aircraft characteristics airport and maintenance planning … · @a321 aircraft characteristics -...

@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: Nov 01/19

@A321AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

HIGHLIGHTS

Revision No. 26 - Nov 01/19

LOCATIONS CHGCODE

DESCRIPTIONS OF CHANGE

CHAPTER 1

Section 1-1

Subject 1-1-0

Purpose R ADDED ADDITIONAL CHARACTERISTICSOF A321NEO.MODIFIED INFORMATION RELATED TOA320 FAMILY CHARACTERISTICS.DELETED FLIGHT TEST PHASE ANDTRAINING PURPOSES INFORMATION FORTHE NEW ENGINE OPTION.

CHAPTER 2

Section 2-1

Subject 2-1-1

General Aircraft Characteristics Data R

Section 2-3

Subject 2-3-0

Ground Clearances R

FIGURE Ground Clearances forA321NEO-ACF

N ADDED ILLUSTRATION FOR GROUNDCLEARANCES FOR A321NEO-ACF.ILLUSTRATION ADDED

CHAPTER 5

Section 5-4

Subject 5-4-10

Waste Water System R DESCRIPTION TITLE UPDATED

FIGURE Ground Service Connections forA321NEO-ACF - Waste Tank Locationfor A321NEO-ACF

N ADDED ILLUSTRATION FOR WASTETANK LOCATION FOR A321NEO-ACF.ILLUSTRATION ADDED

CHAPTER 6

Section 6-3

Subject 6-3-2

HIGHLIGHTSPage 1

Nov 01/19


LOCATIONS CHGCODE


FIGURE Danger Areas of the Engines -CFM56-5B Series Engine

R REVISED ILLUSTRATION FORBREAKAWAY POWER.

FIGURE Danger Areas of the Engines -IAE V2500 Series Engine


FIGURE Danger Areas of the Engines -CFM LEAP-1A Engine


FIGURE Danger Areas of the Engines -PW 1100G Engine


CHAPTER 7

Section 7-2

Subject 7-2-0

FIGURE Landing Gear Footprint R ADDED WV050, WV051, WV056 ANDWV063 INFORMATION FOR LANDINGGEAR FOOTPRINT IN THE TABLE.ILLUSTRATION REVISED

Section 7-3

Subject 7-3-0

FIGURE Maximum Pavement Loads R ADDED INFORMATION FOR WV050,WV051, WV056 AND WV063INFORMATION FOR MAXIMUMPAVEMENT LOADS IN THE TABLE.ILLUSTRATION REVISED

Section 7-4

Subject 7-4-0

Landing Gear Loading on Pavement R

FIGURE Landing Gear Loading onPavement - WV009, MRW 78 400 kg, CG39.21%

R MODIFIED THE GRAPH FOR WV009 FORMLG.

FIGURE Landing Gear Loading onPavement - WV070, MRW 80 400 kg, CG37%

R MODIFIED THE GRAPH FOR WV070 FORMLG.

Section 7-5

Subject 7-5-0

FIGURE Flexible Pavement Requirements- WV009, MRW 78 400 kg, CG 39.21 %

R DELETED WV009, MRW 78 400 Kg, CG39.21 % FROM THE ILLUSTRATION.

HIGHLIGHTSPage 2

Nov 01/19


LOCATIONS CHGCODE


FIGURE Flexible Pavement Requirements- WV070, MRW 80 900 kg, CG 37 %

R REPLACED CG 39.71 % BY CG 37 % INTHE ILLUSTRATION TITLE.MODIFIED THE GRAPH FOR WV070 FORMLG.

FIGURE Flexible Pavement Requirements- WV071, MRW 97 400 kg, CG 36.07 %

R DELETED WV071, MRW 97 400 kg, CG36.07 % FROM THE ILLUSTRATION.

Section 7-7

Subject 7-7-0

FIGURE Rigid Pavement Requirements -WV004, MRW 78 400 kg, CG 41 %

R DELETED WV004, MRW 78 400 kg, CG41% FROM THE ILLUSTRATION.


R DELETED WV008, MRW 89 400 kg, CG38% FROM THE ILLUSTRATION.

FIGURE Rigid Pavement Requirements -WV009, MRW 78 400 kg, CG 39.21%

R DELETED WV009, MRW 78 400 kg, CG39.21% FROM THE ILLUSTRATION.

FIGURE Rigid Pavement Requirements -WV011, MRW 93 900 kg, CG 36.88 %

R DELETED WV011, MRW 93 900 kg, CG36.88% FROM THE ILLUSTRATION.


R REPLACED CG 39.71 % BY CG 37 % INTHE ILLUSTRATION TITLE.MODIFIED THE GRAPH FOR WV070 FORMLG.

FIGURE Rigid Pavement Requirements -WV071, MRW 97 400 kg, CG 36.07 %

R DELETED WV071, MRW 97 400 kg FROMTHE ILLUSTRATION.

Section 7-9

Subject 7-9-0

FIGURE Aircraft Classification Number -ACN Table

R MODIFIED THE ACN TABLE TO CHANGETHE RIGID AND FLEXIBLE PAVEMENTVALUES.

FIGURE Aircraft Classification Number -ACN Table

R MODIFIED THE ACN TABLE TO CHANGETHE RIGID AND FLEXIBLE PAVEMENTVALUES AND ADDED WV050, WV051,WV056, WV063, WV065, WV070 ANDWV080 INFORMATION ON ACN TABLE.

FIGURE Aircraft Classification Number -Flexible Pavement - WV070, MRW 80400 kg, CG 37 %

R REPLACED CG 39.71 % BY CG 37 % INTHE ILLUSTRATION TITLE.MODIFIED THE GRAPH FOR WV070 FORA321NEO.

HIGHLIGHTSPage 3

Nov 01/19


LOCATIONS CHGCODE


FIGURE Aircraft Classification Number -Flexible Pavement - WV071, MRW 97400 kg, CG 36.07 %

R MODIFIED THE GRAPH FOR WV071 FORA321NEO.

CHAPTER 10

Section 10-0

Subject 10-0-0

Aircraft Rescue and Fire Fighting R

FIGURE Front Page R

FIGURE Highly Flammable and HazardousMaterials and Components

R

FIGURE Highly Flammable and HazardousMaterials and Components for A321NEO-ACF

R

FIGURE Batteries Location and Access R

FIGURE Wheel/Brake Overheat - WheelSafety Area

R

FIGURE Composite Materials R

FIGURE Composite Materials forA321NEO-ACF

N ILLUSTRATION ADDED

FIGURE L/G Ground Lock Safety Devices R

FIGURE Emergency Evacuation Devices R

FIGURE Emergency Evacuation Devicesfor A321NEO-ACF

R

FIGURE Pax/Crew Doors and EmergencyExits

R

FIGURE Overwing Emergency Doors forA321NEO-ACF

N ILLUSTRATION ADDED

FIGURE FWD and AFT Lower DeckCargo Doors

R

FIGURE Control Panels R

FIGURE APU Access Door R

FIGURE Aircraft Ground Clearances R

FIGURE Structural Break-in Points R

HIGHLIGHTSPage 4

Nov 01/19


LIST OF EFFECTIVE CONTENT

Revision No. 26 - Nov 01/19

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 1

Subject 1-1-0

Purpose R Nov 01/19

Subject 1-2-0

Glossary Dec 01/17

CHAPTER 2

Subject 2-1-1

General Aircraft Characteristics Data R Nov 01/19

Subject 2-2-0

General Aircraft Dimensions Feb 01/18

FIGURE General Aircraft Dimensions - Wing Tip Fence Feb 01/18

FIGURE General Aircraft Dimensions May 01/15

FIGURE General Aircraft Dimensions for A321NEO-ACF Feb 01/18

Subject 2-3-0

Ground Clearances R Nov 01/19

FIGURE Ground Clearances - Wing Tip Fence Dec 01/15

FIGURE Ground Clearances - Sharklet Dec 01/15

FIGURE Ground Clearances May 01/15

FIGURE Ground Clearances for A321NEO-ACF N Nov 01/19

FIGURE Ground Clearances - Trailing Edge Flaps - Extended May 01/15

FIGURE Ground Clearances - Flap Tracks - Extended May 01/15

FIGURE Ground Clearances - Flap Tracks - Retracted May 01/15

FIGURE Ground Clearances - Flap Tracks - 1 + F May 01/15

FIGURE Ground Clearances - Aileron Down May 01/15

FIGURE Ground Clearances - Aileron Up May 01/15

FIGURE Ground Clearances - Spoilers - Extended May 01/15

L.E.C.Page 1

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Ground Clearances - Leading Edge Slats - Extended May 01/15

Subject 2-4-1

Interior Arrangements - Plan View Feb 01/18

FIGURE Interior Arrangements - Plan View - Typical Configuration -Single-Class, High Density

May 01/16

FIGURE Interior Arrangements - Plan View - Typical Configuration -Two-Class

May 01/16

FIGURE Interior Arrangements - Plan View for A321NEO-ACF -Typical Configuration - Single-Class, Standard

Feb 01/18

Subject 2-5-0

Interior Arrangements - Cross Section May 01/15

FIGURE Interior Arrangements - Cross Section - Economy Class, 6Abreast - Wider Aisle

May 01/15

FIGURE Interior Arrangements - Cross Section - First-Class May 01/15

Subject 2-6-0

Cargo Compartments Dec 01/17

FIGURE Cargo Compartments - Locations and Dimensions May 01/15

FIGURE Cargo Compartments - Loading Combinations Dec 01/17

FIGURE Cargo Compartments for A321NEO-ACF - Locations andDimensions for A321NEO-ACF

Dec 01/17

FIGURE Cargo Compartments for A321NEO-ACF - LoadingCombinations for A321NEO-ACF

Dec 01/17

Subject 2-7-0

Door Clearances Dec 01/18

FIGURE Door Identification and Location - Door Identification Dec 01/18

FIGURE Door Identification and Location for A321NEO-ACF - DoorIdentification for A321NEO-ACF

Dec 01/18

FIGURE Doors Clearances - Forward Passenger/Crew Doors May 01/15

FIGURE Doors Clearances for A321NEO-ACF - ForwardPassenger/Crew Doors for A321NEO-ACF

Dec 01/18

FIGURE Doors Clearances - Emergency Exits Dec 01/18

L.E.C.Page 2

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Doors Clearances for A321NEO-ACF - Emergency Exits forA321NEO-ACF

Dec 01/18

FIGURE Doors Clearances - Aft Passenger/Crew Doors Dec 01/18

FIGURE Doors Clearances for A321NEO-ACF - Aft Passenger/CrewDoors for A321NEO-ACF

Dec 01/18

FIGURE Door Clearances - Forward Cargo Compartment Door May 01/15

FIGURE Door Clearances - Forward Cargo Compartment Door May 01/15

FIGURE Doors Clearances - Aft Cargo Compartment Door Dec 01/18

FIGURE Doors Clearances - Bulk Cargo Compartment Door Dec 01/18

FIGURE Doors Clearances - Main Landing Gear Doors May 01/15

FIGURE Doors Clearances - Radome May 01/15

FIGURE Doors Clearances - APU and Nose Landing Gear Doors May 01/15

Subject 2-8-0

Escape Slides Dec 01/18

FIGURE Escape Slides - Location Feb 01/18

FIGURE Escape Slides - Dimensions Dec 01/18

FIGURE Escape Slides for A321NEO-ACF - Location for A321NEO-ACF

Dec 01/18

FIGURE Escape Slides for A321NEO-ACF - Dimensions forA321NEO-ACF

Dec 01/18

Subject 2-9-0

Landing Gear May 01/14

FIGURE Landing Gear - Main Landing Gear - Twin-Wheel May 01/14

FIGURE Landing Gear - Main Landing Gear Dimensions - Twin-Wheel May 01/14

FIGURE Landing Gear - Nose Landing Gear May 01/14

FIGURE Landing Gear - Nose Landing Gear Dimensions May 01/14

Landing Gear Maintenance Pits May 01/14

FIGURE Landing Gear Maintenance Pits - Maintenance Pit Envelopes May 01/14

FIGURE Landing Gear Maintenance Pits - Maintenance Pit Envelopes May 01/14

Subject 2-10-0

L.E.C.Page 3

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

Exterior Lighting May 01/15

FIGURE Exterior Lighting May 01/14




Subject 2-11-0

Antennas and Probes Location May 01/14

FIGURE Antennas and Probes - Location May 01/14

Subject 2-12-0

Auxiliary Power Unit Dec 01/15

FIGURE Auxiliary Power Unit - Access Doors Dec 01/15

FIGURE Auxiliary Power Unit - General Layout Dec 01/15

Engine and Nacelle May 01/17

FIGURE Power Plant Handling - Major Dimensions - CFM56 SeriesEngine

May 01/14

FIGURE Power Plant Handling - Major Dimensions - CFM56 SeriesEngine

May 01/14

FIGURE Power Plant Handling - Fan Cowls - CFM56 Series Engine May 01/17

FIGURE Power Plant Handling - Thrust Reverser Cowls - CFM56Series Engine

May 01/17

FIGURE Power Plant Handling - Major Dimensions - IAE V2500Series Engine

May 01/14

FIGURE Power Plant Handling - Major Dimensions - IAE V2500Series Engine

May 01/14

FIGURE Power Plant Handling - Fan Cowls - IAE V2500 SeriesEngine

May 01/17

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

May 01/17

FIGURE Power Plant Handling - Major Dimensions - PW 1100GEngine

May 01/17

FIGURE Power Plant Handling - Fan Cowls - PW 1100G Engine May 01/17

L.E.C.Page 4

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Power Plant Handling - Thrust Reverser Halves - PW 1100GEngine

May 01/14

FIGURE Power Plant Handling - Major Dimensions - CFM LEAP-1AEngine

May 01/15

FIGURE Power Plant Handling - Major Dimensions - CFM LEAP-1AEngine

May 01/17

Subject 2-13-0

Leveling, Symmetry and Alignment May 01/14

FIGURE Location of the Leveling Points May 01/14

Subject 2-14-0

Jacking for Maintenance May 01/14

FIGURE Jacking for Maintenance - Jacking Point Locations May 01/15

FIGURE Jacking for Maintenance - Forward Jacking Point May 01/14

FIGURE Jacking for Maintenance - Wing Jacking Points May 01/14

FIGURE Jacking for Maintenance - Safety Stay May 01/15

FIGURE Jacking for Maintenance - Jacking Design May 01/15

FIGURE Loads at the Aircraft Jacking Points - Wing Jacking Pointand Forward Fuselage Jacking Point

May 01/14

FIGURE Jacking for Maintenance - Location of Shoring Cradles May 01/14

Jacking of the Landing Gear May 01/17

FIGURE Jacking of the Landing Gear - MLG Jacking Point Location -Twin Wheels

May 01/14

FIGURE Jacking of the Landing Gear - MLG Jacking with CantileverJack - Twin Wheels

May 01/14

FIGURE Jacking of the Landing Gear - NLG Jacking - Point Location May 01/14

FIGURE Jacking of the Landing Gear - Maximum Load Capacity toLift Each Jacking Point

May 01/17

FIGURE Jacking of the Landing Gear - Maximum Load Capacity toLift Each Jacking Point

May 01/17

CHAPTER 3

Subject 3-1-0

L.E.C.Page 5

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

General Information May 01/14

Subject 3-2-1

Payload/Range - ISA Conditions May 01/15

FIGURE Payload/Range - ISA Conditions May 01/15

FIGURE Payload/Range - ISA Conditions - Sharklet May 01/15

FIGURE Payload/Range - ISA Conditions Dec 01/18

Subject 3-3-1

Take-Off Weight Limitation - ISA Conditions Dec 01/18

FIGURE Take-Off Weight Limitation - ISA Conditions - CFM56Series Engine

May 01/14

FIGURE Take-Off Weight Limitation - ISA Conditions - IAE V2500Series Engine

May 01/14

FIGURE Take-Off Weight Limitation - ISA Conditions - LEAP-1ASeries Engine

Dec 01/18

Subject 3-3-2

Take-Off Weight Limitation - ISA +15˚C (+27˚F) Conditions Dec 01/18

FIGURE Take-Off Weight Limitation - ISA +15˚C (+27˚F)Conditions - CFM56 Series Engine

Dec 01/18

FIGURE Take-Off Weight Limitation - ISA +15˚C (+27˚F)Conditions - IAE V2500 Series Engine

Dec 01/18

FIGURE Take-Off Weight Limitation - ISA +15˚C (+27˚F)Conditions - LEAP-1A Series Engine

Dec 01/18

Subject 3-3-3

Aerodrome Reference Code Dec 01/18

Subject 3-4-1

Landing Field Length - ISA Conditions May 01/14

FIGURE Landing Field Length - ISA Conditions - CFM56 SeriesEngine

May 01/14

FIGURE Landing Field Length - ISA Conditions - IAE V2500 SeriesEngine

May 01/14

Subject 3-5-0

L.E.C.Page 6

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

Final Approach Speed Feb 01/18

CHAPTER 4

Subject 4-1-0


Subject 4-2-0

Turning Radii Dec 01/15

FIGURE Turning Radii, No Slip Angle - (Sheet 1) Dec 01/15

FIGURE Turning Radii, No Slip Angle - (Sheet 2) Dec 01/15

Subject 4-3-0

Minimum Turning Radii Dec 01/15

FIGURE Minimum Turning Radii May 01/14

Subject 4-4-0

Visibility from Cockpit in Static Position May 01/14

FIGURE Visibility from Cockpit in Static Position Dec 01/18

FIGURE Binocular Visibility Through Windows from Captain EyePosition

May 01/14

Subject 4-5-0

Runway and Taxiway Turn Paths May 01/14

Subject 4-5-1

135˚ Turn - Runway to Taxiway May 01/14

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

Dec 01/18

FIGURE 135˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

Dec 01/18

Subject 4-5-2

90˚ Turn - Runway to Taxiway May 01/14

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

Dec 01/18

FIGURE 90˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

Dec 01/18

Subject 4-5-3

L.E.C.Page 7

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

180˚ Turn on a Runway Feb 01/19

FIGURE 180˚ Turn on a Runway - Edge of Runway Method Feb 01/19

Subject 4-5-4

135˚ Turn - Taxiway to Taxiway May 01/14

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

Dec 01/18

Subject 4-5-5

90˚ Turn - Taxiway to Taxiway May 01/14

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

Dec 01/18

Subject 4-6-0

Runway Holding Bay (Apron) May 01/14

FIGURE Runway Holding Bay (Apron) May 01/14

Subject 4-7-0

Minimum Line-Up Distance Corrections Dec 01/18

FIGURE Minimum Line-Up Distance Corrections - 90˚ Turn onRunway Entry

May 01/14

FIGURE Minimum Line-Up Distance Corrections - 180˚ Turn onRunway Turn Pad

May 01/14

FIGURE Minimum Line-Up Distance Corrections - 180˚ Turn onRunway Width

May 01/14

Subject 4-8-0

Aircraft Mooring May 01/14

FIGURE Aircraft Mooring May 01/14

CHAPTER 5

Subject 5-1-1

Aircraft Servicing Arrangements May 01/14

Subject 5-1-2

Typical Ramp Layout - Open Apron May 01/14

FIGURE Typical Ramp Layout - Open Apron - Bulk Loading May 01/14

L.E.C.Page 8

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Typical Ramp Layout - Open Apron - ULD Loading May 01/14

Subject 5-1-3

Typical Ramp Layout - Gate May 01/14

FIGURE Typical Ramp Layout - Gate May 01/14

Subject 5-2-0

Terminal Operations - Full Servicing Turn Round Time Dec 01/18

FIGURE Full Servicing Turn Round Time Chart Dec 01/18

FIGURE Full Servicing Turn Round Time Chart for A321NEO-ACF Dec 01/18

Subject 5-3-0

Terminal Operations -Transit Turn Round Time Dec 01/18

FIGURE Outstation Turn Round Time Chart Dec 01/18

FIGURE Outstation Turn Round Time Chart for A321NEO-ACF Dec 01/18

Subject 5-4-1

Ground Service Connections Layout May 01/14

FIGURE Ground Service Connections Layout May 01/14

Subject 5-4-2

Grounding (Earthing) Points May 01/14

FIGURE Ground Service Connections - Grounding (Earthing) Points -Landing Gear

May 01/14

FIGURE Ground Service Connections - Grounding (Earthing) Points -Wing (If Installed)

May 01/14

FIGURE Ground Service Connections - Grounding (Earthing) Point -Avionics Compartment Door-Frame

May 01/14

FIGURE Ground Service Connections - Grounding (Earthing) Point -Engine Air Intake (If Installed)

May 01/14

Subject 5-4-3

Hydraulic Servicing May 01/16

FIGURE Ground Service Connections - Green System Ground ServicePanel

May 01/16

FIGURE Ground Service Connections - Blue System Ground ServicePanel

May 01/16

L.E.C.Page 9

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Ground Service Connections - Yellow System Ground ServicePanel

May 01/16

FIGURE Ground Service Connections - RAT May 01/16

Subject 5-4-4

Electrical System May 01/15

FIGURE Ground Service Connections - External Power Receptacles May 01/14

Subject 5-4-5

Oxygen System May 01/14

FIGURE Ground Service Connections - Oxygen System May 01/14

Subject 5-4-6

Fuel System May 01/14

FIGURE Ground Service Connections - Refuel/Defuel Control Panel May 01/14

FIGURE Ground Service Connections - Refuel/Defuel Couplings May 01/14

FIGURE Ground Service Connections - Overwing Gravity-Refuel Cap(If Installed)

May 01/14

FIGURE Ground Service Connections - Overpressure Protectors andNACA Vent Intake

May 01/14

Subject 5-4-7

Pneumatic System May 01/14

FIGURE Ground Service Connections - LP and HP GroundConnectors

May 01/14

Subject 5-4-8

Oil System May 01/14

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

May 01/14

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

May 01/14

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

May 01/14

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

May 01/14

L.E.C.Page 10

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

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

May 01/14

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

May 01/14

FIGURE Ground Service Connections - APU Oil Tank May 01/14

Subject 5-4-9

Potable Water System May 01/14

FIGURE Ground Service Connections - Potable Water Ground ServicePanels

May 01/14

FIGURE Ground Service Connections - Potable Water Tank Location May 01/14

Subject 5-4-10

Waste Water System R Nov 01/19

FIGURE Ground Service Connections - Waste Water Ground ServicePanel

May 01/14

FIGURE Ground Service Connections - Waste Tank Location May 01/14

FIGURE Ground Service Connections for A321NEO-ACF - WasteTank Location for A321NEO-ACF

N Nov 01/19

Subject 5-5-0

Engine Starting Pneumatic Requirements May 01/14

FIGURE Example for Use of the Charts May 01/14

FIGURE Engine Starting Pneumatic Requirements - IAE V2500 SeriesEngine

May 01/14

FIGURE Engine Starting Pneumatic Requirements - CFM56 Seriesand CFM LEAP-1A NEO Engine

May 01/14

FIGURE Engine Starting Pneumatic Requirements - PW 1100G NEOEngine

May 01/14

Subject 5-6-0

Ground Pneumatic Power Requirements May 01/15

FIGURE Ground Pneumatic Power Requirements - Heating May 01/14

FIGURE Ground Pneumatic Power Requirements - Cooling May 01/14

Subject 5-7-0

Preconditioned Airflow Requirements May 01/15

L.E.C.Page 11

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Preconditioned Airflow Requirements May 01/16

Subject 5-8-0

Ground Towing Requirements Dec 01/17

FIGURE Ground Towing Requirements Dec 01/17

FIGURE Ground Towing Requirements - PW 1100G Engine May 01/17

Subject 5-9-0

De-Icing and External Cleaning May 01/14

CHAPTER 6

Subject 6-1-0

Engine Exhaust Velocities and Temperatures Dec 01/15

Subject 6-1-1

Engine Exhaust Velocities Contours - Ground Idle Power Dec 01/15

FIGURE Engine Exhaust Velocities - Ground Idle Power -- CFM56-5BSeries Engine

Dec 01/15

FIGURE Engine Exhaust Velocities - Ground Idle Power -- IAE V2500Series Engine

Dec 01/15

FIGURE Engine Exhaust Velocities - Ground Idle Power -- CFMLEAP-1A Engine

Dec 01/15

FIGURE Engine Exhaust Velocities - Ground Idle Power -- PW 1100GEngine

Dec 01/15

Subject 6-1-2

Engine Exhaust Temperatures Contours - Ground Idle Power Dec 01/15

FIGURE Engine Exhaust Temperatures - Ground Idle Power --CFM56-5B Series Engine

Dec 01/15

FIGURE Engine Exhaust Temperatures - Ground Idle Power -- IAEV2500 Series Engine

Dec 01/15

FIGURE Engine Exhaust Temperatures - Ground Idle Power -- CFMLEAP-1A Engine

Dec 01/15

FIGURE Engine Exhaust Temperatures - Ground Idle Power -- PW1100G Engine

Dec 01/15

Subject 6-1-3

L.E.C.Page 12

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

Engine Exhaust Velocities Contours - Breakaway Power Dec 01/18

FIGURE Engine Exhaust Velocities - Breakaway Power 12% MTO --CFM LEAP-1A Engine

Dec 01/15

FIGURE Engine Exhaust Velocities - Breakaway Power 12% MTO --PW 1100G Engine

Dec 01/15

FIGURE Engine Exhaust Velocities - Breakaway Power 24% MTO --CFM LEAP-1A Engine

Dec 01/15

FIGURE Engine Exhaust Velocities - Breakaway Power 24% MTO --PW 1100G Engine

Dec 01/15

FIGURE Engine Exhaust Velocities - Breakaway Power - CFM56Series Engine

Dec 01/18

FIGURE Engine Exhaust Velocities - Breakaway Power - IAE V2500Series Engine

Dec 01/18

Subject 6-1-4

Engine Exhaust Temperatures Contours - Breakaway Power Dec 01/18

FIGURE Engine Exhaust Temperatures - Breakaway Power 12%MTO - CFM LEAP-1A Engine

Dec 01/15

FIGURE Engine Exhaust Temperatures - Breakaway Power 12%MTO - PW 1100G Engine

Dec 01/15

FIGURE Engine Exhaust Temperatures - Breakaway Power 24%MTO - CFM LEAP-1A Engine

Dec 01/15

FIGURE Engine Exhaust Temperatures - Breakaway Power 24%MTO - PW 1100G Engine

Dec 01/15

FIGURE Engine Exhaust Temperatures - Breakaway Power - CFM56Series Engine

Dec 01/18

FIGURE Engine Exhaust Temperatures - Breakaway Power - IAEV2500 Series Engine

Dec 01/18

Subject 6-1-5

Engine Exhaust Velocities Contours - Takeoff Power Dec 01/15

FIGURE Engine Exhaust Velocities - Takeoff Power -- CFM56-5BSeries Engine

Dec 01/15

FIGURE Engine Exhaust Velocities - Takeoff Power -- IAE V2500Series Engine

Dec 01/15

L.E.C.Page 13

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Engine Exhaust Velocities - Takeoff Power -- CFM LEAP-1AEngine

Dec 01/15

FIGURE Engine Exhaust Velocities - Takeoff Power -- PW 1100GEngine

Dec 01/15

Subject 6-1-6

Engine Exhaust Temperatures Contours - Takeoff Power Dec 01/15

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

Dec 01/15

FIGURE Engine Exhaust Temperatures - Takeoff Power -- IAE V2500Series Engine

Dec 01/15

FIGURE Engine Exhaust Temperatures - Takeoff Power - CFMLEAP-1A Engine

Dec 01/15

FIGURE Engine Exhaust Temperatures - Takeoff Power - PW 1100GEngine

Dec 01/15

Subject 6-3-0

Danger Areas of Engines Dec 01/18

Subject 6-3-1

Ground Idle Power Dec 01/15

FIGURE Danger Areas of the Engines - CFM56-5B Series Engine Dec 01/18

FIGURE Danger Areas of the Engines - IAE V2500 Series Engine Dec 01/18

FIGURE Danger Areas of the Engines - CFM LEAP-1A Engine Dec 01/18

FIGURE Danger Areas of the Engines - PW 1100G Engine Dec 01/18

Subject 6-3-2

Breakaway Power Feb 01/18

FIGURE Danger Areas of the Engines - CFM56-5B Series Engine R Nov 01/19

FIGURE Danger Areas of the Engines - IAE V2500 Series Engine R Nov 01/19

FIGURE Danger Areas of the Engines - CFM LEAP-1A Engine R Nov 01/19

FIGURE Danger Areas of the Engines - PW 1100G Engine R Nov 01/19

Subject 6-3-3

Take Off Power Feb 01/18

FIGURE Danger Areas of the Engine - CFM56-5B Series Engine Dec 01/18

L.E.C.Page 14

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Danger Areas of the Engine - IAE V2500 Series Engine Dec 01/18

FIGURE Danger Areas of the Engine - CFM LEAP-1A Engine Dec 01/18

FIGURE Danger Areas of the Engine - PW 1100G Engine Dec 01/18

Subject 6-4-1

APU - APIC & GARRETT May 01/14

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

May 01/14

CHAPTER 7

Subject 7-1-0


Subject 7-2-0

Landing Gear Footprint May 01/16

FIGURE Landing Gear Footprint May 01/14

FIGURE Landing Gear Footprint Dec 01/18

FIGURE Landing Gear Footprint R Nov 01/19

Subject 7-3-0

Maximum Pavement Loads May 01/15

FIGURE Maximum Pavement Loads May 01/16

FIGURE Maximum Pavement Loads Dec 01/18

FIGURE Maximum Pavement Loads R Nov 01/19

Subject 7-4-0

Landing Gear Loading on Pavement R Nov 01/19

FIGURE Landing Gear Loading on Pavement - WV004, MRW 78 400kg, CG 41%

May 01/14


May 01/14

FIGURE Landing Gear Loading on Pavement - WV009, MRW 78 400kg, CG 39.21%

R Nov 01/19


May 01/14

L.E.C.Page 15

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE


R Nov 01/19


Dec 01/17

Subject 7-5-0

Flexible Pavement Requirements - US Army Corps of EngineersDesign Method

Dec 01/17

FIGURE Flexible Pavement Requirements - WV004, MRW 78 400 kg,CG 41 %

May 01/14


May 01/14

FIGURE Flexible Pavement Requirements - WV009, MRW 78 400 kg,CG 39.21 %

R Nov 01/19


May 01/14


R Nov 01/19


R Nov 01/19

Subject 7-6-0

Flexible Pavement Requirements - LCN Conversion May 01/15

Subject 7-7-0

Rigid Pavement Requirements - Portland Cement Association DesignMethod

Dec 01/17

FIGURE Rigid Pavement Requirements - WV004, MRW 78 400 kg,CG 41 %

R Nov 01/19


R Nov 01/19

FIGURE Rigid Pavement Requirements - WV009, MRW 78 400 kg,CG 39.21%

R Nov 01/19

FIGURE Rigid Pavement Requirements - WV011, MRW 93 900 kg,CG 36.88 %

R Nov 01/19


R Nov 01/19

L.E.C.Page 16

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Rigid Pavement Requirements - WV071, MRW 97 400 kg,CG 36.07 %

R Nov 01/19

Subject 7-8-0

Rigid Pavement Requirements - LCN Conversion May 01/15

Subject 7-9-0

Aircraft Classification Number - Flexible and Rigid Pavements May 01/16

FIGURE Aircraft Classification Number - ACN Table Dec 01/18

FIGURE Aircraft Classification Number - Flexible Pavement - WV004,MRW 78 400 kg, CG 41 %

May 01/14


May 01/14

FIGURE Aircraft Classification Number - ACN Table R Nov 01/19

FIGURE Aircraft Classification Number - Flexible Pavement - WV009,MRW 78 400 kg, CG 39.21 %

Dec 01/17


May 01/14

FIGURE Aircraft Classification Number - ACN Table R Nov 01/19


R Nov 01/19


R Nov 01/19

CHAPTER 8

Subject 8-0-0

Scaled Drawings Dec 01/15

FIGURE Scaled Drawing Dec 01/15

FIGURE Scaled Drawing Dec 01/15

CHAPTER 10

Subject 10-0-0

Aircraft Rescue and Fire Fighting R Nov 01/19

FIGURE Front Page R Nov 01/19

FIGURE Highly Flammable and Hazardous Materials and Components R Nov 01/19

L.E.C.Page 17

Nov 01/19


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Highly Flammable and Hazardous Materials and Componentsfor A321NEO-ACF

R Nov 01/19

FIGURE Batteries Location and Access R Nov 01/19

FIGURE Wheel/Brake Overheat - Wheel Safety Area R Nov 01/19

FIGURE Composite Materials R Nov 01/19

FIGURE Composite Materials for A321NEO-ACF N Nov 01/19

FIGURE L/G Ground Lock Safety Devices R Nov 01/19

FIGURE Emergency Evacuation Devices R Nov 01/19

FIGURE Emergency Evacuation Devices for A321NEO-ACF R Nov 01/19

FIGURE Pax/Crew Doors and Emergency Exits R Nov 01/19

FIGURE Overwing Emergency Doors for A321NEO-ACF N Nov 01/19

FIGURE FWD and AFT Lower Deck Cargo Doors R Nov 01/19

FIGURE Control Panels R Nov 01/19

FIGURE APU Access Door R Nov 01/19

FIGURE Aircraft Ground Clearances R Nov 01/19

FIGURE Structural Break-in Points R Nov 01/19

L.E.C.Page 18

Nov 01/19


TABLE OF CONTENTS

1 SCOPE

1-1-0 Introduction

1-2-0 Glossary

2 AIRCRAFT DESCRIPTION

2-1-1 General Aircraft Characteristics Data

2-2-0 General Aircraft Dimensions

2-3-0 Ground Clearances

2-4-1 Interior Arrangements - Plan View

2-5-0 Interior Arrangements - Cross Section

2-6-0 Cargo Compartments

2-7-0 Door Clearances and Location

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

3-2-1 Payload / Range - ISA Conditions

3-3-1 Take-off Weight Limitation - ISA Conditions

3-3-2 Take-off Weight Limitation - ISA +15˚C (+59˚F) Conditions

3-3-3 Aerodrome Reference Code

3-4-1 Landing Field Length - ISA Conditions

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

T.O.C.Page 1

Nov 01/19


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 Minimum Line-Up Distance Corrections

4-8-0 Aircraft Mooring

5 TERMINAL SERVICING

5-1-1 Aircraft Servicing Arrangements

5-1-2 Typical Ramp Layout - Open Apron

5-1-3 Typical Ramp Layout - Gate

5-2-0 Terminal Operations - Full Servicing Turn Round Time Chart

5-3-0 Terminal Operation - Outstation Turn Round Time Chart

5-4-1 Ground Service Connections

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 Oil System

5-4-9 Potable Water System

5-4-10 Waste Water System

5-5-0 Engine Starting Pneumatic Requirements

5-6-0 Ground Pneumatic Power Requirements

5-7-0 Preconditioned Airflow Requirements

5-8-0 Ground Towing Requirements

5-9-0 De-Icing and External Cleaning

6 OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

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

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

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

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

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

T.O.C.Page 2

Nov 01/19


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

6-3-0 Danger Areas of Engines

6-3-1 Ground Idle Power

6-3-2 Breakaway Power

6-3-3 Max Take Off Power

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

7-8-0 Rigid Pavement Requirements - LCN Conversion

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

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 3

Nov 01/19


SCOPE

1-1-0 Introduction

**ON A/C A321-100 A321-200 A321neo

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.

The A320 Family is the world’s best-selling single-aisle aircraft. An A320 takes off or landssomewhere in the world every 1.5 seconds of every day, the family has logged more than 117 millioncycles since entry-into-service and records a best-in-class dispatch reliability of 99.7%.

