991-006-A01

7-5-0

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300


3 10 15 20 30 40 60 80


1400x530R23 OR 54x21−23 (bias) TIRES


(cm)

(in)

6

3 10 15 20 30 40 60 806

10 15 20 30 40 60 80 100 120 150180






F_AC_070500_1_0060201_01_00F_AC_070500_1_0060102_01_00

Flexible Pavement RequirementsWV028, MRW 277 400 kg, CG 35 % (Sheet 2 of 2)

FIGURE-7-5-0-991-006-A01

7-5-0

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



7-6-0 Flexible Pavement Requirements - LCN Conversion

**ON A/C A340-200 A340-300

Flexible Pavement Requirements - LCN Conversion

1. This section gives data about the flexible pavement requirements for Load Classification Number(LCN) conversion.The flexible pavement requirements graphs are given for the lowest and the highest MRW of eachtype of aircraft.To find the aircraft weight that a flexible pavement can support, you must know the LCN of thepavement and the thickness.

Example, see FIGURE 7---0-99--004-A, calculation of the thickness of the flexible pavement for:- An aircraft with a MRW of 254 400 kg (560 850 lb),- The flexible pavement thickness is 1143 mm (45 in) with a related LCN of 103.

The weight on one MLG is 80 000 kg (176 375 lb).2. Flexible Pavement Requirements - LCN table

The following table provides LCN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1977”. In order to use the system accuratelyyou should know the total pavement thickness for flexible pavement.However, the pavement thickness for a particular runway are not frequently published in the standardairport information sources (Jeppesen, AERAD, DOD, etc.).Therefore it is common practice to use a standard thickness (20 in) when determining the LCN andthe ESWL of the aircraft.

If the LCN for an intermediate weight between MRW and the empty weight of the aircraft is requiredor if the real thickness is known, refer to figures that follow.


7-6-0

Page 1Apr 01/13

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**ON A/C A340-200

AIRCRAFT TYPE

A340−200WV000

ALL UPMASS (kg)

LOAD ONONE MAINGEAR LEG

(%)

TIREPRESSURE

(Mpa)

FLEXIBLE PAVEMENT

ESWL

x 1000 kg

h = 510 mm (20 in)

x 1000 lbLCN

254 400130 000

39.146.1

1.30 2515

5633

8454

WV001

WV002

WV021

A340−200

A340−200

A340−200

257 900130 000

39.146.1

1.32 2615

5733

8554

260 900130 000

39.146.1

1.32 2615

5733

8654

275 900130 000

39.246.0

1.42 2815

6133

9557

F_AC_070600_1_0130101_01_00

Flexible Pavement RequirementsLCN table

FIGURE-7-6-0-991-013-A01

7-6-0

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

5 0 0 0 0 k g

( 1 1 0 2 2 5 l b )

6 0 0 0 0 k g

( 1 3 2 2 7 5 l b )

7 0 0 0 0 k g

( 1 5 4 3 2 5 l b )

8 0 0 0 0 k g

( 1 7 6 3 7 5 l b )

9 9 4 1 0 k g

( 2 1 9 1 5 0 l b )

L A N D I N G G E A R

W E I G H T O N O N E M A I N

M A X I M U M P O S S I B L E M A I N

G E A R L O A D A T M A X I M U M

R A M P W E I G H T A N D

A F T C G

1 0

2 0

3 0

4

0

5 0

6 0

8 0

1 0 0

1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 3 0

1 4 0

1 5 0

1 6 0

5 0 0

7 5 0

1 0 0 0

1 5 0 0

2 0 0 0 2 5 0 0

2 0 3 0 4 0 5 0 6 0 7 0

2 0

3 0

4 0

5 0 6 0

8 0

7 0

1 0 0 1 2 0

1 5 0 1 8 0

2 3 0

1 0

F L E X I B L E P A V E M E N T T H

I C K N E S S ( m m )

T I R E P R E S

S U R E C O N S T A N T A T 1 3 b a r ( 1 8 9 p s i )

1 4 0 0 x 5

3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S

F L E X I B L E P A V E M E N T T H I C K N E S S ( i n )

L O A D C L A S S I F I C A T I O N N U M B E R ( L C N )

E Q U I V A L E N T S I N G L E W H E E L L O A D ( 1 0 0 0 l b )

E Q U I V A L E N T S I N

G L E W H E E L L O A D S A R E D E R I V E D B Y M E T H O D S S H O W N I N

I C A O A E R O D R O M

E M A N U A L P A R T 2 P A R 4 . 1 . 3 S E C O N D

E D I T I O N 1 9 6 5

N O T E :

EQUIVALENT SINGLE WHEEL LOAD (1000 kg)

F_AC_070600_1_0040101_01_00

Flexible Pavement Requirements - LCNWV000, MRW 254 400 kg, CG 37.7 % (Sheet 1 of 2)

FIGURE-7-6-0-991-004-A01

7-6-0

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

9 0 0 0 0 k g

( 1 9 8 4 2 5 l b )

1 0 8 2 2 0 k g

( 2 3 8 5 7 5 l b )






A F T C G

1 0

2 0

3 0

4

0

5 0

6 0

8 0

1 0 0

1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 3 0

1 4 0

1 5 0

1 6 0

5 0 0

7 5 0

1 0 0 0

1 5 0 0

2 0 0 0 2 5 0 0

2 0 3 0 4 0 5 0 6 0 7 0

2 0

3 0

4 0

5 0 6 0

8 0

7 0

1 0 0 1 2 0

1 5 0 1 8 0

2 3 0

1 0



T I R E P R E S S U R E C O N S T A N T A T 1 4 . 2 b a r ( 2 0 6 p s i )

1 4 0 0 x 5

3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S






I C A O A E R O D R O M E M A N U A L P A R T 2 P A R 4 . 1 . 3 S E C O N D

E D I T I O N 1 9 6 5

N O T E :

6 0 0 0 0 k g

( 1 3 2 2 7 5 l b )

7 0 0 0 0 k g

( 1 5 4 3 2 5 l b )

