aircraft characteristics airport and maintenance planning … · @a318 aircraft characteristics -...

@AIRBUSA318

AIRCRAFT CHARACTERISTICSAIRPORT AND MAINTENANCE PLANNING

AC

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

AIRBUS S.A.S.Customer Services

Technical Data Support and Services31707 Blagnac Cedex

FRANCE

Issue: Jul 01/02 Rev: Jun 01/12

@A318AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

HIGHLIGHTS

Revision No. 9 - Jun 01/12

LOCATIONS CHGCODE

DESCRIPTIONS OF CHANGE

CHAPTER 1 R

Section 1-1

Subject 1-1-0

Purpose R PURPOSE CHANGED DUE TO MERGE OFTHE MFP AND AC MANUALS.

Section 01-02 D

CHAPTER 2 R

Section 2-1 R

Subject 2-1-0 R

General Airplane Characteristics R WEIGHT DEFINITIONS UPDATED.

Subject 2-1-1 R

General Airplane Characteristics Data R OEW AND PAYLOAD DELETED.

Section 2-2 R

Subject 2-2-0 R

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

FIGURE General Aircraft Dimensions -Wing Tip Fence

R ILLUSTRATION REVISED

Section 2-3

Subject 2-3-0

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

FIGURE Ground Clearances R

FIGURE Ground Clearances - GroundClearances with Sharklets

N ILLUSTRATION ADDED

HIGHLIGHTSPage 1

Jun 01/12


LOCATIONS CHGCODE


FIGURE Ground Clearances - Flaps andFlap Track Fairings When Flaps FullyExtended


FIGURE Ground Clearances - Flap TrackFairings Up


FIGURE Ground Clearances - AileronDown


FIGURE Ground Clearances - Aileron Upand Spoilers 1 to 5 Extended


FIGURE Ground Clearances - SlatsExtended


Section 2-6 R

Subject 2-6-0

Cargo Compartments R

FIGURE Cargo Compartments -Locations, Dimensions and LoadingCombinations


Subject 02-06-01 D

Section 2-8 N

Subject 2-8-0 N

Escape Slides N

FIGURE Escape Slides - Location N ILLUSTRATION ADDED

FIGURE Escape Slides - Dimensions N ILLUSTRATION ADDED

Section 2-9 N

Subject 2-9-0 N

Landing Gear N

FIGURE Landing Gear - Main LandingGear - Twin Wheel


FIGURE Landing Gear - Main LandingGear Dimensions - Twin Wheel


FIGURE Landing Gear - Nose LandingGear


FIGURE Landing Gear - Nose LandingGear Dimensions


HIGHLIGHTSPage 2

Jun 01/12


LOCATIONS CHGCODE


Landing Gear Maintenance Pits N

FIGURE Landing Gear Maintenance Pits -Maintenance Pit Envelopes


FIGURE Landing Gear Maintenance Pits -Maintenance Pit Envelopes


Section 2-10 N

Subject 2-10-0 N

Exterior Lighting N

FIGURE Exterior Lighting N ILLUSTRATION ADDED




Section 2-11 N

Subject 2-11-0 N

Antennas and Probes Location N

FIGURE Antennas and Probes - Location N ILLUSTRATION ADDED

Section 2-12 N

Subject 2-12-0 N

Auxiliary Power Unit N

FIGURE Auxiliary Power Unit - AccessDoors


FIGURE Auxiliary Power Unit - GeneralLayout


Engine and Nacelle N

FIGURE Power Plant Handling - MajorDimensions - CFM56 Series Engine


FIGURE Power Plant Handling - MajorDimensions - CFM56 Series Engine


FIGURE Power Plant Handling - FanCowls - CFM56 Series Engine


FIGURE Power Plant Handling - ThrustReverser Cowls - CFM56 Series Engine


HIGHLIGHTSPage 3

Jun 01/12


LOCATIONS CHGCODE


FIGURE Power Plant Handling - MajorDimensions - PW 6000 Series Engine


FIGURE Power Plant Handling - NacelleDimensions - PW 6000 Series Engine


FIGURE Power Plant Handling - FanCowls - PW 6000 Series Engine


FIGURE Power Plant Handling - ThrustReverser Halves - PW 6000 Series Engine


Section 2-13 N

Subject 2-13-0 N

Leveling, Symmetry and Alignment N

FIGURE Location of the Leveling Points N ILLUSTRATION ADDED

Section 2-14 N

Subject 2-14-0 N

Jacking for Maintenance N

FIGURE Jacking for Maintenance -Jacking Point Location


FIGURE Jacking for Maintenance -Forward Jacking Point


FIGURE Jacking for Maintenance - WingJacking Points


FIGURE Jacking for Maintenance - SafetyStay


FIGURE Jacking for Maintenance -Jacking Design


Jacking for Wheel Change N

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


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


HIGHLIGHTSPage 4

Jun 01/12


LOCATIONS CHGCODE


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


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


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


CHAPTER 3 R

CHAPTER 4

Section 4-2

Subject 4-2-0

FIGURE Turning Radii, No Slip Angle R ILLUSTRATION REVISED

FIGURE Turning Radii, No Slip Angle R ILLUSTRATION REVISED

Section 4-3

Subject 4-3-0

FIGURE Minimum Turning Radii R

Section 4-4

Subject 4-4-0

Visibility from Cockpit in Static Position R

FIGURE Visibility from Cockpit in StaticPosition

R

FIGURE Binocular Visibility ThroughWindows from Captain Eye Position


Section 4-5 R

Subject 4-5-1

135˚ Turn - Runway to Taxiway R

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

R

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


Subject 4-5-2

90˚ Turn - Runway to Taxiway R

HIGHLIGHTSPage 5

Jun 01/12


LOCATIONS CHGCODE


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

R

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


Subject 4-5-3 N

180˚ Turn on a Runway N

FIGURE 180˚ turn on a Runway - Edgeof Runway Method


Subject 4-5-4

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


Subject 4-5-5

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


Subject 04-05-06 D

Section 4-6

Subject 4-6-0

FIGURE Runway Holding Bay (Apron) R

Section 4-7 R

Subject 4-7-0 R

CHAPTER 5 R

Section 5-1 R

Subject 5-1-0 R

Subject 5-1-2 R

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

FIGURE Typical Ramp Layout - OpenApron - Bulk Loading


Subject 5-1-3 R

HIGHLIGHTSPage 6

Jun 01/12


LOCATIONS CHGCODE


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

FIGURE Typical Ramp Layout - Gate R ILLUSTRATION REVISED

Section 5-2 R

Subject 5-2-0 R

Terminal Operations - Full Servicing TurnRound Time

R DESCRIPTION TITLE UPDATED

FIGURE Turn Round Stations - FullServicing (34 Min.)


Subject 05-02-01 D

Section 5-3 R

Subject 5-3-0 R

Terminal Operation - Minimum ServicingTurn Round Time

R DESCRIPTION TITLE UPDATED

FIGURE Turn Round Stations - MinimumServicing (20 Min.)


Subject 05-03-01 D

Section 5-4

Subject 5-4-1

Ground Service Connections Layout R DELETED GROUND SERVICECONNECTIONS LAYOUT TABLE.

FIGURE Ground Service Connections -Ground Service Connections Layout

R

Subject 5-4-3

Hydraulic System R

Subject 5-4-4

Electrical System R

Subject 5-4-6

Fuel System R NOTE AMENDED

HIGHLIGHTSPage 7

Jun 01/12


LOCATIONS CHGCODE


FIGURE Ground Service Connections -Overpressure Protector and NACA FlameArrestor

N ADDED OVERPRESSURE PROTECTORAND NACA FLAME ARRESTORILLUSTRATION.ILLUSTRATION ADDED

Section 5-5

Subject 5-5-0

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

FIGURE Engine Starting PneumaticRequirements - Engine StartingPneumatic Requirements


Subject 5-5-1 R

Low Ambient Temperatures R DESCRIPTION TITLE UPDATED

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

R

FIGURE Engine Starting PneumaticRequirements - Low AmbientTemperature -40˚C (-40˚F) -- PW 6000series engine

R

Subject 5-5-2 R

Medium Ambient Temperatures R DESCRIPTION TITLE UPDATED

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

R

FIGURE Engine Starting PneumaticRequirements - Medium AmbientTemperature +15˚C (+59˚F) -- PW6000 series engine

R

Subject 5-5-3 R

High Ambient Temperatures R DESCRIPTION TITLE UPDATED

HIGHLIGHTSPage 8

Jun 01/12


LOCATIONS CHGCODE


FIGURE Engine Starting PneumaticRequirements - High AmbientTemperature +50˚C (+122˚F) -- CFM56series engine

R

FIGURE Engine Starting PneumaticRequirements - High AmbientTemperature +38˚C (+100˚F) -- PW6000 series engine

R

Section 5-6

Subject 5-6-0

Ground Pneumatic Power Requirements R ADDED NOTE FOR GROUND PNEUMATICPOWER REQUIREMENTS.

Section 5-8

Subject 5-8-0

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

Section 5-9 N

Subject 5-9-0 N

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

CHAPTER 7

Section 7-8 R

Subject 07-08-00 D

Subject 7-8-1

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

R

Subject 7-8-2

Rigid Pavement Requirements - LCNConversion

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

CHAPTER 8 R

Section 8-0 N

Subject 8-0-0 N

HIGHLIGHTSPage 9

Jun 01/12


LOCATIONS CHGCODE


Scaled Drawings N

FIGURE Scaled Drawing N ILLUSTRATION ADDED

Section 08-01 D

CHAPTER 10 N

Section 10-0 N

Subject 10-0-0 N

Aircraft Rescue and Fire Fighting N

FIGURE Front Page N ILLUSTRATION ADDED

FIGURE Highly Flammable and HazardousMaterials and Components


FIGURE Wheel Safety Area N ILLUSTRATION ADDED

FIGURE Composite Materials N ILLUSTRATION ADDED

FIGURE LG Ground Lock Safety Devices N ILLUSTRATION ADDED

FIGURE Evacuation/Escape Slide/Raft N ILLUSTRATION ADDED

FIGURE Pax/Crew Doors N ILLUSTRATION ADDED

FIGURE Emergency Exit Hatch N ILLUSTRATION ADDED

FIGURE FWD and AFT Lower DeckCargo Doors


FIGURE Control Panels N ILLUSTRATION ADDED

FIGURE APU Access Door N ILLUSTRATION ADDED

FIGURE Aircraft Ground Clearances N ILLUSTRATION ADDED

FIGURE Structural Break-in Points N ILLUSTRATION ADDED

HIGHLIGHTSPage 10

Jun 01/12


LIST OF EFFECTIVE CONTENT

Revision No. 9 - Jun 01/12

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 1

Subject 1-1-0

Purpose R Jun 01/12

CHAPTER 2

Subject 2-1-0

General Airplane Characteristics R Jun 01/12

Subject 2-1-1

General Airplane Characteristics Data R Jun 01/12

Subject 2-2-0

General Aircraft Dimensions R Jun 01/12

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

Subject 2-3-0

Ground Clearances R Jun 01/12

FIGURE Ground Clearances R Jun 01/12

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

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

N Jun 01/12

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

FIGURE Ground Clearances - Aileron Down N Jun 01/12

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

FIGURE Ground Clearances - Slats Extended N Jun 01/12

Subject 2-4-0

Interior Arrangements Dec 01/07

Subject 2-4-1

Typical Configuration Sep 01/10

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

Sep 01/10

L.E.C.Page 1

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

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

Subject 2-5-0

Passenger Compartment Cross-section Sep 01/10

FIGURE Passenger Compartment Cross-section Sep 01/10

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

Sep 01/10

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

Sep 01/10

Subject 2-6-0

Cargo Compartments R Jun 01/12

FIGURE Cargo Compartments - Locations, Dimensions and LoadingCombinations

N Jun 01/12

Subject 2-7-0

Doors Clearances Dec 01/07

Subject 2-7-1

Forward Passenger / Crew Doors Dec 01/07

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

Subject 2-7-2

Emergency Exits Dec 01/07

FIGURE Doors Clearances - Emergency Exits Dec 01/07

Subject 2-7-3

Aft Passenger / Crew Doors Dec 01/07

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

Subject 2-7-4

Forward Cargo Compartment Door Dec 01/07

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

Subject 2-7-5

Aft Cargo Compartment Door Dec 01/07

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

Subject 2-7-7

L.E.C.Page 2

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Main Landing Gear Doors Dec 01/07

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

Subject 2-7-8

Radome Dec 01/07

FIGURE Doors Clearances - Radome Dec 01/07

Subject 2-7-9

APU and Nose Landing Gear Doors Dec 01/07

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

Subject 2-8-0

Escape Slides N Jun 01/12

FIGURE Escape Slides - Location N Jun 01/12

FIGURE Escape Slides - Dimensions N Jun 01/12

Subject 2-9-0

Landing Gear N Jun 01/12

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

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

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

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

Landing Gear Maintenance Pits N Jun 01/12

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

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

Subject 2-10-0

Exterior Lighting N Jun 01/12

FIGURE Exterior Lighting N Jun 01/12




Subject 2-11-0

Antennas and Probes Location N Jun 01/12

L.E.C.Page 3

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Antennas and Probes - Location N Jun 01/12

Subject 2-12-0

Auxiliary Power Unit N Jun 01/12

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

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

Engine and Nacelle N Jun 01/12

FIGURE Power Plant Handling - Major Dimensions - CFM56 SeriesEngine

N Jun 01/12

FIGURE Power Plant Handling - Major Dimensions - CFM56 SeriesEngine

N Jun 01/12

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

FIGURE Power Plant Handling - Thrust Reverser Cowls - CFM56Series Engine

N Jun 01/12

FIGURE Power Plant Handling - Major Dimensions - PW 6000 SeriesEngine

N Jun 01/12

FIGURE Power Plant Handling - Nacelle Dimensions - PW 6000Series Engine

N Jun 01/12

FIGURE Power Plant Handling - Fan Cowls - PW 6000 Series Engine N Jun 01/12

FIGURE Power Plant Handling - Thrust Reverser Halves - PW 6000Series Engine

N Jun 01/12

Subject 2-13-0

Leveling, Symmetry and Alignment N Jun 01/12

FIGURE Location of the Leveling Points N Jun 01/12

Subject 2-14-0

Jacking for Maintenance N Jun 01/12

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

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

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

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

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

Jacking for Wheel Change N Jun 01/12

L.E.C.Page 4

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

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

N Jun 01/12

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

N Jun 01/12

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

N Jun 01/12

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

N Jun 01/12

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

N Jun 01/12

CHAPTER 3

Subject 3-1-0

General Information Dec 01/07

Subject 3-2-0

Payload / Range Dec 01/07

Subject 3-2-1

ISA Conditions Dec 01/07

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

FIGURE Payload / Range - PW 6000 series engine Dec 01/07

Subject 3-3-0

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

Subject 3-3-1


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

Dec 01/07

FIGURE FAR / JAR Take-off Weight Limitation - ISA Conditions --PW 6000 series engine

Dec 01/07

Subject 3-3-2

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

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

Dec 01/07

L.E.C.Page 5

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE FAR / JAR Take-off Weight Limitation - ISA +15˚C(+59˚F) Conditions -- PW 6000 series engine

Dec 01/07

Subject 3-4-0

FAR / JAR Landing Field Length Dec 01/07

Subject 3-4-1


FIGURE FAR / JAR Landing Field Length - CFM56-5B series engine Dec 01/07

FIGURE FAR / JAR Landing Field Length - PW 6000 series engine Dec 01/07

Subject 3-5-0

Final Approach Speed Dec 01/07

FIGURE Final Approach Speed - CFM56-5B8 and CFM56-5B9 seriesengine

Dec 01/07

FIGURE Final Approach Speed - PW 6000 series engine Dec 01/07

CHAPTER 4

Subject 4-1-0

General Information Dec 01/07

Subject 4-2-0

Turning Radii Dec 01/07

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

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

Subject 4-3-0

Minimum Turning Radii Dec 01/07

FIGURE Minimum Turning Radii R Jun 01/12

Subject 4-4-0

Visibility from Cockpit in Static Position R Jun 01/12

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

FIGURE Binocular Visibility Through Windows from Captain EyePosition

N Jun 01/12

Subject 4-5-0

Runway and Taxiway Turn Paths Dec 01/07

L.E.C.Page 6

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Subject 4-5-1

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

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

R Jun 01/12

FIGURE 135˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

N Jun 01/12

Subject 4-5-2

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

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

R Jun 01/12

FIGURE 90˚ Turn - Runway to Taxiway - Judgemental OversteeringMethod

N Jun 01/12

Subject 4-5-3

180˚ Turn on a Runway N Jun 01/12

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

Subject 4-5-4

135˚ Turn - Taxiway to Taxiway Dec 01/07

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

R Jun 01/12

Subject 4-5-5

90˚ Turn - Taxiway to Taxiway Dec 01/07

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

R Jun 01/12

Subject 4-6-0

Runway Holding Bay (Apron) Dec 01/07

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

Subject 4-7-0

Airplane Parking Dec 01/07

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

FIGURE Airplane Parking - Steering Geometry Dec 01/07


L.E.C.Page 7

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE






CHAPTER 5

Subject 5-0-0

Terminal Servicing Sep 01/10

Subject 5-1-0

Airplane Servicing Arrangements Sep 01/10

Subject 5-1-1

Symbols Used on Servicing Diagrams Sep 01/10

Subject 5-1-2

Typical Ramp Layout - Open Apron R Jun 01/12

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

Subject 5-1-3

Typical Ramp Layout - Gate R Jun 01/12

FIGURE Typical Ramp Layout - Gate R Jun 01/12

Subject 5-2-0

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

FIGURE Turn Round Stations - Full Servicing (34 Min.) N Jun 01/12

Subject 5-3-0

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

FIGURE Turn Round Stations - Minimum Servicing (20 Min.) N Jun 01/12

Subject 5-4-0

Ground Service Connections Dec 01/07

Subject 5-4-1

Ground Service Connections Layout R Jun 01/12

L.E.C.Page 8

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Ground Service Connections - Ground Service ConnectionsLayout

R Jun 01/12

Subject 5-4-2

Grounding Points Dec 01/07

FIGURE Ground Service Connections - Grounding Points Dec 01/07

FIGURE Ground Service Connections - Grounding Points Dec 01/07

Subject 5-4-3

Hydraulic System R Jun 01/12

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

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

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

Subject 5-4-4

Electrical System R Jun 01/12

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

Subject 5-4-5

Oxygen System Dec 01/07

Subject 5-4-6

Fuel System R Jun 01/12

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

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

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

FIGURE Ground Service Connections - Overpressure Protector andNACA Flame Arrestor

N Jun 01/12

Subject 5-4-7

Pneumatic System Sep 01/10

Subject 5-4-8

Potable Water System Sep 01/10

FIGURE Ground Service Connections - Potable Water Ground ServicePanel

Sep 01/10

Subject 5-4-9

L.E.C.Page 9

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Oil System Sep 01/10

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

Sep 01/10

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

Sep 01/10

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

Sep 01/10

FIGURE Ground Service Connections - Engine Oil Tank -- PW 6000Series Engine

Sep 01/10

FIGURE Ground Service Connections - IDG Oil Tank -- PW 6000Series Engine

Sep 01/10

FIGURE Ground Service Connections - Starter Oil Tank -- PW 6000Series Engine

Sep 01/10

FIGURE Ground Service Connections - APU Oil Tank Dec 01/07

Subject 5-4-10

Vacuum Toilet System Sep 01/10

FIGURE Ground Service Connections - Waste Water Ground ServicePanel

Sep 01/10

Subject 5-5-0

Engine Starting Pneumatic Requirements R Jun 01/12

FIGURE Engine Starting Pneumatic Requirements - Engine StartingPneumatic Requirements

N Jun 01/12

Subject 5-5-1

Low Ambient Temperatures R Jun 01/12

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

R Jun 01/12

FIGURE Engine Starting Pneumatic Requirements - Low AmbientTemperature -40˚C (-40˚F) -- PW 6000 series engine

R Jun 01/12

Subject 5-5-2

Medium Ambient Temperatures R Jun 01/12

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

R Jun 01/12

L.E.C.Page 10

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Engine Starting Pneumatic Requirements - Medium AmbientTemperature +15˚C (+59˚F) -- PW 6000 series engine

R Jun 01/12

Subject 5-5-3

High Ambient Temperatures R Jun 01/12

FIGURE Engine Starting Pneumatic Requirements - High AmbientTemperature +50˚C (+122˚F) -- CFM56 series engine

R Jun 01/12

FIGURE Engine Starting Pneumatic Requirements - High AmbientTemperature +38˚C (+100˚F) -- PW 6000 series engine

R Jun 01/12

Subject 5-6-0

Ground Pneumatic Power Requirements R Jun 01/12

Subject 5-6-1

Heating Dec 01/07

FIGURE Ground Pneumatic Power Requirements - Heating Dec 01/07

Subject 5-6-2

Cooling Dec 01/07

FIGURE Ground Pneumatic Power Requirements - Cooling Dec 01/07

Subject 5-7-0

Preconditioned Airflow Requirements Dec 01/07

FIGURE Preconditioned Airflow Requirements Dec 01/07

Subject 5-8-0

Ground Towing Requirements R Jun 01/12

FIGURE Ground Towing Requirements Sep 01/10

Subject 5-9-0

De-Icing and External Cleaning N Jun 01/12

CHAPTER 6

Subject 6-1-0

Engine Exhaust Velocities and Temperatures Dec 01/07

Subject 6-1-1

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

L.E.C.Page 11

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

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

Dec 01/07

FIGURE Engine Exhaust Velocities - Ground Idle Power -- PW 6000series engine

Dec 01/07

Subject 6-1-2

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

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

Dec 01/07

FIGURE Engine Exhaust Temperatures - Ground Idle Power -- PW6000 series engine

Dec 01/07

Subject 6-1-3

Engine Exhaust Velocities Contours - Breakaway Power Dec 01/07

FIGURE Engine Exhaust Velocities - Breakaway Power -- CFM56series engine

Dec 01/07

FIGURE Engine Exhaust Velocities - Breakaway Power -- PW 6000series engine

Dec 01/07

Subject 6-1-4

Engine Exhaust Temperatures Contours - Breakaway Power Dec 01/07

FIGURE Engine Exhaust Temperatures - Breakaway Power -- CFM56series engine

Dec 01/07

FIGURE Engine Exhaust Temperatures - Breakaway Power -- PW6000 series engine

Dec 01/07

Subject 6-1-5

Engine Exhaust Velocities Contours - Takeoff Power Dec 01/07

FIGURE Engine Exhaust Velocities - Takeoff Power -- CFM56 seriesengine

Dec 01/07

FIGURE Engine Exhaust Velocities - Takeoff Power -- PW 6000 seriesengine

Dec 01/07

Subject 6-1-6

Engine Exhaust Temperatures Contours - Takeoff Power Dec 01/07

FIGURE Engine Exhaust Temperatures - Takeoff Power -- CFM56series engine

Dec 01/07

L.E.C.Page 12

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Engine Exhaust Temperatures - Takeoff Power -- PW 6000series engine

Dec 01/07

Subject 6-2-0

Airport and Community Noise Dec 01/07

Subject 6-2-1

Noise Data Dec 01/07

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

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

FIGURE Airport and Community Noise - PW 6000 series engine Dec 01/07

Subject 6-3-0

Danger Areas of Engines Dec 01/07

Subject 6-3-1

Ground Idle Power Dec 01/07

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

FIGURE Danger Areas of Engines - PW 6000 series engine Dec 01/07

Subject 6-3-2

Takeoff Power Dec 01/07

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

FIGURE Danger Areas of Engines - PW 6000 series engine Dec 01/07

Subject 6-4-0

APU Exhaust Velocities and Temperatures Dec 01/07

Subject 6-4-1

APU - APIC & GARRETT Dec 01/07

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

Dec 01/07

CHAPTER 7

Subject 7-1-0

General Information May 01/11

FIGURE Aircraft Codes May 01/11

Subject 7-2-0

L.E.C.Page 13

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Landing Gear Footprint May 01/11

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



Subject 7-3-0

Maximum Pavement Loads May 01/11

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



Subject 7-4-0

Landing Gear Loading on Pavement May 01/11

Subject 7-4-1

Landing Gear Loading on Pavement May 01/11

FIGURE Landing Gear Loading on Pavement May 01/11









Subject 7-5-0

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

May 01/11

Subject 7-5-1

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

May 01/11

FIGURE Flexible Pavement Requirements May 01/11

L.E.C.Page 14

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE






FIGURE Flexible Pavement Requirements - Flexible PavementRequirements

May 01/11



Subject 7-6-0

Flexible Pavement Requirements - LCN Conversion May 01/11

Subject 7-6-1

Flexible Pavement Requirements - LCN Conversion May 01/11

FIGURE Flexible Pavement Requirements - LCN Conversion May 01/11









Subject 7-7-0

Rigid Pavement Requirements - Portland Cement Association DesignMethod

May 01/11

Subject 7-7-1

Rigid Pavement Requirements - Portland Cement Association DesignMethod

May 01/11

FIGURE Rigid Pavement Requirements (PCA) May 01/11


L.E.C.Page 15

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE








Subject 7-8-1

Radius of Relative Stiffness Dec 01/07

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

R Jun 01/12

Subject 7-8-2

Rigid Pavement Requirements - LCN Conversion R Jun 01/12

FIGURE Rigid Pavement Requirements - LCN Conversion May 01/11









Subject 7-8-3

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

Subject 7-8-4

Radius of Relative Stiffness Dec 01/07

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

Subject 7-9-0

ACN/PCN Reporting System May 01/11

L.E.C.Page 16

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Subject 7-9-1

Aircraft Classification Number - Flexible Pavement May 01/11

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









Subject 7-9-2

Aircraft Classification Number - Rigid Pavement May 01/11

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









CHAPTER 8

Subject 8-0-0

Scaled Drawings N Jun 01/12

FIGURE Scaled Drawing N Jun 01/12

CHAPTER 10

Subject 10-0-0

L.E.C.Page 17

Jun 01/12


CONTENT CHGCODE

LAST REVISIONDATE

Aircraft Rescue and Fire Fighting N Jun 01/12

FIGURE Front Page N Jun 01/12

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

FIGURE Wheel Safety Area N Jun 01/12

FIGURE Composite Materials N Jun 01/12

FIGURE LG Ground Lock Safety Devices N Jun 01/12

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

FIGURE Pax/Crew Doors N Jun 01/12

FIGURE Emergency Exit Hatch N Jun 01/12

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

FIGURE Control Panels N Jun 01/12

FIGURE APU Access Door N Jun 01/12

FIGURE Aircraft Ground Clearances N Jun 01/12

FIGURE Structural Break-in Points N Jun 01/12

L.E.C.Page 18

Jun 01/12


TABLE OF CONTENTS

1 SCOPE

1-1-0 Purpose

2 AIRCRAFT DESCRIPTION

2-1-0 General Aircraft Characteristics

2-1-1 General Aircraft Characteristics Data

2-2-0 General Aircraft Dimensions

2-3-0 Ground Clearances

2-4-0 Interior Arrangements

2-4-1 Passenger Compartment Layout

2-5-0 Passenger Compartment Cross Section

2-6-0 Cargo Compartments

2-7-0 Door Clearances

2-7-1 Forward Passenger / Crew Doors

2-7-2 Emergency Exits

2-7-3 Aft Passenger / Crew Doors

2-7-4 Forward Cargo Compartment Doors

2-7-5 Aft Cargo Compartment Doors

2-7-7 Main Landing Gear Doors

2-7-8 Radome

2-7-9 APU and Nose Landing Gear Doors

2-8-0 Escape Slides

2-9-0 Landing Gear

2-10-0 Exterior Lighting

2-11-0 Antennas and Probes Location

2-12-0 Power Plant

2-13-0 Leveling, Symmetry and Alignment

2-14-0 Jacking

3 AIRCRAFT PERFORMANCE

3-1-0 General Information

3-2-0 Payload / Range

3-2-1 ISA Conditions

3-3-0 FAR / JAR Takeoff Weight Limitation


T.O.C.Page 1

Jun 01/12


3-3-2 ISA +15˚C (+59˚F) Conditions

3-4-0 FAR / JAR Landing Field Length


3-5-0 Final Approach Speed

4 GROUND MANEUVERING


4-2-0 Turning Radii

4-3-0 Minimum Turning Radii

4-4-0 Visibility from Cockpit in Static Position

4-5-0 Runway and Taxiway Turn Paths

4-5-1 135˚ Turn - Runway to Taxiway


4-5-3 180˚ Turn on a Runway

4-5-4 135˚ Turn - Taxiway to Taxiway


4-6-0 Runway Holding Bay (Apron)

