Airbus AC A320 Jun2012

@AIRBUSA320

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 ofthe 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 Services31707 Blagnac Cedex

FRANCE

Issue: Sep 30/85 Rev: Jun 01/12

@A320AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

HIGHLIGHTS

Revision No. 27 - Jun 01/12

LOCATIONS CHGCODE

DESCRIPTIONS OF CHANGE

CHAPTER 1 R

Section 1-1

Subject 1-1-0

Purpose R PURPOSE CHANGED DUE TO MERGE OFTHE MFP AND AC MANUALS.PART EFFECTIVITYADDED/REVISED/DELETED

Section 01-02 D

CHAPTER 2 R

Section 2-1 R

Subject 2-1-0 R

General Airplane Characteristics R WEIGHT DEFINITIONS UPDATED.PART EFFECTIVITYADDED/REVISED/DELETED

Subject 2-1-1 R

General Airplane Characteristics Data R ADDED WV 0017 AND 0018. OEW ANDPAYLOAD DELETED.PART EFFECTIVITYADDED/REVISED/DELETED

Section 2-2 R

Subject 2-2-0 R

General Aircraft Dimensions R REPLACED ”AIRPLANE” BY ”AIRCRAFT”AND COMPLETED TITLE OFILLUSTRATIONS.DESCRIPTION TITLE UPDATED

FIGURE General Aircraft Dimensions -Wing Tip Fence

R ILLUSTRATION REVISED

Section 2-3

Subject 2-3-0

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LOCATIONS CHGCODE


Ground Clearances R REVISED GROUND CLEARANCES TOSHOW THE DIMENSIONS FOR A LIGHTAND HEAVY WEIGHT VARIANT.DELETED THE TERM ”OWE”.PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Clearances R

FIGURE Ground Clearances - GroundClearances with Sharklets

N ILLUSTRATION ADDED

FIGURE Ground Clearances - Flaps andFlap Track Fairings When Flaps FullyExtended


FIGURE Ground Clearances - Flaps andFlap Track Fairings When Flaps FullyExtended


FIGURE Ground Clearances - Flap TrackFairings Up


FIGURE Ground Clearances - AileronDown


FIGURE Ground Clearances - Aileron Upand Spoilers 1 to 5 Extended


FIGURE Ground Clearances - SlatsExtended


Section 2-4

Subject 2-4-0

Interior Arrangements R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 2-4-1

Typical Configuration R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Typical Configuration - TypicalConfiguration Single-Class, High Density

R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Typical Configuration - TypicalConfiguration Two-Class


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LOCATIONS CHGCODE


Section 2-5

Subject 2-5-0

Passenger Compartment Cross-section R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Passenger Compartment Cross-section


FIGURE Passenger Compartment Cross-section - Economy Class, 6 Abreast -Wider Aisle


FIGURE Passenger Compartment Cross-section - Passenger Compartment Cross-section, First-class


Section 2-6 R

Subject 2-6-0

Cargo Compartments R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Cargo Compartments -Locations, Dimensions and LoadingCombinations


Subject 02-06-01 D

Section 2-7

Subject 2-7-0

Doors Clearances R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 2-7-1

Forward Passenger / Crew Doors R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Doors Clearances - ForwardPassenger / Crew Doors


Subject 2-7-2

Emergency Exits R PART EFFECTIVITYADDED/REVISED/DELETED

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LOCATIONS CHGCODE


FIGURE Doors Clearances - EmergencyExits


Subject 2-7-3

Aft Passenger / Crew Doors R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Doors Clearances - Aft Passenger/ Crew Doors


Subject 2-7-4

Forward Cargo Compartment Door R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Doors Clearances - ForwardCargo Compartment Door


Subject 2-7-5

Aft Cargo Compartment Door R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Doors Clearances - Aft CargoCompartment Door


Subject 2-7-6

Bulk Cargo Compartment Door R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Doors Clearances - Bulk CargoCompartment Door


Subject 2-7-7

Main Landing Gear Doors R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Doors Clearances - Main LandingGear Doors


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LOCATIONS CHGCODE


FIGURE Doors Clearances - Main LandingGear Doors (Bogie)


Subject 2-7-8

Radome R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Doors Clearances - Radome R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Subject 2-7-9

APU and Nose Landing Gear Doors R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Doors Clearances - APU andNose Landing Gear Doors


Section 2-8 N

Subject 2-8-0 N

Escape Slides N

FIGURE Escape Slides - Location N ILLUSTRATION ADDED

FIGURE Escape Slides - Dimensions N ILLUSTRATION ADDED

Section 2-9 N

Subject 2-9-0 N

Landing Gear N

FIGURE Landing Gear - Main LandingGear - Twin Wheel


FIGURE Landing Gear - Main LandingGear Dimensions - Twin Wheel


FIGURE Landing Gear - Main LandingGear - Four Wheels - Bogie


FIGURE Landing Gear - Main LandingGear Dimensions - Four Wheels - Bogie


FIGURE Landing Gear - Nose LandingGear


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LOCATIONS CHGCODE


FIGURE Landing Gear - Nose LandingGear Dimensions


Landing Gear Maintenance Pits N

FIGURE Landing Gear Maintenance Pits -Maintenance Pit Envelopes


FIGURE Landing Gear Maintenance Pits -Maintenance Pit Envelopes


Section 2-10 N

Subject 2-10-0 N

Exterior Lighting N

FIGURE Exterior Lighting N ILLUSTRATION ADDED




Section 2-11 N

Subject 2-11-0 N

Antennas and Probes Location N

FIGURE Antennas and Probes - Location N ILLUSTRATION ADDED

Section 2-12 N

Subject 2-12-0 N

Auxiliary Power Unit N

FIGURE Auxiliary Power Unit - AccessDoors


FIGURE Auxiliary Power Unit - GeneralLayout


Engine and Nacelle N

FIGURE Power Plant Handling - MajorDimensions - CFM56 Series Engine


FIGURE Power Plant Handling - MajorDimensions - CFM56 Series Engine


FIGURE Power Plant Handling - FanCowls - CFM56 Series Engine


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LOCATIONS CHGCODE


FIGURE Power Plant Handling - ThrustReverser Cowls - CFM56 Series Engine


FIGURE Power Plant Handling - MajorDimensions - IAE V2500 Series Engine


FIGURE Power Plant Handling - MajorDimensions - IAE V2500 Series Engine


FIGURE Power Plant Handling - FanCowls - IAE V2500 Series Engine


FIGURE Power Plant Handling - ThrustReverser Halves - IAE V2500 SeriesEngine


Section 2-13 N

Subject 2-13-0 N

Leveling, Symmetry and Alignment N

FIGURE Location of the Leveling Points N ILLUSTRATION ADDED

Section 2-14 N

Subject 2-14-0 N

Jacking for Maintenance N

FIGURE Jacking for Maintenance -Jacking Point Location


FIGURE Jacking for Maintenance -Forward Jacking Point


FIGURE Jacking for Maintenance - WingJacking Points


FIGURE Jacking for Maintenance - SafetyStay


FIGURE Jacking for Maintenance -Jacking Design


FIGURE Loads at the Aircraft JackingPoints - Forward Fuselage Jacking Point -Twin Wheel/Bogie


FIGURE Loads at the Aircraft JackingPoints - Wing Jacking Point Rib 8 - TwinWheel/Bogie


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LOCATIONS CHGCODE


FIGURE Jacking for Maintenance -Location of Shoring Cradles


Jacking for Wheel Change N

FIGURE Landing Gear Jacking for WheelChange - MLG Jacking Point Location -Twin Wheels


FIGURE Landing Gear Jacking for WheelChange - MLG Jacking with CantileverJack - Twin Wheels


FIGURE Landing Gear Jacking for WheelChange - Loads at MLG Jacking Points -Twin Wheels


FIGURE Landing Gear Jacking for WheelChange - MLG Jacking Point LocationBogie






FIGURE Landing Gear Jacking for WheelChange - Loads at MLG Jacking Points -Bogie Version


FIGURE Landing Gear Jacking for WheelChange - Loads at MLG Jacking Points -77 000 kg


FIGURE Landing Gear Jacking for WheelChange - NLG Jacking - Point Location


FIGURE Landing Gear Jacking for WheelChange - Loads at NLG Jacking Points


FIGURE Landing Gear Jacking for WheelChange - Loads at NLG Jacking Points -77 000 kg


CHAPTER 3 R

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LOCATIONS CHGCODE


Section 3-1

Subject 3-1-0

General Information R PART EFFECTIVITYADDED/REVISED/DELETED

Section 3-2

Subject 3-2-0

Payload / Range R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 3-2-1

ISA Conditions R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Payload / Range - CFM56-5Aseries engine


FIGURE Payload / Range - CFM56-5Bseries engine


FIGURE Payload / Range - IAE V2500-A1 series engine


FIGURE Payload / Range - IAE V2500-A5 series engine


Section 3-3

Subject 3-3-0

FAR / JAR Take-off Weight Limitation R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 3-3-1


FIGURE FAR / JAR Take-off WeightLimitation - ISA Conditions -- CFM56series engine


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LOCATIONS CHGCODE


FIGURE FAR / JAR Take-off WeightLimitation - ISA Conditions -- IAE V2500series engine


Subject 3-3-2

ISA +15˚C (+59˚F) Conditions R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE FAR / JAR Take-off WeightLimitation - ISA +15˚C (+59˚F)Conditions -- CFM56 series engine


FIGURE FAR / JAR Take-off WeightLimitation - ISA +15˚C (+59˚F)Conditions -- IAE V2500 series engine


Section 3-4

Subject 3-4-0

FAR / JAR Landing Field Length R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 3-4-1


FIGURE FAR / JAR Landing Field Length- CFM56 series engine


FIGURE FAR / JAR Landing Field Length- IAE V2500 series engine


Section 3-5

Subject 3-5-0

Final Approach Speed R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Final Approach Speed - CFM56series engine


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LOCATIONS CHGCODE


FIGURE Final Approach Speed - IAEV2500 series engine


CHAPTER 4

Section 4-1

Subject 4-1-0


Section 4-2

Subject 4-2-0

Turning Radii R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Turning Radii, No Slip Angle -Turning Radii -- Dual Landing Gear


FIGURE Turning Radii, No Slip Angle -Turning Radii -- Dual Landing Gear


FIGURE Turning Radii, No Slip Angle -Turning Radii -- Bogie Landing Gear


FIGURE Turning Radii, No Slip Angle -Turning Radii -- Bogie Landing Gear


Section 4-3

Subject 4-3-0

Minimum Turning Radii R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Minimum Turning Radii R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Section 4-4

Subject 4-4-0

Visibility from Cockpit in Static Position N

FIGURE Visibility from Cockpit in StaticPosition


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LOCATIONS CHGCODE


FIGURE Binocular Visibility ThroughWindows from Captain Eye Position


Section 4-5 R

Subject 4-5-0

Runway and Taxiway Turn Paths R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 4-5-1

135˚ Turn - Runway to Taxiway R PART EFFECTIVITYADDED/REVISED/DELETED

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


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


Subject 4-5-2

90˚ Turn - Runway to Taxiway R PART EFFECTIVITYADDED/REVISED/DELETED

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


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


Subject 4-5-3 N

180˚ Turn on a Runway N

FIGURE 180˚ Turn on a Runway - Edgeof Runway Method


Subject 4-5-4 N

135˚ Turn - Taxiway to Taxiway N

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


Subject 4-5-5

90˚ Turn - Taxiway to Taxiway R PART EFFECTIVITYADDED/REVISED/DELETED

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LOCATIONS CHGCODE


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


Section 4-6

Subject 4-6-0

Runway Holding Bay (Apron) R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Runway Holding Bay (Apron) R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

CHAPTER 5 R

Section 5-0

Subject 5-0-0

Terminal Servicing R PART EFFECTIVITYADDED/REVISED/DELETED

Section 5-1 R

Subject 5-1-0 R

Airplane Servicing Arrangements R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-1-1

Symbols Used on Servicing Diagrams R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-1-2 R

Typical Ramp Layout - Open Apron R TITLE CHANGED FROM ”AIRCRAFT ATTHE GATE” TO ”TYPICAL RAMPLAYOUT - OPEN APRON”. ADDED”STAND SAFETY LINE” DEFINITION.DESCRIPTION TITLE UPDATED

FIGURE Typical Ramp Layout - OpenApron - Bulk Loading


FIGURE Typical Ramp Layout - OpenApron - ULD Loading


Subject 5-1-3 R

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LOCATIONS CHGCODE


Typical Ramp Layout - Gate R TITLE CHANGED FROM ”AIRCRAFT ATAN OPEN APRON” TO ”TYPICAL RAMPLAYOUT - GATE”. ADDED ”STANDSAFETY LINE” DEFINITION.DESCRIPTION TITLE UPDATED

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 Turn Round Stations - FullServicing (43 Min.)


Subject 05-02-01 D

Section 5-3 R

Subject 5-3-0 R

Terminal Operation - Minimum ServicingTurn Round Time

N

FIGURE Turn Round Stations - MinimumServicing (23 Min.)


Subject 05-03-01 D

Section 5-4

Subject 5-4-0

Ground Service Connections R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-4-1

Ground Service Connections Layout R DELETED GROUND SERVICECONNECTIONS LAYOUT TABLE.PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Service Connections -Ground Service Connections Layout


Subject 5-4-2

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LOCATIONS CHGCODE


Grounding Points R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Service Connections -Grounding Points


FIGURE Ground Service Connections -Grounding Points


Subject 5-4-3

Hydraulic System R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Hydraulic System - Green SystemGround Service Panel


FIGURE Hydraulic System - Blue SystemGround Service Panel


FIGURE Hydraulic System - YellowSystem Ground Service Panel


Subject 5-4-4

Electrical System R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Service Connections -External Power Receptacles


Subject 5-4-5

Oxygen System R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-4-6

Fuel System R PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

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LOCATIONS CHGCODE


FIGURE Ground Service Connections -Refuel/Defuel Panel


FIGURE Ground Service Connections -Refuel/Defuel Couplings


FIGURE Ground Service Connections -Gravity Refuel Couplings


FIGURE Ground Service Connections -Overpressure Protector and NACA FlameArrestor

N ADDED OVERPRESSURE PROTECTORAND NACA FLAME ARRESTORILLUSTRATION.ILLUSTRATION ADDED

Subject 5-4-7

Pneumatic System R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-4-8

Potable Water System R UPDATED ACCESS PANEL 133AL ASOPTIONAL FOR A320.UPDATED ACCESS PANEL 133AL ASOPTIONAL FOR A320.PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Ground Service Connections -Potable Water Ground Drain Panel


Subject 5-4-9

Oil System R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Service Connections -Engine Oil Tank -- CFM56 Series Engine


FIGURE Ground Service Connections -IDG Oil Tank -- CFM56 Series Engine


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LOCATIONS CHGCODE


FIGURE Ground Service Connections -Starter Oil Tank -- CFM56 Series Engine


FIGURE Ground Service Connections -Engine Oil Tank -- IAE V2500 SeriesEngine


FIGURE Ground Service Connections -IDG Oil Tank -- IAE V2500 Series Engine


FIGURE Ground Service Connections -Starter Oil Tank -- IAE V2500 SeriesEngine


FIGURE Ground Service Connections -APU Oil Tank


Subject 5-4-10

Vacuum Toilet System R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Service Connections -Waste Water Ground Service Panel


Section 5-5

Subject 5-5-0

Engine Starting Pneumatic Requirements R PART EFFECTIVITYADDED/REVISED/DELETEDCROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETED

FIGURE Engine Starting PneumaticRequirements


Subject 5-5-1 R

Low Ambient Temperatures R DESCRIPTION TITLE UPDATEDPART EFFECTIVITYADDED/REVISED/DELETED

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LOCATIONS CHGCODE


FIGURE Engine Starting PneumaticRequirements - Low AmbientTemperature -40˚C (-40˚F) -- CFM56series engine


FIGURE Engine Starting PneumaticRequirements - Low AmbientTemperature -40˚C (-40˚F) -- IAE V2500series engine


Subject 5-5-2 R

Medium Ambient Temperatures R DESCRIPTION TITLE UPDATEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Engine Starting PneumaticRequirements - Medium AmbientTemperature +15˚C (+59˚F) -- CFM56series engine


FIGURE Engine Starting PneumaticRequirements - Medium AmbientTemperature +15˚C (+59˚F) -- IAEV2500 series engine


Subject 5-5-3 R

High Ambient Temperatures R DESCRIPTION TITLE UPDATEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Engine Starting PneumaticRequirements - High AmbientTemperature +55˚C (+131˚F) -- CFM56series engine


FIGURE Engine Starting PneumaticRequirements - High AmbientTemperature +50˚C (+122˚F) -- IAEV2500 series engine


Section 5-6

Subject 5-6-0

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LOCATIONS CHGCODE


Ground Pneumatic Power Requirements R DELETED THE AIRFLOW DATA TABLE.ADDED A NOTE FOR GROUNDPNEUMATIC POWER REQUIREMENTS.PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

Subject 5-6-1

Heating R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Pneumatic PowerRequirements - Heating


Subject 5-6-2

Cooling R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Pneumatic PowerRequirements - Cooling


Section 5-7

Subject 5-7-0

Preconditioned Airflow Requirements R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Preconditioned AirflowRequirements


Section 5-8

Subject 5-8-0

Ground Towing Requirements R SAE REFERENCES UPDATED ANDFIGURES CORRESPONDING TO TYPICALTOW BAR CONFIGURATION DELETEDPART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

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LOCATIONS CHGCODE


FIGURE Ground Towing Requirements R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Section 5-9 N

Subject 5-9-0 N

De-Icing and External Cleaning N REVISED TABLES FOR DE-ICING ANDEXTERNAL CLEANING AREAS.

CHAPTER 6

Section 6-1

Subject 6-1-0

Engine Exhaust Velocities andTemperatures

R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 6-1-1

Engine Exhaust Velocities Contours -Ground Idle Power


FIGURE Engine Exhaust Velocities -Ground Idle Power -- CFM56 series engine


FIGURE Engine Exhaust Velocities -Ground Idle Power -- IAE V2500 seriesengine


Subject 6-1-2

Engine Exhaust Temperatures Contours -Ground Idle Power


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


FIGURE Engine Exhaust Temperatures -Ground Idle Power -- IAE V2500 seriesengine


Subject 6-1-3

Engine Exhaust Velocities Contours -Breakaway Power


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LOCATIONS CHGCODE


FIGURE Engine Exhaust Velocities -Breakaway Power -- CFM56 series engine


FIGURE Engine Exhaust Velocities -Breakaway Power -- IAE V2500 seriesengine


Subject 6-1-4

Engine Exhaust Temperatures Contours -Breakaway Power


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


FIGURE Engine Exhaust Temperatures -Breakaway Power -- IAE V2500 seriesengine


Subject 6-1-5

Engine Exhaust Velocities Contours -Takeoff Power


FIGURE Engine Exhaust Velocities -Takeoff Power -- CFM56 series engine


FIGURE Engine Exhaust Velocities -Takeoff Power -- IAE V2500 series engine


Subject 6-1-6

Engine Exhaust Temperatures Contours -Takeoff Power


FIGURE Engine Exhaust Temperatures -Takeoff Power -- CFM56 series engine


FIGURE Engine Exhaust Temperatures -Takeoff Power -- IAE V2500 series engine


Section 6-2

Subject 6-2-0

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LOCATIONS CHGCODE


Airport and Community Noise R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 6-2-1

Noise Data R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Airport and Community Noise -CFM56-5A series engine


FIGURE Airport and Community Noise -CFM56-5B series engine


FIGURE Airport and Community Noise -IAE V2500 series engine


Section 6-3

Subject 6-3-0

Danger Areas of Engines R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 6-3-1

Ground Idle Power R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Danger Areas of Engines -CFM56 series engine


FIGURE Danger Areas of Engines - IAEV2500 series engine


Subject 6-3-2

Takeoff Power R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Danger Areas of Engines -CFM56 series engine


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LOCATIONS CHGCODE


FIGURE Danger Areas of Engines - IAEV2500 series engine


Section 6-4

Subject 6-4-0

APU Exhaust Velocities and Temperatures R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 6-4-1

APU - APIC & GARRETT R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Exhaust Velocities andTemperatures - APU -- APIC &GARRETT


CHAPTER 7

Section 7-1

Subject 7-1-0


FIGURE Aircraft Codes R ILLUSTRATION REVISED

Section 7-2

Subject 7-2-0

Landing Gear Footprint R PART EFFECTIVITYADDED/REVISED/DELETEDCROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Landing Gear Footprint R ILLUSTRATION REVISED

FIGURE Landing Gear Footprint R

FIGURE Landing Gear Footprint R

Section 7-3

Subject 7-3-0

Maximum Pavement Loads R PART EFFECTIVITYADDED/REVISED/DELETED

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LOCATIONS CHGCODE


FIGURE Maximum Pavement Loads R

FIGURE Maximum Pavement Loads R ILLUSTRATION REVISED





Section 7-4

Subject 7-4-0

Landing Gear Loading on Pavement R UPDATED TITLE FOR REFERENCESECTION 7-4-1 LANDING GEAR LOADINGON PAVEMENT.PART EFFECTIVITYADDED/REVISED/DELETED

Subject 7-4-1

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

FIGURE Landing Gear Loading onPavement

R


R


R


R


R


R


R


R


R


R

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LOCATIONS CHGCODE






Section 7-5

Subject 7-5-0

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

R UPDATED TITLE FOR REFERENCESECTION 7-5-1 FLEXIBLE PAVEMENTREQUIREMENTS.PART EFFECTIVITYADDED/REVISED/DELETED

Subject 7-5-1

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

R DELETED TWO FIGURES FOR THE A/CCODE ”P”.PART EFFECTIVITYADDED/REVISED/DELETEDCROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Flexible Pavement Requirements R ILLUSTRATION REVISED






FIGURE Flexible Pavement Requirements- Flexible Pavement Requirements

R



FIGURE Flexible Pavement Requirements R

Section 7-6

Subject 7-6-0

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LOCATIONS CHGCODE


Flexible Pavement Requirements - LCNConversion

R UPDATED TITLE FOR REFERENCESECTION 7-6-1 FLEXIBLE PAVEMENTREQUIREMENTS.PART EFFECTIVITYADDED/REVISED/DELETED

Subject 7-6-1

Flexible Pavement Requirements - LCNConversion

R DELETED TWO FIGURES FOR THE A/CCODE ”P”.PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Flexible Pavement Requirements- LCN Conversion

R


R




R


R


R

Section 7-7

Subject 7-7-0

Rigid Pavement Requirements - PortlandCement Association Design Method

R UPDATED TITLE FOR REFERENCESECTION 07-07-01 RIGID PAVEMENTREQUIREMENTS (PCA).PART EFFECTIVITYADDED/REVISED/DELETED

Subject 7-7-1

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LOCATIONS CHGCODE


Rigid Pavement Requirements - PortlandCement Association Design Method

R DELETED TWO FIGURES FOR THE A/CCODE ”P”.PART EFFECTIVITYADDED/REVISED/DELETEDCROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Rigid Pavement Requirements(PCA)

R


R


R


R


R


R

Section 7-8 R

Subject 07-08-00 D

Subject 7-8-1

Radius of Relative Stiffness R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Radius of Relative Stiffness -(Reference: Portland Cement Association)


Subject 7-8-2

Rigid Pavement Requirements - LCNConversion

R MOVED THE TEXT FROM 7-8-0 TO 7-8-2.PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Rigid Pavement Requirements -LCN Conversion

R


R

HIGHLIGHTSPage 27

Jun 01/12


LOCATIONS CHGCODE



R


R


R




R



Subject 7-8-3

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


Subject 7-8-4

Radius of Relative Stiffness R PART EFFECTIVITYADDED/REVISED/DELETED

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


Section 7-9

Subject 7-9-0

ACN/PCN Reporting System R UPDATED TITLE FOR REFERENCESECTION 7-9-1 AND 7-9-2.PART EFFECTIVITYADDED/REVISED/DELETED

Subject 7-9-1

Aircraft Classification Number - FlexiblePavement


FIGURE Aircraft Classification Number --Flexible Pavement

R

HIGHLIGHTSPage 28

Jun 01/12


LOCATIONS CHGCODE



R


R


R


R


R


R

Subject 7-9-2

Aircraft Classification Number - RigidPavement


FIGURE Aircraft Classification Number --Rigid Pavement

R


R


R


R


R


R

CHAPTER 8 R

Section 8-0 N

Subject 8-0-0 N

Scaled Drawings N

FIGURE Scaled Drawing N ILLUSTRATION ADDED

HIGHLIGHTSPage 29

Jun 01/12


LOCATIONS CHGCODE


Section 08-01 D

CHAPTER 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 Wheel Safety Area N ILLUSTRATION ADDED

FIGURE Composite Materials N ILLUSTRATION ADDED

FIGURE LG Ground Lock Safety Devices N ILLUSTRATION ADDED

FIGURE Evacuation/Escape Slide/Raft N ILLUSTRATION ADDED

FIGURE Pax/Crew Doors N ILLUSTRATION ADDED

FIGURE Emergency Exit Hatch N ILLUSTRATION ADDED

FIGURE FWD and AFT Lower DeckCargo Doors


FIGURE Control Panels N ILLUSTRATION ADDED

FIGURE APU Access Door N ILLUSTRATION ADDED

FIGURE Aircraft Ground Clearances N ILLUSTRATION ADDED

FIGURE Structural Break-in Points N ILLUSTRATION ADDED

HIGHLIGHTSPage 30

Jun 01/12


LIST OF EFFECTIVE CONTENT

Revision No. 27 - Jun 01/12

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 1

Subject 1-1-0

Purpose R Jun 01/12

CHAPTER 2

Subject 2-1-0

General Airplane Characteristics R Jun 01/12

Subject 2-1-1

General Airplane Characteristics Data R Jun 01/12

Subject 2-2-0

General Aircraft Dimensions R Jun 01/12

FIGURE General Aircraft Dimensions - Wing Tip Fence R Jun 01/12

Subject 2-3-0

Ground Clearances R Jun 01/12

FIGURE Ground Clearances R Jun 01/12

FIGURE Ground Clearances - Ground Clearances with Sharklets N Jun 01/12

FIGURE Ground Clearances - Flaps and Flap Track Fairings WhenFlaps Fully Extended

N Jun 01/12

FIGURE Ground Clearances - Flaps and Flap Track Fairings WhenFlaps Fully Extended

N Jun 01/12

FIGURE Ground Clearances - Flap Track Fairings Up N Jun 01/12

FIGURE Ground Clearances - Aileron Down N Jun 01/12

FIGURE Ground Clearances - Aileron Up and Spoilers 1 to 5 Extended N Jun 01/12

FIGURE Ground Clearances - Slats Extended N Jun 01/12

Subject 2-4-0

Interior Arrangements R Jun 01/12

Subject 2-4-1

Typical Configuration R Jun 01/12

L.E.C.Page 1

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Typical Configuration - Typical Configuration Single-Class,High Density

R Jun 01/12

FIGURE Typical Configuration - Typical Configuration Two-Class R Jun 01/12

Subject 2-5-0

Passenger Compartment Cross-section R Jun 01/12

FIGURE Passenger Compartment Cross-section R Jun 01/12

FIGURE Passenger Compartment Cross-section - Economy Class, 6Abreast - Wider Aisle

R Jun 01/12

FIGURE Passenger Compartment Cross-section - PassengerCompartment Cross-section, First-class

R Jun 01/12

Subject 2-6-0

Cargo Compartments R Jun 01/12

FIGURE Cargo Compartments - Locations, Dimensions and LoadingCombinations

N Jun 01/12

Subject 2-7-0

Doors Clearances R Jun 01/12

Subject 2-7-1

Forward Passenger / Crew Doors R Jun 01/12

FIGURE Doors Clearances - Forward Passenger / Crew Doors R Jun 01/12

Subject 2-7-2

Emergency Exits R Jun 01/12

FIGURE Doors Clearances - Emergency Exits R Jun 01/12

Subject 2-7-3

Aft Passenger / Crew Doors R Jun 01/12

FIGURE Doors Clearances - Aft Passenger / Crew Doors R Jun 01/12

Subject 2-7-4

Forward Cargo Compartment Door R Jun 01/12

FIGURE Doors Clearances - Forward Cargo Compartment Door R Jun 01/12

Subject 2-7-5

Aft Cargo Compartment Door R Jun 01/12

L.E.C.Page 2

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Doors Clearances - Aft Cargo Compartment Door R Jun 01/12

Subject 2-7-6

Bulk Cargo Compartment Door R Jun 01/12

FIGURE Doors Clearances - Bulk Cargo Compartment Door R Jun 01/12

Subject 2-7-7

Main Landing Gear Doors R Jun 01/12

FIGURE Doors Clearances - Main Landing Gear Doors R Jun 01/12

FIGURE Doors Clearances - Main Landing Gear Doors (Bogie) R Jun 01/12

Subject 2-7-8

Radome R Jun 01/12

FIGURE Doors Clearances - Radome R Jun 01/12

Subject 2-7-9

APU and Nose Landing Gear Doors R Jun 01/12

FIGURE Doors Clearances - APU and Nose Landing Gear Doors R Jun 01/12

Subject 2-8-0

Escape Slides N Jun 01/12

FIGURE Escape Slides - Location N Jun 01/12

FIGURE Escape Slides - Dimensions N Jun 01/12

Subject 2-9-0

Landing Gear N Jun 01/12

FIGURE Landing Gear - Main Landing Gear - Twin Wheel N Jun 01/12

FIGURE Landing Gear - Main Landing Gear Dimensions - Twin Wheel N Jun 01/12

FIGURE Landing Gear - Main Landing Gear - Four Wheels - Bogie N Jun 01/12

FIGURE Landing Gear - Main Landing Gear Dimensions - FourWheels - Bogie

N Jun 01/12

FIGURE Landing Gear - Nose Landing Gear N Jun 01/12

FIGURE Landing Gear - Nose Landing Gear Dimensions N Jun 01/12

Landing Gear Maintenance Pits N Jun 01/12

FIGURE Landing Gear Maintenance Pits - Maintenance Pit Envelopes N Jun 01/12

L.E.C.Page 3

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Landing Gear Maintenance Pits - Maintenance Pit Envelopes N Jun 01/12

Subject 2-10-0

Exterior Lighting N Jun 01/12

FIGURE Exterior Lighting N Jun 01/12




Subject 2-11-0

Antennas and Probes Location N Jun 01/12

FIGURE Antennas and Probes - Location N Jun 01/12

Subject 2-12-0

Auxiliary Power Unit N Jun 01/12

FIGURE Auxiliary Power Unit - Access Doors N Jun 01/12

FIGURE Auxiliary Power Unit - General Layout N Jun 01/12

Engine and Nacelle N Jun 01/12

FIGURE Power Plant Handling - Major Dimensions - CFM56 SeriesEngine

N Jun 01/12

FIGURE Power Plant Handling - Major Dimensions - CFM56 SeriesEngine

N Jun 01/12

FIGURE Power Plant Handling - Fan Cowls - CFM56 Series Engine N Jun 01/12

FIGURE Power Plant Handling - Thrust Reverser Cowls - CFM56Series Engine

N Jun 01/12

FIGURE Power Plant Handling - Major Dimensions - IAE V2500Series Engine

N Jun 01/12

FIGURE Power Plant Handling - Major Dimensions - IAE V2500Series Engine

N Jun 01/12

FIGURE Power Plant Handling - Fan Cowls - IAE V2500 SeriesEngine

N Jun 01/12

FIGURE Power Plant Handling - Thrust Reverser Halves - IAE V2500Series Engine

N Jun 01/12

Subject 2-13-0

L.E.C.Page 4

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Leveling, Symmetry and Alignment N Jun 01/12

FIGURE Location of the Leveling Points N Jun 01/12

Subject 2-14-0

Jacking for Maintenance N Jun 01/12

FIGURE Jacking for Maintenance - Jacking Point Location N Jun 01/12

FIGURE Jacking for Maintenance - Forward Jacking Point N Jun 01/12

FIGURE Jacking for Maintenance - Wing Jacking Points N Jun 01/12

FIGURE Jacking for Maintenance - Safety Stay N Jun 01/12

FIGURE Jacking for Maintenance - Jacking Design N Jun 01/12

FIGURE Loads at the Aircraft Jacking Points - Forward FuselageJacking Point - Twin Wheel/Bogie

N Jun 01/12

FIGURE Loads at the Aircraft Jacking Points - Wing Jacking PointRib 8 - Twin Wheel/Bogie

N Jun 01/12

FIGURE Jacking for Maintenance - Location of Shoring Cradles N Jun 01/12

Jacking for Wheel Change N Jun 01/12

FIGURE Landing Gear Jacking for Wheel Change - MLG JackingPoint Location - Twin Wheels

N Jun 01/12

FIGURE Landing Gear Jacking for Wheel Change - MLG Jacking withCantilever Jack - Twin Wheels

N Jun 01/12

FIGURE Landing Gear Jacking for Wheel Change - Loads at MLGJacking Points - Twin Wheels

N Jun 01/12

FIGURE Landing Gear Jacking for Wheel Change - MLG JackingPoint Location Bogie

N Jun 01/12


N Jun 01/12


N Jun 01/12

FIGURE Landing Gear Jacking for Wheel Change - Loads at MLGJacking Points - Bogie Version

N Jun 01/12

FIGURE Landing Gear Jacking for Wheel Change - Loads at MLGJacking Points - 77 000 kg

N Jun 01/12

L.E.C.Page 5

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Landing Gear Jacking for Wheel Change - NLG Jacking -Point Location

N Jun 01/12

FIGURE Landing Gear Jacking for Wheel Change - Loads at NLGJacking Points

N Jun 01/12

FIGURE Landing Gear Jacking for Wheel Change - Loads at NLGJacking Points - 77 000 kg

N Jun 01/12

CHAPTER 3

Subject 3-1-0

General Information R Jun 01/12

Subject 3-2-0

Payload / Range R Jun 01/12

Subject 3-2-1

ISA Conditions R Jun 01/12

FIGURE Payload / Range - CFM56-5A series engine R Jun 01/12

FIGURE Payload / Range - CFM56-5B series engine R Jun 01/12

FIGURE Payload / Range - IAE V2500-A1 series engine R Jun 01/12

FIGURE Payload / Range - IAE V2500-A5 series engine R Jun 01/12

Subject 3-3-0

FAR / JAR Take-off Weight Limitation R Jun 01/12

Subject 3-3-1


FIGURE FAR / JAR Take-off Weight Limitation - ISA Conditions --CFM56 series engine

R Jun 01/12

FIGURE FAR / JAR Take-off Weight Limitation - ISA Conditions --IAE V2500 series engine

R Jun 01/12

Subject 3-3-2

ISA +15˚C (+59˚F) Conditions R Jun 01/12

FIGURE FAR / JAR Take-off Weight Limitation - ISA +15˚C(+59˚F) Conditions -- CFM56 series engine

R Jun 01/12

FIGURE FAR / JAR Take-off Weight Limitation - ISA +15˚C(+59˚F) Conditions -- IAE V2500 series engine

R Jun 01/12

L.E.C.Page 6

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Subject 3-4-0

FAR / JAR Landing Field Length R Jun 01/12

Subject 3-4-1


FIGURE FAR / JAR Landing Field Length - CFM56 series engine R Jun 01/12

FIGURE FAR / JAR Landing Field Length - IAE V2500 series engine R Jun 01/12

Subject 3-5-0

Final Approach Speed R Jun 01/12

FIGURE Final Approach Speed - CFM56 series engine R Jun 01/12

FIGURE Final Approach Speed - IAE V2500 series engine R Jun 01/12

CHAPTER 4

Subject 4-1-0


Subject 4-2-0

Turning Radii R Jun 01/12

FIGURE Turning Radii, No Slip Angle - Turning Radii -- Dual LandingGear

R Jun 01/12

FIGURE Turning Radii, No Slip Angle - Turning Radii -- Dual LandingGear

N Jun 01/12

FIGURE Turning Radii, No Slip Angle - Turning Radii -- BogieLanding Gear

R Jun 01/12

FIGURE Turning Radii, No Slip Angle - Turning Radii -- BogieLanding Gear

N Jun 01/12

Subject 4-3-0

Minimum Turning Radii R Jun 01/12

FIGURE Minimum Turning Radii R Jun 01/12

Subject 4-4-0

Visibility from Cockpit in Static Position N Jun 01/12

FIGURE Visibility from Cockpit in Static Position N Jun 01/12

FIGURE Binocular Visibility Through Windows from Captain EyePosition

N Jun 01/12

L.E.C.Page 7

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Subject 4-5-0

Runway and Taxiway Turn Paths R Jun 01/12

Subject 4-5-1

135˚ Turn - Runway to Taxiway R Jun 01/12

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

R Jun 01/12

FIGURE 135˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

N Jun 01/12

Subject 4-5-2

90˚ Turn - Runway to Taxiway R Jun 01/12

FIGURE 90˚ Turn - Runway to Taxiway - Cockpit Over CenterlineMethod

R Jun 01/12

FIGURE 90˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

N Jun 01/12

Subject 4-5-3

180˚ Turn on a Runway N Jun 01/12

FIGURE 180˚ Turn on a Runway - Edge of Runway Method N Jun 01/12

Subject 4-5-4

135˚ Turn - Taxiway to Taxiway N Jun 01/12

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

N Jun 01/12

Subject 4-5-5

90˚ Turn - Taxiway to Taxiway R Jun 01/12

FIGURE 90˚ Turn - Taxiway to Taxiway - Cockpit Over CenterlineMethod

R Jun 01/12

Subject 4-6-0

Runway Holding Bay (Apron) R Jun 01/12

FIGURE Runway Holding Bay (Apron) R Jun 01/12

CHAPTER 5

Subject 5-0-0

Terminal Servicing R Jun 01/12

L.E.C.Page 8

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Subject 5-1-0

Airplane Servicing Arrangements R Jun 01/12

Subject 5-1-1

Symbols Used on Servicing Diagrams R Jun 01/12

Subject 5-1-2

Typical Ramp Layout - Open Apron R Jun 01/12

FIGURE Typical Ramp Layout - Open Apron - Bulk Loading R Jun 01/12

FIGURE Typical Ramp Layout - Open Apron - ULD Loading N Jun 01/12

Subject 5-1-3

Typical Ramp Layout - Gate R Jun 01/12

FIGURE Typical Ramp Layout - Gate R Jun 01/12

Subject 5-2-0

Terminal Operations - Full Servicing Turn Round Time N Jun 01/12

FIGURE Turn Round Stations - Full Servicing (43 Min.) N Jun 01/12

Subject 5-3-0

Terminal Operation - Minimum Servicing Turn Round Time N Jun 01/12

FIGURE Turn Round Stations - Minimum Servicing (23 Min.) N Jun 01/12

Subject 5-4-0

Ground Service Connections R Jun 01/12

Subject 5-4-1

Ground Service Connections Layout R Jun 01/12

FIGURE Ground Service Connections - Ground Service ConnectionsLayout

R Jun 01/12

Subject 5-4-2

Grounding Points R Jun 01/12

FIGURE Ground Service Connections - Grounding Points R Jun 01/12

FIGURE Ground Service Connections - Grounding Points R Jun 01/12

Subject 5-4-3

Hydraulic System R Jun 01/12

L.E.C.Page 9

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Hydraulic System - Green System Ground Service Panel R Jun 01/12

FIGURE Hydraulic System - Blue System Ground Service Panel R Jun 01/12

FIGURE Hydraulic System - Yellow System Ground Service Panel R Jun 01/12

Subject 5-4-4

Electrical System R Jun 01/12

FIGURE Ground Service Connections - External Power Receptacles R Jun 01/12

Subject 5-4-5

Oxygen System R Jun 01/12

Subject 5-4-6

Fuel System R Jun 01/12

FIGURE Ground Service Connections - Refuel/Defuel Panel R Jun 01/12

FIGURE Ground Service Connections - Refuel/Defuel Couplings R Jun 01/12

FIGURE Ground Service Connections - Gravity Refuel Couplings R Jun 01/12

FIGURE Ground Service Connections - Overpressure Protector andNACA Flame Arrestor

N Jun 01/12

Subject 5-4-7

Pneumatic System R Jun 01/12

Subject 5-4-8

Potable Water System R Jun 01/12

FIGURE Ground Service Connections - Potable Water Ground DrainPanel

R Jun 01/12

Subject 5-4-9

Oil System R Jun 01/12

FIGURE Ground Service Connections - Engine Oil Tank -- CFM56Series Engine

R Jun 01/12

FIGURE Ground Service Connections - IDG Oil Tank -- CFM56 SeriesEngine

R Jun 01/12

FIGURE Ground Service Connections - Starter Oil Tank -- CFM56Series Engine

R Jun 01/12

FIGURE Ground Service Connections - Engine Oil Tank -- IAE V2500Series Engine

R Jun 01/12

L.E.C.Page 10

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Ground Service Connections - IDG Oil Tank -- IAE V2500Series Engine

R Jun 01/12

FIGURE Ground Service Connections - Starter Oil Tank -- IAE V2500Series Engine

R Jun 01/12

FIGURE Ground Service Connections - APU Oil Tank R Jun 01/12

Subject 5-4-10

Vacuum Toilet System R Jun 01/12

FIGURE Ground Service Connections - Waste Water Ground ServicePanel

R Jun 01/12

Subject 5-5-0

Engine Starting Pneumatic Requirements R Jun 01/12

FIGURE Engine Starting Pneumatic Requirements N Jun 01/12

Subject 5-5-1

Low Ambient Temperatures R Jun 01/12

FIGURE Engine Starting Pneumatic Requirements - Low AmbientTemperature -40˚C (-40˚F) -- CFM56 series engine

R Jun 01/12

FIGURE Engine Starting Pneumatic Requirements - Low AmbientTemperature -40˚C (-40˚F) -- IAE V2500 series engine

R Jun 01/12

Subject 5-5-2

Medium Ambient Temperatures R Jun 01/12

FIGURE Engine Starting Pneumatic Requirements - Medium AmbientTemperature +15˚C (+59˚F) -- CFM56 series engine

R Jun 01/12

FIGURE Engine Starting Pneumatic Requirements - Medium AmbientTemperature +15˚C (+59˚F) -- IAE V2500 series engine

R Jun 01/12

Subject 5-5-3

High Ambient Temperatures R Jun 01/12

FIGURE Engine Starting Pneumatic Requirements - High AmbientTemperature +55˚C (+131˚F) -- CFM56 series engine

R Jun 01/12

FIGURE Engine Starting Pneumatic Requirements - High AmbientTemperature +50˚C (+122˚F) -- IAE V2500 series engine

