aircraft characteristics airport and maintenance …

@AIRBUSA330

AIRCRAFT CHARACTERISTICSAIRPORT AND MAINTENANCE PLANNING

AC

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

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

AIRBUS S.A.S.Customer Services

Technical Data Support and Services31707 Blagnac Cedex

FRANCE

Issue: Jan 01/93 Rev: Apr 01/13

@A330AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

HIGHLIGHTS

Revision No. 21 - Apr 01/13

LOCATIONS CHGCODE

DESCRIPTIONS OF CHANGE

CHAPTER 1

Section 1-1

Subject 1-1-0

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

Section 1-2 R

Subject 1-2-1 N

Glossary N

Subject 01-02-00 D

CHAPTER 2 R

Section 2-1 R

Subject 02-01-00 D

Subject 2-1-1 R

General Aircraft Characteristics Data R DESCRIPTION TITLE UPDATEDNOTE AMENDED

General Aircraft Characteristics Data R DESCRIPTION TITLE UPDATED

Section 2-2 R

Subject 2-2-0 R

General Aircraft Dimensions R DESCRIPTION TITLE UPDATED

FIGURE General Aircraft Dimensions R ILLUSTRATION REVISED

FIGURE General Aircraft Dimensions -(Pre Mod 48979)

R ILLUSTRATION REVISED

General Aircraft Dimensions R DESCRIPTION TITLE UPDATED

FIGURE General Aircraft Dimensions R ILLUSTRATION REVISED

Section 2-3

Subject 2-3-0

HIGHLIGHTSPage 1

Apr 01/13


LOCATIONS CHGCODE


Ground Clearances R ADDED GROUND CLEARANCES FORFLIGHT CONTROLSUPDATED FIGURES LAYOUT.PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Ground Clearances R

FIGURE Ground Clearances N ILLUSTRATION ADDED


FIGURE Ground Clearances - Ailerons Up N ILLUSTRATION ADDED

FIGURE Ground Clearances - AileronsDown

N ILLUSTRATION ADDED

FIGURE Ground Clearances - SpoilersExtended


FIGURE Ground Clearances - Slats FullyExtended


FIGURE Ground Clearances - Flaps FullyExtended


FIGURE Ground Clearances - Flaps-Tracks Fully Extended


Section 2-4 R

Subject 02-04-00 D

Subject 2-4-1 R

Interior Arrangements - Plan View R DESCRIPTION TITLE UPDATED

FIGURE Interior Arrangements - PlanView - Typical Configuration


FIGURE Interior Arrangements - PlanView - Typical Configuration


Section 2-5 R

Subject 2-5-0 R

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

FIGURE Interior Arrangements - CrossSection - Typical Configuration


HIGHLIGHTSPage 2

Apr 01/13


LOCATIONS CHGCODE


Section 2-6 R

Subject 02-06-00 D

Subject 2-6-1 R

Lower Deck Cargo Compartments R

FIGURE Lower Deck CargoCompartments - Location and Dimensions

R

FIGURE Lower Deck CargoCompartments - Loading Combinations


FIGURE Lower Deck CargoCompartments - Loading Combinations


Subject 2-6-2 R

Main Deck Cargo Compartment R DESCRIPTION TITLE UPDATED

FIGURE Main Deck Cargo Compartment -Location and Dimensions


FIGURE Main Deck Cargo Compartment -Loading Combinations








Section 2-7

Subject 2-7-0

Door Clearances R DESCRIPTION TITLE UPDATED

FIGURE Door Identification and location -Door Identification


FIGURE Door Identification and Location- Door Identification


FIGURE Door Identification and Location- Door Identification


Section 2-8 N

Subject 2-8-0 N

Escape Slides N

HIGHLIGHTSPage 3

Apr 01/13


LOCATIONS CHGCODE


FIGURE Escape Slides - Location N ILLUSTRATION ADDED



Section 2-9 N

Subject 2-9-0 N

Landing Gear Maintenance Pits N

FIGURE Landing Gear Maintenance Pits -Maintenance Pit Envelopes


FIGURE Landing Gear Maintenance Pits -Maintenance Pit Envelopes


Landing Gear N

FIGURE Main Landing Gear - General N ILLUSTRATION ADDED

FIGURE Nose Landing Gear - General N ILLUSTRATION ADDED

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

Engine and Nacelle N

FIGURE Engine and Nacelle - EngineDimensions - PW 4000


FIGURE Engine and Nacelle - NacelleDimensions - PW 4000


HIGHLIGHTSPage 4

Apr 01/13


LOCATIONS CHGCODE


FIGURE Engine and Nacelle - Fan Cowls -PW 4000


FIGURE Engine and Nacelle - ThrustReverser Cowls - PW 4000


FIGURE Engine and Nacelle - EngineDimensions - TRENT 700


FIGURE Engine and Nacelle - NacelleDimensions - TRENT 700


FIGURE Engine and Nacelle - Fan Cowls -TRENT 700


FIGURE Engine and Nacelle - ThrustReverser Cowls - TRENT 700


FIGURE Engine and Nacelle - EngineDimensions - GE CF6-80E1


FIGURE Engine and Nacelle - NacelleDimensions - GE CF6-80E1


FIGURE Engine and Nacelle - Fan Cowls -GE CF6-80E1


FIGURE Engine and Nacelle - ThrustReverser Cowls - GE CF6-80E1


Subject 2-12-1 N

Auxiliary Power Unit N

FIGURE Auxiliary Power Unit - AccessDoors


Section 2-13 N

Subject 2-13-0 N

Leveling, Symmetry and Alignment N

FIGURE Location of Leveling Points N ILLUSTRATION ADDED



Section 2-14 N

Subject 2-14-0 N

Jacking for Maintenance N

FIGURE Jacking for Maintenance -Jacking Points Location


HIGHLIGHTSPage 5

Apr 01/13


LOCATIONS CHGCODE






FIGURE Jacking for Maintenance -Forward Jacking Point


FIGURE Jacking for Maintenance -Forward Jacking Point


FIGURE Jacking for Maintenance - WingJacking Points


FIGURE Jacking for Maintenance - WingJacking Points


FIGURE Jacking for Maintenance -Auxiliary Jacking Point - Safety Stay






FIGURE Jacking for Maintenance -Specific Jack-Nose Dimensions


FIGURE Jacking for Maintenance -Jacking Dimensions






FIGURE Jacking for Maintenance - Loadat the Aircraft Jacking Points


FIGURE Jacking for Maintenance - Loadat the Aircraft Jacking Points


Subject 2-14-1 N

Jacking for Wheel Change N

FIGURE Jacking for Wheel Change - MLGJacking Point Heights


HIGHLIGHTSPage 6

Apr 01/13


LOCATIONS CHGCODE


FIGURE Jacking for Wheel Change -Jacking of the NLG


FIGURE Jacking for Wheel Change - MLGJacking Point Loads


FIGURE Jacking for Wheel Change - MLGJacking Point Loads


FIGURE Jacking for Wheel Change - NLGJacking Point Loads


FIGURE Jacking for Wheel Change - NLGJacking Point Loads


Subject 2-14-2 N

Support of Aircraft N

FIGURE Support of Aircraft - Location ofShoring Cradles






CHAPTER 3 R

Section 3-5 R

Subject 3-5-0

Final Approach Speed R PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

Subject 03-05-01 D

CHAPTER 4

Section 4-2

Subject 4-2-0

FIGURE Turning Radii - (Sheet 1) R



Section 4-3

HIGHLIGHTSPage 7

Apr 01/13


LOCATIONS CHGCODE


Subject 4-3-0

FIGURE Minimum Turning Radii R

FIGURE Minimum Turning Radii R ILLUSTRATION REVISED

Section 4-4

Subject 4-4-0

Visibility from Cockpit in Static Position. R

FIGURE Visibility from Cockpit in StaticPosition

R

FIGURE Visibility from Cockpit in StaticPosition

R

FIGURE Binocular Visibility ThroughWindows from Captain Eye Position


Section 4-5

Subject 4-5-3

FIGURE 180˚ Turn on a Runway R ILLUSTRATION REVISED

FIGURE 180˚ Turn on a Runway R ILLUSTRATION REVISED

Section 4-7 R

Subject 4-7-0 R

CHAPTER 5 R

Section 5-1 R

Subject 5-1-0 R

Subject 5-1-1

Symbols Used on Servicing Diagrams R ADDED ”BULK TRAIN”.

Subject 5-1-2 R

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

FIGURE Typical Ramp Layout - OpenApron




HIGHLIGHTSPage 8

Apr 01/13


LOCATIONS CHGCODE


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



Subject 5-1-3 R

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

FIGURE Typical Ramp Layout - Gate R ILLUSTRATION REVISED

FIGURE Typical Ramp Layout - Gate R ILLUSTRATION REVISED

Section 5-2 R

Subject 5-2-0 R

Terminal Operations -- Full ServicingTurn-Round Time

R DESCRIPTION TITLE UPDATED

FIGURE Full Servicing Turn-Round TimeChart


Terminal Operations -- Full ServicingTurn-Round Time

N



Terminal Operations - Full ServicingTurn-Round Time

N



Subject 05-02-01 D

Section 5-3 R

Subject 5-3-0 R

Terminal Operations - Minimum ServicingTurn-Round Time

R DESCRIPTION TITLE UPDATED

FIGURE Minimum Servicing Turn-RoundTime


Terminal Operations - Minimum ServicingTurn-Round Time

N

HIGHLIGHTSPage 9

Apr 01/13


LOCATIONS CHGCODE


FIGURE Minimum Servicing Turn-RoundTime


Subject 05-03-01 D

Section 5-4 R

Subject 05-04-00 D

Subject 5-4-1

Ground Service Connections Layout R

FIGURE Ground Service ConnectionsLayout


Ground Service Connections Layout R

FIGURE Ground Service ConnectionsLayout


Subject 5-4-3

Hydraulic System R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Service Connections -Green System Ground Service Panel


FIGURE Ground Service Connections -Blue System Ground Service Panel


FIGURE Ground Service Connections -Yellow System Ground Service Panel


Subject 5-4-4

Electrical System R NOTE AMENDED

FIGURE Ground Service Connections -Electrical Service Panel


FIGURE Ground Service Connections -Electrical Service Panel


Subject 5-4-5

Oxygen System R PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Ground Service Connections -Oxygen System


HIGHLIGHTSPage 10

Apr 01/13


LOCATIONS CHGCODE


FIGURE Ground Service Connections -Oxygen System


Subject 5-4-6

Fuel System R

Subject 5-4-7

Pneumatic System R

FIGURE Ground Service Connections - LPand HP Ground Connectors


Subject 5-4-8

Potable Water System R PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Ground Service Connections -Potable-Water Ground Service Panels


Potable Water System N

FIGURE Ground Service Connections -Potable-Water Ground Service Panels


Potable Water System N

FIGURE Ground Service Connections -Potable-Water Ground Service Panel


Subject 5-4-9

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

FIGURE Ground Service Connections -APU Oil Servicing

R

Subject 5-4-10

Vacuum Toilet System R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Service Connections -Waste Water Ground Service Panel


FIGURE Ground Service Connections -Waste Water Ground Service Panel


Section 5-5 R

Subject 5-5-0

HIGHLIGHTSPage 11

Apr 01/13


LOCATIONS CHGCODE


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

FIGURE Example for Use of the Charts R ILLUSTRATION REVISED

FIGURE Engine Starting PneumaticRequirements - GE CF6-80E1 SeriesEngine


FIGURE Engine Starting PneumaticRequirements - Rolls Royce Trent 700Series Engine


FIGURE Engine Starting PneumaticRequirements - Pratt & Whitney PW4000Series Engine


Subject 05-05-01 D

Subject 05-05-02 D

Subject 05-05-03 D

Section 5-6 R

Subject 5-6-0

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

FIGURE Ground Pneumatic PowerRequirements - Heating


FIGURE Ground Pneumatic PowerRequirements - Cooling


Subject 05-06-01 D

Subject 05-06-02 D

Section 5-7

Subject 5-7-0

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

HIGHLIGHTSPage 12

Apr 01/13


LOCATIONS CHGCODE


FIGURE Preconditioned AirflowRequirements

R

Section 5-8

Subject 5-8-0

Ground Towing Requirements R

Section 5-9 N

Subject 5-9-0 N

De-Icing and External Cleaning N

CHAPTER 7

Section 7-1

Subject 7-1-0

General Information R TEXT UPDATED

Section 7-2

Subject 7-2-0

Landing Gear Footprint R ILLUSTRATIONS UPDATED

FIGURE Landing Gear Footprint R ILLUSTRATION REVISED

FIGURE Landing Gear Footprint R

FIGURE Landing Gear Footprint R ILLUSTRATION REVISED

Section 7-3

Subject 7-3-0

Maximum Pavement Loads R ILLUSTRATIONS UPDATED

FIGURE Maximum Pavement Loads R ILLUSTRATION REVISED

FIGURE Maximum Pavement Loads R

FIGURE Maximum Pavement Loads R ILLUSTRATION REVISED

Section 7-4 R

Subject 7-4-0

Landing Gear Loading on Pavement R ILLUSTRATIONS AND EXAMPLEUPDATED.

FIGURE Landing Gear Loading onPavement - WV026, MRW 192 900 kg




HIGHLIGHTSPage 13

Apr 01/13


LOCATIONS CHGCODE




Subject 07-04-01 D

Section 7-5 R

Subject 7-5-0

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

R ILLUSTRATIONS AND EXAMPLEUPDATED.DESCRIPTION TITLE UPDATED

FIGURE Flexible Pavement Requirements- WV026, MRW 192 900 kg, CG 38.8 %






Subject 07-05-01 D

Section 7-6 R

Subject 7-6-0

Flexible Pavement Requirements - LCNConversion

R TEXT, ILLUSTRATIONS AND EXAMPLEUPDATED.

FIGURE Flexible Pavement Requirements- LCN table


FIGURE Flexible Pavement Requirements- LCN - WV026, MRW 192 900 kg, CG38.8 %










Subject 07-06-01 D

HIGHLIGHTSPage 14

Apr 01/13


LOCATIONS CHGCODE


Section 7-7 R

Subject 7-7-0

Rigid Pavement Requirements - PortlandCement Association Design Method

R TEXT, ILLUSTRATIONS AND EXAMPLEUPDATED.NOTE AMENDED

FIGURE Rigid Pavement Requirements -WV026, MRW 192 900 kg, CG 38.8 %






Subject 07-07-01 D

Section 7-8 R

Subject 7-8-0

Rigid Pavement Requirements - LCNConversion

R TEXT, ILLUSTRATIONS AND EXAMPLEUPDATED.

FIGURE Rigid Pavement Requirements -LCN table






FIGURE Radius of Relative Stiffness (L) N ILLUSTRATION ADDED

FIGURE Rigid Pavement Requirements -LCN - WV026, MRW 192 900 kg, CG38.8 %






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


Subject 07-08-01 D

HIGHLIGHTSPage 15

Apr 01/13


LOCATIONS CHGCODE


Subject 07-08-02 D

Subject 07-08-03 D

Subject 07-08-04 D

Section 7-9 R

Subject 7-9-0

Aircraft Classification Number - Flexibleand Rigid Pavement

R TEXT, ILLUSTRATIONS AND EXAMPLEUPDATED.DESCRIPTION TITLE UPDATEDNOTE AMENDED

FIGURE Aircraft Classification Number -ACN Table


FIGURE Aircraft Classification Number -Flexible Pavement - WV026, MRW 192900 kg, CG 38.8 %
















Subject 07-09-01 D

Subject 07-09-02 D

HIGHLIGHTSPage 16

Apr 01/13


LOCATIONS CHGCODE


CHAPTER 8 R

Section 8-0 N

Subject 8-0-0 N

Scaled Drawings N

FIGURE Scaled Drawing N ILLUSTRATION ADDED



Section 08-01 D

CHAPTER 10 N

Section 10-0 N

Subject 10-0-0 N

Aircraft Rescue and Fire Fighting N

FIGURE Front Page N ILLUSTRATION ADDED

FIGURE Highly Flammable and HazardousMaterials and Components


FIGURE Crew Rest CompartmentsLocation


FIGURE Wheel/Brake Overheat - WheelSafety Area


FIGURE Composite Materials Location N ILLUSTRATION ADDED

FIGURE Ground Lock Safety Devices N ILLUSTRATION ADDED

FIGURE Emergency Evacuation Devices N ILLUSTRATION ADDED

FIGURE Pax/Crew Doors and EmergencyExits


FIGURE FWD and AFT Lower DeckCargo Doors


FIGURE Control Panels N ILLUSTRATION ADDED

FIGURE APU Compartment Access N ILLUSTRATION ADDED


FIGURE Structural Break-in Points N ILLUSTRATION ADDED

Aircraft Rescue and Fire Fighting N

FIGURE Front Page N ILLUSTRATION ADDED

HIGHLIGHTSPage 17

Apr 01/13


LOCATIONS CHGCODE


FIGURE Highly Flammable and HazardousMaterials and Components


FIGURE Wheel/Brake Overheat - WheelSafety Area


FIGURE Composite Materials Location N ILLUSTRATION ADDED

FIGURE Ground Lock Safety Devices N ILLUSTRATION ADDED

FIGURE Emergency Evacuation Devices N ILLUSTRATION ADDED

FIGURE Crew Doors and Emergency Exits N ILLUSTRATION ADDED

FIGURE Cargo Doors - FWD and AFTLower Deck Compartments


FIGURE Control Panels N ILLUSTRATION ADDED

FIGURE APU Compartment Access N ILLUSTRATION ADDED


FIGURE Structural Break-in Points N ILLUSTRATION ADDED

HIGHLIGHTSPage 18

Apr 01/13


LIST OF EFFECTIVE CONTENT

Revision No. 21 - Apr 01/13

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 1

Subject 1-1-0

Purpose R Apr 01/13

Subject 1-2-1

Glossary N Apr 01/13

CHAPTER 2

Subject 2-1-1

General Aircraft Characteristics Data R Apr 01/13

General Aircraft Characteristics Data R Apr 01/13

Subject 2-2-0

General Aircraft Dimensions R Apr 01/13

FIGURE General Aircraft Dimensions R Apr 01/13

FIGURE General Aircraft Dimensions - (Pre Mod 48979) R Apr 01/13

General Aircraft Dimensions R Apr 01/13

FIGURE General Aircraft Dimensions R Apr 01/13

Subject 2-3-0

Ground Clearances R Apr 01/13

FIGURE Ground Clearances R Apr 01/13

FIGURE Ground Clearances N Apr 01/13


FIGURE Ground Clearances - Ailerons Up N Apr 01/13

FIGURE Ground Clearances - Ailerons Down N Apr 01/13

FIGURE Ground Clearances - Spoilers Extended N Apr 01/13

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

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

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

L.E.C.Page 1

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Subject 2-4-1

Interior Arrangements - Plan View R Apr 01/13

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

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

Subject 2-5-0

Interior Arrangements - Cross Section R Apr 01/13

FIGURE Interior Arrangements - Cross Section - TypicalConfiguration

R Apr 01/13

Subject 2-6-1

Lower Deck Cargo Compartments R Apr 01/13

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

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

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

Subject 2-6-2

Main Deck Cargo Compartment R Apr 01/13

FIGURE Main Deck Cargo Compartment - Location and Dimensions N Apr 01/13

FIGURE Main Deck Cargo Compartment - Loading Combinations R Apr 01/13




Subject 2-6-3

Main and Lower Deck Cross-sections Feb 01/09

FIGURE Main and Lower Deck Cross-sections Jan 01/12

Subject 2-7-0

Door Clearances R Apr 01/13

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

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

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

Subject 2-7-1

L.E.C.Page 2

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Forward Passenger / Crew Door Feb 01/09

FIGURE Forward Passenger / Crew Doors May 01/07

FIGURE Forward Passenger / Crew Doors Feb 01/09

Subject 2-7-2

Mid Passenger / Crew Door May 01/07

FIGURE Mid Passenger / Crew Door May 01/07

Subject 2-7-3

Emergency Exits May 01/07

FIGURE Emergency Exits May 01/07

Subject 2-7-4

Aft Passenger / Crew Doors May 01/07

FIGURE Aft Passenger / Crew Doors May 01/07

Subject 2-7-5

Forward Cargo Compartment Doors May 01/07

FIGURE Forward Cargo Compartment Doors May 01/07

Forward Cargo Compartment Doors Feb 01/09

FIGURE Forward Cargo Compartment Doors Feb 01/09

FIGURE Forward Cargo Compartment Doors Feb 01/09

Subject 2-7-6

Aft Cargo Compartment Doors Feb 01/09

FIGURE Aft Cargo Compartment Doors Feb 01/09



Subject 2-7-7

Bulk Cargo Compartment Doors May 01/07

FIGURE Bulk Cargo Compartment Doors May 01/07

Bulk Cargo Compartment Doors Feb 01/09

FIGURE Bulk Cargo Compartment Doors Feb 01/09

Subject 2-7-8

L.E.C.Page 3

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Main Landing Gear Doors May 01/07

FIGURE Main Landing Gear Doors May 01/07

Main Landing Gear Doors Feb 01/09

FIGURE Main Landing Gear Doors Feb 01/09

Subject 2-7-9

Radome Feb 01/09

FIGURE Radome Feb 01/09

Subject 2-7-10

APU and Nose Landing Gear Doors May 01/07

FIGURE APU and Nose Landing Gear Doors May 01/07

APU and Nose Landing Gear Doors Feb 01/09

FIGURE APU and Nose Landing Gear Doors Feb 01/09

Subject 2-8-0

Escape Slides N Apr 01/13

FIGURE Escape Slides - Location N Apr 01/13



Subject 2-9-0

Landing Gear Maintenance Pits N Apr 01/13

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

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

Landing Gear N Apr 01/13

FIGURE Main Landing Gear - General N Apr 01/13

FIGURE Nose Landing Gear - General N Apr 01/13

Subject 2-10-0

Exterior Lighting N Apr 01/13

FIGURE Exterior Lighting N Apr 01/13



L.E.C.Page 4

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Subject 2-11-0

Antennas and Probes Location N Apr 01/13

FIGURE Antennas and Probes - Location N Apr 01/13



Subject 2-12-0

Engine and Nacelle N Apr 01/13

FIGURE Engine and Nacelle - Engine Dimensions - PW 4000 N Apr 01/13

FIGURE Engine and Nacelle - Nacelle Dimensions - PW 4000 N Apr 01/13

FIGURE Engine and Nacelle - Fan Cowls - PW 4000 N Apr 01/13

FIGURE Engine and Nacelle - Thrust Reverser Cowls - PW 4000 N Apr 01/13

FIGURE Engine and Nacelle - Engine Dimensions - TRENT 700 N Apr 01/13

FIGURE Engine and Nacelle - Nacelle Dimensions - TRENT 700 N Apr 01/13

FIGURE Engine and Nacelle - Fan Cowls - TRENT 700 N Apr 01/13

FIGURE Engine and Nacelle - Thrust Reverser Cowls - TRENT 700 N Apr 01/13

FIGURE Engine and Nacelle - Engine Dimensions - GE CF6-80E1 N Apr 01/13

FIGURE Engine and Nacelle - Nacelle Dimensions - GE CF6-80E1 N Apr 01/13

FIGURE Engine and Nacelle - Fan Cowls - GE CF6-80E1 N Apr 01/13

FIGURE Engine and Nacelle - Thrust Reverser Cowls - GE CF6-80E1 N Apr 01/13

Subject 2-12-1

Auxiliary Power Unit N Apr 01/13

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

Subject 2-13-0

Leveling, Symmetry and Alignment N Apr 01/13

FIGURE Location of Leveling Points N Apr 01/13



Subject 2-14-0

Jacking for Maintenance N Apr 01/13

L.E.C.Page 5

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

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



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

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

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

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

FIGURE Jacking for Maintenance - Auxiliary Jacking Point - SafetyStay

N Apr 01/13


N Apr 01/13


N Apr 01/13

FIGURE Jacking for Maintenance - Specific Jack-Nose Dimensions N Apr 01/13

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



FIGURE Jacking for Maintenance - Load at the Aircraft JackingPoints

N Apr 01/13

FIGURE Jacking for Maintenance - Load at the Aircraft JackingPoints

N Apr 01/13

Subject 2-14-1

Jacking for Wheel Change N Apr 01/13

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

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

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

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

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

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

Subject 2-14-2

L.E.C.Page 6

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Support of Aircraft N Apr 01/13

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



CHAPTER 3

Subject 3-1-0

General Information Jan 01/10

Subject 3-2-0

Payload / Range Feb 01/09

Subject 3-2-1

ISA Conditions May 01/07

FIGURE PAYLOAD / RANGE - PW 4000 Series Engine Feb 01/09

FIGURE PAYLOAD / RANGE - RR TRENT 700 Series Engine Feb 01/09

FIGURE PAYLOAD / RANGE - GE CF6-80E1 Series Engine Feb 01/09



FIGURE PAYLOAD / RANGE - GE CF6-80E1 Series Engine Feb 01/09

ISA Conditions Feb 01/09





Subject 3-3-0

FAR / JAR Takeoff Weight Limitation Feb 01/09

Subject 3-3-1

FAR / JAR Takeoff Weight Limitation Feb 01/09

FIGURE Takeoff Weight Limitation - ISA Conditions - PW 4000Series Engine

Feb 01/09

L.E.C.Page 7

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Takeoff Weight Limitation - ISA Conditions - RR TRENT700 Series Engine

Feb 01/09

FIGURE Takeoff Weight Limitation - ISA Conditions - GE CF6-80E1Series Engine

Feb 01/09

Subject 3-3-2

ISA +15 ˚C (ISA +27 ˚F) Conditions Jan 01/10

FIGURE FAR / JAR Takeoff Weight Limitation - ISA +15˚C (ISA+27˚F) Conditions - PW 4000 Series Engine

Jan 01/10

FIGURE FAR / JAR Takeoff Weight Limitation - ISA +15˚C (ISA+27˚F) Conditions - RR TRENT 700 Series Engine

Jan 01/10

FIGURE FAR / JAR Takeoff Weight Limitation - ISA +15˚C (ISA+27˚F) Conditions - GE CF6-80E1 Series Engine

Jan 01/10

Subject 3-4-0

Landing Field Length Feb 01/09

Subject 3-4-1

ISA Conditions All series engine Jan 01/10

FIGURE FAR / JAR Landing Field Length - ISA Conditions - PW4000 Series Engine

Jan 01/10

FIGURE FAR / JAR Landing Field Length - ISA Conditions - RRTRENT 700 Series Engine

Jan 01/10

FIGURE FAR / JAR Landing Field Length - ISA Conditions - GECF6-80E1 Series Engine

Jan 01/10

Subject 3-5-0

Final Approach Speed R Apr 01/13

CHAPTER 4

Subject 4-1-0

General Information Feb 01/09

Subject 4-2-0

Turning Radii Feb 01/09

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


L.E.C.Page 8

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE


Subject 4-3-0

Minimum Turning Radii Jan 01/11

FIGURE Minimum Turning Radii R Apr 01/13

FIGURE Minimum Turning Radii R Apr 01/13

Subject 4-4-0

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

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

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

FIGURE Binocular Visibility Through Windows from Captain EyePosition

N Apr 01/13

Subject 4-5-0

Runway and Taxiway Turn Paths Jan 01/10

Subject 4-5-1

135˚ Turn - Runway to Taxiway Jan 01/11

FIGURE 135˚ Turn - Runway to Taxiway - Judgemental OversteerMethod

Jan 01/11

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

Jan 01/11


Jan 01/11


Jan 01/11

Subject 4-5-2

90˚ Turn - Runway to Taxiway Jan 01/11


Jan 01/11


Jan 01/11


Jan 01/11


Jan 01/11

L.E.C.Page 9

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Subject 4-5-3

180˚ Turn on a Runway Jan 01/11

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

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

Subject 4-5-4

135˚ Turn - Taxiway to Taxiway Jan 01/11

FIGURE 135˚ Turn - Taxiway to Taxiway - Judgemental OversteerMethod

Jan 01/11

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

Jan 01/11


Jan 01/11


Jan 01/11

Subject 4-5-5

90˚ Turn - Taxiway to Taxiway Jan 01/11


Jan 01/11


Jan 01/11


Jan 01/11


Jan 01/11

Subject 4-6-0

Runway Holding Bay (Apron) Jan 01/11

FIGURE Runway Holding Bay (Apron) Jan 01/11

Subject 4-7-0

Airplane Parking Feb 01/09

FIGURE Airplane Parking - Steering Geometry May 01/07

FIGURE Airplane Parking - Steering Geometry May 01/07

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

L.E.C.Page 10

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Airplane Parking - Steering Geometry Feb 01/09

FIGURE Airplane Parking - Steering Geometry Feb 01/09

FIGURE Airplane Parking - Minimum Parking Space Requirements Feb 01/09

CHAPTER 5

Subject 5-0-0

TERMINAL SERVICING Jan 01/10

Subject 5-1-0

Airplane Servicing Arrangements Jan 01/10

Airplane Servicing Arrangements Jan 01/10

Subject 5-1-1

Symbols Used on Servicing Diagrams R Apr 01/13

Subject 5-1-2

Typical Ramp Layout - Open Apron R Apr 01/13

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


Typical Ramp Layout - Open Apron R Apr 01/13


Subject 5-1-3

Typical Ramp Layout - Gate R Apr 01/13

FIGURE Typical Ramp Layout - Gate R Apr 01/13

FIGURE Typical Ramp Layout - Gate R Apr 01/13

Subject 5-2-0

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

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

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


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


Subject 5-3-0

L.E.C.Page 11

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

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

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

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

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

Subject 5-4-1

Ground Service Connections Layout R Apr 01/13

FIGURE Ground Service Connections Layout R Apr 01/13

Ground Service Connections Layout R Apr 01/13

FIGURE Ground Service Connections Layout R Apr 01/13

Subject 5-4-2

Grounding Points Feb 01/09

FIGURE Ground Service Connections - Grounding Points Feb 01/09

FIGURE Ground Service Connections - Grounding Points Feb 01/09

Subject 5-4-3

Hydraulic System R Apr 01/13

FIGURE Ground Service Connections - Green System Ground ServicePanel

N Apr 01/13

FIGURE Ground Service Connections - Blue System Ground ServicePanel

N Apr 01/13

FIGURE Ground Service Connections - Yellow System Ground ServicePanel

N Apr 01/13

Subject 5-4-4

Electrical System R Apr 01/13

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

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

Subject 5-4-5

Oxygen System R Apr 01/13

FIGURE Ground Service Connections - Oxygen System N Apr 01/13

FIGURE Ground Service Connections - Oxygen System N Apr 01/13

Subject 5-4-6

L.E.C.Page 12

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Fuel System R Apr 01/13

FIGURE Overpressure Protector and NACA Flame Arrestor Jan 01/12

Subject 5-4-7

Pneumatic System R Apr 01/13

FIGURE Ground Service Connections - LP and HP GroundConnectors

N Apr 01/13

Subject 5-4-8

Potable Water System R Apr 01/13

FIGURE Ground Service Connections - Potable-Water Ground ServicePanels

N Apr 01/13

Potable Water System N Apr 01/13

FIGURE Ground Service Connections - Potable-Water Ground ServicePanels

N Apr 01/13

Potable Water System N Apr 01/13

FIGURE Ground Service Connections - Potable-Water Ground ServicePanel

N Apr 01/13

Subject 5-4-9

Oil System Feb 01/09

FIGURE Ground Service Connections - Engine Oil Tank - PW 4000series engine

Feb 01/09

FIGURE Ground Service Connections - Engine Oil Tank - RR Trent700 series engine

Feb 01/09

FIGURE Ground Service Connections - Engine Oil Tank - GECF6-80E1 series engine

May 01/07

FIGURE Ground Service Connections - IDG Oil Tank - PW 4000series engine

Feb 01/09

FIGURE Ground Service Connections - IDG Oil Tank - RR Trent 700series engine

Feb 01/09

FIGURE Ground Service Connections - IDG Oil Tank - GE CF6-80E1series engine

May 01/07

APU Oil System R Apr 01/13

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

L.E.C.Page 13

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Subject 5-4-10

Vacuum Toilet System R Apr 01/13

FIGURE Ground Service Connections - Waste Water Ground ServicePanel

N Apr 01/13

FIGURE Ground Service Connections - Waste Water Ground ServicePanel

N Apr 01/13

Subject 5-5-0

Engine Starting Pneumatic Requirements R Apr 01/13

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

FIGURE Engine Starting Pneumatic Requirements - GE CF6-80E1Series Engine

N Apr 01/13

FIGURE Engine Starting Pneumatic Requirements - Rolls Royce Trent700 Series Engine

N Apr 01/13

FIGURE Engine Starting Pneumatic Requirements - Pratt & WhitneyPW4000 Series Engine

N Apr 01/13

Subject 5-6-0

Ground Pneumatic Power Requirements R Apr 01/13

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

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

Subject 5-7-0

Preconditioned Airflow Requirements R Apr 01/13

FIGURE Preconditioned Airflow Requirements R Apr 01/13

Subject 5-8-0

Ground Towing Requirements R Apr 01/13

FIGURE Ground Towing Requirements Jan 01/11

Subject 5-9-0

De-Icing and External Cleaning N Apr 01/13

CHAPTER 6

Subject 6-1-0

Engine Exhaust Velocities and Temperatures Jan 01/10

Subject 6-1-1

L.E.C.Page 14

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Engine Exhaust Velocities Contours - Ground Idle Power Feb 01/09

FIGURE Engine Exhaust Velocities - Ground Idle Power - PW 4000series engine

Feb 01/09

FIGURE Engine Exhaust Velocities - Ground Idle Power - RR Trent700 series engine

Feb 01/09

FIGURE Engine Exhaust Velocities - Ground Idle Power - GECF6-80E1 series engine

Jan 01/10

Subject 6-1-2

Engine Exhaust Temperatures Contours - Ground Idle Power Jan 01/10

FIGURE Engine Exhaust Temperatures - Ground Idle Power - PW4000 series engine

Feb 01/09

FIGURE Engine Exhaust Temperatures - Ground Idle Power - RRTrent 700 series engine

Feb 01/09

FIGURE Engine Exhaust Temperatures - Ground Idle Power - GECF6-80E1 series engine

Jan 01/10

Subject 6-1-3

Engine Exhaust Velocities Contours - Breakaway Power Feb 01/09

FIGURE Engine Exhaust Velocities - Breakaway Power - PW 4000series engine

Feb 01/09

FIGURE Engine Exhaust Velocities - Breakaway Power - RR Trent700 series engine

Feb 01/09

FIGURE Engine Exhaust Velocities - Breakaway Power - GECF6-80E1 series engine

Jan 01/10

Subject 6-1-4

Engine Exhaust Temperatures Contours - Breakaway Power Jan 01/10

FIGURE Engine Exhaust Temperatures - Breakaway Power - PW4000 series engine

Feb 01/09

FIGURE Engine Exhaust Temperatures - Breakaway Power - RRTrent 700 series engine

Feb 01/09

FIGURE Engine Exhaust Temperatures - Breakaway Power - GECF6-80E1 series engine

Jan 01/10

Subject 6-1-5

L.E.C.Page 15

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Engine Exhaust Velocities Contours - Takeoff Power Feb 01/09

FIGURE Engine Exhaust Velocities - Takeoff Power - PW 4000 seriesengine

Feb 01/09

FIGURE Engine Exhaust Velocities - Takeoff Power - RR Trent 700series engine

Feb 01/09

FIGURE Engine Exhaust Velocities - Takeoff Power - GE CF6-80E1series engine

May 01/07

Subject 6-1-6

Engine Exhaust Temperatures Contours - Takeoff Power Feb 01/09

FIGURE Engine Exhaust Temperatures - Takeoff Power - PW 4000series engine

Feb 01/09

FIGURE Engine Exhaust Temperatures - Takeoff Power - RR Trent700 series engine

Feb 01/09

FIGURE Engine Exhaust Temperatures - Takeoff Power - GECF6-80E1 series engine

May 01/07

Subject 6-2-0

Airport and Community Noise Data Feb 01/09

Subject 6-2-1

Noise Data Feb 01/09

FIGURE Airport and Community Noise - PW 4000 series engine Feb 01/09

FIGURE Airport and Community Noise - RR Trent 700 series engine Feb 01/09

FIGURE Airport and Community Noise - GE CF6-80E1 series engine May 01/07

Subject 6-3-0

Danger Areas of Engines Jan 01/10

Subject 6-3-1

Ground Idle Power Feb 01/09

FIGURE Danger Areas of Engines - PW 4000 series engine Feb 01/09

FIGURE Danger Areas of Engines - RR Trent 700 series engine Feb 01/09

FIGURE Danger Areas of Engines - GE CF6-80E1 series engine May 01/07

Subject 6-3-2

Breakaway Power Feb 01/09

L.E.C.Page 16

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE




Subject 6-3-3

Takeoff Power Feb 01/09




Subject 6-4-0

APU Exhaust Velocities and Temperatures Jan 01/10

Subject 6-4-1

APU - GARRETT Feb 01/09

FIGURE Exhaust Velocities and Temperatures - APU -- GARRETTGTCP 331-350

Feb 01/09

CHAPTER 7

Subject 7-1-0

General Information R Apr 01/13

Subject 7-2-0

Landing Gear Footprint R Apr 01/13

FIGURE Landing Gear Footprint R Apr 01/13



Subject 7-3-0

Maximum Pavement Loads R Apr 01/13

FIGURE Maximum Pavement Loads R Apr 01/13



Subject 7-4-0

Landing Gear Loading on Pavement R Apr 01/13

L.E.C.Page 17

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Landing Gear Loading on Pavement - WV026, MRW 192900 kg

N Apr 01/13


N Apr 01/13


N Apr 01/13

Subject 7-5-0

Flexible Pavement Requirements - US Army Corps of EngineersDesign Method S-77-1

R Apr 01/13

FIGURE Flexible Pavement Requirements - WV026, MRW 192 900kg, CG 38.8 %

N Apr 01/13


N Apr 01/13


N Apr 01/13

Subject 7-6-0

Flexible Pavement Requirements - LCN Conversion R Apr 01/13

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

FIGURE Flexible Pavement Requirements - LCN - WV026, MRW 192900 kg, CG 38.8 %

N Apr 01/13



N Apr 01/13



N Apr 01/13

Subject 7-7-0

Rigid Pavement Requirements - Portland Cement Association DesignMethod

R Apr 01/13

FIGURE Rigid Pavement Requirements - WV026, MRW 192 900 kg,CG 38.8 %

N Apr 01/13


N Apr 01/13

L.E.C.Page 18

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE


N Apr 01/13

Subject 7-8-0

Rigid Pavement Requirements - LCN Conversion R Apr 01/13

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



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

FIGURE Rigid Pavement Requirements - LCN - WV026, MRW 192900 kg, CG 38.8 %

N Apr 01/13


N Apr 01/13


N Apr 01/13

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

Subject 7-9-0

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

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

FIGURE Aircraft Classification Number - Flexible Pavement - WV026,MRW 192 900 kg, CG 38.8 %

N Apr 01/13


N Apr 01/13



N Apr 01/13


N Apr 01/13



N Apr 01/13


N Apr 01/13

L.E.C.Page 19

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 8

Subject 8-0-0

Scaled Drawings N Apr 01/13

FIGURE Scaled Drawing N Apr 01/13



CHAPTER 10

Subject 10-0-0

Aircraft Rescue and Fire Fighting N Apr 01/13

FIGURE Front Page N Apr 01/13

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

FIGURE Crew Rest Compartments Location N Apr 01/13

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

FIGURE Composite Materials Location N Apr 01/13

FIGURE Ground Lock Safety Devices N Apr 01/13

FIGURE Emergency Evacuation Devices N Apr 01/13

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

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

FIGURE Control Panels N Apr 01/13

FIGURE APU Compartment Access N Apr 01/13


FIGURE Structural Break-in Points N Apr 01/13

Aircraft Rescue and Fire Fighting N Apr 01/13

FIGURE Front Page N Apr 01/13

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

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

FIGURE Composite Materials Location N Apr 01/13

FIGURE Ground Lock Safety Devices N Apr 01/13

L.E.C.Page 20

Apr 01/13


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Emergency Evacuation Devices N Apr 01/13

FIGURE Crew Doors and Emergency Exits N Apr 01/13

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

FIGURE Control Panels N Apr 01/13

FIGURE APU Compartment Access N Apr 01/13


FIGURE Structural Break-in Points N Apr 01/13

L.E.C.Page 21

Apr 01/13


TABLE OF CONTENTS

1 SCOPE

1-1-0 Purpose

1-2-1 Glossary

2 AIRCRAFT DESCRIPTION

2-1-1 General Aircraft Characteristics Data

2-2-0 General Aircraft Dimensions

2-3-0 Ground Clearances

2-4-1 Interior Arrangements - Plan View

2-5-0 Interior Arrangements - Cross Section

2-6-1 Lower Deck Cargo Compartments

2-6-2 Main Deck Cargo Compartments

2-6-3 Main and Lower Deck Cross-sections

2-7-0 Door Clearances

2-7-1 Forward Passenger / Crew Doors

2-7-2 Mid Passenger / Crew Doors

2-7-3 Emergency Exits

2-7-4 Aft Passenger / Crew Doors

2-7-5 Forward Cargo Compartment Doors

2-7-6 Aft Cargo Compartment Doors

2-7-7 Bulk Cargo Compartment Doors

2-7-8 Main and Center Landing Gear Doors

2-7-9 Radome

2-7-10 APU and Nose Landing Gear Doors

2-8-0 Escape Slides

2-9-0 Landing Gear

2-10-0 Exterior Lighting

2-11-0 Antennas and Probes Location

2-12-0 Engine and Nacelle

2-12-1 Auxiliary Power Unit

2-13-0 Levelling, symmetry and Alignment

2-14-0 Jacking for Maintenance

2-14-1 Jacking for Wheel Change

2-14-2 Support of Aircraft

T.O.C.Page 1

Apr 01/13


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


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

3-4-0 FAR / JAR Landing Field Length

3-4-1 ISA Conditions All series engines

3-5-0 Final Approach Speed

4 GROUND MANEUVERING


4-2-0 Turning Radii

4-3-0 Minimum Turning Radii

4-4-0 Visibility from Cockpit in Static 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 Aircraft Parking

5 TERMINAL SERVICING

5-0-0 TERMINAL SERVICING

5-1-0 Aircraft Servicing Arrangements

5-1-1 Symbols Used on Servicing Diagrams

5-1-2 Typical Ramp Layout - Open Apron

5-1-3 Typical Ramp Layout - Gate

5-2-0 Terminal Operations - Full Servicing

5-3-0 Terminal Operations - Transit

5-4-1 Ground Service Connections Layout

5-4-2 Grounding Points

5-4-3 Hydraulic System

5-4-4 Electrical System

5-4-5 Oxygen System

T.O.C.Page 2

Apr 01/13


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

5-5-0 Engine Starting Pneumatic Requirements

5-6-0 Ground Pneumatic Power Requirements

5-7-0 Preconditioned Airflow Requirements

5-8-0 Ground Towing Requirements

5-9-0 De-Icing and External Cleaning

6 OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

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

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

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

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

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

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

6-2-0 Airport and Community Noise

6-2-1 Noise Data

6-3-0 Danger Areas of Engines

6-3-1 Ground Idle Power

6-3-2 Breakaway Power

6-3-3 Takeoff Power

6-4-0 APU Exhaust Velocities and Temperatures

6-4-1 APU

7 PAVEMENT DATA


7-2-0 Landing Gear Footprint

7-3-0 Maximum Pavement Loads

7-4-0 Landing Gear Loading on Pavement

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

7-6-0 Flexible Pavement Requirements - LCN Conversion

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

7-8-0 Rigid Pavement Requirements - LCN Conversion

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

T.O.C.Page 3

Apr 01/13


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

Apr 01/13


SCOPE

1-1-0 Purpose

**ON A/C A330-200 A330-200F A330-300

Purpose

1. GeneralThe A330 AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING (AC)manual is issued for the A330-200, A330-200F and A330-300 basic versions to provide necessary datato airport operators, airlines and Maintenance/Repair Organizations (MRO) for airport andmaintenance facilities planning.

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

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

The A330 Family -- with Passenger, Freighter, VIP and Military Transport/Tanker variants - is one ofthe most widely-used, versatile and economic wide-bodies in service and has nearly 100 operators andcustomers flying to more than 300 airports every week.

The A330-200 and A330-300 offer several payload capabilities ranging from 200 passengers in a highcomfort multi-class layout, up to 440 passengers in a high efficiency configuration. The new-generation mid-size freighter, the A330-200F, has up to 70 t (154 324 lb) payload and a range up to4 000 nm (7 408 km). It offers better payload, range and economics than previous-generationfreighters.The ACJ330 offers true space and comfort whilst delivering a ”non-stop to the world” range forcorporate, VIP and government operators.The A330 MRTT is the most capable in-flight refueling platform available.

The A330 combines maturity and reliability with the most up-to-date technology. It consistentlyachieves an average dispatch reliability of over 99% and annual utilization of up to 5 500 FlightHours. At the same time it is continuously improved by incorporating the latest technologies, to loweroperating costs, increase efficiency, improve safety and enhance the passenger product -- pioneering240 minutes ETOPS, introducing RNP to wide-bodies and being the first aircraft to have line-fit totalconnectivity for passengers.

1-1-0Page 1

Apr 01/13


The latest improvement is an increase to 242t (533 519 lb) MTOW adding even more range -- 2 100nm (3 889 km) more range since the A330-300 EIS -- with lower fuel burn. In the meantime the A330engine manufacturers - General Electric, Pratt & Whitney and Rolls-Royce - have recently introducedfeatures to further reduce fuel burn, maintenance costs and improve performance.

This document does not include the latest A330 at 242t (533 519 lb) MTOW which is underdevelopment.

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 2

Apr 01/13


1-2-1 Glossary

**ON A/C A330-200 A330-200F A330-300

Glossary

1. List of Abbreviations

A/C Aircraft

ACN Aircraft Classification NumberAMM Aircraft Maintenance ManualAPU Auxiliary Power Unit

B/C (except A330-200F) Business Class

C/L Center Line

CBR California Bearing Ratio

CC Cargo Compartment

CG Center of Gravity

CKPT Cockpit

E Young’s Modulus

ELEC Electric, Electrical, Electricity

ESWL Equivalent Single Wheel Load

F/C (except A330-200F) First Class

FAA Federal Aviation AdministrationFDL Fuselage Datum Line

FR FrameFSTE Full Size Trolley Equivalent

FWD ForwardGPU Ground Power UnitGSE Ground Support Equipment

HYD Hydraulic

ICAO International Civil Aviation Organisation

IDG Integrated Drive Generator

ISA International Standard Atmosphere

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

LH Left HandLPS (except A330-200F) Last Pax Seating

MAC Mean Aerodynamic Chord

1-2-1Page 1

Apr 01/13


MAX MaximumMD Main DeckMDCC (A330-200F only) Main Deck Cargo Compartment

MIN MinimumMLG Main Landing Gear

MLW Maximum Design Landing Weight

MRW Maximum Design Ramp Weight

MTOW Maximum Design Take-Off Weight

MTW Maximum Design Taxi Weight

MZFW Maximum Design Zero Fuel Weight

NLG Nose Landing Gear

OAT Outside Air Temperature

PAX (except A330-200F) Passenger

PB/D (except A330-200F) Passenger Boarding/Deboarding

PBB Passenger Boarding Bridge

PCA Portland Cement AssociationPCN Pavement Classification Number

PRM (except A330-200F) Passenger with Reduced Mobility

RH Right Hand

ULD Unit Load DeviceUS United StatesWV Weight Variant

Y/C (except A330-200F) Economy Class

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

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

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

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

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

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

- Usable Volume:

1-2-1Page 2

Apr 01/13


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

Maximum volume of cargo compartment.- Usable Fuel:

Fuel available for aircraft propulsion.

1-2-1Page 3

Apr 01/13


2-1-1 General Aircraft Characteristics Data

**ON A/C A330-200 A330-300

General Aircraft Characteristics Data

**ON A/C A330-300

1. The following table provides characteristics of A330-300 Models, these data are specific to eachWeight Variant:

Aircraft CharacteristicsWV000 WV001 WV002 WV003

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

212 900 kg(469 364 lb)

184 900 kg(407 635 lb)

212 900 kg(469 364 lb)

215 900 kg(475 978 lb)

Maximum Take-Off Weight(MTOW)

212 000 kg(467 380 lb)

184 000 kg(405 650 lb)

212 000 kg(467 380 lb)

215 000 kg(473 994 lb)

Maximum Landing Weight (MLW)174 000 kg(383 604 lb)

174 000 kg(383 604 lb)

177 000 kg(390 218 lb)

177 000 kg(390 218 lb)

Maximum Zero Fuel Weight(MZFW)

164 000 kg(361 558 lb)

164 000 kg(361 558 lb)

167 000 kg(368 172 lb)

167 000 kg(368 172 lb)

Aircraft Characteristics

WV004 * WV010 WV011 WV012


209 900 kg to 215900 kg

(462 750 lb to 475978 lb)

217 900 kg(480 387 lb)

212 900 kg(469 364 lb)

218 900 kg(482 592 lb)


209 000 kg to 215000 kg

(460 766 lb to 473994 lb)

217 000 kg(478 403 lb)

212 000 kg(467 380 lb)

218 000 kg(480 608 lb)

Maximum Landing Weight (MLW)

182 000 kg to 177000 kg

(401 241 lb to 390218 lb)

179 000 kg(394 627 lb)

177 000 kg(390 218 lb)

182 000 kg(401 241 lb)


172 000 kg to 167000 kg

(379 195 lb to 368172 lb)

169 000 kg(372 581 lb)

167 000 kg(368 172 lb)

172 000 kg(379 195 lb)

NOTE : * Linear MTOW/MZFW trade-off relationship.

2-1-1Page 1

Apr 01/13


Aircraft CharacteristicsWV013 WV014 WV020 WV022 WV024


215 900 kg(475 978 lb)

205 900 kg(453 932 lb)

230 900 kg(509 047 lb)

233 900 kg(515 661 lb)

205 900 kg(453 932 lb)


215 000 kg(473 994 lb)

205 000 kg(451 948 lb)

230 000 kg(507 063 lb)

233 000 kg(513 677 lb)

205 000 kg(451 948 lb)


182 000 kg(401 241 lb)

185 000 kg(407 855 lb)

187 000 kg(412 264 lb)

185 000 kg(407 855 lb)


167 000 kg(368 172 lb)

172 000 kg(379 195 lb)

173 000 kg(381 400 lb)

175 000 kg(385 809 lb)

173 000 kg(381 400 lb)



217 900 kg(480 387 lb)

230 900 kg(509 047 lb)

212 900 kg(469 364 lb)

233 900 kg(515 661 lb)

205 900 kg(453 932 lb)


217 000 kg(478 403 lb)

230 000 kg(507 063 lb)

212 000 kg(467 380 lb)

233 000 kg(513 677 lb)

205 000 kg(451 948 lb)


185 000 kg(407 855 lb)

187 000 kg(412 264 lb)

187 000 kg(412 264 lb)

185 000 kg(407 855 lb)


169 000 kg(372 581 lb)

173 000 kg(381 400 lb)

175 000 kg(385 809 lb)

175 000 kg(385 809 lb)

173 000 kg(381 400 lb)

Aircraft CharacteristicsWV054 WV055 ** WV056


235 900 kg(520 070 lb)

235 900 kg(520 070 lb)

205 900 kg(453 932 lb)


235 000 kg(518 086 lb)

235 000 kg(518 086 lb)

205 000 kg(451 948 lb)


187 000 kg(412 264 lb)

187 000 kg(412 264 lb)


173 000 kg(381 400 lb)

173 000 kg to 175 000 kg(381 400 lb to 385 809 lb)

175 000 kg(385 809 lb)

NOTE : ** Dynamic Payload between WV052 and WV054.