To ensure this true market leadership, Airbus continues to invest in improvements in the A320Family: enhancements to aerodynamics such as the sharklet wingtip devices, upgrades to the widestpassenger cabin in its class, the A320 Family neo. The latter combines top-of-class engine efficiencyoffered by two new engine options: the PW1100G PurePower from Pratt&Whitney and the LEAP-1Afrom CFM International with superior aerodynamics offered by the new sharklet devices.The A321neo is the largest member of the A320 Family and the market leader in its segmentenjoying around 80% of the market share. With its new door configuration, the A321neo is capable ofaccommodating up to 244 passengers while still providing high levels of passenger comfort.Compared to the previous A321 variant, the most visible modifications are a new rear section and amodified passenger door configuration, where the door located forward of the wing is removed andnew overwing emergency exits in the center section are introduced. The A321neo in new doorconfiguration is an option today and will become standard for all A321neos in the future.The A321neo in its new door configuration is also the base for a longer range variant known as theA321LR. The A321LR has an increased MTOW (Maximum Take-Off Weight) of 97 000 kg (213 848lb) and two or three underfloor fuel tanks allowing airlines to increase its range up to 4 000 nm (7408 km) for intercontinental flights.The A320neo family offers a minimum of 15% fuel savings and an additional flight range of about500 nm (926 km) and up to 20% fuel savings achieved through cabin innovations and efficiencyimprovements. For the environment, the A320neo family is also more eco-friendly, with 5 000 t (11023 113 lb) less CO2 emissions per year per aircraft and nearly 50% reduction in noise footprintcompared to previous generation aircraft.

1-1-0Page 1

Nov 01/19


1-2-0 Glossary

**ON A/C A321-100 A321-200 A321neo

Glossary

1. List of Abbreviations

A/C Aircraft

ACF Aircraft Cabin FlexACN Aircraft Classification NumberAMM Aircraft Maintenance ManualAPU Auxiliary Power Unit

B/C Business Class

CBR California Bearing Ratio

CC Cargo Compartment

CG Center of Gravity

CKPT Cockpit

E Young’s Modulus

ELEC Electric, Electrical, Electricity

ESWL Equivalent Single Wheel Load

FAA Federal Aviation AdministrationF/C First Class

FDL Fuselage Datum Line

FR FrameFSTE Full Size Trolley Equivalent

FWD ForwardGPU Ground Power UnitGSE Ground Support Equipment

HYD Hydraulic

ICAO International Civil Aviation Organisation

IDG Integrated Drive Generator

ISA International Standard Atmosphere

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

LH Left HandLPS Last Pax Seating

MAC Mean Aerodynamic Chord

1-2-0Page 1

Nov 01/19


MAX MaximumMIN MinimumMLG Main Landing Gear

NLG Nose Landing Gear

OAT Outside Air Temperature

PAX Passenger

PBB Passenger Boarding Bridge

PCA Portland Cement AssociationPCN Pavement Classification NumberPRM Passenger with Reduced Mobility

R Right

RH Right Hand

ULD Unit Load DeviceUS United StatesWV Weight Variant

Y/C Tourist Class

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

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

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

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

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

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

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

- Water Volume:Maximum volume of cargo compartment.

- Usable Fuel:Fuel available for aircraft propulsion.

1-2-0Page 2

Nov 01/19


AIRCRAFT DESCRIPTION

2-1-1 General Aircraft Characteristics Data

**ON A/C A321-100 A321-200 A321neo

General Aircraft 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

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

83 400 kg(183 865 lb)

83 400 kg(183 865 lb)

85 400 kg(188 275 lb)

78 400 kg(172 842 lb)

Maximum Take-Off Weight(MTOW)

83 000 kg(182 984 lb)

83 000 kg(182 984 lb)

85 000 kg(187 393 lb)

78 000 kg(171 961 lb)

Maximum Landing Weight (MLW) 73 500 kg(162 040 lb)

74 500 kg(164 244 lb)

74 500 kg(164 244 lb)

73 500 kg(162 040 lb)

Maximum Zero Fuel Weight(MZFW)

69 500 kg(153 221 lb)

70 500 kg(155 426 lb)

70 500 kg(155 426 lb)

69 500 kg(153 221 lb)



83 400 kg(183 865 lb)

78 400 kg(172 842 lb)

80 400 kg(177 252 lb)

89 400 kg(197 093 lb)


83 000 kg(182 984 lb)

78 000 kg(171 961 lb)

80 000 kg(176 370 lb)

89 000 kg(196 211 lb)


74 500 kg(164 244 lb)

73 500 kg(162 040 lb)

75 500 kg(166 449 lb)


71 000 kg(156 528 lb)

70 500 kg(155 426 lb)

69 500 kg(153 221 lb)

71 500 kg(157 630 lb)

2-1-1Page 1

Nov 01/19


**ON A/C A321-200

2. The following table provides characteristics of A321-200 models, these data are specific to eachweight variant:



89 400 kg(197 093 lb)

93 400 kg(205 912 lb)

89 400 kg(197 093 lb)

91 400 kg(201 502 lb)


89 000 kg(196 211 lb)

93 000 kg(205 030 lb)

89 000 kg(196 211 lb)

91 000 kg(200 621 lb)


77 800 kg(171 520 lb)

77 800 kg(171 520 lb)

77 800 kg(171 520 lb)


71 500 kg(157 630 lb)

73 800 kg(162 701 lb)

73 800 kg(162 701 lb)

73 800 kg(162 701 lb)



87 400 kg(192 684 lb)

85 400 kg(188 275 lb)

83 400 kg(183 865 lb)

83 400 kg(183 865 lb)


87 000 kg(191 802 lb)

85 000 kg(187 393 lb)

83 000 kg(182 984 lb)

83 000 kg(182 984 lb)


75 500 kg(166 449 lb)

75 500 kg(166 449 lb)

73 500 kg(162 040 lb)


71 500 kg(157 630 lb)

71 500 kg(157 630 lb)

71 500 kg(157 630 lb)

69 500 kg(153 221 lb)



80 400 kg(177 252 lb)

78 400 kg(172 842 lb)

85 400 kg(188 275 lb)

93 900 kg(207 014 lb)


80 000 kg(176 370 lb)

78 000 kg(171 961 lb)

85 000 kg(187 393 lb)

93 500 kg(206 132 lb)


73 500 kg(162 040 lb)

77 800 kg(171 520 lb)

77 800 kg(171 520 lb)


69 500 kg(153 221 lb)

69 500 kg(153 221 lb)

73 800 kg(162 701 lb)

73 800 kg(162 701 lb)

2-1-1Page 2

Nov 01/19


**ON A/C A321neo

3. The following table provides characteristics of A321NEO models, these data are specific to eachweight variant:

Aircraft CharacteristicsWV050 WV051 WV052 WV053 WV056 WV063 WV065

Maximum RampWeight (MRW)Maximum Taxi Weight(MTW)

89 400 kg(197 093

lb)

89 400 kg(197 093

lb)

93 900 kg(207 014

lb)

93 900 kg(207 014

lb)

92 900 kg(204 809

lb)

91 400 kg(201 502

lb)

90 900 kg(200 400

lb)

Maximum Take-OffWeight (MTOW)

89 000 kg(196 211

lb)

89 000 kg(196 211

lb)

93 500 kg(206 132

lb)

93 500 kg(206 132

lb)

92 500 kg(203 928

lb)

91 000 kg(200 621

lb)

90 500 kg(199 518

lb)

Maximum LandingWeight (MLW)

77 300 kg(170 417

lb)

79 200 kg(174 606

lb)

77 300 kg(170 417

lb)

79 200 kg(174 606

lb)

77 300 kg(170 417

lb)

79 200 kg(174 606

lb)

79 200 kg(174 606

lb)

Maximum Zero FuelWeight (MZFW)

73 300 kg(161 599

lb)

75 600 kg(166 669

lb)

73 300 kg(161 599

lb)

75 600 kg(166 669

lb)

73 300 kg(161 599

lb)

75 600 kg(166 669

lb)

75 600 kg(166 669

lb)

Aircraft CharacteristicsWV070 WV071

(ACF)WV072(ACF)

WV080


80 400 kg(177 252 lb)

97 400 kg(214 730 lb)

97 400 kg(214 730 lb)

95 400 kg(210 321 lb)


80 000 kg(176 370 lb)

97 000 kg(213 848 lb)

97 000 kg(213 848 lb)

95 000 kg(209 439 lb)


77 300 kg(170 417 lb)

79 200 kg(174 606 lb)

79 200 kg(174 606 lb)


67 000 kg(147 710 lb)

73 300 kg(161 599 lb)

75 600 kg(166 669 lb)

75 600 kg(166 669 lb)

**ON A/C A321-100 A321-200 A321neo

4. The following table provides characteristics of A321-100, A321-200 and A321NEO models, these dataare common to each weight variant:

Aircraft CharacteristicsStandardSeating Capacity

185 (Single-Class)202 (Single-Class) for A321 ACF

2-1-1Page 3

Nov 01/19


Aircraft Characteristics

23 700 l - 26 692 l * - 29 684 l **(6 261 US gal - 7 051 US gal * - 7 842 US gal **)

A321CEO CFMI A321CEO IAE A321NEO A321NX

ACT2992 l

(790 US gal)3121 l

(824 US gal)

Basic Aircraft24050 l

(6353 US gal)23700 l

(6261 US gal)23490 l

(6205 US gal)

With 1 ACT27042 l

(7144 US gal)26692 l

(7051 US gal)26482 l

(6996 US gal)26611 l

(7030 US gal)

With 2 ACTs30034 l

(7934 US gal)29684 l

(7842 US gal)29474 l

(7786 US gal)29782 l

(7868 US gal)

Usable FuelCapacity(density = 0.785kg/l)

With 3 ACTs(applicable only

for ACF)X X X

32853 l***(8679 USgal***)

PressurizedFuselage Volume(A/C nonequipped)

418 m3

(14 762 ft3)

PassengerCompartmentVolume

155 m3

(5 474 ft3)

Cockpit Volume 9 m3

(318 ft3)

Usable Volume,FWD CC

22.81 m3

(806 ft3)

Usable Volume,AFT CC

23.03 m3

(813 ft3)

Usable Volume,Bulk CC

5.88 m3

(208 ft3)

Water Volume,FWD CC

25.42 m3

(898 ft3)

Water Volume,AFT CC

25.69 m3

(907 ft3)

Water Volume,Bulk CC

7.76 m3

(274 ft3)

* OPTION: 1 ACT** OPTION: 2 ACT*** OPTION: 3 ACT

2-1-1Page 4

Nov 01/19


2-2-0 General Aircraft Dimensions

**ON A/C A321-100 A321-200 A321neo

General Aircraft Dimensions

1. This section provides general aircraft dimensions.

2-2-0Page 1

Nov 01/19


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

5.87 m(19.26 ft)

4.14 m(13.58 ft)

5.07 m(16.63 ft)

8.97 m(29.43 ft)

7.59 m(24.90 ft)

0.93 m(3.05 ft)

0.50 m(1.64 ft)

34.10 m(111.88 ft)

12.45 m(40.85 ft)

RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.NOTE:

16.90 m(55.45 ft)

N_AC_020200_1_0050101_01_04

General Aircraft DimensionsWing Tip Fence (Sheet 1 of 4)

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

2-2-0Page 2

Nov 01/19


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


44.51 m(146.03 ft)

5.75 m(18.86 ft) 6.07 m

(19.91 ft)

3.95 m(12.96 ft)

4.87 m(15.98 ft)

8.30 m(27.23 ft)

1.24 m(4.07 ft)

3.31 m(10.86 ft)

11.91 m(39.07 ft)

26.72 m(87.67 ft)

CFM56

V2500

15.46 m(50.72 ft)

15.39 m(50.49 ft)

0.76 m(2.49 ft)

1.82 m(5.97 ft)

1.50 m(4.92 ft)

N_AC_020200_1_0050104_01_02

General Aircraft DimensionsWing Tip Fence (Sheet 2 of 4)

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

2-2-0Page 3

Nov 01/19


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


5.87 m(19.26 ft)

4.14 m(13.58 ft)

5.07 m(16.63 ft)

35.80 m(117.45 ft)

8.97 m(29.43 ft)

7.59 m(24.90 ft)

0.93 m(3.05 ft)

0.50 m(1.64 ft)

3.79 m(12.43 ft)

2.43 m(7.97 ft)

12.45 m(40.85 ft)

16.90 m(55.45 ft)

N_AC_020200_1_0050103_01_02

General Aircraft DimensionsSharklet (Sheet 3 of 4)

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

2-2-0Page 4

Nov 01/19


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


44.51 m(146.03 ft)

6.07 m(19.91 ft)

5.75 m(18.86 ft)

3.95 m(12.96 ft) 3.31 m

(10.86 ft)

1.24 m(4.07 ft)

4.87 m(15.98 ft)

16.29 m(53.44 ft)

1.61 m(5.28 ft)3.22 m

(10.56 ft)

1.64 m(5.38 ft)

27.72 m(90.94 ft)

CFM56

V2500

15.46 m(50.72 ft)

15.39 m(50.49 ft)

8.30 m(27.23 ft)

11.91 m(39.07 ft)

N_AC_020200_1_0050105_01_02

General Aircraft DimensionsSharklet (Sheet 4 of 4)

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

2-2-0Page 5

Nov 01/19


**ON A/C A321neo


35.80 m(117.45 ft)

12.45 m(40.85 ft)

8.97 m(29.43 ft)

7.59 m(24.90 ft)

0.93 m(3.05 ft)

0.50 m(1.64 ft)

3.79 m(12.43 ft)

2.43 m(7.97 ft)

4.14 m(13.58 ft)

5.87 m(19.26 ft)

5.07 m(16.63 ft)

16.90 m(55.45 ft)

N_AC_020200_1_0100101_01_01

General Aircraft Dimensions(Sheet 1 of 2)

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

2-2-0Page 6

Nov 01/19


**ON A/C A321neo


3.31 m(10.86 ft)

1.24 m(4.07 ft)

44.51 m(146.03 ft)

5.75 m(18.86 ft) 6.07 m

(19.91 ft)

3.95 m(12.96 ft)

4.87 m(15.98 ft)

8.30 m(27.23 ft)

11.91 m(39.07 ft)

16.29 m(53.44 ft)

27.72 m(90.94 ft)

CFMLEAP−1A/PW 1100G

15.40 m(50.52 ft)

1.61 m(5.28 ft)3.22 m

(10.56 ft)

1.64 m(5.38 ft)

N_AC_020200_1_0100102_01_01

General Aircraft Dimensions(Sheet 2 of 2)

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

2-2-0Page 7

Nov 01/19


**ON A/C A321neo


35.80 m(117.45 ft)

12.45 m(40.85 ft)

8.97 m(29.43 ft)

7.59 m(24.90 ft)

0.93 m(3.05 ft)

0.50 m(1.64 ft)

3.79 m(12.43 ft)

2.43 m(7.97 ft)

4.14 m(13.58 ft)

5.87 m(19.26 ft)

5.07 m(16.63 ft)

16.90 m(55.45 ft)

N_AC_020200_1_0120101_01_00

General Aircraft Dimensions for A321NEO-ACF(Sheet 1 of 2)

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

2-2-0Page 8

Nov 01/19


**ON A/C A321neo


3.31 m(10.86 ft)

1.24 m(4.07 ft)

44.51 m(146.03 ft)

5.75 m(18.86 ft) 6.07 m

(19.91 ft)

3.95 m(12.96 ft)

4.87 m(15.98 ft)

8.30 m(27.23 ft)

11.91 m(39.07 ft)

16.29 m(53.44 ft)

27.72 m(90.94 ft)

CFMLEAP−1A/PW 1100G

15.40 m(50.52 ft)

1.61 m(5.28 ft)3.22 m

(10.56 ft)

1.64 m(5.38 ft)

N_AC_020200_1_0120102_01_00

General Aircraft Dimensions for A321NEO-ACF(Sheet 2 of 2)

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

2-2-0Page 9

Nov 01/19


2-3-0 Ground Clearances

**ON A/C A321-100 A321-200 A321neo

Ground Clearances

1. This section provides the height of various points of the aircraft, above the ground, for differentaircraft configurations.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,- An aircraft at Maximum Ramp Weight with a FWD CG and an AFT CG,- Aircraft on jacks, FDL at 4.60 m (15.09 ft).

NOTE : Passenger and cargo door ground clearances are measured from the center of the door silland from floor level.

2-3-0Page 1

Nov 01/19


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

m ft m ft m ftft11.1211.32

5.686.14

19.2619.72

3.47

5.96

3.48

1.781.825.92

11.3811.42

5.845.9719.4219.55

3.503.57

1.841.995.986.13

6.53

11.4811.71

6.04

19.6220.11

4.134.13

2.432.43

6.586.58

13.5513.55

7.977.97

21.5921.59

12.76 3.90 12.80 4.01 13.16 4.54 14.89

12.4317.8815.5239.27

2.53

3.765.344.61

11.85

0.78

12.3417.5215.1238.88

2.56

3.915.584.8612.10

0.89

12.8318.3115.9439.70

2.92

4.385.935.20

1.42

14.3719.4617.0640.85

4.66

12.45

13.7515.62

4.294.73

14.0715.52

4.304.88

14.1116.01

4.965.35

16.2717.55

A/C CONFIGURATION

mD1D2

F1F2F3F4

1.87

3.393.45

1.73

5.876.01

D3 3.89

W2HTAPVT

3.795.454.73

11.97

0.77

CP1W1

4.194.76

1.94 0.60 1.97 0.71 2.33 4.071.24N1 (CFM) 0.59

6.53 2.05 6.73 2.10 6.89 2.71 8.897.02 2.09 6.86 2.26 7.41 2.71 8.89

C1 1.99C2 2.14

5.38 1.62 5.31 1.76 5.77 2.26 7.41BF1 1.64

CG (25%)

DOORS

FUSELAGE

WINGS

TAILPLANE

ENGINE/NACELLE N1 (IAE)

MRW

FWD CG (19%) AFT CG (36.9%)

47 000 kg(103 617 lb)

OF THE DOOR SILL AND FROM FLOOR LEVEL.

NOTE:PASSENGER AND CARGO DOOR GROUND CLEARANCES ARE MEASURED FROM THE CENTER

7.22 2.14 7.02 2.33 7.64 2.75 9.02C3 2.20

11.84 3.53 11.58 3.73 12.24 4.13 13.55D4 3.61

D3 W2 W1CP1 D1 D2

N1

APD4

VT HT C3

F4

C2 F2 BF1 F1 C1F3

A/C JACKEDFDL = 4.60 m (15.09 ft)

N_AC_020300_1_0050101_01_06

Ground ClearancesWing Tip Fence

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

2-3-0Page 2

Nov 01/19


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


5.686.14

19.2619.72

3.47

5.96

3.48

1.781.825.92

11.3811.42

5.845.9719.4219.55

3.503.57

1.841.995.986.13

6.53

11.4811.71

6.04

19.6220.11

4.134.13

2.432.43

6.586.58

13.5513.55

7.977.97

21.5921.59

12.76 3.90 12.80 4.01 13.16 4.54 14.89

13.3217.8815.5239.27

2.53

4.035.344.61

11.85

0.78

13.2217.5215.1238.88

2.56

4.185.584.8612.10

0.89

13.7118.3115.9439.70

2.92

4.655.935.20

1.42

15.2619.4617.0640.85

4.66

12.45

13.7521.98

4.296.67

14.0721.88

4.306.82

14.1122.38

4.967.29

16.2723.92

A/C CONFIGURATION

mD1D2

F1F2F3F4

1.87

3.393.45

1.73

5.876.01

D3 3.89

W2HTAPVT

4.065.454.73

11.97

0.77

CP1W1

4.196.70

1.94 0.60 1.97 0.71 2.33 4.071.24N1 (CFM) 0.59

6.53 2.05 6.73 2.10 6.89 2.71 8.897.02 2.09 6.86 2.26 7.41 2.71 8.89

C1 1.99C2 2.14

5.38 1.62 5.31 1.76 5.77 2.26 7.41BF1 1.64

CG (25%)

DOORS

FUSELAGE

WINGS

TAILPLANE

ENGINE/NACELLE N1 (IAE)

MRW

FWD CG (19%) AFT CG (36.9%)

47 000 kg(103 617 lb)



7.22 2.14 7.02 2.33 7.64 2.75 9.02C3 2.20

11.84 3.53 11.58 3.73 12.24 4.13 13.55D4 3.61

VT C3 C2 F2 BF1 F1 C1HT

F4 F3

W2 W1CP1 APD1 D2

N1

D3 D4


N_AC_020300_1_0300101_01_02

Ground ClearancesSharklet

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

2-3-0Page 3

Nov 01/19


**ON A/C A321neo


5.686.14

19.2619.72

3.47

5.96

3.48

1.781.825.92

11.3811.42

5.845.9719.4219.55

3.503.57

1.841.995.986.13

6.53

11.4811.71

6.04

19.6220.11

4.134.13

2.432.43

6.586.58

13.5513.55

7.977.97

21.5921.59

12.76 3.90 12.80 4.01 13.16 4.54 14.89

13.3217.8815.5239.27

1.51

4.035.344.61

11.85

0.47

13.2217.5215.1238.88

1.54

4.185.584.8612.10

0.58

13.7118.3115.9439.70

1.90

4.655.935.20

1.13

15.2619.4617.0640.85

3.71

12.45

13.7521.98

4.296.67

14.0721.88

4.306.82

14.1122.38

4.967.29

16.2723.92

A/C CONFIGURATION

mD1D2

F1F2F3F4

1.87

3.393.45

1.73

5.876.01

D3 3.89

W2HTAPVT

4.065.454.73

11.97

0.46

CP1W1

4.196.70

1.51 0.47 1.54 0.58 1.90 3.711.130.46

6.53 2.05 6.73 2.10 6.89 2.71 8.897.02 2.09 6.86 2.26 7.41 2.71 8.89

C1 1.99C2 2.14

5.38 1.62 5.31 1.76 5.77 2.26 7.41BF1 1.64

CG (25%)

DOORS

FUSELAGE

WINGS

TAILPLANE

ENGINE/NACELLE N1 (PW 1100G)

MRW

FWD CG (19%) AFT CG (36.9%)

47 000 kg(103 617 lb)



7.22 2.14 7.02 2.33 7.64 2.75 9.02C3 2.20

11.84 3.53 11.58 3.73 12.24 4.13 13.55D4 3.61

N1 (CFMLEAP−1A)

VT C3 C2 F2 BF1 F1 C1HT

F4 F3

W2 W1CP1 APD1 D2

N1

D3 D4


N_AC_020300_1_0340101_01_01

Ground ClearancesFIGURE-2-3-0-991-034-A01

2-3-0Page 4

Nov 01/19


**ON A/C A321neo

5.686.14

19.2619.72 5.96

1.781.825.92

5.845.9719.4219.55

1.841.995.986.13

6.536.04

19.6220.11

2.432.43

6.586.58

7.977.97

21.5921.59

12.76 3.90 12.80 4.01 13.16 4.54 14.90

13.3217.8815.5239.27

1.51

4.035.344.61

11.85

0.47

13.2217.5215.1238.88

1.54

4.185.584.8612.10

0.58

13.7118.3115.9439.70

1.90

4.655.935.20

1.13

15.2619.4617.0640.85

3.71

12.45

13.7521.98

4.296.67

14.0721.88

4.306.82

14.1122.38

4.967.29

16.2723.92

F1F2F3F4

1.871.73

5.876.01

D3 3.89

W2HTAPVT

4.065.454.73

11.97

0.46

CP1W1

4.196.70

1.51 0.47 1.54 0.58 1.90 3.711.130.46

6.53 2.05 6.73 2.10 6.89 2.71 8.897.02 2.09 6.86 2.26 7.41 2.71 8.89

C1 1.99C2 2.14

5.38 1.62 5.31 1.76 5.77 2.26 7.41BF1 1.64

DOORS

FUSELAGE

WINGS

TAILPLANE

ENGINE/NACELLE N1 (PW 1100G)

7.22 2.14 7.02 2.33 7.64 2.75 9.02C3 2.20

11.84 3.53 11.58 3.73 12.24 4.13 13.55D4 3.61

N1 (CFMLEAP−1A)

m ft m ft m ftft11.12 3.47 11.38 3.50 11.48 4.13 13.55

A/C CONFIGURATION

mD1 3.39

CG (25%)

MRW

FWD CG (19%) AFT CG (36.9%)

47 000 kg(103 617 lb)



VT

C3 C2 F2 BF1 F1 C1

HT

F4 F3

W1CP1 APD1

N1

D4


D3 W2

12.47 3.83 3.93 12.89 4.46 14.63D2 3.80

D2

12.57

N_AC_020300_1_0480101_01_00

Ground Clearances for A321NEO-ACFFIGURE-2-3-0-991-048-A01

2-3-0Page 5

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

m ft m ft m ft

A

B

C

MAXIMUM RAMPWEIGHT AFT CG

MAXIMUM RAMPWEIGHT FWD CG

A/C IN MAINTENANCECONFIGURATION

MID CGDESCRIPTION

FLAP 1 INBD

FLAP 1 TAB INBD

D

FLAP 2 TAB OUTBD

FLAPS EXTENDED

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

FLAP 2 INBD

FLAP 2 OUTBD

E

F

FLAP 1 OUTBD

ABDEF C

N_AC_020300_1_0220101_01_01

Ground ClearancesTrailing Edge Flaps - Extended

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

2-3-0Page 6

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

m ft m ft m ft

A

B

C




MID CGDESCRIPTION

FLAP TRACK 2

FLAP TRACK 3

FLAP TRACK 4

FLAP TRACKS EXTENDED

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

ABC

N_AC_020300_1_0450101_01_00

Ground ClearancesFlap Tracks - Extended

FIGURE-2-3-0-991-045-A01

2-3-0Page 7

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

m ft m ft m ft

A

B

C

2.70

3.10

3.50

2.60

3.00

3.39

2.58

2.97

3.36

8.86 8.53 8.46

10.17

11.48

9.84

11.12

9.74

11.02

FLAP TRACKS RETRACTED




MID CGDESCRIPTION

FLAP TRACK 2

FLAP TRACK 3

FLAP TRACK 4

A B C

N_AC_020300_1_0230101_01_01

Ground ClearancesFlap Tracks - Retracted

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

2-3-0Page 8

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

m ft m ft m ft

A

B 2.31 2.21 2.187.58 7.25 7.15

1.95 1.85 1.836.40 6.07 6.00

FLAP TRACKS 1+F




MID CGDESCRIPTION

FLAP TRACK 3

FLAP TRACK 2

FLAP TRACK 4 C 2.89 2.78 2.759.48 9.12 9.02

A B C

N_AC_020300_1_0460101_01_00

Ground ClearancesFlap Tracks - 1 + F

FIGURE-2-3-0-991-046-A01

2-3-0Page 9

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

m ft m ft m ft

A

B 4.15 4.03 4.0013.62 13.22 13.12

3.81 3.70 3.6712.50 12.14 12.04

AILERON DOWN




MID CGDESCRIPTION

AILERON OUTBD

AILERON INBD

B A

N_AC_020300_1_0240101_01_01

Ground ClearancesAileron Down

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

2-3-0Page 10

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

m ft m ft m ft

A

B 4.53 4.42 4.3714.86 14.50 14.34

4.33 4.22 4.1914.21 13.85 13.75

AILERON UP




MID CGDESCRIPTION

AILERON OUTBD

AILERON INBD

B A

N_AC_020300_1_0470101_01_00

Ground ClearancesAileron Up

FIGURE-2-3-0-991-047-A01

2-3-0Page 11

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

m ft m ft m ft

B

C 4.08

4.20

4.34

3.97

4.10

4.23

3.95

4.07

4.20

13.39 13.02 12.96

13.78

14.24

13.45

13.88

13.35

13.78

SPOILERS EXTENDED

D

E

F

G

4.46

4.59

4.35

4.48

4.32

4.45

14.63 14.27 14.17

15.06 14.70 14.60

A 3.74

4.04

3.63

3.94

3.61

3.92

12.27 11.91 11.84

13.25 12.93 12.86




MID CG

SPOILER 1 OUTBD

SPOILER 2 INBD

SPOILER 2/3

SPOILER 3/4

SPOILER 4/5

SPOILER 5 OUTBD

SPOILER 1 INBD

DESCRIPTION

G F E D C B A

N_AC_020300_1_0250101_01_01

Ground ClearancesSpoilers - Extended

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

2-3-0Page 12

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

m ft m ft m ft

B

C 3.07

3.36

3.61

2.96

3.25

3.50

2.97

3.25

3.49

10.07 9.71 9.74

11.02

11.84

10.66

11.48

10.66

11.45

LEADING EDGE SLATS EXTENDED

D

E

F

G

3.85

4.08

3.74

3.96

3.72

3.94

12.63 12.27 12.20

13.39 12.99 12.93

A 2.58

2.98

2.47

2.88

2.50

2.89

8.46 8.10 8.20

9.78 9.45 9.48




MID CGDESCRIPTION

SLAT 1 OUTBD

SLAT 2 INBD

SLAT 2/3

SLAT 3/4

SLAT 4/5

SLAT 5 OUTBD

SLAT 1 INBD

A B C D E F G

N_AC_020300_1_0260101_01_01

Ground ClearancesLeading Edge Slats - ExtendedFIGURE-2-3-0-991-026-A01

2-3-0Page 13

Nov 01/19


2-4-1 Interior Arrangements - Plan View

**ON A/C A321-100 A321-200 A321neo

Interior Arrangements - Plan View

1. This section provides the typical interior configuration.

2-4-1Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

FWD PASSENGER

EMERGENCY EXIT

/CREW DOOR

EMERGENCY EXIT

FWD PASSENGER

EMERGENCY EXIT

/CREW DOOR

EMERGENCY EXIT

LAVATORYGALLEY

ATTENDANT SEAT

GALLEY ATTENDANT SEAT

LAVATORY

AFT PASSENGER/CREW DOOR


ECONOMYCLASS SEATS

ATTENDANT SEAT

(6 ABREAST − 28/29 in PITCH)

ATTENDANT SEATS 7

LAVATORIES 4

GALLEYS 2

ECONOMY CLASS 220 SEATS

ATTENDANT SEAT

LAVATORY

ATTENDANT SEAT

PASSENGER SEATS (220 TOTAL)

N_AC_020401_1_0040101_01_02

Interior Arrangements - Plan ViewTypical Configuration - Single-Class, High Density

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

2-4-1Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

FWD PASSENGER

EMERGENCY EXIT

/CREW DOOR

EMERGENCY EXIT

FWD PASSENGER

EMERGENCY EXIT

/CREW DOOR

EMERGENCY EXIT

LAVATORYGALLEY

ATTENDANT SEAT


LAVATORY

LAVATORY



ECONOMYCLASS SEATS

ATTENDANT SEAT

ATTENDANT SEAT

GALLEY

FIRSTCLASS SEATS


(6 ABREAST − 32 in PITCH)

ATTENDANT SEATS 6

LAVATORIES 4

GALLEYS 3


(4 ABREAST − 36 in PITCH)FIRST CLASS 16 SEATS

N_AC_020401_1_0060101_01_06

Interior Arrangements - Plan ViewTypical Configuration - Two-Class

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

2-4-1Page 3

Nov 01/19


**ON A/C A321neo

(6 ABREAST − 32 in PITCH)

ATTENDANT SEATS 5

LAVATORIES 3

GALLEYS 2



GALLEY LAVATORY

FWD PASSENGER/CREW DOOR

FWD PASSENGER/CREW DOOR




ECONOMYCLASS SEATS

EMERGENCY EXITEMERGENCY EXIT

EMERGENCY EXIT EMERGENCY EXIT

ATTENDANT SEAT

EMERGENCY EXIT EMERGENCY EXIT(optional) (optional)

ATTENDANT SEAT

LAVATORY

N_AC_020401_1_0110101_01_00

Interior Arrangements - Plan View for A321NEO-ACFTypical Configuration - Single-Class, Standard

FIGURE-2-4-1-991-011-A01

2-4-1Page 4

Nov 01/19


2-5-0 Interior Arrangements - Cross Section

**ON A/C A321-100 A321-200 A321neo

Interior Arrangements - Cross Section

1. This section provides the typical configuration.

2-5-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

6 ABREAST−WIDER AISLE

0.43 m(17 in)

1.50 m(59 in)

0.64 m(25 in)

3.63 m(143 in)

N_AC_020500_1_0050101_01_01

Interior Arrangements - Cross SectionEconomy Class, 6 Abreast - Wider Aisle (Sheet 1 of 2)

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

2-5-0Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

6 ABREAST−WIDER SEAT

0.46 m(18 in)

1.58 m(62 in)

3.63 m(143 in)

0.48 m(19 in)

N_AC_020500_1_0050102_01_03

Interior Arrangements - Cross SectionEconomy Class, 6 Abreast - Wider Seat (Sheet 2 of 2)

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

2-5-0Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

4 ABREAST−FIRST CLASS

0.57 m(22.6 in)

1.45 m(57 in)

3.58 m(141 in)

0.69 m(27 in)

N_AC_020500_1_0060101_01_01

Interior Arrangements - Cross SectionFirst-Class

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

2-5-0Page 4

Nov 01/19


2-6-0 Cargo Compartments

**ON A/C A321-100 A321-200 A321neo

Cargo Compartments

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

2-6-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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 and Dimensions

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

2-6-0Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

ST

AN

DA

RD

: 5 U

LDs

ST

AN

DA

RD

: 5 U

LDs

NOTE:VALID FOR A321−100, A321−200 , A321 NEO AND A321 NEO−ACF WITHOUT ACT INSTALLED

N_AC_020600_1_0070101_01_01

Cargo CompartmentsLoading Combinations

FIGURE-2-6-0-991-007-A01

2-6-0Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

1.81

m(7

1.26

in)

0.86

m(3

3.85

in)

1.81

m(7

1.26

in)

FR

24A

FR

35.5

FW

D C

AR

GO

CO

MP

AR

TM

EN

T(5

CO

NT

AIN

ER

S)

FR

47.2

FR

65

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

LOC

AT

ION

S O

F C

AR

GO

CO

MP

AR

TM

EN

TS

FO

R A

321N

EO−

AC

F W

ITH

OU

T A

CT

INS

TA

LLE

D

FR

24A

FR

35.5

FR

47.2

FR

65

LOC

AT

ION

S O

F C

AR

GO

CO

MP

AR

TM

EN

TS

FO

R A

321N

EO−

AC

F W

ITH

AC

T IN

ST

ALL

ED

11.4

m(4

48.8

2 in

)8.

15 m

(320

.87

in)

DIM

EN

SIO

NS

OF

CA

RG

O C

OM

PA

RT

ME

NT

S F

OR

A32

1NE

O−

AC

F (

WIT

H A

ND

WIT

HO

UT

AC

T IN

ST

ALL

ED

)

FR

59

FR

59

FW

D C

AR

GO

CO

MP

AR

TM

EN

TA

FT

CA

RG

OC

OM

PA

RT

ME

NT

(5 C

ON

TA

INE

RS

)

BU

LK C

AR

GO

CO

MP

AR

TM

EN

T(4

CO

NT

AIN

ER

S)

N_AC_020600_1_0120101_01_00

Cargo Compartments for A321NEO-ACFLocations and Dimensions for A321NEO-ACF

FIGURE-2-6-0-991-012-A01

2-6-0Page 4

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

ST

AN

DA

RD

: 3 U

LDs

ST

AN

DA

RD

: 4 U

LDs

ST

AN

DA

RD

: 3 U

LDs

ST

AN

DA

RD

: 3 U

LDs

LOA

DIN

G C

OM

BIN

AT

ION

S O

F F

WD

CA

RG

O C

OM

PA

RT

ME

NT

WIT

H 1

AC

T IN

ST

ALL

ED

AN

D A

FT

CA

RG

OC

OM

PA

RT

ME

NT

WIT

H 1

AC

T IN

ST

ALL

ED

FO

R A

321N

EO−

AC

F

LOA

DIN

G C

OM

BIN

AT

ION

S O

F F

WD

CA

RG

O C

OM

PA

RT

ME

NT

WIT

H 1

AC

T IN

ST

ALL

ED

AN

D A

FT

CA

RG

OC

OM

PA

RT

ME

NT

WIT

H 2

AC

T IN

ST

ALL

ED

FO

R A

321N

EO−

AC

F

ACT

NOTE:

N_AC_020600_1_0130101_01_00

Cargo Compartments for A321NEO-ACFLoading Combinations for A321NEO-ACF

FIGURE-2-6-0-991-013-A01

2-6-0Page 5

Nov 01/19


2-7-0 Door Clearances and Location

**ON A/C A321-100 A321-200 A321neo

Door Clearances

1. This section provides door identification and location.

NOTE : Dimensions of the ground clearances are approximate and will vary with tire type, weightand balance and other special conditions.