R Jun 01/12

Subject 5-6-0

Ground Pneumatic Power Requirements R Jun 01/12

L.E.C.Page 11

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Subject 5-6-1

Heating R Jun 01/12

FIGURE Ground Pneumatic Power Requirements - Heating R Jun 01/12

Subject 5-6-2

Cooling R Jun 01/12

FIGURE Ground Pneumatic Power Requirements - Cooling R Jun 01/12

Subject 5-7-0

Preconditioned Airflow Requirements R Jun 01/12

FIGURE Preconditioned Airflow Requirements R Jun 01/12

Subject 5-8-0

Ground Towing Requirements R Jun 01/12

FIGURE Ground Towing Requirements R Jun 01/12

Subject 5-9-0

De-Icing and External Cleaning N Jun 01/12

CHAPTER 6

Subject 6-1-0

Engine Exhaust Velocities and Temperatures R Jun 01/12

Subject 6-1-1

Engine Exhaust Velocities Contours - Ground Idle Power R Jun 01/12

FIGURE Engine Exhaust Velocities - Ground Idle Power -- CFM56series engine

R Jun 01/12

FIGURE Engine Exhaust Velocities - Ground Idle Power -- IAE V2500series engine

R Jun 01/12

Subject 6-1-2

Engine Exhaust Temperatures Contours - Ground Idle Power R Jun 01/12

FIGURE Engine Exhaust Temperatures - Ground Idle Power -- CFM56series engine

R Jun 01/12

FIGURE Engine Exhaust Temperatures - Ground Idle Power -- IAEV2500 series engine

R Jun 01/12

Subject 6-1-3

L.E.C.Page 12

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Engine Exhaust Velocities Contours - Breakaway Power R Jun 01/12

FIGURE Engine Exhaust Velocities - Breakaway Power -- CFM56series engine

R Jun 01/12

FIGURE Engine Exhaust Velocities - Breakaway Power -- IAE V2500series engine

R Jun 01/12

Subject 6-1-4

Engine Exhaust Temperatures Contours - Breakaway Power R Jun 01/12

FIGURE Engine Exhaust Temperatures - Breakaway Power -- CFM56series engine

R Jun 01/12

FIGURE Engine Exhaust Temperatures - Breakaway Power -- IAEV2500 series engine

R Jun 01/12

Subject 6-1-5

Engine Exhaust Velocities Contours - Takeoff Power R Jun 01/12

FIGURE Engine Exhaust Velocities - Takeoff Power -- CFM56 seriesengine

R Jun 01/12

FIGURE Engine Exhaust Velocities - Takeoff Power -- IAE V2500series engine

R Jun 01/12

Subject 6-1-6

Engine Exhaust Temperatures Contours - Takeoff Power R Jun 01/12

FIGURE Engine Exhaust Temperatures - Takeoff Power -- CFM56series engine

R Jun 01/12

FIGURE Engine Exhaust Temperatures - Takeoff Power -- IAE V2500series engine

R Jun 01/12

Subject 6-2-0

Airport and Community Noise R Jun 01/12

Subject 6-2-1

Noise Data R Jun 01/12

FIGURE Airport and Community Noise - CFM56-5A series engine R Jun 01/12

FIGURE Airport and Community Noise - CFM56-5B series engine R Jun 01/12

FIGURE Airport and Community Noise - IAE V2500 series engine R Jun 01/12

Subject 6-3-0

L.E.C.Page 13

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Danger Areas of Engines R Jun 01/12

Subject 6-3-1

Ground Idle Power R Jun 01/12

FIGURE Danger Areas of Engines - CFM56 series engine R Jun 01/12

FIGURE Danger Areas of Engines - IAE V2500 series engine R Jun 01/12

Subject 6-3-2

Takeoff Power R Jun 01/12

FIGURE Danger Areas of Engines - CFM56 series engine R Jun 01/12

FIGURE Danger Areas of Engines - IAE V2500 series engine R Jun 01/12

Subject 6-4-0

APU Exhaust Velocities and Temperatures R Jun 01/12

Subject 6-4-1

APU - APIC & GARRETT R Jun 01/12

FIGURE Exhaust Velocities and Temperatures - APU -- APIC &GARRETT

R Jun 01/12

CHAPTER 7

Subject 7-1-0


FIGURE Aircraft Codes R Jun 01/12

Subject 7-2-0

Landing Gear Footprint R Jun 01/12

FIGURE Landing Gear Footprint May 01/11

FIGURE Landing Gear Footprint R Jun 01/12







L.E.C.Page 14

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE



Subject 7-3-0

Maximum Pavement Loads R Jun 01/12

FIGURE Maximum Pavement Loads R Jun 01/12






Subject 7-4-0

Landing Gear Loading on Pavement R Jun 01/12

Subject 7-4-1

Landing Gear Loading on Pavement R Jun 01/12

FIGURE Landing Gear Loading on Pavement R Jun 01/12










FIGURE Landing Gear Loading on Pavement N Jun 01/12

FIGURE Landing Gear Loading on Pavement N Jun 01/12

Subject 7-5-0

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

R Jun 01/12

L.E.C.Page 15

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Subject 7-5-1

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

R Jun 01/12

FIGURE Flexible Pavement Requirements May 01/11





FIGURE Flexible Pavement Requirements R Jun 01/12
















FIGURE Flexible Pavement Requirements - Flexible PavementRequirements

R Jun 01/12




L.E.C.Page 16

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE










Subject 7-6-0

Flexible Pavement Requirements - LCN Conversion R Jun 01/12

Subject 7-6-1

Flexible Pavement Requirements - LCN Conversion R Jun 01/12

FIGURE Flexible Pavement Requirements - LCN Conversion May 01/11















FIGURE Flexible Pavement Requirements - LCN Conversion R Jun 01/12

L.E.C.Page 17

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE



















Subject 7-7-0

Rigid Pavement Requirements - Portland Cement Association DesignMethod

R Jun 01/12

Subject 7-7-1

Rigid Pavement Requirements - Portland Cement Association DesignMethod

R Jun 01/12

FIGURE Rigid Pavement Requirements (PCA) May 01/11






L.E.C.Page 18

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE










FIGURE Rigid Pavement Requirements (PCA) R Jun 01/12



















Subject 7-8-1

L.E.C.Page 19

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Radius of Relative Stiffness R Jun 01/12

FIGURE Radius of Relative Stiffness - (Reference: Portland CementAssociation)

R Jun 01/12

Subject 7-8-2

Rigid Pavement Requirements - LCN Conversion R Jun 01/12

FIGURE Rigid Pavement Requirements - LCN Conversion R Jun 01/12

FIGURE Rigid Pavement Requirements - LCN Conversion May 01/11























L.E.C.Page 20

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE











Subject 7-8-3

Radius of Relative Stiffness (Other values of ”E” and ”L”) R Jun 01/12

Subject 7-8-4

Radius of Relative Stiffness R Jun 01/12

FIGURE Radius of Relative Stiffness - (Effect E and µ on ”L” values) R Jun 01/12

Subject 7-9-0

ACN/PCN Reporting System R Jun 01/12

Subject 7-9-1

Aircraft Classification Number - Flexible Pavement R Jun 01/12

FIGURE Aircraft Classification Number -- Flexible Pavement May 01/11










L.E.C.Page 21

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE






FIGURE Aircraft Classification Number -- Flexible Pavement R Jun 01/12



















Subject 7-9-2

Aircraft Classification Number - Rigid Pavement R Jun 01/12

FIGURE Aircraft Classification Number -- Rigid Pavement May 01/11



L.E.C.Page 22

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE













FIGURE Aircraft Classification Number -- Rigid Pavement R Jun 01/12

















L.E.C.Page 23

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE



CHAPTER 8

Subject 8-0-0

Scaled Drawings N Jun 01/12

FIGURE Scaled Drawing N Jun 01/12

CHAPTER 10

Subject 10-0-0

Aircraft Rescue and Fire Fighting N Jun 01/12

FIGURE Front Page N Jun 01/12

FIGURE Highly Flammable and Hazardous Materials and Components N Jun 01/12

FIGURE Wheel Safety Area N Jun 01/12

FIGURE Composite Materials N Jun 01/12

FIGURE LG Ground Lock Safety Devices N Jun 01/12

FIGURE Evacuation/Escape Slide/Raft N Jun 01/12

FIGURE Pax/Crew Doors N Jun 01/12

FIGURE Emergency Exit Hatch N Jun 01/12

FIGURE FWD and AFT Lower Deck Cargo Doors N Jun 01/12

FIGURE Control Panels N Jun 01/12

FIGURE APU Access Door N Jun 01/12

FIGURE Aircraft Ground Clearances N Jun 01/12

FIGURE Structural Break-in Points N Jun 01/12

L.E.C.Page 24

Jun 01/12


TABLE OF CONTENTS

1 SCOPE

1-1-0 Purpose

2 AIRCRAFT DESCRIPTION

2-1-0 General Aircraft Characteristics

2-1-1 General Aircraft Characteristics Data

2-2-0 General Aircraft Dimensions

2-3-0 Ground Clearances

2-4-0 Interior Arrangements

2-4-1 Passenger Compartment Layout

2-5-0 Passenger Compartment Cross Section

2-6-0 Cargo Compartments

2-7-0 Door Clearances

2-7-1 Forward Passenger / Crew Doors

2-7-2 Emergency Exits

2-7-3 Aft Passenger / Crew Doors

2-7-4 Forward Cargo Compartment Doors

2-7-5 Aft Cargo Compartment Doors

2-7-6 Bulk Cargo Compartment Doors

2-7-7 Main Landing Gear Doors

2-7-8 Radome

2-7-9 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 Power Plant

2-13-0 Leveling, Symmetry and Alignment

2-14-0 Jacking

3 AIRCRAFT PERFORMANCE

3-1-0 General Information

3-2-0 Payload / Range

3-2-1 ISA Conditions

3-3-0 FAR / JAR Takeoff Weight Limitation

T.O.C.Page 1

Jun 01/12



3-3-2 ISA +15˚C (+59˚F) Conditions

3-4-0 FAR / JAR Landing Field Length


3-5-0 Final Approach Speed

4 GROUND MANEUVERING


4-2-0 Turning Radii

4-3-0 Minimum Turning Radii

4-4-0 Visibility from Cockpit in Static Position

4-5-0 Runway and Taxiway Turn Paths

4-5-1 135˚ Turn - Runway to Taxiway


4-5-3 180˚ Turn on a Runway

4-5-4 135˚ Turn - Taxiway to Taxiway


4-6-0 Runway Holding Bay (Apron)

5 TERMINAL SERVICING

5-0-0 TERMINAL SERVICING

5-1-0 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 Operation - Transit

5-4-0 Ground Service Connections

5-4-1 Ground Service Connections Layout

5-4-2 Grounding Points

5-4-3 Hydraulic System

5-4-4 Electrical System

5-4-5 Oxygen System

5-4-6 Fuel System

5-4-7 Pneumatic System

5-4-8 Potable Water System

5-4-9 Oil System

5-4-10 Vacuum Toilet System

T.O.C.Page 2

Jun 01/12


5-5-0 Engine Starting Pneumatic Requirements

5-5-1 Low Ambient Temperatures

5-5-2 Medium Ambient Temperatures

5-5-3 High Ambient Temperatures

5-6-0 Ground Pneumatic Power Requirements

5-6-1 Heating

5-6-2 Cooling

5-7-0 Preconditioned Airflow Requirements

5-8-0 Ground Towing Requirements

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 Power

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

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

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

6-2-0 Airport and Community Noise

6-2-1 Noise Data

6-3-0 Danger Areas of Engines

6-3-1 Ground Idle Power

6-3-2 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 Conversion


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

T.O.C.Page 3

Jun 01/12



7-8-1 Radius of Relative Stiffness

7-8-2 Rigid Pavement Requirements - LCN Conversion

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


7-9-0 ACN/PCN Reporting System

7-9-1 Aircraft Classification Number - Flexible Pavement

7-9-2 Aircraft Classification Number - Rigid Pavement

8 SCALED DRAWINGS

8-0-0 SCALED DRAWINGS

10 AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 AIRCRAFT RESCUE AND FIRE FIGHTING

T.O.C.Page 4

Jun 01/12


SCOPE

1-1-0 Purpose

**ON A/C A320-200

Purpose

1. GeneralThe A320 AIRCRAFT CHARACTERISTICS -- AIRPORT AND MAINTENANCE PLANNING (AC)manual is issued for the A320-200 series aircraft, equipped with wing-tip fences or Sharklets toprovide necessary data to airport operators, airlines and Maintenance/Repair Organizations (MRO)for airport and maintenance facilities planning.

This revision is now a merge of the Maintenance Facility planning (MFP) document and the AirplaneCharacteristics 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.

The data given in this issue of the A320-200 AC equipped with Sharklets can be subject to changepending completion of the flight test phase. It is given for guidance only and does not constitute acontractual commitment.

This non-customized document conforms to NAS 3601 specification.This document must not be used for training purposes.

The single aisle A320 Family is a short to medium range aircraft delivering superior fuel efficiency,passenger comfort, environmental characteristics and economics, with a global market coverage.With record number of operators and wide market approval, the A320 Family benefits fromcontinuous improvements such as:- Sharklets- New Engine Option (neo)The A320 Family wider fuselage, advanced troubleshooting and Cargo Loading System enable easyand cost effective ground handling, whilst minimizing aircraft turn round time.

This document does not include the A320neo which is under development.

Correspondence concerning this publication should be directed to:

AIRBUS S.A.S.Customer ServicesTechnical Data Support and Services

1-1-0Page 1

Jun 01/12


1, Rond Point Maurice BELLONTE31707 BLAGNAC CEDEXFRANCE

1-1-0Page 2

Jun 01/12


AIRCRAFT DESCRIPTION

2-1-0 General Aircraft Characteristics

**ON A/C A320-200

General Airplane Characteristics

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

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

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

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

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

Standard Seating Capacity:Number of passengers specifically certified or anticipated for certification.

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

Usable Fuel Capacity:Fuel available for aircraft propulsion.

Water Volume:Volume of cargo compartment.

2-1-0Page 1

Jun 01/12


2-1-1 General Aircraft Characteristics Data

**ON A/C A320-200

General Airplane Characteristics Data

1. The following table provides characteristics of A320-200 Models, these data are specific to eachWeight Variant:

Aircraft CharacteristicsWV000 WV001 WV002 WV003 WV004

Kilograms 73 900 68 400 70 400 75 900 71 900Maximum Ramp Weight(MRW)Maximum Taxi Weight(MTW)

Pounds162 922 150 796 155 205 167 331 158 512

Kilograms 73 500 68 000 70 000 75 500 71 500Maximum TakeoffWeight (MTOW) Pounds 162 040 149 914 154 324 166 449 157 630

Kilograms 64 500 64 500 64 500 64 500 64 500Maximum LandingWeight (MLW) Pounds 142 198 142 198 142 198 142 198 142 198

Kilograms 60 500 60 500 60 500 60 500 60 500Maximum Zero FuelWeight (MZFW) Pounds 133 380 133 380 133 380 133 380 133 380



Pounds148 592 146 387 170 638 162 922 167 331






Pounds170 638 167 331 170 638 158 512 162 922

2-1-1Page 1

Jun 01/12






Aircraft CharacteristicsWV015 WV016 WV017 WV018

Kilograms 78 400 73 900 78 400 71 900Maximum Ramp Weight(MRW)Maximum Taxi Weight(MTW)

Pounds172 842 162 922 172 482 158 512

Kilograms 78 000 73 500 78 000 71 500Maximum Takeoff Weight(MTOW) Pounds 171 961 162 040 171 961 157 630

Kilograms 64 500 66 000 66 000 66 000Maximum Landing Weight(MLW) Pounds 142 198 145 505 145 505 145 505

Kilograms 61 000 62 500 62 500 62 500Maximum Zero Fuel Weight(MZFW) Pounds 134 482 137 789 137 789 137 789

2. The following table provides characteristics of A320-200 Models, these data are common to eachWeight Variant:

Aircraft CharacteristicsStandard Seating Capacity Single-class 180

Liters 23 859 - 26 759* - 29 659**US gallons 6 303 - 7 069* - 7 835**

Kilograms (density= 0.785 kg/l) 18 729 - 21 005* - 23 282**

Usable Fuel Capacity

Pounds 41 290 - 46 308* - 51 328**Cubic meters 330Pressurized Fuselage Volume

(A/C non equipped) Cubic feet 11 654

Cubic meters 139Passenger Compartment VolumeCubic feet 4 909Cubic meters 9Cockpit VolumeCubic feet 318Cubic meters 13.28Usable Volume, FWD CCCubic feet 469

2-1-1Page 2

Jun 01/12


Aircraft CharacteristicsCubic meters 18.26Usable Volume, AFT CCCubic feet 645Cubic meters 5.88Usable Volume, Bulk CCCubic meters 208Cubic meters 15.56Water Volume, FWD CCCubic feet 549.5Cubic meters 20.77Water Volume, AFT CCCubic feet 733.5Cubic meters 7.76Water Volume, Bulk CCCubic feet 274

* OPTION: 1 ACT** OPTION: 2 ACT

2-1-1Page 3

Jun 01/12


2-2-0 General Aircraft Dimensions

**ON A/C A320-200

General Aircraft Dimensions

1. This section provides General Aircraft Dimensions.

2-2-0Page 1

Jun 01/12


**ON A/C A320-200

12.64 m(41.47 ft)

5.07 m

(16.63 ft)

4.14

m(1

3.58

ft)

5.87

m

(19.

26 ft

)

RELATED TO AIRCRAFT ATTITUDE AND WEIGHTN_AC_020200_1_0040101_01_03

12.45 m(40.85 ft)

34.10 m(111.88 ft)

7.59 m(24.90 ft)

0.93 m(3.05 ft)

0.50 m(1.64 ft)

8.95 m(29.36 ft)

General Aircraft DimensionsWing Tip Fence (Sheet 1 of 4)

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

2-2-0Page 2

Jun 01/12


**ON A/C A320-200


37.57 m(123.26 ft)

5.75

m(1

8.86

ft)

11.9

1 m

(39.

07 ft

)

8.30

m(2

7.23

ft)

11.12 m(36.48 ft)

V2500

11.19 m(36.71 ft)

CFM56

3.95

m(1

2.96

ft)

4.87

m(1

5.98

ft)

General Aircraft DimensionsWing Tip Fence (Sheet 2 of 4)

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

2-2-0Page 3

Jun 01/12


**ON A/C A320-200

12.64 m(41.47 ft)

5.07 m(16.63 ft)

4.14

m(1

3.58

ft)

5.87

m

(19.

26 ft

)


7.59 m(24.90 ft)

0.93 m(3.05 ft)

0.50 m(1.64 ft)

12.45 m

(40.85 ft)

35.80 m

(117.45 ft)

8.95 m(29.36 ft)

3.79 m(12.43 ft)

2.43 m(7.97 ft)

General Aircraft DimensionsSharklet (Sheet 3 of 4)

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

2-2-0Page 4

Jun 01/12


**ON A/C A320-200

37.57 m(123.26 ft)

5.75

m(1

8.86

ft)

11.9

1 m

(39.

07 ft

)

8.30

m(2

7.23

ft)

11.13 m(36.52 ft)

V2500

11.19 m(36.71 ft)

CFM56

RELATED TO AIRCRAFT ATTITUDE AND WEIGHT

3.95

m(1

2.96

ft)

4.87

m(1

5.98

ft)

16.2

9 m

(53.

44 ft

)

1.61 m(5.28 ft)

3.22 m(10.56 ft)

1.64 m(5.38 ft)

23.45 m(76.94 ft)

N_AC_020200_1_0040105_01_00

General Aircraft DimensionsSharklet (Sheet 4 of 4)

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

2-2-0Page 5

Jun 01/12


2-3-0 Ground Clearances

**ON A/C A320-200

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, weight and balance and otherspecial conditions.

The dimensions are given for:- a light weight, for an A/C in maintenance configuration with a mid CG,- the MRW for a light weight variant with a FWD CG and a AFT CG,- the MRW for a heavy weight variant with a FWD CG and a AFT CG,- aircraft on jacks, FDL at 4.6 m (15.09 ft).

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

2-3-0Page 1

Jun 01/12


**ON A/C A320-200

A

CG 26.5% FWD CG 17% FWD CG 17% AFT CG 36.8%

11.426.865.976.40

19.5919.982.202.795.648.9210.3311.457.28

BC1C2D1D2

E (CFM)E (IAE)

FF1F2F3G

11.096.535.686.10

19.2619.681.902.495.358.63

10.0411.156.99

11.426.765.875.87

19.4619.461.942.535.288.539.9511.026.79

11.326.695.775.87

19.3619.461.902.495.258.539.94

13.558.897.977.9721.5921.594.074.667.41

10.6612.07

12.14H 11.84 11.45

11.02 13.166.79 8.8911.48 13.55

39.63J 39.37 38.75 38.81 40.8512.76K1 12.47 12.27 12.27 14.3715.94K2 15.65 15.45 15.45 17.5518.24L 17.95 17.36 17.45 19.467.51M 7.22 6.92 6.92 9.02

13.06N 12.73 12.76 12.73 14.89

AFT CG 40%

14.04P 13.68 14.14 14.01 16.2715.88Q 15.62 14.96 15.06 17.06

11.096.505.646.0419.2319.651.872.465.318.5610.0111.126.9611.8139.3012.4015.6217.917.19

12.7013.6815.55

P B D1 E C2 M Q JC1 D2G

L F F1 F2 F3

K1 K2

3.482.091.821.955.976.090.670.851.722.723.153.492.223.70

12.083.894.865.562.293.984.284.84

3.381.991.731.865.876.000.580.761.632.633.063.402.133.61

12.003.804.775.472.203.884.174.76

3.482.061.791.795.935.930.590.771.612.603.033.362.073.4911.813.744.715.292.113.894.314.56

3.381.981.721.845.865.990.570.751.622.613.053.392.123.6011.983.784.765.462.193.874.174.74

3.452.041.761.795.905.930.580.761.602.603.033.362.073.5011.833.744.715.322.113.884.274.59

4.132.712.432.436.586.581.241.422.263.253.684.012.714.13

12.454.385.355.932.754.544.965.20

m ft m ft m ft m ft m ft m ft

NOTE:FROM THE CENTER OF THE DOOR SILL AND FROM FLOOR LEVEL.

A/C JACKED FDLA/CCONFIG−URATION

41 t 74 tMRW

78 tMRW

= 4.60 m(15.09 ft)

A

N

N_AC_020300_1_0040101_01_05

PASSENGER AND CARGO DOOR GROUND CLEARANCES ARE MEASURED

H

Ground ClearancesFIGURE-2-3-0-991-004-A01

2-3-0Page 2

Jun 01/12


**ON A/C A320-200

N_AC_020300_1_0290101_01_00

A

CG 26.5% FWD CG 17% FWD CG 17% AFT CG 36.8%

11.426.865.976.40

19.5919.982.202.795.648.9210.3311.457.28

BC1C2D1D2

E (CFM)E (IAE)

FF1F2F3G

11.096.535.686.10

19.2619.681.902.495.358.63

10.0411.156.99

11.426.765.875.87

19.4619.461.942.535.288.539.9511.026.79

11.326.695.775.87

19.3619.461.902.495.258.539.94

13.558.897.977.97

21.5921.594.074.667.41

10.6612.07

12.14H 11.84 11.45

11.02 13.166.79 8.8911.48 13.55

39.63J 39.37 38.75 38.81 40.8513.65K1 13.35 13.16 13.16 15.2622.31K2 22.01 21.82 21.82 23.7918.24L 17.95 17.36 17.45 19.467.51M 7.22 6.92 6.92 9.02

13.06N 12.73 12.76 12.73 14.89

AFT CG 40%

14.04P 13.68 14.14 14.01 16.2715.88Q 15.62 14.96 15.06 17.06

11.096.505.646.0419.2319.651.872.465.318.5610.0111.126.9611.8139.3013.2921.9817.917.19

12.7013.6815.55

3.482.091.821.955.976.090.670.851.722.723.153.492.223.70

12.084.166.805.562.293.984.284.84

3.381.991.731.865.876.000.580.761.632.633.063.402.133.61

12.004.076.715.472.203.884.174.76

3.482.061.791.795.935.930.590.771.612.603.033.362.073.4911.814.016.655.292.113.894.314.56

3.381.981.721.845.865.990.570.751.622.613.053.392.123.6011.984.056.705.462.193.874.174.74

3.452.041.761.795.905.930.580.761.602.603.033.362.073.5011.834.016.655.322.113.884.274.59

4.132.712.432.436.586.581.241.422.263.253.684.012.714.13

12.454.657.255.932.754.544.965.20

m ft m ft m ft m ft m ft m ft

NOTE:PASSENGER AND CARGO DOOR GROUND CLEARANCES ARE MEASUREDFROM THE CENTER OF THE DOOR SILL AND FROM FLOOR LEVEL.

P A B C1 E C2 G M H Q

F3F2F1FL

JD1

K2

K1

42 tMRW74 t

MRW78 t

A/C JACKED

= 4.60 m(15.09 ft)

FDLA/CCONFIG−URATION

D2

N

Ground ClearancesGround Clearances with Sharklets

FIGURE-2-3-0-991-029-A01

2-3-0Page 3

Jun 01/12


**ON A/C A320-200

m ft m ft m ft

A

B

C

D

A/C IN MAINTENANCECONFIGURATION MID CG

MAXIMUM RAMPWEIGHT FWD CG

MAXIMUM RAMPWEIGHT AFT CG

HEIGHT FROM GROUND

2.09

2.82

2.86

3.68

1.99

2.71

2.75

3.56

1.96

2.69

2.72

3.52

6.86 6.53 6.43

11.5511.6812.07

9.25

9.38

8.89

9.02

8.83

8.92

CFM 56 ENGINE

DCBA

N_AC_020300_1_0160101_01_00

2.18

2.66

3.10

7.15

8.73

10.17

2.08

2.55

2.99

6.82

8.37

9.81

2.05

2.52

2.95

6.73

8.27

9.68

E

F

G

E F G

Ground ClearancesFlaps and Flap Track Fairings When Flaps Fully Extended

FIGURE-2-3-0-991-016-A01

2-3-0Page 4

Jun 01/12


**ON A/C A320-200

m ft

6.86

8.50

9.94

6.73

11.94

9.09

9.22

m ft m ft

A

B

C

D




HEIGHT FROM GROUNDIAE V2500 ENGINE

DCBA

2.09

2.59

3.03

1.98

2.48

2.92

6.49

8.14

9.58

1.95

2.44

2.88

6.40

8.01

9.45

E

F

G

E F G

N_AC_020300_1_0170101_01_00

2.05

2.77

2.81

3.64

1.94

2.66

2.70

3.53

1.92

2.64

2.68

3.49

6.37 6.30

11.4511.58

8.73

8.86

8.66

8.78

Ground ClearancesFlaps and Flap Track Fairings When Flaps Fully Extended

FIGURE-2-3-0-991-017-A01

2-3-0Page 5

Jun 01/12


**ON A/C A320-200

2.68

3.08

3.48

2.58

2.98

3.37

2.56

2.95

3.34

8.79 8.46 8.40

10.11

11.42

9.78

11.06

9.68

10.96

KJH

N_AC_020300_1_0180101_01_00

m ft m ft m ft

H

J

K




HEIGHT FROM GROUND

Ground ClearancesFlap Track Fairings Up

FIGURE-2-3-0-991-018-A01

2-3-0Page 6

Jun 01/12


**ON A/C A320-200

4.17

3.83

4.06

3.72 12.21

13.32 4.01

3.68 12.07

13.1613.68

12.57

L M

N_AC_020300_1_0190101_01_00

m ft m ft m ft

L

M




HEIGHT FROM GROUND

Ground ClearancesAileron Down

FIGURE-2-3-0-991-019-A01

2-3-0Page 7

Jun 01/12


**ON A/C A320-200

4.01

3.75

14.67

14.27

13.35

13.16

12.30

4.48

4.36

4.24

4.11

3.96

3.90

3.64

14.70

14.31

13.91

13.48

12.99

12.80

11.94

4.45

4.33

4.21

4.08

3.94

3.88

3.63

14.60

14.21

13.81

13.39

12.93

12.73

11.91

13.814.21

4.35

4.47

4.59 15.06

4.07

P R S T WU V

m ft m m




HEIGHT FROM GROUND

Q

R

N

P

ft ft

U

V

S

T

W

14.27

4.44

4.24

14.57

13.91

4.39

4.20

14.40

13.784.35

4.55 14.93

N Q

N_AC_020300_1_0200101_01_00

Ground ClearancesAileron Up and Spoilers 1 to 5 Extended

FIGURE-2-3-0-991-020-A01

2-3-0Page 8

Jun 01/12


**ON A/C A320-200

2.57

2.98

3.07

3.36

3.61

3.86

4.09 13.42

12.66

11.84

11.02

10.07

9.78

8.43 2.48

2.88

2.97

3.26

3.51

3.76

3.98 13.06 3.95 12.96

12.243.7312.34

11.52 3.50 11.48

10.703.2610.70

9.74 2.98 9.78

9.512.909.45

8.14 2.50 8.20

XA’ B’ C’ D’ E’ F’ G’Y Z

N_AC_020300_1_0210101_01_00

m ft m ft m ft

C’

D’

E’



HEIGHT FROM GROUND

F’

G’


X

Y

Z

A’

B’

Ground ClearancesSlats Extended

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

2-3-0Page 9

Jun 01/12


2-4-0 Interior Arrangements

**ON A/C A320-200

Interior Arrangements

1. This section gives the standard interior arrangements configuration.

2-4-0Page 1

Jun 01/12


2-4-1 Passenger Compartment Layout

**ON A/C A320-200

Typical Configuration

1. This section gives the typical interior configuration.

2-4-1Page 1

Jun 01/12


**ON A/C A320-200

FW

D P

AS

SE

NG

ER

/CR

EW

DO

OR

FW

D P

AS

SE

NG

ER

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

S

EM

ER

GE

NC

Y E

XIT

S

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

180

SE

AT

S A

LL T

OU

RIS

T C

LAS

S

28/2

9 in

PIT

CH

. 6 A

BR

EA

ST

. 3.3

LA A

A A

G

G

LAL

ITE

MD

ES

IGN

AT

ION

GG

ALL

EY

(2)

LLA

VA

TO

RY

(3)

AA

TT

EN

DA

NT

SE

AT

(5)

N_AC_020401_1_0030101_01_02

Typical ConfigurationTypical Configuration Single-Class, High Density

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

2-4-1Page 2

Jun 01/12


**ON A/C A320-200

FW

D P

AS

SE

NG

ER

/CR

EW

DO

OR

FW

D P

AS

SE

NG

ER

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

S

EM

ER

GE

NC

Y E

XIT

S

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

LA A

A

G

G

LAL

12 S

UP

ER

FIR

ST

CLA

SS

138

EC

ON

OM

Y C

LAS

S

PA

SS

EN

GE

R S

EA

TS

(15

0 T

OT

AL)

SE

AT

PIT

CH

ES

: F

IRS

T 3

6 in

ITE

MD

ES

IGN

AT

ION

GG

ALL

EY

(2)

LLA

VA

TO

RY

(3)

AA

TT

EN

DA

NT

SE

AT

(4)

N_AC_020401_1_0090101_01_00

EC

ON

OM

Y 3

2 in

Typical ConfigurationTypical Configuration Two-Class

FIGURE-2-4-1-991-009-A01

2-4-1Page 3

Jun 01/12


2-5-0 Passenger Compartment Cross Section

**ON A/C A320-200

Passenger Compartment Cross-section

1. This section gives the typical passenger compartment cross-section configuration.

2-5-0Page 1

Jun 01/12


**ON A/C A320-200

3.95(155.51)

Cargo CompartmentFloor

CABINFLOOR

Top of cargoCompartment

AircraftDatum

Windows

2.64

(103.94)

2.13(83.86)

1.60(62.99)

1.24(48.82)

NOTE: DIMENSIONS m (in)

0.49(19.29)

0.52(20.47)

N_AC_020500_1_0010101_01_01

3.45(135.83)

3.68

(144.88)

1.42(55.91)

Passenger Compartment Cross-sectionFIGURE-2-5-0-991-001-A01

2-5-0Page 2

Jun 01/12


**ON A/C A320-200


1.24

(48.

9)2.

21(8

7)

6 ABREAST−WIDER AISLE

4.14

(163

)

3.95(155.5)

3.64(143)

1.50(59)

0.64(25)

1.50(59)

0.432(17)

N_AC_020500_1_0050101_01_00

Passenger Compartment Cross-sectionEconomy Class, 6 Abreast - Wider Aisle (Sheet 1 of 2)

FIGURE-2-5-0-991-005-A01

2-5-0Page 3

Jun 01/12


**ON A/C A320-200


6 ABREAST−WIDER SEAT

3.95(155.5)

3.64(143)

1.58(62)

0.48(19)

1.58(62)

1.24

(48.

9)2.

21(8

7)

4.14

(163

)

0.457(18)

N_AC_020500_1_0050102_01_02

Passenger Compartment Cross-sectionEconomy Class, 6 Abreast - Wider Seat (Sheet 2 of 2)

FIGURE-2-5-0-991-005-A01

2-5-0Page 4

Jun 01/12


**ON A/C A320-200


4 ABREAST−FIRST CLASS

3.95(155.5)

1.24

(48.

9)2.

21(8

7)

4.14

(163

)

3.59(141)

0.69(27)

1.45(57)

1.45(57)

(22.6)0.57

N_AC_020500_1_0060101_01_00

Passenger Compartment Cross-sectionPassenger Compartment Cross-section, First-class

FIGURE-2-5-0-991-006-A01

2-5-0Page 5

Jun 01/12


2-6-0 Cargo Compartments

**ON A/C A320-200

Cargo Compartments

1. This section gives the cargo compartments locations, dimensions and loading combinations.

2-6-0Page 1

Jun 01/12


**ON A/C A320-200

9.8

m(3

85.8

3 in

)

4.95

m

(194

.88

in)

1.81

m(7

1.26

in)

1.81

m(7

1.26

in)

0.86

m(3

3.85

in)

FW

D C

AR

GO

CO

MP

AR

TM

EN

T(3

CO

NT

AIN

ER

S)

AF

T C

AR

GO

CO

MP

AR

TM

EN

T(4

CO

NT

AIN

ER

S)

BU

LK C

AR

GO

CO

MP

AR

TM

EN

T

FR

24A

FR

34F

R47

FR

59F

R65

N_AC_020600_1_0030101_01_00

Cargo CompartmentsLocations, Dimensions and Loading Combinations

FIGURE-2-6-0-991-003-A01

2-6-0Page 2

Jun 01/12


2-7-0 Door Clearances

**ON A/C A320-200

Doors Clearances

1. This section gives doors clearances.

2-7-0Page 1

Jun 01/12


2-7-1 Forward Passenger / Crew Doors

**ON A/C A320-200

Forward Passenger / Crew Doors

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

2-7-1Page 1

Jun 01/12


**ON A/C A320-200

CRITICAL

CLEARANCE LIMIT

0.61 m(2 ft)

0.48 m(1 ft 6.88 in)

2.54 m(8 ft 3.99 in)

5.02 m(16 ft 5.62 in)

1.8 m(5 ft 10.8 in) 0.81 m

(2 ft 7.8 in)

1.85 m(6 ft 0.82 in)

SEECHAPTER

2.375 m(7 ft 9.48 in)

2−3

CL

CLCL

0.03 m(1.18 in)

N_AC_020701_1_0030101_01_00

Doors ClearancesForward Passenger / Crew Doors

FIGURE-2-7-1-991-003-A01

2-7-1Page 2

Jun 01/12


2-7-2 Emergency Exits

**ON A/C A320-200

Emergency Exits

1. This section gives emergency exits doors clearances.

2-7-2Page 1

Jun 01/12


**ON A/C A320-200

(FRAME 47)

NOTE: ESCAPE SLIDE COMPARTMENT DOOROPENS ON WING UPPER SURFACE.

(FROM NOSE)

CL0.47 m

(1ft 6.49 in)

1.23 m(4 ft 0.42 in)

0.2 m(7.87 in)

FWD

0.9 m(2 ft 11.4 in)

0.495 m(1ft 7.48 in)

(TOP OF FLOOR)

0.12 m(4.72 in)

B B

A

A

B

B

CL

A A

SEESECTION

2−3

14.43 m(47 ft 4.1 in)

0.85 m

(2 ft 9.45 in)

0.5 m(1ft 7.68 in)

N_AC_020702_1_0040101_01_00

Doors ClearancesEmergency Exits

FIGURE-2-7-2-991-004-A01

2-7-2Page 2

Jun 01/12


2-7-3 Aft Passenger / Crew Doors

**ON A/C A320-200

Aft Passenger / Crew Doors

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

2-7-3Page 1

Jun 01/12


**ON A/C A320-200

29.64 m(97 ft 2.9 in)

(FROM NOSE)

2.44 m(8 ft)

1.85 m(6 ft 0.82 in)

0.6 m(1 ft 11.6 in)

(1.18 in)0.03 m

SEE

2−3CHAPTER

A A

1.79 m(5 ft 10.46 in)

0.81 m(2 ft 7.88 in)

0.58 m(1 ft 10.8 in)

CRITICALCLEARANCE

LIMIT

FWD

A

A

N_AC_020703_1_0030101_01_00

Doors ClearancesAft Passenger / Crew DoorsFIGURE-2-7-3-991-003-A01

2-7-3Page 2

Jun 01/12


2-7-4 Forward Cargo Compartment Doors

**ON A/C A320-200

Forward Cargo Compartment Door

1. This section gives forward cargo compartment door clearances.

2-7-4Page 1

Jun 01/12


**ON A/C A320-200

1.24 m

3.945 m(12 ft 11.3 in)

1.495 m(4 ft 10.84 in)

A A

8.16 m

(26 ft 9.25 in)

1.82 m(5 ft 11.65 in)

CFM ENGINE = 2.29 m (7 ft 6.15 in)V2500 ENGINE = 2.04 m (6 ft 8.3 in)

(FROM NOSE)

2.71 m(8 ft 10.69 in)

A

A

FWD

2−3

SEECHAPTER(4 ft 0.81 in)

N_AC_020704_1_0030101_01_00

Doors ClearancesForward Cargo Compartment Door

FIGURE-2-7-4-991-003-A01

2-7-4Page 2

Jun 01/12


2-7-5 Aft Cargo Compartment Doors

**ON A/C A320-200

Aft Cargo Compartment Door

1. This section gives Aft cargo compartment door clearances.

2-7-5Page 1

Jun 01/12


**ON A/C A320-200

22.69 m

(74 ft 5.3 in)

1.82 m(5 ft 11.65 in)

(FROM NOSE)

FWD

FWD

A

A

2.03 m(6 ft 7.92 in)

1.23 m(4 ft 0.42 in)

3.945 m

(12 ft 11.3 in)

1.43 m(4 ft 8.29 in)

2−3

SEECHAPTER

A A

N_AC_020705_1_0030101_01_00

Doors ClearancesAft Cargo Compartment DoorFIGURE-2-7-5-991-003-A01

2-7-5Page 2

Jun 01/12


2-7-6 Bulk Cargo Compartment Doors

**ON A/C A320-200

Bulk Cargo Compartment Door

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

2-7-6Page 1

Jun 01/12


**ON A/C A320-200

0.95 m(3 ft 1.39 in)

0.89 m(2 ft 11 in)

FWD

2.19 m(7 ft 2.22 in)

6.10 m(20 ft)

0.77 m(2 ft 6.31 in)

2−3

SEECHAPTER

A

A

A A

N_AC_020706_1_0010101_01_01

Doors ClearancesBulk Cargo Compartment Door

FIGURE-2-7-6-991-001-A01

2-7-6Page 2

Jun 01/12


2-7-7 Main Landing Gear Doors

**ON A/C A320-200

Main Landing Gear Doors

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

2-7-7Page 1

Jun 01/12


**ON A/C A320-200

A

NOTE: VALUE OF CG: 25% RC.

16.358 m(53 ft 8 in)

1.826 m(5 ft 11.88 in)

GROUND LINE

0.207 m

(8.14 in)

0.485 m

(1 ft 7.09 in)

AIRCRAFT

1.23 m(4 ft 0.42 in)

0.14 m(5.51 in)

1.761 m(5 ft 9.32 in)

84°

1.942 m(6 ft 4.45 in)

A

N_AC_020707_1_0030101_01_02

Doors ClearancesMain Landing Gear Doors

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

2-7-7Page 2

Jun 01/12


**ON A/C A320-200

GROUND LINE1.268 m

(4 ft 1.92 in)

0.16 m(6.29 in)

1.761 m(5 ft 9.32 in)

0.485 m

(1 ft 7.09 in)

1.942 m(6 ft 4.45 in)

82.5°


AIRCRAFT

A

16.227 m(53 ft 2.85 in)

2.23 m(7 ft 3.79 in)

A

N_AC_020707_1_0040101_01_02

Doors ClearancesMain Landing Gear Doors (Bogie)

FIGURE-2-7-7-991-004-A01

2-7-7Page 3

Jun 01/12


2-7-8 Radome

**ON A/C A320-200

Radome

1. This section gives the radome clearances.

2-7-8Page 1

Jun 01/12


**ON A/C A320-200

0.63 m(2 ft 0.79 in)

STA 3500FR1

65°

(5 ft 0.62 in)1.54 m

N_AC_020708_1_0030101_01_00

Doors ClearancesRadome

FIGURE-2-7-8-991-003-A01

2-7-8Page 2

Jun 01/12


2-7-9 APU and Nose Landing Gear Doors

**ON A/C A320-200

APU and Nose Landing Gear Doors

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

2-7-9Page 1

Jun 01/12


**ON A/C A320-200

FR80

FR84

3.23

m(1

0 ft

7.16

in)

3.86

m(1

2 ft

7.96

in)


1.5

m(4

ft 1

1 in

)

1.4

m(4

ft 7

.11

in)

N_AC_020709_1_0030101_01_00

Doors ClearancesAPU and Nose Landing Gear Doors

FIGURE-2-7-9-991-003-A01

2-7-9Page 2

Jun 01/12


2-8-0 Escape Slides

**ON A/C A320-200

Escape Slides

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

2. LocationEscape facilities are provided at the following locations:- one slide-raft at each passenger/crew door (total four)- one slide for emergency exit doors (total two). Dual lane offwing escape slides are installed above

the wings in the left and right wing-to-fuselage fairings for off-the-wing evacuation.

2-8-0Page 1

Jun 01/12


**ON A/C A320-200

FWD CABIN ESCAPE SLIDE

OFF WING ESCAPE SLIDE

N_AC_020800_1_0050101_01_00

AFT CABINESCAPE SLIDE

Escape SlidesLocation

FIGURE-2-8-0-991-005-A01

2-8-0Page 2

Jun 01/12


**ON A/C A320-200

N_AC_020800_1_0060101_01_00

EMERGENCY DESCENT DEVICETHROUGH WINDOW OPENING

GRID EQUALS 1 m (3.28 ft) IN REALITY

Escape SlidesDimensions

FIGURE-2-8-0-991-006-A01

2-8-0Page 3

Jun 01/12


2-9-0 Landing Gear

**ON A/C A320-200

Landing Gear

1. General

The landing gear is of the conventional retractable tricycle type comprising:- Two main gears with twin wheel or four wheels bogie assembly,- A twin wheel nose gear.