2. The following table provides characteristics of A330-300 Models, these data are common to eachWeight Variant:

Aircraft Characteristics

Standard Seating Capacity (Single-class) 335

2-1-1Page 2

Apr 01/13


Aircraft Characteristics97 530 l

(25 765 US gal)Usable Fuel Capacity(density = 0.785 kg/l) 76 561 kg

(168 787 lb)

Pressurized Fuselage Volume (A/C nonequipped)

1 056 m3

(37 292 ft3)

Passenger Compartment Volume372 m3

(13 137 ft3)

Cockpit Volume12 m3

(424 ft3)

Usable Volume, FWD CC(Based on LD3)

78 m3

(2754 ft3)

Usable Volume, AFT CC(Based on LD3)

60.7 m3

(2 142 ft3)

Usable Volume, Bulk CC19.7 m3

(695 ft3)

Water Volume, FWD CC107 m3

(3 789ft3)

Water Volume, AFT CC85.7 m3

(3 026ft3)

Water Volume, Bulk CC22.7 m3

(802 ft3)

**ON A/C A330-200

3. The following table provides characteristics of A330-200 Models, these data are specific to eachWeight Variant:



230 900 kg(509 047

lb)

230 900 kg(509 047

lb)

233 900 kg(515 661

lb)

233 900 kg(515 661

lb)

202 900 kg(447 318

lb)

Maximum Take-Off Weight (MTOW)230 000 kg(507 063

lb)

230 000 kg(507 063

lb)

233 000 kg(513 677

lb)

233 000 kg(513 677

lb)

202 000 kg(445 334

lb)

Maximum Landing Weight (MLW)180 000 kg(396 832

lb)

182 000 kg(401 241

lb)

182 000 kg(401 241

lb)

180 000 kg(396 832

lb)

180 000 kg(396 832

lb)

2-1-1Page 3

Apr 01/13



Maximum Zero Fuel Weight (MZFW)168 000 kg(370 376

lb)

170 000 kg(374 786

lb)

170 000 kg(374 786

lb)

168 000 kg(370 376

lb)

168 000 kg(370 376

lb)



220 900 kg(487 001

lb)

192 900 kg(425 272

lb)

220 900 kg(487 001

lb)

230 900 kg(509 047

lb)

192 900 kg(425 272

lb)


lb)

192 000 kg(423 287

lb)

220 000 kg(485 017

lb)

230 000 kg(507 063

lb)

192 000 kg(423 287

lb)


lb)

180 000 kg(396 832

lb)

180 000 kg(396 832

lb)

180 000 kg(396 832

lb)

180 000 kg(396 832

lb)


lb)

168 000 kg(370 376

lb)

168 000 kg(370 376

lb)

168 000 kg(370 376

lb)

168 000 kg(370 376

lb)



233 900 kg(515 661

lb)

210 900 kg(464 955

lb)

230 900 kg(509 047

lb)

192 900 kg(425 272

lb)

233 900 kg(515 661

lb)


lb)

210 000 kg(462 971

lb)

230 000 kg(507 063

lb)

192 000 kg(423 287

lb)

233 000 kg(513 677

lb)


lb)

180 000 kg(396 832

lb)

182 000 kg(401 241

lb)

182 000 kg(401 241

lb)

180 000 kg(396 832

lb)


lb)

168 000 kg(370 376

lb)

170 000 kg(374 786

lb)

170 000 kg(374 786

lb)

168 000 kg(370 376

lb)

2-1-1Page 4

Apr 01/13


Aircraft CharacteristicsWV057 WV058 WV059 WV060


236 900 kg(522 275 lb)

238 900 kg(526 684 lb)

202 900 kg(447 318 lb)

220 900 kg(487 001 lb)

Maximum Take-Off Weight (MTOW)236 000 kg(520 291 lb)

238 000 kg(524 700 lb)

202 000 kg(445 334 lb)

220 000 kg(485 017 lb)


182 000 kg(401 241 lb)

182 000 kg(401 241 lb)

182 000 kg(401 240 lb)

Maximum Zero Fuel Weight (MZFW)170 000 kg(374 786 lb)

168 000 kg(370 376 lb)

170 000 kg(374 786 lb)

170 000 kg(374 786 lb)

Aircraft CharacteristicsWV061 WV062 ***


230 900 kg(509 047 lb)

238 900 kg(526 684 lb)

Maximum Take-Off Weight (MTOW)230 000 kg(507 063 lb)

238 000 kg(524 700 lb)


182 000 kg(401 241 lb)

Maximum Zero Fuel Weight (MZFW)168 000 kg(370 376 lb)

168 000 kg to 170 000 kg(370 376 lb to 374 786 lb)

NOTE : *** Dynamic Payload between WV057 and WV058.

4. The following table provides characteristics of A330-200 Models, these data are common to eachWeight Variant:

Aircraft CharacteristicsStandard Seating Capacity 303

139 090 l(36 744 US gal)Usable Fuel Capacity

(density = 0.785 kg/l) 109 185 kg(240 711 lb)

Pressurized Fuselage Volume (A/C nonequipped)

950 m3

(33 548 ft3)

Passenger Compartment Volume335 m3

(11 830 ft3)

Cockpit Volume12 m3

(424 ft3)

2-1-1Page 5

Apr 01/13


Aircraft CharacteristicsUsable Volume, FWD CC(Based on LD3)

60.7 m3

(2 142 ft3)


52 m3

(1 836 ft3)


(695 ft3)

Water Volume, FWD CC84.6 m3

(2 988 ft3)


(2 511 ft3)


(802 ft3)

2-1-1Page 6

Apr 01/13


**ON A/C A330-200F

General Aircraft Characteristics Data

1. The following table provides characteristics of A330-200F Models, these data are specific to eachWeight Variant:

Aircraft CharacteristicsWV000 WV001 WV002*

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

233 900 kg(515 661 lb)

227 900 kg(502 433 lb)

233 900 kg(515 661 lb)


233 000 kg(513 677 lb)

227 000 kg(500 449 lb)

233 000 kg(513 677 lb)

Maximum Landing Weight(MLW)

182 000 kg(401 241 lb)

187 000 kg(412 264 lb)

187 000 kg(412 264 lb)


173 000 kg(381 400 lb)

178 000 kg(392 423 lb)

173 000 kg to 178 000kg

(381 399 lb to 392 422lb)

Estimated MaximumPayload PW 4000

64 742 kg(142 732 lb)

69 742 kg(153 755 lb)

64 742 kg to 69 742 kg(142 732 lb to 153 755

lb)

Estimated MaximumPayload TRENT 700

65 000 kg(143 300 lb)

70 000 kg(154 324 lb)

65 000 kg to 70 000 kg(143 300 lb to 154 324

lb)

NOTE : * Dynamic Payload between WV000 and WV001

2. The following table provides characteristics of A330-200F Models, these data are common to eachWeight Variant:

Aircraft CharacteristicsSupernumerary area 6

Usable Fuel Capacity(density = 0.785 kg/l)

139 090 l(36 755 US gal)

Pressurized Fuselage Volume(A/C non equipped)

900 m3

(31 783 ft3)

Cockpit Volume12 m3

(424 ft3)

2-1-1Page 7

Apr 01/13


Aircraft CharacteristicsMain Deck CargoCompartment Usable Volume(Based on 96”x125” pallet)

336.8 m3

(11 894 ft3)

Main Deck CargoCompartment Water Volume

466.5 m3

(16 474 ft3)

Usable Volume, FWD CC(Based on LD3)

60.7 m3

(2 142 ft3)


52 m3

(1 836 ft3)


(695 ft3)

Water Volume, FWD CC84.6 m3

(2 988 ft3)


(2 511 ft3)


(802 ft3)

2-1-1Page 8

Apr 01/13


2-2-0 General Aircraft Dimensions

**ON A/C A330-200 A330-300

General Aircraft Dimensions

1. This section provides General Aircraft Dimensions for pax version.

2-2-0Page 1

Apr 01/13


**ON A/C A330-300

(35.04 ft)10.68 m

(41.37 ft)12.61 m

(61.48 ft)18.74 m

(2.33 ft)0.71 m

(197.83 ft)60.3 m

(63.65 ft)19.4 m

(105.15 ft)32.05 m

(18.5 ft)5.64 m

(25.56 ft)7.79 m

(172.01 ft)52.43 m

(206.33 ft)62.89 m

(208.89 ft)63.67 m

(10.17 ft)3.1 m

(21.88 ft)6.67 m

(27.23 ft)8.3 m

(26.71 ft)8.14 m

NOTE:RELATED TO AIRCRAFT ATTITUDE AND WEIGHT. F_AC_020200_1_0010101_01_02

General Aircraft Dimensions(Sheet 1 of 2)

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

2-2-0Page 2

Apr 01/13


**ON A/C A330-300

(69.82 ft)21.28 m

(138.52 ft)42.22 m

(128.28 ft)39.1 m

(202.33 ft)61.67 m

(208.99 ft)63.7 m

(34.65 ft)10.56 m

(8.23 ft)2.51 m

(6.66 ft)2.03 m

(21.1 ft)6.43 m

(35.7 ft)10.88 m

7.46 m

(46.

62 ft

)14

.21

m

(57.

91 ft

)17

.65

m

(24.48 ft)

(70.37 ft)21.45 m

(69.36 ft)21.14 m

GE

PW

RR

NOTE:RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.

F_AC_020200_1_0010104_01_00


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

2-2-0Page 3

Apr 01/13


**ON A/C A330-200

(94.65 ft)28.85 m

(18.5 ft)5.64 m

(28.15 ft)8.58 m

(154.49 ft)47.09 m

(188.68 ft)57.51 m

(193.57 ft)59 m

(9.15 ft)2.79 m

(21.88 ft)6.67 m

(35.04 ft)10.68 m

(41.37 ft)12.61 m

(61.48 ft)18.74 m

(2.33 ft)0.71 m

(197.83 ft)60.3 m

(63.65 ft)19.4 m

(30.51 ft)9.3 m

(29.92 ft)9.12 m


General Aircraft Dimensions(Pre Mod 48979) (Sheet 1 of 3)

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

2-2-0Page 4

Apr 01/13


**ON A/C A330-200

(94.65 ft)28.85 m

(18.5 ft)5.64 m

(28.15 ft)8.58 m

(154.49 ft)47.09 m

(188.68 ft)57.51 m

(192.98 ft)58.82 m

(10.17 ft)3.1 m

(21.88 ft)6.67 m

(35.04 ft)10.68 m

(41.37 ft)12.61 m

(61.48 ft)18.74 m

(2.33 ft)0.71 m

(197.83 ft)60.3 m

(63.65 ft)19.4 m

(28.87 ft)8.8 m

(28.31 ft)8.63 m


General Aircraft Dimensions(Post Mod 48979) (Sheet 2 of 3)

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

2-2-0Page 5

Apr 01/13


**ON A/C A330-200


(59.32 ft)18.08 m

(128.08 ft)39.04 m

(117.98 ft)35.96 m

(184.91 ft)56.36 m

(191.5 ft)58.37 m

(34.65 ft)10.56 m

(8.07 ft)2.46 m

(6.59 ft)2.01 m

(21.13 ft)6.44 m

(35.7 ft)10.88 m

7.46 m

(46.

62 ft

)14

.21

m

(57.

91 ft

)17

.65

m

(24.48 ft)

(59.88 ft)18.25 m

(58.86 ft)17.94 m

GE

PW

RR

F_AC_020200_1_0020102_01_00


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

2-2-0Page 6

Apr 01/13


**ON A/C A330-200F

General Aircraft Dimensions

1. This section provides General Aircraft Dimensions for cargo version.

2-2-0Page 7

Apr 01/13


**ON A/C A330-200F

(94.65 ft)28.85 m

(154.49 ft)47.09 m

(188.68 ft)57.51 m

(192.98 ft)58.82 m

(18.5 ft)5.64 m

(28.15 ft)8.58 m

(10.17 ft)3.1 m

(28.31 ft)8.63 m

(21.88 ft)6.67 m

(28.87 ft)8.8 m

(197.83 ft)60.3 m

(63.65 ft)19.4 m

(35.04 ft)10.68 m

(41.37 ft)12.61 m

(61.48 ft)18.74 m

(2.33 ft)0.71 m


F_AC_020200_1_0030101_01_02


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

2-2-0Page 8

Apr 01/13


**ON A/C A330-200F


(59.32 ft)18.08m

(126.08 ft)38.43 m

(117.95 ft)35.95 m

(184.84 ft)56.34 m

(191.47 ft)58.36 m

(59.88 ft)18.25 m

PW

RR

(8.14 ft)2.48 m

(6.63 ft)2.02 m

(21.1 ft)6.43 m

(34.61 ft)10.55 m

(35.7 ft)10.88 m

7.46 m(24.48 ft)

(46.

62 ft

)14

.21

m

(57.

91 ft

)17

.65

m

F_AC_020200_1_0030102_01_00


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

2-2-0Page 9

Apr 01/13


2-3-0 Ground Clearances

**ON A/C A330-200 A330-200F A330-300

Ground Clearances

1. This section gives the height of various points of the aircraft, above the ground, for different aircraftpax configurations.Dimensions in the tables are approximate and will vary with tire type, W&B an others specialconditions.

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

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

2-3-0Page 1

Apr 01/13


**ON A/C A330-300

X L C2 Y KE3 H E2

D C1B E1

AM

P N V U T S R O

J

MRW212 900 kg469 360 lb

Am ftm ftm ftm

BC1C2D

GE = RPW = RRR = R

YXVUTS

PONMLKJH

E3E2E1

3.687.484.974.644.333.870.870.900.948.058.336.4617.185.773.435.342.042.742.282.104.838.537.742.704.55

12.0724.54

15.2214.2012.702.852.953.0826.4127.3221.2056.3618.9311.2517.56.7

8.997.486.89

15.8428

25.48.85

14.92

16.30

3.467.244.724.414.133.680.690.720.767.708.096.13

16.945.553.225.311.862.542.101.954.678.317.582.554.41

11.3523.7615.4814.4613.5512.072.262.362.49

25.2626.5420.1155.5818.2010.5617.46.108.336.886.39

15.3227.2624.868.36

14.46

3.357.034.674.374.11

0.720.750.797.617.886.0616.725.413.135.201.852.452.142.034.738.197.672.664.55

3.64

1123.0615.3214.3313.4811.942.362.462.59

24.9625.8519.8854.8517.7510.2717.066.078.037.026.6615.5126.8725.16

8.7214.92

4.398.106.30

65.705.252.212.292.348.969.237.55

17.626.534.246.433.263.683.683.686.329.329.324.146.32

14.426.520.619.618.717.27.257.517.6729.430.224.757.821.4

21.110.7121212

20.730.530.513.520.7

13.9

ft

NOTE:

MAXIMUM RAMPWEIGHT CG 36.5%

MAXIMUM RAMPWEIGHT CG 15%

AIRCRAFTON JACKS

PASSENGER AND CARGO DOOR CLEARANCES ARE MEASURED FROMTHE CENTER OF THE DOOR SILL AND FROM FLOOR LEVEL.

119 000 kgCG 26.8%

F_AC_020300_1_0010101_01_02

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

2-3-0Page 2

Apr 01/13


**ON A/C A330-200

K

E3 H E2 B E1M

P N V U T S R O

ZJ

Am ftm m ftm

BC1C2D

PW = RRR = R

VUTS

PON

MLKJHE3E2E1

3.683.68

6.32

20.619.618.717.27.257.517.6729.430.224.7

21.4

10.7121212

20.730.5

20.7


5.413.667.474.954.634.353.890.870.900.948.088.306.48

5.743.505.36

2.702.232.044.868.547.75

2.02

YZ

2.784.63

12.01

16.2415.1914.2712.762.852.953.0826.5127.2321.26

18.8311.4817.66.638.867.31

28.02

17.75

24.51

25.429.12

15.19

3.437.234.734.424.133.670.670.700.747.718.056.14

5.513.275.151.812.482.031.844.668.317.56

4.442.58

17.1211.2523.7215.52

13.5512.042.192.292.42

25.2926.4120.14

18.0710.73

5.938.136.666.03

27.2624.80

14.568.46

5.433.306.974.674.374.113.640.720.750.797.617.776.05

5.353.165.101.832.402.122.014.78

4.632.74

17.8110.8222.8615.3214.3313.4811.942.362.462.59

24.9625.4919.85

17.5510.3616.7

67.876.956.5915.7

25.2326.77

8.99

ft15.19

7.104.398.106.30

65.705.252.212.292.348.969.237.55

6.534.246.463.26

3.686.369.329.324.14 13.5

30.5

21.213.9

14.423.30

MRW230 900 kg509 042 lb

14.50

8.167.69

ft

MAXIMUM RAMPWEIGHT CG 21%

15.96.7

15.3

16.9

5.22

25.5

V U

V U

M1 18.1261.0959.45

18.23 59.858.17

17.9817.48

58.9957.35

17.7117.21

58.1 18.6256.4617.73

AIRCRAFTON JACKS

M1 = POST MOD 48979 (SHORTER FIN INSTALLATION).NOTE:

GE = R

PASSENGER AND CARGO DOOR CLEARANCES ARE MEASURED FROMTHE CENTER OF THE DOOR SILL AND FROM FLOOR LEVEL.

L C2 D C1 AY

176 000 kgMID CG 27.9%

F_AC_020300_1_0010202_01_00

Ground ClearancesFIGURE-2-3-0-991-001-B01

2-3-0Page 3

Apr 01/13


**ON A/C A330-200F

OR

ST

UV

NP

ZC

1J

VU

M

E5

RH

E6

C2

KY

NO

TE

:P

AS

SE

NG

ER

AN

D C

AR

GO

DO

OR

CLE

AR

AN

CE

S A

RE

ME

AS

UR

ED

FR

OM

TH

E C

EN

TE

RO

F T

HE

DO

OR

SIL

L A

ND

FR

OM

FLO

OR

LE

VE

L.

DB

E3

A

F_AC_020300_1_0010301_01_00

Ground Clearances(Sheet 1 of 2)

FIGURE-2-3-0-991-001-C01

2-3-0Page 4

Apr 01/13


**ON A/C A330-200F

m 5.06

8.44

8.06

3.11

4.98

16.6

027

.69

26.4

410

.20

16.3

4ft

2.98

9.79

17.4

157

.12

1.06

1.13

7.80

3.52

5.55

2.16

2.70

2.47

2.22

3.48

3.71

25.5

9

11.5

518

.21

7.09

8.86

8.10

7.28

8.31

27.2

69.

2330

.28

3.61

7.92

11.8

425

.98

6.22

20.4

1

2.74

2.92

3.02

8.99

9.59

9.91

NO

TE

:P

AS

SE

NG

ER

AN

D C

AR

GO

DO

OR

CLE

AR

AN

CE

S A

RE

ME

AS

UR

ED

FR

OM

TH

E C

EN

TE

R O

F T

HE

DO

OR

SIL

L A

ND

FR

OM

FLO

OR

LE

VE

L.

115

000

kgC

G 2

0%ft

mft

m

4.88

8.06

7.87

2.93

4.82

16.0

126

.44

25.8

29.

6115

.81

5.03

7.91

8.01

3.085

16.5

025

.95

26.2

810

.10

16.4

0

0.82

0.89

7.46

16.9

53.

155.

131.

892.

372.

262.

06

2.69

2.92

24.4

855

.61

10.3

316

.83

6.20

7.78

7.41

6.76

0.87

0.95

7.36

16.6

73.

044.

911.

912.

292.

352.

24

2.85

3.12

24.1

554

.69

9.97

16.1

16.

277.

517.

717.

35

7.85

25.7

57.

5724

.84

8.88

29.1

38.

7828

.81

3.25

7.46

10.6

624

.48

3.12

7.19

10.2

423

.59

6.08

19.9

56.

2920

.64

2.44

2.69

2.63

2.70

8 8.83

8.62

8.86

2.41

2.67

2.60

2.64

7.89

8.75

8.53

8.66

MR

W 2

33 9

00 k

gC

G 2

0.6%

MR

W 2

33 9

00 k

gC

G 3

7.4%

A B C1

C2 D

PW

RR

R R

YVUVUTSMKJHE6

E5

E3 N ZO P

F_AC_020300_1_0010302_01_00

Ground Clearances(Sheet 2 of 2)

FIGURE-2-3-0-991-001-C01

2-3-0Page 5

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

A B C

m ft m ft m ft

A

B

C

D



6.426.506.85

6.58 6.26 6.20

6.206.266.58

6.38 6.07 6.02

D

22.47

21.59

21.59

20.93

21.33

20.54

20.54

19.91

21.06

20.34

20.34

19.75

AILERONS UP

A/C IN MAINTENANCECONFIGURATION

MID CG 26.8%

F_AC_020300_1_0150101_01_00

Ground ClearancesAilerons Up

FIGURE-2-3-0-991-015-A01

2-3-0Page 6

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

A B C D

m ft m ft m ft

A

B

C

D



6.30

5.83

5.83

5.47

5.94

5.51

5.51

5.17

5.87

5.44

5.44

5.11

20.67 19.49 19.26

16.7716.9617.95

19.13

19.13

18.08

18.08

17.85

17.85

AILERONS DOWN


MID CG 26.8%

F_AC_020300_1_0160101_01_00

Ground ClearancesAilerons Down

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

2-3-0Page 7

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

m ft m ft m ft

A

B

C

D

5.10

E

F

G

H

J

K

L

M 4.58

5.68

5.68

5.48



6.60

6.44

6.44

6.29

6.29

6.12

6.12

5.93

5.93

5.72

5.31

4.76

6.31

6.18

6.18

6.04

6.04

5.89

5.89

5.71

5.71

5.51

6.26

6.13

6.13

6.00

6.00

5.86

5.86

5.07

4.55

21.65

21.13

21.13

20.64

20.64

20.08

20.08

19.46

19.46

18.77

17.42

15.62

20.70

20.28

20.28

19.82

19.82

19.32

19.32

18.73

18.73

18.08

16.73

15.03

20.54

20.11

20.11

19.69

19.69

19.23

19.23

18.64

17.98

16.63

14.93

18.64

SPOILERS 1 TO 6 EXTENDED


MID CG 26.8%

A B C D E F G H L MJ K

F_AC_020300_1_0170101_01_00

Ground ClearancesSpoilers Extended

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

2-3-0Page 8

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

m ft m ft m ft

A

B

C

D

E

F

G

H

J

K

L

M

N

P

3.46

4.25

4.28

4.65

4.65

4.99

4.99

5.30

5.37

5.65

5.65

5.91

5.91

6.16

3.28

4.09

4.10

4.45

4.45

4.77

4.77

5.06

5.12

5.37

5.37

5.61

5.61

5.82

3.31

4.10

4.11

4.45

4.45

4.76

4.76

5.03

5.09

5.33

5.33

5.56

5.56

5.76



11.35

13.94

14.04

15.26

15.26

16.37

16.37

17.39

17.62

18.54

18.54

19.39

19.39

20.21

10.76

13.42

13.45

14.60

14.60

15.65

15.65

16.60

16.80

17.62

17.62

18.41

18.41

19.09

10.86

13.45

13.48

14.60

14.60

15.62

15.62

16.50

16.70

17.49

17.49

18.24

18.24

18.90

LEADING EDGE SLATS EXTENDED


MID CG 26.8%

A D E F G H J K L M N PB C

F_AC_020300_1_0180101_01_00

Ground ClearancesSlats Fully Extended

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

2-3-0Page 9

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

m ft m ft m ft

A

B

C

D

A B C D

5.21

4.00

4.00

2.71

4.91

3.79

3.80

2.52

4.85

3.75

3.76

2.49



17.09

13.12

13.12

8.89

16.11

12.43

12.47

8.27

15.91

12.30

12.34

8.17

INNER AND OUTER FLAPS EXTENDED


MID CG 26.8%

F_AC_020300_1_0190101_01_00

Ground ClearancesFlaps Fully Extended

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

2-3-0Page 10

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

m ft m ft m ft

A

B

C

D

3.24

4.08

3.73

3.48

2.95



3.88

3.53

3.29

2.75

3.82

3.48

2.71

13.39

12.24

11.42

9.68

12.73

11.58

10.79

9.02

12.53

11.42

10.63

8.89

A B C D

FLAP TRACKS EXTENDED


MID CG 26.8%

F_AC_020300_1_0200101_01_00

Ground ClearancesFlaps-Tracks Fully ExtendedFIGURE-2-3-0-991-020-A01

2-3-0Page 11

Apr 01/13


2-4-1 Interior Arrangements - Plan View

**ON A/C A330-200 A330-300

Interior Arrangements - Plan View

1. This section gives the typical configuration for A330 pax version.

2-4-1Page 1

Apr 01/13


**ON A/C A330-300

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

FO

RW

AR

D P

AS

SE

NG

ER

/CR

EW

DO

OR

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

FO

RW

AR

D P

AS

SE

NG

ER

/CR

EW

DO

OR

NO

TE

:F

OR

DO

OR

SIZ

ES

SE

E C

HA

PT

ER

2−

7

PA

SS

EN

GE

R S

EA

TS

(29

5 T

OT

AL)

12 F

IRS

T C

LAS

S

241

EC

ON

OM

Y C

LAS

S

CO

AT

ST

OW

AG

E

ST

OW

AG

E

GA

LLE

Y

LAV

AT

OR

Y

AT

TE

ND

AN

TS

SE

AT

42 B

US

INE

SS

CLA

SS

VCC

ITE

MD

ES

IGN

AT

ION

A C G L S

(12)

(4)

(7)

(9)

(1)

A

A AA

A A

A A

A A

AA

GG

GG

GG

G

C C

CC

L LLL

L L L L

L

S

F_AC_020401_1_0010101_01_00

Interior Arrangements - Plan ViewTypical Configuration

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

2-4-1Page 2

Apr 01/13


**ON A/C A330-200

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

FO

RW

AR

D P

AS

SE

NG

ER

/CR

EW

DO

OR

AF

T P

AS

SE

NG

ER

/CR

EW

DO

OR

EM

ER

GE

NC

Y E

XIT

FO

RW

AR

D P

AS

SE

NG

ER

/CR

EW

DO

OR

NO

TE

:F

OR

DO

OR

SIZ

ES

SE

E C

HA

PT

ER

2−

7

PA

SS

EN

GE

R S

EA

TS

(25

3 T

OT

AL)

12 F

IRS

T C

LAS

S

205

EC

ON

OM

Y C

LAS

S

TR

OLL

EY

36 B

US

INE

SS

CLA

SS

VC

C

CO

AT

ST

OW

AG

E

ST

OW

AG

E

GA

LLE

Y

LAV

AT

OR

Y

AT

TE

ND

AN

TS

SE

AT

ITE

MD

ES

IGN

AT

ION

A C G L S

(12)

(2)

(6)

(8)

(1)

Tr

(2)

A

A AA

AA

AA

A A

A AC

C

G

GG

G

G G

L L L LLL

L LS

Tr

Tr

F_AC_020401_1_0020101_01_00

Interior Arrangements - Plan ViewTypical Configuration

FIGURE-2-4-1-991-002-A01

2-4-1Page 3

Apr 01/13


2-5-0 Interior Arrangements - Cross Section

**ON A/C A330-200 A330-300

Interior Arrangements - Cross Section

1. This section gives the typical configuration of A330 pax version.

2-5-0Page 1

Apr 01/13


**ON A/C A330-200 A330-300

AB

C C D

C D C D

F N M

C C D

H

K K

F G

222 in5.640 m

208 in5.290 m

FIRST CLASS, 6 ABREAST BUSINESS CLASS, 7 ABREAST

TOURIST CLASS, 8 ABREAST CHARTER CLASS, 9 ABREAST

A − 54.0 in (1371.6 mm)B − 21.0 in (533 mm)C − 39.6 in (1006 mm)D − 17.7 in (450 mm)E − 72.0 in (1829 mm)F − 19.0 in (483 mm)

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

91.7 in2.330 mA E

H C

M

F_AC_020500_1_0010101_01_00

Interior Arrangements - Cross SectionTypical Configuration

FIGURE-2-5-0-991-001-A01

2-5-0Page 2

Apr 01/13


2-6-1 Lower Deck Cargo Compartments

**ON A/C A330-200 A330-200F A330-300

Lower Deck Cargo Compartments

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

2-6-1Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

0.95 m(3.12 ft)

2.75 m(9.02 ft)

2.78 m(9.12 ft)

15.02 m(49.28 ft)

A330−300

11.82 m(38.78 ft)

A330−200/−200F

12.32 m(40.42 ft)

10.19 m(33.43 ft)

4.04 m(13.25 ft)

4.04 m(13.25 ft)

LOWER DECKFWD CARGO

COMPARTMENT

LOWER DECKAFT CARGO

COMPARTMENT

LOWER DECKBULK CARGO

COMPARTMENT

FR39.1 FR53.2 FR65 FR73FR20

NOTE:APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATION.

F_AC_020601_1_0030101_01_01

Lower Deck Cargo CompartmentsLocation and Dimensions

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

2-6-1Page 2

Apr 01/13


**ON A/C A330-200 A330-200F

14 LD3 60.4 in X 61.5 in

7 LD3 60.4 in X 61.5 in

4 PALLETS 96 in X 125 in


7 PALLETS 60.4 in X 125 in

12 LD3 60.4 in X 61.5 in

6 LD3 60.4 in X 61.5 in




F_AC_020601_1_0040101_01_01

Lower Deck Cargo CompartmentsLoading Combinations

FIGURE-2-6-1-991-004-A01

2-6-1Page 3

Apr 01/13


**ON A/C A330-300

18 LD3 60.4 in X 61.5 in

9 LD3 60.4 in X 61.5 in




14 LD3 60.4 in X 61.5 in

7 LD3 60.4 in X 61.5 in




F_AC_020601_1_0040201_01_00

Lower Deck Cargo CompartmentsLoading Combinations

FIGURE-2-6-1-991-004-B01

2-6-1Page 4

Apr 01/13


2-6-2 Main Deck Cargo Compartments

**ON A/C A330-200F

Main Deck Cargo Compartment

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

2-6-2Page 1

Apr 01/13


**ON A/C A330-200F

3.69 m(12.11 ft)

FR19 FR80

41.04 m(134.65 ft)

MAIN DECKCARGO

COMPARTMENT

NOTE:DEPENDING ON A/C CONFIGURATION. F_AC_020602_1_0060101_01_00

Main Deck Cargo CompartmentLocation and Dimensions

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

2-6-2Page 2

Apr 01/13


**ON A/C A330-200F

1R

1L

2R

2L

3R

3L

4R

4L

5R

5L

6R

6L

7R

7L

8R

8L

9R

9L

10R

10L

11R

11L23 24 25 26

22 HCU−6/E (MILITARY) ULDs

4 HCU−6/E (MILITARY) ULDs

ABR

ABL

BCR

BCL

CER

CEL

EFR

EFL

FHR

FHL

HJR

HJL

JKR

JKL

KMR

KML

MPR

MPL

PRR

PRL

ABL

BCR

BCL

CER

CEL

EFR

EFL

FHR

FHL

HJR

HJL

JKR

JKL

KMR

KML

MPR

MPLSSRR TTPP

18 ULDs

96 in x 125 in

20 ULDs

88 in x 125 in3 ULDs

88 in x 125 in

4 ULDs

96 in x 125 in

ABR

F_AC_020602_1_0010101_01_01

88 in x 108 in

88 in x 108 in

T US

Main Deck Cargo CompartmentLoading Combinations

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

2-6-2Page 3

Apr 01/13


**ON A/C A330-200F

AA BB CC DD EE FF GG HH JJ KK LL MM PP RR SS TT

16 ULDs

96 in x 125 in

17 ULDs

88 in x 125 in

AA BB CC DD EE FF GG HH JJ KK LL MM PP RR SS TT UU

AB BC CE EF FH HJ JK KM MP PP RR SS TT

9 AMA ULDs

96 in x 125 in

4 ULDs

96 in x 125 in

AB BC CE EF FH HJ JK KM MP

9 AMA ULDs

96 in x 125 in

R S T U

F_AC_020602_1_0020101_01_01

4 ULDs

88 in x 125 in


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

2-6-2Page 4

Apr 01/13


**ON A/C A330-200F

42 AYY ULDs

1R

1C

1L

2R 3R 4R 5R 6R 7R 8R 9R 10R 11R 12R 13R 14R

2C 3R 4C 5C 6C 7C 8C 9C 10C 11C 12C 13C 14C

2L 3L 4L 5L 6L 7L 8L 9L 10L 11L 12L 13L 14L

1R 2R 3R 4R 5R 6R 7R 8R 9R 10R 11R 12R 13R 14R

1L 2L 3L 4L 5L 6L 7L 8L 9L 10L15R 16R 17R

15L 16L 17L

1L 2L 3L 4L 5L 6L 7L 8L 9L 10L 11L 12L 13L 14L

2R 3R 4R 5R 6R 7R 8R 9R 10R 11R 12R 13R 14R

15 16 17

15R 16R 17R

15L 16L 17L

1R

88 in x 62 in

6 AYY ULDs

14 AYY ULDs + 10 AMJ ULDs

14 AYY ULDs + 14 SAA ULDs

6 AYY ULDs

SAA

88 in x 62 in

88 in x 62 in

3 SAA ULDs

AYY

AYY

AMJ

88 in x 125 in

62 in x 88 in + 96 in x 125 in

62 in x 88 in + 88 in x 125 in

F_AC_020602_1_0030101_01_02


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

2-6-2Page 5

Apr 01/13


**ON A/C A330-200F

F_AC_020602_1_0050101_01_00

LPR PP RR SS TT

4 ULDs 4 ULDs

96 in x 125 in

JLRFHRCERBBAA

2 ULDs

96 in x 125 in

PP RR SS TT

3 ULDs 5 ULDs

96 in x 125 in

CEGBBAA

2 ULDs

96 in x 125 in

PP RR SS TT

8 ULDs 4 ULDs

96 in x 125 in

4 ULDs

96 in x 125 in

MMFJG JMG

CFRR

CFRL

BCR

BCL

ABR

ABL

FHRR

FHRL

JLRR

JLRL

LPRR

LPRL

16 ft

20 ft

16 ft


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

2-6-2Page 6

Apr 01/13


2-6-3 Main and Lower Deck Cross-sections

**ON A/C A330-200F

Main and Lower Deck Cross-sections

1. This section gives Main and Lower Deck Cross-sections for cargo version.

2-6-3Page 1

Apr 01/13


**ON A/C A330-200F

LD6 / AAFCONTAINER AKE AKE

LD3 LD3ALF / AAF / AMF

CONTAINER PALLET

62"

96"

96"

AMA

125"

96"

96"

AMF96" x 125"

LD988" x 125"

88"

96"

REFERENCE CARGO CONFIGURATION LAYOUT

OPTIONAL CARGO CONFIGURATIONS

PALLETS88" x 108"/125"SIDE BY SIDE

PALLETS96" x 125"

SIDE BY SIDE

88"/96"

88" x 125"

79"

96"

62"

96" AYYSAA

125"

AMJ AYY AYY AYY AYY

F_AC_020603_1_0010101_01_01

Main and Lower Deck Cross-sectionsFIGURE-2-6-3-991-001-A01

2-6-3Page 2

Apr 01/13


2-7-0 Door Clearances

**ON A/C A330-200 A330-200F A330-300

Door Clearances

1. This section gives door identification and location.

2-7-0Page 1

Apr 01/13


**ON A/C A330-200

FWDPASSENGER/CREW

DOOR (1L)

MIDPASSENGER/CREW

DOOR (2L)

EMERGENCY EXITDOOR (3L)

AFTPASSENGER/CREW

DOOR (4L)

BULK CARGOCOMPARTMENT

DOOR AFT CARGO

COMPARTMENTDOOR

AFTPASSENGER/CREW

DOOR (4R)

EMERGENCY EXITDOOR (3R)

FWDPASSENGER/CREW

DOOR (1R)MID

PASSENGER/CREWDOOR (2R)

FWD CARGOCOMPARTMENT

DOOR

F_AC_020700_1_0060101_01_00

Door Identification and locationDoor Identification (Sheet 1 of 2)

FIGURE-2-7-0-991-006-A01

2-7-0Page 2

Apr 01/13


**ON A/C A330-200

45.63 m(149.7 ft)

32.77 m(107.51 ft)

14.56 m(47.77 ft)

5.85 m(19.19 ft)

42.01 m(137.83 ft)

9.53 m(31.27 ft)

38.98 m(127.89 ft)

F_AC_020700_1_0060102_01_00

Door Identification and locationDoor Location (Sheet 2 of 2)FIGURE-2-7-0-991-006-A01

2-7-0Page 3

Apr 01/13


**ON A/C A330-300

FWDPASSENGER/CREW

DOOR (1L)

MIDPASSENGER/CREW

DOOR (2L)

EMERGENCY EXITDOOR (3L)

AFTPASSENGER/CREW

DOOR (4L)


DOOR AFT CARGO

COMPARTMENTDOOR

AFTPASSENGER/CREW

DOOR (4R)

EMERGENCY EXITDOOR (3R)

FWDPASSENGER/CREW

DOOR (1R)MID

PASSENGER/CREWDOOR (2R)


DOOR

F_AC_020700_1_0060201_01_00

Door Identification and LocationDoor Identification (Sheet 1 of 2)

FIGURE-2-7-0-991-006-B01

2-7-0Page 4

Apr 01/13


**ON A/C A330-300

50.96 m(167.19 ft)

35.96 m(117.98 ft)

17.74 m(58.2 ft)

5.85 m(19.19 ft)

47.35 m(155.35 ft)

9.53 m(31.27 ft)

44.36 m(145.54 ft)

F_AC_020700_1_0060202_01_00

Door Identification and LocationDoor Location (Sheet 2 of 2)FIGURE-2-7-0-991-006-B01

2-7-0Page 5

Apr 01/13


**ON A/C A330-200F

FWD CREWDOOR (1L)


DOOR AFT CARGO

COMPARTMENTDOOR

FWD CREWDOOR (1R)


DOOR

MAIN DECKCARGO DOOR

F_AC_020700_1_0060301_01_00

Door Identification and LocationDoor Identification (Sheet 1 of 2)

FIGURE-2-7-0-991-006-C01

2-7-0Page 6

Apr 01/13


**ON A/C A330-200F

5.85 m(19.19 ft)

42.01 m(137.83 ft)

9.53 m(31.27 ft)

39.03 m(128.05 ft)

9.92 m(32.55 ft)

F_AC_020700_1_0060302_01_00

Door Identification and LocationDoor Location (Sheet 2 of 2)FIGURE-2-7-0-991-006-C01

2-7-0Page 7

Apr 01/13


2-7-1 Forward Passenger / Crew Doors

**ON A/C A330-200 A330-200F A330-300

Forward Passenger / Crew Door

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

2-7-1Page 1

Apr 01/13


**ON A/C A330-200 A330-300

CRITICALCLEARANCELIMIT

CL

CL

CL

2.43 m(7 ft 11 in)

0.64 m(2 ft 1 in)

1.07 m(3 ft 6 in)

0.75 m(2 ft 5 in)

5.85 m(19 ft 2 in) 3.00 m

(9 ft 10 in)

1.93 m(6 ft 3 in)

SEECHAPTER

2−3

(10 ft 9 in)3.3 m

G_AC_020701_0_F00AAM0_05_00

0.045 m

(1.77 in)

F_AC_020701_1_0010101_01_00

Forward Passenger / Crew DoorsFIGURE-2-7-1-991-001-A01

2-7-1Page 2

Apr 01/13


**ON A/C A330-200F

CRITICALCLEARANCELIMIT

CL

CL

CL

2.43 m(7 ft 11 in)

0.64 m(2 ft 1 in)

1.07 m(3 ft 6 in)

0.75 m(2 ft 5 in)

5.85 m(19 ft 2 in) 3.00 m

(9 ft 10 in)

1.93 m(6 ft 3 in)

SEECHAPTER

2−3

(10 ft 9 in)3.3 m

0.045 m

(1.77 in)

F_AC_020701_1_0020101_01_00

Forward Passenger / Crew DoorsFIGURE-2-7-1-991-002-A01

2-7-1Page 3

Apr 01/13


2-7-2 Mid Passenger / Crew Doors

**ON A/C A330-200 A330-300

Mid Passenger / Crew Door

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

2-7-2Page 1

Apr 01/13


**ON A/C A330-200 A330-300

(TOP OF FLOOR)

CL

CL

CL

(FROM NOSE)

0.75 m(2 ft 5 in)

1.07 m(3 ft 6 in)

2.43 m(7 ft 11 in)

A330−200: 14.561 m (47ft 9 in)

A330−300: 17.741 m (58 ft 2 in)

0.64 m(2 ft 1 in)

3.41 m(11 ft 2 in)

(6 ft 3 in)

SEECHAPTER

2−3

1.93 m

A

A

A AF_AC_020702_1_0010101_01_00

(1.77 in)0.045 m

Mid Passenger / Crew DoorFIGURE-2-7-2-991-001-A01

2-7-2Page 2

Apr 01/13


2-7-3 Emergency Exits

**ON A/C A330-200 A330-300

Emergency Exits

1. This section gives emergency exits doors clearances.

2-7-3Page 1

Apr 01/13


**ON A/C A330-200 A330-300

CL

(TOP OF FLOOR)

CL

CL

0.75 m(2 ft 5 in)

1.07 m(3 ft 6 in)

3.2 m(10 ft 5 in)

0.64 m(2 ft 1 in)

(FROM NOSE)A330−200: 32.767 m (107 ft 6 in)

A330−300: 35.961 m (117 ft 11 in)

1.66 m(5 ft 5 in)

2−3

SEECHAPTER

A A

A

A

F_AC_020703_1_0010101_01_00

2.43 m(7 ft 11 in)

0.03 m(1.18 in)

Emergency ExitsFIGURE-2-7-3-991-001-A01

2-7-3Page 2

Apr 01/13


2-7-4 Aft Passenger / Crew Doors

**ON A/C A330-200 A330-300

Aft Passenger / Crew Doors

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

2-7-4Page 1

Apr 01/13


**ON A/C A330-200 A330-300

CRITICALCLEARANCE

LIMIT

CL

CL CL

CL

2.43 m(8 ft)

1.07 m(3 ft 6 in)

0.75 m(2 ft 5 in)

3 m(9 ft 10 in)

1.99 m(6 ft 6 in)

0.64 m(2 ft 1 in)

A330−200: 45.628 m (149 ft 8 in)

A330−300: 50.956 m (167 ft 2 in)

(FROMNOSE)

SEECHAPTER

2−3

A A

A

A

F_AC_020704_1_0010101_01_00

0.045 m(1.8 in)

Aft Passenger / Crew DoorsFIGURE-2-7-4-991-001-A01

2-7-4Page 2

Apr 01/13


2-7-5 Forward Cargo Compartment Doors

**ON A/C A330-200 A330-300

Forward Cargo Compartment Doors

1. This section gives forward cargo compartment doors clearances for pax version.

2-7-5Page 1

Apr 01/13


**ON A/C A330-200 A330-300

(FROM NOSE)

CL

CL

CL

SEECHAPTER

2−3

CL

9.53 m(31 ft 3 in)

0.64 m(2 ft 1 in)

6.37 m(20 ft 10 in)

2.7 m(8 ft 10 in)

1.70 m(5 ft 6 in)

2.04 m(6 ft 8 in)

5.27 m(17 ft 3 in)

MID PASSENGER/CREW DOOR CREW DOORFORWARD PASSENGER/

A A

A

A

F_AC_020705_1_0010101_01_00

FORWARD CARGOCOMPARTMENT DOOR

Forward Cargo Compartment DoorsFIGURE-2-7-5-991-001-A01

2-7-5Page 2

Apr 01/13


**ON A/C A330-200F

Forward Cargo Compartment Doors

1. This section gives forward cargo compartment doors clearances for cargo version.

2-7-5Page 3

Apr 01/13


**ON A/C A330-200F

CL

CL

SEECHAPTER

2−3

CL

1.70 m(5 ft 6 in)

2.04 m(6 ft 8 in)

5.27 m(17 ft 3 in)

FORWARD CARGOCOMPARTMENT DOOR

9.53 m (31 ft 3 in) (FROM NOSE)

CREW DOORFORWARD

A A

2.7 m(8 ft 10 in)

A

A

FWD

F_AC_020705_1_0020101_01_01


2-7-5Page 4

Apr 01/13


**ON A/C A330-200F

PW= 8.45 m (27 ft 8 in)RR= 8.13 m (26 ft 8 in)

9.92m(32 ft 6 in)

2.44 m(8 ft 1 in)

2.58 m(8 ft 5.5 in)

3.36 m(11 ft)

4.6 m(15 ft 1 in)

PW= 18.253 m (59 ft 10 in)RR= 18.081 m (59 ft 3 in)

(FROM NOSE)

(FROM NOSE)

CL

SEECHAPTER

2−3

3.69 m(12 ft 1.2 in)

4.07 m(13 ft 1 in)

A

A

A AF_AC_020705_1_0030101_01_01


2-7-5Page 5

Apr 01/13


2-7-6 Aft Cargo Compartment Doors

**ON A/C A330-200 A330-200F A330-300

Aft Cargo Compartment Doors

1. This section gives Aft cargo compartment doors clearances.

2-7-6Page 1

Apr 01/13


**ON A/C A330-200

SEECHAPTER

2−3

1.68 m(5 ft 6 in)

2.03 m(6 ft 7 in)

5.19 m(17 ft)

(FROM NOSE)A330−200: 38.978 m(127 ft 10 in)

AFT CARGO COMPARTMENT DOOR

(9 ft 1in)2.78 m

AFT PASSENGER/CREW DOOR

CL

CL

CL

CL

A A

A

A

BULK CARGOCOMPARTMENT DOOR

F_AC_020706_1_0010101_01_01

Aft Cargo Compartment DoorsFIGURE-2-7-6-991-001-A01

2-7-6Page 2

Apr 01/13


**ON A/C A330-300

SEECHAPTER

2−3

1.68 m(5 ft 6 in)

2.03 m(6 ft 7 in)

5.19 m(17 ft)

(FROM NOSE)A330−300: 44.36 m(145 ft 6 in)


(9 ft 1in)2.78 m

AFT PASSENGER/CREW DOOR

CL

CL

CL

CL

A A

A

A


F_AC_020706_1_0030101_01_00


2-7-6Page 3

Apr 01/13


**ON A/C A330-200F

SEECHAPTER

2−3

1.68 m(5 ft 6 in)

2.03 m(6 ft 7 in)

5.19 m(17 ft)

(FROM NOSE)

A330−200F: 38.978 m (127 ft 10 in)


(9 ft 1in)2.78 m

CL

CL

CL

CL

A A

A

A


F_AC_020706_1_0020101_01_01


2-7-6Page 4

Apr 01/13


2-7-7 Bulk Cargo Compartment Doors

**ON A/C A330-200 A330-300

Bulk Cargo Compartment Doors

1. This section gives the bulk cargo compartment doors clearances for pax version.

2-7-7Page 1

Apr 01/13


**ON A/C A330-200 A330-300

CL

CL

CL

SEECHAPTER

2−3

CL

1.11 m(3 ft 7 in)

0.95 m(3 ft 1 in)

1.41 m(4 ft 7 in)

1.07 m(3 ft 6 in)

(FROM NOSE)A330−200: 42.014 m (137 ft 10 in)

A330−300: 47.342 m (155 ft 3 in)

AFT PASSENGER/CREW DOOR(REF)


A

A


A A

F_AC_020707_1_0010101_01_00

Bulk Cargo Compartment DoorsFIGURE-2-7-7-991-001-A01

2-7-7Page 2

Apr 01/13


**ON A/C A330-200F

Bulk Cargo Compartment Doors

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

2-7-7Page 3

Apr 01/13


**ON A/C A330-200F

(FROM NOSE)A330−200F: 42.014 m (137 ft 10 in)

CL

SEECHAPTER

2−3

0.95 m(3 ft 1 in)

1.11 m(3 ft 7 in)

FWD

A

A


AFT CARGOCOMPARTMENT DOOR

CL

CL

1.41 m(4 ft 7 in)

1.07 m(3 ft 6 in)

A A

F_AC_020707_1_0020101_01_00

Bulk Cargo Compartment DoorsFIGURE-2-7-7-991-002-A01

2-7-7Page 4

Apr 01/13


2-7-8 Main and Center Landing Gear Doors

**ON A/C A330-200 A330-300

Main Landing Gear Doors

1. This section gives the main landing gear doors clearances for pax version.

2-7-8Page 1

Apr 01/13


**ON A/C A330-200 A330-300

A

A

GROUND LINE

A/C

C L

81°

3.96 m(13 ft)

1.56 m(5 ft 1 in)

Z−2 m (6 ft 6 in)

3.03 m(9 ft 11in)

2.34 m(7 ft 8 in)

1.1 m(3 ft 7 in)

2.7 m(8 ft 10 in)

A330−200: 26.786 m (87 ft 10 in)

A330−300: 29.45 m (96 ft 7 in)

0.23 m(9 in)

F_AC_020708_1_0010101_01_00

Main Landing Gear DoorsFIGURE-2-7-8-991-001-A01

2-7-8Page 2

Apr 01/13


**ON A/C A330-200F

Main Landing Gear Doors

1. This section gives the main landing gear doors clearances for cargo version.

2-7-8Page 3

Apr 01/13


**ON A/C A330-200F

A330−200F: 26.786 m (87 ft10 in) 3.96 m(13 ft)

GROUND LINE

A/C

C L

81°

1.56 m(5 ft 1 in)

Z−2 m (6 ft 6 in)

3.03 m(9 ft 11in)

2.34 m(7 ft 8 in)

1.1 m(3 ft 7 in)

2.7 m(8 ft 10 in)

0.23 m(9 in)

A

A

F_AC_020708_1_0020101_01_00

Main Landing Gear DoorsFIGURE-2-7-8-991-002-A01

2-7-8Page 4

Apr 01/13


2-7-9 Radome

**ON A/C A330-200 A330-200F A330-300

Radome

1. This section gives the radome clearances.

2-7-9Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

67°

CL

STA 7662.5FR1

1.32

5 m

(4 ft

4 in

)1.