8 0 0 0 0 k g

( 1 7 6 3 7 5 l b )


F_AC_070600_1_0040201_01_00F_AC_070600_1_0040102_01_00

Flexible Pavement Requirements - LCNWV021, MRW 275 900 kg, CG 37 % (Sheet 2 of 2)

FIGURE-7-6-0-991-004-A01

7-6-0

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

AIRCRAFT TYPE

A340−300

ALL UPMASS (kg)


(%)

TIREPRESSURE

(Mpa)

FLEXIBLE PAVEMENT

ESWL

x 1000 kg

h = 510 mm (20 in)

x 1000 lbLCN

254 400130 000

39.446.2

1.31 2615WV000

5633

8554

260 900

257 900

260 900

271 900

275 900

262 900

275 900

260 900

260 900

275 900

271 900

277 400

260 900

275 900

275 900

277 400

277 400

275 900

39.446.2

1.32WV001

57 8655

39.146.0

1.32WV002

8654

39.446.2

1.32WV003

8655

39.146.0

1.32WV004

8654

39.646.2 1.42WV020

9457

39.746.2

1.42WV021

9657

39.546.2

1.42WV023

9157

39.746.2

1.42WV024

9657

39.546.2

1.42WV025 (CG 38.02%)

9157

39.546.2

1.42WV025 (CG 38%)

9157

39.746.2WV026

9657

39.646.2WV027

9457

39.446.0WV028

9657

39.546.2WV029

9157

39.746.2WV050

9657

39.746.2WV051

9657

39.446.0WV052

9657

39.446.0WV053

9657

39.746.2WV054

9657

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

257 900

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

26

26

26

26

27

28

26

28

26

26

28

27

28

26

28

28

28

28

28

15

15

15

15

15

15

15

15

15

15

15

15

15

15

15

15

15

15

15

57

57

57

60

62

58

62

57

57

62

60

61

57

62

62

61

61

62

33

33

33

33

33

33

33

33

33

33

33

33

33

33

33

33

33

33

33

F_AC_070600_1_0140101_01_00

Flexible Pavement RequirementsLCN table

FIGURE-7-6-0-991-014-A01

7-6-0

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

9 0 0 0 0 k g

( 1 9 8 4 2 5 l b )

1 0 0 2 3 0 k g

( 2 2 0 9 7 5 l b )






A F T C G

1 0

2 0

3 0

4

0

5 0

6 0

8 0

1 0 0

1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 3 0

1 4 0

1 5 0

1 6 0

5 0 0

7 5 0

1 0 0 0

1 5 0 0

2 0 0 0 2 5 0 0

2 0 3 0 4 0 5 0 6 0 7 0

2 0

3 0

4 0

5 0 6 0

8 0

7 0

1 0 0 1 2 0

1 5 0 1 8 0

2 3 0

1 0




1 4 0 0 x 5

3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S








E D I T I O N 1 9 6 5

N O T E :

6 0 0 0 0 k g

( 1 3 2 2 7 5 l b )

7 0 0 0 0 k g

( 1 5 4 3 2 5 l b )

8 0 0 0 0 k g

( 1 7 6 3 7 5 l b )


F_AC_070600_1_0050101_01_00

Flexible Pavement Requirements - LCNWV000, MRW 254 400 kg, CG 38.18 % (Sheet 1 of 2)

FIGURE-7-6-0-991-005-A01

7-6-0

Page 6Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

9 0 0 0 0 k g

( 1 9 8 4 2 5 l b )

1 0 9 1 9 0 k g

( 2 4 0 7 2 5 l b )






A F T C G

1 0

2 0

3 0

4

0

5 0

6 0

8 0

1 0 0

1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 3 0

1 4 0

1 5 0

1 6 0

5 0 0

7 5 0

1 0 0 0

1 5 0 0

2 0 0 0 2 5 0 0

2 0 3 0 4 0 5 0 6 0 7 0

2 0

3 0

4 0

5 0 6 0

8 0

7 0

1 0 0 1 2 0

1 5 0 1 8 0

2 3 0

1 0




1 4 0 0 x 5

3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S







E D I T I O N 1 9 6 5

N O T E :

6 0 0 0 0 k g

( 1 3 2 2 7 5 l b )

7 0 0 0 0 k g

( 1 5 4 3 2 5 l b )

8 0 0 0 0 k g

( 1 7 6 3 7 5 l b )


F_AC_070600_1_0050201_01_00F_AC_070600_1_0050102_01_00

Flexible Pavement Requirements - LCNWV028, MRW 277 400 kg, CG 35 % (Sheet 2 of 2)

FIGURE-7-6-0-991-005-A01

7-6-0

Page 7Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



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

**ON A/C A340-200 A340-300

Rigid Pavement Requirements - Portland Cement Association Design Method

1. This section gives data about the rigid pavement requirements for the PCA (Portland CementAssociation) design method.The rigid pavement requirements graphs are given for the lowest and the highest MRW of each typeof aircraft.To find a rigid pavement thickness, you must know the Subgrade Modulus (K), the permittedworking stress and the weight on one MLG.The procedure that follows is used to develop rigid pavement design curves:- With the scale for pavement thickness on the left and the scale for permitted working stress on

the right, a random load line is made.This represents the MLG maximum weight to be shown.

- A plot is then made of all values of the subgrade modulus (k values).- More load lines for the incremental values of weight on the MLG are made based on the curve fok= 80MN/m3 already shown on the graph.

Example, see FIGURE 7---0-99--004-A, calculation of the thickness of the rigid pavement for:- An aircraft with a MRW of 254 400 kg (560 850 lb),- A k value of 80 MN/m3 (300 lb/in3).- A permitted working stress of 35.15 kg/cm2 (500 lb/in2).- The load on one MLG is 80 000 kg (176 375 lb).The required rigid pavement thickness is 242 mm (10 in).