The main landing gear twin wheel landing gears are located under the wing and retract sidewaystowards the fuselage centerline.The nose landing gear retracts forward into a fuselage compartment located between STA 5394/FR 9and STA 8077/FR 20.

The landing gear and landing gear doors operation is controlled electrically and hydraulicallyoperated.In abnormal operation, the landing gear can be extended by gravity.

For landing gear footprint and tire size, refer to 7-2-0.

2. Main Landing Gear

A. Twin wheel

Each of the two main landing gear assemblies consists of a conventional two wheel direct typewith an integral shock absorber supported in the fore and aft direction by a fixed drag strut andlaterally by a folding strut mechanically locked when in the DOWN position.

B. Four wheels - Bogie

Each of the two main landing gear assemblies consists of a direct action shock absorber onwhich is installed a bogie beam and four wheels.The shock absorber is supported in the fore and aft direction by a fixed drag strut and laterallyby a folding strut mechanically locked when in the DOWN position.

3. Nose Landing Gear

The nose landing gear comprises a leg with a built-in shock absorber strut, carrying twin wheel withadequate shimmy damping and a folding strut mechanically locked when in the DOWN position.

4. Nose Wheel Steering

Steering is controlled by two hand wheels in the cockpit. For steering angle controlled by the handwheels, refer to AMM 32-51-00.For steering angle limitation, refer to AMM 09-10-00.

2-9-0Page 1

Jun 01/12


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

5. Landing Gear Servicing Points

A. General

Filling of the landing gear shock absorbers is through MS28889 standard valves.

Charging of the landing gear shock absorbers is accomplished with nitrogen through MS28889standard valves.

B. Charging Pressure

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

6. Braking

A. General

The four main wheels are equipped with carbon multidisc brakes.

The braking system is electrically controlled and hydraulically operated.

The braking system has four braking modes plus autobrake and anti-skid systems:- Normal braking with anti-skid capability- Alternative braking with anti-skid capability- Alternative braking without anti-skid capability- Parking brake with full pressure application capability only.

B. In-Flight Wheel Braking

The main gear wheels are braked automatically before the wheels enter the wheel bay.

The nose gear wheels are stopped by the wheels contacting a rubbing strip (the brake band)when the gear is in the retracted position.

2-9-0Page 2

Jun 01/12


**ON A/C A320-200

TORQUELINK

DOWNLOCKACTUATOR

MAIN FITTING

SHOCK ABSORBER

SIDE STAY

ACTUATING CYLINDER

LOCK STAY

A

E

D

MAIN DOOR SHOWN OPEN IN GROUND MAINTENANCE POSITION.NOTE: N_AC_020900_1_0100101_01_00

MAIN DOOR(HYDRAULICALLY OPERATED)

FIXEDRAMPS

UPLOCKROLLER

ADJUSTABLERAMP

STEPS

FIXEDFAIRING

HINGEDFAIRING

HINGED FAIRING(MECHANICALLY OPERATED)

PROXIMITY SENSORS

DOOR ACTUATING CYLINDER

A

B

C

Landing GearMain Landing Gear - Twin Wheel (Sheet 1 of 2)

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

2-9-0Page 3

Jun 01/12


**ON A/C A320-200

DOORACTUATINGCYLINDER

FLAG

LOCKSTAYACTUATINGCYLINDER

GROUND LOCK SLEEVE

FLAG

BC

LOCKINGPIN

LOCKINGPIN

N_AC_020900_1_0100102_01_00

BOTTOM FILLING ANDCHARGING CONNECTIONMS28889

EDEXAMPLE

TOP FILLING AND CHARGING CONNECTION MS28889

Landing GearMain Landing Gear - Twin Wheel (Sheet 2 of 2)

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

2-9-0Page 4

Jun 01/12


**ON A/C A320-200

N_AC_020900_1_0110101_01_00

Y=COMPRESSED

EXTENDED

58.4

0 %

AM

C

3 795 mm

3 453 mm(135.94 in) 80°30

RETRACTIONANGLE

(36.50 in)927.10 mm

2 868.70 mm(112.94 in)

2 265 mm(89.17 in)

X= 20 252.50 mm(797.34 in)

469.90 mm(18.50 in)

(149.41 in)

Landing GearMain Landing Gear Dimensions - Twin Wheel

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

2-9-0Page 5

Jun 01/12


**ON A/C A320-200

DOWNLOCKACTUATOR

ACTUATING CYLINDER

LOCK STAY

LEG UNIT

SHOCK ABSORBER

PITCH TRIMMER

BRAKE BAR

TORQUELINK

STRUT ASSEMBLY

HINGEDFAIRING

FIXEDFAIRING

AJUSTABLERAMP

UPLOCKROLLER

DOORRAMPS

STEPS

MAIN DOOR

A

D

DOOR ACTUATINGCYLINDER B

MAIN DOOR SHOWN OPEN IN GROUND MAINTENANCE POSITION.NOTE:

A

N_AC_020900_1_0120101_01_00

C

Landing GearMain Landing Gear - Four Wheels - Bogie (Sheet 1 of 2)

FIGURE-2-9-0-991-012-A01

2-9-0Page 6

Jun 01/12


**ON A/C A320-200


FLAG

TOP FILLING AND CHARGING CONNECTION MS28889

LOCKSTAYACTUATINGCYLINDER

GROUND LOCK SLEEVE

FLAG

BC

LOCKINGPIN

LOCKINGPIN

DN_AC_020900_1_0120102_01_00

Landing GearMain Landing Gear - Four Wheels - Bogie (Sheet 2 of 2)

FIGURE-2-9-0-991-012-A01

2-9-0Page 7

Jun 01/12


**ON A/C A320-200

1 005 mm(39.57 in)

780 mm(30.71 in)

80°30RETRACTION

Y = 3 795 mm(149.41 in)

ANGLE

X = 20 266 mm(797.87 in)

419.

10 m

m(1

6.50

in)

COMPRESSED

EXTENDED

2 506 mm(98.66 in)

2 978.70 mm(117.27 in)

58.4

0 %

AM

C

N_AC_020900_1_0130101_01_00

Landing GearMain Landing Gear Dimensions - Four Wheels - Bogie

FIGURE-2-9-0-991-013-A01

2-9-0Page 8

Jun 01/12


**ON A/C A320-200

N_AC_020900_1_0140101_01_00

ACTUATINGCYLINDER

NOSE WHEELSTEERINGSERVO CONTROL

STEERINGACTUATINGCYLINDER

TORQUELINK

DOWNLOCKPROXIMITY

DETECTORS

SHOCKABSORBER

TOWINGFITTING

LEG DOOR

AFT DOORS

ASSEMBLYFITTING

FWD DOORS

CONTROL ROD


CRANK

DOOR UPLOCKASSEMBLY GEAR UPLOCK

ASSEMBLY

BELL

FR20

FR9

DRAG STRUTASSEMBLY

A

A

ROTATING ROD

BC

E

D

Landing GearNose Landing Gear (Sheet 1 of 2)

FIGURE-2-9-0-991-014-A01

2-9-0Page 9

Jun 01/12


**ON A/C A320-200

TOWING LEVER

(NOSE WHEEL STREERINGNORMAL POSITION

(TOWING POSITION)SAFETY PIN

(NOSE WHEEL STEERING DEACTIVATED)TOWING POSITION

E

DOOR HINGE

NLG DOOR

NLG DOORSAFETY PIN

FLAG

LH SYMMETRICALRH SHOWN

C

D

OPERATIONAL)

FLAG

DOWNLOCKSAFETY PIN

LOCKSTAY

B

N_AC_020900_1_0140102_01_00

CONNECTION MS28889FILLING AND CHARGING

Landing GearNose Landing Gear (Sheet 2 of 2)

FIGURE-2-9-0-991-014-A01

2-9-0Page 10

Jun 01/12


**ON A/C A320-200

N_AC_020900_1_0150101_01_00

92°

9°

X =

500 mm(19.69 in)

7 561 mm(297.68 in)

430 mm(16.93 in)

1 957.03 mm(77.05 in)

2 338 mm(92.05 in)

EXTENDED

COMPRESSED

Landing GearNose Landing Gear Dimensions

FIGURE-2-9-0-991-015-A01

2-9-0Page 11

Jun 01/12


**ON A/C A320-200

Landing Gear Maintenance Pits

1. Description

The minimum maintenance pit envelopes for the main gear shock absorber removal are shown inFigures 1 and 2.

All dimensions shown are minimum dimensions with zero clearances.

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

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

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

2-9-0Page 12

Jun 01/12


**ON A/C A320-200

= =

==

7.61

m(2

4.97

ft)

5.28

m

1 m

(3.2

8 ft)

1.5

m(4

.92

ft)

(17.

32 ft

)

1.92

m(6

.30

ft)

20.2

5 m

(66.

44 ft

)

20.1

0 m

(65.

94 ft

)

7.59

m(2

4.90

ft)

2.95

m(9

.68

ft)

3.76

m(1

2.34

ft)

3.79

m(1

2.43

ft)

6.49

m(2

1.29

ft)

2.5

m(8

.20

ft)

MA

IN J

AC

KIN

G P

OIN

TM

AIN

JA

CK

ING

PO

INT

MA

IN J

AC

KIN

G P

OIN

T

FROM X0

FW

D J

AC

KIN

G P

OIN

T

N_AC_020900_1_0240101_01_00

Landing Gear Maintenance PitsMaintenance Pit EnvelopesFIGURE-2-9-0-991-024-A01

2-9-0Page 13

Jun 01/12


**ON A/C A320-200

NO

TE

:1 2

0.52

1.1

73.

84

mft

AB

mft

AB

ST

AT

IC G

RO

UN

D L

INE

1

2

1

2

7.6

1 m

(24.

97 ft

)

1.7

1

RE

PR

ES

EN

TS

TO

P O

F M

EC

HA

NIC

AL

OR

HY

DR

AU

LIC

ELE

VA

TO

R, W

ITH

AIR

CR

AF

T W

EIG

HT

SU

PP

OR

TE

DA

ND

LA

ND

ING

GE

AR

SH

OC

K A

BS

OR

BE

RS

EX

TE

ND

ED

.

RE

PR

ES

EN

TS

TO

P O

F M

EC

HA

NIC

AL

OR

HY

DR

AU

LIC

ELE

VA

TO

R, S

HO

WN

WIT

H Z

ER

O C

LEA

RA

NC

ELO

WE

RE

D F

OR

SH

OC

K A

BS

OR

BE

R R

EM

OV

AL.

1.60

m(5

.25

ft)0.

40 m

(1.3

1 ft)

20

.25

m(6

6.44

ft)

DIM

QU

OT

ED

ISW

ITH

WH

EE

LS R

EM

OV

ED

AN

D 1

53 m

m (

6.02

in)

CLE

AR

AN

CE

AT

JAC

KIN

G D

OM

E

FROM X0

N_AC_020900_1_0250101_01_00

Landing Gear Maintenance PitsMaintenance Pit EnvelopesFIGURE-2-9-0-991-025-A01

2-9-0Page 14

Jun 01/12


2-10-0 Exterior Lighting

**ON A/C A320-200

Exterior Lighting

1. General

This section gives the location of the aircraft exterior lighting.

EXTERIOR LIGHTINGITEM DESCRIPTION

1 RIGHT NAVIGATION LIGHT (GREEN)

2 TAIL NAVIGATION LIGHT (WHITE)

3 LEFT NAVIGATION LIGHT (RED)

4 RETRACTABLE LANDING LIGHT5 RUNWAY TURN OFF LIGHT6 TAXI LIGHT7 TAKE-OFF LIGHT8 LOGO LIGHT

9 UPPER ANTI-COLLISION LIGHT/BEACON (RED)

10 LOWER ANTI-COLLISION LIGHT/BEACON (RED)

11 WING STROBE LIGHT (HIGH INTENSITY, WHITE)

12 TAIL STROBE LIGHT (HIGH INTENSITY, WHITE)

13 WING/ENGINE SCAN LIGHT

14 WHEEL WELL LIGHT (DOME)

15 CARGO COMPARTMENT FLOOD LIGHT

2-10-0Page 1

Jun 01/12


**ON A/C A320-200

6 75 4

10

12

9

13

8

2

8

N_AC_021000_1_0090101_01_00

11

1

3

111

3

RH

LH

RH

LH

Exterior LightingFIGURE-2-10-0-991-009-A01

2-10-0Page 2

Jun 01/12


**ON A/C A320-200

1

2

3

55

7

N_AC_021000_1_0100101_01_00


2-10-0Page 3

Jun 01/12


**ON A/C A320-200

12

11

1313

4

11

N_AC_021000_1_0110101_01_00

109

6


2-10-0Page 4

Jun 01/12


**ON A/C A320-200

14

8 8

15 15

N_AC_021000_1_0190101_01_00

EXAMPLE FOR LIGHT N° 15

CEILING LIGHT

SPOT LIGHT

GROUND


2-10-0Page 5

Jun 01/12


2-11-0 Antennas and Probes Location

**ON A/C A320-200

Antennas and Probes Location

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

2-11-0Page 1

Jun 01/12


**ON A/C A320-200

RADIO ALTIMETER(2)

RADIO ALTIMETER(1)

VHF(2)

DME(2)

PITOT PROBE(1)

PITOT PROBE(3)

DME(1)

TAT PROBE

VHF(1)

TAT PROBE

PITOT PROBE(2)

GPS(2)

GPS(1)

ATC(1)

ADF(1)

VHF(3)

ELT

ATC(2)

WEATHER RADAR

EMERGENCY STATIC PROBE

TCAS TOP

AOA SENSOR(1)

MARKER

TCAS BOTTOM

STATIC PROBE(1)

STATIC PROBE(2)

LOC

GLIDE

HF

VOREMERGENCY STATIC PROBE

AOA SENSOR(2)

STATIC PROBE(2)

STATIC PROBE(1)

ATC(3)

AOA SENSOR(3) STBY

ATC(4)

N_AC_021100_1_0030101_01_00NOTE: DEPENDING ON AIRCRAFT CONFIGURATION

Antennas and ProbesLocation

FIGURE-2-11-0-991-003-A01

2-11-0Page 2

Jun 01/12


2-12-0 Power Plant

**ON A/C A320-200

Auxiliary Power Unit

1. General

The APU is installed at the rear part of the fuselage in the tail cone. An air intake system with aflap-type door is installed in front of the APU compartment. The exhaust gases pass overboard at theend of the fuselage cone.

2. Controls and Indication

The primary APU controls and indications are installed on the overhead panel, on the center pedestaland on the center instrument panel. Additionally, an external APU panel is installed on the noselanding gear to initiate an APU emergency shutdown.

2-12-0Page 1

Jun 01/12


**ON A/C A320-200

Z310

AIR INTAKE FIXEDON ACCESS DOOR

CUT OUT SEALED WITHLABYRINTH GASKET

FRONTFIREWALL

FIREWALL

FIREWALL RH

LOUVER LH

REARFIREWALL

CUT OUT SEALED WITHLABYRINTH GASKET

B

A

UPPER

A

/ FR80

/FR84STA38945

STA37295

LH ACCESS DOORNOTE: NOT SHOWN FOR CLARITY315AL

RH ACCESS DOOR316AR

N_AC_021200_1_0050101_01_00

Auxiliary Power UnitAccess Doors

FIGURE-2-12-0-991-005-A01

2-12-0Page 2

Jun 01/12


**ON A/C A320-200

OIL

CO

OLE

R O

UT

LET

AIR

INT

AK

E D

UC

T

AP

U−

FU

EL−

LIN

E

AIR

INT

AK

E H

OU

SIN

G

DIV

ER

TE

R

FR

ON

T F

IRE

WA

LL

BLE

ED

AIR

LIN

E

FIR

E E

XT

ING

UIS

HIN

GB

OT

TLE

GE

NE

RA

TO

R

AP

U S

US

PE

NS

ION

(7 R

OD

S)

AP

U

FIR

E O

VE

RH

EA

T D

ET

EC

TO

R

AP

U S

US

PE

NS

ION

(7 R

OD

S)

EX

HA

US

TM

UF

FLE

R

B

N_AC_021200_1_0060101_01_00

/ FR

87

/ FR

84

/ FR

80

/ FR

78

/ FR

77

ST

A40

113

ST

A38

945

ST

A37

295

ST

A36

657

ST

A36

545

Auxiliary Power UnitGeneral Layout

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

2-12-0Page 3

Jun 01/12


**ON A/C A320-200

Engine and Nacelle

1. Engine and Nacelle - CFM Engine

A. EngineThe engine is a dual-rotor, variable stator, high bypass ratio turbo fan power plant for subsonicservices. The principal modules of the engine are:- low pressure compressor (fan stator and fan rotor)- high pressure compressor- turbine frame- combustion chamber- high pressure turbine- low pressure turbine- accessory drives (gear box).The 9 stage high pressure compressor is driven by 1 stage high pressure turbine, and theintegrated front fan and booster is driven by 4 stage low pressure turbine. An annular combustorconverts fuel and compressor discharge air into energy to provide engine thrust part throughprimary exhaust and to drive the turbines. The accessory drive system extracts energy from thehigh pressure rotor to drive the engine accessories and the engine mounted aircraft accessories.Reverse thrust for braking the aircraft after landing is supplied by an integrated system whichacts on the fan discharge airflow.

B. NacelleThe cowls enclose the periphery of the engine so as to form the engine nacelle. Each engine ishoused in a nacelle suspended from a pylon attached to the wing lower surface. The nacelleconsists of the demountable powerplant, the fan cowls and the thrust reverser cowls.The nacelle installation is designed to provide cooling and ventilation air for engine accessoriesmounted along the fan and core casing. The nacelle provides:- protection for the engine and the accessories- airflow around the engine during its operation- lighting protection- HIRF and EMI attenuation.

2. Engine and Nacelle - IAE Engine

A. EngineThe engine is a two spool, axial flow, high bypass ratio turbofan powerplant for subsonic sevice.The main modules of the engine are:- low pressure compressor (fan and booster) assembly- LP compressor/intermediate case- No. 4 bearing and combustion section- high pressure compressor- HP turbine section- LP turbine section- accessory drives (gear box).

2-12-0Page 4

Jun 01/12


The four stage Low Pressure Compressor (LPC) is driven by a five stage Low Pressure Turbine(LPT) and the ten stage High Pressure Compressor (HPC) by a two stage High PressureTurbine (HPT). The HPT also drives a gearbox which, in turn drives the engines and aircraftmounted accessories. The two shafts are supported by five main bearings.The V2500 incorporates a Full Authority Digital Engine Control (FADEC) which governs allengine functions, including power management. Reverse thrust for braking the aircraft afterlanding is supplied by an integrated system which acts on the fan discharge airflow.

B. NacelleThe cowls enclose the periphery of the engine so as to form the engine nacelle. Each engine ishoused in a nacelle suspended from a pylon attached below the wing.The nacelle installation is designed to provide cooling and ventilation air for engine accessoriesmounted along the fan and core casing. The nacelle provides:- protection for the engine and the accessories- airflow around the engine during its operation- lighting protection- HIRF and EMI attenuation.

2-12-0Page 5

Jun 01/12


**ON A/C A320-200

FAN AND BOOSTER COMPRESSOR

TURBINEHP

TURBINELP

DRIVEACCESSORY

AGB TGB

1 820 mm(71.65 in)

1 130 mm(44.49 in)

989 mm(38.94 in)

1 978 mm(77.87 in)

2 145 mm(84.45 in) FWD

2 943 mm(115.87 in)

TURBINEFRAME

2 600 mm(102.36 in)1 125 mm

(44.28 in)

FWD HOISTINGPOINT

FWDHANDLING

POINT

AFT HANDLINGAND HANDLING

POINTDIA 986 mm

(38.82 in)

B

A

BN_AC_021200_1_0270101_01_00

A

COMBUSTOR

Power Plant HandlingMajor Dimensions - CFM56 Series Engine

FIGURE-2-12-0-991-027-A01

2-12-0Page 6

Jun 01/12


**ON A/C A320-200

BLOCKER DOOREXTENDED

1.9 m(6.2 ft)

C C

1.2 m(3.9 ft)

1.8 m(5.9 ft)

D D

2.07 m(6.8 ft)

B B

2.1 m(6.9 ft)

A A

FAN COWL

CENTERBODY

FANREVERSER

6°

PRIMARYNOZZLE

11 m(36.1 ft)

0.93 m

(3.1 ft)

1.3 m(4.3 ft)

1.2 m(3.9 ft)

1.2 m(3.9 ft)

DISTANCE FROMTHE NOSE

0.33 m(1.1 ft)

2.3 m(7.5 ft)

ENGINE AIRINLET COWL

A

A

B

B

C

C

D

D

0.57 m(1.9 ft)

1.6 m(5.2 ft)

N_AC_021200_1_0280101_01_00

Power Plant HandlingMajor Dimensions - CFM56 Series Engine

FIGURE-2-12-0-991-028-A01

2-12-0Page 7

Jun 01/12


**ON A/C A320-200

N_AC_021200_1_0290101_01_00

0.56 m(1.8 ft)

NOTE: APPROXIMATE DIMENSIONS

3.73 m(12.3 ft)

4.25 m(14 ft)

40°55°

0.81 m(2.67 ft)

1.2 m(3.96 ft)

1.51 m(4.98 ft)

1.85 m(6.1 ft)

Power Plant HandlingFan Cowls - CFM56 Series Engine

FIGURE-2-12-0-991-029-A01

2-12-0Page 8

Jun 01/12


**ON A/C A320-200

N_AC_021200_1_0300101_01_00

3.7 m(12.1 ft)

3.3 m(10.8 ft)

35°45°

1 m(3.3 ft)

(3 ft)0.9 m

CAUTIONDO NOT ACTUATE SLATS:

− WITH THRUST REVERSER COWLS 45° OPEN POSITION− WITH BLOCKER DOORS OPEN AND THRUST REVERSER COWLS AT 35° AND 45° OPEN POSITION

APPROXIMATE DIMENSIONSNOTE:

GROUND

0.56 m(1.8 ft)

0.7 m(2.3 ft)

1 m(3.3 ft)

Power Plant HandlingThrust Reverser Cowls - CFM56 Series Engine

FIGURE-2-12-0-991-030-A01

2-12-0Page 9

Jun 01/12


**ON A/C A320-200

FAN AND BOOSTER COMPRESSOR

COMBUSTOR

HPTURBINE

LPTURBINE

TURBINEFRAME

A

3 101 mm(122.1 in)

1 715 mm(67.5 in)

1 067 mm(42.0 in)

DRIVEACCESSORY

FWD

A

N_AC_021200_1_0310101_01_00

Power Plant HandlingMajor Dimensions - IAE V2500 Series Engine

FIGURE-2-12-0-991-031-A01

2-12-0Page 10

Jun 01/12


**ON A/C A320-200

N_AC_021200_1_0320101_01_00

0.5°6°

5.26 m(17.27 ft)

1.50 m(4.95 ft)

5.25 m(17.23 ft)

2.01 6.58 0.99 3.25 1.10 3.63 1.41 4.62

W U V PPS

m ft m ft m ft m ft

ATCOMPONENT

INLETATTACH FLG

TORQUE BOX"V" BLADE

COMB. CHAMBERENTRY FLG

COMB. CHAMBEREXIT FLG

TECH FLGTURB. EXIT CASE

AFT ENDCNA

2.01 6.58 1.00 3.29 1.11 3.64 2.59 8.50

1.98 6.50 0.97 3.19 1.07 3.52 3.26 10.70

1.93 6.32 0.93 3.06 1.03 3.39 3.63 11.90

1.64 5.38 0.78 2.57 0.86 2.83 4.60 15.10

1.24 4.07 0.60 1.96 0.64 2.11 −−−− −−−−

W

U

V

F

F

E

E

D

D

C

C

B

B

A

A

DISTANCE FROMTHE NOSE

11.12 m(36.5 ft)

A−A

B−B

C−C

D−D

E−E

F−F

Power Plant HandlingMajor Dimensions - IAE V2500 Series Engine

FIGURE-2-12-0-991-032-A01

2-12-0Page 11

Jun 01/12


**ON A/C A320-200

N_AC_021200_1_0330101_01_00

2 m

(6.6 ft)

CLOSEDWL100

(5.2 ft)1.2 m(3.9 ft)

GROUND

WL100

3.9 m

(12.8 ft)

FWD VIEW

FAN COWLOPEN 50°

0.67 m(2.2 ft)


1.6 m

Power Plant HandlingFan Cowls - IAE V2500 Series Engine

FIGURE-2-12-0-991-033-A01

2-12-0Page 12

Jun 01/12


**ON A/C A320-200

N_AC_021200_1_0340101_01_00

1.1 m(3.6 ft)

1 m(3.3 ft)

THRUST REVERSEROPEN 45°

0.67 m(2.2 ft)

2 m

(6.6 ft)

AFT VIEW

WL100CLOSED

3.6 m

(11.8 ft)

0.9 m(3 ft)

WL100


Power Plant HandlingThrust Reverser Halves - IAE V2500 Series Engine

FIGURE-2-12-0-991-034-A01

2-12-0Page 13

Jun 01/12


2-13-0 Leveling, Symmetry and Alignment

**ON A/C A320-200

Leveling, Symmetry and Alignment

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

2. Precise LevelingFor precise leveling, it is necessary to install sighting rods in the receptacles located under thefuselage (points 11 and 12 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.

2-13-0Page 1

Jun 01/12


**ON A/C A320-200

2LH

RIB10

2RH

RIB10

FR34FR31

FR50 FR53

12

11

N_AC_021300_1_0040101_01_00

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

2-13-0Page 2

Jun 01/12


2-14-0 Jacking

**ON A/C A320-200

Jacking for Maintenance

1. Jacking for Maintenance

A. General

The A320 aircraft can be jacked:- at no more than the maximum permitted aircraft weight for jacking (59 000 kg (130 072

lb)) and,- within the limits of the permissible wind speed when the aircraft is jacked outside a closed

environment.

B. Primary Jacking Points

The aircraft is provided with three jacking points:- one located under the forward fuselage (STA5194/FR8),- two located under the wings: one under each wing, located at the intersection of

STA4862/RIB9 and the rear of spar-datum.

Three jacking adapters are used as intermediary parts between the airplane and jacks:- one male spherical jacking adapter of 19 mm (0.75 in) radius, forming part of the airplane

structure, FR8,- a wing jack pad, attached to each wing at RIB 9 by 2 bolts, provides the location for

jacking adaptor.Wing jack pads are ground equipment.

C. Auxiliary Jacking Points - Safety Stay

When the aircraft is on jacks, it is recommended that a safety stay be placed under the fuselage,between FR73 and FR74 to prevent tail tipping caused by accidental displacement of the centerof gravity.

The safety stay is not used to lift the aircraft.

A male spherical ball pad with a 19 mm (0.75 in) radius forming part of the airplane structure isprovided for using the safety stay.

2. Jack design

In fully retracted position (jack stroke at minimum) the height is such that the jack may be placedbeneath the airplane under the most adverse conditions, namely, tires deflated and shock absorbersdepressurized.

2-14-0Page 1

Jun 01/12


In addition, a clearance of 50 mm (1.97 in) approximately must be provided between the airplanejacking point and the jack upper end. The lifting jack stroke enables the aircraft to be jacked up sothat the fuselage longitudinal datum line (aircraft center line) parallel to the ground, with a 100 mm(3.94 in) clearance between the main landing gear wheels and the ground.In particular, this enables the landing gear extension/retraction tests to be performed.

Jacking Point Location Z Maximum Permitted Load

Forward Fuselage Jacking Point-1.987 m(-6.52 ft)

6 800 daN(15 287 lbf)

Wing Jacking Point-0.828 m(-2.72 ft)

28 500 daN(64 071 lbf)

Safety Stay-0.748 m(-2.45 ft)

2 000 daN(4 496 lbf)

The maximum permitted aircraft weight for the jacking procedure is 59 000 kg (130 073 lb).Centerline at 4.6 mm (0.18 in) parallel to the ground.

3. Shoring Cradles

When it is necessary to support the aircraft in order to relieve the loads on the structureaccomplishment of modifications or major work, shoring cradles shall be placed under each wing andfuselage as necessary.

NOTE : Aircraft must not be lifted or supported by the wings or fuselage alone without adequatesupport of the other.

A. Under the Fuselage

Frames which are capable of supporting loads are noted below as well as the maximumpermissible loads for each frame.

Under the Fuselage

FR 15 6 700 daN (15 062 lbf)

FR 33 3 400 daN (7 644 lbf)

FR 42 1 000 daN (2 248 lbf)

FR 62/FR 63 3 000 daN (6 744 lbf)

FR 73/FR 74 Safety Stay Pad 2 000 daN (4 496 lbf)

B. Under the Wings

2-14-0Page 2

Jun 01/12


Shoring 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 stressesto an acceptable level at the area of maintenance and repair.

The shoring cradles, each with two adjustable pads, 152.4 mm (6.00 in) square, are positionedat three locations under each wing. These locations are detailed in Table 3.

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

Table 3 shows the maximum load limit allowed at each jack pad when the wings are supportedby the cradles. These load limits apply to all A320 aircraft and variants.

The maximum permitted load, as specified in Table 3, is for a wing with its engines removed.When the wing(s) are held with the shoring cradles, and with the engines installed, the level ofshear stress caused (at the front spar) is not permitted. The weight of the engine can also causea torsion load that will lift the rear spar from its cradle.

Thus it is recommended that you remove the applicable engine(s) before you use the shoringcradles. However, for minor repairs the engines may be installed if their full weight is held.

It is important that the loads at each rib position are not exceeded because damage to theaircraft may occur.

Maximum Allowable Load at each Jack Pad

Maximum Stress Relief Jacking Forces (LIMIT)

Rib 4 Rib 13 Rib 22Configuration

F/Spar R/Spar F/Spar R/Spar F/Spar R/Spar

Engine &MLGRemoved

790 daN(1 776 lbf)

1 330 daN(2 990 lbf)

670 daN(1 506 lbf)

550 daN(1 236 lbf)

320 daN(719 lbf)

380 daN(854 lbf)

EngineRemoved

530 daN(1 191 lbf)

2 510 daN(5 643 lbf)

610 daN(1 371 lbf)

610 daN(1 371 lbf)

310 daN(697 lbf)

380 daN(854 lbf)

4. Airplane Jacking for Removal/Installation of Landing Gear Shock Absorbers

For removal/installation of the nose gear shock absorber with the gear fully extended and the wheelsremoved, the fuselage longitudinal datum line must be not less than 5 300 mm (208.66 in) above theground.

2-14-0Page 3

Jun 01/12


For removal/installation of the main landing gear shock absorber, after removing the bogie beam, thefuselage longitudinal datum line must be not less than 5 210 mm (205.12 in) above the ground.

For reference, for landing gear swinging tests, the fuselage longitudinal datum line must be not lessthan 4 600 mm (181.10 in) above the ground.

2-14-0Page 4

Jun 01/12


**ON A/C A320-200

2.74 m(8.99 ft)

FWD JACKINGPOINT

WING JACKING

6.5 m(21.33 ft)

SAFETYPOINT

WING JACKING

17.56 m(57.61 ft)

32.57 m(106.86 ft)

CL

POINT

POINT

N_AC_021400_1_0300101_01_00

Jacking for MaintenanceJacking Point Location

FIGURE-2-14-0-991-030-A01

2-14-0Page 5

Jun 01/12


**ON A/C A320-200

A

N_AC_021400_1_0310101_01_00

POINT A DETAIL

Z−1 979.8Z−1 987

FR8

A

SPHERICAL RADIUS19 mm (0.75 in)

B

B

Jacking for MaintenanceForward Jacking Point

FIGURE-2-14-0-991-031-A01

2-14-0Page 6

Jun 01/12


**ON A/C A320-200

A

A

N_AC_021400_1_0320101_01_00

LOWER SURFACE

A

WING JACK PAD

POINT BB’ DETAIL

Z−895

Z−828.35

RE

AR

SP

AR

DA

TU

M

INTERSECTION WITH REARSPAR DATUM

RIB9

SPHERICAL RADIUS32 mm (1.26 in)

EXAMPLE

B

B

Jacking for MaintenanceWing Jacking Points

FIGURE-2-14-0-991-032-A01

2-14-0Page 7

Jun 01/12


**ON A/C A320-200

A

Z−748.44

SPHERICAL RADIUS 19 mm (0.75 in)(19 D535−71 595)

X =

35

106

A

Z−729.441

N_AC_021400_1_0330101_01_00

(4.97 in)

126.15 mm

Jacking for MaintenanceSafety Stay

FIGURE-2-14-0-991-033-A01

2-14-0Page 8

Jun 01/12


**ON A/C A320-200

THE CENTER LINE (CL) IS A FICTITIOUS LINE AROUND WHICH THE AIRCRAFT IS BUILT.SAFETY STAY IS NOT USED FOR JACKING.SEE SECTION 1−10, FOR GROUND CLEARANCES A/C ON JACKS.

NOTE:

L

M

L M

1 675 mm(65.94 in)

2 801 mm(110.28 in)

2 858 mm(112.52 in)

2 599 mm(102.32 in)

3 751 mm(147.68 in)

3 834 mm(150.94 in)

1 897 mm(74.69 in)

3 178 mm(125.12 in)

3 391 mm(133.50 in)

1 545 mm(60.83 in)

2 761 mm(108.70 in)

2 940 mm(115.75 in)

N

AIRCRAFT ON WHEELS, SHOCK ABSORBERS DEFLATED AND

AIRCRAFT ON WHEELS, NLG SHOCK ABSORBER DEFLATED

AIRCRAFT ON JACKS, CENTER LINE (CL) PARALLEL TO GROUNDSHOCK ABSORBERS EXTENDED MAIN WHEEL CLEARANCE(STANDARD TIRES) (49 x 17) 120 mm (4.72 in) FOR EXTENDED

AIRCRAFT ON WHEELS, (STANDARD TIRES) AT MAX.PERMITTED WEIGHT FOR JACKING

FLAT TIRES

AND RETRACTED LANDING GEARS

AND FLAT TIRES

N

N_AC_021400_1_0340101_01_00

Jacking for MaintenanceJacking Design

FIGURE-2-14-0-991-034-A01

2-14-0Page 9

Jun 01/12


**ON A/C A320-200

0

3

6

9

12

6.93

25 30 35 40 45 50 55 60 65 70 75

55 66 77 88 99 110 121 132 143 154 165

1000 kg

A/C WEIGHT

MAX PERMISSIBLE LOAD

AS AN EXAMPLE ASSUME THAT THE AIRCRAFT HAS A GROSS WEIGHTOF 66 000 kg AND THE CENTER OF GRAVITY (CG) IS AT 25 %. THUS THEFORCE AT THE FORWARD FUSELAGE JACKING POINT IS 5 300 kg.

NOTE:

LOAD AT FORWARDFUSELAGE JACKING POINT

1000 kg

CG 15 %

CG 25 %

CG 35 %

CG 45 %

1000 lb

N_AC_021400_1_0350101_01_00

Loads at the Aircraft Jacking PointsForward Fuselage Jacking Point - Twin Wheel/Bogie

FIGURE-2-14-0-991-035-A01

2-14-0Page 10

Jun 01/12


**ON A/C A320-200

N_AC_021400_1_0360101_01_00

25 30 35 40 45 50 55 60 65 70 75

55 66 77 88 99 110 121 132 143 154 165

1000 kg

1000 lb

A/C WEIGHT

10

15

20

25

30

35

29.06

EXAMPLE:GROSS WT: 60 000 kgCG 25 %FORCE AT EACH WINGJACKING POINT 27 350 kg

MAX PERMISSIBLE LOAD

CG 45 %

CG 35 %

CG 25 %

CG 15 %

LOAD AT WING JACKING POINT AT1000 kg

STA4067 FR8/

Loads at the Aircraft Jacking PointsWing Jacking Point Rib 8 - Twin Wheel/Bogie

FIGURE-2-14-0-991-036-A01

2-14-0Page 11

Jun 01/12


**ON A/C A320-200

N_AC_021400_1_0370101_01_00

(SAFETY STAY)

FR63

FR73 FR74

FR42

FR33

FR15

/

RIB4 RIB4

RIB22

RIB13

RIB22

RIB13

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

FR64

Jacking for MaintenanceLocation of Shoring CradlesFIGURE-2-14-0-991-037-A01

2-14-0Page 12

Jun 01/12


**ON A/C A320-200

Jacking for Wheel Change

1. General

Landing gear jacking will be required especially for replacing wheels and brake unit components.

The maximum permitted aircraft weight for jacking is 59 000 kg (130 073 lb).

2. Main Gear Jacking (Twin Wheel)

The main gears are normally jacked up by placing a jack directly under the ball pad.

The ball spherical radius is 19 mm (0.75 in).

It is also possible to jack the main gear using a cantilever jack.

3. Main Gear Jacking (4 Wheels Bogie)

The fore and aft pair of MLG wheels can be jacked by placing a jack directly under the ball padslocated at each end of the bogie beam.

The ball spherical radius is 19 mm (0.75 in).

The leading dimensions and environmental distances of these jacking points are shown on Figures 4,5 and 6.

The reactions at each of the jacking points are shown on the graph (Ref. Figure 7).

4. Nose Gear Jacking

For nose gear jacking a 19 mm (0.75 in) radius ball pad is fitted under the lower end of the shockabsorber sliding tube. Jacking can be accomplished either by placing a jack directly under the ballpad, or using an adapter fitting provided with an identical ball pad.

2-14-0Page 13

Jun 01/12


**ON A/C A320-200

N_AC_021400_1_0450101_01_00

NOTE:

45 x 16 R20

552 mm(21.73 in)

38 mm(1.5 in)

DIA. BALL

25 mm (1 in)

218 mm(8.58 in)

180 mm(7.09 in)

ON THE RIM

200 mm(7.87 in)FULLY

RETRACTED

49 x 19 R20

THE FLAT TIRES VIEW SHOWS THE MINIMUM HEIGHT TO ENGAGE JACK WITH 2 FLAT TIRES.TWIN WHEEL TRACK IS 927 mm (36.5 in).

THE INFLATED TIRES VIEW SHOWS THE JACKING HEIGHT TO GIVE 25 mm (1 in)CLEARANCE BETWEEN THE TIRE AND GROUND.

600 mm(23.62 in)FULLY

EXTENDED

FLAT TIRES

INFLATED TIRES

Landing Gear Jacking for Wheel ChangeMLG Jacking Point Location - Twin Wheels

FIGURE-2-14-0-991-045-A01

2-14-0Page 14

Jun 01/12


**ON A/C A320-200

MLG TIRE 49 x 19 R20

TWIN WHEEL TRACK

DOUBLE FLAT MLG TIRES

FORK

CONTOUR OF TIRES ON GROUND

CANTILEVERARM

1 620 mm(63.78 in)

MIN

218 mm (8.58 in)(180 mm (7.09 in)

ON RIM)

552 mm(21.73 in)

FWD

APPROX

N_AC_021400_1_0460101_01_00

643 mm(25.32 in)

927 mm(36.5 in)

MIN25 mm(1 in)

25 mm(1 in)

409 mm(16.1 in)

25 mm(1 in)

Landing Gear Jacking for Wheel ChangeMLG Jacking with Cantilever Jack - Twin Wheels

FIGURE-2-14-0-991-046-A01

2-14-0Page 15

Jun 01/12


**ON A/C A320-200

300

35 40 45 50 55 60 65 70 75 80

5

10

15

20

25

35

40

30

CG 40 %

CG 30 %CG 25 %

CG 20 %CG 17 %

180170160150140130120110100908070

A/C WEIGHT1 000 kg

1 000 lb

LOAD AT MLGJACKING POINT

1 000 kg

N_AC_021400_1_0470101_01_00

Landing Gear Jacking for Wheel ChangeLoads at MLG Jacking Points - Twin Wheels

FIGURE-2-14-0-991-047-A01

2-14-0Page 16

Jun 01/12


**ON A/C A320-200

N_AC_021400_1_0480101_01_00

JAC

KIN

G P

OIN

T 1

80 m

m (

7.09

in)

SIT

TIN

G O

N R

IMS

133

mm

(5.

24 in

)

TWO FRONT TIRES DEFLATED

JAC

KIN

G P

OIN

T 2

29 m

m

ONE FRONT TIRE DEFLATED

JAC

KIN

G P

OIN

T 2

70 m

m

NORMAL ATTITUDE

FWD

(10.

63 in

)(9

.02

in)

JAC

KIN

G P

OIN

T 2

70 m

m(1

0.63

in)

FWD

FWD

Landing Gear Jacking for Wheel ChangeMLG Jacking Point Location Bogie

FIGURE-2-14-0-991-048-A01

2-14-0Page 17

Jun 01/12


**ON A/C A320-200

N_AC_021400_1_0490101_01_00

JAC

KIN

G P

OIN

T 1

80 m

m (

7.09

in)

ON

RIM

S 1

33 m

m (

5.24

in) ALL FOUR TIRES DEFLATED

JAC

KIN

G P

OIN

T 1

80 m

m (

7.09

in)

ON

RIM

S 1

33 m

m (

5.24

in)

JAC

KIN

G P

OIN

T 1

80 m

m (

7.09

in)

ON

RIM

S 1

33 m

m (

5.24

in)

TWO REAR TIRES DEFLATED

JAC

KIN

G P

OIN

T 2

29 m

m

ONE REAR TIRE DEFLATED

FWD

FWD

FWD (9.0

2 in

)


FIGURE-2-14-0-991-049-A01

2-14-0Page 18

Jun 01/12


**ON A/C A320-200

N_AC_021400_1_0500101_01_00

780 mm

46 m

mFLAT TIRE DIMENSIONS

JAC

KIN

G P

OIN

T 3

80 m

m

25 m

m C

LEA

R

MAX DIAMETER915 mm (36.02 in)

REAR WHEELS JACKED UP

25 m

m C

LEA

R

MAX DIAMETER915 mm (36.02 in)

FRONT WHEELS JACKED UP

JAC

KIN

G P

OIN

T 3

80 m

m

(14.

96 in

)

(0.9

8 in

)

(14.

