airbus ac a321 jun2012

@AIRBUSA321

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 30/92 Rev: Jun 01/12

@A321AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

HIGHLIGHTS

Revision No. 16 - 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.

Section 01-02 D

CHAPTER 2 R

Section 2-1 R

Subject 2-1-0 R

General Airplane Characteristics R WEIGHT DEFINITIONS UPDATED.

Subject 2-1-1 R

General Airplane Characteristics Data R OEW AND PAYLOAD DELETED.OEW AND PAYLOAD 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

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

FIGURE Ground Clearances R

FIGURE Ground Clearances - GroundClearances with Sharklets

N ILLUSTRATION ADDED

HIGHLIGHTSPage 1

Jun 01/12


LOCATIONS CHGCODE


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 2-6 R

Subject 2-6-0

Cargo Compartments R

FIGURE Cargo Compartments -Locations, Dimensions and LoadingCombinations


Subject 02-06-01 D

Section 2-8 N

Subject 2-8-0 N

Escape Slides N

FIGURE Escape Slides - Location N ILLUSTRATION ADDED

FIGURE Escape Slides - Location N ILLUSTRATION ADDED

Section 2-9 N

Subject 2-9-0 N

Landing Gear N

FIGURE Landing Gear - Main LandingGear - Twin Wheel


FIGURE Landing Gear - Main LandingGear Dimensions - Twin Wheel


FIGURE Landing Gear - Nose LandingGear


FIGURE Landing Gear - Nose LandingGear Dimensions


HIGHLIGHTSPage 2

Jun 01/12


LOCATIONS CHGCODE


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


FIGURE Power Plant Handling - ThrustReverser Cowls - CFM56 Series Engine


HIGHLIGHTSPage 3

Jun 01/12


LOCATIONS CHGCODE


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 - Wing Jacking Point and ForwardFuselage Jacking Point


FIGURE Jacking for Maintenance -Location of Shoring Cradles


Jacking for Wheel Change N

HIGHLIGHTSPage 4

Jun 01/12


LOCATIONS CHGCODE


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


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


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


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


CHAPTER 3 R

CHAPTER 4

Section 4-2

Subject 4-2-0

FIGURE Turning Radii, No Slip Angle R ILLUSTRATION REVISED

FIGURE Turning Radii, No Slip Angle R ILLUSTRATION REVISED

Section 4-3

Subject 4-3-0

FIGURE Minimum Turning Radii R

Section 4-4

Subject 4-4-0

Visibility from Cockpit in Static Position N

FIGURE Visibility from Cockpit in StaticPosition


FIGURE Binocular Visibility ThroughWindows from Captain Eye Position


Section 4-5 R

Subject 4-5-1

HIGHLIGHTSPage 5

Jun 01/12


LOCATIONS CHGCODE


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

R

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

R

Subject 4-5-2

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

R

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

R

Subject 4-5-3

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 N

90˚ Turn - Taxiway to Taxiway N

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


Subject 04-05-06 D

Section 4-6

Subject 4-6-0

FIGURE Runway Holding Bay (Apron) R

Section 4-7 R

Subject 4-7-0 R

CHAPTER 5 R

Section 5-1 R

Subject 5-1-0 R

Subject 5-1-2 R

HIGHLIGHTSPage 6

Jun 01/12


LOCATIONS CHGCODE


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

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 (51 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 (25 Min.)


Subject 05-03-01 D

Section 5-4

Subject 5-4-1

Ground Service Connections Layout R DELETED GROUND SERVICECONNECTIONS LAYOUT TABLE.

HIGHLIGHTSPage 7

Jun 01/12


LOCATIONS CHGCODE


FIGURE Ground Service Connections -Ground Service Connections Layout

R

Subject 5-4-3

Hydraulic System R

Subject 5-4-4

Electrical System R

Subject 5-4-6

Fuel System R NOTE AMENDED

FIGURE Ground Service Connections -Overpressure Protector and NACA FlameArrestor

N ADDED OVERPRESSURE PROTECTORAND NACA FLAME ARRESTORILLUSTRATION.ILLUSTRATION ADDED

Subject 5-4-8

Potable Water System R NOTE AMENDED

Section 5-5

Subject 5-5-0

Engine Starting Pneumatic Requirements R CROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETED

FIGURE Engine Starting PneumaticRequirements


Subject 5-5-1 R

Low Ambient Temperatures R DESCRIPTION TITLE UPDATED

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

R

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

R

Subject 5-5-2 R

Medium Ambient Temperatures R DESCRIPTION TITLE UPDATED

HIGHLIGHTSPage 8

Jun 01/12


LOCATIONS CHGCODE


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

R

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

R

Subject 5-5-3 R

High Ambient Temperatures R DESCRIPTION TITLE UPDATED

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

R

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

R

Section 5-6

Subject 5-6-0

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

Section 5-8

Subject 5-8-0

Ground Towing Requirements R SAE REFERENCES UPDATED ANDFIGURES CORRESPONDING TO TYPICALTOW BAR CONFIGURATION DELETEDNOTE AMENDED

Section 5-9 N

Subject 5-9-0 N

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

HIGHLIGHTSPage 9

Jun 01/12


LOCATIONS CHGCODE


CHAPTER 7

Section 7-8 R

Subject 07-08-00 D

Subject 7-8-1

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

R

Subject 7-8-2

Rigid Pavement Requirements - LCNConversion

R MOVED THE TEXT FROM 7-8-0 TO 7-8-2.

CHAPTER 8 R

Section 8-0 N

Subject 8-0-0 N

Scaled Drawings N

FIGURE Scaled Drawing N ILLUSTRATION ADDED

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 and EmergencyExits


FIGURE FWD and AFT Lower DeckCargo Doors


FIGURE Control Panels N ILLUSTRATION ADDED

HIGHLIGHTSPage 10

Jun 01/12


LOCATIONS CHGCODE


FIGURE APU Access Door N ILLUSTRATION ADDED

FIGURE Aircraft Ground Clearances N ILLUSTRATION ADDED

FIGURE Structural Break-in Points N ILLUSTRATION ADDED

HIGHLIGHTSPage 11

Jun 01/12


LIST OF EFFECTIVE CONTENT

Revision No. 16 - 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 - 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 Dec 01/07

Subject 2-4-1

Typical Configuration Sep 01/10

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

Sep 01/10

L.E.C.Page 1

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Typical Configuration - Typical Configuration Two-Class Sep 01/10

Subject 2-5-0

Passenger Compartment Cross-section Sep 01/10

FIGURE Passenger Compartment Cross-section Sep 01/10

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

Sep 01/10

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

Sep 01/10

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 Dec 01/07

Subject 2-7-1

Forward Passenger / Crew Doors Dec 01/07

FIGURE Doors Clearances - Forward Passenger / Crew Doors Dec 01/07

Subject 2-7-2

Emergency Exits Dec 01/07

FIGURE Doors Clearances - Emergency Exits Dec 01/07

Subject 2-7-3

Aft Passenger / Crew Doors Dec 01/07

FIGURE Doors Clearances - Aft Passenger / Crew Doors Dec 01/07

Subject 2-7-4

Forward Cargo Compartment Door Dec 01/07

FIGURE Doors Clearances - Forward Cargo Compartment Door Dec 01/07

Subject 2-7-5

Aft Cargo Compartment Door Dec 01/07

FIGURE Doors Clearances - Aft Cargo Compartment Door Dec 01/07

Subject 2-7-6

L.E.C.Page 2

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Bulk Cargo Compartment Door Dec 01/07

FIGURE Doors Clearances - Bulk Cargo Compartment Door Dec 01/07

Subject 2-7-7

Main Landing Gear Doors Dec 01/07

FIGURE Doors Clearances - Main Landing Gear Doors Dec 01/07

Subject 2-7-8

Radome Dec 01/07

FIGURE Doors Clearances - Radome Dec 01/07

Subject 2-7-9

APU and Nose Landing Gear Doors Dec 01/07

FIGURE Doors Clearances - APU and Nose Landing Gear Doors Dec 01/07

Subject 2-8-0

Escape Slides N Jun 01/12

FIGURE Escape Slides - Location N Jun 01/12

FIGURE Escape Slides - Location 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 - 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

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



L.E.C.Page 3

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE


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

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

L.E.C.Page 4

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

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 - Wing Jacking Pointand Forward Fuselage Jacking Point

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

N Jun 01/12

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

N Jun 01/12

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

CHAPTER 3

Subject 3-1-0

General Information Dec 01/07

Subject 3-2-0

Payload / Range Dec 01/07

Subject 3-2-1

ISA Conditions Dec 01/07

FIGURE Payload / Range - CFM56-5B series engine Dec 01/07

FIGURE Payload / Range - IAE V2500-A5 series engine Dec 01/07

Subject 3-3-0

FAR / JAR Take-off Weight Limitation Dec 01/07

Subject 3-3-1

L.E.C.Page 5

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE


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

Dec 01/07

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

Dec 01/07

Subject 3-3-2

ISA +15˚C (+59˚F) Conditions Dec 01/07

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

Dec 01/07

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

Dec 01/07

Subject 3-4-0

FAR / JAR Landing Field Length Dec 01/07

Subject 3-4-1


FIGURE FAR / JAR Landing Field Length - CFM56 series engine Dec 01/07

FIGURE FAR / JAR Landing Field Length - IAE V2500 series engine Dec 01/07

Subject 3-5-0

Final Approach Speed Dec 01/07

FIGURE Final Approach Speed - CFM56 series engine Dec 01/07

FIGURE Final Approach Speed - IAE V2500 series engine Dec 01/07

CHAPTER 4

Subject 4-1-0

General Information Dec 01/07

Subject 4-2-0

Turning Radii Dec 01/07

FIGURE Turning Radii, No Slip Angle R Jun 01/12

FIGURE Turning Radii, No Slip Angle R Jun 01/12

Subject 4-3-0

Minimum Turning Radii Dec 01/07

L.E.C.Page 6

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

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

Subject 4-5-0

Runway and Taxiway Turn Paths Dec 01/07

Subject 4-5-1

135˚ Turn - Runway to Taxiway Dec 01/07

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

R Jun 01/12

FIGURE 135˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

R Jun 01/12

Subject 4-5-2

90˚ Turn - Runway to Taxiway Dec 01/07

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

R Jun 01/12

FIGURE 90˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

R Jun 01/12

Subject 4-5-3

180˚ Turn on a Runway Dec 01/07

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

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

N Jun 01/12

Subject 4-6-0

L.E.C.Page 7

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Runway Holding Bay (Apron) Dec 01/07

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

Subject 4-7-0

Airplane Parking Dec 01/07

FIGURE Runway Length Alterations - Line Up Distances -- 90˚ Turn Dec 01/07

FIGURE Runway Length Alterations - Line Up Distances -- 180˚ Turn Dec 01/07

CHAPTER 5

Subject 5-0-0

Terminal Servicing Sep 01/10

Subject 5-1-0

Airplane Servicing Arrangements Sep 01/10

Subject 5-1-1

Symbols Used on Servicing Diagrams Sep 01/10

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 (51 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 (25 Min.) N Jun 01/12

Subject 5-4-0

Ground Service Connections Dec 01/07

Subject 5-4-1

L.E.C.Page 8

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

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 Dec 01/07

FIGURE Ground Service Connections - Grounding Points Dec 01/07

FIGURE Ground Service Connections - Grounding Points Dec 01/07

Subject 5-4-3

Hydraulic System R Jun 01/12

FIGURE Hydraulic System - Green System Ground Service Panel Sep 01/10

FIGURE Hydraulic System - Blue System Ground Service Panel Sep 01/10

FIGURE Hydraulic System - Yellow System Ground Service Panel Sep 01/10

Subject 5-4-4

Electrical System R Jun 01/12

FIGURE Ground Service Connections - External Power Receptacles Sep 01/10

Subject 5-4-5

Oxygen System Dec 01/07

Subject 5-4-6

Fuel System R Jun 01/12

FIGURE Ground Service Connections - Refuel/Defuel Panel Sep 01/10

FIGURE Ground Service Connections - Refuel/Defuel Couplings Sep 01/10

FIGURE Ground Service Connections - Gravity Refuel Couplings Sep 01/10

FIGURE Ground Service Connections - Overpressure Protector andNACA Flame Arrestor

N Jun 01/12

Subject 5-4-7

Pneumatic System Sep 01/10

Subject 5-4-8

Potable Water System R Jun 01/12

FIGURE Ground Service Connections - Potable Water Ground ServicePanel

Sep 01/10

L.E.C.Page 9

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Subject 5-4-9

Oil System Sep 01/10

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

Sep 01/10

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

Sep 01/10

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

Sep 01/10

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

Sep 01/10

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

Sep 01/10

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

Sep 01/10

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

Subject 5-4-10

Vacuum Toilet System Sep 01/10

FIGURE Ground Service Connections - Waste Water Ground ServicePanel

Sep 01/10

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

L.E.C.Page 10

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

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

Subject 5-6-1

Heating Dec 01/07

FIGURE Ground Pneumatic Power Requirements - Heating Dec 01/07

Subject 5-6-2

Cooling Dec 01/07

FIGURE Ground Pneumatic Power Requirements - Cooling Dec 01/07

Subject 5-7-0

Preconditioned Airflow Requirements Dec 01/07

FIGURE Preconditioned Airflow Requirements Dec 01/07

Subject 5-8-0

Ground Towing Requirements R Jun 01/12

FIGURE Ground Towing Requirements Sep 01/10

Subject 5-9-0

De-Icing and External Cleaning N Jun 01/12

CHAPTER 6

Subject 6-1-0

Engine Exhaust Velocities and Temperatures Dec 01/07

Subject 6-1-1

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

L.E.C.Page 11

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Engine Exhaust Velocities - Ground Idle Power -- CFM56-5Bseries engine

Dec 01/07

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

Dec 01/07

Subject 6-1-2

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

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

Dec 01/07

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

Dec 01/07

Subject 6-1-5

Engine Exhaust Velocities Contours - Takeoff Power Dec 01/07

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

Dec 01/07

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

Dec 01/07

Subject 6-1-6

Engine Exhaust Temperatures Contours - Takeoff Power Dec 01/07

FIGURE Engine Exhaust Temperatures - Takeoff Power -- CFM56-5Bseries engine

Dec 01/07

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

Dec 01/07

Subject 6-2-0

Airport and Community Noise Dec 01/07

Subject 6-2-1

Noise Data Dec 01/07

FIGURE Airport and Community Noise - CFM56-5B series engine Dec 01/07

FIGURE Airport and Community Noise - IAE V2500 series engine Dec 01/07

Subject 6-3-0

Danger Areas of Engines Dec 01/07

Subject 6-3-1

L.E.C.Page 12

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Ground Idle Power Dec 01/07

FIGURE Danger Areas of Engines - CFM56-5B series engine Dec 01/07

FIGURE Danger Areas of Engines - IAE V2500 series engine Dec 01/07

Subject 6-3-2

Takeoff Power Dec 01/07

FIGURE Danger Areas of Engines - CFM56-5B series engine Dec 01/07

FIGURE Danger Areas of Engines - IAE V2500 series engine Dec 01/07

Subject 6-4-0

APU Exhaust Velocities and Temperatures Dec 01/07

Subject 6-4-1

APU - APIC & GARRETT Dec 01/07

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

Dec 01/07

CHAPTER 7

Subject 7-1-0

General Information May 01/11

FIGURE Aircraft Codes - Aircraft Codes May 01/11

Subject 7-2-0

Landing Gear Footprint May 01/11

FIGURE Landing Gear Footprint - Landing Gear Footprint May 01/11





Subject 7-3-0

Maximum Pavement Loads May 01/11

FIGURE Maximum Pavement Loads - Maximum Pavement Loads May 01/11

FIGURE Maximum Pavement Loads May 01/11


L.E.C.Page 13

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE




FIGURE Maximum Pavement Loads - Maximum Pavement Loads May 01/11

Subject 7-4-0

Landing Gear Loading on Pavement May 01/11

Subject 7-4-1

Landing Gear Loading on Pavement May 01/11

FIGURE Landing Gear Loading on Pavement May 01/11









FIGURE Landing Gear Loading on Pavement - Landing Gear Loadingon Pavement

May 01/11











L.E.C.Page 14

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Subject 7-5-0

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

May 01/11

Subject 7-5-1

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

May 01/11

FIGURE Flexible Pavement Requirements May 01/11







FIGURE Flexible Pavement Requirement - Flexible PavementRequirements

May 01/11









FIGURE Flexible Pavement Requirement - Flexible PavementRequirements

May 01/11




Subject 7-6-0

Flexible Pavement Requirements - LCN Conversion May 01/11

L.E.C.Page 15

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Subject 7-6-1

Flexible Pavement Requirements - LCN Conversion May 01/11

FIGURE Flexible Pavement Requirements - LCN Conversion May 01/11




















Subject 7-7-0

Rigid Pavement Requirements - Portland Cement Association DesignMethod

May 01/11

Subject 7-7-1

Rigid Pavement Requirements - Portland Cement Association DesignMethod

May 01/11

FIGURE Rigid Pavement Requirements (PCA) May 01/11


L.E.C.Page 16

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE



















Subject 7-8-1

Radius of Relative Stiffness Dec 01/07

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 May 01/11





L.E.C.Page 17

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE
















Subject 7-8-3

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

Subject 7-8-4

Radius of Relative Stiffness Dec 01/07

FIGURE Radius of Relative Stiffness - (Effect E and µ on ”L” values) May 01/11

Subject 7-9-0

ACN/PCN Reporting System May 01/11

Subject 7-9-1

Aircraft Classification Number - Flexible Pavement May 01/11

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





L.E.C.Page 18

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE
















Subject 7-9-2

Aircraft Classification Number - Rigid Pavement May 01/11

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












L.E.C.Page 19

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 and Emergency Exits 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 20

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)

4-7-0 Parking

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

T.O.C.Page 2

Jun 01/12


5-4-10 Vacuum Toilet System

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

6-1-5 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 A321-100 A321-200

Purpose

1. GeneralThe A321 AIRCRAFT CHARACTERISTICS -- AIRPORT AND MAINTENANCE PLANNING (AC)manual is issued for the A321-100 and A321-200 series aircraft, equipped with wing-tip fences orSharklets to provide necessary data to airport operators, airlines and Maintenance/RepairOrganizations (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 A321-100 and A321-200 AC equipped with Sharklets can besubject to change pending completion of the flight test phase. It is given for guidance only and doesnot constitute a contractual 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 A321neo 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 A321-100 A321-200

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 A321-100 A321-200

General Airplane Characteristics Data

**ON A/C A321-100

1. The following table provides characteristics of A321-100 Models, these data are specific to eachWeight Variant:

Aircraft CharacteristicsWV000 WV002 WV003 WV004 WV005

Kilograms 83 400 83 400 85 400 78 400 83 400Maximum Ramp Weight(MRW)Maximum Taxi Weight(MTW)

Pounds183 865 183 865 188 275 172 842 183 865

Kilograms 83 000 83 000 85 000 78 000 83 000Maximum TakeoffWeight (MTOW) Pounds 182 984 182 984 187 393 171 961 182 984

Kilograms 73 500 74 500 74 500 73 500 75 000Maximum LandingWeight (MLW) Pounds 162 040 164 244 164 244 162 040 165 347

Kilograms 69 500 70 500 70 500 69 500 71 000Maximum Zero FuelWeight (MZFW) Pounds 153 221 155 426 155 426 153 221 156 528

Aircraft CharacteristicsWV006 WV007 WV008

Kilograms 78 400 80 400 89 400Maximum Ramp Weight (MRW)Maximum Taxi Weight (MTW) Pounds 172 842 177 252 197 093

Kilograms 78 000 80 000 89 000Maximum Takeoff Weight(MTOW) Pounds 171 961 176 370 196 211

Kilograms 74 500 73 500 75 500Maximum Landing Weight(MLW) Pounds 164 244 162 040 166 449

Kilograms 70 500 69 500 71 500Maximum Zero Fuel Weight(MZFW) Pounds 155 426 153 221 157 630

2-1-1Page 1

Jun 01/12


**ON A/C A321-200

2. The following table provides characteristics of A321-200 Models, these data are specific to eachWeight Variant:



Pounds197 093 205 912 197 093 201 502 192 684






Pounds188 275 183 865 183 865 177 252 172 842




Aircraft CharacteristicsWV010 WV011

Kilograms 85 400 93 900Maximum Ramp Weight (MRW)Maximum Taxi Weight (MTW) Pounds 188 275 207 014

Kilograms 85 000 93 500Maximum Takeoff Weight (MTOW)

Pounds 187 393 206 132Kilograms 77 800 77 800Maximum Landing Weight (MLW)

Pounds 171 520 171 520

2-1-1Page 2

Jun 01/12


Aircraft CharacteristicsWV010 WV011

Kilograms 73 800 73 800Maximum Zero Fuel Weight (MZFW)

Pounds 162 701 162 701

**ON A/C A321-100

3. The following table provides characteristics of A321-100 Models, these data are common to eachWeight Variant:

Aircraft CharacteristicsStandard SeatingCapacity

Single-class220

Liters 23 700 - 26 692* - 29 684**US gallons 6 261 - 7 051* - 7 842**

Kilograms(density =0.785 kg/l)

18 604 - 20 953* - 23 301**

Usable Fuel Capacity

Pounds 41 015 - 46 193* - 51 370**Cubic meters 418Pressurized Fuselage

Volume (A/C nonequipped)

Cubic feet14 762

Cubic meters 155Passenger CompartmentVolume Cubic feet 5 474

Cubic meters 9Cockpit VolumeCubic feet 318Cubic meters 22.81Usable Volume, FWD CCCubic feet 806Cubic meters 23.03Usable Volume, AFT CCCubic feet 814Cubic meters 5.88Usable Volume, Bulk CCCubic feet 208Cubic meters 25.42Water Volume, FWD CCCubic feet 897.7Cubic meters 25.69Water Volume, AFT CCCubic feet 907.2Cubic meters 7.76Water Volume, Bulk CCCubic feet 274

* OPTION: 1 ACT** OPTION: 2 ACT

2-1-1Page 3

Jun 01/12


**ON A/C A321-200

4. The following table provides characteristics of A321-200 Models, these data are common to eachWeight Variant:

Aircraft CharacteristicsStandard SeatingCapacity

Single-class220

Liters 23 700 - 26 692* - 29 684**US gallons 6 261 - 7 051* - 7 842**

Kilograms(density =0.785 kg/l)

18 604 - 20 953* - 23 301**

Usable Fuel Capacity

Pounds 41 015 - 46 193* - 51 370**Cubic meters 418Pressurized Fuselage

Volume (A/C nonequipped)

Cubic feet14 762

Cubic meters 155Passenger CompartmentVolume Cubic feet 5 474

Cubic meters 9Cockpit VolumeCubic feet 318Cubic meters 22.81Usable Volume, FWD CCCubic feet 806Cubic meters 23.03Usable Volume, AFT CCCubic feet 814Cubic meters 5.88Usable Volume, Bulk CCCubic feet 208Cubic meters 25.42Water Volume, FWD CCCubic feet 897.7Cubic meters 25.69Water Volume, AFT CCCubic feet 907.2Cubic meters 7.76Water Volume, Bulk CCCubic feet 274

* OPTION: 1 ACT** OPTION: 2 ACT

2-1-1Page 4

Jun 01/12


2-2-0 General Aircraft Dimensions

**ON A/C A321-100 A321-200

General Aircraft Dimensions

1. This section provides General Aircraft Dimensions.

2-2-0Page 1

Jun 01/12


**ON A/C A321-100 A321-200

RELATED TO AIRCRAFT ATTITUDE AND WEIGHT

12.45 m(40.85 ft)

34.10 m(111.88 ft)

16.90 m(55.45 ft)

5.07 m(16.63 ft)

5.87

m(1

9.26

ft)

4.14

m(1

3.58

ft)

N_AC_020200_1_0050101_01_03

7.59 m(24.90 ft)

0.93 m(3.05 ft)

0.50 m(1.64 ft)

8.97 m(29.43 ft)

General Aircraft DimensionsWing Tip Fence (Sheet 1 of 4)

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

2-2-0Page 2

Jun 01/12


**ON A/C A321-100 A321-200

RELATED TO AIRCRAFT ATTITUDE AND WEIGHTN_AC_020200_1_0050104_01_00

44.50 m

(146 ft)

15.46 m

(50.72 ft)

15.39 m

(50.49 ft)

CFM56

V2500

11.9

1 m

(39.