4-7-0 Parking

5 TERMINAL SERVICING

5-0-0 TERMINAL SERVICING

5-1-0 Servicing Arrangements

5-1-1 Symbols Used on Servicing Diagrams

5-1-2 Typical Ramp Layout - Open Apron

5-1-3 Typical Ramp Layout - Gate

5-2-0 Terminal Operations - Full Servicing

5-3-0 Terminal Operation - Transit

5-4-0 Ground Service Connections

5-4-1 Ground Service Connections Layout

5-4-2 Grounding Points

5-4-3 Hydraulic System

5-4-4 Electrical System

5-4-5 Oxygen System

5-4-6 Fuel System

5-4-7 Pneumatic System

5-4-8 Potable Water System

5-4-9 Oil System

5-4-10 Vacuum Toilet System

T.O.C.Page 2

Jun 01/12


5-5-0 Engine Starting Pneumatic Requirements

5-5-1 Low Ambient Temperatures

5-5-2 Medium Ambient Temperatures

5-5-3 High Ambient Temperatures

5-6-0 Ground Pneumatic Power Requirements

5-6-1 Heating

5-6-2 Cooling

5-7-0 Preconditioned Airflow Requirements

5-8-0 Ground Towing Requirements

5-9-0 De-Icing and External Cleaning

6 OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

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

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

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

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

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

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

6-2-0 Airport and Community Noise

6-2-1 Noise Data

6-3-0 Danger Areas of Engines

6-3-1 Ground Idle Power

6-3-2 Takeoff Power

6-4-0 APU Exhaust Velocities and Temperatures

6-4-1 APU

7 PAVEMENT DATA


7-2-0 Landing Gear Footprint

7-3-0 Maximum Pavement Loads

7-4-0 Landing Gear Loading on Pavement


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


7-6-0 Flexible Pavement Requirements - LCN Conversion


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

T.O.C.Page 3

Jun 01/12



7-8-1 Radius of Relative Stiffness

7-8-2 Rigid Pavement Requirements - LCN Conversion

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


7-9-0 ACN/PCN Reporting System

7-9-1 Aircraft Classification Number - Flexible Pavement

7-9-2 Aircraft Classification Number - Rigid Pavement

8 SCALED DRAWINGS

8-0-0 SCALED DRAWINGS

10 AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 AIRCRAFT RESCUE AND FIRE FIGHTING

T.O.C.Page 4

Jun 01/12


SCOPE

1-1-0 Purpose

**ON A/C A318-100

Purpose

1. GeneralThe A318 AIRCRAFT CHARACTERISTICS -- AIRPORT AND MAINTENANCE PLANNING (AC)manual is issued for the A318-100 series aircraft, equipped with wing-tip fences or Sharklets toprovide necessary data to airport operators, airlines and Maintenance/Repair Organizations (MRO)for airport and maintenance facilities planning.

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

The data given in this issue of the A318-100 AC equipped with Sharklets can be subject to changepending completion of the flight test phase. It is given for guidance only and does not constitute acontractual commitment.

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

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

Correspondence concerning this publication should be directed to:

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

1-1-0Page 1

Jun 01/12


AIRCRAFT DESCRIPTION

2-1-0 General Aircraft Characteristics

**ON A/C A318-100

General Airplane Characteristics

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

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

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

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

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

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

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

Usable Fuel Capacity:Fuel available for aircraft propulsion.

Water Volume:Volume of cargo compartment.

2-1-0Page 1

Jun 01/12


2-1-1 General Aircraft Characteristics Data

**ON A/C A318-100

General Airplane Characteristics Data

1. The following table provides characteristics of A318-100 Models, these data are specific to eachWeight Variant:

Aircraft CharacteristicsWV000 WV001 WV002 WV003 WV004

Kilograms 59 400 61 900 63 400 64 900 66 400Maximum Ramp Weight(MRW)Maximum Taxi Weight(MTW)

Pounds130 955 136 466 139 773 143 080 146 387

Kilograms 59 000 61 500 63 000 64 500 66 000Maximum TakeoffWeight (MTOW) Pounds 130 073 135 584 138 891 142 198 145 505

Kilograms 56 000 56 000 57 500 57 500 57 500Maximum LandingWeight (MLW) Pounds 123 459 123 459 126 766 126 766 126 766

Kilograms 53 000 53 000 54 500 54 500 54 500Maximum Zero FuelWeight (MZFW) Pounds 116 845 116 845 120 152 120 152 120 152

Aircraft CharacteristicsWV005 WV006 WV007 WV008

Kilograms 68 400 56 400 61 400 64 400Maximum Ramp Weight(MRW)Maximum Taxi Weight(MTW)

Pounds150 796 124 341 135 364 141 978

Kilograms 68 000 56 000 61 000 64 000Maximum Takeoff Weight(MTOW) Pounds 149 914 123 459 134 482 141 096

Kilograms 57 500 56 000 56 000 56 000Maximum Landing Weight(MLW) Pounds 126 766 123 459 123 459 123 459

Kilograms 54 500 53 000 53 000 53 000Maximum Zero Fuel Weight(MZFW) Pounds 120 152 116 845 116 845 116 845

2. The following table provides characteristics of A318 Models, these data are common to each WeightVariant:

Aircraft CharacteristicsStandard SeatingCapacity

Single-class132

2-1-1Page 1

Jun 01/12


Aircraft CharacteristicsLiters 23 859US gallons 6 303

Kilograms(density =0.785 kg/l)

18 729

Usable Fuel Capacity

Pounds 41 290Cubic meters 257Pressurized Fuselage

Volume (A/C nonequipped)

Cubic feet9 076

Cubic meters 107Passenger CompartmentVolume Cubic feet 3 779

Cubic meters 9Cockpit VolumeCubic feet 318Cubic meters 6.72Usable Volume, FWD

CC Cubic feet 237.3Cubic meters 8.87Usable Volume, AFT CCCubic feet 313.3Cubic meters 5.71Usable Volume, Bulk CCCubic feet 201.6Cubic meters 8.34Water Volume, FWD CCCubic feet 294.5Cubic meters 10.38Water Volume, AFT CCCubic feet 366.6Cubic meters 5.97Water Volume, Bulk CCCubic feet 210.8

2-1-1Page 2

Jun 01/12


2-2-0 General Aircraft Dimensions

**ON A/C A318-100

General Aircraft Dimensions

1. This section provides General Aircraft Dimensions.

2-2-0Page 1

Jun 01/12


**ON A/C A318-100

RELATED TO AIRCRAFT ATTITUDE AND WEIGHT

12.45 m(40.85 ft)

34.10 m(111.88 ft)

4.14

m(1

3.58

ft)

10.25 m(33.63 ft)

5.07 m(16.63 ft)

6.62

m(2

1.72

ft)

7.59 m(24.90 ft)

0.93 m(3.05 ft)

0.50 m(1.64 ft)

8.95 m(29.36 ft)

N_AC_020200_1_0010101_01_03

General Aircraft DimensionsWing Tip Fence (Sheet 1 of 4)

FIGURE-2-2-0-991-001-A01

2-2-0Page 2

Jun 01/12


**ON A/C A318-100


31.45 m(103.18 ft)

8.8 m(28.87 ft)

9.1 m(29.86 ft)

CFM56

PW6000

5.75

m(1

8.86

ft)

3.95

m(1

2.96

ft)

8.32

m(2

7.30

ft)

11.9

3 m

(39.

14 ft

)

4.91

m(1

6.11

ft)

N_AC_020200_1_0010107_01_00

General Aircraft DimensionsWing Tip Fence (Sheet 2 of 4)

FIGURE-2-2-0-991-001-A01

2-2-0Page 3

Jun 01/12


**ON A/C A318-100


4.14

m(1

3.58

ft)

10.25 m(33.63 ft)

5.07 m(16.63 ft)

6.62

m(2

1.72

ft)

12.45 m(40.85 ft)

35.80 m(117.45 ft)

7.59 m(24.90 ft)

0.93 m(3.05 ft)

0.50 m(1.64 ft)

8.95 m(29.36 ft)

3.79 m(12.43 ft)

2.43 m(7.97 ft)

N_AC_020200_1_0010102_01_01

General Aircraft DimensionsSharklet (Sheet 3 of 4)

FIGURE-2-2-0-991-001-A01

2-2-0Page 4

Jun 01/12


**ON A/C A318-100


31.45 m

(103.18 ft)

8.8 m

(28.87 ft)

9.1 m

(29.86 ft)

CFM56

PW6000

5.75

m

(18.

86 ft

)

3.95

m

(12.

96 ft

)

8.32

m

(27.

30 ft

)

11.9

3 m

(39.

14 ft

)

4.91

m

(16.

11 ft

)

21.06 m

(69.09 ft)

3.22 m

(10.56 ft)

1.64 m

(5.38 ft)

1.61 m

(5.28 ft)

16.2

9 m

(53.

44 ft

)

N_AC_020200_1_0010108_01_00

General Aircraft DimensionsSharklet (Sheet 4 of 4)

FIGURE-2-2-0-991-001-A01

2-2-0Page 5

Jun 01/12


2-3-0 Ground Clearances

**ON A/C A318-100

Ground Clearances

1. This section gives the height of various points of the aircraft, above the ground, for different aircraftconfigurations.Dimensions in the tables are approximate and will vary with tire type, weight and balance and otherspecial conditions.

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

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

2-3-0Page 1

Jun 01/12


**ON A/C A318-100

A

CG 25% FWD CG 15% FWD CG 15.8%

A/C JACKED FDL

AFT CG 32%

3.452.081.791.935.936.080.660.781.742.733.173.512.20

BC1C2D1D2

E (CFM)E (PW)

FF1F2F3G

3.372.011.711.895.866.040.600.721.692.683.123.472.16

3.442.051.761.855.916.000.610.731.672.663.093.432.13

3.372.001.711.875.866.020.590.711.672.673.113.452.14

3.422.031.741.845.895.990.600.721.652.653.08

4.132.712.432.436.586.581.241.362.263.253.68

3.72H 3.70 3.61 3.67

3.42 4.012.11 2.713.60 4.13

NOTE:

12.89J 12.88 12.74 12.85 12.74 13.203.92K1 3.88 3.83 3.86 3.82 4.384.89K2 4.86 4.80 4.83 4.79 5.355.62L 5.60 5.47 5.57 5.46 5.933.97N 3.91 3.92 3.90 3.90 4.544.22P 4.14 4.23 4.13 4.21 4.964.91Q 4.91 4.76 4.87 4.75 5.20

AFT CG 33.9%

P C1 BD1 E

N

C2G HD2 Q J

L F F1 F2 F3 K1 K2

13.558.897.977.9721.5921.594.074.467.41

10.6612.0713.168.8913.5543.3114.3717.5519.4614.8916.2717.06

11.226.665.716.0419.3219.651.972.365.418.6910.1011.226.9211.8141.8012.5315.7217.9112.8013.8115.58

11.066.565.616.1419.2319.751.942.335.488.7610.2011.327.02

12.0442.1612.6615.8518.2712.8013.5515.98

11.296.735.776.07

19.3919.682.002.405.488.73

10.1411.256.99

11.8441.8012.5715.7517.9512.8613.8815.62

11.066.595.616.2019.2319.821.972.365.548.79

10.2411.387.09

12.1442.2612.7315.9418.3712.8313.5816.11

11.326.825.876.33

19.4619.952.172.565.718.9610.4011.527.22

12.2042.2912.8616.0418.4413.0213.8516.11

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

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

A/CCONFIG−URATION

39 t 59 tMRW

64 tMRW

= 4.60 m(15.09 ft)

A

N_AC_020300_1_0010101_01_05

Ground ClearancesFIGURE-2-3-0-991-001-A01

2-3-0Page 2

Jun 01/12


**ON A/C A318-100

A

CG 25% FWD CG 15% FWD CG 15.8%

A/C JACKED FDL

AFT CG 32%

3.452.081.791.935.936.080.660.781.742.733.173.512.20

BC1C2D1D2

E (CFM)E (PW)

FF1F2F3G

3.372.011.711.895.866.040.600.721.692.683.123.472.16

3.442.051.761.855.916.000.610.731.672.663.093.432.13

3.372.001.711.875.866.020.590.711.672.673.113.452.14

3.422.031.741.845.895.990.600.721.652.653.08

4.132.712.432.436.586.581.241.362.263.253.68

3.72H 3.70 3.61 3.67

3.42 4.012.11 2.713.60 4.13

NOTE:

12.89J 12.88 12.74 12.85 12.74 13.204.19K1 4.15 4.10 4.13 4.09 4.656.83K2 6.80 6.74 6.77 6.73 7.295.62L 5.60 5.47 5.57 5.46 5.933.97N 3.91 3.92 3.90 3.90 4.544.22P 4.14 4.23 4.13 4.21 4.964.91Q 4.91 4.76 4.87 4.75 5.20

AFT CG 33.9%

13.558.897.977.9721.5921.594.074.467.41

10.6612.0713.168.8913.5543.3115.2623.9219.4614.8916.2717.06

11.226.665.716.0419.3219.651.972.365.418.6910.1011.226.9211.8141.8013.4222.0817.9112.8013.8115.58

11.066.565.616.1419.2319.751.942.335.488.7610.2011.327.02

12.0442.1613.5522.2118.2712.8013.5515.98

11.296.735.776.07

19.3919.682.002.405.488.73

10.1411.256.99

11.8441.8013.4522.1117.9512.8613.8815.62

11.066.595.616.2019.2319.821.972.365.548.79

10.2411.387.09

12.1442.2613.6222.3118.3712.8313.5816.11

11.326.825.876.33

19.4619.952.172.565.718.9610.4011.527.22

12.2042.2913.7522.4118.4413.0213.8516.11

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

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

A/CCONFIG−URATION

39 t 59 tMRW

64 tMRW

= 4.60 m(15.09 ft)

L F F1 F2 F3 K1 K2

P A C1 B E C2 G D2 H Q JD1

N_AC_020300_1_0270101_01_00

N

Ground ClearancesGround Clearances with Sharklets

FIGURE-2-3-0-991-027-A01

2-3-0Page 3

Jun 01/12


**ON A/C A318-100

m ft m ft m ft

A

B

C

D

2.05

2.77

2.81

3.65

1.99

2.71

2.75

3.60

1.96

2.68

2.72

3.54

6.73 6.53 6.43

11.6111.8111.98

9.09

9.22

8.89

9.02

8.79

8.92

HEIGHT FROM GROUND

MAXIMUM RAMPWEIGHT AFT CG

AC DB

E

F

G

2.1

2.59

3.05

2.03

2.53

2.99

2.0

2.49

2.94 9.659.8110.01

6.89

8.50

6.66

8.30

6.56

8.17

EF G

N_AC_020300_1_0060101_01_00

MAXIMUM RAMPWEIGHT FWD CG

A/C IN MAINTENANCECONFIGURATION

MID CG

Ground ClearancesFlaps and Flap Track Fairings When Flaps Fully Extended

FIGURE-2-3-0-991-006-A01

2-3-0Page 4

Jun 01/12


**ON A/C A318-100

m ft m ft m ft

H

J

K

2.68

3.09

3.48

2.62

3.02

3.42

2.59

3.0

3.39

8.79 8.60 8.50

10.14

11.42

9.91

11.22

9.84

11.12

HEIGHT FROM GROUND

JHK

N_AC_020300_1_0070101_01_00




MID CG

Ground ClearancesFlap Track Fairings Up

FIGURE-2-3-0-991-007-A01

2-3-0Page 5

Jun 01/12


**ON A/C A318-100

ML

m ft m ft m ft

L

M

4.19

3.84

4.13

3.78

4.07

3.74

13.75 13.55 13.35

12.60 12.40 12.27

HEIGHT FROM GROUND

N_AC_020300_1_0080101_01_00




MID CG

Ground ClearancesAileron Down

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

2-3-0Page 6

Jun 01/12


**ON A/C A318-100

m ft m ft m ft

P

Q 4.60

4.48

4.35

4.54

4.42

4.29

4.50

4.38

4.26

15.09 14.89 14.76

14.70

14.27

14.50

14.07

14.37

13.98

HEIGHT FROM GROUND

R

S

T

U

4.21

4.07

4.01

4.15

4.01

3.94

4.12

3.98

3.92

13.81 13.62 13.52

13.35

13.16

13.16

12.93

13.06

12.86

3.75 3.69 3.6612.30 12.11 12.01

T U V WQ R SPN

N 4.57

4.37

4.51

4.31

4.26

4.45

14.99 14.80 13.98

14.34 14.14 14.60

N_AC_020300_1_0090101_01_00




MID CG

V

W

Ground ClearancesAileron Up and Spoilers 1 to 5 Extended

FIGURE-2-3-0-991-009-A01

2-3-0Page 7

Jun 01/12


**ON A/C A318-100

m ft m ft m ft

X 2.54

2.96

3.05

2.48

2.90

2.99

2.5

2.91

2.99

8.33 8.14 8.20

9.71

10.01

9.51

9.81

9.55

9.81

HEIGHT FROM GROUND

C’Y

F’

X ZE’ G’

A’

B’

C’

D’

E’

3.35

3.35

3.61

3.29

3.29

3.55

3.28

3.28

3.53

10.99 10.79 10.76

10.99

11.84

10.79

11.65

10.76

11.58

3.61

3.86

3.86

3.55

3.80

3.80

3.53

3.77

3.77

11.84 11.65 11.58

12.66

12.66

12.47

12.47

12.37

12.37

4.10 4.04 4.013.45 13.25 13.12

D’A’ B’

Y

Z

N_AC_020300_1_0100101_01_00




MID CG

F’

G’

Ground ClearancesSlats Extended

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

2-3-0Page 8

Jun 01/12


2-4-0 Interior Arrangements

**ON A/C A318-100

Interior Arrangements

1. This section gives the standard interior arrangements configuration.

2-4-0Page 1

Jun 01/12


2-4-1 Passenger Compartment Layout

**ON A/C A318-100

Typical Configuration

1. This section gives the typical interior configuration.

2-4-1Page 1

Jun 01/12


**ON A/C A318-100

A AA

ITE

MD

ES

IGN

AT

ION

GG

ALL

EY

(2)

LLA

VA

TO

RY

(2)

AA

TT

EN

DA

NT

SE

AT

(4)

LL

AG

G

FW

D P

AS

SE

NG

ER

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

FW

D P

AS

SE

NG

ER

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

132

SE

AT

S A

LL T

OU

RIS

T C

LAS

S29

/30

in P

ITC

H. 6

AB

RE

AS

T. 3

.3

N_AC_020401_1_0010101_01_01

Typical ConfigurationTypical Configuration Single-Class, High Density

FIGURE-2-4-1-991-001-A01

2-4-1Page 2

Jun 01/12


**ON A/C A318-100

ITE

MD

ES

IGN

AT

ION

8 S

UP

ER

FIR

ST

CLA

SS

PA

SS

EN

GE

R S

EA

TS

(10

7 T

OT

AL)

LLA

VA

TO

RY

(2)

GG

ALL

EY

(3)

AA

TT

EN

DA

NT

SE

AT

(3)

SE

AT

PIT

CH

ES

:

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

FW

D P

AS

SE

NG

ER

99 E

CO

NO

MY

CLA

SS

FIR

ST

38

inE

CO

NO

MY

32

in

AF

T P

AS

SE

NG

ER

EM

ER

GE

NC

Y E

XIT

/CR

EW

DO

OR

FW

D P

AS

SE

NG

ER

/CR

EW

DO

OR

G

A AL

ALG

L

N_AC_020401_1_0070101_01_00

Typical ConfigurationTypical Configuration Two-Class

FIGURE-2-4-1-991-007-A01

2-4-1Page 3

Jun 01/12


2-5-0 Passenger Compartment Cross Section

**ON A/C A318-100

Passenger Compartment Cross-section

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

2-5-0Page 1

Jun 01/12


**ON A/C A318-100

3.95(155.51)

Cargo CompartmentFloor

CABINFLOOR

Top of cargoCompartment

AircraftDatum

Windows

2.64

(103.94)

2.13(83.86)

1.60(62.99)

1.24(48.82)

NOTE: DIMENSIONS m (in)

0.49(19.29)

0.52(20.47)

N_AC_020500_1_0010101_01_01

3.45(135.83)

3.68

(144.88)

1.42(55.91)

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

2-5-0Page 2

Jun 01/12


**ON A/C A318-100


1.24

(48.

9)2.

21(8

7)

6 ABREAST−WIDER AISLE

4.14

(163

)

3.95(155.5)

3.64(143)

1.50(59)

0.64(25)

1.50(59)

0.432(17)

N_AC_020500_1_0050101_01_00

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

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

2-5-0Page 3

Jun 01/12


**ON A/C A318-100


6 ABREAST−WIDER SEAT

3.95(155.5)

3.64(143)

1.58(62)

0.48(19)

1.58(62)

1.24

(48.

9)2.

21(8

7)

4.14

(163

)

0.457(18)

N_AC_020500_1_0050102_01_02

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

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

2-5-0Page 4

Jun 01/12


**ON A/C A318-100


4 ABREAST−FIRST CLASS

3.95(155.5)

1.24

(48.

9)2.

21(8

7)

4.14

(163

)

3.59(141)

0.69(27)

1.45(57)

1.45(57)

(22.6)0.57

N_AC_020500_1_0060101_01_00

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

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

2-5-0Page 5

Jun 01/12


2-6-0 Cargo Compartments

**ON A/C A318-100

Cargo Compartments

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

2-6-0Page 1

Jun 01/12


**ON A/C A318-100

FW

D C

AR

GO

CO

MP

AR

TM

EN

T

6.07

m

(238

.98

in)

2.68

m

(105

.51

in)

1.28

m

(50.

39 in

)

AF

T C

AR

GO

CO

MP

AR

TM

EN

T BU

LK C

AR

GO

CO

MP

AR

TM

EN

T

1.28

m

(50.

39 in

)

FR

24A

FR

34F

R47

FR

54/

FR

60F

R65

N_AC_020600_1_0010101_01_00

Cargo CompartmentsLocations, Dimensions and Loading Combinations

FIGURE-2-6-0-991-001-A01

2-6-0Page 2

Jun 01/12


2-7-0 Door Clearances

**ON A/C A318-100

Doors Clearances

1. This section gives doors clearances.

2-7-0Page 1

Jun 01/12


2-7-1 Forward Passenger / Crew Doors

**ON A/C A318-100

Forward Passenger / Crew Doors

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

2-7-1Page 1

Jun 01/12


**ON A/C A318-100

CRITICAL

CLEARANCE LIMIT

0.61 m(2 ft)

0.48 m(1 ft 6.88 in)

2.54 m(8 ft 3.99 in)

5.02 m(16 ft 5.62 in)

1.8 m(5 ft 10.8 in) 0.81 m

(2 ft 7.8 in)

1.85 m(6 ft 0.82 in)

SEECHAPTER

2.375 m(7 ft 9.48 in)

2−3

CL

CLCL

0.03 m(1.18 in)

N_AC_020701_1_0010101_01_00

Doors ClearancesForward Passenger / Crew Doors

FIGURE-2-7-1-991-001-A01

2-7-1Page 2

Jun 01/12


2-7-2 Emergency Exits

**ON A/C A318-100

Emergency Exits

1. This section gives emergency exits doors clearances.

2-7-2Page 1

Jun 01/12


**ON A/C A318-100

(FRAME 47)

NOTE: ESCAPE SLIDE COMPARTMENT DOOROPENS ON WING UPPER SURFACE.