7-7-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

1400x530R23 OR 54x21−23 (bias) TIRES

TIRE PRESSURE CONSTANT AT 13 bar (189 psi)

100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8

( k g / c m ² )

A L L O W A B L E W O R K I N G S T R E

S S

( l b / i n ² )

R I G I D P A V E M E N T T H I C K N E S

S

( c m )

( i n )

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

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

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

ASSOCIATION.

8

13

18

23

28

33

38

43

48

53

58

63

60 000 kg (132 275 lb)70 000 kg (154 325 lb)80 000 kg (176 375 lb)99 410 kg (219 150 lb)LANDING GEARWEIGHT ON ONE MAIN

50 000 kg (110 225 lb)

RAMP WEIGHT AND AFT CGGEAR LOAD AT MAXIMUMMAXIMUM POSSIBLE MAIN

K = 150 MN/m³

K = 80 MN/m³

K = 40 MN/m³

K = 20 MN/m³

F_AC_070700_1_0040101_01_00

Rigid Pavement RequirementsWV000, MRW 254 400 kg, CG 37.7 % (Sheet 1 of 2)

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

7-7-0

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

1400x530R23 OR 54x21−23 (bias) TIRES


100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8


S

( c m )

( i n )




ASSOCIATION.

( k g / c m ² )


S S

( l b / i n ² )

8

13

18

23

28

33

38

43

48

53

58

63

K = 150 MN/m³

K = 80 MN/m³

K = 40 MN/m³

K = 20 MN/m³


70 000 kg (154 325 lb)80 000 kg (176 375 lb)90 000 kg (198 425 lb)108 220 kg (238 575 lb)LANDING GEAR

WEIGHT ON ONE MAIN

60 000 kg (132 275 lb)

F_AC_070700_1_0040201_01_00F_AC_070700_1_0040102_01_00

Rigid Pavement RequirementsWV021, MRW 275 900 kg, CG 37 % (Sheet 2 of 2)

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

7-7-0

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

1400x530R23 OR 54x21−23 (bias) TIRES


100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8

( k g / c m ² )


S S

( l b / i n ² )


S

( c m )

( i n )




ASSOCIATION.

8

13

18

23

28

33

38

43

48

53

58

63

K = 150 MN/m³

K = 80 MN/m³

K = 40 MN/m³

K = 20 MN/m³


70 000 kg (154 325 lb)80 000 kg (176 375 lb)90 000 kg (198 425 lb)100 230 kg (220 975 lb)LANDING GEARWEIGHT ON ONE MAIN

60 000 kg (132 275 lb)

F_AC_070700_1_0050101_01_00

Rigid Pavement RequirementsWV000, MRW 254 400 kg, CG 38.18 % (Sheet 1 of 2)

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

7-7-0

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

1400x530R23 OR 54x21−23 (bias) TIRES


100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8


S

( c m )

( i n )




ASSOCIATION.

( k g / c m ² )


S S

( l b / i n ² )

8

13

18

23

28

33

38

43

48

53

58

63

K = 150 MN/m³

K = 80 MN/m³

K = 40 MN/m³

K = 20 MN/m³


70 000 kg (154 325 lb)80 000 kg (176 375 lb)90 000 kg (198 425 lb)109 190 kg (240 725 lb)LANDING GEAR

WEIGHT ON ONE MAIN

60 000 kg (132 275 lb)

F_AC_070700_1_0050201_01_00F_AC_070700_1_0050102_01_00

Rigid Pavement RequirementsWV028, MRW 277 400 kg, CG 35 % (Sheet 2 of 2)

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

7-7-0

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



7-8-0 Rigid Pavement Requirements - LCN Conversion

**ON A/C A340-200 A340-300

Rigid Pavement Requirements - LCN Conversion

1. This section gives data about the rigid pavement requirements for the Load Classification Number(LCN) conversion (radius of relative stiffness).The rigid pavement requirements graphs are given for the lowest and the highest MRW of each typeof aircraft.To find the aircraft weight that a rigid pavement can support, you must know the LCN of thepavement and the radius of relative stiffness (L).The calculation of the radius of relative stiffness (L) is done with the formula and the table given in”Radius of Relative Stiffness” (L values based on Young’s Modulus (E) of 4 000 000 psi andPoisson’s Ratio (µ) of 0.15), see FIGURE 7---0-99--002-A.

Example, see FIGURE 7---0-99--008-AFIGURE 7---0-99--008-B, calculation of the aircraft weightthrough the radius of relative stiffness (L) of the rigid pavement for:- An aircraft with a MRW of 254 400 kg (560 850 lb),- The radius of relative stiffness is shown at 1143 mm (45 in) with a related LCN of 79.The weight on one MLG is 80 000 kg (176 375 lb).

The following table provides LCN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1977”. In order to use the system accuratelyyou should know the total pavement radius of relative stiffness (L-value) for rigid pavement.However, the pavement radius of relative stiffness for a particular runway are not frequently publishedin the standard airport information sources (Jeppesen, AERAD, DOD, etc.).

Therefore it is common practice to use a standard radius of relative stiffness (30 inches) whendetermining the LCN and the ESWL of the aircraft.If the LCN for an intermediate weight between maximum ramp weight and the empty weight of theaircraft is required or if the real thickness is known, refer to figures that follows.

2. Radius of Relative Stiffness (Other values of E and µ)This section gives data about the rigid pavement requirements for the Load Classification Number(LCN) conversion (radius of relative stiffness with other values of E (Young’s modulus) and µ

(Poisson’s ratio).The other values of E and µ have an effect on the radius of relative stiffness value L.The effect of E and µ on the radius of relative stiffness value L is shown in the diagrams of FIGURE

7---0-99--015-A.The table in FIGURE 7---0-99--002-A Radius of Relative Stiffness (L), shows values L based on aYoung’s modulus (E) of 4 000 000 psi and a Poisson’s ratio (µ) of 0.15.To find values L, you must know the values of E and µ.

Example, see FIGURE 7---0-99--015-A, calculation of values L of the rigid pavement for an E of 3000 000 psi.