07 ft

)

8.30

m

(27.

23 ft

)

5.75

m

(18.

86 ft

)

3.95

m

(12.

96 ft

)

4.87

m

(15.

98 ft

)

General Aircraft DimensionsWing Tip Fence (Sheet 2 of 4)

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

2-2-0Page 3

Jun 01/12


**ON A/C A321-100 A321-200


16.90 m

(55.45 ft)

5.07 m

(16.63 ft)

5.87

m

(19.

26 ft

)

4.14

m

(13.

58 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)

N_AC_020200_1_0050103_01_01

8.97 m(29.43 ft)

3.79 m(12.43 ft)

2.43 m(7.97 ft)

General Aircraft DimensionsSharklet (Sheet 3 of 4)

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

2-2-0Page 4

Jun 01/12


**ON A/C A321-100 A321-200


44.50 m(146 ft)

15.46 m(50.72 ft)

15.39 m(50.49 ft)

CFM56

V2500

11.9

1 m

(39.

07 ft

)

8.30

m

(27.

23 ft

)

5.75

m(1

8.86

ft)

3.95

m

(12.

96 ft

)

4.87

m

(15.

98 ft

)

N_AC_020200_1_0050105_01_00

16.2

9 m

(53.

44 ft

)1.

61 m

(5.2

8 ft)

3.22 m(10.56 ft)

1.64 m(5.38 ft)

27.72 m(90.94 ft)

General Aircraft DimensionsSharklet (Sheet 4 of 4)

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

2-2-0Page 5

Jun 01/12


2-3-0 Ground Clearances

**ON A/C A321-100 A321-200

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 A321-100 A321-200

A

CG 25%m

FWD CG 17.5%ft

FWD CG 19% AFT CG 36.9%

11.486.896.046.53

19.6220.112.332.925.779.02

10.4311.557.41

BC1C2D1D2

E (CFM)E (IAE)

FF1F2F3G

3.392.001.731.885.876.030.600.781.652.643.073.412.16

3.482.071.791.825.935.960.610.791.632.633.053.382.10

3.472.051.781.825.925.960.600.781.622.623.05

12.24H 3.63 3.53

3.382.093.53

39.70J 11.99 11.86 11.8512.83K1 3.80 3.77 3.7616.01K2 4.77 4.74 4.7318.31L 5.47 5.34 5.347.64M 2.22 2.14 2.14

13.16N 3.90 3.91 3.9014.11P 4.19 4.30 4.29

AFT CG 38%

15.94Q 4.76 4.61 4.6111.71R 3.46 3.49 3.48

3.391.991.731.875.876.010.590.771.642.633.063.402.143.61

11.973.794.765.452.203.894.194.733.45

P B C1 R E N G D2 M Q JD1 C2

L F1 F2 F3 K1 K2F

3.502.101.841.995.986.130.710.891.762.753.183.522.263.73

12.103.914.885.582.334.014.304.863.57

11.126.565.686.17

19.2619.781.972.565.418.6610.0711.197.0911.9139.3412.4715.6517.957.28

12.8013.7515.6211.35

11.426.795.875.97

19.4619.552.002.595.358.6310.0111.096.8911.5838.9112.3715.5517.527.02

12.8314.1115.1211.45

11.126.535.686.14

19.2619.721.942.535.388.63

10.0411.157.02

11.8439.2712.4315.6217.887.22

12.7613.7515.5211.32

11.386.735.845.9719.4219.551.972.565.318.6010.0111.096.8611.5838.8812.3415.5217.527.02

12.8014.0715.1211.42

m ft m ft m ft m ft4.132.712.432.436.586.581.241.422.263.253.684.012.714.13

12.454.385.355.932.754.544.965.204.13

13.558.897.977.97

21.5921.594.074.667.41

10.6612.0713.168.8913.5540.8514.3717.5519.469.02

14.8916.2717.0613.55

m ft

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

A/C JACKED FDLA/CCONFIG−URATION

47 t 89 tMRW

94 tMRW

= 4.60 m(15.09 ft)

N_AC_020300_1_0050101_01_04

A H

Ground ClearancesFIGURE-2-3-0-991-005-A01

2-3-0Page 2

Jun 01/12


**ON A/C A321-100 A321-200

N_AC_020300_1_0300101_01_00

A

CG 25%m

FWD CG 17.5%ft

FWD CG 19% AFT CG 36.9%

11.486.896.046.53

19.6220.112.332.925.779.02

10.4311.557.41

BC1C2D1D2

E (CFM)E (IAE)

FF1F2F3G

3.392.001.731.885.876.030.600.781.652.643.073.412.16

3.482.071.791.825.935.960.610.791.632.633.053.382.10

3.472.051.781.825.925.960.600.781.622.623.05

12.24H 3.63 3.53

3.382.093.53

39.70J 11.99 11.86 11.8513.71K1 4.07 4.04 4.0322.38K2 6.71 6.68 6.6718.31L 5.47 5.34 5.347.64M 2.22 2.14 2.14

13.16N 3.90 3.91 3.9014.11P 4.19 4.30 4.29

AFT CG 38%

15.94Q 4.76 4.61 4.6111.71R 3.46 3.49 3.48

3.391.991.731.875.876.010.590.771.642.633.063.402.143.61

11.974.066.705.452.203.894.194.733.45

3.502.101.841.995.986.130.710.891.762.753.183.522.263.73

12.104.186.825.582.334.014.304.863.57

11.126.565.686.17

19.2619.781.972.565.418.6610.0711.197.0911.9139.3413.3522.0117.957.28

12.8013.7515.6211.35

11.426.795.875.97

19.4619.552.002.595.358.6310.0111.096.8911.5838.9113.2521.9217.527.02

12.8314.1115.1211.45

11.126.535.686.14

19.2619.721.942.535.388.63

10.0411.157.02

11.8439.2713.3221.9817.887.22

12.7613.7515.5211.32

11.386.735.845.9719.4219.551.972.565.318.6010.0111.096.8611.5838.8813.2221.8817.527.02

12.8014.0715.1211.42

m ft m ft m ft m ft4.132.712.432.436.586.581.241.422.263.253.684.012.714.13

12.454.657.295.932.754.544.965.204.13

13.558.897.977.9721.5921.594.074.667.41

10.6612.0713.168.8913.5540.8515.2623.9219.469.02

14.8916.2717.0613.55

m ft

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

A/C JACKED FDLA/CCONFIG−URATION

47 t 89 tMRW

94 tMRW

= 4.60 m(15.09 ft)

F3F2F1FL

P A B C1 ER G M H Q JD1

K2

K1

C2N D2

Ground ClearancesGround Clearances with Sharklets

FIGURE-2-3-0-991-030-A01

2-3-0Page 3

Jun 01/12


**ON A/C A321-100 A321-200

m ft m m

A

B

C

D

A/C IN MAINTENANCECONFIGURATION MID CG

MAXIMUM RAMPWEIGHT FWD CG

MAXIMUM RAMPWEIGHT AFT CG

HEIGHT FROM GROUND

E

H

J

F

G

1.95

2.84

2.71

3.74

1.83

2.73

2.60

3.62

1.80

2.70

2.57

3.58

6.40 6.00 5.91

11.7511.8812.27

9.32

8.89

8.96

8.53

8.86

8.43

2.49

3.53

2.37

3.41

2.34

3.37 11.0611.1911.58

8.17 7.78 7.68

1.91 1.79 1.76 5.775.876.27

2.31

2.96

2.19

2.84

2.15

2.79 9.159.329.71

7.58 7.19 7.05

ft ft

N_AC_020300_1_0220101_01_00

EB CFD AGJ H

Ground ClearancesFlaps and Flap Track Fairings When Flaps Fully Extended

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

2-3-0Page 4

Jun 01/12


**ON A/C A321-100 A321-200

2.68

3.07

3.46

2.57

2.96

3.35

2.56

2.94

3.32

8.79 8.43 8.40

10.07

11.35

9.71

10.99

9.65

10.89

L MK

N_AC_020300_1_0230101_01_00

m ft m ft m ft

K

L




HEIGHT FROM GROUND

M

Ground ClearancesFlap Track Fairings Up

FIGURE-2-3-0-991-023-A01

2-3-0Page 5

Jun 01/12


**ON A/C A321-100 A321-200

4.15

3.81

4.03

3.70 12.14

13.22 4.00

3.67 12.04

13.1213.62

12.50

N P

N_AC_020300_1_0240101_01_00

m ft m ft m ft




HEIGHT FROM GROUND

N

P

Ground ClearancesAileron Down

FIGURE-2-3-0-991-024-A01

2-3-0Page 6

Jun 01/12


**ON A/C A321-100 A321-200

4.04

3.74

14.63

14.24

13.39

13.25

12.27

4.48

4.35

4.23

4.10

3.97

3.94

3.63

14.70

14.27

13.88

13.45

13.02

12.93

11.91

4.45

4.32

4.20

4.07

3.95

3.92

3.61

14.60

14.17

13.78

13.35

12.96

12.86

11.84

13.784.20

4.34

4.46

4.59 15.06

4.08

VR T U W X Y

N_AC_020300_1_0250101_01_00

m ft m m




HEIGHT FROM GROUND

X

Y

ft ft

4.33

4.53

14.21

4.42

4.22

14.50

13.85

4.37

4.19

14.34

13.75

14.86

SQ

Q

R

S

V

W

T

U

Ground ClearancesAileron Up and Spoilers 1 to 5 Extended

FIGURE-2-3-0-991-025-A01

2-3-0Page 7

Jun 01/12


**ON A/C A321-100 A321-200

C’ E’

m ft m ft m ft



HEIGHT FROM GROUND

2.58

2.98

3.07

2.47

2.88

2.96

2.50

2.89

2.97

8.46 8.10 8.20

9.78

10.07

9.45

9.71

9.48

9.74

A’Z

B’ D’ F’ G’ H’

H’

J’

3.36

3.61

3.85

4.08 13.39

12.63

11.84

11.02 3.25

3.50

3.74

3.96 12.99

12.27

11.48

10.66 3.25

3.49

3.72

3.94 12.93

12.20

11.45

10.66

N_AC_020300_1_0260101_01_00


J’

Z

A’

D’

B’

C’

E’

F’

G’

Ground ClearancesSlats Extended

FIGURE-2-3-0-991-026-A01

2-3-0Page 8

Jun 01/12


2-4-0 Interior Arrangements

**ON A/C A321-100 A321-200

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 A321-100 A321-200

Typical Configuration

1. This section gives the typical interior configuration.

2-4-1Page 1

Jun 01/12


**ON A/C A321-100 A321-200

G

FW

D P

AS

SE

NG

ER

EM

ER

GE

NC

Y E

XIT

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

/CR

EW

DO

OR

FW

D P

AS

SE

NG

ER

AF

T P

AS

SE

NG

ER

220

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

AA

AA

G L

AA

L LL

A

ITE

MD

ES

IGN

AT

ION

GG

ALL

EY

(2)

LLA

VA

TO

RY

(4)

AA

TT

EN

DA

NT

SE

AT

(7)

N_AC_020401_1_0040101_01_01

Typical ConfigurationTypical Configuration Single-Class, High Density

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

2-4-1Page 2

Jun 01/12


**ON A/C A321-100 A321-200

FW

D P

AS

SE

NG

ER

EM

ER

GE

NC

Y E

XIT

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

FW

D P

AS

SE

NG

ER

EM

ER

GE

NC

Y E

XIT

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

16 S

UP

ER

FIR

ST

16

9 E

CO

NO

MY

PA

SS

EN

GE

R S

EA

TS

(18

5 T

OT

AL)

SE

AT

PIT

CH

ES

: FIR

ST

36

in E

CO

NO

MY

32

in

ITE

MD

ES

IGN

AT

ION

GG

ALL

EY

(3)

LLA

VA

TO

RY

(4)

AA

TT

EN

DA

NT

SE

AT

(6)

G LL

LLA

AA A

A

A

G

G

N_AC_020401_1_0060101_01_05

Typical ConfigurationTypical Configuration Two-Class

FIGURE-2-4-1-991-006-A01

2-4-1Page 3

Jun 01/12


2-5-0 Passenger Compartment Cross Section

**ON A/C A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200


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 A321-100 A321-200


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 A321-100 A321-200


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 A321-100 A321-200

Cargo Compartments

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

2-6-0Page 1

Jun 01/12


**ON A/C A321-100 A321-200

1.81

m(7

1.26

in)

8.15

m(3

20.8

7 in

)11

.4 m

(448

.82

in)

0.86

m(3

3.85

in)

1.81

m(7

1.26

in)

FW

D C

AR

GO

CO

MP

AR

TM

EN

T(5

CO

NT

AIN

ER

S)

AF

T C

AR

GO

CO

MP

AR

TM

EN

T(5

CO

NT

AIN

ER

S)

BU

LK C

AR

GO

CO

MP

AR

TM

EN

T

FR

24A

FR

35.5

FR

47.2

FR

59F

R65

N_AC_020600_1_0040101_01_00

Cargo CompartmentsLocations, Dimensions and Loading Combinations

FIGURE-2-6-0-991-004-A01

2-6-0Page 2

Jun 01/12


2-7-0 Door Clearances

**ON A/C A321-100 A321-200

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 A321-100 A321-200

Forward Passenger / Crew Doors

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

2-7-1Page 1

Jun 01/12


**ON A/C A321-100 A321-200

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)

SEECHAPTER

2.375 m(7 ft 9.48 in)

2−3

1.85 m(6 ft 0.82 in)

0.03 m(1.18 in)

N_AC_020701_1_0040101_01_00

Doors ClearancesForward Passenger / Crew Doors

FIGURE-2-7-1-991-004-A01

2-7-1Page 2

Jun 01/12


2-7-2 Emergency Exits

**ON A/C A321-100 A321-200

Emergency Exits

1. This section gives emergency exits doors clearances.

2-7-2Page 1

Jun 01/12


**ON A/C A321-100 A321-200

2.38 m(7 ft 9.69 in)

2.36 m(7 ft 8.9 in)

0.39 m(1 ft 3.34 in)

0.39 m(1 ft 3.34 in)

0.4 m(1 ft 3.74 in)

0.56 m(1 ft 10 in)

CENTER OF FREE AISLE

13.844 m(45 ft 5 in)

24.791 m(81 ft 4 in)

0.83 m(2 ft 8.67 in)

1.73 m(5 ft 8.1 in)

FROM AIRCRAFT NOSE

FREE AISLE

FREE AISLE FREE AISLE

0.76 m(2 ft 5.91 in)

0.76 m(2 ft 5.91 in)

0.04 m(1.57 in)

0.04 m(1.57 in)

0.56 m(1 ft 10 in)

0.83 m(2 ft 8.67 in)

FROM AIRCRAFT NOSE

CENTER OF

LIMITCRITICAL CLEARANCECRITICAL CLEARANCE

LIMIT

1.73 m(5 ft 8.1 in)

0.43 m(1 ft 4.92 in)

1.52 m(4 ft 11.8 in)

(TOP OF FLOOR)1.52 m

(4 ft 11.8 in)

1.85 m(7.03 in)

2.36 m(7 ft 8.9 in)

A

A

B

B

A A

FWD

N_AC_020702_1_0050101_01_00

B B

Doors ClearancesEmergency Exits

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

2-7-2Page 2

Jun 01/12


2-7-3 Aft Passenger / Crew Doors

**ON A/C A321-100 A321-200

Aft Passenger / Crew Doors

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

2-7-3Page 1

Jun 01/12


**ON A/C A321-100 A321-200

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

36.57 m(119 ft 11.7 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

FWD

A A

SEE

2−3CHAPTER

A

A

N_AC_020703_1_0040101_01_00

Doors ClearancesAft Passenger / Crew DoorsFIGURE-2-7-3-991-004-A01

2-7-3Page 2

Jun 01/12


2-7-4 Forward Cargo Compartment Doors

**ON A/C A321-100 A321-200

Forward Cargo Compartment Door

1. This section gives forward cargo compartment door clearances.

2-7-4Page 1

Jun 01/12


**ON A/C A321-100 A321-200

8.16 m(26 ft 9.25 in)

1.82 m(5 ft 11.65 in)

1.24 m(4 ft 0.81 in)

3.945 m(12 ft 11.3 in)

1.495 m(4 ft 10.84 in)

CFM ENGINE = 6.39 m (20 ft 11.56 in)V2500 ENGINE = 6.3 m (20 ft 8 in)

(FROM NOSE)

FWD

2.71 m(8 ft 10.69 in)

A

A

A A

2−3

SEECHAPTER

N_AC_020704_1_0040101_01_01

Doors ClearancesForward Cargo Compartment Door

FIGURE-2-7-4-991-004-A01

2-7-4Page 2

Jun 01/12


2-7-5 Aft Cargo Compartment Doors

**ON A/C A321-100 A321-200

Aft Cargo Compartment Door

1. This section gives Aft cargo compartment door clearances.

2-7-5Page 1

Jun 01/12


**ON A/C A321-100 A321-200

1.82 m(5 ft 11.65 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

29.62 m(97 ft 2.13 in)

A

A

A A

4.69 m(15 ft 4.64 in)

(FROM NOSE)

N_AC_020705_1_0040101_01_00

Doors ClearancesAft Cargo Compartment DoorFIGURE-2-7-5-991-004-A01

2-7-5Page 2

Jun 01/12


2-7-6 Bulk Cargo Compartment Doors

**ON A/C A321-100 A321-200

Bulk Cargo Compartment Door

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

2-7-6Page 1

Jun 01/12


**ON A/C A321-100 A321-200

0.95 m(3 ft 1.39 in)

0.89 m(2 ft 11 in)

FWD

2.19 m(7 ft 2.22 in)

8.76 m(28 ft 8.88 in)

0.77 m

(2 ft 6.31 in)A

A

2−3

SEECHAPTER A A

N_AC_020706_1_0020101_01_01

Doors ClearancesBulk Cargo Compartment Door

FIGURE-2-7-6-991-002-A01

2-7-6Page 2

Jun 01/12


2-7-7 Main Landing Gear Doors

**ON A/C A321-100 A321-200

Main Landing Gear Doors

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

2-7-7Page 1

Jun 01/12


**ON A/C A321-100 A321-200

20.62 m(67.6 ft)

1.826 m

(6 ft)

A

GROUND LINE

0.207 m(8.14 in)

0.485 m(1 ft 7.09 in)

NOTE: VALUE OF CG: 25% RC.AIRCRAFT

1.23 m(4 ft 0.42 in)

0.14 m(5.51 in)

84°

1.942 m

(6 ft 4.45 in)

1.761 m(5 ft 9.32 in)

A

N_AC_020707_1_0050101_01_02

Doors ClearancesMain Landing Gear Doors

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

2-7-7Page 2

Jun 01/12


2-7-8 Radome

**ON A/C A321-100 A321-200

Radome

1. This section gives the radome clearances.

2-7-8Page 1

Jun 01/12


**ON A/C A321-100 A321-200

0.63 m(2 ft 0.79 in)

1.54 m(5 ft 0.62 in)

STA 3500FR1

65°

N_AC_020708_1_0040101_01_00

Doors ClearancesRadome

FIGURE-2-7-8-991-004-A01

2-7-8Page 2

Jun 01/12


2-7-9 APU and Nose Landing Gear Doors

**ON A/C A321-100 A321-200

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 A321-100 A321-200

FR80

FR84

3.42

m(1

1 ft

2.64

in)

4.05

m(1

3 ft

3.44

in)

NOTE: VALUE OF CG: 25% RC.

1.5

m(4

ft 1

1 in

)

1.4

m(4

ft 7

.11

in)

N_AC_020709_1_0040101_01_00

Doors ClearancesAPU and Nose Landing Gear Doors

FIGURE-2-7-9-991-004-A01

2-7-9Page 2

Jun 01/12


2-8-0 Escape Slides

**ON A/C A321-100 A321-200

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 each emergency exit door (total four). Single lane escape slides are installed at

FWD/AFT emergency door.

2-8-0Page 1

Jun 01/12


**ON A/C A321-100 A321-200

FWD CABIN ESCAPE SLIDE

AFT CABIN

FWD EMERGENCY ESCAPE SLIDE

ESCAPE SLIDE

AFT EMERGENCY ESCAPE SLIDE

N_AC_020800_1_0070101_01_00

Escape SlidesLocation

FIGURE-2-8-0-991-007-A01

2-8-0Page 2

Jun 01/12


**ON A/C A321-100 A321-200

EMERGENCY DESCENT DEVICETHROUGH WINDOW OPENING

N_AC_020800_1_0080101_01_00

GRID EQUALS 1 m (3.28 ft) IN REALITY

Escape SlidesLocation

FIGURE-2-8-0-991-008-A01

2-8-0Page 3

Jun 01/12


2-9-0 Landing Gear

**ON A/C A321-100 A321-200

Landing Gear

1. General

The landing gear is of the conventional retractable tricycle type comprising:- Two main gears with twin wheel- 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.

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.

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

2-9-0Page 1

Jun 01/12


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 A321-100 A321-200

TORQUELINKS

DOWNLOCKACTUATOR

MAIN FITTING

SHOCK ABSORBER

SIDE STAY

D

ACTUATING CYLINDER

LOCK STAY

DAMPER

A

MAIN DOOR SHOWN OPEN IN GROUND MAINTENANCE POSITION.NOTE:

E

N_AC_020900_1_0160101_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-2-9-0-991-016-A01

2-9-0Page 3

Jun 01/12


**ON A/C A321-100 A321-200

DOORACTUATINGCYLINDER

FLAG

LOCKSTAYACTUATINGCYLINDER

GROUND LOCK SLEEVE

FLAG

BC

LOCKINGPIN

LOCKINGPIN

N_AC_020900_1_0160102_01_00

BOTTOM FILLING ANDCHARGING CONNECTIONMS28889

EDEXAMPLE

TOP FILLING AND CHARGING CONNECTION MS28889

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

FIGURE-2-9-0-991-016-A01

2-9-0Page 4

Jun 01/12


**ON A/C A321-100 A321-200

Y=COMPRESSED

EXTENDED

58.3

0 %

AM

C

3 795 mm

80°30RETRACTION

ANGLE

(36.50 in)927.10 mm

2 868.70 mm(112.94 in)

2 214 mm(87.17 in)

X= 24 513.89 mm(965.11 in)

470.52 mm(18.52 in)

(149.41 in)

N_AC_020900_1_0170101_01_00

Landing GearMain Landing Gear Dimensions - Twin Wheel

FIGURE-2-9-0-991-017-A01

2-9-0Page 5

Jun 01/12


**ON A/C A321-100 A321-200

N_AC_020900_1_0180101_01_00

ACTUATINGCYLINDER

NOSE WHEELSTEERINGSERVO CONTROL

STEERINGACTUATINGCYLINDER

TORQUELINK

DOWNLOCKPROXIMITY

DETECTORS

SHOCKABSORBER

TOWINGFITTING

LEG DOOR

AFT DOORS

ASSEMBLYFITTING

FWD DOORS

CONTROL ROD

DOORACTUATINGCYLINDER

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-2-9-0-991-018-A01

2-9-0Page 6

Jun 01/12


**ON A/C A321-100 A321-200

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

FLAG

DOWNLOCKSAFETY PIN

LOCKSTAY

BC

D

OPERATIONAL)CONNECTION MS28889FILLING AND CHARGING

N_AC_020900_1_0180102_01_00

Landing GearNose Landing Gear (Sheet 2 of 2)

FIGURE-2-9-0-991-018-A01

2-9-0Page 7

Jun 01/12


**ON A/C A321-100 A321-200

N_AC_020900_1_0190101_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-2-9-0-991-019-A01

2-9-0Page 8

Jun 01/12


**ON A/C A321-100 A321-200

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 9

Jun 01/12


**ON A/C A321-100 A321-200

=

==

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)

24.5

2 m

(80.