2-7-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

DOOR 1L

FORWARD EMERGENCY EXIT

BULK CARGOCOMPARTMENT

DOOR

AFT CARGOCOMPARTMENT

DOOR

FWD CARGOCOMPARTMENT

DOOR

DOOR 4L

DOOR 1RDOOR 4R

FORWARD EMERGENCY EXIT

AFT EMERGENCY EXIT

AFT EMERGENCY EXIT

N_AC_020700_1_0040101_01_01

Door Identification and LocationDoor Identification (Sheet 1 of 2)

FIGURE-2-7-0-991-004-A01

2-7-0Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

5.02 m(16.47 ft)

13.84 m(45.41 ft)

24.79 m(81.33 ft)

36.58 m(120.01 ft)

33.22 m(108.99 ft)

29.62 m(97.18 ft)

8.16 m(26.77 ft)

N_AC_020700_1_0040102_01_01

Door Identification and LocationDoor Location (Sheet 2 of 2)FIGURE-2-7-0-991-004-A01

2-7-0Page 3

Nov 01/19


**ON A/C A321neo

BULK CARGOCOMPARTMENT DOOR

AFT CARGOCOMPARTMENT DOOR

FWD CARGOCOMPARTMENT DOOR

OVERWINGEXIT L

FORWARD

OVERWINGEXIT L

AFT

DOOR 1L DOOR 3L

DOOR 4L

DOOR 4R DOOR 3R

OVERWINGEXIT R

AFT

OVERWINGEXIT R

FORWARD

DOOR 1R

N_AC_020700_1_0470101_01_00

Door Identification and Location for A321NEO-ACFDoor Identification for A321NEO-ACF (Sheet 1 of 2)

FIGURE-2-7-0-991-047-A01

2-7-0Page 4

Nov 01/19


**ON A/C A321neo

5.04 m(16.54 ft)

18.70 m(61.35 ft)

26.82 m(87.99 ft)

36.47 m(119.65 ft)

33.22 m(108.99 ft)

30.02 m(98.49 ft)

8.56 m(28.08 ft)

19.54 m(64.11 ft)

N_AC_020700_1_0470102_01_01

Door Identification and Location for A321NEO-ACFDoor Location for A321NEO-ACF (Sheet 2 of 2)

FIGURE-2-7-0-991-047-A01

2-7-0Page 5

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

SEECHAPTER

2−3

1.85 m(6.07 ft)

0.03 m(0.10 ft)

2.38 m(7.81 ft)

CRITICALCLEARANCE

LIMIT

5.02 m(16.47 ft)

2.54 m(8.33 ft)

0.61 m(2.00 ft)

0.81 m(2.66 ft)

1.80 m(5.91 ft)

0.48 m(1.57 ft)

N_AC_020700_1_0330101_01_00

Doors ClearancesForward Passenger/Crew Doors

FIGURE-2-7-0-991-033-A01

2-7-0Page 6

Nov 01/19


**ON A/C A321neo

SEECHAPTER

2−3

0.03 m(0.10 ft)

CRITICALCLEARANCE

LIMIT

5.04 m(16.54 ft)

2.54 m(8.33 ft)

0.61 m(2.00 ft)

0.81 m(2.66 ft)

1.80 m(5.91 ft)

0.48 m(1.57 ft)

1.85 m(6.07 ft)

2.38 m(7.81 ft)

N_AC_020700_1_0480101_01_00

Doors Clearances for A321NEO-ACFForward Passenger/Crew Doors for A321NEO-ACF

FIGURE-2-7-0-991-048-A01

2-7-0Page 7

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

FREE AISLE FREE AISLE

FROM AIRCRAFT NOSE

(TOP OF FLOOR)

A

A

B

B

A A

FWD

B B

13.84 m(45.41 ft)

CRITICALCLEARANCE

LIMIT0.56 m(1.84 ft)

0.83 m(2.72 ft)

1.73 m(5.68 ft)

CRITICALCLEARANCE

LIMIT

0.56 m(1.84 ft)

0.83 m(2.72 ft)

1.73 m(5.68 ft)

FROM AIRCRAFT NOSE

24.79 m(81.33 ft)

0.76 m(2.49 ft)

0.76 m(2.49 ft)

0.04 m(0.13 ft)

0.04 m(0.13 ft)

0.39 m(1.28 ft)

1.52 m(4.99 ft)

2.36 m(7.74 ft)

1.85 m(6.07 ft)0.40 m

(1.31 ft)

2.38 m(7.81 ft)

2.36 m(7.74 ft)

0.39 m(1.28 ft)

1.52 m(4.99 ft) 0.43 m

(1.41 ft)

CENTER OFFREE AISLE

CENTER OFFREE AISLE

N_AC_020700_1_0340101_01_01

Doors ClearancesEmergency Exits

FIGURE-2-7-0-991-034-A01

2-7-0Page 8

Nov 01/19


**ON A/C A321neo

(TOP OF FLOOR) 0.39 m(1.28 ft)

1.52 m(4.99 ft)

2.36 m(7.74 ft)

(FRAME 47)

CL

FWD

B B

A

A

A A

0.57 m(1.87 ft)

0.47 m(1.54 ft)

1.23 m(4.04 ft)

0.20 m(0.66 ft)

NOTE:ESCAPE SLIDE COMPARTMENT DOOR OPENS ON WING UPPER SURFACE.

SEESECTION

2−3

CRITICALCLEARANCE

LIMIT

0.56 m(1.84 ft)

0.83 m(2.72 ft)

1.73 m(5.68 ft)

FROM AIRCRAFT NOSE

CENTER OFFREE AISLE

FREE AISLE

0.76 m(2.49 ft)

0.04 m(0.13 ft)

C C

C

C

FREE AISLE

1.93 m(6.33 ft)

0.60 m(1.97 ft)

0.36 m(1.17 ft)

1.04 m(3.41 ft)

(TOP OF FLOOR)

B

B

26.82 m(87.99 ft)

18.70 m(61.35 ft)

0.84 m(2.76 ft)

FROM AIRCRAFTNOSE

N_AC_020700_1_0460101_01_01

Doors Clearances for A321NEO-ACFEmergency Exits for A321NEO-ACF

FIGURE-2-7-0-991-046-A01

2-7-0Page 9

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

FWD

A A

A

A

CRITICALCLEARANCE

LIMIT

0.81 m(2.66 ft)

1.79 m(5.87 ft)

0.58 m(1.90 ft)

(FROM NOSE) 36.58 m(120.01 ft)

0.03 m(0.10 ft)

1.85 m(6.07 ft)

0.60 m(1.97 ft)

2.44 m(8.01 ft)

FWD

SEE

2−3CHAPTER

N_AC_020700_1_0350101_01_01

Doors ClearancesAft Passenger/Crew DoorsFIGURE-2-7-0-991-035-A01

2-7-0Page 10

Nov 01/19


**ON A/C A321neo

FWD

A A

A

A

CRITICALCLEARANCE

LIMIT

0.81 m(2.66 ft)

1.79 m(5.87 ft)

0.58 m(1.90 ft)

(FROM NOSE) 36.47 m(119.65 ft)

0.03 m(0.10 ft)

1.85 m(6.07 ft)

0.60 m(1.97 ft)

2.44 m(8.01 ft)

FWD

SEE

2−3CHAPTER

N_AC_020700_1_0490101_01_00

Doors Clearances for A321NEO-ACFAft Passenger/Crew Doors for A321NEO-ACF

FIGURE-2-7-0-991-049-A01

2-7-0Page 11

Nov 01/19


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

A

A

A AFWD

1.24 m(4.07 ft)

1.50 m(4.92 ft)

SEECHAPTER

2−3

3.95 m(12.96 ft)

1.82 m(5.97 ft)

(FROM NOSE)8.16 m(26.77 ft)

CFM56 = 6.45 m (21.16 ft)IAE V2500 = 6.38 m (20.93 ft)

2.71 m(8.89 ft)

N_AC_020700_1_0360101_01_00

Door ClearancesForward Cargo Compartment Door

FIGURE-2-7-0-991-036-A01

2-7-0Page 12

Nov 01/19


**ON A/C A321neo

A

A

A AFWD

1.24 m(4.07 ft)

1.50 m(4.92 ft)

SEECHAPTER

2−3

3.95 m(12.96 ft)

CFM ENGINE = 2.47 m (8.10 ft)PW ENGINE = 2.43 m (7.97 ft)

CFM/PW ENGINE = 6.32 m (20.74 ft)

1.82 m(5.97 ft)

(FROM NOSE)8.16 m(26.77 ft)

N_AC_020700_1_0370101_01_00

Door ClearancesForward Cargo Compartment Door

FIGURE-2-7-0-991-037-A01

2-7-0Page 13

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

A A

1.23 m(4.04 ft)

1.43 m(4.69 ft)

SEECHAPTER

2−3

(FROM NOSE)29.62 m(97.18 ft)

1.82 m(5.97 ft)

A

A

3.95 m(12.96 ft)

4.69 m(15.39 ft)

N_AC_020700_1_0380101_01_01

Doors ClearancesAft Cargo Compartment DoorFIGURE-2-7-0-991-038-A01

2-7-0Page 14

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

FWD

A A

0.89 m(2.92 ft)

0.77 m(2.53 ft)

0.95 m(3.12 ft)

SEECHAPTER

2−3

2.19 m(7.19 ft)

8.76 m(28.74 ft)

A

A

N_AC_020700_1_0390101_01_01

Doors ClearancesBulk Cargo Compartment Door

FIGURE-2-7-0-991-039-A01

2-7-0Page 15

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

A

A

GROUND LINE

AIRCRAFT

0.21 m(0.69 ft)

1.23 m(4.04 ft)

0.14 m(0.46 ft)

NOTE:VALUE OF CG: 25% RC.

1.76 m(5.77 ft)

1.83 m(6.00 ft)

20.62 m(67.65 ft)

1.94 m(6.36 ft)0.49 m

(1.61 ft)

84°

N_AC_020700_1_0400101_01_00

Doors ClearancesMain Landing Gear Doors

FIGURE-2-7-0-991-040-A01

2-7-0Page 16

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

0.63 m(2.07 ft)

1.54 m(5.05 ft)

FR1

65°

N_AC_020700_1_0410101_01_00

Doors ClearancesRadome

FIGURE-2-7-0-991-041-A01

2-7-0Page 17

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

NOTE:VALUE OF CG: 25% RC.

FR84

FR80

3.42 m(11.22 ft)

4.05 m(13.29 ft)

1.50 m(4.92 ft) 1.40 m

(4.59 ft)

N_AC_020700_1_0420101_01_00

Doors ClearancesAPU and Nose Landing Gear Doors

FIGURE-2-7-0-991-042-A01

2-7-0Page 18

Nov 01/19


2-8-0 Escape Slides

**ON A/C A321-100 A321-200 A321neo

Escape Slides

1. GeneralThis section provides location of slides/rafts facilities and related clearances.

2. LocationSlides/rafts facilities are provided at the following location:- One single or dual lane slide at each door 1 and 4 (total 04)- One single lane slide at each door 2 and 3 (total 04) .

**ON A/C A321neo

3. Location for A321NEO-ACFSlides/rafts facilities are provided at the following locations:- One single or dual lane slide at each door 1 and 4 (total 04)- One single lane slide at each door 3 (total 02)- One dual lane overwing slide at each wing (total 2).

2-8-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

COCKPIT ESCAPEROPE

NOTE:LH SHOWN, RH SYMMETRICAL.

DOOR 4 SINGLE or DUAL LANE SLIDE


DOOR 3 SINGLE LANE SLIDE


N_AC_020800_1_0070101_01_04

Escape SlidesLocation

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

2-8-0Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

EM

ER

GE

NC

Y D

ES

CE

NT

TH

RO

UG

H T

HE

WIN

DO

W O

PE

NIN

G W

ITH

TH

E E

SC

AP

E R

OP

E

−3

−6

−9

−12

−15

−18

GR

ID E

QU

ALS

1 m

(3.

28 ft

) IN

RE

ALI

TY

− L

H S

HO

WN

, RH

SY

MM

ET

RIC

AL.

− D

IME

NS

ION

S A

RE

AP

PR

OX

IMA

TE

.

NO

TE

:

EM

ER

GE

NC

Y E

VA

CU

AT

ION

0

N_AC_020800_1_0080101_01_03

Escape SlidesDimensions

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

2-8-0Page 3

Nov 01/19


**ON A/C A321neo

NOTE:LH SHOWN, RH SYMMETRICAL.

COCKPIT ESCAPEROPE



OVERWING DUAL LANE SLIDE

FWD OVERWING EXIT

AFT OVERWING EXIT

DOOR 4 SINGLE orDUAL LANE SLIDE

N_AC_020800_1_0100101_01_01

Escape Slides for A321NEO-ACFLocation for A321NEO-ACFFIGURE-2-8-0-991-010-A01

2-8-0Page 4

Nov 01/19


**ON A/C A321neo

EM

ER

GE

NC

Y D

ES

CE

NT

TH

RO

UG

H T

HE

WIN

DO

W O

PE

NIN

G W

ITH

TH

E E

SC

AP

E R

OP

E

− L

H S

HO

WN

, RH

SY

MM

ET

RIC

AL.

− D

IME

NS

ION

S A

RE

AP

PR

OX

IMA

TE

.

NO

TE

:

EM

ER

GE

NC

Y E

VA

CU

AT

ION

−3

−6

−9

−12

−15

−18

GR

ID E

QU

ALS

1 m

(3.

28 ft

) IN

RE

ALI

TY

0

N_AC_020800_1_0110101_01_01

Escape Slides for A321NEO-ACFDimensions for A321NEO-ACF

FIGURE-2-8-0-991-011-A01

2-8-0Page 5

Nov 01/19


2-9-0 Landing Gear

**ON A/C A321-100 A321-200 A321neo

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 gears are located under the wing and retract sideways towards the fuselagecenterline.The nose landing gear retracts forward into a fuselage compartment located between FR9 and FR20.

The landing gears and landing gear doors are operated and controlled electrically and hydraulically.In abnormal operation, the landing gear can be extended by gravity.

For landing gear footprint and tire size, refer to 07-02-00.

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 directions by a fixed drag strutand laterally by a folding strut mechanically locked when in the DOWN position.

3. Nose Landing Gear

The nose landing gear consists of a leg with a built-in shock absorber strut, carrying twin wheels 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 is installed on the nose landing gear to allow steering deactivation fortowing purposes.

5. Landing Gear Servicing Points

A. General

Filling of the landing-gear shock absorbers is done through MIL-PRF-6164 standard valves.

2-9-0Page 1

Nov 01/19


Charging of the landing-gear shock absorbers is accomplished with nitrogen through MIL-PRF-6164 standard 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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

DOORACTUATINGCYLINDER

FLAG

BOTTOM FILLING ANDCHARGING CONNECTION

LOCKSTAYACTUATINGCYLINDER

GROUND LOCK SLEEVE

FLAG

BC

D

LOCKINGPIN

LOCKINGPIN

EXAMPLE

TOP FILLING AND CHARGING CONNECTION

E

N_AC_020900_1_0160102_01_01

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

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

2-9-0Page 4

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

TOWING LEVER

(NOSE WHEEL STEERINGNORMAL 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)

CONNECTIONFILLING AND CHARGING

N_AC_020900_1_0180102_01_01

Landing GearNose Landing Gear (Sheet 2 of 2)

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

2-9-0Page 7

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

Landing Gear Maintenance Pits

1. Description

The minimum maintenance pit envelopes for the landing-gear shock absorber removal are shown inFIGURE 2-9-0-991-026-A and FIGURE 2-9-0-991-027-A.

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 FIGURE2-9-0-991-026-A and FIGURE 2-9-0-991-027-A.

2-9-0Page 9

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

=

==

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


2-10-0 Exterior Lighting

**ON A/C A321-100 A321-200 A321neo

Exterior Lighting

1. General

This section provides 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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

1

2

3

55

N_AC_021000_1_0140101_01_00

7


2-10-0Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

12

11

1313

4

11

9

N_AC_021000_1_0150101_01_00

6

10


2-10-0Page 4

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


2-11-0 Antennas and Probes Location

**ON A/C A321-100 A321-200 A321neo

Antennas and Probes Location

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

2-11-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


2-12-0 Power Plant

**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

AIR INTAKE FIXEDON ACCESS DOOR

RH ACCESS DOOR

CUT OUT SEALED WITHLABYRINTH GASKET

FRONTFIREWALL

UPPERFIREWALL

FIREWALL RH

LOUVER LH

REARFIREWALL

CUT OUT SEALED WITHLABYRINTH GASKET

A

FR80

FR84

LH ACCESS DOOR NOT SHOWN FOR CLARITY.315AL

316AR

NOTE:

A B

FR87

Z310

FR70

FR77

N_AC_021200_1_0070101_01_01

Auxiliary Power UnitAccess Doors

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

2-12-0Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

OIL COOLER OUTLET

AIR INTAKE DUCT

APU−FUEL−LINE

AIR INTAKE HOUSING

DIVERTER

FRONT FIREWALL

BLEED AIR LINE

FIRE EXTINGUISHING BOTTLE

GENERATOR

APU SUSPENSION(7 RODS)

APU

FIRE OVERHEAT DETECTOR

APU SUSPENSION(7 RODS)

EXHAUSTMUFFLER

FR84

FR80

FR78

FR77

FR87

B

N_AC_021200_1_0080101_01_01

Auxiliary Power UnitGeneral Layout

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

2-12-0Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

Engine and Nacelle

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

1. Engine and Nacelle - CFM Engine

A. Engine

The engine is a dual-rotor, variable stator, high bypass ratio turbofan powerplant 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. Nacelle

The 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. Engine

The engine is a two spool, axial flow, high bypass ratio turbofan powerplant for subsonic service.The main modules of the engine are:

2-12-0Page 4

Nov 01/19


- 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).

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. Nacelle

The 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

Nov 01/19


**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

Nov 01/19


**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

Nov 01/19


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

A

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.

SEECHAPTER

2−3

N_AC_021200_1_0370101_01_01

Power Plant HandlingFan Cowls - CFM56 Series Engine

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

2-12-0Page 8

Nov 01/19


**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 DIMENSIONS.NOTE:

GROUND

0.7 m(2.3 ft)

1 m(3.3 ft)

45°35°

1 m(3.3 ft)

SEECHAPTER

2−3

N_AC_021200_1_0380101_01_01

Power Plant HandlingThrust Reverser Cowls - CFM56 Series Engine

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

2-12-0Page 9

Nov 01/19


**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

Nov 01/19


**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

Nov 01/19


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

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°


SEECHAPTER

2−3

N_AC_021200_1_0410101_01_01

Power Plant HandlingFan Cowls - IAE V2500 Series Engine

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

2-12-0Page 12

Nov 01/19


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


1.1 m(3.6 ft)

1 m(3.3 ft)

THRUST REVERSEROPEN 45°

2 m

(6.6 ft)

AFT VIEW

WL100CLOSED

3.6 m

(11.8 ft)

0.9 m(3 ft)

WL100

SEECHAPTER

2−3

N_AC_021200_1_0420101_01_01

Power Plant HandlingThrust Reverser Halves - IAE V2500 Series Engine

FIGURE-2-12-0-991-042-A01

2-12-0Page 13

Nov 01/19


**ON A/C A321neo

NOSE COWLFAN COWL THRUST

REVERSER

PRIMARYNOZZLE

PLUG

0.46 m(1.51 ft)

0.66 m(2.17 ft) 1.46 m

(4.79 ft)1.53 m(5.02 ft)

1.44 m(4.72 ft)

A

FWD

2.60 m(8.53 ft)

2.67 m(8.76 ft)

ASEE

CHAPTER2−3

N_AC_021200_1_0490101_01_01

Power Plant HandlingMajor Dimensions - PW 1100G Engine

FIGURE-2-12-0-991-049-A01

2-12-0Page 14

Nov 01/19


**ON A/C A321neo

A

A

A

4.70 m(15.42 ft)

1.22 m(4.00 ft)

1 1

FULL: 50°OPEN POSITION:

50°

1: FAN COWLSEE

CHAPTER2−3

N_AC_021200_1_0500101_01_01

Power Plant HandlingFan Cowls - PW 1100G EngineFIGURE-2-12-0-991-050-A01

2-12-0Page 15

Nov 01/19


**ON A/C A321neo

43° 45°

: THRUST REVERSER1

B

A A

A

1 1 1 1

C

B

C

A

A

OPENPOSITION A

BMAX.MIN.

C

43°

45°

4.26 m(13.98 ft)

4.33 m(14.21 ft)

0.80 m(2.62 ft)

0.84 m(2.76 ft)

0.90 m(2.95 ft)

0.95 m(3.12 ft)

SEE AC SECTION2−3−0

NOTE:B AND C DEPENDING ON AIRCRAFT CONFIGURATION. N_AC_021200_1_0510101_01_00

Power Plant HandlingThrust Reverser Halves - PW 1100G Engine

FIGURE-2-12-0-991-051-A01

2-12-0Page 16

Nov 01/19


**ON A/C A321neo

AFWD

HANDLINGPOINT

COMPRESSOR

HPTURBINE

LPTURBINEAGB TGB

ACCESSORYDRIVE

FAN ANDBOOSTER

B

TURBINEFRAME

AFWD

ICN

LEA

P1A

0212

00C

5882

8000

0100

101

1352 mm(53.23 in)

3327 mm(130.98 in)

3548 mm(139.68 in)

2152 mm(84.72 in)

2487 mm(97.91 in)

1236 mm(48.66 in)

1165 mm(45.87 in)

2242 mm(88.27 in)

DIA 1084 mm(42.68 in)

COMBUSTOR

BN_AC_021200_1_0560101_01_00

Power Plant HandlingMajor Dimensions - CFM LEAP-1A Engine

FIGURE-2-12-0-991-056-A01

2-12-0Page 17

Nov 01/19


**ON A/C A321neo

NOSE COWL

PRIMARYNOZZLE

FAN COWLTHRUST

REVERSER

1.58 m(5.18 ft)

0.49 m(1.61 ft)

2.52 m(8.27 ft)

1.98 m(6.50 ft)

0.67 m(2.20 ft)

A

FWD

A

2.60 m(8.53 ft)

PLUG

0.23 m(0.75 ft)

0.98 m(3.22 ft)

SEECHAPTER

2−3

N_AC_021200_1_0570101_01_01

Power Plant HandlingMajor Dimensions - CFM LEAP-1A Engine

FIGURE-2-12-0-991-057-A01

2-12-0Page 18

Nov 01/19


2-13-0 Leveling, Symmetry and Alignment

**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


2-14-0 Jacking

**ON A/C A321-100 A321-200 A321neo

Jacking for Maintenance

1. Aircraft Jacking Points for Maintenance

A. General

(1) The A321 can be jacked:- At not more than 69 000 kg (152 119 lb),- Within the limits of the permissible wind speed when the aircraft is not in a closed

environment.

B. Primary Jacking Points

(1) The aircraft is provided with three primary jacking points:- One located under the forward fuselage (FR8),- Two located under the wings (one under each wing, located at the intersection of RIB9

and the datum of the rear spar).

(2) Three jack adapters are used as intermediary parts between the aircraft and the jacks:- One male spherical jack adapter of 19 mm (0.75 in) radius, forming part of the aircraft

structure (FR8),- Two wing jack pads (one attached to each wing at RIB9 with 2 bolts) for the location

of the jack adaptor.Wing jack pads are ground equipment.

C. Auxiliary Jacking Points (Safety Stay)

(1) When the aircraft is on jacks, it is recommended that a safety stay be placed under thefuselage, between FR73 and FR74, to prevent tail tipping caused by accidentaldisplacement of the center of gravity.

(2) The safety stay must not be used to lift the aircraft.

(3) A male spherical ball pad with a 19 mm (0.75 in) radius, forming part of the aircraftstructure, is provided for using the safety stay.

2. Jacks and Safety Stay

A. Jack Design

(1) The maximum permitted loads given in the table in FIGURE 2-14-0-991-038-A are themaximum loads applicable on jack fittings.

(2) In the fully retracted position (jack stroke at minimum), the height of the jack is such thatthe jack may be placed beneath the aircraft in the most adverse conditions, namely, tiresdeflated and shock absorbers depressurized. In addition, there must be a clearance ofapproximately 50 mm (1.97 in) between the aircraft jacking point and the jack upper end.

2-14-0Page 1

Nov 01/19


(3) The lifting jack stroke enables the aircraft to be jacked up so that the fuselage longitudinaldatum line (aircraft center line) is parallel to the ground, with a clearance of 100 mm (3.94in) between the main landing gear wheels and the ground. This enables the landing gearextension/retraction tests to be performed.

3. Shoring Cradles

When it is necessary to support the aircraft in order to relieve the loads on the structure to domodifications or major work, shoring cradles shall be placed under each wing and the fuselage asnecessary.

NOTE : The aircraft must not be lifted or supported by the wings or fuselage alone withoutadequate support of the other.

2-14-0Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

X

SAFETY STAY

WING JACKINGPOINT

C

B’

B

FORWARD FUSELAGEJACKING POINT A

2.74

21.83

21.83

39.5

8.99

71.62

71.62

129.59

0

6.50

−6.50

0

0

21.33

−21.33

0

MAXIMUMLOAD ELIGIBLE

m ft

6 800

daN

YX

33 400

33 400

2 000

m ft

NOTE:SAFETY STAY IS NOT USED FOR JACKING.

FWD JACKINGPOINT

A

SAFETYSTAY

C

Y

POINT

WING JACKINGPOINT

WING JACKING

B

B’

FR8

FR73

FR74

RIB9

RIB9

N_AC_021400_1_0380101_01_02

Jacking for MaintenanceJacking Point Locations

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

2-14-0Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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 4

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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 5

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

Z−744.932

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

X =

42

040

Z−729.441

FR73 FR74

A

FWD

126.15 mm(4.97 in)

A

N_AC_021400_1_0410101_01_01

Jacking for MaintenanceSafety Stay

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

2-14-0Page 6

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

FORWARD WING JACKJACK

WING JACK M

RIB9 RIB9L

FUSELAGEDATUM LINE

NWING JACK SAFETY STAYFORWARD JACK

FR73 FR74FR8

1 603 mm(63.11 in)

3 124 mm(122.99 in)

3 635 mm(143.11 in)

1 654 mm(65.12 in)

2 761 mm(108.70 in)

2 889 mm(113.74 in)

1 924 mm(75.75 in)

3 125 mm(123.03 in)

3 341 mm(131.54 in)

2 605 mm(102.56 in)

3 706 mm(145.91 in)

3 830 mm(150.79 in)

3 255 mm(128.15 in)

4 356 mm(171.50 in)

4 480 mm(176.38 in)

2 371 mm(93.35 in)

2 930 mm(115.35 in)

NOTE:

DESCRIPTIONCONFIGURATION

− NLG SHOCK ABSORBER DEFLATED AND

− MLG STANDARD TIRES, WITH STANDARDSHOCK ABSORBERS

TIRES FLATSHOCK ABSORBERS DEFLATED

STANDARD TIRESSTANDARD SHOCK ABSORBERS

STANDARD TIRESMLG SHOCK ABSORBERS EXTENDED WITH

WHEEL CLEARANCE OF 120 mm (4.72 in)

STANDARD TIRESMLG SHOCK ABSORBERS EXTENDED WITHWHEEL CLEARANCE OF 770 mm (30.31 in)

FOR REPLACEMENT OF THE MLG

STANDARD TIRESNLG SHOCK ABSORBERS EXTENDED WITH

WHEEL CLEARANCE OF 60 mm (2.36 in)FOR NLG RETRACTION OR EXTENSION

DISTANCE BETWEENJACKING/SAFETY POINTS

AND THE GROUND

L(FORWARD

JACK)

M(WINGJACK)

N(SAFETY

STAY)

FOR MLG RETRACTION OR EXTENSION

NLG TIRES FLAT

−AIRCRAFT ON WHEELS

WING JACKS)FUSELAGE DATUM LINEPARALLEL TO THE GROUND

−

−

(FORWARD JACK ANDAIRCRAFT ON JACKS

AIRCRAFT ON FORWARDJACKMLG WHEELS ON THEGROUND

−

−NA

THE SAFETY STAY IS NOT USED FOR JACKING.

TYPICAL JACK INSTALLATION SHOWN

N_AC_021400_1_0420101_01_02

Jacking for MaintenanceJacking Design

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

2-14-0Page 7

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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 8

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

(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 9

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

Jacking of the Landing Gear

1. General

Landing gear jacking will be required to lift the landing gear wheels off the ground.

NOTE : You can lift the aircraft at Maximum Ramp Weight (MRW).

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

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

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.

The reactions at each of the jacking points are shown in the table, see FIGURE 2-14-0-991-061-A.

**ON A/C A321neo

3. 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.The reactions at each of the jacking points are shown in the table, see FIGURE 2-14-0-991-064-A.

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

4. Nose Gear Jacking

For nose gear jacking, a 19 mm (0.75 in) radius ball pad is fitted under the lower end of the shock-absorber 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.The reactions at each of the jacking points are shown in the table, see FIGURE 2-14-0-991-061-A.

2-14-0Page 10

Nov 01/19


**ON A/C A321neo

5. Nose Gear JackingFor nose gear jacking, a 19 mm (0.75 in) radius ball pad is fitted under the lower end of the shock-absorber 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.The reactions at each of the jacking points are shown in the table, see FIGURE 2-14-0-991-064-A.

2-14-0Page 11

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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.

Jacking of the Landing GearMLG Jacking Point Location - Twin Wheels

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

2-14-0Page 12

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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)

Jacking of the Landing GearMLG Jacking with Cantilever Jack - Twin Wheels

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

2-14-0Page 13

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Jacking of the Landing GearNLG Jacking - Point LocationFIGURE-2-14-0-991-028-A01

2-14-0Page 14

Nov 01/19


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

A321−100/−200WV011

MAXIMUM DESIGN TAXI WEIGHT (MTW)

MAXIMUM DESIGN TAKE−OFF WEIGHT (MTOW)

MAXIMUM LOAD VALUE TO BE APPLIED ON NLGJACKING POINT

NUMBER OF JACKING POINTS ON ONE MLG

MAXIMUM LOAD VALUE TO BE APPLIED ON MLGJACKING POINT (LEFT OR RIGHT)

93 900 kg(207 014 lb)

93 500 kg(206 132 lb)

9 000 kg(19 842 lb)

1

44 500 kg(98 106 lb)

N_AC_021400_1_0610101_01_00

Jacking of the Landing GearMaximum Load Capacity to Lift Each Jacking Point

FIGURE-2-14-0-991-061-A01

2-14-0Page 15

Nov 01/19


**ON A/C A321neo

A321 NEOWV052 AND WV053

MAXIMUM DESIGN TAXI WEIGHT (MTW)

MAXIMUM DESIGN TAKE−OFF WEIGHT (MTOW)

MAXIMUM LOAD VALUE TO BE APPLIED ON NLGJACKING POINT

NUMBER OF JACKING POINTS ON ONE MLG

MAXIMUM LOAD VALUE TO BE APPLIED ON MLGJACKING POINT (LEFT OR RIGHT)

93 900 kg(207 014 lb)

93 500 kg(206 132 lb)

12 207 kg(26 912 lb)

1

59 103 kg(130 300 lb)

N_AC_021400_1_0640101_01_00

Jacking of the Landing GearMaximum Load Capacity to Lift Each Jacking Point

FIGURE-2-14-0-991-064-A01

2-14-0Page 16

Nov 01/19


AIRCRAFT PERFORMANCE


**ON A/C A321-100 A321-200 A321neo

General Information

1. Standard day temperatures for the altitudes shown are tabulated below:

Standard Day Temperatures for the Altitudes

Altitude Standard Day Temperature

FEET METERS ˚F ˚C0 0 59.0 15.02 000 610 51.9 11.14 000 1 220 44.7 7.16 000 1 830 37.6 3.18 000 2 440 30.5 -0.8

3-1-0Page 1

Nov 01/19


3-2-1 Payload / Range - ISA Conditions

**ON A/C A321-100 A321-200 A321neo

Payload/Range - ISA Conditions

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

3-2-1Page 1

Nov 01/19


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

05101530

500

1 00

01

500

2 00

02

500

3 00

03

500

4 00

04

500

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

.T

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.

PA

YLO

AD

(1 0

00 lb

)

RA

NG

E(n

m)

RA

NG

E(k

m)

PA

YLO

AD

(1 0

00 k

g)

1 00

02

000

3 00

04

000

5 00

06

000

7 00

08

000

10 0

MT

OW

− 8

9 00

0 kg

(19

6 21

1 lb

)M

TO

W −

93

500

kg (

206

132

lb)

MT

OW

− 9

3 50

0 kg

(20

6 13

2 lb

); 2

AC

T

2025

2030405060

N_AC_030201_1_0190101_01_00

Payload/Range - ISA ConditionsFIGURE-3-2-1-991-019-A01

3-2-1Page 2

Nov 01/19


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

05101530

500

1 00

01

500

2 00

02

500

3 00

03

500

4 00

04

500

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

.T

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.

PA

YLO

AD

(1 0

00 lb

)

RA

NG

E(n

m)

RA

NG

E(k

m)

PA

YLO

AD

(1 0

00 k

g)

1 00

02

000

3 00

04

000

5 00

06

000

7 00

08

000

10 0

MT

OW

− 8

9 00

0 kg

(19

6 21

1 lb

)M

TO

W −

93

500

kg (

206

132

lb)

MT

OW

− 9

3 50

0 kg

(20

6 13

2 lb

); 2

AC

T

2025

2030405060

N_AC_030201_1_0200101_01_00

Payload/Range - ISA ConditionsSharklet

FIGURE-3-2-1-991-020-A01

3-2-1Page 3

Nov 01/19


**ON A/C A321neo

05101530

500

1 00

01

500

2 00

02

500

3 00

03

500

4 00

04

500

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

.T

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.

PA

YLO

AD

(1 0

00 lb

)

RA

NG

E(n

m)

RA

NG

E(k

m)

PA

YLO

AD

(1 0

00 k

g)

1 00

02

000

3 00

04

000

5 00

06

000

7 00

08

000

10 0

MT

OW

− 8

9 00

0 kg

(19

6 21

1 lb

)M

TO

W −

93

500

kg (

206

132

lb)

MT

OW

− 9

3 50

0 kg

(20

6 13

2 lb

); 1

AC

T

2025

2030405060

MT

OW

− 9

7 00

0 kg

(21

3 84

8 lb

); 2

AC

TM

TO

W −

97

000

kg (

213

848

lb);

3 A

CT

9 00

010

000

5 00

05

500

N_AC_030201_1_0210101_01_01

Payload/Range - ISA ConditionsFIGURE-3-2-1-991-021-A01

3-2-1Page 4

Nov 01/19


3-3-1 Take-off Weight Limitation - ISA Conditions

**ON A/C A321-100 A321-200 A321neo

Take-Off Weight Limitation - ISA Conditions

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

3-3-1Page 1

Nov 01/19


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

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

NOTE:

110

120

130

140

150

160

170

180

190

200

210

220

230

110

100

90

80

70

60

50

40

16141210864

54321

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−

OF

F W

EIG

HT

1000 lb

Take-Off Weight Limitation - ISA ConditionsCFM56 Series Engine

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

3-3-1Page 2

Nov 01/19


**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−

OF

F W

EIG

HT

1000 lb

Take-Off Weight Limitation - ISA ConditionsIAE V2500 Series Engine

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

3-3-1Page 3

Nov 01/19


**ON A/C A321neo


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

1000 kg

TA

KE−

OF

F W

EIG

HT

1000 lb

N_AC_030301_1_0100101_01_00

Take-Off Weight Limitation - ISA ConditionsLEAP-1A Series Engine

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

3-3-1Page 4

Nov 01/19


3-3-2 Take-off Weight Limitation - ISA +15˚C (+59˚F) Conditions

**ON A/C A321-100 A321-200 A321neo

Take-Off Weight Limitation - ISA +15˚C (+27˚F) Conditions

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

3-3-2Page 1

Nov 01/19


**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−

OF

F W

EIG

HT

1000 lb

Take-Off Weight Limitation - ISA +15˚C (+27˚F) ConditionsCFM56 Series Engine

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

3-3-2Page 2

Nov 01/19


**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−

OF

F W

EIG

HT

1000 lb

Take-Off Weight Limitation - ISA +15˚C (+27˚F) ConditionsIAE V2500 Series Engine

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

3-3-2Page 3

Nov 01/19


**ON A/C A321neo


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

1000 kg

TA

KE−

OF

F W

EIG

HT

1000 lb

N_AC_030302_1_0100101_01_00

Take-Off Weight Limitation - ISA +15˚C (+27˚F) ConditionsLEAP-1A Series Engine

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

3-3-2Page 4

Nov 01/19


3-3-3 Aerodrome Reference Code

**ON A/C A321-100 A321-200 A321neo

Aerodrome Reference Code

1. A321-100, A321-200 and A321neo are classified as code 4C as per ICAO Aerodrome Reference Code.

3-3-3Page 1

Nov 01/19


3-4-1 Landing Field Length - ISA Conditions

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

Landing Field Length - ISA Conditions

1. This section provides the landing field length.

3-4-1Page 1

Nov 01/19


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

ISA CONDITIONSSLATS 27 DEG.FLAPS 40 DEG.