96 in

)

(30.71 in) (0.9

8 in

)

(1.8

1 in

)

(5.51 in)140 mm

(12.99 in)330 mm

(48.43 in)1 230 mm


FIGURE-2-14-0-991-050-A01

2-14-0Page 19

Jun 01/12


**ON A/C A320-200

300

35 40 45 50 55 60 65 70 75 80

180170160150140130120110100908070

5

10

15

20

A/C WEIGHT1 000 kg

1 000 lb


1 000 kg

LOADS GIVEN ARE THOSE AT EACH BOGIE BEAMJACKING POINT (FRONT AND REAR)

NOTE:

CG 40 %CG 30 %

CG 25 %CG 20 % CG 17 %

N_AC_021400_1_0510101_01_00

Landing Gear Jacking for Wheel ChangeLoads at MLG Jacking Points - Bogie Version

FIGURE-2-14-0-991-051-A01

2-14-0Page 20

Jun 01/12


**ON A/C A320-200

45 50 55 60 65 70 75 80

KEY:−

18

20

22

24

26

28

30

32

34

36

37.5% CG

33.0% CG

28.0% CG

17.0% CG


1 000 kg

N_AC_021400_1_0520101_01_00

x1 000 lb

x1 000 kg

180170160150140130120110100

AIRCRAFT WEIGHT

Landing Gear Jacking for Wheel ChangeLoads at MLG Jacking Points - 77 000 kg

FIGURE-2-14-0-991-052-A01

2-14-0Page 21

Jun 01/12


**ON A/C A320-200

APPROX326 mm

(12.83 in)38 mm(1.5 in)

DIA. BALLSAE AS 33559

25 mm(1 in)

128 mm(5.06 in)

40 mm(1.57 in)

THE FLAT TIRES VIEW SHOWS THE MINIMUM HEIGHT TO ENGAGE JACK WITH 2 FLAT TIRES.THE INFLATED TIRES VIEW SHOWS THE JACKING HEIGHT TO GIVE 25 mm (1 in)CLEARANCE BETWEEN THE TIRE AND GROUND.

NOTE:

FWD

500 mm (19.69 in)

INFLATED TIRESFLAT TIRES

198 mm(7.8 in)

264 mm MIN (10.39 in)289 mm MAX (11.38 in)

N_AC_021400_1_0530101_01_00

A

A

Landing Gear Jacking for Wheel ChangeNLG Jacking - Point LocationFIGURE-2-14-0-991-053-A01

2-14-0Page 22

Jun 01/12


**ON A/C A320-200

60 70 80

2

3

4

5

6

7

8

9

10

11

12

54

LOAD AT NLGJACKING POINT

1 000 kg

CG 45%

CG 40%

CG 35%

CG 30%

CG 20%

CG 15%

CG 25%

N_AC_021400_1_0540101_01_00

AIRCRAFT WEIGHT

180170160150140130120 x 1 000 lb190 200

x 1 000 kg

Landing Gear Jacking for Wheel ChangeLoads at NLG Jacking PointsFIGURE-2-14-0-991-054-A01

2-14-0Page 23

Jun 01/12


**ON A/C A320-200

45 50 55 60 65 70 75 80

KEY:−

3

4

5

6

7

8

9

10

11

17.0% CG

28.0% CG

33.0% CG

37.5% CG

LOAD AT NLGJACKING POINT

1 000 kg

N_AC_021400_1_0550101_01_00

AIRCRAFT WEIGHT

180170160150140130120110100 x 1 000 lb

x 1 000 kg

Landing Gear Jacking for Wheel ChangeLoads at NLG Jacking Points - 77 000 kg

FIGURE-2-14-0-991-055-A01

2-14-0Page 24

Jun 01/12


AIRCRAFT PERFORMANCE


**ON A/C A320-200

General Information

1. This section gives standard day temperatures.

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

Section 3-3 represents FAR take-off runway length requirements at ISA and ISA +15˚C (+59˚F) forCFM56-5A, CFM56-5B and IAE V2500 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 altitudes shown are tabulated below:

Standard day temperatures for the altitude

Altitude Standard Day Temperature

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

3-1-0Page 1

Jun 01/12


3-2-0 Payload / Range

**ON A/C A320-200

Payload / Range

1. Payload / Range

3-2-0Page 1

Jun 01/12



**ON A/C A320-200

ISA Conditions

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

3-2-1Page 1

Jun 01/12


**ON A/C A320-200

20 10 0

(100

0 lb

)(1

000

kg)

PA

YLO

AD

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LYT

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.

NO

TE

:

50 40 30 20 10 00

1000

2000

3000

4000

7000

6000

4000

5000

3000

2000

1000

0R

AN

GE

(KM

)

RA

NG

E(N

M)

77t

73.5

t75.5

t

200

NM

(37

0 K

M)

DIV

ER

SIO

N30

MIN

UT

ES

HO

LD A

T 1

500

ftA

PP

RO

AC

H A

ND

LA

ND

ING

CR

UIS

E C

ON

DIT

ION

SIS

A +

10°

M =

0.7

635

000

/39

000

ft

INT

ER

NA

TIO

NA

L R

ES

ER

VE

S :

EN

RO

UT

E 1

0% F

LIG

HT

TIM

EO

VE

RS

HO

OT

150

PA

SS

EN

GE

RS

N_AC_030201_1_0060101_01_00

Payload / RangeCFM56-5A series engine

FIGURE-3-2-1-991-006-A01

3-2-1Page 2

Jun 01/12


**ON A/C A320-200

20 10 0

(100

0 lb

)(1

000

kg)

PA

YLO

AD

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LYT

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.

NO

TE

:

50 40 30 20 10 00

1000

2000

3000

4000

7000

6000

4000

5000

3000

2000

1000

0R

AN

GE

(KM

)

RA

NG

E(N

M)

73.5

t

77t

75.5

t

200

NM

(37

0 K

M)

DIV

ER

SIO

N30

MIN

UT

ES

HO

LD A

T 1

500

ftA

PP

RO

AC

H A

ND

LA

ND

ING

CR

UIS

E C

ON

DIT

ION

SIS

A +

10°

M =

0.7

635

000

/39

000

ft

INT

ER

NA

TIO

NA

L R

ES

ER

VE

S :

EN

RO

UT

E 1

0% F

LIG

HT

TIM

EO

VE

RS

HO

OT

150

PA

SS

EN

GE

RS

N_AC_030201_1_0070101_01_00

Payload / RangeCFM56-5B series engine

FIGURE-3-2-1-991-007-A01

3-2-1Page 3

Jun 01/12


**ON A/C A320-200

20 10 0

(100

0 lb

)(1

000

kg)

PA

YLO

AD

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LYT

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.

NO

TE

:

50 40 30 20 10 00

1000

2000

3000

4000

7000

6000

4000

5000

3000

2000

1000

0R

AN

GE

(KM

)

RA

NG

E(N

M)

77t

73.5

t

200

NM

(37

0 K

M)

DIV

ER

SIO

N30

MIN

UT

ES

HO

LD A

T 1

500

ftA

PP

RO

AC

H A

ND

LA

ND

ING

CR

UIS

E C

ON

DIT

ION

SIS

A +

10°

M =

0.7

635

000

/39

000

ft

INT

ER

NA

TIO

NA

L R

ES

ER

VE

S :

EN

RO

UT

E 1

0% F

LIG

HT

TIM

EO

VE

RS

HO

OT

150

PA

SS

EN

GE

RS

75.5

t

N_AC_030201_1_0080101_01_00

Payload / RangeIAE V2500-A1 series engineFIGURE-3-2-1-991-008-A01

3-2-1Page 4

Jun 01/12


**ON A/C A320-200

20 10 0

(100

0 lb

)(1

000

kg)

PA

YLO

AD

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LYT

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.

NO

TE

:

50 40 30 20 10 00

1000

2000

3000

4000

7000

6000

4000

5000

3000

2000

1000

0R

AN

GE

(KM

)

RA

NG

E(N

M)

77t

73.5

t

200

NM

(37

0 K

M)

DIV

ER

SIO

N30

MIN

UT

ES

HO

LD A

T 1

500

ftA

PP

RO

AC

H A

ND

LA

ND

ING

CR

UIS

E C

ON

DIT

ION

SIS

A +

10°

M =

0.7

635

000

/39

000

ft

INT

ER

NA

TIO

NA

L R

ES

ER

VE

S :

EN

RO

UT

E 1

0% F

LIG

HT

TIM

EO

VE

RS

HO

OT

150

PA

SS

EN

GE

RS

75.5

t

N_AC_030201_1_0090101_01_00

Payload / RangeIAE V2500-A5 series engineFIGURE-3-2-1-991-009-A01

3-2-1Page 5

Jun 01/12


3-3-0 FAR / JAR Takeoff Weight Limitation

**ON A/C A320-200

FAR / JAR Take-off Weight Limitation

1. FAR / JAR Take-off Weight Limitation

3-3-0Page 1

Jun 01/12



**ON A/C A320-200

ISA Conditions

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

3-3-1Page 1

Jun 01/12


**ON A/C A320-200

RUNWAY LENGTH

1 000 ft

1 000 m

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

NOTE:

110

120

130

140

150

160

170

180

190

200

210

220

230

110

100

90

80

70

60

50

40

16141210864

54321

8

20

46

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(1

000

ft)

1 000 kg

TA

KE

−O

FF

WE

IGH

T

1 000 lb

N_AC_030301_1_0050101_01_01

FAR / JAR Take-off Weight LimitationISA Conditions -- CFM56 series engine

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

3-3-1Page 2

Jun 01/12


**ON A/C A320-200

RUNWAY LENGTH

1 000 ft

1 000 m


NOTE:

110

120

130

140

150

160

170

180

190

200

210

220

230

110

100

90

80

70

60

50

40

16141210864

54321

46

8

02

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(1

000

ft)

1 000 kg

TA

KE

−O

FF

WE

IGH

T

1 000 lb

N_AC_030301_1_0060101_01_01

FAR / JAR Take-off Weight LimitationISA Conditions -- IAE V2500 series engine

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

3-3-1Page 3

Jun 01/12


3-3-2 ISA +15˚C (+59˚F) Conditions

**ON A/C A320-200

ISA +15˚C (+59˚F) Conditions

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

3-3-2Page 1

Jun 01/12


**ON A/C A320-200

RUNWAY LENGTH

1000 ft

1000 m


NOTE:

110

120

130

140

150

160

170

180

190

200

210

220

230

110

100

90

80

70

60

50

40

16141210864

54321

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 ft

)

1000 kg

TA

KE

−O

FF

WE

IGH

T

1000 lb

02468

N_AC_030302_1_0050101_01_01

FAR / JAR Take-off Weight LimitationISA +15˚C (+59˚F) Conditions -- CFM56 series engine

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

3-3-2Page 2

Jun 01/12


**ON A/C A320-200

1000 ft

1000 m

8

6420

RUNWAY LENGTH


NOTE:

110

100

90

80

70

60

50

40

16141210864

54321

110

120

130

140

150

160

170

180

190

200

210

220

230

N_AC_030302_1_0060101_01_00

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 ft

)

1000 kg

TA

KE

−O

FF

WE

IGH

T

1000 lb

FAR / JAR Take-off Weight LimitationISA +15˚C (+59˚F) Conditions -- IAE V2500 series engine

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

3-3-2Page 3

Jun 01/12


3-4-0 FAR / JAR Landing Field Length

**ON A/C A320-200

FAR / JAR Landing Field Length

1. FAR / JAR Landing Field Length

3-4-0Page 1

Jun 01/12



**ON A/C A320-200

ISA Conditions

1. This section gives the landing field length.

3-4-1Page 1

Jun 01/12


**ON A/C A320-200

2.5

2.0

1.5 1

8 7 6 5 4 3

6080

100

120

140

160

180

9080

7060

5040

3020LE

NG

TH

(100

0 m

)

F.A

.R. L

AN

DIN

GT

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

NO

TE

:

GR

OS

S W

EIG

HT

(100

0 lb

)

GR

OS

S W

EIG

HT

(100

0 kg

)

(100

0 ft)

FA

R L

AN

DIN

G F

IELD

LE

NG

TH

= A

CT

UA

L D

IST

AN

CE

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(100

0 ft)

24

68

10

LEV

EL

N_AC_030401_1_0050101_01_00

0.6

SE

A

FAR / JAR Landing Field LengthCFM56 series engine

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

3-4-1Page 2

Jun 01/12


**ON A/C A320-200

2.5

2.0

1.5 1

8 7 6 5 4 3

6080

100

120

140

160

180

9080

7060

5040

3020LE

NG

TH

(100

0 m

)

F.A

.R. L

AN

DIN

GT

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

NO

TE

:

GR

OS

S W

EIG

HT

(100

0 lb

)

GR

OS

S W

EIG

HT

(100

0 kg

)

(100

0 ft)

FA

R L

AN

DIN

G F

IELD

LE

NG

TH

= A

CT

UA

L D

IST

AN

CE

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(100

0 ft)

24

68

100.

6

N_AC_030401_1_0060101_01_00

LEV

EL

SE

A

FAR / JAR Landing Field LengthIAE V2500 series engine

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

3-4-1Page 3

Jun 01/12


3-5-0 Final Approach Speed

**ON A/C A320-200

Final Approach Speed

1. This section gives the final approach speed.

3-5-0Page 1

Jun 01/12


**ON A/C A320-200

C.A

.S (

Kts

)

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LYT

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.

NO

TE

:

GR

OS

S W

EIG

HT

(100

0 lb

)

GR

OS

S W

EIG

HT

(100

0 kg

)

170

160

150

140

130

120

110

100 60

8010

012

014

016

018

020

0

2030

4050

6070

8090

100

LAN

DIN

G G

EA

R E

XT

EN

DE

DS

LAT

S 2

7 D

EG

.F

LAP

S 3

5 D

EG

.S

EA

LE

VE

L

N_AC_030500_1_0050101_01_00

Final Approach SpeedCFM56 series engine

FIGURE-3-5-0-991-005-A01

3-5-0Page 2

Jun 01/12


**ON A/C A320-200

I.A.S

(K

ts)

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LYT

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.

NO

TE

:

GR

OS

S W

EIG

HT

(100

0 lb

)

GR

OS

S W

EIG

HT

(100

0 kg

)

170

160

150

140

130

120

110

100 60

8010

012

014

016

018

020

0

2030

4050

6070

8090

100

LAN

DIN

G G

EA

R E

XT

EN

DE

DS

LAT

S 2

7 D

EG

.F

LAP

S 4

0 D

EG

.S

EA

LE

VE

L

N_AC_030500_1_0060101_01_00

Final Approach SpeedIAE V2500 series engine

FIGURE-3-5-0-991-006-A01

3-5-0Page 3

Jun 01/12


GROUND MANEUVERING


**ON A/C A320-200

General Information

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

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

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

4-1-0Page 1

Jun 01/12


4-2-0 Turning Radii

**ON A/C A320-200

Turning Radii

1. This section gives the turning radii.

4-2-0Page 1

Jun 01/12


**ON A/C A320-200

R1

R2R3

R5

R4

R6

50°

60°

70°

N_AC_040200_1_0050101_01_01

NOTE:

TURN TYPE:

1. ASYMMETRIC THRUST DIFFERENTIAL BRAKING

FOR STEERING DIMENSION TABLE SEE SHEET 2.

(PIVOTTING ON ONE MAIN GEAR).

2. SYMMETRIC THRUST NO BRAKING.

12.64 m(41.47 ft)

7.59 m(24.9 ft)

Turning Radii, No Slip AngleTurning Radii -- Dual Landing Gear

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

4-2-0Page 2

Jun 01/12


**ON A/C A320-200

N_AC_040200_1_0100101_01_00

706560555040353029

.3

34.2

39.0

48.6

53.3

57.9

62.4

66.8

19.4

15.5

12.5

8.0

6.3

4.8

3.5

2.4

64 51 41 26 21 16 12 8

27.0

23.1

20.1

15.6

13.9

12.4

11.1

9.9

89 76 66 51 46 41 36 33

26.2

22.8

20.4

17.1

16.0

15.1

14.4

13.9

86 75 67 56 52 50 47 46

39.8

35.9

32.9

28.5

26.8

25.4

24.1

22.9

131

118

108

94 88 83 79 75

40.7

36.8

33.8

29.4

27.7

26.2

24.9

23.7

133

121

111

96 91 86 82 78

28.7

25.7

23.6

20.9

20.1

19.4

18.9

18.5

94 84 77 69 66 64 62 61

34.4

31.3

28.9

25.7

24.6

23.7

22.9

22.3

113

103

95 84 81 78 75 73

MA

XIM

UM

RA

MP

WE

IGH

T

EF

FE

CT

IVE

ST

EE

RIN

G A

NG

LE(d

eg)

mft

ft

ft

m

mm

ft

mft

mft

R6

TH

SR

5R

3N

LGR

2LM

LG

mft

R1

RM

LG

ST

EE

RIN

GA

NG

LE(d

eg)

WIN

GT

IPF

EN

CE

SH

AR

KLE

T

R4

− W

ING

NO

SE

TY

PE

TU

RN

OF

75 (

MA

X)

2520

70.2

9.0

301.

5

24.8

32.6

513

.64410

1

125

22.0

72148

174

22.9

7518

.360

21.8

72

24.4

19.5

32.3

40.2

106

132

81107

30.9

38.2

45.1

52.9

46.0

53.8

151

176

33.0

39.8

108

131

39.0

46.0

128

151

22 2 2 2 2 2 2 2 2 2 2

75 (

MA

X)

7065605550

71.9

8.6

1.1

2.1

3.3

4.7

6.2

8.0

13.4

21.6

22.5

7418

.260

21.6

71

67.8

63.1

58.4

53.6

48.8

9.6

10.9

12.3

13.8

15.5

13.8

14.3

15.0

15.9

17.0

22.6

23.9

25.2

26.7

28.4

23.5

24.7

26.0

27.6

29.3

7781859096

18.4

18.8

19.3

20.0

20.9

6162636668

22.1

22.8

23.6

24.5

25.6

73757780841 1 1 1 1 1

284

444547495256

717478838893

3236404551

711152026

4543

.810

.133

17.6

5818

.561

30.5

100

31.4

103

22.1

7227

.189

AB

OV

E 5

0°, A

IRLI

NE

S M

AY

US

E T

YP

E 1

OR

TY

PE

2 T

UR

NS

DE

PE

ND

ING

ON

TH

E S

ITU

AT

ION

.T

YP

E 1

TU

RN

S U

SE

:T

HE

TU

RN

ON

LY.

TY

PE

2 T

UR

NS

US

E:

IT IS

PO

SS

IBLE

TO

GE

T L

OW

ER

VA

LUE

S T

HA

N T

HO

SE

FR

OM

TY

PE

1 B

Y A

PP

LYIN

G D

IFF

ER

EN

TIA

L B

RA

KIN

G D

UR

ING

NO

TE

:

TH

E W

HO

LE T

UR

N.

AS

YM

ME

TR

IC T

HR

US

T D

UR

ING

TH

E W

HO

LE T

UR

N; A

ND

DIF

FE

RE

NT

IAL

BR

AK

ING

TO

INIT

IAT

E

SY

MM

ET

RIC

TH

RU

ST

DU

RIN

G T

HE

WH

OLE

TU

RN

; AN

D N

O D

IFF

ER

EN

TIA

L B

RA

KIN

G A

T A

LL.

Turning Radii, No Slip AngleTurning Radii -- Dual Landing Gear

FIGURE-4-2-0-991-010-A01

4-2-0Page 3

Jun 01/12


**ON A/C A320-200

R5

R3

R4

R1

R6

R2

50°

60°

70°

N_AC_040200_1_0060101_01_02

NOTE: FOR STEERING DIMENSION TABLE SEE SHEET 2.

12.64 m(41.47 ft)

7.59 m(24.9 ft)

Turning Radii, No Slip AngleTurning Radii -- Bogie Landing Gear

FIGURE-4-2-0-991-006-A01

4-2-0Page 4

Jun 01/12


**ON A/C A320-200

mft

R3

R4

R5

R6

mft

mft

mft

mft

mft

R2

R1

ST

EE

RIN

GA

NG

LE(d

eg)

116

13.7

110

173

22.3

973

22.4

035

.28

8325

.29

30.8

6

106

10.7

294

6419

.40

6620

.02

32.3

276

23.2

528

.56

988.

388

5616

.98

6018

.24

29.9

271

21.7

626

.81

926.

2783

4914

.95

5516

.86

27.9

068

20.6

525

.42

864.

5180

4313

.19

5215

.79

26.1

765

19.8

024

.29

812.

9677

3811

.64

4914

.95

24.6

463

19.1

623

.36

781.

5574

3410

.23

4714

.31

23.2

661

18.6

722

.58

720.

2672

298.

9445

13.8

121

.99

6018

.321

.91

128

17.5

558

111

8626

.23

8425

.64

39.1

9228

.16

33.9

6

45 35 27 21 15 10 5 1706560555045403530

N_AC_040200_1_0110101_01_00

Turning Radii, No Slip AngleTurning Radii -- Bogie Landing Gear

FIGURE-4-2-0-991-011-A01

4-2-0Page 5

Jun 01/12


4-3-0 Minimum Turning Radii

**ON A/C A320-200

Minimum Turning Radii

1. This section gives the minimum turning radii.

4-3-0Page 1

Jun 01/12


**ON A/C A320-200

EFFECTIVESTEERING Y A

R3NLG

R4 WING R5NOSE

R6THS

726072457515

21.918.322.013.822.84.6m

ft

WING TIP FENCE

DUAL LANDING GEAR

BOGIE LANDING GEAR

70.0°75 (MAX)

ANGLE

STEERINGANGLE(DEG)

N_AC_040300_1_0030101_01_01

R6

R3

R5

R412.6 m

NOTE:MINIMUM TURNING RADIUS.SLOW CONTINUOUS TURNING.APPROXIMATELY IDLE THRUST

THEORETICAL CENTER OF TURN FOR

(41 ft)

STEERINGANGLE 75°

Y

ON ALL ENGINES.NO DIFFERENTIAL BRAKING.NOSE GEAR RADII TRACK MEASUREDFROM OUTSIDE FACE OF TIRE.

NOTE:BY APPLYING DIFFERENTIAL BRAKING DURING THE WHOLE TURN.IT IS POSSIBLE TO GET LOWER VALUES THAN THOSE FROM TYPE 1

TYPEOF

TURN

1

2

STEERINGANGLE(DEG)

75 (MAX)

75 (MAX)

EFFECTIVESTEERING

ANGLE

71.9°

70.2°

m

m

ft

ft

Y

4.1

4.5

14

15

A

22.3

22.8

73

75

R3NLG

13.4

13.6

44

44

R4 WINGWING TIP

FENCE

21.6

22.0

71

72

SHARKLET

22.5

22.9

74

75

R5NOSE

18.2

18.3

60

60

R6THS

21.6

21.8

71

72

PAVEMENTWIDTH FOR180° TURN

MINIMUM

A

OUTSIDE FACE OF TIRE

EFFECTIVETURN

Minimum Turning RadiiFIGURE-4-3-0-991-003-A01

4-3-0Page 2

Jun 01/12


4-4-0 Visibility from Cockpit in Static Position

**ON A/C A320-200

Visibility from Cockpit in Static Position

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

4-4-0Page 1

Jun 01/12


**ON A/C A320-200

30°

20°

10.14 m(33 ft 3.24 in)

5.07 m(16 ft 7.56 in)

VISUAL ANGLES IN VERTICALPLANE THROUGH PILOTEYE POSITION.

NOT TO BE USED FORLANDING APPROACH VISIBILITY

DIMENSIONS ARE APPROXIMATE

2.41 m(7 ft 10.92 in)4.56 m

(14 ft 11.52 in)

111°

133°

CAPTAIN FIELD OF VIEW

133°

111°

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

VISUAL ANGLES IN HORIZONTALPLANE THROUGH PILOTEYE POSITION.

FIRST OFFICERFIELD OF VIEW

0.53 m(1 ft 8.88 in)

46°

32°

33°

25°

32°

25°

VISUAL ANGLES IN PLANEPERPENDICULAR TOLONGITUDINAL AXIS.

46°

33°

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

N_AC_040400_1_0010101_01_03

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

4-4-0Page 2

Jun 01/12


**ON A/C A320-200

FIR

ST

OF

FIC

ER

FIX

ED

WIN

DO

WF

IRS

T O

FF

ICE

RS

LID

ING

WIN

DO

WF

IRS

T O

FF

ICE

RW

IND

SH

IELD

CA

PT

AIN

WIN

DS

HIE

LDC

AP

TA

IN S

LID

ING

WIN

DO

WC

AP

TA

INF

IXE

D W

IND

OW

PIL

OT

EY

E P

OS

ITIO

N(C

AP

TA

IN P

OS

ITIO

N)

AS

580

B

A32

0

CA

PT

AIN

FIE

LD O

F V

IEW

SH

OW

N.

FIR

ST

OF

FIC

ER

FIE

LD O

F V

IEW

SY

MM

ET

RIC

AL.

EX

AM

PLE

: WH

EN

CA

PT

AIN

TU

RN

S H

IS H

EA

D B

Y 8

0° L

EF

T, V

ISIB

ILIT

YW

ILL

BE

35°

UP

AN

D 2

5° D

OW

N T

HR

OU

GH

TH

E S

LID

ING

WIN

DO

W F

RA

ME

.

35°

30°

20°

10°

0° 10°

20°

25°

110°

100°

90°

80°

70°

50°

40°

30°

20°

10°

0°10

°20

°40

°50

°60

°80

°90

°10

0°13

0°12

0°60

°30

°70

°11

0°

N_AC_040400_1_0050101_01_00

Binocular Visibility Through Windows from Captain Eye PositionFIGURE-4-4-0-991-005-A01

4-4-0Page 3

Jun 01/12


4-5-0 Runway and Taxiway Turn Paths

**ON A/C A320-200

Runway and Taxiway Turn Paths

1. Runway and Taxiway Turn Paths.

4-5-0Page 1

Jun 01/12



**ON A/C A320-200

135˚ Turn - Runway to Taxiway

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

4-5-1Page 1

Jun 01/12


**ON A/C A320-200

FAA LEAD−IN FILLET

L = 45 m (150 ft)

TAXIWAYCENTERLINE

RUNWAY CENTERLINE

TURN R = 30 m(100 ft)

FILLET R = 16.5 m(55 ft)

APPROX 4.3 m(14 ft)

NOTE: FAA GROUP III FACILITIES.

30 m

N_AC_040501_1_0040101_01_01

NLG PATH

MLG PATH

15 m(50 ft)

(100 ft)

135˚ Turn - Runway to TaxiwayCockpit Over Centerline Method

FIGURE-4-5-1-991-004-A01

4-5-1Page 2

Jun 01/12


**ON A/C A320-200

TAXIWAYCENTERLINE

RUNWAY CENTERLINE

TURN R = 30 m(100 ft)



L = 45 m (150 ft)

APPROX 3.2 m(10 ft)

30 m


N_AC_040501_1_0120101_01_00

NLG PATH

MLG PATH

15 m(50 ft)

(100 ft)

135˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

FIGURE-4-5-1-991-012-A01

4-5-1Page 3

Jun 01/12



**ON A/C A320-200

90˚ Turn - Runway to Taxiway

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

4-5-2Page 1

Jun 01/12


**ON A/C A320-200

APPROX 5.8 m(19 ft)


TURN R = 30 m(100 ft)

RUNWAY CENTERLINE

FAA LEAD−IN FILLETL = 45 m (150 ft)

TAXIWAY CENTERLINE

NOTE: FAA GROUP III FACILITIES.N_AC_040502_1_0040101_01_01

NLG PATH

MLG PATH

30 m(100 ft)

15 m(50 ft)

90˚ Turn - Runway to TaxiwayCockpit Over Centerline Method

FIGURE-4-5-2-991-004-A01

4-5-2Page 2

Jun 01/12


**ON A/C A320-200

APPROX 9.2 m(30 ft)


TURN R = 30 m(100 ft)

RUNWAY CENTERLINE


TAXIWAY CENTERLINE


NLG PATH

MLG PATH

30 m(100 ft)

15 m(50 ft)

N_AC_040502_1_0090101_01_00

90˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

FIGURE-4-5-2-991-009-A01

4-5-2Page 3

Jun 01/12


4-5-3 180˚ Turn on a Runway

**ON A/C A320-200

180˚ Turn on a Runway

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

4-5-3Page 1

Jun 01/12


**ON A/C A320-200

30 m(100 ft)

NOTE: TYPE 1 VALUES.

RUNWAY CENTERLINE

R3 = 13.4 m(44 ft)

R5 = 18.2 m(60 ft)

R4

3.15 m(10 ft)

5.75 m(19 ft)

N_AC_040503_1_0060101_01_00

NLG PATH

WINGTIP PATH:

NOSE PATH

MLG PATH

WINGTIP FENCES:R4 = 21.6 m (71 ft)SHARKLETS:R4 = 22.5 m (74 ft)

180˚ Turn on a RunwayEdge of Runway Method (Sheet 1 of 2)

FIGURE-4-5-3-991-006-A01

4-5-3Page 2

Jun 01/12


**ON A/C A320-200

30 m(100 ft)

NOTE: TYPE 1 VALUES.

RUNWAY CENTERLINE

4.33 m(14 ft)

3.13 m(10 ft)

25°

N_AC_040503_1_0060102_01_00

NLG PATH

WINGTIP PATH:

NOSE PATH

MLG PATH

WINGTIP FENCES:R4 = 21.6 m (71 ft)SHARKLETS:R4 = 22.5 m (74 ft)

R3 = 13.4 m(44 ft)

R5 = 18.2 m(60 ft)

R4

180˚ Turn on a RunwayCenter of Runway Method (Sheet 2 of 2)

FIGURE-4-5-3-991-006-A01

4-5-3Page 3

Jun 01/12



**ON A/C A320-200

135˚ Turn - Taxiway to Taxiway

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

4-5-4Page 1

Jun 01/12


**ON A/C A320-200


APPROX 4.9 m(16 ft)

NLG PATH

MLG PATH

TAXIWAY CENTERLINE

NOTE: FAA GROUP III FACILITIES

TAXIWAY CENTERLINE

FILLET R = 16.5 m

TURN R = 30 m

15 m(50 ft)

15 m(50 ft)

N_AC_040504_1_0060101_01_00

(100 ft)

(55 ft)

L = 45 m (150 ft)

135˚ Turn - Taxiway to TaxiwayCockpit Over Centerline Method (Sheet 1 of 2)

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

4-5-4Page 2

Jun 01/12


**ON A/C A320-200

NLG PATH

MLG PATH

TAXIWAY CENTERLINE

NOTE: FAA GROUP III FACILITIES

TAXIWAY CENTERLINE

FILLET R = 16.5 m

TURN R = 30 m


APPROX 3 m

N_AC_040504_1_0060102_01_00

15 m(50 ft)

15 m(50 ft)

L = 45 m (150 ft)(55 ft)

(100 ft)

(10 ft)

135˚ Turn - Taxiway to TaxiwayJudgemental Oversteering Method (Sheet 2 of 2)

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

4-5-4Page 3

Jun 01/12



**ON A/C A320-200

90˚ Turn - Taxiway to Taxiway

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

4-5-5Page 1

Jun 01/12


**ON A/C A320-200

N_AC_040505_1_0020101_01_01

TAXIWAY CENTERLINE

NLG PATH

MLG PATHTAXIWAY CENTERLINE

APPROX 5.2 m(17 ft)


TURN R = 30 m(100 ft)



15 m(50 ft)

15 m(50 ft)

90˚ Turn - Taxiway to TaxiwayCockpit Over Centerline Method (Sheet 1 of 2)

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

4-5-5Page 2

Jun 01/12


**ON A/C A320-200

TAXIWAY CENTERLINE

NOTE:

NLG PATH

MLG PATH

FAA GROUP III FACILITIES.

TAXIWAY CENTERLINE

APPROX 9 m(29 ft)


TURN R = 30 m(100 ft)


N_AC_040505_1_0020102_01_00

15 m(50 ft)

15 m(50 ft)

90˚ Turn - Taxiway to TaxiwayJudgemental Oversteering Method (Sheet 2 of 2)

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

4-5-5Page 3

Jun 01/12


4-6-0 Runway Holding Bay (Apron)

**ON A/C A320-200

Runway Holding Bay (Apron)

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

4-6-0Page 1

Jun 01/12


**ON A/C A320-200

RUNWAY CENTERLINETAXIWAY

CENTERLINE

HOLDING POINT

12.2 m

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

N_AC_040600_1_0030101_01_01

190 m

23 m(75 ft)

45 m(150 ft)

61 m(200 ft)61 m

(200 ft)

6.1 m(20 ft)

6.1 m(20 ft)

190 m(625 ft)

(40 ft)

90 m(300 ft)

Runway Holding Bay (Apron)FIGURE-4-6-0-991-003-A01

4-6-0Page 2

Jun 01/12


TERMINAL SERVICING

5-0-0 TERMINAL SERVICING

**ON A/C A320-200

Terminal Servicing

1. GeneralThis 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.- Section 5.2 shows the minimum turnaround schedules for full servicing arrangements.- Section 5.3 shows the minimum turnaround schedule for reduced servicing arrangements.- Section 5.4 gives the locations of ground service connections, the standard of connections used

and typical capacities and requirements.- Section 5.5 provides the engine starting pneumatic requirements for different engine types and

different ambient temperatures.- Section 5.6 provides the air conditioning requirements for heating and cooling (pull-down and

pull-up) using ground conditioned air for different ambient temperatures.- Section 5.7 provides the air conditioning requirements for heating and cooling to maintain a

constant cabin air temperature using low pressure conditioned air.- Section 5.8 shows the ground towing requirements taking into account different ground surface

and aircraft conditions.

5-0-0Page 1

Jun 01/12


5-1-0 Servicing Arrangements

**ON A/C A320-200

Airplane Servicing Arrangements

1. GeneralThis chapter 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 chart for full servicing is given in section 5.2.The associated turnaround chart for minimum servicing arrangement is given in section 5.3.

5-1-0Page 1

Jun 01/12


5-1-1 Symbols Used on Servicing Diagrams

**ON A/C A320-200

Symbols Used on Servicing Diagrams

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

Ground Support Equipment

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

5-1-1Page 1

Jun 01/12


5-1-2 Typical Ramp Layout - Open Apron

**ON A/C A320-200

Typical Ramp Layout - Open Apron

1. This section gives the typical servicing arrangement for pax version (Open Apron).

The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m from theaircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheel chocks inposition on landing gears).

5-1-2Page 1

Jun 01/12


**ON A/C A320-200

N_AC_050102_1_0030101_01_03

STAND SAFETY LINE

NOTE: TYPICAL RAMP LAYOUTAPPLICABLE TO AIRCRAFTWITH OR WITHOUT SHARKLETS.

8METERS

FEET5 10 150 20

0 2 4 6

CAT

CAT

LV

FUEL

ASTOW

WV

GPU

CB

CB

BULK

BULK

PS

PS

AC

Typical Ramp LayoutOpen Apron - Bulk LoadingFIGURE-5-1-2-991-003-A01

5-1-2Page 2

Jun 01/12


**ON A/C A320-200

N_AC_050102_1_0090101_01_00

STAND SAFETY LINE


8METERS

FEET5 10 150 20

0 2 4 6

CAT

ULD

CAT

LV

ULD

FUEL

ASTOW

WV

BULK

GPU

CB

PS

PS

LD CL

LD CL

AC

Typical Ramp LayoutOpen Apron - ULD LoadingFIGURE-5-1-2-991-009-A01

5-1-2Page 3

Jun 01/12


5-1-3 Typical Ramp Layout - Gate

**ON A/C A320-200

Typical Ramp Layout - Gate

1. This section gives the typical servicing arrangement for pax version (Passenger Bridge).

The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m from theaircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheel chocks inposition on landing gears).

5-1-3Page 1

Jun 01/12


**ON A/C A320-200

LD CL

LD CL

N_AC_050103_1_0020101_01_03

STAND SAFETY LINE


8METERS

FEET5 10 150 20

0 2 4 6

CAT

ULD

CAT

LV

ULDPBB

FUEL

ASTOW

WV

BULK

GPU

CB

AC

Typical Ramp LayoutGate

FIGURE-5-1-3-991-002-A01

5-1-3Page 2

Jun 01/12


5-2-0 Terminal Operations - Full Servicing

**ON A/C A320-200

Terminal Operations - Full 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.

For each turn round time chart, the associated typical ramp layout is given in Section 5-1.

2. Assumptions for full turn round chart

A. PASSENGER HANDLING150 pax, all Y/CAll passengers deboard and board the aircraft1 Passenger Boarding Bridge (PBB) used at door L1Equipment positioning/removal + opening/closing door = 2 min

Deboarding:- 150 pax at door L1- Deboarding rate = 22 pax/min per door- No Passenger with Reduced Mobility (PRM)

Boarding:- 150 pax at door L1- Boarding rate = 18 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +2 min- No Passenger with Reduced Mobility

B. CARGO2 cargo loaders + 1 belt loaderEquipment positioning/removal + opening/closing door = +1 min

Cargo exchange:- FWD cargo compartment: 3 LD3- AFT cargo compartment: 4 LD3- Bulk compartment: 500 kg (1102 lb)

LD3 off-loading/loading times:- Off-loading = 1.2 min/LD3- Loading = 1.4 min/LD3

5-2-0Page 1

Jun 01/12


Bulk off-loading/loading times:- Bulk off-loading rate = 120 kg/min (265 lb/min)- Bulk loading rate = 100 kg/min (220 lb/min)

C. REFUELLING2 hoses, one side7134 l (1885 US gal) at 50 psi (3 bar)Dispenser positioning/removal = 4 min

D. CLEANINGPerformed in available time

E. CATERING1 catering truck for servicing galleys sequentially at doors R1 & R2Equipment positioning/removal + door opening/closing = 2 minTime to drive from one door to the other = 1 minFull Size Trolley Equivalent (FSTE) to unload and load:- 4 FSTE at door R1- 7 FSTE at door R2Time for trolley exchange = 1.5 min per FSTE

F. GROUND HANDLING SERVICINGStart of operations:- Bridges: t0 = 0- Other equipment: t = t0 + 1 minPotable water servicing: 100% uplift, 200 l (53 US gal), max filling pressure = 3.45 bar (50 psi)Toilet servicing: draining + rinsing = 5 min, max rinse & precharge pressure = 3.45 bar (50psi)

5-2-0Page 2

Jun 01/12


**ON A/C A320-200

0 5 15 20 25 30 35 40

CATERING AT DOOR R1

CATERING AT DOOR R2

CLEANING

CARGO FWD CC

BULK

REFUELLING

TOILET SERVICING

HEADCOUNTING

CARGO AFT CC

TRT: 43 min

10 45

POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH

DEBOARDING/BOARDING AT DOOR L1

POTABLE WATERSERVICING

N_AC_050200_1_0060101_01_01

min

AVAILABLE TIME

Turn Round StationsFull Servicing (43 Min.)

FIGURE-5-2-0-991-006-A01

5-2-0Page 3

Jun 01/12


5-3-0 Terminal Operation - Transit

**ON A/C A320-200

Terminal Operation - 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.

For each turn round time chart, the associated typical ramp layout is given in Section 5-1.

2. Assumptions for minimum turn round chart

A. PASSENGER HANDLING180 pax, all Y/C2 Stairways used at doors L1 & L2Equipment positioning/removal + opening/closing door = 2 min

Deboarding:- 90 pax at door L1- 90 pax at door L2- Deboarding rate = 20 pax/min per door- No Passenger with Reduced Mobility (PRM)

Boarding:- 90 pax at door L1- 90 pax at door L2- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +2 min- No Passenger with Reduced Mobility

B. CARGO2 cargo loadersEquipment positioning/removal + opening/closing door = +1 min

Cargo exchange:- FWD cargo compartment: 3 LD3- AFT cargo compartment: 4 LD3- Bulk cargo compartment: 500 kg (1102 lb)

LD3 off-loading/loading times:- Off-loading = 1.2 min/LD3- Loading = 1.4 min/LD3

5-3-0Page 1

Jun 01/12


Bulk off-loading/loading times:- Off-loading rate = 120 kg/min (265 lb/min)- Loading rate = 100 kg/min (220 lb/min)

C. REFUELLING2 hoses, one side7134 l (1885 US gal) at 50 psi (3 bar)Dispenser positioning/removal = 4 min

D. CLEANINGPerformed in available time

E. CATERINGNo catering

F. GROUND HANDLING SERVICINGStart of operations:- Bridges: t0 = 0- Other equipment: t = t0 + 1 minNo potable water servicingNo toilet servicing

5-3-0Page 2

Jun 01/12


**ON A/C A320-200

TRT: 23 min

POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH

0 5 15 20 25 3010

AVAILABLE TIME

AVAILABLE TIME

min

N_AC_050300_1_0030101_01_01

HEADCOUNTING

CATERING

CLEANING

CARGO FWD CC

BULK

REFUELLING

POTABLE WATER SERVICING

TOILET SERVICING

CARGO AFT CC



Turn Round StationsMinimum Servicing (23 Min.)FIGURE-5-3-0-991-003-A01

5-3-0Page 3

Jun 01/12


5-4-0 Ground Service Connections

**ON A/C A320-200

Ground Service Connections

1. Ground Service Connections.

5-4-0Page 1

Jun 01/12


5-4-1 Ground Service Connections Layout

**ON A/C A320-200

Ground Service Connections Layout

1. This section gives the ground service connections layout.

5-4-1Page 1

Jun 01/12


**ON A/C A320-200

1 2 3 11 12 2 4 14−6 7−

141

CONNECTOR (LP) PANELS

EXTERNAL POWER RECEPTACLETOILET SERVICE DOORGROUNDING POINT NLGPOTABLE WATER SERVICE DOORGROUND SERVICE CONDITIONED AIR

IDG OIL FILLINGENGINE OIL FILLING CONNECTOR APU OIL FILLING

GRAVITY REFUEL

HYDRAULIC SYSTEM GROUND SERVICESGROUNDING POINT MLGREFUEL/DEFUEL CONNECTORSREFUEL/DEFUEL PANELGROUND AIR START CONNECTOR (HP)1 −

2 −3 −4 −5 −

8 −9 −

10 −11 −12 −

6 −7 −

13 −14 −

13

10

10

13

67

6

7

42 5 8 12

29

N_AC_050401_1_0050101_01_01

Ground Service ConnectionsGround Service Connections Layout

FIGURE-5-4-1-991-005-A01

5-4-1Page 2

Jun 01/12


5-4-2 Grounding Points

**ON A/C A320-200

Grounding Points

1. Grounding Points.

DISTANCE: Meters (ft)

FROM AIRPLANE CENTERLINEAFT OF NOSE

R SIDE L SIDE

MEAN HEIGHTFROM

GROUNDOn Nose Landing Gearleg:

5.07 m(16.63 ft) on centerline

0.94 m(3.08 ft)

On left Main LandingGear leg:

20.25 m(66.44 ft)

3.79 m(12.43 ft)

1.07 m(3.51 ft)

On right Main LandingGear leg:

20.25 m(66.44 ft)

3.79 m(12.43 ft)

1.07 m(3.51 ft)

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

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

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

5-4-2Page 1

Jun 01/12


**ON A/C A320-200

(2)(1)

GROUND CABLE(OPTIONAL)

LANDINGGEAR

NOSE LANDING GEAR

MAIN LANDING GEAR

(1)

A

A

A

(1)

N_AC_050402_1_0050101_01_00

Ground Service ConnectionsGrounding Points

FIGURE-5-4-2-991-005-A01

5-4-2Page 2

Jun 01/12


**ON A/C A320-200

NOTE: R SIDE SYMMETRICAL

A

FWD

A

FOR SPECIFICATIONS REFERTO FLIGHT MANUAL

B

B

RIB20

RIB19

N_AC_050402_1_0060101_01_00

A

Ground Service ConnectionsGrounding Points

FIGURE-5-4-2-991-006-A01

5-4-2Page 3

Jun 01/12


5-4-3 Hydraulic System

**ON A/C A320-200

Hydraulic System

1. Access.

POSITION FROM AIRCRAFTCENTERLINE

ACCESSAFT OF NOSE

m (ft) RH SIDEm (ft)

LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Green System:Access door 197CB

19.17(62.89)

1.27(4.17)

1.76(5.77)

Yellow System:Access door 198CB

19.17(62.89)

1.27(4.17)

1.76(5.77)

Blue System:Access door 197EB

20.22(66.34)

1.27(4.17)

1.76(5.77)

NOTE : Distances are approximate.