45 ft

)

24.3

7 m

(79.

95 ft

)

7.59

m(2

4.90

ft)

=

6.49

m(2

1.29

ft) 3.

79 m

(12.

43 ft

)3.76

m(1

2.34

ft) 2.

95 m

(9.6

8 ft)

2.5

m(8

.20

ft)

MA

IN J

AC

KIN

G P

OIN

T

MA

IN J

AC

KIN

G P

OIN

TM

AIN

JA

CK

ING

PO

INT

FROM X0

FW

D J

AC

KIN

G P

OIN

T

N_AC_020900_1_0260101_01_00

Landing Gear Maintenance PitsMaintenance Pit EnvelopesFIGURE-2-9-0-991-026-A01

2-9-0Page 10

Jun 01/12


**ON A/C A321-100 A321-200

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)

24

.52

m(8

0.45

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_0270101_01_00

Landing Gear Maintenance PitsMaintenance Pit EnvelopesFIGURE-2-9-0-991-027-A01

2-9-0Page 11

Jun 01/12


2-10-0 Exterior Lighting

**ON A/C A321-100 A321-200

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 A321-100 A321-200

6 75

13

10

9

8

8

2

12

4

N_AC_021000_1_0130101_01_00

11

1

3

111

3

RH

LH

RH

LH

Exterior LightingFIGURE-2-10-0-991-013-A01

2-10-0Page 2

Jun 01/12


**ON A/C A321-100 A321-200

1

2

3

55

N_AC_021000_1_0140101_01_00

7


2-10-0Page 3

Jun 01/12


**ON A/C A321-100 A321-200

12

11

1313

4

11

9

N_AC_021000_1_0150101_01_00

6

10


2-10-0Page 4

Jun 01/12


**ON A/C A321-100 A321-200

1415 15

8 8

N_AC_021000_1_0200101_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 A321-100 A321-200

Antennas and Probes Location

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

2-11-0Page 1

Jun 01/12


**ON A/C A321-100 A321-200

RADIO ALTIMETER(2)

DME(2)PITOT PROBE(1)

PITOT PROBE(3)

DME(1)

TAT PROBE

VHF(1)

TAT PROBE

PITOT PROBE(2)

ADF(1)

ATC(1)

GPS(2)

GPS(1)

VHF(3)

ATC(2)

RADIO ALTIMETER(1)

VHF(2)

WEATHER RADAR

EMERGENCY STATIC PROBE

AOA SENSOR(3) STBY

AOA SENSOR(1)

TCAS TOPELT

MARKER

TCAS BOTTOM

STATIC PROBE(1)

STATIC PROBE(2)

LOCGLIDE

HF

VOREMERGENCY STATIC PROBE

AOA SENSOR(2)

STATIC PROBE(2)

STATIC PROBE(1)

ATC(4)

ATC(3)

NOTE: DEPENDING ON AIRCRAFT CONFIGURATIONN_AC_021100_1_0040101_01_00

Antennas and ProbesLocation

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

2-11-0Page 2

Jun 01/12


2-12-0 Power Plant

**ON A/C A321-100 A321-200

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 A321-100 A321-200

AIR INTAKE FIXEDON ACCESS DOOR

CUT OUT SEALED WITHLABYRINTH GASKET

FRONTFIREWALL

FIREWALL

FIREWALL RH

LOUVER LH

REARFIREWALL

CUT OUT SEALED WITHLABYRINTH GASKET

LH ACCESS DOOR NOTE:

B

UPPER

A

/FR80

/ FR84

NOT SHOWN FOR CLARITY

Z310

STA45879

STA44229

A

315AL

RH ACCESS DOOR316AR

N_AC_021200_1_0070101_01_00

Auxiliary Power UnitAccess Doors

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

2-12-0Page 2

Jun 01/12


**ON A/C A321-100 A321-200

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

FR

87/

ST

A47

047

FR

84/

ST

A45

879

FR

80/

ST

A44

229

FR

78/

ST

A43

591

FR

77/

ST

A43

479

N_AC_021200_1_0080101_01_00

Auxiliary Power UnitGeneral Layout

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

2-12-0Page 3

Jun 01/12


**ON A/C A321-100 A321-200

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 A321-100 A321-200

A

POINTFWD HOISTING

POINTFWD HANDLING

B

1 125 mm(44.28 in)

TURBINE FRAME

COMBUSTOR

COMPRESSOR

2 600 mm(102.36 in)

2 943 mm(115.87 in)

986 mm(38.82 in)

DIA

1 820 mm(71.65 in)

2 145 mm(84.45 in)

1 978 mm(77.87 in)

989 mm(38.94 in)

1 130 mm(44.49 in)

B

HANDLING POINTAFT HOISTING AND

BOOSTERFAN AND

LPTURBINE

DRIVEACCESSORY

AGB

HP

TGBTURBINE

A

N_AC_021200_1_0350101_01_00

Power Plant HandlingMajor Dimensions - CFM56 Series Engine

FIGURE-2-12-0-991-035-A01

2-12-0Page 6

Jun 01/12


**ON A/C A321-100 A321-200

FAN COWL

CENTERBODY

FANREVERSER

6°

(3.9 ft)

1.8 m(5.9 ft)

2.07 m(6.8 ft)

2.1 m(6.9 ft)

BLOCKER DOOREXTENDED

PRIMARYNOZZLE

15.46 m(50.7 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)

1.6 m(5.2 ft)

ENGINE AIRINLET COWL

A

A

B

B

C

C

D

D

0.57 m(1.9 ft)

A A

B B D DC CN_AC_021200_1_0360101_01_00

1.2 m

1.9 m(6.2 ft)

Power Plant HandlingMajor Dimensions - CFM56 Series Engine

FIGURE-2-12-0-991-036-A01

2-12-0Page 7

Jun 01/12


**ON A/C A321-100 A321-200

A

0.55 m(1.8 ft)

C

B

A B C

VIEWCOWLING

AFT

VIEWCOWLING

FWD

m (ft)

42°27

55°15

40°40

52°56

1.8 (5.9)

2.0 (6.6)

1.8 (5.9 )

2.0 (6.6)

1.5 (4.9)

1.8 (5.9)

1.4 (4.6)

1.7 (5.6)

1.3 (4.3)

1.7 (5.6)

1.3 (4.3)

1.6 (5.2)

NOTE: APPROXIMATE DIMENSIONS

N_AC_021200_1_0370101_01_00

Power Plant HandlingFan Cowls - CFM56 Series Engine

FIGURE-2-12-0-991-037-A01

2-12-0Page 8

Jun 01/12


**ON A/C A321-100 A321-200

3.7 m(12.1 ft)

3.3 m(10.8 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

0.5 m(1.6 ft)

0.7 m(2.3 ft)

1 m(3.3 ft)

45°35°

1 m(3.3 ft)

N_AC_021200_1_0380101_01_00

Power Plant HandlingThrust Reverser Cowls - CFM56 Series Engine

FIGURE-2-12-0-991-038-A01

2-12-0Page 9

Jun 01/12


**ON A/C A321-100 A321-200

N_AC_021200_1_0390101_01_00

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

Power Plant HandlingMajor Dimensions - IAE V2500 Series Engine

FIGURE-2-12-0-991-039-A01

2-12-0Page 10

Jun 01/12


**ON A/C A321-100 A321-200

0.5°6°

C

C

D

D

E

E

F

F

U

V

5.26 m(17.26 ft)

1.50 m(4.92 ft)

5.25 m(17.22 ft)

W

B

BA

A

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

TCH 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 −−−− −−−−

15.37 m(50.43 ft)

DISTANCE FROMTHE NOSE

A−A

B−B

C−C

D−D

E−E

F−F

NOTE: ALL SIZES GIVEN ON THIS ILLUSTRATION ARE APPROXIMATE

N_AC_021200_1_0400101_01_00

Power Plant HandlingMajor Dimensions - IAE V2500 Series Engine

FIGURE-2-12-0-991-040-A01

2-12-0Page 11

Jun 01/12


**ON A/C A321-100 A321-200

N_AC_021200_1_0410101_01_00

2 m

(6.6 ft)

CLOSEDWL100

1.6 m(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)

APPROXIMATE DIMENSIONSNOTE:

Power Plant HandlingFan Cowls - IAE V2500 Series Engine

FIGURE-2-12-0-991-041-A01

2-12-0Page 12

Jun 01/12


**ON A/C A321-100 A321-200

APPROXIMATE DIMENSIONSNOTE:N_AC_021200_1_0420101_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-2-12-0-991-042-A01

2-12-0Page 13

Jun 01/12


2-13-0 Leveling, Symmetry and Alignment

**ON A/C A321-100 A321-200

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 A321-100 A321-200

N_AC_021300_1_0050101_01_00

12

11

FR30

FR48

2LH

RIB10

2RH

RIB10

FR47

FR32

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

2-13-0Page 2

Jun 01/12


2-14-0 Jacking

**ON A/C A321-100 A321-200

Jacking for Maintenance

1. Jacking for Maintenance

A. General

The A321 aircraft can be jacked:- at no more than the maximum permitted aircraft weight for jacking (69 000 kg (152 119

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 middle 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)

33 400 daN(75 086 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 69 000 kg (152 119 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 FuselageFrames which are capable of supporting loads are noted below as well as the maximumpermissible loads for each frame.

Under the Fuselage

Shoring Fittings (Per Side)

FR 8 3 000 daN (6 744 lbf)

FR 15 5 000 daN (11 240 lbf)

FR 21 2 000 daN (4 496 lbf)

FR 33 1 700 daN (3 822 lbf)

FR 62/63 4 200 daN (9 442 lbf)

2-14-0Page 2

Jun 01/12


Under the Fuselage

Shoring Cradles

FR 8 1 700 daN (3 822 lbf)

FR 9 3 300 daN (7 419 lbf)

FR 29 to 34 1 330 daN (2 990 lbf) each

FR 56 to 60 2 600 daN (5 845 lbf) each

Under the Fuselage

Safety Stay Pad

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

B. Under the Wings

Shoring cradles are used when it is necessary to stress-jack the aircraft to carry out certainmaintenance and repair work. These are used to oppose the deflections of the wings and reducethe stresses to 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 5.

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 5 shows the maximum load limit allowed at each jack pad when the wings are supportedby the cradles. These load limits apply to all A321 aircraft and variants.

The maximum permitted load, as specified in Table 5, 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.

2-14-0Page 3

Jun 01/12


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.

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 A321-100 A321-200

2.74 m(8.99 ft)

FWD JACKINGPOINT

21.83 m(71.62 ft)

WING JACKINGPOINT

6.5 m(21.33 ft)

WING JACKINGPOINT

SAFETYPOINT

39.5 m(129.59 ft)

CL

N_AC_021400_1_0380101_01_00

Jacking for MaintenanceJacking Point Location

FIGURE-2-14-0-991-038-A01

2-14-0Page 5

Jun 01/12


**ON A/C A321-100 A321-200

A

N_AC_021400_1_0390101_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-2-14-0-991-039-A01

2-14-0Page 6

Jun 01/12


**ON A/C A321-100 A321-200

A

A

N_AC_021400_1_0400101_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-2-14-0-991-040-A01

2-14-0Page 7

Jun 01/12


**ON A/C A321-100 A321-200

Z−748.44

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

X =

42

040

A

A

126.15 mm

N_AC_021400_1_0410101_01_00

(4.97 in)

Jacking for MaintenanceSafety Stay

FIGURE-2-14-0-991-041-A01

2-14-0Page 8

Jun 01/12


**ON A/C A321-100 A321-200

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

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:

M

L

L M

FLAT TIRES

AND RETRACTED LANDING GEARS

AND FLAT TIRES

1 560 mm(61.42 in)

2 846 mm(112.05 in)

3 183 mm(125.31 in)

2 620 mm(103.15 in)

3 772 mm(148.50 in)

3 859 mm(151.93 in)

1 931 mm(76.02 in)

3 082 mm(121.34 in)

3 169 mm(124.76 in)

1 545 mm(60.83 in)

2 761 mm(108.70 in)

2 976 mm(117.17 in)

N

N

N_AC_021400_1_0420101_01_00

Jacking for MaintenanceJacking Design

FIGURE-2-14-0-991-042-A01

2-14-0Page 9

Jun 01/12


**ON A/C A321-100 A321-200

80

70

60

50

40

30

200 3 4 5 6 7 8 9 101 2

30

35

40

45

50

55

60

65

70

75

80051015202530

354045

20

30

40

50

60

70

80

AIR

CR

AF

T W

EIG

HT

(kg

x 1

000)

AIRCRAFT CG (%RC)

PERMISSIBLE WIND SPEED (km/h)

LOA

D O

N W

ING

JA

CK

ING

PO

INT

S (

kg x

100

0)

LOAD ON FORWARD FUSELAGE JACKING POINT (kg x 1000)

TIP UPSECURITYMARGIN

ASSUME AIRCRAFT WITH GROSS WEIGHT OF 67 500 kg AND CENTER OF GRAVITYAT 23 % RC . THE REACTION AT THE WING JACKING POINTS IS 62 750 kg(31 375 kg PER SIDE) AND THE REACTION AT THE FORWARD FUSELAGEJACKING POINT IS 4 750 kg . IF THE AIRCRAFT MUST BE LIFTED OUTSIDE THE WIND

A

BC

D

EXAMPLE:

SPEED MUST NOT BE IN EXCESS OF 70 km/h.

N_AC_021400_1_0430101_01_00

A

C

D

B

Loads at the Aircraft Jacking PointsWing Jacking Point and Forward Fuselage Jacking Point

FIGURE-2-14-0-991-043-A01

2-14-0Page 10

Jun 01/12


**ON A/C A321-100 A321-200

(SAFETY STAY)

RIB13

RIB22

RIB13

RIB22

RIB4

FR29

FR56

FR60

FR34

FR9

RIB4

N_AC_021400_1_0440101_01_00

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

FR73 FR74/

Jacking for MaintenanceLocation of Shoring CradlesFIGURE-2-14-0-991-044-A01

2-14-0Page 11

Jun 01/12


**ON A/C A321-100 A321-200

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 69 000 kg (152 119 lb).

2. Main Gear Jacking

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. 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 12

Jun 01/12


**ON A/C A321-100 A321-200

49 x 18 R22

563 mm(22.17 in)

38 mm(1.5 in)

DIA. BALL

25 mm (1 in)

205 mm(8.07 in)

186 mm(7.32 in)

ON THE RIM

200 mm(7.87 in)FULLY

RETRACTED

1 270 x 455 R22

600 mm(23.62 in)FULLY

EXTENDED

TWIN WHEEL TRACK IS 927 mm (36.5 in).NOTE:

N_AC_021400_1_0240101_01_00

FLAT TIRES

INFLATED TIRES

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.

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

FIGURE-2-14-0-991-024-A01

2-14-0Page 13

Jun 01/12


**ON A/C A321-100 A321-200

MLG TIRE 1 270 x 455−R22

655 mm(25.79 in)

TWIN WHEEL TRACK

DOUBLE FLAT MLG TIRES

FORK

CONTOUR OF TIRES ON GROUND

CANTILEVERARM

1 620 mm(63.78 in)

APPROX

205 mm (8.07 in)(186 mm (7.32 in)

ON RIM)

563 mm(22.17 in)

FWD

N_AC_021400_1_0250101_01_00

25 mm(1 in)

927 mm(36.5 in)

MIN25 mm(1 in)MIN

25 mm(1 in)

409 mm(16.1 in)

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

FIGURE-2-14-0-991-025-A01

2-14-0Page 14

Jun 01/12


**ON A/C A321-100 A321-200

N_AC_021400_1_0260101_01_00

40 9050 60 70 8030

45

40

35

30

25

20

15

10

CG 40%CG 30%CG 25%

CG 20%CG 17%

AIRCRAFT WEIGHT

CG POSITION

LOAD AT MLGJACKING POINT

(x 1 000 kg)

180170160150140130120110100908070 x 1 000 lb190 200

x 1 000 kg

Landing Gear Jacking for Wheel ChangeLoads at MLG Jacking PointsFIGURE-2-14-0-991-026-A01

2-14-0Page 15

Jun 01/12


**ON A/C A321-100 A321-200

45

40

35

30

25

20

15

10

50

40 9050 60 70 80

AIRCRAFT WEIGHT

LOAD AT MLGJACKING POINT

(x 1 000 kg) CG POSITION

CG 38.0%

CG 25.0%CG 17.5%

18017016015014013012011010090 x 1 000 lb190 200

x 1 000 kg

N_AC_021400_1_0270101_01_00

Landing Gear Jacking for Wheel ChangeLoads at MLG Jacking PointsFIGURE-2-14-0-991-027-A01

2-14-0Page 16

Jun 01/12


**ON A/C A321-100 A321-200

APPROX326 mm

(12.83 in)38 mm(1.5 in)

DIA. BALLSAE AS 33559

25 mm(1 in)

128 mm(5.07 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)

289 mm MAX (11.38 in)

INFLATED TIRESFLAT TIRES

198 mm(7.8 in)

264 mm MIN (10.39 in)

N_AC_021400_1_0280101_01_00

A

A

Landing Gear Jacking for Wheel ChangeNLG Jacking - Point LocationFIGURE-2-14-0-991-028-A01

2-14-0Page 17

Jun 01/12


**ON A/C A321-100 A321-200

LOAD ATJACKING POINT

(x 1 000 kg) CG POSITION

CG 17.5%

CG 25.0%

CG 38.0%

7

6

5

4

3

2

1

0

8

9

10

9050 60 70 8040

AIRCRAFT WEIGHT

18017016015014013012011010090 x 1 000 lb190 200

x 1 000 kg

N_AC_021400_1_0290101_01_00

Landing Gear Jacking for Wheel ChangeLoads at NLG Jacking PointsFIGURE-2-14-0-991-029-A01

2-14-0Page 18

Jun 01/12


AIRCRAFT PERFORMANCE


**ON A/C A321-100 A321-200

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 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 A321-100 A321-200

Payload / Range

1. Payload / Range

3-2-0Page 1

Jun 01/12



**ON A/C A321-100 A321-200

ISA Conditions

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

3-2-1Page 1

Jun 01/12


**ON A/C A321-100 A321-200

(1000 lbs) (1000 kg)

PAYLOAD

50

40

30

20

10

0

60

70

5

10

15

20

25

30

35

93.5t

89t

RANGE(NM)

500 1000 1500 2000 2500 3000 3500 4000

2000 4000 6000 8000

185 PASSENGERS

NOTE:

RANGE(KM)

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

N_AC_030201_1_0100101_01_00

Payload / RangeCFM56-5B series engine

FIGURE-3-2-1-991-010-A01

3-2-1Page 2

Jun 01/12


**ON A/C A321-100 A321-200

(1000 kg)

PAYLOAD

50

40

30

20

10

0

60

70

5

10

15

20

25

30

35

500 1000 1500 2000 2500 3000 3500 4000

2000 4000 6000 8000


93.5t

89t

(1000 lbs)

185 PASSENGERS

RANGE(NM)

RANGE(KM)

NOTE:

N_AC_030201_1_0110101_01_00

Payload / RangeIAE V2500-A5 series engineFIGURE-3-2-1-991-011-A01

3-2-1Page 3

Jun 01/12


3-3-0 FAR / JAR Takeoff Weight Limitation

**ON A/C A321-100 A321-200

FAR / JAR Take-off Weight Limitation

1. FAR / JAR Take-off Weight Limitation

3-3-0Page 1

Jun 01/12



**ON A/C A321-100 A321-200

ISA Conditions

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

3-3-1Page 1

Jun 01/12


**ON A/C A321-100 A321-200


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

)

RUNWAY LENGTH

1000 ft

1000 m

8

6

4

20

N_AC_030301_1_0070101_01_00

1000 kg

TA

KE

−O

FF

WE

IGH

T

1000 lb

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

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

3-3-1Page 2

Jun 01/12


**ON A/C A321-100 A321-200


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

)

RUNWAY LENGTH

1000 ft

1000 m

8

6

4

2

0

N_AC_030301_1_0080101_01_00

1000 kg

TA

KE

−O

FF

WE

IGH

T

1000 lb

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

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

3-3-1Page 3

Jun 01/12


3-3-2 ISA +15˚C (+59˚F) Conditions

**ON A/C A321-100 A321-200

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 A321-100 A321-200

4

1

6 8 10 12 14

2 3 4 5

16

RUNWAY LENGTH

1000 ft

1000 m


NOTE:

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 ft

)

200

190

180

170

160

150

140

130

120

110

210

220

230

40

50

60

70

80

90

100

110

8

6

4

2

0

N_AC_030302_1_0070101_01_00

1000 kg

TA

KE

−O

FF

WE

IGH

T

1000 lb

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

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

3-3-2Page 2

Jun 01/12


**ON A/C A321-100 A321-200


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

)

RUNWAY LENGTH

1000 ft

1000 m

8

6

4

2

0

N_AC_030302_1_0080101_01_00

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

3-3-2Page 3

Jun 01/12


3-4-0 FAR / JAR Landing Field Length

**ON A/C A321-100 A321-200

FAR / JAR Landing Field Length

1. FAR / JAR Landing Field Length

3-4-0Page 1

Jun 01/12



**ON A/C A321-100 A321-200

ISA Conditions

1. This section gives the landing field length.

3-4-1Page 1

Jun 01/12


**ON A/C A321-100 A321-200

F.A

.R. L

AN

DIN

G F

IELD

LE

NG

TH

GROSS WEIGHT


NOTE:

km 1000 ft

2.5

2

1.5

13

4

5

6

7

8

80 100 120 140 160 180

30 40 50 60 70 80 90

(1000 lb)

GROSS WEIGHT(1000 kg)

10 8 6 42

SEALEVEL

N_AC_030401_1_0070101_01_00

ISA CONDITIONSSLATS 27 DEG.FLAPS 40 DEG.

AIRFIELD ELEVATION(1000 ft)

FAR / JAR Landing Field LengthCFM56 series engine

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

3-4-1Page 2

Jun 01/12


**ON A/C A321-100 A321-200

AIRFIELD ELEVATION(1000 ft)

ISA CONDITIONSSLATS 27 DEG.FLAPS 40 DEG.

SEA

GROSS WEIGHT


NOTE:

km 1000 ft

2.5

2

1.5

13

4

5

6

7

8

80 100 120 140 160 180

30 40 50 60 70 80 90

10 8 6 4

2

(1000 lb)


LEVEL

N_AC_030401_1_0080101_01_00

F.A

.R. L

AN

DIN

G F

IELD

LE

NG

TH

FAR / JAR Landing Field LengthIAE V2500 series engine

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

3-4-1Page 3

Jun 01/12


3-5-0 Final Approach Speed

**ON A/C A321-100 A321-200

Final Approach Speed

1. This section gives the final approach speed.

3-5-0Page 1

Jun 01/12


**ON A/C A321-100 A321-200

10080 100 120 140 160 180 200

GROSS WEIGHT(1000 lb)


110

120

130

140

150

160

C.A.S (Kts)


NOTE:

40 50 60 70 80 90 100

LANDING GEAR EXTENDEDSLATS 27 DEG.FLAPS 40 DEG.

SEA LEVEL

N_AC_030500_1_0070101_01_00

Final Approach SpeedCFM56 series engine

FIGURE-3-5-0-991-007-A01

3-5-0Page 2

Jun 01/12


**ON A/C A321-100 A321-200

10080 100 120 140 160 180 200

GROSS WEIGHT(1000 lb)


110

120

130

140

150

160

C.A.S (Kts)


NOTE:

40 50 60 70 80 90 100

LANDING GEAR EXTENDEDSLATS 27 DEG.FLAPS 40 DEG.