7-8-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



The ”E” factor is 0.931.The radius of relative stiffness value L is the value found in the table FIGURE 7---0-99--002-Amultiplied by 0.931.


7-8-0

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

AIRCRAFT TYPEALL UP

MASS (kg)


(%)

TIREPRESSURE

(Mpa)

RIGID PAVEMENT

ESWL

x 1000 kg

L = 760 mm (30 in)

x 1000 lbLCN

2414

5231

7951

A340−200WV000

254 400130 000

39.146.1

1.30

WV001

WV002

WV021

A340−200

A340−200

A340−200

257 900130 000

39.146.1

1.32

260 900130 000

39.146.1

1.32

275 900130 000

39.246.0

1.42

14 31 51

14 31 51

14 31 52

24 53 81

24 53 81

26 56 90

F_AC_070800_1_0180101_01_00

Rigid Pavement RequirementsLCN table

FIGURE-7-8-0-991-018-A01

7-8-0

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

AIRCRAFT TYPE

A340−300

ALL UPMASS (kg)


(%)

TIREPRESSURE

(Mpa)

RIGID PAVEMENT

ESWL

x 1000 kg

L = 760 mm (30 in)

x 1000 lbLCN

254 400130 000

39.446.2

1.31WV000

5231

8051

260 900

257 900

260 900

271 900

275 900

262 900

275 900

260 900

260 900

275 900

271 900

277 400

260 900

275 900

275 900

277 400

277 400

275 900

39.446.2

1.32WV001

39.146.0

1.32WV002

39.446.2

1.32WV003

39.146.0

1.32WV004

39.646.2 1.42WV020

39.746.2

1.42WV021

39.546.2

1.42WV023

39.746.2

1.42WV024

39.546.2

1.42WV025 (CG 38.02%)

39.546.2

1.42WV025 (CG 38%)

39.746.2WV026

39.646.2WV027

39.446.0WV028

39.546.2WV029

39.746.2WV050

39.746.2WV051

39.446.0WV052

39.446.0WV053

39.746.2WV054

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

257 900

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

2414

14

14

14

14

14

14

14

14

14

14

14

14

14

14

14

14

14

14

14

24

24

24

25

26

25

26

24

24

26

25

26

24

26

26

26

26

26

24

5331

8151

5331

8151

5331

8151

5331

8151

5631

8953

5731

9053

5431

8753

5731

9053

5431

8653

5431

8653

5731

9053

5631

8953

5731

9052

5431

8653

5731

9053

5731

9053

5731

9052

5731

9052

5731

9053

F_AC_070800_1_0190101_01_00

Rigid Pavement RequirementsLCN table

FIGURE-7-8-0-991-019-A01

7-8-0

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

6.06.57.0

7.5

31.4833.4335.34

37.22

29.3031.1132.89

34.63

26.4728.1129.72

31.29

24.6326.1627.65

29.12

23.3024.7426.15

27.54

22.2623.6424.99

26.32

21.4222.7424.04

25.32

20.7222.0023.25

24.49

19.1320.3121.47

22.618.08.59.09.5

39.0640.8842.6744.43

36.3538.0439.7141.35

32.8534.3735.8837.36

30.5731.9933.3934.77

28.9130.2531.5832.89

27.6228.9130.1731.42

26.5827.8129.0330.23

25.7026.9028.0829.24

23.7424.8425.9327.00

10.010.511.011.5

46.1847.9049.6051.28

38.8340.2841.7143.12

36.1437.4838.8140.13

34.1735.4536.7137.95

32.6533.8735.0736.26

31.4232.5933.7534.89

30.3931.5232.6433.74

28.0629.1130.1431.16

12.012.513.013.5

52.9454.5956.2257.83

49.2750.8052.3253.82

44.5245.9047.2748.63

41.4342.7243.9945.26

39.1840.4041.6142.80

37.4438.6039.7540.89

36.0237.1438.2539.35

34.8435.9236.9938.06

32.1733.1734.1635.14

14.0

14.515.015.5

16.016.517.017.5

55.31

56.7858.2559.70

65.6967.2368.7570.26

61.1362.5663.9865.38

49.98

51.3152.6353.94

46.51

47.7548.9850.20

43.98

45.1646.3247.47

55.2456.5357.8159.08

51.4152.6153.8054.98

48.6249.7550.8852.00

42.02

43.1544.2645.36

40.44

41.5142.5843.64

39.11

40.1541.1942.21

36.12

37.0838.0338.98

46.4547.5448.6149.68

44.7045.7446.7747.80

43.2344.2445.2446.23

39.9240.8541.7842.70

18.019.020.021.0

22.023.024.025.0

71.7674.7377.6680.55

83.4186.2489.0491.81

66.7869.5472.2774.96

77.6380.2682.8685.44

60.3462.8465.3067.74

70.1472.5274.8777.20

56.1558.4860.7763.04

65.2867.4969.6871.84

53.1155.3157.4759.62

61.7363.8365.9067.95

50.7452.8454.9156.96

58.9860.9862.9664.92

48.8250.8452.8454.81

56.7558.6860.5862.46

54.8956.7558.5960.41

47.2249.1751.1053.01

43.6145.4147.1948.95

50.6952.4154.1155.79

d k=75 k=100 k=150 k=200 k=250 k=300 k=350 k=400 k=550

59.43

61.0262.5964.15

42.9744.5746.1647.72

REFERENCE: PORTLAND CEMENT ASSOCIATION

WHERE

=

E

k

d

Ed 4

=

=

=

d

k

= 24.1652 4

RIGID PAVEMENT THICKNESS, (in)

YOUNG’S MODULUS = 4 x 10 psi

RADIUS OF RELATIVE STIFFNESSVALUES IN INCHES

L

SUBGRADE MODULUS, lb/in

= POISSON’S RATIO = 0.15

( )L

12 (1 − ) k

F_AC_070800_1_0020101_01_00

Radius of Relative Stiffness (L)FIGURE-7-8-0-991-002-A01

7-8-0

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

7 5 0

1 0 0 0

1 5 0 0

2 0 0 0

2 5 0 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0 9 0 1 0 0

2 0

3 0

4 0

5 0 6 0 7 0 8 0

1 0 0 1 2 0

1 5 0 1 8 0

2 3 0

1 0

1 5 2 0 2 5 3 0 3 5 4 0 4 5 5 0 5

R A D I U S O F R E L A T I V E S T

I F F N E S S ( m m )