2. Reservoir Pressurization.On the air pressurization manifold:


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Access door 195BB15.65(51.35)

0.25(0.82)

1.74(5.71)

NOTE : Distances are approximate.- One 1/4 in. AEROQUIP AE 96994E self-sealing connection common to the 3 reservoirs.

3. Accumulator Charging.Four (MS28889-1) connections (one for each accumulator) for:


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Yellow Systemaccumulator:Access door 196BB

16.1(52.82)

0.25(0.82)

1.99(6.53)

5-4-3Page 1

Jun 01/12



ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Green Systemaccumulator:Left MLG door

16.77(55.02)

0.25(0.82)

3.2(10.5)

Blue Systemaccumulator:Access door 195BB

18.2(59.71)

0.25(0.82)

1.99(6.53)

Yellow System brakingaccumulator:Access door 196BB

16.1(52.82)

0.76(2.49)

1.74(5.71)


4. Reservoir Filling.On the Green system ground service panel:


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Access door 197CB19.17(62.89)

1.27(4.17)

1.76(5.77)

NOTE : Distances are approximateOne 1/4 in. AEROQUIP AE96993E self-sealing connection for pressurized supply.One handpump filling connection for unpressurized (suction) supply.

5. Reservoir Drain.On 3/8 in. self-sealing connection on reservoir for:


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Yellow System:Access door 196BB -198CB

16.1(52.82)

1.43(4.69)

1.90(6.23)

Green System:Left MLG door

16.77(55.02)

1.27(4.17)

2.61(8.56)

5-4-3Page 2

Jun 01/12



ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Blue SystemAccess door 197EB

20.22(66.34)

1.27(4.17)

1.76(5.77)

NOTE : Distances are approximate.On 3/8 in. self-sealing connection for the Blue system on:- Blue system ground service panel.

6. Ground Test.On each ground service panel:- One self-sealing connector AE80532N (suction).- One self-sealing connector AE80531K (delivery).

5-4-3Page 3

Jun 01/12


**ON A/C A320-200

RESERVOIR FILL SYSTEMHAND PUMP FILL CONNECTION

GROUND TESTPRESSURE

CONNECTION

GROUND TESTSUCTION

CONNECTIONRESERVOIR FILLCONNECTION

AE96993GM

GROUND SUPPLY

AE80531K AE80532N

1698GM

1008GM 1007GM 1006GM

197CB

A

AN_AC_050403_1_0040101_01_00

Hydraulic SystemGreen System Ground Service Panel

FIGURE-5-4-3-991-004-A01

5-4-3Page 4

Jun 01/12


**ON A/C A320-200

GROUND CONNECTIONSUCTION

GROUNDCONNECTION

DELIVERY

AE80531K

AE80532N

2006GM

2008GM

A

Z197

A

N_AC_050403_1_0050101_01_00

Hydraulic SystemBlue System Ground Service Panel

FIGURE-5-4-3-991-005-A01

5-4-3Page 5

Jun 01/12


**ON A/C A320-200

GROUND TESTPRESSURE CONNECTION

GROUND TESTSUCTION CONNECTION

AE80531K AE80532N

A

A

3008GM 3006GM

198CB

N_AC_050403_1_0060101_01_00

Hydraulic SystemYellow System Ground Service Panel

FIGURE-5-4-3-991-006-A01

5-4-3Page 6

Jun 01/12


5-4-4 Electrical System

**ON A/C A320-200

Electrical System

1. Electrical System.This chapter gives data related to the location of the ground service connections.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

A/C External Power:Access door 121AL

2.55(8.37) on centerline

2.00(6.56)


2. Technical SpecificationsThis chapter gives data related to the location of the ground service connections.

A. External Power Receptacle:- One Style3 ISO 461 receptacle - 90 KVA.

B. Power Supply:- Three-phase, 400 Hz, 115/200V

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

D. Electrical Loads in Ground ConfigurationIn ground configuration, in addition to the power necessary for maintenance, all the circuits,except those which are connected to the engines, are supplied as in flight.In these conditions, the maximum power on ground is approximately 75 KVA; this value doesnot take into account the supply of the galleys, which according to the aircraft interior layout,may reach 30 KVA.

E. Electrical Power necessary for Maintenance at Line Stop and Workshops- Hydraulic electric-pumps: 34 KVA- Air Conditioning/Ventilation: 20.8 KVA- Fuel pumps: 12 KVA- Lighting commercial: 6.7 KVA- Lighting technical: 3 KVA- Ice and rain protection: 3 KVA- Cargo loading: 3 KVA- AFS, Flight controls, ADS, Recorders: 3.3 KVA- Communications: 1.3 KVA

5-4-4Page 1

Jun 01/12


- Radio navigation: 1.2 KVA.

5-4-4Page 2

Jun 01/12


**ON A/C A320-200

108VU

A

N_AC_050404_1_0010101_01_01

A

121AL

Ground Service ConnectionsExternal Power ReceptaclesFIGURE-5-4-4-991-001-A01

5-4-4Page 3

Jun 01/12


5-4-5 Oxygen System

**ON A/C A320-200

Oxygen System

1. Oxygen System.

DISTANCE: Meters (ft)

FROM AIRPLANE CENTERLINE

AFT OF NOSER SIDE L SIDE

MEANHEIGHTFROM

GROUNDOne service connection(external charging in theavionics compartment)MS22066 Std.

3.45 m(11.32 ft)

1.15 m(3.77 ft)

2.60 m(8.53 ft)

3/8” UNF × 24 TPI

Nominal pressure: 1850 psi (127.55 bar)

Max fill pressure: 2035 psi (140.31 bar)

NOTE : Internal charging connection provided.

5-4-5Page 1

Jun 01/12


5-4-6 Fuel System

**ON A/C A320-200

Fuel System

1. Refuel/Defuel Control Panel.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Refuel/DefuelIntegrated Panel:Access door 192MB

16.4(53.81)

1.8(5.91)

1.8(5.91)

2. Refuel/Defuel Connectors.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Refuel/Defuel coupling,LeftAccess Door 522HB(Optional)

17.59(57.71)

9.83(32.25)

3.65(11.98)

Refuel/Defuel coupling,RightAccess Door 622HB

17.59(57.71)

9.83(32.25)

3.65(11.98)

Gravity Refuel Coupling19.1(62.66)

12.4(40.68)

12.4(40.68)

3.7(12.14)

A. Refuel/Defuel couplings:- Right wing: one standard ISO 45, 2.5 in.- Left wing: one optional standard ISO 45, 2.5 in.

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

C. Refuel Flow:- 1400 l/minute (369.84 US gal/minute).

5-4-6Page 1

Jun 01/12


3. Overpressure Protector and NACA Flame Arrestor.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Overpressure Protector 20.36(66.80)

14.9(48.88)

14.9(48.88)

4.32(14.17)

NACA Flame Arrestor 19.8(64.96)

13.7(44.95)

13.7(44.95)

4.02(13.19)


5-4-6Page 2

Jun 01/12


**ON A/C A320-200

REFUEL/DEFUELCONTROL PANEL

NOTE: STANDARD CONFIGURATION OF REFUEL/DEFUEL PANEL.

A

FUELkg x 1000

QTY

RIGHTCTRLEFT

LEFT CTR RIGHT

LVLHI

OPEN

NORM

SHUT

OPEN

NORM

SHUT

REFUEL VALVESOPEN

NORM

SHUT

BATT POWERTESTHI LVL ON

OPEN LTS NORM

MODE SELECTREFUEL

OFF

DEFUEL / XFR

kg x 1000

PRESELECTED

DEC INC

ACTUALREFUEL

CKPT END

A

N_AC_050406_1_0010101_01_00

Ground Service ConnectionsRefuel/Defuel Panel

FIGURE-5-4-6-991-001-A01

5-4-6Page 3

Jun 01/12


**ON A/C A320-200

RIB15

RIB14

A

41QM

40QM

LEADINGEDGE

WING FRONTSPAR

A

N_AC_050406_1_0020101_01_00

Ground Service ConnectionsRefuel/Defuel Couplings

FIGURE-5-4-6-991-002-A01

5-4-6Page 4

Jun 01/12


**ON A/C A320-200

RIB19

RIB20

A

ADAPTER(REF ONLY)

GROUND CONNECTION(REF ONLY)

44QM

(45QM)

AFWD

N_AC_050406_1_0030101_01_00

Ground Service ConnectionsGravity Refuel Couplings

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

5-4-6Page 5

Jun 01/12


**ON A/C A320-200

A

A ALH SHOWN

RH SYMMETRICAL

FWD

NACA VENT INTAKE

NACA FLAME ARRESTOR

OVERPRESSURE PROTECTOR

N_AC_050406_1_0040101_01_00

B

C

RIB25RIB24

RIB23

RIB22

550CB (650CB)

550AB (650AB)

C

B

Ground Service ConnectionsOverpressure Protector and NACA Flame Arrestor

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

5-4-6Page 6

Jun 01/12


5-4-7 Pneumatic System

**ON A/C A320-200

Pneumatic System

1. High Pressure Air Connectors.This chapter gives data related to the location of the ground service connections.

POSITION FROM AIRCRAFTCENTERLINEAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

HP ConnectorAccess door 191DB

12.98(42.59)

0.84(2.76)

1.76(5.77)


A. Connector:- One standard 3 in. ISO TC20 connection (MS33740) for engine starting and cabin air

preconditioning (HP) installed on the left side of the belly fairing

2. Low Pressure Air Connectors.This chapter gives data related to the location of the ground service connections.

POSITION FROM AIRCRAFTCENTERLINEAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

LP ConnectorAccess door 191CB

12.45(40.85)

1.11(3.64)

1.73(5.68)


A. Connector:- One standard 8 in. connection (SAE AS4262 type B) for cabin air preconditioning (LP)

installed on the left side of the belly fairing

5-4-7Page 1

Jun 01/12


5-4-8 Potable Water System

**ON A/C A320-200

Potable Water System

1. Potable Water Ground Service Panel.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM GROUND

m (ft)

Potable WaterGround ServicePanel:Access door 171AL:

31.3(102.69)

0.3(0.98)

2.6(8.53)

NOTE : Distances are approximate

2. Potable Water Ground Drain Panel.


ACCESSAFT OF NOSE


LH SIDEm (ft)


m (ft)

Potable WaterGround ServicePanel:Access door 133AL(Optional)

11.8(38.71)

0.15(0.49)

1.75(5.74)

Potable WaterGround ServicePanel:Access door 192NB

12.5(41.01)

0.51(1.67)

1.75(5.74)


3. Technical Specifications

A. Connectors:

(1) On the potable ground service panel (Access Door 171AL)- Fill/Drain Nipple 3/4 in (ISO 17775).- One ground pressurization connector.

5-4-8Page 1

Jun 01/12


(2) On drain panel (Access Door 133AL and/or 192NB)- Drain Nipple 3/4 in (ISO 17775)

B. Usable capacity:- Standard configuration - one tank:200 l (52.83 US gal)

C. Filling pressure:- 3.45 bar (50 psi).

D. Typical flow rate:- 50 l/min (13.21 US gal/min).

5-4-8Page 2

Jun 01/12


**ON A/C A320-200

DRAIN CONNECTION

DRAIN CONNECTIONDISCHARGE ANDOVERFLOW PORT

FILL ANDDRAIN PORT

GROUND CONNECTION

PRESSURIZATION

Z133

Z171

Z138

A

B

B

C

A

C

N_AC_050408_1_0020101_01_00

Ground Service ConnectionsPotable Water Ground Drain Panel

FIGURE-5-4-8-991-002-A01

5-4-8Page 3

Jun 01/12


5-4-9 Oil System

**ON A/C A320-200

Oil System

1. Engine Oil Replenishment for CFM56 Series Engine (See FIGURE 5---9-99--001-A):One gravity filling cap and one pressure filling connection per engine.


ACCESSAFT OF NOSE

m (ft) ENGINE 1 (LH)m (ft)

ENGINE 2 (RH)m (ft)


m (ft)

Engine Oil GravityFilling Cap:Access door: 437BL(LH),447BL (RH)

13.12(43.04)

6.63(21.75)

4.82(15.81)

1.46(4.79)

Engine Oil PressureFilling Port:

13(42.65)

6.49(21.29)

4.74(15.55)

1.42(4.66)


A. Tank capacity:- Full level: 19.6 l (5.18 US gal)- Usable: 9.46 l (2.50 US gal)

B. Maximum delivery pressure required: 25 psi (1.72 bar)Maximum delivery flow required: 180 l/h (47.55 US gal/h)

2. IDG Oil Replenishment for CFM56 Series Engine (See FIGURE 5---9-99--002-A):One pressure filling connection per engine: OMP 2506-18 plus one connection overflow: OMP2505-18.


ACCESSAFT OF NOSE


ENGINE 2 (RH)m (ft)


m (ft)

IDG Oil PressureFilling Connection:Access door 438DR(LH),448DR (RH)

12.2(40.03)

6.9(22.64)

5.52(18.11)

0.68(2.23)


5-4-9Page 1

Jun 01/12


A. Tank capacity: 5 l (1.32 US gal)

B. Delivery pressure required: 5 to 40 psi (0.34 to 2.76 bar) at the IDG inlet.

3. Starter Oil Replenishment for CFM56 Series Engine (See FIGURE 5---9-99--003-A:One gravity filling cap per engine.


ACCESSAFT OF NOSE


ENGINE 2 (RH)m (ft)


m (ft)

Starter Oil FillingConnection:

12.7(41.67)

5.3(17.39)

6.2(20.34)

0.76(2.49)


A. Tank capacity: 0.8 l (0.21 US gal)

4. Engine Oil Replenishment for IAE V2500 Series Engine (See FIGURE 5---9-99--004-B):One gravity filling cap per engine.


ACCESSAFT OF NOSE


ENGINE 2 (RH)m (ft)


m (ft)

Engine Oil GravityFilling Cap:Access door 437BL(LH),447BL (RH)

12.24(40.16)

6.56(21.52)

4.92(16.14)

1.22(4)


A. Tank capacity:- Full level: 28 l (7.4 US gal)- Usable: 23.50 l (6.21 US gal)

1. IDG Oil Replenishment for IAE V2500 Series Engine:One pressure filling connection per engine: OMP 2506-2 plus one overflow connection: OMP 2505-2.

5-4-9Page 2

Jun 01/12



ACCESSAFT OF NOSE


ENGINE 2 (RH)m (ft)


m (ft)

IDG Oil PressureFilling Connection:

12.8(41.99)

5.42(17.78)

6.04(19.82)

0.8(2.62)



5. Starter Oil Replenishment for IAE V2500 Series Engine (See FIGURE 5---9-99--006-B):One gravity filling cap per engine.


ACCESSAFT OF NOSE


ENGINE 2 (RH)m (ft)


m (ft)

Starter Oil FillingConnection:

15.4(50.52)

5.3(17.39)

6.14(20.14)

0.75(2.46)



6. APU Oil System (See FIGURE 5---9-99--007-A):APU oil gravity filling cap.

AFT OF NOSEm (ft)

FROM AIRPLANECENTERLINE(LEFT HAND)

m (ft)

MEAN HEIGHT FROMGROUND

m (ft)

GTCP 36-30035.49(116.44)

0.3(0.98)

4.83(15.85)

APS 320035.49(116.44)

0.3(0.98)

4.78(15.68)

131-935.39(116.11)

0.35(1.15)

4.32(14.17)


A. Tank capacity (usable):- APU type GTCP 36-300: 6.20 l (1.64 US gal)- APU type APS 3200: 5.40 l (1.43 US gal)

5-4-9Page 3

Jun 01/12


- APU type 131-9: 6.25 l (1.65 US gal)

5-4-9Page 4

Jun 01/12


**ON A/C A320-200

ACCESS PANEL: 437BL (LEFT)447BL (RIGHT) OIL IN

VENT

OIL LEVELTRANSMITTER(OPTIONAL)

OIL CAP

SIGHT WINDOW

ANTI−SIPHONDEVICE

AIR PRESSURESWITCH NIPPLE

SELF−SEALING MAGNETICDRAIN PLUG

PRESSURE NIPPLE

OIL OUT

OIL/FUEL HEATEXCHANGER

SERVO FUELHEATER

A

A

B

FWD

B

N_AC_050409_1_0010101_01_00

Ground Service ConnectionsEngine Oil Tank -- CFM56 Series Engine

FIGURE-5-4-9-991-001-A01

5-4-9Page 5

Jun 01/12


**ON A/C A320-200

C

A

B

SIGHT GLASS

NOTE: ATHE YELLOW BAND, OIL SERVICINGIS REQUIRED.

BTHE GREEN AND YELLOW BANDS,OIL SERVICING IS NOT REQUIRED.

CTHE GREEN BAND, OIL SERVICINGIS REQUIRED.

1 − PRESSURE FILL VALVE2 − CASE DRAIN PLUG3 − DUST CAP4 − DUST CAP5 − OVERFLOW DRAIN VALVE6 − OIL LEVEL INDICATOR

(SIGHT GLASS)

1

2

34

5

6

A B

A

B

OVERFULL

ADDOIL

ADDOIL

CFM−56

IF THE OIL LEVEL IS ABOVE

IF THE OIL LEVEL IS WITHIN

IF THE OIL LEVEL IS BELOW

N_AC_050409_1_0020101_01_01

Ground Service ConnectionsIDG Oil Tank -- CFM56 Series Engine

FIGURE-5-4-9-991-002-A01

5-4-9Page 6

Jun 01/12


**ON A/C A320-200

DRAIN PORTAND MAGNETICPLUG

OVERFLOWPLUG

STARTER

OIL FILLERPLUG

A

A

N_AC_050409_1_0030101_01_02

Ground Service ConnectionsStarter Oil Tank -- CFM56 Series Engine

FIGURE-5-4-9-991-003-A01

5-4-9Page 7

Jun 01/12


**ON A/C A320-200

’FULL’ LEVEL NOTCH27.3 LT29.0 US QTS6.0 IMP GAL(WITHIN 60 MIN FROM SHUTDOWN)

NOTCH ’3’20 LT22 US QTS4.5 IMP GAL

NOTCH ’1’26 LT27 US QTS5.7 IMP GALNOTCH ’2’

23 LT24 US QTS5.1 IMP GAL

FCOC

PRISMALITELEVEL INDICATOR

OIL TANK

GRAVITYFILLER CAP

ACCESS PANEL: 437BL (LEFT)447BL (RIGHT)

B

A

A

B

FWD

N_AC_050409_1_0040201_01_00

Ground Service ConnectionsEngine Oil Tank -- IAE V2500 Series Engine

FIGURE-5-4-9-991-004-B01

5-4-9Page 8

Jun 01/12


**ON A/C A320-200

THE OIL LEVEL MUST NOT BE INTHE YELLOW BAND BUT IT CANBE IMMEDIATELY ABOVE THELOWER LIMIT OF THE YELLOWBAND BECAUSE OF THE AIRCRAFTRAMP ANGLE

DO THE IDG SERVICINGTO GET THE CORRECT IDGOIL LEVEL.

AFTER SERVICING ORENGINE SHUTDOWN

(COLD OIL/IDG)

INCORRECTLY FILLED IDG

THE OIL LEVEL MUST NOT BEIN THE RED BAND

PERFORM IDG OIL SERVICINGTO GET THE CORRECT IDG OIL LEVEL.DO NOT USE THE OVERFLOW DRAIN HOSETO GET THE CORRECT IDG OIL LEVEL.

AT ALL TIMES(HOT OR COLD OIL/IDG)

OIL LEVEL CAN BEIN THE GREEN BAND OR THEYELLOW BAND

AFTER ENGINESHUTDOWN

CORRECTLY FILLED IDG

OIL LEVELINDICATOR

DUST CAPPRESSUREFILL HOSE

OIL LEVEL MUST BE AT OR NEARTHE LINE BETWEEN THE YELLOW BANDAND THE GREEN BAND

(HOT OIL/IDG)

PRESSUREFILL VALVE

DUST CAP

OVER FLOWDRAIN VALVE

OVER FLOWDRAIN HOSE

AFTER SERVICING ORENGINE SHUTDOWN

(COLD OIL/IDG)

IDG

B

BB

A

B

A

B

OVER FULL

ADDOIL

ADDOIL

V2500

OVER FULL

ADDOIL

ADDOIL

V2500

OVER FULL

ADDOIL

ADDOIL

V2500

OVER FULL

ADDOIL

ADDOIL

V2500

OVER FULL

ADDOIL

ADDOIL

V2500

N_AC_050409_1_0050201_01_00

Ground Service ConnectionsIDG Oil Tank -- IAE V2500 Series Engine

FIGURE-5-4-9-991-005-B01

5-4-9Page 9

Jun 01/12


**ON A/C A320-200

OIL OVERFLOWPOINT

SIGHT GLASS

EXTERNAL GEARBOX

OIL FILLING POINT

ADAPTER

B

A

B

THE STARTER IS FULL WHEN THE OIL LEVELSHOWS NOT LESS THAN 3/4 FULL

ON THE SIGHT GLASS

*

PNEUMATIC STARTERA

*

N_AC_050409_1_0060201_01_00

Ground Service ConnectionsStarter Oil Tank -- IAE V2500 Series Engine

FIGURE-5-4-9-991-006-B01

5-4-9Page 10

Jun 01/12


**ON A/C A320-200

FR80

Z316Z315

FR84

GRAVITYOIL FILLER

PRESSUREFILL PORT

OVERFLOWDRAIN VALVE

A

A

OIL LEVELSIGHT GLASS

N_AC_050409_1_0070101_01_00

Ground Service ConnectionsAPU Oil Tank

FIGURE-5-4-9-991-007-A01

5-4-9Page 11

Jun 01/12


5-4-10 Vacuum Toilet System

**ON A/C A320-200

Vacuum Toilet System

1. Vacuum Toilet System.


ACCESSAFT OF NOSE

m (ft) R SIDEm (ft)

L SIDEm (ft)


m (ft)

Waste WaterGround ServicePanel:Access door 172AR

31.3(102.69)

0.8(2.62)

2.8(9.18)


2. Technical Specifications

A. Connectors:- Draining: 4 in (ISO 17775).- Flushing and filling: 1 in (ISO 17775).

B. Usable waste tank capacity:- Standard configuration - on tank: 177 l (30.91 US gal).

C. Waste tank - Rinsing:- Operating pressure: 3.45 bar (50 psi).

D. Waste tank - Precharge:- 10 l (2.64 US gal).

5-4-10Page 1

Jun 01/12


**ON A/C A320-200

FILL AND RINSECONNECTION

TOILET DRAINCONNECTION

FR66 FR65

A

Z172

A

N_AC_050410_1_0010101_01_00

Ground Service ConnectionsWaste Water Ground Service Panel

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

5-4-10Page 2

Jun 01/12


5-5-0 Engine Starting Pneumatic Requirements

**ON A/C A320-200

Engine Starting Pneumatic Requirements

1. Engine Starting Pneumatic Requirements.To determinate the airflow required at ground connection, refer to the example given in FIGURE 5---0-99--003-A.

For engine starting pneumatic requirements for:- Low ambient temperatures, refer to 5-5-1,- Medium ambient temperatures, refer to 5-5-2,- High ambient temperatures, refer to 5-5-3.

5-5-0Page 1

Jun 01/12


**ON A/C A320-200

220°C200°C

150°C

100°C

50°C

0°C

230

3

4

40

50

60

5

6

70

80

90

AIR SUPPLY PRESSUREAT GROUND CONNECTIONPSIA ABSOLUTE BARS

AIR SUPPLY TEMPERATUREAT FUSELAGE CONNECTION

MIN. PRESSUREAT GROUND CONNECTION: 33 PSIG

RECOMMENDED PRESSURE:38 PSIG AT GROUNDCONNECTION

SEA LEVEL

Z = 8000 ft

40s

50s70s

35s

Z = 8000 ft

SEA LEVEL

Z = 8000 ft

MAXIMUM DUCT PRESSURE: 60 PSIG

ESTIMATED STARTINGTIMES UP TO IDLE

0.80 1.00 2.001.801.601.401.20 kg/s

48 60 8472 kg/min12010896

SEA LEVEL

MAXIM

UM T

EMPERATURE L

IMIT

AIR FLOW REQUIRED AT GROUND CONNECTION

N_AC_050500_1_0030101_01_00

EXAMPLE TO DETERMINATE THE AIRFLOW REQUIRED AT THE FUSELAGE CONNECTION:−FOR AN AIR START UNIT DELIVERING 60 PSIA (4.14 BARS) AIR PRESSURE AT THE

FUSELAGE CONNECTOR

1. DRAW AN HORIZONTAL LINE FROM THE SUPPLIED AIR PRESSURE (60 PSIA (4.14 BARS)).2. FROM THE INTERSECTION WITH THE AIR SUPPLY TEMPERATURE AT FUSELAGE

CONNECTION (220°C (428°F)), DRAW A VERTICAL LINE.3. THE INTERSECTION WITH THE HORIZONTAL AXIS GIVES THE REQUIRED AIRFLOW AT GROUND

CONNECTION (78 kg/min (1.3 kg/s)).

−AT A SUPPLIED AIR TEMPERATURE OF 220°C (428°F) AT THE FUSELAGE CONNECTOR

Engine Starting Pneumatic RequirementsFIGURE-5-5-0-991-003-A01

5-5-0Page 2

Jun 01/12


5-5-1 Low Ambient Temperatures

**ON A/C A320-200

Low Ambient Temperatures

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

5-5-1Page 1

Jun 01/12


**ON A/C A320-200

AIR SUPPLY PRESSUREAT GROUND CONNECTION

kg/mn

220°C200°C

150°C

100°C

50°C

MAXIM

UM T

EMPERATURE L

IMIT


PSIA ABSOLUTE BARS

35S

Z = 8000 ft

SEA LEVEL38 PSIG AT GROUNDRECOMMENDED PRESSURE:

30

40

50

60

70

80

90

2

3

4

5

6

48 60 72 84 96 108 120

0°C

Z = 8000 ft

SEA LEVEL

Z = 8000 ft

SEA LEVEL

CONNECTION

MIN. PRESSUREAT GROUND CONNECTION: 33 PSIG



40s

50s

70s


N_AC_050501_1_0050101_01_01

Engine Starting Pneumatic RequirementsLow Ambient Temperature -40˚C (-40˚F) -- CFM56 series engine

FIGURE-5-5-1-991-005-A01

5-5-1Page 2

Jun 01/12


**ON A/C A320-200

90

80

70

60

50

40

30 2

3

4

5

6

40 50 60 70 80 90 100 110 120


220°C

200°C

150°C

100°C

50°C

MAXIMUM T

EMPERATURE LIMIT

MAXIMUM DUCT PRESSURE


PSIA ABSOLUTE BARS

75s

70s

65s

60s

0°C

kg/mn



N_AC_050501_1_0060101_01_00

Engine Starting Pneumatic RequirementsLow Ambient Temperature -40˚C (-40˚F) -- IAE V2500 series engine

FIGURE-5-5-1-991-006-A01

5-5-1Page 3

Jun 01/12


5-5-2 Medium Ambient Temperatures

**ON A/C A320-200

Medium Ambient Temperatures

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

5-5-2Page 1

Jun 01/12


**ON A/C A320-200

kg/mn

220°C

200°C

150°C

100°C

50°C

35s

90

80

70

60

50

40

30


PSIA ABSOLUTE BARS

2

3

4

5

6

48 60 72 84 96 108 120

AT GROUND CONNECTION: 22 PSIGMIN. PRESSURE

Z = 8000 ft

SEA LEVEL

0°C

33 PSIG AT GROUND CONNECTIONRECOMMENDED PRESSURE:

Z = 8000 ft

SEA LEVELM

AXIMUM

TEM

PERATURE LIM

IT



TIMES UP TO IDLEESTIMATED STARTING

40s

50s

60s

70s

Z = 8000 ft


SEA LEVEL

N_AC_050502_1_0050101_01_01

Engine Starting Pneumatic RequirementsMedium Ambient Temperature +15˚C (+59˚F) -- CFM56 series engine

FIGURE-5-5-2-991-005-A01

5-5-2Page 2

Jun 01/12


**ON A/C A320-200


120 kg/mn

PSIA ABSOLUTE BARS

220°C200°C

150°C

100°C

50°C

0°C

60s

MAXIMUM T

EMPERATURE LIMIT



90

6

80

705

604

50

40

3

30 2

55s

50s

45s

40 50 60 70 80 90 100 110



N_AC_050502_1_0060101_01_00

Engine Starting Pneumatic RequirementsMedium Ambient Temperature +15˚C (+59˚F) -- IAE V2500 series engine

FIGURE-5-5-2-991-006-A01

5-5-2Page 3

Jun 01/12


5-5-3 High Ambient Temperatures

**ON A/C A320-200

High Ambient Temperatures

1. This section provides the engine starting pneumatic requirements for a temperature upper:- +50˚C (+122˚F) -- IAE V2500- +55˚C (+131˚F) -- CFM56

5-5-3Page 1

Jun 01/12


**ON A/C A320-200

30

40

50

60

70

80

906

5

4

3

2

48 60 72 84 96 108 120


kg/mn

220°C200°C

150°C

100°C

50°C

MAXIM

UM T

EMPERATURE L

IMIT

PSIA ABSOLUTE BARS

AT GROUND CONNECTION: 22 PSIGMIN. PRESSURE

33 PSIG AT GROUND CONNECTION



40s

50s

70s

Z = 8000 ft

SEA LEVEL

35s


SEA LEVEL

Z = 8000 ft


SEA LEVEL

Z = 8000 ft

N_AC_050503_1_0050101_01_00

RECOMMENDED PRESSURE:

60s

Engine Starting Pneumatic RequirementsHigh Ambient Temperature +55˚C (+131˚F) -- CFM56 series engine

FIGURE-5-5-3-991-005-A01

5-5-3Page 2

Jun 01/12


**ON A/C A320-200


120 kg/mn

PSIA ABSOLUTE BARS

220°C200°C

150°C

100°C

50°C

0°C

60s

MAXIMUM T

EMPERATURE LIMIT



90

6

80

705

604

50

40

3

30 2

55s

50s

45s

40 50 60 70 80 90 100 110



N_AC_050503_1_0060101_01_00

Engine Starting Pneumatic RequirementsHigh Ambient Temperature +50˚C (+122˚F) -- IAE V2500 series engine

FIGURE-5-5-3-991-006-A01

5-5-3Page 3

Jun 01/12


5-6-0 Ground Pneumatic Power Requirements

**ON A/C A320-200

Ground Pneumatic Power Requirements

1. Ground Pneumatic Power Requirements

NOTE : The air flow rates and temperature requirements given in sections 5.6 and 5.7 are given ataircraft connection.

5-6-0Page 1

Jun 01/12


5-6-1 Heating

**ON A/C A320-200

Heating

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

5-6-1Page 1

Jun 01/12


**ON A/C A320-200

TOTAL AIRFLOW

(kg/

s)

TOTAL AIRFLOW

CABIN AIRFLOW

1.29

8

1.21

1

1.12

5

1.03

8

0.95

2

0.86

5

0.77

9

0.69

2

0.51

9

0.60

6

0.43

3

1.5

1.2

1.0

0.5

3040

50

TIM

E T

O H

EA

T C

AB

IN T

O 2

1°C

(69

.8°

F)

ON

GR

OU

ND

TIM

E (

min

)

MA

X. A

LLO

WE

D T

OT

AL

AIR

FLO

W (

2 m

bar

CA

BIN

OV

ER

PR

ES

SU

RE

)

1.30

1.73

2.16

2.60

3.0

2.5

2.0

1.5

(lb/s

)

NO

RM

AL

AIR

FLO

W (

1 m

bar

CA

BIN

OV

ER

PR

ES

SU

RE

)

INIT

IAL

CA

BIN

TE

MP

ER

AT

UR

E A

T −

23°

C (

−9.

4°F

)T

EM

PE

RA

TU

RE

AT

GR

OU

ND

CO

NN

EC

TIO

N 7

0°C

(15

8°F

)E

MP

TY

CA

BIN

ELE

CT

RIC

AL

LOA

D =

310

0 W

RE

CIR

CU

LAT

ION

: ON

NO

OT

HE

R H

EA

T L

OA

D

CABIN AIRFLOW

N_AC_050601_1_0030101_01_01

Ground Pneumatic Power RequirementsHeating

FIGURE-5-6-1-991-003-A01

5-6-1Page 2

Jun 01/12


5-6-2 Cooling

**ON A/C A320-200

Cooling

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

5-6-2Page 1

Jun 01/12


**ON A/C A320-200

TOTAL AIRFLOW

(kg/

s)

TOTAL AIRFLOW

CABIN AIRFLOW

1.29

8

1.21

1

1.12

5

1.03

8

0.95

2

0.86

5

0.77

9

0.69

2

0.51

9

0.60

6

0.43

3

1.5

1.2

1.0

0.5

3040

50T

IME

(m

in)

1.30

1.73

2.16

2.60

3.0

2.5

2.0

1.5

(lb/s

)

NO

RM

AL

AIR

FLO

W (

1 m

bar

CA

BIN

OV

ER

PR

ES

SU

RE

)

CABIN AIRFLOW

MA

X. A

LLO

WE

D T

OT

AL

AIR

FLO

W (

2 m

bar

CA

BIN

OV

ER

PR

ES

SU

RE

)

INIT

IAL

CA

BIN

TE

MP

ER

AT

UR

E A

T −

23°

C (

−9.

4°F

)T

EM

PE

RA

TU

RE

AT

GR

OU

ND

CO

NN

EC

TIO

N 7

0°C

(15

8°F

)E

MP

TY

CA

BIN

ELE

CT

RIC

AL

LOA

D =

310

0 W

RE

CIR

CU

LAT

ION

: ON

NO

OT

HE

R H

EA

T L

OA

D

TIM

E T

O H

EA

T C

AB

IN T

O 2

1°C

(69

.8°

F)

ON

GR

OU

ND

N_AC_050602_1_0030101_01_01

Ground Pneumatic Power RequirementsCooling

FIGURE-5-6-2-991-003-A01

5-6-2Page 2

Jun 01/12


5-7-0 Preconditioned Airflow Requirements

**ON A/C A320-200

Preconditioned Airflow Requirements

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

A. Preconditioned Airflow Requirements.

FRESH AIRFLOW CURVE 1TOTAL CABIN T FL

(kg/s) (lb/s) (kg/s) (lb/s) (˚C) (˚F)

0.5 1.10 0.433 0.955 -42.7 -44.90.6 1.32 0.519 1.144 -31.1 -24.00.7 1.54 0.606 1.336 -22.7 -8.90.8 1.76 0.692 1.526 -16.5 2.30.9 1.98 0.779 1.717 -11.6 11.11.0 2.20 0.865 1.907 -7.7 18.11.1 2.43 0.952 2.099 -4.5 23.91.2 2.65 1.038 2.288 -1.9 28.61.3 2.87 1.125 2.480 0.4 32.71.4 3.09 1.211 2.670 2.3 36.11.5 3.31 1.298 2.862 4.0 39.2

NOTE : Data for stabilized conditions see 5-7-0.

B. Preconditioned Airflow Requirements.


(kg/s) (lb/s) (kg/s) (lb/s) (˚C) (˚F)

0.5 1.10 0.433 0.955 27.8 82.00.6 1.32 0.519 1.144 26.6 79.90.7 1.54 0.606 1.336 25.7 78.30.8 1.76 0.692 1.526 25.1 77.20.9 1.98 0.779 1.717 24.6 76.31.0 2.20 0.865 1.907 24.2 75.61.1 2.43 0.952 2.099 23.8 74.81.2 2.65 1.038 2.288 23.5 74.31.3 2.87 1.125 2.480 23.3 73.91.4 3.09 1.211 2.670 23.1 73.6

5-7-0Page 1

Jun 01/12



(kg/s) (lb/s) (kg/s) (lb/s) (˚C) (˚F)

1.5 3.31 1.298 2.862 22.9 73.2


C. Preconditioned Airflow Requirements.


(kg/s) (lb/s) (kg/s) (lb/s) (˚C) (˚F)

0.5 1.10 0.433 0.955 32.2 90.00.6 1.32 0.519 1.144 30.2 86.40.7 1.54 0.606 1.336 28.8 83.80.8 1.76 0.692 1.526 27.8 82.00.9 1.98 0.779 1.717 26.9 80.41.0 2.20 0.865 1.907 26.3 79.31.1 2.43 0.952 2.099 25.7 78.31.2 2.65 1.038 2.288 25.3 77.51.3 2.87 1.125 2.480 24.9 76.81.4 3.09 1.211 2.670 24.6 76.31.5 3.31 1.298 2.862 24.3 75.7


D. Preconditioned Airflow Requirements.


(kg/s) (lb/s) (kg/s) (lb/s) (˚C) (˚F)

0.5 1.10 0.433 0.955 38.9 102.00.6 1.32 0.519 1.144 35.8 96.40.7 1.54 0.606 1.336 33.6 92.50.8 1.76 0.692 1.526 31.9 89.40.9 1.98 0.779 1.717 30.6 87.11.0 2.20 0.865 1.907 29.6 85.31.1 2.43 0.952 2.099 28.7 83.71.2 2.65 1.038 2.288 28.0 82.41.3 2.87 1.125 2.480 27.4 81.31.4 3.09 1.211 2.670 26.9 80.4

5-7-0Page 2

Jun 01/12



(kg/s) (lb/s) (kg/s) (lb/s) (˚C) (˚F)

1.5 3.31 1.298 2.862 26.4 79.5


5-7-0Page 3

Jun 01/12


**ON A/C A320-200

TOTAL AIRFLOW(kg/

s)TOTAL AIRFLOW

CABIN AIRFLOW

1.29

8

1.21

1

1.12

5

1.03

8

0.95

2

0.86

5

0.77

9

0.69

2

0.51

9

0.60

61.

30

1.73

2.16

2.60

3.0

2.5

2.0

1.5

(lb/s

)

0.5

1.0

1.2

1.5

0.43

3

OA

T =

OU

TS

IDE

AIR

TE

MP

ER

AT

UR

E

−40

−30

−20

−10

010

2030

40

−40

−10

010

5010

0

OA

T =

−23

°C

(−

9.4°

F)

OA

T =

−30

°C

(−

22°

F)

OA

T =

−40

°C

(−

40°

F)

(°C

)IN

LET

FLO

WT

EM

PE

RA

TU

RE

(°F

)

NO

TE

:LP

GR

OU

ND

CO

NN

EC

TIO

N M

AX

IMU

M P

RE

SS

UR

E 4

0 m

b

MA

X A

LLO

WE

D T

OT

AL

AIR

FLO

W (

2 m

bar

CA

BIN

OV

ER

PR

ES

SU

RE

)

CABIN AIRFLOW

CU

RV

E 1

: CA

BIN

AT

27°

C (

80.6

°F

)16

4 P

AS

SE

NG

ER

S, 4

CA

BIN

AT

TE

ND

AN

TS

, 3 C

RE

W M

EM

BE

RS

BR

IGH

T D

AY

SO

LAR

LO

AD

: 385

0 W

ELE

CT

RIC

AL

LOA

D =

670

0 W

RE

CIR

CU

LAT

ION

: ON

OA

T (

OU

TS

IDE

AIR

TE

MP

ER

AT

UR

E)

= 3

8°C

(10

0.4°

F)

CU

RV

E 2

, 3, 4

CA

BIN

AT

21°

C (

69.8

°F

)

NO

OT

HE

R H

EA

T L

OA

D

ELE

CT

RIC

AL

LOA

D =

450

0 W

RE

CIR

CU

LAT

ION

: ON

NO

PA

SS

EN

GE

R O

R C

AB

INA

TT

EN

DA

NT

S

(1 m

bar

CA

BIN

OV

ER

PR

ES

SU

RE

)N

OR

MA

L A

IRF

LOW

N_AC_050700_1_0030101_01_01

Preconditioned Airflow RequirementsFIGURE-5-7-0-991-003-A01

5-7-0Page 4

Jun 01/12


5-8-0 Ground Towing Requirements

**ON A/C A320-200

Ground Towing Requirements

1. GeneralThis section provides information on aircraft towing.This aircraft is designed with means for conventional or towbarless towing.Information/procedures can be found for both in chapter 9 of the Aircraft Maintenance Manual.Status on towbarless towing equipment qualification can be found in SIL 09-002.It is possible to tow or push the aircraft, at maximum ramp weight with engines at zero or up to idlethrust, using a tow bar attached to the nose gear leg (refer to AMM chap 9 for conditions andlimitations).One tow bar fitting is installed at the front of the leg.The main landing gears have attachment points for towing or debogging (for details, refer to chapter07 of the Aircraft Recovery Manual).

A. The first part of this section shows the chart to determine the draw bar pull and tow tractormass requirements as function of the following physical characteristics:- Aircraft weight.- Number of engines at idle.- Slope.The chart is based on the engine type with the highest idle thrust level.

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

NOTE : Information on aircraft towing procedures and corresponding aircraft limitations aregiven in chapter 9 on the Aircraft Maintenance Manual.

The aircraft tow bar shall respect the following norms:- SAE AS1614 C, ”Main Line Aircraft Tow Bar Attach Fitting Interface”.- SAE ARP1915 D, ”Aircraft Tow Bar”.- ISO 8267-1, ”Aircraft - Tow bar attachment fitting - Interface requirements - Part 1: Main

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

bar”.A conventional type tow bar is required which should be equipped with a damping system toprotect the nose gear against jerks and with towing shear pins:- A traction shear pin calibrated at 9425 daN (21188 lbf).- A torsion pin calibrated at 826 m.daN (7311 lbf.in).The towing head is designed according to SAE AS1614 C (Aircraft Weight Category I).