SEA LEVEL

N_AC_030500_1_0080101_01_00

Final Approach SpeedIAE V2500 series engine

FIGURE-3-5-0-991-008-A01

3-5-0Page 3

Jun 01/12


GROUND MANEUVERING


**ON A/C A321-100 A321-200

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 A321-100 A321-200

Turning Radii

1. This section gives the turning radii.

4-2-0Page 1

Jun 01/12


**ON A/C A321-100 A321-200

R4

R3

16.9 m

(55.45 ft)

(24.9 ft)7.59 m

R6

R5

R1

R2

50°

60°

70°

N_AC_040200_1_0070101_01_02

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.

APPLICABLE FOR A321−100 AND A321−200.

Turning Radii, No Slip AngleFIGURE-4-2-0-991-007-A01

4-2-0Page 2

Jun 01/12


**ON A/C A321-100 A321-200

MA

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53.6

48.8

44.0

39.2

29.4

34.3

24.5

19.6

22222222222

2.0

2.5

3.9

5.5

7.3

9.4

11.7

14.4

17.6

21.7

26.9

34.0

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78131824313847587188112

145

9.6

10.1

11.5

13.1

14.9

16.9

19.3

22.0

25.2

29.3

34.5

41.6

51.9

32333843495663728396113

136

170

17.8

17.9

18.4

19.1

20.0

21.2

22.7

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27.0

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58596163667074818999114

135

166

22.6

23.1

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747680859198105

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155

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23.4

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25.3

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28.6

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35.6

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7778838894101

108

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128

141

158

181

215

22.6

22.7

23.1

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24.3

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26.5

28.1

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33.1

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747476778083879299109

122

141

172

24.5

24.7

25.4

26.3

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114

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3742485563

18.3

19.0

19.9

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6062656974

24.1

25.8

27.6

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79859197105

25.0

26.6

28.5

30.5

32.8

828793100

108

23.0

23.5

24.2

25.2

26.4

7577808387

25.3

26.2

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8386899499

N_AC_040200_1_0080101_01_01

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Turning Radii, No Slip AngleFIGURE-4-2-0-991-008-A01

4-2-0Page 3

Jun 01/12


4-3-0 Minimum Turning Radii

**ON A/C A321-100 A321-200

Minimum Turning Radii

1. This section gives the minimum turning radii.

4-3-0Page 1

Jun 01/12


**ON A/C A321-100 A321-200

R6

R3

R5

R416.9 m

PAVEMENTWIDTH FOR180° TURN

MINIMUM

NOTE:MEASURED FROM OUTSIDE FACE OF TIRE.THEORETICAL CENTER OF TURNFOR MINIMUM TURNING RADIUS.SLOW CONTINUOUS TURNING,APPROXIMATELY IDLE THRUSTON ALL ENGINES.NO DIFFERENTIAL BRAKING.

NOSE GEAR RADII TRACK

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

73.1°

71.6°

m

m

ft

ft

Y

5.1

5.6

17

18

A

27.7

28.3

91

93

R3NLG

17.8

17.9

58

59

R4 WINGWING TIPFENCE

22.6

23.1

74

76

SHARKLET

23.4

23.9

77

78

R5NOSE

22.6

22.7

74

74

R6THS

24.5

24.7

80

81

(55 ft)

STEERINGANGLE 75°

Y

A

OUTSIDE FACE OF TIRE

EFFECTIVETURN

N_AC_040300_1_0040101_01_02

Minimum Turning RadiiFIGURE-4-3-0-991-004-A01

4-3-0Page 2

Jun 01/12


4-4-0 Visibility from Cockpit in Static Position

**ON A/C A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

FIR

ST

OF

FIC

ER

FIX

ED

WIN

DO

WF

IRS

T O

FF

ICE

RS

LID

ING

WIN

DO

WF

IRS

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ICE

RW

IND

SH

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CA

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WIN

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S H

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35°

UP

AN

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5° D

OW

N T

HR

OU

GH

TH

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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 A321-100 A321-200

Runway and Taxiway Turn Paths

1. Runway and Taxiway Turn Paths.

4-5-0Page 1

Jun 01/12



**ON A/C A321-100 A321-200

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 A321-100 A321-200

FAA LEAD−IN FILLET

L = 45 m (150 ft)

30 m

TAXIWAYCENTERLINE

RUNWAY CENTERLINE

TURN R = 30 m(100 ft)

FILLET R = 16.5 m(55 ft)

APPROX 1.9 m(6 ft)

NOTE: FAA GROUP III FACILITIES.

ADDITIONAL FILLET TO MEET3 m (10 ft) EDGE CLEARANCE

N_AC_040501_1_0060101_01_02

NLG PATH

MLG PATH

15 m(50 ft)

(100 ft)

135˚ Turn - Runway to TaxiwayCockpit Over Centerline Method

FIGURE-4-5-1-991-006-A01

4-5-1Page 2

Jun 01/12


**ON A/C A321-100 A321-200

RUNWAY CENTERLINE

TURN R = 30 m(100 ft)



L = 45 m (150 ft)

APPROX 3 m(10 ft)

TAXIWAYCENTERLINE

30 m


N_AC_040501_1_0070101_01_02

NLG PATH

MLG PATH

15 m(50 ft)

(100 ft)

135˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

FIGURE-4-5-1-991-007-A01

4-5-1Page 3

Jun 01/12



**ON A/C A321-100 A321-200

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 A321-100 A321-200

APPROX 3.7 m(12 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_0060101_01_02

NLG PATH

MLG PATH

30 m(100 ft)

15 m(50 ft)

90˚ Turn - Runway to TaxiwayCockpit Over Centerline Method

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

4-5-2Page 2

Jun 01/12


**ON A/C A321-100 A321-200

APPROX 9.2 m(30 ft)


TURN R = 30 m(100 ft)

RUNWAY CENTERLINE


TAXIWAY CENTERLINE

NOTE: FAA GROUP III FACILITIES.N_AC_040502_1_0070101_01_02

NLG PATH

MLG PATH

30 m(100 ft)

15 m(50 ft)

90˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

FIGURE-4-5-2-991-007-A01

4-5-2Page 3

Jun 01/12


4-5-3 180˚ Turn on a Runway

**ON A/C A321-100 A321-200

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 A321-100 A321-200

45 m(150 ft)

RUNWAY CENTERLINE

3.45 m(11 ft)

14.9 m(49 ft)

R3 = 17.6 m(58 ft)

R5 = 22.6 m(74 ft)

NOTE: TYPE 1 VALUES.

N_AC_040503_1_0020101_01_02

NLG PATH

WINGTIP PATH:

NOSE PATH

MLG PATH

WINGTIP FENCES:R4 = 22.7 m (74 ft)SHARKLETS:R4 = 23.4 m (77 ft)

R4

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

FIGURE-4-5-3-991-002-A01

4-5-3Page 2

Jun 01/12


**ON A/C A321-100 A321-200

12 m(39 ft)

45 m(150 ft)

4.4 m(14 ft)

NOTE: TYPE 1 VALUES.

6.3 m(21 ft)

RUNWAY CENTERLINE

25°

N_AC_040503_1_0020102_01_00

NLG PATH

WINGTIP PATH:

NOSE PATH

MLG PATH

WINGTIP FENCES:R4 = 22.7 m (74 ft)SHARKLETS:R4 = 23.4 m (77 ft)

R3 = 17.6 m(58 ft)

R5 = 22.6 m(74 ft)

R4

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

FIGURE-4-5-3-991-002-A01

4-5-3Page 3

Jun 01/12



**ON A/C A321-100 A321-200

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 A321-100 A321-200


APPROX 2.3 m(8 ft)

NLG PATH

MLG PATH

TAXIWAY CENTERLINE

NOTE: FAA GROUP III FACILITIES

TAXIWAY CENTERLINE

FILLET R = 16.5 m

TURN R = 30 m

ADDITIONAL FILLET TO MEET3 m (10 ft) EDGE CLEARANCE

15 m(50 ft)

15 m(50 ft)

N_AC_040504_1_0070101_01_00

L = 45 m (150 ft)

(55 ft)

(100 ft)

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

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

4-5-4Page 2

Jun 01/12


**ON A/C A321-100 A321-200

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

15 m(50 ft)

15 m(50 ft)

N_AC_040504_1_0070102_01_00

(55 ft)

(100 ft)

L = 45 m (150 ft)

(10 ft)

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

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

4-5-4Page 3

Jun 01/12



**ON A/C A321-100 A321-200

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 A321-100 A321-200

TAXIWAY CENTERLINE


NLG PATH

MLG PATHTAXIWAY CENTERLINE

APPROX 3.2 m(10 ft)


TURN R = 30 m(100 ft)


15 m(50 ft)

15 m(50 ft)

N_AC_040505_1_0040101_01_00

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

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

4-5-5Page 2

Jun 01/12


**ON A/C A321-100 A321-200

TAXIWAY CENTERLINE


NLG PATH

MLG PATHTAXIWAY CENTERLINE

APPROX 9.1 m(30 ft)


TURN R = 30 m(100 ft)


15 m(50 ft)

15 m(50 ft)

N_AC_040505_1_0040102_01_00

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

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

4-5-5Page 3

Jun 01/12


4-6-0 Runway Holding Bay (Apron)

**ON A/C A321-100 A321-200

Runway Holding Bay (Apron)

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

4-6-0Page 1

Jun 01/12


**ON A/C A321-100 A321-200

RUNWAY CENTERLINETAXIWAY

CENTERLINE

HOLDING POINT

12.2 m

NOTE: APPLICABLE FOR A321−100 AND A321−200.

N_AC_040600_1_0040101_01_02

61 m(200 ft)

190 m

23 m(75 ft)

45 m(150 ft)

90 m61 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-4-6-0-991-004-A01

4-6-0Page 2

Jun 01/12


4-7-0 Parking

**ON A/C A321-100 A321-200

Airplane Parking

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

4-7-0Page 1

Jun 01/12


**ON A/C A321-100 A321-200

3.05 m(10 ft)(REF)

3.05 m(10 ft)

AIRPLANE MODEL MIN LINEUP DISTANCE

ASDAm (ft)

A321−100 ANDA321−200

ABREVIATIONS TODA (TAKEOFF DISTANCE ADJUSTMENT)ASDA (ACCELERATE−STOP DISTANCE ADJUSTMENT)

19.92 m(65 ft 4.8 in)

36.83 m(121 ft 2.4 in)

90°

MAX. EFF. STEERINGANGLE DEGREES

19.9(65.4)

36.8(121.2)75°

TODAm (ft)

LINEUP DISTANCES FOR A321−100 AND A321−200 USING 75° STEERING AND NO SLIP ON NOSE TIRES

60 m(196 ft 10.8 in)

RUNWAYWIDTH

(REF)

N_AC_040700_1_0110101_01_01

Runway Length AlterationsLine Up Distances -- 90˚ TurnFIGURE-4-7-0-991-011-A01

4-7-0Page 2

Jun 01/12


**ON A/C A321-100 A321-200

32.63 m(107 ft 1.2 in)

20.73 m(68 ft)

3.05 m(10 ft)(REF)

END OF RUNWAY

EDGE OFRUNWAY

AIRPLANE MODEL MIN LINEUP DISTANCE NOMINAL LINEUP DISTANCE

180° ASDAm (ft) m (ft) ASDA

m (ft)

A321−100 ANDA321−200

26.9(88.3)

43.8(143.8)

32.6(107.1) AS MINIMUM AS MINIMUM

ABREVIATIONS TODA (TAKEOFF DISTANCE ADJUSTMENT)ASDA (ACCELERATE−STOP DISTANCE ADJUSTMENT)

TODAm (ft)

TODAm (ft)

LINEUP DISTANCES FOR A321−100 AND A321−200USING 75° STEERING AND NO SLIP ON NOSE TIRES

REQ’D MIN PAVEMENT WIDTH

43.82 m(143 ft 9.6 in)

26.9 m(88 ft 3.6 in)

3.05 m(10 ft)(REF)3.05 m

(10 ft)(REF)

N_AC_040700_1_0120101_01_01

Runway Length AlterationsLine Up Distances -- 180˚ Turn

FIGURE-4-7-0-991-012-A01

4-7-0Page 3

Jun 01/12


TERMINAL SERVICING

5-0-0 TERMINAL SERVICING

**ON A/C A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

N_AC_050102_1_0050101_01_03

STAND SAFETY LINE

NOTE: TYPICAL RAMP LAYOUTAPPLICABLE TO AIRCRAFTWITH OR WITHOUT SHARKLETS.

8METERS

FEET5 10 150 20

0 2 4 6 AS

CAT

GPU

CAT

WV

LV

FUEL

CB

TOW

CB

BULK

BULK

PS

PS

AC

Typical Ramp LayoutOpen Apron - Bulk LoadingFIGURE-5-1-2-991-005-A01

5-1-2Page 2

Jun 01/12


**ON A/C A321-100 A321-200

N_AC_050102_1_0100101_01_00

STAND SAFETY LINE


8METERS

FEET5 10 150 20

0 2 4 6 AS

CAT

ULD

GPU

CAT

WV

LV

ULD

BULK

FUEL

CB

TOW

LD CL

PS

PS

LD CL

AC

Typical Ramp LayoutOpen Apron - ULD LoadingFIGURE-5-1-2-991-010-A01

5-1-2Page 3

Jun 01/12


5-1-3 Typical Ramp Layout - Gate

**ON A/C A321-100 A321-200

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 A321-100 A321-200

STAND SAFETY LINE


8METERS

FEET5 10 150 20

0 2 4 6 AS

CAT

ULD

GPU

CAT

WV

LV

ULD

PBB

BULK

FUEL

CB

TOW

N_AC_050103_1_0030101_01_03

LD CL

LD CL

AC

Typical Ramp LayoutGate

FIGURE-5-1-3-991-003-A01

5-1-3Page 2

Jun 01/12


5-2-0 Terminal Operations - Full Servicing

**ON A/C A321-100 A321-200

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 HANDLING185 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:- 185 pax at door L1- Deboarding rate = 22 pax/min per door- No Passenger with Reduced Mobility (PRM)

Boarding:- 185 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 minCargo exchange:- FWD cargo compartment: 5 LD3- AFT cargo compartment: 5 LD3- Bulk compartment: 500 kg (1102 lb)

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

Bulk off-loading/loading times:

5-2-0Page 1

Jun 01/12


- 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- 10 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 A321-100 A321-200

0 20 30 40

TRT: 51 min

10 50 60

CATERING AT DOOR R1

CATERING AT DOOR R2

CLEANING

CARGO FWD CC

BULK

REFUELLING

TOILET SERVICING

HEADCOUNTING

CARGO AFT CC

DEBOARDING/BOARDING AT DOOR L1

POTABLE WATERSERVICING

POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH

N_AC_050200_1_0070101_01_01

min

AVAILABLE TIME

Turn Round StationsFull Servicing (51 Min.)

FIGURE-5-2-0-991-007-A01

5-2-0Page 3

Jun 01/12


5-3-0 Terminal Operation - Transit

**ON A/C A321-100 A321-200

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 HANDLING220 pax, all Y/C2 Stairways used at doors L1 & L2Equipment positioning/removal + opening/closing door = 2 min

Deboarding:- 110 pax at door L1- 110 pax at door L2- Deboarding rate = 20 pax/min per door- No Passenger with Reduced Mobility (PRM)

Boarding:- 110 pax at door L1- 110 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: 5 LD3- AFT cargo compartment: 5 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 A321-100 A321-200

0 5 15 20 25 3010

HEADCOUNTING

CATERING

CLEANING

CARGO FWD CC

BULK

REFUELLING

POTABLE WATER SERVICING

TOILET SERVICING

CARGO AFT CC

TRT: 25 min

POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH



min

AVAILABLE TIME

AVAILABLE TIME

N_AC_050300_1_0040101_01_01

Turn Round StationsMinimum Servicing (25 Min.)FIGURE-5-3-0-991-004-A01

5-3-0Page 3

Jun 01/12


5-4-0 Ground Service Connections

**ON A/C A321-100 A321-200

Ground Service Connections

1. Ground Service Connections.

5-4-0Page 1

Jun 01/12


5-4-1 Ground Service Connections Layout

**ON A/C A321-100 A321-200

Ground Service Connections Layout

1. This section gives the ground service connections layout.

5-4-1Page 1

Jun 01/12


**ON A/C A321-100 A321-200

1 3 11 12 2 4 14−6 7−

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 −

114

13

10

10

13

67

6

7

5 8 12 4

9 2

N_AC_050401_1_0070101_01_01

Ground Service ConnectionsGround Service Connections Layout

FIGURE-5-4-1-991-007-A01

5-4-1Page 2

Jun 01/12


5-4-2 Grounding Points

**ON A/C A321-100 A321-200

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:

21.97 m(72.08 ft)

3.79 m(12.43 ft)

1.07 m(3.51 ft)

On right Main LandingGear leg:

21.97 m(72.08 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 A321-100 A321-200

(2)(1)

GROUND CABLE(OPTIONAL)

LANDINGGEAR

NOSE LANDING GEAR

MAIN LANDING GEAR

(1)

A

A

A

(1)

N_AC_050402_1_0070101_01_00

Ground Service ConnectionsGrounding Points

FIGURE-5-4-2-991-007-A01

5-4-2Page 2

Jun 01/12


**ON A/C A321-100 A321-200

NOTE: R SIDE SYMMETRICAL

A

RIB20

RIB19

FWD

A

A

FOR SPECIFICATIONS REFERTO FLIGHT MANUAL

B

B

N_AC_050402_1_0080101_01_00

Ground Service ConnectionsGrounding Points

FIGURE-5-4-2-991-008-A01

5-4-2Page 3

Jun 01/12


5-4-3 Hydraulic System

**ON A/C A321-100 A321-200

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

23.44(76.9)

1.27(4.17)

1.76(5.77)

Yellow System:Access door 198CB

23.44(76.9)

1.27(4.17)

1.76(5.77)

Blue System:Access door 197EB

24.49(80.35)

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 195BB19.92(65.35)

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

20.1(65.94)

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

21.04(69.03)

0.25(0.82)

3.2(10.5)

Blue Systemaccumulator:Access door 195BB

22.3(72.51)

0.25(0.82)

1.99(6.53)

Yellow System brakingaccumulator:Access door 196BB

20.165.94)

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 197CB23.44(76.9)

1.27(4.17)

1.76(5.77)

NOTE : Distances are approximate.One 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 196 BB -198 CB

20.1(65.94)

1.43(4.69)

1.90(6.23)

Green System:Left MLG door

21.04(69.03)

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 197 EB

24.49(80.35)

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

Fuel System

1. Refuel/Defuel Control Panel.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Refuel/DefuelIntegrated Panel:Access door 192MB

20.65(67.75)

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)

21.84(71.65)

9.83(32.25)

3.65(11.98)

Refuel/Defuel coupling,RightAccess Door 622HB

21.84(71.65)

9.83(32.25)

3.65(11.98)

Gravity Refuel Coupling23.35(76.61)

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 24.61(80.74)

14.9(48.88)

14.9(48.88)

4.32(14.17)

NACA Flame Arrestor 24.05(78.90)

13.7(44.95)

13.7(44.95)

4.02(13.19)


5-4-6Page 2

Jun 01/12


**ON A/C A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

Pneumatic System

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


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

HP ConnectorAccess door 191DB

17.25(56.59)

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.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

LP ConnectorAccess door 191CB

16.72(54.86)

1.11(3.64)

1.73(5.68)


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

5-4-7Page 1

Jun 01/12


5-4-8 Potable Water System

**ON A/C A321-100 A321-200

Potable Water System

1. Potable Water Ground Service Panel.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM GROUND

m (ft)

Access door 171AL:38.2(125.33)

0.3(0.98)

2.6(8.53)

NOTE : Distances are approximate

A. Connector:- Fill/Drain Nipple 3/4 in. (ISO 17775)

B. Usable capacity- Standard configuration - one tank:2000 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)

2. Potable Water Ground Drain Panel.


ACCESSAFT OF NOSE


LH SIDEm (ft)


m (ft)

Potable WaterGround ServicePanel:Access door 133AL:

11.8(38.71)

0.15(0.49)

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).

5-4-8Page 1

Jun 01/12


- One ground pressurization connector.

(2) On drain panel (Access Door 133AL)- 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 A321-100 A321-200

DRAIN CONNECTION

FILL ANDDRAIN PORT

GROUND CONNECTION

PRESSURIZATION

Z133

Z171

A

B

B

A

N_AC_050408_1_0010101_01_00

Ground Service ConnectionsPotable Water Ground Service Panel

FIGURE-5-4-8-991-001-A01

5-4-8Page 3

Jun 01/12


5-4-9 Oil System

**ON A/C A321-100 A321-200

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)

17.38(57.02)

6.63(21.75)

4.82(15.81)

1.46(4.79)

Engine Oil PressureFilling Port:

17.26(56.62)

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 (SeeFIGURE 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)

16.46(54)

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:

16.81(55.15)

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)

16.5(54.13)

6.56(21.52)

4.92(16.14)

1.22(4)


A. Tank capacity:- Full level: 28 l (7.39 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: 2506-2 plus one overflow connection: 2505-2..