GROSS WEIGHT (x 1 000 lb)

(x 1 000 m) (x 1 000 ft)

2.5

2.0

1.5

1.03

4

5

6

7

8

80 100 120 140 160 180

30 40 50 60 70 80 90GROSS WEIGHT (x 1 000 kg)

LAN

DIN

G F

IELD

LE

NG

TH

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

NOTE:

9

200

AIRFIELD ELEVATION(x 1 000 ft)

10 8 6 42

SEALEVEL

N_AC_030401_1_0070101_01_01

Landing Field Length - ISA ConditionsCFM56 Series Engine

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

3-4-1Page 2

Nov 01/19


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

ISA CONDITIONSSLATS 27 DEG.FLAPS 40 DEG.

GROSS WEIGHT (x 1 000 lb)

(x 1 000 m) (x 1 000 ft)

2.5

2.0

1.5

1.03

4

5

6

7

8

80 100 120 140 160 180

30 40 50 60 70 80 90GROSS WEIGHT (x 1 000 kg)

LAN

DIN

G F

IELD

LE

NG

TH

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

NOTE:

9

200

AIRFIELD ELEVATION(x 1000 ft)

SEA

10 8 6 4

2

LEVEL

N_AC_030401_1_0080101_01_01

Landing Field Length - ISA ConditionsIAE V2500 Series Engine

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

3-4-1Page 3

Nov 01/19


3-5-0 Final Approach Speed

**ON A/C A321-100 A321-200 A321neo

Final Approach Speed

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

1. Final Approach Speed

A. This section gives the final approach speed which is the indicated airspeed at threshold in thelanding configuration at the certificated maximum flap setting and Maximum Landing Weight(MLW) at standard atmospheric conditions. The approach speed is used to classify the aircraftinto Aircraft Approach Category, a grouping of aircraft based on the indicated airspeed atthreshold.

B. The final approach speed is 140 kt at a MLW of 75 500 kg (166 449 lb) and classifies theaircraft into the Aircraft Approach Category C.

NOTE : This value is given for information only.

C. The final approach speed is 142 kt at a MLW of 77 800 kg (171 520 lb) and classifies theaircraft into the Aircraft Approach Category D.


**ON A/C A321neo

2. Final Approach Speed

A. This section gives the final approach speed which is the indicated airspeed at threshold in thelanding configuration at the certificated maximum flap setting and MLW at standardatmospheric conditions. The approach speed is used to classify the aircraft into AircraftApproach Category, a grouping of aircraft based on the indicated airspeed at threshold.

B. The final approach speed is 136 kt at a MLW of 79 200 kg (174 606 lb) and classifies theaircraft into the Aircraft Approach Category C.


3-5-0Page 1

Nov 01/19


GROUND MANEUVERING


**ON A/C A321-100 A321-200 A321neo

General Information

1. This section provides aircraft 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 a guideline for the method of determination of such parameters and for themaneuvering characteristics of this aircraft type.

In 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 a high risk of jet blast damage. For these reasons, ground maneuvering requirements shouldbe coordinated with the airlines in question prior to layout planning.

4-1-0Page 1

Nov 01/19


4-2-0 Turning Radii

**ON A/C A321-100 A321-200 A321neo

Turning Radii

1. This section provides the turning radii.

4-2-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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 Angle(Sheet 1)

FIGURE-4-2-0-991-007-A01

4-2-0Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

MA

XIM

UM

RA

MP

WE

IGH

T

EF

FE

CT

IVE

ST

EE

RIN

G A

NG

LE(d

eg)

mft

2

ft

ft

m

mm

ft

mft

mft

R6

TH

SR

5R

3N

LGR

2LM

LG

mft

R1

RM

LG

ST

EE

RIN

GA

NG

LE(d

eg)

WIN

GT

IPF

EN

CE

SH

AR

KLE

T

R4 −

WIN

GN

OS

E

TY

PE

TU

RN

75 (

MA

X)

706560555045403525 3020

73.1

71.6

67.4

63.0

58.3

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

44.3

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

24.6

27.0

30.3

34.7

41.1

50.7

58596163667074818999114

135

166

22.6

23.1

24.5

26.1

27.8

29.8

32.1

34.8

38.1

42.1

47.3

54.3

64.7

747680859198105

114

125

138

155

178

212

23.4

23.9

25.3

26.9

28.6

30.7

32.9

35.6

38.9

42.9

48.1

55.2

65.5

7778838894101

108

117

128

141

158

181

215

22.6

22.7

23.1

23.6

24.3

25.3

26.5

28.1

30.2

33.1

37.2

43.1

52.3

747476778083879299109

122

141

172

24.5

24.7

25.4

26.3

27.4

28.6

30.2

32.1

34.6

37.8

42.2

48.5

57.9

80818386909499105

114

124

139

159

190

7065605550

1

68.4

63.6

58.8

54.0

49.1

11111

75 (

MA

X)

3.6

5.3

7.1

9.2

11.5

1217233038

11.2

12.9

14.7

16.8

19.1

3742485563

18.3

19.0

19.9

21.1

22.6

6062656974

24.1

25.8

27.6

29.7

32.0

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

27.2

28.5

30.1

8386899499

N_AC_040200_1_0080101_01_01

AB

OV

E 5

0°, A

IRLI

NE

S M

AY

US

E T

YP

E 1

OR

TY

PE

2 T

UR

NS

DE

PE

ND

ING

ON

TH

E S

ITU

AT

ION

.T

YP

E 1

TU

RN

S U

SE

:T

HE

TU

RN

ON

LY.

TY

PE

2 T

UR

NS

US

E:

IT IS

PO

SS

IBLE

TO

GE

T L

OW

ER

VA

LUE

S T

HA

N T

HO

SE

FR

OM

TY

PE

1 B

Y A

PP

LYIN

G D

IFF

ER

EN

TIA

L B

RA

KIN

G D

UR

ING

NO

TE

:

TH

E W

HO

LE T

UR

N.

AS

YM

ME

TR

IC T

HR

US

T D

UR

ING

TH

E W

HO

LE T

UR

N; A

ND

DIF

FE

RE

NT

IAL

BR

AK

ING

TO

INIT

IAT

E

SY

MM

ET

RIC

TH

RU

ST

DU

RIN

G T

HE

WH

OLE

TU

RN

; AN

D N

O D

IFF

ER

EN

TIA

L B

RA

KIN

G A

T A

LL.

Turning Radii, No Slip Angle(Sheet 2)

FIGURE-4-2-0-991-008-A01

4-2-0Page 3

Nov 01/19


4-3-0 Minimum Turning Radii

**ON A/C A321-100 A321-200 A321neo

Minimum Turning Radii

1. This section provides the minimum turning radii.

4-3-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


4-4-0 Visibility from Cockpit in Static Position

**ON A/C A321-100 A321-200 A321neo

Visibility from Cockpit in Static Position

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

4-4-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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(21 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

CAPTAIN FIELDOF VIEW

FIRST OFFICER FIELD OF VIEW

N_AC_040400_1_0010101_01_04

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

4-4-0Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

FIR

ST

OF

FIC

ER

FIX

ED

WIN

DO

WF

IRS

T O

FF

ICE

RS

LID

ING

WIN

DO

WF

IRS

T O

FF

ICE

RW

IND

SH

IELD

CA

PT

AIN

WIN

DS

HIE

LDC

AP

TA

IN S

LID

ING

WIN

DO

WC

AP

TA

INF

IXE

D W

IND

OW

PIL

OT

EY

E P

OS

ITIO

N(C

AP

TA

IN P

OS

ITIO

N)

AS

580

B

A32

0

CA

PT

AIN

FIE

LD O

F V

IEW

SH

OW

N.

FIR

ST

OF

FIC

ER

FIE

LD O

F V

IEW

SY

MM

ET

RIC

AL.

EX

AM

PLE

: WH

EN

CA

PT

AIN

TU

RN

S H

IS H

EA

D B

Y 8

0° L

EF

T, V

ISIB

ILIT

YW

ILL

BE

35°

UP

AN

D 2

5° D

OW

N T

HR

OU

GH

TH

E S

LID

ING

WIN

DO

W F

RA

ME

.

35°

30°

20°

10°

0° 10°

20°

25°

110°

100°

90°

80°

70°

50°

40°

30°

20°

10°

0°10

°20

°40

°50

°60

°80

°90

°10

0°13

0°12

0°60

°30

°70

°11

0°

N_AC_040400_1_0050101_01_00

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

4-4-0Page 3

Nov 01/19


4-5-0 Runway and Taxiway Turn Paths

**ON A/C A321-100 A321-200 A321neo

Runway and Taxiway Turn Paths

1. Runway and Taxiway Turn Paths.

4-5-0Page 1

Nov 01/19



**ON A/C A321-100 A321-200 A321neo

135˚ Turn - Runway to Taxiway

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

4-5-1Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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)

ADDITIONAL FILLET TO MEET3 m (10 ft) EDGE CLEARANCE

15 m(50 ft)

(100 ft)

NLG PATH (CENTER)

MLG PATH (EDGE)

FAA GROUP III FACILITIES.NOTE:

N_AC_040501_1_0060101_01_03

135˚ Turn - Runway to TaxiwayCockpit Over Centerline Method

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

4-5-1Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

RUNWAY CENTERLINE

TURN R = 30 m(100 ft)



L = 45 m (150 ft)

APPROX 3 m(10 ft)

TAXIWAYCENTERLINE

30 m

15 m(50 ft)

(100 ft)

NLG PATH (CENTER)

MLG PATH (EDGE)


N_AC_040501_1_0070101_01_03

135˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

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

4-5-1Page 3

Nov 01/19



**ON A/C A321-100 A321-200 A321neo

90˚ Turn - Runway to Taxiway

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

4-5-2Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

APPROX 3.7 m(12 ft)


TURN R = 30 m(100 ft)

RUNWAY CENTERLINE

FAA LEAD−IN FILLETL = 45 m (150 ft)

TAXIWAY CENTERLINE

NLG PATH (CENTER)

MLG PATH (EDGE)

30 m(100 ft)

15 m(50 ft)


N_AC_040502_1_0060101_01_03

90˚ Turn - Runway to TaxiwayCockpit Over Centerline Method

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

4-5-2Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

APPROX 9.2 m(30 ft)


TURN R = 30 m(100 ft)

RUNWAY CENTERLINE


TAXIWAY CENTERLINE

NLG PATH (CENTER)

MLG PATH (EDGE)

30 m(100 ft)

15 m(50 ft)


N_AC_040502_1_0070101_01_03

90˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

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

4-5-2Page 3

Nov 01/19


4-5-3 180˚ Turn on a Runway

**ON A/C A321-100 A321-200 A321neo

180˚ Turn on a Runway

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

4-5-3Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

WINGTIP PATH:

NOSE PATH

MLG PATH (EDGE)

WINGTIP FENCES:R4 = 22.6 m (74 ft)SHARKLETS:R4 = 23.4 m (77 ft)

NLG PATH (EDGE)

45 m(148 ft)

RUNWAY CENTERLINE

14.4 m(47 ft)

3 m(10 ft)

R3 = 17.8 m(58 ft)

R5 = 22.6 m(74 ft)

R4 NLG PATH (CENTER)

N_AC_040503_1_0020101_01_05

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

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

4-5-3Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

RUNWAY CENTERLINE

NLG PATH (CENTER)

WINGTIP PATH:

NOSE PATH

MLG PATH (EDGE)

WINGTIP FENCES:R4 = 22.6 m (74 ft)SHARKLETS:R4 = 23.4 m (77 ft)

NLG PATH (EDGE)

45 m(148 ft)

3 m(10 ft)

12 m(39 ft)

R3 = 17.8 m(58 ft)

R4

25°

R5 = 22.6 m(74 ft)

N_AC_040503_1_0020102_01_03

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

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

4-5-3Page 3

Nov 01/19



**ON A/C A321-100 A321-200 A321neo

135˚ Turn - Taxiway to Taxiway

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

4-5-4Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo


APPROX 2.3 m(8 ft)

TAXIWAY CENTERLINE

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)

L = 45 m (150 ft)

(55 ft)

(100 ft)


NLG PATH (CENTER)

MLG PATH (EDGE)

N_AC_040504_1_0070101_01_01

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

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

4-5-4Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

TAXIWAY CENTERLINE

TAXIWAY CENTERLINE

FILLET R = 16.5 m

TURN R = 30 m


APPROX 3 m

15 m(50 ft)

15 m(50 ft)

(55 ft)

(100 ft)

L = 45 m (150 ft)

(10 ft)


NLG PATH (CENTER)

MLG PATH (EDGE)

N_AC_040504_1_0070102_01_01

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

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

4-5-4Page 3

Nov 01/19



**ON A/C A321-100 A321-200 A321neo

90˚ Turn - Taxiway to Taxiway

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

4-5-5Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

TAXIWAY CENTERLINE

NLG PATH (CENTER)

MLG PATH (EDGE)TAXIWAY 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_01

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

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

4-5-5Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

TAXIWAY CENTERLINE

FAA GROUP III FACILITIES.

NLG PATH (CENTER)

MLG PATH (EDGE)TAXIWAY CENTERLINE

APPROX 9.1 m(30 ft)


TURN R = 30 m(100 ft)


15 m(50 ft)

15 m(50 ft)

NOTE:

N_AC_040505_1_0040102_01_01

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

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

4-5-5Page 3

Nov 01/19


4-6-0 Runway Holding Bay (Apron)

**ON A/C A321-100 A321-200 A321neo

Runway Holding Bay (Apron)

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

4-6-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


4-7-0 Minimum Line-Up Distance Corrections

**ON A/C A321-100 A321-200 A321neo

Minimum Line-Up Distance Corrections

1. The ground maneuvers were performed using asymmetric thrust and differential braking only toinitiate the turn.TODA: Take-Off Distance AvailableASDA: Acceleration-Stop Distance Available

2. 90˚ Turn on Runway EntryThis section gives the minimum line-up distance correction for a 90˚ turn on runway entry.This maneuver consists in a 90˚ turn at minimum turn radius. It starts with the edge of the MLG ata distance of 3 m (10 ft) from the taxiway edge, and finishes with the aircraft aligned on thecenterline of the runway, see FIGURE 4-7-0-991-020-A.During the turn, all the clearances must meet the minimum value of 3 m (10 ft) for this category ofaircraft as recommended in ICAO Annex 14.

3. 180˚ Turn on Runway Turn PadThis section gives the minimum line-up distance correction for a 180˚ turn on the runway turn pad.This maneuver consists in a 180˚ turn at minimum turn radius on a runway turn pad with standardICAO geometry.It starts with the edge of the MLG at a distance of 3 m (10 ft) from the pavement edge, and itfinishes with the aircraft aligned on the centerline of the runway, see FIGURE 4-7-0-991-021-A.During the turn, all the clearances must meet the minimum value of 3 m (10 ft) for this category ofaircraft as recommended in ICAO Annex 14.

4. 180˚ Turn on Runway WidthThis section gives the minimum line-up distance correction for a 180˚ turn on the runway width.For this maneuver, the pavement width is considered to be the runway width, which is a frozenparameter (30 m (100 ft), 45 m (150 ft) and 60 m (200 ft)).As per the standard operating procedures for the ”180˚ turn on runway” (described in the FlightCrew Operating Manual), the aircraft is initially angled with respect to the runway centerline whenstarting the 180˚ turn, see FIGURE 4-7-0-991-022-A.The value of this angle depends on the aircraft type and is mentioned in the FCOM.During the turn, all the clearances must meet the minimum value of 3 m (10 ft) for this category ofaircraft as recommended in ICAO Annex 14.

NOTE : The minimum line-up distances may need a steering angle lower than the maximum one.

4-7-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

90° TURN ON RUNWAY ENTRY

AIRCRAFTTYPE

STEERINGANGLE

MAX

DISTANCE CORRECTIONMINIMUM LINE−UP


75°A321 41 ft12.6 m 97 ft29.5 mON TODA ON ASDA ON TODA ON ASDA

WIDE RUNWAY45 m (150 ft)/60 m (200 ft)

46 ft13.9 m 101 ft30.8 m

WIDE RUNWAY30 m (100 ft)

TAXIWAYCENTERLINE

RUNWAYCENTERLINE

TODA

3 m(10 ft)

> 3 m(10 ft)

ASDA

ASDA: ACCELERATION−STOP DISTANCE AVAILABLETODA: TAKE−OFF DISTANCE AVAILABLE

N_AC_040700_1_0200101_01_00

Minimum Line-Up Distance Corrections90˚ Turn on Runway EntryFIGURE-4-7-0-991-020-A01

4-7-0Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

180° TURN ON RUNWAY TURN PAD

AIRCRAFTTYPE

STEERINGANGLE

MAXWIDE RUNWAY

30 m (100 ft)

DISTANCECORRECTION

MINIMUM LINE−UP

75°A321 116 ft35.3 mON TODA

70 ft21.4 mON ASDA

126 ft38.3 m

PAVEMENTWIDTH

MINIMUMREQUIRED

DISTANCECORRECTION

MINIMUM LINE−UP

132 ft40.3 mON TODA

69 ft21 mON ASDA

124 ft37.9 m

PAVEMENTWIDTH

MINIMUMREQUIRED


> 3 m(10 ft)

TODA

ASDA

3 m(10 ft)

3 m(10 ft)

MINIMUM PAVEMENT WIDTH


RUNWAY CENTERLINE

N_AC_040700_1_0210101_01_00

Minimum Line-Up Distance Corrections180˚ Turn on Runway Turn Pad

FIGURE-4-7-0-991-021-A01

4-7-0Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

TODA

> 3 m(10 ft)

20° RUNWAY CENTERLINE

(10 ft)3 m

3 m(10 ft)

ASDA

180° TURN ON RUNWAY WIDTH

AIRCRAFTTYPE

STEERINGANGLE

MAX



75°A321 69 ft21.0 m 124 ft37.9 mON TODA ON ASDA ON TODA ON ASDA

NOT POSSIBLE

NOTE:

WIDTH WITH THE GIVEN ASSUMPTIONS DEFINED IN THIS SECTION (4−7−0) WHILE MAINTAINING THEMINIMUM 3 m (10 ft) MARGIN RECOMMENDED BY ICAO

"NOT POSSIBLE" MEANS THAT IT IS NOT POSSIBLE FOR THE AIRCRAFT TO TURN ON SUCH A RUNWAY


WIDE RUNWAY30 m (100 ft)


N_AC_040700_1_0220101_01_00

Minimum Line-Up Distance Corrections180˚ Turn on Runway WidthFIGURE-4-7-0-991-022-A01

4-7-0Page 4

Nov 01/19


4-8-0 Aircraft Mooring

**ON A/C A321-100 A321-200 A321neo

Aircraft Mooring

1. This section provides information on aircraft mooring.

4-8-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

A

GROUNDANCHOR

TOWINGFITTING

B

B

AFWD

TOWINGFITTING

N_AC_040800_1_0010101_01_00

Aircraft MooringFIGURE-4-8-0-991-001-A01

4-8-0Page 2

Nov 01/19


TERMINAL SERVICING

5-1-1 Aircraft Servicing Arrangements

**ON A/C A321-100 A321-200 A321neo

Aircraft Servicing Arrangements

1. This section provides typical ramp layouts, showing the various GSE items in position during typicalturn-round scenarios.

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

This table gives the symbols used on servicing diagrams.

Ground Support Equipment

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

5-1-1Page 1

Nov 01/19


5-1-2 Typical Ramp Layout - Open Apron

**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


5-1-3 Typical Ramp Layout - Gate

**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


5-2-0 Terminal Operations - Full Servicing Turn Round Time Chart

**ON A/C A321-100 A321-200 A321neo

Terminal Operations - Full Servicing Turn Round Time

1. This section provides a typical turn round time chart showing the typical time for ramp activitiesduring aircraft turn round.Actual times may vary due to each operator’s specific practices, resources, equipment and operatingconditions.

2. Assumptions used for full servicing turn round time chartFIGURE 5-2-0-991-007-A

A. PASSENGER HANDLING185 pax: 16 F/C + 169 Y/C.All passengers deplane and board the aircraft.1 Passenger Boarding Bridge (PBB) used at door 1L.Equipment positioning + opening door = +2 min.Closing door + equipment removal = +1.5 min.No Passenger with Reduced Mobility (PRM) on board.Deplaning:- 185 pax at door 1L- Deplaning rate = 20 pax/min- Priority deplaning for premium passengers.Boarding:- 185 pax at door 1L- Boarding rate = 12 pax/min- Last Pax Seating allowance (LPS) + headcounting = +2 min.

B. CARGO2 cargo loaders + 1 belt loader.Opening door + equipment positioning = +2 min.Equipment removal + closing door = +1.5 min.100% cargo exchange (baggage only):- FWD cargo compartment: 5 containers- AFT cargo compartment: 5 containers- Bulk compartment: 500 kg (1 102 lb).Container unloading/loading times:- Unloading = 1.5 min/container- Loading = 1.5 min/container.Bulk unloading/loading times:- Unloading = 150 kg/min (331 lb/min)- Loading = 120 kg/min (265 lb/min).

C. REFUELING20 000 l (5 283 US gal) at 50 psig (3.45 bars-rel), one hose (right wing).

5-2-0Page 1

Nov 01/19


Dispenser positioning/removal + connection/disconnection times = +2.5 min.

D. CLEANINGCleaning is performed in available time.

E. CATERING1 catering truck for servicing galleys sequentially at doors 1R and 4R.Equipment positioning + opening door = +2 min.Closing door + equipment removal = +1.5 min.Time to drive from one door to the other = +2 min.Full Size Trolley Equivalent (FSTE) to unload and load: 14 FSTE- 4 FSTE at door 1R- 10 FSTE at door 4R.Time for trolley exchange = 1.2 min per FSTE.

F. GROUND HANDLING/GENERAL SERVICINGStart of operations:- Bridges/stairs: t0 = 0- Other equipment: t = t0 + 1 min.Ground Power Unit (GPU): up to 90 kVA.Air conditioning: one hose.Potable water servicing: 100% uplift, 200 l (53 US gal).Toilet servicing: draining + rinsing.

**ON A/C A321neo

3. Assumptions used for full servicing turn round time chart for A321NEO-ACFFIGURE 5-2-0-991-009-A

A. PASSENGER HANDLING202 pax (all Y/C).All passengers deplane and board the aircraft.1 PBB used at door 1L.Equipment positioning + opening door = +2 min.Closing door + equipment removal = +1.5 min.No PRM on board.Deplaning:- 202 pax at door 1L- Deplaning rate = 20 pax/minBoarding:- 202 pax at door 1L- Boarding rate = 12 pax/min- LPS allowance + headcounting = +2 min.

B. CARGO2 cargo loaders + 1 belt loader.Opening door + equipment positioning = +2 min.

5-2-0Page 2

Nov 01/19


Equipment removal + closing door = +1.5 min.100% cargo exchange (baggage only):- FWD cargo compartment: 5 containers- AFT cargo compartment: 5 containers- Bulk compartment: 500 kg (1 102 lb).Container unloading/loading times:- Unloading = 1.5 min/container- Loading = 1.5 min/container.Bulk unloading/loading times:- Unloading = 150 kg/min (331 lb/min)- Loading = 120 kg/min (265 lb/min).

C. REFUELING20 000 l (5 283 US gal) at 50 psig (3.45 bars-rel), one hose (right wing).No optional coupling.Dispenser positioning/removal + connection/disconnection times = +2.5 min.Refuelling with passengers on board: No


E. CATERING1 catering truck for servicing galleys sequentially at doors 1R and 4R.Equipment positioning + opening door = +2 min.Closing door + equipment removal = +1.5 min.Time to drive from one door to the other = +2 min.FSTE to unload and load: 11 FSTE- 4 FSTE at door 1R- 7 FSTE at door 4R.Time for trolley exchange = 1.2 min per FSTE.Maximum catering time = +13.2 min.

F. GROUND HANDLING/GENERAL SERVICINGStart of operations:- Bridges/stairs: t0 = 0- Other equipment: t = t0 + 1 min.Ground Power Unit (GPU): up to 90 kVA.Air conditioning: one hose.Potable water servicing: 100% uplift, 200 l (53 US gal).Toilet servicing: draining + rinsing.

G. SECURITY/SAFETY CHECKSNo security or safety checks are applicable.

5-2-0Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

GSE POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH

DEPLANING/BOARDING AT DOOR 1L

HEADCOUNTING

CATERING AT DOOR 4R

CLEANING

CARGO FWD CC

CARGO BULK CC

REFUELING

POTABLE WATER SERVICING

TOILET SERVICING

CARGO AFT CC

CATERING AT DOOR 1R

0 10 20 30 5040 60

N_AC_050200_1_0070101_01_04

Full Servicing Turn Round Time ChartFIGURE-5-2-0-991-007-A01

5-2-0Page 4

Nov 01/19


**ON A/C A321neo

GSE POSITIONING/REMOVAL/MOVING

ACTIVITY TIME

CRITICAL PATH


LPS + HEADCOUNTING

SECURITY / SAFETY CHECKS

CATERING AT DOOR 1R

CLEANING

CARGO AFT CC

CARGO BULK CC

CARGO FWD CC

CATERING AT DOOR 4R

0 10 20 30 5040 60

REFULING


WASTE WATER SERVICING

N_AC_050200_1_0090101_01_02

Full Servicing Turn Round Time Chart for A321NEO-ACFFIGURE-5-2-0-991-009-A01

5-2-0Page 5

Nov 01/19


5-3-0 Terminal Operation - Outstation Turn Round Time Chart

**ON A/C A321-100 A321-200 A321neo

Terminal Operations -Transit Turn Round Time

1. This section provides a typical turn round time chart showing the typical time for ramp activitiesduring aircraft turn round. Actual times may vary due to each operator’s specific practices, resources,equipment and operating conditions.

2. Assumptions used for transit turn round time chartFIGURE 5-3-0-991-004-A

A. PASSENGER HANDLING220 pax (all Y/C).All passengers deplane and board the aircraft.2 stairways used at doors 1L and 4L.Equipment positioning + opening door = +2 min.Closing door + equipment removal = +1.5 min.No Passenger with Reduced Mobility (PRM) on board.Deplaning:- 110 pax at door 1L- 110 pax at door 4L- Deplaning rate = 20 pax/min. per doorBoarding:- 110 pax at door 1L- 110 pax at door 4L- Boarding rate = 12 pax/min. per door- Last Pax Seating allowance (LPS) + headcounting = +2 min.

B. CARGO2 cargo loaders.Opening door + equipment positioning = +2 min.Equipment removal + closing door = +1.5 min.100% cargo exchange :- FWD cargo compartment: 5 containers- AFT cargo compartment: 5 containersContainer unloading/loading times:- Unloading = 1.5 min./container- Loading = 1.5 min./container.

C. REFUELINGNo refueling.


5-3-0Page 1

Nov 01/19


E. CATERINGOne catering truck for servicing the galleys as required.

F. GROUND HANDLING/GENERAL SERVICINGStart of operations:- Bridges/stairs: t0 = 0- Other equipment: t = t0.Ground Power Unit (GPU): up to 90 kVA.Air conditioning: one hose.No potable water servicing.No toilet servicing.

**ON A/C A321neo

3. Assumptions used for transit turn round time chart for A321NEO-ACFFIGURE 5-3-0-991-007-A

A. PASSENGER HANDLING202 pax (all Y/C).All passengers deplane and board the aircraft.2 Stairs used at door 1L and 4L.Equipment positioning + opening door = +2 min.Closing door + equipment removal = +1.5 min.No PRM on board.Deplaning:- 101 pax at door 1L- 101 pax at door 4L- Deplaning rate = 20 pax/min. per doorBoarding:- 101 pax at door 1L- 101 pax at door 4L- Boarding rate = 12 pax/min. per door- LPS + headcounting = +2 min.

B. CARGO2 cargo loaders.Opening door + equipment positioning = +2 min.Equipment removal + closing door = +1.5 min.100% cargo exchange:- FWD cargo compartment: 5 containers- AFT cargo compartment: 5 containers- Bulk compartment: 500 kg (1 102 lb).Container unloading/loading times:- Unloading = 1.5 min/container- Loading = 1.5 min/container.Bulk unloading/loading times:

5-3-0Page 2

Nov 01/19


- Unloading = 150 kg/min (331 lb/min)- Loading = 120 kg/min (265 lb/min).

C. REFUELING20 000 l (5 283 US gal) at 50 psig (3.45 bars-rel). No optional coupling.Dispenser positioning/removal + connection/disconnection times = +2.5 min.Refuelling with passengers on board: No.


E. CATERING1 catering truck for servicing galleys sequentially at doors 1R and 4R.Equipment positioning + opening door = +2 min.Closing door + equipment removal = +1.5 min.Time to drive from one door to the other = +2 min.Full Size Trolley Equivalent (FSTE) to unload and load: 11 FSTE- 4 FSTE at door 1R- 7 FSTE at door 4R.Time for trolley exchange = 1.2 min per FSTEMaximum catering time = +13.2 min.

F. GROUND HANDLING/GENERAL SERVICINGStart of operations:- Bridges/stairs: t0 = 0- Other equipment: t = t0.GPU: up to 90 kVA.Air conditioning: one hose.Potable water servicing: 100% uplift, 200 l (53 US gal).Toilet servicing: draining + rinsing.

G. SECURITY/SAFETY CHECKSNo safety or security checks are available.

5-3-0Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo


ACTIVITY

CRITICAL PATH


LPS + HEADCOUNTING

CATERING

CLEANING

CARGO AFT CC

REFUELING



CARGO FWD CC

0 5 10 15 2520


SECURITY/SAFETY CHECKS

N_AC_050300_1_0040101_01_05

Outstation Turn Round Time ChartFIGURE-5-3-0-991-004-A01

5-3-0Page 4

Nov 01/19


**ON A/C A321neo



CATERING AT DOOR 1R

CATERING AT DOOR 4R

CARGO AFT CC

REFUELING


CARGO FWD CC

LPS + HEADCOUNTING

0 5 10 15 20 25 30 35 40 45

CARGO BULK CC

CLEANING

SECURITY/SAFETY CHECKS


ACTIVITY

CRITICAL PATH


N_AC_050300_1_0070101_01_02

Outstation Turn Round Time Chart for A321NEO-ACFFIGURE-5-3-0-991-007-A01

5-3-0Page 5

Nov 01/19


5-4-1 Ground Service Connections

**ON A/C A321-100 A321-200 A321neo

Ground Service Connections Layout

1. This section provides the ground service connections layout.

5-4-1Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

8

10

13

1211

2 − OXYGEN SYSTEM3 − NLG GROUNDING (EARTHING) POINT

5 − LOW PRESSURE AIR PRE−CONDITIONING6 − HIGH PRESSURE AIR PRE−CONDITIONING7 − REFUEL/DEFUEL INTEGRATED PANEL8 − IDG/STARTER OIL SERVICING

4 − POTABLE WATER DRAIN PANEL

9 − ENGINE OIL SERVICING10 − OVERPRESSURE PROTECTOR11 − REFUEL/DEFUEL COUPLINGS

(OPTIONAL−LH WING)

12 − OVERWING REFUEL (IF INSTALLED)13 − NACA VENT INTAKE

16 − ACCUMULATOR CHARGING (GREEN SYSTEM)AND RESERVOIR DRAIN (GREEN SYSTEM)

18 − MLG GROUNDING (EARTHING) POINT19 − WASTE WATER SERVICE PANEL20 − POTABLE WATER SERVICE PANEL21 − APU OIL SERVICING

2

13

4 56

1814

15

1416

1715

2019

21

10

131211

7

18

1 − GROUND ELECTRICAL POWER

8

CONNECTOR14 − YELLOW HYDRAULIC−SYSTEM SERVICE PANEL15 − BLUE HYDRAULIC−SYSTEM SERVICE PANEL

17 − GREEN HYDRAULIC−SYSTEM SERVICE PANEL

9

9

N_AC_050401_1_0070101_01_02

Ground Service Connections LayoutFIGURE-5-4-1-991-007-A01

5-4-1Page 2

Nov 01/19


5-4-2 Grounding Points

**ON A/C A321-100 A321-200 A321neo

Grounding (Earthing) Points

1. Grounding (Earthing) Points

DISTANCEFROM AIRCRAFT CENTERLINE

AFT OF NOSELH SIDE RH 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 (earthing) stud on each landing gear leg is designed for use with a clip-onconnector (such as Appleton TGR).

B. The grounding (earthing) studs are used to connect the aircraft to an approved ground (earth)connection on the ramp or in the hangar for:- Refuel/defuel operations,- Maintenance operations,- Bad weather conditions.

NOTE : In all other conditions, the electrostatic discharge through the tire is sufficient.If the aircraft is on jacks for retraction and extension checks or for theremoval/installation of the landing gear, the grounding (earthing) alternative points (ifinstalled) are:- In the hole on the avionics-compartment lateral right door-frame (on FR14),- On the engine nacelles,- Adjacent to the high-pressure connector,- On the wing upper surfaces.

5-4-2Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

NOSE LANDING GEAR MAIN LANDING GEAR

GROUNDING (EARTHING) CABLE

LANDINGGEAR

GROUNDING (EARTHING) POINT

TYPICAL

A

A

A

N_AC_050402_1_0070101_01_01

Ground Service ConnectionsGrounding (Earthing) Points - Landing Gear

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

5-4-2Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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 (Earthing) Points - Wing (If Installed)

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

5-4-2Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

Z822

FR14 FR12

A

PRESS

FR14

FR12

B

C

A

A/C STRUCTURE

GROUNDING(EARTHING) CABLE

B

FWD

(EARTHING) POINTGROUNDING

CN_AC_050402_1_0180101_01_00

Ground Service ConnectionsGrounding (Earthing) Point - Avionics Compartment Door-Frame

FIGURE-5-4-2-991-018-A01

5-4-2Page 4

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

PHONE JACK

A

GROUNDING (EARTHING) POINT

A

N_AC_050402_1_0190101_01_00

Ground Service ConnectionsGrounding (Earthing) Point - Engine Air Intake (If Installed)

FIGURE-5-4-2-991-019-A01

5-4-2Page 5

Nov 01/19


5-4-3 Hydraulic System

**ON A/C A321-100 A321-200 A321neo

Hydraulic Servicing

1. Access


ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUND

Green System:Access Door 197CB

23.44 m(76.90 ft)

1.27 m(4.17 ft)

1.76 m(5.77 ft)

Yellow System:Access Door 198CB

23.44 m(76.90 ft)

1.27 m(4.17 ft)

1.76 m(5.77 ft)

Blue System:Access Door 197EB

24.49 m(80.35 ft)

1.27 m(4.17 ft)

1.76 m(5.77 ft)

2. Reservoir Pressurization


ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUND

Access Door 195BB19.92 m(65.35 ft)

0.25 m(0.82 ft)

1.74 m(5.71 ft)

3. Accumulator Charging

Four MIL-PRF-6164 connections:


ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUNDYellow SystemAccumulator:Access Door 196BB

19.92 m(65.35 ft)

0.25 m(0.82 ft)

1.74 m(5.71 ft)

5-4-3Page 1

Nov 01/19



ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUNDGreen SystemAccumulator:Left MLG Door

21.04 m(69.03 ft)

0.25 m(0.82 ft)

3.20 m(10.50 ft)

Blue SystemAccumulator:Access Door 195BB

19.92 m(65.35 ft)

0.25 m(0.82 ft)

1.74 m(5.71 ft)

Yellow System BrakingAccumulator:Access Door 196BB

19.92 m(65.35 ft)

0.25 m(0.82 ft)

1.74 m(5.71 ft)

4. Reservoir Filling

Centralized filling capability on the Green System ground service panel:


ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUND

Access Door 197CB23.44 m(76.90 ft)

1.27 m(4.17 ft)

1.76 m(5.77 ft)

Filling: Ground pressurized supply or hand pump.