5-8-0Page 1

Jun 01/12


**ON A/C A320-200

EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A320 AT 70 t, AT 1.5% SLOPE,1 ENGINE AT IDLE AND FOR WET TARMAC CONDITIONS:

− ON THE RIGHT HAND SIDE OF THE GRAPH, CHOOSE THE RELEVANT AIRCRAFT WEIGHT (70 t)− FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUIRED SLOPE PERCENTAGE (1.5%)− FROM THE POINT OBTAINED DRAW A STRAIGHT HORIZONTAL LINE UNTIL NO OF ENGINES AT IDLE = 2− 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 (5.8 t)− SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE. THE OBTAINED X−COORDINATE IS

THE RECOMMENDED MINIMUM TRACTOR WEIGHT (10.1 t)

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

10

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

5

0

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

75

455055606570

HA

RD

SN

OW

m =

0.2

ICE m = 0.05

10.15

1 ENGINE ON5.8

1.5% SLOPE70 tons

DR

Y C

ON

CR

ET

E m

= 0

.8

AT IDLE

WE

T C

ON

CR

ET

E m

= 0

.57

BREAKAWAY RESISTANCE 6%# OF ENGINES ON FOR PB: 1ENGINE THRUST 525 daN

N_AC_050800_1_0010301_01_03

Ground Towing RequirementsFIGURE-5-8-0-991-001-C01

5-8-0Page 2

Jun 01/12


5-9-0 De-Icing and External Cleaning

**ON A/C A320-200

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 13 m (42.65 ft).

2. De-Icing

Wing Top Surface(Both Sides)

Wingtip Devices(Both Inside andOutside Surfaces)

(Both Sides)

HTP Top Surface(Both Sides)

VTP(Both Sides)AIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2 m2 ft2

A320 99.7 1073.16 1.8 19.38 27 290.63 43 462.85A320 Sharklet 99.7 1073.16 9.6 103.33 27 290.63 43 462.85

Fuselage Top Surface(Top Third - 120˚ Arc)

Nacelle and Pylon(Top Third - 120˚ Arc)

(All Engines)Total De-Iced Area

AIRCRAFT TYPE

m2 ft2 m2 ft2 m2 ft2

A320 137.9 1484.34 23.6 254.03 333 3584A320 Sharklet 137.9 1484.34 23.6 254.03 341 3670

NOTE : Dimensions are approximate

3. External Cleaning

Wing TopSurface

(Both Sides)

Wing LowerSurface

(Including FlapTrack Fairing)(Both Sides)

Wingtip Devices(Both Inside and

OutsideSurfaces)

(Both Sides)

HTP TopSurface

(Both Sides)

HTP LowerSurface

(Both Sides)AIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2 m2 ft2 m2 ft2

A320 99.7 1073.16 103.4 1112.99 1.8 19.38 27 290.63 27 290.63A320 Sharklet 99.7 1073.16 103.4 1112.99 9.6 103.33 27 290.63 27 290.63

VTP(Both Sides)

Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned Area

AIRCRAFT TYPE


A320 43 462.85 421.2 4533.76 73.2 787.92 796 8568

5-9-0Page 1

Jun 01/12


VTP(Both Sides)

Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned Area

AIRCRAFT TYPE


A320 Sharklet 43 462.85 421.2 4533.76 73.2 787.92 804 8654

NOTE : Dimensions are approximate

5-9-0Page 2

Jun 01/12


OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

**ON A/C A320-200

Engine Exhaust Velocities and Temperatures

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

6-1-0Page 1

Jun 01/12


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

**ON A/C A320-200

Engine Exhaust Velocities Contours - Ground Idle Power

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

6-1-1Page 1

Jun 01/12


**ON A/C A320-200

ELE

VA

TIO

N

FE

ET

PLA

NA

IRP

LAN

E

V (

m/s

)

GR

OU

ND

PLA

NE

ME

TE

RS

4530

2520

1510

4530

2520

1510

40 30 20 10 0036912

mft

40 30 20 10 0036912

mft

N_AC_060101_1_0050101_01_00

050

100

150

200

250

300

350

400

015

3045

6075

9010

512

0

Engine Exhaust VelocitiesGround Idle Power -- CFM56 series engine

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

6-1-1Page 2

Jun 01/12


**ON A/C A320-200

ME

TE

RS

015

3045

60

250

300

ELE

VA

TIO

N

VE

LOC

ITY

= ft

/s (

m/s

)

FE

ET

050

100

150

200

7590

PLA

N

100

(30)

50 (15)

30 (9)

100

(30)

50 (15)

30 (9)

ftm

15 10 5 0

60 40 20 0

ftm

60

15 10 5 0

40 20 0

N_AC_060101_1_0060101_01_00

Engine Exhaust VelocitiesGround Idle Power -- IAE V2500 series engine

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

6-1-1Page 3

Jun 01/12


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

**ON A/C A320-200

Engine Exhaust Temperatures Contours - Ground Idle Power

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

6-1-2Page 1

Jun 01/12


**ON A/C A320-200

ELE

VA

TIO

N

FE

ET

PLA

NA

IRP

LAN

E

T (

°K

)

GR

OU

ND

PLA

NE

ME

TE

RS

400

350

300

325

40 30 20 10 0036912

mft

40 30 20 10 0036912

mft

40035

030

032

5

050

100

150

200

250

300

350

400

015

3045

6075

9010

512

0

N_AC_060102_1_0050101_01_00

Engine Exhaust TemperaturesGround Idle Power -- CFM56 series engine

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

6-1-2Page 2

Jun 01/12


**ON A/C A320-200

ME

TE

RS

015

3045

60

250

300

ELE

VA

TIO

N

TE

MP

ER

AT

UR

E =

°K

FE

ET

050

100

150

200

7590

PLA

N

32531

8 308

300

325

318

308

300

ftm

15 10 5 0

60 40 20 0

ftm

60

15 10 5 0

40 20 0

N_AC_060102_1_0060101_01_00

Engine Exhaust TemperaturesGround Idle Power -- IAE V2500 series engine

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

6-1-2Page 3

Jun 01/12


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

**ON A/C A320-200

Engine Exhaust Velocities Contours - Breakaway Power

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

6-1-3Page 1

Jun 01/12


**ON A/C A320-200

(38%

N1)

NO

TE

:−

add

+ 1

% N

1 pe

r +

15°

C (

27°

F)

AB

OV

E IS

A T

EM

PE

RA

TU

RE

CO

ND

ITIO

NS

− a

dd +

1%

N1

per

2000

ft

3000

lbs

OF

TH

RU

ST

V (

m/s

)

4020

15

ELE

VA

TIO

N

FE

ET

050

100

150

200

250

300

350

400

015

3045

6075

9010

512

0

PLA

NA

IRP

LAN

E

GR

OU

ND

PLA

NE

ME

TE

RS

4020

15

40 30 20 10 0036912

mft

40 30 20 10 0036912

mft

N_AC_060103_1_0030101_01_00

Engine Exhaust VelocitiesBreakaway Power -- CFM56 series engine

FIGURE-6-1-3-991-003-A01

6-1-3Page 2

Jun 01/12


**ON A/C A320-200

ME

TE

RS

015

3045

60

250

300

ELE

VA

TIO

N

VE

LOC

ITY

= ft

/s (

m/s

)

FE

ET

050

100

150

200

7590

PLA

N

100

(30)

50 (15)

30 (9)

100

(30)

50 (15)

30 (9)1.

05

1.04

1.03

050

0010

000

FN

= 3

000

lbf

ISA

/ O

MN

"V25

27A

5MD

V"

BA

SIS

RU

NW

AY

ALT

(ft)

FP

R

A32

0

ftm

15 10 5 0

60 40 20 0

ftm

60

15 10 5 0

40 20 0

N_AC_060103_1_0040101_01_00

Engine Exhaust VelocitiesBreakaway Power -- IAE V2500 series engine

FIGURE-6-1-3-991-004-A01

6-1-3Page 3

Jun 01/12


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

**ON A/C A320-200

Engine Exhaust Temperatures Contours - Breakaway Power

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

6-1-4Page 1

Jun 01/12


**ON A/C A320-200

ELE

VA

TIO

N

FE

ET

050

100

150

200

250

300

350

400

015

3045

6075

9010

512

0

PLA

NA

IRP

LAN

E

GR

OU

ND

PLA

NE

ME

TE

RS

400

350

300

325

400

350

300

325

3000

lbs

OF

TH

RU

ST

T (

°K

)

40 30 20 10 0036912

mft

40 30 20 10 0036912

mft

N_AC_060104_1_0030101_01_00

Engine Exhaust TemperaturesBreakaway Power -- CFM56 series engine

FIGURE-6-1-4-991-003-A01

6-1-4Page 2

Jun 01/12


**ON A/C A320-200

ME

TE

RS

015

3045

60

250

300

ELE

VA

TIO

N

TE

MP

ER

AT

UR

E =

°K

FE

ET

050

100

150

200

7590

PLA

N

325

318

308

300

325

318

308

300

ftm

60

15 10 5 0

40 20 0

ftm

60

15 10 5 0

40 20 0

N_AC_060104_1_0040101_01_00

Engine Exhaust TemperaturesBreakaway Power -- IAE V2500 series engine

FIGURE-6-1-4-991-004-A01

6-1-4Page 3

Jun 01/12


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

**ON A/C A320-200

Engine Exhaust Velocities Contours - Takeoff Power

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

6-1-5Page 1

Jun 01/12


**ON A/C A320-200

420

390

360

330

300

270

240

210

180

150

120

9060

3000

100

200

300

400

500

700

600

800

900

1000

1100

1200

1300

1400

ME

TE

RS

FE

ET

ftm

ftV

= 4

0 m

/sV

= 2

0 m

/sV

= 1

2 m

/s

V =

40

m/s

V =

20

m/s

V =

12

m/s

PLA

NA

IRP

LAN

E

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

TA

KE

OF

F P

OW

ER

INC

LUD

ES

(W

OR

ST

CA

SE

)G

RO

UN

D P

LAN

EH

EA

DW

IND

(20

KT

S.)

m

450

1500

42 36 30 24 18 12 6 0

140

120

100 80 60 40 200

42 36 30 24 18 12 6 0

140

120

100 80 60 40 200

N_AC_060105_1_0050101_01_00

Engine Exhaust VelocitiesTakeoff Power -- CFM56 series engine

FIGURE-6-1-5-991-005-A01

6-1-5Page 2

Jun 01/12


**ON A/C A320-200

ME

TE

RS

015

3045

60

250

300

ELE

VA

TIO

N

VE

LOC

ITY

= ft

/s (

m/s

)

FE

ET

050

100

150

200

7590

PLA

N

200

(60)

150

(45)

100

(30)

50 (15)

30 (9)

200

(60)

150

(45)

100

(30)

50 (15)

30 (9)

ftm

60

15 10 5 0

40 20 0

ftm

60

15 10 5 0

40 20 0

N_AC_060105_1_0060101_01_01

Engine Exhaust VelocitiesTakeoff Power -- IAE V2500 series engine

FIGURE-6-1-5-991-006-A01

6-1-5Page 3

Jun 01/12


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

**ON A/C A320-200

Engine Exhaust Temperatures Contours - Takeoff Power

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

6-1-6Page 1

Jun 01/12


**ON A/C A320-200

60 40 20 0

ftm

18 12 6 0E

LEV

AT

ION

GR

OU

ND

PLA

NE

2040

6080

100

120

140

160

TA

KE

OF

F P

OW

ER

INC

LUD

ES

(W

OR

ST

CA

SE

):G

RO

UN

D P

LAN

EH

EA

DW

IND

(20

KT

S.)

FE

ET

ME

TE

RS

0

PLA

N

T =

425

°K

T =

370

°K

T =

315

°K

T =

425

°K

T =

370

°K

T =

315

°K

AIR

PLA

NE

1020

3040

500

60 40 20 0

ftm

18 12 6 0

N_AC_060106_1_0050101_01_00

Engine Exhaust TemperaturesTakeoff Power -- CFM56 series engine

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

6-1-6Page 2

Jun 01/12


**ON A/C A320-200

ME

TE

RS

015

3045

60

250

300

ELE

VA

TIO

N

FE

ET

050

100

150

200

7590

PLA

N

400

350

325

318

400

350

325

318

300

300

ftm

15 10 5 0

60 40 20 0

ftm

15 10 5 0

60 40 20 0

N_AC_060106_1_0060101_01_00

Engine Exhaust TemperaturesTakeoff Power -- IAE V2500 series engine

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

6-1-6Page 3

Jun 01/12


6-2-0 Airport and Community Noise

**ON A/C A320-200

Airport and Community Noise

1. Airport and Community Noise Data

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

6-2-0Page 1

Jun 01/12


6-2-1 Noise Data

**ON A/C A320-200

Noise Data

1. Noise Data for CFM56-5A 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: 3˚C (37˚F)- Relative humidity: 66%- Atmospheric pressure: 1016 hPa- Wind speed: Negligible- No rain

2. Noise Data for CFM56-5B series engine





The meteorological parameters measured 1.6 m (5.25 ft) from the ground on the day of testwere as follows:- Temperature: 22˚C (72˚F)- Relative humidity: 42%- Atmospheric pressure: 1003 hPa- Wind speed: Negligible- No rain

3. Noise Data for IAE V2500 series engine


6-2-1Page 1

Jun 01/12





The meteorological parameters measured 1.6 m (5.25 ft) from the ground on the day of testwere as follows:- Temperature: 12˚C (54˚F)- Relative humidity: 62.5%- Atmospheric pressure: 1000 hPa- Wind speed: Negligible- No rain

6-2-1Page 2

Jun 01/12


**ON A/C A320-200

NOISE REFERENCEPOINT

112110108106104102100989694929088868482

150°

140°

130°

120°

110°

100°

90°

80°

70°

60°

50°

40°

30°

20°10°

0°350°

340°

330°

320°

310°

300°

290°

280°

270°

260°

250°

240°

230°

220°

210°

GROUND IDLE

N1

CURVE

MAX THRUST POSSIBLEON BRAKES

20.8% 90%

8078

N_AC_060201_1_0070101_01_00

Airport and Community NoiseCFM56-5A series engine

FIGURE-6-2-1-991-007-A01

6-2-1Page 3

Jun 01/12


**ON A/C A320-200


112110108106104102100989694929088868482

150°

140°

130°

120°

110°

100°

90°

80°

70°

60°

50°

40°

30°20°

10°0°

350°340°

330°

320°

310°

300°

290°

280°

270°

260°

250°

240°

230°

220°

210°

GROUND IDLE

N1

CURVE


18.9% 87%

7880

N_AC_060201_1_0080101_01_00

Airport and Community NoiseCFM56-5B series engine

FIGURE-6-2-1-991-008-A01

6-2-1Page 4

Jun 01/12


**ON A/C A320-200


1121101081061041021009896949290888684

150°

140°

130°

120°

110°

100°

90°

80°

70°

60°

50°

40°

30°20°

10°0°

350°340°

330°

320°

310°

300°

290°

280°

270°

260°

250°

240°

230°

220°

210°

GROUND IDLE

N2

CURVE


57.7% 92.5%

E.P.R 1.007 1.397

255°

225°

285°

315°

345°15°

45°

105°

135°

75°

78

8280

N_AC_060201_1_0090101_01_00

Airport and Community NoiseIAE V2500 series engine

FIGURE-6-2-1-991-009-A01

6-2-1Page 5

Jun 01/12


6-3-0 Danger Areas of Engines

**ON A/C A320-200

Danger Areas of Engines

1. Danger Areas of the Engines.

6-3-0Page 1

Jun 01/12


6-3-1 Ground Idle Power

**ON A/C A320-200

Ground Idle Power

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

6-3-1Page 1

Jun 01/12


**ON A/C A320-200

30°TO 55 m (180 ft) INCLUDES CROSS WIND EFFECT

EXHAUST WAKE DANGER AREA 65 MPH (105 km/h)OR GREATER

EXHAUST WAKE DANGER AREA 65 MPH (105 km/h)OR LESS

NO

EN

TR

Y 1

7 m

(55

ft) A

FT

OF

NO

ZZ

LE

(20 ft)

6.1 m

45°

1.5 m(5 ft)

(7.2 ft)R = 2.2 m

INTAKE SUCTION DANGER AREA

ENTRY CORRIDOR

N_AC_060301_1_0050101_01_01

Danger Areas of EnginesCFM56 series engine

FIGURE-6-3-1-991-005-A01

6-3-1Page 2

Jun 01/12


**ON A/C A320-200

0.75 m(2.5 ft)

R = 5.15 m(17 ft)

TO 59 m (195 ft) AFT COMMON NOZZLE ASSEMBLY (CNA)30°

INTAKE SUCTION DANGER AREAMINIMUM POWER

ENTRY CORRIDOR

EXHAUST DANGER AREA

N_AC_060301_1_0060101_01_00

Danger Areas of EnginesIAE V2500 series engine

FIGURE-6-3-1-991-006-A01

6-3-1Page 3

Jun 01/12


6-3-2 Takeoff Power

**ON A/C A320-200

Takeoff Power

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

6-3-2Page 1

Jun 01/12


**ON A/C A320-200

40°

30°

1.8 m(6 ft)

TO

275

m (

900

ft) A

FT

OF

FA

N N

OZ

ZLE

TO 150 m (500 ft) AFTOF FAN NOZZLE

R = 5.9 m(19.5 ft)

INLET SUCTION DANGER AREA

EXHAUST WAKE DANGERAREA 65 MPH (105 km/h)OR GREATER

EXHAUST WAKE DANGERAREA 65 MPH (105 km/h)OR LESS

N_AC_060302_1_0050101_01_01

Danger Areas of EnginesCFM56 series engine

FIGURE-6-3-2-991-005-A01

6-3-2Page 2

Jun 01/12


**ON A/C A320-200

1.5 m(5.5 ft)

R = 5.15 m(17 ft)

TO 348 m (1150 ft) AFT COMMON NOZZLE ASSEMBLY (CNA)

INTAKE SUCTION DANGER AREA

ENTRY CORRIDOR

EXHAUST DANGER AREA

30°

N_AC_060302_1_0060101_01_00

Danger Areas of EnginesIAE V2500 series engine

FIGURE-6-3-2-991-006-A01

6-3-2Page 3

Jun 01/12


6-4-0 APU Exhaust Velocities and Temperatures

**ON A/C A320-200

APU Exhaust Velocities and Temperatures

1. APU Exhaust Velocities and Temperatures.

6-4-0Page 1

Jun 01/12


6-4-1 APU

**ON A/C A320-200

APU - APIC & GARRETT

1. This section gives APU exhaust velocities and temperatures.

6-4-1Page 1

Jun 01/12


**ON A/C A320-200

0 PLAN 5 10 15 2520

0 16.404 32.808 49.212 65.616 82.02

0

0

FEET

0

5

ELEVATION

10

0

16.404

32.808

80°C176°F

100°C212°F

120°C248°F

150°C302°F

200°C392°F

300°C572°F

METERS

HEIGHT

m ft

FEET

METERS

45 m/s147 ft/s

30 m/s98 ft/s

20 m/s65 ft/s

10 m/s32 ft/s

5 m/s16 ft/s

5 10 15 20

16.404 32.808 49.212 65.616

N_AC_060401_1_0030101_01_00

Exhaust Velocities and TemperaturesAPU -- APIC & GARRETTFIGURE-6-4-1-991-003-A01

6-4-1Page 2

Jun 01/12


PAVEMENT DATA


**ON A/C A320-200

General Information

1. General Information

This brief description of the pavement charts that follow will help in their use for airport planning.

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

All curves on the charts represent data at a constant specified tire pressure with:- The airplane loaded to the maximum ramp weight.- The Center of Gravity (CG) at its maximum permissible aft position.

Pavement requirements for commercial airplanes are derived from the static analysis of loads imposedon the main landing gear struts.

The A/C codes are used for configuration management of chapter 07 only. There is no relationbetween these A/C codes and the ICAO A/C codes used for determining the airplane wing span andouter main gear wheel span as described in ICAO-Annex 14 Volume 1, Aerodrome Design andOperation Chapter 1.4, Table 1-1.

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

Section 7-3-0 shows maximum vertical and horizontal pavement loads for certain critical conditions atthe tire-ground interfaces.

Section 7-4-1 contain charts to find these loads throughout the stability limits of the airplane at reston the pavement.

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

Section 7-5-1 uses procedures in Instruction Report No S-77-1 ”Procedures for Development of CBRDesign Curves”, dated June 1977 and as modified according to the methods described in ICAOAerodrome Design Manual, Part 3. Pavements, 2nd Edition, 1983, Section 1.1 (The ACN-PCNMethod), and utilizing the alpha factors approved by ICAO in October 2007.

7-1-0Page 1

Jun 01/12


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 calculate Aircraft Classification Number (ACN).

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

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

that is shown on the graph.

Section 7-7-1 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 PortlandCement Association publications, ”Design of Concrete Airport Pavement”, 1973 and ”ComputerProgram for Airport Pavement Design”, (Program PDILB), 1967 both by Robert G. Packard.

The procedure that follows is used to develop rigid pavement design curves such as shown in Section7-7-1.- With the scale for pavement thickness to the left and the scale for allowable working stress to the

right, an arbitrary load line is drawn. This represents the main landing gear maximum weight tobe shown.

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

the basis of the curve for k = 300 already shown on the graph.

All Load Classification Number (LCN) curves shown in Section 7-6-1 and Section 7-8-2 have beendeveloped from a computer program based on data provided in International Civil AviationOrganisation (ICAO) document 7920-AN/865/2, Aerodrome Manual, Part 2, ”Aerodrome PhysicalCharacteristics”, Second Edition, 1965.

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

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

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

7-1-0Page 2

Jun 01/12


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

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

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

PCNPAVEMENT

TYPESUBGRADECATEGORY

TIRE PRESSURE CATEGORY EVALUATION METHOD

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

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

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

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

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

The four subgrade categories are:- A. High Strength CBR 15- B. Medium Strength CBR 10- C. Low Strength CBR 6- D. Ultra Low Strength CBR 3

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

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

7-1-0Page 3

Jun 01/12


**ON A/C A320-200

MODEL WVAIRCRAFT

CODE

A320−2XX

06 E

A320−2XX

05 F

A320−2XX

01 G

A320−2XX

02 H

A320−2XX

13 04 I

A320−2XX

08 00 14 J

A320−2XX

16 K

A320−2XX

03 09 L

A320−2XX

11 M

A320−2XX

10 07 N

A320−2XX

12 O

A320−2XX

15 P

A320−2XXBogie L/G

00 TT

NOTE: FOR WEIGHT VARIANT DEFINITION, REFER TO CHAPTER 02−01−01.

NOTE: THE A/C CODES ARE USED FOR CONFIGURATION MANAGEMENT OFCHAPTER 07 ONLY.THERE IS NO RELATION BETWEEN THESE A/C CODES AND THE ICAO A/C CODES USED FOR DETERMINING THE AIRPLANE WING SPAN ANDOUTER MAIN GEAR WHEEL SPAN AS DESCRIBED IN ICAO−ANNEX 14 VOLUME 1, AERODROME DESIGN AND OPERATION CHAPTER 1.4, TABLE 1−1.

N_AC_070100_1_0030101_01_01

A320−2XXA320−2XX

17 Q18 R

Aircraft CodesFIGURE-7-1-0-991-003-A01

7-1-0Page 4

Jun 01/12


7-2-0 Landing Gear Footprint

**ON A/C A320-200

Landing Gear Footprint

1. This section gives Landing Gear Footprint.

NOTE : For AC Code definition, refer to chapter 07-01-00.

7-2-0Page 1

Jun 01/12


**ON A/C A320-200

9.2 bar (133 psi)10.2 bar (148 psi)

49 x 19 − 2049 x 17 − 2046 x 17 R20

(46 x 16 − 20)

12.3 bar (178 psi)

927 mm(36.5 in)

500 mm(19.7 in)

12 640 mm(41 ft 5.6 in)

7 590 mm(24 ft 10.8 in)

A/C CODE

PERCENTAGE OF WEIGHT

ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE

NOSE GEAR TIRE PRESSURE

MAIN GEAR TIRE SIZE

MAIN GEAR TIRE PRESSURE

(30 x 8.8 − 15)

30 x 8.8 R15

11 bar (160 psi)

E

SEE SECTION 7−4−1

N_AC_070200_1_0100101_01_01

Landing Gear FootprintFIGURE-7-2-0-991-010-A01

7-2-0Page 2

Jun 01/12


**ON A/C A320-200

927 mm(36.5 in)

500 mm(19.7 in)

12 640 mm(41 ft 5.6 in)

7 590 mm(24 ft 10.8 in)

30 x 8.8 R15


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


11.4 bar (165 psi)

46 x 17 R20 49 x 19 − 2049 x 17 − 20

10.9 bar (158 psi)9.6 bar (139 psi)10.6 bar (154 psi)12.8 bar (186 psi)

A/C CODE F


1 270 x 455 R22

(49 x 18 − 22)

N_AC_070200_1_0270101_01_00


7-2-0Page 3

Jun 01/12


**ON A/C A320-200

927 mm(36.5 in)

500 mm(19.7 in)

12 640 mm(41 ft 5.6 in)

7 590 mm(24 ft 10.8 in)

(30 x 8.8 − 15)

30 x 8.8 R15


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


11.4 bar (165 psi)

(46 x 16 − 20)

46 x 17 R2049 x 17 − 20 49 x 19 − 20

(49 x 18 − 22)

1 270 x 455 R22


A/C CODE G


N_AC_070200_1_0110101_01_01


7-2-0Page 4

Jun 01/12


**ON A/C A320-200

927 mm(36.5 in)

500 mm(19.7 in)

12 640 mm(41 ft 5.6 in)

7 590 mm(24 ft 10.8 in)

(30 x 8.8 − 15)

30 x 8.8 R15


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


11.4 bar (165 psi)

(46 x 16 − 20)

46 x 17 R2049 x 17 − 20 49 x 19 − 20

(49 x 18 − 22)

1 270 x 455 R22


A/C CODE H


N_AC_070200_1_0120101_01_01


7-2-0Page 5

Jun 01/12


**ON A/C A320-200

N_AC_070200_1_0130101_01_02

927 mm(36.5 in)

500 mm(19.7 in)

12 640 mm(41 ft 5.6 in)

7 590 mm(24 ft 10.8 in)

(30 x 8.8 − 15)

30 x 8.8 R15NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


12.3 bar (178 psi)

(46 x 16 − 20)

46 x 17 R2049 x 17 − 20 49 x 19 − 20

(49 x 18 − 22)

1 270 x 455 R22


A/C CODE I − R

SEE SECTION 7−4−1PERCENTAGE OF WEIGHT

ON MAIN GEAR GROUP


7-2-0Page 6

Jun 01/12


**ON A/C A320-200

927 mm(36.5 in)

500 mm(19.7 in)

12 640 mm(41 ft 5.6 in)

7 590 mm(24 ft 10.8 in)

(30 x 8.8 − 15)

30 x 8.8 R15


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


12.3 bar (178 psi)

(46 x 16 − 20)

46 x 17 R2049 x 17 − 20 49 x 19 − 20

(49 x 18 − 22)

1 270 x 455 R22


A/C CODE J − K


N_AC_070200_1_0140101_01_01


7-2-0Page 7

Jun 01/12


**ON A/C A320-200

927 mm(36.5 in)

500 mm(19.7 in)

12 640 mm(41 ft 5.6 in)

7 590 mm(24 ft 10.8 in)

(30 x 8.8 − 15)

30 x 8.8 R15


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


12.3 bar (178 psi)

(46 x 16 − 20)

46 x 17 R2049 x 17 − 20 49 x 19 − 20

(49 x 18 − 22)

1 270 x 455 R22


A/C CODE L − M


N_AC_070200_1_0150101_01_01


7-2-0Page 8

Jun 01/12


**ON A/C A320-200

927 mm(36.5 in)

500 mm(19.7 in)

12 640 mm(41 ft 5.6 in)

7 590 mm(24 ft 10.8 in)

(30 x 8.8 − 15)

30 x 8.8 R15


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


12.3 bar (178 psi)

(46 x 16 − 20)

46 x 17 R2049 x 17 − 20 49 x 19 − 20

(49 x 18 − 22)

1 270 x 455 R22

10.7 bar (155 psi)12 bar (174 psi)12.3 bar (178 psi)14.4 bar (209 psi)

A/C CODE N − O


N_AC_070200_1_0160101_01_01


7-2-0Page 9

Jun 01/12


**ON A/C A320-200

N_AC_070200_1_0170101_01_02

927 mm(36.5 in)

500 mm(19.7 in)

12 640 mm(41 ft 5.6 in)

7 590 mm(24 ft 10.8 in)

(30 x 8.8 − 15)

30 x 8.8 R15


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


12.3 bar (178 psi)

(46 x 16 − 20)

46 x 17 R20

(49 x 18 − 22)

1 270 x 455 R22

12.3 bar (178 psi)14.4 bar (209 psi)

A/C CODE P − Q



7-2-0Page 10

Jun 01/12


**ON A/C A320-200

(30 x 8.8 − 15)

30 x 8.8 R15

12.3 bar (178 psi)

12.2 bar (177 psi)

(36 x 11 − 16)

915 x 300 R16


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


927 mm(36.5 in)

500 mm(19.7 in)

12 640 mm(41 ft 5.6 in)

7 590 mm(24 ft 10.8 in)

1005 mm(39.5 in)

A/C CODE TT


N_AC_070200_1_0180101_01_01


7-2-0Page 11

Jun 01/12


7-3-0 Maximum Pavement Loads

**ON A/C A320-200

Maximum Pavement Loads

1. This section gives Maximum Pavement Loads.

NOTE : For A/C code definition, refer to chapter 7-1-0.

7-3-0Page 1

Jun 01/12


**ON A/C A320-200

1

A/C

CO

DE

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

(1)

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GS

TA

TIC

BR

AK

ING

DE

CE

LER

AT

ION

@ 1

0 ft/

sS

TE

AD

Y B

RA

KIN

G

DE

CE

LER

AT

ION

@ 1

0 ft/

sA

T IN

ST

AN

TA

NE

OU

SB

RA

KIN

GC

OE

FF

ICIE

NT

= 0

.8

23

45

6H

(P

ER

ST

RU

T)

MA

XIM

UM

RA

MP

WE

IGH

T

lbkg

lbkg

lbkg

lbkg

lbkg

lbkg

GE66

400

68 4

00

VM

G (

PE

R S

TR

UT

)V

NG

146

375

150

800

20 3

75

20 9

75

9 24

0

9 51

0

32 2

75

33 2

2515

070

14 6

4069

550

71 6

50

31 5

40

32 5

00

22 7

50

23 4

25

10 3

20

10 6

30

55 6

25

57 3

00

25 2

30

26 0

00

22

(2)

V(N

G)

V(M

G)

H

V(N

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

V(M

G)

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

G

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

GH

(1)

NO

TE

:A

LL L

OA

DS

CA

LCU

LAT

ED

US

ING

AIR

PLA

NE

MA

XIM

UM

RA

MP

WE

IGH

T

FW

D C

G =

17

% M

AC

(2)

AF

T C

G =

43

% M

AC

N_AC_070300_1_0100101_01_01

A/C

CO

DE

E −

G

E −

G

Maximum Pavement LoadsFIGURE-7-3-0-991-010-A01

7-3-0Page 2

Jun 01/12


**ON A/C A320-200

1

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GS

TA

TIC

BR

AK

ING

DE

CE

LER

AT

ION

@ 1

0 ft/

sS

TE

AD

Y B

RA

KIN

G

DE

CE

LER

AT

ION

@ 1

0 ft/

sA

T IN

ST

AN

TA

NE

OU

SB

RA

KIN

GC

OE

FF

ICIE

NT

= 0

.8

23

45

6H

(P

ER

ST

RU

T)

MA

XIM

UM

RA

MP

WE

IGH

T

lbkg

lbkg

lbkg

lbkg

lbkg

lbkg

F67

400

VM

G (

PE

R S

TR

UT

)V

NG

148

600

20 6

759

370

32 7

5014

850

70 6

0032

020

23 1

0010

470

56 4

7525

620

V(N

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

V(M

G)

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

G

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

H

(1)

MR

W =

67

400

kg

NO

TE

:A

LL L

OA

DS

CA

LCU

LAT

ED

US

ING

AIR

PLA

NE

MA

XIM

UM

RA

MP

WE

IGH

T

FW

D C

G =

17

% M

AC

AT

A/C

WE

IGH

T =

67

400

kg

A/C

CO

DE

F

(2)

MR

W =

67

400

kgA

FT

CG

= 4

3 %

MA

C A

T A

/C W

EIG

HT

= 6

7 40

0 kg

F

N_AC_070300_1_0320101_01_00


7-3-0Page 3

Jun 01/12


**ON A/C A320-200

1

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

(1)

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GS

TA

TIC

BR

AK

ING

DE

CE

LER

AT

ION

@ 1

0 ft/

sS

TE

AD

Y B

RA

KIN

G

DE

CE

LER

AT

ION

@ 1

0 ft/

sA

T IN

ST

AN

TA

NE

OU

SB

RA

KIN

GC

OE

FF

ICIE

NT

= 0

.8

23

45

6H

(P

ER

ST

RU

T)

MA

XIM

UM

RA

MP

WE

IGH

T

lbkg

lbkg

lbkg

lbkg

lbkg

lbkg

I − RH

70 4

00

71 9

00

VM

G (

PE

R S

TR

UT

)V

NG

155

200

158

500

21 5

75

22 0

25

9 79

0

9 99

0

34 1

50

34 8

5015

810

15 4

9073

200

(2)

74 8

75 (

3)

33 2

00 (

2)

33 9

60 (

3)

24 1

25

24 6

25

10 9

40

11 1

70

58 5

50

59 9

00

26 5

60

27 1

70

22

V(N

G)

V(M

G)

H

A/C

CO

DE

V(N

G)

V(M

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

G

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

GH

(1) NO

TE

:A

LL L

OA

DS

CA

LCU

LAT

ED

US

ING

AIR

PLA

NE

MA

XIM

UM

RA

MP

WE

IGH

T.

FW

D C

G =

17

% M

AC

(2)

AF

T C

G =

41

% M

AC

AF

T C

G =

41.

42 %

MA

C(3

)

A/C

CO

DE

H −

I −

RH

I − R

N_AC_070300_1_0110101_01_02


7-3-0Page 4

Jun 01/12


**ON A/C A320-200

1

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

(1)

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GS

TA

TIC

BR

AK

ING

DE

CE

LER

AT

ION

@ 1

0 ft/

sS

TE

AD

Y B

RA

KIN

G

DE

CE

LER

AT

ION

@ 1

0 ft/

sA

T IN

ST

AN

TA

NE

OU

SB

RA

KIN

GC

OE

FF

ICIE

NT

= 0

.8

23

45

6H

(P

ER

ST

RU

T)

MA

XIM

UM

RA

MP

WE

IGH

T

lbkg

lbkg

lbkg

lbkg

lbkg

lbkg

L −

M

J −

K73

900

75 9

00

VM

G (

PE

R S

TR

UT

)V

NG

162

925

167

325

22 0

50

22 0

50

10 0

00

10 0

00

34 9

00

34 9

0015

830

15 8

3076

550

(2)

78 2

50 (

3)

34 7

20 (

2)

35 4

90 (

3)

25 3

25

26 0

00

11 4

80

11 8

00

61 2

50

62 6

00

27 7

80

28 3

90

V(N

G)

V(M

G)

H

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

G

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1) N

OT

E:

ALL

LO

AD

S C

ALC

ULA

TE

D U

SIN

G A

IRP

LAN

E M

AX

IMU

M R

AM

P W

EIG

HT

FW

D C

G =

17

% M

AC

AT

A/C

WE

IGH

T =

72

000

kg(2

)A

FT

CG

= 4

0 %

MA

CA

FT

CG

= 3

8.7

% M

AC

N_AC_070300_1_0120101_01_01

(3)

A/C

CO

DE

J −

K −

L −

MJ

− K

L −

M


7-3-0Page 5

Jun 01/12


**ON A/C A320-200

1

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

(1)

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GS

TA

TIC

BR

AK

ING

DE

CE

LER

AT

ION

@ 1

0 ft/

sS

TE

AD

Y B

RA

KIN

G

DE

CE

LER

AT

ION

@ 1

0 ft/

sA

T IN

ST

AN

TA

NE

OU

SB

RA

KIN

GC

OE

FF

ICIE

NT

= 0

.8

23

45

6H

(P

ER

ST

RU

T)

MA

XIM

UM

RA

MP

WE

IGH

T

lbkg

lbkg

lbkg

lbkg

lbkg

lbkg

P −

Q

N −

O77

400

78 4

00

VM

G (

PE

R S

TR

UT

)V

NG

170

650

172

850

22 0

50

22 0

50

10 0

00

10 0

00

34 9

00

34 9

0015

830

15 8

3079

450

(2)

80 2

50 (

3)

36 0

30 (

2)

36 4

00 (

3)

26 5

25

26 8

50

12 0

30

12 1

80

63 5

50

64 2

00

28 8

30

29 1

20

V(N

G)

V(M

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

G

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

22

V(N

G)

V(M

G)

H

A/C

CO

DE

H

(1)

NO

TE

:A

LL L

OA

DS

CA

LCU

LAT

ED

US

ING

AIR

PLA

NE

MA

XIM

UM

RA

MP

WE

IGH

T.

FW

D C

G =

17

% M

AC

AT

A/C

WE

IGH

T =

72

000

kg

(2)

AF

T C

G =

37.

5 %

MA

CA

FT

CG

= 3

6.8

% M

AC

(3)

A/C

CO

DE

N −

O −

P −

Q

N −

OP

− Q

N_AC_070300_1_0130101_01_02


7-3-0Page 6

Jun 01/12


**ON A/C A320-200

1

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GS

TA

TIC

BR

AK

ING

DE

CE

LER

AT

ION

@ 1

0 ft/

sS

TE

AD

Y B

RA

KIN

G

DE

CE

LER

AT

ION

@ 1

0 ft/

sA

T IN

ST

AN

TA

NE

OU

SB

RA

KIN

GC

OE

FF

ICIE

NT

= 0

.8

23

45

6H

(P

ER

ST

RU

T)

MA

XIM

UM

RA

MP

WE

IGH

T

lbkg

lbkg

lbkg

lbkg

lbkg

lbkg

TT

73 9

00

VM

G (

PE

R S

TR

UT

)V

NG

162

925

22 1

5010

050

35 0

0015

870

76 5

0034

700

25 3

2511

480

61 2

0027

760

V(N

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

V(M

G)

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

G

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

H

(1)

NO

TE

:A

LL L

OA

DS

CA

LCU

LAT

ED

US

ING

AIR

PLA

NE

MA

XIM

UM

RA

MP

WE

IGH

T

FW

D C

G =

17

% M

AC

AT

A/C

WE

IGH

T =

72

000

kg

(2)

AF

T C

G =

40

% M

AC

N_AC_070300_1_0140101_01_01

A/C

CO

DE

TT

TT


7-3-0Page 7

Jun 01/12



**ON A/C A320-200

Landing Gear Loading on Pavement

1. General

In the example shown in Section 7-4-1 Landing Gear Loading on Pavement, A/C Code E-F-G, theGross Aircraft Weight is 49 000 kg (108 025 lb) and the percentage of weight on the Main LandingGear is 94.95 %.

For these conditions the total weight on the MLG Group is 46 520 kg (102 575 lb).

7-4-0Page 1

Jun 01/12



**ON A/C A320-200

Landing Gear Loading on Pavement

1. This section gives Landing Gear Loading on Pavement.

NOTE : For A/C Code definition, refer to chapter 7-1-0.