5-4-9Page 2

Jun 01/12



ACCESSAFT OF NOSE


ENGINE 2 (RH)m (ft)


m (ft)

IDG Oil PressureFilling Connection:

17.06(55.97)

5.42(17.78)

6.04(19.81)

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:

19.66(64.5)

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 36-30042.42(139.17)

0.3(0.98)

4.83(15.85)

APS 320042.42(139.17)

0.3(0.98)

4.78(15.68)

131-942.32(138.84)

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

’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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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

38.2(125.33)

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 A321-100 A321-200

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 A321-100 A321-200

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--004-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 A321-100 A321-200

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_0040101_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-5-5-0-991-004-A01

5-5-0Page 2

Jun 01/12


5-5-1 Low Ambient Temperatures

**ON A/C A321-100 A321-200

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 A321-100 A321-200

AIR SUPPLY PRESSUREAT GROUND CONNECTION

kg/mn

220°C

200°C

150°C

100°C

50°C

MAXIM

UM T

EMPERATURE L

IMIT

TIMES UP TO IDLEESTIMATED STARTING

PSIA ABSOLUTE BARS


70s


GROUND CONNECTION:MIN PRESSURE AT

SEA LEVELZ = 8000 ft

SEA LEVEL

30 40 50 60 80 90 100 110 12070

2

3

4

5

4.5

6

7

6.5

5.5

2.5

3.5

30

40

50

60

70

80

90

100

0°C

33 PSIG

38 PSIG ATRECOMMENDED PRESSURE:

GROUND CONNECTION

60s

35s

40s

Z = 8000 ft

Z = 8000 ft

SEA LEVEL

50s

N_AC_050501_1_0070101_01_00


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

FIGURE-5-5-1-991-007-A01

5-5-1Page 2

Jun 01/12


**ON A/C A321-100 A321-200

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


ESTIMATED STARTINGTIMES UP TO IDLE

N_AC_050501_1_0080101_01_00

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

FIGURE-5-5-1-991-008-A01

5-5-1Page 3

Jun 01/12


5-5-2 Medium Ambient Temperatures

**ON A/C A321-100 A321-200

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 A321-100 A321-200


kg/mn

220°C

200°C

150°C

100°C

50°CMAXIM

UM T

EMPERATURE L

IMIT


PSIA ABSOLUTE BARSAIR SUPPLY TEMPERATUREAT FUSELAGE CONNECTION

70s



SEA LEVEL

Z = 8000 ft

SEA LEVEL

0°C

22 PSIG


GROUND CONNECTION60s

Z = 8000 ft

2

2.5

3

3.5

4

7

6.5

6

5.5

5

4.5

100

90

80

70

60

50

40

30

30 40 50 60 70 80 90 100 110 120

Z = 8000 ft

SEA LEVEL

50s

40s

35s


N_AC_050502_1_0070101_01_00

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

FIGURE-5-5-2-991-007-A01

5-5-2Page 2

Jun 01/12


**ON A/C A321-100 A321-200


kg/mn

PSIA ABSOLUTE BARS


220°C200°C

150°C

100°C

50°C

0°CMAXIMUM DUCT PRESSURE



60s

230

3

4

5

6

90

80

70

60

50

40

55s

50s

45s

MAXIMUM T

EMPERATURE LIMIT

40 50 60 70 80 90 100 110 120

N_AC_050502_1_0080101_01_00

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

FIGURE-5-5-2-991-008-A01

5-5-2Page 3

Jun 01/12


5-5-3 High Ambient Temperatures

**ON A/C A321-100 A321-200

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 A321-100 A321-200


kg/mn

220°C200°C

150°C

100°C

50°C

MAXIM

UM T

EMPERATURE L

IMIT


PSIA ABSOLUTE BARS

70s



22 PSIG


GROUND CONNECTION60s

50s

40s

35s

30

40

50

60

70

80

90

100 7

6

4

3

2

30 40 50 60 70 80 90 100 110 120

2.5

3.5

4.5

5

5.5

6.5

Z = 8000 ft

SEA LEVEL

Z = 8000 ft

SEA LEVEL

Z = 8000 ft

SEA LEVEL


N_AC_050503_1_0070101_01_00


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

FIGURE-5-5-3-991-007-A01

5-5-3Page 2

Jun 01/12


**ON A/C A321-100 A321-200


kg/mn

220°C

200°C

150°C

100°C

50°C


PSIA ABSOLUTE BARS



0°C

60s

55s

2

3

4

5

6

90

80

70

60

50

40

30

40 50 60 70 80 90 100 110 120

50s

45s

MAXIMUM DUCT PRESSURE

MAXIMUM T

EMPERATURE LIMIT

N_AC_050503_1_0080101_01_00

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

FIGURE-5-5-3-991-008-A01

5-5-3Page 3

Jun 01/12


5-6-0 Ground Pneumatic Power Requirements

**ON A/C A321-100 A321-200

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 A321-100 A321-200

Heating

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

5-6-1Page 1

Jun 01/12


**ON A/C A321-100 A321-200

TOTAL AIRFLOW(kg/

s)

TOTAL AIRFLOW

CABIN AIRFLOW

0.5

30

TIM

E T

O H

EA

T C

AB

IN T

O 2

1°C

(69

.8°

F O

N G

RO

UN

D)

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

)

1.34(lb

/s)

4050

0.44

9

0.53

9

0.62

8

0.71

8

0.80

8

0.89

8

0.98

8

1.07

7

1.16

7

1.25

7

1.34

7

1.0

1.2

1.5

1.80

2.26

2.71

3.0

2.5

2.0

1.5

CABIN AIRFLOW

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 =

410

0 W

RE

CIR

CU

LAT

ION

: ON

NO

OT

HE

R H

EA

T L

OA

D

N_AC_050601_1_0040101_01_01

Ground Pneumatic Power RequirementsHeating

FIGURE-5-6-1-991-004-A01

5-6-1Page 2

Jun 01/12


5-6-2 Cooling

**ON A/C A321-100 A321-200

Cooling

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

5-6-2Page 1

Jun 01/12


**ON A/C A321-100 A321-200

TOTAL AIRFLOW

(kg/

s)

TOTAL AIRFLOW

CABIN AIRFLOW

1.5

TIM

E T

O C

OO

L C

AB

IN T

O 2

7°C

(80

.6°

F O

N G

RO

UN

D)

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

)

(lb/s

)

0.44

9

0.53

9

0.62

8

0.71

8

0.80

8

0.89

8

0.98

8

1.07

7

1.16

7

1.25

7

1.34

7

1.2

1.0

0.5

3040

50

1.34

1.80

2.26

2.71

3.0

2.5

2.0

1.5

CABIN AIRFLOW

INIT

IAL

CA

BIN

TE

MP

ER

AT

UR

E A

T 3

8°C

(10

0.4°

F)

TE

MP

ER

AT

UR

E A

T G

RO

UN

D C

ON

NE

CT

ION

: 1.5

°C

(34

.7°

F)

EM

PT

Y C

AB

INE

LEC

TR

ICA

L LO

AD

= 2

000

WS

UN

= 4

990

WR

EC

IRC

ULA

TIO

N: O

N

N_AC_050602_1_0040101_01_01

Ground Pneumatic Power RequirementsCooling

FIGURE-5-6-2-991-004-A01

5-6-2Page 2

Jun 01/12


5-7-0 Preconditioned Airflow Requirements

**ON A/C A321-100 A321-200

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 0.449 0.990 -56.4 -69.50.6 1.32 0.539 1.188 -41.8 -43.20.7 1.54 0.628 1.385 -31.3 -24.30.8 1.76 0.718 1.583 -23.5 -10.30.9 1.98 0.808 1.781 -17.5 0.51.0 2.20 0.898 1.980 -12.7 9.11.1 2.43 0.988 2.178 -8.8 16.21.2 2.65 1.077 2.374 -5.5 22.11.3 2.87 1.167 2.573 -2.7 27.11.4 3.09 1.257 2.771 -0.4 31.31.5 3.31 1.347 2.970 1.7 35.1

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 0.449 0.990 32.6 90.70.6 1.32 0.539 1.188 30.5 86.90.7 1.54 0.628 1.385 29.0 84.20.8 1.76 0.718 1.583 27.9 82.20.9 1.98 0.808 1.781 27.1 80.81.0 2.20 0.898 1.980 26.4 79.51.1 2.43 0.988 2.178 25.9 78.61.2 2.65 1.077 2.374 25.4 77.71.3 2.87 1.167 2.573 25.0 77.01.4 3.09 1.257 2.771 24.7 76.5

5-7-0Page 1

Jun 01/12



(kg/s) (lb/s) (kg/s) (lb/s) (˚C) (˚F)

1.5 3.31 1.347 2.970 24.4 75.9


C. Preconditioned Airflow Requirements.


(kg/s) (lb/s) (kg/s) (lb/s) (˚C) (˚F)

0.5 1.10 0.449 0.990 38.4 101.10.6 1.32 0.539 1.188 35.3 95.50.7 1.54 0.628 1.385 33.1 91.60.8 1.76 0.718 1.583 31.5 88.70.9 1.98 0.808 1.781 30.2 86.41.0 2.20 0.898 1.980 29.2 84.61.1 2.43 0.988 2.178 28.4 83.11.2 2.65 1.077 2.374 27.7 81.91.3 2.87 1.167 2.573 27.1 80.81.4 3.09 1.257 2.771 26.6 79.91.5 3.31 1.347 2.970 26.2 79.2


D. Preconditioned Airflow Requirements.


(kg/s) (lb/s) (kg/s) (lb/s) (˚C) (˚F)

0.5 1.10 0.449 0.990 46.6 115.90.6 1.32 0.539 1.188 42.2 108.00.7 1.54 0.628 1.385 39.0 102.20.8 1.76 0.718 1.583 36.6 97.90.9 1.98 0.808 1.781 34.7 94.51.0 2.20 0.898 1.980 33.2 91.81.1 2.43 0.988 2.178 32.0 89.61.2 2.65 1.077 2.374 31.0 87.81.3 2.87 1.167 2.573 30.2 86.41.4 3.09 1.257 2.771 29.5 85.1

5-7-0Page 2

Jun 01/12



(kg/s) (lb/s) (kg/s) (lb/s) (˚C) (˚F)

1.5 3.31 1.347 2.970 28.8 83.8


5-7-0Page 3

Jun 01/12


**ON A/C A321-100 A321-200

TOTAL AIRFLOW

(kg/

s)TOTAL AIRFLOW

CABIN AIRFLOW

(lb/s

)

(°C

)IN

LET

FLO

WT

EM

PE

RA

TU

RE

(°F

)

−40

−30

−20

−10

010

2030

40

100

5010

0−

10−

40

1.34

1.80

2.26

2.71

3.0

2.5

2.0

1.5

0.44

9

0.53

9

0.62

8

0.71

8

0.80

8

0.89

8

0.98

8

1.07

7

1.16

7

1.25

7

1.34

7

0.5

1.0

1.2

1.5

MA

X A

LLO

WE

D T

OT

AL

AIR

FLO

W (

2 m

bar

CA

BIN

OV

ER

PR

ES

SU

RE

)

NO

TE

:LP

GR

OU

ND

CO

NN

EC

TIO

N M

AX

IMU

M P

RE

SS

UR

E 4

0 m

b

CABIN AIRFLOW

CU

RV

E 1

: CA

BIN

AT

29°

C (

84.2

°F

)19

9 P

AS

SE

NG

ER

S, 6

CA

BIN

AT

TE

ND

AN

TS

, 3 C

RE

W M

EM

BE

RS

BR

IGH

T D

AY

SO

LAR

LO

AD

: 499

0 W

ELE

CT

RIC

AL

LOA

D =

780

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)

OA

T =

−23

°C

(−

9.4°

F)

OA

T =

−30

°C

(−

22°

F)

OA

T =

−40

°C

(−

40°

F)

CA

BIN

AT

21°

C (

69.8

°F

)

NO

OT

HE

R H

EA

T L

OA

D

ELE

CT

RIC

AL

LOA

D =

570

0 W

RE

CIR

CU

LAT

ION

: ON

NO

PA

SS

EN

GE

R O

R C

AB

INA

TT

EN

DA

NT

S

CU

RV

E 2

, 3, 4

N_AC_050700_1_0040101_01_01

Preconditioned Airflow RequirementsFIGURE-5-7-0-991-004-A01

5-7-0Page 4

Jun 01/12


5-8-0 Ground Towing Requirements

**ON A/C A321-100 A321-200

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 A321-100 A321-200

EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A321 AT 80 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 (80 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 (6.5 t)− SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE. THE OBTAINED X−COORDINATE IS

THE RECOMMENDED MINIMUM TRACTOR WEIGHT (11.5 t)

95

657075808590

10

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

5

011.47

DR

Y C

ON

CR

ET

E m

= 0

.8

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

WE

T C

ON

CR

ET

E m

= 0

.57

HA

RD

SN

OW

m =

0.2

ICE m = 0.05

1 ENGINE ON1.5% SLOPE

80 tons

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

6.5

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

N_AC_050800_1_0010401_01_03

Ground Towing RequirementsFIGURE-5-8-0-991-001-D01

5-8-0Page 2

Jun 01/12


5-9-0 De-Icing and External Cleaning

**ON A/C A321-100 A321-200

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

A321 102.6 1104.38 1.8 19.38 27 290.63 43 462.85A321 Sharklet 102.6 1104.38 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

A321 167.4 1801.88 23.6 254.03 365 3929A321 Sharklet 167.4 1801.88 23.6 254.03 373 4015

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

A321 102.6 1104.38 108.8 1171.11 1.8 19.38 27 290.63 27 290.63A321 Sharklet 102.6 1104.38 108.8 1171.11 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


A321 43 462.85 509.6 5485.29 73.2 787.92 895 9634

5-9-0Page 1

Jun 01/12


VTP(Both Sides)

Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned Area

AIRCRAFT TYPE


A321 Sharklet 43 462.85 509.6 5485.29 73.2 787.92 902 9709

NOTE : Dimensions are approximate

5-9-0Page 2

Jun 01/12


OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

**ON A/C A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

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

V (

m/s

)

GR

OU

ND

PLA

NE

ME

TE

RS

4530

2520

1510

40 30 20 10 0036912

mft

40 30 20 10 0036912

mft

N_AC_060101_1_0070101_01_00

4530

2520

1510

Engine Exhaust VelocitiesGround Idle Power -- CFM56-5B series engine

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

6-1-1Page 2

Jun 01/12


**ON A/C A321-100 A321-200

ME

TE

RS

015

3045

60

250

300

ELE

VA

TIO

N

GR

OU

ND

IDLE

TH

RU

ST

FE

ET

050

100

150

200

7590

PLA

N

34 M

PH

20 M

PH

68 M

PH

ftm

60

15 10 5 0

40 20 0

ftm

60

15 10 5 0

40 20 0

N_AC_060101_1_0080101_01_00

Engine Exhaust VelocitiesGround Idle Power -- IAE V2500 series engine

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

6-1-1Page 3

Jun 01/12


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

**ON A/C A321-100 A321-200

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 A321-100 A321-200

ELE

VA

TIO

N

FE

ET

050

100

150

200

250

300

350

400

015

3045

6075

9010

512

0

mft

PLA

NA

IRP

LAN

E

T (

°K

)

GR

OU

ND

PLA

NE

ME

TE

RS40 30 20 10 0

036912

mft

400

350

325

300

40 30 20 10 0036912

400

350

325

300

N_AC_060102_1_0070101_01_00

Engine Exhaust TemperaturesGround Idle Power -- CFM56-5B series engine

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

6-1-2Page 2

Jun 01/12


**ON A/C A321-100 A321-200

ME

TE

RS

015

3045

60

250

300

ELE

VA

TIO

N

FE

ET

050

100

150

200

7590

45°

C35

°C

25°

C

ftm

60

15 10 5 0

40 20 0

N_AC_060102_1_0080101_01_00

Engine Exhaust TemperaturesGround Idle Power -- IAE V2500 series engine

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

6-1-2Page 3

Jun 01/12


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

**ON A/C A321-100 A321-200

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 A321-100 A321-200

420

390

360

330

300

270

240

210

180

150

120

9060

30

0

100

200

300

400

500

700

600

800

900

1000

1100

1200

1300

1400

ME

TE

RS

FE

ET

ft

V =

40

m/s

V =

20

m/s

V =

12

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

42 36 30 24 18 12 6 0

140

120

100 80 60 40 200

450

1500

ftm

42 36 30 24 18 12 6 0

140

120

100 80 60 40 200

N_AC_060105_1_0070101_01_00

Engine Exhaust VelocitiesTakeoff Power -- CFM56-5B series engine

FIGURE-6-1-5-991-007-A01

6-1-5Page 2

Jun 01/12


**ON A/C A321-100 A321-200

ME

TE

RS

015

3045

60

250

300

ELE

VA

TIO

N

MA

XIM

UM

TA

KE

OF

F T

HR

US

T

FE

ET

050

100

150

200

7590

PLA

N

136

MP

H10

2 M

PH

68 M

PH

34 M

PH

20 M

PH

TO

990

ft (

301

m)

TO

575

ft (

175

m)

ftm

60

15 10 5 0

40 20 0

ftm

15 10 5 0

60 40 20 0

N_AC_060105_1_0080101_01_00

Engine Exhaust VelocitiesTakeoff Power -- IAE V2500 series engine

FIGURE-6-1-5-991-008-A01

6-1-5Page 3

Jun 01/12


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

**ON A/C A321-100 A321-200

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 A321-100 A321-200

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

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

50

ftm

60

0

40 20 0

18 12 6

ftm

60

0

40 20 0

18 12 6

N_AC_060106_1_0070101_01_00

Engine Exhaust TemperaturesTakeoff Power -- CFM56-5B series engine

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

6-1-6Page 2

Jun 01/12


**ON A/C A321-100 A321-200

ME

TE

RS

1530

4560

250

300

ELE

VA

TIO

N

FE

ET

5010

015

020

0

7590

PLA

N

00

65°

C55

°C

45°

C35

°C

25°

C

ftm

15 10 5 0

60 40 20 0

ftm

15 10 5 0

60 40 20 0

N_AC_060106_1_0080101_01_00

Engine Exhaust TemperaturesTakeoff Power -- IAE V2500 series engine

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

6-1-6Page 3

Jun 01/12


6-2-0 Airport and Community Noise

**ON A/C A321-100 A321-200

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 A321-100 A321-200

Noise Data

1. Noise Data for CFM56-5B 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: 20.3˚C (69˚F)- Relative humidity: 43%- Atmospheric pressure: 988 hPa- Wind speed: Negligible- No rain

2. Noise Data for IAE V2500 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: 12˚C (54˚F)- Relative humidity: 62.5%- Atmospheric pressure: 1000 hPa- Wind speed: Negligible- No rain

6-2-1Page 1

Jun 01/12


**ON A/C A321-100 A321-200

112110108106104102

10098969492908886848280

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°NOISE REFERENCEPOINT

GROUND IDLE

N1

CURVE

MAX THRUST POSSIBLEON BRAKES

96%21.6%

78

N_AC_060201_1_0100101_01_00

Airport and Community NoiseCFM56-5B series engine

FIGURE-6-2-1-991-010-A01

6-2-1Page 2

Jun 01/12


**ON A/C A321-100 A321-200

GROUND IDLE

N2

CURVE

MAX THRUST POSSIBLEON BRAKES

57.7% 92.5%

E.P.R 1.007 1.397

11811611411211010810610410210098969492908886848280

NOISE REFERENCEPOINT

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°

210°

220°

230°

240°

250°

260°78

N_AC_060201_1_0110101_01_00

Airport and Community NoiseIAE V2500 series engine

FIGURE-6-2-1-991-011-A01

6-2-1Page 3

Jun 01/12


6-3-0 Danger Areas of Engines

**ON A/C A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

AREA

A

B

C

D (105−32)

E < 20 (32)

NOT TO SCALE

POSSIBLE EFFECTS WITHIN DANGER ZONE BASED ON"RADIOLOGICAL DEFENSE" VOL. II, ARMED FORCES SPECIALWEAPONS PROJECT, NOV. 1951

A MAN STANDING WILL BE PICKED UP AND THROWN; AIRCRAFT WILL BECOMPLETELY DESTROYED OR DAMAGED BEYOND ECONOMICAL REPAIR;COMPLETE DESTRUCTION OF FRAME OR BRICK HOMES.

A MAN STANDING FACE−ON WILL BE PICKED UP AND THROWN; DAMAGENEARING TOTAL DESTRUCTION TO LIGHT INDUSTRIAL BUILDINGS OR RIGIDSTEEL FRAMING; CORRUGATED STEEL STRUCTURES LESS SEVERELY.MODERATE DAMAGE TO LIGHT INDUSTRIAL BUILDINGS AND TRANSPORT−TYPEAIRCRAFT.

LIGHT TO MODERATE DAMAGE TO TRANSPORT−TYPE AIRCRAFT

BEYOND DANGER AREA

APPROX. WINDVELOCITYMPH (km/h)

210−145(338−233)

145−105(233−169)

105−65(169−105)

EXHAUST DANGER AREASINCLUDE (WORST CASE)GROUND PLANEHEADWIND (20 KTS)

INLET DANGER AREASINCLUDE (WORST CASE)GROUND PLANEHEADWIND (20 KTS)

INLET HAZARDDIMENSIONS CALCULATEDON 40 ft/sec (12 m/sec)CRITICAL VELOCITYWITH A 3 ft (0.9 m)ADJUSTMENT FOR SAFETY

RADIUS = 7.2 ft (2.2 m)

3.4 ft (1 m)

TO 199 ft (61 m)

CLOSE ENTRY CORRIDORFOR WIND DIRECTION > 90°

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

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

INLET SUCTIONDANGER AREA

WIDTH72 ft (22 m)

E

45°

NO ENTRY 82 ft (25 m)AFT OF NOZZLE EXIT

B

C

D

65−20

N_AC_060301_1_0090101_01_01

Danger Areas of EnginesCFM56-5B series engine

FIGURE-6-3-1-991-009-A01

6-3-1Page 2

Jun 01/12


**ON A/C A321-100 A321-200

30°

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

0.91 m(3 ft)

R = 5.79 m(19 ft)

ENTRY CORRIDOR

EXHAUST DANGER AREA

INTAKE SUCTION DANGER AREA GROUND IDLE

N_AC_060301_1_0100101_01_00

Danger Areas of EnginesIAE V2500 series engine

FIGURE-6-3-1-991-010-A01

6-3-1Page 3

Jun 01/12


6-3-2 Takeoff Power

**ON A/C A321-100 A321-200

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 A321-100 A321-200

AREA

A

B

C

D (105−32)

E < 20 (32)

NOT TO SCALE

POSSIBLE EFFECTS WITHIN DANGER ZONE BASED ON"RADIOLOGICAL DEFENSE" VOL. II, ARMED FORCES SPECIALWEAPONS PROJECT, NOV. 1951

A MAN STANDING WILL BE PICKED UP AND THROWN; AIRCRAFT WILL BECOMPLETELY DESTROYED OR DAMAGED BEYOND ECONOMICAL REPAIR;COMPLETE DESTRUCTION OF FRAME OR BRICK HOMES.

A MAN STANDING FACE−ON WILL BE PICKED UP AND THROWN; DAMAGENEARING TOTAL DESTRUCTION TO LIGHT INDUSTRIAL BUILDINGS OR RIGIDSTEEL FRAMING; CORRUGATED STEEL STRUCTURES LESS SEVERELY.MODERATE DAMAGE TO LIGHT INDUSTRIAL BUILDINGS AND TRANSPORT−TYPEAIRCRAFT.

LIGHT TO MODERATE DAMAGE TO TRANSPORT−TYPE AIRCRAFT

BEYOND DANGER AREA

APPROX. WINDVELOCITYMPH (km/h)

210−145(338−233)

145−105(233−169)

105−65(169−105)

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

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

EXHAUST DANGER AREASINCLUDE (WORST CASE)GROUND PLANEHEADWIND (20 KTS)

INLET DANGER AREASINCLUDE (WORST CASE)GROUND PLANEHEADWIND (20 KTS)

INLET HAZARD DIMENSIONSBASED ON 40 ft/sec (12 m/sec)CRITICAL VELOCITY WITH A3 ft (0.9 m) ADJUSTMENTFOR SAFETY

RADIUS = 21.7 ft (6.6 m)

E

TO 1235 ft (376 m)

WIDTH192 ft (59 m)

NO ENTRY 775 ft (236 m)AFT OF NOZZLE EXIT

INLET SUCTIONDANGER AREA

65−20

A

B

C

D

N_AC_060302_1_0070101_01_01

Danger Areas of EnginesCFM56-5B series engine

FIGURE-6-3-2-991-007-A01

6-3-2Page 2

Jun 01/12


**ON A/C A321-100 A321-200

30°

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

1.68 m

(5.5 ft)

R = 5.79 m(19 ft)

ENTRY CORRIDOR

EXHAUST DANGER AREA

INTAKE SUCTION DANGER AREA

N_AC_060302_1_0080101_01_00

Danger Areas of EnginesIAE V2500 series engine

FIGURE-6-3-2-991-008-A01

6-3-2Page 3

Jun 01/12


6-4-0 APU Exhaust Velocities and Temperatures

**ON A/C A321-100 A321-200

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 A321-100 A321-200

APU - APIC & GARRETT

1. This section gives APU exhaust velocities and temperatures.

6-4-1Page 1

Jun 01/12


**ON A/C A321-100 A321-200

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_0040101_01_00

Exhaust Velocities and TemperaturesAPU -- APIC & GARRETTFIGURE-6-4-1-991-004-A01

6-4-1Page 2

Jun 01/12


PAVEMENT DATA


**ON A/C A321-100 A321-200

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 use 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 on the left and the scale for allowable working stress on

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

- 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 in accordance with the ACN/PCN system as referenced inICAO Annex 14, ”Aerodromes”, Volume 1 Fourth Edition July 2004, incorporating Amendments 1 to6.

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-77-1for flexible 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 A321-100 A321-200

WVAIRCRAFT

CODE04 C04 C04 C09 D06 E06 E06 E07 G07 G07 G08 H00 I00 I00 I07 J02 L02 L02 L05 M05 M

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.