(FROM NOSE)

CL

12.89 m(42 ft 3.46 in)

0.56 m

0.47 m(1ft 6.49 in)

1.23 m(4 ft 0.42 in)

0.2 m(7.87 in)

FWD

0.9 m(2 ft 11.4 in)

0.495 m(1ft 7.48 in)

(TOP OF FLOOR)

0.12 m(4.72 in)

SEESECTION

2−3

B B

A

A

B

B

CL

(1ft 10 in)

A A

N_AC_020702_1_0020101_01_00

Doors ClearancesEmergency Exits

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

2-7-2Page 2

Jun 01/12


2-7-3 Aft Passenger / Crew Doors

**ON A/C A318-100

Aft Passenger / Crew Doors

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

2-7-3Page 1

Jun 01/12


**ON A/C A318-100

1.79 m(5 ft 10.46 in)

0.81 m(2 ft 7.88 in)

0.58 m(1 ft 10.8 in)

CRITICALCLEARANCE

LIMIT

23.52 m(77 ft 1.98 in)

(FROM NOSE)

2.44 m(8 ft)

1.85 m(6 ft 0.82 in)

0.6 m(1 ft 11.6 in)

(1.18 in)0.03 m

FWD

SEE

2−3CHAPTER

A A

A

A

N_AC_020703_1_0010101_01_00

Doors ClearancesAft Passenger / Crew DoorsFIGURE-2-7-3-991-001-A01

2-7-3Page 2

Jun 01/12


2-7-4 Forward Cargo Compartment Doors

**ON A/C A318-100

Forward Cargo Compartment Door

1. This section gives forward cargo compartment door clearances.

2-7-4Page 1

Jun 01/12


**ON A/C A318-100

7.89

(25 ft 10.6 in)

1.33 m(4 ft 4.35 in)

1.24 m(4 ft 0.81 in)

3.945 m(12 ft 11.3 in)

1.495 m(4 ft 10.84 in)

0.26 m(10.23 in)

(FROM NOSE)

2−3

SEECHAPTER

A

A

FWD

A A

2.9 m(9 ft 6.16 in)

N_AC_020704_1_0010101_01_00

Doors ClearancesForward Cargo Compartment Door

FIGURE-2-7-4-991-001-A01

2-7-4Page 2

Jun 01/12


2-7-5 Aft Cargo Compartment Doors

**ON A/C A318-100

Aft Cargo Compartment Door

1. This section gives Aft cargo compartment door clearances.

2-7-5Page 1

Jun 01/12


**ON A/C A318-100

1.23 m(4 ft 0.42 in)

3.945 m(12 ft 11.3 in)

1.43 m(4 ft 8.29 in)

2−3

SEECHAPTER

A A

FWD

1 m

(3 ft 3.36 in)

19.96 m

(62 ft 2.44 in)

1.33 m(4 ft 4.35 in)

(FROM NOSE)

FWD

A

A

N_AC_020705_1_0010101_01_01

Doors ClearancesAft Cargo Compartment DoorFIGURE-2-7-5-991-001-A01

2-7-5Page 2

Jun 01/12


2-7-7 Main Landing Gear Doors

**ON A/C A318-100

Main Landing Gear Doors

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

2-7-7Page 1

Jun 01/12


**ON A/C A318-100

13.97 m(45 ft 10 in)

GROUND LINE

0.207 m(8.14 in)

0.485 m

(1 ft 7.09 in)

NOTE: VALUE OF CG: 25% RC.AIRCRAFT

1.23 m(4 ft 0.42 in)

0.14 m(5.51 in)

84°

1.942 m

(6 ft 4.45 in)

1.826 m(5 ft 11.88 in)

A

1.761 m(5 ft 9.32 in)

A

N_AC_020707_1_0010101_01_02

Doors ClearancesMain Landing Gear Doors

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

2-7-7Page 2

Jun 01/12


2-7-8 Radome

**ON A/C A318-100

Radome

1. This section gives the radome clearances.

2-7-8Page 1

Jun 01/12


**ON A/C A318-100

0.63 m(2 ft 0.79 in)

1.54 m(5 ft 0.62 in)

STA 3500FR1

65°

N_AC_020708_1_0010101_01_00

Doors ClearancesRadome

FIGURE-2-7-8-991-001-A01

2-7-8Page 2

Jun 01/12


2-7-9 APU and Nose Landing Gear Doors

**ON A/C A318-100

APU and Nose Landing Gear Doors

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

2-7-9Page 1

Jun 01/12


**ON A/C A318-100

1.5

m(4

ft 1

1 in

)

FR80

FR84

3.23

m(1

0 ft

7.16

in)

3.86

m(1

2 ft

7.96

in)

1.4

m(4

ft 7

.11

in)

NOTE: VALUE OF CG: 25% RC.

N_AC_020709_1_0010101_01_00

Doors ClearancesAPU and Nose Landing Gear Doors

FIGURE-2-7-9-991-001-A01

2-7-9Page 2

Jun 01/12


2-8-0 Escape Slides

**ON A/C A318-100

Escape Slides

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

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

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

2-8-0Page 1

Jun 01/12


**ON A/C A318-100

FWD CABIN ESCAPE SLIDE

OFF WING ESCAPE SLIDE

N_AC_020800_1_0010101_01_00

AFT CABINESCAPE SLIDE

Escape SlidesLocation

FIGURE-2-8-0-991-001-A01

2-8-0Page 2

Jun 01/12


**ON A/C A318-100

EMERGENCY DESCENT DEVICETHROUGH WINDOW OPENING

GRID EQUALS 1 m (3.28 ft) IN REALITY

N_AC_020800_1_0020101_01_00

Escape SlidesDimensions

FIGURE-2-8-0-991-002-A01

2-8-0Page 3

Jun 01/12


2-9-0 Landing Gear

**ON A/C A318-100

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 STA 5394/FR 9and 8077/FR 20.

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

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

2. Main Landing Gear

A. Twin wheel

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

3. Nose Landing Gear

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

4. Nose Wheel Steering

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

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

2-9-0Page 1

Jun 01/12


5. Landing Gear Servicing Points

A. General

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

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

B. Charging Pressure

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

6. Braking

A. General

The four main wheels are equipped with carbon multidisc brakes.

The braking system is electrically controlled and hydraulically operated.

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

B. In-Flight Wheel Braking

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

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

2-9-0Page 2

Jun 01/12


**ON A/C A318-100

ACTUATINGCYLINDER

UNLOCK

LOCK STAY

MAIN

SIDE STAY

TORQUELINK

SHOCK

ACTUATOR

FITTING

ABSORBER

D

E

A

MAIN DOOR SHOWN OPEN IN GROUND MAINTENANCE POSITION.NOTE:

MAIN DOOR(HYDRAULICALLY OPERATED)

FIXEDRAMPS

UPLOCKROLLER

ADJUSTABLERAMP

STEPS

FIXEDFAIRING

HINGEDFAIRING

HINGED FAIRING(MECHANICALLY OPERATED)

PROXIMITY SENSORS

DOOR ACTUATING CYLINDER

A

B

C

N_AC_020900_1_0020101_01_00

D

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

FIGURE-2-9-0-991-002-A01

2-9-0Page 3

Jun 01/12


**ON A/C A318-100

DOORACTUATINGCYLINDER

FLAG

TOP FILLING AND CHARGING CONNECTION MS28889

BOTTOM FILLING ANDCHARGING CONNECTIONMS28889

LOCKSTAYACTUATINGCYLINDER

GROUND LOCK SLEEVE

FLAG

BC

ED

LOCKINGPIN

LOCKINGPIN

EXAMPLEN_AC_020900_1_0020102_01_00

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

FIGURE-2-9-0-991-002-A01

2-9-0Page 4

Jun 01/12


**ON A/C A318-100

Y=COMPRESSED

EXTENDED

58.4

0 %

AM

C

3 795 mm

3 453 mm(135.94 in) 80°30

RETRACTIONANGLE

(36.50 in)927.10 mm

2 868.70 mm(112.94 in)

2 265 mm(89.17 in)

X= 20 252.50 mm(797.34 in)

469.90 mm(18.50 in)

(149.41 in)

N_AC_020900_1_0030101_01_00

Landing GearMain Landing Gear Dimensions - Twin Wheel

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

2-9-0Page 5

Jun 01/12


**ON A/C A318-100

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

N_AC_020900_1_0040101_01_00

Landing GearNose Landing Gear (Sheet 1 of 2)

FIGURE-2-9-0-991-004-A01

2-9-0Page 6

Jun 01/12


**ON A/C A318-100

TOWING LEVER

(NOSE WHEEL STREERINGNORMAL POSITION

(TOWING POSITION)SAFETY PIN

(NOSE WHEEL STEERING DEACTIVATED)TOWING POSITION

E

DOOR HINGE

NLG DOOR

NLG DOORSAFETY PIN

FLAG

LH SYMMETRICALRH SHOWN

FLAG

DOWNLOCKSAFETY PIN

LOCKSTAY

BC

D

OPERATIONAL)

N_AC_020900_1_0040102_01_00

CONNECTION MS28889FILLING AND CHARGING

Landing GearNose Landing Gear (Sheet 2 of 2)

FIGURE-2-9-0-991-004-A01

2-9-0Page 7

Jun 01/12


**ON A/C A318-100

N_AC_020900_1_0050101_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-2-9-0-991-005-A01

2-9-0Page 8

Jun 01/12


**ON A/C A318-100

Landing Gear Maintenance Pits

1. Description

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

All dimensions shown are minimum dimensions with zero clearances.

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

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

the landing gear.

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

2-9-0Page 9

Jun 01/12


**ON A/C A318-100

MA

IN J

AC

KIN

G P

OIN

T

= =

==

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)

17.7

2 m

(58.

14 ft

)M

AIN

JA

CK

ING

PO

INT

2.95

m(9

.68

ft)

3.76

m(1

2.34

ft)

2.5

m(8

.20

ft)7.

59 m

(24.

90 ft

)

3.79

m(1

2.43

ft)

6.49

m(2

1.29

ft)

FROM X0

17.8

7 m

(58.

63 ft

)

FW

D J

AC

KIN

G P

OIN

T

N_AC_020900_1_0200101_01_00

Landing Gear Maintenance PitsMaintenance Pit EnvelopesFIGURE-2-9-0-991-020-A01

2-9-0Page 10

Jun 01/12


**ON A/C A318-100

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)

17

.87

m(5

8.63

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_0210101_01_00

Landing Gear Maintenance PitsMaintenance Pit EnvelopesFIGURE-2-9-0-991-021-A01

2-9-0Page 11

Jun 01/12


2-10-0 Exterior Lighting

**ON A/C A318-100

Exterior Lighting

1. General

This section gives the location of the aircraft exterior lighting.

EXTERIOR LIGHTINGITEM DESCRIPTION

1 RIGHT NAVIGATION LIGHT (GREEN)

2 TAIL NAVIGATION LIGHT (WHITE)

3 LEFT NAVIGATION LIGHT (RED)

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

9 UPPER ANTI-COLLISION LIGHT/BEACON (RED)

10 LOWER ANTI-COLLISION LIGHT/BEACON (RED)

11 WING STROBE LIGHT (HIGH INTENSITY, WHITE)

12 TAIL STROBE LIGHT (HIGH INTENSITY, WHITE)

13 WING/ENGINE SCAN LIGHT

14 WHEEL WELL LIGHT (DOME)

15 CARGO COMPARTMENT FLOOD LIGHT

2-10-0Page 1

Jun 01/12


**ON A/C A318-100

10

12

11

1

3

11

6 75 4

13

8

2

89

1

3

N_AC_021000_1_0010101_01_00

RH

LH

RH

LH

Exterior LightingFIGURE-2-10-0-991-001-A01

2-10-0Page 2

Jun 01/12


**ON A/C A318-100

N_AC_021000_1_0020101_01_00

2

1 3

55

7


2-10-0Page 3

Jun 01/12


**ON A/C A318-100

N_AC_021000_1_0030101_01_00

109

1313

11 11

12

4

6


2-10-0Page 4

Jun 01/12


**ON A/C A318-100

CEILING LIGHT

SPOT LIGHT

GROUND

8 8

1514

15

N_AC_021000_1_0170101_01_00

EXAMPLE FOR LIGHT N° 15


2-10-0Page 5

Jun 01/12


2-11-0 Antennas and Probes Location

**ON A/C A318-100

Antennas and Probes Location

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

2-11-0Page 1

Jun 01/12


**ON A/C A318-100

RADIO ALTIMETER(2)

RADIO ALTIMETER(1)

VHF(2)

MARKER

DME(2)

STATIC PROBE(1)

DME(1)

STATIC PROBE(2)

PITOT PROBE(1)

PITOT PROBE(3)

TAT PROBE

GLIDE

LOC

EMERGENCY STATIC PROBE

WEATHER RADAR

VHF(1)

AOA SENSOR(1)

EMERGENCY STATIC PROBE

TAT PROBE

PITOT PROBE(2)

STATIC PROBE(2)

STATIC PROBE(1)

AOA SENSOR(2)

GPS(2)

GPS(1)

TCAS BOTTOM

ATC(1)

TCAS TOP VHF(3)

ELT

ATC(2)

VOR

HF

ATC(3)

AOA SENSOR(3) STBYATC(4)

NOTE: DEPENDING ON AIRCRAFT CONFIGURATION

ADF(1)

N_AC_021100_1_0010101_01_00

Antennas and ProbesLocation

FIGURE-2-11-0-991-001-A01

2-11-0Page 2

Jun 01/12


2-12-0 Power Plant

**ON A/C A318-100

Auxiliary Power Unit

1. General

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

2. Controls and Indication

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

2-12-0Page 1

Jun 01/12


**ON A/C A318-100

FRONT FIREWALLREAR FIREWALL

LH FIREWALL

RH FIREWALL

AIR INTAKECUT OUT

AIR INTAKE FIXEDON ACCESS DOOR

CUT OUT SEALED WITHLABYRINTH GASKET

CUT OUT SEALEDWITH LABYRINTH GASKET

UPPERFIREWALL

VENTLOUVER

UPPERFIREWALL

A

FR84/STA32824

FR80/STA31174

Z310

315AL

316AR

N_AC_021200_1_0010101_01_00

A B

Auxiliary Power UnitAccess Doors

FIGURE-2-12-0-991-001-A01

2-12-0Page 2

Jun 01/12


**ON A/C A318-100

BLEED AIR LINE

APU SUSPENSION(7 RODS)

GENERATOR

AFT APU MOUNT

EXHAUST MUFFLER

OIL COOLER

OIL COOLER OUTLET

AIR INTAKE DUCT

FIXED DIVERTER

AIR INTAKE HOUSING

FIREWALL

/

LH FORWARD APU MOUNT

APU−FUEL−LINE

FIRE EXINGUISINGBOTTLE

STA33992 FR87

/FR84

/FR80

/FR76

STA32824

STA31174

STA30011

316AR

315AL314AR

B

N_AC_021200_1_0020101_01_00

Auxiliary Power UnitGeneral Layout

FIGURE-2-12-0-991-002-A01

2-12-0Page 3

Jun 01/12


**ON A/C A318-100

Engine and Nacelle

1. Engine and Nacelle - CFM Engine

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

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

2. Engine and Nacelle - PW Engine

A. EngineThe engine is a two spool, axial flow, high bypass ratio turbofan powerplant for subsonic sevice.The main modules of the engine are:- compressor section- combustion section- turbine section- accessory drives (gear box) section.The four stage Low Pressure Compressor (LPC) is driven by a three stage Low Pressure Turbine(LPT) and the six stage High Pressure Compressor (HPC) by a single stage High PressureTurbine (HPT).

2-12-0Page 4

Jun 01/12


The PW6000 incorporates a Full Authority Digital Engine Control (FADEC) which governs allengine functions, including power management.

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

2-12-0Page 5

Jun 01/12


**ON A/C A318-100

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_0110101_01_00

Power Plant HandlingMajor Dimensions - CFM56 Series Engine

FIGURE-2-12-0-991-011-A01

2-12-0Page 6

Jun 01/12


**ON A/C A318-100

FAN COWL

CENTERBODY

FANREVERSER

6°

PRIMARYNOZZLE

8.8 m(28.9 in)

0.93 m

(3.1 ft)

1.3 m(4.3 ft)

1.2 m(3.9 ft)

1.2 m(3.9 ft)

DISTANCE FROMTHE NOSE

0.33 m(1.1 ft)

2.3 m(7.5 ft)

ENGINE AIRINLET COWL

A

A

B

B

C

C

D

D

0.57 m(1.9 ft)

2.07 m(6.8 ft)

B B

1.2 m(3.9 ft)

1.8 m(5.9 ft)

2.1 m(6.9 ft)

BLOCKER DOOREXTENDED

1.9 m(6.2 ft)

A A

D DC C

1.6 m(5.2 ft)

N_AC_021200_1_0120101_01_00

Power Plant HandlingMajor Dimensions - CFM56 Series Engine

FIGURE-2-12-0-991-012-A01

2-12-0Page 7

Jun 01/12


**ON A/C A318-100

A

0.55 m(1.8 ft)

C

B

A B C

VIEWCOWLING

AFT

VIEWCOWLING

FWD

m (ft)

42°27

55°15

40°40

52°56

1.8 (5.9)

2.0 (6.6)

1.8 (5.9 )

2.0 (6.6)

1.5 (4.9)

1.8 (5.9)

1.4 (4.6)

1.7 (5.6)

1.3 (4.3)

1.7 (5.6)

1.3 (4.3)

1.6 (5.2)

NOTE: APPROXIMATE DIMENSIONS

N_AC_021200_1_0130101_01_00

Power Plant HandlingFan Cowls - CFM56 Series Engine

FIGURE-2-12-0-991-013-A01

2-12-0Page 8

Jun 01/12


**ON A/C A318-100

3.7 m(12.1 ft)

3.3 m(10.8 ft)

(3 ft)0.9 m

CAUTIONDO NOT ACTUATE SLATS:

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

APPROXIMATE DIMENSIONSNOTE:

GROUND

0.5 m(1.6 ft)

0.7 m(2.3 ft)

1 m(3.3 ft)

N_AC_021200_1_0140101_01_00

45°35°

1 m(3.3 ft)

Power Plant HandlingThrust Reverser Cowls - CFM56 Series Engine

FIGURE-2-12-0-991-014-A01

2-12-0Page 9

Jun 01/12


**ON A/C A318-100

3 746 mm(147.50 in)

3 355 mm(132.10 in)

1 245 mm(49.02 in)

1 146 mm(45.12 in)

142 mm(5.59 in)

ACCESSORYDRIVE

FAN ANDBOOSTER

COMPRESSOR

COMBUSTOR

TURBINE SECTION

2 002 mm(78.82 in)

(82.60 in)2 098 mm

(45.31 in)1 151 mm

1 590 mm(62.60 in)

A

BN_AC_021200_1_0150101_01_00

A

Power Plant HandlingMajor Dimensions - PW 6000 Series Engine

FIGURE-2-12-0-991-015-A01

2-12-0Page 10

Jun 01/12


**ON A/C A318-100

V

ALL SIZES GIVEN ON THIS ILLUSTRATION ARE APPROXIMATE

1.43 m

(4.7 ft)

W U V

2 m(6.6 ft)

0.9 m(3 ft)

1.05 m(3.4 ft)

2.08 m(6.8 ft)

0.96 m(3.1 ft)

1.07 m(3.5 ft)

1.63 m(5.3 ft)

0.76 m(2.5 ft)

0.81 m(2.7 ft)

1.12 m(3.7 ft)

0.56 m(1.8 ft)

0.56 m(1.8 ft)

W

D

D

C

C

B

B

A

A

1.66 m

(5.44 ft)

1.24 m

(4.1 ft)

8.85 m

(29 ft)

DISTANCEFROM THE

NOSE

AIR INTAKECOWL FAN COWL

THRUSTREVERSER

COMMON NOZZLEASSY

1.03 m

(3.37 ft)

NOTE:

A−A

B−B

C−C

D−D

N_AC_021200_1_0160101_01_00

U

Power Plant HandlingNacelle Dimensions - PW 6000 Series Engine

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

2-12-0Page 11

Jun 01/12


**ON A/C A318-100

27°

53°

A B C D

GROUND

3.05 m(10 ft)3.85 m

(12.63 ft)

0.90 m(2.95 ft)1.65 m(5.41 ft)

D + 0.84 m(D + 2.8 ft)

0.7 m(2.3 ft)

D + 0.2 m(D + 0.7 ft)

A

B

D

C

APPROXIMATE DIMENSIONSONLY MAIN DIMENSIONS SHOWN

NOTE:

N_AC_021200_1_0170101_01_00

°

Power Plant HandlingFan Cowls - PW 6000 Series Engine

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

2-12-0Page 12

Jun 01/12


**ON A/C A318-100

GROUND

OPEN

CLOSED

(6.82 ft)2.08 m

A

CB

45°

A B C

3.5 m(11.48 ft)

1.1 m(3.6 ft)

1.08 m(3.5 ft)

N_AC_021200_1_0180101_01_00

°

Power Plant HandlingThrust Reverser Halves - PW 6000 Series Engine

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

2-12-0Page 13

Jun 01/12


2-13-0 Leveling, Symmetry and Alignment

**ON A/C A318-100

Leveling, Symmetry and Alignment

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

2. Precise LevelingFor precise leveling, it is necessary to install sighting rods in the receptacles located under thefuselage (points 11 and 12 for longitudinal leveling) and under the wings (points 2LH and 2RH forlateral leveling) and use a sighting tube. With the aircraft on jacks, adjust the jacks until thereference marks on the sighting rods are aligned in the sighting plane (aircraft level).

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

2-13-0Page 1

Jun 01/12


**ON A/C A318-100

FR28

FR34

FR54 FR57

11

12

2LH

2RH

RIB10

RIB10

N_AC_021300_1_0010101_01_00

Location of the Leveling PointsFIGURE-2-13-0-991-001-A01

2-13-0Page 2

Jun 01/12


2-14-0 Jacking

**ON A/C A318-100

Jacking for Maintenance

1. Jacking for Maintenance

A. General

The A318 aircraft can be jacked:- at not more than the maximum permitted aircraft weight for jacking (53 000 kg (116 845

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

environment.

B. Primary Jacking Points

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

STA4862/RIB9 and the rear of spar-datum.

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

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

jacking adaptor.Wing jack pads are ground equipment.

C. Auxiliary Jacking Points - Safety Stay

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

The safety stay is not used to lift the aircraft.

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

2. Jack Design

In fully retracted position (jack stroke at minimum), the height of the jack may be placed beneaththe airplane under the most adverse conditions, namely, tires deflated and shock absorbersdepressurized.

2-14-0Page 1

Jun 01/12


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

Jacking Point Location Z Maximum Permitted Load

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

6 800 daN(15 287 lbf)

Wing Jacking Point-0.828 m(-2.72 ft)

28 500 daN(64 071 lbf)

Safety Stay-0.748 m(-2.45 ft)

2 000 daN(4 496 lbf)

The maximum permitted aircraft weight for the jacking procedure is 53 000 kg (116 845 lb).Centerline at 4.6 mm (0.18 in) parallel to the ground.

2-14-0Page 2

Jun 01/12


**ON A/C A318-100

FWD JACKINGPOINT

SAFETYPOINT

26.44 m

15.18 m

2.74 m(8.99 ft)

6.5 m

CL

(49.80 ft)

(86.75 ft)

WING JACKINGPOINT

(21.33 ft)

WING JACKINGPOINT

N_AC_021400_1_0010101_01_00

Jacking for MaintenanceJacking Point Location

FIGURE-2-14-0-991-001-A01

2-14-0Page 3

Jun 01/12


**ON A/C A318-100

POINT A DETAIL

Z−1 979.8Z−1 987

FR8

A

SPHERICAL RADIUS19 mm (0.75 in)

A

N_AC_021400_1_0030101_01_00

B

B

Jacking for MaintenanceForward Jacking Point

FIGURE-2-14-0-991-003-A01

2-14-0Page 4

Jun 01/12


**ON A/C A318-100

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)

A

A

EXAMPLE

B

B

N_AC_021400_1_0560101_01_00

Jacking for MaintenanceWing Jacking Points

FIGURE-2-14-0-991-056-A01

2-14-0Page 5

Jun 01/12


**ON A/C A318-100

Z−744.932

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

X =

35

106

A

Z−729.441

A

N_AC_021400_1_0570101_01_00

(4.95 in)

125.67 mm

Jacking for MaintenanceSafety Stay

FIGURE-2-14-0-991-057-A01

2-14-0Page 6

Jun 01/12


**ON A/C A318-100

M

L

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

NOTE:

L M

1 560 mm(61.42 in)

2 846 mm(112.05 in)

3 047 mm(119.96 in)

2 620 mm(103.15 in)

3 772 mm(148.50 in)

3 859 mm(151.93 in)

1 931 mm(76.02 in)

3 082 mm(121.34 in)

3 169 mm(124.76 in)

1 545 mm(60.83 in)

2 761 mm(108.70 in)

2 892 mm(113.86 in)

N

AIRCRAFT ON WHEELS, SHOCK ABSORBERS DEFLATED AND

AIRCRAFT ON WHEELS, NLG SHOCK ABSORBER DEFLATED

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

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

FLAT TIRES

AND RETRACTED LANDING GEARS

AND FLAT TIRES

N

N_AC_021400_1_0040101_01_00

Jacking for MaintenanceJacking Design

FIGURE-2-14-0-991-004-A01

2-14-0Page 7

Jun 01/12


**ON A/C A318-100

Jacking for Wheel Change

1. General

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

The maximum permitted aircraft weight for jacking is 53 000 kg (116 845 lb).

2. Main Gear Jacking

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

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

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

3. Nose Gear Jacking

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

2-14-0Page 8

Jun 01/12


**ON A/C A318-100

NOTE:

45 x 16 R20

552 mm(21.73 in)

38 mm(1.5 in)

DIA. BALL

25 mm (1 in)

218 mm(8.58 in)

180 mm(7.09 in)

ON THE RIM

200 mm(7.87 in)FULLY

RETRACTED

49 x 19 R20

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

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

600 mm(23.62 in)FULLY

EXTENDED

N_AC_021400_1_0120101_01_00

FLAT TIRES

INFLATED TIRES

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

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

2-14-0Page 9

Jun 01/12


**ON A/C A318-100

N_AC_021400_1_0130101_01_00

MLG TIRE 49 x 19 R20

643 mm(25.32 in)

TWIN WHEEL TRACK

927 mm(36.5 in)

DOUBLE FLAT MLG TIRES

MIN

FORK

CONTOUR OF TIRES ON GROUND

CANTILEVERARM

25 mm(1 in)

1 620 mm(63.78 in)

25 mm(1 in)MIN

25 mm(1 in) APPROX

409 mm(16.1 in)

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

ON RIM)

552 mm(21.73 in)

FWD

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

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

2-14-0Page 10

Jun 01/12


**ON A/C A318-100

32

80 90 100 110 120 130 140 150 (x1 000 lbs)

AIRCRAFT GROSS WEIGHT

30

28

26

22

20

18

16

1435 40 45 50 55 60 65 70 (x1 000 kg)

LOA

D A

T J

AC

KIN

G P

OIN

T (

x1 0

00 k

g)

24

CG POSITION15.0% MAC18.7% MAC25.0% MAC31.0% MAC37.0% MAC

N_AC_021400_1_0140101_01_00

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

FIGURE-2-14-0-991-014-A01

2-14-0Page 11

Jun 01/12


**ON A/C A318-100

APPROX326 mm

(12.83 in)38 mm(1.5 in)

DIA. BALLSAE AS 33559

25 mm(1 in)

128 mm(5.04 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:

500 mm (19.69 in)

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

INFLATED TIRESFLAT TIRES

198 mm(7.8 in)

FWD

N_AC_021400_1_0150101_01_00

A

A

Landing Gear Jacking for Wheel ChangeNLG Jacking - Point LocationFIGURE-2-14-0-991-015-A01

2-14-0Page 12

Jun 01/12


**ON A/C A318-100

12

10

8

6

4

2

14

35 40 45 50 55 60 65 70

CG POSITION15.0% MAC18.7% MAC25.0% MAC31.0% MAC37.0% MAC

80 90 100 110 120 130 140 150 (x1 000 lbs)

AIRCRAFT GROSS WEIGHT

(x1 000 kg)

LOA

D A

T J

AC

KIN

G P

OIN

T (

x1 0

00 k

g)

N_AC_021400_1_0160101_01_00

Landing Gear Jacking for Wheel ChangeLoads at NLG Jacking PointsFIGURE-2-14-0-991-016-A01

2-14-0Page 13

Jun 01/12


AIRCRAFT PERFORMANCE


**ON A/C A318-100

General Information

1. This section gives standard day temperatures.

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

Section 3-3 represents FAR take-off runway length requirements at ISA and ISA +15˚C (+59˚F) forCFM56 and PW 6000 series engine conditions for FAA certification.

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

Section 3-5 indicates final approach speeds.