25 m

(4 ft

1 in

)

1.65 m(5 ft 4 in)

F_AC_020709_1_0010101_01_00

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

2-7-9Page 2

Apr 01/13


2-7-10 APU and Nose Landing Gear Doors

**ON A/C A330-200 A330-300

APU and Nose Landing Gear Doors

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

2-7-10Page 1

Apr 01/13


**ON A/C A330-200 A330-300

FUSELAGE DATUM LINE

FR95

FR101

5.83

m(1

9 ft

1 in

)

6.55

m(2

1 ft

5 in

)

1.82

m(5

ft 1

1 in

)

1.49 m(4 ft 10 in)

F_AC_020710_1_0010101_01_00

APU and Nose Landing Gear DoorsFIGURE-2-7-10-991-001-A01

2-7-10Page 2

Apr 01/13


**ON A/C A330-200F

APU and Nose Landing Gear Doors

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

2-7-10Page 3

Apr 01/13


**ON A/C A330-200F

FUSELAGE DATUM LINE

FR95

FR101

5.83

m(1

9 ft

1 in

)

6.55

m(2

1 ft

5 in

)

1.38 m(4 ft 6 in)

2.00

m(6

ft 6

in)

FWD

F_AC_020710_1_0020101_01_00

APU and Nose Landing Gear DoorsFIGURE-2-7-10-991-002-A01

2-7-10Page 4

Apr 01/13


2-8-0 Escape Slides

**ON A/C A330-200 A330-200F A330-300

Escape Slides

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

**ON A/C A330-200 A330-300

2. LocationEscape facilities are provided at the following locations:

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

**ON A/C A330-200F

3. LocationEscape facilities are provided at the following locations:

A. Door Escape Facility- One dual lane escape slide-raft at each FWD cabin door (total two).The slides are installed in a container in the lower part of the door.

2-8-0Page 1

Apr 01/13


**ON A/C A330-200

FWD CABIN ESCAPE SLIDE

MID CABIN ESCAPE SLIDE

EMERGENCY EXIT

AFT CABIN

ESCAPE SLIDE

ESCAPE SLIDE

F_AC_020800_1_0010101_01_00

Escape SlidesLocation (Sheet 1 of 2)

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

2-8-0Page 2

Apr 01/13


**ON A/C A330-200

GR

ID E

QU

ALS

1 m

(3.

28 ft

) IN

RE

ALI

TY

EM

ER

GE

NC

Y D

ES

CE

NT

DE

VIC

ET

HR

OU

GH

WIN

DO

W O

PE

NIN

G

0 −3

−6 −9

−12

−15 −21

−18

−24

−27

−30 −33

F_AC_020800_1_0010108_01_00

Escape SlidesDimensions (Sheet 2 of 2)FIGURE-2-8-0-991-001-A01

2-8-0Page 3

Apr 01/13


**ON A/C A330-200F

CABIN ESCAPE SLIDE

F_AC_020800_1_0010201_01_00


FIGURE-2-8-0-991-001-B01

2-8-0Page 4

Apr 01/13


**ON A/C A330-200F

GR

ID E

QU

ALS

1 m

(3.

28 ft

) IN

RE

ALI

TY

EM

ER

GE

NC

Y D

ES

CE

NT

DE

VIC

ET

HR

OU

GH

WIN

DO

W O

PE

NIN

G

0 −3

−6 −9

−12

−15 −21

−18

−24

−27

−30 −33

F_AC_020800_1_0010202_01_00

Escape SlidesDimensions (Sheet 2 of 2)FIGURE-2-8-0-991-001-B01

2-8-0Page 5

Apr 01/13


**ON A/C A330-300

EMERGENCY EXITESCAPE SLIDE

FWD CABIN ESCAPE SLIDE

MID CABIN ESCAPE SLIDE

AFT CABINESCAPE SLIDE

F_AC_020800_1_0010301_01_00


FIGURE-2-8-0-991-001-C01

2-8-0Page 6

Apr 01/13


**ON A/C A330-300

GR

ID E

QU

ALS

1 m

(3.

28 ft

) IN

RE

ALI

TY

EM

ER

GE

NC

Y D

ES

CE

NT

DE

VIC

ET

HR

OU

GH

WIN

DO

W O

PE

NIN

G

0 −3

−6 −9

−12

−15 −21

−18

−24

−27

−30 −33

F_AC_020800_1_0010304_01_00

Escape SlidesDimensions (Sheet 2 of 2)FIGURE-2-8-0-991-001-C01

2-8-0Page 7

Apr 01/13


2-9-0 Landing Gear

**ON A/C A330-200 A330-200F A330-300

Landing Gear Maintenance Pits

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

All dimensions shown are minimum dimensions with zero clearances.

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

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

landing gear.

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

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

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

2-9-0Page 1

Apr 01/13


**ON A/C A330-300

3.58

m(1

1.75

ft)

8.51

m(2

7.92

ft)

3.89

m(1

2.76

ft)

6.31

m(2

0.7

ft)

5.34

m(1

7.52

ft)

34.3

1 m

(112

.57

ft)

31.5

5 m

(103

.51

ft)

25.3

8 m

(83.

27 ft

)

3.65

m(1

1.98

ft)

FR

ON

T O

F N

OS

E R

AD

OM

E

FO

RW

AR

D J

AC

KIN

G P

OIN

T

WIN

G J

AC

KIN

G P

OIN

T

AIR

CR

AF

T C

EN

TE

R L

INE

NO

TE

:E

NV

ELO

PE

S S

HO

WN

WIT

H Z

ER

O C

LEA

RA

NC

E T

O O

UT

SID

E E

DG

E O

F T

IRE

S.

WIN

G J

AC

KIN

G P

OIN

T

F_AC_020900_1_0010101_01_00

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

FIGURE-2-9-0-991-001-A01

2-9-0Page 2

Apr 01/13


**ON A/C A330-300

3. ’C

’ RE

PR

ES

EN

TS

PO

SIT

ION

OF

HY

DR

AU

LIC

OR

ME

CH

AN

ICA

L E

LEV

AT

OR

WIT

H T

HE

MLG

SH

OC

K A

BS

OR

BE

R IN

TH

E D

EF

LAT

ED

AN

DC

OM

PR

ES

SE

D C

ON

DIT

ION

FO

R S

HO

CK

AB

SO

RB

ER

RE

MO

VA

L.

4. ’D

’ RE

PR

ES

EN

TS

PO

SIT

ION

OF

HY

DR

AU

LIC

OR

ME

CH

AN

ICA

L E

LEV

AT

OR

WIT

H T

HE

MLG

SH

OC

K A

BS

OR

BE

R IN

TH

E E

XT

EN

DE

D C

ON

DIT

ION

FO

R S

HO

CK

AB

SO

RB

ER

RE

MO

VA

L.

DIM

EN

SIO

NS

mm

ftft

6.53

m(2

1.42

ft)

1.53

5.02

0.2

0.6

60.

812.

66

mft

FU

SE

LAG

E H

OR

IZO

NT

AL

DA

TU

M

(103

.02

ft)31

.4 m

33.1

3 m

(108

.69

ft)

FR

ON

T O

F N

OS

E R

AD

OM

EAB

C

BC

D

mft

A

1.56

5.12

1. ’A

’ RE

PR

ES

EN

TS

PO

SIT

ION

OF

NLG

WH

EE

LA

BO

VE

ST

AT

IC G

RO

UN

D L

INE

WIT

H A

IRC

RA

FT

LEV

ELL

ED

AN

D J

AC

KE

D.

A P

IT IS

NO

T R

EQ

UIR

ED

FO

R T

HE

NLG

.

2. ’B

’ RE

PR

ES

EN

TS

PO

SIT

ION

OF

LO

WE

ST

MLG

MA

IN W

HE

EL

AB

OV

E S

TA

TIC

GR

OU

ND

LIN

EW

ITH

AIR

CR

AF

T J

AC

KE

D IN

TO

PO

SIT

ION

AB

OV

E H

YD

RA

ULI

C O

R M

EC

HA

NIC

AL

ELE

VA

TO

R,

FO

R R

ET

RA

CT

ION

/EX

TE

NS

ION

TE

ST

S.

6.67

m(2

1.88

ft)

NO

TE

:D

MA

IN L

AN

DIN

G G

EA

R

F_AC_020900_1_0010104_01_00


FIGURE-2-9-0-991-001-A01

2-9-0Page 3

Apr 01/13


**ON A/C A330-200 A330-200F

FR

ON

T O

F N

OS

E R

AD

OM

E

FO

RW

AR

D J

AC

KIN

G P

OIN

T

WIN

G J

AC

KIN

G P

OIN

T

AIR

CR

AF

T C

EN

TE

R L

INE

WIN

G J

AC

KIN

G P

OIN

T28

.35

m(9

3.01

ft)

3.58

m(1

1.75

ft)

8.51

m(2

7.92

ft)

3.89

m(1

2.76

ft)

6.31

m(2

0.7

ft)

5.34

m(1

7.52

ft)

31.1

2 m

(102

.1 ft

)22.1

8 m

(72.

77 ft

)

3.65

m(1

1.98

ft)

NO

TE

:E

NV

ELO

PE

S S

HO

WN

WIT

H Z

ER

O C

LEA

RA

NC

E T

O O

UT

SID

E E

DG

E O

F T

IRE

S.

F_AC_020900_1_0010301_01_00


FIGURE-2-9-0-991-001-C01

2-9-0Page 4

Apr 01/13


**ON A/C A330-200 A330-200F

3. ’C

’ RE

PR

ES

EN

TS

PO

SIT

ION

OF

HY

DR

AU

LIC

OR

ME

CH

AN

ICA

L E

LEV

AT

OR

WIT

H T

HE

MLG

SH

OC

K A

BS

OR

BE

R IN

TH

E D

EF

LAT

ED

AN

DC

OM

PR

ES

SE

D C

ON

DIT

ION

FO

R S

HO

CK

AB

SO

RB

ER

RE

MO

VA

L.

4. ’D

’ RE

PR

ES

EN

TS

PO

SIT

ION

OF

HY

DR

AU

LIC

OR

ME

CH

AN

ICA

L E

LEV

AT

OR

WIT

H T

HE

MLG

SH

OC

K A

BS

OR

BE

R IN

TH

E E

XT

EN

DE

D C

ON

DIT

ION

FO

R S

HO

CK

AB

SO

RB

ER

RE

MO

VA

L.

FU

SE

LAG

E H

OR

IZO

NT

AL

DA

TU

M

FR

ON

T O

F N

OS

E R

AD

OM

EAB

C

1. ’A

’ RE

PR

ES

EN

TS

PO

SIT

ION

OF

NLG

WH

EE

LA

BO

VE

ST

AT

IC G

RO

UN

D L

INE

WIT

H A

IRC

RA

FT

LEV

ELL

ED

AN

D J

AC

KE

D.

A P

IT IS

NO

T R

EQ

UIR

ED

FO

R T

HE

NLG

.

2. ’B

’ RE

PR

ES

EN

TS

PO

SIT

ION

OF

LO

WE

ST

MLG

MA

IN W

HE

EL

AB

OV

E S

TA

TIC

GR

OU

ND

LIN

EW

ITH

AIR

CR

AF

T J

AC

KE

D IN

TO

PO

SIT

ION

AB

OV

E H

YD

RA

ULI

C O

R M

EC

HA

NIC

AL

ELE

VA

TO

R,

FO

R R

ET

RA

CT

ION

/EX

TE

NS

ION

TE

ST

S.

6.67

m(2

1.88

ft)

NO

TE

:D

6.53

m(2

1.42

ft)

(92.

36 ft

)28

.15

m

29.3

4 m

(96.

26 ft

)

DIM

EN

SIO

NS

mm

ftft

1.53

5.02

0.2

0.6

60.

812.

66

mft

BC

D

mft

A

1.56

5.12

MA

IN L

AN

DIN

G G

EA

R

F_AC_020900_1_0010302_01_00


FIGURE-2-9-0-991-001-C01

2-9-0Page 5

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

Landing Gear

1. General

The aircraft has:- Two Main Landing Gears (MLG) with four wheel bogie assembly and related doors- A Nose Landing Gear (NLG) with twin wheel assembly and related doors.The Main Landing Gears are located under each wing and retract sideways towards the fuselagecenterline.The Nose Landing Gear retracts forward into a fuselage compartment below the cockpit.The retraction and extension of the landing gears and landing gear doors are operated hydraulicallyand mechanically. The control, sequence and indication are electrical.In abnormal operation, the landing gears can be extended by gravity.

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

2. Main Landing Gear and Doors

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

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

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

3. Nose Landing Gear and Doors

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

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

2-9-0Page 6

Apr 01/13


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

4. Nose Wheel Steering

Nose wheel steering system is a computer controlled electro-hydraulic system. The system uses theGreen main hydraulic power system to operate the hydraulic components.The steering is controlled by two hand wheel transmitters in the cockpit, which supply the primarysteering inputs to the BSCU (Brake and Steering Control Unit ).A steering disconnection box is installed on the NLG to disconnect the steering for towing.

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

5. Landing Gear Servicing Points

A. GeneralFluid filling and gas charging of the MLG and NLG shock absorbers are accomplished throughMS28889 standard valves.

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

6. Landing Gear Control

The landing gear and door operation is controlled electrically by one of the two Landing Gear Controland Interface Units (LGCIU). Control changes from one LGCIU to the other after each extensioncycle.In normal operation, the landing gears and doors are operated by the Green hydraulic system.In abnormal operation, the landing gears can be extended by the operation of electro-mechanical free-fall system. The related electrical switches in the cockpit disengages the doors and the landing gearuplocks. The landing gears then extend by free-fall and the downlock links of each landing gear (L/G)are locked in position by springs.

7. Braking

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

The braking system has four braking modes with autobrake and anti-skid systems:- Normal braking with anti-skid.- Alternate braking with anti-skid.- Alternate braking without anti-skid.- Parking brake with full brake pressure.

2-9-0Page 7

Apr 01/13


B. In-Flight Wheel BrakingBraking occurs automatically during the retraction of the landing gears. This stops the rotationof the MLG wheels before the landing gears go into their related bays.

8. Tire Pressure Indicating System (TPIS)

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

9. Built In Test Equipment (BITE)

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

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

2-9-0Page 8

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

MAIN DOOR

HINGED DOOR

FIXED FAIRING DOOR

A

B

C

D

F

E

DOWNLOCKACTUATOR

SHORTENINGMECHANISM

SIDE STAYASSEMBLY MLG LEG

ASSEMBLY

TORQUE LINKS

BOGIE PITCHTRIMMER

BOGIE BEAMASSEMBLY

SHOCK ABSORBER

ARTICULATING LINKS

RADIAL OR BIASPLY TIRES

A

(HYDRAULICALLYOPERATED)

FWD AXLE

AFT AXLE

BRAKE RODASSEMBLY

F_AC_020900_1_0070101_01_00

Main Landing GearGeneral (Sheet 1 of 3)

FIGURE-2-9-0-991-007-A01

2-9-0Page 9

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

C

WARNING FLAG

GROUND LOCK PIN

LOCK STAY

BLH SHOWN

RH SYMMETRICAL

QUICK RELEASE PIN

SAFETYCOLLAR

WARNING FLAG

WARNING FLAG

QUICK RELEASE PIN

DOOR ACTUATOR

F_AC_020900_1_0070102_01_00

Main Landing GearSafety Devices (Sheet 2 of 3)FIGURE-2-9-0-991-007-A01

2-9-0Page 10

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

SEAL CHANGEOVERVALVE

BLEED/INFLATIONVALVE

D

E

F

FWD

FILL VALVE

GROUND POINT

F_AC_020900_1_0070103_01_00

Main Landing GearServicing (Sheet 3 of 3)

FIGURE-2-9-0-991-007-A01

2-9-0Page 11

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

RETRACTION ACTUATOR

DOWNLOCKACTUATOR

MAIN FITTING

DOWNLOCK SPRINGS

TORQUE LINKS

RADIAL OR BIASPLY TIRES

TOWING BRACKET

SHOCK ABSORBER

AXLE

NWS ACTUATORS

LOWER DRAGSTAY(FOLDING STRUT)

UPPER DRAGSTAY(FOLDING STRUT)

EH

D

AFT DOOR(MECHANICALLY OPERATED)

FWD DOORS

A

(HYDRAULICALLY

AFT DOOR(MECHANICALLY OPERATED)

FIXED FAIRING

A

C

F

G

OPERATED)

B

B

F_AC_020900_1_0080101_01_00

Nose Landing GearGeneral (Sheet 1 of 4)

FIGURE-2-9-0-991-008-A01

2-9-0Page 12

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

DRAG STAYATTACHMENT

GROUNDLOCK PIN

LOCK SPRINGATTACHMENT

LOWERLOCK−LINK

UPPERLOCK−LINK

DOWN LOCKACTUATOR

ATTACHMENT

WARNING FLAG

C

BRH SHOWN

LH SYMMETRICAL

SAFETYCOLLAR

QUICK RELEASE PIN

WARNING FLAG

WARNING FLAG

QUICK RELEASE PIN

DOOR ACTUATOR

F_AC_020900_1_0080102_01_00

Nose Landing GearSafety Devices (Sheet 2 of 4)FIGURE-2-9-0-991-008-A01

2-9-0Page 13

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

SEAL CHANGEOVERVALVE

CHARGE VALVE

BLEED VALVE

E

D

INFLATION VALVE(FIRST STAGE)

FWD

F_AC_020900_1_0080103_01_00

Nose Landing GearServicing (Sheet 3 of 4)

FIGURE-2-9-0-991-008-A01

2-9-0Page 14

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

INFLATION VALVE(SECOND STAGE)

LANDING GEAR

GROUND POINT

FWD

F

TOWING LEVER

SAFETY PIN(TOWING POSITION)

WARNING FLAG

NORMAL POSITION(NOSE WHEEL STEERING

OPERATIONAL)

TOWING POSITION(NOSE WHEEL STEERING

DEACTIVATED)

G

H

F_AC_020900_1_0080104_01_00

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

FIGURE-2-9-0-991-008-A01

2-9-0Page 15

Apr 01/13


2-10-0 Exterior Lighting

**ON A/C A330-200 A330-200F A330-300

Exterior Lighting

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

EXTERIOR LIGHTINGITEM DESCRIPTION

1 RIGHT NAVIGATION LIGHT (GREEN)

2 LEFT NAVIGATION LIGHT (RED)

3 TAIL NAVIGATION LIGHT (WHITE)

4 UPPER ANTI-COLLISION LIGHT/BEACON(RED)

5 LOWER ANTI-COLLISION LIGHT/BEACON(RED)

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

WHITE)

10 TAIL STROBE LIGHT (HIGH INTENSITY,WHITE)

11 LANDING LIGHTS12 RUNWAY TURN-OFF LIGHTS13 TAXI LIGHTS14 TAKE-OFF LIGHTS15 CARGO COMPARTMENT FLOOD LIGHTS16 LANDING GEAR BAY/WELL LIGHTS (DOME)

17 (A330-200F only) CARGO COMPARTMENT FLOOD LIGHTS -MAIN DECK

2-10-0Page 1

Apr 01/13


**ON A/C A330-200

1 RH

2 LH

98 7

46

5

10

3

F_AC_021000_1_0010101_01_00

Exterior Lighting(Sheet 1 of 5)

FIGURE-2-10-0-991-001-A01

2-10-0Page 2

Apr 01/13


**ON A/C A330-200

14

13 12 11

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

F_AC_021000_1_0010102_01_00


FIGURE-2-10-0-991-001-A01

2-10-0Page 3

Apr 01/13


**ON A/C A330-200

21

7 7

1212

13

14

3

F_AC_021000_1_0010103_01_00


FIGURE-2-10-0-991-001-A01

2-10-0Page 4

Apr 01/13


**ON A/C A330-200

10

99

54

8

1111

8

F_AC_021000_1_0010104_01_00


FIGURE-2-10-0-991-001-A01

2-10-0Page 5

Apr 01/13


**ON A/C A330-200

EXAMPLE FOR LIGHT N° 15

CEILING LIGHT

SPOT LIGHT

GROUND

15 16 15 16

6

6

F_AC_021000_1_0010105_01_00


FIGURE-2-10-0-991-001-A01

2-10-0Page 6

Apr 01/13


**ON A/C A330-200F

1 RH

2 LH

6

10

3

5

78

4

9

F_AC_021000_1_0020101_01_00


FIGURE-2-10-0-991-002-A01

2-10-0Page 7

Apr 01/13


**ON A/C A330-200F

14

1113 12


F_AC_021000_1_0020102_01_00


FIGURE-2-10-0-991-002-A01

2-10-0Page 8

Apr 01/13


**ON A/C A330-200F

21

3

77

12 12

13

14

F_AC_021000_1_0020103_01_00


FIGURE-2-10-0-991-002-A01

2-10-0Page 9

Apr 01/13


**ON A/C A330-200F

99

88

1111

10

4 5

F_AC_021000_1_0020104_01_00


FIGURE-2-10-0-991-002-A01

2-10-0Page 10

Apr 01/13


**ON A/C A330-200F


CEILING LIGHT

SPOT LIGHT

GROUND

6

6

15 16 15 16

F_AC_021000_1_0020105_01_00


FIGURE-2-10-0-991-002-A01

2-10-0Page 11

Apr 01/13


**ON A/C A330-200F

HID LIGHT CEILING LIGHT


17

F_AC_021000_1_0020106_01_00


FIGURE-2-10-0-991-002-A01

2-10-0Page 12

Apr 01/13


**ON A/C A330-300

1 RH

LH

10

3

78

46

2

9

5

F_AC_021000_1_0030101_01_00


FIGURE-2-10-0-991-003-A01

2-10-0Page 13

Apr 01/13


**ON A/C A330-300

14

13 12 11


F_AC_021000_1_0030102_01_00


FIGURE-2-10-0-991-003-A01

2-10-0Page 14

Apr 01/13


**ON A/C A330-300

21

7

14

13

12

7

3

12

F_AC_021000_1_0030103_01_00


FIGURE-2-10-0-991-003-A01

2-10-0Page 15

Apr 01/13


**ON A/C A330-300

99

4 5

8

1111

8

10

F_AC_021000_1_0030104_01_00


FIGURE-2-10-0-991-003-A01

2-10-0Page 16

Apr 01/13


**ON A/C A330-300


CEILING LIGHT

SPOT LIGHT

GROUND

6

6

15 16 15 16

F_AC_021000_1_0030105_01_00


FIGURE-2-10-0-991-003-A01

2-10-0Page 17

Apr 01/13


2-11-0 Antennas and Probes Location

**ON A/C A330-200 A330-200F A330-300

Antennas and Probes Location

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

2-11-0Page 1

Apr 01/13


**ON A/C A330-200

NO

TE

:D

EP

EN

DIN

G O

N A

IRC

RA

FT

CO

NF

IGU

RA

TIO

N

VH

F(3

)E

LT

AO

A S

EN

SO

R(1

)

WE

AT

HE

R R

AD

AR

EM

ER

GE

NC

Y S

TA

TIC

PR

OB

E(3

)

LOC

RA

DIO

ALT

IME

TE

R(2

)

HF

RA

DIO

ALT

IME

TE

R(1

)G

LID

E

PIT

OT

PR

OB

E(1

)

PIT

OT

PR

OB

E(3

)

TA

T P

RO

BE

ICE

DE

TE

CT

OR

PR

OB

ET

CA

S B

OT

TO

M

DM

E(1

)

DM

E(2

)

MA

RK

ER

VH

F(4

)

GP

S(1

)

GP

S(2

)

TC

AS

TO

P

VH

F(1

)A

TC

(4) ST

AT

IC P

RO

BE

(2)

ST

AT

IC P

RO

BE

(1)

AT

C(1

)

F_AC_021100_1_0010101_01_00

Antennas and ProbesLocation (Sheet 1 of 2)

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

2-11-0Page 2

Apr 01/13


**ON A/C A330-200

AD

F(2

)A

DF

(1)

VO

R

TA

T P

RO

BE

ICE

DE

TE

CT

OR

PR

OB

E

ST

AT

IC P

RO

BE

(1)

ST

AT

IC P

RO

BE

(2)

EM

ER

GE

NC

Y S

TA

TIC

PR

OB

E(3

)A

OA

SE

NS

OR

(3)

ST

BY

AT

C(2

)

VH

F(2

)

AO

A S

EN

SO

R(2

)

PIT

OT

PR

OB

E(2

)

AT

C(3

)

SA

TC

OM

NO

TE

:D

EP

EN

DIN

G O

N A

IRC

RA

FT

CO

NF

IGU

RA

TIO

N

F_AC_021100_1_0010102_01_00


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

2-11-0Page 3

Apr 01/13


**ON A/C A330-200F

GP

S(1

)

GP

S(2

)

TC

AS

TO

P

VH

F(1

)

VH

F(3

)E

LT

AO

A S

EN

SO

R(1

)

AT

C(4

)

WE

AT

HE

R R

AD

AR

ST

AT

IC P

RO

BE

(2)

ST

AT

IC P

RO

BE

(1)

EM

ER

GE

NC

Y S

TA

TIC

PR

OB

E(3

)

AT

C(1

)

LOC

RA

DIO

ALT

IME

TE

R(2

)

RA

DIO

ALT

IME

TE

R(1

)

HF

GLI

DE

PIT

OT

PR

OB

E(1

)

PIT

OT

PR

OB

E(3

)

TA

T P

RO

BE

ICE

DE

TE

CT

OR

PR

OB

ET

CA

S B

OT

TO

M

DM

E(1

)

DM

E(2

)

MA

RK

ER

VH

F(4

)

NO

TE

:D

EP

EN

DIN

G O

N A

IRC

RA

FT

CO

NF

IGU

RA

TIO

N

F_AC_021100_1_0020101_01_00


FIGURE-2-11-0-991-002-A01

2-11-0Page 4

Apr 01/13


**ON A/C A330-200F

AD

F(2

)A

DF

(1)

TA

T P

RO

BE

ICE

DE

TE

CT

OR

PR

OB

E

ST

AT

IC P

RO

BE

(1)

ST

AT

IC P

RO

BE

(2)

EM

ER

GE

NC

Y S

TA

TIC

PR

OB

E(3

)A

OA

SE

NS

OR

(3)

ST

BY

AT

C(2

)

VH

F(2

)

VO

R

AO

A S

EN

SO

R(2

)

PIT

OT

PR

OB

E(2

)

AT

C(3

)

SA

TC

OM

NO

TE

:D

EP

EN

DIN

G O

N A

IRC

RA

FT

CO

NF

IGU

RA

TIO

N

F_AC_021100_1_0020102_01_00


FIGURE-2-11-0-991-002-A01

2-11-0Page 5

Apr 01/13


**ON A/C A330-300

GP

S(1

)

GP

S(2

)

TC

AS

TO

P

VH

F(1

)

GP

S(2

)

AT

C(4

)

VH

F(3

)E

LT

WE

AT

HE

R R

AD

AR

GP

S(1

)

LOC

HF

ST

AT

IC P

RO

BE

(2)

ST

AT

IC P

RO

BE

(1)

EM

ER

GE

NC

Y S

TA

TIC

PR

OB

E(3

)

AO

A S

EN

SO

R(1

)

MA

RK

ER

RA

DIO

ALT

IME

TE

R(2

)

RA

DIO

ALT

IME

TE

R(1

)

AT

C(1

)

PIT

OT

PR

OB

E(3

)

GLI

DE

PIT

OT

PR

OB

E(1

)

TA

T P

RO

BE

ICE

DE

TE

CT

OR

PR

OB

E

DM

E(1

)

DM

E(2

)

TC

AS

BO

TT

OM

VH

F(4

)

NO

TE

:D

EP

EN

DIN

G O

N A

IRC

RA

FT

CO

NF

IGU

RA

TIO

N

F_AC_021100_1_0030101_01_00


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

2-11-0Page 6

Apr 01/13


**ON A/C A330-300

AD

F(2

)A

DF

(1)

VO

R

VH

F(2

)

AO

A S

EN

SO

R(2

)

TA

T P

RO

BE

AT

C(3

)

PIT

OT

PR

OB

E(2

)S

AT

CO

M

EM

ER

GE

NC

Y S

TA

TIC

PR

OB

E(3

)

ST

AT

IC P

RO

BE

(2)

ST

AT

IC P

RO

BE

(1)

ICE

DE

TE

CT

OR

PR

OB

E

AT

C(2

)

AO

A S

EN

SO

R(3

) S

TB

Y

NO

TE

:D

EP

EN

DIN

G O

N A

IRC

RA

FT

CO

NF

IGU

RA

TIO

N

F_AC_021100_1_0030102_01_00


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

2-11-0Page 7

Apr 01/13


2-12-0 Engine and Nacelle

**ON A/C A330-200 A330-200F A330-300

Engine and Nacelle

1. Engine and Nacelle - PW 4000 Engine

A. EngineThe PW 4000 engine is a two spool, axial flow, high bypass ratio turbofan engine.The engine has four major sections as follows:- The compressor section- The combustion section- The turbine section- The accessory drive section.

The compressor section has a six-stage low pressure compressor, a fan case, an intermediatecase and an eleven-stage high pressure compressor. The 1st stage rotor in the low pressurecompressor flows air through both the fan nozzle and the low compressor rotor/statorassemblies to the core of the engine. The high pressure compressor is used to increase thepressure of the primary airflow from the low compressor and send it to the diffuser.The engine combustion section comprises the diffuser case and a combustion chamber installedin the case. The chamber forms the enclosure where fuel is mixed with air and burned to addenergy to the primary gaspath.The turbine section comprises the rear compressor drive turbine, the front compressor driveturbine and the Turbine Exhaust Case (TEC). The rear compressor drive turbine is the two-stage High Pressure Turbine (HPT) and the front compressor drive turbine is the five-stage LowPressure Turbine (LPT). The HPT case assembly is air-cooled as part of the Turbine CaseCooling (TCC) system. The LPT rotor and stator assembly includes the front compressordriveshaft, the LPT case and the LPT spool case. The LPT case is externally cooled by turbinecase cooling tubes.The accessory drive section comprises the main gearbox and angle gearbox. The high pressurerotor is used to supply the main gearbox with power to drive the engine and aircraft-suppliedaccessories. Power comes from the towershaft in the intermediate case which is geared to thefront of the high pressure rotor. The towershaft drives the angle gearbox bevel gear set whichtransmits power through the horizontal driveshaft assembly to the main gearbox group.

B. NacelleThe nacelle is the aerodynamic structure around the basic engine. The nacelle provides asmooth airflow both around and into the engine to decrease drag and give better engineperformance and prevents damage to the external surface of the engine and its accessories. Thenacelle consists of the following major components:

2-12-0Page 1

Apr 01/13


(1) Air Intake CowlThe air intake cowl is an interchangeable aerodynamic fairing assembly that permitssmooth airflow to the engine fan and core sections during ground and flight operation. Theair intake cowl is attached with bolts to the engine fan case.

(2) Fan CowlsFan cowls comprise a forward (fixed) fan cowl panel assembly and an aft fan cowl doorassembly. The fan cowl panels and doors protect the engine and its components, andoptimize the aerodynamic characteristics of the nacelle.

(3) Thrust ReverserThe thrust reverser system is a component of the aircraft engine nacelle and is used tocancel the forward thrust and to give aerodynamic braking of the aircraft. The principle ofthe thrust reverser is to procedure forward flow of the fan exhaust by a hydraulically-actuated mechanical system. The system is designed to be used on the ground only.

(4) Exhaust SystemThe turbine exhaust system has an exhaust nozzle and an exhaust plug. Both systemcomponents are acoustically treated and made to resist severe ambient conditions. Theexhaust nozzle forms the outer contour of the engine primary exhaust annulus and theinner flow path of the fan airstream. The exhaust plug forms the inner contour of theengine primary exhaust annulus. The exhaust nozzle and exhaust plug are line replaceableunits.

2. Engine and Nacelle - TRENT 700 Engine

A. EngineThe RB211-TRENT 700 engine is a high bypass ratio, triple spool turbofan.The principal modules of the engine are:- The Low Pressure Compressor (LPC) rotor- The Intermediate Pressure (IP) compressor- The intermediate case- The HP system (this includes the High Pressure Compressor (HPC), the combustion system

and the High Pressure Turbine (HPT))- The Intermediate Pressure Turbine (IPT)- The external gearbox- The LPC case- The Low Pressure Turbine (LPT).

2-12-0Page 2

Apr 01/13


The compressor system has three axial flow compressors in a triple spool configuration. Thecompressors are turned independently by their related turbines, each at its most satisfactoryspeed. The LP system has a single-stage compressor installed at the front of the engine. A shaftconnects the compressor to a four-stage turbine at the rear of the gas generator. The gasgenerator also includes an eight-stage IP compressor, a six-stage HPC and a combustion system.Each of the compressors in the gas generator is connected to, and turned by, a different single-stage turbine. Between the HPC and the HPT is the annular combustion system which burns amixture of fuel and air to supply energy as heat. Behind the LPT there is a common nozzleassembly which mixes the cold air and hot gas exhaust flows. The external gearbox module isinstalled below the rear case of the fan case. It has a gear train that decreases and increases thespeed to meet the specified drive requirements of each accessory.

B. NacelleThe nacelle gives the engine an aerodynamic shape. Each engine is housed in a nacellesuspended from a pylon attached below the wing. The nacelle consists of the following majorcomponents:

(1) Air Intake CowlThe air intake cowl is attached to the forward flange of the front LPC case. Its function isto supply inlet air in a satisfactory condition for the engine compressors.

(2) Fan Cowl DoorsThe fan cowl doors hang on the aircraft wing pylon and are closed around the LPC cases.They can be opened during ground maintenance to give access to the components installedon the cases and to let the thrust reverser cowl doors be opened.

(3) Thrust ReverserThe thrust reverser is a component of the aircraft engine nacelle. The thrust reverser is atwin thrust reverser cowl door (’C’ duct) construction providing a fan duct inner wallfairing for the core engine between the top and bottom bifurcation walls. The thrustreverser incorporates hydraulically-powered actuators to operate four pivoting doors whichredirect the fan air flow in reverse thrust. Hydraulic power is provided from the aircrafthydraulic system to position the doors in a ”stowed” position for forward thrust and”deployed” position for reverse thrust.

(4) Common Nozzle Assembly (CNA)The CNA is attached to the aft flange of the exhaust case. The function of the CNA is tomix the core engine exhaust with the LPC outlet air.

**ON A/C A330-200 A330-300

3. Engine and Nacelle - GE CF6--80E1 Engine

A. EngineThe CF6-80E1 engine is a high bypass ratio, dual-rotor, axial-flow turbofan engine.The major modules of the engine are:- The fan module- The core module

2-12-0Page 3

Apr 01/13


- The High Pressure Turbine (HPT)- The Low Pressure Turbine (LPT)- The accessory drive modules.

The fan module supplies approximately 80 percent of the total engine thrust throughsecondary air flow acceleration. The fan module also boosts primary air flow to the highpressure compressor. The fan rotor and booster assembly is part of the fan module. Air,taken in through the fan section, passes through successive stages of compressor rotorblades and compressor stator vanes, being compressed as it passes from stage to stage. Theinlet guide vanes and the first five-stages of the stator are variable, and change their angularposition as a function of the compressor inlet temperature and corrected engine speed. Thecombustion of fuel takes place in the combustor installed in the compressor rear frame. Thetwo main modules of the turbine are the HPT and the LPT. The function of the HPT is todrive the high pressure compressor by converting the combustor exhaust gas flow intomechanical force. The LPT subsequently also converts this flow into force to drive the fanand booster assemblies. The HPT rotor is a two-stage air-cooled turbine. The LPT rotordrives the fan and booster rotors through the LPT rotor shaft by extracting energy from thecombustion gases leaving the HPT. Power for both engine and aircraft accessories isextracted through a system of gearboxes and shafts. The accessory gearbox assembly ismounted on the compressor casing. The gearbox receives torque from the horizontal driveshaft and distributes the torque through spur gears to drive the gearbox-mountedaccessories.

B. NacelleThe nacelle provides protection for the engine and the engine accessories, and aerodynamicairflow around the engine during operation. Each engine is mounted in a nacelle suspended froma pylon attached to the wing lower surface. The nacelle consists of the following majorcomponents:

(1) Air Intake Cowl AssemblyThe air intake cowl structure is an interchangeable aerodynamically-faired assembly whichsupplies the inlet airflow to the fan and core sections of the engine. It is installed on theforward face of the engine fan case.

(2) Fan Cowl DoorsThe fan cowl door assemblies are engine-to-engine interchangeable units enclosing theengine fan case between the air intake cowl and thrust reverser cowl doors. Each assemblyis supported by three hinges at the pylon and latched along the bottom splitline with threetension hook latches.

(3) Thrust ReverserThe thrust reverser is a bifurcated assembly of two halves forming the fan exhaust ductand nozzle, enclosing the engine between the fan frame and the core cowling, andcontaining the mechanism for reversing the fan exhaust flow during aircraft landing.

2-12-0Page 4

Apr 01/13


(4) Core Cowl DoorsThe core cowl door assemblies are interchangeable units which enclose the core enginebetween the thrust reverser cowl doors and the exhaust nozzle. Each assembly is hingedfrom the pylon in three locations and latched along the bottom splitline with three tensionhook latches.

(5) Exhaust NozzleThe exhaust nozzle, through which all exhaust gases are expelled, is part of theaerodynamically-structured nacelle. The exhaust nozzle provides a fixed area annulus forexhausting the core engine gas stream flow and provides a continuation of the aerodynamiccowling from the core cowl interface.

2-12-0Page 5

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

A

TURBINEEXHAUST

CASE

TURBINESECTION

COMBUSTIONSECTION

LOW PRESSURECOMPRESSOR

HIGH PRESSURECOMPRESSOR

COMPRESSORSECTION

TURBINE LOW PRESSURE

HIGHPRESSURE

TURBINE

SECTIONACCESSORY DRIVE

4.14 m(13.58 ft)

2.72 m(8.92 ft)

NOTE:APPROXIMATE DIMENSIONS.

0.83 m(2.72 ft)

2.26 m(7.41 ft)

2.54 m(8.33 ft)

4.29 m(14.07 ft)

A

1.98 m(6.5 ft)

FWD

F_AC_021200_1_0010101_01_00

Engine and NacelleEngine Dimensions - PW 4000FIGURE-2-12-0-991-001-A01

2-12-0Page 6

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

W

U

V

U = VW = U + V

A−A

B−B

C−C

D−D

E−E

F−F

W U V NAC STA

(10.24 ft)3.12 m

(5.12 ft)1.56 m

(5.12 ft)1.56 m

(2.92 ft)0.89 m

(5.87 ft)1.79 m

(5.18 ft)1.58 m

(5.18 ft)1.58 m

(10.37 ft)3.16 m

(10.04 ft)3.06 m

(5.02 ft)1.53 m

(5.02 ft)1.53 m

(8.6 ft)2.62 m

(15.16 ft) *4.62 m

(4.23 ft)1.29 m

(4.23 ft)1.29 m

(8.46 ft)2.58 m

(4.66 ft)1.42 m

(2.33 ft)0.71 m

(2.33 ft)0.71 m

(17.16 ft)5.23 m

(3.28 ft)1 m

(1.64 ft)0.5 m

(1.64 ft)0.5 m

(19.91 ft)6.07 m

*

(20.24 ft)6.17 m(2.92 ft)

0.89 m

INTAKECOWL

(3.25 ft)0.99 m

FAN COWL

(5.68 ft)1.73 m

THRUST REVERSER

(8.53 ft)2.6 m

EXHAUST

(2.76 ft)0.84 m

4°

STOWED POSITION

F

FE

E

D

DC

CB

B

A

A

NOZZLE


DISTANCEFROM NOSE

A330−200/A330−200FA330−300

A (70.37 ft)21.45 m

(59.88 ft)18.25 m

A

(7.81 ft)2.38 m

F_AC_021200_1_0020101_01_00

Engine and NacelleNacelle Dimensions - PW 4000FIGURE-2-12-0-991-002-A01

2-12-0Page 7

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

GROUND

CLOSED

WL 100

(5.87 ft)1.79 m

(2.36 ft)0.72 m

53.8°

(19.32 ft)5.89 m


WL 100

(10.33 ft)3.15 m

F_AC_021200_1_0030101_01_00

Engine and NacelleFan Cowls - PW 4000

FIGURE-2-12-0-991-003-A01

2-12-0Page 8

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

GROUND

48°

(17.68 ft)5.39 m

1.55 m(5.09 ft)

3.15 m(10.33 ft)

CLOSED

WL 100

WL 100

CAUTION:DO NOT ACTUATE SLATS WITH THRUST REVERSERCOWLS AT 48° OPEN POSITION.

NOTE:

VIEW ON REAR OFENGINE

APPROXIMATE DIMENSIONS.

0.72 m(2.36 ft)

F_AC_021200_1_0040101_01_00

Engine and NacelleThrust Reverser Cowls - PW 4000

FIGURE-2-12-0-991-004-A01

2-12-0Page 9

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

3.91 m(12.83 ft)

SECTIONCOMBUSTION

EXHAUST

IP TURBINE

0.81 m(2.66 ft)

NOZZLETURBINE EXHAUST

LP TURBINEHP TURBINE

HP COMPRESSORIP COMPRESSOR

1.4 m(4.59 ft)

4.17 m(13.68 ft)

SECTIONACCESSORY DRIVE

A

2.56 m(8.4 ft)

2.79 m(9.15 ft)

0.84 m(2.76 ft)

0.76 m(2.49 ft)

B

LP COMPRESSOR

CONE

1.55 m(5.09 ft)

B

0.76 m(2.49 ft)


A

FWD

1.22 m(4.0 ft)

0.64 m(2.1 ft)

F_AC_021200_1_0050101_01_00

Engine and NacelleEngine Dimensions - TRENT 700

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

2-12-0Page 10

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

NOSECOWL

THRUSTREVERSER

BL 100BL 100 BL 100

WL100

WL100

(10.01 ft)3.05 m

(10.10 ft)3.08 m

(8.17 ft)2.49 m

(5.68 ft)(8.30 ft)2.53 m

(5.58 ft)1.7 m

(4.49 ft)1.37 m

(24.02 ft)7.32 m

DISTANCEFROM NOSE A330−300 A330−200/

−200F

(69.82 ft)21.28 m

(59.32 ft)18.08 m

1.73 m


A

A

A

B

B

C

C

A A B B C C

(6.2 ft)1.89 m

(7.41 ft)2.26 m

COMMONNOZZLE

ASSEMBLYFAN COWL

(10.5 ft)3.2 m

A

F_AC_021200_1_0060101_01_00

Engine and NacelleNacelle Dimensions - TRENT 700

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

2-12-0Page 11

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

WL 100

GROUND

FAN COWLOPEN 55°

(19.16 ft)5.84 m

(2.26 ft)0.69 m

(9.61 ft)2.93 m

1.99 m(6.53 ft)

CLOSED

WL 100

(10.1 ft)3.08 m


F_AC_021200_1_0070101_01_00

Engine and NacelleFan Cowls - TRENT 700

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

2-12-0Page 12

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

WL 100

GROUND

THRUSTREVERSEROPEN 43°

CLOSED

WL 100


(10.10 ft)3.08 m

(2.26 ft)0.69 m

1.48 m(4.86 ft) 1.28 m

(4.2 ft)

1.91 m(6.27 ft)

(7.19 ft)2.19 m

(17.09 ft)5.21 m


F_AC_021200_1_0080101_01_00

Engine and NacelleThrust Reverser Cowls - TRENT 700

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

2-12-0Page 13

Apr 01/13


**ON A/C A330-200 A330-300

LP

ACCESSORYDRIVE SECTION

HP TURBINE

LP COMPRESSOR CORE MODULE

TURBINE

TURBINE

REAR FRAME

HP COMPRESSOR COMBUSTION

SECTION

A

A

FWD

F_AC_021200_1_0090101_01_00

Engine and NacelleEngine Dimensions - GE CF6-80E1

FIGURE-2-12-0-991-009-A01

2-12-0Page 14

Apr 01/13


**ON A/C A330-200 A330-300

4°

W

U

V

INLETREVERSER

(26.08 ft)7.95 m

(5.02 ft)1.53 m

(5.05 ft)1.54 m

(5.54 ft)1.69 m

(3.54 ft)1.08 m

(5.48 ft)1.67 m

(1.44 ft)0.44 m

(4.76 ft)1.45 m

THRUST

NOZZLE

A

A

C

C

D

D

NOTE:APPROXIMATE DIMENSIONS

A−A

B−B

C−C

D−D

W U V NAC STA

(10.1 ft)3.08 m

(4.95 ft)1.51 m

(5.22 ft)1.59 m

(11.45 ft)3.49 m

(16.5 ft)5.03 m

(4.63 ft)1.41 m

(4.63 ft)1.41 m

(9.25 ft)2.82 m

(8.17 ft)2.49 m

(4.1 ft)1.25 m

(4.1 ft)1.25 m

(21 ft)6.4 m

(27.03 ft)8.24 m

(2.1 ft)0.64 m

(2.1 ft)0.64 m

(4.2 ft)1.28 m

DISTANCE FROMTHE NOSE A330−200A330−300

A (69.36 ft)21.14 m

(58.86 ft)17.94 m

A

PLUGEXHAUST

EXHAUSTB

B

(8.53 ft)2.6 m

COWLFAN

COWLCORECOWL

F_AC_021200_1_0100101_01_00

Engine and NacelleNacelle Dimensions - GE CF6-80E1

FIGURE-2-12-0-991-010-A01

2-12-0Page 15

Apr 01/13


**ON A/C A330-200 A330-300

GROUND

CLOSED

WL 100

(2.53 ft)0.77 m

(12.47 ft)3.8 m

(16.24 ft)4.95 m

(17.19 ft)5.24 m

(10.10 ft)3.08 m

55°


(4.99 ft)1.52 m (5.91 ft)

1.8 m

WL 100

F_AC_021200_1_0110101_01_00

Engine and NacelleFan Cowls - GE CF6-80E1

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

2-12-0Page 16

Apr 01/13


**ON A/C A330-200 A330-300

50°

GROUND

CLOSED

WL 100

WL 100


(8.17 ft)2.49 m

(7.55 ft)2.3 m

1.72 m(5.64 ft)

2 m(6.56 ft)


F_AC_021200_1_0120101_01_00

Engine and NacelleThrust Reverser Cowls - GE CF6-80E1

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

2-12-0Page 17

Apr 01/13


2-12-1 Auxiliary Power Unit

**ON A/C A330-200 A330-200F A330-300

Auxiliary Power Unit

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

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

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

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

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

The power section has a two-stage centrifugal compressor, a reverse-flow annular combustionchamber and a three-stage axial turbine. The power section directly operates the one-stagecentrifugal load-compressor which supplies the bleed-air to the pneumatic system. The inlet guidevanes as part of the load compressor, control the airflow.The power section also operates the gearbox which is attached to the load compressor. The followingLRU’s are mounted on the gearbox :- the APU generator,- the starter motor,- the oil pump,- the Fuel Control Unit (FCU),- the cooling air fan.The APU has a gearbox-driven oil-cooled AC generator.

2-12-1Page 1

Apr 01/13


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

3. Control circuitThe Electronic Control Box (ECB), which controls the Fuel Control Unit (FCU) and the Inlet GuideVanes (IGV), keeps the APU at a constant speed. The control circuit is used to start the APU, toshut it down, to control it and to prevent internal failure.

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

2-12-1Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

FR106A

FR103

FR101

FR95

FR94

FR92

FR91 317AL

315AL

313AL

Z310

A B

A

316AR

F_AC_021201_1_0020101_01_00

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

2-12-1Page 3

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

FIRE EXTINGUISHERBOTTLE

AIR INTAKE DUCT

APU

FIRE WALL

BLEED AIR LINE

OIL COOLER OUTLET

EXHAUST MUFFLER

FIXED DIVERTER

GUTTER

FR90

FR92

FR95

FR106A

FIRE WALL

FR101

B

AIR INTAKE

FORWARD

REAR

F_AC_021201_1_0020102_01_00

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

2-12-1Page 4

Apr 01/13


2-13-0 Levelling, symmetry and Alignment

**ON A/C A330-200 A330-200F A330-300

Leveling, Symmetry and Alignment

**ON A/C A330-200 A330-300

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

**ON A/C A330-200F

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

**ON A/C A330-200 A330-200F A330-300

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

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

2-13-0Page 1

Apr 01/13


**ON A/C A330-200

RIB12

FR57 FR58

RIB12

13

2 RH

12

2 LH

FR38 FR39

F_AC_021300_1_0010101_01_00

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

2-13-0Page 2

Apr 01/13


**ON A/C A330-300

FR57.4 FR58

RIB12

RIB12

FR38 FR39

12

2 LH

2 RH

13

F_AC_021300_1_0020101_01_00


2-13-0Page 3

Apr 01/13


**ON A/C A330-200F

FR57 FR58RIB12

RIB12

FR38 FR39

132 LH

2 RH

12

F_AC_021300_1_0030101_01_00


2-13-0Page 4

Apr 01/13


2-14-0 Jacking for Maintenance

**ON A/C A330-200 A330-200F A330-300

Jacking for Maintenance

**ON A/C A330-200

1. Aircraft Jacking Points for Maintenance

A. General

(1) The A330-200 can be jacked:- At not more than 152 000 kg (335 103 lb)- Within the limits of the permissible wind speed when the aircraft is jacked outside a

closed environment.

B. Primary Jacking Points

(1) The aircraft is provided with three primary jacking points:- One located under the forward fuselage (after FR10A)- Two located under the wings (one under each wing), at the intersection of RIB10 and

the rear of the spar-datum.

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

C. Auxiliary Jacking Point (Safety Stay)

(1) When the aircraft is on jacks, a safety stay is placed under the fuselage at FR87 to preventtail tipping caused by accidental displacement of the aircraft center of gravity.

(2) The safety point must not be used for lifting the aircraft.

(3) One male spherical stay adapter (ground equipment) is used as an intermediary partbetween the aircraft safety point and the stay.

**ON A/C A330-300


A. General

(1) The A330-300 can be jacked:- At not more than 152 000 kg (335 103 lb)- Within the limits of the permissible wind speed when the aircraft is jacked outside a

closed environment.


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

2-14-0Page 1

Apr 01/13


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





(3) One male spherical stay adapter (ground equipment) is used as an intermediary partbetween the aircraft safety point and the stay.

**ON A/C A330-200F


A. General

(1) The A330-200F can be jacked:- At not more than 136 000 kg (299 829 lb)- Within the limits of the permissible wind speed when the aircraft is jacked outside a

closed environment.