5. Reservoir Drain

Three 3/8 in. self-sealing connections:


ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUND

Yellow System:Access Door 196BB

19.92 m(65.35 ft)

0.25 m(0.82 ft)

1.74 m(5.71 ft)

Green System:Left MLG Door

21.04 m(69.03 ft)

0.25 m(0.82 ft)

3.20 m(10.5 ft)

5-4-3Page 2

Nov 01/19



ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEAN HEIGHTFROM

GROUND

Blue System:Access Door 197EB

24.49 m(80.35 ft)

1.27 m(4.17 ft)

1.76 m(5.77 ft)

NOTE : The drain valve is on the Blue System ground service panel for the reservoir of the Bluehydraulic system.The drain valve is on the reservoir for the Green and Yellow Hydraulic Systems.

6. Ground Test

On each ground service panel:- One self-sealing connector (suction).- One self-sealing connector (delivery).

5-4-3Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

RESERVOIR FILL SYSTEMHAND PUMP FILL CONNECTION

RESERVOIR FILLCONNECTION

GROUND SUPPLY

RESERVOIR FILL SYSTEMSELECTOR VALVE INDICATOR

QUANTITY

GROUNDSUCTION

GROUNDDELIVERY

CONNECTION CONNECTION

A

FWD

DEPRESSURIZATIONCONNECTION

RESERVOIR

FR47197CB

A

FR50

N_AC_050403_1_0040101_01_01

Ground Service ConnectionsGreen System Ground Service Panel

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

5-4-3Page 4

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

GROUNDSUCTION

GROUNDDELIVERY

CONNECTION CONNECTION

RESERVOIRDEPRESSURIZATION

VALVE

RESERVOIRDRAIN VALVE

A

FWD

197EBFR47

A

FR50

N_AC_050403_1_0050101_01_01

Ground Service ConnectionsBlue System Ground Service Panel

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

5-4-3Page 5

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

RESERVOIRDEPRESSURIZATION

VALVE

GROUNDSUCTION

GROUNDDELIVERY

CONNECTION CONNECTIONHAND PUMP

LEVER

A

FR50

FR47

FWD

A198CB

N_AC_050403_1_0060101_01_01

Ground Service ConnectionsYellow System Ground Service Panel

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

5-4-3Page 6

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

0.64 m (2.10 ft)

0.69 m (2.26 ft) 02

01

GROUND

B

RAM AIR TURBINE (RAT)

FOR A32102

NOTE:FOR A318, A319 AND A32001

A

RAT UPLOCK SAFETY−PIN

C

C

B

RAT EXTENDED

RAT RETRACTED

195BB

195CB

A

Z195

N_AC_050403_1_0070101_01_00

Ground Service ConnectionsRAT

FIGURE-5-4-3-991-007-A01

5-4-3Page 7

Nov 01/19


5-4-4 Electrical System

**ON A/C A321-100 A321-200 A321neo

Electrical System

1. Electrical SystemThis chapter provides data related to the location of the ground service connections.

DISTANCEFROM AIRCRAFT CENTERLINEACCESS


MEAN HEIGHTFROM GROUND

A/C ExternalPower:

Access Door 121AL

2.55 m(8.37 ft) On centerline

2.00 m(6.56 ft)

NOTE : Distances are approximate.

2. Technical Specifications

A. External Power Receptacle:- One receptacle according to MS 90362-3 (without shield MS 17845-1) -- 90 kVA.

NOTE : Make sure that for connectors featuring micro switches, the connector is chamfered toproperly engage in the receptacle.

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

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

5-4-4Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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 2

Nov 01/19


5-4-5 Oxygen System

**ON A/C A321-100 A321-200 A321neo

Oxygen System

1. Oxygen System


ACCESSAFT OF NOSE

LH SIDE RH SIDE

MEANHEIGHTFROM

GROUND

Oxygen Replenishment:Access Door 812

3.45 m(11.32 ft)

1.15 m(3.77 ft)

-2.60 m(8.53 ft)

2. Technical Specifications- One 3/8 in. MIL-DTL 7891 standard service connection.

NOTE : External charging in the avionics compartment.

5-4-5Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

C

OXYGEN STORAGECYLINDER

TEST PORT

OXYGEN FILLINGINDICATOR

OXYGEN FILLINGPORT

Z125

FR9

FR16

FR12

FR9

A

A

B

C

B

812

N_AC_050405_1_0010101_01_00

Ground Service ConnectionsOxygen System

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

5-4-5Page 2

Nov 01/19


5-4-6 Fuel System

**ON A/C A321-100 A321-200 A321neo

Fuel System

1. Refuel/Defuel Control Panel

DISTANCEPOSITION FROM AIRCRAFT

CENTERLINEACCESS



Refuel/DefuelIntegrated Panel:Access Door192MB

20.65 m(67.75 ft)

-1.8 m

(5.91 ft)1.8 m

(5.91 ft)

2. Refuel/Defuel Connectors


CENTERLINEACCESS



Refuel/DefuelCoupling, Left:Access Panel522HB(Optional)

21.84 m(71.65 ft)

9.83 m(32.25 ft)

- 3.65 m(11.98 ft)

Refuel/DefuelCoupling, Right:Access Panel622HB

21.84 m(71.65 ft)

-9.83 m

(32.25 ft)3.65 m

(11.98 ft)

Overwing Gravity-Refuel Cap

23.35 m(76.61 ft)

12.4 m(40.68 ft)

12.4 m(40.68 ft)

3.7 m(12.14 ft)

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. Average Flow Rate:- 1250 l/min (330 US gal/min).

5-4-6Page 1

Nov 01/19


3. Overpressure Protectors and NACA Vent Intake


CENTERLINEACCESS



Surge TankOverpressure-Protector:Access Panel550CB (650CB)

24.61 m(80.74 ft)

14.9 m(48.88 ft)

14.9 m(48.88 ft)

4.32 m(14.17 ft)

Wing TankOverpressure-Protector:Access Panel540PB (640PB)

24.2 m(79.40 ft)

12.15 m(39.86 ft)

12.15 m(39.86 ft)

4.1 m(13.45 ft)

NACA Vent Intake:Access Panel550AB (650AB)

24.05 m(78.90 ft)

13.7 m(44.95 ft)

13.7 m(44.95 ft)

4.02 m(13.19 ft)


5-4-6Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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 Control PanelFIGURE-5-4-6-991-001-A01

5-4-6Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

RIB19

RIB20

A

ADAPTER(REF ONLY)

GROUND CONNECTION(REF ONLY)

44QM

(45QM)

AFWD

N_AC_050406_1_0030101_01_00

Ground Service ConnectionsOverwing Gravity-Refuel Cap (If Installed)

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

5-4-6Page 5

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

OVERPRESSURE

NACA VENT INTAKE

NACA VENT

NOTE:LH SHOWN, RH SYMMETRICAL01

A

B C 01

01

RIB25RIB24RIB23

RIB22

540PB (640PB)

550AB (650AB)

550CB (650CB)

B

PROTECTOR

PROTECTOR

Z500 (Z600)

RIB20RIB19

A

C

N_AC_050406_1_0040201_01_00

Ground Service ConnectionsOverpressure Protectors and NACA Vent Intake

FIGURE-5-4-6-991-004-B01

5-4-6Page 6

Nov 01/19


5-4-7 Pneumatic System

**ON A/C A321-100 A321-200 A321neo

Pneumatic System

1. High Pressure Air Connector




HP Connector:Access Door 191DB

17.25 m(56.59 ft)

0.84 m(2.76 ft)

-1.76 m(5.77 ft)

A. Connector:- One standard 3 in. ISO 2026 connection.

2. Low Pressure Air Connector




LP Connector:Access Door 191CB

16.72 m(54.86 ft)

1.11 m(3.64 ft)

-1.73 m(5.68 ft)

A. Connector:- One standard 8 in. SAE AS4262 connection.

5-4-7Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

A

B

FR34 FR36

B

191CB

191DB

HP CONNECTOR

LP CONNECTOR

A

N_AC_050407_1_0010101_01_00

Ground Service ConnectionsLP and HP Ground Connectors

FIGURE-5-4-7-991-001-A01

5-4-7Page 2

Nov 01/19


5-4-8 Oil System

**ON A/C A321-100 A321-200 A321neo

Oil System

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

1. Engine Oil Replenishment for CFM56 Series Engine (See FIGURE 5-4-8-991-003-A):One gravity filling cap and one pressure filling connection per engine.


ACCESSAFT OF NOSE

ENGINE 1 (LH) ENGINE 2 (RH)

MEAN HEIGHTFROM

GROUNDEngine Oil Gravity FillingCap:Access door: 437BL(LH),447BL (RH)

17.38 m(57.02 ft)

6.63 m(21.75 ft)

4.82 m(15.81 ft)

1.46 m(4.79 ft)

Engine Oil PressureFilling Port:

17.26 m(56.63 ft)

6.49 m(21.29 ft)

4.74 m(15.55 ft)

1.42 m(4.66 ft)


A. Tank capacity:- Full level: 19.6 l (5 US gal),- Usable: 9.46 l (3 US gal).

B. Maximum delivery pressure required: 1.72 bar (25 psi).Maximum delivery flow required: 180 l/h (48 US gal/h).

2. IDG Oil Replenishment for CFM56 Series Engine (See FIGURE 5-4-8-991-004-A):One pressure filling connection per engine: OMP 2506-18 plus one connection overflow: OMP2505-18.


ACCESSAFT OF NOSE


MEAN HEIGHTFROM

GROUNDIDG Oil Pressure FillingConnection:Access door: 438AR(LH),448AR (RH)

16.46 m(54.00 ft)

6.90 m(22.64 ft)

5.52 m(18.11 ft)

0.68 m(2.23 ft)

5-4-8Page 1

Nov 01/19



A. Tank capacity: 5 l (1 US gal).

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

3. Starter Oil Replenishment for CFM56 Series Engine (See FIGURE 5-4-8-991-005-A):One gravity filling cap per engine.


ACCESSAFT OF NOSE


MEAN HEIGHTFROM

GROUND

Starter Oil FillingConnection:

16.81 m(55.15 ft)

5.30 m(17.39 ft)

6.20 m(20.34 ft)

0.76 m(2.49 ft)


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

4. Engine Oil Replenishment for IAE V2500 Series Engine (See FIGURE 5-4-8-991-006-B):One gravity filling cap per engine.


ACCESSAFT OF NOSE


MEAN HEIGHTFROM

GROUNDEngine Oil Gravity FillingCap:Access door: 437BL(LH),447BL (RH)

16.50 m(54.13 ft)

6.56 m(21.52 ft)

4.92 m(16.14 ft)

1.22 m(4.00 ft)


A. Tank capacity:- Full level: 28 l (7 US gal),- Usable: 23.50 l (6 US gal).

5. IDG Oil Replenishment for IAE V2500 Series Engine (See FIGURE 5-4-8-991-007-B):One pressure filling connection per engine: 2506-2 plus one overflow connection: 2505-2.

5-4-8Page 2

Nov 01/19



ACCESSAFT OF NOSE


MEAN HEIGHTFROM

GROUND

IDG Oil Pressure FillingConnection:

17.06 m(55.97 ft)

5.42 m(17.78 ft)

6.04 m(19.82 ft)

0.80 m(2.62 ft)


A. Tank capacity: 4.10 l (1 US gal).

6. Starter Oil Replenishment for IAE V2500 Series Engine (See FIGURE 5-4-8-991-008-B):One gravity filling cap per engine.


ACCESSAFT OF NOSE


MEAN HEIGHTFROM

GROUND

Starter Oil FillingConnection:

19.66 m(64.50 ft)

5.30 m(17.39 ft)

6.14 m(20.14 ft)

0.75 m(2.46 ft)


A. Tank capacity: 0.35 l (0.09 US gal).

**ON A/C A321-100 A321-200 A321neo

7. APU Oil System (See FIGURE 5-4-8-991-009-A):APU oil gravity filling cap.


ACCESSAFT OF NOSE


MEAN HEIGHTFROM

GROUND

GTCP 36-30042.42 m(139.17 ft)

0.30 m(0.98 ft)

-4.83 m(15.85 ft)

APS 320042.42 m(139.17 ft)

0.30 m(0.98 ft)

-4.78 m(15.68 ft)

131-942.32 m(138.85 ft)

0.35 m(1.15 ft)

-4.32 m(14.17 ft)


5-4-8Page 3

Nov 01/19


A. Tank capacity (usable):- APU type GTCP 36-300: 6.20 l (2 US gal),- APU type APS 3200: 5.40 l (1 US gal),- APU type 131-9: 6.25 l (2 US gal).

5-4-8Page 4

Nov 01/19


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

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

437BL (ENGINE 1)447BL (ENGINE 2)

N_AC_050408_1_0030101_01_00

Ground Service ConnectionsEngine Oil Tank -- CFM56 Series Engine

FIGURE-5-4-8-991-003-A01

5-4-8Page 5

Nov 01/19


**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 VALVE

1

2

34

5

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_050408_1_0040101_01_00

Ground Service ConnectionsIDG Oil Tank -- CFM56 Series Engine

FIGURE-5-4-8-991-004-A01

5-4-8Page 6

Nov 01/19


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

DRAIN PORTAND MAGNETICPLUG

OVERFLOWPLUG

STARTER

OIL FILLERPLUG

A

A

N_AC_050408_1_0050101_01_00

Ground Service ConnectionsStarter Oil Tank -- CFM56 Series Engine

FIGURE-5-4-8-991-005-A01

5-4-8Page 7

Nov 01/19


**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

B

A

B

FWD

437BL (ENGINE 1)447BL (ENGINE 2)

A

N_AC_050408_1_0060201_01_00

Ground Service ConnectionsEngine Oil Tank -- IAE V2500 Series Engine

FIGURE-5-4-8-991-006-B01

5-4-8Page 8

Nov 01/19


**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_050408_1_0070201_01_00

Ground Service ConnectionsIDG Oil Tank -- IAE V2500 Series Engine

FIGURE-5-4-8-991-007-B01

5-4-8Page 9

Nov 01/19


**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_050408_1_0080201_01_00

Ground Service ConnectionsStarter Oil Tank -- IAE V2500 Series Engine

FIGURE-5-4-8-991-008-B01

5-4-8Page 10

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

GRAVITYOIL FILLER

PRESSUREFILL PORT

OVERFLOWDRAIN VALVE

A

OIL LEVELSIGHT GLASS

FR80

FR84

Z315(Z316)

A

N_AC_050408_1_0090101_01_00

Ground Service ConnectionsAPU Oil Tank

FIGURE-5-4-8-991-009-A01

5-4-8Page 11

Nov 01/19


5-4-9 Potable Water System

**ON A/C A321-100 A321-200 A321neo

Potable Water System

1. Potable Water Ground Service Panels


CENTERLINEACCESS



Potable-WaterService Panel:Access Door 171AL

38.2 m(125.33 ft)

0.3 m(0.98 ft)

-2.6 m(8.53 ft)

Potable-WaterDrain Panel:Access Door 133AL

11.8 m(38.71 ft)

0.15 m(0.49 ft)

- 1.75 m(5.74 ft)



A. Connectors:

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

(2) On the potable-water drain panel (Access Door 133AL)- Drain Nipple 3/4 in. (ISO 17775).

B. Usable capacity:- Standard configuration - one tank: 200 l (53 US gal).

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

D. Typical flow rate:- 50 l/min (13 US gal/min).

5-4-9Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

FR65FR66

FILL/DRAINCONTROL HANDLE

GROUND AIR−PRESSURE CONNECTION

FILL/DRAIN PORT

FR29

FR28

B

AOVERFLOW PORT

133AL

171AL

A

B

DRAIN PORT

HANDLEDRAIN CONTROL

POTABLE−WATER DRAIN PANEL

POTABLE−WATER SERVICE PANEL

N_AC_050409_1_0290101_01_00

Ground Service ConnectionsPotable Water Ground Service Panels

FIGURE-5-4-9-991-029-A01

5-4-9Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

A

Z170

A

B

FR65

FR68

POTABLE WATERTANK

OVERFLOWLINE

FILL/DRAINLINE

B

POTABLE WATERDISTRIBUTION LINE

N_AC_050409_1_0300101_01_00

Ground Service ConnectionsPotable Water Tank LocationFIGURE-5-4-9-991-030-A01

5-4-9Page 3

Nov 01/19


5-4-10 Waste Water System

**ON A/C A321-100 A321-200 A321neo

Waste Water System

1. Waste Water System


CENTERLINEACCESS



Waste-WaterGround ServicePanel:Access door 172AR

38.2 m(125.33 ft)

-0.8 m(2.62 ft)

2.8 m(9.19 ft)



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

B. Usable waste tank capacity:- Standard configuration - one tank: 177 l (47 US gal).- A321NEO-ACF- one tank: 250 l (66 US gal).

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

D. Waste tank - Precharge:- 10 l (3 US gal).

5-4-10Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

WASTE TANK

DRAIN LINE FLUSH LINE

A

FR68

FR65

Z170

A

N_AC_050410_1_0040101_01_00

Ground Service ConnectionsWaste Tank Location

FIGURE-5-4-10-991-004-A01

5-4-10Page 3

Nov 01/19


**ON A/C A321neo

A

Z170

FR65

WASTE TANK

FLUSH LINE

DRAIN LINE

A

FR68

FR70

N_AC_050410_1_0050101_01_00

Ground Service Connections for A321NEO-ACFWaste Tank Location for A321NEO-ACF

FIGURE-5-4-10-991-005-A01

5-4-10Page 4

Nov 01/19


5-5-0 Engine Starting Pneumatic Requirements

**ON A/C A321-100 A321-200 A321neo

Engine Starting Pneumatic Requirements

1. The purpose of this section is to provide the minimum air data requirements at the aircraftconnection, needed to start the engine within no more than 60 seconds, at sea level (0 feet), for a setof Outside Air Temperatures (OAT).

ABBREVIATION DEFINITION

A/C Aircraft

ASU Air Start Unit

HPGC High Pressure Ground Connection


A. Air data (discharge temperature, absolute discharge pressure) are given at the HPGC.

B. For a given OAT the following charts are used to determine an acceptable combination for airdischarge temperature, absolute discharge pressure and mass flow rate.

C. This section addresses requirements for the ASU only, and is not representative of the startperformance of the aircraft using the APU or engine cross bleed procedure.

D. To protect the A/C, the charts feature, if necessary:- The maximum discharge pressure at the HPGC- The maximum discharge temperature at the HPGC.

5-5-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

EXAMPLE:FOR AN OAT OF 15° C (59° F) AND AN ASU PROVIDING A DISCHARGE TEMPERATURE OF 220° C (428° F)

− THE REQUIRED PRESSURE AT HPGC IS 41 psia− THE REQUIRED AIRFLOW AT A/C CONNECTION IS 49.5 kg/min.

AT HPGC:

IN CASE THE ACTUAL DISCHARGE TEMPERATURE OF THE ASU DIFFERS SUBSTANTIALLY FROM THEONES GIVEN IN THE CHARTS, A SIMPLE INTERPOLATION (LINEAR) IS SUFFICIENT TO DETERMINE THEREQUIRED AIR DATA.

NOTE:

CFM56 SERIES/SEA LEVELSTARTING TIME: LESS THAN 60 s

AIR DATA AT AIRCRAFT CONNECTION

40 45 5035

−40 −20 0 20 40 60 80 100OUTSIDE AIR TEMPERATURE OAT (° F)

−45 −35 −25 −15 −5 5 15 25 35 55OUTSIDE AIR TEMPERATURE OAT (° C)

50

AIR

FLO

W (

kg/m

in)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

AIR

FLO

W (

lb/m

in)

45

40

35

45

50

55

60

65

70

110

130

140

120

100

220° C (428° F) MAX.150° C (302° F)100° C (212° F)

ASU DISCHARGE TEMPERATURE:

45

120

ABSOLUTE PRESSURE (psia)

150

N_AC_050500_1_0160101_01_00

Example for Use of the ChartsFIGURE-5-5-0-991-016-A01

5-5-0Page 2

Nov 01/19


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

−40 −20 0 20 40 60 80 100 120

OUTSIDE AIR TEMPERATURE OAT (° F)

−50 −40 −30 −20 −10 0 10 20 30 40 50

OUTSIDE AIR TEMPERATURE OAT (° C)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

65

40

220° C (428° F) MAX.150° C (302° F)100° C (212° F)


IAE V2500 SERIES/SEA LEVELSTARTING TIME: LESS THAN 60 s


40 45 50


AIR

FLO

W (

kg/m

in)

AIR

FLO

W (

lb/m

in)

55

60

65

85

35

45

50

35

60

45

50

55

60

70

75

80

55 60 65

110

130

120

140

100

150

160

170

180

140

N_AC_050500_1_0170101_01_00

Engine Starting Pneumatic RequirementsIAE V2500 Series Engine

FIGURE-5-5-0-991-017-A01

5-5-0Page 3

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

−40 −20 0 20 40 60 80 100 120


−45 −35 −25 −15 −5 5 15 25 35 45 55


AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

50

45

40

220° C (428° F) MAX.150° C (302° F)100° C (212° F)


CFM56 SERIES AND CFM LEAP−1A NEO/SEA LEVELSTARTING TIME: LESS THAN 60 s


40 45 50


AIR

FLO

W (

kg/m

in)

AIR

FLO

W (

lb/m

in)

55

60

65

70

110

130

35

45

50

120

140

10035

150

N_AC_050500_1_0180101_01_00

Engine Starting Pneumatic RequirementsCFM56 Series and CFM LEAP-1A NEO Engine

FIGURE-5-5-0-991-018-A01

5-5-0Page 4

Nov 01/19


**ON A/C A321neo

PW 1100G NEO/SEA LEVELSTARTING TIME: LESS THAN 60 s


40 45 50 55


−40 −20 0 20 40 60 80 100


−45 −35 −25 −15 −5 5 15 25 35 45


55

AIR

FLO

W (

kg/m

in)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

AIR

FLO

W (

lb/m

in)

50

45

40

55

60

65

70

75

80

220° C (428° F) MAX.150° C (302° F)100° C (212° F)


140

160

170

150

130

N_AC_050500_1_0190101_01_00

Engine Starting Pneumatic RequirementsPW 1100G NEO Engine

FIGURE-5-5-0-991-019-A01

5-5-0Page 5

Nov 01/19


5-6-0 Ground Pneumatic Power Requirements

**ON A/C A321-100 A321-200 A321neo

Ground Pneumatic Power Requirements

1. GeneralThis section describes the required performance for the ground equipment to maintain the cabintemperature at 27 ˚C (80.6 ˚F) for the cooling or 21 ˚C (69.8 ˚F) for heating cases after boarding(Section 5.7 - steady state), and provides the time needed to cool down or heat up the aircraft cabinto the required temperature (Section 5.6 - dynamic cases with aircraft empty).

ABBREVIATION DEFINITION

A/C Aircraft

AHM Aircraft Handling Manual

AMM Aircraft Maintenance ManualGC Ground ConnectionGSE Ground Service Equipment

IFE In-Flight Entertainment


PCA Pre-Conditioned Air

A. The air flow rates and temperature requirements for the GSE, provided in Sections 5.6 and 5.7,are given at A/C ground connection.

NOTE : The cooling capacity of the equipment (kW) is only indicative and is not sufficient byitself to ensure the performance (outlet temperature and flow rate combinations arethe requirements needed for ground power). An example of cooling capacitycalculation is given in Section 5.7.

NOTE : The maximum air flow is driven by pressure limitation at the ground connection.

B. For temperatures at ground connection below 2 ˚C (35.6 ˚F) (Subfreezing), the groundequipment shall be compliant with the Airbus document ”Subfreezing PCA Carts - ComplianceDocument for Suppliers” (contact Airbus to obtain this document) defining all the requirementswith which Subfreezing Pre-Conditioning Air equipment must comply to allow its use on Airbusaircraft. These requirements are in addition to the functional specifications included in the IATAAHM997.

2. Ground Pneumatic Power RequirementsThis section provides the ground pneumatic power requirements for:- Heating (pull up) the cabin, initially at OAT, up to 21 ˚C (69.8 ˚F) (see FIGURE

5-6-0-991-001-A)- Cooling (pull down) the cabin, initially at OAT, down to 27 ˚C (80.6 ˚F) (see FIGURE

5-6-0-991-002-A).

5-6-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

15 75 900.4

0.8

0.9

1.0

1.1

1.3

1.4

2.5

3.0

AIR

FLO

W A

T G

C (

kg/s

)

AIR

FLO

W A

T G

C (

lb/s

)

PULL UP PERFORMANCE

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

OAT ISA −38° C (−36.4° F); GC INLET +70° C (+158° F); EMPTY CABIN; IFE OFF; NO SOLARLOAD; LIGHTS ON; GALLEYS OFF; RECIRCULATION FANS ON

30 60

1.2

0.7

2.0

1.50.6

0.5

45

MAXIMUM AIRFLOW

1.0

N_AC_050600_1_0010101_01_00

Ground Pneumatic Power RequirementsHeating

FIGURE-5-6-0-991-001-A01

5-6-0Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

30 75 90 1200.6

0.8

0.9

1.0

1.1

1.3

1.4

2.5

3.0

AIR

FLO

W A

T G

C (

kg/s

)

AIR

FLO

W A

T G

C (

lb/s

)

PULL DOWN PERFORMANCE

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

OAT ISA +23° C (+73.4° F); GC INLET +2° C (+35.6° F); EMPTY CABIN; IFE OFF; NO SOLARLOAD; LIGHTS ON; GALLEYS OFF; RECIRCULATION FANS ON

OAT ISA +23° C (+73.4° F); GC INLET −10° C (+14° F); EMPTY CABIN; IFE OFF; NO SOLARLOAD; LIGHTS ON; GALLEYS OFF; RECIRCULATION FANS ON

45 60 105

1.2

0.7

2.0

1.5

MAXIMUM AIRFLOW

N_AC_050600_1_0020101_01_00

Ground Pneumatic Power RequirementsCooling

FIGURE-5-6-0-991-002-A01

5-6-0Page 3

Nov 01/19


5-7-0 Preconditioned Airflow Requirements

**ON A/C A321-100 A321-200 A321neo

Preconditioned Airflow Requirements

1. This section provides the preconditioned airflow rate and temperature needed to maintain the cabintemperature at 27 ˚C (80.6 ˚F) for the cooling or 21 ˚C (69.8 ˚F) for the heating cases.

These settings are not intended to be used for operation (they are not a substitute for the settingsgiven in the AMM). They are based on theoretical simulations and give the picture of a real steadystate.The purpose of the air conditioning (cooling) operation (described in the AMM) is to maintain thecabin temperature below 27 ˚C (80.6 ˚F) during boarding (therefore it is not a steady state).

5-7-0Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

AIR

FLO

W A

T G

C (

kg/s

)

−100.4

AIR

FLO

W A

T G

C (

lb/s

)

0.6

0.8

1.0

1.2

1.4

−5 0 5 10 15 20 25 30 35

2.0

2.5

3.0

20 30 40 50 60 70 80

INLET TEMPERATURE AT GC (° C)

INLET TEMPERATURE AT GC (° F)

COOLING/HEATING PERFORMANCE

SETTINGS NOTINTENDED TO BE USED

FOR OPERATION

OAT ISA +23° C (73.4° F); EMPTY CABIN; IFE ON; LIGHTS ON; SOLAR LOAD; RECIRCULATION

OAT ISA −38° C (−36.4° F); EMPTY CABIN; IFE OFF; LIGHTS ON; NO SOLAR LOAD; RECIRCULATIONFANS ON; GALLEYS OFF

OAT ISA; 164 PAX; IFE ON; LIGHTS ON; SOLAR LOAD; RECIRCULATION FANS ON; GALLEYS ONFANS ON; GALLEYS ON

C1

H

90

1.0

1.5

C2

2

MAXIMUM AIRFLOW (RECIRCULATION FANS OFF)

MAXIMUM AIRFLOW(RECIRCULATION

FANS ON)

N_AC_050700_1_0030101_01_04

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

5-7-0Page 2

Nov 01/19


5-8-0 Ground Towing Requirements

**ON A/C A321-100 A321-200 A321neo

Ground Towing Requirements

1. This section provides information on aircraft towing.This aircraft is designed with means for conventional or towbarless towing. Information/procedurescan be found for both in AMM 09.Status on towbarless towing equipment qualification can be found in ISI 09.11.00001.

NOTE : The NLG steering deactivation pin has the same design for all Airbus programs.

One towbar fitting is installed at the front of the leg.The main landing gears have attachment points for towing or debogging (for details, refer ARM 07).

This section shows the chart to determine the drawbar pull and tow tractor mass requirements as afunction 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.

2. Towbar design guidelines

The aircraft towbar shall comply with the following standards:- ISO 8267-1, ”Aircraft - Towbar Attachment Fitting - Interface Requirements - Part 1: Main Line

Aircraft”,- SAE AS 1614, ”Main Line Aircraft Towbar Attach Fitting Interface”,- SAE ARP 1915, ”Aircraft Towbar”,- ISO 9667, ”Aircraft Ground Support Equipment - Towbar - Connection to Aircraft and Tractor”,- EN 12312-7, ”Aircraft Ground Support Equipment - Specific Requirements - Part 7: Aircraft

Movement Equipment”,- IATA Airport Handling Manual AHM 958, ”Functional Specification for an Aircraft Towbar”.

A conventional type towbar is required which should be equipped with a damping system (to protectthe nose gear against jerks) and with towing shear pins:- A traction shear pin calibrated at 9 425 daN (21 188 lbf),- A torsion pin calibrated at 826 m.daN (6 092 lbf.ft).

The towing head is designed according to ISO 8267-1, cat. I.

5-8-0Page 1

Nov 01/19


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

EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A321 AT 80 000 kg, 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 (80 000 kg),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 No. 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 (4 900 kg),SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE.THE OBTAINED X−COORDINATE IS THE TOTAL TRACTION WHEEL LOAD (8 660 kg).

−−−−−−−

CAPACITY.

NOTE:USE A TRACTOR WITH A LIMITED DRAWBAR PULL TO PREVENT LOADS ABOVE THE TOW−BAR SHEAR−PIN

DRY CONCRETE = 0.8

0 10 20 30 40 50 60 70 80 0 1 2

65707580859095

ICE = 0.05

5

0

HARD SNOW = 0.2

WET CONCRETE = 0.57

0 0.5 1.0 1.5 2.0

1.5% SLOPE

1 ENGINE ON

8.66

BREAKAWAY RESISTANCE 4%# OF ENGINES ON FOR PB: 1ENGINE THRUST 525 daN 80

4.9

No. OF ENGINESAT IDLE

SLOPE ( % )TOTAL TRACTION WHEEL LOAD (x 1 000 kg)

DR

AW

BA

R P

ULL

(x

1 00

0 kg

)

A/C

WE

IGH

T (

x 1

000

kg)

N_AC_050800_1_0010401_01_06

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

5-8-0Page 2

Nov 01/19


**ON A/C A321neo

10

5

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


SLOPE ( % )

DR

AW

BA

R P

ULL

(x

1 00

0 kg

)

A/C

WE

IGH

T (

x 1

000

kg)

TOTAL TRACTION WHEEL LOAD (x 1 000 kg)

9585

5.7

1.5% SLOPE80

75 7065

ICE = 0.05

10.03

DR

Y C

ON

CR

ET

E=

0.8

WE

T C

ON

CR

ET

E=

0.57

HAR

D S

NO

W=

0.2

BREAKAWAY RESISTANCE 4%# OF ENGINES ON FOR PB: 1ENGINE THRUST 750 daN FORALL TEMPERATURES AND BLEEDOFF (COVERS BLEED ON)

1 ENGINE ON

90 90



−−−−−−−

CAPACITY.


N_AC_050800_1_0010701_01_00

Ground Towing RequirementsPW 1100G Engine (Sheet 1 of 2)

FIGURE-5-8-0-991-001-G01

5-8-0Page 3

Nov 01/19


**ON A/C A321neo

10

5

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


SLOPE ( % )

DR

AW

BA

R P

ULL

(x

1 00

0 kg

)

A/C

WE

IGH

T (

x 1

000

kg)

TOTAL TRACTION WHEEL LOAD (x 1 000 kg)

9585

5.7

1.5% SLOPE80

75 7065

ICE = 0.05

10.03

DR

Y C

ON

CR

ET

E=

0.8

WE

T C

ON

CR

ET

E=

0.57

HAR

D S

NO

W=

0.2

1 ENGINE ON

90 90



−−−−−−−

CAPACITY.


BREAKAWAY RESISTANCE 4%# OF ENGINES ON FOR PB: 1ENGINE THRUST 750 daN FORALL TEMPERATURES AND SLSAND ECS NOMINAL

N_AC_050800_1_0010702_01_00

Ground Towing RequirementsCFM LEAP-1A Engine (Sheet 2 of 2)

FIGURE-5-8-0-991-001-G01

5-8-0Page 4

Nov 01/19


5-9-0 De-Icing and External Cleaning

**ON A/C A321-100 A321-200 A321neo

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 (43 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 103 1 109 2 22 27 291 43 463

A321 Sharklet/neo 103 1 109 10 108 27 291 43 463

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 1 798 24 258 365 3 929

A321 Sharklet/neo 167 1 798 24 258 373 4 015

NOTE : Dimensions are approximate.

3. External Cleaning

Wing Top Surface(Both Sides)

Wing Lower Surface(Including Flap Track

Fairing)(Both Sides)

Wingtip Devices(Both Inside andOutside Surfaces)

(Both Sides)AIRCRAFT TYPE


A321 103 1 109 109 1 173 2 22A321 Sharklet/neo 103 1 109 109 1 173 10 108


HTP Lower Surface(Both Sides)



A321 27 291 27 291 43 463

5-9-0Page 1

Nov 01/19



HTP Lower Surface(Both Sides)



A321 Sharklet/neo 27 291 27 291 43 463

Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned Area

AIRCRAFT TYPE


A321 510 5 490 73 786 895 9 634

A321 Sharklet/neo 510 5 490 73 786 902 9 709

NOTE : Dimensions are approximate.

5-9-0Page 2

Nov 01/19


OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

**ON A/C A321-100 A321-200 A321neo

Engine Exhaust Velocities and Temperatures

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

1. GeneralThis section provides the estimated engine exhaust efflux velocities and temperatures contours forGround Idle, Breakaway and Maximum Take-Off (MTO) conditions.

**ON A/C A321neo

2. GeneralThis section provides the estimated engine exhaust velocity and temperature contours for MTO,Breakaway 12% MTO, Breakaway 24% MTO and Ground Idle conditions for the CFM LEAP-1A andPW 1100G engines.

The MTO data are presented at the maximum thrust rating. The Breakaway data are presented at arating that corresponds to the minimum thrust level necessary to start the movement of the A/Cfrom a static position at its maximum ramp weight. Breakaway thrust corresponds to 12% MTO ifapplied on both engines and 24% MTO when applied on a single engine (Idle thrust on the otherengine).

The Idle data, provided by the engine manufacturer, are calculated for operational conditions ISA+15K (+15˚C), Sea Level, Static and no headwind. In the charts, the longitudinal distances aremeasured from the inboard engine core-nozzle exit section. The lateral distances are measured fromthe aircraft fuselage centerline.

The effects of on-wing installation are not taken into account. The effects of ground proximity arenot taken into account for PW 1100G engines, but they are taken into account for the CFMLEAP-1A engines.