Standard day temperatures for the altitudes shown are tabulated below:

Standard day temperatures for the altitude

Altitude Standard Day Temperature

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

3-1-0Page 1

Jun 01/12


3-2-0 Payload / Range

**ON A/C A318-100

Payload / Range

1. Payload / Range

3-2-0Page 1

Jun 01/12



**ON A/C A318-100

ISA Conditions

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

3-2-1Page 1

Jun 01/12


**ON A/C A318-100

50 40 30 20 10 0

20 10 0

(100

0 lb

)(1

000

kg)

PA

YLO

AD

200

NM

(37

0 K

M)

DIV

ER

SIO

N30

MIN

UT

ES

HO

LD A

T 1

500

ftA

PP

RO

AC

H A

ND

LA

ND

ING

010

0020

0030

0040

00

7000

6000

5000

4000

3000

2000

1000

0R

AN

GE

(KM

)

RA

NG

E(N

M)

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LYT

HE

AP

PR

OV

ED

VA

LUE

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

NO

TE

:

CR

UIS

E C

ON

DIT

ION

SIS

A +

10°

M =

0.7

635

000

/39

000

ftIN

TE

RN

AT

ION

AL

RE

SE

RV

ES

:E

N R

OU

TE

10%

FLI

GH

T T

IME

OV

ER

SH

OO

T

59t

63t

68t

107

PA

SS

EN

GE

RS

N_AC_030201_1_0010101_01_00

Payload / RangeCFM56 series engine

FIGURE-3-2-1-991-001-A01

3-2-1Page 2

Jun 01/12


**ON A/C A318-100

50 40 30 20 10 0

20 10 0

(100

0 lb

)(1

000

kg)

PA

YLO

AD

200

NM

(37

0 K

M)

DIV

ER

SIO

N30

MIN

UT

ES

HO

LD A

T 1

500

ftA

PP

RO

AC

H A

ND

LA

ND

ING

010

0020

0030

0040

00

7000

6000

5000

4000

3000

2000

1000

0R

AN

GE

(KM

)

RA

NG

E(N

M)

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LYT

HE

AP

PR

OV

ED

VA

LUE

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

NO

TE

:

CR

UIS

E C

ON

DIT

ION

SIS

A +

10°

M =

0.7

635

000

/39

000

ftIN

TE

RN

AT

ION

AL

RE

SE

RV

ES

:E

N R

OU

TE

10%

FLI

GH

T T

IME

OV

ER

SH

OO

T

59t

63t

68t

107

PA

SS

EN

GE

RS

N_AC_030201_1_0020101_01_00

Payload / RangePW 6000 series engine

FIGURE-3-2-1-991-002-A01

3-2-1Page 3

Jun 01/12


3-3-0 FAR / JAR Takeoff Weight Limitation

**ON A/C A318-100

FAR / JAR Take-off Weight Limitation

1. FAR / JAR Take-off Weight Limitation

3-3-0Page 1

Jun 01/12



**ON A/C A318-100

ISA Conditions

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

3-3-1Page 1

Jun 01/12


**ON A/C A318-100

30

40

50

60

70

80

90 200

190

180

170

160

150

140

130

120

110

100

90

80

704

1

6 8 10 12 14

2 3 4 5

16

RUNWAY LENGTH

1000 ft

1000 m

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

NOTE:

864

02

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 ft

)

N_AC_030301_1_0010101_01_00

1000 kg

TA

KE

−O

FF

WE

IGH

T

1000 lb

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

FIGURE-3-3-1-991-001-A01

3-3-1Page 2

Jun 01/12


**ON A/C A318-100

30

40

50

60

70

80

90 200

190

180

170

160

150

140

130

120

110

100

90

80

704

1

6 8 10 12 14

2 3 4 5

16

RUNWAY LENGTH

1000 ft

1000 m


NOTE:

2 4 6

8

0

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 ft

)

N_AC_030301_1_0020101_01_00

1000 kg

TA

KE

−O

FF

WE

IGH

T

1000 lb

FAR / JAR Take-off Weight LimitationISA Conditions -- PW 6000 series engine

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

3-3-1Page 3

Jun 01/12


3-3-2 ISA +15˚C (+59˚F) Conditions

**ON A/C A318-100

ISA +15˚C (+59˚F) Conditions

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

3-3-2Page 1

Jun 01/12


**ON A/C A318-100

30

40

50

60

70

80

90 200

190

180

170

160

150

140

130

120

110

100

90

80

704

1

6 8 10 12 14

2 3 4 5

16

RUNWAY LENGTH

1000 ft

1000 m


NOTE:

864

02

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 ft

)

N_AC_030302_1_0010101_01_00

1000 kg

TA

KE

−O

FF

WE

IGH

T

1000 lb

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

FIGURE-3-3-2-991-001-A01

3-3-2Page 2

Jun 01/12


**ON A/C A318-100

30

40

50

60

70

80

90 200

190

180

170

160

150

140

130

120

110

100

90

80

704

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

)

8

642

N_AC_030302_1_0020101_01_00

1000 kg

TA

KE

−O

FF

WE

IGH

T

1000 lb

FAR / JAR Take-off Weight LimitationISA +15˚C (+59˚F) Conditions -- PW 6000 series engine

FIGURE-3-3-2-991-002-A01

3-3-2Page 3

Jun 01/12


3-4-0 FAR / JAR Landing Field Length

**ON A/C A318-100

FAR / JAR Landing Field Length

1. FAR / JAR Landing Field Length

3-4-0Page 1

Jun 01/12



**ON A/C A318-100

ISA Conditions

1. This section gives the landing field length.

3-4-1Page 1

Jun 01/12


**ON A/C A318-100

LENGTH(1000 m)

LANDING FIELD(1000 ft)


NOTE:

12

10

8

6

4

2 1.0

1.5

2.0

2.5

3.0

3.5

35 40 45 50 55 60 65

1401301201101009080

GROSS WEIGHT(1000 kg)

GROSS WEIGHT(1000 lb)

02468

AIRFIELD ELEVATION(1000 ft)

N_AC_030401_1_0010101_01_00

FAR / JAR Landing Field LengthCFM56-5B series engine

FIGURE-3-4-1-991-001-A01

3-4-1Page 2

Jun 01/12


**ON A/C A318-100

12

10

8

6

4

265605550454035

2

1.5

2.0

2.5

3.0

3.5

86420

LENGTH(1000 m)LENGTH

(1000 ft)

LANDING FIELD


NOTE:


PRESSURE ALTITUDE(1000 ft)

80 90 100 110 120 130 140GROSS WEIGHT

(1000 lb)

N_AC_030401_1_0020101_01_00

FAR / JAR Landing Field LengthPW 6000 series engine

FIGURE-3-4-1-991-002-A01

3-4-1Page 3

Jun 01/12


3-5-0 Final Approach Speed

**ON A/C A318-100

Final Approach Speed

1. This section gives the final approach speed.

3-5-0Page 1

Jun 01/12


**ON A/C A318-100


NOTE:

90

100

110

120

130

140

35 40 45 50 55 60 65

1401301201101009080



C.A.S (Kts)

N_AC_030500_1_0010101_01_00

Final Approach SpeedCFM56-5B8 and CFM56-5B9 series engine

FIGURE-3-5-0-991-001-A01

3-5-0Page 2

Jun 01/12


**ON A/C A318-100


NOTE:

90

100

110

120

130

140

35 40 45 50 55 60 65

1401301201101009080



C.A.S (Kts)

N_AC_030500_1_0020101_01_00

Final Approach SpeedPW 6000 series engine

FIGURE-3-5-0-991-002-A01

3-5-0Page 3

Jun 01/12


GROUND MANEUVERING


**ON A/C A318-100

General Information

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

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

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

4-1-0Page 1

Jun 01/12


4-2-0 Turning Radii

**ON A/C A318-100

Turning Radii

1. This section gives the turning radii.

4-2-0Page 1

Jun 01/12


**ON A/C A318-100

R6

R4

R5

R3

R2

R1

NOTE:

TURN TYPE:

1. ASYMMETRIC THRUST DIFFERENTIAL BRAKING

FOR STEERING DIMENSION TABLE SEE SHEET 2.

N_AC_040200_1_0010101_01_02

10.25 m(33.63 ft)

50°

60°

70°

(PIVOTTING ON ONE MAIN GEAR).

2. SYMMETRIC THRUST NO BRAKING.

7.59 m(24.9 ft)

Turning Radii, No Slip AngleFIGURE-4-2-0-991-001-A01

4-2-0Page 2

Jun 01/12


**ON A/C A318-100

MA

XIM

UM

RA

MP

WE

IGH

T

EF

FE

CT

IVE

ST

EE

RIN

G A

NG

LE(d

eg)

mft

ft

ft

m

mm

ft

mft

mft

R6

TH

SR

5R

3N

LGR

2LM

LG

mft

R1

RM

LG

ST

EE

RIN

G

(deg

)A

NG

LEW

ING

TIP

FE

NC

ES

HA

RK

LET

R4

− W

ING

NO

SE

TY

PE

TU

RN

OF

75 (

MA

X)

7065605550454025 3020

70.3

8.2

270.

6

1.3

2.3

3.4

4.6

6.1

7.7

9.7

19.8

15.4

26.1

211

.03637394043465055708310

3

21.2

6972757983879399118

132

152

22.0

7215

.852

18.2

60

66.6

62.2

57.6

52.9

48.2

43.4

38.6

24.1

19.3

8.9

9.9

11.0

12.2

13.7

15.3

17.3

27.3

23.0

33.7

2932364045505790 75111

48111520253265 5186

11.3

11.8

12.3

13.1

14.0

15.2

16.7

21.5

25.4

31.3

21.9

22.9

24.0

25.2

26.6

28.2

30.2

35.8

40.2

46.5

22.8

23.7

24.8

26.0

27.4

29.1

31.1

36.7

41.0

47.3

757881859095102

120

135

155

16.0

16.2

16.6

17.2

17.9

18.8

20.0

24.0

27.5

33.0

525355565962667990108

18.7

19.2

19.9

20.7

21.7

22.9

24.5

29.1

32.9

38.6

6163656871758095108

127

29.0

22 2 2 2 2 2 2 2 2 2 2

3512

.261

107

33.8

19.8

6540

18.7

32.7

33.5

110

21.7

7126

.487

75 (

MA

X)

7065605550

71.8

7.8

0.3

1.2

2.2

3.3

4.6

6.0

10.9

20.9

21.7

7115

.751

18.1

59

67.3

62.8

57.9

53.1

48.3

8.8

9.7

10.9

12.2

13.6

11.3

11.7

12.3

13.0

14.0

21.8

22.7

23.9

25.1

26.5

22.6

23.6

24.7

26.0

27.4

7477818590

15.9

16.2

16.6

17.1

17.8

5253555658

18.6

19.2

19.9

20.7

21.7

61636568711 1 1 1 1 1

261

363738404346

687175788287

2932364045

47111520

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

:

N_AC_040200_1_0020101_01_01

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 AngleFIGURE-4-2-0-991-002-A01

4-2-0Page 3

Jun 01/12


4-3-0 Minimum Turning Radii

**ON A/C A318-100

Minimum Turning Radii

1. This section gives the minimum turning radii.

4-3-0Page 1

Jun 01/12


**ON A/C A318-100

R6

R3

R5

R4

10.3 m

PAVEMENTWIDTH FOR180° TURN

MINIMUM

(34 ft)

STEERINGANGLE 75°

A

EFFECTIVETURN

Y

NOTE:MEASURED FROM OUTSIDE FACE OF TIRE.MODEL 100 TURN DIMENSION SHOWN.THEORETICAL CENTER OF TURNFOR MINIMUM TURNING RADIUS.SLOW CONTINUOUS TURNING.APPROXIMATELY IDLE THRUSTON BOTH ENGINES.

NOSE GEAR RADII TRACK R3,

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

TYPEOF

TURN

1

2

STEERINGANGLE(DEG)

75 (MAX)

75 (MAX)

EFFECTIVESTEERING

ANGLE

71.8°

70.3°

m

m

ft

ft

Y

3.4

3.7

11

12

A

19.0

19.4

62

64

R3NLG

10.9

11.0

36

36

R4 WINGWING TIPFENCE

20.9

21.2

68

69

SHARKLET

21.7

22.0

71

72

R5NOSE

15.7

15.8

51

52

R6THS

18.1

18.2

59

60

NO DIFFERENTIAL BRAKING.DRY SURFACE.

N_AC_040300_1_0010101_01_02

OUTSIDE FACE OF TIRE

Minimum Turning RadiiFIGURE-4-3-0-991-001-A01

4-3-0Page 2

Jun 01/12


4-4-0 Visibility from Cockpit in Static Position

**ON A/C A318-100

Visibility from Cockpit in Static Position

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

4-4-0Page 1

Jun 01/12


**ON A/C A318-100

30°

20°

10.14 m(33 ft 3.24 in)

5.07 m(16 ft 7.56 in)

VISUAL ANGLES IN VERTICALPLANE THROUGH PILOTEYE POSITION.

NOT TO BE USED FORLANDING APPROACH VISIBILITY

DIMENSIONS ARE APPROXIMATE

2.41 m(7 ft 10.92 in)4.56 m

(14 ft 11.52 in)

111°

133°

CAPTAIN FIELD OF VIEW

133°

111°

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

VISUAL ANGLES IN HORIZONTALPLANE THROUGH PILOTEYE POSITION.

FIRST OFFICERFIELD OF VIEW

0.53 m(1 ft 8.88 in)

46°

32°

33°

25°

32°

25°

VISUAL ANGLES IN PLANEPERPENDICULAR TOLONGITUDINAL AXIS.

46°

33°

WITH HEAD MOVED125 mm (5 in) OUTBOARD

NOTE:PILOT EYE POSITION WHEN PILOT’S EYES ARE IN LINE WITH THE RED AND WHITE BALLS.

ZONE THAT CANNOT BE SEEN

N_AC_040400_1_0010101_01_03

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

4-4-0Page 2

Jun 01/12


**ON A/C A318-100

FIR

ST

OF

FIC

ER

FIX

ED

WIN

DO

WF

IRS

T O

FF

ICE

RS

LID

ING

WIN

DO

WF

IRS

T O

FF

ICE

RW

IND

SH

IELD

CA

PT

AIN

WIN

DS

HIE

LDC

AP

TA

IN S

LID

ING

WIN

DO

WC

AP

TA

INF

IXE

D W

IND

OW

PIL

OT

EY

E P

OS

ITIO

N(C

AP

TA

IN P

OS

ITIO

N)

AS

580

B

A32

0

CA

PT

AIN

FIE

LD O

F V

IEW

SH

OW

N.

FIR

ST

OF

FIC

ER

FIE

LD O

F V

IEW

SY

MM

ET

RIC

AL.

EX

AM

PLE

: WH

EN

CA

PT

AIN

TU

RN

S H

IS H

EA

D B

Y 8

0° L

EF

T, V

ISIB

ILIT

YW

ILL

BE

35°

UP

AN

D 2

5° D

OW

N T

HR

OU

GH

TH

E S

LID

ING

WIN

DO

W F

RA

ME

.

35°

30°

20°

10°

0° 10°

20°

25°

110°

100°

90°

80°

70°

50°

40°

30°

20°

10°

0°10

°20

°40

°50

°60

°80

°90

°10

0°13

0°12

0°60

°30

°70

°11

0°

N_AC_040400_1_0050101_01_00

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

4-4-0Page 3

Jun 01/12


4-5-0 Runway and Taxiway Turn Paths

**ON A/C A318-100

Runway and Taxiway Turn Paths

1. Runway and Taxiway Turn Paths.

4-5-0Page 1

Jun 01/12



**ON A/C A318-100

135˚ Turn - Runway to Taxiway

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

4-5-1Page 1

Jun 01/12


**ON A/C A318-100

15 m(50 ft)

RUNWAY CENTERLINE

TURN R = 30 m(100 ft)

FILLET R = 16.5 m(55 ft)

TAXIWAYCENTERLINE

FAA LEAD−IN FILLET

L = 45 m (150 ft)

APPROX 5.7 m(19 ft)

30 m(100 ft)

NOTE: FAA GROUP III FACILITIES.

NLG PATH

MLG PATH

N_AC_040501_1_0010101_01_02

135˚ Turn - Runway to TaxiwayCockpit Over Centerline Method

FIGURE-4-5-1-991-001-A01

4-5-1Page 2

Jun 01/12


**ON A/C A318-100

RUNWAY CENTERLINE

TURN R = 30 m(100 ft)



L = 45 m (150 ft)

APPROX 3.2 m(10 ft)

TAXIWAYCENTERLINE

30 m


N_AC_040501_1_0110101_01_00

NLG PATH

MLG PATH

15 m(50 ft)

(100 ft)

135˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

FIGURE-4-5-1-991-011-A01

4-5-1Page 3

Jun 01/12



**ON A/C A318-100

90˚ Turn - Runway to Taxiway

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

4-5-2Page 1

Jun 01/12


**ON A/C A318-100

APPROX 6.9 m(22 ft)


TURN R = 30 m(100 ft)

RUNWAY CENTERLINE

FAA LEAD−IN FILLETL = 45 m (150 ft)

30 m(100 ft)

TAXIWAY CENTERLINE

15 m(50 ft)


NLG PATH

MLG PATH

N_AC_040502_1_0010101_01_02

90˚ Turn - Runway to TaxiwayCockpit Over Centerline Method

FIGURE-4-5-2-991-001-A01

4-5-2Page 2

Jun 01/12


**ON A/C A318-100

APPROX 9.3 m(30 ft)


TURN R = 30 m(100 ft)

RUNWAY CENTERLINE


TAXIWAY CENTERLINE


NLG PATH

MLG PATH

30 m(100 ft)

15 m(50 ft)

N_AC_040502_1_0080101_01_00

90˚ Turn - Runway to TaxiwayJudgemental Oversteering Method

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

4-5-2Page 3

Jun 01/12


4-5-3 180˚ Turn on a Runway

**ON A/C A318-100

180˚ Turn on a Runway

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

4-5-3Page 1

Jun 01/12


**ON A/C A318-100

30 m(100 ft)

NOTE: TYPE 1 VALUES.

7.4 m(24 ft) 3 m

(10 ft)

RUNWAY CENTERLINE

R3 = 10.9 m(36 ft)

R5 = 15.8 m(52 ft)

R4

N_AC_040503_1_0050101_01_00

NLG PATH

WINGTIP PATH:

NOSE PATH

MLG PATH

WINGTIP FENCES:R4 = 20.9 m (69 ft)SHARKLETS:R4 = 21.7 m (71 ft)

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

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

4-5-3Page 2

Jun 01/12


**ON A/C A318-100

30 m(100 ft)

NOTE: TYPE 1 VALUES.

RUNWAY CENTERLINE

6.23 m(20 ft)

4.76 m(16 ft)

25°

N_AC_040503_1_0050102_01_00

NLG PATH

WINGTIP PATH:

NOSE PATH

MLG PATH

WINGTIP FENCES:R4 = 20.9 m (69 ft)SHARKLETS:R4 = 21.7 m (71 ft)

R3 = 10.9 m(36 ft)

R5 = 15.8 m(52 ft)

R4

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

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

4-5-3Page 3

Jun 01/12



**ON A/C A318-100

135˚ Turn - Taxiway to Taxiway

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

4-5-4Page 1

Jun 01/12


**ON A/C A318-100


L = 45 m (150 ft)

APPROX 6.3 m(21 ft)

NLG PATH

MLG PATH

TAXIWAY CENTERLINE

NOTE: FAA GROUP III FACILITIES

TAXIWAY CENTERLINE

(100 ft)


TURN R = 30 m

N_AC_040504_1_0010101_01_02

15 m(50 ft)

15 m(50 ft)

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

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

4-5-4Page 2

Jun 01/12


**ON A/C A318-100

NLG PATH

MLG PATH

TAXIWAY CENTERLINE

NOTE: FAA GROUP III FACILITIES

TAXIWAY CENTERLINE

FILLET R = 16.5 m

TURN R = 30 m


APPROX 3.1 m(10 ft)

15 m(50 ft)

15 m(50 ft)

N_AC_040504_1_0010102_01_00

(55 ft)

(100 ft)

L = 45 m (150 ft)

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

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

4-5-4Page 3

Jun 01/12



**ON A/C A318-100

90˚ Turn - Taxiway to Taxiway

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

4-5-5Page 1

Jun 01/12


**ON A/C A318-100

15 m(50 ft)

TAXIWAY CENTERLINE


NLG PATH

MLG PATHTAXIWAY CENTERLINE

APPROX 6.4 m(21 ft)


TURN R = 30 m(100 ft)

FAA LEAD−IN FILLETL = 45 m (150 ft) 15 m

(50 ft)

N_AC_040505_1_0010101_01_02

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

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

4-5-5Page 2

Jun 01/12


**ON A/C A318-100

TAXIWAY CENTERLINE


NLG PATH

MLG PATHTAXIWAY CENTERLINE

APPROX 9.3 m(30 ft)


TURN R = 30 m(100 ft)


15 m(50 ft)

15 m(50 ft)

N_AC_040505_1_0010102_01_00

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

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

4-5-5Page 3

Jun 01/12


4-6-0 Runway Holding Bay (Apron)

**ON A/C A318-100

Runway Holding Bay (Apron)

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

4-6-0Page 1

Jun 01/12


**ON A/C A318-100

6.1 m(20 ft)

RUNWAY CENTERLINETAXIWAY

CENTERLINE

6.1 m(20 ft)

190 m(625 ft)

23 m(75 ft)

45 m(150 ft)

HOLDING POINT

12.2 m(40 ft)

90 m(300 ft)61 m

(200 ft)

N_AC_040600_1_0010101_01_02

Runway Holding Bay (Apron)FIGURE-4-6-0-991-001-A01

4-6-0Page 2

Jun 01/12


4-7-0 Parking

**ON A/C A318-100

Airplane Parking

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

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

4-7-0Page 1

Jun 01/12


**ON A/C A318-100

0

20

40

80

120

140

160

180

200

100

60

0

10

20

30

40

50

60

0

10 20 30 40 50 60 70 80 90

300280260240220200180160140120100806040200

DISTANCE ALONG TERMINAL (m)

DISTANCE ALONG TERMINAL (ft)

NOTE: ± 75° NOSE WHEEL STEERING (POWER OUT).± 95° NOSE WHEEL STEERING (PUSH BACK, PUSH OUT).3.05 m (10 ft) TRAVEL WITH NOSE WHEEL STRAIGHT AHEAD BEFORE AND AFTER

PARKED POSITION.

4.5 m (15 ft) BUILDING CLEARANCE FOR NOSE−IN PARKING.7.5 m (25 ft) BUILDING CLEARANCE FOR OTHER PARKING POSITIONS.7.5 m (25 ft) AIRPLANE TO AIRPLANE CLEARANCE DURING PARKING MANOEUVRES.LIAISE WITH USER AIRLINE FOR SPECIFIC PLANNED OPERATION PROCEDURE.

DISTANCE OUTFROM TERMINAL

(ft) (m)

PARALLEL PARKPOWER OUT

45° ENTRYPOWER OUT

90° ENTRYPUSH OUT

45° ENTRYPUSH OUT

STRAIGHT ENTRYPUSH BACK

N_AC_040700_1_0010101_01_00

Airplane ParkingMinimum Parking Space Requirements

FIGURE-4-7-0-991-001-A01

4-7-0Page 2

Jun 01/12


**ON A/C A318-100

35.95 m(117 ft 11.4 in)

48.94 m(160 ft 6.86 in)

STRAIGHT ENTRY−PUSH BACK

N_AC_040700_1_0020101_01_01

Airplane ParkingSteering Geometry

FIGURE-4-7-0-991-002-A01

4-7-0Page 3

Jun 01/12


**ON A/C A318-100

48.94 m(160 ft 6.86 in)

57.56 m(188 ft 10.2 in)

PARALLEL IN−POWER OUT

N_AC_040700_1_0030101_01_01


FIGURE-4-7-0-991-003-A01

4-7-0Page 4

Jun 01/12


**ON A/C A318-100

53.52 m(175 ft 6.96 in)

43.7 m(143 ft 4.32 in)

90° ENTRY−PUSH OUT

N_AC_040700_1_0040101_01_01


FIGURE-4-7-0-991-004-A01

4-7-0Page 5

Jun 01/12


**ON A/C A318-100

41.55 m(136 ft 3.72 in)

58.61 m(192 ft 3.36 in)

45° ENTRY IN−POWER OUT

N_AC_040700_1_0050101_01_01


FIGURE-4-7-0-991-005-A01

4-7-0Page 6

Jun 01/12


**ON A/C A318-100

31.07 m(101 ft 11.16 in)

41.57 m(136 ft 4.56 in)

45° ENTRY−PUSH OUT

N_AC_040700_1_0060101_01_01


FIGURE-4-7-0-991-006-A01

4-7-0Page 7

Jun 01/12


**ON A/C A318-100

27.4 m(89 ft 10.8 in)

13.7 m(44 ft 10.8 in)

3.05 m

NOTE: 73.2° EFFECTIVE STEERING ANGLE.

END OF RUNWAY

EDGE OFRUNWAY

44.1 m(46 ft 3.6 in)

24.4 m(79 ft 10.8 in)

REF(10 ft)

REF3.05 m(10 ft) REF

3.05 m(10 ft)

N_AC_040700_1_0070101_01_01


FIGURE-4-7-0-991-007-A01

4-7-0Page 8

Jun 01/12


**ON A/C A318-100

RUNWAY WIDTH 60.0 m

ED

GE

OF

RU

NW

AY

20.9

m

10.6

m

3.05

mR

EF

END OF RUNWAY

(68

ft 4.

8 in

)

(34

ft 9.

6 in

)

NOTE: 73.2° EFFECTIVE STEERING ANGLE.

(10

ft)

(196 ft 10.8 in)

N_AC_040700_1_0080101_01_01


FIGURE-4-7-0-991-008-A01

4-7-0Page 9

Jun 01/12


TERMINAL SERVICING

5-0-0 TERMINAL SERVICING

**ON A/C A318-100

Terminal Servicing

1. GeneralThis chapter provides typical ramp layouts, corresponding minimum turnaround time estimations,locations of ground service points and service requirements.The information given in this chapter reflects ideal conditions. Actual ramp layouts and servicerequirements may vary according to local regulations, airline procedures and the airplane condition.- Section 5.1 shows typical ramp layouts for passenger aircraft at the gate or on an open apron.- Section 5.2 shows the minimum turnaround schedules for full servicing arrangements.- Section 5.3 shows the minimum turnaround schedule for reduced servicing arrangements.- Section 5.4 gives the locations of ground service connections, the standard of connections used

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

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

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

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

and aircraft conditions.

5-0-0Page 1

Jun 01/12


5-1-0 Servicing Arrangements

**ON A/C A318-100

Airplane Servicing Arrangements

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

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

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

5-1-0Page 1

Jun 01/12


5-1-1 Symbols Used on Servicing Diagrams

**ON A/C A318-100

Symbols Used on Servicing Diagrams

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

Ground Support Equipment

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

5-1-1Page 1

Jun 01/12


5-1-2 Typical Ramp Layout - Open Apron

**ON A/C A318-100

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 7.5 m from the aircraft).No vehicle must be parked in this area before complete stop of the aircraft (wheel chocks in positionon landing gears).