(1) The aircraft is provided with three primary jacking points:- One located under the forward fuselage (at FR10A), covered by nose fairing panel

125AL.- Two located under the wings (one under each wing), at the intersection of RIB10 and

the rear of the spar-datum.





(3) One male spherical stay adapter (installed on the aircraft) is used as an intermediary partbetween the aircraft safety point and the stay.

2-14-0Page 2

Apr 01/13


**ON A/C A330-200 A330-300

4. Jacks and Safety Stay

A. Jack Design

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

(2) In fully retracted position (jack stroke at minimum), the height of the jack is such that thejack may be placed beneath the aircraft under the most adverse conditions, namely, tiresdeflated and shock absorbers depressurized, with sufficient clearance between the aircraftjacking point and the jack upper end.

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

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

**ON A/C A330-200F

5. Jacks and Safety Stay

A. Jack Design

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

(2) In fully retracted position (jack stroke at minimum), the height of the jack is such that thejack may be placed beneath the aircraft under the most adverse conditions, namely, tiresdeflated and shock absorbers depressurized, with sufficient clearance between the aircraftjacking point and the jack upper end.

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

(4) At the forward jacking point, specific jack dimensions are necessary (Ref. Fig. SpecificJack-Nose Dimensions):- Maximum jack tube diameter 320 mm (12.6 in)- Maximum threaded rod diameter 160 mm (6.3 in)- Minimum threaded rod length 250 mm (9.8 in).

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

2-14-0Page 3

Apr 01/13


**ON A/C A330-200

FWD JACKINGPOINT

SAFETYSTAY

Y

B’

B

WING JACKINGPOINT

X

SAFETY STAY

WING JACKINGPOINT

C

B’

B

FORWARD FUSELAGEJACKING POINT A

3.58

28.35

28.35

51.54

11.75

93.01

93.01

169.09

0

8.51

−8.51

0

0

27.92

−27.92

0

MAXIMUMLOAD ELIGIBLE

m ft

12 300

daN

YX

81 084

81 084

4 500

m ft

CA

NOTE:SAFETY STAY IS NOT USED FOR JACKING.

WING JACKINGPOINT

F_AC_021400_1_0010101_01_00

Jacking for MaintenanceJacking Points Location

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

2-14-0Page 4

Apr 01/13


**ON A/C A330-300

SAFETY STAY

WING JACKINGPOINT

C

B’

B


3.58 11.75 0

8.51

−8.51

0

0

27.92

−27.92

0


m ft daN

YX

m ft

31.55

31.55

55.81

103.51

103.51

183.1

12 300

81 084

81 084

4 500

Y

X

B

A C


FWD JACKINGPOINT

SAFETYSTAY

WING JACKINGPOINT

WING JACKINGPOINT

B’

F_AC_021400_1_0010201_01_00


FIGURE-2-14-0-991-001-B01

2-14-0Page 5

Apr 01/13


**ON A/C A330-200F

SAFETY STAY

WING JACKINGPOINT

C

B’

B


3.57

28.35

28.35

51.54

11.71

93.01

93.01

169.09

0

8.51

−8.51

0

0

27.92

−27.92

0


m ft

11 246

daN

YX

65 389

65 389

4 500

m ft

Y

B’

X


FWD JACKINGPOINT

SAFETYSTAY

WING JACKINGPOINT

B

WING JACKINGPOINT

CA

F_AC_021400_1_0010301_01_00


FIGURE-2-14-0-991-001-C01

2-14-0Page 6

Apr 01/13


**ON A/C A330-200 A330-300

Z−2157.8

Z−2136

FR10A

AFR10A

A

FWD

B

ADAPTOR −JACK NOSE

B

SPHERICALRADIUS 19 mm (0.75 in)

F_AC_021400_1_0020101_01_00

Jacking for MaintenanceForward Jacking Point

FIGURE-2-14-0-991-002-A01

2-14-0Page 7

Apr 01/13


**ON A/C A330-200F

Z−2156.8

Z−2135

FR10AA

FR10A

ADAPTOR −JACK NOSE

B


A

FWD

B

F_AC_021400_1_0020201_01_00

Jacking for MaintenanceForward Jacking Point

FIGURE-2-14-0-991-002-B01

2-14-0Page 8

Apr 01/13


**ON A/C A330-200 A330-300

A

A

RIB10

RIB10

LOWER SURFACE

EXAMPLE

Z−790.3

Z−700.6

SPHERICALRADIUS 32 mm

(1.26 in)

JACKING PADSET−WING

OUTER SKIN

RIB10OUTER SKIN

B

B

A

DATUM INTERSECTIONAT MID REAR SPAR DATUM

F_AC_021400_1_0030101_01_00

Jacking for MaintenanceWing Jacking Points

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

2-14-0Page 9

Apr 01/13


**ON A/C A330-200F

A

A RIB10

RIB10

LOWER SURFACE

EXAMPLE

Z−1019.7

Z−930

SPHERICALRADIUS 32 mm

(1.26 in)

JACKING PADSET−WING

OUTER SKIN

RIB10OUTER SKIN

B

B

A

DATUM INTERSECTIONAT MID REAR SPAR DATUM

F_AC_021400_1_0030201_01_00

Jacking for MaintenanceWing Jacking Points

FIGURE-2-14-0-991-003-B01

2-14-0Page 10

Apr 01/13


**ON A/C A330-200

FR87

A


Z 83.4

Z 116.7

A

FR87

B

FWD

ADAPT−SUPP, AFT JACK

B

F_AC_021400_1_0040101_01_00

Jacking for MaintenanceAuxiliary Jacking Point - Safety Stay

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

2-14-0Page 11

Apr 01/13


**ON A/C A330-300

FR85

A


Z−474.0

Z−440.7

A

B

FWD

FR85


B

F_AC_021400_1_0040201_01_00


FIGURE-2-14-0-991-004-B01

2-14-0Page 12

Apr 01/13


**ON A/C A330-200F

FR87

A


Z−117.7

Z−84.4

A

B

FWD

FR87


B

F_AC_021400_1_0040301_01_00


FIGURE-2-14-0-991-004-C01

2-14-0Page 13

Apr 01/13


**ON A/C A330-200F

MAKE SURE THAT THE JACK YOU USE IS APPLICABLE FOR THIS AIRCRAFT.IF THE JACK DIMENSIONS ARE NOT IN THE RANGE FOR THIS AIRCRAFT,DAMAGE TO THE AIRCRAFT STRUCTURE CAN OCCUR.

MAX 320 mm(12.6 in)

CAUTION:

H MIN 250 mm (9.84 in)THREADED ROD EXTENSION

A

A

(6.3 in)

MAX 160 mm

FR10A FR11

F_AC_021400_1_0220101_01_00

Jacking for MaintenanceSpecific Jack-Nose DimensionsFIGURE-2-14-0-991-022-A01

2-14-0Page 14

Apr 01/13


**ON A/C A330-200

L

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

2.59 m(8.5 ft)

4.46 m(14.63 ft)

5.68 m(18.64 ft)

AIRCRAFT ON WHEELS, SHOCK ABSORBERS DEFLATED ANDFLAT TIRES

2.26 m(7.4 ft)

4.1 m(13.45 ft)

5.07 m(16.63 ft)

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

4.37 m(14.34 ft)

5.8 m(19.03 ft)

6.38 m(20.93 ft)

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

5.07 m(16.63 ft)

6.5 m(21.33 ft)

7.08 m(19.19 ft)

L M N

AIRCRAFT ON WHEELS WITH STANDARD TIRES,OEW 124 500 kg (274 475 lb)

2.61 m(8.56 ft)

4.51 m(14.8 ft)

5.85 m(19.19 ft)

FUSELAGE

N

DATUM LINE

M

F_AC_021400_1_0050101_01_00

Jacking for MaintenanceJacking Dimensions

FIGURE-2-14-0-991-005-A01

2-14-0Page 15

Apr 01/13


**ON A/C A330-300

N


2.52 m(8.27 ft)

2.2 m(7.22 ft)

4.37 m(14.34 ft)

5.07 m(16.63 ft)

2.5 m(8.20 ft)

4.46 m(14.63 ft)

5.39 m(17.68 ft)


4.1 m(13.45 ft)

4.77 m(15.65 ft)


5.8 m(19.03 ft)

6.06 m(19.88 ft)


6.5 m(21.33 ft)

6.76 m(22.18 ft)

L M N


4.51 m(14.8 ft)

5.57 m(18.27 ft)

FUSELAGEDATUM LINE

L

M

F_AC_021400_1_0050201_01_00


FIGURE-2-14-0-991-005-B01

2-14-0Page 16

Apr 01/13


**ON A/C A330-200F


3.04 m(9.97 ft)

3.07 m(10.07 ft)

4.37 m(14.34 ft)

5.06 m(16.6 ft)

3.05 m(10.01 ft)

4.42 m(14.5 ft)

5.39 m(17.68 ft)


4.54 m(14.9 ft)

4.75 m(15.58 ft)


5.58 m(18.31 ft)

6.38 m(20.93 ft)


6.26 m(20.54 ft)

7.06 m(23.16 ft)

L M N


4.53 m(14.86 ft)

5.58 m(18.31 ft)

FUSELAGEDATUM LINE

M

N

L

F_AC_021400_1_0050301_01_00


FIGURE-2-14-0-991-005-C01

2-14-0Page 17

Apr 01/13


**ON A/C A330-200 A330-200F

AT 26.5% RC . THE REACTION AT THE WING JACKING POINTS IS 127 000 kg(63 500 kg PER SIDE) AND THE REACTION AT THE FORWARD FUSELAGE JACKING POINT

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

ASSUME AIRCRAFT WITH A GROSS WEIGHT OF 135 000 kg AND CENTER OF GRAVITYAB

CD

BE IN EXCESS OF 60 km/h.

EXAMPLE:

0 6 8 10 12 14 16 18 20

80

90

100

110

120

130

140

150

160

170 40

2015

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

10

LOA

D O

N W

ING

JA

CK

ING

PO

INT

S (

kg x

1 0

00)

45

50

AIR

CR

AF

T G

RO

SS

WE

IGH

T (

kg x

1 0

00)

2 4

80

90

100

110

120

130

140

150

160

170

22

20 30 40 50 60 70 80

2530

35

TIP UPSECURITYMARGIN

PERMISSIBLE WIND SPEED (km/h)

AIRCRAFT CG (%RC)

B

A

C

D

F_AC_021400_1_0060101_01_00

Jacking for MaintenanceLoad at the Aircraft Jacking Points

FIGURE-2-14-0-991-006-A01

2-14-0Page 18

Apr 01/13


**ON A/C A330-300

0 6 8 10 12 14 16 18 20

80

90

100

110

120

130

140

150

160

170 4035

2520

1510

45 20 30 40 50 60 70

50

2 4

80

90

100

110

120

130

140

150

160

170

EXAMPLE:

AT 22.8% RC . THE REACTION AT THE WING JACKING POINTS IS 136 000 kg(68 000 kg PER SIDE) AND THE REACTION AT THE FORWARD FUSELAGE JACKING POINT

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

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

CD

BE IN EXCESS OF 60 km/h.

TIP UPSECURITYMARGIN

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

LOA

D O

N W

ING

JA

CK

ING

PO

INT

S (

kg x

1 0

00)

AIR

CR

AF

T G

RO

SS

WE

IGH

T (

kg x

1 0

00)

PERMISSIBLE WIND SPEED (km/h)

30

A

B

D

C

AIRCRAFT CG (%RC)

F_AC_021400_1_0060201_01_00

Jacking for MaintenanceLoad at the Aircraft Jacking Points

FIGURE-2-14-0-991-006-B01

2-14-0Page 19

Apr 01/13


2-14-1 Jacking for Wheel Change

**ON A/C A330-200 A330-200F A330-300

Jacking for Wheel Change

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

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

2. Main Landing Gear (MLG)To lift the MLG bogie with jacks, a dome shaped pad (PN MS33559 TYPE IV) is installed below theFWD and AFT ends of each bogie beam. Each pair of wheels and brake units can be replaced on theend of the bogie that is lifted.Both FWD and AFT ends of the bogie beam can be lifted together, but the bogie beam must be keptlevel during the lift to prevent damage.The MLG has a pitch trimmer installed. If an MLG has all four tires deflated or shredded, replace thewheel assemblies in this sequence:- Replace the wheel assemblies on the AFT axle,- Replace the wheel assemblies on the FWD axle.

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

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

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

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

2-14-1Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

AFT WHEELS JACKED UPFWD WHEELS INSTALLED AND INFLATED

FWD WHEELS JACKED UPAFT WHEELS INSTALLED AND INFLATED

JACKING POINT570 mm

(22.44 in)

MAX DIAMETER1 443.7 mm(56.84 in)

25.4 mm(1 in)

NORMAL ATTITUDE

JACKING POINT376 mm(14.8 in)

25.4 mm(1 in)

FWD

FWD

FWD


JACKING POINT570 mm

(22.44 in)

F_AC_021401_1_0010102_01_00

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

FIGURE-2-14-1-991-001-A01

2-14-1Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

FWD AXLEBOTH TIRES SHREDDED OR DEFLATED

AFT AXLEBOTH TIRES SHREDDED OR DEFLATED

FWD AND AFT AXLEBOTH TIRES SHREDDED OR DEFLATED

JACKING POINT376 mm(14.8 in)JACKING POINT

145.9 mm(5.74 in)

JACKING POINT376 mm(14.8 in) JACKING POINT

145.5 mm(5.73 in)



FWD

FWD

FWD

F_AC_021401_1_0010103_01_00


FIGURE-2-14-1-991-001-A01

2-14-1Page 3

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

AFT AXLEBOTH TIRES SHREDDED OR DEFLATED AND WHEEL RIMS WORN

JACKING POINT376 mm(14.8 in) JACKING POINT

118.8 mm(4.68 in)

FWD

FWD AND AFT AXLESTIRES SHREDDED OR DEFLATED AND WHEEL RIMS WORN



FWD

JACKING POINT376 mm(14.8 in)JACKING POINT

118.8 mm(4.68 in)

FWD

FWD AXLEBOTH TIRES SHREDDED OR DEFLATED AND WHEEL RIMS WORN

F_AC_021401_1_0010104_01_00


FIGURE-2-14-1-991-001-A01

2-14-1Page 4

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

1 FLAT TIRE110 mm(4.33 in)180 mm MAX

(7.09 in)

(1 in)25.4 mm

400 mm

(15.75 in)

170 mm(6.69 in) FWD

F_AC_021401_1_0020101_01_00

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

FIGURE-2-14-1-991-002-A01

2-14-1Page 5

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

1 083 mm(42.64 in)

270 mm(10.63 in)

NORMAL ATTITUDE

TWO TIRES DEFLATED OR SHREDDED

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

297.5 mm(11.71 in)

JACKING POINT290 mm

(11.42 in)

JACKING POINT148.5 mm(5.85 in)

JACKING POINT400 mm

(15.75 in)

25.4 mm(1 in)

FWD

FWD

FWD

F_AC_021401_1_0020102_01_00

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

FIGURE-2-14-1-991-002-A01

2-14-1Page 6

Apr 01/13


**ON A/C A330-300

AIRCRAFT GROSS WEIGHT

280 320 360 400 440 480 520

120 140 160 180 200 220 24050

60

70

80

90

100

110

120

130

260

560

(x 1 000 kg)

(x 1 000 lb)

35% MAC30% MAC25% MAC20% MAC15% MAC

41% MACCG POSITION

LOA

D A

T J

AC

KIN

G P

OIN

T (

x 1

000

kg)

LOA

D A

T J

AC

KIN

G P

OIN

T (

x 1

000

lb)

110

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

F_AC_021401_1_0030101_01_00

Jacking for Wheel ChangeMLG Jacking Point Loads

FIGURE-2-14-1-991-003-A01

2-14-1Page 7

Apr 01/13


**ON A/C A330-200 A330-200F


120 140 160 180 200 220 24050

60

70

80

90

100

110

120

130

260(x 1 000 kg)

(x 1 000 lb)

35% MAC30% MAC25% MAC18% MAC

40% MACCG POSITION

LOA

D A

T J

AC

KIN

G P

OIN

T (

x 1

000

kg)

LOA

D A

T J

AC

KIN

G P

OIN

T (

x 1

000

lb)

110

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

280 320 360 400 440 480 520 560

F_AC_021401_1_0030201_01_00

Jacking for Wheel ChangeMLG Jacking Point Loads

FIGURE-2-14-1-991-003-B01

2-14-1Page 8

Apr 01/13


**ON A/C A330-300

10

15

20

25

30

35

40

45

50

55

60

65

140 160 180 200 220 240120 260(x 1 000 kg)

280 320 360 400 440 480 520 560

(x 1 000 lb)


LOA

D A

T J

AC

KIN

G P

OIN

T (

x 1

000

kg)

LOA

D A

T J

AC

KIN

G P

OIN

T (

x 1

000

lb)

20% MAC25% MAC30% MAC35% MAC41% MAC

15% MACCG POSITION

6

8

10

12

14

16

18

20

22

24

26

28

30

4

F_AC_021401_1_0040101_01_00

Jacking for Wheel ChangeNLG Jacking Point Loads

FIGURE-2-14-1-991-004-A01

2-14-1Page 9

Apr 01/13


**ON A/C A330-200 A330-200F

15

20

25

30

35

40

45

50

55

60

65

140 160 180 200 220 240120 260(x 1 000 kg)

280 320 360 400 440 480 520 560

(x 1 000 lb)


LOA

D A

T J

AC

KIN

G P

OIN

T (

x 1

000

kg)

LOA

D A

T J

AC

KIN

G P

OIN

T (

x 1

000

lb)

6

8

10

12

14

16

18

20

22

24

26

28

30

70

75

32

34

36

30% MAC35% MAC40% MAC

18% MACCG POSITION

25% MAC

F_AC_021401_1_0040201_01_00

Jacking for Wheel ChangeNLG Jacking Point Loads

FIGURE-2-14-1-991-004-B01

2-14-1Page 10

Apr 01/13


2-14-2 Support of Aircraft

**ON A/C A330-200 A330-200F A330-300

Support of Aircraft

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

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

A. Shoring CradlesShoring cradles are used when it is necessary to stress-jack the aircraft to carry out maintenanceand repair work. These are used to oppose the deflections of the wings and reduce the stressesto an acceptable level at the area of maintenance and repair.

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

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

2-14-2Page 1

Apr 01/13


**ON A/C A330-200

FR80

FR72

FR58

FR26

FR17

FR11

RIB6

RIB16

RIB21

RIB31

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

(SAFETY STAY)FR87

RIB6

RIB16

RIB21

RIB31

FR53.2

F_AC_021402_1_0010101_01_00

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

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

2-14-2Page 2

Apr 01/13


**ON A/C A330-200

FR7

FR17

FR20

FR53.8 FR59 FR76

FR29

FR36

FR39.1

A

LH SHOWN

(9.02 ft)2.75 m

(15.09 ft)4.6 m

(6.89 ft)2.1 m

EXAMPLE

A

B

RH SYMMETRICAL

B B

F_AC_021402_1_0010102_01_00

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

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

2-14-2Page 3

Apr 01/13


**ON A/C A330-300

FR85

FR80

FR72

FR58

FR26

FR17

FR11

(SAFETY STAY)


RIB6

RIB16

RIB21

RIB31

FR53.2

RIB6

RIB16

RIB21

RIB31

F_AC_021402_1_0010201_01_00


FIGURE-2-14-2-991-001-B01

2-14-2Page 4

Apr 01/13


**ON A/C A330-300

FR7

FR17

FR20

FR26.1

FR39.1 FR53.8 FR59 FR76

FR36

A

LH SHOWN

(9.02 ft)2.75 m

(15.09 ft)4.6 m

(6.89 ft)2.1 m

EXAMPLE

A

B

RH SYMMETRICAL

B B

F_AC_021402_1_0010202_01_00


FIGURE-2-14-2-991-001-B01

2-14-2Page 5

Apr 01/13


**ON A/C A330-200F

FR80

FR72

FR26

FR17

FR11

(SAFETY STAY)FR87


RIB6

RIB16

RIB21

RIB31

FR58

FR53.2

RIB6

RIB16

RIB21

RIB31

F_AC_021402_1_0010301_01_00


FIGURE-2-14-2-991-001-C01

2-14-2Page 6

Apr 01/13


**ON A/C A330-200F

FR17

FR20

FR53.8 FR59 FR76

FR29

FR36

FR39.1FR7

A

LH SHOWN

(9.02 ft)2.75 m

(15.09 ft)4.6 m

(6.89 ft)2.1 m

EXAMPLE

A

B

RH SYMMETRICAL

B B

F_AC_021402_1_0010302_01_00


FIGURE-2-14-2-991-001-C01

2-14-2Page 7

Apr 01/13


AIRCRAFT PERFORMANCE


**ON A/C A330-200 A330-200F A330-300

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/JAR takeoff runway length requirements at ISA and ISA +15˚C(+27˚F) for engine conditions for FAA/EASA certification :

- PRATT & WHITNEY (PW 4000).- ROLLS-ROYCE (RR Trent 700).- GENERAL ELECTRIC (GE CF6-80E1). (A330-200 and A330-300 only)

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

Section 3-5 indicates final approach speeds.

Standard day temperatures for the altitude shown are tabulated below :

Standard day temperatures for the altitude

Altitude Standard Day Temperature

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

3-1-0Page 1

Apr 01/13


3-2-0 Payload / Range

**ON A/C A330-200 A330-200F A330-300

Payload / Range

1. Payload / Range

3-2-0Page 1

Apr 01/13



**ON A/C A330-200 A330-300

ISA Conditions

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

3-2-1Page 1

Apr 01/13


**ON A/C A330-200

0

102030405060708090

100

110

120

3000

3500

4000

4500

5000

5500

6000

6500

7000

7500

8000

9000

8500 16

000

5000

6000

7000

8000

9000

1000

011

000

1200

013

000

1400

015

000

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

PA

YLO

AD

(100

0lb)

RA

NG

E(N

M)

RA

NG

E(K

M)

NO

TE

:M

AX

ZE

RO

FU

EL

WE

IGH

T :

170

T

50 0

00

45 0

00

40 0

00

35 0

00

30 0

00

25 0

00

20 0

00

15 0

00

10 0

00

5 00

0

MA

X T

AK

E−

OF

F W

EIG

HT

: 23

3 T

PA

YLO

AD

(kg)

0

1000

095

00

1700

018

000

MA

X S

TR

UC

TU

RA

L P

AY

LOA

D

F_AC_030201_1_0010101_01_01

PAYLOAD / RANGEPW 4000 Series Engine

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

3-2-1Page 2

Apr 01/13


**ON A/C A330-200

0

102030405060708090

100

110

120

3000

3500

4000

4500

5000

5500

6000

6500

7000

7500

8000

9000

8500 16

000

5000

6000

7000

8000

9000

1000

011

000

1200

013

000

1400

015

000

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

PA

YLO

AD

(100

0lb)

RA

NG

E(N

M)

RA

NG

E(K

M)

NO

TE

:M

AX

ZE

RO

FU

EL

WE

IGH

T :

170

T

50 0

00

45 0

00

40 0

00

35 0

00

30 0

00

25 0

00

20 0

00

15 0

00

10 0

00

5 00

0

MA

X T

AK

E−

OF

F W

EIG

HT

: 23

3 T

PA

YLO

AD

(kg)

0

1000

095

00

1700

018

000

MA

X S

TR

UC

TU

RA

L P

AY

LOA

D

F_AC_030201_1_0020101_01_01

PAYLOAD / RANGERR TRENT 700 Series EngineFIGURE-3-2-1-991-002-A01

3-2-1Page 3

Apr 01/13


**ON A/C A330-200

0102030405060708090

100

110

120

3000

3500

4000

4500

5000

5500

6000

6500

7000

7500

8000

9000

8500 16

000

5000

6000

7000

8000

9000

1000

011

000

1200

013

000

1400

015

000

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

PA

YLO

AD

(100

0lb)

RA

NG

E(N

M)

RA

NG

E(K

M)

NO

TE

:M

AX

ZE

RO

FU

EL

WE

IGH

T :

170

T

50 0

00

45 0

00

40 0

00

35 0

00

30 0

00

25 0

00

20 0

00

15 0

00

10 0

00

5 00

0

MA

X T

AK

E−

OF

F W

EIG

HT

: 23

3 T

PA

YLO

AD

(kg)

0

1000

095

00

1700

018

000

MA

X S

TR

UC

TU

RA

L P

AY

LOA

D

F_AC_030201_1_0030101_01_01

PAYLOAD / RANGEGE CF6-80E1 Series EngineFIGURE-3-2-1-991-003-A01

3-2-1Page 4

Apr 01/13


**ON A/C A330-300

0

102030405060708090

100

110

120

3000

3500

4000

4500

5000

5500

6000

6500

7000

7500

8000

9000

8500 16

000

5000

6000

7000

8000

9000

1000

011

000

1200

013

000

1400

015

000

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

PA

YLO

AD

(100

0lb)

RA

NG

E(N

M)

RA

NG

E(K

M)

NO

TE

:M

AX

ZE

RO

FU

EL

WE

IGH

T :

175

T

50 0

00

45 0

00

40 0

00

35 0

00

30 0

00

25 0

00

20 0

00

15 0

00

10 0

00

5 00

0

MA

X T

AK

E−

OF

F W

EIG

HT

: 23

3 T

PA

YLO

AD

(kg)

0

1000

095

00

1700

018

000

MA

X S

TR

UC

TU

RA

L P

AY

LOA

D

F_AC_030201_1_0040101_01_01


FIGURE-3-2-1-991-004-A01

3-2-1Page 5

Apr 01/13


**ON A/C A330-300

0

102030405060708090

100

110

120

3000

3500

4000

4500

5000

5500

6000

6500

7000

7500

8000

9000

8500 16

000

5000

6000

7000

8000

9000

1000

011

000

1200

013

000

1400

015

000

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

PA

YLO

AD

(100

0 lb

)

RA

NG

E(n

m)

RA

NG

E(k

m)

50 0

00

45 0

00

40 0

00

35 0

00

30 0

00

25 0

00

20 0

00

15 0

00

10 0

00

5 00

0PA

YLO

AD

(kg)

0

1000

095

00

1700

018

000

MA

X S

TR

UC

TU

RA

L P

AY

LOA

D

F_AC_030201_1_0050101_01_01

NO

TE

:M

AX

ZE

RO

FU

EL

WE

IGH

T :

175

TM

AX

TA

KE

−O

FF

WE

IGH

T :

233

T


3-2-1Page 6

Apr 01/13


**ON A/C A330-300

0

102030405060708090

100

110

120

3000

3500

4000

4500

5000

5500

6000

6500

7000

7500

8000

9000

8500 16

000

5000

6000

7000

8000

9000

1000

011

000

1200

013

000

1400

015

000

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

PA

YLO

AD

(100

0lb)

RA

NG

E(N

M)

RA

NG

E(K

M)

NO

TE

:M

AX

ZE

RO

FU

EL

WE

IGH

T :

175

T

50 0

00

45 0

00

40 0

00

35 0

00

30 0

00

25 0

00

20 0

00

15 0

00

10 0

00

5 00

0

MA

X T

AK

E−

OF

F W

EIG

HT

: 23

3 T

PA

YLO

AD

(kg)

0

1000

095

00

1700

018

000

MA

X S

TR

UC

TU

RA

L P

AY

LOA

D

F_AC_030201_1_0060101_01_01

PAYLOAD / RANGEGE CF6-80E1 Series EngineFIGURE-3-2-1-991-006-A01

3-2-1Page 7

Apr 01/13


**ON A/C A330-200F

ISA Conditions

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

3-2-1Page 8

Apr 01/13


**ON A/C A330-200F

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

PA

YLO

AD

(100

0lb)

RA

NG

E(N

M)

RA

NG

E(K

M)

NO

TE

:M

AX

ZE

RO

FU

EL

WE

IGH

T :

173

TM

AX

TA

KE

−O

FF

WE

IGH

T :

233

T

PA

YLO

AD

(kg)

160

150

140

130

120

110

100 90 80 70 60 50 40 30 20 10 0

70 0

00

65 0

00

60 0

00

55 0

00

50 0

00

45 0

00

40 0

00

35 0

00

30 0

00

25 0

00

20 0

00

15 0

00

10 0

00

5 00

0 0

MA

X S

TR

UC

TU

RA

L P

AY

LOA

D

010

0020

0030

0040

0050

0060

0070

0080

00

1600

014

000

1200

010

000

8000

6000

9000

1000

0

1800

040

0020

000

F_AC_030201_1_0070101_01_01


3-2-1Page 9

Apr 01/13


**ON A/C A330-200F

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

PA

YLO

AD

(100

0lb)

RA

NG

E(N

M)

RA

NG

E(K

M)

NO

TE

:M

AX

ZE

RO

FU

EL

WE

IGH

T :

178

TM

AX

TA

KE

−O

FF

WE

IGH

T :

227

T

PA

YLO

AD

(kg)

160

150

140

130

120

110

100 90 80 70 60 50 40 30 20 10 0

70 0

00

65 0

00

60 0

00

55 0

00

50 0

00

45 0

00

40 0

00

35 0

00

30 0

00

25 0

00

20 0

00

15 0

00

10 0

00

5 00

0 0

MA

X S

TR

UC

TU

RA

L P

AY

LOA

D

010

0020

0030

0040

0050

0060

0070

0080

00

1600

014

000

1200

010

000

8000

6000

9000

1000

0

1800

040

0020

000

F_AC_030201_1_0080101_01_01


3-2-1Page 10

Apr 01/13


**ON A/C A330-200F

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

PA

YLO

AD

(100

0lb)

RA

NG

E(N

M)

RA

NG

E(K

M)

NO

TE

:M

AX

ZE

RO

FU

EL

WE

IGH

T :

173

TM

AX

TA

KE

−O

FF

WE

IGH

T :

233

T

PA

YLO

AD

(kg)

160

150

140

130

120

110

100 90 80 70 60 50 40 30 20 10 0

70 0

00

65 0

00

60 0

00

55 0

00

50 0

00

45 0

00

40 0

00

35 0

00

30 0

00

25 0

00

20 0

00

15 0

00

10 0

00

5 00

0 0

MA

X S

TR

UC

TU

RA

L P

AY

LOA

D

010

0020

0030

0040

0050

0060

0070

0080

00

1600

014

000

1200

010

000

8000

6000

9000

1000

0

1800

040

0020

000

F_AC_030201_1_0090101_01_01


FIGURE-3-2-1-991-009-A01

3-2-1Page 11

Apr 01/13


**ON A/C A330-200F

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

D IN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

O T

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T.

PA

YLO

AD

(100

0lb)

RA

NG

E(N

M)

RA

NG

E(K

M)

NO

TE

:M

AX

ZE

RO

FU

EL

WE

IGH

T :

178

TM

AX

TA

KE

−O

FF

WE

IGH

T :

227

T

PA

YLO

AD

(kg)

160

150

140

130

120

110

100 90 80 70 60 50 40 30 20 10 0

70 0

00

65 0

00

60 0

00

55 0

00

50 0

00

45 0

00

40 0

00

35 0

00

30 0

00

25 0

00

20 0

00

15 0

00

10 0

00

5 00

0 0

MA

X S

TR

UC

TU

RA

L P

AY

LOA

D

010

0020

0030

0040

0050

0060

0070

0080

00

1600

014

000

1200

010

000

8000

6000

9000

1000

0

1800

040

0020

000

F_AC_030201_1_0100101_01_01


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

3-2-1Page 12

Apr 01/13


3-3-0 FAR / JAR Takeoff Weight Limitation

**ON A/C A330-200 A330-200F A330-300

FAR / JAR Takeoff Weight Limitation

1. FAR / JAR Takeoff Weight Limitation

3-3-0Page 1

Apr 01/13



**ON A/C A330-200 A330-200F A330-300

FAR / JAR Takeoff Weight Limitation

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

3-3-1Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

RU

NW

AY

LE

NG

TH

(100

0 F

t)

RU

NW

AY

LE

NG

TH

(100

0 m

)

NO

TE

:

320

340

360

380

400

420

440

460

480

500

520

540

560

300

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LY.

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

DIN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

OT

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T

46

810

1214

162 0.5

11.

52

2.5

33.

54

4.5

5

255

135

155

175

195

215

235TA

KE

−O

FF

WE

IGH

T10

00 L

b10

00 K

g

02

46

8

0 2 4 6 8

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 F

t)

V.M

.C

BR

AK

E E

NE

RG

Y L

IMIT

AT

ION

F_AC_030301_1_0010101_01_01

Takeoff Weight LimitationISA Conditions - PW 4000 Series Engine

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

3-3-1Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

RU

NW

AY

LE

NG

TH

(100

0 F

t)

RU

NW

AY

LE

NG

TH

(100

0 m

)

NO

TE

:

02

46

8

320

340

360

380

400

420

440

460

480

500

520

540

560

300

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LY.

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

DIN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

OT

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T

46

810

1214

162 0.5

11.

52

2.5

33.

54

4.5

5

255

135

155

175

195

215

235

20 4 6 8

TA

KE

−O

FF

WE

IGH

T10

00 L

b10

00 K

g

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 F

t)

V.M

.C

BR

AK

E E

NE

RG

Y L

IMIT

AT

ION

F_AC_030301_1_0020101_01_01

Takeoff Weight LimitationISA Conditions - RR TRENT 700 Series Engine

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

3-3-1Page 3

Apr 01/13


**ON A/C A330-200 A330-300

RU

NW

AY

LE

NG

TH

(100

0 F

t)

RU

NW

AY

LE

NG

TH

(100

0 m

)

NO

TE

:

02

46

8

320

340

360

380

400

420

440

460

480

500

520

540

560

300

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LY.

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

DIN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

OT

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T

46

810

1214

162 0.5

11.

52

2.5

33.

54

4.5

5

255

135

155

175

195

215

235

TA

KE

−O

FF

WE

IGH

T10

00 L

b10

00 K

g

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 F

t)V

.M.C

BR

AK

E E

NE

RG

Y L

IMIT

AT

ION0 2 4 6 8

F_AC_030301_1_0030101_01_01

Takeoff Weight LimitationISA Conditions - GE CF6-80E1 Series Engine

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

3-3-1Page 4

Apr 01/13


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

**ON A/C A330-200 A330-200F A330-300

ISA +15 ˚C (ISA +27 ˚F) Conditions

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

3-3-2Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

TA

KE

−O

FF

WE

IGH

T10

00 L

b10

00 K

g

RU

NW

AY

LE

NG

TH

(100

0 F

t)

RU

NW

AY

LE

NG

TH

(100

0 m

)

NO

TE

:

02

46

8

320

340

360

380

400

420

440

460

480

500

520

540

560

300

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LY.

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

DIN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

OT

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T

46

810

1214

162 0.5

11.

52

2.5

33.

54

4.5

5

255

135

155

175

195

215

235

0 2 4 6 8

BR

AK

E E

NE

RG

Y L

IMIT

AT

ION

V.M

.C

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 F

t)

F_AC_030302_1_0010101_01_01

FAR / JAR Takeoff Weight LimitationISA +15˚C (ISA +27˚F) Conditions - PW 4000 Series Engine

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

3-3-2Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

RU

NW

AY

LE

NG

TH

(100

0 F

t)

RU

NW

AY

LE

NG

TH

(100

0 m

)

NO

TE

:

320

340

360

380

400

420

440

460

480

500

520

540

560

300

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LY.

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

DIN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

OT

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T

46

810

1214

162 0.5

11.

52

2.5

33.

54

4.5

5

255

135

155

175

195

215

235TA

KE

−O

FF

WE

IGH

T10

00 L

b10

00 K

g

0 2 4 6 8

BR

AK

E E

NE

RG

Y L

IMIT

AT

ION

V.M

.C

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 F

t)

02

46

8

F_AC_030302_1_0020101_01_01

FAR / JAR Takeoff Weight LimitationISA +15˚C (ISA +27˚F) Conditions - RR TRENT 700 Series Engine

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

3-3-2Page 3

Apr 01/13


**ON A/C A330-200 A330-300

RU

NW

AY

LE

NG

TH

(100

0 F

t)

RU

NW

AY

LE

NG

TH

(100

0 m

)

NO

TE

:

02

46

8

320

340

360

380

400

420

440

460

480

500

520

540

560

300

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LY.

TH

E A

PP

RO

VE

D V

ALU

ES

AR

E S

TA

TE

DIN

TH

E "

OP

ER

AT

ING

MA

NU

ALS

" S

PE

CIF

IC T

OT

HE

AIR

LIN

E O

PE

RA

TIN

G T

HE

AIR

CR

AF

T

46

810

1214

162 0.5

11.

52

2.5

33.

54

4.5

5

255

135

155

175

195

215

235

0 2 4 6 8

TA

KE

−O

FF

WE

IGH

T10

00 L

b10

00 K

g

BR

AK

E E

NE

RG

Y L

IMIT

AT

ION

V.M

.C

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

(10

00 F

t)

F_AC_030302_1_0030101_01_01

FAR / JAR Takeoff Weight LimitationISA +15˚C (ISA +27˚F) Conditions - GE CF6-80E1 Series Engine

FIGURE-3-3-2-991-003-A01

3-3-2Page 4

Apr 01/13


3-4-0 FAR / JAR Landing Field Length

**ON A/C A330-200 A330-200F A330-300

Landing Field Length

1. Landing Field Length

3-4-0Page 1

Apr 01/13


3-4-1 ISA Conditions All series engines

**ON A/C A330-200 A330-200F A330-300

ISA Conditions All series engine

1. This section gives the landing field length.

3-4-1Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

.T

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.F

AR

/JA

R L

AN

DIN

GLE

NG

TH

GR

OS

S W

EIG

HT

(100

0 K

g)

GR

OS

S W

EIG

HT

(100

0 Lb

)

(100

0 m

)(1

000

Ft) 15

050

020

025

040

045

030

035

0

230

7010

020

015

0

3456782.

5 1

1.52

24

68

10S

EA

LE

VE

L

(100

0 F

t)A

IRF

IELD

ELE

VA

TIO

N

F_AC_030401_1_0010101_01_01

ISA

CO

ND

ITIO

NS

CO

NF

. FU

LL

FAR / JAR Landing Field LengthISA Conditions - PW 4000 Series Engine

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

3-4-1Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

.T

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.F

AR

/JA

R L

AN

DIN

GLE

NG

TH

GR

OS

S W

EIG

HT

(100

0 K

g)

GR

OS

S W

EIG

HT

(100

0 Lb

)

(100

0 m

)(1

000

Ft)

46

810

150

500

200

250

400

450

300

350

230

7010

020

015

0

3456782.

5 1

1.52

SE

A L

EV

EL

2

AIR

FIE

LD E

LEV

AT

ION

(100

0 F

t)

F_AC_030401_1_0020101_01_01

ISA

CO

ND

ITIO

NS

CO

NF

. FU

LL

FAR / JAR Landing Field LengthISA Conditions - RR TRENT 700 Series Engine

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

3-4-1Page 3

Apr 01/13


**ON A/C A330-200 A330-300

NO

TE

:T

HE

SE

CU

RV

ES

AR

E G

IVE

N F

OR

INF

OR

MA

TIO

N O

NLY

.T

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

IN T

HE

"O

PE

RA

TIN

GM

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.F

AR

/JA

R L

AN

DIN

GLE

NG

TH

GR

OS

S W

EIG

HT

(100

0 K

g)

GR

OS

S W

EIG

HT

(100

0 Lb

)

(100

0 m

)(1

000

Ft)

46

810

150

500

200

250

400

450

300

350

230

7010

020

015

0

3456782.

5 1

1.52

SE

A L

EV

EL

2

AIR

FIE

LD E

LEV

AT

ION

(100

0 F

t)

F_AC_030401_1_0030101_01_01

ISA

CO

ND

ITIO

NS

CO

NF

. FU

LL

FAR / JAR Landing Field LengthISA Conditions - GE CF6-80E1 Series Engine

FIGURE-3-4-1-991-003-A01

3-4-1Page 4

Apr 01/13


3-5-0 Final Approach Speed

**ON A/C A330-200 A330-200F A330-300

Final Approach Speed

**ON A/C A330-200

1. Final Approach Speed

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

B. The final approach speed is 136 kt at a Maximum Landing Weight (MLW) of 182 000 kg (401241 lb) and classifies the aircraft into the Aircraft Approach Category C.

NOTE : This value is given for information only.

**ON A/C A330-200F





**ON A/C A330-300





3-5-0Page 1

Apr 01/13


GROUND MANEUVERING


**ON A/C A330-200 A330-200F A330-300

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

Apr 01/13


4-2-0 Turning Radii

**ON A/C A330-200 A330-200F A330-300

Turning Radii

1. This section gives the turning radii.

4-2-0Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

NOTE:FOR TURNING RADII VALUES, REFER TO SHEET 2.

72°

65°

60°

55°

R1

R5

R2

R3

R4

R6

F_AC_040200_1_0040101_01_03

Turning Radii(Sheet 1)

FIGURE-4-2-0-991-004-A01

4-2-0Page 2

Apr 01/13


**ON A/C A330-300

19.420

TYPE OFTURN

267.7222

A330−300 TURNING RADII

m

ft78.4257

76.9252

R4WING

102.7337

R5NOSE

78.9259

R6TAIL

85.9282

R1RMLG

R2LMLG

R3NLG

24.225252.1171

62.8206

62.4205

87.1286

64.9213

71.2234

29.030241.4136

52.1171

52.8173

76.5251

55.9183

61.4201

33.835233.5110

44.2145

46.1151

68.7225

49.6163

54.4178

38.640227.490

38.1125

41.1135

62.7206

45.1148

49.1161

43.245222.674

33.3109

37.5123

58.0190

41.9137

45.2148

47.850218.6

6129.396

34.6114

54.0177

39.5130

42.0138

52.255215.350

26.085

32.5107

50.7166

37.6123

39.5130

56.360212.5

4123.276

30.8101

48.0158

36.2119

37.4123

60.165210.233

20.969

29.697

45.8150

35.2115

35.8117

63.87228.127

18.862

28.594

43.7143

34.4113

34.4113

48.250118.360

29.095

34.4113

53.7176

39.3129

41.7137

52.955114.849

25.584

32.2106

50.3165

37.4123

39.1128

57.660111.738

22.473

30.4100

47.2155

35.9118

36.9121

62.16519.130

19.765

29.095

44.6146

34.7114

35.1115

67.87216.020

16.755

27.691

41.6136

33.7111

33.1109

m

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ft

STEERING ANGLE (deg)EFFECTIVESTEERING

ANGLE (deg)

NOTE:ABOVE 50°, AIRLINES MAY USE TYPE 1 OR TYPE 2 TURNS DEPENDING ON THE SITUATION.TYPE 1 TURNS USE:ASYMMETRIC THRUST DURING THE WHOLE TURN; ANDDIFFERENTIAL BRAKING TO INITIATE THE TURN ONLY.TYPE 2 TURNS USE:SYMMETRIC THRUST DURING THE WHOLE TURN; AND NO DIFFERENTIAL BRAKING AT ALL.IT IS POSSIBLE TO GET LOWER VALUES THAN THOSE FROM TYPE 1 BY APPLYINGDIFFERENTIAL BRAKING DURING THE WHOLE TURN. F_AC_040200_1_0020101_01_03


FIGURE-4-2-0-991-002-A01

4-2-0Page 3

Apr 01/13


**ON A/C A330-200 A330-200F

19.220

TYPE OFTURN

259.3195

A330−200/−200F TURNING RADII

m

ft70.0230

68.0223

R4WING

94.4310

R5NOSE

69.9229

R6TAIL

79.1260

R1RMLG

R2LMLG

R3NLG

23.925245.7150

56.4185

55.3181

80.9265

57.8190

66.6219

28.630236.3119

47.0154

46.8154

71.6235

49.9164

58.4192

33.335229.496

40.1132

40.9134

64.7212

44.4146

52.5172

38.040224.079

34.7114

36.5120

59.4195

40.5133

48.2158

42.545219.865

30.5100

33.2109

55.3181

37.7124

45.0148

46.950216.454

27.189

30.8101

51.9170

35.5116

42.4139

51.255213.544

24.179

28.894

49.1161

33.9111

40.4133

55.160211.136

21.872

27.490

46.8154

32.7107

38.8127

59.66528.628

19.363

26.085

44.4146

31.6104

37.2122

62.07227.424

18.159

25.483

43.2142

31.2102

36.5120

48.450115.350

26.085

30.098

50.9167

34.9115

41.7137

52.255112.842

23.577

28.493

48.5159

33.6110

39.9131

57.76019.631

20.367

26.587

45.4149

32.1105

37.9124

62.26517.324

18.059

25.383

43.1141

31.1102

36.5120

68.17214.515

15.250

24.179

40.4133

30.299

34.9115

m

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ftm

ft


ANGLE (deg)

NOTE:ABOVE 50°, AIRLINES MAY USE TYPE 1 OR TYPE 2 TURNS DEPENDING ON THE SITUATION.TYPE 1 TURNS USE:ASYMMETRIC THRUST DURING THE WHOLE TURN; ANDDIFFERENTIAL BRAKING TO INITIATE THE TURN ONLY.TYPE 2 TURNS USE:SYMMETRIC THRUST DURING THE WHOLE TURN; AND NO DIFFERENTIAL BRAKING AT ALL.IT IS POSSIBLE TO GET LOWER VALUES THAN THOSE FROM TYPE 1 BY APPLYINGDIFFERENTIAL BRAKING DURING THE WHOLE TURN. F_AC_040200_1_0030101_01_03


FIGURE-4-2-0-991-003-A01

4-2-0Page 4

Apr 01/13


4-3-0 Minimum Turning Radii

**ON A/C A330-200 A330-200F A330-300

Minimum Turning Radii

1. This section gives the minimum turning radii.

4-3-0Page 1

Apr 01/13


**ON A/C A330-300

NOTE:TYPE 1 TURNS USE:ASYMMETRIC THRUST DURING THE WHOLETURN; AND DIFFERENTIAL BRAKING TOINITIATE THE TURN ONLY.TYPE 2 TURNS USE:SYMMETRIC THRUST DURING THE WHOLETURN; AND NO DIFFERENTIAL BRAKING AT ALL.

A(MINIMUM TURNING WIDTH)

62.165 (MAX)

TYPE OFTURN

113.444

A330−300 MINIMUM TURNING RADII

m

ft49.0161

29.095

R4WING

44.6146

R5NOSE

34.7114

R6TAIL

35.1115

R3NLG

60.165 (MAX)214.648

50.7166

29.697

45.8150

35.2115

35.8117

m

ft


ANGLE (deg)

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

25.483

25.483

AX Y

Y

72 (MAX)

72 (MAX)

2

1

63.8

67.8m

ftm

ft

10.434

44.6146

27.691

41.6136

33.7111

33.1109

12.541

47.6156

28.594

43.7143

34.4113

34.4113

25.483

25.483

OUTSIDE FACEOF TIRE

X

R3

R5

R6

R4

F_AC_040300_1_0010101_01_05

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

4-3-0Page 2

Apr 01/13


**ON A/C A330-200 A330-200F

NOTE:TYPE 1 TURNS USE:ASYMMETRIC THRUST DURING THE WHOLETURN; AND DIFFERENTIAL BRAKING TOINITIATE THE TURN ONLY.TYPE 2 TURNS USE:SYMMETRIC THRUST DURING THE WHOLETURN; AND NO DIFFERENTIAL BRAKING AT ALL.

A(MINIMUM TURNING WIDTH)

62.265 (MAX)

TYPE OFTURN

111.738

A330−200/−200F MINIMUM TURNING RADII

m

ft43.6143

25.383

R4WING

43.1141

R5NOSE

31.1102

R6TAIL

36.5120

R3NLG

59.665 (MAX)213.043

45.6150

26.085

44.4146

31.6104

37.2122

m

ft


ANGLE (deg)

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

22.273

22.273

AX Y

72 (MAX)

72 (MAX)

2

1

62.0

68.1m

ftm

ft

8.929

39.7130

24.179

40.4133

30.299

34.9115

11.839

43.8144

25.483

43.2142

31.2102

36.5120

22.273

22.273

R6

R4

R5

Y

R3OUTSIDE FACE

OF TIRE

X

F_AC_040300_1_0070101_01_01

Minimum Turning RadiiFIGURE-4-3-0-991-007-A01

4-3-0Page 3

Apr 01/13


4-4-0 Visibility from Cockpit in Static Position

**ON A/C A330-200 A330-200F A330-300

Visibility from Cockpit in Static Position.

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

4-4-0Page 1

Apr 01/13


**ON A/C A330-200 A330-300

25°

20°

13.75 m(45.11 ft)

6.67 m(21.88 ft)

VISUAL ANGLES IN VERTICALPLANE THROUGH PILOTEYE POSITION.

DIMENSIONS ARE APPROXIMATE

2.4 m(7.87 ft)

115°

CAPTAIN FIELD OF VIEW

135°

115°

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(1.74 ft)

62°

42°

30°36°

30°

VISUAL ANGLES IN PLANEPERPENDICULAR TOLONGITUDINAL AXIS.

62°

42°

WITH HEAD MOVED125 mm (5 in) OUTBOARD

135°

36°

NOT TO BE USED FORLANDING APPROACH VISIBILITY

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

ZONE THAT CANNOT BE SEENF_AC_040400_1_0010101_01_01

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

4-4-0Page 2

Apr 01/13


**ON A/C A330-200F

25°

20°

15.75 m(51.67 ft)

6.67 m(21.88 ft)

VISUAL ANGLES IN VERTICALPLANE THROUGH PILOTEYE POSITION.

DIMENSIONS ARE APPROXIMATE

2.4 m(7.87 ft)

115°

CAPTAIN FIELD OF VIEW

135°

115°

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(1.74 ft)

62°

42°

30°36°

30°

VISUAL ANGLES IN PLANEPERPENDICULAR TOLONGITUDINAL AXIS.

62°

42°

WITH HEAD MOVED125 mm (5 in) OUTBOARD

135°

36°

NOT TO BE USED FORLANDING APPROACH VISIBILITY

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

ZONE THAT CANNOT BE SEENF_AC_040400_1_0030101_01_01

Visibility from Cockpit in Static PositionFIGURE-4-4-0-991-003-A01

4-4-0Page 3

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

CA

PT

AIN

WIN

DS

HIE

LDC

AP

TA

IN S

LID

ING

WIN

DO

WC

AP

TA

INF

IXE

D W

IND

OW

WIN

G T

IPV

ISIB

LE

CA

PT

AIN

’S F

IELD

OF

VIE

W S

HO

WN

, TH

RO

UG

H C

AP

TA

IN W

IND

OW

S O

NLY

.F

IRS

T O

FF

ICE

R F

IELD

OF

VIE

W S

YM

ME

TR

ICA

L.