T I R E P R E S S U R E C O N S T A N T A T 1 3 b a r ( 1 8 9 p s i )

1

4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3

R A D I U S O F R E L A T I V E S

T I F F N E S S ( i n )






E D I T I O N 1 9 6 5

N O T E :





A F T C G

5 0 0 0 0 k g

( 1 1 0 2 2 5 l b )

6 0 0 0 0 k g

( 1 3 2 2 7 5 l b )

7 0 0 0 0 k g

( 1 5 4 3 2 5 l b )

8 0 0 0 0 k g

( 1 7 6 3 7 5 l b )

9 9 4 1 0 k g

( 2 1 9 1 5 0 l b )




F_AC_070800_1_0080101_01_00

Rigid Pavement Requirements - LCNWV000, MRW 254 400 kg, CG 37.7 %

FIGURE-7-8-0-991-008-A01

7-8-0

Page 6Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

7 5 0

1 0 0 0

1 5 0 0

2 0 0 0

2 5 0 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0 9 0 1 0 0

2 0

3 0

4 0

5 0 6 0 7 0 8 0

1 0 0 1 2 0

1 5 0 1 8 0

2 3 0

1 0

1 5 2 0 2 5 3 0 3 5 4 0 4 5 5 0 5



T I R E P R E S S

U R E C O N S T A N T A T 1 4 . 2 b a r ( 2 0 6 p s i )

1

4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3








E D I T I O N 1 9 6 5

N O T E :


7 0 0 0 0 k g

( 1 5 4 3 2 5 l b )

8 0 0 0 0 k g

( 1 7 6 3 7 5 l b )

9 0 0 0 0 k g

( 1 9 8 4 2 5 l b )

1 0 8 2 2 0 k g

( 2 3 8 5 7 5 l b )

W E I G H T O N O N E M A I N L A N D

I N G G E A R

6 0 0 0 0 k g

( 1 3 2 2 7 5 l b )




A F T C G


F_AC_070800_1_0080201_01_00

Rigid Pavement Requirements - LCNWV021, MRW 275 900 kg, CG 37 %

FIGURE-7-8-0-991-008-B01

7-8-0

Page 7Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

7 5 0

1 0 0 0

1 5 0 0

2 0 0 0

2 5 0 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0 9 0 1 0 0

2 0

3 0

4 0

5 0 6 0 7 0 8 0

1 0 0 1 2 0

1 5 0 1 8 0

2 3 0

1 0

1 5 2 0 2 5 3 0 3 5 4 0 4 5 5 0 5



T I R E P R E S S


1

4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3








E D I T I O N 1 9 6 5

N O T E :


7 0 0 0 0 k g

( 1 5 4 3 2 5 l b )

8 0 0 0 0 k g

( 1 7 6 3 7 5 l b )

9 0 0 0 0 k g

( 1 9 8 4 2 5 l b )

1 0 0 2 3 0 k g

( 2 2 0 9 7 5 l b )


I N G G E A R

6 0 0 0 0 k g

( 1 3 2 2 7 5 l b )




A F T C G


F_AC_070800_1_0090101_01_00

Rigid Pavement Requirements - LCNWV000, MRW 254 400 kg, CG 38.18 %

FIGURE-7-8-0-991-009-A01

7-8-0

Page 8Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

7 5 0

1 0 0 0

1 5 0 0

2 0 0 0

2 5 0 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0 9 0 1 0 0

2 0

3 0

4 0

5 0 6 0 7 0 8 0

1 0 0 1 2 0

1 5 0 1 8 0

2 3 0

1 0 1 5 2 0 2 5 3 0 3 5 4 0 4 5 5 0 5



T I R E P R E S S


1

4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3







E D I T I O N 1 9 6 5

N O T E :


7 0 0 0 0 k g

( 1 5 4 3 2 5 l b )

8 0 0 0 0 k g

( 1 7 6 3 7 5 l b )

9 0 0 0 0 k g

( 1 9 8 4 2 5 l b )

1 0 9 1 9 0 k g

( 2 4 0 7 2 5 l b )


I N G G E A R

6 0 0 0 0 k g

( 1 3 2 2 7 5 l b )




A F T C G


F_AC_070800_1_0090201_01_00

Rigid Pavement Requirements - LCNWV028, MRW 277 400 kg, CG 35 %

FIGURE-7-8-0-991-009-B01

7-8-0

Page 9Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200 A340-300

0 1 2 3 4 50.80

0.85

0.90

0.95

1.00

1.05

1.10

EFFECT OF E ON

E F A C T O R

0.00 0.05 0.10 0.15 0.20 0.250.995

1.000

1.005

1.010

1.015EFFECT OF

F A C T O R

, POISSON’S RATIO

E, YOUNG’S MODULUS (10 psi)

ON

VALUESL

VALUESL

NOTE: BOTH CURVES ON THIS PAGE ARE USED TO ADJUST THEOF RADIUS OF RELATIVE STIFFNESS ( ) TABLEL

L VALUES

F_AC_070800_1_0150101_01_00

Radius of Relative Stiffness (Effect E and µ ON ”L” values)FIGURE-7-8-0-991-015-A01

7-8-0

Page 10Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



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

**ON A/C A340-200 A340-300

Aircraft Classification Number - Flexible and Rigid Pavements

1. This section gives data about the Aircraft Classification Number (ACN) for an aircraft gross weight inrelation with a subgrade strength value for flexible and rigid pavement.The flexible and rigid pavement requirements graphs are given for the lowest and the highest MRWof each type of aircraft.To find the ACN of an aircraft on flexible and rigid pavement, you must know the aircraft grossweight and the subgrade strength.