5-1-2Page 1

Jun 01/12


**ON A/C A318-100

N_AC_050102_1_0010101_01_03

STAND SAFETY LINE

NOTE: TYPICAL RAMP LAYOUTAPPLICABLE TO AIRCRAFTWITH OR WITHOUT SHARKLETS.

8METERS

FEET5 10 150 20

0 2 4 6

CAT

CAT

WV

LV

BULK

FUEL

CB

CB

ASTOW

GPU

BULK

PS

PS

AC

Typical Ramp LayoutOpen Apron - Bulk LoadingFIGURE-5-1-2-991-001-A01

5-1-2Page 2

Jun 01/12


5-1-3 Typical Ramp Layout - Gate

**ON A/C A318-100

Typical Ramp Layout - Gate

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

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

5-1-3Page 1

Jun 01/12


**ON A/C A318-100

N_AC_050103_1_0040101_01_02

STAND SAFETY LINE

NOTE: TYPICAL RAMP LAYOUTAPPLICABLE TO AIRCRAFTWITH OR WITHOUT SHARKLETS.

8METERS

FEET5 10 150 20

0 2 4 6

CAT

CAT

WV

LV

BULK

FUEL

CB

CB

TOW

GPU

PBB

BULK

AS

AC

Typical Ramp LayoutGate

FIGURE-5-1-3-991-004-A01

5-1-3Page 2

Jun 01/12


5-2-0 Terminal Operations - Full Servicing

**ON A/C A318-100

Terminal Operations - Full Servicing Turn Round Time

1. This section provides typical turn round time chart showing the typical times for ramp activitiesduring aircraft turn round.

Actual times may vary due to each operator’s specific practice and operating conditions.

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

2. Assumptions for full turn round chart

A. PASSENGER HANDLING107 pax, all Y/CAll passengers deboard and board the aircraft1 Passenger Boarding Bridge (PBB) used at door L1Equipment positioning/removal + opening/closing door = 2 min

Deboarding:- 107 pax at door L1- Deboarding rate = 22 pax/min per door- No Passenger with Reduced Mobility (PRM)

Boarding:- 107 pax at door L1- Boarding rate = 18 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +2 min- No Passenger with Reduced Mobility

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

Cargo exchange:- 15 kg (33 lb) per pax- FWD cargo compartment: 700 kg (1543 lb)- AFT cargo compartment: 900 kg (1984 lb)- Bulk off-loading rate = 120 kg/min (265 lb/min)- Bulk loading rate = 100 kg/min (220 lb/min)

C. REFUELLING2 hoses, one side6624 l (1750 US gal) at 50 psi (3 bar)

5-2-0Page 1

Jun 01/12


Dispenser positioning/removal = 4 min

D. CLEANINGPerformed in available time

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

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

5-2-0Page 2

Jun 01/12


**ON A/C A318-100

0 5 15 20 25 30 35 40

HEADCOUNTING

CATERING AT DOOR R2

CLEANING

CARGO FWD CC

REFUELLING

TOILET SERVICING

CARGO AFT CC

TRT: 34 min

10

CATERING AT DOOR R1

DEBOARDING/BOARDING AT DOOR L1

POTABLE WATERSERVICING

POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH

min

N_AC_050200_1_0040101_01_01

AVAILABLE TIME

Turn Round StationsFull Servicing (34 Min.)

FIGURE-5-2-0-991-004-A01

5-2-0Page 3

Jun 01/12


5-3-0 Terminal Operation - Transit

**ON A/C A318-100

Terminal Operation - Minimum Servicing Turn Round Time

1. This section provides typical turn round time chart showing the typical times for ramp activitiesduring aircraft turn round.

Actual times may vary due to each operator’s specific practice and operating conditions.

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

2. Assumptions for minimum turn round chart

A. PASSENGER HANDLING132 pax, all Y/C2 Stairways used at doors L1 & L2Equipment positioning/removal + opening/closing door = 2 min

Deboarding:- 66 pax at door L1- 66 pax at door L2- Deboarding rate = 20 pax/min per door- No Passenger with Reduced Mobility (PRM)

Boarding:- 66 pax at door L1- 66 pax at door L2- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +2 min- No Passenger with Reduced Mobility

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

Cargo exchange:- 10 kg (22 lb) per pax- FWD cargo compartment: 660 kg (1455 lb)- AFT cargo compartment: 660 kg (1455 lb)- Bulk off-loading rate = 120 kg/min (265 lb/min)- Bulk loading rate = 100 kg/min (220 lb/min)

C. REFUELLING2 hoses, one side

5-3-0Page 1

Jun 01/12


6624 l (1750 US gal) at 50 psi (3 bar)Dispenser positioning/removal = 4 min

D. CLEANINGPerformed in available time

E. CATERINGNo catering

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

5-3-0Page 2

Jun 01/12


**ON A/C A318-100

0 5 15 20 25 3010

TRT: 20 min

POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH

HEADCOUNTING

CATERING

CLEANING

CARGO FWD CC

REFUELLING

POTABLE WATER SERVICING

TOILET SERVICING

CARGO AFT CC

AVAILABLE TIME

AVAILABLE TIME

min



N_AC_050300_1_0010101_01_01

Turn Round StationsMinimum Servicing (20 Min.)FIGURE-5-3-0-991-001-A01

5-3-0Page 3

Jun 01/12


5-4-0 Ground Service Connections

**ON A/C A318-100

Ground Service Connections

1. Ground Service Connections.

5-4-0Page 1

Jun 01/12


5-4-1 Ground Service Connections Layout

**ON A/C A318-100

Ground Service Connections Layout

1. This section gives the ground service connections layout.

5-4-1Page 1

Jun 01/12


**ON A/C A318-100

1 3 6 7 11 12 2 4 14− −

67

6

7

13

10

1

10

13

14

CONNECTOR (LP) PANELS

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

IDG OIL FILLINGENGINE OIL FILLING CONNECTOR APU OIL FILLING

GRAVITY REFUEL

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

2 −3 −4 −5 −

8 −9 −

10 −11 −12 −

6 −7 −

13 −14 −

5 12

2

4

98

N_AC_050401_1_0010101_01_01

Ground Service ConnectionsGround Service Connections Layout

FIGURE-5-4-1-991-001-A01

5-4-1Page 2

Jun 01/12


5-4-2 Grounding Points

**ON A/C A318-100

Grounding Points

1. Grounding Points.

DISTANCE: Meters (ft)

FROM AIRPLANE CENTERLINEAFT OF NOSE

R SIDE L SIDE

MEAN HEIGHTFROM

GROUNDOn Nose Landing Gearleg:

5.07 m(16.63 ft) on centerline

0.94 m(3.08 ft)

On left Main LandingGear leg:

15.32 m(50.26 ft)

3.79 m(12.43 ft)

1.07 m(3.51 ft)

On right Main LandingGear leg:

15.32 m(50.26 ft)

3.79 m(12.43 ft)

1.07 m(3.51 ft)

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

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

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

5-4-2Page 1

Jun 01/12


**ON A/C A318-100

(2)(1)

GROUND CABLE(OPTIONAL)

LANDINGGEAR

NOSE LANDING GEAR

MAIN LANDING GEAR

(1)

A

A

A

(1)

N_AC_050402_1_0010101_01_00

Ground Service ConnectionsGrounding Points

FIGURE-5-4-2-991-001-A01

5-4-2Page 2

Jun 01/12


**ON A/C A318-100

NOTE: R SIDE SYMMETRICAL

RIB20

RIB19

FWD

A

FOR SPECIFICATIONS REFERTO FLIGHT MANUAL

B

B

A

N_AC_050402_1_0020101_01_00

A

Ground Service ConnectionsGrounding Points

FIGURE-5-4-2-991-002-A01

5-4-2Page 3

Jun 01/12


5-4-3 Hydraulic System

**ON A/C A318-100

Hydraulic System

1. Access.

FROM AIRPLANE CENTERLINE

ACCESSAFT OF NOSE

m (ft)RH SIDEm (ft)

LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Green System:Access door 197CB

16.43(53.9)

1.27(4.17)

1.76(5.77)

Yellow System:Access door 198CB

16.43(53.9)

1.27(4.17)

1.76(5.77)

Blue System:Access door 197EB

16.96(55.64)

1.27(4.17)

1.76(5.77)

NOTE : Distances are approximate.

2. Reservoir Pressurization.On the air pressurization manifold:

POSITION FROM AIRCRAFTCENTERLINE

ACCESSAFT OF NOSE

m (ft) RH SIDEm (ft)

LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Access door 195BB13.2(43.31)

0.25(0.82)

1.74(5.71)

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

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


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Yellow Systemaccumulator:Access door 196BB

13.8(45.28)

0.25(0.82)

1.99(6.53)

5-4-3Page 1

Jun 01/12



ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Green Systemaccumulator:Left MLG door

14.3(46.92)

0.25(0.82)

3.2(10.5)

Blue Systemaccumulator:Access door 195BB

15.8(51.84)

0.25(0.82)

1.99(6.53)

Yellow System brakingaccumulator:Access door 196BB

13.8(45.28)

0.76(2.49)

1.74(5.71)


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


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Access door 197CB16.43(53.9)

1.27(4.17)

1.76(5.77)

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

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


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Yellow System:Access door 196 BB -198 CB

13.8(45.27)

1.43(4.69)

1.9(6.23)

Green System:Left MLG door

14.3(46.92)

1.27(4.17)

2.61(8.56)

5-4-3Page 2

Jun 01/12



ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Blue System:Access door 197 EB

16.96(55.64)

1.27(4.17)

1.76(5.77)


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

5-4-3Page 3

Jun 01/12


**ON A/C A318-100

RESERVOIR FILL SYSTEMHAND PUMP FILL CONNECTION

GROUND TESTPRESSURE

CONNECTION

GROUND TESTSUCTION

CONNECTIONRESERVOIR FILLCONNECTION

AE96993GM

GROUND SUPPLY

AE80531K AE80532N

1698GM

1008GM 1007GM 1006GM

197CB

A

AN_AC_050403_1_0040101_01_00

Hydraulic SystemGreen System Ground Service Panel

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

5-4-3Page 4

Jun 01/12


**ON A/C A318-100

GROUND CONNECTIONSUCTION

GROUNDCONNECTION

DELIVERY

AE80531K

AE80532N

2006GM

2008GM

A

Z197

A

N_AC_050403_1_0050101_01_00

Hydraulic SystemBlue System Ground Service Panel

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

5-4-3Page 5

Jun 01/12


**ON A/C A318-100

GROUND TESTPRESSURE CONNECTION

GROUND TESTSUCTION CONNECTION

AE80531K AE80532N

A

A

3008GM 3006GM

198CB

N_AC_050403_1_0060101_01_00

Hydraulic SystemYellow System Ground Service Panel

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

5-4-3Page 6

Jun 01/12


5-4-4 Electrical System

**ON A/C A318-100

Electrical System

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


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

A/C External Power:Access door 121AL

2.55(8.37) on centerline

2.00(6.56)


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

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

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

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

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

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

5-4-4Page 1

Jun 01/12


- Radio navigation: 1.2 KVA.

5-4-4Page 2

Jun 01/12


**ON A/C A318-100

108VU

A

N_AC_050404_1_0010101_01_01

A

121AL

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

5-4-4Page 3

Jun 01/12


5-4-5 Oxygen System

**ON A/C A318-100

Oxygen System

1. Replenishment of high pressure oxygen source.

A. For the A318 aircraft (basic version), the oxygen source is replenished by replacing the oxygencylinder installed in the avionics compartment.

5-4-5Page 1

Jun 01/12


5-4-6 Fuel System

**ON A/C A318-100

Fuel System

1. Refuel/Defuel Control Panel.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Refuel/DefuelIntegrated Panel:Access door 192MB

14.01(45.96)

1.8(5.91)

1.8(5.91)

2. Refuel/Defuel Connectors.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

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

15.2(49.87)

9.83(32.25)

3.65(11.98)

Refuel/Defuel coupling,RightAccess Door 622HB

15.2(49.87)

9.83(32.25)

3.65(11.98)

Gravity Refuel Coupling16.71(54.82)

12.4(40.68)

12.4(40.68)

3.7(12.14)

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

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

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

5-4-6Page 1

Jun 01/12


3. Overpressure Protector and NACA Flame Arrestor.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

Overpressure Protector 17.96(58.92)

14.9(48.88)

14.9(48.88)

4.32(14.17)

NACA Flame Arrestor 17.4(57.09)

13.7(44.95)

13.7(44.95)

4.02(13.19)


5-4-6Page 2

Jun 01/12


**ON A/C A318-100

REFUEL/DEFUELCONTROL PANEL

NOTE: STANDARD CONFIGURATION OF REFUEL/DEFUEL PANEL.

A

FUELkg x 1000

QTY

RIGHTCTRLEFT

LEFT CTR RIGHT

LVLHI

OPEN

NORM

SHUT

OPEN

NORM

SHUT

REFUEL VALVESOPEN

NORM

SHUT

BATT POWERTESTHI LVL ON

OPEN LTS NORM

MODE SELECTREFUEL

OFF

DEFUEL / XFR

kg x 1000

PRESELECTED

DEC INC

ACTUALREFUEL

CKPT END

A

N_AC_050406_1_0010101_01_00

Ground Service ConnectionsRefuel/Defuel Panel

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

5-4-6Page 3

Jun 01/12


**ON A/C A318-100

RIB15

RIB14

A

41QM

40QM

LEADINGEDGE

WING FRONTSPAR

A

N_AC_050406_1_0020101_01_00

Ground Service ConnectionsRefuel/Defuel Couplings

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

5-4-6Page 4

Jun 01/12


**ON A/C A318-100

RIB19

RIB20

A

ADAPTER(REF ONLY)

GROUND CONNECTION(REF ONLY)

44QM

(45QM)

AFWD

N_AC_050406_1_0030101_01_00

Ground Service ConnectionsGravity Refuel Couplings

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

5-4-6Page 5

Jun 01/12


**ON A/C A318-100

A

A ALH SHOWN

RH SYMMETRICAL

FWD

NACA VENT INTAKE

NACA FLAME ARRESTOR

OVERPRESSURE PROTECTOR

N_AC_050406_1_0040101_01_00

B

C

RIB25RIB24

RIB23

RIB22

550CB (650CB)

550AB (650AB)

C

B

Ground Service ConnectionsOverpressure Protector and NACA Flame Arrestor

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

5-4-6Page 6

Jun 01/12


5-4-7 Pneumatic System

**ON A/C A318-100

Pneumatic System

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


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

HP ConnectorAccess door 191DB

10.43(34.22)

0.84(2.76)

1.76(5.77)


A. Connector:- One standard MS33740, 3 in.

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


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM

GROUNDm (ft)

LP ConnectorAccess door 191CB

9.9(32.48)

1.11(3.64)

1.73(5.68)

NOTE : Distances are approximate

A. Connector:- One standard SAE AS4262 type B, 8 in.

5-4-7Page 1

Jun 01/12


5-4-8 Potable Water System

**ON A/C A318-100

Potable Water System

1. Potable Water Ground Service Panel.


ACCESSAFT OF NOSE


LH SIDEm (ft)

MEAN HEIGHTFROM GROUND

m (ft)

Potable WaterGround ServicePanel:Access door 171AL:

25.2(82.67)

0.3(0.98)

2.6(8.53)


2. Potable Water Ground Drain Panel.


ACCESSAFT OF NOSE


LH SIDEm (ft)


m (ft)

Potable WaterGround ServicePanel:Access door 133AL:

11.4(37.4)

0.15(0.49)

1.75(5.74)


3. Technical Specifications

A. Connectors:

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

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

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

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

5-4-8Page 1

Jun 01/12


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

5-4-8Page 2

Jun 01/12


**ON A/C A318-100

DRAIN CONNECTION

FILL ANDDRAIN PORT

GROUND CONNECTION

PRESSURIZATION

Z133

Z171

A

B

B

A

N_AC_050408_1_0010101_01_00

Ground Service ConnectionsPotable Water Ground Service Panel

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

5-4-8Page 3

Jun 01/12


5-4-9 Oil System

**ON A/C A318-100

Oil System

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


ACCESSAFT OF NOSE

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

ENGINE 2 (RH)m (ft)


m (ft)

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

12.3(40.35)

6.63(21.75)

4.82(15.81)

1.46(4.79)

Engine Oil PressureFilling Port:

12.2(40.03)

6.49(21.29)

4.74(15.55)

1.42(4.66)


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

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

2. IDG Oil Replenishment for CFM56 Series Engine (See FIGURE 5---9-99--002-A):One pressure filling connection per engine.


ACCESSAFT OF NOSE


ENGINE 2 (RH)m (ft)


m (ft)

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

11.4(37.4)

6.9(22.64)

5.52(18.11)

0.68(2.23)


A. IDG oil tank capacity: 5 l (1.32 US gal)

5-4-9Page 1

Jun 01/12


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

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


ACCESSAFT OF NOSE


ENGINE 2 (RH)m (ft)


m (ft)

Starter Oil FillingConnection:

10.4(34.12)

5.3(17.39)

6.2(20.34)

0.76(2.49)


A. Tank capacity: 0.8 l (0.206 US gal)

4. Engine Oil Replenishment for PW 6000 Series Engine (See FIGURE 5---9-99--004-A):One gravity filling cap per engine.


ACCESSAFT OF NOSE


ENGINE 2 (RH)m (ft)


m (ft)

Engine Oil GravityFilling Cap:Access door: 438BR(LH),448BR (RH)

10.16(33.33)

4.8(15.75)

6.63(21.75)

1.8(5.9)


A. Tank capacity:- Full level: 18.36 l (4.85 US gal)- Usable: 23.50 l (6.21 US gal)- Engine oil tank capacity: 18.36 l (4.85 US gal)

1. IDG Oil Replenishment for PW 6000 Series Engine:One pressure filling connection per engine.

5-4-9Page 2

Jun 01/12



ACCESSAFT OF NOSE


ENGINE 2 (RH)m (ft)


m (ft)

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

10(32.81)

5.33(17.49)

6.17(20.24)

1.02(3.35)



B. Maximum servicing pressure: 35 psi (2.41 bar)

5. Starter Oil Replenishment for PW 6000 Series Engine (See FIGURE 5---9-99--006-A):One gravity filling cap per engine.


ACCESSAFT OF NOSE


ENGINE 2 (RH)m (ft)


m (ft)

Starter Oil FillingConnection:

10.16(33.33)

5.84(19.16)

5.59(18.34)

1.02(3.35)



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

AFT OF NOSEm (ft)

FROM AIRPLANECENTERLINE(LEFT HAND)

m (ft)

MEAN HEIGHT FROMGROUND

m (ft)

GTCP 36-30029.37(96.36)

0.3(0.98)

4.83(15.85)

APS 320029.37(96.36)

0.3(0.98)

4.78(15.68)

131-929.27(96.03)

0.35(1.15)

4.32(14.17)

5-4-9Page 3

Jun 01/12



A. Tank capacity (usable):- APU type GTCP 36-300: 6.20 l (1.64 US gal)- APU type APS 3200: 5.40 l (1.43 US gal)- APU type 131-9: 6.25 l (1.65 US gal)

5-4-9Page 4

Jun 01/12


**ON A/C A318-100

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

VENT

OIL LEVELTRANSMITTER(OPTIONAL)

OIL CAP

SIGHT WINDOW

ANTI−SIPHONDEVICE

AIR PRESSURESWITCH NIPPLE

SELF−SEALING MAGNETICDRAIN PLUG

PRESSURE NIPPLE

OIL OUT

OIL/FUEL HEATEXCHANGER

SERVO FUELHEATER

A

A

B

FWD

B

N_AC_050409_1_0010101_01_00

Ground Service ConnectionsEngine Oil Tank -- CFM56 Series Engine

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

5-4-9Page 5

Jun 01/12


**ON A/C A318-100

C

A

B

SIGHT GLASS

NOTE: ATHE YELLOW BAND, OIL SERVICINGIS REQUIRED.

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

CTHE GREEN BAND, OIL SERVICINGIS REQUIRED.

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

(SIGHT GLASS)

1

2

34

5

6

A B

A

B

OVERFULL

ADDOIL

ADDOIL

CFM−56

IF THE OIL LEVEL IS ABOVE

IF THE OIL LEVEL IS WITHIN

IF THE OIL LEVEL IS BELOW

N_AC_050409_1_0020101_01_01

Ground Service ConnectionsIDG Oil Tank -- CFM56 Series Engine

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

5-4-9Page 6

Jun 01/12


**ON A/C A318-100

DRAIN PORTAND MAGNETICPLUG

OVERFLOWPLUG

STARTER

OIL FILLERPLUG

A

A

N_AC_050409_1_0030101_01_02

Ground Service ConnectionsStarter Oil Tank -- CFM56 Series Engine

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

5-4-9Page 7

Jun 01/12


**ON A/C A318-100

A

B

N−02463(0601)PW V

OIL

FULL FULL

LTRLOW

1

LOW

1

QTS

LEVEL

OIL TANK

CAP

A

SIGHT GLASS

B

N_AC_050409_1_0040101_01_02

Ground Service ConnectionsEngine Oil Tank -- PW 6000 Series Engine

FIGURE-5-4-9-991-004-A01

5-4-9Page 8

Jun 01/12


**ON A/C A318-100

IDG

N−01198 (0601)PW V

B

A

A

B

OVER FULL

ADDOIL

ADDOIL

IDG OVERFILLDRAIN VALVE

IDG OIL LEVELSIGHT GLASS

IDG PRESSUREFILL VALVE

N_AC_050409_1_0050101_01_01

Ground Service ConnectionsIDG Oil Tank -- PW 6000 Series Engine

FIGURE-5-4-9-991-005-A01

5-4-9Page 9

Jun 01/12


**ON A/C A318-100

A

STARTER

MAGNETICCHIP COLLECTOR

FILLPLUG

OVERFLOWPLUG

N−01199 (1100)PW VA

N_AC_050409_1_0060101_01_00

Ground Service ConnectionsStarter Oil Tank -- PW 6000 Series Engine

FIGURE-5-4-9-991-006-A01

5-4-9Page 10

Jun 01/12


**ON A/C A318-100

FR80

Z316Z315

FR84

GRAVITYOIL FILLER

PRESSUREFILL PORT

OVERFLOWDRAIN VALVE

A

A

OIL LEVELSIGHT GLASS

N_AC_050409_1_0070101_01_00

Ground Service ConnectionsAPU Oil Tank

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

5-4-9Page 11

Jun 01/12


5-4-10 Vacuum Toilet System

**ON A/C A318-100

Vacuum Toilet System

1. Vacuum Toilet System.


ACCESSAFT OF NOSE

m (ft) R SIDEm (ft)

L SIDEm (ft)


m (ft)

Waste WaterGround ServicePanel:Access door 172AR

25.2(82.67)

0.8(2.62)

2.8(9.18)


2. Technical Specifications

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

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

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

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

5-4-10Page 1

Jun 01/12


**ON A/C A318-100

FILL AND RINSECONNECTION

TOILET DRAINCONNECTION

FR66 FR65

A

Z172

A

N_AC_050410_1_0010101_01_00

Ground Service ConnectionsWaste Water Ground Service Panel

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

5-4-10Page 2

Jun 01/12


5-5-0 Engine Starting Pneumatic Requirements

**ON A/C A318-100

Engine Starting Pneumatic Requirements

1. Engine Starting Pneumatic Requirements.To determinate the airflow required at ground connection, refer to the example given in FIGURE 5---0-99--001-A.