05 M06 O06 O

WVAIRCRAFT

CODE03 P03 P03 P05 Q05 Q10 R10 R04 S04 S08 U08 U08 U00 V00 V02 X02 X02 X02 X03 Z03 Z01 AA01 AA11 AB11 AB

MODEL

A321−111A321−112A321−131A321−214A321−111A321−112A321−131A321−111A321−112A321−131A321−214A321−111A321−112A321−131A321−214A321−111A321−112A321−131A321−111A321−112A321−131A321−211A321−231

MODEL

A321−111A321−112A321−131A321−211A321−231A321−211A321−231A321−211A321−231A321−111A321−112A321−131A321−211A321−231A321−211A321−231A321−213A321−232A321−211A321−231A321−211A321−231A321−211A321−231

N_AC_070100_1_0040101_01_00

Aircraft CodesAircraft Codes

FIGURE-7-1-0-991-004-A01

7-1-0Page 4

Jun 01/12


7-2-0 Landing Gear Footprint

**ON A/C A321-100 A321-200

Landing Gear Footprint

1. This section gives Landing Gear Footprint.

NOTE : For A/C Code definition, refer to chapter 7-1-0.

7-2-0Page 1

Jun 01/12


**ON A/C A321-100 A321-200

C − D − E

10.1 bar (146 psi)

1 270 x 455 R22 (49 x 18 − 22)

12.8 bar (186 psi)

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 R15 (30 x 8.8 − 15)

927 mm(36.5 in)

500 mm(19.7 in)

16 905 mm(55 ft 5.6 in)

7 590 mm(24 ft 10.8 in)

SEE SECTION 7−4−1

A/C CODE

N_AC_070200_1_0280101_01_00

Landing Gear FootprintLanding Gear Footprint

FIGURE-7-2-0-991-028-A01

7-2-0Page 2

Jun 01/12


**ON A/C A321-100 A321-200

G − H − I − J − L − M − O

10.8 bar (157 psi)

1 270 x 455 R22 (49 x 18 − 22)

13.6 bar (197 psi)


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


30 x 8.8 R15 (30 x 8.8 − 15)

927 mm(36.5 in)

500 mm(19.7 in)

16 905 mm(55 ft 5.6 in)

7 590 mm(24 ft 10.8 in)


A/C CODE

N_AC_070200_1_0290101_01_00


FIGURE-7-2-0-991-029-A01

7-2-0Page 3

Jun 01/12


**ON A/C A321-100 A321-200

P − Q − R

11 bar (160 psi)

1 270 x 455 R22 (49 x 18 − 22)

13.9 bar (202 psi)


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


30 x 8.8 R15 (30 x 8.8 − 15)

927 mm(36.5 in)

500 mm(19.7 in)

16 905 mm(55 ft 5.6 in)

7 590 mm(24 ft 10.8 in)


A/C CODE

N_AC_070200_1_0300101_01_00


FIGURE-7-2-0-991-030-A01

7-2-0Page 4

Jun 01/12


**ON A/C A321-100 A321-200

S − U − V − X

11.6 bar (168 psi)

1 270 x 455 R22 (49 x 18 − 22)

14.6 bar (212 psi)


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


30 x 8.8 R15 (30 x 8.8 − 15)

927 mm(36.5 in)

500 mm(19.7 in)

16 905 mm(55 ft 5.6 in)

7 590 mm(24 ft 10.8 in)


A/C CODE

N_AC_070200_1_0310101_01_00


FIGURE-7-2-0-991-031-A01

7-2-0Page 5

Jun 01/12


**ON A/C A321-200

Z − AA − AB

11.6 bar (168 psi)

1 270 x 455 R22 (49 x 18 − 22)

15 bar (218 psi)


ON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE


30 x 8.8 R15 (30 x 8.8 − 15)

927 mm(36.5 in)

500 mm(19.7 in)

16 905 mm(55 ft 5.6 in)

7 590 mm(24 ft 10.8 in)


A/C CODE

N_AC_070200_1_0320101_01_00


FIGURE-7-2-0-991-032-A01

7-2-0Page 6

Jun 01/12


7-3-0 Maximum Pavement Loads

**ON A/C A321-100 A321-200

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 A321-100 A321-200

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

C78

400

VM

G (

PE

R S

TR

UT

)V

NG

172

850

18 6

758

480

35 1

2515

930

82 7

0037

510

26 8

5012

180

66 1

5030

010

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

HM

AX

IMU

M H

OR

IZO

NT

AL

GR

OU

ND

LO

AD

FR

OM

BR

AK

ING

(1)

MR

W =

78

400

kgM

RW

= 7

8 40

0 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

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

FW

D C

G =

15.

4 %

MA

C A

T A

/C W

EIG

HT

= 7

8 40

0 kg

FW

D C

G =

15.

4 %

MA

C A

T A

/C W

EIG

HT

= 7

8 40

0 kg

D E

MR

W =

78

400

kgF

WD

CG

= 1

5.4

% M

AC

AT

A/C

WE

IGH

T =

78

400

kg

(2)

MR

W =

78

400

kgM

RW

= 7

8 40

0 kg

AF

T C

G =

41

% M

AC

AT

A/C

WE

IGH

T =

78

400

kgA

FT

CG

= 4

1 %

MA

C A

T A

/C W

EIG

HT

= 7

8 40

0 kg

MR

W =

78

400

kgA

FT

CG

= 4

1 %

MA

C A

T A

/C W

EIG

HT

= 7

8 40

0 kg

78 4

0017

2 85

018

675

8 47

035

075

15 9

1030

010

82 7

0037

510

26 8

5012

180

66 1

50

78 4

0017

2 85

018

675

8 48

035

125

15 9

3082

700

37 5

1026

850

12 1

8066

150

30 0

10

C D E C D E

A/C

CO

DE

N_AC_070300_1_0330101_01_00

Maximum Pavement LoadsMaximum Pavement LoadsFIGURE-7-3-0-991-033-A01

7-3-0Page 2

Jun 01/12


**ON A/C A321-100 A321-200

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

G80

400

VM

G (

PE

R S

TR

UT

)V

NG

177

250

18 7

508

510

35 6

0016

140

84 8

0038

470

27 5

5012

490

67 8

5030

780

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

HM

AX

IMU

M H

OR

IZO

NT

AL

GR

OU

ND

LO

AD

FR

OM

BR

AK

ING

(1)

MR

W =

80

400

kgM

RW

= 8

0 40

0 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

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

FW

D C

G =

16.

3 %

MA

C A

T A

/C W

EIG

HT

= 8

0 40

0 kg

FW

D C

G =

16.

3 %

MA

C A

T A

/C W

EIG

HT

= 8

0 40

0 kg

H I

MR

W =

83

400

kgF

WD

CG

= 1

7.5

% M

AC

AT

A/C

WE

IGH

T =

83

400

kg

(2)

MR

W =

80

400

kgM

RW

= 8

0 40

0 kg

AF

T C

G =

41

% M

AC

AT

A/C

WE

IGH

T =

80

400

kgA

FT

CG

= 4

0.7

% M

AC

AT

A/C

WE

IGH

T =

80

400

kgM

RW

= 8

3 40

0 kg

AF

T C

G =

41

% M

AC

AT

A/C

WE

IGH

T =

83

400

kg

80 4

0017

7 25

018

750

8 51

035

550

16 1

2030

750

84 7

5038

440

27 5

5012

490

67 8

00

83 4

0018

3 87

518

900

8 57

036

300

16 4

7087

975

39 9

1028

575

12 9

6070

375

31 9

20

G H I G H I

A/C

CO

DE

N_AC_070300_1_0340101_01_00

Maximum Pavement LoadsFIGURE-7-3-0-991-034-A01

7-3-0Page 3

Jun 01/12


**ON A/C A321-100 A321-200

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

J83

400

VM

G (

PE

R S

TR

UT

)V

NG

183

875

18 8

758

560

36 2

5016

440

87 6

7539

770

28 5

7512

960

70 1

5031

820

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

HM

AX

IMU

M H

OR

IZO

NT

AL

GR

OU

ND

LO

AD

FR

OM

BR

AK

ING

(1)

MR

W =

83

400

kgM

RW

= 8

3 40

0 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

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

FW

D C

G =

17.

5 %

MA

C A

T A

/C W

EIG

HT

= 8

3 40

0 kg

FW

D C

G =

17.

5 %

MA

C A

T A

/C W

EIG

HT

= 8

3 40

0 kg

L M

MR

W =

83

400

kgF

WD

CG

= 1

7.5

% M

AC

AT

A/C

WE

IGH

T =

83

400

kg

(2)

MR

W =

83

400

kgM

RW

= 8

3 40

0 kg

AF

T C

G =

39.

7 %

MA

C A

T A

/C W

EIG

HT

= 7

9 53

8 kg

AF

T C

G =

41

% M

AC

AT

A/C

WE

IGH

T =

83

400

kgM

RW

= 8

3 40

0 kg

AF

T C

G =

41

% M

AC

AT

A/C

WE

IGH

T =

83

400

kg

83 4

0018

3 87

518

900

8 57

036

300

16 4

7031

920

87 9

7539

910

28 5

7512

960

70 3

75

J L M J L M

83 4

0018

3 87

518

900

8 57

036

300

16 4

7031

920

87 9

7539

910

28 5

7512

960

70 3

75

A/C

CO

DE

N_AC_070300_1_0350101_01_00


7-3-0Page 4

Jun 01/12


**ON A/C A321-100 A321-200

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

O83

400

VM

G (

PE

R S

TR

UT

)V

NG

183

875

18 8

758

560

36 2

5016

440

87 6

7539

770

28 5

7512

960

70 1

5031

820

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

HM

AX

IMU

M H

OR

IZO

NT

AL

GR

OU

ND

LO

AD

FR

OM

BR

AK

ING

(1)

MR

W =

83

400

kgM

RW

= 8

5 40

0 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

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

FW

D C

G =

17.

5 %

MA

C A

T A

/C W

EIG

HT

= 8

3 40

0 kg

FW

D C

G =

18.

3 %

MA

C A

T A

/C W

EIG

HT

= 8

5 40

0 kg

P Q

MR

W =

85

400

kgF

WD

CG

= 1

7.5

% M

AC

AT

A/C

WE

IGH

T =

85

400

kg

(2)

MR

W =

83

400

kgM

RW

= 8

5 40

0 kg

AF

T C

G =

39.

7 %

MA

C A

T A

/C W

EIG

HT

= 8

3 40

0 kg

AF

T C

G =

41

% M

AC

AT

A/C

WE

IGH

T =

85

400

kgM

RW

= 8

5 40

0 kg

AF

T C

G =

39.

1 %

MA

C A

T A

/C W

EIG

HT

= 8

5 40

0 kg

85 4

0018

8 27

518

950

8 60

036

775

16 6

8032

690

90 1

0040

860

29 2

5013

270

72 0

75

O P Q O P Q

85 4

0018

8 27

519

325

8 76

037

075

16 8

2032

530

89 6

5040

660

29 2

5013

270

71 7

00

A/C

CO

DE

N_AC_070300_1_0360101_01_00


7-3-0Page 5

Jun 01/12


**ON A/C A321-100 A321-200

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

R85

400

VM

G (

PE

R S

TR

UT

)V

NG

188

275

19 3

258

760

37 0

7516

820

89 6

5040

660

29 2

5013

270

71 7

0032

530

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

HM

AX

IMU

M H

OR

IZO

NT

AL

GR

OU

ND

LO

AD

FR

OM

BR

AK

ING

(1)

MR

W =

85

400

kgM

RW

= 8

7 40

0 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

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

FW

D C

G =

17.

5 %

MA

C A

T A

/C W

EIG

HT

= 8

5 40

0 kg

FW

D C

G =

17.

5 %

MA

C A

T A

/C W

EIG

HT

= 8

7 40

0 kg

S U

MR

W =

89

400

kgF

WD

CG

= 1

7.5

% M

AC

AT

A/C

WE

IGH

T =

89

400

kg

(2)

MR

W =

85

400

kgM

RW

= 8

7 40

0 kg

AF

T C

G =

39.

1 %

MA

C A

T A

/C W

EIG

HT

= 8

5 40

0 kg

AF

T C

G =

38.

5 %

MA

C A

T A

/C W

EIG

HT

= 8

7 40

0 kg

MR

W =

89

400

kgA

FT

CG

= 3

8 %

MA

C A

T A

/C W

EIG

HT

= 8

9 40

0 kg

87 4

0019

2 67

518

725

8 49

036

900

16 7

4033

440

92 1

5041

800

29 9

5013

580

73 7

25

R S U R S U

89 4

0019

7 10

020

225

9 18

038

850

17 6

2033

950

93 5

5042

440

30 6

2513

890

74 8

50

A/C

CO

DE

N_AC_070300_1_0370101_01_00


7-3-0Page 6

Jun 01/12


**ON A/C A321-200

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

V89

400

VM

G (

PE

R S

TR

UT

)V

NG

197

100

19 1

258

680

37 7

2517

110

94 1

2542

700

30 6

2513

890

75 3

0034

160

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

HM

AX

IMU

M H

OR

IZO

NT

AL

GR

OU

ND

LO

AD

FR

OM

BR

AK

ING

(1)

MR

W =

89

400

kgM

RW

= 8

9 40

0 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

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

FW

D C

G =

17.

5 %

MA

C A

T A

/C W

EIG

HT

= 8

9 40

0 kg

FW

D C

G =

17.

5 %

MA

C A

T A

/C W

EIG

HT

= 8

9 40

0 kg

X Z

MR

W =

91

400

kgF

WD

CG

= 1

7.5

% M

AC

AT

A/C

WE

IGH

T =

89

000

kg

(2)

MR

W =

89

400

kgM

RW

= 8

9 40

0 kg

AF

T C

G =

38

% M

AC

AT

A/C

WE

IGH

T =

89

400

kgA

FT

CG

= 3

8 %

MA

C A

T A

/C W

EIG

HT

= 8

9 40

0 kg

MR

W =

91

400

kgA

FT

CG

= 3

7.5

% M

AC

AT

A/C

WE

IGH

T =

91

400

kg

V X Z V X Z

91 4

0020

1 50

019

050

8 64

037

525

17 0

3034

880

96 1

2543

600

31 3

2514

200

76 9

00

A/C

CO

DE

89 4

0019

7 10

019

125

8 68

037

725

17 1

1094

125

42 7

0030

625

13 8

9075

300

34 1

60

A/C

CO

DE

N_AC_070300_1_0380101_01_00


7-3-0Page 7

Jun 01/12


**ON A/C A321-200

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

AA

93 4

00

VM

G (

PE

R S

TR

UT

)V

NG

205

900

18 8

258

530

37 8

0017

140

98 1

0044

490

32 0

0014

510

78 4

7535

590

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

HM

AX

IMU

M H

OR

IZO

NT

AL

GR

OU

ND

LO

AD

FR

OM

BR

AK

ING

(1)

MR

W =

93

400

kgM

RW

= 9

3 90

0 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

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

FW

D C

G =

19

% M

AC

AT

A/C

WE

IGH

T =

91

500

kgF

WD

CG

= 1

9.7

% M

AC

AT

A/C

WE

IGH

T =

91

500

kg

AB

(2)

MR

W =

93

400

kgM

RW

= 9

3 90

0 kg

AF

T C

G =

37

% M

AC

AT

A/C

WE

IGH

T =

93

400

kgA

FT

CG

= 3

6.9

% M

AC

AT

A/C

WE

IGH

T =

93

900

kg

AA

AB

AA

AB

A/C

CO

DE

93 9

0020

7 02

518

475

8 38

037

450

16 9

9098

575

44 7

2032

175

14 5

9078

875

35 7

70

A/C

CO

DE

N_AC_070300_1_0390101_01_00

Maximum Pavement LoadsMaximum Pavement LoadsFIGURE-7-3-0-991-039-A01

7-3-0Page 8

Jun 01/12



**ON A/C A321-100 A321-200

Landing Gear Loading on Pavement

1. General

In the example shown in Section 7-4-1 Landing Gear Loading on Pavement, A/C Code C, the GrossAircraft Weight is 60 000 kg (132 275 lb) and the percentage of weight on the Main Landing Gear is95.7 %.

For these conditions the total weight on the Main Landing Gear is 57 420 kg (126 575 lb).

7-4-0Page 1

Jun 01/12



**ON A/C A321-100 A321-200

Landing Gear Loading on Pavement

1. This section gives Landing Gear Loading on Pavement.


7-4-1Page 1

Jun 01/12


**ON A/C A321-100

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

80

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)

MLW = 73 500 kg

MZFW = 69 500 kg

MTOW = 78 000 kg

CG FOR ACNCALCULATIONS

5 15 25 35 45 55

PERCENTAGE MAC

PERCENTAGE OF WEIGHT ON MAIN GEAR

A/C CODE C

LANDING

TAKE OFF

N_AC_070401_1_0650101_01_00

Landing Gear Loading on PavementFIGURE-7-4-1-991-065-A01

7-4-1Page 2

Jun 01/12


**ON A/C A321-200

86 88 90 92 94 96 98 10035

40

45

50

55

60

65

70

75

805 15 25 35 45 55

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)

PERCENTAGE MAC


MZFW = 69 500 kg

LANDING

MTOW = 78 000 kg

A/C CODE D

MLW = 73 500 kg


TAKE OFF

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

)

N_AC_070401_1_0660101_01_00


7-4-1Page 3

Jun 01/12


**ON A/C A321-100

N_AC_070401_1_0670101_01_00

TAKE OFF

35

40

45

50

55

60

65

70

75

80

35

40

45

50

55

60

65

70

75

80

LANDING

MTOW = 78 000 kg

MLW = 74 500 kg

MZFW = 70 500 kg

CG FOR ACNCALCULATIONSA/C CODE E

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


86 88 90 92 94 96 98 100

5 15 25 35 45 55


7-4-1Page 4

Jun 01/12


**ON A/C A321-100

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


86 88 90 92 94 96 98 10035

40

45

50

55

60

65

70

75

80

85

35

40

45

50

55

60

65

70

75

80

855 15 25 35 45 55

MTOW = 80 000 kg

LANDING

MLW = 73 500 kg

TAKE OFF

A/C CODE G

MZFW = 69 500 kg


N_AC_070401_1_0680101_01_00


7-4-1Page 5

Jun 01/12


**ON A/C A321-200

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


86 88 90 92 94 96 98 10035

40

45

50

55

60

65

70

75

80

85

35

40

45

50

55

60

65

70

75

80

855 15 25 35 45 55

MTOW = 80 000 kg

MLW = 73 500 kg

MZFW = 69 500 kg

LANDING


A/C CODE H

TAKE OFF

N_AC_070401_1_0690101_01_00


7-4-1Page 6

Jun 01/12


**ON A/C A321-100

N_AC_070401_1_0700101_01_00

86 88 90 92 94 96 98 100

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)


LANDING

MTOW = 83 000 kg

CG FOR ACN

MLW = 73 500 kg

CALCULATIONS

35

40

45

50

55

60

65

70

75

80

85

35

40

45

50

55

60

65

70

75

80

855 15 25 35 45 55

PERCENTAGE MAC

A/C CODE I

MZFW = 69 500 kg

TAKE OFF


7-4-1Page 7

Jun 01/12


**ON A/C A321-200

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)

MLW = 73 500 kg

MZFW = 69 500 kg

LANDING

MTOW = 83 000 kg


35

40

45

50

55

60

65

70

75

80

85

35

40

45

50

55

60

65

70

75

80

855 15 25 35 45 55

86 88 90 92 94 96 98 100


PERCENTAGE MAC

A/C CODE J

TAKE OFF

N_AC_070401_1_0710101_01_00


7-4-1Page 8

Jun 01/12


**ON A/C A321-100

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)


MTOW = 83 000 kg

MZFW = 70 500 kg


MLW = 74 500 kg

35

40

45

50

55

60

65

70

75

80

85

35

40

45

50

55

60

65

70

75

80

85

86 88 90 92 94 96 98 100

5 15 25 35 45 55

PERCENTAGE MAC

A/C CODE L

TAKE OFF

LANDING

N_AC_070401_1_0720101_01_00


7-4-1Page 9

Jun 01/12


**ON A/C A321-100

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)


MTOW = 83 000 kg

MLW = 75 000 kg

MZFW = 71 000 kg

86 88 90 92 94 96 98 10035

40

45

50

55

60

65

70

75

80

85

35

40

45

50

55

60

65

70

75

80

855 15 25 35 45 55

PERCENTAGE MAC

A/C CODE M


TAKE OFF

LANDING

N_AC_070401_1_0730101_01_00


7-4-1Page 10

Jun 01/12


**ON A/C A321-200

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 = 83 000 kg

MLW = 75 500 kg

MZFW = 71 500 kg

86 88 90 92 94 96 98 10035

40

45

50

55

60

65

70

75

80

85

35

40

45

50

55

60

65

70

75

80

855 15 25 35 45 55

A/C CODE O


TAKE OFF

LANDING

N_AC_070401_1_0740101_01_00

Landing Gear Loading on PavementLanding Gear Loading on Pavement

FIGURE-7-4-1-991-074-A01

7-4-1Page 11

Jun 01/12


**ON A/C A321-100

35

40

45

50

55

60

65

70

75

80

85

90

35

MTOW = 85 000 kg

MLW = 74 500 kg

LANDING

TAKE OFF

MZFW = 70 500 kg


A/C CODE P

35

40

45

50

55

60

65

70

75

80

85

90

86 88 90 92 94 96 98 100


5 15 25 35 45 55

PERCENTAGE MAC

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)

N_AC_070401_1_0750101_01_00


7-4-1Page 12

Jun 01/12


**ON A/C A321-200

35

40

45

50

55

60

65

70

75

80

85

90

3535

40

45

50

55

60

65

70

75

80

85

90

86 88 90 92 94 96 98 100


5 15 25 35 45 55

PERCENTAGE MAC

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)

MLW = 75 500 kg


MZFW = 71 500 kg

MTOW = 85 000 kg

A/C CODE Q

LANDING

TAKE OFF

N_AC_070401_1_0760101_01_00


7-4-1Page 13

Jun 01/12


**ON A/C A321-200


MLW = 77 800 kg

MZFW = 73 800 kg

MTOW = 85 000 kg

TAKE OFF

LANDING

A/C CODE R

35

40

45

50

55

60

65

70

75

80

85

90

3535

40

45

50

55

60

65

70

75

80

85

90

86 88 90 92 94 96 98 100


5 15 25 35 45 55

PERCENTAGE MAC

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)

N_AC_070401_1_0770101_01_00


7-4-1Page 14

Jun 01/12


**ON A/C A321-200

35

40

45

50

55

60

65

70

75

80

85

90

3535

40

45

50

55

60

65

70

75

80

85

90

86 88 90 92 94 96 98 100


5 15 25 35 45

PERCENTAGE MAC

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)

MTOW = 87 000 kg

MLW = 75 500 kg

MZFW = 71 500 kg


LANDING

TAKE OFF

A/C CODE S

N_AC_070401_1_0780101_01_00


7-4-1Page 15

Jun 01/12


**ON A/C A321-100

A/C CODE U

MTOW = 89 000 kg

35

40

45

50

55

60

65

70

75

80

85

90

3535

40

45

50

55

60

65

70

75

85

90

86 88 90 92 94 96 98 100


5 15 25 35 45 55

PERCENTAGE MAC

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)

MLW = 75 500 kg

80


MZFW = 71 500 kg

LANDING

TAKE OFF

N_AC_070401_1_0790101_01_00


7-4-1Page 16

Jun 01/12


**ON A/C A321-200

35

40

45

50

55

60

65

70

75

80

85

90

3535

40

45

50

55

60

65

70

75

85

90

86 88 90 92 94 96 98 100


5 15 25 35 45

PERCENTAGE MAC

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)

80


LANDING

A/C CODE V

MZFW = 71 500 kg

MLW = 75 500 kg

TAKE OFF

MTOW = 89 000 kg

N_AC_070401_1_0800101_01_00


7-4-1Page 17

Jun 01/12


**ON A/C A321-200

N_AC_070401_1_0810101_01_00

MLW = 77 800 kg


LANDING

MZFW = 73 800 kg

MTOW = 89 000 kg

35

40

45

50

55

60

65

70

75

80

85

90

3535

40

45

50

55

60

65

70

75

85

90

86 88 90 92 94 96 98 100


5 15 25 35 45

PERCENTAGE MAC

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)

80

A/C CODE X

TAKE OFF


7-4-1Page 18

Jun 01/12


**ON A/C A321-200

35

40

45

50

55

60

65

70

75

80

85

90

3535

40

45

50

55

60

65

70

75

85

90

86 88 90 92 94 96 98 100


5 15 25 35 45

PERCENTAGE MAC

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) 80

MLW = 77 800 kg


LANDING

MZFW = 73 800 kg

MTOW = 91 000 kg

TAKE OFF

95 95

A/C CODE Z

N_AC_070401_1_0820101_01_00


7-4-1Page 19

Jun 01/12


**ON A/C A321-200

N_AC_070401_1_0830101_01_00

35

40

45

50

55

60

65

70

75

80

85

90

3535

40

45

50

55

60

65

70

75

85

90

86 88 90 92 94 96 98 100


5 15 25 35 45

PERCENTAGE MAC

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) 80

95 95

MLW = 77 800 kg


LANDING

MTOW = 93 000 kg

TAKE OFF

MZFW = 73 800 kg

A/C CODE AA


7-4-1Page 20

Jun 01/12


**ON A/C A321-200

N_AC_070401_1_0840101_01_00

35

40

45

50

55

60

65

70

75

80

85

90

3535

40

45

50

55

60

65

70

75

85

90

86 88 90 92 94 96 98 100


5 15 25 35 45

PERCENTAGE MAC

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) 80

95 95

MLW = 77 800 kg


LANDING

MZFW = 73 800 kg

TAKE OFF

MTOW = 93 500 kg

A/C CODE AB


7-4-1Page 21

Jun 01/12



**ON A/C A321-100 A321-200

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 C for:- a CBR value of 10- an Annual Departure Level of 25 000- the Load on one MLG of 30 000 kg (66 150 lb).