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

Example, see FIGURE 7---0-99--014-A (sheet 1), calculation of the ACN for flexible pavement for:- An aircraft with a MRW of 254 400 kg (560 850 lb),- An aircraft gross weight of 200 000 kg (440 925 lb),- A medium subgrade strength (code B).The ACN for flexible pavement is 42.

Example, see FIGURE 7---0-99--014-A (sheet 2), calculation of the ACN for rigid pavement for:- An aircraft with a MRW of 254 400 kg (560 850 lb),- An aircraft gross weight of 200 000 kg (440 925 lb),- A medium subgrade strength (code B).

The ACN for flexible pavement is 40.2. Aircraft Classification Number - ACN table

The table FIGURE 7---0-99--004-A and FIGURE 7---0-99--005-A provide ACN data in tabular formatsimilar to the one used by ICAO in the ”Aerodrome Design Manual Part 3, Pavements - Edition1983”. If the ACN for an intermediate weight between MRW and the minimum weight of the aircraftis required, refer to figures that follows.


7-9-0

Page 1Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

AIRCRAFT TYPEALL UP

MASS (kg)


(%)

TIREPRESSURE

(Mpa)

4528

ACN FOR

High150

RIGID PAVEMENTSUBGRADES − MN/m³

5228

Medium80

6232

Low40

7337

Ultral−low20

5028

ACN FOR

High15

FLEXIBLE PAVEMENTSUBGRADES − CBR

5429

Medium10

6232

Low6

8439

Ultral−low3

A340−200WV000

254 400130 000

39.146.1

1.30

WV001

WV002

WV021

A340−200

A340−200

A340−200

257 900130 000

39.146.1

1.32

260 900130 000

39.146.1

1.32

275 900130 000

39.246.0

1.42

4628

5328

6332

7437

5128

5529

6332

8639

4728

5428

6432

7637

5228

5629

6532

8739

5229

6029

7133

8338

5628

6129

7032

9539

F_AC_070900_1_0040101_01_00

Aircraft Classification NumberACN Table

FIGURE-7-9-0-991-004-A01

7-9-0

Page 2Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

3 0 0

4 0 0

5

0 0

6 0 0

0 1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 0 0

1 5 0

2 0 0

2 5 0

3 0 0

( x 1 0 0 0 k g )


A I R C R A F T C L A S S I F I C A T I O N N U M B E R ( A C N )

( x 1 0 0 0 l b )


1 4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S

S E E S E C

T I O N 7 − 4 − 0

C H A P T E R 1 . S E C O N D E D I T I O N 1 9 8 3 .

I C A O A E R O D R O M E D E S I G N M A N U A L P A R T 3

A C N W A S D E T E R M I N E D A S R E F E R E N C E D I N

A L P H A F A C

T O R = 0 . 8

D − C

B R 3

( U L T R A L O W )

S U B G R A D E

S T R E N G T H

C − C

B R 6

( L O W )

B − C

B R 1 0 ( M E D I U M )

A − C

B R 1 5 ( H I G H )

F_AC_070900_1_0140101_01_00

Aircraft Classification NumberFlexible Pavement - WV000, MRW 254 400 kg, CG 37.7 % (Sheet 1 of 2)

FIGURE-7-9-0-991-014-A01

7-9-0

Page 3Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

3 0 0

4 0 0

5

0 0

6 0 0

0 1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 0 0

1 5 0

2 0 0

2 5 0

3 0 0

( x 1 0 0 0 k g )



( x 1 0 0 0 l b )


1 4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S

S E E S E C

T I O N 7 − 4 − 0




D − K =

2 0 M N / m ³

( U L T R A L O W )

S U B G R A D E S T R E N G T H

C − K =

4 0 M N / m ³

( L O W )

B − K =

8 0 M N / m ³

( M

E D I U M )

A − K = 1 5 0 M N / m ³

( H I G H )

F_AC_070900_1_0140102_01_00

Aircraft Classification NumberRigid Pavement - WV000, MRW 254 400 kg, CG 37.7 % (Sheet 2 of 2)

FIGURE-7-9-0-991-014-A01

7-9-0

Page 4Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

3 0 0

4 0 0

5

0 0

6 0 0

0 1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 0 0

1 5 0

2 0 0

2 5 0

3 0 0

( x 1 0 0 0 k g )



( x 1 0 0 0 l b )


1 4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S

S E E S E C

T I O N 7 − 4 − 0




A L P H A F A C

T O R = 0 . 8

D − C

B R 3

( U L T R A L O W )

S U B G R A D E

S T R E N G T H

C − C

B R 6

( L O W )

B − C

B R 1 0

( M E D I U M )

A − C

B R 1 5

( H I G H )

F_AC_070900_1_0150101_01_00

Aircraft Classification NumberFlexible Pavement - WV021, MRW 275 900 kg, CG 37 % (Sheet 1 of 2)

FIGURE-7-9-0-991-015-A01

7-9-0

Page 5Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

3 0 0

4 0 0

5

0 0

6 0 0

0 1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 0 0

1 5 0

2 0 0

2 5 0

3 0 0

( x 1 0 0 0 k g )



( x 1 0 0 0 l b )


1 4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S

S E E S E C

T I O N 7 − 4 − 0




D − K =

2 0 M N / m

³

( U L T R A L O W )

S U B G R A D E S T R

E N G T H

C − K =

4 0 M N / m

³

( L O W )

B − K =

8 0 M N / m

³

( M E D I U M )

A − K = 1 5 0 M N / m

³

( H I G H )

F_AC_070900_1_0150102_01_00

Aircraft Classification NumberRigid Pavement - WV021, MRW 275 900 kg, CG 37 % (Sheet 2 of 2)

FIGURE-7-9-0-991-015-A01

7-9-0

Page 6Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

AIRCRAFT TYPEALL UP

MASS (kg)


(%)

TIREPRESSURE

(Mpa)