The velocity contours are presented at 50 ft/s (15 m/s), 100 ft/s (30 m/s) and 150 ft/s (46 m/s).The temperature contours are shown at 313K (+40˚C), 323K (+50˚C) and 333K (+60˚C). Thevelocity and temperature contours do not take into account possible variations affecting performance,such as ambient temperature, field elevation or failure cases leading to an abnormal bleedconfiguration. To evaluate the impact of these specific variables on the exhaust contours, a specificstudy of the airport where the aircraft is intended to operate should be carried out.

6-1-0Page 1

Nov 01/19


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

**ON A/C A321-100 A321-200 A321neo

Engine Exhaust Velocities Contours - Ground Idle Power

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

6-1-1Page 1

Nov 01/19


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

ELE

VA

TIO

N

050

100

150

200

250

300

350

400

015

3045

6075

9010

512

0

PLA

NA

IRC

RA

FT

V (

m/s

)

GR

OU

ND

PLA

NE

4530

2520

1510

40 30 20 10 0036912

mft

mft

4530

2520

1510

40 30 20 10 0036912

ft m

N_AC_060101_1_0070101_01_01

Engine Exhaust VelocitiesGround Idle Power -- CFM56-5B Series Engine

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

6-1-1Page 2

Nov 01/19


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

015

3045

60

250

300

ELE

VA

TIO

N

GR

OU

ND

IDLE

TH

RU

ST

050

100

150

200

7590

PLA

N

34 m

ph20

mph

68 m

ph

ftm

60

15 10 5 0

40 20 0

ftm

60 40 20 0

V (

mph

)

34 m

ph20

mph

68 m

ph

15 10 5 0

ft m

N_AC_060101_1_0080101_01_01

Engine Exhaust VelocitiesGround Idle Power -- IAE V2500 Series Engine

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

6-1-1Page 3

Nov 01/19


**ON A/C A321neo

150

(46)

100

(30)

50 (15)

100

(30)

50 (15)

GR

OU

ND

IDLE

, SE

A L

EV

EL,

ISA

+15

K D

AY

, FN

= 1

591

lbf.

NO

TE

:

mft

00

0 0

5010

015

020

025

030

035

0

1530

4560

7590

105

10203040

36912

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

150

(46) P

LAN

AIR

CR

AF

T

mft

00

10203040

36912

VE

LOC

ITY

= ft

/s (

m/s

)

FE

ET

ME

TE

RS

N_AC_060101_1_0130101_01_00

Engine Exhaust VelocitiesGround Idle Power -- CFM LEAP-1A Engine

FIGURE-6-1-1-991-013-A01

6-1-1Page 4

Nov 01/19


**ON A/C A321neo

150

(46)

100

(30)

50 (15)

0 0

5010

015

020

025

030

035

0

1530

4560

7590

105

PLA

N

mft

00

10203040

36912

AIR

CR

AF

T

VE

LOC

ITY

= ft

/s (

m/s

)

FE

ET

ME

TE

RS

N_AC_060101_1_0140101_01_00

Engine Exhaust VelocitiesGround Idle Power -- PW 1100G Engine

FIGURE-6-1-1-991-014-A01

6-1-1Page 5

Nov 01/19


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

**ON A/C A321-100 A321-200 A321neo

Engine Exhaust Temperatures Contours - Ground Idle Power

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

6-1-2Page 1

Nov 01/19


**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

IRC

RA

FT

GR

OU

ND

PLA

NE

ME

TE

RS40 30 20 10 0

036912

mft

400

350

325

300

400

350

325

300

TE

MP

ER

AT

UR

E =

K

40 30 20 10 0036912

N_AC_060102_1_0070101_01_01

Engine Exhaust TemperaturesGround Idle Power -- CFM56-5B Series Engine

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

6-1-2Page 2

Nov 01/19


**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

Nov 01/19


**ON A/C A321neo

NO

TE

:G

RO

UN

D ID

LE, S

EA

LE

VE

L, IS

A+

15K

DA

Y, F

N =

1 5

91 lb

f.

mft

00

0 0

5010

015

020

025

030

035

0

1530

4560

7590

105

10203040

36912

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

313

323

333

313

323

333 P

LAN

AIR

CR

AF

T

mft

00

10203040

36912

TE

MP

ER

AT

UR

E =

K

FE

ET

ME

TE

RS

N_AC_060102_1_0130101_01_00

Engine Exhaust TemperaturesGround Idle Power -- CFM LEAP-1A Engine

FIGURE-6-1-2-991-013-A01

6-1-2Page 4

Nov 01/19


**ON A/C A321neo

0 0

5010

015

020

025

030

035

0

1530

4560

7590

105

333

323

313

PLA

NA

IRC

RA

FT

mft

00

10203040

36912

TE

MP

ER

AT

UR

E =

K

FE

ET

ME

TE

RS

N_AC_060102_1_0140101_01_00

Engine Exhaust TemperaturesGround Idle Power -- PW 1100G Engine

FIGURE-6-1-2-991-014-A01

6-1-2Page 5

Nov 01/19


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

**ON A/C A321-100 A321-200 A321neo

Engine Exhaust Velocities Contours - Breakaway Power

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

6-1-3Page 1

Nov 01/19


**ON A/C A321neo

ME

TE

RS

ELE

VA

TIO

N

VE

LOC

ITY

= ft

/s (

m/s

)

FE

ET

PLA

N

40 30 20 10 0036912

mft

40 30 20 10 0036912

mft

GR

OU

ND

PLA

NE

AIR

CR

AF

T

NO

TE

:T

WO−

EN

GIN

E B

RE

AK

AW

AY

, SE

A L

EV

EL,

ISA

+15

K D

AY

, FN

= 3

873

lbf.

150

(46)

100

(30)

50 (15)

150

(46)

100

(30)

50 (15)

050

100

150

200

250

300

015

3045

6075

90

N_AC_060103_1_0110101_01_00

Engine Exhaust VelocitiesBreakaway Power 12% MTO -- CFM LEAP-1A Engine

FIGURE-6-1-3-991-011-A01

6-1-3Page 2

Nov 01/19


**ON A/C A321neo

VE

LOC

ITY

= ft

/s (

m/s

)

PLA

NA

IRC

RA

FT

40 30 20 10 0036912

mft

200

(61)

100

(30)

50 (15)

150

(46)

250

(76)

FE

ET

ME

TE

RS

0 030

4560

7590

5010

015

020

025

030

0

15

N_AC_060103_1_0120101_01_00

Engine Exhaust VelocitiesBreakaway Power 12% MTO -- PW 1100G Engine

FIGURE-6-1-3-991-012-A01

6-1-3Page 3

Nov 01/19


**ON A/C A321neo

NO

TE

:

mft

00

0 0

5010

015

020

025

030

035

0

1530

4560

7590

105

10203040

36912

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

50 (15)

100

(30)

150

(46)

ON

E−

EN

GIN

E B

RE

AK

AW

AY

, SE

A L

EV

EL,

ISA

+15

K D

AY

, FN

= 7

747

lbf.

VE

LOC

ITY

= ft

/s (

m/s

)

50 (15)

100

(30)

150

(46)

PLA

N

mft

00

10203040

36912

AIR

CR

AF

T

FE

ET

ME

TE

RS

N_AC_060103_1_0190101_01_00

Engine Exhaust VelocitiesBreakaway Power 24% MTO -- CFM LEAP-1A Engine

FIGURE-6-1-3-991-019-A01

6-1-3Page 4

Nov 01/19


**ON A/C A321neo

0 0

5010

015

020

025

030

035

0

1530

4560

7590

105

50 (15)

200

(61)

250

(76)

300

(91)

350

(107

)

PLA

NA

IRC

RA

FT

mft

00

10203040

36912

VE

LOC

ITY

= ft

/s (

m/s

)

100

(30)

150

(46)

FE

ET

ME

TE

RS

N_AC_060103_1_0200101_01_00

Engine Exhaust VelocitiesBreakaway Power 24% MTO -- PW 1100G Engine

FIGURE-6-1-3-991-020-A01

6-1-3Page 5

Nov 01/19


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

(38%

N1)

NO

TE

:−

AD

D +

1%

N1

PE

R +

15°

C (

27°

F)

AB

OV

E IS

A T

EM

PE

RA

TU

RE

CO

ND

ITIO

NS

− A

DD

+ 1

% N

1 P

ER

2 0

00 ft

3 00

0 lb

s O

F T

HR

US

T V

(m

/s)

ELE

VA

TIO

N

PLA

NA

IRC

RA

FT

GR

OU

ND

PLA

NE

40 30 20 10 0036912

mft

40 30 20 10 0036912

mft

FE

ET

ME

TE

RS

15

15

20

2040

5010

015

020

025

030

0

1530

4560

7590

00

40

N_AC_060103_1_0230101_01_00

Engine Exhaust VelocitiesBreakaway Power - CFM56 Series Engine

FIGURE-6-1-3-991-023-A01

6-1-3Page 6

Nov 01/19


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

ME

TE

RS

015

3045

60

250

300

ELE

VA

TIO

N

VE

LOC

ITY

= ft

/s (

m/s

)

FE

ET

050

100

150

200

7590

PLA

N

100

(30)

50 (15)

30 (9)

100

(30)

50 (15)

30 (9)1.

05

1.04

1.03

050

0010

000

FN

= 3

000

lbf

ISA

/ O

MN

"V25

27A

5MD

V"

BA

SIS

RU

NW

AY

ALT

(ft)

FP

R

A32

1

ftm

15 10 5 0

60 40 20 0

ftm

60

15 10 5 0

40 20 0

N_AC_060103_1_0240101_01_00

Engine Exhaust VelocitiesBreakaway Power - IAE V2500 Series Engine

FIGURE-6-1-3-991-024-A01

6-1-3Page 7

Nov 01/19


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

**ON A/C A321-100 A321-200 A321neo

Engine Exhaust Temperatures Contours - Breakaway Power

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

6-1-4Page 1

Nov 01/19


**ON A/C A321neo

ELE

VA

TIO

N

FE

ET

100

030

AIR

CR

AF

T

GR

OU

ND

PLA

NE

ME

TE

RS

40 20 0069

mft

12

PLA

N

NO

TE

:T

WO−

EN

GIN

E B

RE

AK

AW

AY

, SE

A L

EV

EL,

ISA

+15

K D

AY

, FN

= 3

873

lbf.

31030 40 20 0

069

mft

12 31030

TE

MP

ER

AT

UR

E =

K

050

150

200

250

300

015

4560

7590

333

323

313

333

323

313

N_AC_060104_1_0170101_01_00

Engine Exhaust TemperaturesBreakaway Power 12% MTO - CFM LEAP-1A Engine

FIGURE-6-1-4-991-017-A01

6-1-4Page 2

Nov 01/19


**ON A/C A321neo

323

313

ME

TE

RS

015

3045

60

FE

ET

050

100

150

200

PLA

N

ftm

12 3 0

40 20 0

AIR

CR

AF

T

TE

MP

ER

AT

UR

E =

K

30 10

69

N_AC_060104_1_0180101_01_00

Engine Exhaust TemperaturesBreakaway Power 12% MTO - PW 1100G Engine

FIGURE-6-1-4-991-018-A01

6-1-4Page 3

Nov 01/19


**ON A/C A321neo

ELE

VA

TIO

N

FE

ET

050

100

150

200

250

300

015

3045

6075

90

AIR

CR

AF

T

GR

OU

ND

PLA

NE

ME

TE

RS

40 20 0069

mft

12

333

323

313

333

323

313

NO

TE

:O

NE−

EN

GIN

E B

RE

AK

AW

AY

, SE

A L

EV

EL,

ISA

+15

K D

AY

, FN

= 7

747

lbf.

31030 40 20 0

069

mft

12 31030

TE

MP

ER

AT

UR

E =

K

PLA

N

N_AC_060104_1_0190101_01_00

Engine Exhaust TemperaturesBreakaway Power 24% MTO - CFM LEAP-1A Engine

FIGURE-6-1-4-991-019-A01

6-1-4Page 4

Nov 01/19


**ON A/C A321neo

ME

TE

RS

015

3045

60

FE

ET

050

100

150

200

PLA

N

ftm

12 3 0

40 20 0

AIR

CR

AF

T

TE

MP

ER

AT

UR

E =

K

30 10

6933

332

331

3

N_AC_060104_1_0200101_01_00

Engine Exhaust TemperaturesBreakaway Power 24% MTO - PW 1100G Engine

FIGURE-6-1-4-991-020-A01

6-1-4Page 5

Nov 01/19


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

ELE

VA

TIO

N

PLA

NA

IRC

RA

FT

GR

OU

ND

PLA

NE

300

400

350

300

325

3 00

0 lb

s O

F T

HR

US

TT

EM

PE

RA

TU

RE

= K

FE

ET

1530

4560

7590

40 30 20 10 0036912

mft

ME

TE

RS

5010

015

020

025

030

0

mft

40 30 20 10 0036912

325

350

400

0 0

N_AC_060104_1_0230101_01_00

Engine Exhaust TemperaturesBreakaway Power - CFM56 Series Engine

FIGURE-6-1-4-991-023-A01

6-1-4Page 6

Nov 01/19


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

ELE

VA

TIO

N

TE

MP

ER

AT

UR

E =

K

325

318

308

300

0

40 30 20 10 0036912

mft

5010

015

020

025

030

0F

EE

T

GR

OU

ND

PLA

NE

325

318

308

300

PLA

N1530

4560

7590

40 20 0069

mft

12 31030

0M

ET

ER

S

AIR

CR

AF

T

N_AC_060104_1_0240101_01_00

Engine Exhaust TemperaturesBreakaway Power - IAE V2500 Series Engine

FIGURE-6-1-4-991-024-A01

6-1-4Page 7

Nov 01/19


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

**ON A/C A321-100 A321-200 A321neo

Engine Exhaust Velocities Contours - Takeoff Power

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

6-1-5Page 1

Nov 01/19


**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

1 00

01

100

1 20

01

300

1 40

0

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

IRC

RA

FT

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

kts

)

m

42 36 30 24 18 12 6 0

140

120

100 80 60 40 200

450

1 50

0

ftm

42 36 30 24 18 12 6 0

140

120

100 80 60 40 200ft m

N_AC_060105_1_0070101_01_01

Engine Exhaust VelocitiesTakeoff Power -- CFM56-5B Series Engine

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

6-1-5Page 2

Nov 01/19


**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

Nov 01/19


**ON A/C A321neo

MA

X T

AK

EO

FF

, SE

A L

EV

EL,

ISA

+15

K, F

N =

32

517

lbf.

NO

TE

:

mft

0 0

00

5010

015

020

025

030

035

040

045

050

055

060

065

070

075

080

0

2040

1530

4560

7590

105

120

135

150

165

180

195

210

225

240

60

61218

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

PLA

NA

IRC

RA

FT

mft

00

204060

61218

50 (15)

100

(30)

150

(46)

VE

LOC

ITY

= ft

/s (

m/s

)

150

(46)

100

(30)

50 (15)

FE

ET

ME

TE

RS

N_AC_060105_1_0130101_01_00

Engine Exhaust VelocitiesTakeoff Power -- CFM LEAP-1A Engine

FIGURE-6-1-5-991-013-A01

6-1-5Page 4

Nov 01/19


**ON A/C A321neo

PLA

NA

IRC

RA

FT

mft

0 0

00

5010

015

020

025

030

035

040

045

050

055

060

065

070

075

080

0

2040

1530

4560

7590

105

120

135

150

165

180

195

210

225

240

60

61218

FE

ET

ME

TE

RS

50 (15)

100

(30)

150

(46)

VE

LOC

ITY

= ft

/s (

m/s

)

350

(107

)300

(91)

250

(76)

200

(61)

40 (12)

N_AC_060105_1_0140101_01_00

Engine Exhaust VelocitiesTakeoff Power -- PW 1100G Engine

FIGURE-6-1-5-991-014-A01

6-1-5Page 5

Nov 01/19


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

**ON A/C A321-100 A321-200 A321neo

Engine Exhaust Temperatures Contours - Takeoff Power

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

6-1-6Page 1

Nov 01/19


**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

kts

)

PLA

N425

370

315

425

370

315

AIR

CR

AF

T

1020

3040

50

ftm

60

0

40 20 0

18 12 6

ftm

60

0

40 20 0

18 12 6

TE

MP

ER

AT

UR

E =

K

00ft m

N_AC_060106_1_0070101_01_01

Engine Exhaust TemperaturesTakeoff Power -- CFM56-5B Series Engine

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

6-1-6Page 2

Nov 01/19


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

1530

4560

250

300

ELE

VA

TIO

N

5010

015

020

0

7590

PLA

N

00

6555

4535

25

ftm

15 10 5 0

60 40 20 0

ftm

15 10 5 0

60 40 20 0

2535

4555

65

TE

MP

ER

AT

UR

E =

° C

ft m

N_AC_060106_1_0080101_01_01

Engine Exhaust TemperaturesTakeoff Power -- IAE V2500 Series Engine

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

6-1-6Page 3

Nov 01/19


**ON A/C A321neo

333

323

313

323

313

MA

X T

AK

EO

FF

, SE

A L

EV

EL,

ISA

+15

K D

AY

, FN

= 3

2 51

7 lb

f.N

OT

E:

mft

00

0 0

5010

015

020

025

030

035

0

1530

4560

7590

105

10203040

36912

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

333

PLA

NA

IRC

RA

FT

mft

00

10203040

36912

TE

MP

ER

AT

UR

E =

K

FE

ET

ME

TE

RS

N_AC_060106_1_0130101_01_00

Engine Exhaust TemperaturesTakeoff Power - CFM LEAP-1A Engine

FIGURE-6-1-6-991-013-A01

6-1-6Page 4

Nov 01/19


**ON A/C A321neo

0 0

5010

015

020

025

030

035

0

1530

4560

7590

105

PLA

N

mft

00

10203040

36912

AIR

CR

AF

T

333

323

313

366

TE

MP

ER

AT

UR

E =

K

FE

ET

ME

TE

RS

N_AC_060106_1_0140101_01_00

Engine Exhaust TemperaturesTakeoff Power - PW 1100G Engine

FIGURE-6-1-6-991-014-A01

6-1-6Page 5

Nov 01/19


6-3-0 Danger Areas of Engines

**ON A/C A321-100 A321-200 A321neo

Danger Areas of Engines

1. Danger Areas of the Engines

A. The danger areas of the engines shown below are given in the normalized format:- Entry corridors are only available at ground idle.- Do not go into the areas between the engines.- The exhaust danger areas are given for 0 kt headwind (if not specified otherwise).

6-3-0Page 1

Nov 01/19


6-3-1 Ground Idle Power

**ON A/C A321-100 A321-200 A321neo

Ground Idle Power

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

6-3-1Page 1

Nov 01/19


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

INLET SUCTION DANGER AREA

ENTRY CORRIDOR

EXHAUST WAKE DANGER AREA

NOTE:

1 m(3.3 ft) R = 2.23 m

(7.3 ft)

30°

TO 55 m (180 ft) AFT OF COMMON NOZZLE ASSEMBLY (CNA)INCLUDES CROSS WIND EFFECT

N_AC_060301_1_0090101_01_04

Danger Areas of the EnginesCFM56-5B Series Engine

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

6-3-1Page 2

Nov 01/19


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

0.91 m(3 ft) R = 2.74 m

(9 ft)

INTAKE SUCTION DANGER AREA MINIMUM IDLE POWER

ENTRY CORRIDOR

EXHAUST DANGER AREA

NOTE:

30°


N_AC_060301_1_0100101_01_04

Danger Areas of the EnginesIAE V2500 Series Engine

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

6-3-1Page 3

Nov 01/19


**ON A/C A321neo

30°

R = 2.9 m(9.5 ft)


ENTRY CORRIDOR

EXHAUST DANGER AREA

NOTE:

1 m(3.3 ft)

TO 38.7 m (127 ft) AFT OF COMMON NOZZLE ASSEMBLY (CNA) INCLUDES CROSS WIND EFFECT

N_AC_060301_1_0150101_01_02

Danger Areas of the EnginesCFM LEAP-1A Engine

FIGURE-6-3-1-991-015-A01

6-3-1Page 4

Nov 01/19


**ON A/C A321neo

30°

TO 40.3 m (132 ft) AFT OF COMMON NOZZLE ASSEMBLY (CNA)


ENTRY CORRIDOR

EXHAUST DANGER AREA

NOTE:

1 m(3.3 ft)

R = 2.74 m(9 ft)

INCLUDES CROSS WIND EFFECT

N_AC_060301_1_0160101_01_02

Danger Areas of the EnginesPW 1100G Engine

FIGURE-6-3-1-991-016-A01

6-3-1Page 5

Nov 01/19


6-3-2 Breakaway Power

**ON A/C A321-100 A321-200 A321neo

Breakaway Power

1. This section provides danger areas of the engines at breakaway power.

6-3-2Page 1

Nov 01/19


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

30°TO 74.7 m (245 ft) AFT OF COMMON NOZZLE ASSEMBLY (CNA) INCLUDES CROSS WIND EFFECT

R = 5.2 m(17.1 ft)

1.6 m(5.2 ft)

INTAKE SUCTION DANGER AREA MAX. TAKEOFF POWER

EXHAUST WAKE DANGER AREA

NOTE:

N_AC_060302_1_0070101_01_03

Danger Areas of the EnginesCFM56-5B Series Engine

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

6-3-2Page 2

Nov 01/19


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

30°


EXHAUST DANGER AREA

1.2 m(3.9 ft)

NOTE:

R = 5 m(16.4 ft)

TO 91.4 m (300 ft) AFT OF COMMON NOZZLE ASSEMBLY (CNA)INCLUDES CROSS WIND EFFECT

N_AC_060302_1_0080101_01_03

Danger Areas of the EnginesIAE V2500 Series Engine

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

6-3-2Page 3

Nov 01/19


**ON A/C A321neo

30°


EXHAUST DANGER AREA

1.1 m(3.6 ft)

NOTE:

R = 3.8 m(12.5 ft)


N_AC_060302_1_0130101_01_02

Danger Areas of the EnginesCFM LEAP-1A Engine

FIGURE-6-3-2-991-013-A01

6-3-2Page 4

Nov 01/19


**ON A/C A321neo

30°


EXHAUST DANGER AREA

1.9 m(6.2 ft)

NOTE:

R = 3.7 m(12.1 ft)


N_AC_060302_1_0140101_01_02

Danger Areas of the EnginesPW 1100G Engine

FIGURE-6-3-2-991-014-A01

6-3-2Page 5

Nov 01/19


6-3-3 Max Take Off Power

**ON A/C A321-100 A321-200 A321neo

Take Off Power

1. This section provides danger areas of the engines at maximum take-off power conditions.

6-3-3Page 1

Nov 01/19


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

40°

R = 6.5 m(21.4 ft)

INTAKE SUCTION DANGER AREA

EXHAUST WAKE DANGER

NOTE:

1.3 m(4.3 ft)

TO 275 m (900 ft) AFT OF COMMON NOZZLE ASSEMBLY (CNA) INCLUDES CROSS WIND EFFECT

N_AC_060303_1_0110101_01_01

Danger Areas of the EngineCFM56-5B Series Engine

FIGURE-6-3-3-991-011-A01

6-3-3Page 2

Nov 01/19


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


EXHAUST DANGER AREA

NOTE:

30°

R = 5.18 m(17 ft)

1.7 m(5.5 ft)


N_AC_060303_1_0120101_01_01

Danger Areas of the EngineIAE V2500 Series Engine

FIGURE-6-3-3-991-012-A01

6-3-3Page 3

Nov 01/19


**ON A/C A321neo

R = 10 m(32.8 ft)


EXHAUST DANGER AREA

NOTE:

1.6 m(5.2 ft)

30°


N_AC_060303_1_0130101_01_01

Danger Areas of the EngineCFM LEAP-1A Engine

FIGURE-6-3-3-991-013-A01

6-3-3Page 4

Nov 01/19


**ON A/C A321neo

30°

TO 243 m (797.4 ft) AFT OF COMMON NOZZLE ASSEMBLY (CNA) INCLUDES CROSS WIND EFFECT

R = 6.1 m(20 ft)


EXHAUST DANGER AREA

NOTE:

3.1 m(10 ft)

N_AC_060303_1_0140101_01_01

Danger Areas of the EnginePW 1100G Engine

FIGURE-6-3-3-991-014-A01

6-3-3Page 5

Nov 01/19


6-4-1 APU

**ON A/C A321-100 A321-200 A321neo

APU - APIC & GARRETT

1. This section gives APU exhaust velocities and temperatures.

6-4-1Page 1

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


PAVEMENT DATA


**ON A/C A321-100 A321-200 A321neo

General Information

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

To aid in the interpolation between the discrete values shown, each aircraft configuration is shownwith a minimum range of five loads on the Main Landing Gear (MLG).

All curves on the charts represent data at a constant specified tire pressure with:- The aircraft loaded to the Maximum Ramp Weight (MRW),- The CG at its maximum permissible aft position.

Pavement requirements for commercial aircraft are derived from the static analysis of loads imposedon the MLG struts.

Landing Gear Footprint:Section 07-02-00 presents basic data on the landing gear footprint configuration, MRW and tire sizesand pressures.

Maximum Pavement Loads:Section 07-03-00 shows maximum vertical and horizontal pavement loads for certain criticalconditions at the tire-ground interfaces.

Landing Gear Loading on Pavement:Section 07-04-00 contains charts to find these loads throughout the stability limits of the aircraft atrest on the pavement.These MLG loads are used as the point of entry to the pavement design charts which follow,interpolating load values where necessary.

Flexible Pavement Requirements - US Army Corps of Engineers Design Method:Section 07-05-00 uses procedures in Instruction Report No. S-77-1 ”Procedures for Development ofCBR Design Curves”, dated June 1977 and as modified according to the methods described in ICAOAerodrome Design Manual, Part 3. Pavements, 2nd Edition, 1983, Section 1.1 (The ACN-PCNMethod), and utilizing the alpha factors approved by ICAO in October 2007.The report was prepared by the ”U.S. Army Corps Engineers Waterways Experiment Station, Soilsand Pavement Laboratory, Vicksburg, Mississippi”.The line showing 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).

Flexible Pavement Requirements - LCN Conversion Method:

7-1-0Page 1

Nov 01/19


The Load Classification Number (LCN) curves are no longer provided in section 07-06-00 since theLCN system for reporting pavement strength is obsolete, having been replaced by the ICAOrecommended ACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

Rigid Pavement Requirements - PCA (Portland Cement Association) Design Method:Section 07-07-00 gives the rigid pavement design curves that have been prepared with the use of theWestergaard Equation.This is in general accordance with the procedures outlined in the Portland Cement Associationpublications, ”Design of Concrete Airport Pavement”, 1973 and ”Computer Program for AirportPavement Design” (Program PDILB), 1967 both by Robert G. Packard.

Rigid Pavement Requirements - LCN Conversion:The Load Classification Number (LCN) curves are no longer provided in section 07-08-00 since theLCN system for reporting pavement strength is obsolete, having been replaced by the ICAOrecommended ACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

ACN/PCN Reporting System:Section 07-09-00 provides ACN data prepared according to the ACN/PCN system as referenced inICAO Annex 14, ”Aerodromes”, Volume 1 ”Aerodrome Design and Operations” Fourth Edition, July2004, incorporating Amendments 1 to 6.The ACN/PCN system provides a standardized international aircraft/pavement rating systemreplacing the various S, T, TT, LCN, AUW, ISWL, etc., rating systems used throughout the world.ACN is the Aircraft Classification Number and PCN is the corresponding Pavement ClassificationNumber.An aircraft having an ACN less than or equal to the PCN can operate without restriction on thepavement.Numerically the ACN is two times the derived single wheel load expressed in thousands of kilograms.The derived single wheel load is defined as the load on a single tire inflated to 1.25 MPa (181 psi)that would have the same pavement requirements as the aircraft.Computationally the ACN/PCN system uses PCA program PDILB for rigid pavements and S-77-1 forflexible pavements to calculate ACN values.

The Airport Authority must decide on the method of pavement analysis and the results of theirevaluation shown as follows:

PCNPAVEMENT

TYPESUBGRADECATEGORY

TIRE PRESSURE CATEGORYEVALUATION

METHODR -- Rigid A -- High W -- No pressure limit T -- Technical

F -- Flexible B -- MediumX -- High pressure limited to 1.75MPa (254 psi)

U -- Using Aircraft

7-1-0Page 2

Nov 01/19


PCNPAVEMENT

TYPESUBGRADECATEGORY

TIRE PRESSURE CATEGORYEVALUATION

METHOD

C -- LowY -- Medium pressure limited to 1.25MPa (181 psi)

D -- Ultra LowZ -- Low pressure limited to 0.5 MPa(73 psi)

For flexible pavements, the four subgrade categories (CBR) are:

- A. High Strength CBR 15

- B. Medium Strength CBR 10

- C. Low Strength CBR 6

- D. Ultra Low Strength CBR 3

For rigid pavements, the four subgrade categories (k) are:

- A. High Strength k = 150 MN/m3 (550 pci)

- B. Medium Strength k = 80 MN/m3 (300 pci)

- C. Low Strength k = 40 MN/m3 (150 pci)

- D. Ultra Low Strength k = 20 MN/m3 (75 pci)

7-1-0Page 3

Nov 01/19


7-2-0 Landing Gear Footprint

**ON A/C A321-100 A321-200 A321neo

Landing Gear Footprint

1. This section provides data about the landing gear footprint in relation to the aircraft MRW and tiresizes and pressures.The landing-gear footprint information is given for all the operational weight variants of the aircraft.

7-2-0Page 1

Nov 01/19


**ON A/C A321-100

WEIGHTVARIANT

MAXIMUMRAMP

WEIGHT

PERCENTAGEOF WEIGHT

ON MAINGEAR GROUP

NOSE GEAR TIRESIZE

NOSE GEARTIRE

PRESSUREMAIN GEAR TIRE

SIZEMAIN GEAR

TIREPRESSURE

A321−100WV000

83 400 kg(183 875 lb) 95.7%

10.8 bar(157 psi)

1 270x455R22(49x18−22)

13.6 bar(197 psi)

30x8.8R15(30x8.8−15)

A321−100WV002

83 400 kg(183 875 lb) 95.7%

10.8 bar(157 psi)

13.6 bar(197 psi)

A321−100WV003

85 400 kg(188 275 lb) 95.7%

11 bar(160 psi)

13.9 bar(202 psi)

A321−100WV004

78 400 kg(172 850 lb) 95.7%

10.1 bar(146 psi)

12.8 bar(186 psi)

A321−100WV005

83 400 kg(183 875 lb) 95.7%

10.8 bar(157 psi)

13.6 bar(197 psi)

A321−100WV006

78 400 kg(172 850 lb) 95.7%

10.1 bar(146 psi)

12.8 bar(186 psi)

A321−100WV007

80 400 kg(177 250 lb) 95.7%

10.8 bar(157 psi)

13.6 bar(197 psi)

A321−100WV008

89 400 kg(197 100 lb) 94.9%

11.6 bar(168 psi)

14.6 bar(212 psi)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

0.927 m(3.041 ft)

0.500 m(1.640 ft)

16.906 m(55.465 ft)

7.590 m(24.901 ft)

N_AC_070200_1_0280101_01_01

Landing Gear FootprintFIGURE-7-2-0-991-028-A01

7-2-0Page 2

Nov 01/19


**ON A/C A321-200

WEIGHTVARIANT

MAXIMUMRAMP

WEIGHT

PERCENTAGEOF WEIGHT

ON MAINGEAR GROUP

NOSE GEAR TIRESIZE

NOSE GEARTIRE

PRESSUREMAIN GEAR TIRE

SIZEMAIN GEAR

TIREPRESSURE

A321−200WV000

89 400 kg(197 100 lb) 95.5%

11.6 bar(168 psi)

1 270x455R22(49x18−22)

14.6 bar(212 psi)

30x8.8R15(30x8.8−15)

A321−200WV001

93 400 kg(205 900 lb) 95.3%

11.6 bar(168 psi)

15 bar(218 psi)

A321−200WV002

89 400 kg(197 100 lb) 95.5%

11.6 bar(168 psi)

14.6 bar(212 psi)

A321−200WV003

91 400 kg(201 500 lb) 95.4%

11.6 bar(168 psi)

15 bar(218 psi)

A321−200WV004

87 400 kg(192 675 lb) 95.7%

11.6 bar(168 psi)

14.6 bar(212 psi)

A321−200WV005

85 400 kg(188 275 lb) 95.2%

11 bar(160 psi)

13.9 bar(202 psi)

A321−200WV006

83 400 kg(183 875 lb) 95.4%

10.8 bar(157 psi)

13.6 bar(197 psi)

A321−200WV007

83 400 kg(183 875 lb) 95.4%

10.8 bar(157 psi)

13.6 bar(197 psi)

A321−200WV008

80 400 kg(177 250 lb) 95.6%

10.8 bar(157 psi)

13.6 bar(197 psi)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

A321−200WV009

78 400 kg(172 850 lb) 95.5%

10.1 bar(146 psi)

12.8 bar(186 psi)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

0.927 m(3.041 ft)

0.500 m(1.640 ft)

16.906 m(55.465 ft)

7.590 m(24.901 ft)

A321−200WV010

85 400 kg(188 275 lb) 95.2%

11 bar(160 psi)

13.9 bar(202 psi)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

A321−200WV011

93 900 kg(207 025 lb) 95.2%

11.6 bar(168 psi)

15 bar(218 psi)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

(CG 40.51%)

A321−200WV008

80 400 kg(177 250 lb) 95.4%

10.8 bar(157 psi)

13.6 bar(197 psi)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

(CG 39.71%)

(CG 40.08%)

A321−200WV009

78 400 kg(172 850 lb) 95.2%

10.1 bar(146 psi)

12.8 bar(186 psi)

1 270x455R22(49x18−22)

30x8.8R15(30x8.8−15)

(CG 39.21%)

N_AC_070200_1_0350101_01_02

Landing Gear FootprintFIGURE-7-2-0-991-035-A01

7-2-0Page 3

Nov 01/19


**ON A/C A321neo

0.927 m(3.041 ft)

0.500 m(1.640 ft)

7.590 m(24.901 ft)

16.906 m(55.465 ft)

WEIGHTVARIANT

MAXIMUMRAMP

WEIGHT

PERCENTAGEOF WEIGHT

ON MAINGEAR GROUP

NOSE GEAR TIRESIZE

NOSE GEARTIRE

PRESSUREWING GEAR TIRE

SIZEWING GEAR

TIREPRESSURE

A321NEOWV050 (CG 38.02%)

89 400 kg(197 100 lb) 95.5%

11.6 bar(168 psi)

1 270x455R22(49x18−22)

14.6 bar(212 psi)

30x8.8R15(30x8.8−15)

A321NEOWV050 (CG 37%)

89 400 kg(197 100 lb) 95.3%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

A321NEOWV051 (CG 38.02%)

89 400 kg(197 100 lb) 95.5%

11.6 bar(168 psi)

1 270x455R22(49x18−22)

14.6 bar(212 psi)

30x8.8R15(30x8.8−15)

A321NEOWV051 (CG 37%)

89 400 kg(197 100 lb) 95.3%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

14.6 bar(212 psi)

14.6 bar(212 psi)

A321NEOWV052

93 900 kg(207 025 lb) 95.2%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

15 bar(218 psi)

A321NEOWV053

93 900 kg(207 025 lb) 95.2%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

15 bar(218 psi)

A321NEOWV056 (CG 37.12%)

92 900 kg(204 800 lb) 95.3%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

15 bar(218 psi)

A321NEOWV056 (CG 37%)

92 900 kg(204 800 lb) 95.3%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

15 bar(218 psi)

A321NEOWV063 (CG 37.5%)

91 400 kg(201 500 lb) 95.3%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

15 bar(218 psi)

A321NEOWV063 (CG 37%)

91 400 kg(201 500 lb) 95.3%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

15 bar(218 psi)

A321NEOWV065 (CG 37.62%)

90 900 kg(200 400 lb) 95.4%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

15 bar(218 psi)

N_AC_070200_1_0380101_01_04

Landing Gear Footprint(Sheet 1 of 2)

FIGURE-7-2-0-991-038-A01

7-2-0Page 4

Nov 01/19


**ON A/C A321neo

WEIGHTVARIANT

MAXIMUMRAMP

WEIGHT

PERCENTAGEOF WEIGHT

ON MAINGEAR GROUP

NOSE GEAR TIRESIZE

NOSE GEARTIRE

PRESSUREWING GEAR TIRE

SIZEWING GEAR

TIREPRESSURE

A321NEOWV065 (CG 37%)

90 900 kg(200 400 lb) 95.3%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

15 bar(218 psi)

A321NEOWV070 (CG 38.71%)

80 400 kg(177 250 lb) 95.1%

30x8.8R15(30x8.8−15)

10.8 bar(157 psi)

1 270x455R22(49x18−22)

13.6 bar(197 psi)

A321NEOWV070 (CG 37%)

80 400 kg(177 250 lb) 94.7%

30x8.8R15(30x8.8−15)

10.8 bar(157 psi)

1 270x455R22(49x18−22)

13.6 bar(197 psi)

A321NEOWV071

97 400 kg(214 725 lb) 95.0%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

15.7 bar(228 psi)

A321NEOWV072

97 400 kg(214 725 lb) 95.0%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

15.7 bar(228 psi)

A321NEOWV080

95 400 kg(210 325 lb) 95.2%

30x8.8R15(30x8.8−15)

11.6 bar(168 psi)

1 270x455R22(49x18−22)

15.7 bar(228 psi)

N_AC_070200_1_0380105_01_00

Landing Gear Footprint(Sheet 2 of 2)

FIGURE-7-2-0-991-038-A01

7-2-0Page 5

Nov 01/19


7-3-0 Maximum Pavement Loads

**ON A/C A321-100 A321-200 A321neo

Maximum Pavement Loads

1. This section provides maximum vertical and horizontal pavement loads for some critical conditions atthe tire-ground interfaces.The maximum pavement loads are given for all the operational weight variants of the aircraft.