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50°

40°

30°

20°

10°

0°10

°20

°30

°40

°50

°60

°70

°80

°90

°10

0°11

0°12

0°13

0°14

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30°

20°

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F_AC_040400_1_0060101_01_00

Binocular Visibility Through Windows from Captain Eye PositionFIGURE-4-4-0-991-006-A01

4-4-0Page 4

Apr 01/13


4-5-0 Runway and Taxiway Turn Paths

**ON A/C A330-200 A330-200F A330-300

Runway and Taxiway Turn Paths

1. Runway and Taxiway Turn Paths.

4-5-0Page 1

Apr 01/13



**ON A/C A330-200 A330-200F A330-300

135˚ Turn - Runway to Taxiway

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

4-5-1Page 1

Apr 01/13


**ON A/C A330-300

FILLET R = 25.5 m(85 ft)

TURN R = 45 m(150 ft)

APPROX 10.6 m(35 ft)

(15 ft)APPROX 4.7 m

45 m(150 ft)

FAA LEAD−IN FILLET

L = 75 m (250 ft)

23 m(75 ft)

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

NLG PATH

MLG PATH

F_AC_040501_1_0010101_01_01

135˚ Turn - Runway to TaxiwayJudgemental Oversteer Method

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

4-5-1Page 2

Apr 01/13


**ON A/C A330-300

TURN R = 45 m(150 ft)


APPROX 1.3 m

ADDITIONAL FILLET TO MEET4.5 m (15 ft) EDGE CLEARANCE

(4 ft)


L = 75 m (250 ft)

45 m(150 ft)

RUNWAY

23 m(75 ft)

NLG PATH

MLG PATH

CENTERLINE

TAXIWAYCENTERLINE

F_AC_040501_1_0060101_01_00

135˚ Turn - Runway to TaxiwayCockpit Over Centerline Method

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

4-5-1Page 3

Apr 01/13


**ON A/C A330-200 A330-200F


L = 75 m (250 ft)


TURN R = 45 m(150 ft)

(19 ft)APPROX R = 5.9 m


45 m(150 ft)

23 m(75 ft)

NLG PATH

MLG PATH

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

F_AC_040501_1_0020101_01_01


FIGURE-4-5-1-991-002-A01

4-5-1Page 4

Apr 01/13


**ON A/C A330-200 A330-200F


L = 75 m (250 ft)


TURN R = 45 m(150 ft)

(15 ft)APPROX 4.5 m

45 m(150 ft)

23 m(75 ft)

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

NLG PATH

MLG PATH

F_AC_040501_1_0070101_01_00


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

4-5-1Page 5

Apr 01/13



**ON A/C A330-200 A330-200F A330-300

90˚ Turn - Runway to Taxiway

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

4-5-2Page 1

Apr 01/13


**ON A/C A330-300

45 m(150 ft)

23 m(75 ft)

(45 ft)APPROX 13.8 m


TURN R = 45 m(150 ft)

FAA LEAD−IN FILLETL = 75 m (250 ft)


NLG PATH

MLG PATH

F_AC_040502_1_0010101_01_01

RUNWAYCENTERLINE

TAXIWAYCENTERLINE


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

4-5-2Page 2

Apr 01/13


**ON A/C A330-300


23 m(75 ft)

TURN R = 45 m(150 ft)

(17 ft)APPROX 5.1 m


45 m(150 ft) NLG PATH

MLG PATH

F_AC_040502_1_0080101_01_00

RUNWAYCENTERLINE

TAXIWAYCENTERLINE


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

4-5-2Page 3

Apr 01/13


**ON A/C A330-200 A330-200F



TURN R = 45 m

45 m(150 ft)

23 m(75 ft)



NLG PATH

MLG PATH

(150 ft)

F_AC_040502_1_0020101_01_01

RUNWAYCENTERLINE

TAXIWAYCENTERLINE


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

4-5-2Page 4

Apr 01/13


**ON A/C A330-200 A330-200F

(24 ft)APPROX 7.3 m


TURN R = 45 m(150 ft)

(150 ft)


23 m(75 ft)

NLG PATH

MLG PATH

45 m

F_AC_040502_1_0090101_01_00

RUNWAYCENTERLINE

TAXIWAYCENTERLINE


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

4-5-2Page 5

Apr 01/13


4-5-3 180˚ Turn on a Runway

**ON A/C A330-200 A330-200F A330-300

180˚ Turn on a Runway

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

4-5-3Page 1

Apr 01/13


**ON A/C A330-300

R4 = 41.6 m(136 ft)

R6 = 33.1 m(109 ft)

R3 = 27.6 m(91 ft)

R5 = 33.7 m(111 ft)

4.5 m(15 ft)

4.5 m(15 ft)

NLG PATH

MLG PATH

NOSE TIP PATH

WING TIP PATH

TAIL TIP PATHNOTE:

TYPE 1 VALUES FOR MAX STEERING ANGLE = 72°.

RUNWAY CENTERLINE

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


F_AC_040503_1_0130101_01_01

180˚ Turn on a RunwayFIGURE-4-5-3-991-013-A01

4-5-3Page 2

Apr 01/13


**ON A/C A330-200 A330-200F

R4 = 40.4 m(133 ft)

R6 = 34.9 m(115 ft)

R3 = 24.1 m(79 ft)

R5 = 30.2 m(99 ft)

NLG PATH

MLG PATH

NOSE TIP PATH

WING TIP PATH

TAIL TIP PATHNOTE:

TYPE 1 VALUES FOR MAX STEERING ANGLE = 72°.


4.5 m(15 ft)

RUNWAY CENTERLINE

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

4.5 m(15 ft)

F_AC_040503_1_0140101_01_01

180˚ Turn on a RunwayFIGURE-4-5-3-991-014-A01

4-5-3Page 3

Apr 01/13



**ON A/C A330-200 A330-200F A330-300

135˚ Turn - Taxiway to Taxiway

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

4-5-4Page 1

Apr 01/13


**ON A/C A330-300



TAXIWAY CENTERLINE

TURN R = 45 m(150 ft)

APPROX 5.3 m(17 ft)


L = 75 m (250 ft)

23 m(75 ft)

TAXIWAY CENTERLINE

(75 ft)23 m

NLG PATH

MLG PATH

F_AC_040504_1_0030101_01_01

135˚ Turn - Taxiway to TaxiwayJudgemental Oversteer Method

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

4-5-4Page 2

Apr 01/13


**ON A/C A330-300

(75 ft)23 m


APPROX 2.5 m(8 ft)

TAXIWAY CENTERLINE

TURN R = 45 m(150 ft)


L = 75 m (250 ft)

ADDITIONAL FILLET TO MEET4.5 m (15 ft) EDGE CLEARANCE

TAXIWAY CENTERLINE

23 m(75 ft)

NLG PATH

MLG PATH

F_AC_040504_1_0070101_01_00

135˚ Turn - Taxiway to TaxiwayCockpit Over Centerline Method

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

4-5-4Page 3

Apr 01/13


**ON A/C A330-200 A330-200F

(75 ft)23 m


APPROX 13 m(43 ft)

TAXIWAY CENTERLINE

TURN R = 45 m(150 ft)

APPROX 6.3 m(21 ft)


L = 75 m (250 ft)

23 m(75 ft)

TAXIWAY CENTERLINE

NLG PATH

MLG PATH

F_AC_040504_1_0040101_01_01


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

4-5-4Page 4

Apr 01/13


**ON A/C A330-200 A330-200F


APPROX 5.5 m(18 ft)

TAXIWAY CENTERLINE

TURN R = 45 m(150 ft)


L = 75 m (250 ft)

TAXIWAY CENTERLINE 23 m(75 ft)

(75 ft)23 m

NLG PATH

MLG PATH

F_AC_040504_1_0080101_01_00


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

4-5-4Page 5

Apr 01/13



**ON A/C A330-200 A330-200F A330-300

90˚ Turn - Taxiway to Taxiway

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

4-5-5Page 1

Apr 01/13


**ON A/C A330-300

TAXIWAY CENTERLINE

(75 ft)

TAXIWAY CENTERLINEAPPROX 12.2 m

(40 ft)


TURN R = 45 m(150 ft)



23 m

23 m(75 ft)

NLG PATH

MLG PATH

F_AC_040505_1_0030101_01_01


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

4-5-5Page 2

Apr 01/13


**ON A/C A330-300

APPROX 3.8 m(12 ft)

4.5 m (15 ft) EDGE CLEARANCEADDITIONAL FILLET TO MEET


TURN R = 45 m(150 ft)


TAXIWAY CENTERLINE

(75 ft)23 m NLG PATH

MLG PATH

TAXIWAY CENTERLINE

23 m(75 ft)

F_AC_040505_1_0100101_01_00


FIGURE-4-5-5-991-010-A01

4-5-5Page 3

Apr 01/13


**ON A/C A330-200 A330-200F

TAXIWAY CENTERLINE

TAXIWAY CENTERLINE

APPROX 13 m(43 ft)


TURN R = 45 m(150 ft)


(75 ft)


23 m

23 m(75 ft)

NLG PATH

MLG PATH

F_AC_040505_1_0040101_01_01


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

4-5-5Page 4

Apr 01/13


**ON A/C A330-200 A330-200F

23 m(75 ft)

TAXIWAY CENTERLINE(20 ft)APPROX 6.2 m


TAXIWAY CENTERLINE


23 m(75 ft)

TURN R = 45 m(150 ft)

NLG PATH

MLG PATH

F_AC_040505_1_0110101_01_00


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

4-5-5Page 5

Apr 01/13


4-6-0 Runway Holding Bay (Apron)

**ON A/C A330-200 A330-200F A330-300

Runway Holding Bay (Apron)

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

4-6-0Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

6.1 m(20 ft)

6.1 m(20 ft)

COORDINATE WITH USING AIRPLANE FOR SPECIFICPLANNED OPERATING PROCEDURES.

NOTES:

12.2 m(40 ft)

45 m(150 ft)

RUNWAYCENTERLINE

TAXIWAYCENTERLINE

23 m(75 ft)

190 m(625 ft)

90 m(300 ft)

HOLDINGPOINT

F_AC_040600_1_0010101_01_01

97.3 m(319 ft)

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

4-6-0Page 2

Apr 01/13


4-7-0 Aircraft Parking

**ON A/C A330-200 A330-200F A330-300

Airplane Parking

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

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

4-7-0Page 1

Apr 01/13


**ON A/C A330-300

73.85

PARKING45° ENTRY PUSH OUT

PARKINGSTRAIGHT ENTRY PUSH BACK


67.2356

.53 68

.26

82.5

7

96.76

F_AC_040700_1_0010101_01_00

Airplane ParkingSteering Geometry

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

4-7-0Page 2

Apr 01/13


**ON A/C A330-300

100.7773

.85

PARKINGPARALLEL IN POWER OUT

PARKING45° ENTRY POWER OUT

95.89

72.0

2

F_AC_040700_1_0020101_01_00


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

4-7-0Page 3

Apr 01/13


**ON A/C A330-300

0

20

40

60

80

100

120

140

160

180

200

220

240

260

280

300

10

20

30

40

50

60

70

80

90

100

0 10 20 30 40 50 60 70 80 90 100 110

0 20 40 60 80 100 120 140 160 180 200 220 240 260 280 300 320 340

DISTANCE ALONG TERMINAL (m)

DISTANCE ALONG TERMINAL (ft)

(m)

DISTANCE OUTFROM TERMINAL

45° ENTRY PUSH OUT

STRAIGHT ENTRY PUSH BACK

PARALLEL IN POWER OUT

45° ENTRY POWER OUT

90° ENTRY PUSH OUT

F_AC_040700_1_0040101_01_00

Airplane ParkingMinimum Parking Space Requirements

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

4-7-0Page 4

Apr 01/13


**ON A/C A330-200 A330-200F

PARKINGSTRAIGHT ENTRY PUSH BACK

93.68

82.1

6


63.89 75.3053

.39 66

.14


F_AC_040700_1_0030101_01_00


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

4-7-0Page 5

Apr 01/13


**ON A/C A330-200 A330-200F

73.8

5PARKING

PARALLEL IN POWER OUT

PARKING45° ENTRY POWER OUT

99.42

95.89

71.3

6

F_AC_040700_1_0050101_01_00


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

4-7-0Page 6

Apr 01/13


**ON A/C A330-200 A330-200F

0

20

40

60

80

100

120

140

160

180

200

220

240

260

280

300

10

20

30

40

50

60

70

80

90

100

0 10 20 30 40 50 60 70 80 90 100 110

0 20 40 60 80 100 120 140 160 180 200 220 240 260 280 300 320 340

DISTANCE ALONG TERMINAL (m)

DISTANCE ALONG TERMINAL (ft)

(m)

DISTANCE OUTFROM TERMINAL

PARALLEL IN POWER OUT45° ENTRY POWER OUT

90° ENTRY PUSH OUT

STRAIGHT ENTRY PUSH BACK

45° ENTRY PUSH OUT

F_AC_040700_1_0060101_01_00

Airplane ParkingMinimum Parking Space Requirements

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

4-7-0Page 7

Apr 01/13


TERMINAL SERVICING

5-0-0 TERMINAL SERVICING

**ON A/C A330-200 A330-200F A330-300

TERMINAL SERVICING

1. Terminal servicing

This chapter provides typical ramp layouts, corresponding minimum turnaround time estimations,locations of ground service points and service requirements.The information given in this chapter reflects ideal conditions. Actual ramp layouts and servicerequirements may vary according to local regulations, airline procedures and the airplane condition.

Section 5.1 shows typical ramp layouts for passenger aircraft at the gate or on an Open Apron andfreighter aircraft on an Open Apron.

Section 5.2 shows the minimum turnaround schedules for full servicing arrangements (turnroundstations).

Section 5.3 shows the minimum turnaround schedule for reduced servicing arrangements (en routestations).

Section 5.4 gives the locations of ground service connections, the standard of connections used andtypical capacities and requirements.

Section 5.5 provides the engine starting pneumatic requirements for different engine types anddifferent ambient temperatures.

Section 5.6 provides the air conditioning requirements for heating and cooling (pull-down and pull-up)using ground conditioned air for different ambient temperatures.

Section 5.7 provides the air conditioning requirements for heating and cooling to maintain a constantcabin air temperature using low pressure conditioned air.

Section 5.8 shows the ground towing requirements taking into account different ground surface andaircraft conditions.

5-0-0Page 1

Apr 01/13


5-1-0 Aircraft Servicing Arrangements

**ON A/C A330-200 A330-300

Airplane Servicing Arrangements

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

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

The associated turnaround station is given in the section 5-2-1 for Full Servicing Turn Round Charts.

The associated minimum turnaround time for Transit Turn Round Charts is given in a section 5-3-1.

5-1-0Page 1

Apr 01/13


**ON A/C A330-200F

Airplane Servicing Arrangements

1. Airplane Servicing Arrangements

This section provides typical ramp layouts, showing the various GSE items in position during typicalturnaround scenarios for the passenger aircraft.

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

The associated turnaround station is given in the section 5-2-1 for Full Servicing Turn Round Charts.

5-1-0Page 2

Apr 01/13


5-1-1 Symbols Used on Servicing Diagrams

**ON A/C A330-200 A330-200F A330-300

Symbols Used on Servicing Diagrams

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

Ground Support Equipment

AC AIR CONDITIONING UNITAS AIR START UNIT

BULK BULK TRAINCAT CATERING TRUCK

CB CONVEYOR BELTCLEAN CLEANING TRUCK

FUEL FUEL HYDRANT DISPENSER or TANKERGPU GROUND POWER UNIT

LD CL LOWER DECK CARGO LOADERLV LAVATORY VEHICLE

MD CL (A330-200F only) MAIN DECK CARGO LOADER

PBB PASSENGER BOARDING BRIDGEPS PASSENGER STAIRS

TOW TOW TRACTORULD ULD TRAINWV POTABLE WATER VEHICLE

5-1-1Page 1

Apr 01/13


5-1-2 Typical Ramp Layout - Open Apron

**ON A/C A330-200 A330-300

Typical Ramp Layout - Open Apron

1. This section gives the typical servicing arrangements on the open apron, for the passenger version ofthe aircraft.The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m (24.61 ft) fromthe aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).

5-1-2Page 1

Apr 01/13


**ON A/C A330-200

GPU

TOW

PS CAT

PS CAT

AS

CATPS

AC LD CL

LD CL

LV

WVULD BULK

FUEL

ULD

FUEL

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

CB

STAND SAFETY LINE

F_AC_050102_1_0010101_01_02

Typical Ramp LayoutOpen Apron

FIGURE-5-1-2-991-001-A01

5-1-2Page 2

Apr 01/13


**ON A/C A330-300

GPU

TOW

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

CATPS

PS CAT

CATPS

AS

ULD

ULD

CB BULK

LV

FUELFUEL

ACLD CL

LD CL

WV

STAND SAFETY LINE

F_AC_050102_1_0070101_01_01


FIGURE-5-1-2-991-007-A01

5-1-2Page 3

Apr 01/13


**ON A/C A330-200F

Typical Ramp Layout - Open Apron

1. This section gives the typical servicing arrangements on the open apron, for the cargo version of theaircraft.The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m (24.61 ft) fromthe aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).

5-1-2Page 4

Apr 01/13


**ON A/C A330-200F

WV

PS

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

GPU

AS

LD CL

ULD

BULKULDCB

FUELFUEL

TOW

STAND SAFETY LINE

MD CL

LV

ULDLD CL

AC

F_AC_050102_1_0020101_01_03


FIGURE-5-1-2-991-002-A01

5-1-2Page 5

Apr 01/13


5-1-3 Typical Ramp Layout - Gate

**ON A/C A330-200 A330-300

Typical Ramp Layout - Gate

1. This section gives the typical servicing arrangements in the gate area for the passenger version of theaircraft, with two Passenger Boarding Bridges.The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m (24.61 ft) fromthe aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).

5-1-3Page 1

Apr 01/13


**ON A/C A330-200

CAT

CAT

CLEAN CAT

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

GP

U

AS

AC

ULDLD CL

LD CL

ULD

LV

BULKCB

FUELFUEL

PBB

PBB

TOW

WV

STAND SAFETY LINE

F_AC_050103_1_0010101_01_02

Typical Ramp LayoutGate

FIGURE-5-1-3-991-001-A01

5-1-3Page 2

Apr 01/13


**ON A/C A330-300

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

AS

GP

U

AC LD CL

CAT

CAT

CAT

LD CL

LV

CLEAN

WV

BULK

ULD

CB

FUEL FUEL

PBB

PBB

TOW

ULD

STAND SAFETY LINE

F_AC_050103_1_0060101_01_01

Typical Ramp LayoutGate

FIGURE-5-1-3-991-006-A01

5-1-3Page 3

Apr 01/13


5-2-0 Terminal Operations - Full Servicing

**ON A/C A330-300

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.

2. Assumptions for full servicing turn-round time chart

A. PASSENGER HANDLING332 pax (30 B/C + 302 Y/C)All passengers deboard and board the aircraft2 Passenger Boarding Bridges (PBB) used at doors L1 and L2Equipment positioning/removal + opening/closing door = 3 minNo Passenger with Reduced Mobility (PRM) on board

Deboarding:- 166 pax at door L1 (30 B/C and 136 Y/C)- 166 pax at door L2 (166 Y/C)- Deboarding rate = 25 pax/min per door- Priority deboarding for premium passengers

Boarding:- 166 pax at door L1 (30 B/C and 136 Y/C)- 166 pax at door L2 (166 Y/C)- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min

B. CARGO2 cargo loaders + 1 belt loaderEquipment positioning/removal + opening/closing door = 2.5 min

Cargo exchange:- 6 LD3 + 2 pallets in AFT cargo compartment- 12 LD3 + 2 pallets in FWD cargo compartment- 1 000 kg (2 205 lb) in bulk cargo compartment

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

Pallet off-loading/loading times:- Off-loading = 2.4 min/pallet

5-2-0Page 1

Apr 01/13


- Loading = 2.8 min/pallet

Bulk off-loading/loading times:- Off-loading = 9.2 min/t- Loading = 10.5 min/t

C. REFUELLINGBlock-fuel quantity for nominal range through 2 nozzles90 000 l (23 775 US gal) at 50 psi (3.45 bar)Dispenser positioning/removal = 3 min

D. CLEANINGPerformed in available time

E. CATERING3 catering trucks for servicing galleys at doors R1, R2 and R4Equipment positioning + door opening = 5 minEquipment removal + door closing = 3 minFull Size Trolley Equivalent (FSTE) to unload and load: 39 FSTE- 8 FSTE at door R1- 13 FSTE at door R2- 18 FSTE at door R4Time for trolley exchange = 1.5 min per FSTE

F. GROUND HANDLING/SERVICINGStart of operations:- Bridges: t0 = 0- Others: t0 + 1 min

Vehicle positioning/removal = 2 min (except for fuel and catering trucks)Ground Power Unit (GPU): up to 2 × 90 kVAAir conditioning: two hosesPotable water servicing: 100% uplift, 700 l (185 US gal) at 60 l/min (15.85 US gal/min)Toilet servicing: draining + rinsing

5-2-0Page 2

Apr 01/13


**ON A/C A330-300

GSE POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH

TRT: 55 min

100 20 30 40 50 60 70

AT L1DEBOARDING/BOARDING

HEADCOUNTING

CATERING AT R2

CLEANING

CARGO FWD CC

BULK

REFUELLING

POTABLE WATER SERVICING

TOILET SERVICING

DEBOARDING/BOARDINGAT L2

CATERING AT R4

CARGO AFT CC

CATERING AT R1

AVAILABLE TIME

F_AC_050200_1_0010201_01_00

Full Servicing Turn-Round Time ChartFIGURE-5-2-0-991-001-B01

5-2-0Page 3

Apr 01/13


**ON A/C A330-200

Terminal Operations -- Full Servicing Turn-Round Time



A. PASSENGER HANDLING293 pax (30 B/C + 263 Y/C)All passengers deboard and board the aircraft2 Passenger Boarding Bridges (PBB) used at doors L1 and L2Equipment positioning/removal + opening/closing door = 3 minNo Passenger with Reduced Mobility (PRM) on board

Deboarding:- 146 pax at door L1 (30 B/C and 116 Y/C)- 147 pax at door L2 (147 Y/C)- Deboarding rate = 25 pax/min per door- Priority deboarding for premium passengers

Boarding:- 146 pax at door L1 (30 B/C and 116 Y/C)- 147 pax at door L2 (147 Y/C)- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min

B. CARGO2 cargo loaders + 1 belt loaderEquipment positioning/removal + opening/closing door = 2.5 min

Cargo exchange:- 6 LD3 + 2 pallets in AFT cargo compartment- 8 LD3 + 2 pallets in FWD cargo compartment- 1 000 kg (2 205 lb) in bulk cargo compartment


Pallet off-loading/loading times:- Off-loading = 2.4 min/pallet- Loading = 2.8 min/pallet

5-2-0Page 4

Apr 01/13





E. CATERING3 catering trucks for servicing galleys at doors R1, R2 and R4Equipment positioning + door opening = 5 minEquipment removal + door closing = 3 minFull Size Trolley Equivalent (FSTE) to unload and load: 36 FSTE- 10 FSTE at door R1- 9 FSTE at door R2- 17 FSTE at door R4Time for trolley exchange = 1.5 min per FSTE


Vehicle positioning/removal = 2 min (except for fuel and catering trucks)Ground Power Unit (GPU): up to 2 × 90 kVAAir conditioning: two hosesPotable water servicing: 100% uplift, 700 l (185 US gal) at 60 l/min (15.85 US gal/min)Toilet servicing: draining + rinsing

5-2-0Page 5

Apr 01/13


**ON A/C A330-200


ACTIVITY

CRITICAL PATH

TRT: 51 min

100 20 30 40 50 60 70


HEADCOUNTING

CATERING AT R2

CLEANING

CARGO FWD CC

BULK

REFUELLING


TOILET SERVICING

DEBOARDING/BOARDINGAT L2

CATERING AT R4

CARGO AFT CC

CATERING AT R1

AVAILABLE TIME

F_AC_050200_1_0080101_01_00

Full Servicing Turn-Round Time ChartFIGURE-5-2-0-991-008-A01

5-2-0Page 6

Apr 01/13


**ON A/C A330-200F

Terminal Operations - Full Servicing Turn-Round Time



A. COURIER HANDLING4 CouriersDoor used: L1

B. CARGO100% cargo exchangeMain deck cargo compartment: 22 palletsLower deck AFT cargo compartment: 4 palletsLower deck FWD cargo compartment: 2 LD3 + 4 palletsLower deck bulk cargo compartment: 1 000 kg (2 205 lb)


Pallet off-loading/loading times:- Off-loading = 2.4 min/pallet- Loading = 2.8 min/pallet




E. CATERINGCatering of galley (if installed) is performed through door L1 (standard units only) and inavailable time.

F. GROUND HANDLING/SERVICINGStart of operations:- Stairs: t0 = 0- Others: t0 + 1 min

5-2-0Page 7

Apr 01/13


Vehicle positioning/removal = 2 min (fuel truck excluded)Ground Power Unit (GPU): up to 2 × 90 kVAAir conditioning: two hosesPotable water servicing: 100% uplift, 700 l (185 US gal) at 60 l/min (15.85 US gal/min)Toilet servicing: draining + rinsing

5-2-0Page 8

Apr 01/13


**ON A/C A330-200F


ACTIVITY

TRT: 62 min

100 20 30 40 50 60 70


CARGO FWD CC

BULK

REFUELLING


TOILET SERVICING

CATERING AT L1

CARGO AFT CC

CLEANING

CARGO MD

AVAILABLE TIME

AVAILABLE TIME

F_AC_050200_1_0090101_01_00

Full Servicing Turn-Round Time ChartFIGURE-5-2-0-991-009-A01

5-2-0Page 9

Apr 01/13


5-3-0 Terminal Operations - Transit

**ON A/C A330-300

Terminal Operations - Minimum Servicing Turn-Round Time


2. Assumptions for minimum servicing turn-round time chart

A. PASSENGER HANDLING332 pax (30 B/C + 302 Y/C)50% of passengers deboard and board the aircraft1 Passenger Boarding Bridge (PBB) used at door L1Equipment positioning/removal + opening/closing door = 3 minNo Passenger with Reduced Mobility (PRM) on board

Deboarding:- 166 pax at door L1- Deboarding rate = 25 pax/min per door

Boarding:- 166 pax at door L1- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min

B. CARGO1 cargo loader + 1 belt loaderEquipment positioning/removal + opening/closing door = 2.5 min

Cargo exchange:- 5 LD3 in AFT cargo compartment- 500 kg (1 102 lb) in bulk cargo compartment



C. REFUELLINGRefuelling through 2 nozzles30% of max capacity at 50 psi (3.45 bar)

5-3-0Page 1

Apr 01/13


Dispenser positioning/removal = 3 min


E. CATERING1 catering truck for servicing galleys as requiredEquipment positioning + door opening = 5 minEquipment removal + door closing = 3 minPerformed in available timeTime for trolley exchange = 1.5 min per FSTE


Vehicle positioning/removal = 2 min (except for fuel and catering trucks)Ground Power Unit (GPU): up to 2 × 90 kVAAir conditioning: two hosesNo potable water servicingNo toilet servicing

5-3-0Page 2

Apr 01/13


**ON A/C A330-300

TRT: 34 min

50 10 15 20 25 30 35


HEADCOUNTING

CLEANING

CARGO FWD CC

BULK

REFUELLING


TOILET SERVICING

CATERING

CARGO AFT CC

40


ACTIVITY

CRITICAL PATH

AVAILABLE TIME

F_AC_050300_1_0010201_01_00

Minimum Servicing Turn-Round TimeFIGURE-5-3-0-991-001-B01

5-3-0Page 3

Apr 01/13


**ON A/C A330-200

Terminal Operations - Minimum Servicing Turn-Round Time


2. Assumptions for minimum servicing turn-round time chart

A. PASSENGER HANDLING293 pax (30 B/C + 263 Y/C)50% of passengers deboard and board the aircraft1 Passenger Boarding Bridge (PBB) used at door L1Equipment positioning/removal + opening/closing door = 3 minNo Passenger with Reduced Mobility (PRM) on board

Deboarding:- 147 pax at door L1- Deboarding rate = 25 pax/min per door

Boarding:- 147 pax at door L1- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min

B. CARGO1 cargo loader + 1 belt loaderEquipment positioning/removal + opening/closing door = 2.5 min

Cargo exchange:- 5 LD3 in AFT cargo compartment- 500 kg (1 102 lb) in bulk cargo compartment



C. REFUELLINGRefuelling through 2 nozzles30% of max capacity at 50 psi (3.45 bar)Dispenser positioning/removal = 3 min

5-3-0Page 4

Apr 01/13



E. CATERING1 catering truck for servicing galleys as requiredEquipment positioning + door opening = 5 minEquipment removal + door closing = 3 minPerformed in available timeTime for trolley exchange = 1.5 min per FSTE


Vehicle positioning/removal = 2 min (except for fuel and catering trucks)Ground Power Unit (GPU): up to 2 × 90 kVAAir conditioning: two hosesNo potable water servicingNo toilet servicing

5-3-0Page 5

Apr 01/13


**ON A/C A330-200

TRT: 32 min

50 10 15 20 25 30 35


HEADCOUNTING

CLEANING

CARGO FWD CC

BULK

REFUELLING


TOILET SERVICING

CATERING

CARGO AFT CC

40

AVAILABLE TIME


ACTIVITY

CRITICAL PATH

F_AC_050300_1_0040101_01_00

Minimum Servicing Turn-Round TimeFIGURE-5-3-0-991-004-A01

5-3-0Page 6

Apr 01/13


5-4-1 Ground Service Connections Layout

**ON A/C A330-200 A330-300

Ground Service Connections Layout

1. This section gives the ground service connections layout.

5-4-1Page 1

Apr 01/13


**ON A/C A330-200 A330-300

1 17 2 3 6 7 11 3 14 15 16

16

15

143131017

111217

8

17

76

517

1 2 3 4

17

8

67

9

9

1 − OXYGEN SYSTEM2 − GROUND ELECTRICAL POWER CONNECTORS3 − POTABLE WATER DRAIN4 − LOW PRESSURE AIR PRE−CONDITIONING

AND ENGINE STARTING6 − ENGINE OIL FILLING7 − IDG OIL FILLING8 − PRESSURE REFUEL/DEFUEL COUPLINGS9 − OVERWING REFUEL

5 − HIGH PRESSURE AIR PRE−CONDITIONING12 − HYD RESERVOIR AIR PRESSURIZATION AND

GROUND POWER SUPPLY (BLUE)

14 − POTABLE WATER SERVICE PANEL15 − TOILET AND WASTE SERVICE PANEL16 − APU OIL FILLING17 − GROUNDING POINTS

13 − REFUEL/DEFUEL PANEL

11 − HYD RESERVOIR FILLING AND GROUND POWER SUPPLY (GREEN)

10 − HYDRAULIC GROUND POWER SUPPLY (YELLOW)

F_AC_050401_1_0010101_01_01

Ground Service Connections LayoutFIGURE-5-4-1-991-001-A01

5-4-1Page 2

Apr 01/13


**ON A/C A330-200F

Ground Service Connections Layout

1. This section gives the ground service connections layout.

5-4-1Page 3

Apr 01/13


**ON A/C A330-200F

1 − OXYGEN SYSTEM2 − GROUND ELECTRICAL POWER CONNECTORS3 − LOW PRESSURE AIR PRE−CONDITIONING4 − HIGH PRESSURE AIR PRE−CONDITIONING

5 − ENGINE OIL FILLING6 − IDG OIL FILLING7 − PRESSURE REFUEL/DEFUEL COUPLINGS8 − OVERWING REFUEL9 − HYDRAULIC GROUND POWER SUPPLY (YELLOW)

AND ENGINE STARTING11 − HYD RESERVOIR AIR PRESSURIZATION AND

GROUND POWER SUPPLY (BLUE)

13 − POTABLE WATER SERVICE PANEL14 − TOILET AND WASTE SERVICE PANEL15 − APU OIL FILLING16 − GROUNDING POINTS

12 − REFUEL/DEFUEL PANEL

10 − HYD RESERVOIR FILLING AND GROUND POWER SUPPLY (GREEN)

14 16 2 1 13 5 6 10 15

15

16 2 1

14 13 3 4

56

7

816

56

78

16

16

129

11

16

10

F_AC_050401_1_0020101_01_02

Ground Service Connections LayoutFIGURE-5-4-1-991-002-A01

5-4-1Page 4

Apr 01/13


5-4-2 Grounding Points

**ON A/C A330-200 A330-200F A330-300

Grounding Points

**ON A/C A330-200 A330-200F

1. Grounding Points.

DISTANCE : Meters (ft)

FROM AIRPLANE CENTERLINE

AFT OF NOSER SIDE L SIDE

MEANHEIGHTFROMGROUND

On Nose Landing Gear leg :6.67 m(21.88 ft) on centerline

1.40 m(4.59 ft)

On left Main Landing Gearleg :

28.37 m(93.08 ft)

5.34 m(17.52 ft)

1.50 m(4.92 ft)

On right Main LandingGear leg :

28.37 m(93.08 ft)

5.34 m(17.52 ft)

1.50 m(4.92 ft)

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

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

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

**ON A/C A330-300

2. Grounding Points.


FROM AIRPLANE CENTERLINE

AFT OF NOSER SIDE L SIDE

MEANHEIGHTFROMGROUND

5-4-2Page 1

Apr 01/13



On Nose Landing Gear leg :6.67 m(21.88 ft) on centerline

1.40 m(4.59 ft)

On left Main Landing Gearleg :

31.53 m(103.44 ft)

5.34 m(17.52 ft)

1.50 m(4.92 ft)

On right Main LandingGear leg :

31.53 m(103.44 ft)

5.34 m(17.52 ft)

1.50 m(4.92 ft)

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

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

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

5-4-2Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

(1)(2)

LANDINGGEAR

GROUND CABLE(OPTIONAL)

GROUNDINGPOINT

GROUNDINGPOINT

NOSE GEAR MAIN GEAR

AA

A

F_AC_050402_1_0010101_01_00

Ground Service ConnectionsGrounding Points

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

5-4-2Page 3

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

NOTE:

RIB22

RIB23

A

A

R SIDE SYMETRICAL

B

A

B

F_AC_050402_1_0020101_01_00

Ground Service ConnectionsGrounding Points

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

5-4-2Page 4

Apr 01/13


5-4-3 Hydraulic System

**ON A/C A330-200 A330-200F A330-300

Hydraulic System

1. Ground Service Panels

DISTANCEFROM AIRCRAFT CENTERLINEACCESS

AFT OF NOSERH SIDE LH SIDE

MEAN HEIGHTFROM GROUND

Green System:(Access Door197CB)

41.3 m(135.5 ft)

- 1.34 m(4.4 ft)

2.23 m(7.32 ft)

Yellow System:(Access Door196BB)

35.4 m(116.14 ft)

1.3 m(4.27 ft)

- 1.95 m(6.4 ft)

Blue System:(Access Door195BB)

34.41 m(112.89 ft)

- 1.28 m(4.2 ft)

1.94 m(6.36 ft)

2. Reservoir Pressurization

DISTANCEFROM AIRCRAFT CENTERLINEACCESS



One 1/4 in. self-sealing connectioncommon to the 3reservoirs(Blue SystemGround ServicePanel):(Access Door195BB)

34.47 m(113.09 ft)

- 1.41 m(4.63 ft)

1.89 m(6.2 ft)

**ON A/C A330-200 A330-200F

3. Accumulator Charging

Five connections (one for each accumulator):

5-4-3Page 1

Apr 01/13


DISTANCEFROM AIRCRAFT CENTERLINE

ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHTFROM

GROUNDYellow SystemAccumulator:(Access Door 196BB)

35.55 m(116.63 ft)

1.43 m(4.69 ft)

-1.91 m(6.27 ft)

Green SystemAccumulator:(Access Door 197CB)

41.52 m(136.22 ft)

-1.33 m(4.36 ft)

2.19 m(7.19 ft)

Blue System Accumulator:(Access Door 195BB)

34.54 m(113.32 ft)

-1.38 m(4.53 ft)

1.9 m(6.23 ft)

Blue System BrakeAccumulator:(Access Door 195BB)

34.54 m(113.32 ft)

-1.24 m(4.07 ft)

1.9 m(6.23 ft)

**ON A/C A330-300

4. Accumulator Charging

Five connections (one for each accumulator):


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHTFROM

GROUNDYellow SystemAccumulator:(Access Door 196BB)

35.55 m(116.63 ft)

1.43 m(4.69 ft)

-1.91 m(6.27 ft)

Green SystemAccumulator:(Access Door 197CB)

41.52 m(136.22 ft)

-1.33 m(4.36 ft)

2.19 m(7.19 ft)

Blue System Accumulator:(Access Door 195BB)

34.54 m(113.32 ft)

-1.38 m(4.53 ft)

1.9 m(6.23 ft)

Blue System BrakeAccumulator:(Access Door 195BB)

34.54 m(113.32 ft)

-1.18 m(3.87 ft)

1.9 m(6.23 ft)

5-4-3Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

5. Reservoir Filling

Two connections (one self-sealing connection for pressurized supply on the Green system groundservice panel).


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHTFROM

GROUNDOne handpump fillingconnection(Access Door 197CB)

41.31 m(135.53 ft)

-1.3 m

(4.27 ft)2.11 m(6.92 ft)

6. Reservoir Drain

One 3/8 in. self-sealing connection on the reservoir for:


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHTFROM

GROUND

Yellow System29.03 m(95.24 ft)

2.12 m(6.96 ft)

-2.4 m

(7.87 ft)

Green System33.17 m

(108.83 ft)-

0.7 m(2.3 ft)

3.8 m(12.47 ft)

Blue System29.03 m(95.24 ft)

-2.12 m(6.96 ft)

2.4 m(7.87 ft)

7. Ground Test

Three 1 in. self-sealing connections and three 1-1/2 in. self-sealing connections (one pair per system).


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUNDGreen System GroundService Panel:(Access Door 197CB)

34.92 m(114.57 ft)

-1.35 m(4.43 ft)

2.2 m(7.22 ft)

5-4-3Page 3

Apr 01/13



ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUNDYellow System GroundService Panel:(Access Door 196BB)

29.03 m(95.24 ft)

1.3 m(4.27 ft)

-2 m

(6.56 ft)

Blue System GroundService Panel:(Access Door 195BB)

28.03 m(91.96 ft)

-1.28 m(4.2 ft)

2 m(6.56 ft)

5-4-3Page 4

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

MAN SELECTORVALVE−RSVR

FILLING

LEVER HANDPUMP

GND CNCTR−SELFSEALING RSVR

FILLING

HAND PUMPRSVR FILLING

FILTER−RSVRFILLING

RSVRFILLING VALVE

GND CNCTR−SELFSEALING, G SUCTION

GND CNCTR−SELFSEALING, G DELIVERY

VALVE−MANDEPRESS, G−RSVR

HYDRSVR FILLINGADJUSTMENT

INDICATOR

PRESS GAGEG POWER ACCU

GND CNCTRNITROGEN CHARGING

G POWER ACCU

FWD

A

FR53.4 FR53.5197CB

A

F_AC_050403_1_0010101_01_00

Ground Service ConnectionsGreen System Ground Service Panel

FIGURE-5-4-3-991-001-A01

5-4-3Page 5

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

PRESS GAGEB POWER ACCU

GND CNCTRNITROGENCHARGING

B POWER ACCU

GND CNCTRSELF−SEALING,

B SUCTION

VALVE−MANDEPRESS, B RSVR

GND CNCTR−SELFSEALING,

B DELIVERY

GND CNCTRSELF−SEALING,

B/Y RSVR PRESS

GND CNCTRSELF−SEALING,G RSVR PRESS

PRESS GAGESPARK BRK ACCU

PARK BRK ACCU

FWD

A

195BBFR44 FR45

A

F_AC_050403_1_0020101_01_00

Ground Service ConnectionsBlue System Ground Service Panel

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

5-4-3Page 6

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

SIGHTGLASSCARGO DOOR

SELECTOR MANIFOLD

HAND PUMPCARGO DOORS, Y RAT STOW PANEL

GND CNCTR−SELFSEALING, Y SUCTION

VALVE−MANDEPRESS, Y RSVR

GND CNCTR−SELFSEALING, Y DELIVERY

PRESS GAGEY POWER ACCU

GND CNCTRNITROGEN CHARGING

Y POWER ACCU

FWD

A

196BBFR46FR47

A

F_AC_050403_1_0030101_01_00

Ground Service ConnectionsYellow System Ground Service Panel

FIGURE-5-4-3-991-003-A01

5-4-3Page 7

Apr 01/13


5-4-4 Electrical System

**ON A/C A330-200 A330-200F A330-300

Electrical System

**ON A/C A330-200 A330-300

1. Electrical System


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUND

A/C External Power:Access Door 121EL

7.2 m(23.62 ft) On centerline

1.98 m(6.50 ft)

NOTE : Distances are approximate.

2. Technical Specifications

A. External Power Receptacles:- Two standard ISO 461 receptacles - 90 kVA each.

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

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

D. Electrical Loads in Ground ConfigurationIn ground configuration, in addition to the power necessary for maintenance, all the circuits,except those which are directly connected to the engines, are supplied as in flight. In theseconditions, the maximum power on the ground is approximately 105 kVA; this value does nottake into account the supply of the galleys, which according to the aircraft interior layout, mayreach 90 kVA.

E. Electrical Power necessary for Maintenance at Line Stop and Workshops:- Hydraulic electric-pumps: 20 × 3 kVA- Air Conditioning/ventilation: 49.5 kVA- Fuel pumps: 11.2 kVA- Lighting (commercial): 13.1 kVA- Lighting (technical): 2 kVA- Ice and rain protection: 11.3 kVA- Cargo loading: 12.6 kVA- AFS, flight controls, ADS, recorders: 3 kVA- Communications: 3.2 kVA

5-4-4Page 1

Apr 01/13


- Radio navigation: 1 kVA.

**ON A/C A330-200F

3. Electrical System


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUND

A/C External Power:Access Door 125EL

7.2 m(23.62 ft) On centerline

2.29 m(7.51 ft)



A. External Power Receptacles:- Two standard ISO 461 receptacles - 90 kVA each.

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

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

D. Electrical Loads in Ground ConfigurationIn ground configuration, in addition to the power necessary for maintenance, all the circuits,except those which are directly connected to the engines, are supplied as in flight. In theseconditions, the maximum power on the ground is approximately 105 kVA; this value does nottake into account the supply of the galleys, which according to the aircraft interior layout, mayreach 90 kVA.

E. Electrical Power necessary for Maintenance at Line Stop and Workshops:- Hydraulic electric-pumps: 20 × 3 kVA- Air Conditioning/ventilation: 49.5 kVA- Fuel pumps: 11.2 kVA- Lighting (commercial): 13.1 kVA- Lighting (technical): 2 kVA- Ice and rain protection: 11.3 kVA- Cargo loading: 12.6 kVA- AFS, flight controls, ADS, recorders: 3 kVA- Communications: 3.2 kVA- Radio navigation: 1 kVA.

5-4-4Page 2

Apr 01/13


**ON A/C A330-200 A330-300

B

FWD

FR19 FR18

B

A

A121EL

GROUND CONNECTOR925VU

F_AC_050404_1_0050101_01_00

Ground Service ConnectionsElectrical Service Panel

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

5-4-4Page 3

Apr 01/13


**ON A/C A330-200F

EXTERNAL POWER RECEPTACLES

A

B

FWD

GROUND CONNECTOR

B

FR17

FR19125EL

FR17 FR19

A

925VU

F_AC_050404_1_0010201_01_00

Ground Service ConnectionsElectrical Service Panel

FIGURE-5-4-4-991-001-B01

5-4-4Page 4

Apr 01/13


5-4-5 Oxygen System

**ON A/C A330-200 A330-200F A330-300

Oxygen System

**ON A/C A330-200 A330-300

1. Oxygen System


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUNDOxygen Replenishment(Option 1):Access Door 811

2.5 m(8.2 ft)

0.53 m(1.74 ft)

-3.2 m(10.5 ft)

Oxygen Replenishment(Option 2):Access Door 811

2.5 m(8.2 ft)

0.68 m(2.23 ft)

- 3.2 m(10.5 ft)

- 0 -- Basic: External charging in the avionic compartment- 1 -- Option- 2 -- Option.Zero, one or two service connections (external charging in the avionics compartment) MS22066 Std.

NOTE : Internal charging connection provided.

**ON A/C A330-200F

2. Oxygen System


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEAN HEIGHTFROM

GROUND

Oxygen Replenishment:Access Panel 132NW

11.26 m(36.94 ft)

2.5 m(8.2 ft)

- 4.2 m(13.78 ft)

- Basic: External charging in the FWD cargo compartment.One service connection (external charging in the FWD cargo compartment) MS22066 Std.

NOTE : Internal charging connection provided.

5-4-5Page 1

Apr 01/13


**ON A/C A330-200 A330-300

BA

B

OXYGENFILLING PORT

TESTPORT

FR7

FR10

Z120

A

811

FWD

FR4

FR7

NOTE:THE NUMBER OF OXYGEN CYLINDERS DEPENDS ON THE SYSTEM CONFIGURATION.

F_AC_050405_1_0010101_01_00

Ground Service ConnectionsOxygen System

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

5-4-5Page 2

Apr 01/13


**ON A/C A330-200F

OXYGENFILLING PORT

TESTPORTB

A

FR26

FR29

B

FR26132NW

NOTE:THE NUMBER OF OXYGEN CYLINDERS DEPENDS ON THE SYSTEM CONFIGURATION.

FR20

FR39.2

Z130

A

F_AC_050405_1_0020101_01_00

Ground Service ConnectionsOxygen System

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

5-4-5Page 3

Apr 01/13


5-4-6 Fuel System

**ON A/C A330-200 A330-200F A330-300

Fuel System

**ON A/C A330-200

1. Refuel/Defuel Access



MEAN HEIGHTFROM

GROUND

Refuel/Defuel Coupling,Left (Optional):Access Door 522HB

26.8 m(87.93 ft)

-12.6 m(41.34 ft)

5 m(16.4 ft)

Refuel/Defuel Coupling,Right:Access Door 622HB

26.8 m(87.93 ft)

12.6 m(41.34 ft)

-5 m(16.4 ft)

Overwing GravityRefuel Cap

31.3 m(102.69 ft)

17.2 m(56.43 ft)

17.2 m(56.43 ft)

5.8 m(19.03 ft)

A. Four standard 2.5 in. ISO 45 connections.

B. Two service connections (gravity refuel).

2. Refuel/Defuel Control Panel



MEAN HEIGHTFROM

GROUND

Refuel/Defuel ControlPanel:Access Door 198DB

31.1 m(102.03 ft)

0.8 m(2.62 ft)

-1.9 m(6.23 ft)

A. Flow rate: 1580 l/min (417 US gal/min) per connection.

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

5-4-6Page 1

Apr 01/13


3. Overpressure Protector and NACA Flame Arrestor



MEAN HEIGHTFROM

GROUND

Overpressure Protector36.3 m(119.09 ft)

27.17 m(89.14 ft)

27.17 m(89.14 ft)

5.75 m(18.86 ft)

NACA Flame Arrestor35.94 m(117.91 ft)

26.53 m(87.04 ft)

26.53 m(87.04 ft)

5.7 m(18.7 ft)

**ON A/C A330-300




MEAN HEIGHTFROM

GROUND


30 m(98.43 ft)

-12.6 m(41.34 ft)

5 m(16.4 ft)


30 m(98.43 ft)

12.6 m(41.34 ft)

-5 m(16.4 ft)


34.5 m(113.19 ft)

17.2 m(56.43 ft)

17.2 m(56.43 ft)

5.8 m(19.03 ft)






MEAN HEIGHTFROM

GROUND


34.3 m(112.53 ft)

0.8 m(2.62 ft)

-1.9 m(6.23 ft)



5-4-6Page 2

Apr 01/13





MEAN HEIGHTFROM

GROUND


27.17 m(89.14 ft)

27.17 m(89.14 ft)

5.75 m(18.86 ft)


26.53 m(87.04 ft)

26.53 m(87.04 ft)

5.7 m(18.7 ft)

**ON A/C A330-200F




MEAN HEIGHTFROM

GROUND


26.8 m(87.93 ft)

-12.6 m(41.34 ft)

5.1 m(16.73 ft)


26.8 m(87.93 ft)

12.6 m(41.34 ft)

-5.1 m(16.73 ft)


31.3 m(102.69 ft)

17.2 m(56.43 ft)

17.2 m(56.43 ft)

6.1 m(20.01 ft)






MEAN HEIGHTFROM

GROUND


31.1 m(102.03 ft)

0.8 m(2.62 ft)

-1.9 m(6.23 ft)



5-4-6Page 3

Apr 01/13





MEAN HEIGHTFROM

GROUND


27.17 m(89.14 ft)

27.17 m(89.14 ft)

5.75 m(18.86 ft)


26.53 m(87.04 ft)

26.53 m(87.04 ft)

5.7 m(18.7 ft)

5-4-6Page 4

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

OVERPRESSURE PROTECTOR

A

NACA FLAME ARRESTOR

FWD

LH SIDE SHOWNRH SIDE SYMMETRICAL

A

A

RIB36

RIB37

RIB38

550EB(650EB)

550DB(650DB)

B

C

B

C

F_AC_050406_1_0020101_01_00

Overpressure Protector and NACA Flame ArrestorFIGURE-5-4-6-991-002-A01

5-4-6Page 5

Apr 01/13


5-4-7 Pneumatic System

**ON A/C A330-200 A330-200F A330-300

Pneumatic System

**ON A/C A330-200 A330-200F

1. High Pressure Air Connection



MEANHEIGHTFROM

GROUND20.72 m(67.98 ft)

-0.84 m(2.76 ft)

1.96 m(6.43 ft)HP Connectors:

Access door 193CB 21.08 m(69.16 ft)

- 0.84 m(2.76 ft)

1.94 m(6.36 ft)

A. Connectors:- Two standard 3 in. ISO 2026 connections.

2. Low Pressure Air Connection



MEANHEIGHTFROM

GROUND19.29 m(63.29 ft)

-0.31 m(1.02 ft)

2.08 m(6.82 ft)LP Connectors:

Access door 191EB 19.29 m(63.29 ft)

- 0.76 m(2.49 ft)

2.11 m(6.92 ft)

A. Connectors:- Two standard 8 in. SAE AS4262 connections.

5-4-7Page 1

Apr 01/13


**ON A/C A330-300

3. High Pressure Air Connection



MEANHEIGHTFROM

GROUND23.9 m(78.41 ft)

- 0.84 m(2.76 ft)

1.79 m(5.87 ft)HP Connectors:

Access door 193CB 24.25 m(79.56 ft)

-0.84 m(2.76 ft)

1.79 m(5.87 ft)

A. Connectors:- Two standard 3 in. ISO 2026 connections.

4. Low Pressure Air Connection



MEANHEIGHTFROM

GROUND22.48 m(73.75 ft)

-0.31 m(1.02 ft)

1.86 m(6.1 ft)LP Connectors:

Access door 191EB 22.48 m(73.75 ft)

-0.76 m(2.49 ft)

0.76 m(2.49 ft)

A. Connectors:- Two standard 8 in. SAE AS4262 connections.

5-4-7Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

193CB

191EB

A

B

A

FR40

HP CONNECTOR

B

LP CONNECTOR

F_AC_050407_1_0010101_01_00

Ground Service ConnectionsLP and HP Ground Connectors

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

5-4-7Page 3

Apr 01/13


5-4-8 Potable Water System

**ON A/C A330-300

Potable Water System

1. Potable Water System


ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHTFROM

GROUND

Potable-Water Service Panel:Access Door 164AR

48.15 m(157.97 ft)

0.51 m(1.67 ft)

-3.15 m(10.33 ft)

FWD Drain Panel:Access Door 133BL

14.7 m(48.23 ft)

-0.6 m(1.97 ft)

1.9 m(6.23 ft)

AFT Drain Panel:Access Door 154AR

40.18 m(131.82 ft)

0.72 m(2.36 ft)

-2.46 m(8.07 ft)



A. Connections

(1) On the potable-water service panel (Access Door 164AR):- One heated 3/4 in. quick release filling connection- One heated 3/4 in. overflow and discharge connection- One ground pressurization connection.