4628

ACN FOR

High150

RIGID PAVEMENTSUBGRADES − MN/m³

5328

Medium80

6332

Low40

7437

Ultral−low20

5128

ACN FOR

High15

FLEXIBLE PAVEMENTSUBGRADES − CBR

55

Medium10

63

Low6

8540

Ultral−low3

A340−300 254 400130 000

39.446.2

1.31WV000

260 900

257 900

260 900

271 900

275 900

262 900

275 900

260 900

260 900

275 900

271 900

277 400

260 900

275 900

275 900

277 400

277 400

275 900

39.446.2

1.32WV001

39.146.0

1.32WV002

39.446.2

1.32WV003

39.146.0

1.32WV004

39.646.2

1.42WV020

39.746.2

1.42WV021

39.546.2

1.42WV023

39.746.2

1.42WV024

39.5

46.21.42WV025

39.5

46.21.42WV025

39.746.2WV026

39.646.2WV027

39.446.0WV028

39.546.2WV029

39.746.2WV050

39.746.2WV051

39.446.0WV052

39.446.0WV053

39.746.2WV054

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

A340−300

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

130 000

257 900

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

(CG 38.02%)

(CG 38%)

28

28

28

28

29

29

29

29

29

29

29

29

29

29

29

29

29

29

29

47

47

47

47

52

53

49

53

48

48

53

52

53

48

53

53

53

53

53

54 64 75 52 56 64 87

54 64 76 52 56 65 8739

54 64 75 52 56 64 8740

54 64 76 52 56 65 8739

6029

7133

8338

56 61 70 9440

61 73 85 57 62 72 9740

57 67 79 54 58 66 9040

61 73 85 57 62 72 9740

29 33 38 28 29 32 40

29 33 38 28 29 32 40

56 67 78 53 57 66 88

56 67 78 53 57 66 88

61 73 85 57 62 72 9740

60 71 83 56 61 70 9440

61 72 84 57 62 71 9639

56 67 78 53 57 66 88

61 73 85 57 62 72 97

61 73 85 57 62 72 97

61 72 84 57 62 71 9639

61 72 84 57 62 71 9639

61 73 85 57 62 72 9740

28

28

28

28

29

29

29

29

29

29

29

29

29

29

29

29

32

32

32

32

33

33

33

33

33

33

33

33

33

33

33

33

37

37

37

37

38

38

38

38

38

38

38

38

38

38

38

38

28

28

28

28

28

28

28

28

28

28

28

28

28

28

28

28

28

29

29

29

29

29

29

29

29

29

29

29

29

29

29

29

29

29

29

32

32

32

32

32

32

32

32

32

32

32

32

32

32

32

32

32

32

40

40

40

40

F_AC_070900_1_0050101_01_00

Aircraft Classification NumberACN Table

FIGURE-7-9-0-991-005-A01

7-9-0

Page 7Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

3 0 0

4 0 0

5

0 0

6 0 0

0 1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 0 0

1 5 0

2 0 0

2 5 0

3 0 0

( x 1 0 0 0 k g )



( x 1 0 0 0 l b )


1 4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S

S E E S E C

T I O N 7 − 4 − 0




A L P H A F A C

T O R = 0 . 8

D − C

B R 3

( U L T R A L O W )

S U B G R A D E

S T R E N G T H

C − C

B R 6

( L O W )

B − C

B R 1 0

( M E D I U M )

A − C

B R 1 5

( H I G H )

F_AC_070900_1_0160101_01_00

Aircraft Classification NumberFlexible Pavement - WV000, MRW 254 400 kg, CG 38.18 % (Sheet 1 of 2)

FIGURE-7-9-0-991-016-A01

7-9-0

Page 8Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-300

3 0 0

4 0 0

5

0 0

6 0 0

0 1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 0 0

1 5 0

2 0 0

2 5 0

3 0 0

( x 1 0 0 0 k g )



( x 1 0 0 0 l b )


1 4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S

S E E S E C

T I O N 7 − 4 − 0




D − K =

2 0 M N / m ³

( U L T R A L O W )

S U B G R A D E S T R E N

G T H

C − K =

4 0 M N / m ³

( L O W )

B − K =

8 0 M N / m ³

( M E D I U M )

A − K = 1 5 0 M N / m ³

( H I G H )

F_AC_070900_1_0160102_01_00

Aircraft Classification NumberRigid Pavement - WV000, MRW 254 400 kg, CG 38.18 % (Sheet 2 of 2)

FIGURE-7-9-0-991-016-A01

7-9-0

Page 9Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

3 0 0

4 0 0

5

0 0

6 0 0

0 1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 0 0

1 5 0

2 0 0

2 5 0

3 0 0

( x 1 0 0 0 k g )



( x 1 0 0 0 l b )


1 4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S

S E E S E C

T I O N 7 − 4 − 0




A L P H A F A C

T O R = 0 . 8

D − C

B R 3

( U L T R A L O W )

S U B G R A D E

S T R E N G T H

C − C

B R 6

( L O W )

B − C

B R 1 0

( M E D I U M )

A − C

B R 1 5

( H I G H )

F_AC_070900_1_0170101_01_00

Aircraft Classification NumberFlexible Pavement - WV028, MRW 277 400 kg, CG 35 % (Sheet 1 of 2)

FIGURE-7-9-0-991-017-A01

7-9-0

Page 10Apr 01/13

7/16/2019 Airbus-AC-A340-200-300-Apr2013



**ON A/C A340-200

3 0 0

4 0 0

5

0 0

6 0 0

0 1 0

2 0

3 0

4 0

5 0

6 0

7 0

8 0

9 0

1 0 0

1 1 0

1 2 0

1 0 0

1 5 0

2 0 0

2 5 0

3 0 0

( x 1 0 0 0 k g )



( x 1 0 0 0 l b )


1 4 0 0 x 5 3 0 R 2 3 O R 5 4 x 2 1 − 2 3 ( b i a s ) T I R E S

S E E S E C

T I O N 7 − 4 − 0




D − K =

2 0 M N / m ³

( U L T R A L O W )

S U B G R A D E S T R E N

G T H

C − K =

4 0 M N / m ³

( L O W )