7-4-1Page 1

Jun 01/12


**ON A/C A320-200

TAKE OFF & LANDING

TAKE OFF LANDING

MTOW = 66 000 kg

MTOW = 67 000 kg

MTOW = 68 000 kg

MLW = 64 500 kg

MZFW = 60 500 kg

35

40

45

50

55

60

65

70W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R −

(x

1 00

0 kg

)

82 84 86 88 90 92 94 96 98 100

PERCENTAGE OF WEIGHT ON MAIN GEAR

5 10 15 20 25 30 35 40 45 50 55

PERCENTAGE MAC

35

40

45

50

55

60

65

70

AIR

CR

AF

T G

RO

SS

WE

IGH

T−

(x

1 00

0 kg

)

CG FOR ACNCALCULATION

A/C CODE E − F − G

N_AC_070401_1_0110101_01_02

Landing Gear Loading on PavementFIGURE-7-4-1-991-011-A01

7-4-1Page 2

Jun 01/12


**ON A/C A320-200

35

40

45

50

55

60

65

70

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

82 84 86 88 90 92 94 96 98 100


35

40

45

50

55

60

65

70W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R −

(x

1 00

0 kg

)

5 10 15 20 25 30 35 40 45 50 55

PERCENTAGE MAC

MZFW = 60 500 kg

MLW = 64 500 kg

MTOW = 70 000 kg

TAKE OFF & LANDING

TAKE OFF LANDING


A/C CODE H

N_AC_070401_1_0120101_01_02


7-4-1Page 3

Jun 01/12


**ON A/C A320-200

5 10 15 20 25 30 35 40 45 50 55

PERCENTAGE MAC

35

40

45

50

55

60

65

75W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R −

(x

1 00

0 kg

)

35

40

45

50

55

60

70

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

82 84 86 88 90 92 94 96 98 100


TAKE OFF & LANDING

TAKE OFF LANDING

MZFW = 61 000 kg

MLW = 64 500 kg

MTOW = 71 500 kg

65

70


A/C CODE I

N_AC_070401_1_0130101_01_02

MZFW = 60 500 kg


7-4-1Page 4

Jun 01/12


**ON A/C A320-200

MZFW = 61 000 kg

MZFW = 61 500 kg

MLW = 64 500 kg

MTOW = 73 500 kg

5 10 15 20 25 30 35 40 45 50 55

PERCENTAGE MAC

TAKE OFF & LANDING

TAKE OFF LANDING

35

40

45

50

55

60

65

75W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R −

(x

1 00

0 kg

)

70

82 84 86 88 90 92 94 96 98 100


35

40

45

50

55

60

70

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

65

MZFW = 60 500 kg


A/C CODE J − TT

N_AC_070401_1_0140101_01_02


7-4-1Page 5

Jun 01/12


**ON A/C A320-200

5 10 15 20 25 30 35 40 45 50 55

PERCENTAGE MAC

35

40

45

50

55

60

70

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

65

35

40

45

50

55

60

65

75W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R −

(x

1 00

0 kg

)

70

82 84 86 88 90 92 94 96 98 100


TAKE OFF

MZFW = 62 500 kg

MTOW = 73 500 kg

MLW = 66 000 kg

TAKE OFF & LANDING

LANDING


A/C CODE K

N_AC_070401_1_0150101_01_02


7-4-1Page 6

Jun 01/12


**ON A/C A320-200

5 10 15 20 25 30 35 40 45 50 55

PERCENTAGE MAC

82 84 86 88 90 92 94 96 98 100


35

40

45

50

55

60

65

75W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R −

(x

1 00

0 kg

)

70

35

40

45

50

55

60

70

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)65

TAKE OFF & LANDING

TAKE OFFLANDING

MTOW = 75 500 kg

CG FOR ACNCALCULATIONS

MLW = 64 500 kg

MLW = 60 500 kg

MZFW = 61 000 kg

A/C CODE L

N_AC_070401_1_0160101_01_02


7-4-1Page 7

Jun 01/12


**ON A/C A320-200

82 84 86 88 90 92 94 96 98 100


35

40

45

50

55

60

70

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)65

35

40

45

50

55

60

65

75W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R −

(x

1 00

0 kg

)

70

5 10 15 20 25 30 35 40 45 50 55

PERCENTAGE MAC

TAKE OFF & LANDING

TAKE OFF LANDING

MZFW = 62 500 kg

MLW = 66 000 kg

MTOW = 75 500 kg


A/C CODE M

N_AC_070401_1_0170101_01_02


7-4-1Page 8

Jun 01/12


**ON A/C A320-200

35

40

45

50

55

60

65

70

75

80W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R −

(x

1 00

0 kg

)

35

40

45

50

55

60

65

70

75

80

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

TAKE OFF & LANDING

TAKE OFF LANDING


MLW = 64 500 kg

MTOW = 77 000 kg

82 84 86 88 90 92 94 96 98 100


5 10 15 20 25 30 35 40 45 50 55

PERCENTAGE MAC

A/C CODE N

MZFW = 61 000 kg

MZFW = 60 500 kg

N_AC_070401_1_0180101_01_02


7-4-1Page 9

Jun 01/12


**ON A/C A320-200

5 10 15 20 25 30 35 40 45 50 55

PERCENTAGE MAC

35

40

45

50

55

60

65

70

75

80

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

82 84 86 88 90 92 94 96 98 100


35

40

45

50

55

60

65

70

75

80W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R −

(x

1 00

0 kg

)

TAKE OFF & LANDING

TAKE OFFLANDING

MZFW = 62 500 kg

MLW = 66 000 kg

MTOW = 77 000 kg


A/C CODE O

N_AC_070401_1_0190101_01_02


7-4-1Page 10

Jun 01/12


**ON A/C A320-200

82 84 86 88 90 92 94 96 98 100


35

40

45

50

55

60

65

70

75

80W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R −

(x

1 00

0 kg

)

35

40

45

50

55

60

65

70

75

80

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

5 10 15 20 25 30 35 40 45 50 55

PERCENTAGE MAC

MTOW = 78 000 kg


MLW = 64 500 kg

MZFW = 61 000 kg

TAKE OFF & LANDING

TAKE OFFLANDING

A/C CODE P

N_AC_070401_1_0200101_01_02


7-4-1Page 11

Jun 01/12


**ON A/C A320-200

82 84 86 88 90 92 94 96 98 10035

40

45

50

55

60

65

70

75

80

35

40

45

50

55

60

65

70

75

805 10 15 20 25 30 35 40 45 50 55

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)


PERCENTAGE MAC

MTOW = 78 000 kg

A/C CODE Q

MLW = 66 000 kg

MZFW = 62 500 kg


TAKE OFFLANDING

TAKE OFFAND LANDING

N_AC_070401_1_0850101_01_00


7-4-1Page 12

Jun 01/12


**ON A/C A320-200

82 84 86 88 90 92 94 96 98 10035

40

45

50

55

60

65

70

75

35

40

45

50

55

60

65

70

755 10 15 20 25 30 35 40 45 50 55

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)


PERCENTAGE MAC

MTOW = 71 500 kg

A/C CODE R

MLW = 66 000 kg

MZFW = 62 500 kg


TAKE OFFLANDING

TAKE OFFAND LANDING

N_AC_070401_1_0860101_01_00


7-4-1Page 13

Jun 01/12



**ON A/C A320-200

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

1. General

In order to determine a particular Flexible Pavement Thickness, the Subgrade Strength (CBR), theAnnual Departure Level and the weight on one Main Landing Gear must be known.

In the example shown in Section 7-5-1 Flexible Pavement Requirements, A/C Code E (Main GearTire Size 46 x 17 R20 (46 x 16 - 20), inflated at 12.3 bar (178 psi)):- a CBR value of 10- an Annual Departure Level of 15 000- the Load on one MLG of 20 000 kg (44 100 lb).

For these conditions, the Flexible Pavement Thickness is 41.5 cm (16.3 in).

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

7-5-0Page 1

Jun 01/12



**ON A/C A320-200

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

1. This section gives Flexible Pavement Requirements.


7-5-1Page 1

Jun 01/12


**ON A/C A320-200

8060403020151063

[CENTIMETERS]

FLEXIBLE PAVEMENT THICKNESS

46 x 17 R20 TIRES

TIRE PRESSURE CONSTANT AT 12.3 bar (178 psi)

SUBGRADE STRENGTH − CBR

10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063

FOR ACN CALCULATIONS10 000 COVERAGES USED

A/C CODE E ALPHA FACTOR = 0.9

ANNUAL DEPARTURES*1 2003 0006 00015 00025 000*20 YEAR PAVEMENT LIFE

N_AC_070501_1_0720101_01_00

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)

WEIGHT ON ONE MAIN LANDING GEAR31 540 kg (69 550 lb)

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

Flexible Pavement RequirementsFIGURE-7-5-1-991-072-A01

7-5-1Page 2

Jun 01/12


**ON A/C A320-200

8060403020151063

[CENTIMETERS]


49 x 17−20 TIRES



10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063





N_AC_070501_1_0730101_01_00

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)



7-5-1Page 3

Jun 01/12


**ON A/C A320-200

8060403020151063

[CENTIMETERS]


49 x 19−20 TIRES



10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063



N_AC_070501_1_0740101_01_00


31 540 kg (69 550 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)

WEIGHT ON ONE MAIN LANDING GEAR



7-5-1Page 4

Jun 01/12


**ON A/C A320-200

8060403020151063

[CENTIMETERS]


46 x 17 R20 TIRES



10 15 20 30 40 60 80 100 120 150 180

[INCHES]

32 020 kg (70 600 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)

8060403020151063


A/C CODE F ALPHA FACTOR = 0.9




N_AC_070501_1_0750101_01_00


7-5-1Page 5

Jun 01/12


**ON A/C A320-200

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063



DEPARTURES*1 2003 0006 00015 00025 000*20 YEAR PAVEMENT LIFE


ANNUAL

32 020 kg (70 600 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)


[CENTIMETERS]


49 x 17−20 TIRES

TIRE PRESSURE CONSTANT AT 10.6 bar (154 psi)N_AC_070501_1_0760101_01_00


7-5-1Page 6

Jun 01/12


**ON A/C A320-200

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063





ANNUAL

32 020 kg (70 600 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)


[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES



7-5-1Page 7

Jun 01/12


**ON A/C A320-200

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063


ALPHA FACTOR = 0.9



ANNUAL

32 020 kg (70 600 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)


[CENTIMETERS]


49 x 19−20 TIRES


A/C CODE F


7-5-1Page 8

Jun 01/12


**ON A/C A320-200

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063


ALPHA FACTOR = 0.9



ANNUAL

32 500 kg (71 650 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)


[CENTIMETERS]


46 x 17 R20 TIRES


A/C CODE G


7-5-1Page 9

Jun 01/12


**ON A/C A320-200

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063


ALPHA FACTOR = 0.9



ANNUAL

32 500 kg (71 650 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)


[CENTIMETERS]


49 x 17−20 TIRES


A/C CODE G

N_AC_070501_1_0800101_01_00


7-5-1Page 10

Jun 01/12


**ON A/C A320-200

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063


ALPHA FACTOR = 0.9



ANNUAL

32 500 kg (71 650 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)


[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES


A/C CODE G

N_AC_070501_1_0810101_01_00


7-5-1Page 11

Jun 01/12


**ON A/C A320-200

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063


ALPHA FACTOR = 0.9



ANNUAL

32 500 kg (71 650 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)


[CENTIMETERS]


49 x 19−20 TIRES


A/C CODE G

N_AC_070501_1_0820101_01_00


7-5-1Page 12

Jun 01/12


**ON A/C A320-200

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063


ALPHA FACTOR = 0.9



ANNUAL

33 200 kg (73 200 lb)

25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)


[CENTIMETERS]


46 x 17 R20 TIRES


A/C CODE H

N_AC_070501_1_0830101_01_00


7-5-1Page 13

Jun 01/12


**ON A/C A320-200

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063


ALPHA FACTOR = 0.9



ANNUAL

[CENTIMETERS]


49 x 17−20 TIRES


A/C CODE H

N_AC_070501_1_0840101_01_00

33 200 kg (73 200 lb)

25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)



7-5-1Page 14

Jun 01/12


**ON A/C A320-200

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063


ALPHA FACTOR = 0.9



ANNUAL

[CENTIMETERS]


1 270 x 455 R 22 (49 x 18−22) TIRES


A/C CODE H

N_AC_070501_1_0850101_01_00

33 200 kg (73 200 lb)

25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)



7-5-1Page 15

Jun 01/12


**ON A/C A320-200

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

8060403020151063


ALPHA FACTOR = 0.9



ANNUAL

[CENTIMETERS]


49 x 19−20 TIRES


A/C CODE H

N_AC_070501_1_0860101_01_00

33 200 kg (73 200 lb)

25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)



7-5-1Page 16

Jun 01/12


**ON A/C A320-200




8060403020151063

8060403020151063

[CENTIMETERS]


46 x 17 R20 TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

ALPHA FACTOR = 0.9A/C CODE I − R

N_AC_070501_1_0870101_01_01


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

3 0006 00015 000

ANNUAL DEPARTURES*

*20 YEAR PAVEMENT LIFE25 000

1 200


7-5-1Page 17

Jun 01/12


**ON A/C A320-200




8060403020151063

8060403020151063

[CENTIMETERS]


49 x 17−20 TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

ALPHA FACTOR = 0.9

N_AC_070501_1_0880101_01_01

A/C CODE I − R


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

1 2003 0006 00015 000

ANNUAL DEPARTURES*



7-5-1Page 18

Jun 01/12


**ON A/C A320-200




8060403020151063

8060403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

ALPHA FACTOR = 0.9

1 2003 0006 00015 000

N_AC_070501_1_0890101_01_01

A/C CODE I − R

ANNUAL DEPARTURES*



25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)


7-5-1Page 19

Jun 01/12


**ON A/C A320-200




8060403020151063

8060403020151063

[CENTIMETERS]


49 x 19−20 TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

ALPHA FACTOR = 0.9

N_AC_070501_1_0900101_01_01

A/C CODE I − R

3 0006 00015 000

ANNUAL DEPARTURES*


1 200


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)


7-5-1Page 20

Jun 01/12


**ON A/C A320-200




8060403020151063

8060403020151063

[CENTIMETERS]


46 x 17 R20 TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

ALPHA FACTOR = 0.9


A/C CODE J−K


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

N_AC_070501_1_0910101_01_00


7-5-1Page 21

Jun 01/12


**ON A/C A320-200




8060403020151063

8060403020151063

[CENTIMETERS]


49 x 17−20 TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

ALPHA FACTOR = 0.9


A/C CODE J−K


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

N_AC_070501_1_0920101_01_00


7-5-1Page 22

Jun 01/12


**ON A/C A320-200




8060403020151063

8060403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

ALPHA FACTOR = 0.9


A/C CODE J−K


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

N_AC_070501_1_0930101_01_00

Flexible Pavement RequirementsFlexible Pavement Requirements

FIGURE-7-5-1-991-093-A01

7-5-1Page 23

Jun 01/12


**ON A/C A320-200




8060403020151063

8060403020151063

[CENTIMETERS]


49 x 19−20 TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

ALPHA FACTOR = 0.9


A/C CODE J−K


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

N_AC_070501_1_0940101_01_00


7-5-1Page 24

Jun 01/12


**ON A/C A320-200




8060403020151063

8060403020151063

[CENTIMETERS]


46 x 17 R20 TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

ALPHA FACTOR = 0.9


A/C CODE L−M


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

N_AC_070501_1_0950101_01_00


7-5-1Page 25

Jun 01/12


**ON A/C A320-200




8060403020151063

8060403020151063

[CENTIMETERS]


49 x 17−20 TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

ALPHA FACTOR = 0.9


A/C CODE L−M


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

N_AC_070501_1_0960101_01_00


7-5-1Page 26

Jun 01/12


**ON A/C A320-200




8060403020151063

8060403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

ALPHA FACTOR = 0.9


A/C CODE L−M


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

N_AC_070501_1_0970101_01_00


7-5-1Page 27

Jun 01/12


**ON A/C A320-200

10 15 20 30 40 60 80 100 120 150 180[CENTIMETERS]


49 x 19−20 TIRESTIRE PRESSURE CONSTANT AT 10.3 bar (149 psi)

[INCHES]



25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)


8060403020151063

8060403020151063

ALPHA FACTOR = 0.9A/C CODE L−M


N_AC_070501_1_0980101_01_00



7-5-1Page 28

Jun 01/12


**ON A/C A320-200

10 15 20 30 40 60 80 100 120 150 180[CENTIMETERS]


46 x 17 R20 TIRESTIRE PRESSURE CONSTANT AT 14.4 bar (209 psi)

[INCHES]



8060403020151063

8060403020151063



25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

ALPHA FACTOR = 0.9A/C CODE N−O


N_AC_070501_1_0990101_01_00


7-5-1Page 29

Jun 01/12


**ON A/C A320-200

10 15 20 30 40 60 80 100 120 150 180[CENTIMETERS]


49 x 17−20 TIRESTIRE PRESSURE CONSTANT AT 12 bar (174 psi)

[INCHES]



8060403020151063

8060403020151063



25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

ANNUAL DEPARTURES*

*20 YEAR PAVEMENT LIFE

1 2003 0006 00015 00025 000


N_AC_070501_1_1000101_01_00


7-5-1Page 30

Jun 01/12


**ON A/C A320-200

10 15 20 30 40 60 80 100 120 150 180[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRESTIRE PRESSURE CONSTANT AT 12.3 bar (178 psi)

[INCHES]



8060403020151063

8060403020151063

ANNUAL DEPARTURES*


1 2003 0006 00015 00025 000


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)



N_AC_070501_1_1010101_01_00


7-5-1Page 31

Jun 01/12


**ON A/C A320-200

10 15 20 30 40 60 80 100 120 150 180[CENTIMETERS]



[INCHES]



8060403020151063

8060403020151063


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

ANNUAL DEPARTURES*


1 2003 0006 00015 00025 000



N_AC_070501_1_1020101_01_00


7-5-1Page 32

Jun 01/12


**ON A/C A320-200

8060403020151063


8060403020151063

[CENTIMETERS]


46 x 17 R20 TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]



25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)


ALPHA FACTOR = 0.9


N_AC_070501_1_1030101_01_01

A/C CODE P − Q


7-5-1Page 33

Jun 01/12


**ON A/C A320-200

8060403020151063


8060403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES


10 15 20 30 40 60 80 100 120 150 180

[INCHES]



ALPHA FACTOR = 0.9A/C CODE P − Q

3 0006 00015 000


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

1 200

N_AC_070501_1_1050101_01_01

ANNUAL DEPARTURES*



7-5-1Page 34

Jun 01/12


**ON A/C A320-200

10 15 20 30 40 60 80 100 120 150 180(cm)


915 x 300 R16 (36 x 11−16) TIRESTIRE PRESSURE CONSTANT AT 12.2 bar (177 psi)

(in)



8060403020151063

8060403020151063

ALPHA FACTOR = 0.8

USED FOR ACN10 000 COVERAGES

CALCULATIONS

ANNUAL DEPARTURES*


1 2003 0006 00015 00025 000

N_AC_070501_1_1070101_01_01


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)

A/C CODE TT


7-5-1Page 35

Jun 01/12



**ON A/C A320-200

Flexible Pavement Requirements - LCN Conversion

1. General

In order to determine the airplane weight that can be accommodated on a particular FlexiblePavement, both the LCN of the pavement and the thickness (h) must be known.

In the example shown in Section 7-6-1 Flexible Pavement Requirements - LCN Conversion, A/C CodeE (Main Gear Tire Size 46 x 17 R20 (46 x 16 - 20), inflated at 12.3 bar (178 psi)) for:The thickness (h) is shown at 20 inches with an LCN of 53.

For these conditions, the weight on one Main Landing Gear is 25 000 kg (55 125 lb).

7-6-0Page 1

Jun 01/12



**ON A/C A320-200

Flexible Pavement Requirements - LCN Conversion

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


7-6-1Page 1

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.3

bar

(178

psi

)46

x 1

7 R

20 T

IRE

S

35 30 25 20 15 10 5 080

100

6050

4030

20

EQUIVALENT SINGLE WHEEL LOAD [1 000 kg]

10

EQUIVALENT SINGLE WHEEL LOAD [1 000 lb]

1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

WE

IGH

T O

N O

NE

MA

IN

31 5

40 k

g

(69

550

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

2 03

21

524

1 01

676

225

450

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

E

N_AC_070601_1_0750101_01_00

70

Flexible Pavement Requirements - LCN ConversionFIGURE-7-6-1-991-075-A01

7-6-1Page 2

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

WE

IGH

T O

N O

NE

MA

IN

31 5

40 k

g

(69

550

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

2 03

21

524

1 01

676

225

450

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

E

N_AC_070601_1_0760101_01_00

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.2

bar

(148

psi

)49

x 1

7−20

TIR

ES

70


7-6-1Page 3

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

WE

IGH

T O

N O

NE

MA

IN

31 5

40 k

g

(69

550

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

2 03

21

524

1 01

676

225

450

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

E

N_AC_070601_1_0770101_01_00

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 9

.2 b

ar (

133

psi)

49 x

19−

20 T

IRE

S

70


7-6-1Page 4

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

WE

IGH

T O

N O

NE

MA

IN

32 0

20 k

g

(70

600

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

2 03

21

524

1 01

676

225

450

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

F

46 x

17

R20

TIR

ES

N_AC_070601_1_0780101_01_00

70


7-6-1Page 5

Jun 01/12


**ON A/C A320-200

NO

TE

:E

QU

IVA

LEN

T S

ING

LE W

HE

EL

LOA

DS

AR

E D

ER

IVE

D B

Y M

ET

HO

DS

SH

OW

N IN

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3 S

econ

d E

ditio

n 19

65

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.6

bar

(154

psi

)49

x 1

7−20

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

F

2 03

21

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN

32 0

20 k

g

(70

600

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

70

N_AC_070601_1_0790101_01_00


7-6-1Page 6

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.9

bar

(158

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

F

2 03

21

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN

32 0

20 k

g

(70

600

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

70

N_AC_070601_1_0800101_01_00


7-6-1Page 7

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 9

.6 b

ar (

139

psi)

49 x

19−

20 T

IRE

S

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

F

2 03

21

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN

32 0

20 k

g

(70

600

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

70

N_AC_070601_1_0810101_01_00


7-6-1Page 8

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)46

x 1

7 R

20 T

IRE

S

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

G

2 03

21

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN

32 5

00 k

g

(71

650

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

70

N_AC_070601_1_0820101_01_00


7-6-1Page 9

Jun 01/12


**ON A/C A320-200

NO

TE

:E

QU

IVA

LEN

T S

ING

LE W

HE

EL

LOA

DS

AR

E D

ER

IVE

D B

Y M

ET

HO

DS

SH

OW

N IN

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3 S

econ

d E

ditio

n 19

65

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.6

bar

(154

psi

)49

x 1

7−20

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

G

2 03

21

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN

32 5

00 k

g

(71

650

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

70

N_AC_070601_1_0830101_01_00


7-6-1Page 10

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.9

bar

(158

psi

)1

270

x 45

5 R

22 (

19 x

18−

22)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

G

2 03

21

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN

32 5

00 k

g

(71

650

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

70

N_AC_070601_1_0840101_01_00


7-6-1Page 11

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 9

.6 b

ar (

139

psi)

49 x

19−

20 T

IRE

S

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

G

2 03

21

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN

32 5

00 k

g

(71

650

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

70

N_AC_070601_1_0850101_01_00


7-6-1Page 12

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)46

x 1

7 R

20 T

IRE

S

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

H

2 03

21

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN

33 2

00 k

g

(73

200

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

70

N_AC_070601_1_0860101_01_00


7-6-1Page 13

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.6

bar

(154

psi

)49

x 1

7−20

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

H

2 03

21

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN

33 2

00 k

g

(73

200

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

70

N_AC_070601_1_0870101_01_00


7-6-1Page 14

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.9

bar

(158

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

H

2 03

21

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN

33 2

00 k

g

(73

200

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

70

N_AC_070601_1_0880101_01_00


7-6-1Page 15

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 9

.6 b

ar (

139

psi)

49 x

19−

20 T

IRE

S

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

H

2 03

21

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN

33 2

00 k

g

(73

200

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

70

N_AC_070601_1_0890101_01_00


7-6-1Page 16

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.8

bar

(200

psi

)46

X 1

7 R

20 T

IRE

S

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)2

032

1 52

41

016

762

508

254

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

WE

IGH

T O

N O

NE

MA

IN

33 9

60 k

g

(74

875

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

70

N_AC_070601_1_0900101_01_01

A/C

CO

DE

I −

R


7-6-1Page 17

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.4

bar

(165

psi

)49

X 1

7−20

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)2

032

1 52

41

016

762

508

254

70

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

WE

IGH

T O

N O

NE

MA

IN

33 9

60 k

g

(74

875

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

A/C

CO

DE

I −

R

N_AC_070601_1_0910101_01_01


7-6-1Page 18

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.8

bar

(171

psi

)1

270

X 4

55 R

22 (

49 x

18−

22)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)2

032

1 52

41

016

762

508

254

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

WE

IGH

T O

N O

NE

MA

IN

33 9

60 k

g

(74

875

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

70

N_AC_070601_1_0920101_01_01

A/C

CO

DE

I −

R


7-6-1Page 19

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)2

032

1 52

41

016

762

508

254

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

WE

IGH

T O

N O

NE

MA

IN

33 9

60 k

g

(74

875

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

70

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.3

bar

(149

psi

)49

X 1

9−20

TIR

ES

A/C

CO

DE

I −

R

N_AC_070601_1_0930101_01_01


7-6-1Page 20

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.8

bar

(200

psi

)46

X 1

7 R

20 T

IRE

S

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)2

032

1 52

41

016

762

508

254

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

WE

IGH

T O

N O

NE

MA

IN

34 7

20 k

g

(76

550

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

A/C

CO

DE

J−

K

70

N_AC_070601_1_0940101_01_00


7-6-1Page 21

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.4

bar

(165

psi

)49

X 1

7−20

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)2

032

1 52

41

016

762

508

254

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

WE

IGH

T O

N O

NE

MA

IN

34 7

20 k

g

(76

550

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

A/C

CO

DE

J−

K

70

N_AC_070601_1_0950101_01_00


7-6-1Page 22

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.8

bar

(171

psi

)1

270

X 4

55 R

22 (

49 x

18−

22)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)2

032

1 52

41

016

762

508

254

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

WE

IGH

T O

N O

NE

MA

IN

34 7

20 k

g

(76

550

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

A/C

CO

DE

J−

K

70

N_AC_070601_1_0960101_01_00


7-6-1Page 23

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.3

bar

(149

psi

)49

X 1

9−20

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)2

032

1 52

41

016

762

508

254

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

WE

IGH

T O

N O

NE

MA

IN

34 7

20 k

g

(76

550

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

A/C

CO

DE

J−

K

70

N_AC_070601_1_0970101_01_00


7-6-1Page 24

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.8

bar

(200

psi

)46

X 1

7 R

20 T

IRE

S

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)2

032

1 52

41

016

762

508

254

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

WE

IGH

T O

N O

NE

MA

IN

35 4

90 k

g

(78

250

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

A/C

CO

DE

L−

M

70

N_AC_070601_1_0980101_01_00


7-6-1Page 25

Jun 01/12


**ON A/C A320-200

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.4

bar

(165

psi

)49

X 1

7−20

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)2

032

1 52

41

016

762

508

254

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

WE

IGH

T O

N O

NE

MA

IN

35 4

90 k

g

(78

250

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

A/C

CO

DE

L−

M

70

N_AC_070601_1_0990101_01_00


7-6-1Page 26

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.8

bar

(171

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

L−

M

2 03

21

524

1 01

6

70

WE

IGH

T O

N O

NE

MA

IN

35 4

90 k

g

(78

250

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

N_AC_070601_1_1000101_01_00


7-6-1Page 27

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.3

bar

(149

psi

)49

x 1

9−20

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

L−

M

2 03

21

524

1 01

6

70

WE

IGH

T O

N O

NE

MA

IN

35 4

90 k

g

(78

250

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

N_AC_070601_1_1010101_01_00


7-6-1Page 28

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.4

bar

(209

psi

)46

x 1

7 R

20 T

IRE

S

40 30 25 20 15 10 5 010

012

070

5040

3020


10


1020304050607090

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 03

21

524

1 01

6

80

35

60

80M

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

A/C

CO

DE

N−

O

WE

IGH

T O

N O

NE

MA

IN

36 0

30 k

g

(79

450

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

N_AC_070601_1_1020101_01_00


7-6-1Page 29

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2 ba

r (1

74 p

si)

49 x

17−

20 T

IRE

S

40 30 25 20 15 10 5 010

012

070

5040

3020


10


1020304050607090

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 03

21

524

1 01

6

80

35

60

80M

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

A/C

CO

DE

N−

O

WE

IGH

T O

N O

NE

MA

IN

36 0

30 k

g

(79

450

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

N_AC_070601_1_1030101_01_00


7-6-1Page 30

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.3

bar

(178

psi

)1

270

x 45

5 R

22

40 30 25 20 15 10 5 010

012

070

5040

3020


10


1020304050607090

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 03

21

524

1 01

6

80

35

60

80M

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

A/C

CO

DE

N−

O

WE

IGH

T O

N O

NE

MA

IN

36 0

30 k

g

(79

450

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

N_AC_070601_1_1040101_01_00


7-6-1Page 31

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.7

bar

(155

psi

)49

x 1

9−20

TIR

ES

40 30 25 20 15 10 5 010

012

070

5040

3020


10


1020304050607090

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 03

21

524

1 01

6

80

35

60

80M

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

A/C

CO

DE

N−

O

WE

IGH

T O

N O

NE

MA

IN

36 0

30 k

g

(79

450

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

N_AC_070601_1_1050101_01_00


7-6-1Page 32

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.4

bar

(209

psi

)46

x 1

7 R

20 T

IRE

S

40 30 25 20 15 10 5 010

012

070

5040

3020


10


1020304050607090

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 03

21

524

1 01

6

80

35

60

80M

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

TW

EIG

HT

ON

ON

E M

AIN

36 4

00 k

g

(80

250

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

N_AC_070601_1_1060101_01_01

A/C

CO

DE

P −

Q


7-6-1Page 33

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.3

bar

(178

psi

)1

270

x 45

5 R

22

40 30 25 20 15 10 5 010

012

070

5040

3020


10


1020304050607090

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 03

21

524

1 01

6

80

35

60

80M

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

TW

EIG

HT

ON

ON

E M

AIN

36 4

00 k

g

(80

250

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

N_AC_070601_1_1080101_01_01

A/C

CO

DE

P −

Q


7-6-1Page 34

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.2

bar

(177

psi

)91

5 x

300

R16

(36

x 1

1−16

)

10 5 080

120

6050

4030

20


10


10203040506070

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 03

21

524

1 01

6

70

15202530354045505560M

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

A/C

CO

DE

TT

WE

IGH

T O

N O

NE

MA

IN

34 7

00 k

g

(76

500

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

100

N_AC_070601_1_1100101_01_00


7-6-1Page 35

Jun 01/12



**ON A/C A320-200

Rigid Pavement Requirements - Portland Cement Association Design Method

1. GeneralIn order to determine a Rigid Pavement Thickness, the Subgrade Modulus (k), the allowable workingstress and the weight on one Main Landing Gear must be known.

In the example shown in Section 7-7-1 Rigid Pavement Requirements (PCA), A/C Code E (MainGear Tire Size 46 x 17 R20 (46 x 16 - 20), inflated at 12.3 bar (178 psi)) for:- a ”k” value of 80 MN/m3 (300 lb/in3)- an allowable working stress of 32 kg/cm2 (450 lb/in2)- a load on one MLG of 25 000 kg (55 125 lb).

For these conditions, the Rigid Pavement Thickness is 23 cm (9.1 in).

7-7-0Page 1

Jun 01/12



**ON A/C A320-200

Rigid Pavement Requirements - Portland Cement Association Design Method

1. This section gives Rigid Pavement Requirements.


7-7-1Page 1

Jun 01/12


**ON A/C A320-200

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

SLIGHTLY FOR ANY OTHER

THE CURVES ARE EXACT FORK = 80 MN/m³ BUT DEVIATE

VALUES OF K

REFERENCE:

AIRPORT PAVEMENTS" AND "COMPUTER PROGRAM FOR AIRPORT PAVEMENT DESIGN − PROGRAM PDILB" PORTLAND CEMENT ASSOCIATION

"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

31 540 kg (69 550 lb)

A/C CODE E

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

N_AC_070701_1_0720101_01_00

Rigid Pavement Requirements (PCA)FIGURE-7-7-1-991-072-A01

7-7-1Page 2

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

31 540 kg (69 550 lb)

A/C CODE E

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

N_AC_070701_1_0730101_01_00


7-7-1Page 3

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

31 540 kg (69 550 lb)

A/C CODE E

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


N_AC_070701_1_0740101_01_00


7-7-1Page 4

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

32 010 kg (70 550 lb)

A/C CODE F

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


N_AC_070701_1_0750101_01_00


7-7-1Page 5

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


20 000 kg (44 100 lb)15 000 kg (33 075 lb)

25 000 kg (55 125 lb)32 010 kg (70 550 lb)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

N_AC_070701_1_0760101_01_00

A/C CODE F


7-7-1Page 6

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


20 000 kg (44 100 lb)15 000 kg (33 075 lb)

25 000 kg (55 125 lb)32 010 kg (70 550 lb)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

A/C CODE F

N_AC_070701_1_0770101_01_00


7-7-1Page 7

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


20 000 kg (44 100 lb)15 000 kg (33 075 lb)

25 000 kg (55 125 lb)32 010 kg (70 550 lb)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

A/C CODE F

N_AC_070701_1_0780101_01_00


7-7-1Page 8

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


20 000 kg (44 100 lb)15 000 kg (33 075 lb)

25 000 kg (55 125 lb)32 500 kg (71 650 lb)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

A/C CODE G

N_AC_070701_1_0790101_01_00


7-7-1Page 9

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


20 000 kg (44 100 lb)15 000 kg (33 075 lb)

25 000 kg (55 125 lb)32 500 kg (71 650 lb)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

A/C CODE G

N_AC_070701_1_0800101_01_00


7-7-1Page 10

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


20 000 kg (44 100 lb)15 000 kg (33 075 lb)

25 000 kg (55 125 lb)32 500 kg (71 650 lb)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

A/C CODE G


N_AC_070701_1_0810101_01_00


7-7-1Page 11

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


20 000 kg (44 100 lb)15 000 kg (33 075 lb)

25 000 kg (55 125 lb)32 500 kg (71 650 lb)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

A/C CODE G


N_AC_070701_1_0820101_01_00


7-7-1Page 12

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)33 200 kg (73 200 lb)

A/C CODE H


N_AC_070701_1_0830101_01_00


7-7-1Page 13

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)33 200 kg (73 200 lb)

A/C CODE H


N_AC_070701_1_0840101_01_00


7-7-1Page 14

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)33 200 kg (73 200 lb)

A/C CODE H

N_AC_070701_1_0850101_01_00



7-7-1Page 15

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)33 200 kg (73 200 lb)

A/C CODE H


N_AC_070701_1_0860101_01_00


7-7-1Page 16

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)33 960 kg (74 875 lb)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


100

55

61

N_AC_070701_1_0870101_01_01

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


A/C CODE I − R


7-7-1Page 17

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)33 960 kg (74 875 lb)

N_AC_070701_1_0880101_01_01

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


A/C CODE I − R


7-7-1Page 18

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)33 960 kg (74 875 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


A/C CODE I − R

N_AC_070701_1_0890101_01_01


7-7-1Page 19

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)33 960 kg (74 875 lb)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

A/C CODE I − R

N_AC_070701_1_0900101_01_01


7-7-1Page 20

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


100

55

61

N_AC_070701_1_0910101_01_00


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)34 720 kg (76 550 lb)

A/C CODE J−K

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³



7-7-1Page 21

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)34 720 kg (76 550 lb)

A/C CODE J−K

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


N_AC_070701_1_0920101_01_00


7-7-1Page 22

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


100

55

61

N_AC_070701_1_0930101_01_00


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)34 720 kg (76 550 lb)

A/C CODE J−K

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³



7-7-1Page 23

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)34 720 kg (76 550 lb)

A/C CODE J−K

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

N_AC_070701_1_0940101_01_00


7-7-1Page 24

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)35 490 kg (78 250 lb)

A/C CODE L−M

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


100

55

61

N_AC_070701_1_0950101_01_00


7-7-1Page 25

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


100

55

61

N_AC_070701_1_0960101_01_00


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)35 490 kg (78 250 lb)

A/C CODE L−M

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³



7-7-1Page 26

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)35 490 kg (78 250 lb)

A/C CODE L−M

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


N_AC_070701_1_0980101_01_00


7-7-1Page 27

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)35 490 kg (78 250 lb)



N_AC_070701_1_0990101_01_00

A/C CODE L−M


7-7-1Page 28

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)36 030 kg (79 450 lb)



N_AC_070701_1_1000101_01_00

A/C CODE N−O


7-7-1Page 29

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)36 030 kg (79 450 lb)

A/C CODE N−O


N_AC_070701_1_1010101_01_00

49 x 17−20 TIRESTIRE PRESSURE CONSTANT AT 12 bar (174 psi)


7-7-1Page 30

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)36 030 kg (79 450 lb)



N_AC_070701_1_1020101_01_00

A/C CODE N−O


7-7-1Page 31

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)36 030 kg (79 450 lb)



N_AC_070701_1_1030101_01_00

A/C CODE N−O


7-7-1Page 32

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)36 400 kg (80 250 lb)



K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

A/C CODE P − Q

N_AC_070701_1_1040101_01_01


7-7-1Page 33

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

33

31

29

27

25

23

21

19

17200

300

400

500

600

700

800

900

49

43

37

31

25

19

13

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

100

55

61


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)36 400 kg (80 250 lb)


A/C CODE P − Q

N_AC_070701_1_1060101_01_01


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


7-7-1Page 34

Jun 01/12


**ON A/C A320-200




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

7

8

9

10

11

12

13

1436

34

32

30

28

26

24

22

20

200

300

400

500

600

700

800

900

56

50

44

38

32

26

20

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

915 x 300 R16 (36 x 11−16)TIRE PRESSURE CONSTANT AT 12.2 bar (177 psi)


62

68

N_AC_070701_1_1080101_01_00

15 1 000


25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)

30 000 kg (66 150 lb)34 700 kg (76 500 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

A/C CODE TT


7-7-1Page 35

Jun 01/12



**ON A/C A320-200

Radius of Relative Stiffness

1. This section gives Radius of Relative Stiffness.

7-8-1Page 1

Jun 01/12


**ON A/C A320-200

d6.06.57.07.5

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

8.08.59.09.5

10.010.511.011.512.012.513.013.514.014.515.015.516.016.517.017.518.019.020.021.022.023.024.025.0

31.4833.4335.3437.2239.0640.8842.6744.4346.1847.9049.6051.2852.9454.5956.2257.8359.4361.0262.5964.1565.6967.2368.7570.2671.7674.7377.6680.5583.4186.2489.0491.81

29.3031.1132.8934.6336.3538.0439.7141.3542.9744.5746.1647.7249.2750.8052.3253.8255.3156.7858.2559.7061.1362.5663.9865.3866.7869.5472.2774.9677.6380.2682.8685.44

26.4728.1129.7231.2932.8534.3735.8837.3638.8340.2841.7143.1244.5245.9047.2748.6349.9851.3152.6353.9455.2456.5357.8159.0860.3462.8465.3067.7470.1472.5274.8777.20

24.6326.1627.6529.1230.5731.9933.3934.7736.1437.4838.8140.1341.4342.7243.9945.2646.5147.7548.9850.2051.4152.6153.8054.9856.1558.4860.7763.0465.2867.4969.6871.84

23.3024.7426.1527.5428.9130.2531.5832.8934.1735.4536.7137.9539.1840.4041.6142.8043.9845.1646.3247.4748.6249.7550.8852.0053.1155.3157.4759.6261.7363.8365.9067.95

22.2623.6424.9926.3227.6228.9130.1731.4232.6533.8735.0736.2637.4438.6039.7540.8942.0243.1544.2645.3646.4547.5448.6149.6850.7452.8454.9156.9658.9860.9862.9664.92

21.4222.7424.0425.3226.5827.8129.0330.2331.4232.5933.7534.8936.0237.1438.2539.3540.4441.5142.5843.6444.7045.7446.7747.8048.8250.8452.8454.8156.7558.6860.5862.46

20.7222.0023.2524.4925.7026.9028.0829.2430.3931.5232.6433.7434.8435.9236.9938.0639.1140.1541.1942.2143.2344.2445.2446.2347.2249.1751.1053.0154.8956.7558.5960.41

19.1320.3121.4722.6123.7424.8425.9327.0028.0629.1130.1432.1632.1733.1734.1635.1436.1237.0838.0338.9839.9240.8541.7842.7043.6145.4147.1948.9550.6952.4154.1155.79

L = Ed

= 24.1652dk

RADIUS OF RELATIVE STIFFNESS (L)VALUES IN INCHES

43 3

4

12 (1 − ) k2

N_AC_070801_1_0030101_01_01

E = YOUNG’S MODULUS = 4 x 10 psi

k = SUBGRADE MODULUS, lb/in

d = RIGID PAVEMENT THICKNESS, (in)

= POISSON’S RATIO = 0.15

WHERE6

3

Radius of Relative Stiffness(Reference: Portland Cement Association)

FIGURE-7-8-1-991-003-A01

7-8-1Page 2

Jun 01/12


7-8-2 Rigid Pavement Requirements - LCN Conversion

**ON A/C A320-200

Rigid Pavement Requirements - LCN Conversion

1. GeneralIn order to determine the airplane weight that can be accommodated on a particular Rigid Pavement,both the LCN of the pavement and the Radius of Relative Stiffness (L) must be known.

In the example shown in this section Rigid Pavement Requirements - LCN Conversion, A/C Code E(Main Gear Tire Size 46 x 17 R20 (46 x 16 - 20), inflated at 12.3 bar (178 psi)) for:- The Radius of Relative Stiffness is shown at 762 mm (30 in) with an LCN of 57.

For these conditions, the weight on one Main Landing Gear is 25 000 kg (55 125 lb).


7-8-2Page 1

Jun 01/12


**ON A/C A320-200

N_AC_070802_1_0750101_01_01

508

762

1 01

61

270

1 52

42

540

2 03

2

6080

5040

3020

10051015202530

2030

4050

100

9080

7060

010203040506070

70


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)


46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.3

bar

(178

psi

)F

LEX

IBLE

PA

VE

ME

NT

TH

ICK

NE

SS

(m

m)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R31

540

kg

(6

9 55

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)10

000

kg

(2

2 05

0 lb

)

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T M

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

A/C

CO

DE

E

Rigid Pavement Requirements - LCN ConversionFIGURE-7-8-2-991-075-A01

7-8-2Page 2

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.2

bar

(148

psi

)49

x 1

7−20

TIR

ES

5 080

6050

4030

20


10


10203040506070

9080

7060

5040

20030

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

1015202530

A/C

CO

DE

E

100

WE

IGH

T O

N O

NE

MA

IN

31 5

40 k

g

(69

550

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

762

2 54

01

270

1 01

61

524

2 03

2

N_AC_070802_1_0760101_01_00

508

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 3

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 9

.2 b

ar (

133

psi)

49 x

19−

20 T

IRE

S

5 070

5040

3020


10


10203040506070

9080

7060

5040

20030

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

1015202530

A/C

CO

DE

E

100

WE

IGH

T O

N O

NE

MA

IN

31 5

40 k

g

(69

550

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

762

2 54

01

270

1 01

61

524

2 03

250

8

N_AC_070802_1_0770101_01_00

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 4

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)46

x 1

7 R

20 T

IRE

S

5 080

6050

4030

20


10


10203040506070

9080

7060

5040

20030

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

1015202530

A/C

CO

DE

F

100

WE

IGH

T O

N O

NE

MA

IN

32 0

20 k

g

(70

600

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

762

2 54

01

270

1 01

61

524

2 03

250

8

N_AC_070802_1_0780101_01_00

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 5

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.6

bar

(154

psi

)49

x 1

7−20

TIR

ES

5 080

6050

4030

20


10


10203040506070

9080

7060

5040

200

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

30762

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 54

01

270

1 01

6

1015202530

A/C

CO

DE

F

100

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

1 52

42

032

WE

IGH

T O

N O

NE

MA

IN

32 0

20 k

g

(70

600

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

N_AC_070802_1_0790101_01_00


7-8-2Page 6

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.9

bar

(158

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

5 080

6050

4030

20


10


10203040506070

9080

7060

5040

2003076

250

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 54

01

270

1 01

6

1015202530

A/C

CO

DE

F

100

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

1 52

42

032

WE

IGH

T O

N O

NE

MA

IN

32 0

20 k

g

(70

600

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

N_AC_070802_1_0800101_01_00

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 7

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 9

.6 b

ar (

139

psi)

49 x

19−

20 T

IRE

S

5 080

6050

4030

20


10


10203040506070

9080

7060

5040

2003076

250

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 54

01

270

1 01

6

1015202530

A/C

CO

DE

F

100

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

1 52

42

032

WE

IGH

T O

N O

NE

MA

IN

32 0

20 k

g

(70

600

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

N_AC_070802_1_0810101_01_00

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 8

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)46

x 1

7 R

20 T

IRE

S

5 080

6050

4030

20


10


10203040506070

9080

7060

5040

2003076

250

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 54

01

270

1 01

6

1015202530

A/C

CO

DE

G

100

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

1 52

42

032

WE

IGH

T O

N O

NE

MA

IN

32 5

00 k

g

(71

650

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

N_AC_070802_1_0820101_01_00

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 9

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.6

bar

(154

psi

)49

x 1

7−20

TIR

ES

5 080

6050

4030

20


10


10203040506070

9080

7060

5040

2003076

250

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 54

01

270

1 01

6

1015202530

A/C

CO

DE

G

100

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

1 52

42

032

WE

IGH

T O

N O

NE

MA

IN

32 5

00 k

g

(71

650

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

N_AC_070802_1_0830101_01_00

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 10

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.9

bar

(158

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

5 080

6050

4030

20


10


10203040506070

9080

7060

5040

2003076

250

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 54

01

270

1 01

6

1015202530

A/C

CO

DE

G

100

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

1 52

42

032

WE

IGH

T O

N O

NE

MA

IN

32 5

00 k

g

(71

650

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

N_AC_070802_1_0840101_01_00

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 11

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 9

.6 b

ar (

139

psi)

49 x

19−

20 T

IRE

S

5 080

6050

4030

20


10


10203040506070

9080

7060

5040

2003076

250

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 54

01

270

1 01

6

1015202530

A/C

CO

DE

G

100

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

1 52

42

032

N_AC_070802_1_0850101_01_00

WE

IGH

T O

N O

NE

MA

IN

32 5

00 k

g

(71

650

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 12

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)46

x 1

7 R

20 T

IRE

S

5 080

6050

4030

20


10


10203040506080

9080

7060

5040

2003076

250

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 54

01

270

1 01

6

1015202535

100

1 52

42

032

7030

A/C

CO

DE

H

WE

IGH

T O

N O

NE

MA

IN

33 2

00 k

g

(73

200

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

LAN

DIN

G G

EA

R

15 0

00 k

g

(33

075

lb)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

N_AC_070802_1_0860101_01_00

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 13

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.6

bar

(154

psi

)49

x 1

7−20

TIR

ES

5 080

6050

4030

20


10


10203040506080

9080

7060

5040

2003076

250

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 54

01

270

1 01

6

1015202535

100

1 52

42

032

7030

A/C

CO

DE

H

WE

IGH

T O

N O

NE

MA

IN

33 2

00 k

g

(73

200

lb)

LAN

DIN

G G

EA

RM

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

N_AC_070802_1_0870101_01_00

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 14

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.9

bar

(158

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

5 080

6050

4030

20


10


10203040506080

9080

7060

5040

2003076

250

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 54

01

270

1 01

6

1015202535

100

1 52

42

032

7030

A/C

CO

DE

H

WE

IGH

T O

N O

NE

MA

IN

33 2

00 k

g

(73

200

lb)

LAN

DIN

G G

EA

RM

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

N_AC_070802_1_0880101_01_00

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]


7-8-2Page 15

Jun 01/12


**ON A/C A320-200

NO

TE

:EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 9

.6 b

ar (

139

psi)

49 x

19−

20 T

IRE

S

5 080

6050

4030

20


10


10203040506080

9080

7060

5040

2003076

250

8

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 54

01

270

1 01

6

1015202535

100

1 52

42

032

7030

A/C

CO

DE

H

WE

IGH

T O

N O

NE

MA

IN

33 2

00 k

g

(73

200

lb)

LAN

DIN

G G

EA

RM

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

N_AC_070802_1_0890101_01_00

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

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(44

100

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(33

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L LO

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2 03

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S (

mm

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A/C

CO

DE

I −

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6090

5040

3020

1005101520253035

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

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ST

AN

T A

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3.8

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(200

psi

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N N

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BE

R (

LCN

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WE

IGH

T O

N O

NE

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IN L

AN

DIN

G G

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R33

960

kg

(7

4 87

5 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

N_AC_070802_1_0900101_01_01


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7060

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49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

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11.