(2) On the FWD drain panel (Access Door 133BL):- One standard 3/4 in. drain connection with back-up mechanical control.

(3) On the AFT drain panel (Access Door 154AR):- One standard 3/4 in. drain connection with back-up mechanical control- One standard 3/4 in. overflow and discharge connection with back-up mechanical

control.

B. Capacity- 700 l (184.92 US gal) standard- 1050 l (277.38 US gal) standard option.

C. Filling Pressure and Flow Rate

FWD tank:- Filling pressure: 50/125 psi (3.45/8.62 bar)- Flow rate: 45/73 l/min (11.89/19.28 US gal/min).

5-4-8Page 1

Apr 01/13


AFT tank:- Filling pressure: 50/125 psi (3.45/8.62 bar)- Flow rate: 56/85 l/min (14.79/22.45 US gal/min).

5-4-8Page 2

Apr 01/13


**ON A/C A330-300

164AR

154AR

133BL

A

B

C

DRAIN VALVECONTROL HANDLE

DRAIN NIPPLE

OVERFLOWNIPPLE

(FILL/DRAIN VALVE)OVERFLOW CONTROL HANDLE

(FILLING LINE DRAIN VALVE)DRAIN CONTROL HANDLE

DRAIN NIPPLE

FWD POTABLE−WATER DRAIN PANELAFT POTABLE−WATER DRAIN PANEL

CB

FR29

FR28

FR57.2

FR57.1

OVERFLOW NIPPLE

CAP

NIPPLE

CONTROL HANDLEFILL/DRAIN MAINTENANCE DOOR

LIMIT−SWITCH

FILL/DRAIN

A

POTABLE−WATER SERVICE PANEL

ASSEMBLY

GROUND AIRCONNECTION

FR70

FR69

F_AC_050408_1_0010101_01_00

Ground Service ConnectionsPotable-Water Ground Service Panels

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

5-4-8Page 3

Apr 01/13


**ON A/C A330-200




ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHTFROM

GROUND

Potable-Water Service Panel:Access Door 164AR

48.15 m(157.97 ft)

0.51 m(1.67 ft)

-3.15 m(10.33 ft)

FWD Drain Panel:Access Door 133BL

14.7 m(48.23 ft)

- 0.6 m(1.97 ft)

1.9 m(6.23 ft)

AFT Drain Panel:Access Door 154AR

40.18 m(131.82 ft)

0.72 m(2.36 ft)

-2.46 m(8.07 ft)



A. Connections

(1) On the potable-water service panel (Access Door 164AR):- One heated 3/4 in. quick release filling connection- One heated 3/4 in. overflow and discharge connection- One ground pressurization connection.

(2) On the FWD drain panel (Access Door 133BL):- One standard 3/4 in. drain connection with back-up mechanical control.

(3) On the AFT drain panel (Access Door 154AR):- One standard 3/4 in. drain connection with back-up mechanical control- One standard 3/4 in. overflow and discharge connection with back-up mechanical

control.

B. Capacity- 700 l (184.92 US gal) standard- 1050 l (277.38 US gal) standard option.

C. Filling Pressure and Flow Rate

FWD tank:- Filling pressure: 50/125 psi (3.45/8.62 bar)- Flow rate: 45/73 l/min (11.89/19.28 US gal/min).

AFT tank:

5-4-8Page 4

Apr 01/13


- Filling pressure: 50/125 psi (3.45/8.62 bar)- Flow rate: 56/85 l/min (14.79/22.45 US gal/min).

5-4-8Page 5

Apr 01/13


**ON A/C A330-200

164AR

154AR

133BL

A

B

C

DRAIN VALVECONTROL HANDLE

DRAIN NIPPLE

OVERFLOWNIPPLE

(FILL/DRAIN VALVE)OVERFLOW CONTROL HANDLE

(FILLING LINE DRAIN VALVE)DRAIN CONTROL HANDLE

DRAIN NIPPLE

FWD POTABLE−WATER DRAIN PANELAFT POTABLE−WATER DRAIN PANEL

CB

FR35

FR34

FR57

FR56

OVERFLOW NIPPLE

CAP

NIPPLE

CONTROL HANDLEFILL/DRAIN MAINTENANCE DOOR

LIMIT−SWITCH

FILL/DRAIN

APOTABLE−WATER SERVICE PANEL

ASSEMBLY

GROUND AIRCONNECTION

FR70

FR69

F_AC_050408_1_0030101_01_00

Ground Service ConnectionsPotable-Water Ground Service Panels

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

5-4-8Page 6

Apr 01/13


**ON A/C A330-200F




ACCESSAFT OF NOSE

RH SIDE LH SIDE

MEANHEIGHTFROM

GROUND

Potable-Water Service Panel:Access Door 133BL

14.03 m(46.03 ft)

-0.76 m(2.49 ft)

2.64 m(8.66 ft)



A. Connections

(1) On the potable-water service panel (Access Door 133BL):- One heated 3/4 in. quick release filling connection- One heated 3/4 in. overflow and discharge connection- One ground pressurization connection.

(2) On the drain panel (Access Door 133BL):- One standard 3/4 in. drain connection with back-up mechanical control.

B. Capacity- 100 l (26.42 US gal).

C. Filling Pressure and Flow Rate- Filling pressure: 50 psi (3.45 bar)- Flow rate: 45 l/min (11.89 US gal/min).

5-4-8Page 7

Apr 01/13


**ON A/C A330-200F

OVERFLOW NIPPLE

CAP

NIPPLE

CONTROL HANDLEFILL/DRAIN

MAINTENANCE DOORLIMIT−SWITCH

FILL/DRAIN

APOTABLE−WATER SERVICE PANEL

ASSEMBLY

FR34

FR33

133BL

A

F_AC_050408_1_0040101_01_00

Ground Service ConnectionsPotable-Water Ground Service Panel

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

5-4-8Page 8

Apr 01/13


5-4-9 Oil System

**ON A/C A330-200 A330-200F A330-300

Oil System

1. Engine Oil Tank and IDG for PW 4000 series engine.

A. Engine Oil Replenishment :

One gravity filling cap and one pressure filling connection per engine.


FROM AIRPLANE CENTERLINEAFT OF NOSE

ENGINE 1 (Left) ENGINE 2 (Right)

MEANHEIGHT FROM

GROUND

Engine Oil Filling:25.7 m

(84.32 ft)10.6 m

(34.78 ft)8.07 m

(26.48 ft)2.23 m(7.32 ft)

(1) Tank capacity :- Full level : 8.00 US gal (30.28 l).- Usable : 5.75 US gal (21.77 l).

B. IDG Oil Replenishment :

One pressure filling connection per engine.




MEANHEIGHT FROM

GROUND

IDG Oil Pressure FillingConnection:

26.16 m(85.83 ft)

10.07 m(33.04 ft)

8.66 m(28.41 ft)

1.50 m(4.92 ft)

- Max delivery pressure required : 40 psi (2.76 bar).- Max OIL capacity of the IDG : 1.1 US gal (4.16 l).

2. Engine Oil Tank and IDG for RR Trent 700 series engine


One gravity filling cap.

One ozone self sealing pressure fill and overfill connector per engine.

5-4-9Page 1

Apr 01/13





MEANHEIGHT FROM

GROUND

Engine Oil Filling:23.9 m

(78.41 ft)7.92 m

(25.98 ft)10.82 m(35.50 ft)

2.05 m(6.73 ft)

(1) Tank capacity :- Full level : 7.18 US gal (27.18 l.- Usable : 6.00 US gal (22.71 l).


One ozone self sealing pressure fill and overfill connector per engine.




MEANHEIGHT FROM

GROUND


24.38 m(79.99 ft)

9.65 m(31.66 ft)

9.09 m(29.82 ft)

0.8 m(2.62 ft)


**ON A/C A330-200 A330-300

3. Engine Oil Tank and IDG for GE CF6-80E1 series engine


One gravity filling cap and one pressure filling connection per engine.




MEANHEIGHT FROM

GROUND

Engine Oil Filling:24.93 m(81.79 ft)

10.00 m(32.81 ft)

8.73 m(28.64 ft)

1.71 m(5.61 ft)

5-4-9Page 2

Apr 01/13


(1) Tank capacity :- Full level : 6.49 US gal (24.57 l).- Usable : 6.09 US gal (23.05 l).


One pressure filling connection per engine.




MEANHEIGHT FROM

GROUND


23.03 m(75.56 ft)

7.96 m(26.12 ft

10.77 m(35.33 ft)

2.35 m(7.71 ft)


5-4-9Page 3

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

YELLOW

GREEN

OIL LEVELSIGHTGLASS

OIL TANKCAP

DUSTCOVER

OVERFLOWCONNECTOR

PRESSUREFILL

VALVE

PRESSUREFILL

CONNECTOR

OIL TANK

FULL

1 QT

2 QT

3 QT

FULL

−1 QT

−2 QT

−3 QT

AB

B

FULL

−1 QT

−2 QT

−3 QTCLOSE

OPEN

A

F_AC_050409_1_0010101_01_00

Ground Service ConnectionsEngine Oil Tank - PW 4000 series engine

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

5-4-9Page 4

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

1 OIL FILLER CAP

2 OVERFLOW COUPLING

3 PRESSURE FILLCOUPLING

D5324

A

B

B

FULL FULL

LIT

RE

S R

EQ

UIR

ED

US

QU

AR

TZ

RE

QU

IRE

D

5

4

3

2

1

5

4

3

2

1

A

F_AC_050409_1_0020101_01_00

Ground Service ConnectionsEngine Oil Tank - RR Trent 700 series engine

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

5-4-9Page 5

Apr 01/13


**ON A/C A330-200 A330-300

SIGHT GLASS

TANK FULL

TANK NOT FULLSCUPPER

DRAIN

RELIEFVALVE

OVERFILLPORT

ENGINEOIL TANKFILLER CAP

PRESSUREFILL PORT

5000EN

ENGINE OILTANK

A

B

B

A

F_AC_050409_1_0030101_01_00

Ground Service ConnectionsEngine Oil Tank - GE CF6-80E1 series engine

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

5-4-9Page 6

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

RED

YELLOW

GREEN

RED

2

1

PRESSUREFILL VALVE

CONNECTOR

OVERFLOWDRAIN VALVECONNECTOR

OIL LEVELSIGHTGLASS

OIL DIFFERENTIALPRESSUREINDICATOR

A

B

A

B

OVER FULL

ADDOIL

F_AC_050409_1_0040101_01_00

Ground Service ConnectionsIDG Oil Tank - PW 4000 series engine

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

5-4-9Page 7

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

OVER FULL

ADDOIL

RED

YELLOW

GREEN

RED

1 SIGHT GLASS

2 DRAIN PLUG

3 OVERFILL DRAIN CONNECTOR

4 PRESSURE FILL CONNECTOR

A

A

F_AC_050409_1_0050101_01_00

Ground Service ConnectionsIDG Oil Tank - RR Trent 700 series engine

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

5-4-9Page 8

Apr 01/13


**ON A/C A330-200 A330-300

1

A

A

B

PRESSUREFILL VALVE

CONNECTOR

OVERFLOWDRAIN VALVECONNECTOR

5

3

B

A

F_AC_050409_1_0060101_01_00

Ground Service ConnectionsIDG Oil Tank - GE CF6-80E1 series engine

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

5-4-9Page 9

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

APU Oil System

**ON A/C A330-200 A330-200F

1. APU Oil SystemAPU oil gravity filling cap.




APU OilReplenishment:Access Doors316AR, 315AL

55 m(180.45 ft)

-0.4 m(1.31 ft)

8 m(26.25 ft)

A. Tank capacity (usable):- APU Type: 331-350: 7.3 l (1.93 US gal).

**ON A/C A330-300

2. APU Oil SystemAPU oil gravity filling cap.




APU OilReplenishment:Access Doors316AR, 315AL

60.3 m(197.83 ft)

- 0.4 m(1.31 ft)

8 m(26.25 ft)

A. Tank capacity (usable):- APU Type: 331-350: 7.3 l (1.93 US gal).

5-4-9Page 10

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

F_AC_050409_1_0070101_01_01

FR95

316AR

315AL

FR101

A

PRESSURE FILLOVERFLOW PORT

OIL SCUPPER

GRAVITY FILLPORT

LUBRIFICATION OIL FILTER

GENERATOR SCAVENGE OIL FILTER

OIL PUMPMODULE5100KT9

A

B

OIL FILLERCAP

OVERFLOW PORT

PRESSUREFILL PORT

OIL SIGHTGLASS

OIL SCUPPER

GRAVITY FILL PORT

B

DO NOT REMOVE OILFILLER CAP WHEN OILLEVEL IS ABOVE FULLMARK ON SIGHT GLASS

FWD

Ground Service ConnectionsAPU Oil Servicing

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

5-4-9Page 11

Apr 01/13


5-4-10 Vacuum Toilet System

**ON A/C A330-200 A330-200F A330-300

Vacuum Toilet System

**ON A/C A330-200

1. Vacuum Toilet System

DISTANCEFROM AIRPLANE CENTERLINE


MEAN HEIGHTFROM

GROUNDWaste Water GroundService Panel:Access Door 171AL

44.66 m(146.52 ft)

-0.09 m(0.3 ft)

3.6 m(11.81 ft)

A. Waste water ground service panel comprising:- Standard: One standard 4 in. drain connection and two 1 in. flushing connections- Standard option: One standard 4 in. drain connection and three 1 in. flushing connections.

B. Capacity waste tanks:- Standard: 700 l (184.92 US gal)- Standard option: 1050 l (277.38 US gal).

C. Chemical fluid:- Standard: 36 l (9.51 US gal)- Standard option: 54 l (14.27 US gal).

**ON A/C A330-300




MEAN HEIGHTFROM

GROUNDWaste Water GroundService Panel:Access Door 171AL

50 m(164.04 ft)

-0.09 m(0.3 ft)

3.6 m(11.81 ft)

A. Waste water ground service panel comprising:- Standard: One standard 4 in. drain connection and two 1 in. flushing connections- Standard option: One standard 4 in. drain connection and three 1 in. flushing connections.

B. Capacity waste tanks:- Standard: 700 l (184.92 US gal)

5-4-10Page 1

Apr 01/13


- Standard option: 1050 l (277.38 US gal).

C. Chemical fluid:- Standard: 36 l (9.51 US gal)- Standard option: 54 l (14.27 US gal).

**ON A/C A330-200F




MEAN HEIGHTFROM

GROUNDWaste Water GroundService Panel 1:Access Door 121EL

5.49 m(18.01 ft)

-1.43 m(4.69 ft)

2.95 m(9.68 ft)

Waste Water GroundService Panel 2:Access Door 121FL

5.98 m(19.62 ft)

-1.69 m(5.54 ft)

3.15 m10.33 ft)

A. There are two waste water ground service panels:- First panel: One standard connection Roylyn 1 in. for flushing and filling- Second panel: One standard Taco type valve 4 in. for draining.

NOTE : Handle used for drainage is located on the first panel.

B. Capacity waste tanks:- Standard: 35 l (9.25 US gal).

C. Chemical fluid:- Standard: 9.5 l (2.51 US gal).

5-4-10Page 2

Apr 01/13


**ON A/C A330-200 A330-300

LIMIT SWITCHWASTE−PANEL

RINSE CONNECTIONTANK 2 FILL AND

TANK 1 FILL ANDRINSE CONNECTION

WASTEDRAIN−LINE VALVE

DRAIN−VALVECONTROL LEVERS

FR75

FR59

FR74 FR73

A

A

FWD

171AL

OPEN

CLOSE

LH RH

F_AC_050410_1_0010101_01_00

Ground Service ConnectionsWaste Water Ground Service Panel

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

5-4-10Page 3

Apr 01/13


**ON A/C A330-200F

FR14

FR16

FR20

FR12

121FL121EL

A

B

FR15A FR16LIMIT SWITCH

WASTE−PANEL

WASTEDRAIN−LINE VALVE

A

FWD

DRAIN−VALVECONTROL LEVER LIMIT SWITCH

WASTE−PANEL

TANK FILL ANDRINSE CONNECTION

DRAINAGE OFLEAK PROTECTION

B

FWD

FR14A FR15

OPEN

CLOSE

F_AC_050410_1_0040101_01_00

Ground Service ConnectionsWaste Water Ground Service Panel

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

5-4-10Page 4

Apr 01/13


5-5-0 Engine Starting Pneumatic Requirements

**ON A/C A330-200 A330-200F A330-300

Engine Starting Pneumatic Requirements

1. The purpose of this section is to provide the minimum air data requirements at the aircraftconnection, needed to start the engine within no more than 90 seconds, at sea level (0 feet), for a setof Outside Air Temperatures (OAT).

ABBREVIATION DEFINITION

A/C Aircraft

ASU Air Start UnitHPGC High Pressure Ground Connection

OAT Outside Air Temperature

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

B. For the requirements below, the configuration with two HPGC is used. Using one connector only(for a given mass flow rate and discharge pressure from the ASU) will increase the pressure lossin the ducts of the bleed system and therefore lower the performances at the engine starter.

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

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

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

5-5-0Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

AIR

FLO

W (

kg/m

in)

AIR

FLO

W (

lb/m

in)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

0 10 20 30 40 50 60

GE CF6−80E1 SERIES/SEA LEVELSTARTING TIME: LESS THAN 70 s

AIR DATA AT AIRCRAFT CONNECTION (TWO CONNECTORS)

OUTSIDE AIR TEMPERATURE OAT (° C)

OUTSIDE AIR TEMPERATURE OAT (° F)

−10−20−30−40−50

0 20 40 60 80 100 120 140−20−40

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

EXAMPLE:FOR AN OAT OF 15° C (59° F) AND AN ASU PROVIDING A DISCHARGE TEMPERATURE OF 150° C (302° F) AT HPGC:− THE REQUIRED PRESSURE AT HPGC IS 23.75 psia− THE REQUIRED AIRFLOW AT HPGC IS 43 kg/min.

EXAMPLE:FOR AN OAT OF 15° C (59° F) AND AN ASU PROVIDING A DISCHARGE TEMPERATURE OF 195° C (383° F) AT HPGC, INTERPOLATING BETWEEN THE LINES 150° C (302° F) AND 220° C (428° F) RESULTS IN:− A REQUIRED PRESSURE AT HPGC OF 22.5 psia− A REQUIRED AIRFLOW AT HPGC OF 39.5 kg/min.

40

35

30

25

20

30 35 40

40

45

50

55

60

65

70

75

90

100

110

120

130

140

150

160

352520

80

ABSOLUTE PRESSURE (psia)

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

F_AC_050500_1_0010101_01_01

Example for Use of the ChartsFIGURE-5-5-0-991-001-A01

5-5-0Page 2

Apr 01/13


**ON A/C A330-200 A330-300

AIR

FLO

W (

kg/m

in)

AIR

FLO

W (

lb/m

in)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

GE CF6−80E1 SERIES/SEA LEVELSTARTING TIME: LESS THAN 70 s



OUTSIDE AIR TEMPERATURE OAT (° F)0 20 40 60 80 100 120 140−20−40

30 35 40

40

45

50

55

60

65

70

75

90

100

110

120

130

140

150

160

352520

80

40

0 10 20 30 40 50 60−10−20−30−40−50

35

30

25

20



F_AC_050500_1_0040101_01_00

Engine Starting Pneumatic RequirementsGE CF6-80E1 Series EngineFIGURE-5-5-0-991-004-A01

5-5-0Page 3

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

AIR

FLO

W (

kg/m

in)

AIR

FLO

W (

lb/m

in)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

ROLLS ROYCE TRENT 700 SERIES/SEA LEVELSTARTING TIME: LESS THAN 90 s



OUTSIDE AIR TEMPERATURE OAT (° F)

190

200

210

220

230

240

8045

180

50 55 60

90

100

110

120

130

140

65

4040

60

55

50

45

3020100−10−20−30−40−50−60

0 20 40 60 80 100−20−40−60



F_AC_050500_1_0050101_01_00

Engine Starting Pneumatic RequirementsRolls Royce Trent 700 Series Engine

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

5-5-0Page 4

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

AIR

FLO

W (

kg/m

in)

AIR

FLO

W (

lb/m

in)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

PRATT & WHITNEY PW4000 SERIES/SEA LEVELSTARTING TIME: LESS THAN 80 s



OUTSIDE AIR TEMPERATURE OAT (° F)0 20 40 60 80 100 120 140−20−40

6030

140

70

80

90

100

110

120

35 40 45 50 55

160

180

200

220

240

260

50

0 10 20 30 40 50 60−10−20−30−40−50

45

40

35

30



F_AC_050500_1_0060101_01_00

Engine Starting Pneumatic RequirementsPratt & Whitney PW4000 Series Engine

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

5-5-0Page 5

Apr 01/13


5-6-0 Ground Pneumatic Power Requirements

**ON A/C A330-200 A330-200F A330-300

Ground Pneumatic Power Requirements

1. GeneralThis section describes the required performance for the ground equipment to maintain the cabintemperature at 27˚C (80.6˚F) after boarding (Section 5.7 - steady state), and provides the timeneeded to cool down or heat up the aircraft cabin to the required temperature (Section 5.6 - dynamiccases with aircraft empty).

ABBREVIATION DEFINITION

A/C Aircraft

AHM Aircraft Handling Manual

GC Ground ConnectionGSE Ground Service Equipment

IFE In-Flight Entertainment

LP Low PressureOAT Outside Air Temperature

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

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

B. The air flow rates and temperature requirements for the GSE are given for the A/C in theconfiguration ”2 LP ducts connected”.

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

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

2. Ground Pneumatic Power RequirementsThis section provides the ground pneumatic power requirements for:- Heating (pull up) the cabin, initially at OAT, up to 21˚C (69.8˚F) FIGURE 5---0-99--001-A- Cooling (pull down) the cabin, initially at OAT, down to 27˚C (80.6˚F) FIGURE 5---0-99--003-

A.

5-6-0Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

30 60 90 120 1500.8

1.2

1.4

1.6

1.8

2.2

2.4

2.0

2.5

3.0

3.5

4.0

4.5

5.0

AIR

FLO

W A

T G

C (

kg/s

)

AIR

FLO

W A

T G

C (

lb/s

)

PULL UP PERFORMANCE

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

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

40 50 70 80 100 110 130 140

MAXIMUM AIR FLOW

1.0

2.0

F_AC_050600_1_0010101_01_00

Ground Pneumatic Power RequirementsHeating

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

5-6-0Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

NOTE:ONLY SUPPLY TEMPERATURE ABOVE +2° C (+35.6° F) (NO SUBFREEZING) FOR THE A330−200F.

30 60 90 120 1500.8

1.2

1.4

1.6

1.8

2.2

2.4

2.0

2.5

3.0

3.5

4.0

4.5

5.0

AIR

FLO

W A

T G

C (

kg/s

)

AIR

FLO

W A

T G

C (

lb/s

)

PULL DOWN PERFORMANCE

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

OAT ISA +23° C (+73.4° F); GC OUTLET +2° C (+35.6° F); EMPTY CABIN; IFE OFF; SOLAR LOAD; LIGHTS ON; GALLEYS OFF; RECIRCULATION FANS ON

OAT ISA +23° C (+73.4° F); GC OUTLET −10° C (+14° F); EMPTY CABIN; IFE OFF; SOLAR LOAD; LIGHTS ON; GALLEYS OFF; RECIRCULATION FANS ON

40 50 70 80 100 110 130 140

MAXIMUM AIR FLOW

2.0

1.0

F_AC_050600_1_0030101_01_00

Ground Pneumatic Power RequirementsCooling

FIGURE-5-6-0-991-003-A01

5-6-0Page 3

Apr 01/13


5-7-0 Preconditioned Airflow Requirements

**ON A/C A330-200 A330-200F A330-300

Preconditioned Airflow Requirements

1. This section provides the preconditioned airflow rate and temperature needed to maintain the cabintemperature at 27 ˚C (80.6 ˚F).

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

5-7-0Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

AIR

FLO

W A

T G

C (

kg/s

)

−150.8

AIR

FLO

W A

T G

C (

lb/s

)

1.0

1.2

1.4

1.6

1.8

2.0

2.2

2.4

−10 −5 0 5 10 15 20 25 30 35 40 45 50 55 60

2.0

2.5

3.0

3.5

4.0

4.5

5.0

0 10 20 30 40 50 60 70 80

INLET TEMPERATURE AT GC (° C)

INLET TEMPERATURE AT GC (° F)

MAXIMUM AIRFLOW

COOLING/HEATING PERFORMANCE

SETTINGS NOTINTENDED TO BE USED

FOR OPERATION

OAT ISA; EMPTY CABIN; IFE ON; LIGHTS ON; SOLAR LOAD; RECIRCULATION FANS ON; GALLEYS ON

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

C H

EXAMPLE:COOLING CAPACITY CALCULATION:FOR THE CONDITIONS "C", THE COOLING CAPACITY OF 1.9 kg/s x 1 kJ/(kg.° C) x (27− 5) = 41.8 kW(OR 12.5 TONS COOLING CAPACITY) IS NEEDED TO MAINTAIN THE CABIN TEMPERATURE AT 27° C (80.6° F)(1.9 kg/s AT 5° C (41° F) FOR AIR AT GC INLET).

NOTE:ONLY SUPPLY TEMPERATURE ABOVE +2° C (+35.6° F) (NO SUBFREEZING) FOR THE A330−200F.

90 100 110 120 130 140

F_AC_050700_1_0010101_01_03

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

5-7-0Page 2

Apr 01/13


5-8-0 Ground Towing Requirements

**ON A/C A330-200 A330-200F A330-300

Ground Towing Requirements

1. This section provides information on aircraft towing.

The A330 is designed with means for conventional or towbarless towing.Information/procedures can be found for both in chapter 9 of the Aircraft Maintenance Manual.Status on towbarless towing equipment qualification can be found in SIL 09-002.It is possible to tow or push the aircraft, at maximum ramp weight with engines at zero or up to idlethrust, using a towbar attached to the nose gear leg (refer to AMM chapter 9 for conditions andlimitations). One towbar fitting is installed at the front of the leg (optional towing fitting for towingfrom the rear of the NLG available).The Main Landing Gears have attachment points for towing or debogging (for details, refer tochapter 7 of the Aircraft Recovery Manual).

This section shows the chart to determine the draw bar pull and tow tractor mass requirements as afunction of the following physical characteristics:- Aircraft weight,- Number of engines at idle,- Slope.

The chart is based on the A330 engine type with the biggest idle thrust.The chart is therefore valid for all A330 models.

2. Towbar design guidelines

The aircraft towbar shall comply with the following standards:- SAE AS 1614, ”Main Line Aircraft TowBar Attach Fitting Interface”,- SAE ARP 1915, ”Aircraft TowBar”,- ISO 8267-1, ”Aircraft - Towbar attachment fitting - Interface requirements - Part 1: Main line

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

A conventional type towbar is required which should be equipped with a damping system (to protectthe nose gear against jerks) and with towing shear pins:- A traction shear pin calibrated at 28 620 daN (64 340 lbf),- A torsion pin calibrated at 3 130 m.daN (276 991 lbf.in).The towing head is designed according to SAE AS 1614, cat. III.

5-8-0Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

50

45

40

35

30

25

20

15

10

5

00 10 20 30 40 50 60 70 80 0 1 2 0 0.5 1.0 1.5 2.0

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

DRAWBAR PULL [ t ]

WET C

ONCRETE =

0.57

HARD SNOW = 0.2

ICE = 0.05

DRY CO

NCRETE

=

0.8

A/C WEIGHT [ t ]

EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A330 AT 230 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 (230 t),− FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUIRED SLOPE PERCENTAGE (1.5%),− FROM THIS POINT OBTAINED DRAW A STRAIGHT HORIZONTAL LINE UNTIL NO OF ENGINES AT IDLE = 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 (18.8 t),− SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE. THE OBTAINED X−COORDINATE IS THE RECOMMENDED MINIMUM TRACTOR WEIGHT (32.9 t).

AT IDLE

F_AC_050800_1_0020101_01_01

230210190170150130110

18.8

32.9

1 ENGINE ON

230 tons1.5% SLOPE

BREAKWAY RESISTANCE 6%# OF ENGINES ON FOR PB: 1ENGINE THRUST 1 500 daN

Ground Towing RequirementsFIGURE-5-8-0-991-002-A01

5-8-0Page 2

Apr 01/13


5-9-0 De-Icing and External Cleaning

**ON A/C A330-200 A330-200F A330-300

De-Icing and External Cleaning

1. De-Icing and External Cleaning on GroundThe mobile equipment for aircraft de-icing and external cleaning must be capable of reaching heightsup to approximately 17 m (56 ft).

**ON A/C A330-200 A330-200F

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

A330-200/-200F306 3 294 11 118 65 700 106 1 141

Fuselage Top Surface(Top Third - 120˚ Arc)

Nacelle and Pylon(Top Third - 120˚ Arc)

(All Engines)Total De-Iced AreaAIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2

A330-200/-200F 288 3 100 46 495 821 8 837

NOTE : Dimensions are approximate.

**ON A/C A330-300

3. De-Icing



(Both Sides)


VTP(Both Sides)AIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2 m2 ft2

A330-300 306 3 294 11 118 65 700 91 980

5-9-0Page 1

Apr 01/13


Fuselage Top Surface(Top Third - 120˚ Arc)

Nacelle and Pylon(Top Third - 120˚ Arc)

(All Engines)Total De-Iced AreaAIRCRAFT

TYPE

m2 ft2 m2 ft2 m2 ft2

A330-300 319 3 434 46 495 838 9 020


**ON A/C A330-200

4. External Cleaning


Wing LowerSurface

(Including FlapTrack Fairing)(Both Sides)


(Both Sides)


HTP LowerSurface

(Both Sides)AIRCRAFTTYPE

m2 ft2 m2 ft2 m2 ft2 m2 ft2 m2 ft2

A330-200/-200F306 3 294 345 3 714 11 118 65 700 65 700

VTP(Both Sides)

Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned AreaAIRCRAFT

TYPEm2 ft2 m2 ft2 m2 ft2 m2 ft2

A330-200/-200F106 1 141 877 9 440 154 1 658 1 940 20 882


**ON A/C A330-300

5. External Cleaning


Wing LowerSurface

(Including FlapTrack Fairing)(Both Sides)


(Both Sides)


HTP LowerSurface

(Both Sides)AIRCRAFTTYPE

m2 ft2 m2 ft2 m2 ft2 m2 ft2 m2 ft2

A330-300 306 3 294 345 3 714 11 118 65 700 65 700

5-9-0Page 2

Apr 01/13


VTP(Both Sides)

Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned AreaAIRCRAFT

TYPEm2 ft2 m2 ft2 m2 ft2 m2 ft2

A330-300 91 980 971 10 452 154 1 658 2 016 21 700


5-9-0Page 3

Apr 01/13


OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

**ON A/C A330-200 A330-200F A330-300

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

Apr 01/13


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

**ON A/C A330-200 A330-200F A330-300

Engine Exhaust Velocities Contours - Ground Idle Power

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

6-1-1Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

0 60 (18) 40 (12) 20 (6) 0

FE

ET

ME

TE

RS

050

100

1530

0

150

200

250

300

4661

7691

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

PLA

NA

IRP

LAN

EC L

CO

NV

ER

SIO

N F

AC

TO

R1

MP

H =

1.6

km

/h

NO

TE

:

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

60 (18)

40 (12) 20 (6)

G−

0022

6 (0

000)

102

MP

H68

MP

H51

MP

H34

MP

H13

6 M

PH

34 M

PH

51 M

PH

68 M

PH

102

MP

H13

6 M

PH

ALL

VE

LOC

ITY

VA

LUE

S A

RE

IN S

TA

TU

TE

MIL

ES

PE

R H

OU

R.

GR

OU

ND

IDLE

PO

WE

R, S

EA

LE

VE

L S

TA

TIC

, ZE

RO

WIN

DS

TA

ND

AR

D D

AY

, ZE

RO

RA

MP

GR

AD

IEN

T E

NG

INE

TY

PE

.

F_AC_060101_1_0010101_01_00

Engine Exhaust VelocitiesGround Idle Power - PW 4000 series engine

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

6-1-1Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

ft

ft

m

m

00

00

0

0

FEET

METERS

50

ELEVATION

100 150

15 30 45

205

5 20

PLAN

200 fps 100 fps 50 fps


10

15

20

40

60

10

15

20

25

60

40

80

(100 fps = 68 MPH = 109 kmph)

(100 fps = 68 MPH = 109 mph)

F_AC_060101_1_0020101_01_00

Engine Exhaust VelocitiesGround Idle Power - RR Trent 700 series engine

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

6-1-1Page 3

Apr 01/13


**ON A/C A330-200 A330-300

0

0

ft

0

ft

25

25

50

50

ELEVATION

PLAN

m

15

0

10

5

m

15

0

10

5

0 50 100 150 200FEET

METERS15 30 45 60

V=51.3V=95.3

(100 fps = 68 MPH = 109 kmph)

(100 fps = 68 MPH= 109 kmph)

ft/s6535 MPH

10556 km/h

F_AC_060101_1_0030101_01_01

Engine Exhaust VelocitiesGround Idle Power - GE CF6-80E1 series engine

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

6-1-1Page 4

Apr 01/13


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

**ON A/C A330-200 A330-200F A330-300

Engine Exhaust Temperatures Contours - Ground Idle Power

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

6-1-2Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

FE

ET

ME

TE

RS

050

100

1530

0

150

200

250

300

4661

7691

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

AIR

PLA

NE

C L

NO

TE

:

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

125°

F(5

2°C

)

0 60 (18) 40 (12) 20 (6)

060 (18) 40 (12) 20 (6)

150°

F(6

6°C

)

150°

F(6

6°C

)12

5°F

(52°

C)

100°

F(3

8°C

)

100°

F(3

8°C

)

G−

0022

9 (1

294)

TE

MP

ER

AT

UR

ES

AR

E IN

DE

GR

EE

S F

AH

RE

NH

EIT

(D

EG

RE

ES

C)

GR

OU

ND

IDLE

PO

WE

R −

SE

A L

EV

EL

ST

AT

IC, Z

ER

O W

IND

,S

TA

ND

AR

D D

AY

, ZE

RO

RA

MP

GR

AD

IEN

T E

NG

INE

TY

PE

.

PLA

N

F_AC_060102_1_0010101_01_00

Engine Exhaust TemperaturesGround Idle Power - PW 4000 series engine

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

6-1-2Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

FEET

METERS

50 100 150

15 30 45

ELEVATION

PLAN

0

60(18)

80(24)

40(12)

20(6)

FEET(METERS)

0

0

113°F(45°C)

95°F(35°C)

77°F(25°C)

0

60(18)

80(24)

40(12)

20(6)

FEET(METERS)

113°F(45°C)

95°F(35°C)

77°F(25°C)

F_AC_060102_1_0020101_01_00

Engine Exhaust TemperaturesGround Idle Power - RR Trent 700 series engine

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

6-1-2Page 3

Apr 01/13


**ON A/C A330-200 A330-300

ELEVATION

PLAN

50 100 150FEET

METERS 15 30 45

0

60(18)

80(24)

40(12)

20(6)

FEET(METERS)

141°F(60°C)

91°F(31°C)

116°F(47°C)

141°F(60°C)

116°F(47°C)

91°F(31°C)

0

60(18)

80(24)

40(12)

20(6)

FEET(METERS)

0

0

F_AC_060102_1_0030101_01_01

Engine Exhaust TemperaturesGround Idle Power - GE CF6-80E1 series engine

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

6-1-2Page 4

Apr 01/13


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

**ON A/C A330-200 A330-200F A330-300

Engine Exhaust Velocities Contours - Breakaway Power

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

6-1-3Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

60 (18) 40 (12) 20 (6) 0 60 (1

8) 40 (12) 20 (6) 0

FE

ET

ME

TE

RS

050

100

1530

0

150

200

250

300

4661

7691

PLA

NA

IRP

LAN

EC L

NO

TE

:

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

CO

NV

ER

SIO

N F

AC

TO

R

136

MP

H10

2 M

PH

68 M

PH

51 M

PH

34 M

PH

G−

0324

7 (0

000)

ALL

VE

LOC

ITY

VA

LUE

S A

RE

IN S

TA

TU

TE

MIL

ES

PE

R H

OU

R.

GR

OU

ND

IDLE

PO

WE

R −

SE

A L

EV

EL

ST

AT

IC, Z

ER

O W

IND

ST

AN

DA

RD

DA

Y, Z

ER

O R

AM

P G

RA

DIE

NT

EN

GIN

E T

YP

E.

136

MP

H10

2 M

PH

68 M

PH

51 M

PH

34 M

PH

1 M

PH

= 1

.6 k

m/h

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

F_AC_060103_1_0010101_01_00

Engine Exhaust VelocitiesBreakaway Power - PW 4000 series engine

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

6-1-3Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

ELEVATION


(100 fps = 68 MPH = 109 kmph)


(100 fps = 68 MPH = 109 kmph)ft

ft

m

m

00

00

0

0

FEET

METERS

50 100

15 30

205

5 20

PLAN

10

15

20

40

60

10

15

20

25

60

40

80

150 200 250 300

6045 75 90

F_AC_060103_1_0020101_01_00

Engine Exhaust VelocitiesBreakaway Power - RR Trent 700 series engine

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

6-1-3Page 3

Apr 01/13


**ON A/C A330-200 A330-300

0

0

ft

2550

ELE

VA

TIO

N

PLA

N

m15 010 5

010

0F

EE

T

ME

TE

RS

30

02550m

15 010 5

200

60

300

400

500

600

9012

015

018

0

105

MP

H65

MP

H35

MP

H

210

MP

H14

5 M

PH

105

MP

H65

MP

H35

MP

H

210

MP

H14

5 M

PH

51.3

V=

V=

154

V=

213

V=

308

(100

fps

= 6

8 M

PH

= 1

09 m

ph)

(100

fps

= 6

8 M

PH

= 1

09 m

ph)

ft

ft/s

65 105

145

210

3510

516

923

333

8

56V

=95

.3M

PH

km/h

F_AC_060103_1_0030101_01_01

Engine Exhaust VelocitiesBreakaway Power - GE CF6-80E1 series engine

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

6-1-3Page 4

Apr 01/13


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

**ON A/C A330-200 A330-200F A330-300

Engine Exhaust Temperatures Contours - Breakaway Power

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

6-1-4Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

60 (18) 40 (12) 20 (6) 0 60 (1

8) 40 (12) 20 (6)

0

FE

ET

ME

TE

RS

050

100

1530

0

150

200

250

300

4661

7691

GR

OU

ND

PLA

NE

PLA

NA

IRP

LAN

EC L

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

100°

F(3

8°C

)12

5°F

(52°

C)

(66°

C)

125°

F(5

2°C

)15

0°F

(66°

C)

NO

TE

:T

EM

PE

RA

TU

RE

S A

RE

IN D

EG

RE

ES

FA

HR

EN

HE

IT (

DE

GR

EE

S C

)G

RO

UN

D ID

LE P

OW

ER

− S

EA

LE

VE

L S

TA

TIC

, ZE

RO

WIN

D,

ST

AN

DA

RD

DA

Y, Z

ER

O R

AM

P G

RA

DIE

NT

EN

GIN

E T

YP

E.

G−

0324

6 (0

000)

100°

F(3

8°C

)

150°

F

ELE

VA

TIO

N

F_AC_060104_1_0010101_01_00

Engine Exhaust TemperaturesBreakaway Power - PW 4000 series engine

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

6-1-4Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

ELEVATION

0

FEET

METERS

50 100 150

15 30 45

PLAN

113°F(45°C)

95°F(35°C)

77°F(25°C)

113°F(45°C)

77°F(25°C)

0

60(18)

80(24)

40(12)

20(6)

FEET(METERS)

0

60(18)

80(24)

40(12)

20(6)

FEET(METERS)

0

95°F(35°C)

F_AC_060104_1_0020101_01_00

Engine Exhaust TemperaturesBreakaway Power - RR Trent 700 series engine

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

6-1-4Page 3

Apr 01/13


**ON A/C A330-200 A330-300

0

0

ft

0

ft

25

25

50

50

ELEVATION

PLAN

m

15

0

10

5

m

15

0

10

5

0 50 100 150 200FEET

METERS 15 30 45 60

341°F(172°C)

141°F(60°C)

241°F(116°C)

116°F(47°C)

91°F(31°C)

341°F(172°C)

141°F(60°C)

241°F(116°C)

116°F(47°C)

91°F(31°C)

F_AC_060104_1_0030101_01_01

Engine Exhaust TemperaturesBreakaway Power - GE CF6-80E1 series engine

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

6-1-4Page 4

Apr 01/13


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

**ON A/C A330-200 A330-200F A330-300

Engine Exhaust Velocities Contours - Takeoff Power

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

6-1-5Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

0 60 (18) 40 (12) 20 (6) 0

FE

ET

ME

TE

RS

050

100

1530

0

150

200

250

300

4661

7691

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

PLA

NA

IRP

LAN

EC L

CO

NV

ER

SIO

N F

AC

TO

R1

MP

H =

1.6

km

/h

NO

TE

:

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

ALL

VE

LOC

ITY

VA

LUE

S A

RE

IN S

TA

TU

TE

MIL

ES

PE

R H

OU

R.

TA

KE

OF

F P

OW

ER

− S

EA

LE

VE

L S

TA

TIC

, ZE

RO

WIN

DS

TA

ND

AR

D D

AY

, ZE

RO

RA

MP

GR

AD

IEN

T E

NG

INE

TY

PE

.

60 (18) 40 (12) 20 (6)

682

MP

H47

7 M

PH

341

MP

H20

4 M

PH

102

MP

H

477

MP

H34

1 M

PH

204

MP

H10

2 M

PH

34 M

PH

TO

740

ft22

5 m

682

MP

H34

MP

HT

O 7

40 ft

225

m

G−

0022

8 (1

294)

68 M

PH

460

ft14

0 m

68 M

PH

460

ft14

0 m

F_AC_060105_1_0010101_01_00

Engine Exhaust VelocitiesTakeoff Power - PW 4000 series engine

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

6-1-5Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

50 fp

s

0

FE

ET

ME

TE

RS

ELE

VA

TIO

N

PLA

N

60

5

101520

250

200

150

100

0

7560

4530

150

m

40 20Ft

50 fp

s

(100

fps

= 6

8 M

PH

= 1

09 k

mph

)

TO

1175

ft35

8 m

TO

1175

ft35

8 m

05

1015

m

40 20Ft

2060

30 25

100

80

50

(100

fps

= 6

8 M

PH

= 1

09 k

mph

)

200

fps

100

fps

200

fps

100

fps

D29

81A

300

90

350

105

TO

470

ft14

3 m

TO

470

ft14

3 m

F_AC_060105_1_0020101_01_00

Engine Exhaust VelocitiesTakeoff Power - RR Trent 700 series engine

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

6-1-5Page 3

Apr 01/13


**ON A/C A330-200 A330-300

0

0

ft

2550

ELE

VA

TIO

N

PLA

N

m15 010 5

010

0F

EE

T

ME

TE

RS

30

0

ft

2550m

15 010 5

200

60

300

400

500

600

9012

015

018

0

105

MP

H65

MP

H35

MP

H

105

MP

H65

MP

H35

MP

H

V=

V=

V=

154

V=

213

V=

308

(100

fps

= 6

8 M

PH

= 1

09 k

m/h

)

(100

fps

= 6

8 M

PH

= 1

09 k

m/h

)

65 105

145

210

105

169

233

338

35 M

PH

56 k

m/h

51.3

ft/s

95.3

F_AC_060105_1_0030101_01_00

Engine Exhaust VelocitiesTakeoff Power - GE CF6-80E1 series engine

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

6-1-5Page 4

Apr 01/13


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

**ON A/C A330-200 A330-200F A330-300

Engine Exhaust Temperatures Contours - Takeoff Power

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

6-1-6Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

0

60 (18) 40 (12) 20 (6) 0

FE

ET

ME

TE

RS

050

100

1530

0

150

200

250

300

4661

7691

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

PLA

NA

IRP

LAN

EC L

NO

TE

:

FE

ET

(ME

TE

RS

)

FE

ET

(ME

TE

RS

)

60(1

8) 40(1

2) 20 (6)

G−

0023

1 (0

000)

TE

MP

ER

AT

UR

ES

AR

E IN

DE

GR

EE

S F

AH

RE

NH

EIT

(D

EG

RE

ES

C).

TA

KE

OF

F P

OW

ER

− S

EA

LE

VE

L S

TA

TIC

, ZE

RO

WIN

D,

ST

AN

DA

RD

DA

Y, Z

ER

O R

AM

P G

RA

DIE

NT

EN

GIN

E T

YP

E.

250°

F(1

21°

C)

150°

F(6

6°C

)12

5°F

(52°

C)

200°

F(9

3°C

)30

0°F

(149

°C

)10

0°F

(38°

C)

250°

F(1

21°

C)

150°

F(6

6°C

)12

5°F

(52°

C)

200°

F(9

3°C

)30

0°F

(149

°C

)10

0°F

(38°

C)

F_AC_060106_1_0010101_01_00

Engine Exhaust TemperaturesTakeoff Power - PW 4000 series engine

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

6-1-6Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

ftft

mm

00

00

FE

ET

ME

TE

RS

50ELE

VA

TIO

N

100

150

200

250

300

350

1530

4560

7590

105

205

101520 25 20 15 105

80 60 40 20

TO

430

ft(1

31 m

)

TO

430

ft(1

31 m

)

PLA

N

4060

113°

F(4

5°C

)77

°F

(25°

C)

95°

F(3

5°C

)

0 0

113°

F(4

5°C

)77

°F

(25°

C)

95°

F(3

5°C

)

F_AC_060106_1_0020101_01_00

Engine Exhaust TemperaturesTakeoff Power - RR Trent 700 series engine

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

6-1-6Page 3

Apr 01/13


**ON A/C A330-200 A330-300

0

ft

0

ft

252550 50

ELE

VA

TIO

N

PLA

N

m

15 0

10

5

m

15 0

10

5

5010

015

020

0F

EE

T

ME

TE

RS

1530

4560

250

300

7590

341°

F(1

72°

C)

241°

F(1

16°

C)

141°

F(6

0°C

)11

6°F

(47°

C)

91°

F(3

1°C

)

341°

F(1

72°

C)

241°

F(1

16°

C)

141°

F(6

0°C

)11

6°F

(47°

C)

91°

F(3

1°C

)

00

F_AC_060106_1_0030101_01_00

Engine Exhaust TemperaturesTakeoff Power - GE CF6-80E1 series engine

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

6-1-6Page 4

Apr 01/13


6-2-0 Airport and Community Noise

**ON A/C A330-200 A330-200F A330-300

Airport and Community Noise Data

1. Airport and Community Noise Data

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

6-2-0Page 1

Apr 01/13


6-2-1 Noise Data

**ON A/C A330-200 A330-200F A330-300

Noise Data

1. Noise Data for PW 4000 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 : 24.8 ˚C (76.64 ˚F)- Relative humidity : 46%- Atmospheric pressure : 1000 hPa- Wind speed : Negligible- No rain

2. Noise Data for RR Trent 700 series engine





The meteorological parameters measured 1.6 m (5.25 ft) from the ground on the day of testwere as follows :- Temperature : 16.8 ˚C (62.24 ˚F)- Relative humidity : 70%- Atmospheric pressure : 1009 hPa- Wind speed : Negligible- No rain

6-2-1Page 1

Apr 01/13


**ON A/C A330-200 A330-300

3. Noise Data for GE CF6-80E1 series engine





The meteorological parameters measured 1.6 m (5.25 ft) from the ground on the day of testwere as follows :- Temperature : 24.5 ˚C (76.10 ˚F)- Relative humidity : 47%- Atmospheric pressure : 1003.1 hPa- Wind speed : Negligible- No rain

6-2-1Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

7880

8284

8688

9092

9496

0°10°20°

60°

70°

80°

90°

100°

110°

120°

130°

140°

150°

98100

102104

106108

110112

350°340°

330°

270°

240°

230°

220°

210°

NOISE REFERENCEPOINT

GROUND IDLE

E.P.R.

N1

CURVE

25% 82.4%

MAX THRUST POSSIBLEON BRAKES

1.016 1.337

30°

40°

50°

320°

310°

300°

290°

280°

250°

260°

F_AC_060201_1_0010101_01_00

Airport and Community NoisePW 4000 series engine

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

6-2-1Page 3

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

7880

8284

8688

9092

9496

0°10°20°

30°

40°

50°

60°

70°

80°

90°

100°

110°

120°

130°

140°

150°

98100

102104

106108

110112

350°340°

330°

320°

310°

300°

290°

280°

270°

260°

250°

240°

230°

220°NOISE REFERENCE

POINT

GROUND IDLE

E.P.R.