B − K =

8 0 M N / m ³

( M E D I U M )

A − K = 1 5 0 M N / m ³

( H I G H )

F_AC_070900_1_0170102_01_00

Aircraft Classification NumberRigid Pavement - WV028, MRW 277 400 kg, CG 35 % (Sheet 2 of 2)

FIGURE-7-9-0-991-017-A01

7-9-0

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SCALED DRAWINGS

8-0-0 SCALED DRAWINGS

**ON A/C A340-200 A340-300Scaled Drawings

1. This section provides the scaled drawings.

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

8-0-0

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**ON A/C A340-200

0

1 0

2 0

3 0

4 0

F E E T

0

4

8

1 2

1 6

2 0

ME T E R S

0 10 20 30 40FEET

0 4 8 12 16 20METERS

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

5 0

6 0

50 60

F_AC_080000_1_0030101_01_00

Scaled DrawingFIGURE-8-0-0-991-003-A01

8-0-0

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**ON A/C A340-300

0

1 0

2 0

3 0

4 0

F E E T

0

4

8

1 2

1 6

2 0

ME T E R S

0 10 20 30 40FEET

0 4 8 12 16 20METERS

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

5 0

6 0

50 60

F_AC_080000_1_0030201_01_00

Scaled DrawingFIGURE-8-0-0-991-003-B01

8-0-0

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AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 AIRCRAFT RESCUE AND FIRE FIGHTING

**ON A/C A340-200 A340-300Aircraft Rescue and Fire Fighting

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

10-0-0

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**ON A/C A340-200 A340-300

F_AC_100000_1_0270101_01_00

Front PageFIGURE-10-0-0-991-027-A01

10-0-0

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**ON A/C A340-200 A340-300

F_AC_100000_1_0280101_01_00

Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-0-0-991-028-A01

10-0-0

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**ON A/C A340-200 A340-300

F_AC_100000_1_0290101_01_00

Crew Rest Compartments LocationFIGURE-10-0-0-991-029-A01

10-0-0

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**ON A/C A340-200 A340-300

F_AC_100000_1_0300101_01_00

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

FIGURE-10-0-0-991-030-A01

10-0-0

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**ON A/C A340-200 A340-300

F_AC_100000_1_0300102_01_00

Wheel/Brake OverheatRecommendations (Sheet 2 of 2)

FIGURE-10-0-0-991-030-A01

10-0-0

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**ON A/C A340-200 A340-300

F_AC_100000_1_0310101_01_00

Composite Materials LocationFIGURE-10-0-0-991-031-A01

10-0-0

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**ON A/C A340-200 A340-300

B

A

A

B

C

C

F_AC_100000_1_0320101_01_00

Ground Lock Safety DevicesFIGURE-10-0-0-991-032-A01

10-0-0

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**ON A/C A340-200 A340-300

F_AC_100000_1_0330101_01_00

Emergency Evacuation DevicesFIGURE-10-0-0-991-033-A01

10-0-0

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**ON A/C A340-200 A340-300

F_AC_100000_1_0340101_01_00

Pax/Crew Doors and Emergency ExitsFIGURE-10-0-0-991-034-A01

10-0-0

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**ON A/C A340-200 A340-300

1 2 2 C R

F W D

7 1 5 5 J E

1 9 6 B B

1 5 2 N R

/

1 9 7 C B

F_AC_100000_1_0350101_01_00

FWD and AFT Lower Deck Cargo DoorsFIGURE-10-0-0-991-035-A01

10-0-0

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**ON A/C A340-200 A340-300

C A B F A N S

E X T R A C T

A V N C S

B T L 2

B T L 1

T E S T

D I S C H

A F T A G E N T

F W D A G E N T

S M O K E

S Q U I B

S M O K E

S Q U I B

O F F

F A U L T

O F F

F A U L T

O F F

F A U L T

O F F

F A U L T

C A R G O A I R C O N D

F W D

A F T

B U L K

I S O L V A L V E S

I S O L V A L V E S

I S O L V A L V E S

H O T A I R

A U T O

C A R G O S M O K E

V E N T I L A T I O N

O V R D

F A U L T

S M O K E

F A U L T

O F F / R

F A U L T

O F F / R

F A U L T

O F F / R

P R I M 2

P R I M 3

S E C 2

F L T C T L

2 1 2 V U

O F F

N O R M

M A X

C O O L I N G

C O L D

H O T

C O L D

H O T

W I P E R

R A I N R P L N T

O F F

S L O W

F A S T

O F F

4

2

1

3

M A N S T A R T

E N G

O N

O N

O N

O N

B C A

R O U T E R T K

R O U T E R T K

O V E R F L O W

I N C

L O A D

H I L E V E L

T E S

T

T R A N S F . V A L V E

O P E N

C L O S E D

A P U E M E R G .

S H U T

D O W N

P W R

S U P P

L Y

N

O R M

B A T

L

T T

R

D E C

R E F U E L / D E F U E L V A L V E S

M O D E S E L E C T

L O U T E R T K

L I N N E R T K

C T R T K

L O U T E R T K

L I N N E R T K

C T R T K

T R I M T K

H I G H L E V E L

R E F U E L

O F F

D E F U E L

R I N N E R T K

R I N N E R T K

O P E N

N O R M

S H U T

L I N R .

C E N T E R

R I N R .

L O U T E R

R O U T E R

T R I M

A C T U A L

C K P T

E N D

x 1 0 0 0 k

g

1 b

P R E S E L E C T E D

T R I M T K

C

E

B

D

A

D

4

3

2

1

E

F_AC_100000_1_0360101_01_00

Control PanelsFIGURE-10-0-0-991-036-A01

10-0-0

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**ON A/C A340-200 A340-300

A 3 1 5 A L

3 1 6 A R

A

F_AC_100000_1_0370101_01_00

APU Compartment AccessFIGURE-10-0-0-991-037-A01

10-0-0

Page 13Apr 01/13

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**ON A/C A340-200 A340-300

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