For these conditions, the Flexible Pavement Thickness is 52.5 cm (20.7 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 A321-100 A321-200

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 A321-100

N_AC_070501_1_1080101_01_00

SUBGRADE STRENGTH − CBR

806050403020151063

[CENTIMETERS]

FLEXIBLE PAVEMENT THICKNESS

1 270 x 455 R22 (49 x 18−22) TIRESTIRE PRESSURE CONSTANT AT 12.8 bar (186 psi)

806050403020151063

10 15 20 30 40 60 80 100 120 150 180

[INCHES]

WEIGHT ON ONE MAIN LANDING GEAR37 510 kg (82 700 lb)

30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)

ANNUAL DEPARTURES*1 2003 0006 00015 00025 000*20 YEAR PAVEMENT LIFE

A/C CODE C

FOR ACN CALCULATIONS10 000 COVERAGES USED

ALPHA FACTOR = 0.9

N_AC_070501_1_1080101_01_00

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

Flexible Pavement RequirementsFIGURE-7-5-1-991-108-A01

7-5-1Page 2

Jun 01/12


**ON A/C A321-200


806050403020151063

[CENTIMETERS]



806050403020151063

10 15 20 30 40 60 80 100 120 150 180

[INCHES]

N_AC_070501_1_1090101_01_00


30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)


A/C CODE D


ALPHA FACTOR = 0.9



7-5-1Page 3

Jun 01/12


**ON A/C A321-100


806050403020151063

[CENTIMETERS]



806050403020151063

10 15 20 30 40 60 80 100 120 150 180

[INCHES]


30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)


A/C CODE E


ALPHA FACTOR = 0.9


N_AC_070501_1_1100101_01_00


7-5-1Page 4

Jun 01/12


**ON A/C A321-100


806050403020151063

[CENTIMETERS]



806050403020151063

10 15 20 30 40 60 80 100 120 150 180

[INCHES]


A/C CODE G


ALPHA FACTOR = 0.9


30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)


N_AC_070501_1_1110101_01_00


7-5-1Page 5

Jun 01/12


**ON A/C A321-200


806050403020151063

[CENTIMETERS]



806050403020151063

10 15 20 30 40 60 80 100 120 150 180

[INCHES]


30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)


A/C CODE H


ALPHA FACTOR = 0.9


N_AC_070501_1_1120101_01_00


7-5-1Page 6

Jun 01/12


**ON A/C A321-100


806050403020151063

[CENTIMETERS]



806050403020151063

10 15 20 30 40 60 80 100 120 150 180

[INCHES]


30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)


A/C CODE I


ALPHA FACTOR = 0.9


N_AC_070501_1_1130101_01_00


7-5-1Page 7

Jun 01/12


**ON A/C A321-200


806050403020151063

[CENTIMETERS]



806050403020151063

10 15 20 30 40 60 80 100 120 150 180

[INCHES]


A/C CODE J


ALPHA FACTOR = 0.9



30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)

N_AC_070501_1_1140101_01_00


7-5-1Page 8

Jun 01/12


**ON A/C A321-100


806050403020151063

[CENTIMETERS]



806050403020151063

10 15 20 30 40 60 80 100 120 150 180

[INCHES]


30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)


A/C CODE L


ALPHA FACTOR = 0.9


N_AC_070501_1_1150101_01_00

Flexible Pavement RequirementFlexible Pavement Requirements

FIGURE-7-5-1-991-115-A01

7-5-1Page 9

Jun 01/12


**ON A/C A321-100


806050403020151063

[CENTIMETERS]



806050403020151063

10 15 20 30 40 60 80 100 120 150 180

[INCHES]


30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)


A/C CODE M


ALPHA FACTOR = 0.9


N_AC_070501_1_1160101_01_00


7-5-1Page 10

Jun 01/12


**ON A/C A321-200


806050403020151063

[CENTIMETERS]



806050403020151063

10 15 20 30 40 60 80 100 120 150 180

[INCHES]


30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)


A/C CODE O


ALPHA FACTOR = 0.9


N_AC_070501_1_1170101_01_00


7-5-1Page 11

Jun 01/12


**ON A/C A321-100

806050403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES

TIRE PRESSURE CONSTANT AT 13.9 bar (202 psi)


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

806050403020151063


A/C CODE P ALPHA FACTOR = 0.9


40 860 kg (90 100 lb)

30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)

WEIGHT ON ONE MAIN LANDING GEAR


N_AC_070501_1_1180101_01_00


7-5-1Page 12

Jun 01/12


**ON A/C A321-200

806050403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES



10 15 20 30 40 60 80 100 120 150 180

[INCHES]

806050403020151063

40 660 kg (89 650 lb)

30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)


A/C CODE Q ALPHA FACTOR = 0.9

MAXIMUM POSSIBLE MAIN GEAR LOAD AT MAXIMUM RAMP WEIGHT AND AFT CG WEIGHT ON ONE MAIN LANDING GEAR


N_AC_070501_1_1190101_01_00


7-5-1Page 13

Jun 01/12


**ON A/C A321-200

806050403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES



10 15 20 30 40 60 80 100 120 150 180

[INCHES]

806050403020151063


A/C CODE R ALPHA FACTOR = 0.9



N_AC_070501_1_1200101_01_00


30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)


7-5-1Page 14

Jun 01/12


**ON A/C A321-200

806050403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES



10 15 20 30 40 60 80 100 120 150 180

[INCHES]

806050403020151063

N_AC_070501_1_1210101_01_00


A/C CODE S ALPHA FACTOR = 0.9




30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)


7-5-1Page 15

Jun 01/12


**ON A/C A321-100

806050403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES



10 15 20 30 40 60 80 100 120 150 180

[INCHES]

806050403020151063


A/C CODE U ALPHA FACTOR = 0.9




30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)

N_AC_070501_1_1220101_01_00


7-5-1Page 16

Jun 01/12


**ON A/C A321-200

806050403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES



10 15 20 30 40 60 80 100 120 150 180

[INCHES]

806050403020151063


A/C CODE V ALPHA FACTOR = 0.9




30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)

N_AC_070501_1_1230101_01_00


7-5-1Page 17

Jun 01/12


**ON A/C A321-200

806050403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES



10 15 20 30 40 60 80 100 120 150 180

[INCHES]

806050403020151063


ALPHA FACTOR = 0.9




30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)

N_AC_070501_1_1240101_01_00

A/C CODE X

Flexible Pavement RequirementFlexible Pavement Requirements

FIGURE-7-5-1-991-124-A01

7-5-1Page 18

Jun 01/12


**ON A/C A321-200

806050403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES

TIRE PRESSURE CONSTANT AT 15 bar (218 psi)


10 15 20 30 40 60 80 100 120 150 180

[INCHES]

806050403020151063

N_AC_070501_1_1250101_01_00


A/C CODE Z ALPHA FACTOR = 0.9




25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)30 000 kg (66 150 lb)


7-5-1Page 19

Jun 01/12


**ON A/C A321-200

806050403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES



10 15 20 30 40 60 80 100 120 150 180

[INCHES]

806050403020151063


A/C CODE AA ALPHA FACTOR = 0.9




30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)

N_AC_070501_1_1260101_01_00


7-5-1Page 20

Jun 01/12


**ON A/C A321-200

806050403020151063

[CENTIMETERS]


1 270 x 455 R22 (49 x 18−22) TIRES



10 15 20 30 40 60 80 100 120 150 180

[INCHES]

806050403020151063


A/C CODE AB ALPHA FACTOR = 0.9




30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

35 000 kg (77 150 lb)

N_AC_070501_1_1270101_01_00


7-5-1Page 21

Jun 01/12



**ON A/C A321-100 A321-200

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 CodeC for:The thickness (h) is shown at 20 inches with an LCN of 73.5.

For these conditions, the weight on one Main Landing Gear is 35 000 kg (77 150 lb).

7-6-0Page 1

Jun 01/12



**ON A/C A321-100 A321-200

Flexible Pavement Requirements - LCN Conversion

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


7-6-1Page 1

Jun 01/12


**ON A/C A321-100

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 10 580

120

6050

4030

EQUIVALENT SINGLE WHEEL LOAD [1 000 kg]

EQUIVALENT SINGLE WHEEL LOAD [1 000 lb]

1020304050607080

8070

6050

4030

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

4045

7010

0

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

90100

WE

IGH

T O

N O

NE

MA

IN

37 5

10 k

g

(82

700

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

C

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_070601_1_1110101_01_00

Flexible Pavement Requirements - LCN ConversionFIGURE-7-6-1-991-111-A01

7-6-1Page 2

Jun 01/12


**ON A/C A321-200

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 580

120

6050

4030



1020304050607080

8070

6050

4030

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

4045

7010

0

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

90100

WE

IGH

T O

N O

NE

MA

IN

37 5

10 k

g

(82

700

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

D

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

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_070601_1_1120101_01_00


7-6-1Page 3

Jun 01/12


**ON A/C A321-100

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 580

120

6050

4030



1020304050607080

8070

6050

4030

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

4045

7010

0

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

90100

WE

IGH

T O

N O

NE

MA

IN

37 5

10 k

g

(82

700

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

E

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

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_070601_1_1130101_01_00


7-6-1Page 4

Jun 01/12


**ON A/C A321-100

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 580

120

6050

4030



1020304050607080

8070

6050

4030

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

4045

7010

0

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.6

bar

(197

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

90100

WE

IGH

T O

N O

NE

MA

IN

38 4

70 k

g

(84

800

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

G

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

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_070601_1_1140101_01_00


7-6-1Page 5

Jun 01/12


**ON A/C A321-200

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 580

120

6050

4030



1020304050607080

8070

6050

4030

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

4045

7010

0

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.6

bar

(197

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

90100

WE

IGH

T O

N O

NE

MA

IN

38 4

40 k

g

(84

750

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

H

N_AC_070601_1_1150101_01_00

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

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


7-6-1Page 6

Jun 01/12


**ON A/C A321-100

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 580

120

6050

4030



1020304050607080

8070

6050

4030

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

4045

7010

0

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.6

bar

(197

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

90100

WE

IGH

T O

N O

NE

MA

IN

39 9

10 k

g

(87

975

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

I

N_AC_070601_1_1160101_01_00

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

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


7-6-1Page 7

Jun 01/12


**ON A/C A321-200

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 580

120

6050

4030



1020304050607080

8070

6050

4030

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

4045

7010

0

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.6

bar

(197

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

90100

WE

IGH

T O

N O

NE

MA

IN

39 7

70 k

g

(87

675

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

J

N_AC_070601_1_1170101_01_00

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

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


7-6-1Page 8

Jun 01/12


**ON A/C A321-100

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 580

120

6050

4030



1020304050607080

8070

6050

4030

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

4045

7010

0

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.6

bar

(197

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

90100

WE

IGH

T O

N O

NE

MA

IN

39 9

10 k

g

(87

975

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

L

N_AC_070601_1_1180101_01_00

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

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


7-6-1Page 9

Jun 01/12


**ON A/C A321-100

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 580

120

6050

4030



1020304050607080

8070

6050

4030

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

4045

7010

0

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.6

bar

(197

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

90100

WE

IGH

T O

N O

NE

MA

IN

39 9

10 k

g

(87

975

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

M

N_AC_070601_1_1190101_01_00

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

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


7-6-1Page 10

Jun 01/12


**ON A/C A321-200

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

35 30 25 20 15 10 580

120

6050

4030



1020304050607080

8070

6050

4030

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

20

4045

7010

0

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.6

bar

(197

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

90100

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

39 7

70 k

g

(87

675

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

O

N_AC_070601_1_1200101_01_00

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


7-6-1Page 11

Jun 01/12


**ON A/C A321-100

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

3.9

bar

(202

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES

8010

060

5040

30



1020304050607080

8070

6050

4030

10

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

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

90100

A/C

CO

DE

P

35 30 25 20 15 1045 540

WE

IGH

T O

N O

NE

MA

IN

40 8

60 k

g

(90

075

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

N_AC_070601_1_1210101_01_00

7012

0


7-6-1Page 12

Jun 01/12


**ON A/C A321-200

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

3.9

bar

(202

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES



1020304050607080

8070

6050

4030

10

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

)

90100

A/C

CO

DE

Q

35 30 25 20 15 1045 540

WE

IGH

T O

N O

NE

MA

IN

40 6

60 k

g

(89

650

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

N_AC_070601_1_1220101_01_00

8010

060

5040

30

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

7012

0


7-6-1Page 13

Jun 01/12


**ON A/C A321-200

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

3.9

bar

(202

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES



1020304050607080

8070

6050

4030

10

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

)

90100

A/C

CO

DE

R

35 30 25 20 15 1045 540

WE

IGH

T O

N O

NE

MA

IN

40 6

60 k

g

(89

650

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

N_AC_070601_1_1230101_01_00

8010

060

5040

30

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

7012

0


7-6-1Page 14

Jun 01/12


**ON A/C A321-200

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

4.6

bar

(212

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES



1020304050607080

8070

6050

4030

10

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

)

90100

A/C

CO

DE

S

35 30 25 20 15 1045 540

WE

IGH

T O

N O

NE

MA

IN

41 8

00 k

g

(92

150

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

8010

060

5040

30

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

7012

0

N_AC_070601_1_1240101_01_00


7-6-1Page 15

Jun 01/12


**ON A/C A321-100

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

4.6

bar

(212

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES



1020304050607080

8070

6050

4030

10

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

)

90100

A/C

CO

DE

U

35 30 25 20 15 1045 540

WE

IGH

T O

N O

NE

MA

IN

42 4

40 k

g

(93

575

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

8010

060

5040

30

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

7012

0

N_AC_070601_1_1250101_01_00


7-6-1Page 16

Jun 01/12


**ON A/C A321-200

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

4.6

bar

(212

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES



1020304050607080

8070

6050

4030

10

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

)

90100

A/C

CO

DE

V

35 30 25 20 15 1045 540

WE

IGH

T O

N O

NE

MA

IN

42 7

00 k

g

(94

125

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

N_AC_070601_1_1260101_01_00

8010

060

5040

30

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

7012

0


7-6-1Page 17

Jun 01/12


**ON A/C A321-200

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

4.6

bar

(212

psi

)1

270

x 45

5 R

22 (

49 x

18−

22)

TIR

ES



1020304050607080

8070

6050

4030

10

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

)

90100

A/C

CO

DE

X

35 30 25 20 15 1045 540

WE

IGH

T O

N O

NE

MA

IN

42 7

00 k

g

(94

125

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

N_AC_070601_1_1270101_01_00

8010

060

5040

30

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

7012

0


7-6-1Page 18

Jun 01/12


**ON A/C A321-200

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

5 ba

r (2

18 p

si)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

S



1020304050607080

8070

6050

4030

10

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

)

90100

A/C

CO

DE

Z

35 30 25 20 15 1045 540

WE

IGH

T O

N O

NE

MA

IN

43 6

00 k

g

(96

125

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

N_AC_070601_1_1280101_01_00

8010

060

5040

30

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

7012

0


7-6-1Page 19

Jun 01/12


**ON A/C A321-200

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

5 ba

r (2

18 p

si)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

S



1020304050607080

8070

6050

4030

10

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

)

90100

A/C

CO

DE

AA

35 30 25 20 15 1045 540

WE

IGH

T O

N O

NE

MA

IN

44 4

90 k

g

(98

075

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

N_AC_070601_1_1290101_01_00

8010

060

5040

30

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

7012

0


7-6-1Page 20

Jun 01/12


**ON A/C A321-200

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

5 ba

r (2

18 p

si)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

S



1020304050607080

8070

6050

4030

10

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

)

90100

WE

IGH

T O

N O

NE

MA

IN

44 7

20 k

g

(98

600

lb)

35 0

00 k

g

(77

150

lb)

30 0

00 k

g

(66

150

lb)

25 0

00 k

g

(55

125

lb)

LAN

DIN

G G

EA

R

20 0

00 k

g

(44

100

lb)

A/C

CO

DE

AB

35 30 25 20 15 1045 540

N_AC_070601_1_1300101_01_00

8010

060

5040

30

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

7012

0


7-6-1Page 21

Jun 01/12



**ON A/C A321-100 A321-200

Rigid Pavement Requirements - Portland Cement Association Design Method

1. General

In order to determine a particular Rigid Pavement Thickness, the Subgrade Modulus (k), theallowable working stress 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 C for:- a ”k” value of 80 MN/m3 (300 lbf/in3)- an allowable working stress of 31.6 kgf/cm2 (450 lbf/in2)- the load on one MLG of 30 000 kg (66 150 lb).For these conditions, the Rigid Pavement Thickness is 24.9 cm (9.8 in).

7-7-0Page 1

Jun 01/12



**ON A/C A321-100 A321-200

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 A321-100

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20

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

6

7

8

9

10

11

12

13

14


N_AC_070701_1_1090101_01_00


WEIGHT ON ONE MAINLANDING GEAR

A/C CODE C

N_AC_070701_1_1090101_01_00

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

37 510 kg (82 700 lb)

20 000 kg (44 100 lb)

Rigid Pavement Requirements (PCA)FIGURE-7-7-1-991-109-A01

7-7-1Page 2

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14


N_AC_070701_1_1100101_01_00



A/C CODE D

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

37 515 kg (82 700 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_1100101_01_00


7-7-1Page 3

Jun 01/12


**ON A/C A321-100

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14


N_AC_070701_1_1110101_01_00



A/C CODE E

N_AC_070701_1_1110101_01_00

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

37 510 kg (82 700 lb)

20 000 kg (44 100 lb)


7-7-1Page 4

Jun 01/12


**ON A/C A321-100

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14




A/C CODE G

N_AC_070701_1_1120101_01_00

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

38 470 kg (84 800 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


7-7-1Page 5

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14




A/C CODE H

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

38 440 kg (84 750 lb)

20 000 kg (44 100 lb)

N_AC_070701_1_1130101_01_00


7-7-1Page 6

Jun 01/12


**ON A/C A321-100

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14




A/C CODE I

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

39 905 kg (87 975 lb)

20 000 kg (44 100 lb)

N_AC_070701_1_1140101_01_00


7-7-1Page 7

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14



A/C CODE J


N_AC_070701_1_1150101_01_00

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

39 770 kg (87 675 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


7-7-1Page 8

Jun 01/12


**ON A/C A321-100

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14



A/C CODE L

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


N_AC_070701_1_1160101_01_00

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

39 905 kg (87 975 lb)

20 000 kg (44 100 lb)


7-7-1Page 9

Jun 01/12


**ON A/C A321-100

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14



A/C CODE M

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


N_AC_070701_1_1170101_01_00

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

39 905 kg (87 975 lb)

20 000 kg (44 100 lb)


7-7-1Page 10

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14



A/C CODE O

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³


N_AC_070701_1_1180101_01_00

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

39 770 kg (87 675 lb)

20 000 kg (44 100 lb)


7-7-1Page 11

Jun 01/12


**ON A/C A321-100

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14



WEIGHT ON ONEMAIN LANDING GEAR

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

40 865 kg (90 100 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_1190101_01_00

A/C CODE P


7-7-1Page 12

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14




35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

40 660 kg (89 650 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_1200101_01_00

A/C CODE Q


7-7-1Page 13

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14




35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

40 660 kg (89 650 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_1210101_01_00

A/C CODE R


7-7-1Page 14

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14




35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

41 805 kg (92 150 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_1220101_01_00

A/C CODE S


7-7-1Page 15

Jun 01/12


**ON A/C A321-100

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14




35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

42 435 kg (93 550 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_1230101_01_00

A/C CODE U


7-7-1Page 16

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14




35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

42 700 kg (94 125 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_1240101_01_00

A/C CODE V


7-7-1Page 17

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14




35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

42 700 kg (94 125 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_1250101_01_00

A/C CODE X


7-7-1Page 18

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14


1 270 x 455 R22 (49 x 18−22) TIRESTIRE PRESSURE CONSTANT AT 15 bar (218 psi)


35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

43 595 kg (96 125 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_1260101_01_00

A/C CODE Z


7-7-1Page 19

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14




35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

44 490 kg (98 100 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_1270101_01_00

A/C CODE AA


7-7-1Page 20

Jun 01/12


**ON A/C A321-200

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]

200

300

400

500

600

700

800

900

1000

34

32

30

28

26

24

22

20

18

16

70

58

52

45

39

33

27

20




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

6

7

8

9

10

11

12

13

14




35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)

44 715 kg (98 575 lb)

20 000 kg (44 100 lb)

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_1280101_01_00

A/C CODE AB


7-7-1Page 21

Jun 01/12



**ON A/C A321-100 A321-200

Radius of Relative Stiffness

1. This section gives Radius of Relative Stiffness.

7-8-1Page 1

Jun 01/12


**ON A/C A321-100 A321-200

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

43

43

12 (1 − ) k2

RADIUS OF RELATIVE STIFFNESS (L)VALUES IN INCHES

N_AC_070801_1_0040101_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-7-8-1-991-004-A01

7-8-1Page 2

Jun 01/12


7-8-2 Rigid Pavement Requirements - LCN Conversion

**ON A/C A321-100 A321-200

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 Cfor:- The Radius of Relative Stiffness is shown at 762 mm (30 in) with an LCN of 78.3.

For these conditions, the weight on one Main Landing Gear is 35 000 kg (77 150 lb).


7-8-2Page 1

Jun 01/12


**ON A/C A321-100

2030

4050

100

8070

602030405060708090

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.

8 ba

r (1

86 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

C

37 5

10 k

g

(82

700

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

RM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

G

N_AC_070802_1_1110101_01_00

Rigid Pavement Requirements - LCN ConversionFIGURE-7-8-2-991-111-A01

7-8-2Page 2

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

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.

8 ba

r (1

86 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

D

37 5

15 k

g

(82

700

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

RM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

G

N_AC_070802_1_1120101_01_00


7-8-2Page 3

Jun 01/12


**ON A/C A321-100

2030

4050

100

8070

602030405060708090

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.