N1

CURVE

23% 79.5%


1.017 1.43

210°

F_AC_060201_1_0020101_01_00

Airport and Community NoiseRR Trent 700 series engineFIGURE-6-2-1-991-002-A01

6-2-1Page 4

Apr 01/13


**ON A/C A330-200 A330-300

7880

8284

8688

9092

9496

0°10°20°

30°

40°

50°

60°

70°

80°

90°

100°

110°

120°

130°

140°

150°

98100

102104

106108

110112

350°340°

330°

320°

310°

300°

290°

280°

270°

260°

250°

240°

230°

220°

210°

NOISE REFERENCEPOINT

GROUND IDLE

N1

CURVE

26% 99.5%


F_AC_060201_1_0030101_01_00

Airport and Community NoiseGE CF6-80E1 series engineFIGURE-6-2-1-991-003-A01

6-2-1Page 5

Apr 01/13


6-3-0 Danger Areas of Engines

**ON A/C A330-200 A330-200F A330-300

Danger Areas of Engines

1. Danger Areas of the Engines.

6-3-0Page 1

Apr 01/13


6-3-1 Ground Idle Power

**ON A/C A330-200 A330-200F A330-300

Ground Idle Power

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

6-3-1Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

INTAKE SUCTIONDANGER AREA

30°

EXHAUST DANGERAREA

SAFE ENTRYAREA

G−00224(0992)

TO 175 ft AT 34 MPHTO 53.35 m AT 54.4 kph

8.2 m(27 ft)

1.7 m(5.5 ft)

F_AC_060301_1_0010101_01_00

Danger Areas of EnginesPW 4000 series engine

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

6-3-1Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

TO 256 ft (78 m) AFT COMMON NOZZLE ASSEMBLY (CNA)

INTAKE SUCTION DANGER AREA MINIMUM POWER

ENTRY CORRIDOR

EXHAUST DANGER AREA

30°

3.75 ft10 ft

D4816

(3 m)(1 m)

F_AC_060301_1_0020101_01_00

Danger Areas of EnginesRR Trent 700 series engineFIGURE-6-3-1-991-002-A01

6-3-1Page 3

Apr 01/13


**ON A/C A330-200 A330-300

INLET SUCTION DANGER AREA

ENTRY CORRIDOR

EXHAUST WAKE DANGER. WIND 105 km/h/57 kts OR GREATER

TO

54.90 m/180 ft A

FT

FA

N N

OZ

ZLE

7.62 m(25 ft)

1.25

m(4

.1 ft

)

45°

30°

RAD

IUS

F_AC_060301_1_0030101_01_00

Danger Areas of EnginesGE CF6-80E1 series engineFIGURE-6-3-1-991-003-A01

6-3-1Page 4

Apr 01/13


6-3-2 Breakaway Power

**ON A/C A330-200 A330-200F A330-300

Breakaway Power

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

6-3-2Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300


EXHAUST DANGERAREA

TO 290 ft AT 34 MPHTO 88.4 m m AT 54.4 kph

(37 ft)11.3 m

G−03248 (0000)

F_AC_060302_1_0010101_01_00


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

6-3-2Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

(8 ft)2.4 m

(25 ft)7.6 m

30°TO 150 m (490 ft) AFT COMMON NOZZLE ASSEMBLY (CNA)

INTAKE SUCTION DANGER AREA BREAKAWAY POWER

ENTRY CORRIDOR

EXHAUST DANGER AREA

F_AC_060302_1_0020101_01_00


6-3-2Page 3

Apr 01/13


**ON A/C A330-200 A330-300


ENTRY CORRIDOR

EXHAUST WAKE DANGER. WIND 105 km/h/57 kts OR GREATER

TO

48.8 m/160 ft A

FT

FA

N N

OZ

ZLE

(50 ft)15.2 m

45°

(5 ft

)1.

5 m

30°

RAD

IUS

F_AC_060302_1_0030101_01_00


6-3-2Page 4

Apr 01/13


6-3-3 Takeoff Power

**ON A/C A330-200 A330-200F A330-300

Takeoff Power

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

6-3-3Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

30°


EXHAUST DANGERAREA

PW 4164 / PW 4168 −TAKEOFFG − 00225 (0493)

TO 740 ft AT 34 MPHTO 225.5 m AT 54.4 kph

2 m6.5 ft

54 ft16.5 m

F_AC_060303_1_0010101_01_00


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

6-3-3Page 2

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

30°

TO 2100 ft (640 m) AFT COMMON NOZZLE ASSEMBLY (CNA)

INTAKE SUCTION DANGER AREA TAKE−OFF POWER

ENTRY CORRIDOR

EXHAUST DANGER AREA

2.4 m(8 ft)

7.6 m(25 ft)

F_AC_060303_1_0020101_01_00


6-3-3Page 3

Apr 01/13


**ON A/C A330-200 A330-300


ENTRY CORRIDOR

TO 274.30 m

/900 ft AFT FA

N N

OZZLE

EXHAUST WAKE DANGER. WIND 105 km/h / 57Kts OR GREATER

G_AC_060303_0_F00CAM0_00_00

(6 ft)1.80 m

15.25 m(50 ft)

45°

40°

RADIUS

F_AC_060303_1_0030101_01_00


6-3-3Page 4

Apr 01/13


6-4-0 APU Exhaust Velocities and Temperatures

**ON A/C A330-200 A330-200F A330-300

APU Exhaust Velocities and Temperatures

1. APU Exhaust Velocities and Temperatures.

6-4-0Page 1

Apr 01/13


6-4-1 APU

**ON A/C A330-200 A330-200F A330-300

APU - GARRETT

1. This section gives APU exhaust velocities and temperatures

6-4-1Page 1

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

20

METERS

0

5 10 15

FEET

0

10 20 30 40 50

0

60

0

10

5

10

20

30

40

METERS FEET

20

METERS

0

5 10 15

FEET

0

10 20 30 40 50

0

60

0

10

5

10

20

30

40

METERS FEET

121°C

93°C

149°C177°C

15 m/s

FD

315.5°C

204°C260°C

427°C

18 m/s24 m/s

30.5 m/s46 m/s

61 m/s

FD

F_AC_060401_1_0010101_01_00

Exhaust Velocities and TemperaturesAPU -- GARRETT GTCP 331-350

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

6-4-1Page 2

Apr 01/13


PAVEMENT DATA


**ON A/C A330-200 A330-200F A330-300

General Information

1. General Information

A brief description of the pavement charts that follow will help in airport planning.

To aid in the interpolation between the discrete values shown, each aircraft configuration is shownwith a minimum range of five loads on the MLG.

All curves on the charts represent data at a constant specified tire pressure with :- The aircraft loaded to the Maximum Ramp Weight (MRW),- The CG at its maximum permissible aft position.

Pavement requirements for commercial aircraft are derived from the static analysis of loads imposedon the MLG struts.

Landing Gear FootprintSection 7-2-0 presents basic data on the landing gear footprint configuration, MRW and tire sizes andpressures.

Maximum Pavement LoadsSection 7-3-0 shows the maximum vertical and horizontal pavement loads for certain criticalconditions at the tire-ground interfaces.

Landing Gear Loading on PavementSection 7-4-0 contains charts to find these loads throughout the stability limits of the aircraft at reston the pavement.These MLG loads are used as the point of entry to the pavement design charts, which follow,interpolating load values where necessary.

Flexible Pavement Requirements - US Army Corps of Engineers Design MethodSection 7-5-0 uses procedures in Instruction Report No S-77-1 ”Procedures for Development of CBRDesign Curves”, dated June 1977 and as modified according to the methods described in ICAOAerodrome Design Manual, Part 3. Pavements, 2nd Edition, 1983, Section 1.1 (The ACN-PCNMethod), and utilizing the alpha factors approved by ICAO in October 2007.The report was prepared by the U.S. Army Corps Engineers Waterways Experiment Station, Soils andPavement Laboratory, Vicksburg, Mississippi”. The line showing 10 000 coverages is used to calculateAircraft Classification Number (ACN).

7-1-0Page 1

Apr 01/13


Flexible Pavement Requirements - LCN Conversion MethodThe flexible pavement charts in Section 7-6-0 show Load Classification Number (LCN) againstequivalent single wheel load (ESWL), and ESWL against pavement thickness.All LCN curves shown in ’Flexible Pavement Requirements’ were developed from a computer programbased on data in International Civil Aviation Organization (ICAO) document 7920-AN/865/2,Aerodrome manual, Part 2, ”Aerodrome Physical Characteristics”, Second Edition, 1965.

Rigid Pavement Requirements - PCA (Portland Cement Association) Design MethodSection 7-7-0 gives the rigid pavement design curves that have been prepared with the use of theWestergaard Equation.This is in general accordance with the procedures outlined in the Portland Cement Associationpublications, ”Design of Concrete Airport Pavement”, 1973 and ”Computer Program for AirportPavement Design”, (Program PDILB), 1967 both by Robert G. Packard.

Rigid Pavement Requirements - LCN ConversionSection 7-8-0 gives data about the rigid pavement requirements for the LCN Conversion.- For the radius of relative stiffness,- For the radius of relative stiffness (other values of E and µ).All LCN curves shown in Rigid Pavement Requirements - LCN conversion - were developed from acomputer program based on data in International Civil Aviation Organization (ICAO) document 7920-AN/865/2, Aerodrome manual, Part 2, ”Aerodrome Physical Characteristics”, Second Edition, 1965.Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness.The rigid pavement charts show LCN against ESWL, and ESWL against radius of relative stiffness.Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness (other values of E andµ)The rigid pavement charts show LCN against ESWL and ESWL against radius of relative stiffnessaffected by the other values of E and µ.ACN/PCN Reporting SystemSection 7-9-0 provides ACN data prepared according to the ACN/PCN system as referenced in ICAOAnnex 14, ”Aerodromes”, Volume 1 ”Aerodrome Design and Operations.” Fourth Edition July 2004,incorporating Amendments 1 to 6.The ACN/PCN system provides a standardized international aircraft/pavement rating systemreplacing the various S, T, TT, LCN, AUW, ISWL, etc... rating systems used throughout the world.ACN is the Aircraft Classification Number and PCN is the corresponding Pavement ClassificationNumber.An aircraft having an ACN equal to or less than the PCN can operate without restriction on thepavement.Numerically the ACN is two times the derived single wheel load expressed in thousands of kilograms.The derived single wheel load is defined as the load on a single tire inflated to 1.25 Mpa (181 psi)that would have the same pavement requirements as the aircraft.Computationally the ACN/PCN the system uses PCA program PDILB for rigid pavements and S-77-1for flexible pavements to calculate ACN values.

7-1-0Page 2

Apr 01/13


The Airport Authority must decide on the method of pavement analysis and the results of theirevaluation shown as follows :

PCNPAVEMENT

TYPESUBGRADECATEGORY

TIRE PRESSURE CATEGORY EVALUATION METHOD

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

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

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

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

Section 7-9-0 shows the aircraft ACN values.For flexible pavements, the four subgrade categories are :

- A. High Strength CBR 15

- B. Medium Strength CBR 10

- C. Low Strength CBR 6

- D. Ultra Low Strength CBR 3

For rigid pavements, the four subgrade categories are :

- A. High StrengthSubgrade k

= 150 MN/m3 (550 pci

- B. Medium StrengthSubgrade k

= 80 MN/m3 (300 pci)

- C. Low StrengthSubgrade k

= 40 MN/m3 (150 pci)

- D. Ultra Low StrengthSubgrade k

= 20 MN/m3 (75 pci)

7-1-0Page 3

Apr 01/13


7-2-0 Landing Gear Footprint

**ON A/C A330-200 A330-200F A330-300

Landing Gear Footprint

1. This section gives data about the landing gear footprint in relation with the aircraft MRW and tiresizes and pressures.The landing gear footprint information is given for all the aircraft operational weight variants.

7-2-0Page 1

Apr 01/13


**ON A/C A330-200

1.39

7 m

1.98

1 m

0.71

0 m

(4.5

83 ft

)(6

.499

ft)

(2.3

29 ft

)

10.6

84 m

22.1

80 m

(35.

052

ft)

(72.

768

ft)

WE

IGH

TM

AX

IMU

MP

ER

CE

NT

AG

EN

OS

E G

EA

R T

IRE

NO

SE

GE

AR

MA

IN G

EA

R T

IRE

MA

IN G

EA

RR

AM

PW

EIG

HT

OF

WE

IGH

TO

N M

AIN

GE

AR

GR

OU

PS

IZE

TIR

EP

RE

SS

UR

ES

IZE

TIR

EP

RE

SS

UR

E

A33

0−20

0W

V02

023

0 90

0 kg

(509

050

lb)

94.7

%10

50x3

95R

1612

.7 b

ar(1

84 p

si)

1400

x530

R23

OR

54x2

1−23

(bi

as)

14.2

bar

(206

psi

)

A33

0−20

0W

V02

123

0 90

0 kg

(509

050

lb)

94.7

%10

50x3

95R

1612

.7 b

ar(1

84 p

si)

A33

0−20

0W

V02

223

3 90

0 kg

(515

650

lb)

94.6

%10

50x3

95R

1612

.7 b

ar(1

84 p

si)

A33

0−20

0W

V02

323

3 90

0 kg

(515

650

lb)

94.6

%10

50x3

95R

1612

.7 b

ar(1

84 p

si)

A33

0−20

0W

V02

420

2 90

0 kg

(447

325

lb)

94.9

%10

50x3

95R

1612

.7 b

ar(1

84 p

si)

VA

RIA

NT

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

F_AC_070200_1_0030101_01_04

Landing Gear Footprint(Sheet 1 of 2)

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

7-2-0Page 2

Apr 01/13


**ON A/C A330-200

WE

IGH

TM

AX

IMU

MP

ER

CE

NT

AG

EN

OS

E G

EA

R T

IRE

NO

SE

GE

AR

MA

IN G

EA

R T

IRE

MA

IN G

EA

RR

AM

PW

EIG

HT

OF

WE

IGH

TO

N M

AIN

GE

AR

GR

OU

PS

IZE

TIR

EP

RE

SS

UR

ES

IZE

TIR

EP

RE

SS

UR

EV

AR

IAN

T

A33

0−20

0W

V02

522

0 90

0 kg

(487

000

lb)

94.8

%10

50x3

95R

1612

.7 b

ar(1

84 p

si)

A33

0−20

0W

V02

619

2 90

0 kg

(425

275

lb)

95.0

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V02

722

0 90

0 kg

(487

000

lb)

94.8

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V05

023

0 90

0 kg

(509

050

lb)

94.7

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V05

119

2 90

0 kg

(425

275

lb)

95.0

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V05

223

3 90

0 kg

(515

650

lb)

94.6

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V05

321

0 90

0 kg

(464

950

lb)

94.8

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V05

423

0 90

0 kg

(509

050

lb)

94.7

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V05

519

2 90

0 kg

(425

275

lb)

95.0

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V05

623

3 90

0 kg

(515

650

lb)

94.6

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V05

723

6 90

0 kg

(522

275

lb)

93.4

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V05

823

8 90

0 kg

(526

675

lb)

92.7

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V05

920

2 90

0 kg

(447

325

lb)

94.9

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V06

022

0 90

0 kg

(487

000

lb)

94.8

%12

.7 b

ar(1

84 p

si)

A33

0−20

0W

V06

123

0 90

0 kg

(509

050

lb)

94.7

%12

.7 b

ar(1

84 p

si)

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

F_AC_070200_1_0030104_01_01


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

7-2-0Page 3

Apr 01/13


**ON A/C A330-200F

WE

IGH

TM

AX

IMU

MP

ER

CE

NT

AG

EN

OS

E G

EA

R T

IRE

NO

SE

GE

AR

MA

IN G

EA

R T

IRE

MA

IN G

EA

RR

AM

PW

EIG

HT

OF

WE

IGH

TO

N M

AIN

GE

AR

GR

OU

PS

IZE

TIR

EP

RE

SS

UR

ES

IZE

TIR

EP

RE

SS

UR

E

A33

0−20

0FW

V00

023

3 90

0 kg

(515

650

lb)

94.6

%10

50x3

95R

1612

.7 b

ar(1

84 p

si)

1400

x530

R23

OR

54x2

1−23

(bi

as)

14.2

bar

(206

psi

)

A33

0−20

0FW

V00

122

7 90

0 kg

(502

425

lb)

94.7

%10

50x3

95R

1612

.7 b

ar(1

84 p

si)

A33

0−20

0FW

V00

223

3 90

0 kg

(515

650

lb)

94.6

%10

50x3

95R

1612

.7 b

ar(1

84 p

si)

VA

RIA

NT

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

0.71

0 m

(2.3

29 ft

)

10.6

84 m

22.1

80 m

(35.

052

ft)

(72.

768

ft)

1.39

7 m

1.98

1 m

(4.5

83 ft

)(6

.499

ft)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

F_AC_070200_1_0170101_01_03

Landing Gear FootprintFIGURE-7-2-0-991-017-A01

7-2-0Page 4

Apr 01/13


**ON A/C A330-300

0.71

0 m

(2.3

29 ft

)

10.6

84 m

25.3

75 m

(35.

052

ft)

(83.

251

ft)

1.39

7 m

1.98

1 m

(4.5

83 ft

)(6

.499

ft)

WE

IGH

TM

AX

IMU

MP

ER

CE

NT

AG

EN

OS

E G

EA

R T

IRE

NO

SE

GE

AR

MA

IN G

EA

R T

IRE

MA

IN G

EA

RR

AM

PW

EIG

HT

OF

WE

IGH

TO

N M

AIN

GE

AR

GR

OU

PS

IZE

TIR

EP

RE

SS

UR

ES

IZE

TIR

EP

RE

SS

UR

E

A33

0−30

0W

V00

021

2 90

0 kg

(469

375

lb)

94.9

%10

50x3

95R

1610

.7 b

ar(1

55 p

si)

1400

x530

R23

OR

54x2

1−23

(bi

as)

13.1

bar

(190

psi

)

A33

0−30

0W

V00

118

4 90

0 kg

(407

625

lb)

95.9

%10

50x3

95R

1610

.7 b

ar(1

55 p

si)

1050

x395

R16

10.7

bar

(155

psi

)

1050

x395

R16

1050

x395

R16

VA

RIA

NT

13.1

bar

(190

psi

)

13.1

bar

(190

psi

)

13.3

bar

(193

psi

)

13.3

bar

(193

psi

)

10.9

bar

(158

psi

)

10.9

bar

(158

psi

)

94.9

%

94.4

%

95.7

%

A33

0−30

0W

V00

221

2 90

0 kg

(469

375

lb)

A33

0−30

0W

V00

321

5 90

0 kg

(475

975

lb)

A33

0−30

0W

V00

420

9 90

0 kg

(462

750

lb)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

F_AC_070200_1_0060101_01_04


FIGURE-7-2-0-991-006-A01

7-2-0Page 5

Apr 01/13


**ON A/C A330-300

WE

IGH

TM

AX

IMU

MP

ER

CE

NT

AG

EN

OS

E G

EA

R T

IRE

NO

SE

GE

AR

MA

IN G

EA

R T

IRE

MA

IN G

EA

RR

AM

PW

EIG

HT

OF

WE

IGH

TO

N M

AIN

GE

AR

GR

OU

PS

IZE

TIR

EP

RE

SS

UR

ES

IZE

TIR

EP

RE

SS

UR

E

1050

x395

R16

VA

RIA

NT

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

1050

x395

R16

13.3

bar

(193

psi

)

13.3

bar

(193

psi

)

14.2

bar

(206

psi

)

14.5

bar

(210

psi

)

14.2

bar

(206

psi

)

14.2

bar

(206

psi

)

14.5

bar

(210

psi

)

14.5

bar

(210

psi

)

14.5

bar

(210

psi

)

14.5

bar

(210

psi

)

13.3

bar

(193

psi

)

13.3

bar

(193

psi

)

13.3

bar

(193

psi

)

13.3

bar

(193

psi

)

13.3

bar

(193

psi

)

1050

x395

R16

14.5

bar

(210

psi

)

10.9

bar

(158

psi

)

10.9

bar

(158

psi

)

10.9

bar

(158

psi

)

10.9

bar

(158

psi

)

10.9

bar

(158

psi

)

10.9

bar

(158

psi

)

10.9

bar

(158

psi

)

11.4

bar

(165

psi

)

11.6

bar

(168

psi

)

11.4

bar

(165

psi

)

11.4

bar

(165

psi

)

11.6

bar

(168

psi

)

11.6

bar

(168

psi

)

11.6

bar

(168

psi

)

11.6

bar

(168

psi

)

11.6

bar

(168

psi

)

95.6

%

94.0

%

95.6

%

95.7

%

95.6

%

95.6

%

95.7

%

95.5

%

95.5

%

95.7

%

95.6

%

95.5

%

95.7

%

95.5

%

95.7

%

94.7

%

A33

0−30

0W

V00

421

5 90

0 kg

(475

975

lb)

A33

0−30

0W

V01

021

7 90

0 kg

(480

375

lb)

A33

0−30

0W

V01

021

7 90

0 kg

(480

375

lb)

A33

0−30

0W

V01

121

2 90

0 kg

(469

375

lb)

A33

0−30

0W

V01

221

8 90

0 kg

(482

600

lb)

A33

0−30

0W

V01

321

5 90

0 kg

(475

975

lb)

A33

0−30

0W

V01

420

5 90

0 kg

(453

925

lb)

A33

0−30

0W

V02

023

0 90

0 kg

(509

050

lb)

A33

0−30

0W

V02

223

3 90

0 kg

(515

650

lb)

A33

0−30

0W

V02

420

5 90

0 kg

(453

925

lb)

A33

0−30

0W

V02

521

7 90

0 kg

(480

375

lb)

A33

0−30

0W

V05

023

0 90

0 kg

(509

050

lb)

A33

0−30

0W

V05

121

2 90

0 kg

(469

375

lb)

A33

0−30

0W

V05

223

3 90

0 kg

(515

650

lb)

A33

0−30

0W

V05

320

5 90

0 kg

(453

925

lb)

A33

0−30

0W

V05

423

5 90

0 kg

(520

075

lb)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

1400

x530

R23

OR

54x2

1−23

(bi

as)

F_AC_070200_1_0060102_01_00


FIGURE-7-2-0-991-006-A01

7-2-0Page 6

Apr 01/13


7-3-0 Maximum Pavement Loads

**ON A/C A330-200 A330-200F A330-300

Maximum Pavement Loads

1. This section shows maximum vertical and horizontal pavement loads for some critical conditions atthe tire-ground interfaces.The maximum pavement loads are given for all the aircraft operational weight variants.

7-3-0Page 1

Apr 01/13


**ON A/C A330-200

12

34

56

VN

GV

MG

(P

ER

ST

RU

T)

H (

PE

R S

TR

UT

)

A33

0−20

0W

V02

0

MO

DE

LM

AX

IMU

MR

AM

PM

OS

T F

WD

C.G

.@

10

ft/s

DE

CE

LER

AT

ION

MA

X A

FT

C.G

.@

10

ft/s

DE

CE

LER

AT

ION

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

WE

IGH

T

230

900

kg(5

09 0

50 lb

)

ST

AT

IC L

OA

D A

TS

TA

TIC

BR

AK

ING

ST

AT

IC L

OA

D A

TS

TE

AD

Y B

RA

KIN

GA

T IN

ST

AN

TA

NE

OU

S

25 1

70 k

g(5

5 50

0 lb

)39

570

kg

(87

225

lb)

109

290

kg(2

40 9

50 lb

)35

880

kg

(79

100

lb)

87 4

30 k

g(1

92 7

50 lb

)

A33

0−20

0W

V02

123

0 90

0 kg

(509

050

lb)

25 1

70 k

g(5

5 50

0 lb

)39

570

kg

(87

225

lb)

109

290

kg(2

40 9

50 lb

)35

880

kg

(79

100

lb)

87 4

30 k

g(1

92 7

50 lb

)

A33

0−20

0W

V02

223

3 90

0 kg

(515

650

lb)

25 1

70 k

g(5

5 50

0 lb

)39

750

kg

(87

625

lb)

110

670

kg(2

43 9

75 lb

)36

350

kg

(80

150

lb)

88 5

40 k

g(1

95 2

00 lb

)

A33

0−20

0W

V02

323

3 90

0 kg

(515

650

lb)

25 1

70 k

g(5

5 50

0 lb

)39

750

kg

(87

625

lb)

110

670

kg(2

43 9

75 lb

)36

350

kg

(80

150

lb)

88 5

40 k

g(1

95 2

00 lb

)

21%

MA

C37

.5%

MA

C

21%

MA

C

21.4

%M

AC

21.4

%M

AC

37.5

%M

AC

37.4

%M

AC

37.4

%M

AC

A33

0−20

0W

V02

420

2 90

0 kg

(447

325

lb)

24 2

20 k

g(5

3 40

0 lb

)36

990

kg

(81

550

lb)

96 3

00 k

g(2

12 3

00 lb

)31

530

kg

(69

500

lb)

77 0

40 k

g(1

69 8

50 lb

)

18%

MA

C38

.4%

MA

C

A33

0−20

0W

V02

522

0 90

0 kg

(487

000

lb)

25 1

60 k

g(5

5 47

5 lb

)38

980

kg

(85

925

lb)

104

650

kg(2

30 7

25 lb

)34

330

kg

(75

675

lb)

83 7

20 k

g(1

84 5

75 lb

)

19.5

7%M

AC

37.8

%M

AC

A33

0−20

0W

V02

619

2 90

0 kg

(425

275

lb)

23 0

50 k

g(5

0 82

5 lb

)35

240

kg

(77

700

lb)

91 6

70 k

g(2

02 1

00 lb

)29

980

kg

(66

100

lb)

73 3

30 k

g(1

61 6

75 lb

)

18%

MA

C38

.8%

MA

C

A33

0−20

0W

V02

722

0 90

0 kg

(487

000

lb)

25 1

60 k

g(5

5 47

5 lb

)38

980

kg

(85

925

lb)

104

650

kg(2

30 7

25 lb

)34

330

kg

(75

675

lb)

83 7

20 k

g(1

84 5

75 lb

)

19.5

7%M

AC

37.8

%M

AC

V(M

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

V(N

G)

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

GH

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

V(N

G)

V(M

G)

H

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

NO

TE

:

(a)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T M

RW

F_AC_070300_1_0010101_01_03

Maximum Pavement Loads(Sheet 1 of 2)

FIGURE-7-3-0-991-001-A01

7-3-0Page 2

Apr 01/13


**ON A/C A330-200

A33

0−20

0W

V05

119

2 90

0kg

(425

275

lb)

23 0

50 k

g(5

0 82

5 lb

)35

240

kg

(77

700

lb)

91 6

70 k

g(2

02 1

00 lb

)29

980

kg

(66

100

lb)

73 3

30 k

g(1

61 6

75 lb

)

A33

0−20

0W

V05

223

3 90

0 kg

(515

650

lb)

25 1

70 k

g(5

5 50

0 lb

)39

750

kg

(87

625

lb)

110

670

kg(2

43 9

75 lb

)36

350

kg

(80

150

lb)

88 5

40 k

g(1

95 2

00 lb

)

A33

0−20

0W

V05

321

0 90

0 kg

(464

950

lb)

25 1

50 k

g(5

5 45

0 lb

)38

390

kg

(84

625

lb)

100

010

kg(2

20 4

75 lb

)32

770

kg

(72

250

lb)

80 0

10 k

g(1

76 4

00 lb

)

A33

0−20

0W

V05

423

0 90

0 kg

(509

050

lb)

25 1

70 k

g(5

5 50

0 lb

)39

570

kg

(87

225

lb)

109

290

kg(2

40 9

50 lb

)35

880

kg

(79

100

lb)

87 4

30 k

g(1

92 7

50 lb

)

18%

MA

C38

.8%

MA

C

21.4

%M

AC

18%

MA

C

21%

MA

C

37.4

%M

AC

38.1

%M

AC

37.5

%M

AC

A33

0−20

0W

V05

519

2 90

0 kg

(425

275

lb)

23 0

50 k

g(5

0 82

5 lb

)35

240

kg

(77

700

lb)

91 6

70 k

g(2

02 1

00 lb

)29

980

kg

(66

100

lb)

73 3

30 k

g(1

61 6

75 lb

)

18%

MA

C38

.8%

MA

C

A33

0−20

0W

V05

623

3 90

0 kg

(515

650

lb)

25 1

70 k

g(5

5 50

0 lb

)39

750

kg

(87

625

lb)

110

670

kg(2

43 9

75 lb

)36

350

kg

(80

150

lb)

88 5

40 k

g(1

95 2

00 lb

)

21.4

%M

AC

37.4

%M

AC

A33

0−20

0W

V05

723

6 90

0 kg

(522

275

lb)

25 1

70 k

g(5

5 50

0 lb

)39

910

kg

(87

975

lb)

110

670

kg(2

43 9

75 lb

)36

820

kg

(81

175

lb)

88 5

40 k

g(1

95 2

00 lb

)

21.8

%M

AC

33.7

%M

AC

A33

0−20

0W

V05

823

8 90

0 kg

(526

675

lb)

25 1

70 k

g(5

5 50

0 lb

)40

020

kg

(88

225

lb)

110

670

kg(2

43 9

75 lb

)37

130

kg

(81

850

lb)

88 5

40 k

g(1

95 2

00 lb

)

22.0

6%M

AC

31.3

%M

AC

A33

0−20

0W

V05

920

2 90

0 kg

(447

325

lb)

24 2

20 k

g(5

3 40

0 lb

)36

990

kg

(81

550

lb)

96 3

00 k

g(2

12 3

00 lb

)31

530

kg

(69

500

lb)

77 0

40 k

g(1

69 8

50 lb

)

18%

MA

C38

.4%

MA

C

A33

0−20

0W

V06

022

0 90

0 kg

(487

000

lb)

25 1

40 k

g(5

5 42

5 lb

)38

960

kg

(85

900

lb)

104

650

kg(2

30 7

25 lb

)34

330

kg

(75

675

lb)

83 7

20 k

g(1

84 5

75 lb

)

19.6

%M

AC

37.8

%M

AC

A33

0−20

0W

V06

123

0 90

0 kg

(509

050

lb)

25 1

70 k

g(5

5 50

0 lb

)39

570

kg

(87

225

lb)

109

290

kg(2

40 9

50 lb

)35

880

kg

(79

100

lb)

87 4

30 k

g(1

92 7

50 lb

)

21%

MA

C37

.5%

MA

C

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

12

34

56

VN

GV

MG

(P

ER

ST

RU

T)

H (

PE

R S

TR

UT

)

MO

DE

LM

AX

IMU

MR

AM

PS

TA

TIC

LO

AD

AT

MO

ST

FW

D C

.G.

ST

AT

IC B

RA

KIN

G@

10

ft/s

DE

CE

LER

AT

ION

ST

AT

IC L

OA

D A

TM

AX

AF

T C

.G.

ST

EA

DY

BR

AK

ING

@ 1

0 ft/

sD

EC

ELE

RA

TIO

N

AT

INS

TA

NT

AN

EO

US

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

WE

IGH

T

NO

TE

:

(a)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T M

RW

A33

0−20

0W

V05

023

0 90

0 kg

(509

050

lb)

25 1

70 k

g(5

5 50

0 lb

)39

570

kg

(87

225

lb)

109

290

kg(2

40 9

50 lb

)35

880

kg

(79

100

lb)

87 4

30 k

g(1

92 7

50 lb

)M

AC

37.5

%M

AC

(a)

(a)

21%

F_AC_070300_1_0010107_01_01


FIGURE-7-3-0-991-001-A01

7-3-0Page 3

Apr 01/13


**ON A/C A330-200F

12

34

56

VN

GV

MG

(P

ER

ST

RU

T)

H (

PE

R S

TR

UT

)

A33

0−20

0FW

V00

0

MO

DE

LM

AX

IMU

MR

AM

P

233

900

kg(5

15 6

50 lb

)

ST

AT

IC L

OA

D A

TM

OS

T F

WD

C.G

.

ST

AT

IC B

RA

KIN

G@

10

ft/s

DE

CE

LER

AT

ION

ST

AT

IC L

OA

D A

TM

AX

AF

T C

.G.

ST

EA

DY

BR

AK

ING

@ 1

0 ft/

sD

EC

ELE

RA

TIO

N

AT

INS

TA

NT

AN

EO

US

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

WE

IGH

T

25 1

70 k

g(5

5 50

0 lb

)39

750

kg

(87

625

lb)

110

670

kg(2

43 9

75 lb

)36

350

kg

(80

150

lb)

88 5

40 k

g(1

95 2

00 lb

)

21.4

%M

AC

37.4

%M

AC

V(M

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

V(N

G)

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

GH

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

V(N

G)

V(M

G)

H

A33

0−20

0FW

V00

122

7 90

0 kg

(502

425

lb)

25 1

50 k

g(5

5 45

0 lb

)39

380

kg

(86

825l

b)10

7 90

0 kg

(237

875

lb)

35 4

20 k

g(7

8 10

0 lb

)86

320

kg

(190

300

lb)

20.6

%M

AC

37.6

%M

AC

A33

0−20

0FW

V00

223

3 90

0 kg

(515

650

lb)

25 1

70 k

g(5

5 50

0 lb

)39

750

kg

(87

625

lb)

110

670

kg(2

43 9

75 lb

)36

350

kg

(80

150

lb)

88 5

40 k

g(1

95 2

00 lb

)

21.4

%M

AC

37.4

%M

AC

NO

TE

:

(a)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T M

RW

(a)

(a)

(a)

(a)

(a)

(a)

F_AC_070300_1_0060101_01_03

Maximum Pavement LoadsFIGURE-7-3-0-991-006-A01

7-3-0Page 4

Apr 01/13


**ON A/C A330-300

12

34

56

VN

GV

MG

(P

ER

ST

RU

T)

H (

PE

R S

TR

UT

)

A33

0−30

0W

V00

0

MO

DE

LM

AX

IMU

MR

AM

P

212

900

kg(4

69 3

75 lb

)

ST

AT

IC L

OA

D A

TM

OS

T F

WD

C.G

.

ST

AT

IC B

RA

KIN

G@

10

ft/s

DE

CE

LER

AT

ION

ST

AT

IC L

OA

D A

TM

AX

AF

T C

.G.

ST

EA

DY

BR

AK

ING

@ 1

0 ft/

sD

EC

ELE

RA

TIO

N

AT

INS

TA

NT

AN

EO

US

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

WE

IGH

T

24 3

40 k

g(5

3 65

0 lb

)35

930

kg

(79

200

lb)

100

970

kg(2

22 6

00 lb

)33

090

kg

(72

950

lb)

80 7

80 k

g(1

78 1

00 lb

)

15%

MA

C36

.5%

MA

C

15%

MA

C

15%

MA

C

15%

MA

C

A33

0−30

0

A33

0−30

0

A33

0−30

0

WV

001

WV

002

WV

003

184

900

kg(4

07 6

25 lb

)21

200

kg

(46

750

lb)

31 3

70 k

g(6

9 15

0 lb

)88

620

kg

(195

375

lb)

28 7

30 k

g(6

3 35

0 lb

)70

900

kg

(156

300

lb)

212

900

kg(4

69 3

75 lb

)24

340

kg

(53

650

lb)

35 9

30 k

g(7

9 20

0 lb

)10

0 97

0 kg

(222

600

lb)

33 0

90 k

g(7

2 95

0 lb

)80

780

kg

(178

100

lb)

215

900

kg(4

75 9

75 lb

)24

670

kg

(54

400

lb)

36 4

10 k

g(8

0 27

5 lb

)10

1 86

0 kg

(224

575

lb)

33 5

50 k

g(7

3 97

5 lb

)81

490

kg

(179

650

lb)

40.1

%M

AC

36.5

%M

AC

34.8

%M

AC

15%

MA

C

15%

MA

C

15%

MA

C

15%

MA

C

A33

0−30

0

A33

0−30

0

A33

0−30

0

A33

0−30

0

WV

004

WV

004

WV

010

WV

010

209

900

kg(4

62 7

50 lb

)35

440

kg

(78

125

lb)

100

430

kg(2

21 4

00 lb

)32

620

kg

(71

925

lb)

80 3

40 k

g(1

77 1

25 lb

)M

AC

24 0

00 k

g(5

2 90

0 lb

)

215

900

kg(4

75 9

75 lb

)36

410

kg

(80

275

lb)

103

250

kg(2

27 6

25 lb

)33

550

kg

(73

975

lb)

82 6

00 k

g(1

82 1

00 lb

)M

AC

24 6

70 k

g(5

4 40

0 lb

)

217

900

kg(4

80 3

75 lb

)36

740

kg

(81

000

lb)

102

390

kg(2

25 7

25 lb

)33

860

kg

(74

650

lb)

81 9

10 k

g(1

80 5

75 lb

)M

AC

24 9

00 k

g(5

4 90

0 lb

)

217

900

kg(4

80 3

75 lb

)36

740

kg

(81

000

lb)

104

180

kg(2

29 6

75 lb

)33

860

kg

(74

650

lb)

83 3

50 k

g(1

83 7

50 lb

)M

AC

24 9

00 k

g(5

4 90

0 lb

)

39.4

%

39.2

%

33.5

%

39.1

3%

V(M

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

V(N

G)

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

GH

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

V(N

G)

V(M

G)

H

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

NO

TE

:

(a)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T M

RW

F_AC_070300_1_0030101_01_03


FIGURE-7-3-0-991-003-A01

7-3-0Page 5

Apr 01/13


**ON A/C A330-300

12

34

56

VN

GV

MG

(P

ER

ST

RU

T)

H (

PE

R S

TR

UT

)

MO

DE

LM

AX

IMU

MR

AM

PS

TA

TIC

LO

AD

AT

MO

ST

FW

D C

.G.

ST

AT

IC B

RA

KIN

G@

10

ft/s

DE

CE

LER

AT

ION

ST

AT

IC L

OA

D A

TM

AX

AF

T C

.G.

ST

EA

DY

BR

AK

ING

@ 1

0 ft/

sD

EC

ELE

RA

TIO

N

AT

INS

TA

NT

AN

EO

US

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

WE

IGH

T

15%

MA

C

15%

MA

C

15%

MA

C

18%

MA

C

18.4

%M

AC

15%

MA

C

16.1

1%M

AC

18%

MA

C

15.3

3%M

AC

18.4

%M

AC

15%

MA

C

18.7

%M

AC

A33

0−30

0

A33

0−30

0

A33

0−30

0

A33

0−30

0

A33

0−30

0

A33

0−30

0

A33

0−30

0

A33

0−30

0

A33

0−30

0

A33

0−30

0

A33

0−30

0

WV

012

WV

013

WV

014

WV

020

WV

022

WV

024

WV

025

WV

050

WV

052

WV

051

WV

053

WV

054

38.6

%

39.6

%

39.1

2%

38.7

%

39.2

9%

218

900

kg(4

82 6

00 lb

)36

900

kg

(81

350

lb)

104

650

kg(2

30 7

25 lb

)34

020

kg

(75

000

lb)

83 7

20 k

g(1

84 5

75 lb

)M

AC

25 0

10 k

g(5

5 15

0 lb

)

215

900

kg(4

75 9

75 lb

)36

410

kg

(80

275

lb)

103

250

kg(2

27 6

25 lb

)33

550

kg

(73

975

lb)

82 6

00 k

g(1

82 1

00 lb

)M

AC

24 6

70 k

g(5

4 40

0 lb

)

205

900

kg(4

53 9

25 lb

)34

790

kg

(76

700

lb)

98 5

70 k

g(2

17 3

00 lb

)32

000

kg

(70

550

lb)

78 8

60 k

g(1

73 8

50 lb

)M

AC

23 5

50 k

g(5

1 92

5 lb

)

230

900

kg(5

09 0

50 lb

)36

940

kg

(81

450

lb)

110

270

kg(2

43 1

00 lb

)35

880

kg

(79

100

lb)

88 2

20 k

g(1

94 5

00 lb

)M

AC

24 3

40 k

g(5

3 65

0 lb

)

233

900

kg(5

15 6

50 lb

)37

130

kg

(81

850

lb)

111

670

kg(2

46 2

00 lb

)36

350

kg

(80

150

lb)

89 3

40 k

g(1

96 9

50 lb

)M

AC

24 3

80 k

g(5

3 75

0 lb

)

205

900

kg(4

53 9

25 lb

)34

790

kg

(76

700

lb)

98 5

70 k

g(2

17 3

00 lb

)32

000

kg

(70

550

lb)

78 8

60 k

g(1

73 8

50 lb

)M

AC

23 5

50 k

g(5

1 92

5 lb

)

217

900

kg(4

80 3

75 lb

)36

030

kg

(79

425

lb)

104

180

kg(2

29 6

75 lb

)33

860

kg

(74

650

lb)

83 3

40 k

g(1

83 7

25 lb

)M

AC

24 1

90 k

g(5

3 32

5 lb

)

212

900

kg(4

69 3

75 lb

)35

720

kg

(78

750l

b)10

1 83

0 kg

(224

500

lb)

33 0

90 k

g(7

2 95

0 lb

)81

470

kg

(179

600

lb)

MA

C

24 1

30 k

g(5

3 20

0 lb

)M

AC

233

900

kg(5

15 6

50 lb

)37

030

kg

(81

625

lb)

111

670

kg(2

46 2

00 lb

)36

350

kg

(80

150

lb)

89 3

40 k

g(1

96 9

50 lb

)M

AC

24 3

80 k

g(5

3 75

0 lb

)

205

900

kg(4

53 9

25 lb

)34

790

kg

(76

700

lb)

98 5

70 k

g(2

17 3

00 lb

)32

000

kg

(70

550

lb)

78 8

60 k

g(1

73 8

50 lb

)M

AC

23 5

50 k

g(5

1 92

5 lb

)

235

900

kg(5

20 0

75 lb

)37

130

kg

(81

850

lb)

111

670

kg(2

46 2

00 lb

)36

660

kg

(80

825

lb)

89 3

40 k

g(1

96 9

50 lb

)M

AC

24 3

80 k

g(5

3 75

0 lb

)

38.6

%

39.6

%

35.7

%

39.1

%

39.2

%

39.6

%

38.7

%

230

900

kg(5

09 0

50 lb

)36

840

kg

(81

225

lb)

110

270

kg(2

43 1

00 lb

)35

880

kg

(79

100

lb)

88 2

20 k

g(1

94 5

00 lb

)24

340

kg

(53

650

lb)

(a)

NO

TE

:

(a)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T M

RW

A33

0−30

0

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

(a)

15%

MA

CA

330−

300

WV

011

212

900

kg(4

69 3

75 lb

)35

930

kg

(79

200

lb)

101

840

kg(2

24 5

25 lb

)33

090

kg

(72

950

lb)

81 4

70 k

g(1

79 6

00 lb

)M

AC

24 3

40 k

g(5

3 65

0 lb

)

39.3

%

(a)

(a)

F_AC_070300_1_0030102_01_01


FIGURE-7-3-0-991-003-A01

7-3-0Page 6

Apr 01/13


7-4-0 Landing Gear Loading on Pavement

**ON A/C A330-200 A330-200F A330-300

Landing Gear Loading on Pavement

1. This section gives data about the landing gear loading on pavement.The MLG loading on pavement graphs are given for the weight variants that produce (at the MRWand max aft CG) the lowest MLG load and the highest MLG load of each A/C type.

Example, see FIGURE 7---0-99--001-A, calculation of the total weight on the MLG for:- An aircraft with a MRW of 192 900 kg (425 275 lb),- The aircraft gross weight is 160 000 kg (352 740 lb),- A percentage of weight on MLG of 95,0% (percentage of weight on MLG at MRW and CG max

aft).The total weight on the MLG group is 152 060 kg (335 250 lb).

7-4-0Page 1

Apr 01/13


**ON A/C A330-200

120

130

140

150

160

170

180

190

200

210

220

230

240

PERCENTAGE OF WEIGHT ON MAIN GEAR

(x 1

000

kg)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1000

Kg)

CG FOR ACNCALCULATION

38.8% MAC

TAKE OFF

MTOW − 192 000 Kg

MLW

LANDING

18% MAC

MZFW

500

450

400

350

300

250

(x 1

000

lb)

11010098969492908886

110

120

130

140

150

160

170

180

190

200

210

220

230

240

AIR

CR

AF

T G

RO

SS

WE

IGH

T

F_AC_070400_1_0010101_01_01

Landing Gear Loading on PavementWV026, MRW 192 900 kg (Sheet 1 of 2)

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

7-4-0Page 2

Apr 01/13


**ON A/C A330-200

120

130

140

150

160

170

180

190

200

210

220

230

240


(x 1

000

kg)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1000

Kg)

500

450

400

350

300

250

(x 1

000

lb)

11010098969492908886

110

120

130

140

150

160

170

180

190

200

210

220

230

240

AIR

CR

AF

T G

RO

SS

WE

IGH

T


31.3% MACMTOW − 238 000 Kg

22.06% MAC

MLW

MZFW

TAKE OFF

LANDING

F_AC_070400_1_0020101_01_01F_AC_070400_1_0010103_01_00


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

7-4-0Page 3

Apr 01/13


**ON A/C A330-200F

120

130

140

150

160

170

180

190

200

210

220

230

240


(x 1

000

kg)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1000

Kg)

500

450

400

350

300

250

(x 1

000

lb)

11010098969492908886

110

120

130

140

150

160

170

180

190

200

210

220

230

240

AIR

CR

AF

T G

RO

SS

WE

IGH

T


37.6% MACMTOW − 227 000 kg

20.6% MAC

MLW

MZFW

TAKE OFF

LANDING

F_AC_070400_1_0030101_01_01


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

7-4-0Page 4

Apr 01/13


**ON A/C A330-200F

120

130

140

150

160

170

180

190

200

210

220

230

240


(x 1

000

kg)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1000

Kg)

500

450

400

350

300

250

(x 1

000

lb)

11010098969492908886

110

120

130

140

150

160

170

180

190

200

210

220

230

240

AIR

CR

AF

T G

RO

SS

WE

IGH

T

MTOW − 233 000 kg

21.4% MAC

MLW

MZFW

TAKE OFF


37.4% MAC

LANDING

F_AC_070400_1_0030201_01_01F_AC_070400_1_0030102_01_00


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

7-4-0Page 5

Apr 01/13


**ON A/C A330-300

120

130

140

150

160

170

180

190

200

210

220

230

240


(x 1

000

kg)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1000

Kg)

500

450

400

350

300

250

(x 1

000

lb)

11010098969492908886

110

120

130

140

150

160

170

180

190

200

210

220

230

240

AIR

CR

AF

T G

RO

SS

WE

IGH

T

15% MAC

MLW

MZFW

TAKE OFF


40.1% MAC

MTOW − 184 000 kg

LANDING

F_AC_070400_1_0040101_01_01


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

7-4-0Page 6

Apr 01/13


**ON A/C A330-300

120

130

140

150

160

170

180

190

200

210

220

230

240


(x 1

000

kg)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1000

Kg)

500

450

400

350

300

250

(x 1

000

lb)

11010098969492908886

110

120

130

140

150

160

170

180

190

200

210

220

230

240

AIR

CR

AF

T G

RO

SS

WE

IGH

T

18.7% MAC

TAKE OFF


35.7% MACMTOW − 235 000 kg

MLW

MZFW

LANDING

F_AC_070400_1_0040201_01_01F_AC_070400_1_0040102_01_00


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

7-4-0Page 7

Apr 01/13


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

**ON A/C A330-200 A330-200F A330-300

Flexible Pavement Requirements - US Army Corps of Engineers Design Method S-77-1

1. This section gives data about the flexible pavement requirements.The flexible pavement requirements graphs are given at standard tire pressure for the weight variantsthat produce (at the MRW and max aft CG) the lowest main MLG and the highest MLG load ofeach A/C type.They are calculated with the US Army Corps of Engineers Design Method.To find a flexible pavement thickness, you must know the Subgrade Strength (CBR), the annualdeparture level and the weight on one MLG.The line that shows 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).The procedure that follows is used to develop flexible pavement design curves:- With the scale for pavement thickness at the bottom and the scale for CBR at the top, a random

line is made to show 10 000 coverages,- A plot is then made of the incremental values of the weight on the MLG,- Annual departure lines are made based on the load lines of the weight on the MLG that is shown

on the graph.

Example, see FIGURE 7---0-99--002-A, calculation of the thickness of the flexible pavement for:- An aircraft with a MRW of 192 900 kg (425 275 lb),- A ”CBR” value of 10,- An annual departure level of 3 000,- The load on one MLG of 80 000 kg (176 375 lb).The required flexible pavement thickness is 48.7 cm (19 in).

NOTE : The CG in the figure title is the CG used for ACN / LCN calculation

7-5-0Page 1

Apr 01/13


**ON A/C A330-200

SUBGRADE STRENGTH − CBR

3 10 15 20 30 40 60 80

FLEXIBLE PAVEMENT THICKNESS

1400x530R23 OR 54x21−23 (bias) TIRESTIRE PRESSURE CONSTANT AT 14.2 bar (206 psi)

(cm)

(in)

MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT ANDAFT CG

10 000 COVERAGESUSED FOR ACNCALCULATIONS

6

3 10 15 20 30 40 60 806

10 15 20 30 40 60 80 100 120 150180

50 000 kg (110 225 lb)60 000 kg (132 275 lb)70 000 kg (154 325 lb)80 000 kg (176 375 lb)91 670 kg (202 100 lb)WEIGHT ON ONE MAIN LANDING GEAR

ALPHA FACTOR = 0.8*20 YEAR PAVEMENT LIFE25.00015.0006.0003.0001.200ANNUAL DEPARTURES*

F_AC_070500_1_0020101_01_00

Flexible Pavement RequirementsWV026, MRW 192 900 kg, CG 38.8 % (Sheet 1 of 2)

FIGURE-7-5-0-991-002-A01

7-5-0Page 2

Apr 01/13


**ON A/C A330-200


3 10 15 20 30 40 60 80



(cm)

(in)

6

3 10 15 20 30 40 60 806

10 15 20 30 40 60 80 100 120 150180





F_AC_070500_1_0020201_01_00F_AC_070500_1_0020102_01_00


FIGURE-7-5-0-991-002-A01

7-5-0Page 3

Apr 01/13


**ON A/C A330-200F


3 10 15 20 30 40 60 80



(cm)

(in)

6

3 10 15 20 30 40 60 806

10 15 20 30 40 60 80 100 120 150180





F_AC_070500_1_0030101_01_00


FIGURE-7-5-0-991-003-A01

7-5-0Page 4

Apr 01/13


**ON A/C A330-200F


3 10 15 20 30 40 60 80



(cm)

(in)

6

3 10 15 20 30 40 60 806

10 15 20 30 40 60 80 100 120 150180





F_AC_070500_1_0030201_01_00F_AC_070500_1_0030102_01_00


FIGURE-7-5-0-991-003-A01

7-5-0Page 5

Apr 01/13


**ON A/C A330-300


3 10 15 20 30 40 60 80



(cm)

(in)



6

3 10 15 20 30 40 60 806

10 15 20 30 40 60 80 100 120 150180



F_AC_070500_1_0040101_01_00


FIGURE-7-5-0-991-004-A01

7-5-0Page 6

Apr 01/13


**ON A/C A330-300


3 10 15 20 30 40 60 80



(cm)

(in)

6

3 10 15 20 30 40 60 806

10 15 20 30 40 60 80 100 120 150180





F_AC_070500_1_0040201_01_00F_AC_070500_1_0040102_01_00


FIGURE-7-5-0-991-004-A01

7-5-0Page 7

Apr 01/13


7-6-0 Flexible Pavement Requirements - LCN Conversion

**ON A/C A330-200 A330-200F A330-300

Flexible Pavement Requirements - LCN Conversion

1. This section gives data about the flexible pavement requirements for Load Classification Number(LCN) conversion.The flexible pavement requirements graphs are given at standard tire pressure for the weight variantsproducing (at the MRW and max aft CG) the lowest MLG load and the highest MLG load of eachA/C type.To find the aircraft weight that a flexible pavement can support, you must know the LCN of thepavement and the thickness.