7-3-0Page 1

Nov 01/19


**ON A/C A321-100

V(M

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T F

WD

CG

V(N

G)

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

AF

T C

GH

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

1

WE

IGH

TV

AR

IAN

T

MA

XIM

UM

RA

MP

WE

IGH

T

2

A32

1−10

0W

V00

083

400

kg

(183

875

lb)

FW

D C

GS

TA

TIC

LO

AD

AT

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

AT

IC B

RA

KIN

G

34

V(N

G)

17.5

%M

AC

(a)

AF

T C

GS

TA

TIC

LO

AD

AT

5(P

ER

ST

RU

T)

V(M

G)

41 %

MA

C (

a)

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

EA

DY

BR

AK

ING

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

AT

INS

TA

NT

AN

EO

US

6H

(P

ER

ST

RU

T)

8 57

0 kg

(18

900

lb)

13 7

30 k

g(3

0 27

5 lb

)39

910

kg

(87

975

lb)

12 9

60 k

g(2

8 57

5 lb

)31

920

kg

(70

375

lb)

83 4

00 k

g(1

83 8

75 lb

)41

%M

AC

(a)

8 57

0 kg

(18

900

lb)

13 7

30 k

g(3

0 27

5 lb

)39

910

kg

(87

975

lb)

12 9

60 k

g(2

8 57

5 lb

)31

920

kg

(70

375

lb)

85 4

00 k

g(1

88 2

75 lb

)41

%M

AC

(a)

8 60

0 kg

(18

950

lb)

13 8

80 k

g(3

0 60

0 lb

)40

860

kg

(90

100

lb)

13 2

70 k

g(2

9 25

0 lb

)32

690

kg

(72

075

lb)

78 4

00 k

g(1

72 8

50 lb

)41

%M

AC

(a)

8 48

0 kg

(18

675

lb)

13 3

40 k

g(2

9 42

5 lb

)37

510

kg

(82

700

lb)

12 1

80 k

g(2

6 85

0 lb

)30

010

kg

(66

150

lb)

83 4

00 k

g(1

83 8

75 lb

)41

%M

AC

(a)

8 57

0 kg

(18

900

lb)

13 7

30 k

g(3

0 27

5 lb

)39

910

kg

(87

975

lb)

12 9

60 k

g(2

8 57

5 lb

)31

920

kg

(70

375

lb)

78 4

00 k

g(1

72 8

50 lb

)41

%M

AC

(a)

8 48

0 kg

(18

675

lb)

13 3

40 k

g(2

9 42

5 lb

)37

510

kg

(82

700

lb)

12 1

80 k

g(2

6 85

0 lb

)30

010

kg

(66

150

lb)

80 4

00 k

g(1

77 2

50 lb

)41

%M

AC

(a)

8 51

0 kg

(18

750

lb)

13 4

90 k

g(2

9 75

0 lb

)38

470

kg

(84

800

lb)

12 4

90 k

g(2

7 55

0 lb

)30

770

kg

(67

850

lb)

89 4

00 k

g(1

97 1

00 lb

)38

%M

AC

(a)

9 18

0 kg

(20

225

lb)

14 6

90 k

g(3

2 37

5 lb

)42

430

kg

(93

550

lb)

13 8

90 k

g(3

0 62

5 lb

)33

950

kg

(74

825

lb)

A32

1−10

0W

V00

2

A32

1−10

0W

V00

3

A32

1−10

0W

V00

4

A32

1−10

0W

V00

5

A32

1−10

0W

V00

6

A32

1−10

0W

V00

7

A32

1−10

0W

V00

8

17.5

%M

AC

(a)

18.3

%M

AC

(a)

15.4

%M

AC

(a)

17.5

%M

AC

(a)

15.4

%M

AC

(a)

16.3

%M

AC

(a)

17.5

%M

AC

(a)

NO

TE

:(a

) LO

AD

S C

ALC

ULA

TE

D U

SIN

G A

IRC

RA

FT

AT

MR

W.

V(N

G)

V(M

G)

H

N_AC_070300_1_0330101_01_02

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

7-3-0Page 2

Nov 01/19


**ON A/C A321-200

V(N

G)

V(M

G)

H

V(M

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T F

WD

CG

V(N

G)

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

AF

T C

GH

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

1

WE

IGH

TV

AR

IAN

T

MA

XIM

UM

RA

MP

WE

IGH

T

2

A32

1−20

0W

V00

089

400

kg

(197

100

lb)

FW

D C

GS

TA

TIC

LO

AD

AT

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

AT

IC B

RA

KIN

G

34

V(N

G)

17.5

%M

AC

(a)

AF

T C

GS

TA

TIC

LO

AD

AT

5(P

ER

ST

RU

T)

V(M

G)

38 %

MA

C (

a)

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

EA

DY

BR

AK

ING

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

AT

INS

TA

NT

AN

EO

US

6H

(P

ER

ST

RU

T)

8 68

0 kg

(19

150

lb)

14 1

90 k

g(3

1 27

5 lb

)42

700

kg

(94

150

lb)

13 8

90 k

g(3

0 62

5 lb

)34

160

kg

(75

325

lb)

93 4

00 k

g(2

05 9

00 lb

)37

%M

AC

(a)

8 64

0 kg

(19

050

lb)

14 1

10 k

g(3

1 10

0 lb

)44

490

kg

(98

100

lb)

14 5

10 k

g(3

2 00

0 lb

)35

590

kg

(78

475

lb)

89 4

00 k

g(1

97 1

00 lb

)38

%M

AC

(a)

8 68

0 kg

(19

150

lb)

14 1

90 k

g(3

1 27

5 lb

)42

700

kg

(94

150

lb)

13 8

90 k

g(3

0 62

5 lb

)34

160

kg

(75

325

lb)

91 4

00 k

g(2

01 5

00 lb

)37

.49

%M

AC

(a)

8 64

0 kg

(19

050

lb)

14 1

20 k

g(3

1 12

5 lb

)43

600

kg

(96

125

lb)

14 2

00 k

g(3

1 32

5 lb

)34

880

kg

(76

900

lb)

87 4

00 k

g(1

92 6

75 lb

)38

.53

%M

AC

(a)

8 49

0 kg

(18

725

lb)

13 8

80 k

g(3

0 60

0 lb

)41

810

kg

(92

175

lb)

13 5

80 k

g(2

9 95

0 lb

)33

440

kg

(73

725

lb)

A32

1−20

0W

V00

1

A32

1−20

0W

V00

2

A32

1−20

0W

V00

3

A32

1−20

0W

V00

4

17.5

%M

AC

(b)

17.5

%M

AC

(a)

17.5

%M

AC

(b)

17.5

%M

AC

(a)

NO

TE

:(a

) LO

AD

S C

ALC

ULA

TE

D U

SIN

G A

IRC

RA

FT

AT

MR

W.

(b)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T 8

9 00

0 kg

(19

6 20

0 lb

).

N_AC_070300_1_0440101_01_01

Maximum Pavement Loads(Sheet 1 of 2)

FIGURE-7-3-0-991-044-A01

7-3-0Page 3

Nov 01/19


**ON A/C A321-200

1

WE

IGH

TV

AR

IAN

T

A32

1−20

0W

V00

5

A32

1−20

0W

V00

6

A32

1−20

0W

V00

7

A32

1−20

0W

V00

8

A32

1−20

0W

V01

0

A32

1−20

0W

V01

1

(CG

40.

51 %

)

MA

XIM

UM

RA

MP

WE

IGH

T

2

FW

D C

GS

TA

TIC

LO

AD

AT

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

AT

IC B

RA

KIN

G

34

V(N

G)

AF

T C

GS

TA

TIC

LO

AD

AT

5(P

ER

ST

RU

T)

V(M

G)

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

EA

DY

BR

AK

ING

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

AT

INS

TA

NT

AN

EO

US

6H

(P

ER

ST

RU

T)

85 4

00 k

g(1

88 2

75 lb

)39

.1 %

MA

C (

a)8

760

kg(1

9 32

5 lb

)14

030

kg

(30

925

lb)

40 6

60 k

g(8

9 62

5 lb

)13

270

kg

(29

250

lb)

32 5

30 k

g(7

1 70

0 lb

)

83 4

00 k

g(1

83 8

75 lb

)39

.7 %

MA

C (

a)8

560

kg(1

8 87

5 lb

)13

710

kg

(30

225

lb)

39 7

70 k

g(8

7 67

5 lb

)12

960

kg

(28

575

lb)

31 8

20 k

g(7

0 15

0 lb

)

83 4

00 k

g(1

83 8

75 lb

)39

.7 %

MA

C (

a)8

560

kg(1

8 87

5 lb

)13

710

kg

(30

225

lb)

39 7

70 k

g(8

7 67

5 lb

)12

960

kg

(28

575

lb)

31 8

20 k

g(7

0 15

0 lb

)

17.5

%M

AC

(a)

17.5

%M

AC

(a)

17.5

%M

AC

(a)

80 4

00 k

g(1

77 2

50 lb

)40

.51

%M

AC

(a)

8 51

0 kg

(18

750

lb)

13 4

80 k

g(2

9 72

5 lb

)38

420

kg

(84

700

lb)

12 4

90 k

g(2

7 55

0 lb

)30

740

kg

(67

750

lb)

16.2

8 %

MA

C (

a)

80 4

00 k

g(1

77 2

50 lb

)39

.71

%M

AC

(a)

8 51

0 kg

(18

750

lb)

13 4

80 k

g(2

9 72

5 lb

)38

340

kg

(84

525

lb)

12 4

90 k

g(2

7 55

0 lb

)30

670

kg

(67

625

lb)

16.2

8 %

MA

C (

a)

78 4

00 k

g(1

72 8

50 lb

)40

.08

%M

AC

(a)

8 47

0 kg

(18

675

lb)

13 3

30 k

g(2

9 37

5 lb

)37

420

kg

(82

500

lb)

12 1

80 k

g(2

6 85

0 lb

)29

940

kg

(66

000

lb)

15.4

1 %

MA

C (

a)

78 4

00 k

g(1

72 8

50 lb

)39

.21

%M

AC

(a)

8 47

0 kg

(18

675

lb)

13 3

30 k

g(2

9 37

5 lb

)37

330

kg

(82

300

lb)

12 1

80 k

g(2

6 85

0 lb

)29

870

kg

(65

850

lb)

15.4

1 %

MA

C (

a)

NO

TE

:(a

) LO

AD

S C

ALC

ULA

TE

D U

SIN

G A

IRC

RA

FT

AT

MR

W.

(b)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T 8

9 00

0 kg

(19

6 20

0 lb

).

85 4

00 k

g(1

88 2

75 lb

)39

.1 %

MA

C (

a)8

760

kg(1

9 32

5 lb

)14

030

kg

(30

925

lb)

40 6

60 k

g(8

9 62

5 lb

)13

270

kg

(29

250

lb)

32 5

30 k

g(7

1 70

0 lb

)17

.5 %

MA

C (

a)

93 9

00 k

g(2

07 0

25 lb

)36

.88

%M

AC

(a)

8 64

0 kg

(19

050

lb)

14 1

10 k

g(3

1 12

5 lb

)44

720

kg

(98

575

lb)

14 5

90 k

g(3

2 17

5 lb

)35

770

kg

(78

875

lb)

17.5

%M

AC

(b)

A32

1−20

0W

V00

8(C

G 3

9.71

%)

A32

1−20

0W

V00

9(C

G 4

0.08

%)

A32

1−20

0W

V00

9(C

G 3

9.21

%)

N_AC_070300_1_0440102_01_03


FIGURE-7-3-0-991-044-A01

7-3-0Page 4

Nov 01/19


**ON A/C A321neo

NO

TE

:(a

) LO

AD

S C

ALC

ULA

TE

D U

SIN

G A

IRC

RA

FT

AT

MR

W.

(b)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T 8

9 00

0 kg

(19

6 20

0 lb

).

V(M

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T F

WD

CG

V(N

G)

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

AF

T C

GH

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

V(N

G)

V(M

G)

H

1

WE

IGH

TV

AR

IAN

T

MA

XIM

UM

RA

MP

WE

IGH

T

2

FW

D C

GS

TA

TIC

LO

AD

AT

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

AT

IC B

RA

KIN

G

34

V(N

G)

AF

T C

GS

TA

TIC

LO

AD

AT

5(P

ER

ST

RU

T)

V(M

G)

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

EA

DY

BR

AK

ING

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

AT

INS

TA

NT

AN

EO

US

6H

(P

ER

ST

RU

T)

89 4

00 k

g(1

97 1

00 lb

)38

.02

%M

AC

(a)

8 68

0 kg

(19

125

lb)

14 1

90 k

g(3

1 27

5 lb

)42

700

kg

(94

125

lb)

13 8

90 k

g(3

0 62

5 lb

)34

160

kg

(75

300

lb)

A32

1NE

OW

V05

0(C

G 3

8.02

%)

17.5

%M

AC

(a)

89 4

00 k

g(1

97 1

00 lb

)37

%M

AC

(a)

8 68

0 kg

(19

125

lb)

14 1

90 k

g(3

1 27

5 lb

)42

580

kg

(93

875

lb)

13 8

90 k

g(3

0 62

5 lb

)34

070

kg

(75

100

lb)

A32

1NE

OW

V05

0(C

G 3

7 %

)17

.5 %

MA

C (

a)

89 4

00 k

g(1

97 1

00 lb

)38

.02

%M

AC

(a)

8 68

0 kg

(19

125

lb)

14 1

90 k

g(3

1 27

5 lb

)42

700

kg

(94

125

lb)

13 8

90 k

g(3

0 62

5 lb

)34

160

kg

(75

300

lb)

A32

1NE

OW

V05

1(C

G 3

8.02

%)

17.5

%M

AC

(a)

89 4

00 k

g(1

97 1

00 lb

)37

%M

AC

(a)

8 68

0 kg

(19

125

lb)

14 1

90 k

g(3

1 27

5 lb

)42

580

kg

(93

875

lb)

13 8

90 k

g(3

0 62

5 lb

)34

070

kg

(75

100

lb)

A32

1NE

OW

V05

1(C

G 3

7 %

)17

.5 %

MA

C (

a)

93 9

00 k

g(2

07 0

25 lb

)36

.88

%M

AC

(a)

8 64

0 kg

(19

050

lb)

14 1

90 k

g(3

1 27

5 lb

)44

720

kg

(98

600

lb)

14 5

90 k

g(3

2 17

5 lb

)35

770

kg

(78

850

lb)

A32

1NE

OW

V05

217

.5 %

MA

C (

b)

93 9

00 k

g(2

07 0

25 lb

)36

.88

%M

AC

(a)

8 64

0 kg

(19

050

lb)

14 1

10 k

g(3

1 10

0 lb

)44

720

kg

(98

600

lb)

14 5

90 k

g(3

2 17

5 lb

)35

770

kg

(78

850

lb)

A32

1NE

OW

V05

317

.5 %

MA

C (

b)

A32

1NE

OW

V05

6(C

G 3

7.12

%)

92 9

00 k

g(2

04 8

00 lb

)37

.12

%M

AC

(a)

8 64

0 kg

(19

050

lb)

14 1

10 k

g(3

1 10

0 lb

)44

270

kg

(97

600

lb)

14 4

40 k

g(3

1 82

5 lb

)35

420

kg

(78

100

lb)

17.5

%M

AC

(b)

A32

1NE

OW

V05

6(C

G 3

7 %

)

92 9

00 k

g(2

04 8

00 lb

)37

%M

AC

(a)

8 64

0 kg

(19

050

lb)

14 1

10 k

g(3

1 10

0 lb

)44

250

kg

(97

550

lb)

14 4

40 k

g(3

1 82

5 lb

)35

400

kg

(78

050

lb)

17.5

%M

AC

(b)

A32

1NE

OW

V06

3(C

G 3

7.5

%)

91 4

00 k

g(2

01 5

00 lb

)37

.5 %

MA

C (

a)8

640

kg(1

9 05

0 lb

)14

110

kg

(31

100

lb)

43 6

00 k

g(9

6 12

5 lb

)14

200

kg

(31

300

lb)

34 8

80 k

g(7

6 90

0 lb

)17

.5 %

MA

C (

b)

N_AC_070300_1_0450101_01_05


FIGURE-7-3-0-991-045-A01

7-3-0Page 5

Nov 01/19


**ON A/C A321neo

A32

1NE

OW

V06

3(C

G 3

7 %

)

91 4

00 k

g(2

01 5

00 lb

)37

%M

AC

(a)

8 64

0 kg

(19

050

lb)

14 1

10 k

g(3

1 10

0 lb

)43

540

kg

(96

000

lb)

14 2

00 k

g(3

1 30

0 lb

)34

830

kg

(76

775

lb)

17.5

%M

AC

(b)

A32

1NE

OW

V06

5(C

G 3

7.62

%)

90 9

00 k

g(2

00 4

00 lb

)37

.62

%M

AC

(a)

8 64

0 kg

(19

050

lb)

14 1

20 k

g(3

1 12

5 lb

)43

370

kg

(95

625

lb)

14 1

30 k

g(3

1 15

0 lb

)34

700

kg

(76

500

lb)

17.5

%M

AC

(b)

A32

1NE

OW

V06

5(C

G 3

7 %

)

90 9

00 k

g(2

00 4

00 lb

)37

%M

AC

(a)

8 64

0 kg

(19

050

lb)

14 1

20 k

g(3

1 12

5 lb

)43

300

kg

(95

450

lb)

14 1

30 k

g(3

1 15

0 lb

)34

640

kg

(76

375

lb)

17.5

%M

AC

(b)

A32

1NE

OW

V07

0(C

G 3

8.71

%)

80 4

00 k

g(1

77 2

50 lb

)38

.71

%M

AC

(a)

8 51

0 kg

(18

750

lb)

13 4

80 k

g(2

9 72

5 lb

)38

230

kg

(84

275

lb)

12 4

90 k

g(2

7 52

5 lb

)30

590

kg

(67

450

lb)

16.2

8 %

MA

C (

a)

A32

1NE

OW

V07

0(C

G 3

7 %

)

80 4

00 k

g(1

77 2

50 lb

)37

%M

AC

(a)

8 51

0 kg

(18

750

lb)

13 4

80 k

g(2

9 72

5 lb

)38

060

kg

(83

900

lb)

12 4

90 k

g(2

7 52

5 lb

)30

450

kg

(67

125

lb)

16.2

8 %

MA

C (

a)

A32

1NE

OW

V07

197

400

kg

(214

725

lb)

36.0

7 %

MA

C (

a)8

640

kg(1

9 05

0 lb

)14

100

kg

(31

075

lb)

46 2

80 k

g(1

02 0

25 lb

)15

140

kg

(33

375

lb)

37 0

30 k

g(8

1 62

5 lb

)17

.5 %

MA

C (

b)

A32

1NE

OW

V07

297

400

kg

(214

725

lb)

36.0

7 %

MA

C (

a)8

640

kg(1

9 05

0 lb

)14

100

kg

(31

075

lb)

46 2

80 k

g(1

02 0

25 lb

)15

140

kg

(33

375

lb)

37 0

30 k

g(8

1 62

5 lb

)17

.5 %

MA

C (

b)

A32

1NE

OW

V08

095

400

kg

(210

325

lb)

36.5

3 %

MA

C (

a)8

640

kg(1

9 05

0 lb

)14

110

kg

(31

100

lb)

45 3

90 k

g(1

00 0

75 lb

)14

830

kg

(32

700

lb)

36 3

10 k

g(8

0 05

0 lb

)17

.5 %

MA

C (

b)

1

WE

IGH

TV

AR

IAN

T

MA

XIM

UM

RA

MP

WE

IGH

T

2

FW

D C

GS

TA

TIC

LO

AD

AT

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

AT

IC B

RA

KIN

G

34

V(N

G)

AF

T C

GS

TA

TIC

LO

AD

AT

5(P

ER

ST

RU

T)

V(M

G)

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

EA

DY

BR

AK

ING

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

AT

INS

TA

NT

AN

EO

US

6H

(P

ER

ST

RU

T)

NO

TE

:(a

) LO

AD

S C

ALC

ULA

TE

D U

SIN

G A

IRC

RA

FT

AT

MR

W.

(b)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T 8

9 00

0 kg

(19

6 20

0 lb

).

N_AC_070300_1_0450102_01_00


FIGURE-7-3-0-991-045-A01

7-3-0Page 6

Nov 01/19


7-4-0 Landing Gear Loading on Pavement

**ON A/C A321-100 A321-200 A321neo

Landing Gear Loading on Pavement

1. Landing Gear Loading on Pavement

This section provides data about the landing gear loading on pavement.The MLG loading on pavement graphs are given for the weight variants that produce (at the MRWand maximum aft CG) the lowest MLG load and the highest MLG load for each type of aircraft.Example, see FIGURE 7-4-0-991-014-A, calculation of the total weight on the MLG for:- An aircraft with a MRW of 78 400 kg (172 850 lb),- The aircraft gross weight is 60 000 kg (132 275 lb),- A percentage of weight on the MLG of 95.7% (percentage of weight on the MLG at MRW and

maximum aft CG).The total weight on the MLG group is 57 410 kg (126 575 lb).

NOTE : The CG in the figure title is the CG used for ACN/LCN calculation.

7-4-0Page 1

Nov 01/19


**ON A/C A321-100

86 88 100

PERCENTAGE OF WEIGHT ON MAIN GEAR

90 92 94 96 9835

80W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R (

x 1

000

kg)

35

80

(x 1

000

kg)

130

120

110

100

90

80

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T140

150

40

45

50

55

60

65

70

75

160

40

45

50

55

60

70

75

65

170

15.4% MAC

MTOW − 78 000 kg

TAKE OFF

MZFW

MLW

LANDING

CG FOR ACNCALCULATION

41% MAC

N_AC_070400_1_0140101_01_00

Landing Gear Loading on PavementWV004, MRW 78 400 kg, CG 41%

FIGURE-7-4-0-991-014-A01

7-4-0Page 2

Nov 01/19


**ON A/C A321-100

86 88 100


90 92 94 96 9835

90W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R (

x 1

000

kg)

35

90

(x 1

000

kg)

130

120

110

100

90

80

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

140

150

40

45

50

55

60

65

70

75

160

40

45

50

55

60

70

75

65

170

17.5% MAC

MTOW − 89 000 kgCG FOR ACN

CALCULATION38% MAC

TAKE OFF

MZFW

MLW

LANDING

8080

8585

180

190

N_AC_070400_1_0160101_01_00


FIGURE-7-4-0-991-016-A01

7-4-0Page 3

Nov 01/19


**ON A/C A321-200

86 88 100


90 92 94 96 9835

80

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1 00

0 kg

)

35

80

(x 1

000

kg)

130

120

110

100

90

80

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T140

150

40

45

50

55

60

65

70

75

160

40

45

50

55

60

70

75

65

170

CG FOR ACNCALCULATION39.21% MAC

TAKE OFF

15.41% MAC

MLW

MTOW − 78 000 kg

MZFW

LANDING

N_AC_070400_1_0170101_01_02

Landing Gear Loading on PavementWV009, MRW 78 400 kg, CG 39.21%

FIGURE-7-4-0-991-017-A01

7-4-0Page 4

Nov 01/19


**ON A/C A321-200

86 88 100


90 92 94 96 9835

95W

EIG

HT

ON

MA

IN L

AN

DIN

G G

EA

R (

x 1

000

kg)

35

95

(x 1

000

kg)

130

120

110

100

90

80

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

140

150

40

45

50

55

60

65

70

75

160

40

45

50

55

60

70

75

65

170

21.65% MAC

MTOW − 93 500 kg

CG FOR ACNCALCULATION36.88% MAC

TAKE OFF

MZFW

MLW

8585

9090

180

190

200

210

8080

LANDING

N_AC_070400_1_0180101_01_00


FIGURE-7-4-0-991-018-A01

7-4-0Page 5

Nov 01/19


**ON A/C A321neo

86 88 100


90 92 94 96 98

80

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1 00

0 kg

)

(x 1

000

kg)

130

120

110

100

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

140

150

45

50

55

60

65

70

75

160

45

50

55

60

70

75

65

TAKE OFF

LANDING

85

80

85

165

170

MZFW

MLW

16.28% MAC

CG FOR ACNCALCULATION

37% MAC

MTOW − 80 000 kg

N_AC_070400_1_0190101_01_03


FIGURE-7-4-0-991-019-A01

7-4-0Page 6

Nov 01/19


**ON A/C A321neo


100

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1 00

0 kg

)

100

(x 1

000

kg)

130

120

110

100

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

140

150

45

50

55

60

65

70

75

160

45

50

55

60

70

75

65

170

CG FOR ACN

36.07% MAC

TAKE OFF

MZFW

8585

9595

180

190

200

210

8080

9090

220

MLW

CALCULATION

86 88 10090 92 94 96 98

26.02% MAC

MTOW − 97 000 kg

LANDING

WV071, MRW 97 400 kg, CG 36.07%

N_AC_070400_1_0200101_01_01


FIGURE-7-4-0-991-020-A01

7-4-0Page 7

Nov 01/19


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

**ON A/C A321-100 A321-200 A321neo

Flexible Pavement Requirements - US Army Corps of Engineers Design Method

1. This section provides data about the flexible pavement requirements.The flexible pavement requirement graphs are given at standard tire pressure for the weight variantsproducing (at the MRW and maximum aft CG) the lowest MLG load and the highest MLG load foreach type of aircraft.They are calculated with the US Army Corps of Engineers Design Method.To find a flexible pavement thickness, you must know the Subgrade Strength (CBR), the annualdeparture level and the weight on one MLG.The line that shows 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).The procedure that follows is used to develop flexible pavement design curves:- With the scale for pavement thickness at the bottom and the scale for CBR at the top, a random

line is made to show 10 000 coverages,- A plot is then made of the incremental values of the weight on the MLG,- Annual departure lines are made based on the load lines of the weight on the MLG that is shown

on the graph.

Example, see FIGURE 7-5-0-991-014-A, calculation of the thickness of the flexible pavement forMLG:- An aircraft with a MRW of 78 400 kg (172 850 lb),- A ”CBR” value of 10,- An annual departure level of 25 000,- The load on one MLG of 30 000 kg (66 150 lb).The required flexible pavement thickness is 57.4 cm (23 in).

NOTE : The CG in the figure title is the CG used for ACN calculation.

7-5-0Page 1

Nov 01/19


**ON A/C A321-100

SUBGRADE STRENGTH − CBR

8060403020151063

8060403020151063

FLEXIBLE PAVEMENT THICKNESS

10 15 20 30 40 60 80 100 120 150 180(cm)

(in)

1 270x455R22 (49x18−22) TIRES

TIRE PRESSURE CONSTANT AT 12.8 bar (186 psi)

10 000 COVERAGES USEDFOR ACN CALCULATIONSALPHA FACTOR = 0.9

MAXIMUM POSSIBLEMAIN GEAR LOADAT MAXIMUM RAMPWEIGHT AND AFT CG

37 510 kg (82 700 lb)WEIGHT ON ONE MAIN LANDING GEAR

35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

1 2003 0006 00015 000

*20 YEAR PAVEMENT LIFE25 000

ANNUAL DEPARTURES*

N_AC_070500_1_0140101_01_00

Flexible Pavement RequirementsWV004, MRW 78 400 kg, CG 41 %

FIGURE-7-5-0-991-014-A01

7-5-0Page 2

Nov 01/19


**ON A/C A321-100


8060403020151063

8060403020151063


10 15 20 30 40 60 80 100 120 150 180(cm)

(in)

1 270x455R22 (49x18−22) TIRES





1 2003 0006 00015 000


ANNUAL DEPARTURES*


N_AC_070500_1_0150101_01_00


FIGURE-7-5-0-991-015-A01

7-5-0Page 3

Nov 01/19


**ON A/C A321-200


8060403020151063

8060403020151063


10 15 20 30 40 60 80 100 120 150 180(cm)

(in)

1270x455R22 (49x18−22) TIRESTIRE PRESSURE CONSTANT AT 12.8 bar (186 psi)

37 330 kg (82 300 lb)WEIGHT ON ONE WING LANDING GEAR


MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT ANDAFT CG

10 000 COVERAGESUSED FOR ACNCALCULATIONS

ALPHA FACTOR = 0.9

ANNUAL DEPARTURES*1 2003 0006 00015 000


N_AC_070500_1_0160101_01_02

Flexible Pavement RequirementsWV009, MRW 78 400 kg, CG 39.21 %

FIGURE-7-5-0-991-016-A01

7-5-0Page 4

Nov 01/19


**ON A/C A321-200


8060403020151063

8060403020151063


10 15 20 30 40 60 80 100 120 150 180(cm)

(in)

1 270x455R22 (49x18−22) TIRES

TIRE PRESSURE CONSTANT AT 15 bar (218 psi)





1 2003 0006 00015 000


ANNUAL DEPARTURES*

N_AC_070500_1_0170101_01_00


FIGURE-7-5-0-991-017-A01

7-5-0Page 5

Nov 01/19


**ON A/C A321neo


8060403020151063


1 2003 0006 00015 000


ANNUAL DEPARTURES*

8060403020151063

10 15 20 30 40 60 80 100 120 150 180(cm)

(in)


1270x455R22 (46x18−22) TIRES



WEIGHT ON ONE MAIN LANDING GEAR38 060 kg (83 900 lb)35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)

N_AC_070500_1_0180101_01_02


FIGURE-7-5-0-991-018-A01

7-5-0Page 6

Nov 01/19


**ON A/C A321neo


8060403020151063

8060403020151063


10 15 20 30 40 60 80 100 120 150 180

(cm)

(in)


MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT ANDAFT CG

46 280 kg WEIGHT ON ONE WING LANDING GEAR

40 000 kg 35 000 kg30 000 kg25 000 kg

10 000 COVERAGES USED FOR ACNCALCULATIONS

ALPHA FACTOR = 0.9

(102 025 lb)(88 175 lb)(77 150 lb)(66 150 lb)(55 125 lb)

ANNUAL DEPARTURES*1 2003 0006 00015 000


N_AC_070500_1_0190101_01_02


FIGURE-7-5-0-991-019-A01

7-5-0Page 7

Nov 01/19


7-6-0 Flexible Pavement Requirements - LCN Conversion

**ON A/C A321-100 A321-200 A321neo

Flexible Pavement Requirements - LCN Conversion

1. The Load Classification Number (LCN) curves are no longer provided in section 07-06-00 since theLCN system for reporting pavement strength is obsolete, having been replaced by the ICAOrecommended ACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

7-6-0Page 1

Nov 01/19


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

**ON A/C A321-100 A321-200 A321neo

Rigid Pavement Requirements - Portland Cement Association Design Method

1. This section provides data about the rigid pavement requirements for the PCA (Portland CementAssociation) design method.The rigid pavement requirement graphs are given at standard tire pressure for the weight variantsproducing (at the MRW and maximum aft CG) the lowest MLG load and the highest MLG load foreach A/C type.They are calculated with the PCA design method.To find a rigid pavement thickness, you must know the Subgrade Modulus (k), the permitted workingstress and the weight on one MLG.The procedure that follows is used to develop rigid pavement design curves:- With the scale for pavement thickness on the left and the scale for permitted working stress on

the right, a random load line is made. This represents the MLG maximum weight to be shown,- A plot is then made of all values of the subgrade modulus (k values),- More load lines for the incremental values of the weight on the MLG are made based on the

curve for k = 150 MN/m3, which is already shown on the graph.

Example, see FIGURE 7-7-0-991-016-A, calculation of the thickness of the rigid pavement for theMLG:- An aircraft with a MRW of 78 400 kg (172 850 lb),- A k value of 80 MN/m3 (300 lbf/in3),- A permitted working stress of 31.64 kg/cm2 (450 lb/in2),- The load on one MLG is 30 000 kg (66 150 lb).The required rigid pavement thickness is 257 mm (10 in).


7-7-0Page 1

Nov 01/19


**ON A/C A321-100

7

8

9

10

11

12

13

14

15

100

200

300

400

500

600

700

800

(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

m)


FOR LOADS LESS THAN MAXIMUM,EXACT.LINE AND ANY VALUES FOR k ARETHE MAXIMUM LOAD REFERENCETHE VALUES OBTAINED BY USINGNOTE:

THE CURVES ARE EXACT FOR k =80 MN/m³ BUT DEVIATE SLIGHTLYFOR ANY OTHER VALUES OF k.

PDILB" PORTLAND CEMENTPAVEMENT DESIGN − PROGRAMPROGRAM FOR AIRPORTPAVEMENTS" AND "COMPUTER"DESIGN OF CONCRETE AIRPORTREFERENCE:

ASSOCIATION.

34

32

30

28

26

24

22

20

18

1270x455R22 (49x18−22) TIRES

36

38

MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT AND AFT CG

k = 40 MN/m³k = 80 MN/m³k = 150 MN/m³

k = 20 MN/m³

WEIGHT ON ONE MAIN LANDING GEAR


37 510 kg (82 700 lb)

50

40

30

20

10

60

900

(in)

N_AC_070700_1_0160101_01_02

Rigid Pavement RequirementsWV004, MRW 78 400 kg, CG 41 %

FIGURE-7-7-0-991-016-A01

7-7-0Page 2

Nov 01/19


**ON A/C A321-100

7

8

9

10

11

12

13

14

15

100

200

300

400

500

600

700

800

(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

m)





ASSOCIATION.

34

32

30

28

26

24

22

20

18

1270x455R22 (49x18−22) TIRES

36

38


k = 40 MN/m³k = 80 MN/m³k = 150 MN/m³

k = 20 MN/m³



42 430 kg (93 550 lb)

50

40

30

20

10

60

900

(in)

N_AC_070700_1_0170101_01_02


FIGURE-7-7-0-991-017-A01

7-7-0Page 3

Nov 01/19


**ON A/C A321-200

7

8

9

10

11

12

13

14

15

100

200

300

400

500

600

700

800

(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

m)





ASSOCIATION.

34

32

30

28

26

24

22

20

18

1270x455R22 (49x18−22) TIRES

36

38


k = 40 MN/m³k = 80 MN/m³k = 150 MN/m³

k = 20 MN/m³



37 330 kg (82 300 lb)

50

40

30

20

10

60

900

(in)

N_AC_070700_1_0180101_01_02

Rigid Pavement RequirementsWV009, MRW 78 400 kg, CG 39.21%

FIGURE-7-7-0-991-018-A01

7-7-0Page 4

Nov 01/19


**ON A/C A321-200

7

8

9

10

11

12

13

14

15

100

200

300

400

500

600

700

800

(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

m)

TIRE PRESSURE CONSTANT AT 15 bar (218 psi)




ASSOCIATION.