4 ba

r (1

65 p

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WH

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L LO

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L P

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65N

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MA

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508

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2 03

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FN

ES

S (

mm

)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

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R33

960

kg

(7

4 87

5 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

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A/C

CO

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I −

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MA

XIM

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RA

MP

WE

IGH

T A

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N_AC_070802_1_0910101_01_01


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**ON A/C A320-200

1270

x 4

55 R

22 (

49 x

18−

22)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.8

bar

(171

psi

)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

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S [I

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S (

mm

)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R33

960

kg

(7

4 87

5 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

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49 x

19−

20 T

IRE

ST

IRE

PR

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SU

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NT

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10.

3 ba

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49 p

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WH

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S (

mm

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WE

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T O

N O

NE

MA

IN L

AN

DIN

G G

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R33

960

kg

(7

4 87

5 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

N_AC_070802_1_0930101_01_01

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05101520253035


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ME

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INIC

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AE

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E M

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65N

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mm

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J−

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6090

5040

3020

1005101520253035

46 x

17

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TIR

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TIR

E P

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T A

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(200

psi

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LOA

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N N

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BE

R (

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WE

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T O

N O

NE

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IN L

AN

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G G

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R34

720

kg

(7

6 55

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

N_AC_070802_1_0940101_01_00


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4050

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9080

7060

01020304050607080

6090

5040

3020

1005101520253035

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

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TA

NT

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11.

4 ba

r (1

65 p

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WH

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mm

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WE

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T O

N O

NE

MA

IN L

AN

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G G

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R34

720

kg

(7

6 55

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

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000

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(3

3 07

5 lb

)

A/C

CO

DE

J−

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4050

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9080

7060

01020304050607080

6090

5040

3020

1005101520253035

1270

x 4

55 R

22 (

49 x

18−

22)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.8

bar

(171

psi

)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

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S [I

NC

HE

S]

LOA

D C

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N N

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NT

SIN

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WH

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BY

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mm

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WE

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T O

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IN L

AN

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G G

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R34

720

kg

(7

6 55

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

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(4

4 10

0 lb

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000

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(3

3 07

5 lb

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A/C

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4050

100

9080

7060

01020304050607080

6080

5040

3020

1005101520253035

49 x

19−

20 T

IRE

ST

IRE

PR

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SU

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CO

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NT

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10.

3 ba

r (1

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WH

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L LO

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IN L

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R34

720

kg

(7

6 55

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

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000

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(4

4 10

0 lb

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000

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(3

3 07

5 lb

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A/C

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4050

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01020304050607080


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HE

S]

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UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

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BY

ME

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AE

RO

DR

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E M

AN

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L P

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R 4

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n 19

65N

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MA

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A/C

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L−

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N_AC_070802_1_0980101_01_00

6090

5040

3020

1005101520253035

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

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ST

AN

T A

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(200

psi

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LOA

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N N

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BE

R (

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WE

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T O

N O

NE

MA

IN L

AN

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G G

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R35

490

kg

(7

8 25

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)


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2030

4050

100

9080

7060

01020304050607080

6090

5040

3020

1005101520253035

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)


RA

DIU

S O

F R

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NT

SIN

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WH

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L LO

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BY

ME

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INIC

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AE

RO

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65N

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S (

mm

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WE

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T O

N O

NE

MA

IN L

AN

DIN

G G

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R35

490

kg

(7

8 25

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

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(4

4 10

0 lb

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000

kg

(3

3 07

5 lb

)

A/C

CO

DE

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N_AC_070802_1_0990101_01_00


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7060

01020304050607080

6090

5040

3020

1005101520253035

1270

x 4

55 R

22 (

49 x

18−

22)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.8

bar

(171

psi

)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

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S [I

NC

HE

S]

LOA

D C

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SIF

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NT

SIN

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WH

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BY

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INIC

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)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R35

490

kg

(7

8 25

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

A/C

CO

DE

L−

M

N_AC_070802_1_1000101_01_00


7-8-2Page 27

Jun 01/12


**ON A/C A320-200

2030

4050

100

9080

7060

01020304050607080

6080

5040

3020

1005101520253035

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

3 ba

r (1

49 p

si)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:


MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T M

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

508

762

1 01

61

270

1 52

42

540

2 03

2

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R35

490

kg

(7

8 25

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

A/C

CO

DE

L−

M

N_AC_070802_1_1010101_01_00


7-8-2Page 28

Jun 01/12


**ON A/C A320-200

2030

4050

100

9080

7060

01020304050607080


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

508

762

1 01

61

270

1 52

42

540

2 03

2

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

A/C

CO

DE

N−

O

6090

5040

3020

1005101520253035

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.4

bar

(209

psi

)

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)


WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R36

030

kg

(7

9 45

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

G

N_AC_070802_1_1020101_01_00


7-8-2Page 29

Jun 01/12


**ON A/C A320-200

2030

4050

100

9080

7060

01020304050607080


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

508

762

1 01

61

270

1 52

42

540

2 03

2

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

A/C

CO

DE

N−

O

6090

5040

3020

1005101520253035

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12

bar

(174

psi

)

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)


WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R36

030

kg

(7

9 45

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

G

N_AC_070802_1_1030101_01_00


7-8-2Page 30

Jun 01/12


**ON A/C A320-200

2030

4050

100

9080

7060

01020304050607080


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

508

762

1 01

61

270

1 52

42

540

2 03

2

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

A/C

CO

DE

N−

O

6090

5040

3020

1005101520253035

1 27

0 x

455

R22

(49

x 1

8−22

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

3 ba

r (1

78 p

si)

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)


WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R36

030

kg

(7

9 45

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

G

N_AC_070802_1_1040101_01_00


7-8-2Page 31

Jun 01/12


**ON A/C A320-200

2030

4050

100

9080

7060

01020304050607080


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

508

762

1 01

61

270

1 52

42

540

2 03

2

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

A/C

CO

DE

N−

O

6090

5040

3020

1005101520253035

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

7 ba

r (1

55 p

si)

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)


WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R36

030

kg

(7

9 45

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

G

N_AC_070802_1_1050101_01_00


7-8-2Page 32

Jun 01/12


**ON A/C A320-200


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:

508

762

1 01

61

270

1 52

42

540

2 03

2

6090

5040

3020

1005101520253035

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)


WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R36

400

kg

(8

0 25

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.4

bar

(209

psi

)

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T M

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

A/C

CO

DE

P −

Q

N_AC_070802_1_1060101_01_01

2030

4050

100

9080

7060

01020304050607080


7-8-2Page 33

Jun 01/12


**ON A/C A320-200


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:

508

762

1 01

61

270

1 52

42

540

2 03

2

6090

5040

3020

1005101520253035

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)


WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R36

400

kg

(8

0 25

0 lb

)30

000

kg

(6

6 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)

2030

4050

100

9080

7060

01020304050607080

1 27

0 x

455

R22

(49

x 1

8−22

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

3 ba

r (1

78 p

si)

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T M

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

A/C

CO

DE

P −

Q

N_AC_070802_1_1080101_01_01


7-8-2Page 34

Jun 01/12


**ON A/C A320-200

2030

4050

100

9080

7060

0102030405060


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

508

762

1 01

61

270

1 52

42

540

2 03

2

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

A/C

CO

DE

TT

6010

050

4030

2010

0510152025

915

x 30

0 R

16 (

36 x

11−

16)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.2

bar

(177

psi

)

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)


MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GW

EIG

HT

ON

ON

E M

AIN

LA

ND

ING

GE

AR

34 7

00 k

g

(76

500

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

N_AC_070802_1_1100101_01_00


7-8-2Page 35

Jun 01/12


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

**ON A/C A320-200

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

1. General

The table of Section 7-8-1, Radius of Relative Stiffness, presents ”L” values based on Young’sModulus (E) of 4 000 000 psi and Poisson’s Ratio (µ) of 0.15.

To find ”L” values based on other values of ”E” and ”µ”, see Section 7-8-4.

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

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

7-8-3Page 1

Jun 01/12



**ON A/C A320-200

Radius of Relative Stiffness

1. This section gives Radius of Relative Stiffness.

7-8-4Page 1

Jun 01/12


**ON A/C A320-200

0.80

0.85

0.90

0.95

1.00

1.05

1.10

0 1 2 3 4 5

0.995

1.000

1.005

1.010

1.015

0.00 0.05 0.10 0.15 0.20 0.25

E F

AC

TO

R

BOTH CURVES ON THIS PAGE ARE USED TO ADJUST THE L VALUES OF TABLE 7−8−1NOTE:

EFFECT OF ON L VALUES

E, Young’s Modulus (10 , PSI)

EFFECT OF E ON L VALUES

, Poisson’s Ratio

FA

CT

OR

N_AC_070804_1_0030101_01_01

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

FIGURE-7-8-4-991-003-A01

7-8-4Page 2

Jun 01/12


7-9-0 ACN/PCN Reporting System

**ON A/C A320-200

ACN/PCN Reporting System

1. General

To determine the ACN of an aircraft on flexible or rigid pavement, both the aircraft gross weight andthe subgrade strength must be known.

In the example shown in Section 7-9-1 Aircraft Classification Number -- Flexible Pavement, A/C CodeE (Main Gear Tire Size 46 x 17 R20 (46 x 16 - 20), inflated at 12.3 bar (178 psi)), for an aircraftgross weight of 55 000 kg (121 250 lb) and medium subgrade strength (code B), the ACN for theflexible pavement is 28.

In the example shown in Section 7-9-2 Aircraft Classification Number -- Rigid Pavement, A/C Code E(Main Gear Tire Size 46 x 17 R20 (46 x 16 - 20), inflated at 12.3 bar (178 psi)), for an aircraft grossweight of 55 000 kg (121 250 lb) and medium subgrade strength (code B), the ACN for the rigidpavement is 32.

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).

7-9-0Page 1

Jun 01/12


7-9-1 Aircraft Classification Number - Flexible Pavement

**ON A/C A320-200

Aircraft Classification Number - Flexible Pavement

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


7-9-1Page 1

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.3

bar

(178

psi

)

45 35 30 25 20 15 1035

AIRCRAFT CLASSIFICATION NUMBER (ACN)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

E

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0870101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E E

Aircraft Classification Number -- Flexible PavementFIGURE-7-9-1-991-087-A01

7-9-1Page 2

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

2 ba

r (1

48 p

si)

45 35 30 25 20 15 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

E

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0880101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E E


7-9-1Page 3

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

9.2

bar

(13

3 ps

i)

45 35 30 25 20 15 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

E

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0890101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E E


7-9-1Page 4

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)

45 35 30 25 20 15 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

N_AC_070901_1_0900101_01_00

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

F

ALP

HA

FA

CT

OR

= 0

.9

ON

PA

VE

ME

NT

− A

/C C

OD

E F


7-9-1Page 5

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

6 ba

r (1

54 p

si)

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

45 35 30 25 20 15 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0910101_01_00

A/C

CO

DE

F

ON

PA

VE

ME

NT

− A

/C C

OD

E F


7-9-1Page 6

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

ON

PA

VE

ME

NT

− A

/C C

OD

E F

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

9 ba

r (1

58 p

si)

45 35 30 25 20 15 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

F

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0920101_01_00


7-9-1Page 7

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

9.6

bar

(13

9 ps

i)

45 35 30 25 20 15 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

F

ALP

HA

FA

CT

OR

= 0

.9

ON

PA

VE

ME

NT

− A

/C C

OD

E F

N_AC_070901_1_0930101_01_00


7-9-1Page 8

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)

45 35 30 25 20 15 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

G

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0940101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E G


7-9-1Page 9

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

6 ba

r (1

54 p

si)

45 35 30 25 20 15 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

G

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0950101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E G


7-9-1Page 10

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

45 35 30 25 20 15 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

G

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

9 ba

r (1

58 p

si)

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0960101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E G


7-9-1Page 11

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

45 35 30 25 20 15 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

G

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 9

.6 b

ar (

139

psi)

ALP

HA

FA

CT

OR

= 0

.9

49 x

19−

20 T

IRE

S

N_AC_070901_1_0970101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E G


7-9-1Page 12

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

A/C

CO

DE

H

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

ALP

HA

FA

CT

OR

= 0

.9

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)

45 35 25 15

N_AC_070901_1_0980101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E H


7-9-1Page 13

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

6 ba

r (1

54 p

si)

A/C

CO

DE

H

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

ALP

HA

FA

CT

OR

= 0

.9

45 35 25 15

N_AC_070901_1_0990101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E H


7-9-1Page 14

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

A/C

CO

DE

H

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

ALP

HA

FA

CT

OR

= 0

.9

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

9 ba

r (1

58 p

si)

45 35 25 15

N_AC_070901_1_1000101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E H


7-9-1Page 15

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

9.6

bar

(13

9 ps

i)

A/C

CO

DE

H

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

D −

CB

R

3 (U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

ALP

HA

FA

CT

OR

= 0

.9

45 35 25 15

N_AC_070901_1_1010101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E H


7-9-1Page 16

Jun 01/12


**ON A/C A320-200

7065

6055

5045

4035

101520253035404550

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

80

75

9010

011

012

013

014

015

016

0

(x 1

000

lb)

ALP

HA

FA

CT

OR

= 0

.9

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1.42

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G46

x 1

7 R

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

8 ba

r (2

00 p

si)

ON

PA

VE

ME

NT

− A

/C C

OD

E I

− R

A/C

CO

DE

I −

R

N_AC_070901_1_1020101_01_01


7-9-1Page 17

Jun 01/12


**ON A/C A320-200

7065

6055

5045

4035

101520253035404550

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

80

75

9010

011

012

013

014

015

016

0

(x 1

000

lb)

ALP

HA

FA

CT

OR

= 0

.9

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1.42

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G49

x 1

7−20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.4

bar

(165

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

I −

R

A/C

CO

DE

I −

R

N_AC_070901_1_1030101_01_01


7-9-1Page 18

Jun 01/12


**ON A/C A320-200

7065

6055

5045

4035

101520253035404550

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

80

75

9010

011

012

013

014

015

016

0

(x 1

000

lb)

ALP

HA

FA

CT

OR

= 0

.9

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1.42

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.8

bar

(171

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

I −

R

A/C

CO

DE

I −

R

N_AC_070901_1_1040101_01_01


7-9-1Page 19

Jun 01/12


**ON A/C A320-200

7065

6055

5045

4035

101520253035404550

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

80

75

9010

011

012

013

014

015

016

0

(x 1

000

lb)

ALP

HA

FA

CT

OR

= 0

.9

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1.42

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G49

x 1

9−20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.3

bar

(149

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

I −

R

A/C

CO

DE

I −

R

N_AC_070901_1_1050101_01_01


7-9-1Page 20

Jun 01/12


**ON A/C A320-200

7065

6055

5045

4035

101520253035404550

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


80

75

9010

011

012

013

014

015

016

0

(x 1

000

lb)

A/C

CO

DE

J−

K

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.95560

N_AC_070901_1_1060101_01_00

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

0 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.8

bar

(200

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

J−

K


7-9-1Page 21

Jun 01/12


**ON A/C A320-200

7065

6055

5045

4035

101520253035404550

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


80

75

9010

011

012

013

014

015

016

0

(x 1

000

lb)

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.95560

A/C

CO

DE

J−

K

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

0 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)

ON

PA

VE

ME

NT

− A

/C C

OD

E J

−K

N_AC_070901_1_1070101_01_00


7-9-1Page 22

Jun 01/12


**ON A/C A320-200

7065

6055

5045

4035

101520253035404550

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


80

75

9010

011

012

013

014

015

016

0

(x 1

000

lb)

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.95560

A/C

CO

DE

J−

K

N_AC_070901_1_1080101_01_00

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

0 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

8 ba

r (1

71 p

si)

ON

PA

VE

ME

NT

− A

/C C

OD

E J

−K


7-9-1Page 23

Jun 01/12


**ON A/C A320-200

7065

6055

5045

4035

101520253035404550

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


80

75

9010

011

012

013

014

015

016

0

(x 1

000

lb)

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.95560

A/C

CO

DE

J−

K

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

0 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

3 ba

r (1

49 p

si)

ON

PA

VE

ME

NT

− A

/C C

OD

E J

−K

N_AC_070901_1_1090101_01_00


7-9-1Page 24

Jun 01/12


**ON A/C A320-200

7065

6055

5045

4035

101520253035404550

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


80

75

9010

011

012

013

014

015

016

0

(x 1

000

lb)

5560

A/C

CO

DE

L−

M

80

170

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_1100101_01_00

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

8.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G46

x 1

7 R

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

8 ba

r (2

00 p

si)

ON

PA

VE

ME

NT

− A

/C C

OD

E L

−M


7-9-1Page 25

Jun 01/12


**ON A/C A320-200

7065

6055

5045

4035

101520253035404550

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


80

75

9010

011

012

013

014

015

016

0

(x 1

000

lb)

5560

A/C

CO

DE

L−

M

80

170

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_1110101_01_00

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

8.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G49

x 1

7−20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.4

bar

(165

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

L−

M


7-9-1Page 26

Jun 01/12


**ON A/C A320-200

7065

6055

5045

4035

101520253035404550

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


80

75

9010

011

012

013

014

015

068

0

(x 1

000

lb)

5560

A/C

CO

DE

L−

M

80

720

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_1120101_01_00

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

8.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.8

bar

(171

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

L−

M


7-9-1Page 27

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

8.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G49

x 1

9−20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.3

bar

(149

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

L−

M

60 40 35 30 20 15 10

3540


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

2555 50 45

4550

5560

6570

7580

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

D −

CB

R 3

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

ALP

HA

FA

CT

OR

= 0

.9

A/C

CO

DE

L−

M

170

160

150

140

130

120

110

100

9080

N_AC_070901_1_1130101_01_00


7-9-1Page 28

Jun 01/12


**ON A/C A320-200

60 40 35 30 20 15 10

3540


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

2555 50 45

4550

5560

6570

7580

A/C

CO

DE

N−

O

170

160

150

140

130

120

110

100

9080

N_AC_070901_1_1140101_01_00

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

7.5

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G46

x 1

7 R

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

4 ba

r (2

09 p

si)

ON

PA

VE

ME

NT

− A

/C C

OD

E N

−O

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

D −

CB

R 3

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

ALP

HA

FA

CT

OR

= 0

.9


7-9-1Page 29

Jun 01/12


**ON A/C A320-200

60 40 35 30 20 15 10

3540


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

2555 50 45

4550

5560

6570

7580

A/C

CO

DE

N−

O

170

160

150

140

130

120

110

100

9080

N_AC_070901_1_1150101_01_00

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

7.5

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G49

x 1

7−20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2 ba

r (1

74 p

si)

ON

PA

VE

ME

NT

− A

/C C

OD

E N

−O

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

D −

CB

R 3

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

ALP

HA

FA

CT

OR

= 0

.9


7-9-1Page 30

Jun 01/12


**ON A/C A320-200

60 40 35 30 20 15 10

3540


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

2555 50 45

4550

5560

6570

7580

A/C

CO

DE

N−

O

170

160

150

140

130

120

110

100

9080

N_AC_070901_1_1160101_01_00

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

7.5

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.3

bar

(178

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

N−

O

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

D −

CB

R 3

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

ALP

HA

FA

CT

OR

= 0

.9


7-9-1Page 31

Jun 01/12


**ON A/C A320-200

60 40 35 30 20 15 10

3540


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

2555 50 45

4550

5560

6570

7580

A/C

CO

DE

N−

O

170

160

150

140

130

120

110

100

9080

N_AC_070901_1_1170101_01_00

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

7.5

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G49

x 1

9−20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.7

bar

(155

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

N−

O

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

D −

CB

R 3

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

ALP

HA

FA

CT

OR

= 0

.9


7-9-1Page 32

Jun 01/12


**ON A/C A320-200

60 40 35 30 20 15 10

3540

2555 50 45

4550

5560

6570

7580

170

160

150

140

130

120

110

100

9080

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

6.8

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G46

x 1

7 R

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

4 ba

r (2

09 p

si)

ON

PA

VE

ME

NT

− A

/C C

OD

E P

− Q

(x 1

000

lb)

ALP

HA

FA

CT

OR

= 0

.9

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)C

− C

BR

6

(LO

W)

A/C

CO

DE

P −

Q

N_AC_070901_1_1180101_01_01


7-9-1Page 33

Jun 01/12


**ON A/C A320-200

60 40 35 30 20 15 10

3540

2555 50 45

4550

5560

6570

7580

170

160

150

140

130

120

110

100

9080

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

6.8

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.3

bar

(178

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

P −

Q

(x 1

000

lb)

ALP

HA

FA

CT

OR

= 0

.9

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

N_AC_070901_1_1200101_01_01

A/C

CO

DE

P −

Q


7-9-1Page 34

Jun 01/12


**ON A/C A320-200

0

3540


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

40

4550

5560

6570

7580

170

160

150

140

130

120

110

100

9080

A/C

CO

DE

TT

35 30 25 20 15 10 5

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

0 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

915

x 30

0 R

16 (

36 x

11−

16)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.2

bar

(177

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

TT

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

D −

CB

R 3

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

ALP

HA

FA

CT

OR

= 0

.8

N_AC_070901_1_1220101_01_01


7-9-1Page 35

Jun 01/12


7-9-2 Aircraft Classification Number - Rigid Pavement

**ON A/C A320-200

Aircraft Classification Number - Rigid Pavement

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


7-9-2Page 1

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.3

bar

(178

psi

)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

N_AC_070902_1_1280101_01_00

A/C

CO

DE

E

ON

PA

VE

ME

NT

− A

/C C

OD

E E

15253545

Aircraft Classification Number -- Rigid PavementFIGURE-7-9-2-991-128-A01

7-9-2Page 2

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

2 ba

r (1

48 p

si)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

N_AC_070902_1_1290101_01_00

A/C

CO

DE

E

ON

PA

VE

ME

NT

− A

/C C

OD

E E

15253545S

UB

GR

AD

E S

TR

EN

GT

HD

− K

=

20 M

N/m

³ (

ULT

RA

LO

W)

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)


7-9-2Page 3

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

9.2

bar

(13

3 ps

i)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

N_AC_070902_1_1300101_01_00

A/C

CO

DE

E

ON

PA

VE

ME

NT

− A

/C C

OD

E E

15253545


7-9-2Page 4

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

N_AC_070902_1_1310101_01_00

A/C

CO

DE

F

ON

PA

VE

ME

NT

− A

/C C

OD

E F

15253545


7-9-2Page 5

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

6 ba

r (1

54 p

si)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

45 35 25 15

N_AC_070902_1_1320101_01_00

A/C

CO

DE

F

ON

PA

VE

ME

NT

− A

/C C

OD

E F


7-9-2Page 6

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

9 ba

r (1

58 p

si)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

A −

K =

150

MN

/m³

(H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

45 35 25 15

N_AC_070902_1_1330101_01_00

A/C

CO

DE

F

ON

PA

VE

ME

NT

− A

/C C

OD

E F


7-9-2Page 7

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

9.6

bar

(13

9 ps

i)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

45 35 25 15

N_AC_070902_1_1340101_01_00

A/C

CO

DE

F

ON

PA

VE

ME

NT

− A

/C C

OD

E F


7-9-2Page 8

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

45 35 25 15

N_AC_070902_1_1350101_01_00

A/C

CO

DE

G

ON

PA

VE

ME

NT

− A

/C C

OD

E G


7-9-2Page 9

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

6 ba

r (1

54 p

si)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

45 35 25 15

N_AC_070902_1_1360101_01_00

A/C

CO

DE

G

ON

PA

VE

ME

NT

− A

/C C

OD

E G


7-9-2Page 10

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

9 ba

r (1

58 p

si)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

45 35 25 15

N_AC_070902_1_1370101_01_00

A/C

CO

DE

G

ON

PA

VE

ME

NT

− A

/C C

OD

E G


7-9-2Page 11

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

3 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

9.6

bar

(13

9 ps

i)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

45 35 25 15

N_AC_070902_1_1380101_01_00

A/C

CO

DE

G

ON

PA

VE

ME

NT

− A

/C C

OD

E G


7-9-2Page 12

Jun 01/12


**ON A/C A320-200

30 20 1035

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

45 35 25 15

N_AC_070902_1_1390101_01_00

A/C

CO

DE

H

ON

PA

VE

ME

NT

− A

/C C

OD

E H


7-9-2Page 13

Jun 01/12


**ON A/C A320-200

30 20 1035

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

6 ba

r (1

54 p

si)


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

45 35 25 15

N_AC_070902_1_1400101_01_00

A/C

CO

DE

H

ON

PA

VE

ME

NT

− A

/C C

OD

E H


7-9-2Page 14

Jun 01/12


**ON A/C A320-200

30 20 1035

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

9 ba

r (1

58 p

si)


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

SU

BG

RA

DE

ST

RE

NG

TH

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)45 35 25 15

A/C

CO

DE

H

ON

PA

VE

ME

NT

− A

/C C

OD

E H

N_AC_070902_1_1410101_01_00


7-9-2Page 15

Jun 01/12


**ON A/C A320-200

30 20 1035

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

9.6

bar

(13

9 ps

i)


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)C

− K

=

40 M

N/m

³ (

LOW

)B

− K

=

80 M

N/m

³ (

ME

DIU

M)

A −

K =

150

MN

/m³

(H

IGH

)

45 35 25 15

A/C

CO

DE

H

ON

PA

VE

ME

NT

− A

/C C

OD

E H

N_AC_070902_1_1420101_01_00


7-9-2Page 16

Jun 01/12


**ON A/C A320-200

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

A/C

CO

DE

I −

R

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H45 35 25 15

N_AC_070902_1_1430101_01_01

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1.42

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G46

x 1

7 R

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

8 ba

r (2

00 p

si)

ON

PA

VE

ME

NT

− A

/C C

OD

E I

− R


7-9-2Page 17

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1.42

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G49

x 1

7−20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.4

bar

(165

psi

)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H45 35 25 15

ON

PA

VE

ME

NT

− A

/C C

OD

E I

− R

A/C

CO

DE

I −

R

N_AC_070902_1_1440101_01_01


7-9-2Page 18

Jun 01/12


**ON A/C A320-200

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H45 35 25 15

A/C

CO

DE

I −

R

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1.42

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.8

bar

(171

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

I −

R

N_AC_070902_1_1450101_01_01


7-9-2Page 19

Jun 01/12


**ON A/C A320-200

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

7075

160

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H45 35 25 15

A/C

CO

DE

I −

R

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

1.42

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G49

x 1

9−20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.3

bar

(149

psi

)O

N P

AV

EM

EN

T −

A/C

CO

DE

I −

R

N_AC_070902_1_1460101_01_01


7-9-2Page 20

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

0 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.8

bar

(200

psi

)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

30 20 1035


(x 1

000

kg)

(x 1

000

lb)

4050

8090

100

110

120

130

140

150

4045

5055

6065

7075

160

60

A/C

CO

DE

J−

K

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

45 35 25 1555

N_AC_070902_1_1470101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E J

−K


7-9-2Page 21

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

0 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

405080

9010

011

012

013

014

015

0

4045

5055

6065

70

A/C

CO

DE

J−

K

75

160

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H45 35 25 15

ON

PA

VE

ME

NT

− A

/C C

OD

E J

−K

N_AC_070902_1_1480101_01_00


7-9-2Page 22

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

0 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

8 ba

r (1

71 p

si)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

4050

8090

100

110

120

130

140

150

4045

5055

6065

7075

160

60

A/C

CO

DE

J−

K

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

45 35 25 1555

N_AC_070902_1_1490101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E J

−K


7-9-2Page 23

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

0 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

3 ba

r (1

49 p

si)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

4050

8090

100

110

120

130

140

150

4045

5055

6065

70

A/C

CO

DE

J−

K

75

160

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

60 45 35 25 1555

N_AC_070902_1_1500101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E J

−K


7-9-2Page 24

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

8.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G46

x 1

7 R

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

8 ba

r (2

00 p

si)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

4050

8090

100

110

120

130

140

150

4045

5055

6065

7075

160

6017

0

80

A/C

CO

DE

L−

M

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

45 35 25 1555

N_AC_070902_1_1510101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E L

−M


7-9-2Page 25

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

8.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G49

x 1

7−20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.4

bar

(165

psi

)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

4050

8090

100

110

120

130

140

150

4045

5055

6065

7075

160

6017

0

80

A/C

CO

DE

L−

M

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

45 35 25 1555

N_AC_070902_1_1520101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E L

−M


7-9-2Page 26

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

8.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.8

bar

(171

psi

)

30 20 1035


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

4050

8090

100

110

120

130

140

150

4045

5055

6065

7075

160

6017

0

80

A/C

CO

DE

L−

M

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

45 35 25 1555

N_AC_070902_1_1530101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E L

−M


7-9-2Page 27

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

8.7

% M

AC

.

152025303540455055

3540

4550

5560

6570

7580

AIR

CR

AF

T G

RO

SS

WE

IGH

T

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

3 ba

r (1

49 p

si)

(x 1

000

kg)

(x 1

000

lb)


SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

L−

M

80

10

9010

011

012

013

014

015

016

017

060

N_AC_070902_1_1540101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E L

−M


7-9-2Page 28

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

7.5

% M

AC

.

152025303540455055

3540

4550

5560

6570

7580

AIR

CR

AF

T G

RO

SS

WE

IGH

T

46 x

17

R20

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.4

bar

(209

psi

)

(x 1

000

kg)

(x 1

000

lb)


SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

N−

O

106080

9010

011

012

013

014

015

016

017

0

N_AC_070902_1_1550101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E N

−O


7-9-2Page 29

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

7.5

% M

AC

.

152025303540455055

3540

4550

5560

6570

7580

AIR

CR

AF

T G

RO

SS

WE

IGH

T

49 x

17−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12

bar

(174

psi

) (x 1

000

kg)

(x 1

000

lb)


SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

N−

O

80

10

9010

011

012

013

014

015

016

017

060

N_AC_070902_1_1560101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E N

−O


7-9-2Page 30

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

7.5

% M

AC

.

152025303540455055

3540

4550

5560

6570

7580

AIR

CR

AF

T G

RO

SS

WE

IGH

T

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

3 ba

r (1

78 p

si)

(x 1

000

kg)

(x 1

000

lb)


SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

N−

O

80

10

9010

011

012

013

014

015

016

017

060

N_AC_070902_1_1570101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E N

−O


7-9-2Page 31

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

7.5

% M

AC

.

152025303540455055

3540

4550

5560

6570

7580

AIR

CR

AF

T G

RO

SS

WE

IGH

T

49 x

19−

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

7 ba

r (1

55 p

si)

(x 1

000

kg)

(x 1

000

lb)


SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

N−

O

80

10

9010

011

012

013

014

015

016

017

060

N_AC_070902_1_1580101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E N

−O


7-9-2Page 32

Jun 01/12


**ON A/C A320-200

152025303540455055

4045

5055

6065

7075

8010

9010

011

012

013

014

015

016

017

060

80

35


C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

P −

Q

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

6.8

% M

AC

.S

EE

SE

CT

ION

7−

4−1

FIG

UR

E 1

246

x 1

7 R

20 T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

4 ba

r (2

09 p

si)

ON

PA

VE

ME

NT

− A

/C C

OD

E P

− Q

N_AC_070902_1_1590101_01_01

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)


7-9-2Page 33

Jun 01/12


**ON A/C A320-200

152025303540455055

4045

5055

6065

7075

8010

9010

011

012

013

014

015

016

017

060

80

35


C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

A/C

CO

DE

P −

Q

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.C

G U

SE

D F

OR

AC

N C

ALC

ULA

TIO

NS

: 36.

8 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

3 ba

r (1

78 p

si)

ON

PA

VE

ME

NT

− A

/C C

OD

E P

− Q

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

N_AC_070902_1_1610101_01_01


7-9-2Page 34

Jun 01/12


**ON A/C A320-200

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 4

0 %

MA

C.

15202530

3540

4550

5560

6570

7580

AIR

CR

AF

T G

RO

SS

WE

IGH

T

915

x 30

0 R

16 (

36 x

11−

16)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.2

bar

(177

psi

)

(x 1

000

kg)

(x 1

000

lb)


80

10

9010

011

012

013

014

015

016

017

0

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

TT

5 0

N_AC_070902_1_1630101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E T

T


7-9-2Page 35

Jun 01/12


SCALED DRAWINGS

8-0-0 SCALED DRAWINGS

**ON A/C A320-200

Scaled Drawings

1. This section provides the scaled drawings.

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

8-0-0Page 1

Jun 01/12


**ON A/C A320-200

0 10 20 30 40 50FEET

0 5 10 15METERS

010

2030

4050

FE

ET

05

1015

ME

TE

RS

N_AC_080000_1_0030101_01_00

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

Scaled DrawingFIGURE-8-0-0-991-003-A01

8-0-0Page 2

Jun 01/12


AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 AIRCRAFT RESCUE AND FIRE FIGHTING

**ON A/C A320-200

Aircraft 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 poster available for download on AIRBUSWorld and the Airbus website.

10-0-0Page 1

Jun 01/12


**ON A/C A320-200

N_AC_100000_1_0010301_01_00

Front PageFIGURE-10-0-0-991-001-C01

10-0-0Page 2

Jun 01/12


**ON A/C A320-200

N_AC_100000_1_0020301_01_00

Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-0-0-991-002-C01

10-0-0Page 3

Jun 01/12


**ON A/C A320-200

N_AC_100000_1_0030101_01_00

Wheel Safety Area(Sheet 1 of 2)

FIGURE-10-0-0-991-003-A01

10-0-0Page 4

Jun 01/12


**ON A/C A320-200

N_AC_100000_1_0030102_01_00

Wheel Safety AreaRecommendations (Sheet 2 of 2)

FIGURE-10-0-0-991-003-A01

10-0-0Page 5

Jun 01/12


**ON A/C A320-200

N_AC_100000_1_0040301_01_00

Composite MaterialsFIGURE-10-0-0-991-004-C01

10-0-0Page 6

Jun 01/12


**ON A/C A320-200

A AB

B

N_AC_100000_1_0050101_01_00

LG Ground Lock Safety DevicesFIGURE-10-0-0-991-005-A01

10-0-0Page 7

Jun 01/12


**ON A/C A320-200

C L

N_AC_100000_1_0060301_01_00

Evacuation/Escape Slide/RaftFIGURE-10-0-0-991-006-C01

10-0-0Page 8

Jun 01/12


**ON A/C A320-200

N_AC_100000_1_0070101_01_00

Pax/Crew DoorsFIGURE-10-0-0-991-007-A01

10-0-0Page 9

Jun 01/12


**ON A/C A320-200

N_AC_100000_1_0080301_01_00

Emergency Exit HatchFIGURE-10-0-0-991-008-C01

10-0-0Page 10

Jun 01/12


**ON A/C A320-200

134A

R15

4AR

/

198C

B

N_AC_100000_1_0090101_01_00

FWD and AFT Lower Deck Cargo DoorsFIGURE-10-0-0-991-009-A01

10-0-0Page 11

Jun 01/12


**ON A/C A320-200

FL

T IN

T

LIG

HT

TE

ST

CK

PT

CA

LL

RE

SE

T

AP

U S

HU

T O

FF

AP

U F

IRE

AD

IRU

&C

KP

T C

AL

LA

VN

CS

VE

NT

AV

AIL

NO

T IN

US

E

EL

T

108V

U

EX

T P

WR

ENG

MAS

TER

2M

ASTE

R 1

ON

OF

F

ON

OF

FM

OD

E

IGN

ENG 1

FIR

E

FA

ULT

FIR

E

FA

ULT

21

CR

AN

KS

TA

RT

ENG 2

NO

RM

A

D

RA

IN R

PL

NT

SL

OW

FA

ST

OF

FW

IPE

R

MA

IN S

TA

RT

12

EN

G

OV

RD

FA

UL

TA U T O

BLO

WE

R

OV

RD

FA

UL

TA U T O

EX

TR

AC

TV

EN

TIL

AT

ION

OF

F

CA

B F

AN

S

ON

ON

TE

ST

AF

T

DIS

CH

22V

U

HO

T

AF

T

CA

RG

O S

MO

KE

CO

LD

OF

F

FA

UL

T

HO

T A

IR

OF

F

FA

UL

T

AF

T IS

OL V

ALV

E

CA

RG

O

DIS

CH

SM

OK

E

FW

D

DIS

CH

DIS

CH

SM

OK

E

APU

SH

PU

SH

PU

SH

DIS

CH

SQ

UIB

DIS

CH

SQ

UIB

DIS

CH

SQ

UIB

DIS

CH

SQ

UIB

DIS

CH

SQ

UIB

AG

EN

T 1

AG

EN

T 2

AG

EN

T 1

AG

EN

T 2

TE

ST

TE

ST

TE

ST

AG

EN

T

F I R E

F I R E

AP

UFI

RE

FIR

EEN

G2

FIR

EEN

G1

B

C E

ED

B C

FA

ULT

FA

ULT

OF

F

OF

F

OF

F

FA

ULT

OF

F

FA

ULT

OF

F

FA

ULT

OF

F

FA

ULT

OF

F

FA

ULT

ALT

N

FA

ULT

ON

AV

AIL

E L E CID

G 2

GE

N 2

DC

BU

S 2

AC

ES

S F

EE

D

EX

T P

WR

AP

U G

EN

GE

N 1

BA

T 2

BA

T2

1B

AT

1

AC

BU

S 1

DC

BU

S 1

CO

MM

ER

CIA

L

GA

LY &

CA

B

IDG

1

E L E C

BU

S T

IEA U T O

VV

35V

U

OF

F

A U T O

AC

BU

S 2

AC E

SS B

US

ON

FA

ULT

ON

FA

ULT

ON

FA

ULT

ON

FA

ULT

ON

AN

TI IC

EPR

OBE

/WIN

DO

WH

EAT

EN

G 1

EN

G 2

WIN

GM

AN

V/S

CTL

MO

DE

SE

LLD

G E

LEV

AU

TOD

ITC

HIN

GC

ABIN

PR

ESS

UP

ON

A U T O

A U T O

25V

U

ON

FA

ULT

ON

AV

AIL

INT

LT

SIG

NS

APU

STB

Y C

OM

PA

SS

AN

N L

TD

OM

ETE

ST

BR

T

DIM

OFFDIM

BR

T

OFF

SE

AT

BE

LTS

NO

SM

OK

ING

EM

ER

EX

IT L

T

A U T OO

FFO

FF

ON

ON

ON

AR

M

OFF

BRT

OFFOV

HD

INTE

G L

T

MA

STE

R S

W

STA

RT

WIN

GN

AV

& L

OG

OS

TRO

BE

BE

AC

ON

OFF

OFF

OFF

ON

ON

ON

OFF

EXT

LT

A U T O

RW

Y T

UR

N O

FFO

NO

N

OFF

OFF

OFF

RETR

ACT

LAN

DL

RN

OS

ET.

O

TAX

I

ON

OF

F

N_AC_100000_1_0120101_01_00

Control PanelsFIGURE-10-0-0-991-012-A01

10-0-0Page 12

Jun 01/12


**ON A/C A320-200

316A

R

A

315A

L

A

N_AC_100000_1_0130101_01_00

APU Access DoorFIGURE-10-0-0-991-013-A01

10-0-0Page 13

Jun 01/12


**ON A/C A320-200

N_AC_100000_1_0140301_01_00

Aircraft Ground ClearancesFIGURE-10-0-0-991-014-C01

10-0-0Page 14

Jun 01/12


**ON A/C A320-200

N_AC_100000_1_0150101_01_00

Structural Break-in PointsFIGURE-10-0-0-991-015-A01

10-0-0Page 15

Jun 01/12

Airbus AC A320 Jun2012

Documents

Transcript of Airbus AC A320 Jun2012