Example, see FIGURE 7---0-99--010-A, calculation of the thickness of the flexible pavement for:- An aircraft with a MRW of 192 900 kg (425 275 lb),- The flexible pavement thickness is 1143 mm (45 in) with a related LCN of 108.The weight on one MLG is 80 000 kg (176 375 lb).

2. Flexible Pavement Requirements - LCN tableThe following table provides LCN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1977”. In order to use the system accuratelyyou should know the total pavement thickness for flexible pavement.However, the pavement thickness for a particular runway are not frequently published in the standardairport information sources (Jeppesen, AERAD, DOD, etc.).Therefore it is common practice to use a standard thickness (20 in) when determining the LCN andthe ESWL of the aircraft.

If the LCN for an intermediate weight between MRW and the empty weight of the aircraft is requiredor if the real thickness is known, refer to figures that follow.


7-6-0Page 1

Apr 01/13


**ON A/C A330-200

AIRCRAFT TYPE

A330−200WV020

ALL UPMASS (kg)

LOAD ONONE MAINGEAR LEG

(%)

TIREPRESSURE

(Mpa)

FLEXIBLE PAVEMENTESWL

x 1000 kg h = 510 mm (20 in)

x 1000 lbLCN

230 900120 000

47.347.2

1.42 2814

6131

9654

A330−200WV021

230 900 47.347.2

A330−200WV022

233 900 47.347.2

A330−200WV023

233 900 47.347.2

A330−200WV024

202 900 47.547.3

24

A330−200WV025

220 900 47.447.2

27

A330−200WV026

192 900 47.547.4

23

A330−200WV027

220 900 47.447.2

27

A330−200WV050

230 900 47.347.2

28

A330−200WV051

192 900 47.547.4

23

A330−200WV052

233 900 47.347.2

28

A330−200WV053

210 900 47.447.3

25

A330−200WV054

230 900 47.347.2

28

A330−200WV055

192 900 47.547.4

23

A330−200WV056

233 900 47.347.2

28

A330−200WV057

236 900 46.746.6

28

A330−200WV058

238 900 46.346.2

28

A330−200WV059

202 900 47.547.3

24

A330−200WV060

220 900 47.447.2

27

A330−200WV061

230 900 47.347.2

28

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

281428142814

14

14

14

14

14

14

14

14

14

14

14

14

14

14

14

14 31 54

31 54

31 54

31 53

31 53

31 54

31 54

31 54

31 54

31 54

31 54

31 54

31 54

31 54

31 54

31 54

31 54

31 54

31 54

62

62

53

59

51

59

61

51

62

56

61

51

62

62

62

53

59

61

96

97

97

86

92

82

92

96

82

97

89

96

82

97

97

97

86

92

96

61120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

F_AC_070600_1_0100101_01_00

Flexible Pavement RequirementsLCN table

FIGURE-7-6-0-991-010-A01

7-6-0Page 2

Apr 01/13


**ON A/C A330-200

50 0

00 k

g

(110

225

lb)

60 0

00 k

g

(132

275

lb)

70 0

00 k

g

(154

325

lb)

80 0

00 k

g

(176

375

lb)

91 6

70 k

g

(202

100

lb)

LAN

DIN

G G

EA

RW

EIG

HT

ON

ON

E M

AIN

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG

1020

3040

5060

8010

010203040506070809010

0

110

120

130

140

150

160

500

750

1000

1500

2000

2500

203040506070

2030

4050

6080

7010

0 120

150 18

023

0

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

2 ba

r (2

06 p

si)

1400

x530

R23

OR

54x

21−

23 (

bias

) T

IRE

S

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

in)

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQUIVALENT SINGLE WHEEL LOAD (1000 lb)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:

EQUIVALENT SINGLE WHEEL LOAD (1000 kg)

F_AC_070600_1_0010101_01_00

Flexible Pavement Requirements - LCNWV026, MRW 192 900 kg, CG 38.8 % (Sheet 1 of 2)

FIGURE-7-6-0-991-001-A01

7-6-0Page 3

Apr 01/13


**ON A/C A330-200

1020

3040

5060

8010

0102030405060708090100

110

120

130

140

150

160

500

750

1000

1500

2000

2500

203040506070

2030

4050

6080

7010

0 120

150 18

023

0

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

2 ba

r (2

06 p

si)

1400

x530

R23

OR

54x

21−

23 (

bias

) T

IRE

S

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

in)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:

70 0

00 k

g

(154

325

lb)

80 0

00 k

g

(176

375

lb)

90 0

00 k

g

(198

425

lb)

100

000

kg

(22

0 45

0 lb

)11

0 67

0 kg

(

243

975

lb)

LAN

DIN

G G

EA

RW

EIG

HT

ON

ON

E M

AIN

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG


F_AC_070600_1_0010201_01_00F_AC_070600_1_0010103_01_00


FIGURE-7-6-0-991-001-A01

7-6-0Page 4

Apr 01/13


**ON A/C A330-200F

AIRCRAFT TYPE

A330−200FWV000

ALL UPMASS (kg)


(%)

TIREPRESSURE

(Mpa)


x 1000 kg h = 510 mm (20 in)

x 1000 lbLCN

233 900120 000

47.347.2

1.42 2814

6231

9754

A330−200FWV001

227 900120 000

47.347.2

A330−200FWV002

1.42

1.42 2714 31 54

9561

2814

6231

9754

233 900120 000

47.347.2

F_AC_070600_1_0110101_01_00


FIGURE-7-6-0-991-011-A01

7-6-0Page 5

Apr 01/13


**ON A/C A330-200F

1020

3040

5060

8010

0102030405060708090100

110

120

130

140

150

160

500

750

1000

1500

2000

2500

203040506070

2030

4050

6080

7010

0 120

150 18

023

0

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

2 ba

r (2

06 p

si)

1400

x530

R23

OR

54x

21−

23 (

bias

) T

IRE

S

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

in)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:

70 0

00 k

g

(154

325

lb)

80 0

00 k

g

(176

375

lb)

90 0

00 k

g

(198

425

lb)

107

900

kg

(23

7 87

5 lb

)LA

ND

ING

GE

AR

WE

IGH

T O

N O

NE

MA

IN

60 0

00 k

g

(132

275

lb)

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG


F_AC_070600_1_0020101_01_00


FIGURE-7-6-0-991-002-A01

7-6-0Page 6

Apr 01/13


**ON A/C A330-200F

1020

3040

5060

8010

0102030405060708090100

110

120

130

140

150

160

500

750

1000

1500

2000

2500

203040506070

2030

4050

6080

7010

0 120

150 18

023

0

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

2 ba

r (2

06 p

si)

1400

x530

R23

OR

54x

21−

23 (

bias

) T

IRE

S

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

in)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:

70 0

00 k

g

(154

325

lb)

80 0

00 k

g

(176

375

lb)

90 0

00 k

g

(198

425

lb)

100

000

kg

(22

0 45

0 lb

)11

0 67

0 kg

(

243

975

lb)

LAN

DIN

G G

EA

RW

EIG

HT

ON

ON

E M

AIN

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG


F_AC_070600_1_0020201_01_00F_AC_070600_1_0020102_01_00


FIGURE-7-6-0-991-002-A01

7-6-0Page 7

Apr 01/13


**ON A/C A330-300

AIRCRAFT TYPE

A330−300

WV001

WV003

WV002

WV004 (209)

WV010

WV004 (215)

WV010b

WV012

WV011

WV013

WV020

WV014

WV022

WV025

WV024

WV050

WV052

WV051

WV053

WV054

WV055

ALL UPMASS (kg)


(%)

TIREPRESSURE

(Mpa)


x 1000 kg h = 510 mm (20 in)

x 1000 lbLCN

212 900 47.447.3

1.31 2615

A330−300 212 900 47.447.3

1.31 26

A330−300 184 900 47.947.9

1.31 2215

A330−300 215 900 47.247.1

1.33 26

A330−300 215 900 47.847.7

1.33 26

A330−300 209 900 47.847.8

1.33 26

A330−300 217 900 47.046.9

1.33 26

A330−300 212 900 47.847.7

1.33 26

A330−300 217 900 47.847.7

1.33 27

A330−300 218 900 47.847.7

1.33 27

A330−300 205 900 47.947.8

1.33 25

A330−300 215 900 47.847.7

1.33 26

A330−300 230 900 47.847.7

1.42 28

A330−300 205 900 47.947.8

1.42 25

A330−300 233 900 47.747.6

1.45 28

A330−300 217 900 47.847.7

1.42 26

A330−300 212 900 47.847.7

1.45 26

A330−300 230 900 47.847.7

1.45 28

A330−300 233 900 47.747.6

1.45 28

A330−300 205 900 47.947.8

1.45 25

A330−300 235 900 47.347.2

1.45 28

A330−300 235 900 42.142.0

1.45 2513

15

15

15

15

15

15

15

15

15

15

15

15

15

15

15

15

15

15

15

WV0005733

8554

5733

8554

4933

7654

5732

8754

5833

8855

5633

8655

5832

8754

5733

8755

5933

8855

5933

8955

5533

8455

5833

8855

6233

9656

5533

8757

6333

9957

5833

9256

5733

9157

6233

9857

6333

9957

5533

8857

6333

9956

5529

8951

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

125 000

F_AC_070600_1_0120101_01_00


FIGURE-7-6-0-991-012-A01

7-6-0Page 8

Apr 01/13


**ON A/C A330-300

1020

3040

5060

8010

0102030405060708090100

110

120

130

140

150

160

500

750

1000

1500

2000

2500

203040506070

2030

4050

6080

7010

0 120

150 18

023

0

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

1 ba

r (1

90 p

si)

1400

x530

R23

OR

54x

21−

23 (

bias

) T

IRE

S

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

in)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:

50 0

00 k

g

(110

225

lb)

60 0

00 k

g

(132

275

lb)

70 0

00 k

g

(154

325

lb)

40 0

00 k

g

(88

175

lb)

88 6

20 k

g

(195

375

lb)

LAN

DIN

G G

EA

RW

EIG

HT

ON

ON

E M

AIN

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG


F_AC_070600_1_0030101_01_00


FIGURE-7-6-0-991-003-A01

7-6-0Page 9

Apr 01/13


**ON A/C A330-300

1020

3040

5060

8010

0102030405060708090100

110

120

130

140

150

160

500

750

1000

1500

2000

2500

203040506070

2030

4050

6080

7010

0 120

150 18

023

0

10

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

5 ba

r (2

10 p

si)

1400

x530

R23

OR

54x

21−

23 (

bias

) T

IRE

S

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

in)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:

70 0

00 k

g

(154

325

lb)

80 0

00 k

g

(176

375

lb)

90 0

00 k

g

(198

425

lb)

100

000

kg

(22

0 45

0 lb

)

LAN

DIN

G G

EA

RW

EIG

HT

ON

ON

E M

AIN

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG

111

670

kg

(24

6 20

0 lb

)


F_AC_070600_1_0030201_01_00F_AC_070600_1_0030102_01_00


FIGURE-7-6-0-991-003-A01

7-6-0Page 10

Apr 01/13


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

**ON A/C A330-200 A330-200F A330-300

Rigid Pavement Requirements - Portland Cement Association Design Method

1. This section gives data about the rigid pavement requirements for the PCA (Portland CementAssociation) design method.The rigid pavement requirements graphs are given at standard tire pressure for the weight variantsproducing (at the MRW and max aft CG) the lowest MLG load and the highest MLG load of eachA/C type.To find a rigid pavement thickness, you must know the Subgrade Modulus (K), the permittedworking stress and the weight on one MLG.The procedure that follows is used to develop rigid pavement design curves:- With the scale for pavement thickness on the left and the scale for permitted working stress on

the right, a random load line is made.This represents the MLG maximum weight to be shown.

- A plot is then made of all values of the subgrade modulus (k values).- More load lines for the incremental values of weight on the MLG are made based on the curve for

k= 80MN/m3 already shown on the graph.

Example, see FIGURE 7---0-99--001-A, calculation of the thickness of the rigid pavement for:- An aircraft with a MRW of 192 900 kg (425 275 lb),- A k value of 80 MN/m3 (300 lbf/in3),- A permitted working stress of 38.67 kg/cm2 (550 lb/in2),- The load on one MLG is 80 000 kg (176 375 lb).The required rigid pavement thickness is 230 mm (9 in).


7-7-0Page 1

Apr 01/13


**ON A/C A330-200


60

50

40

30

20

10

100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8

(kg/

cm²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

(lb/in

²)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S(c

m)

(in)

FOR LOADS LESS THAN MAXIMUM,EXACT.LINE AND ANY VALUES FOR K ARETHE MAXIMUM LOAD REFERENCETHE VALUES OBTAINED BY USINGNOTES:

THE CURVES ARE EXACT FOR K =80 MN/m³ BUT DEVIATE SLIGHTLYFOR ANY OTHER VALUES OF K.

PDILB" PORTLAND CEMENTPAVEMENT DESIGN − PROGRAMPROGRAM FOR AIRPORTPAVEMENTS" AND "COMPUTER"DESIGN OF CONCRETE AIRPORTREFERENCE:

ASSOCIATION.

K = 150 MN/m³K = 80 MN/m³K = 40 MN/m³K = 20 MN/m³

RAMP WEIGHT AND AFT CGGEAR LOAD AT MAXIMUMMAXIMUM POSSIBLE MAIN

60 000 kg (132 275 lb)70 000 kg (154 325 lb)80 000 kg (176 375 lb)91 670 kg (202 100 lb)LANDING GEARWEIGHT ON ONE MAIN

50 000 kg (110 225 lb)

F_AC_070700_1_0010101_01_00

Rigid Pavement RequirementsWV026, MRW 192 900 kg, CG 38.8 % (Sheet 1 of 2)

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

7-7-0Page 2

Apr 01/13


**ON A/C A330-200


60

50

40

30

20

10

100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8

(kg/

cm²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

(lb/in

²)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S(c

m)

(in)




ASSOCIATION.




70 000 kg (154 325 lb)

F_AC_070700_1_0010201_01_00F_AC_070700_1_0010102_01_00


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

7-7-0Page 3

Apr 01/13


**ON A/C A330-200F


60

50

40

30

20

10

100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8

(kg/

cm²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

(lb/in

²)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S(c

m)

(in)




ASSOCIATION.




60 000 kg (132 275 lb)

F_AC_070700_1_0020101_01_00


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

7-7-0Page 4

Apr 01/13


**ON A/C A330-200F


60

50

40

30

20

10

100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8

(kg/

cm²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

(lb/in

²)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S(c

m)

(in)




ASSOCIATION.




70 000 kg (154 325 lb)

F_AC_070700_1_0020201_01_00F_AC_070700_1_0020102_01_00


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

7-7-0Page 5

Apr 01/13


**ON A/C A330-300


60

50

40

30

20

10

100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8

(kg/

cm²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

(lb/in

²)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S(c

m)

(in)




ASSOCIATION.




40 000 kg (88 175 lb)

F_AC_070700_1_0030101_01_00


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

7-7-0Page 6

Apr 01/13


**ON A/C A330-300


60

50

40

30

20

10

100

200

300

400

500

600

700

800

90015

14

38

36

34

32

13

1230

28 11

26

24

22

10

9

20

18 7

8

(kg/

cm²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S

(lb/in

²)

RIG

ID P

AV

EM

EN

T T

HIC

KN

ES

S(c

m)

(in)




ASSOCIATION.




70 000 kg (154 325 lb)

F_AC_070700_1_0030201_01_00F_AC_070700_1_0030102_01_00


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

7-7-0Page 7

Apr 01/13


7-8-0 Rigid Pavement Requirements - LCN Conversion

**ON A/C A330-200 A330-200F A330-300

Rigid Pavement Requirements - LCN Conversion

1. This section gives data about the rigid pavement requirements for the Load Classification Number(LCN) conversion (radius of relative stiffness).The rigid pavement requirements graphs are given at standard tire pressure for the weight variantsproducing (at the MRW and max aft CG) the lowest MLG load and the highest MLG load of eachA/C type.To find the aircraft weight that a rigid pavement can support, you must know the LCN of thepavement and the radius of relative stiffness (L).The calculation of the radius of relative stiffness (L) is done with the formula and the table given in”Radius of Relative Stiffness” (L values based on Young’s Modulus (E) of 4 000 000 psi andPoisson’s Ratio (µ) of 0.15), see FIGURE 7---0-99--001-A.

Example, see FIGURE 7---0-99--004-A, calculation of the aircraft weight through the radius ofrelative stiffness (L) of the rigid pavement for:- An aircraft with a MRW of 192 900 kg (425 275 lb),- The radius of relative stiffness is shown at 1143 mm (45 in) with a related LCN of 83.The weight on one MLG is 80 000 kg (176 375 lb).

The following table provides LCN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1977”. In order to use the system accuratelyyou should know the total pavement radius of relative stiffness (L-value) for rigid pavement.However, the pavement radius of relative stiffness for a particular runway are not frequently publishedin the standard airport information sources (Jeppesen, AERAD, DOD, etc.).Therefore it is common practice to use a standard radius of relative stiffness (30 inches) whendetermining the LCN and the ESWL of the aircraft.If the LCN for an intermediate weight between maximum ramp weight and the empty weight of theaircraft is required or if the real thickness is known, refer to figures that follows.

2. Radius of Relative Stiffness (Other values of E and µ)This section gives data about the rigid pavement requirements for the Load Classification Number(LCN) conversion (radius of relative stiffness with other values of E (Young’s modulus) and µ(Poisson’s ratio).The other values of E and µ have an effect on the radius of relative stiffness value L.The effect of E and µ on the radius of relative stiffness value L is shown in the diagrams of FIGURE7---0-99--014-A.The table in FIGURE 7---0-99--001-ARadius of Relative Stiffness, shows values L based on a Young’smodulus (E) of 4 000 000 psi and a Poisson’s ratio (µ) of 0.15.To find values L, you must know the values of E and µ.

7-8-0Page 1

Apr 01/13


Example, see FIGURE 7---0-99--014-A, calculation of values L of the rigid pavement for an E of 3000 000 psi.The ”E” factor is 0.931.The radius of relative stiffness value L is the value found in the table FIGURE 7---0-99--001-Amultiplied by 0.931.


7-8-0Page 2

Apr 01/13


**ON A/C A330-200

AIRCRAFT TYPE

A330−200WV020

ALL UPMASS (kg)


(%)

TIREPRESSURE

(Mpa)

RGID PAVEMENTESWL

x 1000 kg L = 760 mm (30 in)

x 1000 lbLCN

47.347.2

1.42

A330−200WV021

47.347.2

A330−200WV022

47.347.2

A330−200WV023

47.347.2

A330−200WV024

47.547.3

A330−200WV025

47.447.2

A330−200WV026

47.547.4

A330−200WV027

47.447.2

A330−200WV050

47.347.2

A330−200WV051

47.547.4

A330−200WV052

47.347.2

A330−200WV053

47.447.3

A330−200WV054

47.347.2

A330−200WV055

47.547.4

A330−200WV056

47.347.2

A330−200WV057

46.746.6

A330−200WV058

46.346.2

A330−200WV059

47.547.3

A330−200WV060

47.447.2

A330−200WV061

47.347.2

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

2613

5729

9049

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

13 29

26 57 9049

26 58 9149

26 58 9149

23 50 8250

25 55 8749

22 48 7850

25 55 8749

26 57 9049

22 48 7850

26 58 9149

24 52 8449

26 57 9049

22 48 7850

26 58 9149

26 58 9149

26 58 9148

23 50 8250

25 55 8749

26 57 9049

230 900120 000230 900120 000233 900

233 900

202 900

220 900

192 900

220 900

230 900

192 900

233 900

210 900

230 900

192 900

233 900

236 900

238 900

202 900

220 900

230 900

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

F_AC_070800_1_0170101_01_00

Rigid Pavement RequirementsLCN table

FIGURE-7-8-0-991-017-A01

7-8-0Page 3

Apr 01/13


**ON A/C A330-300

AIRCRAFT TYPE

A330−300

ALL UPMASS (kg)


(%)

TIREPRESSURE

(Mpa)

RIGID PAVEMENTESWL

x 1000 kg L = 760 mm (30 in)

x 1000 lbLCN

212 900125 000

47.447.3

1.31 2414WV000

5331

8150

WV001

WV002

WV003

WV004 (209)

WV004 (215)

WV010

WV010b

WV011

WV012

WV013

WV014

WV020

WV022

WV024

WV025

WV050

WV051

WV052

WV053

WV054

125 00047.947.9

1.31 2114

4631

7351

184 900

125 00047.447.3

1.31 2414

5331

8150

212 900

125 00047.247.1

1.33 2414

5331

8250

215 900

125 00047.847.8

1.33 2414

5231

8151

209 900

125 00047.847.7

1.33 2414

5431

8351

215 900

125 00047.046.9

1.33 2414

5330

8250

217 900

125 00047.847.7

1.33 2514

5431

8351

217 900

125 00047.847.7

1.33 2414

5331

8251

212 900

125 00047.847.7

1.33 2514

5531

8451

218 900

125 00047.847.7

1.33 2414

5431

8351

215 900

125 00047.947.8

1.33 2314

5131

8051

205 900

125 00047.847.7

1.42 2614

5831

9152

230 900

125 00047.747.6

1.45 2614

5831

9353

233 900

125 00047.947.8

1.42 2314

5131

8352

205 900

125 00047.847.7

1.42 2514

5431

8752

217 900

125 00047.847.7

1.45 2614

5831

9253

230 900

125 00047.847.7

1.45 2414

5331

8653

212 900

125 00047.747.6

1.45 2614

5831

9353

233 900

125 00047.947.8

1.45 2314

5131

8453

205 900

125 00047.347.2

1.45 2614

5831

9352

235 900

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

A330−300

F_AC_070800_1_0170201_01_00


FIGURE-7-8-0-991-017-B01

7-8-0Page 4

Apr 01/13


**ON A/C A330-200F

AIRCRAFT TYPE

A330−200FWV000

ALL UPMASS (kg)


(%)

TIREPRESSURE

(Mpa)

RIGID PAVEMENTESWL

x 1000 kg L = 760 mm (30 in)

x 1000 lbLCN

233 900120 000

47.347.2

1.42 2613

5829

9149

A330−200FWV001

227 900120 000

47.347.2

A330−200FWV002

1.42

1.42 2613 29 49

8956

2613

5829

9149

233 900120 000

47.347.2

F_AC_070800_1_0170302_01_00


FIGURE-7-8-0-991-017-C01

7-8-0Page 5

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

WHERE

=

E

k

d

Ed4

=

=

=

dk

= 24.1652 4

RIGID PAVEMENT THICKNESS, (in)

YOUNG’S MODULUS = 4 x 10 psi

RADIUS OF RELATIVE STIFFNESS VALUES IN INCHES

L

SUBGRADE MODULUS, lb/in

= POISSON’S RATIO = 0.15

6.06.57.07.5

31.4833.4335.3437.22

29.3031.1132.8934.63

26.4728.1129.7231.29

24.6326.1627.6529.12

23.3024.7426.1527.54

22.2623.6424.9926.32

21.4222.7424.0425.32

20.7222.0023.2524.49

19.1320.3121.4722.61

8.08.59.09.5

39.0640.8842.6744.43

36.3538.0439.7141.35

32.8534.3735.8837.36

30.5731.9933.3934.77

28.9130.2531.5832.89

27.6228.9130.1731.42

26.5827.8129.0330.23

25.7026.9028.0829.24

23.7424.8425.9327.00

10.010.511.011.5

46.1847.9049.6051.28

38.8340.2841.7143.12

36.1437.4838.8140.13

34.1735.4536.7137.95

32.6533.8735.0736.26

31.4232.5933.7534.89

30.3931.5232.6433.74

28.0629.1130.1431.16

12.012.513.013.5

52.9454.5956.2257.83

49.2750.8052.3253.82

44.5245.9047.2748.63

41.4342.7243.9945.26

39.1840.4041.6142.80

37.4438.6039.7540.89

36.0237.1438.2539.35

34.8435.9236.9938.06

32.1733.1734.1635.14

14.014.515.015.5

16.016.517.017.5

55.3156.7858.2559.70

65.6967.2368.7570.26

61.1362.5663.9865.38

49.9851.3152.6353.94

46.5147.7548.9850.20

43.9845.1646.3247.47

55.2456.5357.8159.08

51.4152.6153.8054.98

48.6249.7550.8852.00

42.0243.1544.2645.36

40.4441.5142.5843.64

39.1140.1541.1942.21

36.1237.0838.0338.98

46.4547.5448.6149.68

44.7045.7446.7747.80

43.2344.2445.2446.23

39.9240.8541.7842.70

18.019.020.021.0

22.023.024.025.0

71.7674.7377.6680.55

83.4186.2489.0491.81

66.7869.5472.2774.96

77.6380.2682.8685.44

60.3462.8465.3067.74

70.1472.5274.8777.20

56.1558.4860.7763.04

65.2867.4969.6871.84

53.1155.3157.4759.62

61.7363.8365.9067.95

50.7452.8454.9156.96

58.9860.9862.9664.92

48.8250.8452.8454.81

56.7558.6860.5862.46

54.8956.7558.5960.41

47.2249.1751.1053.01

43.6145.4147.1948.95

50.6952.4154.1155.79

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

59.4361.0262.5964.15

42.9744.5746.1647.72

( )L

12 (1 − ) k

REFERENCE: PORTLAND CEMENT ASSOCIATION

F_AC_070800_1_0010101_01_00

Radius of Relative Stiffness (L)FIGURE-7-8-0-991-001-A01

7-8-0Page 6

Apr 01/13


**ON A/C A330-200

102030405060708090100

110

120

750

1000

1500

2000

2500

2030

4050

6070

8090

100

2030

4050

6070

8010

0 12015

0 18023

0

101520253035404550 5

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

2 ba

r (2

06 p

si)

1400

x530

R23

OR

54x

21−

23

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

in)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:


50 0

00 k

g

(110

225

lb)

60 0

00 k

g

(132

275

lb)

70 0

00 k

g

(154

325

lb)

80 0

00 k

g

(176

375

lb)

91 6

70 k

g

(202

100

lb)

LAN

DIN

G G

EA

RW

EIG

HT

ON

ON

E M

AIN

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG


F_AC_070800_1_0040101_01_00

Rigid Pavement Requirements - LCNWV026, MRW 192 900 kg, CG 38.8 % (Sheet 1 of 2)

FIGURE-7-8-0-991-004-A01

7-8-0Page 7

Apr 01/13


**ON A/C A330-200

102030405060708090100

110

120

750

1000

1500

2000

2500

2030

4050

6070

8090

100

2030

4050

6070

8010

0 12015

0 18023

0

101520253035404550 5

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

2 ba

r (2

06 p

si)

1400

x530

R23

OR

54x

21−

23

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

in)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:


70 0

00 k

g

(154

325

lb)

80 0

00 k

g

(176

375

lb)

90 0

00 k

g

(198

425

lb)

100

000

kg

(22

0 45

0 lb

)11

0 67

0 kg

(

243

975

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG


F_AC_070800_1_0050101_01_00F_AC_070800_1_0040102_01_00


FIGURE-7-8-0-991-004-A01

7-8-0Page 8

Apr 01/13


**ON A/C A330-200F

102030405060708090100

110

120

750

1000

1500

2000

2500

2030

4050

6070

8090

100

2030

4050

6070

8010

0 12015

0 18023

0

101520253035404550 5

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

2 ba

r (2

06 p

si)

1400

x530

R23

OR

54x

21−

23

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

in)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:


70 0

00 k

g

(154

325

lb)

80 0

00 k

g

(176

375

lb)

90 0

00 k

g

(198

425

lb)

107

900

kg

(23

7 87

5 lb

)W

EIG

HT

ON

ON

E M

AIN

LA

ND

ING

GE

AR

60 0

00 k

g

(132

275

lb)

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG


F_AC_070800_1_0060101_01_00


FIGURE-7-8-0-991-006-A01

7-8-0Page 9

Apr 01/13


**ON A/C A330-200F

102030405060708090100

110

120

750

1000

1500

2000

2500

2030

4050

6070

8090

100

2030

4050

6070

8010

0 12015

0 18023

0

101520253035404550 5

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

2 ba

r (2

06 p

si)

1400

x530

R23

OR

54x

21−

23

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

in)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:


70 0

00 k

g

(154

325

lb)

80 0

00 k

g

(176

375

lb)

90 0

00 k

g

(198

425

lb)

100

000

kg

(22

0 45

0 lb

)11

0 67

0 kg

(

243

975

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG


F_AC_070800_1_0060201_01_00F_AC_070800_1_0060102_01_00


FIGURE-7-8-0-991-006-A01

7-8-0Page 10

Apr 01/13


**ON A/C A330-300

102030405060708090100

110

120

750

1000

1500

2000

2500

2030

4050

6070

8090

100

2030

4050

6070

8010

0 12015

0 18023

0

101520253035404550 5

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

13.

1bar

(19

0 ps

i)14

00x5

30R

23 O

R 5

4x21

−23

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

in)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:


MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG

50 0

00 k

g

(110

225

lb)

60 0

00 k

g

(132

275

lb)

70 0

00 k

g

(154

325

lb)

40 0

00 k

g

(88

175

lb)

88 6

20 k

g

(195

375

lb)

LAN

DIN

G G

EA

RW

EIG

HT

ON

ON

E M

AIN


F_AC_070800_1_0070101_01_00


FIGURE-7-8-0-991-007-A01

7-8-0Page 11

Apr 01/13


**ON A/C A330-300

102030405060708090100

110

120

750

1000

1500

2000

2500

2030

4050

6070

8090

100

2030

4050

6070

8010

0 12015

0 18023

0

101520253035404550 5

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

mm

)T

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

14.

5 ba

r (2

10 p

si)

1400

x530

R23

or

54x2

1−23

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

in)

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

SE

CO

ND

ED

ITIO

N 1

965

NO

TE

:



70 0

00 k

g

(154

325

lb)

80 0

00 k

g

(176

375

lb)

90 0

00 k

g

(198

425

lb)

100

000

kg

(22

0 45

0 lb

)11

1 67

0 kg

(

246

200

lb)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R

MA

XIM

UM

PO

SS

IBLE

MA

ING

EA

R L

OA

D A

T M

AX

IMU

MR

AM

P W

EIG

HT

AN

DA

FT

CG

F_AC_070800_1_0070201_01_00F_AC_070800_1_0070102_01_00


FIGURE-7-8-0-991-007-A01

7-8-0Page 12

Apr 01/13


**ON A/C A330-200 A330-200F A330-300

0 1 2 3 4 50.80

0.85

0.90

0.95

1.00

1.05

1.10EFFECT OF E ON

E F

AC

TO

R

0.00 0.05 0.10 0.15 0.20 0.250.995

1.000

1.005

1.010

1.015EFFECT OF

FA

CT

OR

, POISSON’S RATIO

NOTE: BOTH CURVES ON THIS PAGE ARE USED TO ADJUST THE

E, YOUNG’S MODULUS (10 psi)

ON

OF RADIUS OF RELATIVE STIFFNESS ( ) TABLEL

VALUESL

VALUESL

L VALUESF_AC_070800_1_0140101_01_00

Radius of Relative Stiffness (Effect E and µ ON ”L” values)FIGURE-7-8-0-991-014-A01

7-8-0Page 13

Apr 01/13


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

**ON A/C A330-200 A330-200F A330-300

Aircraft Classification Number - Flexible and Rigid Pavement

1. This section gives data about the Aircraft Classification Number (ACN) for an aircraft gross weight inrelation with a subgrade strength value for flexible and rigid pavement.The flexible and rigid pavement requirements graphs are given at standard tire pressure for theweight variants producing (at the MRW and max aft CG) the lowest MLG load and the highest MLGload of each A/C type.To find the ACN of an aircraft on flexible and rigid pavement, you must know the aircraft grossweight and the subgrade strength.

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

Example, see FIGURE 7---0-99--008-A (sheet 1), calculation of the ACN for flexible pavement for:- An aircraft with a MRW of 192 900 kg (425 275 lb),- An aircraft gross weight of 180 000 kg (396 825 lb),- A medium subgrade strength (code B).The ACN for flexible pavement is 45.

Example, see FIGURE 7---0-99--008-A (sheet 2), calculation of the ACN for rigid pavement for:- An aircraft with a MRW of 192 900 kg (425 275 lb),- An aircraft gross weight of 180 000 kg (396 825 lb),- A medium subgrade strength (code B).The ACN for rigid pavement is 45.

2. Aircraft Classification Number - ACN tableThe table FIGURE 7---0-99--001-A, FIGURE 7---0-99--002-A and FIGURE 7---0-99--003-A provideACN data in tabular format similar to the one used by ICAO in the ”Aerodrome Design Manual Part3, Pavements - Edition 1983”. If the ACN for an intermediate weight between MRW and theminimum weight of the aircraft is required, refer to figures that follows.


7-9-0Page 1

Apr 01/13


**ON A/C A330-200

AIRCRAFT TYPE

A330−200WV020

ALL UPMASS (kg)


(%)

TIREPRESSURE

(Mpa)

230 900120 000

47.347.2

1.42

A330−200WV021

230 900120 000

47.347.2

A330−200WV022

233 900 47.347.2

A330−200WV023

233 900 47.347.2

A330−200WV024

202 900 47.547.3

A330−200WV025

220 900 47.447.2

A330−200WV026

192 900 47.547.4

A330−200WV027

220 900 47.447.2

A330−200WV050

230 900 47.347.2

A330−200WV051

192 900 47.547.4

A330−200WV052

233 900 47.347.2

A330−200WV053

210 900 47.447.3

A330−200WV054

230 900 47.347.2

A330−200WV055

192 900 47.547.4

A330−200WV056

233 900 47.347.2

A330−200WV057

236 900 46.746.6

A330−200WV058

238 900 46.346.2

A330−200WV059

202 900 47.547.3

A330−200WV060

220 900 47.447.2

A330−200WV061

230 900 47.347.2

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

1.42

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

120 000

5328

ACN FOR

High150

RIGID PAVEMENTSUBGRADES − MN/m³

6127

Medium80

7230

Low40

8535

Ultral−low20

5726

ACN FOR

High15

FLEXIBLE PAVEMENTSUBGRADES − CBR

6227

Medium10

7130

Low6

9736

Ultral−low3

53 6127

7230

8535

5726

6227

71 97

28

28

28

28

28

28

28

28

28

28

28

28

28

27

27

27

28

28

28

27

27

27

27

27

27

27

27

27

27

27

27

27

27

26

27

27

27

54

54

45

50

43

50

53

43

54

47

53

43

54

54

54

45

50

53

62 7430

8635

5826

63 73 98

62 7430

8635

5826

63 73 98

52 6131

7135

4926

52 60 8037

58 6831

8035

5426

58 67 9136

49 5731

6735

4626

49 56 7537

58 6831

8035

5426

58 67 9136

61 7230

8535

5726

62 71 9736

49 5731

6735

4626

49 56 7537

62 7430

8635

5826

63 73 9836

54 6431

7535

5126

55 63 8537

61 7230

8535

5726

62 71 9736

49 5731

6735

4626

49 56 7537

62 7430

8635

5826

63 73 9836

62 7430

8634

5826

63 73 9836

62 7430

8634

5825

63 73 9835

52 6131

7135

4926

52 60 8037

58 6831

8035

5426

58 67 9136

61 7230

8535

5726

62 71 973627

27

27

26

27

27

27

27

27

27

27

27

27

27

27

27

27

27

30

30

30

29

29

30

30

30

30

30

30

30

30

30

30

30

30

30

30 36

36

36

F_AC_070900_1_0010101_01_00

Aircraft Classification NumberACN Table

FIGURE-7-9-0-991-001-A01

7-9-0Page 2

Apr 01/13


**ON A/C A330-200

100

120

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160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

300

400

500

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.2

bar

(206

psi

)14

00x5

30R

23 O

R 5

4x21

−23

(bi

as)

TIR

ES

SE

E S

EC

TIO

N 7

−4−

0

AIRCRAFT CLASSIFICATION NUMBER (ACN)

(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ALP

HA

FA

CT

OR

= 0

.8

D −

CB

R

3 (

ULT

RA

LO

W)

SU

BG

RA

DE

ST

RE

NG

TH

C −

CB

R

6 (

LOW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

F_AC_070900_1_0080101_01_00

Aircraft Classification NumberFlexible Pavement - WV026, MRW 192 900 kg, CG 38.8 % (Sheet 1 of 2)

FIGURE-7-9-0-991-008-A01

7-9-0Page 3

Apr 01/13


**ON A/C A330-200

100

120

140

160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

250

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.2

bar

(206

psi

)14

00x5

30R

23 O

R 5

4x21

−23

(bi

as)

TIR

ES

SE

E S

EC

TIO

N 7

−4−

0


(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

300

350

400

450

500

550

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

F_AC_070900_1_0080102_01_00

Aircraft Classification NumberRigid Pavement - WV026, MRW 192 900 kg, CG 38.8 % (Sheet 2 of 2)

FIGURE-7-9-0-991-008-A01

7-9-0Page 4

Apr 01/13


**ON A/C A330-200

100

120

140

160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

300

400

500

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.2

bar

(206

psi

)14

00x5

30R

23 O

R 5

4x21

−23

(bi

as)

TIR

ES

SE

E S

EC

TIO

N 7

−4−

0


(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ALP

HA

FA

CT

OR

= 0

.8

D −

CB

R

3 (

ULT

RA

LO

W)

SU

BG

RA

DE

ST

RE

NG

TH

C −

CB

R

6 (

LOW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

F_AC_070900_1_0110101_01_00


FIGURE-7-9-0-991-011-A01

7-9-0Page 5

Apr 01/13


**ON A/C A330-200

100

120

140

160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

250

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.2

bar

(206

psi

)14

00x5

30R

23 O

R 5

4x21

−23

(bi

as)

TIR

ES

SE

E S

EC

TIO

N 7

−4−

0


(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

300

350

400

450

500

550

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

F_AC_070900_1_0110102_01_00


FIGURE-7-9-0-991-011-A01

7-9-0Page 6

Apr 01/13


**ON A/C A330-200F

AIRCRAFT TYPEALL UP

MASS (kg)


(%)

TIREPRESSURE

(Mpa)

5428

ACN FOR

High150


6227

Medium80

7430

Low40

8635

Ultral−low20

5826

ACN FOR

High15


6327

Medium10

7330

Low6

9836

Ultral−low3

A330−200FWV000

233 900120 000

47.347.2

1.42

A330−200FWV001

227 900120 000

47.347.2

A330−200FWV002

1.42

1.42

233 900120 000

47.347.2

28 27 30 35 26 27 30 36

28 27 30 35 26 27 30 3654 62 74 86 58 63 73 98

52 60 71 83 56 61 70 95

F_AC_070900_1_0020101_01_00


FIGURE-7-9-0-991-002-A01

7-9-0Page 7

Apr 01/13


**ON A/C A330-200F

100

120

140

160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

300

400

500

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.2

bar

(206

psi

)14

00x5

30R

23 O

R 5

4x21

−23

(bi

as)

TIR

ES

SE

E S

EC

TIO

N 7

−4−

0


(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ALP

HA

FA

CT

OR

= 0

.8

D −

CB

R

3 (

ULT

RA

LO

W)

SU

BG

RA

DE

ST

RE

NG

TH

C −

CB

R

6 (

LOW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

F_AC_070900_1_0090101_01_00


FIGURE-7-9-0-991-009-A01

7-9-0Page 8

Apr 01/13


**ON A/C A330-200F

100

120

140

160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

250

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.2

bar

(206

psi

)14

00x5

30R

23 O

R 5

4x21

−23

(bi

as)

TIR

ES

SE

E S

EC

TIO

N 7

−4−

0


(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

300

350

400

450

500

550

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

F_AC_070900_1_0090102_01_00


FIGURE-7-9-0-991-009-A01

7-9-0Page 9

Apr 01/13


**ON A/C A330-200F

100

120

140

160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

300

400

500

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.2

bar

(206

psi

)14

00x5

30R

23 O

R 5

4x21

−23

(bi

as)

TIR

ES

SE

E S

EC

TIO

N 7

−4−

0


(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ALP

HA

FA

CT

OR

= 0

.8

D −

CB

R

3 (

ULT

RA

LO

W)

SU

BG

RA

DE

ST

RE

NG

TH

C −

CB

R

6 (

LOW

)B

− C

BR

10

(ME

DIU

M)

A −

CB

R 1

5 (H

IGH

)

F_AC_070900_1_0120101_01_00


FIGURE-7-9-0-991-012-A01

7-9-0Page 10

Apr 01/13


**ON A/C A330-200F

100

120

140

160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

250

(x 1

000

lb)

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

4.2

bar

(206

psi

)14

00x5

30R

23 O

R 5

4x21

−23

(bi

as)

TIR

ES

SE

E S

EC

TIO

N 7

−4−

0


(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

300

350

400

450

500

550

D −

K =

20

MN

/m³

(U

LTR

A L

OW

)S

UB

GR

AD

E S

TR

EN

GT

H

C −

K =

40

MN

/m³

(LO

W)

B −

K =

80

MN

/m³

(M

ED

IUM

)A

− K

= 1

50 M

N/m

³ (

HIG

H)

F_AC_070900_1_0120102_01_00


FIGURE-7-9-0-991-012-A01

7-9-0Page 11

Apr 01/13


**ON A/C A330-300

AIRCRAFT TYPEALL UP

MASS (kg)


(%)

TIREPRESSURE

(Mpa)

4628472846284728472848284728482847284528532955294629502954294829552947295529

ACN FOR

High150


5327

Medium80

6331

Low40

7536

Ultral−low20

5127

ACN FOR

High15


5528

Medium10

6431

Low6

8639

Ultral−low3

A330−300

WV001

WV003

WV002

WV004 (209)

WV010

WV004 (215)

WV010b

WV012

WV011

WV013

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WV000212 900 47.4

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F_AC_070900_1_0030101_01_00


FIGURE-7-9-0-991-003-A01

7-9-0Page 12

Apr 01/13


**ON A/C A330-300

100

120

140

160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

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400

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(x 1

000

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T A

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(x 1

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F_AC_070900_1_0100101_01_00


FIGURE-7-9-0-991-010-A01

7-9-0Page 13

Apr 01/13


**ON A/C A330-300

100

120

140

160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

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(x 1

000

lb)

TIR

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(190

psi

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N 7

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(x 1

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D A

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D IN

300

350

400

450

500

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D −

K =

20

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/m³

(U

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AD

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(LO

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/m³

(M

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− K

= 1

50 M

N/m

³ (

HIG

H)

F_AC_070900_1_0100102_01_00


FIGURE-7-9-0-991-010-A01

7-9-0Page 14

Apr 01/13


**ON A/C A330-300

100

120

140

160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

300

400

500

(x 1

000

lb)

TIR

E P

RE

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UR

E C

ON

ST

AN

T A

T 1

4.5

bar

(210

psi

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(bi

as)

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N 7

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(x 1

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F_AC_070900_1_0130101_01_00


FIGURE-7-9-0-991-013-A01

7-9-0Page 15

Apr 01/13


**ON A/C A330-300

100

120

140

160

110

130

150

170

180

190

200

210

220

230

240

250

0102030405060708090100

110

120

250

(x 1

000

lb)

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E P

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bar

(210

psi

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(bi

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(x 1

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350

400

450

500

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/m³

(U

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− K

= 1

50 M

N/m

³ (

HIG

H)

F_AC_070900_1_0130102_01_00


FIGURE-7-9-0-991-013-A01

7-9-0Page 16

Apr 01/13


SCALED DRAWINGS

8-0-0 SCALED DRAWINGS

**ON A/C A330-200 A330-200F A330-300

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

Apr 01/13


**ON A/C A330-200

010

2030

40F

EE

T

04

812

1620

ME

TE

RS

0 10 20 30 40FEET

0 4 8 12 16 20METERS

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

5060

50 60

F_AC_080000_1_0020101_01_00

Scaled DrawingFIGURE-8-0-0-991-002-A01

8-0-0Page 2

Apr 01/13


**ON A/C A330-300

010

2030

40F

EE

T

04

812

1620

ME

TE

RS

0 10 20 30 40FEET

0 4 8 12 16 20METERS


5060

50 60

F_AC_080000_1_0020201_01_00

Scaled DrawingFIGURE-8-0-0-991-002-B01

8-0-0Page 3

Apr 01/13


**ON A/C A330-200F

010

2030

40F

EE

T

04

812

1620

ME

TE

RS

0 10 20 30 40FEET

0 4 8 12 16 20METERS


5060

50 60

F_AC_080000_1_0020301_01_00

Scaled DrawingFIGURE-8-0-0-991-002-C01

8-0-0Page 4

Apr 01/13


AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 AIRCRAFT RESCUE AND FIRE FIGHTING

**ON A/C A330-200 A330-300

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 (ARFC) poster available on AIRBUSWorld and the Airbus website.

10-0-0Page 1

Apr 01/13


**ON A/C A330-200 A330-300

F_AC_100000_1_0010101_01_00

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

10-0-0Page 2

Apr 01/13


**ON A/C A330-200 A330-300

F_AC_100000_1_0020101_01_00

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

10-0-0Page 3

Apr 01/13


**ON A/C A330-200 A330-300

F_AC_100000_1_0030101_01_00

Crew Rest Compartments LocationFIGURE-10-0-0-991-003-A01

10-0-0Page 4

Apr 01/13


**ON A/C A330-200 A330-300

F_AC_100000_1_0040101_01_00

Wheel/Brake OverheatWheel Safety Area (Sheet 1 of 2)

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

10-0-0Page 5

Apr 01/13


**ON A/C A330-200 A330-300

F_AC_100000_1_0040102_01_00

Wheel/Brake OverheatRecommendations (Sheet 2 of 2)

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

10-0-0Page 6

Apr 01/13


**ON A/C A330-200 A330-300

F_AC_100000_1_0050101_01_00

Composite Materials LocationFIGURE-10-0-0-991-005-A01

10-0-0Page 7

Apr 01/13


**ON A/C A330-200 A330-300

BA

AB

F_AC_100000_1_0060101_01_00

Ground Lock Safety DevicesFIGURE-10-0-0-991-006-A01

10-0-0Page 8

Apr 01/13


**ON A/C A330-200 A330-300

F_AC_100000_1_0070101_01_00

Emergency Evacuation DevicesFIGURE-10-0-0-991-007-A01

10-0-0Page 9

Apr 01/13


**ON A/C A330-200 A330-300

F_AC_100000_1_0080101_01_00

Pax/Crew Doors and Emergency ExitsFIGURE-10-0-0-991-008-A01

10-0-0Page 10

Apr 01/13


**ON A/C A330-200 A330-300

122C

R

FW

D

7155

JE 196B

B

152N

R/

197C

B

F_AC_100000_1_0090101_01_00

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

10-0-0Page 11

Apr 01/13


**ON A/C A330-200 A330-300

A B CD

E

A

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F_AC_100000_1_0100101_01_00

Control PanelsFIGURE-10-0-0-991-010-A01

10-0-0Page 12

Apr 01/13


**ON A/C A330-200 A330-300

A

315A

L

316A

R

A

F_AC_100000_1_0110101_01_00

APU Compartment AccessFIGURE-10-0-0-991-011-A01

10-0-0Page 13

Apr 01/13


**ON A/C A330-200 A330-300

F_AC_100000_1_0120101_01_00


10-0-0Page 14

Apr 01/13


**ON A/C A330-200 A330-300

F_AC_100000_1_0130101_01_00

Structural Break-in PointsFIGURE-10-0-0-991-013-A01

10-0-0Page 15

Apr 01/13


**ON A/C A330-200F

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 (ARFC) poster available on AIRBUSWorld and the Airbus website.

10-0-0Page 16

Apr 01/13


**ON A/C A330-200F

F_AC_100000_1_0140101_01_00

Front PageFIGURE-10-0-0-991-014-A01

10-0-0Page 17

Apr 01/13


**ON A/C A330-200F

F_AC_100000_1_0150101_01_00

Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-0-0-991-015-A01

10-0-0Page 18

Apr 01/13


**ON A/C A330-200F

F_AC_100000_1_0160101_01_00

Wheel/Brake OverheatWheel Safety Area (Sheet 1 of 2)

FIGURE-10-0-0-991-016-A01

10-0-0Page 19

Apr 01/13


**ON A/C A330-200F

F_AC_100000_1_0160102_01_00

Wheel/Brake OverheatRecommendations (Sheet 2 of 2)

FIGURE-10-0-0-991-016-A01

10-0-0Page 20

Apr 01/13


**ON A/C A330-200F

F_AC_100000_1_0180101_01_00

Composite Materials LocationFIGURE-10-0-0-991-018-A01

10-0-0Page 21

Apr 01/13


**ON A/C A330-200F

BA

AB

F_AC_100000_1_0190101_01_00

Ground Lock Safety DevicesFIGURE-10-0-0-991-019-A01

10-0-0Page 22

Apr 01/13


**ON A/C A330-200F

F_AC_100000_1_0200101_01_00

Emergency Evacuation DevicesFIGURE-10-0-0-991-020-A01

10-0-0Page 23

Apr 01/13


**ON A/C A330-200F

F_AC_100000_1_0210101_01_00

Crew Doors and Emergency ExitsFIGURE-10-0-0-991-021-A01

10-0-0Page 24

Apr 01/13


**ON A/C A330-200F

122C

R

FW

D

7155

JE 196B

B

152N

R/

197C

B

F_AC_100000_1_0220101_01_00

Cargo DoorsFWD and AFT Lower Deck Compartments (Sheet 1 of 2)

FIGURE-10-0-0-991-022-A01

10-0-0Page 25

Apr 01/13


**ON A/C A330-200F

221N

Q

835B

L

803M

J

805M

J

F_AC_100000_1_0220102_01_00

Cargo DoorsUpper Deck Compartment (Sheet 2 of 2)

FIGURE-10-0-0-991-022-A01

10-0-0Page 26

Apr 01/13


**ON A/C A330-200F

CA

B F

AN

SE

XTR

AC

TA

VN

CS

BTL

2

BTL

1

TES

TD

ISC

HA

GE

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CA

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& L

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x 10

00kg1b

PR

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TK

C

E

B

D

F_AC_100000_1_0230101_01_00

Control PanelsFIGURE-10-0-0-991-023-A01

10-0-0Page 27

Apr 01/13


**ON A/C A330-200F

A

315A

L

316A

R

A

F_AC_100000_1_0240101_01_00

APU Compartment AccessFIGURE-10-0-0-991-024-A01

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**ON A/C A330-200F

F_AC_100000_1_0250101_01_00


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**ON A/C A330-200F

AA

AA

AA

AF

WD

F_AC_100000_1_0260101_01_00

Structural Break-in PointsFIGURE-10-0-0-991-026-A01

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aircraft characteristics airport and maintenance …

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