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

5-5-0Page 1

Jun 01/12


**ON A/C A318-100

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

FUSELAGE CONNECTOR

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

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

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

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

N_AC_050500_1_0010101_01_00

220°C200°C

150°C

100°C

50°C

0°C

230

3

4

40

50

60

5

6

70

80

90

AIR SUPPLY PRESSUREAT GROUND CONNECTIONPSIA ABSOLUTE BARS

AIR SUPPLY TEMPERATUREAT FUSELAGE CONNECTION

MIN. PRESSUREAT GROUND CONNECTION: 33 PSIG

RECOMMENDED PRESSURE:38 PSIG AT GROUNDCONNECTION

SEA LEVEL

Z = 8000 ft

40s

50s70s

35s

Z = 8000 ft

SEA LEVEL

Z = 8000 ft

MAXIMUM DUCT PRESSURE: 60 PSIG

ESTIMATED STARTINGTIMES UP TO IDLE

0.80 1.00 2.001.801.601.401.20 kg/s

48 60 8472 kg/min12010896

SEA LEVEL

MAXIM

UM T

EMPERATURE L

IMIT

AIR FLOW REQUIRED AT GROUND CONNECTION

Engine Starting Pneumatic RequirementsEngine Starting Pneumatic Requirements

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

5-5-0Page 2

Jun 01/12


5-5-1 Low Ambient Temperatures

**ON A/C A318-100

Low Ambient Temperatures

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

5-5-1Page 1

Jun 01/12


**ON A/C A318-100

220°C

200°C

150°C

100°C

50°C

0°C

kg/mn1201089684726048

230

3

4

40

50

60

5

6

70

80

90

AIR SUPPLY PRESSUREAT GROUND CONNECTION

PSIA ABSOLUTE BARS





SEA LEVEL

Z = 8000 ft

40s

50s

70s

35S

SEA LEVEL

Z = 8000 ft

SEA LEVEL

Z = 8000 ft


MAXIM

UM T

EMPERATURE L

IMIT


N_AC_050501_1_0010101_01_01

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

FIGURE-5-5-1-991-001-A01

5-5-1Page 2

Jun 01/12


**ON A/C A318-100

40 50 60 70 80 90 100 110 120 kg/min

1

2

3

4

5

6

7

100.0

PSIA

87.0

72.5

58.0

43.5

29.0

14.5

ABSOLUTE BARS −40°F (−40°C)

220°C200°C

150°C

100°C

50°C

0°CMAXIMUM TEMPERATURE LIM

IT

101.5



N−03649 (0402)PW V

MAXIMUM DESIGN DUCT PRESSURE

80s

70s

60s

50sESTIMATED STARTINGTIMES UP TO IDLE


N_AC_050501_1_0020101_01_00

Engine Starting Pneumatic RequirementsLow Ambient Temperature -40˚C (-40˚F) -- PW 6000 series engine

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

5-5-1Page 3

Jun 01/12


5-5-2 Medium Ambient Temperatures

**ON A/C A318-100

Medium Ambient Temperatures

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

5-5-2Page 1

Jun 01/12


**ON A/C A318-100

220°C

200°C

150°C

100°C

50°C

35S

0°C

kg/mn1201089684726048

230

3

4

40

50

60

5

6

70

80

90

PSIA ABSOLUTE BARS

MAXIM

UM T

EMPERATURE L

IMIT






SEA LEVEL

Z = 8000 ft

TIMES UP TO IDLEESTIMATED STARTING

40s


SEA LEVEL

Z = 8000 ft

SEA LEVEL

Z = 8000 ft

50s

60s

70s

N_AC_050502_1_0010101_01_01

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

FIGURE-5-5-2-991-001-A01

5-5-2Page 2

Jun 01/12


**ON A/C A318-100

40 50 60 70 80 90 100 110 120 kg/min

1

2

3

4

5

6

7

100.0

PSIA

87.0

72.5

58.0

43.5

29.0

14.5

ABSOLUTE BARS 59°F (15°C)

220°C200°C

150°C

100°C

50°C

0°CMAXIMUM TEMPERATURE LIM

IT

101.5

AIR SUPPLY PRESSUREAT GROUND CONNECTION AIR SUPPLY TEMPERATURE

AT FUSELAGE CONNECTION

N−02538 (0402)PW V

50s

60s

70s

80s




N_AC_050502_1_0020101_01_00

Engine Starting Pneumatic RequirementsMedium Ambient Temperature +15˚C (+59˚F) -- PW 6000 series engine

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

5-5-2Page 3

Jun 01/12


5-5-3 High Ambient Temperatures

**ON A/C A318-100

High Ambient Temperatures

1. This section provides the engine starting pneumatic requirements for a temperature upper:- +38˚C (+100˚F) -- PW 6000- +50˚C (+122˚F) -- CFM56

5-5-3Page 1

Jun 01/12


**ON A/C A318-100

220°C

200°C

150°C

100°C

50°C

kg/mn1201089684726048

230

3

4

40

50

60

5

6

70

80

90

AIR SUPPLY PRESSUREAT GROUND CONNECTIONPSIA ABSOLUTE BARS

MINI. PRESSUREAT GROUND CONNECTION: 22 PSIG



MAXIM

UM T

EMPERATURE L

IMIT


40s

50s

60s

70s

Z = 8000 ft

SEA LEVEL

SEA LEVEL

Z = 8000 ft

Z = 8000 ft

SEA LEVEL


35s


N_AC_050503_1_0010101_01_00

Engine Starting Pneumatic RequirementsHigh Ambient Temperature +50˚C (+122˚F) -- CFM56 series engine

FIGURE-5-5-3-991-001-A01

5-5-3Page 2

Jun 01/12


**ON A/C A318-100

40 50 60 70 80 90 100 110 120 kg/min

1

2

3

4

5

6

7

100.0

PSIA

87.0

72.5

58.0

43.5

29.0

14.5

ABSOLUTE BARS 100°F (38°C)

220°C200°C

150°C

100°C

50°C

0°C

101.5



N−03650 (0402)PW V



60s

50s

70s

80s


MAXIMUM TEMPERATURE LIM

IT

N_AC_050503_1_0020101_01_00

Engine Starting Pneumatic RequirementsHigh Ambient Temperature +38˚C (+100˚F) -- PW 6000 series engine

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

5-5-3Page 3

Jun 01/12


5-6-0 Ground Pneumatic Power Requirements

**ON A/C A318-100

Ground Pneumatic Power Requirements

1. Ground Pneumatic Power Requirements

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

5-6-0Page 1

Jun 01/12


5-6-1 Heating

**ON A/C A318-100

Heating

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

5-6-1Page 1

Jun 01/12


**ON A/C A318-100

3040

50T

IME

(m

in)

0.5

0.42

9

0.51

5

0.60

0.68

6

0.72

2

1.0

0.85

8

1.2

1.03

0.94

4

1.11

5

1.20

1

1.5

1.28

7

(kg/

s)

TOTAL AIRFLOW

CABIN AIRFLOW

TOTAL AIRFLOW

(lb/s

)

2.59

2.15

1.72

1.28

1.5

2.0

2.5

3.0

MA

X A

LLO

WE

D T

OT

AL

AIR

FLO

W (

2 m

bar

CA

BIN

OV

ER

PR

ES

SU

RE

)

TIM

E T

O H

EA

T C

AB

IN T

O 2

1°C

(69

.8°

F O

N G

RO

UN

D)

INIT

IAL

CA

BIN

TE

MP

ER

AT

UR

E A

T −

23°

C (

−9.

4°F

)T

EM

PE

RA

TU

RE

AT

GR

OU

ND

CO

NN

EC

TIO

N: 7

0°C

(15

8°F

)E

MP

TY

CA

BIN

ELE

CT

RIC

AL

LOA

D =

270

0 W

RE

CIR

CU

LAT

ION

: ON

NO

T O

TH

ER

HE

AT

LO

AD

CABIN AIRFLOW

N_AC_050601_1_0010101_01_01

Ground Pneumatic Power RequirementsHeating

FIGURE-5-6-1-991-001-A01

5-6-1Page 2

Jun 01/12


5-6-2 Cooling

**ON A/C A318-100

Cooling

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

5-6-2Page 1

Jun 01/12


**ON A/C A318-100

2030

40T

IME

(m

in)

0.5

0.42

9

0.51

5

0.60

0.68

6

0.72

2

1.0

0.85

8

1.2

1.03

0.94

4

1.11

5

1.20

1

1.5

1.28

7

(kg/

s)

TOTAL AIRFLOW

CABIN AIRFLOW

TOTAL AIRFLOW

(lb/s

)

2.59

2.15

1.72

1.28

1.5

2.0

2.5

3.0

MA

X A

LLO

WE

D T

OT

AL

AIR

FLO

W (

2 m

bar

CA

BIN

OV

ER

PR

ES

SU

RE

)

TIM

E T

O C

OO

L C

AB

IN T

O 2

7°C

(80

.6°

F O

N G

RO

UN

D)

INIT

IAL

CA

BIN

TE

MP

ER

AT

UR

E A

T −

38°

C (

−10

0.4°

F)

TE

MP

ER

AT

UR

E A

T G

RO

UN

D C

ON

NE

CT

ION

: 1.5

°C

(34

.7°

F)

EM

PT

Y C

AB

INE

LEC

TR

ICA

L LO

AD

= 2

000

WS

UN

= 4

990

WR

EC

IRC

ULA

TIO

N: O

N

CABIN AIRFLOW

N_AC_050602_1_0010101_01_01

Ground Pneumatic Power RequirementsCooling

FIGURE-5-6-2-991-001-A01

5-6-2Page 2

Jun 01/12


5-7-0 Preconditioned Airflow Requirements

**ON A/C A318-100

Preconditioned Airflow Requirements

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

5-7-0Page 1

Jun 01/12


**ON A/C A318-100

2.59

2.1

5

1.7

2

1.2

8

3.0

2.5

2.0

1.5

1.2

87

1.1

15

1.2

01

1.0

3

0.94

4

0.85

8

0.72

2

0.68

6

0.60

0.5

15

0.42

9

1.5

0.5

1.0

1.2

TOTAL AIRFLOW

CABIN AIRFLOW

CABIN AIRFLOW

TOTAL AIRFLOW(kg/s

)

30−3

0−4

0−2

0−1

01

020

40 0

−40

0

−10

50

10

10

0

INLE

T F

LOW

TE

MP

ER

AT

UR

E

NO

TE

:

(°C

)

(°F

)

(lb

/s)

MA

X A

LLO

WE

D T

OT

AL

AIR

FLO

W (

2 m

bar

CA

BIN

OV

ER

PR

ES

SU

RE

)

OA

T =

−40°

C (−

40°F

)

OA

T =

−23

°C (

−9.4

°F)

OA

T =

−30°

C (−

22°F

)

CU

RV

E 2

, 3, 4

CA

BIN

AT

21°

C (

69.8

°F

)

RE

CIR

CU

LAT

ION

: ON

NO

OT

HE

R H

EA

T L

OA

D

ELE

CT

RIC

AL

LOA

D =

380

0 W

NO

PA

SS

EN

GE

R O

R C

AB

IN

LP

GR

OU

ND

CO

NN

EC

TIO

N M

AX

IMU

M P

RE

SS

UR

E 4

0 M

B

CU

RV

E 1

: C

AB

IN A

T 2

7°C

(80

.6°

F)

134

PA

SS

EN

GE

R, 4

CA

BIN

AT

TE

ND

AN

TS

, 3 C

RE

W M

EM

BE

RS

BR

IGH

T D

AY

SO

LAR

LO

AD

: 297

5 W

ELE

CT

RIC

AL

LOA

D =

620

0 W

RE

CIR

CU

LAT

ION

: ON

OA

T (

OU

TS

IDE

AM

BIE

NT

TE

MP

ER

AT

UR

E)

= 3

8°C

(10

0.4°

F)

AT

TE

ND

AN

TS

N_AC_050700_1_0010101_01_01

Preconditioned Airflow RequirementsFIGURE-5-7-0-991-001-A01

5-7-0Page 2

Jun 01/12


5-8-0 Ground Towing Requirements

**ON A/C A318-100

Ground Towing Requirements

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

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

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

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

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

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

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

5-8-0Page 1

Jun 01/12


**ON A/C A318-100

10

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

35404550556065

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

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

0

1.5% SLOPE60 tons

EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A318 AT 60 t, AT 1.5% SLOPE,1 ENGINE AT IDLE AND FOR WET TARMAC CONDITIONS:

− ON THE RIGHT HAND SIDE OF THE GRAPH, CHOOSE THE RELEVANT AIRCRAFT WEIGHT (60 t)− FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUIRED SLOPE PERCENTAGE (1.5%)− FROM THE POINT OBTAINED DRAW A STRAIGHT HORIZONTAL LINE UNTIL NO OF ENGINES AT IDLE = 2− FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUESTED NUMBER OF ENGINES (1)− FROM THIS POINT DRAW A STRAIGHT HORIZONTAL LINE TO THE DRAWBAR PULL AXIS− THE Y−COORDINATE OBTAINED IS THE NECESSARY DRAWBAR PULL FOR THE TRACTOR (5.1 t)− SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE. THE OBTAINED X−COORDINATE IS

THE RECOMMENDED MINIMUM TRACTOR WEIGHT (9 t)

ICE m = 0.05

1 ENGINE ON5

5.1

WE

T C

ON

CR

ET

E m

= 0

.57

HA

RD

SN

OW

m =

0.2

AT IDLE

DR

Y C

ON

CR

ET

E m

= 0

.8

BREAKAWAY RESISTANCE 6%# OF ENGINES ON FOR PB: 1ENGINE THRUST 616 daN

9.0

N_AC_050800_1_0010101_01_04

Ground Towing RequirementsFIGURE-5-8-0-991-001-A01

5-8-0Page 2

Jun 01/12


5-9-0 De-Icing and External Cleaning

**ON A/C A318-100

De-Icing and External Cleaning

1. De-Icing and External Cleaning on GroundThe mobile equipment for aircraft de-icing and external cleaning must be capable of reaching heightsup to approximately 13 m (42.65 ft).

2. De-Icing

Wing Top Surface(Both Sides)

Wingtip Devices(Both Inside andOutside Surfaces)

(Both Sides)

HTP Top Surface(Both Sides)

VTP(Both Sides)AIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2 m2 ft2

A318 99.7 1073.16 1.8 19.38 27 290.63 46.2 497.29A318 Sharklet 99.7 1073.16 9.6 103.33 27 290.63 46.2 497.29

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

A318 111.9 1204.48 23.6 254.03 310 3337A318 Sharklet 111.9 1204.48 23.6 254.03 318 3423

NOTE : Dimensions are approximate

3. External Cleaning

Wing TopSurface

(Both Sides)

Wing LowerSurface

(Including FlapTrack Fairing)(Both Sides)

Wingtip Devices(Both Inside and

OutsideSurfaces)

(Both Sides)

HTP TopSurface

(Both Sides)

HTP LowerSurface

(Both Sides)AIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2 m2 ft2 m2 ft2

A318 99.7 1073.16 103.4 1112.99 1.8 19.38 27 290.63 27 290.63A318 Sharklet 99.7 1073.16 103.4 1112.99 9.6 103.33 27 290.63 27 290.63

VTP(Both Sides)

Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned Area

AIRCRAFT TYPE


A318 46.2 497.29 343.2 3694.17 73.2 787.92 723 7782

5-9-0Page 1

Jun 01/12


VTP(Both Sides)

Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned Area

AIRCRAFT TYPE


A318 Sharklet 46.2 497.29 343.2 3694.17 73.2 787.92 731 7868

NOTE : Dimensions are approximate

5-9-0Page 2

Jun 01/12


OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

**ON A/C A318-100

Engine Exhaust Velocities and Temperatures

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

6-1-0Page 1

Jun 01/12


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

**ON A/C A318-100

Engine Exhaust Velocities Contours - Ground Idle Power

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

6-1-1Page 1

Jun 01/12


**ON A/C A318-100

ELE

VA

TIO

N

FE

ET

40 30 20 10 0036912

mft

PLA

NA

IRP

LAN

E

V (

M/S

)

GR

OU

ND

PLA

NE

ME

TE

RS

40 30 20 10 0036912

mft

4530

2520

1510

050

100

150

200

250

300

350

400

015

3045

6075

9010

512

0

4530

2520

1510

N_AC_060101_1_0010101_01_00

Engine Exhaust VelocitiesGround Idle Power -- CFM56 series engine

FIGURE-6-1-1-991-001-A01

6-1-1Page 2

Jun 01/12


**ON A/C A318-100

AIR

PLA

NE

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

102

MP

H62

MP

H34

MP

H20

MP

H

PLA

NC

ON

VE

RS

ION

FA

CT

OR

1 M

PH

= 1

.6 k

m/h

102

MP

H62

MP

H34

MP

H20

MP

H

015

3046

61

250

300

050

100

150

200

7691

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

PW

A 6

000

− G

RO

UN

D ID

LEA

LL V

ELO

CIT

Y V

ALU

ES

AR

E IN

ST

AT

UE

MIL

ES

PE

R H

OU

R.

NO

TE

:

(18)60

(12)40 (6

)20 0

(18)60

(12)40 (6

)20 0

N_AC_060101_1_0020101_01_00

Engine Exhaust VelocitiesGround Idle Power -- PW 6000 series engine

FIGURE-6-1-1-991-002-A01

6-1-1Page 3

Jun 01/12


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

**ON A/C A318-100

Engine Exhaust Temperatures Contours - Ground Idle Power

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

6-1-2Page 1

Jun 01/12


**ON A/C A318-100

ELE

VA

TIO

N

FE

ET 40 30 20 10 0

036912

mft

PLA

NA

IRP

LAN

E

GR

OU

ND

PLA

NE

ME

TE

RS

mft

400

350

325

300

40 30 20 10 0036912

3000

lbs

OF

TH

RU

ST

T (

°K

)

400

350

325

300

050

100

150

200

250

300

350

400

015

3045

6075

9010

512

0

N_AC_060102_1_0010101_01_00

Engine Exhaust TemperaturesGround Idle Power -- CFM56 series engine

FIGURE-6-1-2-991-001-A01

6-1-2Page 2

Jun 01/12


**ON A/C A318-100

AIR

PLA

NE

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

PLA

N

PW

A 6

000

− G

RO

UN

D ID

LEA

LL T

EM

PE

RA

TU

RE

S A

RE

IN F

AH

RE

NH

EIT

(C

ELS

IUS

).N

OT

E:

160°

F(7

1°C

)10

0°F

(38°

C)

160°

F(7

1°C

)10

0°F

(38°

C)

015

3046

61

250

300

050

100

150

200

7691

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

(18)60

(12)40 (6)

20 0

(18)60

(12)40 (6)

20 0

N_AC_060102_1_0020101_01_00

Engine Exhaust TemperaturesGround Idle Power -- PW 6000 series engine

FIGURE-6-1-2-991-002-A01

6-1-2Page 3

Jun 01/12


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

**ON A/C A318-100

Engine Exhaust Velocities Contours - Breakaway Power

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

6-1-3Page 1

Jun 01/12


**ON A/C A318-100

ELE

VA

TIO

N

FE

ET

050

100

150

200

250

300

350

400

015

3045

6075

9010

512

0

40 30 20 10 0036912

mft

PLA

NA

IRP

LAN

E

GR

OU

ND

PLA

NE

ME

TE

RS

40 30 20 10 0036912

mft

(38%

N1)

NO

TE

:−

add

+ 1

% N

1 pe

r +

15°

C (

27°

F)

AB

OV

E IS

A T

EM

PE

RA

TU

RE

CO

ND

ITIO

NS

− a

dd +

1%

N1

per

2000

ft

3000

lbs

OF

TH

RU

ST

V (

M/S

)

4020

15

4020

15

N_AC_060103_1_0010101_01_00

Engine Exhaust VelocitiesBreakaway Power -- CFM56 series engine

FIGURE-6-1-3-991-001-A01

6-1-3Page 2

Jun 01/12


**ON A/C A318-100

PW

A 6

000

− B

RE

AK

AW

AY

PO

WE

RA

LL V

ELO

CIT

Y V

ALU

ES

AR

E IN

ST

AT

UE

MIL

ES

PE

R H

OU

R.

NO

TE

:

AIR

PLA

NE

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

102

MP

H62

MP

H34

MP

H20

MP

H

PLA

NC

ON

VE

RS

ION

FA

CT

OR

1 M

PH

= 1

.6 k

m/h

102

MP

H62

MP

H34

MP

H20

MP

H

015

3046

61

250

300

050

100

150

200

7691

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

(18)60

(12)40 (6

)20 0

(18)60

(12)40 (6

)20 0

N_AC_060103_1_0020101_01_00

Engine Exhaust VelocitiesBreakaway Power -- PW 6000 series engine

FIGURE-6-1-3-991-002-A01

6-1-3Page 3

Jun 01/12


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

**ON A/C A318-100

Engine Exhaust Temperatures Contours - Breakaway Power

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

6-1-4Page 1

Jun 01/12


**ON A/C A318-100

ELE

VA

TIO

N

FE

ET

050

100

150

200

250

300

350

400

015

3045

6075

9010

512

0

40 30 20 10 0036912

mft

PLA

NA

IRP

LAN

E

3000

lbs

OF

TH

RU

ST

GR

OU

ND

PLA

NE

ME

TE

RS

40 30 20 10 0036912

mft

T (

°K

)40

035

032

530

0

400

350

325

300

N_AC_060104_1_0010101_01_00

Engine Exhaust TemperaturesBreakaway Power -- CFM56 series engine

FIGURE-6-1-4-991-001-A01

6-1-4Page 2

Jun 01/12


**ON A/C A318-100

PW

A 6

000

− B

RE

AK

AW

AY

PO

WE

RA

LL T

EM

PE

RA

TU

RE

S A

RE

IN F

AH

RE

NH

EIT

(C

ELS

IUS

).N

OT

E:

AIR

PLA

NE

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

PLA

N

160°

F(7

1°C

)10

0°F

(38°

C)

160°

F(7

1°C

)10

0°F

(38°

C)

015

3046

61

250

300

050

100

150

200

7691

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

(18)60

(12)40 (6

)20 0

(18)60

(12)40 (6

)20 0

N_AC_060104_1_0020101_01_00

Engine Exhaust TemperaturesBreakaway Power -- PW 6000 series engine

FIGURE-6-1-4-991-002-A01

6-1-4Page 3

Jun 01/12


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

**ON A/C A318-100

Engine Exhaust Velocities Contours - Takeoff Power

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

6-1-5Page 1

Jun 01/12


**ON A/C A318-100

450

420

390

360

330

300

270

240

210

180

150

120

9060

30

010

020

030

040

050

070

060

080

090

010

0011

0012

0013

0014

0015

00

ME

TE

RS

FE

ET

ftm

V =

40

m/s

V =

20

m/s

V =

12

m/s

V =

40

m/s

V =

20

m/s

V =

12

m/s

PLA

NA

IRP

LAN

E

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

TA

KE

OF

F P

OW

ER

INC

LUD

ES

(W

OR

ST

CA

SE

)G

RO

UN

D P

LAN

EH

EA

DW

IND

(20

KT

S.)

mft

42 36 30 24 18 12 6 0

140

120

100 80 60 40 200

42 36 30 24 18 12 6 0

140

120

100 80 60 40 200

N_AC_060105_1_0010101_01_00

Engine Exhaust VelocitiesTakeoff Power -- CFM56 series engine

FIGURE-6-1-5-991-001-A01

6-1-5Page 2

Jun 01/12


**ON A/C A318-100

015

3046

61

250

300

AIR

PLA

NE

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

050

100

150

200

7691

0

CO

NV

ER

SIO

N F

AC

TO

R1

MP

H =

1.6

km

/h

PW

A 6

000

− T

AK

EO

FF

ALL

VE

LOC

ITY

VA

LUE

S A

RE

IN S

TA

TU

E M

ILE

S P

ER

HO

UR

.N

OT

E:

150

MP

H10

2 M

PH

62 M

PH

34 M

PH

TO

320

ft (9

8 m

)20

MP

H T

O40

0 ft

(122

m)

150

MP

H10

2 M

PH

62 M

PH

34 M

PH

TO

320

ft (9

8 m

)20

MP

H T

O40

0 ft

(122

m)

60(1

8) 40 (12) 20 (6

)FE

ET

(ME

TE

RS

)

060 (18) 40 (12) 20 (6

)FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

PLA

N

N_AC_060105_1_0020101_01_00

Engine Exhaust VelocitiesTakeoff Power -- PW 6000 series engine

FIGURE-6-1-5-991-002-A01

6-1-5Page 3

Jun 01/12


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

**ON A/C A318-100

Engine Exhaust Temperatures Contours - Takeoff Power

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

6-1-6Page 1

Jun 01/12


**ON A/C A318-100

60 40 20 0

18 12 6 0E

LEV

AT

ION

GR

OU

ND

PLA

NE

ftm

2040

6080

100

120

140

160

TA

KE

OF

F P

OW

ER

INC

LUD

ES

(W

OR

ST

CA

SE

):

HE

AD

WIN

D (

20 K

TS

)

GR

OU

ND

PLA

NE

FE

ET

ME

TE

RS

0

T =

425

° K

T =

370

° K

T =

315

° K

T =

425

° K

T =

370

° K

T =

315

° K

AIR

PLA

NE

1020

3040

50

ftm

PLA

N

60 40 20 0

18 12 6 0

N_AC_060106_1_0010101_01_00

Engine Exhaust TemperaturesTakeoff Power -- CFM56 series engine

FIGURE-6-1-6-991-001-A01

6-1-6Page 2

Jun 01/12


**ON A/C A318-100

PLA

N

200°

F(9

3°C

)10

0°F

(38°

C)

320°

F(1

60°

C)

(18)60

(12)40 (6

)20 0

015

3046

61

250

300

AIR

PLA

NE

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

050

100

150

200

7691

PW

A 6

000

− T

AK

EO

FF

ALL

TE

MP

ER

AT

UR

ES

AR

E IN

FA

HR

EN

HE

IT (

CE

LSIU

S).

NO

TE

:

320°

F(1

60°

C)

200°

F(9

3°C

)10

0°F

(38°

C)

FE

ET

(ME

TE

RS

)

(18)60

(12)40 (6

)20 0F

EE

T(M

ET

ER

S)

FE

ET

(ME

TE

RS

)

N_AC_060106_1_0020101_01_00

Engine Exhaust TemperaturesTakeoff Power -- PW 6000 series engine

FIGURE-6-1-6-991-002-A01

6-1-6Page 3

Jun 01/12


6-2-0 Airport and Community Noise

**ON A/C A318-100

Airport and Community Noise

1. Airport and Community Noise Data

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

6-2-0Page 1

Jun 01/12


6-2-1 Noise Data

**ON A/C A318-100

Noise Data

1. Noise Data for CFM56-5A series engine

A. Description of test conditions:

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

B. Engine parameters: 2 engines running

C. Meteorological data:

The meteorological parameters measured 1.6 m (5.25 ft) from the ground on the day of testwere as follows:- Temperature: 3˚C (37˚F)- Relative humidity: 66%- Atmospheric pressure: 1016 hPa- Wind speed: Negligible- No rain

2. Noise Data for CFM56-5B series engine






3. Noise Data for PW 6000 series engine


6-2-1Page 1

Jun 01/12






6-2-1Page 2

Jun 01/12


**ON A/C A318-100

N_AC_060201_1_0010101_01_00

GROUND IDLE

N1

CURVE

MAX THRUST POSSIBLEON BRAKES

20.8% 90%

8082

8486

8890

9294

9698

100102

104106

108110

112

0°10°

20°

30°

40°

50°

60°

70°

80°

90°

100°

110°

120°

130°

140°

150°

350°340°

330°

320°

310°

300°

290°

280°

270°

250°

240°

230°

220°

210°

NOISE REFERENCEPOINT

260°78

Airport and Community NoiseCFM56-5A series engine

FIGURE-6-2-1-991-001-A01

6-2-1Page 3

Jun 01/12


**ON A/C A318-100

GROUND IDLE

N1

CURVE


18.9% 87%

8082

8486

8890

9294

9698

100102

104106

108110

112

0°10°

20°

30°

40°

50°

60°

70°

80°

90°

100°

110°

120°

130°

140°

150°

350°340°

330°

320°

310°

300°

290°

280°

270°

250°

240°

230°

220°

210°


260°

N_AC_060201_1_0020101_01_00

78

Airport and Community NoiseCFM56-5B series engine

FIGURE-6-2-1-991-002-A01

6-2-1Page 4

Jun 01/12


**ON A/C A318-100

GROUND IDLE

N1

CURVE


0°10°

20°

30°

40°

50°

60°

70°

80°

90°

100°

110°

120°

140°

150°

350°340°

330°

320°

23.4% 92.7%

8082

8486

8890

9294

9698

100102

104106

108110

112

310°

300°

290°

280°

270°

250°

230°

220°

210°


260°

240°

130°

N_AC_060201_1_0030101_01_00

78

Airport and Community NoisePW 6000 series engine

FIGURE-6-2-1-991-003-A01

6-2-1Page 5

Jun 01/12


6-3-0 Danger Areas of Engines

**ON A/C A318-100

Danger Areas of Engines

1. Danger Areas of the Engines.

6-3-0Page 1

Jun 01/12


6-3-1 Ground Idle Power

**ON A/C A318-100

Ground Idle Power

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

6-3-1Page 1

Jun 01/12


**ON A/C A318-100

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

1.5 m(5 ft)

(7.2 ft)R = 2.2 m

INTAKE SUCTION DANGERAREA

ENTRY CORRIDOR

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

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

NO

EN

TR

Y 1

7 m

(55

ft) A

FT

OF

NO

ZZ

LE45°

(20 ft)

6.1 m

N_AC_060301_1_0010101_01_01

Danger Areas of EnginesCFM56 series engine

FIGURE-6-3-1-991-001-A01

6-3-1Page 2

Jun 01/12


**ON A/C A318-100

FEET(METERS)

60(18)

50(15)

40(12)

30(9)

20(6)

10(3) 0

10(3)

20(6)

30(9)

40(12)

50(15)

60(18)

INTAKE SUCTION DANGER AREA

ENTRY CORRIDOR

EXHAUST DANGER AREA (AFT OF EXHAUST NOZZLE):200 ft (61 m) − GROUND IDLE (20 kt HEADWIND)

3.3 ft(1 m)

R = 9 ft(2.74 m)

R = 9 ft(2.74 m)

3.3 ft(1 m)

30° 30°

N_AC_060301_1_0020101_01_01

Danger Areas of EnginesPW 6000 series engine

FIGURE-6-3-1-991-002-A01

6-3-1Page 3

Jun 01/12


6-3-2 Takeoff Power

**ON A/C A318-100

Takeoff Power

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

6-3-2Page 1

Jun 01/12


**ON A/C A318-100

40°

30°

INLET SUCTION DANGERAREA

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

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

TO

275

m (

900

ft) A

FT

OF

FA

N N

OZ

ZLE

TO 150 m (500 ft) AFTOF FAN NOZZLE

R = 5.9 m(19.5 ft)

1.8 m(6 ft)

N_AC_060302_1_0010101_01_01

Danger Areas of EnginesCFM56 series engine

FIGURE-6-3-2-991-001-A01

6-3-2Page 2

Jun 01/12


**ON A/C A318-100

FEET(METERS)

60(18)

50(15)

40(12)

30(9)

20(6)

10(3) 0

10(3)

20(6)

30(9)

40(12)

50(15)

60(18)

INTAKE SUCTION DANGER AREA

ENTRY CORRIDOR

EXHAUST DANGER AREA (AFT OF EXHAUST NOZZLE):600 ft (183 m) − TAKE OFF POWER (20 kt HEADWIND)

6 ft(1.83 m)

R = 20 ft(6.10 m)

R = 20 ft(6.10 m)

6 ft(1.83 m)

30° 30°

N_AC_060302_1_0020101_01_01

Danger Areas of EnginesPW 6000 series engine

FIGURE-6-3-2-991-002-A01

6-3-2Page 3

Jun 01/12


6-4-0 APU Exhaust Velocities and Temperatures

**ON A/C A318-100

APU Exhaust Velocities and Temperatures

1. APU Exhaust Velocities and Temperatures.

6-4-0Page 1

Jun 01/12


6-4-1 APU

**ON A/C A318-100

APU - APIC & GARRETT

1. This section gives APU exhaust velocities and temperatures.

6-4-1Page 1

Jun 01/12


**ON A/C A318-100

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

METERS

HEIGHT

m ft

FEET

METERS

5 10 15 20

16.404 32.808 49.212 65.616

80°C176°F

100°C212°F

120°C248°F

150°C302°F

200°C392°F

300°C572°F

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

N_AC_060401_1_0010101_01_00

Exhaust Velocities and TemperaturesAPU -- APIC & GARRETTFIGURE-6-4-1-991-001-A01

6-4-1Page 2

Jun 01/12


PAVEMENT DATA


**ON A/C A318-100

General Information

1. General Information

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

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

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

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

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

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

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

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

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

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

7-1-0Page 1

Jun 01/12


The report was prepared by the U.S Army Corps Engineers Waterways Experiment Station, Soils andPavement Laboratory, Vicksburg, Mississippi.