34

32

30

28

26

24

22

20

18

1270x455R22 (49x18−22) TIRES

36

38

k = 40 MN/m³k = 80 MN/m³k = 150 MN/m³

k = 20 MN/m³



44 720 kg (98 600 lb)

50

40

30

20

10

60

900

(in)

MAXIMUM POSSIBLE MAIN GEAR LOAD ATMAXIMUM RAMPWEIGHT AND AFT CG

N_AC_070700_1_0190101_01_02

Rigid Pavement RequirementsWV011, MRW 93 900 kg, CG 36.88 %

FIGURE-7-7-0-991-019-A01

7-7-0Page 5

Nov 01/19


**ON A/C A321neo

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S(c

m)

34

32

30

28

26

24

22

20

18 7

8

9

10

(in)

11

12

13

14

15





ASSOCIATION.

(lb/in

²)

(kg/

cm²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

60

50

40

30

20

100

200

300

400

500

600

800

900

700

WEIGHT ON ONE MAIN LANDING GEAR 38 060 kg (83 900 lb)35 000 kg (77 150 lb)30 000 kg (66 150 lb)25 000 kg (55 125 lb)20 000 kg (44 100 lb)


10

36

38

k = 40 MN/m³k = 80 MN/m³k = 150 MN/m³

k = 20 MN/m³

N_AC_070700_1_0200101_01_02


FIGURE-7-7-0-991-020-A01

7-7-0Page 6

Nov 01/19


**ON A/C A321neo

900

800

700

600

500

400

300

200

100

k = 40 MN/m³k = 80 MN/m³k = 150 MN/m³

k = 20 MN/m³



46 280 kg (102 025 lb)




ASSOCIATION.

(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

m)

TIRE PRESSURE CONSTANT AT 15.7 bar (228 psi)1270x455R22 (49x18−22) TIRES

(lb/in

²)

(in)

7

8

9

10

11

12

13

14

15

MAXIMUM POSSIBLE MAIN GEAR LOAD ATMAXIMUM RAMPWEIGHT AND AFT CG

34

32

30

28

26

24

22

20

18

36

38

60

50

40

30

20

10

N_AC_070700_1_0210101_01_02

Rigid Pavement RequirementsWV071, MRW 97 400 kg, CG 36.07 %

FIGURE-7-7-0-991-021-A01

7-7-0Page 7

Nov 01/19


7-8-0 Rigid Pavement Requirements - LCN Conversion

**ON A/C A321-100 A321-200 A321neo

Rigid Pavement Requirements - LCN Conversion

1. The Load Classification Number (LCN) curves are no longer provided in section 07-08-00 since theLCN system for reporting pavement strength is obsolete, having been replaced by the ICAOrecommended ACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

7-8-0Page 1

Nov 01/19


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

**ON A/C A321-100 A321-200 A321neo

Aircraft Classification Number - Flexible and Rigid Pavements

1. This section provides data about the Aircraft Classification Number (ACN) for an aircraft grossweight in relation to a subgrade strength value for flexible and rigid pavement.The flexible and rigid pavement requirement graphs are given at standard tire pressure for the weightvariants producing (at the MRW and maximum aft CG) the lowest MLG load and the highest MLGload for each type of aircraft.To find the ACN of an aircraft on flexible and rigid pavement, you must know the aircraft grossweight and the subgrade strength.

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

Example, see FIGURE 7-9-0-991-020-A (sheet 1), calculation of the ACN for flexible pavement for:- An aircraft with a MRW of 78 400 kg (172 850 lb),- An aircraft gross weight of 65 000 kg (143 300 lb),- A low subgrade strength (code C).The ACN for flexible pavement is 38.

Example, see FIGURE 7-9-0-991-020-A (sheet 2), calculation of the ACN for rigid pavement for:- An aircraft with a MRW of 78 400 kg (172 850 lb),- An aircraft gross weight of 65 000 kg (143 300 lb),- A medium subgrade strength (code B).The ACN for rigid pavement is 40.

2. Aircraft Classification Number - ACN tableThe tables in FIGURE 7-9-0-991-019-A, FIGURE 7-9-0-991-022-A and FIGURE 7-9-0-991-025-Aprovide ACN data in tabular format similar to the one used by ICAO in the ”Aerodrome DesignManual Part 3, Pavements - Edition 1983” for all the operational weight variants of the aircraft.As an approximation, use a linear interpolation in order to get the ACN at the required operatingweight using the following equation:- ACN = ACN min + (ACN max - ACN min) x (Operating weight - 47 000 kg)/(MRW - 47 000

kg)As an approximation, also use a linear interpolation in order to get the aircraft weight at thepavement PCN using the following equation:- Operating weight = 47 000 kg + (MRW - 47 000 kg) x (PCN - ACN min)/(ACN max - ACN

min)With ACN max: ACN calculated at the MRW in the table and with ACN min: ACN calculated at 47000 kg.

7-9-0Page 1

Nov 01/19



7-9-0Page 2

Nov 01/19


**ON A/C A321-100

452345234723422345234223

4724472449

44

47

4424

24

24

24

532653

55

49

53

4926

26

26

26

26

593059

60

55

59305530

30

30

30

43234923

45

5224

2451

5726

2656306330

ALL UPMASS (kg)

LOAD ONONE MAINGEAR LEG

(%)

TIREPRESSURE

(MPa)

ACN FORRIGID PAVEMENT

SUBGRADES − MN/m³

High150

Medium80

Low40

Ultra−low20

ACN FORFLEXIBLE PAVEMENTSUBGRADES − CBR

High15

Medium10

Low6

Ultra−low3

WEIGHTVARIANT

A321−100WV000

A321−100WV002

A321−100WV003

A321−100WV004

A321−100WV005

A321−100WV006

A321−100WV007

A321−100WV008

83 40047 00083 40047 00085 400

78 400

83 400

78 400

47 000

47 000

47 000

47 00080 400

89 40047 000

47 000

47.847.847.847.847.947.847.847.847.847.847.847.847.847.847.547.4

1.36

1.39

1.28

1.36

1.28

1.36

1.36

1.46

512651

26

25

26

25

2653

47

51

47

26

26

49

56

54285428

28

27

28

27

56

50

54

50

28

28

52

59

57295729592952295729522954296229

59315931613154305931543057316431

N_AC_070900_1_0190101_01_01

Aircraft Classification NumberACN Table

FIGURE-7-9-0-991-019-A01

7-9-0Page 3

Nov 01/19


**ON A/C A321-100

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

AIRCRAFT CLASSIFICATION NUMBER (ACN)

1 27

0x45

5R22

(49

x18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

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.

SE

E S

EC

TIO

N 7−

4−0.

2025303540455060 55 15

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R 3

(U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.9

8090

100

110

120

130

140

150

160

170

4555

6540

5060

7580

3570

N_AC_070900_1_0200101_01_00

Aircraft Classification NumberFlexible Pavement - WV004, MRW 78 400 kg, CG 41 % (Sheet 1 of 2)

FIGURE-7-9-0-991-020-A01

7-9-0Page 4

Nov 01/19


**ON A/C A321-100

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


1 27

0x45

5R22

(49

x18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

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.

SE

E S

EC

TIO

N 7−

4−0.

(x 1

000

lb)

2025303540455060 55 15

8090

100

110

120

130

140

150

160

170

SU

BG

RA

DE

ST

RE

NG

TH

A −

k =

150

MN

/m³

(HIG

H)

D −

k =

20

MN

/m³

(ULT

RA

LO

W)

C −

k =

40

MN

/m³

(LO

W)

B −

k =

80

MN

/m³

(ME

DIU

M)

4555

6540

5060

7580

3570

N_AC_070900_1_0200102_01_00

Aircraft Classification NumberRigid Pavement - WV004, MRW 78 400 kg, CG 41 % (Sheet 2 of 2)

FIGURE-7-9-0-991-020-A01

7-9-0Page 5

Nov 01/19


**ON A/C A321-100


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.

SE

E S

EC

TIO

N 7−

4−0.

8090

100

110

120

130

140

150

160

170

190

180

152025303540455065 5560

4555

6575

8540

5060

7080

9035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

(x 1

000

lb)

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R 3

(U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.9

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.6

bar

(212

psi

)1

270x

455R

22 (

49x1

8−22

) T

IRE

S

N_AC_070900_1_0210101_01_00


FIGURE-7-9-0-991-021-A01

7-9-0Page 6

Nov 01/19


**ON A/C A321-100

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.6

bar

(212

psi

)1

270x

455R

22 (

49x1

8−22

) T

IRE

S

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.

SE

E S

EC

TIO

N 7−

4−0.

8090

100

110

120

130

140

150

160

170

190

180

152025303540455065 5560

4555

6575

8540

5060

7080

9035

SU

BG

RA

DE

ST

RE

NG

TH

A −

k =

150

MN

/m³

(HIG

H)

D −

k =

20

MN

/m³

(ULT

RA

LO

W)

C −

k =

40

MN

/m³

(LO

W)

B −

k =

80

MN

/m³

(ME

DIU

M)

(x 1

000

lb)

N_AC_070900_1_0210102_01_00


FIGURE-7-9-0-991-021-A01

7-9-0Page 7

Nov 01/19


**ON A/C A321-200

A321−200WV000

89 40047 000

47.847.8

1.46

93 40047 000

47.647.6

89 400 47.847.8

91 400 47.747.7

87 400 47.847.8

85 400 47.647.6

1.46

1.50

1.46

1.39

1.50

47 000

47 000

47 000

47 000

5727

6028

6230

6531

60 6328

6630

6831

27

27

27

26

27

28

28

28

28

57

59

55

53

60 6230

6531

62 6430

6731

58 6130

6331

56 5829

6130

A321−200WV001

A321−200WV002

A321−200WV003

A321−200WV004

A321−200WV005

502452245024512448244623

5224552452

54

51

4924

24

24

24

582661

58

60

56

5426

26

26

26

26

643067

64

65

62306030

30

30

30

83 400 47.747.7

83 400 47.747.7

1.36

1.36

47 000

47 000

26

26

27

27

51

51

54 5729

5930

54 5729

5930

A321−200WV006

A321−200WV007

45234523

47

4724

2453

5326

2659305930

80 400 47.847.8

78 400 47.747.7

1.36

1.28

47 000

47 000

26

25

28

27

49

47

52 5429

5730

49 5229

5430

4323

4223

45

4324

2451

4926

265630

5530

85 400 47.647.6

93 900 47.647.6

1.39

1.50

47 000

47 000

26

27

28

28

53

61

56 5829

6130

63 6630

6931

A321−200WV010

A321−200WV011

46235324

49

5624

2454

6126

2660306730

ALL UPMASS (kg)


(%)

TIREPRESSURE

(MPa)



High150

Medium80

Low40

Ultra−low20

ACN FORFLEXIBLE PAVEMENTSUBGRADES − CBR

High15

Medium10

Low6

Ultra−low3

WEIGHTVARIANT

A321−200WV008 (CG 40.51%)

80 400 47.747.7

1.3647 000 26 27

49 52 5429

5630

4323

4524

5026

5630

A321−200WV008 (CG 39.71%)

A321−200WV009 (CG 40.08%)

78 400 47.647.6

1.2847 000 25 27

46 49 5229

5430

4123

4324

4926

5530

A321−200WV009 (CG 39.21%)

N_AC_070900_1_0220101_01_03


FIGURE-7-9-0-991-022-A01

7-9-0Page 8

Nov 01/19


**ON A/C A321-200

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


1 27

0x45

5R22

(49

x18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

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.

SE

E S

EC

TIO

N 7−

4−0.


(x 1

000

lb)

2025303540455060 55 15

8090

100

110

120

130

140

150

160

170

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R 3

(U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.9

4555

6540

5060

7580

3570

WV

009,

MR

W 7

8 40

0 K

g, C

G 3

9.21

%

N_AC_070900_1_0230101_01_01

Aircraft Classification NumberFlexible Pavement - WV009, MRW 78 400 kg, CG 39.21 % (Sheet 1 of 2)

FIGURE-7-9-0-991-023-A01

7-9-0Page 9

Nov 01/19


**ON A/C A321-200

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)A

CN

WA

S D

ET

ER

MIN

ED

AS

RE

FE

RE

NC

ED

INIC

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.S

EE

SE

CT

ION

7−

4−0.

(x 1

000

lb)


1 27

0x45

5R22

(49

x18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.8

bar

(186

psi

)

2025303540455060 55 15

8090

100

110

120

130

140

150

160

170

SU

BG

RA

DE

ST

RE

NG

TH

D −

k =

20

MN

/m³

(ULT

RA

LO

W)

A −

k =

150

MN

/m³

(HIG

H)

B −

k =

80

MN

/m³

(ME

DIU

M)

C −

k =

40

MN

/m³

(LO

W)

4555

6540

5060

7580

3570

WV

009,

MR

W 7

8 40

0 K

g, C

G 3

9.21

%

N_AC_070900_1_0230102_01_01

Aircraft Classification NumberRigid Pavement - WV009, MRW 78 400 kg, CG 39.21 % (Sheet 2 of 2)

FIGURE-7-9-0-991-023-A01

7-9-0Page 10

Nov 01/19


**ON A/C A321-200

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


1 27

0x45

5R22

(49

x18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

5 ba

r (2

18 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.

SE

E S

EC

TIO

N 7−

4−0.

4555

6575

85

2535455565

9540

5060

7080

90

203040506070 1535

(x 1

000

lb)

8090

100

110

120

130

140

150

160

170

180

190

200

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R 3

(U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070900_1_0240101_01_00


FIGURE-7-9-0-991-024-A01

7-9-0Page 11

Nov 01/19


**ON A/C A321-200

SU

BG

RA

DE

ST

RE

NG

TH

D −

k =

20

MN

/m³

(ULT

RA

LO

W)

A −

k =

150

MN

/m³

(HIG

H)

B −

k =

80

MN

/m³

(ME

DIU

M)

C −

k =

40

MN

/m³

(LO

W)

4555

6575

85

2535455565

9540

5060

7080

90

203040506070

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


1 27

0x45

5R22

(49

x18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

5 ba

r (2

18 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.

SE

E S

EC

TIO

N 7−

4−0.

1535

(x 1

000

lb)

8090

100

110

120

130

140

150

160

170

180

190

200

N_AC_070900_1_0240102_01_00


FIGURE-7-9-0-991-024-A01

7-9-0Page 12

Nov 01/19


**ON A/C A321neo

ALL UPMASS (kg)


(%)

TIREPRESSURE

(MPa)



High150

Medium80

Low40

20

Ultra−low

2015

High10

Medium6

Low

3

ACN FORFLEXIBLE PAVEMENTSUBGRADES − CBRWEIGHT

VARIANT

A321NEOWV050 (CG 38.02%)

A321NEOWV052

93 90047 000

47.647.6

1.506127

6328

6630

6931

5324

5624

6126

6730

89 40047 000

47.847.8

1.465727

6028

6230

6531

5024

5224

5826

6430

A321NEOWV050 (CG 37%)

89 40047 000

47.647.6

1.465726

6028

6229

6431

4924

5224

5826

6330

A321NEOWV051 (CG 38.02%)

89 40047 000

47.847.8

1.465727

6028

6230

6531

5024

5224

5826

6430

A321NEOWV051 (CG 37%)

89 40047 000

47.647.6

1.465726

6028

6229

6431

4924

5224

5826

6330

A321NEOWV053

93 90047 000

47.647.6

1.506127

6328

6630

6931

5324

5624

6126

6730

A321NEOWV056 (CG 37.12%)

92 90047 000

47.747.6

1.506027

6328

6530

6831

5224

5524

6126

6630

A321NEOWV056 (CG 37%)

92 90047 000

47.647.6

1.506027

6328

6530

6831

5224

5524

6126

6630

A321NEOWV063 (CG 37.5%)

91 40047 000

47.747.7

1.505927

6228

6430

6731

5124

5424

6026

6530

A321NEOWV063 (CG 37%)

91 40047 000

47.647.6

1.505927

6228

6430

6631

5124

5424

5926

6530

A321NEOWV065 (CG 37.62%)

90 90047 000

47.747.7

1.505827

6128

6430

6631

5124

5324

5926

6530

A321NEOWV065 (CG 37%)

90 90047 000

47.647.6

1.505827

6128

6430

6631

5124

5324

5926

6530

A321NEOWV070 (CG 38.71%)

80 40047 000

47.647.5

1.364926

5127

5429

5630

4323

4524

5026

5630

A321NEOWV070 (CG 37%)

80 40047 000

47.347.3

1.364826

5127

5429

5630

4323

4523

5025

5630

A321NEOWV071

A321NEOWV072

97 40047 000

47.547.5

1.576427

6728

7030

7231

5524

5824

6426

7030

97 40047 000

47.547.5

1.576427

6728

7030

7231

5524

5824

6426

7030

A321NEOWV080

95 40047 000

47.647.6

1.576227

6528

6830

7031

5424

5724

6326

6830

Ultra−low

N_AC_070900_1_0250101_01_04


FIGURE-7-9-0-991-025-A01

7-9-0Page 13

Nov 01/19


**ON A/C A321neo


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.6

bar

(197

psi

)1

270x

455R

22 (

49x1

8−22

) T

IRE

S

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.

SE

E S

EC

TIO

N 7−

4−0.

(x 1

000

lb)

60 55 50 45 40 35 30 2025 1545

5055

6065

7075

8085

100

110

120

130

140

150

160

170

180

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R 3

(U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070900_1_0260101_01_02


FIGURE-7-9-0-991-026-A01

7-9-0Page 14

Nov 01/19


**ON A/C A321neo


AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

3.6

bar

(197

psi

)1

270x

455R

22 (

49x1

8−22

) T

IRE

S

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.

SE

E S

EC

TIO

N 7−

4−0.

(x 1

000

lb)

60 55 50 45 40 35 30 25 20 1545

5055

6065

7075

8085

100

110

120

130

140

150

160

170

180

C −

k =

40

MN

/m³

(LO

W)

B −

k =

80

MN

/m³

(ME

DIU

M)

A −

k =

150

MN

/m³

(HIG

H)

SU

BG

RA

DE

ST

RE

NG

TH

D −

k =

20

MN

/m³

(ULT

RA

LO

W)

N_AC_070900_1_0260102_01_02


FIGURE-7-9-0-991-026-A01

7-9-0Page 15

Nov 01/19


**ON A/C A321neo


(x 1

000

lb)

1 27

0x45

5R22

(49

x18−

22)

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

5.7

bar

(228

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.

SE

E S

EC

TIO

N 7−

4−0.

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

C −

CB

R 6

(LO

W)

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

SU

BG

RA

DE

ST

RE

NG

TH

ALP

HA

FA

CT

OR

= 0

.9

D −

CB

R 3

(U

LTR

A L

OW

)

75 70 65 60 55 50 45 40 35 30 25 20 1545

5055

6065

7075

8085

9095

100

100

110

120

130

140

150

160

170

180

190

200

210

220

N_AC_070900_1_0270101_01_02


FIGURE-7-9-0-991-027-A01

7-9-0Page 16

Nov 01/19


**ON A/C A321neo


TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

5.7

bar

(228

psi

)1

270x

455R

22 (

49x1

8−22

) T

IRE

S

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.

SE

E S

EC

TIO

N 7−

4−0.

(x 1

000

lb)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

75 70 65 60 55 50 45 40 35 30 25 20 1545

5055

6560

7075

8090

8510

095

100

110

120

130

140

150

160

170

180

190

200

210

220

SU

BG

RA

DE

ST

RE

NG

TH

A −

k =

150

MN

/m³

(HIG

H)

D −

k =

20

MN

/m³

(ULT

RA

LO

W)

C −

k =

40

MN

/m³

(LO

W)

B −

k =

80

MN

/m³

(ME

DIU

M)

N_AC_070900_1_0270102_01_02


FIGURE-7-9-0-991-027-A01

7-9-0Page 17

Nov 01/19


SCALED DRAWINGS

8-0-0 SCALED DRAWINGS

**ON A/C A321-100 A321-200 A321neo

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

Nov 01/19


**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

Nov 01/19


**ON A/C A321neo

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

010

2030

4050

FE

ET

05

1015

ME

TE

RS

0 10 20 30 40 50FEET

0 5 10 15METERS

N_AC_080000_1_0070101_01_00

Scaled DrawingFIGURE-8-0-0-991-007-A01

8-0-0Page 3

Nov 01/19


AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 AIRCRAFT RESCUE AND FIRE FIGHTING

**ON A/C A321-100 A321-200 A321neo

Aircraft Rescue and Fire Fighting

1. Aircraft Rescue and Fire Fighting ChartsThis sections provides 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

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

/

AIR

BU

S S

.A.S

. 201

8 . A

ll rig

hts

rese

rved

.

SH

EE

T 2

/2

NO

V 2

019

/

N_AC_100000_1_0430101_01_04

Front PageFIGURE-10-0-0-991-043-A01

10-0-0Page 2

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

N_AC_100000_1_0440101_01_02

Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-0-0-991-044-A01

10-0-0Page 3

Nov 01/19


**ON A/C A321neo

N_AC_100000_1_0590101_01_01

Highly Flammable and Hazardous Materials and Components for A321NEO-ACFFIGURE-10-0-0-991-059-A01

10-0-0Page 4

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

AC

CE

SS

VIA

A

CC

ES

S D

OO

R 8

22

BA

T−

2

A

BA

T−

1

B

A

B

FR

64

FR

70

ELT

AN

TE

NN

A

AF

T P

AX

DO

OR

261B

CE

LT

Z12

0

Z26

0

N_AC_100000_1_0580101_01_02

Batteries Location and AccessFIGURE-10-0-0-991-058-A01

10-0-0Page 5

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

01 02

01

02

02

01

N_AC_100000_1_0450101_01_02

Wheel/Brake OverheatWheel Safety Area (Sheet 1 of 2)

FIGURE-10-0-0-991-045-A01

10-0-0Page 6

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

N_AC_100000_1_0450102_01_00

Wheel/Brake OverheatRecommendations (Sheet 2 of 2)

FIGURE-10-0-0-991-045-A01

10-0-0Page 7

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

AF

RP

+ C

FR

P

Ara

mid

Fib

er R

einf

orce

d P

last

ic (

AF

RP

)

Gla

ss F

iber

Rei

nfor

ced

Pla

stic

(G

FR

P)

Car

bon

Fib

er R

einf

orce

d P

last

ic (

CF

RP

)

N_AC_100000_1_0460101_01_01N_AC_100000_1_0460101_01_01

Composite MaterialsFIGURE-10-0-0-991-046-A01

10-0-0Page 8

Nov 01/19


**ON A/C A321neo

AF

RP

+ C

FR

P

Ara

mid

Fib

er R

einf

orce

d P

last

ic (

AF

RP

)

Gla

ss F

iber

Rei

nfor

ced

Pla

stic

(G

FR

P)

Car

bon

Fib

er R

einf

orce

d P

last

ic (

CF

RP

)

AF

RP

+ C

FR

P

Ara

mid

Fib

er R

einf

orce

d P

last

ic (

AF

RP

)

Gla

ss F

iber

Rei

nfor

ced

Pla

stic

(G

FR

P)

Car

bon

Fib

er R

einf

orce

d P

last

ic (

CF

RP

)

N_AC_100000_1_0620101_01_00

Composite Materials for A321NEO-ACFFIGURE-10-0-0-991-062-A01

10-0-0Page 9

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

A

B

BA

N_AC_100000_1_0470101_01_01

L/G Ground Lock Safety DevicesFIGURE-10-0-0-991-047-A01

10-0-0Page 10

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

CO

CK

PIT

ES

CA

PE

RO

PE

−3

−6 −9

EM

ER

GE

NC

Y D

ES

CE

NT

TH

RO

UG

H T

HE

WIN

DO

W O

PE

NIN

G W

ITH

TH

E E

SC

AP

E R

OP

E

GR

ID E

QU

ALS

1 m

(3.

28 ft

) IN

RE

ALI

TY

0

DO

OR

3 S

ING

LE L

AN

E S

LID

E

DO

OR

2 S

ING

LE L

AN

E S

LID

E

DO

OR

4 S

ING

LE o

r D

UA

L LA

NE

SLI

DE

DO

OR

1 S

ING

LE o

r D

UA

L LA

NE

SLI

DE

NO

TE

:−

LH

SH

OW

N, R

H S

YM

ME

TR

ICA

L.−

DIM

EN

SIO

NS

AR

E A

PP

RO

XIM

AT

E.

N_AC_100000_1_0480101_01_04

Emergency Evacuation DevicesFIGURE-10-0-0-991-048-A01

10-0-0Page 11

Nov 01/19


**ON A/C A321neo

NO

TE

:−

LH

SH

OW

N, R

H S

YM

ME

TR

ICA

L.−

DIM

EN

SIO

NS

AR

E A

PP

RO

XIM

AT

E.

CO

CK

PIT

ES

CA

PE

RO

PE

DO

OR

4 S

ING

LE o

r D

UA

L LA

NE

SLI

DE

DO

OR

1 S

ING

LE o

r D

UA

L LA

NE

SLI

DE

DO

OR

3 S

ING

LE L

AN

E S

LID

E

OV

ER

WIN

G D

UA

L LA

NE

SLI

DE

FO

RW

AR

D O

VE

RW

ING

EX

IT

AF

T O

VE

RW

ING

EX

IT

EM

ER

GE

NC

Y D

ES

CE

NT

TH

RO

UG

H T

HE

WIN

DO

W O

PE

NIN

G W

ITH

TH

E E

SC

AP

E R

OP

E

−3

−6

−90

GR

ID E

QU

ALS

1 m

(3.

28 ft

) IN

RE

ALI

TY

N_AC_100000_1_0600101_01_01

Emergency Evacuation Devices for A321NEO-ACFFIGURE-10-0-0-991-060-A01

10-0-0Page 12

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

DO

OR

OP

EN

ING

:TY

PIC

AL

C

B

AW

AR

NIN

G L

IGH

TS

BC

A

N_AC_100000_1_0490101_01_01

Pax/Crew Doors and Emergency ExitsFIGURE-10-0-0-991-049-A01

10-0-0Page 13

Nov 01/19


**ON A/C A321neo

WA

RN

ING

AU

TO

MA

TIC

DO

OR

ST

AY

CL

EA

R O

F D

OO

R P

AT

HD

OO

R M

AY

OP

EN

WIT

HO

UT

WA

RN

ING

TO

OP

EN

2− P

RE

SS

DO

WN

1− P

RE

SS

FIR

ST

CA

UT

ION

DO

OR

SW

ING

S O

UT

AN

D P

UT

HO

LD

YO

UR

BO

DY

AG

AIN

ST

DO

OR

WH

ILE

OP

EN

ING

OR

SE

RIO

US

INJU

RY

CA

N O

CC

UR

EX

IT

1 −

PU

SH

TH

E S

MA

LL H

AT

CH

WH

ICH

WIL

L U

NLO

CK

TH

E V

EN

T F

LAP

.2 −

TH

E V

EN

T F

LAP

IS F

RE

E T

O B

E R

OT

AT

ED

AN

D D

RIV

E T

HE

ME

CH

AN

ISM

IN T

HE

SA

ME

WA

Y A

S T

HE

INN

ER

HA

ND

LE.

DO

OR

SW

ING

S O

UT

AN

D P

UT

HO

LD Y

OU

R B

OD

Y A

GA

INS

T D

OO

R W

HIL

E O

PE

NIN

G O

R S

ER

IOU

S IN

JUR

Y C

AN

OC

CU

R.

OP

ER

AT

ION

:

A

SM

ALL

HA

TC

H

VE

NT

FLA

P

OV

ER

WIN

G E

ME

RG

EN

CY

DO

OR

WA

RN

ING

:IN

ST

RU

CT

ION

S O

N T

HE

OU

TS

IDE

EX

PLA

IN H

OW

TO

OP

ER

AT

E A

ND

HO

W T

O P

RO

TE

CT

TH

E O

PE

RA

TO

R A

GA

INS

T IN

JUR

IES

.

BB

AB

LH S

HO

WN

RH

SY

MM

ET

RIC

AL

F W DF

WD LH

SH

OW

NR

H S

YM

ME

TR

ICA

L

A

N_AC_100000_1_0630101_01_00

Overwing Emergency Doors for A321NEO-ACFFIGURE-10-0-0-991-063-A01

10-0-0Page 14

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

134A

R15

4AR

/

DO

OR

HA

ND

LEA

A

198C

B

A

B

CD

BC

D

198C

B

TY

PIC

AL

N_AC_100000_1_0500101_01_01

FWD and AFT Lower Deck Cargo DoorsFIGURE-10-0-0-991-050-A01

10-0-0Page 15

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

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

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

BL

OW

ER

OV

RD

FA

UL

TA U T O

EX

TR

AC

TV

EN

TIL

AT

ION

OF

F

CA

B F

AN

S

ON

ON

TE

ST

AF

T

DIS

CH

22V

U

HO

T

AF

T

CA

RG

O S

MO

KE

CO

LD

OF

F

FA

UL

T

HO

T A

IR

OF

F

FA

UL

T

AF

T I

SO

L V

ALV

E

CA

RG

O

DIS

CH

SM

OK

E

FW

D

DIS

CH

DIS

CH

SM

OK

E

APU

SH

PU

SH

PU

SH

DIS

CH

SQ

UIB

DIS

CH

SQ

UIB

DIS

CH

SQ

UIB

DIS

CH

SQ

UIB

DIS

CH

SQ

UIB

AG

EN

T 1

AG

EN

T 2

AG

EN

T 1

AG

EN

T 2

TE

ST

TE

ST

TE

ST

AG

EN

T

F I R E

F I R E

AP

UFI

RE

FIR

EEN

G2

FIR

EEN

G1

E

FA

ULT

FA

ULT

OF

F

OF

F

OF

F

FA

ULT

OF

F

FA

ULT

OF

F

FA

ULT

OF

F

FA

ULT

OF

F

FA

ULT

ALT

N

FA

ULT

ON

AV

AIL

E L E CID

G 2

GE

N 2

DC

BU

S 2

AC

ES

S F

EE

D

EX

T P

WR

AP

U G

EN

GE

N 1

BA

T 2

BA

T2

1B

AT

1

AC

BU

S 1

DC

BU

S 1

CO

MM

ER

CIA

L

GA

LY &

CA

B

IDG

1

E L E C

BU

S T

IEA U T O

VV

35V

U

OF

F

A U T O

AC

BU

S 2

AC E

SS B

US

ON

FA

ULT

ON

FA

ULT

ON

FA

ULT

ON

FA

ULT

ON

AN

TI IC

EPR

OBE

/WIN

DO

WH

EAT

EN

G 1

EN

G 2

WIN

GM

AN

V/S

CTL

MO

DE

SE

LLD

G E

LEV

AU

TOD

ITC

HIN

GC

ABIN

PR

ESS

UP

ON

A U T O

A U T O

25V

U

ON

FA

ULT

ON

AV

AIL

INT

LT

SIG

NS

APU

STB

Y C

OM

PA

SS

AN

N L

TD

OM

ETE

ST

BR

T

DIM

OFFDIM

BR

T

OFF

SE

AT

BE

LTS

NO

SM

OK

ING

EM

ER

EX

IT L

T

A U T OO

FFO

FF

ON

ON

ON

AR

M

OFF

BRT

OFFOV

HD

INTE

G L

T

MA

STE

R S

W

STA

RT

WIN

GN

AV

& L

OG

OS

TRO

BE

BE

AC

ON

OFF

OFF

OFF

ON

ON

ON

OFF

EXT

LT

A U T O

RW

Y T

UR

N O

FFO

NO

N

OFF

OFF

OFF

RETR

ACT

LAN

DL

RN

OS

ET.

O

TAX

I

ON

OF

F

45V

UT

YP

ICA

L

35V

UT

YP

ICA

L

25V

UT

YP

ICA

L

108V

UT

YP

ICA

L

A

F

E

22V

U

TY

PIC

AL

EN

GM

AS

TE

RF

TY

PIC

AL

121A

L B

C D

B

C D

N_AC_100000_1_0510101_01_01

Control PanelsFIGURE-10-0-0-991-051-A01

10-0-0Page 16

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

A

LAT

CH

SH

OW

N IN

CLO

SE

D P

OS

ITIO

NB

TY

PIC

AL

DO

OR

ST

RU

CT

UR

E

TY

PIC

AL

316A

R

HA

ND

LE

FR

84

FR

80

315A

L

B

A

2 −

PU

LL T

HE

HA

ND

LE T

O M

OV

E T

HE

AC

CE

SS

DO

OR

DO

WN

TO

ITS

VE

RT

ICA

L P

OS

ITIO

N.

3 −

PU

SH

TH

E H

AN

DLE

OU

TB

OA

RD

TO

MO

VE

TH

E A

CC

ES

S D

OO

R T

O IT

S O

VE

RC

EN

TE

R P

OS

ITIO

N.

SP

RIN

G

4 −

TH

E S

PR

ING

OF

TH

E D

OO

R M

EC

HA

NIS

M H

OLD

S T

HE

DO

OR

IN T

HE

FU

LLY

OP

EN

PO

SIT

ION

.

N_AC_100000_1_0520101_01_01

APU Access DoorFIGURE-10-0-0-991-052-A01

10-0-0Page 17

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

RW

4W

3W

1W

2

DIM

EN

SIO

NS

AR

E R

ELA

TE

D T

O A

IRC

RA

FT

WE

IGH

T A

ND

CG

CO

NF

IGU

RA

TIO

N

NO

TE

:P

AS

SE

NG

ER

AN

D C

AR

GO

DO

OR

GR

OU

ND

CLE

AR

AN

CE

S A

RE

ME

AS

UR

ED

FR

OM

TH

E C

EN

TE

R O

F T

HE

DO

OR

SIL

L A

ND

FR

OM

FLO

OR

LE

VE

L.

DO

OR

S

47 0

00 k

g(1

03 6

17 lb

)A

FT

CG

(25

%)

A/C

CO

NF

IGU

RA

TIO

Nm

ftD

1D

2D

3D

4C

1C

2C

3

3.50

3.57

4.01

3.73

2.10

2.26

2.33

11.4

811

.71

13.1

612

.24

6.89

7.41

7.64

5.58

4.86

12.1

0

2.75

3.18

3.52

4.88

3.91

6.82

4.18

0.64

TA

ILP

LAN

EH

TA

PV

T

FU

SE

LAG

E

A/C

CO

NF

IGU

RA

TIO

Nm

ftF

1F

2F

3F

4B

F1

CP

1

EN

GIN

E/

NA

CE

LLE

N1

(CF

M56

)N

1 (I

AE

V25

00)

WIN

GS

mft

FT

1F

T2

FT

3W

1W

2W

3W

4 R

A/C

CO

NF

IGU

RA

TIO

N

N1

(CF

M L

EA

P−

1A)

N1

(PW

110

0G)

47 0

00 k

g(1

03 6

17 lb

)A

FT

CG

(25

%)

1.84

1.99

5.98

6.13

1.76

4.30

0.71

0.89

0.58

0.58

6.04

6.53

19.6

220

.11

5.77

14.1

12.

332.

921.

901.

90

47 0

00 k

g(1

03 6

17 lb

)A

FT

CG

(25

%)

18.3

115

.94

39.7

0

9.02

10.4

311

.55

16.0

112

.83

22.3

813

.71

2.10

FT

3F

T2

FT

1N

1

VT

AP

HT

D4

C3

C2

F2

D3

BF

1

D2

C1

D1

CP

1

F4

F3

F1

N_AC_100000_1_0530101_01_02

Aircraft Ground ClearancesFIGURE-10-0-0-991-053-A01

10-0-0Page 18

Nov 01/19


**ON A/C A321-100 A321-200 A321neo

N_AC_100000_1_0540101_01_01

Structural Break-in PointsFIGURE-10-0-0-991-054-A01

10-0-0Page 19

Nov 01/19

aircraft characteristics airport and maintenance planning … · @a321 aircraft characteristics -...

Documents