8 ba

r (1

86 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

E

37 5

10 k

g

(82

700

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

RM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

G

N_AC_070802_1_1130101_01_00


7-8-2Page 4

Jun 01/12


**ON A/C A321-100

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

6 ba

r (1

97 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

G

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

N_AC_070802_1_1140101_01_00

38 4

70 k

g

(84

800

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R


7-8-2Page 5

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

6 ba

r (1

97 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

H

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

38 4

40 k

g

(84

750

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

N_AC_070802_1_1150101_01_00


7-8-2Page 6

Jun 01/12


**ON A/C A321-100

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

6 ba

r (1

97 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

I

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

39 9

05 k

g

(87

975

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

N_AC_070802_1_1160101_01_00


7-8-2Page 7

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

6 ba

r (1

97 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

J

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

N_AC_070802_1_1170101_01_00

39 7

70 k

g

(87

675

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R


7-8-2Page 8

Jun 01/12


**ON A/C A321-100

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

6 ba

r (1

97 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

L

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

39 9

05 k

g

(87

975

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

N_AC_070802_1_1180101_01_00


7-8-2Page 9

Jun 01/12


**ON A/C A321-100

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

6 ba

r (1

97 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

M

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

N_AC_070802_1_1190101_01_00

39 9

05 k

g

(87

975

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R


7-8-2Page 10

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

6 ba

r (1

97 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

O

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

39 7

70 k

g

(87

675

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

N_AC_070802_1_1200101_01_00


7-8-2Page 11

Jun 01/12


**ON A/C A321-100

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

9 ba

r (2

02 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

P

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

N_AC_070802_1_1210101_01_00

40 8

65 k

g

(90

100

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R


7-8-2Page 12

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

9 ba

r (2

02 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

Q

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

N_AC_070802_1_1220101_01_00

40 6

60 k

g

(89

650

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R


7-8-2Page 13

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

9 ba

r (2

02 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

R

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

40 6

60 k

g

(89

650

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

N_AC_070802_1_1230101_01_00


7-8-2Page 14

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

6 ba

r (2

12 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

S

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

41 8

05 k

g

(92

150

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

N_AC_070802_1_1240101_01_00


7-8-2Page 15

Jun 01/12


**ON A/C A321-100

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

6 ba

r (2

12 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

U

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

N_AC_070802_1_1250101_01_00

42 4

35 k

g

(93

550

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R


7-8-2Page 16

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

6 ba

r (2

12 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

V

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

42 7

00 k

g

(94

125

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

N_AC_070802_1_1260101_01_00


7-8-2Page 17

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

6 ba

r (2

12 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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

X

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

42 7

00 k

g

(94

125

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

N_AC_070802_1_1270101_01_00


7-8-2Page 18

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

15

bar

(218

psi

)


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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

Z

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

43 5

95 k

g

(96

125

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

N_AC_070802_1_1280101_01_00


7-8-2Page 19

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

15

bar

(218

psi

)


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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

AA

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

N_AC_070802_1_1290101_01_00

44 4

90 k

g

(98

100

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R


7-8-2Page 20

Jun 01/12


**ON A/C A321-200

2030

4050

100

8070

602030405060708090

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

15

bar

(218

psi

)


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

INN

OT

E:

ICA

O A

ER

OD

RO

ME

MA

NU

AL

PA

RT

2 P

AR

4.1

.3

Sec

ond

Edi

tion

1965


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

508

762

1 01

61

270

1 77

82

286

9010

080

7060

5040

93439 29 24 19 14

A/C

CO

DE

AB

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

44 7

15 k

g

(98

575

lb)

35 0

00 k

g

(77

150

lb)

20 0

00 k

g

(44

100

lb)

25 0

00 k

g

(55

125

lb)

30 0

00 k

g

(66

150

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

N_AC_070802_1_1300101_01_00


7-8-2Page 21

Jun 01/12


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

**ON A/C A321-100 A321-200

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 A321-100 A321-200

Radius of Relative Stiffness

1. This section gives Radius of Relative Stiffness.

7-8-4Page 1

Jun 01/12


**ON A/C A321-100 A321-200

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

EFFECT OF ON L VALUES

E, Young’s Modulus (10 , PSI)

EFFECT OF E ON L VALUES

BOTH CURVES ON THIS PAGE ARE USED TO ADJUST THE L VALUES OF TABLE 7−8−1NOTE:

, Poisson’s Ratio

E F

acto

rF

acto

r

N_AC_070804_1_0040101_01_02

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

FIGURE-7-8-4-991-004-A01

7-8-4Page 2

Jun 01/12


7-9-0 ACN/PCN Reporting System

**ON A/C A321-100 A321-200

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 CodeC, for an aircraft gross weight of 65 000 kg (143 300 lb) and low subgrade strength (code C), theACN for the flexible pavement is 38.3.

In the example shown in Section 7-9-2 Aircraft Classification Number -- Rigid Pavement, A/C CodeC, for an aircraft gross weight of 65 000 kg (143 300 lb) and medium subgrade strength (code B),the ACN for the rigid pavement is 39.7.

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 A321-100 A321-200

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 A321-100

1520253035404550

AIRCRAFT CLASSIFICATION NUMBER (ACN)

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.

8 ba

r (1

86 p

si)

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

7782

8690

9599

104

108

112

(x 1

000

lb)

117

121

126

130

134

139

143

148

152

157

161

165

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

170

174

60

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_1230101_01_00

A/C

CO

DE

C

ON

PA

VE

ME

NT

− A

/C C

OD

E C

Aircraft Classification Number -- Flexible PavementFIGURE-7-9-1-991-123-A01

7-9-1Page 2

Jun 01/12


**ON A/C A321-200

1520253035404550


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.

8 ba

r (1

86 p

si)

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

7782

8690

9599

104

108

112

(x 1

000

lb)

117

121

126

130

134

139

143

148

152

157

161

165

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

170

174

60

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

)

A/C

CO

DE

D

N_AC_070901_1_1240101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E D


7-9-1Page 3

Jun 01/12


**ON A/C A321-100

1520253035404550


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.

8 ba

r (1

86 p

si)

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

7782

8690

9599

104

108

112

(x 1

000

lb)

117

121

126

130

134

139

143

148

152

157

161

165

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

170

174

60

N_AC_070901_1_1250101_01_00

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

)

A/C

CO

DE

E

N_AC_070901_1_1250101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E E


7-9-1Page 4

Jun 01/12


**ON A/C A321-100

1520253035404550


1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

6 ba

r (1

97 p

si)

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

7782

8690

9599

104

108

112

(x 1

000

lb)

117

121

126

130

134

139

1431

4815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

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

)

A/C

CO

DE

G

N_AC_070901_1_1260101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E G


7-9-1Page 5

Jun 01/12


**ON A/C A321-200

1520253035404550


1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

6 ba

r (1

97 p

si)

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

0.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G

7782

8690

9599

104

108

112

(x 1

000

lb)

117

121

126

130

134

139

1431

4815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

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

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A/C

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H

ON

PA

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ME

NT

− A

/C C

OD

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IRE

ST

IRE

PR

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SU

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6 ba

r (1

97 p

si)

AC

N W

AS

DE

TE

RM

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D A

S R

EF

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CE

D IN

ICA

O A

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OD

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DE

SIG

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AN

UA

L P

AR

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AP

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R 1

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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

7782

8690

9599

104

108

112

(x 1

000

lb)

117

121

126

130

134

139

1431

4815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

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 −

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3 (U

LTR

A L

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)

A/C

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PA

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ME

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/C C

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PR

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SU

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r (1

97 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

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SIG

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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

9.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G

7782

8690

9599

104

108

112

(x 1

000

lb)

117

121

126

130

134

139

1431

4815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

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

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)

A/C

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PR

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6 ba

r (1

97 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

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DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

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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

7782

8690

9599

104

108

112

(x 1

000

lb)

117

121

126

130

134

139

1431

4815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

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

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)

A/C

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6 ba

r (1

97 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

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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

7782

8690

9599

104

108

112

(x 1

000

lb)

117

121

126

130

134

139

1431

4815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

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

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)

A/C

CO

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ON

PA

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ME

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/C C

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x 1

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) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

6 ba

r (1

97 p

si)

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

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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

9.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G

7782

8690

9599

104

108

112

(x 1

000

lb)

117

121

126

130

134

139

1431

4815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

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

)

A/C

CO

DE

O

ON

PA

VE

ME

NT

− A

/C C

OD

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x 1

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) T

IRE

ST

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PR

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SU

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r (2

02 p

si)

AC

N W

AS

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TE

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INE

D A

S R

EF

ER

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CE

D IN

ICA

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ER

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SIG

N M

AN

UA

L P

AR

T 3

CH

AP

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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

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GE

AR

LO

AD

ING

7782

8690

9599

104

108

112

(x 1

000

lb)

117

1211

2613

013

413

914

314

815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

90

192

196

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

)

A/C

CO

DE

P

65

ALP

HA

FA

CT

OR

= 0

.9

ON

PA

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ME

NT

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/C C

OD

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r (2

02 p

si)

AC

N W

AS

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D A

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EF

ER

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CE

D IN

ICA

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SIG

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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

9.1

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G

7782

8690

9599

104

108

112

(x 1

000

lb)

117

1211

2613

013

413

914

314

815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

90

192

196

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

)

A/C

CO

DE

Q

65

ALP

HA

FA

CT

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= 0

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NT

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/C C

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IRE

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PR

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9 ba

r (2

02 p

si)

AC

N W

AS

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D A

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EF

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CE

D IN

ICA

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SIG

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AN

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AR

T 3

CH

AP

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R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

9.1

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G

7782

8690

9599

104

108

112

(x 1

000

lb)

117

1211

2613

013

413

914

314

815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

90

192

196

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

)

A/C

CO

DE

R

65

ALP

HA

FA

CT

OR

= 0

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r (2

12 p

si)

AC

N W

AS

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CE

D IN

ICA

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AN

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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

8.53

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G

7782

8690

9599

104

108

112

(x 1

000

lb)

117

1211

2613

013

413

914

314

815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

90

192

196

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

)

A/C

CO

DE

S

65

ALP

HA

FA

CT

OR

= 0

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PR

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SU

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14.

6 ba

r (2

12 p

si)

AC

N W

AS

DE

TE

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D A

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EF

ER

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CE

D IN

ICA

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DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

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R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

8 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

7782

8690

9599

104

108

112

(x 1

000

lb)

117

1211

2613

013

413

914

314

815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

90

192

196

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

)

A/C

CO

DE

U

65

ALP

HA

FA

CT

OR

= 0

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/C C

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12 p

si)

AC

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AP

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R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

8 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

7782

8690

9599

104

108

112

(x 1

000

lb)

117

1211

2613

013

413

914

314

815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

90

192

196

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

)

A/C

CO

DE

V

65

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_1380101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E V


7-9-1Page 17

Jun 01/12


**ON A/C A321-200

1520253035404550


1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

6 ba

r (2

12 p

si)

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 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

7782

8690

9599

104

108

112

(x 1

000

lb)

117

1211

2613

013

413

914

314

815

215

716

1

7065

6055

5045

4035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75

55

80

174

60

85

165

170

187

179

183

90

192

196

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

)

A/C

CO

DE

X

65

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_1390101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E X


7-9-1Page 18

Jun 01/12


**ON A/C A321-200


1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

15

bar

(218

psi

)

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

7.49

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G

(x 1

000

lb)

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

)

A/C

CO

DE

Z

ALP

HA

FA

CT

OR

= 0

.9

1520253035404550

7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

7065

6055

5045

4035

75

55

80

174

60

85

165

170

187

179

183

90

192

196

6520

120

5

95

N_AC_070901_1_1400101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E Z


7-9-1Page 19

Jun 01/12


**ON A/C A321-200


1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

15

bar

(218

psi

)

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 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

(x 1

000

lb)

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

)

ALP

HA

FA

CT

OR

= 0

.9

A/C

CO

DE

AA

1520253035404550

7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

7065

6055

5045

4035

75

55

80

174

60

85

165

170

187

179

183

90

192

196

6520

120

5

95

N_AC_070901_1_1410101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E A

A


7-9-1Page 20

Jun 01/12


**ON A/C A321-200


1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

15

bar

(218

psi

)

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

6.88

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G

(x 1

000

lb)

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

)

ALP

HA

FA

CT

OR

= 0

.9

A/C

CO

DE

AB

1520253035404550

7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

7065

6055

5045

4035

75

55

80

174

60

85

165

170

187

179

183

90

192

196

6520

120

5

95

N_AC_070901_1_1420101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E A

B


7-9-1Page 21

Jun 01/12


7-9-2 Aircraft Classification Number - Rigid Pavement

**ON A/C A321-100 A321-200

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 A321-100

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

1 %

MA

C.

1520253035404550

3540

4550

5560

6570

75

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.

8 ba

r (1

86 p

si)

(x 1

000

kg)

(x 1

000

lb)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

60

80

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)

55

N_AC_070902_1_1640101_01_00

A/C

CO

DE

C

ON

PA

VE

ME

NT

− A

/C C

OD

E C

Aircraft Classification Number -- Rigid PavementFIGURE-7-9-2-991-164-A01

7-9-2Page 2

Jun 01/12


**ON A/C A321-200

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

1 %

MA

C.

1520253035404550

3540

4550

5560

6570

75

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.

8 ba

r (1

86 p

si)

(x 1

000

kg)

(x 1

000

lb)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

60

80

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)

55

N_AC_070902_1_1650101_01_00

A/C

CO

DE

D

ON

PA

VE

ME

NT

− A

/C C

OD

E D


7-9-2Page 3

Jun 01/12


**ON A/C A321-100

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

1 %

MA

C.

1520253035404550

3540

4550

5560

6570

75

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.

8 ba

r (1

86 p

si)

(x 1

000

kg)

(x 1

000

lb)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

60

80

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)

55

165

170

174

N_AC_070902_1_1660101_01_00

A/C

CO

DE

E

ON

PA

VE

ME

NT

− A

/C C

OD

E E


7-9-2Page 4

Jun 01/12


**ON A/C A321-100

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

1 %

MA

C.

1520253035404550

3540

4550

5560

6570

75

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

13.

6 ba

r (1

97 p

si)

(x 1

000

kg)

(x 1

000

lb)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

60

80

55

179

183

187

85

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)

N_AC_070902_1_1670101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E G

A/C

CO

DE

G


7-9-2Page 5

Jun 01/12


**ON A/C A321-200

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

0.7

% M

AC

.

1520253035404550

3540

4550

5560

6570

75

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

13.

6 ba

r (1

97 p

si)

(x 1

000

kg)

(x 1

000

lb)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

60

80

55

179

183

187

85

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)

N_AC_070902_1_1680101_01_00

A/C

CO

DE

H

ON

PA

VE

ME

NT

− A

/C C

OD

E H


7-9-2Page 6

Jun 01/12


**ON A/C A321-100

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

1 %

MA

C.

1520253035404550

3540

4550

5560

6570

75

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

13.

6 ba

r (1

97 p

si)

(x 1

000

kg)

(x 1

000

lb)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

60

80

55

179

183

187

85

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)

N_AC_070902_1_1690101_01_00

A/C

CO

DE

I

ON

PA

VE

ME

NT

− A

/C C

OD

E I


7-9-2Page 7

Jun 01/12


**ON A/C A321-200

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

9.7

% M

AC

.

1520253035404550

3540

4550

5560

6570

75

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

13.

6 ba

r (1

97 p

si)

(x 1

000

kg)

(x 1

000

lb)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

60

80

55

179

183

187

85

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)

N_AC_070902_1_1700101_01_00

A/C

CO

DE

J

ON

PA

VE

ME

NT

− A

/C C

OD

E J


7-9-2Page 8

Jun 01/12


**ON A/C A321-100

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

1 %

MA

C.

1520253035404550

3540

4550

5560

6570

75

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

13.

6 ba

r (1

97 p

si)

(x 1

000

kg)

(x 1

000

lb)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

60

80

55

179

183

187

85

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)

N_AC_070902_1_1710101_01_00

A/C

CO

DE

L

ON

PA

VE

ME

NT

− A

/C C

OD

E L


7-9-2Page 9

Jun 01/12


**ON A/C A321-100

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

1 %

MA

C.

1520253035404550

3540

4550

5560

6570

75

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

13.

6 ba

r (1

97 p

si)

(x 1

000

kg)

(x 1

000

lb)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

60

80

55

179

183

187

85

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)

N_AC_070902_1_1720101_01_00

A/C

CO

DE

M

ON

PA

VE

ME

NT

− A

/C C

OD

E M


7-9-2Page 10

Jun 01/12


**ON A/C A321-200

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

9.7

% M

AC

.

1520253035404550

3540

4550

5560

6570

75

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

13.

6 ba

r (1

97 p

si)

(x 1

000

kg)

(x 1

000

lb)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

60

80

55

179

183

187

85

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)

N_AC_070902_1_1730101_01_00

A/C

CO

DE

O

ON

PA

VE

ME

NT

− A

/C C

OD

E O


7-9-2Page 11

Jun 01/12


**ON A/C A321-100

1520253035404550

3545

5565

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

65 55

179

183

196

85

N_AC_070902_1_1740101_01_00

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)

192

187

A/C

CO

DE

P

60

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

9 ba

r (2

02 p

si)

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

ON

PA

VE

ME

NT

− A

/C C

OD

E P


7-9-2Page 12

Jun 01/12


**ON A/C A321-200

1520253035404550

3545

5565

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

65 55

179

183

196

85

192

187

60

N_AC_070902_1_1750101_01_00

A/C

CO

DE

Q

(x 1

000

lb)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

9 ba

r (2

02 p

si)

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

9.1

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

GO

N P

AV

EM

EN

T −

A/C

CO

DE

Q

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)


7-9-2Page 13

Jun 01/12


**ON A/C A321-200

1520253035404550

3545

5565

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

65 55

179

183

196

85

192

187

60

A/C

CO

DE

R

N_AC_070902_1_1760101_01_00

(x 1

000

lb)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

9 ba

r (2

02 p

si)

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

9.1

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

GO

N P

AV

EM

EN

T −

A/C

CO

DE

R

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)


7-9-2Page 14

Jun 01/12


**ON A/C A321-200

1520253035404550

3545

5565

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

65 55

179

183

196

85

192

187

60

A/C

CO

DE

S

N_AC_070902_1_1770101_01_00

(x 1

000

lb)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

6 ba

r (2

12 p

si)

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

8.53

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

GO

N P

AV

EM

EN

T −

A/C

CO

DE

S

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)


7-9-2Page 15

Jun 01/12


**ON A/C A321-100

1520253035404550

3545

5565

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

65 55

179

183

196

85

192

187

60

A/C

CO

DE

U

N_AC_070902_1_1780101_01_00

(x 1

000

lb)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

6 ba

r (2

12 p

si)

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 %

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 U

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)


7-9-2Page 16

Jun 01/12


**ON A/C A321-200

1520253035404550

3545

5565

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

65 55

179

183

196

85

192

187

60

A/C

CO

DE

V

N_AC_070902_1_1790101_01_00

(x 1

000

lb)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

6 ba

r (2

12 p

si)

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 %

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 V

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)


7-9-2Page 17

Jun 01/12


**ON A/C A321-200

1520253035404550

3545

5565

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

65 55

179

183

196

85

192

187

60

A/C

CO

DE

X

N_AC_070902_1_1800101_01_00

(x 1

000

lb)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

6 ba

r (2

12 p

si)

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 %

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 X

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)


7-9-2Page 18

Jun 01/12


**ON A/C A321-200

1520253035404550

3545

5565

75

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

65 55

179

183

196

85

192

187

60

A/C

CO

DE

Z

N_AC_070902_1_1810101_01_00

(x 1

000

lb)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

15

bar

(218

psi

)

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

7.49

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

GO

N P

AV

EM

EN

T −

A/C

CO

DE

Z

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)


7-9-2Page 19

Jun 01/12


**ON A/C A321-200

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


1535

4555

6575

7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

179

183

196

85

192

187

201

206

2535455565

9540

5060

7080

90

203040506070

N_AC_070902_1_1820101_01_00N_AC_070902_1_1820101_01_00

A/C

CO

DE

AA

(x 1

000

lb)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

15

bar

(218

psi

)

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 %

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 A

A

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)


7-9-2Page 20

Jun 01/12


**ON A/C A321-200

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


N_AC_070902_1_1830101_01_00

1535

4555

6575

7782

8690

9599

104

108

112

117

121

126

130

134

139

143

148

152

157

161

174

165

170

179

183

196

85

192

187

201

205

2535455565

9540

5060

7080

90

203040506070

A/C

CO

DE

AB

(x 1

000

lb)

1 27

0 x

455

R22

(49

x 1

8−22

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

15

bar

(218

psi

)

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

6.88

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

GO

N P

AV

EM

EN

T −

A/C

CO

DE

AB

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)


7-9-2Page 21

Jun 01/12


SCALED DRAWINGS

8-0-0 SCALED DRAWINGS

**ON A/C A321-100 A321-200

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 A321-100 A321-200

0 10 20 30 40 50FEET

0 5 10 15METERS

010

2030

4050

FE

ET

05

1015

ME

TE

RS

N_AC_080000_1_0040101_01_00

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

Scaled DrawingFIGURE-8-0-0-991-004-A01

8-0-0Page 2

Jun 01/12


AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 AIRCRAFT RESCUE AND FIRE FIGHTING

**ON A/C A321-100 A321-200

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 A321-100 A321-200

N_AC_100000_1_0010401_01_00

Front PageFIGURE-10-0-0-991-001-D01

10-0-0Page 2

Jun 01/12


**ON A/C A321-100 A321-200

N_AC_100000_1_0020401_01_00

Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-0-0-991-002-D01

10-0-0Page 3

Jun 01/12


**ON A/C A321-100 A321-200

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 A321-100 A321-200

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 A321-100 A321-200

N_AC_100000_1_0040401_01_00

Composite MaterialsFIGURE-10-0-0-991-004-D01

10-0-0Page 6

Jun 01/12


**ON A/C A321-100 A321-200

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 A321-100 A321-200

C L

N_AC_100000_1_0060401_01_00

Evacuation/Escape Slide/RaftFIGURE-10-0-0-991-006-D01

10-0-0Page 8

Jun 01/12


**ON A/C A321-100 A321-200

N_AC_100000_1_0070201_01_00

Pax/Crew Doors and Emergency ExitsFIGURE-10-0-0-991-007-B01

10-0-0Page 9

Jun 01/12


**ON A/C A321-100 A321-200

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 10

Jun 01/12


**ON A/C A321-100 A321-200

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

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CO

LD

OF

F

FA

UL

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HO

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IR

OF

F

FA

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AF

T IS

OL V

ALV

E

CA

RG

O

DIS

CH

SM

OK

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FW

D

DIS

CH

DIS

CH

SM

OK

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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

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AG

EN

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ST

TE

ST

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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

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OF

F

FA

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OF

F

FA

ULT

OF

F

FA

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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

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VV

35V

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OF

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A U T O

AC

BU

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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

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LEV

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ITC

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GC

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PR

ESS

UP

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A U T O

A U T O

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U

ON

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ULT

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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

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EM

ER

EX

IT L

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A U T OO

FFO

FF

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AR

M

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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

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ACT

LAN

DL

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OF

F

N_AC_100000_1_0120101_01_00

Control PanelsFIGURE-10-0-0-991-012-A01

10-0-0Page 11

Jun 01/12


**ON A/C A321-100 A321-200

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 12

Jun 01/12


**ON A/C A321-100 A321-200

N_AC_100000_1_0140401_01_00

Aircraft Ground ClearancesFIGURE-10-0-0-991-014-D01

10-0-0Page 13

Jun 01/12


**ON A/C A321-100 A321-200

N_AC_100000_1_0150101_01_00

Structural Break-in PointsFIGURE-10-0-0-991-015-A01

10-0-0Page 14

Jun 01/12

airbus ac a321 jun2012

Documents

rgeneral aircraft dimensions

purpose r purpose

airbus s

property of airbus

title ofillustrations

merge ofthe mfp

owners ofthe copyright

lightand heavy weight