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

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

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

that is shown on the graph.

Section 7-7-1 gives the rigid pavement design curves that have been prepared with the use of theWestergaard Equation. This is in general accordance with the procedures outlined in the PortlandCement Association publications, ”Design of Concrete Airport Pavement”, 1973 and ”ComputerProgram for Airport Pavement Design”, (Program PDILB), 1967 both by Robert G. Packard.

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

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

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

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

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

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

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

Section 7-9-0 gives ACN data prepared in accordance with the ACN/PCN system as referenced inICAO Annex 14, ”Aerodromes”, Volume 1 Fourth Edition July 2004, incorporating Amendments 1 to6.The ACN/PCN system gives a standardized international airplane/pavement rating system replacingthe various S, T, TT, LCN, AUW, ISWL, etc., rating systems used throughout the world.

7-1-0Page 2

Jun 01/12


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

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

Numerically the ACN is two times the derived single wheel load expressed in thousands of kilograms.The derived single wheel is defined as the load on a single tire inflated to 1.25 Mpa (181 psi) thatwould have the same pavement requirements as the aircraft.

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

PCNPAVEMENT

TYPESUBGRADECATEGORY

TIRE PRESSURE CATEGORY EVALUATION METHOD

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

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

C -- Low Y -- To 1 Mpa (145 psi)

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

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

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

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

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

7-1-0Page 3

Jun 01/12


**ON A/C A318-100

MODEL WVAIRCRAFT

CODEA318−100 06 CA318−100 00 DA318−100 07 EA318−100 01 FA318−100 02 GA318−100 08 HA318−100 03 IA318−100 04 JA318−100 05 K

NOTE:

NOTE:CHAPTER 07 ONLY.THERE IS NO RELATION BETWEEN THESE A/C CODES AND THE ICAO A/C CODES USED FOR DETERMINING THE AIRPLANE WING SPAN ANDOUTER MAIN GEAR WHEEL SPAN AS DESCRIBED IN ICAO−ANNEX 14 VOLUME 1, AERODROME DESIGN AND OPERATION CHAPTER 1.4, TABLE 1−1.

FOR WEIGHT VARIANT DEFINITION, REFER TO CHAPTER 02−01−01.

THE A/C CODES ARE USED FOR CONFIGURATION MANAGEMENT OF

N_AC_070100_1_0010101_01_00

Aircraft CodesFIGURE-7-1-0-991-001-A01

7-1-0Page 4

Jun 01/12


7-2-0 Landing Gear Footprint

**ON A/C A318-100

Landing Gear Footprint

1. This section gives Landing Gear Footprint.

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

7-2-0Page 1

Jun 01/12


**ON A/C A318-100

A/C CODE

NOSE GEAR TIRE SIZE

NOSE GEAR TIRE PRESSURE

MAIN GEAR TIRE SIZE

12.3 bar (178 psi)

MAIN GEAR TIRE PRESSURE 10.2 bar (148 psi)

46 x 17 R20(46 x 16 − 20)

30 x 8.8 R15(30 x 8.8 − 15)

PERCENTAGE OF WEIGHT ON MAIN GEAR GROUP

C

SEE SECTION 7−4−1

927 mm(36.5 in)

500 mm(19.7 in)

10 252 mm

7 590 mm(24 ft 10.8 in)

(33 ft 7.6 in)

N_AC_070200_1_0010101_01_01

Landing Gear FootprintLanding Gear Footprint

FIGURE-7-2-0-991-001-A01

7-2-0Page 2

Jun 01/12


**ON A/C A318-100

927 mm(36.5 in)

500 mm(19.7 in)

10 252 mm

A/C CODE


NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE

D − E − F − G

30 x 8.8 R15(30 x 8.8 − 15)

12.8 bar (186 psi)


(33 ft 7.6 in)

46 x 17 R20(46 x 16 − 20)

7 590 mm(24 ft 10.8 in)


N_AC_070200_1_0020101_01_01


FIGURE-7-2-0-991-002-A01

7-2-0Page 3

Jun 01/12


**ON A/C A318-100

927 mm(36.5 in)

500 mm(19.7 in)

10 252 mm

7 590 mm(24 ft 10.8 in)


NOSE GEAR TIRE SIZE


MAIN GEAR TIRE SIZE

30 x 8.8 R15(30 x 8.8 − 15)

13.5 bar (196 psi)


46 x 17 R20(46 x 16 − 20)

(33 ft 7.6 in)

A/C CODE H − I − J − K


N_AC_070200_1_0030101_01_01


FIGURE-7-2-0-991-003-A01

7-2-0Page 4

Jun 01/12


7-3-0 Maximum Pavement Loads

**ON A/C A318-100

Maximum Pavement Loads

1. This section gives Maximum Pavement Loads.


7-3-0Page 1

Jun 01/12


**ON A/C A318-100

1

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GS

TA

TIC

BR

AK

ING

DE

CE

LER

AT

ION

@ 1

0 ft/

sS

TE

AD

Y B

RA

KIN

G

DE

CE

LER

AT

ION

@ 1

0 ft/

sA

T IN

ST

AN

TA

NE

OU

SB

RA

KIN

GC

OE

FF

ICIE

NT

= 0

.8

23

45

6H

(P

ER

ST

RU

T)

MA

XIM

UM

RA

MP

WE

IGH

T

lbkg

lbkg

lbkg

lbkg

lbkg

lbkg

C56

400

VM

G (

PE

R S

TR

UT

)V

NG

124

350

23 2

5010

550

35 8

7516

270

56 0

7525

430

19 3

258

760

44 8

5020

340

V(N

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

(MG

)M

AX

IMU

M V

ER

TIC

AL

MA

IN G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T A

FT

CG

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

MR

W =

56

400

kgM

RW

= 5

9 40

0 kg

NO

TE

:A

LL L

OA

DS

CA

LCU

LAT

ED

US

ING

AIR

PLA

NE

MA

XIM

UM

RA

MP

WE

IGH

T

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

FW

D C

G =

14

% M

AC

AT

A/C

WE

IGH

T =

56

400

kgF

WD

CG

= 1

5 %

MA

C A

T A

/C W

EIG

HT

= 5

9 40

0 kg

D E60

450

27 4

3021

025

9 54

048

375

21 9

40

MR

W =

61

400

kgF

WD

CG

= 1

5 %

MA

C A

T A

/C W

EIG

HT

= 6

1 40

0 kg

MR

W =

56

400

kgM

RW

= 5

9 40

0 kg

AF

T C

G =

35

% M

AC

AT

A/C

WE

IGH

T =

56

400

kgA

FT

CG

= 3

3.9

% M

AC

AT

A/C

WE

IGH

T =

59

400

kgM

RW

= 6

1 40

0 kg

AF

T C

G =

32.

9 %

MA

C A

T A

/C W

EIG

HT

= 6

1 40

0 kg

59 4

0013

0 95

023

900

10 8

4037

150

16 8

5058

750

26 6

5020

350

9 23

047

000

21 3

20

61 4

0013

5 37

524

700

11 2

0038

350

17 4

00

N_AC_070300_1_0200101_01_00

V

H

(1)

A/C

CO

DE

C D E

(2)

C D E

Maximum Pavement LoadsMaximum Pavement LoadsFIGURE-7-3-0-991-020-A01

7-3-0Page 2

Jun 01/12


**ON A/C A318-100

1

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GS

TA

TIC

BR

AK

ING

DE

CE

LER

AT

ION

@ 1

0 ft/

sS

TE

AD

Y B

RA

KIN

G

DE

CE

LER

AT

ION

@ 1

0 ft/

sA

T IN

ST

AN

TA

NE

OU

SB

RA

KIN

GC

OE

FF

ICIE

NT

= 0

.8

23

45

6H

(P

ER

ST

RU

T)

MA

XIM

UM

RA

MP

WE

IGH

T

lbkg

lbkg

lbkg

lbkg

lbkg

lbkg

F61

900

VM

G (

PE

R S

TR

UT

)V

NG

136

475

24 9

0011

290

38 6

7517

540

60 9

0027

620

21 2

009

620

48 7

0022

100

(NG

)M

AX

IMU

M V

ER

TIC

AL

NO

SE

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

FO

RW

AR

D C

G

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

G

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

MR

W =

61

900

kgM

RW

= 6

3 40

0 kg

NO

TE

:A

LL L

OA

DS

CA

LCU

LAT

ED

US

ING

AIR

PLA

NE

MA

XIM

UM

RA

MP

WE

IGH

T

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

FW

D C

G =

15

% M

AC

AT

A/C

WE

IGH

T =

61

900

kgF

WD

CG

= 1

5 %

MA

C A

T A

/C W

EIG

HT

= 6

3 40

0 kg

G H63

150

28 6

4022

075

10 0

1050

525

22 9

20

MR

W =

64

400

kgF

WD

CG

= 1

5.8

% M

AC

AT

A/C

WE

IGH

T =

64

400

kg

MR

W =

61

900

kgM

RW

= 6

3 40

0 kg

AF

T C

G =

32.

7 %

MA

C A

T A

/C W

EIG

HT

= 6

1 90

0 kg

AF

T C

G =

32

% M

AC

AT

A/C

WE

IGH

T =

63

400

kgM

RW

= 6

4 40

0 kg

AF

T C

G =

32

% M

AC

AT

A/C

WE

IGH

T =

64

400

kg

63 4

0013

9 77

525

475

11 5

6039

575

17 9

5062

175

28 2

0021

725

9 85

049

725

22 5

60

64 4

0014

1 97

525

400

11 5

2039

700

18 0

10

N_AC_070300_1_0210101_01_00

V

(MG

)V

H

(1)

A/C

CO

DE

F G H

(2)

F G H


7-3-0Page 3

Jun 01/12


**ON A/C A318-100

1

ST

AT

IC L

OA

D A

TM

OS

T F

WD

CG

ST

AT

IC L

OA

D A

TM

AX

AF

T C

GS

TA

TIC

BR

AK

ING

DE

CE

LER

AT

ION

@ 1

0 ft/

sS

TE

AD

Y B

RA

KIN

G

DE

CE

LER

AT

ION

@ 1

0 ft/

sA

T IN

ST

AN

TA

NE

OU

SB

RA

KIN

GC

OE

FF

ICIE

NT

= 0

.8

23

45

6H

(P

ER

ST

RU

T)

MA

XIM

UM

RA

MP

WE

IGH

T

lbkg

lbkg

lbkg

lbkg

lbkg

lbkg

I64

900

VM

G (

PE

R S

TR

UT

)V

NG

143

075

25 3

5011

500

39 7

7518

040

63 6

5028

870

22 2

2510

090

50 9

2523

090

(NG

)M

AX

IMU

M V

ER

TIC

AL

NO

SE

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

FO

RW

AR

D C

G

(MG

)M

AX

IMU

M V

ER

TIC

AL

MA

IN G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T A

FT

CG

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

MR

W =

64

900

kgM

RW

= 6

6 40

0 kg

NO

TE

:A

LL L

OA

DS

CA

LCU

LAT

ED

US

ING

AIR

PLA

NE

MA

XIM

UM

RA

MP

WE

IGH

T

22

V(N

G)

V(M

G)

H

A/C

CO

DE

(1)

(2)

FW

D C

G =

16.

2 %

MA

C A

T A

/C W

EIG

HT

= 6

4 90

0 kg

FW

D C

G =

15

% M

AC

AT

A/C

WE

IGH

T =

63

000

kg

J K67

100

30 4

3023

425

10 6

3053

675

24 3

40

MR

W =

68

400

kgF

WD

CG

= 1

5 %

MA

C A

T A

/C W

EIG

HT

= 6

3 00

0 kg

MR

W =

64

900

kgM

RW

= 6

6 40

0 kg

AF

T C

G =

32

% M

AC

AT

A/C

WE

IGH

T =

64

900

kgA

FT

CG

= 3

2 %

MA

C A

T A

/C W

EIG

HT

= 6

6 40

0 kg

MR

W =

68

400

kgA

FT

CG

= 3

2 %

MA

C A

T A

/C W

EIG

HT

= 6

8 40

0 kg

66 4

0014

6 37

525

325

11 4

9039

275

17 8

2065

125

29 5

4022

750

10 3

2052

100

23 6

30

68 4

0015

0 80

025

325

11 4

9039

250

17 8

10

N_AC_070300_1_0220101_01_00

V V

H

(1)

A/C

CO

DE

I J K

(2)

I J K


7-3-0Page 4

Jun 01/12



**ON A/C A318-100

Landing Gear Loading on Pavement

1. General

In the example shown in Section 7-4-1 Landing Gear Loading on Pavement, A/C Code C, the GrossAircraft Weight is 48 000 kg (105 825 lb) and the percentage of weight on the Main Landing Gear is90.2 %.

For these conditions, the total weight on the Main Landing Gear is 43 280 kg (95 425 lb).

7-4-0Page 1

Jun 01/12



**ON A/C A318-100

Landing Gear Loading on Pavement

1. This section gives Landing Gear Loading on Pavement.


7-4-1Page 1

Jun 01/12


**ON A/C A318-100

78 80 82 84 86 88 100

PERCENTAGE OF WEIGHT ON MAIN GEAR

90 92 94 96 9835

40

45

50

55

6010 20 30 40 50

PERCENTAGE MAC

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)

35

40

45

50

55

60

TAKE OFF

A/C CODE C

CG FOR ACNCALCULATIONS

MZFW = 53 000 kg

MTOW/MLW = 56 000 kg

LANDING

N_AC_070401_1_0290101_01_00

Landing Gear Loading on PavementFIGURE-7-4-1-991-029-A01

7-4-1Page 2

Jun 01/12


**ON A/C A318-100

78 80 82 84 86 88 100


90 92 94 96 9835

40

45

55

50

6010 20 30 40 50

PERCENTAGE MAC

35

40

45

50

55

60

AIR

CR

AF

T G

RO

SS

WE

IGH

T−

(x

1 00

0 kg

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)

A/C CODE D

MTOW = 59 000 kg


MLW = 56 000 kg

LANDING

TAKE OFF

N_AC_070401_1_0300101_01_00

MZFW = 53 000 kg


7-4-1Page 3

Jun 01/12


**ON A/C A318-100

78 80 82 84 86 88 10090 92 94 96 9835 35

65 65

40

45

50

55

40

45

50

55

6060


AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)

10 20 30 40 50

PERCENTAGE MAC

A/C CODE E

MTOW = 61 000 kg

MLW = 56 000 kg

MZFW = 53 000 kg


LANDING

TAKE OFF

N_AC_070401_1_0310101_01_00


7-4-1Page 4

Jun 01/12


**ON A/C A318-100

78 80 82 84 86 88 10090 92 94 96 9835 35

65 65

40

45

50

55

40

45

50

55

6060


AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)

10 20 30 40 50

PERCENTAGE MAC

A/C CODE F

MTOW = 61 500 kg

MLW = 56 000 kg

MZFW = 53 000 kg

CG FOR ACNCALCULATIONSLANDING

TAKE OFF

N_AC_070401_1_0320101_01_00


7-4-1Page 5

Jun 01/12


**ON A/C A318-100

78 80 82 84 86 88 10090 92 94 96 9835 35

65 65

40

45

50

55

40

45

50

55

6060

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)

10 20 30 40 50

PERCENTAGE MAC

A/C CODE G

MTOW = 63 000 kg

MLW = 57 500 kg


N_AC_070401_1_0330101_01_00

MZFW = 54 500 kg

LANDING

TAKE OFF



7-4-1Page 6

Jun 01/12


**ON A/C A318-100

78 80 82 84 86 88 10090 92 94 96 9835 35

65 65

40

45

50

55

40

45

50

55

6060


AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)

10 20 30 40 50

PERCENTAGE MAC

A/C CODE H

MTOW = 64 000 kg

CG FOR ACNCALCULATIONSLANDING

TAKE OFF

MLW = 56 000 kg

MZFW = 53 000 kg

N_AC_070401_1_0340101_01_00


7-4-1Page 7

Jun 01/12


**ON A/C A318-100

78 80 82 84 86 88 10090 92 94 96 9835 35

65 65

40

45

50

55

40

45

50

55

6060


AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)

10 20 30 40 50

PERCENTAGE MAC


TAKE OFF

LANDING

MTOW = 64 500 kg

A/C CODE I

MLW = 57 500 kg

MZFW = 54 500 kg

N_AC_070401_1_0350101_01_00


7-4-1Page 8

Jun 01/12


**ON A/C A318-100

78 80 82 84 86 88 10090 92 94 96 9835 35

65 65

40

45

50

55

40

45

50

55

6060


AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)

10 20 30 40 50

PERCENTAGE MAC

A/C CODE J


TAKE OFF

LANDING

MLW = 57 500 kg

MTOW = 66 000 kg

MZFW = 54 500 kg

70 70

N_AC_070401_1_0360101_01_00


7-4-1Page 9

Jun 01/12


**ON A/C A318-100

78 80 82 84 86 88 10090 92 94 96 9835 35

65 65

40

45

50

55

40

45

50

55

6060

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(x

1 00

0 kg

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

− (

x 1

000

kg)

10 20 30 40 50

PERCENTAGE MAC

70 70

MTOW = 68 000 kg

TAKE OFF


MZFW = 54 500 kg

MLW = 57 500 kg


A/C CODE K

N_AC_070401_1_0370101_01_00

LANDING


7-4-1Page 10

Jun 01/12



**ON A/C A318-100

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

1. General

In order to determine a particular Flexible Pavement Thickness, the Subgrade Strength (CBR), theAnnual Departure Level and the weight on one Main Landing Gear must be known.

In the example shown in Section 7-5-1 Flexible Pavement Requirements, A/C Code C for:- a CBR value of 10- an Annual Departure Level of 25 000- the Load on one MLG of 20 000 kg (44 100 lb).

For these conditions, the Flexible Pavement Thickness is 40.9 cm (16.1 in).

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

7-5-0Page 1

Jun 01/12



**ON A/C A318-100

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

1. This section gives Flexible Pavement Requirements.


7-5-1Page 1

Jun 01/12


**ON A/C A318-100

10 15 20 30 40 60 80 100 120 150 180

806050403020151063

806050403020151063

[CENTIMETERS]

FLEXIBLE PAVEMENT THICKNESS

46 x 17 R20 (46 x 16−20) TIRESTIRE PRESSURE CONSTANT AT 10.2 bar (148 psi)

[INCHES]

SUBGRADE STRENGTH − CBR

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

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

A/C CODE C ALPHA FACTOR = 0.9

FOR ACN CALCULATIONS10 000 COVERAGES USED

WEIGHT ON ONE MAIN LANDING GEAR25 430 kg (56 075 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)

N_AC_070501_1_0290101_01_00

Flexible Pavement RequirementsFIGURE-7-5-1-991-029-A01

7-5-1Page 2

Jun 01/12


**ON A/C A318-100

10 15 20 30 40 60 80 100 120 150 180

806050403020151063

806050403020151063

[CENTIMETERS]



[INCHES]


N_AC_070501_1_0300101_01_00



ALPHA FACTOR = 0.9


A/C CODE D


20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)


7-5-1Page 3

Jun 01/12


**ON A/C A318-100

10 15 20 30 40 60 80 100 120 150 180

806050403020151063

806050403020151063

[CENTIMETERS]



[INCHES]




ALPHA FACTOR = 0.9


A/C CODE E


20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)

N_AC_070501_1_0310101_01_00


7-5-1Page 4

Jun 01/12


**ON A/C A318-100

10 15 20 30 40 60 80 100 120 150 180

806050403020151063

806050403020151063

[CENTIMETERS]



[INCHES]



ALPHA FACTOR = 0.9



A/C CODE F


20 000 kg (44 100 lb)15 000 kg (33 075 lb)

25 000 kg (55 125 lb)

N_AC_070501_1_0320101_01_00

10 000 kg (22 050 lb)


7-5-1Page 5

Jun 01/12


**ON A/C A318-100

10 15 20 30 40 60 80 100 120 150 180

806050403020151063

806050403020151063

[CENTIMETERS]



[INCHES]




ALPHA FACTOR = 0.9


A/C CODE G

28 200 kg (62 175 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)

WEIGHT ON ONE MAIN LANDING GEAR

N_AC_070501_1_0330101_01_00


7-5-1Page 6

Jun 01/12


**ON A/C A318-100

10 15 20 30 40 60 80 100 120 150 180

806050403020151063

806050403020151063

[CENTIMETERS]



[INCHES]




ALPHA FACTOR = 0.9


A/C CODE H


20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)

N_AC_070501_1_0340101_01_00


7-5-1Page 7

Jun 01/12


**ON A/C A318-100

10 15 20 30 40 60 80 100 120 150 180

806050403020151063

806050403020151063

[CENTIMETERS]



[INCHES]




ALPHA FACTOR = 0.9


A/C CODE I

28 870 kg (63 650 lb)

20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)


N_AC_070501_1_0350101_01_00

Flexible Pavement RequirementsFlexible Pavement Requirements

FIGURE-7-5-1-991-035-A01

7-5-1Page 8

Jun 01/12


**ON A/C A318-100

10 15 20 30 40 60 80 100 120 150 180

806050403020151063

806050403020151063

[CENTIMETERS]



[INCHES]




ALPHA FACTOR = 0.9


A/C CODE J


20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)

N_AC_070501_1_0360101_01_00


7-5-1Page 9

Jun 01/12


**ON A/C A318-100

10 15 20 30 40 60 80 100 120 150 180

806050403020151063

806050403020151063

[CENTIMETERS]



[INCHES]




ALPHA FACTOR = 0.9


A/C CODE K


20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 000 kg (55 125 lb)

N_AC_070501_1_0370101_01_00


7-5-1Page 10

Jun 01/12



**ON A/C A318-100

Flexible Pavement Requirements - LCN Conversion

1. General

In order to determine the airplane weight that can be accommodated on a particular FlexiblePavement, both the LCN of the pavement and the thickness (h) must be known.

In the example shown in Section 7-6-1 Flexible Pavement Requirements - LCN Conversion, A/C CodeC for:The thickness (h) is shown at 20 inches with an LCN of 47.7.For these conditions, the weight on one Main Landing Gear is 25 000 kg (55 125 lb).

7-6-0Page 1

Jun 01/12



**ON A/C A318-100

Flexible Pavement Requirements - LCN Conversion

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


7-6-1Page 1

Jun 01/12


**ON A/C A318-100

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

0.2

bar

(148

psi

)46

x 1

7 R

20 (

46 x

16−

20)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20

EQUIVALENT SINGLE WHEEL LOAD [1 000 kg]

10

EQUIVALENT SINGLE WHEEL LOAD [1 000 lb]

1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

WE

IGH

T O

N O

NE

MA

IN

25 4

30 k

g

(56

075

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

RM

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

20

10 0

00 k

g

(22

050

lb)

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

C

N_AC_070601_1_0320101_01_00

2 03

21

524

1 01

6

Flexible Pavement Requirements - LCN ConversionFIGURE-7-6-1-991-032-A01

7-6-1Page 2

Jun 01/12


**ON A/C A318-100

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.4

bar

(165

psi

)46

x 1

7 R

20 (

46 x

16−

20)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

WE

IGH

T O

N O

NE

MA

IN

26 6

50 k

g

(58

750

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

RM

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

20

10 0

00 k

g

(22

050

lb)

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

D

2 03

21

524

1 01

6

N_AC_070601_1_0330101_01_00


7-6-1Page 3

Jun 01/12


**ON A/C A318-100

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.4

bar

(165

psi

)46

x 1

7 R

20 (

46 x

16−

20)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

WE

IGH

T O

N O

NE

MA

IN

27 4

30 k

g

(60

475

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

RM

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

20

10 0

00 k

g

(22

050

lb)

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 03

21

524

1 01

6

N_AC_070601_1_0340101_01_00

A/C

CO

DE

E


7-6-1Page 4

Jun 01/12


**ON A/C A318-100

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.4

bar

(165

psi

)46

x 1

7 R

20 (

46 x

16−

20)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

WE

IGH

T O

N O

NE

MA

IN

27 6

20 k

g

(60

900

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

RM

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

20

10 0

00 k

g

(22

050

lb)

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

2 03

21

524

1 01

6

N_AC_070601_1_0350101_01_00

A/C

CO

DE

F


7-6-1Page 5

Jun 01/12


**ON A/C A318-100

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

1.4

bar

(165

psi

)46

x 1

7 R

20 (

46 x

16−

20)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

WE

IGH

T O

N O

NE

MA

IN

28 2

00 k

g

(62

175

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

RM

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

20

10 0

00 k

g

(22

050

lb)

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

G

2 03

21

524

1 01

6

N_AC_070601_1_0360101_01_00


7-6-1Page 6

Jun 01/12


**ON A/C A318-100

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.4

bar

(180

psi

)46

x 1

7 R

20 (

46 x

16−

20)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

WE

IGH

T O

N O

NE

MA

IN

28 6

40 k

g

(63

150

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

RM

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

20

10 0

00 k

g

(22

050

lb)

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

H

2 03

21

524

1 01

6

N_AC_070601_1_0370101_01_00


7-6-1Page 7

Jun 01/12


**ON A/C A318-100

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.4

bar

(180

psi

)46

x 1

7 R

20 (

46 x

16−

20)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

20

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

I

2 03

21

524

1 01

6

N_AC_070601_1_0380101_01_00

WE

IGH

T O

N O

NE

MA

IN

28 8

70 k

g

(63

650

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

R

10 0

00 k

g

(22

050

lb)


7-6-1Page 8

Jun 01/12


**ON A/C A318-100

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.4

bar

(180

psi

)46

x 1

7 R

20 (

46 x

16−

20)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

WE

IGH

T O

N O

NE

MA

IN

29 5

40 k

g

(65

125

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

RM

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

20

10 0

00 k

g

(22

050

lb)

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

J

2 03

21

524

1 01

6

N_AC_070601_1_0390101_01_00


7-6-1Page 9

Jun 01/12


**ON A/C A318-100

NO

TE

:IC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

Sec

ond

Edi

tion

1965

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

IN

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

2.4

bar

(180

psi

)46

x 1

7 R

20 (

46 x

16−

20)

TIR

ES

35 30 25 20 15 10 5 080

100

6050

4030

20


10


1020304050607080

8070

6050

4030

100

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S [I

NC

HE

S]

WE

IGH

T O

N O

NE

MA

IN

30 4

30 k

g

(67

075

lb)

25 0

00 k

g

(55

125

lb)

20 0

00 k

g

(44

100

lb)

15 0

00 k

g

(33

075

lb)

LAN

DIN

G G

EA

RM

AX

IMU

M R

AM

P W

EIG

HT

AN

D A

FT

CG

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

R L

OA

D A

T

20

10 0

00 k

g

(22

050

lb)

762

254

508

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)

A/C

CO

DE

K

2 03

21

524

1 01

6

N_AC_070601_1_0400101_01_00


7-6-1Page 10

Jun 01/12



**ON A/C A318-100

Rigid Pavement Requirements - Portland Cement Association Design Method

1. General

In order to determine a particular Rigid Pavement Thickness, the Subgrade Modulus (k), theallowable working stress and the weight on one Main Landing Gear must be known.

In the example shown in Section 7-7-1 Rigid Pavement Requirements (PCA), A/C Code C for:- a ”k” value of 150 MN/m3 (550 lbf/in3)- an allowable working stress of 31.6 kgf/cm2 (450 lbf/in2)- the load on one MLG of 20 000 kg (44 100 lb).For these conditions, the Rigid Pavement Thickness is 18.4 cm (7.2 in).

7-7-0Page 1

Jun 01/12



**ON A/C A318-100

Rigid Pavement Requirements - Portland Cement Association Design Method

1. This section gives Rigid Pavement Requirements.


7-7-1Page 1

Jun 01/12


**ON A/C A318-100

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

SLIGHTLY FOR ANY OTHER

THE CURVES ARE EXACT FORK = 80 MN/m³ BUT DEVIATE

VALUES OF K

REFERENCE:

AIRPORT PAVEMENTS" AND "COMPUTER PROGRAM FOR AIRPORT PAVEMENT DESIGN − PROGRAM PDILB" PORTLAND CEMENT ASSOCIATION

"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

1436

33

31

29

27

24

22

20

17

15 200

300

400

500

600

700

800

900

1000 70

58

52

45

39

33

27

20



25 000 kg (55 125 lb)20 000 kg (44 100 lb)15 000 kg (33 075 lb)10 000 kg (22 050 lb)

25 430 kg (56 075 lb)

A/C CODE CRIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_0290101_01_00

Rigid Pavement Requirements (PCA)FIGURE-7-7-1-991-029-A01

7-7-1Page 2

Jun 01/12


**ON A/C A318-100




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

200

300

400

500

600

700

800

900

1000 70

58

52

45

39

33

27

20




26 655 kg (58 750 lb)

A/C CODE DRIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³

N_AC_070701_1_0300101_01_00

36

33

31

29

27

24

22

20

17

15


7-7-1Page 3

Jun 01/12


**ON A/C A318-100




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

200

300

400

500

600

700

800

900

1000 70

58

52

45

39

33

27

20

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


36

33

31

29

27

24

22

20

17

15

N_AC_070701_1_0310101_01_00


A/C CODE E

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³



27 425 kg (60 450 lb)


7-7-1Page 4

Jun 01/12


**ON A/C A318-100




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

200

300

400

500

600

700

800

900

1000 70

58

52

45

39

33

27

20

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


36

33

31

29

27

24

22

20

17

15


A/C CODE F

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³



27 620 kg (60 900 lb)

N_AC_070701_1_0320101_01_00


7-7-1Page 5

Jun 01/12


**ON A/C A318-100




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

200

300

400

500

600

700

800

900

1000 70

58

52

45

39

33

27

20

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


36

33

31

29

27

24

22

20

17

15

N_AC_070701_1_0330101_01_00


A/C CODE G

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³



28 195 kg (62 175 lb)


7-7-1Page 6

Jun 01/12


**ON A/C A318-100




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

200

300

400

500

600

700

800

900

1000 70

58

52

45

39

33

27

20


A/C CODE HRIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³



28 645 kg (63 150 lb)

N_AC_070701_1_0340101_01_00

36

33

31

29

27

24

22

20

17

15


7-7-1Page 7

Jun 01/12


**ON A/C A318-100




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

200

300

400

500

600

700

800

900

1000 70

58

52

45

39

33

27

20

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


36

33

31

29

27

24

22

20

17

15


A/C CODE I

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³



28 865 kg (63 650 lb)

N_AC_070701_1_0350101_01_00


7-7-1Page 8

Jun 01/12


**ON A/C A318-100




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

200

300

400

500

600

700

800

900

1000 70

58

52

45

39

33

27

20


A/C CODE JRIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³



29 535 kg (65 125 lb)

N_AC_070701_1_0360101_01_00

36

33

31

29

27

24

22

20

17

15


7-7-1Page 9

Jun 01/12


**ON A/C A318-100




VALUES OF K

REFERENCE:


"DESIGN OF CONCRETE

[INC

HE

S]

[lb/in

²]

[kg/

cm²]

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

6

7

8

9

10

11

12

13

14

200

300

400

500

600

700

800

900

1000 70

58

52

45

39

33

27

20

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S[C

EN

TIM

ET

ER

S]


36

33

31

29

27

24

22

20

17

15

N_AC_070701_1_0370101_01_00


A/C CODE K

K = 40 MN/m³K = 80 MN/m³K = 150 MN/m³

K = 20 MN/m³



30 430 kg (67 100 lb)


7-7-1Page 10

Jun 01/12



**ON A/C A318-100

Radius of Relative Stiffness

1. This section gives Radius of Relative Stiffness.

7-8-1Page 1

Jun 01/12


**ON A/C A318-100

d6.06.57.07.5

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

8.08.59.09.5

10.010.511.011.512.012.513.013.514.014.515.015.516.016.517.017.518.019.020.021.022.023.024.025.0

31.4833.4335.3437.2239.0640.8842.6744.4346.1847.9049.6051.2852.9454.5956.2257.8359.4361.0269.5964.1565.6967.2368.7570.2671.7674.7377.6680.5583.4186.2489.0491.81

29.3031.1132.8934.6336.3538.0439.7141.3542.9744.5746.1647.7249.2750.8052.3253.8255.3156.7858.2559.7061.1362.5663.9865.3866.7869.5472.2774.9677.6380.2682.8685.44

26.4728.1129.7231.2932.8534.3735.8837.3638.8340.2841.7143.1244.5245.9047.2748.6349.9851.3152.6353.9455.2456.5357.8159.0860.3462.8465.3067.7470.1472.5274.8777.20

24.6326.1627.6529.1230.5731.9933.3934.7736.1437.4838.8140.1341.4342.7243.9945.2646.5147.7548.9850.2051.4152.6153.8054.9856.1558.4860.7763.0465.2867.4969.6871.84

23.3024.7426.1527.5428.9130.2531.5832.8934.1735.4536.7137.9539.1840.4041.6142.8043.9845.1646.3247.4748.6249.7550.8852.0053.1155.3157.4759.6261.7363.8365.9067.95

22.2623.6424.9926.3227.6228.9130.1731.4232.6533.8735.0736.2637.4438.6039.7540.8942.0243.1544.2645.3646.4547.5448.6149.6850.7452.8454.9156.9658.9860.9862.9664.92

21.4222.7424.0425.3226.5827.8129.0330.2331.4232.5933.7534.8936.0237.1438.2539.3540.4441.5142.5843.6444.7045.7446.7747.8048.8250.8452.8454.8156.7558.6860.5862.46

20.7222.0023.2524.4925.7026.9028.0829.2430.3931.5232.6433.7434.8435.9236.9938.0639.1140.1541.1942.2143.2344.2445.2446.2347.2249.1751.1053.0154.8956.7558.5960.41

19.1320.3121.4722.6123.7424.8425.9327.0028.0629.1130.1431.1632.1733.1734.1635.1436.1237.0838.0338.9839.9240.8541.7842.7043.6145.4147.1948.9550.6952.4154.1155.79

L = Ed

= 24.1652dk

43

43

12 (1 − ) k2

RADIUS OF RELATIVE STIFFNESS (L)VALUES IN INCHES

E = YOUNG’S MODULUS = 4 x 10 psi

k = SUBGRADE MODULUS, lb/in

d = RIGID PAVEMENT THICKNESS, (in)

= POISSON’S RATIO = 0.15

WHERE6

3

N_AC_070801_1_0010101_01_01

Radius of Relative Stiffness(Reference: Portland Cement Association)

FIGURE-7-8-1-991-001-A01

7-8-1Page 2

Jun 01/12


7-8-2 Rigid Pavement Requirements - LCN Conversion

**ON A/C A318-100

Rigid Pavement Requirements - LCN Conversion

1. GeneralIn order to determine the airplane weight that can be accommodated on a particular Rigid Pavement,both the LCN of the pavement and the Radius of Relative Stiffness (L) must be known.

In the example shown in this section Rigid Pavement Requirements - LCN Conversion, A/C Code Cfor:- The Radius of Relative Stiffness is shown at 762 mm (30 in) with an LCN of 51.1.

For these conditions, the weight on one Main Landing Gear is 25 000 kg (55 125 lb).


7-8-2Page 1

Jun 01/12


**ON A/C A318-100

2030

4050

100

8070

6001020304050607080

6080

5040

3020

1005101520253035

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

2 ba

r (1

48 p

si)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:


N_AC_070802_1_0320101_01_00

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

762

254

508

2 28

61

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R25

430

kg

(5

6 07

5 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)10

000

kg

(2

2 05

0 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

A/C

CO

DE

C

Rigid Pavement Requirements - LCN ConversionFIGURE-7-8-2-991-032-A01

7-8-2Page 2

Jun 01/12


**ON A/C A318-100

2030

4050

100

8070

6001020304050607080

6080

5040

3020

1005101520253035

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

762

254

508

2 28

61

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R26

655

kg

(5

8 75

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)10

000

kg

(2

2 05

0 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

A/C

CO

DE

D

N_AC_070802_1_0330101_01_00


7-8-2Page 3

Jun 01/12


**ON A/C A318-100

2030

4050

100

8070

6001020304050607080

6080

5040

3020

1005101520253035

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

762

254

508

2 28

61

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R27

425

kg

(6

0 45

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)10

000

kg

(2

2 05

0 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

A/C

CO

DE

E

N_AC_070802_1_0340101_01_00


7-8-2Page 4

Jun 01/12


**ON A/C A318-100

2030

4050

100

8070

6001020304050607080

6080

5040

3020

1005101520253035

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

762

254

508

2 28

61

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R27

620

kg

(6

0 90

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)10

000

kg

(2

2 05

0 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

A/C

CO

DE

F

N_AC_070802_1_0350101_01_00


7-8-2Page 5

Jun 01/12


**ON A/C A318-100

2030

4050

100

8070

6001020304050607080

6080

5040

3020

1005101520253035

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

762

254

508

2 28

61

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R28

195

kg

(6

2 17

5 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)10

000

kg

(2

2 05

0 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

A/C

CO

DE

G

N_AC_070802_1_0360101_01_00


7-8-2Page 6

Jun 01/12


**ON A/C A318-100

2030

4050

100

8070

6001020304050607080

6080

5040

3020

1005101520253035

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

762

254

508

2 28

61

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R28

645

kg

(6

3 15

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)10

000

kg

(2

2 05

0 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

A/C

CO

DE

H

N_AC_070802_1_0370101_01_00


7-8-2Page 7

Jun 01/12


**ON A/C A318-100

2030

4050

100

8070

6001020304050607080

6080

5040

3020

1005101520253035

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

762

254

508

2 28

61

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R28

865

kg

(6

3 65

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)10

000

kg

(2

2 05

0 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

A/C

CO

DE

I

N_AC_070802_1_0380101_01_00


7-8-2Page 8

Jun 01/12


**ON A/C A318-100

2030

4050

100

8070

6001020304050607080

6080

5040

3020

1005101520253035

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

762

254

508

2 28

61

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R29

535

kg

(6

5 12

5 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)10

000

kg

(2

2 05

0 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

A/C

CO

DE

J

N_AC_070802_1_0390101_01_00


7-8-2Page 9

Jun 01/12


**ON A/C A318-100

2030

4050

100

8070

6001020304050607080

6080

5040

3020

1005101520253035

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S [I

NC

HE

S]

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

econ

d E

ditio

n 19

65N

OT

E:


RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)

762

254

508

2 28

61

524

1 01

6

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R30

430

kg

(6

7 10

0 lb

)25

000

kg

(5

5 12

5 lb

)20

000

kg

(4

4 10

0 lb

)15

000

kg

(3

3 07

5 lb

)10

000

kg

(2

2 05

0 lb

)

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

GM

AX

IMU

M P

OS

SIB

LE M

AIN

GE

AR

LO

AD

AT

A/C

CO

DE

K

N_AC_070802_1_0400101_01_00


7-8-2Page 10

Jun 01/12


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

**ON A/C A318-100

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

1. General

The table of Section 7-8-1, Radius of Relative Stiffness, presents ”L” values based on Young’sModulus (E) of 4 000 000 psi and Poisson’s Ratio (µ) of 0.15.

To find ”L” values based on other values of ”E” and ”µ”, see Section 7-8-4.

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

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

7-8-3Page 1

Jun 01/12



**ON A/C A318-100

Radius of Relative Stiffness

1. This section gives Radius of Relative Stiffness.

7-8-4Page 1

Jun 01/12


**ON A/C A318-100

E F

AC

TO

RF

AC

TO

R

EFFECT OF E ON L VALUES

0.00 0.05 0.10 0.15 0.20 0.25

1.015

1.010

1.005

1.000

0.995

0.80

0.85

0.90

0.95

1.00

1.05

1.10

0 1 2 3 4 5

EFFECT OF ON L VALUES

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

E, Young’s Modulus (10 , PSI)

, Poisson’s Ratio

N_AC_070804_1_0010101_01_02

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

FIGURE-7-8-4-991-001-A01

7-8-4Page 2

Jun 01/12


7-9-0 ACN/PCN Reporting System

**ON A/C A318-100

ACN/PCN Reporting System

1. General

To determine the ACN of an aircraft on flexible or rigid pavement, both the aircraft gross weight andthe subgrade strength must be known.

In the example shown in Section 7-9-1 Aircraft Classification Number -- Flexible Pavement, A/C CodeC, for an aircraft gross weight of 50 000 kg (110 225 lb) and low subgrade strength (code C), theACN for the flexible pavement is 25.5.

In the example shown in Section 7-9-2 Aircraft Classification Number -- Rigid Pavement, A/C CodeC, for an aircraft gross weight of 50 000 kg (110 225 lb) and medium subgrade strength (code B),the ACN for the rigid pavement is 25.5.

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

7-9-0Page 1

Jun 01/12


7-9-1 Aircraft Classification Number - Flexible Pavement

**ON A/C A318-100

Aircraft Classification Number - Flexible Pavement

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


7-9-1Page 1

Jun 01/12


**ON A/C A318-100

5550

4540

3510152025303540

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)

AIRCRAFT CLASSIFICATION NUMBER (ACN)

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

2 ba

r (1

48 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

5 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

77

60

8899

110

121

132

(x 1

000

lb)

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

A/C

CO

DE

C

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0420101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E C

Aircraft Classification Number -- Flexible PavementFIGURE-7-9-1-991-042-A01

7-9-1Page 2

Jun 01/12


**ON A/C A318-100

5550

4540

3510152025303540

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

3.93

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G

77

60

8899

110

121

132

(x 1

000

lb)

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

A/C

CO

DE

D

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0430101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E D


7-9-1Page 3

Jun 01/12


**ON A/C A318-100

5550

4540

3510152025303540

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2.93

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G

77

60

8899

110

121

132

(x 1

000

lb)

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

A/C

CO

DE

E

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0440101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E E


7-9-1Page 4

Jun 01/12


**ON A/C A318-100

6055

5040

3510152025303540

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2.7

% M

AC

.S

EE

SE

CT

ION

7−

4−1

LAN

DIN

G G

EA

R L

OA

DIN

G

77

65

8811

012

113

214

3

(x 1

000

lb)

4599

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

A/C

CO

DE

F

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0450101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E F


7-9-1Page 5

Jun 01/12


**ON A/C A318-100

6055

5040

3510152025303540

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

77

65

8811

012

113

214

3

(x 1

000

lb)

4599

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

A/C

CO

DE

G

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0460101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E G


7-9-1Page 6

Jun 01/12


**ON A/C A318-100

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

(x 1

000

lb)

6055

5040

3510152025303545

77

65

8811

012

1

459913

214

3

40

A/C

CO

DE

H

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

ALP

HA

FA

CT

OR

= 0

.9

N_AC_070901_1_0470101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E H


7-9-1Page 7

Jun 01/12


**ON A/C A318-100

6055

5040

3510152025303545

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

77

70

8811

012

113

215

4

(x 1

000

lb)

4599

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

A/C

CO

DE

I

ALP

HA

FA

CT

OR

= 0

.9

65143

40

N_AC_070901_1_0480101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E I


7-9-1Page 8

Jun 01/12


**ON A/C A318-100

6055

5040

35

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

77

70

8811

012

113

215

4

(x 1

000

lb)

4599

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

A/C

CO

DE

J

ALP

HA

FA

CT

OR

= 0

.9

65143

10152025303545 40

N_AC_070901_1_0490101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E J


7-9-1Page 9

Jun 01/12


**ON A/C A318-100

6055

5040

35

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

kg)


46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2 %

MA

C.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

77

70

8811

012

113

215

4

(x 1

000

lb)

4599

C −

CB

R

6 (L

OW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

SU

BG

RA

DE

ST

RE

NG

TH

D −

CB

R

3 (U

LTR

A L

OW

)

A/C

CO

DE

K

ALP

HA

FA

CT

OR

= 0

.9

65143

10152025303545 40

N_AC_070901_1_0500101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E K


7-9-1Page 10

Jun 01/12


7-9-2 Aircraft Classification Number - Rigid Pavement

**ON A/C A318-100

Aircraft Classification Number - Rigid Pavement

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


7-9-2Page 1

Jun 01/12


**ON A/C A318-100

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

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IC

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AE

RO

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OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

5 %

MA

C.

1035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

10.

2 ba

r (1

48 p

si)

(x 1

000

kg)

(x 1

000

lb)


152025303577

8899

110

121

132

4045

5055

60

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

C

N_AC_070902_1_0410101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E C

Aircraft Classification Number -- Rigid PavementFIGURE-7-9-2-991-041-A01

7-9-2Page 2

Jun 01/12


**ON A/C A318-100

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

3.93

% M

AC

.

1035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)

(x 1

000

kg)

(x 1

000

lb)


1520253035

7788

9911

012

113

2

4045

5055

60

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

D

40

N_AC_070902_1_0420101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E D


7-9-2Page 3

Jun 01/12


**ON A/C A318-100

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2.93

% M

AC

.

1035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)

(x 1

000

kg)

(x 1

000

lb)


1520253035

7788

9911

012

113

2

4045

5055

60

40

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

E

65143

N_AC_070902_1_0430101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E E


7-9-2Page 4

Jun 01/12


**ON A/C A318-100

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2.7

% M

AC

.

1035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)

(x 1

000

kg)

(x 1

000

lb)


1520253035

7788

9911

012

113

2

4045

5055

60

40

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

F

65143

N_AC_070902_1_0440101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E F


7-9-2Page 5

Jun 01/12


**ON A/C A318-100

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2 %

MA

C.

1035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

11.

4 ba

r (1

65 p

si)

(x 1

000

kg)

(x 1

000

lb)


1520253035

7788

9911

012

113

2

4045

5055

60

40S

UB

GR

AD

E S

TR

EN

GT

HD

− K

= 2

0 M

N/m

(U

LTR

A L

OW

)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

G

65143

45

N_AC_070902_1_0450101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E G


7-9-2Page 6

Jun 01/12


**ON A/C A318-100

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2 %

MA

C.

1035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)

(x 1

000

kg)

(x 1

000

lb)


1520253035

7788

9911

012

113

2

4045

5055

60

40S

UB

GR

AD

E S

TR

EN

GT

HD

− K

= 2

0 M

N/m

(U

LTR

A L

OW

)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

H

65143

45

N_AC_070902_1_0460101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E H


7-9-2Page 7

Jun 01/12


**ON A/C A318-100

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2 %

MA

C.

1035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)

(x 1

000

kg)

(x 1

000

lb)


1520253035

7788

9911

012

113

2

4045

5055

60

40

65143

45

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

I

154

70

N_AC_070902_1_0470101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E I


7-9-2Page 8

Jun 01/12


**ON A/C A318-100

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2 %

MA

C.

1035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)

(x 1

000

kg)

(x 1

000

lb)


1520253035

7788

9911

012

113

2

4045

5055

60

40

65143

45

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

J

154

70

N_AC_070902_1_0480101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E J


7-9-2Page 9

Jun 01/12


**ON A/C A318-100

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

IC

AO

AE

RO

DR

OM

E D

ES

IGN

MA

NU

AL

PA

RT

3C

HA

PT

ER

1 S

EC

ON

D E

DIT

ION

198

3.

SE

E S

EC

TIO

N 7

−4−

1 LA

ND

ING

GE

AR

LO

AD

ING

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

2 %

MA

C.

1035

AIR

CR

AF

T G

RO

SS

WE

IGH

T

46 x

17

R20

(46

x 1

6−20

) T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

12.

4 ba

r (1

80 p

si)

(x 1

000

kg)

(x 1

000

lb)


1520253035

7788

9911

012

113

2

4045

5055

60

40

65143

45

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m

(ULT

RA

LO

W)

A −

K =

150

MN

/m

(HIG

H)

B −

K =

80

MN

/m

(ME

DIU

M)

C −

K =

40

MN

/m

(LO

W)

A/C

CO

DE

K

154

70

N_AC_070902_1_0490101_01_00

ON

PA

VE

ME

NT

− A

/C C

OD

E K


7-9-2Page 10

Jun 01/12


SCALED DRAWINGS

8-0-0 SCALED DRAWINGS

**ON A/C A318-100

Scaled Drawings

1. This section provides the scaled drawings.

NOTE : When printing this drawing, make sure to adjust for proper scaling.

8-0-0Page 1

Jun 01/12


**ON A/C A318-100

0 10 20 30 40 50FEET

0 5 10 15METERS

010

2030

4050

FE

ET

05

1015

ME

TE

RS

N_AC_080000_1_0010101_01_00

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

Scaled DrawingFIGURE-8-0-0-991-001-A01

8-0-0Page 2

Jun 01/12


AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 AIRCRAFT RESCUE AND FIRE FIGHTING

**ON A/C A318-100

Aircraft Rescue and Fire Fighting

1. Aircraft Rescue and Fire Fighting ChartsThis sections gives data related to aircraft rescue and fire fighting.The figures contained in this section are the figures that are in the Aircraft Rescue and Fire FightingCharts poster available for download on AIRBUSWorld and the Airbus website.

10-0-0Page 1

Jun 01/12


**ON A/C A318-100

N_AC_100000_1_0010101_01_00

Front PageFIGURE-10-0-0-991-001-A01

10-0-0Page 2

Jun 01/12


**ON A/C A318-100

N_AC_100000_1_0020101_01_00

Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-0-0-991-002-A01

10-0-0Page 3

Jun 01/12


**ON A/C A318-100

N_AC_100000_1_0030101_01_00

Wheel Safety Area(Sheet 1 of 2)

FIGURE-10-0-0-991-003-A01

10-0-0Page 4

Jun 01/12


**ON A/C A318-100

N_AC_100000_1_0030102_01_00

Wheel Safety AreaRecommendations (Sheet 2 of 2)

FIGURE-10-0-0-991-003-A01

10-0-0Page 5

Jun 01/12


**ON A/C A318-100

N_AC_100000_1_0040101_01_00

Composite MaterialsFIGURE-10-0-0-991-004-A01

10-0-0Page 6

Jun 01/12


**ON A/C A318-100

A AB

B

N_AC_100000_1_0050101_01_00

LG Ground Lock Safety DevicesFIGURE-10-0-0-991-005-A01

10-0-0Page 7

Jun 01/12


**ON A/C A318-100

C L

N_AC_100000_1_0060101_01_00

Evacuation/Escape Slide/RaftFIGURE-10-0-0-991-006-A01

10-0-0Page 8

Jun 01/12


**ON A/C A318-100

N_AC_100000_1_0070101_01_00

Pax/Crew DoorsFIGURE-10-0-0-991-007-A01

10-0-0Page 9

Jun 01/12


**ON A/C A318-100

N_AC_100000_1_0080101_01_00

Emergency Exit HatchFIGURE-10-0-0-991-008-A01

10-0-0Page 10

Jun 01/12


**ON A/C A318-100

134A

R15

4AR

/

198C

B

N_AC_100000_1_0090101_01_00

FWD and AFT Lower Deck Cargo DoorsFIGURE-10-0-0-991-009-A01

10-0-0Page 11

Jun 01/12


**ON A/C A318-100

FL

T IN

T

LIG

HT

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AP

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AN

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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

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**ON A/C A318-100

316A

R

A

315A

L

A

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APU Access DoorFIGURE-10-0-0-991-013-A01

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**ON A/C A318-100

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Aircraft Ground ClearancesFIGURE-10-0-0-991-014-A01

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**ON A/C A318-100

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

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aircraft characteristics airport and maintenance planning … · @a318 aircraft characteristics -...

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